CHEROKEE

SERVICE
MANUAL
CARD1 OF4

PA-28-140
PA-28-150
PA-28-160
PA-28-180
PA-28-235
PA-28R-180
PA-28R-200

PIPERAIRCRAFT
CORPORATION

(PARTNUMBER
753586) lA1
 PIPER CHEROKEESERVICE MANUAL

AEROFICHE EXPLANATION AND REVISION STATUS

The Service Manual information incorporated in this set of Aerofiche cards has been arranged in accordance
with the general specifications of Aerofiche adopted by the General Aviation Manufacturer's Association,
(GAMA). The information compiled in this Aerofiche Service Manual will be kept current by revisions distributed
periodically. These revisions will supersede all previous revisions and will be complete Aerofiche card replace-
ments and shall supersede Aerofiche cards of the same number in the set.

Conversion of Aerofiche alpha/numeric code numbers:

First number is the Aerofiche card number.
Letter is the horizontal line reference per card.
Second number is the vertical line reference per card.
Example: 2J16 = Aerofiche card number two of given set, Grid location J16.

To aid in locating the various chapters and related service information desired, the following is provided:

1. A complete manual Table of Contents is for all fiche in this set.

2. A complete list of Illustrations is given and follows the Table of Contents.
3. A complete list of Tables is given for all fiche in this set and follows the list of Illustrations.
4. A complete list of paragraph titles and appropriate Grid location numbers is given at the beginning of each
Chapter relating to the information within that Chapter.
5. Identification of Revised Material:
Revised text and illustrations are indicated by a black vertical line along the left-hand margin of the
frame, opposite revised, added or deleted material. Revision lines indicate only current revisions with changes and
additions to or deletions of existing text and illustrations. Changes in capitalization, spelling, punctuation, indexing,
the physical location of the material or complete page additions are not identified by revision lines.
6. Revisions to this Service Manual 753 586 issued August 16, 1972 are as follows:

Effectivity Publication Date Aerofiche Card Effectivity

ORG720816 August 16, 1972 ---

CR810115 January 15, 1981 1,2, 3 and 4
PR810803 August 3, 1981 1, 2, 3 and 4
PR831003 October 3, 1983 1, 2, 3 and 4
PR840423 April 23, 1984 1, 2, 3 and 4
PR860115 January 15, 1986 1 and 3
IR860730 July 30, 1986 1
IR870506 June 12, 1987 1
IR950215* February 15, 1995 1 and 2

* INTERIM CHANGE

Chapters II, III, and IV of Card 1, and Chapters VIIA and VIII of Card 2 have been revised.
There are no other changes included in this interim change revision. Please discard your
current cards 1 and 2, and replace them with the revised ones. DO NOT DISCARD CARDS
3 AND 4.

The date on Aerofiche cards should not be earlier than the date noted for the respective card effectivity. Consult
the latest card in this series for current Aerofiche card effectivity.

1A2
 TABLE OF CONTENTS

AEROFICHE
CARD
NO.1 AIX
INTRODUCTION INTRODUCTION IIIX
HANDLING
............... 1A24
INSPECTION IX
STRUCTURES

X
V........................ 2A8 2A8
VI...... . ........ (PA-28R) VIIIA
LANDING
GEAR AND

VIIA POWER
(PA-28R)
PLANT 2K2
VIII VIIA
AEROFACE
CARD
NO.3 IIA
VIIIA
. ........ . .. PLANT
(PA-28R) IA
IX . A

AEROFACE
CARD
NO. Al
XI 4A8
II
XIII NI I
XIV
ACCESSORIES
ANDUTILITIES

1A3
 1A4
INTENTIONALLYLEFT BLANK
 PIPER CHEROKEE SERVICE MANUAL

LIST OF ILLUSTRATIONS

Figure Aerofiche
Grid No.

2-1. Three View of Cherokee, PA-28-140. -150, -160, -180, Serial Nos.
28-1 to 28-1760 incl., Flite Liner, Serial Nos. 28-7125174
and up............................ ...................... B4
2-2. Three View of Cherokee, PA-28-140, Serial Nos.
28-7225001 and up ...... ... ......... ............. B5
2-3. Three View of Cherokee, PA-28-150. -160. -180, Serial Nos.
28-1761 to 28-4377 incl ............... ......... ...... 1B6
2-4. Three View of Cherokee. PA-28-180, Serial Nos. 28-4378
to 28-7105244 inc .............. ............... lB7
2-5. Three View of Cherokee. PA-28-180, Serial Nos. 28-7205001
to 28-7205328 incl ......................................... B8
2-6. Three View of Cherokee. PA-28-180. Serial Nos.
28-7305001 and up ........................................ 1B9
2-7. Three View of Cherokee, PA-28-235. Serial Nos. 28-10000
to 28-11039 incl ..................... .. ...... ............ 1B10
2-8. Three View of Cherokee, PA-28-235. Serial Nos. 28-11040
to 28-7110042 incl......................................... 1B11
2-9. Three View of Cherokee, PA-28-235. Serial Nos. 28-7210001
to 28-7210033 incl ......................................... 1B12
2-10. Three View of Cherokee, PA-28-235. Serial Nos.
28-7310001 and up ........................................ IB13
2-11. Three View of Cherokee. PA-28R-180, -200,
-180 Serial Nos. 28-30005 to 28-7130019 incl.
-200 Serial Nos. 28-30482 to 28-7135238 incl ............... 1B14
2-12. Three View of Cherokee, PA-28R-200, Serial Nos.
28-7235001 and up .......... .... ............ ......... IB15
2-13. Station Reference Lines. PA-28-140. -150, -160, -180. Serial Nos.
28-1 to 28-1760 incl.: Flite Liner. Serial Nos. 28-7125174
and up .................................................. C4
2-14. Station Reference Lines. PA-28-140, Serial Nos. 28-7225001
and up .................................................. IC
2-15. Station Reference Lines, PA-28-150, -160. -180, Serial Nos.
28-1761 to 28-4377 incl .................................. C6
2-16. Station Reference Lines, PA-28-180. Serial Nos. 28-4378
to 28-7105244 incl ....................................... IC7
2-17. Station Reference Lines. PA-28-180. Serial Nos. 28-7205001
to 28-7205328 incl ........................................ IC8
2-18. Station Reference Lines. PA-28-180, Serial Nos. 28-7305001
and up. IC9
2-19. Station Reference Lines. PA-28-235. Serial Nos. 28-10000
to 28-11039 incl .......... ............................ 1C10
2-20. Station Reference Lines, PA-28-235. Serial Nos. 28-11040
to 28-7110042 incl ........................................ 1C11

Reissued: 1/15/81 1A5

1A5
 PIPER CHEROKEE SERVICE MANUAL

LIST OF ILLUSTRATIONS (cont.)

Figure Aerofiche
Grid No.
2-21. Station Reference Lines, PA-28-235, Serial Nos. 28-7210001
to 28-7210033 incl ........................................ . 1C12
2-22. Station Reference Lines. PA-28-235, Serial Nos. 28-7310001
and up .................................................. 1C13
2-23. Station Reference Lines, PA-28R-180,-200,
-180 Serial Nos. 28-30005 to 28-7130019 incl.
-200 Serial Nos. 28-30482 to 28-7135238 incl .................. 1C14
2-24. Station Reference Lines, PA-28R-200, Serial Nos. 28-7235001
and up .................................................. IC15
2-25. Access Plates and Panels, PA-28-140 and Flite Liner. Serial
Nos. 28-7225001 and up as noted ........................... 1C16
2-26. Access Plates and Panels, PA-28-150, -160, -180 .... .............. C17
2-27. Access Plates and Panels, PA-28-235 ................. .. ......... C18
2-28. Access Plates and Panels, PA-28R .............................. 1C19
2-29. Identification of Aircraft Fluid Lines ............................ 1D7
2-30. Torque Wrench Formula ...................................... 1C21
2-31. Removing Cherrylock Rivets ................................... 1D8
2-32. Jacking Arrangement ......................................... 1D9
2-33. Weighing Airplane ............................................. 1D10
2-34. Leveling Longitudinally ....................................... 1
2-35. Leveling Laterally ............................................ 1D11
2-36. Servicing Points, PA-28-140 ................................... 1D20
2-37. Servicing Points, PA-28-150,-160, -180 ....................... 1
2-38. Servicing Points, PA-28-235 ................................... 1D22
2-39. Servicing Points, PA-28R ..................................... 1d23
2-40. Main Gear Oleo Struts (Cutaway View), PA-28-140;
PA-28-150,-160,-180; PA-28-235 ........................... 1D24
2-41. Fuel Strainer. PA-28-140; PA-28-150, -160, -180; and PA-28R...... 1E9
2-42. Fuel Selector and Filter, PA-28-235 ............................ 1E9
2-43. Lubrication Chart (Landing Gear, Main), PA-28-140, -150,
-160, -180 and -235 ....................................... 1E17
2-44. Lubrication Chart (Landing Gear, Main), PA-28R-180
and -200 ............................................... E18
2-45. Lubrication Chart (Landing Gear, Nose), PA-28-140, -150.
-160. -180 and -235 ....................................... 1E19
2-46. Lubrication Chart (Landing Gear, Nose), PA-28R-180 and -200 .... 1
2-47. Lubrication Chart (Control System) ............................ I E21
2-48. Lubrication Chart (Control System) (cont.) ...................... 1E22
2-49. Lubrication Chart (Control System) (cont.) ...................... 1E23
2-50. Lubrication Chart (Control System) (cont.) . ..................... 1E24
2-51. Lubrication Chart (Cabin Door. Baggage Door and Seat) ......... IF1

Revised: 8/3/81
1A6
 PIPER CHEROKEESERVICE MANUAL

LIST OF ILLUSTRATIONS (cont.)

Figure Aerofiche
Grid No.

2-52. Lubrication Chart (Power Plant, Propeller and Control Pivot Points) ....................... 1F2
2-53. Lubrication Chart (Back-Up Extender and Fuel Selector) ........................................1F3
2-54 Lubrication Chart (Air Conditioning Condenser) ...................................................... F4
3-1 Typical Muffler Fatigue Areas . ................................................... .................... 1F10
3-2 Exhaust System Inspection Points ............................................................................. 1F11
3-3 Exhaust System Inspection Points ............................................................................. F12
3-4 Exhaust System Installation, PA-28R-180,-200 ........................................................IF14
3-5 Control Wheel Inspection Points ...............................................................................1F15
3-6 Flap Control Cable Attachment Bolt Inspection........................................................ 1Fl6
3-7 Inspection of Main Landing Gear Torque Link ......................................................... 1Fl7
4-1 Aileron and Flap Installation ....................................................................................1G19
4-2 Wing Installation ..................................................................... 1G23
4-3 Methods of Securing Control Cables ........................................ .......... 1H7
4-4 Empennage Group Installation ................................................................................. 1H
4-5 Windshield Installation (Typical)............................... ..........................1H16
4-6 Side Window Installation, Single Pane (Typical) ......................................................1H18
4-7 Side Window Installation, Double Pane (Typical)....................................................1H18
4-8 Door Snubber Installation . ......................................................... 1H20
4-9 Seat Back Lock ........................................ 1H24
..................
4-10 Skin Materials and Thickness .................................................................................... 1I1
4-11 Surface Scratches, Abrasions or Ground-in-Dirt.......................................................1I8
4-12 Deep Scratches, Shallow Nicks and Small Holes ................... .............
1...................
119
4-13 Mixing of Epoxy Patching Compound .................................................... 119
4-14 Welding Repair Method .............................................................................................
4-15 Repairing of Cracks ...................................................................................................1I11
4-16 Various Repairs .......................................................................................................... 1I12
4-17 Repair of Stress Lines ...............................................................................................1I13
4-18 Repair of Impacted Damage ......................................................................................1I13
4-19 Control Surface Balance Tool ....................................................................................1I20
4-20 Aileron and Rudder Balance Configuration ..............................................................1Ii21
4-21 Stabilator Balance ......................................................................................................1122
4-22 Wing Rib Modification ..............................................................................................1I24
4-23 Balance Weight Assembly Installation ...................................................................... 1124
4-24 Fabricated Tool for Baggage Door Lock ................................................................... J
4-25 Additional Drain Holes in Stabilator ........................................................................1J2
4-26 Baggage Compartment Inspection Holes Cutout Details .......................................... J5
5-1 Control Column Assembly, PA-28-140,-150,-160, -180 and 235 .............................2A15
5-2 Control Column Assembly, PA-28R ..........................................................................2A16
5-3 Aileron Controls.........................................................................................................2A20
5-4 Bellcrank Rigging Tool, PA-28-140, -150, -160, -180, -235 .....................................2A23
5-5 Bellcrank Rigging Tool, PA-28R ...............................................................................2A23

Interim Revision: February 15, 1995

1A7
 PIPER CHEROKEE SERVICE MANUAL

LIST OF ILLUSTRATIONS (cont.)

Figure Aerofiche
Grid No.
5-6. Aileron Rigging Tool ......................................... 2A24
5-7. Stabilator Rigging Tool ....................................... 2B3
5-8. Stabilator Controls ....................................... .... 2B4
5-9. Stabilator Trim Control (Overhead Control) ... ............. 2B8
5-10. Methods of Securing Trim Cables .............................. 2B10
5-11. Stabilator Trim Control (Floor Control) ......................... 2B18
5-12. Rudder and Steering Pedal Assembly ........................... 2B24
5-13. Rudder Controls ............................................. 2C4
5-14. Rudder Rigging Tool .................................... 2C5
5-15. Clamping Rudder Pedals ...................................... 2C5
5-16. Rudder and Stabilator Travel Adjustments ... ................... 2C6
5-17. Rudder Trim Control ......................................... 2C8
5-18. Flap Controls ................... ............................. 2C10
5-19. Flap Step Adjustment ......................................... 2C14
5-20. Flap Rigging Tool ............................................ 2C12
5-21. Fabricated Aileron Bellcrank Rigging Tool ...................... 2C15
5-22. Correct Method of Installing Rod End Bearings .................. 2C15
5-23. Fabricated Aileron and Flap Rigging Tool ....................... 2C16
5-24. Fabricated Stabilator Rigging Tool ............................. 2C17
5-25. Fabricated Rudder Rigging Tool ............................... 2C18
6-1. Schematic Diagram of Hydraulic System ... .............. 2D5
6-2. Hydraulic System Installation .................................. 2D6
6-3. Hydraulic Pump/Reservoir. Exploded View ...................... 2D10
6-4. Test and Adjustments of Hydraulic Pump ............. ............... 2D14
6-5. Pump Shock Mounts ......................................... 2D16
6-6. Checking Aligning Brackets of Gear Back-Up Extender
Actuator ................................................ 2D 17
6-7. Gear Back-Up Extender Actuator .............................. 2D21
6-8. Nose Gear Actuator Cylinder .................................. 2E2
6-9. End Gland Locking Device .................................... 2E4
6-10. Main Gear Actuating Cylinder ................................. 2E5
6-11. Gear Back-Up Extender Actuator Aligning Tool .................. 2E20
7-1. Nose Gear Oleo Strut Assembly ................................ 2F2
7-2. Nose Gear Installation ........................................ 2F6
7-3. Clamping Rudder Pedals in Neutral Position ..................... 2F8
7-4. Rudder Pedals at Neutral Angle .. ........................ ... 2F8
7-5. Main Gear Oleo Strut Assembly. PA-28-140, -150, -160
and -180 ................................................ 2F13
7-6. Main Gear Oleo Strut Assembly, PA-28-235 ..................... 2F15
7-7. Main Gear Installation ... ........................ .......... 2F19
7-8. Nose Wheel Assembly ......................................... 2F21
7-9. Main Wheel Assembly ........................................ 2F23

Revised: 4 23/84 1A8

1A8
 PIPER CHEROKEE SERVICE MANUAL

LIST OF ILLUSTRATIONS (cont.)

Figure Aerofiche
Grid No.

7-10. Wheel Brake Assembly ........................................ 2G1

7-11. Removal of Anchor Bolt ...................................... 2G2
7-12. Installation of Anchor Bolt .................................... 2G3
7-13. Brake Disc Minimum Thickness ................................ 2G5
7-14. Brake System Installation ..................................... 2G5
7-15. Brake Master Cylinder (Hand Brake). PA-28-150. -160.
Serial Nos. 28-1 to 28-250 incl ............................. 2G8
7-16. Brake Master Cylinder (Hand Parking Brake), PA-28-140.
Serial Nos. 28-20002 to 28-21036 incl.: PA-28-150.
-160. -180. Serial Nos. 28-251 to 28-2700 incl.:
PA-28-235. Serial Nos. 28-10003 to 28-10697 incl ............ 2G8
7-17. Brake Master Cylinder (Hand Parking Brake). PA-28-140.
Serial Nos. 28-21037 and up: PA-28-150. -160. -180.
Serial Nos. 28-2701 and up: PA-28-235. Serial Nos.
28-10698 and up.......................................... 2G9
7-18. Parking Valve. PA-28-150. -160. Serial Nos. 28-1 to
28-250 incl ............................................... 2G11
7-19. Toe Brake Installation ........................................ 2G12
7-20. Brake Cylinder 10-20. 10-27. 17000 (Toe Brake) .................. 2G14
7-21. Brake Cylinder 10-30 (Toe Brake) .............................. 2G 15
7-22. Bleeding Brake (Gravity) ...................................... 2G 18
7-23. Bleeding Brake (Pressure) ......... ............................ 2G 18
7-24. Orifice Replacement Tool ..................................... 2G23
7-25. Retainer Ring Tool ........................................... 2G24
7A-I. Nose Gear Oleo Strut Assembly ............................... . 2H9
7A-2. Nose Gear Installation ........................................ 2H 12
7A-3. Nose Gear Adjustment (Without Gear Up Stop) .................. 2H 16
7A-4. Nose Gear Adjustment (With Gear Up Stop) ...... ............... 2H 17
7A-5. Clamping Rudder Pedals in Neutral Position ..................... 2H 19
7A-6. Rudder Pedals at Neutral Angle ................................ 2H19
7A-7. Nose Gear Door Retraction Mechanism ............. .............. 2H20
7A-8. Main Gear Oleo Strut Assembly ............................... . 211
7A-9. Main Gear Installation ....................................... 214
7A-10. Aligning Main Gear .......................................... 2110
7A-11. Adjustment of Nose Gear Down Limit Switch .................... 2115
7A-12. Adjustment of Main Gear Down Limit Switch ................... 2115
7A-13. Wiring Diagram of Landing Gear Electrical Circuit ............... 2117
7A- 14. Throttle Warning Switches .................................... 2119
7A-15. Nose Wheel Assembly.......................................... 2122
7A-16. Main Wheel Assembly ........................................ 2123
7A-17. Wheel Brake Assembly .................... ................... 2J1
7A-18. Brake Disc Minimum Thickness ................................ 2J3

Revised: 8 3 81 1A9
1A9
 PIPER CHEROKEE SERVICE MANUAL

LIST OF ILLUSTRATIONS (cont.)

Figure Aerofiche
Grid No.

7A-19. Brake System Installation ..................................... 2J3

7A-20. Brake Master Cylinder (Hand Parking Brake) ................... 2J5
7A-21. Toe Brake Installation ........................................ 2J6
7A-22. Brake Cylinder (Toe Brake) (10-20. 10-27. 17000) ................. 2J8
7A-23. Brake Cylinder (Toe Brake) (10-30) ............................. 2J10
7A-24. Bearing Installation ........................................... 2J11
7A-25. Nose Gear Ser ice Tolerances. PA-28R .......................... 2J20
7A-26. Main Gear Service Tolerances. PA-28R ....... .................. 2J23
8-1. Typical Nicks and Removal Method ............................ 2K8
8-2. Propeller Installation (Constant Speed). PA-28-235 ............... 2K8
8-3. Propeller Installation ......................................... 2K9
8-4. Adjustment of Propeller Control. PA-28-235 ................... 2K 13
8-5. Propeller Governor. PA-28-235 ...... ....................... 2K 13
8-6. Engine Installation. PA-28-140. -150. -160. -180.
Serial Nos. 28-1 to 28-1760 ............................... 2K16
8-7. Engine Installation. PA-28-140. -150. -160. -180.
Serial Nos. 28-1761 and up...... ......... ............. 2K17
8-8. Engine Shock Mount Installation. PA-28-140.
Serial Nos. 28-25000 and up ........................... .... 2K 18
8-9. Engine Installation. PA-28-235 ................................. 2K22
8-10. Adjustment of Engine Controls ................................. 2K24
8-11. Carburetor. PA-28-140. -150. -160 ............................ .. 2L3
8-12. Carburetor. PA-28-180. -235 ................................... 2L3
8-13. Magneto Inspection ........................................... 2L5
8-14. Contact Spring Inspection ..................................... 2L6
8-15. Impulse Coupling ............................................ 2L6
8-16. Magneto Timing Marks ....................................... 2L7
8-17. Timing Pointer .............................................. 2L7
8-18. Timing Kit Installed .......................................... 2L8
8-19. Breaker Compartment With Cast Timing Marks .................. 2L8
8-20. Removing Spark Plug Frozen to Bushing ........................ 2L13
8-21. Ignition Switch Wiring Positions ........................... .... 2L16
8A-1. Propeller Installation ......................................... 3A12
8A-2. Typical Nicks and Removal Method ............................ 3A13
8A-3. Propeller Governor ........................................... 3A16
8A-4. Engine Installation. PA-28R-180 ............................... 3A19
8A-5. Engine Installation. PA-28R-200 ............................... 3A21
8A-6. Adjustment of Engine Controls ................................. 3B1
8A-7. Fuel Injector ................................................. 3B3
8A-8. Schematic Diagram of RSA Fuel Injection System ................ 3B4
8A-9. Fuel-Air Bleed Nozzle ......................................... 3B6
8A-10. Contact Points ............................................... 3B8

Revised: 8 3 81
1A10
 PIPER CHEROKEE SERVICE MANUAL

LIST OF ILLUSTRATIONS (cont.)

Figure Aerofiche
Grid No.
8A-11. Rotor Holding Tool Installed .................................. 3B10
8A-12. Timing Kit Installed ............. ..................... 3B10
8A-13. Aligning Timing Marks ....................................... 3B11
8A-14. Checking Flyweight Clearance of Impulse Coupling ............. 3B12
8A-15. Engine Timing Marks . ................. . ..................... 3B13
8A-16. Magneto Adjustment Limits . .............................. . 3B14
8A-17. Magneto Timing Marks . ...................................... 3B14
8A-18. Removing Spring From Lead Assembly . . ............ 3B16
8A-19. Assembly Tool . .............................................. 3B16
8A-20. Using Assembly Tool ......................................... 3B 17
8A-21. Measuring Lead Assembly Length . ............................. 3B17
8A-22. Cutting Metallic Braid From End of Lead ....................... 3B18
8A-23. Unbraiding Metallic Shielding ................................ 3B18
8A-24. Forming Shielding Around Ferrule ...... .......... ....... 3B19
8A-25. Ferrule Seating Tool .... ... ... ..... .............. 3B19
8A-26. Needle ...................................................... 3B19
8A-27. Measuring Wire From Top of Ferrule . . ................ 3B20
8A-28. Installing Grommet Over Lead Assemblies ... ............. 3B20
8A-29. Lead Assembly Installed in Grommet . .......................... 3B20
8A-30. Wire Doubled Over For Installation of Eyelet ..... ............. 3B20
8A-31. Removing Spark Plug Frozen to Bushing ........ .............. 3B22
8A-32. Ignition Switch Wiring Positions . .............................. 3B24
9-1. Fuel System Diagram, PA-28-140, -150, -160. -180 ... .......... . 3CII
9-2. Fuel System Diagram. PA-28-235. Serial Nos. 28-10003
to 28-10719 inc ........................................... 3C12
9-3. Fuel System Diagram. PA-28-235. Serial Nos. 28-10720 and up.... 3C13
9-4. Fuel System Diagram. PA-28R................................. 3C14
9-5. Deleted .....................
9-6. Fuel Quantity Transmitter (P N 62037-00) ......... . 3C21
9-7. Fuel Quantity Transmitter (P/N 68101-00) . ...................... 3C21
9-8. Fuel Selector and Filter. PA-28-235 . ............................ 3C24
9-9. Fuel Filter. PA-28-235 ...... ................... 3DI
9-10. Fuel Filter Bowl and Screen. PA-28-140, -150, -160, -180
and PA-28R............................................. 3D3
9-11. Plunger Fuel Pump (Early). PA-28-150, -160, -180 . .......... 3D6
9-12. Plunger Fuel Pump (Late), PA-28-140, -150, -160. -180, -235 ....... 3D6
9-13. Engine Primer ............................................... 3D12
9-14. Fabricated Fuel Quantity Transmitter Checking Jig . ............. 3D17
10-1. Instrument Panel, PA-28-140, Serial Nos. 28-25000 to
28-26956 incl.......................... .................. 3E4
10-2. Instrument Panel. PA-28-140, Serial Nos. 28-7125001 to
28-7325684 inc . .......................................... 3E5

Revised: 8/3/81 lA11

1All
 PIPER CHEROKEE SERVICE MANUAL

LIST OF ILLUSTRATIONS (cont.)

Figure Aerofiche
Grid No.

10-3. Instrument Panel. PA-28-140. Serial Nos. 28-7425001 and up ...... 3E6
10-4. Instrument Panel ............................................. 3E7
10-5. Instrument Panel. PA-28-150. -160. -180. Serial Nos. 28-1761
to 28-4377 incl ........................................... 3E8
10-6. Instrument Panel. PA-28-180. Serial Nos. 28-4378 to
28-7205328 incl .......................................... 3E9
10-7. Instrument Panel. PA-28-180. Serial Nos. 28-7305001 to
28-7305611 incl .......................................... 3E10
10-8. Instrument Panel. PA-28-180. Serial Nos. 28-7405001 and up ...... 3E11
10-9. Instrument Panel. PA-28-235. Serial Nos. 28-10720 to
28-11039 inc ............................................. 3E12
10-10. Instrument Panel. PA-28-235. Serial Nos. 28-11040 to
28-7210033 inc ........................................... 3E13
10- 11. Instrument Panel. PA-28-235. Serial Nos. 28-7310001 to
28-7310187 incl .......................................... 3E14
10-12. Instrument Panel. PA-28-235. Serial Nos. 28-7410001 and up...... 3E15
10-13. Instrument Panel. PA-28R-180. Serial Nos. 28-30005 to
28-30879 incl ............................................ 3E16
10-14. Instrument Panel. PA-28R-180. Serial Nos. 28-30880 to
28-7130019 incl.: PA-28R-200. Serial Nos. 28-30482.
28-35001 to 28-35830 incl. and 28-7135001 to
28-7135238 incl .......................................... 3E17
10-15. Instrument Panel. PA-28R-200. Serial Nos. 28-7235001 to
28-7335455 incl .......................................... 3E18
10-16. Instrument Panel. PA-28R-200. Serial Nos. 28-7435001 and up..... 3E19
10-17. Warning Light Pressure Switch ................................. 3E23
10-18. Typical Pitot Static System. PA-28-140. -150. -160. -180. -235.
PA-28R-180 and 200...................................... 3F4
10-19. EGT Probe Location. PA-28R-180 and 200 ...................... 3F24
10-20. EGT Probe Location. PA-28-235 ............................... 3GI
10-21. EGT Probe Location. PA-28-150. -160. -180. S N 1761 and up..... 3G2
11-1. Generator and Starter System .................................. 4A 18
11-2. Generator Wiring Diagram .................................... 4A19
11-3. Sectional View of Generator ................................... 4A22
11-4. Current Voltage Regulator ............................. 4B7
11-5. Use of Riffler File to Clean Contact Points ...................... 4B10
11-6. Voltage Regulator Air Gap ....................... 4B 10
11-7. Checking Voltage Setting Fixed Resistance Method ............... 4B 11
11-8. Checking Voltage Setting Variable Resistance Method ............ 4B I
11-9. Adjusting Voltage Regulator Setting ............................ 4B 12
11-10. Cutout Relay Air Gap Check and Adjustment ................... 4B14
11-11. Cutout Relay Point Opening Check and Adjustment .............. 4B14

Revised: 8 3 81 1A12
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 PIPER CHEROKEE SERVICE MANUAL

LIST OF ILLUSTRATIONS (cont.)

Figure Aerofiche
Grid No.

11-12. Checking Cutout Relay Closing Voltage ......................... 4B15

11-13. AdJustment of Cutout Relay Closing Voltage .................. 4B15
11-14. Checking Current Regulator. Load Method ...................... 4B16
11-15. Checking Current Regulator. Jumper Lead Method ............... 4B16
11-16. Alternator and Starter System.
PA-28-140. Serial Nos. 28-20000 to 28-24999 incl.:
PA-28-150. -160. Serial Nos. 28-508 to 28-3643 incl.:
PA-28-180. Serial Nos. 28-671 to 28-3643 incl.:
PA-28-235. Serial Nos. 28-10002 to 28-10762 incl ............ 4B20
11-17. Alternator and Starter System.
PA-28-140. Serial Nos. 28-25000 and up:
PA-28-150. -160. -180. Serial Nos. 28-3644 and up:
PA-28-235. Serial Nos. 10763 and up and PA-28R............ 4B21
11-18. Lamp-Bank Load .......... ................................. 4B23
11-19. Checking Field Circuit ...... .................................. 4B24
11-20. Testing Field Circuit .......................................... 4B24
11-21. Testing Rectifiers (Positixe) .................................... 4C2
11-22. Testing Rectifiers (Negative) ................................... 4C3
11-23. C-3928 Fixtures and Adapters .................................. 4C4
11-24. Removing Rectifiers ..... .............................. ..... 4C4
11-25. Installing Rectifiers ..... ...................................... 4C5
11-26. Soldering Rectifier Lead ....................................... 4C6
11-27. Testing Stator Coils ......................................... 4C7
11-28. Removing End Bearing ........................................ 4C9
11-29. Installing End Bearing ..... ............................ .... 4C9
11-30. Removing Drive Pulley ....................................... 4C10
11-31. Removing Drive End Bearing .................................. 4C10
11-32. Removing Slip Ring ...................... .................. 4C 11
11-33. Aligning Slip Ring .......................................... 4C11
11-34. Installing Slip Ring ........................................... 4C12
11-35. Installing Retainer ........................................... 4C12
11-36. Solder Points ................................................ 4C13
11-37. Installing Drive End Shield and Bearing (Typical) ................ 4C14
11-38. Installing Pulley ..................... ...................... 4C 14
11-39. Meter Connections for Alternator Performance Test .............. 4C17
11-40. Voltage Regulator ............................................ 4C19
11-41. Checking Air Gap ............................................ 4C19
11-42. Voltage Regulator Fusible Wires ............................... 4C20
11-43. Voltage Regulator Resistance Units ............................. 4C20
11-44. No-Load Test Hookup ........................................ 4D2
11-45. Lock Torque Test Hookup ................................... 4D3
11-46. Resistance Test Hookup ....................................... 4D3

Revised: 8 3 81 1A13
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 PIPER CHEROKEE SERVICE MANUAL

LIST OF ILLUSTRATIONS (cont.)

Figure Aerofiche
Grid No.

11-47. Exploded View of Gear Reduction Starting Motor ................ 4D8

11-48. Turning Starting Motor Commutator ........................... 4D I
11-49. Testing Motor Armature for Shorts ............................. 4D I
11-50. Testing Motor Field for Grounds ............................. 4D I
11-51. No-Load Test Hookup ..... . ....................... 4D13
11-52. Stall Torque Hookup ......................................... 4D13
11-53. Terminal Block ............................................ 4F5
11-54. For Index to these Figures, see Table XI-I, Index - Electrical 4F11
thru System Schematics thru
11-70. 4G17
11-71. Exploded View of Alternator .................................. 4D20
11-72. Removal of Slip Ring End Bearing ............................. 4D21
11-73. Removal of Rectifier .......................................... 4D21
11-74. Removal of Drive End Head .................................. 4D22
11-75. Removal of End Head Bearing ................ .... .. ..... 4D22
11-76. Testing Rotor for Ground ..................................... 4D23
11-77. Testing Rotor for Shorts ..................................... 4D23
11-78. Installation of Bearing ..................................... 4D24
11-79. Installation of Rectifier ....................................... 4D24
11-80. Terminal Assembly ........................................... 4E I
11-81. Slip Ring End Bearing Assembly ............................... 4E2
11-82. Testing Alternator ............................................ 4E2
11-83. Brush Installation ............................................ 4E3
11-84. Internal Wiring Diagram ...................................... 4E3
11-85. For Index to these Figures. see Table XI-I, Index - Electrical 4G20
thru System Schematics thru
11-143. 4H 24
11-144. Strobe Light Connections ..................................... 4E9
12-1. Two Year Magnesium Battery Connections ......... ......... 413
12-2. Five Year, Lithium Battery Connections ... .... .................. 414
12-3. Communications Components ELT Schematic ................... 4111
13-1. Cabin Heater. Defroster and Fresh Air System,
PA-28-140. Serial Nos. 28-2002 to 28-24999 incl..
and PA-28-150, -160, -180, Serial Nos. 28-1 to
28-1760 incl ............... ... .................. 4117
13-2. Cabin Heater. Defroster and Fresh Air System,
PA-28-140, Serial Nos. 28-25000 and up ..................... 4118
13-3. Cabin Heater. Defroster and Fresh Air System,
PA-28-150. -160, -180. Serial Nos. 28-1761 to
28-2477 incl .............................................. 4119

Revised: 10 3,83 lA14

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 PIPER CHEROKEE SERVICE MANUAL

LIST OF ILLUSTRATIONS (cont.)

Figure Aerofiche
Grid No.

13-4. Cabin Heater. Defroster and Fresh Air System.

PA-28-150. -160. -180, Serial Nos. 28-2478 to
28-4377 incl.............................................. 4120
13-5. Cabin Heater. Defroster and Fresh Air System.
PA-28-180. Serial Nos. 28-4378 and up ...................... 4121
13-6. Cabin Heater. Defroster and Fresh Air System.
PA-28-235. Serial Nos. 28-10003 to 28-10675 incl ............ 4122
13-7. Cabin Heater. Defroster and Fresh Air System.
PA-28-235. Serial Nos. 28-10676 to 28-11039 incl ............ 4123
13-8. Cabin Heater. Defroster and Fresh Air System,
PA-28-235. Serial Nos. 28-11040 to 28-7210033 incl. .......... 4124
13-9. Cabin Heater. Defroster and Fresh Air System.
PA-28-235. Serial Nos. 28-7310001 and up................... 4.11
13-10. Cabin Heater. Defroster and Fresh Air System.
PA-28R ................................................. 4J2
13-11. Overhead Vent System. ........................................ 4.13
14-1. Air Conditioning System Installation ............................ 4J7
14-2. Service Valves ............................................... 4J 12
14-3. Test Gauge and Manifold Set .................................. 4J13
14-4. Manifold Set Operation ....................................... 4J 14
14-5. Leak Test Hookup ........................................... 4.115
14-6. Evacuation Hookup .......................................... 4J 17
14-7. Charging Stand ...... ........................................ 4J 19
14-8. Charging Hookup ...................................... ...... 4J21
14-9. Compressor and Fabricated Oil Dipstick .......................... 4K I
14-10. Compressor and Alternator Belt Installation ..................... 4K5
14-11. Magnetic Clutch ............................................. 4K7
14-12. Condenser Air Scoop Installation ............................ 4K11
14-13. Expansion Valve ............................................. 4K13
14-14. Components Installation ...................................... 4K15
14-15. Control Head - Diode Mounting Board, Diode Location and
Number. PA-28-140. Serial Nos. 28-7125472 to 28-7325057;
PA-28-180. Serial Nos. 28-7205092 to 28-7305071;
PA-28R-200. 28R-7235001 to 28R-7335057 .................. 4K16
14-16. Air Conditioning Wiring Schematic,
PA-28-140. Serial Nos. 28-7125472 thru 28-7225131 incl.:
PA-28-180, Serial Nos. 28-7205092 thru 28-7205144 incl........ 4K18

Revised: 10 3 83 1A15
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 PIPER CHEROKEE SERVICE MANUAL

LIST OF ILLUSTRATIONS (cont.)

Figure Aerofiche
Grid No.

14-17. Air Conditioning Wiring Schematic,

PA-28-140. Serial Nos. 28-7225132 to 28-7225612;
PA-28-180. Serial Nos. 28-7205145 to 28-7205328;
PA-28R-200. Serial Nos. 28R-7235001 to 28R-7235330........ 4K19
14-18. Air Conditioning Wiring Schematic,
PA-28-140. Serial Nos. 28-7325001 and up:
PA-28-180. Serial Nos. 28-7305001 and up:
PA-28R-200. Serial Nos. 28-7335001 and up .................. 4K20

Revised: 10 3/83 1A16

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 PIPER CHEROKEE SERVICE MANUAL

LIST OF TABLES

Table Aerofiche
Grid No.
11-I. Leading Particulars and Principal Dimensions ................. IB16
11-11. Consumable Materials ......... ............................. IC3
11-111. Recommended Nut Torques ................................. 1C22
II-IV. Deleted ........................................
1l-V. Conversion Tables .......................................... IC24
II-VI. Decimal Millimeter Equivalents of Drill Sizes ........................ ID5
II-VII. Maximum Distance Between Supports for Fluid Tubing ......... D6
II-VIII. Hose Clamp Tightening .................................... ID6
II-IX. Recommended Engine Lubricating Oils ....................... IE 15
II-X. Thread Lubricants .................................... ...... 1E15
II-XI. Summary of Recommended Lubricants used on PA-28
Series Aircraft ......................................... E16
111-I. Inspection Report, PA-28-140. -150. -160. -180;
PA-28-235 ..................... ........................ 1F18
111-11. Inspection Report. PA-28R .................................. IG3
IV-I. List of Materials (Thermoplastic Repair) ...................... 117
IV-II. Balancing Specifications ................................. .... 1117
V-l. Control Surface Travel and Cable Tension .................... 2A 11
V-ll. Cable Tension Vs. Ambient Temperature ...................... 2A13
V-Ill. Troubleshooting Chart (Surface Controls) ..................... 2C19
VI-1. Leading Particulars. Hydraulic System ........................ 2D8
VI-lI. Characteristics, Hydraulic Pump Motor ....................... 2D13
VI-III. Hydraulic System Troubleshooting ........................... 2E9
VII-I Nose Gear Alignment Tolerances ............................. 2F9
VII-II. Landing Gear Troubleshooting ............................... 2G20
VIIA-I. Landing Gear Troubleshooting ............................... 2J 12
VIIA-II. PA-28R Nose Gear Service Tolerances ....................... 2J21
VIIA-III. PA-28R Main Gear Service Tolerances ........................ 2J24
VIII-I. Propeller Torque Limits ..................................... 2K10
VIII-II. Engine Troubleshooting Chart ............................... 2L17
VIIIA-I. Engine Troubleshooting Chart ........................... .... 3CI
IX-1. Transmitter/Fuel Gauge Tolerances .......................... 3C20
IX-II. Fuel Quantity Transmitter Calibration Tolerances .............. 3C21
IX-III. Fuel System Troubleshooting ............................... 3D15
X-l. Vacuum System ............................................ 3D24
X-ll. Directional Gyro Indicator .................................. 3F5

Revised: 8 3 81 1A17
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 PIPER CHEROKEE SERVICE MANUAL

LIST OF TABLES (cont.)

Table Aerofiche
Grid No.

X-lll. Gyro Horizon Indicator.............. ....................... 3F7

X-IV. Rate of Climb Indicator.............. ....................... 3F8
X-V. meter ........................... ....................... 3F10
X-VI. Airspeed Tubes and Indicator......... ....................... 3F 12
X-VII. Magnetic Compass .................. ....................... 3F14
X-VIII. Manifold Pressure Indicator.......... ....................... 3F15
X-IX. Tachometer ........................ ....................... 3F 16
X-X. Engine Oil Pressure Gauge ........... ....................... 3F 17
X-XI. Fuel Pressure Gauge................. ....................... 3F18
X-XII. Turn and Bank Indicator............. ....................... 3F19
X-XIII. Fuel Quantity Indicators .................................... 3F20
X-XIV. Oil Temperature Indicators .................................. 3F21
X-XV. Troubleshooting EGT Gauge ................................ 3F23
X-XVI. Cylinder Head Temperature Gauge ........................... 3F24
X-XVII. Fuel Flow Gauge ......... ................................. 3GI
XI-I. Electrical System Schematic Index............................ 4A12
XI-lI. Electrical System Troubleshooting .......................... 4E10
XI-lll. Electrical System Component Loads .......................... 4F8
XI-IV. Electrical Symbols.......................................... 4F9
XI-V. Electrical Wire Coding ..................................... 4F10
XIV-I. Temperature Pressure Chart ................................. 4.18
XIV-II. Aluminum Tubing Torque................................... 4JII
XIV-III. Compressor Oil Change ..................................... 4.124
XIV-IV. Air Conditioning System Troubleshooting ..................... 4K21
XIV-V. Blower System Wire Color Codes ............................ 4L6

Revised: 10 383
1A18
 SECTION
I

INTRODUCTION

Aerofiche
Grid No.

1-1. General ....... ... . 1A20

1-2. Scope of Manual ..... ... ..1A20
1-3. Description ....... ... . 1A20
1-4. Wing ........ ... . 1A20
1-5. Empennage ....... ... ..1A20
1-6. Fuselage ....... ... . 1A21
1-7. Landing Gear (Fixed) .... . 1A21
1-8. Landing Gear (Retractable) .... .... A21
1-9. Hydraulic System (PA-28R) .... .... A21
1-10. Brake System ...... . .. 1A21
1-11. Engines ........ 1A21
1-12. Propellers . ...... .... 1A21
1.-13. Fuel System ............. ..... 1A21
1-14. Flight Controls ............. ... . 1A22
1-15. Radio ....... ... . 1A22
1-16. Cabin Heater, Defroster, and Fresh Air System . .. 1A22
1-17. Instrument and AutoPilot System ... . 1A22

Reissued:1/15/81
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 PIPER CHEROKEE SERVICE MANUAL

SECTIONI
INTRODUCTION

WARNING
When servicing or inspecting vendor equipment installed in Piper
aircraft,it is the user'sresponsibilityto referto the applicablevendor
publication.

1-1. GENERAL. This manual contains serviceand maintenanceinstructionsfor PA-28-140.

-150. -160. -180. -235 and PA-28R-180 200 Cherokees. designed and manufactured as
versatile airplanes in the personal and business aviation field. by the Piper Aircraft
Corporation . Vero Beach. Florida.

1-2. SCOPE OF MANUAL. Sections II and III comprise the service part of this manual,
whereas Sections IV through XIII comprise the maintenance instructions. The service
instructions include ground handling, servicing and inspections. The maintenance
instructions for each system include troubleshooting, removal and installation of
components, and corrective maintenance and testing; each major system of the airplane is
covered in a separate section. Only qualified personnel should perform the operations
described in this manual.
The description of the airplane included in this section is limited to general
information. Section II gives leading particulars and principal dimensions, while each major
system is described in its appropriate section of the manual. For a more detailed description
of the airplane, refer to the Owner's Handbook, or Pilot's Information Manual for the
particular airplane.

1-3. DESCRIPTION. The Cherokee PA-28 is a single-engine. low-wing monoplane of all

metal construction. The standard PA-28-140 is a two place. with third and fourth family seats
available as optional equipment. The PA-28-150. -160. -180. -235 and PA-28R-180 200 are
four place airplanes. Paragraphs 1-4 through 1-17 provide descriptions of the major
components and systems.

1-4. WING. The laminar flow wing is of all-metal stressed-skin, full cantilever, low-wing
design, consisting of two wing panels bolted to a spar box assembly in the fuselage. The
wing tips are removable. The ailerons are cable and push rod controlled and are dynamically
balanced. The trailing edge wing flaps are manually operated.

1-5. EMPENNAGE. The empennage consists of the fin, rudder, stabilator and stabilator
trim tabs. The stabilator is dynamically balanced.

Revised: 1/15/86 INTRODUCTION

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 PIPER CHEROKEE SERVICE MANUAL

1-6. FUSELAGE. The fuselage consists of three basic units: The engine section, the cabin
section, and the sheet-metal tail cone.

1-7. LANDING GEAR. (Fixed) The tricycle landinggearis of the fixed type, consistingof
shock absorbingair-oiltype oleo struts.

1-8. LANDINGGEAR.(Retractable)The tricycle landinggearis a hydraulicallyoperated,

fully retractableunit consistingof shock absorbingair-oiltype oleo struts.

1-9. HYDRAULIC SYSTEM. (PA-28R-180 200) The hydraulic system incorporates an

electrically driven pump which is controlled by a lever on the instrument panel which in turn
operates the retraction and extension of the landing gear.

1-10. BRAKE SYSTEM. The brake system operated hydraulically is controlled by a hand
lever connected to a single brake cylinder that operates both wheel brakes. On later models,
the hand lever plus individually operated brakes and cylinder control the brakes. Dual toe
brakes may be installed as optional equipment.

1-11. ENGINES. The engines installed in the PA-28 series airplanes are Avco-Lycoming
direct drive, wet sump. horizontally opposed. air cooled models. The four-cylinder engines
in the PA-28-140. -150.-160. -180 and the six-cylinder engine in the PA-28-235 are carburetor
equipped while the four-cylinder engine in the PA-28-180 200 is fuel injector equipped. The
engine model. rated horsepower and other related information for each engine may be found
in Table 11-1of Section II.

1-12. PROPELLERS. The PA-28-140. -150. -160. -180 and -235 models are equipped with
an all-metal fixed pitch propeller. A constant speed propeller may be installed as optional
equipment on the PA-28-235. and is installed as standard equipment on the PA-28R-180 200.
The constant speed propellers are controlled by a governor mounted on the engine. The
governor is in turn controlled by a lever on the power quadrant. Propeller specifications may
be found in Table 11-1of Section 11.
1-13. FUEL SYSTEM. The fuel system on the PA-28-140. -150. -160. -180 and
PA-28R-180 200 consists of two aluminum tanks in the leading edge of the wings.
a strainer
bowl with fuel screen. one electrical auxiliary pump and one engine driven pump. The fuel
system for the PA-28-235 consists of two aluminum tanks in the wings plus an auxiliary
fiberglass tank in each wing tip. There also is a combination fuel selector and filter, electrical
auxiliary fuel pump(s) and one engine driven pump.

Revised: 10 3 83 INTRODUCTION

1A21
 PIPER CHEROKEE SERVICEMANUAL

1-14. FLIGHT CONTROLS. The flight controls are conventional equipment, consistingof
a control wheel which operates the ailerons and stabilator, and pedals which operate the
rudder. Duplicate controls are provided for the copilot.

1-15. RADIO. Provisions are provided for the installations of microphone and headset
jacks, loudspeaker, and panel space for radios.

1-16. CABIN HEATER. DEFROSTER AND FRESH AIR SYSTEM. Heated air for the
cabin and defroster is obtained directly from the exhaust system muffler shroud. Fresh air
for the PA-28-140. PA-28-150.-160. -180. Serial Nos. 28-1 to 28-2477incl.. and PA-28-235.
Serial Nos. 28-10003 to 28-10675 incl.. is obtained through an intake located on the left
forward side of the fuselage. directing air to the forward section of the cockpit. Additional
intakes are located on each side of the fuselage. venting air to the individual seat location.
On the PA-28-150. -160. -180. Serial Nos. 28-2478 and up: PA-28-235. Serial Nos. 28-10676
and up. and PA-28R-180 200. fresh air is picked up from an inlet in the leading edge of each
wing. The air passed through the wings to indivually controlled outlets located just forward of
each seat. An air ent is located in the top or bottom of the fuselage to take exhaust air from
the cabin interior.

1-17. INSTRUMENTAND AUTOPILOT SYSTEM. Provisions for instrument installation

include panels for engine instruments and advanced instruments, as well as for an Autopilot
System.

Revised: 10 3 83 INTRODUCTION
1A22
 1A23
INTENTIONALLY LEFT BLANK
 SECTION II
HANDLING AND SERVICING
Paragraph Aerofiche
Grid No.

2-1. Introduction ......... ........................................ 1B3

2-2. Dimensions .................................................. 1B3
2-3. Station Reference Lines ....................................... 1B3
2-4. Weight and Balance Data ..................................... 1B3
2-5. Serial Number Plate .......................................... 1C20
2-6. Access and Inspection Provisions ............................... 1C20
2-7. Tools and Test Equipment ..................................... 1C20
2-8. Torque Requirements ......................................... IC20
2-8a. Torque Wrenches ............................................. 1C21
2-9. Walkway. Handhold and Step ................................. C24
2-10. Removal of Cherrylock Rivets ................................. 1D8
2-11. Ground Handling ........................................... 1D9
2-12. Introduction to Ground Handling ...................... 1D9
2-13. Jacking ............................................. D9
2-14. Weighing ........................................... ID10
2-15. Leveling ............................................ ID10
2-16. Mooring............................................ 1D11
2-17. Locking Airplane .................................... 1D12
2-18. Parking ............................................ 1D12
2-19. Towing ............................................. D13
2-20. Taxiing .......................... ................ 1D13
2-21. External Power Receptacle .................................... 1D13
2-22. Operation of External Power Receptacle ................ ID13
2-23. Cleaning .................................................... 1D14
2-24. Cleaning Engine Compartment ........................ 1D14
2-25. Cleaning Landing Gear ............................... D 15
2-26. Cleaning Exterior Surfaces............................ 1D15
2-27. Cleaning Windshield and Windows .................... ID15
2-28. Cleaning Headliner, Side Panels and Seats.............. 1D16
2-29. Cleaning Carpets .................................... D 16
2-30. Servicing.................................................... D 16
2-31. Introduction to Servicing ............................. 1D16
2-32. Hydraulic System (PA-28R) ................................... 1D16
2-33. Servicing Hydraulic System ........................... 1D16
2-34. Servicing Hydraulic Pump / Reservoir ................... 1D17

Revised: 8/3/81 A24

1A 24
 PIPER CHEROKEE SERVICE MANUAL

Paragraph Aerofiche
Grid No.
2-35. Landing Gear System ................................... 1D17
2-36. Servicing Landing Gear ........................ 1D17
2-37. Oleo Struts (PA-28-140. -150. -160. -180 and PA-28-235) .... 1D17
2-38. Servicing Oleo Struts ............. 1D17
2-39. Filling Nose Gear Oleo Strut ...... ID18
2-40. Filling Main Gear Oleo Strut ...... 1 D24
2-41. Inflating Oleo Struts .............. 1E1
2-42. Oleo Struts (PA-28R) ...................... IE2
2-43. Servicing Oleo Struts ............. IE2
2-44. Filling Oleo Struts ................ IE3
2-45. Inflating Oleo Struts .............. IE4
2-46. Brake System ............................. IE4
2-47. Servicing Brake System............ 1E4
2-48. Filling Brake Cylinder Reservoir.... 1E4
2-49. Draining Brake System............ IE5
2-50. Tires..................................... IE5
2-51. Servicing Tires ................... IE5
2-52. Power Plant.............................. IE5
2-53. Servicing Power Plant............. IE5
2-54. Induction Air Filter . ................... IE5
2-55. Removal of Air Filter ............. IE5
2-56. Service Instruction (Cleaning and Ins pection)............ 1E6
2-57. Installation of Air Filter .......... ............. 1E7
2-58.
2-58. Propeller.
Propeller .................................................... 1E7
2-59. Servicing Propeller................................. 1E7
2-60. Fuel System ................................................ IE7
2-61. Servicing Fuel System ................................ IE7
2-62. Filling Fuel Tanks (PA-28-140. -150, -180 and
PA-28R) ....................................... IE8
2-63. Filling Fuel Tanks (PA-28-235) ........................ IE8
2-64. Draining Moisture From Fuel System (PA-28-140, -150,
-160. -180 and PA-28R) ...................... 1E8
2-65. Draining Moisture From Fuel System (PA-28-235) .... IE8
2-66. Draining Fuel System ................................ IE10
2-67. Anti-Icing Fuel Additive ............................. IE10
2-68. Electrical System ............................................. IEIO
2-69. Ser icing Electrical System ............................ IE1O
2-70. Lubrication .................................................. 1E11
2-71. Oil System (Engine) .......................................... 1E11
2-72. Servicing Oil System ................................. 1E11
2-73. Filling Oil Sump .................................... IEII

Reissued: 1/15/81
1B1
 PIPER CHEROKEE SERVICE MANUAL

Aerofiche
Grid No.

2-74. Draining Oil Sump .......... IE12

2-75. Oil Screens. (Suction.) .. . ... 1E12
2-76. Oil Screen. (Pressure.) ....... 1E12
2-77. Oil Filter. (Full Flow.) ....... IE12
2-78. Recommendations for Changing Oil . E13
2-79. Lubrication Instructions . ...... 1E13
2-80. Application of Oil .......... IE13
2-81. Application of Grease ........ IE14
2-82. Winterization Plate ......... 1E14
2-83. Lubrication Chart . . . .... . 1E14

Reissued:1/15/81 IB2
 PIPER CHEROKEE SERVICE MANUAL

SECTION II

HANDLING AND SERVICING

2-1. INTRODUCTION. This section contains routine handling and servicing

procedures that are most frequently encountered. Frequent reference to this
section will aid the individual by providing information such as the location of
various components, ground handling procedures, routine service procedures
and lubrication. When any system or component requires service other than the
routine procedures as outlined in this section, refer to the appropriate section
for that component.

2-2. DIMENSIONS. The principal airplane dimensions are shown in Figures 2-1 through
2-12 and are listed in Table II-I.

2-3. STATION REFERENCE LINES. In order to facilitate the location of vari-

ous components of theairplanewhichrequiremaintenance and servicing, a method
utilizing fuselage station (Sta.), wing station or buttock line (BL), and water line
(WL) designations is frequently employed in this manual. (Refer to Figures 2-13
thru 2-24.) Fuselage stations, buttock lines, and water lines are reference points
measured by inches in the vertical or horizontal direction from a given reference
line which indicates station locations of structural members of the airplane. Sta-
tion 0 of the fuselage is 78.4 inches aheadof thewing leading edge or 49.5 inches
ahead of the lower edge of the firewall; station 0 (BL) of the wing and stabilator
is the centerline of the airplane; and station 0 (WL) of the fuselage vertical stab-
ilizer and rudder is 20.5 inches below the cabin floor as measured at the rear
wing spar with the airplane level. The reference datum line is located 78.4 inches
ahead of the wing leading edge at the intersection of the straight and tapered sec-
tion.

2-4. WEIGHT AND BALANCEDATA. Whenfiguringvarious weight and balance

computations, the empty, static and gross weight, and center of gravity of the
airplane may be found in the Weight and Balance Form of the Airplane Flight
Manual.

HANDLING AND SERVICING

Reissued: 1/15/81

1B3
 PIPER CHEROKEE SERVICE MANUAL

C329

63.75"
-

Figure 2-1. Three-Viewof Cherokee

PA-28-140and PA-28-150-160-180,Serial Nos. 28-1 to 28-1760 incl.
PA-28-140Flite Liner, Serial Nos. 28-7125174 and up

Reissued: 1/15/81 HANDLING AND SERVICING

1B4
 PIPER CHEROKEE SERVICE MANUAL

862

*1974 MODELS AND UP

30'

Figure 2-2. Three-View of Cherokee 140

PA-28-140, SerialNos. 28-7225001 and up

Reissued: 1/15/81 HANDLING AND SERVICING

1B5
 PIPER CHEROKEE SERVICE MANUAL

1694

Reissued: 1/15/81 HANDLINGAND SERVICING

1B6
 PIPER CHEROKEE SERVICE MANUAL

1836

Figure 2-4. Three-Viewof Cherokee

PA-28-180,Serial Nos. 28-4378 to 28-7105244 incl.

HANDLING AND SERVICING

Reissued:1/15/81
1B7
 PIPER CHEROKEE SERVICE MANUAL

1732

Figure 2-5. Three-View of Cherokee PA-28-180,

SerialNos. 28-7205001 to 28-7205328 incl.

HANDLINGAND SERVICING
Reissued: 1/15/81
1B8
 PIPER CHEROKEE SERVICE MANUAL

1724

1974 MODELS AND UP

Figure 2-6. Three-View of Cherokee PA-28-180,

Serial Nos. 28-7305001 and up

HANDLING AND SERVICING

Reissued: 1/15/81
 PIPER CHEROKEESERVICEMANUAL

1691

63.0"

1840

23' 8.55"

Figure 2-7. Three-View of Cherokee

PA-28-235, Serial Nos. 28-10000 to 28-11039 incl.

Reissued: 1/15/81 HANDLINGAND SERVICING

1BlO
 PIPER CHEROKEE SERVICE MANUAL

182B

Figure 2-8. Three-View of Cherokee

PA-28-235,Serial Nos. 28-11040 to 28-7110042 incl.

HANDLING AND SERVICING

Reissued:1/15/81

1Bll
 PIPER CHEROKEE SERVICE MANUAL

C330

Figure 2-9. Three-View of Cherokee PA-28-235,

SerialNos. 28-7210001 to 28-7210033 incl.

Reissued: 1/15/81 HANDLING AND SERVICING

1B12
 PIPER CHEROKEE SERVICE MANUAL

886

*1974 MODELS AND UP

Figure 2-10. Three-View of Cherokee PA-28-235,

Serial Nos. 28-7310001 and up

Reissued: 1/15/81 HANDLING AND SERVICING

1B13
 PIPER CHEROKEE SERVICE MANUAL

1796

30'

Figure 2-11. Three-View of Cherokee

PA-28R-180,Serial Nos. 28-30005 to
PA-28R-200,SerialNos. 28-30482 to 28-7130019 incl.
28-7135238 incl.

Reissued: 1/15/81
HANDLINGAND SERVICING

1B14
 PIPER CHEROKEESERVICEMANUAL

1796

*1974 MODELS AND Up

5' 3.0"

32' 2.32"

7° DIHEDRAL

11.83"
74.00" <1
72.50"

Figure 2-12. Three-View of Cherokee

PA-28R-200, SerialNos. 28-7235001 and up

HANDLING AND SERVICING

Reissued: 1/15/81
1B15
 PIPER CHEROKEE SERVICE MANUAL

TABLE II-I. LEADING PARTICULARS AND PRINCIPAL DIMENSIONS

MODEL PA-28-140
ENGINE

Manufacturer Avco-Lycoming
Model O-320-E2A or O-320-E3D

FAA Type Certificate 274

Rated Horsepower 140 or 150
Rated Speed:
Full Throttle 2450 RPM - 2700 RPM
Oil, SAE Number See Table II-IX
Oil Sump Capacity 8 U.S. quarts
Fuel, Aviation Grade (Minimum Octane) 80/87
Fuel, Aviation Grade (Specified Octane) 80/87
Fuel, Aviation Grade (Alternate) See Note 37
Fuel Injector, Bendix
Magnetos, Scintilla: Scintilla or Slick
Left S4LN-21 or 4051
Right S4LN-204 or 4050
Magneto Timing 25° BTC
Magneto Point Clearance 0.018 + 0.006
Spark Plugs (Shielded):
Refer to the latest revision of Lycoming
Service Instruction No. 1042.
Firing Order 1-3-2-4

Starter:
Delco-Remy, 12 Volt 1109657
Prestolite, 12 Volt MZ4204
Alternator, Chrysler (35 AMP) 20 2098615 or 2642996
Voltage Regulator, Chrysler 2098613 or 87-87102-21 32
Alternator, Chrysler (60 AMP) 30 2642997 or 2642210
Voltage Regulator, WICO X16300B
Overvoltage Relay, WICO X16799B
Alternator, Prestolite (60 AMP) ALY-6422 31
Voltage Regulator, WICO X16300B
Fuel Pump Drive Plunger

PROPELLER

Fixed Pitch:
Manufacturer Sensenich
Model M74DM

Refer to Grid IC2 for foot Notes:

HANDLING AND SERVICING

Revised: 10 3 83
1B16
 PIPER CHEROKEE SERVICE MANUAL

TABLE II-I. LEADING PARTICULARS AND PRINCIPAL DIMENSIONS (cont)

MODEL PA-28-140
PROPELLER (cont.)
Diameter 74.0 in.
Diameter, Minimum 72.5 in.
Blade Pitch in Inches at the 75% Radius Station 9 58 thru 62 in. 21
56 thru 58 in. 22
FUEL SYSTEM

Inboard (Main Fuel Tanks Two

Capacity) (each) 25 U.S. gal.
Unusable Fuel (each) 0.125 U.S. gal.
Total Capacity 50 U.S. gal.
Total Unusable Fuel
Refer to Owner's Handbook, Pilot's
Information Manual or Flight Manual
for particular airplane.

LANDING GEAR

Type Fixed
Shock Strut Type Combination Air-Oil
Fluid Required (Struts, Hydraulic System
and Brakes) MIL-H-5606
Strut Exposure (Exposure under static load):
Nose 3.25 + .25 in.
Main 4.50 ± .25 in.
Wheel Tread 10.0 ft.
Wheel Base 6 ft. 2.65 in. 17 or 6 ft. 1.92 in. 14
Nose Wheel Travel REFER TO SECTION VII
TABLE VII-I
Wheel, Nose Cleveland 38501, 6:00 x 6
Wheel, Main Cleveland 40-28, 6:00 x 6 14
Cleveland 40-86, 6:00 x 6 15
Brake Type Cleveland 30-18 14
Cleveland 30-55 15
Tires, Nose 6:00 x 6, 4 ply rating
Tires, Main 6:00 x 6, 4 ply rating
Tire Pressure, Nose 24 psi
Tire Pressure, Main 24 psi

ALL MODELS, CONTROL SURFACES

AND CABLE TENSIONS REFER TO SECTION V
TABLE V-I
Refer to Grid 1C2 for foot Notes:

Revised: 10 3 83 HANDLING AND SERVICING

lB17
 PIPER CHEROKEE SERVICE MANUAL

TABLE II-I. LEADING PARTICULARS AND PRINCIPAL DIMENSIONS (cont)

MODEL PA-28-150 PA-28-160

ENGINE

Manufacturer Avco-Lycoming Avco-Lycoming

Model O-320-A2B or O-320-E2A O-320-B2B or O-320-D2A

FAA Type Certificate 274 274

Rated Horsepower 150 160
Full Throttle 2700 RPM 2700 RPM
Oil, SAE Number See Table II-IX See Table II-IX
Oil Sump Capacity 8 U.S. quarts 8 U.S. quarts
Fuel, Aviation Grade (Minimum Octane) 80/87 90/96
Fuel, Aviation Grade (Specified Octane) 80/87 90/96
Fuel, Aviation Grade (Alternate) See Note 37
Fuel Injector, Bendix
Magnetos, Scintilla:
Left S4LN-21 S4LN-21
Right S4LN-204 S4LN-20
Magneto Timing 25° BTC 25° BTC
Magneto Point Clearance 0.018 ± 0.006 in. 0.018 +.006 in.
Spark Plugs (Shielded):
Refer to the latest revision of Lycoming
Service Instruction No. 1042.
Firing Order 1-3-2-4 1-3-2-4

Starter:
Delco-Remy, 12 Volt 1109657 1109657 or 1109511
Prestolite, 12 Volt MZ4204 MZ4206
Generator, Delco-Remy (35 AMP) 1101900 1101900
Voltage Regulator, Delco-Remy 1118704 1118704
Alternator, Chrysler (35 AMP) 20 2098615 or 2642996 2098615 or 2642996
Voltage Regulator, Chrysler 2098613 or 87-87102-21 32 2098613 or 87-87102-21 32
Alternator, Chrysler (60 AMP) 30 2642997 or 2642210 2642997 or 2642210
Voltage Regulator, WICO X16300B X16300B
Overvoltage Relay, WICO X16799B 5 X16799B5
Fuel Pump Drive Plunger Plunger

PROPELLER
Fixed Pitch:
Manufacturer Sensenich Sensenich
Model M74DM 7 or M74DMS 8 M74DM 7 or M74DMS 8

I Refer to Grid 1C2 for foot Notes:

Revised: 10 3 83 HANDLINGANDSERVICING

lB18
 PIPER CHEROKEE SERVICE MANUAL

TABLE II-I. LEADING PARTICULARS AND PRINCIPAL DIMENSIONS (cont)

MODEL PA-28-150 PA-28-160

PROPELLER (cont.)
Diameter 74.0 in. 74.0 in.
Diameter, Minimum 72.5 in. 72.5 in.
Blade Angle 9 58 in. 60 in. - 47 in. 27

FUEL SYSTEM
Inboard (Main Fuel Tanks Two Two
Capacity) (each) 25 U.S. gal. 25 U.S. gal.
Unusable Fuel (each) 0.125 U.S. gal. 0.125 U.S. gal.
Total Capacity 50 U.S. gal. 50 U.S. gal.
Total Unusable Fuel
Refer to Owner's Handbook, Pilot's
Information Manual or Flight Manual
for particular airplane.

LANDING GEAR
Type Fixed Fixed
Shock Strut Type Combination Air-Oil Combination Air-Oil
Fluid Required (Struts, Hydraulic System
and Brakes) MIL-H-5606 MIL-H-5606
Strut Exposure (Exposure under static
load):
Nose 3.25 ±.25 in. 3.25 + .25 in.
Main 4.50 + .25 in. 4.50 + .25 in.
Wheel Tread 10.0 ft. 10.0ft.
Wheel Base 6 ft. 2.65 in. 6 ft. 2.65 in.
Nose Wheel Travel REFER TO SECTION VII REFER TO SECTION VII
TABLE VII-I TABLE VII-I
Wheel, Nose Cleveland 38501, 6:00 x 6 Cleveland 38501, 6:00 x 6
Wheel, Main Cleveland 40-28, 6:00 x 6 7 Cleveland40-28, 6:00 x 6 7
Cleveland 40-86, 6:00 x 6 8 Cleveland 40-86, 6:00 x 6 8
Brake Type Cleveland 30-18 7 Cleveland 30-18 7
Cleveland 30-55 8 Cleveland 30-55 8
Tires, Nose 6:00 x 6, 4 ply rating 6:00 x 6, 4 ply rating
Tires, Main 6:00 x 6, 4 ply rating 6:00 x 6, 4 ply rating
Tire Pressure, Nose 24 psi 24 psi
Tire Pressure, Main 24 psi 24 psi

ALL MODELS, CONTROL SURFACES

AND CABLE TENSIONS REFER TO SECTION V REFER TO SECTION V
TABLE V-I TABLE V-I
Refer to Grid 1C2for foot Notes:
Revised: 10 3 83 HANDLINGAND SERVICING

lB19
 PIPER CHEROKEE SERVICE MANUAL

TABLE II-I. LEADING PARTICULARS AND PRINCIPAL DIMENSIONS (cont)

MODEL PA-28-180 38 PA-28-235 39

ENGINE
Manufacturer Avco-Lycoming Avco-Lycoming
Model O-360-A3A or O-360-A4A O-540-B2B5,0-540-B1B5
or O-540-B4B5
FAA Type Certificate 286 295
Rated Horsepower 180 235
Rated Speed:
Full Throttle 180 @ 2700 RPM 235 @ 2575 RPM
Oil, SAE Number See Table II-IX See Table II-IX
Oil Sump Capacity 8 U.S. quarts 12 U.S. quarts
Fuel, Aviation Grade (Minimum Octane) 90/96 80/87
Fuel, Aviation Grade (Specified Octane) 90/96 80/87
Fuel, Aviation Grade (Alternate) See Note 37
Fuel Injector, Bendix
Magnetos, Scintilla:
Left S4LN-21 S6LN-21
Right S4LN-20 35 or S4LN-204 36 S6LN-20 2 or S6LN-204 3
Magneto Timing 25° BTC 25° BTC
Magneto Point Clearance 0.018 + 0.006 in. 0.018 ± 0.006 in.
Spark Plugs (Shielded):
Refer to the latest revision of Lycoming
Service Instruction No. 1042.
Firing Order 1-3-2-4 1-4-5-2-3-6

Starter:
Delco-Remy, 12 Volt 1109657or 1109511 1109657or 1109511
Prestolite, 12 Volt MZ4206 MZ4206
Alternator, Chrysler (35 AMP) 20 2098615or 2642996 2098615or 2642996
Voltage Regulator, Chrysler 2098613or 87-87102-2132 2098613or 87-87102-2132
Alternator, Chrysler (60 AMP) 30 2642997or 2642210 2642997or 2642210
Voltage Regulator, WICO X16300B X16300B
Overvoltage Relay, WICO X16799B 5 X16799B 6
Alternator, Prestolite (60 AMP) ALY-6422 31
Voltage Regulator, WICO X16300B
Fuel Pump Drive Plunger Plunger

I Refer to Grid IC2 for foot Notes:

Revised: 10 3 83 HANDLINGANDSERVICING

1B20
 PIPER CHEROKEE SERVICE MANUAL

TABLE II-I. LEADING PARTICULARS AND PRINCIPAL DIMENSIONS (cont)

MODEL PA-28-180 PA-28-235

ENGINE (cont)

PROPELLER

Fixed Pitch:
Manufacturer Sensenich McCauley or Sensenich
Model M76EMM 7 or M76EMMS 8 IP235PFA80 M80BMM

Diameter 76.0 in. 80.0 in. 80.0 in.

Diameter, Minimum 76.0 in. 78.5 in. 78.5 in.
Blade Angle 9 57 thru 60 in. - 48 in. 28 66 thru 71 in. 69 thru 71 in.

Constant Speed:
Manufacturer Hartzell
Hub, Model HC-C2YK-1BF
Blade, Model F8468A-4
Diameter, Minimum 80.0 in.
Blade Angle, Low Pitch 9 13.5° + 2 °
Blade Angle, High Pitch 9 27° + 2°
Governor Control Hartzell
Governor Model F-4-3

I Refer to Grid 1C2 for foot Notes:

Revised: 10 3 83 HANDLING ANDSERVICING

1B21
 PIPER CHEROKEE SERVICE MANUAL

TABLE II-I. LEADING PARTICULARS AND PRINCIPAL DIMENSIONS (cont)

MODEL PA-28-180 PA-28-235

FUEL SYSTEM

Inboard (Main Fuel Tanks Two Two

Capacity) (each) 25 U.S. gal. 25 U.S. gal.
Unusable Fuel (each) 0.125 16 or 0.82 U.S. gal. 15 0.125 16 or 0.82 U.S. gal. 15
Outboard (Tip) Fuel Tanks Two
Capacity (each) 17 U.S. gal.
Unusable Fuel (each) 0.125 16 or 0.11 U.S. gal. 15
Total Capacity 50 U.S. gal. 84 U.S. gal.
Total Unusable Fuel
Refer to Owner's Handbook, Pilot's
Information Manual or Flight Manual
for particular airplane.

LANDING GEAR

Type Fixed Fixed

Shock Strut Type Combination Air-Oil Combination Air-Oil
Fluid Required (Struts, Hydraulic System
and Brakes) MIL-H-5606 MIL-H-5606
Strut Exposure (Exposure under static
load):
Nose 3.25 + .25 in. 3.25 ±..25 in.
Main 4.50 .25 in. 4.50 ± .25 in.
Wheel Tread 10.0 ft. 10.0 ft.
Wheel Base 6 ft. 2.65 in. 17 or 6 ft. 6.9 in. 147 ft. 2.68 in. 17or 6 ft. 6.06 in. 14
Nose Wheel Travel REFER TO SECTION VII REFER TO SECTION VII
TABLE VII-I TABLE VII-I
Wheel, Nose Cleveland 38501, 6:00 x 6 Cleveland 38501, 6:00 x 6
Wheel, Main Cleveland 40-28, 6:00 x 6 7 Cleveland 40-58, 6:00 x 6 18
Cleveland 40-86, 6:00 x 6 8 Cleveland 40-86, 6:00 x 6 19
Brake Type Cleveland 30-18 ' Cleveland 30-34 18
Cleveland 30-55 8 Cleveland 30-55 9
Tires, Nose 6:00 x 6, 4 ply rating 6:00 x 6, 4 ply rating
Tires, Main 6:00 x 6, 4 ply rating 6:00 x 6, 6 ply rating
Tire Pressure, Nose 28-30 psi
Tire Pressure, Main 24 psi 35-40 psi

ALL MODELS, CONTROL SURFACES

AND CABLE TENSIONS REFER TO SECTION V REFER TO SECTION V
TABLE V-I TABLE V-I

I Refer to Grid IC2 for foot Notes:

Revised: 10 3 83 HANDLING AND SERVICING

1B22
 PIPER CHEROKEE SERVICE MANUAL

TABLE II-I. LEADING PARTICULARS AND PRINCIPAL DIMENSIONS (cont)

MODEL PA-28R- 180 PA-28R-200

ENGINE
Manufacturer Avco-Lycoming Avco-Lycoming
Model IO-360-B 1E IO-360-C1Cor IO-360-C1C64

FAA Type Certificate 1E10 1E10

Rated Horsepower 180 200
Rated Speed:
Full Throttle 180 @ 2700 RPM 200 @ 2700 RPM
Oil, SAE Number See Table II-IX See Table II-IX
Oil Sump Capacity 8 U.S. quarts 8 U.S. quarts
Fuel, Aviation Grade (Minimum Octane) 100/130 100/130
Fuel, Aviation Grade (Specified Octane) 100/130 100/130
Fuel, Aviation Grade (Alternate)
Fuel Injector, Bendix RSA-5AD1 RSA-5ADI
Magnetos, Scintilla:
Left S4LN- 1227 S4LN-1227
Right S4LN- 1209 S4LN-1209
Magneto Timing 25 ° BTC 20° BTC 41
Magneto Point Clearance 0.016 in. 0.016 in.
Spark Plugs (Shielded):
Refer to the latest revision of Lycoming
Service Instruction No. 1042.
Firing Order 1-3-2-4 1-3-2-4
Starter:
Prestolite, 12 Volt MZ4206 MZ4206 or MZ4218 40
Generator, Delco-Remy (35 AMP)
Voltage Regulator, Delco-Remy
Alternator, Chrysler (35 AMP) 20
Voltage Regulator, Chrysler
Alternator, Chrysler (60 AMP) 30 2642997or 2642210 2642997
Voltage Regulator, WICO X16300B X16300B
Overvoltage Relay, WICO X16799B X16799B
Alternator, Prestolite (60 AMP) ALY-6422 31
Voltage Regulator, WICO X16300B
Fuel Pump Drive Type JT Type JT

Refer to Grid 1C2 for foot Notes:

Revised: 103 83 HANDLINGANDSERVICING

1B23
 PIPER CHEROKEE SERVICE MANUAL

TABLE II-I. LEADING PARTICULARS AND PRINCIPAL DIMENSIONS (cont)

MODEL PA-28R-180 PA-28R-200

PROPELLER

Constant Speed:
Manufacturer Hartzell Hartzell or McCauley 40
Hub, Model HC-C2YK-IBF HC-C2YK-1B B2D34C213
Blade, Model F7666A-0 F7666A-2 90DHA-16
Diameter 76.0 in. 74.0 74.0
Diameter, Minimum 74.0 72.5 73.0
I Blade Angle, Low Pitch 9 14.30 14° ± 0.2° 13.0° + 0.2°
Blade Angle, High Pitch 9 30° 29° + 2° 29.8 ° + 0.5°
Governor Control Hartzell Hartzell Hartzell
Governor Model F-2-2 F-2-7 F-2-7 ( )
F-2-7

Refer to Grid 1C2 for foot Notes:

Revised: 4 23 84 HANDLINGANDSERVICING

1B24
 PIPER CHEROKEE SERVICE MANUAL

TABLE II-I. LEADING PARTICULARS AND PRINCIPAL DIMENSIONS (cont)

MODEL PA-28R-180 PA-28R-200

FUEL SYSTEM
Inboard (Main Fuel Tanks Two Two
Capacity) (each) 25 U.S. gal. 25 U.S. gal.
Unusable Fuel (each) 0.125 U.S. gal. 0.82 U.S. gal.
Total Capacity 50 U.S. gal. 50 U.S. gal.
Total Unusable Fuel
Refer to Owner's Handbook, Pilot's
Information Manual or Flight Manual
for particular airplane.

LANDING GEAR
Type Hydraulically Retractable Hydraulically Retractable
Shock Strut Type Combination Air-Oil Combination Air-Oil
Fluid Required (Struts, Hydraulic System
and Brakes) MIL-H-5606 MIL-H-5606
Strut Exposure (Exposure under static
load):
Nose 2.75 ± .25 in. 2.75 + .25 in.
Main 2.0 ± .25 in. 2.0 .25 in.
Wheel Tread 10 ft. 5.72 in. 10 ft. 5.72 in.
Wheel Base 7 ft. 5.382 in. 7 ft. 5.4 in. 17or 7 ft. 10.6 in. 14
Nose Wheel Travel REFER TO SECTION VII REFER TO SECTION VII
TABLE VII-I TABLE VII-I
Wheel, Nose Cleveland 40-77, 5:00 x 5 Cleveland 40-77, 5:00 x 5
Wheel, Main Cleveland 40-84, 6:00 x 6 Cleveland 40-84, 6:00 x 6
Brake Type Cleveland 30-41 Cleveland 30-41
Tires, Nose 5:00 x 5, 4 ply rating 5:00 x 5, 4 ply rating
Tires, Main 6:00 x 6, 4 ply rating 6:00 x 6, 4 ply rating
Tire Pressure, Nose 30 psi 30 psi
Tire Pressure, Main 27 psi 27 psi

ALL MODELS, CONTROL SURFACES

AND CABLE TENSIONS REFER TO SECTION V REFER TO SECTION V
TABLE V-I TABLE V-I

I Refer to Grid 1C2 for foot Notes:

Revised: 10 3 83 HANDLINGAND SERVICING

1C1
 PIPER CHEROKEE SERVICE MANUAL

TABLE II-II. CONSUMABLE MATERIALS

Material Specification or Brand Name Manufacturer

Rain Repellant REPCON UNELKO Corporation

FSCM 50159 727 E. 110th Street
Chicago Illinois 60628

Teflon Tape .003 x .50 wide -1 Minesota Mining & Manufacturing Co.
3M Center
St. Paul, Minesota 55101

Teflon Tape .003 x .50 wide -l Shamban W.S. & Company

713 Mitchell Road
Newbury Park, California 91320

Teflon Tape .003 x .25 wide -2 Johnson & Johnson Inc.

Permacel Division
501 George Street
New Brunswick. N.J. 08903

3-M Co.
Adhesive. 3MEC 1300. C Adhesive Coatings and Sealers Div.
Door Snubber Scotch Grip 2210 3-M Center
St. Paul, Minnesota 55101
PROCO Adhesive 6205-1 Protective Coatings, Inc.
807 N. Fremont Ave.
Tampa. Fla.

Reissued: 1/15/81 HANDLING AND SERVICING

1C3
 PIPER CHEROKEE SERVICE MANUAL

1689

Figure 2-13. Station Reference Lines,

PA-28-140and PA-28-150-160-180,Serial Nos. 28-1 to 28-1760 incl.
PA-28-140Flite Liner, Serial Nos. 28-7125174 and up

Reissued: 1/15/81 HANDLING AND SERVICING

1C4
 PIPER CHEROKEE SERVICE MANUAL

1761

*1974 MODELS AND UP

Figure 2-14. Station Reference Lines,

PA-28-140, SerialNos. 28-7225001 and up

Reissued: 1/15/81 HANDLING AND SERVICING

1C5
 PIPER CHEROKEE SERVICE MANUAL

1798

Figure 2-15. Station Reference Lines,

PA-28-150-160-180,Serial Nos. 28-1761 to 28-4377 incl.

Reissued: 1/15/81 HANDLINGAND SERVICING

1C6
 PIPER CHEROKEE SERVICE MANUAL

C331

Figure 2-16. Station Reference Lines,

PA-28-180, SerialNos. 28-4378 to 28-7105244 incl.

Reissued:1/15/81 HANDLING AND SERVICING

1C7
 PIPER CHEROKEE SERVICE MANUAL

1710

Figure 2-17. Station Reference Lines,

PA-28-180, SerialNos. 28-7205001 to 28-7205328 incl.

Reissued: 1/15/81 HANDLINGAND SERVICING

1C8
 PIPER CHEROKEE SERVICE MANUAL

1754

Figure 2-19. Station Reference Lines,

PA-28-235,Serial Nos. 28-10000 to 28-11039 incl.

Reissued: 1/15/81 HANDLINGAND SERVICING

1C10
 PIPER CHEROKEE SERVICE MANUAL

1906

Figure 2-20. Station Reference Lines,

PA-28-235,Serial Nos. 28-11040 to 28-7110042 incl.

Reissued: 1/15/81 HANDLING AND SERVICING

1C11
 PIPER CHEROKEE SERVICE MANUAL

1908

Figure 2-21. Station Reference Lines,

PA-28-235,Serial Nos. 28-7210001 to 28-7210033 incl.

Reissued: 1/15/81 HANDLINGAND SERVICING

1C12
 PIPER CHEROKEE SERVICE MANUAL

1731

Figure 2-23. Station Reference Lines,

PA-28R-180, SerialNos. 28-30005 to 28-7130019 incl.
PA-28R-200,SerialNos. 28-30482 to 28-7135238 incl.

Reissued: 1/15/81 HANDLINGAND SERVICING

1C14
 PIPER CHEROKEE SERVICE MANUAL

1760

Figure 2-24. Station Reference Lines,

PA-28R-200,SerialNos. 28-7235001 and up

Reissued: 1/15/81
HANDLING AND SERVICING

1C15
 PIPER CHEROKEE SERVICE MANUAL

1. TIP, STABILATOR 1794 16. PANEL, TORQUE TUBE AND

2. TIP, RUDDER CONTROL CABLES & BATTERY
3. FAIRING, FIN 17. PLATE, CONTROL CABLES
4. TAIL CONE, CONTROL CABLE, MIDDLE
AND TRIM SCREW 2 18. PLATE, AILERON AND
5. TIP, WING STABILATOR CONTROL
6. COVER, BELLCRANK AND CABLE FORWARD
CONTROL CABLES 19. COVERS, AILERON AND
7. FAIRING, MAIN GEAR STRUT STABILATOR CONTROL
ASSEMBLY CABLE
8. FAIRING, FLAP TORQUE TUBE 20. PANEL, AFT AREA OF
AND AILERON CABLES FUSELAGE
9. CAP, FUEL TANK ASSEMBLY 21. PLATE, CONTROL CABLES
10. CAP, STRUT FILLER AND PULLEYS REAR
11. FAIRING, FUEL LINES 22. COVER, FLAP CONTROL
12. COVER, FUEL LINES AND
SPAR ATTACHMENT BOLTS
13. SPINNER, PROPELLER
14. COWL ASSEMBLY, ENGINE
15. COWL ASSEMBLY, ENGINE
PA-28- 140 SERIAL NO'S
26-7225001 & UP

Figure 2-25. Access Plates and Panels

PA-28-140and Flite Liner
PA-28-140,Serial Nos. 28-7225001 and up as noted

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 PIPER CHEROKEE SERVICE MANUAL

C332
1
UPPER SURFACE
LOWERSURFACE

13-

1. TIP, STABILATOR
2. TIP, RUDDER
3. FAIRING, FIN
4. TAIL CONE, CONTROL CABLE AND TRIM SCREW
5. TIP, WING 15
6. COVER, BELLCRANK AND CONTROL CABLES
7. FAIRING, MAIN GEAR STRUT ASSEMBLY 16
8. FAIRING, FLAP TORQUE TUBE AND AILERON CABLES
9. CAP, FUEL TANK ASSEMBLY
10. CAP, STRUT FILLER
11. FAIRING, FUEL LINES 21
12. COVER, FUEL LINES AND SPAR ATTACHMENT BOLTS
13. DOOR, OIL FILLER 17
14. COWL ASSEMBLY, ENGINE
15. SPINNER, PROPELLER
16. SEAT, TOROUE TUBE AND CONTROL CABLES 18
17. PLATE, CONTROL CABLES MIDDLE
18. PLATE, AILERON AND STABILATOR CONTROL CABLE FORWARD
19. COVERS, AILERON AND STABILATOR CONTROL CABLE
20. PANEL, BATTERY AND AFT AREA OF FUSELAGE
21. PLATE, CONTROL CABLES AND PULLEYS REAR
22. COVER, FLAP CONTROL

Figure2-26. Access Plates and Panels

PA-28-150-160-180

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 PIPER CHEROKEE SERVICE MANUAL

UPPERSURFACE 1 2 1

LOWER SURFACE
1793

6 6

14

1. TIP, STABILATOR 16
2. TIP, RUDDER
3. FAIRING, FIN
4. TAIL CONE, CONTROL CABLES AND TRIM SCREW
5. COVER, TANK ATTACHMENT FITTINGS
6. COVER, BELLCRANK AND CONTROL CABLES
7. FAIRING, MAIN GEAR STRUT ASSEMBLY 17
8. FAIRING, FLAP TORQUE TUBE AND AILERON CABLES
9. FUEL SELECTOR AND DRAIN VALVE ASSEMBLY
10. ELECTRIC FUEL PUMP ASSEMBLY
11. COVER, FUEL LINES AND SPAR ATTACHMENT BOLTS
12. FAIRING, FUEL LINES
13. CAP, STRUT FILLER
14. CAP, FUEL TANK ASSEMBLY
15. FUEL TANK ASSEMBLY, WING TIP
16. DOOR, OIL FILLER
17. SPINNER, PROPELLER
18. COWL ASSEMBLY, ENGINE
19. SEAT, TORQUE TUBE AND CONTROL CABLES
20. PLATE, CONTROL CABLES AND PULLEYS REAR
21. COVER, FLAP AND TRIM CONTROL
22. COVERS, AILERON AND STABILATOR CONTROL CABLE
23. PANEL, BATTERY & AFT AREA OF FUSELAGE
24. PLATE, CONTROL CABLES MIDDLE
25. PLATE, AILERON AND STABILATOR CONTROL CABLE FORWARD

Figure 2-27. Access Plates and Panels

PA-28-235

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 PIPER CHEROKEE SERVICE MANUAL

UPPERSURFACE
LOWERSURFACE

1752

4
3-

5 6 7 8 8 7 6 5

10

1. TIP, STABILATOR
2. TIP, RUDDER
3. FAIRING, FIN
4. TAIL CONE, CONTROL CABLES & TRIM SCREW 15
5. TIP, WING
6. COVER, BELLCRANK & CONTROL CABLES
7. CAP, FUEL TANK ASSEMBLY
8. COVER, GEAR ATTACHMENT FITTING
9. FAIRING, FLAP TORQUE TUBE AND AILERON CABLES
10. DOOR, MAIN GEAR
11. FAIRING, FUEL LINES
12. COVER, FUEL LINES AND SPAR ATTACHMENT BOLTS
13. DOOR, OIL FILLER
14. COWL ASSEMBLY, ENGINE
15. SPINNER, PROPELLER
16. PLATE, AILERON AND STABILATOR CONTROL CABLE FORWARD
17. PLATE, CONTROL CABLES MIDDLE
18. SEAT, TORQUE TUBE AND CONTROL CABLES
19. COVER, FLAP AND TRIM CONTROL
20. PLATE, CONTROL CABLES AND PULLEYS REAR
21. COVERS, AILERON AND STABILATOR CONTROL CABLE
22. PANEL, HYDRAULIC PUMP, BATTERY & AFT AREA OF FUSELAGE

Figure 2-28. Access Plates and Panels

PA-28R

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 PIPER CHEROKEE SERVICE MANUAL

2-5. SERIAL NUMBER PLATE. The serial number plate is located on the left side of the
fuselage near the leading edge of the stabilator. The serial number should always be used
when referring to the airplane on service or warranty matters.

2-6. ACCESS AND INSPECTION PROVISIONS. The access and inspection provisions
for the airplane are shown in Figures 2-25 thru 2-28. The component to be serviced or in-
spected through each openingis identified in the illustration. All access plates and panels are
secured by either metal fasteners or screws.
CAUTION
Before entering the aft section of the fuselage, be sure the
airplane is supported at the tail skid.
To enter the aft section of the fuselage,open the baggage compartment door and remove
the access panel.

2-7. TOOLS AND TEST EQUIPMENT. Because of the simplicity and easy accessibility
of components, few special tools outside normal shop tools will be required. Tools that are
required are listed in the back of the PA-28 Parts Catalog and may be fabricated to dimensions
given in the back of the section that pertains to a particular component.

2-8. TORQUE REQUIREMENTS. The torque values given in Table II-III are derived
from oil-free, cadmium-plated threads and, unless otherwise noted, are recommended for all
air-frame installation procedures where torquing is required. Engine torque valuesare given
in the latest revision of Avco-LycomingService BulletinNo. 268, and propeller torque values
are given in Section VIII or VIIIA.

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 PIPER CHEROKEE SERVICE MANUAL

2-8a. TORQUE WRENCHES.

Torque wrenches should be checked daily and calibrated by means of weights and a measured lever arm to
make sure that inaccuracies are not present. Checking one torque wrench against another is not sufficient and
is not recommended. Some wrenches are quite sensitive as to the way they are supported during a tightening
operation. Any instructions furnished by the manufacturer must be followed explicitly.
When it is necessary to use a special extension or adapter wrench together with a torque wrench, a simple
mathematical equation must be worked out to arrive at the correct torque reading. Following is the formula to
be used: (Refer to Figure 2-30.)
T = Torque desired at the part.
A = Basic lever length from center of wrench shank to center of handle or stamped on wrench or listed for
that model wrench.
B = Length of adapter extension, center of bolt to center of shank.
C = Scale reading needed to obtain desired torque (T).

The formula: C= A xT
A +B
A+B
EXAMPLE

A bolt requires 30 foot-pounds and a 3 inch adapter (one-quarter of

a foot or .25) is needed to get at it. You want to know what scale
reading it will take on a one-foot lever arm wrench to obtain the 30
foot-pounds at.the bolt.

C = 30 or C 30 = 24 ft. -lbs.
I + .25 .1.25
Remember, the 3 inch adapter must be projecting 3 inches straight
along the wrench axis. In general, avoid all complex assemblages or
adapters and extensions of flex joints.
A933

Figure 2-30. Torque Wrench Formula

Revised: 8/3/81 HANDLING AND SERVICING

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 PIPER CHEROKEE SERVICE MANUAL

TABLE II-III RECOMMENDED NUT TORQUES (Inch-Pounds)

TORQUES:The importanceof correct applicationcan not be BOLTS

overemphasized. Undertorque canresultin unnecessary wearof nuts Steel Tension
and bolts as well as the parts they are holdingtogether.When
insufficientpressures are applied,unevenloadswill be transmitted AN 3 thru AN 20
throughoutthe assemblywhich may result in excessive wear or AN 42 thru AN 49
AN 73thru AN 81
premature failuredueto fatigue.Overtorque canbe equallydamaging AN 173 thru AN 186
because of failureof a boltor nut from overstressing
thethreaded areas. MS 20033 thru MS 20046
Therearea fewsimple,but veryimportant,procedures that shouldbe MS 20073
followedto assure thatthe correcttorqueisapplied: MS 20074
1. Calibratethe torquewrenchperiodicallyto assureaccuracy; AN 509 NK9
andrecheck frequently. MS 24694
AN 525 NK525
2. Ascertainthat the bolt and nut threadsare cleanand dry MS 27039
(unlessotherwise specified by themanufacturer).
3. Run nut downto nearcontactwith the washeror bearing NUTS
surfaceandcheck"friction dragtorque"requiredto turnthe
Steel Tension Steel Shear
nut.
4. Add the friction drag torque to the desiredtorque AN 310 AN 320
AN 315 AN 364
recommended by the manufacturer,or obtaindesiredtorque AN 363 NAS 1022
as shownin Chart9103. Thisis referredto as final torque AN 365 MS 17826
which shouldregisteron the indicatoror the settingfor a NAS 1021 MS 20364
snapover typewrench. MS 17825
MS 21045
MS 20365
NOTE
MS 20500
NAS 679
For more detailson torquing, refer to FAA Manual
AC 43.13-1.
COARSE THREAD SERIES

Nut-bolt Torque Limits Torque Limits

FRICTIONDRAG TORQUES size in-lbs in-lbs
COARSEAND FINE

Min. Max. Min. Max

BOLT SIZE FRICTIONDRAG TORQUE (IN.-LBS.)

8 -32 12 15 7 9
10 18 10 -24 20 25 12 15
1/4-20 40 50 25 30
5/16-18 80 90 48 55
1/4 30 3/8-16 160 185 95 110
7/16-14 235 255 140 155
1/2-13 400 480 240 290
5/16 60 9/16-12 500 700 300 420
5/8-11 700 900 420 540
3/4-10 1.150 1.600 700 950
o 3/8 80 7/8- 9 2,200 3.000 1.300 1,800
1 -8 3.700 5.000 2.200 3.000
1./8-8 5.500 6.500 3.300 4.000
7/16 100 1-1/4-8 6.500 8.000 4,000 5.000
.

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 PIPER CHEROKEE SERVICE MANUAL

TABLE II-111. RECOMMENDED NUT TORQUES (Inch-Pounds) (cont.)

FINE THREAD SERIES

BOLTS BOLTS BOLTS

Steel Tension Steel Tension Aluminum

AN 3 thru AN 20 MS 20004 thru MS 20024 AN 3DD thru AN 20DD

AN 42 thru AN 49 NAS 144 thru NAS 158 AN 173DD thru AN 186DD
AN 73 thru AN 81 NAS 333 thru NAS 340 AN 509DD
AN 173 thru AN 186 NAS 583 thru NAS 590 AN 525D
MS 20033 thru MS 20046 NAS 624 thru NAS 644 MS 27039D
MS 20073 NAS 1303 thru NAS 1320 MS 2469400
MS 20074 NAS 172
AN 509 NK9 NAS 174
MS 24694 NAS 517 Steel shearbolt
AN 525 NK525
MS 27039 NAS 464

NUTS NUTS NUTS

Steel Tension Steel Sheer Steel Tension Steel Shear Alum. Tension Alum. Shear

AN 310 AN 320 AN 310 AN 320 AN 365D AN 320D

AN 315 AN 364 AN 315 AN 364 AN 310D AN 364D
AN 363 NAS 1022 AN 363 NAS 1022 NAS 1021d NAS 1022d
AN 365 MS 17826 AN 365 MS 17826
NAS 1021 MS 20364 MS 17825 MS 20364
MS 17825 MS 20365
MS 21045 MS 21045
MS 20365 NAS 1021
MS 20600 NAS 679
NAS 679 NAS 1291

Nut-bolt Torque Limits Torque Limits Torque Limits Torque Limits Torque Limits Torque Limits
size in-lbs in-lbs in-lbs in-lbs in-lbs in-lbs

Min. Max. Min. Max. Min. Max. Min. Max. Min. Max. Min. Max.

-36 12 15 7 9 5 10 3 6
10 -32 20 25 12 15 25 30 15 20 10 15 5 10
1/4-28 50 70 30 40 80 100 50 60 30 45 15 30
5/16-24 100 140 60 85 120 145 70 90 40 65 25 40
3/8-24 160 190 95 110 200 250 120 150 75 110 45 70
7/16-20 450 500 270 300 520 630 300 400 180 280 110 170
1/2-20 480 690 290 410 770 950 450 550 280 410 160 260
9/16-18 800 1.000 480 600 1,100 1,300 650 800 380 580 230 360
5/8-18 1.100 1.300 660 780 1,250 1,550 750 950 550 670 270 420
3/4-16 2.300 2,500 1.300 1,500 2,650 3,200 1,600 1,900 950 1,250 560 880
7/8-14 2,500 3,000 1.500 1.800 3,550 4,350 2,100 2,690 1,250 1,900 750 1,200
1 -14 3,700 4,500 2,200 3.300 4,500 5,500 2,700 3,300 1,600 2,400 ,950 1,500
1-1/8-12 5,000 7,000 3,000 4,200 6,000 7,300 3,600 4,400 2,100 3,200 1.250 2,000
1-1/4-12 9,000 11.000 5,400 6,600 11.000 13,400 6,600 8,000 3,900 5,600 2,300 3,650

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 PIPER CHEROKEESERVICEMANUAL

2-9. WALKWAY, HANDHOLD AND STEP. The walkwayis made of a non-skidcom-

pound appliedto paperand bondedto the wing surface.A fixed handholdis locatedon the
rightside of the fuselagenearthe rearwindow.A step is availableas optionalequipmentand
is installedjust aft of the trailingedge of the right flap.

TABLE II-V. CONVERSION TABLES

1. These charts contain the various conversion data that may be useful when figuring capacities. lengths.
temperatures. and various weights and measures from the English systemvaluesto the metricsystem
values or back again.

2. The English system is in use by England and the United States. All other countries use the metric
system.

3. Procedurefor ConvertingInches to Millimeters.(Refer to Table II-V.)

A. Example: Convert 1.5 inches to millimeters.

(1) Read down inches column to 1. inches.

(2) Read across top inch column to 0.5.
(3) Read down and across to find millimeters (1.5 inches is 38.10 millimeters).

4. Procedure for Converting Fahrenheit (°F) and Celsius (°C) (Centigrade) Temperature. (Refe:
Table II-V.)
A. Read number in middle column. if in degrees Celsius (°C). read Fahrenheit equivalent in
right-hand column. If in degrees Fahrenheit (°F). read Celsius equivalent in left-hand column.

(1) 70F = 21.1°C.

(2) 30°C = 86.0°F.

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 PIPER CHEROKEE SERVICE MANUAL

TABLE II-V. CONVERSION TABLES (cont)

MULTIPLY BY TO OBTAIN MULTIPLY BY TO OBTAIN

CENTIMETERS 0.3937 IN. KILOGRAMS 2.205 LB.

0.03281 FT. 35.27 OZ.
CU. CENTIMETERS 1000 GRAMS
0.001 LITERS
0.06102 CU. IN. LITERS 1000 CU. CM.
0.0002642 U.S. GAL. 61.03 CU. IN.
CU. FT. 28.320 CU. CM. 0.03532 CU. FT.
1.728 CU. IN. 0.2642 U.S. GAL
7.481 U.S. GAL. 0.22 IMPERIAL GAL.
28.32 1.057 QUARTS
LITERS
CU. IN. METERS 39.37 IN.
16.39 CU. CM.
0.01639 LITERS 3.281 FT.
0.004329 U.S. GAL. 1000 MM.
0.01732 QUARTS METER-KILOGRAM 7.233 FT.-LB
CU. METERS 1000000 9.807 JOULES
CU. CM.
35.314 CU. FT. OUNCES. AVDP 0.0625 LB.. AVDP
61.023 CU. IN. 28.35 GRAMS
264.17 GAL. 437.5 GRAINS
999.97 LITERS
OUNCES. FLUID 29.57 CU. CM
FEET 0.3048 METERS 1.805 CU. IN
12.000 MILS.
304.8 MM. LB.. AVDP 453.6 GRAMS
0.3333 YARDS 7000 GRAINS
16.0 OUNCES
FT.-LB. 0.1383 M-KG
0.001285 BTU SQUARE INCH 6.4516 SQ. CM.
0.000000376 KW-HR POUND PER 0.0703 KG-CM
FLUID OZ. 8 DRAM SQUARE INCH SQUARED
29.6 CU. CM. (PSI)

GAL.. IMPERIAL 277.4 CU. IN. STATUTE MILE 1.609 KILOMETER

1.201 U.S. GAL. 0.8684 NAUTICAL MILE
4.546 LITERS NAUTICAL MILE 1.151 STATUTE
GAL.. U.S. DRY 268.8 CU. IN. MILE
0.1556 CU. FT. QUART .9463 LITER
1.164 U.S. GAL.. LIQ.
4.405 LITERS MILLIMETER 1000 MICRON
GAL.. U.S. LIQ. 231.0 CU. IN. MICRON 0.001 MILLIMETER
0.1337 CU. FT. 0.000039 INCH
3.785 LITERS
INCH 11.521 METER
0.8327 IMPERIAL GAL.
POUNDS GRAMS
128 FLUID OZ.
IN. INCH 0.72 METER
2.540 CM.
OUNCES GRAMS
.08333 FT.
POUNDS 0.453 KILOGRAMS
JOULES 0.000948 BTU
0.7376 FT.-LB.

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 PIPER CHEROKEE SERVICE MANUAL

TABLE II-V. CONVERSION TABLES (cont)

C328

INCHES TO MILLIMETER
INCHES 0.0000 0.0001 0.0002 0.0003 0.0004 0.0005 0.0006 0.0007 0.0008 0.0009
I MILLIMETER
0.000 0.0025 0.0050 0.0076 0.0101 0.0127 0.0152 0.0177 0.0203 0.0228
0.001 0.0254 0.0279 0.0304 0.0330 0.0355 0.0381 0.0406 0.0431 0.0457 0.0482
0.002 0.0508 0.0533 0.0558 0.0584 0.0609 0.0635 0.0660 0.0685 0.0711 0.0736
0.003 0.0762 0.0787 0.0812 0.0838 0.0863 0.0889 0.0914 0.0939 0.0965 0.0990
0.004 0.1016 0.1041 0.1066 0.1092 0.1117 0.1143 0.1168 0.1193 0.1219 0.1244
0.005 0.1270 0.1295 0.1320 0.1346 0.1371 0.1397 0.1422 0.1447 0.1473 0.1498
0.006 0.1524 0.1549 0.1574 0.1600 0.1625 0.1651 0.1676 0.1701 0.1727 0.1752
0.007 0.1778 0.1803 0.1828 0.1854 0.1879 0.1905 0.1930 0.1955 0.1981 0.2006
0.008 0.2032 0.2057 0.2082 0.2108 0.2133 0.2159 0.2184 0.2209 0.2235 0.2260
0.009 0.2286 0.2311 0.2336 0.2362 0.2387 0.2413 0.2438 0.2463 0.2489 0.2514
INCHES 0.000 0.001 0.002 0.003 0.004 0.005 0.006 0.007 0.008 0.009
MILLIMETER
0.00 0.025 0.050 0.076 0.101 0.127 0.152 0.177 0.203 0.228
0.01 0.254 0.279 0.304 0.330 0.355 0.381 0.406 0.431 0.457 0.482
0.02 0.508 0.533 0.558 0.584 0.609 0.635 0.660 0.685 0.711 0.736
0.03 0.762 0.787 0.812 0.838 0.863 0.889 0.914 0.939 0.965 0.990
0.04 1.016 1.041 1.066 1.092 1.117 1.143 1.168 1.193 1.219 1.244
0.05 1.270 1.295 1.320 1.346 1.371 1.397 1.422 1.447 1.473 1.498
0.06 1.524 1.549 1.574 1.600 1.625 1.651 1.676 1.701 1.727 1.752
0.07 1.778 1.803 1.828 1.854 1.879 1.905 1.930 1.955 1.981 2.006
0.08 2.032 2.057 2.082 2.108 2.133 2.159 2.184 2.209 2.235 2.260
0.09 2.286 2.311 2.336 2.362 2.387 2.413 2.438 2.463 2.489 2.514
INCHES 0.00 0.01 0.02 0.03 0.04 0.05 0.06 0.07 0.08 0.09
MILLIMETER
0.0 0.254 0.508 0.762 0.016 1.270 1.524 1.778 2.032 2.286
0.1 2.540 2.794 3.048 3.302 3.556 3.810 4.064 4.318 4.572 4.826
0.2 5.080 5.334 5.588 5.842 6.096 6.350 6.604 6.858 7.112 7.366
0.3 7.620 7.874 8.128 8.382 8.636 8.890 9.144 9.398 9.652 9.906
0.4 10.160 10.414 10.668 10.922 11.176 11.430 11.684 11.938 12.192 12.446
0.5 12.700 12.954 13.208 13.462 13.716 13.970 14.224 14.478 14.732 14.986
0.6 15.240 15.494 15.748 16.002 16.256 16.510 16.764 17.018 17.272 17.526
0.7 17.780 18.034 18.288 18.542 18.796 19.050 19.304 19.558 19.812 20.066
0.8 20.320 20.574 20.828 21.082 21.336 21.590 21.844 22.098 22.352 22.606
0.9 22.860 23.114 23.368 23.622 23.876 24.130 24.384 24.638 24.892 25.146
INCHES 0.00 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 09
I MILLIMETER
0. 2.54 5.08 7.62 10.16 12.70 15.24 17.78 20.32 22.86
I. 25.40 27.94 30.48 33.02 35.56 38.10 40.64 43.18 45.72 48.26
2. 50.80 53.34 55.88 58.42 60.96 63.50 66.04 68.58 71.12 73.66
3. 76.20 78.74 81.28 83.82 86.36 88.90 91.44 93.98 96.52 99.06
4. 101.60 104.14 106.68 109.22 111.76 114.30 116.84 119.38 121.92 12446
5. 127.00 129.54 132.08 134.62 137.16 139.70 142.24 144.78 147.32 149.86
6. 152.40 154.94 157.48 160.02 162.56 165.10 167.64 170.18 172.72 175.26
7. 177.80 180.34 182.88 185.42 187.96 190.50 193.04 195.58 198.12 200 66
8. 203.20 205.74 208.28 210.82 213.36 215.90 218.44 220.98 223.52 226.06
9. 228.60 231.14 233.68 236.22 238.76 241.30 243.84 246.38 248.92 251.46

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 PIPER CHEROKEE SERVICE MANUAL

TABLE II-V. CONVERSION TABLES (cont)

CENTIGRADE-FAHRENHEIT CONVERSION TABLE

Example: To convert 20°C. to Fahrenheit, find 20 in the center

column headed (F-C); then read 68.0°F. in the column (F) to the
right. To convert 20° F. to Centigrade; find 20 in the center column
and read -6.67°C. in the (C) column to the left.

C F-C F C F-C F

-56.7 -70 -94.0 104.44 220 428.0

-51.1 -60 -76.0 110.00 230 446.0
-45.6 -50 -58.0 115.56 240 464.0
-40.0 -40 -40.0 121.11 250 482.0
-34.0 -30 -22.0 126.67 260 500.0
-38.9 -20 -4.0 132.22 270 518.0
-23.3 -10 14.0 137.78 280 536.0
-17.8 0 32.0 143.33 290 554.0
-12.22 10 50.0 148.89 300 572.0
-6.67 20 68.0 154.44 310 590.0
-1.11 30 86.0 160.00 320 608.0
4.44 40 104.0 165.56 330 626.0
10.00 50 122.0 171.11 340 644.0
15.56 60 140.0 176.67 350 662.0
21.11 70 158.0 182.22 360 680.0
26.67 80 176.0 187.78 370 698.0
32.22 90 194.0 193.33 380 716.0
27.78 100 212.0 198.89 390 734.0
43.33 110 230.0 204.44 400 752.0
38.89 120 248.0 210.00 410 770.0
54.44 130 266.0 215.56 420 788.0
60.00 140 284.0 221.11 430 806.0
65.56 150 302.0 226.67 440 824.0
71.00 160 320.0 232.22 450 842.0
76.67 170 338.0 257.78 460 860.0
82.22 180 356.0 243.33 470 878.0
87.78 190 374.0 248.89 480 896.0
93.33 200 392.0 254.44 490 914.0
98.89 210 410.0 260.00 500 932.0

I
Reissued: 1/15/81 HANDLING AND SERVICING

1D4
 VI. DECIMAL MILLIMETER
N o o o
0000
0000 o

Equivalents of Drill Sizes 1/2"

From to No. 80

0
LL
z

S
 PIPER CHEROKEE SERVICE MANUAL

TABLE II-VII. MAXIMUM DISTANCE BETWEENSUPPORTS FOR FLUID TUBING

TUBEOD DISTANCEBETWEENSUPPORTS(IN.)
(IN.)
ALUMINUM
ALLOY STEEL

1/8 9-1/2 11-1/2

3/16 12 14
1/4 13-1/2 ]6
5/16 15 18
3/8 16-1/2 20
1/2 19 23
5/8 22 25-1/2
3/4 24 27-1/2
1 26-1/2 30

TABLE II-VIII. HOSE CLAMP TIGHTENING. (INITIAL INSTALLATION)

Types of clamps
Types of hose
Worm screw type All other types

Self sealing Finger-tight-plus Finger-tight-plus

2 complete turns 2 1/2 complete turns

All other hose Finger-tight-plus Finger-tight-plus

1/4 complete Turns 2 complete turns

If clamps do not seal at specified tightening. examine hose connection and replace parts as
necessa ry.

Reissued:1/15/81 HANDLING AND SERVICING

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 PIPER CHEROKEE SERVICE MANUAL

8362
TWO COTTON BRAIDS - IMPREGNATED
WITH SYNTHETIC COMPOUND YELLOW NUMERALS.
LETTERSAND STRIPE

NON-SELF-SEALING
YELLOW SINGLE WIRE BRAID -
D. AROMATIC RESISTANTHOSE
SYNTHETICINNER TU BE

A. FLAME AND AROMATIC RESISTANTHOSE

WHITE NUMEERALS, LETTERSAND STRIPE RED

B. (VIEW SHOWS OPPOSITESIDES OF HOSE)

NON-SELF-SEALING AROMATIC AND HEAT-RESISTANTHOSE

RED NUMERALS LETTERSAND STRIPE

E. SELF-SEALING AROMATIC
RED NUMERALS AND LETTERS RESISTANTHOSE
C. FLAME, AROMATIC AND OIL RESISTANTHOSE

MARKINGS
HOSEIDENTIFICATION

BROWN ORANGE ORANGE ORANGE GRAY GRAY

ELECTRICAL COMPRESSED INSTRUMENT

CONDUIT GAS AIR

GREEN RED ORANGE BLUE YELLOW

BREATHING FUEL PNEUMATIC LUBRICATION AIR

OXGYEN CONDITION

RED

FLUID LINE IDENTIFICATION USING TAPE AND DECALS

Figure 2-29. Identification of Aircraft Fluid Lines

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8362

DRIFT PIN 4.

SMALL
CENTERDRILL 6.

3.

Figure 2-31. Removal of Cherrylock Rivets

2-10. REMOVALOF CHERRYLOCKRIVETS.

To remove cherrylock rivet:

1. File head flat.
2. Centerpunch rivet head.
3. In thick material, remove the lock by driving out the rivet stem using. a tapered steel drift pin. (See
View 1.)

- NOTE -

Do not drill completely through the rivet sleeve to remove a rivet, as

this will tend to enlarge the hole.

4. In thin material, use a small center drill to provide a guide for a larger drill on top of the rivet stem.
and the tapered position of the stem be drilled away to destroy the lock.
5. Remove the remainder of the locking collar out of the rivet head by prying it loose with the drift pin.
(See View 3.)
6. Drill nearly through the head of the rivet. using a drill the same site as the rivet shank. (See View4.)
7. Pry off the rivet head using the drift pin. (See View 5.)
8. Drive out the remaining shank with a pin having the same diameter as the rivet shank. (See View6.)

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949

947

Figure 2-32. Jacking Arrangement

2-11. GROUNDHANDLING.
2-12. INTRODUCTION TO GROUND HANDLING. This includes jacking, weighing,
leveling,mooring, parking, towing and taxiing. Handling the airplane in the manner described
in the following paragraphs will minimize damage to the airplane and its equipment.
CAUTION
When moving airplane forward by hand avoid pushing on the
trailing edge of the ailerons for this will result in an out of
trim condition.

2-13. JACKING. Jacking the airplane is necessary to service the landing gear and to
perform other service operations. Proceed as follows:
a. Placejacks under jack pads on the front wing spar. (Refer to Figure 2-32.)
b. Attach the tail support to the tail skid. Place approximately 250 pounds of ballast
on the base of the tail support to hold down the tail.
CAUTION
Be sure to apply sufficient tail support ballast; otherwise the
airplane will tip forward.

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948

947

Figure 2-33. Weighing Airplane

NOTE

A jacking point on the PA-28R airplanes is also pro-

vided on the underside of the fuselage directly behind
the nose gear actuating cylinder. This may be used
along with the wing jack points to raise the airplane,
or alone it may be used to raise the front end.

c. Raise the jacks until all three wheels are clear of the surface.

2-14. WEIGHING. (Refer to Figure 2-33.) For weighing purposes, place the airplane on
scales as follows:
a. Position a scale and ramp in front of each of the three wheels.
b. Secure the scales from rolling forward and tow the airplane up onto the
scales. (Refer to Paragraph 2-19.)
c. Remove the ramp so as not to interfere with the scales.
d. If the airplane is to be weighed for weight and balance computations, level
the airplane per instructions given in paragraph 2-15.

2-15. LEVELING. All configurationsof the airplane are provided with ameans
for longitudinal and lateral leveling. The airplane maybe leveled while on jacks,
during theweighing procedure while the wheels are on scales, orwhile thewheels
are on the ground. To level the airplane for purposes of weighing or rigging, the

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896
896 902
902

Figure 2-34. Leveling Longitudinally Figure 2-35. Leveling Laterally

followingprocedures may be used:

a. To longitudinally level the airplane, partially withdraw the two leveling screws
located immediately below the left front side window. (Refer to Figure 2-34.) Place a level
on these screws heads and adjust the jacks until the level is centered. Should the airplane be
either on scales or on the floor, first block the main gear oleos to full extension; then deflate
the nose wheel until the proper position is reached.
b. To laterally level the airplane, place a level across the spar box assemblylocated at
the forward baggage area of the PA-28-140 or under the rear seat of the PA-28-150,-160,
-180; PA-28-235; PA-28R. (Refer to Figure 2-35.)Raise or lower one wing tip by deflating
the appropriate tire on the high side of the airplane or adjust eitherjack until the bubble of the
level is centered.

2-16. MOORING. The airplane is moored to insure its immovability, protection and
security under various weather conditions. In order to properly moor the airplane use the
followingprocedures:
a. Head the airplaneinto the wind, if possible.
b. Block the wheels.
c. Secure the aileron and stabilator controls using the front seat belt or control surface
blocks.
d. Secure tie-down ropes to the wing tie-down rings and the tail skid at approximately
45 degree angles to the ground. When using rope constructed of non-synthetic material,
leave sufficient slack to avoid damage to the airplane when the ropes contract due to
moisture.

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CAUTION
Use square or bowline knots. Do not use slip knots.
NOTE
Additional preparations for high windsinclude usingtie-down
ropes on the landing gear forks, and securing the rudder.
e. Install pitot tube cover, if available.

2-17. LOCKING AIRPLANE. The cabin and baggage compartment doors are provided
with an outside lock. The ignition switch and cabin door require the same key while the
baggage compartment door has a different key.

2-18. PARKING. When parking the airplane, insure that it is sufficientlyprotected against
adverse weather conditions and presents no danger to other aircraft. When parking the air-
plane for any length of time or overnight, it is recommended that it be moored as in
Paragraph 2-16.
a. Park the airplane headed into the wind, if possible.
b. PA-28-150, -160, Serial Nos. 28-1 to 28-250 incl. Set the parking brake by pulling
back the brake lever and pulling the parking brake knob located at the left of the control
panel. Release the brake lever while holding the knob, then release the knob. To release the
parking brake, either push in the parking brake knob or pull back the brake lever.
c. PA-28-140; PA-28-150, -160, -180, Serial Nos. 28-251 and up; PA-28-235 and
PA-28R. Set the parking brake by pulling back the brake lever and depressing the knob
attached to the left side of the handle, then release the handle. To release the parking brake,
pull back on the brake leverto disengagethe catch mechanism,and allow the handle to swing
forward.
NOTE
Care should be taken when setting brakes that are overheated
during cold weather when accumulated moisture may freeze
the brakes.

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d. The aileron and stabilator controls may be secured using the front seat belt.

2-19. TOWING. The airplane may be moved by using the nose wheel steering bar that is
stowed in the baggage area of the PA-28-150,-160,-180; PA-28-235and PA-28R, or by using
power equipment that will not damage or cause excess strain to the nose gear steering
assembly. Towing lugs are incorporated as part of the nose gear fork of modelsPA-28-140;
PA-28-150,-160, -180;PA-28-235and PA-28R. On the PA-28R, the stem on the bar is inserted
in the hollow of the nose wheel axle at its right side.

CAUTIONS

1. When towing with power equipment, do not turn the

nose gear in either direction beyond its steering radius
limits as this will result in damage to the nose gear and
steering mechanism.
2. Do not tow the airplane with control locks installed.
3. When moving the airplane forward by hand, avoid
pushing on the trailing edge of the control surfaces as this
will cause the control surface contour to change resulting
in an out-of-trim condition.

In the event towing lines are necessary, lines (rope) should be attached to both main
gear struts as high up on the tubes as possible. Linesshould be long enough to clear the nose
and/or tail by not less than 15 feet, and a qualified person to ride in the pilot's seat to
maintain control by use of the brakes.

2-20. TAXIING. Before attempting to taxi the airplane, ground personnel should be
checked out by a qualified pilot or other responsibleperson. Engine starting and shutdown
procedures should be covered as well. When it is ascertained that the propeller back blast
and taxi areas are clear, apply power to start the taxi roll and perform the followingchecks:
a. Taxi forward a few feet and apply brakes to determine their effectiveness.
b. Taxi with propeller set in low pitch, high RPM setting, where applicable.
c. While taxiing, make slight turns to ascertain the effectivenessof steering.
d. Observe wing clearances when taxiing near buildings or other stationary objects. If
possible, station a guide outside the airplane to observe.
e. When taxiing on uneven ground, avoid holes and ruts.
f. Do not operate the engine at high RPM when running-up, or taxiing, over ground
containing loose stones, gravel or any loose material that may cause damage to the propeller
blades.

2-21. EXTERNAL POWER RECEPTACLE.

2-22. OPERATION OF EXTERNAL POWER RECEPTACLE. The receptacle is located
on the left side of the nose section,just aft of the enginecowling.Whenused for enginestarting
or operation of the airplanes' other equipment, proceed as follows:

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a. Set MASTER SWITCH to OFF.

b. Ensure that the RED lead of PEP (Piper External Power) kit jumper cable is con-
nected to the POSITIVE (+) terminal of an external 12-voltbattery or a power cart and that
the BLACK lead is connected to the NEGATIVE (-) terminal of same.
NOTE
If using an external battery, and the airplanes' battery is low
or depleted, disconnect the airplane battery at the negative
terminal to prevent excessiveloading of the external battery.
c. Insert the plug of the jumper cable into the receptacle.
d. Set MASTER SWITCH to ON and proceed with NORMAL engine starting.
e. After starting engine, set the MASTER SWITCH to OFF and remove the jumper
cable plug from the receptacle.
f. Set the MASTER SWITCH to ON and checkthe alternator ammeter for an indication
of output.
WARNING
Do not attempt any flight without an indication of alternator
output.

2-23. CLEANING.

2-24. CLEANINGENGINE COMPARTMENT.Before cleaning the engine compartment,

place a strip of tape on the magneto vents to prevent any solvent from entering these units.
a. Place a pan under the engine to catch waste.
b. With the enginecowlingremoved, spray or brush the engine with solvent or a mixture
of solvent and degreaser, as desired. Brushing may be necessarywhere heavy grease and dirt
deposits have collected.

CAUTION
Do not spray solvent into the alternator, starter, air intake,
and alternate air inlets.
c. Allow the solvent to remain on the engine from five to ten minutes; then rinse the
engine clean with additional solvent and allow to dry.

CAUTION
Do not operate engine until excess solvent has evaporated or
otherwise been removed.
d. Removethe protective covers from the magnetos.
e. Lubricate controls, bearingsurfaces, etc., per Lubrication Chart.

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2-25. CLEANING LANDING GEAR. Before cleaning the landing gear, place a plastic
cover or similar material over the wheel and brake assembly.
a. Place a pan under the gear to catch waste.
b. Spray or brush the gear area with solvent or a mixture of solvent and degreaser, as
desired. Brushing may be necessary where heavy grease and dirt deposits have collected.
c. Allow the solvent to remain on the gear from five to ten minutes, then rinse the gear
with additional solvent and allow to dry.
d. Remove the cover from the wheel and remove the catch pan.
e. Lubricate the gear per Lubrication Chart.

2-26. CLEANING EXTERIOR SURFACES. The airplane should be washed with

a mild soap and water. Harsh abrasives or detergents used on painted or plastic
surfaces couldmake scratches or cause corrosionof metal surfaces. Cover areas
where cleaning solution could cause damage. Cover the mast of the PA-28R-180
gear back-up extender. To wash the airplane, the following procedure may be
used:
a. Flush away loose dirt with water.
b. Apply cleaning solution with a rag, sponge or soft bristle brush.
c. To remove stubborn oil and grease, use a cloth dampened with naptha.
d. Where exhaust stains exist, allow solution to remain on the surface longer.
e. Any good automotive wax may be used to preserve the painted surfaces.
Soft cleaning cloths or a chamois should be used to prevent scratches when clean-
ing or polishing. A heavier coating of wax on the leading surfaces will reduce
the abrasion problems in these areas.

2-27. CLEANING WINDSHIELD AND WINDOWS.

a. Remove dirt, mud, etc. from exterior surfaces with clean water.
b. Wash with mild soap and warm water or an aircraft plastic cleaner using
a soft cloth or sponge and a straight rubbing motion. Do not harshly rub sur-
faces.
c. Remove oil and grease with a cloth moistened with kerosene.

NOTE

Do not use gasoline, alcohol, benzene, carbon tetra-

chloride, thinner, acetone or window cleaning sprays.

d. After cleaning plastic surfaces, apply a thin coat of hard polishing wax.
Rub lightly with a soft cloth. Do not use a circular motion.

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e. A severescratch or mar in plastic can be removed by usingjeweler's rouge to rub out the
scratch. Smooth both sides and apply wax.
f. To improve visibilitythrough windshieldand windowsduring flight through rain, a rain
repellant such as REPCON should be applied to the windshieldand windows. The surfaces of
the windshieldand windowstreated become so smooth that water beads up and readily flows
off the surface. Apply this product in accordance with the manufacturer's instructions. (Refer
to Table II-II Consumable Materials, for specifications and Manufacturer's address.)

2-28. CLEANINGHEADLINER,SIDEPANELSAND SEATS.

a. Clean headliner, side panels and seats with a stiff bristle brush and vacuum where
necessary.
b. Soiled upholstery, except leather, may be cleaned by using an approved air type
cleaner or foam upholstery cleaner. Carefully follow the manufacturer's instructions. Avoid
soaking or harsh rubbing.

CAUTION
Solvent cleanersrequire adequate ventilation.
c. Leather material should be cleaned with saddle soap or mild soap and water.

2-29. CLEANING CARPETS. Use a small whisk broom or vacuum to remove dirt. For
soiledspots, use a non-inflammabledry-cleaningfluid.

2-30. SERVICING.

2-31. INTRODUCTION TO SERVICING. This includes replenishment of fuel, oil, and

hydraulic fluids; the maintenance of tire pressures; and the lubrication of various items.

2-32. HYDRAULICSYSTEM(PA-28R)

2-33. SERVICING HYDRAULIC SYSTEM. The general condition of the hydraulic pump
and landing gear actuating cylinders should be checked. Ensure that there are no leaks and
that the line fittings are tight. The cylinder rods are to be free of all dirt and grit. To clean the
rods use an oil soaked rag and carefully wipe them. All the hydraulic lines should also be
checked for freedom of leaks, kinks, and corrosion. Check for tightness of the attachment
fittings.
The gear back up extender actuator assemblyis located beneath the rear seat and should
be checked to determine that it is operating properly. The diaphragm shaft may be operated
by hand to make sure that it is free to fluctuate and that the actuating arm and its components

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are operating freely. Check the pressure housing assembly for absence of cracks, breaks, or
fatigue. Check to ensure that the hydraulic valve and fittings are free of leaks.
Repair and check procedures for the hydraulic pump, cylinders and various components
may be found in Section VI of this manual.

2-34. SERVICING HYDRAULIC PUMP/RESERVOIR. The fluid level of the reservoir of

the combination pump and reservoir should be checked every 50 hours by viewing the fluid
through the filler plug hole in the hydraulic pump. Access to the pump is through the panel at
the right rear side of the baggage compartment.
To check fluid level, remove the plug located on the forward side of the pump and
ascertain that fluid is visible up to the bottom of the filler plug hole. Should fluid be below the
hole, add fluid, MIL-H-5606A, through the filler hole until full. Reinstall the filler plug and
tighten.

NOTE

A small vent hole is located under the vent screw head. Retain
1/64 inch clearance between the screw head and the small vent
hole.

2-35. LANDING GEAR SYSTEM.

2-36. SERVICING LANDING GEAR. The landing gear consists of tires, brakes, oleo strut
assemblies and on some models, wheel fairings. The gear should be inspected for proper
extension, unscored piston tubes, soundness of hydraulic fluid seals, the security and firm
mechanical condition of all connection points and the absence of cracks in the fiberglass
fairings. Check the brake linings for excessive wear, the brake discs for scoring and replace as
necessary. The PA-28R should be checked for proper adjustment of down locks, the
mechanical soundness and firm action of drag and side brace links. Minor servicing is
described in the following paragraphs. Detailed service and overhaul instructions are given in
Sections VII or VIIA.

2-37. OLEO STRUTS. (PA-28-140; PA-28-150,-160,-180 and PA-28-235.)

2-38.. SERVICING OLEO STRUTS. Air-oil struts are incorporated in each landing gear
oleo to absorb the shock resulting from the impact of the wheels on the runway during landing.
To obtain proper oleo action, the nose gear oleo strut must have approximately 3.25 ± .25
inches of piston tube exposed, while the main gear struts require approximately 4.5 ±.50 inches
of tube exposure.

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CAUTION

Do not exceed the foregoingtube exposures.

These measurements are taken with the airplane setting on a level surface
under normal static load (empty weight of airplane plus full fuel and oil). If the
strut has less tube exposed than that prescribed, determine whether it needs air
or oil by raising the airplane on jacks. With the strut extended, remove the cap
from the air valve at the top of the housing and depress the valve core to allow
air to escape from the strut piston until it is fully compressed. Allow the foam
from the air-oil mixture to settle and then determine if oil is visible up to the
bottom of the filler plug hole. If oil is visible at the bottom of the hole, then all
that is required is the valve be checked for unsatisfactory conditions and air added
as described in paragraph 2-41. Should fluid be at any level below the bottom of
the filler plug hole, the oleo should be checked for leaks, etc. and oil added as
described in paragraph 2-39 for the nose gear or paragraph 2-40 for the main
gear. For repair procedures of the landing gear and/or oleo struts, refer to
Section VII or VIIA.

WARNING

Do not release air byremovingthe strutvalve core or

filler plug. Depress the valve core pin until strut
chamber pressure has diminished.

CAUTION

Dirt and foreign particles form around the filler plugs

of the landing gear struts, therefore, before attempt-
ing to remove these plugs, the tops of the struts should
be cleaned with compressed air and/orwith a dry sol-
vent.

2-39. FILLINGNOSE GEAROLEOSTRUT. Regardlessof the amountof oil requiredfill

the nose gear oleo strut with hydraulicfluid (MIL-H-5606)as follows:
a. Raise the airplane on jacks until the nose wheel is completely clear of the
ground. (Refer to Paragraph 2-13.)
b. Place a pan under the gear to catch spillage.
c. If not previously accomplished, remove the engine cowl and relieve air

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from the strut housing chamber by removing the cap from the air valve and depressingthe
valve core.
d. There are two methods by which the strut chamber may be filled and these are as
follows:
Method 1:
1. Remove the valve core from the filler plug at the top of the strut housing. Allow
the plug to remain installed.
2. Attach one end of a clear plastic hose to the valve stem of the filler plug and
submerge the other end in a container of hydraulic fluid. Ascertain that the end of the hose
on the valve stem is tight and the fluid container is approximately equal in height to the top
of the strut housing.
3. Fully compress and extend the strut thus drawing fluid from the fluid container
and expelling air from the strut chamber. By watching the fluid pass through the plastic
hose, it can be determined when the strut is full and no air is present in the chamber.
4. When air bubbles cease to flow through the hose, compress the strut fully and
remove the hose from the valvestem.
5. With strut compressed, remove the filler plug to determine that the fluid level is
visible up to the bottom of the filler plug hole.
6. Reinstall the core in the filler plug and apply thread lubricated (Parker#6PB) to
the threads of the filler plug and install the plug in the top of the strut housing.Torque the
plug to 45 foot pounds.
Method 2:
1. Remove the filler plug from the top of the strut housing.
2. Raise the strut piston until it is fully compressed.
3. Pour fluid from a clean container through the filler opening until it reaches the
bottom of the filler plug hole.
4. Install the filler plug finger tight, and extend and compress the strut two or three
times to remove any air that may be trapped in the housing.
5. Remove the filler plug, raise the strut to full compression and fill with fluid if
needed.
6. Apply thread lubricant (Parker #6PB) to the threads of the filler plug. Reinstall
the filler plug and torque to 45 foot pounds.
e. With the airplane raised, compress and extend the gear strut several times to
ascertain that the strut actuates freely. The weight of the gear fork and wheel should extend
the strut.
f. Clean off overflow of fluid, and inflate the strut as described in Paragraph 2-41.
g. Check that fluid is not leaking from around the strut piston at the bottom of the
housing.

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1757

951

1. FILLER, FUEL TANK, LEFT

2. DRAIN, FUEL TANK, LEFT
3. FILTER, VACUUM REGULATOR AND CENTRAL AIR
4. RESERVOIR, BRAKE SYSTEM
5. SCREEN OR CARTRIDGE FILTER, OIL PRESSURE, ENGINE
6. FILLER/INDICATOR, OIL, ENGINE
7. FILTER, FUEL PUMP, ELECTRIC
8. SCREEN, FUEL DRAIN
9. FILLER, OLEO SHOCK STRUT, NOSE
10. DRAIN, FUEL, ENGINE
11. SCREEN OIL SUCTION, ENGINE
12. FILTER, CARTRIDGE, ENGINE INDUCTION
13. TIRE, NOSE
14. CARBURETOR, ENGINE
15. FILLER, OLEO SHOCK STRUT, L AND R
16. DRAIN, FUEL TANK, RIGHT
17. TIRE, L AND R
IS. FILLER, FUEL TANK, RIGHT
19. BATTERY
20. FILTER, INSTRUMENTS, (WITHOUT CENTRAL AIR FILTER)
21. AIR CONDITIONING SERVICE VALVES

Figure 2-36. Servicing Points

PA-28-140

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1812

1. FILTER, INSTRUMENTS, (WITHOUT CENTRAL AIR FILTER)

2. FILLER, TIP FUEL TANK, LEFT
3. DRAIN, TIP FUEL TANK, LEFT
4. FILLER, MAIN FUEL TANK, LEFT
5. DRAIN, MAIN FUEL TANK, LEFT
6. FILTER, VACUUM REGULATOR AND CENTRAL AIR
7. RESERVOIR, BRAKE SYSTEM
8. SCREEN OR CARTRIDGE FILTER, OIL PRESSURE, ENGINE
9. FILLER/INDICATOR, OIL, ENGINE
10. FILLER, OLEO SHOCK STRUT, NOSE
11. PROPELLER
12. TIRE, NOSE
13. CARBURETOR, ENGINE
14. FILTER, CARTRIDGE, ENGINE INDUCTION
15. SCREEN, OIL SUCTION, ENGINE
16. DRAIN, FUEL
17. FILLER, OLEO SHOCK STRUT, L AND R
18. DRAIN, MAIN FUEL TANK, RIGHT
19. FILLER, MAIN FUEL TANK, RIGHT
20. FILLER, TIP FUEL TANK, RIGHT
21. DRAIN, TIP FUEL TANK, RIGHT
22. BATTERY
23. FILTER, FUEL PUMP, ELECTRIC

Figure 2-38. Servicing Points

PA-28-235

HANDLING AND SERVICING

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1811

1. FILLER, FUEL TANK, LEFT

2. DRAIN, FUEL TANK, LEFT
3. FILTER, VACUUM REGULATOR AND CENTRAL AIR
4. RESERVOIR, BRAKE SYSTEM
5. SCREEN OR CARTRIDGE FILTER, OIL PRESSURE, ENGINE
6. FILLER/INDICATOR, OIL, ENGINE
7. SCREEN, FUEL DRAIN
8. FILTER, CARTRIDGE, ENGINE INDUCTION
9. DRAIN, FUEL ENGINE
10. FILLER, OLEO SHOCK STRUT, NOSE
11. PROPELLER
12. TIRE, NOSE
13. INJECTOR, FUEL
14. SCREEN, OIL SUCTION, ENGINE
15. FILLER, OLEO SHOCK STRUT, L AND R
16. DRAIN, FUEL TANK, RIGHT
17. TIRE, L AND R
18. FILLER, FUEL TANK, RIGHT
19. PUMP/RESERVOIR, HYDRAULIC SYSTEM
20. BATTERY
21. FILTER, INSTRUMENTS

Figure 2-39. Servicing Points

PA-28R

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1758
FILLERPLUG
2-40. FILLING MAIN GEAR OLEO FLUID
LEVEL
- STRUT
STRUT. A main gear oleo strut that is FULLY
COMPRESSED
partly full or one that has been completely STRUT
CHAMBER
- TOP
emptied may be filled with MIL-H-5606
Fluid as follows:
TOP
OFSTRUT
TUBE
a. Raise the airplane on jacks until the FULLY
COMPRESSED
landing gear torque link assembly has
almost reached its full travel. (Refer to
Paragraph 2-13.) STRUT
CHAMBER
b. Place a pan under the gear to catch MIDDLE
spillage.
c. If not previously accomplished,
remove the cap on top of the wing to gain
access to the top of the strut housing, and
relieve air from the strut housing chamber
by removing the cap from the air valveand
depressing the valve core.
d. Remove any one of the three TOP
OF
torque link bolts, and again raise the STRUT
TUBE
EXTENDED
10"
airplane until a minimum of ten inches (do
not exceed twelve inches of tube exposure) STRUT
CHAMBER
of strut tube is exposed with the wheel BOTTOM
remaining on the ground. With this amount
of tube exposed, fluid will flow from the
middle chamber to the bottom chamber of
the strut housing, insuring that the bottom
chamber is filled with fluid.
STRUT
EXPOSURE
LOAD
STATIC
STRUT
FULLY 4.50 .50
COMPRESSED
NOTE
With the torque links
disconnected, the piston
STRUT
EXTENSION
tube is free to slide from UNDER
the strut housing. STATIC
LOAD

STRUTEXTENSION

e. Fill the main gear housing by one

of two methods which are as follows:
Method 1: STRUT 10"
EXTENDED
1. Remove the valve core from the
filler plug at the top of the strut housing. Figure 2-40. Main Gear Oleo Struts
Allow the plug to remain installed. (Cut-away View) PA-28-140;
PA-28-150, -160, -180; PA-28-235

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2. Attach one end of a clear plastic hose to the valve stem of the filler plug and
submerge the other end in a container of hydraulic fluid.
3. Fully compress and extend (10 + 2-0 inches of strut tube exposed) the strut
thus drawing fluid from the strut chambers. By watching the fluid pass through the plastic
hose, it can be determined when the strut is full and no air is present in the chambers.The
strut must be extended to full ten inches to allow fluid to enter the bottom chamber of
strut housing.
4. When air bubbles cease to flow through the hose, compress the strut fully and
remove the hose from the valvestem.
5. With the strut fully compressed, remove the filler plug to determine that the
fluid level is visibleup to the bottom of the filler plug hole.
6. Reinstall the core in the filler plug and apply thread lubricant (Parker #6PB) to
the threads of the filler plug and install the plug in the top of the strut housing.Torque the
plug to 45 foot pounds.
Method 2:
1. Remove the filler plug from the top of the strut housing.
2. Raise the strut to full compression.
3. Pour fluid from a clean container through the filler opening until it is visible at
the top of the strut chamber. If the housing has been completely emptied or nearly so, allow
sufficient time for the fluid to drain through the orifice from the upper chamber into the
middle chamber.
4. Lower the gear until the wheel touches the ground (10 + 2-0 inches of strut
exposure) and then fully compress and extend the strut three or four times to remove any
air that may be trapped and to allow fluid to enter the bottom chamber of the housing.
5. Raise the strut to full compressionand if needed, fill with fluid to the bottom of
the filler plug.
6. Apply thread lubricant (Parker# 6PB) to the threads of the filler plug. Reinstall
the filler plug and torque to 45 foot pounds.
e. Replace the torque link bolt. Tighten bolt only tight enough to allowno side play in
the connection.
f. With the airplane raised, retract and extend the gear strut severaltimes to ascertain
that the strut actuates freely. The weight of the gear fork and wheel should extend the strut.
g. Clean off overflow of fluid and inflate the strut as described in Paragraph 2-41.
h. Check that fluid is not leaking around the strut piston at the bottom of the housing.

2-41. INFLATING OLEO STRUTS. After making certain that the oleo strut has
sufficient fluid, attach a strut pump to the air valve and inflate the oleo strut. The strut
should be inflated until the correct inches of piston is exposed with normal static load
(empty weight of airplane plus full fuel and oil) on the gears. (Refer to Paragraph 2-38.)
Rock the airplane several times to ascertain that the gear settles back to the correct strut
position. (If a strut pump is not available,the airplane may be raised and line pressure from
a high pressure air system used. Lower the airplane and while rocking it, let air from the
valve to bring the strut down to the proper extension.) Before capping the valve,check for
valve core leakage.

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2-42. OLEO STRUTS. (PA-28R)

2-43. SERVICING OLEO STRUTS. The air-oil type oleo strut should be maintained at
proper strut tube exposures for best oleo action. The nose gear strut must have
approximately 2.75 inches of piston tube exposed, while the main gear strut requires
approximately 2.0 inches of tube exposure. These measurementsare taken with the airplane
sitting on levelsurface under normal static load. (Empty weight of airplane plus full fuel and
oil.) If the strut has lesstube exposure than prescribed, determine whether it needs air or oil
by rocking the airplane. If the oleo strut oscillated with short strokes (approximately one
inch) and the airplane settles to its normal position within one or two cycles after the
rocking force is removed, the oleo strut requires inflating. Check the valve core and filler
plug for air leaks, correct if required, and add air as described in Paragraph 2-45. If the oleo
strut oscillateswith long strokes (approximately three inches) and the airplane continues to
oscillate after the rocking force is removed, the oleo struts require fluid. Check the oleo for
indications of oil leaks, correct if required and add fluid as described in Paragraph 2-44. For
repair proceduresof the landinggear and/or oleo struts, refer to Section VIIA.
WARNING
Do not release air by removing the strut valve core or filler
plug. Depressthe valve core pin until strut chamber pressure
has diminished.
CAUTION
Dirt and foreign particles form around the filler plugs of the
landing gear struts, therefore, before attempting to remove
these plugs, the tops of the struts should be cleaned with
compressedair and/or with a dry solvent.

THIS SPACEINTENTIONALLYLEFT BLANK

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2-44. FILLING OLEO STRUTS. To fill the nose or main gear oleo strut with fluid
(MIL-H-5606), whether it be the addition of a small or large amount, proceed as follows:
a. Raise the airplane on jacks. (Refer to Paragraph 2-13.)
b. Place a pan under the gear to catch spillage.
c. At the filler plug, relieve air pressure from the strut housing chamber by removing
the cap from the air valveand depressingthe valvecore.
d. There are two methods by which the strut chamber may be filled and these are as
follows:
Method 1:
1. Remove the valve core from the filler plug at the top of the nose gear strut
housing or at the top inboard side of the main gear housing. Allow the filler plug to remain
installed.
2. Attach one end of a clean plastic hose to the valve stem of the filler plug and
submergethe other end in a container of hydraulic fluid.
NOTE

An air-tight connection is necessary between the plastic tube

and the valve stem. Without such a connection, a small
amount of air will be sucked into the oleo strut during each
sequence, resulting in an inordinate amount of air bubbles
and a prolonged filling operation.

3. Fully compress and extend the strut thus drawing fluid from the fluid container
and expelling air from the strut chamber. By watching the fluid pass through the plastic
hose, it can be determined when the strut is full and no air is present in the chamber.
4. When air bubbles cease to flow through the hose, compress the strut fully and
remove the hose from the valvestem.
5. With the strut compressed, remove the filler plug to determine that the fluid
level is visible up to the bottom of the filler plug hole.
6. Reinstall the core in the filler plug and apply thread lubricant (Parker#6PB) to
the threads of the filler plug and install the plug in the top of the strut housing.Torque the
plug to 45 foot pounds.
Method 2:
1. Remove the filler plug from the top of the nose gear strut housing or at the top
inboard side of the main gear housing.
2. Raise the strut piston tube until it is fully compressed.
3. Pour fluid from a clean container through the filler opening until it reaches the
bottom of the filler plug hole. (Air pressure type oil container may be helpful.)
4. Install the filler plug finger-tightand extend and compress the strut two or three
times to remove air from the housing.
5. Remove the filler plug, raise the strut to full compression and fill with fluid if
needed.

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6. Apply thread lubricant (Parker#6PB) to the threads of the filler plug. Reinstall
the filler plug and torque -to 45 foot pounds.
e. With the airplane raised, compress and extend the gear strut several times to
ascertain that the strut movesfreely. The weightof the gear fork and wheel should extend the
strut.
f. Clean off overflow of fluid and inflate the strut as described in Paragraph 2-45.
g. Check that fluid is not leaking around the strut piston at the bottom of the housing.

2-45. INFLATING OLEO STRUTS. After making certain that an oleo strut has sufficient
fluid, attach a strut pump to the air valve and inflate the oleo strut. The strut should be inflated
until the correct inches of piston are exposed with normal static load on the gears (empty
weight of the airplane plus full fuel and oil). (Refer to Paragraph 2-43.) Rock the airplane
severaltimes to ascertain that the gear settles back to the correct strut position. If a strut pump
is not available, the airplane may be raised and line pressure from a high pressure air system
used. Lower the airplane and whilerocking it, let air from the valveto bring the strut down to
the proper extension. (Beforecapping the valve, check for tightness of the valve core, that is,
no leakage.)

2-46. BRAKESYSTEM.

2-47. SERVICING BRAKE SYSTEM. The brake system incorporates a hydraulic fluid
reservoir through which the brake system is periodically serviced. Fluid is drawn from the
reservoir by the brake cylinders to maintain the volume of fluid required for maximum
braking efficiency. Spongy brake pedal action is often an indication that the brake fluid
reservoir is running low on fluid. Instructions for filling the reservoir are given in Paragraph
2-48. When necessaryto repair any of the brake system components, or to bleed the system,
refer to instructions in Section VII or VIIA.
2-48. FILLING BRAKE CYLINDER RESERVOIR. The brake cylinder reservoir should
be filled to the level marked on reservoir, with the fluid specified in Table II-I. The reservoir,
located on the left side of the fire wallin the engine compartment, should be checked at every

HANDLING AND SERVICING

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50 hour inspection and replenish as necessary. No adjustment of the brakes is necessary,

though they should be checked periodically per instructions given in Section VII or VIIA.

2-49. DRAINING BRAKE SYSTEM. To drain the brake system, connect a hose to the
bleeder fitting on the bottom of the cylinder and place the other end of the line in a suitable
container. Open the bleeder and slowly pump the hand brake lever and the desired brake
pedal until fluid ceases to flow. To clean the brake system, flush with denatured alcohol.

2-50. TIRES.

2-51. SERVICING TIRES. The tires should be maintained at the pressure specified in
Table II-I. When checking tire pressure, examine the tires for wear, cuts, bruises and slippage
on the wheel. The tire, tube, and wheel should be properly balanced when installed with the
index mark on the tire aligned with the index mark on the tube.

2-52. POWER PLANT.

2-53. SERVICING POWER PLANT. Regularly check the engine compartment for oil and
fuel leaks, chaffing of lines, loose wires and tightness of all parts. For cleaning of the engine
compartment, refer to paragraph 2-24. Maintenance instructions for the power plant may be
found in Section VIII or VIIIA of this manual and in the appropriate manufacturers'
manuals.

2-54. INDUCTION AIR FILTER.

2-55. REMOVAL OF AIR FILTER. (Refer to INSPECTION, SECTION III, for additional
requirements.)
a. PA-28-140, PA-28-150, -160, -180, Serial Nos. 28-1 to 28-1760 incl. The induction
air filter is located below the spinner assembly within the nose cowling. If the airplane is
equipped for night flying, a landing light will be installed within the center of the filter
assembly. The filter may be removed in accordance with the following instructions:
1. Within the aft side of the nose cowl, loosen and remove the thumb screw on the
back of the assembly.
2. Remove the retainer assembly. If a landing light is installed, it will be necessary
to remove the wires aft the connections on the light before removal.

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3. Remove the filter and clean or replace in accordance with Paragraph 2-56.
b. On PA-28-180, Serial Nos. 28-1761and up, the filter is located on the right side and
midway in the engine compartment and may be removed by the following procedure:
1. Remove the two nuts and washers on the cover assemblyand pull off the cover.
2. The filter is now free to be removed and cleaned per Paragraph 2-56.
c. On PA-28-235, Serial Nos. 28-10003to 28-10560incl., the air filter is located on the
right side and midway in the engine compartment. For removal, refer to the followingsteps:
1. Loosen and remove the wing nut on the filter cover and remove cover.
2. Remove the filter and clean or replace in accordance with Paragraph 2-56.
d. On PA-28-235,Serial Nos. 28-10561and up, the air filter is located on the right side of
the engine and in front of the fire wall. Remove the filter per the following instructions:
1. Remove the two wing nuts and remove the cover.
2. The filter is now free to be removed and cleaned per Paragraph 2-56.
e. On PA-28R, the filter is located on the left side and just in front of the fire wall. Re-
move by the following procedure:
1. Loosen the three studs and carefullymove the cover assemblyaside. Be sure not to
damage or bend the alternate air cable.
2. The filter is now free for removal. Clean or replace the filter as givenin Paragraph
2-56.

2-56. SERVICE INSTRUCTION. (CLEANING AND INSPECTION.)

a. The filter should be cleaneddaily when operating in dusty conditions and if any holes
or tears are noticed, the filter should be replaced immediately. For type of replacement filter,
refer to PA-28 Parts Catalog.
b. Remove the filter elementand shake off loose dirt by tapping on a hard surface, being
careful not to damage or crease the sealing ends.
CAUTION

Never wash the filter element in any liquid or soak in oil. Never
attempt to blow off dirt with compressed air.
c. The filter housing can be cleaned by wiping with a clean cloth soaked in suitable quick
drying type solvent. When the housing is dry, reinstall in accordance with Paragraph 2-56.

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2-57. INSTALLATION OF AIR FILTER. After cleaning and inspection, install

the filter element and cover in reverse order of removal instructions.

2-58. PROPELLER.

2-59. SERVICING PROPELLER. The spinner, back plate and propeller surfaces should
be cleaned and inspected frequently for freedom from nicks, scratches, corrosion and cracks.
Minor nicks and scratchesmay be removedas found in SectionVIII or VIIIA. The face of each
blade should be painted when necessarywith a flat paint to retard glare. To prevent corrosion,
wipe surfaces with a light oil or wax.
In addition, constant speed propellers should be inspected for absence of grease or oil
leakage and freedom of rotation on the hub pilot tube. To check freedom of rotation, rock the
blade back and forth through the slight freedom allowed by the pitch change mechanism.
Lubricate the propeller at 100-hour intervals in accordance with the Lubrication Chart.
Additional service information for the propeller may be found in Section VII, VIII or
VIIIA.

2-60. FUEL SYSTEM.

2-61. SERVICING FUEL SYSTEM.

a. At intervals of 50 hours or 90 days, whichevercomesfirst, clean the fuelscreensand / or
filters as follows:
1. PA-28-140; PA-28-150, -160, -180. The fuel strainer screen, located in the fuel
bowl, mounted on the lower left side of the fire wall; the screen in the electric fuel pump,
located at the lower left side of the engine compartment; and the screen in the inlet side of the
carburetor.
2. PA-28-235.The screens and bowl of the fuelfilter unit of the fuel selector and the
screen of the electricfuel pump(s), located in the area under the rear seat aft of the main spar;
and the screen located in the inlet side of the carburetor.
3. PA-28R. The fuel strainer screen, located in the fuel bowl mounted on the lower
left side of the fire wall; and the screen in the inlet side of the injector.
b. Remove and clean the screens in accordance with the instructions outlined in Section
IX. Additional serviceinformation is given in Section IX. Inspection intervals of the various
fuel system components is given in Section III.

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2-62. FILLING FUEL TANKS. (PA-28-140; PA-28-150, -160, -180 and PA-28R.) Observe
all required precautions for handling gasoline. Fill the fuel tanks with the fuel as specified in
Table II-I. Each fuel tank holds a maximum of 25 U.S. gallons. To obtain the standard fuel
quantity of 36 U.S. gallons total, or 18 gallons per tank, the tanks are filled only to the bottom
of the filler neck tube or visual indicator, each of which extend into the fuel tank about 3.50
inches. To obtain the standard plus reserve quantity, the tanks are filled to the top of the filler
neck.

2-63. FILLING FUEL TANKS. (PA-28-235.) The fuel tanks of each wing are filled through
filler necks located on the forward slope of the wings and at the wing tip. Each wing tank holds
25 U.S. gallons while each tip tank holds 17 U.S. gallons. Observe all required safety pre-
cautions for handling gasoline. Fill the tanks with fuel as specified on the placard adjacent to
the filler neck or as indicated in Table II-I.

2-64. DRAINING MOISTURE FROM FUEL SYSTEM. (PA-28-140, -150, -160, -180 and
PA-28R.) The fuel tanks and fuel strainer should be drained daily prior to first flight and after
refueling to avoid the accumulation of water or sediment. Each fuel tank is equipped with an
individual quick drain located at the lower inboard rear corner of the tank. The fuel strainer
with a quick drain valve (refer to Figure 2-41) is located on the lower left side of the fire wall.
Drain fuel tanks and strainer per the following:
a. Drain each tank through its individual quick drain located at the lower inboard rear
corner of the tank, making sure that enough fuel has been drained to insure that all water
and sediment is removed.
b. Place a container under the fuel strainer drain. Drain the fuel strainer by opening the
quick drain on the strainer.
c. Examine the contents of the container placed under the fuel strainer drain for water
and sediment and dispose of the contents.

CAUTION

When draining any amount of fuel, care should be taken to

insure that no fire hazard exists before starting engine.

2-65. DRAINING MOISTURE FROM FUEL SYSTEM. (PA-28-235.) The fuel system
should be drained daily prior to first flight and after refueling to avoid the accumulation of
water or sediment. Each fuel tank is equipped with an individual quick drain located at the
lower inboard rear corner of the tank. The fuel strainer and a system quick drain valve (refer
to Figure 2-42) are located in the fuselage at the lowest point of the fuel system. It is
important that the fuel system be drained in the following manner:

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A658 1673

1. BOWL 4 — 1. DRAIN LEVER 6. RIGHT MAIN TANK

2. BAIL 2. LEVER ACCESS DOOR 7. LEFT MAIN TANK
3. SAFETY WIRE 3. SELECTOR ROD ASSEMBLY 8. LEFT TIP TANK
4. DRAIN 4. DRAIN 9. TO FUEL PUMPS
5. THUMB NUT 5. RIGHT TIP TANK

Figure 2-41. Fuel Strainer Figure 2-42. Fuel Selector and Filter
PA-28-140; PA-28-150,-160, -180 PA-28-235
PA-28R

a. Drain each tank through its individual quick drain located at the lower inboard rear
corner of the tank, making sure that enough fuel has been drained to insure that all water
and sediment is removed.
b. Place a container under the fuel sump drain outlet, which is located under the
fuselage.
c. Drain the fuel strainer by pressing down on the lever located on the right-hand side
of the cabin below the forward edge of the rear seat. The fuel selector must be positioned in
the following sequence: off position, left tip, left main, right main, and right tip while
draining the strainer to insure that the fuel lines between each tank outlet and fuel strainer
are drained as well as the strainer. Whenthe fuel tanks are full, it will take approximately 11
seconds to drain all the fuel in one of the lines between a tip tank and the fuel strainer and
approximately six seconds to drain all the fuel in one of the lines from a main tank to the
fuel strainer. When the fuel tanks are less than full, it will take a few secondslonger.
d. Examine the contents of the container placed under the fuel sump drain outlet for
water and sediment and dispose of the contents.

CAUTION
When draining any amount of fuel, care should be taken to
insure that no fire hazard exists before starting engine.

NOTE
After using the underseat quick drain, it should be checked
from outside to make sure it has closed completely and is not
leaking.

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2-66. DRAINING FUEL SYSTEM. Fuel may be drained from the system by opening the
valve at the inboard end of each fuel tank. Push up on the arms of the drain valve and turn
counterclockwise to hold the drain in the open position. The flush type drain valve requires
the drain cup pin to hold valve open. The remaining fuel in the system may be drained through
the filter bowl. Any individual tank may be drained by closing the selector valve and then
draining as desired.

2-67. ANTI-ICING FUEL ADDITIVE. The operation of the aircraft is approved with an
anti-icing additive in the fuel. When an anti-icing additive is used it must meet the specification
MIL-1-27686. must be uniformly blended with the fuel while refueling, must not exceed .15%
by volume of the refueled quantity, and. to ensure its effectiveness, should be blended at not
less than .10% by volume. One and one half liquid ozs. per ten gallon of fuel would fall within
this range. A blender supplied by the additive manufacturer should be used. Except for the
information contained in this section, the manufacturer's mixing or blending instructions
should be carefully followed.

CAUTION

Assure that the additive is directed into flowing fuel stream.

The additive flow should start after and stop before the fuel
flow. Do not permit the concentrated additive to come in
contact with the aircraft painted surfaces or the interior
surfaces of the fuel tanks.

Some fuels have anti-icing additives preblended in the fuel at

the refinery, so no further blending should be performed.

Fuel additive cannot be used as a substitute for preflight

draining of the fuel system drains.

2-68. ELECTRICAL SYSTEM.

2-69. SERVICING ELECTRICAL SYSTEM. Servicing the electrical system involves adding
distilled water to the battery to maintain correct electrolyte level, and checking cable
connections and for any spilled electrolyte that would lead to corrosion. The security of all
electrical connections should be checked as well as the operation of all lights, general
condition of the generator or alternator and starter. All electrical wires should be inspected
for chafing and bare wires. For detailed information on this system, refer to Section XI of
this manual.

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2-70. LUBRICATION.

2-71. OIL SYSTEM. (ENGINE.)

2-72. SERVICINGOIL SYSTEM. The engine oil level should be checked before each flight
and changed after each 50 hours of engine operation. During oil change, the oil screen(s)
should be removed and cleaned, and when installed, the oil filter cartridge replaced.
Intervals between oil changes can be increased as much as 100%on engines equipped with
full flow (cartridge type) oil filters provided the element is replaced each 50 hours of
operation. Should fuel other than the specified octane rating for the power plant be used,
refer to the latest revision of Lycoming Service Letter No. L185 for additional information
and recommended service procedures. The engine manufacturer does not recommendoils by
brand names. Use a quality brand Aviation Grade Oil of the proper season viscosity.For in-
formation on the use of detergent oil, refer to paragraph 2-77 and/or the latest revision of
Lycoming Service Instruction No. 1014.

CAUTION

Do not introduce any trade additive to the basic lubricant

unless recommended by the engine manufacturer.

2-73. FILLING OIL SUMP. The oil sump should normally be filled with oil to the mark on
the engine dipstick. The quantity of oil required for the enginesmay be found in Table II-I.
The specified grade of oil may be found in Table II-IX, the Lubrication Chart, or on the
right cowl panel or each engine oil filler accessdoor. To servicethe engine with oil, open the
right cowl panel or quick release accessdoor on top of the cowl and remove the oil filler cap
with dipstick.

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2-74. DRAINING OIL SUMP. To drain the oil sump, provide a suitable container with a
minimum capacity of that required to fill the sump. Remove the engine cowl and open the
oil drain valve located on the underside of the engine by pushing the arms of the drain up
and turning counterclockwise. This will hold the drain in the open position. It is
recommended the engine be warmed to operating temperature to insure complete draining
of the old oil.
CAUTION

On PA-28R-200 aircraft, if an oil quick drain valve is

installed, ascertain that it is Piper P/N 492 172. (Refer to the
latest revisionof Piper ServiceLetter No. 534.)
2-75. OIL SCREENS. (SUCTION.) The oil suction screen, located either on the bottom
aft end of the engine sump, installed horizontally, or forward of the carburetor installed
vertically. To remove both types, cut the safety wire and remove the hex head plug. The
screen should be cleaned at each oil change to remove any accumulation of sludge and to
examine for metal filings or chips. If metal particles are found in the screen, the engine
should be examined for internal damage. After cleaning and inspection, place the screen
inside the recess in the hex head plug, to eliminate possible damage to the screen. Insert the
screen into the housing and when certain that the screen is properly seated, tighten and
safety the plug with MS-20995-C41safety wire.

2-76. OIL SCREEN. (PRESSURE.) The oil pressure screen, located in a housing on the
accessory case of the engine, between the magnetos, should be cleaned at each oil change to
remove any accumulation of sludge and to examine for metal filings or chips. If metal
particles are found in the screen, the engine should be examined for internal damage.When
reinstalling the screen, it is recommended that a new gasket be used. Ascertain that the
screen fits flush with the base surface of the screen housing. Position housing on mounting
pad and install attachment bolts. Torque bolts within 50 to 70 inch-pounds.

2-77. OIL FILTER. (FULL FLOW.)

a. The oil filter element should be replaced after each 50 hours of engine operation;
this is accomplished by removing the lockwire from the bolt-head at the end of the filter
housing, looseningthe bolt, and removingthe filter assemblyfrom the adapter.
b. Before discarding the filter element, remove the outer perforated paper cover, and
using a sharp knife, cut through the folds of the element at both ends, close to the metal
caps. Then, carefully unfold the pleated element and examine the material trapped in the
filter for evidence of internal engine damage such as chips or particles from bearings.In new
or newly overhauled engines,some small particle of metallic shavingsmight be found; these
are generally of no consequence and should not be confused with particles produced by
impacting, abrasion or pressure. Evidenceof internal engine damage found in the oil filter
justifies further examination to determine the cause.

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c. After the element has been replaced, tighten the attaching bolt within 15 to 18
foot-pounds of torque. Lockwire the bolt through the loops on the side of the housing to
the drilled head of the thermostatic valve. Be sure the lockwire is replaced at both the
attaching bolt head and the thermostatic oil cooler bypassvalve.

2-78. RECOMMENDATIONSFOR CHANGING OIL. (Refer to the latest revision of

Lycoming ServiceInstruction No. 1014 and Lycoming ServiceLetter No. L185.)
a. In engines that have been operating on straight mineraloil for severalhundred hours,
a change to additive oil should be made with a degree of caution, since the cleaningaction
of some additive oils will tend to loosen sludge deposits and cause plugged oil passages.
When an engine has been operating on straight mineral oil and is known to be in excessively
dirty condition, the switch to additive or compounded oil should be deferred until after the
engineis overhauled.
b. When changing from straight mineral oil to compounded oil, the following
precautionary steps should be taken:
1. Do not add additive oil to straight mineral oil. Drain the straight mineral oil
from the engine and fill with additiveoil.
2. Do not operate the engine longer than five hours before the first oil change.
3. Check all oil screens for evidence of sludge or pluggingand change oil every ten
hours if sludge conditions are evident. Resume normal oil drain periods after sludge
conditions improve.

2-79. LUBRICATION INSTRUCTIONS.Proper lubrication procedures are of

immeasurable value both as a means of prolonging the service life of the airplane and as a
means of reducing the frequency of extensive and expensive repairs. The periodic
application of recommended lubricants to their relevant bearing surfaces, as detailed in the
following paragraphs, together with observance of cleanliness,will insure the maximum
efficiency and utmost service of all moving parts. Lubrication instruction regarding the
locations, time intervals, and type of lubricants used may be found in the Lubrication Chart.
To insure the best possible results from the application of lubricants, the following
precautions should be observed:
a. Use recommended lubricants. Where general purpose lubricatingoil is specified, but
unavailable,clean engine oil may be used as a satisfactory substitute.
b. Check the components to be lubricated for evidence of excessivewear and replace
them as necessary.
c. Remove all excess lubricants from components in order to prevent the collection of
dirt and sand in abrasivequantities capable of causing excessivewear or damage to bearing
surfaces.

2-80. APPLICATION OF OIL. Whenever specific instructions for lubrication of

mechanismsrequiring lubrication are not available,observe the followingprecautions:
a. Apply oil sparingly,never more than enough to coat the bearing surfaces.
b. Since the control cables are sufficiently coated by the manufacturer, additional
protection for the prevention of corrosion is unnecessary.
c. Squeeze the magneto cam follower felts at regular inspection periods. If oil appears
on fingers, do not add oil. If the felt is dry, moisten with light oil.

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CAUTION
Be careful not to add too much oil, because the excess will be
thrown off during operation and will cause pitting and
burning of the magneto points.

2-81. APPLICATIONGREASE. Care must be taken when lubricating bearingsand bearing

surfaces with a grease gun, to insure that gun is filled with new, clean grease of the grade
specified for the particular application before applying lubricant to the grease fittings.
a. Where a reservoiris not provided around a bearing, apply the lubricant sparinglyand
wipe off any excess.
b. Remove wheel bearings from the wheel hub and clean thoroughly with a suitable
solvent. When repacking with grease, be sure the lubricant enters the space between the
rollers in the retainer ring. Do not pack the greaseinto the wheel hub.
c. Use extra care when greasingthe constant speed propeller hub to avoidblowing the
clamp gaskets. Remove one grease fitting and apply grease to the other fitting until fresh
grease appearsat the hole of the removed fitting.

2-82. WINTERIZATION PLATE. For winter operations there is a winterization plate kit,
No. 763 828Vavailable. When the ambient temperature is 50°F or lessthe plate is installed on
the inlet opening of the oil cooler plenum chamber.
Whenthe plate is not being used it can be stowed on a bracket, provided for this purpose,
located on the oil cooler plenum chamber.
2-83. LUBRICATION CHARTS. A series of lubrication charts (starting with Figure 2-43)
depict numbered lubrication points and the tables therein list the component to be lubricated
along with the type of lubricant and frequency of lubrication.
The following special instructions, Note and Cautions apply when lubricating various
items of the aircraft.
a. Bearings and Bushings - Clean exterior with a dry type solvent before lubricating.
b. Lubrication Points - Wipe all lubrication points clean of old grease, oil, dirt, etc.,
before lubricating.

THIS SPACEINTENTIONALLYLEFT BLANK

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TABLE II-IX. RECOMMENDED ENGINE LUBRICATING OILS

Average Average Ambient Oil Inlet Temperatures

Grade Oil Air Temperature Desired Maximum

SAE 50 Above 60° F 180° F 245 ° F

(16 ° C) (82 ° C) (118 ° C)

SAE 40 30 ° F to 90 ° F 180° F 2450 F

(-1 ° C to 32 ° C) (82 ° C) (118 ° C)

SAE 30 0 ° F to 70 ° F 170 ° F 225 ° F

(-17 ° Cto 20 ° C) (77 ° C) (107 ° C)

SAE 20 Below 10° F 160° F 210 ° F

(12 ° C) (71 ° C) (99 ° C)

TABLE II-X. THREAD LUBRICANTS

TYPE OF LINE TYPE OF LUBRICANT

Brakes MIL-H-5606
Freon TT-A-580or MIL-T-5544,Anti-SeizeCompound
Fuel MIL-T-5544,Anti-Seize,Graphite Petrolatum
Landing Gear (Air Valve) 6PBParker
Oil MIL-G-6032,Lubricating Grease
(Gasolineand Oil Resistant)
Pitot and Static TT-A-580(JAN-A-669),Anti-SeizeCompound
(WhiteLead Base)

NOTE
Lubricate engine fittings only with the fluid contained in the particular lines.

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TABLE II-XI. SUMMARY OF RECOMMENDED LUBRICANTS USED

ON PA-28 SERIES AIRCRAFT

PREFERRED PRODUCT
LUBRICANT SPECIFICATION AND VENDOR

LUBRICATING OIL, GENERAL PURPOSE, LOW MIL-L-7870

TEMPERATURE

LUBRICATING OIL, AIRCRAFT RECIPRO- MIL-L-6082

CATING ENGINE (PISTON) GRADE AS
SPECIFIED
SAE 50 ABOVE 60°F AIR TEMP.
SAE 40 30 ° TO 90°F AIR TEMP.
SAE 30 0 ° TO 70°F AIR TEMP.
SAE 20 BELOW 10OF AIR TEMP.

HYDRAULIC FLUID PETROLEUM BASE MIL-H-5606

GREASE, AIRCRAFT AND INSTRUMENT, GEAR MIL-G-23827

AND ACTUATOR SCREW

GREASE, AIRCRAFT HIGH TEMPERATURE TEXACO MARFAK ALL

PURPOSEGREASE,
MOBIL GREASE 77
(OR MOBILUX EP2),
SHELL ALVANIA EP
GREASE 2

PARKER O-RING LUBRICANT

AERO LUBRIPLATE FISKE BROS.

OR REFINING CO.
MAG-1
FLUOROCARBON RELEASE AGENT DRY MS-122
LUBRICANT

GREASE - LUBRICATION GENERAL MI L-G-7711

PURPOSE AIRCRAFT

SILICONE, COMPOUND MIL-C-21567

GREASE, AIRCRAFT WIDE-TEMPERATURE MIL-G-81322 MOBIL GREASE 28
AERO SHELL GREASE 22

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COMPONENT LUBRICANT FREQUENCY

1. OLEO STRUT FILLER POINT MIL-H-5606 AS REQUIRED
2. UPPER TORQUE LINK BEARING MIL-G-23827 100 HRS
3. TORQUE LINK BUSHING MIL-L-7870 100 HRS
4. TORQUE LINK CONNECTING BUSHING MIL-G-23827 100 HRS
5. MAIN WHEEL BEARING TEXACO MARFAX ALL
PURPOSE GREASE OR
MOBIL GREASE 77
(OR MOBIL EP2
GREASE) 100 HRS
6. EXPOSED OLEO STRUT FLUOROCARBON RELEASE
AGENT DRY LUBRICANT
MS-122 100 HRS
7. BRAKE RESERVOIR MIL-H-5606 100 HRS

C333

the roller and cone. Do not pack grease in wheel

housing. Wheel bearings require cleaning and repacking
after exposure to an abnormal quantity of water.
2. Oleo struts and brake reservoir - Fill per Instructions on
unit or container or refer to service manual.

Figure 2-43. Lubrication Chart (Landing Gear, Main) PA-28-140,-150, -160, -180 and -235

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COMPONENT LUBRICANT FREQUENCY

1. OLEO STRUT FILLER POINT MIL-H-S606 AS REQUIRED
2. STEERING BELLCRANK PIVOT POINT MIL-L-7870 100 HRS
3. SHIMMY DAMPENER PIVOT POINT MIL-L-7870 100 HRS
4. TORQUE LINK ASSEMBLY MIL-L-7870 100 HRS
5. NOSE WHEEL BEARING TEXACO MARFAX ALL
PURPOSE GREASE OR
MOBIL GREASE 77
(OR MOBIL EP2
GREASE) 100 HRS
6. NOSE GEAR STEERING ROD END BEARINGS MIL-L-7870 100 HRS
7. BUNGEE SEAL (1974 MODELS AND UP) PARKER O-RING
LUBRICANT 100 HRS
8. EXPOSED OLEO STRUT FLUOROCARBON RELEASE
AGENT DRY LUBRICANT
MS-122 100 HRS
C334

SPECIAL INSTRUCTIONS

Nose wheel bearings Disassemble and clean with a dry

type solvent. Ascertain that grease is packed between
the roller and cone. Do not pack grease in wheel
housing. Wheel bearings require cleaning and repacking
after exposure to an abnormal quanity of water.
Oleo struts - Fill per instructions on unit or refer to
service manual.
Bungee - Lubricate springs if bungee Is disassembled.

Figure 2-45. Lubrication Chart (Landing Gear, Nose) PA-28-140,-150, -160, -180 and -235

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COMPONENT LUBR ICANT FREQUENCY

1. NOSE GEAR STRUT HOUSING GREASE FITTING MIL-G-23827 100 HRS

2. NOSE GEAR PIVOT POINT AND HYDRAULIC
CYLINDER ROD END MIL-L-7870 100 HRS
3. NOSE GEAR DOOR RETRACTION MECHANISM MIL-L-787 0 100 HRS
4. NOSE GEAR DOOR HINGES MIL-L-787 0 100 HRS
5. EXPOSED OLEO STRUT FLUOROCARBON RELEASE
AGENT DRY LUBRICANT
MS-122 100 HRS
6. NOSE WHEEL BEARINGS TEXACO MARFAX ALL
PURPOSE GREASE OR
MOBIL MOBIL GREASE
77 (OR MOBIL EP2
GREASE) 100 HRS
7. NOSE GEAR DRAG LINK ASSEMBLIES MIL-L-7870 100 HRS
8. NOSE GEAR TORQUE LINK ASSEMBLY AND
STRUT HOUSING MIL-G-23827 100 HRS
9. DOWNLOCK, ROLLER TENSION SPRING,
SHIMMY DAMPENER AND ALIGNING ROLLER
PIVOT POINTS MIL-L-787 0 100 HRS
10. STEERING BELL- NK PIVOT POINTS AND
ROD ENDS MIL-L-7870 100 HRS
11. NOSE GEAR OLEO STRUT FILLER POINT MIL-H-5606 AS REQUIRED
12. BUNGEE SPRING (1974 MODELS AND UP) MIL-G-7711 100 HRS
13. FIRE WALL BUNGEE SEAL (1974 MODELS AND UP) AERO LUBRIPLATE 100 HRS

1723

SPECIAL INSTRUCTIONS
1. Nose wheel bearings- Disassemble and clean with a
dry type solvent. Ascertain that grease Is packed
between the roller and cone. Do not pack grease In
wheel housing. Wheel bearings require cleaning and
repacking after exposure to an abnormal quantity of
water.
2. Oleo struts - Fill per Instructions on unit or refer to
service manual.

Figure 2-46. Lubrication Chart (Landing Gear, Nose) PA-28R-180and -200

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- CA UTION -

Do not lubricatecontrol wheelshaft or bushing. Cleanonly using

alcohol or other suitable solvent.

COMPONENT LUBRICANT FREQUENCY

1. AILERON HINGE PINS MIL-L-7870 100 HRS

2. FLAP HINGE BEARINGS MIL-L-7870 100 HRS
3. STABILATOR HINGE PINS MIL-L-787 0 100 HRS
4. RUDDER HINGE BEARINGS MIL-L-7870 100 HRS
5. CONTROL CABLE PULLEYS MIL-L-787 100 HRS
6. TRIM CONTROL WHEELOR OVERHEAD CRANK MIL-L-7870 100 HRS
7. O-RING CONTROL SHAFT BUSHING PARKER O-RING **
LUBRICANT AS REQUIRED
8. TEE BAR PIVOT POINT MIL-L-7870 100 HRS
9. CONTROL COLUMN CHAIN MIL-L-7870 500 HRS
10. CONTROL COLUMN FLEX. JOINTS AND SPROCKET MIL-L-787 0 100 HRS
11. STABILATOR CONTROL MIL-L-787 0 100 HRS

SPECIAL INSTRUCTIONS

** Disassemble "0" ring retainer plates

from Instrument panel; lubricate "0"
ring and reassemble (on 1.125 Inch dia.
shaft only).

11
SPECIAL INSTRUCTIONS

Aileron hinges with teflon sleeves should not be lubricated.

Aileron hinges without teflon sleeves should first be cleaned
with a dry type solvent then lubricated with MIL-L-7870.

Figure 2-47. Lubrication Chart (Control System)

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COMPONENT LUBRICANT FREQUENCY

1. RUDDER TUBE BEARING BLOCKS FLUOROCARBON RELEASE
AGENT DRY LUBRICANT
MS-122 100 HRS
2. TOE BRAKE CYLINDER ATTACHMENTS MIL-L-7870 100 HRS
3. RUDDER TUBE CONNECTIONS MIL-L-7870 100 HRS
4. BRAKE ROD ENDS MIL-L-7870 100 HRS
937

1608 1720

SKETCH
A PA-28-140,150,-160,-180
AND-235 SKETCH
A PA-28R-180AND.200

Figure 2-49. Lubrication Chart (Control System) (cont.)

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COMPONENT LUBRICANT FREQUENCY

1. RUDDER ARM CABLE ENDS MIL-L-7870 100 HRS

2. STABILATOR TRIM SCREW AERO LUBRIPLATE,
FISKE BROS. RE-
FINING CO. 100 HRS
3. STABILATOR SCREW/TAB LINKS MIL-L-787 0 100 HRS
4. STABILATOR HINGE POINTS MIL-L-7870 100 HRS
5. RUDDER TRIM ASSEMBLY MIL-L-7870 100 HRS

937

1810
938

SKETCH A SKETCH B

Figure 2-50. Lubrication Chart (Control System) (cont.)

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COMPONENT LUBRICANT FREQUENCY

1. DOOR HINGES MIL-L-7870 100 HRS
2. DOOR SEALS FLUOROCARBON RELEASE
AGENT DRY LUBRICANT
MS-122 50 HRS
3. DOOR LATCH MECHANISMS MIL-L-7 870 500 HRS
4. SEAT TRACK ROLLERS, STOP PINS AND REAR SEAT AERO LUBRIPLATE
LEG RETAINER (CLIP AND CAM)
OR
MAG-1 100 HRS

1744

SPECIAL INSTRUCTIONS

Apply fluorocarbon dry lubricant to door seals at least once a

month to prevent the seal from sticking, and improve sealing
characteristics.

Figure 2-51. Lubrication Chart (Cabin Door, BaggageDoor and Seat)

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 0

0
ENGINE
SUMP

FILTERS
a
0

,
A
0

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COMPONENT LUBRICANT FREQUENCY

1. DIAPHRAGM SHAFT AND BUSHING MIL-L-7870 ABOVE

20 F
MIL-C-21567 BELOW
20 F 100 HRS
2. BACK-UP EXTENDER LINKS AND CONTROL ARM
PIVOT POINTS MIL-L-7870 100 HRS
3. BACK-UP EXTENDER SPRING ATTACHMENT POINTS MIL-L-7870 100 HRS
4. FUEL SELECTOR LINKAGE MIL-L-7870 100 HRS
5. FUEL SELECTOR VALVE COVER PLATE FLUOROCARBON RELEASE
AGENT DRY LUBRICANT
MS-122 100 HRS

6. ACTUATING RODCONTACT POINTS AERO LUBRIPLATE OR MAG-1 100 HRS

A103 1673
PA-28R-180 & 200

PA-28-235

SPECIAL INSTRUCTIONS

1. Diaphragm shaft and bushing - soft film silicon

compound (MIL-C-21567) Is recommended for use
when operating at temperatures below 200 F.
2. Fuel selector valve - Lubricate area where detent ball
moves across cover plate (on external detent valves
only).

Figure 2-53. Lubrication Chart (Back-UpExtender and Fuel Selector)

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LUBRICANT FREQUENCY
COMPONENT
MIL-L-7870 100 HRS
1. CONDENSER HINGE AND ACTUATORS 500 HRS
TRANSMISSION MIL-G-23827
2. CONDENSER DOOR ACTUATING

1778

SPECIAL INSTRUCTIONS

Transmission to be 1/2 full of grease. Apply grease during

assembly and lubricate transmission ball nut and screw with
MIL-G-23827 grease.

Figure 2-54. Lubrication Chart (Air Conditioning Condenser)

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SECTIONm

INSPECTION

Aerofiche
Grid No.

3-1 Introduction ............................................................................................... 1F7

3-2 Recommended Lubricants................................................................... F7
3-3 Inspection Periods ..................................................................................... 1F7
3-4 Inspection Requirements ................................................... 1f7
3-5 Preflight Check..................................................................1F8
3-6 Overlimits Inspection ........................................................ 1F9
3-7 Special Inspections...........................................................1F9
3-8 Programmed Maintenance ...............................................1F9
3-9 Inspection of Exhaust System ......... . ....................... 1F9
3-10 Field Check of PA-28R-180, -200 Muffler Assembly ...... F13
3-11 Inspection of Control W heels 1F15.................................. 1F15
I 3-1 la Elevator Control Cable Inspection .................................... IF16
3-12 Inspection of Flap Control Cable Attachment Bolt........... F16
3-13 Inspection of Induction Air Inlet Duct and Alternate
Heat Duct ................................................................. F17
3-13a Inspection of Seals at Landing Light on Air Filter
Retaining Plate ........................................................1F17
3-14 Inspection of Main Landing Gear Torque Links ............... 1F17

Interim Revision: February 15, 1995

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SECTION III

INSPECTION

3-1. INTRODUCTION. This section provides instructions for conducting inspections.

These inspections are described in paragraphs 34 and 3-5. Repair or replacement
instructions for those components found to be unserviceable at inspection may be found in
the section covering the applicable aircraft system.

CAUTION

When working on engines, ground the magneto primary

circuit before performing any operation.

3-2. RECOMMENDED LUBRICANTS. Refer to Recommended Lubricants. Section II for

Lubrication Servicing Instructions.

3-3. INSPECTION PERIODS.

3-4. INSPECTION REQUIREMENTS. Required inspection procedures are listed in Table

1ll-1 (PA-28-140; PA-28-150, -160. -180: PA-28-235) or ll-11 (PA-28R). The inspection
procedure is broken down into nine major groups which are Propeller. Engine. Cabin,
Fuselage and Empennage. Wing. Landing Gear, Float Group. Operational Inspection and
General. The first column in each group lists the inspection or procedure to be performed. The
second column is divided into four columns indicating the required inspection intervals of
50 hours. 100 hours. 500 hours. and 1000 hours. Each inspection or operation is required at
each of the inspection intervals as indicated by a circle (O). If an item is not entirely accessible
or must be removed. refer to the applicable section of this manual for instructions on how to
gain access to remove the item. When performing inspections, use forms furnished by the Piper
Factory Service Department. available through Piper Dealers or Distributors.

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NOTE
In addition to inspection intervals required in Table III-I or
III-II, preflight check must be performed as described in
Paragraph3-5.
3-5. PREFLIGHT CHECK. The airplane must be given a thorough preflight and
walk-around check. The pilot and/or mechanic must include the preflight check as a normal
procedure necessary for the safe operation of the aircraft. Refer to the Pilot's Operating
Manual for a listing of items that must be checked.

THIS SPACEINTENTIONALLYLEFT BLANK

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INSPECTION

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3-6. OVERLIMITS INSPECTION. If the airplane has been operated so that any of its
components have exceeded their maximum operational limits, check with the appropriate
manufacturer.

3-7. SPECIAL INSPECTIONS.The special inspections given in the followingparagraphs,

supplement the scheduled inspections as outlined in the Inspection Report, Table III-I or
III-II, to include inspection of items which are required to be examined at intervals not
compatible with airframe operating time or airframe inspection intervals. Typical of this
type are:
a. Inspection is required because of special conditions or incidents that arise, and
because of these conditions or incidents, an immediate inspection would be required to
insure further safe flight.
b. Inspection of airframe or components on a calendar basis. This type of inspection
could often be accomplishedduring the nearest scheduled inspection.
c. Specific definitive inspection on engines based strictly upon engine operating time.
d. Those inspections not completely covered in other sections of this manual, but
outlined in the Inspection Report and must be explainedin more detail to givea clearer and
complete inspection.

3-8. PROGRAMMEDMAINTENANCE.The programmed maintenance was designed to

permit the utilization of the aircraft, by scheduling inspectionsthrough the use of a planned
inspection schedule. ProgrammedMaintenance schedulesare availablefrom ServiceSales.

3-9. INSPECTION OF EXHAUST SYSTEM. (Refer to Figure 3-1 thru 3-3.) The entire
exhaust system, including heat exchange shroud, muffler, muffler baffles, stacks and all
exhaust connections must be rigidly inspected at each 100 hour inspection. The possibility
of exhaust system failure increases with use. It is recommended that the system be checked
more carefully as the number of hours increase, therefore inspection at the 700 hour period,
that the exhaust system has been in use, would be more critical than one in the 100 hour
period. The system should also be checked carefully before winter operation when the cabin
heat will be in use.

NOTE
It is recommended that all PA-28 airplanes be fitted with a
new muffler at or near the 1000 hour period of which the
muffler has been in use.

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A950
INSPECT
FOR
CRACKS
INTHESE
AREAS

INSPECT
FORCRACKS
INTHIS
AREA

Figure 3-1. Typical Muffler Fatigue Areas

Removal of the tail pipe and stacks is required for inspectionof the muffler
baffle. Remove or loosen all exhaust shields, carburetor and cabin heat muffs,
shrouds, heat blankets, etc., as required to permit inspection of the complete
system. Perform the necessary cleaning operations and inspect all external sur-
faces for dents, cracks and missing parts. Pay particular attention to welds,
clamps, supports and support attachment lugs, slip joints, stack flanges and
gaskets. Inspect internal baffle or diffusers. Any cracks, warpage or severe
oxidation are cause for replacement of the muffler.
If any component is inaccessible for a thorough visual inspection, accom-
plish one of the following:
a. Accomplish a submerged pressure check of the muffler and exhaust stack
at 2 psi air pressure.
b. Conduct a ground test using a carbon monoxide indicator by heading the
airplane into the wind, warming the engine on the ground, advancing the throttle
to full static RPM with cabin heat valves open, and taking readings of the heated
airstream inside the cabin at each outlet (including rear seat heat outlet, if in-
stalled). Appropriate sampling procedures applicable to the particular indicator
must be followed. If carbon monoxide concentration exceeds .005 percent or if
a dangerour reading is obtained on an indicator not calibrated in percentages,
the muffler must be replaced.

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 PIPER CHEROKEE SERVICE MANUAL

965

PA-28-140;PA-28-150,.160, -180,SERIAL
NOS.28-1 TO 28-1760INCL.

981

ALL WELDS AS
INDICATEDBY ARROW

PA-28-150,.160,SERIALNOS.28-1761TO
28-4377INCL.
PA-28-180,SERIALNOS.28-1761ANDUP.

Figure 3-2. Exhaust System Inspection Points

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968

ALL WELDS AS INDICATED

BY ARROW

PA-28-235

1718

OUTER

INNER BAFFLE

ALL WELDS AS INDICATEDBY ARROW

PA-28R

Figure 3-3 Exhaust System Inspection Points

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3-10. FIELD CHECK OF PA-28R-180 and -28R-200 MUFFLER ASSEMBLIES. (Refer

to Figure 3-4.)
a. Remove end clips.
b. Check for any movement between the heater muff end plates and the muffler pipes in
the directions shown on Figure 3-4. If there is no movement, the muffler assembly is accept-
able.
c. If there is any movement,remove the muffler assemblyand inspect all parts, especial-
ly for abnormal wear on muffler shroud. Rework the end plates to give a .03" min. gap after
assembly.
d. Prior to reassembly, the two top screw holes in the upper shroud assembly should be
slotted as necessary to allow the screwsto be installed without causing any deformations of
the skin.
e. Install, but do not tighten, the two screws which hold the lower shroud assembly in
place.
f. Install the end strap clamps and torque them from 25 to 30 inch-pounds before in-
stalling the two top screws which hold the top shroud assembly in place.
g. Tighten the two lower screws and then the two upper screws.
h. Check the muffler for tightness after assembly.

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INSPECTION
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 PIPER CHEROKEE SERVICE MANUAL

3030

TOP SCREWS(ADDAFTER
STRAPCLAMPSARE TORQUED)

CHECKFORANY MOVEMENT
OFTHEENDPLATESIN
THESEDIRECTIONS .03" MINIMUMGAP
BETWEENENDPLATES
AFTERASSEMBLY

1. END PLATES
2. END CLIPS
3. END

Figure 3-4. Exhaust System Installation, PA-28R-180, -200

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913

Figure 3-5. Control Wheel Inspection Points

3-11. INSPECTIONOF CONTROLWHEELS. (Refer to Figure 3-5.)

a. This inspection should be accomplished at the next 100 hour or annual inspection
and repeated at each 100 hour or annual inspection thereafter.
b. It is required to detect and replace any cracked control wheels.
c. Inspect the front, bottom and back of the control wheels using an ordinary (3x)
magnifyingglass and light.

NOTE
Do not confuse any surface irregularitiesor mold marks with
actual cracks. (Refer to Figure 3-5.)
CAUTION
No solvents or dye penetrant should be used to perform this
inspection.

d. Any control wheel assemblies which are found defective should be replaced
immediately. Refer to PA-28 Parts Catalog for applicable part numbers.

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3-1la. ELEVATOR CONTROL CABLE INSPECTION. (Refer to Paragraph 4-57a.)

Special care should be taken to inspect elevator control cables beneath aft baggage compart-
ment floor. Add access panels per instructions in Paragraphs 4-57a and 4-79 to ease this inspection.

MOUNTINGBRACKET

I
EMERGENCYGEAR LEVER
BUSHING INSPECTTHIS BOLT
(SEE LATESTREVISIONOF AT EACH100 HOURS
PIPERSERVICEBULLETIN965)

Figure 3-6. Flap Control Cable Attachment Bolt Inspection

3-12. INSPECTION OF FLAP CONTROL CABLE ATTACHMENT BOLT. (Refer to

Figure 3-6.)
a. This inspection should be accomplished at each 100 hours time in service.
b. The inspection is required to detect any possible wear and replacement of
attachment bolt, should evidence of wear be detected.
c. Remove the royalite flap or flap/trim cover.
d. On aircraft having the flap handle only, proceed as follows:
1. Remove flap handle mounting bracket attachment bolts.
2. Raise flap handle and bracket assembly to gain access to the control cable
attachment bolt.
e. On aircraft having the flap handle and trim wheel mounted together, proceed as
follows:
1. Loosen the trim wheel attachment bolt.
2. Remove the trim wheel bracket attachment bolts and remove bracket from top
of tunnel.
3. Remove flap handle mounting bracket attachment bolts and raise handle and
bracket assembly to gain access to control cable attachment bolt.
f. Remove and inspect cable attachment bolt for possible wear. Should wear be
detected, replace bolt with new AN23-11 clevis bolt.
g. Reinstall all parts that were removed and make appropriate log book entry.

Interim Revision: February 15, 1995 INSPECTION

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 PIPER CHEROKEE SERVICE MANUAL
3-13. INSPECTION OF INDUCTION AIR INLET DUCT AND ALTERNATEHEAT DUCT.
This inspection should be accomplished at the next 25 hours of operation and at each subsequent
100 hours of operation thereafter. This inspection is a visual inspection of the external surface of
the subject ducts and does not require duct removal and replacement to accomplish the inspection.
Inspect the ducts for evidence of deterioration as follows:
a. Inspect the external surface of the ducts for loose or broken strings.
b. Inspect the ducts for loose or displaced supporting wire.
c. Inspect the ducts for signs of wear or perforation.
Should any of the above conditions exist, remove and replace the affected duct or ducts prior to
the next flight. Refer to PA-28 Cherokee Parts Catalog for replacement part numbers.
3-13a. INSPECTION OF SEALS AT LANDING LIGHT ON AIR FILTER RETAINING PLATE.
As part of the inlet air, the landing light is retained at the center of the air filter by a retaining plate.
Unfiltered air is blocked by seals around the landing light and retaining ring. Piper issued Service
Bulletin 975 (or latest revision) which requires inspection of the seals and installation of a new sup-
port bracket and new seals. This section requires accomplishment of Piper Service Bulletin 975 (or
latest revision) and an initial inspection of landing light seals, with a recurring inspection annually,
or at each 100 hours. Seals should be inspected for aging, weather, checking, cracks, or looseness.
Replace as required.
3-14. INSPECTION OF MAIN LANDING GEAR TORQUE LINKS. (Refer to Figure 3-7.)
This inspection should be accomplished within the next 100 hours and at intervals not to exceed
500 hours of operation from previous inspection.
The main landing gear torque links should be inspected for possible cracks which may appear
on the areas referenced in Figure 3-7. These cracks may form just behind the large boss which
attaches to the strut or to the wheel, and in the center of the link progressing toward the edge. The
following steps should be used to make this inspection:
a. Remove paint from the area to be inspected, using acetone, MEK, or any suitable commer-
cial paint remover which does not contain wax.
b. Allow the cleaned part to dry thoroughly.
c. If cracks do not readily appear, inspect by one of the following methods:
1. 10X magnifying glass.
2. Dye check or other penetrant inspection.
d. Should cracks be detected, replace defective torque links prior to further flight.
e. If no cracks appear, make proper log book entry and return aircraft to service.

INSPECTFOR CRACKS
(Referto the latestrevision
of PiperServiceLetter760.)

CHECK FOR
POSSIBLECRACKS
ON BOTHSIDES
OF TORQUELINKS.

Figure 3-7. Inspection of Main Landing Gear Torque Links

Interim Revision: February 15, 1995 INSPECTION

1F17
 PIPER CHEROKEE SERVICE MANUAL

TABLE III-I. INSPECTION REPORT

PA-28-140; PA-28-150, -160, -180; PA-28-235

NOTE
Perform inspection or operation at each of the inspection inter-
vals as indicated by a circle (O).

Nature of Inspection Inspection time (hrs)

50 100 500 1000
A. PROPELLER GROUP

1. Inspect spinner and back plate. ..................................................................................... 0 0 0 0

2. Inspect blades for nicks and cracks ............................................................................... 0 0 0 0
3. Inspect for grease and oil leaks. .................................................................................... 0 0 0 0
4. Lubricate propeller. (Refer to Service Manual Section VIII of VIIIA) ......................... 0 0 0 0
5. Inspect spinner mounting brackets ................................................................................ 0 0 0
6. Inspect propeller mounting bolts and safety. (Check torque if safety is broken).......... 0 0 0
7. Inspect hub parts for cracks and corrosion..................................................................... 0 0 0
8. Rotate blades of constant speed propeller and check for tightness in hub pilot tube. 0 0 0
9. Remove constant speed propeller; remove sludge from propeller and crankshaft. 0 0
10. Inspect complete propeller and spinner assembly for security, chafing, cracks,
deterioration, wear, and correct installation............................................................. 0 0 0
11. Overhaul propeller. (See Note 21)..................................................................................

B. ENGINE GROUP.

NOTE: Read Note 5 prior to completing this inspection group.

CAUTION: Ground Magneto Primary Circuit before working on engine.
1. Remove engine cowl and inspect for damage (See Note 19)......................................... 0 00 0
2. Clean and inspect cowling for cracks, distortion, and loose or missing fasteners
(See the latest revisionof Piper S/L 796) (See Note 23) ............................................... 0 00
3. Drain oil sump. (See Note 6)......................................................................................... 0 0 00
4. Clean suction oil strainer at oil change. (Inspect strainer for foreign particles) ........... 0 0 00
5. Clean pressure oil strainer or change full flow (cartridge type) oil filter
element. (Inspect strainer or element for foreign particles).................................... 0 0 00
6. Inspect oil temperature sender unit for leaks and security ............................................ 0 00
7. Inspect oil lines and fitting for leaks, security, chafing, dents and cracks.
(See Note 8)............................................................................................................. 0
8. Clean and inspect oil radiator cooling fins..................................................................... 0
9. Remove and flush oil radiator. ....................................................................................... 0
10. Fill engine with oil per lubrication chart in Service Manual.......................................... 0
11. Clean engine................................................................................................................... 0
CAUTION: Do not contaminate the vacuum pump with cleaning fluid.
(Ref: Latest revision of Lycoming Service Instruction No. 1221.)

Interim Revision: February 15, 1995 INSPECTION

1F18
 PIPER CHEROKEE SERVICE MANUAL

TABLE 11l-1. INSPECTION REPORT (cont)

PA-28-140; PA-28-150, -160, -180; PA-28-235

Inspection Time (hrs)

Nature of Inspection
50 100 500 1000
B. ENGINE GROUP (cont.)
12. Inspect condition of spark plugs (Clean and adjust gap as required, adjust
per the latest revision of Lycoming Service Instruction No. 1042)
(See N ote 15) ...............................................
NOTE: If fouling of spark plugs has been apparent, rotate bottom plugs
to upper plugs.
13. Inspect spark plug cable leads and ceramics for corrosion and deposits ... O 0 0
14. Check cylinder compression (Ref: AC 43.13-lA) ....................... O 0 0
15. Inspect cylinders for cracked or broken fins ........................... O 0 0
16. Inspect rocker box covers for evidence of oil leaks. If found, replace
gasket; torque cover screws 50 inch-pounds (See Note 13) ............... 0 O 0 0
NOTE: Lycoming requires a Valve Inspection be made at completion of
every 400 hours of operation. (See Note 12)
17. Inspect ignition harness and insulators (high tension leakage and
continuity) ........................................................ O 0 0
18. Inspect magneto points for condition and proper clearance (Refer to
Service Manual Section VIII or VIIIA) .............................. O 0 0
19. Inspect magneto for oil leakage ...................................... O 0 0
20. Inspect breaker felts for proper lubrication ............................ O 0 0
21. Inspect distributor block for cracks, burned areas or corrosion and
height of contact springs ........................................... 0 0
22. Check magnetos to engine timing .................................... O 0 0
23. Overhaul or replace magnetos (See Note 7)............................
24. Remove air filter and tap gently to remove dirt particles (Replace
as required, refer to latest revision of Piper Service Bulletin 975, as applicable.). 0 O 0 0
25. Drain carburetor and clean inlet line fuel'strainer ...................... 0 O 0 0
26. Inspect condition of carburetor heat air door and box (See Note 14) ..... 0 O 0 0
27. Inspect vent lines for evidence of fuel or oil seepage .................... 0 O 0 0
28. Inspect intake seals for leaks and clamps for tightness .................. 0 O 0 0
29. Inspect all air inlet duct hoses (Replace as required) .................... 0 O O O
30. Inspect condition of flexible fuel lines ................................ O O O
31. Replace flexible fuel lines (See Note 7) ................................
32. Inspect fuel system for leaks (See Note 16) ............................ 0 O 0 O
33. Clean screens in electric fuel pump(s) and check operation
(engine and electric) ................................................ 0 O O 0
34. Overhaul or replace fuel pumps (engine driven) (See Note 7) ...........
35. Remove and clean fuel filter bowl and screen (Clean at least every
90 days) (PA-28-140, -150, -160, -180) ................................ 0 O O O
36. Inspect vacuum pump and lines ..................................... O O 0
37. Overhaul or replace vacuum pump (See Note 7) .......................
38. Inspect throttle, carburetor heat, mixture and propeller governor controls
for security, travel and operating conditions (Refer to the latest revision
of Piper Service Bulletin No. 448 and Service Letter No. 747) ....... O O 0
39. Inspect exhaust stacks, connections and gaskets (Refer to Service
Manual, Section III) (Replace gaskets as required) ..................... O O 0
40. Inspect muffler, heat exchange and baffles (Refer to Service Manual,
Section III) ....................................................... 0 0 0

Interim Revision:February 15, 1995 1F19 INSPECTION

 PIPER CHEROKEE SERVICE MANUAL

TABLE III-I. INSPECTION REPORT (cont)

PA-28-140; PA-28-150, -160, -180; PA-28-235

Nature of Inspection Inspection time (hrs)

50 100 500 1000
A. ENGINE GROUP (cont.)
41. Check recommended time for replacement of muffler per Service Manual,
Section III ...................................................................................................................... 0 O 0
42. Inspect breather tube for obstructions and security ....................................................... O O O
43. Inspect crankcase for cracks, leaks, and security of seam bolts .................................... O O O
44. Inspect engine mounts for cracks and loose mountings................................................. O O O
45. Inspect all engine baffles .............................................................................................. O O O
46. Inspect all wiring connected to the engine or accessories............................................. O O O O
47. Inspect rubber engine mount bushings for deterioration (Replace as required) ............ O O O
48. Inspect fire wall seals ..................................................................................................... O O O
49. Inspect condition and tension of alternator drive belt (Refer to Service Manual O O
Section XI) .................................................................................................................... O O O
50. Lubricate alternator idler pulley (if installed) per lubrication chart in Service Manual O O O
Section II ....................................................................................................................... O O o
51. Inspect condition of alternator and starter ..................................................................... O O O
52. Inspect security of alternator mounting ......................................................................... O O O
53 Check air conditioning compressor oil level (See Note 9) ............................................
54. Inspect condition of compressor belt and tension (Refer to Service Manual Section
XIV) .............................................................................................................................. O O O
55. Inspect compressor clutch security and wiring (See Note 10) ...................................... O O O
56. Inspect security of compressor mounting ...................................................................... O O O
57. Check fluid in brake reservoir (Fill as required) ........................................................... O O O O
58. Lubricate all controls (Refer to Service Manual Section II) ......................................... O O O
59. Overhaul or replace propeller governor (See Note 7) ....................................................
60. Complete overhaul of engine or replace with factory rebuilt (See Note 7) ..................
61. Reinstall engine cowl .................................................................................................... O O O O
C. CABIN GROUP
1. Inspect cabin entrance, door and windows for damage, operation and security............ O O O
2. Inspect upholstery for tears ........................................ ................................................... O O0
3. Inspect seats, seat belts, security brackets and bolts ......................................................
O O O
4. Check trim operation (See Note 17)...................................... .................................. O O O
5. Inspect rudder pedals...................................................................................................... O O O
6. Inspect parking brake and brake handle for operation and cylinder leaks. .................... O O O
7. Inspect control wheels, column, pulleys and cables ...................................................... O O O
8. Inspect flap control cable attachment bolt...................................................................... O O
9. Inspect landing, navigation, cabin and instrument lights. (See latest revision of Piper
Service Bulletin 975 if the landing light is located in the air filter)............................... O O O O
10. Inspect instruments, lines and attachments (See the latest revision of Piper Service
Bulletin No. 582) ........................................................................................................... O O O
11. Inspect gyro operated instruments and electric turn and bank (Overhaul or replace
as required)................................................. ........................................ ............................ O O O
12. Replace filters on gyro horizon and directional gyro or replace central air filter .........
O O O
13. Clean or replace vacuum regulator filter ....................................................................... O O O
Interim Revision: February 15, 1995 INSPECTION
1F20
 CHEROKEESERVICE MANUAL

TABLEIII-I. INSPECTIONREPORT (cont)

PA-28-140;PA-28-150,-160,-180; PA-28-235

Inspection Time (hrs)

Nature of Inspection
50 100 500 1000
C. CABIN GROUP (cont)
14. Inspect altimeter (Calibrate altimeter system in accordance with
FAR 91.170 if appropriate) ......................................... O 0 0
15. Check operation of fuel selector valve (See Note 18).................... O 0 0
16. Check operation of fuel drain (PA-28-235) ............................ O 0 0
17. Inspect condition of heater controls and ducts ......................... O 0 0
18. Inspect condition and operation of air vents ........................... o 0 0
19. Inspect condition of air conditioning ducts ............................ O 0 0
20. Remove and clean air conditioning evaporator filter .................... O 0 0
D. FUSELAGE AND EMPENNAGE GROUP
1. Remove inspection plates and panels ................................. O O O
2. Inspect baggage door, latch and hinges for operation and security ........ O O O
3. Inspect battery, box and cables (Inspect at least every 30 days. Flush
box as required and fill battery per instructions on box) ................ O O 0 0
4. Inspect electronic installation ........................................ O 0 0
5. Inspect bulkheads and stringers for damage ........................... O 0 0
6. Inspect antenna mounts and electric wiring............................ O 0 0
7. Inspect air conditioning system for freon leaks ......................... o 0 0
8. Check freon level in sight gauge of receiver-dehydrator (Refer to
Service Manual, Section XIV........................................ 0 O 0 0
9. Inspect air conditioning condenser air scoop rigging (Refer to Service
Manual, Section XIV) .............................................. 0 O 0 0
10. Inspect fuel lines, valves, and gauges for damage and operation .......... o 0 0
11. Clean screens in fuel pumps (PA-28-235only) ......................... O 0 0
12. Inspect fuel valve drain lever cover for security and door for proper
operation (PA-28-235 only) ......................................... 0 o 0 0
13. Remove, drain and clean fuel strainer bowl and screen located in bottom
of selector valve (Drain and clean at least every 90 days) (PA-28-235)..... 0 o 0 0
14. Inspect security of all lines .......................................... O 0 0
15. Inspect vertical fin and rudder surfaces for damage ..................... o 0 0
16. Inspect rudder hinges, horn and attachments for damage and operation ... o 0 0
17. Inspect rudder control stop to insure stop has not loosened and
locknut is tight .................................................... 0
18. Inspect vertical fin attachments ...................................... 0 O 0
19. Inspect rudder hinge bolts for excess wear (Replace as required) ......... 0 O 0
20. Inspect stabilator surfaces for damage ................................ 0
O O O
21. Inspect stabilator, tab hinges, horn and attachments for damage and O
operation ......................................................... 0 0 0
22. Inspect stabilator control stops to insure stop has not loosened and
locknut is tight .................................................... O
23. Inspect stabilator attachments (see latest Piper ServiceBulletin856) ...... 0 0 0

Revised: 8/3/81
Interim Revision: 5/6/87 INSPECTION
IF21
 PIPER CHEROKEE SERVICE MANUAL

TABLE III-I. INSPECTION REPORT (cont)

PA-28-140; PA-28-150, -160, -180; PA-28-235

Nature of Inspection Inspection time (hrs)

D. FUSELAGE AND EMPENNAGE GROUP (cont.) 50 100 5001000

24. Inspect stabilator and tab hinge bolts and bearings for excess wear (Replace as
required) ........................................................................................................................ 0 0 0
25. Inspect stabilator trim mechanism.................................................................................. 0 0 0
26. Inspect aileron, rudder, stabilator, stabilator trim cables, turbuckles, guides and 0 0 0
pulleys for safety, damage and operation (See Note 24)................................................ 0 0 0
27. Check all cable tensions (use tensiometer, see Note 20)................................................ 0 0 0
28. Clean and lubricate stabilator trim drum screw ............................................................ 0 0
29. Clean and lubricate all exterior needle bearings ........................................................... O
30. Lubricate per lubrication chart in Service Manual......................................................... O O O O
31. Inspect rotating beacon for security and operation ....................................................... 0 0 0
32. Inspect security of Autopilot bridle cable clamps (See Note 11) .................................. 0 0 0
33. Inspect all control cables, air ducts, electrical leads, lines, radio antenna leads and
attaching parts for security, routing, chafing, deterioration, wear and correct
installation ..................................................................................................................... 0 0 0
34. Inspect E.L.T. installation and condition of battery and antenna (See the latest
revision of Piper S/L No. 820) ....................................................................................... 0 0 0
35. Reinstall inspection plates and panels............................................................................ 0 0 0

E. WING GROUP
1. Remove inspection plates and fairings .......................................................................... O 0 0
2. Inspect surfaces and tips for damage, loose rivets, and condition of walk-way ............ O 0 0
3. Inspect aileron hinges and attachments ....................................................................... o O O
4. Inspect aileron control stops to insure stop has not loosened and lock nut is tight........ O
5. Inspect aileron cables, pulleys and bellcranks for damage and operation ..................... O 0 0
6. Inspect flaps and attachments for damage and operation .............................................. O 0 0
7. Inspect condition of bolts used with hinges (Replace as required)................................ O 0 0
8. Lubricate per lubrication chart in Service Manual (Section II) .................................... 0 0 0 0
9. Inspect wing attachment bolts and brackets (See Note 18) ........................................... O 0 0
10. Inspect fuel tanks and lines for leaks, water and contamination (See Note 18)............. O 0 0
1 . Fuel tanks marked for capacity ..................................................................................... O 0 0
12. Fuel tanks marked for minimum octane rating .............................................................. O O O
13. Inspect fuel cell vents (See Note 18) ............................................................................. O O O
14. Inspect all control cables, air ducts. electrical leads, lines and attaching parts for
security, routing, chafing, deterioration, wear and correct installation .......................... 0 0 0
15. Reinstall inspection plates and fairings .......................................................................... 0 0 0

Interim Revision: February 15, 1995 INSPECTION

1F22
 `
PIPER CHEROKEE SERVICE MANUAL

TABLE 1ll-1. INSPECTION REPORT (cont)

PA-28-140: PA-28-150, -160. -180; PA-28-235

Inspection Time (hrs)

Nature of Inspection
50 100 500 1000
F. LANDING GEAR GROUP

1. Inspect oleo struts for proper extension per Service Manual (Check
fluid level as required) .............................................. O O 0 0
2. Inspect nose gear steering control and travel ........................... O 0 0
3. Inspect wheels for alignment ........................................ O 0 0
4. Put airplane on jacks ............................................... O 0 0
5. Inspect tires for cuts. uneven or excessive wear and slippage ............. O 0 0
6. Remove wheels, clean, check and repack bearings ...................... O 0 0
7. Inspect wheels for cracks, corrosion and broken bolts................... O 0 0
8. Check tire pressure per Service Manual ............................... O O 0 0
9. Inspect brake lining and disc for condition and wear ................... O 0 0
10. Inspect brake backing plates for condition and wear .................... O 0 0
11. Inspect brake lines ................................................. O O 0
12. Inspect shimmy dampener ......................................... O 0 0
13. Inspect gear forks for damage ....................................... O 0 0
14. Inspect oleo struts for fluid leaks and scoring .......................... O 0 0
15. Inspect gear struts, attachments, torque links, and bolts for condition
and security ....................................................... O 0 0
16. Inspect all hydraulic lines, electrical leads. and attaching parts for
security, routing, chafing. deterioration. wear and correct
installation ........................................................ O 0 0
17. Lubricate per lubrication chart in Service Manual...................... O O 0 0
18. Remove airplane from jacks ......................................... O 0 0

G. FLOAT GROUP

1. Inspect float attachment fittings ...................... O 0 0

2. Inspect floats for damage ........................... O 0 0
3. Inspect pulleys and cables........................... O 0 0

H. OPERATIONAL INSPECTION

1. Check fuel pump and fuel tank selector (For PA-28-235. See the latest
revision of Piper Service Bulletin No. 519) ............................ 0 O 0 0
2. Check fuel quantity, pressure and flow readings ...... ................. 0 O O O
3. Check oil pressure and temperature .................................. 0 0 0 O
4. Check alternator output ............................................ 0 O 0
5. Check manifold pressure ................... .................. 0 0 0 O
6. Check alternate air................................................. 0 0 0 O
7. Check parking brake ............................................... 0 0 0 O
8. Check vacuum gauge ............................................... 0 0 0 O
9. Check gyros for noise and roughness ................................. 0 0 0 O
10. Check cabin heater operation........................................ 0 0 0 O

Reissued: 1 15 81 1F23 INSPECTION

1F23
 PIPER CHEROKEE SERVICE MANUAL

TABLE 111-I. INSPECTION REPORT (cont)

PA-28-140: PA-28-150. -160. -180: PA-28-235

Inspection Time (hrs)

Nature of Inspection
50 100 500 1000
H. OPERATIONAL INSPECTION (cont)

II. Check magneto switch operation .............. ....................... 0 O 0 0

12. Check magneto RPM variation ..................................... 0 O 0 0
13. Check throttle and mixture operation (See the latest revision of
Piper Ser ice Bulletin No. 448) ...................................... 0 O 0 0
14. Check propeller smoothness ......................................... 0 O 0 0
15. Check propeller o\ ernor action ..................................... 0 O O O
16. Check engine idle .................................................. 0 O 0 O
17. Check electronic equipment operation ................................ 0 O 0 0
18. Check operation of Autopilot including automatic pitch trim. and Manual
Electric Trim (See Note 22) ......................................... 0 O 0 0
19. Check air conditioner compressor clutch operation ..................... 0 O 0 0
20. Check air conditioner condenser scoop operation ...................... 0 O 0 0
O
I. GENERAL

1. Aircraft conforms to FAA Specification .............................. O O O O

2. All latest FAA Airworthiness Directives complied with ................. O O O C
3. All latest Manufacturer's Service Bulletins and Letters complied with ..... O O O O
4. Check for proper Flight Manual ..................................... O O O O
5. Aircraft papers in proper order ...................................... O O O O

Revised: 10 3 83 1F24 INSPECTION

1F24
 CHEROKEE SERVICE MANUAL

TABLE III-I. INSPECTION REPORT (cont)

PA-28-140; PA-28-150, -160, -180; PA-28-235

NOTES:
1. Referto the last card of the Piper Parts Price List- Aerofiche,for a checklistof current revisiondates
to Piper Inspection Reports and Manuals.
2. All inspectionsor operations are required at each of the inspectionintervals as indicatedby a (O).
Both the annual and 100 hour inspections are complete inspections of the airplane, identical in
scope, while both the 500 and 1000 hour inspections are extensions of the annual or 100 hour
inspection, which require a more detailed examination of the airplane,and overhaulor replacement
of some major components. Inspectionsmust be accomplishedby persons authorized by the FAA.
3. Piper Service Bulletins are of special importance and Piper considers compliance mandatory.
4. Piper Service Letters are product improvements and service hints pertaining to servicing the
airplane and should be given careful attention.
5. Inspectionsgivenfor the power plant are based on the engine manufacturer'soperator's manual for
the particular airplane. Any changes issued to the engine manufacturer's operator's manual shall
supersede or supplement the inspections outlined in this report.
6. Intervals between oil changescan be increasedas much as 100%on enginesequipped with full flow
cartridge type oil filters, provided the element is replaced each 50 hours of operation and the
specified octane fuel is used. Should fuel other than the specifiedoctane rating for the power plant
be used, refer to latest revision of Lycoming Service Letter No. L185 for additional infor-
mation and recommended service procedures.
7. Replaceor overhaul as required or at engine overhaul. (For engine overhaul, referto latest revision
of Lycoming Service Letter No. L201.)
8. Replace flexible oil lines as required, but no later than 1000hours of service.
9. The compressor oil level should not be checked unless a freon leak has occurred which requires an
addition of freon to the system.
10. Clean any traces of oil from the clutch surface.
11. Check security and condition of Autopilot servo bridle cables,clamps, and shear pin in accordance
with the latest revision of Piper Service Letter No. 695.
12. At every 400 hours of engine operation, remove the rocker box covers and check for freedom of
valve rockers when valves are closed. Look for evidence of abnormal wear or broken parts in the
area of the valvetips, valve keeper,springsand springseat. If any indicationsare found, the cylinder
and all of its components should be removed (including the piston and connecting rod assembly)
and inspected for further damage. Replace any parts that do not conform with limits shown in the
latest revision for Special Service Publication No. SSP 1776.
13. Check cylinders for evidence of excessive heat indicated by burned paint on the cylinders.
This condition is indicative of internal damage to the cylinder and, if found, its cause must be
determined and corrected before the aircraft is returned to service.
Heavy discoloration and appearance of seepage at the cylinder head and barrel attachment
area is usuallydue to emission of thread lubricant used during assemblyof the barrel at the factory,
or by slightgas leakage which stops after the cylinderhas been in servicefor awhile.This condition
is neither harmful nor detrimental to engine performance and operation. If it can be proven
that leakage exceeds these conditions, the cylinder should be replaced.
14. Check throttle body attaching screwsfor tightness; the correct torque for these screwsis 40 to 50
inch-pounds.
15. When using alternate fuels, refer to the latest revision of Lycoming Service Letter No. L185 for
additional information and recommended service procedures.
16. Replace fuel tank vent line flexibleconnections as required, but no later than 1000hours of service.
17. If airplane has electric trim system refer to the latest revision of Piper S/B556.

Revised: 1/15/86
Interim Revision: 5/6/87 INSPECTION
1G1
 PIPER CHEROKEE SERVICE MANUAL

TABLE III-I. INSPECTION REPORT (cont)

PA-28-140; PA-28-150, -160, -180; PA-28-235

NOTES:
18. Refer to and comply with Piper Service Bulletin No. 571 A. Replace flexible fuel tank supply hose at
time of engine overhaul.
19. Refer to the latest revision of Piper Service Bulletin No. 580.
20. Maintain cable tensions specified in Section V of Service Manual.
21. Refer to the latest information for the particular propeller being inspected:
McCauley Service Bulletin No. 137.
Hartzell Service Letter No. 61.
Sensenich Propeller Bulletin No. RBHR-978 or R-14 and AD69-9-3 for PA-28-180 aircraft with
Lycoming 0-360-A3A engines and M76EM Sensenich propellers, built up to and including 1969.
22. Refer to Flight Manual Supplement for preflight and flight check, for intended function in all modes.
23. Inspect Teflon bushing (lower to upper cowling attachment) for condition at each 100 hours. Replace
bushing on condition, but no later than 500 hours time in service. Inspect pin for condition and replace
as necessary.
24. If not already installed, add access panels, see Paragraph 4-57a. Inspect stabilator control cables, see
Paragraph 3-11a.

Interim Revision: February 15, 1995 INSPECTION

1G2
 PIPER CHEROKEE SERVICE MANUAL

TABLE III-II. INSPECTION REPORT

PA-28R

NOTE
Perform inspection or operation at each of the inspection inter-
vals as indicated by a circle (O).

Nature of Inspection Inspection time (hrs)

50 100 500 1000
A. PROPELLER GROUP

1. Inspect spinner and back plate. ..................................................................................... O 0 00

2. Inspect blades for nicks and cracks ............................................................................... O 0 00
3. Inspect for grease and oil leaks. ................................................................................... O 0 00
4. Lubricate propeller per lubrication chart in Service Manual (Section II) ...................... O 0 00
5. Inspect spinner mounting brackets................................................................................. 0 00
6. Inspect propeller mounting bolts and safety. (Check torque if safety is broken).......... 0 00
7. Inspect hub parts for cracks and corrosion..................................................................... 0 00
8. Rotate blades of constant speed propeller and check for tightness in hub pilot tube..... 0 00
9. Remove constant speed propeller; remove sludge from propeller and crankshaft........ 00
10. Inspect complete propeller and spinner assembly for security, chafing, cracks,
deterioration, wear, and correct installation............................................................. O O O
11. Overhaul propeller. (See Note 22)..................................................................................

B. ENGINE GROUP.

NOTE: Read Note 5 prior to completing this inspection group.

CAUTION: Ground Magneto Primary Circuit before working on engine.
1. Remove engine cowl and inspect for damage................................................................ 0 0 0 O
2. Clean and inspect cowling for cracks, distortion, and loose or missing fasteners
(See Note 23).................................................................................................................. 0 0 0
3. Drain oil sump. (See Note 6)......................................................................................... O 0 0 0
4. Clean suction oil strainer at oil change. (Inspect strainer for foreign particles) ........... O 0 0 0
5. Clean pressure oil strainer or change full flow (cartridge type) oil filter
element. (Inspect strainer or element for foreign particles).................................... O 0 0 0
6. Inspect oil temperature sender unit for leaks and security. ........................................... 0 0 0
7. Inspect oil lines and fitting for leaks, security, chafing, dents and cracks.
(See Note 8) ............................................................................................................. O 0 0 0
8. Clean and inspect oil radiator cooling fins..................................................................... 0 0 0
9. Remove and flush oil radiator ....................................................................................... O O
10. Fill engine with oil per lubrication chart in Service Manual (Section II) ...................... O 0 0 0
11. Clean engine ................................................................................................................... 0 0 0
CAUTION: Do not contaminate the vacuum pump with cleaning fluid.
(Ref: Latest revision of Lycoming Service Instruction No. 1221.)

Interim Revision: February 15, 1995 INSPECTION

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 PIPER CHEROKEE SERVICE MANUAL

TABLE III-II. INSPECTION REPORT (cont)

PA-28R

Inspection Time (hrs)

Nature of Inspection
50 100 500 1000
B. ENGINE GROUP (cont.)

12. Inspect condition of spark plugs (Clean and adjust gap as required; adjust
per the latest revision of Lycoming Service Instruction No. 1042) ....... 0 0 0
NOTE: If fouling of spark plugs has been apparent, rotate bottom plugs
to upper plugs. (Refer to the latest revisionof Lycoming Service
Instruction No. 1070 for additional information and
recommended service procedures when using alternate fuels.)
13. Inspect spark plug cable leads and ceramics for corrosion and deposits ... 0 O0 0
14. Check cylinder compression (Ref: AC 43.13-lA) ....................... O0 0
15. Inspect cylinders for cracked or broken fins ........................... O 0 0
16. Inspect rocker box covers for evidence of oil leaks. If found, replace
gasket; torque cover screws 50 inch-pounds (See Note 12) ............... O O 0 0
NOTE: Lycoming requires a Valve Inspection be made after every
400 hours of operation. (See Note 11)
17. Inspect ignition harness and insulators (high tension leakage and
continuity) ........................................................ O 0 0
18. Inspect magneto points for condition and proper clearance (Refer to
Service Manual) .................................................. O 0 0
19. Inspect magneto for oil leakage ...................................... O 0 C
20. Inspect breaker felts for proper lubrication ............................ O 0 O
21. Inspect distributor block for cracks, burned areas or corrosion and
height of contact springs ........................................... 0 0
22. Check magnetos to engine timing (Refer to Service Manual)............. O 0 0
23. Overhaul or replace magnetos (See Note 7)............................
24. Remove air filter and tap gently to remove dirt particles (Replace
as required) ....................................................... O O 0 0
25. Clean fuel injector inlet line screen (Clean injector nozzles as required)
(Clean with acetone only) ........................................... O O 0 0
26. Inspect condition of injector alternate air door and box (See Note 13) .... O O 0 0
27. Inspect vent lines for evidenceof fuel or oil seepage .................... O O 0 0
28. Inspect intake seals for leaks and clamps for tightness .................. O O 0 0
29. Inspect all air inlet duct hoses (Replace as required) .................... O O 0 0
30. Inspect condition of flexible fuel lines ................................ O 0 0
31. Replace flexible fuel lines ........................................... O
32. Inspect fuel system for leaks......................................... O O 0 0
33. Inspect fuel pumps for operation (engine driven and electric) ............ O 0 0
34. Overhaul or replace fuel pumps (engine driven and electric) (See Note 7)..
35. Clean gascolator bowl and screens (Clean at least every 90 days) ......... O O 0 0
36. Inspect vacuum pump and lines...................................... O 0 0
137.Overhaul or replace vacuum pump (See Note 7) .......................
38. Inspect throttle, alternate air, mixture and propeller governor controls
for security, travel and operating condition (Refer to the latest revision
of Piper Service Bulletin No. 448 and Service Letter No. 747) ......... O 0 0
39. Inspect exhaust stacks, connections and gaskets (Replace gaskets as
required).......................................................... 0 0 O
40. Inspect muffler, heat exchange and baffles (Refer to the latest 0 0 O
revision of Piper S/B No. 691) ...................................

Revised: 8/3/81 1G4 INSPECTION

 PIPER CHEROKEE SERVICE MANUAL

TABLE III-II. INSPECTION REPORT (cont.)

PA-28 R

Inspection Time (hrs)

Nature of Inspection
50 100 500 1000
B. ENGINE GROUP (cont)

41. Inspect breather tube for obstructions and security ..................... O 0 0

42. Inspect crankcase for cracks, leaks, and security of seam bolts ........... O 0 0
43. Inspect engine mounts for cracks and loose mountings .................. O 0 0
44. Inspect condition of all engine baffles................................. O 0 0
45. Inspect condition of all wiring connected to the engine or accessories ..... O 0 0
46. Inspect rubber engine mount bushings for deterioration (Replace as
required) ......................................................... O 0 0
47. Inspect condition of fire wall seals ................................... O 0 0
48. Inspect condition and tension of alternator drive belt (Refer to
Service Manual Section XI.) ........................................ O 0 0
49. Lubricate idler pulley (if installed) per lubrication chart in
Service Manual ................................................... O 0 0
50. Inspect condition of alternator and starter ............................. O 0 0
51. Inspect security of alternator mounting ............................... O 0 0
52. Inspect air conditioning compressor oil level (See Note 9) ...............
53. Inspect condition of compressor belt and tension (Refer to Service
Manual Section XIV.) .............................................. O O O
54. Inspect compressor clutch security and wiring (See Note 10) ............. O 0 0
55. Inspect security of compressor mounting .............................. O 0 0
56. Check fluid in brake reservoir (Fill as required) ........................ O O 0 0
57. Lubricate all controls per lubrication chart in Service Manual (Section 11). O 0 0
58. Overhaul or replace propeller governor (See Note 7) (Refer to the
latest revision of Hartzell Service Letter 61) ...........................
59. Complete overhaul of engine or replace with factory rebuilt (See Note 7)..
60. Reinstall engine cowl ............................................... 0 O 0 0

C. CABIN GROUP

1. Inspect cabin entrance door and windows for damage. operation and
security ........................................................... O O O O
2. Inspect upholstery for tears ......................................... O O O
3. Inspect seats, seat belts. security brackets and bolts ..................... O O 0
4. Inspect trim operation (See Note 17) ................................. O 0 0
5. Inspect rudder pedals ............................................... O O O
6. Inspect parking brake and brake handle for operation and cylinder leaks.. 0 0 0
7. Inspect control wheels, column, pulleys and cables ..................... 0 0 0
8. Inspect flap control cable attachment bolt ............................. O O
9. Inspect landing. navigation. cabin and instrument lights................. O O 0 0
10. Inspect instruments. lines and attachments ............................ 0 0 0
11. Inspect gyro operated instruments and electric turn and bank (Overhaul
or replace as required) .............................................. 0 0 0
O INSPECTION
O O
O O O

Revised: 10 3 83 INSPECTION
1G5
 PIPER CHEROKEE SERVICE MANUAL

TABLE 111-11.INSPECTION REPORT (cont.)

PA-28R

Inspection Time (hrs)

Nature of Inspection
50 100 500 1000
C. CABIN GROUP (cont)

12. Replace filters on gyro horizon and directional gyro or replace central
air filter .......................................................... O 0 0
13. Clean or replace vacuum regulator filter .............................. O 0 0
14. Inspect altimeter (Calibrate altimeter system in accordance with
FAR 91.170. if appropriate) ......... ................................ O 0 0
15. Check operation of fuel selector valve (See Note 20) .................... O 0 0
16. Inspect condition of heater controls and ducts ......................... O 0 0
17. Inspect condition and operation of air vents ........................... O 0 0
18. Inspect condition of air conditioning ducts ........................... O 0 0
19. Remove and clean air conditioning evaporator filter .................... O 0 0
D. FUSELAGE AND EMPENNAGE GROUP

1. Remove inspection plates and panels ................................. O O O

2. Inspect baggage door. latch and hinges for condition, operation and
security ........................................................... O O O
3. Inspect battery, box and cables (Inspect at least every 30 days. Flush
box as required and fill battery per instructions on box) ................ O O 0 0
4. Inspect electronic installations ....................................... O 0 0
5. Inspect bulkheads and stringers for damage ........................... O 0 0
6. Inspect antenna mounts and electric wiring for security and corrosion
in plugs........................................................... O 0 0
7. Inspect hydraulic pump motor brushes (See Note 19) ................... O 0 0
8. Inspect hydraulic pump fluid level (Fill as required) .................... O O 0 0
9. Inspect hydraulic pump lines for damage and leaks ..................... O 0 0
10. Inspect for obstructions and contamination in inlet of backup landing
gear extender actuator inlet head..................................... O O 0 0
11. Inspect air conditioning system for freon leaks ......................... O 0 0
12. Check freon level in sight gauge of receiver-dehydrator (Refer to
Service Manual)................................................... O O 0 0
13. Inspect air conditioner condenser air scoop rigging ..................... O O 0 0
14. Inspect fuel lines. valves. sender units, and gauges for damage and
operation ......................................................... O 0 0
15. Inspect security of all lines .......................................... O 0 0
16. Inspect vertical fin and rudder surfaces for damage ..................... O 0 0
17. Inspect rudder hinges. horn and attachments for damage and
operation......................................................... O 0 0
18. Inspect rudder control stop to insure stop has not loosened and
lock nut is tight. .................... ............................... 0
19. Inspect vertical fin attachments ...................................... 0 0 0
20. Inspect rudder hinge bolts for excess wear (Replace as required) ......... 0 O O
21. Inspect stabilator surfaces for damage ................................ 0O 0 0
22. Inspect stabilator. tab hinges. horn and attachments for damage and O
operation ......................................................... O O OO

Revised: 8 3 81 INSPECTION
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 PIPER CHEROKEESERVICE MANUAL

TABLE III-II. INSPECTION REPORT (cont)

PA-28R

Nature of Inspection Inspection time (hrs)

D. FUSELAGE AND EMPENNAGE GROUP (cont.) 500 1000

23. Inspect stabilator control stops to insure stops have not loosened and locknut is tight. O
24. Inspect stabilator attachments (see latest revision of Piper Service Bulletin 856)......... O O O
25. Inspect stabilator and tab hinge bolts and bearings for excess wear (Replace as
required) ........................................................................................................................ 0 0O
26. Inspect stabilator trim mechanism.................................................................................. 0 0O
27. Check all cable tensions (use tensiometer) (See Note 18) ............................................. 0 0O
28. Inspect aileron, rudder, stabilator, stabilator trim cables, turnbuckles, guides and
pulleys for safety, damage and operation (See Note 24)................................................ 0 0O
29. Clean and lubricate stabilator trim drum screw (Refer to lubrication chart in
Service Manual) ............................................................................................................. 0 0
30. Inspect stabilator balance weight attachments and arm for security and condition ....... 0 0O
31. Inspect emergency locator transmitter battery for replacement date per Service
Manual (Refer to the latest revision of Piper S/L No. 820) ........................................... 0 0o
32. Clean and lubricate all exterior needle bearings ............................................................ O
33. Lubricate per lubrication chart in Service Manual............................ ............................. O Oo o
34. Inspect anti-collision light for security and operation ................................................... 0 0O
35. Inspect security of Autopilot bridle cable clamps.......................................................... 0 0O
36. Inspect all control cables, air ducts, electrical leads, lines, radio antenna leads and
attaching parts for security, routing, chafing, deterioration, wear and correct
installation ...................................................................................................................... 0 0O
37. Reinstall inspection plates and panels............................................................................ 0 0O

E. WING GROUP
1. Remove inspection plates and fairings .......................................................................... O 0 0
2. Inspect surfaces and tips for damage, loose rivets, and condition of walk-way ............ O 0 0
3. Inspect aileron hinges and attachments.......................................................................... O 0 0
4. Inspect aileron control stops to insure stop has not loosened and lock nut is tight........ O
5. Inspect aileron balance weight and arm for security and condition............................... 0 0 0
6. Inspect aileron cables, pulleys and bellcranks for damage and operation ..................... 0 0 0
7. Inspect flaps and attachments for damage and operation .............................................. 0 0 0
8. Inspect condition of bolts used with hinges (Replace as required)................................ O
9. Lubricate per lubrication chart in Service Manual (Section II) ..................................... O0 O
10. Inspect wing attachment bolts and brackets................................................................... 0 0 0
11. Inspect fuel tanks and lines for leaks and water (See Note 15)...................................... 0 0 0
12. Fuel tanks marked for capacity ..................................................................................... 0 0 0
13. Fuel tanks marked for minimum octane rating .............................................................. 0 0 0
14. Inspect fuel cell vents (See Note 16) ............................................................................. 0 0 0

Interim Revision: February 15, 1995 INSPECTION

1G7
 PIPER CHEROKEE SERVICE MANUAL

TABLE III-II. INSPECTION REPORT (cont)

PA-28R

Inspection Time (hrs)

Nature of Inspection
50 100 500 1000
E. WING GROUP (cont)

15. Inspect all control cables, air ducts, electrical leads, lines and attaching
parts for security, routing, chafing, deterioration, wear and correct
installation ........................................................ O 0 0
16. Reinstall inspection plates and fairings ................................ O 0 0
F. LANDING GEAR GROUP

1. Inspect oleo struts for proper extension (N-2.75 in., M-2.0 in.) Check
fluid level as required) .............................................. O O O 0
2. Inspect nose gear steering control and travel ........................... O 0 0
3. Inspect wheels for alignment ........................................ O o 0
4. Put airplane on jacks ............................................ O 0 0
5. Inspect tires for cuts, uneven or excessive wear and slippage ............. O O 0
6. Remove wheels, clean, check and repack bearings ...................... O O 0
7. Inspect wheels for cracks, corrosion and broken bolts ................... O 0 0
8. Check tire pressure (N-30 psi M-27 psi) ............................... O O 0 O
9. Inspect brake lining and disc ........................................ O 0
10. Inspect brake backing plates......................................... O 0 O
11. Inspect brake and hydraulic lines .................................... O 0 0
12. Inspect shimmy dampener ........................................... o 0 0
13. Inspect gear forks for damage ....................................... O 0 0
14. Inspect oleo struts for fluid leaks and scoring .......................... O 0 0
15. Inspect gear struts, attachments, torque links, retraction links and
bolts for condition and security ...................................... O 0 0
16. Inspect downlock for operation and adjustment ........................ O 0 0
17. Inspect torque link bolts and bushings (Rebush as required) ............. 0 0
18. Inspect drag and side brace link bolts (Replace as required) ............. O
19. Inspect gear doors and attachments .................................. O 0 0
20. Inspect warning horn and light for operation .......................... O 0 0
21. Retract gear - check operation ....................................... O 0 0
22. Retract gear - check doors for clearance and operation ................. O 0 0
23. Inspect anti-retraction system ...................................... O 0 0
24. Inspect actuating cylinders for leaks and security ....................... O O 0
25. Inspect all hydraulic lines, electrical leads, and attaching parts for
security. routing, chafing, deterioration, wear and correct installation
(See the latest revision of Piper SL No. 808 and 810) .................. O 0 0
26. Inspect position indicator switch and electrical leads for security ......... O 0 0
27. Lubricate per lubrication chart in Service Manual (Section II) ........... O O O O
28. Remove airplane from jacks ......................................... O O 0
G. OPERATIONAL INSPECTION

1. Check fuel pump and fuel tank selector ............................... O O O O

2. Check fuel quantity. pressure and flow readings........................ O O O

Reissued: 1 15 81 INSPECTION
1G8
 PIPER CHEROKEE SERVICE MANUAL

TABLE III-11. INSPECTION REPORT (cont.)

PA-28 R

Inspection Time (hrs)

Nature of Inspection
50 100 500 1000
G. OPERATIONAL INSPECTION (cont)

3. Check oil pressure and temperature .................................. O O 0 0

4. Check alternator output ............................................ O O 0 0
5. Check manifold pressure ............................................ O O 0 0
6. Check alternate air ................ .............................. O O 0 0
7. Check parking brake ............................................... O O 0 0
8. Check vacuum gauge ............................................... O O 0 0
9. Check gyros for noise and roughness ................................. O O 0 0
10. Check cabin heater operation ........................................ O O 0 0
11. Check magneto switch operation ..................................... O O 0 0
12. Check magneto RPM variation ...................................... O O 0 0
13. Check throttle and mixture operation (See the latest revision of
Piper Service Bulletin No. 448) ...................................... O O 0 0
14. Check propeller smoothness ......................................... O O 0 0
15. Check propeller governor action..................................... O O 0 0
16. Check engine idle................................................. O O 0 0
17. Check electronic equipment operation ................................ O O 0 0
18. Check operation of Autopilot. including automatic pitch trim. and
Manual Electric Trim (See Note 21.) ................................. O O 0 0
19. Check air conditioner compressor clutch operation ..................... O O 0 0
20. Check air conditioner condenser scoop operation ...................... O O 0 0
21. Check (FLY Aircraft) Landing Gear System (See Note 14) .............. O 0 0

H. GENERAL

1. Aircraft conforms to FAA Specification ......................... O O O o

2. All latest FAA Airworthiness Directives complied with ............ O O O O
3. All latest Manufacturers Service Bulletins and Letters complied with O O O O
4. Check for proper Flight Manual ................................ O O O O
5. Aircraft papers in proper order ................................. O O O O

Revised: 10 3 83 INSPECTION
1G9
 PIPER CHEROKEESERVICEMANUAL

TABLEIII-II. INSPECTIONREPORT (cont)

PA-28R
NOTES:
1. Referto the last card of the Piper Parts Price List - Aerofiche,for a checklistof current revisiondates
to Piper Inspection Reports and Manuals.
2. All inspectionsor operations are required at each of the inspection intervals as indicated by a (O).
Both the annual and 100 hour inspections are complete inspections of the airplane, identical in
scope, while both the 500 and 1000 hour inspections are extensions of the annual or 100 hour
inspections,which require a more detailed examination of the airplane, and overhaulor replacement
of some major components. Inspections must be accomplished by persons authorized
by the FAA.
3. Piper Service Bulletins are of special importance and Piper considers compliance mandatory.
4. Piper Service Letters are product improvements and service hints pertaining to servicing the
airplane and should be given careful attention.
5. Inspectionsgiven for the power plant are based on the enginemanufacturer's operator's manual for
the particular airplane. Any changes issued to the engine manufacturer's operator's manual shall
supersede or supplement the inspections outlined in this report.
6. Intervals between oil changes can be increased as much as 100%on enginesequipped with full flow
(cartridge type) oil filters, provided the element is replaced each 50 hours of operation. (Refer to
latest revision of Lycoming Service Instruction No. 1070, for additional information and re-
commended service procedures when using alternate fuels.)
7. Replace or overhaul as required or at engine overhaul. (For engine overhaul, referto latest revision
of Lycoming Service Instruction No. 1009.)
8. Replace flexible oil lines as required, but no later than 1000 hours.
9. The compressor oil level should not be checked unless a freon leak has occurred which requiresan
addition of freon to the system.
10. Clean any traces of oil from the clutch surface.
11. At every 400 hours of engine operation, remove the rocker box covers and check for freedom of
valve rockers when valvesare closed. Look for evidenceof abnormal wear or broken parts in the
area of the valve tips, valvekeeper,springsand spring seat. If any indicationsare found, the cylinder
and all of its components should be removed (including the piston and connecting rod assembly)
and inspected for further damage. Replace any parts that do not conform with limits shown in the
latest revision for Lycoming Special Service Publication No. SSP1776.
12. Check cylinders for evidence of excessive heat indicated by burned paint on the cylinders.
This condition is indicative of internal damage to the cylinder and, if found, its cause must be
determined and corrected before the aircraft is returned to service.
Heavy discoloration and appearance of seepage at the cylinder head and barrel attachment
area is usuallydue to emissionof thread lubricant used during assemblyof the barrel at the factory,
or by slight gas leakagewhich stops after the cylinder has been in servicefor awhile. This condition
is neither harmful nor detrimental to engine performance and operation. If it can be proven
that leakage exceeds these conditions, the cylinder should be replaced.
13. Check throttle body attaching screws for tightness; the correct torque for these screwsis 40 to 50
inch-pounds.

Revised: 10/3/83
Interim Revision: 5/6/87 INSPECTION
 PIPER CHEROKEE SERVICE MANUAL

TABLE III-II. INSPECTION REPORT (cont)

PA-28R

NOTES:
14. Fly aircraft to check landing gear system in accordance with instructions given in Section VI, Paragraph
6-14, of PA-28 Service Manual 753 586. (Refer to the latest revision of Piper Service Letter No. 810.)
15. Replace flexible fuel tank supply hose at time of engine overhaul.
16. Replace fuel tank vent line flexible connections as required, but no later than 1000 hours of service.
17. If airplane has electric trim, refer to the latest revision of Piper Service Bulletin No. 556.
18. Maintain cable tensions specified in Section V of Service Manual.
19. Inspect brushes every 100 hours on airplanes used for training or every 500 hours on airplanes used for
normal service. (Refer to Service Manual, Section VI.)
20. Refer to latest revision of Piper Service Bulletin No. 355.
21. Refer to Flight Manual Supplement for preflight and flight checks, for intended function in all modes.
22. Refer to latest information for the particular propeller being inspected:
Hartzell Service Letter No. 61
McCauley Service Bulletin No. 137.
23. Inspect Teflon bushing (lower to upper cowling attachment) for condition at each 100 hours. Replace
bushing on condition, but no later than 500 hours time in service. Inspect pin for condition and replace
as necessary.
24. If not already installed, add access panels, see Paragraph 4-57a. Inspect stabilator control cables, see
Paragraph 3-11a.

Interim Revision: February 15, 1995 INSPECTION

1Gll
 1G12
INTENTIONALLY LEFT BLANK
 SECTION
IV

STRUCTURES

Aerofiche
Grid No.

4-1. Introduction ................................ .... 1

4-2. Description IG15
4-3. Wing Group . IG16
4-4. Wing Tip .. 1G16
4-5. Removal of Wing . . . .Tip.................. . . . . . . . .
. . . . . . . . . . . .. .. .... 1G16
4-6. Removal of Wing Tip ................. 1G17
4-7. Aileron ... IG17
4-8. Installation of Aileron .................. 1G17
4-9. 1G17
4-10. Wing Flap . 1G18
4-11. Removal of Wing Flap .................. 1G18
4-12. Installation of Wing Flap. 1G18
4-13. Wing .....
Removal of Aileron...................
Installationof Aileron ..................
Removal
. of.................
Wing 1G18
4-14. 1G18
4-15. 1H2
4-16. Empennage Gr Removal of Stabilator ................. 1H6
4-17. Stabilator Installation of Stabilator ................ 1H6
4-18. 1H6
4-19. 1H8
4-20. Stabilator TrimTrim
Tab............................ IH13
4-21. Removal of StabilatorTrim Tab ............ IH13
4-22. Installation of Stabilator Trim Tab. 1H13
4-23. Rudder ... IH13
4-24. Removal
Installation of ofRudder ..................
RudderFin............. 1H13
Removal of Vertical
Installation of Vertical Fin............
4-25. 1H13
4-26. Vertical Fin . 1H14
4-27. Assembly............................ 1H14
Removal of Vertical Fin...........
4-28. 1H14
4-29. Fuselage Assen Installation of of Windshield
Vertical ..... .......... 1H15
4-30. Windshield
Removal
Installation of Vertical................
Fin
Fin.................
1H15
4-31. 1H15
4-32. 1H15
4-33. Side Windows IH17
4-34. Removal of Side Windows............... 1H17
4-35. Installation of Side Windows .............. 1H18

Reissued:1/15/81 1G13
 PIPER CHEROKEE SERVICE MANUAL

Paragraph Aerofiche
Grid No.
4-36. Door (Entrance) .......................................................................................... 1H 19
4-37. Removal of Door...............................................................1H19
4-38. Installation of Door .......................................................... 1H19
4-39. Adjustment of Door ..................................... 1H 19
4-40. Removal of Door Latch Mechanism ................................. 1H19
4-41. Removal and Installation of Door Seal Snubbers ............. 1H20
4-42. Installation of Door Latch Mechanism ............................. 1H21
4-43. Adjustment of Door Latch Mechanism ............................. 1H21
4-44. Removal of Door Lock Assembly .................................... 1H21
4-45. Installation of Door Lock Assembly .................................1 H21
4-46. Removal of Door Safety Latch ........................................ H21
4-47. Installation of Door Safety Latch ..................................... 1H22
4-48. Adjustment of Door Safety Latch ..................................... 1H22
4-49. Baggage Door ........................................................................................... H22
4-50. Removal of Baggage Door ................................................ H22
4-51. Installation of Baggage Door ........................................... 1H22
4-52. Removal of Baggage Door Lock Assembly ...................... 1H22
4-53. Installation of Baggage Door Lock Assembly .................. 1H23
4-54. Removal of Baggage Door Hinge ..................................... 1H23
4-55. Installation of Baggage Door Hinge ................................. 1H23
4-56. Rigging Instructions - Seat Back Lock and Release .........1H23
4-57. Structural Repairs ....................................................................................... 113
4-57a. Baggage Compartment Inspection Hole and Cover Plate .......................... 13
4-58. Fiberglas Repairs ............................................................... 113
4-59. Fiberglas Touch-Up and Surface Repairs..........................1I3
4-60. Fiberglas Fracture and Patch Repairs ................................1I4
4-61. Thermoplastic Repairs ...................................................... 1I6
4-62. A.B.S. Thermoplastic Landing Gear and Strut Fairing
Repair Instructions ..................................................... 1I10
4-63. Safety Walk Repair.....................................................................................1I14
4-64. Surface Preparation for Liquid Safety Walk ..................... 1114
4-65. Product Listing for Liquid Safety Walk Compound ......... 1114
4-66. Application of Liquid Safety Walk Compound ................. 1I14
4-67. Surface Preparation for Pressure Sensitive Safety Walk...1I14
4-68. Application of Pressure Sensitive Safety Walk................. 1I15
4-69. Control Surface Balancing ........................................................................ 1I16
4-70. Checking Control Surface Balance ................................... 1116
4-71. Checking Control Surface Free Play ................................. 1116
4-72. Balancing Equipment ........................................................ 1I18
4-73. Balancing Ailerons...........................................................1I18
4-74. Balancing Rudder..............................................................1I19
4-75. Balancing Stabilator ......................................................... 1I22
4-76. Aileron Balance Weight Modification .............................. 1I23
4-77. Flap Inspection and Modification ..................................... 1J1
4-78. Stabilator Drain Holes ..................................................... 1J1
4-79 Baggage Compartment Inspection Hole and Cover Plate .......................... 1J3

Interim Revision: February 15, 1995

1G14
 PIPER CHEROKEE SERVICE MANUAL

SECTIONIV
STRUCTURES

4-1. INTRODUCTION.This section explains the removal and installation procedures for
the structural surfaces of the airplane. For the removal, installation, and rigging and
adjustment procedures of the controlling components of the various structural surfaces,
refer to Section V.
NOTE
When torquing structural assemblies, standard torque values
are to be used as found in Section II, Federal Aeronautics
Manual 18 or FAA Advisory Circular 43.13-1, unless
otherwise stated in this section.

4-2. DESCRIPTION. The PA-28 is an all metal semi-monocoquestructure with an overall

length ranging from 23 feet 5.40 inches to 24 feet 7.38 inches depending on the model
involved. The fuselage is constructed of bulkheads, stringer and stiffeners, to which all of
the outer skin is riveted. Windowsinclude a single pane windshield and four to six side
windows, again depending upon the model. All windows are singlepane, the exception being
the PA-28-235, Serial Nos. 28-10720 and up, which are equipped with double pane side
windows. A storm window is located in the forward lower section of the left window and
can be opened inward when the latch is released. The cabin entrance door is located on the
right side of the fuselage, above the wing, and is equipped with a safety latch on the top of
the door, which can be operated from the inside or outside. A door provided for entrance to
the baggagecompartment (all models except PA-28-140) is locatedjust aft of the right wing
with a key lock installed.
Each wing panel is an all metal, full cantilever semi-monocoquetype construction with a
removable wing tip. Installed in each wing ahead of the main spar is a metal fuel tank with a
capacity of 25 U.S. gallons each or 50 U.S. gallons total. The PA-28-235 is equipped with
fiberglass tip tanks which increases the capacity to 42 U.S. gallons per wing or 84 U.S.
gallons total. Attached to each wing is an aileron, flap and main landing gear.The wingsare
attached to each side of the fuselageby inserting the butt ends of the main spars into a spar
box carry-through. The spar box is an integral part of the fuselagestructure which provides,
in effect, a continuous main spar with splicesat each side of the fuselage.There are also fore
and aft attachments at the front and rear spars.

Reissued:1/15/81 1G15 STRUCTURES

 PIPER CHEROKEE SERVICE MANUAL

The all metal empennage group is a full cantilever design consisting of a vertical
stabilizer (fin), rudder and stabilator, all with removable tips. The stabilator has a trim tab
attached that is controllable from the cockpit. The stabilator also incorporates one channel
main spar that runs the full length of the stabilator and hinges to the aft bulkhead assembly
of the fuselage. All exterior surfaces are coated with enamel or acrylic lacquer. As an option
the airplane may be completely primed with zinc chromate.

4-3. WINGGROUP.
NOTE

The major subassemblies of the wing may be removed

individually or the wing may be removed as a unit. To
remove a wing, a fuselage supporting cradle is required.

4-4. WINGTIP.

4-5. REMOVALOF WINGTIP.

a. PA-28-140 PA-28-150,-160, -180 and PA-28R:
1. Remove the screwsholding the wing tip to the wing, being careful not to damage
the wing or wing tip.
2. Pull off the wing tip far enough to disconnect the position light wire assembly.
The ground lead may be disconnected at the point of connection on the wing rib, and the
positive lead may be disconnected at the wire terminal or unscrewed from the light
assembly.
b. PA-28-235: Incorporated in each wing tip is a 17 gallon auxiliary fuel tank. Given
below are the steps recommended for removal of the tip:
1. Drain fuel from the tank to be removed. (Refer to Draining Fuel System,
Section II.)
2. Remove the accesscover from the bottom of the wing tip.
3. By working through the access, disconnect the fuel line, fuel quantity
transmitting wire and position light wire. Remove the two nuts, washers and bolts which
hold the tank to the wing.
4. Carefully remove the screws from around the wing tip and remove the tip
assembly.
c. Inspect the wing tip to ascertain that it is free of cracks, severe nicks and minor
damage. If repair is required, refer to paragraph 4-57.

Reissued:1/15/81 1G16 STRUCTURES

 PIPER CHEROKEE SERVICE MANUAL

4-6. INSTALLATIONOF WINGTIP.

a. PA-28-140;PA-28-150,-160, -180 and PA-28R:
1. Place the wing tip in a position that the navigationlight leads may be connected.
Connect the ground lead to the wing rib by use of a screw and nut, and the positive lead to
the position light by connecting the wire terminals or screwing the connectors together.
Insulate the wire terminals and be certain that the ground lead is free of dirt and film to
insure a good connection.
2. Insert the wing tip into position and install the screws around the tip. Use
caution to refrain from damaging the wing tip or wing. Check operation of the position
light.
b. PA-28-235:
1. Position the wing tip in place on the wing and insert the two bolts, washersand
nuts into their proper places and tighten. Replace the severalscrewsaround the tip tank and
tighten. Connect the position light leads, the fuel quantity transmitting wire and the fuel
line.
2. After the wing tip is installed and all connections are secured, fill the tip tank
and check for fuel leaks, operation of the fuel gauge and position light. Install the access
cover to the bottom of the wing tip.

4-7. AILERON.

4-8. REMOVALOF AILERON. (Refer to Figure 4-1.)

a. Disconnect the aileron control rod at the aileron attachment point by removing the
nut, washers and bolt from the rod end bearing. To simplify installation note location of
washersremoved.
b. Remove the attaching screws, with nuts, from the hinges at the leading edge of the
aileron, and remove the aileron by lowering the inboard end and swingingit forward to
allow the balance arm to clear the opening in the outboard rib.

4-9. INSTALLATIONOF AILERON. (Refer to Figure 4-1.)

a. Install the balance arm into the opening in the outboard rib by movingthe inboard
end of the aileron forward to allow the arm to be inserted through the opening. (When
installing an aileron, should the balance weight assembly, P/N 66766-00, replace an earlier
balance weight assembly, P/N 65388-34 (L) or 65388-35 (R), the wing butt rib will require
modifying per instructions in Paragraph 4-75.) Move the aileron into place and install
attaching screws and nuts. Ascertain that the aileron is free to move with no interference.
b. Attach the aileron control rod with bolt, washers and nut, dividing the washers so
that the aileron is free to rotate from stop to stop without the control rod binding or
rubbing on the opening in the aft spar. Be certain that the rod end bearing has no side play
when tightening the bolt and that the rod does not contact the side of the bracket.
c. Actuate the aileron controls to insure freedom of movement.

STRUCTURES
Reissued: 1/15/81 1G17
 PIPER CHEROKEE SERVICE MANUAL

4-10. WINGFLAP.

4-11. REMOVALOF WINGFLAP. (Refer to Figure 4-1.)

a. Extend the flaps to their fullest degree and remove the bolt and bushing from the
rod end bearing by use of an angle or offset screwdriver.
b. Remove the nuts, washers, bushing and hinge bolts that hold the flap to the wing
assembly.
c. Pull the flap straight back off the wing. (Refer to Paragraph 4-75 for flap inspection
and modification.)

4-12. INSTALLATIONOF WINGFLAP. (Refer to Figure 4-1.)

a. Replace the wing flap by placing the flap onto its proper position and inserting the
hinge bolts, bushings,washers,and nuts.
b. With the flap control in the full flap position, place the bushing on the outboard side
of the rod end bearing and insert and tighten the bolt.
c. Operate the flap severaltimes to be certain it is operating freely.

4-13. WING.

4-14. REMOVALOF WING. (Refer to Figure 4-2.)

a. PA-28-140;PA-28-150,-160, -180 and PA-28-235.
1. Close the fuel valve and drain the fuel from the wing to be removed. (Refer to
DrainingFuel System, Section II.)
2. Drain the brake lines and reservoir.(Refer to DrainingBrake System, Section II.)
3. Remove the accessplate at the wing butt rib and wing inspection panels. (Refer
to AccessPlates and Panels, Section II.)
4. Remove the front and back seats from the airplane.
5. Expose the spar box and remove the cockpit side trim panel assembly that
corresponds with the wingbeing removed.

Reissued: 1/15/81 1G18 STRUCTURES

 PIPER CHEROKEE SERVICE MANUAL

A339

A337 A336

WING

SCREW AN525-10-8
WASHER R AN960-10
NUT MS 20365-1032C
8 REQ
13 REQ PA-28-181 ONLY BOLT AN3-12A
WASHER AN960-10 (6 REQ)
AILERON NUT MS20365-1032C
SKETCH A SKETCH B
A322 A322
AN3-11A
AN960-1 0
MS20365-1032C
63900-19 (2 REQ)
2 REQ

AN3-13A
AN960-10
MS20365-1032C
63900-20 (2 REQ)

SKETCH C SKETCH D
Figure 4-1. Aileron and Flap Installation

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1G19
 PIPER CHEROKEE SERVICE MANUAL

A321

EXISTING ANCHORNUT
TO BE MODIFIED TO
AGREE WITH SKETCH E-2

SKETCH E-1
C335

1.10
MODIFIED
DEMENSION

.81
EXISTING
DIMENSION

NUT AN310-3
WASHER AN960-10
COTTER PIN
.55R-
MS24665-132

MODIFIED CUTOUTDETAIL
RIGHT AND LEFT SIDE

SKETCH E-2

Figure 4-1. Aileron and Flap Installation (cont.)

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1G20
 PIPER CHEROKEESERVICEMANUAL

6. Place the airplane on jacks. (Refer to Jacking, Section II.)

NOTE

To help facilitate reinstallation of control cables, and

fuel and hydraulic lines, mark cable and line ends in
some identifying manner and attach a line where ap-
plicable to cables before drawing them through the
fuselage or wing.

7. Disconnect the aileron balance and control cables at the turnbuckles

that are located within the fuselage aft of the spar.
8. If the left wing is being removed, remove the cotter pin from the pulley
bracket assembly to allow the left aileron balance cable end to pass between the
pulley and bracket.
9. Disconnect the flap from the torque tube by extending the flap to its
fullest degree, and removing the bolt and bushing from the bearing at the aft end
of the control rod.
10. Disconnect the fuel line at the fitting located aftof the spar at the wing
butt line.

CAUTION

To prevent damage or contaminationof fuel, hydraulic

and miscellaneous lines, placea protective cover over
the line fittings and ends.

11. Remove the clamps necessary to release the electrical harness as-
sembly. Disconnect the leads from the terminal strip assembly by removing the
cover, and appropriate nuts and washers.
12. With the appropriate trim panel removed, disconnect the hydraulic
brake line at the fitting located within the cockpit at the leading edge of the wing.
13. If the left wing is being removed, it will be necessary to disconnect
the pitot and static tubes at the elbows located within the cockpit at the wing butt
line.
14. Arrange a suitable fuselage cradle and supports for both wings.
15. Remove the wing jacks.
16. Remove the front and rear spar nuts, washers and bolts.
17. Remove the eighteen main spar bolts.
18. Slowly remove the wing being certain that all electrical leads. cables
and lines are disconnected.

Reissued: 1/15/81 STRUCTURES

1G21
 1G22
INTENTIONALLY LEFT BLANK
 PIPER CHEROKEE SERVICE MANUAL

BOLT LEGEND WASHER

POSITION BOLT* NUT* UNDER HEAD UNDER NUT
A-1 AN176-13A MS20365-624C (1) AN960-616 (1) AN960-616& (1) 96352-3
A-2 AN176-12A MS20365-624C (1) AN960-616 (1) AN960-616&(1) 96352-3
A-3 AN176-12A MS20365-624C (1) AN960-616 (1) AN960-616& (1) 96352-3
A-4 AN176-12A MS20365-624C (1) AN960-616 (1) AN960-616& (1) 96352-3
B-1 AN176-14A MS20365-624C (1) AN960-616 (2) AN960-616
B-2 AN176-13A MS20365-624C (1) AN960-616 (2) AN960-616
B-3 AN176-13A MS20365-624C (1) AN960-616 (2) AN960-616
B4 AN176-13A MS20365-624C (1) AN960-616 (2) AN960-616
C-1 AN176-13A MS20365-624C (1) 96352-3 (1) AN960-616
C-2 AN 176-13A MS20365-624C (1) 96352-3 (2) AN960-616
C-3 AN176-13A MS20365-624C (1) 96352-3 (2) AN960-616
C-4 AN176-13A MS20365-624C (1) 96352-3 (2) AN960-616
C-5 AN176-13A MS20365-624C (1) 96352-3 (1) 96352-3
D-1 AN176-13A MS20365-624C (1) 96352-3 (1) AN960-616
D-2 AN176-13A MS20365-624C (1) 96352-3 (2) AN960-616
D-3 AN176-13A MS20365-624C (1) 96352-3 (2) AN960-616
D-4 AN 175-13A MS20365-624C (1) 96352-3 (2) AN960-616
D-5 AN176-13A MS20365-624C (1) 96352-3 (1) 96352-3

*Torque Boltheads on Upper Spar Cap and Nuts on Lower Spar Cap 360-390 in-lbs
1785

SKETCH D

Figure 4-2. Wing Installation (cont.)

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1G24
 PIPER CHEROKEE SERVICE MANUAL

b. PA-28R:
1. Close the fuel valve and drain the fuel from the wing to be removed.
(Refer to Draining Fuel System, Section II.)
2. Drain the brake lines and reservoir. (Refer to Draining Brake System,
Section II. )
3. Drain the hydraulic lines of the landing gear of the wing to be removed
by separating the lines and elbows at the actuating cylinder.
4. Remove the access plate at the wing butt rib and wing inspection pan-
els. (Refer to Access Plates and Panels, Section II.)
5. Remove the front and back seats from the airplane.
6. Expose the spar box and remove the side trim cockpit panel assembly
that corresponds with the wing being removed.
7. Place the airplane on jacks. (Refer to Jacking, Section II.)

NOTE

To help facilitate reinstallation of control cables, and

fuel and hydraulic lines, mark cable and line ends in
some identifying manner and attach a line where ap-
plicable to cables before drawing them through the
fuselage or wing.

8. Disconnect the aileron balance and control cables at the turnbuckles that
are located within the fuselage aft of the spar.
9. If the left wing is being removed, remove the cotter pin from the pulley
bracket assembly to allow the left aileron balance cable end to pass between the
pulley and bracket.
10. Disconnect the flap from the torque tube by extending the flap to its
fullest degree, and removing the bolt and bushing from the bearing at the aft end
of the control rod.
11. Disconnect the fuel line at the fitting located inside of thewing, by re-
moving the acces panel on the forward inboard portion of the wheel well and
reaching through to the fuel line coupling.

CAUTION

To prevent damage or contamination of fuel, hydraulic

and miscellaneous lines, place a protective cover over
the line fittings and ends.

12. Remove the clamps that are necessary to release the electrical harness
assembly. Disconnect the leads from the terminal strip by removing the cover,

Reissued: 1/15/81 1H1 STRUCTURES

 PIPER CHEROKEE SERVICE MANUAL

and appropriate nuts and washers.

13. With the appropriate trim panel removed, disconnect the hydraulic
brake line at the fitting located within the cockpit at the leading edge of the wing.
14. Disconnect the landing gear hydraulic lines at the fittings aft of the spar
and within the fuselage.
15. If the left wing is being removed, it will be necessary to disconnect
pitot and static tubes at the elbows located within the cockpit at thewing butt line.
16. Arrange a suitable fuselage cradle and supports for both wings.
17. Remove the wing jacks.
18. Remove the front and rear spar nuts, washers and bolts.
19. Remove the eighteen main spar bolts.
20. Slowly remove the wing being certain that all electrical leads, cables
and lines are disconnected.

4-15. INSTALLATION OF WING. (Refer to Figure 4-2. )

a. PA-28-140;PA-28-150,-160, -180 and PA-28-235:

NOTE

PA-28-150,-160 Serial Nos. 28-1 to 28-45 incl., 28-47 to

28-54 incl., 28-56, 28-57, 28-61 to 28-77 incl., 28-79 to
28-84 incl., 28-86 to 28-89 incl., 28-92, 28-93 and 28-94.

The subject airplanes indicated by the above serial numbers were equipped
at the factory with wing panel assemblies having a wasHout of 0 ° , (P/N 62010-41
L W and P/N 62010-42 R W).
All airplanes not indicated in the above serial number listing are equipped
with wing panels modified to 20of washout, (P/N 62015-04 L W and P/N 62015-03
R W).
During the service life of the subject airplanes there may be occasion to
replace one or bothof thewingpanels having 0° washout. Undernocircumstances
should one twisted and one nontwisted wing be used on the same airplane. If an
interchange of salvaged nontwisted wing panels is made in the field, the stall
characteristics shall be tested to the requirement of Civil Air Regulation 3.120
by an authorized representative of Piper Aircraft Corporation or the Federal
Aviation Administration. Since the number of airplanes equipped with 0°washout
wing panels is relatively small, this type wing assembly will not be available for
replacement. All replacement wing panels, when required, will be furnished
having the 20 washout.
1. Ascertain that the fuselage is positioned solidly on a support cradle.
2. Place the wing in position for installation, with the spar end a few inches

Reissued: 1/15/81 STRUCTURES

1H2
 PIPER CHEROKEE SERVICE MANUAL

from the side of the fuselage and set on trestles.

3. Prepare the various lines, control cables, etc. for inserting into the
wing or fuselage when the wing is slid into place.
4. Slide the wing into position on the fuselage.
5. Install the eighteen main spar bolts in accordance with the bolt legend.

NOTE

When replacing a wing assembly, ascertain the wing

butt clearance is maintained. (Refer to Sketch A,
Figure 4-2.)

6. Install the bolt, washers and nut that attaches the front spar with the
fuselage fitting. A minimum of one washer is required under the nut, then add
washers as needed to leave a maximum of one and one-half threads visible or a
minimum of the bolt chamfer exposed.
7. Insert the number of washers required between the forward face of the
wing fitting and aft face of the fuselage fitting. The maximum number of washers
allowedis one AN960C-516Land one AN960C-516. It is also acceptable to have
the faces of the fittings against each other. After the required washers are in-
serted between the plates, install the bolt and check to insure that no threads are
bearing on the forward plate prior to installing the nut. Use the shortest bolt
which will leave 0.580 of an inch minimum from the fitting to the end of the bolt.
Add washers, AN960-516, as required, (minimum of one), to leave a maximum
of one andone-half visible thread, or minimum of the bolt chamfer exposed after
the nut is torqued.
8. Torque the eighteen main spar bolt nuts or bolt heads 360 to 390 inch-pounds.Be
certain that the bolts, nuts and washersare installed in accordance with the bolt legend. The
forward spar attachment bolt should be torqued, in accordance with the chart of
recommended torque requirements givenin Section II. Torque the rear spar attachment bolt
from 200 to 225 inch-pounds.
9. Install the wing jacks and the tail support to the tail skid with approxi-
mately 250 pounds of ballast on the base of the tail support. Remove the fuselage
cradle and wing supports.
10. If the left wing was removed, it is necessary that the pitot and static
tubes to be connected at the elbows located within the cockpit at thewing butt line.
On occasion, one tube may be painted red, denoting the pitot tube. Replace or
install clamps where found necessary. In the event that a heated pitot is installed,
the plus lead must be connected at the fuselage.
11. Connect the hydraulic brake line onto the fitting located within the cock-
pit at the leading edge of the wing.
12. Connect the leads to the appropriate posts on the terminal strip and

Reissued: 1/15/81 STRUCTURES

Reissued: 1/15/81 STRUCTURES
 PIPER CHEROKEE SERVICE MANUAL

install the washers and nuts. (For assistance in connecting the electrical lead,
refer to the Electrical Schematics in Section VI.) Place the clamps along the
electrical harness to secure it in position and install the terminal strip dust cover.
13. Remove the cap from the fuel line and connect it at the fitting located
aft of the spar at the wing butt line.
14. Connect the aileron balance and control cables at the turnbuckles that
are located within the fuselage aft of the spar. After the left balance cable has
been inserted through the bracket assembly and connected, install a cotter pin
cable guard into the hold that is provided in the bracket assembly.
15. Connect the flap by placing the flap handle in the full flap position, place
the bushing on the outside of the rod end bearing and insert and tighten bolt.
16. Check the rigging and control cable tension of the ailerons and flaps.
(Refer to Rigging and Adjustment of Ailerons, and Rigging and Adjustment of
Flaps, Section V.)
17. Service and refill the brake system with hydraulic fluid in accordance
with Servicing Brake System, Section II. Bleed the system as given in Section VII
and check for fluid leaks.
18. Service and fill the fuel system in accordance with Servicing Fuel
System, Section II. Open the fuel valve and.check far leaks and flow.
19. Check the operation of all electrical equipment, and pitot and static
system.
20. Remove the airplane from the jacks.
21. Tnstall the cockpit trim panel assembly, spar box carpet, the front and
back seats, and wing butt rubber molding.
22. Replace all the access plates and panels on the wing involved.
b. PA-28R:
1. Ascertain that the fuselage is positioned solidly on a support cradle.
2. Place the wing in position for installation, with the spar end a few inches
from the side of the fuselage and set on trestles.
3. Prepare the various lines, control cables, etc. for inserting into the
wing or fuselage when the wing is eased into place.
4. Slide the wing into position of the fuselage.
5. Install the eighteen main spar bolts in accordance with the bolt legend.
6. Install the bolt, washers, and nut that attaches the front spar and fuse-
lage fitting. A minimum of one washer is required under the nut, then add wash-
ers as needed to leave a maximum of one and one-half threads visible or a mini-
mum of the bolt chamfer exposed-
7. Insert the number of washers required between the forward face of the
wing fitting and aft face of the fuselage fitting. The maximum number of washers
allowed is one ofAN960C-516Land oneAN960C-516. It is also acceptable to have
the faces of the fitting against each other. After the required washers are in-
serted between the plates, install the bolt and check to insure that no threads are

Reissued: 1/15/81 ' 1H4 STRUCTURES

__- - -- - -- - - -- -_

PIPER CHEROKEE SERVICE MANUAL

bearing on the forward plate prior to installing the nut. Use the shortest bolt
which will leave 0.580 of an inch minimum from the fitting to the end of the bolt.
Add washers, AN960-516, as required, (minimum of one), to leave a maximum
of one and one-half visible threads, or minimum of the bolt chamfer exposed
after the nut is torqued.
8. Torque the eighteen main spar bolts to 360 inch pounds. Be certain that
the bolts, nuts and washers are installed in accordance with the bolt legend. The
forward spar attachment bolt should be torqued in accordance with the chart of
recommended torque requirements given in Section II. Torque the rear spar at-
tachment bolt from 200 to 225 pounds.
9. Install the wing jacks and the tail support to the tail skid with approxi-
mately 250 pounds of ballast on the base of the tail support. Removethefuselage
cradle and wing supports.
10. If the left wing was removed, it is necessary that the pitot and static
tubes be connected at the elbows located within the cockpit at the wing butt line.
On occasion, one tube may be painted red, denoting the pitot tube. Replace or
install clamps where found necessary.
11. Connect the hydraulic brake line onto the fitting locatedwithin the cock-
pit at the leading edge of the wing, and the landing gear hydraulic lines at the fit-
tings within the fuselage aft of the spar.
12. Connect the leads to the appropriate posts on the terminal strip and
install the washers and nuts. (For assistance in connecting the electrical leads,
refer to the electrical schematics in Section XI.) Place the clamps along the
electrical harness to secure it in position and install the terminal strip dust cover.
13. Connect the fuel line at the fitting located inside of the wing, by reach-
ing through the access panel on the forward inboard portion of the wheel well.
14. Connect the aileron balance and control cables at the turnbuckles that
are located within the fuselage aft of the spar. After the left balance cable has
been inserted through the bracket assembly and connected, install a cotter pin
cable guard into the hole that is provided in the bracket assembly.
15. Connect the flap by placing the flap handle in the full flap position, place
the bushing on the outside of the rod end bearing, and insert and tighten bolt.
16. Check the rigging and control cable tension of the ailerons and flaps.
(Refer to Rigging and Adjustment of Ailerons, and Rigging and Adjustment of
Flaps, Section V.)
17. Service and refill the brake system with hydraulic fluid in accordance
with Servicing Brake System, Section II. Bleed the system as given in Section
VII and check for fluid leaks.
18. Check the fluid level of the landing gear hydraulic system and fill in
accordance with Servicing Hydraulic Pump/Reservoir, Section II. With the air-
plane setting on jacks, operate the gear through several retraction and extension
cycles to be certain that there are no hydraulic leaks. Bleed the hydraulic sys-

Reissued: 1/15/81 1H5 STRUCTURES

 PIPER CHEROKEE SERVICE MANUAL

tern in accordance with Section VI.

19. Service and fill the fuel system in accordance with Servicing Fuel
System, Section II. Open the fuel valve and check for leaks and flow.
20. Check the operation of all electrical equipment, pitot and static sys-
tem s.
21. Remove the airplane from jacks.
22. Install the cockpit trim panel assembly, spar box carpet, the front
and back seats and wing root rubber.
23. Replace all the access plates and panels on the wing involved.

4-16. EMPENNAGE GROUP.

4-17. STABILATOR.

4-18. REMOVAL OF STABILATOR. (Refer to Figure 4-4.)

NOTE

Before entering the aft portion of the fuselage, attach

a stand to the tail skid for support; and with the use of
a heavy pad, protect the inside of the fuselage. Be
certain to distribute weight on top of the bulkheads so
as not to damage the fuselage skin.

NOTE

Should it be necessary to move the rudder to its ex-

treme left or right for clearance, do so with the use of
the rudder pedals or toe bar.

a. PA-28-150,-160,-180, Serial Nos. 28-1 to 28-2171 incl. and PA-28-235,

Serial Nos. 28-10003 to 28-10605 incl. (The exception being those airplanes with
Piper Kit No. 756 930 or 756 896, Stabilator Trim Modification, installed. Air-
planes with either kit installed, refer to step b.)
1. Remove the access panel to the aft section of the fuselage located at the
back wall of the baggage compartment.
2. Install cable blocks, as illustrated in Figure 4-3, on the stabilator trim
control cable at the first set of pulleys forward of the cable turnbuckle to prevent
the forward portion of the cable from unwrapping.

Reissued: 1/15/81 1H6 STRUCTURES

 PIPER CHEROKEE SERVICE MANUAL

982

Figure 4-3. Methods of Securing Control Cables

3. Disconnect the trim cable at the turnbuckle withinthe aft section of the
fuselage.
4. Relieve tension from the stabilator control cables by loosening one of
the cable turnbuckles in the aft section of the fuselage.
5. Disconnect the stabilator control cables from the stabilator balance arm
by removing cotter pins, nuts, washers, bushings and clevis bolts.
6. Remove the screws from around the upper and lower tail cone fairing
assembly and remove the fairings separately.
7. Disconnect trim indicator cable at trim screw and trim tab control arm
from the trunnion or screw link by removing nut, washers, bushings and bolt.
8. Disconnect the trim assembly from the aft bulkhead of the fuselage by
removing the attaching nuts, washers and bolts of the horizontal and diagonal
support brackets.
9. Move the trim assembly up through the tail cone fairing cutout in the
stabilator, allowing cable to draw out, and tape it to the tail cone out of the way.
10. Remove the stabilator by disconnecting the stabilator at its hinge points
by removing attaching nuts, washers and bolts.
b. PA-28-140; PA-28-150, -160, -180, Serial Nos. 28-2171 and up; PA-28-235, Serial
Nos. 28-10606and up; and PA-28R:
1. Remove the screws from around the upper and lower tail cone fairing
assembly and remove the fairing separately.

Reissued:
Issued: 1/15/81
1/15/81 STRUCTURES
Reissued: 1/15/81
1H7
 PIPER CHEROKEE SERVICE MANUAL

2. Block the trim cable at the barrel of the trim screw assembly to prevent
the cable from unwrapping.
3. Remove the access panel to the aft section of the fuselage located at the
back wall of the baggage compartment.
4. Install cable blocks, as illustrated in Figure 4-3, on the stabilator trim
control cable at the first set of pulleys forward of the cable turnbuckles to prevent
the forward cable from unwrapping.
5. Disconnect the trim cables at the turnbuckles within the aft section of
the fuselage.
6. Relieve tension from the stabilator control cables by loosening one of
the cable turnbuckles in the aft section of the fuselage.
7. Disconnect the stabilator control cables from the stabilator balance arm
by removing cotter pins, nuts, washers, bushings and clevis bolts.
8. Disconnect the trim indicator cable (overhead trim only) and the tab
control arm connecting links from the trim screw by removing nut, washers,
bushings and bolts.
9. Disconnect the trim assembly from the aft bulkhead of the fuselage by
removing the attaching nuts, washers and bolts of the horizontal and diagonal
support brackets.
10. Move the trim assembly up through the tail cone fairing cutout in the
stabilator and remove, with cable, from the airplane.
11. Remove the stabilatorby disconnectingthe stabilator at its hinge points
by removing attaching nuts, washers and bolts.

4-19. INSTALLATION OF STABILATOR. (Refer to Figure 4-4.)

NOTE

A clearance of .25 + .06 of an inch between the stabi-

lator and the side of the fuselage and .18 of an inch
minimum between all parts of the stabilator and the
tail cone assembly must be maintained throughout the
stabilator travel. Use a proper washer combination
on the stabilator hinges to attain the necessary toler-
ances.
a. PA-28-150,-160,-180, Serial Nos. 28-1 to 28-2171 incl. and PA-28-235,
Serial Nos. 28-10003 to 28-10605 incl. (The exception being those airplanes with
Piper Kit No. 756 930 or 756 896, Stabilator Trim Modification, installed. Air-
planes with either kit installed, refer to step b.)
1. Insert the stabilator in position and install attaching hinge bolts, washers
and nuts.

Reissued: 1/15/81 1H8 STRUCTURES

 PIPER CHEROKEE SERVICE MANUAL

2. Move the trim assembly through the cutout in the stabilator and attach the
brackets of the assembly to the aft bulkhead with bolts, washers and nuts. Draw the trim
cable around the idler pulley and trim drum, and insert the cable end into the fuselage.
3. Attach the stabilator control cables to the stabilator balance arm with clevis
bolts, bushings, washers,nuts and cotter pins.
4. Connect the fore and aft end of the trim cable at the turnbuckle within the aft
section of the fuselage.
5. Removethe cable blocks from the trim control cable.
6. Set stabilator control cable tension and check riggingand adjustment according
to Riggingand Adjustment of Stabilator, Section V.
7. Set stabilator trim control cable tension and check rigging and adjustment
according to instructions in Section V. During this procedure, connect the trim indicator
cable and tab control arm to the trim screw trunnion or links with bolt, washers,bushings
and nut. Insure that the tab attachment bolt head is on the side next to the trim indicator
cable to insure no interference with indicator cable.
8. Remove the pad from the aft section of the fuselage and replace the access
panel.
9. Install the tail cone fairingand remove tail stand.
b. PA-28-140; PA-28-150, -160, -180, Serial Nos. 28-2171and up; PA-28-235, Serial
Nos. 28-10606and up; and PA-28R:
1. Insert the stabilator in position and install attaching hinge bolts, washersand
nuts.
2. Move the trim assembly through the cutout in the stabilator and attach the
brackets of the assembly to the aft bulkhead with bolts, washersand nuts. Insert the trim
cable ends into the fuselage.
3. Attach the stabilator control cables to the stabilator balance arm with clevis
bolts, bushings,washers,nuts and cotter pins.
4. Connect the ends of the fore and aft trim cables at the turnbuckles within the
aft section of the fuselage.
5. Remove the cable block from the trim control cable within the fuselage.
6. Set stabilator control cable tension and check riggingand adjustment according
to Riggingand Adjustment of Stabilator, Section V.
7. Remove the cable blocks from the trim cable at the barrel of the trim screw
assembly.
8. Set stabilator trim control cable tension and check rigging and adjustment
according to instructions in Section V. During this procedure, connect the trim indicator
cable (overhead trim only) and the tab control arm to the trim screw, with the connecting
links of the control arm, with bolt, bushings, washers and nut. Insure that the tab
attachment bolt head is on the side next to the trim indicator cable to insure no interference
with indicator cable.
9. Remove the pad from the aft section of the fuselage and replace the access
panel.
10. Install the tail cone fairingand remove tail stand.

Reissued: 1/15/81 1H9 STRUCTURES

 1H10
INTENTIONALLY LEFT BLANK
 PIPERCHEROKEESERVICEMANUAL

C335
908
1791
SKETCHA

SKETCHB 908

868
907

SKETCHC

Al16

SKETCHF
SKETCHE A109 BOLT AN3-11
NUT AN310-3

BOLT AN3-5A
WASHER AN960-10L
4 REQ.
SKETCHD

Figure 4-4. EmpennageGroup Installation

Reissued:1/15/81 1H11 STRUCTURES

 PIPER CHEROKEE SERVICE MANUAL

4-20. STABILATORTRIMTAB.

4-21. REMOVALOF STABILATORTRIM TAB. (Refer to Figure 4-4.)

a. Disconnect the stabilator trim control rod by removing the bolts that attach the
control rod to the stabilator trim tab.
b. Remove the stabilator trim hinge pins by cutting one end of the wire pins and
removing.
c. The stabilator trim tab can now be removed.

4-22. INSTALLATIONOF STABILATORTRIM TAB. (Refer to Figure 4-4.)

a. Place the trim tab in position on the aft end of the stabilator.
b. Insert new pins and secure by bending the end to a 45 degreeangle.
c. Install the control rod and attach with the four bolts and washers.

4-23. RUDDER.

4-24. REMOVALOF RUDDER.

a. Remove the screwsfrom around the upper tail cone fairing assemblyand remove the
fairing.
b. Remove the rudder tip by removing the attaching screws and disconnect the tail
position light wire at the quick disconnect located at the tip of the rudder. Open the access
panel in the rear of the baggage compartment to gain access to the aft section of the
fusleage.
c. Relieve the cable tension from the rudder control system by loosening one of the
cable turnbuckles in the aft section of the fuselage.
d. Disconnect the two control cables from the rudder horn by removing the cotter
pins, nuts, washers,bushingsand bolts.
e. Remove the cotter pins, nuts, washers and bolts from the upper and lower rudder
hinge pivot points.
f. Pull the rudder up and aft from the vertical fin.

4-25. INSTALLATIONOF RUDDER. (Refer to Figure 4-4.)

a. Place the rudder in position and install the hinge bolts, washers,nuts and cotter pins.

Issued:
1/15/81 1H13 STRUCTURES
 PIPER CHEROKEE SERVICE MANUAL

NOTE

Use any washer combination of the hinge assembly to

suit best the centering and operation of the rudder.

b. Connect the tail position light electrical lead at the quick disconnect and
cover the connector with an insulating sleeve. Tie both ends of the sleeve with
number six electrical lacing twine.
c. Connect the control cables to the rudder horn with bolts, washers, nuts and
cotter pins.
d. Check the rudder in accordance with Rigging and Adjustment of Rudder,
Section V.
e. Install the upper tail cone fairing and rudder tip and secure with the attach-
ment screws. Secure the access panel to the aft section of fuselage.

4-26. VERTICAL FIN.

4-27. REMOVAL OF VERTICAL FIN.

a. Remove the screws from the upper and lower tail cone fairing, the fin tip
cover and the fairing at the forward base of the fin.
b. Remove the rudder per instructions given in Paragraph 4-24.
c. Disconnect the leads from the antenna terminals (optional) and attach a line
to the leads to assist in reinstallation.
d. Disconnect the wire antenna (optional) that attaches to the leading edge of
the fin.
e. Disconnect the positive lead to the rotating beacon (optional) and attach a
line prior to removal. Disconnect the ground lead by removing the attachment
screw.
f. Remove the stabilator trim assembly and aft trim cable in accordance with
Removal of Stabilator Trim Assembly (Aft), Section V.
g. Remove the bolt and washer that attaches the leading edge of the fin to the
fuselage.
h. Remove the nuts, washers and bolts that secure the fin spar to the aft bulk-
head and remove the vertical fin.

4-28. INSTALLATION OF VERTICAL FIN.

a. Insert the vertical fin into position and install the bolts, washers and nuts
that secure the fin spar to the aft bulkhead.
b. Install the bolt and washer that attaches the leading edge of the fin to the

Reissued: 1/15/81 1H14 STRUCTURES

 PIPER CHEROKEE SERVICE MANUAL

fuselage.
c. Install the stabilator trim assembly and aft trim cable per instructions
given in Installation of Stabilator Trim Assembly, Section V.
d. Install the rudder per paragraph 4-25.
e. Pull the electrical and antenna leads through the vertical fin with the line
that was attached.
f. Connect the antenna leads to the proper terminals and secure with washers
and nuts.
g. Connect the electrical leads at the disconnects and insulate.
h. Rig and adjust the rudder and trim control cables as given in Section V.
i . Check the operation of the radios and electrical lights.
j . Replace all fairings and access plates, and secure with attaching screws.

4-29. FUSELAGE ASSEMBLY.

4-30. WINDSHIELD.

4-31. REMOVAL OF WINDSHIELD.

a. Remove the collar molding from around the bottom of the windshield and the
trim strip from between the windshield halves by removing the attaching screws.
b. Remove the windshield by raising the lower portion of the windshield and
carefully pulling it out and downward to release the top and side edges.

NOTE

A damaged windshield should be saved since it can be

used as a pattern for drilling required holes in the new
windshield.

c. Clean the old tape and sealer from the windshield channels, strips and di-
vider post.

4-32. INSTALLATION OF WINDSHIELD. (Refer to Figure 4-5.)

a. Be certain that thenew windshield outside contours are the same as that of
the old windshield. It may be found that it is necessary to cut or grind the new
windshield to acquire the proper dimensions.
b. Apply black vinyl plastic tape around the outer edges of the entire wind-
shield.

Reissued: 1/15/81 STRUCTURES

1H15
 PIPER CHEROKEE SERVICE MANUAL

390 963 955

WHITE WHITE
SEALANT SEALANT WHITE VINYL
FOAM TAPE
:I VINYL

BLACK

- BLACK

1800

898 966
WHITE
SEALANT

WHITE
SEALANT
VINYL

BLACK
VINYL TAPE

BLACK
VINYL TAPE
BLACK
VINYL TAPE
F.F

Figure 4-5. WindshieldInstallation (Typical)

STRUCTURES
Reissued: 1/15/81 1H16
 PIPER CHEROKEE SERVICE MANUAL

c. Apply Behr-Manningvinyl foam tape number 560 or equivalent over the plas-
tic tape, completely around the edges of the windshield.
d. Apply Behr-Manning sealant number PRC 5000 or equivalent under the edge
of the moldings and trim strips.
e. Place the windshield in position for installation and slide the windshield aft
and up into place, using caution not to dislocate the tape around the edges. Allow
clearance between the two windshields at the divider post for expansion.
f . Lay sealant at the bottom and center (inboard) of the windshield in the hol-
low between the outside edge and channel.
g. Lay a small amount of sealant under the center trim strip, install and se-
cure.
h. Lay black vinyl tape on the underside of the collar molding, install and se-
cure.
i . Seal with sealant any areas around windshield that mayallow water to pen-
etrate past the windshield.
j . Remove excess exposed sealer to tape.

4-33. SIDE WINDOWS.

4-34. REMOVAL OF SIDE WINDOWS. PA-28 airplanes are equipped witha sin-
gle pane side windows, the exception being the PA-28-235, Serial Nos. 28-10720 to
28-7210033 inclusive, which are installed with double pane side windows. For removal of
both types of windows, the following instructions may be used:
a. Single Panel.
1. Remove the retainer molding from around the window by removing the
attachment screws.
2. Carefully remove the window from the frame.

NOTE

A damaged window should be saved to provide a pattern

for shaping the new window.

3. Remove excess tape and sealer from the window frame and molding.
b. Double Pane.
1. Remove the trim and retainer moldings from around the window by re-
moving the attachment screws.
2. Carefully remove the window from the frame.

Issued: 9 1 68 1H17 STRUCTURES

1H17
 PIPER CHEROKEE SERVICE MANUAL

980 C337

INNER PANE
(LIGHT GAUGE)
OUTER PANE
(HEAVY GAUGE)
WHITE SEALANT

WHITE SEALANT
VINYL FOAM TAPE

ADHESIVE SPONGE
RUBBER

Figure 4-6. Side Window Installation, Figure 4-7. Side Window Installation,
Single Pane (Typical) Double Pane (Typical)

NOTE

A damagedwindow should be saved to provide a pattern

for shaping the new window.

3. Remove excess tape and sealer from the window frame.

4-35. INSTALLATION OF SIDE WINDOWS.

a. Single Pane. (Refer to Figure 4-6.)
1. Cut or grind the new window to the same dimension as the window re-
moved.
2. Apply Behr-Manning vinyl foam tape number 560 or equivalent, on both
sides of the window around the outer edges.
3. Apply Behr-ManningSealant number PRC 5000 or equivalent, completely
around the outer surface of the windows at all attachment flanges.
4. Insert the window in the frame and install the retainer moldings.
5. Secure the molding with attachment screws and tighten until the vinyl
foam tape is 25% compressed by the retainers.
6. Remove the excess exposed sealer and tape.
b. Double Pane. (Refer to Figure 4-7.)
1. Cut or grind the new window to the same dimension as the window re-
moved.
2. Apply Raybestos R-15 black #565C sponge rubber adhesive or equiva-

Reissued: 1/15/81
Reissued:
1/15/81 1H18 1H18
STRUCTUR ES
 PIPER CHEROKEE SERVICE MANUAL

lent, between the edges of the outer (heavy gauge)and inner (light gauge)windows, prior to
installation.
3. Apply Behr-Manning sealant number PRC 5000 or equivalent, completely
around the outer surface of the attachment flanges.
4. Insert the window assemblyin the frame and install the retainer moldings.
5. Secure the window and retainer moldings in position by installing the
attachment screws.
6. Install the trim moldings and attachment screws.
7. Remove the excess exposed sealer from around the window.

4-36. DOOR (ENTRANCE).

4-37. REMOVALOF DOOR.

a. Remove the clevisbolt, washer and bushing from the door holder assembly.
b. Removecotter pins, clevispins and washersfrom serrated door hinges.
c. Remove the door from the airplane.

4-38. INSTALLATIONOF DOOR.

a. Insert the door into position and install the washers, clevis bolts and cotter pins on
the door hinges.
b. For adjustment of door, refer to Paragraph4-39.
c. Hook up and install the clevis bolt, bushing and washer into the door holder
assembly.

4-39. ADJUSTMENTOF DOOR.

a. To acquire the proper vertical adjustment of the door, insert the necessary washer
combination between the cabin door hinge and fuselagebracket assembly.
b. Additional adjustments may be made by tapping out the serrated door hinge,
bushings and rotating them to obtain the hinge centerline location that will provide proper
door fit.
c. To insure long life of door seals and improve sealing characteristics, it is
recommended they be lubricated with a fluorocarbon or similar dry lubricant in a spray can.

4-40. REMOVALOF DOOR LATCHMECHANISM

a. Remove the door latch mechanism by removing the door trim upholstery and the
screwsthat attach the latch plate and latch mechanismto the door.
b. Disconnect the latch pull rod from the inside door handle.
c. Remove the complete latch mechanism.

Reissued: 1/15/81 STRUCTURES

1H19
 PIPER CHEROKEE SERVICE MANUAL

4-41. REMOVALAND INSTALLATIONOF DOOR SEAL SNUBBERS. (Refer to Figure 4-8.)

A. To remove old seals use a thinner, such as toluol. that won't affect the painted surface, and strip off
the old seal.
B. Install the door seal as follows:
1. If the surface has just been painted. allow to dry for a minimum of 2 hours before installing the
seal.
2. Wipe the surface clean with a cleaner solvent. such as DuPont Prep-Sol 3919S.
-NOTE -

Refer to the List of ConsumableMaterialsfor types of

appropriate neopreneadhesive.
3. Make sure both the seal and surface are 65° to 100°F.
4. Adhesive should only be applied to that area to be covered by the seal. If necessary. tape off the
affected area. The adhesive can be thinned as required with toluol. Apply adhesive in a continuous coat of.002
to .010 of an inch thick.
5. Apply a continuous coat of adhesive of the same thickness to the seal.
6. With the adhesive applied to the mating surface and seal. allow them to cure 30 to 60 min. apart
before bonding them in place.
7. With reference to Figure 4-8, make sure the seal is properly aligned before allowing the
surfaces to come in contact. The seal should not be stretched or pulled such that the cross section of the seal is
reduced or distorted. Make sure the door closes properly and that an airtight seal is produced.
8. After positioning the seal. apply pressure to remove air bubbles and assure firm contact.

B95S
DO NOT STRETCH SNUBBER
AROUND CORNERS (TYP) FIGURE 1
ORIENT SNUBBER FLAT VIEW LOOKING INBOARD
WITH THIS SURFACE R.H. SIDE

ADHESIVE

C
I-

STRIKER PLATE

SECTION C-C

Figure4-8. Door Snubber Installation

STRUCTURES
Reissued: 1/15/81 1H20
 PIPER CHEROKEE SERVICE MANUAL

4-42. INSTALLATION OF DOOR LATCH MECHANISM.

a. Place the latch assembly into position on the door.
b. Connect the latch pull rod to the inside door handle.
c. Replace the screws that attach the latch plate and mechanism to the door.
Install the door trim upholstery and secure with screws.

4-43. ADJUSTMENT OF DOOR LATCH MECHANISM. To adjust the door latch,

loosen the screws on the striker plate, make necessary adjustment, and retighten
the screws.

4-44. REMOVAL OF DOOR LOCK ASSEMBLY.

a. Remove the door trim upholstery by removing the attachment screws.
b. Loosen the nut on the lock assemblyand remove the lock by turning it side-
ways.

4-45. INSTALLATION OF DOOR LOCK ASSEMBLY.

a. Install the lock in the door by turning it sideways and placing it through the
opening provided.
b. Replace the nut on the back of the lock assembly and tighten.
c. Replace the door trim upholstery and secure with the attachment screws.

4-46. REMOVAL OF DOOR SAFETY LATCH.

a. PA-28-150, -160,-180 Serial Nos. 28-1 to 28-990 incl:
1. Remove the latch assembly by removing the two knobs and the small
trim plate at the aft end of the latch.
2. Remove the two screws from the inside trim plate and remove the plate.
3. Remove the latch assembly from the door.
b. PA-28-140; PA-28-150, -160, -180, Serial Nos. 28-991 and up; PA-28-235 and
PA-28R:
1. Remove the two handles and the five screws holding the pan on the inside
of the door.
2. Remove the pane and pull the latch assembly through the openingon the
door.

STRUCTURES
Reissued:1/15/81
1H21
 PIPER CHEROKEE SERVICE MANUAL

4-47. INSTALLATION OF DOOR SAFETY LATCH

a. PA-28-150, -160, -180 Serial Nos. 28-1 to 28-990 incl:
1. Place the latch assembly into position for installation.
2. Install the small trim plate on the aft end of the door and on the inside
of the door. Secure in place with the attachment screws.
3. Replace the knobs and tighten. Check latch for proper operation and
that the knobs are free of rubbing on the trim panels.
b. PA-28-140; PA-28-150,-160,-180 Serial Nos. 28-991 and up; PA-28-235
and PA-28R:
1. Place the latch assembly into position for installation.
2. Replace the pan and install the five screws and handles.
3. Check the latch assembly for operation and be certain that it is free of
rubbing on the trim panels.

4-48. ADJUSTMENT OF DOOR SAFETY LATCH. (PA-28-140;PA-28-150,-160,-180,

Serial Nos. 28-991and up; PA-28-235and PA-28R.)
a. To adjust the door safety latch remove the two screws from latch plate found
at the top of the door opening.
b. Remove the plate and turn the loop assembly in or out to make necessary
adjustments.
c. Replace the latch plate and secure with the two attachment screws.

4-49. BAGGAGEDOOR.

4-50. REMOVAL OF BAGGAGEDOOR. With the dooropen removethehinge pin

from the hinge and remove the door.

4-51. INSTALLATION OF BAGGAGEDOOR. Place the door in position so that

the hinge halves are properly matched and install the hinge pin. It will not be
necessary to replace the hinge pin with a new pin if it is free of bends and wear.

4-52. REMOVAL OF BAGGAGEDOOR LOCK ASSEMBLY.

a. With the door open remove the nut from the back of the lock assembly by
use of a special made wrench. (This tool may be fabricated from the dimensions
given in Figure 4-24.)
b. Remove the lock assembly through the front of the door.

Reissued: 1/15/81 STRUCTURES

1H22
 PIPER CHEROKEE SERVICE MANUAL

4-53. INSTALLATIONOF BAGGAGEDOOR LOCKASSEMBLY.

a. Place the lock into position for installation.
b. Install the nut on the lock assemblyand tighten with the use of a special wrench.

4-54. REMOVALOF BAGGAGEDOOR HINGE.

a. Remove the door from the airplane as described in Removal of BaggageDoor,
Paragraph4-49.
b. Remove the hinge half from the airplane or door by drilling out the rivets and
removing the hinge.

4-55. INSTALLATIONOF BAGGAGEDOOR HINGE.

a. Placethe hinge halvestogether and install the hinge pin.
b. Install the door into the closed position and drill the two end rivet holes and install
the rivets.
c. Operate the door and check for proper fit and installation. Drill the remainingholes
and install the rivets.

4-56. RIGGINGINSTRUCTIONS- SEAT BACKLOCKAND RELEASE.(Refer to Figure

4-9.)
a. Loosen screws (1 and 2) and ascertain that clamps (3 and 4) are in a relaxed
condition. (Push-pull cable (6) is able to move within the clamps.)
b. Place a straightedge along the lower surface of bushing (5) of the seat back release.
c. Adjust the push-pull cable (6) by raisingor loweringit until the lower surface of the
stop assembly(7) is parallel to the straightedge.
d. Secure the push-pull cable in this position by tightening screws(1 and 2) on clamps
(3 and 4). The stop (7) should be lubricated and free to swivelwithout excessiveplay.
e. Push on seat back with stop assembly (7) in an engaged position to check
engagement. Rotate the seat back release handle and check for disengagementof seat back.

STRUCTURES
Reissued: 1/15/81
1H23
 `
PIPER CHEROKEE SERVICE MANUAL

A282

SCREW
SCREW
CLAMP
CLAMP
BUSHING
CABLE
STOP ASSY.

STOP SHOULD BE LUBRICATED AND FREE

TO SWIVEL WITHOUT EXCESSIVE PLAY
STRAIGHTEDGE

Figure 4-9. Seat Back Lock

Reissued:1/15/81 1H24 STRUCTURES

 a

0
0

o
 PIPER CHEROKEE SERVICE MANUAL

LEFT, BOTTOM C33B

SEE NOTE 5 1 2
SEE NOTE 4 2
SEE NOTE 6
SEE NOTE 6

3 3,4 SEE NOTE 3

3
5 6 7 5

PA-28-140,-150,-160,-180 AND 23
235

LEFT, TOP

5 6 7 3
SEE NOTE 3
8

3 4

SEE NOTE 5 3
1,2
SEE NOTE 4 1

LEFT, BOTTOM PA-2 8 R ONLY

2
3

3 3 5

8 5

LEFT, TOP

5 6 7 5

I I
4
13

Figure 4-10. Skin Materialsand Thickness(cont.)

Reissued: 1/15/81 STRUCTURES

112
 PIPER CHEROKEESERVICE MANUAL

4-57. STRUCTURAL REPAIRS. Structural repair methods used may be made in accordance
with the regulations set forth in Federal Aeronautics Manual 18 or FAA Advisory Circular
43.13-1A. To assist in making repairs, Figure 4-10 identifies the type and thickness of skin
structure used. Never make a skin replacement or patch from a material thinner than the original
skin. Original material and thickness is recommended and must result in a surface which is as
strong as, or stronger than, the original skin. However, flexibility must be retained so that the
surrounding areas will not receive extra stress.
When making major structural repairs, other than using factory manufactured parts, it is
recommended the manufacturer be contacted. No major alterations are recommended without
contacting the manufacturer.

4-57a. BAGGAGE COMPARTMENT INSPECTION HOLE AND COVER PLATE.

If baggage compartment inspection holes are not already installed, see Paragraph 4-79 for
installation details.

4-58. FIBERGLAS REPAIRS. The repair procedure in this manual will describe the methods
for repair of fiberglas reinforced structures. Paragraph 4-59 describes Fiberglas Touch-Up and
Surface Repairs such as blisters, open seams, delamination, cavities, small holes and minor
damages that have not harmed the fiberglas cloth material. Paragraph 4-60 describes Fiberglas
Fracture and Patch Repairs as puncture, breaks and holes that have penetrated through the structure
and damaged the fiberglas cloth. A repair kit, part number 756 729 will furnish necessary material
for such repairs, is available through Piper Aircraft Dealers.

NOTE
Very carefully follow resin and catalyst mixing instruc-
tions furnished with repair kit.

4-59. FIBERGLAS TOUCH-UP AND SURFACE REPAIRS.

a. Remove wax, oil and dirt from around the damaged area with acetone, Methylethylketone
or equivalent and remove paint to gel coat.
b. The damaged area may be scraped with a fine blade knife or a power drill with a burr
attachment to roughen the bottom and sides of the damaged area. Feather the edge surrounding the
scratch or cavity. Do not undercut the edge. (If the scratch or cavity is shallow and penetrates only
the surface coat, continue to step h.)
c. Pour a small amount of resin into ajar lid or on a piece of cardboard, just enough to fill the
area being worked on. Mix an equal amount of milled fiberglas with the resin, using a putty knife
or stick. Add catalyst, according to kit instruction, to the resin and mix thoroughly. A hypodermic
needle may be used to inject gel into small cavities not requiring fiberglas millings mixed with the
gel.

Interim Revision: February 15, 1995 STRUCTURES

113
 PIPER CHEROKEE SERVICE MANUAL

d. Work the mixture of resin, fibers and catalyst into the damaged area, using
the sharp point of a putty knife or stick to press it into the bottom of the hole and
to puncture any air bubbles which may be present. Fill the scratch or hole above
the surrounding undamaged area about 1/16 inch.
e. Lay a piece of cellophane or waxed paper over the repair to cut off air and
start the cure of gel mixture.
f. Allow the gel to cure 10 to 15 minutes until it feels rubbery to the touch.
Remove the cellophane and trim flush with the surface, using a sharp razor blade
or knife. Replace the cellophane and allow to cure completely for 30 minutes to
an hour. The patch will shrink slightly below the structure surface as it cures.
(If wax paper is used, ascertain wax is removed from surface.)
g. Rough up the bottom and edges of the holewith the electric burr attachment
or rough sand paper. Feather hole into surrounding gel coat, do not undercut.
h. Pour out a small amount of resin, add catalyst and mix thoroughly, using
a cutting motion rather than stirring. Use no fibers.
i . Using the tip of a putty knife or finger tips, fill the hole at about 1/16 inch
above the surrounding surface with the gel coat mixture.
j . Lay a piece of cellophane over the patch to start the curing process. Re-
peat step f, trimming patch when partially cured.
k. After trimming the patch, immediately place another small amount of gel
coat on one edge of the patch and cover with cellophane. Then, using a squeegee
or the back of a razor blade, squeegee level wtih area surrounding the patch,
leave the cellophane onpatch for one or two hours or overnight, for complete cure.
1 . After repair has cured for 24 hours, sand patched the area using a sanding
block with fine wet sandpaper. Finish by priming, again sanding and applying
color coat.

4-60. FIBERGLAS FRACTURE AND PATCH REPAIRS.

a. Remove wax, oil and dirt from around damaged area with acetone, methyl-
ethylketone or equivalent.
b. Using a key hole saw, electric saber saw, or sharp knife cut away ragged
edges. Cut back to sound material.
c. Remove paint three inches back from around damaged area.
d. Working inside the structure, bevel the edges to approximately a 30 degree
angle and rough-sand the hole and the area around it, using 80-grit dry paper.
Feather back for about two inches all around the hole. This roughens the surface
for strong bond with patch.
e. Cover a piece of cardboard or metal with cellophane. Tape it to the out-
side of the structure covering the hole completely. The cellophane should face
toward the inside of the structure. If the repair is on a sharp contour or shaped

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area, a sheet of aluminum formed to a similar contour may be placed over the
area. The aluminum should also be covered with cellophane.
f . Prepare a patch of fiberglas matand cloth to cover an area two inches larger
than the hole.
g. Mix a small amount of resin and catalyst, enough to be used for one stepat
a time, according to kit instructions.
h. Thoroughlywetmat andcloth withcatalyzedresin. Daub resin on mat first,
and then on cloth. Mat should be applied against structures surface with cloth on
top. Both pieces may be wet out on cellophane and applied as a sandwich. Enough
fiberglas cloth and mat reinforcements should be used to at least replace the
amount of reinforcements removed in order to maintain the original strength. If
damage occurred as a stress crack, an extra layer or two of cloth may be used
to strengthen area.
i. Lay patch over hole on inside of structure, cover with cellophane, and
squeegee from center to edges to remove all air bubbles and assure adhesion
around edge of hole. Air bubbles will show white in the patch and they should all
be worked out to the edge. Remove excess resin before it gels on the part. Al-
low patch to cure completely.
j . Remove cardboard or aluminum sheet from outside of hole and rough-sand
the patch and edge of hole. Feather edge of hole about two inches into undamaged
area.
k. Mask area around hole with tape and paper to protect surface. Cut a piece
of fiberglas mat about one inch larger than the hole and one or more pieces of
fiberglas cloth two inches larger than the hole. Brush catalyzed resin over hole,
lay mat over hole and wet out with catalyzed resin. Use a daubing action with
brush. Then apply additional layer or layers of fiberglas cloth to build up patch
to the surface of structure. Wet out each layer thoroughly with resin.
1 . With a squeegee or broad knife, work out all air bubbles in the patch. Work
from center to edge, pressing patch firmly against the structure. Allow patch to
cure for 15 to 20 minutes.
m. As soon as the patch begins to set up, but while still rubbery, take a sharp
knife and cut away extra cloth and mat. Cut on outside edge of feathering. Strip
cut edges of structure. Do this before cure is complete, to save extra sanding.
Allow patch to cure overnight.
n. Using dry 80 grit sandpaper on a power sander or sanding block, smooth
patch and blend with surrounding surface. Should air pockets appear while sand-
ing, puncture and fill with catalyzed resin. A hypodermic needle may be used to
fill cavities. Let cure and resand.
o. Mix catalyzed resin and work into patch with fingers. Smooth carefully and
work into any crevices.
p. Cover with cellophane and squeegee smooth. Allow to cure completely be-
fore removing cellophane. Let cure and resand.

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q. Brush or spray a coat of catalyzed resin to seal patch. Sand patch, finish by priming,
again sanding and applying color coat.

NOTE

Brush and hands may be cleaned in solvents such as acetone

or methylethylketone. If solvents are not available, a strong
solution of detergent and water may be used.

4-61. THERMOPLASTIC REPAIRS. The following procedure will assist in making field
repairs to items made of thermoplastic which are used throughout the airplane. A list of
material needed to perform these repairs is given along with suggested suppliers of the
material. Common safety precautions should be observed when handling some of the
materials and tools used while making these repairs.
a. Surface Preparation:
1. Surface dirt and paint if applied must be removed from the item being repaired.
Household cleaners have proven most effective in removing surface dirt.
2. Preliminary cleaning of the damaged area with perchlorethylene or VM&P
Naptha will generally insure a good bond between epoxy compounds and thermoplastic.
b. Surface Scratches, Abrasion or Ground-in-Dirt: (Refer to Figure 4-11.)
1. Shallow scratches and abraded surfaces are usually repaired by following direc-
tions on containers of conventional automotive buffing and rubbing compounds.
2. If large dirt particles are embedded in thermoplastic parts, they can be removed
with a hot air gun capable of supplying heat in the temperature range of 300° to 400° F. Use
care not to overheat the material. Hold the nozzle of the gun about 1/4 of an inch away from
the surface and apply heat with a circular motion until the area is sufficiently soft to remove
the dirt particles.
3. The thermoplastic will return to its original shape upon cooling.
c. Deep Scratches, Shallow Nicks and Small Holes: (Less than 1 inch in diameter.)
(Refer to Figure 4-12.)
1. Solvent cements will fit virtually any of these applications. If the area to be re-
paired is very small, it may be quicker to make a satisfactory cement by dissolving thermo-
plastic material of the same type being repaired in solvent until the desired paste-like con-
sistency is achieved.
2. This mixture is then applied to the damaged area. Upon solvent evaporation, the
hard durable solids remaining can easily be shaped to the desired contour by filing or sanding.
3. Solvent adhesives are not recommended for highly stressed areas, on thin walled
parts or for patching holes greater than 1/4 inch in diameter.
4. For larger damages an epoxy patching compound is recommended. This type
material is a two part, fast curing, easy sanding commercially available compound.
5. Adhesion can be increased by roughing the bonding surface with sandpaper and
by utilizing as much surface area for the bond as possible.
6. The patching compound is mixed in equal portions on a hard flat surface using a
figure eight motion. The damaged area is cleaned with perchlorethylene or VM&P Naptha
prior to applying the compound. (Refer to Figure 4-13.)
7. A mechanical sander can be used after the compound is cured, providing the
sander is kept in constant motion to prevent heat buildup.

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8. For repairs in areas involving little or no shear stress, the hot melt adhesives,
polyamids which are supplied in stick form may be used. This type of repair has a low cohesive
strength factor.
9. For repairs in areas involving small holes, indentations or cracks in the material
where high stress is apparent or thin walled sections are used, the welding method is suggested.

TABLE IV-I. LIST OF MATERIALS (THERMOPLASTIC REPAIR)

ITEMS DESCRIPTIONS SUPPLIERS

Buffing and Rubbing Automotive Type - DuPont Company

Compounds DuPont #7 Wilmington, Del. 19898

Ram Chemical #69 x 1 Ram Chemicals

Gardena, Cal. 90248

Mirror Glaze #1 Mirror Bright Polish Co.,

Inc.
Irvin, Cal. 92713

Cleaners Fantastic Spray Obtain From Local

Perchlorethylene Suppliers
VM&P Naptha (Lighter
Fluid)

ABS-Solvent Cements Solarite #11 Series Solar Compounds Corp.

Linden, N.J. 07036

Solvents Methylethyl Ketone Obtain From Local

Methylene Chloride Suppliers
Acetone

Epoxy Patching Solarite #400 Solar Compounds Corp.

Compound Linden, N.J. 07036

Hot Melt Adhesives Stick Form 1/2 in. dia. Sears Roebuck & Co.
Polyamids and Hot Melt 3 in. long or Most Hardware Stores
Gun

Hot Air Gun Temp. Range 300 ° to Local Suppliers

400° F

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871

Figure 4-11., Surface Scratches, Abrasions or Ground-in-Dirt

10. This welding method requires a hot air gun and ABS rods. To weld, the gun should
be held to direct the flow of hot air into the fusion (repair) zone, heating the damaged area and
rod simultaneously. The gun should be moved continuously in a fanning motion to prevent
discoloration of the material. Pressure must be maintained on the rod to insure good adhesion.
(Refer to Figure 4-14.)
11. After the repair is completed, sanding is allowed to obtain a surface finish of
acceptable appearance.
d. Cracks: (Refer to Figure 4-15.)
1. Before repairing a crack in the thermoplastic part, first determine what caused the
crack and alleviate that condition to prevent it recurring after the repair is made.
2. Drill small stop holes at each end of the crack.
3. If possible, a double plate should be bonded to the reverse side of the crack to
provide extra strength to the part.
4. The crack should be "V" grooved and filled with repair material, such as solvent
cement, hot melt adhesive, epoxy patching compound or hot air welded, whichever is
preferred.
5. After the repair has cured, it may be sanded to match the surrounding finish.
e. Repairing Major Damage: (Larger than 1 inch in diameter.) (Refer to Figure 4-16.)
1. If possible, a patch should be made of the same material and cut slightly larger
than the section being repaired.
2. When appearances are important, large holes, cracks, tears, etc., should be
repaired by cutting out the damaged area and replacing it with a piece of similar material.
3. When cutting away the damaged area, under cut the perimeter and maintain a
smooth edge. The patch and/or plug should also have a smooth edge to insure a good fit.

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871

Figure 4-12. Deep Scratches, Shallow Nicks and Small Holes

826

THOROUGHLY MIX
USING FIGUREEIGHT
MOTION.

Figure 4-13. Mixing of Epoxy Patching Compound

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4. Coat the patch with solvent adhesive and firmly attach it over the damaged area.
5. Let the patch dry for approximately one hour before any additional work is
performed.
6. The hole, etc., is then filled with the repair material. A slight overfilling of the
repair material is suggested to allow for sanding and finishing after the repair has cured. If
patching compound is used the repair should be made in layers, not exceeding a 1/2 inch in
thickness at a time, thus allowing the compound to cure and insuring a good solid buildup of
successive layers as required.
f. Stress Lines: (Refer to Figure 4-17.)
1. Stress lines produce a whitened appearance in a localized area and generally
emanate from the severe bending or impacting of the material. (Refer to Figure 4-18.)
2. To restore the material to its original condition and color, use a hot air gun or
similar heating device and carefully apply heat to the affected area. Do not overheat the
material.
g. Painting the Repair:
1. An important factor in obtaining a quality paint finish is the proper preparation
of the repair and surrounding area before applying any paint.
2. It is recommended that parts be cleaned prior to painting with a commercial
cleaner or a solution made from one-fourth cup of detergent mixed with one gallon of water.
3. The paint used for coating thermoplastic can be either lacquers or enamels de-
pending on which is preferred by the repair facility or customer. (See NOTE.)

NOTE

It is extremely important that solvent formulations be con-

sidered when selecting a paint, because not all lacquers or
enamels can be used satisfactorily on thermoplastics. Some
solvents used in the paints can significantly affect and degrade
the plastic properties.

4. Another important matter to consider is that hard, brittle coatings that are usually
best for abrasion resistance should not be used in areas which incur high stress, flexing or
impact. Such coating may crack, thus creating a weak area.

4-62. A.B.S. THERMOPLASTIC LANDING GEAR WHEELS AND STRUT FAIRING

REPAIR INSTRUCTIONS. Instructions covering the wheel and strut fairing is contained
in a special Wheel and Strut Fairing Repair Instruction Manual, P/N 761 708V. This manual
is obtainable from Vero Beach Service and Sales Department, Piper Aircraft Corporation,
Vero Beach, Florida 32960.

Reissued: 1/15/81 1110 STRUCTURES

 PIPER CHEROKEE SERVICE MANUAL

B70

Figure 4-14. Welding Repair Method

827

DOUBLERPLATE TO

HOLES

Figure 4-15. Repairing of Cracks

Revised: 10 3 83 STRUCTURES
1I11
 PIPER CHEROKEE SERVICE MANUAL

831

830

828

DAMAGED AREA

Figure 4-16. Various Repairs

1112 STRUCTURES
 PIPER CHEROKEE SERVICE MANUAL

827

STRESS
LINES

Figure 4-17. Repair of Stress Lines

829

PROFILE VIEW INDICATING

DAMAGED AREA

Figure 4-18. Repair of Impacted Damage

Revised: 10 3 83 1113 STRUCTURES

 PIPER CHEROKEE SERVICE MANUAL

4-63. SAFETY WALKREPAIR.

4-64. SURFACEPREPARATIONFOR LIQUID SAFETY WALK.

a. Clean all surfaces with a suitable cleaning solvent to remove dirt, grease and oils.
Solvents may be applied by dipping, spraying or mopping.
b. Insure that no moisture remains on the surface by wiping with a clean cloth.
c. Outline the area to which the liquid safety walk compound is to be applied, and
mask adjacent surfaces.
NOTE
Newly painted surfaces, shall be allowed to dry for 2.5 hours
minimum prior to the application of the safety walk.
4-65. PRODUCTLISTINGFOR LIQUID SAFETY WALKCOMPOUND.
a. SuggestedSolvents:
Safety Solvent per MIL-S-18718
Sherwin WilliamsLacquer Thinner R7KC120
Glidden Thinner No. 207
b. Safety Walk Material:
WalkwayCompound and matting nonslip
(included in Piper Part No. 179872.)
4-66. APPLICATION OF LIQUID SAFETY WALK COMPOUND.Liquid safety walk
compound shall be applied in an area, free of moisture for a period of 24 hours minimum
after application. Do not apply when surface to be coated is below 50 ° F. Apply liquid
safety walk compound as follows:
a. Mix and thin the liquid safety walk compound in accordance with the
manufacturer's instructions on the container.
b. Coat the specified surfaces with a smooth, unbroken film of the liquid safety walk
compound. A nap type roller or a stiff brush is recommended, using fore and aft strokes.
c. Allow the coating to dry for 15 minutes to one hour before recoating or touch-up; if
required after application of the initial coating.
d. After recoating or touch-up, if done, allow the coating to dry for 15 minutes to one
hour before removingmasking.
NOTE
The coated surface shall not be walked on for six hours
minimum after application of final coating.
4-67. SURFACE PREPARATION FOR PRESSURE SENSITIVE SAFETY WALK. The
areas to which the pressure sensitive safety walk is to be installed must be free from all
contaminates and no moisture present. If liquid safety walk is installed the area must be
prepared as follows:
a. Area must be masked off to protect painted surfaces.
b. Apply suitable stripper MEK Federal Spec. TT-M-261, U.S. Rubber No. 3339 to
wingwalk compound. As compound softens remove by using putty knife or other suitable
tool.
c. Area must be clean and dry prior to painting.
d. Prime and paint area.

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STRUCTURE
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 PIPER CHEROKEE SERVICE MANUAL

NOTE

Newly painted surfaces, shall be allowed to dry for 2.5 hours

minimumprior to the application of the safety walk.
4-68. APPLICATIONOF PRESSURE SENSITIVESAFETY WALK. (Kit 763 848V)
Wipe area with a clean dry cloth to insure that no moisture remains on surface. Do not
apply when surface temperature is below 500 F. Apply pressure sensitive safety walk as
follows:
a. Peel back the full width of the protective liner approximately 2 inches from the
leading edge of the safety walk.
b. Apply the safety walk to the wing area, begin at the leading edge, insure proper
alignment and position from wing lap.
c. Remove the remaining protective liner as the safety walk is being applied from front
to back of wing area.
d. Roll firmly with a long handled cylindrical brush in both lengthwise directions.
Make sure all edges adhere to the wing skin.
e. Install and rivet leadingedge retainer.

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 PIPER CHEROKEE SERVICE MANUAL

4-69. CONTROLSURFACEBALANCING.

4-70. CHECKINGCONTROLSURFACEBALANCE. The movable control surfaces have

been statically balanced at the time of installation at the factory and normally should not
require rebalancing. Where possible the control surfaces were set with the balance weight on
the heavy side of the limits, to permit limited repair or paint touch-up without adjusting the
balance weight. It should be noted however, that spare control surfaces are delivered
unpainted and the static balance will not necessarily fall within the limits provided, this is
more pronounced on the stabilators and rudders. The completed control surface, including
paint, should be within the limits givenin Table IV-II. If the surface is not to be painted, the
balance weight will probably require adjustment. All replacement control surfaces, or
surfaces that have been repainted or repaired, should be rebalanced according to the
procedures given in Paragraphs 4-69 thru 4-75. The static balance of the surfaces must be as
specified in Table IV-II.
Before balancing any control surface, it must be complete including tip, trim/servo tabs
and tab actuating arms or push rods with bearingsas applicable,and all optional equipment
which is mounted on or in the control surface when it is flown, including paint, position
lights and wiring, static wicks, scuff boots, etc.
If optional equipment is added or removed after balancing,the control surface must be
rebalanced. During balancing, trim/servo tabs must be maintained in their neutral positions.

4-71 CHECKINGCONTROLSURFACESFREE PLAY. The following checks are

recommended before balancing to ascertain the amount of "free play" in the stabilator,
stabilator trim tab and aileron:
a. Stabilator: Check the stabilator for any "free play" at its attachment points by
grasping each half near the tip and gently trying to move it up and down, fore and aft, and
in and out. No play is allowed.
b. Stabilator Trim Tab: Set the stabilator trim tab in neutral position. This neutral
position is determined with the airplane properly rigged per instructions givenin Section V
of this Service Manualand the trim indicator at its neutral position. Obtain a straightedge
long enough to extend from the ground up to a few inches above the trim tab trailing edge.
Place the straightedge next to the trim tab inboard (center) trailing edge, secure the
stabilator in neutral and graspingthe tab, gently move it up and down, mark the limit of tab
free play on the straightedge.The overall travel (free play) must not exceed 0.15 of an inch.
The use of a dial indicator and fixed stand is recommended.
c. Aileron: Set the aileron in its neutral position and secure. Obtain a straightedgelong
enough to extend from the ground up to a few inches above the aileron trailing edge. Place
the straightedge next to the aileron trailing edge and gently move the aileron up and down,
mark the limit of travel (free play) on the straightedge.The overall travel (free play) must
not exceed 0.24 of an inch. Should free play exceed the limit stated make necessary repairs
as required to eliminate excessive free play. Grasp the aileron and move it spanwise
(inboard/outboard) to insure maximum end play of .035 of an inch is not exceeded.

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 PIPERCHEROKEESERVICEMANUAL

TABLE IV-II. BALANCING SPECIFICATIONS

Maximum Limits - Flight Conditions

STATIC BALANCE LIMITS (INCH-POUNDS)

SERIAL NOS. HEAVY SIDE HEAVYSIDE

SURFACE MODEL EFFECTED LEADING EDGE TRAILINGEDGE

S PA-28-140 THRU 28-7325614 0 TO -30

T PA-28-140 28-7425001 AND UP 0 TO -30
A PA-28-150 ALL 0 TO -30
B PA-28-160 ALL 0 TO -30
I PA-28-180 NON-STRETCHED 0 TO -30
L STABILATOR
A PA-28-180 STRETCHED STABILATOR
T 7305001 TO 7305601 +5 TO -40
O PA-28-180 28-7405001 AND UP +5 TO -40
R PA-28R-180/200 TO 7235000 -5 TO -14
S PA-28R-200 STRETCHED STABILATOR
7235001 TO 7335446 -5 TO -40
PA-28R-200 28R-7435001 AND UP -5 TO -40
PA-28-235 NON-STRETCHED
STABILATOR -5 TO -14
PA-28-235 7310001 TO 7310176 +5 TO -40
PA-28-235 28-7410001 AND UP +5 TO -40

R PA-28-140 UP TO 28-7325614 0 TO -20.9

U PA-28-140 28-7425001 AND UP O TO -13
D PA-28-150 ALL 0 TO -20.9
D PA-28-160 ALL 0 TO -20.9
E PA-28-180 THRU 7305000 0 TO -20.9
R PA-28-180 7305001 TO 7305611 0 TO -25.0
I S PA-28-180
PA-28R-180
7435001 AND UP
THRU 7235000
0
0
TO
TO
-13
-15
PA-28R-200 THRU 7235000 0 TO -15
PA-28R-200 7235001 TO 7335455 0 TO -14
PA-28R-200 7435001 AND UP 0 TO -13
PA-28-235 THRU 7310000 0 TO -15
PA-28-235 731001 TO 7310187 0 TO -14
PA-28-235 741001 AND UP 0 TO -14

A PA-28-140 ALL 0 -17

I PA-28-150 ALL 0 -17
L PA-28-160 ALL 0 -17
E PA-28-180 ALL 0 -17
R PA-28R-180 ALL -15
ALL +2
+2 -15
PA-28R-200
N PA-28-235 ALL +2 -20

STRUCTURES
Revised: 10/3/83
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 PIPER CHEROKEE SERVICE MANUAL

4-72 BALANCING EQUIPMENT (Refer to Figure 4-19). The balancing must be done
using a suitable tool capable of measuring unbalance in inch-pounds from the centerline of
the control surface hinge pin. A suggested tool configuration is shown in Figure 4-17. Other
tool configurations may be used, provided accuracy is maintained and recalibration capability
is provided. The tool shown in Figure 4-17 may be calibrated by placing it on the control
surface to be balanced with the balance points over the control surface hinge centerline and
the balance bar parallel to the cord line. Position the trailing edge support to align the tool
with the control surface cord line and secure in this position. Remove the tool without dis-
turbing the trailing edge support and balance the tool by adding weight to the light end as
required. (The movable weight must be at the centerline.) Place the tool on the control surface
perpendicular to the hinge centerline as shown in Figures 4-18 and 4-19. Read the scale when
the bubble level has been centered by adjustment of the movable weight.

4-73. BALANCING AILERONS. (Refer to Figure 4-20.) Position the aileron on the
balancing fixture in a draft free area and in a manner which allows unrestricted movement of
the aileron. Place the tool on the aileron, avoid rivets and keep the beam perpendicular to the
hinge centerline. Calibrate the tool as described in Paragraph 4-72. Read the scale when the
bubble level has been centered by adjustment of the movable weight and determine the static
balance. If the static balance is not within the limits specified in Table IV-II, proceed as
follows:
a. Leading Edge Heavy: This condition is highly improbable; recheck measurements
and calculations.
b. Training Edge Heavy: There are no provisions for adding weight to balance weight to
counteract a trailing edge heavy condition; therefore, it will be necessary to determine the
exact cause of the unbalance. If the aileron is too heavy because of painting over old paint, it
will be necessary to strip all paint from the aileron and repaint. If the aileron is too heavy re-
sulting from repair to the skin or ribs, it will be necessary to replace all damaged parts and
recheck the balance.

Revised: 10/3/83 STRUCTURES

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 PIPER CHEROKEE SERVICE MANUAL

4-74. BALANCING RUDDER. (Refer to Figure 4-20.)To balance the rudder, the
assembly must be complete including the tip assembly with all attaching screws and the posi-
tion light wiring. Place the complete assembly horizontally on knife edge supports in a draft-
free area in a manner that allows unrestricted movement. Place the tool on the rudder with
the beam perpendicular to the hinge centerline. Calibrate the tool as described in Para-
graph 4-72. Read the scale when the bubble level has been centered by adjustment of the
movable weight and determine the static balance limit. If the static balance is not within the
limits given in Table IV-II, proceed as follows:
a. Nose Heavy: This condition is highly improbable; recheck calculations and
measurements.
b. Nose Light: In this case, the mass balance weight is too light or the rudder is too
heavy because of painting; it will be necessary to strip the paint and repaint. If the rudder is too
heavy as a result of repairs, the repair must be removed and the damaged parts replaced.

Revised: 10 3 83 1I19 STRUCTURES

 PIPER CHEROKEE SERVICE MANUAL

C368

3 LB MOVABLE WEIGHT WITH

NUTS AND OR
WASHERS ADDED
AS REQUIRED
TO BALANCE
TOOL ITSELF

SURFACE CHORD LINE

BEAMBALANCING
5 FT. EXTRUDED CHANNEL
BOLT (USED FOR
BALANCING THE
TOOL ITSELF ONCE
THE TRAILING
EDGE SUPPORT
HAS BEEN SET)

HINGE CENTERLINE
MARK GRADUATIONS IN INCHES
PLACED DIRECTLYOVER
HINGE LINE OF CONTROL SURFACE
HORIZONTALLY
ADJUSTABLE FOR
SETTING TOOL TO
WIDTH OF CONTROL
SURFACE

BUBBLE LEVEL

SET SCREW

VERTICALLY AND HORIZONTALLY

ADJUSTABLETRAILING EDGESUPPORT

VERTICALLYADJUSTABLE
FOR SETTINGBEAM
PARALLEL TO CHORD
LINEOF CONTROLSURFACE

Figure 4-19. Control Surface Balance Tool

Reissued: 1/15/81 STRUCTURES

1I20
 PIPER CHEROKEE SERVICE MANUAL

A12r

HOLDING
FIXTURE BALANCING TOOL
(REFERTO FIG. 4-19)

LEVEL SUPPORT

Figure 4-20. Aileron and Rudder Balance Configuration

Revised: 10/3/83 STRUCTURES

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 PIPER CHEROKEE SERVICE MANUAL

NOTE
The 1974and up models of the PA-28-140and PA-28-180,all
PA-28-235, PA-28R-180 and PA-28R-200 have a non-
adjustable mass balance weight molded in the nose of the
rudder tip. All rudders should be maintained within the
static balance weights provided in Table IV-II.

4-75. BALANCING STABILATOR. (Refer to Figure 4-21.) To balance the stabilator, the
assembly must be complete including the trim tab, the tab push rod and end bearing,
stabilator tips and all attaching screws.Beforebalancing,tape the trim tab in neutral position
with a small piece of tape. Place the complete assemblyon the knife edgesupports in a draft-
free area in a manner that allows unrestricted movement. Place the tool on the stabilator with
the beam perpendicular to the hingecenterline.Do not place the tool on the trim tab. Calibrate
the tool as describedin Paragraph 4-72 Read the scale whenthe bubble levelhas been centered
by adjustment of the movable weight and determine the static balance limit. If the static
balance is not within the limits given in Table IV-II, proceed as follows:
a. If the stabilator is out of limits on the leading edge heavy side, removebalance plates
from the mass balance weight until the static balance is within limits. Do not attempt to
adjust the stabilator tip balance weight.
b. If the stabilator is out of limits on the trailing edgeheavy side, add balanceplates to
the mass balance weight until the static balanceis within limits.

Figure 4-21. Stabilator Balance

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 PIPER CHEROKEE SERVICE MANUAL

4-76. AILERON BALANCE WEIGHT MODIFICATION. (PA-28-140, Serial Nos.

28-20002 to 28-25547 incl.; PA-28-150,-160, -180, SerialNos. 28-1 to 28-5339 incl.; PA-28-235,
Serial Nos. 28-10003 to 28-11235 incl.; PA-28R-180, Serial Nos. 28-30005 to 28-31119 incl.)
To facilitate the use of new aileron balance weight assembly (P/N 66766-00) on above stated
airplanes, it will be necessary to modify the balance weight cutout in the wing rib. (Refer to
Figure 4-22.)The hole pattern in the new balance weight bracket is the same as the old bracket
with the exception of two holes. When replacing the old bracket with the new one, it is per-
missible to use the new bracket as a hole template to drill the two new holes at their proper
location. To install the balance weight assembly, the following procedure may be used:
a. Remove the aileron per Paragraph 4-8.
b. Remove the old balance weight by drilling out the rivets from around the perimeter
of the bracket.
c. Modify the wing end rib, balance arm hole as shown in Figure 4-21.
d. Using the new bracket as a template, drill the two new holes in the rib. (Refer to
Figure 4-22.)
e. Place six cherry lock rivets, CR22494-2, in the holes within the bracket and set the
rivets.
f. Replace the six rivets around the perimeter of the bracket with MS20470AD 3-3,
and set.
g. Prior to installation, paint metal parts where necessary.
h. Install the aileron per Paragraph 4-9.

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 PIPER CHEROKEE SERVICE MANUAL

969

.50R.

Figure 4-22. Wing Rib Modification

885.

RIVETS - MS20470AD3-3

Figure 4-23. Balance Weight Assembly Installation

Reissued: 1/15/81 STRUCTURES

1124
 PIPER CHEROKEE SERVICE MANUAL

888

1.25"

.44"
.88"
.19"

1.75"

Figure 4-24. Fabricated Tool for Baggage Door Lock

4-77. FLAP INSPECTION AND MODIFICATION. (Refer to Figure 4-1.) Inspect

the aft flap attaching point for security. If it is found secure, no modification is
required. If the clevis bolt appears to be working loose from the anchor nut, the
attachment point should be modified in accordancewith the following instructions.
a. Remove the clevis bolt and related parts from the inboard flap hinge at-
taching point.
b. The skin on the flap must be modified in accordance with Figure 4-1.
c. Remove the existing anchor nuts from the inboard flap hinge.
d. Install a new clevis bolt and related parts and secure with castellated nuts
and cotter pins.

4-78. STABILATOR DRAIN HOLES. In order to prevent the accumulation of

water or ice in the stabilator when the aircraft is parked, it is recommended
that drain holes be added in accordance with Figure 4-25.

Reissued: 1/15/81 STRUCTURES

1J1
 PIPER CHEROKEE SERVICE MANUAL

924

1.13

43.20

.191 HOLE
(4 PLACES)

EDGE OF LEADING
EDGE OF SKIN

FWD
FWD.
STABILATOR
(BOTTOM VIEW)

Figure 4-25. Additional Drain Holes in Stabilator

Reissued: 1/15/81 J2 STRUCTURES

 PIPER CHEROKEESERVICEMANUAL

4-79. BAGGAGE COMPARTMENT INSPECTION HOLE AND COVER PLATE.

(See latest revision of Piper Service Bulletin 977.)

a. General.
Airplanes manufactured before 1979 may not have had control cable inspection access
holes in the baggage compartment floor. The following is a method of fabricating inspection
access holes in the floor of the baggage compartment, if desired.
b. Baggage Compartment Inspection Holes Fabrication Procedure. (Refer to Figure 4-26.)
While Figure 4-26 shows the hole in the left side of the baggage compartment, a
similar hole is also cut out in the right side baggage compartment floor. Installation will
require two each inspection access covers, Piper P/N 62109-00.

1. Layout cut lines

(a) Gain access to baggage compartment.

(b) Carefully remove:
(1) Right side baggage compartment Royalite plastic close out panel.
(2) Rear close out panel.
(3) Carpeting from baggage compartment floor.
(c) Determine and mark a reference center line running through baggage
compartment. Refer to Figure 4-26 for measurements.
(d) Measure two points 14.99 inches each side of the reference centerline. Joining
these two points will form the centerlines of each inspection hole.
(e) Measure two points on each side of each centerline of both holes at distances of
8.48 inches and 10.98 inches from the aft edge of the baggage compartment
floor.
(f) Connect the two 8.48" points and the two 10.98" points so that the resulting lines
cross the centerline of each hole.
(g) Using the intersection of the lines constructed in step (f) with each hole's center-
line as the center, scribe an arc having a radius of 2.00"
(h) Draw a line (four lines total) tangent to each side of the arcs constructed on step (g).
(i) There should now be two ovals, like the one in Figure 4-26, laid out on each side
of the baggage compartment floor.

2. Cutting the holes.

- CAUTION-
Baggage compartment flooring is made of 0.025
inch thick aluminum. Use care when cutting
through flooring so as not to damage cables and
wiring routed below the floor.
(a) Drill a 1/4 inch hole inside of, and adjacent to, one of the scribed lines layed out
for each hole.
(b) Using a 1/8 inch router bit, cut out the two inspection holes by following the lines
layed out on each side of the baggage compartment floor.
(c) Deburr each cut edge using a file or emery wheel.

Interim Revision: February 15, 1995 STRUCTURES

1J3
 PIPER CHEROKEE SERVICE MANUAL

3. Installing covers.

(a) Lay one of the 62109-00 covers over one of the inspection holes. Using the
screw holes in the cover, scribe the position for the screw holes on the baggage
compartment floor.
(b) Drill a 0.120 inch hole in baggage compartment floor at each position layed out
in step (a).
(c) Attach cover to flooring with No.8 X 0.38 corrosion resistant steel sheet metal
screws.
(d) Repeat steps (a) through (c) on remaining hole.

4. Install baggage compartment rear and side close out panels.

5. Install baggage compartment floor carpet.

InterimRevision: February15, 1995 STRUCTURES

1J4
 PIPER CHEROKEESERVICE MANUAL

21.80"

0 0

14.99" —

2.28" R
TYP

2.00" R
o TYP;M
0.120" HOLETHRU
N0.8 X 38 CRESTR USS
RECESSED HEADSHEET
METALSCREWS (16 REQD

10.98"

8.48"

AFT
'V
19.11"

Figure 4-26. Baggage Compartment Inspection Holes Cutout Details

Interim Revision: February 15, 1995 STRUCTURES

1J5
PIPER CHEROKEE SERVICE MANUAL

1J6 THRU 1L24

INTENTIONALLY LEFT BLANK

1J6
 CHEROKEE
SERVICE
MANUAL
CARD2 OF4

PA-28-140
PA-28-150
PA-28-160
PA-28-180
PA-28-235
PA-28R-180
PA-28R-200

PIPERAIRCRAFT
CORPORATION
NUMBER
(PART 753586) 2A1
 TABLE
OFCONTENTS AIX
NO.1
AEROFICHE
CARD IIIX
INTRODUCTION
...................... . 1A19 IIX
II ANDSERVICING........
HANDLING IX
MODIFICATION

IV . . ........... X
IV .................... NO.2
CARD
AEROFICHE 1
V .......... . . CONTROLS
SURFACE VIIIA
(PA-28R)
SYSTEM
HYDRAULIC

VII .. .............. LANDING

GEARAND
BRAKE
SYSTEM. IIIA
VIIA..... GEAR
. LANDING BRAKE
AND (PA-28R)
SYSTEM VIIA
VIII . ..... POWER (PA-28)
PLANT 2K2
VIII .. . . . . . . . (POWER (PA-28)
PLANT IA
VIIIA
............. .. A
FUELSYSTEM

X 3D18
X . ........
. . .INSTRUMENTS 3D18
NO.4
CARD
AEROFICHE
XI ELETRICAL 4A8
XII . ........
ELECTRONICS 411
XIII AND
HEATINGVENTILATING

ANDUTILITIES
ACCESSORIES
 PIPER CHEROKEE SERVICE MANUAL

LIST OF ILLUSTRATIONS (cont)

Figure Aerofiche
Grid No.
5-1. Control Column Assembly, PA-28-140,-150, -160,
-180 and -235 ............................................ 2A15
5-2. Control Column Assembly, PA-28R ................... ......... 2A 16
5-3. Aileron Controls .................................. .......... 2A20
5-4. Bellcrank RiggingTool. PA-28-140,-150, -160, -180, -235.......... 2A23
5-5. Bellcrank Rigging Tool. PA-28R ............................... 2A23
5-6. Aileron RiggingTool ........................................... 2A24
5-7. Stabilator RiggingTool ....................................... 2B3
5-8. Stabilator Controls ........................................... 2B4
5-9. Stabilator Trim Control (Overhead Control) ..................... 2B8
5-10. Methods of Securing Trim Cables ............................... 2B10.
5-11. Stabilator Trim Control (Floor Control). ... ......... ........ 2B18
5-12. Rudder and Steering Pedal Assembly ........................... 2B24
5-13. Rudder Controls ............. .....
. . .. . . ... ...... . 2C4
5-14. Rudder Rigging Tool ............................ ........ 2C5
5-15. Clamping Rudder Pedals ...................................... 2C5
5-16. Rudder and Stabilator Travel Adjustments ...................... 2C6
5-17. Rudder Trim Control ......................................... 2C8
5-18. Flap Controls........... ........ ........... 2C10
5-19. Flap Step Adjustment ................... 2C12
5-20. Flap Rigging Tool ............................................ 2C14
5-21. Fabricated Aileron Bellcrank Rigging Tool ...................... 2C15
5-22. Correct Method of Installing Rod End Bearings .................. 2C15
5-23. Fabricated Aileron and Flap Rigging Tool ....................... 2C16
5-24. Fabricated Stabilator Rigging Tool ............................. 2C17
5-25. Fabricated Rudder Rigging Tool ............................... 2C18
6-1. Schematic Diagram of Hydraulic System ........................ 2D5
6-2. Hydraulic System Installation .................................. 2D6
6-3. Hydraulic Pump/Reservoir, Exploded View..................... 2D10
6-4. Test and Adjustments of Hydraulic Pump ....................... 2D14
6-5. Pump Shock Mounts ......................................... 2D16
6-6. Checking Aligning Brackets of Gear Back-Up Extender
Actuator ............................................... 2D
2D17
17
6-7. Gear Back-Up Extender Actuator .............................. 2D21
6-8. Nose Gear Actuator Cylinder .................................. 2E2
6-9. End Gland Locking Device .................................... 2E4
6-10. Main Gear Actuating Cylinder ................................. 2E5
6-11. Gear Back-Up Extender Actuator Aligning Tool.................. 2E20

Revised: 4 23 S42A4 2A4

 PIPER CHEROKEE SERVICE MANUAL

LIST OF ILLUSTRATIONS (cont)

Figure Aerofiche
Grid No.
7-1. Nose Gear Oleo Strut Assembly ................................ 2F2
7-2. Nose Gear Installation ................................... . 2F6
7-3. Clamping Rudder Pedals in Neutral Position ..................... 2F8
7-4. Rudder Pedals at Neutral Angle ................................. 2F8
7-5. Main Gear Oleo Strut Assembly, PA-28-140, -150, -160 and -180 2F13
7-6. Main Gear Oleo Strut Assembly, PA-28-235 ................... 2F15
7-7. Main Gear Installation ...................................... 2F19
7-8. Nose Wheel Assembly........................................... 2F21
7-9. Main Wheel Assembly ........................................ 2F23
7-10. Wheel Brake Assembly........................................ 2GI
7-11. Removal of Anchor Bolt ..................................... 2G2
7-12. Installation of Anchor Bolt .................................... 2G3
7-13. Brake Disc Minimum Thickness .......................... . 2G5
7-14. Brake System Installation ..................................... 2G5
7-15. Brake Master Cylinder (Hand.Brake), PA-28-150,-160,
Serial Nos. 28-1 to 28-250 incl ............................... 2G8
7-16. Brake Master Cylinder (Hand/Parking Brake), PA-28-140.
Serial Nos. 28-20002to 28-21036incl.; PA-28-150,
-160, -180, Serial Nos. 28-251to 28-2700incl.;
PA-28-235,Serial Nos. 28-10003to 28-10697 incl .. .......... 2G8
7-17. Brake Master Cylinder (Hand/Parking Brake), PA-28-140,
Serial Nos. 28-21037and up; PA-28-150,-160, -180,
Serial Nos. 28-2701 and up; PA-28-235,Serial Nos.
28-10698and up......................................... 2G9
7-18. Parking Valve, PA-28-150,-160, Serial Nos. 28-1 to 28-250incl .... 2G11
7-19. Toe Brake Installation ........................................ 2G12
7-20. Brake Cylinder 10-20, 10-27, 17000(Toe Brake) ................ 2G14
7-21. Brake Cylinder 10-30(Toe Brake) .............................. 2G23
7-22. Bleeding Brake (Gravity) ...................................... 2G17
7-23. Bleeding Brake (Pressure) ..................................... 2G17
7-24. Orifice Replacement Tool ..................................... 2G22
7-25. Retainer Ring Tool ........................................... 2G15
7A-1. Nose Gear Oleo Strut Assembly ................................ 2G18
7A-2. Nose Gear Installation ........................................ 2G18
7A-3. Nose Gear Adjustment (Without Gear Up Stop) ................. 223
7A-4. Nose Gear Adjustment (With Gear Up Stop).................... 2G24
7A-5. Clamping Rudder Pedals in Neutral Position ..................... 2H19
7A-6. Rudder Pedals at Neutral Angle................................ 2H19
7A-7. Nose Gear Door Retraction Mechanism ......................... 2H20
7A-8. Main Gear Oleo Strut Assembly.............................. 211
7A-9. Main Gear Installation ........... ........................ 214
7A-10. Aligning Main Gear .......................................... 2110
7A-11. Adjustment of Nose Gear Down Limit Switch .................... 2115

Revised: 8/3/81 2A5

 PIPER CHEROKEE SERVICE MANUAL

LIST OF ILLUSTRATIONS (cont)

Figure Aerofiche
Grid No.
7A-12. Adjustment of Main Gear Down Limit Switch ................... 2115
7A-13. Wiring Diagram of Landing Gear Electrical Circuit ................ 2117
7A-14. Throttle Warning Switches .................................... 2119
7A-15. Nose Wheel Assembly................ ... .............. 2122
7A-16. Main Wheel Assembly ........................................ 2123
7A-17. Wheel Brake Assembly................. ....................... 2J I
7A-18. Brake Disc Minimum Thickness ................................ 2J3
7A-19. Brake System Installation ..................................... 2J3
7A-20. Brake Master Cylinder (Hand/ Parking Brake) ................... 2J5
7A-21. Toe Brake Installation ......................................... 2J6
7A-22. Brake Cylinder (Toe Brake) (10-20, 10-27. 17000)................. 2J8
7A-23. Brake Cylinder (Toe Brake) (10-30) ............................. 2J 10
'7A-24. Bearing Installation ................... ..... ................. 2J11
7A-25. Nose Gear Service Tolerances, PA-28R .......................... 2J20
7A-26. Main Gear Service Tolerances. PA-28R ......................... 2J23
8-1. Typical Nicks and Removal Method ........................... 2K8
8-2. Propeller Installation (Constant Speed) PA-28-235 ......... 2K8
8-3. Propeller Installation .......................... 2K9
8-4. Adjustment of Propeller Control (PA-28-235) . . . ........ . 2K13
8-5. Propeller Governor (PA-28-235) ..................... 2K 13
8-6. Engine Installation (PA-28-140,-150.-160.-180:
Serial Nos. 28-1 to 28-1760) . . . .............. 2K16
8-7. Engine Installation (PA-28-140. -150, -160. -180
Serial Nos. 28-1761 and up) .................... 2K17
8-8. Engine Shock Mount Installation (PA-28-140.
Serial Nos. 28-25000 and up) ................... 2K18
8-9. Engine Installation(PA-28-235) .................. 2K22
8-10. Adjustment of Engine Controls .......... .......... 2K24
8-11. Carburetor (PA-28-140, -150. -160) ................... 2L3
8-12. Carburetor (PA-28-180. -181.-235) ................... 2L3
8-13. Magneto Inspection ............... ............ 2L5
8-14. Contact Spring Inspection ......... ............... 2L6
8-15. Impulse Coupling ......... .................. 2L6
8-16. MagnetoTiming Marks . ...... . ...... ........ 2L7
8-17. Timing Pointer ................................ 2L7
8-18. Timing Kit Installed . ........................... 2L8
8-19. Breaker Compartment with Cast Timing Marks . .......... . 2L8
8-20. RemovingSpark Plug Frozen to Bushing ................. 2L13

Revised: 8/3/81
2A6
 PIPER CHEROKEE SERVICE MANUAL

LISTOFTABLES
Aerofiche
Table Grid No.
V-l. Control Surface Travel and Cable Tension .......... .... 2A11
V-II. Cable Tension vs. Ambient Temperature ................... . 2A13
V-Ill. Troubleshooting Chart (Surface Controls) .............. 2C19
VI-I Leading Particulars. Hydraulic System ................. 2D8
VI-II. Characteristics. Hydraulic Pump Motor .................... . 2D13
VI-III. Hydraulic System Troubleshooting ................... 2E9
VII-. Nose Gear Alignment Tolerances .................... 2F9
VII-II. Landing Gear Troubleshooting ................... ... 2G20
VIIA-I. Landing Gear Troubleshooting ..................... 2J 12
VIIA-II. PA-28R Nose Gear ServiceTolerances ................ 2J21
VIIA-III. PA-28R Main Gear ServiceTolerances ................ 2J24
VIII-I. Propeller Torque Limits ............. .......... 2K 10
VIII-II. Engine Troubleshooting Chart ..................... 2L17

Revised: 8/3/81 2A7

 SECTION V
SURFACE CONTROLS
Paragraph Aerofiche
Grid No.
5-1. Introduction ..................... ........................... 2A10
5-2. Description ..................... .......................... 2A10
5-3. Standard Procedures .......................................... 2A 14
5-4. Control Column Assembly.................................. 2A17
5-5. Removal of Control Column Assembly ................. 2A 17
5-6. Installation of Control Column Assembly ............... 2A 18
5-7. Aileron Controls ............................................. 2A19
5-8. Removal of Aileron Control Cables ................... 2A19
5-9. Installation of Aileron Control Cables .................. 2A21
5-10. Removal of Aileron Bellcrank Assembly ................ 2A22
5-11. Installation of Aileron Bellcrank Assembly.............. 2A22
5-12. Rigging and Adjustment of Aileron Controls ............ 2A23
5-13. Adjustment of Aileron Trim.. ....................... 2B2
5-14. Stabilator Controls ........................................... 2B2
5-15. Removal of Stabilator Control Cables .................. 2B2
5-16. Installation of Stabilator Control Cables................ 2B3
5-17. Rigging and Adjustment of Stabilator Controls.......... 2B5
5-18. Stabilator Trim Controls (Overhead Trim) . ...................... 2B7
5-19. Removal of Stabilator Trim Assembly (Forward) ........ 2B7
5-20. Installation of Stabilator Trim Assembly (Forward) ...... 2B9
5-21. Removal of Stabilator Trim Controls (Aft) ............. 2B9
5-22. Installation of Stabilator Trim Controls (Aft) ........... 2B 12
5-23. Rigging and Adjustment of Stabilator Trim
(Overhead Control) ............ ............... 2B15
5-24. Stabilator Trim Controls (Floor Trim) ......... . ....... 2B17
5-25. Removal of Stabilator Trim Assembly (Forward) ........ 2B17
5-26. Installation of Stabilator Trim Assembly (Forward) ...... 2B 19

Reissued: 1/15/81
2A8
 Aerofiche
Grid No.

5-27. Removal of Stabilator Trim Assembly (Aft) 2B20

5-28. Installation of Stabilator Trim Assembly
(Aft) . . . . . . . . . . . . 2B21
5-29. Rigging and Adjustment of Stabilator Trim
(Floor Control) . .... 2B22
5-30. Rudder and Steering Pedal Assembly .. ..... 2B23
5-31. Removal of Rudder and Steering Pedal
Assembly .. ........ 2B23
5-32. Installation of Rudder and Steering Pedal
Assembly ........... 2C1
5-33. Rudder Controls . ............... 2C2
5-34. Removal of Rudder Control Cables 2C2
5-35. Installation of Rudder Control Cables 2C3
5-36. Rigging and Adjustment of Rudder Controls 2C5
5-37. Rudder Trim Controls ...... . . . . . 2C7
5-38. Removal of Rudder Trim Controls . . 2C7
5-39. Installation of Rudder Trim Controls . 2C7
5-40. Rigging and Adjustment of Rudder Trim
Controls ............ 2C8
5-41. Wing Flap Controls . . . ........... 2C8
5-42. Removal of Wing Flap Controls . .. 2C8
5-43. Installation of Wing Flap Controls . . 2Cll
5-44. Rigging and Adjustment of Wing Flaps . 2C12

Reissued: 1/15/81
2A9
 PIPER CHEROKEE SERVICE MANUAL

SECTION V
SURFACE CONTROLS

5-1. INTRODUCTION. This section contains removal, installation, rigging, adjustment

and trim procedures for ailerons, flaps (lesstrim), stabilator and rudder flight control surfaces.
Also included are similar procedures for the control column and rudder and steering pedal
assembly. For removal, installation, and repair of structural surfaces of the airplane, refer to
Section IV.

5-2. DESCRIPTION. The PA-28 is controlled in flight by the use of three stand-
ard primary control surfaces, consisting of the ailerons, stabilator and rudder.
Operation of these controls is through the movement of the dual control columns
and dual rudder pedals. The individual surfaces are connected to their control
components through the use of cables and push-pull tubes. Provision for direc-
tional and longitudinal trim control is provided by an adjustable trim mechanism
for the rudder and stabilator. The flaps on the PA-28 are mechanically operated
and can be positioned in four locations of 0, 10, 25 and 40 degrees.
The aileron controls consist of two-control wheels connected by torque
tubes to sprockets on each end of the horizontal control column. A chain is wrap-
ped around the sprockets and around a double sprocket on the vertical post of the
control column. The chain is connected to the primary aileron control cable
which is routed through the center of the fuselage to the main spar and out through
the wings to a bellcrank in each wing. A balance cable is also connected to the
bellcrank. As the control wheels are moved, the control cables move the bell-
cranks and actuate push-pull rods to move the ailerons.
The stabilator controls are also connected to the control column. From
the connecting point, cables are routed around a series of pulleys down under the
floor and aft to the tail section of the airplane. The aft end of the cables connect
to the stabilator balance arm which in turn is connected to the stabilator. When
the control wheels are moved forward or aft, the cables move the balance arm
up and down rotating the stabilator on its hinge points.
The rudder is controlled by the pilot's and co-pilot's rudder pedals. Cables
are connected to both sides of the rudder pedal assembly and are routed aft
through the bottom of the fuselage to the rudder horn. When one rudder pedal is
pushed, the cables move in opposite directions turning the rudder horn and rud-
der. The wing flap system is operated by a lever located between the front seats.

Reissued: 1/15/81
2A10 SURFACECONTROLS
 PIPER CHEROKEE SERVICE MANUAL

TABLE V-l CONTROLSURFACETRAVEL AND CABLETENSION

40
C3
Aileron

A 30° + 2UP ALLMODELS

AILERON CHORDLINE
°
B 15 + 2ODN ALL MODELS

C 0° 53' UP ALL MODELS

PREVIOUSTO 1973

0° + 2UP 1973 MODELS

AND UP
Maximum free play for aileron is 0.24 of an inch.
measured at trailing edge(up/down movement).
Maximum free play spanwise is .035 (inboard/
outboard movement).
4-70.
Referto SectionIV,Paragraph

C340
Rudder 1681

A 27 ± 2 L ALL MODELS

B 27 + 2° R ALL MODELS

C340
Flap

C340 + 2
A 25 ALL MODELS

B 100 ± 2 ° ALL MODELS FLAP CHORD LINE

A
C 0 53'UP ALL MODELS
PREVIOUSTO 1973
O° + 1 UP 1973 MODELS
AND UP

D 40 + 2 ALL MODELS
WING CHORD LINE

Revised: 10/3/83 2All SURFACE CONTROLS

 PIPER CHEROKEE SERVICE MANUAL

TABLE V-I CONTROL SURFACE TRAVEL AND CABLETENSION (cont.)

Stabilator
Stabilator Trim Tab
STABILATORCHORD LINE
A 18' 11 UP 1974PA-28-140MODELS (NEUTRAL POSITION)
All PA-28-140Models.All modelsprevious (SEE NOTE 3)
to 1973 exceptthe PA-28R-200which includes
modelspreviousto 1972.

16 ± 1 UP ALL PA-28R-200MODELS
PA-28R-200ModelsSerialNos. 28-7235001
and up endPA-28-235ModelsSerialNos.
28-7310001andup.
14 ± 1 UF 1973PA-28-180SERIAL
PA-28-180 ModelsSerial Nos. 28-73050'1
and up.

B 3° ± 1* UP ALL MODELS 1. Maximum free play for control surface tab is

C 2* + 1° DN ALL MODELS 0.15 of an inch measuredit tabtrailing edge.
D 12° 1* DN ALL MODELS 2. Referto SectionIV,Paragraph4-70.
3. Neutral position of stabilator is with the
stabilator chord line parallel with the top of
the front seat tracks.

8 degrees, 15 minutes PA-28-140,Serial Nos. 28-20002 to 28-20520 incl.

Rudder Pedal Neutral Angle PA-28-150,-160.-180. Serial Nos. 28-1 to 28-1760 incl.
PA-28-235.Seriel Nos. 28-10000 to 28-10486 incl.
AFTOF VERTICAL
11degrees PA-28-140,Serial Nos. 28-20521 to 28-7325684
PA-28-150, -160.-180. Serial Nos. 28-1761 to 28-730561
PA-28-235,Serial Nos. 28-10487 to 28-7310187
PA-28R-200Models Previousto 1974
14 +3 .-1 All 1974Modelsandup

Cable Tensions
AILERON 40 lbs ± 5 lbs ALL MODELS
FLAP 10 1 lb ALL MODELS
STABILATOR 40 lbs 5 1bs ALL MODELS
I STABILATORTRIM TAB 14 lbs ± 1 lbs ALL MODELS
RUDDER 40 lbs ± 5 lbs 1973 MODELS
AND ALL MODELS
PREVIOUSTO 1973
35 bs ± 5 lbs ALL 1974 MODELSAND UP

NOTE

CABLE TENSIONS GIVEN APPLY ONLY TO AIRPLANES WITHOUT

AUTOPILOT BRIDLE CABLES ATTACHED. REFER TO APPROPRIATE
AUTOPILOT SERVICE MANUAL FOR PROPER CABLE TENSIONS WHEN
ATTACHING BRIDLE CABLES.
CABLE RIGGING TENSIONS SPECIFIED MUST BE CORRECTED TO
AMBIENTTEMPERATURE IN THE AREA WHERE THE TENSION IS BEING
CHECKEDUSING TABLE V-II.

Revised: 10.3.83 2A12 SURFACE CONTROLS

 PIPER CHEROKEE SERVICE MANUAL

TABLE V-II. CABLETENSIONVS. AMBIENTTEMPERATURE

A99

120

110

100

z 90

LL 80

70

60

50

UJ
40

30

20

-10 -8 -6 -4 -2 0 2 4 6 10

I SUBTRACT I ADD

RIGGING LOAD CORRECTION,POUNDS

Revised: 10 3 83 2A13 SURFACECONTROLS

 PIPER CHEROKEE SERVICE MANUAL

For a visual description of the various control systems, refer to the illustrated figures.
throughout this section.

5-3. STANDARD PROCEDURES. The following tips may be helpful in the removal,
installation and riggingof the various assemblies:
a. It is recommended, though not always necessary to level and place the airplane on
jacks during rigging and adjustment.
b. Remove turnbuckle barrels from cable ends before withdrawing the cables through
the structures.
c. Tie a cord to the cable end before withdrawing the cable through the structures to
facilitate reinstallation of cable.
d. Turnbuckle stations are givenat their neutral positions.
e. When referring to marking cable end, etc., before disconnectinga felt marking.pen
may be used.
f. Assemble and adjust the turnbuckles so that each terminal is screwed an
approximately equal distance into the barrel. Do not turn the terminals in such a manner
that will put a permanent "twist" into the cables.
g. Cable tensions should be taken with the appropriate control surface in its neutral
position.
h. After completion of each adjustment, check the turnbuckles to be sure not more
than three terminal threads are visibleoutside the barrel. Install the locking clips, and check
for proper installation by trying to remove the clips using fingers only. Both locking clips
may be installed in opposite holes. Locking clips which have been installed and removed
must be scrapped and not reused. Turnbuckles may be safetied in accordance with Advisory
Circular 43.13-1A Chapter 4, Section 2.
i. When push rods or rod ends are provided with an inspection hole, the screw must be
screwed in far enough to pass the inspection hole. This can be determined visually or by
feel, inserting a piece of wire into the inspection hole. If no hole is provided, there must be a
minimum of .375 of an inch thread engagement.
j. After completion of adjustments, each jam nut must be tightened securely (Refer to
Figure 5-22 for proper installation method).
NOTE
Cable rigging tensions specified must be corrected to ambient
temperature in the area where the tension is being checked,
using Table V-II.
k. When normal operation requires movement between any of the components being
clamped together, the bolt (screw)-nut shall be tightenedas required to insure intended normal
operation of the assembly, without reference to Table II-II.
1. Unless otherwisespecified, whencastellatednuts are usedwith a cotter pin on moving
joints, the nut shall not be torqued to the Table II-II values. Nuts shall be tightened to remove
looseness in the joint and then the cotter pin installed.

Reissued: 1/15 / 81
2A14 SURFACE CONTROLS
0
 PIPER CHEROKEE SERVICE MANUAL

54. CONTROL COLUMNASSEMBLY.

5-5. REMOVALOF CONTROLCOLUMNASSEMBLY. (Refer to Figure 5-1 or 5-2.)

a. To remove either control wheel (1) with tube (2), the followingprocedure may be
used:
1. Separate the control wheel tube (2) from the flexiblejoint (4) that is located on
either side of the tee bar assembly (5) by removing the nut, washer and bolt (3). Pull the
tube from the flexiblejoint.
2. If removing the left control tube, slide the stop (6) from the tube.
3. Should wires for the various Autopilot systems be installed in the control tube,
disconnect them at the quick disconnect terminals behind the instrument panel. Draw the
wires back into the tube and out through the forward end of the tube.
4. Remove the control wheel assembly from the instrument panel.
b. The tee bar (5) with assembled parts may be removed from the airplane by the
following procedure:
1. Remove the accesspanel or door to the aft section of the fuselage.
2. Relieve cable tension from the stabilator control cables (11) at one of the
stabilator cable turnbuckles in the aft section of the fuselage.
3. Relieve tension from the aileron control cables (12) and chains (7 and 8)
and at the turnbuckle (9) that connects the chains at the top of the tee bar (5).
4. Disconnect the control chains from the control cables where the chains
and cables join by removing the cotter pins, nuts, bolts and bushings (10).
5. Remove the tunnel cover by the following procedure:
(a) PA-28-140; PA-28-1-50,-160, -180; and PA-28R:
Remove the rudder trim control knob and trim cover attaching screws. Roll back
the carpet from the tunnel and remove the tunnel plate that is located just aft of
the tee bar assembly, by removing the plate attaching screws.
(b) PA-28-235:
Remove the fuel selector and rudder trim covers by removing the knobs and the
attaching screws. Disconnect the fuel indicator control lever from the fuel se-
lector torque tube by removing the attaching pin located at the bottom of the lever.
Remove the tunnel plate, located just aft of the tee bar, by laying back enough
tunnel carpet to remove the plate attaching screws..
6. Remove the two aileron control cable pulleys (13)attached to the lower
section of the tee bar by removing the pulley attaching bolt (14).
7. Disconnect the stabilator controls (11) from the lower end of the tee bar
assembly.
8. Disconnect the necessary controls, such as the mixture control, throttle
control, etc., that will allow the tee bar assembly to be removed.
9. Remove the tee bar assembly by removing the attaching bolts (15) with
washers and nuts, which are through each side of the floor tunnel, and lifting it
up and out through the right side of the cabin.

Reissued: 1/15/81 2A17 SURFACECONTROLS

 PIPER CHEROKEE SERVICE MANUAL

5-6. INSTALLATION OF CONTROL COLUMN ASSEMBLY.

(Refer to Figure 5-1 or 5-2.)
a. The tee bar assembly may be installed in the airplane by the following pro-
cedure:
1. Swing the tee bar assembly into place from the right side of the cabin
and secure with attaching bolts (15), washers and nuts inserted in through each
side of the floor tunnel.
2. Connect the stabilator controls (11) to the lower end of the tee bar with
bolt, washer, nut and cotter pin (16). Allow the cable ends free to rotate.
3. Place the aileron control cables (12) around the pulleys (13) that attach to the
lower section of the tee bar (5), position pulleys and secure with bolt, washersand nut (14).
4. Install the control wheel per step b.
5. Place the control wheels in neutral (centered) position and install the aileron
control chains (7 and 8) on the control wheel sprockets (17 and 18) and idler crossover
sprockets (19 and 21). This turnbuckle (9) must be centered between the two control wheel
sprockets.
6. Loosen the connecting bolts (22) of the idler sprockets (i9 nd 21) to allow the
chain to fit snug around the control wheel sprockets and over the idler sprockets.
7. Connect the aileron control cables (12) to the ends of the chains(7 and 8) with
bolts, bushings,nuts and cotter pins (10).
8. Adjust the chain turnbuckle (9) between the two control wheel sprockets to
allow the control wheels to be neutral and obtain proper cable tension as givenin Table V-I.
It may be necessary, in order to have both control wheels neutral, to set the chain
turnbuckle to neutralize the wheels and then set cable tension with the turnbuckleslocated
under the floor panel aft of the main spar as instructed in paragraph 5-12. Beforesafetying
the tumbuckle, check that when the ailerons are neutral, the control wheels willbe neutral
and the chain turnbuckle centered. Also, the aileron bellcranks should contact their stops
before the control wheel hits its stop. Maintain .030 to .040 clearancebetween sprocket pin
and adjustable stop bolts on models having adjustable aileron tee bar stops.
9. Set stabilator cable tension with the turnbuckle in the aft section of the fuselage
and instructions given in paragraph 5-17. Check safety of all turnbuckles upon completion
of adjustments.
10. Tighten the connecting bolts (22) of the idler sprockets (19 and 21).
1 1. Install the floor tunnel plate trim covers by the followingprocedure:
(a) PA-28-140;PA-28-150, -160, -180; and PA-28R: Place the tunnel plate into
position for installation and secure with the appropriate screws. Roll the
carpet into place and install the rudder trim cover and knob.
(b) PA-28-235: Install the floor tunnel plate and secure with the appropriate
screws. Fasten the tunnel carpet into place and install the fuel selector lever
on the selector torque tube and secure with a clevis pin and cotter pin.
Replace the fuel selector and rudder trim knob.
b. Either control wheel assemblymay be installed by the followingprocedure:
1. Insert the control wheel tube through the instrument panel.
2. Should wires for the various Autopilot systems need to be installed in the
control tube, route them through the hole in the forward side of the tube and out of the
small hole in the forward side. Position the rudder grommet in the hole in the side of the
tube.
3. On the left control tube install the stop (6).

SURFACE CONTROLS
Reissued:1/15/81
2A18
 PIPER CHEROKEE SERVICE MANUAL

4. Connect the control wheel tube (2) to the flexible joint (4) of the tee bar
assembly. If the control cables and/or chains have not been removed or loosened, place the
ailerons in neutral and install the control tube on the flexible joint to allow the control
wheel to be neutral. Install bolt, washerand nut (3) and tighten.

5-7. AILERON CONTROLS.

5-8. REMOVALOF AILERONCONTROLCABLES. (Refer to Figure 5-3.)

a. For the removal of either the control cables in the fuselage or thewings, first remove
the baggage area floor panel of the PA-28-140 airplane, or the rear seat bottom on the
PA-28-150, -160, -180; PA-28-235and PA-28R airplanes.
b. To remove either the right or left primary control cables (14 or 15) that are located
in the fuselage,the followingprocedure may be used:
1. Remove the two front seats from the airplane.
2. Remove the tunnel cover located aft of the tee bar assembly by the following
procedure:
(a) PA-28-140; PA-28-150,-160, -180; and PA-28R: Remove the rudder trim
control knob and trim coverattaching screws.Roll back the carpet from the
tunnel and remove the tunnel plate that is located just aft of the tee bar
assembly by removingthe plate attaching screws.
(b) PA-28-235: Remove the fuel selector and rudder trim covers by removing
the knobs and the attaching screws. Disconnect the fuel indicator control
lever from the fuel selector control lever from the fuel selector torque tube
by removing the attaching pin located at the bottom of the lever. Remove
the tunnel plate locatedjust aft of the tee bar by laying back enough tunnel
carpet to removethe plate attaching screws.

NOTE
To help facilitate reinstallation of control cables, mark the
cable ends and attach a line where applicable before drawing
them through the fuselageor wing.
3. Separate the primary control cable (14 or 15) at the turnbuckle (12 or 16)
located under the rear seat or floor panel aft of the main spar.
4. Remove the cable pulleys (8) attached to the lower section of the control
column tee bar assembly by removingthe pulley attaching bolt (21).
5. Move the cable guard (20) under the pulley cluster (9) located just aft of the
lower portion of the tee bar by removingthe cotter pin from the exposed end of the guard
and sliding it to the left or right as required.
6. Remove the cotter pins used as cable guards at the pulley (10) in the forward
area of the floor opening aft of the main spar.
7. Disconnect the cable (14 or 15) from the control chain (4) at the control
column tee bar assembly by removing the cotter pin, nut, bolt and bushing (23) that
connect the two together. Secure the chains in some manner to prevent them from
unwrapping from around the sprockets.
8. Draw the cable back through the floor tunnel.

Reissued: 1/15/81
2A19 SURFACE CONTROLS
 PIPER CHEROKEE SERVICE MANUAL

c. The primary control cable (13 or 17) in either wing may be removed by the
followingprocedure:
1. Remove the access plate to the aileron bellcrank (6) located on the underside of
the wing forward of the inboard end of the aileron.
2. If not previously disconnected, separate the cable at the turnbuckle (12 or 16)
located in the area aft of the main spar.
3. Disconnect the cable from the forward end of the aileron bellcrank by removing
the cotter pin, nut, washer and bolt.
4. Drawthe cable from the wing
c. Either balance cable (18 or 19) may be removed by the following procedure:
1. Separate the balance cable at the turnbuckle (24) in the right side of the opening
aft of the main spar.
2. If the left balance cable is to be removed, remove the cotter pin used as a cable
guard at the pulley (11) in the center of the opening.
3. Remove the accessplate to the aileron bellcrank (6) located on the underside of
the wing forward of the inboard end of the aileron.
4. Disconnect the cable from the aft end of the aileron bellcrank by removing the
cotter pin, nut, washer and bolt.
5. Drawthe cable from the wing.

5-9. INSTALLATIONOF AILERONCONTROLCABLES. (Refer to Figure 5-3.)

a. The installation of either the right or left primary control cable (14 or 15) that is
located in the fuselagemay be accomplishedas follows:
1. Draw the cable through the fuselagefloor funnel.
2. Connect the cable to the end of the control chain (4) and secure using bushing,
bolt, nut and cotter pin (23).
3. Place the cable around the pulley (9) that is located in the tunnel aft of the tee
bar. Install the cable guard (20) and secure with a cotter pin.
4. Position cables and install the cable pulleys (8) that attach to the lower section
of the tee bar assembly.Secure with bolt, washer and nut (21).
5. Place the cable around the pulley (10) that is located within accessopeningjust
aft of the main spar and install cotter pin cable guards.
6. If the primary control cable in the wing is installed, connect the control cable
ends at the tumbuckle (12 or 16) located within accessopening just aft of the main spar.
7. Checkriggingand adjustment per pargraph 5-12.
8. Install the floor tunnel plate trim cowersby the following procedure:
(a) PA-28-140;PA-28-150,-160, -180; and PA-28R: Place the tunnel plate into
position for installation and secure with the attachment screws. Roll the
carpet into place and install the rudder trim cover and knob.
(b) PA-28-235: Install the floor tunnel plate and secure with the attachment
..screws. Fasten the tunnel carpet into place and install the fuel selector lever
on the selector torque tube and secure with a clevis pin and cotter pin.
Replace the fuel selector and rudder trim covers and the rudder trim knob.
b. The primary control cable (13 or 17) in either wing may be installed by the
followingprocedure:
1. Drawthe control cable into the wing.
2. Connect the cable to the forward end of the aileron bellcrank (6) using a bolt,
washer, nut and cotter pin. Allow the cable end to rotate freely on the bellcrank.

SURFACE CONTROLS
Reissued: 1/15/81 2A21
 PIPER CHEROKEE SERVICE MANUAL

3. If the primary control cable in the fuselage is installed, connect the ends at the
turnbuckle (12 or 16) located under the rear seat aft of the main spar.
4. Check riggingand adjustment per paragraph 5-12.
5. Install the access plate on the underside of the wing.
c. Either balance cable (18 or 19) may be installed by the followingprocedure:
1. Draw the cable into the wing.
2. Connect the cable to the aft end of the aileron bellcrank (6) using a bolt, washer,
nut and cotter pin. Allow the cable end to rotate freely on the bellcrank.
3. Connect the balance cable ends at the turnbuckle (24) that is located under the
rear seat aft of the main spar.
4. If the left cable was removed, install the cotter pin cable guard at the pulley (10)
located within the fuselage, aft of the main spar.
5. Check riggingand adjustment per paragraph 5-12.
6. Install the access plate on the underside of the wing.
d. Replace the rear seat bottom or floor panel and the two front seats.

5-10: REMOVAL OF AILERON BELLCRANK ASSEMBLY (Refer to Figure 5-3.)

a. Remove the baggage area floor panel of PA-28-140 airplanes or the bottom half of
the rear seat of the PA-28-150, -160, -180; PA-28-235 and PA-28R airplanes.
b. Remove the access plate to the aileron bellcrank (6) located on the underside of the
wing, forward of the inboard end of the aileron.
c. Relieve tension from the aileron control cables by loosening the balance cable
turnbuckle (24) located in the opening aft of the main spar.
d. Disconnect the primary (13 or 17) and balance (18 or 19) control cables from the
bellcrankassembly by removingcotter pins, nuts, washers and bolts.
e. Disconnect the aileron control rod (7) at the aft or forward end, as desired, by
removingthe cotter pin, nut, washer and bolt.
f. Remove the nut, pivot bolt (25) and washers that secure the bellcrank. The nut is
visiblefrom the underside of the wing.
g. Remove the bellcrank from within the wing.

5-11. INSTALLATIONOF AILERONBELLCRANK ASSEMBLY. (Refer to Figure 5-3.)

a. Ascertain that the bellcrankpivot bushing (26) is lubricated and install in the torque
tube portion of the bellcrank (6).
b. Place the bellcrank in position in the wing with a washer located between each end
of the torque tube and the mounting brackets.
c. Install the bellcrank pivot bolt (25) with the head up. Install a washer and nut on
the bolt, and torque nut within 20 to 25 inch-pounds. Check that the bellcrank rotates
freely with little up-down play.
d. Install and adjust control rod (7) and check aileron travel per paragraph 5-12.
e. Connect the ends of the primary (13 or 17) and balance (18 or 19) control cables to
the bellcrank usingbolts, washers,nuts and cotter pins. Allow the cable ends to rotate freely
on the bellcrank.
f. Tighten the control cables at the balance cable turnbuckle (24) in the floor opening
aft of the main spar. Check cable tension per paragraph 5-12.
g. Install the access plate on the underside of the wing and replace the floor panel or
rear seat bottom.

Reissued: 1/15/ 81 2A22 SURFACE CONTROLS

 PIPER CHEROKEE SERVICE MANUAL

1652 2054

I Refer to Figure 5-21 for tool fabrication Refer to Figure 5-21 for tool fabrication

Figure 5-4. BellcrankRiggingTool Figure 5-5. Bellcrank RiggingTool

PA-28-140,-150, -160, -180, -235 PA-28R

5-12. RIGGING AND ADJUSTMENTOF AILERON CONTROLS. (Refer to Figures 5-4

thru 5-6.)

NOTE
Flap adjustment must be complete before starting aileron
adjustment.
a. To check and adjust the riggingof the aileron controls, first set the right and left
aileron bellcranks at neutral position.(Ascertainthat the control chains have been rigged per
paragraph 5-6.) This may be accomplishedby the following procedure:
1. Place tee bar in full forward position. Maintain in this position by use of a
suitable tool or by placing weights on aft side of stabilator if stabilator cables have been
previouslytensioned.
2. Remove the accessplate to each aileron bellcrank located on the underside of the
wing. forward of the inboard end of the aileron by removing the plate attaching screws.
3. Affix a bellcrank rigging tool, as shown in Figures 5-4 or 5-5. between the
forward arm of each bellcrankand the adjacent rib. (This tool may be fabricated to dimensions
given in Figure 5-21.)The slotted end of the tool fits on the arm forward of. and adjacent to, the
primary control cable end. The other end of the tool is positioned so that the side of the tool
contacts the aft side of the bellcrankstop. The bellcrank must be moved to allow a snug fit of
the tool betweenthe bellcrankarm and rib. To do so. it may be necessaryto loosen a primary
control cable or the balance cable. Neutral position of the bellcranks may also be found by
locating the centers of the forward and aft cable connection holes an equal distance from the
adjacent inboard wing rib.

Revised: 10 3 83 2A23 SURFACE CONTROLS

 PIPER CHEROKEE SERVICE MANUAL

b. With each bellcrank set at neutral, the ailerons on the PA-28-140, -150, -160, -180,
-235 and 28R may be checked and adjusted for neutral as follows:
1. Ascertain that the bellcrank rigging tool fits snug between the bellcrank and the
rib.
2. Place an aileron rigging tool as shown in Figure 5-6 against the underside of the
wing and aileron as close as possible to the inboard end of the aileron without contacting
any rivets. The tool must be positioned paralleled with the wing ribs, with the aft end of the
tool, even with the trailing edge of the aileron. (This tool may be fabricated to dimensions
given in Figure 5-23.)
3. With the aileron control rod connected between the bellcrank and aileron, check
that the surface of the wing contacts the tool at its forward surface and at the spacer, and
the trailing edge of the flap contacts the aft end of the tool. The aileron is neutral at this
position.
4. Should the three points not contact, loosen the jam nut at the aft end of the
control rod and rotate the rod until the three points contact. Apply a slight up pressure
against the trailing edge of the aileron while making this adjustment. After adjustment,
retighten the jam nut.

.375 HEIGHTSPACER IS TO BE IN LINEWITH AFTSPAR

RIVET LINE.BUT SHOULD NOT MAKE CONTACTWITH
ANYRIVETS.
NEUTRALPOSITION OF AILERONWILL OCCUR WHEN
THESETHREEPOINTS MAKECONTACTWITH WING AND
AILERONSKIN.

I
REFER
TO FIGURE5-23 FORTOOLFABRICATION

Figure 5-6. Aileron Rigging Tool

Revised: 4/23 84 2A24 SURFACE CONTROLS

 PIPER CHEROKEE SERVICE MANUAL

c. Adjust primary and balance cable tension as given in Table V-I by the following
procedure:
1. Remove the two front seats, if desired, and the baggage area floor panel of the
PA-28-140 airplanes or the bottom of the rear seat of the PA-28-150, -160, -180; PA-28-235
and PA-28R airplanes to facilitate in the necessary operation.
2. Loosen the connecting bolts of the idler cross-over sprockets at the control tee
bar to allow the chain to fit snug around the control wheel sprockets,and-over the idler
sprockets.
3. Ascertain that both bellcranks are at neutral position.
4. Adjust the turnbuckles, located in the access opening just aft of the main spar,
of the primary and balance cables to their proper cable tension and maintain neutral-center
position of the control wheels. To obtain neutral position of both control wheels, it may
also be necessary to adjust the roller chain turnbuckle located between the control wheel
sprockets. During adjustment, obtain a little more tension on the primary control cables to
hold the bellcranks in neutral against the rigging tools, finishing with even tension on all
cables.
5. Tighten the bolts to secure the idler cross-oversprockets.
6. Remove the aileron bellcrank riggingtool from each wing.
d. Check the ailerons for correct travel from neutral perdimensions givenin Table V-I,
by the following procedure:
1. Center the bubble of a protractor over the surface of an aileron at neutral
position and note the reading.
2. Move the aileron full up and down, checking the degree of travel for each direction.
The degree of travel on the protractor is determined by taking the difference between the
protractor reading at neutral and up, and neutral and down. The bubble must be centered at
each reading. When measuring down travel from the neutral position, maintain a light up
pressure at the center of the aft edge of the aileron. When measuring up travel from the
neutral position, maintain a light down pressure at the center of the aft edge of the aileron;
just sufficient to remove the slack between the bellcrank and the aileron.
3. Should the travel not be correct, the travel may be set by rotating the bellcrank
stops in or out. Stops are located in the wing attached to the rib that is adjacent to the
aileron bellcrank.
4. Repeat this procedure for the other aileron.
e. Check to insure that the left aileron up and right aileron down stops are contacted
simultaneously and vice versa. Adjust stops as required.
f. Check the bellcrank stops to assure that the bellcrank contact is made
simultaneously, but still have cushion before contacting the control wheel stops. Maintain
.030 to .040 clearance between sprocket pin and adjustable stop bolts on models having
adjustable tee bar stops.
g. Check complete system for operation and safety of turnbuckles, bolts, etc.
h. Install accessplates and panels.

Reissued: 1/15/81 2B1 SURFACE CONTROLS

 PIPER CHEROKEE SERVICE MANUAL

5-13. ADJUSTMENT OF AILERON TRIM. (PA-28-150, -160, -180, Serial Nos. 28-1 to'
28-1321 incl.) Lateral trim can be effected on the ground by adjusting the metal tab attached
to the trailing edge of the left aileron.

NOTE
When an out of trim condition persists despite all the rigging
corrections that can be made, there is a possibility that the
trailing edge of the aileron has been used to move the aircraft
forward. This can result in a slight bulging of the aileron
contour at the trailing edge which will cause an out of rig
condition that is very difficult to correct.

5-14. STABILATORCONTROLS.

5-15. REMOVALOF STABILATORCONTROL CABLES. (Refer to Figure 5-8.)

a. To remove either the forward or aft stabilator cables, first remove the accesspanel
to the aft section of the fuselage located in the baggage compartment, the two front seats,
and the baggagearea floor panel on the PA-28-140 airplanes or the bottom of the rear seat
on the PA-28-150, -160, -180; PA-28-235 and PA-28R airplanes.
b. Disconnect the desired control cable at the turnbuckle in the aft section of the
fuselage.
c. Either forward stabilator cable (2 or 3) may be removed by the followingprocedure:
1. Remove the tunnel carpet and cover plate by the followingprocedure:
(a) PA-28-140; PA-28-150, -160, -180 and PA-28R:
Remove the rudder trim control knob and trim cover attaching screws.Roll back the carpet
from the tunnel and remove the tunnel plate that is located just aft of the tee bar assembly
by removing the plate attaching screws.
(b) PA-28-235:
Remove the fuel selector and rudder trim covers by removing the knobs and the attaching
screws. Disconnect the fuel indicator control lever from the fuel selector torque tube by
removing the attaching pin located at the bottom of the lever. Remove the tunnel plate
located just aft of the tee bar by laying back enough tunnel carpet to remove the plate
attaching screws.
2. If the right (upper) stabilator control cable (2) is to be removed, remove the
cotter pin guards at the pulley(2) located in the forward area of the tunnel.
3. Disconnect the cables (2 and 3) from the lower end of the tee bar on PA-28-140;
PA-28-150, -160, -180 and PA-28-235 or from the idler arm on the PA-28R by removing
cotter pin, nut, washer and bolt (15).
4. Within the access opening aft of the main spar, remove the cable rub blocks that
are attached to the spar housing by removing the block attaching screws.
5. Remove the cotter pin cable guard at the pulley cluster located in the aft area
the access opening aft of the main spar.

Reissued: 1/15/81
2B2 .SURFACE CONTROLS
 PIPER CHEROKEE SERVICE MANUAL

A641

Refer to Figure 5-24 for tool fabrication

Figure 5-7. Stabilator RiggingTool

NOTE
To facilitate in the installation of control cables, a line may
be attached to the cable end prior to removal.

6. Draw the cable aft through the floor tunnel.

d. Either aft stabilator control cable (4 or 5) may be removed by the following
procedure:
1. Disconnect the cable end at the balance arm (18) of the stabilator by removing
the cotter pin, nut, washer and bolt (8).
2. Remove the cotter pin cable guard at the pulley (7) located either above or
below the balance arm.
3. Remove the cable from the airplane.

5-16. INSTALLATIONOF STABILATORCONTROLCABLES. (Refer to Figure 5-8.)

a. The forward stabilator cables (2 and 3) may be installed by the followingprocedure:
1. Draw the control cable through the floor tunnel. Ascertain that the right (upper)
cable (2) is routed around the pulley(s) (14) in the forward area of the floor tunnel.
2. Connect the cables (2 and 3) to the lower end of the control column tee bar (1)
or the idler arm with bolt, washer,nut and cotter pin (15). Allow the cable ends freedom to
rotate.
3. If the aft control cable (4 or 5) is not installed,install per step b.
4. Connect the control cable to the aft cable at the turnbuckle (16) in the aft
section of the fuselage.
5. For the right control cable (2), install the cotter pin cable guards at the pulley(s)
(14) in the forward area of the tunnel.
6. Within the access opening aft of the main spar, install the cable rub blocks (10)
to the spar housing and secure with screws.

Revised: 4 23 84 2B3 SURFACE CONTROL S

0
 PIPER CHEROKEE SERVICE MANUAL

7. In the accessopening, install the cotter pin cable guard at the pulley cluster (6).
8. Set cable tension and check riggingand adjustment per paragraph 5-17.
9. Install the floor tunnel plate and trim covers by the following procedure:
(a) PA-28-140;PA-28-150,-160, -180 and PA-28R: Place the tunnel plate into
position for installation and secure with the attaching screws. Roll the carpet
into place and install the rudder trim cover and knob.
(b) PA-28-235: Install the floor tunnel plate and secure with the attachment
screws. Fasten the tunnel carpet into place and install the fuel selector lever
on the selector torque tube and secure with a clevis pin and cotter pin.
Replace the fuel selector and rudder trim covers and the rudder trim knob.
10. Install the front seats and rear seat bottom on floor panel.
b. Either aft stabilator control cable (4 or 5) may be installed by the following
procedure:
1. Route the cable (4 or 5) around its pulley (7) located either over or under the
balance arm (18) of the stabilator.
2. Connect the cable to the stabilator balance arm and secure with bolt, washer,
nut and cotter pin (8). (Insure bushing is installed with bolt.)
3. Connect the cable to the forward cable at the turnbuckle (16) in the aft section
of the fuselage. The upper aft cable (5) connects to the right forward cable (2) and the
lower cable (4) to the left cable (3).
4. Install the cotter pin cable guard at the pulley (7), where required.
5. Set cable tension and check riggingand adjustment per paragraph 5-17.
6. Install the seats and accesspanels.

5-17. RIGGINGAND ADJUSTMENTOF STABILATORCONTROLS.

a. Level the airplane. (Refer to Leveling,Section II.)
b. To check and set the correct degree of stabilator travel, the following procedure may
be used:
1. Check the stabilator travel by placing a rigging tool on the upper surface of the
stabilator as shown in Figure 5-7. (This tool may be fabricated from dimensions given in
Figure 5-24.)
2. Set on a bubble protractor the number of degree up travel as givenin Table V-I
and place it on the riggingtool. Raise the trailing edge of the stabilator and determine that
when the stabilator contacts its stops, the bubble of the protractor is centered.
NOTE

The stabilator should contact both of its stops before the

control wheel contacts its stops.
The neutral position of the stabilator is with the stabilator
chord line parallel with the top of the front seat tracks.

Reissued: 1/15/81
2B5 SURFACE CONTROLS
 PIPER CHEROKEE SERVICE MANUAL

3. Set on the protractor the number of degrees down travel as given in

Table V-I and again place it on the rigging tool. Lower the trailing edge of the
stabilator and determine that when it contacts its stops, the bubble of the pro-
tractor is centered.
4. Should the stabilator travel be incorrect in either the up or down posi-
tion, remove the tail cone fairing by removing the attaching screws and with the
use of the rigging tool and bubble protractor turn the stops located at each stabi-
lator hinge in or out (Refer to Figure 5-16. )to obtain the correct degree of travel
5. Ascertain that the lock nuts of the stop screws are secure and reinstall
the tail cone fairing.
c. To check and set stabilator control cable tension, the following procedure
may be used:
1. Ascertain that the stabilator travel is correct.
2. Remove the access panel to the aft section of the fuselage.
3. Secure the control column in the near forward position. Allow one-
quarter inch between the column and the stop bumper
4. Check each control cable for the correct tension as given in Table V-I.
5. Should tension be incorrect, loosenthe turnbuckle of the lower cable in
the aft section of the fuselage and adjust the turnbuckle of the upper cable to ob-
tain correct tension. Cable tension should be obtained with the control wheel at
the one-quarter inch dimension from the stop and the stabilator contacting its
stop.
6. Check safety of all turnbuckles and bolts.
7. With the tension of the upper, cable correct and the control wheel still
forward, adjust the turnbuckle of the lower cable to obtain correct tension.
8. Check the full travel of the control wheel with relation to the full travel
of the stabilator to determine that the stabilator contacts its stops before the
control wheel contacts its stops. With the control wheel in the fore and aft posi-
tions, the travel distance from the point where the stabilator contacts its stops
and the control wheel contacts its stops should be approximately equal. Readjust
turnbuckles if incorrect.
9. Reinstall access panels.
d. Remove the airplane from jacks.

Reissued: 1/15/81 SURFACE CONTROLS

2B6
 PIPER CHEROKEE SERVICE MANUAL

5-18. STABILATOR TRIM CONTROLS. (OVERHEADTRIM.)

NOTE

If the airplane involved is equipped with a single sta-

bilator trim cable (one turnbuckle),it will be necessary
to follow the combined instructions for removal of both
forward and aft cables.

5-19. REMOVAL OF STABILATOR TRIM ASSEMBLY. (FORWARD.)-

(Refer to Figure 5-9.)
a. Rotate the stabilator trim crank to bring the indicator to full aft (extreme
nose high) position to facilitate removal of the trim indicator from the panel.
b. Remove the spring clip from the stabilator trim crank handle and remove
the handle.
c. Remove the headliner trim panel (light panel) from around the trim crank
assembly by the following procedure:
1. Remove the attaching screws that secure the panel.
2. Disconnect the light wires at the quick disconnects.

NOTE

It is recommended that the wires be marked for iden-

tification before removal.

3. Remove the panel.

d. Remove the access panel at the aft wall of the baggage compartment to gain
entry to the aft section of the fuselage.
e. Install a cable block on the aft trim control cables, as shown in Figure 5-10.
f. Disconnect the stabilator trim cable(s) at the turnbuckle(s) located in the
aft section of the fuselage.
g. Remove the cable guard pins from the pulleys located at stations 108.16
and 138.33. Station 138.33 is accessible through the zipper on the aft area of
the headliner.
h. Remove the clevis pin cable guard from the trim crank assembly.

NOTE

To facilitate installation, it is recommended that a

line be attached to the cable end prior to removal.

Reissued: 1/15/81 2B7 SURFACE CONTROLS

 PIPER CHEROKEESERVICE MANUAL

1761

1. STABILATOR TRIM CRANK

2. STABILATOR TRIM PULLEY
3. TRIM INDICATOR TEE SPRING
4. TRIM INDICATOR TEE ASSEMBLY
5. TRIM INDICATOR WIRE
6. STABILATOR TRIM CONTROL CABLE
7. STABILATOR TRIM CABLE IDLER PULLEY
8. TURNBUCKLE BARREL
9. STABILATOR TRIM UPPER SUPPORT ASSEMBLY
10. TRIM SHAFT PULLEY

PA-20-150-160-180
SERIAL NOS. 2B-1 TO 2B-1410 INCL.
PA-28-140 SERIAL NOS. 2-20002 TO 28-20656 INCL.
PA2-2-140-160-10 SERIAL NOS. 28-141 TO 21-2 171
PA-28-235 SERIAL NOS. 21-10003 TO 28-10605 INCL.

1751

PA-2B-140 SERIAL NOS. 28-20657 AND UP

PA-2-150-160-180 SERIAL NOS. 28-2172 TO 28-9377 INCL.
PA-28-235 SERIAL NOS. 28-1060 TO 28-10719 INCL.

Figure 5-9. Stabilator Trim Control (Overhead Control)

Reissued:1/15/81 2B8 SURFACE CONTROLS

 PIPER CHEROKEE SERVICE MANUAL

i. Remove the cable from the airplane.

j. The trim crank and pulley assembly may be removed by removing the
mounting bracket attaching screws.

5-20. INSTALLATION OF STABILATORTRIM ASSEMBLY. (FORWARD.)

(Refer to Figure 5-9.)
a. If the trim crank and pulley assembly has been removed, install assembly
and secure with attachment screws.
b. Install the forward stabilator trim cable using the following procedure:
1. Attach a line to the right end of the control cable and pull the cable for-
ward to the crank assembly.
2. Route the cable clockwise (as view from the underside) around and into
the top groove of the crank pulley, and on to the left side of the idler pulley.
3. From around the idler pulley, route the cable around and in the bottom
groove of the crank pulley.
4. With the use of a line attached to the cable end, pull the cable through
to the turnbuckle located in the aft section of the fuselage.
c. Attach the cable ends together and install guard pins in the pulley assem-
blies.
d. Insert the guard pin in the trim bracket assembly and safety with a cotter
pin.
e. Actuate the trim crank fore and aft several times to seat the cables into
the pulleys.
f. Rig and adjust in accordance with paragraph 5-23.
g. Replace all the access plates and panels.
h. Install the headliner trim panel by connecting the electrical leads and in-
stalling attaching screws.
i . Replace the trim handle and secure with the snap ring.

5-21. REMOVAL OF STABILATORTRIM CONTROLS. (AFT.)

(Refer to Figure 5-9.)
a. PA-28-150,-160,-180, Serial Nos. 28-1 to 28-1410 incl. (The exception
being airplanes with Piper Kit No. 756 930 Stabilator Trim Modifications install-
ed. Airplanes with this kit installed, refer to step c.)
1. Remove the tail cone fairing by removing attaching screws.
2. Remove the access panel located at the aft wall of the baggage compart-
ment to allow access to the aft section of the fuselage.
3. To remove the trim control cable, proceed as follows:
(a) Disconnect the cable at the turnbuckle (8) in the aft section of the
fuselage.

Reissued: 1/15/81 2B9 SURFACE CONTROLS

 PIPER CHEROKEE SERVICE MANUAL

A977

Figure 5-10. Methods of Securing Trim Cables

(b) Remove the cable guard pin from the pulleys located within the fuse-
lage at station 228.30.
(c) Remove the cable guard from the top support brace of the trim
mechanism located just aft of the trim screw pulley.
(d) Remove the cotter pin cable guard at the idler pulley (18) which is
attached to the aft side of the rearward most bulkhead of the fuselage.
(e) Draw the cable aft around the trim screw pulley (10) and then for-
ward.
(f) Removethe forward portion of the cable as givenin paragraph5-19.
4. The trim mechanism may be disassembled and removed from the aft
bulkhead of the fuselage as follows:
(a) Disconnect the trim tab control arm (15) from its support bracket
by removing nuts, washers, bushings and bolts.
(b) Disconnect the trim indicator cable (17) from the trim screw trun-
nion (12) by removing attaching nut, washer and screw. Remove the cotter pin
cable guard at the cable pulley (10) located directly below the trunnion.
(c) Remove the trim mechanism assembly (11) by removing the nut,
washer and bolt at each support brace (20) attachment point, and at the aft most
fuselage bulkhead.
(d) Disassemble the trim mechanism by removing the cotter pin, washer
and nut located at each end of shaft assembly, and pulling the supports with
washers from the shaft.
(e) Disassemble the shaft by removing the roll pins from the desired
component.

Reissued: 1/15/81 2B10 SURFACE CONTROLS

 PIPER CHEROKEE SERVICE MANUAL

b. PA-28-140, Serial Nos. 28-20002 to 28-20656 incl; PA-28-150, -160, -180,

Serial Nos. 28-1411 to 28-2171 incl. and PA-28-235, Serial Nos. 28-10603 to
28-10605 incl. (The exception being those airplanes with Piper Kit No. 756 896
Stabilator Trim Modification installed. Airplanes with this kit installed, refer
to step c.)
1. Remove the tail cone fairing by removing attaching screws.
2. Remove the access panel located at the aft wall of the baggage compart-
ment to allow access to the aft section of the fuselage.
3. To remove the trim control cable, proceed as follows:
(a) Disconnect the cable at the turnbuckle (8) in the aft section of the
fuselage.
(b) Remove the cable guard pin from the pulleys located within the
fuselage at station 228.30.
(c) Disconnect the links (19), located between the trim screw (11) and
control arm (15) at the trim screw, by removing nut, washers, bushing and bolt.
(d) Remove the cotter pin that extends through the top of the trim screw
and the cable guard pin located just aft of the trim barrel (10).
(e) Remove the cotter pin cable guard at the idler pulleys which are
attached to the aft side of the rearward most bulkhead.
(f) Turn the screw down and out from the underside of the barrel.
(g) Remove the snap ring, washer and thrust washer from the bottom
of the barrel.
(h) Disconnect the diagonal and horizontal trim assembly support ribs
from one another by removing their four attaching nuts, washers and bolts.
(i) Loosen the bolts where the horizontal ribs attach to the fuselage
bulkhead, raise the aft end of the ribs, and move the barrel (21) aft far enough
to unwrap the trim cable from around the barrel and idler pulleys (18).
(j) Remove the forward portion of the cable (6) as given in paragraph
5-19.
4. The horizontal and diagonal support ribs may be removed by removing
the cotter pin cable guard at the trim indicator cable pulley located on the diagonal
rib, and removing the attaching nuts, washers and bolts that secure the ribs to
the aft bulkhead.
c. PA-28-140, Serial Nos. 28-20657 and up; PA-28-150,-160,-180, Serial
Nos. 28-2172 to 28-9377 incl. and PA-28-235, Serial Nos. 28-10606 to 28-10719
incl.
1. Remove the tail cone fairing by removing attaching screws.
2. Remove the access panel located at the aft wall of the baggage compart-
ment to allow access to the aft section of the fuselage.
3. To remove the trim control cable, proceed as follows:
(a) Block the first set of pulleys forward of the cable turnbuckles (8) in
the aft section of the fuselage by the method shown in Figure 5-10.

Reissued: 1/15/81 SURFACE CONTROLS

2B11
 PIPER CHEROKEE SERVICE MANUAL

(b) Remove the cable guard pin from the pulleys located withinthe fuse-
lage at station 228.30.
(c) Disconnect the links (19), located between the trim screw (11) and
control arm (15) at the trim screw by removing nut, washers and bolt.
(d) Remove the cotter pin that extends through the top of the trim screw
and the cable guard pin located just aft of the trim barrel (21).
(e) Turn the screw down and out from the underside of the barrel.
(f) Remove the snap ring, washer and thrust washer from the bottom
of the barrel.
(g) Disconnect the diagonal and horizontal (20) trim assembly support
ribs from one another by removing their four attaching nuts, washers and bolts.
(h) Loosen the attaching bolts where the horizontal ribs attach to the
fuselage bulkhead, raise the aft end of the ribs and remove the barrel with cable.
Draw the cable from the fuselage.
4. The horizontal and diagonal support ribs may be removed by removing
the cotter pin cable guard at the trim indicator cable pulley located on the diago-
nal rib, and removing the attachment nuts, washers and bolts that secure the ribs
to the aft bulkhead.
d. The trim indicator cable(17) may be removed from the aft area of the fuse-
lage by disconnecting the cable from the trim screw trunnion or at the lower end
of the trim screw (11), removing the cotter pin cable guard at the pulley located
below the trim screw and disconnecting the cable from the indicator wire.

5-22. INSTALLATION OF STABILATOR TRIM CONTROLS. (AFT.)

(Refer to Figure 5-9.)
a. PA-28-150,-160, -180, Serial Nos. 28-1 to 28-1410' incl. (The exception
being airplanes with Piper Kit No. 756 930, Stabilator Trim Modification, in-
stalled. Airplanes with this kit installed, refer to step c.)
1 The trim mechanism may be assembled and attached to the aft bulkhead
of the fuselage as follows:
(a) Assemble the trunnion (12), stops and pulley (10) in the trim shaft
and secure with roll pins.
(b) Assemble the trim mechanism by placing an AN960-516L washer
followed by a support on each end of the shaft assembly (11). Install washers and
nuts, check freedom of rotation of the shaft with no end play and then secure nuts
with cotter pins.
(c) Align the attachment hole of each support brace with those of the
aft bulkhead, install bolts and secure with washers and nuts.
(d) Draw the trim cable and attach the end to the trim screw trunnion,
and secure with bolts, nut and washer. With the cable placed around the pulley
located directly below, the trunnion, install the cotter pin cable guard at the pulley.

Reissued:1/15/81 2B12 SURFACECONTROLS

 PIPER CHEROKEE SERVICE MANUAL

2. The trim control cable may be installed by the following procedure:

(a) Install the forward portion of the cable as givenin paragraph 5-20.
(b) With the forward portion installed, route the long length (the long
length should be the left end of the cable) aft, counterclockwise around to the top
groove of the trim pulley (10), around the idler pulley (18), back around the bot-
tom groove of the trim pulley and forward to the inside of the fuselage.
(c) Draw the cable end forward and connect it with its mating end within
the fuselage.
(d) Ascertain that the cable is seated in the groove of each pulley, and
install the cotter pin cable guards at the pulleys located within the fuselage at
station 228.30 and at idler pulley at the aft fuselage bulkhead.
(e) Install the cable guard at the top support brace located just aft
the trim screw pulley.
3. The trim indicator cable may be installed by attaching one end to the
trim screw trunnion. (Refer to Figure 5-9 for correct location.) Loop the cable
around the pulley below the trim screw; Install the cotter pin cable guard at the
pulley. Attach other end of the cable to the indicator wire, and at the same time
make adjustments given in paragraph 5-23.
4. Set cable tension and check rigging and adjustment per paragraph 5-23.
Check safety of turnbuckle.
5. Install tail cone fairing and secure with screws.
6. Install the access panel to the aft section of the fuselage.
b. PA-28-140, Serial Nos. 28-20002 to 28-20656 incl; PA-28-150, -160, -180,
Serial Nos. 28-1411 to 28-2171 incl. and PA-28-235, Serial Nos. 28-10003 to
28-10605 incl. (The exception being those airplanes with Piper Kit No. 756 896,
Stabilator Trim Modification, installed. Airplanes with this kit installed, refer
to step c.)
1. Ascertain that the trim barrel bushings are lubricated and installed in
the rib plate and clip.
2. Attach the horizontal (20) and diagonal support ribs to the aft bulkhead
of the fuselage with bolts, washers and nuts. Start nuts only a few threads so as
to allow ribs to hang loose. Do not connect the ribs at this time.
3. Install the forward portion of the cable as given in paragraph 5-20.
4. Wrap the trim cable around the barrel(21)and idler pulley (18). To do
this, hold the barrel next to the aft end of the support braces and wrap, bringing
the end of the long length(The long length should be the left end of the cable.) aft
to the left side of the trim barrel, around the bottom groove of the idler pulley,
then continuing to wrap in this direction until all grooves are filled.
5. Install the trim barrel (21) in the bushing between the horizontal and
diagonal ribs, and then attach the ribs, securing with bolts, washers and nuts.
Tighten bolts where the ribs attach to the aft bulkhead.

Reissued: 1/15/81 2B13 SURFACE CONTROLS

 PIPER CHEROKEE SERVICE MANUAL

6. Install the thrust washer, washer and snap ring on lower end of the
barrel.
7. Install the trim screw in the barrel and secure each end with a cotter
pin through the screw.
8. Draw the cable end forward and connect it with its mating end within
the fuselage.
9. Ascertain that the cable is seated in the groove of each pulley and in-
stall the cotter pin cable guards at the pulleys located within the fuselage at sta-
tion 228.30 and at the idler pulley at the aft fuselage bulkhead.
10. Set cable tension and check rigging and adjustment per paragraph 5-17.
Check safety of turnbuckle.
11. The trim indicator cable may be installed by attaching one end to the
lower end of the trim screw (Refer to Figure 5-9 for correct location.) and loop-
ing the cable around the pulley below thetrim screw. Install the cotter pin cable
guard at the pulley. Attach other end of the cable to the indicator wire, and at
the same time make adjustments given in paragraph 23.
12. Install tail cone fairing and secure with screws.
13. Install access panel to the aft section of the fuselage.
c. PA-28-140, Serial Nos. 28-20657 and up; PA-28-150,-160,-180, Serial No.
28-2172 to 28-9377 incl. and PA-28-235, Serial Nos. 28-10606 to 28-10719 incl.
1. Ascertain that the trim barrel bushings are lubricated and installed in
the rib plate and clip.
2. Attach the horizontal (20) and diagonal support ribs to the aft bulkhead
of the fuselage with bolts, washers and nuts. Start nuts only a few threads so as
to allow ribs to hang loose. Do not connect the ribs at this time.
3. Wrap the trim barrel (21). To do this, first lay the center (as meas-
ured equally from each end to the center of the cable) of the trim cable in the slot
of the barrel. Bring the upper cable through the diagonal slot in the flange at the
upper end of the barrel and wrap down in a counterclockwise direction. Bring the
lower cable through the diagonal slot in the lower end of the barrel and wrap up
in a clockwise direction. Wrap the cable as evenlyas possible to obtain 23 wraps
on the barrel as viewed from the side opposite the slot and with the cables extend-
ing out from the slotted side.
4. Block both cables by clamping them between two pieces of wood laid next
to the wraps to prevent them from unwrapping. (Refer to Figure 5-10.)
5. Install the barrel in the bushings between the horizontal and diagonal
ribs, and then attach rib securing with bolts, washers and nuts. Tighten bolts
where the ribs attach to the aft bulkhead.
6. Install the thrust washer, washer and snap ring on the lower end of the
barrel.
7. Install the trim screw (11) in the barrel and secure each end with a cot-
ter pin through the screw.

Reissued: l/15/81 2B14 SURFACE CONTROLS

 PIPER CHEROKEE SERVICE MANUAL

8. Route the cable ends into the fuselage and attach the ends to the mating
end of the forward cable.
9. Remove the blocks holding the forward cable tight and the aft cables at
the barrel.
10. Set cable tension and check rigging and adjustment per paragraph 5-23.
Check safety of turnbuckles.
11. The trim indicator cable may be installed by attaching one end to the
lower end of the trim screw (Refer to Figure 5-9 for correct location.) and loop-
ingthe cable around the pulley below the trim screw. Install the cotter pin cable
guard at the pulley. Attach other end of the cable to the indicator wire, and at
the same time make adjustments given in paragraph 5-23.
12. Install tail cone fairing and secure with screws.
13. Install the access panel to the aft section of the fuselage.

5-23. RIGGING AND ADJUSTMENT OF STABILATOR TRIM.

(OVERHEAD CONTROL.)
a. PA-28-150, -160, -180, Serial Nos. 28-1 to 28-1410 incl. (The exception
being those airplanes with Piper Kit No. 756 930, Stabilator Trim Modification,
installed. Airplanes with this kit installed, refer to step b.) (Refer to Figure
5-9.)
1. Level the airplane. (Refer to Leveling, Section II.)
2. Check for proper stabilator trim cable tension as given in Table V-I.
If the cables were disconnected, rotate control crank (1) several times to allow
the cables to seat and recheck tension.
3. Position the stabilator against its down stop. Ascertain that the stab-
ilator travel is correctly set according to Table V-I.
4. Turn the trim crank until the aft end of the turnbuckle of the right trim
cable is positioned approximately one-half inch forward of the double pulley clus-
ter at the top of the rear bulkhead at station 228.3.
5. Check that the trim screw trunnion (12) is turned down until it contacts
the top of the lower screw stop of the trim assembly If the trunnion is not con-
tacting the stop, and the fork (14) between the trim support bracket (13) and the
trim control arm (15) is not disconnected, -disconnect the arm from the tab by
removing the connecting bolts. With the turnbuckle still at the one-half dimen-
sion from the pulley, turn the screw down until the trunnion contacts the stop.
6. With the stabilator positioned against its down stop, adjust the trim
actuating arm until the trailing edge of the tab aligns with the trailing edge of the
stabilator. Adjust by loosening the jam nut on the fork of the control arm and
turning the fork in or out as required.
7. Connect the control arm to the tab and secure with bolts.

Reissued: 1/15/81 2B15 SURFACE CONTROLS

 PIPER CHEROKEE SERVICE MANUAL

8. Move the stabilator to the neutral position and secure. To find neutral,
place a rigging tool on the upper surface of the stabilator as shown in Figure 5-8.
Zero a bubble protractor, set it on the rigging tool and tilt the stabilator until
the bubble is centered.
9. Turn the trim crank until the trailing edge of the tab aligns with the
trailing edge of the stabilator.
10. Check the bubble of the protractor over the neutral tab and then check
tab travels as given in Table V-I. The degree of travel on the protractor is de-
termined by taking the difference between the protractor reading at neutral and
up, and neutral and down. The bubble must be centered at each reading with the
airplane level.
11. To obtain correct travels, if incorrect, adjust by disconnecing the ac-
tuating arm and turning it in or out as required. Reconnect the arm to the tab.
12. Secure the jam nut against the fork.
13. Turn the trim wheel to full travel and check for turnbuckle clearance
and location of tab indicator.
b. PA-28-140;PA-28-150, -160, -180, Serial Nos. 28-1411 to 28-4377 incl. and
PA-28-235, Serial Nos. 28-10003 to 28-10719 incl. (Refer to Figure 5-9.)
1. Level the airplane. (Refer to Leveling, Section II.)
2. Check for proper stabilator trim cable tension as given in Table V- .
If the cables were disconnected, rotate control crank (1) several times to allow
the cables to seat and recheck tension.
3. Position the stabilator against its down stop. Ascertain that the stabi-
lator travel is correctly set according to Table V-I.
4. Turn the trim crank until the aft end of the turnbuckle of the right trim
cable is positioned approximately one-half inchforward of the double pulley clus-
ter at the top of the rear bulkhead at station 228.3.
5. Check that the trim screw is turned down until the cotter pin stop in the
top of the screw is contacting the plate (9) on the horizontal support rib (20) of
the trim assembly. If the stop is not contacting the plate, and the links between
the screw (11) and the trim control arm (15) are not disconnected, disconnect the
two by removing the connecting nut, washer and bolt. With the turnbuckle still
at the one-half dimension from the pulley, turn the screw down until the pin con-
tacts the plate.
6. Withthe stabilator positioned against its down stop, adjust thetrim ac-
tuating arm until the trailing edge of the tab aligns with the trailing edge of the
stabilator. Adjust by loosening the jam nut on the end bearing of the control arm
and turning the bearing in or out as required.
7. Connect the links to the control arm and secure with bolt, washers and
nut.

Reissued: 1/15/81
2B16 SURFACE CONTROLS
 PIPER CHEROKEE SERVICE MANUAL

8. Move the stabilator to the neutral position and secure. To find neutral,
place a rigging tool on the upper surface of the stabilator as shown in Figure
5-8. Zero a bubble protractor, set it on the rigging tool and tilt the stabilator
until the bubble is centered.
9. Turn the trim crank until trailing edge of the tab aligns with the trail-
ing edge of the stabilator.
10. Check the bubble of the protractor over the neutral tab and then check
tab travels as given in Table V-I. The degree of travel on the protractor is de-
termined by taking the difference between the protractor reading at neutral and
up, and neutral and down. The bubble must be centered at each reading with the
airplane level.
11. To obtain correct travels, if incorreci, adjust by disconnecting the links
at the actuating arm rod end and turning the end in or out as required. Reconnect
links to rod end.
12. Secure the jam nut on the actuating arm rod end.
13. Turn the trim wheel to full travel and check for turnbuckle clearance
and location of tab indicator.

5-24. STABILATOR TRIM CONTROLS. (FLOOR TRIM.)

5-25. REMOVAL OF STABILATOR TRIM ASSEMBLY. (FORWARD.)

(Refer to Figure 5-11.)
a. To remove the trim control wheel assembly and/or the trim control cables,
first remove the panel to the aft section of the airplane.
b. If the aft trim cable (12) is not to be removed, block the cables atthe pulleys
(13) inthe upper aft section of the fuselage to prevent them from unwrappingfrom
the trim drum. (Refer to Figure 5-10.)
c. Loosen the cables if the trim control wheel (1) is to be removed or discon-
nect if the cables are also to be removed. Do this at the trim cable turnbuckles
(10 and 11) in the aft section of the fuselage.
d. The control wheel (1) with drum (3) may be removed by the following pro-
cedure:
1. Remove the control wheel cover by removing the cover attaching screws.
2. The wheel assembly may be removed from its mounting brackets by
removing nut, washer and bolt (7) that secures the wheel between the brackets.
Draw the wheel from the brackets. Use caution not to damage trim indicator
wire (2).
3. Unwrap the left cable (9) from the drum.
4.. The wheel and drum are joined by a push fit, separate these two items
with their center bushing and unwrap the right cable (8).

Reissued:1/15/81 2B17 SURFACE CONTROLS

 PIPER CHEROKEE SERVICEMANUAL

C339

28

19. BUSHING, BARREL

1. CONTROL WHEEL TRIM 20. BARREL, TRIM
2. INDICATOR TRIM POSITION 21. CLIP, DIAGONAL RIB
3. DRUM, TRIM CABLE 22. RIB, DIAGONAL SUPPORT
4. MOUNTING BRACKET 23. SCREW, TRIM
5 CLEVIS PIN, WASHER & COTTER PIN 24. BOLT, WASHER (2) & NUT
6. PULLEY CLUSTER 25. LINK
BOLT, BUSHING, WASHER & NUT 26. ROD END
CABLE, RIGHT FORWARD 27. JAM NUT
9. CABLE, LEFT FORWARD 28. ARM, TRIM CONTROL
10.. TURNBUCKLE, RICHT 29. BUSHING BARREL
11. TURNBUCKLE, LEFT 30. WASHER, THRUST
12. CABLE, AFT 31. WASHER, SPACER
13. PULLEY CLUSTER 32. SNAP RING
a 14 BOLT, BUSHING, WASHER (3) & NUT 33. PULLEY CLUSTER
15. GUARD-BOLT, BUSHING, WASHER & NUT 34. PULLEY CLUSTER
16 RIB, HORIZONTAL SUPPORT 35. BOLT, WASHER & NUT
17. PLATE, RIB 36. GUARD, CABLE
18. GUARD 37. RUB BLOCK

Figure 5-11. Stabilator Trim Control (Floor Control)

Reissued:1/15/81 2B18 SURFACE CONTROLS

 PIPER CHEROKEE SERVICE MANUAL

5. Tie the cables forward to prevent them from slipping back into the floor
tunnel.
e. The trim control cables (8 and 9) may be removed by the following proce-
dure:
1 . Remove the rear seat bottom or floor panel, whichever applies, and the
front seats, if desired.
2. Unfasten the carpet from the aft portion of the floor tunnel and lay it
forward.
3. Remove the tunnel cover located between the trim control wheel and the
spar cover by removing attaching screws.
4. Remove the cable pulleys (6) located in the tunnel by removing the cotter
pin, washer and clevis pin (5).
5. Remove the cable rub blocks (37) located on the aft side of the main spar
by removing the block attaching screws.
6. Remove the cable guard pin (36) at the pulley cluster (34) located just
aft of the wing flap torque tube at station 127.25.
7. If installed, remove the cable pulleys (33) within the aft section of the
fuselage at station 156.5 by removing nut, washer, bushing and bolt.
8. With the cables disconnected from the trim control wheel, draw the
cable(s) through the floor tunnel.

5-26. INSTALLATION OF STABILATOR TRIM ASSEMBLY. (FORWARD.)

(Refer to Figure 5-11.)
a. The trim control wheel with drum may be installed by the following proce-
dure:
1. Wrapthe right trim cable on the trim drum byinsertingthe swaged ball
of the cable in the slot provided in the side (right side) of the drum that mates
with the control wheel, and looking at this side, wrap the drum with three wraps
of the cable in a clockwise direction.
2. Attach the control wheel to the cable drum by aligning the long lug of
the drum with the long slot of the wheel and pushing the two pieces together.
3. Wrap the left trim cable on the drum by inserting the swaged ball of the
cable in the slot provided in the flanged side (left side) of the drum and looking
at this side, wrap the drum with three wraps of the cable in a clockwise direction.
4. Lubricate and install the bushing in the control wheel and drum.
5. Alignthe controlcables andpositionthe control wheel assembly between
its mounting brackets. Ascertain that the end of the trim indicator wire is posi-
tioned in the spiraled slot of the drum withno bind on the end. Install the retainer
bolt from the left side and install washer and nut.
6. Install the cover over the control wheel and secure with screws, unless
the control cables have yet to be installed.

Reissued: 1/15/81 2B19 SURFACE CONTROLS

 PIPER CHEROKEE SERVICE MANUAL

... b. The trim control cables may be installed by the following procedure:
1. Draw the cable(s) through the floor tunnel.
2. Wrap the cable drum and install the trim control wheel as given in
step a.
3. Position the cable pulleys on their mounting bracket within the floor
tunnel and install the clevis pin, washer and cotter pin.
4. Connect the cable to the aft cable at the turnbuckle in the aft section of
the fuselage. Install aft cable if not installed.
5. If previously installed, install the pulleys in the aft lower section of the
fuselage at station 156.5 forward of the cable turnbuckles.
6. Install the cable guard atthe underside of the pulleys located just aft of
the flap torque tube at station 127.25 and secure.
7.. Install the cable rub blocks located on the aft side of the main spar
housing and secure with screws.
8. Remove the blocks that secure the aft trim cable and check that the
cables are seated on their pulleys.
c. Set cable tension and check rigging and adjustment per paragraph 5-29.
Check safety of all turnbuckles.
d. Install the tunnel cover on the tunnel and secure with screws.
e. Install the carpet over the floor tunnel.
f. Install the cover over the trim control wheel and secure with screws and
special washers.
g. Install the floor panel and seat belt attachments aft of the main spar and
secure panel with screws.
h. Install the panel to the aft section of the airplane and the seats.

5-27. REMOVAL OF STABILATOR TRIM ASSEMBLY. (AFT.)

(Refer to Figure 5-11.)
a. Remove the access panel to the aft section of the fuselage.
b. Block the trim cables at the first set of pulleys (33) forward of the cable
turnbuckles (10 and 11) in the aft section of the fuselage by a method shown in
Figure 5-10.
c. Disconnect the cable (12) at the turnbuckles (10 and 11) in the aft section
of the fuselage.
d. Remove the tail cone by removing its attaching screws.
e. Disconnect the link (25) between the trim screw (23) and the trim control
arm (28) by removing the nut, washer and bolt (24) that connects the link to the
screw.
f. Remove the cotter pin from the top of the screw (23), and turn the screw
down and out of the barrel (20).

Reissued: 1/15/81 SURFACE CONTROLS

2B20
 PIPER CHEROKEE SERVICE MANUAL

g. Remove the snap ring (32), washer (31) and thrust washer (30) from the
bottom of the barrel.
h. Disconnect the diagonal rib (22) from the horizontal rib (16) that supports
the trim assembly by removing the four attaching nuts, washers and bolts.
i. Draw the trim cable (12) from the fuselage.

5-28. INSTALLATION OF STABILATOR TRIM ASSEMBLY. (AFT.)

(Refer to Figure 5-11.)
a. Wrap the trim barrel (20) by first laying the center (as measured equally
from each end to the center of the cable) of the trim cable (12) in the slot of the
barrel. Bring the upper cable through the diagonal slot in the flange at the upper
end of the barrel and wrap down in a counterclockwise direction. Bring the lower
cable through the diagonal slot in the lower end of the barrel and wrap up in a
clockwise direction. Wrap the cable as evenly as possible to obtain 23 wraps on
the barrel as viewed from the side opposite the slot and with the cables extending
out from the slotted side.
b. Block both cables by clamping them between two pieces of wood laid next to
the wraps to prevent them from unwrapping.
c. Ascertain that the barrel bushings (19 and 29) are installed in the rib plate
(17) and clip (21).
d. Lubricate the bushings and install the trim barrel (20) in the bushings be-
tween the two support ribs. Attach the bottom diagonal rib (22) to horizontal rib
(16) and secure with bolt, washers and nuts.
e. Install the thrust washer (30), washer (31) and snap ring (32) on the lower
end of the barrel.
f. Install the trim screw (23) in the barrel (20) and secure each end with a
cotter pin through the screw.
g. Route the cables into the fuselage and attach the ends to the forward trim
cables (8 and 9).
h. Remove the blocks that are holding the forward cables tight and aft cables
at the barrel.
i. Set cable tension and check rigging and adjustment per paragraph 5-29.
Check safety of all turnbuckles.
j. Install the tail cone and secure with screws.
k. Install the access panel to the aft section of the fuselage.

Reissued: 1/15/81 2B21 SURFACE CONTROLS

 PIPER CHEROKEE SERVICE MANUAL

5-29. RIGGING AND ADJUSTMENT OF STABILATOR TRIM. (FLOOR

CONTROL.) PA-28-180, Serial Nos. 28-4378 and up; PA-28-235,Serial Nos. 28-10720and
up; and PA-28R. (Refer to Figure 5-11.)
a. Level the airplane. (Refer to Leveling, Section II.)
b. Check for proper stabilator trim cable tension as given in Table V-I. If
cables were disconnected, rotate control wheel several times to allow the cables
to seat and recheck tension.
c. Secure the stabilator in neutral position. To find neutral, place a rigging
tool onthe upper surface of the stabilator as shownin Figure 5-7. Zero a bubble
protractor, set it on the rigging tool and tilt the stabilator until the bubble is cen-
tered.
d. With the stabilator centered, turn the trim wheel (1) until the aft end of the
turnbuckle (10) of the right trim cable (8) is approximately two inches forward of
the double pulleys (13) at the top of the rear bulkhead at station 228.3.
e. Check that the trim screw (23) is turned down until the cotter pin stop in
the top of the screw is contacting the plate (17) on the horizontal support rib (16)
of the trim assembly. If the stop is not contacting the plate, the links (25) be-
tween the screw (23) and the trim control arm (28) are not disconnected, discon-
nect the two by removing the connecting nut, washers and bolt (24). With the
turnbuckle still at the two inch dimension from the pulley, turn the screw down
until the pin contacts the plate.
f. Check the rod end (26) on the tab actuating arm (28) for approximately six
threads forward of the jam nut (27).
g. Connect the links to the trim screw and secure with bolt, washers and nut.
h. Turn the trim control wheel until the trim tab streamlines with the neutral
stabilator.
i. Check the bubble of the protractor over the neutral tab and then check tab
travels as given in Table V-I. The degree of travel on the protractor is deter-
mined by taking the difference between the protractor reading at neutral and up,
and neutral and down. The bubble must be centered at each reading with the air-
plane level.
j. To obtain correct travels, if incorrect, adjust by disconnecting the links
(25) at the actuating arm rod end (26) and turning the end in or out as required.
Reconnect links to rod end.
k. Secure the jam nut (27) on the actuating arm rod end.
1. Turn the trim wheel to full travel and check for turnbuckle clearance and
location of tab indicator.

Reissued: 1/15/81
2B22 SURFACE CONTROLS
 PIPER CHEROKEE SERVICE MANUAL

5-30. RUDDERAND STEERINGPEDALASSEMBLY.

5-31. REMOVALOF RUDDER AND STEERING PEDAL ASSEMBLY.(Refer to Figure

5-12.)
a. Remove the accesspanel to the aft section of the fuselage.
b. Relieve rudder and stabilator cable tension by loosening one of the rudder and
stabilator cable turnbuckles in the aft section of the fuselage.
c. Remove the tunnel plate located just aft of the tee bar assembly by the following
procedure:
1. PA-28-140;PA-28-150,-160,-180 and PA-28R. Remove the rudder trim control
knob, trim cover attaching screwsand trim cover. Roll back the carpet from the tunnel and
remove the tunnel plate that is locatedjust aft of the tee bar assembly by removing the plate
attaching screws.
2. PA-28-235: Remove the fuel selector and rudder trim covers by removing the
knobs and the attaching screws. Disconnect the fuel indicator control lever from the fuel
selector torque tube by removing the attaching pin located at the bottom of the lever.
Remove the tunnel plate located just aft of the tee bar by laying back enough tunnel carpet
to remove the plate attaching screws. -
d. Disconnect the stabilator control cable from the lower end of the tee bar assembly.
e. Remove the tee bar attaching bolts with their washers and nuts which are through
each side of the floor tunnel. Pull the lower end of the tee bar aft.
f. Disconnect the control cable (19) ends from the arms on the torque tube (3) by
removing the cotter pins, washers,nuts and bolts (20).
g. Disconnect the rudder trim from the torque tube assembly by removing the cotter
pin, washers and bolt that connects the arm to the trim. Remove the cotter pin and clevis
pin from the rudder trim mechanism and remove the mechanism from the mounting
channel. Remove the screw from the engine control bracket assembly and swing it out of
the way. Disconnect the alternate air cable and move aside.
h. Disconnect the steering rods (21) at the rudder (32 and 33) by removing nuts and
bolts (24).
i If airplane is equipped with toe brakes, disconnect the brake cylinders (12) at the
lower end of each cylinder rod (11) by removing the cotter pins, washers, nut and bolts
(20).
j. Disconnect the vee brace(s) (29) (two braces are used with right hand brakes) from
the torque tube by removing nuts, washers and bolts (27) that secure the strap bracket (28)
to the vee brace.
k. Disconnect the torque tube support bracket (35) where it attaches by removing its
attaching bolts.
1. Remove the two bolts (25 and 26) that extend through the torque tube and are
located at the center of the tube assembly over the floor tunnel. Compress the tubes.
Remove the left and right toe brake pedal assembly.

Reissued: 1/15/81 2B23 SURFACE CONTROLS

 PIPER CHEROKEE SERVICE MANUAL

1608

14

TUBE, L. OUTER 17. ROD END

2. TUBE, L. CENTER 18. JAM NUT
3. TUBE, R. CENTER 19. CONTROL CABLE, RUDDER
4. TUBE, R. OUTER 20. BOLT, WASHER, NUT & COTTER PIN
5. PLATE 21. ROD, NOSE WHEEL STEERING
6. BOLT & NUT 22. JAM NUT
7. SUPPORT BLOCK, UPPER 23. ROD END, STEERING
8. SUPPORT BLOCK, LOWER 24. BOLT & NUT
9. WASHER, SPACER
25. BOLT, WASHER & NUT
10. ARM, IDLER
26. BOLT, WASHER & NUT
1I. ROD, BRAKE CYLINDER 27. BOLT, WASHER & NUT
12. BRAKE CYLINDER 28. BRACKET
13. CLEVIS PIN & COTTER PIN 29. VEE BRACE -
14. TUBE, RUDDER CONTROL 30. CLEVIS PIN · COTTER PIN
15. CLEVIS ROD 31. RUDDER PEDAL, L. OUTER
16. CLEVIS PIN & COTTER PIN
32. RUDDER PEDAL, L. INNER
33. RUDDER PEDAL, R INNER
34. RUDDER PEDAL, R. OUTER
35. BRACKET, TUBE SUPPORT

Figure 5-12. Rudder and Steering Pedal Assembly

Reissued: 1/15/81 2B24 SURFACE CONTROLS

 PIPER CHEROKEE SERVICE MANUAL

m. Disconnect the torque tube support blocks (7 and 8) from their support brackets on
each side of the fuselageby removing the attaching nuts, washersand bolts (6).
n. Remove the trim side panels,if desired.
o. Rotate the rudder pedal bar assembly toward the cabin door far enough to pull the
right pedal bar out. Rotate the remaining assembly to the left and remove the assembly
from the aircraft. Note the spacers and washers (9) on each end and between the support
blocks.

5-32. INSTALLATION OF RUDDER AND STEERING PEDAL ASSEMBLY.(Refer to

Figure 5-12.)
a. Assemble the torque tube assembly (1, 2, 3 and 4) as shown in Figure 5-12. Do not
at this time install the two bolts (25 and 26) through the center of the tube assembly.
b. Place the upper support blocks (7) on the ends of the torque tube assembly.Note
that a washer (9) is required on each end of the tube.
c. Position the support blocks (7 and 8) on their mounting brackets at each side of the
fuselage and secure with bolts, washers and nuts. Note that a bushing is required in the bolt
holes of the upper support block, a plate on top of the upper block, between the upper and
lower blocks and under the block mounting bracket.
d. Align the bolt holes in the center area of the torque tube assembly,install bolts,
washers and nuts (25 and 26) and tighten.
e. Position the torque tube support bracket (35) on the floor tunnel and secure with
bolts.
f. Position the vee brace(s) (29) on the torque tube, install the strap bracket (28)
around the torque tube and brace and secure with bolts, washers and nuts (27).
g. Check that the rod end (17) on the clevis rod (15) is adjusted to givea dimension of
7.94 inches between hole centers.
h. Connect the ends of the brake cylinder rods (11) and clevis rods (15) to the idler
arms (10) and secure with clevis and cotter pins (13).
i. Connect the steering rods (21) to the rudder pedals (32 and 33) and secure with
bolts and nuts (24). Check steering rod adjustment per Alignment of Nose Gear, Section VII
or VIIA.
j. Connect the rudder trim to the arm of the torque tube and secure with bolt, washer,
nut and cotter pin. A thin washer is installed under the nut which is tightened only finger
tight.
k. Connect the ends of the rudder control cables (19) to the arms provided on the
torque tube and secure with bolts, washers, nuts and cotter pins (20). Allowthe ends free to
rotate.
1. Swing the tee bar into place and secure with attachment bolts, washers and nuts
(15). Insert bolts through each side of the floor tunnel. (See Figure 5-1 or 5-2.)

Reissued: 1/15/81 2CI SURFACE CONTROLS

 PIPER CHEROKEE SERVICE MANUAL

m. Connect the stabilator control cables (11) to the lower end of the tee bar with bolt,
washer and nut (16), and secure with cotter pin. (See Figure 5-1 or 5-2.) Allow the cable
ends to rotate freely.
n. Set rudder cable tension and check rigging and adjustment per paragraph
5-40.
o. Set stabilator cable tension and check rigging and adjustment per para-
graph 5-17.
p. Check aileron cable tension.
q. Check safety of bolt and turnbuckles.
r. Install the floor tunnel plate and secure with screws. Fasten the tunnel
carpet in place.
s. Install the rudder trim cover and control knob.
t. Install the access to the aft section of the fuselage.

5-33. RUDDER CONTROLS.

5-34. REMOVAL OF RUDDER CONTROL CABLES. (Refer to Figure 5-13.)

a. To remove either the forward (10 or 11) or aft (14 or 15) rudder cables,
first remove the access panel to the aft section of the fuselage.
b. Disconnect the desired cable at the turnbuckle (12 or 13) in the aft section
of the fuselage.
c. Either forward rudder cable may be removed by the following procedure:
1. Remove the rear seat or floor panel, whichever applies, and the front
seats.
2. Remove the cable guard pin(7) from the underside of the pulley cluster
(9) that is located in the aft area of the flap torque tube.
3. From within the area aft of the main spar, remove the cable rub blocks
(6) that are attached to the spar housing by removing the block attaching screws.
4. Remove the rudder trim knob and the cover attaching screws.
5. Remove the tunnel plate just aft of the tee bar by removing enough car-
pet from the tunnel to allow the plate attaching screws and the plate to be removed.
6. Move the cable guard pin (4) located under the pulley cluster (5) just aft
of the tee bar by removing the cotter pin from the exposed end and sliding it to
the left or right, as required.
7. Disconnect the end of the cable from the arm on the rudder pedal torque
tube by removing the cotter pin, nut, washer and bolt (2).
8. Draw the cable from the floor tunnel.

Reissued:1/15/81 2C2 SURFACE CONTROLS

 PIPER CHEROKEE SERVICE MANUAL

d. The aft rudder control cables may be removed by the following procedure:
1. Remove the tail cone fairing by removing its attaching screws.
2. Disconnect the cable (14 or 15) from the rudder horn (17) by removing
cotter pin, nut, washer and bolt (16).
6. 3. Draw the cable through the fuselage.

5-35. INSTALLATION OF RUDDER CONTROL CABLES. (Refer to Figure 5-13.)

a. The forward rudder control cables may be installed by the following pro-
cedure:
1. Draw the control cable through the floor tunnel.
2. Connect the end of the cable to the arm on the rudder pedal torque tube
by installing bolt, washer, nut and cotter pin (2). Allow the cable end free to
rotate on the arm.
3. Connect the cable to the aft control cable at the turnbuckle (12 or 13) in
the aft section of the fuselage. If the aft control cables are not installed, install
at this time per step b. Ascertain that each cable is in the groove of its pulley.
4. Move the cable guard (4) into position, that is located in the forward
area of the tunnel, under the pulley cluster (5) and secure with cotter pin.
5. Within the area aft of the main spar, install the cable guard blocks (6)
onto the spar housing and secure with screws.
6. Install the cable guard (7) under the pulley cluster (9) located just aft
of the flap torque tube.
7. Set cable tension and check rigging and adjustment per paragraph 5-36.
8. Install the forward tunnel plate aft of the tee bar and secure with screws.
9. Put the floor carpet in place and secure.
10. (PA-28-235.) Place the fuel selector lever on the selector torque tube
and secure with pin and cotter pin.
11. Install the lower and upper selector covers and secure with screws.
12. Install the rear seat or floor panel and install the seats.
b. The aft rudder control cables may be installed by the following procedure:
1. Position the control cable in the fuselage.
2. Connect the end of the cable (14 or 15) to the rudder horn (17) with bolt,
washer, nut and cotter pin (16). Allow the cable end free to rotate.
3. Connect the other cable end to forward control cable (10 or 11) at the
turnbuckle (12 or 13) in the aft section of the fuselage.
4. Set cable tension and check rigging and adjustmentper paragraph 5-36.
5. Install tail cone fairing and secure with screws.
c. Install the access panel to the aft section of the fuselage.

Reissued: 1/15/81 2C3 SURFACE CONTROLS

 PIPER CHEROKEE SERVICE MANUAL

1690

11

1. RUDDER & STEERING PEDAL ASSY.

2. BOLT, WASHER, NUT & COTTER PIN
3. BOLT, BUSHINGS, WASHER & NUT
4. GUARD PIN, CABLE
5. PULLEY CLUSTER
6. RUB BLOCKS
7. GUARD PIN, CABLE
8. BOLT, BUSHINGS, WASHER & NUT
9. PULLEY CLUSTER
10. CABLE, RIGHT FORWARD
11. CABLE, LEFT FORWARD
12. TURNBUCKLE, LEFT
13. TURNBUCKLE, RIGHT
14. CABLE, RIGHT AFT
15. CABLE, LEFT AFT
16. BOLT, BUSHING, WASHER & NUT
17. HORN RUDDER

Figure 5-13. Rudder Controls

Reissued: 1/15/81 2C4 SURFACE CONTROLS

 PIPER CHEROKEE SERVICE MANUAL

Refer to Figure 5-25 for tool fabrication

Figure 5-14. Rudder Rigging Tool Figure 5-15. Clamping Rudder Pedals

5-36. RIGGING AND ADJUSTMENT OF RUDDER CONTROLS.

a. To check and set the correct degree of rudder travel, the following proce-
dure may be used:
1. Check the rudder travel by swinging the rudder until it contacts its stop.
If the control cables are connected, use the rudder pedals to swing the rudder.
2. With the rudder against its stop, place a rigging tool against the side of
the rudder and vertical stabilizer as shown in Figure 5-14. (Ascertain that the
tool is not contacting any rivets.) If no gap exists between the rigging tool and
the surface of the rudder and vertical stabilizer, the rudder stop for one direc-
tion of travel is correct as required in Table V-I. (This tool may be fabricated
from dimensions given in Figure 5-23.)
3. Swing the rudder in the other direction and check travel as directed in
step 2.
4. Should the rudder travel be incorrect showing a gap between the tool
and any part of the control surfaces, the tail cone fairing should be removed and
the stops reset to obtain correct rudder travel. (Refer to Figure 5-16.)
b. To set cable tension and alignment of the rudder, the following procedure
may be used:
1. Remove the access panel to the aft section of the fuselage.
2. Ascertain that thenose gearsteeringhasbeen alignedand rudderpedals
set fore and aft according to Alignment of Nose Landing Gear, Section VII or VIIA.
3. Clamp the rudder pedals to align in a lateral position as shown in Fig-
ure 5-15.
4. Adjust the turnbuckles in the aft section of the fuselage to obtain proper
cable tension as given in Table V-I and to allow the rudder to align at neutral

Revised: 103 83 2C5 SURFACE CONTROLS

 PIPER CHEROKEE SERVICE MANUAL

1. RUDDER TRAVEL ADJUSTMENT

2. STABILATOR TRAVEL ADJUSTMENT

Figure 5-16. Rudder and Stabilator Travel Adjustments

position. Adjust cables evenly to prevent undue strain on aircraft components. Neutral
position can be determined by standing behind the airplane and sighting the rudder with the
vertical stabilizer or the center of the trim screw.
5. Check safety of turnbuckles.
c. On fixed landing gears check that when the rudder contacts its stop, the clearance
between the nose wheelstops and the nose wheelhorn is between..06and . 12of an inch. A more
accurate check can be made with the weight off the nose wheel. Adjust the stops according to
Alignment of Nose Landing Gear. Section VII.
d. On 1974 models adjust the rudder pedal stops by pushing on the pilot's left rudder
pedal until the rudder stop is contacted. Adjust the pedal stop (on the fire wall)to provide 0.060
to 0. 120of an inch clearance. Repeat the procedure with the copilot's right rudder pedal. Do
not push rudder harder than necessary to avoid cable stretch.
e. Install the tail cone fairing and the access panel to the aft section of the fuselage.

Reissued: 1/15/81 2C6 SURFACE CONTROLS

 PIPER CHEROKEE SERVICE MANUAL

5-37. RUDDER TRIM CONTROLS.

5-38. REMOVALOF RUDDERTRIM CONTROLS. (Refer to Figure 5-17.)

a. Remove the cover (1) from over the trim control assemblyby removingattaching
screws.
b. Remove the rudder trim knob (2) and the coverattaching screws.
c. Rotate the trim knob to the extreme left (counterclockwise)trim position.
d. Disconnect the housing lug from the arm on the rudder pedal torque tube by
removingcotter pin, nut, washer and bolt (7).
e. Remove the threaded bushing (4) from the aft end of the mounting channel (8) by
removing cotter pin and clevis pin (5). Some mounting channelshave two holes in the aft
end, note from which hole in the clevispin wasremoved.
f. The mounting channel may be removedby removingthe channelattaching screwsat
the inside of the channel.

5-39. INSTALLATIONOF RUDDERTRIM CONTROLS.(Refer to Figure 5-17.)

Install the rudder trim mechanism and set it at the neutral (no load on spring)position.
Perform the procedure only after all other rudder and nose wheelriggingis complete.
a. Install the trim control mounting channel (8) on the upper side of the floor tunnel.
A spacer plate (14) on some models is installedbetween the channeland the tunnel. Install
the attaching screws (9) which are securedwith anchor nuts.
b. Before attaching the assemblyto the mounting channel, ascertainthat the clips(1 1)
are installed so the safety wire (12) will be on top. Also, that the threaded bushing (4) is
installed on the assembly shaft (15) with the weldedattachment bushingforward or toward
the housing.
c. Attach the housing lug to the arm provided on the rudder pedal torque tube and
secure with bolt, washer and nut (7). Tighten the nut only finger tight and safety with
cotter pin.
d. Clamp the rudder pedals in neutral and position the threaded bushing in the
mounting channel (8). Turn the control shaft until the holes in the bushing and channel
align and then install the clevis pin and cotter pin (5). Should two thru holes be located in
the aft end of the mounting channel, the pin must be installed through the hole that will
give equal travel and hit rudder stops before bottoming out of the trim assembly.
e. With the rudder pedals neutral and no pressure fore or aft on the clevispin, install
the assembly cover (1) so that the indicator washer (13) and the neutral mark on the cover
align.
f. Install the trim cover, securewith screws,and install the trim control knob.

Reissued: 1/15/81 2C7 SURFACE CONTROLS

 PIPER CHEROKEE SERVICE MANUAL

1660

.25 must be held when trim assembly

Installed with rudder pedals In neutral position.

1. COVER
2. RUDDER TRIM XNOS
3. LOCK SCREW
. BUSHING
5. CLEVIS PIN
6. HOUSING, CONTROL SHAFT
8. BOLT ASSEMBLY
9. CHANNEL, MOUNTING
9. SCREW
10. SCREW
11. CLIPS
12. SAFETY WIRE
13. WASHER, INOICATOR
14. SPACER PLATE
15. SHAFT, CONTROL

Figure 5-17. Rudder Trim Control

5-40. RIGGING AND ADJUSTMENTOF RUDDER TRIM CONTROLS.Perform these

procedures only after all other rudder and nose wheelriggingis complete. No adjustments
are necessary other than those required during installation of the assemblyin the airplane as
givenin paragraph 5-39.

5-41. WING FLAP CONTROLS.

5-42. REMOVALOF WINGFLAP CONTROLS.(Refer to Figure 5-18.)

a. The flap torque tube assemblymay be removedby the followingprocedure:
1. Remove the accessplate located between the undersideof the aft section of each
wing and the fuselageby removing attachingscrews.
2. Remove the two front seats and the bottom half of the rear seat or floor panel,
whichever applies.
3. Disconnect the left and right flap control tubes (rods) (4) at the flaps by
removing the nuts, washers and bolts (2) or at the torque tube cranks (arms) (11) by

Reissued:
ed: 1/15/81 SURFACE CONTR(
 PIPER CHEROKEE SERVICE MANUAL

removing the bolts (12) and washersfrom the inner side of each crank. It will be necessay
to remove bolt through a hole in the side skin of the fuselagelocated over the torque tube
with the flap handlemovedto its 40 degreeposition.
4. With the flap handle (29), fully extend the flaps and disconnect the flap tension
spring (22) at the spar or the aft end of the control cable (23), as desired.
5. Grasp the flap handle, release the plunger(33) and allow the flap to return to
the retracted position. Use caution as forward pressure will be on the handle with the
tension spring disconnected.
6. Disconnect the flap return spring (32) at the spar or return chain (30), as
desired.
7. Disconnect the control cable from the chain (20) by removingcotter pin, nut
and clevisbolt (21).
8. Remove the tube support blocks (16 and 31) by removingthe block attaching
bolts (15).
9. Removethe nuts, washersand bolts (10) securingthe right and left cranks ( 1)
and stop fittings(13) on the torque tube.
10. From between each wing and the fuselage, remove the cranks from the torque
tube.
11. Disconnect one bearing block (7) from its mounting brackets (6) by removing
nuts, washersand bolts (5).
12. Slide the tube from the bearing block still attached to its brackets; raise the end
and lift it from the floor opening.
b. The flap control cable(23) may be removedby the followingprocedure:
1. If the front seats and bottom of the rear seat havenot been removed, remove the
seats.
2. Disconnect the flap tension spring (22) from the cable, if not previously
disconnected,by extendingthe flapsto relievespringtension.
3. Retract the flap. Use caution as forward pressurewillbe on the handle with the
spring disconnected.
4. Disconnect the cable from the chain (20) by removingcotter pin, nut, clevispin
and bushing(21).
5. Removethe flap handlebracket and cover.
6. Lift the aft section of the tunnel carpet far enough to remove the screws
securing the tunnel cover that is between the flap handle and the spar cover. Remove the
cover.
7. Removethe cotter pin cable guard from the flap cablepulley (24) located inside
the floor tunnel just ahead of the spar housing.
8. Removethe cable rub blocks located in the floor openingon the aft side of the
spar housing by removingthe attachingscrews.
9. Disconnectthe cable turnbuckle (25) at the flap handleby removingcotter pin,
nut and bolt (26). Checkclevisbolt (26) for wear. Replacebolt if any wear is evident.

Reissued: 1/15/81 2C9 SURFACE CONTROLS

 `
PIPER CHEROKEE SERVICE MANUAL

1707

19-

1. BRACKET, ROD ATTACHENT 12. BOLT, WASHER & BUSHING 23. CABLE, FLAP CONTROL
2. BOLT, WASHER S NUT 13. FITTING, TORQUE TUBE STOP 24. PULLEY
3. JAM NUT 14. TUBE, TORQUE 25. TURNBUCKLE
4. ROD, FLAP CONTROL 15. BOLT, WASHER & NUT 26. CLEVIS BOLT, NUT & COTTER PIN
5. BOLT, BEARING BLOCK ATTACHMENT 16. BLOCK, BEARING 27. BOLT, BUSHING, WASHER & NUT
6. BRACKET, BEARING BLOCK 17. SPROCKET, TENSION SPRING 28. BRACKET, FLAP HANDLE
7. BLOCK, BEARING 18. BOLT, WASHER & NUT 29. HANDLE, FLAP
8. NUT, LOCK 19. BRACKET, BEARING BLOCK 30. CHAIN, RETURN SPRING
9. SCREW, FLAP ADJUSTMENT 20. CHAIN, TENSION SPRING 31. BLOCK, BEARING
10. BOLT, WASHER & NUT 21. CLEVIS BOLT, BUSHING NUT & COTTER PIN 32. SPRING, RETURN
11. CRANK (ARM), TORQUE TUBE 22. SPRING, TENSION 33. BUTTON, FLAP RELEASE

Figure 5-18. Flap Controls

Reissued: 1/15/81 2C10 SURFACE CONTROLS

 PIPER CHEROKEE SERVICE MANUAL

c. Remove the flap handle (29)and bracket (28)by disconnecting the cable turn-
buckle from the handle and removing the bolts securing the bracket to thefloor
tunnel.

5-43. INSTALLATION OF WING FLAP CONTROLS. (Refer to Figure 5-18.)

a. The flap torque tube assembly may be installed by the following procedure:
1. Install the chain sprocket (17) with chain (20 and 30) on the torque tube
(14) and secure with bolts, washers and nuts (18).
2. Slide the tube stop fittings (13) on their respective ends of the torque
tube.
3. Ascertain that one bearing block fitting (7) is installed between its at-
tachment brackets (6).
4. Slide the other bearing block over its respective end of the torque tube.
5. Position the torque tube by placing the end with the bearing block on it
between the mounting bracket and sliding the other end into the previously attach-
ed bearing block.
6. Position the remaining bearing block and secure with bolts, washers
and nuts (5).
7. Push the torque tube cranks (arms) (11) on each end of the torque tube
and slide the stop fitting (13) in place. Align the bolt hole of the crank and stop
fitting with the holes in the torque tube and install bolts. The holes in the stop
fitting are longated to allow the stop fitting to be pushed against the bearing blocks
(7) thus allowing no side play of the assembly. Tighten the bolt assemblies (10)
on the stop fittings.
8. Install the tube support blocks (16 and 31) on their support brackets (19)
and secure with bolts (15).
9. Connect. the flap return spring (32) to the return chain (30) and/or at
the spar housing.
10. Connect the control cable end to the tension chain (20) and secure with
bushing, clevis bolt, nut and cotter pin.
11. Pull the flap handle full back and connect the tension spring (22). Re-
lease the flap handle to the forward position.
12. Connect the flap control tube (4) to the flap and/or torque tube crank (11)
and secure. The bolt (12) and bushing that connects the control tube to the crank
is installed through a hole in the side of the fuselage located over the torque tube.
b. To install the flap handle (29) with bracket (28), place the assembly on the
floor tunnel and secure with bolts.
c. The flap control cable (23) may be installed by the following procedure:
1. Attach the cable and turnbuckle (25) to the flap handle arm and secure
with clevis bolt, nut and cotter pin (26). Ascertain that the turnbuckle endis free
to rotate on the arm.

Reissued: 1/15/81 2Cll SURFACE CONTROLS

 PIPER CHEROKEE SERVICEMANUAL

Figure 5-19. Flap Step Adjustment

2. Route the cable through the tunnel and spar housing.

3. Install the cable rub blocks on the aft side of the spar housing and
secure with screws.
4. Install cotter pin cable guard over pulley (24) located just ahead of the
spar housing in the floor tunnel.
5. Attach the cable end to the tension chain(20) and secure with bushings,
clevis bolt, nut and cotter pin. If the chain is not installed because of the torque
tube assembly being removed, install the assembly as given in step c.
6. Pull the flap handle (29) full back and connect the tension spring (22) to
the cable end.
d. Install the tunnel cover and secure with screws. Also, the tunnel carpet
and bracket cover.
e. Install and secure the seats.

5-44. RIGGING AND ADJUSTMENT OF WING FLAPS.

a. Place the flap handle in the full forward position.
b. If not previously removed, remove the bottom half of the rear seat.
c. To adjust the flap up stop and step lock, loosen the jam nut of the right
torque tube stop screw, located in the floor opening along the outer end of the
flap torque tube, and turn the stop screw to obtain approximately .60 of an inch
between the stop fitting and the bearing block as measured along the top side of
the screw. (Refer to Figure 5-19.) It may be necessary to loosen the adjust-
ment screw of the left stop.

Revised: 4 23 84 2C12 SURFACE CONTROLS

 PIPER CHEROKEE SERVICE MANUAL

d. Place a .125 spacer between the stop fitting and the end of the screw. De-
termine that when pressure is applied down on the flap, it will remain in the up-
lock position. If it extends, turnthe adjustment screw out a few threads at a time
until the flap remains in the up-lock position with the spacer inserted. Tighten
the jam nut.
e. Rotate the left stop adjustment screw until it contacts the stop fitting.
Tighten the jam nut.
f. Set the flap control cable tension (handle next to floor, 0 degrees) as given
in Table V-I at the turnbuckle that is attached to the lower end of the flap handle
in the floor tunnel. To do this and if not previously removed, remove the flap
handle cover and enough tunnel carpet to remove the tunnel cover just aft of the
handle. Adjust and resafety the turnbuckle.

NOTE

Do not rotate the torque tube while."retensioning the

cable or tighten tight enough to allow tube to be pulled
away from its stops.

g. To check up-neutral position of the flaps, place a flap rigging tool as shown
in Figure 5-20 against the underside of the wing and flap as close as possible to
the outboard end of the flap without contacting any rivets. The tool must be po-
sitioned parallel with the wing ribs with the aft end of the tool even with the trail-
ing edge of the flap. (This tool may be fabricated from dimensions given in Fig-
ure 5-22.)
h. With the flap control rod connected between the torque tube crank arm and
the flap, check that the surface of the wing contacts the tool at its forward sur-
face and at the spacer, and the aft end of the flap contacts the aft end of the tool.
The flap is neutral at this position.
i. Should the three points not contact, loosen the jam nuts on each end of the
control rod and rotate the rod until the three points contact. Apply a slight up
pressure against the trailing edge of the flap while making this adjustment. After
adjustment, retighten the jam nuts.
j . Check and adjust the other flap in a like manner.

Reissued: 1/15/81 2C13 SURFACE CONTROLS

 PIPER CHEROKEE SERVICE MANUAL

NOTE

In the event of wing heaviness during flight, the flap

on the side of the heavy wing can be adjusted down
from neutral to remedy this condition by lengthening
the control rod. Check the inspection hole in each rod
end to ascertain that there are sufficient threads re-
maining and a wire cannot be inserted through these
holes. Rod ends without check holes, maintain a min-
imum of .375 of an inch thread engagement. Do not
raise the flap of the other wing above neutral.

k. Check the flap for full down travel to the degrees required in Table V-I.
Should the travel not be as that required, readjust the torque tube stop screw in
or out as required. After readjusting the screw, it will be necessary to review-
steps d thru j.
1. Check operation of the flap and flap handle ratchet mechanism.
m. Install access plates and panels.

857 1. 375 HEIGHT SPACER IS TO BE IN LINE WITH AFT SPAR

RIVET LINE. BUT SHOULD NOT MAKE CONTACTWITH ANY
RIVETS.
UP NEUTRAL (0) OF FLAPS WILL OCCUR WHEN THESE
POINTS MAKE CONTACT WITH WING AND FLAP SKIN.

.
TOOL:

Refer to Figure 5-23 for tool fabrication

Figure 5-20. Flap Rigging Tool

Revised: 4 23 84
2C14 SURFACE CONTROLS
 PIPER CHEROKEESERVICEMANUAL

A114
MATERIAL:
.125 X 3.53 X 1.0 ALUM. PLATE
OR
.125 X 3.85 X 1.0 ALUM. PLATE

3.531

.062R.
.125 .625

.062R.

2
2.781

Figure 5-21.- Fabricated AileronBellcrankRiggingTool

901
HERE

ONLY CORRECT METHOD

HERE

IMPROPERTOOL (RESULTING
IN LOCKEDBALL)

5-22. Correct Method of Installing Rod End Bearings

Reissued:1/15/81
SURFACE CONTROLS
2C15
 PIPERCHEROKEE SERVICE MANUAL

A115

SEE NOTE1

.375 13.250

I .187

4.0

31.50

SEE NOTE 2

NOTES
1. DRILLAND TAP TO 10-32NF. AN-3 BOLT,JAM NUTAND
INTERNALSTAR WASHER. MAY BE USED FORSPACER
OR AN-3 BOLTWITH HEADFILEDTOREQUIREDLENGTH.
2. SPAR STOCK MAY BE USED IN PLACEOF ALUM.BAR
STOCK.

.375

.750

MATERIAL:
: .750 X 31.50 X 4.00 ALUM. BAR OR
.750 X 31.5 X .750 ALUM. BAR (MIN.)

Figure 5-23. Fabricated Aileron and Flap Rigging Tool

Revised: 4'23 84 2C16 SURFACE CONTROLS

 PIPER CHEROKEE SERVICE MANUAL

932

MATERIAL:
1.0 X 23.19 X 3.82 ALUM. BAR
SURFACE PARALLEL TO BASE
SE LINE

STABILATOR CONTOUR
1.10
.803, 1.121 1.39, 1.60 . / 25 SET BACK

BASE LINE

22 20.00
.94
1.53
1.00
24.03 18.03 15.03

EDGE

Figure 5-24. Fabricated Stabilator Rigging Tool

Reissued: 1/15/81 2C17 SURFACE CONTROLS

 PIPER CHEROKEE SERVICE MANUAL

C341

8
.281
I

5.2

20
MATERIAL:
STEELOR HARDALUMINUM
.125 X 20.0 X 6.187 PLATE

Figure 5-25. Fabricated Rudder Rigging Tool

Reissued:1/15/81 2C18 SURFACE CONTROLS

 PIPER CHEROKEE SERVICE MANUAL

TABLEV-III. TROUBLESHOOTINGCHART(SURFACECONTROLS)

Trouble Cause Remedy

AILERONCONTROLSYSTEM

Lost motion between con- Cable tension too low. Adjust cable tension.
trol wheel and aileron. (Refer to paragraph
5-12.)

Linkage loose or worn. Check linkage and

tighten or replace.

Broken pulley. Replace pulley.

Cables'not in place on Install cables cor-

pulleys. rectly. Check cable
guards.

Resistance to control System not lubricated Lubricate system.

wheel rotation. properly.
Cable tension too high. Adjust cable tension.
(Refer to paragraph
5-12.)

Control column hori- Adjust chain tension.

zontal chain improperly (Refer to paragraph
adjusted. 5-6.)

Pulleys binding or Replace binding pulleys

rubbing. and/or provide clearance
between pulleys and
brackets.

Cablesnot in place on Install cables cor-

pulleys. rectly. Check cable
guards.

Bent aileron and/or Repair or replace ai-

hinge. leron and/or hinge.

Cables crossed or Check routing of control

routed incorrectly. cables.

Reissued: 1/15/81 SURFACE CONTROLS

2C19
 PIPER CHEROKEE SERVICE MANUAL

TABLE V-III. TROUBLESHOOTINGCHART (SURFACECONTROLS)(cont.)

Trouble Cause Remedy

AILERONCONTROLSYSTEM(cont.)

Control wheels not Incorrect control Rig in accordance with

synchronized. column rigging. paragraph 5-6.

Control wheelsnot hori- Incorrect riggingof Rig in accordance with

zontal when ailerons aileron system. paragraph 5-12.
are neutral.

Incorrect aileron Aileron control rods Adjust in accordance

travel. not adjusted properly. with paragraph 5-12.
Aileron bellcrank stops Adjust in accordance
not adjusted properly. with paragraph 5-12.

Correct aileron travel Incorrect riggingof Rig in accordance with

cannot be obtained by aileron cables, control paragraph 5-12.
adjusting bellcrank wheeland control rod.
stops.

Control wheel stops Incorrect rigging Rig in accordance with

before control between control wheel paragraph 5-12.
surfaces reach full and control cables.
travel.

Reissued: 1/15/811
2C20 STRUCTURES
 PIPER CHEROKEE SERVICE MANUAL

TABLEV-III. TROUBLESHOOTINGCHART (SURFACECONTROLS) (cont.)

Trouble Cause Remedy

STABILATORCONTROL SYSTEM

Lostmotion between
Lost Cable tension too low. Adjust cable tension
ntrol wheel and stabi- per paragraph 5-17.
lator.
Linkage loose or worn. Check linkage and
tighten or replace.

Broken pulley. Replace pulley.

Cablesnot in place Install cables cor-

on pulleys. rectly.

to stabilator
ReResistance System not lubricated Lubricate system.
ntrol movement. properly.
Cable tension too high. Adjust cable tension
per paragraph 5-17.

Bindingcontrol column. Adjust and lubricate

per paragraph 5-6.

Pulleys binding or Replace binding pulley

rubbing. and/or provide clearane
between pulleys and
brackets.

Cablesnot in place on Install cables cor-

pulleys. rectly.

Cables crossed or - Check routing of control

routed incorrectly. cables.

Bent stabilator hinge. Repair or replace

stabilator hinge.

Incorrect stabilator Stabilator stops Adjust stop screws per

travel. incorrectly adjusted. paragraph 5-17.

Reissued: 1/15/81 2C21 SURFACECONTROLS

 PIPER CHEROKEE SERVICE MANUAL

TABLE V-III. TROUBLESHOOTINGCHART (SURFACE CONTROLS)(cont.)

...

Trouble Cause Remedy

STABILATORCONTROL SYSTEM-(cont.)

Correct stabilator Stabilator cables Rig cablesin accordance

travel cannot be incorrectly rigged. with paragraph 5-17.
obtained by adjusting
stops.

STABILATORTRIM CONTROL SYSTEM

(FLOOR TRIM

Lost motion between - Cable tension too low. Adjustin accordance

trim control wheel with paragraph 5-29.
and trim tab.
Cables not in place on Install cables accord-
pulleys. ing to paragraphs 5-26
and 5-28.
Broken pulley. Replace pulley.
Linkage loose or worn. Check linkage and
tighten or replace.

Trim control wheel System not lubricated Lubricate system.

moves with excessive properly.
resistance.
Cable tension too high. Adjust in accordance
with paragraph 5-29.
Pulleys binding or Replace binding pulleys.
rubbing. Provide clearance between
pulleys and brackets.
Cables not in place on Refer to paragraphs
pulleys. 5-26 and 5-28.
Trim tab hinge binding. Lubricate hinge. If
necessary,replace.
Cables crossed or Check routing of control
routed incorrectly. cables.

Reissued: 1/15/81 SURFACE CONTROLS

2C22
 PIPER CHEROKEE SERVICE MANUAL

TABLE V-III. TROUBLESHOOTINGCHART(SURFACECONTROLS)(cont.)

Trouble Cause Remedy

STABILATORTRIM CONTROLSYSTEM(cont.)
FLOOR TRIM (cont.)

Trim tab fails to System incorrectly Check and/or adjust

reach full travel. rigged. riggingper paragraph
5-29.

Trim drum incor- Check and/or adjust

rectly wrapped. riggingper paragraph
5-29.

Trim indicator fails Trim indicator unit Adjust in accordance

to indicate correct not adjusted properly. with paragraph 5-29.
trim position.

OVERHEADTRIM

Lost motion between Cable tension too low. Adjust in accordance

trim control crank with paragraph 5-23.
and trim tab.
Cablesnot in place on Install cables accord-
pulleys. ing to paragraphs5-20
and 5-22.

Broken pulley. Replace pulley.

Linkage loose or worn. Check linkage and

tighten or replace.

Trim control crank System not lubricated Lubricate system.

moves with excessive properly.
resistance.
Cable tension too high. Adjust in accordance
with paragraph 5-23.

Reissued: 1/15/81 2C23 SURFACE CONTROLS

 PIPER CHEROKEE SERVICE MANUAL

TABLE V-III. TROUBLESHOOTINGCHART (SURFACE CONTROLS)(cont.)

Trouble Cause Remedy

STABILATORTRIM CONTROLSYSTEM(cont.)
OVERHEADTRIM (cont)

Trim control crank Pulleys binding or Replace binding pulleys.

moves with excessive rubbing. Provide clearance between
resistance. (cont.) pulleys and brackets.
Cablesnot in place on Refer to paragraphs
pulleys. 5-20 and 5-22.
. Trim tab hinge binding. Lubricate hinge. If
necessary, replace.
Cablescrossed or Check routing of control
routed incorrectly. cables.

Trim tab fails to System incorrectly Check and/or adjust

reach full travel. rigged. riggingper paragraph
5-23.

Trim drum incor- Check and/or adjust

rectly wrapped. riggingper paragraph
5-23.

Trim indicator fails Trim indicator unit Adjust in accordance

to indicate correct not adjusted properly. with paragraph 5-23.
trim position.

Reissued:1/15/81 2C24 SURFACE CONTROLS

 PIPER CHEROKEE SERVICE MANUAL

TABLEV-III. TROUBLESHOOTINGCHART (SURFACE CONTROLS)(cont.)

Trouble Cause Remedy

RUDDER CONTROL SYSTEM

Lost motion between Cable tension too low. Adjust cable tension
rudder pedals and per paragraph 5-36.
rudder.
Linkage loose or worn. Check linkage and
tighten or replace.

Broken pulley. Replace pulley.

Bolts attaching rudder Tighten bellcrank bolts.
to bellcrank are loose.

Excessiveresistance System not lubricated Lubricate system.

to rudder pedal properly.
movement.
Rudder pedal torque Lubricate torque tube
tube bearing in need bearings.
of lubrication.

Cable tension too high. Adjust cable tension

per paragraph 5-36.

Pulleys binding or Replace binding pulleys

rubbing. and/or provide clearance
between pulleys and
brackets.

Cablesnot in place on Install cables cor-

pulleys. rectly. Check cable
guards.

Cables crossed or Check routing of control

routed incorrectly. cables.

Rudder pedals not Rudder cables Rig in accordance with

neutral when rudder incorrectly rigged. paragraph 5-36.
is streamlined.

Reissued: 1/15/81
2D1 SURFACE CONTROLS
 PIPER CHEROKEE SERVICE MANUAL

TABLE V-III. TROUBLESHOOTINGCHART (SURFACE CONTROLS)(cont.)

Trouble Cause Remedy

RUDDER CONTROL SYSTEM(cont.)

Incorrect rudder Rudder bellcrank stop Rig in accordance with

travel. incorrectly adjusted. paragraph 5-36.
Nose wheel contacts Rig in accordance with
stops before rudder. paragraph 3-36.

RUDDER TRIM CONTROL SYSTEM

Trim control knob System not lubricated Lubricate system.

moves with excessive properly.
resistance.

FLAP CONTROL SYSTEM

Flaps fail to extend Control cable broken Replace or reconnect

or retract. or disconnected. control cable. (Refer
to paragraph 5-43.)

Flaps not synchro- Incorrect rigging Adjust flaps per in-

nized or fail to of system. structions in paragraph
move evenly when 5-44.
retracted.

Reissued: 1/15/81 2D2 SURFACE CONTROLS

 SECTION
VI

HYDRAULIC
SYSTEM
(PA-28R) Aerofiche
Grid No.
6-1. Introduction ................................ 2D4
6-2. Description ................................. 2D4
6-3. Troubleshooting ............................. 2D8
6-4. Hydraulic Pump ............................. 2D9
6-5. Removal of Hydraulic Pump .............. 2D9
6-6. Disassemblyof Hydraulic Pump ............ 2D9
6-7. Cleaning, Inspection and Repairsof
Hydraulic Pump.................. 2D11
6-8. Assembly of Hydraulic Pump ... .......... 2D11
6-9. Test and Adjustment of Hydraulic Pump ....... 2D12
6-10. Installation of Hydraulic Pump ............ 2D16
6-11. Filling Hydraulic Pump Reservoir ........... 2D16
6-12. Gear Back-Up Extender Actuator Assembly .............. 2D16
6-13. Removal of Gear Back-UpExtender Actuator
Assembly ...................... 2D16
6-14. Installation of Gear Back-UpExtender
Actuator Assembly ................ 2D17
6-15. Check and Adjustment of Gear Back-Up
Extender Actuator................. 2D18
6-16. Operational Check of Retractable
Landing Gear System ................
6-17. Nose Gear Actuating Cylinder . . . .................. 2E3
6-18. Removal of Nose Gear Actuating Cylinder ...... 2E3
6-19. Disassemblyof Nose Gear Actuating Cylinder .... 2E3
6-20. Cleaning,Inspection, and Repair of Nose
Gear Actuating Cylinder ... . .......... 2E3
6-21. Assembly of Nose Gear Actuating Cylinder ..... 2E4
6-22. Installation of Nose Gear Actuating Cylinder ... 2E6
6-23. Main Gear Actuating Cylinder ..................... 2E6
6-24. Removal of Main Gear Actuating Cylinder ...... 2E6
6-25. Disassemblyof MainGear Actuating Cylinder .... 2E6
6-26. Cleaning,Inspection, and Repair of Main
Gear Actuating Cylinder ............ 2E7
6-27. Assemblyof Main Gear Actuating Cylinder ..... 2E7
6-28. Installation of Main Gear Actuating Cylinder .... 2E7
6-29. Hydraulic Lines .............................. 2E7
6-30. Removal and Installation of Hydraulic Lines ..... 2E7

Reissued: 1/15/81
2D3
 PIPER CHEROKEE SERVICE MANUAL

SECTION VI

HYDRAULIC SYSTEM
PA-28R

6-1. INTRODUCTION.. The PA-28R hydraulic system components covered

in this section consist of the combination hydraulic pump and reservoir, gear
back-up extender actuator assembly, actuating cylinders and hydraulic lines.
The brake system, although hydraulically operated, is not included inthis section
as it has its own hydraulic system independent of the gear retraction system.
The brake system along with the landing gearand components is covered in Sec-
tion VIIA.
This section provides -instructions for remedying difficulties which may
arise in the operation of the hydraulic system. The instructions are organized
so that the mechanic can refer to: Description of the System, for a basic under-
standing of the system; Troubleshooting, for a methodical approach in locating
difficulty; Corrective Maintenance, for the removal, repair and installation of
components; and Adjustments and Checks, for the operation of the repaired sys-
tem.

CAUTION

Prior to starting anyinvestigation of the hydraulic sys -

tem, place the airplane on jacks. (Refer to Jacking,
Section II.)

6-2. DESCRIPTION. Hydraulic fluid is supplied to the landing gear actuating cylinders by
an electrically powered, reversible hydraulic pump located aft of the baggagecompartment
at right side of station 156.00. A reservoiris also an integral part of the pump. The pump is
controlled by a selector handle on the instrument panel to the left of the control quadrant.
As the handle is selected to either the up or down position, the pump directs fluid through a
single line to a manifold and from that manifold to each individual actuating cylinder. As
fluid pressure increases at one side of a cylinder piston, fluid at the other side is directed
back through another manifold to the pump. The two manifolds and their connecting lines
serve either as pressure or return passagesdepending on the rotation of pump to retract or
extend the gear.
On the manifold through which pressure fluid passed during gear retraction

Reissued: 1/15/81 HYDRAULIC SYSTEM

2D4
 PIPER CHEROKEE SERVICE MANUAL

HYDRAULICPUMPRESERVOIR
FILTER

RELIEF
THEWRMAL

PRESSURE
LOW

SHUTTLE
SWITCH

GEARDOWNSNUBBER
ORIFICE

MANUAL FALL
FREE GEAR
AUTORMATIC &
DOWN
EXTEND
EMERGENCY FALL
FREE
EMERGENCY
CYLINDER VALVE.
GEAR CYLINDER
HYDAULIC

SIDE
ONFUSELAGE

CHAMBER
SENSING

Figure 6-1. Schematic Diagram of Hydraulic System

Reissued: 1/15/81 2D5 HYDRAULIC SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

1817

1. PUMP/RESERVOIR
2. ACTUATING CYLINDER, RIGHT
3. MANIFOLD, GEAR DOWN
4. MANIFOLD, GEARUP
. PRESSURE SWITCH
6. GEAR BACK-UP EXTENDER ACTUATOR
7. MAST, ACK-UP EXTENDER
8. ACTUATING CYLINDER, LEFT
9. LEVER, EMERGENCY EXTENDER
10. ACTUATING CYLINDER NOSE
11. FITTING, RESTRICTOR

Figure 6-2. Hydraulic System Installation

Reissued: 1/15/81 2D6 HYDRAULIC SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

is a pressure switch. This switch opens the electrical circuit to the pump solenoid when the
gear fully retracts and pressure in the system increases to approximately 1400 psi The
switch will continue to hold the circuit open until pressure in the system drops to
approximately 1100 psi, when at that time the pump will again operate to build up pressure
as long as the gear selector handle is in up position. The down position of the handle does
not effect the pressure switch.
The hydraulic pump is a gear type unit driven by a 14-volt reversiblemotor designedto
operate at a maximum pressure of 1600 to 2000 psi. To prevent excessivepressure in the
hydraulic system due to fluid expansion, there is a thermal relief valve incorporated in the
pump that vill open at 4000 psi and allow fluid to flow to the pump reservoir. Other valves
in the pump system channel fluid to the proper outlets during gear retraction or extension.
In the base of the pump is a shuttle valve that allows fluid displaced by the cylinder piston
rods to return to the reservoir without back-pressure.
Also in the system is a by-pass or free-fall valve that allows the gear to drop should a
malfunction in the pump system occur. To prevent the gear from extending too fast, there is
a special restrictor fitting on the side of the valve. The valve is controlled manually or by a
gear back-up extension device that is operated by a pressure sensingdevice which lowers the
gear regardless of gear selector handle position, depending upon airspeed and engine power
(propeller slipstream). Gear extension occurs even if the selector is in the up position, at
airspeeds below approximately 105 MPH with engine power off. The device also prevents
the gear from retracting at airspeeds below approximately 85 MPHwith full power, though
the selector switch may be in the up position. This speed increases with reduced power
and/or increased altitude. The sensing device operation is controlled by a differential air
pressure across a flexible diaphragm which is mechanically linked to the hydraulic valveand
an electrical switch which actuates the pump motor.A high pressure and static air source for
actuating the diaphragm is provided in a mast mounted on the left side of the fuselageabove
the wing. Manual override of the device is provided by an emergency gear lever located
between the front seats to the left of the flap handle.
The emergency gear lever, used for emergency extension of the gear, manually releases
hydraulic pressure to permit the gear to free-fall with spring assistance on the nose gear. The
lever must be held in the downward position for emergency.extension. This same lever,
when held in the raised position, can be used to override the system, and gear position is
controlled by the selector switch regardlessof airspeed/power combinations. The lever must
also be held in the raised position when hydraulic system operational checks are being
conducted. An override lock is installed on 1972 models and is also availablein kit form for
earlier models. This lock allows the emergency extension lever to be locked in the up
override position. A warning light is mounted below the gear selector lever, and flashes to
indicate whenever the lock is in use. The lock is disengagedby pulling up on the extension
lever.
For a description of the landing gear and electrical switches, refer to Section VII,
Landing Gear and Brake System.

Reissued: 1/15/81 2D7 HYDRAULIC SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

TABLE VI-I. LEADING PARTICULARS, HYDRAULIC SYSTEM

Hydraulic Pump
High Pressure 1600 to 2000 psi
Low Pressure 650 ± 150 psi
Flow Rate @ 1000 psi 45 cu. in. per min.
High Pressure Control 1600 to 2000 psi
Thermal Relief 4000 psi
Hydraulic Fluid MIL-H-5606

Pressure Switch
Open (OFF) Pressure 1100 ± 100 psi
Close (ON) Pressure 400 ± 200 psi below opening pressure
6-3. TROUBLESHOOTING Malfunctions
6-3. TROUBLESHOOTING. Malfunctions of the hydraulic systemwill result in
failure of the landing gear to operate properly. When trouble arises, jack up the
airplane (Refer to Jacking, Section II.) and then proceed to determine the extent
of the trouble. Generally, hydraulic system troubles fall into two types, troubles
involving the hydraulic supplying system and troubles in the landing gear hydrau -
lic system. Table VI-III at the back of this section, lists the troubles which may
be encountered and their probable cause, and suggests a remedy for the trouble
involved. A hydraulic system. operational check may be conducted using Figures
6-1 or .6-2. When the trouble has been recognized, the first step in trouble-
shooting is isolating the cause. Hydraulic system troubles are not always trace-
able to one cause. It is possible that a malfunction may be the result of more
than one difficulty within the system. Starting first with the most obvious and
most probable reasons for the trouble, check each possibility in turn and, by
process of elimination, isolate the troubles.

NOTE

If it is found that the hydraulic pump is at fault and re-

quires disassembly, itis recommended that it be over-
hauled by a recommended overhaul shop. However, if
this cannot be achieved, minor repairs of the pump
such as replacement of gaskets and motor components,
and pressure checks with adjustments maybe accom-
plished in accordance with instructions given in para-
graphs 6-6 thru 6-9.

Reissued:1/15/81 HYDRAULIC SYSTEM

2D8
 PIPER CHEROKEE SERVICE MANUAL

6-4. HYDRAULIC PUMP.

6-5. REMOVAL OF HYDRAULIC PUMP. The hydraulic pump with reservoir incor-
porated is located in the aft section of the fuselage. Accessto the pump is through the access
panel in the aft wall of the baggage compartment.
a. Disconnect the pump electrical leads from the pump solenoid relays and the ground
wire from the battery shelf.
b. Disconnect the hydraulic lines from the pump. Cap the line ends to prevent contamina-
tion.
c. Remove the pump by removing the pump attaching bolts.

6-6. DISASSEMBLY OF HYDRAULIC PUMP. (RefertoFigure6-3.) Afterthehydraulic

pump has been removed from the airplane, cap or plug all ports and clean the exterior of the
pump with a dry type solvent to remove accumulated dust or dirt. To disassembleany one of
the three main components of the pump, proceed as follows:
a. The base (16) of the pump may be removed from the case (15) as follows:
1. Cut the safety wire and remove the bolts (17) with washers that secure the base
to the pump case.
2. The shuttle valve within the base should be removed for cleaning purposes only.
To remove the valve, cut safety wire. Remove plug with spring and valve.

NOTE
The shuttle valve and'pump base are matched, lapped parts.
Should it be necessaryto replace, replaceas an assembly only.
b. Pump Motor: The pump motor may be removed from the pump and disassembledas
follows:
1. Remove thru bolts (4) from head (1) of motor. Using a knife cut the seal coating
between the motor head and case.
2. Lift the head up from the case approximately .50 of an inch, this will allow in-
spection of brushes (3) without the.brushes unseating from the commutator. (Refer to Para-
graph 6-7 for brush inspection.) The brush leads are secured to the head assembly.
3. Raise the head assembly (1) off the armature (8) and note the small thrust ball (7)
located between the end of the armature (8) and motor head. Do not misplace this bearing.
4. Draw the armature from the motor frame (9). Note the number of thrust washers
(11) mounted on the drive end of the armature shaft.
5. Remove the motor frame from the pump reservoir (13.)

Reissued:1/15/81 2D9 HYDRAULICSYSTEM

 PIPER CHEROKEE SERVICE MANUAL

2024

2 6

10

11

13

14

15
1. HEAD, MOTOR
2. SPRING,BRUSH
3. BRUSH
18
4. BOLT, THRU
5. "0." RING 5
6. WIRE LEAD
7. BALL THRUST
8. ARMATURE
9. FRAME, MOTOR
10. SLEEVE 16
11 . WASHER, THRUST
12. SCREW, VENT AND FILLER
13. RESERVOIR
14. SEAL
15. CASE, VALVE AND SEAR 17
16. BASE, PUMP
*
17. BOLT
18. SCREWS (8 REQ.)

Figure 6-3. Hydraulic Pump/Reservoir, Exploded View

Reissued: 2D10
1/15/81 2D10 2D10
HYDRAULIC SYSTEM
 PIPER CHEROKEE SERVICE MANUAL

c. The valve body and gear case assembly (15) may be separated from the reservoir
(13) as follows:
1. Remove the screws from the flange of the body and separate the two assemblies.
2. The pump gears and valves should be removed for cleaning purposes only. To
remove cap securing gears, remove cap attaching bolts. There are two valve springs that
should be positively identified with their valve cavities.Otherwise, it will be necessary to
readjust each valve for proper operating pressure.

6-7. CLEANING,INSPECTIONAND REPAIRS OF HYDRAULICPUMP.

a. Discard all old O-rings.
b. Remove cap or plugs and clean all parts with a dry type cleaning solvent and dry
thoroughly.

NOTE
The conditions at repair require cleanliness,carefulness and
proper handling of parts. Ensure that foreign materials are
prevented from entering the system and that no parts are
damaged.

c. Inspect pump components for scratches, scores, chips, cracks and wear.
d. Inspect motor for worn brushes (minimum of.218 brush remains between the braided
wire and commutator end), excess commutator wear and excess bearing wear.

6-8. ASSEMBLYOF HYDRAULICPUMP. (Refer to Figure 6-3.)

a. The pump motor may be assembled and installed on the pump reservoirassembly as
follows:
1. Position the motor frame (9) on the reservoir (13). Note the aligning marks on
the frame and reservoir.
2. Place thrush washers ( 1), of the same amount removed, on the drive end of the
armature (8).
3. Lubricate the entire length of the armature shaft, on the drive end, with a light
grease to protect the O-ring seal from damage and insert the end of the shaft in the reservoir.
4. Saturate the felt oiling pad around the-commutator end bearing with SAE20 oil.
Allow excess oil to drain off before assembling motor.
5. Insert the thrust ball(7) in the bearing of the head assembly(1). To hold the ball
in position, place a small amount of light greaseinside the bearing.

Reissued: 1/15/81
2D11 HYDRAULIC SYSTEM
 PIPER CHEROKEE SERVICE MANUAL

6. Place head assembly on frame and allow brushes to extend over commutator.
Remove the string securing the brushes in the holders. Push head assembly on frame and
insure proper indexing of head and frame assemblies. Secure in place with thru bolts (4).
7. Check freedom of rotation and end play (thrust) of the armature within
the assembly. A minimum of .005 of an inch end play is allowable. Should this
be incorrect, adjust by adding or removing thrust washers (11) on drive end of
armature shaft, as required.
b. The valve body and gear case assembly (15) may be assembled to the res-
ervoir (13) as follows:
1. If removed, place the pump gears in the gear case and install cover.
Install cover attaching bolts and secure.
2. Lubricate the reservoir seal ring(14) with hydraulic fluid (MIL-H-5606)
and place it in the recess provided in the case (15).
3. Position the valve body and gear case assembly (15) with the reservoir
(13). Care should be taken when lining upthe armature drive with the pump gear.
Do not run the motor to do this.
4. Ascertain that the seal ring is properly positioned and install attaching
screws. Tighten the screws so that with the motor connected to a 14-volt source
and with an ammeter in the circuit, the current drawn does not exceed 12-amp-
eres.
c. The base of the pump may be attached to the pump as follows:
1. With the pump in the up-side down position, lubricate "O" ring seals,
and install inthe recesses providedinthe valve body andgear case assembly (15).
2. Install attaching bolts with washers and torque to 70 inch pounds.
3. Safety attaching bolts with MS20995-C32 wire.
d. Conduct motor operational check not to exceed 10 seconds running time.

6-9. TEST AND ADJUSTMENT OF HYDRAULIC PUMP. (Refer to Figure 6-4.)

a. Test Equipment:
1. Hydraulicpump and mounting base.
2. Pressure gauge (0 to 1000 psi).
3. Pressure gauge (0 to 3000 psi).
4. Hoses with fittings to connect between base and gauges.
5. Power supply (14VDC).
6. Ammeter (0 to 100 amps).
7. Fuse or circuit protector (100 amp).
b. Test and Adjustment:
1. Connect a 0 to 1000 psi gauge to the low pressure port (port No. 3) of
the pump base. (The low pressure port, No. 3, is located nearest to the pipe
plug installed in the base.)
2. Connect a 0 to 3000 psi gauge to the high pressure port (port No. 1) of
the pump base. (The high pressure port, No. 1, is located farthest from the pipe
plug installed in the base.)

Reissued: 1/15/81 2D12 HYDRAULIC SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

TABLE VI-II. CHARACTERISTICS, HYDRAULIC PUMP MOTOR

Electrical Characteristics:

Voltage 14DC
Rotation Reversible
Polarity Negative ground
Operating Current 18 amps, max. at 14volts
(both rotations)
Operating Time 5 to 10 seconds with a current load
of 100 amperes at 77° F
Overload Protection 'Thermal circuit breaker
Automatic Reset Time 12 seconds, max.
Location, Automatic Reset Commutator end head of motor

Mechanical Characteristics:

Bearings Absorbent bronze

(Drive end bearing in upper pump
and valve assembly casting.)
Steel ball
(Thrust, between commutator
end head and end of armature
- shaft.)
End Play, Armature .005 inch, min.
(Adjust by selection of thrust
washers on drive end of arm-
ature shaft.)

Reissued: 1/15/81 2D13 HYDRAULIC SYSTEM

 PIPER CHEROKEESERVICE MANUAL

922

GROUND-BLACK
HIGHPRESS
LOWPRESS.

- 14 V. D.
C.

Figure 6-4. Test and Adiustments of Hydraulic Pump

Reissued: 1/15/81 2D14 HYDRAULIC SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

3. Connect the black lead of the pump motor to the negative terminal of
the DC power supply.
- 4. Fill the pump reservoir and bleed all air from the attached lines. (Lines
may be bled by alternately connecting the blue electrical lead and green lead to.
the positive terminal of the power supply until all air is exhausted.)
5. Connect the blue lead to the positive terminal of the power supply. Pump
should operate and the high pressure gauge should indicate between 1600 to 2000
psi. (Should the pressure be incorrect, adjust valve "A", Figure 6-3, in pump
reservoir.)
6. Disconnect the blue lead, and the high pressure reading should not drop
more than 300psi in five minutes. High pressure may not be selected until after
five minutes.
7. Connect the green lead to the positive terminal of the power supply.
Pump should operate in reverse, dropping the high pressure gauge to zero and
the low pressure gauge should indicate between 500 to 800 psi. When the green
lead is disconnected, both pressure gauges should indicate zero psi. (Should the
pressure of 500 to 800 psi be incorrect, adjust valve "B", Figure 6-3, in pump
reservoir.)

NOTE

During test steps 5 thru 7, there should not be any

external leakage.

8. Should it be necessary to check the pump motor, first connect the am-
meter in the electrical circuit with the positive terminal of the meter to the black
lead and the negative terminal of the meter to negative terminal of the DC power
supply.
9. Connect the blue lead to the positive terminal of the power supply. With
the high pressure indication within the 1600 to 2000 psi range on the pressure
gauge, the ammeter should read between 35 to 60 amperes. Disconnect the elec-
trical lead.
10. Connect the green lead to the positive terminal of the power supply.
With the high pressure indication within the 500 to 800 psi range, the ammeter
should read between 15 to 35 amperes.

NOTE

In the event that any of the various tests do not per-

form satisfactorily, the pump assembly should be
overhauled or replaced.

Reissued: 1/15/81 HYDRAULIC SYSTEM

Reissued: 1/15/81
2D15
 PIPER CHEROKEE SERVICE MANUAL

11. Connect the green lead to the

.power supply to drop pressures before
disconnecting the hydraulic lines.
3
6-10. INSTALLATION OF HYDRAULIC
PUMP.
a. Install the rubber shock mounts
through the mounting holes of the pump.
Insert a bushing through the holes of each
shock mount.
b. Position the pump on its mounting
flange. Install mounting bolt with washer
and tighten. (Refer to Figure 6-5.)
c. Connect the hydraulic lines to the
pump.
2 WASHER 5. BUSHING
d. Connect the pump electrical leads. 3. SHOCKMOUNT
6. BUSHING
Green wire to outboard relay, blue wire to 4 PUMP BASE 7. SHELF
inboard relay and black wire to ground on
battery shelf. Figure 6-5. Pump Shock Mounts
e. Check fluid level in pump. Fill per instructions givenin Section II.
f. With the airplane on jacks, operate the pump to purge the hydraulic system of air,
and check for leaks. After operation, recheck fluid level.
6-11. FILLING HYDRAULIC PUMPRESERVOIR. To check fluid level, remove the plug
located on the forward side of the pump and ascertain that fluid is visible up to the bottom
of the filler plug hole. Should fluid be below the hole, add fluid, MIL-H-5606A,through the
filler hole until full. Reinstall the filler plug and tighten.
NOTE
A small vent hole is located under the vent screw head.
Retain 1/64 inch clearance between the screw head and the
small vent hole.
6-12. GEAR BACK-UPEXTENDER ACTUATORASSEMBLY.

6-13. REMOVAL OF GEAR BACK-UPEXTENDER ACTUATOR ASSEMBLY. (Refer to

Figure 6-6.) The back-up extender actuator is located under the rear seat. To reach the
actuator, remove the rear seats.
a. Disconnect the actuator electrical leads at-the quick disconnect terminals.
b. On early installations disconnect the manual override control rod (30) at the
actuator control arm (19) by removing cotter pin, washer, and clevis pin (1). On later
installations the control rod (30) is not connected to the actuator arm (19).
c. Disconnect the pressure (13) and static (11) hoses from the elbows (12) of the
diaphragm housing (10) by releasing clamps and sliding the hoses from their elbows. The
hoses should be tagged for ease of reassembly.
d. Place a shop cloth under the actuator hydraulic valve (25) to absorb fluid, and then
disconnect the hydraulic lines (5) and (25) from the elbows (4) and (27) of the hydraulic
valve (25). Cover the lines to prevent contamination.

Reissued: 1/15/81 HYDRAULIC SYSTEM

2D16
 PIPER CHEROKEESERVICE MANUAL

1722

1. ALIGNINGTOOL
2. LANDINGGEAR OVERRIDESUPPORTBRACKET
3. DIAPHRAGM SUPPORT BRACKET

Refer to Figure 6-11 for tool fabrication

I

Figure 6-6. Checking Aligning Brackets of Gear Back-Up Extender Actuator

e. Remove the machine screws that secure the actuator base to the mounting brackets.
There are two mounting screws at the inboard side of the base and one at the outboard side
of the diaphragm housing. Remove the actuator from the mounting brackets.

6-14. INSTALLATION OF GEAR BACK-UP EXTENDER ACTUATOR ASSEMBLY.

(Refer to Figure 6-7.)
a. Position the gear back-up extender actuator against its mounting brackets and install
attaching machine screws. Do not tighten screws.

NOTE
With the base attached and before installing the attaching
screw through the ring of the diaphragm housing, insure that
the attaching holes in the housing and mounting bracket align
without using force. Should they misalign, it may be
necessary to reform the main fuselage mounting bracket.
To reform the main fuselagemounting bracket, an Aligning
Tool may be used. (Refer to Figure 6-6.) This tool may be
fabricated from dimensions given in Figure 6-11. When
proper alignment has been accomplished, tighten the machine
screws.

Revised: 10/3/83
2D17 HYDRAULIC SYSTEM
 PIPER CHEROKEE SERVICE MANUAL

b. On early installations connect the manual control push rod (30) to the actuator
control arm (19) using clevis pin (1). Place a washer over end of clevispin and secure with
cotter pin.
c. Move the actuator on its mounting brackets to allow the manual control push rod to
have maximum clearance from the left stabilator cable and center in the fairlead on the aft
face of the main spar box. Check system for sufficient travel and freedom of movement of
controls. Tighten actuator attaching screws.

NOTE

Care should be used when attaching the forward hose (13) to

the diaphragm assembly (10) so that no strain is placed on
the teflon bushing (15) and diaphragm shaft (16), thus
causing friction in movement.

d. Connect the hydraulic lines (5) and (26) to the elbows (4) and (27) of the actuator
hydraulic valve (25).

NOTE

A special fitting (27) with a restriction orifice of .063 of an

inch is installed in the side of the hydraulic valve (25). Do
not mistake this for a standard AN fitting.

e. Connect the pressure (13) and static (11) hoses to the elbows (12) of the diaphragm
housing (10). Secure hoses with clamps.
f. Connect the actuator electrical leads terminal to their mating terminals and insulate.
Refer to the electrical schematic for hookup.
g. Check the actuator adjustments as given in paragraph 6-15.
h. Install the rear seat.

6-15. CHECK AND ADJUSTMENT OF GEAR BACK-UP EXTENDER

ACTUATOR. (Refer to Figure 6-7.)
a. If diaphragm failure is suspected note the following:
1. If the landing gear retracts or extends at too high an airspeed or willnot retract
at all unless the back-up extender is placed in the override position, then the diaphragm is
possibly defective.
2. If it is determined that the diaphragm is defective, then remove the back-up
extender per instructions given in Paragraph 6-13 and install, Piper Kit No. 761 138V,
Back-Up Gear Extender Diaphragm Replacement. Instructions for installing the diaphragm
are included in the kit.
3. Following completion of Replacement Kit, reinstall the extender unit in the
aircraft and functionally test and adjust as outlined below and in Paragraph 6-16.

Reissued: 1/15/81
2D18 HYDRAULICSYSTEM
 PIPER CHEROKEE SERVICE MANUAL

b. Adjustment of the gear back-up extender actuator is preset to allow the hydraulic
valve (25) of the actuator to open when the airspeed is reduced below 105 MPH with the
engine power OFF. This adjustment is accomplished by setting the tension of springs (24)
on the actuator with adjustment screw (2).

NOTE

The airspeed at which the hydraulic valve of the actuator

opens was preset at the factory under ideal conditions. There
could be some variations at different altitudes and
atmosphere conditions.
CAUTION
The micro switch (21) on all units, and eccentric bolt (35) on
later units must not be adjusted. These components are set at
the factory under specific conditions, with the use of special
set-up equipment.
NOTE
This adjustment will require two persons, a qualified pilot
and a mechanic to set the actuator adjustment screw (2).
1. Remove the bottom of the rear seat.
2. The pivot screw (20) should be torqued 8 to 10 inch-pounds.
3. Loosen the jam nut (28) of the adjustment screw (2).
4. Ascertain that the electrical switch (21) will actuate with the use of the
emergency gear extension lever.
5. Fly the airplane (refer to Owner's Handbook). Should the spring tension be out
of adjustment very much, it may be necessary to assist gear retraction with the use of the
emergency gear extension lever moved to the up override position.
6. Loosen the adjustment screw (2) by turning counterclockwise until spring (24)
tension is free.

WARNING
While making adjustments, do not lay tools in area under seat
which may interfere with control of the airplane.
7. With the airplane at a safe altitude, slow the airplane to a glide of 110 MPH with
the gear selector handle up and the throttle reduced to power OFF. (Gear warning light and
horn will indicate when power is reduced.) At 110 MPH, slow the airplane at a rate of one
(1) MPH per second until 105 MPHis obtained, hold the airplane at this speed.

HYDRAULICSYSTEM
Reissued: 1/15/81 2D19
INTENTIONALLY LEFT BLANK

2D20
4~L
 PIPERCHEROKEE SERVICEMANUAL

943 943.

I
I
I
I
I
I
I

PA-21R-110 SERIAL NOS 21-30000 TO PA-28R-200 SERIAL NOS 28-1073 AND PA-28R-200SERIALNO'S28-7235001
28-31078 INCL. 24-30483 TO UP. ANDUP.
28-31078 INCL. PA-28R-200 SERIAL NO'S 28-30482.
28-33001 TO 28-7232238 INCL.

DETAIL A
826

826
826
826

EAR.LY LATE PRESENT

DETAIL B

Figure 6-7. Gear Back-up Extender Actuator (Cont.)

Reissued: 1/15/81 2D 22 HYDRAULIC SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

NOTE
On later installations, adjustment of the nut (32) may be
necessary to increase or decrease the spread between the gear
up and gear down actuation speeds. To expand the spread
between these speeds, loosen the nut. Tighten the nut to
bring the airspeeds closer together. Whenever the nut is
adjusted, it may be necessary to readjust the tension on the
springs (24) and to repeat the nut adjustment procedure. If
the eccentric bolt (35) is installed on the unit being adjusted,
CAUTION should be observed so as not to disturb its
position in relation to the rest of the unit.
8. With the glide established, turn the adjustment screw (2) clockwiseuntil the gear
drops. (First indication of gear dropping will be that the yellow intransit light comes ON.)
9. Climb again to a safe altitude and check that the gear drops at the correct
airspeed.
10. Land the airplane and tighten the adjustment screwjam nut (28).
c. - To check adjustment of electrical switch, the followingprocedure may be used:
1. Place the airplane on jacks. (Refer to Jacking, Section II.)
2. Move the mixture control back to idle cut-off and the throttle to full forward to
prevent gear warning horn from sounding during adjustment.
3. Ascertain that the actuator tension springs are properly adjusted according to
Step a.
4. Retract the landing gear hydro electrically by turning the master switch ON,
raising the emergency gear extension lever and moving the gear selector handle to the up
position. The emergency gear extension lever must be retained in the up position to keep
the gear up.
5. Check for proper switch operation by the following procedure:
(a) Turn master switch ON and move gear selector handle to the up position.
Pump should not operate.
(b) Move the emergency gear extension lever to the up override position. Pump
should operate and gear should retract.
(c) With selector lever up, slowly lower emergency gear extension lever to allow
gear to drop to down position. The pump should not operate at any time
during extension.
(d) Turn master switch OFF.
6. Check gear operation in the normal manner with the use of the gear selector
handle. The emergency extension lever must be held in the up override position.
7. Ascertain that gear is down and locked and remove airplane from jacks. Then
flight check the retractable landing gear system. (Refer to Paragraph 6-16.)

Reissued: 1/15/81 2D23 HYDRAULIC SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

6-16. OPERATIONALCHECKOF RETRACTABLELANDINGGEAR SYSTEM.

a. Maximum Gear Extend: Place the gear selector in the down position at 150 MPH
(130 Kts). In approximately 5 to 10 seconds the three green gear lights should be on
indicating that the gear is down and locked.
b. Minimum Gear Retract: Allow approximately 8 seconds for the pressure in the
hydraulic system to normalize between gear extension and retraction. Place the selector
switch in the UP position at 125 MPH (109 Kts). In approximately 5 to 10 seconds all the
gear indicating lights should be out, indicating that the gear is fully retracted.
c. Override Gear Down and Up:
1. Down: Establish a normal glide at approximately 120 MPH (104 Kts), with
power at idle. Slowly move the override lever down, while observing the ammeter to
confirm that the hydraulic pump does not start. The gear should go down and lock. Move
the gear selector switch down. Release the override lever. The gear should remain down.
2. Up: Set maximum climb power. Maintain approximately 70 MPH (61 Kts) for
approximately 15 seconds. Move the gear selector switch to the up position. The gear should
not retract. Pull the override lever up. The gear should retract. Allow the airspeed to
increase to at least 120 MPH (109 Kts). Release the override lever and the gear should
remain up.

INTENTIONALLY LEFT BLANK

Reissued: 1/15/81 2D24 HYDRAULIC SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

d. Gear "Back-Up" Down and Up:

1. Gear Down: Set power at idle. Glide the aircraft at 120 MPH (109 Kts).
Decrease the airspeed at the rate of 1 MPH (1 Kt) per second. The gear should start down
between. 100 and 110 MPH (87 to 96 Kts). Place the gear selector switch down, after the
gear is down and locked.
for 2. Gear Up: Set maximum climb power. Maintain approximately 70 MPH (61 Kts)
for approximately 15 seconds. Move the gear selector up. The gear should stay down and
locked. Increase the airspeed at the rate of 1 MPH (1 Kt) per second. The gear should begin
to retract between 80 and 90 MPH (70 and 78 Kts) at zero density altitude. The speed at
which the gear starts up will increase 1.5 MPH (1.3 Kts) for each 1000' increase of density
altitude.
3. Manual Override Up Latch: With the gear up, the aircraft in normal flight
configuration, select up on the gear override lever. Engagethe up latch. The amber up latch
warning light, below the gear selector switch, should be flashing.Gradually slow the aircraft
below the auto gear extend speed and observe that the gear stays fully retracted. Disengage
the up latch. The flashing amber warning light should stay out.
e. Gear Indicator Lights:
1. The green lights indicate when the correspondinggear is in the down and locked
position. Turn landing light switch on and off- observe ammeter for indication.
2. The amber light indicates when the gear is in an intermediate position, neither
fully up nor down.
3. The Red gear warning light will indicate an unsafe condition. It will indicate
when the throttle setting is less than 14 ± 2 inches of manifold pressure while the gear is not
down and locked. It will also indicate when the gear is down and locked while the selector is
in the UP position, except at full throttle.
f. The Gear WarningHorn: It will sound wheneverthe red gear warning light is on.
g. Micro Switch Check:
1. The forward throttle micro switch is checked by moving the throttle full
forward while the gear is down and the gear selector switch is in the up position. The horn
should stop sounding and the red light should go out. Retard the throttle slightly and the
horn and light should come on.
2. The aft throttle micro switch setting is-checked as follows: with the gear up,
reduce the throttle at a normal rate. The gear warning horn and the red light should come
on at 14 inches of manifold pressure ± 2".

2E1 HYDRAULICSYSTEM
 PIPER CHEROKEE SERVICE MANUAL

1706

4
SYNCRODEVICES
CYLINDER

EARLY

1. SNAP RING
2. END GLAND
3. BACK-UP RING
4. "0" RING
5. "0" RING
6. PISTON
7. BODY, CYLINDER
8. "O" RING
9. SAFETY WIRE

GAR-KENYON
CYLINDER

LATER

Figure 6-8. Nose Gear Actuating Cylinder

Reissued: 1/15/81 2E2 HYDRAULICSYSTEM

 PIPER CHEROKEE SERVICE MANUAL

6-17. NOSE GEAR ACTUATINGCYLINDER.

6-18. REMOVALOF NOSE GEAR ACTUATINGCYLINDER.

a. Place the airplane on jacks. (Refer to Jacking, Section II.)
b. Disconnect the hydraulic lines from the actuating cylinder and cover the open line
ends to prevent contamination.
c. Disconnect the cylinder operating rod end from the downlock hook by removing
attachment nut and bolt.
d. Disconnect the cylinder from its attachment fitting by removingnut and bolt.
e. Remove the cylinder from the wheel well.
6-19. DISASSEMBLYOF NOSE GEAR ACTUATINGCYLINDER. (Refer to Figure 6-8.)
a. With the cylinder removed from the airplane, remove the fitting from the piston rod
(6) end of the cylinder (7). Mark the position of the fitting to facilitate reinstallation.
b. On Syncro Devicesnose gear actuating cylinders remove the snap ring (1) from the
annular slot in the end of the housing. On Gar-Kenyonnosegear actuating cylinder remove
safety wire (9) and unscrew end gland(2).
c. On Syncro Devices Assemblies pull the piston (6) with end gland (2) from the
cylinder housing. On Gar-Kenyon Assembliesremove piston (6) after unscrewingend gland
(2).
6-20. CLEANING, INSPECTION, AND REPAIR OF NOSE GEAR ACTUATING
CYLINDER.
a. Clean the cylinder parts with a suitable dry type solvent and dry thoroughly.
b. Inspect the cylinder assemblyfor the following:
1. Interior walls of the cylinder and exterior surfaces of the piston for scratches
burrs, corrosion, etc.
2. Threaded areas for damage.
3. Rod end fitting and swivel fitting of cylinder for wear and corrosion.
c. Repairs to the cylinder and limited to polishing out small scratches, burrs, etc. and
replacing parts.

Reissued: 1/15/81
2E3 HYDRAULIC SYSTEM
 PIPER CHEROKEE SERVICE MANUAL

BEARING
END

Figure 6-9. End Gland Locking Device

6-21. ASSEMBLY OF NOSE GEAR ACTUATING.CYLINDER. (Refer to Figure 6-8.)

a. Install "O" ring (5) on the exterior of the end gland (2).
b. Install 'O" ring (4) in the interior of the end gland. The Syncro DevicesAssemblies
also includes a ring back-up (3) with the "O" ring (4)
c. Install "O" ring (8) on the body of the piston assembly.
d. Lubricate the areas around the "O" rings with hydraulic fluid, slide the end gland on
the piston rod and the piston into the cylinder housing (7).
e. Secure the end gland in the cylinder by installing the snap ring ( 1)in the annular slot
in the Syncro Devices cylinder. The end gland on the Gar-Kenyon cylinder is secured by
threading gland into cylinder body (7) and securing with safety wire (9).
f. Install restrictor fitting in the piston rod end of the cylinder.
g Check smoothness of operation of the piston.

Reissued:1/15/81 HYDRAULIC SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

1767

N'• \

1 END GLAND
2. BACK-UP RING
3 "O" RING
4. RETAINER RING
5. "O"
RING
6. PISTON
7. CYLINDER BODY
8. "0" RING
9. CLEVIS
10. BEARING

Figure 6-10. Main Gear Actuating Cylinder

Reissued: 1/15/81
Issued: 2E5 HYDRAULIC SYSTEM
 PIPER CHEROKEE SERVICE MANUAL

6-22. INSTALLATIONOF NOSE GEAR ACTUATINGCYLINDER.

a. Attach the cylinder to its attachment fitting using bolt and nut.
b. Attach the operating rod end to the downlock link using bolt. Install nut after
adjustment is completed.
c. Connect the hydraulic lines to the cylinder fittings.
d. Check the adjustment of the cylinder rod end. (Refer to Adjustment of Nose
Landing Gear, Section VIIA.)
e. Operate pump to purge system of air and check fluid level in reservoir.
f. Remove the airplane from jacks.

6-23. MAINGEAR ACTUATINGCYLINDER.

REMOVALOF MAIN GEAR ACTUATINGCYLINDER.

a. Place the airplane on jacks. (Refer to Jacking, Section II.)
b. Disconnect the hydraulic lines from the actuating cylinder and cover the open line
ends to prevent contamination.
c. Disconnect the gear downlock spring from the swivelfitting at the upper end of the
spring.
d. Remove the downlock spring swivel fitting and disconnect the cylinder operating
rod end from the upper side brace retraction fitting by removing the attaching nut. washer
and bolt.
e. Disconnect the cylinder from its attachment by removing nut and bolt.
f. Remove the cylinder from the wheel well.

6-25. DISASSEMBLY OF MAIN GEAR ACTUATING CYLINDER. (Refer to Figure 6-

10.)
a. With the cylinder removed from the airplane, push the piston rod (6) (by hand)
toward the clevis(9) to remove oil from the unit.
b. Put clevis(9) only in a soft jaw vise and clamp against the clevisbearing (10).
c. If no pipe fitting is installed in the port of the end gland (1), install a fitting (1/8 -
27) into the port. This fitting need not be tight as it willbe used for leverageonly.
d. Rotate the gland (with use of fitting) until the end of the gland lock ring (4) shows
in the slot in the cylinder body (7). Reverserotation of the gland to allow the lock ring to
move out of the slot. (Refer to Figure 6-9.) (It may be necessaryto give the ring an assist to
start out of the slot. If so, insert a strong wire pick or other availabletool in the slot to lift
up the end of the ring and then rotate gland.)
e. Pull the piston (6) and end gland from the cylinder.
f. Remove O-ringsas desired.

Reissued: 1/15/81 2E6 HYDRAULIC SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

6-26. CLEANING, INSPECTION AND REPAIR OF MAIN GEAR ACTUATING

CYLINDER.
a. Clean the cylinder parts with, a suitable dry type solvent and dry thoroughly.
b. Inspect the cylinder assemblyfor the following:
1. Interior walls of cylinder and exterior surfaces of piston for scratches, burrs,
corrosion, etc.
2. Threaded areas for damage.
3. End fitting retainer slot for excess wear.
4. Rod end fitting and swivelfitting of cylinder for wear and corrosion.
c. Repairs to the cylinder are limited to polishing out small scratches, burrs, etc. and
replacing parts.

6-27. ASSEMBLY OF MAIN GEAR ACTUATING CYLINDER. (Refer to Figure 6-10.)

a. Install O-ring (5) on the exterior of the end gland (1).
b. Install O-ring (3) and back-up ring (2) in the interior of the end gland.
c. Install O-ring (8) on the body of the piston assembly.
d. Lubricate the areas around the O-ringswith hydraulic fluid, park-o-lubeor vaseline,
slide the end gland on the piston rod and the piston into the cylinder housing (7).
e. Insert the hook end of a new lock ring (4) (P/N 755 997) in the slot in the cylinder
body (7) and slot in the end gland (1). Rotate gland to completely wrap lock ring into
assembly.
f. Align port in end gland and cylinder body.
g. Check smoothness of operation of piston and static pressure test unit to check for
possible cut O-rings.

6-28. INSTALLATIONOF MAIN GEAR ACTUATINGCYLINDER.

a. Attach the cylinder to its attachment fitting in the wheel well using bolt and nut.
b. Attach the operating rod end and downlock spring swivel fitting to the upper side
brace retraction fitting by using bolt, washer and nut. Ascertain swivel fitting is free to
rotate.
c. Connect the downlock spring to the swivel fitting.
d. Check the adjustment of the cylinder rod end. (Refer to Adjustment of Main
Landing Gear, Section VIIA.)
e. Operate pump to purge system of air and check fluid level in reservoir.
f. Remove the airplane from jacks.

6-29. HYDRAULICLINES.

6-30. REMOVAL AND INSTALLATION OF HYDRAULIC LINES. Remove a damaged

hydraulic line by disconnecting the fitting at each end and by disconnecting where secured
by brackets. Refer to Figure 6-2 as an aid in the location of attaching brackets and bends in
the lines. Provide a small container for draining the line. Install a new or repaired line in
reverse. Operate the pump to purge the system of air and check fluid level in reservoir

Reissued: 1/15/81 2E7 HYDRAULIC SYSTEM

INTENTIONALLY LEFT BLANK

2E8
 PIPER CHEROKEE SERVICE MANUAL

TABLE VI-III. HYDRAULIC SYSTEM TROUBLESHOOTING

Trouble Cause Remedy

Landing gear retraction Landing gear actuator Reset circuit breaker

system fails to operate. circuit breaker open. and determine cause
for open circuit
breaker.

Landing gear selector Reset circuit breaker

circuit breaker open. and determine cause
for open circuit
breaker.

Landing gear actuator Check wiring.

circuit wires broken.

Landing gear selector Check wiring.

circuit wires broken.

Safety (squat) switch Readjust switch (Refer

out of adjustment. toAdjustment of Safety
Switch, Section VIIA.)

Squat switch inoper- Replace switch.

ative.

Pressure switch Replace switch.

inoperative.

Pump retraction Replace solenoid.

solenoid inoper-
ative (inboard
solenoid).

Reissued:1/15/81 2E9 HYDRAULIC SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

TABLE VI-Ill. HYDRAULIC SYSTEM TROUBLESHOOTING (cont)

.Trouble Cause
I Remedy

NOTE

If the retracting solenoid of the pump can be heard to

actuate when operating the gear selector switch, it may
be assumed that the gear control circuit is operating
properly and the actuator circuit should be further
checked.

Landing gear retraction Gear selector switch Check ground.

system fails to oper- ground incomplete.
ate (cont.)

Gear selector switch Replace switch.

inoperative.

Hydraulic pump ground Check ground.

incomplete.

Hydraulic pump inop- Replace or overhaul

erative. pump.

Auxiliary extender Replace unit..

switch inoperative.

Hydraulic fluid In Fill reservoir with

reservoir below hydraulic fluid.
operating level.

Battery low or dead. Check condition of

battery.

Reissued: 1/15/81 2E10 HYDRAULIC SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

TABLE VI-III. HYDRAULIC SYSTEM TROUBLESHOOTING(cont)

Trouble Cause Remedy

Landing gear retraction Pressure head air Clearobstruction.

system fails to oper- passage obstructed. *
ate (cont.).

Pressure head hose Reconnect hose.

off.*

Split or hole in dia- Replacediaphragm.

phragm of auxiliary Refer to the latest
revisionof Piper Service
extender. * Letter No. 810.

*Can be checked by
using override.

Landing gear exten- Landing gear actuator Reset circuit breaker

sion system fails to circuit breaker open. and determine cause
operate. for open circuit
breaker.

Landing gear selector Reset circuit breaker

circuit breaker open. and determine cause
for open circuit
breaker.

Landing gear actuator Check wiring.

circuit wires broken.

Landing gear selector Check wiring.

circuit wires broken.

Reissued: 1/15/81
2Ell HYDRAULIC SYSTEM
 PIPER CHEROKEESERVICE MANUAL

TABLE VI-III. HYDRAULIC SYSTEM TROUBLESHOOTING (cont)

Trouble Cause Remedy

Landing gear extension Pump extension sole- Replace solenoid.

system fails to oper- noid inoperative (out-
ate (cont.). board solenoid).

NOTE

If the extension solenoid of the pump can be heard to

actuate when operating the gear selector switch, it may
be assumed that the gear control circuit is operating
properly and the actuator circuit should be further
checked.

Gear selector switch Check ground.

ground incomplete.

Gear selector switch Replace switch.

inoperative.

Hydraulic pump ground Check ground.

incomplete.

Hydraulic pump inop- Replace or overhaul

erative. pump.

Hydraulic fluid in Fill reservoir with

reservoir below hydraulic fluid.
operating level.

Low or dead battery. Check condition of

battery.

Reissued: 1/15/81 2E12 HYDRAULIC SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

TABLE VI-III. HYDRAULIC SYSTEM TROUBLESHOOTING(cont)

Trouble Cause Remedy

Landing gear retraction Hydraulic fluid in res- Fill reservoir with

extremely slow. ervoir below operating hydraulic fluid.
level.

Restriction in hydraulic Isolate and check hy-

lines. draulic lines.

Shuttle valve sticking in Check cause.

pump base.

Pump stops during gear Landing gear actuator Reset circuit breaker
retraction. circuit breaker opens. and determine cause
for overload.

Landing gear selector Reset circuit breaker

circuit breaker opens. and determine cause
for overload.

Pressure switch out of Remove and readjust or

adjustment. replace switch.

Mechanical restriction Place airplane on jacks

or obstruction in hyd- and run retraction
raulic system to allow check. Isolate and
pressure to build up determine cause.
and shut off pump be-
fore gear has retracted.

Shuttle valve sticking in Check cause.

pump base.

Pump stops during gear Landing gear actuator Reset circuit breaker
extension. circuit breaker opens. and determine cause
for overload.

Landing gear selector Reset circuit breaker

circuit breaker opens. and determine cause
for overload.

Reissued: 1/15/81 2E13 HYDRAULIC SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

TABLE VI-III. HYDRAULIC SYSTEM TROUBLESHOOTING(cont)

Trouble Cause Remedy

Pump fails to shut off Pressure switch inop- Replace switch.

though gear has fully erative.
retracted.

Pressure switch out of Replace switch.

adjustment.

Pump retraction sole- Replace solenoid.

noid sticking (inboard
solenoid).

Internal leakage of Check back-up exten-

system. sion unit valve for
internal leakage.

Check gear actuating

cylinders for internal
leakage.

Check for internal dam-

age to hydraulic pump.

External leakage of Check back-up exten-

system. sion unit valve for
external leakage.

Check gear actuating

cylinders for external
leakage.

Reissued: 1/15/81 2E14 HYDRAULIC SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

TABLE VI-III. HYDRAULIC SYSTEM TROUBLESHOOTING(cont)

Trouble Cause Remedy

Pump fails to shut off External leakage of Check for broken or

though gear has fully system .(cont.). damaged hydraulic
retracted (cont.). lines or hoses.

Pump relief valve out Replace pump.

of adjustment.

Pump fails to shut off Pump extension sole- Replace solenoid.

though the gear has noid sticking (out-
fully extended. board solenoid).

Nose gear down limit Adjust switch actuator

switch actuator out (Refer to Adjustment
of adjustment. of Nose Gear Down
Limit Switch, Section
VIIA.)

Nose gear down limit Replace switch.

switch failed.

Main gear down limit Adjust switch (Refer to

switch out of adjust- Adjustment of Main
ment. Gear Down Limit
Switch, Section VIIA.)

Main gear down limit Replace switch.

switch failed.

HYDRAULIC SYSTEM
Reissued: 1/15/81 2E15
 PIPER CHEROKEE SERVICE MANUAL

TABLE VI-III. HYDRAULIC SYSTEM TROUBLESHOOTING (cont)

Trouble Cause Remedy

NOTE

The out of adjustment or failed switch may be deter-

mined by noting which down light is not lit.

Pump running inter- Leakage of high pres- Remove pump and re-
mittently after gear sure check valve. place check valve.
has retracted.

Internal leakage of Check auxiliary retrac-

system. tion unit valve for
internal leakage.

Check gear actuating

cylinders for internal
leakage.

External leakage of Check back-up exten-

system. sion unit valve for
external leakage.

Check gear actuating

cylinders for external
leakage.

Check for broken or

damaged hydraulic
lines.

Gear stops part way Pump high pressure Replace pump.

up, but pump con- relief valve out of
tinues to run. adjustment.

Reissued: 1/15/81
2E16 HYDRAULIC SYSTEM
 PIPER CHEROKEE SERVICE MANUAL

TABLE VI-III. HYDRAULIC SYSTEM TROUBLESHOOTING(cont)

Trouble Cause Remedy

Gear stops part way up, Internal leakage of Check back-up exten-
but pump continues to system. sion unit valve for
run (cont.). internal leakage.

Check gear actuating

cylinders for internal
leakage.

Check for broken or

damaged hydraulic
lines.

Hydraulic fluid in Fill reservoir with

reservoir below hydraulic fluid.
operating level.

All gears fail to Back-up extension unit Check unit and valve
free fall. valve fails to open. and replace.

Gear free falls at Back-up extender unit Check extender unit

air speeds above hydraulic valve fails spring adjustment.
that required. to close.

Check hydraulic valve

for sticking open.

Check extender unit

diaphragm for damage.

Check for restriction in

air pressure and static
lines.

Reissued: 1/15/81
2E17 HYDRAULIC SYSTEM
 PIPER CHEROKEE SERVICE MANUAL

TABLE VI-III. HYDRAULIC SYSTEM TROUBLESHOOTING(cont)

Trouble Cause Remedy

Landing gear fails to Manual control rod Form the rod to allow
operate at required between over-ride clearance through full
speeds. (Gear up at lever (manual ex- fore and aft travel.
85 mph , gear down truder) and rear
at 105 mph.) seat rubbing or
chafing on spar web
where rod passes
beneath the spar.

Friction or tight Clean, free and lub-

connection at any of ricate all pivot points.
the attachment points
(pivot points) of the
over-ride lever or
actuator arm.

Binding of diaphragm Clean all moving parts.

shaft caused by build
up of sand or dirt.

Landing gear will not Restriction in pres- Disconnect hoses at

retract after selecting sure head of gear back-up extender and
up at an airspeed above back-up extender clean out hoses and
actuator speed. (Also, actuator. head.
upon trying to over-ride
it is found that only with
a steady pressure can
the over-ride be activ-
ated. After gear does
retract and the over-
ride lever (manual
extruder) is relaxed
(approximately 11 to
15 seconds.) the gear
will fall free.

Reissued:1/15/81 2E18 HYDRAULIC SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

TABLE VI-III. HYDRAULIC SYSTEM TROUBLESHOOTING(cont)

Trouble Cause Remedy

With gear selector down Shorted gear up Replace solenoid.

and three green lights solenoid.
on, in transit light
comes on or inter-
mittently on.

With gear selector down Shorted gear up Replace solenoid.

and three green lights solenoid.
on, pump motor circuit
breaker opens.

With in transit light on, Shorted gear down Replace solenoid.

pump operates on and solenoid.
off.

With in transit light on, Shorted gear down Replace solenoid.

pump motor circuit solenoid.
breaker opens.

Reissued: 1/15/81 2E19 HYDRAULIC SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

A659

ALLEN SET-SCREW .25

MATERIAL: Steel

Figure 6-11. Gear Back-up Extender Actuator Aligning Tool

Reissued: 1/15/81 HYDRAULIC SYSTEM

2E20
INTENTIONALLY LEFT BLANK

2E21
 SECTION VII
LANDING GEAR AND BRAKE SYSTEM
(PA-28-140, -150, -160, -180, -235)

Paragraph Aerofiche
Grid No.

7-1. Introduction .................................................. 2E24

7-2. Description .................................................. 2E24
7-3. Troubleshooting ............... 2E24
7-4. Landing Gear System ......................................... 2F1
7-5. Nose Landing Gear ........................................... 2F1
7-6. Disassembly of Nose Gear Oleo ....................... 2FI
7-7. Cleaning. Inspection and Repair of Nose Gear Oleo ...... 2F3
7-8. Nose Gear Oil Orifice Retainer Ring Installation ......... 2F3
7-9. Assembly of Nose Gear Oleo .......................... 2F4
7-10. Removal of Nose Landing Gear ....................... 2F5
7-11. Cleaning, Inspection and Repair of Nose
Landing Gear ........................ 2F5
7-12. Installation of Nose Landing Gear ..................... 2F5
7-13. Alignment of Nose Gear .............................. 2F7
7-14. Main Landing Gear .......................................... 2F10
7-15. Disassembly of Main Gear Oleo ....................... 2F10
7-16. Cleaning, Inspection and Repair of Main
Gear Oleo ...................................... 2F11
7-17. Assembly of Main Gear Oleo ......................... 2F11
7-18. Removal of Main Landing Gear ....................... 2F18
7-19. Cleaning, Inspection and Repair of Main
Landing Gear ........................ 2F18
7-20. Installation of Main Landing Gear ..................... 2F20
7-21. Wheels ...................................................... 2F20
7-22. Removal and Disassembly of Nose Wheel ............... 2F20
7-23. Inspection of Nose Wheel Assembly .................... 2F22
7-24. Assembly and Installation of Nose Wheel ............... 2F22
7-25. Removal and Disassembly of Main Wheel .............. 2F22
7-26. Inspection of Main Wheel Assembly ................... 2F23
7-27. Assembly and Installation of Main Wheel ............... 2F24
7-28. Brake System .............................. ............. 2F24
7-29. Wheel Brake Assembly ........................................ 2F24
7-30. Brake Adjustment and Lining Tolerance ................ 2F24
7-31. Removal and Disassembly of Wheel Brake
Assembly ...................... ................ 2G1

Reissued: 1/15/81

2E22
 Paragraph Aerofiche
Grid No.
7-32. Cleaning, Inspection and Repair of Wheel
Brake Assemblies ................................ 2G4
7-33. Assembly and Installation of Wheel Brake
Assembly....................................... 2G4
7-34. Brake Master Cylinder ........................................ 2G4
7-35. Removal of Brake Master Cylinder .................... 2G4
7-36. Disassembly of Brake Master Cylinder ................. 2G6
7-37. Cleaning. Inspection and Repair of Brake
Master Cylinder................................. 2G7
7-38. Assembly of Brake Master Cylinder ................... 2G7
7-39. Installation of Brake Master Cylinder
(Hand Brake) ................................... 2G10
7-40. Parking Valve................................................ 2G11
7-41. Removal of Parking Valve ............................ 2G 11
7-42. Disassembly of Parking Valve ......................... 2G11
7-43. Cleaning. Inspection and Repair of Parking
Valve .......................................... 2G11
7-44. Assembly of Parking Valve ........................... 2G11
7-45. Installation of Parking Valve.......................... 2G13
7-46. Brake Cylinder (Toe Brake).............................. ..... 2G13
7-47. Removal of Brake Cylinder ........................... 2G13
7-48. Disassembly of Brake Cylinder ........................ 2G13
7-49. Cleaning, Inspection and Repair of Brake
Cylinder........................................ 2G14
7-50. Assembly of Brake Cylinder........................... 2G16
7-51. Installation of Brake Cylinder ......................... 2G17
7-52. Brake Bleeding Procedure ..................................... 2G17
7-53. Brake Bleeding Procedure (Gravity) .................... 2G17
7-54. Brake Bleeding Procedure (Pressure) ................... 2G17
7-55. Brake System Leak Check ............................ 2G19
7-56. Bleeding of the Brakes After a Unit has
Been Changed................................... 2G19

Reissued: 1/15/81 2E23

 PIPER CHEROKEE SERVICE MANUAL

SECTIONVII

LANDING GEAR AND BRAKE SYSTEM

PA-28-140, -150, -160, -180 and -235

7-1. INTRODUCTION. In this section are instructions for the removal, disassembly,
inspection, overhaul and installation of the various landing gear and brake system
components used on the alignment of the nose gear, and the repair and serviceof the brake
system.
7-2. DESCRIPTION. The landing gear incorporated on the PA-28-140,-150, -160,-180 and
-235 airplanes is a fixed tricycle type, fitted with three 600 x 6 wheels. The landing gear
struts are of the air-oil type. The nose gear, steerable through a wide arc, enables a short
turning radius in each direction. (For turning arc of each airplane by serialnumber, refer to
Table VII-I.) To aid in nose wheel and rudder centering and to provide rudder trim there is a
spring device attached to the rudder pedal torque tube assembly. A shimmy dampener is
also incorporated in the nose wheel steering mechanism. Bungee springs are also
incorporated on the push rods of later models. (1974 models and up) These springs make
lighter and smoother ground steering possible.
The two main wheels are equipped with a singledisc hydraulic brake assemblywhich is
actuated by a hand lever connected to a cylinder located below and behind the center of the
instrument panel, or by individual cylinders attached to each rudder pedal. The hand lever
also doubles as a parking brake and may be operated by pulling back on the handle and
pulling out the parking brake tee handle, holding it until the hand lever is released or
pushing in on the button at the side of the handle. To disengage the parking brake, either
push in on the tee handle or pull back on the hand brake handle. A brake fluid reservoir is
installed on the left forward face of the engine firewall.
7-3. TROUBLESHOOTING.Troubles peculiar to the landing gear are listed in Table VII-II,
at the back of this section, along with their probable causes and suggestedremedies. When
troubleshooting the landing gear system, it may be found that it is necessary to place the
airplane on jacks. If so, refer to Jacking, Section II.

2E24 LANDING GEAR AND BRAKE SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

7-4. LANDING GEAR SYSTEM.

7-5. NOSE LANDINGGEAR.

7-6. DISASSEMBLY OF NOSE GEAR OLEO. (Refer to Figure 7-1.) The nose
gear oleo strut assembly maybe removed and disassembled from the strut hous-
ing with the gear removed from or installed on the airplane.
a. Remove the lower engine cowling by the following procedure:
1. Release the cowl fasteners, two on each side and remove the top cowl.
2. Disconnect the electrical lead to the landing light at the quick disconnect
at the inside of the bottom cowl.
3. Remove the bottom cowl attaching screws from around its aft end and
remove cowl.
b. Place airplane on jacks. (Refer to Jacking, Section II.)
c. Place a drip pan under the nose gear to catch spillage.
d. To remove air from the strut, depress the air valve core pin found at the
top of the strut assembly. After the pressure in the strut chamber has dimin-
ished, remove the valve core pin, and attach a small hose to the air valve, and
drain the fluid by slowly compressing the piston tube. If it is desirable to ex-
tract more fluid from the strut chamber, remove the filler plug, insert the si-
phon hose and drain fluid from the upper area of the housing.
e. To remove the strut assembly from the strut housing (4), cut the safety
wire at the top of the housing that secures the steering horn attaching bolt to the
tube retainer nut. Then remove the steering horn attaching bolt and the flat head
pin, thus relieving the steering horn from the top of the strut housing.
f. Loosen the strut assembly retainer nut (1) that secures the strut assembly
in the strut housing. At the same time, slide the strut assembly out through the
bottom of the strut housing. Remove the nut (1) and washer (2) from the top of
the strut housing after the assembly is removed.

NOTE

The strut assembly may fit tight inside of the housing.

It may be necessary to tap the top of the fork with a
plastic mallet.

g. If desired, remove the top and bottom bearing (3 and 5) from the strut
housing. The bearings are compressed slightly into place, and light tapping may
be needed to free them.

Reissued: 1/15/81 2F1 LANDINGGEAR AND BRAKE SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

1768

18

NUT, RETAINER
2. WASHER
3. BEARING, TOP
4. STRUT HOUSING
5. BEARING, BOTTOM
6. CAP, VALVE
7. PLUG, FILLER
8. TUBE METERING
9. CYLINDER
10. RING, RETAINER
11. SNAP RING
12. BEARING
13. "0" RING, PACKING
14. "0" RING OR QUAD RING
15. WASHER, CACK-UP
RING ,RETAINER 17. WIPER STRIP
17. TUBE, PISTON
1973 PA-28-180 AND PA-28-235 SERIAL NOS. AND UP 18. "0" RING
19. PLUG, PISTON TUBE

Figure 7-1. Nose Gear Oleo Strut Assembly

Reissued: 1/15/81 2F2 LANDING GEAR AND BRAKE SYSTEM

 PIPER CHEROKEE SERVICE MANUAL-

h. To remove the piston tube and fork assembly (17) from the cylinder (9), proceed as
follows:
1. Separate the upper and lower torque links by removing the connecting nut,
washer and bolt.
2. Compress the piston tube and fork assembly slightly and remove the retainer
ring (10) from the annular slot in the bottom of the cylinder tube. Then remove piston tube
and fork assembly by sliding out from the bottom of the cylinder tube.
i. To remove the bearing assembly from the piston tube, release the snap ring (11)
from the top of the piston tube and slide bearing assemblyoff the end.
1. If desired, carefully remove the wiper strip (16), back-up washer (15) and quad
ring or "O" ring (14) from the inside of the bearing sleeve,and also the "0" ring gasket (13)
from the outside of the bearing sleeve.
j. To remove the piston tube plug (19) with "O" ring (18) located in the lower end of
the tube, the following procedure may be used:
1. Remove the nose wheel from the fork as described in paragraph 7-22.
2. Loosen and remove the bolt, washer and nut that extends through the piston
tube and block assembly.
3. Push the plug through the top of the piston tube by use of a rod inserted
through the bottom of the tube.

7-7. CLEANING,INSPECTIONAND REPAIROF NOSE GEAR OLEO.

a. Clean all parts with a suitable dry type cleaningsolvent.
b. Inspect the landing gear oleo assemblycomponent for the following:
1. Cylinder tube assemblyfor corrosion, scratches, nicks and excessivewear.
2. Lock rings for cracks, burrs, wear.
3. Fork assemblyfor corrosion, scratches, nicks, and misalignment.
4. Link assembly for elongated holes, cracks, corrosion, scratches, nicks and
straightness.
5. General condition of air valve.
c. Repair of the oleo is limited to smoothing out minor scratches, nicks and dents and
replacement of parts.

7-8. NOSE GEAR OIL ORIFICE RETAINER RING INSTALLATION.(Refer to Figures

7-1 and 7-22.)
a. With the piston tube (17) and fork removed from the cylinder (9), ascertain that all
traces of the old retainer ring (10) are removed from the meteringtube (8).
b. A tool can be fabricated to simplify the installation of the new retainer ring. (Refer
to Figure 7-22.)
c. With the use of the fabricated tool, position the new retainer ring on the end of the
tool with the locating stud.
d. Insert the tool into the cylinder (9), with the centering stud positioned into the hole
in the base of the metering tube (8).
e. Hold the tool tightly against the metering tube and slide the sleeve of the tool
towards the metering tube. This will move the new retainer ring (10) over the end of the
metering tube and position itself into the groove of the metering tube (8).

Reissued: 1/15/81 2F3 LANDINGGEAR AND BRAKE SYSTEM

 PIPER CHEROKEESERVICE MANUAL

7-9. ASSEMBLY OF NOSE GEAR OLEO. (Refer to Figure 7-1.)

a. Ascertain that all parts are cleaned and inspected.
b. To install the piston tube plug, proceed as follows:
1. Lubricate thetube plug(19) and "O" ring(18) with hydraulic fluid (MIL-
H-5606) and install the "O" ring on the plug.
2. Lubricate the inside wall of the piston tube, and insert the plug into the
top of the tube, pushing it to the fork end.
3. Align the bolt holes of the fork, tube and plug; install the bolt, washer
and nut.
c. Carefully install in the bearing sleeve the quad ring (14), back-up washer
(15) and the wiper strip (16). Slide the "O" ring (13) in place on the outside of
the sleeve.
d. Lubricate the bearing assembly and carefully install it on the piston tube
(17).
e. Position the snap ring (11) on the upper end of the piston tube.
f. Insert the piston tube with bearing assembly in the cylinder tube (9). Secure
it with the retainer ring (10) in the annular slot at the bottom of the tube.
g. Connect the torque links on the tube and fork securing them with a bolt,
washer and nut. Tighten the nuts only tight enough to retard side play, but still
allowing the links to rotate freely.
h. Ascertain that the upper and lower bearings (3 and 5) are installed in the
strut housing. Bearings are a press fit with the grooves in the inner and outer
races in the up position.
i. Position washer (2) and strut assembly retainer nut (1) on top of the strut
housing. Insert the strut assembly up through the washer until it contacts the nut.
Tighten the nut to a snug fit.
j. To install the steering horn assembly, insert the flat head pin through the
side of the horn and top of the strut assembly. When it protrudes through the
other side of the steering horn, install the washer and secure with a cotter pin.
k. Install the steering horn attaching bolt through the top of the horn into the
strut assembly. Do not tighten bolt at this time. If a space appears between the
steering horn plate and the top of the strut assembly, it will then be necessary
to install spacer washer(s), (AN960-416L), between the horn and strut. Then
tighten the bolt and safety the bolt to the strut assembly retainer nut (1) with
MS20995C40 wire.
1. Compress and extend the strut several times to ascertain that the strut will
operate freely. The weight of the gear wheel and fork should allow the strut to
extend.
m. Service the oleo strut with fluid and air. (Refer to Oleo Struts, Section II.)
n. Check the gear for alignment. (Refer to Alignment of Nose Landing Gear,
Paragraph 7-12.)

Reissued: 1/15/81
2F4 LANDING GEAR AND BRAKE SYSTEM
 PIPER CHEROKEE SERVICE MANUAL

7-10. REMOVAL OF NOSE LANDING GEAR. (Refer to Figure 7-2.)

a. Remove the engine cowling by the following procedure:
1. Release the fasteners, two on each side and two at the top of the cowl.
2. Lift the aft end of the top cowl and then slide it forward to release the
two stud type front fasteners. Remove the top cowl.
3. Disconnect the electrical lead to the landinglightat the quick disconnect
at the right inside of the bottom cowl.
4. Remove the bottom cowl attaching screws from around its aft end and
remove the cowl.
b. Remove the propeller. (Refer to Removal of Propeller, Section VIII.)
c. Place the airplane on jacks. (Refer to Jacking, Section II.)
d. Remove the engine. (Refer to Removal of Engine, Section VIII.)
e. Disconnect the two steering rods (lland4) at the nose gear horn assembly
(3) by removing the cotter pins, nuts, washers and bolts.
f. Disconnect the oil lines, vacuum lines, fuel lines, hoses and wires which
are secured to the mount with clamps and Koroseal lacing. Mark all wires and
lines for identification and reinstallation.
g. Remove the nose gear and engine mount by removing the five bolts (16)
which attach the mount to the firewall.

7-11. CLEANING, INSPECTION AND REPAIR OF NOSE LANDING GEAR.

a. Clean all parts with a suitable dry type cleaning solvent.
b. Inspect the nose gear assembly for the following:
1. Bolts, bearings and bushings for excess wear, corrosion and damage.
2. Strut housing and torque links for cracks, bends or misalignment.
c. The shimmy dampener requires no service other than routine inspection.
In case of damage or malfunction, the dampener should be replaced rather than
repaired.
d. Repair to the landing gear is limited to reconditioning of parts, such as
replacing bearings and bushings, smoothing out minor nicks and scratches, re-
painting of areas where paint has chipped or peeled and replacement of parts.

7-12. INSTALLATION OF NOSE LANDING GEAR. (Refer to Figure 7-2.)

a. Install the nose gear and engine mount assembly to the firewall with bolts,
washers and nuts. Torque nuts as specified in Torque Requirements, Section II
of this manual.
b. Attach the two steering rods (11 and4) to the nose gear steering horn (3)
with bolts, washers and nuts (1).

Reissued: 1/15/81
2F5 LANDING GEAR AND BRAKESYSTEM
 PIPER CHEROKEE SERVICE MANUAL

1829

16

BUNGEE ASSEMBLY (1974 MODELS AND UP)

983

18

19

20

1. BOLT, WASHER & NUT

2. CAP, SCREW
3. HORN ASSY.
4. RIGHT STEERING CONTROL ROD
21 5. ROD END BEARING
6. AIR VALVE CAP
7. AIR VALVE
8. BOLT
9. PIN, WASHER & COTTER PIN
22 10. CAP SCREW
11. LEFT STEERING CONTROL ROD
12. SHIMMY DAMPENER
13. BOLT, WASHER & NUT
14. BOLT, WASHER & NUT
23 19. NOSE GEAR STRUT ASSY.
18. BOLT, WASHER & NUT
17. LINK ASSY.
18. BUMPER BLOCK
19 . PISTON TUBE ASSY.
20. TOW BAR BRACKET
21. FORK ASSY.
22. TIRE
23. AXLE ROD ASSY.

Figure 7-2. Nose Gear Installation

Reissued: 1/15/81 2F6 LANDING GEAR AND BRAKE SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

c. If removed, connect the shimmy dampener(12)to the steering horn with bolts,
washers and nuts(l4).A spacer bushing and cotter pin are required at the body attachment
point.
d. Install the engine and connect controls. (Refer to Installation of Engine, Section
VIII.)
e. Attach hoses, wires and cables to engine mount tubing, securingwith clamps and
Koroseal lacing where required.
f. Check the alignment of the nose gear per paragraph 7-12.
g. Remove the airplane from the jacks.
h. Install the propeller, (Refer to Installation of Propeller, Section VIII.) and engine
cowling.

7-13. ALIGNMENT OF NOSE GEAR. On 1974 models the nose wheel steering has been
modified by the addition of the bungee steering system. This new system will require some
different adjustment procedures which are included with the regular instructions.
a. Place the airplane on a smooth level floor that will accomodate the striking of a
chalk line.
b. Place the airplane on jacks. (Refer to Jacking, Section II.)
c. Level the airplane laterally and longitudinally. (Refer to Leveling,Section II.)
d. From the center of the tail skid, extend a plumb bob and mark the contact point on
the floor.
e. Extend a chalk line from the mark on the floor below the tail skid to a point
approximately three feet forward of the nose wheel.Allow the line to pass under the wheel
at the center line of the tire. Snap the chalk line.
f. Ascertain that the rudder is properly rigged and the rudder cable tension is correct.
(Refer to Riggingof Rudder, Section V.)
g. Clamp the rudder pedals to align in a lateral position. (Refer to Figure 7-3.)
h. Ascertain that the nose wheel is in alignment with the longitudinal axis of the
airplane or chalk line.
i. On airplanes prior to 1974 models adjust the rod end bearings of each steering
control rod to align the nose wheel with the chalk line and bring the rudder pedals into their
neutral angle fore and aft. (Refer to Table VII-I for neutral angle.) Do not attempt to make
the adjustments by means of one rod end, divide the adjustment between rod ends. Place a
bubble protractor against a pedal steering tube to check this angle.
j. On 1974 models install the steering bungee assembliesbetween the steering horn and
rudder pedals without any load on the bungees. Adjust the rod ends to obtain this no load
condition, and connect the bungees to the steering horn.
NOTE

Check that the rod ends have sufficient thread engagement,

by use of the check holes in the rods or a minimum of
three-eights of an inch thread engagement.

k. On 1974 models ascertain that the rudder pedal stops are adjusted in accordance
with instructions givenin Riggingand Adjustment of Rudder, Section V.

Reissued: 1/15/81 2F7 LANDING GEAR AND BRAKE SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

1641

SeeTable VII-1 For Rudder Pedal Neutral Angle

Figure 7-3. Clamping Rudder Figure 7-4. Rudder Pedals

Pedals in Neutral Position at Neutral Angle

L To check the nose gear steering for its maximum right and left travel, mark on each
side of the nose wheel an angle line from the center line and wheel pivot point. (Refer to
Table VII-I for nose wheel turning angle of the particular model being serviced.) Turn the
wheel to its maximum travel in both directions to check for allowabletravel. Should travel
be exceeded in one direction and not enough in the other direction, check for possible
damage to the gear fork or torque links,
m. When the wheel is turned to its extreme right or left travel, there should be .06 to
.12 of an inch clearance between the nose wheel steering stops. This is due to the stops on
the rudder making contact ahead of the nose gear stops. Prior to checking and/or making
this adjustment, ascertain that the rudder travel is correct per Riggingand Adjustment of
Rudder, Section V.
n. Adjust the shimmy dampener by turning the nose wheel against its stops and
adjusting the rod end of the dampener for adequate travel to both directions.
o. Remove the aircraft from jacks.

NOTE
When the nose wheel fairing is removed, centering springs
should be installed for proper nose wheel centering. Refer to
the latest revision of Piper Service Bulletin No. 291 for more
information.

Reissued: 1/15/81 2F8 LANDING GEAR AND BRAKE SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

TABLEVII-I. NOSEGEAR ALIGNMENTTOLERANCES

Rudder Pedal Neutral Angle (Aft of Vertical)

8 degrees, 15 minutes 1. PA-28-140,

Serial Nos. 28-20002 to 28-20520 incl.
2. PA-28-150,-160,-180,
SerialNos. 28-1 to 28-1760 incl.
3. PA-28-235,
Serial Nos. 28-10000 to 28-10486 incl.

11 degrees 1. PA-28-140,
Serial Nos. 28-20521to 28-7325684
2. PA-28-150. -160, -180,
Serial Nos. 28-1760to 28-7305611
3. PA-28-235.
Serial Nos. 28-10487to 28-7310187
4. PA-28R-200. Models Previous to 1974
5. PA-28R-180, Serial Nos. 28R-713001and up
14 degrees +3 All 1974 Models and up
.-

Nose Wheel Travel

30 degreesleft, 1. PA-28-140,
30 degreesright + 1° SerialNos. 28-20002 to 28-21845 incl;
- 1° 28-21847 to 28-21929 incl; 28-21931 to
28-21934 incl.
2. PA-28-150,-160,-180,
SerialNos. 28-1 to 28-3377 incl.
3. All PA-28R-200 Models
4. All 1974 Modelsand up

22 degreesleft, 1. PA-28-140,
22 degreesright SerialNos. 28-21846, 28-21930, 28-21935
to 28-7325684
2. PA-28-150,-160,-180,
Serial Nos. 28-3378 to 28-7305611
3. PA-28-235Modelsup to SerialNo.
28-7310187
.

Revised: 10'3;'83 2F9 LANDING GEAR AND BRAKE SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

7-14. MAIN LANDINGGEAR.

7-15. DISASSEMBLYOF MAIN GEAR OLEO. (Refer to Figure 7-5 or 7-6.) The main gear
axle (19) and piston tube assembly(18) may be removed from the cylinder housing (9) with
the gear removed from or installed on the airplane. On some airplanes the metering
components of the gear that are located in the top of the housing may be removed, but only
with the gear removed from the airplane. (Refer to Paragraph 7-17 for Removal of Gear.)
a. Place the airplane on jacks. (Refer to Jacking, Section II.)
b. Place a drip pan under the main gear to catch spillage.
c. The gear axle and piston tube assembly may be removed by the following
procedure:
1. Remove the air from the oleo chamber by depressing the air valvecore pin found
in the inspection hole on top of the wing. After the pressure in the oleo chamber has
diminished, remove the valve core pin, attach a small hose to the air valve, and drain the
fluid by slowly compressing the piston tube. If it is desirable to extract more fluid from the
chamber, remove the filler plug, insert a siphon hose and drain fluid from the upper area of
the housing.
2. Disconnect the flexible brake line at the elbow on the brake assembly.
3. Disconnect the torque link assembly by removing any one of the three cotter
pins, nuts, washers and bolts. Note arrangement of the components for reinstallation.
Carefully slide the piston tube from the cylinder housing.
4. The scraper ring (15) located inside the lower end of the cylinder housing may
be removed by first removing the retainer ring (17), spacer ring (16) and then the scraper
ring.
5. The "O" ring seal (14) located just before the scraper ring may be removed by
using a curved wire or spoon shaped tool and inserting it under the ring.
d. The cylinder head, and in some airplanes the orifice assembly, may be removed by
the following procedure:
1. Cut safety wire and remove the bolts that secure the cylinder head (4) in the top
of the housing. Remove the assemblyfrom the housing.
2. If "O" ring was used with cylin4er head (4), remove and discard. If "0" ring was
not used with cylinder head (4), remove all traces of sealant from around the cylinder head
(4) and top of housing.
3. If, when removed, the cylinder head is equipped with a metering tube (6), this
indicates that the orifice assembly (8) may be removed. (Those assemblies without a
metering tube, the metering deviceis cast into the housing.)
4. The orifice assembly may be removed from within the housing by rotating it
counterclockwise out of the housing with the use of a .50 x .125 stud type spanner wrench
(Refer to Figure 7-21). Do not remove orifice unless it necessitates replacement.

Reissued: 1/15/81 2FI0 LANDINGGEAR ANDBRAKE SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

7-16. CLEANING,INSPECTIONAND REPAIR OF MAINGEAR OLEO.

a. Clean all parts with a suitable dry type cleaningsolvent.
b. Inspect the landing gear oleo components for the following:
1. Bearing surfaces of housing for excess wear, corrosion, scratches and overall
damage.
2. Retaining ing for cracks,-burrs, etc.
3. Cylinder tube for corrosion, scratches, nicks, excessivewear and misalignment.
4. Air valve for operation and general condition.
5. Orifice plate for hole restriction.
c. Repair of the oleo is limited to smoothing out minor scratches,nicks and dents, and
replacement of parts.

7-17. ASSEMBLYOF MAINGEAR OLEO. (Refer to Figure 7-5 or 7-6.)

a. Install the orifice assembly,if removed, by the followingprocedure:
1. Lubricate with hydraulic fluid (MIL-H-5606)and install an "O" ring (7) in the
annular slot in the metering orifice (8).
2. Insert the orifice through the opening in the top of the gearhousing and turn it
into the threaded hole web. Tighten the orifice with the use of a stud type spanner wrench.
3. Lubricate and install an "O" ring or apply a thin layer of Permatex
Forma-GasketNo. 6 Sealant, directly underneath the flange of the cylinder head (4).
NOTE
/({~~ ~~On models without the groove for the "O" ring, apply
Permatex Forma-Gasket#6 Sealant beneath the flangeof the
cylinder head (4).

4. Insert The tube of the metering assembly through the openingin the top of the
housing and into the orifice. Use caution not to cut or dislodge the "0" ring slot in the
orifice.
5. Secure the metering tube assembly with bolts and safety with MS20995-C32
wire..
b. Assemble the-components of the piston tube (18) on the tube by placing, in order,
the retainer ring (17), spacer ring (16) and scraper ring (15). Insert an "O" ring (14) into the
annular slot in the bottom of the housing.
c. Lubricate the wall of the piston and carefully insert it into the housing being careful
not to damage or dislocate the "0O"ring in the housing.
d. Ascertain that the bushings are installed in the upper and lower torque links and
then install links. At cable end of each link, install with the use of brake line bracket,
bearing washers, bolt, washer, nut and cotter pin. Do not over tighten causing binding or
damage to the link. At the connection point of the upper and lower links, attach with the
. use of brake line brackets, spacer washers, grease bolt, washers, nut and cotter pins. Install
washers (AN960-816L) under the head of the bolt to allow a firm sliding fit between the
two links.
e. Slide the scraper and spacer rings into place and securewith the retainer ring in the
annular slot in the bottom of the housing.

(
Reissued:1/15/81 2Fll LANDINGGEARAND BRAKESYSTEM
INTENTIONALLY LEFT BLANK

2F12
 PIPER CHEROKEE SERVICE MANUAL

1898

1.

2
1. CAP, VALVE
2. PLUG, FILLER
3
3. "O" RING 4
4. HEAD CYLINDER
5. DELETED
6. DELETE
7. DELETE
8. ORIFICE ASSEMBLY
9. STRUT HOUSING
10. WASHER
11. NUT
12. WASHER
13. TORQUE LINKS
14. "O" RING OR QUAD RING
15. RING, SCRAPER
16. RING, SPACER
17. RING, RETAINER
18. TUBE, PISTON
19. AXLE STUB
20. SPACER
21. SPACER 9
22. NUT, WHEEL RETAINER
23. PIN, CLEVIS

10

11
12

13

NOTE: PART NO. 78033-0 TORQUE LINK ASSEMBLY IS A MATCHED

SET AND THEREFORE MUST NOT BE INTERCHANGED WITH
6569 -0 TORQUE LINK ASSEMBLY.

Torque links can be installed individually on Serial Nos.

28-140 28-7225584 & up
28-180 28-7305002 & up

Figure 7-5. Main Gear Oleo Strut Assembly; PA-28-140, -150, -160 and -180

Reissued:1/15/81 LANDINGGEAR AND BRAKESYSTEM

2F13
 PIPER CHEROKEE SERVICE MANUAL

1698

SEE NOTE

Figure 7-5. Main Gear Oleo Strut Assembly; PA-28-140, -150, -160 and -180 (cont.)

Reissued: 1/15/81 2F14 LANDING GEAR AND BRAKE SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

1699

NOTE: PART NO. 78033-0 TORQUE LINK ASSEMBLY IS A MATCHED

SET AND THEREFORE MUST NOT BE INTERCHANGED WITH
65691-0 TORQUE LINK ASSEMBLY.

Torque links can be installed Individually on Serial Nos.

28-235 28-7310003 & UP

1. CAP, VALVE
2. PLUG, FILLER
3. "0" RING
4. HEAD CYLINDER
5. DELETED
6 TUBE, METERING
7. "0" RING
8. ORIFICE ASSEMBLY /
9. SRUT HOUSING
10. WASHER
12 . NUT
12. WASHER
13 TORQUE LINKS
14. "O" RING OR QUAD RING
15 RING, SCRAPER \
16. RING SPACER
17 RETAINERRING
17. TUBE, PISTON
19 AXLE STUB
20. SPACER
21. SPACER
22 NUT, WHEEL RETAINER
23 PIN, CLEVIS

Figure 7-6. Main Gear Oleo Strut Assembly, PA-28-235

Reissued: 1/15/81 2F15 LANDINGGEAR AND BRAKE SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

1999

2
3
4

7
8

13

SEE NOTE

Figure 7-6. Main Gear Oleo Strut Assembly, PA-28-235(cont.)

Reissued: 1/15/81
2F 16 LANDING GEAR AND BRAKE SYSTEM
INTENTIONALLY LEFT BLANK

2F17
 PIPERCHEROKEESERVICEMANUAL

f. Install the hydraulic brake line.

g. If removed, install the landing gear as described in paragraph 7-19.
h. Service the oleo strut as given in Oleo Struts, Section II.
i. Actuate the gear several times by hand to be certain it operates freely.

NOTE

Links should be loose enough to allow free action of the gear.

but also resist side play. To eliminate side play shim washers
63311-03 (.005) may be used as required. Maximum side
play .005/.007.
j . Remove the drip pan and slowly lower the airplane from the jacks.
k. If necessary, bleed brakes by instructions given in paragraph 7-51.

7-18. REMOVAL OF MAIN LANDING GEAR. (Refer to Figure 7-7.)

a. Place the airplane on jacks. (Refer to Jacking, Section II.)
b. Place a drip pan under the main gear to catch spillage.
c. If desired, remove the air from the oleo chamber by depressing the air
valve core pin found in the inspection hole ontop of the wing. After the pressure
in the oleo chamber has diminished, remove the valve core pin and attach a small
hose to the air valve and drain the fluid by slowly compressing the piston tube.
If it is desirable to extract more fluid from the chamber, remove the filler plug,
insert the siphon hose and drain fluid from the upper area of the housing.
d. Remove the fairing from around the cylinder housing and the access plate
located on the bottom of the wing and to the rear of the housing by removing at-
taching screws.
e. Unhook the hydraulic brake line inside the wing assembly. This is acces-
sible through the access plate. Cap the line by use of a threaded cap or wrapping
with plastic.
f. Remove the top four bolts by holding them with a slotted screwdriver and
turning the nut with the appropriate wrench. Remove the remaining six by use
of a wrench. Carefully remove the gear assembly from the wing.

7-19.. CLEANING, INSPECTION AND REPAIR OF MAIN LANDING GEAR.

a. Clean all parts with a suitable dry type cleaning solvent.
b. Inspect the gear components for excessive wear, corrosion and damage.
Check the cylinder housing and torque links for cracks, nicks and misalignment.
c. Repair of the landing gear is limited to reconditioning of parts, replace-
ment of parts, smoothing out minor nicks and scratches and repainting areas
where paint has chipped or peeled.

Revised: 10/3/83
2F18 LANDING GEAR AND BRAKE SYSTEM
 PIPER CHEROKEE SERVICE MANUAL

1777

,/

100

1. SCREW
2. AIR VALVE CAP
3. BOLT
4. AIR VALVE
5. CYLINDER
6. BOLT
7. BRAKE LINE HOSE
8. BOLT, WASHER, NUT & COTTER PIN
9. OLEO ASSEMBLY
10. TORQUE LINK ASSEMBLY
11. TOROUE LINK ASSEMBLY
12. STUB AXLE

Figure 7-7. Main Gear Installation

Reissued: 1/15/81
2F19 LANDING GEAR AND BRAKE SYSTEM
 PIPER CHEROKEE SERVICE MANUAL

7-20..INSTALLATION OF MAIN LANDINGGEAR. (Refer to Figure 7-7.)

a. The main landing gear assembly may be installed on the wing by the follow-
ing procedure:
1. Position the gear up in the wing through the access opening and secure
with bolts, washers and nuts.
2. Reconnect the brake line at the point of disconnection.
b. Service the oleo strut per Oleo Struts, Section II.
c. Service the brake system. (Refer to Brake System, Section II.)
d. Install the access plate to the bottom of the wing and the oleo housing fair-
ing to the gear.
e. Slide the drip pan from under the gear and remove the airplane from the
jacks.

7-21. WHEELS.

7-22. REMOVAL AND DISASSEMBLYOF NOSE WHEEL. (Refer to Figure 7-8.)

a. Jack the airplane enough to raise the nose wheel clear of the ground. (Refer
to Jacking, Section II.)
b. If wheel fairing is installed, remove four bolts, two on each side, and the
small plate on top held by metal screws. Slide fairing up on the gear until the
wheel is removed.
c. Remove wheel by the following procedure:
1. Remove the nut and washer from one end of the axle rod and slide out
the rod and axle plugs.
2. Lightly tap the axle tube out from the center of the wheel assembly by
use of an object of near equal diameter.

NOTE

Be certain not to damage the axle tube end in any way.

This will make removal and installation extremely
difficult.

3. Remove the spacer tubes and the wheel assembly.

4. Slide down wheel fairing and remove by turning it sideways.

Reissued: 1/15/81 2F20 LANDING GEAR AND BRAKE SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

1695

/
2
//

1J

11
as, 3
-I

1. WHEEL HALF
2. WHEEL HALF
3. WASHER
4. WHEEL THROUGHBOLT
5. NUT
6. SEAL RETAINER SCREW
9.
7. SNAP RING
S. SEAL RETAINERS
9. GREASE SEAL
10. BEARING CONES
II. BEARING CUP

Figure 7-8. Nose Wheel Assembly

d. The wheel halves (1 and 2) may be separated by first deflating the tire.
With the tire sufficiently deflated, remove the wheel through bolts (4). Pull the
wheel halves from the tire by removing the wheel half opposite the valve stem
first and then the other half.
e. The wheel bearing assemblies (10 and 11) maybe removed from each wheel
half by first removing the three screws (6) or snap ring (7) which hold in the
grease seal (9) and seal retainers (8), and then the bearing cones (10). The bear-
ing cup (11) should be removed by tapping out evenly from the inside.

Reisesued: 1/15/81 2F21 LANDING GEAR AND BRAKESSYSTEM

 PIPER CHEROKEE SERVICE MANUAL

7-23. INSPECTION OF NOSE WHEEL ASSEMBLY.

a. Visuallycheck all parts for cracks, distortion, defects and excess wear.
b. Check tie bolts for looseness or failure.
c. Check internal diameter of felt grease seals. Replace the felt grease seal if surface
is hard or gritty.
d. Check tire for cuts, internal bruises and deterioration.
e. Check bearing cones and cups for wear and pitting and relubricate.
f. Replace any wheel casting having visible cracks.

7-24. ASSEMBLY AND INSTALLATION OF NOSE WHEEL. (Refer to Figure 7-8.)

a. Ascertain that the bearing cup (11) for each wheel half (I and 2) is properly
installed. Install the tire with tube on the wheel half with the valve stem hole and then
join the two wheel halves. Install the through bolts (4) with the washers (3) and nuts (5) to
the valve stem side, torque nuts to 90 inch pounds and inflate tire. (Refer to TableII-I,
Section II for tire pressure.)
b. Lubricate the bearing cones (10) and install the cones and grease seal assembly(8
and 9). Secure with the same three screws(6) or snap ring (7).
c. Replace the wheel fairing by turning sideways and slipping it up over the fork
assembly.
d. Place the spacer tubes one on each side of the wheel and install unit in fork. Align
and slide the axle tube through the spacer tubes and wheel assembly. Reinstall the axle
plugs and rod with washer and nut. Tighten the nuts until no side play is felt, yet allowing
the wheel to rotate freely.
e. Turn fairing so it will fall into place and reinstall it with the four bolts and screws
in the small plate.

7-25. REMOVAL AND DISASSEMBLY OF MAIN WHEEL. (Refer to Figure 7-9.)

a. Place the airplane on jacks. (Refer to Jacking, Section II.)
b. To remove the main wheel, remove the two cap bolts that join the brake cylinder
housing and the lining back plate assemblies. Remove the back plate from between brake
disc and wheel.
c. Remove the dust cover, the cotter pin and flat head pin that safeties the wheelnut,
and the wheel nut. Slide the wheel from the axle.
d. The wheel halves (1 and 2) may be separated by first deflating the tire. With the tire
deflated, remove the wheel through bolts (16). Pull the wheel halves from the tire by
removing the inner half from the tire first, and then the outer half. The brake disc can be
removed at this time.

Revised: 10/3/83 LANDING GEAR AND

2F22 BRAKE SYSTEM
 PIPER CHEROKEE SERVICE MANUAL

1. WHEEL HALF
2. WHEEL HALF
3. BRAKE DISC
4. SCREW
5. LOCK WASHER
6. DUST SHIELD

/l 7. RETAINER RINGS
8. NUT
9. WASHER
10. BEARING CUP

/'

I · 13

18

11. BEARING CONE

12. RETAINER RINGS
13. GREASE SEAL
14. RETAINER RINGS
15.
I5. SEAL RETAINER SCREW
16. WHEEL THROUGH BOLT
17. SNAP RING
18. GREASE SEAL RETAINER
19. GREASE SEAL
20. GREASE SEAL RETAINER

Figure 7-9. Main Wheel Assembly

e. The wheel bearing assemblies may be removed from each wheel half by
first removing the retainer rings (7 or 12) or snap rings (17) that secure the
grease seal retainers (18 or 20), and then the retainers, grease seals (13 or 19)
and bearing cone (II). The bearing cups (10) should not be removed only for
replacement and may be removed by tapping out evenly from the inside.

7-26. INSPECTION OF MAIN WHEEL ASSEMBLY.

a. Visually check all parts for cracks, distortion, defects and excess wear.
b. Check tie bolts for looseness or failure.
c. Check internal diameter of felt grease seals. Replace the felt grease seal
if surface is hard or gritty.

Reissued: 1/15/81
2F23 LANDING GEAR AND BRAKE SYSTEM
 PIPER CHEROKEE SERVICE MANUAL

d. Check tire for cuts, internal bruises and deterioration.

e. Check bearing cones and cups for wear and pitting and relubricate.
f. Replace any wheel casting having visible cracks.

7-27. ASSEMBLY AND INSTALLATION OF MAIN WHEEL. (Refer to Figure 7-9.)

a. Ascertain that the bearing cup (10) for each wheel is properly installed. Install
the tire with tube on the outer wheel half and then join the two wheel halves. Position the
brake disc (3) in the inner wheel half and install the through bolts with the nuts on the
valve stem side. Torque wheel nuts to 150 inch,pounds and inflate tire. (Refer to Table 11-1.
Section II for tire pressure.)
b. Lubricate the bearing cones (I ) and install the cones, grease seals (13 and 19) and
seal retainer rings (18 or 20). Secure with retainer rings (14) or snap ring (17).
c. Slide the wheel on the axle and secure with retainer nut. Tighten the nut to allow
no side play. yet allow the wheel to rotate freely. Safety the nut with a flat head pin. washer
and cotter pin. Reinstall the dust cover.
d. Position the brake lining back plates between the wheel and brake disc and the
brake cylinder on the torque plate. Insert the spacer blocks between the back plates and
cylinder, and install the four bolts to secure the assembly.If the brake line was disconnected.
reconnect the line and bleed the brakes per paragraph 7-52.

7-28. BRAKE SYSTEM.

7-29. WHEEL BRAKE ASSEMBLY.

7-30. BRAKE ADJUSTMENT AND LINING TOLERANCE. No adjustment of the

brake lining clearance is necessary as they are self-adjusting. Inspection of the lining is
necessary, and it may be inspected visually while installed on the airplane. The linings are
of the riveted type and should be replaced if the thickness of any one segment becomes
worn below .099 of an inch or unevenly worn.

LANDING GEAR AND

Revised: 10/3/83 2F24 BRAKE SYSTEM
 PIPER CHEROKEE SERVICE MANUAL

C342

18

1. BOLT
2- 2. WASHER
3. NUT
4. WASHER
5. BRAKE CYLINDER
6. BLEEDER CAP
7. BLEEDER SCREW
8. BLEEDER SEAT
9. RIVET
4 10. "O" RING
11. PISTON
12. PRESSURE PLATE
13. LINING
14. LINING
15. BACK PLATE
16. SHIM
17. ANCHOR BOLT
18. TORQUE PLATE

Figure 7-10. Wheel Brake Assembly

7-31. REMOVAL AND DISASSEMBLYOF WHEEL BRAKE ASSEMBLY. (Refer

to Figure 7-10.)
a. To remove the brake assembly, first disconnect the brake line from the
brake cylinder at the tube fitting.
b. Remove the two cap bolts that jointhe brake cylinder housing and the lining
back plate assembly. Remove the back plate from between the brake disc and
wheel.
c. Slide the brake cylinder housing from the torque plate.
d. Remove the pressure plate by sliding it off the anchor bolts of the housing.
e. The piston may be removed by injecting low air pressure in the cylinder
fluid inlet and forcing the piston from the housing.

Reissued: 1/15/81 2G1 LANDING GEAR AND BRAKE SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

f. Check Anchor Bolt for wear.

g. Remove anchor bolt by the following procedure.
1. Position cylinder assembly on a holding fixture. (Refer to Figure 7-11.)
2. Use a suitable arbor press to remove the anchor bolt from the cylinder body.

923

PRESS

CYLINDER
BODY

Figure 7-11. Removal of Anchor Bolt

2G2 LANDING GEAR AND BRAKE SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

h. Install Anchor Bolt by the following procedure.

1. Support Anchor Bolt in a holding fixture. (Refer to Figure 7-12. Step A.)
2. Align cylinder body over anchor bolt. (Refer to Figure 7-12. Step B.)
3. Use a suitable arbor press and apply pressure on the spot face directly over the
anchor bolt hole. (Refer to Figure 7-12. Step C).

A122
ANCHOR
BOLT

HOLDING
FIXTURE

STEP A CYLINDER
BODY

HOLDING
FIXTURE

STEP B

PRESS

CYLINDER
BODY

HOLDING
FIXTURE

STEP C

Figure 7-12. Installation of Anchor Bolt

Revised: 10/'3/83 2G3 LANDING GEAR AND BRAKE SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

7-32. CLEANING,INSPECTIONAND REPAIR OF WHEEL BRAKEASSEMBLIES.

a. Clean the assembly with a suitable solvent and dry thoroughly.
b. Check the wall of the cylinder housing and piston for scratches, burrs, corrosion,
etc., that may damage "O" rings.
c. Check the general condition of the brake bleeder screw and lines.
d. Check the brake disc for grooves, scratches or pits. Minimum service thickness of
Disc 164-5used on Wheel Assembly 40-28 is .157. Minimum dimension for Disc 164-9used
on Wheel Assembly 40-58 is .227. Minimum thickness of Disc 164-20 used on Wheel
Assembly 40-86B is .205. (Refer to Figure 7-13.) A single groove or isolated grooves up to
.031 of an inch deep would not necessitate replacement. but a grooving of the entire surface
would reduce lining life and should be replaced. Should it be necessary to remove the wheel
disc. refer to paragraph 7-25.
e. Lining may be removed from the backing plates by drilling or punching out the old
rivets, and installing a new set using the proper rivets and a rivet set that will properly stake
the lining and form a correct flare of the rivet. (A rivet setting kit is availablethrough Piper
Dealers under part number 754 165.)

7-33; ASSEMBLY AND INSTALLATION OF WHEEL BRAKE ASSEMBLY. (Refer to

Figure 7-10.)
a. Lubricate the piston "O" ring with fluid MIL-H-5606and install on piston. Slide the
piston in cylinder housing until flush with surface of housing.
b. Slide the lining pressure plate onto the anchor bolts of the housing.
c. Slide the cylinder housing assemblyon the torque plate of the gear.
d. Position the lining back plate between the wheel and brake disc. Install the two bolts
to secure the assembly.
e. Connect the brake line to the brake cylinder housing.
f. Bleed the brake system as described in paragraph 7-52.

7-34. BRAKEMASTER CYLINDER. (Hand Parking Brake.)

7-35. REMOVAL OF BRAKE MASTER CYLINDER. (Hand Brake.) (Refer to Figure

7-14.)
a. To remove the brake master cylinder (8), first disconnect the inlet supply line (13)
from the fitting at the top of the cylinder and allow fluid to drain from the reservoir and
line into a suitable container.
b. Disconnect the pressure line from the fitting on the cylinder and allow fluid to drain
from the cylinder line.
c. Disconnect the end of the cylinder rod from the brake handle (6) by removingthe
cotter pin that safeties the connecting clevis pin (12). Remove the clevis pin and spacer
washers.
d. Disconnect the base of the cylinder from its mounting bracket by removing the
attaching bolt assembly (11).

Revised: 10/3/83 LANDINGGEAR AND BRAKE SYSTEM

2G4
 PIPER CHEROKEE SERVICE MANUAL

C343

MINIMUM WHEEL
THICKNESS ASSEMBLIES

.157 40-28
.227 40-58
- MINIMUMTHICKNESS .205 40-86

- MEASURE2 OR 3 POINTSTO GET AVERAGE

DISC THICK NESS

!,, MM

Figure 7-13. Brake Disc Minimum Thickness

1786

1. BRAKE RESERVOIR
2. RIGHT BRAKE AND RUDDER PEDAL
3. LEFT BRAKE AND RUDDER PEDAL
4. RIGHT BRAKE CYLINDER
5. LEFT BRAKE CYLINDER
6. BRAKE HANDLE
7. HANDLE RELEASE BUTTON
8. MASTER CYLINDER ASSEMBLY
9. TORQUE TUBE
10. RUDDER PEDAL PADS
II. BOLT ASSEMBLY
12. CLIVIS PIN
13. LINE, INLET

I,

Figure 7-14. Brake System Installation

Revised: 10/3/83 2G5 LANDING GEAR AND BRAKE SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

e. The handle assembly may be removed by removing the attaching bolt assembly that
secures the handle to its mounting bracket.
7-36. DISASSEMBLYOF BRAKEMASTERCYLINDER.
a. PA-28-150.-160. Serial Nos. 28-1 to 28-250 incl. (Refer to Figure 7-15.)
1. Remove the cylinder from its mounting bracket as per Paragraph 7-35.
2. To disassemble the cylinder, first remove the piston rod assembly by removing
the retainer ring (2) from the annular slot at the rod end of the cylinder. Draw the piston
rod assembly from the cylinder. Remove the spring (13) from the cylinder.
3. The piston rod assembly may be disassembled by first removing the clevis end
from the piston rod (6) and then slidingoff the brake cylinder cap (3).
4. Remove the roll pin (8) from the bushing (7) thus releasingthe piston head and
O-rings (9 and 11).
b. PA-28-140. Serial Nos. 28-20002 to 28-21036 incl: PA-28-150. -160. -180 Serial
Nos. 28-251 to 28-2700 incl: PA-28-235. Serial Nos. 28-10003 to 28-10679 incl. (Refer to
Figure 7-16.)
1. Remove the cylinder from the airplane per Paragraph 7-35.
2. Cut the safety wire and remove screw (10) that secures the plug (1) in the end of
the cylinder (9).
3. Remove the plug (1) and piston assembly from the cylinder by pulling the
cylinder actuator shaft (4) from the cylinder.
4. Remove the spring(8) from within the cylinder.
5. Remove the roll pin (7) from the cylinder actuator piston (5) and pull off the
piston.
c. PA-28-140. Serial Nos. 28-21037and up: PA-28-150.-160. -180. Serial Nos. 28-2701
and up: PA-28-235. Serial Nos. 28-10698 and up. (Refer to Figure 7-17.)
1. Remove the cylinder from its mounting bracket as per Paragraph 7-35.
2. To disassemble the cylinder, first remove the piston rod assembly by removing
the snap ring (11) from the annular slot at the rod end of the cylinder. Draw the piston rod
assembly from the cylinder.
3. The piston rod assembly may be disassembled by first removing the small snap
ring (2) securing the retainer bushing (3), spring (4), piston (6), seal (7), gland (9), and, if
desired, the large retainer spring (13).
4. Remove the O-ringsfrom the piston and gland.

Revised: 10/3/83 2G 6 LANDING GEAR AND BRAKE SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

7-37. CLEANING, INSPECTIONAND REPAIR OF BRAKE MASTERCYLINDER.(All.)

a. Clean the cylinder parts with a suitable solvent and dry thoroughly.
b. Inspect the interior walls of the cylinder for scratches, burrs, corrosion, etc.
c. Inspect the general condition of the fitting threads of the cylinder.
d. Check the piston for scratches, burrs, corrosion, etc.
e. Repairs to the cylinder are limited to polishing out small scratches, burrs, etc. and
O-rings.

7-38. ASSEMBLYOF BRAKE MASTERCYLINDER.

a. PA-28-150. -160. Serial Nos. 28-1 to 28-250 incl. (Refer to Figure 7-15.)
NOTE
Use a small amount of hydraulic fluid (MIL-H-5606)on the
O-rings and component parts to prevent damage and ease of
handling during reassembly.

1. Install new O-rings (4 and 5) on the inside and outside of the brake cylinder cap
(3).
2. Install new O-ring(10) on the piston head (11) and slide onto the guide pin (12).
3. Slide the O-ring(9) onto the small end of the guide pin.
4. Fit the guide pin with piston head into the end of the piston plunger rod (6).
Slide the bushing (7) onto the plunger rod and align the holes through the bushing, rod and
pins. Install the roll pins (8).
5. Install the large spring (13) onto the pin and carefully slide the assemblyinto the
cylinder housing.
6. Slide the brake cylinder cap assembly onto the plunger rod and install the
retainer ring (2) into the annular groove provided.
7. Replace the clevisend and jam nut on the end of the piston arm.
8. Fully extend the cylinder and check the extended length. The extension length
from the center line of attachment holes should be 10. 125 + .125 inches. Should
adjustment be needed, rotate the clevisend and set jam nut.
9. Install the cylinder per Paragraph7-38. -

Revised: 10/3/83 2G7 LANDING GEAR AND BRAKE SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

A601

1. CYLINDER
2. RETAINERRING
3. BRAKECYLINDERCAP
4. "O" RING
5. "O" RING
6. ROD
7. BUSHING
8. ROLLPIN
9. "0" RING
10. "O" RING
11. PISTONHEAD
12. PIN
13. SPRING
REFERTO FIGURE7-18 14. PARKINGVALVE

Figure 7-15. Brake Master Cylinder (Hand Brake)

PA-28-150, -160, Serial Nos. 28-1 to 28-250 incl.
1. CYLINDERACTUATORPLUG A600
2. "0" RING
3. "0" RING
4. CYLINDERACTUATORSHAFT
5. CYLINDERACTUATORPISTON
6. PISTON
7. ROLLPIN
8. SPRING 9
9. CYLINDER
10. SCREW

Figure 7-16. Brake Master Cylinder (Hand/Parking Brake)

PA-28-140, Serial Nos. 28-20002 to 28-21036 incl;
PA-28-150, -160,-180, Serial Nos. 28-251 to 28-2700 incl;
PA-28-235, Serial Nos. 28-10003 to 28-10697 incl.

Revised: 10/3;83
2G8 LANDING GEAR AND BRAKE SYSTEM
 PIPER CHEROKEE SERVICE MANUAL

A349
889

COUNTER BORE
.562 DIA. .0625 DEEP

12 13 14 15

.75

1 HOUSING 6 PISTON 11 SNAP RING

2 SNAP RING 7 DYNA SEAL 12 ROD. PISTON
3 BUSHING. RETAINER 8. O-RING 13 SPRING. RETAINING
4 SPRING 9. GLAND PACKING 14. ROLL PIN
5. O-RING 10. O-RING 15 WASHER

Figure 7-17. Brake Master Cylinder. (Hand/Parking Brake)

PA-28-140, Serial Nos. 28-21037and up;
PA-28-150, -160, -180, Serial Nos. 28-2701 and up;
PA-28-235, Serial Nos. 28-10698and up

b. PA-28-140. Serial Nos. 28-20002 to 28-21037; PA-28-150, -160, -180, Serial Nos. 28-251 to
28-2700 inch PA-28-235, Serial Nos. 28-10003to 28-10697incl. (Refer to Figure 7-16.)
NOTE
Use a small amount of hydraulic fluid (MIL-H-5606) on the "0"
rings and component parts to prevent damage and ease of handling
during reassembly.
1. Install the new "0" rings (2 and 3) on the cylinder plug (1).
2. Install the cylinder actuator piston (5) on the actuator shaft (4) and secure with the roll
pin (7).
3. Install a new "0" ring (6) on the actuator pin.
4. Place the spring (8) into the cylinder housing, and carefully slide the actuator and shaft
assembly into the housing.

Revised: 10/3/83 2G9 LANDING GEAR AND BRAKE SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

5. Install the plug assembly(1)on the shaft and install the screw through the housing.
6. Safety the screw with MS20995-C40 wire.
7. -Install the cylinder per Paragraph 7-38.
c. PA-28-140. Serial Nos. 28-21037 and up: PA-28-150. -160. -180. Serial Nos. 28-
28-2701and up: PA-28-235. Serial Nos. 28-10698and up. (Refer to Figure 7-17.)

NOTE

Use a small amount of hydraulic fluid (MIL-H-5606) on the

"0" ring and component parts to prevent damage and ease of
handling during reassembly.

1. Install new "O" ring on the inside and outside of the packing gland (9) and on
the outside of the piston (6). (When installingteflon "O" ring (5) on piston, it is recommended
that it be installed with the use of a cone placed against the piston. The cone may be con-
structed of plastic or metal with dimensions shown in Figure 7-17.)
2. To assemble the piston rod assembly, install on the rod (12), in order, the roll
pins (14), return spring retainer washer (15), retaining spring (13), packing gland (9) with
"0" rings (10), seal (7), piston (6) with "0" ring, spring (4) and retainer bushing (3). Secure
these pieces with snap ring (2) on the end of the rod.
3. Insert the piston rod assembly in the housing (1) and secure packing gland with
snap ring ( 1).
4. Install the cylinder per Paragraph 7-39.

7-39. INSTALLATION OF BRAKE MASTER CYLINDER. (Hand Brake.) (Refer

to Figure 7-14.)
a. Install the brake handle assembly between its mounting bracket and secure with
bolt, washers, nut and cotter pin. Washers should be placed on each side of the handle,
between the bracket, and under the nut.
b. Place the cylinder (8) between the mounting bracket and secure the base end with
bolt, washers, nut and cotter pin. This, too, should have washers placed on each side of the
cylinder and under the nut.
c. Connect the rod end of the cylinder to the brake handle with a clevis pin and thin
washers.Safety the cleviswith a cotter pin.
d. Connect the pressure line to the fitting at the bottom of the cylinder.
e. Connect the inlet supply line (13) to the fitting at the top of the cylinder and secure
with spring clamp.
f. Bleed the brake system per Paragraph 7-51.

Revised: 10/3/83 2G10 LANDING GEAR AND BRAKE SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

7-40. PARKING VALVE. (PA-28-150,

-160, Serial Nos. 28-1 to 28-250 incl.)

7-41. REMOVAL OF PARKING

VALVE.
a. Remove the brake master cylin-
der as given in paragraph 7-35.
b. Remove the parking valve from
the cylinder by turning the elbow from
END FITTING the cylinder housing.
2. RING
3. "0" RING
4. RING. STOP
5.
6.
BODY
PISTON
7-42. DISASSEMBLY OF PARKING
VALVE. (Refer to Figure 7-18. )
Figure 7-18. Parking Valve a. Remove the end fitting (1) from
PA-28-150, -160 the valve body (5).
Serial Nos. 28-1 to 28-250 incl. b. Pushthe piston(6)out through the
body. Ascertainthat the endof the pis-
ton that connects to the link is free from damage or burrs that could- cause the
body piston wall to become scratched or galled as the piston is pushed through.
c. Remove "O" ring packings from the end fitting and piston.

7-43. CLEANING, INSPECTION AND REPAIR OF PARKING VALVE.

a. Clean the valve-components in a suitable dry type cleaning solvent.
b. Inspect the valve for the following:
1. Check that the friction surfaces of the valve body and stem are free
from nicks, dents and burrs.
2. Check that the stop on the piston is secure and undamaged.
3. Check that the threaded surfaces of the body and end fitting are not
stripped or cross-threaded.
c. Repair to the valve is limited to reconditioning of parts, such as smoothing
out minor nicks and scratches, and the replacement of "O" ring packings.

7-44. ASSEMBLY OF PARKING VALVE. (Refer to Figure 7-18. )

a. Install "O" ring packings (3) on the piston (6) and install piston in the valve
body (5). Lubricate "O" rings with hydraulic fluid before installing piston.
b. Install "O" ring packing (2) on end fitting (1) and install end fitting in the
valve body.

Revised: 1013/83 2Gll LANDING GEAR AND BRAKE SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

1. SPRING CLIP 1884

2. TOE BRAKE PEDAL
3. ARM, TRIM CONTROL ATTACHMENT
4. CLEVIS PIN, WASHER & COTTER PIN
5. CLEVIS ASSEMBLY
6. CLEVIS PIN
7. ARM, IDLER
8. JAM NUT 16

9. CLEVIS PIN, WASHER & COTTER PIN

10. CLEVIS PIN, WASHER & COTTER PIN
11. SPRING, RETURN
12. BRACKET
13. BRACE ASSEMBLY
14. CYLINDER ASSEMBLY, HYDRAULIC
15. TUBE ASSEMBLY, LEFT
16. CLEVIS PIN & COTTER PIN
17. HOSE ASSEMBLY - FLEXIBLE
18. TUBE ASSEMBLY, RIGHT
19. PEDAL PADS

Figure 7-19. Toe Brake Installation

Reissued: 1/15/81
2G12 LANDING GEAR AND BRAKE SYSTEM
 PIPER CHEROKEE SERVICE MANUAL

7-45. INSTALLATION OF PARKING VALVE.

a. Install the parking valve onto the cylinder housing by turning the elbow into the
threaded housing.
b. Install the brake master cylinder as given in Paragraph 7-39.

7-46. BRAKE CYLINDER. (Toe Brake.)

7-47. REMOVAL OF BRAKE CYLINDER. (Refer to Figure 7-19.)

a. Disconnect the upper and lower lines from the cylinder (14) to be removed and cap
the lines to prevent fluid leakage or drain the fluid from the brake reservoir and master
cylinder.
b. Remove the cylinder from its attachment fittings by first removing cotter pins that
safety the cylinder attaching pins (4 and 16)and then removing the pins.

7-48. DISASSEMBLY OF BRAKE CYLINDER.

a. Cleveland cylinder number 10-20.(Refer to Figure 7-20.)
1. Remove the cylinder from its mounting bracket as per Paragraph 7-47.
2. To disassemble the cylinder, first remove the piston rod assembly by unscrewing
the packing gland (9) from the cylinder.
3. The piston rod assembly may be disassembled by first removing the small snap
ring (2) securingthe retainer bushing (3) and then removing the bushing, spring (4),piston (5),
seal (7), gland (9), and, if desired, the large return spring.
4. Remove the O-rings from the piston and packing gland.
b. Cleveland cylinder number 10-27. (Refer to Figure 7-20.)
1. Remove the cylinder from its mounting bracket per Paragraph 7-47.
2. To disassemble the cylinder, first remove the piston rod assembly by removingthe
snap ring (10)from the annular slot in the cylinder housing (1). Draw the piston rod assembly
from the cylinder.
3. The piston rod assembly may be disassembledby first removing the roll pin (12)
and then the piston assembly (3), seal (5), packing gland (7).
4. Remove the O-rings from the piston and packing gland.
c. Cleveland cylinder number 10-30.(Refer to Figure 7-21.)
1. Remove the cylinder from its mounting bracket per Paragraph 7-47.
2. To disassemblethe cylinder, first remove the piston rod assemblyby removing the
reta ning ring from the annular slot in the cylinder housing (1). Draw the piston rod assembly
from the cylinder.
3. The piston rod assembly may be disassembled by first removing the retaining
ing (2), sleeve(3), spring (4), and then the piston assembly, O-ring (5), and gland (8), and, if
desired, the return spring (13).
4. Remove the O-rings from the piston and packing gland.
d. Gar-Kenyon cylinder number 17000.(Refer to Figure 7-20.)
1. Remove the cylinder from its mounting bracket as per Paragraph 7-47.
2. To disassemble the cylinder, first remove the piston rod assembly by unscrewing
the fitting (8) from the cylinder.
3. The piston rod assembly may be disassembled by first removing the retaining
ring (2) securingthe sleeve(3) and then removing the spring (4), piston (6), seal (7), fitting (8),
and, if desired, the large return spring (11).
4. Remove the O-rings from the piston and fitting.

Revised: 10/3/83 LANDING GEAR AND BRAKE SYSTEM

2G13
 PIPER CHEROKEE SERVICE MANUAL

C344

14
4
13

12
11

10-20 10-27 17000

14
12

12 11
3 10
10
8
8
7
7
6 .5

1. HYDRAULIC 4 1. HYDRAULIC
CYLINDER
2. SNAP RING CYLINDER 3
2. SPRING 1. HOUSING
3. BUSHING
3. PISTON 2 2. RETAINING RING
4. SPRING
4. "O" RING 3. SLEEVE
5. PISTON
5. SEAL WASHER 4. SPRING
6. "0" RING
6. "O" RING 5. "O" RING
7. DYNA-SEAL
WASHER 7. PACKING GLAND 6.. PISTON
8. "O" RING 8. "O" RING 7. SEAL
9. PACKING GLAND 9. WIPER WASHER 8. FITTING
10. "O" RING 10. RETAINING RING 1 9. "O" RING
11. PISTON ROD 11. SPRING 10. "O" RING
12. SPRING 12. ROLL PIN 11. SPRING
13. DELETED 13. PISTON ROD 12. PISTON ROD
14. WASHER 14. WASHER 13. WASHER
15. ROLL PIN 15. ROLL PIN 14. ROLL PIN

Figure 7-20. Brake Cylinder (Toe Brake)

7-49. CLEANING, INSPECTION AND REPAIR OF BRAKE CYLINDER.

a. Clean the cylinder parts with a suitable solvent and dry thoroughly.
b. Inspect the interior walls of the cylinder for scratches, burrs, corrosion,
etc.
c. Inspect the general condition of the fitting threads of the cylinder.
d. Check the piston and valve for scratches, burrs, corrosion, etc.
e. Repairs to the cylinder are limited to polishing out small scratches, burrs,
etc. and replacing valve, washer, seal, and "O" rings.

Reissued:1/15/81 2G14 LANDING GEAR AND BRAKESYSTEM

 PIPER CHEROKEE SERVICE MANUAL

C343
I 2637 10-30

1. HOUSING 5. O-RING 9. O-RING 13. SPRING

2. RETAINING RING 6. PISTON 10. O-RING 14. WASHER
3. SLEEVE 7. O-RING 11. WASHER WIPER 15. ROLL PIN
4. SPRING 8. GLAND 12. ROD

Figure 7-21. Brake Cylinder (10-30) (Toe Brake)

I THIS SPACE INTENTIONALLY LEFT BLANK

Revised: 10/3/83 2G15 LANDING GEAR AND BRAKE SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

7-50. ASSEMBLYOF BRAKE CYLINDER.

a. Cleveland cylinder number 10-20. (Refer to Figure 7-20.)

NOTE
Use a small amount of hydraulic fluid (MIL-H-5606)on the
"O" ring and component parts to prevent damage and ease of
handling during reassembly.

1. Install new "O" rings on the inside and outside of the packing gland (9) and on
the outside of the piston (5).
2. To assemble the piston rod assembly, install on the rod (11), in order, the roll
pin (15), return spring retainer washer (14), return spring (12), packing gland (9) with "O"
rings, seal (7), piston (5) with "0" ring, spring (4) and retainer bushing (3). Secure these
pieces with the small ring (2) on the end ofthe rod.
3. Insert the piston rod assembly in the cylinder (1) and secure packing (9).
4. Install the cylinder per paragraph 7-51.
b. Cleveland cylinder number 10-27. (Refer to Figure 7-20.)
1. Install new "0" rings on the inside and outside of the packing gland (7) and on
the outside of the piston (3). (Refer to above note.)
2. To assemble the piston rod assembly, install on the rod (13), in order, the roll
pin (15), washer (14), spring (11), washer (9), packing gland (7), seal (5), piston assembly
(3) and spring (2).
3. Insert the piston rod assembly in the cylinder (1) and secure with the snap ring
(10).
4. Install the cylinder per paragraph 7-51.
c. Cleveland cylinder number 10-30. (Refer to Figure 7-21.)
1. Install new O-rings on the inside and outside of the packing gland (7) and on the
outside of the piston (3).
2. To assemble the piston rod assembly, install on the rod (12), in order, the roll pin
(14), washer (13), spring (11), washer (9), packing gland (7) with O-rings, seal (5), piston
assembly (3) with O-ring, spring (2), and roll pin (15).
3. Insert the piston rod assembly in the cylinder (1) and secure with the retaining
ring (10).
4. Install the cylinder per paragraph 7-51.
d. Gar-Kenyon cylinder number 17000.(Refer to Figure 7-20.)
1. Install new O-rings on the inside and outside of the fitting (8) and on the outside
of the piston (6). (Refer to above note.)
2. To assemble the piston rod assembly; install on the rod (12), in order, the roll
pin (14), return spring retainer washer (13), return spring ( 11), fitting (8)with O-rings, seal(7),
piston (6) with O-ring, spring (4) and sleeve(3). Secure these pieces with the retaining ring (2)
on the end of the rod.
3. Insert the piston rod assembly in the cylinder (1) and secure fitting (8).
4. Install the cylinder per paragraph 7-51.

Reissued: 1/15/81 2G16 LANDINGGEAR AND BRAKE SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

7-51. INSTALLATION OF BRAKE CYLINDER. (Refer to Figure 7-19.)

a. Position the cylinder (14) at its mounting points and attach with clevispins. Safety
the pins with cotter pins.
b. Connect the brake lines to the cylinder fittings.
c. Bleed the brakes per paragraph 7-52.
7-52. BLEEDINGBRAKES.

7-53. BRAKE BLEEDING PROCEDURE (Gravity). (Refer to Figure 7-22.)

a. Attach a clean, clear plastic tube to the brake bleeder of the right landing gear.
Extend the free end of the tube to a container partially filled with hydraulic fluid
(MIL-H-5606). Determine that the end of the tube is submerged in the fluid. Open the
bleeder 1/2 to 1 turn.
b. Fill the brake fluid reservoir located on the firewall with hydraulic fluid.
c. Check to determine the right hand toe brake pedal(s) in the cockpit have been
pulled full aft.
d. Pull the hand brake handle and slowly pump the master cylinder approximately 50
times or until hydraulic fluid is observed passing through the plastic tube at the brake
bleeder.

NOTE
Fluid level in the reservoir must be maintained to prevent air
from entering the system.

e. Pump right brake cylinder very slowly approximately 12 times. This will purge air
from the toe brake cylinder system. Watch for any air forced through the clear plastic tube
during this operation to insure air has been forced from the toe brake system.
f. Pump the hand brake an additional 25 times or until no air is observed through the
clear plastic tube.
g. Tighten brake bleeder and remove the plastic tube.
h. Repeat steps a through f to the left main landing gear.
7-54. BRAKE BLEEDING PROCEDURE (Pressure). (Refer to Figure 7-23.)
a. Place a clean, clear plastic tube on the vent fitting on top of the brake fluid
reservoir. Extend the free end of the tube to a container partially filled with hydraulic fluid
(MIL-H-5606).Be certain the end of the tube is submerged in the fluid.
b. Attach another clear plastic tube to the brake bleeder of the right landing gear.
Connect the free end of this tube to the pressure source. Open the bleeder 1 to 2 turns and
pressure fill the system with fluid.
c. With fluid continually flowing through the system, SLOWLYand simultaneously
actuate the hand brake and toe brake pedal, of the side being bled, several times to purge
the cylinders of air. On dual brake installations, both pedals for the brake being bled must
be actuated.

Reissued: 1/15/81 2G17 LANDING GEAR AND BRAKE SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

NOTE

By watching the fluid pass through the plastic hose at the fluid
reservoir and the bleeder fitting on the gear beingbled, it can be
determined whether any air is left in the system. If air bubbles
are evident, filling of the system shall be continued until all the
air is out of the system and a steady flow of fluid is obtained.
Should the brake handle remain spongy,it may be necessaryto
disconnect the bottom of the
1756
1756

Figure 7-22. Bleeding Brake (Gravity) Figure 7-23. Bleeding Brake (Pressure)

Reissued: 1/15/81 2G18 LANDING GEAR AND BRAKE SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

toe brake cylinders (next to the pedal) and rotating the

cylinder horizontally or even above horizontal and by use of
the hand brake alone, purge the air from the system.
d. Close the open bleeder fitting to which the pressure hose is attached. Do not remove
the tube from the fluid reservoir until both brakes have been bled. Check the brakes on the
side being bled for proper pedal pressure. Replace cap on bleeder fitting.

NOTE
It may be necessary to remove any trapped air in the top of
the wheel brake unit by applying pressure to the system with
the brake hand lever and slowly opening the bleeder and
release the hand lever.

e. Repeat steps b through d to the left main landing gear.

f. Drain excess fluid from the reservoirto fluid level with a syringe.

7-55. BRAKE SYSTEMLEAK CHECK. Pull for a good, firm hand brake and lock parking
brake mechanism. Allow system to stand for approximately 10 minutes, then -by gripping
the park brake handle it should not be able to be pulled aft further than the original set.
Should the handle be able to be pulled towards the panel and feel spongy, a leak is present
at some point in the system. This leak may appear at any one of the connections throughout
the system or internally in the master brake cylinder or wheel brake assemblies.

7-56. BLEEDINGOF THE BRAKESAFTER A UNIT HAS BEEN CHANGED.

a. Actuate the hand brake handle until some pressure builds up in the system. At this
time, crack the attaching B nuts at any of the hose connections of the replacedunit. Most of
the handle sponge feeling should be displaced by this action.
b. Actuate the master cylinder and the toe brake cylinder of the side unit was changed
and bleed fluid through the brake assemblyon the wheel by pumping pressure and cracking
bleeder until pressure drops.

CAUTION

Do not allow pressure to bleed off before closingbleeders,

for this will allow air to enter the system. Repeat the
pumping and bleeding approximately 10 or more times or
until all the air is released from the system. During all
bleeding, fluid level of the reservoirmust be maintained.

Reissued: 1/15/81
2G19 LANDING GEAR AND BRAKE SYSTEM
 PIPER CHEROKEE SERVICE MANUAL

TABLE VIL-II.. LANDING GEAR TROUBLESHOOTING

Trouble Cause Remedy

Nose landing gear Internal wear in Replace shimmy
shimmies during fast shimmy dampener. dampener.
taxi, take-off, or
landing.
Shimmy dampener or Replace necessary
bracket loose at parts and bolts.
mounting.

Tire out of balance. Check balance and re-

place tire if necessary.

Worn or loose wheel Replace and/or adjust

bearings. wheel bearings.

Worn torque link bolts Replace bolts and/or

and/or bushings. bushings.

Excessive or uneven Incorrect operating Inflate tire to correct

wear on nose tire pressure. pressure.

Wear resulting from Refer to proceedings

shimmy. for correction.

Nose gear fails to Oleo cylinder binding Lubricate strut housing

steer properly. in strut housing. (Refer to Lubrication
Chart).

Cylinder and/or strut

housing bushings
damaged.

Reissued: 1/15/81
2G20 LANDING GEAR AND BRAKE SYSTEM
 PIPER CHEROKEE SERVICE MANUAL

TABLE VII-II. LANDING GEAR TROUBLESHOOTING (cont)

Trouble Cause Remedy

Nose gear fails to One brake dragging. Determine cause and

steer properly (cont). correct.

Steering bellcrank loose Readjust and tighten.

on attachment plate.

Steering bellcrank bear- Replace bearing and/or

ing and/or bolt worn. bolt.

Shimmy dampener Replace.

galling or binding.

Main landing shimmies Tire out of balance. Check balance and re-
during fast taxi, take- place tire if necessary.
off, or landing.

Worn or loose wheel Replace and/or adjust

bearings. wheel bearings.

Worn torque link bolts Replace bolts and/or

and/or bushings. bushings.

Excessive or uneven Incorrect operating Inflate tire to correct

wear on main tires. pressure. pressure.

Wheel out of alignment Check wheel alignment.

(toe in or out).

Reissued: 1/15/81
2G21 LANDING GEAR AND BRAKE SYSTEM
 PIPER CHEROKEE SERVICE MANUAL

TABLE VII-II. LANDING GEAR TROUBLESHOOTING (cont)

Trouble Cause Remedy

Strut bottoms on Insufficient air and/or Service strut with air

normal landing or fluid in strut. and/or fluid.
taxiing on rough
ground
Defective internal parts Replace defective parts.
in strut.

Reissued: 1/15/81 2G22 LANDING GEAR AND BRAKE SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

MATERIAL:STEEL

Figure 7-24. Orifice Replacement Tool

Reissued: 1/15/81
2G23 LANDING GEAR AND BRAKE SYSTEM
 PIPER CHEROKEE SERVICE MANUAL

904

WELD
HANDLE .50 DIA.

4.00 3 .125
7.50

Figure 7-25. Retainer Ring Tool

Reissued: 1/15/81 2G 24 LANDINGGEAR AND BRAKESYSTEM

 SECTION VIIA
LANDING GEAR AND BRAKE SYSTEM
(PA-28R)

Paragraph Aerofiche
Grid No.
7A- . Introduction ............................................... 2H4
7A-2. Description ............................................... 2H4
7A-3. Troubleshooting .......................... 2H6
7A-4. Landing Gear System ......................................... 2H6
7A-5. Nose Landing Gear ........................................... 2H6
7A-6. Disassembly of Nose Gear Oleo ....................... 2H6
7A-7. Cleaning, Inspection and Repair of Nose Gear Oleo ...... 2H7
7A-8. Assembly of Nose Gear Oleo ........................... 2H7
7A-9. Removal of Nose Landing Gear ...................... . 2H 0.
7A-10. Cleaning, Inspection.and Repair of Nose Landing
Gear............................................. -2H13
7A-11. Installation of Nose Landing Gear ..................... 2H 14
7A-12. Adjustment of Nose Landing Gear (Without
Gear Up Stop) .................................. 2H16
7A-13. Adjustment of Nose Landing Gear (With Gear
Up Stop) ....................................... 2H17
7A-14. Alignment of Nose Landing Gear ...................... 2H18
7A-15. Removal of Nose Gear Door Assembly ................. 2H 19
7A-16. Cleaning, Inspection and Repair of Nose Gear
Door Assembly.................................. 2H21
7A-17. Installation of Nose Gear Door Assembly ............... 2H21
7A-18. Adjustment of Nose Gear Doors ....................... 2H22
7A-19. Main Landing Gear System.... ............................... 2H22
7A-20. Disassembly of Main Gear Oleo ....................... 2H22
7A-21. Cleaning, Inspection and Repair of Main
Gear Oleo ...................................... 2H23
7A-22. Assembly of Main Gear Oleo .......................... 2H23
7A-23. Removal of Main Landing Gear ........................ 213
7A-24. Cleaning, Inspection and Repair of Main
Landing Gear .................................. 216
7A-25. Installation of Main Landing Gear .... ................. 217
7A-26. Adjustment of Main Landing Gear ...................... 218
7A-27. Alignment of Main Landing Gear ...................... 2III
7A-28. Removal of Main Gear Door Assembly ................ 2113
7A-29. Cleaning, Inspection and Repair of Main
Gear Door Assembly ............................. 2I13
7A-30. Installation of Main Gear Door Assembly .............. 2I13
7A-31. Adjustment of Main Gear Door Assembly .............. 2I14

Revised: 10/3/83 2H1

 Paragraph Aerofiche
Grid No.
7A-32. Landing Gear Limit Switches .................................. 2114
7A-33. Adjustment of Nose Gear Up Limit Switch ............. 2114
7A-34. Adjustment of Nose Gear Down Limit Switch ........... 2115
7A-35. Adjustment of Main Gear Up Limit Switch ............. 2116
7A-36. Adjustment of Main Gear Down Limit Switch .......... 2116
7A-37. Adjustment of Landing Gear Safety Switch
(Squat Switch) ............................. .... 2118
7A-38. Adjustment of Gear Back-Up Extender Actuator
Switch ........................................ 2118
7A-39. Landing Gear Warning Switches (Throttle Switches) .............. 2118
7A-40. Landing Gear Up/Power Reduced Warning Switch ...... 2118
7A-41. Removal of Landing Gear Up/Power Reduced
Warning Switch ................... .............. 2118
7A-42. Installation of Landing Gear Up/Power Reduced
Warning Switch .......... ..................... 2118
7A-43. Adjustment of Landing Gear Up/Power Reduced
Warning Switch .................................. 2119
7A-44. Gear Down/ Selector Handle Up Warning Switch ........ 2120
7A-45. Removal of Gear Down/Selector Handle Up
Warning Switch ................................. 2120
7A-46. Installation of Gear Down/Selector Handle Up
Warning Switch .............................. 2120
7A-47. Adjustment of Gear Down/Selector Handle Up
Warning Switch ................................. 2120
7A-48. Wheels ....................................................... 2121
7A-49. Removal and Disassembly of Nose Wheel ............... 2121
7A-50. Inspection of Nose Wheel Assembly. ................... 212
7A-51. Assembly and Installation of Nose Wheel ............... 2121
7A-52. Removal and Disassembly of Main Wheel .............. 2123
7A-53. Inspection of Main Wheel Assembly ................... 2124
7A-54. Assembly and Installation of Main Wheel............... 2124
7A-55. Brake System ................................................ 2124
7A-56. Wheel Brake Assembly ........................................ 2124
7A-57. Brake Adjustment and Lining Tolerance ................ 2124
7A-58. Removal and Disassembly of Wheel Brake
Assembly ....................................... 2J
7A-59. Cleaning, Inspection and Repair ofWheel
Brake Assemblies ................................ 2J2
7A-60. Assembly and Installation of Wheel Brake
Assembly ....................................... 2J2

Revised: 8/3/81 2H2

 Paragraph Aerofiche
Grid No.

7A-61. Brake Master Cylinder (Hand Parking Brake) .................... 2J2

7A-62. Removal of Brake Master Cylinder .................... 2J2
7A-63. Disassembly of Brake Master Cylinder ................. 2J4
7A-64. Cleaning, Inspection and Repair of Brake
Master Cylinder ................................ 2J4
7A-65. Assembly of Brake Master Cylinder .................... 2J4
7A-66. Installation of Brake Master Cylinder ............ ...... 2J5
7A-67. Brake Cylinder (Toe Brake) ............................... 2J7
7A-68. Removal of Brake Cylinder ........................... 2J7
7A-69. Disassembly of Brake Cylinder ........................ 2J7
7A-70. Cleaning, Inspection and Repair of Brake
Cylinder ........................................ 2J8
7A-71. Assembly of Brake Cylinder ...................... .... 2J9
7A-72. Installation of Brake Cylinder ......................... 2J10
7A-73. Bleeding Procedure ................................ ........... 2J10
7A-74. Bearing Replacement ........................................ 210
7A-75. Nose Gear Service Tolerances ................................... 2J20
7A-76. Main Gear Service Tolerances .................................. 2J23

Revised: 10/3/83
2H3
 PIPER CHEROKEE SERVICE MANUAL

SECTIONVIIA
LANDINGGEAR AND BRAKESYSTEM
PA-28R

7A-1, INTRODUCTION. In this section are instructions for the overhaul, inspection and
adjustment of the various components of the PA-28R landing gear and brake system. Also
included are adjustments for the electricallimit, safety and warning switches, and the hydraulic
function of the brakes. Information on the hydraulic system for raising and lowering the
landing gear is covered in Section VI.

7A-2. DESCRIPTION. The PA-28R airplane is equipped with a retractable, tricycle, air-oil,
strut-type landing gear which is-hydraulically operated by an electrically powered reversible
pump. A selector handle on the instrument panel to the left of the control quadrant is used to
select gear UP or DOWN positions.
Gear positions are indicated by three green lights located below the selector lever for gear
down and locked, and a yellow light located at the top of the instrument panel for intransit
positions. There is no light to indicate the gear has fully retracted other than all lights are out.
As the landing gear swings to the down position and each downlock hook moves into its
locked position, a switch at each hook actuates the switch to the NO (Normally Open) circuit
to indicate by a green light that the individual gear is safelydown and locked. The activation
of all three downlock switches will also shut the hydraulic pump off. As the instrument lights
are turned on, the green lightswill dim. When the gear beginsto retract and the downlock hook
disengages, the down limit switch actuates the switch to the NC circuit, and in series with the
NC circuit of the up limit switch, allows the intransit light to come on. The intransit light will
remain on until the gear is up and all up limit switches are actuated to their NO (Normally
Open) circuit.
To the left of the yellow intransit light is a red warning light which operates
simultaneously in conjunction with the warning horn, and they have a twofold purpose.
Their primary purpose is to give warning when power is reduced below approximately 14
inches of manifold pressure and the landing gear has not reached the down and locked
position. This circuit is controlled by the three paralleling down limit switches connected in
series with a throttle switch (Switch "A") located in the control quadrant. The secondary
function of the warning light and horn is to givewarning when the gear selector handle is up
and while the airplane is on the ground or airspeed is below that required to close the
hydraulic valve and the pump switch of the backup gear extender unit. When the airplane is
setting on the ground, the warning circuit is controlled through the NO side of the safety
switch (squat switch) located on the left gear and the up position of the selector lever.
Should the airplane be raised from the ground, such as in flight, far enough to move the
safety switch to its NC position, then current is directed in series through the hydraulic
pressure switch, the pump switch (providing airspeed has actuated the switch to its NO
position), throttle switch (Switch "B") and the up positioned selector lever. Throttle switch
"B" is located forward of the instrument panel directly below the arm of the throttle lever.

Reissued:
1/15/81 2H4 LANDING GEAR AND BRAKE SYSTEM
 PIPER CHEROKEE SERVICE MANUAL

The up limit, safety, throttle, pressure and selector switch, and pump solenoids are all
protected by the landing gear control and warning circuit protector. (Refer to Figure
7A-13.)
Each landing gear is retracted and extended by a single hydraulic cylinder attached to
the drag link assembly of the nose gear and the side brace link assemblyof the main gears.
As the gears retract, doors partially enclose each gear through mechanical linkage.The gears
are held in their up position by hydraulic pressure alone on the cylinder. There are no
uplocks and loss of hydraulic pressure will allow the gears to drop. It is preferred that the
gears be extended and retracted with the use of the gear selector handle; however in the
event of hydraulic loss or electrical failure, they can be lowered by pushing down on the
emergency extension lever between the pilot seats or they will drop themselves should
arispeed drop below approximately 105 MPH, engine power off. In either instant the
hydraulic valve of the back-up extender unit opens to allow hydraulic pressure to neutralize
between each side of the cylinder pistons The emergency extension lever can also be used
to manually overcome system malfunctions or to meet special pilot needs such as, a
deliberate wheels up landing - needed for emergency landings on water, or during various
flight maneuvers where airpseed and power settings would normally allow the gear to
extend. It also permits gear retraction after take-off at speeds lower than those normally
permitted by the automatic system. Whenusing the manual extension lever the gear position
is controlled by the selector switch, regardlessof airspeed/power combinations.An override
lock mechanism is installed on 1972 models and is also available in Kit form for earlier
models, which allows the pilot to lock the extension lever in the up overrideposition, thus
bypassing the automatic portion of the system. A flashing warning light is mounted below
the gear selector lever to indicate whenever the lock is in use. The lock is disengagedby
pulling up on the extension lever. To assist the nose gear to extend under these conditions
are two springs attached to the nose gear. The main gears require no assist springs.Once the
gears are down and the downlock hooks engage, a spring maintains each hook in the locked
position until hydraulic pressure again releases it. A further description of the hydraulic
system and the gear back-up extender unit may be found in Section VI, Hydraulic System.
The nose gear is steerable through a 60 degree arc by the use of the rudder pedals. As
the gear retracts, however, the steering linkage becomes separated from the gear so that
rudder pedal action with the gear retracted is not impeded by the nose gear operation. A
shimmy dampener is also incorporated in the nose wheel steering mechanism. Bungees are
also incorporated on the push rods of later models. (1974 models and up) These springs
make lighter and smoother ground steering possible.
The two main wheels are equipped with self-adjusting single disc hydraulic brake
assemblies. On models previous to 1974 models, these brake assemblies are actuated by
individual toe brake cylinders mounted on the pilot's (optional on the copilot's) rudder.
pedals and a handle connected to a brake cylinder located below and forward of the center
of the instrument panel. On 1974 models and up, these toe brakes are standard on both the
pilot's and copilot's rudder pedals. A parking brake is incorporated with the handle, and
may be used by pulling back on the handle and pushing forward on the button to the left of
the handle. To release the hand brake, pull aft on the handle and allow it to swingforward.
Hydraulic fluid for the cylinders is supplied by a reservoirinstalled on the left forward side
of the fire wall.

Reissued: 1/15/81 LANDING GEAR AND BRAKE SYSTEM

2H5
 PIPER CHEROKEE SERVICE MANUAL

7A-3. TROUBLESHOOTING. Mechanical and electrical switchtroubles peculiar

to the landing gear system are listed in Table VIIA-I at the back of this section.
When troubleshooting, first eliminate hydraulic malfunctions as listed in Section
VI. Then proceed to switch malfunctions and last to the mechanical operation of
the gear itself, both of which are listed in this section. Always place the airplane
on jacks before attempting any troubleshooting of the gear. To operate the gear,
the emergency gear lever must be maintained in the up override position.

7A-4. LANDING GEAR SYSTEM.

7A-5. NOSE LANDING GEAR.

7A-6. DISASSEMBLY OF NOSE GEAR OLEO. (Referto Figure 7A-1.) The nose
gear oleo assembly may be removed and disassembled from the gear oleo hous-
ing with the gear removed from or installed on the airplane.
a. Place the airplane on jacks. (Referto Jacking, Section II.)
b. Place a drip pan under the nose gear to catch spillage.
c. Remove air and fluid from the oleo strut. Depress the air valve core pin
until strut chamber pressure has diminished, remove the filler plug and with a
small hose siphon as much hydraulic fluid from the strut as possible.
d. To remove the complete cylinder and fork assembly from the oleo housing
(21), cut safety wire (2) at the top of the unit and remove cap bolts (1) that attach
steering arm (11) and aligner guide bracket (12) to the top of the oleo cylinder (23).
e. Disconnect the shimmydampener by removing each cotter pin, nut, washer
and bolt that connects the dampener to the oleo cylinder (23) and housing.
f. Release and remove the snap ring (17) and washer(s) (43), if installed at
the top of the housing (21), and pullthe complete cylinder and fork assembly from
the bottom of the housing. The upper and lower housing bushings (20 and 22)
should remain pressed in the housing.
g. To remove the piston tube (39) and fork (42) from the cylinder (23), first
separate the upper and lower torque links (24 and 26) by removing the link con-
necting bolt assembly (25) and then separate the two links. Note spacer washer
between the two links.
h. Compress the piston tube (39), reach up along the tube and release the snap
ring (38) from the annular slot at the bottom of the oleo housing.

Reissued: 1/15/81
2H6 LANDING GEAR AND BRAKE SYSTEM
 PIPER CHEROKEESERVICE MANUAL

i . Pull the piston tube (39) with component parts from the cylinder.
j . The piston tube components may be removed by reaching in the tube and
pushing out the upper bearing retainer pins (27). Slide from the tube, the upper
bearing (29), lower bearing (34) with outer and inner "O" rings (33 and 35), wiper
strip (36), washer (37) and snap ring (38).
k. To remove the orifice tube (30), remove the large lock nut (16) and lock
washer (19) from the top of the cylinder. Pull the tube from the cylinder.
1. The orifice plate (31) is removed from the bottom of the orifice tube by re-
leasing the snap ring (32) that holds the plate in position.
m. To remove the piston tube plug (40) with "O" ring (41) located in the lower
end of the tube, remove the bolt assembly and insert a rod up through the hole in
the body of the fork (42). Push the plug out through the top of the tube.

7A-7. CLEANING, INSPECTION AND REPAIR OF NOSE GEAR OLEO.

a. Cleanall parts with a suitable dry type cleaning solvent.
b. Inspect the landing gear oleo assembly component for the following:
1. Bearings and bushings for excess wear, corrosion, scratches and over-
all damage.
2. Retaining pins for wear and damage.
3. Lock rings for cracks, burrs, etc.
4. Cylinder and orifice tube for corrosion, scratches, nicks and excess
wear.
5. Upper and lower cylinder bushings loose or turning in cylinder.
6. Orifice plate for hole restriction.
7. Fork tube for corrosion, scratches, nicks, dents and misalignment.
8. Air valve general condition.
c. Repair of the oleo is limited to smoothing out minor scratches, nicks and
dents and replacement of parts. (See Figure 7A-26 and Table VIIA-II.)

7A-8. ASSEMBLY OF NOSE GEAR OLEO. (Refer to Figure 7A-1.)

a. Ascertain that parts are cleaned and inspected.
b. To install the piston tube plug (40), first lubricate the tube plug and "0"
ring (41) with hydraulic fluid (MIL-H-5606) and install the "0" ring on the plug.
Lubricate the inside wall of the tube (39), insert the plug into the top of the tube
and push it to the fork end. Align the bolt holes of the fork, tube and plug, and
install bolt assembly.
c. If desired, cement a cork in the hole in the bottom of the fork body to pre-
vent dirt from entering between the fork and tube.
d. To assemble the components of the orifice tube (30), insert the orifice plate
(31) into the bottom of the tube, with the countersunk side of the orifice hole ex-

Reissued: 1/15/81 2H7 LANDING GEAR AND BRAKE SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

1714

12
13
14

2. CAP BOLTS AND WASHERS

3. SUPPORT FITTING
22
4. RUSHING SUPPORT FITTING
5. BUSHING 23
6. BOLT, WASHERS, NUT AND COTTER PIN
7. BOLT, WASHERS, NUT AND COTTER PIN
8. AXLE3
9 CAP BOLT
I. BUSHING, ROLLER FITTING
11. ARM, STEERING
12. BRACKET ALIGNER 24
13. CAP, AIR VALVE
14. CORE, AIR VALVE 25
15. BODY, AIR VALVE
16. NUT, ORIFICE TUBE 26
17. SNAP RING
18. ROLL PIN
19. WASHER, STOP
20. BUSHING, UPPER\
21. HOUSING, STRUT
22. BUSHING, LOWER
23. OLEO CYLINDER
24. LINK, UPPER TORQUE
25. BOLT, WASHER, BUSHINGS, NUT AND COTTER PIN
26. LINK, LOWER TORQUE
27. PIN, BEARING RETAINING
28. "O" RING
29. BEARING, UPPER TUBE
30. TUBE, ORIFICE
31. PLATE, ORIFICE
32. SNAP RING
33. "O" RING
34. BEARING, LOWER TUBE
35. "O" RING
36. WIPER STRIP
37. WASHER
36. SNAP RING
39. TUBE, PISTON
40. PISTON TUBE PLUG
41. "O" RING
42. PORK
43. WASHER

Figure 7A-1. Nose Gear Oleo Strut Assembly

Reissued: 1/15/81
Reissued: 1/15/81 2H8 LANDING GEAR AND BRAKE SYSTEM
2H8
 PIPER CHEROKEE SERVICE MANUAL

1716 1733

10
11
12
13
14
15
16 27
17
18
19
19
43
20

21

29
30
31
22

38
23

39

24

25
26 40
41

42

1736

Figure 7A-I. Nose Gear Oleo Strut Assembly (cont)

Reissued: 1/15/81 2H9 LANDING GEAR AND BRAKE SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

posed. Secure the plate with the snap ring (32), lubricate and install the "O" ring
(28) on the upper end of the tube.
e. Insert the orifice tube (30) up through the bottom of the cylinder (23). With
the tube exposed through the top of the cylinder, install the lock washer (19) and
insert roll pin (18) through the lock washer into the piston. Install the tube lock
nut (16) finger tight at this time.
f. The fork (42)and tube (39)assemblymay be assembled byinstallingthe tube
components on the tube. In order slide onto the tube, the snap ring (38), washer
(37), lower bearing (34) with outer and inner "O" rings (33and 35)andupperbear-
ing (29). Align the lock pin holes in the upper bearing with the pin holes in the
piston tube (39) and install pins (27).
g. Lubricate the inner wall of the cylinder(23) withhydraulic fluid. Carefully
insert the piston tube assembly into the bottom of the cylinder, allowing the ori-
fice tube to guide itself into the fork tube, until the snap ring (38) can be installed
in the annular slot at the bottom of the cylinder. Install wiper strip (36), slide
washer (37) into position and secure assembly with snap ing (38).
h. At the top of the cylinder (23), tighten (torque) the orfice tube lock nut (16).
i. Ascertain that bushings are installed in the upper and lower torque links
(24 and 26) and then install both links. The torque link bolt assemblies should be
lubricated and installed with the flat of the bolt head hex adjacent to the milled
stop on the wide end of the link. Tighten the bolts only tight enough to allow no
side play in the link, yet be free enough to rotate.
j. Ascertain that the upper and lower oleo housing bushings (20 and 22) are.
installed. Install the cylinder into the oleo housing, position spacer washer(s)
(43) over the top of the cylinder and secure with snap ring (17). Install spacer
washers as required to obtain .0 to .015 of an inch thrust of the cylinder within
the housing.
k. At the top of the oleo housing, install on the cylinder the aligner guide brack-
et (12) and steering arm (11). Install cap bolts (1), tighten 20 to 25 inch pounds
torque and safety with MS20995C40 wire (2).
l. Install the shimmy dampener and safety.
m. Lubricate the gear assembly (Refer to Lubrication Chart, Section II).
n. Compress and extend the strut several times to ascertain that the strut will
operate freely. Weight of the gear wheel and fork should allow the strut to extend.
o. Service the oleo strut with fluid and air. (Refer to Oleo Struts, Section II.)
p. Checknosegearfor alignment (Referto Paragraph '7A-14)andgear operation.

7A-9. REMOVAL OF NOSE LANDING GEAR. (Refer to Figure 7A-2.)

a. Remove the engine cowling by the following procedure:
1. Release the fasteners on each side and at the top aft end of the cowl.
2. Lift the aft end of the top cowl and then slide it forward to release the

Reissued: 1/15/81 2H10 LANDING GEAR AND BRAKE SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

SEE VIEW A

FORCLARITY

SEEVIEW A

1. ROD, STEERING
2. JAM NUT
3. BOLT AND NUT ASSEMBLY
4. STEERING BELLCRANK
5. BUSHING. STEERINGARM
6. BEARING,SPRING ROLLER
7. BOLT,WASHER, NUT,
AND COTTERPIN
8. CAP, AIR VALVE
9. BODY,AIR VALVE
10. SAFETYWIRE
11. CAP BOLT AND WASHER
12. ROLLER,ALIGNERGUIDE
13. BOLTASSEMBLY
(SEE VIEWS A & B)
14. BRACKET,ALIGNER
15. SPRING, INNER
16. ARM, STEERING
17. SPRING OUTER
18. BOLT, WASHERS, NUT,
AND COTTER PIN

Figure 7A-2. Nose Gear Installation

Interim Revision: February 15, 1995 LANDINGGEAR AND BRAKE SYSTEM

2H11
 PIPER CHEROKEE SERVICE MANUAL

BUNGEEASSEMBLY(1974MODELSANDUP)

VIEWA

VIEWB VIEWC
PRIORTO 1974 VIEWB ANDC 1974MODELSANDUP

19.LINK,UPPER BUSHING,
37. BOLT,WASHERS,
20. ROD,PISTON SHOULDER NUT,ANDCOTTERPIN
BUSHING,
21. BOLT,WASHERS,NUT, 38. BOLTANDNUT
ANDCOTTERPIN ANDNUT
39. BOLT,WASHERS,
22. LINK,LOWER 40. JAMNUT
23. WHEEL 41.JAM NUT
24. TIRE 42. SPRING,DOWNLOCK
25. FORK 43. FITTING,DOWNLOCKHOOK
26. SHIMMYDAMPENER 44. RODENDBEARING
27. BOLT,WASHER,NUT, 45.JAM NUT
AND COTTER PIN 46. ROD,ACTUATOR
28. BRACKET,SHIMMYDAMPENER 47. ROD,RETRACTION
29. BOLT,WASHERS,NUT, 48. JAMNUT
ANDCOTTERPIN 49. RODENDBEARING
30. JAM NUT 50. RETRACTION GEARDOOR
ASSEMBLY,
31. RODENDBEARING 51.SPRING
32. DRAGLINK,LOWER 52.CYLINDER,HYDRAULIC
33. BOLT,WASHERS,NUT, 53.ARM,SPRING
ANDCOTTERPIN 54. HOUSING,STRUT
34. BOLT,WASHERS,NUT, 55. ENGINEMOUNT
ANDCOTTERPIN 56. GEARUP STOP
35. DRAGLINK,UPPER
36. GEARDOORS

Figure 7A-2. Nose Gear Installation (cont.)

Interim Revision: February 15. 1995 LANDINGGEARAND BRAKE SYSTEM

2H12
 PIPER CHEROKEE SERVICE MANUAL

two stud type front fasteners. Remove the top cowl.

3. Disconnect the electrical lead to the landing light at the quick discon-
nect at the left inside of the bottom cowl.
4. Disconnect the nose landing gear door control rods at each door by re-
moving the connecting bolts with nuts and washers.
.. Remove the bottom cowl support screws, two located at.the side of each
gear door hinge.
6. Remove the bottom cowl attaching screws from around its aft end and
remove cowl.
b. Place the airplane on jacks. (Refer to Jacking; Section II.)
c. Disconnect the two gear tension springs (15 and 17) from the spring arm
(53) that is attached to the right side of the strut housing (54).
d. Retract nose gear slightly to remove the gear from its downlocked position.
e. To remove the upper and lower drag links (32 and 35), the following pro-
cedure may be used:
1. Disconnect the rod end (44) of the hydraulic cylinder (52) from the down-
lock fitting (43) by removing nut and bolt that connects these two units.
2. Retract the gear and disconnect the gear downlock spring (42) from the
upper drag link (35).
3. Remove the gear tension spring arm (53) from the right side of the oleo
housing (54) and lower drag link (32) by removing the cotter pin, nut and washer
from the bolt (29) that connects the drag link to the housing. Slide the arm and
spacer washer from the bolt.
4. Remove the cotter pins, washers and nuts from the bolts that secure the
upper drag link (35) to the engine mount (55).
5. Slide the attachment bolts from the upper and lower drag links and re-
move the links.
f. With the lower drag link (32) disconnected from the gear oleo housing (54),
the housing may be removed by removing cotter pins, nuts, washers, and bolts
(7 and 33) at the attachment points on each side of the housing at the engine mount.
g. The steering bellcrank (4) may be removed by removing the nut and bolt (3)
at the steering rod, and the bolt assembly(13) with bushing at the bellcrankpivot point.

7A-10. CLEANING, INSPECTION AND REPAIR OF NOSE LANDINGGEAR

a. Clean all parts with a suitable dry type cleaning solvent.
b. Inspect the gear components for the following unfavorable conditions:
1. Bolts, bearings and bushings for excess wear, corrosion and damage.
2. Gear housing, drag links, torque links, and tension spring arm for
cracks, bends or misalignment.
3. Downlock hook for excess wear of the hook and bearing surfaces.
4. Downlock rollerbearing for freedom of movement and excessive wobble.

Reissued: 1/15/81 2H13 LANDING GEAR AND BRAKE SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

c. Inspect the gear tension and downlock hook springsfor the following:
1. Excess wear or corrosion, especially around the hook portion of the springs. A
spring should be rejected if wear or corrosion exceeds one-quarter the diameter of the
spring. Clean away all corrosion and repaint.
2. Check the gear tension springs for load tensions below minimum allowable
tolerances. The minimum allowable tension of the inner spring is 37 pounds pull at 13.75
inches and the outer is 60 pounds pull at 13.75 inches. Measurement is taken from the inner
side of each hook. If it is found that either spring should be rejected, replace both springs.
3. Check the gear downlock hook spring for load tension below minimum
allowable tolerance. The minimum tension of the spring is 10.5 pounds pull at 4.5 inches.
Measurement is also taken from the inner side of each hook.
d. Check the general condition of each limit switch and its actuator, and wiring for
fraying, poor connections or conditions that may lead to failures.
e. Check drag link through center travel by attaching the upper and lower drag links,
setting them on a surface table, and ascertaining that when the stop surfaces of the two links
touch, linkage is not less than .062 to .125 nor more than .125 to .250 of an inch through
center. Should the distance exceed the required through center travel and bolt and bushing
are tight, replace one or both drag links.
f. The shimmy dampener requires no service other than routine inspection. In case of
damage or malfunction, the dampener should be replaced rather than repaired.
g. Repair to the landing gear is limited to reconditioning of parts such as replacing
bearings and bushings, smoothing out minor nicks and scratches, repainting of areas where
paint has chipped or peeled and replacement of parts.

7A-11. INSTALLATIONOF NOSE LANDINGGEAR. (Refer to Figure 7A-2.)

NOTE
When assembling any units of the landing gear; lubricate
bearings, bushings, and friction surfaces with the proper
lubricant as described in Section II.

a. Attach the steering bellcrank (4) with bushing to its mounting plate on the engine
mount (55) securing with the bolt assembly (13). Align the steering bellcrank (4) and the
steering arm bushings (5) by positioning the spacer washers as shown in Figure 7A-2.
Connect the steering rods (1) to the bellcrank (4) and install bolt and nut assemblies (3).
The adjustment, fore and aft of the bellcrank, may be made after the gear has been installed
and riggedand adjusted.
b. To install the gear housing assembly, position the gear so that the bolt attachment
points on the housing (54) align with the attachment points on the engine mount (55).
Install pivot bolts, washers and nuts (7 and 33). Tighten the nuts to a snug fit, yet allowing
the gear to swingfree, and safety.

Reissued: 1/15/81 2H14 LANDING GEAR AND BRAKE SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

c. The drag links (32 and 35) and gear tension spring arm (53) may be installed by the
followingprocedure:
1. Ascertain that the upper and lower links (32 and 35) are assembled with the
downlock hook attached, and the through travel of the links checked according to
paragraph 7A-10.
2. Position the link assembly to allow the bolt holes in the links to align with the
bolt holes in the gear housing and the engine mount. Install the link attachment bolts.
3. Install nuts and washers on the upper link (35) attachment bolts. Tighten the
nuts to allow the links to rotate freely and safety.
4. Check alignment of the downlock hook to determine if it grips the roller bearing
so as not to contact the bolt head, the bearing attachment block or washer. If the downlock
hook is inboard, or it contacts the bolt head, shim between the bearing and the bearing
attachment block with washer AN960-1OL,not to exceed three. The bearing must be free to
rotate, therefore, it may be necessary to replace the bearing retainingbolt with longer bolt,
AN23-36A, depending on the number of washers used. Should the downlock hook be
onboard, or in contact with the bearing attachment block, add one washer, P/N 62833-40
of P/N 62833-41 between the engine mount (55) and upper drag link (35). Washer, P/N
6283341, is to be tried first.
5. Install the gear tension spring arm (53) on the drag link bolt (29) on the right
side of the gear oleo housing (54), secure and safety. A washer is installed on the bolt
between the lower drag link and the arm.
d. Retract and extend the landing gear several times to ascertain smoothness of
operation. Also check that the drag link assembly falls into the through center-locked
position.
e. Retract the gear and connect the gear downlock spring (42) between the downlock
hook (43) and the upper drag link (35).
f. Extend the gear and connect the two gear tension springs (15 and 17) between the
attachment point on the oleo housing (54) and the spring arm (53).
g. Ascertain that the landing gear is lubricated per Lubrication Chart, Section II.
h. Check adjustment of the gear per paragraph 7A-12 or 7A-13.
i. Install engine cowling. (The cowl support jacks located at each forward side of the
nose gear door hinges are adjusted down to contact the cowl surface after attaching screws
are secure.)
j. Retract landing gear and check door operation as per paragraph 7A-18.
k. Check the alignment of the nose gear per paragraph 7A-14.
1. Remove the airplane from jacks.

Reissued: 1/15/81 2H15 LANDINGGEAR AND BRAKE SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

1. STEERIN BELLCRANK 5. JAM NUT . SHIMMY DAMPENER

2. CROSS-OVER TUBE 6. ROD END BEARING 10. STRUT HOUSING
3. STEERING ROD 7. OLT ASSEMBLY 11. SPRING
4. ACTUATOR ROD, CYLINDER 8. DOWNLOCK HOOK

Figure 7A-3. Nose Gear Adjustment (Without Gear Up.Stop)

7A-12. ADJUSTMENT OF NOSE LANDINGGEAR (Without GearUp Stop). (Refer.

to Figure 7A-3.)
a. Place the airplane on jacks. (Refer to Jacking, Section II. )
b. With the gear extended, disconnect the nose gear door retraction rods from
each door by removing the rod attaching bolts. If desired, the lower engine cowl
may be removed to facilitate easier access for adjustments.
c. Retract the landing gear hydro-electrically by turning the master switch
on, raising the emergency gear extension lever and moving the gear selector han -
dle to the up position. Retain the emergency extension lever in the up override
position.
d. Clearance between the strut housing (10) and the cross-over tube (2) where
the steering bellcrank (1) attaches should be 0. 015± 0. 003 of an inch with the
piston of the actuator cylinder bottomed. Should this dimension be incorrect and
it will require more than 0. 010 of an inch to bring the housing to the correct
clearance, then block the gear in the up position, disconnect the piston rod end
bearing from the downlock by removing the attaching bolt, loosen the jam nut on
the end bearing to obtain correct adjustment. Reinstall attaching bolt and safety.
When adjustment requires less than 0. 010 of an inch, the rod end bearing need

Reissued: 1/15/81 2H16 LANDING GEAR AND BRAKE SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

1823
2

12
1. STEERING BELLCRANK 5. JAM NUT 9. BOLT ASSEMBLY
2. STEERING ROD 6. ACTUATOR ROD, CYLINDER 10. DOWNLOCK HOOK
* 3. UPPER DRAG LINK 7. JAM NUT 11. SHIMMY DAMPENER
4. GEAR UP STOP 8. ROD END BEARING 12. STRUT HOUSING

Figure 7A-4. Nose Gear Adjustment (With Gear Up Stop).

not be disconnected and therefore all that will be required is to loosen the jam
nut, place a wrench on the flat at the end of the piston rod and turn to obtain the
correct adjustment.
e. Check rod end bearing for adequate thread engagement and tighten jam nut.
f. With gear extended, adjust shimmy dampener by turningnose wheelagainst
stops and adjusting rod end for adequate travel for both extremes.
g. Remove the airplane from jacks.

7A-13. ADJUSTMENT OF NOSE LANDING GEAR (With Gear Up Stop). (Refer

to Figure 7A-4.) The gear up stop (4) is located just above the gear door re-
traction roller near the lower aft end of the engine.
a. Remove the engine cowl. For removal instructions, refer to paragraph
.7A-9, step a.
b. Place the airplane on jacks. (Refer to Jacking, Section II.)
c. Retract the landing gear hydro-electrically by turning the master switch
on, raising the emergency gear extension lever and moving the gear selector
handle to the UP position. Retain the emergency extension lever in the UP Over-
ride position.

Reissued: 1/ 15/81 2H17 LANDING GEAR AND BRAKE SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

d. Check the adjustment of the gear up stop by placing a carpenters square

with the longest end along the bottom of the fuselage, and the shortest end run-
ning up through the centerline of the wheel axle. Measure up along the square
from the bottom of the fuselage 6.25 ± .25 inches, to determine if the center of
the wheel axle meets this measurement. If this measurement is incorrect, ex-
tend the gear, loosen the jam nut (5) on the gear up stop, and make the required
adjustment by turning the stop.
e. Check the adjustment of the hydraulic cylinder by extending the gear and
removing the nut and bolt (9) from the rod end bearing (8). Loosen the jam nut
that secures the rod end bearing and turn the rod end approximately one thread
in past the safety hole on the cylinder rod (6).
f. Hook-up cylinder rod end bearing and retract gear. Recheck all adjustments
and retighten the jam nut on the gear up stop. When the gear is fully retracted,
the upper drag link (3) should be firmly against the gear up stop. Extend the gear.
g. Adjust shimmy dampener by turningnose wheel against stops and adjusting
the rod end of the dampener for adequate travel to both extremes.
h. Install engine cowling, retract landing gear and check door per paragraph
7A-18.
i. Remove the airplane from jacks.

7A-14. ALIGNMENT OF NOSE LANDING GEAR. On 1974 models the nose wheel
steering has been modified by the addition of the bungee system. This will require some
different adjustment procedures which are included with the regular instructions below.
a. Place the airplane on a smooth level floor that will accommodate the striking of a
chalk line.
b. Ascertain that the nose gear is properly adjusted as given in Paragraph 7A-12 or
7A-13.
c. With the landing gear in the down-locked position, weight proportionally on the
nose gear and the nose wheel facing forward, adjust the steering bellcrank. The bellcrank is
attached at the lower front of the engine mount directly aft of the gear housing and may be
adjusted by looseningits attachment bolt and slidingthe bellcrank fore and aft until it clears
each steering arm rollers by .03 of an inch. Retighten the attachment bolt.
d. Place the airplane on jacks. (Refer to Jacking, Section II.)
e. Level the airplane laterally and longitudinally. (Refer to Leveling,Section II.)
f. From the center point of the tail skid, extend a plumb bob and mark the contact
point on the floor.
g. Extend a chalk line from the mark on the floor below the tail skid to a point
approximately three feet forward of the nose wheel. Allow the line to pass under the wheel
at the center line of the tire. Snap the chalk line.
h. Clamp the rudder pedals to align then in a lateral position. Ascertain that the rudder
pedals are in there neutral position. (Refer to Figure 7A-6 and Table VII-I.)

Reissued: 1/15/81
2H18 LANDING GEAR AND BRAKE SYSTEM
 PIPER CHEROKEE SERVICE MANUAL

A599 1737

See Table VII-I for RudderPedalNeutral Angle

Figure 7A-5. Clamping Rudder Figure 7A-6. Rudder Pedals

Pedals in Neutral Position at Neutral Angle
i. Adjust the rod end bearings of each steering control rod to align the nose wheel with
the chalk line and to bring the rudder pedals into neutral angle fore and aft.
j. On 1974 models install the steering push rods on the pilot's rudder pedals. Adjust
the rods so the lengths are both the same and the rudder pedals are at their neutral position.
(Refer to Table VII-I.)
k. To align the nose wheel straight forward, stand in front of the nose gear and align
the center rib of the tire with the chalk line, or lay a straight edgealong the side of the tire
and parallel the straight edge with the chalk line.
1. On 1974 models install the nose wheel bungees in there neutral position (no load on
the bungee springs.)Adjust bungee rod ends as necessary.
m. Place a bubble protractor against a rudder pedal steering tube to check the neutral
angle as givenin Table VII-I for the perticular model being serviced.
n. On earlier models one end of each rod must be disconnected and the jam nuts
loosened to make any adjustments. Do not attempt to make the adjustment by means of
one rod end bearing, but divide the adjustment between the bearings at each end of each
rod. Check that the rod ends have sufficient thread engagement by ascertainingthat a wire
will not go through the check hole in the rod. Reinstall the rods and tighten the jam nuts.
o. To check the nose gear steering for its maximum right and left travel, mark on each
side of the nose wheel an angle line from the center line and wheel pivot point. (Refer to
Table VII-I for nose wheel turning angle of the perticular model being serviced.) Turn the
wheel to its maximum travel in both directions to check for allowabletravel. Should travel
be exceeded in one direction and not enough in the other direction, check for possible
damage to the gear fork or torque links.
7A-15. REMOVALOF NOSE GEAR DOOR ASSEMBLY. (Refer to Figure 7A-7.)
a. With the nose gear extended, disconnect the door retraction rod (1) from the door
(2) by removing nut, bolt and washers. If desired the bottom cowl may be removed to
facilitate easier removal.

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 PIPERCHEROKEESERVICEMANUAL

1730

1. ROD, DOOR RETRACTION

2. DOOR, GEAR
3. SPRING, TENSION
4. SELLCRANK ASSEMBLY
5 ROLLER ASSEMBLY
6. ROLLER
7. THREADED LINK, ROLLER
8. COTTER PIN
9. GEAR UP STOP

Figure 7A-7. Nose Gear Door Retraction Mechanism

Reissued: 1/15/81 2H20 LANDINGGEAR AND BRAKESYSTEM

 PIPERCHEROKEE
SERVICEMANUAL

b. To remove the door(s) from the cowl, bend the end of the hinge pin straight
and from the other end pull out the pin.
c. The bellcrank assembly (4) of the door retraction mechanism may be re-
moved by removing the attached hardware, disconnecting the door down tension
spring (3) and removing the cotter pins (8) at each end of the pivot tube. Slide
the insulating sleeve and bushing tube from the bellcrank.
d. The roller assembly (5) of the mechanism may be removed by removing the
attached hardware and pivot bolt with insulator.

7A-16. CLEANING, INSPECTION AND REPAIR OF NOSE GEAR DOOR ASSEM-

BLY.
a. Clean all parts with a suitable cleaning solvent.
b. Inspect doors for cracks or damage, loose or damaged hinges and brackets.
c. Inspect door retraction rods for damage and rod end bearing for corrosion.
d. Check the door tension spring for wear and tension below minimum allow-
able tolerance. Reject spring if load tension is below 8.0 pounds pull at 4.75 in-
ches.
e. Check general condition of bellcrank and roller assembly.
f . Repairs to the doors may be replacement of hinges, repair of fiberglass
and painting.
g. Repairs to the retraction mechanism is limited to replacement of parts,
and sanding and painting.

7A-17. INSTALLATION OF NOSE GEAR DOOR ASSEMBLY. (Refer to Figure

7A-7.)
a. The roller assembly (5) of the retraction mechanism may be installed by
first assembling the roller (6), threaded link (7) and rollerlinks (5), and thenin-
stalling this assembly on its mountingbracket. Ascertain that an insulator sleeve
is installed with the attachment bolt and link bolt.
b. The bellcrank assembly (4) of the retraction mechanism may be installed
by positioning the bellcrank between its mounting bushing and inserting the in-
sulator sleeve and bushing tube. Install a cotter pin through each attachment
bushing and the pivot tube. New tubes will require a .070 hole drilled through
each end to facilitate a cotter pin. Use the existing hole in the mounting bushings
as a guide. Do not connect link between roller assembly and bellcrank until time
of door adjustment.
c. Install the gear door(s) by positioning the hinge halves of the door and cowl,
and inserting the hinge pin. It is recommended a new pin be used. Bend the end
of the pin to secure in place.
d. Install the cowl and adjust doors as given in paragraph 7A-18.

Reissued: 1/15/81 2H21 LANDING GEAR AND BRAKE SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

7A-18. ADJUSTMENT OF. NOSE GEAR DOORS

a.. Place the airplane on jacks. (Refer to Jacking, Section II.)
b. Adjust the door retraction rods so thatthe gear will swing throughthe door
opening with a . 12 .06 of an inch clearance between the gear and door at their
closest point. This can best be done with the nose gear down, tension springs
disconnected and operating the nose gear manually.
c. With door clearance adjusted, adjust the link between the roller assembly
and bellcrank assembly so thatthe doors will pull uptightly when gear is full up.
Over-tightening may result in door buckling, however if the link is too loose,
doors will gap in flight.
d. Check all rod ends for adequatethreadengagement, for safetyandtightness
of jam nuts.
e. Remove the airplane from jacks .

7A -19. MAINLANDING GEAR SYSTEM.

7A-.20 ... DISASSEMBLY OF MAIN GEAR OLEO. (Refer to Figure 7A.-8) The
main gear oleo assembly may be removed and disassembled from the gear oleo
housing with the gear removed from or installed on the airplane.
a. Place the airplane on jacks. (Refer to Jacking, Section II.)
b. Place a drip pan under the main gear to catch spillage.
c. Remove the air and fluid from the oleo. To do this, depress the air valve
core pin until strut pressure has diminished, remove the filler plug and with a
small hose siphon as much hydraulic fluid from the strut as possible.
.d. D isconnect the brake. line. at the jint located in the wheel well.,
e. To remove piston tube 25) assembly from oleo housing (11), remove the
upper and lower torque link connecting bolt assembly (3) and separate the links.
Note number and thickness of spacer washer(s) between the two links (15 and 16).
f. Compress the piston tube (25), reach up along the tube and release the snap
ring (24) from the annualar slot at the bottom of the oleo housing.
g. Pull the piston tube(25) with component parts from the cylinder housing.
h. The piston tube (25) components may be removed by reaching in the tube
and pushing out the upper bearing (18) retainer pins (17). Slide off the upper bear-
ing(18), 'lower bearing (20) with "O" rings (19 and 21), wiper (22), washer (23)
and' snap ring (24).
i. To remove the orifice tube (12) from the oleo housing, remove the lock nut
(6) and washer (7) from the top of the housing. Draw the tube with "O" ring (9)
and retainer (8) from the housing.
j. The orifice plate (13) is removed from the bottom of the orifice tube (12)
by releasing the snap ring (14) that holds the plate in position.

Reissued: 1/15/81 2H22 LANDING GEAR AND BRAKE SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

k. To remove the piston tube plug (26) with "0" ring (27) located in the lower end of
the tube, remove the bolt assembly and insert a rod up through the hole in the body of the
fork (28), pushing the plug out through the top of the tube.

7A-21. CLEANING,INSPECTIONAND REPAIR OF MAIN GEAR OLEO.

a. Clean all parts with a suitable dry type cleaningsolvent.
b. Inspect the landing gear oleo assembly component for the following:
1. Bearingsand bushings for excess wear, corrosion, scratches and overall damage.
2. Retaining pins for wear and damage.
3. Lock rings for cracks, burrs, etc.
4. Cylinder and orifice tube for corrosion, scratches, nicks and excess wear.
5. Orifice plate for hole restriction.
6. Fork tube for corrosion, scratches, nicks, dents and misalignment.
7. Air valve general condition.
c. Repair of the oleo is limited to smoothing out minor scratches, nicks and dents and
replacement of parts. (See Figure 7A-26 and Table VIIA-III for bearingreplacement.)

7A-22. ASSEMBLYOF MAINGEAR OLEO. (Refer to Figure 7A-8.)

a. Ascertain that all parts are cleaned and inspected.
b. To install the piston tube plug (26), first lubricate the plug "O" ring (27) with
hydraulic fluid (MIL-H-5606) and install it on the plug. Lubricate the inside wall of the
tube. Insert the plug into the top of the tube (25) and push it to the fork end. Align the bolt
holes of the fork, tube and plug, and install bolt assembly.
c. If desired, cement a cork in the hole in the bottom of the fork body to prevent dirt
from entering between the fork and tube.
d. To assemble the components of the orifice tube (12) insert the orifice plate (13)
into the bottom of the tube and secure with snap ring (14).
e. To install the tube (12) in the oleo housing (11), insert the tube up through the
housing. With the end of the tube exposed through the top of the housing, install the "O"
ring (9), retainer (8), washer (7), and lock nut (6). Tighten lock nut only finger tight at this
time.
f. Assemble the components of the piston tube (25) on the tube by placing, in order,
the snap ring (24), washer (23), lower bearing (20) with outer and inner "0" rings (19 and
21) and upper bearing (18). Align the two .125 diameter holes and the lock pin holes with
the corresponding holes in the piston tube (25) and install pins (17) without force. The
outer surface of the pins must not protrude beyond the outer diameter of the bearing (18).
g. Lubricate the wall of the cylinder oleo housing (11) and tube (25), and carefully
insert the tube assembly into the housing, guiding the orifice tube (12) into the piston tube
until the snap ring (24) can be installed in the annular slot at the lower end of the housing.
Install the wiper strip (22); slide the washer (23) into position and secure the assembly with
snap ring (24).

Reissued: 1/15/81
2H23 LANDINGGEARANDBRAKESYSTEM
 INTENTIONALLYLEFTBLANK

Reissued: 1/15/81 2H24

 PIPER CHEROKEE SERVICE MANUAL

1711

. BRACKET SWITCH ACTUATOR

2. BOLT WASHERS, NUT AND COTTER PIN
3. BOLT, WASHERS NUT AND COTTER PIN
4. BOLT WASHERS, NUT AND COTTER PIN
5. AXLE NUT
6. NUT
7. WASHER
8. RETAINER
9. "C" RINS
10. VALVE ASSEMBLY
11 . HOUSING OLEO STRUT
12. ORIFICE TUBE
13. PLATE ORIFICE
14. SNAP RING
15. LINK ASSEMBLY. UPPER
16. LINK ASSEMBLY, LOWER
17. RETAINER PIN, BEARING
18. BEARING UPPER
19. "0" RING, OUTER
20. BEARING. LOWER
21. "O" RING, INNER
22. WIPER STRIP
23. WASHER
24. SNAP RING
25. PISTON TUBE
26. PLUG
27. "O" RING
22. FORK ASSEMBLY

Figure 7A-8. Main Gear Oleo Strut Assembly

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 PIPER CHEROKEE SERVICE MANUAL

1713

1717

17

19s
19s
20

23
24

25

26
27

21

Figure 7A-8. Main Gear Oleo Strut Assembly (cont.)

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 PIPER CHEROKEE SERVICE MANUAL

h. At the top of the housing, tighten the lock nut (6).

i. Ascertain that the bushings are installed in the upper and lower torque links (1 and
16) and then install links. The torque link bolt assemblies(2, 3 and 4) should be lubricated
and installed with the flat of the bolt head hex adjacent to the milled stop of the wide end
of the link. (Use the same thickness of spacer washers between the two links as those
removed to maintain correct wheel alignment.) Tighten the bolts only tight enough to allow
no side play in the links, yet be free enough to rotate.
j. Connect the brake line and bleed the brakes per paragraph 7A-73.
k. Lubricate the gear assembly. (Refer to Lubrication Chart, Section II.)
1. Compress and extend the strut several times to ascertain that the strut will operate
freely. The weight of the gear wheel and fork should allow the strut to extend.
m. Servicethe oleo strut with fluid and air. (Refer to Oleo Struts, Section II.)
n. Check main gear alignment (refer to paragraph 7A-27) and gear operation.
o. Remove the airplane from jacks.

7A-23. REMOVALOF MAIN LANDINGGEAR. (Refer to Figure 7A-9.)

a. Place the airplane on jacks. (Refer to Jacking, Section II.)
b. The side brace link assemblymay be removed by the followingprocedure:
1. With the gear in the extended position, disconnect the gear downlock spring
(18).
2. Disconnect the rod end (46) of the actuating cylinder (24) from the retraction
fitting (21) of the upper side brace link (28) by removing the nut, washer and bolt (47) with
bushing and spring swivel(20).
3. Disconnect the lower side brace link (33) from the gear housing (13) by
removing the attachment nut, washer and bolt (7). Note bushings on each side of the end
bearing.
4. Disconnect the upper side brace link (28) from the side brace support fitting
stud (26) by removing the cotter pin, nut, washer and attachment bolt (25).
5. The side brace support fitting may be removed by removing the cap bolts that
secure the fitting to the web of the spar.
6. Remove the assembly, and further disassembleand inspect as needed.
c. The landing gear housing (13) with components may be removed by the following
procedure:
1. Disconnect the brake line (42) at its upper end in the wheel well.
2. Disconnect the gear door actuating rod (38) at the gear housing.
3. Remove the access plate located on the underside of the wing, aft of landing
gear.

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 PIPER CHEROKEESERVICE MANUAL

NOTE
It may have been necessaryto use specal
landing gearattachment hardware during
assembly of the aircraft due to
manufacturing tolerances. Therfore,
special attention should be given when
removing hardware to inspect and insure
the same diameter hardware is used upon
reassembly. Standard AN4 or AN5 bolts
are replaced by alternate oversized bolts
NAS3004 or NAS3005 respectively
when oversized hardware is required.

Figure 7A-9. Main Gear Installation

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 PIPER CHEROKEESERVICE MANUAL

1.SUPPORT FITTING. AFT

2. SNAP RING
3. BEARING
4. RETAINER, TUBE ASSEMBL
5. FITTING GREASE
6. HINGE, GEARDOOR
7.BOLT, WASHERS AND NUT
8.LINK, UPPER
9. WASHER,
SPACER
10. LINK, LOWER
11. DOOR,GEAR
12. NUT
13. HOUSING, STRUt
14. PLUG. HYDRAULIC FLUID
15. VALVE ASSEMBLY
16. SUPPORT FITTINGS, FORWARD
17. FITTING. GREASE
18. SPRING, DOWNLOCK
19. TURNBUCKLE
20. SWIVEL ASSEMBLY
21. RETRACTICN FITTING
22. JAM NUT
23. ROD,`PISTON
24. CYLINDER, HYDRAULIC ACTUATING
25. BOLT, WASHERS, NUT AND COTTER PIN
26. STUD, SIDE BRACE SUPPORT
27. SUPPORT BRAKE-
28. LINK, UPPER SIDE BRACE SKETCHA
29. PLATE
30. HOOK, DOWNLOCK
31. BOLT, WASHERS, NUT AND COTTER PIN
32. PIN, DOWNLOCK
33. LINK, LOWER SIDE BRACE
34. BRACKET, SPRING
35. SWITCH. SAFETY 1734
36. ACTUATOR, SAFETY SWITCH
37. BOLT, WASHERS. NUT AND COTTER PIN
38. ROD, GEAR DOOR 21
39 . BOLT, WASHERS. NUT AND COTTER PIN
40. FORK GEAR
41. CLAMP 19
42. HOSE. BRAKE
43. BRAKE HOUSING
44J. BRAKE DISC 58
45. TIRE
46. ROD END 56 57 33
. BOLT,WASHER. NUT AND BUSHING
e. BOLT
49. SHIM WASHER
50. BOLT
51. WASHER
52. WASHER
53. BEARING, FORWARD SUPPORT
54. BEARING, AFT SUPPORT
55. SNAP RING
56. ROD END BEARING 31 28
57. JAM NUT
58. BRACKET, SWITCH
59. CLIP, SAFETY

SKETCHB

Figure 7A-9. Main Gear Installation(cont.)

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 PIPER CHEROKEESERV CE MANUAL

4. If not previously disconnected, disconnect the lower side brace link (33)
from the gear housing.
5. Disconnect the forward support fitting (16) of the housing (13) from the
web of the main spar by removing the fitting attachment bolts.
6. Remove the retainer tube (4) in the aft support fitting (1) that supports
the aft arm of the housing by reaching through the access opening on the underside
of the wing, through the hole in the web and removing the bolt (48) that secures
the tube in the housing. Insert a hook through the bolt hole in the tube, and slide
it aft from the support fitting. Remove the tube from the wing. Note the number
of spacer washers (52) between the arm and support fitting (1).
7. Allow the gear to drop down removing it from the wing.
8. The aft support fitting (1) may be removed by holding the nuts, reach-
ing through the access opening, and removing the fitting attachment bolts.
9. The forward support fitting (16) may be removed from the arm of the
housing by removing the bolt and washer from the base side of the fitting. Slide
the fitting from the arm. Remove the washer (52) from the arm.
d. Either bearing (53 or 54) installed in the support fittings may be removed
by removing the snap rings (2) that hold the bearing in the housing. Push the
bearing from the housing.

7A-24. CLEANING, INSPECTION AND REPAIR OF MAIN LANDINGGEAR.

a. Clean all parts with a suitable dry type cleaning solvent.
b. Inspect the gear components for the following unfavorable conditions:
1. Bolts, bearing and bushings for excess wear, corrosion and damage.
2. Gear housing, side brace links, torque links and attachment plates for
cracks, bends or misalignment.
3. Downlock hook for excessive wear of the bearing surfaces.
c. Inspect the gear downlock spring for the following:
1. Excessive wear or corrosion, especially around the hook portion of the
spring. A spring should be rejected if wear or corrosion exceeds one-quarter
the diameter of the spring. Clean away all corrosion and repaint.
2. Check the spring for load tensions below minimumallowable tolerance.
The minimum tension of the spring is 48 pounds pull at 7.9 inches. Measurement is taken
from the inner side of each hook.
d. Check the general condition of each limit switch and its actuator, and wir-
ing for fraying, poor connections or conditions that may lead to failures.
e. Check side brace link through centertravel byattaching the upper and lower
links, setting them on a surface table, and ascertaining that when the stop sur-
faces of the two links touch, linkage is not less than .062 nor more than . 125 of
an inch through center. Should the distance exceed the required through center
travel and bolt and bushings are tight, replace one or both links.

Reissued: 1/15/81 216 LANDING GEAR AND BRAKE SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

f. With the side brace links assembled and checked, ascertain that when the
stop surfaces of the two links contact, the clearance between each downlock hook
and the flat of the downlock pin is not less than 0.010 of an inch. Should clear-
ance be less than that required, the hook only may be filed not to exceed a gap
of more than 0.025 of an inch. The maximum allowable clearance between each
hook and the downlock pin that are service worn is 0.055 of an inch. Should
clearance be more than 0.055 of an inch, replace the pin, check clearance and
then if still beyond tolerance, replace hooks. The gap between each hook should
be equal.
g. Repair of the landing gear is limited to reconditioning of parts such as
replacing components, bearings and bushings, smoothing out minor nicks and
scratches and repainting areas where paint has chipped or peeled.

7A-25. INSTALLATION OF MAIN LANDING GEAR. (Refer to Figure 7A-9.)

NOTE

When assembling components of the landing gear, lu-

bricate bearings, bushings and friction surfaces with
proper lubricant as described in Section II.

a. Insert a gear support bearing (53 or 54) in each support fitting (1 or 16)
and secure with snap rings (2). Check bearing (53) for excess end play, shim as
necessary with shim washers (49) (P/N 62833-44).
b. The gear housing may be installed in the wheel well of the wing by the fol-
lowing procedure:
1. Place a spacer washer (52) and then the forward support fitting (16) on
the forward arm of the housing. Ascertain that the barrel nut (55) is positioned
in the arm and insert the attachment bolt through washer (51) and the fitting into
the arm. Tighten bolt and ascertain that the bearing is free to rotate.
2. Position the aft support fitting (1) at its attachment point in the wheel
well and secure with bolts, washers and nuts. Install the nuts and washers by
reaching through the access hole on the underside of the wing.
3. With the retainer tube (4) for the aft arm of the housing in hand, reach
up through the access opening and insert the tube into the support fitting (1)
through the hole in the web.
4. Position the gear housing up in the wheel well and install the forward
support fitting (16) bolts and washers. (One each AN960-416 and AN960-416L
washer per bolt.)
5. Push the retainer tube into the arm of the housingand secure with bolt.

Reissued:1/15/81 2I7 LANDING GEAR AND BRAKE SYSTEM

 PIPER CHEROKEESERVICEMANUAL

6. Check that the gear rotates freely in its support fitings and recheck
thrust.
7. Connect the brake line to its mating line in the wheel well and bleed
brakes as given in paragraph 7A-73.
c. The gear side brace link assembly may be installed by the following pro-
cedure:
1.' Position the link support bracket (27) with swivel stud (26) installed at
its attachment point on the web of the spar and secure with bolts and washers.

NOTE

When installing a new wing, it will be necessary to

back drill two (2) holes 0.250 inch and countersink
100° x .499 through the spar cap. (Screw head should
be flush with spar). Use hole in the support bracket
as a guide in the drilling.

2. Ascertain that the upper and lower links(28 and 33)are assembled with
downlock hook (30), retraction fitting (21), etc. attached, and the through travel
of the links and downlock hook clearance checked according to paragraph 7A-24.
3. Attach the upper link to the swivel stud of the support fitting and secure.
with bolt, bushing, washer, nut and cotter pin.
4. The actuating cylinder rod end bearing (46) and lower side brace link
(33) may be attached respectively to the retraction fitting (21) and gear housing
during the adjustment of the landing gear.
d. Ascertain that the landing gear is lubricated per Lubrication Chart.
e. Check adjustment of the landing gear per paragraph 7A-26.
f. Check alignment of the wheel per paragraph.7A-27_
g. Install the access plate on the underside of the wingand remove the airplane
from jacks.

7A-26. ADJUSTMENT OF MAIN LANDING GEAR.

- a..Place the airplane on jacks. (Refer to Jacking, Section II.)
b. Level the airplane laterally and longitudinally. (Refer to Leveling, Section II.)
c. Disconnect the gear door actuating rods at either the door or the housing,
as desired, by removing the rod attachment bolt. Secure the door out of the way.

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 PIPERCHEROKEESERVICEMANUAL

d. Adjust the gear oleo housing to obtain a vertical position with the airplane
level (90 degrees to horizontal). To do this, set 90 degrees on a bubble protrac-
tor, place the protractoralong the side of the gear piston tube and adjust the end
bearing of the lower side brace link allowing thebubble of the protractor to center
when the end bearing isconnected tothe gear housing. This shouldallow anangle
of 83 degrees between the gear housing and the spar cap of the wing. Place a bush-
ing on each side of the end bearing and secure with bolt, washer and nut.
e. Check that the rod end has sufficient thread engagement in the end bearing,
align the flat sides of the bearing casting with the flat side of the bearing and
tighten the jam nut.
f. Adjust the turnbuckle of the downlock mechanism by first ascertaining that
the gear is down and locked, and then move the retraction fitting outboard until
it contacts the stop slot of the side brace link. Hold the fitting in this position
and turn the turnbuckle barreluntil the downlock hooks make contact with the lock
pin. Safety the turnbuckle.
g. For easier adjustment of the downlock limit switch, it may be set at this
time as given in paragraph 7A-36.
h. Retract and extend the gear manually several times to ascertain that the
side brace link falls through center, the downlock hook falls into position and
there is no binding of the gear assembly.
i. The gear should beadjustedin the upposition to allow the gear fork topress
lightly into the rubber bumper pad on the wing. The adjustment may be accom-
plished as follows:

NOTE

If it requires less than .025 of an inch to move the

gear into the correct adjustment, steps 2 and 6 thru
8 need only be followed.

1. Ascertain that the rod end bearing of the actuating cylinder is discon-
nected from the retraction fitting.
2. Actuate the hydraulic system to bring the hydraulic cylinder to the up
position by turning the master switch on, raising the emergency gear extension
lever and moving the gear selector handle to the up position. Retain the emer-
gency extension lever in the up override position. The piston of the cylinder
should be bottomed.
3. Raise the gear by pushing up onthe retraction fitting, thus disengaging
the hooks, and pushing up on the pivot point at the bottom of the side brace links
to bring the links out of the locked position. Raise the gear until the fork presses
lightly into the rubber pad. Retain the gear in this position.

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 PIPER CHEROKEESERVICEMANUAL

.
BRACKET
RIVET

SKETCHB

Figure A -10. Aligning Main Gear

Reissued: 1/15/81 2110 LANDING GEAR AND BRAKE SYSTEM

 PIPER CHEROKEESERVICE MANUAL.

4. Loosen the jam nut on the piston rod of the actuating cylinder and turn
the rod end bearing in or out to allow a slip fit of the attachment bolt.
5. Install with the attachment bolt, bushing, spring swivel and secure with
washer and nut. Install the gear downlock spring.
6. Whenthe gear is towithin .125 of aninch ofcorrect adjustment, the rod
end need not be disconnected and therefore all that will be required is to loosen
the jam nut, place a wrench on the flat at the endof the piston rod and turn to ob-
tain correct adjustment.
7. Check the rod end bearing for adequate thread engagement and tighten
jam nut.
8. If the downlock limit switch is properlyadjusted, retract and extend the
gear hydro-electrically to ascertain that the gear operates properly.

7A-27. ALIGNMENT OF MAIN LANDING GEAR.

a. Place a straightedge no less than twelve feet long across the front of both
main landing gear wheels. Butt the straightedge against the tire at the hub level
of the landing gear wheels. Jack the airplane up just high enough to obtain a six
and one-half inch dimension between the centerline of the strut piston and the
.centerline of the center pivot bolt of the gear torque links. (Refer to Figure 7A- 10.)
Devise a support to hold the straightedge in this position.
b. Set a square against the straightedge and check to see if its outstanding leg
bears on the front and rear side of the brake disc. (It may be necessary to re-
move the brake assembly to have clear access to the disc.) (Refer to Figure
7A-10.) If it touches both forward and rear flange, the landing gear is correctly
aligned. The toe-in for the main landing gear wheels is 0 ± 1/2 degrees.

NOTE

A carpenter's square, because of its especially long

legs, is recommended for checking main landing gear
wheel alignment.

c. If the square contacts the rear side of the disc, leaving a gapbetween it and
the front flange, the wheel is toed-out. If a gap appears at the rear flange, the
wheel is toed-in.
d. To rectify the toe-in or toe-out condition, remove the bolt connecting the
upper and lower torque links and remove or add spacerwashers to move the wheel
in the desired direction. Refer to the chart on the following page.

Reissued:1/15/81 2111 LANDING GEAR AND BRAKE SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

TOE-IN - TOE-OUT CORRECTION CHART

TOE-IN . .

TOE -OUT SHIM WASHERS WASHERS AN' 174

ANGLE WASHERS UNDER HEAD UNDER NUT BOLT
.

0 AN960-416 AN960-416 -(3) -14

0033 ' AN960-416 AN960-416 AN960-416 (2) -14

0048 ' AN960-416L AN960-416 AN960-416 -14

AN960-416

1°04 ' AN960-416 (2) AN960-416 AN960-416 -14

1°19 ' AN960 -416L AN960-416L AN960-416 -14

AN960-416 (2)

1°35 ' AN960-416 (3) AN960-416 AN960-416 (2) -15

2°05'
Max. Allow AN960-416 (4) AN960-416 AN960-416 -15

AN960-416L Washers .031 Thick

AN960-416 Washers .062 Thick

e. Should a condition exist that all spacer washers have been removed and it
is still necessary to move the wheel further in or out, then it will be necessary
to turn the torque link assembly over. This will put the link connecting point on
the opposite side allowing the use of spacers to go in the same direction.
f. Recheck wheel alignment. If the alignment is correct, safety the castellated
nut with cotter pin.
g. If a new link on the top left main gear had to be installed or it had to be re -
versed during the alignment check, it will bienecessary to check the gear safety
switch (squat switch) bracket for engagement and locking in place. If the large
machine surface of the link is inboard, the bracket is mountedwith the small rivet
hole next to link. (Refer to Sketch "A", Figure 7A-10) This should be aligned on
the centerline of link and a hole drilled to .096 of an inch, .15 of an inch deep.
Insert an MS20426AD3-3 rivet in the hole. This locking rivet is held in place by
the flat washer, castellated nut and cotter pin. If link has to be reversed, then
the bracket and bolt are-also reversed. (Refer to Sketch "B", Figure 7A-10.)

Reissued: 1/15/81 2112 LANDINGGEAR AND BRAKE SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

h. Check adjustment of landing gear safety switch (squat switch) per paragraph
7A-37.

7A-28. REMOVAL OF MAIN GEAR DOOR ASSEMBLY,

a. With the landing gear extended, disconnect the door retraction rod from the
door by removing nut, washers and bolt.
b. Remove the door from the wing panel bybending the door hinge pin straight
and from the other end pulling out the pin.
c. The door retraction rod may be removed from the gear housing by cutting
the safety wire and removing the attachment bolt and washer. Note the number
of washers between rod end bearing and housing.

7A-29. CLEANING, INSPECTION AND REPAIR OF MAIN GEAR DOOR ASSEM-

BLY.
a. Clean the door and retraction rod with a suitable cleaning solvent.
b. Inspect the door for cracks or damage, loose or damaged hinges and brackets.
c. Inspect the door retraction rod and end bearing for damage and corrosion.
d. Repairs to a door may be replacement of hinge, repair of fiberglass and
painting.

7A-30. INSTALLATION OF MAIN GEAR DOOR ASSEMBLY.

a. Install the door by positioning the hinge halves of the door and wing, and in-
serting the hinge pin. It is recommended a new pin be used. Bend the end of the
pin to secure in place.
b. Install the door retraction rod bypositioningthe rod at its attachment points
at the door and strut housing. At the door attachment, thin washers are inserted
at each side of the rod end bearing and it is secured with bolt, washer and nut.
At the strut housing, place washers between rod end bearing and housing not to
exceed . 12 of an inch to obtain proper clearance and secure with bolt. Safety bolt
with MS20995C41 wire.
c. Check that the all around clearance between the door and the wing skin is
not less than .032 of an inch.

Reissued: 1/15/81 2I13 LANDING GEAR AND BRAKE SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

7A-31. ADJUSTMENT OF MAIN GEAR DOOR ASSEMBLY.

a. Place the airplane on jacks. (Refer to Jacking. Section II.)
b. Ascertain that the main gear is properly adjusted for gear up as given in paragraph
7A-26.
c. Adjust the retraction rod end at the door so that the,door will pull up tightly when
the gear is full up. Over-tightening may result in door buckling: however if the door is too
loose, it will gap in flight.
d. Check all rod ends for adequate thread engagement. for safety and tightness of
jam nuts.
e. Remove the airplane from jacks.

7A-32. LANDING GEAR LIMIT SWITCHES.

NOTE
All adjustments of the limit switches should be made with
the airplane on jacks. (Refer to Jacking. Section II.)

NOTE
Do not bend the actuator springs mounted on the limit
switches.

7A-33. ADJUSTMENT OF NOSE GEAR UP LIMIT SWITCH. The gear up limit switch is
mounted on a bracket on the engine mount above the point where the-right side of the upper
drag link attaches to the engine mount.
a. To facilitate adjustment of the limit switch. disconnect the gear doors or remove the
bottom cowl. as desired.
b. Retract the landing gear hydro-electrically by turning the master switch on.
raising the emergency gear extension lever and moving the gear selector handle to the up
position. Retain the emergency extension lever in the up position and turn the master switch
off.
c.' Block the nose gear in, the up position and then slowly release the emergency
extension lever. This will relieve hydraulic pressure and the main gears will drop.
d. Rig the nose gear up limit switch so that the switch activates when the nose gear is
within .12 of an inch of the full up position per rigging instructions given in paragraphs
7A-12 or 7A-13.

Revised: 4 23 84 2114 LANDING GEAR AND BRAKE SYSTEM

 PIPER CHEROKEESERVICEMANUAL

A127
_

Figure 7A- 11. Adjustment of Nose Figure 7A-12. Adjustment of Main

Gear Down Limit Switch Gear Down Limit Switch

e. Loosen the attachment screws of the switch and rotate the switch toward
the actuator tang until it is heard to actuate. Retighten the attachment screws
of the switch.
f. Manually move the gear up and down only as far as necessary to ascertain
that the switch actuates at the correct position. Remove the block from under
the gear and allow it to slowly extend.
g. Retract the gear hydro-electrically and ascertain that the yellow transit
light will go out when the gear has retracted and the pump has shut off.

7A-34. ADJUSTMENT OF NOSE GEAR DOWN LIMIT SWITCH. The gear down
limit switch is mounted on the horizontal support tube of the engine mount that
runs between the right attachment points of the gear housing and upper drag link.
a. Ascertain that the gear is down and locked.
b. The down limit switch should actuate only after the leading edge of the down-
lock hook, when moving to the locked position, has passed the downlock roller
by .06 of an inch. Refer to Figure 7A-11.) Position the hook at this location
in relation to the roller bymoving the actuator piston manually toward the up po-
sition. The downlock spring may be disconnected, if desired.
c. Loosen the attachment screws of the actuator located on the downlock hook
and move it toward the switch until it is heard to actuate. Retighten the actuator
screws.
d. Manually move the hook from the locked to the unlocked position and ascer-

Reissued:1/15/81 2I15 LANDING GEAR AND BRAKE SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

tain that the switch actuates at the correct location of the hook,
e. Retract and extend the gar hydro-electrically by turning the master switch
on, raising the emergency gear extension lever and moving thegear selector han-
dle to the up position. As the gear begins to retract the green light below the se-
lector should go out and the yellow transit light at the top of the instrument panel
should come on.

7A -35. ADJUSTMENT OF MAIN GEAR UP LIMIT SWITCH.

A gear up limit switch is located in each wheel well above the gear door
hinge. There is no adjustment of these switches other than check that the gear,
when retracting, will actuate the switch within .88 of an inch of full up. Switch
operation turns the yellow transit light out.

.7A-36. ADJUSTMENT OF MAIN GEAR DOWN LIMIT SWITCH. A gear .down

limit switch is mounted on a bracket which is attached to the lower drag link of
each main gear. The switch should be adjusted to allow it to actuate thus turning
on the green indicator light within the cockpit when the downlock hook has entered
the locked position and is within .025 to .035 of an inch of contacting the down-
lock pin. (Refer to Figure 7A-12.) Adjustment of the switch may be as follows:
a. Ascertain that the main gear downlock is properly adjusted as described
in paragraph 7A-26.
b. Raise the airplane on jacks. (Refer to Jacing, Section II.)
c. Ascertain that the landing gear is down and pressure is relieved from the
hydraulic system. To relieve pressure, hold down the emergency extender lever.
d. Raise the downlock hook assembly and place a .030 of an inch feeler gauge
between the horizontal surface of the hook that is next to the switch (The surface
that contacts the downlock pin.) and the rounded surface of the pin. Lower the
hook and allow it to rest on the feeler gauge.
e. Loosen the attaching screws of the switch and, while pushing up on the
center of the link assembly, rotate the switch toward the hook until it is heard
to actuate. Retighten the attaching screws of the switch.
f. Manually move the hook assembly up from the pin until the hook nearly dis-
engages from the pin. Then, with pressure against the bottom of the link assem-
bly, move back to ascertain that the switch actuates within .025 to .035 of an
inch of full lock.
g. Retract and extend the gear hydro-electrically by turningthe master switch
on, raising the emergency gear extension lever and moving the gear selector
handle to the up position. As the gear begins to retract, the green light below
the selector should go out and the yellow transit light at the top of the instrument
panel should come on.

Reissued: 1/ 15/81 2I16 LANDING GEAR AND BRAKE SYSTEM

 )

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 PIPER CHEROKEE
SERVICEMANUAL

7A-37. ADJUSTMENTOF LANDINGGEAR SAFETY SWITCH(SQUATSWITCH).

The landing gear safety switch, located on the left main gear housing is adjusted
so that the switch is actuated within the last quarter of an inch of gear extension.
a. Compress the strut until 7.875 inches is obtained between thetop of the gear
fork and the bottom of the gear housing. Hold the gear at this measurement.
b. Adjust the switch down until it actuates at this point. Secure the switch.
c. Extend and then compress the strut to ascertain thatthe switch will actuate
within the last quarter of an inch of oleo extension.

7A-38. ADJUSTMENT OF GEAR BACK-UP EXTENDER ACTUATOR SWITCH.

The back-up gear extender actuator switch is mounted on the extender unit located
under the bottom section of the rear seat. Inasmuch as the switch is a component
of the back-up extender, instructions for the adjustment of the switch will be
found with the adjustment instructions for the extender as found in Section VI.

7A-39. LANDING GEAR WARNING SWITCHES (THROTTLE SWITCHES).

7A-40. LANDINGGEAR UP/POWERREDUCED WARNINGSWITCH. The gear

up/power reduced warning switch (Switch "A") is within the control quadrant be-
low the throttle control lever. (Refer to Figure 7A-14.) This switch will actuate
the warning horn and red light simultaneously when the landing gear is not down
and locked, and the throttle is reduced to and below 14 inches of manifold pressure.

7A-41. REMOVAL OF LANDING GEAR UP/POWER REDUCED WARNING

SWITCH.
a. Loosen the quadrant cover by removing the cover attaching screws from
each side and at the bottom of the cover.
b. Pull the cover aft enough to remove the screws that secure the reinforcing
clip to the top underside of the cover. Remove the cover.
c. Remove the switch from its mounting bracket by removing the switch at-
taching screws.
d. Disconnect the electrical leads from the switch.

7A-42. INSTALLATION OF LANDING GEAR UP/POWER REDUCED WARNING

SWITCH.
a. Connect the electrical leads to the switch.
b. Position the switch with actuator follower against its mounting bracket and

Reissued: 1/15/81 2118 LANDING GEAR AND BRAKE SYSTEM

 PIPERCHEROKEESERVICEMANUAL

PA-20R-180, SERIAL NOS. P .

28-0005 TO 28-30199 INCL.

Figure 7A-14. Throttle Warning Switches

secure with screws.

c. The switch may be adjusted at this time per instructions in paragraph 7A-43.
d. With the control levers aft, slide the quadrant cover into position around
the controls far enough to allow the cover reinforcement clip to be installed to
the top underside of the cover and secure with screws.
e. Install the cover and secure with screws.

7A-43. ADJUSTMENTOF LANDINGGEAR UP/POWER REDUCED WARNING

SWITCH.
a. Remove the control quadrant cover as given in paragraph 7A-41.
b. Flight test the airplane and at a safe altitude, establish a normal descent
with gear up and the propeller control at a desired low pitch setting.
c. Retard the throttle to a manifold pressure of approximately 14 inches.
This setting should be an airspeed above 110 MPH.
d. In some manner, mark the throttle lever in relation to its position next to
the mounting bracket.
e. With the airplane on the ground and the throttle positioned to the mark,
loosen the screws that secure the switch and rotate it toward the throttle until it
is heard to actuate. Retighten the switch attachment screws.
f. Advance and retard the throttle to ascertain that the switch actuates at the
desired throttle lever setting. The airplane mayalso be flown to ascertain that
the horn and light will actuate when the throttle is reduced below approximately
14 inches of manifold pressure with gear up.
g. Reinstall the quadrant cover as given in paragraph 7A-42.

Reissued:1/15/81 2119 LANDINGGEAR AND BRAKESYSTEM

 PIPER CHEROKEESERVICEMANUAL

7A-44. GEAR DOWN/SELECTORHANDLE UPWARNING SWITCH. The gear

down/selector handle up warning switch (Switch "B") is located directly forward
of the instrument panel, below the arm of the throttle control lever. (Refer to
Figure 7A-14.) This switch will actuate the gear warning horn and light simul-
taneously when the gear selector handle is at the up position and the airplane is
on the ground or airspeed is below that required to close the hydraulic valve and
the pump switch of the back-up gear extender. The latter applies except at full
throttle.

7A-45. REMOVALOFGEARDOWN/SELECTORHANDLEUPWARNING SWITCH.

a. Remove the switch from its mounting bracket by removing the switch attach-
ment screws.
b. Disconnect the electrical leads from the switch.

NOTE

The switch with mounting bracket may be removed by

removing the control quadrant cover and removing the
two screws that secure the bracket.

7A-46. INSTALLATION OF GEAR DOWN/SELECTOR HANDLE UP WARNING

SWITCH.
a. Connect the electrical leads tothe switch. Leads attach to terminals C and
NC.
b. Position the switch against its mounting bracket and secure with attachment
bolts.
c. Adjust the switch as given in paragraph 7A-47.

7A-47-. ADJUSTMENT OF GEAR DOWN/SELECTOR HANDLE UP WARNING

SWITCH.
a. Loosen the quadrant cover by removing the cover attachment screws from
each side and at the bottom of the cover.
b. Pull the cover aft far enough to remove the screws that secure the reinforc -
ing clip to the top underside of the cover. Remove the cover.
c. Position the throttle control lever. 25 of an inch from its full forward stop.
d. Loosen the switch bracket attachment screw from the quadrant side and
move the bracket with switch toward the arm of the control lever until the switch
actuates. Tighten the attachment screws.
e. Move aft and then forward to ascertain that the switch actuates at the .25

Reissued:1/15/81 2120 LANDING GEAR AND BRAKE SYSTEM

 PIPERCHEROKEESERVICEMANUAL

of an inch dimension the throttle lever should still move approximately .125 of
an inch before it stops.
f. Reinstall the quadrant cover.

7A-48. WHEELS.

7A-49. REMOVAL AND DISASSEMBLY OF NOSE WHEEL. (RefertoFigure

7A-15.)
a. Jack the airplane enough to raise the nosewheelclearof the ground. (Refer
to Jacking, Section II. )
b. To remove the nose wheel, first remove the cotter pin and washer that se-
cures the safety clevis pin of the wheel nut. Next remove the clevis pin, wheel
nut and then slide the wheel from the axle.
c. The wheel halves (7 and 10) may be separated by first deflating the tire.
With the tire sufficiently deflated, remove the wheel through bolts (18). Pull the
wheel halves from the tire by removing the wheel half opposite the valve stem
first and then the other half.
d. The wheel bearing assemblies may be removed from each wheel half by first
removing the snap rings (1 or 16) that secure the grease seal retainers, and then
the retainers, grease seals (4 or 13) and bearing cones (6 or 12). The bearing
cups (5 or 11) should be removed by tapping out evenly from the inside.

7A-50. INSPECTION OF NOSE WHEEL ASSEMBLY.

a. Visually check all parts for cracks, distortion, defects and excess wear.
b. Check tie bolts for looseness or failure.
c. Check internal diameter of felt grease seals. Replace the felt grease seal
if surface is hard or gritty.
d. Check tire for cuts, internal bruises and deterioration.
e. Check bearing cones and cups for wear and pitting and relubricate.
f. Replace any wheel casting having visible cracks.

7A-51. ASSEMBLY AND INSTALLATION OF NOSE WHEEL. (Refer to Figure

7A-15.)
a. Ascertain that the bearing cup (5 or 11) for each wheel half (7 and 10) is
properly installed. Install the tire with tube on the wheel half with the valve stem
hole and then join the two wheel halves. Install the through bolts (18)with the
washers (9 and 17) and nuts (8) to the valve stem side.

Reissued:1/15/81 2121 LANDING GEAR AND BRAKE SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

Isea NOTE
. I
ON McCAULEY NOSE WHEEL
ASSEMBIES ONLY, BUSHING (19) IS
REQUIRED TO PREVENT TUBE
MOVEMENT.

19

II

3
4

1. SNAP RING
2. RING. GREASE RETAINER 7
3. FELT RING
4. RING, GREASE SEAL
5. BEARING CUP
6. BEARING CONE
7. WHEEL HALF
8. NUT 10
9. WASHER
10. WHEEL HALF
11. BEARING CUP
12. BEARING CONE
13. RING, GREASE SEAL 11
14. FELT RING 12
15. RING. GREASE RETAINER 13
16. SNAP RING
17. WASHER 14
18. BOLT
19. RUBBER BUSHING 15

Figure 7A-15. Nose Wheel Assembly

NOTE
On aircraft models which use the ClevelandWheelAssembly
torque nuts to 90 inch-pounds. Those aircraft models which
use the McCauley Wheel Assembly torque nuts to 140-150
inch-pounds.
b. Lubricate the bearing cones (6 and 12) and install the cones, grease seals (4 or 13),
felt rings (3 or 14) and seal retainer rings (2 or 15). Secure with snap rings (lor 16).
c. Slide the wheel on the axle and secure with retainer nut. Tighten nut to allow no
side play, yet allow the wheel to rotate freely. Safety the nut with clevispin and secure pin
with washer and cotter pin.

Reissued: 1/15/81 2122 LANDING GEAR AND BRAKE SYSTEM

 PIPER CHEROKEESERVICEMANUAL

1893

SNAP RING
2. RING, GREASE RETAINER

4.3. RING,
FELT, GREASE
RING SEAL

6. BEARING CONE
7; WHEEL HALF, OUTER
8. WHEEL HALF, INNER
9. BEARING CUP
10. BEARING CONE
11. RING, GREASE SEAL
12. FELT RING
13. RING, GREASE RETAINER 12
14. SNAP RING 13
15. BRAKEDISC 14
16. BOLT
17. WASHERS
18. NUT

Figure 7A-16. Main Wheel Assembly

7A-52. REMOVAL AND DISASSEMBLY OF MAIN WHEEL. (Refer to Figure

7A-16.)
a. Place the airplane on jacks. (Refer to Jacking, Section II.)
b. To remove the main wheel, remove the four cap bolts that join the brake
cylinder housing and the lining back plate assemblies. Remove the back plate
from between brake disc and wheel.
c. Remove the dust cover and the cotter pin that safeties the wheel nut, remove
the wheel nut and slide the wheel from the axle.
d. The wheel halves (7 and 8) may be separated by first deflating the tire.
With the tire sufficiently deflated, remove the wheel through bolts (16). Pull the
wheel halves from the tire by removing the inner half (8) from the tire first, and

Reissued: 1/15/81 2123 LANDING GEAR AND BRAKE SYSTEM

 PIPER CHEROKEESERVICE MANUAL

then the outer half.

e. The wheel bearing assemblies may be removed from each wheel half by
first removing the snap rings (1 or 14) that secure the grease seal retainers (2
or 13), and then the retainers, grease seals (4 or 11) and bearing cones (6 or 10).
The bearing cups (5 or 9) should not be removed only for replacement and may be
removed by tapping out evenly from the inside.

7A-53. INSPECTION OF MAIN WHEELASSEMBLY. The inspection of the main

wheel is the same as that given for the nose wheel, paragraph 7A-50.

7A-54. ASSEMBLY AND INSTALLATION OF MAIN WHEEL. (Refer to Figure

7A- 16)
a. Ascertain that the bearing cup(5 or 9) foreach wheel is properly installed.
Install the tire with tube on the outer'wheel half (7) and then join the two wheel
halves. Position the brake disc (15) in the inner wheel half and install the through
bolts with the nuts on the valve stem side. Torque wheel nuts to 150 inch pounds
and inflate tire.
b. Lubricate the bearing cones (6 or 10) and install the cones, grease seals
(4 or 11), seal retainer rings (2 or 13) and felt rings (3 or 12). Secure with snap
rings (1 or 14).
c. Slide the wheel on the axle and secure with retainer nut. Tighten the nut
to allow no side play, yet allow the wheel to rotate freely. Safety the nut with a
cotter pin and install dust cover.
d. Position the brake lining back plates between the wheel and brake disc and
the brake cylinder on the torque plate. Insert the spacer blocksbetween the back
plates and cylinder, and install the four bolts to secure the assembly. If the brake
line was disconnected, reconnect the line and bleed the brakes.

7A-55. BRAKE SYSTEM.

7A-56. WHEEL BRAKE ASSEMBLY.

7A -57. BRAKE ADJUSTMENT AND LINING TOLERANCE. No adjustment of the

brake lining clearance is necessary as they are self adjusting. Inspection of the
lining is necessary, and it may be inspected visually while installed on the air-
plane. The linings are of the riveted type and should be replaced if the thickness
of any one segment becomes worn below .097 of an inch or unevenly worn.

Reissued: 1/15/81 2124 LANDING GEAR AND BRAKE SYSTEM

 PIPERCHEROKEESERVICEMANUAL

1726

2. . WASHER
3. CYLINDER
5. SHIM
6. PISTON

Figure7A-17. Whee LINING

11.
12.BACK PLATE
RIVET
13. BACK
PLATE
the lining assemblies
backplate (11 and 13). Remove the backplate 14. LINING
15. BOLT
ANCHOR

17. "O"RING
18. PISTON
19.SEAT, BLEEDER

21. CAP, BLEEDER

22 22. NUT

a. To remove the brake assembly, first- disconnect the brake line from the
brake cylinder at the tube fitting (4).
b. Remove the four cap bolts (1) that join the brake cylinder housing (3) and
the lining back plate assemblies (1 and 13). Remove the back plate from between
the brake disc and wheel.
c. Slide the brake cylinder housing (3) from the torque plate.
d. Remove pressure plate (8) by sliding it off anchor bolts (15) of the housing.
e. The pistons may be removed by injecting low air pressure in the cylinder
fluid inlet and forcing the pistons from the housing.

Reissued:1/15/81 2J 1 LANDING GEAR AND BRAKE SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

7A-59. CLEANING, INSPECTIONAND REPAIR OF WHEELBRAKE ASSEMBLIES.

a. Clean the assembly with a suitable solvent and dry thoroughly.
b. Check the walls of the cylinder housing and pistons for scratches, burrs, corrosion,
etc., that may damage "O" rings.
c. Check the genera condition of the brake bleeder screw andlines.
d. Check the brake disc for grooves. scratches, pits or coning. Coning beyond .015 in
either direction would because.for replacement. The minimum dimension of Disc 164-19
used on Wheel Assembly 40-84 is .227. and Disc 164-20used on Wheel Assembly 40-86B is
.205 (Referto Figure 7A-18.) A single groove or isolated grooves up to .031 of an inch deep
would not necessitate replacement, but a grooving of the entire surface would reduce lining
life.
braking applications to remove it. A heavier coating of rust may require removal of the disc
so that it may be wire-brushed and then sanded with 220 grit sandpaper.
e. Lining may be removed from the backing plates by drilling or punching out the old
rivets, and installing a new set using the proper rivets and a rivet set that willproperly stake
the lining and form a correct flair of the rivet..
f. After replacing brake linings, condition them by performing a minimum of six light
pedal effort braking applications from 25 to 40 MPH, allowing the brake discs to partially
cool between stops.

7A-60. ASSEMBLY AND INSTALLATION OF WHEEL BRAKE ASSEMBLY. (Refer to

Figure 7A-17.)
a. Lubricate the piston "O" rings (7 and 17) with fluid MIL-H-5606 and install on
pistons (6 and 18). Slide the pistons in cylinder housing until flush with surface of housing.
b. Slide the lining pressure plate (8) onto the anchor bolts(15) of the housing.
c. Slide the cylinder housing assembly on the torque plate of the gear.
d. Position the lining back plates (11 and 13) between the wheel and brake disc. Insert
the shim blocks (5) between the back plates and cylinder, and install the four bolts to secure
the assembly.
e. Connect the brake line to the brake cylinder housing.
f. Bleed the brake system as described in paragraph 7A-73.

7A-61. BRAKE MASTER CYLINDER(Hand Parking Brake).

7A-62. REMOVAL OF BRAKE MASTERCYLINDER. (Refer to Figure 7A 19.)

a. To remove the brake master cylinder (8) first disconnect the inlet supply line (13)
from the fitting at the top of the cylinder and allow fluid to drain from the reservoir and
line into a suitable container.
b. Disconnect the pressure line from the fitting at the bottom of the cylinder and allow
fluid to drain from the cylinder line.
c. Disconnect the end of the cylinder rod from the brake handle (6) by removing the
cotter pin that safeties the connecting clevis pin (12). Remove the clevis pin and spacer
washers.
d. Disconnect the base of the cylinder from its mounting bracket by removing the
attachment bolt assembly (11).

Revised: 10 3 83 2J2 LANDINGGEAR AND BRAKE SYSTEEM

 PIPER CHEROKEE SERVICE MANUAL

C343
MINIMUM
THICKNESS WHEELASSEMBLY
227 40-84
MINIMUM THICKNESS 205 40-86B

MEASURE2 OR 3 POINTSTO GET AVERAGE

DISC THICKNESSS

Figure 7A-18. Brake Disc Minimum Thickness

1739

7/
1.BRAKE RESERVED
2. RIGHT BRAKE AND RUDDER
3. LEFT BRAKE
ANDRUDDER PEGS
4. RIGHTBRAKE CLINDER
5. LEFT BRAKE CYLINDER
6. BRKE HANDLE
7. HANDLE RELEASE BUTTON
8. MASTER CLINDER ASSEMBLY

10. RUDDER PEDAL PADS

11. BOLT ASSEMBLY
10- 12. CLEVIS PIN
13. LINE. INLET

Figure 7A-19. Brake System Installation

Revised: 10 3 83 2J3 LANDING GEAR AND BRAKE SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

e. The handle assembly (6) may be removed by removing the attachment bolt
assembly that secures the handle to its mounting bracket.

7A-63. DISASSEMBLY OF BRAKE MASTER CYLINDER. (Refer to Figure 7A-20.)

a. Remove the cylinder from its mounting bracket as per paragraph 7A-62.
b. To disassemble the cylinder, first remove the piston rod assembly by re-
moving the snap ring (11) from the annular slot at the rod end of the cylinder.
Draw the piston rod assembly from the cylinder.
c. The piston rod assembly may be disassembled by first removing the small
snap ring (2) securing the retainer bushing (3), spring (4), piston (6), seal (7),
gland (9) and if desired, the large return spring.
d. Remove the "O" rings from the piston and gland.

7A-64. CLEANING, INSPECTION AND REPAIR OF BRAKEMASTER CYLINDER.

a. Clean the cylinder parts with a suitable solvent and dry thoroughly.
b. Inspect the interior walls of the cylinder, for scratches, burrs, corrosion,
etc.
c. Inspect the general condition of the fitting threads of the cylinder.
d. Check the piston and valve for scratches, burrs, corrosion, etc.
e. Repairs to the cylinder are limitedtopolishing out smallscratches, burrs,
etc. and replacing valve washer seal and "O" rings.

7A-65. ASSEMBLY OF BRAKE MASTER CYLINDER. (Refer to Figure 7A-20.)

NOTE

Use a small amount of hydraulic fluid (MIL-H-5606)

on the "O" ring and component parts to prevent damage
and ease of handling during reassembly.

a. Install new "O" rings on the inside and outside of the packing gland (9) and
on the outside of the piston (6). (When installing teflon "O" ring (5) on piston, it
is recommended that it be installed withthe use of a cone placed against the pis-
ton. The cone may be constructed of plastic or metal with dimensions shown in
Figure 7A-20.)
b. To assemble the piston rod assembly, install on the rod (12), in order, the
return spring retainer washer (15), return spring(13), packing gland (9) with "O"
rings, seal (10), piston (6) with "O" ring, spring (4) and retainer bushing (3).
Secure these pieces with the small ring (2) on the end of the rod.

Reissued: 1/15/81 2J4 LANDING GEAR AND BRAKE SYSTEM

 PIPER CHEROKEESERVICE MANUAL

A349
889

COUNTERBORE
562 DIA 0625 DEEP

312 745
0 11 12 13 14 15
193
75

1 HOUSING 6 PISTON 11 SNAP RING

2 SNAP RING 7 DYNASEAL 12 ROD PISTON
3 BUSHING RETAINER 8 O-RING 13 SRING RETAINING
4 SPRING 9 GLAND.PACKING 14 ROLLPIN
5 O RING 10 O-RING 15 WASHER

Figure 7A-20. Brake Master Cylinder (Hand Parking Brake)

c. Insert the piston rod assembly in the cylinder (1) and secure packing gland with snap ring (11).
d. Install the cylinder per Paragraph 7A-67.
A-66. INSTALLATION OF BRAKE MASTER CYLINDER. (Refer to Figure 7A-19.)
a. Install the brake handle assemblybetween its mounting bracket and secure with bolt. washers. nut
and cotter pin. Washers should be placed on each side of the handle, betweenthe bracket. and under the nut.
b. Place the cylinder (8) between the mounting bracket and secure the base end with bolt, washers.
nut and cotter pin. This too should have washers placed on each side of the cylinder and under the nut.
c. Connect the rod end of the cylinder to the brake handle with a clevispin and thin washers. Safety
the clevis with a cotter pin.
d. Connect the pressure line to the fitting at the bottom of the cylinder.
e. Connect the inlet supply line (13) to the fitting at the top of the cylinder and secure with spring
clamp.
f. Bleed the brake system per Paragraph 7A-73.

Reissued: 1/15/81 2J5 LANDING GEAR AND BRAKE SYSTEM

 PIPER CHEROKEE SERVICE MAN UAL

1684
1. ARM, RUDDER CABLE ATTACHMENT
2. ARM, RUDDER CABLE ATTACHMENT
3. ARM, TRIM CONTROL ATTACHMENT
4. CLEVIS PIN, WASHER & COTTER PIN
5. CLEVIS ASSEMBLY
6. CLEVIS PIN
7. ARM, IDLER
8. JAM NUT

1
.
1

Figure 7A-21. Toe Brake Installation

Reissued: 1/15/81 2J6 LANDINGGEAR AND BRAKE SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

7A-67. BRAKECYLINDER(Toe Brake).

7A-68. REMOVALOF BRAKECYLINDER. (Refer to Figure 7A-21.)

a. Disconnect the upper and lower lines from the cylinder (14) to be removed and cap
the lines to prevent fluid leakage or drain the fluid from the brake reservoir and master
cylinder.
b. Remove the cylinder from its attachment fittings by first removing cotter pins that
safety the cylinder attaching pins (16) and then removingthe pins.

7A-69. DISASSEMBLYOF BRAKECYLINDER.

a. Clevelandcylinder number 10-20. (Refer to Figure 7A-22.)
1. Remove the cylinder from its mounting bracket as per paragraph 7A-68.
2. To disassemble the cylinder, first remove the piston rod assemblyby unscrewing
the packing gland (9) from the cylinder. Draw the piston rod assembly from the cylinder.
3. The piston rod assembly may be disassembledby first removing the small snap
ring (2) securing the retainer bushing (3) and then removing the bushing, spring (4), piston
(5), seal (7), gland (9). and, if desired, the large return spring (12).
4. Remove the "O" rings from the piston and gland.
b. Clevelandcylinder number 10-27. (Refer to Figure 7A-22.)
1. Removethe cylinder from its mounting bracket per paragraph 7A-68.
2. To disassemble the cylinder, first remove the piston rod assembly by removing
the snap ring (10) from the annular slot in the cylinder housing (1). Draw the piston rod
assembly from the cylinder.
3. The piston rod assembly may be disassembledby first removing the roll pin (12)
and then the piston assembly (3), seal (5). and packing gland (7).
4. Remove the O-ringsfrom the piston and packing gland.
c. Cleveland cylinder number 10-30.(Refer to Figure 7A-23.)
1. Remove the cylinder from its mounting bracket per Paragraph 7A-68.
2. To disassemblethe cylinder, first remove the piston rod assemblyby removing the
retaining ring from the annular slot in the cylinder housing (1). Draw the piston rod assembly
from the cylinder.
3. The piston rod assembly may be disassembled by first removing the retaining
ring (2), sleeve(3), spring (4), and then the piston assembly, O-ring(5), and gland (8), and, if
desired, the return spring (13).
4. Remove the O-ringsfrom the piston and packing gland.
d. Gar-Kenyon cylinder number 17000. (Refer to Figure 7A-22.)
1. Remove the cylinder from its mounting bracket as per Paragraph 7A-68.
2. To disassemble the cylinder, first remove the piston rod assembly by unscrewing
the fitting (8) from the cylinder.
3. The piston rod assembly may be disassembled by first removing the retaining
ring (2) securingthe sleeve(3) and then removing the spring (4), piston (6), seal (7), fitting (8),
and, if desired, the large return spring (11).
4. Remove the O-rings from the piston and fitting.

Reissued:1/15/81 2J7 LANDING GEAR AND BRAKE SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

C344
15 14
14
13

12

10-20 10-27 13 17000

11

10

10
8

5 6. "O" RING

1. HYDRAULIC 4 1. HYDRAULIC 3
CYLINDER
2. SNAP RING
3. BUSHING
4. SPRING
5. PISTON
3 2. SPRING
3. PISTON
4. "O" RING
2
1. HOUSING
2. RETAINING RING
3. SLEEVE
4. SPRING
2
6. "O" RING
7. DYNA-SEAL
WASHER
5. SEAL WASHER
6. "O" RING
7. PACKING GLAND
5.
6.
7.
"O" RING
PISTON
SEAL
1
8. "O" RING 8. "O" RING
9. WIPER WASHER 8. FITTING
9. PACKING GLAND 9. "O" RING
10. "O" RING 10. RETAINING RING 1 "O" RING
11.SPRING 10.
11. PISTON ROD 1
12. ROLL PIN 11. SPRING
12. SPRING 12. PISTON ROD
13. DELETED 13. PISTON ROD
14. WASHER 13. WASHER
14. WASHER 14. ROLL PIN
15. ROLL PIN 15. ROLL PIN

Figure 7A-22. Toe Brake Cylinders

7A-70. CLEANING, INSPECTIONAND REPAIR OF BRAKE CYLINDER.
a. Clean the cylinder parts with a suitable solvent and dry thoroughly.
b. Inspect the interior walls of the cylinder for scratches, burrs, corrosion, etc.
c. Inspect the general condition of the fitting threads of the cylinder.
d. Check the piston and valve for scratches, burrs, corrosion, etc.
e. Repairs to the cylinder are limited to polishing out small scratches, burrs, etc., and
replacing valve, washer, seal, and "0" rings.

Reissued: 1/15/81 2J 8 LANDING GEAR AND BRAKE SYSTEM

 PIPER CHEROKEESERVICEMANUAL

7A-71. ASSEMBLYOF BRAKECYLINDER.

a. Clevelandcylinder number 10-20. (Refer to Figure 7A-22.)
NOTE
Use a small amount of hydraulic fluid (MIL-H-5606)on the
"O" ring and component parts to prevent damage and ease of
handling during reassembly.

1. Install new "O" rings on the inside and outside of the packing gland (9) and on
the outside of the piston (5).
2. To assemble the piston rod assembly, install on the rod (11), in order, the roll
pin (15), return spring retainer washer (14), return spring (12), packing gland (9) with "O"
rings, seal (7), piston (5) with "O" ring, spring (4) and retainer bushing (3). Secure these
pieces with the small ring (2) on the end of the rod.
3. Insert the piston rod assemblyin the cylinder (1) and secure packing (9).
4. Install the cylinder per paragraph 7A-72.
b. Clevelandcylinder number 10-27. (Refer to Figure 7A-22.)
NOTE
Use a small amount of hydraulic fluid (MIL-H-5606)on the
"O" ring and component parts to prevent damage and ease of
handling during reassembly.

1. Install new "O" rings on the inside and outside of the packing gland (7) and on
the outside of the piston (3).
2. To assemble the piston rod assembly, install on the rod (13), in order, the roll
pin (15), washer (14), spring (11), washer (9), packing gland (7), seal (5), piston assembly
(3) and spring (2), and roll pin (12).
3. Insert the piston rod assembly in the cylinder (1) and secure with the snap ring
(10).
4. Install the cylinder per paragraph 7A-72.
c. Cleveland cylinder number 10-30.(Refer to Figure 7A-23.)
1. Install new O-rings on the inside and outside of the packing gland (7) and on the
outside of the piston (3).
2. To assemble the piston rod assembly, install on the rod (12), in order, the roll
pin (14), washer (13), spring (11), washer (9), packing gland (7) with O-rings, seal (5), piston
assembly (3) with O-ring, spring (2), and roll pin (15).
3. Insert the piston rod assembly in the cylinder (1) and secure with the retaining
ring (10).
4. Install the cylinder per Paragraph 7A:72.
d. Gar-Kenyon cylinder number 17000.(Refer to Figure 7A-22.)
1. Install new O-rings on the inside and outside of the fitting (8) and on the outside
of the piston (6). (Refer to above note.)
2. To assemble the piston rod assembly, install on the rod (12), in order, the roll
pin (14), return spring retainer washer (13), return spring (11), fitting (8)with O-rings, seal (7),
piston (6) with O-ring, spring (4) and sleeve(3). Secure these pieces with the retaining ring (2)
on the end of the rod.
3. Insert the piston rod assembly in the cylinder (1) and secure fitting (8).
4. Install the cylinder per Paragraph 7A-72.

Reissued: 1/15/81 2J9 LANDING GEAR AND BRAKE SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

7A-72. INSTALLATIONOF BRAKE CYLINDER. (Referto Figure 7A-21.)

a. Position the cylinder (14) at its mounting points and attach with clevis pin. Safety
the pins with cotter pins. (See 16, Figure 7A-21.)
b. Connect the brake lines to the cylinder fittings.
c. Bleed the brakes per Paragraph 7A-73.

7A-73. BLEEDINGPROCEDURE. When it becomes necessary to bleed the brake system,

refer to Section VII, paragraphs 7-52 through 7-55.

7A-74. BEARING REPLACEMENT. (Refer to Figure 7A-25.) When it becomes necessary

to replace a bearing in any link attachment housing, follow instructions listed below:
a. Remove bearings being replaced.

NOTE
An individual bearing can be removed and replaced only if
existing boss includes the .089 grease hole (noted in
illustration). If existing boss does not include the .089 grease
hole, both bearings on a boss must be removed and the .089
greasehole added before installing the new bearings.

C343

1. HOUSING 5. O-RING 9. O-RING 13. SPRING

2. RETAINING RING 6. PISTON 10. O-RING 14. WASHER
3. SLEEVE . 7. O-RING 11. WASHER WIPER 15. ROLL PIN
4.. SPRING 8. GLAND 12. ROD

Figure 7A-23. Brake Cylinder

(10-30) (Toe Brake)

Revised: 10 3 83
2J 10 LANDINGGEAR AND BRAKE SYSTEM
 PIPER CHEROKEE SERVICE MANUAL

b. Addition of the grease hole is accomplished by drilling a .089 hole centered on the
boss as shown in the illustration. After drilling hole, deburr any rough edges and clean out
any shavings that accumulate inside the boss hole.
c. Press fit new bearing(s) P/N 67026-07 tight against boss and line ream bearing(s) to
.31 dimension.
d. The .089 grease holes will require a needle type adapter on the greasegun nozzle.

1738

.089 Grease Hole

Boss
Bearing - 67026-07 (press fit) (2 Req.)
Line Ream .314

Boss

.089 Grease Hole

Typical Bearing Installation

Nose Gear Assembly Main Gear Assembly

Figure 7A-24. Bearing Installation

Reissued: 1/15/81 2J11 LANDING GEAR AND BRAKE SYSTEM

 PIPER CHEROKEE SERVICEMANUAL

TABLE VILA-I. LANDING GEAR TROUBLESHOOTING

Trouble Cause Remedy

Yellow transit light out Indicator lamp burned Replace lamp.

while gear is in tran- out.
sit.

Indicator light ground Check ground circuit.

incomplete.

Indicator light circuit Check wiring.

wire broken.

Indicator light circuit Reset circuit breaker

breaker open. and determine cause
for open circuit
breaker.

Yellow transit light on One or more up limit Isolate and replace

though gear has re- switches failed. switch.
tracted.

Nose gear up limit Check gear up adjust-

switch out of ad- ment and readjust up
justment. limit switch.

Main gear not re- Check gear up adjust-

tracting far enough ment.
to actuate switch.

Yellow transit light on One or more down limit Isolate and replace
though gear is down switches failed. switch.
and locked.

Nose gear down limit Readjust down limit

switch out of adjust- switch.
ment.

Reissued: 1/15/81 2J12 LANDING GEAR AND BRAKE SYSTEM

 PIPER CHEROkEE SERVICE MANUAL

TABLE VIIA-I. LANDINGGEAR TROUBLESHOOTING(cont)

Trouble Cause Remedy

Yellow transit light on Main gear down limit Readjust down limit
though gear is down switch out of adjust- switch.
and locked. (cont) ment.

NOTE

The out of adjustment or failed switch may be deter-

mined by noting which down light is not lit.

Yellow transit light Light circuit wire Check wiring.

operates on and off loose.
after gear has re-
tracted.

Hydraulic system Refer to Hydraulic

losing pressure. System Section VI..

Gear up switch out of Check gear up adjust-

adjustment. ment and then switch
adjustment.

Yellow transit light out Lamp burned out. Replace lamp.

and one green gear
down light out though
gear is down and locked. Gear down limit switch Replace switch.
failed.

NOTE
Light circuit wire Check wiring.
Ascertain navigation broken.
lights are off (daytime).

Reissued: 1/15/81 2J13 LANDING GEAR AND BRAKE SYSTEM

 PIPER CHEROKEESERVICE MANUAL

TABLE VIIA-I. LANDINGGEAR TROUBLESHOOTING (cont)

Trouble Cause Remedy

Transit yellow light and Indicator lights circuit Reset circuit breaker
all green lights out. breaker open. and determine cause
for open circuit
NOTE breaker.

Ascertain navigation Light circuit wire Check wiring.

lights are off (day- broken.
time).

Green gear down lights Failed instrument panel Replace switch.

dim though position light control switch.
light switch is off, and (Lights grounding
gear is down and locked. through dimming resis -
tor instead of instrument
panel light control.)

Green gear down light Gear down limit switch Replace switch.
fails to go outwith gear failed.
in transit or retracted.

Green gear down lights Green light ground Replace resistor.

will go out and not dim dimming resistor
when position light open.
switch is turned on
though gear is down
and locked.

Gear warning light and Landing gear selector Reset circuit breaker
horn fail to operate circuit breaker open. and determine cause
when throttle is near for open circuit
closed and landing gear breaker.
is retracted.
Micro switch "A" at Adjust micro switch
throttle out of "A".
adjustment.

Reissued: 1/15/81 2J14 LANDINGGEAR AND BRAKE SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

TABLE VIIA-I. LANDING GEAR TROUBLESHOOTING (cont)

Trouble Cause Remedy

Gear warning light and Micro switch "A" failed. Replace switch.
horn fail to operate
when throttle is near
closed and landing gear Warning horn and light Check wiring.
is retracted (cont). circuit wire broken.

Diode in circuit between Replace diode.

throttle switch "A" and
light/horn open.
NOTE

When replacing diode,

connect banded end
(cathode) to terminal
ends of wires G2R,
G2Q and G2K on mount-
ing block.

Gear warning light and Gear selector handle Place handle in down
horn fail to stop when in up position. position.
throttle is closed and
gear has extended.
(Gear extended through
the use of the free fall
lever or lack of air
speed.

Warning light and horn Warning light and horn Check wiring.
fail to operate when circuit wire broken.
selector switch is
moved to up position
with gear extended
and throttle not full
forward.

Reissued: 1/15/81
2J15 LANDING GEAR AND BRAKE SYSTEM
 PIPER CHEROKEESERVICE MANUAL

TABLE VIIA-I. LANDING GEAR TROUBLESHOOTING (cont)

Trouble Cause Remedy

Above condition on Defective safety (squat) Replace switch.

ground. switch.

Above condition in Pressure switch open. Replace switch.

the air.

Warning light and horn Throttle micro swich Adjust switch.

fail to shut off at full "B" out of adjustment.
throttle. Gear selec-
tor at up position and
gear extended. Throttle micro switch Replace switch.
"B" failed.

Hydraulic pump shuts Gear not fully retracted. Determine cause and
off, but gear yellow, remedy.
in transit, light re-
mains on.

Landing gear doors Landing gear not re- Check adjustment of

fail to completely tracting completely. landing gear.
close.

Door retraction rods Check adjustment door

out of adjustment. retraction rods.

Nose landing gear Internal wear in shimmy Replace shimmy

shimmies during fast dampener. dampener.
taxi, take-off, or
landing.
Shimmy dampener or Replace necessary
bracket loose at parts and bolts.
mounting.

Reissued: 1/15/81 2J16 . LANDING GEAR AND BRAKE SYSTEM

 PIPER CHEROKEESERVICEMANUAL.

TABLE VIIA-I. LANDING GEAR TROUBLESHOOTING (cont)

Trouble Cause Remedy

Nose landing gear Tire out of balance. Check balance and re-
shimmies during fast place tire if necessary.
taxi, take-off, or
landing (cont).
Worn or loose wheel Replace and/or adjust
bearings. wheel bearings.

Worn torque link bolts Replace bolts and/or

and/or bushings. bushings.

Excessive or uneven Incorrect operating Inflate tire to correct

wear on nose tire. pressure. pressure.

Wear resulting from Refer to proceedings

shimmy. for correction.

Nose gear fails to Oleo cylinder binding Lubricate strut housing

steer properly. in strut housing. (Refer to Lubrication
Chart).

Cylinder and/or strut

housing bushings
damaged.

One brake dragging. Determine cause and

correct.

Steering arm roller Replace defective

sheared at top of roller.
strut.

Reissued:1/15/81 2J17 LANDING GEAR AND BRAKE SYSTEM

 PIPER CHEROKEESERVICE MANUAL

TABLEVIIA-I. LANDINGGEARTROUBLESHOOTING
(cont)

Trouble Cause Remedy

Nose gear fails to Steering bellcrank loose Readjust and tighten.

steer properly (cont). on attachment plate.

Steering bellcrank bear- Replace bearing and/or

ing and/or bolt worn. bolt.

Shimmy dampener Replace.

galling or binding.

Nose gear fails to Steering arm roller Replace defective

straighten when sheared at top of roller.
landing gear extends. strut.

Incorrect rigging of Check nose gear steer-

nose gear steering., ing adjustment.

Nose gear fails to Centering guide roller Replace roller.

straighten when sheared.
landing gear retracts.
Damaged guide. Replace guide.

Main landing shimmies Tire out of balance. Check balance and re-
during fast taxi, take- place tire if necessary.
off, or landing.
Worn or loose wheel Replace and/or adjust
bearings. wheel bearings.

Worn torque link bolts Replace bolts and/or

and/or bushings. bushings.

Reissued: 1/15/81 2J18 LANDING GEAR AND BRAKE SYSTEM

 PIPER CHEROKEE SERVICE MANUAL.

TABLE VIIA-I. LANDING GEAR TROUBLESHOOTING (cont)

Trouble Cause Remedy

Excessive or uneven Incorrect operating Inflate tire to correct

wear on main tires. pressure. pressure.

Wheel out of alignment Check wheel alignment.

(toe in or out).

Lower side brace link Check gear adjustment.

out of adjustment,
allowing gear to slant
in or out.

Strut bottoms on Insufficient air and/or Service strut with air

normal landing or fluid in strut. and/or fluid.
taxiing on rough
ground.
Defective internal parts Replace defective parts.
in strut.

Reissued: 1/15/81 LANDING GEAR AND BRAKE SYSTEM

2J19
 PIPER CHEROKEE SERVICE MANUAL

7A-75. NOSE GEAR SERVICE TOLERANCES.

1770

24.225 1.2 1.2

7-8

11-12
13-14

11-12

3.4
5

9-10
6
19
15-16 1718
19

20-21

19
22-23 19
19

Figure 7A-25. Nose Gear Service Tolerances, PA-28R

Revised: 10 383 2J20. LANDINGGEAR AND BRAKE SYSTEM

 Bu
uo!

LL

dn
pue 6L80
0

S3
 OO

pue (

06

u 6

LL

6u
91
S

S
S L
 PIPER CHEROKEE SERVICE MANUAL

I 7A-76. MAIN GEAR SERVICE TOLERANCES.

3056

NOTE

WHEN BUSHINGS14843-16
(NO. 8 OR 11) ARE TO BE
REPLACED,THEYSHOULD
BE LINE REAMED TO
.376/.375. THE BUSHINGS
SHOULD BE A PRESS FIT,
HOWEVER, IF THEY ARE
LOOSE THEY MAY BE IN-
STALLEDUSING LOCTITE.

Figure 7A-26. Main Gear Service Tolerances, PA-28R

Revised: 10 3 83 2J23 LANDINGGEAR AND BRAKE SYSTEM

 18

00

9
(

06 Z

9
( LL

06

(S
6
9L
( 8

06 Z SZ L

S9 00-

9
6 00

SOS
00

6 68`

99! Z-S .
s uo ' N '6!d

S33MOi
 18/

09 (

000
( OO

OLE OL
Alq

uo

O O
O-9 6L

(
ap 8L

86 66 uo

ap 9L

(
 SECTION VIII
POWERPLANT
(PA-28-140,-150, -160,-180, -235)

Paragraph Aerofiche
Grid No.
8-1. Introduction...............................................................................................
2K4
8-2. Description..... ..............................................................................
2K4
8-3. StandardPractices-Engine.........................................................................2K6
8-4. Troubleshooting.........................................................................................
2K6
8-5. Propeller...................................................................................................
2K7
8-6. Removalof Propeller(FixedPitch).................................. 2K7
8-7. Cleaning.Inspectionand Repair of Propeller...................2K7
8-8. Installationof Propeller(FixedPitch)............................... 2K7
8-9. Removalof Propeller(ConstantSpeed)...........................2K10
8-10. Cleaning,Inspectionand Repairof Propeller
(ConstantSpeed)........................................................ 2K 0
8-11. InstallingPropeller(ConstantSpeed) ............................... 2K11
8-12. Blade Track...................................................................... 2K11
8-13. PropellerGovernor.................................................................................. 2K 12
8-14. Removalof PropellerGovernor........................................ 2K 12
8-15. Installationof PropellerGovernor.................................... 2K 2
8-16. Riggingand Adjustmentof PropellerGovernor
(PA-28-235) 2K 2
................................................................
8-17. Engine.........................................................................................................K14
8-17a. Removalof EngineCowlings........................................2K14
8-17b. Installationof EngineCowlings........................................ 2K 4
8-17c. Installationof Bushingsand Pins for FiberglasType
Cowlings................................................................... 2K14
8-18. Removalof Engine(PA-28-140,-150, -160, -180)...........2K4
8-19. Installationof Engine(PA-28-140,-150, -160, -180).......2K15
8-20. Installationof EngineShockMounts
(PA-28-140,SerialNos. 28-2500and up) ..................2K19
8-21. Removalof Engine(PA-28-235).......................................2K20
8-22. Installationof Engine(PA-28-235)................................... 2K21
8-23. Installationof Oil Cooler............................................................................2K23
8-24. Adjustmentof Throttleand MixtureControls............................................2K 3
8-25. Adjustmentof Throttle and MixtureControls............................................2K24
8-26. Carburetor..................................................................................................2L2
8-27. CarburetorMaintenance.................................................... 2L2
8-28 ThrottleArm..................................................................... 2L2
8-29. Adjustmentof Idle Mixture...............................................2L2
8-30. Adjustmentof Idle Speed..................................................2L4
8-31. Magneto(Bendix)...................................................................................... 2L4
8-32. Inspectionof Magnetos..................................................... 2L4
8-33. Removalof Magnetos....................................................... 2L6
8-34. TimingProcedure..............................................................2L7
8-35. Installationand TimingProcedure...................................2L9

Interim Revision: February 15, 1995

2K2
Paragraph Aerofiche
Grid No.

8-36. Magneto (Slick) ..................... ......................... 2L1

8-37. Harness Assembly ..................................... . 2L II
8-38. Inspection of Harness ................................ 2L 11
8-39. Removal of Harness ................................. 2L 11`
8-40. Installation of Harness ............................... 2L12
8-41. Spark Plugs ....................................... 2L12
8-42. Removal of Spark Plugs .............................. 2L12
8-43. Inspection and Cleaning of Spark Plugs ................ 2L 14
8-44. Installation of Spark Plugs ............................ 2L14
8-45. Lubrication System ........................................... 2L14
8-46. Oil Pressure Relief Valve ............................. 2L14
8-47. Switching ................................................... 2L15
8-48. Removal of Ignition Switch ........................... 2L15
8-49. Installation of Ignition Switch ......................... 2L 15

Revised: 83 81 2K3
 PIPER CHEROKEE SERVICE MANUAL

SECTION VIII
POWER PLANT
(PA-28-140,-150,-160,-180,-235)

8-1. INTRODUCTION. This section covers the power plants used in PA-28-140,-150. -160,
-180, -235 airplanes, and is comprised of instructions for the removal and installation, minor
repairs, and service of the propeller, propeller governor, engine, induction system com-
ponents, ignition system components and lubrication system.
For further instructions and for major repairs, consult the appropriate publication of the
engine or component manufacturer.

8-2. DESCRIPTION. The PA-28 Cherokee is powered by an Avco-Lycoming engine of

either 150, 160, 180, or 235 horsepower. (Refer to Power Plant Specifications in Table II-I.)
Engines are 0-320 and 0-360 series which are four-cylinder units and 0-540 series which are
six-cylinder units. All are wet sump, horizontally opposed, direct drive, air-cooled engines.
The cylinders are not directly opposed from each other but are staggered, thus permitting a
separate throw on the crankshaft for each connecting rod.
The cylinders are of conventional air-cooled design with the two major parts, head and
barrel, screwed and shrunk together. The heads are made from an aluminum alloy castingwith
a fully machined combustion chamber. The cylinder barrel, which is machinedfrom a chrome
nickel molybdenum steel forging with deep integral cooling fins, is ground and honed to a
specified finish. Standard engines are furnished with unplated cylinder barrels and chrome
plated piston rings. Engines manufactured with optional chrome plated barrels require
unplated piston rings.
The propellers installed on the PA-28-140,-150,-160,-180 are Sensenichfixed pitch type.
The PA-28-235 may be equipped with either Sensenich or McCauley fixed pitch propellers or
as an option, may be equipped with a Hartzell constant speed unit. The constant speed pro-
peller utilizes oil pressure from a governor to move the blades into high pitch (reduced rpm).
The centrifugal twisting moment of the blades tend to move them into low pitch (high rpm) in
the absence of governor oil pressure.
The induction system on these engines consists of a dry type air filter, a Marvel-Schebler
MA-4SPA or MA-4-5 float type carburetor and Bendix electric pulsating plunger type fuel
pumps. Engines are normally aspirated with no restrictions on maximum power output.

Reissued: 1/15/81 2K4 POWER PLANT

 PIPER CHEROKEESERVICE MANUAL

The magnetos used on these engines may be either Bendix-ScintillaS-20 or S-200 series
or Slick 4000 series. The Bendix series magnetos are installed with their associated
components. This magneto system consists of two single contact magnetos with the left
magneto incorporating an impulse coupling to aid in starting. These are serviceable units.
The Slick series magnetos are installed with their associated components. Refer to the latest
revision of Lycoming Service Letter No. SL-L177 for Slick exchange policy. These magnetos
are non-serviceable,sealed units.
In addition to the previously mentioned components, each engine is furnished with a
starter, 35 ampere or 60 ampere output, 14-voltelectrical system, shielded ignition, vacuum
pump drive and fuel pump. The exhaust system is stainless steel with a large muffler or two
small mufflers and a shroud is provided to supply heat for both the cabin and carburetor.
The lubrication system is of the pressure wet sump type. The oil pump, which is located
in the accessory housing, draws oil through a drilled passage leading from the oil suction
screen located in the sump. The oil from the pump then enters a drilled passage in the
accessory housing, which feeds the oil to a threaded connection on the rear face of the
accessory housing, where a flexible line leads the oil to the external oil cooler. Pressure oil
from the cooler returns to a second threaded connection on the accessory housing from
which point a drilled passage conducts oil to the oil pressure screen or filter. In the event
that cold oil or an obstruction should restrict the oil flow to the cooler, an oil bypass valve
is provided to pass the oil directly from the oil pump to the oil pressure screen or filter.
The oil pressure screen or filter element, located on the accessoryhousing is provided as
a means to filter from the oil any solid particles that may have passed through the suction
screen in the sump. After being filtered in the pressure screen or filter, the oil is fed through
a drilled passage to the oil pressure relief valve, located in the upper right side of the
crankcase in front of the accessory housing.
This relief valve regulates the engine oil pressure by allowingexcessive oil to return to
the sump, while the balance of the pressure oil is fed to the main oil gallery in the right half
of the crankcase. Residual oil is returned by gravity to the sump where, after passing
through a screen, it is again circulated through the engine.

Reissued: 1/15/81 2K5 POWER PLANT

 PIPER CHEROKEESERVICE MANUAL

8-3. STANDARD PRACTICES-ENGINE. The following suggestions should be applied

wherever they are needed when working on the powerplant.
a. To insure proper reinstallation and/or assembly, tag and mark all parts, clips, and
brackets as to their location prior to their removal and/ or disassembly.
b. During removal of various tubes or engine parts,,inspect then for indications of
scoring, burning or other undesirable conditions. To facilitate reinstallation. observe the
location of each part during removal. Tag any unserviceable part and or units for
investigation and possible repair.
c. Extreme care must be taken to prevent foreign matter from entering the engine,such
as lockwire. washers. nuts, dirt, dust, etc. This precaution applies whenever work is done on
the engine, either on or off the aircraft. Suitable protective caps, plugs, and covers must be used
to protect all openings as they are exposed.

NOTE

Dust caps used to protect open lines must always be installed

OVER the tube ends and NOT INthe tube ends. Flow through
the lines may be blocked off if lines are inadvertently installed
with dust caps in the tube ends.

d. Should any items be dropped into the engine, the assemblyprocess must stop and the
item removed. even though this may require considerabletime and labor. Insure that all parts
are thoroughly clean before assembling.
e. Never reuse any lockwire, lockwashers, tablocks, tabwashers or cotter pins. All
lockwire and cotter pins must fit snuglyin holes drilled in studs and bolts for locking purposes.
Cotter pins should be installed so the head fits into the castellation of the nut. and unless
otherwise specified, bend one end of the pin back over the stud or bolt and the other end down
flat against the nut. Use only corrosion resistant steel lockwire and/ or cotter pins. Bushing
plugs shall be lockwired to the assembly base or case. Do-not lockwirethe plugto the bushing.
f. All gaskets, packings and rubber parts must be replaced with new items of the same
type at reassembly. Insure the new nonmetallic parts being installed show no sign of having
deteriorated in storage.
g. When installing engine parts which require the use of a hammer to facilitateassembly
or installation, use only a plastic or rawhide hammer.
h. Anti-seize lubrication should be applied to all loose-fit spline drives which are
external to the engine and have no other means of lubrication. For certain assembly
procedures, molybdenum disulfide in either paste or powdered form mixed with engine oil or
grease may be used.
CAUTION
Ensure that Anti-seize compounds are applied in thin even
coats, and that excess compound is completely removed to
avoid contamination of adjacent parts.
i. Temporary marking methods are those markings which will ensure identification
during ordinary handling, storage and final assembly of parts.
8-4. TROUBLESHOOTING.Troubles peculiar to the power plant are listed in Table VIII-I,
at the back of this section, along with their probable causes and suggestedremedies. When
troubleshooting the engine, ground the magneto primary circuit before performing any
checks on the engine.

2K62K6 POWER PLANT

Reissued:1/15/81
 PIPER CHEROKEESERVICE MANUAL

8-5. PROPELLER.

8-6. REMOVAL OF PROPELLER. (Fixed Pitch.)

a. Insure master and magneto switches are off.
b. Move fuel selector to off position and place mixture control in idle cut-off.
c. Note the position of each component to facilitate reinstallation.
d. Remove the screws attaching the spinner assembly and remove the spinner.
e. Remove the safety wire that secures the six attaching bolts and remove the
bolts. The propeller is now free to be removed.

8-7. CLEANING, INSPECTION AND REPAIR OF PROPELLER. (Fixed Pitch.)

a. Clean the spinner, back plate and propeller surfaces with a non-corrosive
solvent, and inspect for nicks, scratches, corrosion and cracks.
b. Nicks in the leading edges of the blades should be filed out and all edges
rounded, as cracks sometimes start from such places. Use fine emery cloth for
finishing. (Refer to Figure 8-1 for propeller blade care.) A propeller with severe
nicks, scratches, corrosion or cracks should be returned to a propeller overhaul
shop or the manufacturer for inspection and repair.
c. Each blade face should be sanded lightly and painted, when necessary, with
a flat black paint to retard glare. A light application of oil or wax may be applied
to the surfaces to prevent corrosion.

8-8. INSTALLATION OF PROPELLER. (Fixed Pitch.)

a. Insure magneto switch is OFF.
b. Place the generator or alternator drive belt in the groove of the starter
ring gear and position the starter gear on the flange of the crankshaft. Ascertain
that the stamped "O" on the gear is aligned with the "O" on the crankshaft flange.
c. Install the propeller spinner backplate or bulkhead on the starter ring gear.
d. Rotate crankshaft until the top center (TC) mark on the starter gear and the
crankcase parting flange or the index mark on starter housing are aligned.
e. Install propeller with tips pointing at the two and eight o'clock position.
f. Install and tighten each propeller bolt, with washer, finger tight. Use a
torque wrench for final tightening and tighten in sequence so that all bolts are
pulled down evenly. Torque three-eights inch bolts to 280 to 300 inch-pounds
or one-half inch bolts to 720 to 780 inch-pounds (60 to 65 foot-pounds).
g. Check the propeller blade track as given in paragraph 8-12.
h. Safety the propeller mounting bolts with MS20995-C41 wire.
i . Install the spinner and tighten cap bolts to a torque of 35 to 40 inch-pounds.
j. Adjust generator or alternator drive belt as given in Checking Generator
and Alternator Belt Tension, Section XI.

Reissued: 1/15/81 2K7 POWER PLANT

 PIPER CHEROKEESERVICE MANUAL

C345

Exagerated view of nicks

in leading edge Exagerated view ofnick
in face of bladsd

Recommended method for removing SECTION AA-

nicks by riffle file and crocuscloth. Nick in face of blade
Blenddeepest portion of nick into
0 removed by file and
leading edge alignmentwith smooth
ereci cloth asrecom-
curves
mended

Figure 8-1. Typical Nicks and Removal Method

C367
1. SPINNER - PROPELLER
2. PROPELLER
3. BULKHEAD ASSEMBLY - SPINNER
4. "O" RING
5. GOVERNOR
6. CONTROL CABLE
7. CONTROL - KNOB
8. HOSE - MANIFOLD GAUGE
9. GAUGE - MANIFOLD PRESSURE

Figure 8-2. Propeller Installation (Constant Speed)

PA-28-235

POWER PLANT
Reissued:1/15/81 2K8
 PIPER CHEROKEESERVICEMANUAL

1740

14

10S

15

'
15

20

4.

1. SCREW, SPINNER ATTACHMENT 11. PROPELLER BLADE

2. SPINNER ASSEMBL 12. SPINNER BACK PLATE
3. BOLT, BULKHEAD ATTACHMENT 13. STARTER RING
4. WASHER 14. "" RING SEAL
5. PLATE 15. NUT, FLYWHEEL
6. BULKHEAD, FORWARD SPINNER 16. STUD
7. CUFF, SPINNER 17. WASHER
8. Low PITCH STOP 18. NUT
9. JAM NUT 19. SAFETY WIRE
10. PROPELLER HUB 20. GREASE FITTING

Figure 8-3. Propeller Installation

Reissued: 1/15/81 2K9 POWERPLANT

 PIPER CHEROKEE SERVICE MANUAL

TABLE VIII-I. PROPELLER TORQUE LIMITS

DESCRIPTION REQUIRED TORQUE

Propeller Mounting Nuts - 55-65 Foot Pounds(1 )

Forward Bulkhead Attachment Bolts 30-35 Inch Pounds

Spinner Attachment Screws 20-25 Inch Pounds

(1) Fixed Pitch and constant Speed.

8-9. REMOVALOF PROPELLER. (Constant Speed.)

a. Insure that the master and magneto switches are off.
b. Move fuel selector to off position.
c. Place the mixture control in idle cut-off.
d. Note position of each component to facilitate reinstallation.
e. Remove the screws from around the spinner assembly and remove spinner.
f. Remove the safety wire from the six propeller mounting nuts on studs and remove
studs.
g. Place a drip pan under the propeller to catch oil spillage, then remove the propeller.

8-10. CLEANING. INSPECTION AND REPAIR OF PROPELLER. (Constant Speed.)

a; Check for oil and grease leaks.
b. Clean the spinner, propeller hub interior and exterior, and blades with a
non-corrosive solvent.
c. Inspect the hub parts for cracks.
d. Steel hub parts should not be permitted to rust. Use aluminum paint to touch up, if
necessary, or replate during overhaul.
e. Check all visible parts for wear and safety.
f. Check blades to determine whether they turn freely on the hub pivot tube. This can
be done by rocking the blades back and forth through the slight freedom allowed by the
pitch change mechanism. If they appear tight and are properly lubricated, the pitch change
mechanism should be removed so that each blade can be checked individually. If blades are
tight, the propeller should be disassembled.
g. Inspect blades for damage or cracks. Nicks in leading edges of blades should be filed
out and all edges rounded, as cracks sometimes start from such places. Use fine emery cloth
for finishing. (Refer to Figure 8-1 for propeller blade care.) Each blade face should be
sanded lightly and painted, when necessary, with a flat black paint to retard glare. A light
application of oil or wax may be applied to the surfaces to prevent corrosion.
h. It is recommended that for severe damage, internal repairs and replacement of parts,
the propeller should be referred to the Hartzell Factory or an authorized Service Station.
i. Grease blade hub through zerk fittings. Remove one of the two fittings for each
propeller blade, alternate the next time. Apply grease through the zerk fitting until fresh
grease appears at the fitting hole of the removed fitting. Care should be taken to avoid
blowing out hub gaskets.
j. Check condition of the propeller mounting nuts on studs.

Reissued: 1/15/81 2K10 POWER PLANT

 PIPER CHEROKEESERVICE MANUAL

8-11. INSTALLING PROPELLER. (Constant Speed.)

a. Insure master and magneto switches are off.
b. Place fuel selector to off position.
c. Place mixture control in idle cut-off.
d. Observe the starter ring gear to make sure it is mounted properly on the
engine crankshaft flange. One of the bushings on the crankshaft is stamped with
an "O" mark and it must be inserted in the starter ring gear hole, likewise iden-
tified with an "O" mark.
e. Wipe crankshaft and propeller pilot to assure thatno chips or foreign mat-
ter enter the propellermechanism.
f. Check interior of propeller hubfor proper seating of "O" ring. Wipe inside
of hub to remove any traces of dirt. Check to see that "O" ring is covered with
grease.
g Raise propeller into position so that each stud mates with an engine flange
bushing and screw each stud in a few threads at a time until all are tight. Torque
to 60 to 70 foot pounds.
h. Check the propeller blade track as given in paragraph 8-12.
i . Safety the propeller mounting bolts with MS20995-C41 safety wire.
j . Install the spinner, torque cap bolts 35 to 40 inch pounds.

8-12. BLADE TRACK. Blade track is the ability of one blade tip to follow the
other, while rotating, in almost the same plane. Excessive difference in blade
track - more than .0625 inch - may be an indication of bent blades or improper
propeller installation. Check blade track as follows:
a. With the engine shut down and blades vertical, secure to the aircraft a
smooth board just under the tip of the lower blade. Move the tip fore and aft
through its full "blade-shake" travel, making small marks with a pencil at each
position. Then center the tip between these marks and scribe a line onthe board
for the full width of the tip.
b. Carefully rotate propeller by hand to bring the opposite blade down. Center
the tip and scribe a pencil line as before and check that lines are not separated
more than .0625 inch.
c. Propellers having excess blade track should be removed and inspected for
bent blades. Constant speed propellers should be checked for parts of sheared
"O" ring, or foreign particles, which have lodged between hub and crankshaft
mounting faces. Bent blades will require repair and overhaul of assembly.

Reissued: 1/15/81 2K11 POWER PLANT

 PIPER CHEROKEE SERVICE MANUAL

8-13. PROPELLER GOVERNOR. (PA-28-235.)

8-14. REMOVAL OF PROPELLER GOVERNOR.

a. Remove the upper engine cowl.
b. Disconnect the control cable end from the governor control arm.
c. Remove the governor mounting stud nuts. It will be:necessary to raise the
governor as the nuts are being removed before the nuts can be completely re-
moved.
d. Remove the mounting gasket. If the governor is to be removed for a con-
siderable length of time and another unit not substituted, it is advisable to cover
the mounting pad to prevent damage caused by foreign matter.

8-15. INSTALLATION OF PROPELLER GOVERNOR.

a. Clean the mounting pad thoroughly, making very certain that there are no
foreign particles in the recess around the drive shaft.
b. Place the governor mounting gasket in position with the raised portion of
the screen facing away from the engine,
c. Align the splines on the governor shaft with the engine drive and slide the
governor into position.
d. With the governor in position, raise the governor enough to install washers
and start mounting nuts. Torque nuts even.
e. Connect the control cable end to the governor control arm. The ball stud
is installed in the inner hole of the control arm.
f. Adjust governor control per paragraph 8-16.
g. Install engine cowl.

8-16. RIGGING AND ADJUSTMENT OF PROPELLER GOVERNOR. (PA-28-235.)

(Refer to Figure 8-5.)
a. Start engine, park 90° to wind direction and warm in normal manner.
b. To check high RPM, low pitch setting, move the propeller control all the
way forward. At this position, the governor speed control arm (1) should be
against the high RPM fine adjusting screw (2). With the throttle full forward,
observe engine RPM, which should be 2575 RPM with high RPM properly adjusted.
c. Should engine RPM not be as required, the high RPM setting should be ad-
justed as follows:
1. Shut down the engine and remove the upper engine cowl.
2. Adjustthe governor by means ofthefine adjustmentscrew for 2575 RPM.
To do this, loosen the high RPM fine adjustment screw locknut and turn the screw
in a clockwise direction to decrease engine speed or in a counterclockwise direc-
tion to increase engine speed.

Reis
Reissued:
1/15/81
1/15/81 2K12 POWERPLANT
 PIPER CHEROKEESERVICE MANUAL

960 O90

.K2 TS .125

Figure 8-4. Adjustment of Propeller Control (PA-28-235)

NOTE

One revolution of the fine adjustment screw.will in-

crease or decrease the engine speed approximately
20 RPM.

3. Reinstall upper engine cowl and repeat step b to ascertain proper RPM
C308
setting.
4. After setting the proper high
RPM adjustment, run the self-locking
nut on the fine adjustment screw against
the base projection to lock.
5. Ascertain that the governor
control arm is adjusted to the proper
angle on the control wheel (4) as shown
in Figure 8-5.
d. With the high RPM adjustment
complete, the control system should be
adjusted so that the governor control
1. CONTROL ARM
2. RPM ADJUSTMENT SCREW
arm will contact the high RPM stop.
3. LOCK NUT On airplanes with Serial Nos. 28-10166
4. CONTROL WHEEL
5. BOLT ASSEMBLY to 28-11039 incl., the cockpit knob
should be .062 to .125 of an inch from
Figure 8-5. Propeller Governor its full forward stop. Airplanes with
(PA-28-235) Serial Nos. 28-11040 and up, the cockpit

Reissued: 1/15/81 2K13 POWER PLANT

 PIPERCHEROKEESERVICEMANUAL

control lever should be .031 to .062 of an inch from its full forward stop. (Referto Figure 8-4.) To
adjust the control travel, disconnect the control cable end from the control arm, loosen the cable
jam nut and rotate the end to obtainthe desiredlevel clearance.Reconnectthe cable end and tighten
jam nut.
e. It is usually only necessaryto adjustthe high RPM settingof the governorcontrol system,
as the action automaticallytakescare of the positivehigh pitch setting.
8-17. ENGINE.
8-17a. REMOVALOF ENGINECOWLINGS.
a. Release cowlingfastenersor attachmentscrews,dependingon the type installed.
b. Disconnectall electricalleads.
c. Removecowlings.(Moveupper cowlingup and forward,drop lowercowling down.)
8-17b. INSTALLATIONOF ENGINECOWLINGS.
a. Position cowlings in place. (Bottomcowlingfirst, insert locator pins of upper cowling and
lower into place.)
b. Connectelectricalleads.
c. Securefastenersor attachmentscrews,dependingon the type of cowlinginstalled.
8-17c. INSTALLATIONOF BUSHINGSAND PINSFOR FIBERGLASTYPE COWLINGS.
a. With cowlings removed,locatebushingson lowercowling.(See Figure 8-7.)
b. Using snap ringpliers, removesnap ring and old bushing.
c. Install new bushingand new snap ring.
NOTE
Bushings should be inspected each 100 hours and
should be replacedupon condition,but no later than
500 hours time in service.
d. Locate pins in upper cowling.
NOTE
It should not be necessaryto replace the pins unless
bushing in lower cowling has worn enough to allow
damage to the pin. Any noticeable notching or cut-
ting of the pin requiresreplacement.
e. If it is necessaryto remove the pins, appropriatetools should be used to remove the fiber-
glas resin from around the pin and plate assembly.(A template or adequatemeasurementsshould
be made to assure proper alignmentof the new pin and plate assembly.)
f. Removepin and plate assembly
g. To install new pin and plate assemblyit will be necessaryto preparethe fiberglassurface to
accept the new plate. (See Paragraph4-58, FIBERGLASREPAIRS.)
1. Clean area as required,and roughen.
2. Preparecowlingsurfaceby applyingresin. Do not allowto harden.
3. Installplate and pin.
4. Lay in a layer ofresin impregnatedfiberglascloth over the plate and surroundingfiber-
glas. (Use templateor measurementsfrom step e to assurealignment.)Allow to cure.
8-18. REMOVALOF ENGINE.(PA-28-140,-150, -160,-180) (Referto Figure 8-6 or 8-7.)
a. Turn off all electrical switches in the cockpit and then disconnect the bat-
tery ground wire at the battery.
b. Move the fuel selectorlever in the cockpit to the OFF position.
c. Remove ihe engine cowlings per Paragraph 8-17a. Be certain that-all electrical leads
are disconnectedprior to removalof the cowling.
d. Removethe propellerper paragraph8-6.
e. Disconnect the starter positive and ground leads at the starter, and their
attachment clamps.

Interim Revision: February 15, 1995 POWERPLANT

2K14
 PIPERCHEROKEESERVICEMANUAL

f. Disconnectthe cabin heat and defrostertubes from the muffler.

g. Disconnectthe primer line at the tee connection.
h. Disconnect the throttle and mixture cables at the carburetor and carburetor heat control.
The carburetormay be removedif it is founddesirable.
i. Disconnectthe mechanicalfuel pump supply line at the pump.
NOTE
When a question may arise as where to reconnect
hose, line or wire, the item at the separation should
be identified (tagged) to facilitate reinstallation.Open
fuel. oil, vacuum lines and fittings should be capped
to preventcontamination.
j. Disconnectthe engine oil coolerlines from the cooler.
k.Disconnect the magneto "P" leads at the magnetos . Insert a protective cover
over the connection.
l. Disconnectthe engine oil temperaturelead at the aft end of the engine.
m. Disconnectthe tachometerdrive cable from the rear of the engine.
n. Untie the ignitionharness,hosesand lines at the aft end of the engine.
o. Disconnectthe vacuumpump lines at the pump.
p. Disconnectthe oil pressureline from the rearof the engine.
q. Disconnectthe generatoror alternatorleadsand the cable attachmentclamps.
r. Attach a one-half ton (minimum) hoist to the hoisting straps and relieve the
tension from the mounts.
NOTE
Place a tail stand under the tail of the airplanebefore
removingthe engine.
s. Checkthe eneine for any attachmentsremainingto obstructits removal.
t. Drain the engine oil, if desired,and close the drain.
u. Remove the four engine mount assemblies and swing the engine free, being careful
not to damage any attachingparts.

8-19. INSTALLATIONOF ENGINE.(PA-28-140,-150,-160, -180) (Refer to Figure 8-6

or 8-7.)
a. Prior to installing the engine, be certain that all components of the engine such as
exhaust stacks,carburetor,etc. are installed.
b. Attach a one-half ton (minimum) hoist to the engine hoisting straps and swing the
engine into alignmentwith its attachingpoints.
NOTE
On PA-28-140 aircraft with Serial Nos. 28-25000
and up, refer to paragraph 8-20 and Figure 8-8 for
shock mount installation instructions. When using
these instructions,steps c thru e, of paragraph 8-19
may be skipped.

c. Insert an engine mount bolt, with washer against head, in the engine mount and
slide half of the mount assembly on the bolt. Repeat this procedure for the other three
attachment points.
d. Position the mounting lugs of the engine so that they align with the engine mount
attachingpoints, then move the engine rearwardonto the mounts.
e. Slide onto each mounting bolt a spacer washer, spacer and the forward half of the
mount. Installwasher and nuts, and torquethe nuts of thebolts to 450 to 500 inchpounds.

Reissued: 1/15/81 POWER PLANT

2K15
 PIPER CHEROKEE SERVICE MANUAL

C310
1. ENGINE AND NOSE GEAR MOUNT 10. PROPELLER
2. THROTTLE CONTROL 11. SPINNER MOUNTING PLATE
3. CARBURATOR HEAT CONTROL 12. SPINNER ASSEMBLY
4. MIXTURE CONTROL 13. LANDING LIGHT
8
5. TACHOMETER HAET 14. PAPER AIR FILTER
6. OIL COOLER LINES 15. LANDING LIGHT - AIR FILTER
7. OIL COOLER ATTACHMENT BOLT
8. BAFFLING 16. HEATER SHROUD
9. TOP COWL

12

13

15

Figure 8-6. Engine Installation (PA-28-140, -150, -160, -180;

Serial Nos. 28-1 to 28-1760.)

Reissued: 1/15/81 2K16 POWER PLANT

 PIPER CHEROKEESERVICEMANUAL

1. ENGINEAND NOSEGEAR MOUNT 10. BOTTOMCOWL

2. THROTTLECONTROL 11. SPINNERMOUNTINGPLATE
3. CARBURETORHEAT CONTROL 12. PROPELLER
4. MIXTURECONTROL 13. SPINNERSUPPORTPLATE
5. TACHOMETERSHAFT 14. SPINNER
6. ENGINESHOCKMOUNT 15. HEATERANDMUFFLERASSEMBLY
7. OIL COOLER 16. AIR FILTER
8. BAFFLING 17. FRESHAIR INTAKE
9. TOP COWL 18. POWERPLANTASSEMBLY
19. PLATEASSEMBLY,BUSHING,
RETAININGRING,WASHERS,NUTS
NOTE: A maximumof (3) AN960-616
washerscan be used to permita max. of
2.5 threadsexposedon the bolt.Torque
to 230/240inch-pounds.

Figure 8-7. Engine Installation

(PA-28-140, -150. -160, -180, Serial Nos. 28-1761 and up)

Interim Revision: February 15, 1995 POWER PLANT

2K17
 PIPERCHEROKEE
SERVICEMANUAL

138

I
BOLT
WASHER
SHOCKMOUNT
SPACER
ENGINEMOUNT
SHOCKMOUNT

ENGINEMOUNTINGLUG

SECTIONA-A SECTIONB-B
TORQUE - 450-500 IN. LBS. ..

SPACERWASHER

SECTIONC-C SECTIOND-D

Figure. 8-8. Engine Shock Mount Installation (PA-28-140, Serial Nos. 28-25000 and up)

Reissued: 1/15/81 POWER PLANT

2K18 POWER PLANT
 PIPERCHEROKEE
SERVICEMANUAL

f. Connect the generator or alternator leads and secure cables with clamps.
g. Connect the oil pressure line, tachometer drive cable, oil temperature lead and the
engine vent tube to the aft end of the engine.
h. Connect the vacuum pump line at the pump.
i. Secure the ignition harness, hoses and lines at the aft end of the engine using
koroseal lacing.
j. Connect both lines to the oil cooler.
k. Connect the mechanical fuel pump supply line at the pump.
1. Connect the magneto "P" leads to the magnetos.
m. Connect the throttle, mixture and carburetor heat cables at the engine
components.
n. Connect the cabin heat and defroster tubes to the muffler.
o. Connect the starter positive and ground leads at the starter and secure with
attachment clamps.
p. Be certain that the magneto switches are OFF 'and install the propeller per
paragraph 8-8.
q. Install the proper grade and amount of engine oil. Refer to Lubrication Chart,
Section II.
r. Connect the battery ground wire at the battery.
s. Open the throttle and fuel valve completely. Turn on the electric fuel pump and
check the fuel line for leaks.
t. Install the engine cowlings and remove the tail stand.

NOTE
To avoid a possible high speed bearing failure resulting from a
lack of lubrication during initial starts, refer to the latest
revision of Avco-LycomingService Instruction No. 1241 for
information on pre-oiling the engine.

u. Perform an engine operational check. Refer to the engine manufacturer's

appropriate operator's manual.

8-20. INSTALLATION OF ENGINE SHOCK MOUNTS. (PA-28-140, Serial Nos. 28-2500

and up.) (Refer to Figure 8-8.)
a. Assemble the engine shock mounts on the engine mount as shown in Figure 8-8.
Note the position of each mount carefully. The upper right and lower left mounts are the
same, as are the upper left and lower right.
b. Swing the engine into place, positioning the engine mounting lugs so they align
.with the engine mount attachment points.
c. Position the shock mount bolts through the'mounting lugs and secure with nuts.
Torque the nuts progressively,followinga circular sequence until a torque value of 450-500
inch pounds is reached.

Reissued: 1/15/81
2K19 r
 PIPER CHEROKEESERVICE MANUAL

8-21. REMOVAL OF ENGINE (PA-28-235). (Refer to Figure 8-9.)

a. Turn off all electrical switches in the cockpit and then disconnect the battery
ground wire at the battery.
b. Move the fuel selector lever in the cockpit to the OFF position.
c. Remove the engine cowling by the following procedure:
1. Release the cowl fasteners, two on each side and two at the top aft of
cowl.
2. Lift the aft end of the cowl and then slide it forward to release the two
stud type front fasteners. Remove the top cowl.
3. Disconnect the landing light lead at the quick disconnect located in the
bottom cowl.
4. Remove the screws securing the bottom cowl at its aft end and brace
across bottom aft of cowl. Remove the bottom cowl.
d. Remove the propeller per paragraph 8-6 or 8-9.
e. Disconnect the cabin heat and defroster tubes from the heat muff.
f. Disconnect the primer line at the tee connection.
g. Disconnect the mechanical fuel pump inlet line that is connected to the right
side of the pump.
h. Disconnect the starter leads at the starter and their attachment clamps.
i . Disconnect the alternator leads and the attachment clamps.
j . Disconnect the carburetor heat, throttle and mixture controls from the en-
gine components.
k. Disconnect the tachometer cable from the rear of the engine.
1. Disconnect the hose from the vacuum pump.
m. Disconnect the magneto "P" leads and insert a protective cover over the
connection.
n. Disconnect the oil pressure line from the rear of the engine.
o. If the airplane involved is equipped with a constant speed propeller, dis-
connect the propeller control cable at the propeller governor and the manifold
pressure line from the left rear cylinder of the engine.
p. Attach a one-half ton (minimum) hoist to the hoisting strap and relieve the
tension on the engine mount.

NOTE

Place a tail stand under the tail of the airplane before

removing the engine.

POWER PLANT
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 PIPER CHEROKEESERVICE MANUAL

q. Check the engine for any attachments remaining to obstruct its removal.
r. Drain the engine oil, if desired, and then close the drain.
s. Remove the four engine mount assemblies and swingthe engine free, being
careful not to damage any attaching parts.

8-22. INSTALLATION OF ENGINE (PA-28-235). (Refer to Figure 8-9.)

a. Attach a one-half ton (minimum) hoist to the engine hoisting straps and
swing the engine into alignment with its attaching points on the mounts.
b. Insert an engine mount bolt through the hole of a mount attachment point
(A washer is installed next to the head of the bolt.) and slide a half of the shock
mount assembly on the bolt. Repeat for the other three mounts.
c. Position the mounting lugs of the engine so that they align with the engine
mount attaching points, then move the engine rearward onto the mounts.
d. Slide onto each mounting bolt a spacerwasher, spacer and the forward half
of mount. Install the washer and nut, and torque the nuts to 450 to 500 inch pounds.
e. If the airplane involved is equipped with a constant speed propeller, connect
the propeller control cable at the propeller governor and the manifold pressure
line to the left rear cylinder of the engine.
f. Connect the oil pressure line to the aft end of the engine.
g. Remove the protective cover from the magneto "P" leads and connect the
leads to the magnetos.
h. Connect the hose to the vacuum pump.
i. Connect the tachometer cable to the rear of the engine.
j. Connect the carburetor heat, throttle and mixture controls to the engine
components.
k. Connect the alternator leads and secure with the attachment clamps.
1. Connect the starter leads at the starter and secure with the attachment
clamps.
m. Connect the mechanical fuel pump inlet line that is connected to the right
side of the pump.
n. Connect the primer line at the tee connection.
o. Connect the cabin heat line and defroster tubes at the heat muff.
p. Be certain that the magneto switches-are OFF and install the propeller per
paragraph 8-9 or 8-13.
q. Install the proper grade and amount of engine oil. Refer to Lubrication
Chart, Section II.

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 PIPER CHEROKEESERVICE MANUAL

1120
1. ENGINE MOUNT ASSEMBLY
2. CARBURATOR HEAT CONTROL CABLE
3. MIXTURE CONTROL CABLE
4. TACHOMETER SHAFT
5. OIL RADIATORHOSE
6. OIL RADIATOR
7. ENGINE BAFFLES
8. TOP COWL ASSEMBLY
9. PROPELLER ASSEMBLY

NOTE: A maximum of (3) AN960416 17

washers can be used to permit a max. of
2.5 threads exposed on the bolt. Torque
to 230/240 Inch-pounds.
10. SPINNER BULKHEAD ASSEMBLY
11. PROPELLER SPINNER ASSEMBLY
12. CARBURETOR AIR FILTER ASSEMBLY
13. CABIN HEAT BOX
14. MUFFLER ASSEMBLY
15. CARBURETOR HEAT SHROUD
16. OIL DRAIN VALVE
17. BOTTOM COWL ASSEMBLY

Figure 8-9. Engine Installation (PA-28-235)

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 PIPER CHEROKEE SERVICE MANUAL

r. Connect the battery ground wire at the battery.

s. Open the throttle and fuel valve completely; turn on the electric fuel pump and
check the fuel lines for leaks.
t. Install the engine cowlingsand remove the tail stand.
NOTE
To avoid a possible high speed bearing failure resulting from a
lack of lubrication during initial starts, refer to the latest
revision of Avco-Lycoming Service Instruction No. 1241 for
information on pre-oiling the engine.
u. Perform an engine operational check. Refer to engine manufacturer's appropriate
operator's manual.

8-23. INSTALLATION OF OIL COOLER.

a. When installing fittings in the oil coolers, care should be used to prevent excessive
torque being applied to the cooler. When a rectangular fitting boss is provided, a backup
wrench should be used, employing a scissor motion, so that no load is transmitted to the
cooler. When the oil cooler has a rounds fitting boss, care should be taken not to permit
excessivetorque on the fittings.
b. If a pipe thread fitting is used, it should be installed only far enough to seal with
sealing compound.
c. Apply Lubon No. 404 to all male pipe thread fittings; do not allow sealant to enter
the system.
d. If fitting cannot be positioned correctly using a torque of 10 to 15 foot-pounds.
another fitting should be used.
e. When attaching lines to the cooler, a backup wrench should be used.
f. After installation, inspect the cooler for distorted end cups.
g. Run-up engine. After run-up, check for oil leaks.

8-24. ADJUSTMENT OF THROTTLE AND MIXTURE CONTROLS. (Refer to Figure

8-10.) Throttle and mixture controls are adjusted so that when the throttle arm on the
carburetor is rotated forward against its full throttle stop and the mixture control is rotated
forward against its full rich stop, the cockpit control knobs of the throttle and mixture
should have 0.062 to 0.125 of an inch spring back when in the forward position.
a. The throttle may be adjusted as follows:
1. At the carburetor, disconnect the clevis end of the throttle control cable from
the control arm. Loosen the jam nut that secures the clevisend.
2. Adjust the linkage by rotating the clevis end on the cable to obtain 0.062 to
0.125 of an inch spring back when the control is in the forward position.
3. Reconnect the clevisend to the control arm and safety.
b. The mixture may be adjusted as follows:
1. At the carburetor, loosen the swivelfitting that connects the wire of the control
cable to the mixture arm.

Reissued: 1/15/81
2K23 POWERPLANT
 PIPER CHEROKEE SERVICE MANUAL

OLDA/C 890 NEWA/C

0.062 TO 0.125 0.010 TO 0.030

Figure 8-10. Adjustment of Engine Controls

2. Reposition the fitting on the wire to obtain .062 to .125 of an inch spring back
between the knob and plate when the mixture control arm isagainst its stop.
3. Tighten the swivel fitting and safety. The control wire should be straighted to
align with the control cable casingafter tightening the swivel fitting.
c. Check security of cable casingattachments.
d. Pull throttle and mixture knobs in cockpit full aft to ascertain that the idle screw
contacts its stop and the mixture control arm contacts its lean position.

8-25 ADJUSTMENT OF THROTTLE AND MIXTURE CONTROLS. (PA-28-140,

Serial Nos. 28-25000and up; PA-28-180, Serial Nos. 28-4378and up; PA-28-235,Serial Nos.
28-11040 and up.) (Refer to Figure 8-10.) Throttle and mixture controls are adjusted so that
when the throttle arm on the carburetor is rotated forward against its full throttle stop and the
mixture control is rotated forward against its full rich stop, the cockpit control levers of the
throttle and mixture should have 0.010 to 0.030 of an inch spring back when in the forward
position.
a. The throttle may be adjusted as follows:
1. For PA-28-140 aircraft, S/N 28-25001 thru 28-7225373 with Kit 760 780
installed, ascertain that there is some cushion at the throttle control handle in the cockpit
with the throttle completely closed. Check that the bearing on the carburetor end of the
control cable has the proper thread engagement by use of the inspection hole. Tighten the
jam nut against the rod end of the bearing.
2. For aircraft other than those listed in Step 1, proceed as follows:
(a) At the carburetor, disconnect the clevis end of the throttle control cable
from the control arm. Loosen the jam nut that secures the clevisend.
(b) Adjust the linkage by rotating the clevis end on the cable to obtain 0.010 to
0.030 of an inch spring back on instrument stop when in full throttle
position.

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 PIPER CHEROKEESERVICE MANUAL

(c) Reconnect the clevis end to the control arm and safety.
b. The mixture may be adjusted as follows:
1. At the carburetor, disconnect the clevis end of the mixture control cable from
the control arm. Loosen the jam nut that secures.the clevis end.
2. Adjust the linkage by rotating the clevis end on the cable to obtain 0.010 to
0.030 of an inch spring back on the instrument panel stop when in full rich position.
3. On aircraft equipped with air conditioning systems, a micro switch is located
below the throttle control which is set to actuate in the full open position. With the throttle
control adjusted to obtain a clearance of .010 to .030, adjust the micro switch to actuate at
this point also.
4. Reconnect the clevisend to the control arm and safety.
c. Check security of cable casingattachment.
d. Pull throttle and mixture levers in cockpit full aft to ascertain that the idle screw
contacts its stop and the mixture control arm contacts its lean position. On 1975 models
and up, a mixture control lock is incorporated in the quadrant cover which prevents the
mixture control from being moved to the idle cutoff position inadvertently. The lock must
be depressed before the control can be moved completely aft. Ascertain that the lock
operates freely without any tendency to bind or hang up.

THIS SPACE INTENTIONALLYLEFT BLANK

Reissued
Reissued
1 /15 /01
1/15/81
2L1 PLANT
POWER
 PIPER CHEROKEESERVICEMANUAL

8-26. CARBURETOR.

8-27. CARBURETOR MAINTENANCE. In general, little attention is required between

carburetor overhauls. However, it is recommended that the following items be checked
during recommended inspection periods of the engine.
a. Check tightness and safety of all nuts and screwswhich fasten the carburetor to the
engine.
b. Check all fuel lines for tightness and evidence of leakage.
c. Check throttle and mixture control rods and levers for travel, tightness and safety.
d. Clean the fuel inlet screen. (Refer to Figure 8-11 or 8-12.)
e. Remove the plug at the aft position of the carburetor and drain any accumulation of
foreign matter.
f. Check carburetor air box for wear and full travel of heat door.
g. Check the adjustment of the idle mixture and idle speed. (Refer to paragraphs 8-29
and 8-30.)

8-28. THROTTLE ARM.

a. Remove screw securing the throttle arm to the carburetor. Do not remove the
throttle arm.
b. Remove and discard lock tab.
c. Examine the screw to determine if there is a hole through the head of the screw. If
not, drill a 1/16 inch diameter hole through the head of the screw.
d. Reinstall the screw; torque to 20 to 28 inch-pounds.
NOTE
Be sure the torque handle is correctly calibrated to insure the
attaching screw is neither under nor over tightened.
e. Using .032 inch diameter safety wire, first tie the wire to the idle stop lever and then
continue as shown in Figures 8-11 and 8-12.
f. Depending upon the carburetor model, the sequence and direction of tying may
vary; however, the idle stop arm, throttle arm, and attaching screws must all be tied
together.

8-29. ADJUSTMENT OF IDLE MIXTURE. (Refer to Figures 8-11 and 8-12.)

a. After performing the standard engine starting procedure, operate the engine for at
least two minutes between 800 to 1200 RPM to insure proper engine warmup.

Reissued: 1/15/81 2L2 POWER PLANT

 PIPER CHEROKEESERVICE MANUAL

C345
2573
1

TIGHTEN THROTTLE ARM SCREW

(8) TO 20 - 28 IN. LBS. TORQUE

Figure 8-11. Carburetor Figure 8-12. Carburetor

(PA-28-140, -150, -160) (PA-28-180, -235)

WARNING
When performing engine warm-up indoors, provide a barrier
about the engine to prevent serious injury. Also provide
adequate means of ventilating the work area.

b. Draw back on the cockpit throttle control lever to obtain a reading of

approximately 550 RPM on the tachometer.
c. Turn the idle mixture adjusting screw (1) located near the rear of the carburetor,
clockwise, leaning the fuel mixture. Continue to do this until the engine begins to run
roughly, at which time the engine speed will decrease.
d. Turn the screw counterclockwise until the engine runs smoothly again. Continue to
turn the screw in the same direction until the engine begins to run roughly once more. At
this point, the fuel mixture will be too rich and engine speed will decrease again.
e. Now advance the screw to a midway position between the lean and rich fuel
mixture; the RPM of the engine will reach a maximum speed for idle mixture settings.

Reissued:1/15/81 2L3 POWERPLANT

 PIPER CHEROKEE SERVICE MANUAL

8-30. ADJUSTMENTOF IDLE SPEED.

a. Pull back the cockpit throttle control until it is completely aft and in the closed
position: Observe the engine speed on the tachometer.
b. Adjust idle adjustment screw to obtain from 550 to 650 RPM.Rotate the screw
clockwise to increase the speed of the engine; counterclockwise to decrease the engine
speed. The screw is located on the throttle arm.

NOTE
One complete revolution of the carburetor idle screw
provides a variation of approximately 100 RPM in idling
speed.

8-31. MAGNETO.(Bendix.)

CAUTION

Ascertain that the primary circuits of both engines

are grounded before working on the engine.

8-32. INSPECTION OF MAGNETOS. (Refer to Figure 8-12.) At time of engine inspection

or when a magneto has been removed from the engine, the following checks may be per-
formed.
1. Inspect distributor block contact springs. Top of spring must not be
more than .422 inches below, top of tower as shown in Figure 8-14. If broken or
corroded, they should be replaced.
2. Inspect oil felt washer, It should be saturated with oil. If dry, check
for worn bushing. If O.K., add No. 30 oil.
3. Inspect distributor block for cracks or burned areas. The wax coating
on the block should not be removed. Do not use solvents.
4. Look for excess oil in breaker compartment. If present, it may mean
a bad oil seal or oil seal bushing at drive end. Check manufacturer's overhaul
procedure.
5. Look for frayed insulation or broken wire strands in leads in back of
magneto. See that terminals are secure. Be sure wires are properly positioned.
6. Inspect capacitor visually. If possible, test for leakage, capacity and
series resistance. Remember, an electrical failure of an aircraft capacitor is
rare.
7. Adjustment of breakers must be correct for proper internal timing of
magneto. (Refer to paragraph 8-34.)
8. Check if breaker cam is clean and smooth; if cam screw is. tight (25 in.

Reissued:1/15/81 2L4 POWER PLANT

 PIPER CHEROKEESERVICE MANUAL

A851

15

21

4 9

CONTACTSPRING 13
CONTACT SPRING 5. LEAD WIRE 9. IMPULSE COUPLING
2 RETAINNGRING 6 CAPACITOR 10. FLYWEIGHTS 13. CONTACTSPRING
3 DISTRIBUTORBLOCK 7 BREAKERASSEMBLY 11. DELETED 14. INSULATOR
4 BREAKERCOMPARTMENT 8 BREAKERCAM 12 LEADCIRCUIT 15. VENTPLUG

Figure 8-13. Magneto Inspection(Bendix)

lbs.). If new points are installed, blot a little oil on cam.

9. Inspect impulsecoupling (-21 and -204 magneto) flyweights for excessive
looseness on the axles. Design couplings having .927 inch thick body should be
checked with 1/8 inch drill. Couplings with .974 inch thick body are checked with
a No. 18 drill. If drill fits between cam and flyweight, the fit is too loose and
coupling should be replaced. (Refer to Figure 8- 15.)
10. Check impulse coupling for excess wear on the contact edges of body
and flyweights.
-11. Checkthat the impulse couplingflyweight axle rivets are tight and there
are no cracks in body.
12. Look at the lead conduits. A few broken strands won't hurt, but if the
insulation looks tired, you may be in for trouble. The special high temperature
coating, used on light-weight harnesses, is provided chiefly for vibration resist-
ance and mechanical protection. The integrity of the harness is not sacrificed if
small areas of the braid show peeling or flaking of this coating.
13. Check the springs for breaks, corrosion, or deformation. If possible,
check continuity from block with tester or light.
14. Check insulators for cracks, breaks, or evidence of "old age". Be sure
they are clean.
15. Timing and ventilator plugs. Ventilator has drilled holes and should be
in lowest hole in magneto to serve also as drain for excess water or oil. Solid
plug is used in other hole or in location exposed to rain or water.

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.2L5
 PIPER CHEROKEESERVICE MANUAL

A825 0.422 MAX. C326

MEASURE BODY
THICKNESS HERE

Figure 8-14. Contact Spring Inspection Figure 8-15. Impulse Coupling

8-33. REMOVAL OF MAGNETOS. Before removing the magneto, make sure
magneto switches are OFF.
a. Remove the harness assembly terminal plate-from the magneto.

WARNING

The magneto is not internally grounded; when the

ground lead is disconnected, the magneto is hot. Re-
moving the harness assembly terminal plate first and
installing them last, minimizes the danger of starting
the engine accidentally when the ground lead is re-
moved from the magneto.

b. Disconnect the ground lead at the magneto.

c. Remove the nuts and washers and draw the magneto from the engine.

NOTE

The magneto service instructions in this manual are

to cover minor repairs and timing. For further re-
pairs and adjustments of the magnetos, it is recom-
mended that the latest revision of the magneto manufacturer's
service instructions be followed.

POWER PLANT
Reissued: 1/15/81 2L6
 PIPER CHEROKEESERVICE MANUAL

826 C326
RED OR
WHITE TOOTH

2 1/4 IN.

SOFTWIRE 3/ 4IN.
SOLDER

CAM WASHER

TIMING MARK-

Figure 8-16. Magneto Timing Marks Figure 8-17. Timing Pointer

8-34. TIMING PROCEDURE. (Internal Timing) (-20 and -200 Series Magnetos)
When installing new or adjusting breaker points and before timing the magneto to
the engine, it is important that the internal timing of the magneto be correct.
a. To internally time the -20 series and the early -200 series magneto with-
out the case in timing marks, the magneto should be removed from the engine to
determine "E" gap.
b. To determine "E" gap, find neutral position of the magneto drive by rotat-
ing drive coupling in a left hand direction until the red or white chamfered tooth
on the distributor drive gear appears through the timing inspection hole. At the
same location, the drive should feel to have fallen into a notch or neutral position.
c. With timing plate and pointer attached (Refer to Figure 8-17.) and pointer
set at zero, rotate couplingfrom neutralin a left hand direction 10 degrees. Ap-
pearing through timing hole, ascertain if the white or red tooth aligns with the
white line of the distributor block. (Refer to Figure 8-16.) Alignment may not
vary over + 4 degrees.

NOTE-

A timing kit, including timing plate, etc. may be pur-

chased through the engine or magneto manufacturer.
A pointer may be formed as shown in Figure 8-17.

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 PIPER CHEROKEESERVICE MANUAL

C326 C326

MARK HOUSING
HOUSING CENTER CENTER
MARK

~30 30 TIMING LINE

NUMBER OF DEGREES RETARD

Figure 8-18. Timing Kit Installed Figure 8-19. Breaker Compartment

with Cast Timing Marks

d. Using the alignment of the gear marked with the white line of the distribu-
tor block as a reference, adjust breaker points to open at this point. Turn the
magneto drive until the cam follower is on high point of the cam lobe. Measure
contact clearance, it must be .018 inch + .006 with the "E" gap set 10 degrees
+ 4 degrees. If breaker points do not come within tolerances, they should be re-
placed.

NOTE

A pointer can also be made by wrapping a piece of soft

wire tightly around the head of cam securing screw and
bending it to extend over timing marks.

e. If magneto is type which has "cast in" timing marks (-200 series, see Fig-
ure 8-19), main breaker may be adjusted with magneto on engine as follows: turn
engine crankshaft until notch in cam is aligned with mark at top of breaker com -
partment. Set wire pointer in center of the "E" gap boss at the side of breaker
compartment. Connect timing light across main breaker. Adjust main breaker
contacts to open at this point. Turn engine crankshaft until cam follower is on
the high point of the cam lobe. Measure contact clearance. It must be .018 +
.006. If necessary, readjust breaker and recheck to be sure that contacts will
open within "E" gap tolerance + 4 degrees. (Width of "E" gap boss.)

Reissued:1/15/81 2L8. POWER PLANT

 PIPER CHEROKEESERVICE MANUAL

CAUTION

If cam screw was removed, be sure to replace flat

washer, lock washer and screw. Torque to 25 inch
pounds.

f. With internal timing checked, the magneto may be timed to the engine.
(Refer to paragraph 8-35.)

8.35. INSTALLATION AND TIMING PROCEDURE. (Timing Magneto to Engine).

The magnetos can be installed and timed to the engine by the following procedure:

NOTE

Ascertain that the breakers are correct for proper in-

ternal timing of magnetos.

a. Remove the top spark plug from No. one cylinder. Place the thumb of one
hand over the spark plug hole and rotate the crankshaft in direction of normal ro-
tation until the compression stroke is reached. The compression stroke is indi-
cated by a positive pressure inside the cylinder tending to lift the thumb off the
spark plug hole. In this position both valves of No. one cylinder are closed. Turn
the crankshaft opposite to its normal direction of rotation until it is approximately
35 degrees BTC on the compression stroke of No. one cylinder. Rotate the crank-
shaft in its normal direction of rotation until the 25 degrees mark on the starter
gear and the crankcase parting flange or the index on the front of the starter
housing are aligned.
b. Rotate the magneto gear on the right magneto until the chamfered tooth on
the distributor gear inside the magneto aligns with the white pointer as seen
through the window in the magneto cover. Without allowing the gear to turn from
this position, assemble the magneto and gasket. Secure magneto in place with
washers and nuts; tighten the nuts only finger tight.
c. Fasten ground wire on electric timing light to any unpainted metallic por-
tion of the engine, and one of the positive wires of the timing light to a suitable
terminal connected to the ground terminal connection of the right magneto. Turn
engine crankshaft several degrees from BTC in directionopposite to that of nor-
mal rotation.

Reissued: 1/15/81 2L9 POWER PLANT

 PIPER CHEROKEE SERVICE MANUAL

d. Turn on the switch of the timing light. Turn the crankshaft very slowly in
direction of normal rotation until the timing mark on the front face of the ring
gear support aligns with the drilled hole in the starter, at which point the light
should go on, (on battery operated models). If not, turn the magneto in its mount-
ing flange slots and repeat the procedure until the light goes on at 25 degrees be-
fore top dead center. Tighten the two mounting nuts and replace magneto inspec-
tion plug.
e. Install the impulse coupling magneto adapter and gasket on the left magneto
mounting pad of the accessory housing.

CAUTION

The impulse coupling magneto can be used only on the

left side of the engine (as viewed from rear).

f. Remove inspection plug, depress pawl on impulse coupling shaft and turn
impulse coupling on left magneto until the white beveled tooth (or middle tooth, if
timing gear has three beveled teeth) aligns with the timing pointer. Without al-
lowing the magneto gear to turn from this position, assemble the left magneto to
the accessory housing and secure with washers and nuts. Tighten nuts only finger
tight.
g. Connect the other positive wire of the timing light to a suitable terminal
connection of the left magneto and time the magneto in the same manner as de-
scribed for the right magneto.
h. After both magnetos have been timed, leave the timing light wires connected
and recheckmagneto timing as previously described to make sure that both mag-
netos are set to fire together. If timing is correct, both timing lights will go on
simultaneously when the 25 degree mark aligns with the centerline of the crank-
case. If the breaker points open too early, loosen the mounting nuts and rotate
the magneto clockwise. If the breaker points open too late, rotate the magneto
counterclockwise. Remove timing light and ignition timing pointer, and replace
timing inspection plug in magneto.
i. After the magnetos have been properly timed, clean the breaker points to
remove any trace of oil or dirt. Replace breaker cover and lock the retaining
screws together with lockwire.

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2L10 POWER PLANT
 PIPER CHEROKEE SERVICE MANUAL

NOTE
The crankshaft should not be rotated more than 10 degrees
in direction opposite normal rotation as the pawl on the
impulse coupling will engage with the stop pin and late
timing will be indicated through the impulse coupling
mechanism. If this should happen, rotate crankshaft in
normal direction until sharp click is heard; this will indicate
that the impulse coupling has passed through fiing position.
Turn crankshaft in direction opposite normal rotation to
approximately 35 degrees BTC and proceed with timing
check.

8-36. MAGNETO. (Slick.)

a. For service information concerning these magnetos refer to the latest revisions of
Lycoming Service Letter No. L177 and Lycoming Service Instruction No. 1189.

8-37. HARNESSASSEMBLY

8-38. INSPECTION OF HARNESS.

a. Check lead assemblies for nicks, cuts, mutilated braiding, badly worn section or any
other evidence of physical damage. Inspect spark plug sleeves for chafing or tears and
damaged or stripped threads on coupling nuts. Check compression spring to see if it is
broken or distorted. Inspect grommet for tears. Check all mounting brackets and clamps to
see that they are secure and not cracked.
b. Using an ohmmeter, buzzer, or other suitable low voltage device, check each lead for
continuity. If continuity does not exist, wire is broken and must be replaced.
c. Minor repair of the harness assembly, such as replacement of contact springs, spring
retainer assemblies, insulating sleevesor of one lead assembly, can be accomplished with the
harness assembly mounted on the engine. However, should repair require replacement of
more than one lead assemblyor of a cable outlet plate, the harness should be removed from
the engine and sent to an overhaul shop.

8-39. REMOVALOF HARNESS.

a. Disconnect the clamps that secure the wires to the engine and accessories.
b. Loosen the coupling nuts at the spark plugs and remove the insulators from the
spark plug barrel well. Use caution when withdrawing the insulator not to damage the
insulator spring.
c. Place a guard over the harness insulators.

Reissued: 1/15/81 2L11 POWER PLANT

 PIPER CHEROKEESERVICE MANUAL

d. Remove the harness assembly terminal plate from the magneto.

e. Remove the engine baffle plate that receives the harness assembly.
f. Remove the harness from the airplane.

8-40. INSTALLATION OF HARNESS. Before installing harness on magneto,

check mating surfaces for cleanliness. Spray entire face of grommet with a light
coat of Plastic Mold Spray, SM-O-O-TH Silicone Spray or equivalent. This will
prevent harness grommet from sticking to magneto distributor block.
a. Place the harness terminal plate on the magneto and tighten nuts around the
plate alternately to seat cover squarely on magneto. Torque nuts to 18 to 22 inch
pounds.
b. Route ignition wires to their respective cylinders.
c. Clamp the harness assembly in position and replace the engine baffle plate.
d. Connect the leads to the spark plugs.

8-41. SPARK PLUGS.

8-42. REMOVAL OF SPARK PLUGS.

a. Loosen the coupling nut onthe harness lead and remove the terminal insu-
lator from the spark plug barrel well.

NOTE

When withdrawing the ignition cable lead connection

from the plug, care must be taken to pull the lead
straight out and in line with the center line of the plug
barrel; otherwise, a side load will be applied which
frequently results in damage to the barrel insulator
and connector. If the lead cannot be removed easily in
this manner, the resisting contact between the neo-
prene collar and the barrel insulator will be broken by
a rotary twisting of the collar. Avoid undue distortion
of the collar and possible side loading of the barrel
insulator.

b. Remove the spark plug from the engine. Inthe course of engine operation,
carbon and other combustion products will be deposited on the end of the spark
plug and will penetrate the lower threads to some degree. As a result, greater
torque is frequently required for removing a plug than for its installation. Ac-

Reissued: 1/15/81 POWER PLANT

2L12
 PIPERCHEROKEE
SERVICEMANUAL

cordingly, the torque limitations given 234

do not apply to plug removal and suffi-
cient torque must be used to unscrew
the plug. The higher torque in removal
is not as detrimental as in installation,
since it cannot stretch the threaded sec-
tion. It does, however, impose a shear-
ing load on this section and may, if suf-
ficiently severe, produce a failure in
this location.

NOTE

Torque indicating handle

should not be used for spark
plug removal because of the Figure 8-20. Removing Spark Plug
greater torque require- Frozen to Bushing
ment.

c. Place spark plugs in a tray that will identify their position in the engine as
soon as they are removed.

NOTE

Spark plugs should not be used if they have been drop-

ped.

d. Removal of seized spark plugs inthe cylinder may be accomplished by ap-

plication of liquid carbon dioxide by a Conical metal funnel adapter with a hole at
the apex just large enough to accommodate the funnel of a CO2 bottle. (Refer to
Figure 8-20.) When a seized spark plug cannot be removed by normal means,
the funnel adapter is placed over and around the spark plug. Place the funnel of
the CO2 bottle inside the funnel adapter and release the carbon dioxide to chill
and contract the spark plug. Break the spark plug loose with a wrench. A warm
cylinder head at the time the carbon dioxide is applied will aid in the removal of
an excessively seized plug.
e. Do not allow foreign objects to enter the spark plug hole.

Reissued: 1/15/81 2L13 POWER PLANT

 PIPER CHEROKEE SERVICE MANUAL

8-43. INSPECTION AND CLEANING OF SPARK PLUG.

a. Visually inspect each spark plug for the following non-repairable defects:
1. Severely damaged shell or shield threads nicked up, stripped or cross-
threaded.
2. Badly battered or rounded shell hexagons.
3. Out-of-round or damaged shielding barrel.
4. Chipped, cracked, or broken ceramic insulator portions.
5. Badly eroded electrodes worn to approximately 50% of original size.
b. Clean the sparkplug as required, removing carbon and foreign deposits.
c. Test the spark plug both electrically and for resistance.
d. Set the electrode gap at .015 to .018 of an inch or if a smoother operation
at idle speed and reduced magneto drop-off is desired, set at .018 to .022 of an
inch. However, with wide gap setting the plugs must be serviced at more fre-
quent intervals. Fine wire platinum or iridium electrodes should be set at .015
to .018 of an inch only.

8-44. INSTALLATION OF SPARK PLUGS. Before installing spark plugs, ascer-

tain that the threads within the cylinder are clean and not damaged.
a. Apply anti-seize compound sparingly on the threads and install gasket and
spark plugs. Torque 360 to 420 inch pounds.

CAUTION

Make certainthe deep socketis properly seated on the

spark plug hexagon as damage to the plug could result
if the wrench is cocked to one side when pressure is
applied.

b. Carefully insert the terminal insulator in the spark plug and tighten the
coupling nut.

8-45. LUBRICATION SYSTEM.

8-46. OIL PRESSURE RELIEF VALVE. Subject engines may be equipped with
either an adjustable or non-adjustable oil pressure relief valve. A brief descrip-
tion of both types follows:
a. Non-adjustable Oil Pressure Relief Valve - The valve is notadjustable; how-
ever, the pressure can be controlled by the addition of a maximum of three STD-
425 washers under the cap to increase pressure or the use of a spacer (Lycoming

Reissued: 1/15/81 2L14 POWER PLANT

 PIPER CHEROKEESERVICE MANUAL

P N 73629or 73630)to decrease pressure. Particles of metal or otherforeign matter lodgedbe-

tween the ball and seat will result in a drop in oil pressure. It is advisable, therefore, to dis-
assemble. inspect, and clean the valve if excessivepressure fluctuations are noted. The oil pres-
sure relief valve is not to be mistaken for the oil cooler by-pass valve, whose function is to per-
mit pressure oil to by-pass the oil cooler in case of an obstruction.
b. Adjustable Oil Pressure Relief Valve- The adjustable oil pressure relief valve enables
the operator to maintain engine oil pressure within the specified limits (refer to the engine
manufacturer's appropriate manual). The valve is located above and to the rear of No. 3
cylinder. If the pressure under normal operating conditions should consistently exceed 90
psi.. or run less than 60 psi.. adjust the valve as follows:
With the engine thoroughly warmed up and running at a maximum of 2200 RPM.
observe the reading on the oil pressure gauge. If the pressure is above 90 psi.. stop engine.
loosen the adjusting lock nut: and back off the adjusting screw one or two full turns. Tighten
lock nut and retest. If pressure istoo low.turn adjusting screwfurther into the reliefvalveplug.
thereby increasing the tension on the relief valve spring. When the valvehas beensatisfactorily
adjusted. tighten the lock nut and lockwirethe crown nut to the drilled ear projectingfrom the
valve mounting boss.

8-47. SWITCHING.

8-48. REMOVAL OF IGNITION SWITCH.

a. Insure the ignition switch is in the off position.
b. Gain access to and disconnect the power lead (+) from the battery.
c. Remove the ignition switch retaining nut from the switch on the forward side of the
instrument panel and withdraw the switch from the panel.
d. Mark the wires and note their position on the switch. then disconnect the wires.

8-49. INSTALLATION OF IGNITION SWITCH. (Refer to Figure 8-21.)

a. Attach wires to the switch as shown in Figure 8-21.
b. Position the ignition switch in the instrument panel and secure with retaining nut.
c. Connect the power lead (-) to the battery and reinstall any access covers previously
removed.

Revised: 8 3 81 2L15 POWER PLANT

 PIPER CHEROKEE SERVICE MANUAL

C216

PA-28-180..S/N 28-7505001 AND UP

PA-28-235. S/N 28-7510001 AND UP

J2A

K1B

GND

C236

PA-28-140. S/N 28-25000 AND UP

PA-28-180. S/N 28-4378 TO 28-7405290
B
PA-28-235, S/N 28-11040 TO 7410120

Figure 8-21. Ignition Switch WiringPositions

Added: 8 3 81 2L16 POWER PLANT

 PIPER CHEROKEE SERVICE MANUAL

TABLE VIII-I. ENGINE TROUBLESHOOTINGCHART

Trouble Cause Remedy

Failure of engine to Lack of fuel. Check fuel system for

start. leaks.
Fill fuel tank.
Clean dirty lines,
strainers, or fuel
cocks.

Underpriming. Prime with two or three

strokes of primer.

Overpriming. Open throttle and "un-

load" engine by turn-
ing in counter-clock-
wise direction.

Incorrect throttle set- Open throttle to one-

ting. tenth of its range.

Defective spark plugs. Clean and adjust or re-

place spark plug or
plugs. Refer to
Table I for spark plug
gap adjustments.

Defective ignition wire. Check with electric test-

er and replace any
defective wires.

Improper operation of Check internal timing

magneto breaker of magnetos.
points. Check points.

Internal failure. Check oil sump screen

for metal particles.
If found, complete
overhaul of the en-
gine may be indicated.

Reissued:1/15/81 2L17 POWER PLANT

 PIPER CHEROKEE SERVICE MANUAL

TABLE VIII-II. ENGINE TROUBLESHOOTING CHART (cont)

Trouble Cause Remedy

Failure of engine Improper switch wiring Reverse magneto switch

to start. (cont) for left magneto wires.
starting.

Magnetized impulse Demagnetize impulse

coupling - left mag- couplings.
neto only.

Frozen spark plug Replace spark plugs or

electrodes. dry out removed
plugs.

Mixture control in idle Open mixture control.

cut-off.

Shorted ignition switch Check and replace or

or loose ground. repair.

Failure of engine to Incorrect carburetor Adjust throttle stop to

idle properly. idle adjustment. obtain correct idle.

Idle mixture. Adjust mixture. Refer

to engine manufac-
turer's handbook for
proper procedure.

Leak in the induction Tighten all connections

system. in the induction sys-
tem. Replace any
parts that are defec-
tive.

Low cylinder com- Check cylinder com-

pression. pression.

Reissued:1/15/81 2L18 POWER PLANT

 PIPER CHEROKEESERVICEMANUAL

TABLEVII-II. ENGINE TROUBLESHOOTINGCHART (cont)

Trouble Cause Remedy

Failure of engine to Faulty ignition system. Check entire ignition

idle properly. (cont) system.

Open primer.. Lock primer.

Improper spark plug Check spark plug gap.

setting for altitude.

Dirty air filter. Clean or replace.

Low power and uneven Mixture too rich; in- Check primer. Read- d-
running engine. dicated by sluggish justment of carb-
engine operation, uretor indicated.
red exhaust flame
and black smoke.

Mixture too lean; in- Check fuel lines for dirt

dicated by overheat- or other restrictions.
ing or backfiring. Check fuel supply.

Leaks in induction Tighten all connections.

system. Replace defective
parts.

Defective spark plugs. Clean or replace spark

plug.

Improper grade-of Fill tank with recom-

fuel. mended grade.

Magneto breaker Clean points.

points not working Check internal timing of
properly. magneto.

Defective ignition wire. Check wire with elec-

tric tester. Replace

Reissued:1/15/81 2L19 POWER PLANT

 PIPER CHEROKEE SERVICE MANUAL

TABLEVIII-II. ENGINE TROUBLESHOOTING CHART (cont)

Trouble Cause Remedy

Low power and uneven defective wire.

running engine. (cont)

Defective spark plug Replace connectors on

terminal connectors. spark plug wire.

Restriction in exhaust Check for loose muffler

system. baffles.

Improper ignition tim- Check magnetos for

ing. trimming and
synchronization.

Failure of engine to Throttle lever out of Adjust throttle lever.

develop full power. adjustment.

Leak in induction Tighten all connections,

system. and replace defective
parts.

Restriction in carb- Examine air scoop and

uretor air scoop. remove restriction.

Improper fuel. Fill tank with recom-

mended fuel.

Faulty ignition. Tighten all connections.

Check system. Check

ignition timing.

Reissued: 1/15/81 2L20 POWER PLANT

 PIPER CHEROKEE SERVICE MANUAL

TABLE VIII-II. ENGINE TROUBLESHOOTINGCHART (cont)

Trouble Cause Remedy

Rough running engine. Cracked engine mounts. Repair or replace engine

mount.

Unbalanced propeller. Remove propeller and

have it checked for
balance.

Bent propeller blades. Check propeller for

track.

Defective mounting. Install new mounting

bushings.

Lead deposit on spark Clean or replace plugs.

plug.

Malfunctioning engine. Check entire engine.

Low oil pressure. Insufficient oil. Check oil supply.

Dirty oil screens. Remove and clean oil

screens.

Defective pressure Replace gauge.

gauge.

Air lock or dirt in Remove and clean oil

relief valve. pressure relief valve.

Leak in suction line or Check gasket between

pressure line. accessory housing
crankcase.

High oil temperature. See "High Oil Temper-

ature" in Trouble
Column.

Reissued: 1/15/81 2L21 POWER PLANT

 PIPER CHEROKEE SERVICE MANUAL

TABLEVIII-II. ENGINE TROUBLESHOOTING CHART(cont)

Trouble Cause Remedy

Low oil pressure. Stoppage in oil pump Check line for obstruc-
(cont) intake passage. tion. Clean suction
screen.

Worn or scored Overhaul.

bearings.

High oil temperature. Insufficient air cool- Check air inlet and out-
ing. let for deformation
or obstruction.

Insufficient oil supply. Fill oil sump to proper

level.

Clogged oil lines or Remove and clean oil

screens. screens.

Failing or failed bear- Examine sump for metal

ing. particles and, if
found, overhaul
engine.

Defective thermo- Replace.

stats.

Defective temper- Replace gauge.

ature gauge.

Excessive blow-by. Usually caused by weak

or stuck rings. Over-
haul.

Improper engine oper- Check entire engine.

ation.

Reissued:1/15/81 2L22 POWER PLANT

 CHEROKEE
MANUAL
SERVICE
CARD3 OF4

PA-28-140
PA-28-150
PA-28-160
PA-28-180
PA-28-235
PA-28R-180
PA-28R-200

CORPORATION
PIPERAIRCRAFT
753586)
(PARTNUMBER 3A1
 PIPER CHEROKEESERVICEMANUAL

AEROFICHE EXPLANATION AND REVISION STATUS

The Service Manual information incorporated in this set of Aerofiche cards has been arranged in
accordance with the general specifications of Aerofiche adopted by the General Aviation Manufacturer's
Association, (GAMA). The information compiled in this Aerofiche Service Manual willbe kept current by
revisions distributed periodically. These revisionswill supersede all previous revisionsand willbe complete
Aerofiche card replacements and shall supersede Aerofiche cards of the same number in the set.
Conversion of Aerofiche alpha/numeric code numbers:
First number is the Aerofiche card number.
Letter is the horizontal line reference per card.
Second number is the vertical line reference per card.
Example: 2J16 = Aerofiche card number two of given set, Grid location J16.
To aid in locating the various chapters and related service information desired,the followingis provided:

1. A complete manual Table of Contents is for all fiche in this set.

2. A complete list of Illustrations is given and follows the Table of Contents.
3. A complete list of Tables is given for all fiche in this set and follows the list of Illustrations.
4. A complete list of paragraph titles and appropriate Grid locationnumbers is givenat the beginningof
each Chapter relating to the information within that Chapter.
5. Identification of Revised Material:
Revisedtext and illustrations are indicated by a black vertical line along the left-hand marginof
the frame, opposite revised,added or deleted material. Revision linesindicate only current revisions
with changes and additions to or deletionsof existingtext and illustrations.Changesin capitalization,
spelling, punctuation, indexing, the physical location of the material or completepageadditions are
not identified by revision lines.
6. Revisions to this Service Manual 753 586 issued August 16, 1972are as follows:
Effectivity Publication Date Aerofiche Card Effectivity
ORG720816 August 16, 1972 -
CR810115 January 15, 1981 1, 2, 3 and 4
PR810803 August 3, 1981 1, 2, 3 and 4
PR831003 October 3, 1983 1, 2, 3 and 4
PR840423 April 23, 1984 1, 2, 3 and 4
PR860115 January 15, 1986 1 and 3
IR860730 July 30, 1986 1
IR870506* June 12,1987 1

This publication contains material revisedas of January 15, 1986(with two interim revisionseffectiveJuly
30, 1986and May 6, 1987).
* INTERIM CHANGE
Revisions appear in Table III-I and Table III-II of card 1.
There are no other changes included in this maintenance
manual.Pleasediscardyour currentcard 1 and replaceit with
this revisedone. DO NOT DISCARD CARDS 2, 3, or 4.
The date on Aerofiche cards should not be earlier than the date noted for the respectivecard effectivity.
Consult the latest card in this series for current Aerofiche card effectivity.

3A2
 AIX
NIIV IIIX
IIX
8V 33 IX

8 X
8 X
VIIIA

III
VIIA
IIA
IA
A

S3 Al

II
. ... . .. . . . .
I
L'ONO

S
 PIPER CHEROKEE SERVICE MANUAL

LIST OF ILLUSTRATIONS (cont.)

Figure Aerofiche
Grid No.

8A-1. Propeller Installation ........................................ 3A12

8A-2. Typical Nicks and Removal Method ............................ 3A13
8A-3. Propeller Governor ........................................... 3A16
8A-4. Engine Installation, PA-28R-180 ............................... 3A19
8A-5. Engine Installation, PA-28R-200 ............................... 3A21
8A-6. Adjustment of Engine Controls ................................. 3BI
8A-7. Fuel Injector ................................................. 3B3
8A-8. Schematic Diagram of RSA Fuel Injection System ................ 3B4
8A-9. Fuel-Air Bleed Nozzle......................................... 3B6
8A-10. Contact Points .......... ... ................. ........... 3B8
8A-11. Rotor Holding Tool Installed .... .............................. 3B10
8A-12. Timing Kit Installed .......................................... 3B10
8A-13. Aligning Timing Marks ....................................... 3B11
8A-14. Checking Flyweight Clearance of Impulse Coupling ............... 3B 12
8A-15. Engine Timing Marks ..................... ................... 3B13
8A-16. Magneto Adjustment Limits ................................... 3B14
8A-17. Magneto Timing Marks ........................ ............... 3B14
8A-18. Removing Spring From Lead Assembly ......................... 3B16
8A-19. Assembly Tool ............................................... 3B16
8A-20. Using Assembly Tool ...................................... . 3B 17
8A-21. Measuring Lead Assembly Length .............................. 3B 17
8A-22. Cutting Metallic Braid From End of Lead ....................... 3B18
8A-23. Unbraiding Metallic Shielding.................................. 3B18
8A-24. Forming Shielding Around Ferrule ............................. 3B19
8A-25. Ferrule Seating Tool .......................................... 3B19
8A-26. Needle ...................................................... 3B19
8A-27. Measuring Wire From Top of Ferrule ........................... 3B20
8A-28. Installing Grommet Over Lead Assemblies....................... 3B20
8A-29. Lead Assembly Installed in Grommet ........................... 3B20
8A-30. Wire Doubled Over For Installation of Eyelet .................... 3B20
8A-31. Removing Spark Plug Frozen to Bushing ........................ 3B22
8A-32. Ignition Switch Wiring Positions ...................... ......... 3B24
9-1. Fuel System Diagram, PA-28-140,-150, -160, -180 ................ 3C11
9-2. Fuel System Diagram, PA-28-235, Serial Nos. 28-10003
to 28-10719incl........................................... 3C12
9-3. Fuel System Diagram, PA-28-235, Serial Nos. 28-10720 and up .... 3C13
9-4. Fuel System Diagram, PA-28R ................................. 3C14
9-5. Deleted .....................................................
9-6. Fuel Quantity Transmitter (P/N 62037-00)....................... 3C21
9-7. Fuel Quantity Transmitter (P/N 68101-00)....................... 3C21
9-8. Fuel Selector and Filter, PA-28-235 ............................. 3C24
9-9. Fuel Filter, PA-28-235 ........................................ 3DI

Revised: 8/3/81 3A4

 PIPER CHEROKEE SERVICE MANUAL

LIST OF ILLUSTRATIONS(cont.)

Aerofiche
Figure Grid No.

9-10. Fuel Filter Bowl and Screen (PA-28-140, -150, -160, -180
and PA-28R) .............................. 3D3
9-11. Plunger Fuel Pump (Early), PA-28-150, -160, -180 .......... 3D6
9-12. Plunger Fuel Pump (Late), PA-28-140, -150, -160, -180,
-235 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3D6
9-13. Engine Primer ............................... 3D12
9-14. Fabricated Fuel Quantity Transmitter Checking Jig .......... 3D17
10-1. Instrument Panel, PA-28-140, Serial Nos. 28-25000 to
28-26956 incl. ............................ 3E4
10-2. Instrument Panel, PA-28-140, Serial Nos. 28-7125001 to
28-7325684 incl ........................... 3E5
10-3. Instrument Panel, PA-28-140, Serial Nos. 28-7425001
and up .. ... ... .. . ... . .. ... ... ... ... . .. . 3E6
10-4. Instrument Panel .............................. 3E7
10-5. Instrument Panel, PA-28-150, -160, -180, Serial Nos.
28-1761 to 28-4377 incl ....... 3E8
10-6. Instrument Panel, PA-28-180, Serial Nos. 284378 to
28-7205328 incl . .......... 3E9
10-7.. Instrument Panel, PA-28-180, Serial Nos. 28-7305001 to
28-7305611 incl . .......... 3E10
10-8. Instrument Panel, PA-28-180, Serial Nos. 28-7405001 and up ... 3E11
10-9. Instrument Panel, PA-28-235, Serial Nos. 28-10720 to
28-11039 incl.............. . . . . . . . . . . . . . . . . 3E12
10-10. Instrument Panel, PA-28-235, Serial Nos. 28-11040 to
28-7210033 incl . .......... · . . . . . . . . . . . .. 3E13
10-11. Instrument Panel, PA-28-235, Serial Nos. 28-7310001 to
28-7310187 incl . .......... 3E14
10-12. Instrument Panel. PA-28-235, Serial Nos. 28-7410001 and up .... 3E15
10-13. Instrument Panel, PA-28R-180, Serial Nos. 28-30005 to
28-30879 incl............................. 3E16
10-14. Instrument Panel, PA-28R-180, Serial Nos. 28-30880 to
28-7130019 incl.; PA-28R-200, Serial Nos. 28-30482,
28-35001 to 28-35830 incl. and 28-7135001 to
28-7135238 incl . .......................... 3E17
10-15. Instrument Panel, PA-28R-200, Serial Nos. 28-7235001 to
28-7335455 incl . .......................... 3E18
10-16. Instrument Panel. PA-28R-200. Serial Nos. 28-7435001 and up . . . 3E19
10-17. Warning Light Pressure Switch ...................... 3E23
10-18. Typical Pitot Static System, PA-28-140,-150,-160, -180,-235,
PA-28R-180 and 200 ......................... 3F4
10-19. EGT Probe Location (PA-28R-180 and 200) .................... 3 F24
10-20. EGT Probe Location (PA-28-235) ............................. 3G1
10-21. EGT Probe Location (PA-28-150/ 160/180) S/N 1761 and up . ... 3G2

Reissued: 1/15/81 3A5

 PIPER CHEROKEE SERVICE MANUAL

LISTOFTABLES
Aerofiche
Table Grid No.
VIIIA-I
IIA-I. Engine Troubleshooting Chart ........... . ... . .. . .. 3C1
IX-I. Transmitter/Fuel Gauge Tolerances ........ . .. . . .. . .. . 3C20
IX-II. Fuel Quantity Transmitter Calibration Tolerances . . .. . . . ... . 3C21
IX-III. Fuel System Troubleshooting ..... . ... .. . . .. . 3D15
X-I. Vacuum System ................... . ... . . . ... . 3D24
X-II. Directional Gyro Indicator ............. . . .. ... ... . 3F5
X-III. Gyro Horizon Indicator ............... . ... .. . ... . 3F7
X-IV. Rate of Climb Indicator ............... . ... . .. . .. . 3F8
X-V. Altimeter ........... . . .. . .. .. .. 3F10
X-VI. Airspeed Tubes and Indicator ..... . ... .. . .. .. 3F12
X-VII. MagneticCompass ........... ...... . ... .. . .. . . 3F 14
X-VIII. ManifoldPressure Indicator ............ . .. . . .. ... . 3F15
X-IX. Tachometer...................... . ... .. . . .. . 3F 16
X-X. Engine Oil PressureGauge ...... . ... . . . ... . 3F17
X-XI. Fuel PressureGauge ................. . .. . . .. ... . 3F18
X-XII. Turn and Bank Indicator .............. . ... . . . ... . 3F19
X-XIII. Fuel Quantity Indicators ... ...... ..... . ... ... ... . 3F20
X-XIV. Oil Temperature Indicators ...... ...... . . .. .. . .. . . 3F21
X-XV. Troubleshooting EGT Gauge ............ . . .. . .. ... . 3F23
X-XVI. Cylinder Head Temperature Gauge ... . .. .. . ... .. 3G3
X-XVII. Fuel Flow Gauge ................. ... . .. . .... 3G4

Reissued: 1/15/81 3A6

 3A7
INTENTIONALLY LEFT BLANK
 PIPER CHEROKEE SERVICE MANUAL

SECTION VIIIA
POWER PLANT
(PA-28R)

Paragraph Aerofiche
Grid No.
8A-1. Introduction ................................................. 3A10
8A-2. Description ............................................... 3A10
8A-3. Troubleshooting .............................................. 3A10
8A-4. Propeller .................................................... 3A11
8A-5. Removal of Propeller ................................ 3A11
8A-6. Cleaning, Inspection and Repair of Propeller ............ 3A11
8A-7. Installing Propeller .................................. 3A13
8A-8. Blade Track ......................................... 3A14
8A-9. Propeller Governor ........................................... 3A14
8A-10. Removal of Propeller Governor ....................... 3A14
8A- 11. Installation of Propeller Governor ..................... 3A14
8A-12. Rigging and Adjustment of Propeller Governor.......... 3A15
8A-13. Engine ...................................................... 3A16
8A-14. Removal of Engine ................. .............. 3A16
8A-15. Installation of Engine ................................ 3A17
8A-16. Installation of Oil Cooler ..................................... 3A24
8A-17. Adjustment of Throttle and Mixture Controls .................... 3B 1
8A-18. Induction Air Filter. .......................................... 3B2
8A-19. Alternate Air Door ........................................... 3B2
8A-20. Fuel Injector ................................................ 3B3
8A-21. Fuel Injector Maintenance ............................ 3B3
8A-22. Adjustment of Idle Speed and Mixture .......................... 3B5
8A-23. Fuel Air Bleed Nozzle......................................... 3B6
8A-24. Removal of Fuel-Air Bleed Nozzle ..................... 3B6
8A-25. Cleaning and Inspection of Fuel-Air Bleed
Nozzle ........................................ 3B6
8A-26. Installation of Fuel-Air Bleed Nozzle ................... 3B6
8A-27. Ignition System Maintenance .................................. 3B7
8A-28. Magneto .................................................... 3B7
8A-29. Inspection of Magneto ............................... 3B7
8A-30. -Removal of Magneto ................................. 3B9
8A-31. Timing Procedure (Internal Timing) .................... 3B9
8A-32. Installation and Timing Procedure (Timing
Magneto to Engine) .............................. 3B 12

Reissued: 1/15/81 3A8

 PIPER CHEROKEE SERVICE MANUAL

Paragraph Aerofiche
Grid No.
8A-33. Harness Assembly ............................................ 3B15
8A-34. Inspection of Harness ................................ 3B15
8A-35. Removal of Harness ................................. 3B15
8A-36. Maintenance of Harness .............................. 3B15
8A-37. Installation of Harness ...................... ......... 3B21
8A-38. Spark Plugs ................................................. 3B21
8A-39. Removal of Spark Plugs .............................. 3B21
8A-40. Inspection and Cleaning of Spark Plug ................. 3B23
8A-41. Installation of Spark Plugs ............................ 3B23
8A-42. Lubrication System ........................................... 3B23
8A-43. Oil Pressure Relief Valve ............................. 3B23
8A-44. Switching ............................... .................... 3B24
8A-45. Removal of Ignition Switch ..... ...................... 3B24
8A-46. Installation of Ignition Switch ......................... 3B24

Revised: 8/3/81 3A9

 PIPER CHEROKEE SERVICE MANUAL

SECTIONVIIIA
POWERPLANT
(PA-28R)

8A-1. INTRODUCTION.This section covers the power plant used in PA-28R-180airplanes

and is comprised of instructions for the removal, minor repair, serviceand installation of the
propeller, propeller governor, engine, induction system, fuel injector, fuel air bleed nozzle,
ignition system and lubrication system.
For further instructions on major repairs, consult the appropriate publication of the
engine or component manufacturer.

8A-2. DESCRIPTION. The PA-28R-180 is powered by an Avco-Lycoming IO-360-B1E

engine of 180 horsepower and the PA-28R-200 is powered by an Avco-Lycoming
IO-360-C1Cengine of 200 horsepower. (Refer to Power Plant Specificationsin Table II-I.)
The engines are furnished with starters, 60 ampere, 14-volt alternators, voltage regulators,
shielded ignition systems, vacuum pump drive, fuel pump, fuel injector and dry paper type
induction air filter. An alternate air door that will open automatically in the event of air
stoppage through the filter or may be operated manually with the use of a control in the
cockpit is provided in the induction system.
The exhaust system is constructed of stainless steel, directing gasesinboard to a muffler
located directly under the engine. The large muffler with a heater shroud provides heat for
both the cabin and defrosting.
The engines are provided with a constant speed propeller controlled by a governor
mounted on the engine supplying oil through the propeller shaft at various pressures.
Service of both engines is identical and wherever there is any difference in service
instructions it will be so noted.

8A-3. TROUBLESHOOTING.Troubles peculiar to the power plant are listed in Table

VIIIA-I along with their probable causes and suggestedremedies. Whentroubleshooting the
engine, ground the magneto primary circuit before performing any checks of the engine.

POWER PLANT
Reissued: 1/15/81 3A10
 PIPER CHEROKEE SERVICE MANUAL

8A-4. PROPELLER.

8A-5. REMOVAL OF PROPELLER.

a. Insure master and magneto switches are off.
b. Move fuel selector to off position.
c. Place mixture control in idle cut-off.
d. Note position of components to facilitate reinstallation.
e. Remove screws from the spinner assembly and remove spinner.
f. Remove the-safety wire from the six propeller mounting nuts on studs and
remove studs.
g. Place a drip pan under propeller to catch oil spillage, remove propeller.

8A-6. CLEANING, INSPECTION AND REPAIR OF PROPELLER.

a. Check for oil and grease leaks.
b. Clean the spinner, propeller hub interior and exterior, and blades with a
non-corrosive solvent.
c. Inspect the hub parts for cracks.
d. Steel hub parts should not be permitted to rust. Use aluminum paint to
touch up if found necessary.
e. Check all visible parts for wear and safety.
f. Check blades to determine whether they turn freely on the hub pivot tube.
This can be done by rocking the blades back and forth through the slight freedom
allowed by the pitch change mechanism. If they appear tight and are properly
lubricated, the pitch change mechanism should be removed so that -each blade can
be checked individually. If blades are tight, the propeller should be disassem-
bled.
g. Inspect blades for damage or cracks. Nicks in leading edges of blades
should be filed out and all edges rounded, as cracks sometimes start from such
places. Use fine emery cloth for finishing. Refer to Figure 8A-2 for propeller
blade care.
h. It is recommended that for severe damage, internal repairs and replace-
ment of parts, the propeller should be referredto the Hartzell Factory or Service
Station.
i. Grease blade hub through zerk fittings. Remove one of the two fittings for
each propeller blade, alternate the next time. Apply grease through the zerk fit-
ting until fresh grease appears at the fitting hole of the removed fitting. Care
should be taken to avoid blowing out hub gaskets.
j . Checkconditionof propeller mounting nuts onstuds,

POWER PLANT
Reissued: 1/15/81 3All
 PIPER CHEROKEE SERVICE MANUAL

1801

1. LOW PITCH STOP

2. JAM NUT
3. PROPELLER HUB
4. SPINNER
5. PROPELLER BLADE
6. SPINNER BACK PLATE
7. STARTER RING
8. "O" RING SEAL
9. GREASE FITTING
10. WASHER
II. NUT
12. SAFETY WIRE
13. STUD
14. NUT, FLYWHEEL

\14

Figure 8A-1. Propeller Installation

Reissued: 1/15/81 POWER PLANT

3A12
 PIPER CHEROKEE SERVICE MANUAL

C345

Exaggerated view of nicks

in leading edge. Exaggerate I view of nick
in faceof blade
blade

Recommended methodfor removing

SECTIONAA-
nicksby riffle file and crocus cloth.
Nick in face of blade
Blenddeepestportionof nick into removedby file and
leadingedge alignmentwith smooth
crocuscloth as recom-
curves.
mended

Figure 8A-2 Typical Nicks and Removal Method

8A-7. INSTALLING PROPELLER.

a. Insure master and magneto switches are off.
b. Place fuel selector to off position.
c. Place mixture control in idle cut-off.
d. Observe the starter ring gear to make sure it is mounted properly on the
engine crankshaft flange. One of the bushings on the crankshaft is stamped with
an "O" mark and it must be inserted in the starter ring gear hole, likewise iden-
tified with an "O" mark.
e. Wipe crankshaftand propeller pilot to assure that no chips or foreign mat-
ter enter the propeller mechanism.
f. Check interior of propeller hub for proper seating of "O" ring. Wipe in-
side of hub to remove any traces of dirt. Check to see that "O" ring is covered
with grease.
g. Raise propeller into position so that each stud mates with an engine flange.
bushing, and screw each stud in a few turns at a time until all are tight. Torque
to 55 to 65 foot pounds.
h. Check the propeller blade track as given in paragraph 8A-8.

Revised: 10/3/83 POWER PLANT

3A13
 PIPER CHEROKEE SERVICE MANUAL

i. Safety the propeller mounting bolts with MS20995-C41 safety wire.

j. Install the spinner, torque cap bolts 35 to 40 inch pounds.

8A-8. BLADE TRACK. Blade track is the ability of one blade tip to follow the
other, while rotating, in almost the same plane. Excessive difference in blade
track - more than .0625 inch - may be an indication of bent blades or improper
propeller installation. Check blade track as follows:
a. With the engine shut down and blades vertical, secure to the aircraft a
smooth board just under the tip of the lower blade. Move the tip fore and aft
through its full "blade-shake" travel, making small marks with a pencil at each
position. Then center the tip between these marks and scribe a line on the board
for the full width of the tip.
b. Carefully rotatepropeller by hand to bring the opposite blade down. Center
the tip and scribe a pencil line as before and check that lines are not separated
more than .0625 inch.
c. Propellers having excess blade track should be removed and inspected for
bent blades, or for parts of sheared "O" ring, or foreign particles, which have
lodged between hub and crankshaft mounting faces. Bent blades will require re-
pair and overhaul of assembly.

8A-9. PROPELLER GOVERNOR.

8A-10. REMOVAL OF PROPELLER GOVERNOR.

a. Remove the upper engine cowl.
b. Disconnect the control cable end from the governor control arm.
c. Remove the governor mounting stud nuts. It will be necessary to raise the
governor as the nuts are being removed before the nuts can be completely re-
moved.
d. Remove the mounting gasket. If the governor is to be removed for a con-
siderable length of time and another unit not substituted, it is advisable to cover
the mounting pad to prevent damage caused by foreign matter.

8A-11. INSTALLATION OF PROPELLER GOVERNOR.

a. Clean the mounting pad thoroughly, making very certain that there are no
foreign particles in the recess around the drive shaft.
b. Place the governor mounting gasket in position with the raised portion of
the screen facing away from the engine.
c. Align the splines on the governor shaft with the engine drive and slide the

Reissued:1/15/81 3A14 POWER PLANT

 PIPER CHEROKEE SERVICE MANUAL

governor into position.

d. With the governor in position, raise the governor enough to install wash-
ers and start mounting nuts. Torque nuts even.
e. Connect the control cable end to the governor control arm. The ball stud
is installed in the inner hole of the control arm.
f. Adjust governor control per paragraph 8A-12.
g. Install engine cowl.

8A-12. RIGGING AND ADJUSTMENT OF PROPELLER GOVERNOR. (Refer to

Figure 8A-3.)
a. Start engine, park 90° to wind direction and warm in normal manner.
b. To check high RPM, low pitch setting, move the propeller control all the
way forward. At this position the governor speed control arm (1) should be against
the high RPM fine adjusting screw (2). With the throttle full forward, observe
engine RPM, which should be 2700 RPM with high RPM properly adjusted.
c. Should engine RPM not be as required, the high RPM setting should be ad-
justed as follows:
1. Shut down the engine and remove the upper engine cowl.
2. Adjust the governor by means of the fine adjustment screw (2) for 2700
RPM. To do this, loosen the high RPM fine adjustment screw lock nut and turn
the screw in a clockwise direction to decrease engine speed or in a counterclock-
wise direction to increase engine speed.

NOTE

One revolution of the fine adjustment screw will in-

crease or decreasethe engine speedapproximately 20
RPM.

3. Reinstall upper engine cowl and repeat step b to ascertain proper RPM
setting.
4. After setting the proper high RPM adjustment, run the self-locking nut
on the fine adjustment screw against the base projection to lock.
5. Ascertain that the governor control arm (1) is adjusted to the proper
angle on the control wheel (4) as shown in Figure 8A-3.
d. With the high RPM adjustment complete, the control system should be ad-
justed so that the governor control arm will contact the high RPM stop when the
cockpit control knob is .032 to .047 of an inch from its full forward stop. To ad-
just the control knob travel, disconnect the control cable end from the control
arm, loosen the cable end jam nut and rotate the end to obtain the desired level
clearance. Reconnect the cable end and tighten jam nut.

Reissued: 1/15/81 POWER PLANT

3A15
 PIPER CHEROKEESERVICEMANUAL

e. It is usually only necessary to ad- A617

just the high RPM (low pitch) setting of
the governor control system, as the ac- 5 5 /3
tion automatically takes care of the pos-
itive low RPM (high pitch) setting.

8A-13. ENGINE.

8A-14. REMOVAL OF ENGINE.

a. Turn off all electrical switches
in the cockpit and then disconnect the 1 . CONTROL ARM
2. RPM ADJUSTMENT SCREW
battery ground wire at the battery. 3. LOCKNUT
b. Move the fuel selector lever in 4. CONTROL WHEEL
5. BOLT ASSEMBLY
the cockpit to "OFF".
c. Remove the engine cowlingby the Figure 8A-3. Propeller Governor
following procedure:
1. Release the cowl fasteners, two on each side of the cowl.
2. Lift the aft end of the cowl and then slide it forward to release the two
stud type front fasteners. Remove the top cowl.
3. Disconnect thelanding light lead at the quickdisconnect at the left rear
side of the bottom cowl.
4. Disconnect the nose gear door rods by removing the nuts, washers, and
bolts.
5. Remove the screws securing the bottom cowl at its aft end. Remove the
bottom cowl.
d. Remove the propeller. (Refer to Paragraph 8A-5.)
e. Disconnect the starter positive and ground leads at the starter, and their
attachment clamps.
f. Disconnect thegovernor control cable at the governor and cable attachment
clamps.
g. Disconnect the heater hose at the muffler.
h. Disconnect the throttle and mixture cables at the injector. (The injector
may be removed if desired.)d.
i . Remove the air filter box by removing the bolts that secure the box to its
attachment clamps. The cover may remain attached to the alternate air door
control cable.
j. Disconnect the fuel pump supply line at the left side of the pump. Discon-
nect the pump vent line.

Reissued: 1/15/81 POWER PLANT

3A16
 PIPER CHEROKEE SERVICE MANUAL

NOTE

Where a question may arise as where to reconnect

hose, line or wire, the item at the separation should
be identified (tagged) to facilitate reinstallation. Open
fuel, oil, vacuum lines and fittings should be covered
to prevent contamination.

k. Disconnect both lines from the oil cooler.

1. Disconnect the magneto "P" leads at the magnetos.
m. Disconnect the engine vent tube at the engine.
n. Disconnect the engine oil temperature lead at the aft end of the engine.
o. Disconnect the tachmeter drive cable at the engine.
p. Untie the ignition harness, hoses and lines at the aft end of the engine.
q. Disconnect the vacuum pump lines at pump and remove fittings from pump.
r. Disconnect the oil pressure line at the engine.
s. Disconnect the static and fuel flow line at the right rear engine baffle.
t. Disconnect the manifold pressure line at the right rear side of the engine.
u. Disconnect the injector line at the flow divider.
v. Disconnect the alternator leads and the cable attachment clamps.
w. Attach a one-half ton (minimum) hoist to the hoisting straps and relieve the
tension from the engine mounts.

NOTE

Place a tail stand under the tail of the airplane before

removing the engine.

x. Check the engine for any attachments remaining to obstruct its removal.
y. Drain the engine oil, if desired, and then close drain.
z. Remove the four engine mount assemblies and swing the engine free, being
careful not to damage any attaching parts.

8A-15. INSTALLATION OF ENGINE.

a. Attach a one-half ton (minimum) hoist to the engine hoisting straps and
swing the engine into alignment with its attaching points.
b. Insert an engine mount bolt, with washer against head, in the engine mount
and slide half of the mount assembly on the bolt. Repeat this procedure for the
other three attachment points. (Refer to Figure 8A-4.)
c. Position the mounting lugs of the engine so that they align with the engine
mount attaching points, then move the engine rearward onto the mounts.

Reissued: 1/15/81 3A17 POWER PLANT

 3A18
INTENTIONALLY LEFT BLANK
 PIPER CHEROKEE SERVICE MANUAL

1727

3 4 5 6 7 8 9 10 11

NOTE: A maximum of (3)

AN960-616 washers can be Section A-A
used to permit a maximum of
2.5 threads exposed on the
bolt. Torque to 230/240
inch-pounds.

1. AIR FILTER BOX 9. SHOCK MOUNT (SEE SKETCH A) 17. FUEL INJECTOR 25. BOLT
2. BAFFLE ASSEMBLY, LEFT 10. FLOW DIVIDER 18. OIL COOLER INLET HOSE (180 ONLY) 26. WASHER
3. MAGNETO, LEFT 11. OIL FILLER 19. MANIFOLD PRESSURE LINE 27. SPACER
4. OIL TEMPERATURE LEAD 12. LIFTING STRAP 20. BAFFLE ASSEMBLY, RIGHT 28. SHOCK MOUNT (SILVER CODING)
5. VACUUM PUMP 13. STARTER RING GEAR 21. SPARK PLUGS 29. SHOCK MOUNT (GOLD CODING)
I 6. TACHOMETER CABLE 14. OIL FILTER 22. INJECTOR NOZZLE 30. ENGINE MOUNT ASSEMBLY
7. ENGINE MOUNT ASSEMBLY 15. PROPELLER GOVERNOR 23. INTAKE TUBE 31. ENGINE .
8. MAGNETO, RIGHT 16. INJECTOR INLET HOSE 24. EXHAUST STACK

Figure 8A-4.- Engine Installation (PA-28R-180)

Reissued:1/15/81 3A19 POWER PLANT

 PIPER CHEROKEE SERVICE MANUAL

C311

NOTE
REFERTO PIPERSERVICE LET-
TER NO. 910 ON OIL QUICK
SKETCHA DRAIN INSTALLATION

VIEWAA VIEWBB

Figure 8A-4. Engine Installation (PA-28R-180) (cont.)

POWER PLANT
Revised: 10/3/83 3A20
 PIPER CHEROKEE SERVICE MANUAL

1705
1. STARTER RING GEAR 17. INTAKE TUBE 25. BOLT
2. FLOW DIVIDER 18. BAFFLE ASSEMBLY, LEFT 26. WASHER
3. LIFTING STRAP 19. MAGNETO, LEFT 27. SPACER
4. SHOCK MOUNT (SEE SKETCK A) 20. AIR FILTER BOX 28. SHOCK MOUNT (SILVER CODING)
5. INJECTOR NOZZLE 21. FUEL PUMP 29. SHOCK MOUNT (GOLD CODING)
6. OIL FILTER 22. FUEL INJECTOR 30. ENGINE MOUNT ASSEMBLY
7. BAFFLE ASSEMBLY, RIGHT 23. OIL TEMPERTURE LEAD 31. ENGINE
8. TACHOMETER CABLE 24. INJECTOR INLET HOSE
9. VACUUM PUMP
10. MAGNETO, RIGHT
11. OIL FILLER
12. MANIFOLD PRESSURE LINE
13. PROPELLER GOVERNOR
14. ENGINE MOUNT ASSEMBLY
15. EXHAUST STACK
16. SPARK PLUG NOTE: A maximum of (3) AN960616
washers can be used to permit a max. of
25 threads exposed on the bolt. Torque
to 230/240 inch-pounds.

Figure 8A-5. Engine Installation (PA-28R-200)

Reissued: 1/15/81 3A21 POWER PLANT

 PIPER CHEROKEE SERVICE MANUAL

C311

NOTE
REFER TO PIPER SERVICE LET-
TER NO. 910 ON OIL QUICK
DRAIN INSTALLATION

SKETCHA

VIEWAA VIEWBB
I

Figure 8A-5. Engine Installation (PA-28R-200) (cont.)

POWER PLANT
Revised: 10/3/83 3A22
 PIPER CHEROKEE SERVICE MANUAL

d. Slide onto each mounting bolt a spacer washer, spacer and the forward half of the
mount. Install washer and nut, and torque the nuts of the bolts to 450 to 500 inch pounds.
e. Connect the alternator leads and secure cable with clamps.
f. Connect the injector line to the flow divider.
g. Connect the manifold pressure line at the right rear side of the engine.
h. Connect the static and fuel flow line at the right rear engine baffle.
i. Connect the oil pressure line.
j. Install the line fitting in the vacuum pump and install lines.
k. Connect the tachometer drive cable.
1. Connect the oil temperature lead.
m. Connect the engine vent tube.
n. Connect the oil cooler.
o. Connect the magneto "P" leads. Check that magneto switch is "OFF."
p. Connect the fuel pump supply and vent line.
q. Install the injector.
r. Connect the throttle and mixture cables to the injector. Check adjustment of the
control by referring to paragraph 8A-17.
s. Connect the heater hose to the muffler.
t Install the air filter box, filter and box cover. Check adjustment of the alternate air
door by referring to Paragraph 8A-19.
u. Connect the governor control cable and secure with clamps.
v. Connect the starter positive and ground leads and secure cables with clamps.
w. Secure the ignition harness, lines, hoses, wires, etc. that may be loose.
x. Install the propeller. (Refer to Figure 8A-8.)
y. Install the cowlingby attaching the bottom cowl to the firewall and then installing
the top. Connect the electricallead to the landing light.
z. Connect the gear door retraction rods and secure with bolts, washersand nut.
aa. Install the proper grade and amount of engine oil.
ab. Turn on the fuel valve; open the throttle full and turn on the electric fuel pump.
Check the fuel lines for leaks.
NOTE

To avoid a possible high speed bearing failure resulting from a

lack of lubrication during initial starts, refer to the latest
revision of Avco-LycomingService Instruction No. 1241 for
information on pre-oiling the engine.

ac. Perform an engine operational check.

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 PIPER CHEROKEE SERVICE MANUAL

8A-16. INSTALLATION OF OIL COOLER.

a. When installing fittings in the oil coolers, care should be used to prevent excessive
torque being applied to the cooler. When a rectangular fitting boss is provided, a backup
wrench should be used, employing a scissor motion, so that no load is transmitted to the
cooler. When the oil cooler has a round fitting boss, care should be taken not to permit
excessivetorque on the fittings.
b. If a pipe thread fitting is used, it should be installed only far enough to seal with
sealingcompound.
c. Apply Lubon No. 404 to all male pipe thread fittings; do not allow sealant to enter
the system.
d. If fitting cannot be positioned correctly using a torque of 10 to 15 foot-pounds,
another fitting should be used.
e. When attaching lines to the cooler, a backup wrench should be used.
f. After installation, inspect the cooler for distorted end cups.
g. Run-up engine. After run-up, check for oil leaks.

THIS SPACE INTENTIONALLYLEFT BLANK

POWER PLANT
Reissued: 1/15/81 3A24
 PIPER CHEROKEE SERVICE MANUAL

890

COCKPIT
CONTROLS

0.010 TO 0.030

STOP

Figure 8A-6. Adjustment of Engine Controls

8A-17. ADJUSTMENTOF THROTTLE AND MIXTURE CONTROLS. (Refer to Figure

8A-6.) Throttle and mixture controls are adjusted so that when the throttle arm on the
carburetor is rotated forward against its full throttle stop and the mixture control is rotated
forward against its full rich stop, the cockpit control levers of the throttle and mixture
should have 0.010 to 0.030 of an inch spring back on instrument panel stop when in full
throttle or full rich position.
a. The throttle may be adjusted as follows:
1. At the carburetor, disconnect the clevisend of the throttle control cable from
the control arm. Loosen the jam nut that secures the clevisend.
2. Adjust the linkage by rotating the clevis end on the cable to obtain 0.010 to
0.030 of an inch spring back on instrument panel stop when in full throttle position.
3. On PA-28R aircraft equipped with air conditioning systems, a micro switch is
located below the throttle control which is set to actuate in the full open position. With the
throttle control adjusted to obtain a clearance of .010 to .030, adjust the micro switch to
actuate at this point also.
4. Reconnect the clevisend to the control arm and safety.
b. The mixture may be adjusted as follows:
1. At the carburetor, disconnect the clevis end of the mixture control cable from
the control arm. Loosen the jam nut that secures the clevis end.
2. Adjust the linkage by rotating the clevis end on the cable to obtain 0.010 to
0.030 of an inch spring back on the instrument panel stop when in full rich position.
3. Reconnect the clevisend to the control arm and safety.
c. Check security of cable casingattachments.

Reissued: 1/15/81 3B1 POWERPLANT

 PIPER CHEROKEE SERVICE MANUAL

d. Pull the throttle and mixture levers in the cockpit full aft to ascertain that the idle
screw contacts its stop and the mixture control arm contacts its lean position. On 1975
models and up, a mixture control lock is incorporated in the quadrant cover which prevents
the mixture control from being moved to the idle cutoff position inadvertently. The lock
must be depressed before the control can be moved completely aft. Ascertain that the lock
operates freely without any tendency to bind or hang up.

8A-18. INDUCTIONAIR FILTER.

a. The filter should be cleaned daily when operating in dusty conditions. If any holes
or tears are noticed, the filter must be replaced immediately.
b. Remove the filter element and shake off loose dirt by rapping on a hard flat surface,
being careful not to damage or crease the sealingends.

CAUTION
Never wash the filter element in any liquid or soak it in oil.
Never attempt to blow off dirt with compressed air.
c. The filter housing can be cleaned by wiping with a clean cloth soaked in a suitable
dry type solvent. Whenthe housing is dry, reinstall and seal the filter element.

8A-19. ALTERNATE AIR DOOR. The alternate air door is located in the cover of the
filter box to provide a source of air to the engine should there be an air stoppage through
the filter system. The followingshould be checked during inspection:
a. Check that air door seals are tight and hinge is secure.
b. Ascertain that the spring tension of the door is tight enough to allow the door to
remain closed at full engine RPM,yet should there be an air stoppage, it will be drawn open.
c. Actuate the door by pushing in on it with the fingers to determine that it is not
sticking or binding.
d. Check the cockpit control cable for free travel.
e. Check that when the control lever in the cockpit is in the open position, the cable is
adjusted to allow approximately .0625 to .125 of an inch between the actuating arm roller
and the door when fully closed.

Reissued:1/15/81 3B2 POWER PLANT

 PIPER CHEROKEE SERVICE MANUAL

A616

1. THROTTLE ARM
2. IDLE MIXTURE ADJUSTMENT
3. IDLE SPEED ADJUSTMENT
4. FUEL SCREEN
5. MIXTURE ARM

Figure 8A-7. Fuel Injector

8A-20. FUEL INJECTOR.

8A-21. FUEL INJECTOR MAINTENANCE.

a. In general, little attention is required between injector overhauls. However, it is
recommended that the following items be checked during periodic inspection of the engine.
1. Check tightness and lock of all nuts and screws which fasten the injector to the
engine, torquing all nuts to 135-150 inch-pounds.
2. Seat the pal type locknuts and finger tighten them against the plain nuts. After
this has been done tighten the locknuts an additional 1/3 to 1/2 turn.
3. Check all fuel lines for tightenss and evidence of leakage. A slight fuel stain
adjacent to the air bleed nozzles is not cause for concern.
4. Check throttle and mixture control rod ends and leversfor tightness and lock.
5. Remove and clean the injector inlet strainer at the first 25 hours of operation
and each 50 hour inspection thereafter. Check the screen for distortion or openings in the
strainer. Replace for either of these conditions. Clean screen assembly in solvent and dry
with compressed air. Damaged strainer "O"rings should be replaced. To install the screen
assembly, place the gasket on the screen assembly and install the assembly in the throttle
body and tighten to 35-40 inch-pounds torque.

Reissued: 1/15/81 3B3 POWER PLANT

 PIPER CHEROKEE SERVICE MANUAL

C348

1/8 INCHO.D.STAINLESS
STEEL LINE

NOZZLE
(ONE PER CYLINDER)

FLOW DIVIDER VALVE

\\

\\
\\

FUEL INLET STRAINER

\\
\\\\

I
SECTION- AA
IDLE VALVE LEVER
CONNECTED TO It
THROTTLE LEVER MANUAL MIXTURE
LINKAGE CONTROL AND IDLE
CUT-OFF LEVER

' IDLE SPEED

ADJUSTMENT
. ' I
- -

CONSTANT HEAD
IDLE SPRING
CONSTANT EFFORT
SPRING
AIR DIAPHRAGM IMPACTTUBE
FUEL DIAPHRAGM
AIR INLET
BALL SERVO VALVE I

Figure 8A-8. Schematic Diagram of RSA Fuel Injection System

Reissued: 1/15/81 3B4 POWERPLANT

 PIPER CHEROKEE SERVICE MANUAL

8A-22. ADJUSTMENTOF IDLE SPEEDAND MIXTURE.

a. Start the engine and warm up in the usual manner until oil and cylinder head
temperatures are normal.
b. Check magnetos. If the "mag-drop" is normal, proceed with idle adjustment.
c. Set throttle stop screw so that the engine idles at 550-600 RPM. If the RPM changes
appreciable after making the mixture adjustment during the succeedingsteps, readajust the
idle speed to the desired RPM.
d. When the idling speed has been stabilized, move the cockpit mixture control lever
with a smooth, steady pull toward the "Idle-Cut-Off" position and observe the tachometer
for any change during the leaning process. Caution must be excerised to return the mixture
control to the "Full Rich" position before the RPM can drop to a point where the engine
cuts out. An increase of more than 10 RPM while "leaning out" indicates an excessivelyrich
idle mixture. An immediate decrease in RPM (if not preceded by a momentary increase)
indicates the idle mixture is too lean.
e. If the above indicates that the idle adjustment is too rich or too lean, turn the idle
mixture adjustment in the direction required for correction, and check this new position by
repeating the above procedure. Make additional adjustments as necessary until a check
results in a momentary pick-up of approximately 5 (never more than 10) RPM. Each time
the adjustment is changed, the engine should be run up to 2000 RPM to clear the engine
before proceeding with the RPM check. Make final adjustment of the idle speed adjustment
to obtain the desired idling RPM with closed throttle. The above method aims at a setting
that will obtain maximum RPM with minimum manifold pressure. In case the setting does
not remain stable, check the idle linkage; any looseness in this linkage would cause erratic
idling. In all cases, allowance should be made for the effect of weather conditions and field
altitude upon idling adjustment.

THIS SPACEINTENTIONALLYLEFT BLANK

Reissued:1/15/81 3B5 POWER PLANT

 PIPER CHEROKEE SERVICE MANUAL

8A-23. FUEL-AIR BLEED NOZZLE.

8A-24. REMOVAL OF FUEL-AIR

BLEED NOZZLE. The nozzles must be
carefully removed as they or the cylin-
ders may be damaged.
a. Remove the lower engine cowl.
b. Disconnect the fuel line from the
nozzle.
c. Carefully remove the nozzle,
using the correct size deep socket.
d. Clean and inspect the nozzle as
given in Paragraph 8A-25.

Figure 8A-9. Fuel-Air

8A-25. CLEANING AND INSPECTION Bleed Nozzle
OF FUEL-AIR BLEED NOZZLE.
a. Clean the nozzle with acetone or equivalent and blow out all foreign par-
ticles with compressed air in the direction opposite that of fuel flow. Do not use
wire or other hard objects to clean orifices.
b. Inspect the nozzle and cylinder threads for nicks, stripping or cross-
threading.
c. Inspect for battered or rounded hexagons.

8A-26. INSTALLATION OF FUEL-AIR BLEED NOZZLE.

a. Install nozzle and torque 60 inch-pounds.

CAUTION

Startnozzles and line couplings by handto prevent the

possibility of cross-threading.

b. Connect fuel line to nozzle.

c. Install the engine cowl.

Reissued: 1/15/81 3B6 POWER PLANT

 PIPER CHEROKEE SERVICE MANUAL

8A-27. IGNITION SYSTEM MAINTENANCE.

8A-28. MAGNETO.

CAUTION

Ascertain that the primary circuit of both magnetos

is grounded before working on the engine.

8A-29. INSPECTION OF MAGNETO.

a. After the first 25 hour and 50. hour periods, and periodically thereafter,
the contact assemblies should be checked. Examine the points for excessive
wear or burning. Points which have deep pits or excessively burned areas should
be discarded. Examine the cam follower felt for proper lubrication. If neces-
sary, points can be cleaned by using any hard finished paper. Clean breaker
compartment with dry cloth.
b. If engine operating troubles develop which appear to be caused by the igni-
tion system, it is advisable to check the spark plugs and wiringfirst beforework-
ing on the magnetos.
c. Should the trouble appear definitely associated with the magneto, the most
effective measure is to install a replacement magneto which is known to be in
satisfactory condition and send the suspected unit to the overhaul shop for test
and repair.
d. Should this not be possible, a visual inspection may disclose the source of
trouble. Remove the harness outlet plate from the magneto. Inspect for the
presence of moisture and foreign matter on the rubber grommet and high tension
outlet side of the distributor block. Check height of block contact springs, (0.422
maximum from top of the block tower to the spring). Also check for broken leads
or damaged insulation. If either is present, remove magneto and replace with
one known to be in satisfactory condition.
e. Remove the breaker cover and harness securing screws and nuts, and sep-
arate cover from magneto housing. Check contact assemblies to see that cam
follower is securely riveted to its spring. Examine the contact points for ex-
cessive wear or burning. Figure 8A-10 shown how the average contact point will
look when surfaces are separated for inspection. Desired contact surfaces have
a dull gray, sand-blasted (almost rough) or frosted appearance, over the area
where electrical contact is made. This means that points are worn in and mated
to each other, thereby providing the best possible electrical contact and highest
efficiency of performance.
f . Minor irregularities or roughness of point surfaces are not harmful (Refer

Reissued: 1/15/81 3B7 POWER PLANT

 PIPER CHEROKEE SERVICE MANUAL

223

NORMAL POINT IS SMOOTH MINOR IRREGULARITIES - WELL DEFINED MOUND

AND FLAT. SURFACE HAS SMOOTH ROLLING HILLS EXTENDING NOTICEABLY
DULL GRAY "SANDBLASTED" AND DALES WITHOUT ANY ABOVE SURROUNDING
APPEARANCE DEEP PITS OR HIGH PEAKS. SURFACE. REJECT POINTS.
THIS IS A NORMAL CON-
DITION OF POINTWEAR.

Figure 8A-10. Contact Points

to Figure 8A-10 center). Neither are small pits or mounds, if not too pronounced.
If there is a possibility of pit becoming deep enough to penetrate pad, Figure
8A-10, right, reject contact assembly.

NOTE

No attempt should be made to stone or dress contact

points. Should contact assembly have bad points or
show excessive wear, the complete contact assembly
should be replaced.

g. Check the condition of the cam follower felt. Squeeze felt tightly between
thumb and forefinger. If fingers are not moistened with oil, re-oil using 2 or 3
drops of Scintilla 10-391200 lubricant. Allow approximately 30 minutes for felt to
absorb the oil. Blot off the excess with a clean cloth. Too much oil may, foul con-
tact points and cause excessive burning.
h. Check the capacitor mounting bracket for cracks or looseness. Using the
Scintilla 11-1767-1, -2 or -3 Condenser Tester or equivalent, check capacitor
for capacitance, series resistance and leakage. Capacitance shall be at least
0.30 microfarads.
i . Check magneto to engine timing as follows:
1. Connect Scintilla 11-851 Timing Light or equivalent across the contact
assembly.
2. Slowly bring the engine up to number one cylinder advance firing posi-
tion as instructed in paragraph 8A-32. At this instant the timing light should go

Reissued: 1/15/81 3B8 POWER PLANT

 PIPER CHEROKEE SERVICE MANUAL

out. If it does, the magneto is properly timed to the engine. If the timing light
does not go out, removal of the magneto for internal timing check and inspection
is recommended.

NOTE

The magneto service instructions in this manual are

to cover minor repairs and timing. For further re-
pairs and adjustments of the magneto, it is recom-
mended that the manufacturer's recommended serv-
ice instructions be followed.

8A-30.. REMOVAL OF MAGNETO. Before removing the magneto, make sure

magneto switches are off.
a. Remove the harness assembly terminal plate from the magneto.

WARNING

The magneto is not internally grounded; when the ground

lead is disconnected, the magneto is hot. Removing
the harness assembly terminal plate first and instal-
ling them last minimizes the danger of starting the
engine accidentally when the ground lead is removed
from the magneto.

b. Disconnect the ground lead at the magneto.

c. Remove the nuts and washers and draw the magneto from the engine.

8A-31.. TIMING PROCEDURE (Internal Timing).

a. Remove the cover to the contact(s), distributor block, etc.
b. To internally time the contact assembly of the single-breaker magnetos,
proceed as follows:
1. Loosen the nut securing the drive plate to the magneto shaft sufficiently
in order to install the Scintilla 11-8465 Rotor Holding Tool under the nut and flat
washer as shown in Figure 8A-11. Tighten the nut securely.
2. Remove the timing inspection plug from the top of the magneto. Turn
rotating magneto to proper neutral position. This position is determined by lo-
cating keyways on drive end of magnet shaft at 12 o'clock with respect to name
plate on housing. Tighten adjusting knob of 11-8465 Rotor Holding Tool until
pressure is applied on housing flange preventing magnet from turning.

Reissued:1/15/81
3B9 POWER PLANT
 PIPER CHEROKEE SERVICE MANUAL

230 226

Figure 8A-11. Rotor Holding Tool Figure 8A-12. Timing Kit Installed
Installed

3. Loosen and rotate cam until cam follower of contact assembly rests on
highest point of cam lobe. Adjust contact assembly to obtain the clearance of
0.016 of an inch. Tighten contact assembly securing screws to 20-25 inch pounds.
4. Install the 11-8693 Timing Plate Assembly and the 11-8149 Pointer As-
sembly of the 11-8150 Scintilla Timing Kit to breaker compartment of magneto.
(Refer to Figure 8A-12.) Align pointer assembly with the 0° mark on timing plate.
Loosen adjusting knob of 11-8465 Rotor Holding Tool and turn rotating magnet in
normal direction of rotation until pointer indexes with the respective E gap mark
(150 ± 20). Tighten adjusting knob of 11-8465 Tool and remove the 11-8149Point-
er Assembly from magneto. Using a timing light, adjust contact points to just
open. This adjustment shall be made by rotating cam, in opposite direction of
rotation until contacts just open. While holding cam in this exact position, push
cam on magnet shaft as far as possible with the fingers. Extreme care must be
exercised in this operation. If cam adjustment is changed in the slightest degree,
the timing of the magneto will be thrown off. Do not drive cam on shaft with a
mallet or other instrument. Tighten the securing screw thereby drawing the cam
down, evenly and tightly. Torque screw to 16-20 inch pounds. Loosenthe 11-8465
Rotor Holding Tool adjusting knob and return rotating magnet to neutral position.
Reinstall the 11-8149 Pointer Assembly over 0° mark on timing plate. Rotate
magnet shaft in normal direction of rotation and check for opening of main con-
tact points at E gap setting (15 + 2).
c. If the distributor block was not removed from the housing, the internal tim-
ing may be checked by turning the magneto in the normal rotation to number one
firing position (keyway up and points just opening). At this position, the reference

Reissued: 1/15/81 3B10 POWER PLANT

 PIPER CHEROKEE SERVICE MANUAL

226 line on the distributor block should line

up between the L and LB marks on the
gear. On single contact magnetos the
line should favor the L mark, if possible.
d. If the distributor block was re-
moved from the housing, the distrib-
utor gear alignment and internal check
may be accomplished as followed:
1. Turn rotating magnet in di-
rection of rotation until it is located in
firing position (keyway up and points
just opening). Tighten adjusting knob
of 11-8465 Rotor Holding Tool Apply
a light coating of Bendix Grease P/N
10-27165 to teeth of distributor gear,
if needed. The large distributor gear
incorporates four timing makrs, Land
Figure 8A-13. Aligning Timing Marks LB for left hand rotation and R and RB
for right hand rotation.
2. With distributor gear assembled to block, turn gear until raised rib on
block lines up between the L and LB marks. Assemble block and gear into hous-
ing, meshing the distributor gears together. The rib should favor the L mark,
if possible, (Refer to Figure 8A-13.)
3. Secure distributor block to housing with studs and washers. Tighten
studs finger tight. Loosen the 11-8465 Rotor HoldingTool and turn rotating mag-
net in reverse direction of rotation until timing light indicates contact assembly
had just opened and check to make certain timing marks align within tolerance
indicated above. Tighten block securing studs, first to 4-8 inch pounds torque
and then final torque to 20 inch pounds.
4. Insert the tip of your small finger through timing hole in housing and
against large distributor gear teeth. Rockdistributor gear back and forth slightly.
There must be perceptible backlash between teeth of large and small gears. This
check should be made at three different points, 120° apart on gear. If backlash
is not evident, replace large distributor gear.
5. Install the breaker cover and complete reassembly of the magneto. Re-
fer to the manufacturer's publications for complete disassembly and reassembly
procedures.
e. On the magneto employing the impulse coupling, check clearance between
each flyweight and each stop pin as follows:
1. Bend the end of a stiff piece of wire into a right angle 1/8 inch long (max-
imum).
2. Hold magneto as shown in Figure 8A-14. Pull heel of flyweight outward

Reissued: 1/15/81 3B11 POWER PLANT

 PIPER CHEROKEE SERVICE MANUAL

with the hooked wire and make certain A626

that feeler gauge of 0.010 inch mini-
mum thickness will pass between stop
pin and the highestpoint of the flyweight. 0.10 A

NOTE

A true and accurate check

of the clearance between
flyweight and stop pin.can
only be obtained by pulling
the flyweight outward as
described above. Do not
attempt the check by push-
ing in on flyweight at point
"A"

f. Install and time magneto, re-

moved from engine, in accordance with
paragraph8A-32.
g. Secure external switch leads to
the breaker cover terminals. Connect Figure 8A-14.Checking Flyweight
harness assembly to the magneto. Clearance of Impulse Coupling

8A-32. INSTALLATION AND TIMING PROCEDURE. (Timing Magneto to En-

gine.) Although only the left magneto is equipped with an impulse coupling, the
timing procedure, in the following paragraphs, is the same for both magnetos.
a. Remove the spark plug from No. 1cylinder and place a thumb over the
spark plug hole. Rotate the crankshaft in direction of normal rotation until the
compression stroke is reached, this is indicated by a positive pressure inside
the cylinder tending to push the thumb off the spark plug hole. Continue rotating
the crankshaft in direction of normal rotation until the advance timing mark (20)
on the front face of the starter ring gear is in exactalignment with the small hole
located at the two o'clock position on the front face of the starter housing. (Refer
to Figure 8A-15.)

Reissued: 1/15/81 3B12 POWER PLANT

 PIPER CHEROKEE SERVICE MANUAL

228 Refer to the latest revision NOTE

of Lycoming Service
Bulletin No. 380 The advance timingmarkon
the top face of the starter
ring gear is marked at both
20 ° and 25 BTC. Use only
the 20 ° BTC mark when tim -
ingthe magnetos to the en-
gine.

NOTE

If the crankshaft is acci-

dently turned in the direc-
tion opposite normal rota-
tion, repeat the above pro-
Figure 8A-15. Engine Timing Marks cedure as accumulated
backlashwill make the final
timing incorrect.

b. At this point, the engine is ready for assembly of the magnetos. Remove
the inspection plugs from both magnetos and turn the drive shafts in direction of
normal rotation (counterclockwise facing the coupling), until the first painted
chamfered tooth on the distributor gear is aligned in the center of the inspection
window. (Refer to Figure 8A-16.) Being sure that the gear does not move from
this position, install gaskets and magnetos on the engine. Secure with washers
and nuts; tighten only finger tight.

NOTE

The magnetos are held in placebyclampswhichallows

them to be timed in several positions. Since all po-
sitions will not give the required clearance between
magneto and engine mount, the magnetos must be in-
stalled from the horizontal position to 20° above the
horizontal as shown in Figure 8A-16. Improper in-
stallation of magnetos could cause damage or failure.

NOTE

In order to turn the shaft on an impulse coupling magne-

to, depress pawl on the impulse couplingwith the finger.

Reissued: 1/15/81 3B13 POWER PLANT

 PIPER CHEROKEE SERVICE MANUAL

897 229
RED
OR
TOOTH
WHITE

TIMING
MARK

Figure 8A-16. Magneto Adjustment Figure 8A-17. Magneto Timing Marks

Limits

c. Using a battery powered timing light, attach the positive lead to a suitable
terminal connected to the ground terminal of the magneto and the negative lead to
any unpainted portion of the engine. Rotate the magneto in its mounting flange to
a point where the light comes on, then slowly turn it in the opposite direction un-
til the light goes out. Bring the magneto back slowly until the light just comes
on. Repeat this with the second magneto.

NOTE

AC timinglights operate in the reverse manner as de-

scribed above, the light goes out when the breaker
points open.

d, After both magnetos have been timed, check, as described below, to as-
certain that both magnetos are set to fire together.
e. Backoff the crankshaft a few degrees, the timinglights shouldgo out. Bring
the crankshaft slowly back in direction of normal rotation until the timing mark
and the hole in the starter housing are in alignment. At this point, both lights
should go on simultaneously. Tighten nuts to specified torque.
f . After magnetos have been properly timed, replace breaker cover and secure.
g. Install the ground lead and the retard spark lead on the left magneto.
h. Place the harness terminal plate on the magneto and tighten nut around the
plate alternately to seat cover squarely on magneto. Torque nuts to 18 to 22 inch
pounds.

Reissued: 1/15/81 3B14 POWER PLANT

 PIPER CHEROKEE SERVICE MANUAL

8A-33. HARNESS ASSEMBLY.

8A-34. INSPECTION OF HARNESS.

a. Check lead assemblies for nicks, cuts, mutilated braiding, badlyworn sec-
tion or any other evidence of physical damage. Inspect spark plug sleeves for
chafing or tears and damaged or stripped threads on coupling nuts. Check com-
pression spring to see if it is broken or distorted. Inspect grommet for tears.
Check all mounting brackets and clamps to see that they are secure and not cracked.
b. Using an ohmmeter, buzzer, or other suitable low voltage device, check
each lead for continuity. If continuity does not exist, wire is broken and must be
replaced.
c. For electrical test of harness assembly, use a high voltage, directcurrent
tester such as the TAKK Model 86 or 86A or an equivalent direct current high
voltage tester capable of delivering a test potential of 10, 000 volts. Connect
ground lead to high voltage tester to outer shielding braid of a single lead. Con-
nect plug terminal. Turn tester "ON" and apply 10, 000 volts. The insulation
resistance should be 100 megohms minimum. Proceed to check other leads of
harness in same manner.
d. Minor repair of the harness assembly, such as replacement of contact
springs, spring retainer assemblies, insulating sleeves or of one lead assembly,
can be accomplished with the harness assembly mounted on the engine. However,
should repair require replacement of more than one lead assembly or of a cable
outlet plate, the harness should be removed from the engine and sent to anover-
haul shop.

8A-35. REMOVAL OF HARNESS.

a. Disconnect the clamps that secure the wires to the engine and accessories.
b. Loosen the coupling nuts at the sparkplugs andremove the insulators from
the spark plug barrel well. Use caution when withdrawing the insulator not to
damage the insulator spring.
c. Place a guard over the harness insulators.
d. Remove the harness assembly terminal plate from the magneto.
e. Remove the harness from the airplane.

8A-36. MAINTENANCE OF HARNESS.

a. To replace contact springs, spring retainer assemblies or insulating sleeves,
proceed as follows:
1. Using a Scintilla 11-7073 Needle or a mechanical pencil with the lead
retracted, hook the end of the contact spring as shown in Figure 8A-18.

Reissued:1/15/81 POWER PLANT

3B15
 PIPER CHEROKEE SERVICE MANUAL

230
2. Using the needle or pencil,
unscrew the spring.
3. Slide insulating sleeve and
spring retainer assembly off end of lead
assembly.
4. Replace defective component
and reassemble as follows:
(a) Fabricate a tool as shown
in Figure 8A-19 for instal-
ling the insulating sleeves
over cable terminals.
(b) Push the tool thru insula-
ting sleeve and spring re-
tainer assembly as shown
in Figure 8A-20. Screw
the cable terminal into the Figure 8A-18. Removing Spring
tool. From Lead Assembly

(c) Work insulating sleeve and spring retainer assembly into position
over the cable and unscrew the tool. Install contact spring on cable
terminal.

NOTE

It may be necessary to lubricate cable and insulating

sleeve with a thin film of MC 200 (200, 000 centistokes)
or commercial grade alcohol to facilitate assembly.
C 346

BRAZE DRILL NO. 47 1/4 IN. DEEP

TAP 3-48
2-1/2 IN.

BLEND O.D. TO I.D.

POLISHO.D.
12.000 IN.

MAT: NO. 30 DRILL RODOR EQUIVALENT

Figure 8A-19. Assembly Tool

Reissued: 1/15/81 3B16 POWER PLANT

 PIPER CHEROKEE SERVICE MANUAL

C346

SPRING RETAINER ASSY

SLEEVE TOOL CABLE

Figure 8A-20. Using Assembly Tool

C346

REQUIRED LENGTH

Figure 8A-21. Measuring Lead Assembly Length

b. To replace one of the lead assemblies proceed as follows:

1. Remove clamps and brackets from applicable lead assembly. Cut cable
ties from assembly and discard.
2. Cut off condemned lead flush with outer surface of cable outlet plate.
3. Grip eyelet of lead with a pair of pliers and pull short length of con-
ductor out of grommet and cable outlet plate.
4. Using a 3 inch long, 0.270 inch diameter drift, applied atouter surface
of plate, drive out tapered ferrule and remaining pieces of insulation and shield-
ing.
5. To determine what length the new lead assembly should be cut to, pro-
ceed as follows:
(a) Measure the length of the condemned lead assembly. Move coupling
nut back on lead assembly and measure from outer end of ferrule
at spark plug end. (Refer to Figure 8A-21.)
(b) To the length determined in step (a), add 1-3/4 inches.

IReissued: 1/15/81 3B17 POWER PLANT

 PIPER CHEROKEE SERVICE MANUAL

231 231

Figure 8A-22. Cutting Metallic Figure 8A-23. Unbraiding Metallic

Braid From End of Lead Shielding

NOTE

Spare part leads are supplied in various length. Use

a lead which is longer than, but nearest to, the de-
sired length.

6. Cut lead assembly to the length determined in step 5. Mark ferrule on

spark plug end of lead with a metal stamp, scribe or rubber stamp to correspond
with correct cylinder number.
7. Starting at spark plug location, thread new cable thru grommets and
clamps as necessary for correct routing of cut end of cable to magneto location.
8. Using electrician's scissors, carefully remove 1.250 inch of outer braid
from end of lead. (Refer to Figure 8A-22.)

CAUTION

Use care not to nick or cut insulation when removing

braid.

9. Using a scribe or similar pointed tool, unbraid 3/8 inch of braided

shielding. (Refer to Figure 8A-23.) Wrap a single thickness of electrical tape
around unbraided strands to facilitate insertionof lead end thru hole in cable out-
let plate.
10. Remove cable outlet plate from magneto. Support plate securely and,
using suitable cutting pliers, split and remove eyelets from leads adjacent to lead
being replaced. When splitting eyelet make certain that wire strands are not cut.
Removal of eyelets on adjacent leads will allow grommet to be pulled away from
outlet plate to facilitate insertion of new lead.

Reissued: 1/15/81 3B18 POWER PLANT

 PIPER CHEROKEE SERVICE MANUAL

C347

UNBRAIDED
SHIELDING POSITIONOF

RED COATING FERRULEUNDER

SHIELDING

- 3/8"

Figure 8A-24. Forming Shielding Around Ferrule

11. Pass the taped end of new lead through hole in outlet plate. Remove
electrical tape from lead and install tapered end of ferrule under the unbraided
strands of shielding. Form strands of shielding evenly
as shown in Figure '8A-24 and pull lead assembly back through cable outlet plate
until ferrule binds in the outlet well. Position the Scintilla 11-7074 Ferrule Seat-
ing Tool (Figure 8A-25) over the wire and firmly seat the ferrule by tapping the
seating tool with a hammer or by using an arbor press.
12. Measure 1/2 inch from tapered ferrule and strip remaining insulation
from wire. (Refer to Figure 8A-27.)
13. Insert Scintilla 11-7073 Needle (Figure 8A-26) thru small hole grom-
met and over stripped end of wire. (Refer to Figure 8A-28.) Slide grommet down
needle until it seats tightly against the tapered ferrule.
C347 C347

2.750
2.031
2.375
0.370 0.095 DIA

0.047 SPHERICAL
RAD 0.047 DIA
2 PLACES
MATERIAL-BRASS

Figure 8A-25. Ferrule Seating Tool Figure 8A-26. Needle

Reissued:1/15/81 3B19 POWER PLANT

 PIPER CHEROKEE SERVICE MANUAL

232
232
1-7073 NEEDLE 0.50

Figure 8A-27. Measuring Wire From Figure 8A-28. Installing Grommet

Top of Ferrule Over Lead Assemblies

14. Cut wire 3/8 inch from top of grommet outlet (Refer to Figure 8A-28).
Double wire over as shown in A of Figure 8A-30. Slide eyelet over doubled wire
until it is firmly seated in recess of grommet outlet.
15. Using the "AB" groove of Scintilla 11-4152 Crimping Tool, or equiva-
lent, crimp eyelet to wire. Approximately 1/32 of an inch of wire should extend
from end of eyelet after crimping. (Refer to B of Figure 8A-30.)

233 233

Figure 8A-29. Lead Assembl

Assembly Figure 8A-30. Wire Doubled Over
Installed in Grommet For Installation of Eyelet

POWER PLANT 3B20 Reissued: 1/15/81

 PIPER CHEROKEE SERVICE MANUAL

NOTE

If the crimping tool is not available, a satisfactory

connection can be made by soldering with Kester Flux
709 or equivalent and a non-corrosive solder. After
soldering, clean solder joints using denatured alcohol.

16. Install clamps and calbe ties as necessary to secure lead to the engine.

8A-37. INSTALLATION OF HARNESS. Before installing harness on magneto,

check mating surfaces for cleanliness. Spray entire face of grommet with a light
coat of Plastic Mold Spray, SM-O-O-TH Silicone Spray or equivalent. This will
prevent harness grommet from sticking to magneto distributor block.
a. Placetheharness terminal plate on the magneto and tighten nuts around the
plate alternately to seat cover squarely on magneto. Torque nuts to 18 to 22 inch
pounds.
b. Route ignition wires to their respective cylinders.
c. Clamp the harness assembly in position.
d. Connect the leads to the spark plugs.

8A-38. SPARK PLUGS.

8A-39. REMOVAL OF SPARK PLUGS.

a. Loosen the coupling nut on the harness lead and remove the terminal in-
sulator from the spark plug barrel well.

NOTE

When withdrawing the ignition cable lead connection

from the plug, care must be taken to pull the lead
straight out and in line with the center line of the plug
barrel; otherwise a side load will be applied, which
frequently results in damage to the barrel insulator
and connector. If the lead cannot be removed easily
in this manner, the resistingcontact between the neo-
prene collar and the barrel insulator will be broken
by a rotary twisting of the collar. Avoid undue dis-
tortion of the collar and possible side loading of the
barrel insulator.

Reissued: 1/15/81 3B21 POWER PLANT

 PIPER CHEROKEE SERVICE MANUAL

b. Remove the spark plug from the engine. In the course of engine operation,
carbon and other combustion products will be deposited on the end of the spark
plug and will penetrate the lower threads to some degree. As a result, greater
torque is frequently required for removing a plug than for its installation. Ac-
cordingly, the torque limitations given do not apply to plug removal and sufficient
torque must be used to unscrew the plug. The higher torque in removal is not as
detrimental as in installation, since it cannot stretch the threaded section. It
does, however, impose a shearing load on this section and may, if sufficiently
severe, produce a failure in this location.

NOTE

Torque indicating handle should not be used for spark

plug removal because of the greater torque require-
ment.

c. Place spark plugs in a tray that will identify their position in the engine as
soon as they are removed.

NOTE

Spark plugs should not be used if they have been dropped.

d. Removalof seized spark plugs in

the cylinder may be accomplished by 234
application of liquid carbon dioxide by
a Conical metal funnel adapter with a
hole at the apex just large enough to
accommodate the funnel of a CO2 bottle.
(Refer to Figure 8A-31.) When a seized
sparkplug cannot be removed by normal
means, the funnel adapter is placed over
and around the spark plug. Place the
funnel of the CO2 bottle inside the funnel
adapter and release the carbon dioxide
to chill and contract the spark plug.
Break the sparkplug loose witha wrench.
A warm cylinder head at the time the
carbon dioxide is appliedwill aidin the
removal of an excessively seized plug.
e. Do not allow foreign objects to Figure 8A-31. Removing Spark Plug
enter the spark plug hole. Frozen to Bushing

Reissued: 1/15/81 3B22 POWER PLANT

 PIPER CHEROKEE SERVICE MANUAL

8A-40.. INSPECTION AND CLEANING OF SPARK PLUG.

a. Visually inspect each spark plug for the following non-repairable defects:
1. Severely damaged shellor shield threads nicked up, stripped or cross-
threaded.
2. Badly battered or rounded shell hexagons.
3. Out-of-round or damaged shielding barrel.
4. Chipped, cracked or broken ceramic insulator protions.
5. Badly eroded electrodes worn to approximately 50% of original size.
b. Clean the spark plug as required, removing carbon and foreign deposits.
c. Set the electrode gap at .015 to .018 inches.
d. Test the spark plug both electrically and for resistance.

8A-41. INSTALLATION OF SPARK PLUGS. Before installing spark plugs, as-

certain that the threads within the cylinder are clean and not damaged.
a. Apply anti-seize compound sparingly on the threads and install gasket and
spark plugs. Torque 360 to 420 inch pounds.

CAUTION

Make certain the deep socket is properly seated on the

spark plug hexagon as damage to the plug could result
if the wrench is cocked to one side when pressure is
applied.

b. Carefully insert the terminal insulator in the spark plug and tighten the
coupling unit.

8A-42. LUBRICATION SYSTEM.

8A-43. OIL PRESSURE RELIEF VALVE.

The function of the oil pressure relief valve, which is located between the
upper right engine mounting lug and No. 3 cylinder, is to maintain engine oil
pressure within specified limits by withdrawing a portion of the oil from the cir-
culating system and returning the oil to the sump should the pressure become
excessive. This valve is not adjustable; however, particles of metal or other
foreign matter lodged between ball and seat will result in a drop in oil pressure.
It it advisable, therefore, to disassemble, inspect and clean the relief valve if
excessive pressure fluctuations are noted.
The oil pressure relief valve is by no means to be confused with the oil

Reissued: 1/15/81 3B23 POWER PLANT

 PIPER CHEROKEE SERVICE MANUAL

cooler by-pass which is located on the oil pressure screen housing mounting pad. The sole
purpose of the by-pass valve is to serve as a safety measure, permitting pressure oil to by-pass
the oil cooler entirely in case of an obstruction within the cooler.

8A-44. SWITCHING.

8A-45. REMOVING IGNITION SWITCH.

a. Insure the ignition switch is in the OFF position.
b. Gain access to and disconnect the power lead (+) from the battery.
c. Remove the ignition switch retaining nut from the switch on the forward side of the
instrument panel and withdraw the switch from the panel.
d. Mark the wires and note their position on the switch, then disconnect the wires.

8A-46. INSTALLATION OF IGNITION SWITCH. (Refer to Figure 8A-32.)

a. Attach wires to the switch as shown in Figure 8A-32.
b. Position the ignition switch in the instrument panel and secure with retaining nut.
c. Connect the power lead (+) to the battery and reinstall any access covers previously
removed.

.C236 J1A

TAB

K1A GND

J2A

BAT

PR K1B

PA-28R-180,S/N 28R-30005TO 28-7130019

PA-28R-200,S/N 28R-30482,28R-35001 TO 28R-7435331

Figure 8A-32. Ignition Switch Wiring Positions

Revised: 8/3/81 3B24 POWER PLANT

 PIPER CHEROKEE SERVICE MANUAL

TABLE VIIIA-I. ENGINE TROUBLESHOOTING

Trouble Cause Remedy

Failure of engine to Lack of fuel. Check fuel system for

start. leaks. Fill fuel tank.
Clean dirty lines, strain-
ers or fuel valves.
Check fuel selectorvalve
for proper tank.
Check fuel pressure with
electric boost pump ON.
Check mixture control
knob for full rich.

Overpriming. Open throttle and "unload"

engine by engaging
starter. Mixture in
idle-cut-off.

Incorrect throttle Open throttle to one-

setting. eight of its range.

Defective spark plugs. Clean and adjust or re-

place spark plugs.

Defective ignition wire. Check with electric test-

er and replace defective
wires.

Defective battery. Replace with charged

battery.

Improper operation of Clean points. Check in-

magneto breaker. ternal timing of mag-
netos.

Lack of sufficient fuel Disconnect fuel line at

flow. fuel injector and check
fuel flow.

Reissued: 1/15/81
3C1 POWER PLANT
 PIPER CHEROKEE SERVICE MANUAL

TABLE VIIIA-I. ENGINE TROUBLESHOOTING (cont.)

Trouble Cause Remedy

Failure of engine to Internal failure. Check oil screens for

start. (cont.) metal particles. If
found, complete over-
haul of engine may be
indicated.

Failure of engine to Incorrect idle mixture. Adjust mixture.

idle properly.
Leak in the induction Tighten all connections
system. in the induction sys-
tem. Replace any parts
that are defective.

Incorrect idle adjust- Adjust throttle stop to

ment. obtain correct idle.

Uneven cylinder com- Check condition of pis-

pression. ton rings and valve
seats.

Faulty ingition system. Check entire ignition

system.

Insufficient fuel pres- Adjust fuel pressure.

sure.

Low power and uneven Mixture too rich; indi- Readjustment of fuel in-
cated by sluggish en- jector by authorized
gine operation, red ex- personnel is indicated.
haust flame at night.
Extreme cases indi-
cated by black smoke
from exhaust.

Reissued:1/15/81 3C2 POWER PLANT

 PIPER CHEROKEE SERVICE MANUAL

TABLE VIIIA-I. ENGINE TROUBLESHOOTING (cont.)

Trouble Cause Remedy

Low power and uneven Mixture too lean; indi- Check fuel lines for
running. (cont.) cated by overheating dirt or other restric-
or backfiring. tions. Check fuel in-
jection nozzles.

Leaks in induction Tighten all connections.

system. Replace defective
parts.

Defective spark plugs. Clean and gap or re-

place spark plugs.

Improper fuel. Fill tank with fuel of

recommended grade.

Magneto breaker points Clean points. Check

not working properly. internal timing of mag-
netos.

Defective ignition wire. Check wire with electric

tester. Replace de-
fective wire.

Defective spark plug Replace connectors on

terminal connectors. spark plug wire.

Failure of engine to Leak in the induction Tighten all connections

develop full power. system. and replace defective
parts.

Throttle lever out of Adjust throttle lever.

adjustment.

Improper fuel flow. Check strainer, gauge

and flow at fuel injec-
tor inlet.

Reissued: 1/15/81 3C3 POWER PLANT

 PIPER CHEROKEE SERVICE MANUAL

TABLE VIIIA-I. ENGINE TROUBLESHOOTING (cont.)

Trouble Cause Remedy

Failure of engine to Restriction in air scoop. Examine air scoop and

develop full power. remove restrictions.
(cont.)
Improper fuel. Drain and refill tank
with recommended
fuel.

Faulty ignition. Tighten all connections.

Check system with
tester. Check ignition
timing.

Rough engine. Cracked engine mount. Replace or repair

mount.

Defective mounting Install new mounting

bushings. bushings.

Uneven compression. Check compression.

Low oil pressure. Insufficient oil. Fill sump with recom-

mended oil.

Air lock or dirt in re- Remove and clean oil

lief valve. pressure relief valve.

Leak in suction line or Check gasket between

pressure line. accessory housing and
crankcase.

Dirty oil strainers. Remove and clean oil

strainers.

Defective pressure Replace gauge.

gauge.

Reissued:1/15/81 3C4 POWER PLANT

 PIPER CHEROKEE SERVICE MANUAL

TABLE VIIIA-I. ENGINE TROUBLESHOOTING (cont.)

Trouble Cause Remedy

Low oil pressure. Stoppage in oil pump Check line for obstruc-
(cont. ) intake passage. tion. Clean suction
strainer.

High oil temperature. See "High Oil Temper-

ature" in "Trouble"
column.

High oil temperature. Insufficient air cooling. Check air inlet and out-
let for deformation or
obstruction.

Insufficient oil supply. Fill oil sump to proper

level with specified oil.

Low grade of oil. Replace with oil con-

forming to specifica-
tions.

Clogged oil lines or Remove and clean oil

strainers. strainers.

Excessive blow-by. Usually caused by worn

or stuck rings.

Failing or failed Examine sump for

bearing. metal particles. If
found, overhaul of en-
gine is indicated.

Defective temperature Replace gauge.

gauge.

Excessive oil consump- Low grade of oil. Fill tank with oil con-
tion. forming to specifica-
tions.

Reissued: 1/15/81 3C5 POWER PLANT

 PIPER CHEROKEE SERVICE MANUAL

TABLE VIIIA-I. ENGINE TROUBLESHOOTING (cont.)

Trouble Cause Remedy

Excessive oil consump- Failing or failed bear- Check sump for metal
tion. (cont.) ings. particles.

Worn piston rings. Install new rings.

Incorrect installation of Install new rings.

piston rings.

Failure of rings to seat Use mineral base oil.

(new nitrided cylin- Climb to cruise altit-
ders. ) ude at full power and
operate at 75% cruise
power setting with high
oil temperature until
oil consumption stabil-
izes.

Reissued: 1/15/81 3C6 POWER PLANT

 3C7
INTENTIONALLYLEFT BLANK
 SECTION IX
FUEL SYSTEM
Paragraph Aerofiche
Grid No.
9-1. Introduction ................................................. 3C10
9-2. Description .................................................. 3C10
9-3. Troubleshooting .............................................. 3C17
9-4. Main Fuel Tanks (PA-28-140, -150, -160, -180, -235
and PA-28R) ............................................ 3C17
9-5. Removal of Main Fuel Tanks .................. ...... 3C17
9-6. Inspection and Repair of Main Fuel Tank .............. 3C17
9-7. Installation of Main Fuel Tank ........................ 3C18
9-8. Tip Fuel Tanks (PA-28-235) ................................... 3C18
9-9. Removal of Tip Tank ............................. ... 3C18
9-10. Fuel Tank Repair (Fiberglas) ................ .................. 3C18
9-11. Installation of Tip Tank ......................... ... .. 3C19
9-12. Fuel Quantity Transmitter Unit ................................ 3C19
9-13. Removal of Fuel Quantity Transmitter Unit ............. 3C19
9-14. Installation of Fuel Quantity Transmitter Unit .......... 3C19
9-15. Fuel Quantity Transmitter/Gauge Check ............... 3C19
9-16. Check and Adjustment of Fuel Quantity
Transmitter Unit ................................ 3C20
9-17. Fuel Valves .................................................. 3C22
9-18. Fuel Shutoff Valve (PA-28-140, -150, -160,
-180, and PA-28R) ............................... 3C22.
9-19. Removal of Fuel Shutoff Valve ........................ 3C22
9-20. Disassembly of Fuel Shutoff Valve ..................... 3C22
9-21. Cleaning, Inspection and Repair of Fuel
Shutoff Valve................................... 3C22
9-22. Assembly of Fuel Shutoff Valve ....................... 3C23
9-23. Installation of Shutoff Valve .......................... 3C23
9-24. Fuel Selector Valve and Filter (PA-28-235) .......... ............ 3C23
9-25. Fuel Selector Valve Operation......................... 3C23
9-26. Removal of Fuel Selector Valve and Filter .............. 3C23
9-27.. Port Repair of 1H26-4 Fuel Selector ................... 3C24
9-28. Cleaning Filter Assembly ............................. 3D1
9-29. Installation of Fuel Selector and Filter Valve............ 3D2
9-30. Fuel Filter Bowl and Screen (PA-28-140, -150, -160,
-180, and PA-28R) ....................... 3D3
9-31. Removal of Fuel Filter Bowl and Housing .............. 3D3
9-32. Installation of Fuel Filter Bowl and Screen ............. 3D3
9-33. Cleaning and Inspection of Filter Bowl Screens.......... 3D4

Reissued: 1/15/81
3C8
 PIPER CHEROKEE SERVICE MANUAL

Paragraph Aerofiche
Grid No.
9-34. Electric Fuel Pumps .......................................... 3D4
9-35. Plunger Fuel Pumps (PA-28-140,-150, -160, -180, and -235) ....... 3D4
9-36. Removal of Fuel Pumps .............................. 3D4
9-37. Disassembly of Fuel Pump ........................... 3D5
9-38. Cleaning, Inspection and Repair of Fuel Pump .......... 3D7
9-39. Resistance Check (Plunger Type Pump) ................ 3D7
9-40. Assembly of Fuel Pump .............................. 3D7
9-41. Adjustment of Electric Fuel Pump (Bench Test) ......... 3D8
9-42. Adjustment of Electric Fuel Pump (In Airplane)......... 3D8
9-43. Installation of Fuel Pumps ............................ 3D9
9-44. Rotary Fuel Pumps (Weldon) (PA-28R) .. .................. 3D10
9-45. Removal of Fuel Pump .............................. 3D10
9-46. Disassembly, Repair and Assembly of Fuel Pump ....... 3D10
9-47. Adjustment of Electric Fuel Pump (Bench Test) ......... 3D11
9-48. Adjustment of Electric Fuel Pump (In Airplane) ......... 3D 11
9-49. Installation of Fuel Pump ............................ 3D12
9-50. Engine Primer Pump ........................................ 3D12
9-51. Removal of Engine Primer ......... ................. 3D 12
9-52. Disassembly, Cleaning and Assembly of Engine
Primer ......................................... 3D 12
9-53. Installation of Engine Primer Pump .................... 3D13
9-54. Primer Jets .................................................. 3D13
9-55. Cleaning Fuel System ......................................... 3D13

Reissued: 1/15/81 3C9

 PIPER CHEROKEE SERVICE MANUAL

SECTIONIX

FUEL SYSTEM

9-1. INTRODUCTION. The fuel system components covered in this section consist of the
fuel tanks, selector valves, filter screens and fuel pumps. Instructions are given for
remedying difficulties which may arise in the normal operation of the fuel system. The
instructions are organized so the mechanic can refer to: Removal, Repair, Installation and
Adjustment of each part of the system.
Maintenance for carburetion and fuel injection may be found under Power Plant,
Section VIII or VIIIA.

9-2. DESCRIPTION. The PA-28-140,-150, -160, -180 and PA-28R airplanes are equipped
with aluminum fuel tanks consisting of one in the inboard leading edgesection of each wing.
Each tank has a capacity of 25 gallons. A strainer is installed in the fuel outlet of each tank.
From the tank outlet a fuel line is routed through the wings to the fuel selector valve located
on the left side of the cabin in front of the pilot's seat; from the fuel selector valve a line leads
to the fuel strainer bowl mounted on the left forward face of the fire wall. A fuel line is routed
from the strainer bowl to the electric fuel pump, engine driven fuel pump and then to the
carburetor injector inlet port.
Two electrical fuel quantity gauges are mounted within the instrument cluster. Each
gaugeis connected to a transmitter unit installed in the fuel tanks.
On the PA-28-235 the fuel tanks consist of one aluminum tank located in the inboard
leading edge section of each wing plus fiberglas tanks located in each wing tip. The main
tanks have a maximum capacity of 25 gallonseach while the tip tanks hold 17 gallonseach.
A strainer is installed in the fuel outlet of each tank. From the tank outlet a fuel line is
routed through the wings to a fuel selector and strainer valve located under the rear seat.
The fuel selector valve is controlled remotely by a selector mechanism located on the
sloping face of the control tunnel. The strainer portion of the valve is operated by a lever
located on the lower right front of the rear seat. From the selector valve, fuel is drawn
through the electric fuel pump(s) located in the area under the rear seat, through the engine
driven pump and onto the carburetor.
Four electrical fuel quantity gauges are mounted within the instrument cluster. Each
gauge is connected to a transmitter unit installed in the fuel tanks.

Reissued: 1/15/81 3C10 FUEL SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

1787

FUEL
QUANTITY
GAUGES

FUEL
VALVE
TANK
SELECTOR

FUELTANK
SELECTOR
VALVE

FUEL
STRAINER
RIGHT
MAINTANK LEFT
MAINTANK

PRIMER
-ENGINE
FUEL
PUMP

ELECTRIC
FUELPUMP
FUEL
PRESSURE
GAUGE

CARBURETOR

Figure 9-1. Fuel System Diagram (PA-28-140,-150, -160, -180)

Reissued: 1/15/81 FUEL SYSTEM

3C11
 PIPER CHEROKEE SERVICE MANUAL

1780

CARBURETOR

THROTTLE
MIXTURE
CONTROL
SELECTOR
FUEL

PUMP
FUEL
ENGINE

LEFT
TIPTANK LEFT TANK
MAIN RIGHT TANK
MAIN TIPTANK
RIGHT

PUMPS
FUEL

GAUGES
QUANTITY
FUEL

Figure 9-2. Fuel System Diagram

(PA-28-235, Serial Nos. 28-10003 to 28-10719 incl.)

Reissued: 1/15/81 3C12 FUEL SYSTEM

 PIPER CHEROKEE SERVICE MA NUAL

1771

CARBURETOR

CONTROL
SELECTOR
FUEL

ENGINE

LEFT
TIPTANK LEFT TANK
MAIN RIGHT
MAIN
TANK RIGHT
TIPTANK

ELECTRIC
FUEL
PUMP

FUEL
QUANTITY
GAUGES

Figure 9-3. Fuel System Diagram

(PA-28-235, Serial Nos. 28-10720 and up)

Reissued: 1/15/81 3C13 FUEL SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

C350
FUELQUANTITY FUEL QUANTITY
PRESSURE FUEL
GAUGE GAUGE GAUGE

RIGHT
TANK FUEL LEFT
TANK
SELECTOR
U U
DRAIN DRAIN

GASCOLATOR

FLOW
FUEL
GAUGE

VENT ELECTRIC
FUELPUMP

ENGINE
DRIVEN
FUELPUMP

FLOW FUELINJECTOR

Figure 9-4. Fuel System Diagram(PA-28R)

Reissued: 1/15/81 3C14 FUEL SYSTEM

 3C15
INTENTIONALLYLEFT BLANK
 3C16
INTENTIONALLY LEFT BLANK
 PIPER CHEROKEE SERVICE MANUAL

9-3. TROUBLESHOOTING.Troubles peculiar to the PA-28 fuel system are listed in Table
IX-III along with their probable causes and suggested remedies. When troubleshooting,
check from the power supply to the items affected. If no trouble is found by this method,
the trouble probably exists inside individual pieces of equipment; they may then be
removed from the airplane and an identical unit or units, tested and known to be good,
installed in their place.

9-4. MAIN FUEL TANKS. (PA-28-140,-150, -160, -180, -235 and PA-28R.)

9-5. REMOVALOF MAINFUEL TANKS.

a. Drain the fuel from the fuel tank. (Refer to DrainingFuel System, Section II.)
b. Remove the screwsfrom around the perimeter of the tank assembly.
c. Disconnect fuel line attached to tank.
d. Pull the tank away from the wing assemblyfar enough to gain accessfor removal of
the sender wire.
e. The tank is now free to be removed.

9-6. INSPECTIONAND REPAIR OF MAINFUEL TANK. The entire interior of the main
tanks should be inspected for peeling of small areas of the sloshingcompound. Indications
are that in the majority of cases the peeling is started just inside the filler neck as a result of
the metal nozzle of the gas filler hose nicking the compound. The following items are
recommended:
a. The entire interior of the main tanks should be inspected with the tanks drained.
This is accomplishedwith a mirror and inspection light through the filler neck. Small scrapes
in the film adjacent to the filler neck may be disregardedprovided there is no indication of
peeling.
b. If peeling has occurred and separated material is found, the main tank should be
removed and resloshed in accordance with the instructions included with each can of
Randolph Sloshing Sealer 802, Piper part number 757 572v. (Approved under Mil. Spec.
MIL-L-6047B.) One gallon of sloshing compound is required per tank. After sloshing the
tank, apply 1.5 lbs. air pressure and using a soap and water solution, check for leaks.
c. After resloshing, reinspect as above at intervals of 100 hours. These inspections may
be discontinued after the second inspection if no peeling is discovered.

Reissued: 1/15/81 FUEL SYSTEM

3C17
 PIPER CHEROKEE SERVICE MANUAL

NOTE
The fuel tank should be replaced if the tank is damaged to
the extent it cannot be repaired by the above method.

9-7. INSTALLATIONOF MAIN FUEL TANK.

a. Slide the main tank partly into position and connect the sender wire.
b. Slide the tank completely into place and secure with screwsaround its perimeter.
c. Connect fuel line on inboard side of tank. The flexible hose from the fuel tank must
not be twisted during installation on applicable models.
d. Fill the fuel tank and check for leaks, unrestricted fuel flow and proper sender
indications on the quantity gauge.

9-8. TIP FUEL TANKS(PA-28-235).

9-9. REMOVALOF TIP TANK.

a. Drain the fuel from the tank to be removed. (Refer to Draining Fuel System,
Section II.)
b. Remove the accesscover from the bottom of the wing tip.
c. By working through the access, disconnect the fuel line, fuel quantity transmitting
wire and position light wire. Remove the two nuts, washers and bolts which hold the tank to
the wing.
d. Carefully remove the screws from around the wing tip and remove the tip assembly.

9-10. FUEL TANK REPAIR. (Fiberglas). The wing tip tanks are constructed of fiberglas.
Minor repair of the tank can be accomplished with the use of Fiberglas Repair Kit No.
756 729. This kit along with instructions is obtained from Piper Dealers or Distributors.
Additional fiberglasrepairs may be found in Section IV of the Manual.

Reissued: 1/15/81 3C18 FUEL SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

9-11. INSTALLATION OF TIP TANK.

a. Position the wing tip in place on the wing and insert the two bolts, washers and
nuts on their proper places and tighten. Replace the several screws around the tip tank and
tighten. Connect the position light leads, the fuel quantity transmitting wire and the fuel line.
b. After the wing tip is installed and all connections are secured, fill the tip tank and
check for fuel leaks, operation of the fuel gauge and position light.
c. Install the access cover to the bottom of the wing tip.

9-12. FUEL QUANTITY TRANSMITTER UNIT.

9-13. REMOVAL OF FUEL QUANTITY TRANSMITTER UNIT.

a. Remove the fuel tank. (Refer to Paragraph 9-5 or 9-9.)
b. Disconnect the transmitter wire from the connection post.
c. Cut the safety wire which secures the five attaching screws.
d. Remove the five screws or bolts and remove the unit.

9-14. INSTALLATION OF FUEL QUANTITY TRANSMITTER UNIT.

a. Position the transmitter and gasket to the fuel tank and secure with machine screws
or bolts and washers. Torque bolts to 25 inch pounds. (Tip tank installation, install ground
wire under head of mounting screw.)
b. Safety the machine screws with MS20995-C32 wire.
c. Install the fuel tank. (Refer to Paragraph 9-7 or 9-10.)

9-15. FUEL QUANTITY TRANSMITTER/GAUGE CHECK. Fuel quantity trans-

mitter unit and gauge may be checked, while installed in the airplane, by the following
procedure:
a. Turn the fuel selector valve off.
b. Completely drain the fuel tank that relates to the gauge to be checked. (Refer to
Draining Fuel System, Section II.)
c. Level the airplane longitudinally and laterally.

NOTE

The electrical system should supply 14-volts to the gauge.

Revised: 10/3/83 3C19 FUEL SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

TABLE IX-I. TRANSMITTER/FUEL GAUGE TOLERANCES

MAIN TANK TIP TANK

Actual Fuel in Gauge Reading Actual Fuel in Gauge Reading

Tank (U. S. Gal) (U. S. Gal) Tank (U. S. Gal) (U. S. Gal)

Full 22 to Full* Full 15 to Full*

20 17 to 24 10 7 to 12
15 12 to 17 5 3 to 7
10 7 to 12 0 0 to-2
5 2to 6
0 0 to -2 *Plusone needle width

d. Turn the master switch on and observe the fuel quantity gauge. It should
read empty. Refer to Table IX-I for tolerances that are permitted between the
fuel gauge reading and the actual fuel in the tank.
e. Add fuel to the tank in the amount of five U. S. gallon increments until the
tank is full and observe the gauge readings.

NOTE

It will bepermissible to adjust the float assembly to

obtain specified tolerances. This adjustment may be
accomplished per instructions given in Paragraph 9-16.

9-16. CHECK AND ADJUSTMENT OF FUEL QUANTITY TRANSMITTER UNIT.

(Refer to Figure 9-6 or 9-7.)
a. If not previously removed, remove the transmitter unit to be checked from
the fuel tank. (Refer to Paragraph 9-13.)
b. Check and adjust the transmitter unit float position by using the following
procedure:
1. Fasten the unit to a fabricated checking jig with washers and nuts. (This
jig may be fabricated from dimensions given in Figure 9-14.)
2. Ascertain that with the float arm down against the mechanical stop on
the transmitter, the float is just touching (The float may be to .18 of aninch above
base the base of the jig. Should the float not be touching the base or the float arm
is not against the bottom stop, adjust the arm of float assembly, P/N 62037-00,
by bending it at the location as indicated in Figure 9-6 orthe arm stop of float
assembly, P/N 68101-00, by bending it where shown in Figure 9-7. (On rubber
type floats, the entire surface of the float must be horizontal with the base of jig.

FUEL SYSTEM
Reissued: 1/15/81 3C20
 PIPER CHEROKEE SERVICE MANUAL

A963
I IA
ADJUSTMENT LOCATIONS

Figure 9-6. Fuel Quantity Figure 9-7. Fuel Quantity

Transmitter (P/N 62037-00) Transmitter (P/N 68101-00)

TABLE IX-II. FUEL QUANTITY TRANSMITTER

CALIBRATION TOLERANCES

UNIT POSITION RESISTANCE

P/N 62037-00 Empty .00 to 0.5 ohms

(Metal Float) Full 29.6 to 31.3 ohms

P/N 68101-00 Empty 240 + 20, -0 ohms

(Rubber Float) Full 33.5 + 0, - 4.5 ohms

c. Check the transmitter unit for correct resistance and dead spots by the
following procedure:
1. Connect an ohmmeter to the transmitter unit and move the float arm to
its bottom mechanical stop. The ohmmeter should indicate the ohms resistance
as indicated in Table IX-II.
2. Move the float arm to its upper mechanical stop and check the ohms
resistance.
3. Check for dead spots by slowly moving the float arm from the bottom
stop to the upper stop and back. Watch the ohmmeter indicator; it should steadily
move up and down the scale without fluctuation as the float arm is moved.
4. If an incorrect resistance and/or dead spots are found, the transmitter
unit should be replaced.

Reissued: 1/15/81 FUEL SYSTEM

3C21
 PIPER CHEROKEE SERVICE MANUAL

9-17. FUEL VALVES.

9-18. FUEL SHUTOFF VALVE. (PA-28-140,-150, -160, -180 and PA-28R.)

9-19. REMOVALOF FUEL SHUTOFF VALVE.

a. Remove two screws holding the fuel valve placard plate and the screw holding the
fuel shutoff valve handle.
b. Remove fuel shutoff valve handle and placard plate.
c. Disconnect right and left fuel inlet lines from fuel valveassembly.
d. Disconnect fuel outlet line from fuel valve assembly.
e. Remove fuel valve assemblyby removing attaching screws.

9-20. DISASSEMBLYOF FUEL SHUTOFF VALVE. Aircraft equipped with fuel selector
valve P/N 11383-04,must be disassembled according to the latest revision of Piper Service
Bulletin No. 355. Disassembly of other fuel selector valves is not recommended.

9-21. CLEANING, INSPECTIONAND REPAIR OF FUEL SHUTOFF VALVE. Aircraft

equipped with fuel selector valve P/N 11383-04, must be cleaned, inspected, and repaired
according to the latest revision of Piper Service Bulletin No. 355. No cleaning, inspection, or
repair is recommended for other fuel selector valves.

THIS SPACEINTENTIONALLYLEFT BLANK

FUEL SYSTEM
Reissued: 1/15/81
3C22
 PIPER CHEROKEE SERVICE MANUAL

9-22. ASSEMBLY OF FUEL SHUTOFF VALVE. Aircraft equipped with fuel selector
valve P/N 11383-04must be assembled according to the latest revision of Piper Service Bul-
letin No. 355.
9-23. INSTALLATIONOF SHUTOFFVALVE.
a. Secure the valve to the bulkhead attachment plate with attaching screws.
b. Connect the fuel lines to the valve.
c. Install the fuel valveplacard with attaching screws.
d. Install the valve control handle with attaching screw.

9-24. FUEL SELECTORVALVEAND FILTER. (PA-28-235.)

9-25. FUEL SELECTORVALVE OPERATION. When the fuel selector handle is not in a
positive selector detent position, more than one fuel port will be open at the same time. It
should be ascertained that the fuel selector is positioned in a detent, which can be easily felt
when movingthe handle through its various positions.

9-26. REMOVALOF FUEL SELECTORVALVEAND FILTER.

a. Drain fuel from tanks. (Refer to Draining Fuel System, Section II.)
b. Remove rear seats, seat belt attachments and floor panel just aft of the main spar by
removingthe floor attachment screws. Lift the panel and remove.
c. Remove plate from bottom of the fuselagewhich coversfuel selector.
d. Disconnect the fuel lines and selector linkage from valveassembly.
e. Remove the four mounting screws which hold the fuel selector in place and remove
the selector assembly.

THIS SPACEINTENTIONALLYLEFT BLANK

Reissued: 1/15/81 3C23 FUEL SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

827 EXTERNALDETENT 926

10

1H28-4VALVES ONLY

1. PLATE, QUICK DRAIN

2. SHAFT, QUICK DRAIN
3. SLEEVE
4 BALL, HANDLE
7 5. VALVE HANDLE
6. BALL
7. FILTER
8. SPECIAL "O" RING
9. SPRING
10. SNAP RING

Figure 9-8. Fuel Selector and Filter (PA-28-235)

9-27. PORT REPAIR OF 1H264 FUEL SELECTOR. (Refer to Figure 9-8.) The
followinginformation is for the 1H26-4 valvesonly, and the PA-28 parts catalog should be
used to order replacement parts.
a. Remove and discard the snap ring (10), spring(9), ball (6) and "O" ring (8) from the
valveport.
b. Replace parts removedin Step a with new parts.
NOTE
Use only special "O" ring provided by service sparesand use
care not to push "O" ring into center of valvehousing.
c. Pressure check valve with 10 +5 -0 psi of air applied at outlet port. No bubbles
should be observed when valve is held with the four inlet ports pointing up and gasoline
placed in each port.
d. Rotate the fuel selector through its full cycle of tank positions to insure proper
operation.
e. Reinstall fittings with new "O" rings in each inlet port and reinstall the valve into
the airplane in accordance with Paragraph 9-29;,

R
Reissued: 1/15/81 3C24 FUEL SYSTE
 PIPER CHEROKEE SERVICE MANUAL

1715

1. FILTER
2. SPRING
3. RETAINERWASHER
METALLIC FILTER ASSEMBLY 4. BOWL NYLONFILTER ASSEMBLY

Figure 9-9. Fuel Filter (PA-28-235)

9-28. CLEANINGFILTER ASSEMBLY.

a. Remove the accesspanel to the filter bowl on the bottom of the fuselage.
b. Remove fuel strainer bowl.
c. Remove filter disc assembly from center stem by compressing filter retainer spring
and removing filter retainer washer. (Refer to Figure 9-9.)
d. Inspect bowl gasketand replace if necessary.
e. Filter discs may be cleanedas follows:
1. Plug open ends of filter disc center with stoppers to prevent dirt from entering.
2. Wash metallic filter disc in acetone, gasoline, carbon tetrachloride,
trichlorethylene (permachor) or Bendix cleaner. Washnylon filter disc with soap and water.
CAUTION

Do not use acetone, methylethylketone, etc., to clean nylon

filter discs.
3. Remove stubborn deposits from filter disc with a soft bristle brush.
4. Rinse all traces of soap solution. Drain or blow dry and remove stoppers.
f. Replace the filter disc if damageis evident.
g. Reinstall filter disc assemblyand strainer bowl.

FUEL SYSTEM
Revised: 10/3/83 3D1
 PIPER CHEROKEE SERVICE MANUAL

9-29. .INSTALLATIONOF FUEL SELECTORAND FILTER VALVE.

a. Position the valveinside the airplanejust aft of the main spar.
b. Secure the valvewith machinescrews,washers and self-lockingnuts.
c. Connect the fuel lines.
d. Rig fuel selector valve linkage to insure that selector handle engagesleft indent
position when it is against the safety stop on console cover.
e. Fill the fuel tanks and check all connections for leaks.
f. Install the rear seat.
g. Install the accessplate to the bottom of the fuselagewith attaching screws.
NOTE

When installing the fuel selector valve, it is recommended the

complete fuel system and tanks be drained and flushed to
ascertain no contamination is present. (Refer to paragraph
9-55.)

Reissued: 1/15/81 FUEL SYSTEM

3D2
 PIPER CHEROKEE SERVICE MANUAL

A640

1. BODY
2. SCREEN
3. GASKET
4. STRAINER 30WL
5. BAIL WIRE
6. BAIL ASSEMBLY
7. SAFETY WIRE
8. DRAIN VALVE

Figure 9-10. Fuel Filter Bowl and Screen

(PA-28-140, -150, -160, -180 and PA-28R)
9-30. FUEL FILTER BOWL AND SCREEN. (PA-28-140,-150, -160, -180 and PA-28R.)
(Refer to Figure 9-10.)

9-31.. REMOVAL OF FUEL FILTER BOWL AND HOUSING.

a. Ascertain that the fuel shutoff is in the off position.
b. Remove the engine cowlings by releasing the cowl fasteners or the attach-
ing screws, depending on the type installed. Be certain that all electrical leads
are disconnected prior to removal of the cowl.
c. Disconnect the fuel lines from the filter bowl housing.
d. Cut the safety wire, loosen the bail nut, move the bail wire to the side and
remove the bowl.
e. Remove the housing of the filter bowl by spreading the ends of the bail wire
allowing the housing to be lifted from the bracket.

9-32. INSTALLATION OF FUEL FILTER BOWL AND SCREEN.

a. Position the top of the filter bowl to the bracket and connect the fuel lines.
b. Spread the bail wire ends and insert them through the holes in the side of
the mounting bracket and the top of the filter bowl.
c. Position the bowl and bail wire, and tighten the bail nut.
d. Safety the bail nut and the bail wire assembly.
e. Install the engine cowling.

Reissued: 1/15/81 3D3 FUEL SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

9-33. CLEANING AND INSPECTION OF FILTER BOWL SCREEN.

a. Follow steps a, b and d of paragraph 9-31 for removal of the filter bowl.
b. Remove the gasket and screenfrom the filter housing.
c. Clean the screen and bowl with acetone or a suitable dry type solvent. If damaged,
replacescreen.
d. Replacethe screenfollowedby a new gasket.
e. Position the bowl and bail wire, and tighten the bail nut.
f. Safety the bail nut and the bail wire assembly.

9-34. ELECTRICFUELPUMPS.

9-35. PLUNGER FUEL PUMPS. (PA-28-140,-150, -160, -180 and -235.)

9-36. REMOVAL OF FUEL PUMPS.

a. On the PA-28-140, -150, -160, and -180, the fuel pump may be removed by the
following procedure:
1. Remove the cowlingsby releasing the cowl fasteners or the attaching screws,
depending on the type installed. Be certain all electrical leads are disconnected prior to
removal.
2. Ascertain that the fuel shutoff valveis in the off position.
3. Disconnectthe fuel pump electrical leads.
4. Disconnectthe fuel lines from the inlet and outlet sides of the pump.
5. Remove the nuts and bolts securing the pump to its mounting bracket and
remove the fuel pump.
b. On the PA-28-235, the electric fuel pump(s) may be removed by the following
procedure:
1. Ascertainthe fuel selector is in the off position.
2. Remove the fuel drain placard coverfrom the front of the rear seat by removing
the attaching screws.
3. Remove the bottom portion of the rear seat by unsnapping it across the front
and lifting the seat pullingit forward at the same time.
4. Removethe pump coverlocated in the left side of the floor opening.
5. Disconnectthe electricallead from the pump.
6. Disconnectthe inlet and oulet lines from the pump.
7. Removethe pump by removingthe pump attaching bolts.

Reissued:1/15/81 FUEL SYSTEM

3D4
 PIPER CHEROKEE SERVICE MANUAL

9-37. DISASSEMBLYOF FUEL PUMP. The following procedure is given for disassembly
of the fuel pump. Repair of the pump is limited to the fuel reservoir area only, since the
electrical system is sealed. For cleaning and servicing purposes, refer to the appropriate
instructions coveringthe particular type pump being serviced:
a. Early Type Pump: (Refer to Figure 9-11.)
1. Cut the safety wire and remove the bottom cover, gasket and filter
screen from the pump.

NOTE

If the screen does not come out, use caution removing

it from the pump housing so as not to damage it.

2. Remove the three screws securing the plunger spring cup inside the
pump. Remove the cup and gasket.
3. Pull the plunger spring and plunger assembly from the pump with fingers.

CAUTION

Do not remove the buffer spring and valve from the

plunger assembly.

b. Late Type Pump: (Refer to Figure 9-12.)

1. Cut the safety wire and remove the bottom cover, gasket, magnet and
filter screen from the pump.

NOTE

If the screen does not come out use caution removing

it from the pump housing so as not to damage it.

2. Remove the retainer spring from the plunger tube using thin nose pliers
to spread and remove the ends of the retainer from the tube.
3. Remove the washer, "O" ring seal, cup valve, plunger assembly from
the pump.

FUELSYSTEM
Reissued: 1/15/81 3D5
 PIPER CHEROKEE SERVICE MANUAL

C349

7 9

. COVER 7. PLUNGER VALVE

2. COVER GASKET 8. PLUNGER CUP
3. SCREW 9. PLUNGER SPRING
4. SCREEN 10. PLUNGER
5. CUP VALVE 11. PUMP BODY
6. GASKET

Figure 9-11. Plunger Fuel Pump (Early)

(PA-28-150,-160, -180)

C349

9 8 7 6 5 3 2 1

1. COVER 7. "O" RING

2. COVER GASKET 8. CUP VALVE
3. MAGNET 9. SPRING
4. FILTER 10. PLUNGER
5. RETAINER 11. PLUNGER TUBE
6. WASHER 12. PUMP BODY

Figure 9-12. Plunger Fuel Pump (Late)

(PA-28-140,-150, -160, -180, -235)

Reissued: 1/15/81 3D6 FUEL SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

CAUTION

Do not remove the buffer spring and valve from the

plunger assembly.

Do not tamper with seal at center of mounting bracket

at side of pump as it retains the dry gas which sur-
rounds the electric system in the upper portion of the
pump.

9-38. CLEANING, INSPECTION AND REPAIR OF FUEL PUMP.

a. Clean all parts with acetone or a suitable dry type solvent. If plunger
assembly does not come clean or there are any rough spots, polish gently with
crocus cloth.
b. Inspect the pump for the following:
1. Check the filter screen for damage or distortion.
2. Gently touch the cup valve and check for freedom of movement. Do not
disassemble.
3. Shake the plunger assembly and listen for clicks to indicate valve action.
4. On the late model pumps, check the condition of the "O" ring.
5. Check the condition of the cover gasket and plunger spring cup gasket.
c. Repair of the pump is limited to replacementof parts found defective during
inspection.

9-39. RESISTANCE CHECK (PLUNGER TYPE PUMP). To check the resistance

of the pump, connect an ohmmeter to the lead wire of the pump and the pump
body. A reading of 4.87 to 6.4 ohms for a 12-volt pump should be obtained.

9-40. ASSEMBLY OF FUEL PUMP.

a. Later Type Pump: (Refer to Figure 9-11.)
1. Insert the plunger assembly (10) in the tube with the buffer spring end
first. Check fit by slowly raising and lowering the plunger to stick. If a click
cannot be heard, the interrupter assembly is not functioning properly in which
case the pump should be replaced.
2. Install the component parts in the following order: Cup valve, "O" ring
seal, and washer. Install the retainer spring securing the components inside the
pump housing.
3. Place the cover gasket and magnet in the bottom cover with the filter
screw.

Reissued: 1/15/81 3D7 FUEL SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

4. Carefully guide the screen around the plunger spring cup. The screen
must fit snugly at both ends. Do not pinch or distort the screw. Draw the bottom
cover tight with a wrench and safety.
b. Early Type Pump: (Refer to Figure 9-12.)
1. Insert the plunger spring assembly (10) in the tube with the buffer spring
end first. Check fit by slowly raising and lowering the plunger in the tube. It
should move fully without any tendency to stick. If a click cannot be heard, the
interrupter assembly is not functioning properly in which case the pump should
be replaced.
2. Install the plunger spring cup gasket (use a new one) and the plunger
spring cup. Draw the screws reasonably tight, but do not over tighten them. Be
sure the cup is not cocked to prevent the plunger from binding in the tube.
3. Place the filter screen around the bottom cover magnet.
4. Carefully guide the screen around the plunger spring cup. The screen
must fit snugly at both ends. Do not pinch or distort the screen. Draw the bottom
cover tight with a wrench and safety.

9-41. ADJUSTMENT OF ELECTRIC FUEL PUMP (BENCHTEST).

a. Ascertain that the pump is sufficiently lubricated to prevent damage if run
dry for a period greater than five minutes.
b. Connect the electrical lead of one pump to a 14-volt DC power source.
c. Using a suitable container with the proper octane fuel, connect a fuel line
from a container to the inlet side of the pump.
d. Connect another line from the outlet side of the pump to a pressure gauge
and by-pass valve and back to the container.
e. Run the pump with the by-pass valve open until a steady flow of fuel is ob-
tained. Then close the by-pass valve and check the pressure gauge for the proper
reading of 4 to 4.75 psi maximum, no flow.
f. Repeat steps b through e for the second fuel pump.
g. If the proper pressure is not obtained, the plunger spring may be replaced
or it may be necessary to replace the complete pump assembly.

9-42. ADJUSTMENT OF ELECTRIC FUEL PUMP (IN AIRPLANE).

a. With the access panel removed and the fuel selector in the OFF position,
remove the fuel line from the outlet end of the pump.
b. Connect a test line with a by-pass valve and pressure gauge to the outlet
end of the pump to be checked.
c. Place a container below the pumpto catch any fuel from the test line during
the adjustment of the pump.

Reissued: 1/15/81 3D8 FUEL SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

d. Disconnect the electrical lead to the pump that is not being checked.
e. Turn the fuel selector on, open the by-pass valve on the test line and start
the pump.
f. When a steady flow of fuel is obtained, close the by-pass valve and check
the reading on the pressure gauge. It should read 4 to 4.75 psi maximum, no
flow. Do not keep by-pass valve closed for more than one minute during pump
operation and adjustment.
g. Repeat steps b through f for the other pump.
h. If the proper pressure is not obtained, the plunger spring may be replaced
or it may be necessary to replace the complete pump assembly.
i. Reconnect the original fuel line to the pump. Open fuel selector and run
the pump to check for any fuel leaks.
j . Shut off the pump, close the fuel selector and replace and secure the access
panel.

9-43. INSTALLATION OF FUEL PUMPS.

a. Install the fuel pump on PA-28-140,-150, -160, and -180 airplanes by the following
procedure:
1. Position the fuel pump tothe engine mount frame and secure with bolts,
washers and nuts.
2. Connect the fuel lines to the pump.
3. Connect the electrical leads to the pump.
4. Turn the fuel shutoff on and operate the fuel pump. Check all fuel line
fittings for leakage.
5. Install the cowling.
b. Install the fuel pump(s)on PA-28-235 airplanes by the following procedure:
1. Position the fuel pump(s) behind the main spar and secure with bolts,
washers and nuts.
2. Connect the inlet and outlet lines to the pump.
3. Connect the electrical leads to the pump.
4. Turn the fuel selector on and operate the pump(s). Check all fuel line
fittings for leakage.
5. Install the pump cover with attaching screws.
6. Install the bottom section of the rear seat.
7. Install the fuel drain cover with attaching screws.

Reissued: 1/15/81 3D9 FUEL SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

9-44. ROTARY FUEL PUMPS (WELDON) (PA-28R).

9-45. REMOVAL OF FUEL PUMP.
a. Remove the engine cowling from the aircraft.
b. Ensure the fuel shutoff valve is in the off position.
c. Disconnect the electrical leads from the pump.
d. Disconnect the fuel lines from the pump.
e. Remove the cap screws, washers, and plate.
f. Remove the fuel pump from the airplane.
9-46. REPAIR OF FUEL PUMP.
-CAUTION -
Overhauling fuel pump is not recommended
because of special tools needed. If overhauling
is necessary,the pump should be returned to:
The Weldon Tool Company
300 Woodhill Road
Cleveland, Ohio 44104
However, some repairs may be accomplished as follows:
a. Replacing the shaft seal.
1. Remove the pump end assembly from the motor by removing the four machine screws.
2. Pry the shaft seal loose from the insert.
3. Check the shaft for burrs, scratches or any defects which might cause the seal to wear.
Any defect would be cause for pump replacement.
4. Replace the seal on the shaft and press into place.
5. Install the pump end assemblyto the motor in its original position. Install the four machine
screws and safety.
b. Repairing the relief valve.
1. Remove the adjusting screw from the pump end assembly. Do not change the position
of the jam nut.
2. Remove the valve plunger and spring.
3. Inspect the valve seat, plunger and spring for condition and wear. If the valve seat is
damaged, replace the pump.
4. Install the plunger, spring, and adjusting screw to the pump.
5. Adjust the pump pressure as described in paragraph 9-47 or 9-48.
c. Replacing fitting O-rings.

- WARNING -
If O-rings are defective or if inlet fitting is not
properly installed, air will be drawn into fuel line,
causing engine to run lean or stop running. Install
new O-rings whenever fuel pump is removed for
service.
1. Remove inlet and outlet fittings.
2. Remove O-rings. Inspect chamfered O-rings seat for nicks.

Reissued: 1/15/86 3D10 FUEL SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

3. Install new O-rings.

- CAUTION -
Seal all pipe threads with Lubon #404.Do not apply
to the first two threads or sealant may enter fuel
system.
4. Replace fittings. Torque to 230-360in.-lb.
9-47. ADJUSTMENT OF ELECTRIC FUEL PUMP (BENCH TEST).
a. Ensure that the pump is sufficeintlylubricated to prevent damage.
b. Connect the electric leads to a 14-voltDC power source.
c. Using an approved container with the proper octane fuel, connect a fuel line
from the container to the inlet fitting.
d. Connect another line from the pump outlet to a pressure gauge and by-passvalve
and back to the container.
e. Run the pump with the by-pass valve open until a steady flow of fuel is ob-
tained.
f. Close the by-pass valve and check the pressure gauge for a proper reading of 26
to 29 psi, no flow. Do not keep the by-passvalve closedfor more than one minute
during pump operation and adjustment.
g. Loosen the locknut and turn the adjusting scre until there is a reading of 29 psi
maximu, no flow, on the gauge. Repeat steps e, f, and g until the proper pressure
is obtained.
h. Disconnect the power source from the pump and lock the adjustment screw with
the locknut. Remove the fuel lines from the pump.

9-48. ADJUSTMENT OF ELECTRIC FUEL PUMP (IN AIRPLANE).

a. With the access panel removed and the fuel selector valve in the OFF position,
remove the fuel line from the outlet end of the pump.
b. Connect a test line with a by-pass valve and pressure gauge to pump outlet.
c. Place a container below the pump to catch any fuel from the test line.
d. Turn the fuel selector valve on, open the by-pass valve on the test line, and start
the pump.
e. When fuel flow becomes steady, clsoe the by-pass valve and check the reading
on the pressure gauge. The gauge should read 26 to 29 psi, no flow. Do not keep
the by-pass valve closed for more than one minute during pump operation and
adjustment.
f. Loosen locknut on adjusting screw and turn the screw to obtain the proper
pressure of 29 psi maximum, no flow. Repeat this step until adjustment is
complete. Lock adjusting screw with locknut.
g. turn off fuel pump and close fuel selector valve. Remove the test line from the
pump.
h. connect the original fuel lines to the pump. Open fuel selector valve and run
the pump to check for any fuel leaks.
i. Shut off the pump, close the fuel selector valve and replace access panel.

Revised: 1/15/86 3D11 FUEL SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

9-49. INSTALLATION OF FUEL

C349
PUMP.
a. Place fuel pump inside cover
assembly and secure with cap
screws, washers and plate. -
WARNING -

If O-rings are defectiveor if inlet fitting

is not properly installed, air will be
drawn into fuel line, cuasing engine to
run very lean or stop running. Install
new O-rings whenever fuel pump is 1. CHECK BALL 8. STOP PIN
removed for service. 2. BALL SPRING 9. PUMP HANDLE
3. RETAINER SCREW 10. FACE NUT
4. "O" RINGS II. WASHER
b. Inspect chamfered O-ring seat 5. CYLINDER 12. LOCK NUT
6. SEALING SPRING 13. SEALING PIN
for nicks. 7. PISTON
c. Install new O-rings between
the fittings and the pump. Figure 9-13. Engine Primer
d. Connect fittings to fuel pump.
Torque to 230-360in.-lb.
e. Connect fuel linesto fuel pump
fittings.
f. Connect the electrical leads to
the pump.
g. Turn the fuel selector valve on
and operate the fuel pump. Check
the line fittings for leakage.
h. Install the cowling.

9-50. ENGINE PRIMER PUMP.

9-51. REMOVAL OF ENGINE PRIMER (Refer to Figure 9-13).
a. Disconnect the fuel lines from the primer behind the instrument panel.
b. Loosen the locknut (12) from behind the panel.
c. Unscrew the knurled face nut (10), withdraw the pump handle (9) and piston (7)
from the cylinder (5).
d. Remove the remaining portion of the primer.
9-52. DISASSEMBLY, CLENAING, AND ASSEMBLY OF ENGINE PRIMER
(Refer to Figure 9-13).
a. The primer may be disassembledafter removal by removingthe screws(3), springs
(2), and check balls (1) from the end of the cylinder housing.
b. Clean the primer parts with acetone or a dry type solvent.
c. Install new O-rings to the piston (7) and lubricate with light motor oil.
d. Install the balls (1), springs (2), and screws (3) to the cylinder housing.
e. Insert the pump handle (9) and piston (7) into the cylinder (5), finger tighten the
knurled face nut (10).
f. Immerse the pump in gasolineand operate severaltimes to ensure proper operation.

Revised: 1/15/86 3D12 FUEL SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

9-53. INSTALLATION OF ENGINE PRIMER PUMP. (Refer to Figure 9-13.)

a. Remove the pump handle (9) and piston (7) by unscrewing the knurled face
nut (10), if previously installed.
b. Insert the cylinder assembly through the back side of the panel.
c. Insert the piston into the cylinder (5) and tighten the knurled face nut.
d. Position the primer and tighten the locknut (12) on the cylinder behind the
panel.
e. Connect the fuel lines to the primer.
f. Disconnect the primer line inside the engine compartment. Operate the
pump to ascertain proper operation.

9-54. PRIME JETS.

a. To remove the prime jets, disconnect the supply line from each jet. With
a deep socket and light pressure, remove the jet from the cylinder.
b. To clean the jet, soak in a carbon remover solution long enough to loosen
any dirt and blow clean with air pressure. Do not use sharp objects or wire
brush to clean the jet tube.
c. Install the jet finger tight to assure that the threads are not crossed and
then torque 60 inch-pounds. Align and install the fuel supply lines, tighten to a
snug fit.

NOTE

Should further fuel stoppage of the primer system

exist, check the supply lines for stoppage, bent or
collapsed walls.

9-55. CLEANING FUEL SYSTEM.

a. To flush the fuel tanks and selector valve, disconnect the fuel line at the
carburetor or injector.
b. Select a fuel tank, turn on the electric fuel pump and flush fuel through the
system until it is determined there is no dirt and foreign matter inthe fuel valve
or tank. During this operation, agitation of the fuel within the tank will help pick
up and remove any dirt.
c. Repeat this procedure for each tank.
d. When all tanks are flushed, clean all filters.

Reissued: 1/15/81 3D13 FUEL SYSTEM

 3D14
INTENTIONALLY LEFT BLANK
 PIPER CHEROKEE SERVICE MANUAL

TABLE IX-III. FUEL SYSTEM TROUBLESHOOTING

Trouble Cause Remedy

Failure of fuel to flow. Blockage in fuel line. Flush fuel system.

Blockage of cap vent. Check and clean vent

hole in cap.

Failure of mechanical Check and replace if

or electrical fuel pump. necessary.

Failure of fuel selector Check position of

to be in proper position. selector and adjust
if required.

Damage of fuel Replace fuel valve.

selector valve.

Fuel gauge fails to Broken wire. Check and repair.

operate.
Gauge inoperative. Replace.

Float partially or Replace float.

completely filled
with fuel.

Circuit breaker open Check and reset or

or fuse blown. replace.

Incomplete ground. Check ground connec-

tions at fuel trans-
mitter in wings.

Float and arm assem- Check fuel transmitter

bly of fuel transmitter in wings and repair or
in wing sticking. replace.

Reissued: 1/15/81 3D15 FUEL SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

TABLE IX-III. FUEL SYSTEM TROUBLESHOOTING (cont)

Trouble Cause Remedy

Fuel gauge indicates full Complete ground on Check ground connec-

when tanks are not full. transmitter wire. tions at fuel trans-
mitting in wings.

No fuel pressure indica- Fuel valve stuck. Check valve.

tion.
No fuel in tanks. Check fuel level and fill.

Defective fuel pump. Check pump for pres-

sure build up. Check
diaphragm and relief
valves in engine pump.
Check for obstructions
in electric pump. Check
by-pass valve. Air
leak in intake lines.
Air leak in intake Check O-rings for
lines. damage and inlet fitting
Pressure low or for proper installation.
Defective gauge. Replace gauge.
pressure surges.
Failure of fuel Check position of selec-
selector to be in tor and adjust if requir-
proper position. ed.

Obstruction in inlet Trace lines and locate

Unidentified leak. side of pump. obstruction.
Faulty by-pass valve. Replace.
Fuel valve leaks. Faulty diaphragm. Replace or rebuild pump.
Fuel line damaged Locate and repair or
or improperly tighten.
installed.
Worn "O" rings. Replace "O" rings or
valve.

Revised: 1/15/86 3D16 FUEL SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

C351

.219" R

.188"HOLE
3 REQ.
(T.M.M.P.)
I

9.938"

2 WOOD
SCREWS
EVENLY
SPACED

MATERIAL
LIST
2-8.75x9.938x.125 2024-T3 ALUM.
1.8.75x 6 x .75RICH MASONITE
LITE, ORHARDWOOD
MASONITE
LITE,
1.8.75x 6 x 1 RICHLITE ORHARDWOOD
1-1.50 x 6 x .50RICHLITE
CHLITEMASONITEORHARDWOOD
1 2.50x 6.25x .50 .50
RICHLITE,MASONITE
ORHARDWOOD
I 2. 1.625 x 2.50x .125 2024-T3 ALUM.
1252024-T3 ALUM.
26WOOD SCREWS 6 WOOD
SCREWS
EVENLY
SPACED

t i
. "1
Figure 9-14. Fabricated Fuel Quantity Transmitter Checking Jig

Reissud:d:1/15/81
1/15/81 3D17 FUELSYS TEM
 SECTION X
INSTRUMENTS
Paragraph Aerofiche
Grid No.
10-1. General ..................................................... 3D22
10-2. Non-Electrical Instruments .................................... 3D22
10-3. Vacuum System .............................................. 3D22
10-4. Vacuum System Service Tips .......................... 3D22
10-5. Troubleshooting ..................................... 3D24
10-6. Suction Gauge ............................................... 3E21
10-7. General ............................................ 3E21
10-8. Troubleshooting ..................................... 3E21
10-9. Vacuum Regulator Valve ...................................... 3E21
10-10. General ............................................ 3E21
10-11. Troubleshooting ..................... ........... 3E21
10-12. Adjustment of Vacuum Regulator Valve
(Without Vacuum Warning Lights) ................ 3E21
10-13. Adjustment of Vacuum Regulator Valve
(With Vacuum Warning Lights) ................... 3E22
10-14. Adjustment of Vacuum Warning Light Pressure
Switch ........................................ 3E22
10-15. Adjustment of Vacuum Turn and Bank Indicator
Regulator Valve................................. 3E24
10-16. Removal and Replacement of Regulator Valve .......... 3E24
10-17. Vacuum Pump ............................................... 3E24
10-18. General ............................................ 3E24
10-19. Troubleshooting ..................................... 3F1
10-20. Removal of Vacuum Pump ........................... 3F1
10-21. Replacing Pump Fittings ............................. 3F1
10-22. Installation of Vacuum Pump ......................... 3F2
10-23. Instrument Air System ............................... 3F2
10-24. Directional Gyro ............................................. 3F3
10-25. General . .. .................................. 3F3
10-26. Troubleshooting ..................................... 3F5
10-27. Removal and Replacement............................ 3F6
10-28. Gyro Horizon ................................................ 3F6
10-29. General ............................................ 3F6
10-30. Troubleshooting ..................................... 3F7
10-31. Removal and Replacement............................ 3F8

Reissued: 1/15/81 3D18

 Aerofiche
Grid No.
10-32. Rate of Climb Indicator ......... ..................... 3F8
10-33. General ............ ........... ....... 3F8
10-34. Troubleshooting ....... ...................... 3F8
10-35. Removal and Replacement ...................... 3F9
10-36. SensitiveAltimeter ..... ...................... 3F9
10-37. General ............ ...................... 3F9
10-38. Troubleshooting ....... .................... 3F10
10-39. Removal and Replacement .................... . 3F11
..
10-40. Airspeed Indicator ............ .................... . .3F11
10-41. General ...... .................... . .3F11
10-42. Troubleshooting ....... .................... . .3F12
1043. Removaland Replacement .................... . .3F12
10-44. MagneticCompass ........... . .................... . .3F13
10-45. General ............ .................... . .3F13
10-46. Adjustment of Compass . . . .................... . .3F13
10-47. Troubleshooting ....... .................... . .3F14
10-48. ManifoldPressureGauge .... .................... 3F15
10-49. General ............ .................... .. 3F15
10-50. Troubleshooting ....... .................... ..3F15
10-51. Removal and Replacement ..................... 3F15
10-52. Tachometer Indicator . ......... .................... . .3F15
10-53. General ............ .................... . .3F15
10-54. Troubleshooting ....... .................... 3F16
10-55. Removal and Replacement .................... 33F16
10-56.. Engine Oil PressureGauge ....... .................... 3F16
10-57. General ............ ...................... 3F16
10-58. Troubleshooting ....... .................... 3F17
10-59. Removal and Replacement ............. ........ 3F17
10-60. Fuel PressureGauge ........... .................... 3F17
10-61. General ............ ...................... 3F17
10-62. Troubleshooting ....... .................... 3F18
10-63. Removal and Replacement ..................... 3F19
10-64. Turn and Bank Indicator .... ..................... 3F19
10-65. General ............ .................... 3F19
10-66. Troubleshooting ....... .................... 3F19
10-67. Electrical Instruments .......... .................... 3F20
10-68. Removal and Replacement ............ ......... 3F20
10-69. Fuel Quantity Indicator ......... ........... .......... 3F20
10-70. General ............ ..................... 3F20
10-71. Troubleshooting ....... ................. ..... 3F20
10-72. - Removal and Replacement .................... 3F21
10-73. Oil Temperature Indicator ... ...................... 3F21
10-74. General ............ .............. ........ 3F21
10-75. Troubleshooting ...... ................ ...... 3F21
10-76. Removal and Replacement ............... ....... 3F21

Reissued: 1/15/81 3D19

 Aerofiche
Grid No.
10-77. Ammeter ..................................... 3F21
10-78. General ............................... . 3F21
10-79. Troubleshooting ........................... 3F21
10-80. Removal and Replacement ..................... 3F21
10-81. Removal and Replacementof Face Mounted Instruments ........ . 3F21
10-82. General ............................... . 3F22
10-83. Removal and Replacementof Cluster Mounted Instruments ........ 3F22
10-84. General ............................... . 3F22
10-85. Exhaust Gas Temperature Gauge (Alcor) . ........ ..... .... . 3F22
10-86. General .............................. ........... . 3F22
10-87. Cleaningand Inspection ............................ . 3F23
10-88. Troubleshooting .......................... . 3F23
10-89. Cylinder Head Temperature Gauge ..................... . 3G3
10-90. General ................................ 3G3
10-91. Troubleshooting .......................... . 3G3
10-92. Removal and Replacement .................... . 3G3
10-93. Fuel Flow Gauge ................................. 3G3
10-94. General .............................. ........... . 3G3
10-95. Troubleshooting .......................... . 3G4
10-96. Removal and Replacement .................... . 3G4
10-97. Piper AutoControl System .......................... . 3G4
10-98. Annunciator Panel ............. ................... 3G4
10-99. General ................................ 3G4
10-100. Troubleshooting . . . . . . . . . . . . . . . . . . . ........ 3G4
10-101. Removal and Replacement ..................... 3G4

Reissued: 1/15/81 3D20

 3D21
INTENTIONALLYLEFT BLANK
 PIPER CHEROKEE SERVICE MANUAL

SECTIONX
INSTRUMENTS

10-1. GENERAL. The instrumentation in the Cherokee is designed to give a quick and
actual indication of the attitude, performance and condition of the airplane. Maintenance,
other than described in these sections, shall be done by the instrument manufacturer or an
authorized repair station.
The two types of instruments have been classified in this section as non-electrical and
electrical. The first part of this section will pertain to maintenance and troubleshooting of
all the instruments and their systems which depend on non-electrical sources for their
operation. The remaining portion of this section is directed to maintenance and
troubleshooting of all the electrically operated instruments.

10-2. NON-ELECTRICALINSTRUMENTS.

10-3. VACUUMSYSTEM.

10-4. VACUUM SYSTEM SERVICE TIPS. The following information is intended to

acquaint field service personnel with a means to diagnosevacuum system servicesymptoms
on those components which are serviced by removal and replacement. These items include
hoses, clamps, gyro filters, vacuum regulatingvalvesand vacuum gauges.
a. Hoses and Clamps:
1. These items should be examined periodically and inspected carefully whenever
engine maintenance activities cause hose disconnections to be made at the pump, regulating
valve, gyros and/or vacuum gauge.
2. The ends of the hoses should be examined for rubber separation and slivers of
rubber on the inside diameter of the hoses. These slivers can and do become detached. If
this happens, the vacuum pump suck these loose particles and eventually ingest them. This
can cause premature pump service.
3. Hose clamps and fittings should be replaced when broken, damaged or corroded.

CAUTION
When replacing any of the threaded fittings, DO NOT USE
PIPE DOPE or any other anti-seize tape or compound. The
AIRBORNE fittings are all cadmium plated to avoid the need
for any other anti-seizematerials. The reason for this caution
is to protect the pump from ingesting any foreign materials
that could cause premature service.

Reissued: 1/15/81 3D22 INSTRUMENTS

 PIPER CHEROKEE SERVICE MANUAL

b. Vacuum Gauges:
1. Vacuum gauges seldom require service and usually are replaced when
malfunctions occur.
NOTE
Vacuum gauge failure in a properly operating vacuum system
does not impair safety of flight.
2. If the vacuum gaugemalfunctions in a manner to cause an incorrect reading in
normal cruise conditions, the gaugemust be checked by comparing the reading with a gauge
of known accuracy. If the gauge is indicating correct values and the system vacuum level is
not in accordance with the specifiedvacuum, then and only then should the regulator be
reset.
3. Visual examination of the gaugeperformance should cover the followingsteps:
(a) With engine stopped and no vacuum applied to the gauge, its pointer should
rest against the internal stop in the 9 o'clock position. Any other
displacement from this position suggestsneed for replacement.
(b) A slight overshoot during engine startup, not to exceed half an inch (1/2")
of mercury, is normal and is not causeto replace gauge.
(c) With engine operating at normal cruiseRPM, the gaugeshould read from 4.9
inches to 5.1 inches of mercury (vacuum).
(d) At 1200 RPM, the vacuum gaugereading should be more than four inches of
mercury.
c. Gyro Filters:
1. Gyro filters must be servicedon a scheduled basis, not to exceed 100 hours, or
sooner as condition indicates.
NOTE
Several gyro filter systemshave been used on various aircraft,
depending on when the aircraft was built.
2. The oldest aircraft installations generally did not have central filters. They
depended on the small cloth or paper disc-typefilters built into the instruments themselves.
This type of filter requires frequent replacement for proper gyro operation.
3. The later system installation employed a large central filter which eliminatedthe
frequent replacement of the small internal filters in the gyros.
4. The latest system installation employs a large central filter and differential
vacuum gauge that continuously monitors the filter condition while indicating vacuum
readings.
NOTE
In the aircraft systems described in items (2) and (3) above,
failure to replace filters would cause a slight increase in
vacuum gauge readings. The AIRBORNE regulator will
automatically adjust to the flow changes that result when
dirty filters are allowed to remain in the system.

Reissued: 1/15/81 3D23 INSTRUMENTS

 PIPER CHEROKEE SERVICE MANUAL

NOTE

The latest systems which employ a central filter in

combination with a differential vacuum gauge will indicate a
decline in panel gauge reading when the filter becomes
clogged and vacuum declines below the recommended value.
The filters should be replaced when gauge reading declines
below the recommended value; do not adjust regulator.
d. Vacuum Regulator:
1. The vacuum regulatingvalve seldom needs replacement. Symptoms that suggest
replacement are:
(a) Chatter as indicated by rapid fluctuation of the vacuum gauge needle or an
audible sound.
(b) Non-repeatability of the vacuum gauge reading when the panel gauge is not
suspect or has been checked against a known test gauge (cruise RPM only).
2. All modes of regulator malfunction tend to increase the vacuum power applied
to the gyros. Thus, although excess vacuum is applied, a loss of vacuum does not occur.
3. The gyros themselves act as a limiting device to keep the vacuum power applied
from exceeding safe levels.
NOTE

If the panel gauge has been checked and found OK and the
vacuum gaugereading does not repeat within the range of 4.8
to 5.2 inches of mercury, then the regulating valveshould be
changed. Observe the usual precautions for maintaining
system cleanlinessto avoid premature pump service.

10-5. TROUBLESHOOTING.
TABLEX-I. VACUUMSYSTEM

NOTE

Aircraft Serial Numbers prior to: 28-7125001, 28-7105001,

28-7110001, 28S-7105001, 28R-7130001 and 28R-7135001.

Trouble Cause. Remedy

No vacuum pressure Pump inoperative. Dis- Replace pump. Locate

gauge indication. connected, broken or trouble and correct.
restricted lines

Reissued: 1/15/81 3D24 INSTRUMENTS

 PIPER CHEROKEE SERVICE MANUAL

TABLEX-I. VACUUMSYSTEM(cont)

Trouble Cause Remedy

No vacuum gaugeindica- Hose from instrument to Check all lines and

tion at instrument. gauge leaking or re- connections.
stricted.

No vacuum gauge indica- Faulty gauge.Mal- Check operation of

tion at either instru- functioning, regulator instrument. If oper-
ment or source. valve,or vacuum pump. ation is normal, re-
place gauge.If instru-
ments are inoperative,
check operation of
vacuum pump or regulator
valve.

Vacuumlines restricted Check system.

or broken.

Low vacuum system Vacuum regulator valve Adjust regulator valves

pressure. incorrectly adjusted. in accordance with
Adjustments of this
section.

Leakingof the system Checkall lines and

lines or fittings. fittings.

Malfunctioningpump. Replace pump.

Overboardline from Replace line.

vacuum pump restricted.
Sealingplugs loose in
gyros.

Normal pressure indica- Instruments air filter Remove and clean or

tion, but sluggish elements dirty. replace.
operation of instru-
ments.

Line restricted be- Check all lines and

tween gyro and filter. fittings.

Reissued: 1/15/81 3E INSTRUMENTS

 PIPER CHEROKEE SERVICE MANUAL

TABLEX-I. VACUUMSYSTEM(cont)

Trouble Cause Remedy

High system pressure. Vacuum regulator valve Adjust in accordance

incorrectly adjusted. with Adjustments of
this section.

Vacuum regulator valve Clean and check opera-

sticking or dirty tion of regulator
screen. valve.

Faulty gauge. Replace gauge.

Aircraft Serial Numbers: 28-7125001,28-7105001,28-7110001,28S-7105001,
28R-7130001,28R-7135001and above.

No acuum gaugeindica- Filter cloggedor I Clean or replace filter.

tion at instrument. dirty.

Line from gyro to Check line.

filter restricted.

No vacuum gauge indica- Faulty gaugemal- Replace gauge.

tion at instrument or functioning pump. Replace pump.
source.

Low vacuum system Filter dirty. Clean or replace filter.

pressure.

Vacuum regulator valve Adjust regulator valve

incorrectly adjusted. in accordance with
Adjustments in this
section.

Line from gyros to Repair line.

filter restricted.

Line from pump to gyros Check all lines and

leaking. fittings.

Normal pressure indica- Faulty instrument. Replace instrument.

but sluggishoperation
of instruments.

INSTRUMENTS
Reissued: 1/15/81 3E2
 PIPER CHEROKEE SERVICE MANUAL

TABLEX-I. VACUUMSYSTEM(cont)

Trouble Cause Remedy

High system pressure. Vacuumregulator in- Adjust regulator.

correctly adjusted.

Vacuum regulator Clean and check opera-

sticking or dirty tion of regulator.
screen.

Regulator cannot be Linesleaking. Check lines and fittings.

adjusted to produce
correct pressure.
Vacuum pump mal- Replace pump.
functioning.

Vacuum correct on Vacuumpump mal- Replace pump.

ground but will not functioning.
maintain pressure at
altitude.
Regulator sticky. Clean regulator.

Vacuum correct but Regulator sticky. Clean regulator.

pilot reports pressure
erratic or shows
complete loss in
flight.
Oil in pump due to Replace pump.
leaky engine seal
or cleaningfluid
blown into pump
while cleaningengine.

Pressure can only be Leak in system. Repair or replace

maintained at full lines.
throttle on ground.

Worn pump. Replace pump.

Stuck regulator. Clean or replace

regulator.

Reissued: 1/15/81 3E3 INSTRUMENTS

 PIPERCHEROKEESERVICEMANUAL

POH

1. STALL WARNING INDICATOR 19. PHONE JACKS

2. CLOCK 20. AUTOCONTROL III AUTOPILOT
3. TURN INDICATOR 21. OMNI COUPLER
4. AIRSPEED INDICATOR 22. PITCH CONTROL
5. DIRECTIONAL GYRO 23. MAGNETO SWITCHES & STARTER
6. ATTITUDE GYRO 24. INSTRUMENT CLUSTER
7. PLACARD 25. RPM CRUISE CHART
8. VERTICAL SPEED INDICATOR 26. CHECK LISTS
9. ALTIMETER 27. TACHOMETER
10. PLACARD 28. ENGINE PRIMER
11. MARKER BEACON LIGHTS 29. THROTTLE QUADRANT
12. OMNI AND GLIDE SLOPE INDICATORS 30. THROTTLE QUADRANT FRICTION LOCK
13. TRANSMITTER SELECTOR SWITCH 31. CARBURETOR HEAT CONTROL
14. VHF TRANSCEIVERS 32. AMMETER
IS. ADF RECEIVER 33. SWITCH PANEL
16. DME RECEIVER 34. CIRCUIT BREAKER PANEL
17. SUCTION GAUGE 35. HEAT AND DEFROST CONTROLS
18. CIGAR LIGHTER

Figure 10-1. Instrument Panel, PA-28-140, Serial

Nos. 28-25000 to 28-26956 incl.

Reissued: 1/15/81 3E4 INSTRUMENTS

-
 PIPER CHEROKEE SERVICE MANUAL

5 6 7 8
L

12 11 9

1. COMPASS 8. VACUUM GAUGE

2. AIRSPEED INDICATOR 9. INSTRUMENT CLUSTER
3. DIRECTIONAL GYRO INDICATOR 10. TURN AND BANK INDICATOR
. GYRO HORIZON INDICATOR 11. CLOCK
5. AUTONAV RADIO 12. STALL WARNING LIGHT
6. SUPERHOMER RADIO 13. ALTIMETER INDICATOR
7. TACHOMETER 14. RATE OF CLIMB INDICATOR

3 4 5 6 7 8

14 13 12 11 10

Figure 10-4. Instrument Panel

Reissued:1/15/81 3E7 INSTRUMENTS

 PIPER CHEROKEE SERVICE MANUAL

18 17 16 15 14 13 12 11 10

1. COMPASS 7. ADF RECEIVER AND INDICATOR 13. AUTOCONTROL II AUTOPILOT

2. AIRSPEED INDICATOR 8. TACHOMETER 14. STALL WARNING LIGHT
3. DIRECTIONAL GYRO 9. VACUUM INDICATOR 15. TURN AND BANK INDICATOR
4. GYRO HORIZON 10. COMMUNICATIONS AND NAVIGATION TRANSCEIVERS 16. ALTIMETER
5. MARKER BEACON RECEIVER CONTROL 11. ENGINE AND FUEL SYSTEM INSTRUMENT CLUSTER 17. VERTICAL SPEED INDICATOR
6. OMNI AND GLIDE SLOPE INDICATORS 12. OME CONTROL AND INDICATOR 18. CLOCK

Figure 10-5. Instrument Panel, PA-28-150, -160, -180

Serial Nos. 28-1761 to 28-4377 incl.

Reissued: 1/15/8J 3E8 INSTRUMENTS

 PIPER CHEROKEESERVICEMANUAL

C353

1. STALL WARNING LIGHT 12. OMNI AND GLIDE SLOPE INDICATORS 23. FUEL SYSTEM CLUSTER
2. CLOCK 13. TRANSMITTER SELECTOR SWITCH 24. TAKE-OFF AND LANDING CHECK LIST
3. TURN AND BANK INDICATOR 14. COMMUNICATIONS AND NAVIGATION TRANSCEIVERS 25. TACHOMETER
4. AIRSPEED INDICATOR 15. ADF RECEIVER AND INDICATOR 26. ENGINE PRIMER
5. DIRECTIONAL GYRO 16. DME CONTROL AND INDICATOR 27. THROTTLE QUADRANT
6. ATTITUDE GYRO 17. CIGAR LIGHTER 28. THROTTLE QUADRANT FRICTION KNOB
7. HI-LO VACUUM WARNING LIGHT 18. HEAT AND DEFROST CONTROLS 29. CARBURETOR HEAT CONTROL
8. VERTICAL SPEED INDICATOR 19. AUTOCONTROL III AUTOPILOT 30. EXHAUST GAS TEMPERATURE GAUGE
9. ALTIMETER 20. ENGINE INSTRUMENT CLUSTER 31. SWITCH PANEL
10. PLACARD 21. OMNI-COUPLER 32. CIRCUIT BREAKER PANEL
11. MARKER BEACON RECEIVER CONTROL 22. MAGNETO SWITCHES AND STARTER

Figure 10-6. InstrumentPanel, PA-28-180,

SerialNos. 284378 to 28-7205328 incl.

Reissued: 1/15/81 3E9 INSTRUMENTS

i
 PIPER CHEROKEESERVICEMANUAL

976

1. CLOCK 17. SUCTION GAUGE

2. COMPASS 18. RADIO
3. ALTIMETER 19. MIXTURE CONTROL
4. AIRSPEED 20. AUTOFLITE
5. TURN AND BANK INDICATOR 21. PROPELLER CONTROL
6. DIRECTIONAL GYRO INDICATOR 22. THROTTLE CONTROL
7. STALL WARNING LIGHT 23. AUDIO SELECTOR
8. GYRO HORIZON INDICATOR 24._CARBURETOR HEAT
9. OMNI INDICATOR 25. ROTATING BEACON
10. MARKER BEACON 26. LANDING LIGHT
11. RADIO ADF 27. NAV AND INST. LIGHTS
12. RADIO 28. FUEL PUMP
13. DISTANCE/SPEED INDICATOR 29. VERTICAL SPEED
14. MANIFOLD PRESSURE 30. STARTER
15. INSTRUMENT CLUSTER 31. MASTER SWITCH
16. TACHOMETER 32. PRIMER

- WHEN CONSTANT SPEED PROPELLER IS INSTALLED.

Figure 10-9. Instrument Panel, PA-28-235, Serial Nos. 28-10720 to 28-11039 incl.

Reissued: 1/15/81 3E12 INSTRUMENTS

INSTRUMENTS
 PIPER CHEROKEESERVICEMANUAL

1825

1. STALL WARNING LIGHT 23. MANIFOLD PRESSURE INDICATOR

2. CLOCK 24. TAKE-OFF AND LANDING CHECK LISTS
3. TURN AND BANK INDICATOR 25. TACHOMETER
4. AIRSPEED INDICATOR 26. ENGINE PRIMER
5. DIRECTIONAL GYRO 27. THROTTLE QUADRANT
6. GYRO HORIZON 28. THROTTLE QUADRANT FRICTION KNOB
7. VERTICAL SPEED INDICATOR 29. CARBURETOR HEAT CONTROL
8. ALTIMETER 30. EXHAUST GAS TEMPERATURE GAUGE
9. MARKER BEACON RECEIVER CONTROL 31. SWITCH PANEL
10. OMNI AND GLIDE SLOPE INDICATORS 32. CIRCUIT BREAKER PANEL
II. TRANSMITTER SELECTOR SWITCH
12. COMMUNICATIONS AND NAVIGATION TRANSCEIVERS
13. ADF RECEIVER AND INDICATOR
14. DME CONTROL AND INDICATOR
15. CIGAR LIGHTER
16. VACUUM INDICATOR
17. HEAT AND DEFROST CONTROLS
18. AUTOCONTROL III AUTOPILOT
19. ENGINE INSTRUMENT CLUSTER
20. OMNI-COUPLER
21. MAGNETO SWITCHES AND STARTER
22. FUEL SYSTEM CLUSTER

-WHEN CONSTANT SPEED PROPELLER IS INSTALLED.

Figure 10-10. Instrument Panel, PA-28-235

Serial Nos. 28-11040 to 28-7210033 incl.

Reissued: 1/15/81 3E13 INSTRUMENTS

 ZZ

__
.
 PIPER CHEROKEESERVICEMANUAL

1831

1. STALL WARNING LIGHT 23. FUEL SYSTEM CLUSTER

2. CLOCK 24. MANIFOLD PRESSURE - FUEL FLOW INDICATOR
3. TURN AND BANK INDICATOR 25. TACHOMETER
4. AIRSPEED INDICATOR 26. LANDING GEAR CONTROL HANDLE
5. DIRECTIONAL GYRO 27. LANDING GEAR INDICATOR LIGHTS
6. ATTITUDE GYRO 28. THROTTLE QUADRANT
7. HI-LO VACUUM WARNING LIGHT 29. ALTERNATE AIR CONTROL
8. VERTICAL SPEED INDICATOR - 30. MIXTURE MONITOR
9. ALTIMETER 31. SWITCH PANEL
10. GEAR UP WARNING LIGHT 32. CIRCUIT BREAKER PANEL
11. GEAR IN TRANSIT LIGHT
12. MARKER BEACON RECEIVER CONTROL
13. OMNI AND GLIDE SLOPE INDICATORS
14. COMMUNICATIONS AND NAVIGATION TRANSCEIVERS
15. ADF RECEIVER AND INDICATOR
16. DME CONTROL AND INDICATOR
17. CIGAR LIGHTER
18. HEAT AND DEFROST CONTROLS
19. AUTOCONTROL III AUTOPILOT
20. ENGINE INSTRUMENT CLUSTER
21. OMNI-COUPLER
22. MAGNETO SWITCHES AND STARTER

Figure 10-13. Instrument Panel

PA-28R-180, Serial Nos. 28-30005 to 28-30879 incl.

INSTRUMENTS
Reissued: 1/15/81 3E16
 PIPERCHEROKEESERVICEMANUAL

1831

1. STALL WARNING LIGHT 12. OMNI AND GLIDE SLOPE INDICATORS 23. FUEL SYSTEM CLUSTER
2. CLOCK 13. COMMUNICATIONSAND NAVIGATION TRANSCEIVERS 24. MANIFOLD PRESSURE- FUEL FLOW INDICATOR
3. TURN AND BANK INDICATOR 14. ADF RECEIVER AND INDICATOR 25. TACHOMETER
4. AIRSPEED INDICATOR 15. DME CONTROLAND INDICATOR 26. LANDING GEAR CONTROLHANDLE
5. DIRECTIONAL GYRO 16. SUCTION GAUGE 27. LANDING GEAR INDICATOR LIGHTS
6. ATTITUDE GYRO 17. CIGAR LIGHTER 28. THROTTLE QUADRANT
7. VERTICAL SPEED INDICATOR 18. HEAT AND DEFROST CONTROLS 29. ALTERNATE AIR CONTROL
8. ALTIMETER 19. AUTOCONTROLIII AUTOPILOT 30. MIXTURE MONITOR
9. GEAR UP WARNINGLIGHT 20. ENGINE INSTRUMENT CLUSTER 31. SWITCH PANEL
10. GEAR IN TRANSIT LIGHT 21. OMNI-COUPLER 32. CIRCUIT BREAKER PANEL
11.MARKER BEACON RECEIVER CONTROL 22. MAGNETO SWITCHES AND STARTER 33. GEAR OVERRIDE WARNING LIGHT

Figure 10-14. Instrument Panel

PA-28R-180SerialNos. 28-30880 to 28-7130019 incl.
PA-28R-200 SerialNos. 28-30482, 28-35001 to 28-35830 incl.
and 28-7135001 to 28-7135238 incl.
INSTRUMENTS
Reissued: 1/15/81 3E17
 0

.
 3E20
INTENTIONALLY LEFT BLANK
 PIPER CHEROKEE SERVICE MANUAL

10-6. SUCTIONGAUGE.

10-7. GENERAL. The suction gauge is mounted in the right side of the instrument panel
above the glove compartment. This gauge is calibrated in inches of mercury and indicates
the amount of vacuum created by the engine driven vacuum pump. The suction gauge
installed in "71" models have a direct pressure line and a vent line. Therefore, these aircraft
indicate the differential pressure or actual pressure being applied to the gyro instruments. As
the system filter becomes clogged or lines obstructed, the gauge will show a decrease in
pressure. Do not reset the regulator until the filter and lines have been checked.

10-8. TROUBLESHOOTING.For troubleshooting of this instrument, refer to Table X-I of

this section.

10-9. VACUUMREGULATORVALVE.

10-10. GENERAL. One vacuum regulator valve is incorporated in the system to control
vacuum pressure to the gyro instruments. The regulator valve is located under the
instrument panel. Access to the valve for maintenance and adjustment is gained from below
the instrument panel.

10-11. TROUBLESHOOTING.For troubleshooting of the vacuum regulator refer to Table

X-I.

10-12. ADJUSTMENTSOF VACUUMREGULATORVALVE. (Without VacuumWarning

Lights)
a. Loosen the locking nut or remove the protective cap from the valve, depending on
which type is installed.

NOTE
Do not attempt adjustment of this valve with the engine in
operation, without a qualified pilot or other responsible
person at the controls.

b. Start the engine, after allowingtime for warm-up, run the engine at medium RPM.
c. With the engine running at medium RPM, the suction gauge should indicate 5.0
inches of mercury ± .1 inches of mercury. If the pressure reading fails to fall within this
range, shut down the engine and adjust the regulator valve by moving the valveadjustment
screw clockwise to increase the pressure, and counter-clockwise to decrease the pressure.
Start the engine and repeat the check. With engine running at medium RPM, the suction
gauge should indicate 5.0 inches of mercury ± .1 inches of mercury. If the airplane is not
equipped with a suction gauge, it will be necessaryto connect a gauge by removingthe plug
from the back of the artificial horizon, and attaching a temporary gauge.
d. Restart the engineand repeat the check.

Reissued: 1/15/81 INSTRUMENTS

3E21
 PIPER CHEROKEE SERVICE MANUAL

e. After the system pressure has been adjusted to these recommended settings,
remove the gauge and install the plug, replace the protective cap or retighten the locknut,
whicheverapplies to the type of valveinstalled.
10-13. ADJUSTMENT OF VACUUM REGULATOR VALVE (PA-28-180, Serial Nos.
28-4378 to 28-5227; PA-28R-180, Serial Nos. 28R-30005 to 28R-30878) (With Vacuum
WarningLights).
a. Remove the plug from the back of the artificial horizon and install an appropriate
AN fitting that will accommodate a small hose from a suction gauge.
b. Locate the valve adjustment screw on the bottom of the regulator and loosen the
regulator screwjam nut.
NOTE
Do not attempt adjustment of this valve with the engine
in operation, without a qualified pilot or other
responsibleperson at the controls.
c. Start the engine, allow time for warm-up, and operate at a medium RPM.
d. With the engine operating at medium RPM,the suction gaugeshould indicate 5.0
± .1 inches of mercury. If pressure reading fails to fall within this range, shut-down the
engine and adjust the regulator valve by movingthe adjustment screw clockwiseto increase
the pressure and counterclockwiseto decrease the pressure.
e. Restart the engine and repeat the check.
f. After the system pressure has been adjusted to this recommended setting,
retighten the regulator screw jam nut, remove the suction gauge, hose and fitting. Replace
the plug into the back of the artificial horizon.
10-14. ADJUSTMENT OF VACUUM WARNING LIGHT PRESSURE SWITCH
(PA-28-180, Serial Nos. 28-4378 to 28-5227; PA-28R-180, Serial Nos. 28R-30005 to
28R-30878). The vacuum warning light switch should allow the low vacuum light to
actuate when the suction has decreased to or below 4.25 ± .2 inches of mercury, and the
high vacuum light with suction in excess of 5.2 + .2 -.0 inches of mercury. To check and
adjust the operation of the vacuum warning switch, the following procedure may be used:
a. Remove the plug from the back of the artificial horizon and install an appropriate
AN fitting that will accommodate a small hose from-a suction gauge.
b. Start the engine, allow time for warm-up and operate at a medium RPM.
NOTE
Do not attempt adjustment of any system in this
airplane with the engine in operation, without a
qualified pilot or other responsible person at the
controls.
c. Reduce RPM until low vacuum is indicated by the light, and determine if the
switch has actuated the light at 4.25 .2. Adjust by the followingprocedure:

Reissued: 1/15/81 3E22 INSTRUMENTS

 PIPER CHEROKEE SERVICE MANUAL

976 LOW ADJUSTMENT

CLOCKWISE- INCREASES
LOWSETTING
BLACK

WHITE

YELLOW
HIGH ADJUSTMENT
CLOCKWISE - DECREASES
HIGH SETTING

Figure 10-17. Warning Light Pressure Switch

1. Increase RPM to a high setting, then decrease to 4.25 inches of mercury.
2. Adjust switch to activate the low vacuum light at this setting by locating the
vacuum switch in the back of the directional gyro. Directly in the center of the switch is a
small adjustment screw which by turning clockwisewill increase the low setting and turning
counterclockwise will decrease the low setting. (Refer to Figure 10-17.)
3. After making adjustment, recheck the vacuum switch by increasing to a high
RPM and again decreasing to a setting of 4.25. If the light does not actuate at 4.25 ± .2
inches of mercury, repeat steps 2 and 3. After proper adjustments have been made, shut
down the engine.
d. To adjust the high vacuum light, locate the valve adjustment screw on the bottom of
the regulator and loosen the regulator jam nut.
e. Start the engine and set the throttle at 1400 to 1600 RPM. Whilereading the suction
gauge, turn valve adjustment screw of the vacuum regulator clockwise to increase the
suction. At 5.2 + .2 -.0 the high vacuum light, if adjusted properly, should light. If
adjustment is proper, proceed to step g.
f. With high vacuum light not operating correctly, shut down engine and adjust by the
followingprocedure:
1. Adjustment of the high vacuum light necessitates the removal of the vacuum
warning light pressure switch. This switch, which is located in the back of the directional
gyro, has three wires that have to be disconnected and then the switch will turn from the
instrument. The adjustment screw for the switch is found inside the neck of the 1/8 NPT
fitting that threads into the directional gyro. Turning this adjustment screw clockwise will
decrease the high setting and counterclockwisewill increase the high setting.
2. After making the necessary adjustments, reinstall the vacuum switch into the
instrument and replace the wires in accordance with the Electrical System Schematic as
found in Section XI.

INSTRUMENTS
Reissued: 1/15/81 3E23
 PIPER CHEROKEE SERVICE MANUAL

3. Recheck the high vacuum light by restarting the engine and increasing the
RPM. Determine if the high light indicates high vacuum at 5.2 +.2 - 0. If further adjustment
is necessary, return to step f. After proper adjustment to the high vacuum light has been
made, shut down the engine.
g. Readjust the vacuum regulator by setting throttle at a medium RPM. At this setting
the suction gauge should read from 4.6 to 5.2. To prevent intermittent actuation of the
warning light due to closeness of the pressure settings of the light pressure switch and the
vacuum regulator, it should be determined that the regulator is set 0.2 inches of mercury
less than that of the pressure switch as long as vacuum is within the required range. Make
necessary adjustments by turning clockwiseto increase the suction and counterclockwise to
decrease the suction. Then tighten the jam nut on the regulator valve adjustment screw and
remove the vacuum gauge and fitting from the back of the artificial horizon. Reinstall the
plug into the artificial horizon.
10-15. ADJUSTMENT OF VACUUM TURN AND BANK INDICATOR REGULATOR
VALVE.
a. To adjust the turn and bank indicator, remove the plug found in the back of the
instrument and install the proper AN fitting that will accommodate a small hose from a
suction gauge.
NOTE
Do not attempt adjustment of any system in this airplane,
with the engine in operation, without a qualified pilot or
other responsibleperson at the controls.
b. Start the engine and operate at a medium RPM with the suction gaugeindicating 5.0
with central air filter. If adjustment is necessary, refer to Paragraph 10-12 or 10-13.
c. With the suction gauge reading within the stated range, the gauge attached to the
turn and bank should indicate 2.0 inches of mercury. If adjustment is necessary,turning the
adjustment screw, found in the valveassemblyat the back of the instrument, clockwisewill
decrease the suction and counterclockwise will increase the suction. After the proper
reading is acquired, shut down the engine, remove the gauge,hose and fitting from the turn
and bank and install the plug.
10-16. REMOVALAND REPLACEMENTOF REGULATORVALVE.
a. To remove the regulator valve, disconnect the three lines and remove the mounting
nut. Remove the valve from the airplane.
b. Replace regulator in reverse order given for removal. Check complete vacuum system
for proper operation.

10-17. VACUUMPUMP.
10-18. GENERAL. The vacuum pump is of the rotary vane, positive displacement type. This
unit consists essentiallyof an aluminum housing containing a tempered sleevein which an off-
set rotor, with moving blades is incorporated. This assembly is driven by means of a coupling
mated to the engine driven gear assembly. The pump is mounted on the accessory section of
the engine.

Reissued: 1/15/81 INSTRUMENTS

3E24
 PIPER CHEROKEE SERVICE MANUAL

10-19. TROUBLESHOOTING.For troubleshooting of the pumps, refer to Table X-I of

this section.

10-20. REMOVALOF VACUUMPUMP.

a. Remove the top portion of the engine cowling. (Refer to Section VIII.)
b. Loosen the hose clamp and remove the hose from the pump fitting.
c. Remove the four retaining nuts, lock washers and plain washers used to secure the
pump to the engine; then remove the pump.

10-21. REPLACINGPUMPFITTINGS.
a. Before installing any fittings on the pump, check for any external damage. A pump
that has been damaged or dropped should not be installed.
b. When a vise is used to hold the pump while installingfittings, suitable caution must
be exercised to avoid pump damage. The square mounting flangemust be held between soft
wood blocks and only at right anglesto the visejaws. Use only enough vise pressure to hold
the pump firmly.
CAUTION
DO NOT apply vise pressure to the outside diameter or
overall length of the pump.
c. The ports of the AIRBORNE pump have been treated with a dry film lubricant and
the AIRBORNEfittings are cadmiumplated thus eliminatingany need for thread lubricants.
If thread lubricant is required, use a powdered moly-sulfideor graphite in dry form or in an
evaporating vehicle; or employ a silicone spray. Apply sparingly to external threads of
fittings only.
CAUTION

DO NOT use pipe tape, thread dope, hydrocarbon oil or

grease, as these can contaminate the pump and cause
malfunction.
d. With the pump properly secured in the vise, insert fittings in ports and hand tighten
firmly.
e. Usinga wrench, tighten each fitting from one-half to two additional turns.

Reissued: 1/15/81 3F1 INSTRUMENTS

 PIPER CHEROKEE SERVICE MANUAL

10-22. INSTALLATION OF VACUUM PUMP.

a. Place the pump gasket in its proper place and align the spline on the pump drive
with the spline on the engine drive assembly.
CAUTION

The only pump mounting gasket authorized and approved for

use on the Airborne vacuum pump is the Airborne gasket
B3-1-2, Piper part number 751 859. Use of any other gasket
may result in oil seepage or leakage at the mounting surface.
b. Secure the pump to the engine with four plain washers, lock washers and retaining
nuts. Torque the nuts 40 to 50 inch-pounds.
c. Connect the hoses to the pump and secure with hose clamps.
d. Reinstall the engine cowling.

10-23. INSTRUMENT AIR SYSTEM. (Refer to Figure 10-18.)The instrument air system
consists of a pitot air system and a static air system. The system supplies both pitot and static
pressure for the airspeed indicator, altimeter and vertical speed indicator. Refer to Figure 10-
18 for PA-28-140, -150, -160, -180 -235, PA-28R-180 and -200 system layout.
Pitot air system consists of a pitot mast located on the underside of the left wing, with
its related plumbing. Impact air pressure entering the pitot is transmitted from the pitot
inlet through hose and tubing routed in the wing to the airspeed indicator on the instrument
panel. A partially or completely blocked pitot head will giveerratic or zero readings on the
instruments.
Static air system consists of a static port located on the bottom of the pitot mast. The
static port is directly connected to the airspeed indicator, altimeter and rate of climb
indicator on the instrument panel by means of hose and tubing routed through the wing
along with the pitot line. An alternate static air source is located below the instrument panel
in front of the pilot. The alternate static source is part of the standard system and has a
shutoff valve which closes the port when it is not needed. A placard givinginstructions for
use is located on the instrument panel.

Reissued: 1/15/81 3F2 INSTRUMENTS

 PIPER CHEROKEE SERVICE MANUAL

10-24. DIRECTIONALGYRO.

10-25. GENERAL. The directional gyro is a flight instrument incorporating an air driven
gyro stabilized in the vertical plane. The gyro is rotated at high speed by lowering the
pressure in the air tight case and simultaneously allowing atmospheric air pressure to enter
the instrument against the gyro buckets. Due to gyroscopic inertia, the spin axis continues
to point in the same direction even though the aircraft yaws to the right or left. This relative
motion between the gyro and the instrument case is shown on the instrument dial which is
similar to a compass card. The dial, when set to agree with the airplane magnetic compass,
provides a positive indication free from swing and turning error. However, the directional
gyro has no sense of direction and must be set to the magnetic compass, since the magnetic
compass is subject to errors due to magnetic fields, electric instruments, etc. The directional
gyro is only accurate for the heading it has been set for. If the gyro is set on 270° , for
instance, and the aircraft is turned to some other heading, there can be a large error between
the gyro and the magnetic compass due to the error in compass compensation. This will
appear as gyro precession. The gyro should only be checked to the heading on which it was
first set. Due to internal friction, spin axis error, air turbulence and airflow, the gyro should
be set at least every 15 minutes for accurate operation, whether it has drifted or not.

INSTRUMENTS
Reissued: 1/15/81 3F3
 PIPER CHEROKEESERVICEMANUAL

C358

1. ALTIMETER INDICATOR
2. AIRSPEED INDICATOR
3. PITOT HEAT SWITCH
4. VERTICAL SPEED INDICATOR
5. PITOT HEAD

Figure 10-18.Typical Pitot Static System

(PA-28-140,-150, -160, -180, -235, PA-28R-180 and 200)

Reissued: 1/15/81 3F4 INSTRUMENTS

 PIPER CHEROKEE SERVICE MANUAL

10-26. TROUBLESHOOTING.

TABLEX-II. DIRECTIONALGYRO INDICATOR

Trouble Cause Remedy

Excess drift in either Setting error. Paragraph 10-25.

direction.

Defectiveinstrument. Replace instrument.

High or low vacuum.

If vacuum is not
correct, check for the
following:
a. Relief valveim-
properly adjusted. a. Adjust.
b. Incorrect gauge
reading. b. Replacegauge.
c. Pump failure. c. Repair or replace.
d. Vacuum line kinked d. Checkand repair.
or leaking. Checkfor collapsed
inner wall of hose.

Dial spins during turn. Limits (55 ° bank) of Recage gyro in level
gimbal exceeded. flight.

Dial spins continuously. Defectivemechanism. Replace.

Reissued: 1/15/81 3F5 INSTRUMENTS

 PIPER CHEROKEE SERVICE MANUAL

10-27.REMOVAL AND REPLACEMENT. The following procedure pertains to aircraft

having the Edo-Aire Air Driven Gyro installation. For installations other than Edo-Airerefer
to Paragraph 10-81of this section.
NOTE
Permit no oil, grease, pipe compound or any foreign material
to enter parts prior to installation of fittings. Make sure that all
air lines are clean and free of foreign particles and/or residue
before connecting lines to gyro. Do not use thread lube on
fittings or in parts.
The use of teflon tape on fitting threads is recommendedand should be installed as follows:
a. Lay teflon tape on threads keepingone thread visiblefrom the end of the fitting. Hold in
place and wrap in the direction of the threads.
b. Apply sufficienttension whilewinding to assure that tape conforms to thread grooves.
One full wrap plus 1/2" overlap is sufficient.
c. After completing wrap, maintain tension and tear tape by pulling in direction of wrap.
Do not cut tape.
d. Press tape well into threads.
e. Screw fitting into part being careful not to exceed touque requirementsnoted on decal
on the cover of the gyro. (Referto Table,II-II .ConsumableMaterials,for specifications
and Manufacturer's address.)

10-28. GYRO HORIZON.

10-29. GENERAL. The gyro horizon is essentially an air driven gyroscope rotating in a
horizontal plane and is operated by the same principal as the directional gyro. Due to the
gyroscopic inertia, the spin axis continues to point in the vertical direction, providing a
constant visual reference to the attitude of the airplane relative to pitch and roll axis. A bar
across the face of the indicator represents the horizon and aligningthe miniature airplane to
the horizon bar simulates the alignment of the airplaneto the actual horizon. Any deviation
simulates the deviation of the airplane from the true horizon. The gyro horizon is marked
for different degreesof bank.

Reissued: 1/15/81 3F6 INSTRUMENTS

 PIPER CHEROKEE SERVICE MANUAL

10-30. TROUBLESHOOTING.

TABLEX-III. GYRO HORIZONINDICATOR

Trouble Cause Remedy

Bar fails to respond. Insufficient vacuum. Check pump and tubing.

Filter dirty. Clean or replace filter.

Bar does not settle. Insufficient vacuum. Check line and pump.
Adjust valve.

Incorrect instrument. Check part number.

Defective instrument. Replace.

Bar oscillatesor Instrument loose in Tighten mounting screws.

shimmies continuously. panel.

Vacuum too high. Adjust valve.

Defectivemechanism. Replace instrument.

Instrument does not Instrument not level in Loosen screwsand level

indicate level flight. panel. instrument.

Aircraft out of trim. Trim aircraft.

Bar high after 180° Normal, if it does not

turn. exceed 1/16 inch.

Instrument tumbles in Low vacuum. Reset regulator.

flight.

Dirty filter. Clean or replace filter.

Line to filter re- Replace line.

stricted.

Plugmissing or loose Replace or tighten plug.

in instrument.
I I I

Revised: 8/3/81 INSTRUMENTS

3F7
 PIPER CHEROKEE SERVICE MANUAL

10-31. REMOVALAND REPLACEMENT. Refer to Paragraph 10-27of this section.

10-32. RATE OF CLIMBINDICATOR.

10-33. GENERAL. The rate of climb indicator measures the rate of change in static
pressure when the airplane is climbing or descending. By means of a pointer and dial this
instrument will indicate the rate of ascent or descent of the airplane in feet per minute. But
due to the lag of the instrument, the aircraft will be climbing or descending before the
instrument starts to read and the instrument will continue to read after the aircraft has
assumed level flight. In rough air this should not be considered a malfunction.

10-34. TROUBLESHOOTING.
TABLEX-IV. RATE OF CLIMBINDICATOR

Trouble Cause Remedy

Pointer does not set Aging of diaphragm. Reset pointer to zero

on zero. by means of setting
screw. Tap instrument
while resetting.

Pointer fails to Obstruction in static Disconnect all instru-

respond. line. ments connected to the
static line. Clear line.
Pitot head frozenover.

Waterin static line. Check individualinstru-

ments for obstruction
in lines.

Obstruction in pitot Clean lines and head.

head.

Pointer oscillates. Leaks in static lines. Disconnect all instru-

ments connected to the
static line. Check
individualinstruments
for leaks. Reconnect
instruments to static
line and test installa-
tion for leaks.

Defectivemechanism. Replace instrument.

Reissued: 1/15/81 3F8 INSTRUMENTS

 PIPER CHEROKEE SERVICE MANUAL

TABLE X-IV. RATE OF CLIMBINDICATOR(cont)

Trouble Cause Remedy

Rate of climb indi- Water in static line. Disconnect static lines
cates when aircraft and blow out lines from
is banked. cockpit out to pitot
head.
Pointer has to be Temperature compen- Replace instrument.
set before every sator inoperative.
flight.

Pointer cannot be reset Diaphragmdistorted. Replace instrument.

to zero.
Instrument reads very Case of instrument Replace instrument.
low during climb or broken or leaking.
descent.

NOTE
When any connections in the static system are opened for
checking, system must be rechecked per F.A.R. 23.1325.

10-35. REMOVALAND REPLACEMENT.Refer to Paragraph 10-81 of this section.

10-36. SENSITIVEALTIMETER.

10-37. GENERAL. The altimeter indicates pressure altitude in feet above sea level. The
indicator has three pointers and a dial scale; the long pointer is read in hundreds of feet, the
middle pointer in thousandths of feet and the short pointer in ten thousandth of feet. A
barometric pressure window is located on the right side of the indicator dial and is set by
the knob located on the lower left corner of the instrument. The altimeter consists of a
sealed diaphragm that is connected to the pointers through a mechanical linkage. The
instrument case is vented to the static air system and as static air pressure decreases,the
diaphragm expands, causingthe pointers to move through the mechanicallinkage.

Reissued: 1/15/81 3F9 INSTRUMENTS

 PIPER CHEROKEE SERVICE MANUAL

10-38. TROUBLESHOOTING.
TABLEX-V. ALTIMETER

Trouble Cause Remedy

Excessivescale error. Improper calibration Replace instrument.
adjustment.
Excessivepointer Defectivemechanism. Replace instrument.
oscillation.
High or low reading. Improper venting. Eliminate leak in
static pressure system
and check alignment of
airspeed tube.
Setting knob is hard Wronglubrication or Replace instrument.
to turn. lack of lubrication.
Inner reference marker Out of engagement. Replace instrument.
fails to move when
setting knob is
rotated.
Setting knob set screw Not tight when Tighten instrument
loose or missing. altimeter was reset. screw,if loose. Re-
place instrument, if
screw is missing.
Cracked or loose Case gasket hardened. Replace instrument.
cover glass.
Dull or discolored Age.
markings.

Barometric scale and Slippageof mating Replace instrument.

reference markers out parts.
of synchronism.

Barometric scale and Drift in mechanism. Refer to the latest re-

reference markers out vision of AC 43.13-1.
of synchronism with
pointers.

Reissued: 1/15/81 3F10 INSTRUMENTS

 PIPER CHEROKEE SERVICE MANUAL

TABLEX-V. ALTIMETER(cont)

Trouble Cause Remedy

Altimeter sticks at Water or restriction in Remove static lines

altitude or does not static line. from all instruments,
change with change of blow line clear from
altitude. cockpit to pitot head.

Altimeter changes Water in static line. Remove static lines

reading as aircraft from all instruments,
is banked. and blow line clear from
cockpit to pitot head.

Altimeter requires Temperature compensator Changeinstrument.

resetting frequently. inoperative.

NOTE

When any connections in the static system are opened for

check, system must be rechecked per F.A.R. 23.1325.

10-39. REMOVALAND REPLACEMENT. Refer to Paragraph 10-81 of this section.

10-40. AIRSPEED INDICATOR.

10-41. GENERAL. The airspeed indicator provides a means of indicating the speed of the
airplane passing through the air. The airspeed indication is the differential pressure reading
between pitot air to pressure and static air pressure. This instrument has the diaphragm
vented to the pitot air source and the caseis vented to the static air system. As the airplane
increases speed, the pitot air pressure increases, causing the diaphragm to expand. A
mechanical linkage picks up this motion and moves the instrument pointer to the indicated
speed. The instrument dial is calibrated in knots and miles per hour, and also has the
necessary operating range markings for safe operation of the airplane.

INSTRUMENTS
Reissued: 1/15/81 3F11
 PIPER CHEROKEE SERVICE MANUAL

10-42. TROUBLESHOOTING.

TABLEX-VI. AIRSPEEDTUBES AND INDICATOR

Trouble Cause Remedy

Pointers of static Leak in instrument case Check for leak and seal.
instruments do not or in pitot lines.
indicate properly.

Pointer of instrument Defectivemechanism. Replace instrument.

oscillates.

Instrument reads high. Pointer not on zero. Replace instrument.

Leaking static system. Find leak and correct.

Instrument reads low. Pointer not on zero. Replace instrument.

Leaking static system. Find leak and correct.

Pitot head not aligned Realign pitot head.

correctly.

Airspeed changesas Water in pitot line. Remove lines from static

aircraft is banked. instruments and blow
out lines from cockpit
to pitot head.

NOTE

When any connections in static system are opened for

checking, system must be checked per F.A.R. 23.1325.

10-43. REMOVALAND REPLACEMENT. Refer to Paragraph 10-81 of this section.

Reissued: 1/15/81 3F12 INSTRUMENTS

 PIPER CHEROKEE SERVICE MANUAL

10-44. MAGNETICCOMPASS.

10-45. GENERAL. The magnetic compass is a self-contained instrument. This instrument

has an individual light which is connected to the instrument lighting circuit. The compass
correction card is located in the card holder mounted on the instrument. The compass
should be swung wheneverinstruments or radios are changed and at least once a year.
10-46. ADJUSTMENTOF COMPASS.Before attempting to compensate compass, every
effort should be made to place the aircraft in simulated flight conditions; check to see that
the doors are closed, flaps in retracted position, engine running, throttle set at cruise
position and aircraft in level flight attitude. Aircraft master switch, alternator switch and all
radio switches should be in the ON position. All other cockpit controlled electrical switches
should be in the OFF position.
a. Set adjustment screws of compensator on zero. Zero position of adjusting screws
is when the dot of the screw is lined up with the dot of the frame.
b. Head aircraft on a magnetic North heading. Adjust N-S adjustment screw until
compass reads exactly North.
c. Head aircraft on a magnetic East heading and do the same as Step b, adjusting
E-Wadjusting screw.
d. Head aircraft on a magnetic South heading and note resulting South error. Adjust
N-S adjusting screw until one-half of this error has been removed.
e. Head aircraft on magnetic West and do same as Step d, adjusting E-Wadjustment
screw.
f. Head aircraft in successive.magnetic 30 degree headings and record compass
readings on appropriate deviation card. Deviations must not exceed ± 10° on any heading.

Reissued: 1/15/81 3F13 INSTRUMENTS

 PIPER CHEROKEE SERVICE MANUAL

10-47. TROUBLESHOOTING.
TABLEX-VII. MAGNETICCOMPASS

Trouble Cause Remedy

Excessivecard error. Compassnot properly Compensate instrument.

compensated. (Refer to Paragraph
10-46.)
External magnetic Locate magnetic inter-
interference. ference and eliminate
if possible.

Excessivecard Insufficient liquid. Replace instrument.

oscillation.

Card sluggish. Weak card magnet. Replace instrument.

Excessivepivot fric- Replace instrument.

tion or broken jewel.

Liquid leakage. Loose bezel screws. Replace instrument.

Broken cover glass. Replace instrument.

Defective sealing Replace instrument.

gaskets.

Discolored markings. Age. Replace instrument.

Defectivelight. Burned out lamp or Check lamp or continuity

broken circuit. of wiring.

Card sticks. Altitude compensating Replace instrument.

diaphragm collapsed.

Card does not move The gears that turn Replace instrument.
when compensating compensatingmagnets
screwsare turned. are stripped.

Compassswings Normal.
erratically when
radio transmitter
is keyed.

Reissued: 1/15/81 3F14 INSTRUMENTS

 PIPER CHEROKEE SERVICE MANUAL

10-48. MANIFOLDPRESSURE GAUGE.

10-49. GENERAL. The manifold pressure gauge is a vapor proof, absolute pressure type
instrument. Pressure from the intake manifold of the engine is transmitted to the instrument
through a line. A pointer indicates the manifold pressure availableat the engine in inches of
mercury.
10-50. TROUBLESHOOTING.

TABLE X-VIII. MANIFOLDPRESSURE INDICATOR

Trouble Cause Remedy
Excessiveerror at ex- Pointer shifted. Replace instruments.
isting barometric pressure.
Excessiveerror when Line leaking. Tighten line connections.
engine is running.
Sluggishor jerky Defectiveinstrument. Replace instrument.
pointer movement.
Dull or discolored Age. Replaceinstrument.
marking.
Incorrect reading. Moisture or oil in Disconnect lines and
line. blow out.

10-51. REMOVALAND REPLACEMENT. (Refer to Paragraph 10-81 of this section.)

10-52. TACHOMETERINDICATOR.
10-53. GENERAL. The tachometer is connected to the engine accessory by a flexible cable
and provides an indication of crankshaft speed in revolutions per minute. The instrument
has a recording mechanism for recording the time that the engine is in actual operation.
NOTE
On PA-28-180 aircraft Serial Nos. 28-1761 to 28-3555,
28-3557 to 28-3572 and 28-3574 to 28-3626. The aircraft
tachometer must be placarded to show a red ARC between
2150 and 2350 RPM in accordance with the latest revision of
Piper Service Letter No. 526.
Propeller Limits: avoid continuous operation between 2150
and 2350 RPM.

INSTRUMENTS
Reissued: 1/15/81 3F15
 PIPER CHEROKEE SERVICE MANUAL

10-54. TROUBLESHOOTING.

TABLEX-IX. TACHOMETER

Trouble Cause Remedy

No reading on indica- Broken shaft. Replace instrument.

tor, either permanent
or intermittent.

Loose cable connections. Tighten cable.

Pointer oscillates Rough spot on, or Repair or replace.

excessively. sharp bend in shaft.

Excessivefriction in Replace instrument.

instrument.

Indicator changesin Excessiveclearance in Replace instrument.

climb. speed cup.

Pointer goes all the Excessivelubricant in Replace instruments.

way to stop, more instruments.
noticeable in cold
weather.

Pointer jumps at idle. Speed cup hitting ro- Replace instrument.

tating magnet.

Tachometer cable breaks. Cable bent too sharply. Reroute cable.

10-55. REMOVALAND REPLACEMENT. Refer to Paragraph 10-81of this section.

10-56. ENGINEOIL PRESSURE GAUGE.

10-57. GENERAL. The oil pressure gauge is mounted in the cluster on the instrument
panel. This gauge will indicate the amount of oil pressure available at the pressurized engine
oil passage.

Reissued: 1/15/81 3F16 INSTRUMENTS

 PIPER CHEROKEE SERVICE MANUAL

10-58. TROUBLESHOOTING.

TABLEX-X. ENGINE OIL PRESSUREGAUGE

Trouble Cause Remedy

Excessiveerror at Pointer loose on shaft. Replace instrument.

zero. Overpressureor
seasoning of bourdon
tube.

Excessivescale error. Improper calibration Replace instrument.

adjustment.

Excessivepointer Air in line or rough Disconnect line and

oscillation. engine relief. fill with light oil.
Check for leaks. If
trouble persists, clean
and adjust relief valve.

Sluggishoperation of Engine relief valve Clean and check.

pointer or pressure open.
fails to build up.

10-59. REMOVALAND REPLACEMENT. Refer to Paragraph 10-83 of this section.

10-60. FUEL PRESSURE GAUGE.

10-61. GENERAL. The fuel pressure gauge instrument is mounted in the cluster on the
instrument panel. This gauge is connected to the fuel system at the carburetor fuel inlet
fitting.

Reissued: 1/15/81 3F17 INSTRUMENTS

 PIPER CHEROKEE SERVICE MANUAL

10-62. TROUBLESHOOTING.

TABLEX-XI. FUEL PRESSUREGAUGE

Trouble Cause Remedy

No fuel pressure Fuel valve stuck. Check valve.

indication.

No fuel in tanks. Check fuel, fill.

No fuel pressure Defective fuel pump. Check pump for pres-

indication (cont). sure build-up. Check
diaphragm and relief
valvesin engine pump.
Check for obstruction
in electric pump.
Check bypass valve.
Air leak in intake
lines.

Defectivegauge. Replacegauge.

Pressure low or Obstruction in inlet Trace lines and locate

pressure surges. side of pump. obstruction.

Faulty bypass valve. Replace.

Faulty diaphragm. Replace or rebuild pump.

Needle fluctuation. Surge dome on pump Remove and empty.

filled with fuel.

Air in line. Loosen line at gauge,

turn on electric pump.
Purge line of air and
retighten.

High fuel pressure Fuel in line expanding Normal.

with engine shut off due to heat build up
right after flight. in cowling.

Reissued: 1/15/81 3F18 INSTRUMENTS

 PIPER CHEROKEE SERVICE MANUAL

10-63. REMOVALAND REPLACEMENT.Refer to Paragraph 10-79 of this section.

10-64. TURN AND BANKINDICATOR.
10-65. GENERAL. The turn and bank indicator can be either vacuum driven or electric.
The turn portion of the indicator is a gyroscope, while the bank portion of the indicator is a
ball sealed in a curved glass tube filled with damping fluid. There are two styles of this unit.
The first is the old style with a vertical needle in the center of the dial. This instrument
reads only the rate of turn, and unless the aircraft is turning, the needle will not move
regardless of bank angle. The other style is the turn coordinator which indicates both the
rate of turn and rate of roll.With this indicator, if the aircraft is rolled right and left rapidly,
the indicator will move, indicating a turn, but if the aircraft is held in a bank, and rudder is
applied, the indicator will come back to zero indicating no turn.

10-66. TROUBLESHOOTING.

TABLE X-XII. TURN AND BANK INDIATOR

Trouble Cause Remedy

Pointer fails to Foreign matter lodged in Replace instrument.

respond. instrument.

Incorrect sensitivity. Out of calibration. Replace instrument.

Incorrect turn rate High or low vacuum. Check vacuum and adjust.
(vacuum style).
Filter dirty. Replace filter.

Incorrect turn rate Out of calibration. Replace instrument.

(electric).
Aircraft not in Center ball in turn.
coordinated turn.

Ball sticky. Flat spot on ball. Replaceinstrument.

Ball not in center Instrument not level Levelinstrument.

when aircraft is in panel.
correctly trimmed.

Instrument will not No power to instrument. Check circuit and repair.

run (electric).
Instrument malfunction. Replace instrument.

INSTRUMENTS
Reissued: 1/15/81 3F19
 PIPER CHEROKEE SERVICE MANUAL

10-67. ELECTRICALINSTRUMENTS.

10-68. REMOVALAND REPLACEMENT.Refer to Paragraph 10-81 of this section.

10-69. FUEL QUANTITYINDICATOR.

10-70. GENERAL. The two fuel quantity gauges are mounted in the cluster on the
instrument panel. These instruments are calibrated in fractional divisions of one fourth, one
half, three fourths and full. A transmitter unit is installed in each fuel cell. This unit
contains a resistance strip and a movable control arm. The position of this arm is controlled
by a float in the fuel cell and this position is transmitted electrically to the indicator gauge
to show the amount of fuel in the cell.

10-71. TROUBLESHOOTING.

TABLE X-XIII. FUEL QUANTITYINDICATORS

Trouble Cause Remedy

Fuel gauge fails to Broken wiring. Check and repair.

indicate.

Gauge not operating. Replace.

Blown fuse. Replace fuse.

Fuel gauge indicates Incomplete ground. Check ground connections

empty when tanks are at fuel transmitter in
full. wings.

Fuel gaugeindicates Incomplete ground. Check ground at instru-

full with tanks empty. ment.

Float arm stuck. Replace fuel transmitter.

Fuel gaugeindicates Intermittent ground. Check ground at trans-

incorrectly. mitter and instrument.

Float arm sticky. Replace fuel transmitter.

Reissued: 1/15/81 3F20 INSTRUMENTS

 PIPER CHEROKEE SERVICE MANUAL

10-72. REMOVALAND REPLACEMENT. Refer to Paragraph 10-83of this section.

10-73. OIL TEMPERATUREINDICATOR.

10-74. GENERAL. The oil temperature indicator is mounted in the instrument cluster on
the instrument panel. This instrument will provide a temperature indication of the engine oil
in degrees Fahrenheit. The instrument has a temperature bulb located in the oil screen
assembly,on the engine accessorysection.

10-75. TROUBLESHOOTING.

TABLE X-XIV. OIL TEMPERATUREINDICATORS

Trouble Cause Remedy

Instrument fails to Broken or damaged bulb. Check engine unit and

show any reading. Wiringopen. wiring to instrument.

Excessivescale error. Improper calibration Repair or replace.

adjustment.

Pointer fails to move Broken or damaged bulb Check engine unit and
as engine is warmed up. or open wiring. wiring.

Dull or discolored Age. Replaceinstrument.

marking.

10-76. REMOVALAND REPLACEMENT. Refer to Paragraph 10-83 of this section.

10-77. AMMETER.

10-78. GENERAL. The ammeter is mounted in the instrument cluster located on the
instrument panel. This instrument measures the output of the alternator into the entire
electrical system including the battery charging demand.

10-79. TROUBLESHOOTING.Refer to Section XI. (Alternator Section)

10-80. REMOVALAND REPLACEMENT. Refer to Paragraph 10-83of this section.

10-81. REMOVALAND REPLACEMENTOF FACE MOUNTEDINSTRUMENTS.

INSTRUMENTS
Reissued: 1/15/81 3F21
 PIPER CHEROKEE SERVICE MANUAL

10-82. GENERAL. Since all instruments are mounted in a similar manner, a description of
a typical removal and installation is provided as a guide for the removal and installation of
the instruments. Special care should be taken when any operation pertaining to the
instruments is performed.
a. Remove the face panel by removing the screws from around the perimeter of the
panel.
b. With the face panel removed, the mounting screws for the individual instruments
will be exposed. Remove the connections to the instrument prior to removing the mounting
screwsof the instrument to be removed.

NOTE

Tag instrument connections for ease of installation.

c. Installation of the instruments will be completed by reversing the removal

instructions. After the installation is completed and before replacing the instrument face
panel, check all components for security and clearance of the control column.

10-83. REMOVALAND REPLACEMENTOF CLUSTER MOUNTEDINSTRUMENTS.

10-84. GENERAL. A cluster, located on the instrument panel, contains six individual
instruments. Removal of these instruments can be accomplished by the followingprocedure.
a. Remove the face panel by removing the screws from around the perimeter of the
panel.
b. With the face panel removed, the clear plastic cover on the cluster assemblywill be
exposed. Remove the coverand cluster by removing the six mounting screws.
c. Remove the connection to the individual instrument to be removed and remove the
instrument from the cluster assembly.
d. Replace the instruments by reversing the removal instructions. Check all
mountings and connections for security.
10-85. EXHAUSTGAS TEMPERATUREGAUGE. (ALCOR)

10-86..GENERAL. This instrument, which is commonly referred to as EGT, is used to aid

the pilot in selecting the economical fuel-air mixture for cruising flight at a power setting of
75% or less. It is a sensing device to monitor the fuel-air mixture leaving the engine
cylinders. This gauge is adjustable. If it is found defective after checking with
troubleshooting chart it should be replaced. If the leads to the gauge are defective in any
way they should be replaced. When replacing leads, it is very important to use the same
type and length of wire as the resistance of the leads is critical for the proper operation of
this gauge.

Reissued: 1/15/81 3F22 INSTRUMENTS

 PIPER CHEROKEE SERVICE MANUAL

10-87. CLEANING AND INSPECTION. Unless mechanical damage is evident, broken

glass, bent or broken pointer, or broken case, the following checks should be performed
before removing the instrument.
a. Remove the probe from the exhaust stack and check for a broken weld (at tip
end) or a burnt off end. The measured resistance of probe should be .8 ohms. Clean the
connections with steel wool before reassembly.
b. Disconnect the lead wires at the instrument and measure. Resistance with the lead
wires connected to probe should be 3.3 ohms. Clean connections with steel wool before
reassembly.
c. With the leads connected to instrument, heat probe with propane torch to dull
red. The meter should read up to the fourth graduation or approximately 1500 °F. Before
making this check, make sure that the adjustment screw, located at the rear of the
instrument case, is in the center of its travel. If this screw has been turned to either end of
full travel, it will shut the instrument off and no indication will be shown on the pointer. If
meter still does not read, replace it.
CAUTION
Do not connect ohmmeter across meter. It will burn out
the movement of the meter.
10-88. TROUBLESHOOTING.

TABLE X-XV. EXHAUSTGAS TEMPERATUREGAUGE(ALCOR)

Trouble Cause Remedy

Gauge inoperative. Defectivegauge,probe Check probe and lead

or wiring. wires for chafing,
breaks or shorting
between wires and/or
metal structure.

Adjusting potentio- Reset potentiometer.

meter turned off scale.

Fluctuating reading. Loose, frayed or broken Clean and tighten

electricalleads or connections. Repair
faulty connections. or replace defective
leads.

Reissued: 1/15/81 INSTRUMENTS

3F23
 PIPER CHEROKEE SERVICE MANUAL

C314

PROBE(SEENOTE)

LEFTSIDEVIEW

NOTE
.129 HOLE IN NO. 2 CYLINDEREXHAUST
STACK.REFER TO TOPVIEWFORCORRECT
LOCATION.

Figure 10-19. EGT PROBE LOCATION (PA-28R-180 and 200)

5/81
Reissued: 1/15/81 3F24 INSTRUMENTS
 PIPER CHEROKEE SERVICE MANUAL

C316

ENGINECENTERLINE

45°

TOPVIEW

EGT

2.00

NOTE
.129 HOLE IN NO. 2 CYLINDEREXHAUST
STACK.REFERTO TOPVIEW FORCORRECT
LOCATION.

Figure 10-20. EGT PROBE LOCATION (PA-28-235)

Reissued: 1/15/81 3G1 INSTRUMENTS

 PIPER CHEROKEE SERVICE MANUAL

C315
8152

ENGINECENTERLINE

TOP VIEW

EGT PROBE (SEE NOTE)

LEFTSIDE VIEW

NOTE
.129 HOLE IN NO. 4 CYLINDEREXHAUST
STACKIN LINEWITHCENTERLINEOFENGINE.

Figure 10-21. EGT PROBE LOCATION (PA-28-150/160/180) (S/N 1761 and up)

/15/81
Reissued: 1/15/81 3G2 INSTRUTRUMENTS
 PIPER CHEROKEE SERVICE MANUAL

10-89. CYLINDERHEADTEMPERATUREGAUGE.
10-90. GENERAL. The cylinder head temperature gaugeis in the instrument cluster on the
instrument panel. This instrument measures the cylinder head temperature using a sender
located in a cylinder head. The head location is determined by the engine manufacturer. It is
an electrical instrument and is wired through the instruments circuit breaker.
10-91. TROUBLESHOOTING.

TABLEX-XVI. CYLINDERHEADTEMPERATUREGAUGE

Trouble Cause Remedy

Instrument shows no Power supply wire Repair wire.

indication. broken.

Defectiveinstrument. Replace instrument.

Master switch off.

Instrument goes all Wirebroken between Repair wire.

the way to upper stop. sender and gauge.

Defectivesender. Replace sender.

10-92. REMOVALAND REPLACEMENT.Refer to Paragraph 10-83 of this section.

10-93. FUEL FLOWGAUGE.
10-94. GENERAL.The fuel flow gauge is a non-electric pressure gauge mounted in the
bottom half of the manifold pressure gauge. This gauge is located in the lower portion of the
instrument panel.
This instrument measures flow by reading the pressure drop across a fixed orifice
located in the fuel divider. When a constant fuel pressure is being supplied by the engine
driven pump, one can put a fixed orifice in the fuel divider head and measure the pressure
drop downstream of the orifice against a constant static pressure. This resultant pressurecan
be calibrated in gallons per hour flow. The constant static pressure is supplied by a vent line
running to the engine compartment. The vent line to the engine compartment automatically
compensates the instrument for altitude.

Reissued: 1/15/81 3G3 INSTRUMENTS

 PIPER CHEROKEE SERVICE MANUAL

10-95..TROUBLESHOOTING.

TABLEX-XVII. FUEL FLOW GAUGE

Trouble Cause Remedy

Pointer oscillates. Air in fuel line. Purge line.

Gauge reads low at Vent line restricted. Check line and fittings.
altitude.

Pointer does not return Fuel in diaphragm of Replace gauge.

to zero. gauge.

10-96. REMOVALAND REPLACEMENT. Refer to Paragraph 10-81of this section.

10-97. PIPER AUTOCONTROLSYSTEM. (See AutoControl ServiceManual)

10-98. ANNUNCIATORPANEL.

10-99. GENERAL. The annunciator panel consists of three amber lights and a push-button
test switch located on the upper left center portion of the instrument panel. (Refer to
Figure 10-4b.) The panel monitors alternator output, oil pressure and the vacuum system.
The ALT warning light will illuminate when alternator output is zero; the VAC light when
the pressure difference is below 3.5 in. Hg, and the OIL light when the oil pressure is below
35 psi. A test button is included to check the operation of the lights. This installation is
availableon 1975 models and up. (Refer to Section XI for serviceinformation.)

10-100.TROUBLESHOOTING.(Refer to Table XI-I.)

10-101. REMOVALAND REPLACEMENT.(Refer to paragraph 10-81.)

Reissued: 1/15/81 3G4 INSTRUMENTS

 3G5 THRU 3L24
INTENTIONALLYLEFT BLANK
 CHEROKEE
MANUAL
SERVICE
CARD
4 OF4

PA-28-140
PA-28-150
PA-28-160
PA-28-180
PA-28-235
PA-28R-180
PA-28R-200

CORPORATION
PIPERAIRCRAFT
(PART
NUMBER
753586) 4A1
 PIPER CHEROKEE SERVICE MANUAL

AEROFICHE EXPLANATION AND REVISION STATUS

The Service Manual information incorporated in this set of Aerofiche cards has been arranged in
accordance with the general specifications of Aerofiche adopted by the General Aviation Manufacturer's
Association, (GAMA). The information compiled in this Aerofiche Service Manual will be kept current by
revisions distributed periodically. These revisions will supersede all previous revisionsand will be complete
Aerofiche card replacements and shall supersede Aerofiche cards of the same number in the set.
Conversion of Aerofiche alpha/numeric code numbers:
First number is the Aerofiche card number.
Letter is the horizontal line reference per card.
Second number is the vertical line reference per card.
Example: 2J16 = Aerofiche card number two of given set, Grid location J16.
To aid in locating the various chapters and related service information desired,the followingis provided:
1. A complete manual Table of Contents is for all fiche in this set.
2. A complete list of Illustrations is given and follows the Table of Contents.
3. A complete list of Tables is given for all fiche in this set and follows the list of Illustrations.
4. A complete list of paragraph titles and appropriate Grid location numbers is givenat the beginningof
each Chapter relating to the information within that Chapter.
5. Identification of Revised Material:
Revisedtext and illustrationsare indicated by a black vertical line along the left-hand margin of
the frame, opposite revised,added or deleted material. Revisionlines indicate only current revisions
with changesand additions to or deletions of existingtext and illustrations.Changesin capitalization,
spelling, punctuation, indexing, the physical location of the material or complete pageadditions are
not identified by revision lines.
6. Revisions to this Service Manual 753 586 issued August 16, 1972are as follows:
Effectivity Publication Date Aerofiche Card Effectivity

ORG720816 August 16, 1972

CR810115 January 15, 1981 1, 2, 3 and 4
PR810803 August 3, 1981 1, 2, 3 and 4
PR831003 October 3, 1983 1, 2, 3 and 4
PR840423 April 23, 1984 1, 2, 3 and 4
PR860115 January 15, 1986 1 and 3
IR860730 July 30, 1986 1
IR870506* June 12,1987 1

This publication contains material revisedas of January 15, 1986(with two interim revisionseffectiveJuly
30, 1986and May 6, 1987).
* INTERIM CHANGE
Revisions appear in Table III-I and Table III-I of card 1.
There are no other changes included in this maintenance
manual.Pleasediscardyour currentcard 1 andreplaceit with
this revisedone. DO NOT DISCARD CARDS 2 3, or 4.

The date on Aerofiche cards should not be earlier than the date noted for the respectivecard effectivity.
Consult the latest card in this series for current Aerofiche card effectivity.
4A2
 AIX
IIIX
IIX
8V IX

8 X
8313 XI
8 VIIIA

IIIA
VIIA
IIA
IA
8V A
Z'ON

S A
9 III
I
6 N I
'ON

S
 PIPER CHEROKEESERVICEMANUAL

Figure
LISTOFILLUSTRATIONS Aerofiche
Grid No.
1 1-1. Generator and Starter System ......................... 4A18
11-2. Generator WiringDiagram ............. 4A19
11-3. Sectional View of Generator ............. 4A22
1-4. Current/Voltage Regulator ............. 4B7
11-5. Useof Riffler File to Clean Contact Points .................. 4B10
11-6. Voltage Regulator Air Gap .......................... 4B10
11-7. CheckingVoltage Setting Fixed Resistance Method ............. 4B11
11-8. CheckingVoltage Setting Variable Resistance Method ..... 4B11
11-9. Adjusting Voltage Regulator Setting ..... ..... 4B12
1 -10. Cutout Relay Air Gap Check and Adjustment ................ 4B14
11-11. Cutout Relay Point Opening Check and Adjustment ............ 4B14
11-12. CheckingCutout Relay Closing Voltage ................... 4B15
11-13. Adjustment of Cutout Relay Closing Voltage ................ 4B15
11-14. CheckingCurrent Regulator, Load Method .................. 4B16
11-15. CheckingCurrent Regulator, Jumper Lead Method ............. 4B16
11-16. Alternator and Starter System,
PA-28-140, SerialNos. 28-20000 to 28-24999 incl.:
PA-28-150,-160. Serial Nos. 28-508 to 28-3643 incl.:
PA-28-180,Serial Nos. 28-671 to 28-3643 incl.;
PA-28-235,Serial Nos. 28-10002 to 28-10762 incl. ........... 4B20
11-17. Alternator and Starter System,
PA-28-140,Serial Nos. 28-25000 and up;
PA-28-150.-160, -180, Serial Nos. 28-3644 and up;
PA-28-235 Serial Nos. 10763 and up and PA-28R ........ .. 4B21
11-18. Lamp-BankLoad ................................ 4B23
11-19. Checking Field Circuit ............................. 4B24
11-20. Testing Field Circuit ............................... 4B24
11-21. Testing Rectifiers(Positive) .......................... 4C2
11-22. Testing Rectifiers(Negative) .......................... 4C3
11-23. C-3928 Fixtures and Adapters ........................ 4C4
11-24. RemovingRectifiers ............................... 4C4
11-25. Installing Rectifiers ............................... 4C5
11-26. SolderingRectifier Lead ............................ 4C6
11-27. Testing Stator Coils ............................... 4C7
11-28. RemovingEnd Bearing ............................. 4C9
11-29. Installing End Bearing .............................. 4C9
11-30. RemovingDrive Pulley ............................. 4C10
11-31. RemovingDrive End Bearing .......................... 4C10
11-32. RemovingSlip Ring . ............................ 4C11
11-33. AligningSlip Ring ................................ 4C11
11-34. Installing Slip Ring ............................... 4C12
11-35. Installing Retainer ................................ 4C12
11-36. Solder Points ................................... 4C13
11-37. Installing Drive End Shieldand Bearing(Typical) .............. 4C14
11-38. InstallingPulley ................................. 4C14
11-39. Meter Connections for Alternator Performance Test ............ 4C17

4A4
 PIPER CHEROKEE SERVICE MANUAL

LIST OF ILLUSTRATIONS (cont.)

Figure Aerofiche
Grid No.
11-40. Voltage Regulator ...................................... ...... 4C19
11-41. Checking Air Gap .................... ....................... 4C19
11-42. Voltage Regulator Fusible Wires ............................... 4C20
11-43. Voltage Regulator Resistance Units ............................. 4C20
11-44. No-Load Test Hookup ........................................ 4D2
11-45. Lock Torque Test Hookup ........... ...................... 4D3
11-46. Resistance Test Hookup ............................. .......... 4D3
11-47. Exploded View of Gear Reduction Starting Motor ................ 4D8
11-48. Turning Starting Motor Commutator ........................... 4D11
11-49. Testing Motor Armature for Shorts ................... .......... 4D11
11-50. Testing Motor Field for Grounds ............................... 4D11
11-51. No-Load Test Hookup ........................................ 4D13
11-52. Stall Torque Hookup .......................................... 4D13
11-53. Terminal Block ............................................. 4F5
11-54. For Index to these figures. see Table XI-I. Index
thru Electrical System Schematics 4A 12
11-70.
11-71. Exploded Viewof Alternator .................................. 4D20
11-72. Removal of Slip Ring End Bearing ............................. 4D21
11-73. Removal of Rectifier.......................................... 4D21
11-74. Removal of Drive End Head ................................... 4D22
11-75. Removal of End Head Bearing ................................. 4D22
11-76. Testing Rotor for Ground ..................................... 4D23
11-77. Testing Rotor for Shorts ...................................... 4D23
11-78. Installation of Bearing ...................................... .. 4D24
11-79. Installation of Rectifier........................................ 4D24
11-80. Terminal Assembly ........................................... 4E I
11-81. Slip Ring End Bearing Assembly ....................... ........ 4E2
11-82. Testing Alternator ............................................ 4E2
11-83. Brush Installation ........................................... 4E3
11-84. Internal Wiring Diagram ...................................... 4E3
11-85. For Index to these figures. see Table XI-I. Index
thru Electrical System Schematics 4A 12
11-143.
11-144. Strobe Light Connections ..................................... 4E9
12-1. Two Year. Magnesium Battery Connections...................... 413
12-2. ELT Portable Folding Antenna ................................ 414
12-3. ELT Using Fixed Aircraft Antenna ............................. 414
12-4. Emergency Locater Transmitter Schematic (Narco) ............... 415
12-5. Communications Components ELT Schematic ................... 416
13-1. Cabin Heater. Defroster and Fresh Air System.
PA-28-140.Serial Nos. 28-2002to 28-24999incl..
and PA-28-150.-160. -180. Serial Nos. 28-1 to
28-1760incl ........................................... 4117
13-2. Cabin Heater. Defroster and Fresh Air System.
PA-28-140.Serial Nos. 28-25000and up ..................... 4118
13-3. Cabin Heater. Defroster and Fresh Air System.
PA-28-150.-160. -180. Serial Nos. 28-1761to
28-2477inc .............................................. 4119

Revised: 10/3 83 4A5

 PIPER CHEROKEESERVICE MANUAL

LIST OF ILLUSTRATIONS(cont.)

Figure Aerofiche
Grid No.
13-4. Cabin Heater, Defroster and Fresh Air System,
PA-28-150,-160, -180, Serial Nos. 28-2478 to
28-4377 incl............. ....................... 4120
13-5. Cabin Heater, Defroster and Fresh Air System,
PA-28-180,Serial Nos. 28-4378 and up ........ 4121
13-6. Cabin Heater, Defroster and Fresh Air System.
PA-28-235.Serial Nos. 28-10003 to 28-10675 incl. ............ 4122
13-7. Cabin Heater, Defroster and Fresh Air System.
PA-28-235,Serial Nos. 28-10676 to 28-1 1039 incl. ........... 4123
13-8. Cabin Heater. Defroster and Fresh Air System.
PA-28-235, Serial Nos. 28-11040 to 28-7210033 incl. ........... 4124
13-9. Cabin Heater. Defroster and Fresh Air System.
PA-28-235, Serial Nos. 28-7310001 and up ............... 4JI
13-10. Cabin Heater, Defroster and Fresh Air System.
PA-28R. ................................... 4J2
13-11. OverheadVent System ............ .............. ....... ;4J3
14-1. Air Conditioning System Installation .... ................. 4J7
4J7
14-2. ServiceValves ................. ................. .. 4J12
14-3. Test Gaugeand ManifoldSet ......... ........ ·......... .. 4J13
14-4. ManifoldSet Operation ............ ................. 4J14
U
14-5. Leak Test Hookup ............... ................. 4J15
14-6. Evacuation Hookup .............. ................. .......
4J17
14-7. ChargingStand ................. ................... 4J19
14-8. ChargingHookup ....... ........ ................. 4J21
14-9. Compressorand Fabricated Oil Dipstick . . ................. .. 4K1
14-10. Compressorand Alternator Belt Installation . ................ . 4K5
14-11. MagneticClutch ................ .... .. ............ 4K7
14-12. Condenser Air Scoop Installation ...... ................. ..4K11
14-13. Expansion Valve ................ ................. ..4K13
14-14. Components Installation ........... ................. 4K15
14-15. Control Head - Diode Mounting Board, Diode Location and
Number, PA-28-140,Serial Nos. 28-7125472 to 28-7325057;
PA-28-180,Serial Nos. 28-7205092 to 28-7305071;
PA-28R-200. 28R-7235001 to 28R-7335057 .............. 4K16
14-16. Air Conditioning WiringSchematic.
PA-28-140,SerialNos. 28-7125472 thru 28-7225131 incl.;
PA-28-180,SerialNos. 28-7205092 thru 28-7205 44 incl ...... 4K18
14-17. Air Conditioning WiringSchematic,
PA-28-140, SerialNos. 28-7225132 to 28-7225612;
PA-28-180, SerialNos. 28-7205145 to 28-7205328;
PA-28R-200,Serial Nos. 28R-7235001 to 28R-7235330 ....... 4K19
14-18. Air Conditioning WiringSchematic,
PA-28-140, SerialNos. 28-7325001 and up;
PA-28-180, SerialNos. 28-7305001 and up;
PA-28R-200,Serial Nos. 28-7335001 and up .............. 4K20

Revised: 10/3/83 4A6

 PIPERCHEROKEESERVICEMANUAL

LIST
OFTABLES
Aerofiche
Table Grid No.
XI-I. Electrical System Schematic Index .................. 4A12
XI-II. Electrical System Troubleshooting .................. 4E10
XI-III. Electrical System Component Loads ................. 4F8
XI-IV. Electrical Symbols ............................ 4F9
XI-V. ElectricalWireCoding .......................... 4F10
XIV-I. Temperature PressureChart ....................... 4J8
XIV-II. AluminumTubing Torque ....................... 4J11
XIV-III. CompressorOil Change ......................... 4J24
XIV-IV. Air Conditioning System Troubleshooting .............. 4K21
XIV-V. Blower System WireColor Codes ................... 4L6

Revised: 10/3/83 4A7

 SECTION
XI

ELECTRICAL
SYSTEM

Aerofiche
Grid No.
11-1. Introduction ................................... 4A17
11-2. Description ........................ ... .. 4A17
11-3. Troubleshooting ................................. 4A17
11-4. Generator System (Delco-Remy) ....................... 4A20
11-5. Description of Generator System ................. 4A20
11-6. CheckingGenerator System ................... 4A20
11-7. Adjustments,Tests and Maintenanceof
Generator System ........................ 4A21
11-8. Test and Maintenanceof Generator (Delco-Remy) ....... 4A22
11-9. Inspection of Generator ....................... 4A22
11-10. Shunt Generator Output ...................... 4A23
11-11. Check DefectiveGenerators .................... 4A24
11-12. No Output ......................... 4A24
11-13. Unsteady or Low Output . .. .................. .. 4B1
11-14. ExcessiveOutput .......................... 4B2
11-15. NoisyGenerator ........................... 4B2
11-16. Disassembly,Repair and Reassembly ............... 4B3
11-17. Field Coil Removal ............ 4B3
11-18. Inspection and Repair of Parts ................... 4B3
11-19. Field Coil Service ............. 4B3
11-20. Armature Service .......................... 4B4
11-21. PolarizingGenerator ......................... 4B4
11-22. Generator ServiceTest Specifications (Delco-Remy) ...... 4B5
11-23. Regulatorr (Delco-Remy) ............ ................ 4B6
11-24. Description of Regulator ....... ................ 4B6
11-25. Cutout Relay .............. ·..... ........... 4B6
11-26. Voltage Regulator ........... ............... 4B7
11-27. Current Regulator ........... ............... 4B8
11-28. Resistances .............. ............... 4B8
11-29. Temperature Compensation ..... ............... 4B9
11-30. Regulator Polarity ........... ............... 4B9
11-31. Regulator Maintenance ........ ........... .... ..
4B9
11-32. Maintenance Instructions ....... ............... 4B9
11-33. CleaningContact Points ........ ............... .4B10
11-34. Regulator Checks and Adjustments ............... 4B11
11-35. Voltage Regulator ........... ............ 4B11

Revised: 10/3/83 4A8

 Aerofiche
Grid No.

11-36. Cutout Relay ........................... 4B14

11-37. Current Regulator .......................... 4B15
11-38. Repairs ................................ 4B17
11-39. Regulator Spring Replacement ... ............
. 4B17
11-40. Radio By-PassCondensers ..................... 4B17
11-41. Regulator Armature Replacement .... ............ 4B17
11-42. High Points on Regulator Performance and Checks ....... 4B17
11-43. Regulator ServiceTest Specifications (Delco-Remy) ...... 4B18
11-44. Alternator System (Chrysler) ......................... 4B19
11-45. Description of Alternator System ................. 4B19
11-46. Alternator System Test Procedure ................. 4B22
11-47. Bench TestingAlternator ...................... 4B24
11-48. Field Current Draw ......................... 4B24
11-49. Testing Alternator Internal Field Circuit For
A Ground ............................ 4C1
11-50. Inspection .............................. 4C1
11-51. Testing Rectifiers(Positive) .................... 4C1
11-52. Testing Rectifiers(Negative) .................... 4C3
11-53. Removingand Installing Rectifiers ................ 4C4
11-54. RemovingRectifiers ......................... 4C5
11-55. Installing Rectifiers ......................... 4C5
11-56. Testing Stator Coils for Ground .................. 4C8
11-57. Testing Alternator Capacitors ................... 4C8
11-58. RemovingNeedleBearing From End Shield ........... 4C9
11-59. InstallingNeedle Bearingin End Shield .............. 4C9
11-60. RemovingDrive Pulley ....................... 4C10
11-61. RemovingDrive End Bearing .................... 4C10
11-62. ReplacingSlip Rings ......................... 4C11
11-63. RemovingSlip Rings ........................ 4C12
11-64. Installation of Slip Rings ...................... 4C12
11-65. InstallingGrease Retainer ...................... 4C15
11-66. Installing Drive End Bearing .................... 4C15
11-67. InstallingPulley ........................... 4C15
11-68. AssemblingEnd Shield Sub-Assemblies .............. 4C16
11-69. Bench Run-up Test ......................... 4C16
11-70. Bench Hot Stabilation Output Test ................ 4C18
11-71. Voltage Regulator Servicing(Chrysler) .................... 4C19
11-72. Air Gap Adjustment ......................... 4C19
11-73. Contact ClearanceAdjustment ................... 4C20
11-74. Voltage Regulator Fusible WireReplacement . . . . . . . . 4C21
11-75. Voltage Regulator (Wico) .................. . . . . . . . . 4C21
11-76. CheckingVoltage Regulator .......... . . . . . . . . 4C21
11-77. Over Voltage Relay (Wico) ................. . . . . . . . . 4C22
11-78. CheckingOver Voltage Relay ......... . . . . . . . . 4C22
11-79. Checking Generator or Alternator BeltTension ..... . . . . . . . . 4C23
11-80. Starting Motor (Delco-Remy) ............... . . . . . . . . 4C24
11-81. Operation of Starting Motor .......... . . . . . . . . 4C24
11-82. Checking Starting Motor ............ . . . . . . . . 4D1

Revised: 10/3/83 4A9

 Aerofiche
Grid No.

11-83. Test and Maintenanceof Starting Motors . ............ 4D2

11-84. Inspection ............. ................. 4D2
11-85. No Load Test ................... .......... 4D2
11-86. Lock-Torque Test ...... .............. ..... . 4D3
11-87. Resistance Test .......... .... ..... . 4D4
11-88. Disassembly .............................. 4D4
11-89. Component Inspection and Repair . ............... 4D5
11-90. Assembly ............................... 4D6
11-91. Starting Motor ServiceTest Specification (Delco Remy) .... 4D6
11-92. Starting Motors (Prestolite) ..... ..................... . 4D7
11-93. Description .............................. 4D7
11-94. Operation ............................... 4D7
11-95. Maintenance ........... ........... 4D7
11-96. Overhaul ............................... 4D10
11-97. Removal ....... ........................ 4D10
11-98. Disassembly ............... . .. ..... 4D10
11-99. Brushes ................... ... ...... ... 4D11
11-100. Armature .... ........................ 4D11
11-101. Field Coils ... ............. ........... 4D12
11-102. Brush Holders ...................... ........ 4D12
11-103. Gear and Pinion Housing ...................... 4D12
11-104. Bendix Drive .................. ....... 4D12
11-105. Assembly ................ ................ 4D12
11-106. BenchTests ....... 4D13
11-107. Starting Motor Control Circuit . ........... 4D14
11-108. Starting Motor ServiceTest Specification (Prestolite) ...... 4D14
11-109. Battery ..... ................................. 4D15
11-110. ServicingBattery ........................... 4D15
11-111. Removalof Battery ......................... 4D15
11-112. Installation of Battery ................... ..... 4D15
11-113. ChargingBattery ................................ 4D16
11-114. Battery Box Corrosion Prevention . ................... 4D16
11-115. Starting Through External Power . ................... 4D17
11-116 Alternator System (Prestolite) ........ .............. 4D18
11-117. CheckingAlternator System .................... 4D18
11-118. Alternator Nomenclature ........ . 4D19
11-119. Alternator ServicePrecautions . ................. . 4D19
11-120. Description of Alternator ......... ............. 4D 19
11-121. Overhaulof Alternator .......... ............ . 4D20
11-122. Disassemblyof Alternator . ....... ........ .... 4D21
11-123. Inspection and Testing of Components ......... .... 4D22
11-124. Assemblyof Alternator ....................... 4D24
11-125. Testing of Alternator ........................ 4E1
11-126. Alternator ServiceTest Specifications (Prestolite) ....... . 4E2
11-127. CheckingAlternator Belt Tension . .................... 4E3
11-128. Instrument and Panel Lights ......... ....... .. . 4E3
11-129.. Removalof Dimmer Control Assembly ... ............ 4E3
11-130. Installation of Dimmer Control Assembly ............ 4E3

Revised: 10/3/83 4A10

 Aerofiche
Grid No.
11-131. Annunciator Panel ................................ 4E4
11-132. Description .............................. 4E4
11-133. Removalof Oil PressureSensor .................. 4E4
11-134. Installation of Oil PressureSensor ................. 4E4
11-135. Removalof Vacuum Sensor . ............... . 4E4
11-136. Installation of Vacuum Sensor ................... 4E5
11-137. Anti-CollisionLight (Rotating Beacon) ................... 4E5
11-138. Removal .......................... 4E5
11-139. Installation ............................. 4E5
11-140. Anti-CollisionLight (Strobe) .......................... 4E5
11-141. Description ................ 4E5
11-142. Removalof WingTip Strobe Light ................ 4E5
11-143. Installation of WingTip Strobe Light .............. 4E6
11-144. Removalof Fin Tip Strobe Light . ...... ... 4E6
11-145. Installation of Fin Tip Strobe Light . .......... 4E6
11-146. Removalof Strobe Power Supply . ........... 4E6
11-147. Installation of Strobe Power Supply ......... ....... 4E7
11-148. TroubleshootingProcedure . ............ 4E7

Reissued: 1/15/81 4A11

 TABLE XI-I. INDEX - ELECTRICAL SYSTEM SCHEMATICS

Aerofiche
System Figure Grid No.
Electrical System Schematic, PA-28-140, Serial Nos. 28-20000to
28-24999incl ............................................. 11-54 4F11
Electrical System Schematic, PA-28-140, Serial Nos. 28-25000to
28-7325052incl ........................................... 11-55 4F13
Electrical System Schematic, PA-28-150,-160, Serial Nos. 28-1
to 28-507 incl. ........................................... 11-56 4F15
Electrical System Schematic, PA-28-150,-160, Serial Nos. 28-508
to 28-670 incl. ........................................... 11-57 4F17
Electrical System Schematic, PA-28-150,-160, -180, Serial Nos.
28-671to 28-1760incl. ................ ............... 11-58 4F19
Electrical System Schematic, PA-28-150,-160, -180, Serial Nos.
28-1761to 28-3643incl...................................... 11-59 4F21
Electrical System Schematic, PA-28-150,-160,-180, Serial Nos.
28-3644to 28-4377incl................................... 11-60 4F23
Electrical System Schematic, PA-28-180,Serial Nos. 28-4378
to 28-5227incl .......................................... 11-61 4GI
Electrical System Schematic, PA-28-180, Serial Nos. 28-5228
to 28-7305063incl. ....................................... 11-62 4G3
Electrical System Schematic, PA-28-235, Serial Nos. 28-10003
to 28-10719incl. ......................................... 11-63 4G5
Electrical System Schematic, PA-28-235, Serial Nos. 28-10720
to 28-10762incl. ......................................... 11-64 4G7
Electrical System Schematic, PA-28-235, Serial Nos. 28-10763
to 28-11039incl. ........................................ 11-65 4G9
Electrical System Schematic, PA-28-235, Serial Nos. 28-11040
to 28-7310038incl. ....................................... 11-66 4G11
Electrical System Schematic, PA-28R-180, Serial Nos. 28-30005
to 28-30879incl. ......................................... 11-67 4G13
Electrical System Schematic, PA-28R-180, -200, Serial Nos.
28-30880to 28-7335054incl ............................... 11-68 4G15
Landing Gear Back-up Actuator Override Mechanism ........... 11-69 4G17
Landing Gear Back-up Actuator Override Mechanism .......... 11-70 4G 17
See Note on Grid No..................................... 4G19
A/C Air Blower, PA-28-140, Serial Nos. 28-7425001& up;
PA-28R-200, Serial Nos. 28-7435001& up;
PA-28-235, Serial Nos. 28-7410001& up;
PA-28-180, Serial Nos. 28-7405001& up .................... 11-107 4H10
Alternator, Starter, Cabin Light, Cigar Lighter and
External Power Receptacle, PA-28-140, Serial Nos. 28-25000
to 28-7325052incl. ..................................... 11-85
Alternator, Starter, Cabin Light, Cigar Lighter and
External Power Receptacle, PA-28-140, Serial Nos.
28-7325053to 28-7425454incl. ........................... 11-86

Reissued: 1/15/81 4A12

 .

oo

00

I0
0

6
0

4
~~~

.
 TABLE XI-I. INDEX - ELECTRICAL SYSTEM SCHEMATICS (cont)

Aerofiche
System Figure Grid No.

Stall Warning, PA-28-140, Serial Nos. 28-7625001& up;

PA-28R-200, Serial Nos. 28-7635001& up; PA-28-235,Serial Nos.
28-7610001& up ......................................... 11-138 4H23
Turn & Bank, PA-28-140,Serial Nos. 28-7325053& up ......... 11-121 4H 14
Turn & Bank, PA-28-180,Serial Nos. 28-7405001& up;
PA-28-235, Serial Nos. 28-7410001& up ........ ............ 11-122 4H 14
Turn & Bank, PA-28R-200, Serial Nos. 28-7335055& up........ 11-123 4H 14

Reissued: 1/15/81 4A16

 PIPER CHEROKEE SERVICE MANUAL

SECTIONXI

ELECTRICALSYSTEM

11-1. INTRODUCTION.This section contains instructions for correcting difficulties which

may arise in the operation of the electrical system in PA-28 series airplanes. It includes a
general description and function of each part of the system along with test and adjustments
of the various components. This does not include any electronics installations such as
Autopilot or radios. For Autopilot ServiceInformation, refer to Section XII of this manual.
Radio Service and Repairs may be found in the appropriate radio manufacturer's manuals.

11-2. DESCRIPTION. The electrical system is a 14-volt, direct current, single wire,
negative ground system. All electrical equipment is grounded to the metal structure of the
airplane, therefore, the structure takes the place of the second wire. A 12-volt battery is
incorporated in the system to furnish power for starting and as a reserve power source in
case of generator or alternator failure. The battery and generator or alternator are both
connected to the bus bar, from which all electrical equipment is powered, with the
exception of the starter which receives its power from the load side of the battery. The
master switch controls the battery relay and field circuit. The master switch must be on
before any electrical equipment will operate. The airplane can be equipped with standard
navigationlights, rotating beacon and one landing light located in the nose cowl.

11-3. TROUBLESHOOTING.Troubles peculiar to the electrical system are listed in Table

XI-I at the back of this section along with their probable causes and suggestedremedies. The
wiring diagrams included at the end of this section will give physical breakdown of the
different electrical circuits used in this airplane.
After the trouble has been corrected, check the entire electrical system for security and
operation of its components.

WARNING

All checks and adjustments of the generator or alternator

and/or its components should be made with the engine
stopped. Therefore, to complete some checks or adjustments,
it will be necessary to remove these units from the airplane
and place on a test stand.

Reissued: 1/15/81 ELECTRICAL SYSTEM

4A17
 PIPER CHEROKEE SERVICE MANUAL

C317
NOTE

THIS IS A TYPICAL WIRING

DIAGRAM FOR GENERAL
REFERENCE ONLY. FOR DETAILED
SCHEMATIC, SEE TABLE XI-I.

VOLTAGE
REGULATOR

BAT F GENERATOR
T CIRCUITPROTECTOR
35AMP

- -
SHIE

i
MASTER

MASTERSWITCH
. .CONTACTOR

_ BATTERY

AMMETER

TO BUSBAR SELINOID
STARTER
SWITCH

Figure11-1. Generatorand Starter System(Typical)

Reissued: 1/15/81 4A18 STEM

ELECTRICAL SYSTEM
 PIPER CHEROKEE SERVICE MANUAL

A143 NOTE

THIS IS A TYPICAL WIRING

DIAGRAM FOR GENERAL
REFERENCE ONLY. FOR DETAILED
SCHEMATIC, SEE TABLE XI-I.

REGULATOR

I I
I

F
BAT. GEN.

"A"

BATTERY

LOAD
GENERATOR

Figure 11-2. Generator WiringDiagram(Typical)

Reissued: 1/15/81 4A19 ELECTRICAL SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

11-4. GENERATOR SYSTEM .(Delco-Remy.)

11-5. DESCRIPTION OF GENERATOR SYSTEM. The generator is of the two

brush, shunt type and is controlled by a regulator operating on the principal of
inserting resistance into the generator field circuit to cause a reduction of gen-
erator voltage and current output. With each generator is the regulator assem-
bly, composed of a voltage regulatorand current regulator, to prevent overload-
ing of the battery and electrical circuits. Also with the regulator is a reverse
current cutout to prevent the generator from beingmotorized by the battery when
the generator output drops below the battery voltage. Field current between the
regulator and generator maybe broken through the use of the master switch. The
generator is located on the front lower right side of the engine and utilizes a belt
drive from the engine crankshaft. The generator voltage regulator is located on
the engine firewall. The best assurance of obtaining maximum service from the
generator with minimum trouble is to follow a regular inspection and maintenance
procedure.

11-6. CHECKING GENERATOR SYSTEM. Inanalyzingcomplaints of generator-

regulator operation, any of several basic conditions may be found.
a. Fully Charged Battery and Low Charging Rate: This indicates normalgen-
erator-regulator operation. Regulator settingmay be checked as outlined inpara-
graph 11-23.
b. Fully Charged Batteryand a HighChargingRate: This indicatesthatthevolt-
age regulator is not reducing the generator output as it should. A high charging
rate to a fully charged battery will damage the battery and the accompanying high
voltage is very injurious to all electrical units.
This operating condition may result from:
1. Improper voltage regulator setting.
2. Defective voltage regulator unit.
3. Grounded generator fieldcircuit (in eithergenerator, regulatoror wir-
ing).
4. Poor ground connection at regulator.
5. High temperature which reduces the resistance of the battery to charge
so that it will accept a high charging rate even though the voltage regulator set-
ting is normal.
If the trouble is not due to high temperature, determine the cause of trouble
bydisconnecting the lead from the regulator "F" terminal with the generator op-
erating at medium speed. If the output remains high, the generator field i s ground -
ed either in the generator or in the wiring harness. If the output drops off, the
regulatoris at fault, and it should be checked for a high voltage settingorgrounds.

Reissued: 1/15/81 4A20 ELECTRICAL SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

c. Low Battery and High Charging Rate: This is normal generator-regulator

action. Regulator settings may be checked as outlined in paragraph 11-23.
d. Low Battery and Low or No Charging Rate: This condition could be due to:
1. Loose connections, frayed or damaged wires.
2. Defective battery.
3. High circuit resistance.
4. Low regulator setting.
5. Oxidized regulator contact points.
6. Defects within the generator.
If the condition is not caused by loose connections, frayed or damaged wires,
proceed as follows to locate cause of trouble.
To determine whether the generator or regulator is at fault, momentarily
ground the "F" terminal of the regulator and increase generator speed. If the
output does not increase, the generator is probably at fault and it should be check -
ed as outlined in paragraph 11-8. If the generator output increases, the trouble
is due to:
1. A low voltage (or current) regulator setting.
2. Oxidized regulator contactpointswhich insert excessive resistance into
the generator field circuit so that output remains low.
3. Generator field circuit open within the regulator at the connections or
in the regulator wiring.
e. Burned Resistances, Windings or Contacts: These result from open circuit
operation or high resistance in the charging circuit. Where burned resistances,
windings or contacts are found, always check wiring before installing a new reg-
ulator. Otherwise the new regulator may also fail in the same way.
f. Burned Relay Contact Points: This is due to reversed generator polarity.
Generator polarity must be corrected as explained in paragraph 11-21 after any
checks of the regulator or generator or after disconnecting and reconnecting leads.

11-7. ADJUSTMENTS, TESTS AND MAINTENANCE OF GENERATOR SYSTEM.

The best assurance of obtaining maximum service from generators with
minimum trouble is to follow a regular inspection and maintenance procedure.
Periodic lubrication where required, inspection of the brushes and commutator
and checking of the brush spring tension are essentials in the inspection proce-
dure. In addition, disassembly and thorough overhauling of the generator at pe-
riodic intervals are desirable as a safeguard against failures from accummula-
tions of dust and grease and normal wear of parts. This is particularly desir-
able on installations where maintenance of operating schedules is of special im-
portance. In addition to the generator itself, the external circuits between the
generator, regulator and battery must be kept in good condition since defective
wiring or loose or corroded connections will prevent normal generator and reg-

Reissued: 1/15/81 4A21 ELECTRICAL SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

C359
BLASTTUBE
COMMUTATOR

TERMINALS

01

I
FIELD COMMUTATOR
DRIVE END FRAME COIL END FRAME

Figure 11-3. Sectional View of Generator

ulator action. At times it maybe found necessary to adjust the voltage regulator.
More detailed inspection and overhaul instructions may be found in the paragraphs
to follow.

11-8. TEST AND MAINTENANCE OF GENERATOR (Delco-Remy).

11-9. INSPECTION OF GENERATOR.

a. At periodic intervals the generator should be inspected to determine its con-
dition. The frequency with which this should be done will be determined by the
type of service in which it is used. High speed operation, excessive dust or dirt,
high temperatures and operating the generator at or near full output most of the
time are all factors which increase bearing, commutator, and brush wear. Gen-
erally speaking, the units should be inspected at approximately 100 hour intervals.

Reissued: 1/15/81 4A22 ELECTRICAL SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

The inspection procedure follows.

b. First inspect the terminals, external connections and wiring, mounting,
pulley and belt. Then remove the cover band so that the commutator, brushes
and internal connections can be inspected. If the commutator is dirty it may be
cleaned with a strip of No. 00 sandpaper. Never use emery cloth to clean the
commutator.
c. The sandpaper may be used byholding it against the commutatorwith a wood
stick while the generator is rotated, moving it backand forth across the commu-
tator. Gum and dirt will be sanded off in a few seconds. All dust should be blown
from the generator after the commutator has been cleaned. A brush seating stone
can also be used to clean the commutator.
d. If the commutator is rough, out of round, or has high mica, the generator
must be removed and disassembled so that the armature can be turned down in a
lathe and the mica undercut.
e. If the brushes are worn down to less than half their original length, they
should be replaced. Compare the old brush with anewone todetermine howmuch
it is worn. New brushes should be seated to make sure that they are in good con-
tact with the commutator. A convenient tool for seating brushes is a brush seat -
ing or bedding stone. This is a soft abrasive material which, when held against
a revolving commutator, disintegrates so that particles are carried under the
brushes and wear their contacting faces to the contour of the commutator in a few
seconds. All dust should be blown fromthegeneratorafter the brushes are seated.
f. The brush spring tension must be correct since excessive tension will cause
rapid brush and commutator wear, while low tension causes arcing and burning
of the brushes and commutator. Brush springtension can be checked with a spring
gauge hooked on the brusharm or brush attaching screw. Correction can be made
by bending the brush spring as required. If the brush spring shows evidence of
overheating (blued or burned), do not attempt to readjust it, but install a new
spring. Overheating will cause a spring to lose its temper.
g. The belt should bechecked to make sure that it is in good condition and has
correct tension. Low belt tensionwill permit belt slippagewith a resulting rapid
belt wear and low or erratic generator output. Excessive belt tension will cause
rapid belt and bearing wear. Check the tension of a new belt 25 hours after in-
stallation. Proper adjustment is given in paragraph 11-79.

11-10. SHUNT GENERATOR OUTPUT. Themaximumoutputofshuntgenerators

is determined by the current setting of the current regulator with which the shunt
generator is used. Checking of this setting is discussed in the applicable regula-
tor bulletin.

Reissued: 1/15/81 4A23 ELECTRICAL SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

11-11. CHECKING DEFECTIVE GENERATORS. If the generator-regulator sys-

tem does not perform according to specifications (generator does not produce
rated output or produces excessive output), and the trouble has been isolated in
the generator itself by following the procedure outlined in paragraph 11-6, the
generator may be checked further as follows to determine the location of trouble
in the generator.

11-12 NO OUTPUT.
a. If the generator will not produce any output, remove the cover band and
check the commutator, brushes and internal connections. Sticking brushes, a
dirty or gummycommutator (Refer to paragraph 11-20.)orpoor connections may
prevent the generator from producing any output. Thrown solder on the cover
band indicates that the generator has been overloaded (allowed to produce exces-
sive output) so it has overheated and melted the solder at the commutator riser
bars. Solder thrown out often leads to an open circuit and burned commutator
bars. If the brushes are satisfactorily seated and are making good contact with
the commutator, and the cause of trouble is not apparent, use a set of test points
and a test lamp as follows to locate the trouble (leads must be disconnected from
generator terminals).
b. Raise the grounded brush from the commutator and insulate with a piece of
cardboard. Check for grounds with test points from the generator main brush to
the generator frame. If the lamp lights, it indicates that the generator is inter-
nally grounded. Location of the ground can be found by raising and insulating all
brushes from the commutator and checking the brush holders, armature, com-
mutator and field separately. Repair or replace defective parts as required.
(Refer to paragraph 11-18.)

NOTE

If a grounded field is found, check the regulator con-

tact points, since a grounded field may have permit-
ted an excessive field current which will have burned
the regulator contact points. Burned regulator points
should be cleaned or replaced as required.

c. If the generator is not grounded, check the field for an open circuit with a
test lamp. The lamp should light when one test point is placed on the field ter-
minal or grounded field lead and the other is placed on the brush holder to which
the field is connected. If it does not light, the circuit is open. If the open is due
to a broken lead or bad connection, it can be repaired, but if the open is inside
one of the field coils, it must be replaced.

Reissued: 1/15/81 4A24 ELECTRICAL SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

d. If the field is not open, check for a short circuit in the field by connecting
a battery of the specified voltage and an ammeter in series with the field circuit.
Proceed with care, since a shorted field may draw excessive current which might
damage the ammeter. If the field is not within specification, new field coils will
be required. (Refer to Paragraph 11-16.)

NOTE

If a shorted field is found, check the regulator contact

points, since a shorted field may have permitted ex-
cessive field current whichwould have caused the reg-
ulator contact points to burn. Clean or replace points
as required.

e. If the trouble has not yet been located, check the armature for open and
short circuits. Open circuits in the armatureareusually obvious, since the open
circuited commutator bars will arc every time they pass under the generator
brushes so that they will soon become burned. If the bars are not too badly burn-
ed and the open circuit can be repaired, the armature can usually be saved. In
addition to repairing the armature, generator output must be brought down to
specifications to prevent overloading by readjustment of the regulator.
f. Short circuits in the armature are located by use of a growler. The ar-
mature is placed in the growler and slowly rotated (while a thin strip of steel such
as a hacksaw blade is held above the armature core). The steel strip will vibrate
above the area of the armature core in which short circuited armature coils are
located. If the short circuit is obvious, it can often be repaired so that the ar-
mature can be saved.

11-13. UNSTEADY OR LOW OUTPUT. If the generator produces a low or un-

steady output, the following factors should be considered:
a. A loose drive belt will slip and cause a low or unsteady output.
b. Brushes which stick in their holders, or low brushspring tension will pre-
vent good contact between the brushes and commutator so that output will be low
and unsteady. This will also cause arcing and burning of the brushes and com-
mutator.
c. If the commutator is dirty, out of round, or has high mica, generator out-
put is apt to be low and unsteady. The remedy here is to turn the commutator
down in a lathe and undercut the mica. Burned commutator bars may indicate an
open circuit condition in the armature as already stated above. (Refer to Para-
graph 11-12.)

Reissued:1/15/81 4B1 ELECTRICAL SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

11-14. EXCESSIVE OUTPUT.

a. When a generator produces excessive output on an application, the proce-
dure for determining whether the trouble is in the generator, regulator, or else-
where is outlined in paragraph 11-6. If the generator output remains high, even
with the "F" terminal lead disconnected, then the trouble is in the generator it-
self, and it must be further analyzed to locate the source of trouble.
b. In the systemwhich has thegenerator fieldcircuit groundedexternally, ac-
cidental internal grounding of the field circuit would prevent normal regulation so
that excessive output might be produced by the generator. On this type of unit,
an internally grounded field which would cause excessive output may be located
by use of test points connected between the "F" terminal and thegenerator frame.
Leads should be disconnected from the "F" terminal and the brush to which the
field lead is connected inside the generator should be raised from the commu-
tator before this test is made. If the lamp lights, the field is internallygrounded.
.If the field has.become grounded because the insulation on a field lead has worn
away, repair can be made by reinsulating the lead. It is also possible to make
repair where the ground has occurred at the pole shoes by removing the field coils
and reinsulating and reinstalling them. A ground at the "F" terminal stud can be
repaired by installing new insulating washers or bushings.

NOTE

If battery temperature is excessive, battery over-

charge is apt to occur, even though regulator settings
are normal. Under this condition, it is permissible
to reduce the voltage regulator setting as explained in
the applicable bulletin pertaining to the regulator used
on the application.

11-15. NOISY GENERATOR. Noise emanating from agenerator may be caused

by a loose mounting, drive pulley, or gear; worn or dirty bearings: or improp-
erly seated brushes. Dirty bearings may sometimes be saved by cleaning and
relubrication, but worn bearings should be replaced. Brushes can be seated as
explained in paragraph 11-9. If the brush holder is bent, it may be difficult to
reseat the brush so that it will function properly without excessive noise. Such
a brush holder will require replacement.

Reissued: 1/15/81 4B2 ELECTRICAL SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

11-16. DISASSEMBLY, REPAIR AND REASSEMBLY. Normally, disassembly

should proceed only so far as is necessary to make repair or replacement of the
defective parts. For example, the field coils should be checked for opens, shorts,
or grounds before being removed from the field frame. They should be removed
only if they require repair or replacement.

11-17. FIELD COIL REMOVAL. Fieldcoilscanbe removedfromthefieldframe

most easily by use of a pole shoe screw driver. It is also advisable to use a pole
shoe spreader, since this prevents distortion of the field frame. The pole shoe
screw driver permits easy loosening and removal of the pole shoe screws so that
the pole shoes and field coils can be taken out of the field frame. The pole shoe
sc rew driver and spreader should be used on reassembly of the field frame. Ca re -
ful reassembly is necessary to prevent shorting orgrounding of the field coils as
the pole shoes are tightened into place.

11-18. INSPECTIONAND REPAIR OF PARTS. The armature or field should not

be cleaned in any degreasing tank or by use of degreasing compounds, since this
might damage insulation so that a short or ground would subsequently develop.
Sealed ball bearings do not require cleaning or relubrication. Other generator
parts should be cleaned and carefully inspected for wear and other damage. Any
defective parts should be repaired or replaced. On reassembly all soldered elec -
trical connections should be made with rosin flux. Acid flux must never be used
on electrical connections.

11-19. FIELD COIL SERVICE.

a. The field coils should be checked for grounds, opens or shorts as already
explained in paragraph 11-12.
b. Grounded field coils may sometimes be repaired by removing them so they
can be reinsulated. Care must be used to avoid excessive bulkiness when ap-
plying new insulation, since this might cause the pole shoe to cut through and
cause another ground when the coils are reinstalled.
c. Usually if a field coil is open or shorted internally it will require replace-
ment, since it is difficult to repair such a defect.
d. To remove or replace field coils in the field frame, the use of a pole shoe
spreader and screw driver is recommended.

Reissued:1/15/81 ELECTRICAL SYSTEM

4B3
 PIPER CHEROKEE SERVICE MANUAL

11-20. ARMATURE SERVICE.

a. The armature should be checked for opens, shorts and grounds as explained
in followingparagraphs. If the armature commutator is worn, dirty, out of round,
or has high mica, the armature should be put in a lathe so the commutator can be
turned down and the mica undercut. The mica should be undercut .031 of an inch
and the slots cleaned out carefully to remove any trace of dirt or copper dust. As
a final step in this procedure, the commutator should be sanded lightly with No.
00 sandpaper to remove any slight burrs that might be left as a result of the un-
dercutting procedure.
b. Open circuited armatures can often be saved when the open is obvious and
repairable. The most likely place an open will occur is at the commutator riser
bars. This usually results from overloading of the generator which causes over-
heating and melting of the solder. Repair can be effected by resoldering the leads
in the riser bars (usingrosin flux) and turning down the commutator in a lathe to
remove the burned spot and then undercutting the mica as explained in the pre-
vious paragraph. In some heavy-duty armatures, the leads are welded into the
riser bars and these cannot be repaired by resoldering.
c. Short circuits in the armature are located by use of a growler. When the
armature is revolved in the growler, with a steel strip such as a hacksaw blade
held above it, the blade will vibrate above the area of the armature core in which
the short is located. Copper or brush dust in the slots between the commutator
bars sometimes causes shorts between bars which can be eliminated by cleaning
out the slots. Shorts at cross-overs of the coils at the core endcan often be elim-
inated by bending wires slightly and reinsulating the exposed bare wire.
d. Grounds in the armature are detectedby use of atest lamp and test points.
If the lamp lights when one test point is placed on the commutator with the other
point on the core or shaft, the armature is grounded. Grounds occur as a result
of insulation failure, which is often brought on by overloading and consequent
overheating of the generator. Repairs can sometimes be made if grounds are at
core ends (where coils come out of slots) by placing insulating strips between
core and coil which has grounded.

11-21. POLARIZING GENERATOR. After a generator has been repaired and

reinstalled or at any time after a generator has been tested, it must be repolar-
ized to make sure that it has the correct polarity with respect to the battery it is
to charge. Failure to repolarize the generator may result in burned relay con-
tact points, a run-down battery and possibly serious damage to the generator it-
self. The procedure to follow in correcting generator polarity depends upon the
generator-regulatorwiringcircuits; that is, whether the generator field is inter-
nally grounded or is grounded through the regulator. (Refer to paragraph 11-30. )

Reissued: 1/15/81 4B4 ELECTRICAL SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

11-22. GENERATOR SERVICE TEST SPECIFICATIONS. Delco-Remy specifi-

cations for 14 volt generators installed on PA-28 series airplanes are as follows:

Generator 1101900

Delco-Remy,
Ref, Service Bulletin 1G-150

Brush Spring Tension 24 oz.

Field Current (80° F)

Amps 1.62 to 1.72
Volts 12

Cold Output
Amps 35
Volts 14.0
Approx. RPM 3100

COLD OUTPUT: Cold output data applies to generators at 80 degrees F,

and with brushes well seated. Variations in temperature and brush seating
as well as the condition of the generator may cause deviations of 100 RPM
or more from rated speed.
HOT OUTPUT: Hot output is maximum output as controlled bycurrent reg-
ulator.

ELECTRICAL SYSTEM
Reissued: 1/15/81 4B5
 PIPER CHEROKEE SERVICE MANUAL

11-23. REGULATOR.

11-24. DESCRIPTION OF REGULATOR. The regulator shown in Figure 11-4

consists of a cutout relay, a voltage regulator and a current regulator unit. The
cutout relaycloses the generator to batterycircuit when the generator voltage is
sufficient to charge the battery, and it opens the circuit when the generator slows
down or stops. The voltage regulator unit is a voltage-limiting device that pre-
vents the system voltage from exceeding a specified maximum and thus protects
the battery and other voltage-sensitive equipment. The current regulator unit is
a current-limiting device that limits the generator output so as not to exceed its
rated maximum.

11-25. CUTOUT RELAY.

a. The cutout relay (Refer to Figure 11-4.) has twowindings, a series winding
of a few turns of heavy wire and a shunt winding of many turns of fine wire (shown
in dashed lines). The shunt winding is connected across the generator so that
generator voltage is impressed upon it at all times. The series winding is con-
nected in series with the charging circuit so that all generator output passes
through it. The relay core and windings are assembled into a frame. A flat steel
armature is attached to the frame by a flexible hinge so that it is centered just
above the stationary contact points. When the generator is not operating, the ar-
mature contact points are held away from the stationary points by the tension of
a flat spring riveted on the side of the armature.
b. When the generator voltage builds up a value great enough to charge the
battery, the magnetism induced by the relay windings is sufficient to pull the ar-
mature toward the core so that the contact points close. This completes the cir-
cuit between the generator and battery. The current which flows from the gen-
erator to the battery passes through the series winding in a direction to add to the
magnetism holding the armature down and the contact points closed.
c. When the generator slows down or stops, current begins to flow from the
battery to the generator.
d. This reverse flow of current through the series winding causes a reversal
of the series winding magnetic field. The magnetic field of the shunt winding does
not reverse. Therefore, instead of helping each other, the two windings now
oppose so that the resultant magnetic field becomes insufficient to hold the arm-
ature down. The flat spring pulls the armature away from the core so that the
points separate; this opens the circuit between the generator and battery.

Reissued: 1/15/81 4B6 ELECTRICAL SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

11-26. VOLTAGE REGULATOR. C360

CURRENT
a. The voltage regulator (Refer to REGULATOR
Figure 11-4.) has two windings assem-
/ VOLTAGE
bled on a single core, a shunt winding __ REGULATOR
consisting of many turns of fine wire
(shown in dashed lines) which is shunt-
ed across the generator, and a series
winding of a few turns of relatively
heavy wire which is connected in series CUTOUT
RELAY
with the generator field circuit when
the regulator contact points are closed.
b. The windings and core are as- BATTERY GENERATOR FIELD
sembled into a frame. A flat steel TERMINAL TERMINAL TERMINAL
armature is attached to the frame by a
flexible hinge so that it is just above Figure 11-4. Current/Voltage
the end of the core. The armature Regulator
contains a contact point which is just
beneath a stationary contact point. When the voltage regulator is not operating,
the tension of a spiral spring holds the armature away from the core so that the
points are in contact and the generator field circuit is completed to ground through
them.
c. When the generator voltage reaches the value for which the voltage regu-
lator is adjusted, the magnetic field produced by the two windings (shunt and se-
ries) overcomes the armature spring tension and pulls the armature down so that
the contact points separate. This inserts resistance into the generator field cir-
cuit so that the generator field current and voltage are reduced. Reduction of the
generator voltage reduces the magnetic field of the regulator shunt winding. Also,
opening the regulator points opens the regulator series winding circuit sothat its
magnetic field collapses completely. The consequence is that the magnetic field
is reduced sufficiently to allow the spiral spring to pull the armature away from
the core so that the contact points again close. This directly grounds the gener-
ator so that generator voltage and output increase. The above cycle of action
again takes place and the cycle continues at a rate of 50 to 200 times a second,
regulating the voltage to a predetermined value. With the voltage thus limited,
the generator supplies varying amounts of current to meet the varying states of
battery charge and electrical load.

Reissued: 1/15/81 4B7 ELECTRICAL SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

11-27. CURRENT REGULATOR

a. The current regulator (Refer to Figure 11-4.) has a series winding of a few
turns of heavy wire which carries all generator output. The winding core is as-
sembled into a frame. Aflat steel armature is attached to the frame by a flexible
hinge so that it is just above the core. The armature has a contact pointwhich is
just below a stationary contact point. When the current regulator is not operating,
the tension of a spiral spring holds the armature away from the core so that the
points are in contact. In this position the generator field circuit is completed to
ground through the current regulator contact points in series with the voltage reg-
ulator contact points.
b. When the load demands are heavy, as for example, when electrical devices
are turned on and the battery is in adischargedcondition, thevoltage may not in-
crease to a value sufficient to cause the voltage regulator to operate. Consequen-
tly, generator output will continue to increase until the generator reaches rated
maximum current. This is the current value for which the current regulator is
set. Therefore, when the generator reaches rated output, this output, flowing
through the current regulator winding, creates sufficient magnetism to pull the
current regulator armature down and open the contact points. With the points
open, resistance is inserted into the generator field circuit so that the generator
output is reduced.
c. As soon as the generator output starts to fall off, the magnetic field of the
current regulator winding is reduced, the spiral spring tension pulls the arma-
ture up, the contact points close and directly connect the generator field to ground.
Output increases and the above cycle is repeated. The cycle continues to take
place while the current regulator is in operation 50 to 200 times a second, pre-
venting the generator from exceeding its rated maximum. When the electrical
load is reduced (electrical devices turned off or battery comes up to charge), then
the voltage increases so that the voltage regulator begins to operate and tapers
the generator output down. This prevents the current regulator from operating.
Either the voltage regulator or the current regulator operates at any one time -
the two do not operate at the same time.

11-28. RESISTANCES. The current and voltage regulator circuits use a common
resistor which is inserted in the field circuit when either the current or voltage
regulator operates. A second resistor* is connected between the regulator field
terminal and the cutout relay frame, which places it in parallel with the generator
field coils. The sudden reduction in field current occurring when the current or
voltage regulator contact points open, is accompanied by a surge of induced volt-
age in the field coils as the strength of the magnetic field changes. These surges

Reissued: 1/15/81 4B8 ELECTRICAL SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

are partially dissipated by the two resistors, thus preventing excessive arcing at
the contact points.
*(The second resistor is not present on all regulators. Many aircraft regulators
have this resistor omitted.)

11-29. TEMPERATURE COMPENSATION. Voltage regulators are compensated

for temperature by means of a bimetal thermostatic hinge on the armature. This
causes the regulator to regulate at a higher voltage when cold which partly com-
pensates for the fact that a higher voltage is required to charge a cold battery.
Many current regulators also have a bimetal thermostatic hinge on the armature.
This permits a somewhat highergenerator output when the unit is cold, but causes
the output to drop off as temperature increases.

11-30. REGULATOR POLARITY. Some regulators are designed for use with
negative grounded systems, while other regulators are designed for use with po-
sitive grounded systems. Usingthe wrong polarity regulator on an installation will
cause the regulator contact points to pit badlyand give short life. As a safeguard
against installation of the wrong polarity regulator, all regulators of this type
have the model number and the polarity clearly stamped on the end of the regu-
lator base. (Refer to paragraph 11-32, step e. )

11-31. REGULATOR MAINTENANCE.

11-32. MAINTENANCE INSTRUCTIONS.

a. Mechanical checks and adjustments (air gaps, point opening) must be made
with battery disconnected and regulator preferably off the aircraft.

CAUTION

The cutout relay contact points must never be closed

by hand with the battery connected to the regulator.
This would cause a high current to flow through the
units which would seriously damage them.

b. Electrical checks and adjustments may be made either on or off the air-
plane. The regulator must always be operated with the type generator for which
it is designed.
c. The regulator must be mounted in the operating position when electrical

Reissued: 1/15/81 4B9 ELECTRICAL SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

C359 C159
FILE AIR GAP
(CHECKWITH
POINT
JUST
TOUCHING)

CONTACT
TO CLEANCONTACTPOINTS MOUNTING SCREWS
(LOOSENUPPERCONTACT (LOOSENTO SETAIR GAP)
BRACKET
MOUNTINGSCREWS)

Figure 11-5. Use of Riffler File Figure 11-6. Voltage Regulator

to Clean Contact Points Air Gap

settings are checked and adjusted and it must be at operating temperature.

d. Specified generator speeds for testing and adjusting.
1. Voltage Regulator
(a) Operating speed
2. Current Regulator
(a) All generators must be operated at a speed sufficient to produce
current in excess of specified setting.
(b) Voltage of the generator must be kept high enough to insure suffi-
cient current output, but below the operating voltage of the voltage reg-
ulator unit.
e. After any tests oradjustments thegenerator on the airplane must be polar-
ized after leads are connected, but before the engine is started, as follows:
After reconnecting leads, momentarily connect a jumper lead between the
."GEN" and "BAT" terminals of the regulator. This allows a momentary surge
of current to flow through the generator which correctly polarizes it. Failure to
do this may result in severe damage to the equipment since reversed polarity
causes vibration, arcing and burning of the relay contact points.

11-33. CLEANING CONTACT POINTS. The contact points of a regulator will

not operate indefinitely without some attention. It has been found that a great
majority of all regulator trouble can be eliminated by a simple cleaning of the
contact points, plus some possible readjustment. The flat points should be clean-
ed with a spoon or riffler file. On negative grounded regulators which have the

Reissued: 1/15/81 4B10 ELECTRICAL SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

C318

Figure 11-7. Checking Voltage Figure 11-8. Checking Voltage

Setting Fixed Resistance Method Setting Variable Resistance Method

flat contact point on the regulator armatures, loosen the contact bracket mount-
ing screws so that the bracket can be tilted to one side. A flat file cannot be used
successfully to clean the flat contact points since it will not touch the center of
the flat point where point wear is most apt to occur. Never use emery cloth or
sandpaper to clean the contact points. Remove all the oxides from the contact
points but note that it is not necessary to remove any cavity that may have devel-
oped.

11-34. REGULATOR CHECKS AND ADJUSTMENTS.

11-35. VOLTAGE REGULATOR. Two checks and adjustments are required on

the voltage regulator; air gap and voltage setting.
a. Air Gap: To check air gap, push armature down until the contact points are
just touchingand then measure air gap. (Refer to Figure 11-6.) Adjust by loosen-
ing the contact mounting screws and raising or lowering contact bracket as re-
quired. Be sure the points are lined up and tighten screws after adjustment.
b. Voltage Setting: There are two ways to check the voltage setting; the fixed
resistance method and the variable resistance method. (Refer to Figures 11-7
and 11-8.)
1. Fixed Resistance Method:
(a) Connect a fixed resistance between the battery terminal and ground
as shown in Figure .11-7 after disconnecting the battery lead from the

Reissued: 1/15/81
4B11 ELECTRICAL SYSTEM
 PIPER CHEROKEE SERVICE MANUAL

C36 battery terminal of the regu-

lator. The resistance must
ADJUSTINGSCREW
( TO ADJUST
TURN SETTING) be 1-1/2 ohms for 14volt
units. It must be capable of
carrying 10 amperes without
any change of resistance with
temperature changes .
(b) Connect avoltmeterfrom
regulator "BAT" terminal to
ground.
(c) Place the thermometer
within 1/4 inch of regulator
cover to measure regulator
ambient temperature.
(d) Operate generator at
specified speed for 15 minutes
Figure 11-9. Adjusting Voltage with regulator cover in place
Regulator Setting to bring the voltage regulator
to operating temperature.
(e) Cycle the generator:
Method 1: Move voltmeter lead from "BAT" to "GEN" terminal of
regulator. Retard generator speed until generator voltage is re-
duced to 4-volts. Move voltmeter lead back to "BAT" terminal of
regulator. Bring generator back to specified speed and note voltage
setting.
Method 2: Connect a variable resistance into the field circuit as in
Figure 11-7. Turn out all resistance. Operate generator at spec-
ified speed. Slowly increase (turn in) resistance until generator
voltage is reduced to 4-volts. Turn out all resistance again and
note voltage setting (with voltmeter connected as in Figure-II-7).
Regulator cover must be in place.
(f) Note the thermometer reading and select the Normal Range of Volt-
age for this temperature as listed in specifications paragraph 11-43.
(g) Note the voltmeter reading with regulator cover in place.
(h) To adjust voltage setting, turn adjusting screw. (Refer to Figure
11-9.) Turn clockwise toincrease setting andcounterclockwise to de-
crease setting.

Reissued:1/15/81 4B12 ELECTRICAL SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

CAUTION

If adjusting screw is turned down (clockwise) beyond

range, spring support may not return when screw is
backed off. In such case, turn screw counterclock-
wise until there is ample clearance between screw head
and spring support. Then bend spring supportup care-
fully until it touches the screw head. Final setting of
the unit should always be made by increasing spring
tension, never by reducing it. If setting is too high,
adjust unit below required value and then raise to ex-
act settingby increasingthe spring tension. After each
adjustment and before taking reading, replace the reg-
ulator cover and cycle the generator.

2. Variable Resistance Method:

(a) Connect ammeter and 1/4-ohm variable resistor in series with the
battery as shown in Figure 11-8.

NOTE

It is very important that the variable resistance be

connected at the "BAT" terminal as shown in Figure
11-7 rather than at the "GEN" terminal even though
these terminals are in the same circuit. An examin-
ation of the wiring diagram, Figure 11-2, will show
that regulation begins at the point where the shunt
windings are connected to the series circuit. Any
small resistance added to the circuit between the gen-
erator and this point will simply be offset by a rise in
generator voltage without affecting the output shown at
the ammeter.

(b) Connect voltmeter between "BAT" terminal and ground.

(c) Place thermometer within 1/4 inch of regulator cover to measure
regulator ambient temperature.
(d) Operate generator at specified speed. Adjust variable resistor un-
til current flow is 8 to 10-amperes. If less current than is required
above is flowing, it will be necessary to turn on airplane lights to per-
mit increased generator output. Variable resistance can then be used
to decrease current flow to the required amount.
Allow generator to operate at this speed and current flow for 15

Reissued: 1/15/81 ELECTRICAL SYSTEM

4B13
 PIPER CHEROKEE SERVICE MANUAL

AIR GAP C360 UPPERARMATURESTOP

AIR GAP (BENDTO ADJUST

ADJUSTING
SCREWS
(LOOS TO SETAIRGAP)

POINTOPENING

Figure 11-10. Cutout Relay Air Gap Figure-11-11. Cutout Relay Point
Check and Adjustment Opening Check and Adjustment

minutes with regulator cover in place in order to bring the voltage reg-
ulator to operating temperature.
(e) Cycle the generator by either method listed in "Fixed Resistance
Method" of "Voltage Setting" procedure.
(f) Note the thermometer reading and select the "Normal Range" of
voltage for this temperature as listed in specifications paragraph 11-43.
(g) Note the voltmeter reading with regulator cover in place.
(h) Adjustvoltage regulator as requiredasdescribed in step(h) of"Fix-
ed Resistance Method of "Voltage Setting Procedure." In using the vari -
able resistance method, it is necessary to readjust the variable resis-
tance after each voltage adjustment to assure that 8 to 10 amperes are
flowing. Cycle generator after each adjustment before reading voltage
regulator setting with cover in place.

11-36. CUTOUT RELAY. The cutout relay requires three checks and adjust-
ments: air gap, point opening and closing voltage. The air gap and point open-
ing adjustments must be made with the battery disconnected.
a. Air Gap: Place fingers on armature directly above core and move armature
down until points just close and then measureairgap between armature and center
of core. (Refer to Figure 11-12.) On multiple contact point relays, make sure
that all points close simultaneously. If they do not, bend spring finger so they
do. To adjust air gap, loosen two screws at the back of relay and raise or lower
the armature as required. Tighten screws after adjustment.

Reissued: 1/15/81
4B14 ELECTRICAL SYSTEM
 PIPER CHEROKEE SERVICE MANUAL

ADJUSTING
SCEW

Figure 11-12. Checking Cutout Relay Figure 11-13. Adjustment of

Closing Voltage Cutout Relay Closing Voltage

b. Point Opening. Check point opening and adjust by bending the upper arma-
ture stop. (Refer to Figure 11-11.)
c. Closing Voltage: Connect regulator to proper generator and battery. Con-
nect voltmeter between the regulator "GEN" terminal and ground. (Refer to Fig-
ure 11-12.).
Method 1: Slowly increase generator speed and note relay closing voltage.
Decrease generator speed and make sure the cutout relay points open.
Method 2: Make connections as in step c; but, in addition, add a variable
resistor connected into the field circuit. (Refer to Figure 11-12.) Use a
25-ohm 25-watt resistor. Operate generator at medium speed with vari-
able resistance turned all in. Slowly decrease (turn out) the resistance un-
til cutout relay points close. Note closing voltage. With cover in place,
slowly increase (turn in) resistance to make sure points open.
d. Adjust closingvoltage by turning adjusting screw. (Refer to Figure 11-13.)
Turn screw clockwise to increase setting and counterclockwise to decrease set-
ting.

11-37. CURRENT REGULATOR. Two checks and adjustments are required on

the current regulator. air gap and current setting.
a. Air Gap: Check and adjust in exactly the same manner as for the voltage
regulator.
b. Current Setting: Current regulator setting on current regulators having
temperature compensation should be checked by the following method:

Reissued: 1/15/81 4B15 ELECTRICAL SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

C321 C321

TO REGULATOR
REGULATOR
CONNECT

Figure 11-14. Checking Current Figure 11-15. Checking Current

1. Load Method:
(a) Connect ammeter into charging circuit as in Figure 11-14.
(b) Turn on all accessory load (lights, radio, etc. ) and connect an ad-
ditional load across the battery (such as a carbon pile or band of lights)
so as to drop the system voltage approximately one volt below the volt-
age regulator setting.
(c) Operate generator at specified speed for 15 minutes with cover in
place. (This establishes operating temperature; see steps (c) and (d)
in paragraph 11-32.) If current regulator is not temperature-compen-
..sated, disregard 15 minute warm-up period.
(d) Cycle generator and note current setting.
(e) Adjust in same manner as described for voltage regulator. (Refer
to Figure 11-9.))
2. Jumper Lead Method: (Use onlyforcurrent regulators without temper-
ature compensation.)
(a) Connect ammeter into charging circuit as in Figure 11-15.
(b) Connect jumper leadac ross voltage regulator points as
in Figure
11-15.
(c) Turnon all lights and access ories or load battery as in (b) und er
Load Method:
(d) Operate generator at specified speed and note current setting.
(e) Adjust in same manner as described for thevoltage regulator. (Re-
fer to Figure 11-9.))

ELECTRICAL SYSTEM
Reissued:1/15/81 4B16
 PIPER CHEROKEE SERVICE MANUAL

11-38. REPAIRS.

11-39. REGULATOR SPRING REPLACEMENT. If it becomes necessary to re-

place the spiral spring on either the current or voltage regulator unit, the new
spring should first be hooked on the lower spring support and then stretched up
until it can be hooked at the upper end. Stretch the spring only by means of a
screw driver blade inserted between the turns (or in a similar manner). Do not
pry the spring into place as this is likely to bend the spring support. After in-
stalling a new spring, readjust the unit setting as already described.

11-40. RADIO BY-PASS CONDENSERS. The installation of radio by-pass con-

densers on the field terminal of the regulator or generator will cause the regula-
tor contact points to burn and oxidize so that generator output will be reduced and
a run down battery will result. If a condenser is found connected to either of these
terminals, disconnect the condenser and clean the regulator contact points as pre -
viously explained.

11-41. REGULATOR ARMATURE REPLACEMENT. The armature may be re-

placed by drilling out the two rivets attaching the armature to the regulator frame.
Support the frame to avoid bending. Center-punch the rivet heads and drill out
with a 3/32 inch drill. Attach the new armature with screws, lockwashers and
nuts supplied with the service armature. Assemble screws down so that they will
not ground against cover.

11-42. HIGH POINTS ON REGULATOR PERFORMANCE AND CHECKS.

a. The voltage regulator unit limits the voltage of the circuit, thus protecting
the battery, distributor points, lights and other accessories from high voltage.
b. The current regulator unit provides protection to the generator, preventing
it from exceeding its maximum rated output.
c. Never set the current regulator above the maximum specified output of the
generator.
d. Many of the regulators are designed to be used with a positive grounded
battery while others are designed to be used with a negative grounded battery
only. Never attempt to use the wrong polarity regulator on an application.
e. The majority of reported regulator troubles arise from dirty or oxidized
contact points which cause a reduced generator output. Clean the contact points
with a spoon or riffler file. Never use emery cloth or sandpaper to clean points.
f . Always make sure that the rubber gasket is in place between the cover and

ELECTRICAL SYSTEM
Reissued:1/15/81 4B17
 PIPER CHEROKEE SERVICE MANUAL

base before replacing the cover. The. gasket prevents entrance of moisture, dust
and oil vapors which might damage the regulator.
g. The proper testing equipment in the hands of a qualified mechanic is nec-
essary to assure proper and accurate regulator settings. Any attempt on the part
of untrained personnel to adjust regulators is apt to lead to serious damage to the
electrical equipment and should therefore be discouraged.
h. After any generator or regulator tests or adjustments, the generator must
be polarized as explained in paragraph 11-32, step e, in order to avoid damage
to the equipment.
i. It is recommended that following replacement or repair of a generator or
regulator they be adjusted on a test bench as a matched unit.

11-43. REGULATOR SERVICE TEST SPECIFICATIOS. Delco-Remy specifi-

cations for .14 volt regulators installed as standard equipment on PA-28 series
airplanes are as follows:

Regulator Model 1118704

Delco -Remy,
Ref, Service Bulletin 1R-116 (c)

Cutout Relay:
Air Gap .020 in.
Point Opening .020 in.
Closing Voltage 11.8 to 13.5-volts

Voltage Regulator
Air Gap .075 in.
Current Setting 13.9 to 14.7-volts

Current Regulator:
Air Gap .075 in.
Current Setting 33 to 37-amps

Reissued: 1/15/81 4B18 ELECTRICAL SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

11-44. ALTERNATORSYSTEM(Chrysler).

11-45. DESCRIPTIONOF ALTERNATORSYSTEM. The electrical power is supplied by

one 12-volt battery and a 14-volt direct current 37 or 60 ampere alternator. The alternator
is located on the front lower right side of the engine and utilizes a belt drive from the engine
crankshaft. Many advantages both in operation and maintenance are derived from this
system. The main advantage is that full electrical power output is available regardlessof
engine RPM.
The alternator has no armature or commutator and only a small pair of carbon brushes,
which make contact with a pair of copper slip rings.The rotating member of the alternator,
known as the rotor, is actually the field windings.The rotor draws only 1/13th (37 amp) or
1/20th (60 amp) of the current output. Therefore, there is very little friction and negligible
wear and heat in this area. The alternating current is converted to direct current by diodes
pressed into the end bell housing of the alternator. The diodes are highly reliable solid-state
devices,but are easily damaged if current flow is reversed through them.
The alternator system does not require a reversecurrent relay, because of the high back
resistance of the diodes and the inability of the alternator to draw current or motorize. A
current regulator is unnecessary because the windings have been designed to limit the
maximum current available.Therefore, the voltage regulator is the only control needed.
An additional latching circuit is used to help keep the master solenoid closed when the
battery voltage is low and the engine starter is being operated. This circuit routes voltage
from the alternator to the master solenoid coil, thus holding the master solenoid in the
closed position and allowing the starter to function. This circuit will also supply some
voltage to the battery. A diode is placed into this circuit to prevent the reverse flow of
current from the battery to the alternator.
The circuit breaker panel contains a 5 ampere circuit breaker marked ALT FIELD. If
the field circuit breaker trips, it will result in a complete shutdown of power from the
generating system. After a one or two minute cool-down period, the breaker can be reset
manually. If tripping reoccurs and holding the breaker down will not prevent continual
tripping, then a short exists in the alternator field.
Unlike previous systems, the ammeter does not indicate battery discharge,but displays
the load in amperes placed on the generating system. With all electrical equipment off
(except master) the ammeter will indicate the amount of chargingcurrent demanded by the
battery. This amount will vary, depending on the percentage of charge in the battery at the
time. As the battery becomes charged, the amount of current displayed on the ammeter will
reduce to approximately two amperes. The amount of current shown on the ammeter will
tell immediately whether or not the alternator system is operating normally, if the following
principles are kept in mind.

Reissued: 1/15/81 4B19 ELECTRICAL SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

C319

NOTE

THIS IS A TYPICAL WIRING

I
I DIAGRAM FOR GENERAL
REFERENCE ONLY. FOR DETAILED
SCHEMATIC, SEE TABLE XI-I.

ALTERNATOR

AMMETER
VOLTAGE
REGULATOR

6
—

l
ALTERNATORSOURCE- POWER
RELAY ENERGIZINGCIRCUIT

PA-28-140,Serial Nos. 28-20000to 28-24999incl.;

PA-28-150,-160, Serial Nos. 28-508 to 28-3643incl.;
PA-28-180, Serial Nos. 28-671 to 28-3643incl.;
PA-28-235,Serial Nos. 28-10002to 28-10762incl.

Figure 11-16. Early Alternator and Starter Systems (Typical)

4B20 ELE( SYSTEM

ELECTRICAL
Reissued: 1/15/81
 PIPER CHEROKEE SERVICE MANUAL

C320

NOTE

THIS IS A TYPICAL WIRING

DIAGRAM FOR GENERAL
REFERENCE ONLY. FOR DETAILED
SCHEMATIC, SEE TABLE XI-I.
I

RADIO

ALTERNATOR

ALTERNATOR SOURCE - POWE

RELAY ENERGIZING CIRCUIT
PA-28-140,Serial Nos. 28-25000and up;
PA-28-150,-160, -180, Serial Nos. 28-3644and up;
PA-28-235,Serial Nos. 10763and up and PA-28R.

Figure 11-17. Later Alternator and Starter Systems (Typical)

Reissued:1/15/81 4B21 ELECTRICAL SYSTEM

SYSTEM
Reissued: 1/15/81 ELECTRICAL SYSTEM
 PIPER CHEROKEE SERVICE MANUAL

NOTE

The amount of current shown on the ammeter is the

load in amperes that is demanded by the electrical
system from the alternator. As a check, take for ex-
ample a condition where the battery is demanding 10-
amperes charging current, then switch on the landing
light. Note the value in amperes placarded on the
panel for the landing light fuse (10-amps) and multiply
this by 80 per cent, you will arrive at a current of 8-
amperes. This is the approximate current drawn by
the light. Therefore, when the light is switched on,
there will be an increase of current from 10 to 18-
amperes displayed on the ammeter. As each unit of
electrical equipment is switched on, the currents will
add up and the total, including the battery, will appear
on the ammeter.

Using the example that the airplane's maximum continuous load with all
equipment on is approximately 30-amperes for the 37-ampere alternator or 48-
amperes for the 60-ampere alternator. This approximate 30 or 48-ampere value,
plus approximately two amperes for a fully charged battery, will appear contin-
uously under these flight conditions. If the ammeter reading were to go much
below this value, under the aforementioned conditions, trouble with the generating
system would be indicated and corrective action should be taken by switching off
the least essential equipment.

11-46. ALTERNATOR SYSTEM TEST PROCEDURE.

a. Start engine and set throttle for 1000.to 1200 RPM.
b. Switch on the following loads and observe the ammeter output increase as
indicated:
1. Rotating beacon - 3 to 6 amps.
2. Navigation and instrument lights (bright position) - 4 to 6 amps.
3. Landing light - 7 to 9 amps.
4. Mark 12 radio - 4 to 6 amps each. If alternator does not meet above
indications, refer to troubleshooting chart. (Follow troubleshooting procedure
outlined on chart in a step-by-step fashion checking each cause and isolation
procedure under a given trouble before proceeding with the following cause and
isolation procedure.)

Reissued: 1/15/81 4B22 ELECTRICAL SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

On airplanes with a 37-ampere alternator without night-flying equipment,

load required by test can be simulated by connecting a lamp-bank load consisting
of four landing lights wired in parallel from main buss (+)to airframe ground (-).
(Refer to Figure 11-18.)
On airplanes with a 60-ampere alternator without night-flying equipment,
load required by test can be simulated by connecting a lamp-bank load consisting
of 8 landing lights wired in parallel from main buss (±) to airframe ground (-)
(Refer to Figure 11-18.) or 14, 3-ohm, 100-watt resistors.

C31

Alligator Clips

(4) 8A Landing Lights

37- Ampere Alternator

2612

Alligator Clips

(8) 8A Landing Lights

60- Ampere Alternator

Figure 11-18. Lamp-Bank Load

Reissued: 1/15/81
4B23 ELECTRICAL SYSTEM
 PIPER CHEROKEE SERVICE MANUAL

11-47. BENCH TESTING ALTERNATOR.

11-48. FIELD CURRENT DRAW. Connect a test ammeter in series between a

12-volt battery positive post and the alternator field terminal. (Refer to Figure
11-19.) Connect a jumper wire to a machined surface on one of the alternator end
shields (ground) and to the negative battery post. The reason for connecting to
the machined surface is to ensure a good electrical connection. The end shields
are treated to oppose corrosion. The material used to treat the end shields is
not a good electrical conductor.
Observe the ammeter to determine the current flowing through the rotor
coil and connected circuit and record the amount. Slowly rotate the rotor with
the pulley while watching the meter. The current will be a little less while ro-
tating the rotor than when stationary. However, if the slip rings are clean and
the brushes are making good contact, the reading should be fairly even. A slight
fluctuation will be normal due to variation in turning speed when operated by hand.
The current draw should not be less than 2.3-amperes nor more than 2.7-
amperes. A reading of less than 2.3-amperes indicates high resistance due to
poorly soldered coil leads at the slip rings, dirty, oily slip rings or poor brush
contact. A reading higher than 2.7-amperes indicates shorted coil windings.

C322 C322

Firure 11-19.. Checking Field Circuit Figure 11-20 -Testing Field Circuit

Reissued: 1/15/81 4B24 ELECTRICAL SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

11-49. TESTING ALTERNATOR INTERNAL FIELD CIRCUIT FOR A GROUND.

To test the alternator internal field circuit for a short circuit to ground, proceed
as follows:
a. Remove the ground brush and using a 110-volt test lamp, place one test
probe to a machined surface at one of the alternator end shields. (Refer to Fig-
ure 11-20.) The test lamp should not light.
If the test lamp lights, carefully observe the order in which the parts were
installed as you remove the insulated brush assembly. Remove the three through
bolts. Then, separate the two end shield assemblies. Touch one of the test lamp
probes to one of the slip rings and the remaining test probe to the rotor shaft.
The lamp should notlight. If the lamp lights, the rotor assembly is grounded and
requires replacement.
If the test lamp does not light, the ground condition was in the insulated
brush assembly and the parts were either assembled wrong or damaged and short
circuiting through to ground. Inspect the brush holder and insulatedwasher. Re-
place if damaged. The stack of parts attaching the insulated brush holder assem-
bly to the end shield must always be installed in the proper sequence as follows:
Insulated brush holder, "FLD" terminal, insulating washer, lockwasher and at-
taching screw.

11-50. INSPECTION. Inspect the condition of the alternator components paying

special attention to the condition of the slip rings for indications of oil, being
burnt or worn. Inspect brushes for signs of sticking in holder or shield and for
wear.
Inspect the bearing surface of the rotor shaft and the roller bearings at
the rectifier end. Rotate the rotor in the drive end shield to feel for roughness
in the drive end bearing. Inspect the grease retainer, if so equipped, on late
alternators. Inspect the rectifier leads especially at connections for a good sol-
der joint, also inspect insulation. Rectifier/stator lead must be pushed down in-
to the slots that are cast into the end shield and cemented with MoPar Cement
#2299314.

11-51. TESTING RECTIFIERS (POSITIVE.)(Referto Figure 11-21.) Specialtest box tool

C-3829 has been developed to test the diode rectifiers without opening the "Y" connection
as is necessarywhere the test lamp method is used.
Due to the short leads at the "Y" connection it is quite difficult to separate and
reconnect them properly. This tool C-3829 will save much time and is accurate.
Insulate alternator from metal bench and plug tester tool C-3829 into a 110 volt
supply. Connect the alligator clip of tool C-3829 to the alternator "BAT" terminal and
touch the bare metal of each of the positive case rectifier lead wires in the heat sink at the
rectifiers.

Reissued: 1/15/81 4C1 ELECTRICAL SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

C361

TO "BAT"
TERMINAL

POSITIVECASE
61X361 C-3829 RECTIFIERS

Figure 11-21. Testing Rectifiers (Positive)

The meter reading for each of the rectifiers should be the same.Always contact the
connection nearest the rectifiers.
Do not break the sealingon the rectifier lead wire or on the top of the rectifiers. The
sealingmaterial is used for corrosion protection.
The reading on the meter will indicate 1.7 or over for good rectifiers. Where two of
the rectifiers are good and one is shorted, the reading taken at the good rectifiers will show
low. The reading at the shorted rectifier will be zero. Cut the lead at the bad rectifier and
the reading at the two good rectifiers will come up to normal. Where one of the rectifiers is
open, it will read low (1 amp or less) the two good rectifiers will show normal.

NOTE

Any tools calledout by a "C" or "SP" number in this section

may be purchased from:
MillerSpecial Tools
A Divisionof Utica Tool Company, Inc.
32615 Park Lane
Garden City, Michigan 48135 Phone: (313) 522-6717

Revised: 8/3/81 4C2 ELECTRICAL SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

C361

NEGATIVECASE
RECTIFIERS

END HOUSING

61X362 C3829

Figure 11-22. Testing Rectifiers (Negative)

11-52. TESTING RECTIFIERS (NEGATIVE). To test the negative case rectifiers in the
end shield, connect the alligator clip of tool C-3829 to the end shield.
Touch the test prod to the bare wire of the rectifier leads at the rectifiersin the end
shield. The meter will indicate the condition of the rectifier.
The test indications are the same for the negative case rectifiers in the end shield as
they are for the positive case rectifiers in the heat sink. However,the meter willread at the
opposite end of the scale.
NOTE
If all three of the negative rectifiers read low, before
condemning the rectifiers, test for a grounded stator. A
grounded stator will cause the negative rectifiers (in the end
shield) to read low.
NOTE
A common cause of an open or a shorted rectifier is a
defective capacitor or a battery that has been installed in
reverse polarity. If the battery is installed properly and the
rectifiers are open, test the capacitor with a condensertester.

Reissued: 1/15/81 4C3 ELECTRICAL SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

C362 C362

FIXTURE

AND ADAPTERS
C.3928 FIXTURE

REMOVING

Figure 11-23. C-3928 Fixtures Figure 11-24. Removing Rectifiers

and Adapters

11-53. REMOVING AND INSTALLING RECTIFIERS. The use of proper tools

for the removal and installation of rectifiers cannot be over emphasized. A spe-
cial tool kit has been developed to remove and replace new rectifiers without
damage.
NOTE
Only new rectifiers should be installed. It is not rec-
ommended to reinstall rectifiers once they have been
removed.
The tool kitcan beused on all Chrysler built alternators. A press is not required
when using the C-3928 tool kit for removing or installing rectifiers. Three diode
rectifiers are pressed into the heat sink and three in the end shields.
The new tool consists of a clamp type fixture with special adapters. This
tool makes it unnecessary to use a press.
The tool assembly consists of the following components:
C-3928 - Fixutre and Adapters
SP-3821 - Removing Adapter
SP-3818 - Installing Adapter
SP-3820 - Installing Support

Reissued: 1/15/81 4C4 EM

ELECTRICAL SYSTEM
 PIPER CHEROKEE SERVICE MANUAL

11-54. REMOVING RECTIFIERS. C362

After cutting the lead from the mal- FIXTURE

functioning rectifier, position the fix-
ture with the rectifier to be removed
over the fixture anvil.
Position the removing adapter
SP-3821 around the rectifier. Rotate
the threaded screw clockwise. As the
screw approaches the removing adap-
ter, guide its shank into the hole in the
end of the screw.
Just before the downward motion
of the screw bottoms, recheck the a- INSTALLING
dapter to be sure it is in the proper SUPPORT
position. Then continue to rotate the
screw until the rectifier is free of the Figure 11-25. Installing Rectifiers
end shield or heat sink.
Reverse the screw by rotating
it counter-clockwise. Remove adapter
and old rectifier.
Remove the end shield assembly from the fixture and position SP-3820
installing support on the fixture anvil.

11-55. INSTALLING RECTIFIERS. Start the new rectifier as squarely as pos-

sible into the hole the old rectifier was removed from after first checking to be
sure it is of the proper polarity. The negative rectifiers are marked with black
numerals and the positive with red.
Reposition the end shield in the fixture, locating the hole over the install-
ing support.
With the installing adapter SP-3818 positioned on the rectifier, rotate the
screw clockwise.
Guide the shank of the adapter into the screw. Continue to move the screw
downward until just before bottoming.

CAUTION

Check carefully to be certain that the adapter is posi-

tioned properly over the rectifier and the rectifier is
started squarely in the hole.

Reissued:1/15/81 4C5 ELECTRICAL SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

C362

Figure 11-26. Soldering Rectifier Lead

Rotate the screw clockwise pressing the rectifier in place until it bottoms.
When the rectifier bottoms, it can easily be felt. Remove the end shield assem-
bly from the fixture and inspect to see that rectifier is installed properly.

NOTE STATORLEAD
RECTIFIER
Clean LEAD
all wire 11-26
beforeSoldering. Formcareful
the
Leadrectifier
lead
Rotate around
thethe the
screwclockwise connector, being
pressing the very
rectifier in the not until
place to it bottoms.
heting, rectifier bottoms,
grip itea
bly from the fixture and inspect to seeNOTE that rectifier is installedendproperly.
be
felt. Remove shield assem-
Clean all wires before soldering. Form
lead around the connector, being very careful not tothe rectifier
crack the seal. To protect the rectifier from over-
heating, grip the rectifier lead between the rectifier
and the point being soldered with a pair of long nose
pliers. The pliers absorb heat to protect the recti-
fier. Under no circumstances use acid flux or acid
core solder. Use rosin core solder only. The solder
must be hot enough to flow and form a positive con-

Reissued:1/15/81 4C6 ELECTRICAL SYSTEM

 PIPERCHEROKEE
SERVICEMANUAL

C363

WOOD

110-VOLTBULB
WOOD

Figure 11-27. Testing Stator Coils

nection. Cold solder joints will break open. A good

solder connection will be smooth while a poor solder
joint (cold) will be rough and pitted.

NOTE

After soldering, to quickly cool the soldered connec-

tion, touch a dampened cloth against it. This will aid
in forming a solid joint.

With the rectifier properly installed, test to ensure that the rectifier has not been
damaged while installing. If the lead wires have been pulled away from the end shield, rece-
ment them.

Reissued: 1/15/81 4C7 ELECTRICAL SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

11-56. TESTING STATOR COILS FOR GROUND. The stator coils are insulated
from the core. A break in the insulation allowing the bare wire to touch the core
will ground the coil and result in no output.
To test the stator for aground (end shields separated), lift the stator away
from the end shieldand place wooden blocks approximately .50 inch thick between
the stator and the shield to keep them separated.
Using a 110volt test lamp, place one test probe on the core and the other
test probe to one of the rectifier leads, making certain to have good electrical
connections at both test probes. The lamp should not light. If the lamp lights,
it is an indication that the coil windings are grounded to the core and a replace-
ment of the stator is required.

11-57. TESTING ALTERNATOR CAPACITORS. Capacitors are used in connec-

tion with alternators to suppress any transient peak.voltage that may occur. It
is essential therefore, to test the capacitor when servicing the alternator.
This is especially true where diode rectifiers test open or short circuited.
The capacitor is connected to the inner end of the alternator "BAT" term-
inal screw and to the inner surface of the rectifier end shield (ground).

NOTE

On some early models, the capacitorwas installed on

the outside.

Connect the capacitor tester to the alternator "BAT" terminal screw and
the disconnected ground lead.

CAUTION

Do not allow the tester probes or clips to touch the end

shield or the rectifier leads while the test is in pro-
gress or damage to the rectifiers may occur.

Specified capacity for alternator capacitors of the early models is as follows:

Internally mounted .158 MFD (min.)
Very early external mount .5 MFD (min.)

The specified capacity for later built alternators (capacitor part of ter-
minal screw) is .5 ± .1 MFD (min.).
Replace capacitors with low capacity, shorted or with high series resist-
ance.

Reissued: 1/15/81 4C8 ELECTRICAL SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

C321
C321
C-3770-A

B SP-3381

BEARING

C-3925 C-3925

Figure 11-28. RemovingEnd Bearing Figure 11-29. Installing End Bearing

11-58. REMOVING NEEDLE BEARING FROM END SHIELD. (Refer to Figure

11-28.) If inspection indicates that the needle bearingis faulty, it may be replaced.
The bearing is a press fit in the end shield.To protect the end shield, it is necessary
to support it with tool C-3925 while pressingthe bearing out with tool C-3770-A.
NOTE

Tool C-3925 is a double end tool. One end will only fit into
the counterbore on alternators provided with the grease
retainer. The opposite end is used as a support for end shields
without the greaseretainer counterbore.

11-59. INSTALLING NEEDLE BEARING IN END SHIELD. (Refer to Figure

11-29.) Support the end shield on the C-3925 tool and press the bearing into the end shield
with tool SP-3381. Tool SP-3381 has a concaved end that is shaped to fit over the end of
the bearing case. It is essential to use this tool to prevent damage to the bearing.
The face of the tool has been relieved to prevent pressure being applied on the
center of the bearing. The use of a flat object to press in the bearingcan cause the bearing to
become distorted and result in a noisy bearing. Tool SP-3381 will also position the bearing
properly. When the tool contacts the end shield the bearing is in the end shield, the proper
distance.

Reissued: 1/15/81 4C9 ELECTRICAL SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

C323 C323

C-4068 TOOL
TOOL

BEARING
RETAINER

Figure 11-30. RemovingDrive Pulley Figure 11-31. Removing

Drive End Bearing
NOTE

New bearings are prelubricated, additional lubrication is not

required and should not be used.

11-60. REMOVINGDRIVE PULLEY. The drive pulley is an interference fit on the rotor
shaft. The pulley is removed with puller C-4068. The use of this puller set to remove the
pulley will prevent damage to the pulley.

11-61. REMOVINGDRIVE END BEARING. The drive end bearing is an interference fit
on the rotor shaft. It is also retained in the end shield by a retainer. The retainer on the
early production alternators was attached to the end shield by three stud nuts and washers.
All late retainers are of spring steel construction and three integral fingers snap over
a shoulder on the end shield.
Remove the drive end shield from the bearing by removingeither the three retaining
nuts from the retainer studs or by unsnapping the spring retainer fingers with a screwdriver.
The end shield may then be removed by tapping on the end of the rotor shaft with a soft
hammer while holding the end shield.
Remove the drive end bearing from the rotor shaft with puller C-4068 and special
adapters as follows:
a. Position the center screw of tool C-4068 on the rotor shaft.
b. Place the thin lower end of the adapters SP-3375 under the bearing equally spaced

Reissued: 1/15/81
4C10 ELECTRICALSYSTEM
 PIPER CHEROKEE SERVICE MANUAL

C322 C322

SLIP RING

GUIDEWIRE

GUIDEWIRE
SOLDERED
TO LEAD

OLDSLIP RING

CUT WITH CHISEL

Figure 11-32. Removing Slip Ring Figure 11-33. AligningSlip Ring

and the upper end of the adapters around the center screw.
c. Hold adapters and center screw in position with the tool sleeve.
CAUTION

Tool sleevemust bottom on bearing, otherwise adapters may

be damaged.
d. Turning the center screw while holding the outer body of the tool will withdraw the
bearing from the shaft.

11-62. REPLACINGSLIP RINGS. Slip rings that are damaged may be replaced. Two sizes
are available. The early rotor shaft was smooth and the slip rings were pressed on and the
ring cemented to the rotor fan. Later rotor shafts were knurled and the slip rings were
pressed on the knurled surface of the shaft
The early slip rings have a smaller inside diameter and must be pressed on the
smooth rotor shafts ONLY.
The later slip rings have a larger inside diameter and must be pressed on the knurled
shaft ONLY.
There is also another difference in the rotor shafts installed on the late alternators.
This shaft has a greaseretainer and an insulator. The retainer is pressed on over the insulator
ahead of the slip rings. These rotors are not interchangeablewith rotors used on alternators
without the counterbore in the rectifier end shield.

Reissued: 1/15/81 4C11 ELECTRICAL SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

C324 C324

I
GREASE
RETAINER

Figure 11-34. Installing Slip Ring Figure 11-35. Installing Retainer

11-63. REMOVINGSLIP RINGS. (Refer to Figure 11-32.)

a. Unsolder the rotor coil (field) leads from the solder lugs.
b. If the rotor has a greaseretainer (installed on all late production alternators), remove
it with a pair of diagonal pliers.
c. Cut through the copper of both slip rings at opposite points (180° apart) with a
chisel.
d. Break the insulator and remove the ring.
e. Clean away any dirt and all particles of the old ring.
f. Scrape the face of the fan to be sure it is smooth.
g. Clean the shaft surface on the area that contacts the inner diameter of the ring and
also the ends of the rotor coil leads.

11-64. INSTALLATIONOF SLIP RINGS. (Refer to Figure 11-35.) There are two types
of slip rings which can be installed.The followinginstructions will describe each type.
a. Old Style:
1. Obtain a three inch long piece of bar wire (approx. 18 gauge) and scrape one
end (about 0.19 of an inch) clean and tin this area with rosin core solder.
2. Lap the tinned end of the wire over the field coil lead to the insulated ring and
solder the two together. (Refer to Figure 11-33.)

Reissued: 1/15/81 4C12 ELECTRICALSYSTEM

 PIPER CHEROKEESERVICEMANUAL

C323
GROUND BRUSH INSULATED
RING SOLDER

SOLDERWITH
OLD STYLE RESINCORE NEW STYLE
SOLDER

Figure 11-36. Solder Points

3. Position the slip ring carefully over the bare wire and the shaft so the wire will
lay in the slip ring groove.
4. The groove in the slip ring must be in line with the insulated brush field lead to
provide room for the lead without damagingit.
5. Place installing tool C-3900 over the rotor shaft with the guide wire protruding
from the slot in the tool. (Refer to Figure 11-34.)
6. Position the assembly in an arbor press. Pull up on the guide wire being careful
to guide the insulated field lead into the slip ring groove.
7. While guiding the insulated field lead through the groove, press the slip ring on
the shaft. When the slip ring bottoms on the rotor fan, the end of the field lead should be
visible at the solder lug.
8. Unsolder the guide wire from the insulated slip ring lead. Press the field lead
into the solder lug and solder to lug with rosin core solder. (Refer to Figure 11-36.) Solder
securely but do not leave an excessive blob of solder on rotors equipped with grease
retainer.

CAUTION

Under no circumstance use acid core solder. A short circuit

may result and corrosion will definitely occur.

Reissued:1/15/81 4C13 ELECTRICALSYSTEM

 PIPER CHEROKEE SERVICE MANUAL

C325 C325

DRIVE END
TOOL
PRESSING SHIELD PULLEY
C-3858
BEARING
RETAINER

DRIVEEND
SHIELD ROTOR ROTOR
SHAFT

Figure 11-37. Installing Driver End Figure 11-38. Installing Pulley

Shield and Bearing (Typical)

9. Coil the ground brush ring field lead around the solder lug and solder with rosin
core solder.
10. Test slip rings for ground with 110-volttest lamp by touching one test probe to
rotor pole shoe and remaining probe to slip rings. Test lamp should not light. If lamp lights,
slip rings are shorted to ground, possibly due to grounding insulated field lead when
installing slip ring. If rotor is not grounded, lightly clean slip ring surface with -00-sandpaper
and assemblealternator.
b. New Style (Refer to Figure 11-36):
1. Position the slip ring on the rotor shaft so the solder lugs align with the rotor
coil leads.
2. Place assemblytool C-3900 over rotor shaft and slip ring.
3. Position assembly in an arbor press and press the slip ring on the shaft until it
bottoms on the rotor fan.
4. Coil the insulated brush slip ring lead around the solder lug and solder securely
with rosin core solder.
5. Coil the ground brush ring field lead around the solder lug located 180° from
the slip ring lug and solder with rosin core solder.
6. Test the slip rings for ground with 110 volt test lamp as outlined in step a-10.

Reissued:1/15/81 4C14 ELECTRICALSYSTEM

 PIPER CHEROKEE SERVICE MANUAL

11-65. INSTALLINGGREASERETAINER. If the solder connection where the rotor field

coil lead is soldered to the insulated brush ring lug has a sharp point or if the blob of solder
is excessive, smooth with a scraper or file before installing the grease retainer insulator. If
smooth, place fibre insulator on shaft and press the retainer (cupped side to end of shaft) on
the shaft with tool C-3921 in an arbor press.

11-66. INSTALLING DRIVE END BEARING. Insert the sealed drive end bearing in the
drive end shield and install the bearing retainer. Install the washers and nuts to hold the
bearing in place on all early production. Snap the spring steel retainer fingers in place on all
later production models.
If the rotor and its components require no service,position the bearing and the drive
end shield assembly on the rotor shaft and while supporting the parts on the end of the
rotor shaft, press the bearing and end shield assemblyin position on the rotor shaft using an
arbor press and tool C-3858.

CAUTION
Make sure that the bearing is installed squarely at the start;
otherwise, damage to the bearing will result. Press the bearing
on the rotor shaft until the bearing contacts the shoulder on
the rotor shaft.

11-67. INSTALLING PULLEY. Install pulley on the rotor shaft using an arbor press
before the rectifier end shield is assembledto the drive end shield.

THIS SPACEINTENTIONALLYLEFT BLANK

Reissued: 1/15/81
4C15 ELECTRICAL SYSTEM
 PIPER CHEROKEE SERVICE MANUAL

WARNING

Do not press pulley on with a vise. Use a press.

The shaft must be the support while the pulley is pressed on with the pres-
sure being applied to the pulley hub.

NOTE

Do not exceed 6800 pounds pressure. Press the pul-

ley on the rotor shaft until the pulley contacts the in-
ner face of the drive end bearing.

11-68. ASSEMBLING END SHIELD SUB-ASSEMBLIES. Position the rotor and

drive end shield assembly on the rectifier end shield. Align the through bolt holes
through the drive end shield, stator and the rectifier end shield.
Compress stator and both end shields by hand and install the through bolts.
Install the insulated brush and holder, terminal, insulating washer, lock-
washer and terminal attaching screw. Install the ground brush and attaching
screw.
Rotate the pulley slowly by hand to be sure that the rotor fans do not hit the
rectifiers and stator connectors.
After installing the alternator on the engine, always test the complete charg-
ing system to be certain it is functioning properly.

NOTE

New through bolt locking tabs should be installed at

each alternator disassembly. Torque through bolts
evenly to 25 inch pounds and bend both ears of the
locking tabs against bolt head. Check proper belt
tension.

11-69. BENCH RUN-UP TEST. This test is to be performed at room ambient

conditions and consists of four checks which are to be made quickly to avoid heat-
ing of the windings. These are as follows:

NOTE

For test c and d external field excitation may be used.

Reissued: 1/15/81 4C16 ELECTRICAL SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

C324 OUTPUT
AMPERES
OUTPUT
TERMINAL

FIELD
AMPERES
VARIABLE
OUTPUT LOAD
TEST VOLTAGE
TEST FIELD
ALTERNATOR TERMINAL

GROUND

Figure. 11-39. Meter Connections for Alternator

Performance Test

but must be removed and self excitation used to obtain

output amperes. (Refer to Figure 11-39 for meter
connections.)

a. 37-Ampere Alternator:
1. With the alternator at rest, apply 15-volts between the alternator bat-
tery terminal and ground with polarity such that the rectifiers will block current
flow (positive of supply to positive of the alternator). Monitor rectifier reverse
current which shall be not more than 1 milliampere.
2. With the alternator at rest, apply 15-volts to the field circuit and mon-
itor field current. This shall be between the limits of 3.0-amperes minimum
and 3.5-amperes maximum.
3. Drive the alternator at 1500 RPM with an electrical load connected to
the alternator. Adjust the load to obtain 15-volts. Net output(not including field
current) shall be not less than 19.0-amperes.
4. Drive the alternator at 2500 RPM with an electrical load connected to
the alternator. Adjust the load to obtain 15-volts. Net output(not including field
current) shall be not less than 32.0-amperes.

Reissued: 1/15/81 4C17 ELECTRICAL SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

b. 60-Ampere Alternator:
1. With the alternator at rest, supply 15-volts between the alternator bat-
tery terminal and ground with polarity such that the rectifiers will block current
flow (positive of supply to positive of the alternator). Monitor rectifier reverse
current which shall be not more than 1 milliampere.
2. With the alternator at rest, apply 15-volts to the field circuit and mon-
itor field current. This shall be betweenthe limits of 3.3-amperes minimum and
3.6-amperes maximum.
3. Drive the alternator at 1500 RPM with an electrical load connected to
the alternator. Adjust the load to obtain 15-volts. Net output(not including field
current) shall be not less than 26.5-amperes.
4. Drive the alternator at 2500 RPM with an electrical load connected to
the alternator. Adjust the load to obtain 15-volts. Net output (not including field
current) shall be not less than 49.0-amperes.

11-70. BENCH HOT STABILATION OUTPUT TEST. To determine the hot stabi-
lized output, the alternator must be driven with a suitable driving mechanism.
During this test, the following shall be monitored: (Refer to Figure 11-39 for
meter connections.)
a. Alternator output voltage.
b. Alternator output current.
c. Field current.
d. Alternator rpm.
Drive the alternator at sufficient rpm to obtain 14-volts at the alternator
battery terminal. Alternator shall be self excited, otherwise no external load
shall be applied. An external D.C. power source may be used to polarize the
field but must be removed as soon as the alternator is self sustaining. Maintain
14-volts at no load by adjusting rpm for a period of 15 minutes, at which time re-
cord the above specified data.
Apply an electrical load to the alternator and increase speed so as to ob-
tain 5-amperes output (not including field exictation) at 14-volts. Maintain this
condition for 15 minutes by adjusting the rpm. At the end of this period record
the above specified data.
Maintain output voltage at 14-volts and vary the load in 5-ampere intervals.
At each 5-amp interval allow a 15 minute stabilization period maintaining output
by varying rpm. Record the required data at each interval. Continue this pro-
cedure through the maximum output (approximately 10, 000 rpm).

Reissued: 1/15/81, 4C18 ELECTRICAL SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

C363 C363

UPPERCONTACT

SPING

CONTACT SPRING CONTACT POINTS

ADJUSTING
61X232 SPRING ANGER
2x 105

Figure 11-40. Voltage Regulator Figure 11-41. Checking Air Gap

11-71. VOLTAGE REGULATOR SERVICING. (Chrysler.)

11-72. AIR GAP ADJUSTMENT. (Regulator removed.) The mostaccurate meth-

od of measuring the air gap between the lower side of the armature and the top of
the core is to use a volt test lamp.
a. Connect one lead from the test lamp to a 12-volt battery positive post and
the remaining lead to the regulator "IGN" terminal.
b. Connect a jumper wire from the battery negative post to the regulator
"Field" terminal.
c. Insert a .048 inch gauge betweenthe armature and the core at the hinge side
of the stop.
d. Press the armature (not the contact reed) down against the gauge. The test
lamp light should dim.
e. Insert a .052 inch gauge and when the armature is pressed down the lamp
should not dim.
f. If an adjustment is required, loosen the adjustable bracket retaining screw
and raise or lower the support as required to bring the air gap to specifications
and retighten retaining screw.

Reissued: 1/15/81 4C19 ELECTRICAL SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

971 c363

UPPERFUSIBLEWIRE ADJUSTABLE RESISTOR

BRACKET RESISTOR NUMBER1

LOWERCONTACT RESISTOR

WIRE
FISUBLE
SOLDERING

TERMINAL

VOLTAGE
COILWIRES 61x236 61X236

Figure 11-42._ Voltage Regulator Figure 11-43. Voltage Regulator

Fusible Wires Resistance Units

NOTE

The base air gap is .048 to .052 inch. However, the

final air gap is determined by the transfer voltage.
The transfer voltage is the rise in voltage from the
reading taken while operating on the upper contact at
1250 RPM with a load of 15-amps, and the voltage taken
at 2200 RPM with a load of 7-amps, or less. This dif-
ference should not be less than .2-volt nor more than
.7-volt. If the transfer voltage is less than .2-volt, it
is permissible to increase the air gap but not to exceed
.005 inch (.057).

g. If the transfer voltage is greater than .7-volt, the air gap can be decreased
not to exceed .005 inch (.043). These adjustments should only be made following
the tests and then retested after adjustment.

11-73. CONTACT CLEARANCE ADJUSTMENT. The distance betweenthe upper

and lower contacts is pre-set at the factory and the contact clearance between the
movable contact and the lower contact should be correct. Even though the air gap
is readjusted, the contact clearance should remain the same.
Should the regulator be maladjusted, the contact clearance can be returned
to the specified .014 inch + .002 inch by bending the lower contact bracket.

ReiSSUED
issued::1/15/81
1/15/81 4C20 ELECTRICAL SYSTEM
 PIPER CHEROKEE SERVICE MANUAL

11-74. VOLTAGE REGULATOR FUSIBLE WIRE REPLACEMENT.

a. Cut fuse wire above solder connection at the base and unwind wire at top
bracket.

CAUTION

If an attempt is made to unsolder the old fuse, the very

small wire from voltage coil may be damaged.

b. Tin end of fuse wire. (Use resin core solder only.)

c. Holding tinned end of new fuse wire into recessed rivet at base of regulator
and against old piece of fuse wire that remains, cause a drop of solder from
soldering iron to fall on these parts. Allow solder to cool sufficiently for fuse
wires to make a good solder joint.
d. Pull new fuse wire up enough to remove slack and wrap it around the brack-
et. Solder coiled wire to the bracket and cut off surplus fuse wire.
(The original fuse wire is machine wound on the upper bracket. Replace-
ment fuse should be soldered to the bracket to ensure a good electrical contact.)

11-75. VOLTAGE REGULATOR. (Wico.)

11-76. CHECKING VOLTAGE REGULATOR. Theregulator is a fully transistor-

ized unit in which all of the components are encapsulated in epoxy, which makes
field repair of the unit impractical, and if it does not meet the specifications, it
must be replaced. The regulator may be tested by the following procedure:
a. Be sure that the battery is fully charged and in good condition.
b. Check the alternator according to the manufacturer's instructions, to deter-
mine if it is functioning properly. This test must be done with the regulator out
of the circuit. After completing this test, reconnect the regulator into the circuit.
c. Use a good quality accurate voltmeter with at least a 15-volt scale.
d. Connect the positive voltmeter lead to the red wireat the regulator harness
connector, or terminal block. Connect the negative voltmeter lead to the regula-
tor housing. (Note) Do not connect the voltmeter across the battery, because the
regulator is designed to compensate for resistance contained within the wiring
harness.
e. With the alternator turning at sufficient rpm to produce a half load condition,
or approximately 25-amperes output, the voltmeter should read between 13.6and
14.3 volts. The ambient temperatures surrounding the voltage regulator should
be between 50°F. to 100°F. while this test is being made.
f. The voltage regulator heat sink, or case, is the ground connection for the

ELECTRICAL SYSTEM
Reissued: 1/15/81 4C21
 PIPER CHEROKEE SERVICE MANUAL

electronic circuit. Therefore, if this unit is tested on the bench it is most im-
portant that a wire, No. 14, be connected between the regulator case and the al-
ternator. If the regulator does not regulate between 13.6 and 14.4-volts, one of
the following conditions may exist:
1. Regulates, but out of specification. The regulator is out of calibration
and must be replaced.
2. The voltmeter continues to read battery voltage.
a. Poor or open connections within the wiring harness.
b. The regulator is "open."
3. Voltage continues to rise.
a. Regulator housing not grounded.
b. Regulator shorted, must be replaced.
g. These are some of the things to look for in case of failure:

1. Poor or loose connections.

2. Poor ground on the regulator housing.
3. Shorted alternator windings.
4. A grounded yellow wire (This will cause instantaneous failure.)
5. Disconnecting the regulator while the circuit energized.
6. Open circuit operation of the alternator (The battery disconnected.)

11-77.. OVER VOLTAGE RELAY. (Wico.)

11-78. CHECKING OVER VOLTAGE RELAY. The relay may be tested with the
use of a good quality, accurate voltmeter, with a scale of at least 20-volts and a
suitable power supply, with an output of at least 20-volts, or sufficient batteries
with a voltage divider to regulate voltage. The test equipment may be connected
by the following procedure:
a. B+ is connected to "Bat" of the over-voltage control.
b. B- is connected to the frame of the over-voltage control.
c. Be sure both connections are secure, and connected to a clean, bright sur-
face.
d. Connect the positive lead of thevoltmeter to the "Bat" terminal of the over-
voltage control.
e. Connect the negative lead of the voltmeter to the frame of the over-voltage
control.
f. The over-voltage control is set to operate between 16.2-volts to 17 .3-volts..
By adjusting the voltage, anaudible "click" may be heard when the relay operates.
g. If the over-voltage control does not operate between 16.2 and 17.3-volts,
it must be replaced.

Reissued: 1/15/81 ELECTRICAL SYSTEM

4C22
 PIPER CHEROKEE SERVICE MANUAL

11-79. CHECKING GENERATOR OR ALTERNATOR BELT TENSION. If properly

installed and checked periodically, the generator or alternator drive belt will give very sat-
isfactory service. However,an improperly tensioned belt will wear rapidly and may slip and
reduce unit output. Consequently,a belt should be checked for proper tension at the time of
installation, again after 25 hours of operation and each 100 hours thereafter.
The method of checking belt tension is simple and requires little time for accom-
plishment. This method of checking belt tension consists of measuring torque required to
slip the belt at the pulley on the generator or alternator, and is accomplished as follows:
a. Apply a torque indicating wrench to the nut that secures the pulley to the generator
or alternator and turn the pulley in a clockwisedirection. Observe the torque shown on the
wrench at the instant the pulley slips.
b. Check the torque indicated in Step a with the torque specifiedin the followingchart.
Adjust the belt tension accordingly.

BELT BELT BELT SLIP TORQUE

TYPE WIDTH IN. CONDITION FOOT POUNDS

RUBBER .375 NEW 11-13

RUBBER .375 USED 7-9
RUBBER .500 NEW 13-15
RUBBER .500 USED 9-11
PLASTIC .328 NEW 11-13
PLASTIC .328 USED 7-9

11-80. STARTING MOTOR (Delco-Remy.)

11-81. OPERATION OF STARTING MOTOR. When the starting motor switch is closed.
the armature begins to rotate. The drive pinion, being a loose fit on the drive sleevelocated
on the armature shaft, does not pick up speed as fast as the armature. Therefore, the drive
pinion, having internally matched splines with respect to the splined drive sleeve, moves
endwise on the shaft and into mesh with the flywheel. As the pinion hits the pinion stop, it
begins to rotate with the armature and cranks the engine.
When the engine starts, the flywheelbegins to spin the pinion faster than the armature.
Again, because of the splined action of the pinion and drive sleeveassembly,the pinion backs
out of mesh with the flywheel ring gear protecting the armature from excessivespeeds.
Some Bendix drives incorporate a small anti-drift spring between the drive pinion stop
which prevents the pinion from drifting into mesh when the engine is running. Others use a
small anti-drift pin and spring inside the pinion which provides enough friction to keep the
pinion from drifting into mesh.
Never operate the motor for more than 30 seconds without pausing for two minutes
to allow it to cool.

Revised: 10/3/83 4C23 ELECTRICAL SYSTEM

THIS PAGE INTENTIONALLY LEFT BLANK

4C24
 PIPER CHEROKEE SERVICE MANUAL

11-82. CHECKING STARTING MOTOR. Several checks, both visual and elec-
trical, should be made in a defective cranking circuit to isolate trouble before
removing any unit. Many times a component is removed from the airplane only
to find it is not defective after reliable tests. Therefore, before removing a unit
in a defective cranking system, the following checks should be made:
a. Determine the condition of the battery.

NOTE

If a solderless terminal on an aluminum cable is loose, cor-

roded or otherwiseunsatisfactory, it is recommended that the
complete cable assembly be replaced instead of replacing or
repairing the solderless terminal.
Should replacement of the complete assembly not be prac-
tical, it is permissible to replace the aluminum cable assembly
with a copper cable assembly which is two sizes smaller (ex.:
an AL-1 aluminum cable assembly is replaced with an AN-3
copper cable assembly).
The new cable should be installed in accordance with AC-
43-13-2A.
b. Inspect the wiring for frayed insulation or other damage. Replace anywir-
ing that is damaged. Inspect all connections to the starting motor solenoid
switch, starting switch or any other control switch, and battery, including all
ground connections. Clean and tighten all connections and wiring as required.
The engine manufacturer specifies allowable voltage drop in the cranking circuit.
For this information, refer to the manufacturer's shop manual.
c. Inspect starting and solenoid switches to determine their condition. Con-
nect a jumper lead around any switch or solenoid suspected of being defective.
If the system functions properlyusing this method, repair or replace the bypassed
unit.
d. If specified battery voltage can be measured at the motor terminal of the
starting motor, allowing for some voltage drop in the circuit and the engine is
known to be functioning properly, remove the motor and follow the test proce-
dures outlined below.

Reissued: 1/15/81 4D1 ELECTRICAL SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

C325 11-83. TESTAND MAINTENANCEOF

STARTING MOTORS.

BATTERY 11-84. INSPECTION. With the start-

_^ ing motor removed from the engine, the
I pinion should be checked for freedom
of operation by turning it on the screw
shaft. The armature should be check-
ed for freedom of operation by turning
the pinion. Tight, dirty, or worn bear-
ings, bentarmature shaft, or loose pole
shoe screw will cause the armature to
drag and it will not turn freely. If the
armature does not turn freely, the mo-
Figure 11-44. No-Load Test Hookup tor should be disassembled immedi-
ately. However, if the armature does
operate freely, the motor should be given electrical tests before disassembly.

11-85. NO LOAD TEST. (Refer to Figure 11-44.) Connect the starting motor
in series with a fully charged battery of the specified voltage, an ammeter ca-
pable of reading several hundred amperes, and a variable resistance. Also con-
nect a voltmeter as illustrated, from the motor terminal to the motor frame. An
RPM indicator is necessary to measure armature speed. Obtain the specified
voltage by varying the resistance unit. Then read the current draw and the ar-
mature speed and compare these readings with the values listed in paragraph
11-91. Interpret the test results as follows:
a. Rated current draw and no -load speed indicate normal condition of the crank -
ing motor.
b. Low free speed and high current draw indicate:
1. Too much friction - tight, dirty, or worn bearings, bentarmature shaft
or loose pole shoes allowing armature to drag.
2. Shorted armature. This can be furtherchecked on a growler after dis-
assembly.
c. Failure to operate with high current draw indicates:
1. A direct ground in the terminal or fields.
2. "Frozen" bearings (this should have been determined by turning the ar-
mature by hand).
d. Failure to operate with no current draw indicates:
1. Open field circuit. This can be checked after disassembly by inspec-
ting internal connections and tracing circuit with a test lamp.

Reissued: 1/15/81 4D2 ELECTRICAL SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

C325 C325

Figure 11-45. Lock-Torque Figure 11-46 Resistance

Test Hookup Test Hookup

2. Open armature coils. Inspect the commutator for badly burned bars
after disassembly.
3. Broken brush springs, worn brushes, high insulation between the com-
mutator bars orothercauseswhich wouldpreventgood contact betweenthe brush-
es and commutator.
e. Low no-load speed and low current draw indicate high internal resistance
due to poorconnections, defective leads, dirtycommutatorand causes listed under
step d.
f. High free speed and high current draw indicate shorted fields. If shorted
fields are suspected, replace the field coil assemblyand check for improved per-
formance .

11-86. LOCK-TORQUE TEST. (Refer to Figure 11-45.) The lock-torque test

requires the equipment illustrated. A variable resistance with a high current
capacity should be used. The cranking motor should be securely mounted and a
brake arm hooked to the drive pinion. Use extreme caution during this test to
make sure the end of the brake arm does not slip off the pinion when current is
applied. When specified current is applied, the torque can be computed from the
reading on the scale. A one foot brake arm will directly indicate pound-feet.
Compare the pound-feet of torque as read on the scale with that listed in para-
graph 11-91. If the torque is low, the motor must be disassembled for further
tests and repair.

Reissued: 1/15/81 4D3 ELECTRICAL SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

11-87. RESISTANCE TEST. (Refer to Figure.11-46.) This test requires equip-

ment similar to the lock-torque test, with the exception that the pinion is locked
securely so it cannot rotate. When the specified voltage is applied, the current
should fall in a range as indicated in paragraph 11-91. A high current indicates
grounded or shorted conductors, and a low current indicates excessive resistance.

11-88. DISASSEMBLY. If the motor does not perform in accordance with pub-
lished specifications, it may need to be disassembled for further testing of the
components. Normally the cranking motor should be disassembled only so far
as is necessary to make repair or replacement of the defective parts. As a pre -
caution, it is suggested that safety glasses be worn when disassembling or as-
sembling the cranking motor. Following are general instructions for disassem-
bling a typical Bendix drive starting motor.
a. Remove the cover band, if present, and detach the field coil leads from the
brush holders.
b. If gear reduction, remove the drive housing and reduction housing.
c. Remove the bolts attaching the drive housing and commutator end frame to
the field frame assembly. Discard the tang lock washers.
d. Separate the commutator end frame, armature assembly, field frame and
drive housing.
e. Remove and disassemble the drive from the armature shaft by first iden-
tifying the type Bendix drive and then following one of the guides below:
1. Standard Bendix Drive: Remove the head spring screw and slip it off
the armature shaft.
2. Folo-Thru-Bendix Drive: Push in the outer anchor plate so the pilot
screw or pin can be removed.

CAUTION

Do not disassemble this drive, service is by complete

replacement.

NOTE

Some Folo-Thru drives use a rubber cushion in place

of a drive spring. To remove from shaft, screw pin-
ion out to drive position, then force pin from shaft
through screw sleeve holes.

Reissued: 1/15/81 ELECTRICAL SYSTEM

4D4
 PIPER CHEROKEE SERVICE MANUAL

11-89. COMPONENT INSPECTION AND REPAIR.

a. Brushes and Brush Holders: Inspect thebrushes for wear. If they areworn
down to one-half their original length, when compared with a new brush, they
should be replaced. Make sure the brush holders are clean and the brushes are
not binding in the holders. The full brush surface should ride on the commutator
with proper spring tension (Refer to paragraph 11-91.) to give good, firm con-
tact. Brush leads and screws should be tight and clean.
b. Armature: The armature should be checked for short circuits, opens and
grounds:
1. Short circuits are located by rotating the armature in a growler with a
steel strip such as a hacksaw blade held on the armature. The steel strip will
vibrate on the area of the short circuit. Shorts between bars are sometimes pro-
duced by brush dust or copper between the bars. Undercutting the insulation will
eliminate these shorts.
2. Opens: Inspect the points where the conductors are joined to the com-
mutator for loose connections. Poor connections cause arcing and burning of the
commutator. If the bars are not badly burned, resolder the leads in the riser
bars and turn the commutator down in a lathe. Then undercut the insulation be-
tween the commutator bars .031 of an inch.
3. Grounds in the armature can be detected by the use of a test lamp and
prods. If the lamp lights when one test prod is placed on the commutator and the
other test prod on the armature core or shaft, the armature is grounded. If the
commutator is worn, dirty, out of round, or has high insulation, the commutator
should be turned down and undercut as previously described.
c. Field Coils: The field coils should be checked for grounds and opens using
a test lamp.
1. Grounds: Disconnect field coil ground connections. Connect one test
prod to the field frame and the other to the field connector. If the lamp lights,
the field coils are grounded and must be repaired or replaced.
2. Opens: Connect test lamp prods to ends of field coils. If lamp does not
light, the field coils are open.
If the field coils need to be removed for repair or replacement, a pole shoe
spreader and pole shoe screw driver should be used. Care should be exercised
in replacing the field coils to prevent grounding or shorting them as they are tight-
ened into place. Where the pole shoe has a long lip on one side, it should be as-
sembled in the direction of armature rotation.

Reissued: 1/15/81 4D5 ELECTRICAL SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

11-90. ASSEMBLY. To reassemble the motorfollowthedisassemblyprocedures

in reverse. Install new tang lock washers where removed.

CAUTION

If Folo-Thru drive is manually rotated to locked posi-

tion, do not attempt to force it in a reverse direction.
Proceed to install with pinion meshing with flywheel.
When engine starts, the drive will return to the de-
meshed position.

11-91. STARTING MOTOR SERVICE TEST SPECIFICATIONS. Delco-Remy

specifications for 12-volt starting motors installed as standard equipment on
PA-28 series airplanes are as follows:

Motor Model 1109657 1109657

Delco-Remy, Ref,
Service Bulletin IM- 110 M-110

Minimum Brush Tension 24 oz. 24 oz.

No-Load Test
Volts 10.6 10.6
Min. Amps 48
Max. Amps 80 80
Min. RPM 5800 3000
Max. RPM 8200

Lock Test
Amps - 300
Torque (ft.-lbs.) 18.0
Approx. Volts -7.3

Resistance Test
Volts 4.0
Min. Amps 365
Max. Amps 420

Reissued: 1/15/81 4D6 ELECTRICAL SYSTEM

 PIPER CHEROKEESERVICEMANUAL

11-92. STARTING MOTORS .Prestolite.)

11-93. DESCRIPTION. The gear reduction starting motor consists of six major
components: The Commutator End Head Assembly, The Armature, The Frame
and Field Assembly, theGear Housing, The Pinion Housing, and The Bendix Drive
Assembly. Refer to Figure 11-47.

11-94. OPERATION. When the starting circuit is energized, battery current is

applied to the starting motor terminal. Current flows through the field coils,
creating a strong magnetic field. At the same time, current flows through the
brushes to the commutator, through the armature windings to ground. The mag-
netic force created in the armature combined with that created in the field wind-
ings begins to turn the armature.
The gear cut on the drive end of the armature shaft extends through the gear
housing, where it is supported bya roller bearing. The gear mates with the teeth
of the reduction gear that drives the bendix shaft. The shaft is keyed to the re-
duction gear. The Bendix drive is held in position on the shaft by a "spirol" pin.
The shaft is supported in the gear housing by a closed end roller bearing and in
the pinion housing by a graphitized bronze bearing.
When the armature turns the reduction gear, the Bendix drive pinion meshes
with the flywheel ring gear by inertia and action of the screw threads within the
Bendix sleeve. A detent pin engages in a notch in the screw threads which pre-
vents demeshing if the engine fails to start when the starting circuit is de-ener-
gized.
When the engine reaches a predetermined speed, centrifugal action forces
the detent pin out of the notch in the screw shaft and allows the pinion to demesh
from the flywheel.

11-95. MAINTENANCE. The starting circuit should be inspected at regular

intervals, the frequency of which should be determined by the amount of service
and the conditions under which the vehicle is operated. It is recommended that
such inspection be made at each 100 hours and include the following:
a. The battery should be checked with a hydrometer to be sure if is fully
charged and filled to the proper level with approved water. A load test should
be made to determine battery condition. If dirt and corrosion have accumulated
on the battery, it should be cleaned with a solution of baking soda and water. Be
sure none of the solution enters the battery cells.
b. The starting circuit wiring should be inspected to be sure that all connec-
tions are clean and tight and that the insulation is sound. A voltage loss test

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374

-THRUST WASHER PKG.

Figure 11-47. Exploded View of Gear Reduction Starting Motor

should be made to locate any high-resistanceconnections that would affect start-

ing motor efficiency. This test is made with a low-reading voltmeter while crank-
ing the engine or at approximately 100 amperes, and the following limits should
be used:

NOTE
If a solderless terminal on an aluminum cable is loose, cor-
roded or otherwise unsatisfactory, it is recommendedthat the
complete cable assembly be replaced instead of replacing or
repairing the solderless terminal.
Should replacement of the complete assembly not be prac-
tical, it is permissibleto replace the aluminum cable assembly
with a copper cable assembly which is two sizes smaller (ex.:
an AL-1 aluminum cable assembly is replaced with an AN-3
copper cable assembly).
The new cable should be installed in accordance with AC-
43-13-2A.

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4D8
 PIPER CHEROKEE SERVICE MANUAL

. Voltage loss from insulated battery post to starting motor terminal -

0.3-volt maximum.
2. Voltage loss from battery ground post to starter frame - 0.1-volt
maximum.
NOTE

If voltage loss is greater than the above limits, add-

itional tests should be made over each part of the cir-
cuit to locate the high-resistance connections.

THIS SPACE INTENTIONALLY LEFT BLANK

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 PIPER CHEROKEE SERVICE MANUAL

c. No lubrication is required on the starting motor except at the time of over-

haul. Then lubricate the entire shaft under Bendix Drive, fill grooves in arma-
ture shaft at drive end and pack gear box with 1.3 to 2.0 ounces of Lithium Soap
Base Grease #1925 Molytex "O" or equivalent.
d. The starting motor should be operated for a few seconds with the ignition
switch off to make sure that the pinion engages properly and that it turns freely
without bindingor excessive noise. Then the engine should be started two or three
times to see that the pinion disengages properly when the engine is turned off.

11-96. OVERHAUL. If during the above inspection any indication of starting

motor difficulty is noted, the starting motor should be removed from the engine
for cleaning and repair.

11-97. REMOVAL. To remove the starting motor from the engine, first dis-
connect the ground cable from the battery post to prevent short circuiting. Dis-
connect the lead from the starting motor terminal, then take out the mounting
bolts. The motor can then be lifted off and taken to the bench for overhaul.

11-98. DISASSEMBLY.
a. Remove the frame screws from the commutator end head and pull end head
and armature from frame. Lift the brushes and lock in elevated position with
brush springs. Use a puller to remove the end head from the armature. Use a
special bearing puller to remove the sealed ball bearing from the armature shaft.
b. Remove the frame screws that secure the gear housing to the frame. Re-
move bolts and nuts holding the gear housing to the pinion housing and separate
the two units. Pull Bendix shaft from pinion housing. Do not lose the steel spacer
that is located on the pinion end of the shaft. Remove reduction gear, woodruff
key and steel spacer from shaft.
c. Turn the Bendix pinion until it locks in the extended position. Locate "spi-
rol" pin and use a punch to remove. Slide drive assembly off the shaft. Do not
attempt to disassemble the drive and do not dip it in cleaning solvent.
d. To remove the roller bearings from the gear housing, use an arbor press
and the correct bearing arbor. DO NOT HAMMER OUT. Each part should be
cleaned and inspected for excessive wear or damage. Bearings should be checked
for proper clearance and evidence of roughness orgalling. Oil and dirt should be
removed from insulation and the condition of the insulation checked.

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376
375

Figure 11-48. Turning Starting Figure 11-49. Testing Motor

Motor Commutator Armature for Shorts
11-99. BRUSHES. Check the brushes to see that they slide freely in their hold-
ersandmake full contacton the commutator. If worn to half their original length
or less, they should be replaced.

11-100. ARMATURE.
a. Check the commutator for uneven wear, excessive glazing or evidence of
excessive arcing. If only slightly dirty, glazed or discolored, the commutator
can be cleaned with 00 or 000 sandpaper. If the commutator is rough or worn, it
should be turned in a lathe. Refer to Figure.11-48. The armature shaft should
be inspected for rough bearing surfaces and rough or damaged splines.
b. To test the armature for grounds, a set of test probes connected in series
with a 110-volt light should be used. Touch one probe to a commutator segment
and the other to the armature core. If the test lamp lights, the armature is
grounded and should be replaced.
c. To test for shorted armature coils, a growler is used. (Refer to Figure

11-49.) The armature is placed onthe 376o,

growler and slowly rotated by hand
while a steel stripis held over the core
so that it passes over each armature
core slot. If a coil is shorted, the steel
strip will vibrate.
d. A quick check for opens can be
made by inspecting the trailing edge
(in direction of rotation) of the com-
mutator segments for excessive dis-
coloration. This condition indicates
an open circuit.
Figure 11-50. Testing Motor
Fields for Grounds

ELECTRICAL SYSTEM
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 PIPER CHEROKEE SERVICE MANUAL

11-101. FIELD COILS.

a. Check the field coils for grounds (Refer to Figure 11-50) by placing one
testprobe on the frame and the other on the starter terminal. Be sure the brushes
are not accidentally touching the frame. If the lamp lights, the fields are ground-
ed. Repair or replace.
b. Inspect all connections to make sure they are clean and tight and inspect
insulation for deterioration.

11-102. BRUSH HOLDERS.

a. To test brush holders, touch one test probe to the brush plate and the other
to each brush holder.
b. The test lamp should light when the grounded brush holders are touched and
should not light when the insulated brush holders are touched.

11-103. GEAR AND PINIONHOUSING. Inspect housings for cracks and bearings
for excessive wear. Remove rust, paint or grease from mounting surfaces.

11-104. BENDIX DRIVE.The Bendix Drive should be wiped clean with a dry cloth.
The pinion should turn smoothly in one direction and should lock in the other di-
rection. Replace drive if it fails to check as above or if the pinion teeth are ex-
cessively worn or damaged.

11-105. ASSEMBLY.
a. When assembling the starting motor, always use an arbor press and the
proper bearing arbor for installing graphitized bronze and roller bearings. The
Bendix shaft should have a thin film of Lubriplate #777 or equivalent on the Bendix
portion of the shaft. End play should be .005 to .050 of an inch.
b. New brushes should be properly seated when installing by wrapping a strip
of 00 sandpaper around the commutator (with the sanding side out) 1-1/4 to 1-1/2
times maximum. Drop brushes on sandpaper covered commutator and turn the
armature slowly in the direction of rotation. Dust should be blown out of the motor
after sanding.

NOTE

The spring tension is 32 to 40 ounces with new brushes.

This tension is measured with the scale hooked under the
brush spring near the brush and the reading is taken at
right angles to the line of force exerted by the brush spring.

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Figure 11-51. No-Load Figure 11-52. Stall-Torque

Test Hook-up Hook-up

c. Check the position of the pinion to be sure the unit will mesh properly with
the flywheel ring gear. See specifications for unit for correct dimensions. Refer
to paragraph 11-108.

11-106. BENCH TESTS.

a. After the starting motor is reassembled, it should be tested to see that the
no-load currentat a certain voltage is within specifications as given in paragraph
11-108. To make this test, connect as shown in Figure 11-51. If current is too
high, check the bearing alignment and end play to make sure there is no binding
or interference. Two or three sharp raps on the frame with a rawhide hammer
will often help to align the bearings and free the armature.
b. If no difficulty is indicated in the above test, a stall torque test may be made
to see if the starting motor is producing its rated cranking power. Make test
connections as shown in Figure 11-52.
c. If torque and current are not within specifications, check the seating of the
brushes and internal connections for high resistance. If these checks are made
and found to be in good order, replace frame and field assembly and retest
starter.

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4D13 ELECTRICAL SYSTEM
 PIPER CHEROKEE SERVICE MANUAL

11-107. STARTING MOTORCONTROLCIRCUIT.

a. Inspect the control circuit wiring between the battery, solenoid and manual starting
switches for breaks, poor connections and faulty insulation. Tighten all connections and
make sure solenoid is firmly mounted and makes a good ground connection.
b. Check the voltage loss across the switch contacts during normal starting. If loss is in
excess of 0.2 volts per 100 amperes, the solenoid should be replaced.
c. If solenoid fails to operate when the manual starting switch is turned on or if it fails
to release when the manual starting switch is released, it should be removed and tested to
specifications. If either opening or closing voltages are not to specifications, replace the
solenoid.

11-108. STARTING MOTORSERVICETEST SPECIFICATIONS.Prestolite specifications

for 12-volt starting motors installed as standard equipment on PA-28 series airplanes are as
follows:

Motor Model MZ-4204 or MZ-4206

Min. Brush Tension 32 oz.

Max. Brush Tension 40 oz.

No-Load Test (77° F)

Volt 10
Max. Amps 75
Min. R.P.M. 2000

Stall Torque
Amps 560
Min. Toruqe, Ft. lbs. 38.0
Approx. volts 4.0

Pinion Position*
Drive at rest 1.748 in. - 1.855 in.
Drive extended 2.388 in. - 2.495 in.

*This dimension is measured from the centerline of

the mounting hole nearest the drive end head to the
edge of the pinion.

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4D14 ELECTRICAL SYSTEM
 PIPER CHEROKEE SERVICE MANUAL

11-109. BATTERY.

11-110. SERVICING BATTERY. Access to the battery is through the aft side of the
baggage compartment (PA-28-150, -160, -180 and PA-28R-180,-200) or the access panel
located in the baggage compartment floor (PA-28-140). It is enclosed in a protective box
with a vent system and a drain. The vents allow fresh air to enter the box and draw off
fumes that may accumulatedue to the charging process of the battery. The drain is clamped
off and should be opened occasionally to drain any accumulation of liquid or during
cleaning of the box. The battery should be checked for fluid level but must not be filled
above the baffle plates. A hydrometer check should be performed to determine the percent
of charge in the battery. All connections must be clean and tight.

NOTE
If a solderless terminal on an aluminum cable is loose, cor-
roded or otherwiseunsatisfactory, it is recommendedthat the
complete cable assembly be replaced instead of replacing or
repairing the solderless terminal.
Should replacementof the complete assemblynot be prac-
tical, it is permissibleto replace the aluminumcable assembly
with a copper cable assemblywhich is two sizes smaller (ex.:
an AL-I aluminum cable assemblyis replaced with an AN-3
copper cable assembly).
The new cable should be installed in accordance with AC-
43-13-2A.

11-111. REMOVALOF BATTERY.

a. Removethe accesspanel to the aft section of the fuselage(PA-28-150,-160,-180 and
PA-28R-180,-200) or the floor panel located aft of the main spar (PA-28-140).
b. Removebattery box cover.
c. Disconnectthe battery cables.
NOTE
Always remove the ground cable first and install last to
prevent accidentalshort circuiting or arcing.
*d. Lift the battery from the box.

11-112. INSTALLATIONOF BATTERY.

a. Ascertain that the battery and battery box have been cleanedand are free of acid.
b. Install the battery in box.
c. Connect the positive lead to the positivebattery terminal and secure.
d. Connect the ground cable to the negativebattery terminal and secure.
e. Install the battery box coverand secure with wing nuts.
f. Install accesspanel.

Reissued: 1/15/81 ELECTRICAL SYSTEM

4D15
 PIPER CHEROKEE SERVICE MANUAL

11-113. CHARGING BATTERY. If the battery is notup to normalcharge, remove

the battery and recharge starting with a charging rate of 4-amps and finishing with
2-amps. A fast charge is not recommended.

HYDROMETER READING AND BATTERY CHARGE PER CENT

Hydrometer Reading Per cent of Charge

1280 100
1250 75
1220 50
1190 25
1160 Very little useful capacity
1130 or below discharged

11-114. BATTERY BOX CORROSIONPREVENTION. The battery should be checked for

spilled electrolyte or corrosion at least each 50 hour inspection or at least every 30 days,
whichever comes first. Should this be found in the box, on the terminals or around the
battery, the battery should be removed and both the box and battery cleaned by the
followingprocedure:
a. Remove the box drain cap from the under side of the fuselage and drain off any
electrolyte that may have overflowedinto the box.
b. Clean the battery and the box. Corrosion effects may be neutralized by applying a
solution of baking soda and water mixed to a consistency of thin cream. The application of
this mixture should be applied until all bubbling action has ceased.

CAUTION
Do not allowsoda solution to enter battery.
c. Rinse the battery and box with clean water and dry.
d. As necessary, paint the metal battery box with an acid resistant paint. Allow paint
to dry thoroughly.
e. Place the cap over the battery box drain.
f. Reinstall the battery.

Reissued: 1/15/81
4D16 ELECTRICAL SYSTEM
 PIPER CHEROKEE SERVICE MANUAL

11-115. STARTING THROUGH EXTERNAL POWER RECEPTACLE WITH

AIRPLANE'S BATTERYNEARLYDEPLETED.
a. When using a 12-voltbattery for external power starting and the airplane's battery is
nearly depleted, the followingprocedure should be used:
1. Disconnect the airplane's battery at the negative terminal to prevent excessive
loading of the external starting battery.
2. Check that all of the airplane's electrical equipment is turned OFF.
3. Connect the external battery to the external power receptacle; turn master
switch ON and start engine usingnormal starting procedure.
4. Turn master switch OFF; remove external battery, and then reconnect the
battery at the negativeterminal.
5. Turn master switch ON.
When starting with a power cart and the airplane's battery is nearly depleted, the
procedure in step a need not be followed. The capacity of a power cart is sufficient to start
an aircraft with a low battery.

THIS SPACEINTENTIONALLYLEFT BLANK

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 PIPER CHEROKEE SERVICE MANUAL

11-116. ALTERNATORSYSTEM(RRESTOLITE).

11-117. CHECKINGALTERNATORSYSTEM. With all electrical equipment off (except

master switch) the ammeter will indicate the amount of chargingcurrent demanded by the
battery. This amount will vary, depending on the percentage of charge in the battery at the
time. As the battery becomescharged, the amount of current displayed on the ammeter will
reduce to approximately two amperes. The amount of current shown on the ammeter will
tell immediately whether or not the alternator system is operating normally, if the following
principles are kept in mind.

NOTE
The amount of current shown on the ammeter is the load in
amperes that is demanded by the electrical system from the
alternator. As a check, take for example a condition where
the battery is demanding 10 amperes chargingcurrent, then
switch on the landing light. Note the value in amperes
placarded on the circuit breaker panel for the landing light
circuit breaker (10 amps) and multiply this by 80 percent,
you will arrive at a current of 8 amperes. This is the
approximate current drawn by the light. Therefore, when the
light is switched on, there will be an increase of current from
10 to 18 amperes displayed on the ammeter. As each unit of
electrical equipment is switched on, the current will add up
and the total, including the battery, will appear on the
ammeter.

Using the example that the airplane's maximum continuous load with all equipment on is
approximately 48 amperes for the 60-amperealternator. This approximate 48-ampere value,
plus approximately two amperes for a fully charged battery, will appear continuously under
these flight conditions. If the ammeter reading were to go much below this value, under the
aforementioned conditions, trouble with the alternator system would be indicated and
corrective action should be taken by switching off the least essential equipment.
The followingtest procedure could be helpful in locating faulty components:
a. Ascertain that the airplaneis positioned so that the prop blast will not interfere with
other operations going on near by. Start engine and set throttle for 1000 to 1200 RPM.
b. Switch on the followingloads and observe the ammeter output increase as indicated.
1. Rotating beacon - 3 to 6 amps.
2. Navigationand instrument lights (bright position) - 4 to 6 amps.
3. Landinglight - 7 to 9 amps.
If alternator does not meet above indications, refer to troubleshooting chart. Follow
troubleshooting procedure outlined on the chart in a step by step fashion checking each
cause and isolation procedure under a giventrouble before proceeding to the next.
On airplanes without night-flying equipment, load required by test can be simulated by
connecting a lamp-bank load consisting of 8 landing lights wired in parallel from main bus
(+) to airframe ground (-) (Refer to Figure 11-18) or 3 ohm, 100 watt resistors.

Reissued:1/15/81 4D18 ELECTRICAL SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

11-118. ALTERNATORNOMENCLATURE.
a. Bearings: These units have a sealed ball bearing at the drive end and a two-piece
roller bearing at the slip ring end. The inner race is pressed onto the rotor shaft and the rest
of the bearing is in the slip ring end head. When the unit is assembled,the inner race aligns
with the bearing. When the bearing is replaced, the new inner race must be installed on the
rotor shaft.
b. Lubrication: The slip ring end bearing should be lubricated wheneverthe alternator
is disassembled.The bearing should be thoroughly cleaned and repacked with Shell Alvania
No. 2 or an equivalent bearing lubricant. The cavity behind the bearing should be packed
one-third to one-half full with the same lubricant.
c. Brushes: These units have a separate brush holder assemblythat is installed after the
alternator has been assembled. The brush holder has a small hole that intersects the brush
cavities. Use a pin or a piece of wire, as shown in Figure 11-83 to hold the brushes in the
holder during assembly. Remove the pin after the brush holder retaining screwshave been
tightened. Make a continuity check to be sure the brushes are seated against the slip rings.
d. Drive Pulley: Torque the drive pulley retaining nut to 35 foot pounds.

11-119. ALTERNATOR SERVICEPRECAUTIONS.Since the alternator and regulator are

designed for use on only one polarity system, the following precautions must be observed
when testing or servicingthe electrical system. Failure to observe these precautions will
result in serious damageto the electrical equipment.
a. Disconnect the battery before connecting or disconnectingtest instruments (except
voltmeter) or before removing or replacing any unit or wiring. Accidental grounding or
shorting at the regulator, alternator, ammeter or accessories,will cause severe damage to the
units and/or wiring.
b. The alternator must not be operated on open circuit with the rotor winding
energized.
c. Do not attempt to polarize the alternator. No polarization is required. Any attempt
to do so may result in damage to the alternator, regulator or circuits.
d. Grounding of the alternator output terminal may damage the alternator and/or
circuit and components.
e. Reversed battery connections may damage the rectifiers, wiring or other
components of the charging system. Battery polarity should be checked with a voltmeter
before connecting the battery. Most aircraft are negativeground.
f. If a booster battery or fast charger is used, its polarity must be connected correctly
to prevent damage to the electrical system components.

11-120. DESCRIPTIONOF ALTERNATOR. (Refer to Figure 11-71.)

The principal components of the alternator are the brush holder assembly (1), the slip
ring end head (2), the rectifiers (3), the stator (4), the rotor (5) and the drive end head (6).
a. The brush and holder assembly contains two brushes, two brush springs, a brush
holder and insulator. One brush is connected to a terminal stud and is insulated from
ground. The other brush is connected to ground thru the brush holder. The brush and
holder assembly can easilybe removed for inspection or brush replacement purposes.

Reissued: 1/15/81 4D19 ELECTRICAL SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

1240

1. BRUSHHOLDERASSY. 4.STATOR
2. SLIP RINGEND HEAD 5. ROTOR
3. RECTIFIERS 6. DRIVEEND HEAD

Figure 11-71. Exploded View of Alternator

b. The slip ring end head provides the mounting for the rectifiers and rectifier
mounting plate, output and auxiliary terminal studs, and the brush and holder assembly.
The slip ring end head contains a roller bearing and outer race assemblyand a grease seal.
c. The rectifiers used in these units are rated at 150 peak inverse voltage (P.I.V.)
minimum for transient voltage protection. Three positive rectifiers are mounted in the
rectifier mounting plate while the three negative rectifiers are mounted in the slip ring end
head. Each pair of rectifiers is connected to a stator lead with high temperature solder. The
stator leads are anchored to the rectifier mounting plate with epoxy cement for vibration
protection.
d. The stator contains a special lead which is connected to the center of the three phase
windings. The stator has been treated with a special epoxy varnish for high temperature
resistance.
e. The rotor contains the slip ring end bearing inner race and spacer on the slip ring end
of the shaft. The rotor winding and winding leads have been specially treated with a high
temperature epoxy cement to provide vibration and temperature resistance characteristics.
High temperature solder is used to secure the winding leads to the slip rings.
f. The drive end head supports a sealed, prelubricated ball bearing in which the drive
end of the rotor shaft rotates.

11-121., OVERHAUL OF ALTERNATOR. When repairing the alternator, complete

disassemblymay not be required. In some cases it will only be necessary to perform those
operations which are required to effect the repair. However, in this section, the complete
overhaul is covered step-by-stepto provide detailed information on each operation. In actual
service practice, these operations may be used as required.

Revised: 10/3/83 4D20 ELECTRICALSYSTEM

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362 361

Figure 11-72. Removal of Slip Ring Figure 11-73. Removal of Rectifier

End Bearing

11-122. DISASSEMBLYOF ALTERNATOR.

a. Remove the two Number 10-24screws holding the brush holder assemblyin the slip
ring end head. Remove the brush and holder assemblyfrom the end head.
b. Remove the safety wire from the through bolts. Hold the pulley with a strap wrench
and remove the pulley nut. The pulley must be removed with a puller. Remove the fan,
woodruff key and spacer from the shaft.
c. Remove the four through bolts and tap the drive end head lightly to separate the
drive end head and rotor, as a unit, from the stator and slip ring end head.
d. Remove the nuts, lock washers, flat washers and insulators from the output and
auxiliary terminal studs. Note carefully the correct assembly of the insulator washers and
bushings. Using the special tools shown in Figure 11-73, support the end head and press out
the three negative rectifiers. The end head can now be separated from the stator assembly.
e. To remove the slip ring end bearing and grease seal, it will be necessary to have a
hook type or impact type bearing puller as shown in Figure 11-72. Do not remove the
bearing unless replacement is necessary.

NOTE
The inner race of the slip ring end bearing is pressed onto the
rotor shaft. When bearing replacement is necessary, always
replace the complete bearing assembly, including the inner
race.

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363 364

Figure 11-74. Removal of Drive End Head Figure 11-75. Removal of End Head Bearing

f. To remove the drive end head from the rotor shaft, use a puller that grips on the
bearing retainer plate as shown in Figure 11-74. Do not attempt to remove by supporting
the end head and pressing on the shaft, as this may result in distortion of the end head or
stripping of the retainer plate screws. Remove the three retainer plate screws and press the
bearing out of the end head. (Refer to Figure 11-75.)

11-123.INSPECTION AND TESTING OF COMPONENTS.Upon completion of the

disassembly, all parts should be cleaned and visuallyinspected for cracks, wear or distortion
and any signsof overheating or mechanical interference.
a. Rotor: The rotor should be tested for grounded or shorted windings. The ground
test can be made with test probes, connected in series with a 110 volt test lamp, an
ohmmeter or any type of continuity tester. (Refer to Figure 11-76.) There must not be any
continuity between the slip rings and the rotor shaft or poles. To test for shorted turns in
the rotor winding, connect a voltmeter, ammeter and rheostat as shown in Figure 11-77, or
use an ohmmeter. Rotor current draw and resistance are listed in the Alternator ServiceTest
Specifications paragraph. Excessive current draw or a low ohmmeter reading indicates
shorted windings. No current draw or an infinite ohmmeter reading would indicate an open
winding.
b. Rectifiers: A diode rectifier tester will detect and pinpoint open or shorted
rectifiers without going through the operation of disconnectingthe stator leads. However, if
a tester is not available, test probes and a No. 57 bulb, connected in series with a 12 volt
battery, can be used in the following manner. Touch one test probe to a rectifier heat sink
and the other test probe to a lead from one of the rectifiers in that heat sink. Then reverse
the position of the leads. The test bulb should light in one direction and not light in the

Revised: 8/3/81 4D22 ELECTRICALSYSTEM

 PIPER CHEROKEE SERVICE MANUAL

365A 365B
RHEOSTAT

AMMETER

Figure 11-76. Testing Rotor for Ground Figure 11-77. Testing Rotor for Shorts

other direction. If the test bulb lightsin both directions, one or more of the rectifiers in that
heat sink is shorted. To pinpoint the defective rectifier, the stator leads must be
disconnected and the above test repeated on each rectifier. Open rectifiers can only be
detected, when using the test bulb, by disconnectingthe stator leads. The test bulb will fail
to light in either direction if the rectifier is open.
c. Stator: The stator can be tested for open or grounded windings with a 12 volt test
bulb, described in the rectifier section, or an ohmmeter, in the followingmanner. Separate
the stator from the slip ring end head just far enough to insert a fold of rags or blocks of
wood. In other words, insulate the stator from the end head. To test for grounded windings,
touch one test bulb or ohmmeter probe to the auxiliary terminal or any stator lead, and the
other test bulb or ohmmeter probe to the stator frame. If the test bulb lights, or the
ohmmeter indicates continuity, the stator is grounded. To test for open windings, connect
one test probe to the auxiliary terminal or the stator winding center connection and touch
each of the three stator leads. The test bulb must light, or the ohmmeter must show
continuity. Due to the low resistance in the stator windings, shorted windings are almost
impossible to locate. However, shorted stator windings will usually cause the alternator to
"growl" or be noisy during operation and will usually show some signsof overheating.If all
other electrical checks are normal and alternator fails to supply its rated output, the stator
should be replaced to determine whether or not it is the faulty component.
d. Bearingsand Seals: Wheneverthe alternator is overhauled, new bearings and oil or
grease seals are recommended, even though the bearings and seals appear to be in good
condition. A faulty seal can cause an alternator to fail within a very short period of time.

Reissued: 1/15/81 4D23 ELECTRICAL SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

366 367

Figure 11-78. Installation of Bearing Figure 11-79. Installation of Rectifier

11-124. ASSEMBLYOF ALTERNATOR.

a. Press the ball bearing into the drive end head using a flat block approximately two
inch square so that the pressure is exerted on the outer race of the bearing. Install the
retainer plate. With the snapring and retainer cup in place on the rotor shaft, use a tool that
fits over the shaft and against the inner bearing race, and press until the inner bearing race is
against the snap ring retainer cup. (Refer to Figure 11-78.)
b. Carefully install the rectifiers in the slip ring end head or rectifier mounting plate by
supporting the unit and using the special tools illustrated in Figure 11-79.

CAUTION
Use an arbor press, do not hammer. Reconnect the stator
leads to the rectifiers. When soldering these connections, use
pliers as a heat dam on the lead between the solder joint and
the rectifier. Too much heat will damage the rectifiers.

c. Reassemblethe rectifier mounting plate studs and insulators, making sure they are in
the correct order. (Refer to Figure 11-80.)
d. After the slip ring end head is completely assembled, the stator and rectifier leads
must be secured to the rectifier mounting plate with epoxy. Make sure the stator leads are
positioned so that they do not interfere with the rotor.
e. Install the slip ring end bearing and oil seal. Make sure the lip of the oil seal is
toward the bearing. Stake the seal in place. Correct assemblyof bearing, seal, inner race and
spacer as shown in Figure 11-81.

Revised: 8/3/81 4D24 ELECTRICALSYSTEM

 PIPER CHEROKEE SERVICE MANUAL

368

NUT
LOCKWASHER
FLATWASHER
FIBERWASHER
ENDHEAD

INSULATOR
RECTIFIERMOUNTING
PLATE

TERMINALSTUD

OUTPUT(+)
TERMINAL
AUXILIARY TERMINAL
TERMINAL PRESTOLITE ONLY

Figure 11-80. Terminal Assembly

f. Assemble the alternator and install the through bolts. Spin the rotor to make sure
there is no mechanical interference. Torque the through bolts to 30 to 35 inch pounds.
Safety wire should be installed after the unit has been bench tested for output. Install
spacer, woodruff key, fan, pulley, lock washer and nut. Torque the nut to 35 foot pounds,
using a strap wrench to hold the pulley.
g. Install the brush and holder assemblyand retaining screws.Spin the rotor and check
for interference between the brush holder and rotor. Check between the field terminal and
ground with an ohmmeter. The ohmmeter must indicate the amount of rotor resistance
listed with paragraph 11-125, Alternator ServiceTest Specifications.

11-125. TESTINGOF ALTERNATOR.

a. Wiringconnections for bench testing the alternator are shown in Figure 11-82. Refer
to the individual specification pages for output test figures. Adjust the carbon pile if
necessary, to obtain the specified voltage.
b. After bench testing the alternator, install the safety wire and install the alternator on
the engine.

NOTE
Always refer to the wiring diagram (Refer to Figure 11-55)
when installingthe alternator or testing the alternator.

Revised: 10/3/83 4E1 ELECTRICAL SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

369 370

SEAL-INSTALL SEAL
WITH LIP
TOWARDBEARING

INNER RACE

SPACER

Figure 11-81. Slip Ring End .Figure 11-82. Testing Alternator

Bearing Assembly

11-126. ALTERNATOR SERVICE TEST SPECIFICATIONS. Prestolite specifications for

the 14 volt alternators installed as standard equipment on PA-28 airplanes equipped with air
conditioning.

ALTERNATOR SPECIFICATIONS PRESTOLITE

Alternator Model ALY 6422

Voltage 12 volts
Rated Output 60 amperes
Ground Polarity Negative
Rotation Bi-Directional
Rotor:
Current Draw (77 F) 3.0 to 3.3 amps @ 12.0 volts
Resistance (77 F) 3.6 to 3.9 ohms

Output Test (77 F)

Volts 12.8 14.2
Amperes Output 10.0 65.2
Field Amperes 3.15 3.45
Alternator RPM 1730 min. 5000 min.

Revised: 10/3/83 4E2 ELECTRICALSYSTEM

 PIPER CHEROKEE SERVICE MANUAL

371 C326

PIN

END IVIEW SIDE VIEW

Figure 11-83. Brush Installation Figure 11-84. Internal Wiring Diagram

11-127. CHECKINGALTERNATORBELT TENSION.See paragraph 11-79, Checking

Generator and Alternator Belt Tension. For aircraft with airconditioning installed, see
paragraph 14-22, Section XIV, Replacementof compressor and/or Alternator Drive Belts.

11-128.,INSTRUMENTAND PANEL LIGHTS.The instrument and panel lights are

broken up into three groups; Lower Panel Light, Upper Panel Lights, and Compass Light.
The instrument lights are controlled by a 5 amp circuit breaker through a transistorized
dimmer. The dimmer control is located in the middle of the instrument panel just above the
pedestal. In earlier model airplanes there is one control knob connected to a varible resistor
that controls the intensity of the instrument lights. On 1974 model aircraft there is a second
control knob connected to a varible resistor which controls the light intensity for all the
avionic equipment. It may be necessary to gain access to the Dimmer Control Assembly;if
so follow the instructions givenbelow.

11-129. REMOVALOF DIMMERCONTROLASSEMBLY.

a. Access to the DimmerControl Assembly is from beneath the instrument panel.
b. Disconnect the electrical connection from the assembly.
c. Remove the two screwssecuringthe assemblyto the instrument panel.
d. Remove assemblyfrom the airplane.

11-130. INSTALLATION
OFDIMMERCONTROLASSEMBLY.
a. Position the assembly in the instrument panel with the control knobs inserted into
their appropriate slots.
b. Secure, the assembly to the instrument panel with the two screws previously
removed.
c. Connect the electrical connection to the assembly.
d. Check operation of DimmerControl Assembly.

Revised:8/3/81 4E3 ELECTRICAL SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

11-131. ANNUNCIATOR PANEL.

11-132. DESCRIPTION. The annunciator panel is a small cluster of lights which warn of
malfunctions in the various circuits or systems. A malfunction is identified by the
illumination of an individual warning light There are three amber waning lights and a
push-button test switch. (Refer to Figure 10-8.) Power is supplied from the bus bar
through a 5 amp fuse located behind the switch panel
The VAC warning light is controlled by a vacuum sensor switch located at the firewall
and is attached to the vacuum regulator. The sensor switch will activate when the
differential pressure is below 3.5 in. Hg.
The OIL warning light is controlled by an oil pressure sensor switch incorporated in the
oil line to the oil pressure gauge and is located at the firewall The sensor switch will activate
when the oil pressure is below 35 psi.
The ALT warning light is illuminated by current flowing from the bus bar to the
alternator circuit. (Refer to Figure 11-125.) This condition exists when the alternator is not
operating properly and the output is zero. During normal operation, the alternator warning
circuit is also supplied with power from the top diode terminal This current flows through a
5 amp fuse, located near the diode heat sink, to the resistor and diode creating a no-flow
condition which does not allow the warning light to light.
The test button is used to check the operation of the lights when the engine is running.
The lights will work when the engine is not running with the master switch turned on.
NOTE

Oil pressure sensor and vacuum sensor switches are similar in

looks and size. Insure correct unit is to be installed per Parts
Catalog part number and description.

11-133. REMOVALOF OIL PRESSURE SENSOR. Access to the sensor unit is gainedby
reaching up under the instrument panel. Removal is accomplishedby the following:
a. Disconnect the two electrical leads.
b. Unscrewthe sensor unit from the bulkhead fitting.
c. Catch spillageand cover hole to prevent foreign matter from entering oil line.

11-134. INSTALLATIONOF OIL PRESSURE SENSOR.

a. Seal sensor unit pipe threads with thread sealant tape (3M-TeflonNo. 48 x 1/4").
b. Screw the sensor unit into the bulkhead fitting.
c. Reconnect the two electrical leads.
d. Perform operational check.

11-135. REMOVAL OF VACUUM SENSOR. Access to the sensor unit is gained by

reaching up under the instrument panel to the vacuum regulator. Removal is accomplished
by the following:
a. Disconnect the two electrical leads.
b. Unscrewthe sensor unit from the vacuum regulator.
c. Cover hole to prevent foreign matter from entering regulator.

Revised: 8/3/81 4E4 ELECTRICALSYSTEM

 PIPER CHEROKEE SERVICE MANUAL

11-136. INSTALLATIONOF VACUUMSENSOR.

a. Screwsensor unit into vacuum regulator.
b. Reconnect the two electrical leads.
c. Perform operational check.

11-137. ANTI-COLLISIONLIGHT (ROTATINGBEACON).

11-138. REMOVAL.
a. Loosen screw securing clamp around rotating beacon lens. Remove clamp and lens.
b. Remove light bulb from bayonet socket.
NOTE
To remove complete rotating beacon assembly, remove
screws securing it to rudder tip. Next pull rotating beacon
assembly out and disconnect the electrical leads. Take note
of their placement to facilitate reinstallation. Rotating
beacon assemblycan now be removed.

11-139. INSTALLATION.
a. Install light bulb in bayonet socket.
b. Replacelens and clamp and secure by tightening screw on clamps.

11-140. ANTI-COLLISION(STROBE).

11-141. DESCRIPTION. The lights are located on each wing tip in the same assemblywith
the navigation lights on the fin tip. They are rated to flash at approximately 50 times a
minute. There is just one power supply for all three lights.

11-142. REMOVALOF WINGTIP STROBE LIGHT.

a. Remove the screw securingthe navigationlight coverand remove cover.
b. Remove the three screwssecuringnavigationlight bracket assembly and pull out.
c. Remove the strobe lamp by cutting the wires on the lamp beneath the mounting
bracket.
d. Remove the defective lamp.
e. Remove and discard the plug with the cut wires from its electrical socket.

Revised: 8/3/81 4E5 ELECTRICAL SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

11-143. INSTALLATIONOF WINGTIP STROBELIGHT.

a. Route the wires from the new lamp down through the hole in the navigation light
bracket.
b. Insert the wire terminals in the plastic plug supplied with the new lamp. Wire
according to the schematic diagram located in the back of this section.
c. Position strobe lamp on navigationlight bracket.
d. Securenavigationlight assemblyand bracket with appropriate screws.
e. Install navigationlight cover and secure with appropriate screw.

11-144. REMOVALOF FIN TIP STROBELIGHT.

a. Remove clamp securinglens to mounting plate on fin tip.
b. Remove lens from strobe light assembly.
c. Remove screwssecuringfin tip to fin.
d. Lift up fin tip and disconnect electrical plug.
e. Pull strobe light assembly out of fin tip, electrical plug will pull up through hole in
middle of mounting plate.

11-145. INSTALLATIONOF FIN TIP STROBE LIGHT.

a. Insert new electrical plug down through hole in mounting plate and position strobe
light assemblyin place.
b. Position lens in place.
c. Securelens to mounting plate by the clamp previously removed.
d. Reconnect electrical plugs underneath fin tip.
e. Replace fin tip and secure with appropriate screws.

11-146. REMOVALOF STROBE POWER SUPPLY. The strobe power supply is in the aft
section of the fuselage.
a. Remove access panel to the aft section of the fuselage in the rear baggage
compartment to gain accessto power supply.
b. To remove power supply disconnect the electrical plugs. (One to four plugs
depending on installation. Make note of the placement of the plugs to facilitate
reinstallation.)
c. Disconnect the other electrical leads.
NOTE
Make note of the placement of the leads to facilitate reinstallation.
d. Remove the four screws securing power supply to the fuselage. Power supply can
now be removed.

Revised: 8/3/81 4E6 ELECTRICALSYSTEM

 PIPER CHEROKEE SERVICE MANUAL

11-147.:INSTALLATION OF STROBE POWER SUPPLY. (Refer to Figure 11-143.)

a. Position the power supply in place and secure with the four screws previously
removed.
b. Reconnect the electrical leadsin their proper place.
c. Reconnect the electricalplugs previously removed in their proper place.
d. Replace accesspanel in rear baggagecompartment.

11-148. TROUBLESHOOTINGPROCEDURE. The strobe light functions as a condenser

discharge system. A condenser in the power supply is charged to approximately 450-volts
DC then discharged across the Xenon flash tube at intervals of approximately 50 flashesper
minute. The condenser is parallel across the Xenon flash tube which is designated to hold
off the 450-volts DCapplied until the flash tube is triggered by an external pulse. This pulse
is generated by a solid state timing circuit in the power supply.
When troubleshooting the strobe light system, it must first be determined if the trouble
is in the flash tube or the power supply. Replacement of the flash tube will confirm if the
tube is defective. A normally operating power supply will emit an audible tone of 1 to 1.5
KHZ. If there is no sound emitted, check the system according to the followinginstructions.
When troubleshooting the system, utilize the appropriate schematic at the back of this
section.
a. Ascertain the input voltage at the power supply is 14-volts.

CAUTION
When disconnecting and connecting the power supply input
connections, do not get the connections reversed. Reversed
polarity of the input voltage for just an instant will
permanently damage the power supply. The reversedpolarity
destroys a protective diode in the power supply, causing
self-destruction from overheating of the power supply. This
damage is sometimes not immediately apparent, but will
cause failure of the system in time.
b. Check for malfunction in interconnecting cables.
1. Ascertain Pins 1 and 3 of interconnecting cable are not reversed.
2. Using an ohmmeter, check continuity between Pin I and 3 of interconnecting
cable. If a reading is obtained on the meter, the cable is shorted and should be replaced.

NOTE
A short of the type described in Steps 1 and 2 will not cause
permanent damage to the power supply, but the system will
be inoperative if such a short exists. Avoid any connection
between Pins 1 and 3 of the interconnecting cable as this will
discharge the condenser in the power supply and destroy the
trigger circuits.

Revised:8/3/81 4E7 ELECTRICAL SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

CAUTION
When disconnecting the power supply, allow five minutes of
bleed down time prior to handling the unit.
c. Check interconnecting cables for shorts.
1. Disconnect the output cables from the power supply outlets.
2. The followingcontinuity checks can be made with an ohmmeter.
3. Check for continuity between the connectors of each interconnecting cable by
checking from Pin 1 to Pin 1, Pin 2 to Pin 2, and Pin 3 to Pin 3. Whenmaking these checks
if no continuity exists, the cable is broken and should be replaced.
4. Check continuity between Pins 1 and 2, 1 and 3, 2 and 3 of the interconnecting
cable. If continuity exists between any of these connections, the cable is shorted and should
be replaced.
d. Check the tube socket assemblyfor shorts.
1. Disconnect the tube socket assembly of the anti-collision light from the
interconnecting cable.
2. The followingcontinuity checks can be made with an ohmmeter.
3. Check for continuity between Pin I of AMP connector to Pin 1 of tube socket.
Pin 2 of AMP connector to Pins 6 and 7 of tube socket and Pin 3 of AMPconnector to Pin 4
of tube socket. Whenmaking these tests, if no continuity exists, the tube socket assemblyis
broken and should be replaced.

Reissued: 1/15/81 4E8 ELECTRICALSYSTEM

 PIPER CHEROKEE SERVICE MANUAL

901

L4B
BLACK

SPLIT SWITCH

OFF OFF
FIN WING

AN TI

BLACK (WITHSHIELD)

VIEW A WHITE

TO FIN TIP
(SEE VIEWA)

TO RIGHT
TO LEFT WINGTIP WING TIP
(SEE VIEWA) (SEEVIEW A)

REFERTO FIGURE11-139FORSCHEMATIC 28-140, 180,235, AND 28R-180 & 28R-200

Figure 11-144.Strobe Light Connections

Reissued: 1/15/81 4E9 ELECTRICALSYSTEM

 PIPER CHEROKEE SERVICE MANUAL

TABLEXI-II. ELECTRICALSYSTEMTROUBLESHOOTING

Trouble
I Cause Remedy

GENERATOR

Generator operating If the voltage is low, Check for loose or high-

within rated speed the generator is resistance connections;
range but voltage operating on re- clean and tighten.
output low. sidual magnetism.

Loose or high-resist- Clean and tighten all

ance electrical con- electrical connections.
nections.

Brushes excessively When brush wears down

worn. to 1/2 inch, replace
with a new one.

CAUTION

Do not use abra-

sives of any des-
cription in seat-
ing the brushes.

Brushes binding in the The brushes should be a

brush boxes. free fit without ex-
cessive side play in
the brush boxes. Bind-
ing brushes and the
brush boxes should be
wiped clean with a
cloth moistened in
a dry type cleaning
solvent.

Excessive side play of Replace the brushes as

brushes in brush outlined above.
boxes.

Reissued: 1/15/81
4E1O ELECTRICAL SYSTEM
 PIPER CHEROKEE SERVICE MANUAL

TABLEXI-II. ELECTRICALSYSTEMTROUBLESHOOTING(cont.)

Trouble
I Cause Remedy

GENERATOR (cont)

Generator operating Brushes not properly Reseat brushes as out-

within rated speed seated. lined above.
range but voltage out-
put low. (cont)
Low brush spring Brush spring should
tension. bear centrally on the
top of the brushes, in-
suring full brush con-
tact with the face of
the commutators

Dirty commutator. Clean the commutator

with a cloth moistened
in a dry type cleaning
solvent.

Scored or pitted com- Turn down commutator

mutator. or replace armature.

Shorted or open arm- Replace generator or

ature coils. armature.

Improper operation of Adjust regulator.

the voltage regulator.

Generator operating Wiring not properly See electrical system

within rated speed connected. wiring diagram.
range but voltmeter
indicates zero. Grounded or open Remove the generator
field coil assembly. and replace with one
known to be in good
condition.

Reissued: 1/15/81 4Ell ELECTRICAL SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

TABLEXI-II. ELECTRICALSYSTEMTROUBLESHOOTING(cont.)

Trouble
I Cause
I Remedy

GENERATOR (cont)

Generator operating Unstable operation of Replace voltage reg-

within rated speed the voltage regulator. ulator. Use remedy
range, but voltage Same as "Generator under "Generator
output is erratic.
operating within rated operating within rated
speed range but volt- speed range but volt-
age output "low", age output low", above.
above.

Excessive sparking at Same as "Generator Use remedy under

generator brushes. operating within rated "Generator operating
speed range but volt- within rated speed
age output low, above. range but voltage
output low", above.

Generator operating Generator field mag- Flash field with a

within rated speed netized in the wrong jumper wire on reg-
range but system am- direction. ulator between gen-
meter reads off scale. erator and battery.

System ammeter fluc- Generating system is Check the system for

tuates excessively overloaded. abnormal loads.
when indicating rated
load. Improper operation of Readjust to operate
generator reverse- properly.
current relay.

Loose connections. Tighten connections.

Burned-out system Discharged battery. Replace with a fully

ammeter or line fuse. charged battery.

Burned-out system Defective wiring. Replace all defective

ammeter or line fuse. wiring.

Reissued: 1/15/81 4E12 ELECTRICAL SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

TABLEXl-II. ELECTRICALSYSTEMTROUBLESHOOTING(cont.)

Trouble
I Cause
I Remedy

ALTERNATOR

Zero output indicated Open field circuit. With master switch

on ammeter regard- turned on, check for
less of RPM (refer to battery voltage from
alternator system test airplane's main buss
procedure). through entire field
circuit to alternator
field terminal. Mea-
sure voltage from
ground (-) to the follow-
ing points (+) in se-
quence: buss bar, out-
put circuit breaker (40A)
(60A), field circuit
breaker (5A), field
terminals of master
switch, voltage regu-
lator and alternator
field terminal.

Interruption of voltage
through any of these
points isolates the faulty
component or wire
which must be replaced.
(See wiring schematic. )

Open output circuit. With master switch

turned on, check for
battery voltage from
airplane's main buss
through entire output
circuit to alternator
battery post. Measure
voltage from ground (-)
to the following points
(+) in sequence: buss

Reissued: 1/15/81 4E13 ELECTRICAL SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

TABLEXI-II ELECTRICALSYSTEMTROUBLESHOOTING(cont.)

Trouble Cause
I Remedy

ALTERNATOR (cont)

Zero output indicated on Open output circuit. bar, output circuit

ammeter regardless of (cont) breaker, ammeter,
RPM (refer to alterna- and alternator battery
tor system test proce- post.
dure) (cont) Interruption of voltage
through any of these
points isolates the
faulty component or
wire which must be
replaced. (See wiring
schematic. )

Open field winding in Disconnect field termi-

alternator. nal of alternator from
field wiring and check
for continuity from field
terminal to ground with
ohmeter (20-100 ohms)
depending on brush
contact resistance.
(Pull propeller slowly
by hand turning alter-
nator rotor through
360° of travel.)

CAUTION

Turn magneto switch to

off before turning prop.

If resistance is high,
check brushes for
spring tension and ex-
cessive wear and re-
place if necessary. If
brushes are okay and

Reissued: 1/15/81 4E14 ELECTRICAL SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

TABLEXI-II. ELECTRICALSYSTEMTROUBLESHOOTING(cont.)

Trouble Cause Remedy

ALTERNATOR (cont)

Zero output indicated on Open output circuit. field reads open, re-
ammeter regardless of (cont) place alternator
RPM (refer to alterna-
tor system test proce-
dure) (cont)

Output indicated on Faulty voltage regu- Start engine, turn on

ammeter does not lator. load (Ref. alternator
meet minimum values test procedure), set
specified in alternator throttle at 2300 RPM.
system test procedure. Check voltage at buss
bar (convenient check
point, remove cigar
lighter and check from
center contact (+) to
ground (-). Voltage
should be 13.5 volts
minimum. If voltage
is below this value,
replace regulator.

High resistance con- Check visually for loose

nections in field or binding posts at the
output circuit. various junction points
in system, alternator
battery post, lugs on
ammeter, connections
at voltage regulator,
circuit breaker, etc.,
(See wiring schematic. )
Examine crimped ter-
minal ends for signs of
deterioration at crimp
or strands of broken
wire at crimp. Tighten
any loose binding posts.

Reissued: 1/15/81 4E15 ELECTRICAL SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

TABLE XI-II. ELECTRICALSYSTEMTROUBLESHOOTING(cont.)

Trouble
I Cause
I Remedy

ALTERNATOR (cont)

Output indicated on High resistance connec- or replace bad wire

ammeter does not tions in field or output terminals.
meet minimum values circuit. (cont)
specified in alternator
system test procedure.
(cont)
Open rectifier. If any of the six recti-
fiers pressed into the
rear bell housing of the
alternator open up
internally, it will result
in a definite limitation
on the current that can
be drawn from the
alternator. After
having checked the
previous causes of low
output it can be assum-
ed that a faulty rectifier
exists.
See paragraph's titled Testing
of Rectifiers or Inspection and
Testing of Components
Field circuit breaker Short circuit in field Disconnect field wiring
trips. circuit. at terminal of alter-
nator. Turn on master
switch. If breaker
continues to trip, pro-
ceed to disconnect each
leg of field circuit,
working from the alter-
nator towards the cir-
cuit breaker until
breaker can be reset
and will hold. Replace
component or wire

Reissued: 1/15/81 4E16 ELECTRICAL SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

TABLEXI-I. ELECTRICALSYSTEMTROUBLESHOOTING(cont.)

Trouble
I Cause Remedy

ALTERNATOR (cont)

Field circuit breaker Short circuit in field which was isolated as

trips. (cont) circuit. (cont) defective. (See wiring
schematic. )

Short circuit in field Disconnect field wiring

winding of alternator. at terminal of alter-
nator. Turn on master
switch. Reset breaker
and if breaker fails to
retrip, this isolates
short circuit to field of
alternator itself. Check
brush holders for
shorting against frame.
If there are no obvious
signs of a physical
short circuit at field
terminal or brush
holder, replace alter-
nator. (Note: Inter-
mittent short circuit.)
Internal short circuiting
of the field can occur
at various positions of
the rotor, therefore,
reconnect field, reset
breaker, pull propeller
slowly by hand turning
alternator rotor through
360° of travel. Observe
circuit breaker for
signs of tripping.

Reissued: 1/15/81 4E17 ELECTRICAL SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

TABLEXI-II. ELECTRICALSYSTEMTROUBLESHOOTING(cont.)

Trouble Cause Remedy

ALTERNATOR (cont)

Field circuit breaker Short circuit in field CAUTION

trips. (cont) winding of alternator.
(cont) Turn magneto switch to
off before turning pro-
peller .

Output circuit breaker Short circuit in output Disconnect wiring at

trips. circuit.. battery post of alter-
nator. Turn on master
switch. Reset breaker
and if breaker continues
to trip, proceed to dis-
connect each leg of out-
put circuit, working
from the alternator
towards the circuit
breaker until breaker
can be reset and will
hold. Replace com-
ponent or wire which
was isolated as defec-
tive. (See schematic. ).

Shorted alternator Disconnect wiring at

diode. battery post of alter-
nator. Turn on master
switch. Reset breaker
and if breaker fails to
retrip, this isolates
short circuit to alter-
nator. Replace alter-
nator.

Battery installed with Remove battery and

reversed polarity. reinstall with correct
polarity.

Reissued: 1/15/81
4E18 ELECTRICAL SYSTEM
 PIPER CHEROKEE SERVICE MANUAL

TABLE XI-II. ELECTRICALSYSTEMTROUBLESHOOTING(cont.)

Trouble
I Cause
I Remedy

ALTERNATOR (cont)

Output circuit breaker Battery charged back- Remove battery. Con-

trips. (cont) wards. nect load such as land-
ing light lamp or simi-
lar load and discharge
battery. Recharge
with correct polarity
and test each cell for
signs of damage due to
reversed charging.

NOTE

This type of condition

can only occur in a
case where a dis-
charged battery has
been removed from the
airplane and put on a
charger with the
polarity reversed.
This reversal in
polarity cannot occur
in the airplane due to
any fault in the alter-
nator system.

Excessiveammeter Excessiveresistance Check all connections

fluctuation. in field circuit. and wire terminals in
field circuit for de-
terioration such as
loose binding posts,
broken wire strands at
terminals, etc. Tighten
all connections and
replace faulty term-
inals

ELECTRICAL SYSTEM 4E19 Reissued:1/15/81

 PIPER CHEROKEE SERVICE MANUAL

TABLEXI-II. ELECTRICALSYSTEMTROUBLESHOOTING(cont.)

Trouble Cause Remedy

ALTERNATOR (cont)

Excessive ammeter High field circuit If problem persists,

fluctuation. (cont) resistance. jump across terminals
of the following com-
ponents one at a time
until the faulty unit
is isolated.
a. Field 5 amp (al-
ternator) circuit
protector.
b. Alternator half
of master switch.
c. Overvoltagerelay.
Defectivevoltage Replacevoltage regu-
regulator. lator.

Reissued: 1/15/81 ELECTRICAL SYSTEM

4E20
 PIPER CHEROKEE SERVICE MANUAL

TABLE XI-II. ELECTRICALSYSTEMTROUBLESHOOTING(cont.)

Trouble Cause

STARTER
I Remedy

Motor fails to operate. Low battery charge. Check and recharge if

necessary.

Defective or improper Refer to electrical

wiring or loose wiring diagram and
connections. check all wiring.

Defective starter Replace faulty unit.

solenoid or control
switch.

Binding, worn, or im- Brushes should be a free

properly seated fit in the brush boxes
brush, or brushes without excessive side
with excessive side play. Binding brushes
play. and brush boxes should
be wiped clean with a
gasoline (undoped)
moistened cloth. A new
brush should be run in
until at least 50 percent
seated; however, if
facilities are not avail-
able for running in
brushes, then the brush
should be properly
seated by inserting a
strip of number 000
sandpaper between the
brush and commutator,
with the sanded side
next to the brush. Pull
sandpaper in the direc-
tion of rotation, being
careful to keep it in the
same contour as the

Reissued: 1./15/81 4E21 ELECTRICAL SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

TABLEXI-II. ELECTRICALSYSTEMTROUBLESHOOTING(cont.)

Trouble Cause
I Remedy

STARTER (cont)

Motor fails to operate. Binding, worn, or im- commutator.

(cont) properly seated
brush, or brushes CAUTION
with excessive side
play. (cont) Do not use coarse
sandpaper or emery
cloth. After seating,
clean thoroughly to
remove all sand and
metal particles to
prevent excessive
wear. Keep motor
bearing free from
sand or metal particles.

Dirty commutator. If commutator is rough

or dirty, smooth and
polish with number 0000
sandpaper. If too rough
and pitted, remove and
turn down. Blow out
all particles.

Shorted, grounded, Remove and replace with

or open armature. an armature known to
be in good condition.

Grounded or open Test, repair if possible

field circuit. or replace with a new
part.

Low motor and crank- Worn, rough, or im- Disassemble, clean, in-
ing speed. properly lubricated spect, and relubricate,
motor or starter replacing ball bearings
gearing. if worn.

Reissued: 1/15/81 4E22 ELECTRICAL SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

TABLEXI-II. ELECTRICALSYSTEMTROUBLESHOOTING(cont.)

Trouble
I Cause
I Remedy

STARTER (cont)

Low motor and crank- Same electrical causes Same remedies listed
ing speed. (cont) as listed under "Motor for these troubles.
fails to operate".

Excessive arcing of Binding, worn, or im- See information above

motor brushes. properly seated brush dealing with this
or brushes with ex- trouble.
cessive side play.

Dirty commutator, Clean as outlined above.

rough, pitted, or
scored.

Excessive wear and Rough or scored Remove and turn com-

arcing of motor commutator. mutator down on a lathe.
brushes.
Armature assembly Reface commutator.
not concentric.

Reissued:1/15/81 4E23 ELECTRICAL SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

TABLEXI-II. ELECTRICALSYSTEMTROUBLESHOOTING(cont.)

Trouble Cause Remedy

BATTERY

Discharged
schargedbattery.
battery. Battery worn out. Replace battery.

Charging rate not Reset.

set right.

Standing too long. Remove and recharge

charge
battery if left in
unused airplane three
weeks or more.

Equipment left on Remove and recharge.

accidentally.

Impurities in Replace.
electrolyte.

Short circuit (ground) Check wiring.

in wiring.

Broken cell partitions. Replace.

Battery life is short. Overcharge due to Maintain electrolyte.

level of electrolyte
being below top of
plates.

Sulfation due to disuse. Replace.

Impurities in electro- Replace battery.

lyte.

Low charging rate. Adjust voltage regulator.

Reissued: 1/15/81 4E24 ELECTRICAL SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

TABLEXI-II. ELECTRICALSYSTEMTROUBLESHOOTING(cont.)

Trouble
I Cause Remedy

BATTERY (cont)

Cracked cell jars. Hold-down bracket Replace battery and

loose. tighten.

Frozen battery. Replace.

Compound on top of Charging rate too Reduce charging rate by

battery melts. high. adjusting voltage regu-
lator or replace tran-
sistorized regulator.

Electrolyte runs out Too much water added Drain and keep at proper
of vent plugs. to battery and charg- level and adjust voltage
ing rate too high. regulator.

Excessive corrosion Spillage from over- Use care in adding

inside container. filling. water.

Vent lines leaking or Repair or clean.

clogged.

Charging rate too high. Adjust voltage regulator.

Battery freezes. Discharged battery. Replace.

Water added and Always recharge battery

battery not charged for 1/2 hour following
immediately. addition of water in
freezing weather.

Leaking battery jar. Frozen. Replace.

Battery polarity Connected backwards Battery should be slowly

reversed. on airplane or discharged completely
charger. and then charged
correctly and tested.

Reissued: 1/15/81 ELECTRICAL SYSTEM

4F1
 PIPER CHEROKEE SERVICE MANUAL

TABLEXI-II. ELECTRICALSYSTEMTROUBLESHOOTING(cont.)

Trouble Cause Remedy

BATTERY (cont)

Batter y consumes Charging rate too high Correct chargi ng rate.

excessive water.
exces (if in all cells).

Cracked jar (one cell Replace battery

attery.
only).

Reissued: 1/15/81 4F2 ELECTRICAL SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

TABLEXI-II. ELECTRICALSYSTEMTROUBLESHOOTING(cont.)

Trouble Cause Remedy

ANNUNCIATORPANEL

All the warning lights Blown fuse., Replace the 5 amp fuse
fail to operate. behind instrument panel.
No current from bus. Check all wire segments,
connections, and the
receptacle at the left
side of the annunciator
panel.

All the warning lights Test switch grounded Check terminals and
fail to extinguish out. replace switch if
after engine is running. necessary.

OIL warninglight Bulb burned out. Replace.

fails to operate.
No current to sensor. Check all wire segments
and connections.
Sensor activates at a Replace.
too low setting.
Defectivesensor. Replace.

OIL warning light Sensoractivates at a Replace.

fails to extinguish. too high setting.
Sensorterminals Remove material
bridged. between terminals.
Defectivesensor. Replace.

Reissued: 1/15/81 4F3 ELECTRICAL SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

TABLE XI-II. ELECTRICALSYSTEMTROUBLESHOOTING(cont.)

Trouble Cause Remedy

ANNUNCIATORPANEL(cont.)

VAC warninglight fails Bulb burned out. Replace.

to operate.
No current to sensor. Check all wire segments
and connections.

Sensor activates at a Replace.

too low setting.
Defectivesensor. Replace.

VAC warning light fails Sensor activates at a Replace.

to extinguish. too high setting.
Sensor terminals Remove material
bridged. between terminals.

Defectivesensor. Replace.

ALT warning light fails Bulb burned out. Replace.

to operate.
No current from bus Check all wire segments
to resistor. and connections.

ALT warning light fails Blown fuse. Replace 5 amp fuse

to extinguish. near the diode heat
sink.

No current from the Check all wire segments

fuse to the resistor. and connections.

Test switch fails to Bad switch or Check wires and replace

activate warninglights. connections. switch if necessary.

Reissued:1/15/81 4F4 ELECTRICAL SYSTEM

 PIPER CHEROKEESERVICEMANUAL

NOTE: TERMINAL 12 AS SHOWN USED

ON PA-21 R MODELS TO SERIAL
NOS. 28R-7335055 INCLUSIVE.

12
012
012

LIG

Q4B 10
Q4B

Q3A
FIB
FIC

L4E
74E
L45

06B

Q7B
PA-28-140 SERIAL NOS. 28-25000 TO
28-7425454 INCLUSIVE.
4 PA-28-180 SERIAL NOS. 28-4378 TO
28-7405290 INCLUSIVE.

PA-28-235 SERIAL NOS. 28-11040 TO

28-7410120 INCLUSIVE.

PA-28R-180 (ALL) PA-28R-200

SERIAL NOS. TO 28R-7435331
INCLUSIVE.

Figure 11-53. Terminal Block

Reissued: 1/15/81 ELECTRICALSYSTEM

4F5
 PIPER CHEROKEE SERVICE MANUAL

2 2
3
4 4
4 4
5 5
6 6 6 6
7 7
8 8
9 9
10 10

UPPER PANEL LOWER PANEL

PA-28-235 SERIAL NOS. 28-10003 TO 28-11039 INCLUSIVE.

PA-28-140 SERIAL NOS.

28-20002 TO 28-24999 INCLUSIVE
PA-28-150, PA-28-160 AND PA-28-130 PA-28-150, PA-28-160, AND
SERIAL NOS. 28-1411 TO 2-4377 PA-28-180 SERIAL NOS.
INCLUSIVE. 28-1 TO 2-14 10 INCLUSIVE.

Figure 11-53. Terminal Block (cont.)

ELECTRICAL SYSTEM
Reissued:1/15/81 4F6.
 PIPER CHEROKEESERVICEMANUAL

012 012 012

PA-28-140 SERIAL NOS. 28-7525001 & UP

012

PA-28-235 SERIAL NOS. 28-7510001

AND UP

PA-28 R-200 SERIAL NOS.

28 R-7535001 AND UP

PA-28-180 SERIAL NOS. 28-7505001 & UP

Figure 11-53. Terminal Block (cont.)

Reissued:1/15/81 4F7 ELECTRICALSYSTEM

 PIPER CHEROKEE SERVICE MANUAL

TABLEXI-III. ELECTRICALSYSTEMCOMPONENTLOADS

-DUTY CYCLE EQUIPMENT LOAD PA-28-

CONT. INMT. (AMPS) 140 *180 235 PA-28R

X Anti-CollisionLight
(2) Grimes D7080A-3-12 Each 6.0 X
Grimes 40-0101-XX-12 3.5 X X X X
Whelen WRML-12 3.5 X X X
Whelen Red Strobe 3.4 OPT OPT OPT OPT
Whelen Red/White Strobe 3.8 OPT OPT OPT OPT
X Position Lights 4.0 X X X X
X Landing Lights 8.0 X X X X
X Instrument Light(s) (Max)
Red Flood 1.0 X X X X
Panel 2.4 X X X
X Reading Light
Dome 0.6 X X X X
X Fuel Pump
Pulsating (Carb) .5 X X X
Rotary (Fuel Inj't) 6.0 X
X Engine Gages Approx 1.0 X X X X
X Elec. Turn & Bank 0.5 X X X X
X Pitot Heat 13.2 X X X
17.0 X
X Cigar Lighter 8.0 X X X X
X Master Solenoid 0.8 X X X X
X Starter Solenoid 10.0 X X X X
X Landing Gear
Pump (Circuit breaker) 25.0 X
Solenoid 0.8 X
X Gear Down Lights Total 0.3 X
X AutoPilot (Avg) 0.6
Radio (See Mfg's Installation
Manual)

*Also 150 & 160

Reissued: 1/15/81 4F8 ELECTRICAL SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

TABLEXI-IV. ELECTRICALSYMBOLS

CIRCUIT BREAKER BATTERY SWITCH

GROUND BATTERY SWITCH
BUSBAR

RESISTOR FUSE DIODE

DIODE
LIGHT

NNECTORS

NOISE
KNIFE FILTER
DISCONNECT
WING ROOT
PRESSURE SOLENOID CONNECTOR
CONNECTOR PIN
PIN
SWITCH

INSULATEDCONNECTOR SHIELDEDCONDUCTORS

USH-BUTTON
SWITCH

*CONDUCTORS

•CONDUCTORS:CROSSINGSAND JUNCTIONSOF CONDUCTORS.

THE DOT AT THE INTERSECTION INDICATES A JOINING OF
CONDUCTORS.

Reissued: 1/15/81
4F9 ELECTRICAL SYSTEM
 .~~Y , ~ . . .A. _ = =

PIPER CHEROKEE SERVICE MANUAL

TABLEXI-V. "ELECTRICALWIRECODING

WIRENUMBER
WIRE SEGMENTLETTER
I WIREGAUGE
P7A

CIRCUIT FUNCTION
LETTER CIRCUITS

A AUTOPILOT
C CONTROLSURFACE
E ENGINEINSTRUMENT
F FLIGHT INSTRUMENT
G LANDINGGEAR
H HEATER - VENTILATING& DEICING
L LIGHTING
P POWER
Q FUEL & OIL
RP RADIO POWER
RZ RADIO AUDIO& INTERPHONE
J IGNITION
RG RADIO GROUND
W WARNING
K STARTER

ELECTRICAL SYSTEM
Reissued: 1/15/81 4F10
 PIPER CHEROKEE SERVICE MANUAL

Figure 11-55. Electrical System Schematic, PA-28-140, Serial Nos. 28-25000 to 28-7325052 incl.

Reissued:1/15/81 ELECTRICAL SYSTEM

4F13 4F14
 PIPER CHEROKEE SERVICE MANUAL

Figure 11-56. Electrical System Schematic, PA-28-150, -160, Serial Nos. 28-1 to 28-507 incl.

Reissued: 1/15/81 ELECTRICAL SYSTEM

4F15 4F16
 O~-

E3II-r
-

'

, ——
I
IIi
WHY
- T\ B<• —

1am

l z

n C0
\0u
 PIPER CHEROKEE SERVICE MANUAL

EXTERNAL o
POWER 0
RECEPTACLE
OPTIONAL

ALTERNATOR

STARTER
10 AMP
FUSE

CAPACITOR SEE RADIO

LIFT INDICATOR

DOME LIGHT
SWITCH

VOLTAGE
REGULATOR

RADIOINTERFERENCE
FILTER ASSY

Figure 11-58. Electrical System Schematic, PA-28-150, -160, -180, Serial Nos. 28-671 to 28-1760 incl.

Reissued: 1/15/81 ELECTRICAL SYSTEM

4F19 4F20
 0

0
m
 PIPER CHEROKEE SERVICE MANUAL

~
0

SEE RADIO

Figure 11-60. Electrical System Schematic, PA-28-150, -160, -180, Serial Nos. 28-3644 to 28-4377 incl.

Reissued: 1/15/81
ELECTRICAL SYSTEM
4F23
4F24
 w

I
oo

z z

I I 0o -
 PIPER CHEROKEE SERVICE MANUAL

Figure 11-62. Electrical System Schematic, PA-28-180, Serial Nos. 28-5228 to 28-7305063 incl.

Reissued: 1/15/81 ELECTRICAL SYSTEM

4G3 4G4
 PIPER CHEROKEE SERVICE MANUAL

S EE NOT T L°T

Figure 11-63. Electrical System Schematic, PA-28-235, Serial Nos. 28-10003 to 28-10719 incl.

ELECTRICAL SYSTEM
Reissued: 1/15/81
4G5 4G6
 U

0
z

Ir

I II
 t

1.I...O 3 -- -
-_ - _ - _-_- - - - - - --- - <1 - -- - - - 8s
s^—6 I- l — ^—6—0
 _L-iL
---- ICIY

PIPER CHEROKEE SERVICE MANUAL

6 —MAIN BUS

G I\-_-'_ o LANDINGGEARCONTROL
GC6c)—--
-(11—osB —--c( R^ a6WARNINGCIRCUIT
'"J'—CCSAD—[^
BREAKER (5 AMP)

FLASHER G

NC

Figure 11-69. Landing Gear Back-up Actuator Override Mechanism

MAIN BUS
FLASHER "1 LANDINGGEARCONTROL
J WARNINGCIRCUIT
BREAKER (S AMP)

NC

Figure 11-70.Landing Gear Back-up Actuator Override Mechanism

Reissued: 1/15/8 Reissued:

1 4G17
~41/1/7RC ELECITRICALLSSE
SYSTEM
 4G18
INTENTIONALLYLEFT BLANK
 PIPER CHEROKEE SERVICE MANUAL

NOTE
Figures 11-71thru 11-84have been used for illustrations in the
context of Section XI. See List of Illustrations for index to
these figures.

ELECTRICALSYSTEM
Reissued:1/15/81 4G19
 PIPER CHEROKEE SERVICE MANUAL

ALTERNATOR

I
I
I
I
AMMETER
ALTERNATOR
OUTPUT
FILTER
CAPACITOR

\ STARTER & ACC.

I 15 AMP
I I
I EXTERNAL

HIA

II EXTERNAL
POWER
I RECEPTACLE

I I
I
I

MECHANICAL
CIGAR
INTERLOCK LIGHTER
STARTER

ALTERNATOR SOURCE
PA-28-140, Serial Nos. POWER RELAY
28-25000 to 28-7325052 Incl. ENERGIZING CIRCUIT

Figure 11-85. Alternator, Starter, Cabin Light, Cigar Lighter and

External Power Receptacle

Reissued: 1/15/81 4G20 ELECTRICAL SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

ALTERNATOR
FIELD 5 AMP

ALTERNATOR
AMMETER OUTPUT
AMP
CIRCUIT BREAKER
FILTER
CAPACITOR

I
b STARTER & ACC.
IS AMP

EXTERNAL
HIA

EXTERNAL
POWER
RECEPTACLE

L MECHANICAL CIGAR
INTERLOCK LIGHTER

ALTERNATORSOURCE
POWER RELAY
ENERGIZING CIRCUIT

PA-28-140, Serial Nos. 28-7325053 to 28-7425454 Incl.

Figure 11-86. Alternator, Starter, Cabin Light, Cigar Lighter and

External Power Receptacle

Reissued:1/15/81 4G21 ELECTRICAL

ELECTRICAL
SYSTEM
 PIPER CHEROKEE SERVICE MANUAL

GENERATOR
FIELD
5 AMP

AMMETER

FILTER
CAPACITOR

OPTIONAL STARTER & ACC.

15 AMP

EXTERNAL
POWER
SOLENOID
HIA

EXTERNAL
POWER
RECEPTACLE

MECHANICAL _ CIGAR
LIGHTER
INTERLOCK

9
IGENERATOR SOURCE
PA-28-180 Serial Nos. POWER RELAY
28-5228 to 28-7305063 Incl. ENERGIZING CIRCUIT
PA-28-235, Serial Nos.
28-11040 to 28-7310038 Incl.

Figure 11-87. Alternator, Starter, Cabin Light, Cigar Lighter and

External Power Receptacle

Reissued: 1/15/81 4G22 ELECTRICAL SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

MASTER
GENERATOR
FIELD 5 AMP

OPTIONAL
STARTER & ACC.
15 AMP

EXTERNAL
POWER
SOLENOID
HIA

I
EXTERNAL
POWER
RECEPTACLE

MECHANICAL CIGAR
INTERLOCK LIGHTER

GENERATOR SOURCE
PA-28-235,Seral Nos. POWER RELAY
28-7310039 to 28-7310187 Incl. ENERGIZING CIRCUIT

Figure 11-88.Alternator, Starter, Cabin Light, Cigar Lighter and

External Power Receptacle

ELECTRICALSYSTEM
Reissued:1/15/81 4G23
 PIPER CHEROKEE SERVICE MANUAL

ALTERNATOR
FIELD 5 AMP

FILTER
CAPACITOR

OPTIONAL
STARTER &
ACCESSORY
15 AMP
EXTERNAL
POWER
SOLENOID

EXTERNAL
IPOWER
RECEPTACLE

MECHANICAL CIGAR
INTERLOCK LIGHTER

PA28-180, Serial Nos. 28-730064 to ALTERNATOR SOURCE

28-7405290 Incl. POWER RELAY
PA-28R-200, Serial Nos. 28-7335055 to ENERGIZING CIRCUIT
28-7435331 Incl.
PA28-28-235,Serial Nos. 28-7410001 to
28-7410120 Incl.

Figure 11-89. Alternator, Starter, Cabin Light, Cigar Lighter and

External Power Receptacle

Reissued:1/15/81 4G24 ELECTRICAL SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

NOTES - LANDING
GEAR LANDING GEAR
I. GEAR SHOWN IN LOCKED DOWN CONTROL a WARNING
POSITION WITH STRUTS COMPRESSED ACTUATOR
25 AMPS 5 AMP
AND THROTTLE CLOSED.
2. AUTOMATIC GEAR DOWN ACTUATOR
SWITCH SHOWN IN LOW AIRSPEED POSITION.
3.

SWITCH

THROTTLE
SWITCH
"A"

PA-28R-200,Serial Nos. 28-7335055 to 28-7335455 Incl.

Figure 11-90. Landing Gear

Reissued: 1/15/81 4H1 ELECTRICALSYSTEM.

 PIPER CHEROKEE SERVICE MANUAL

CONTROL
WARNING
TERMINAL 5AMP

NOTE :
I EAR SHOWNIN LOCKEDDOWN
POSITION WITH STRUT COMPRESSED
AND THROTTLE CLOSED.
AUTOMATICGEAR DOWNACTUATION
SWITCH SHOWN IN LOW AIRSPEED
POSITION.
3. LEGEND:
RL- RED LIGHT
YL- YELLOW LIGHT
GL- GREEN LIGHT
C- COMMON
NC- NORMALLY CLOSED
NO- NORMALLY OPEN

PA-28R-200, Serial Nos.28-7435001 to28-7435331 Incl.

Figure 11-91. Landing Gear

Reissued: 1/15/81 4H2 ELECTRICAL SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

AUDIO PANEL COMM/NAV I a GLIDE SLOPE COMM/NAV II

AMP 15 AMP 15AMP

SEE RADIO SEE RADIO SEE GLIDE SLOPE SEE RADIO

SYSTEM:S INSTL. INSTALLATION INSTALLION INSTALLION

ADF & MARKER BEACON DME

AMP 10 AMP

SEE ADF SEE M.B. SEE DME

INSTALLATION INSTALLATION
INSTALLATION INSTALLATION

PA-28-140, Serll Nos. 28-732505 3 to 28-7425454 Incl.

Figure 11-92.Avionics

TRANSPONDER DME GLIDE SLOPE MARKER BEACON

5 AMP 10
AMP 5 AMP 5 AMP

RPB RP7 RP6 RP5

SEE SEE SEE G/S SEE M/9

TRANSPONDER DME INSTALLATION INSTALLATION
INSTALLATION INSTALLATION INSTALLATION
_
ADF NAV COMM II NAV COMM I AUDIO AMPLIFIER AUTOPILOT

5 AMP 15 AMP 15 AMP AMP

5 5 AMP

RP3 RP2 RPI RP4

SEE RADIO RADIO SEE RADIO SEE RADIO SEE RADIO SEE
SYSTEM AUTO PILOT
PILOT
INSTALLATION INSTALLATION INSTALLATION SYSTEM INSTALLATION INSTALLA
INSTALLATION INSTALLATION
_ _

PA-28-180 Serial Nos.28-7305064 to28-7305611 Incl. PA-2R-200.Serial Nos. 2-7335055 to28-7335455 Incl.
PA-28-35,Serial Nos.28-7310039 to 28-7310187 Incl.

Figure 11-93. Avionics

Reissued: 1/15/81 4H3 ELECTRICALSYSTEM

 PIPER CHEROKEE SERVICE MANUAL

AUDIO PANEL COMM/NAV I a GLIDE SLOPE COMM/ NAV II

5AMP 15 AMP 15 AMP

SEE RADIO SEE SEE SEE

SYSTEMS RADIO GLIDE SLOPE RADIO
INSTALLATION INSTALLATION INSTALLATION INSTALLATION

ADF & MARKER BEACON DME TRANSPONDER AUTO PILOT

AMP 10 AMP 5 AMP 5 AMP

Y
SEE SEE SEE SEE SEE
ADF MARKER DME TRANSPONDER AUTOPILOT
INSTALLATION INSTALLATION INSTALLATION INSTALLAT ION INSTALLATION

PA-28-180, Serial Nos. 28-7405001 to 28-7405290 Incl.

PA-28-235, Serial Nos. 28-7410001 to 28-7410120 Incl.

Figure 11-94. Avionics

TRANSPONDER DME GLIDE SLOPE MARKER BEACON

I 5 AMP 10 AMP 5 AMP 5 AMP

SEE SEE SEE

TRANSPONDER G/S M/S
INSTALLATION INSTALLATION INSTALLATION

ADF NAV-COMM II NAV-COMMI AUDIO AMPLIFIER AUTO PILOT

5 AMP 15 AMP 15 AMP 5 AMP AMP

Y Y
SEE EE SEE SEE SEE AUTO CONTROL
RADIO RADIO RADIC RADIO SYSTEM OR AUTO FLITE
INSTALL ATION INSTALLATION INSTALLATION
INSTALLATION INSTALLATION INSTALLATION

PA-28R-200, Serial Nos. 28-7435001 to 28-7435331 Incl.

Figure 11-95. Avionics

Reissued:1/15/81 4H4 ELECTRICAL SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

ENGINE
GAUGES
5 AMP

LEFT RIGHT
TANK TANK

PA-28-140, Serial Nos. 28-7325053 to 2-7425454 Incl.

PA-28-180, Serial Nos. 28-7405001 to 28-7405290 Inl.
PA-2R-200, Serial Nos 28-7435001 to 2-7435331 ncl.

Figure 11-96. Engine Gauges

ENGINE
GROUP
5 AMP

FUEL TANK
SENDERS

PA-28-180, Serial Nos. 28-7305064 to 2-7305611 Incl.

PA-28R-200, Serial Nos. 2-7335055 to 2-7335455 incl.

Figure 11-97. Engine Gauges

ReiReissued: 4H5
1/15/81 4H5 ELECTRICAL
SYSTEM
ELECTRICALSYSTEM
 PIPER CHEROKEE SERVICE MANUAL

PA-28-235, Serial Nos. 28-7310039 to 28-7410120 Inl.

Figure 11-98. Engine Gauges

INSTRUMENT INSTRUMENT
LIGHTS LIGHT
5 AMP
NAV LIGHT
SWITCH

COMPASS
LIGHT

PA-28-140, Serial Nos. 28-7325053 to 28-7325684 Incl.

Figure 11-99. Instrument Lights

Reissued: 1/15/81 4H6 ELECTRICAL SYSTEM

 PIPER CHEROKEESERVICEMANUAL

INSTRUMENT
LIGHTS
5 AMP

INSTRUMENT
COMPASS FLOOD
LIGHT LIGHT

PA-28-140, SerialNos. 28-7325053 to 28-7425454 Inl.

Figure 11-100. Instrument Lights

PA-28-180, Serial Nos.28-7305064 to28-7305611 incl.

Figure 11-101.Instrument Lights

Reissued: 1/15/81 4H7 ELECTRICALSYSTEM

 PIPER CHEROKEE SERVICE MANUAL

INSTRUMENT
PANELLIGHTS LOWER PANEL LIGHTS

UPPER PANEL LIGHTS

PA-28-10, Serial Nos. 2-74050001 to 28-7405290 incl.

Figure 11-102.Instrument Lights

INSTRUMENT LIGHTS (PANEL) INSTRUMENTLIGHTS (OVERHEAD)

TO LANDING GEAR TO NAV
LIGHT
SWITCH LIGHT SWITCH
5 AMP INSTRUMENT LIGHT
INTENSITY CONTROL
NOTES:
1. INTENSITY CONTROL
RI COMPONENTVALUES RI
Q2 RI-2.5K.5W Q2
R2-100K 2W
QI- 2N669
QZ-2N443 R2
R2 2. LIGHT LEGEND
RL- RED LIGHT

RL

PA-28R-200.Serial Nos.28-7335055 to 28-7335455 Incl.

Figure 11-103. Instrument Lights

Reissued: 1/15/81 4H8 ELECTRICAL SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

INSTRUMENT
LOWER PANEL LIGHTS

COMPASS
LIGHT

INSTRUMENT

PA-28R-200, Serial Nos. 28-7435001 to 28-7435331 Incl.

. Figure 11-104. Instrument Lights

PA-28-235 Serial Nos. 28-7310039 to 28-7310187 Incl.

Figure 11-105.InstrumentLights

Reissued: 1/15/81 ELECTRICALSYSTEM

4H9
 PIPER CHEROKEE SERVICE MANUAL

PA-28-235,Serial Nos.28-7410001 to 28-7410120 incl.

Figure 11-106. Instrument Lights

A132
ANTI-COLL.
LIGHT
10 AMP

TERMINAL 7

PA-28-140. Serial Nos. ANTI-COLL.

28-7325053 & up LIGHT
PA-28-180, Serial NO.
28-7305064 & up (
PA-28R-200. Serial Nos.
PA-28-140, Serial Nos. 28-7425001 & up 28-7335055 & up
PA-28-180, Serial Nos. 28-7405001 & up PA-28-235, Serial Nos.
PA-28R-200, Serial Nos. 28-7435001 & up 28-7310039 & up
PA-28-235, Serial Nos. 28-7410001 & up

Figure 11-107.A/C Air Blower Figure 11-108. Rotating Beacon

Reissued:1/15/81 ELECTRICAL SYSTEM

4H10
0
 c
PIPERCHEROKEE
SERVICE

Figure 11-114. Pitch

Figure 11-113. Pitch Trim

0
 .
c

oo
Figure 11-118. Pitot
18. Pitot and Pressure Head Heat
and Pressure

C 0

&
C
 PIPERCHEROKEESERVICEMANUAL

A129

TURN &
TURN a
BANK 5 AMP
5 AMP

20

PA-28-140, Serial Nos. 28-7325053 & up PA-28-180.SerialNos.28-7405001 & up

PA-28-235,Serial Nos.28-7410001 & up

Figure 11-121.Turn & Bank Figure 11-122.Turn& Bank

A137 A121

PA-28-140.Serial Nos. 28-7525005 & up

PA-28-180,Serial Nos.28-7505005 & up
PA-28R-200,Serial Nos. 28-7335055 & up
PA-28R-200,Serial Nos.28-7535005 & up
PA-28-235,SerialNos.28-7510005 & up

Figure 11-123.Turn& Bank Figure 11-124.Fuel Pump

ELECTRICAL SYSTEM
Reissued:1/15/81 4H14
 PIPER CHEROKEE SERVICEMANUAL

1702

ALTERNATOR
SWITCH

ALTERNATOR _

I I
I
I I
II
II
I I
II
I I
I I
I

OPTIONAL

EXTERNAL
POWER

STARTER & ACC.

15 AMP

EXTERNAL
POWER I
RECEPTACLE
I

CIGAR
LIGHTER

MECHANICAL
INTERLOCK

r - ALTERNATOR SOURCE
POWER RELAY
ENERGIZING CIRCUIT

PA-28-140. Serial Nos. 28-7525001 to 28-7625234

Figure 11-125.Alternator, Starter,Cabin Light, Cigar Lighter and

External Power Receptacle
Reissued: 1/15/81 ELECTRICALSYSTEM
4H15
 PIPER CHEROKEESERVICEMANUAL

ALTERNATOR

EXTERNAL
POWER
SOLENOID
STARTER a ACC.
15 AMP

EXTERNAL
POWER
RECEPTACLE

MECHANICAL
INTERLOCK

ALTERNATOR SOURCE
POWER RELAY
ENERGIZING CIRCUIT
PA-28-180. Serial Nos. 28-7505001 & up
PA-28R-200. Serial Nos. 28-7535001 to 28-7635545
PA-28-235. Serial Nos. 28-7510001 to 28-7610206

Figure 11-126.Alternator, Starter, Cabin Light, Cigar Lighter and

External Power Receptacle.

Reissued:1/15/81 ELECTRICAL SYSTEM

4H16
 PIPER CHEROKEE SERVICE MANUAL

1704

AUTOMATIC
LANDINGGEAR GEARDOWN
ACTUATOR ACTUATOR
as AMP (NOTE3)

PA-28R-200, Serial Nos. 28-7535001 & up

Figure 11-127. Landing Gear

Reissued: 1/15/81 ELECTRICALSYSTEM

4H17
 PIPER CHEROKEE SERVICE MANUAL

1701
AUDIO PANEL COMM/NAVI & GLIDE SLOPE COMM/NAV II

AMP 10AMP AMP

RP4 RP2

SEE RADIO SEE SEE SEE

SYSTEMS RADIO GLIDE SLOPE RADIO
INSTALLATION INSTALLATION INSTALLATION INSTALLATION

TRANSPONDER
ADF & MARKER BEACON
ON DME TRANSPONDER AUTOPILOT

5 AMP 10 AMP -5AMP

SEE MARKER
SEE SEE MARKER SEE SEE SEE
ADF BEACON DME TRANSPONDER AUTOPILOT
INSTALLATION INSTALLATION INSTALLATION INSTALLATION INSTALLATION

PA-28-140, Serial Nos.28-7525001 & up Figure 11-128.Avionics

PA-28-180, Serial Nos.28-7505001 & up
PA-28-235, Serial Nos.28-7510001 & up

AUDIO PANEL COM/NAVI GLIDESLOPE COMM/NAV II

5 AMP AMP AMP AMP

RPI RP2

SEE RADIO SEE SEE SEE

SYSTEMS RADIO GLIDE SLOPE RADIO
INSTALLATION INSTALLATION INSTALLATION INSTALLATION

ADF MARKERBEACON DME TRANSPONDER AUTOPILOT

AMP AMP 5 AMP

5 AMP

SEE SEE MARKER SEE SEE SEE

ADF BEACON DME TRANSPONDER AUTOPILOT
INSTALLATION INSTALLATION INSTALLATION INSTALLATION INSTALLATION

PA-2 R-200, Serial No. 28-7535001 & up Figure 11-129.Avionics

Reissued: 1/15/81 4H18 ELECTRICAL SYSTEM

 PIPER CHEROKEE SERVICE MANUAL

NOTE:
RESISTORUSED ON LATERMODELS ONLY

PA-28-140, Serial No. 28-7525001 & up

Figure 11-130.InstrumentLights

NOTE:
PA-28-180, SerialNos. 28-7505001 & up RESISTORUSED ON LATERMODELSONLY
PA-28-235, SerialNos. 28-7510001 & up

Figure 11-131. Instrument Lights

Reissued: 1/15/81
ELECTRICALSYSTEM

4H19
 PIPER CHEROKEE SERVICE MANUAL

NOTE:
RESISTOR USED ON LATER MODELS ONLY

PA-28R-200, Serial Nos. 28-7535001 & up

Figure 11-132. Instrument Lights

PA-28-235,Serial Nos.28-7510001 & up

Figure 11-133. Engine Gauges

Reissued:1/15/81 ELECTRICAL SYSTEM

4H20
 PIPER CHEROKEE SERVICE MANUAL

PA-28-140, Serial Nos. 28-7525001 & up

PA-28-180, Serial Nos. 28-7505001 & up

Figure 11-134. Engine Gauges

A130

PA-28 R-200, Seral No. 28-7535001 &up

Figure 11-135.Engine Gauges

Reissued: 1/15/81 ELECTRICALSYSTEM

4H21
 PIPER CHEROKEESERVICEMANUAL

ANNUNCIATOR
LIGHTS 5 AMP

P3D AMMETER

(NOTE
1)

II

NOTES 4)
(NOTE

L NO.4 GAUGEWIRE ON
PA-28-235 ONLY.
2. NO.4 GAUGE WIRE ON
PA-28R-200 ONLY.
. WIRE CODE NO. W3A ON
PA-2-140 ONLY.
4. NOT USED ON 0
PA-2- 140.

(NOTE2)
OPTIONAL A L

EXTERNAL
POWER
SOLENOID
MASTER
SOLENOID STARTER & ACC
15 AMP

EXTERNAL
POWER
RECEPTACLE STARTER

·
CIGAR
LIGHTER

MECHANICAL
INTERLOCK

ALTERNATOR SOURCE
POWER RELAY
ENERGIZING CIRCUIT
PA-28-140, Serial Nos. 28-7725001 & up
PA-28R-200. Serial Nos. 28-7735001 & up
PA-28-235, Serial Nos. 28-7710001 & up

Figure 11-136.Alternator, Starter, Cabin Light, Cigar Lighter and

External Power Receptacle
Reissued: 1/15/81 ELECTRICAL
SYSTEM
4H22
 PIPER CHEROKEESERVICEMANUAL

A11S

PA-28-140, SerialNos. 28-7525001 & up

I PA-28-140. SerialNos.28-7625001 up
PA-28-180, SerialNos. 28-7505001 & up PA-28R-200,Serial Nos.28-7635001 & up
PA-28-235, Serial Nos. 28-7510001 & up I PA-28-235, SerialNos. 28-7610001 & up

Figure 11-137. Pitot Heat Figure 11-138. Stall Warning

PA-28-235 2668 PA-2B-140, SerialNos. 28-7525001 & up A133

PA-25-180, SerialNos. 28-750001 & up
PA-28R-200, Serial Nos.28-7535001 up
FINSTROBE PA-28-235, SerialNos. 28-7510001 & up
ANTI-COLLISION
10AMP

7 AMP
28-180
SWITCH

7.5 AMP
28-140
28 R-200
28-235

TERMINALII

Figure 11-139. Fin Strobe Anti-Collision Figure 11-140.Navigation Lights

Light

Reissued: 1/15/81 ELECTRICALSYSTEM

4H23
 PIPERCHEROKEE
SERVICEMANUAL

A120 A119
OVERHEAD
INST. LIGHTS
5 AMP

i
PA-28-140, SerialNos.28-7525001 & up PA-28-140, SerialNos. 28-7525001 & up
PA 28-l80,Serial Nos. 28-7505001 & up PA-28-180, SerialNos. 28-7505001 & up
PA-28R-200, SerialNos. 28-7535001 & up PA-28R-200, Serial Nos. 28-7358001 & up
PA-28-235, Serial Nos. 28-7510001 & up PA-28-235. SerialNos. 28-7510001 & up

Figure 11-141. OverheadFlood Light Figure 11-142. LandingLight

A13

ANTI COLLISION
LIGHTS
15 AMP

BEACON
ANTI COL.
LIGHT

PA-2 R-200. Serial Nos. 28-7535001 & up PA-28-235

Figure 11-144. Anti-Collision Light

Figure 11-143. Pitot and Pressure
Head Heater
Reissued:1/15/81 ELECTRICALSYSTEM

4H24
 PIPER CHEROKEE SERVICE MANUAL

SECTION XII
ELECTRONICS
Aerofiche
Grid No.
12-1. Introduction ................................................ 412
12-2. EmergencyLocator Transmitter (Garrett Mfg. Ltd.) .............. 412
12-3. Description .................................................. 412
12-4. Battery Removal and Installation (2 Year Magnesium) ............ 412
12-5. Battery Removal and Installation (NARCO) ..................... 415
12-6. Testing EmergencyLocator Transmitter ......................... 417
12-7. Pilot's Remote Switch......................................... 418
12-8. Testing Pilot's Remote Switch.................................. 418
12-9. Inadvertent Activation ........................................ 419
12-10. EmergencyLocator Transmitter (Communications
Components Corp.) ......................................... 4110
12-11. Description ................................................. 4110
12-12. Battery Removal and Installation ............................... 4110
12-13. Pilot's Remote Switch........................................ 4111
12-14. Testing EmergencyLocator Transmitter ......................... 4111
12-15. Testing Pilot's Remote Switch.................................. 4111
12-16. Inadvertent Activation ........................................ 4111
12-17. Autoflight - General .......................................... 4112
12-18. Non-Piper A.F.C.S. Equipment Contacts ........................ 4112
12-19. Piper A.F.C.S. Equipment..................................... 4113

Revised: 10/3/83 ELECTRONICS

411
 PIPER CHEROKEE SERVICE MANUAL

SECTIONXII
ELECTRONICS

12-1. INTRODUCTION.This section of the manual contains information necessary to

perform operational checksof the Emergency Locator Transmitter (ELT), with and without
a pilot's remote switch. Included are the appropriate removal and installation instructions to
facilitate battery replacement.

12-2. EMERGENCYLOCATORTRANSMITTER(GARRETT MFG. LTD.).

12-3. DESCRIPTION. The electrical power for the ELT is totally supplied by its own
self-contained battery. The magnesium batteries used on early models have a service life of
four years. The lithium batteries used on later models have a service life of ten years.
However, to comply with FAA regulations, magnesium batteries must be replaced every 2
years and lithium batteries must be replaced at 5 year intervals. If the transmitter has been
used in an emergencysituation during this 2 or 5 year period or it has more than one hour
of accumulated test time, the battery must be replaced according to FAA regulations. To
replace the battery pack in the transmitter, it is necessary to remove the transmitter from
the aircraft. (Refer to Paragraph 12-4or 12-5.)

12-4. BATTERY REMOVALAND INSTALLATION. (2 year, magnesiumbattery, refer to

Figure 12-1.) The ELT is located on mounting brackets on the right side of the fuselageaft
ofsta. 228.30.
a. Remove the accessplate on the right side of the fuselage aft of sta. 228.30.
b. Set the ON/ARM/OFF switch on the transmitter to the OFF position.
c. Disconnect the antenna coax from the transmitter.
d. Disconnect the harness to the pilot's remote switch.
e. Remove the rear mounting bracket by pulling the plastic knob out. Remove the
transmitter from the airplane.
f. Remove the two long or four short screws securing the transmitter plain end cap.
Remove the plain end cap.
g. Disconnect the battery connector from the board terminals.
h. Withdraw the battery pack from the transmitter case.
i Before installing the new battery pack, check the replacement date printed on the
battery. Transfer this date onto the outside of the ELT.
j. Slide the new battery pack, plain end first, into transmitter. It may be necessaryto
rotate the battery slightly to get it seated properly in the transmitter case and to achieve.
correct orientation of the battery connector.
k. Connect the battery connector to board terminals.
1. Insure O-ringis fitted in plain end cap and correctly seated.

Reissued:1/15/81 ELECTRONICS
4I2
 PIPER CHEROKEE SERVICE MANUAL

278
BATTERY
CONNECTOR LONG
SCREWS

PLAIN
END
CAP

Figure 12-1. Two Year, MagnesiumBattery Connections

NOTE
Red ELT's have no O-ring; replace end cap using fresh RTV
silicone rubber compound.
m. Refit end cap and secure with the screwspreviouslyremoved.

NOTE
Do not overtighten the end cap screws.
n. Place transmitter into its mounting bracket; replace rear mounting bracket by
pushing plastic knob into place.
o. Connect the pilot's remote switch harness to the transmitter.
p. Connect the antenna coax to the transmitter.

NOTE
Before installingaccess plate ascertain that transmitter switch
is in the ARM position. It may also be advisable to test the
unit operation before installing the access panel (Refer to
Paragraph 12-6.)
q. Install the access plate on the right side of the fuselage aft of sta. 228.30. Make an
entry in the aircraft logbook, including the new battery run out date.

NOTE
Inspect the external whip antenna for any damage. Avoid
bending the whip. Any sharply bent or kinked whip should
be replaced. Antenna damage may cause structural failure of
whip inflight.

ELECTRONICS
Reissued: 1/15/81
413
 PIPER CHEROKEE SERVICE MANUAL

B965
NOTCH PIN PORTABLE
STOP ANTENNA
OPERATIVE
BUTSTORED ANTENNA
EXTENSION
TAB

VIEW SET
A
ON-OFF-ARM
SWITCH
TO
ANTENNA
"ON"
LATCH POPSOUT
OF
CHANNEL
AND DOWN
VIEW
B

PIN
STOP
PULL TAB
VIEW
TO EXTEND TO FULL LENGTH C

Figure 12-2. ELT Portable Folding Antenna (Narco)

B965
CONTACT PORTABLE ANTENNA BLADE
PORTABLE NOT
MAKING CONTACT
ANTENNA
CONTACT
FINGER

NOTCH FOR
ANDLE RELEASE

FIXED ANTENNA'S
CABLE CONNECTOR AND
CONTACT SEPARATOR

TO REMOTE SWITCH

Figure 12-3. ELT Using Fixed Aircraft Antenna (Narco)

Reissued: 1/15/81 ELECTRONICS

414
 PIPER CHEROKEE SERVICE MANUAL

12-5. BATTERY REMOVAL AND INSTALLATION (NARCO) (Refer to Figures 12-2 and 12-3).
a. Set the ON/OFF/ARM switch on the transmitter to OFF.
b. Disconnect antenna coaxial cable from ELT.
c. Remove ELT from its mounting bracket by releasingthe latch on the strap and slidingthe ELT off
the bracket.
d. Extend the portable antenna.
e. Unscrew the four screwsthat hold the control head to the battery casing and slide apart.
f. Disconnectthe battery by unsnapping the snap-off battery pigtail terminalsfrom the bottom of the
transmitter printed circuit board.
g. Discard old battery pack. (Do not expose to flame.)
CAUTION
The battery pack is shipped with a sealant on the insidelip so that a
water tight seal will be retained. Do not remove this sealant.
h. Connect new battery pack terminals to the bottom of the circuit board.
i. Reinsert the control head section into battery pack being careful not to pinch any wiresand replace
the four screws. If the four holes do not line up, rotate the battery pack 180 and reinsert.
j. Slide the portable antenna back into the towed position.
k. Place transmitter into its mounting bracket and fasten the strap latch.
l. Connect the antenna coaxial cable to the ELT and ensure that the contact separator is inserted be-
tween the antenna contact finger and portable antenna. (Refer to Figure 12-3).
m. Press RESET button and set ON/OFF/ARM switch to ARM.
n. Make an entry in the aircraft logbook, including the new battery expiration date.
o. A unit operational check may now be performed on the ELT.

B126

WHITE
ELT
BLACK I
BLACK SHIELD SHIELD

Figure 12-4. Emergency Locator Transmitter Schematic (Narco)

Reissued: 1/15/81 ELECTRONICS

4I5
 PIPER CHEROKEE SERVICE MANUAL

NOTE
As a routine precaution, it is recommended that the ELT
battery be replaced at the earliest opportunity after
inadvertent activation and a functional test be made in
accordance with Paragraph 12-6. Note, however, that the
problem may not be in the transmitter. Check the following:
1. Proper spacing of antennas so as to minimize antenna
conducted RF.
2. Rigidity of the transmitter installation.
CAUTION
Under normal conditions, the pilot's remote switch must be
set to ARM position.

347

COMMUNICATIONSCOMPONENTSCORP.
SWITCH POSITIONS
OFF/RESET NORMAL
REMOTI
E AUTO/ARM FLIGHT
"RESET" ON POSITION

SHIELD

BLK
ELT

WHITE
SW.-79762-2
REMOTE
"ON" +14 VOLT DC KEYWAY
(TEST) TO OVERHEAD BLK
FLOOD LIGHT
TRANSMITTER NO. CIR-II-2 SHLD WHT
CIRCUITPROTECTOR
RED
NOTE: AIRCRAFT POWER USED TO SHUT OFF THE ELT WITH REMOTE SWITCH. VIEW A

Figure 12-5. Communications Components ELT Schematic

Reissued: 1/15/81 ELECTRONICS

416
 PIPER CHEROKEE SERVICE MANUAL

12-6. TESTING EMERGENCYLOCATORTRANSMITTER. The transmitter operates on

the emergency frequencies of 121.5 and 243 MHz;both of these frequenciesare monitored
by the various FAA installations. Before performing any operational test of the ELT, the
followingprecautions should be observed:

CAUTION
Testing of an ELT should be conducted in a screen room or
metal enclosure to ensure that electromagnetic energy is not
radiated during testing. If a shielded enclosure is not
available, testing may be performed in accordance with the
followingprocedures:
1. Test should be no longer than three audio sweeps.
2. If the antenna is removed, a dummy load should be
substituted during the test.
3. Test should be conducted only within the time period
made up of the first fiveminutes after any hour.
4. If the operational tests must be made at a time not
included within the first five minutes after the hour,
the test should be coordinated with the closest FAA
Tower or Flight ServiceStation.
Consult FAA Advisory Circular AC 20-81 for detailed
information concerning above caution.
a. Remove the accessplate on the right side of the fuselageaft of sta. 228.30.
b. Tune the aircraft communications receiver to 121.5 MHz and switch the receiver
ON; deactivate the squelch, and turn the receiver volume up until a slight background noise
is heard.

NOTE
If the aircraft is not fitted with a communications receiver,
request that the tower listen for your test.
c. On the transmitter, set the ON/ARM/OFF switch to the ON position. Keep the
switch in this position for only a few seconds; then set to the OFF position. Return to the
ARM position.

NOTE
The test transmission should have been picked up by the
aircraft communications receiver and/or control tower.
During cold weather, there may be a slight delay before
transmissionoccurs.
d. A transmitter which is functioning properly should emit a characteristic downward
swept tone.
e. When the test is completed, ascertain the transmitter ON/ARM/OFF switch is in the
ARM position.

Reissued: 1/15/81 ELECTRONICS

417
 PIPER CHEROKEE SERVICE MANUAL

f. Place the access panel on the right side of the fuselage aft of sta. 228.30.

WARNING
Whenever the unit is checked by moving the transmitter
ON/ARM/OFF switch from the ARM to the ON position, it
must then be moved to the OFF position before reverting to
the ARM position again.

CAUTION
Under normal conditions, the transmitter switch must be set
to arm.

12-7. PILOT'SREMOTE SWITCH. A pilot's remote switch, located on the left side panel,
is provided to allow the transmitter to be controlled from inside the cabin. The switch is
locked into each position. To move the switch, the toggle-must be pulled out and moved to
the new desired position, On early models the pilot's remote switch is placarded "ON,"
"ARM," "OFF/RESET." If the pilot's remote switch has been placed in the "ON" position
for any reason, the "OFF/RESET" position must be selected for one second before the
switch is placed in the "ARM" position. On later models the pilot's remote switch is
placarded "ON/RESET" and "ARM (NORMALPOSITION)." The switch is normally left in
the down or "ARM" position. To turn the transmitter off, move the switch to the
"ON/RESET" position for one second then return it to the "ARM" position. To actuate the
transmitter for tests or other reasons, move the switch upward to the "ON/RESET"
position and leave it in that position as long as transmissionis desired.

CAUTION
Under normal conditions the switch must be set to ARM.

12-8. TESTING PILOT'S REMOTE SWITCH. Before performing any operational test of
the pilot's remote switch, the followingprecautions should be observed:

CAUTION
The transmitter operates on the emergency frequencies of
121.5 and 243 MHz;both of these frequencies are monitored
by the various FAA installations. Permission should be
obtained from the FAA/FCC Representative (or other
applicable Authority) prior to testing. Keep your test
transmissionto a minimal duration.
a. Tune the aircraft communications receiver to 121.5 MHz and switch the receiver
ON; deactivate the squelch, and turn the receivervolume up until a slight background noise
is heard.

Reissued:1/15/81 ELECTRONICS
4I8
 PIPER CHEROKEE SERVICE MANUAL

NOTE
If the aircraft is not fitted with a communications receiver,
request that the tower listen for your test.
b. Set the pilot's remote switch to the ON position. Hold the switch in this position for
only a few seconds.
NOTE
The test transmission should have been picked up by the
aircraft communications receiver and/or control tower.
During cold weather there may be a slight delay before
transmissionoccurs.

c. Set the pilot's remote switch to the RESET position for one second; then select the
ARM position.

12-9. INADVERTENTACTIVATION.
a. In the event the ELT is inadvertently activated in aircraft without a pilot's remote
switch, the ELT will have to be reset by gaining access to the ELT. (Refer to Paragraphs
12-4 or 12-5.) Put the ON/ARM/OFF switch in the OFF position. To reset for automatic
operation, return switch to the ARMposition. (See Note.)
b. In aircraft with a pilot's remote switch, if the ELT is inadvertently activated, set the
pilot's remote switch to the RESET position; then return it to the ARM position. (See
Note.)
NOTE

As a routine precaution, it is recommended that the ELT

battery be replaced at the earliest opportunity after
inadvertent activation and a functional test be made in
accordance with Paragraph 12-6. Note, however, that the
problem may not be in the transmitter. Checkthe following:
1. Proper spacing of antennas so as to minimize antenna
conducted RF.
2. Rigidity of the transmitter installation.
CAUTION
Under normal conditions,the pilot's remote switch must be
set to ARMposition.

Reissued: 1/15/81 ELECTRONICS

4I9
 PIPER CHEROKEE SERVICE MANUAL

12-10. EMERGENCYLOCATORTRANSMITER (COMMUNICATIONS

COMPONENTS
CORP.).

12-11. DESCRIPTION.The electrical power for the ELT transmissionsis totally supplied
by its own self-contained battery. However, aircraft power is required to shut off
transmitter with the remote switch. For portable use, the ELT can be easily removed from
its mounting in the aircraft. The battery must also be replaced if the transmitter has been used
in an emergencysituation or if accumulated test time exceedsone hour. The replacement date
is marked on the transmitter label.

12-12. BATTERY REMOVAL AND INSTALLATION. The ELT is located on the right
side of the airplane tail section, ahead of the stabilator.
a. Removethe accessplate on the right side of fuselageaft of sta. 228.30.
b. Rotate the ON/ARM/OFFswitch to the OFF position.
c. Disconnect the antenna coax cable (twist left, then pull outwards).
d. Disconnect the harness to the pilot's remote switch.
e. Remove the forward mounting bracket by pulling the black plastic knob .out.
Remove the transmitter from the airplane.
f. Remove the six Phillips-head screws securing the transmitter cover. Remove the
cover.
g. Lift out the old battery pack.
h. Copy the expiration date on the battery into the space provided on the external
ELT name and date plate.
i Disconnect and replace with a new battery pack. The nylon battery connector is a
friction fit and is easily removed by pulling on the exposed end.
j. Insert transmitter into airplane and fit into place. Replace mounting bracket by
pushing the black plastic knob into place.
k. Reconnect the pilot's remote switch harness and the antenna coax cable to the
transmitter.
L Set the ON/ARM/OFF switch to the ARM position.
m. Reinstall the accessplate previouslyremoved.
NOTE
It may be advisable to test the unit operation before
installingthe accessplate. (See Paragraph 12-6.)

NOTE

Inspect the external whip antenna for any damage. Avoid

bending the whip. Any sharply bent or kinked whip should
be replaced. Antenna damage may cause structural failure of
whip in flight.

Reissued: 1 /15/81I ELECTRONICS

4I10
 PIPER CHEROKEE SERVICE MANUAL

12-13. PILOT'S REMOTESWITCH. A pilot's remote switch, located on the left side panel,
is provided to allow the transmitter to be controlled from inside the cabin. The pilot's
remote switch is placarded ON, AUTO/ARMand OFF/RESET. The switch is normally left
in the AUTO/ARMposition. To turn the transmitter off, move the switch momentarily to
the OFF/RESET position. The aircraft master switch must be ON to turn the transmitter
OFF. To actuate the transmitter for tests or in the event the automatic feature was not
triggered by impact, move the switch upward to the ON position and leave it in that
position as long as transmissionis desired.

12-14. TESTING EMERGENCYLOCATOR TRANSMITTER. (Testing done the same as

noted in Paragraph 12-6.)

12-15. TESTING PILOTS REMOTE SWITCH. Before performing any operational test of
the pilot's remote switch, the same precautions noted in Paragraph 12-6 must be observed.
a. Tune the aircraft communications receiver to 121.5 MHz and switch the receiver
ON, deactivate the squelch, and turn the receivervolume up until a slight background noise
is heard.
NOTE
If the aircraft is not fitted with a communications receiver,
request that the tower listen for your test.
b. Set the pilot's remote switch to the ON position. Hold the switch in this position for
only a few seconds.
NOTE

The test transmission should have been picked up by the

aircraft communications receiver and/or control tower.
During cold weather there may be a slight delay before
transmissionoccurs.

c. Set the pilot's remote switch to the momentary OFF,RESETposition. The switch is
spring loaded to automatically return to the ARM position.

12-16. INADVERTENTACTIVATION. The remote switch allowsthe pilot to turn off the
transmitter inadvertently activated by impact or improper switch selection.The pilot simply
selects the momentary OFFRESET position. The transmitter shuts off and the spring
loaded switch automatically returns to the ARM position. The aircraft master switch must
be ON to turn transmitter OFF with the remote switch. Stopping inadvertent activation at
the transmitter itself is accomplishedin the followingmanner:
a. Improper switch selection is corrected by rotating the switch to the OFF position
and then to the ARM position.
b. If the transmitter is inadvertently activated through impact, deactivate by pushing in
on the OFF/ARM/ON switch.

Reissued: 1/15/81 ELECTRONICS

4111
 PIPER CHEROKEE SERVICE MANUAL

12-17. AUTOFLIGHT. GENERAL. Due to the wide variety of A.F.C.S. (Automated

Flight Control System) options, it is mandatory to follow the serviceliterature published by
the individual manufacturer of the A.F.C.S. equipment installed in any particular airplane.
This includes mechanical service such as: adjusting, bridle cable tension, servo removal and
installation, servo clutch adjustments, etc.

12-18. NON-PIPER A.F.C.S. EQUIPMENT CONTACS. Refer to the following list of

AutoPilot/Flight Director manufacturers to obtain service direction parts support, and
service literature.
Bendix Avionics Division
2100 N.W. 62nd Street
Fort Lauderdale, Fla. 33310
(305) 776-4100/TWX 5109559884
Collins General Aviation Division
Rockwell International
Cedar Rapids, Iowa, 52406
(319) 395-3625 Telex: 464-421
Edo Corporation - Avionics Division
Box 610
Municipal Airport
Mineral Wells. Texas 76067
(817) 325-2517 Telex: 76067
King Radio Corporation
400 North Rodgers Road
Olathe. Kansas. 66061
(913) 782-0400 Telex: 4-2299-Kingrad
Sperry Flight Systems/Avionics Div.
8500 Balboa Blvd.
P.O. Box 9028
VanNuys, CA. 91409
(213) 894-8111 Telex: 65-1367
Global Navigation
2144 Michelson Drive
Irvine, CA 92715
(714) 851-0119

Added: 10/3/83 ELECTRONICS

4112
 PIPER CHEROKEE SERVICE MANUAL

12-19.PIPER A.F.C.S. EQUIPMENT. In the case of early models, Piper AutoPilot

equipment bears the Piper name, and the appropriate Piper AutoPilot/Flight Director
Service Manual shall be used.
NOTE
If a Roll Axis - only AutoPilot is installed,or if no AutoPilot
is installed, consult the Piper Pitch Trim Service Manual -
753 771 for manual electric pitch trim service information.
The followingis a complete listing of Piper A.F.C.S. equipment serviceliterature. It is
imperative to correctly identify the AutoPilot system by "faceplate" model name, in order
to consult the appropriate service manual. Each manual identifies the revision level and
revision status as called out on the Master Parts Price List - Aerofichepublished monthly
by Piper. Consult the aircraft's parts catalog for replacementparts.

NAME PIPER PART NO.

AutoControl I/II & AltiMatic I/II 753 798
AutoControl III & AltiMatic III and IIIB 753 723
AutoControl IIIB & AltiMatic IIIB-1 761 502
AltiMatic IIIC 761 602
AltiMatic V and V-I 761 525
AltiMatic V F/D and V F/D-I 761 526
AltiMatic X F.D./A.P./ & X A.P 761 668
AutoFlite 753 720
AutoFlite II 761 481
Piper Pitch Trim (Manual-Electric) 757 771

Added: 10/3/83 ELECTRONICS

4113
 SECTION
XIII

HEATING
ANDVENTILATING

Aerofiche
Grid No.
13-1. Introduction ................................ 4115
13-2. Description ... ..................... 4115
13-3. Heater Maintenance ............................ 4116
13-4. OverheadVent System .......................... 4116

Revised: 10/3/83

4114
 PIPER CHEROKEE SERVICE MANUAL

SECTION XIII

HEATING AND VENTILATING SYSTEM

13-1. INTRODUCTION. Because of the simplicity of the heating and ventilating

system installed on the PA-28, the operation and maintenance instructions of the
components are contained in paragraph 13-3. A pictorial description of these
systems may be found in Figure 13-1 thru 13-6.

13-2. DESCRIPTION. Heat forthe cabinofthe Cherokee is provided bya hot air
heater installed on the exhaust manifold. Fresh air enters the engine compart-
ment through the nose cowling, passes over the engine and is vented to the heater
muff through a flexible hose located on the bafflingat the rear of the engine. The
air is then heated and vented into the cabin area through a valve which can be
controlled from the instrument panel. When the valve is completely closed off,
the heated air is vented back into the engine compartment. The heater outlet in
the cabin is located between the two front seats. Control for the heater system
is located on the right panel, below the instruments. The windshield is kept clear
of frost, ice and etc. by a defroster system which operates from the heater muff,
but has an individual control.
Fresh air for the PA-28-140;PA-28-150,-160,-180, Serial Nos. 28-1to 28-2477incl., and
PA-28-235,Serial Nos. 28-10000to 28-10675incl. is obtained through an intake located on
the left forward side of the fuselage,directing air to the forward sectionof the cockpit. Addi-
tional intakes are located on each side of the fuselage, venting air to the individualseat loca-
tion. On the PA-28-150, -160, -180, Serial Nos. 28-2478 and up; PA-28-235, Serial Nos.
28-10676and up; PA-28R, fresh air is picked up from an inlet in the leadingedgeof each wing.
The air passes through the wings to individually controlled outlets located just forward of
each seat. An air vent is located in the top or bottom of the fuselagedependingon the model
involved, to take exhaust air from the cabin interior.

Reissued: 1/15/81 Reissued: 1/15/81

4I15
 PIPER CHEROKEE SERVICE MANUAL

13-3. HEATER MAINTENANCE.If the exhaust manifold should become defective,

carbon monoxide fumes may be discharged into the cabin area, therefore it is imperative
that the exhaust manifold be inspected regularly. Refer to Section III, paragraph 3-9 for
inspection of exhaust systems. The heater muff must be removed in order to inspect the
manifold assembly. Check the operation of the push-pull controls to insure the valvedoors
function properly. Whenthe controls are pulled out, the door should be completely open to
permit full air flow. When the controls are pushed in, the valves should close off all air
passage and vent the air into the engine compartment. Refer to Figures 13-1 thru 13-9 for
an illustration of the heater system,

13-4. OVERHEADVENT SYSTEM. (Optional 1974 Modelsand up.) "NOT AVAILABLE

WITH AIR CONDITIONING."
The overhead vent system utilizes the same ducting as that of the air conditioning
system. (Refer to Figure 13-10.) Air enters an inlet at the top of the fin and is ducted
through the vent system. Small louvers control the flow of air into the cabin. This vent
system may also be equipped with a blower (optional). This blower, mounted aft of the
close-out panel underneath the top of the fuselage,will force air through the overhead vent
system wheneverdesired.

Reissued: 1/15/81 HEATING AND VENTILATING SYSTEM

4116
 PIPER CHEROKEESERVICEMANUAL

C364

. DEFROSTER AIR OUTLET

DEFROSTER CONTROL
3. FRESH AIR CONTROL
. HEATER CONTROL
. FRESH AIR INLET
. HEATER OUTLET
7. FRESH AIR INLET
8. CABIN HEAT CONTROL BOX
. FLEXIBLE HOSE
10. DEFROSTER CONTROL BOX

Figure 13-1. Cabin Heater, Defroster and Fresh Air System

PA-28-140, Serial Nos. 28-20002 to 28-24999 incl. and
PA-28-150, -160, -180, Serial Nos. 28-1 to 28-1760 incl.

Reissued:l/15/81 HEATING AND VENTILATING

4117
 PIPER CHEROKEE SERVICE MANUAL

1747

FRESH AIR 1. FRESH AIR CONTROL 4. DEFROSTER AIR OUTLET

2. DEFROSTER CONTROL 5. FRESH AIR INLET
CABIN HEAT 3. HEATER CONTROL 6. CABIN EXHAUST OUTLET

Figure 13-2. Cabin Heater, Defroster and Fresh Air System

PA-28-140, Serial Nos. 28-25000 and up
Reissued1/15/81 HEATING AND VENTILATING SYSTEM.
4I18
 PIPER CHEROKEE SERVICE MANUAL

1826

Figure 13-3. Cabin Heater, Defroster and Fresh Air System

PA-28-150, -160, -180, Serial Nos. 28-1761 to 28-2477 incl.
Reissued:1/15/81 HEATING AND VENTILATING SYSTEM
4119
 PIPER CHEROKEE SERVICE MANUAL

1797

FRESH AIR 1. FRESH AIR CONTROL 4. DEFROSTER AIR OUTLET

2. DEFROSTER CONTROL 5. FRESH AIR INLET
CABIN HEAT 3. HEATER CONTROL 3. CABIN EXHAUST OUTLET

Figure 13-4. Cabin Heater, Defroster and Fresh Air System

PA-28-150, -160, -180, Serial Nos. 28-2478 to 28-4377 incl.
Reissed: 1/15/11 HEATING AND VENTILATING SYSTEM
4120
 PIPER CHEROKEE SERVICE MANUAL

1748

1. FRESH AIR CONTROL 4. DEFROSTER AIR OUTLET

FRESHAIR
2. DEFROSTER CONTROL 5. FRESHAIR INLET
Figure
CABIN HEAT 3. HEATER CONTROL 6. CABIN EXHAUST OUTLET

Figure 13-5. Cabin Heater, Defroster and Fresh Air System

PA-28-180,Serial Nos. 28-4378and up
Reissued:1/15/81 HEATING AND VENTILATING SYSTEM
4I21
 PIPER CHEROKEE SERVICE MANUAL

C365

__

/ I

/1-

1. FRESH AIR INLET, HEATER

2. DEFROSTER OUTLET
3. FRESH AIR INLET, CABIN
4. CABIN HEAT OUTLET
5. CABIN AIR AND HEAT CONTROLS
6. CABIN AIR EXHAUST OUTLET

Figure 13-6. Cabin Heater, Defroster and Fresh Air System

PA-28-235, Serial Nos. 28-10003 to 28-10675 incl.
Reissued: 1/15/81 HEATING AND VENTILATING SYSTEM
4122
 PIPER CHEROKEE SERVICE MANUAL

1816

FRESH AIR 1. FRESH AIR CONTROL 4. DEFROSTER AIR OUTLET

2. DEFROSTER CONTROL 5. FRESH AIR INLET
CABIN HEAT 3. HEATER CONTROL 6. CAIN EXHAUST OUTLET

Figure 13-7. Cabin Heater, Defroster and Fresh Air System

PA-28-235, Serial Nos. 28-10676 to 28-11039 incl.
Reissued: l/15/81 HEATING AND VENTILATING SYSTEM
4123
 PIPER CHEROKEE SERVICE MANUAL

1587

FRESH AIR 1. FRESH AIR CONTROL 4. DEFROSTER AIR OUTLET

2. DEFROSTER CONTROL 5. FRESH AIR INLET
CABIN HEAT 3. HEATER CONTROL 6. CABIN EXHAUST OUTLET

Figure 13-8. Cabin Heater, Defroster and Fresh Air System

PA-28-235, Serial Nos. 28-11040 and up

Reissued:1/15/81 HEATING AND VENTILATING SYSTEM

4124
 PIPER CHEROKEESERVICEMANUAL

CabinHeat, Defroster,FreshAir

Fresh
Air
CabinHeat

1. Fr AirControl 4. Defroster
Air Outlet
2. DefrosterControl
5. Fresh
Air Inlet
3. Heater Control Cabin
6. ExhaustOutlet
7. Heat Duct

Figure 13-9. Cabin Heater, Defroster and Fresh Air System

PA-28-235, Serial Nos. 28-7310001and up
Reissued: 1/15/81 HEATINGAND VENTILATINGSYSTEM
4J1
 PIPER CHEROKEE SERVICE MANUAL

1669

FRESH AIR 1. FRESH AIR CONTROL 4. DEFROSTER AIR OUTLET

2. DEFROSTER CONTROL 5. FREST AIR INLET
CABIN HEAT 3. HEATER CONTROL 6. CABIN EXHAUST OUTLET

Figure 13-10.Cabin Heater, DefrosterandFresh Air System

PA-28R-180and200
Reissued:1/15/8 2 HEATINGAND VENTILATING SYSTEM
4J2
S

I
 SECTION
XIV

ACCESSORIES
AND
UTILITIES
Aerofiche
Grid No.
14-1. Air Conditioning Installation .................... ... 4J6
14-2. Description .............................. ... 4J6
14-3. Air Conditioning System Operation ................ ... 4J6
14-4. Malfunction Detection ....................... 4J9
14-5. Special ServicingProcedures .................... ... 4J10
14-6. ServiceValves ............................ .. 4J12
14-7. ServiceValve Replacement ..................... .... 4J12
14-8. Test Gauge and ManifoldSet . ................... .4J13
14-9. Checkingthe System for Leaks .................. ·... 4J13
14-10. Leak Check - Method I ....................... ... 4J15
14-11. Leak Check- Method II ....................... ... 4J16
14-12. Discharging .............................. . 4J16
14-13. Evacuatingthe System ....................... ·... 4J17
14-14. Chargingthe System ......................... .. 4J18
14-15. With a ChargingStand ..................... . 4J19
14-16. Usingthe Airplane Compressorto Chargethe System ...... ... 4J20
14-17. Addition of Partial Chargeto System ............... .... 4J21
14-18. CompressorService ......................... . 4J22
14-19. CompressorRemoval ........................ ... 4J23
14-20. CompressorInstallation ....................... ... 4J23
14-21. CheckingCompressorOil ...................... 4J24
14-22. Replacement of Compressorand/or Alternator DriveBelts . . . ...
·. . 4K1
4K3
14-23. Adjustment of Drive Belt Tension ................. 4K3
14-24. MagneticClutch ........................... 4K7
14-25. MagneticClutch Removal ...................... 4K7
14-26. MagneticClutch Installation .................... 4K8
14-27. Refrigerant Linesand Routing ................... 4K8
14-28. Receiver-Dehydrator ............ 4K9
14-29. Receiver-DehydratorRemoval ................... 4K9
14-30. Receiver-DehydratorInstallation ................. 4K9
14-31. Condenser .............................. 4K9
14-32. Condenser AssemblyRemoval ................ : . .. 4K9
14-33. Condenser Installation ....................... 4K10
14-34. Condenser Door Actuator ..................... 4K10
14-35. CondenserAssembly RiggingInstructions ............ 4K12
14-36. Expansion Valve ........................... 4K13
14-37. ExpansionValve Removal ..................... 4K13
14-38. Expansion ValveInstallation .................... 4K13

Revised: 10/3/83

4J4
 Aerofiche
Grid No.
14-39. Evaporator Assembly ........................... 4K14
14-40. Evaporator Assembly Removal...................... 4K14
14-41. Evaporator Assembly Installation ................... 4K14
14-42. PressureRelief Switch (Ranco) ..................... 4K15
14-43. Electrical Installation ........................... 4K16
14-44. Adjustment of Throttle Switch ..................... 4K16
14-45. Fuse Replacement(Ser No. PA-28-140,28-7125472 to
28-7325057, PA-28-180,28-7205092 to 28-7305071,
PA-28R-180,28R-7235001 to 28R-7335057.) .......... 4K17
14-46. Fuse Replacement (Ser Nos. PA-28-140, 28-7325058 and up,
PA-28-180,28-7305072 and up, PA-28R-200,
28R-7335058 and up.) ........................ 4K17
14-47. Shoulder- HarnessInertia Reel Adjustment .............. 4L4
14-48. OverheadVent Blower .......................... 4L4
14-49. Description ................................ 4L4
14-50. Removal of BlowerAssembly ...................... 4L4
14-51. Disassemblyof Blower Assembly .................... 4L4
14-52. Reassemblyof Blower Assembly ..................... 4L5
14-53. Installation of BlowerAssembly ..................... 4L5

Revised: 10/3/83

4J5
 PIPER CHEROKEE SERVICE MANUAL

SECTIONXIV
ACCESSORIESAND UTILITIES

14-1. AIR CONDITIONINGINSTALLATION.

14-2. DESCRIPTION. This installation consists of a compressor with its special bracketry,
an evaporator, a condenser, a receiver-dehydrator, circulating fan, thermal expansion valve,
and related plumbing.
The evaporator filters, dehumidifies and cools the air. The evaporator is mounted in a
fabricated housing along with the receiver-dehydrator, circulating fan, thermal expansion
valve and related plumbing. This housing is located at the rear of the cabin, aft of the
baggagearea. The compressor is a two cylinder, piston type compressorwhich is supported
by special bracketry at the front of the engine. A V-belt connected to the engine ring gear
drives the compressor through a magnetic clutch. The condenser is installed on a hinge
mounted door that is located on the bottom portion of the fuselage tail section. The
condenser door is hinge mounted to allow extension into the airstream during system
operation. The condenser door is electrically activated to provide the following positions,
(system on - fully extended or system off - fully retracted).
The system is protected by a Ranco type pressure switch which automatically controls
the condenser maximum head pressure by temporarily de-clutching the compressor in the
event the pressure becomes excessively high. The controls are located on the aircraft
instrument panel adjacent to the heater and defroster levers, and consist of an Air
Conditioning control, a fan control to govern the cold air velocity, and a temperature
control.
The system design is such that there is no increase in drag to the aircraft during its
take-off flight conditions. During maximum power demands the compressor is de-clutched
and the condenser door is automatically retracted.
14-3. AIR CONDITIONINGSYSTEMOPERATION.
The air conditioning system in this aircraft is a recirculating,independent unit. It filters,
dehumidifies.and cools the air as it cycles through the evaporator. The unit is operated from
controls mounted on the right side of the instrument panel. The air conditioning master
switch has three positions on early models: "FAN only, OFF and AIR COND" and a two
position ON-OFF switch on later models. When the "AIR COND" position is selected the
compressor clutch engages,the condenser scoop opens and the circulating fan is turned on.
The temperature is controlled by a thermostat operated by the temperature control selector.
A three position fan swithc (LOW-MED-HIGH)operates the blower. The fan may be
operated to circulate air without using the air conditioning unit
The air conditioning system uses Refrigerant 12 as the refrigerant. The refrigerant enters
the compressor as a vapor. The Compressor pressurized the heat-laden vapor until its
pressure and heat reach a point much hotter than the outside air. The compressor then
pumps the vapor to the condenser where it cools and changes to a liquid. The liquid then
passes to the receiver-dehydrator. Its function is to filter, remove any moisture and insure a
steady flow of liquid refrigerant into the evap rator through the expansion valve. The
expansion valve is a temperature controlled metering valve which regulates the flow of the
liquid refrigerant to the evaporator. The evaporator absorbs the heat from the air passing
over the coils. From the evaporator the refrigerant vapor returns to the compressor where
the cycle is repeated.

Reissued: 1/15/81 ACCESSORIES AND UTILITIES

4J6
0~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~b 4
 PIPER CHEROKEE SERVICE MANUAL

NOTE

A table at the end of these instructions will assistin locating

and correcting malfunctions which may arise in this system.

NOTE

The air conditioning system should be operated at least once

a month to prevent sticking valves and keep the system
lubricated.

144. MALFUNCTION DETECTION. The detection of system malfunction largely

depends on the mechanic's ability to interpret the gauge pressure readings into system
problems. A system operating normally will have a low side gaugepressure reading that will
correspond with the temperature of the refrigerant evaporating in the evaporator, allowing
for a few degrees temperature rise due to loss in the tube walls and fins. The high side will
have a gauge pressure that will correspond with the temperature of the refrigerant
condensing in the condenser, allowing for a few degreestemperature drop due to loss in the
tube walls and fins.
Any deviation from that which is normal indicates a malfunction within the system due
to a faulty control device,obstruction, defective part, or improper installation.
Detection of system malfunction is made easier with the knowledge that the
temperature and pressure of Refrigerant 12 is in close proximity between the pressures of
twenty and eighty pounds per square inch (psi). A glance at the temperature-pressurechart
will show that there is only a slight variation between the temperature and pressure of the
refrigerant in the lower range.
It is correct to assume that for every pound of pressure added to the low side, a
temperature increase of about one degree Fahrenheit takes place. For instance, a pressure of
23.8 on the chart indicates a temperature of 24° F. A change of pressure of almost one
pound to 24.6 psi givesus a temperature increase to 25 ° F.

NOTE
For each 1,000 feet of elevation above sea level, the gauge
readings will be about one inch of mercury or 1/2 psi higher
than the chart indicates.

It must be pointed out that the actual temperature of the air passing over the coils of
the evaporator will be severaldegrees warmer allowingfor a temperature rise caused by the
loss in the fins and tubing of the evaporator.
The importance of a seasonalcheck up of the air conditioning system should be brought
to the attention of the customer whenever possible. A thorough check of the system
performed in a methodical manner will reveal trouble the customer is often not aware of.

Reissued: 1/15/81 ACCESSORIES AND UTILITIES

4J9
 PIPER CHEROKEE SERVICE MANUAL

Locating and repairing the trouble early will usually result in savingsto the customer both in
time and additional troubles that too often result from neglect.
A Performance Test of the system is the only positive way in which the complete system
can be checked for efficient operation. The air conditioning system should be given this test
before work is begun on the system wheneverpossible, however, if the system is completely
inoperative, repairs must be performed before the system can be properly tested. The test
can uncover further work that must be performed before the system is brought to its full
operating efficiency. The Performance Test should always be performed after repair work
has been done and before the aircraft is released to the customer. The serviceman
performing this test carefully will insure that the repairs have been properly performed and
that the system will operate satisfactorily.
The Performance Test when properly performed includes a thorough examination of the
outside of the system as well as the inside. Many related parts are overlooked because it is
felt they are of no bearing on the operating efficiency of the unit. For this reason, a
thorough visual inspection of the complete system should be performed, followed by an
operating inspection of the system.

14-5. SPECIAL SERVICING PROCEDURES. The air conditioning system should be

serviced by a qualified shop with trained personnel. The following procedures and
precautions should be observed.
The efficiency of this system depends upon the pressure-temperature relationship of
pure refrigerant. As long as the system contains only pure refrigerant plus a specified
amount of compressor oil (which is mixed with the refrigerant), it is considered to be
chemically stable. Foreign materials within the system will affect the chemical stability,
contaminate the system, and decrease its efficiency.
I. GENERAL REFRIGERATION SYSTEMPROCEDURES.
A. REFRIGERANT SAFETY PRECAUTIONS.
1. Refrigerant 12 (commonly known as R-12 or "Freon" 12) is odorless and
colorless in either the liquid or gaseous state. R-12 for charging refrigeration
systems is supplied in pressurized containers (approx. 70 psi at 700F) in
liquid form. Since this material is essentially inert at room temperatures the
dangers are primarily associated with the pressure and the refrigeration
effects of the release and subsequent evaporation of this pressurized liquid.
2. Wear suitable eye protection when handling R-12 due to the possibility of
freezing of the eye if contacted by escaping liquid refrigerant. If liquid R-12
does strike the eye, the following actions should be taken:
a. DO NOT RUB THE EYE.
b. Splash large quantities of cool water into the eye to raise the
temperature.
c. Tape on an eye patch to avoid the possibility of dirt entering the eye.
d. Rush to a physician or hospital for immediate professional aid.
e. DO NOT ATTEMPT TO TREAT IT YOURSELF.
3. If liquid R-12 strikes the skin frostbite can occur. Treat with cool water and
protect with petroleum jelly.
4. Do not discharge large quantities of R-12 into closed rooms. It may displace
most of the air in the room and this could cause oxygen starvation. Gaseous
R-l 2 is heavier than air and flows to the bottom of a container.

Reissued: 1/15/81 ACCESSORIESAND UTILITIES

4J10
 PIPER CHEROKEE SERVICE MANUAL

5. Do not discharge R-12 into an open flame or onto a very hot surface
(500°F+). Poisonous phosgene gas is generated by the action of the heat on
the refrigerant.
6. Do not apply direct flame or other high heat source to a R-12 container due
to the high pressures which will result. If any heating is done to R-12
containers the container pressure should be monitored and kept below 150
psi.
B. SYSTEMSERVICINGPRECAUTIONS.
1. Systems should be discharged slowly to prevent the escape of liquid
refrigerant and the loss of the lubricating oil.
2. Systems should not be left open to the atmosphere when discharged.
Moisture and other contamination may enter and damage open systems.
3. Never introduce anything but pure refrigerant and refrigerant oil into a
system.
4. Keep refrigerant oil containers tightly sealed and clean to prevent absorption
of moisture or other contamination.
5. Use only approved refrigeration oil in the compressor. If any doubt exists
about the cleanlinessof the compressor oil, replace it with new oil.
6. Never reuse oil removed from the system. Discard it.
7. When Loctite Refrigerant Sealant has been used on a joint it must be heated
to 400°F prior to disassembly.Loctite must be used to seal any pipe threads
in the system lines.
8. Replace the receiver-dehydrator assembly on any system which has been
operating with a leak allowing air to enter the system. If a
receiver-dehydratoris left open to the atmosphere it should be replaced due
to the loss of effectivenessof the drying compound it contains.
NOTE
A very strong acid (HCL) is formed when R-12 comes in
contact with moisture.
A new receiver-dehydrator should be opened and connected to the system
only when ready to charge the system with refrigerant.
9. Recommended torque values must be used on all flare fitting and O-ring
joints. See Table XIV-II.

TABLEXIV-II. ALUMINUMTUBINGTORQUE

Metal Tube Thread and Fitting Alum. Tubing

O.D. Size Torque
1/4 7/16 5-7 ft. Ibs.
3/8 5/8 11-13 ft. lbs.
1/2 3/4 15-20 ft. lbs.
5/8 7/8 21-27 ft. lbs.
3/4 1-1/16 28-33 ft. lbs.

Reissued: 1/15/81 ACCESSORIES AND UTILITIES

4J11
 PIPER CHEROKEE SERVICE MANUAL

914

COMPRESSOR
VALVE (SCHRADER
CHARGING) INLINESERVICEVALVE (SCHRADER)

Figure 14-2. ServiceValves

14-6. SERVICE VALVES. The purpose of the service valve is to service the air
conditioning system. (Testing, Bleeding, Evacuatingand Charging).This aircraft is equipped
with servicevalves mounted in the suction and discharge lines of the evaporator assembly.
These valves are the "2" position type Schrader valves.All normal air conditioning service
should be performed at the evaporator assemblymounted valves.

NOTE
Service valves are also located on the compressor. However,
use of these valvesin servicingis not recommended.

NOTE
If a Schrader service valve is not serviceable, the core
assemblymust be replaced.

14-7. SERVICEVALVE REPLACEMENT.The valves on the compressor are sealed with a

gasket placed in the valve port boss. Lubricate the gasket with refrigerant oil of the type
used in the compressor,place the valveswith the tube fitting facing aft and secure with .312
bolts, torque to 15-23inch pounds.

NOTE
Whenever the air conditioning refrigerant lines or system is
opened for any reason, the lines and fittings should be
capped and sealed immediately to prevent dirt and other
contaminants from entering the system. (It is not advisableto
put a plug into the hoses or fittings.)

Reissued:1/15/81 ACCESSORIESAND UTILITIES

4J12
 PIPER CHEROKEE SERVICE MANUAL

408

COMPOUNDLOW HIGHPRESSURE
GAGE
PRESSURE GAGE

TO SUCTION TO DISCHARGE
SERVICEVALVE SERVICEVALVE
TO VACUUMPUMPOR
REFRIGERANT
CYLINDER

Figure 14-3. Test Gauge and ManifoldSet

14-8. TEST GAUGE AND MANIFOLD SET. The proper testing and diagnosis of the air
conditioning system require that a manifold gauge set be attached into the system. This set
consists of two gauges mounted to a manifold. One gauge is a high pressure gaugeused in
the discharge side of the system. The other is a low pressure gaugeused in the suction side
of the system. The manifold is a device havingfittings for both gaugesand connection hoses
with provisions for controlling the flow of refrigerant through the manifold. See Figures
14-3 and 144.
The center port of the manifold set is used for chargingor evacuation procedures, or any
other servicethat may be necessary.
Both the high and low side of the manifold have hand shut-off valves.When the hand
valve is turned all the way in, in a clockwisedirection, the manifold is closed.The pressures
on that side of the system will, however, be recorded on the gaugeabove the hose.
Cracking the hand valve, in the counterclockwise direction, opens the system to the
middle service port of the manifold set. This is desirable only when it is necessary to let
refrigerant out or into the system. Refer to Figures 14-3 and 14-4.

14-9. CHECKINGTHE SYSTEM FOR LEAKS. There are several methods of doing this
operation, depending on the type of equipment which is available. Two methods of
performing this check will be covered in the followingparagraphs.

Reissued: 1/15/81 ACCESSORIES AND UTILITIES

4J13
 PIPER CHEROKEE SERVICE MANUAL

1257

A
DIAGRAM

DIAGRAM
B

C
DIAGRAM

DIAGRAM
D
Figure 14-4.Manifold Set Operation

Reissued:1/15/81 ACCESSORIESAND UTILITIES

4J14
 PIPER CHEROKEE SERVICE MANUAL

COMPOUND
GAGE50 P.S.I. PRESSURE
GAGE
VALVE
SCHRADER

CLOSED
L H SCHRADERVALVE

MANIFOLD
GAGESET
REFRIGERANT
CONTAINER
OPENTO 50 P.S.I. EVAPORATOR
ASS'Y
THENCLOSE

Figure 14-5. Leak Test Hookup

NOTE
Evacuate system prior to leak check.

14-10. LEAK CHECK- METHODI.

a. Connect the manifold gauge set into the system and determine if there is any
refrigerant in the system. A minimum of 50 psi refrigerant pressure in the system is needed
for leak detection. (Refer to Figure 14-5.)
b. Purge the hoses of air by allowing some refrigerant to escape from the connections
at the servicevalves.Then tighten connections at the servicevalve.
c. Close the low side manifold valve and open the high side manifold valve.
d. Open the refrigerant container service valve and allow the pressure at the low side
gauge to reach 50 psi at which time close the high side manifold valve.
e. Close the refrigerant container service valve and remove the hose if no leaks are
evident.
f. It is advisable to use an electronic leak detector to check this system instead of an
open flame leak detector due to the possible presence of gasoline fumes in the engine area.
g. If any leaks are found, purge the system of refrigerant, make the necessary repairs
and check the compressor oil.
h. Add oil, if required, (refer to Paragraph 14-21 and Table XIV-II) then repeat steps a
thru e.
i. If no further leaks are found, the system may be evacuated and charged. Refer to
Paragraphs 14-13 and 14-14.

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 PIPER CHEROKEE SERVICE MANUAL

14-11. LEAKCHECK- METHODII.

a. Remove the access panel at the rear of the cabin to gain accessto the servicevalves.
b. Remove the protective cap on the high pressure Schradervalvefitting and connect a
charging hose with a shut-off valve arrangement to the fitting. The charginghose must have
a Schrader fitting or adapter to fit the valve.
c. Connect the other end of the charging hose to a small cylinder of refrigerant and
purge the hose by allowing a slight amount of refrigerant gas to escape from the Schrader
valvefitting.
d. The cylinder of refrigerant should be placed upright in a container of warm (125°F
max. water on a small scale.)
e. Allow approximately 1/2 pound of refrigerant to enter the system by opening the
valve on the charginghose and observingthe weight change on the scale.
f. Usingan electronic leak detector, check alljoints and repair any leaks.
g. After completion of repair of any leaks, proceed to check the system in accordance
with one of the methods outlined for any other leaks.
h. If no further repair is required on the system, it is now ready to evacuate in
accordance with paragraph 14-13.

14-12. DISCHARGING. (Required only if system contains refrigerant.)

NOTE
Applies to Kent Moore J23500 or similar charging station.
Refer to Figure 14-7.
a. Close all valveson chargingstation.
b. Connect red high pressure charging line to high pressure Schrader valve at the
evaporator fitting.
c. Open valve 8 (high pressure control) on chargingstation one turn.
d.. Hold end of blue low pressure charging line in a shop rag and slowly open valve2
(low pressure control) on charging station allowing refrigerant to exhaust from system into
shop rag.

CAUTION
Refrigerant can cause freezing of skin. Be particularly careful
not to allowcontact with the eyes.
Do not allow refrigerant to escape too rapidly, as excessive
oil may be carried out of system. Whenhissing stops, system
is empty and valve should be closed if no further work is
planned.

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 PIPER CHEROKEE SERVICE MANUAL

988
COMPOUNDGAGE
PULL26 TO 28 PRESSUREGAGE
INCHESVACUUM

SCHRADER
VACUUMPUMP VALVE

NOTE: OPEN BOTHSERVICE VALVES EVAPORATORASS'Y

(COUNTERCLOCKWISE) ONE TURN

Figure 14-6. Evacuation Hookup

14-13. EVACUATINGTHE SYSTEM. If the system has been operated in a discharged

condition or anytime the system has been open to atmospheric pressure, the
receiver-dehydrator must be replaced and the system evacuated to remove any trapped air
and moisture which has entered it. A vacuum pump capable of pulling 29 inches of mercury
or better should be used. As we lower the pressure in the air conditioningsystem, we lower
the boiling temperature of the water (moisture) that may be present. Then we are able to
pull this water, in the form of vapor, out of the system. The followingtable demonstates the
effectivenessof moisture removal under a givenvacuum.

System Vacuum Temperature F.

27.99 100
COMPOUND GAUGE
READING IN INCHES
28.89 80
OF MERCURY VACUUM 29.40 60
29.71 40
29.82 20
29.88 0

NOTE

For each 1,000 feet of elevation above sea level, the

compound gauge reading will be about one inch lower,
numerically.

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 PIPER CHEROKEE SERVICE MANUAL

The followingsteps should be ofhelp-when performing this operation.

a. Remove access panel at the rear of the cabin to gain access to the Schrader service
valves.
CAUTION
Ascertain that all system pressure is released before
attempting the evacuation. (Refer to Paragraph 14-5.)

b. Connect the manifold gaugeset to the airplane servicevalves.(Refer to Figure 14-6.)

c. The high and low manifold hand valvesshould be in the closed position. (Refer to
Figures 14-3 and 14-4.) .
d. Connect the center manifold hose to the inlet of the vacuum pump.

NOTE
Make sure the exhaust port on the vacuum pump is open to
avoid damage to the vacuum pump.

e. Start the vacuum pump and open the low side manifold hand valve. Observe the
compound, low pressure gaugeneedle, it should show a slight vacuum.
f. Continue to operate the vacuum pump until 26 to 28 inches of vacuum is attained
on the low pressure gauge, then extend the operation for another 25 minutes.
g. If the system cannot maintain 26 to 28 inches of vacuum, close both manifold hand
valvesand observe the compound gauge.
h. Should the compound gauge show a loss of vacuum, there is a leak in the system
which must be repaired before continuing with evacuation.
i If no leaks are evident, reopen both manifold hand valves and continue the
evacuation for another 30 minutes.
j. Closeboth manifold hand valves,stop vacuum pump and disconnect center manifold
hose from the vacuum pump.
k. Proceed to charge the system in accordance with Paragraph 14-14.

NOTE
The system should be charged as soon as it has been evacuated.

14-14. CHARGING THE SYSTEM. When the system is completely evacuated in

accordance with instructions given in paragraph 14-13, one of the following procedures
should be used to charge the system.

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 PIPER CHEROKEE SERVICE MANUAL

. CYLINDER PRESSURE GAUGE. I

COMPOUND SAUSE
8. VALVE. LOW PRiESURE CONTROL 1
4. VALVE, VACUUMCONTROL 2 9
S. CHARSIN CYLINDOR 2
S. lReACET 3 1A
7. SIlT LASS I
S. CYLINDER BAE VALVE
S. HlIN PRESSURE «AUSE _ 2—
2
I. VALVE. HIGH PCRESSURE CONTROL
11. VALVE, REPRI. CONTROL 5 _ 2
to. CHARIN LINE HOSE HOLDER
13. BRACKET
14. LOW PRESSURE CHARIINS LINE 14
IS. HIlG PRESSURE CHARNIN LINE — =
IS. HEATIMN ELEMENT PLUS 15
17. VACUUMPuMP 7 2
S. OIL FILL LOCATION
3. NECKAEMLY 16 21
20. REFRISERANT DRUM SUPPORT
2 L» RIEFRIERANT DRUM VALVE
IL VACUUM PUMP VALVE
2. VACUUM PUMP EXHAUS POT17
OT
24. TOP CYLINDER VALVE
. REPRIERAKT DRUM 22
236. WEE STRAP 23
T2. IRERIOERNAT DRUM REOUCER
2. CHARIN CYLINDER HOSE 31
2a. VACUUM PUMP INTAKE HOSE
SO. VACUUM PUMP SWITCH
41. VACUUMPUMP POWERCORD

Figure 14-7. ChargingStand

14-15. WITH A CHARGING STAND. This is the preferred method of chargingthe system.
NOTE
The following instructions apply to Kent Moore. J23500
charging stand. (Refer to Figure 14-7.)
a. With the system discharged and evacuated, proceed to hook-up the charging stand.
(Refer to Figure 14-8.)
b. Fill the charging cylinder by openingthe valve (8) at the base of the charging cylinder
and filling the sight glass with two pounds of liquid refrigerant.
c. As refrigerant stops filling the sight glass, open the valve (24) at the top of the gauge
neck assembly intermittently to relievehead pressure and allow refrigerant to continue filling
the sight glass to the required amount.
d. When refrigerant reachesthe required level in the sight glass, closeboth the valve(8)at
the base of the cylinder and the valve (21)at the bottom of refrigerant tank. Be sure the top
valve (24) is fully closed.
NOTE
If bubbling occurs in sight glass, reopen the cylinder base
valve (8) momentarily to equalize drum and cylinder pressure.

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 PIPER CHEROKEE SERVICE MANUAL

e. Connect the heating element plug to a 110-voltoutlet.

f. Turn cylindersight glass to match pressure reading on cylinderpressuregauge (1). This
scale should be used during entire charging operation.
g. Close valve (3) (low pressure control), fully open valve ( 11)(refrigerant control) and
allow all the liquid refrigerant contained in the charging cylinder to enter high side of aircraft
system.
h. Whenthe full charge of refrigerant has entered the system,closevalve(11)(refrigerant
control) and valve (10) (high pressure control).
i. After completion of charging, close all valves on the charging stand. Disconnect the
high and low pressure charging linesfrom the aircraft system. (A smallamount of refrigerant
remaining in the lines will escape.) Replace lines on holder of charging stand to keep air and
dirt out of lines.Open the valve (24) at the top of cylinder to relieveany remaining pressure,
then reclose the valve.
j. Reinstallprotective caps of Schrader valvesand any accesspanelspreviouslyremoved.

14-16. USING THE AIRPLANE COMPRESSOR TO CHARGE THE SYSTEM. This

method is the least desirable due to the requirement of operating the airplane's engine to run
the compressor.
CAUTION
Ascertain that the area around the airplane is clear and a
qualified person is at the controls of the airplane.
a. With the system evacuated as outlined in Paragraph 14-13,connect the refrigerant
charging hose to the manifold (refer to Figure 14-8)and purge the charging hose of air.
b. Place the refrigerant container on a scale to observe the amount of refrigerant
entering the system. Open the high pressure valve and add as much refrigerant as possible.
c. Close the high pressure valve, start the engine and operate it at 900 to 1000 RPM.
d. Operate the air conditioner and set controls to maximum cooling.
e. -Open-the low pressure valve and complete charging the system.
f. Close the low pressure valve after two pounds of refrigerant has been added to the
system.
g. With the system still operating, observe the sight glass in the top of the receiver-
dehydrator by removing the plastic plug.
h. The sight glass should be clear of any bubbles or foam. If bubbles or foam are seen
passing through the sight glass, it is an indication of a low refrigerant charge in the system
and more refrigerant is required. This check should be made with OAT of 70° F or higher
and with the air conditioner operating.
i. If more refrigerant must be added to the system, open the low pressure valve and
increase engine speed to 2000 RPM and observe the sight glass. After the sight glass has
cleared, close the low pressure valve and observe the pressure gauges. At 1000 RPM the
gauge pressure should be 15to 20 psi on the low side and 150to 200 on the high side.

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 PIPER CHEROKEESERVICEMANUAL

DISCHARGE
U

SUCTION
LINE
I CONDENSE

COIL FITTING

COMPRESSOR EVAPORATOR

THIS
ENDOFHOSE
MUSTHAVEDEVICE
TO DEPRESS
SCHRADERVALVE

CHARGING
STAND

OPTIONALMETHOD PREFERRED
METHOD

Figure 14-8. ChargingHookup

NOTE
Suspect leaks or an inaccurate scale if two pounds of
refrigerantdoesnot fill the system.

j. Shut off the air conditioning system and airplane engine. Then, remove the charging
lines from the Schradervalveswith care due to the refrigerant remainingin the hose.

NOTE

A shop cloth should be used to divert escaping refrigerant

when disconnecting the charging hose from the Schrader
valve. Recap the valve.

14-17. ADDITION OF PARTIAL CHARGE TO SYSTEM. It is possible to top off this

system with refrigerantby the followingmethod.
a. Remove the accesspanel at the rear of the cabin.

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 PIPER CHEROKEE SERVICE MANUAL

b. Connect a charging hose-di:a refrigerant cylinder and also to the Schrader valve
fitting on the suction line. (Refer to Figure 14-8.)
c. Purge the charginghose by allowinga small amount of refrigerant gas to escape at
the Schradervalve fitting.
d. Start the engineand operate at 1000 RPMand turn the air conditioner on maximum
cool.
e. Remove the plastic plug from the sight glassin the top of the receiver-dehydrator.
f. With a low refrigerant charge in the system, bubbles will be seen passing thru the
sight glasswhen the system is operating.
g. Open the valve on the refrigerant cylinder.
h. Allow refrigerant to flow into the system until the bubbles disappear from the sight
glass.
i. Close the refrigerant valve and check to see that the sight glassremains clear during
system operation.
j. When the sight glass stays clear of bubbles, add an additional 1/4 pound of
refrigerant to the system. (Engine should be operating at 1000 RPM).
NOTE
This should be done with OAT at 700F, or higher, with the
air conditioner operating.
k. Shut off the air conditioner and engine. Remove the charging hose from the
Schrader valvewith care due to refrigerant remainingin the line.
1. Replace the accesspanels.

14-18. COMPRESSORSERVICE. It is not advisableto servicethe compressor in the field.

It should be done by a qualified shop which has the special equipment and trained personnel
required to properly servicethe unit.
Maintenance to this unit and its related components is limited to the replacement of
worn drive belt and magnetic clutch. Any other service requires removal of the compressor
from the system.

NOTE
An important factor in air conditioning servicing is
cleanliness and care should be exercised to prevent dirt or
foreign material from entering the system. All hose and
tubing ends should be capped immediately. Any lubrication
required in the assembly of the components should be
refrigerant oil of the type used in the compressor.

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 PIPER CHEROKEE SERVICE MANUAL

14-19. COMPRESSORREMOVAL. (The removal of the compressor requires a complete

system discharge.) See Paragraph 14-12.
a. Be certain the circuit protector is off for the air conditioning system.
b. Remove the engine cowlingand right front baffles.
c. Disconnect the electricalleads to the magnetic clutch on the compressor.
d. Depressurizethe air conditioning system.
e. Remove the suction and dischargelines from the servicevalveson the compressor.

NOTE
All open lines should be capped immediately to prevent dirt
and moisture from entering the system.

f. Loosen the bolt securing the compressor idler pulley to release the belt tension and
remove belt from compressor pulley. (Do not force belt over the pulleys.)
g. Support the compressor and remove,the 6 bolts securing the compressor to the
engine mounting brackets.

14-20. COMPRESSORINSTALLATION.
a. Place the compressor to the mounting brackets. Install the six bolts and
progressivelytorque to 14-17 ft. pounds. (Safety all bolts with .032 safety wire.)
b. Check the oil level in the compressor in, accordance with instructions given in
paragraph 14-21.
c. Place drive belt over clutch pulley and adjust the alignment of the pulleys and belt in
accordance with instructions givenin paragraph 14-22.

CAUTION
Do not force the belt into the pulley sheavie.If necessary,
remove the idler assembly.

d. Connect the dischargeand suction lines to their respectiveservicevalvefittings.

e. Evacuate and charge the system per paragraphs 14-13 and 14-14.

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Ressued: 1158423
4J23
 PIPER CHEROKEE SERVICE MANUAL

WARNING

If the air conditioner is to be operated on the ground for

servicing,the test area should be clean and free of any loose
objects lying on the ramp. Only the servicevalveslocated on
the evaporator assemblyshould be used for testing.

14-21. CHECKING COMPRESSOROIL. The oil level should be checked any time the
system is discharged. The followingsteps should be followed to perform this check.
a. It will be necessaryto dischargethe system. (Refer to Paragraph 14-12.)
b. Fabricate an oil dipstick. (Refer to Figure 14-9.)
c. Remove the oil fill plug. (A .375 inch plug in the top side of the compressor
crankcase.)
d. Before inserting the dipstick, the crankshaft Woodruff key should be located in the
up position. (The front face of the compressor clutch is marked with a stamped "K"
ndicating the key position). The oil level should be measured from the lowest point in the
crankcase. Usethe long end of the dipstick. (See Figure 14-9.)
e. With the compressor in the installed position use Table XlV-IIIto determine the
amount of oil in crankcase.
f. The compressor should never be operated with less than 6 ounces of oil. When oil is
added the level should not go above 10 ounces. Piper refrigerant oil PMS-L2000 or
equivalent 500 viscosityrefrigerant oil must be used.
g. Evacuate and charge system. (Per Paragraphs 14-13 and 14-14.)

NOTE
The 10 ounce oil level is required in compressorsinstalled on
new systems. Some oil is distributed in the system during
operation. Replacement compressors should be charged with
10 ounces of oil.

CAUTION
The oil plug should not be removed with pressure in the
system.

TABLEXIV-III. COMPRESSOROIL CHARGE

Oil ChargeOunces 6 8 10
Dipstick Reading Inches 13/16" 1.00" 1-3/16"

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 PIPER CHEROKEE SERVICE MANUAL

4078

4.68
1.50
TORQUE-
15-23Ft. Lbs.
4PLCS THIS ENDFOR
HORIZONTAL
MOUNT

1/8 INCHAPART
NOTE;12 NOTCHES
STARTINGAT EACHEND. 1.50

THIS ENDFOR
VERTICAL
OIL CHECKPLUG MOUNT
(TYPICALTWOSIDES)

Figure 14-9. CompressorAnd Fabricated Oil Dipstick

14-22. REPLACEMENT OF COMPRESSOR AND/OR ALTERNATOR DRIVE

BELTS. (Refer to Figure 14-10.)
a. Remove the old belts by removing the spinner, propeller, nose cowl, right front
baffle, starter ring gear assemblyand drivebelts.
b. Place the new belt or belts in their appropriate positions on the starter ring gear
sheaves.
c. Reinstall the starter ring gear assembly,propeller and spinner.
d. Route the belts to the proper pulley sheavesas shown in Figure 14-10.
CAUTION

Do not force the belts into the pulley sheaves. Remove the
idler assemblies if necessary and the alternator lower
mounting bolts in order to install the belts.
e. Check the belt and pulley alignment of the compressor and/or alternator by the
followingmethod:
1. A datum line must be established for checking belt and pulley alignment. A
nominal dimension must be established between the forward edge of each belt and the
forward machined surface of the ring gear. This dimension should be taken at the ring gear
assembly where the belts are in their sheaves. The amount of misalignment can then be
determined at the other pulley sheaves by using a stiff straightedge of sufficient length to
extend from the front of the ring gear to the component sheaves.

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 PIPER CHEROKEE SERVICE MANUAL

NOTE
Insure adequate ring gear surface contact to provide a solid
base for the straightedge.

2. Obtain a basic measurement from the top of the ring gear by measuring the
width of the starter ring gear plus the dimensionfrom the forward machined surface of the
ring gear to the forward edge of the compressor or alternator (on early installations) drive
belt. (Refer to Figure 14-10.)
3. The check and adjustments of the compressor and/or alternator drive belts
require different procedures; refer to followingappropriate instructions:
f. Compressor Belt Alignment: (Refer to Figure 14-10.)
1. Place the straightedge against the right forward side of the ring gear and measure
belt alignment at compressor sheave(Point-B).
2. Measure belt alignment at the compressor idler pulley (Point-A). The belt
misalignment at Point-A should be half the misalignment of Point-B and the dimension at
the top of the ring gear and in the same direction fore and aft.
3. If at Point-A nominal misalignment is not within + .030 of an inch as obtained
from Step 2, add or remove shims as required. Belt alignment should be made as close to
nominal as shims will allow.
4. On earlier installations, insure that there is a positive clearance between the jam
nut on the idler pulley shoulder bolt and the face of the mounting bracket. Refer to
paragraph 14-23 for belt tension adjustment. No jam nut is used on newer idler pulley
bracket.
g. Alternator Belt Alignment - Early Installations: (Refer to Figure 14-10.) On early
installations there are no provisions for shimming the alternator and/or the alternator idler
pulley in the forward direction, On later installations shims can be transferred as required
from forward or aft of the alternator mounting lugs to achieve alignment. If shimming is
required, insure that the alternator mounting bolts are of adequate length. For present
installations which incorporate the new bracket assembly,P/N 79584-02, proceed to step h.
Older installations must still follow steps 1 thru 5 until the new bracket is used:
1. Place the straightedge against the left forward side of the ring gear and measure
belt alignment at the alternator pulley sheave(Point-C).
2. If at Point-C nominal misalignment is not within + .025 of an inch, add or
remove shims as required between the alternator mounting bracket and the alternator
mounting lugs. (Refer to Figure 14-10.) On later installations, transfer shims as required
from forward or aft of the alternator mounting lugs to achieve alignment.
3. On later installations, measure belt alignment at the alternator idler pulley
sheave (Point-D). The belt misalignment at Point-D should be halfway between the
misalignment of Point-C and the dimension at the top of the ring gear and in the same
direction fore and aft. Earlier models provide no means of shimmingat the alternator idler
pulley, and therefore need not comply with this paragraph.
4. Alternator Pulley Skew: (Refer to Figure 14-10.) The face of the alternator
pulley must be parallel to the starter ring gear. If skew (misalignment) is in excess of .015 of
an inch, loosen the alternator attachment bolts and adjust the alternator to the minimum
skew. Tighten the mounting bolts and safety the support bracket bolt if not already
safetied.

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 PIPER CHEROKEE SERVICE MANUAL

5. The belt alignment at the alternator pulley should be made as close as possible to
the nominal alignment, and pulley skew is to be held within this alignment. Refer to
paragraph 14-23 for belt tension adjustment.
h. Alternator Belt Alignment - Present Installation: (Refer to Figure 14-10.)
1. With the alternator belt installed, align the idler pulley in the belt plane by
adding or removing shims, P/N 62833-82 as required. Refer to paragraph 14-23 for belt
tension adjustment.

14-23. ADJUSTMENTOF DRIVE BELT TENSION. The adjustment of the compressor

and/or alternator drive belts is very important to obtain long belt life and proper component
operation.
a. Adjust new compressor belt to 120 pounds span tension and new alternator belt to
90-100 pounds span tension. Use a calibrated belt tension gauge.
NOTE

The higher tension specified for a new belt isto compensate

for the initial stretch that takes place as soon as it is
operated. These higher tension values should not be applied
to belts which previously have been used. See tensions noted
below for used belts.
b. Install the right front engine baffle and secure the engine cowling if previously
removed.
c. Run the engine for a 15 minute period at 1200 RPM.
WARNING
If the air conditioner is to be operated on the ground for
servicing,the test area should be clean and free of any loose
objects lying on the ramp. Only the servicevalveslocated on
the evaporator assemblyshould be used for testing.
d. Shut down engine and recheck both belt tensions. If compressorbelt tension falls as
low as 60 pounds, retension to 80 pounds. If alternator belt tension falls below 50 pounds,
retension to 70 pounds.
e. This tension check should be made at every 100 hours or annual inspection,
whicheveroccurs first.
f. Check all idler and bracket bolts for safety and replace engine cowling.

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4K3
 4K4
INTENTIONALLYLEFT BLANK
 PIPER CHEROKEESERVICEMANUAL

903

NOMINAL DIMENSION FOR NOMINAL DIMENSION FOR

COMPRESSOR BELT ALIGNMENT ALTERNATOR BELT ALIGNMENT

MISALIGNMENT MISALIGNMENT
DIMENSION DIMENSION
CHECK CHECK

DATUM LINE DATUM LINE

(FORWARD SURFACE OF RING GEAR) (FORWARD SURFACE OF RING GEAR)

941

PRESENTINSTL. INSURE
URE THERE IS POSITIVE
CLEARANCE BETWEEN JAM NUT
CLEARANCE
AND MOUNTING BRACKET.

1. RING GEAR
2. COMPRESSORIDLER PULLEY
3. COMPRESSOR
4. COMPRESSOR
5. ALTERNATOR
6. RING GEAR
7. COMPRESSORBELT
8. COMPRESSORIDLER SHEAVE
9. COMPRESSORSHEAVE
10. RING GEAR SHEAVE
11. ALTERNATOR BELT
12. ALTERNATOR SHEAVE
13. ALTERNATOR IDLER SHEAVE
14. RING GEAR
.15. ALTERNATOR SUPPORT BRACKET
16. ALTERNATOR
17. ALTERNATOR MOUNTING BRACKET

ADD OR REMOVE SHIMS (P/N

62833-83) AS REQUIRED FOR
PROPER COMPRESSOR BELT
ALIGNMENT.
VIEW A

Figure 14-10. Compressor and Alternator Belt Installation

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4K5
 PIPER CHEROKEE SERVICE MANUAL

918 LATER INSTL. 917

,14
EDGE
STRAIGHTEDGE

SAFETYWIRETO
FWD

FWD POINT "A"

A
TO ESTABLISH ALTERNATOR
PULLEY AND RING GEAR POINT "B"
PARALLEL ALIGNMENT, MEASURE
FROMSTRAIGHTEDGETO FACEOF
PULLEY (AT TWO PLACES),POINT
"C", RELATIVE
and
BELT-PULLEYCONTACT.

ADD SHIMS (P/N 62833-41) AS

REQUIRED FOR PROPER
ALTERNATORBELT ALIGNMENT.

936 PRESENTINSTL.
BRACKETASSY. P/N 79584-2
ADD OR REMOVESHIMSP/N62833-82
AS REQUIREDTO ALIGN IDLER IN
BELT PLANE

................................
. . . ................................................
.
VIEW A-A 911

"C"

-12

POINT "D"

Figure 14-10. Compressor and Alternator Belt Installation (cont.)

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 PIPER CHEROKEESERVICEMANUAL

413

1. CAPSCREW
2. ROTOR PULLEY AS'Y
3. CAPSCREWS AND LOCK WASERS
4. FIELD ASSY
5. COMPRESSOR

Figure 14-11. Magnetic Clutch

14-24. MAGNETICCLUTCH.

14-25. MAGNETICCLUTCHREMOVAL. (Refer to Figure 14-11.)

a. Remove the self-lockingcapscrew and washer (1) from the compressor shaft.
b. Insert a 5/8 - 11 UNC-2Bbolt in the threaded portion of the hub and tighten. The
pressure exerted by the bolt on the end of the compressor crankshaft will force off the rotor
pulley assembly (2) without damage to the clutch or compressor.

CAUTION
Do not use a wheel puller on the outer flange of the pulley.
This can damage the pulley groovesor clutch bearings.

c. Remove the four bolts securingthe field assemblyagainst the compressor bosses and
remove the bolts, washers and field assembly.

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 PIPER CHEROKEE SERVICE MANUAL

14-26. MAGNETICCLUTCHINSTALLATION. (Refer to Figure 14-11.)

a. Position the field assembly(4) against the compressor bosses, with the electrical
leads to the cylinder side of the compressor.
b. Secure the field assembly (4) with four capscrews and lockwashers (3), do not
torque at this time.
c. Connect the electrical lead from the field assembly.

NOTE
The compressor shaft must be clean and free from burrs.

d. Slide the pulley assembly (2) over the field assembly and onto the crankshaft, now
torque the field assembly 85 to 120 inch pounds. Then secure pulley assembly with washer
and new self-lockingcapscrew(1). Torque the capscrew to 180 to 240 inch pounds.

'NOTE

If the clutch is not engaged while tightening the cap screw,

insert a spanner into the holes provided in the armature face.

e. Spin the pulley by hand to check for any interference between the field (4) and
rotor pulley assemblies (2). A rubbing noise can be heard as the pulley rotates if there is
interference. The rotor pulley assembly must be removed and the mounting of the field
assemblyadjusted until the interference is eliminated.

14-27. REFRIGERANT LINES AND ROUTING.

The refrigerant lines in this aircraft are flexible high pressure hoses and should be
handled accordingly. The hoses in the power plant area are routed so as to provide
maximum protection from heat and abrasion. They couple at the firewall to hoses routed
through the two inboard, external hat section on the bottom of the fuselage, up thru the
floor to the condenser and evaporator in the tail cone. The discharge is in the right hat
section and the suction in the left.

NOTE
Before any of the hose couplings are uncoupled, the system
must be completely discharged.(See Paragraph 14-12.)

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 PIPER CHEROKEE SERVICE MANUAL

14-28. RECEIVER-DEHYDRATOR.

14-29. RECEIVER-DEHYDRATORREMOVAL. This unit is mounted on the inboard side

of the evaporator assemblyhousing.
a. Dischargethe system of all refrigerant. (See Paragraph 14-12.)
b. Uncouple the refrigerant lines at the receiver-dehydrator.(See Paragraph 14-5, B-7.)
c. Remove the clamp attaching the unit to the evaporator housing.

NOTE

This part is not serviceable, it must be replaced. The

receiver-dehydrator should be replaced when the system has
been operated without a charge or is left open.

14-30. RECEIVER-DEHYDRATORINSTALLATION.
a. Slip the mounting bracket around the receiver and put it in place on the evaporator
housing with the tube fitting on top. Align the fittings to the proper line before securingthe
mounting bracket.

NOTE
Torque the fittings (See Table XIV-I).

b. Evacuate and recharge the system in accordance with paragraph 14-13 and 14-14.

14-31. CONDENSER. The condenser is mounted in a frame assembly located in the

bottom of the fuselagebetween stations 156.00 and 191.00.

14-32. CONDENSERASSEMBLYREMOVAL.
a. Dischargethe system. (See Paragraph 14-5 and 14-12.)
b. Remove accesspanel from the aft bulkhead of cabin.
c. Remove the forward cover panel.
d. Uncouple the suction and discharge hoses at the condenser fitting. (See Paragraph
14-5, B-7). Remove the hose clamps holding the hoses to the condenser frame.
e. Remove the AN-3 bolts from the upper ends of the side hinges and rod ends.
f. Support the condenser assembly and remove the bolt attaching the actuating rod to
the condenser assembly.

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 PIPER CHEROKEE SERVICE MANUAL

g. Lower the aft end of the assembly on the piano hinge at the forward end of
assembly.
h. Remove the eight screws attaching the piano hinge to the condenser frame assembly
and remove from aircraft.
i. To remove condenser core from assembly, remove the screws in the side mounting
frame.

14-33. CONDENSERINSTALLATION.
a. Install the condenser core to the frame assembly with the hose fittings forward and
up.
b. Place the condenser and frame assembly to the fuselageframe mounting bracket and
insert the (8) screwsinto the piano hinge.
c. Attach the side hingesand actuating rod and rig per Paragraph 14-35.
d. Seal and couple the hose fittings (seal with Loctite refrigerant sealant applied to
flangesonly).
e. Adjust the condenser in accordancewith Paragraph 14-35.
f. Seal all around forward cover panel (and aft coverpanel if removed) with Permagum
Bead No. 576 purchased from Prestolite EngineeringCompany. (See Figure 14-12.)

WARNING

Wheneverit is necessaryto remove and replace the cabin rear

panel, it should be replaced and sealed in the original manner
to prevent exhaust gases from entering the cabin. After
removing and replacing the rear panel, conduct a carbon
monoxide test on ground and in flight with and without the
air conditioner operating. Presence of CO shall not exceed 1
part in 20,000.

14-34. CONDENSERDOOR ACTUATOR. The actuator is on a bracket mounted between

two bulkheads in the tail cone. It is coupled to the condenser assembly through a bellcrank
mounted to a bracket on the bulkhead aft of the condenser. The actuator travel is
controlled by two limit switches. On early installations the down switch is located on the
inboard bellcrank support and the up switch on the condenser frame. On later installations
both the up and down switches are located on the actuator. Refer to Figure 14-12for the
switch locations of the particular installation.

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 PIPER CHEROKEE SERVICE MANUAL

1. ACTUATING TRANSMISSION ASSY. Seal all around forward and aft covers with
2. BELLCRANK ASSY. (CONDENSER)
Permagum Bead No. 576 purchased
from Prestollte
3. PUSHRODASSY. Engineering
Company.
4. BELLCRANK ASSY. (MECHANISM)
5. OPEN LIMIT SWITCH
6. CLOSED LIMIT IWITCH
7. CONDENSER
8. CONDENSER DOOR
10. PUSH ROD
1831

REARAND SIDES

5 + .50

Early Installation - Detail A

SEAL ALL AROUND FORWARD AND-AFT COVERS WITH PERMAGUM BEAD NO. 576
17SS PURCHASED FROM PRESTOUTE ENGINEERING COMPANY.

I 10

Present Installation- Detail B

LIMITSWITCH
44
ACTUATING TRANSMISSION ASSY.
2. BELLCRANKASSY. (CONDENSER)
3. PUSH ROD ASY.
4. BELLCRANK ASSY. (MECHANISM)
S. OPEN LIMIT SWITCH
6.CLOSED LIMIT SWITCH
7. CONDENSER
.12
8. CONDENSER DOOR
.22 NOM.CLEARANCE
9. PUSH ROD
10. TRANSMISSION MOTOR ASSY. PRIOR TO PRELOAD

Figure 14-12. Condenser Air Scoop Installation

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 PIPER CHEROKEE SERVICE MANUAL

14-35. CONDENSERASSEMBLYRIGGING INSTRUCTIONS.(Refer to :Figure 14-12.)

The condenser assembly is actual. by an electric motor through bellcranks, push rods
and limit switches.

NOTE

There are two installations of this system. The first or early

installation had the limit switches located as shown in Figure
14-12, Detail A. The second or present installation has the
limit switches located as shown in Figure 14-12, Detail B.
The instructions covering the adjustment of the limit
switches will be covered in separate steps.

It is necessary for the condenser door to fit flush with the fuselage skin, and with
increased force along the forward edge. The following steps will help accomplish this..
requirement:
Early Installations: (Refer to Figure 14-12, Detail A.).
a. With actuator fully extended, adjust push rod (3) to open the condenser door (8)
five inches ± .5 when measured from the leading edge of the door to the fuselage skin.
Adjust the open limit switch (5) to actuate when the door is approximately .25 of an inch
before the fully open position.
b. Adjust the push rods (9) so that a vertically measured gap of .062 of an inch exists
along the trailing edge of the door at the instant the forward edge becomes flush with
fuselage.
c. When the above adjustments have been completed, assure that the door actuator
assembly (1) is fully retracted and that the door is held upward with sufficient force to close
the trailing edge gap. While maintaining these conditions, adjust push rod (3) so that the
upper edge of hole in rod end bearing is tangent to lower edge of hole in bellcrank (2).
Adjust the closedlimit switch (6) to shut off motor once this fit has been obtained.
d. Cyclethe assembly several times to be certain it operates properly without binding
or misalignment.
Present Installations: (Refer to Figure 14-12, Detail B.)
a. Adjust open limit switch (5) to open the condenser door (8) 5.00 + .50 inches when
measured from the leading edge of the door to the fuselage skin.
b. Adjust the push rods (9) so that a vertically measured gap of .16 of an inch exists
along the trailing edge of the door at the instant the forward edge of the door becomes flush
with the fuselageskin.
c. With the door fully closed adjust the "CLOSED" (6) limit switch so that the
actuator (1) travels an additional .12 of an inch after the door is fully closed, this is
necessary to preload the mechanism.Refer to Figure 14-12, Detail B - View AA.
d. Cycle the assembly several times to be certain it operates properly without binding.

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 PIPER CHEROKEE SERVICE MANUAL

TO EVAPORATOR3
2612 TO EVAPORATOR

VALVEASS'Y

CAPILLARYCOIL

FROMRECEIVER
DEHYDRATOR

Figure 14-13. Expansion Valve

14-36. EXPANSIONVALVE. (See Figure 14-13.)

14-37. EXPANSIONVALVEREMOVAL. The expansion valveis located in the evaporator

assembly between the receiver drier and the evaporator inlet. The capillary coil is attached
to the evaporator outlet line.
a. Remove the necessaryaccesspanels and discharge system.
b. Remove the capillary coil from the outlet line. (Do not kink the capillary tube.)
c. Uncouple all related tube fittings. (See Paragraph 14-5, B-7.)

NOTE
If this part is not serviceable,it must be replaced with a new
part.

14-38. EXPANSIONVALVEINSTALLATION.
a. Install the expansion valve in the inlet line of the evaporator core by coupling the
related fittings. (Sealall couplingswith sealant applied to tube flangesonly.) Torque fittings
per Table XIV-I.
b. Secure the capillarycoil to the evaporator outlet line.
c. Evacuate and charge the system. (See Paragraphs 14-13and 14-14.)Check for leaks.
(See Paragraph 14-9.)
d. -Replace accesspanels.

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 PIPER CHEROKEESERVICEMANUAL

14-39. EVAPORATORASSEMBLY.The evaporator assembly consists of the evaporator

core, receiver-dehydrator, expansion valve,circulating fan and pressure switch together with
necessary housing and plumbing. The housing is fabricated of Cycolac type material. The
condensed moisture is dumped overboard through a hose clamped to a fitting on the bottom
of the evaporator housing.

14-40. EVAPORATOR ASSEMBLY REMOVAL. The evaporator assembly is located

behind the cabin rear panel, attached to the mounting panel with 12 screwsand washersand
a bracket securingthe back to the mounting panel.
a. Remove air conditioning filter Cover,filter and rear accesspanels.

NOTE
Dischargethe system before disassembling.

b. Uncouple the liquid line from the inlet side of the receiver-dehydrator and the
suction line from the evaporator core outlet. (See Paragraph 14-5, B-7.)
c. Disconnect the related electrical wires.
d. Remove flexible air duct from housing outlet.-Remove drain hose from housing.
e. Remove temperature probe from evaporator housing.
f. Remove the screws attaching the support bracket and evaporator housing to the
mounting panel. Remove the assemblythrough the accesshole in the bulkhead.

14-41. EVAPORATORASSEMBLYINSTALLATION.
a. Cement gasket in place on the flangesof the evaporator housing and attach the large
end of the mounting gasket to the back of the housing.
b. Install the housing through the access hole with the air duct outlet on top. Mate the
mounting flangesto the mating surface of the mounting panel and insert the screws.(Do not
tighten at this time.)
c. Line up the mounting bracket with mating holes in mounting panel, insert screws
and tighten. Tighten screws in the flange at this time. Be certain gasket is in place. The
flange must have an air tight seal.
d. Couple the suction and discharge lines to their respective fittings (apply Loctite
refrigerant sealant to tube flangesonly).
e. Evacuate and charge system. (See Paragraphs 14-13 and 14-14.)
f. Check for leaks (see Paragraph 14-9) if no leaks are detected. Seal and install access
panel on evaporator housing.
h. Couple flexible air duct and drain tube.
i. Make and check electrical connections. (Refer to Figure 14-14.)
j. Check operation of blower and refrigerant systems.
k. Install rear bulkhead panels. Be certain to seal. (See NOTE.)

Reissued: 1/15/81 ACCESSORIESAND UTILITIES

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 PIPER CHEROKEE SERVICE MANUAL

1774
912

WRAP TAPE AROUND THERMOSTAT

CAPILLARY LEAVING SERVICE
PORT ACCESSIBLE.

1. SIGHT GLASS
2 SERVICE VALVE (SCHRADER) (HI)
3. CAPILLARY COIL
4. HOUSING ASS'Y
. SERVICE VALVE (SCHRADER)(LOW)
6. RECEIVER DEHYDRATOR CLAMP
7. RECEIVER DEHYDRATOR
. PRESSURE RELIEF SWITCH (RANCO)
9. EXPANSION VALVE
10. OUTLET HOSE

Figure 14-14. Components Installation

WARNING
Wheneverit is necessaryto remove and replace the cabin rear
panel, it should be replaced and sealed in the original manner
to prevent exhaust gases from entering the cabin. After
removing and replacing the rear panel, conduct a carbon
monoxide test on the ground and in flight with and without
the air conditioner operating. Presence of .CO shall not
exceed one part in 20,000.

14-42. PRESSURE RELIEF SWITCH (Ranco). The pressure relief switch automatically
prevents the system from over pressurization by breaking the electrical circuit to the
magnetic clutch, stopping the compressor until pressure is reduced. The switch is located in
the line between the receiverand expansion valve,and set to cut out at 350 ± 10 psi and cut
in at 250 ± 10 psi.

NOTE

Before the relief switch is removed, the air conditioning

system must be discharged.(See Paragraph 14-12.)

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 PIPER CHEROKEE SERVICE MANUAL

1443. ELECTRICALINSTALLATION.The electrical system, routing and component are

installed and routed in the conventionalaircraft manner. The wiring harness is connected to
switches in the climate control center on the right side of the instrument panel. The
harnesses cross the instrument panel to the left side where two (2) wires are taken off for
the compressor clutch. The harness then passes aft along the left side of the fuselagewhere
it connects to the blower motor, pressure relief switch and the condenser actuating motor.

14-44. ADJUSTMENTOF THROTTLE SWITCH. The throttle switch is mounted forward

and below the throttle arm. The switch must be adjusted so it will actuate at the last quarter
inch of full open throttle travel.
The switch should be positioned so the throttle arm contacts the center of the switch
actuator button.

C366
CR8 ABOVE
CR9 BELOW
1N3659(2)

DIODE BOARD
R2 ASSY.

CONTROL

OTHER DIODES ARE IN 4001 CR7

MR1120 OR
IN 1200 A

Figure 14-15.Control Head - Diode Mounting Board, Diode Location and number Serial
Nos. PA-28-140, 28-7125472 to 28-7325057, PA-28-180, 28-7205092 to 28-7305071,
PA-28R-200, 28R-7235001 to 28R-7335057)

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 PIPER CHEROKEE SERVICE MANUAL

14-45. FUSE REPLACEMENT (Refer to Figure 14-15.) (Serial Nos. PA-28-140,

28-7125472 to 28-7325057, PA-28-180, 28-7205092 to 28-7305071, PA-28R-200,
28R-7235001 to 28R-7335057.) There are two fuses located behind the air conditioning
system control panel. A 25 amp circuit breaker mounted in the circuit breaker panel
protects the complete air conditioning electricalsystem.

14-46. FUSE REPLACEMENT(Serial Nos. PA-28-140, 28-7325058 and up, PA-28-180,

28-7305072 and up, PA-28R-200, 28R-7335058 and up.) There are three fuses located
behind the air conditioning system control panel. A 20 amp circuit breaker mounted in the
circuit breaker panel protects the complete air conditioning electrical system.

NOTE
The Control Head will be replaced when needed with new
parts used in the Air Conditioning Control System
Modification Kit installed in the PA-28-140, Serial Numbers
28-7325058 and up, the PA-28-180, Serial Numbers
28-7305072 and up, and the PA-28R-200, Serial Numbers
28R-7335058 and up.

THIS SPACEINTENTIONALLYLEFT BLANK

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 PIPER CHEROKEE SERVICE MANUAL

A145

I
I
RELAY
EARLY INSTALLATION

RELAY CONDENSERDOOR
K2 MOTORAND RELAYS
(CLOSE) INSTALLATION

PRESENTINSTALLATION

NOTE
SHOWNWITHAC ON,THROTTLENOT FULL
DOOROPEN.THERMO-
OPEN,CONDENSER
STAT CALLINGFOR COOING. FREON
BELOWLIMIT.HIGHBLOWER
PRESSURE
SPEED SELECTED.

Figure 14-16. Air Conditioning Wiring Schematic

PA-28-140 Serial Nos., 28-7125472thru 28-7225131incl.
PA-28-180 Serial Nos., 28-7205092thru 28-7205144incl.

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 PIPER CHEROKEE SERVICE MANUAL

A146

CLOSE

CONTROLHEAD

CONTROL
.

NOTE:
SHOWNWITHAC ON,THROTTLENOTFULL
OPEN,
CONDENSER DOOROPEN,THERMO-
STATCALLINGFOR COOLING, FREON
PRESSUREBELOW LIMIT,HIGHBLOWER
SPEED SELECTED.

Figure 14-17. Air Conditioning Wiring Schematic

PA-28-140 Serial Nos., 28-7225132to 28-7225612
PA-28-180 Serial Nos., 28-7205145to 28-7205328
PA-28R-200 Serial Nos., 28R-7235001to 28R-7235330
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 PIPER CHEROKEE SERVICE MANUAL

1700
NO. COMPONENT LOCATION
F1 Fuse InstrumentPanel
F2 Fuse InstrumentPanel
F3 Fuse InstrumentPanel
K1 Relay(Door Open) Rear of Cabin
K2 Relay(Door Close) Rearof Cabin
K3 Relay(Logic) Intrument Panel
S2 Air Cond.ON-OFFSw. InstrumentPanel
S3 Throttle Sw. Throttle Quadrnt R.
S4 Door Open Limit Sw. TransmissionAssy
S5 PressureSwitch Rearof Cabin
NC S6 Thermostat Intrument Panel
S7 Door Close Umit Sw. TransmissionAssy

LATER

5A F3

5 4

S2 COND.
K2 ON SW.

THERMOSTAT
OPEN
COMPRESSOR 4 3 RELAY 2
CLUTCH

SHOWN CONDITIONING
WITHAIR CONDITIONINGFANSWITCHINOFF POSITION, MOTOR
THROTTLENOT WIDEOPENEN, AIRCONDITIONING
SWITCHIN ON
POSITION,FREONPRESSIUREBELOWLIMIT,THERMOSTATCALL-
ING FORCOOLING,AND CONDENSERDOORCLOSED.

Figure 14-18.Air ConditioningWiringSchematic

PA-28-140Serial Nos., 28-7325001andup
PA-28-180Serial Nos., 28-7305001and up
PA-28R-200Serial Nos., 28-7335001andup

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 PIPER CHEROKEE SERVICE MANUAL

TABLEXIV-IV. TROUBLESHOOTINGCHART(AIR CONDITIONER)

Gauge Indication Probable Causes Remedy

High dischargepressure. Overchargeof Purge excess re-

refrigerant. frigerant.

Air in system. Check for leaks. Bleed

charge from system.
Evacuateand recharge
system 14-13and 14-14.

Overheatedcondenser Cleanbugs and dirt

due to blocking air from condenser fins.
passage. Straighten fins if
bent.

Flooded evaporator Check that capillary

indicated by heavy bulb is securely
frosting on suction clamped to suction
line and compressor line. If capillary
suction servicevalve. bulb OK replace
expansionvalve.

Restriction in liquid Check for kinked hoses

line from condenser. and stopped up filter.

Low dischargepressure. Undercharge of re- Add refrigerant until

frigerant. Sight glass bubbles disappear. Check
shows bubbles or foam. system leaks 14-17,
14-10and 14-11.

Damagedcompressor Replace compressor,

valvesor dirt under 14-18.
valves.
Damagedcompressor. Replace compressor,
Worn or broken piston 14-18.
or piston rings.

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 PIPER CHEROKEE SERVICE MANUAL

TABLEXIV-IV. TROUBLESHOOTINGCHART(AIR CONDITIONER)(cont.)

Gauge Indication Probable Causes Remedy

Low suction pressure. Low air supply through Repair blower or
(Accompaniedby icing evaporator. blower motor. Clean
evaporator.) stoppage in air ducts.
Very dirty evaporator Clean and flush with
fins and coils. water.
Low suction pressure. Underchargeof Add refrigerant.
(Evaporator not cold refrigerant. Moisture Install new dryer.
enough) suction gauge freezing in expansion Evacuate and recharge
may read a vacuum in- valve. Valvewillshow 14-13 and 14-14.
dicating evaporator frost. Expansionvalve
lacks refrigerant inlet screen clogged. Remove screen. Clean
Inoperative expansion Clean with solvent
valve. Valvestuck and replace. Warm
closed or capillary capillaryby holding
bulb has lost its in hand. If suction
charge. pressure does not
charge, replace ex-
pansion valve.

Restriction anywhere Locate restriction

in liquid line. Re- and repair.
striction will show
frost.
High suction pressure. Capillarybulb clamp Clean contact surfaces
loose on suction line. of suction line and
Suction line shows cap bulb. Tighten
frost. clamp.
Expansionvalve not Replace expansion
closing.Evaporator valve.
flooded. Suction line
frosted to compressor.

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 PIPER CHEROKEE SERVICE MANUAL

TABLEXIV-IV. TROUBLESHOOTINGCHART(AIR CONDITIONER)(cont.)

Gauge Indication Probable Causes Remedy

High suction pressure. Compressordrive belt Adjust belt tension,

(cont.) slipping. 14-23.

Magneticclutch Check electrical

slipping circuit for correct
voltage to clutch
coil. Clean clutch
surfaces of oil.

Leaking or broken Replace compressor.

compressorvalves.

Trouble Cause Remedy

Door will not close Faulty relay "K-2." Replace relay.

when air conditioner
switch is in OFF
position.

System produces no Electrical.

cooling.
Blownfuse in Replace fuse.
control head.

Open circuit breaker. Reset circuit breaker.

Broken or disconnected Check all terminals

electrical wire. for loose connections;
check wiring for hidden
breaks.

Broken or disconnected Check ground wire to

ground wire. to see if loose, broken,
or disconnected.

Clutch coil burned out Check current flow to

or disconnected. clutch, replace if
inoperative.

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TABLEXIV-IV. TROUBLESHOOTINGCHART(AIR CONDITIONER)(cont.)

Trouble Cause Remedy

System produces no Electrical. (cont.)

no cooling. (cont.)
Thermostat sensing Check thermostat and
element defective. cabin comfort control
panel.
Blowermotor dis- Checkcurrent flow
connected or burned to blower motor.
out. Repair or replace if
inoperative.
Mechanical
Loose or broken drive Replace drivebelts
belt. and/or tighten to
specifications. 14-22
and 14-23.

Compressorpartially Removecompressor for

or completely frozen. serviceor replacement,
14-18.

Expansionvalvestuck Replace expansion

in open position. valve, 14-35.

Refrigeration

Broken refrigerant Examine all lines for

line. evidenceof breakage
by external stress or
rubbing wear.

Leak in system. Evacuate system, apply

static charge, leak
test system, and repair
leak as necessary,
14-13and 14-9.

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 PIPER CHEROKEE SERVICE MANUAL

TABLEXIV-IV. TROUBLESHOOTINGCHART(AIR CONDITIONER)(cont.)

Trouble Cause Remedy

System produces no Compressorshaft seal Replacecompressor,

cooling. (cont) leaking. 14-18.

Cloggedscreen or Repair as necessary.

screensin receiver
dehydrator or expansion
valve;pluggedhose or
coil.

System will not produce Electrical

sufficient cooling.
Blower motor sluggish Remove blower motor
in operation. for serviceor re-
placement.

Mechanical
Compressorclutch Removeclutch assembly
slipping. for service or replace-
ment, 14-24.

Obstructed blower Examine entire passage

passage. for obstruction. Correct
as necessary.

Insufficient air Cleancondenser coils.

circulation over
condensercoils;
fins clogged with
dirt or bugs.

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 PIPER CHEROKEE SERVICE MANUAL

TABLEXIV-IV. TROUBLESHOOTINGCHART(AIR CONDITIONER)(cont.)

Trouble Cause Remedy

System will not Mechanical
produce sufficient
cooling. (cont.)

Evaporator filter Clean with cleaning

clogged. solvent to remove
cigarette tars.
Refrigeration
Insufficient re- Recharge system until
frigerant in system. bubbles disappearin
receiver dehydrator
and gaugereadings
stabilize to specifi-
cations, 14-14.
Cloggedscreen in Purge system and re-
expansionvalve. place expansion valve,
14-35.
Expansionvalve Purge system; replace
thermal bulb has expansion valve, 14-35.
lost charge.
Cloggedscreen in Purge system; replace
receiver dehydrator. receiver dehydrator,
14-32.
Excessivemoisture Purge system; replace
in system. receiver dehydrator,
14-32.
Air in system. Purge, evacuate and
charge system. 14-13
and 14-14. (Replace
receiver dehydrator,
14-32.)

Reissued: 1/15/81 ACCESSORIESAND UTILITIES

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 PIPER CHEROKEE SERVICE MANUAL

TABLE XIV-IV. TROUBLESHOOTINGCHART(AIR CONDITIONER)(cont.)

Trouble Cause Remedy

Excessivelynoisy Electrical
system
Defectivewinding or Replace or repair
improper connection as necessary, 14-24.
in compressor clutch
coil.
Mechanical
Loose or excessively Tighten or replace as
worn drive belts. required. 14-22 and
14-23.
Noisy clutch. Remove clutch for
serviceor replace-
ment as necessary,
14-24.
Compressornoisy. Check mountings and
repair; remove com-
pressor for service
or replacement, 14-18.
Compressoroil level Fill with correct
low. amount of specified
oil, 14-21.
Refrigeration

Excessivecharge in Dischargeexcess freon

system. until high pressure
gaugedrops within
specifications.
Low charge in system. Check system for
leaks; charge system,
14-9 and 14-14.
Excessivemoisture in Replace dehydrator;
system. purge, evacuate, and
charge system, 14-32,
14-13 and 14-14.

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 PIPER CHEROKEE SERVICE MANUAL

14-47. SHOULDER-HARNESSINERTIA REEL ADJUSTMENT.

a. Allow the harness to wind up on the reel as much as possible.
b. On the end of the reel, pry off the plastic cap over the spring, making sure the spring
does not come out of the plastic cap, and set cap aside.
c. Unwind the harness completely, then measure and mark the harness 24 inches from
the reel center.
d. Wind the harness onto the reel until the 24 inch mark is reached, then hold reel and
place cap with spring over the reel shaft end.
e. Aligningslot in shaft with spring tang, wind spring 6 turns ± 1/2 turn and snap the
plastic cover into holes in reel end shaft.
f. Release harness and allowing it to wind up, extend the harness a few times to check
reel for smooth operation.
g. With reel fully wound, hold with inertia mechanism end up and pry off plastic cap
over mechanismand set reel aside.
h. Install nut in plastic cap so that stud in cap is flush with nut surface, then reposition
cap over reel end and orientating properly, snap in place. Extend harness a few times to
make sure action is correct.

14-48. OVERHEADVENT BLOWER.

1449. DESCRIPTION. The blower is mounted in the aft section of the fuselage and is
connected to the overhead vent system. The blower draws air in from the dorsal fin and
forces it through the ducting, whenever desired. The four position blower switch on the
instrument panel controls the three speed blower.

14-50. REMOVALOF BLOWERASSEMBLY.

a. Remove the accessdoor from the aft wall of the baggagearea.
b. With the master switch off, disconnect the plug assembliesat the blower assembly.
c. Remove the inlet and outlet hoses from the blower assembly by removing the
clamps.
d. Remove the screws, washers and nuts that secure the blower assemblyto the hangar
braces.
e. Remove the screws and washers which secure the blower assembly to the retainer
and hangars.
f. Remove the blower assemblyfrom the aircraft.

14-51. DISASSEMBLYOF BLOWERASSEMBLY.

a. Remove the hose duct from the forward edge of the blower assembly by removing
the nuts, washersand screws.
b. Remove the cover from the blower assembly by removing the nuts, washers and
screws.
c. Remove the blower fan from the motor shaft by removingthe set screw.

Reissued: 1/15/81 ACCESSORIESAND UTILITIES

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d. For removal of the motor, proceed as follows:

1. Separate the plate from the motor cover by carefully drilling out the connecting
rivets.
2. Cut the motor wires at the edge of the receptacle and plug and remove the wire
ends from the blocks.
3. Remove the motor from the mounting plate by removingthe nuts, washersand
bolts.

14-52. REASSEMBLYOF BLOWERASSEMBLY.

a. Mount the motor on the plate and secure it with the bolts, washers and nuts. Be sure
that the motor nuts are snug and the shaft spins freely.
b. Position the coverover the motor plate with the motor wiresprotruding through the
covergrommet.
c. With the holes in the cover matching the holes in the motor plate, secure the two
parts together with rivets.
d. Apply PRC-5000 sealant to fill any openingleft after the wires are brought through
the grommet.
e. Install the wires in the plug and receptacle according to Table XIV-V.
f. Position the blower fin on the motor shaft and secure with set screw.
g. Secure the cover to the blower assemblywith screws,washers and nuts.
h. Position the hose duct on the blower assembly and secure it with screws, washers
and nuts. The screwsmust be installed with their heads inside the duct.
i. After cleaning the surfaces of all old sealant, use white rubber chalk PRC-5000
sealant to seal where the duct attaches to the blower assembly.

14-53. INSTALLATIONOF BLOWERASSEMBLY.

a. Position the blower assemblyin the hangars and retainer and install the washersand
screws.
b. Install the nuts, washers and screws securing the blower assembly to the hangar
braces.
c. Seal all hose joints with Arno No. C-520 grap tape; then install the inlet and outlet
hoses securingthem with the clamps.
d. With the master switch off, connect the plug and receptacles at the blower.
e. Check the blower for the proper operation.
f. Install the access door to the aft wall of the baggage area and secure with the
attaching hardware.

Reissued: 1/15/81 ACCESSORIES AND UTILITIES

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TABLEXIV-V. BLOWERSYSTEMWIRE COLORCODES

MOTOR WIRES AIRCRAFT

WIRES

15920-01 E362Q F0018075FA

Pin. General Singer Leece- Aircraft Pin
Nos. Industries Controls Neville Harness Nos.

.2
Ground I0 2 Brown Brown Black AC26A 2 .
0. I 0
Low Speed 1 Red Yellow Yellow Black 1 o

Medium Speed g 2 Black Red Red White 2

High Speed 8 I YellowN · Orange Orange Red 1 _

C2

NOTE
Pin number 1 is at the pointed side of the plug and receptacle.
Wire color codes for YY75062 ESB-Universal Electric
Company are same as E 362QSinger Control color code listed
above.

Reissued: 1/15/81 ACCESSORIES AND UTILITIES

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