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Cessna 500 Series CMM

The Model 500 Series Component Maintenance Manual (Rev 17) provides essential maintenance instructions and updates for Cessna Model 500 series airplanes, including a list of revisions dating back to the original issue in 1989. It emphasizes the importance of using current data for maintenance and outlines procedures for continued airworthiness, customer assistance, and the use of supplemental instructions. Additionally, it includes details on the structure of the manual, page numbering, and the identification of revisions and warnings.

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100% found this document useful (2 votes)

821 views535 pages

Cessna 500 Series CMM

Uploaded by

Emi Castelli

We take content rights seriously. If you suspect this is your content, claim it here.

Available Formats

Download as PDF, TXT or read online on Scribd

You are on page 1/ 535

Model 500 Series Component Maintenance Manual (Rev 17)

-0 (Rev 17)

LIST OF REVISIONS
1. General
A. This Model 500 Series Component Maintenance Manual includes the original issue and the following listed revisions. To
ensure that information in this manual is current and the latest maintenance and inspections procedures are available,
revisions must be incorporated in the manual as they are issued.
Table 1. Original Issue - 1 September 1989
Revision Number Date Revision Number Date
1 1 March 1990 2 3 December 1990
3 2 August 1993 4 1 August 1994
5 1 June 1995 6 1 September 1995
7 1 October 1996 8 1 August 1997
9 5 June 2000 10 1 November 2001
11 4 February 2002 12 3 May 2004
13 1 August 2007 14 1 August 2013
15 1 August 2014 16 1 February 2016
17 1 March 2017
2. Export Compliance
A. This publication contains technical data and is subject to U.S. export regulations. This information has been exported from
the United States in accordance with export administration regulations. Diversion contrary to U.S. law is prohibited.
ECCN: 9E991

Copyright © Textron Aviation Inc. Page 1 of 1

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 12:34:12 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
-0 (Rev 16)

INTRODUCTION
1. General
A. The Instructions for Continued Airworthiness (ICA) in this publication uses the data available at the time of publication. This
publication is updated, supplemented, and changed by service letters, service bulletins, publication revisions, reissues,
ICA supplements, and temporary revisions, which are supplied by subscription services available from Cessna Customer
Service. All of these changes become part of and are specifically included in this publication which is the principal manual
for ICA. The latest changes to this publication are given through the Cessna Customer Service subscription services
and/or Citation Service Centers and Citation Service Stations.
B. The ICAs in this manual have been written for Cessna approved parts. If non-Cessna approved parts are installed, refer to
the manufacturers and/or seller's publications for inspection intervals, replacement time limits, methods of inspections, life
limits, etc.
C. Inspection, maintenance and parts requirements for Supplemental Type Certificate (STC) installations are not given in this
manual. When the airplane has an STC installation, those parts of the airplane that the installation has an effect on, must
be examined in accordance with the inspection program published by the owner of the STC. Cessna-supplied inspection
criteria may not be valid for airplanes that have STC installations because these installations may change the systems
interface, operating characteristics, and component loads or stresses on adjacent structures.
2. How to Get Customer Assistance
A. Customer Service
CESSNA CUSTOMER SERVICE

Mailing Address One Citation Lane

Wichita, KS 67209
(1) If you need assistance with a general support question, publication information, subscriptions, or maintenance
programs visit our website at CessnaSupport.com or contact:
CESSNA CUSTOMER SERVICE
316-517-5800
Phone Numbers
1-800-4Cessna option 2 (1-800-423-7762)
Fax 316-517-5802
Email Address Customercare@txtav.com
3. Scope
A. This manual provides component maintenance instructions and illustrated parts list for repairable components
manufactured by Cessna Aircraft Company for the related Cessna Maintenance Manuals:
Maintenance Manual Part Number
Model 500 C500MM
Model 550 C55MM
Model S550 CS55MM
Model 550 Bravo C55BMM
Model 560 C56MM
4. Coverage
A. This Maintenance Manual is prepared with information given by the ATA (Air Transport Association) Specification Number
2200 for Manufacturer's Technical Data.
B. The information in this maintenance manual is applicable to US and foreign-certified Cessna Model 500 series airplanes.
Information unique to a particular country is identified in the affected chapter(s).
C. This manual gives the necessary information to help maintenance personnel service, examine, troubleshoot, remove, and
replace components, or repair systems on the Model 500 series airplanes.
D. Additional information not given in this manual can be found in the Cessna Aircraft Company Model 500 series Wiring

Copyright © Textron Aviation Inc. Page 1 of 4

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 12:34:13 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
-0 (Rev 16)

Diagram Manual, Illustrated Parts Catalog, Structural Repair Manual, Maintenance Manual, Nondestructive Testing
Manual, and Illustrated Tools and Equipment Manual. For technical aid applicable to this manual, contact Cessna Aircraft
Company, Citation Marketing Division.
E. Use the technical publications available from manufacturers of the different airplane components and systems, which are
not covered in this manual, as necessary for maintenance of those components and systems.
5. Instructions for Continued Airworthiness (ICA)
A. Maintenance Manual
(1) The instructions provided in this manual are the principal instructions for continued airworthiness. This manual may be
revised to add changes to the ICAs or to add additional ICAs when changes to the airplane type design require
changes to these instructions. When a revision to this manual is not possible within the time constraints for these
ICAs, the instructions may be transmitted with a temporary revision or with an ICA supplement. Temporary revisions
will be incorporated in the next revision to this manual and ICA supplements will also be incorporated in the next
revision unless these instructions require restricted distribution.
B. Temporary Revisions
(1) Temporary revisions may be produced to transmit supplemental instructions for continued airworthiness when a
revision to the maintenance manual is not possible within the time constraints for these ICAs. They consist of
complete page blocks which replace the existing paper and will temporally supersede the electronic data. Temporary
revisions will be included on the next electronic release cycle. Temporary revisions are numbered consecutively in the
ATA chapter assignment. Page numbering uses the three-element number, which matches the maintenance manual.
(2) Paper Version of the Maintenance Manual
(a) Paper temporary revisions will be distributed on yellow paper. File the temporary revision cover sheet after the
title page of the chapter to which it applies and substitute or add the remaining pages in the paper manual.
(3) Electronic Version of the Maintenance Manual
(a) The cover sheet will be located in the maintenance manual electronic library at the beginning of the chapter to
which it applies and the changed or added page blocks will be located in the appropriate location by ATA. All
revised or added information will have a teal background.
C. ICA Supplements
(1) ICA supplements may be produced to transmit supplemental instructions for continued airworthiness when a revision
to the maintenance manual is not possible within the time constraints for these ICAs. ICA supplements will provide
supplemental instructions for one or more ICA manual and is to be used in conjunction with the affected manuals
(maintenance manual, wiring diagram manual, etc.) until those instructions are incorporated into the manuals. ICA
supplements are numbered consecutively by model in the ATA chapter assignment. Page numbering uses the three-
element number, which matches the affected manuals.
(2) Refer to the ICA Supplement List to determine the incorporation status for each manual affected.
6. Electronic Media
A. Model 500 series publications are available in paper and as electronic media. The paper publications are available as
individual publications such as the Maintenance Manual, Parts Catalog, etc. The electronic media service publications are
available in a DVD, download, online and mobile application library that contain multiple books together. These
publications are kept up to date through routine revisions.
7. Using the Component Maintenance Manual
A. Division of Subject Matter.
(1) Component maintenance information is divided into two chapters: Flight Controls and Landing Gear. Each chapter is
subdivided according to repairable components. Each repairable component is an end item not dependent upon a
system or airplane.
B. List of Effective Pages (Paper Version of this Manual Only).
(1) A list of effective pages is provided with each chapter. All pages listed are active and shall appear in sequence as
recorded in the List of Effective Pages.
(2) The List of Effective Pages contains tabular listing of Air Transport Association number, page and date of each page
in that chapter. A change in the chapter requires a revision to the chapter’s List of Effective Pages. The date
corresponds to the date that appears on the individual page which defines when that page was issued.

Copyright © Textron Aviation Inc. Page 2 of 4

C. Page Numbering System.

(1) The Component Maintenance Manual page numbering system consists of the Air Transport Association
Specification 2200 three-element numbers, separated by dashes, beside which the page number and date are
printed. The three-element number is assigned to a component, with the first set of numbers corresponding to Air
Transport Association Specification 2200 assigned chapter number.
(2) The page number beside the three-element number complies with Air Transport Association Specification 2200 for
subdividing a Component Maintenance Manual. Blocks of sequential page numbers are used to identify:
Pages 1 through 99 - Description and Operation
Pages 101 through 199 - Testing and Troubleshooting
Pages 301 through 399 - Disassembly
Pages 401 through 499 - Cleaning
Pages 501 through 599 - Check
Pages 601 through 699 - Repair
Pages 701 through 799 - Assembly (Including Storage)
Pages 801 through 899 - Fits and Clearances
Pages 901 through 999 - Special Tools, Fixtures and Equipment
Pages 1001 through 1099 - Illustrated Parts List
(3) The date which appears below the page number signifies when the page was issued. If no revisions to that page
have occurred, the date signifies original date.
(4) Illustrations use the same figure numbering as the page block in which they appear. For example: Figure 602 would
be the second figure in a repair section.
8. Revision Filing Instructions (Paper Version of this Manual Only)
A. Regular Revision.
(1) Pages to be removed or inserted in the Component Maintenance Manual are controlled by the List of Effective
Pages. Pages are listed in sequence by the three-element number and then by page number. When two pages
display the same three-element number and page number, the page displaying the most recent Date of Page Issue
shall be inserted into the Component Maintenance Manual. The date column on the corresponding chapter List of
Effective Pages shall verify the active page.
B. Temporary Revision.
(1) Temporary revision pages are filed in the Component Maintenance Manual by replacing existing pages in the
manual. File the temporary revision cover page according to the filing instructions on the Temporary Revision Cover
Page.
C. Revision Bars.
(1) Additions or revisions to existing text will be identified by a revision bar in the left margin adjacent to the change.
(2) When extensive technical changes are made to the text involving deletion, addition, revising or relocating information,
a revision bar may appear the full length of the text.
9. Identifying Revised Material
A. Paper Manual
(1) Additions or revisions to text in a section will be identified by a revision bar adjacent to the change in the left margin
of the page. The current revision date for that section will show in the lower right corner of the section, below the page
number.
(2) When large technical changes are made to text in a section, a revision bar will be shown the full length of the text.
B. Electronic Manual
(1) Additions or revisions to text in a section will have a teal background to show the revised text. The current revision
number for the manual will show in parenthesis in the upper right corner of the page adjacent to the title of the manual.
The revision number for that section will show in parenthesis in the upper left corner of the page adjacent to the
chapter-section-subject.

Copyright © Textron Aviation Inc. Page 3 of 4

(2) When large technical changes are made to text in a section, the teal background will show the full length of the text.
10. Dimensions and Units
A. Dimensions and Units.
(1) All dimensions and units are given in both English and metric (International Standard [SI]) units in the text and the
illustrations. The English value is given and then the metric unit is given in parenthesis.
(2) Metric units are given in standard abbreviations.
(3) Station lines and locations are not given in metric units
11. Abbreviation
A. Abbreviations are not often given in this manual; however, abbreviated identification for switches, circuit breakers and
annunciator panel legends are shown as they are seen on the placards or electroluminescent panels.
12. Warnings, Cautions and Notes
A. Warnings, cautions and notes, related to the procedures being done, are used. Each gives important information.
(1) WARNING - Tells maintenance personnel how to use the materials, processes, methods, procedures or limits, which
must be followed accurately to prevent injury or death to persons.
(2) CAUTION - Tells maintenance personnel how to use the materials, processes, methods, procedures or limits, which
must be followed accurately to prevent damage to equipment.
(3) NOTE - Tells maintenance personnel how to use methods, which will make the work easier.

Copyright © Textron Aviation Inc. Page 4 of 4

ICA SUPPLEMENT LIST

1. Applicability
A. This section contains the list of released ICA Supplements that affect the Model 500 Series Component Maintenance
Manual at the time the latest revision was released. For a complete list of ICA Supplements, refer to the applicable
Maintenance Manual, Introduction, ICA Supplement List.
ICA Supplement Title ICA Supplement Manual
Number Date Incorporation
Date
ICA-560-23-00009 Rev 560 Encore+ Gravel Runway Option ICA Supplement Sep 10, 2010 Incorporation
B Pending

Copyright © Textron Aviation Inc. Page 1 of 1

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 12:34:15 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
-0 (Rev 13)

SUPPLIER ADDRESS LIST

00779 TYCO ELECTRONICS CORP. 13778 PACIFIC SINTERED CO.
2800 Fulling Mill 14000 Avalon Blvd.
M/X 38-77 Los Angeles, CA 90061-2636
Middletown, PA 17057
02697 PARKER-HANNIFIN CORP. 13899 HYDRO FITTING MFG. CORP.
O-RING DIV. - SEAL GROUP 733 E. Edna Pl.
2360 Palumbo Dr. P.O. Box 1558
P.O. Box 11751 Covina, CA 91722-3246
Lexington, KY 40509
03508 GENERAL ELECTRIC CO. SEMI-CONDUCTOR 14412 AMERICAN PRECISION INDUSTRIES INC.
PRODUCTS DEPT. 2777 Walden Ave.
West Genessee St. Buffalo, NY
Auburn, NY
04713 MOTOROLA, INC. SEMICONDUCTOR PROD 15860 NEW HAMPSHIRE BALL BEARING, INC. ASTRO
SECTOR DIV.
SERVICE AND LOGISTICS 155 Lexington Ave.
2100 E. Elliott Rd. Laconia, NH 03426
Tempe, AZ 85284
07060 CONOVER C.E. & CO. INC. 24444 GENERAL SEMICONDUCTOR INDUSTRIES, INC.
DIV. OF CONOVER INDUSTRIES SUBDIVISION OF SQUARE D CO.
333 Passaic Ave. 2001 W. 10th Pl.
Fairfield, NJ 07006 Tempe, AZ 85281
07688 JOINT ELECTRON DEVICE ENGINEERING 27745 BARNES GROUP, INC.
CO.UNCIL 1225 State Fair Blvd.
2500 Wilson Blvd., Suite 220 Syracuse, NY 13209-1011
Arlington, VA 22201-3834
09257 SHAMBAN W S AND CO. 30781 PARKER-HANNIFAN CORP.
SEALS DIV. PACKING DIV.
2531 Bremer Dr. 2270 S. 3600 W.
P.O. Box 176 P.O. Box 30505
Fort Wayne, IN Salt Lake City, UT
11139 THE DEUTSCH CO. 37942 NORTH AMERICAN CAPACITOR CO.
ENGINEERED CONNECTING DEVICES MALLORY DIV.
36033 Whittier Ave. Indianapolis Rd. Hwy. 240
Hemet, CA 92545 P.O. Box 273
Indianapolis, IN 46135
13103 THERMALLOY CO., INC. 39428 MCMASTER-CARR SUPPLY CO.
2021 W. Valley View Ln. 600 County Line Rd.
P.O. Box 810839 Elmhurst, IL
Dallas, TX
57606 PSI BEARING 86887 SIGMA TEK, INC.
2175 Union Place 1001 Industrial Rd.
Simi Valley, CA 93065 Augusta, KS 67010
59023 O'KEEFE CONTROLS CO. 91637 DALE ELECTRONICS, INC.
4 Maple Dr. 1122 23rd St.
Monroe, CT 06468 P.O. Box 609
Columbus, NE 68601-3632

Copyright © Textron Aviation Inc. Page 1 of 2

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 12:34:16 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
-0 (Rev 13)

5F573 GREENE TWEED & CO. 91929 HONEYWELL, INC.

Detwiler Rd. MICRO SWITCH DIV.
P.O. Box 305 11 W. Spring St.
Kulpsville, PA 19443-0305 Freeport, IL 61032
60380 TIMKEN U.S. CORP. 92555 THE LEE CO.
NEEDLE BEARINGS DIV. 2 Pettipaug Rd.
336 Mechanic St. P.O. Box 424
Lebanon, NH 03766-0267 Westbrook, CT 06498
70628 VESPER CORP. ARROWHEAD PRODUCTS DIV.
4411 Katella Ave.
Los Alamitos, CA 90720
71286 ALCOA GLOBAL FASTENERS, INC. CAMLOC
PRODUCTS DIV.
DBA ALCOA FASTENING SYSTEMS
3014 West Lomita Blvd.
Torrance, CA 90505
72800 EATON CORP.
ENGINEERED FASTENERS DIV.
204 Fourth St. N. W.
Massillon, OH
80205 NATIONAL AEROSPACE STANDARDS
COMMITTEE AEROSPACE INDUSTRIES
ASSOCIATION OF AMERICA INC.
1250 Eye St. NW.
Washington DC
80756 SPIROLOX
DIV. OF KAYDON CORP.
29 Cassens Ct.
Fenton, MO 63026-2542
84971 TA MFG., INC.
SUBDIVISION OF ESTERLINE
28065 W. Franklin Pkwy.
Santa Clarita, CA 91380-9031

Copyright © Textron Aviation Inc. Page 2 of 2

THRUST REVERSER JUNCTION BOX - ILLUSTRATED PARTS LIST

1. Illustrated Parts List
A. Introduction
(1) The Illustrated Parts List has been prepared to assist customer personnel in requisitioning, storing, and issuing the
thrust reverser junction box components and in identifying new and reclaimed parts. It is not approved for any other
purpose.
(2) This parts list covers the thrust reverser junction boxes used on the Models 500, 550, S550 and 560 airplanes. These
part numbers are covered:
5538328-1 5538328-8 5538328-16 5538328-22
(3) The indention system used in the detailed parts list of this catalog shows the relationship of one part to another. For a
given item, the indention code shows a system, installation or general heading starting at the extreme left position
continuing on down into succeeding columns until the end detail is reached. Example:
A18017
1234567
Installation
Detail Parts for Installation
Assembly
Attaching Parts for Assembly
Detail Parts for Assembly
Subassembly
Attaching Parts for Subassembly
Detail Parts for Subassembly
Sub−Subassembly
Attaching Parts for Sub−Subassembly
Detail Parts for Sub−Subassembly

(4) The quantities given in the UNITS PER ASSY column of the parts list are, in the case of assemblies, the total used at
the indicated location. For component parts indented under the assemblies, the quantity is those used in the
assembly. The quantities specified, therefore, are not necessarily the total used per installation.
(5) Effectivity for detail parts of assemblies covered by this technical manual are listed in the Effect column. The code,
A,B,C etc. listed for the assembly is the code for the detail parts peculiar to that assembly. If no code appears in the
Effect column, that detail part is used in all assemblies listed.
(6) When a part of later design is not interchangeable with the part it replaces, both parts applicable to the particular
usage are listed. The individual part usage is listed in the Effect column. Care should be exercised in determining
proper usage when ordering to ensure receipt of the correct part.
(7) When a part of later design is completely interchangeable with the part it replaces, both parts will be serialized and
the notation FSO (for spares order) will be entered following the listing of the earlier design part. FSO means that the
earlier design part is not available and the later design part must be used.
(8) The basic number identifies the Cessna drawing only. Each installation, assembly or detail part is assigned a part
number which consists of the drawing number and an appropriate dash number. Example:
A12537
EXAMPLE:
Part Number
6707005 − 7

Basic Number Dash Number

(Drawing Identification
Only)

NOTE: Parts stamped with a dash 400 series are for internal control purposes only and should not be
used by the operator for ordering/identifying purposes.
B. For Vendor names and addresses with Federal Supply Codes, refer to Introduction - Supplier Address List.

Copyright © Textron Aviation Inc. Page 1 of 1

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Model 500 Series Component Maintenance Manual (Rev 17)
24-50-01-0 (Rev 17)

THRUST REVERSER JUNCTION BOX - DESCRIPTION AND OPERATION

1. General
A. Accomplishment of the procedures in this manual on a thrust reverser junction box will constitute an overhaul as defined in
Federal Aviation Regulations Part 43.2.
B. For a list of steps required to accomplish an overhaul, assuming that the thrust reverser junction box is faulty, refer to Thrust
Reverser Junction Box - Check.
2. Description
A. The thrust reverser junction box incorporates electrical components to provide electrical logic control for the operation of
the thrust reversers. The logic control consists primarily of steering diodes and transistors to control solenoid valves. The
solenoid valves control hydraulic power to the thrust reversers. Refer to Figure 1, Figure 2, and Figure 3.
B. These thrust reverser junction box part numbers are affected by this individual Component Maintenance Manual:
5538328-1 5538328-8 5538328-16 5538328-22

Copyright © Textron Aviation Inc. Page 1 of 6

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Model 500 Series Component Maintenance Manual (Rev 17)
24-50-01-0 (Rev 17)

Figure 1 : Sheet 1 : Printed Circuit Board Components Identification

Copyright © Textron Aviation Inc. Page 2 of 6

Figure 2 : Sheet 1 : 5538328-1 Thrust Reverser Junction Box Wiring Diagram

Copyright © Textron Aviation Inc. Page 3 of 6

Figure 2 : Sheet 2 : 5538328-1 Thrust Reverser Junction Box Wiring Diagram

Copyright © Textron Aviation Inc. Page 4 of 6

Figure 3 : Sheet 1 : 5538328-8, -16 and -22 Thrust Reverser Junction Box Wiring Diagram

Copyright © Textron Aviation Inc. Page 5 of 6

Figure 3 : Sheet 2 : 5538328-8, -16 and -22 Thrust Reverser Junction Box Wiring Diagram

Copyright © Textron Aviation Inc. Page 6 of 6

THRUST REVERSER JUNCTION BOX - TESTING

1. Check Junction Box
A. Before performing this functional test, verify that pins L and N of connector J203 and pin L of connector J204 are correctly
wired, as indicated on the appropriate electrical wiring diagram. If the pins are not properly wired, correct before
proceeding with the functional test. Refer to Figure 602 for wires and jumpers, which must be checked and installed, if not
already installed.
B. Functional Test.
(1) Connect a 6587000-1 thrust reverser junction box tester to the junction box to be tested.
NOTE: Instructions for fabrication of 6587000-1 thrust reverser junction box tester are included in this
section.
NOTE: This test may be performed with the junction box installed in the airplane or may be performed
as a bench test. The sequence of steps is designed to simulate the operating sequence in a
functioning thrust reverser system.
(2) Set switches on the tester:
S1, S2 NORMAL
S3, S4 STOW
S5, S6 STOWED
S7, S8 AIR
S9, S10 STOWED/IN TRANSIT
S11 OFF
NOTE: The steps within this test must be performed sequentially. The test box switches must be reset
only as instructed during the functional test steps.
(3) Connect a source of 28.5 VDC, +0.5 or -0.5 VDC to the tester.
(4) Set switch S11 to LAMP TEST.
(a) Verify that all indicator lights on tester are illuminated.
(5) Set S11 to OFF.
(a) Verify that all indicator lights on tester are extinguished.
NOTE: Steps (6) through (10) check the left deploy circuit.
(6) Set switch S7 to GND.
(a) Verify that light L11 DEPLOY GND is illuminated.
(b) Verify that lights L13 M.W. GND and L14 M.W. GND are illuminated. (L13 and L14 should never be illuminated
when testing a 5538328-1 junction box.)
NOTE: If L11 is not illuminated, check for open diode D183 or D191 or faulty transistor Q12. If L13
and L14 are not illuminated (-8, -16 junction boxes only), check for open diode D191 or
D469.
(7) Set switch S3 to DEPLOY.
(a) Verify that lights L3 DEPLOY, L5 ISOLATION VALVE, L7 CENTER VALVE 1, L9 CENTER VALVE 3, L10
CENTER VALVE 2, L11 DEPLOY GND, L13 M.W. GND and L14 M.W. GND are illuminated.
NOTE: If L3 is not illuminated, the jumper between pins F and T of connector J203 is open. If L5 is
not illuminated, diode D169 is open. If L7, L9 and L10 are not illuminated, check for open
diode D169 or D178. If L7 and L9 are illuminated but L10 is not, check for open jumper
between diodes D178 and D180.
(8) Set switch S3 to STOW and switch S5 to DEPLOYED/IN TRANSIT.
(a) Verify that light L3 extinguishes and that light L1 STOW illuminates. All other lights remain as in step (7).
NOTE: If L1 is not illuminated, diode D167 is open. If L1 is illuminated but L5 is not illuminated,
diode D171 is open.

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Model 500 Series Component Maintenance Manual (Rev 17)
24-50-01-1 (Rev 5)

(9) Connect a 3 1/2 digit voltmeter to TP3(+) and TP1(-).

(10) Set switch S9 to DEPLOYED position and switch S3 to DEPLOY.
(a) Verify that light L1 extinguishes and light L3 illuminates.
(b) Verify that voltmeter momentarily reads 22.5 VDC, +1.5 or -1.5 VDC and then gradually drops to 6.8 volts within
one minute.
NOTE: If initial voltage is low or not present, check resistor R77, diode D229, capacitor C25 for
open or transistors Q5 or Q6 may be faulty.
NOTE: If voltage does not drop, verify the electrical integrity of transistor Q5.
NOTE: Step (11) checks the left emergency stow circuit.
(11) Set switch S1 to EMER STOW, switch S3 to STOW, switch S5 to STOWED and switch S9 to STOWED/IN
TRANSIT.
(a) Verify that light L1 illuminates and light L3 extinguishes.
NOTE: If L5 is not illuminated, diode D171 is open. If L5, L7, L9 and L10 are not illuminated, diode
D171 and D179 are open. Also check diode D178 for open.
(b) Verify that voltage across TP3(+) and TP1(-) is O VDC.
(12) Set switch S1 to NORMAL and switch S7 to AIR.
(a) Verify that all test box lights extinguish.
NOTE: Steps (13) through (17) check the right deploy circuit.
(13) Set switch S8 to GND.
(a) Verify that light L12 DEPLOY GND is illuminated.
(b) Verify that lights L13 M.W. GND and L14 M.W. GND are illuminated. (L13 and L14 should never be illuminated
when testing a 5538328-1 junction box.)
NOTE: If L12 is not illuminated, check for open diode D182 or D190 or faulty transistor Q11. If L13
and L14 are not illuminated (-8, -16 junction boxes only), check for open diode D190 or
D469.
(14) Set switch S4 to DEPLOY.
(a) Verify that lights L4 DEPLOY, L6 ISOLATION VALVE, L7 CENTER VALVE 1, L9 CENTER VALVE 3, L10
CENTER VALVE 2, L12 DEPLOY GND, L13 M.W. GND and L14 M.W. GND are illuminated.
NOTE: If L4 is not illuminated, the jumper between pins F and T of connector J204 is open. If L6 is
not illuminated, diode D170 is open. If L7, L9 and L10 are not illuminated, check for open
diode D170 or D180. If L10 is illuminated but L7 and L9 are not, check for open jumper
between diodes D178 and D180.
(15) Set switch S4 to STOW and switch S6 to IN TRANSIT/DEPLOYED.
(a) Verify that light L4 extinguishes and that light L2 STOW illuminates. All other lights remain as in step (14).
NOTE: If L2 is not illuminated, diode D168 is open. If L2 is illuminated but L6 is not illuminated,
diode D172 is open.
(16) Connect a 3 1/2 digit voltmeter to TP4(+) and TP2(-).
(17) Set switch S10 to DEPLOYED position and switch S3 to DEPLOY.
(a) Verify that light L2 extinguishes and light L4 illuminates.
(b) Verify that voltmeter reads 22.5 VDC, +1.5 or -1.5 VDC, and then gradually drops to 6.8 volts within one minute.
NOTE: If initial voltage is low or not present, check resistor R76, diode D230 or capacitor C26 for
open, or transistors Q7 or Q8 may be faulty.
NOTE: If voltage does not drop, verify the electrical integrity of transistor Q7.
NOTE: Step 18 checks the right emergency stow circuit.
(18) Set switch S2 to EMER STOW, switch S4 to STOW, switch S6 to STOWED and switch S10 to STOWED/IN
TRANSIT.
(a) Verify that light L2 illuminates and light L4 extinguishes.

Copyright © Textron Aviation Inc. Page 2 of 11

NOTE: If L6 is not illuminated, diode D172 is open. If L6, L7, L9 and L10 are not illuminated, diode
D172 and D180 are open. Also check diode D181 for open.
(b) Verify that voltage across TP4(+) and TP2(-) is O VDC.
(19) Set switch S2 to NORMAL and switch S8 to AIR.
(a) Verify that all test box lights extinguish.
(20) Remove external power from thrust reverser junction box tester.
(21) Disconnect thrust reverser junction box tester from thrust reverser junction box.
(22) Check the isolation diodes on the thrust reverser printed circuit board for open by connecting the positive lead of a
voltmeter to pin R of either P203 or P204 and successively applying the negative voltmeter terminal to the pins listed
in Table 101.
Table 101. Checking Isolation Diodes
P203 pin N diode D177
P203 pin E diode D173
P203 pin F diode D165
P203 pin D diode D163
P204 pin F diode D166 (NOTE)
P204 pin E diode D174 (NOTE)
P204 pin D diode D164 (NOTE)
NOTE: Varister on 5538328-8, 5538378-16 may be Varister on 5538328-1.
(23) After completion of and passing of the functional test, attach a tag to the thrust reverser junction box indicating that the
box conforms to the requirements of the Components Maintenance Manual.
C. Fabrication of 6587000-1 Thrust Reverser Junction Box Tester. Refer to Figure 101.
(1) Using the drawings and parts list provided, fabricate a thrust reverser junction box tester.
(2) Parts List for the 6587000-1 Thrust Reverser Junction Box Tester.
TERMINOLOGY PART NUMBER QUANTITY FEDERAL SUPPLY
REQUIRED CODE
Binding Post 1464-102 1 83330
Binding Post 1464-103 3 83330
Binding Post 1464-107 2 83330
Resistor F204 or 2 44655
VPR-20-14-10 or 12697
HL-20-10 91637
Light 922-404X-410RT or 13 75915
5131-038-304 71744
RED or 162-971 72619
Box AC-406BPA 112611 71218
Plate 15931N4006 71218
Diode MST-205N or 95146
Switch 7201-S-Y-Z-Q or 09353
JMT-223 15605
Terminal Board 15299 2 91833
Connector MS3126F14-19SY 1 11139
Connector MS3126F14- 19SN 1 11139
Strain Relief SL13 1 8U767

Copyright © Textron Aviation Inc. Page 3 of 11

Backshell GTR00V14B 2 06324

Wire 20 Gage MIL-W-81044/12-20-9 200 Feet
Screw MS35206-327 12
Screw MS35206-217 4
Spacer NAS43DD1-8 12
Nut MS21042-04 4
Nut MS21042-06 12
D. Manufacturer’s Federal Supply Codes and addresses for fabrication of Thrust Reverser Junction Box Tester.
06323 GLENAIR 72619 AMPEREX ELECTRIC CORP.
1211 Air Way 203 Harrison Pl.
Glendale, CA 91201 Brooklyn, NY
09353 C & K COMPONENTS, INC. 75915 TRACOR LITTELFUSE INC.
15 Riverdale Ave. 800 E. NW Highway
Newton, MA 02158 Des Plaines, IL 60016
11139 DEUTSCH CO. 83330 KULKA SMITH INC.
700 S. Hathaway 1913 Atlantic Ave.
Municipal Airport Manasquan, NJ 08736
Banning, CA 92220
12697 CLAROSTAT MANUFACTURING CO. 91637 DALE ELECTRONICS INC.
Lower Washington Street P.O. Box 609
Dover, NH 03820 Columbus, NE 68601
15605 EATON CORP. 91833 KEYSTONE ELECTRONICS CORP.
4201 N. 27th St. 49 Bleecker St.
Milwaukee, WI 53216 New York, NY 10012
44655 OHMITE MANUFACTURING CO. 95146 ALCO ELECTRIC PRODUCTS, INC.
3601 W. Howard St. 1551 Osgood St.
Skokee, IL 60076 North Andover, MA 01845
71218 BUD INDUSTRIES, INC. 8U767 OLFLEX WIRE AND CABLE, INC.
4605 E. 355th St. 30 Plymouth Street
Willoughby, OH 44094 Fairfield, NJ 07006
71744 GENERAL INSTRUMENT CORP. LAMP
DIV.
4433 N. Ravenswood Ave.
Chicago, IL 60640

Copyright © Textron Aviation Inc. Page 4 of 11

Figure 101 : Sheet 1 : Fabrication of Thrust Reverser Junction Box Tester

Copyright © Textron Aviation Inc. Page 5 of 11

Figure 101 : Sheet 2 : Fabrication of Thrust Reverser Junction Box Tester

Copyright © Textron Aviation Inc. Page 6 of 11

Figure 101 : Sheet 3 : Fabrication of Thrust Reverser Junction Box Tester

Copyright © Textron Aviation Inc. Page 7 of 11

Figure 101 : Sheet 4 : Fabrication of Thrust Reverser Junction Box Tester

Copyright © Textron Aviation Inc. Page 8 of 11

Figure 101 : Sheet 5 : Fabrication of Thrust Reverser Junction Box Tester

Copyright © Textron Aviation Inc. Page 9 of 11

Figure 101 : Sheet 6 : Fabrication of Thrust Reverser Junction Box Tester

Copyright © Textron Aviation Inc. Page 10 of 11

Figure 601 : Sheet 1 : Thrust Reverser Junction Box Printed Circuit Board Components Immobilization

Copyright © Textron Aviation Inc. Page 11 of 11

THRUST REVERSER JUNCTION BOX - DISASSEMBLY

1. Disassembly
A. Disassemble Thrust Reverser Junction Box (Refer to Illustrated Parts List).
(1) Remove six screws (17) and spacers (18) securing diode plates (16) leaving diodes installed in diode plates.
(2) Remove four screws (21) securing resistors (75C).
(3) Remove four screws (12) (13), spacers (15) and nuts (14) securing printed circuit board (77) to junction box.
(4) Remove eight screws (19) and nuts (20) securing electrical connectors (26) and (28) to junction box.
(5) Disconnect soldered connectors in accordance with the Wiring Diagram Manual, Chapter 20, Soldering -
Maintenance Practices.

Copyright © Textron Aviation Inc. Page 1 of 1

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 12:35:25 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
24-50-01-5 (Rev 5)

THRUST REVERSER JUNCTION BOX - CHECK

1. Check
A. The following should be accomplished in the order printed to determine which portions of the procedures presented in the
manual must be performed to restore or overhaul a thrust reverser junction box.
(1) Remove the cover and examine the interior components for broken capacitor, diodes or varistor leads, signs of
overheating of resistors, broken or disconnected electrical leads.
(2) Perform a functional test of the box. Refer to Thrust Reverser Junction Box - Testing.
(3) Disassemble as required to repair faulty components. Refer to Thrust Reverser Junction Box - Disassembly and
Thrust Reverser Junction Box - Repair.
(4) Assemble box. Refer to Thrust Reverser Junction Box -Assembly.
(5) Perform a functional test of the box to verify proper functioning. Refer to Thrust Reverser Junction Box - Testing.

Copyright © Textron Aviation Inc. Page 1 of 1

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Model 500 Series Component Maintenance Manual (Rev 17)
24-50-01-6 (Rev 5)

THRUST REVERSER JUNCTION BOX - REPAIR

1. Repair
A. Repair Thrust Reverser Junction Box (Refer to Figure 601 and Illustrated Parts List).
(1) Replace any faulty components using standard shop practices. Refer to Wiring Diagram Manual, Chapter 20,
Soldering - Maintenance Practices.
NOTE: The preferred method for installing capacitors and diodes to the printed circuit board is the
clinch method.
(2) If the printed circuit board is cracked, the entire printed circuit board assembly should be replaced. If several
components on the printed circuit board must be replaced, it may be more economically feasible to replace the entire
printed circuit board assembly.
(3) When performing repairs or inspections, all solder connections must be verified as being in good condition.
(4) Check all wires. Verify that insulation is intact and there is no evidence of chafing.
(5) Repair conformal coating as required. Refer to Repair RTV Type Conformal Coating on Printed Circuit Board.
B. Immobilize Printed Circuit Board Components (Refer to Illustrated Parts List).
(1) Locate varistors (D163 and D164) and capacitors (C25 and C26) on the printed circuit board.
NOTE: Some printed circuit boards have 1N5601 diodes installed instead of varistors. If diodes are
faulty or questionable, replace with varistors.
(2) Ensure capacitors (C25 and C26) are not touching leads to varistors (D163 and D164) or other components
adjacent to the capacitors. If capacitors are touching the varistors or other components, gently reposition the
capacitors away from leads or other components. In addition, check all other components to ensure that they are not
contacting each other and carefully reposition if necessary. Perform a general inspection of the printed circuit board
to ensure wire connections and components leads are satisfactory. If capacitors or components are defective,
replace in accordance with the Wiring Diagram Manual, Chapter 20, Soldering - Maintenance Practices.
CAUTION: Use only adhesive sealants specified for sealant application to prevent electrical terminal corrosion
on the printed circuit board.
(3) Apply a small bead of adhesive sealant, Dow Corning Silastic RTV738 or General Electric RTV162, between the
upper surface of the printed circuit board and lower surface of capacitors (C25 and C26) and varistors (D163 and
D164), as shown in Figure 601. For varistors (D163 and D164), apply a small amount of RTV on the printed circuit
board below the heads of varistors (D163 and D164) and place the head of each varistor into the adhesive sealant
as shown in Figure 601. This procedure will reduce component movement. Also, apply adhesive sealant between the
capacitors and any other components within 0.25 inch to ensure separation.
C. Repair RTV Type Conformal Coating on Printed Circuit Board (Refer to Illustrated Parts List).
NOTE: RTV type coating is transparent but has an obvious RTV (soft rubbery) feel.
NOTE: The coating provides protection of electrical components against the effects of moisture and
fungus attack.
(1) Remove existing coating as required by softening the area using clean cheesecloth dampened with xylene and
cutting/trimming the coating with a sharp knife such as an X-acto knife.
(2) Clean the area with cheesecloth moistened with isopropyl alcohol. Dry at room temperature for at least 15 minutes.
(3) Apply primer (DC1204).
NOTE: Primer need not be applied if affected area is relatively small.
NOTE: If coating being applied is other than Dow Corning R4-3117 or Dow Corning 3140, no primer is
required.
(a) Apply primer by brushing with soft bristle brush to provide thinnest possible complete coverage of surfaces to be
coated.
(b) Allow to air dry for two hours minimum at room temperature prior to application of the main coating material.
(4) Apply conformal coating.
(a) Coat by brushing to provide a cured thickness of approximately 0.003 inch.
(b) The coating may be thinned as necessary with xylene to obtain good application properties. Excessive air

Copyright © Textron Aviation Inc. Page 1 of 4

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 12:35:28 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
24-50-01-6 (Rev 5)

bubbles in coating normally indicate coating should be thinned. Thin only the quantity of coating required.
(c) Position printed circuit board horizontally. With a soft bristle brush, apply a uniform coating. Brush around
components as required to completely cover them and the board surface, except do not coat surface of
transistors to which heat sinks will be mounted.
NOTE: If impractical to coat both sides, cure one side to handling condition prior to coating
opposite side of printed circuit board.
(d)
Cure at room temperature for 30 minutes minimum before applying additional coats.
(e)
Break bubbles using soft bristle brush.
(f)
Repeat procedural steps as necessary to obtain desired coating thickness.
(g)
Allow coating to dry at room temperature for six hours minimum before handling. Full cure will be obtained in 24
hours.
D. Repair Urethane Type Conformal Coating on Printed Circuit Board (Refer to Illustrated Parts List).
NOTE: The coating provides protection of electrical components against the effects of moisture and
fungus attack.
(1) Remove existing coating as required by softening the area using clean cheesecloth dampened with xylene and
cutting/trimming the coating with a sharp knife such as an X-acto knife.
(2) Clean the area with cheesecloth moistened with isopropyl alcohol. Dry at room temperature for at least 15 minutes.
(3) Using pressure sensitive tape, mask the surface of the four transistors which mount against the heat sinks.
(4) Apply conformal coating.
(a) Apply coating by spraying Miller Stephenson MS-470 or equivalent urethane coating according to the
manufacturer's instructions. Apply two coats allowing 30 minutes drying time between coats.
(b) Allow coating to dry at room temperature for six hours minimum before handling. Full cure will be obtained in 24
hours.
E. Repair Junction Box Wiring (Refer to Illustrated Parts List).
(1) Refer to Figure 602 for the specific wires to be checked and verify that the required wires or jumpers are installed. If
not installed, install wires or jumpers using good shop practices. Refer to Wiring Diagram Manual, Chapter 20,
Soldering - Maintenance Practices.

Copyright © Textron Aviation Inc. Page 2 of 4

Figure 601 : Sheet 1 : Thrust Reverser Junction Box Printed Circuit Board Components Immobilization

Copyright © Textron Aviation Inc. Page 3 of 4

Figure 602 : Sheet 1 : Repair of Thrust Reverser Junction Box Wiring

Copyright © Textron Aviation Inc. Page 4 of 4

THRUST REVERSER JUNCTION BOX - ASSEMBLY

1. Assembly
A. Assemble Thrust Reverser Junction Box (Refer to Illustrated Parts List).
(1) Install silkscreens on thrust reverser junction box as follows:
(a) Install 5538328-10 silkscreen on the inside of the box above the R77 and R76 resistor mounting locations.
(b) Install the 5538328-11 silkscreen on the outside of the box above the J203 and J204 connectors.
(c) Install the 5538328-17 and 5538328-18 silkscreens to the inside of the junction box with reference designators
aligned with diode locations. Refer to Figure 701.
(2) Apply Dow Corning conductive grease Type 340 to surface of transistors to which heat sinks are installed.
(3) Install heat sinks (90) to transistors Q5 (78) and Q7 (78) with screws (79), washers (80) and nuts (81).
(4) Install printed circuit board (77) and heat sink (22) to junction box (7) with screws (12) (13), spacers (15) and nuts
(14).
(5) Install electrical connectors (26) (28) with screws (19) and nuts (20).
(6) Install diodes on diode plate (16) ensuring that diodes are in the correct order and installed in the correct holes to
match the silkscreens.
(7) Install diode plates (16) with screws (17) and spacers (18).

Copyright © Textron Aviation Inc. Page 1 of 2

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 12:35:36 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
24-50-01-7 (Rev 7)

Figure 701 : Sheet 1 : Diode Silkscreen Installation

Copyright © Textron Aviation Inc. Page 2 of 2

JUNCTION BOX-THRUST REVERSER

NOMENCLATURE EFFECTIVITY UNITS
PER
ITEM PART NUMBER 1 2 3 4 5 6 7 FROM TO ASSY
- JUNCTION BOX-THRUST REVERSER
- 1 5538377-4 . LID ASSY 01
2 5538377-3 . . LID 01
3 2600-1 . . STUD V71286 03

- . BOX ASSY-JUNCTION
4 5538328-1 A 01
REFER TO NOTE 1
BOX ASSY-JUNCTION
- 5 5538328-8 . REFER TO NOTE 2 FSO B NP
5538328-24
BOX ASSY-JUNCTION
- 6 5538328-16 . REFER TO NOTE 3 FSO C NP
5538328-24
BOX ASSY-JUNCTION
- 6A 5538328-22 . REFER TO NOTE 3 FSO D NP
5538328-24
- 7 5538377-1 . . BOX ASSY C 01
- 7A 5538377-5 . . BOX ASSY D 01
8 5538377-2 . . . BOX C 01
- 8A 5538377-6 . . . BOX D 01
9 MS21047L06 . . . NUTPLATE 06
10 MS21047L04 . . . NUTPLATE 04

11 26R5-1 . . . RECEPTACLE- V71286 03

FASTENER
SCREW-FORWARD
12 MS24693S7 . . PRINTED CIRCUIT 02
BOARD SUPPORT
SCREW-AFT PRINTED
13 MS24693S8 . . CIRCUIT BOARD AND 02
HEAT SINK SUPPORT
NUT-PRINTED CIRCUIT
14 MS21042-04 . . BOARD AND HEAT 04
SINK SUPPORT
SPACER-PRINTED
. . CIRCUIT BOARD AND
15 NAS43DD0-16 04
HEAT SINK
STANDOFF
16 5538328-2 . . DIODE PLATE 02
ATTACHING
PARTS
17 MS35206-233 . . SCREW 06
18 NAS43DD1-32 . . SPACER 06
---*---

Copyright © Textron Aviation Inc. Page 1 of 6

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 12:35:41 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
24-50-01-1001 (Rev 13)

SCREW-
19 MS35206-214 . . CONNECTORS J203 08
AND J204 ATTACH
NUT-CONNECTOR
20 MS21042-04 . . J203 AND J204 08
ATTACH
. . SCREW-RESISTOR
21 AN508-4-5 04
R77 AND R76 ATTACH
22 5538328-3 . . HEATSINK ASSY 01
- . . BUNDLE ASSY-
23 5538203-1 A 01
JUNCTION BOX
- . . BUNDLE ASSY-
24 6538203-3 B 01
JUNCTION BOX

- . . BUNDLE ASSY-
25 6538203-7 C &D 01
JUNCTION BOX
CONNECTOR-
26 M83723-02R1419N . . . JUNCTION BOX V11139 01
J203
CONNECTOR-
JUNCTION BOX
- 26A MS3470L14-19P . . . J203 ALTERNATE 01
FOR M83723-
02R1419N
BACKSHELL-
- 27 M85049/60-2E14N . . . JUNCTION BOX 01
J203
CONNECTOR-
28 M83723-02R1419Y . . . JUNCTION BOX V11139 01
J204
CONNECTOR-
JUNCTION BOX
- 28A MS3470L14-19PY . . . J204 ALTERNATE 01
FOR M83723-
02R1419Y
BACKSHELL-
- 29 M85049/60-2E14N . . . JUNCTION BOX 01
J204
DIODE-JUNCTION
BOX UPPER
30 1N1201 . . . MOUNT D183, V07688 05
D178, D179, D167,
D171
DIODE-JUNCTION
BOX LOWER
31 1N1201 . . . MOUNT D181, V07688 05
D180, D168, D182,
D172
DIODE-JUNCTION
32 1N1201R . . . BOX D169 AND V07688 02
D170

Copyright © Textron Aviation Inc. Page 2 of 6

RESISTOR-
33 S3154-25-40 . . . JUNCTION BOX V91637 02
R76 AND R77
TUBING-HEAT
SHRINK 3/8 INCH
34 3/8HT SH TUBING . . . AR
DIAMETER PER
MIL-I-23053
A 5538328-1 THRUST REVERSER JUNCTION BOX WHICH HAS BEEN OVERHAULED
NOTE 1: INACCORDANCE WITH THIS MANUAL MAY BE USED ON MODEL 500 AIRPLANES -0001
THRU -0500.
A 5538328-8 THRUST REVERSER JUNCTION BOX WHICH HAS BEEN OVERHAULED IN
NOTE 2: ACCORDANCE WITH THIS MANUAL MAY BE USED ON ALL MODEL 500, MODEL 550 (THRU -
0800), AND ALL MODEL S550 AIRPLANES.
A 5538328-22 THRUST REVERSER JUNCTION BOX MAY BE USED AS SPARES FOR MODEL
NOTE 3: 500, MODEL 550 (-0002 THRU -0800), ALL MODEL S550 AND MODEL 560 (-0001 THRU -0259)
AIRPLANES.
NOMENCLATURE EFFECTIVITY UNITS
PER
ITEM PART NUMBER 1 2 3 4 5 6 7 FROM TO ASSY
- JUNCTION BOX-THRUST REVERSER
BOARD ASSY-
- 75 5518141-3 . . . A 01
PRINTED CIRCUIT
BOARD ASSY-
- 76 5518141-8 . . . B 01
PRINTED CIRCUIT
- . . . BOARD ASSY-
77 5518141-10 C &D 01
PRINTED CIRCUIT
TRANSISTOR
78 MJE3055 . . . . Q5 AND Q7 V04713 02
REFER TO
NOTE 1
ATTACHING
PARTS
79 AN508-4-6 . . . . SCREW 01
80 NAS1149DN416J . . . . WASHER 01
81 MS21042-04 . . . . NUT 01
---*---
TRANSISTOR
. . . . Q11 AND Q12
82 MJE2955 V04713 02
REFER TO
NOTE 1
. . . . TRANSISTOR
83 2N2102 V07688 02
Q6 AND Q8
DELETED-NOT
- 84 . . . .
USED
DIODE D165,
D166, D190,
85 1N5061 . . . . V07688 06
D191, D229,
AND D230

Copyright © Textron Aviation Inc. Page 3 of 6

DIODE D173,
86 1N5556 . . . . D174, AND V07688 03
D177
. . . . CAPACITOR
87 M39006/22-0399 02
C25 AND C26
88 1N5061 . . . . DIODE D469 V07688 B,C& D 01
VARISTOR D163
89 V47ZA1 . . . . V03508 02
AND D164
90 6107B14 . . . . HEATSINK V13103 02
- . . PLACARD-R76 AND R77
91 5538328-10 01
RESISTORS
- . . PLACARD-J203 AND
92 5538328-11 01
J204 CONNECTORS
- . . PLACARD-DIODE D170
93 5538328-18 01
THRU D181
- . . PLACARD-DIODE D169
94 5538328-17 01
THRU D183
NOTE 1: ASSURE THAT ONLY GENUINE MOTOROLA PARTS ARE INSTALLED.
- Item Not Illustrated

Copyright © Textron Aviation Inc. Page 4 of 6

Figure 1001 : Sheet 1 : JUNCTION BOX-THRUST REVERSER

Copyright © Textron Aviation Inc. Page 5 of 6

Figure 1001 : Sheet 2 : JUNCTION BOX-THRUST REVERSER

Copyright © Textron Aviation Inc. Page 6 of 6

THRUST REVERSER JUNCTION BOX - ILLUSTRATED PARTS LIST

1. Illustrated Parts List
A. Introduction
(1) The Illustrated Parts List has been prepared to assist customer personnel in requisitioning, storing, and issuing the
thrust reverser junction box components and in identifying new and reclaimed parts. It is not approved for any other
purpose.
(2) This parts list covers the thrust reverser junction boxes used on the Models 550 Bravo and 560 airplanes -0260 and
On. These part numbers are covered:
5538328-24 5538328-26
(3) The indention system used in the detailed parts list of this catalog shows the relationship of one part to another. For a
given item, the indention code shows a system, installation or general heading starting at the extreme left position
continuing on down into succeeding columns until the end detail is reached. Example:
A18017
1234567
Installation
Detail Parts for Installation
Assembly
Attaching Parts for Assembly
Detail Parts for Assembly
Subassembly
Attaching Parts for Subassembly
Detail Parts for Subassembly
Sub−Subassembly
Attaching Parts for Sub−Subassembly
Detail Parts for Sub−Subassembly

Basic Number Dash Number

(Drawing Identification
Only)

Copyright © Textron Aviation Inc. Page 1 of 1

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Model 500 Series Component Maintenance Manual (Rev 17)
24-50-02-0 (Rev 17)

THRUST REVERSER JUNCTION BOX - DESCRIPTION AND OPERATION

1. General
A. Accomplishment of the procedures in this manual on a thrust reverser junction box will constitute an overhaul as defined in
Federal Aviation Regulations Part 43.2.
B. For a list of steps required to accomplish an overhaul, assuming that the thrust reverser junction box is faulty, refer to Thrust
Reverser Junction Box - Check.
2. Description
A. The thrust reverser junction box incorporates electrical components to provide electrical logic control for the operation of
the thrust reversers. The logic control consists primarily of steering diodes and transistors to control solenoid valves. The
solenoid valves control hydraulic power to the thrust reversers. Refer to Figure 1 and Figure 2.
B. These thrust reverser junction box part numbers are affected by this individual Component Maintenance Manual:
5538328-24 5538328-26 6518407-2

Copyright © Textron Aviation Inc. Page 1 of 4

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Model 500 Series Component Maintenance Manual (Rev 17)
24-50-02-0 (Rev 17)

Figure 1 : Sheet 1 : Printed Circuit Board Components Identification

Copyright © Textron Aviation Inc. Page 2 of 4

Figure 2 : Sheet 1 : Thrust Reverser Junction Box Wiring Diagram

Copyright © Textron Aviation Inc. Page 3 of 4

Figure 2 : Sheet 2 : Thrust Reverser Junction Box Wiring Diagram

Copyright © Textron Aviation Inc. Page 4 of 4

THRUST REVERSER JUNCTION BOX - TESTING

1. Check Junction Box
A. Functional Test.
(1) Connect a 6587000-1 thrust reverser junction box tester to the junction box to be tested.
NOTE: Instructions for fabrication of 6587000-1 thrust reverser junction box tester are included in this
section.
NOTE: This test may be performed with the junction box installed in the airplane or may be performed
as a bench test. The sequence of steps is designed to simulate the operating sequence in a
functioning thrust reverser system.
(2) Set switches on the tester:
S1, S2 NORMAL
S3, S4 STOW
S5, S6 STOWED
S7, S8 AIR
S9, S10 STOWED/IN TRANSIT
S11 OFF
NOTE: The steps within this test must be performed sequentially. The test box switches must be reset
only as instructed during the functional test steps.
(3) Connect a source of 28.5 VDC, +0.5 or -0.5 VDC to the tester.
(4) Set switch S11 to LAMP TEST.
(a) Verify that all indicator lights on tester are illuminated.
(5) Set S11 to OFF.
(a) Verify that all indicator lights on tester are extinguished.
NOTE: Steps (6) through (10) check the left deploy circuit.
(6) Set switch S7 to GND.
(a) Verify that light L11 DEPLOY GND is illuminated.
(b) Verify that lights L13 M.W. GND and L14 M.W. GND are illuminated.
NOTE: If L11 is not illuminated, check for open diode D183 or D191.
(7) Set switch S3 to DEPLOY.
(a) Verify that lights L3 DEPLOY, L5 ISOLATION VALVE, L7 CENTER VALVE 1, L9 CENTER VALVE 3, L10
CENTER VALVE 2, L11 DEPLOY GND, L13 M.W. GND and L14 M.W. GND are illuminated.
NOTE: If L3 is not illuminated, the jumper between pins F and T of connector J203 is open. If L5 is
not illuminated, diode D169 is open. If L7, L9 and L10 are not illuminated, check for open
diode D169 or D178. If L7 and L9 are illuminated but L10 is not, check for open jumper
between diodes D178 and D180.
(8) Set switch S3 to STOW and switch S5 to DEPLOYED/IN TRANSIT.
(a) Verify that light L3 extinguishes and that light L1 STOW illuminates. All other lights remain as in step (7).
NOTE: If L1 is not illuminated, diode D167 is open. If L1 is illuminated but L5 is not illuminated,
diode D171 is open.
(9) Connect a 3 1/2 digit voltmeter to TP3(+) and TP1(-).
(10) Set switch S9 to DEPLOYED position and switch S3 to DEPLOY.
(a) Verify that light L1 extinguishes and light L3 illuminates.
(b) Verify that voltmeter momentarily reads 22.5 VDC, +1.5 or -1.5 VDC and then gradually drops to 6.8 volts within
one minute.
NOTE: If initial voltage is low or not present, check resistor R77, diode D229, capacitor C25 for

Copyright © Textron Aviation Inc. Page 1 of 10

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Model 500 Series Component Maintenance Manual (Rev 17)
24-50-02-1 (Rev 7)

open or transistor Q1 may be faulty.

NOTE: If voltage does not drop, verify the electrical integrity of transistor Q1.
NOTE: Step (11) checks the left emergency stow circuit.
(11) Set switch S1 to EMER STOW, switch S3 to STOW, switch S5 to STOWED and switch S9 to STOWED/IN
TRANSIT.
(a) Verify that light L1 illuminates and light L3 extinguishes.
NOTE: If L5 is not illuminated, diode D171 is open. If L5, L7, L9 and L10 are not illuminated, diode
D171 and D179 are open. Also check diode D178 for open.
(b) Verify that voltage across TP3(+) and TP1(-) is O VDC.
(12) Set switch S1 to NORMAL and switch S7 to AIR.
(a) Verify that all test box lights extinguish.
NOTE: Steps (13) through (17) check the right deploy circuit.
(13) Set switch S8 to GND.
(a) Verify that light L12 DEPLOY GND is illuminated.
(b) Verify that lights L13 M.W. GND and L14 M.W. GND are illuminated.
NOTE: If L12 is not illuminated, check for open diode D182 or D190 or faulty transistor Q4.
(14) Set switch S4 to DEPLOY.
(a) Verify that lights L4 DEPLOY, L6 ISOLATION VALVE, L7 CENTER VALVE 1, L9 CENTER VALVE 3, L10
CENTER VALVE 2, L12 DEPLOY GND, L13 M.W. GND and L14 M.W. GND are illuminated.
NOTE: If L4 is not illuminated, the jumper between pins F and T of connector J204 is open. If L6 is
not illuminated, diode D170 is open. If L7, L9 and L10 are not illuminated, check for open
diode D170 or D180. If L10 is illuminated but L7 and L9 are not, check for open jumper
between diodes D178 and D180.
(15) Set switch S4 to STOW and switch S6 to IN TRANSIT/DEPLOYED.
(a) Verify that light L4 extinguishes and that light L2 STOW illuminates. All other lights remain as in step (14).
NOTE: If L2 is not illuminated, diode D168 is open. If L2 is illuminated but L6 is not illuminated,
diode D172 is open.
(16) Connect a 3 1/2 digit voltmeter to TP4(+) and TP2(-).
(17) Set switch S10 to DEPLOYED position and switch S3 to DEPLOY.
(a) Verify that light L2 extinguishes and light L4 illuminates.
(b) Verify that voltmeter reads 22.5 VDC, +1.5 or -1.5 VDC, and then gradually drops to 6.8 volts within one minute.
NOTE: If initial voltage is low or not present, check resistor R76, diode D230 or capacitor C26 for
open, or transistor Q2 may be faulty.
NOTE: If voltage does not drop, verify the electrical integrity of transistor Q2.
NOTE: Step 18 checks the right emergency stow circuit.
(18) Set switch S2 to EMER STOW, switch S4 to STOW, switch S6 to STOWED and switch S10 to STOWED/IN
TRANSIT.
(a) Verify that light L2 illuminates and light L4 extinguishes.
NOTE: If L6 is not illuminated, diode D172 is open. If L6, L7, L9 and L10 are not illuminated, diode
D172 and D180 are open. Also check diode D181 for open.
(b) Verify that voltage across TP4(+) and TP2(-) is 0 VDC.
(19) Set switch S2 to NORMAL and switch S8 to AIR.
(a) Verify that all test box lights extinguish.
(20) Remove external power from thrust reverser junction box tester.
(21) Disconnect thrust reverser junction box tester from thrust reverser junction box.
(22) Check the isolation diodes on the thrust reverser printed circuit board for open by connecting the positive lead of a

Copyright © Textron Aviation Inc. Page 2 of 10

voltmeter to pin R of either P203 or P204 and successively applying the negative voltmeter terminal to the pins listed
in .
Table 101. Checking Isolation Diodes
P203 pin N diode D177
P203 pin E diode D173
P203 pin F diode D165
P203 pin D diode D163
P204 pin F diode D166
P204 pin E diode D174
P204 pin D diode D164
(23) After completion of and passing of the functional test, attach a tag to the thrust reverser junction box indicating that the
box conforms to the requirements of the Components Maintenance Manual.
B. Fabrication of 6587000-1 Thrust Reverser Junction Box Tester. Refer to Figure 101.
(1) Using the drawings and parts list provided, fabricate a thrust reverser junction box tester.
(2) Parts List for the 6587000-1 Thrust Reverser Junction Box Tester.
TERMINOLOGY PART NUMBER QUANTITY FEDERAL SUPPLY
REQUIRED CODE
Binding Post 1464-102 1 83330
Binding Post 1464-103 3 83330
Binding Post 1464-107 2 83330
Resistor F204 or 2 44655
VPR-20-14-10 or 12697
HL-20-10 91637
Light 922-404X-410RT or 13 75915
5131-038-304 71744
RED or 162-971 72619
Box AC-406BPA 112611 71218
Plate 15931N4006 71218
Diode MST-205N or 95146
Switch 7201-S-Y-Z-Q or 09353
JMT-223 15605
Terminal Board 15299 2 91833
Connector MS3126F14-19SY 1 11139
Connector MS3126F14- 19SN 1 11139
Strain Relief SL13 1 8U767
Backshell GTR00V14B 2 06324
Wire 20 Gage MIL-W-81044/12-20-9 200 Feet
Screw MS35206-327 12
Screw MS35206-217 4
Spacer NAS43DD1-8 12
Nut MS21042-04 4
Nut MS21042-06 12
C. Manufacturer’s Federal Supply Codes and addresses for fabrication of Thrust Reverser Junction Box Tester.

Copyright © Textron Aviation Inc. Page 3 of 10

06323 GLENAIR 72619 AMPEREX ELECTRIC CORP.

1211 Air Way 203 Harrison Pl.
Glendale, CA 91201 Brooklyn, NY
09353 C & K COMPONENTS, INC. 75915 TRACOR LITTELFUSE INC.
15 Riverdale Ave. 800 E. NW Highway
Newton, MA 02158 Des Plaines, IL 60016
11139 DEUTSCH CO. 83330 KULKA SMITH INC.
700 S. Hathaway 1913 Atlantic Ave.
Municipal Airport Manasquan, NJ 08736
Banning, CA 92220
12697 CLAROSTAT MANUFACTURING CO. 91637 DALE ELECTRONICS INC.
Lower Washington Street P.O. Box 609
Dover, NH 03820 Columbus, NE 68601
15605 EATON CORP. 91833 KEYSTONE ELECTRONICS CORP.
4201 N. 27th St. 49 Bleecker St.
Milwaukee, WI 53216 New York, NY 10012
44655 OHMITE MANUFACTURING CO. 95146 ALCO ELECTRIC PRODUCTS, INC.
3601 W. Howard St. 1551 Osgood St.
Skokee, IL 60076 North Andover, MA 01845
71218 BUD INDUSTRIES, INC. 8U767 OLFLEX WIRE AND CABLE, INC.
4605 E. 355th St. 30 Plymouth Street
Willoughby, OH 44094 Fairfield, NJ 07006
71744 GENERAL INSTRUMENT CORP. LAMP
DIV.
4433 N. Ravenswood Ave.
Chicago, IL 60640

Copyright © Textron Aviation Inc. Page 4 of 10

Figure 101 : Sheet 1 : Fabrication of Thrust Reverser Junction Box Tester

Copyright © Textron Aviation Inc. Page 5 of 10

Figure 101 : Sheet 2 : Fabrication of Thrust Reverser Junction Box Tester

Copyright © Textron Aviation Inc. Page 6 of 10

Figure 101 : Sheet 3 : Fabrication of Thrust Reverser Junction Box Tester

Copyright © Textron Aviation Inc. Page 7 of 10

Figure 101 : Sheet 4 : Fabrication of Thrust Reverser Junction Box Tester

Copyright © Textron Aviation Inc. Page 8 of 10

Figure 101 : Sheet 5 : Fabrication of Thrust Reverser Junction Box Tester

Copyright © Textron Aviation Inc. Page 9 of 10

Figure 101 : Sheet 6 : Fabrication of Thrust Reverser Junction Box Tester

Copyright © Textron Aviation Inc. Page 10 of 10

THRUST REVERSER JUNCTION BOX - DISASSEMBLY

1. Disassembly
A. Disassemble Thrust Reverser Junction Box (Refer to Illustrated Parts List).
(1) Remove six screws (17) and spacers (18) securing diode plates (16) leaving diodes installed in diode plates.
(2) Remove four screws (21) securing resistors (92, 99).
(3) Remove four screws (12) (13), spacers (15) and nuts (14) securing printed circuit board (77) to junction box.
(4) Remove eight screws (19) and nuts (20) securing electrical connectors (93) and (102) to junction box.
(5) Disconnect soldered connectors in accordance with the Wiring Diagram Manual, Chapter 20, Soldering -
Maintenance Practices.

Copyright © Textron Aviation Inc. Page 1 of 1

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 12:36:21 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
24-50-02-5 (Rev 7)

THRUST REVERSER JUNCTION BOX - CHECK

1. Check
A. The following should be accomplished in the order printed to determine which portions of the procedures presented in the
manual must be performed to restore or overhaul a thrust reverser junction box.
(1) Remove the cover and examine the interior components for broken capacitor, diodes or varistor leads, signs of
overheating of resistors, broken or disconnected electrical leads.
(2) Perform a functional test of the box. Refer to Thrust Reverser Junction Box - Testing.
(3) Disassemble as required to repair faulty components. Refer to Thrust Reverser Junction Box - Disassembly and
Thrust Reverser Junction Box - Repair.
(4) Assemble box. Refer to Thrust Reverser Junction Box - Assembly.
(5) Perform a functional test of the box to verify proper functioning. Refer to Thrust Reverser Junction Box - Testing.

Copyright © Textron Aviation Inc. Page 1 of 1

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 12:36:23 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
24-50-02-6 (Rev 7)

THRUST REVERSER JUNCTION BOX - REPAIR

1. Repair
A. Repair Thrust Reverser Junction Box (Refer to Figure 601 and ).
(1) Replace any faulty components using standard shop practices. Refer to Wiring Diagram Manual, Chapter 20,
Soldering - Maintenance Practices.
NOTE: The preferred method for installing capacitors and diodes to the printed circuit board is the
clinch method.
(2) If the printed circuit board is cracked, the entire printed circuit board assembly should be replaced. If several
components on the printed circuit board must be replaced, it may be more economically feasible to replace the entire
printed circuit board assembly.
(3) When performing repairs or inspections, all solder connections must be verified as being in good condition.
(4) Check all wires. Verify that insulation is intact and there is no evidence of chafing.
(5) Repair conformal coating as required. Refer to Repair RTV Type Conformal Coating on Printed Circuit Board.
B. Immobilize Printed Circuit Board Components (Refer to Illustrated Parts List).
(1) Locate capacitors (C25 and C26) on the printed circuit board.
(2) Ensure capacitors (C25 and C26) are not touching other components adjacent to the capacitors. If capacitors are
touching other components, gently reposition the capacitors away from other components. In addition, check all other
components to ensure that they are not contacting each other and carefully reposition if necessary. Perform a general
inspection of the printed circuit board to ensure wire connections and components leads are satisfactory. If
capacitors or components are defective, replace in accordance with the Wiring Diagram Manual, Chapter 20,
Soldering - Maintenance Practices.
CAUTION: Use only adhesive sealants specified for sealant application to prevent electrical terminal corrosion
on the printed circuit board.
(3) Apply a small bead of adhesive sealant, Dow Corning Silastic RTV738 or General Electric RTV162, between the
upper surface of the printed circuit board and lower surface of capacitors (C25 and C26) as shown in Figure 601.
This procedure will reduce component movement. Also, apply adhesive sealant between the capacitors and any
other components within 0.25 inch to ensure separation.
C. Repair Urethane Type Conformal Coating on Printed Circuit Board (Refer to Illustrated Parts List).
NOTE: The coating provides protection of electrical components against the effects of moisture and
fungus attack.
(1) Remove existing coating as required by softening the area using clean cheesecloth dampened with xylene and
cutting/trimming the coating with a sharp knife such as an X-acto knife.
(2) Clean the area with cheesecloth moistened with isopropyl alcohol. Dry at room temperature for at least 15 minutes.
(3) Using pressure sensitive tape, mask the surface of the four darlingtons which mount against the heat sinks.
(4) Apply conformal coating.
(a) Apply coating by spraying Miller Stephenson MS-470 or equivalent urethane coating according to the
manufacturer's instructions. Apply two coats allowing 30 minutes drying time between coats.
(b) Allow coating to dry at room temperature for six hours minimum before handling. Full cure will be obtained in 24
hours.

Copyright © Textron Aviation Inc. Page 1 of 2

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 12:36:24 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
24-50-02-6 (Rev 7)

Figure 601 : Sheet 1 : Thrust Reverser Junction boc Printed Circuit Board Components Immobilization

Copyright © Textron Aviation Inc. Page 2 of 2

THRUST REVERSER JUNCTION BOX - ASSEMBLY

1. Assembly
A. Assemble Thrust Reverser Junction Box (Refer to Illustrated Parts List).
(1) Install silkscreens on thrust reverser junction box as follows:
(a) Install 5538328-10 silkscreen on the inside of the box above the R77 and R76 resistor mounting locations.
(b) Install the 5538328-11 silkscreen on the outside of the box above the J203 and J204 connectors.
(c) Install the 5538328-17 and 5538328-18 silkscreens to the inside of the junction box with reference designators
aligned with diode locations. Refer to Figure 701.
(2) If darlingtons have been replaced or if heat sinks have been removed from printed circuit board, apply Dow Corning
conductive grease Type 340D to surface of darlingtons to which heat sinks are installed.
(3) Install heat sinks (86) to darlingtons Q1 (76) and Q2 (76) with screws (78), washers (79, 80) and nuts (81).
(4) Install printed circuit board (75) to junction box (6) with screws (12, 13), spacers (15) and nuts (14).
(5) Install electrical connectors (93) (100) with screws (19) and nuts (20).
(6) Install diodes on diode plate (16) ensuring that diodes are in the correct order and installed in the correct holes to
match the silkscreens.
(7) Install diode plates (16) with screws (17) and spacers (18).

Copyright © Textron Aviation Inc. Page 1 of 2

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 12:36:30 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
24-50-02-7 (Rev 7)

Figure 701 : Sheet 1 : Diode Silkscreen Installation

Copyright © Textron Aviation Inc. Page 2 of 2

JUNCTION BOX-THRUST REVERSER

NOMENCLATURE EFFECTIVITY UNITS
PER
ITEM PART NUMBER 1 2 3 4 5 6 7 FROM TO ASSY
- JUNCTION BOX-THRUST REVERSER
- 1 5538377-4 . LID ASSY 01
2 5538377-3 . . LID 01
3 2600-1 . . STUD V71286 03

- . BOX ASSY-JUNCTION
4 5538328-24 A 01
REFER TO NOTE 1
BOX ASSY-JUNCTION
- 5 5538328-26 . B 01
REFER TO NOTE 2
6 5538377-5 . . BOX ASSY A 01
- 7 5538377-7 . . BOX ASSY B 01
8 MS21047L06 . . . NUTPLATE 06
9 MS21047L04 . . . NUTPLATE 04

10 26R5-1 . . . RECEPTACLE- V71286 03

FASTENER
11 MS21075L08N . . . NUTPLATE B 04
SCREW-FWD
12 MS24693S7 . . PRINTED CIRCUIT 02
BOARD SUPPORT
SCREW-AFT PRINTED
13 MS24693S8 . . CIRCUIT BOARD AND 02
HEAT SINK SUPPORT
NUT-PRINTED CIRCUIT
14 MS21042-04 . . BOARD AND HEAT 04
SINK SUPPORT
SPACER-PRINTED
15 NAS43DD0-16 . . CIRCUIT BOARD AND 04
HEAT SINK STANDOFF
16 5538328-2 . . DIODE PLATE 02
ATTACHING
PARTS
17 MS35206-233 . . SCREW 06
18 NAS43DD1-32 . . SPACER 06
---*---
SCREW-
19 MS35206-214 . . CONNECTORS J203 08
AND J204 ATTACH
NUT-CONNECTOR
20 MS21042-04 . . J203 AND J204 08
ATTACH

21 AN508-4-5 . . SCREW-RESISTOR 04
R77 AND R76 ATTACH
22 7721-7PPS . . INSULATING WASHER V13103 02

Copyright © Textron Aviation Inc. Page 1 of 5

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 12:36:34 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
24-50-02-1001 (Rev 13)

A 5538328-24 THRUST REVERSER JUNCTION BOX MAY BE USED AS SPARES FOR 5538328-
NOTE 1:
1, -8, -16, -22.
A 5538328-26 THRUST REVERSER JUNCTION BOX MAY BE USED AS SPARES FOR MODEL
NOTE 2:
550 AIRPLANES -0801 AND ON.
NOMENCLATURE EFFECTIVITY UNITS
PER
ITEM PART NUMBER 1 2 3 4 5 6 7 FROM TO ASSY
- JUNCTION BOX-THRUST REVERSER
- 75 6518350-1 . . . BOARD ASSY-PRINTED CIRCUIT 01

76 TIP122 . . . . DARLINGTON Q1 AND Q2 REFER V04713 02

TO NOTE 1

77 TIP107 . . . . DARLINGTON Q3 AND Q4 REFER V04713 02

TO NOTE 1
ATTACHING
PARTS
78 MS35206-216 . . . . SCREW USED WITH Q1 & Q2 02
79 NAS1149DN416K . . . . WASHER USED WITH Q1 & Q2 02
80 7721-7PPS . . . . WASHER USED WITH Q1 & Q2 V13103 02
81 MS21042-04 . . . . NUT USED WITH Q1 AND Q2 02
---*---
. . . . TRANSZORB
82 1.5KE36A V24444 05
D163,D164,D173,D174 AND D177
DIODE
83 1N4006 . . . . D165,D166,D190,D191,D229,D230 V07688 07
AND D469
84 M39006/22-0399 . . . . CAPACITOR C25 AND C26 02
CAPACITOR C25 AND C26
- 85 100MICROFARAD75V . . . . ALTERNATE FOR M39006/22- V37942 02
0399
86 6079B . . . . HEATSINK V13103 04
87 43-77-9 . . . . TRANSISTOR INSULATOR V13103 04
- 88 6518204-11 . . BUNDLE ASSEMBLY-JUNCTION BOX A 01
- 89 6578234-5 . . . WIRE BUNDLE SUB-ASSEMBLY- A 01
JUNCTION BOX
- . . . . DIODE D167 D171 D178 D179
90 1N1201 V07688 A 05
D183
- 91 1N1201R . . . . DIODE D169 V07688 A 01
92 S3154-25-40 . . . . RESISTOR R77 V91637 A 01 R
CONNECTOR-JUNCTION BOX
93 MS3470L14-19P . . . . A 01 R
J203
CONNECTOR-JUNCTION BOX
- 94 M83723-02R1419N . . . . J203 ALTERNATE FOR A 01
MS3470L14-19P
- . . . . BACKSHELL-JUNCTION BOX
95 M85049/31-14N A 01
J203

Copyright © Textron Aviation Inc. Page 2 of 5

WIRE BUNDLE SUB-ASSEMBLY-

- 96 6578235-7 . . . A 01
JUNCTION BOX
- . . . . DIODE D168 D172 D180 D181
97 1N1201 V07688 A 05
D182
- 98 1N1201R . . . . DIODE D170 V07688 A 01
99 S3154-25-40 . . . . RESISTOR R76 V91637 A 01 R
CONNECTOR-JUNCTION BOX
- 100 MS3470L14-19PY . . . . A 01
J204
CONNECTOR-JUNCTION BOX
- 101 M83723-02R1419Y . . . . J204 ALTERNATE FOR A 01
MS3470L14-19PY
- 102 M85049/31-14N . . . .
BACKSHELL-CONNECTOR J204 A 01
- 103 6518220-18 . . BUNDLE ASSEMBLY-JUNCTION BOX B 01
BUNDLE SUB-ASSEMBLY-JUNCTION
- 104 6577204-5 . . . B 01
BOX
- 105 MS3470L14-19P . . . . CONNECTOR J203 B 01
CONNECTOR J203 ALT FOR
- 106 M83723-02R1419N . . . . B 01
MS3470L14-19P
- 107 M85049/31-14N . . . . BACKSHELL-CONNECTOR J203 B 01
- 108 S3154-25-40 . . . . RESISTOR R77 V91637 B 01
- . . . . DIODE D167 D171 D178 D179
109 1N1201 V07688 B 05
D183
- 110 1N1201R . . . . DIODE D169 V07688 B 01
- . . . BUNDLE SUB-ASSEMBLY-JUNCTION
111 6577205-7 B 01
BOX
- 112 MS3470L14-19PY . . . . CONNECTOR J204 B 01
- . . . . CONNECTOR J204 ALT FOR
113 M83723-02R1419Y B 01
MS3470L14-19PY
- 114 M85049/31-14N . . . . BACKSHELL-CONNECTOR J204 B 01
- 115 S3154-25-40 . . . . RESISTOR R76 V91637 B 01
- . . . . DIODE D168 D172 D180 D181
116 1N1201 V07688 B 05
D182
- 117 1N1201R . . . . DIODE D170 V07688 B 01
- 118 5538328-10 . . PLACARD-R76 AND R77 RESISTORS 01
- 119 5538328-11 . . PLACARD-J203 AND J204 CONNECTORS 01
- 120 5538328-18 . . PLACARD-DIODE D170 THRU D181 01
- 121 5538328-17 . . PLACARD-DIODE D169 THRU D183 01
NOTE 1: ASSURE THAT ONLY GENUINE MOTOROLA PARTS ARE INSTALLED.
- Item Not Illustrated

Copyright © Textron Aviation Inc. Page 3 of 5

Figure 1001 : Sheet 1 : JUNCTION BOX-THRUST REVERSER

Copyright © Textron Aviation Inc. Page 4 of 5

Figure 1001 : Sheet 2 : JUNCTION BOX-THRUST REVERSER

Copyright © Textron Aviation Inc. Page 5 of 5

TRIM TAB ACTUATOR - ILLUSTRATED PARTS LIST

1. Illustrated Parts List
A. Introduction.
(1) The Illustrated Parts List will help the customer to order, keep, and supply the trim tab actuator components. It will also
identify new and reclaimed parts. It is not approved for any other purpose.
(2) The trim tab actuator part numbers that follow are covered in this parts list:
5565450-7 5565450-42 5565450-61 5565450-72 5565450-89 5565450-102
5565450-8 5565450-43 5565450-62 5565450-76 5565450-90
5565450-22 5565450-51 5565450-63 5565450-77 5565450-91
5565450-23 5565450-52 5565450-64 5565450-78 5565450-92
5565450-30 5565450-53 5565450-65 5565450-79 5565450-93
5565450-32 5565450-54 5565450-66 5565450-80 5565450-94
5565450-34 5565450-55 5565450-67 5565450-81 5565450-95
5565450-36 5565450-56 5565450-68 5565450-82 5565450-201
5565450-38 5565450-59 5565450-70 5565450-87 5565450-98
5565450-41 5565450-60 5565450-71 5565450-88 5565450-99
(3) The indention system used in the detailed parts list of this catalog shows the relationship of one part to another. For a
given item, the indention code shows a general heading at the extreme left position and continues with indented
columns until the end detail is reached as follows:
A18017
1234567
Installation
Detail Parts for Installation
Assembly
Attaching Parts for Assembly
Detail Parts for Assembly
Subassembly
Attaching Parts for Subassembly
Detail Parts for Subassembly
Sub−Subassembly
Attaching Parts for Sub−Subassembly
Detail Parts for Sub−Subassembly

(4) The quantities given in the UNITS PER ASSY column of the parts list are the total number of parts used at the
indicated location for that assembly. Component parts that are indented under the assembly show the quantity used
in the assembly. The quantities are not necessarily the total used per installation.
(5) Effectivity for detail parts of assemblies in this technical manual is listed in the EFFECT column. The numbers listed
for the assembly also apply to the code for the detail parts specific to that assembly. If no numbers are shown in the
EFFECT column, that detail part is used in all assemblies listed.
(6) When a part of later design is not interchangeable with the part that it replaces, both parts that apply to the particular
usage are listed. The individual part usage is listed in the EFFECT column. Make sure you find out the proper use
when you send an order to make sure the correct part is received.
(7) The base number identifies the Cessna drawing only. Each installation, assembly, or detail part is assigned a part
number which has a drawing number and a dash number.

Copyright © Textron Aviation Inc. Page 1 of 2

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 12:58:05 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
27-10-06-10 (Rev 14)

A12537
EXAMPLE:
Part Number
6707005 − 7

Basic Number Dash Number

(Drawing Identification
Only)

NOTE: Parts that have a dash 400 series stamp are for internal control purposes only and must not be
used by the operator to order or to identify parts.

Copyright © Textron Aviation Inc. Page 2 of 2

TRIM TAB ACTUATOR - DESCRIPTION AND OPERATION

1. Description
A. The trim tab actuator incorporates two internally threaded screws, two externally threaded screws and thrust bearings.
Sprockets are mounted on one end of each internally threaded screw and are connected together with a chain to drive the
two externally threaded screws in unison.
B. These trim tab actuator part numbers are affected by this individual component maintenance manual:
5565450-7 5565450-42 5565450-61 5565450-72 5565450-89 5565450-102
5565450-8 5565450-43 5565450-62 5565450-76 5565450-90
5565450-22 5565450- 51 5565450-63 5565450-77 5565450-91
5565450-23 5565450-52 5565450-64 5565450-78 5565450-92
5565450-30 5565450-53 5565450-65 5565450-79 5565450-93
5565450-32 5565450-54 5565450-66 5565450-80 5565450-94
5565450-34 5565450-55 5565450-67 5565450-81 5565450-95
5565450-36 5565450-56 5565450-68 5565450-82 5565450-201
5565450-38 5565450-59 5565450-70 5565450-87 5565450-98
5565450-41 5565450-60 5565450-71 5565450-88 5565450-99
NOTE 1: For information concerning actuators Part Numbers 5565450-7 and -8, refer to actuators Part
Numbers 5565450-22 and -23.
2. Operation
A. The trim tab actuator is controlled by an airplane cable-chain system, which rotates the primary sprocket of the actuator.
Secondary sprockets, connected together, rotate in unison and drive two internally threaded screws. The internally
threaded screws mate with two externally threaded screws, which will extend or retract as the internal screws rotate.
Bearings at each end of the actuator permit smooth operation of the screws. Refer to Figure 1.

Copyright © Textron Aviation Inc. Page 1 of 2

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 12:58:06 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
27-10-06-0 (Rev 14)

Figure 1 : Sheet 1 : Trim Tab Actuator

Copyright © Textron Aviation Inc. Page 2 of 2

TRIM TAB ACTUATOR - TESTING

1. Testing
A. Screw Travel (Refer to Illustrated Parts List, Figure 1001, Figure 1002, and Figure 1003).
(1) Test aileron actuator assembly by rotating primary sprocket (11) with fingers, while holding bearing end of extending
screws (46). Extending screws (46) should travel in and out of internal screws (30) smoothly with no indication of
binding.
(2) Test rudder actuator assembly by rotating primary sprocket (7) with fingers while holding bearing end of extending
screws (36). Extending screws (36) should travel in and out of internal screws (24) smoothly with no indication of
binding.
(3) Test elevator actuator assembly by rotating primary sprocket (10) with fingers while holding bearing end of extending
screws (95). Extending screws (95) should travel in and out of internal screws (82) smoothly with no indication of
binding.
B. End Play (Refer to Illustrated Parts List, Figure 1001, Figure 1002, and Figure 1003).
(1) Aileron actuator relative end movement between internal screws (30) and bearings (22) should be 0.004 to 0.006
inch with an ambient temperature of 70°F.
(2) Rudder actuator relative end movement between internal screws (24) and bearings (17) should be 0.004 to 0.006
inch with an ambient temperature of 70°F.
(3) Elevator actuator relative end movement between internal screws (82) and bearings (22) should be 0.004 to 0.006
inch with an ambient temperature of 70°F.
(4) End play of less than 0.004 inch may cause the actuator (aileron, rudder, elevator) to bind or lock during flight where
very cold temperatures are encountered. Actuators not within end play limits shall be reworked. Refer to Trim Tab
Actuator - Repair.
C. Screw Alignment. (Refer to Figure 1001, Figure 1002, and Figure 1003).
(1) Aileron actuator extending screws (45) shall align with each other equal distance from actuator within 0.010 inch.
Methods of checking alignment - measure the distance from the housing (26) to centerline of bearing (46) in each
screw (45), also, use a bolt for a slip fit check traveling through bearings (46).
(2) Rudder actuator extending screws (36) shall align with each other equal distance from actuator within 0.010 inch.
Methods of checking alignment - measure the distance from the housing (21) to centerline of bearing (37) in each
screw (36), also, use a bolt for a slip fit check traveling through bearings (37).
(3) Elevator actuator extending screws (95) shall align with each other equal distance from actuator within 0.010 inch.
Methods of checking alignment - measure the distance from the housing (78) to centerline of bearing (97), also use a
bolt for a slip fit check traveling through bearings (97).

Copyright © Textron Aviation Inc. Page 1 of 2

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 12:58:11 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
27-10-06-1 (Rev 9)

Figure 101 : Sheet 1 : Trim Tab Actuator Testing

Copyright © Textron Aviation Inc. Page 2 of 2

TRIM TAB ACTUATOR - DISASSEMBLY

1. Disassembly
A. Disassemble Aileron Actuator (Refer to Illustrated Parts List, Figure 1001).
(1) Remove chain guard (17) by removing screws (19).
(2) Drive groove pins (14) from secondary sprockets (13) and internal screws (30). Remove primary sprocket (11), plug
button (16), secondary sprockets (13), and chain (15).
NOTE: It may be necessary to apply heat not to exceed 180°F, to the internal screws (30) to break the
Loctite seal between internal screws (30) and primary sprocket (11).
(3) Starting with a short 1/16 inch pin punch and then using a progressively longer punch, drive groove pins (23 and 39)
from housing (26) and bearings (22 and 38).
NOTE: Prior to removal of bearings (22 and 38), identify position and location of each bearing relative
to the housing by using a scratch scribe or center punch. This will ensure proper alignment of
groove pin holes upon reassembly.
(4) Tapping lightly with a soft hammer against extending screws (46), remove bearings (22).
(5) Tapping lightly with a soft hammer against internal screws (30), drive bearings (38) from housing (26).
(6) On the 5565450-7, -22 and -32 actuator assemblies turn extending screws (46) counterclockwise until separated
from internal screws (30), remove bearings (38) and packings (34).
(7) On the 5565450-38, -41, -42, -43, -51, -52, -61, -62, -72 ,-78, -89, -90, -91, and -94 actuator assemblies, turn
extending screws (46) counterclockwise until separated from internal screws (30), remove bearing races (32),
bearings (31), bearings (38) and packings (34).
(8) If bearing (49) requires replacement, press bearing from extending screw (46) using a suitable arbor press and
mandrel.
B. Disassemble Rudder Actuator (Refer to Illustrated Parts List, Figure 1002).
(1) Remove chain guard (13) by removing screws (15).
(2) Drive groove pins (10) from secondary sprockets (9) and internal screws (24). Remove primary sprocket (7), plug
button (12), secondary sprockets (9), and chain (11).
NOTE: It may be necessary to apply heat not to exceed 180°F, to the internal screws (24) to break the
Loctite seal between internal screws (24) and primary sprocket (7).
(3) Starting with a short 1/16 inch pin punch and then using a progressively longer punch, drive groove pins (18 and 31)
from housing (21) and bearings (17 and 30).
NOTE: Prior to removal of bearings (17 and 30), identify position and location of each bearing relative
to the housing by using a scratch scribe or center punch. This will ensure proper alignment of
groove pin holes upon reassembly.
(4) Remove bearings (17) by tapping lightly with a soft hammer against extending screws (36).
(5) Drive bearing (30) from housing (21) by tapping lightly with a soft hammer against internal screws (24).
(6) Rotate extending screws (36) counterclockwise until separated from internal screws (24), remove bearing races (26),
bearings (25), bearings (30) and packings (32).
(7) If bearing (37) requires replacement, press bearing from screw (36) using a suitable arbor press and mandrel.
C. Disassemble Elevator Actuator (Refer to Illustrated Parts List, Figure 1003).
(1) Remove chain guard (19) by removing screws (20).
(2) Drive groove pins (13) from secondary sprockets (12) and internal screws (82). Remove primary sprocket (10), plug
button (15), secondary sprockets (12), and chain (14).
NOTE: It may be necessary to apply heat not to exceed 180°F, to the internal screws (82) to break the
Loctite seal between internal screws (82) and primary sprocket (10).
(3) Starting with a short 1/16 inch pin punch and then using a progressively longer punch, drive groove pins (23 and 89)
from housing (78) and bearings (22 and 88).
NOTE: Prior to removal of bearings (22 and 88), identify position and location of each bearing relative
to the housing by using a scratch scribe or center punch. This will ensure proper alignment of

Copyright © Textron Aviation Inc. Page 1 of 2

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 12:58:15 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
27-10-06-3 (Rev 12)

groove pin holes upon reassembly.

(4) Remove bearings (22) by tapping lightly with a soft hammer against extending screws (95).
(5) Drive bearing (88) from housing (78) by tapping lightly with a soft hammer against internal screws (82).
(6) Rotate extending screws (95) counterclockwise until separated from internal screws (82), remove bearing races (84),
bearings (83), bearings (88) and packings (90).
(7) If bearing (97) requires replacement, press bearing from extending screw (95) using a suitable arbor press and
mandrel.

Copyright © Textron Aviation Inc. Page 2 of 2

TRIM TAB ACTUATOR - CLEANING

1. Cleaning
A. Tools and Equipment
NOTE: Equivalent substitute may be used for the following listed item.
NAME NUMBER MANUFACTURER USE
Methyl n-Propyl Ketone Clean metal parts.
Solvent Blend Desoclean 110 PRC-DeSoto International Clean metal parts.
5426 SanFernando Rd.
Glendale, CA 94710
Naptha MIL-PRF-680 (Type Commercially Available Metal parts cleaning that
III) require soak cleaning.
B. Cleaning.
WARNING: Use only approved cleaning solvents and only in well-ventilated areas. Avoid inhaling solvent
vapors. Keep solvent and solvent containers away from sparks or open flame.
CAUTION: If bearings (46, aileron actuator), (37, rudder actuator), (97, elevator actuator) are not being
replaced, do not allow solvent to enter bearing.
(1) Clean metal parts with approved solvent. Apply approved solvent to all channels to ensure cleanliness. Thoroughly dry
all parts with filtered, dry, compressed air, lint-free cloth or lint-free disposable tissue.

Copyright © Textron Aviation Inc. Page 1 of 1

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 12:58:17 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
27-10-06-5 (Rev 5)

TRIM TAB ACTUATOR - CHECK

1. Check
A. Check parts as follows:
(1) Check all parts visually, preferably under magnification. When parts are suspected of irregularities or deformity,
additional inspection shall be administered to verify the service life of the part or the part shall be replaced.
(2) Check internal screws and extending screws for damaged threads or bends that may impair smooth operation.
(3) Check sprockets for chipped or worn teeth. Check for bent primary sprocket. Check alignment of secondary
sprockets.
(4) Check chain for wear.
(5) Check applicable parts for dimensional conformity, refer to Trim Tab Actuator - Fits and Clearances.
B. Discarded Components.
(1) Verify all defective items are discarded during assembly; this includes discarded packings and groove pins.
C. Trim Tab Actuator Assembly.
(1) Verify that lubrication is included when actuator is assembled.
(2) Verify screw alignment and that the extending screws are pinned together, refer to Testing.
(3) Verify that the assembled actuator is packaged for storage. Packaging shall consist of protective material to protect
assembly against moisture, dust and shock (shock being the result of falling from its stored position).
NOTE: Packaging not required when actuator assembly is to be returned to service immediately.

Copyright © Textron Aviation Inc. Page 1 of 1

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 12:58:19 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
27-10-06-6 (Rev 11)

TRIM TAB ACTUATOR - REPAIR

1. Repair
A. Finish.
NAME NUMBER MANUFACTURER USE
Lacquer 27H54958 335-566 Sherwin-Williams Finish coat.
(Vivid Orange) Industrial Coatings
630 E. 13th St.
Andover, KS 67002
Lacquer 27H511 (Vestal Sherwin-Williams Finish coat.
White)
Color Chemical Film Alodine 1203 Henkel (Parker Amchem) Protective treatment of
Treatment 32100 Stephenson Highway aluminum.
Madison Heights, MI 48071
Pretreatment Primer 728-013/702-701 Sherwin-Williams Pretreatment primer.
DOD-P-15328
Corrosion Resistant 513 x 419/910 x PRC-DeSoto International Corrosion protection primer.
Primer MIL-PRF- 942 5426 San Fernando Rd.
23377G or later. Glendale, CA 91209
Waterborne Corrosion 44-GN-60 /44-GN- Deft, Inc. Corrosion protection primer.
Resistant Primer 60 CATA 17151 Von Karman Ave.
Irvine, CA 92714
Waterborne Corrosion U-4800/U-4801 Sterling Laquer Manufacturing Co. Corrosion protection primer.
Resistant Primer MIL- 3150 Brannon St.
PRF-85582 St. Louis, MO 63139
(1) For cleaning actuator, refer to Trim Tab Actuator - Cleaning and for parts replacement, refer to Trim Tab Actuator -
Assembly.
(2) The finish on the actuator housing is to be repaired as follows:
(a) When the finish on the actuator housing has been damaged and bare metal is exposed, the finish shall be
repaired. Permissible to abrasive clean in lieu of chemically clean. Apply chemical film treatment and corrosion
resistant primer. Refer to the Model 500 Series Structural Repair Manual, Chapter 51, Protective Treatment of
Metal for application.
(3) The finish on the chain guard is the same as actuator housing, except on the chain guard, Nitrocellulose Lacquer has
been applied to aid control cable rigging.
B. Bearing Installation.
(1) Number of repairs is limited: Permissible to have one repair at an individual bearing location; the repair may be
either a repositioned bearing or a new bearing.
(2) New bearing installation; repositioning original bearing.
(a) At the time the actuator is assembled, a shim is inserted on the internal screw (sprocket end of the actuator)
prior to installing the bearing. The shim (laminated washer or suitable shim stock) shall be thick enough to
provide the internal screw with a minimum linear movement of 0.004 inch and a maximum linear movement of
0.006 inch at an ambient temperature of 70°F.
(b) On original bearing; rotate bearing 90 degrees from drilled groove pin hole alignment.
(c) Place a clamp across assembled actuator, holding bearings against the internal screw tight enough to prevent
linear movement of the internal screw.
(d) With the aid of a drill fixture, position the actuator assembly to drill two 0.094 inch diameter groove pin holes
through the actuator housing (same location as original 0.062 groove pin location) and through the bearing.
(e) During installation on all enlarged groove pin holes (0.094) install groove pin S2637-6Z11 in lieu of the 0.062
diameter groove pin.

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Model 500 Series Component Maintenance Manual (Rev 17)
27-10-06-6 (Rev 11)

(3) Disassemble actuator sufficiently to remove shim. Reassemble actuator in accordance with applicable Trim Tab
Actuator - Assembly procedure.

Copyright © Textron Aviation Inc. Page 2 of 2

TRIM TAB ACTUATOR - ASSEMBLY

1. Assemble Trim Tab Actuator
A. Assemble Aileron Trim Tab Actuator (Refer to Illustrated Parts List, Figure 1001, ).
CAUTION: Use 5565450-28 silicone grease. Use no substitutes.
(1) If bearings (49) have been removed from extending screws (46); apply corrosion resistant primer to exterior surface
of bearing (49), refer to the Model 500 Series Structrual Repair Manual, Chapter 51, Protective Treatment of Metal
for application. Press the bearing into extending screw (46).
(2) Install new packings (33) in bearings (37).
(3) Actuator Assembly 5565450-7, -22 and -32.
CAUTION: Verify that the extending screws (46) are the correct part. Actuator assembly 5565450-7, -22
and -32 requires an extending screw length of 5.00 inches, measured from center of bearing
(49) to the end of screw (46).
(a) Apply 5565450-28 lubricant to bearings (37) and install on extending screws (46); apply 5565450-28 lubricant to
threads of extending screws (46) and threads of internal screws (30) and thread internal screws (30) onto
extending screws (46).
NOTE: When original bearings (37) are to be reinstalled, observe identification reference marks to
ensure correct installation location. If new bearing (37) is installed, refer to procedural
step (9).
(b) Apply 5565450-28 lubricant to internal and extending screws liberally (pack); insert screws (internal and
extending) into housing (26). Proceed to following applicable procedural step.
(4) Actuator Assembly 5565450-42, -43, -51, -52, -61, -62, -72, -78 and -89.
CAUTION: Verify that the extending screws (46) are the correct part. Actuator assembly 5565450-42, -43, -
51, -52, -61, -62, -72, -78 and -89 require an extending screw length of 4.85 inches, measured
from center of bearing (49) to the end of screw (46).
(a) Apply 5565450-28 lubricant to bearings, threads of extending screws and internal screws; install bearings (37)
on extending screws (46); install bearing races (32) and bearings (31) on internal screws (30); thread internal
screws (30) onto extending screws (46).
NOTE: When original bearings (37) are to be reinstalled, observe identification reference marks to
ensure correct installation location. If new bearing (37) is installed, refer to procedural
step (9).
(b) Apply 5565450-28 lubricant to bearings and to the internal and extending screws liberally (pack); install bearing
races (32) and bearings (31) on internal screws (30); insert screws (internal and extending) into housing (26).
Proceed to following applicable procedural step.
(5) Actuator Assembly 5565450-38, -41, -90, -91 and -94.
CAUTION: Verify that the extending screws (46) are the correct part. Actuator assembly 5565450-38, -41, -
90, -91 and -94 requires an extending screw length of 5.00 inches, measured from center of
bearing (49) to the end of screw (46).
(a) Apply 5565450-28 lubricant to bearings, threads of extending screws and internal screws; install bearings (37)
on extending screws (46); install bearing races (32) and bearings (31) on internal screws (30); thread internal
screws (30) onto extending screws (46).
NOTE: When original bearings (37) are to be reinstalled, observe identification reference marks to
ensure correct installation location. If new bearing (37) is installed, procedural step (9).
(b) Apply 5565450-28 lubricant to bearings and to the internal and extending screws liberally (pack); install bearing
races (32) and bearings (31) on internal threads; insert screws (internal and extending) into housing (26).
Proceed to following applicable procedural step.
(6) Align groove pin holes in housing (26) and bearings (37) and install new groove pins (39). If new bearing (37) is
installed, refer to procedural step (9).
(7) Apply 5565450-28 lubricant on bearings (22); position bearings (22) on internal screws (30) and tapping lightly, drive
bearings (22) into housing (26) until groove pin holes in bearings (22) align with groove pin holes in housing (26).
Install new groove pins (23).

Copyright © Textron Aviation Inc. Page 1 of 4

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 12:58:21 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
27-10-06-7 (Rev 9)

(8) Operate the extending screw in and out 2 or 3 times, wipe off excess grease.
NOTE: When original bearings (22) are to be reinstalled, observe identification reference marks to
ensure correct installation location. If new bearing (22) is installed, refer to procedural step (9).
(9) Check linear movement of internal screws (30) refer to Trim Tab Actuator - Fits and Clearances.
(10) If new bearings (22 and/or 38) are being installed or lineal clearance of original bearing is not within limits, refer to
Trim Tab Actuator - Repair.
(11) Position secondary sprockets (13) on internal screws (30). Do not install a 5565452-2 secondary sprocket; rework
the 5565452-2 sprocket to a 5565452-3 configuration, refer to Trim Tab Actuator - Fits and Clearances. The
5565452-3 sprocket has an additional groove pin hole; this feature aids in rigging the actuator for extending screw
alignment.
(12) Apply Loctite number 609 to external shaft surface (mating surface) of the primary sprocket (11) and install primary
sprocket (11) by inserting primary sprocket (11) shaft into secondary sprocket (13) and internal screw (30). Align
groove pin holes (primary sprocket (11), secondary sprocket (13), internal screw (30) and install new groove pin (14).
The Loctite eliminates loose sprockets.
(13) Align the other secondary sprocket (13) groove pin holes with internal screw groove pin hole and install new groove
pin (14). Install plug (16) in secondary sprocket (13).
(14) Install chain (15) around secondary sprockets (13).
(a) Centerline of bearing (49) must be capable of adjusting to equal distance from the housing. If not, rotating one
secondary sprocket slightly before installing the chain will permit acceptable alignment. Maximum misalignment,
refer to Trim Tab Actuator - Testing.
(b) The chain includes a Type A spring lock type connecting link to connect chain for a continuous loop.
(15) Install chain guard (17) and secure with screws (19). Secure screws (19) with lock wire.
B. Assemble Rudder Trim Tab Actuator (Refer to Illustrated Parts List, , Figure 1002, and ).
CAUTION: Use 5565450-28 silicone grease. Use no substitutes.
(1) If bearings (37) have been removed from extending screws (36), apply corrosion resistant primer to exterior surface
of bearing (37), refer to the Model 500 Series Structural Repair Manual, Chapter 51, Protective Treatment of Metal
for application. Press bearing into extending screw (36).
(2) Install new packings (32) in bearings (30).
(3) Actuator Assembly 5565450-8, -23, -34, -53, -55, -59, -63, -65, -66, -67, -71 -76 and -77.
CAUTION: Verify that the extending screws (36) are the correct part. The actuator assembly requires an
extending screw length of 5.50 inches, measured from center of bearing (37) to the end of
screw (36).
(a) Apply 5565450-28 lubricant to bearings, threads of extending screws and internal screws; install bearings (30)
on extending screws (36); install bearing races (26) and bearings (25) on internal screws (24); thread internal
screws (24) onto extending screws (36).
NOTE: When original bearings (30) are to be reinstalled, observe identification reference marks to
ensure correct installation location. If new bearing (30) is installed, refer to procedural
step (8).
(b) Apply 5565450-28 lubricant to bearings and to the internal and extending screws liberally (pack); install bearing
races (26) and bearings (25) on internal screws (24); insert screws (internal and extending) into housing (21).
(4) Actuator Assembly 5565450-93
CAUTION: Verify that the extending screws (36) are the correct part. The actuator assembly 5565450-93
requires an extending screw length of 5.75 inches, measured from center of bearing (37) to the
end of screw (36).
(a) Apply 5565450-28 lubricant to bearings, threads of extending screws and internal screws; install bearings (30)
on extending screws (36); install bearing races (26) and bearings (25) on internal screws (24); thread internal
screws (24) onto extending screws (36).
NOTE: When original bearings (30) are to be reinstalled, observe identification reference marks to
ensure correct installation location. If new bearing (30) is installed, refer to procedural

Copyright © Textron Aviation Inc. Page 2 of 4

step (8).
(b) Apply 5565450-28 lubricant to bearings and to the internal and extending screws liberally (pack); install bearing
races (26) and bearings (25) on internal screws (24); insert screws (internal and extending) into housing (21).
(5) Align groove pin holes in housing (21) and bearings (30) and install new groove pins (31). If new bearing (30) is
installed, refer to procedural step (8).
(6) Apply 5565450-28 lubricant on bearings (17); position bearings (17) on internal screws (24) and tapping lightly, drive
bearings (17) into housing (21) until groove pin holes in bearings (17) align with groove pin holes in housing (21).
Install new groove pins (18).
(7) Operate the extending screw in and out 2 or 3 times, wipe off excess grease.
NOTE: When original bearings (17) are to be reinstalled, observe identification reference marks to
ensure correct installation location. If new bearing (17) is installed, refer to procedural step (8).
(8) Check linear movement of internal screws (24), refer to Trim Tab Actuator - Fits and Clearances.
(9) If new bearings (17 and/or 30) are being installed or lineal clearance of original bearing is not within limits, refer to
Trim Tab Actuator - Repair.
(10) Position secondary sprockets (9) on internal screws (24). Do not install a 5565452-2 sprocket, rework the 5565452-2
sprocket to a 5565452-3 configuration, refer to Trim Tab Actuator - Fits and Clearances. The 5565452-3 sprocket
has an additional groove pin hole; this feature aids in rigging the actuator for extending screw alignment.
(11) Apply Loctite number 609 to external shaft surface (mating surface) of the primary sprocket (7) and install primary
sprocket (7) by inserting primary sprocket (7) shaft into secondary sprocket (9) and internal screw (24). Align groove
pin holes in primary sprocket (7), secondary sprocket (9), internal screw (24) and install new groove pin (10). The
Loctite eliminates loose sprockets.
(12) Align the other secondary sprocket (9) groove pin holes with internal screw groove pin hole and install new groove pin
(10). Install plug (12) in secondary sprocket (9)
(13) Install chain (11) around secondary sprockets (9).
(a) Centerline of bearing (37) must be capable of adjusting to equal distance from the housing (21). If not, rotating
one secondary sprocket slightly before installing the chain will permit acceptable alignment. Maximum
misalignment, refer to Trim Tab Actuator - Testing.
(b) The chain includes a Type A spring lock type connecting link to connect chain for a continuous loop.
(14) Install chain guard (13) and secure with screws (15). Secure screws (15) with lock wire.
C. Assemble Elevator Trim Tab Actuator (Refer to Illustrated Parts List, , and Figure 1003 ).
CAUTION: Use 5565450-28 silicone grease. Use no substitutes.
(1) If bearing (97) has been removed from extending screw (95), apply corrosion resistant primer to exterior surface of
bearing (97), refer to the Model 500 Series Structural Repair Manual, Chapter 51, Protective Treatment of Metal for
application. Press bearing into extending screw (95).
(2) Install new packings (90) in bearings (88).
(3) Actuator Assembly 5565450-8, -23, -30, -34, -36, -54, -56, -60, -64, -65, -66, -68, -70, -76, -79, -80, -81, -82, -87 and
-88.
CAUTION: Verify that the extending screws (95) are the correct part. The actuator assembly 5565450-8, -
23, -30, -34, -36, -54, -56, -60, -64, -65, -66, -68, -70, -76, -79, -80, -81, -82, -87, and -88 requires an
extending screw length of 5.50 inches, measured from center of bearing (97) to the end of
screw (95).
(a) Apply 5565450-28 lubricant to bearings, threads of extending screws and internal screws; install bearings (88)
on extending screws (95); install bearing races (84) and bearings (83) on internal screws (82); thread internal
screws (82) onto extending screws (95).
NOTE: When original bearings (88) are to be reinstalled, observe identification reference marks to
ensure correct installation location. If new bearing (88) is installed, refer to procedural
step (8).
(b) Apply 5565450-28 lubricant to bearings and to the internal and extending screws liberally (pack); install bearing
races (84) and bearings (83) on internal screws (82); insert screws (internal and extending) into housing (78).

Copyright © Textron Aviation Inc. Page 3 of 4

(4) Actuator Assembly 5565450-92, -93 and -201.

CAUTION: Verify that the extending screws (95) are the correct part. The actuator assembly 5565450-92, -
93 and -201 requires an extending screw length of 5.75 inches, measured from center of
bearing (97) to the end of screw (95).
(a) Apply 5565450-28 lubricant to bearings, threads of extending screws and internal screws; install bearings (88)
on extending screws (95); install bearing races (84) and bearings (83) on internal screws (82); thread internal
screws (82) onto extending screws (95).
NOTE: When original bearings (88) are to be reinstalled, observe identification reference marks to
ensure correct installation location. If new bearing (88) is installed, refer to procedural
step (8).
(b) Apply 5565450-28 lubricant to bearings and to the internal and extending screws liberally (pack); install bearing
races (84) and bearings (83) on internal screws (82); insert screws (internal and extending) into housing (78).
(5) Align groove pin holes in housing (78) and bearings (88) and install new groove pins (89). If new bearing (88) is
installed, refer to procedural step (8).
(6) Apply 5565450-28 lubricant on bearings (22); position bearings (22) on internal screws (82) and tapping lightly, drive
bearings (22) into housing (78) until groove pin holes in bearings (22) align with groove pin holes in housing (78).
Install new groove pins (23).
(7) Operate the extending screw in and out 2 or 3 times; wipe off excess grease.
NOTE: When original bearings (22) are to be reinstalled, observe identification reference marks to
ensure correct installation location. If new bearing (22) is installed refer to procedural step (8).
(8) Check linear movement of internal screws (82), refer to Trim Tab Actuator - Fits and Clearances.
(9) If new bearings (22 and/or 88) are being installed or lineal clearance of original bearing is not within limits, refer to
Trim Tab Actuator - Repair.
(10) Position secondary sprockets (12) on internal screws (82). Do not install a 5565452-2 sprocket, rework the 5565452-
2 sprocket to a 5565452-3 configuration, refer to Trim Tab Actuator - Fits and Clearances. The 5565452-3 sprocket
has an additional groove pin hole; this feature aids in rigging the actuator for extending screw alignment.
(11) Apply Loctite number 609 to external shaft surface (mating surface) of the primary sprocket (10) and install primary
sprocket (10) by inserting primary sprocket (10) shaft into secondary sprocket (12) and internal screw (82). Align
groove pin holes (primary sprocket (10), secondary sprocket (12), internal screw (82), and install new groove pin (13).
The Loctite eliminates loose sprockets.
(12) Align the other secondary sprocket (12) groove pin holes with internal screw groove pin hole and install new groove
pin (13). Install plug (15) in secondary sprocket (12).
(13) Install chain (14) around secondary sprockets (12).
(a) Centerline of bearing (97) must be capable of adjusting to equal distance from the housing (78). If not, rotating
one secondary sprocket slightly before installing the chain will permit acceptable alignment. Maximum
misalignment, refer to Trim Tab Actuator - Testing.
(b) The chain includes a Type A spring lock type connecting link to connect chain for a continuous loop.
(14) Install chain guard (19) and secure with screws (20). Secure screws (20) with lock wire.

Copyright © Textron Aviation Inc. Page 4 of 4

TRIM TAB ACTUATOR - FITS AND CLEARANCES

1. Fits and Clearances
A. Bearing 5565450-4
A4340

(1) (2)

5596T1006

(1) 0.828 inch, +0.000, or -0.001 inch (21.62 mm, +0.00 or -0.025 mm) diameter
(2) 0.435 inch, +0.001, or -0.000 inch (11.05 mm, +0.025 or -0.000 mm) diameter
B. Bearing 5565450-16
A4340

(1) (2)

5596T1006

(1) 0.828 inch, +0.000, or -0.001 inch (21.62 mm, +0.00 or -0.025 mm) diameter
(2) 0.378 inch, +0.001, or -0.000 inch (9.60 mm, +0.025 or -0.000 mm) diameter
C. Bearing 5565450-18

(1) 0.828 inch, +0.000, or -0.001 inch (21.62 mm, +0.00 or -0.025 mm) diameter
(2) 0.435 inch, +0.001, or -0.000 inch (11.05 mm, +0.025 or -0.000 mm) diameter
(3) 0.3105 inch, +0.001, or -0.000 inch (7.89 mm, +0.025 or -0.000 mm) diameter
D. Bearing 5565450-19
A68675

(2)

(3) (1)

5596T1006

(1) 0.828 inch, +0.000, or -0.001 inch (21.62 mm, +0.00 or -0.025 mm) diameter
(2) 0.378 inch, +0.001, or -0.000 inch (9.60 mm, +0.025 or -0.000 mm) diameter
(3) 0.3105 inch, +0.001, or -0.000 inch (7.89 mm, +0.025 or -0.000 mm) diameter

Copyright © Textron Aviation Inc. Page 1 of 9

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 12:58:23 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
27-10-06-8 (Rev 14)

E. Bearing 5565450-46 (NOTE)

A68675

(2)

(3) (1)

5596T1006

(1) 0.828 inch, +0.000, or -0.001 inch (21.62 mm, +0.00 or -0.025 mm) diameter
(2) 0.383 inch, +0.001, or -0.001 inch (9.73 mm, +0.025 or -0.025 mm) diameter
(3) 0.311 inch, +0.001, or -0.000 inch (7.90 mm, +0.025 or -0.000 mm) diameter
NOTE: Diameter (1) Shall be concentric to (3) within 0.002 Inch (0.051 mm) Total Indicator Reading.
NOTE: Diameter (2) Shall be concentric to (3) within 0.002 Inch (0.051 mm) Total Indicator Reading.
F. Bearing 5565450-47
A4340

(1) (2)

5596T1006

(1) 0.828 inch, +0.000, or -0.001 inch (21.62 mm, +0.00 or -0.025 mm) diameter
(2) 0.435 inch, +0.001, or -0.000 inch (11.05 mm, +0.025 or -0.000 mm) diameter
NOTE: Diameter (1) Shall be concentric to (2) within 0.002 Inch (0.051 mm) Total Indicator Reading.
G. Internal Screw 5565450-24

(1) 0.4325 inch, +0.000, or -0.001 inch (10.99 mm, +0.00 or -0.025 mm) diameter
(2) 0.432 inch, +0.001, or -0.000 inch (10.97 mm, +0.25 or -0.000 mm) diameter
(3) 0.250 inch (typical) (6.35 mm)
(4) 0.200 inch (5.08 mm)
(5) 1.05 inch (26.67 mm)
H. Internal Screw 5565450-25

Copyright © Textron Aviation Inc. Page 2 of 9

(1) 0.375 inch, +0.000, or -0.010 inch (9.53 mm, +0.00 or -0.25 mm) diameter
(2) 0.432 inch, +0.010, or -0.000 inch (10.97 mm, +0.25 or -0.000 mm) diameter
(3) 0.100 inch (typical) (2.54 mm)
(4) 0.310 inch (7.87 mm)
(5) 1.19 inch (30.23 mm)
I. Internal Screw 5565450-39

(1)

(1) (2)
SHALL BE CONCENTRIC TO (1) WITHIN
0.003 INCH TOTAL INDICATOR READING 5596T1009

(1) 0.375 inch, +0.001, or -0.000 inch (9.53 mm, +0.025 or -0.00 mm) diameter
(2) 0.100 inch (typical) (2.54 mm)
(3) 3.97 inch (100.8 mm)
(4) 1.19 inch (30.23 mm)
K. Internal Screw 5565450-45

Copyright © Textron Aviation Inc. Page 3 of 9

A4343
(3)
(4)

(1)

(1) (2)
SHALL BE CONCENTRIC TO (1) WITHIN
0.003 INCH TOTAL INDICATOR READING 5596T1009

(1) 0.375 inch, +0.001, or -0.000 inch (9.53 mm, +0.025 or -0.00 mm) diameter
(2) 0.100 inch (typical) (2.54 mm)
(3) 4.97 inch (126.2 mm)
(4) 1.19 inch (30.23 mm)
L. Internal Screw 5565450-74
A4343
(3)
(4)

(1)

(1) (2)
SHALL BE CONCENTRIC TO (1) WITHIN
0.003 INCH TOTAL INDICATOR READING 5596T1009

(1) 0.375 inch, +0.001, or -0.000 inch (9.53 mm, +0.025 or -0.00 mm) diameter
(2) 0.100 inch (typical) (2.54 mm)
(3) 7.59 inch (192.8 mm)
(4) 1.19 inch (30.23 mm)
M. Sprocket 5565452-1

(1) 0.435 inch, +0.001, or -0.001 inch (21.62 mm, +0.025 or -0.025 mm) diameter
(2) 0.093 inch (2.36 mm) diameter
N. Sprocket 5565452-2

Copyright © Textron Aviation Inc. Page 4 of 9

(1) 0.3375 inch, +0.001, or -0.000 inch (8.57 mm, +0.025 or -0.00 mm) diameter
(2) 0.093 inch (2.36 mm) diameter
O. Sprocket 5565452-3

(1) 0.3375 inch, +0.001, or -0.000 inch (8.57 mm, +0.025 or -0.00 mm) diameter
(2) 0.093 inch (2.36 mm) diameter
(3) 0.110 inch (2.79 mm)
P. Screw 5565451-3
A3805

4
2
1
3

5 THREAD 5/16 − 18 UNC −3A

QUADRUPLE THREADS.
5596T1022

(1) 2.25 inch (57.15 mm)

(2) 5.00 inch (127.0 mm)
(3) 0.3075 inch, +0.001 or -0.000 inch (7.81 mm, +0.025 or -0.00 mm) diameter
(4) 0.40 inch (10.16 mm)
(5) 0.4995 inch, +0.001 or -0.000 inch (12.687 mm, +0.025 or -0.00 mm) diameter
Q. Screw 5565451-4

Copyright © Textron Aviation Inc. Page 5 of 9

A3805

4
2
1
3

5 THREAD 5/16 − 18 UNC −3A

QUADRUPLE THREADS.
5596T1022

(1) 2.70 inch (53.34 mm)

(2) 5.50 inch (139.7 mm)
(3) 0.3075 inch, +0.001 or -0.000 inch (7.81 mm, +0.025 or -0.00 mm) diameter
(4) 0.40 inch (10.16 mm)
(5) 0.4995 inch, +0.001 or -0.000 inch (12.687 mm, +0.025 or -0.00 mm) diameter
R. Screw 5565451-6
A3805

4
2
1
3

5 THREAD 5/16 − 18 UNC −3A

QUADRUPLE THREADS.
5596T1022

(1) 2.10 inch (53.34 mm)

(2) 4.85 inch (123.2 mm)
(3) 0.3075 inch, +0.001 or -0.000 inch (7.81 mm, +0.025 or -0.00 mm) diameter
(4) 0.40 inch (10.16 mm)
(5) 0.4995 inch, +0.001 or -0.000 inch (12.687 mm, +0.025 or -0.00 mm) diameter
S. Screw 5565451-7
A3805

4
2
1
3

5 THREAD 5/16 − 18 UNC −3A

QUADRUPLE THREADS.
5596T1022

(1) 2.70 inch (53.34 mm)

Copyright © Textron Aviation Inc. Page 6 of 9

A3805

4
2
1
3

5 THREAD 5/16 − 18 UNC −3A

QUADRUPLE THREADS.
5596T1022

(1) 2.10 inch (53.34 mm)

(1) 2.70 inch (53.34 mm)

(2) 5.50 inch (139.7 mm)
(3) 0.3075 inch, +0.001 or -0.000 inch (7.81 mm, +0.025 or -0.00 mm) diameter
V. Screw 5565451-16

(1) 2.10 inch (53.34 mm)

(2) 4.85 inch (123.2 mm)
(3) 0.3075 inch, +0.001 or -0.000 inch (7.81 mm, +0.025 or -0.00 mm) diameter
W. Screw 5565451-21

Copyright © Textron Aviation Inc. Page 7 of 9

(1) 2.25 inch (57.15 mm)

(2) 5.75 inch (146.1 mm)
(3) 0.3075 inch, +0.001 or -0.000 inch (7.81 mm, +0.025 or -0.00 mm) diameter
X. Screw 5565451-22

(1) 1.95 inch (49.53 mm)

(2) 5.00 inch (127.0 mm)
(3) 0.3075 inch, +0.001 or -0.000 inch (7.81 mm, +0.025 or -0.00 mm) diameter
Y. Actuator Housing

Copyright © Textron Aviation Inc. Page 8 of 9

(1) 0.828 inch (21.03 mm) diameter

(2) 0.828 inch (21.03 mm) diameter
(3) 1.50 inch, +0.000 or -0.030 inch (38.10 mm, +0.00 or -0.76 mm)
NOTE: (2) Shall be parallel to (1) within 0.005 Inch (0.127 mm) Total Indicator Reading.
NOTE: (4) Shall be concentric to (1) within 0.003 Inch (0.076 mm) Total Indicator Reading.
NOTE: (5) Shall be concentric to (2) within 0.003 Inch (0.076 mm) Total Indicator Reading.
Z. Actuator Assembly
A4346
1

5596T1007

(1) Internal movement between internal screw and bearing (longitudinal) shall be 0.004 inch (0.102 mm) minimum and
0.006 inch (0.152 mm) maximum to prevent binding under extreme temperature variations.

Copyright © Textron Aviation Inc. Page 9 of 9

AILERON TRIM TAB ACTUATOR ASSEMBLY

NOMENCLATURE EFFECTIVITY UNITS
PER
ITEM PART NUMBER 1 2 3 4 5 6 7 FROM TO ASSY
- AILERON TRIM TAB ACTUATOR
ASSEMBLY

- 1 5565450-7 . ACTUATOR ASSY-TRIM A NP

TAB FSO 6660361-22

- . ACTUATOR ASSY-TRIM
2 5565450-22 B NP
TAB FSO 6660361-22

- . ACTUATOR ASSY-TRIM
3 5565450-32 C NP
TAB FSO 5565450-91
ACTUATOR ASSY-TRIM
- 4 5565450-38 . D NP
TAB FSO 6660361-22
- . ACTUATOR ASSY-TRIM
5 5565450-41 E NP
TAB FSO 6660361-22

- . ACTUATOR ASSY-TRIM
6 5565450-42 F NP
TAB FSO 6660361-22

- . ACTUATOR ASSY-TRIM
7 5565450-43 G NP
TAB FSO 5565450-91
ACTUATOR ASSY-TRIM
- 8 5565450-51 . H NP
TAB FSO 6660361-22

- . ACTUATOR ASSY-TRIM
9 5565450-52 J NP
TAB FSO 5565450-91
- . ACTUATOR ASSY-TRIM
9A 5565450-61 K NP
TAB FSO 6660361-22

- . ACTUATOR ASSY-TRIM
9B 5565450-62 L NP
TAB FSO 5565450-91

- . ACTUATOR ASSY-TRIM
9C 5565450-72 M NP
TAB FSO 6660361-22

- . ACTUATOR ASSY-TRIM
9D 5565450-78 N NP
TAB FSO 5565450-91
ACTUATOR ASSY-TRIM
- 9E 5565450-89 . P NP
TAB FSO 5565450-94
- . ACTUATOR ASSY-TRIM
9F 5565450-90 Q NP
TAB FSO 6660361-22

- . ACTUATOR ASSY-TRIM
9G 5565450-91 R 01
TAB

- . ACTUATOR ASSY-TRIM
9H 5565450-94 S 01
TAB
- 10 5565450-6 . . SPROCKET-PRIMARY A 01
11 5565450-20 . . SPROCKET-PRIMARY B THRU S 01
- . . SPROCKET-
12 5565452-1 A THRU C 02
SECONDARY

. . SPROCKET-
13 5565452-3 D THRU S 02
SECONDARY

Copyright © Textron Aviation Inc. Page 1 of 4

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 12:58:32 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
27-10-06-1001 (Rev 13)

ATTACHING
PARTS
14 S2637-6Z11 . . PIN-GROOVE A THRU S 02
15 5565450-11 . . CHAIN 01
- 15A C419175 . . LINK ASSY A THRU S 01
16 CM2692-10-1S . . PLUG BUTTON A THRU S 01
. . GUARD-CHAIN FSO
17 5565450-1 A,B,D,F,H,K 01
6565021-1

- . . GUARD-CHAIN FSO
18 5565450-33 C,E,G,J,L 01
6565021-4
- 18A 6565021-1 . . GUARD-CHAIN M,Q 01
- 18B 6565021-4 . . GUARD-CHAIN N,R 01
- 18C 6565021-5 . . GUARD-CHAIN P,S 01
ATTACHING
PARTS
19 MS35265-26 . . SCREW A THRU S 02
---*---
- 20 5565450-4 . . BEARING A&B 02
- 21 5565450-16 . . BEARING C THRU G 02
22 5565450-47 . . BEARING H THRU S 02
ATTACHING
PARTS
23 S2637-4Z10 . . PIN-GROOVE A THRU S 02
---*---
- 24 5565450-9 . . HOUSING-ACTUATOR A 01
FSO 5565450-26
- 25 5565450-26 . . HOUSING-ACTUATOR A THRU G 01
26 5565450-48 . . HOUSING-ACTUATOR H THRU S 01
- . . SCREW-INTERNAL
27 5565450-2 A 02
FSO 5565450-24
- 28 5565450-24 . . SCREW-INTERNAL A,B,C 02
- 29 5565450-39 . . SCREW-INTERNAL D THRU G 02
30 5565450-44 . . SCREW-INTERNAL H THRU S 02
31 S2013-3 . . BEARING D THRU S 04
32 S2014-10 . . RACE D THRU S 08
33 MS28775-011 . . O-RING A THRU S 02
- 34 5565450-5 . . BEARING A 02
- 35 5565450-18 . . BEARING B,C 02
- 36 5565450-19 . . BEARING D THRU G 02
37 5565450-46 . . BEARING H THRU S 02
ATTACHING
PARTS
38 S2637-4Z10 . . PIN-GROOVE A THRU S 02

Copyright © Textron Aviation Inc. Page 2 of 4

---*---
- . . SCREW ASSY FSO
39 5565451-1 A THRU E NP
5565451-20
SCREW ASSY FSO
- 40 5565451-5 . . F&G NP
5565451-20
- . . SCREW ASSY FSO
41 5565451-10 H&J NP
5565451-20
SCREW ASSY FSO
- 42 5565451-18 . . K THRU P NP
5565451-20
- 43 5565451-20 . . SCREW ASSY Q THRU S 02
- 44 5565451-3 . . . SCREW A THRU E 01
- 45 5565451-6 . . . SCREW F THRU G 01
46 5565451-8 . . . SCREW H&J 01
- 47 5565451-16 . . . SCREW K THRU P 01
- 48 5565451-22 . . . SCREW Q THRU S 01
49 S2629-1 . . . BEARING 01
- Item Not Illustrated

Copyright © Textron Aviation Inc. Page 3 of 4

Figure 1001 : Sheet 1 : AILERON TRIM TAB ACTUATOR ASSEMBLY

A18054

17
14

13
11

15 19
16 13 38

26
32
31
22 32

37
33
32
32 31
46
30

6561T2002

Copyright © Textron Aviation Inc. Page 4 of 4

RUDDER TRIM TAB ACTUATOR ASSEMBLY

NOMENCLATURE EFFECTIVITY UNITS
PER
ITEM PART NUMBER 1 2 3 4 5 6 7 FROM TO ASSY
- RUDDER TRIM TAB ACTUATOR
ASSEMBLY

- 1 5565450-8 . ACTUATOR ASSY-TRIM A NP

TAB FSO 5565450-71

- . ACTUATOR ASSY-TRIM
2 5565450-23 B NP
TAB FSO 5565450-71

- . ACTUATOR ASSY-TRIM
3 5565450-34 C NP
TAB FSO 5565450-65
ACTUATOR ASSY-TRIM
- 4 5565450-53 . D NP
TAB FSO 5565450-71
- . ACTUATOR ASSY-TRIM
5 5565450-63 E NP
TAB FSO 5565450-71

- . ACTUATOR ASSY-TRIM
5A 5565450-59 F NP
TAB FSO 5565450-67

- . ACTUATOR ASSY-TRIM
5B 5565450-55 G NP
TAB FSO 5565450-66
ACTUATOR ASSY-TRIM
- 5C 5565450-66 . H NP
TAB FSO 5565450-93

- . ACTUATOR ASSY-TRIM
5D 5565450-67 J 01
TAB
- . ACTUATOR ASSY-TRIM
5E 5565450-71 K NP R
TAB FSO 5565450-102

- . ACTUATOR ASSY-TRIM
5F 5565450-77 L NP
TAB FSO 5565450-93

- . ACTUATOR ASSY-TRIM
5G 5565450-65 M 01
TAB

- . ACTUATOR ASSY-TRIM
5H 5565450-76 N 01
TAB
ACTUATOR ASSY-TRIM
- 5J 5565450-93 . P 01
TAB
- . ACTUATOR ASSY-TRIM
5K 5565450-102 Q 01 R
TAB
- 6 5565450-13 . . SPROCKET-PRIMARY A 01
. . B THRU K,
7 5565450-21 SPROCKET-PRIMARY 01 R
M,N,Q
- 7A 5565450-31 . . SPROCKET-PRIMARY L,P 01
SPROCKET-
- 8 5565452-2 . . SECONDARY FSO A &B NP
5565452-3

9 5565452-3 . . SPROCKET- B THRU Q 02 R

SECONDARY
ATTACHING
PARTS

Copyright © Textron Aviation Inc. Page 1 of 4

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 12:58:34 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
27-10-06-1002 (Rev 14)

10 S2637-6Z11 . . PIN-GROOVE 02
---*---
11 5565450-11 . . CHAIN 01
- 11A C419175 . . LINK ASSY 01
12 CM2692-10S1 . . PLUG BUTTON 01

. . GUARD-CHAIN FSO
13 5565450-17 A,B,D NP
6565019-2
- 14 5565450-35 . . GUARD-CHAIN C,E,H,M 01
- 14A 5565450-57 . . GUARD-CHAIN F &J 01
- 14B 6565019-2 . . GUARD-CHAIN K 01
- 14C 6565019-3 . . GUARD-CHAIN L,P 01
- 14D 6565019-4 . . GUARD-CHAIN N 01
ATTACHING
PARTS
15 MS35265-26 . . SCREW 02
---*---
- 16 5565450-16 . . BEARING-FORWARD A THRU C 02
17 5565450-47 . . BEARING-FORWARD C THRU Q 02 R
ATTACHING
PARTS
18 S2637-4Z10 . . PIN-GROOVE 04
---*---
- . . HOUSING-ACTUATOR
19 5565450-10 A NP
FSO 5565450-27
- 20 5565450-27 . . HOUSING-ACTUATOR B &C 01
. . D THRU
21 5565450-49 HOUSING-ACTUATOR 01
K,M,N
- 21A 5565450-50 . . HOUSING-ACTUATOR L,P 01
- 21B 5565450-101 . . HOUSING-ACTUATOR Q 01 R
- 21C MS15001-3 . . FITTING Q 02 R
SCREW-INTERNAL
- 22 5565450-3 . . A NP
FSO 5565450-25
- 23 5565450-25 . . SCREW-INTERNAL A THRU C 02
24 5565450-45 . . SCREW-INTERNAL D THRU P 02
- 24A 5565450-100 . . SCREW-INTERNAL Q 02 R
25 S2013-3 . . BEARING 04
26 S2014-10 . . RACE 08
- 27 . . DELETED-NOT USED
- 28 5565450-15 . . BEARING A 02
- 29 5565450-19 . . BEARING B &C 02
30 5565450-46 . . BEARING D THRU Q 02 R
ATTACHING
PARTS

Copyright © Textron Aviation Inc. Page 2 of 4

31 S2637-4Z10 . . PIN-GROOVE 04
---*---
32 MS28775-011 . . O-RING 02
SCREW ASSY FSO
- 33 5565451-2 . . A THRU C NP
5565451-19
- . . SCREW ASSY FSO
34 5565451-9 D THRU F NP
5565451-19
SCREW ASSY FSO G THRU
- 34A 5565451-17 . . NP R
5565451-19 N,Q
- 34B 5565451-19 . . SCREW ASSY P 02
- 35 5565451-4 . . . SCREW A THRU C 01
36 5565451-7 . . . SCREW D THRU F 01
- 36A 5565451-15 . . . SCREW G THRU N 01
- 36B 5565451-21 . . . SCREW P 01
37 S2629-1 . . . BEARING 01
- Item Not Illustrated

Copyright © Textron Aviation Inc. Page 3 of 4

Figure 1002 : Sheet 1 : RUDDER TRIM TAB ACTUATOR ASSEMBLY

Copyright © Textron Aviation Inc. Page 4 of 4

ELEVATOR TRIM TAB ACTUATOR ASSEMBLY

NOMENCLATURE EFFECTIVITY UNITS
PER
ITEM PART NUMBER 1 2 3 4 5 6 7 FROM TO ASSY
- ELEVATOR TRIM TAB ACTUATOR
ASSEMBLY

- 1 5565450-8 . ACTUATOR ASSY-TRIM A NP

TAB FSO 6565141-2

- . ACTUATOR ASSY-TRIM
2 5565450-23 B NP
TAB FSO 6565141-2

- . ACTUATOR ASSY-TRIM
3 5565450-30 C NP
TAB FSO 6565141-2
ACTUATOR ASSY-TRIM
- 4 5565450-34 . D NP
TAB FSO 5565450-76
- . ACTUATOR ASSY-TRIM
5 5565450-36 E NP
TAB FSO 5565450-66

- . ACTUATOR ASSY-TRIM
6 5565450-54 F NP
TAB FSO 6565141-2

- . ACTUATOR ASSY-TRIM
7 5565450-56 G NP
TAB FSO 5565450-66
ACTUATOR ASSY-TRIM
- 7A 5565450-60 . H NP
TAB FSO 5565450-93

- . ACTUATOR ASSY-TRIM
7B 5565450-64 J NP
TAB FSO 6565141-2
- . ACTUATOR ASSY-TRIM
7C 5565450-65 K NP
TAB FSO 5565450-76

- . ACTUATOR ASSY-TRIM
7D 5565450-68 L NP
TAB FSO 5565450-93

- . ACTUATOR ASSY-TRIM
7E 5565450-70 M 01
TAB

- . ACTUATOR ASSY-TRIM
7F 5565450-76 N 01
TAB
ACTUATOR ASSY-TRIM
- 7G 5565450-79 . P NP
TAB FSO 5565450-201
- . ACTUATOR ASSY-TRIM
7H 5565450-80 Q NP
TAB FSO 6565141-2

- . ACTUATOR ASSY-TRIM
7J 5565450-81 R NP
TAB FSO 6361215-21

- . ACTUATOR ASSY-TRIM
7K 5565450-82 S NP
TAB FSO 6361215-22
- . ACTUATOR ASSY-TRIM
7L 5565450-87 T NP
TAB FSO 6361215-29
- . ACTUATOR ASSY-TRIM
7M 5565450-88 U NP
TAB FSO 6361215-30

- . ACTUATOR ASSY-TRIM
7N 5565450-92 V NP
TAB FS0 6565141-2

Copyright © Textron Aviation Inc. Page 1 of 6

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 12:58:39 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
27-10-06-1003 (Rev 13)

- . ACTUATOR ASSY-TRIM
7P 5565450-93 W 01
TAB

- . ACTUATOR ASSY-TRIM
7Q 5565450-201 X 01
TAB
- . ACTUATOR ASSY-TRIM
7R 5565450-95 Y NP
TAB FSO 6565141-1
- . ACTUATOR ASSY TRIM
7S 5565450-98 Z NP
TAB FSO 6565141-2

- . ACTUATOR ASSY-TRIM
7T 5565450-99 AA NP
TAB FSO 6565141-1

- . ACTUATOR ASSY REFER

7U 6565141-2 01
TO 27-10-08 FIGURE 1001
- . ACTUATOR ASSY REFER
7V 6565141-1 01
TO 27-10-08 FIGURE 1001
- 8 5565450-13 . . SPROCKET-PRIMARY A 01
- 9 5565450-21 . . SPROCKET-PRIMARY B,D,K & N 01
C,E THRU
10 5565450-31 . . SPROCKET-PRIMARY J,L & M & P 01
THRU AA
SPROCKET-
- 11 5565452-2 . . SECONDARY FSO A,B,C NP
5565452-3

. . SPROCKET-
12 5565452-3 B THRU AA 02
SECONDARY
ATTACHING
PARTS
13 S2637-6Z11 . . GROOVE PIN 02
---*---
14 5565450-11 . . CHAIN 01
- 14A C419175 . . LINK LINK ASSY 01
15 CM2692-10J1S . . PLUG BUTTON Y,Z,AA 01 R
GUARD-CHAIN FSO
- 16 5565450-17 . . A &B NP
6565019-2
GUARD-CHAIN FSO
- 17 5565450-29 . . C F& J NP
6565019-1
- . . GUARD-CHAIN FSO
18 5565450-35 D NP
6565019-3
GUARD-CHAIN FSO
19 5565450-37 . . E,G& K NP
6565019-4
- 19A 5565450-58 . . GUARD-CHAIN H&L 01
- 19B 6565019-1 . . GUARD-CHAIN M 01
- 19C 6565019-2 . . GUARD-CHAIN A&B 01
- 19D 6565019-3 . . GUARD-CHAIN N,V 01
- 19E 6565019-4 . . GUARD-CHAIN E G& K 01
- 19F 6565019-5 . . GUARD-CHAIN P,R,X,Y,AA 01

Copyright © Textron Aviation Inc. Page 2 of 6

- 19G 6565019-6 . . GUARD-CHAIN Q,S,W,Z 01

- 19H 6565019-9 . . GUARD-CHAIN T 01
- 19J 6565019-10 . . GUARD-CHAIN U 01
ATTACHING
PARTS
20 MS35265-26 . . SCREW 02
---*---
- 21 5565450-16 . . BEARING-FORWARD A THRU E 02
22 5565450-47 . . BEARING-FORWARD F THRU AA 02
ATTACHING
PARTS
23 S2637-4Z10 . . GROOVE PIN A THRU AA 04
---*---

NOMENCLATURE EFFECTIVITY UNITS

PER
ITEM PART NUMBER 1 2 3 4 5 6 7 FROM TO ASSY
ELEVATOR TRIM TAB ACTUATOR
-
ASSEMBLY
- . . HOUSING-ACTUATOR
75 5565450-10 A NP
FSO 5565450-27
- 76 5565450-27 . . HOUSING-ACTUATOR A THRU D 01
- 77 5565450-40 . . HOUSING-ACTUATOR E 01
78 5565450-49 . . HOUSING-ACTUATOR F,J,M,N,P,Q,Y 01
- 79 5565450-50 . . HOUSING-ACTUATOR G,H,K & L 01
- 79A 5565450-73 . . HOUSING-ACTUATOR R THRU X 01
- 79B 5565450-101 . . HOUSING-ACTUATOR Z,AA 01
79C MS15001-3 . . FITTING Z,AA 02
- . . SCREW-INTERNAL
80 5565450-3 A NP
FSO 5565450-25
- 81 5565450-25 . . SCREW-INTERNAL A THRU E 02
. . F THRU
82 5565450-45 SCREW-INTERNAL 02
Q,V,W,X,Y
- 82A 5565450-74 . . SCREW-INTERNAL R THRU U 02
- 82B 5565450-100 . . SCREW-INTERNAL Z,AA 02
83 S2013-3 . . BEARING 04
84 S2014-10 . . RACE 08
- 85 . . DELETED-NOT USED
- 86 5565450-15 . . BEARING-AFT A 02
- 87 5565450-19 . . BEARING-AFT B THRU E 02
88 5565450-46 . . BEARING-AFT F THRU AA 02
ATTACHING
PARTS
89 S2637-4Z10 . . PIN-GROOVE 04

Copyright © Textron Aviation Inc. Page 3 of 6

---*---
90 MS28775-011 . . O-RING 02
- . . SCREW ASSY FSO
91 5565451-2 A THRU E NP
5565451-19
- . . SCREW ASSY FSO
92 5565451-9 F THRU H NP
5565451-19
SCREW ASSY FSO
- 93 5565451-17 . . J THRU U NP
5565451-19
- 93A 5565451-19 . . SCREW ASSY V THRU AA 01
- 94 5565451-4 . . . SCREW A THRU E 01
95 5565451-7 . . . SCREW F THRU H 01
- 96 5565451-15 . . . SCREW J THRU U 01
- 96A 5565451-21 . . . SCREW V THRU AA 01
97 S2629-1 . . . BEARING 01
- Item Not Illustrated

Copyright © Textron Aviation Inc. Page 4 of 6

Figure 1003 : Sheet 1 : ELEVATOR TRIM TAB ACTUATOR ASSEMBLY

Copyright © Textron Aviation Inc. Page 5 of 6

Figure 1003 : Sheet 2 : ELEVATOR TRIM TAB ACTUATOR ASSEMBLY

A18063

78 89

79C
84
83
84 88
97
90
84
83
84
95

6563T2001

Copyright © Textron Aviation Inc. Page 6 of 6

TRIM TAB ACTUATOR - ILLUSTRATED PARTS LIST

1. Illustrated Parts List
A. Introduction
(1) The Illustrated Parts List will help the customer to order, keep, and supply the rudder trim actuator components. It will
also identify new and reclaimed parts. It is not approved for any other purpose.
(2) This parts list includes the trim tab actuator part numbers:
6361215-13 6361215-14 6361215-21 6361215-22 6361215-23
6361215-24 6361215-29 6361215-30 6361215-31
6361215-32
6561194-1 6561194-3
6660361-16 6660361-18 6660361-23 6660361-22 6660361-25
6660361-29
(3) The indention system used in the detailed parts list of this catalog shows the relationship of one part to another. For a
given item, the indention code shows a general heading at the extreme left position and continues with indented
columns until the end detail is reached as follows:
A18017
1234567
Installation
Detail Parts for Installation
Assembly
Attaching Parts for Assembly
Detail Parts for Assembly
Subassembly
Attaching Parts for Subassembly
Detail Parts for Subassembly
Sub−Subassembly
Attaching Parts for Sub−Subassembly
Detail Parts for Sub−Subassembly

(4) The quantities given in the UNITS PER ASSY column of the parts list are the total number of parts used at the
indicated location for that assembly. Component parts that are indented under the assembly show the quantity used
in the assembly. The quantities are not necessarily the total used per installation.
(5) Effectivity for detail parts of assemblies in this technical manual is listed in the EFFECT column. The numbers listed
for the assembly also apply to the code for the detail parts specific to that assembly. If no numbers are shown in the
EFFECT column, that detail part is used in all assemblies listed.
(6) When a part of later design is not interchangeable with the part that it replaces, both parts that apply to the particular
usage are listed. The individual part usage is listed in the EFFECT column. Make sure you find out the proper use
when you send an order to make sure the correct part is received.
(7) The basic number identifies the Cessna drawing only. Each installation, assembly, or detail part is assigned a part
number which has a drawing number and a dash number.
A12537
EXAMPLE:
Part Number
6707005 − 7

Basic Number Dash Number

(Drawing Identification
Only)

NOTE: Parts that have a dash 400 series stamp are for internal control purposes only and must not be
used by the operator to order or to identify parts.

Copyright © Textron Aviation Inc. Page 1 of 2

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 12:58:44 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
27-10-07-10 (Rev 14)

B. For Vendor names and addresses with Federal Supply Codes, refer to Introduction - Supplier Address List.

Copyright © Textron Aviation Inc. Page 2 of 2

TRIM TAB ACTUATOR - DESCRIPTION AND OPERATION

1. Description
A. The trim tab actuator incorporates two internally threaded screws, two externally threaded screws and bearings. Sprockets
are mounted on one end of each drive screw and are connected together with a chain to drive the two extending screws in
unison.
B. These trim tab actuator part numbers are affected by this individual component maintenance manual:
6361215-13 6361215-14 6361215-21 6361215-22 6361215-23
6361215-24 6361215-29 6361215-30 6361215-31
6361215-32
6561194-1 6561194-3
6660361-16 6660361-18 6660361-22 6660361-23 6660361-25
6660361-29
2. Operation
A. The trim tab actuator is controlled by an airplane cable-chain system which rotates the primary sprocket of the actuator
(Refer to Figure 1). Secondary sprockets, connected together, rotate in unison and drive two externally threaded screws.
The internally threaded screws mate with two externally threaded screws which will extend or retract as the internal screws
rotate. Bearings at each end of the actuator permit smooth operation of the screws.

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Model 500 Series Component Maintenance Manual (Rev 17)
27-10-07-0 (Rev 14)

Figure 1 : Sheet 1 : Trim Tab Actuator

Copyright © Textron Aviation Inc. Page 2 of 2

TRIM TAB ACTUATOR - TESTING

1. Testing
A. Screw Travel (Refer to Elevator Trim Actuator Assembly, Figure 1001).
(1) Test elevator actuator assembly by rotating primary sprocket (10) with fingers while holding bearing end of extending
screws (32). Extending screws (32) should travel in and out of internal screws (26) smoothly with no indication of
binding.
B. End Play.
(1) Maximum relative movement between elevator externally threaded screw (32) and housing (24) after assembly is
0.007 inch (0.18 mm).
C. Screw Alignment (Refer to Figure 101).
(1) Elevator actuator extending screws (32) shall align with each other equal distance from actuator within 0.010 inch
(0.254 mm). Methods of checking alignment - measure the distance from the end cap (22) to centerline of bearing
(33); also, use a bolt for a slip fit check traveling through bearings (33).

Copyright © Textron Aviation Inc. Page 1 of 2

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Model 500 Series Component Maintenance Manual (Rev 17)
27-10-07-1 (Rev 8)

Figure 101 : Sheet 1 : Trim Tab Actuator Testing

Copyright © Textron Aviation Inc. Page 2 of 2

TRIM TAB ACTUATOR - DISASSEMBLY

1. Disassembly
A. Disassemble Elevator Actuator (Refer to Elevator Trim Tab Actuator, Figure 1001).
(1) Remove chain guard (17) by removing screws (21).
(2) Drive groove pins (12) from secondary sprockets (11) and internally threaded screws (26). Remove primary sprocket
(10), secondary sprockets (11), and chain (13).
NOTE: It may be necessary to apply heat to the internally threaded screws (26) to break the Loctite
seal between externally threaded screws (26) and primary sprocket (10).
(3) Remove center screw (21) securing end plate (20).
(4) Tap lightly with a soft hammer against externally threaded screws (32), to remove bearings (27).
(5) Remove screws (23) securing end plate (22) to housing (24).
(6) Tap lightly with a soft hammer against internally threaded screws (26), to remove split bearings (29).
(7) Remove externally threaded screw (32) and internally threaded screw (26) from housing (24).
(8) Separate split bearing (29) and remove from externally threaded screw.
(9) Remove externally threaded screw (32) from internally threaded screw (26).
(10) Remove wiper ring (30) from shaft of externally threaded screw (32).
B. Disassemble Rudder Actuator (Refer to Rudder Trim Tab Actuator, Figure 1002).
(1) Remove chain guard (8) by removing screws (11).
(2) Drive groove pins (4) from secondary sprockets (3) and internally threaded screws (13). Remove primary sprocket
(2), secondary sprockets (3), and chain (5).
NOTE: It may be necessary to apply heat to the internally threaded screws (13) to break the Loctite
seal between externally threaded screws (13) and primary sprocket (2).
(3) Remove center screw (11) securing end plate (9).
(4) Tap lightly with a soft hammer against externally threaded screws (18), to remove bearings (14).
(5) Remove screws (11) securing end plate (10) to housing (12).
(6) Tap lightly with a soft hammer against internally threaded screws (13), to remove split bearings (16).
(7) Remove externally threaded screw (18) and internally threaded screw (13) from housing (12).
(8) Separate split bearing (16) and remove from externally threaded screw.
(9) Remove externally threaded screw (13) from internally threaded screw (26).
(10) Remove wiper ring (17) from shaft of externally threaded screw (18).
C. Disassemble Aileron Actuator (Refer to Aileron Trim Tab Actuator, Figure 1003).
(1) If installed remove guard block-chain (8) by removing screws (9) and nuts (10).
(2) Remove chain guard (7) by removing screws (14).
(3) Remove connecting link (12) from chain (11) and remove from secondary sprockets (3).
(4) Drive groove pins (4) from secondary sprockets (3) and internally threaded screws (19). Remove primary sprocket
(2) and secondary sprockets (3).
NOTE: It may be necessary to apply heat to the internally threaded screws (19) to break the Loctite
seal between externally threaded screws (23) and primary sprocket (2) and secondary
sprockets (3).
(5) Remove center screw (15) securing end plate (13).
(6) Tap lightly with a soft hammer against externally threaded screws (23), to remove bearings (16).
(7) Remove screws (26) securing end plate (25) to housing (17).
(8) Tap lightly with a soft hammer against internally threaded screws (19), to remove split bearings (20).
(9) Remove externally threaded screws (23) and internally threaded screws (19) from housing (17).
(10) Separate split bearings (20) and remove from externally threaded screws (23).
(11) Remove externally threaded screws (23) from internally threaded screws (19).

Copyright © Textron Aviation Inc. Page 1 of 2

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Model 500 Series Component Maintenance Manual (Rev 17)
27-10-07-3 (Rev 16)

(12) Remove wiper rings (21) from shaft of externally threaded screws (23).

Copyright © Textron Aviation Inc. Page 2 of 2

TRIM TAB ACTUATOR - CLEANING

1. Cleaning
A. Tools and Equipment
NOTE: Equivalent substitute may be used for the listed items.
NAME NUMBER MANUFACTURER USE
Methyl n-Propyl Ketone Clean metal parts.
Solvent Blend Desoclean 110 PRC-DeSoto International Clean metal parts.
5426 San Fernando Rd.
Glendale, CA 94710
Naptha MIL-PRF-680 (Type Commercially Available Metal parts cleaning that
III) require soak cleaning.
B. Cleaning.
WARNING: Use only approved cleaning solvents and only in well-ventilated areas. Avoid inhaling solvent
vapors. Keep solvent and solvent containers away from sparks or open flame.
CAUTION: If bearings (30), of the elevator trim actuator, are not being replaced, do not allow solvent to enter
bearing.
(1) Clean metal parts with approved solvent. Apply approved solvent to all channels to ensure cleanliness. Thoroughly dry
all parts with filtered, dry, compressed air, lint-free cloth or lint-free disposable tissue.

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Model 500 Series Component Maintenance Manual (Rev 17)
27-10-07-5 (Rev 8)

TRIM TAB ACTUATOR - CHECK

1. Check
A. Check parts as follows:
(1) Check all parts visually, preferably under magnification. When parts are suspected of irregularities or deformity,
additional inspection shall be administered to verify the service life of the part, or the part shall be replaced.
(2) Check internal screws and extending screws for damaged threads or bends that may impair smooth operation.
(3) Check sprockets for chipped or worn teeth. Check for bent primary sprocket. Check alignment of secondary
sprockets.
(4) Check chain for wear.
(5) Check applicable parts for dimensional conformity. Refer to Trim Tab Actuator - Fits and Clearances.
B. Discarded Components.
(1) Verify all defective items are discarded during assembly; this includes replacing all wiper rings and groove pins.
C. Trim Tab Actuator Assembly.
(1) Verify that lubrication is included when actuator is assembled.
(2) Verify screw alignment and that the extending screws are pinned together, refer to Trim Tab Actuator - Testing.
(3) Verify that the assembled actuator is packaged for storage. Packaging shall consist of protective material to protect
assembly against moisture, dust and shock (shock being the result of falling from its stored position).
NOTE: Packaging not required when actuator assembly is to be returned to service immediately.

Copyright © Textron Aviation Inc. Page 1 of 1

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Model 500 Series Component Maintenance Manual (Rev 17)
27-10-07-6 (Rev 10)

TRIM TAB ACTUATOR - REPAIR

1. Repair
A. Finish.
NAME NUMBER MANUFACTURER USE
Color Chemical Film Alodine 1203 Henkel (Parker Amchem) Protective treatment of
Treatment 32100 Stephenson Highway aluminum
Madison Heights, MI
Corrosion Resistant 513 x 419/910 x PRC-DeSoto International Corrosion protection primer
Primer MIL-PRF- 942 5426 San Fernando Rd.
23377G or later. Glendale, CA 91209
Waterborne Corrosion 44-GN-60 /44-GN- Deft, Inc. Corrosion protection primer
Resistant Primer 60 CATA 17151 Von Karman Ave.
Irvine, CA 92714
Waterborne Corrosion U-4800/U-4801 Sterling Laquer Manufacturing Co. Corrosion protection primer
Resistant Primer MIL- 3150 Brannon St.
PRF-85582 St. Louis, MO 63139
(1) For cleaning actuator, refer to Trim Tab Actuator - Cleaning, and for parts replacement, refer to Trim Tab Actuator -
Assembly.
(2) The finish on the actuator housing and chain guard is to be repaired as follows:
(a) When the finish on the actuator housing has been damaged and bare metal is exposed, the finish shall be
repaired. Permissible to abrasive clean in lieu of chemically clean. Apply chemical film treatment using Iridite
14-2 and MIL-PRF-23377 corrosion resistant primer. Refer to the Model 500 Series Structural Repair Manual,
Chapter 51, Protection Treatment of Metal for application.

Copyright © Textron Aviation Inc. Page 1 of 1

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Model 500 Series Component Maintenance Manual (Rev 17)
27-10-07-7 (Rev 16)

TRIM TAB ACTUATOR - ASSEMBLY

1. Assemble Trim Tab Actuator
A. Assemble Elevator Trim Tab Actuator. Refer to Elevator Trim Tab Actuator Assembly, Figure 1001.
CAUTION: Use 5565450-28 silicone grease. Use no substitutes.
(1) If bearings (33) have been removed from externally threaded screws (32), apply corrosion resistant epoxy primer to
exterior surface of bearing (33) and press bearing into externally threaded screw (32).
(2) Insert externally threaded screws (32) through openings in end plate (22).
(3) If removed, carefully thread new wiper ring (30) onto externally threaded screw until past the end of the threads.
(4) Prior to assembly, apply 1/8 inch (3 mm) thick coating of 5565450-28 lubricant to:
(a) Threads and outer surface of externally threaded screw (32)
(b) Outside diameter of internally threaded screws (26).
(5) Install bearings (27) into housing (24) and secure with center screw (21).
(6) Begin threading externally threaded screw (32) into internally threaded screw (26).
(7) Apply a shank seal of Type X Class B sealant to the outer diameter of the bearings (29).
(8) Position bearing halves (29) around the externally threaded screws (32) and insert into the housing (24).
(9) Insert internally threaded screw (32) and externally threaded screw into housing (24).
(10) Install end plate (20) with screws (21). Secure screws (21) with lock wire.
(11) Operate the externally threaded screw in and out two or three times, wiping off excess grease from both ends of
actuator at the end of each cycle.
(12) Check linear movement of externally threaded screws (32) refer to Trim Tab Actuator - Testing.
(13) If linear movement of externally threaded screws is not within limits, replace bearing (27).
(14) Apply Loctite number 609 to external shaft surface (mating surface) of the primary sprocket (10) and install primary
sprocket (10) by inserting primary sprocket (10) shaft into secondary sprocket (11) and internally threaded screw
(26). Align groove pin holes (primary sprocket (10), secondary sprocket (11), internally threaded screw (26) and
install new groove pin (12). The Loctite eliminates loose sprockets.
(15) Align the other secondary sprocket (11) groove pin holes with internally threaded screw groove pin hole and install
new groove pin (12).
(16) Install chain (13) around secondary sprockets (11).
(a) Centerline of bearing (33) must be capable of adjusting to equal distance from the housing. If not, rotating one
secondary sprocket slightly before installing the chain will permit acceptable alignment. For maximum allowable
misalignment, refer to Trim Tab Actuator - Testing.
(b) The chain includes a Type A spring lock type connecting link to connect chain for a continuous loop.
(17) Install chain guard (17) and secure with screws (21). Secure screws (21) with lock wire.
(18) Perform Trim Tab Actuator Break-in Procedure.
B. Assemble Rudder Trim Tab Actuator. Refer to rudder Trim Tab Actuator Assembly, Figure 1002.
CAUTION: Use 5565450-28 silicone grease. Use no substitutes.
(1) If bearings (19) have been removed from externally threaded screws (18), apply corrosion resistant epoxy primer to
exterior surface of bearing (33) and press bearing into externally threaded screw (18).
(2) Insert externally threaded screws (18) through openings in end plate (10).
(3) If removed, carefully thread new wiper ring (17) onto externally threaded screw until past the end of the threads.
(4) Prior to assembly, apply 1/8 inch (3 mm) thick coating of 5565450-28 lubricant to:
(a) Threads and outer surface of externally threaded screw (18)
(b) Outside diameter of internally threaded screws (13).
(5) Install bearings (14) into housing (12) and secure with center screw (11).
(6) Begin threading externally threaded screw (18) into internally threaded screw (13).
(7) Position bearing halves (16) around the externally threaded screws (18) and insert into the housing (12).

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Model 500 Series Component Maintenance Manual (Rev 17)
27-10-07-7 (Rev 16)

(8) Insert internally threaded screw (18) and externally threaded screw into housing (12).
(9) Install end plate (10) with screws (11). Secure screws (11) with lock wire.
(10) Operate the externally threaded screw in and out two or three times, wiping off excess grease from both ends of
actuator at the end of each cycle.
(11) Check linear movement of externally threaded screws (18) refer to Trim Tab Actuator - Testing.
(12) If linear movement of externally threaded screws is not within limits, replace bearing (14).
(13) Apply Loctite number 609 to external shaft surface (mating surface) of the primary sprocket (2) and install primary
sprocket (2) by inserting primary sprocket (2) shaft into secondary sprocket (3) and internally threaded screw (13).
Align groove pin holes (primary sprocket (2), secondary sprocket (3), internally threaded screw (13) and install new
groove pin (4). The Loctite eliminates loose sprockets.
(14) Align the other secondary sprocket (3) groove pin holes with internally threaded screw groove pin hole and install new
groove pin (4).
(15) Install chain (5) around secondary sprockets (3).
(a) Centerline of bearing (19) must be capable of adjusting to equal distance from the housing. If not, rotating one
secondary sprocket slightly before installing the chain will permit acceptable alignment. For maximum allowable
misalignment, refer to Trim Tab Actuator - Testing.
(b) The chain includes a Type A spring lock type connecting link to connect chain for a continuous loop.
(16) Install chain guard (8) and secure with screws (11). Secure screws (11) with lock wire.
(17) Perform Trim Tab Actuator Break-in Procedure.
C. Assemble Aileron Trim Tab Actuator. Refer to Aileron Trim Tab Actuator Assembly, Figure 1003.
CAUTION: Use 5565450-28 silicone grease. Use no substitutes.
NOTE: To ensure correct orientation of the actuator (1A thru 1F) once installed in the aircraft the grease
zerks need to be on the bottom of the actuator with the primary sprocket (2) on the right side as
viewed from the end with the externally threaded screws (23). For actuator (1) the zerks are located
on top with primary sprocket on the right as viewed from the same end.
(1) If bearings (24) have been removed from externally threaded screws (23), apply corrosion resistant epoxy primer to
exterior surface of bearing (24) and press bearing into externally threaded screw (23).
(2) Insert externally threaded screws (23) through openings in end plate (25).
(3) If removed, carefully thread new wiper ring (21) onto externally threaded screw until past the end of the threads.
(4) Prior to assembly, apply 1/8 inch (3 mm) thick coating of 5565450-28 lubricant to:
(a) Threads and outer surface of externally threaded screw (23).
(b) Outside diameter of internally threaded screws (19).
(c) Threads of internal screw (19).
(5) Install bearings (16) into housing (17) and secure with end plate (13) and center screw (15).
(6) Thread externally threaded screw (23) into internally threaded screw (19).
(7) Position bearing halves (20) around the externally threaded screws (23) and insert into the housing (17).
(8) Insert internally threaded screw (19) and externally threaded screw (23) into housing (17).
(9) Install end plate (25) with screws (26). Secure screws (26) with lock wire.
(10) Operate the externally threaded screw in and out two or three times, wiping off excess grease from both ends of
actuator at the end of each cycle.
(11) Check linear movement of externally threaded screws (23), refer to Trim Tab Actuator - Testing.
(12) If linear movement of externally threaded screws is not within limits, replace bearing (16).
(13) Apply Loctite number 609 to the mating surfaces of the primary sprocket (2) and the secondary sprockets (3). Slide
secondary sprockets (3) over internally threaded screws (19). Insert primary sprocket (2) inside of internally threaded
screw (19) insuring orientation as noted above. The Loctite eliminates loose sprockets.
(14) Install new groove pin (4) by aligning groove pin holes in the primary sprocket (2), secondary sprocket (3) and
internally threaded screw (19).

Copyright © Textron Aviation Inc. Page 2 of 3

(15) Install chain (11) around secondary sprockets (3).

(a) Centerline of bearing (24) must be capable of adjusting to equal distance from the housing. If not, rotating one
secondary sprocket slightly before installing the chain will permit acceptable alignment. For maximum allowable
misalignment, refer to Trim Tab Actuator - Testing.
(b) Secure the chain with the included Type A spring lock type connecting link (12).
(16) Install chain guard (7) and secure with screws (14).
(17) Install guard block (8) using screws (9) and nuts (10).
(18) If removed install grease fittings (18A or 18B) pointing aft and service with 5565450-28 grease.
(19) Perform Trim Tab Actuator Break-in Procedure.
2. Trim Tab Actuator Break-in Procedure
A. Break-in
(1) Mount actuator in a suitable holding device.
(2) Install a length of chain over primary sprocket.
(3) Apply a five pound (2.2 kg) load longitudinally to the rod ends and extend the actuator fully.
(4) Apply a five pound (2.2 kg) load longitudinally to the rod ends and retract the actuator fully.
(5) Repeat steps (3) and (4) 100 times.
(6) Verify that breakout torque is less than 3 inch pounds (0.34 N.m).

Copyright © Textron Aviation Inc. Page 3 of 3

TRIM TAB ACTUATOR - FITS AND CLEARANCES

1. Fits and Clearances
A. Screw Assembly 6361215-4, -28

(1) 3.00 inch (76.20 mm)

(2) 6.39 inch (162.31 mm)
(3) 0.3125 inch, +0.001 or -0.000 inch (7.81 mm, +0.025 or -0.00 mm) diameter
(4) 0.4995 inch, +0.001 or -0.000 inch (12.687 mm, +0.025 or -0.00 mm) diameter
B. Screw Assembly 6660251-23

(1) 2.10 inch (53.34 mm)

(2) 5.79 inch (123.2 mm)
(3) 0.3125 inch, +0.001 or -0.000 inch (7.81 mm, +0.025 or -0.00 mm) diameter
(4) 0.4995 inch, +0.001 or -0.000 inch (12.687 mm, +0.025 or -0.00 mm) diameter
C. Screw Assembly 2661215-7

(1) 0.75 inch (19.05 mm)

(2) 4.14 inch (105.16 mm)
(3) 0.3125 inch, +0.001 or -0.000 inch (7.81 mm, +0.025 or -0.00 mm) diameter
(4) 0.4995 inch, +0.001 or -0.000 inch (12.687 mm, +0.025 or -0.00 mm) diameter
D. Actuator Housing

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Model 500 Series Component Maintenance Manual (Rev 17)
27-10-07-8 (Rev 9)

(1) 0.828 inch (21.03 mm) diameter

(2) 0.828 inch (21.03 mm) diameter
(3) 1.50 inch, +0.000 or -0.030 inch (38.10 mm, +0.00 or -0.76 mm)
(4) 0.875inch (22.22 mm) diameter
(5) 0.875inch (22.22 mm) diameter
NOTE: (2) Shall be parallel to (1) within 0.005 Inch (0.127 mm) Total Indicator Reading.
NOTE: (4) Shall be concentric to (1) within 0.003 Inch (0.076 mm) Total Indicator Reading.
NOTE: (5) Shall be concentric to (2) within 0.003 Inch (0.076 mm) Total Indicator Reading.

Copyright © Textron Aviation Inc. Page 2 of 2

ELEVATOR TRIM TAB ACTUATOR ASSEMBLY

NOMENCLATURE EFFECTIVITY UNITS
PER
ITEM PART NUMBER 1 2 3 4 5 6 7 FROM TO ASSY
- ELEVATOR TRIM TAB ACTUATOR
ASSEMBLY

- 1 6361215-13 . ACTUATOR ASSY-TRIM A NP

TAB LH FSO 6361215-21

- . ACTUATOR ASSY-TRIM
2 6361215-21 B 01
TAB LH

- . ACTUATOR ASSY-TRIM
3 6361215-14 C NP
TAB RH FSO 6361215-22
ACTUATOR ASSY-TRIM
- 4 6361215-22 . D 01
TAB RH
- . ACTUATOR ASSY-TRIM
5 6361215-23 E 01
TAB LH

- . ACTUATOR ASSY-TRIM
6 6361215-29 F 01
TAB LH

- . ACTUATOR ASSY-TRIM
7 6361215-24 G 01
TAB RH
ACTUATOR ASSY-TRIM
- 8 6361215-30 . H 01
TAB RH

- . ACTUATOR ASSY-TRIM
8A 6361215-31 I 01
TAB LH
- . ACTUATOR ASSY-TRIM
8B 6361215-32 J 01
TAB RH

- 9 6361620-10 . . SPROCKET-14 A,C,F,H 01

TOOTH-PRIMARY

10 6361215-20 . . SPROCKET-14 B,D,E,G,I,J 01

TOOTH-PRIMARY

11 6361620-11 . . SPROCKET-12 02
TOOTH-SECONDARY
ATTACHING
PARTS
12 MS35675-12 . . PIN-GROOVE 04
---*---
13 5565450-11 . . CHAIN 01
14 CM2692-10-1S . . PLUG BUTTON 01

- . . PLUG BUTTON-ALT
15 CM2692-10J1S 01
FOR CM2692-10-1S
- 16 6361215-9 . . CHAIN GUARD ASSY A,B,I 01
17 6361215-10 . . CHAINGUARD ASSY C,D,J 01
- . . CHAINGUARD ASSY
18 6361215-19 E,F 01
LH

- . . CHAINGUARD ASSY
19 6361215-18 G,H 01
RH

Copyright © Textron Aviation Inc. Page 1 of 3

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Model 500 Series Component Maintenance Manual (Rev 17)
27-10-07-1001 (Rev 14)

20 6361620-8 . . END PLATE 01

ATTACHING
PARTS
21 MS35266-59 . . SCREW A,B,C,D,E,F,G,H 03
- 21A MS35266-60 . . SCREW I,J 03
---*---
22 6361620-7 . . END PLATE 01
ATTACHING
PARTS
23 MS35266-59 . . SCREW A,B,C,D,E,F,G,H 03
- 23A MS35266-60 . . SCREW I,J 03
---*---
24 6361215-15 . . HOUSING-ACTUATOR 01

- 25 6361215-17 . . INTERNAL SCREW A,C,F,H 02

ASSY

26 6361215-25 . . INTERNAL SCREW B,D,E,G,I,J 02

ASSY
27 MS27641-6G . . BEARING 02
28 MS15001-4 . . FITTING A,B,C,D,E,F,G,H 02
- 28A MS15001-3 . . FITTING I,J 02
. . BEARING-AFT FSO
29 6361620-6 A,B,C,D,E,F,G,H NP R
6361620-14
- 29A 6361620-14 . . BEARING-AFT I,J 04 R
- 29B MS28775-010 . . O-RING I,J 02
30 SHD250 . . WIPER RING V30781 02
- 31 6361215-4 . . SCREW ASSY A,C,F,H 02
32 6361215-28 . . SCREW ASSY B,D,E,G,I,J 02
33 S2629-1 . . . BEARING 01
- Item Not Illustrated

Copyright © Textron Aviation Inc. Page 2 of 3

Figure 1001 : Sheet 1 : ELEVATOR TRIM TAB ACTUATOR ASSEMBLY

Copyright © Textron Aviation Inc. Page 3 of 3

RUDDER TRIM TAB ACTUATOR ASSY

NOMENCLATURE EFFECTIVITY UNITS
PER
ITEM PART NUMBER 1 2 3 4 5 6 7 FROM TO ASSY
- RUDDER TRIM TAB ACTUATOR ASSY

- . ACTUATOR ASSY-
1 6561194-1 A 01 R
RUDDER TRIM
- . ACTUATOR ASSY-
1A 6561194-3 B 01 R
RUDDER TRIM

2 6561194-2 . . SPROCKET-16 01
TOOTH

3 6361620-11 . . SPROCKET-12 02 R
TOOTH
ATTACHING
PARTS
4 MS35675-12 . . PIN 02
---*---
5 5565450-11 . . CHAIN 01
6 S2294-25 . . CONNECTING LINK 01 R
7 CM2692-10J1S . . PLUG BUTTON 01
8 6660251-16 . . CHAIN GUARD ASSY 01 R
9 6361620-8 . . END PLATE-FWD 01
10 6361620-7 . . END PLATE-AFT 01
ATTACHING
PARTS
11 MS35266-59 . . SCREW 03
---*---
12 6660251-3 . . ACTUATOR HOUSING 01 R

13 6660251-4 . . INTERNAL SCREW 02 R

ASSY
14 MS27641-6G . . BEARING-FWD 02
15 MS15001-3 . . FITTING 02
16 6361620-6 . . BEARING-AFT A 04 R
- 16A 6961423-14 . . BEARING-AFT B 04 R
- 16B MS28775-010 . O-RING B 02 R
17 SHD250 . . WIPER RING 02 R
18 6660251-23 . . SCREW ASSY 02
19 S2629-1 . . . BEARING 01
- Item Not Illustrated

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Model 500 Series Component Maintenance Manual (Rev 17)
27-10-07-1002 (Rev 12)

Figure 1002 : Sheet 1 : RUDDER TRIM TAB ACTUATOR ASSY

A10450

14
9
8
19
4

2
5 18
6 16
3
7 11
4 11
10
17
16

A5663T1014

Copyright © Textron Aviation Inc. Page 2 of 2

AILERON TRIM TAB ACTUATOR ASSEMBLY

NOMENCLATURE EFFECTIVITY UNITS
PER
ITEM PART NUMBER 1 2 3 4 5 6 7 FROM TO ASSY
- AILERON TRIM TAB ACTUATOR
ASSEMBLY

- 1 6660361-16 . ACTUATOR ASSY-TRIM A NP

TAB

- . ACTUATOR ASSY-TRIM
1A 6660361-18 B NP
TAB

- . ACTUATOR ASSY-TRIM
1B 6660361-23 C 01
TAB
ACTUATOR ASSY-TRIM
- 1C 6660361-25 . D 01
TAB
- 1D . DELETED-NOT USED

- . ACTUATOR ASSY-TRIM
1E 6660361-22 E 01
TAB
- . ACTUATOR ASSY-TRIM
1F 6660361-29 F 01
TAB
2 6660351-20 . . SPROCKET-8 TOOTH 01
3 6660351-19 . . SPROCKET-12 TOOTH 02
ATTACHING
PARTS
4 MS35675-12 . . PIN-GROOVE 02
---*---
5 CM2692-10-1S . . PLUG BUTTON 01

- 6 6660361-14 . . GUARD ASSY-CHAIN A,B NP

FSO 6660361-24
- 6A 6660361-24 . . GUARD ASSY-CHAIN C,D,E,F 01
- 6B . . DELETED-NOT USED
7 6660361-11 . . . GUARD-CHAIN 01
GUARD BLOCK-
8 6660361-15 . . . CHAIN FSO A,B NP
6660361-21
- 8A 6660361-21 . . . GUARD BLOCK- C,D,E,F 01
CHAIN
ATTACHING
PARTS
9 MS35206-326 . . . SCREW 02
10 MS21042-04 . . . NUT 02
- . . . NUT ALT FOR
10A NAS1291X04 02
MS21042-04
---*---
11 5565450-11 . . CHAIN 01
12 S2294-25 . . LINK-CONNECTING 01

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Model 500 Series Component Maintenance Manual (Rev 17)
27-10-07-1003 (Rev 16)

13 2661615-4 . . END PLATE 01

ATTACHING
PARTS
14 MS24694C47 . . SCREW 02
15 MS35266-59 . . SCREW 01
---*---
16 MS27641-6G . . BEARING 02
17 6660361-3 . . ACTUATOR HOUSING 01
18 MS15001-3 . . FITTING A,B,E,F 02
- 18A MS15001-4 . . FITTING C,D 02
19 6660361-4 . . INTERNAL SCREW 02

. . BEARING FSO
20 6361620-6 A,B,C,E NP
6361620-14
- 20A 6961423-14 . . BEARING D,F 04
- 20B MS28775-010 . . O-RING D,F 04
21 SHD250 . . WIPER RING 021
- 22 2661215-8 . . SCREW ASSY 02
23 2661215-7 . . . SCREW 01
24 S2629-1 . . . BEARING 01
25 2661615-3 . . END PLATE 01
ATTACHING
PARTS
26 MS35266-59 . . SCREW 04
---*---
- Item Not Illustrated

Copyright © Textron Aviation Inc. Page 2 of 3

Figure 1003 : Sheet 1 : AILERON TRIM TAB ACTUATOR ASSEMBLY

A10452

26 23

20
19 24

25
21
20

16
7 9
11
12
4

17
2

13
15 18
5

10
8 3 14

6661T1017

Copyright © Textron Aviation Inc. Page 3 of 3

TRIM TAB ACTUATOR - ILLUSTRATED PARTS LIST

1. Illustrated Parts List
A. Introduction.
(1) The Illustrated Parts List has been prepared to assist customer personnel in requisitioning, storing, and issuing the
trim tab actuator components and in identifying new and reclaimed parts. It is not approved for any other purpose.
(2) The trim tab actuator part numbers that follow are covered in this parts list:
6565141-1 6565141-2
(3) The indention system used in the detailed parts list of this catalog shows the relationship of one part to another. For a
given item, the indention code shows a system installation or general heading starting at the extreme left position
continuing on down into succeeding columns until the end detail is reached. Example:
A18017
1234567
Installation
Detail Parts for Installation
Assembly
Attaching Parts for Assembly
Detail Parts for Assembly
Subassembly
Attaching Parts for Subassembly
Detail Parts for Subassembly
Sub−Subassembly
Attaching Parts for Sub−Subassembly
Detail Parts for Sub−Subassembly

(4) The quantities given in the UNITS PER ASSY column of the Illustrated Parts List are, in the case of assemblies, the
total used at the indicated location. For component parts indented under the assemblies, the quantities are those
used in the assembly. The quantities specified, therefore, are not necessarily the total used per installation.
(5) Effectivity for detail parts of assemblies covered by this technical manual are listed in the Effect column. The code A,
B, C, etc., listed for the assembly is the code for the detail parts peculiar to that assembly. If no code appears in the
Effect column, that detail part is used in all assemblies listed.
(6) When a part of later design is not interchangeable with the part it replaces, both parts applicable to the particular
usage are listed. The individual part usage is listed in the Effect column. Care should be exercised in determining
proper usage when ordering to insure receipt of the correct part.
(7) When a part of later design is completely interchangeable with the part it replaces, both parts will be serialized and
the notation FSO (for spares order) will be entered following the listing of the earlier design part. FSO means that the
earlier design part is not available and the later design part must be used.
(8) The basic number identifies the Cessna drawing only. Each installation, assembly or detail part is assigned a part
number which consists of the drawing number and an appropriate dash number. Example:
A12537
EXAMPLE:
Part Number
6707005 − 7

Basic Number Dash Number

(Drawing Identification
Only)

NOTE: Parts stamped with a dash 400 series are for internal control purposes only and should not be
used by the operator for ordering/identifying purposes.

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Model 500 Series Component Maintenance Manual (Rev 17)
27-10-08-0 (Rev 10)

TRIM TAB ACTUATOR - DESCRIPTION AND OPERATION

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Model 500 Series Component Maintenance Manual (Rev 17)
27-10-08-0 (Rev 10)

Figure 1 : Sheet 1 : Trim Tab Actuator

Copyright © Textron Aviation Inc. Page 2 of 2

TRIM TAB ACTUATOR - TESTING

1. Testing
A. Screw Travel (Refer to Illustrated Parts List, Figure 1001).
(1) Test elevator actuator assembly by rotating primary sprocket (3) with fingers while holding bearing end of extending
screws (16). Extending screws (16) should travel in and out of internal screws (19) smoothly with no indication of
binding.
B. End Play (Refer to Illustrated Parts List, Figure 1001).
(1) Elevator actuator relative end movement between internal screws (19) and bearings (10) should be 0.004 to 0.006
inch with an ambient temperature of 70°F.
(2) End play of less than 0.004 inch may cause the actuator to bind or lock during flight where very cold temperatures are
encountered. Actuators not within end play limits shall be reworked. Refer to Trim Tab Actuator - Repair.
C. Screw Alignment. (Refer to Figure 101).
(1) Elevator actuator extending screws (16) shall align with each other equal distance from actuator within 0.010 inch.
Methods of checking alignment - measure the distance from the housing (13) to centerline of bearing (17), also use a
bolt for a slip fit check traveling through bearings (17).

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Model 500 Series Component Maintenance Manual (Rev 17)
27-10-08-1 (Rev 14)

Figure 101 : Sheet 1 : Trim Tab Actuator Testing

Copyright © Textron Aviation Inc. Page 2 of 2

TRIM TAB ACTUATOR - DISASSEMBLY

1. Disassembly
A. Disassemble Elevator Actuator (Refer to Illustrated Parts List, and Figure 1001).
(1) Remove chain guard (20) by removing screws (23).
(2) Drive groove pins (5) from secondary sprockets (4) and internal screws (19). Remove primary sprocket (3), plug
button (7), secondary sprockets (4), and chain (6).
NOTE: It may be necessary to apply heat not to exceed 180°F (82°C), to the internal screws (19) to
break the Loctite seal between internal screws (19) and primary sprocket (3).
(3) Remove end plate (18) by removing center screw (23).
(4) Remove bearings (11) by tapping lightly with a soft hammer against extending screws (16).
(5) Starting with a short 1/16 inch pin punch and then using a progressively longer punch, drive groove pins (15) from
housing (13) and bearings (14).
NOTE: Prior to removal of bearings (14), identify position and location of each bearing relative to the
housing by using a scratch scribe or center punch. This will ensure proper alignment of
groove pin holes upon reassembly.
(6) Drive bearing (14) from housing (13) by tapping lightly with a soft hammer against internal screws (19).
(7) Rotate extending screws (16) counterclockwise until separated from internal screws (19), remove bearing races (10),
bearings (9).
(8) Remove packing (12) from bearing (14).
(9) If bearing (17) requires replacement, press bearing from extending screw (16) using a suitable arbor press and
mandrel.

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Model 500 Series Component Maintenance Manual (Rev 17)
27-10-08-4 (Rev 10)

TRIM TAB ACTUATOR - CLEANING

1. Cleaning
A. Tools and Equipment
NOTE: Equivalent substitute may be used for the following listed item.
NAME NUMBER MANUFACTURER USE
Methyl n-Propyl Ketone Clean metal parts.
Solvent Blend Desoclean 110 PRC-DeSoto International Clean metal parts.
5426 San Fernando Rd.
Glendale, CA 94710
Naptha MIL-PDF-680 Commercially Available Metal parts cleaning that
(Type III) require soak cleaning.
B. Cleaning.
WARNING: Use only approved cleaning solvents and only in well-ventilated areas. Avoid inhaling solvent
vapors. Keep solvent and solvent containers away from sparks or open flame.
CAUTION: If bearings (10, elevator actuator) are not being replaced, do not allow solvent to enter bearing.
(1) Clean metal parts with approved solvent. Apply approved solvent to all channels to ensure cleanliness. Thoroughly dry
all parts with filtered, dry, compressed air, lint-free cloth or lint-free disposable tissue.

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Model 500 Series Component Maintenance Manual (Rev 17)
27-10-08-5 (Rev 10)

TRIM TAB ACTUATOR - CHECK

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Model 500 Series Component Maintenance Manual (Rev 17)
27-10-08-6 (Rev 10)

TRIM TAB ACTUATOR - REPAIR

1. Repair
A. Finish.
NAME NUMBER MANUFACTURER USE
Color Chemical Film Alodine 1203 Henkel (Parker Amchem) Protective treatment of
Treatment 32100 Stephenson Highway aluminum
Madison Heights, MI 48071
Pretreatment Primer 728-013/702-701 Sherwin-Williams Pretreatment primer
DOD-P-15328 Industrial Coatings
630 E. 13th St.
Andover, KS 67002
Corrosion Resistant 513 x 419/910 x PRC-DeSoto International Corrosion protection primer
Primer MIL-PRF- 942 5426 San Fernando Rd.
23377G or later. Glendale, CA 91209
Waterborne Corrosion 44-GN-60 /44-GN- Deft, Inc. Corrosion protection primer
Resistant Primer 60 CATA 17151 Von Karman Ave.
Irvine, CA 92714
Waterborne Corrosion U-4800/U-4801 Sterling Laquer Manufacturing Co. Corrosion protection primer
Resistant Primer MIL- 3150 Brannon St.
PRF-85582 St. Louis, MO 63139
(1) For cleaning actuator, refer to Trim Tab Actuator - Cleaning and for parts replacement, refer to Trim Tab Actuator -
Assembly.
(2) The finish on the actuator housing is to be repaired as follows:
(a) When the finish on the actuator housing has been damaged and bare metal is exposed, the finish shall be
repaired. Permissible to abrasive clean in lieu of chemically clean. Apply chemical film treatment and corrosion
resistant primer. Refer to the Model 500 Series Structural Repair Manual, Chapter 51, Protective Treatment of
Metal for application.
(3) The finish on the chain guard is the same as actuator housing.
B. Bearing Installation (External Screw End).
(1) Number of repairs is limited: Permissible to have one repair at an individual bearing location; the repair may be
either a repositioned bearing or a new bearing.
(2) New bearing installation; repositioning original bearing.
(a) Face of bearing must be flush with face of housing.
(b) When repairing original bearing; rotate bearing 90 degrees from drilled groove pin hole alignment.
(c) With the aid of a drill fixture, position the actuator assembly to drill two 0.094 inch diameter groove pin holes
through the actuator housing (same location as original 0.062 groove pin location) and through the bearing.
(d) During installation on all enlarged groove pin holes (0.094) install groove pin GP3-094 x 650-12 in lieu of the
0.062 diameter groove pin. Groove pin part number is from Groove-Pin Corporation.

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Model 500 Series Component Maintenance Manual (Rev 17)
27-10-08-7 (Rev 10)

TRIM TAB ACTUATOR - ASSEMBLY

1. Assemble Trim Tab Actuator
A. Assemble Elevator Trim Tab Actuator (Refer to Illustrated Parts List and Figure 1001).
CAUTION: Use 5565450-28 silicone grease. Use no substitutes.
(1) If bearing (17) has been removed from extending screw (16), apply corrosion resistant primer to exterior surface of
bearing (17), refer to the Model 500 Series Structural Repair Manual, Chapter 51, Protective Treatment of Metal for
application. Press bearing into extending screw (16).
(2) Install new packings (12) in bearings (14).
(3) Actuator Assembly.
CAUTION: Verify that the extending screws (16) are the correct part.
(a) Apply 5565450-28 lubricant to bearings, threads of extending screws and internal screws; install bearings (14)
on extending screws (16); install bearing races (10) and bearings (9) on internal screws (19); thread internal
screws (19) onto extending screws (16).
NOTE: When original bearings (14) are to be reinstalled, observe identification reference marks to
ensure correct installation location. If new bearings (14) are being installed, refer to Trim
Tab Actuator - Repair.
(4) Align groove pin holes in housing (13) and bearings (14) and install new groove pins (15).
(5) Position bearings (11) on internal screws (19) and tapping lightly, drive bearings (11) into housing (13).
(a) Verify there is no clearance between end plate (18) and bearing (11) outer race after screws (23) are installed.
(6) Install end plate (18) with screws (23).
(7) Operate the extending screw in and out 2 or 3 times; wipe off excess grease.
(8) Position secondary sprockets (4) on internal screws (19).
(9) Apply Loctite number 609 to external shaft surface (mating surface) of the primary sprocket (3) and install primary
sprocket (3) by inserting primary sprocket (3) shaft into secondary sprocket (4) and internal screw (19). Align groove
pin holes (primary sprocket (3), secondary sprocket (4), internal screw (19), and install new groove pin (5). The
Loctite eliminates loose sprockets.
(10) Align the other secondary sprocket (4) groove pin holes with internal screw groove pin holes and install new groove
pins (5). Install plug (7) in secondary sprocket (4).
(11) Install chain (6) around secondary sprockets (4).
(a) Centerline of bearing (17) must be capable of adjusting to equal distance from the housing (13). If not, rotating
one secondary sprocket slightly before installing the chain will permit acceptable alignment. Maximum
misalignment, refer to Trim Tab Actuator - Testing.
(b) The chain includes a Type A spring lock type connecting link to connect chain for a continuous loop.
(12) Install chain guard (19) and secure with screws (20). Secure screws (23) with safety wire through holes in end plate
(18) and chain guard (20).

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Model 500 Series Component Maintenance Manual (Rev 17)
27-10-08-8 (Rev 14)

TRIM TAB ACTUATOR - FITS AND CLEARANCES

1. Fits and Clearances
A. Bearing 5565450-46
A68675

(2)

(3) (1)

5596T1006

(1) 0.828 inch, +0.000, or -0.001 inch (21.62 mm, +0.00 or -0.025 mm) diameter (NOTE)
(2) 0.383 inch, +0.001, or -0.001 inch (9.73 mm, +0.025 or -0.025 mm) diameter (NOTE)
(3) 0.311 inch, +0.001, or -0.000 inch (7.90 mm, +0.025 or -0.000 mm) diameter
NOTE: Diameter (1) Shall be concentric to (3) within 0.002 Inch (0.051 mm) Total Indicator Reading.
NOTE: Diameter (2) Shall be concentric to (3) within 0.002 Inch (0.051 mm) Total Indicator Reading.
B. Internal Screw 5565450-74
A22469
SHALL BE CONCENTRIC TO (1) WITHIN
0.002 INCH TOTAL INDICATOR READING
(5) (1)

(6)
(2)
(7) (3)
(4)
(9) (8)
5596T1009

(1) 0.375 inch, +0.001, or -0.000 inch (9.53 mm, +0.025 or -0.00 mm) diameter
(2) 0.100 inch (2.54 mm)
(3) 0.310 inch (7.87 mm)
(4) 3.74 inch, +0.010 or -0.010 inch (95.00 mm, +0.25 or -0.25 mm)
(5) 0.328 inch, +0.002, or -0.001 inch (12.54 mm, +0.051 or -0.025 mm) diameter
(6) 0.887 inch, +0.010 or -0.010 inch (22.53 mm, +0.25 or -0.25 mm)
(7) 0.512 inch, +0.010 or -0.010 inch (13.00 mm, +0.25 or -0.25 mm)
(8) 4.05 inch, (102.87 mm)
(9) 1.00 inch, (25.40 mm)
C. Screw 5565451-21

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Model 500 Series Component Maintenance Manual (Rev 17)
27-10-08-8 (Rev 14)

(1) 2.25 inch (57.15 mm)

(2) 5.75 inch (146.1 mm)
(3) 0.3075 inch, +0.001 or -0.000 inch (7.81 mm, +0.025 or -0.00 mm) diameter
D. Actuator Housing

(1) 0.828 inch (21.03 mm) diameter

Copyright © Textron Aviation Inc. Page 2 of 3

A22470
(3) (2) 1

END PLATE
BEARING 6564T1015

(1) Dimension determined by machining tolerances of internal screw.

(2) There shall be no free play between bearing outer race and end plate
(3) There shall be no free play between secondary sprocket and bearing inner race

Copyright © Textron Aviation Inc. Page 3 of 3

ELEVATOR TRIM TAB ACTUATOR ASSEMBLY

NOMENCLATURE EFFECTIVITY UNITS
PER
ITEM PART NUMBER 1 2 3 4 5 6 7 FROM TO ASSY
- ELEVATOR TRIM TAB ACTUATOR
ASSEMBLY

- 1 6565141-1 . ACTUATOR ASSY-TRIM 01 R

TAB LH

- . ACTUATOR ASSY-TRIM
2 6565141-2 01 R
TAB RH
3 5565450-31 . . SPROCKET-PRIMARY 01 R
. . SPROCKET-
4 6565141-8 02 R
SECONDARY
ATTACHING
PARTS
5 S2637-6Z11 . . PIN-GROOVE 02 R
---*---
6 5565450-11 . . CHAIN 01 R
7 CM2692-10J1S . . PLUG BUTTON 01 R
8 MS15001-1 . . FITTING-LUBRICATION 02 R
9 S2013-3 . . BEARING-THRUST 02 R
10 S2014-10 . . RACE 04 R
11 MS27641-6G . . BEARING 02 R
12 MS28775-011 . . PACKING 02 R
13 6565141-3 . . HOUSING 01 R
14 5565450-46 . . BEARING 02 R
15 S2637-4Z10 . . PIN-GROOVE 04 R
16 5565451-19 . . SCREW ASSY 02 R
17 S2629-1 . . . BEARING 01 R
18 6361620-8 . . PLATE-END 01 R
19 6565141-4 . . SCREW-INTERNAL 02 R
. . GUARD ASSY-CHAIN
20 6565141-7 01 R
LH

- . . GUARD ASSY-CHAIN
21 6565141-6 01 R
RH
22 MS21069L3 . . . NUTPLATE 01 R
23 MS35266-59 . . SCREW 03 R
- Item Not Illustrated

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Model 500 Series Component Maintenance Manual (Rev 17)
27-10-08-1001 (Rev 10)

Figure 1001 : Sheet 1 : ELEVATOR TRIM TAB ACTUATOR ASSEMBLY

A22810

20
22

6
3
5
15
13
23

4
7
11

18 17

23 8 16
9

14
12
10

6563T1024

Copyright © Textron Aviation Inc. Page 2 of 2

ELECTRIC TRIM ACTUATOR - ILLUSTRATED PARTS LIST

1. Illustrated Parts List
A. Introduction
(1) The Illustrated Parts List will help the customer to order, keep, and supply the replaceable components. It will also
identify new and reclaimed parts. It is not approved for any other purpose.
(2) This parts list includes the electric trim actuator assembly used on the Model Cessna Citation, Citation I and Citation
II airplanes. These part numbers are included:
5115231-12 5115231-23 5115231-26 5115231-29 5565430-22
5115231-18 5115231-24 5115231-27 5115231-30 5565430-25
5115231-19 5115231-25 5115231-28
(3) The indention system used in the detailed parts list of this catalog shows the relationship of one part to another. For a
given item, the indention code shows a general heading at the extreme left position and continues with indented
columns until the end detail is reached as follows:
A18017
1234567
Installation
Detail Parts for Installation
Assembly
Attaching Parts for Assembly
Detail Parts for Assembly
Subassembly
Attaching Parts for Subassembly
Detail Parts for Subassembly
Sub−Subassembly
Attaching Parts for Sub−Subassembly
Detail Parts for Sub−Subassembly

Basic Number Dash Number

(Drawing Identification
Only)

NOTE: Parts that have a dash 400 series stamp are for internal control purposes only and must not be
used by the operator to order or to identify parts.
B. For Vendor names and addresses with Federal Supply Codes, refer to Introduction - Supplier Address List.

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Model 500 Series Component Maintenance Manual (Rev 17)
27-30-06-0 (Rev 10)

ELECTRIC TRIM ACTUATOR - DESCRIPTION AND OPERATION

1. Description
A. The electric trim actuator consists of an electric motor assembly and a drive clutch assembly interconnected by chain and
sprockets enclosed within a housing. A cable drum assembly is mounted on a clutch shaft. The electric motor is 28 VDC
bi-directional and is electrically connected in parallel with the clutch solenoid. Refer to Figure 1.
B. These electric trim actuator part numbers are affected by this individual component maintenance manual.
5115231-12 5115231-23 5115231-26 5115231-29 5565430-22
5115231-18 5115231-24 5565430-27 5115231-30 5565430-25
5115231-19 5115231-25 5115231-28
2. Operation
A. Energizing the electric motor also energizes the clutch solenoid which engages the serrated clutch. The cable drum
assembly is friction driven by the clutch assembly. As flight control trim cable tension load increases, the drum will slip on
the drive shaft. Cable tension slippage load is adjustable.

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Model 500 Series Component Maintenance Manual (Rev 17)
27-30-06-0 (Rev 10)

Figure 1 : Sheet 1 : Electric Trim Actuator - Description and Operation

A18065

CLUTCH WIRES AFT CABLE

(MODEL 500)

SLIP CLUTCH
CLUTCH TO DRUM
DRIVE (SOLENOID
ACTUATED) SPRING WASHER

JAM NUT
BUSHING
BUSHING
CHAIN DRUM DRIVE
ADJUSTING NUT
CLUTCH
SOLENOID DRUM

CABLE GUARD MOTOR

(BEND AS SHOWN)

MOTOR
WIRES

FORWARD CABLE
(MODEL 500)

5561T1032A

Copyright © Textron Aviation Inc. Page 2 of 3

Figure 1 : Sheet 2 : Electric Trim Actuator - Description and Operation

A22468

FORWARD CABLE
(MODEL 550)

CLUTCH WIRES

SLIP CLUTCH
CLUTCH TO DRUM
DRIVE (SOLENOID
ACTUATED) SPRING WASHER

JAM NUT
BUSHING
BUSHING
CHAIN DRUM DRIVE
ADJUSTING NUT
CLUTCH
SOLENOID DRUM

CABLE GUARD MOTOR

(BEND AS SHOWN)

MOTOR
WIRES

AFT CABLE
(MODEL 550)

5561T1032A

Copyright © Textron Aviation Inc. Page 3 of 3

ELECTRIC TRIM ACTUATOR - TESTING

1. Testing
A. It is recommended that the electric trim actuator assembly be secured to a suitable work bench and test equipment be
provided as shown in Figure 101.
B. Conduct test as follows:
(1) Disconnect alligator clamps to clutch assembly.
(2) Actuate switch to provide 28 VDC, +0.2 or -0.2 VDC to motor. Note direction of rotation of motor and that clutch is
disengaged. Motor drive sprocket should rotate at 6.8 to 7.20 RPM rated load. Turn switch off.
(3) Reverse polarity of wires to motor and actuate switch. Direction of rotation of motor should reverse. Turn switch off.
(4) Connect alligator clamps to clutch wires.
(5) Actuate switch to provide 28 VDC, +0.2 or -0.2 VDC to motor and clutch assembly. Motor should rotate and clutch
should engage.
(6) Clutch Slippage
(a) Attach a spring scale to the cable end.
(b) Apply force (pull) on the spring scale and the clutch shall slip when the pounds of tension is within the specified
limits described in Figure 101.
CAUTION: Be prepared to stop motor if clutch shows no indication of slippage as the spring scale
reaches the top tension limit.
(c) If the clutch does not slip within the specified limits defined in Figure 101, adjust the clutch in accordance with
step C.
(7) Reverse direction of rotation of motor and check clutch slippage. The slippage shall be within the tension limits
specified in Figure 101.
C. Adjust clutch slippage as follows:
(1) Remove side cover to gain access to adjusting nut.
CAUTION: Make sure electrical power is off while making adjustment.
(2) Using two one-eighth inch punches or use modified spanner wrenches as holding tools, loosen jam nut and turn
adjusting nut until slippage of the clutch assembly is as specified in Figure 101.
NOTE: The inch-pound angular torque is converted to pound tension and is described in chart form
in Figure 101. A spring scale is used to measure pound tension.
(3) When adjustment is correct, tighten jam nut while holding adjustment nut position.
(4) Install side cover.

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Model 500 Series Component Maintenance Manual (Rev 17)
27-30-06-1 (Rev 10)

Figure 101 : Sheet 1 : Test Set-Up

Copyright © Textron Aviation Inc. Page 2 of 2

ELECTRIC TRIM ACTUATOR - DISASSEMBLY

1. Disassembly
A. Disassemble Trim Tab Actuator (Refer to Illustrated Parts List).
(1) Remove covers (27) from housing (36) by removing screws (26).
(2) Remove cover (13) from housing by removing screws (12).
(3) Remove nuts (23) and screws (24) from motor support (22). Reposition motor assembly so that chain (29) can be
removed from sprocket (20). Remove motor assembly from housing assembly.
(4) Disassemble motor assembly as follows:
(a) Drive pin (21) from motor shaft and sprocket (20). Remove sprocket (20).
(b) Remove nuts (17) and screws (16). Remove motor assembly (18) from support (22).
(5) Remove cover (8) by removing screws (7).
(6) Raise the entire clutch and cable drum assembly until disengaged from bearing (43) and stop (42). Disengage chain
(29) from sprocket (81) and remove assembly from housing.
(7) Remove bushings (75 and 111).
(8) Disassemble clutch assembly as follows:
(a) Using two 0.125 inch punches as holding tools to loosen nut (110), remove nuts (110) from shaft (85).
(b) Remove washers (108 and 107) and spring (109).
(c) Lift drum assembly (93) and washer (107) from shaft (85).
(d) Remove shaft (85) from clutch assembly (80).
(e) Remove sprocket (81) from clutch assembly by removing screws (82).
(9) Disassemble drum assembly as follows:
(a) Remove flanges (96) from drum (93) by removing screws (97).
(b) Identify cables (99 and 104) as to relative position to drum and actuator assembly to aid in reinstallation.
Remove cables from drum.
(c) Press bearing (106) from drum (93).

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Model 500 Series Component Maintenance Manual (Rev 17)
27-30-06-4 (Rev 9)

ELECTRIC TRIM ACTUATOR - CLEANING

1. Cleaning
A. Tools and Equipment Required.
NOTE: Equivalent substitutes may be used for the listed items:
NAME NUMBER MANUFACTURER USE
Methyl n-Propyl ketone Clean metal parts.
Paint Stripper T-6776 LO Turco Products, Inc. Strip paint from metal parts
Westminster, CA 92684 prior to inspection.
Protective Oil Oakite Special Oakite Products Inc. Protect parts that have had
Protective Oil 50 Valley Road paint removed.
Berkeley Heights, NJ 07922
B. Cleaning Procedure.
WARNING: Use cleaning solvents only in well ventilated areas. Avoid inhaling solvent vapors. Keep solvent
and solvent containers away from sparks or open flame.
(1) Clean metal parts and phenolic bearing with a suitable solvent. Remove stubborn deposits by hand rubbing with
nonabrasive pads or material. Apply solvent under pressure to all lubrication fittings, channels and other internal
cavities to insure cleanliness. Thoroughly dry all parts with filtered, dry, compressed air, lint-free cloth, or lint-free
disposable tissue.
NOTE: It is not necessary to remove paint to accomplish a visual inspection of covers and housing;
however, if stripping is required, remove phenolic rub strips and rub blocks from housing or
provide protection.
WARNING: All paint strippers are harmful to eyes and skin. Operators shall wear goggle type eye glasses,
rubber gloves, aprons and boots. In case of contact with skin, flush with water. In case of contact
with eyes, flush eyes thoroughly with water and consult a physician immediately. Paint stripping
shall be done in a well ventilated area. Follow manufacturer's instructions carefully to relieve
pressure before opening paint stripper storage containers.
(2) Brush a suitable paint-stripper on painted parts. Allow the first application to work from 5 to 45 minutes or as advised
by manufacturer's instructions. If necessary, scrub softened areas with brush to loosen paint. Rinse with water.
Repeat as necessary to remove all paint. After paint is completely removed, rinse part thoroughly with water spray.
Dry part with filtered, dry, compressed air, lint- free cloth or lint-free
(3) If inspection and repair procedures do not immediately follow cleaning, coat all surfaces that have had paint removed
with a suitable protective oil.

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Model 500 Series Component Maintenance Manual (Rev 17)
27-30-06-5 (Rev 5)

ELECTRIC TRIM ACTUATOR - CHECK

1. Check
A. Check parts.
(1) Check all parts visually, preferably under magnification. When parts are suspected of irregularities or deformities,
additional inspection shall be administered to verify the service life of the part or the part shall be replaced.
(2) Check applicable parts for dimensional conformity, refer to Electric Trim Actuator - Fits and Clearances.
(3) Check cables for cable to drum attaching hardware, cable wraps around cable drum, and coiled (storage position)
cable. The cable(outside actuator housing) shall be stored in a straight line or in a coil with the coil inside diameter
not less than 150 times the cable diameter.
(4) Check rub blocks for wear. Excessive wear requires replacement and possible additional corrective maintenance.
(5) Check sprocket for worn or damaged teeth.
(6) Check chain for wear and lubrication. Use 5565450- 28 grease if lubrication is required.
(7) Check covers and grommets for condition and security of installation. Replace grommets when evidence of
excessive chaffing has worn through the grommet.
B. Discarded Components.
(1) Verify all defective items are discarded during assembly.
C. Electric Trim Actuator Assembly.
(1) Verify test results, refer to testing.
(2) Verify that the assembled actuator is packaged for storage. Packaging shall consist of protective material to protect
assembly against moisture, dust, and shock (shock being the result of falling from storage shelf).
NOTE: Packaging not required when actuator assembly is to be returned to service immediately.

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Model 500 Series Component Maintenance Manual (Rev 17)
27-30-06-6 (Rev 12)

ELECTRIC TRIM ACTUATOR - REPAIR

1. Repair
A. Tools and Equipment Required.
NOTE: Equivalent substitutes may be used for the listed items.
NAME NUMBER MANUFACTURER USE
Waterborne Corrosion U-4800/U-4801 Sterling Laquer Manufacturing Co. Corrosion protection primer
Resistant Primer MIL- 3150 Brannon St.
PRF-85582 St. Louis, MO 63139
Waterborne Corrosion W9100-K11/ U.S. Paint Corp. Corrosion protection primer
Resistant Primer MIL- W3100 831 South 21st St.
PRF-85582 St. Louis, MO 63130
Waterborne Corrosion 10PW20-4 Akzo Nobel Aerospace Coatings Corrosion protection primer
Resistant Primer MIL- East Water Street
PRF-85582 Waukegan, IL 60085
Enamel, Black Wrinkle Commercially Available Prime coat parts.
Finish
Adhesive EC880 Commercially Available Installation of grommet.
B. Repair Procedures.
(1) Replace all parts that have visual cracks or flaws.
(2) Replace all parts that are worn beyond the limits given in Electric Trim Actuator - Fits and Clearances.
(3) Detail parts of housing may be replaced using standard shop practices.
(4) Caterpillar grommet may be replaced using a rubber base adhesive for a bonding agent. Refer to airplane
maintenance manual, Chapter 20, Adhesive Bonding - Maintenance Practices, for adhesive application.
(5) After painting housing, identify assembly as 5115231-12, -18, -19, -23, -24, -25, -26, -27, -28, -29, -30 or 5565430-
22 and -25 using rubber stamp and ink or marking pencil.
C. Rework Procedures (Refer to Figure 601).
(1) Rework 5565470-42, 5565470-51 and 5565470-57 drums as follows:
(a) Secure drum (clamp) to drill press to provide accurate alignment for drilling.
(b) Using a number 7 drill, drill hole for cable swagged ball to a depth of 0.130 inch (two places). Refer to Figure
601.
(c) Secure drum in vise or other suitable fixture.
NOTE: Ensure no damage occurs while securing drum in fixture.
(d) Using a flat bastard file or other suitable tool, rework cable slots to a depth of 0.120 inch. Refer to Figure 601.
NOTE: After rework is complete, cable surface of drum must be finished to 300 - 400 RMS
minimum and perpendicular to cable direction. End surfaces of drum must have a finish
of 50 RMS minimum.
(e) After rework of drum, reidentify as 5565470-101, using rubber stamp and ink or marking pencil.
D. Painting.
WARNING: Solvent is toxic and flammable. Use only in a well ventilated area. Avoid breathing fumes to prevent
harming physical health. Keep away from sparks or open flame.
(1) Clean covers and housing to be painted with approved solvent.
(2) Mask bearings and phenolic rub blocks.
(3) Apply primer to both sides of covers and housing.
(4) Apply paint to surface of covers using black wrinkle finish paint.

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Model 500 Series Component Maintenance Manual (Rev 17)
27-30-06-6 (Rev 12)

Figure 601 : Sheet 1 : Drum Repair

Copyright © Textron Aviation Inc. Page 2 of 2

ELECTRIC TRIM ACTUATOR - ASSEMBLY

1. Assembly
A. Assemble Trim Tab Actuator (Refer to Illustrated Parts List).
(1) Assemble drum assembly as follows:
(a) If bearing (106) was removed from drum (93), press bearing into place.
(b) Install forward and aft cable assemblies into drum as shown. Refer to Figure 701.
(c) Secure cable assemblies (99 and 104) in place with flanges (96) and screws (97).
(d) Wrap aft cable four turns on the drum and forward cable a minimum of one-half turn and temporarily secure
cable wraps to drum with masking tape, or equivalent, to facilitate installation of drum into next assemblies.
(2) Assemble clutch assembly as follows:
(a) Secure sprocket (81) to clutch assembly with screws (82) using Loctite 222 on threads of screws.
(b) Ascertain that component parts of clutch assembly (80) are properly assembled before proceeding with
assembly of parts.
NOTE: The clutch assembly (80) is purchased as a unit. The breakdown is shown only as a guide
in assembly of component parts.
(3) Assemble in sequence shaft assembly (85), washer (107), drum assembly (93), washers (107 and 108), spring
(109), washer (108), adjusting nut (110) and locking nut (110).
NOTE: When installing a reworked drum, Part Number 5565470-101, new flanges, Part Number
5565470-102 must be installed.
(4) Spray both sides of washers (107) with Molycote 321R dry lubricant prior to installation. Lubricate the following
locations with MIL-PRF-23827:
(a) Gears and shaft of clutch assembly (80).
(b) Bearings (43 and 10).
(c) Chain (29).
(d) Shaft (85) (inside, outside and face).
(e) Drum (93) (bearing only).
(f) Washers (108) (between washers and drum assembly).
(5) Position bushings (75 and 111) on clutch shaft and install the assembly into housing (36), routing cable (99) through
housing and installing chain on sprocket (81) before installation of shaft into bearing (43).
(6) Ascertain that solenoid locking pin is engaged with the hole in stop (43) and install cover (8). Secure cover with
screws (7) and safety wire screws.
(7) Assemble motor assembly as follows:
(a) Position motor assembly (18) to support (22) and secure with screws (16) and nuts (17).
(b) Install sprocket (20) to motor shaft and secure with pin (21). Safety wire through roll pin with 0.020 inch diameter
monel safety wire.
(8) Slide motor assembly into housing (36).
(9) Engage motor sprocket (20) with chain (29), then position motor assembly in place and secure with screws (24) and
nuts (23).
(10) Install cover (13) over motor and secure with screws (12). Safety wire screws.
(11) Install cable guard (32). Hand form cable guard, refer to Electric Trim Actuator - Description. Remove tape from cable
drum.
(12) Attach cleco clamps to cables at forward and aft side of elevator electric trim actuator to retain cable wrap around
drum. Remove tape from cable drum. Refer to Figure 701.
(13) Route electrical wires through grommet (33) in cover plate (27). Secure cover plates (27) with screws (26).
B. Storage.
(1) Roll cables into a 10 inch loop (inside diameter of loop) and tape cables to housing assembly for storage.
(2) Store trim actuator in a clean plastic bag.

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Model 500 Series Component Maintenance Manual (Rev 17)
27-30-06-7 (Rev 13)

Figure 701 : Sheet 1 : Cable Drum Assembly

Copyright © Textron Aviation Inc. Page 2 of 3

Figure 701 : Sheet 2 : Cable Drum Assembly

Copyright © Textron Aviation Inc. Page 3 of 3

ELECTRICAL TRIM ACTUATOR - FITS AND CLEARANCES

1. Fits and Clearances
A. Bearing 5565470-48

(1) 0.689 inch, +0.000, or -0.001 inch (17.50 mm, +0.00 or -0.03 mm) diameter
(2) 0.814 inch, +0.001, or -0.000 inch (20.68 mm, +0.03 or -0.00 mm) diameter
B. Bearing S1004-44A

(1) 0.828 inch, +0.000, or -0.001 inch (21.03 mm, +0.00 or -0.025 mm) diameter
(2) 0.435 inch, +0.001, or -0.000 inch (11.05 mm, +0.025 or -0.000 mm) diameter
C. Drum Assembly 5565470-41, -49, -54

D. Drum Assembly 5565470-58, -86, -88, -103, -104, -105

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Model 500 Series Component Maintenance Manual (Rev 17)
27-30-06-8 (Rev 9)

Copyright © Textron Aviation Inc. Page 2 of 2

ELECTRIC TRIM ACTUATOR ASSEMBLY

NOMENCLATURE EFFECTIVITY UNITS
PER
ITEM PART NUMBER 1 2 3 4 5 6 7 FROM TO ASSY
- ELECTRIC TRIM ACTUATOR ASSEMBLY
- 1 5115231-12 . ACTUATOR ASSY A 01
- 2 5115231-18 . ACTUATOR ASSY B 01
- . ACTUATOR ASSY FSO
3 5115231-19 C NP
5115231-30
- . ACTUATOR ASSY FSO
4 5115231-23 D NP
5115231-28

- . ACTUATOR ASSY FSO

5 5115231-24 E NP
5115231-29

- . ACTUATOR ASSY FSO

5A 5115231-25 F NP
5115231-28

- . ACTUATOR ASSY FSO

5B 5115231-26 G NP
5115231-29
- . ACTUATOR ASSY FSO
5C 5115231-27 H NP
5115231-30
- 5D 5115231-28 . ACTUATOR ASSY J 01
- 5E 5115231-29 . ACTUATOR ASSY K 01
- 5F 5115231-30 . ACTUATOR ASSY L 01
- 6 1560322-5 . . COVER ASSY-CLUTCH 01
ATTACHING
PARTS
7 MS35265-41 . . SCREW 04
---*---
8 1560322-6 . . . COVER 01

- 9 1560322-7 . . . SUPPORT 01
BEARING
10 S1004-44A . . . BEARING 01
- 11 1560322-18 . . COVER ASSY-MOTOR 01
ATTACHING
PARTS
12 MS35265-41 . . SCREW 04
---*---
13 1560322-19 . . . COVER 01
. . . GROMMET 4.50 IN
14 S1050-3 01
LG BKI

- . . MOTOR ASSY-ELECT
15 5115231-13 01
TRIM
ATTACHING
PARTS
16 MS35206-244 . . SCREW 04

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Model 500 Series Component Maintenance Manual (Rev 17)
27-30-06-1001 (Rev 13)

17 MS21042L08 . . NUT 04
- 17A NAS1291-08 . . NUT ALT FOR 04 R
MS21042L08
---*---
18 9910059-2 . . . MOTOR ASSY 01

- . . . DELETED-NOT
19
USED
20 5565470-29 . . . SPROCKET 01
21 NAS561P4-8 . . . PIN 01
- . . . PIN ALT FOR
21A MS16562-33 01 R
NAS561P4-8
22 1560322-9 . . .
SUPPORT 01
ATTACHING
PARTS
23 S2903-08 . . . NUT 04
24 MS24694S3 . . . SCREW 04 R
---*---
- 25 5115233-1 . . COVER ASSY FSO A THRU E NP
5115233-6
- 25A 5115233-6 . . COVER ASSY F THRU L 02
ATTACHING
PARTS
26 MS35206-244 . . SCREW 04
---*---
27 5115233-2 . . . COVER A THRU E 02
- 27A 5115233-5 . . . COVER F THRU L 02
. . . GROMMET 1.80 IN
28 S1050-1 01
LG BKI
29 5115231-14 . . CHAIN 01
30 5115232-1 . . RUB BLOCK 02
ATTACHING
PARTS
- 31 S1726-2 . . RIVET 02
---*---
32 1560322-17 . . CABLE GUARD 01
33 MS35489-4 . . GROMMET 01
HOUSING ASSY-TRIM
- 34 5565470-16 . . A&B 01
ACTUATOR
- . . HOUSING ASSY-TRIM
35 5565470-62 C THRU L 01
ACTUATOR
36 5565470-19 . . . HOUSING 01
- 37 5565470-18 . . . GUARD A&B 01
GUARD FSO
- 38 5565470-61 . . . C NP
5565470-80

Copyright © Textron Aviation Inc. Page 2 of 7

39 5565470-80 . . . GUARD C THRU L 01

- . . . GUARD FSO
40 5565470-60 C NP
5565470-79
41 5565470-79 . . . GUARD C THRU L 01
42 1560322-4 . . . STOP 01
43 S1004-44A . . . BEARING 01
44 NAS42DD4-28 . . . SPACER 04
45 AN256F8 . . . NUTPLATE 08

NOMENCLATURE EFFECTIVITY UNITS

PER
ITEM PART NUMBER 1 2 3 4 5 6 7 FROM TO ASSY
- ELECTRIC TRIM ACTUATOR ASSEMBLY
75 NAS76A4-004 . . BUSHING 01
- 76 5565470-20 . . CLUTCH ASSY A 01
- . . CLUTCH ASSY FSO
77 5565470-55 B NP R
5565470-204
- 77A 5565470-204 . . CLUTCH ASSY B 01 R
- 78 5565470-59 . . CLUTCH ASSY C&H 01 R
- 79 5565470-85 . . CLUTCH ASSY D&F 01 R
- 79A 5565470-87 . . CLUTCH ASSY E&G 01 R
- . . CLUTCH ASSY FSO
79B 5565470-97 J NP R
5565470-202
CLUTCH ASSY FSO
- 79C 5565470-99 . . K NP R
5565470-203
- 79D 5565470-100 . . CLUTCH ASSY L 01
- 79E 5565470-202 . . CLUTCH ASSY J 01 R
- 79F 5565470-203 . . CLUTCH ASSY K 01 R
CLUTCH ASSY-
80 TCS20B . . . ELECTRIC REFER V14412 01 R
TO NOTE 1
81 1560321-6 . . .
SPROCKET 01
ATTACHING
PARTS
82 AN507-440R6 . . . SCREW 03
---*---
83 MS3367-1-9 . . . STA STRAP 01
- . . . DELETED-NOT
84
USED
85 1560321-2 . . . SHAFT ASSY 01
- 86 5565470-41 . . . DRUM ASSY A 01
- 87 5565470-49 . . . DRUM ASSY B 01
DRUM ASSY FSO
- 88 5565470-54 . . . B NP
5565470-49

Copyright © Textron Aviation Inc. Page 3 of 7

- 88A 5565470-58 . . . DRUM ASSY C&H 01

- 88B 5565470-86 . . . DRUM ASSY D&F 01
- 88C 5565470-88 . . . DRUM ASSY E&G 01
- 88D 5565470-105 . . . DRUM ASSY J 01
- 89 5565470-104 . . . DRUM ASSY K 01
- 90 5565470-103 . . . DRUM ASSY L 01
DRUM FSO
- 91 5565470-42 . . . . A&B NP
5565470-51
- 92 5565470-51 . . . . DRUM B 01
- 92A 5565470-57 . . . . DRUM C THRU H 01
93 5565470-101 . . . . DRUM J,K&L 01
FLANGE FSO
- 94 5565470-43 . . . . A&B NP
5565470-50
- 95 5565470-50 . . . . FLANGE B 02
- 95A 5565470-56 . . . . FLANGE C THRU H 01 R
96 5565470-102 . . . . FLANGE J,K&L 01
ATTACHING
PARTS
97 NAS1189-04P4W . . . . SCREW 04
---*---
- . . . . CABLE ASSY-
98 5565470-46 A &B 01
AFT
. . . . CABLE ASSY-
99 5565470-72 C,H&L 01
AFT
CABLE ASSY-
- 100 6565007-147 . . . . J 01
AFT
- . . . . CABLE ASSY-
101 6565007-153 K AR
AFT
- . . . . CABLE ASSY-
102 5565470-44 A 01
FWD
CABLE ASSY-
- 103 5565470-52 . . . . B 01
FWD
. . . . CABLE ASSY- C,D,F,H &
104 5565470-74 01
FWD L
- . . . . CABLE ASSY-
105 5565470-89 E,GJ & K 01
FWD
106 5565470-48 . . . . BEARING 01
107 5565470-98 . . . . WASHER J,K&L 02
108 1560321-4 . . . WASHER 02
109 1560321-9 . . . SPRING 01

Copyright © Textron Aviation Inc. Page 4 of 7

SPRING WASHER
USED ON
5565470-202, -203,
- 109A B1500-062-S . . . & -204 CLUTCH 02 R
ASSEMBLIES
INPLACE OF
1560321-9 SPRING
110 1560321-10 . . . NUT 02
111 NAS76A4-009 . . BUSHING 01
PERMISSIBLE TO INSTALL NAS1149C0416R WASHER IN TCS208 ELECTRIC CLUTCH
NOTE 1: UNDER SPRING WASHER TO MAINTAIN CLUTCH SPACING AND EXTEND SPRING WASHER R
LIFE.
- Item Not Illustrated

Copyright © Textron Aviation Inc. Page 5 of 7

Figure 1001 : Sheet 1 : ELECTRIC TRIM ACTUATOR ASSEMBLY

Copyright © Textron Aviation Inc. Page 6 of 7

Figure 1001 : Sheet 2 : ELECTRIC TRIM ACTUATOR ASSEMBLY

Copyright © Textron Aviation Inc. Page 7 of 7

FLAP/ELEVATOR TRIM MIXER ASSEMBLY - ILLUSTRATED PARTS LIST

1. Illustrated Parts List
A. Introduction.
(1) The Illustrated Parts List has been prepared to assist customer personnel in requisitioning, storing and issuing the
flap/elevator trim mixer assembly components, and in identifying new and reclaimed parts. It is not approved for any
other purpose.
(2) This parts list covers the flap/elevator trim mixer assemblies used on the Cessna Citation S/II and Citation V
airplanes. These part numbers are covered:
6565102-1 6565102-6 6565102-7 6565102-10 6565102-11
6565102-13
(3) The indention system used in the detailed parts list of this catalog shows the relationship of one part to another. For a
given item, the indention code shows a system, installation or general heading starting at the extreme left position
continuing on down into succeeding columns until the end detail is reached. Example:
A18017
1234567
Installation
Detail Parts for Installation
Assembly
Attaching Parts for Assembly
Detail Parts for Assembly
Subassembly
Attaching Parts for Subassembly
Detail Parts for Subassembly
Sub−Subassembly
Attaching Parts for Sub−Subassembly
Detail Parts for Sub−Subassembly

(4) The quantities given in the UNITS PER ASSY column of the Illustrated Parts List are, in the case of assemblies, the
total used at the indicated location. For component parts indented under the assemblies, the quantities are those
used in the assembly. The quantities specified, therefore, are not necessarily the total used per installation.
(5) Effectivity for detail parts of assemblies covered by this technical manual are listed in the Effect column. The code A,
B, C, etc., listed for the assembly is the code for the detail parts peculiar to that assembly. If no code appears in the
Effect column, that detail part is used in all assemblies listed.
(6) When a part of later design is not interchangeable with the part it replaces, both parts applicable to the particular
usage are listed. The individual part usage is listed in the Effect column. When ordering, care should be exercised in
determining proper usage, to ensure receipt of the correct part.
(7) When a part of later design is completely interchangeable with the part it replaces, both parts will be serialized and
the notation FSO (for spares order) will be entered following the listing of the earlier design part. FSO means that the
earlier design part is not available and the later design part must be used.
(8) The basic number identifies the Cessna drawing only. Each installation, assembly or detail part is assigned apart
number which consists of the drawing number and an appropriate dash number.
A12537
EXAMPLE:
Part Number
6707005 − 7

Basic Number Dash Number

(Drawing Identification
Only)

NOTE: Parts stamped with a dash 400 series are for internal control purposes only and should not be
used by the operator for ordering/ identifying purposes.

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Model 500 Series Component Maintenance Manual (Rev 17)
27-30-07-10 (Rev 14)

B. For Vendor names and addresses with Federal Supply Codes, refer to Introduction - Supplier Address List.

Copyright © Textron Aviation Inc. Page 2 of 2

FLAP/ELEVATOR TRIM MIXER ASSEMBLY - DESCRIPTION AND OPERATION

1. Description
A. The flap/elevator trim mixer assembly consists of an electric actuator, a frame assembly, a switch/gear set assembly and a
slip clutch. Refer to Figure 1.
(1) The electric actuator is a 28-volt direct current (VDC) bi-directional motor that is energized by the elevator trim
switches on the control wheel and the autopilot.
(2) The switch/gearset assembly consists of gearset, spacers, switches, switch plates and cams.
(3) To compensate for rapid pitch changes when the flaps are extended or retracted, the flap interconnect switch
energizes the clutch in the actuator to provide elevator trim when the flaps are in motion between 7 degrees and 25
degrees for the -1, -6 or between 15 degrees and 25 degrees, for the -7.
(4) The gear warning switch will sound the gear warning horn when the flaps are beyond the approach position and the
gear is not down.
B. These flap/elevator trim mixer assembly part numbers are affected by this individual component maintenance manual:
6565102-1 6565102-6 6565102-7 6565102-10 6565102-11
6565102-13

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Model 500 Series Component Maintenance Manual (Rev 17)
27-30-07-0 (Rev 14)

Figure 1 : Sheet 1 : Flap/Elevator Trim Mixer Assembly

Copyright © Textron Aviation Inc. Page 2 of 2

FLAP/ELEVATOR TRIM MIXER ASSEMBLY - TESTING

1. Testing
A. It is recommended that the flap/elevator trim mixer assembly be secured to a suitable work bench and test equipment be
provided, as shown in Figure 101
B. Check output shaft free running torque as follows:
(1) Install chain assembly onto output sprocket, as shown in Figure 101.
(2) Hook spring scale to chain assembly, as shown in Figure 101.
(3) Pull on spring scale until sprocket rotates; observe the pounds tension registered on spring scale. The free running
torque should not exceed 6 inch-pounds.
NOTE: The inch-pound torque is converted to pounds tension and described in chart form in Figure
101.
NOTE: If free running torque exceeds 6 inch-pounds, the most probable cause is misalignment of the
trim actuator on the frame assembly. The mixer assembly should be partially disassembled
and the trim actuator re-aligned.
C. Check flap input shaft free running torque as follows:
(1) Install chain assembly onto flap input sprocket, as shown in Figure 101.
(2) Hook spring scale to chain assembly, as shown in Figure 101.
(3) Pull on spring scale until sprocket rotates; observe the pounds tension registered on spring scale. The free running
torque should not exceed 22 inch-pounds.
NOTE: The inch-pound torque is converted to pounds tension and described in chart form in Figure
101.
NOTE: If the free running torque exceeds 22 inch-pounds, the most probable cause is a pinched
nylon washer or spring in the cam/switch plate stackup. The mixer assembly should be
disassembled and the stackup checked.
D. Check slip clutch breakaway torque as follows:
(1) With mixer assembly assembled, as shown in Figure 101, energize the trim actuator's internal engage clutch by
applying 28 VDC to P1240 pigtail, pins 1 and 2.
(2) Install chain assembly onto output sprocket, as shown in Figure 101.
(3) Restrain the flap input sprocket from rotation.
(4) Pull on spring scale until output sprocket rotates; observe the pounds tension registered on spring scale. The
breakaway torque should be 75.0 inch-pounds, +10.0 or -10.0 inch-pounds.
NOTE: The inch- pound torque is converted to pounds tension and described in chart form in Figure
101.
(5) If breakaway torque is not within the acceptable limits, adjust torque by loosening or tightening nuts (2). Refer to
Illustrated Parts List, Figure 1001.

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Model 500 Series Component Maintenance Manual (Rev 17)
27-30-07-1 (Rev 5)

Figure 101 : Sheet 1 : Test Set-Up

Copyright © Textron Aviation Inc. Page 2 of 2

FLAP/ELEVATOR TRIM MIXER ASSEMBLY - DISASSEMBLY

1. Disassembly
A. Disassemble flap/elevator trim mixer assembly (Refer to Illustrated Parts List).
(1) Remove cotter pin (23), pin (20) and washers (21 and 22) securing adjusting screws to frame assembly (12).
(2) Remove actuator assembly.
(a) Remove bolts (25), washers (26) (-1 assembly only), spacers (27); then, remove actuator (24) and plate (31)
from frame assembly (12).
(3) Remove nuts (2), washers (3), spring washer (4), sprocket (5) and washers (6).
(4) Remove bolts (8), washers (9), and bearing retainer (10) with bearing (11).
(5) Remove bolts (16), washers (17) and bearing retainer (18) with bearing (19), washer (14) and spacer (13).
(6) Lift switch/gearset assembly from frame assembly (12).
(7) Disassemble switch/gearset assembly.
(a) Remove cotter pin (111), washer (110), pin (109), terminals (113), screws (112) and lugs (114).
(b) Remove bolts (76) and washer (77).
(c) Remove cams (90, 98 and 106), spacers (81), spring washers (82), spacers (107), switch plates (84, 92, and
100), spacer (79), retainer (80) and sprocket (78).
(d) Identify, tag and remove switches (86, 94 and 102) by removing screws, nuts and washers that secure switches
to switch plates (84, 92 and 100).
(8) Disassemble gearset assembly.
(a) Remove snap-ring (153), washer (154), bearing (160) and carrier (158).
NOTE: If alternate bearing is installed, remove O-ring (162) and bearing (161) in lieu of bearing
(160).
(b) Remove planet gears (155), pins (157) and bearings (159).
NOTE: Pins (157) will need to be removed only when replacement is necessary due to wear.
(c) Remove snap ring (151), washer (152) and bearing (167).
NOTE: If alternate bearing (168) is installed, remove O-ring (169) and bearing (167) in lieu of
bearing (168).
(d) Remove ring gear (165), bearing (166) and seal (164) from pinion shaft (170).
(9) Remove bearings (11 and 19).
(a) Using an arbor press and mandrel, press bearing (11) from retainer (10).
(b) Using an arbor press and mandrel, press bearing (19) from retainer (18).

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Model 500 Series Component Maintenance Manual (Rev 17)
27-30-07-4 (Rev 12)

FLAP/ELEVATOR TRIM MIXER ASSEMBLY - CLEANING

1. Cleaning
A. Tools and Equipment Required.
NOTE: Equivalent substitutes may be used for the listed items:
NAME NUMBER MANUFACTURER USE
Methyl n-Propyl Ketone Type II Cleaning Solvent
Solvent Blend DeSoclean 110 PRC-DeSoto International Type II Cleaning Solvent
5426 San Fernando Rd.
Glendale, CA 91209
Solvent, dry cleaning, MIL-PRF-680 Commercially Available Type I Cleaning Solvent
Protective Oil Oaklite Special Oaklite Products, Inc. 50 Valley Road Protect parts that have had
Protective Oil Berkeley Heights, NJ 07922 paint removed.
B. Cleaning Procedure.
WARNING: Use cleaning solvent only in well ventilated area. Avoid inhaling solvent vapors. Keep solvent
containers away from sparks or open flame.
(1) Clean metal parts with approved solvent. Remove stubborn deposits by hand rubbing with nonabrasive pads or
material. Apply solvent under pressure to all channels and other internal cavities to ensure cleanliness. Thoroughly dry
all parts with filtered, dry, compressed air, lint free cloth or lint free disposable tissue.
NOTE: It is not necessary to remove paint to accomplish a visual inspection of covers and housing.
WARNING: All paint strippers are harmful to eyes and skin. Operators shall wear goggle-type air glasses,
rubber gloves and aprons. In case of contact with eyes, flush eyes thoroughly with water and
consult a physician immediately. Paint stripping shall be done in a ventilated area. Follow
manufacturer's instructions carefully to relieve pressure before opening paint stripper storage
container.
(2) Apply a suitable paint stripper on painted parts. Allow the first application to work from 5 to 45 minutes or as advised
by manufacturer's instructions. If necessary, scrub softened areas with a brush to loosen paint. Rinse with water.
Repeat as necessary to remove all paint. After paint is completely removed, rinse part thoroughly with water spray.
Dry part with filtered, dry, compressed air, lint free cloth or lint free disposable tissue.
(3) If inspection and repair procedures do not immediately follow cleaning, coat all surfaces that have had paint removed
with a suitable protective oil.

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Model 500 Series Component Maintenance Manual (Rev 17)
27-30-07-5 (Rev 5)

FLAP/ELEVATOR TRIM MIXER ASSEMBLY - CHECK

1. Check
A. Check Parts as Follows:
(1) Check all parts visually, preferably under magnification. When parts are suspected of irregularities or deformities,
additional inspection shall be administered to verify the service life of the part or the part shall be replaced.
(2) Check all parts for dimensional conformity. Refer to Flap/Elevator Trim Mixer Assembly - Fits and Clearances.
(3) Check sprockets for worn or damaged teeth.
B. Discarded Components.
(1) Verify that all defective parts are discarded during assembly.
(2) Always discard packings and packing back-up rings and install new parts.

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Model 500 Series Component Maintenance Manual (Rev 17)
27-30-07-6 (Rev 5)

FLAP/ELEVATOR TRIM MIXER ASSEMBLY - REPAIR

1. Repair
A. Repair Procedures:
(1) Replace all parts that have visual cracks or flaws.
(2) Replace all parts that are worn beyond the limits given in Flap/Elevator Trim Mixer Assembly - Fits and Clearances.
(3) Replace all packings, seals and snap rings.

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Model 500 Series Component Maintenance Manual (Rev 17)
27-30-07-7 (Rev 5)

FLAP/ELEVATOR TRIM MIXER ASSEMBLY - ASSEMBLY

1. Assembly
A. Assemble Flap/Elevator Trim Mixer Assembly (Refer to Illustrated Parts List).
(1) Assemble bearings.
(a) If bearings (11 and 19) have been removed from retainers (10 and 18), apply epoxy primer to exterior surface of
bearings and press bearings into retainers.
(b) If bearings (166 and 167) have been removed from ring gear (165), press bearings (166 and 167) into ring gear
(165); observe dimensions shown in Flap/Elevator Trim Mixer Assembly - Fits and Clearances. Position bearing
with seal end as shown.
NOTE: If alternate bearing (168) is being installed, install bearing (168) and O-ring (169); observe
dimensions shown in Flap/Elevator Trim Mixer Assembly - Fits and Clearances.
(c) If bearings (159 and 160) have been removed from carrier (158), press bearings (159 and 160) into carrier
(158); observe dimensions shown in Flap/Elevator Trim Mixer Assembly - Fits and Clearances. Position
bearings with seal end as shown.
NOTE: If alternate bearing (161) is being installed, install bearing (161) and O-ring (162); observe
dimensions shown in Flap/Elevator Trim Mixer Assembly - Fits and Clearances.
(2) Assembly gearset assembly.
(a) Assemble seal (164) into ring gear (165).
(b) Install ring gear (165) onto pinion shaft (170).
(c) Install washer (152) and secure with snap ring (151).
(d) Press pins (157) into carrier (158) to dimensions shown in Flap/Elevator Trim Mixer Assembly - Fits and
Clearances.
(e) Install planet gears (155) onto pins (157).
(f) Pack gearbox with Dow Corning, DC-33 light consistency silicone grease.
(g) Install carrier assembly onto pinion shaft and secure with washer (154) and snap ring (153).
(3) Install switch gearset assembly.
(a) Identify switches (86, 94 and 102) and install on switch plates (84, 92 and 100) securing with screws, washers
and nuts.
(b) Install sprocket (78), retainer (80), spacer (79), switch plates (84, 92 and 100), spacers (107), spring washers
(82), spacers (81) and cams (90, 98 and 106).
(c) Install bolts (76) with washers (77). Safety wire bolts (76).
(d) Install terminals (113), pin (109), washer (110), cotter pin (111), lugs (114) and screws (112).
(4) Install actuator assembly.
(a) Position switch/gearset assembly in place on frame assembly (12).
(b) Install spacer (13), washer (14), retainer (18) with bearing (19) and secure with bolts (16) and washers (17).
Safety wire bolts.
(c) Install bearing retainer (10) with bearing (11) and secure with bolts (8) and washers (9). Safety wire bolts.
(d) Install washers (3 and 6), sprocket (5), spring washer (4) and nuts (2).
(e) Position actuator (24) and plate (31) to frame (12) and secure with bolts (25), washers (26) (-1 assembly only)
and bushings (27) or (27A).
NOTE: Frame (12A) or (12B) must be engaged in the slots in bushings (27A).
(5) Install pin (20), washers (21 and 22) and cotter pin (23).
(6) Check free running and breakaway torques in accordance with instructions in Flap/Elevator Trim Mixer Assembly -
Testing.
NOTE: When the (27A) bushings are used in the -6 , -7, and -10 assemblies the motor will be loose
(float) on the frame assembly. This prevents binding of components within the assembly.

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Model 500 Series Component Maintenance Manual (Rev 17)
27-30-07-8 (Rev 9)

FLAP/ELEVATOR TRIM MIXER ASSEMBLY - FITS AND CLEARANCES

1. Fits and Clearances
A. Pinion Shaft 6565091-1

(1) 0.030 inch, +0.001, or -0.001 inch (0.76 mm, +0.03 or -0.03 mm)
(2) 0.2500 inch, +0.0000, or -0.0005 inch (6.350 mm, +0.000 or -0.013 mm) diameter
(3) 1.3750 inch, +0.0000, or -0.0005 inch (34.930 mm, +0.000 or -0.013 mm) diameter
(4) 0.5000 inch, +0.0000, or -0.0005 inch (12.700 mm, +0.000 or -0.013 mm) diameter
(5) 0.0405 inch, +0.0015, or -0.0015 inch (1.029 mm, +0.038 or -0.038 mm) diameter
(6) 0.3750 inch, +0.0015, or -0.0015 inch (9.525 mm, +0.038 or -0.038 mm) diameter
B. Ring Gear Assembly 6565090-3

(1) 0.130 inch, +0.010, or -0.010 inch (3.30 mm, +0.25 or -0.25 mm)
(2) 0.030 inch, +0.010, or -0.010 inch (0.76 mm, +0.25 or -0.25 mm)
C. Planet Gear 6565094-1

(1) 0.2520 inch, +0.010, or -0.010 inch (6.40 mm, +0.25 or -0.25 mm)
D. Pin 98381A541

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Model 500 Series Component Maintenance Manual (Rev 17)
27-30-07-8 (Rev 9)

(1) 0.2500 inch, +0.0001, or -0.0001 inch (6.350 mm, +0.025 or -0.025 mm)
E. Planet Carrier Asembly 6565090-2

(1) 0.440 inch, +0.0002, or -0.0002 inch (11.18 mm, +0.005 or -0.005 mm)
(2) 0.250 inch, +0.010, or -0.010 inch (6.35 mm, +0.25 or -0.25 mm)
(3) 0.030 inch, +0.010, or -0.010 inch (0.76 mm, +0.25 or -0.25 mm)
(4) 0.130 inch, +0.010, or -0.010 inch (3.3 mm, +0.25 or -0.25 mm)

Copyright © Textron Aviation Inc. Page 2 of 2

MIXER ASSEMBLY-FLAP/ELEVATOR TRIM

NOMENCLATURE EFFECTIVITY UNITS
PER
ITEM PART NUMBER 1 2 3 4 5 6 7 FROM TO ASSY
- MIXER ASSEMBLY-FLAP/ELEVATOR
TRIM

- 1 6565102-1 . MIXER ASSY-TRIM FSO A NP

6565102-6
- 1A 6565102-6 . MIXER ASSY-TRIM B 01
MIXER ASSY-TRIM FSO
- 1B 6565102-7 . C NP
6565102-13
- . MIXER ASSY-TRIM FSO
1C 6565102-10 D NP
6565102-13

- . MIXER ASSY-TRIM FSO

1D 6565102-11 E NP
6565102-13
- 1E 6565102-13 . MIXER ASSY-TRIM F NP
2 1560321-10 . . NUT E 02
3 S2393-2 . . WASHER 03
4 1560321-9 . . WASHER-SPRING E 01
- 4A B1500-062S . . WASHER-SPRING F 02
5 6565103-13 . . SPROCKET 01
6 5565470-98 . . WASHER 02

- 7 6565102-4 . . RETAINER ASSY- 01

BEARING
ATTACHING
PARTS
8 AN3-5A . . BOLT 03
9 AN960-10 . . WASHER 03
WASHER
- 9A NAS1149F0363P . . ALTERNATE FOR 03
AN960-10
---*---
10 6565104-1 . . . RETAINER 01
11 MS27646-41 . . . BEARING 01
12 6565106-1 . . FRAME ASSY A 01
12A 6565106-5 . . FRAME ASSY B 01
12B 6565131-1 . . FRAME ASSY C,D,E 01
13 6565103-14 . . SPACER 01
14 S2014-2 . . WASHER V60380 01

- . . RETAINER ASSY-
15 6565102-5 01
BEARING
ATTACHING
PARTS
16 AN3-4A . . BOLT 03

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Model 500 Series Component Maintenance Manual (Rev 17)
27-30-07-1001 (Rev 14)

17 AN960-10L . . WASHER 03
WASHER
- 17A NAS1149F0332P . . ALTERNATE FOR 03
AN960-10L
---*---
18 6565105-2 . . . RETAINER 01
19 JTT87 . . . BEARING V60380 01
BEARING
- 19A JTT870H . . . ALTERNATE FOR V60380 01
JTT87
20 MS20392-2C57 . . PIN 01
21 AN960-10 . . WASHER AR
WASHER
- 21A NAS1149F0363P . . ALTERNATE FOR AR
AN960-10
22 AN960-10L . . WASHER AR
WASHER
- 22A NAS1149F0332P . . ALTERNATE FOR AR
AN960-10L
23 MS24665-208 . . PIN-COTTER 01
. . ACTUATOR-TRIM FSO
24 44430-3257 V86887 A NP
44430-3657

. . ACTUATOR-TRIM FSO
24A 44430-3357 V86887 B,C,D,E 01
44430-3657
- 24B 44430-3657 . . ACTUATOR-TRIM V86887 B,C,D 01
ATTACHING
PARTS
25 MS9556-14 . . BOLT 04
26 AN960-10L . . WASHER A 04
WASHER
- 26A NAS1149F0332P . . ALTERNATE FOR A 04
AN960-10L
27 NAS43DD3-29 . . SPACER A 04
27A 6565103-16 . . BUSHING B,C,D,E 04
---*---
. . WIRE BUNDLE ASSY-
28 6508010-41 A &B 01
TRIM SWITCH
29 206486-2 . . . CONNECTOR V00779 A &B 01
30 206062-1 . . . BACKSHELL V00779 A &B 01
31 6565103-15 . . PLATE 01

NOMENCLATURE EFFECTIVITY UNITS

PER
ITEM PART NUMBER 1 2 3 4 5 6 7 FROM TO ASSY
- MIXER ASSEMBLY-FLAP/ELEVATOR TRIM

Copyright © Textron Aviation Inc. Page 2 of 8

- 75 6565102-2 . . SWITCH/GEARSET ASSY A &B 01

- 75A 6565102-8 . . SWITCH/GEARSET ASSY C 01
- 75B 6565102-9 . . SWITCH/GEARSET ASSY D,E 01
- 75C 6565102-12 . . SWITCH/GEARSET ASSY F 01
76 AN3H23A . . . BOLT 03
77 AN960-10L . . . WASHER 03
WASHER
- 77A NAS1149F0332P . . . ALTERNATE FOR 03
AN960-10L
78 6565103-12 . . . SPROCKET A &B 01
- 78A 6565103-19 . . . SPROCKET C,D,E 01
79 6565103-8 . . . SPACER 01
80 6565103-6 . . . RETAINER 01
81 6565103-7 . . . SPACER 21
. . . WASHER-SPRING
82 W2028-022 V27745 03
WAVY
PLATE ASSY-
- . . . SWITCH
83 6565103-10 A,B,C,D,E 01
INTERCONNECT
SYSTEM
PLATE ASSY-
SWITCH
- 83A 6565103-23 . . . F 01
INTERCONNECT
SYSTEM
84 6565103-1 . . . . PLATE-SWITCH A,B,C,D,E 01
- 84A 6565103-22 . . . . PLATE-SWITCH F 01
85 JE5 . . . . ACTUATOR V91929 01
86 1SE3-3 . . . . SWITCH V91929 01
ATTACHING
PARTS
87 MS35206-208 . . . . SCREW 02
88 NAS620-2 . . . . WASHER 02
89 MS21042-02 . . . . NUT 02
---*---
CAM-
90 6565103-5 . . . INTERCONNECT A &B 01
SYSTEM
CAM-
- 90A 6565103-18 . . . INTERCONNECT C,D,E 01
SYSTEM
PLATE ASSY-
- 91 6565103-9 . . . SWITCH GEAR 01
WARNING
92 6565103-1 . . . . PLATE-SWITCH 01
93 JE5 . . . . ACTUATOR V91929 01

Copyright © Textron Aviation Inc. Page 3 of 8

94 1SE3-3 . . . . SWITCH V91929 01

ATTACHING
PARTS
95 MS35206-208 . . . . SCREW 02
96 NAS620-2 . . . . WASHER 02
97 MS21042-02 . . . . NUT 02
---*---
. . . CAM-GEAR
98 6565103-4 A &B 01
WARNING
- . . . CAM-GEAR
98A 6565103-20 C,D,E 01
WARNING
PLATE ASSY-
- 99 6565103-11 . . . SWITCH AUTOPILOT 01
FLAP POSITION
100 6565103-1 . . . . PLATE-SWITCH 01
101 JE5 . . . . ACTUATOR V91929 01
102 1SE1-3 . . . . SWITCH V91929 01
ATTACHING
PARTS
103 MS35206-208 . . . . SCREW 02
104 NAS620-2 . . . . WASHER 02
105 MS21042-02 . . . . NUT 02
---*---
106 6565103-2 . . . CAM-AUTOPILOT A,B 01 R
CAM-AUTOPILOT
- 106A 6565103-2 . . . C 01 R
FSO 6565103-21
- 106B 6565103-21 . . . CAM-AUTOPILOT D,E 01 R
107 6565103-3 . . . SPACER 03
- . . SCREW ASSY-
.
108 5565806-2 03
ADJUSTING
ATTACHING
PARTS
109 5565806-4 . . . PIN 01
110 AN960-10 . . . WASHER 01
WASHER
- 110A NAS1149F0363P . . . ALTERNATE FOR 01
AN960-10
111 MS24665-208 . . . PIN-COTTER 01
---*---
112 5565806-3 . . . . SCREW 01
113 AN665-21L . . . . TERMINAL 01
114 5015056-1 . . . . LUG ASSY 01
- 115 MS21209F4-15 . . . . . HELICOIL 01

Copyright © Textron Aviation Inc. Page 4 of 8

NOMENCLATURE EFFECTIVITY UNITS

PER
ITEM PART NUMBER 1 2 3 4 5 6 7 FROM TO ASSY
- MIXER ASSEMBLY-FLAP/ELEVATOR TRIM
- 150 6565090-1 . . . GEARSET ASSY 01
151 MS16624-1025 . . . . RING-SNAP 01
152 6565094-4 . . . . WASHER 01
153 MS16624-1050 . . . . RING-SNAP 01
154 6565094-5 . . . . WASHER 01
155 6565094-1 . . . . GEAR-PLANET 03
- . . . . CARRIER ASSY-
156 6565090-2 01
PLANET
157 MS16555-47 . . . . . PIN 03
PIN ALT FOR
- 157A 98381A541 . . . . . V39428 03
MS16555-47
158 6565092-1 . . . . . CARRIER 01
159 B86 . . . . . BEARING V60380 01
160 JT86 . . . . . BEARING V60380 01
BEARING
161 B86 . . . . . ALT FOR V60380 01
JT86
O-RING USE
162 MS28775-112 . . . . . WITH B86 01
BEARING
- . . . . RING GEAR
163 6565090-3 01
ASSY
164 343099 . . . . . SEAL V70628 01
165 6565093-1 . . . . . RING GEAR 01
166 B66 . . . . . BEARING V60380 01
167 JT48 . . . . . BEARING V60380 01
BEARING
168 B45 . . . . . ALT FOR V60380 01
JT48
O-RING USE
169 MS28775-108 . . . . . WITH B45 01
BEARING
170 6565091-1 . . . . SHAFT-PINION 01
- Item Not Illustrated

Copyright © Textron Aviation Inc. Page 5 of 8

Figure 1001 : Sheet 1 : MIXER ASSEMBLY-FLAP/ELEVATOR TRIM

Copyright © Textron Aviation Inc. Page 6 of 8

Figure 1001 : Sheet 2 : MIXER ASSEMBLY-FLAP/ELEVATOR TRIM

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Figure 1001 : Sheet 3 : MIXER ASSEMBLY-FLAP/ELEVATOR TRIM

Copyright © Textron Aviation Inc. Page 8 of 8

FLAP GEARBOX - ILLUSTRATED PARTS LIST

1. Illustrated Parts List
A. Introduction.
(1) The Illustrated Parts List will help the customer to order, keep, and supply the flap gearbox components. It will also
identify new and reclaimed parts. It is not approved for any other purpose.
(2) The flap gearbox assembly part numbers that follow are covered in this parts list:
5565175-18 5565175-28 5565175-31 5565175-38 5565175-41
(3) The indention system used in the detailed parts list of this catalog shows the relationship of one part to another. For a
given item, the indention code shows a general heading at the extreme left position and continues with indented
columns until the end detail is reached as follows:
A18017
1234567
Installation
Detail Parts for Installation
Assembly
Attaching Parts for Assembly
Detail Parts for Assembly
Subassembly
Attaching Parts for Subassembly
Detail Parts for Subassembly
Sub−Subassembly
Attaching Parts for Sub−Subassembly
Detail Parts for Sub−Subassembly

Basic Number Dash Number

(Drawing Identification
Only)

NOTE: Parts stamped with a dash 400 series are for internal control purpose only and should not be
used by the operator for ordering/identifying purposes.

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Model 500 Series Component Maintenance Manual (Rev 17)
27-50-03-0 (Rev 16)

FLAP GEARBOX - DESCRIPTION AND OPERATION

1. Description and Operation
A. The flap gearbox consists of an input gear and shaft assembly, intermediate gears and an output gear and shaft assembly
enclosed in a housing and cover. Refer to Figure 1.
B. The two intermediate gears permit incoming power to be transmitted from the input gear and shaft assembly to the output
gear and shaft assembly. The input and output gears rotate in roller bearings installed in bearing bores of the gearbox
housing and cover.
C. These flap gearbox part numbers are affected by this individual component maintenance manual:
5565175-18 5565175-28 5565175-31 5565175-38 5565175-41

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Model 500 Series Component Maintenance Manual (Rev 17)
27-50-03-0 (Rev 16)

Figure 1 : Sheet 1 : Flap Gearbox

Copyright © Textron Aviation Inc. Page 2 of 2

FLAP GEARBOX - TESTING

1. Testing
A. Tools and Equipment Required.
NOTE: Equivalent substitutes may be used for the following items.
NAME NUMBER MANUFACTURER USE
Motor 9910055-3 Drive gearbox.
Ammeter 0-30 Commercially Available Measure current.
B. Test Flap Gearbox.
(1) Assemble drive motor to flap gearbox with four M60AS428-10C screws and secure assembly in a suitable holding
device.
(2) Connect a 24 volt direct current (VDC) power source to the drive motor.
(3) Connect a 0-30 ampere ammeter in series with the power lead to the motor.
CAUTION: During operation be prepared to stop should binding or excess friction occur.
(4) Operate motor in each direction of rotation and check for freedom of rotation.
(5) Check ammeter during operation. An ammeter reading of less than 10 amperes is acceptable.

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Model 500 Series Component Maintenance Manual (Rev 17)
27-50-03-2 (Rev 14)

FLAP GEARBOX - OVERHAUL

1. Overhaul
NOTE: Overhaul of 5565175-18, 5565175-28 and 5565175-31 flap gearboxes consists of upgrading them to a
5565175-38 flap gearbox. Overhaul of 5565175-38 and 5565175-41 flap gear boxes consists of restoring
to the original 5565175-38 or 5565175-41 configuration. Refer to the Maintenance Manual, Chapter 5,
Component Time Limits.
A. Overhaul of the flap gearboxes consists of these steps:
(1) Disassemble. Refer to Flap Gearbox - Disassembly. Retain all parts, except discard the listed parts:
(a) 5565175-18
(7) MS16562-3 Pin
(8) AN201KP5A Bearing
(9) 0861558-1 Gear Assembly, Transfer - Consists of gear (10) and bushing
(11)
(12) 5565176-1 Gear, Output
(13) 5565177-2 Shaft, Output
(15) AN201KP8A Bearing
(18) 5565190-7 Pin
(19) 0861560-1 Drive Assembly, Input - Consists of shaft (20), gear (21), gear
(23) and bushing (24)
(26) 5565175-200 Overhaul Placard - If installed
(b) 5565175-28
(7) MS16562-3 Pin
(8) AN201KP5A Bearing
(9) 0861558-1 Gear Assembly, Transfer - Consists of gear (10) and bushing
(11)
(12) 5565176-2 Gear, Output
(13) 5565177-2 Shaft, Output
(15) AN201KP8A Bearing
(18) 5565190-7 Pin
(19) 0861560-3 Drive Assembly, Input - Consists of shaft (20), gear (21), gear
(23) and bushing (24)
(26) 5565175-200 Overhaul Placard - If installed
(c) 5565175-31
(7) MS16562-3 Pin
(8) MS27641-5 Bearing
(9) 0861558-5 Gear Assembly, Transfer - Consists of gear (10) and bushing
(11)
(12) 5565176-2 Gear, Output
(13) 5565177-4 Shaft, Output
(15) MS27641-8 Bearing
(18) 5565190-7 Pin

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Model 500 Series Component Maintenance Manual (Rev 17)
27-50-03-2 (Rev 14)

(19) 0861560-3 Drive Assembly, Input - Consists of shaft (20), gear (21), gear
(23) and bushing (24)
(26) 5565175-200 Overhaul Placard
(28) MS16624- 1050 Snap Ring - Removed from output shaft (13)
(d) 5565175-38
(7) MS16562-3 Pin
MS27641-5
(8) (S3952-5) Bearing
(9) 0861558-5 Gear Assembly, Transfer - Consists of gear (10) and bushing
(11)
(12) 5565176-3 Gear, Output
(13) 5565177-4 Shaft, Output
(15) MS27641-8 Bearing
(18) 5565190-7 Pin
(19) 0861560-4 Drive Assembly, Input - Consists of shaft (20), gear (21), gear
(23) and bushing (24)
(28) MS16624-1050 Snap Ring - Removed from output shaft (13)
(e) 5565175- 41
(7) MS16562-3 Pin
MS27641-5
(8) (S3952-5) Bearing
(9) 0861558-5 Gear Assembly, Transfer - Consists of gear (10) and bushing
(11)
(12A) 5565176-4 Gear, Output
(13A) 5565177-6 Shaft, Output
(15) MS27641-8 Bearing
(18) 5565190-7 Pin
(19A) 0861560-5 Drive Assembly, Input - Consists of shaft (20), gear (21), gear
(23) and bushing (24)
NOTE 1: Number in parentheses refers to index number on Illustrated Parts List.
(2) Clean. Refer to Flap Gearbox - Cleaning.
(3) Check and repair (replace). Refer to Flap Gearbox - Check.
(4) Assemble. Refer to Flap Gearbox - Assembly. Use new parts to replace those found to be out of tolerance and those
which were discarded. Refer to the Illustrated Parts List for proper replacement parts.
(5) Test. Refer to Flap Gearbox - Testing.
(6) Reidentify 5565175-18, 5565175-28 and 5565175-31 flap gearboxes by installing 5565175-40 placard on side of
gear box, and stamp date of overhaul on placard.

Copyright © Textron Aviation Inc. Page 2 of 2

FLAP GEARBOX - DISASSEMBLY

1. General
A. Each part number flap gearbox that is repaired or overhauled will require discarding some parts and subsequent parts
replacement upon reassembly.
B. Disassembly is presented in two sections. The disassembly of flap gearboxes 5565175-18, 5565175-28, 5565175-31
and 5565175-38 is presented first. Refer to Flap Gearbox - Overhaul for listing of discarded parts to replace. Other parts
will be replaced if unserviceable.
2. Disassembly (Flap Gearboxes 5567175-18, 5565175-28, 5565175-31 and 5565175-38)
A. Disassemble Gearbox (Refer to Illustrated Parts List).
(1) Drive roll pin (7) from pinion (6) and output shaft (13). Remove pinion from shaft.
(2) Remove safety wire from pins (18); then drive pins from sprocket (17) and shaft (13). Remove sprocket (17) from
shaft (13).
(3) Remove screws (5) from cover (4) and housing (3).
(4) Tap cover (4) lightly with a soft hammer and separate from housing (3).
CAUTION: Use care not to damage cover or box.
(5) Invert the assembly and remove housing (3) from cover and gear group.
(6) Remove and discard input drive assembly (19), consisting of shaft (20), gear (21), gear (23) and bushing (24), from
cover (4).
(7) Remove gear (12) and shaft (13) from cover (4).
NOTE: Assembly bearing (15) installed in 5565175-31 and 5565175- 38 flap gearboxes is secured on
shaft (13) with lock ring(s) and secured to cover (4) with Loctite. Bearing will remain on the
shaft when the shaft is driven from the cover. Some shafts (13) have provisions for two lock
rings.
(8) Remove bearings (8 and 15) from cover (4) and housing (3) (Refer to Figure 301).
(a) Remove bearings (8) from bearing bores using shop air and a standard air nozzle held snug in the bearing inner
race.
NOTE: Normally, 100 PSI will blow bearing out of bearing bore.
1 If bearing cannot be removed using shop air, completely fill bearing bore and inner race with heavy grease,
preferably wheel bearing grease. Insert shaft, which normally fits into the bearing, and strike it with a soft
hammer.
CAUTION: Cover shaft and housing with a cloth to prevent grease from splattering. Use care not to
damage cover or box.
2 After each strike with a soft hammer, remove shaft and completely fill bearing bore and inner bearing race
with grease and repeat step.
3 If, after attempting preceding steps, bearing cannot be removed, fabricate a tool as shown in Figure 301,
or equivalent, and insert tool to break bearing loose from bore. Repeat steps 2.A.(8)(a)1 thru 3 as required.
CAUTION: Use care not to damage cover or box.
(b) Remove bearings (15) using approved method. Refer to appropriate maintenance manual.
3. Disassembly (Flap Gearbox 5565175-41)
A. Disassemble Gearbox (Refer to Illustrated Parts List).
(1) Drive roll pin (7) from pinion (6) and output shaft (13). Remove pinion from shaft.
(2) Remove safety wire from pins (18) and drive pins from coupling (17A) and shaft (13A). Remove coupling (17A) from
shaft (13A).
(3) Remove screws (5) from cover (4), spacer (25) and housing (3).
(4) Tap cover (4) lightly with a soft hammer and separate from spacer (25) and housing (3).
CAUTION: Use care not to damage cover or box.
(5) Invert the assembly and remove spacer (25) and housing (3) from cover and gear group.

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Model 500 Series Component Maintenance Manual (Rev 17)
27-50-03-3 (Rev 9)

(6) Remove and discard input drive assembly (19A), consisting of shaft (20A), gear (21A), gear (23) and bushing (24),
from cover (4).
(7) Remove gear (12A) and shaft (13A) from cover (4).
(8) Remove bearings (8 and 15) from cover (4) and housing (3).
(a) Remove bearings (8) from bearing bores using shop air and a standard air nozzle held snug in the bearing inner
race.
NOTE: Normally, 100 PSI will blow bearing out of bearing bore.
1 If bearing cannot be removed using shop air, completely fill bearing bore and inner race with heavy grease,
preferably wheel bearing grease. Insert shaft, which normally fits into the bearing, and strike it with a soft
hammer.
CAUTION: Cover shaft and housing with a cloth to prevent grease from splattering. Use care not to
damage cover or box.
2 After each strike with a soft hammer, remove shaft and completely fill bearing bore and inner bearing race
with grease and repeat step.
3 If, after attempting preceding steps, bearing cannot be removed, fabricate a tool as shown in Figure 301,
or equivalent, and insert tool to break the bearing loose from bore. Repeat steps 3.A.(8)(a)1 thru 3 as
required.
CAUTION: Use care not to damage cover or box.
(b) Remove bearings (15) using approved method. Refer to appropriate maintenance manual.

Copyright © Textron Aviation Inc. Page 2 of 3

Figure 301 : Sheet 1 : Fabrication and Insertion - Bearing Removal Tool

Copyright © Textron Aviation Inc. Page 3 of 3

FLAP GEARBOX - CLEANING

1. Cleaning
A. Before cleaning the flap gearbox parts, visually inspect for signs of rubbing, misalignment, or other damage that may not
be visible after cleaning.
B. Clean parts as follows:
WARNING: Use cleaning solvent in a well ventilated area. Avoid breathing fumes and keep solvent away from
open flame.
(1) Soak all parts in clean naptha, MIL-PRF-680, (Type III) solvent, for 20 to 30 minutes.
(2) After soaking, use a stiff bristle, non-metallic brush and remove all dirt particles.
(3) Parts should be dried with a lint-free cloth or a jet of dry, moisture-free, compressed air at 20 to 30 PSIG.

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Model 500 Series Component Maintenance Manual (Rev 17)
27-50-03-5 (Rev 11)

FLAP GEARBOX - CHECK

1. Check
A. Recommended Check Methods.
(1) Consult Table 501 for recommended method of checking each component.
(2) Using a strong light, preferably under magnification, visually inspect all parts for wear, deep scratches, gouges,
missing or damaged gear teeth and for deterioration and corrosion.
(3) Replace all parts showing cracks or flaws under dye penetrant, magnetic particle or visual checking.
(4) Inspect screw threads, both internal and external for evidence of stripping or scoring.
(5) Check all friction surfaces and machined holes for wear beyond tolerances given in Flap Gearbox - Fits and
Clearances.
NOTE: If the bearing bores allow the bearing to be inserted in place without the aid of an arbor press
or tapped in with a drift punch, they are oversize and the gearbox housing must be replaced.
B. Table 501 contains inspection recommendations. Refer to Illustrated Parts List.
Table 501. Recommended Inspection
NOMENCLATURE METHOD OF CHECK FOR REQUIREMENT
ITEM NUMBER CHECKING
Housing (3) Visual Wear, damage No damage that is not repairable.
Gears (10), (12), (21), Dye penetrant Cracks No cracks.
(23)
Visual Wear, damage No damage.
Shafts (13), (20) Magniflux Cracks No cracks.
Visual Wear, damage No damage.
Magniflux Cracks No cracks.

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Model 500 Series Component Maintenance Manual (Rev 17)
27-50-03-6 (Rev 12)

FLAP GEARBOX - REPAIR

1. General Repair
A. Recommended Repair Procedures.
(1) Replace all parts that show visual wear, cracks or flaws.
(2) Replace all parts that show cracks under dye penetrant inspection.
(3) Replace all parts that have machined surfaces or holes that are worn beyond tolerance limits.
(4) Polish or burnish out minor surface damage. Use silicone carbide abrasive cloth for aluminum parts, followed by color
chemical film treatment. Refer to the Model 500 Series Structural Repair Manual, Chapter 51, Protective Treatment of
Metal for application.
(5) Prime exterior surfaces of housing with MIL-PRF-23377G or later corrosion resistant primer.
2. Flap Gearbox Attach Flange Thread Repair
A. The following repair procedure and materials may be utilized for repair of damaged threads (1/4-28UNF-3B) on the four
(4) flap gearbox attach flange mounting holes.
B. Tools and Materials.
NOTE: Equivalent substitutes may be used for the listed items:
NAME NUMBER MANUFACTURER USE
Heli-Coil Kit, 5402-4 Heli-Coil Products Repair damaged flap gearbox
Consisting of the Division of Mite Corporation attach flange threads.
following items: Shelter Rock Lane
Danbury, CT 06810
(24) Inserts 1191-4CN
(1) Tap FPB
(1) Insertion Tool 2299-4
(1)17/64 Drill Bit N/A
C. Repair procedure.
(1) Secure flap gearbox housing in a bench vise or similar device.
CAUTION: When drilling out damaged threads in either of the two (2) blind attach flange holes, a drill stop set
to 0.50 inch must be utilized to prevent damage to the flap gearbox housing.
(2) Utilizing the 17/64 inch drill bit supplied with the 5402-4 Heli-Coil Kit, drill out damaged threads in the affected
gearbox attach flange hole(s). A drill stop set to 0.50 inch must be utilized when drilling out blind holes in attach flange
to prevent damage to the housing. Clean and deburr the hole.
(3) Utilizing the tap supplied with the 5402-4 Heli-Coil Kit, tap threads in the hole under repair to accept the Heli-Coil
insert. Clean and deburr the hole.
(4) Utilizing the insertion tool supplied with the 5402-4 Heli-Coil Kit, thread the Heli-Coil insert into the threaded hole until
flush with, or slightly below the surface of the hole.
(5) Remove tang on insert by tapping with a punch. Discard removed tang.

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Model 500 Series Component Maintenance Manual (Rev 17)
27-50-03-7 (Rev 9)

FLAP GEARBOX - ASSEMBLY

1. Assembly
A. Before starting assembly of flap gearbox, make sure the work bench area and tools are clean and free of abrasive dust or
foreign particles that may be allowed to contaminate gearbox during assembly. Refer to Illustrated Parts List.
B. Assemble (Refer to Illustrated Parts List).
(1) Install bearings (8) in cover (4) using a suitable arbor press and mandrel.
CAUTION: Do not press against inner race of bearing as bearing damage may result.
(2) Press bearings (8) into housing (3).
(3) Verify shaft (20) to gear (21) dimension, from end of shaft to face of small gear, is 0.287 inch, +0.010 or -0.010 inch.
Refer to Flap Gearbox - Fits and Clearances.
(4) Press shaft (13) into gear (12) using a suitable arbor and mandrel to prevent damage to gear.
CAUTION: Use care to ensure gear is not damaged during shaft installation.
(5) If shaft (13) or coupling (17) is new, line ream the pin holes to 0.196 inch, +0.001 or -0.000 inch diameter to ensure
proper fit of pins (18).
(6) Assemble components to cover (4) in sequence as follows:
CAUTION: Do not fill gearbox with grease; excessive grease could stall the drive motor.
(a) Apply a liberal coat of MIL-G-21164 grease to bearings and gear teeth.
(b) Install bearing (15) on shaft (13).
1 Apply Loctite Retaining Compound 35 to the mating surfaces between bearing (15) and cover (4).
2 The mating surfaces shall be treated with Loctite Primer T. The Loctite Retaining Compound 35 shall be
applied to the activated surface when the solvent odor of the primer is no longer present (usually four to five
minutes).
3 Assemble bearing (15) and shaft (13) to cover (4).
(c) Assemble gear (12), shaft (20) and gear assembly (21), gear (10) and gear (23) to cover (4).
(7) On 5565175-41 flap gearbox only, install and align spacer (25) to cover (4).
(a) Assemble cover (4) with spacer (25) while guiding gear assemblies into housing (3).
(8) Install dowel pins (16) through cover, into housing, and secure cover (4) with screws (5).
(9) Install coupling (17) and secure in place with pins (18). Safety wire pins (18).
CAUTION: Use caution when driving in pins (18) and pin (7). Always provide a backup to prevent damage to
the shaft.
(10) Install pinion (6) and secure with roll pin (7). Secure roll pin by installing safety wire through roll pin.
2. Storage
A. Prepare flap gearbox for storage.
(1) Seal input shaft opening with tape.
(2) Store the flap gearbox in a sealed plastic container to protect against moisture.

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Model 500 Series Component Maintenance Manual (Rev 17)
27-50-03-8 (Rev 9)

FLAP GEAR BOX - FITS AND CLEARANCES

1. Fits and Clearances
A. Housing 5115573-2

(1) 0.8113 inch, +0.0012, or -0.0000 inch (20.607 mm, +0.030 or -0.000 mm)
B. Cover 0861554-2

(1) 0.8113 inch, +0.0012, or -0.0000 inch (20.607 mm, +0.030x or -0.000 mm)
(2) 1.1238 inch, +0.0012, or -0.0000 inch (28.545 mm, +0.030 or -0.000 mm)
C. Gear Assembly 0861558-5

(1) 0.3750 inch, +0.0005, or -0.0005 inch (9.525 mm, +0.013 or -0.013 mm) diameter
(2) 0.313 inch, +0.000, or -0.001 inch (7.95 mm, +0.00 or -0.25 mm) diameter
(3) 0.295 inch, +0.005, or -0.005 inch (7.49 mm, +0.13 or -0.13 mm)
(4) 0.636 inch, +0.000, or -0.005 inch (16.15 mm, +0.00 or -0.13 mm)
(5) 0.698 inch, +0.002, or -0.005 inch (17.73 mm, +0.51 or -0.13 mm)

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Model 500 Series Component Maintenance Manual (Rev 17)
27-50-03-8 (Rev 9)

D. Shaft 5565177-5

(1) 0.196 inch, +0.001, or -0.000 inch (4.98 mm, +0.03 or -0.000 mm) diameter
(2) 0.500 inch, +0.000, or -0.001 inch (12.70 mm, +0.00 or -0.03 mm) diameter
(3) 0.312 inch, +0.000, or -0.002 inch (7.92 mm, +0.00 or -0.05 mm) diameter
(4) 0.540 inch, +0.005, or -0.005 inch (13.72 mm, +0.13 or -0.13 mm) diameter
(5) 0.156 inch, +0.000, or -0.002 inch (3.96 mm, +0.00 or -0.05 mm)
(6) 0.283 inch, +0.000, or -0.002 inch (7.19 mm, +0.00 or -0.05 mm)
(7) 1.560 inch, +0.010, or -0.010 inch (39.62 mm, +0.25 or -0.25 mm)
(8) 0.062 inch, +0.005, or -0.000 inch (1.57 mm, +0.13 or -0.000 mm) diameter
E. Shaft 5565177-6

(1) 0.196 inch, +0.001, or -0.000 inch (4.98 mm, +0.03 or -0.000 mm) diameter
(2) 0.500 inch, +0.000, or -0.001 inch (12.70 mm, +0.00 or -0.03 mm) diameter
(3) 0.312 inch, +0.000, or -0.002 inch (7.92 mm, +0.00 or -0.05 mm) diameter
(4) 0.540 inch, +0.005, or -0.005 inch (13.72 mm, +0.13 or -0.13 mm) diameter
(5) 0.156 inch, +0.000, or -0.002 inch (3.96 mm, +0.00 or -0.05 mm)
(6) 0.533 inch, +0.000, or -0.002 inch (13.54 mm, +0.00 or -0.05 mm)
(7) 1.560 inch, +0.010, or -0.010 inch (39.62 mm, +0.25 or -0.25 mm)
(8) 0.062 inch, +0.005, or -0.000 inch (1.57 mm, +0.13 or -0.000 mm) diameter
F. Coupling 5565175-45, -47

(1) 0.196 inch, +0.001, or -0.000 inch (4.98 mm, +0.03 or -0.00 mm) diameter (two places after reaming)

Copyright © Textron Aviation Inc. Page 2 of 5

(2) 0.500 inch, +0.001, or -0.000 inch (12.70 mm, +0.03 or -0.00 mm)
G. Pin 5565190-7

(1) 0.198 inch, +0.001, or -0.000 inch (xx mm, +0.0xx or -0.000 mm) diameter (two places after reaming)
H. Output Gear 5565176-3
A9306

(1)

(3) (2) 5596C1025

(1) 0.017 inch, +0.002, or -0.002 inch (0.43 mm, +0.05 or -0.05 mm)
(2) 0.374 inch, +0.000, or -0.002 inch (9.50 mm, +0.00 or -0.05 mm)
(3) 0.281 inch, +0.000, or -0.002 inch (7.14 mm, +0.00 or -0.05 mm)
I. Output Gear 5565176-4
A9306

(1)

(3) (2) 5596C1025

(1) 0.017 inch, +0.002, or -0.002 inch (0.43 mm, +0.05 or -0.05 mm)
(2) 0.624 inch, +0.000, or -0.002 inch (15.85 mm, +0.00 or -0.05 mm)
(3) 0.531 inch, +0.000, or -0.002 inch (13.49 mm, +0.00 or -0.05 mm)
J. Input and Transfer Gear Assembly 0861558-4

Copyright © Textron Aviation Inc. Page 3 of 5

(1) 0.287 inch (7.29 mm)

(2) 0.3110 inch, +0.0000, or -0.0005 inch (7.899 mm, +0.000 or -0.013 mm) diameter
(3) 0.3130 inch, +0.0005, or -0.0005 inch (7.950 mm, +0.013 or -0.013 mm) diameter
(4) 0.3755 inch, +0.0005, or -0.0005 inch (9.538 mm, +0.013 or -0.013 mm) diameter
(5) 0.010 inch, +0.0005, or -0.0005 inch (0.25 mm, +0.013 or -0.013 mm)
(6) 0.250 inch, +0.005, or -0.005 inch (6.35 mm, +0.13 or -0.13 mm)
(7) 0.377 inch, +0.000, or -0.005 inch (9.58 mm, +0.00 or -0.13 mm)
(8) 0.687 inch, +0.0000, or -0.0005 inch (17.45 mm, +0.013 or -0.013 mm) diameter
K. Input and Transfer Gear Assembly 0861558-5

(1) 0.287 inch (7.29 mm)

Copyright © Textron Aviation Inc. Page 4 of 5

(2) 0.3110 inch, +0.0000, or -0.0005 inch (7.899 mm, +0.000 or -0.013 mm) diameter
(3) 0.3130 inch, +0.0005, or -0.0005 inch (7.950 mm, +0.013 or -0.013 mm) diameter
(4) 0.3755 inch, +0.0005, or -0.0005 inch (9.538 mm, +0.013 or -0.013 mm) diameter
(5) 0.010 inch, +0.0005, or -0.0005 inch (0.25 mm, +0.013 or -0.013 mm)
(6) 0.250 inch, +0.005, or -0.005 inch (6.35 mm, +0.13 or -0.13 mm)
(7) 0.377 inch, +0.000, or -0.005 inch (15.93 mm, +0.00 or -0.13 mm)
(8) 0.687 inch, +0.0000, or -0.0005 inch (17.45 mm, +0.013 or -0.013 mm) diameter

Copyright © Textron Aviation Inc. Page 5 of 5

FLAP GEAR BOX ASSEMBLY

NOMENCLATURE EFFECTIVITY UNITS
PER
ITEM PART NUMBER 1 2 3 4 5 6 7 FROM TO ASSY
- FLAP GEAR BOX ASSEMBLY

- . GEAR BOX ASSY FSO

1 5565175-18 A NP
5565175-38
- . GEAR BOX ASSY FSO
1A 5565175-28 B NP
5565175-38
GEAR BOX ASSY FSO
- 2A 5565175-31 . C NP
5565175-38
- 2B 5565175-38 . GEAR BOX ASSY D 01
- 2C 5565175-41 . GEAR BOX ASSY E 01
3 5115573-2 . . HOUSING 01
4 0861554-2 . . COVER 01
ATTACHING
PARTS
5 MS24693S28 . . SCREW D 06
- 5A MS24693S30 . . SCREW E 06
---*---
6 5565198-4 . . PINION 01
ATTACHING
PARTS
7 MS16562-3 . . PIN 01
---*---
8 MS27641-5 . . BEARING 03

- 9 0861558-5 . . GEAR ASSY- 01

TRANSFER
10 0861558-6 . . . GEAR 01
11 0861557-1 . . . BUSHING 02
12 5565176-3 . . GEAR-OUTPUT D 01
- 12A 5565176-4 . . GEAR-OUTPUT E 01
13 5565177-4 . . SHAFT-OUTPUT 01
13A 5567177-6 . . SHAFT-OUTPUT E 01
- 14 . . DELETED-NOT USED R
15 MS27641-8 . . BEARING 01
16 NAS607-3-4 . . PIN-DOWEL D 02
16A NAS607-3-6 . . PIN-DOWEL E 02
17 5565194-5 . . SPROCKET D 01
17A 5565175-47 . . COUPLING E 01
ATTACHING
PARTS
18 5565190-7 . . PIN 02

Copyright © Textron Aviation Inc. Page 1 of 3

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 13:01:19 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
27-50-03-1001 (Rev 12)

---*---
- 19 0861560-4 . . DRIVE ASSY-INPUT D 01
- 19A 0861560-5 . . DRIVE ASSY-INPUT E 01
20 0861560-2 . . . SHAFT D 01
- 20A 0861560-6 . . . SHAFT E 01
21 0861558-7 . . . GEAR-TRANSFER D 01
- 21A 0861558-8 . . . GEAR-TRANSFER E 01
- . . . GEAR ASSY-
22 0861561-1 01
INPUT
23 0861561-2 . . . . GEAR 01
24 S1003-17B . . . . BEARING 01
25 5565175-43 . . SPACER E 01
26 5565175-40 . . PLACARD D 01
- 27 5565175-44 . . PLACARD E 01
28 MS16624-1050 . . SNAP RING D 01
- Item Not Illustrated

Copyright © Textron Aviation Inc. Page 2 of 3

Figure 1001 : Sheet 1 : FLAP GEAR BOX ASSEMBLY

Copyright © Textron Aviation Inc. Page 3 of 3

SPEED BRAKE ACTUATOR - ILLUSTRATED PARTS LIST

1. Illustrated Parts List
A. Introduction.
(1) The Illustrated Parts List has been prepared to assist customers in requisitioning, storing and issuing the speed
brake actuator components and in identifying new and reclaimed parts. It is not approved for any other purpose.
(2) The speed brake actuator part number that follows is covered in this parts list: 5527230-1
(3) The indention system used in the detailed parts list of this catalog shows the relationship of one part to another. For a
given item, the indention code shows a general heading at the extreme left position and continues with indented
columns until the end detail is reached as follows:
A18017
1234567
Installation
Detail Parts for Installation
Assembly
Attaching Parts for Assembly
Detail Parts for Assembly
Subassembly
Attaching Parts for Subassembly
Detail Parts for Subassembly
Sub−Subassembly
Attaching Parts for Sub−Subassembly
Detail Parts for Sub−Subassembly

(4) The quantities given in the UNITS PER ASSY column of the Illustrated Parts List are, in the case of assemblies, the
total used at the indicated location. For component parts indented under the assemblies, the quantities are those
used in the assembly. The quantities specified, therefore, are not necessarily the total used per installation.
(5) Effectivity for detail parts of assemblies covered by this technical manual are listed in the Effect column. The code A,
B, C, etc., listed for the assembly is the code for the detail parts peculiar to that assembly. If no code appears in the
Effect column, that detail part is used in all assemblies listed.
(6) When a part of later design is not interchangeable with the part it replaces, both parts applicable to the particular
usage are listed. The individual part usage is listed in the Effect column. Care should be exercised in determining
proper usage when ordering to ensure receipt of the correct part.
(7) When a part of later design is completely interchangeable with the part it replaces, both parts will be serialized and
the notation FSO (for spares order) will be entered following the listing of the earlier design part. FSO means that the
earlier design part is not available and the later design part must be used.
(8) The basic number identifies the Cessna drawing only. Each installation, assembly or detail part is assigned a part
number which consists of the drawing number and an appropriate dash number. Example:
A12537
EXAMPLE:
Part Number
6707005 − 7

Basic Number Dash Number

(Drawing Identification
Only)

NOTE: Parts stamped with a dash 400 series are for internal control purposes only and should not be
used by the operator for ordering/identifying purposes.

Copyright © Textron Aviation Inc. Page 1 of 1

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Model 500 Series Component Maintenance Manual (Rev 17)
27-60-04-0 (Rev 12)

SPEED BRAKE ACTUATOR - DESCRIPTION AND OPERATION

1. Description
A. The speed brake actuator is attached to the wing structure and to the bellcrank for extending and retracting the speed
brake doors.
B. The speed brake actuator consists of a barrel assembly, end cap and piston rod. Seals, packings and scrapers prevent
fluid leakage Refer to Figure 1.
2. Operation
A. The speed brake actuator is electrically controlled and hydraulically actuated. Hydraulic fluid acting on the piston will drive
the piston rod to the extend or retract position depending on the positioning of the solenoid operated control valve. The
tapered end of the piston rod acts as an orifice and slows the velocity of the actuator during the retract stroke.
3. Phosphate Ester Base Hydraulic Fluid Safety Precautions
A. Before performing any operation on the speed brake actuator, personnel should read and thoroughly understand the
following instructions.
WARNING: Observe the following safety precautions when working on systems containing phosphate ester
base fluid. Long exposure to this fluid can cause skin dehydration and chapping.
(1) Wash hands thoroughly with soap and water before starting work.
(2) Apply barrier cream (silicone hand cream) to hands, wrists and forearms. Rub cream under fingernails and into
creases in the skin.
(3) Wear goggles when pressure testing components of system or anytime there is a possibility of hydraulic fluid
splashing into eyes.
(4) If hydraulic fluid splashes into eyes, treat eyes immediately by irrigating thoroughly with clear cold water.
(5) Wash hands, wrists and forearms with soap and hot water after contact with hydraulic fluid.
(6) If clothing becomes soaked with hydraulic fluid, remove clothing as soon as possible. Wash hydraulic fluid from
exposed skin with soap and warm water. Wash hydraulic fluid exposed clothes before wearing.
4. Technical Precautions
A. Before any maintenance is performed on hydraulic systems, personnel should read and thoroughly understand the
following precautions. Careful adherence to these instructions will aid in maintaining a functional and trouble-free system.
CAUTION: Observe the following technical precautions when working on hydraulic systems. Phosphate ester
base fluid will attack a wide range of materials including rubber, copper, various plastics and
paints. Failure to observe these precautions could result in damage to equipment.
(1) Make sure that hydraulic fluid does not come into contact with any part or component outside of the hydraulic system.
Keep spillage to an absolute minimum. Clean up spilled hydraulic fluid immediately to prevent contamination of non-
hydraulic components and to avoid false hydraulic leak observations. If spillage occurs, wipe up the fluid with a dry
cloth and wash area with naptha MIL-PRF-680, (Type III).
(2) When components are disassembled, provide suitable protection to prevent foreign material from entering lines or
components by use of caps or covers.
(3) When washing metal parts before assembly, use naptha MIL PRF-680, (Type III) or Methyl n-Propyl Ketone, and
make sure that all traces of the solvent are removed before assembly.
(4) Use only clean hydraulic fluid for flushing or testing hydraulic components.
(5) Do not unpack seals and packings until they are required and ensure that only approved packings and seals are
used.
(6) When assembling hydraulic system packings and seals, lubricate with MCS352 (Aviation Fluids Service Co., St.
Louis, MO 63166) or Skydrol hydraulic fluid. Always lubricate packings and seals immediately before installation.
Threaded fittings should be assembled without the use of lubricants whenever possible. If a lubricant is required to
prevent galling or to otherwise ease installation, use hydraulic fluid or VV-P-236 Petrolatum.
(7) Take care to prevent contamination of phosphate ester base hydraulic fluid with other hydraulic fluids, oils, water or
dirt.

Copyright © Textron Aviation Inc. Page 1 of 2

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Model 500 Series Component Maintenance Manual (Rev 17)
27-60-04-0 (Rev 12)

Figure 1 : Sheet 1 : Speed Brake Actuator

Copyright © Textron Aviation Inc. Page 2 of 2

SPEED BRAKE ACTUATOR - TESTING

1. Testing
A. The actuator shall be carefully examined for any visible defects and conformance with good workmanship.
B. All tests shall be conducted using Skydrol 500B hydraulic fluid at a room temperature of 50°F to 110°F and fluid
temperature between 70°F and 100°F.
C. Tools and Equipment.
NOTE: Equivalent substitutes may be used for the listed item:
NAME NUMBER MANUFACTURER USE
Hydraulic Service Unit, CJMD112-001 Cessna Aircraft Co. Cycle and leakage check
Portable Citation Marketing Div. actuator.
Department 579
P.O. Box 7706
Wichita, KS 67277
D. Functional Check.
(1) With the actuator connected to the hydraulic service unit, cycle the actuator at least two cycles with the piston
unrestrained to demonstrate satisfactory operation, stroke and leakage characteristics. Pressure shall build up to
1500 PSI at the end of each stroke. There shall be no leakage allowed at any joint or boss. Leakage at points where
motion through external packing exists shall be no greater than at the rate of 1 drop per 25 cycles. Dampening shall
be apparent at the end of the retract stroke.
(2) Apply a proof pressure of 2250 PSI, +50 or -50 PSI for a period of three minutes for each pressure application. This
pressure shall be applied to one port and then to the other with the opposite port open to the atmosphere and the
piston bottomed at the opposite end. There shall be no evidence of external or internal leakage. There shall be no
indication of loosening, permanent deformation or rupture of parts of the actuator.
(3) Repeat step (2) above using 1500 PSI.
E. Table 101contains troubleshooting information.
Table 101. Troubleshooting
TROUBLE PROBABLE CAUSE MANUFACTURER
ROUGH OPERATION Damaged barrel. Replace barrel.
Damaged piston. Replace piston.
Contaminated hydraulic fluid. Drain fluid, clean chamber, refill with clean fluid.
FLUID LEAKAGE Damaged or improperly installed Replace packings.
packings.
Worn parts. Replace parts.
NO OPERATION Broken parts. Replace assembly.
Internal seals damaged. Replace seals.

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Model 500 Series Component Maintenance Manual (Rev 17)
27-60-04-3 (Rev 5)

SPEED BRAKE ACTUAT0R - DISASSEMBLY

1. Disassembly
NOTE: Review safety and technical precautions described in Speed Brake Actuator - Description and
Operation concerning the handling of phosphate ester base hydraulic fluid.
A. Disassemble Speed Brake Actuator (Refer to Illustrated Parts List.
NOTE: To remove speed brake actuator from the airplane, refer to the Maintenance Manual, Chapter 27.
(1) Ensure hydraulic fluid is drained from the actuator.
(2) Secure actuator in holding device using care not to damage paint or actuator.
(3) Remove safety wire, then loosen nut (18) while removing key (19) from piston rod (6).
(4) Remove rod end (17) from piston rod (6), then remove nut (18) and key (19) from rod end. Retain nut and key for
reassembly.
(5) Remove safety wire from locknut (15) and lock (16).
(6) Remove locknut (15) and lock (16) from barrel assembly (3).
(7) Separate end cap (14) from barrel (3) by unscrewing end cap and sliding end cap over piston rod (6).
(8) Remove piston rod (6) from barrel (3).
(9) Remove packing (7) and retainers (8) from piston rod (6). Discard packing and retainers.
(10) Remove packing (9) and retainer (10) from barrel (3). Discard packing and retainer.
(11) Remove packing (11), retainer (12) and scraper (13) from end cap (14). Discard packing, retainer and scraper.
(12) Remove nameplate (20) from barrel (3) if required.
(13) Remove barrel assembly from holding device and press bearing (4) from barrel (3).

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Model 500 Series Component Maintenance Manual (Rev 17)
27-60-04-4 (Rev 12)

SPEED BRAKE ACTUATOR - CLEANING

1. Cleaning
A. Tools and Equipment.
NOTE: Equivalent substitutes may be used for the listed item:
NAME NUMBER MANUFACTURER USE
Methyl n-Propyl Ketone Type II Cleaning Solvent
Solvent Blend DeSoclean 110 PRC-DeSoto International Type II Cleaning Solvent
5426 San Fernando Rd.
Glendale, CA 91209
Naptha MIL-PRF-680 (Type Commercially Available Metal parts cleaning that
III) require soak cleaning.
Protective Oil Oaklite Special Oaklite Products, Inc. Protect parts that have had
Protective Oil 50 Valley Road paint removed.
Berkeley Heights, NJ 07922
B. Cleaning.
(1) Clean metal parts with approved solvent. Apply approved solvent under pressure to all channels to ensure
cleanliness. Thoroughly dry all parts with filtered, dry, compressed air and lint-free cloth or lint-free disposable tissue.
WARNING: Use cleaning solvents only in a well ventilated area avoid inhaling solvent vapors. Keep solvent
container away from sparks or open flame. Failure to adhere to this warning could result in injury
to personnel.
CAUTION: If bearings in rod end of barrel assembly are not being replaced, do not allow solvent to enter
bearings. Solvent entering the bearing will destroy the bearing lubricant.

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Model 500 Series Component Maintenance Manual (Rev 17)
27-60-04-5 (Rev 5)

SPEED BRAKE ACTUATOR - CHECK

1. Checking Speed Brake Actuator
A. Always discard packing and packing backup rings and install new parts.
B. Do not attempt to repair damaged or worn parts of the actuator assembly. Discard all defective items and install new parts
during assembly.
C. Check parts.
(1) Check all parts visually, preferably under magnification, for stripped threads, cracks, deep nicks and dents.
(2) Check applicable parts for dimensional conformity to Speed Brake Actuator - Fits and Clearances .

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Model 500 Series Component Maintenance Manual (Rev 17)
27-60-04-6 (Rev 5)

SPEED BRAKE ACTUATOR - REPAIR

1. Repair
A. Repair Procedures.
(1) Replace all parts that have visual cracks or flaws.
(2) Replace all parts that are worn beyond the limits given in Speed Brake Actuator - Fits and Clearances.
(3) Replace all packings, seals and backup rings with new parts.

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Model 500 Series Component Maintenance Manual (Rev 17)
27-60-04-7 (Rev 5)

SPEED BRAKE ACTUATOR - ASSEMBLY

1. Assembly
NOTE: Review safety and technical precautions described in Speed Brake Actuator - Description and
Operation concerning the handling of phosphate ester base hydraulic fluid.
A. Tools and Equipment List.
NOTE: Equivalent substitute may be used for the following item:
NAME NUMBER MANUFACTURER USE
Hydraulic Service Unit, CJMD112-001 Cessna Aircraft Co. To apply pressure to ports of
Portable Citation Marketing Div. actuator.
Department 579
P.O. Box 7706
Wichita, KS 67277
B. Assemble Actuator (Refer to Illustrated Parts List).
(1) Press bearing (4) into barrel (3).
(2) Install new packing (9) and retainer (10) into barrel (3).
(3) Install new packing (11), retainer (12) and scraper (13) into end cap (14).
(4) Install new packing (7) and retainer (8) onto piston rod (6).
(5) Insert piston rod (6) into barrel (3) using care not to damage seals.
(6) Slip end cap (14) over piston rod (6) using care not to damage packings and scraper.
(7) Screw end cap (14) onto barrel (3) until barrel bottoms; then, back off a maximum of one turn to align ports for lock.
(8) Install lock (16) and locknut (15). Tighten locknut snugly at this time.
(9) Install key (19) nut (18) onto rod end (17).
(10) Screw rod end (17) into piston rod (6) to the desired length and then tighten nut (18).
(11) Safety wire nut (18) and key (19).
(12) Place actuator in vise or other suitable holding device.
(13) Using portable hydraulic service unit, apply 2250 PSI, +50 or -50 PSI to extend port of actuator.
(14) With actuator extended, torque locknut (15) to a torque value of 100 inch-pounds.
(15) Safety wire locknut (15) and lock (16).
(16) Remove actuator from holding device and install nameplate (20).

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Model 500 Series Component Maintenance Manual (Rev 17)
27-60-04-8 (Rev 9)

SPEED BRAKE ACTUATOR - FITS AND CLEARANCES

1. Fits and Clearances
A. Barrel

(1) 1.250 inch, +0.002 or -0.000 inch (31.75 mm, +0.05 or -0.00 mm)
B. End Cap

(1) 0.500 inch, +0.001 or -0.000 inch (12.70 mm, +0.03 or -0.00 mm)
C. Piston Rod

(1) 1.050 inch, +0.001 or -0.000 inch (26.67 mm, +0.03 or -0.00 mm)
(2) 0.250 inch, +0.000 or -0.002 inch (6.35 mm, +0.00 or -0.05 mm)
(3) 0.499 inch, +0.001 or -0.000 inch (12.67 mm, +0.03 or -0.00 mm)
(4) 1.249 inch, +0.001 or -0.000 inch (12.70 mm, +0.03 or -0.00 mm)

Copyright © Textron Aviation Inc. Page 1 of 1

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Model 500 Series Component Maintenance Manual (Rev 17)
27-60-04-1001 (Rev 13)

SPEED BRAKE ACTUATOR ASSEMBLY

NOMENCLATURE EFFECTIVITY UNITS
PER
ITEM PART NUMBER 1 2 3 4 5 6 7 FROM TO ASSY
- SPEED BRAKE ACTUATOR ASSEMBLY

- . ACTUATOR ASSY-
1 5527230-1 01
SPEED BRAKE
- 2 5527233-1 . . BARREL ASSY 01
3 5527233-3 . . . BARREL 01
4 MS21232-4 . . . BEARING 01

- 5 MS14101-4 . . . BEARING ALT 01

FOR MS21232-4
6 5527231-1 . . ROD-PISTON 01
7 NAS1611-214 . . O-RING 01
8 MS28774-214 . . RETAINER 02
9 NAS1611-127 . . O-RING 01
10 MS28774-127 . . RETAINER 01
11 NAS1611-112 . . O-RING 01
12 MS28774-112 . . RETAINER 01
13 S30388-1-1 . . SCRAPER 01
14 5527234-1 . . CAP-END 01
15 5527236-2 . . LOCKNUT 01
16 NAS559-3 . . LOCK 01
17 MS21242S04K . . ROD END 01
18 NAS509-5 . . NUT 01
19 NAS559-1 . . KEY 01
20 5527230-2 . . NAMEPLATE 01
- Item Not Illustrated

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Model 500 Series Component Maintenance Manual (Rev 17)
27-60-04-1001 (Rev 13)

Figure 1001 : Sheet 1 : SPEED BRAKE ACTUATOR ASSEMBLY

Copyright © Textron Aviation Inc. Page 2 of 2

MAIN GEAR ASSEMBLY - ILLUSTRATED PARTS LIST

1. Illustrated Parts List
A. Introduction.
(1) The Illustrated Parts List will help the customer to order, keep, and supply the main landing gear components. It will
also identify new and reclaimed parts. It is not approved for any other purpose.
(2) This parts list includes the main landing gear assembly used on the Citation I and Citation II airplanes. Part numbers:
5541000-3 5541000-11 6541000-3 6541000-27 6541000-34
5541000-4 5541000-12 6541000-4 6541000-28 6541000-37
5541000-9 5541000-17 6541000-11 6541000-33 6541000-38
5541000-10 5541000-18 6541000-12
(3) The indention system used in the detailed parts list of this catalog shows the relationship of one part to another. For a
given item, the indention code shows a general heading at the extreme left position and continues with indented
columns until the end detail is reached as follows:
A18017
1234567
Installation
Detail Parts for Installation
Assembly
Attaching Parts for Assembly
Detail Parts for Assembly
Subassembly
Attaching Parts for Subassembly
Detail Parts for Subassembly
Sub−Subassembly
Attaching Parts for Sub−Subassembly
Detail Parts for Sub−Subassembly

Basic Number Dash Number

(Drawing Identification
Only)

NOTE: Parts that have a dash 400 series stamp are for internal control purposes only and must not be
used by the operator to order or to identify parts.
NOTE: Repair parts available and packaged as a kit are identified in the parts list with an asterisk (*).
Kits may be ordered by the kit part number located at the end of the parts list.

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Model 500 Series Component Maintenance Manual (Rev 17)
32-10-00-10 (Rev 14)

B. For Vendor names and addresses with Federal Supply Codes, refer to Introduction - Supplier Address List.

Copyright © Textron Aviation Inc. Page 2 of 2

MAIN GEAR ASSEMBLY - DESCRIPTION AND OPERATION

1. Description
A. The main gear assembly is designed and assembled to permit maneuverability of the airplane on the ground and to retract
into the wing when airborne. It is designed to absorb shock during airplane takeoffs, landings and taxiing. The main gear
assembly consists of a trunnion, shock strut, axle and torque links. Refer to Figure 1 and Figure 2.
(1) The trunnion is connected to the shock strut and is mounted in the wing wheel will with trunnion pins to allow the gear
assembly to retract into the wing.
(2) The shock strut consists of a cylinder assembly, a piston assembly and an isolation piston which floats within the
piston assembly. The chamber above the isolation piston is filled with hydraulic fluid. The chamber below the isolation
piston is charged with dry air or nitrogen. O-ring packings are used on the isolation piston to prevent leakage of
air/nitrogen or hydraulic fluid around the isolation piston.
(3) The axle is connected to the bottom of the strut piston; press fitted and secured with a pin.
(4) Torque links enable adjustment of the gear toe-in and toe-out. The upper torque link is connected at the shock strut
cylinder and the lower torque link connected to the shock strut piston. The upper and lower torque links are connected
together to permit piston vertical movement in the cylinder and prevent piston rotation in the cylinder.
(5) These main gear assembly part numbers are affected by this Section:
5541000-3 5541000-11 6541000-3 6541000-27 6541000-34
5541000-4 5541000-12 6541000-4 6541000-28 6541000-37
5541000-9 5541000-17 6541000-11 6541000-33 6541000-38
5541000-10 5541000-18 6541000-12
2. Operation
A. As weight of the airplane is applied to the main gear assembly, the piston assembly is forced to slide into the cylinder
assembly. This movement forces hydraulic fluid to flow from the cylinder chamber through an orifice in the top of the piston
into the piston chamber against the isolation piston. The restricted fluid flow and the resistance of the compressed
air/nitrogen below the isolation piston dampens the movement of the piston assembly and absorbs compression shocks.
As the weight of the airplane is removed from the main gear assembly, the compressed air/nitrogen forces the isolation
piston toward the top of the piston chamber. The hydraulic fluid is forced into the cylinder chamber and the piston assembly
extends. Refer to Figure 3.
3. Personnel Safety Precautions - Hydraulic Fluid
A. The main gear assembly contains phosphate ester base hydraulic fluid. Before performing maintenance or any operation
on the main gear shock strut assembly, personnel should read and thoroughly understand this warning.
WARNING: Observe the following safety precautions when working on systems containing phosphate ester
base fluid. Prolonged exposure to the fluid can cause skin dehydration and chapping.
(1) Wash hands thoroughly with soap and water before starting work; apply barrier cream (silicone hand cream) to
hands, wrists and forearms. Rub cream under fingernails and into creases of skin.
(2) Wear eye goggles when pressure testing components or systems or anytime there is a possibility of hydraulic fluid
spraying/splashing in the eyes.
(3) If hydraulic fluid enters the eyes, treat eyes immediately by irrigating thoroughly with clear, cold water.
(4) Wash hands, wrists and forearms with soap and warm water after contacting hydraulic fluid.
(5) !f clothing becomes soaked with hydraulic fluid, remove the clothing as soon as possible. Wash hydraulic fluid
exposed skin with soap and warm water. Wash hydraulic fluid contaminated clothes before wearing.
4. Technical Safety Precautions - Hydraulic Fluid
A. Because the main gear strut contains phosphate ester base hydraulic fluid, improper maintenance practices can be
damaging to gear components and other equipment. Before performing maintenance or any operation on the main gear
shock strut assembly, personnel should read and thoroughly understand the following technical precautions.
CAUTION: Phosphate ester base hydraulic fluid will damage and/or deteriorate a wide range of materials,
including rubber, copper, various plastics and paints.
(1) Make sure that hydraulic fluid does not come in contact with any part of the component outside of the main gear

Copyright © Textron Aviation Inc. Page 1 of 5

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 13:08:00 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
32-10-00-0 (Rev 14)

shock strut. Keep spillage to an absolute minimum. Clean up spilled hydraulic fluid immediately to prevent
contamination of non- hydraulic components and to avoid false hydraulic leak detections. If spillage occurs, wipe up
the fluid with a dry cloth and wash area with naphtha MIL-PRF-680, (Type III).
(2) When gear components are disassembled, provide suitable protection for preventing entry of foreign material by
using caps and/or covers.
(3) Always check angle and position of components prior to disassembly to ensure proper alignment and placement of
components and hardware during assembly or replacement.
(4) Use naphtha MIL-PRF-680, (Type III) or Methyl n-Propyl Ketone, when washing metal parts prior to assembly. Make
sure all traces of the cleaning agent are removed before assembly.
(5) Use only clean hydraulic fluid for flushing or testing hydraulic components.
(6) Do not unpack seals, O-rings/packings until they are required and insure that only correct and approved seals, O-
rings/packings are used.
(7) When assembling the gear shock strut hydraulic seals and O-rings/packings, lubricate only with phosphate ester
base hydraulic fluid. Always lubricate seals, O-rings/packings immediately before installation. Threaded fittings
should be assembled without the use of lubricants whenever possible. If a lubricant is required to prevent galling or to
otherwise ease installation, use phosphate ester base hydraulic fluid or VV-P-236 Petrolatum.
CAUTION: Take special care not to contaminate seals, o-rings/ packings after lubrication.
CAUTION: Prevent contamination of phosphate ester base hydraulic fluid with other hydraulic fluids, oil, water
or dirt.

Copyright © Textron Aviation Inc. Page 2 of 5

Figure 1 : Sheet 1 : Main Gear Assembly

A83872

Trunnion

Strut Drag Brace

Torque Links

Axle

5641T1063

Copyright © Textron Aviation Inc. Page 3 of 5

Figure 2 : Sheet 1 : Main Gear Strut Assembly

Copyright © Textron Aviation Inc. Page 4 of 5

Figure 3 : Sheet 1 : Main Gear Strut Assembly Operation

Copyright © Textron Aviation Inc. Page 5 of 5

MAIN GEAR ASSEMBLY - TESTING

1. Testing
A. Service Main Gear Strut for Test.
WARNING: Do not stand in front of valve assembly while releasing air/ nitrogen pressure. Do not turn 0.75 inch
hex nut while releasing air/nitrogen pressure. Removing air filler valve without releasing
air/nitrogen pressure first can cause bodily injury.
(1) Position and maintain strut in an upright position to expel any fluid collected in the air chamber.
(a) Entry of fluid in the air chamber occurs as the oil film seeps by the seal during strut operation. A nominal amount
of oil seepage on a strut is approximately one drop per 100 hours of operation; however, some struts may have
more or less seepage and still be serviceable.
(b) Fluid accumulation in the strut air chamber with little or no piston movement requires additional inspection and
maintenance to correct oil from leaking into the air chamber.
(2) Rotate outer 0.625 inch hex nut on the air filler valve (AN6287-1) counterclockwise (CCW) to lift internal valve poppet.
Attach a valve core depressor or remove valve core to release any trapped air/nitrogen and/or fluid.
(3) Remove plug (AN814-4) from the top of the strut and replace with a union (AN815-4) and gasket (NAS1612-4).
(4) Attach hose from a hand pump containing clean hydraulic fluid (Skydrol 500B or equivalent), and operate pump until
the strut is partially extended, but not to the stop limit.
CAUTION: Do not exceed 300 PSIG applied pressure.
(5) Open pump check valve and force strut to the collapsed position as trapped air expels into hand pump reservoir.
(6) Repeat pump cycling of strut until no air/nitrogen is being discharged from the fluid chamber.
(7) Discontinue pump cycling of the strut with the strut in the collapsed position. Remove hose, fitting (union) and gasket.
(8) Keep full of fluid and do not disturb strut from the collapsed position until plug and new gasket has been installed in
the top of the strut and tightened. The fluid chamber is to be entirely free of air/nitrogen. Safety wire plug to trunnion
attach nut using the double-twist method of installing safety wire.
NOTE: Strut assembly to be charged/serviced with nitrogen only.
WARNING: Servicing the strut with air before strut is properly serviced with hydraulic fluid could result in
blowing strut apart causing damage to equipment and/or injury to personnel.
(9) Install nitrogen filler valve core (if previously removed). Connect nitrogen source with pressure gage and charge strut
by turning 0.625 inch hex nut a maximum of 1-1/2 turns CCW. Charge strut with nitrogen.
(a) On P/N 5541000-3, -4, -9 and -10 main gear assemblies, charge strut to 250 PSIG with strut fully extended.
Bleed pressure down to 192 PSIG.
(b) On P/N 5541000-11 and -12 and 6541000-11 and -12 main gear assemblies, charge strut to 250 PSIG with
strut fully extended. Bleed pressure down to 212 PSIG.
(c) On P/N 6541000-3, -4, -27 and -28 main gear assemblies, charge strut to 250 PSIG with strut fully extended.
Bleed pressure down to:
1 For Model 550: 234 PSIG.
2 For Model 551: 222 PSIG.
(10) Tighten 0.625 inch hex nut to 50-70 inch-pounds.
B. Test.
(1) After accomplishing Testing, paragraph A, leave strut assembly charged for a one hour period. No fluid leakage or
loss of nitrogen pressure as indicated on the pressure gage is permissible.
WARNING: Do not stand in front of filler valve assembly when releasing nitrogen pressure. Do not turn 0.75
inch hex nut while releasing pressure. Removing nitrogen filler valve without releasing nitrogen
pressure first can cause bodily injury.
(2) Release all nitrogen from the strut through the filler valve. If fluid is noted coming through the filler valve, consult
troubleshooting procedure.
2. Troubleshooting
A. The main gear assembly may be tested as outlined in Testing, for determining fluid or nitrogen leakage. Testing results,

Copyright © Textron Aviation Inc. Page 1 of 2

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 13:08:07 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
32-10-00-1 (Rev 5)

visual checking and/or a review of information received with the gear assembly may be utilized in conjunction with the
following while troubleshooting.
B. Trouble/Probable Cause/Remedy.
TROUBLE PROBABLE CAUSE REMEDY
OIL LEAK AROUND Damaged packings or seals on lower bearing Replace packings and seals. Hone
PISTON piston.
Damaged scraper Replace scraper.
Cracked bearing Replace bearing.
Piston cut or nicked Polish out cut or nick.
Flat spot on piston Replace piston.
STRUT DOES NOT Damaged or worn packings on isolation piston. Replace packings.
EXTEND WHEN
WEIGHT REMOVED
Isolation piston damaged. Replace isolation piston.
Low nitrogen pressure. Replace nitrogen valve.
OIL PRESENT WHEN Piston wall damaged. Replace piston.
NITROGEN VALVE
OPENED

Copyright © Textron Aviation Inc. Page 2 of 2

MAIN GEAR ASSEMBLY - DISASSEMBLY

1. Disassembly
NOTE: Review safety precautions in Main Gear Assembly - Description and Operation before beginning
disassembly.
A. Preparation for Disassembly (Refer to Figure 1001).
(1) Rotate 0.625 inch (15.875 mm) hex nut on air valve (154) counterclockwise one and one-half turns to lift internal valve
poppet, then release any trapped gas or liquid by depressing valve core.
WARNING: Do not stand in front of valve assembly while releasing gas pressure. Do not turn 0.75 inch (19.05
mm) hex nut while releasing gas pressure. Removing air valve without releasing compressed gas
can cause bodily injury.
(2) Ensure that gas is released by sliding piston in and out of cylinder.
(3) Cut lockwire and remove air valve (154) and packing (155) from piston assembly.
(4) Remove plug (159) and packing (160) from top of cylinder assembly (106B).
(5) Drain hydraulic fluid by inverting strut assembly.
B. Torque Link Removal. (Refer to Figure 1002)
(1) Remove upper and lower torque link shaft attach pins (20 and 21).
(2) Remove upper and lower torque link shafts (19). Note shaft positions for reassembly.
(3) Remove torque links (24 and 25) from strut assembly before further disassembly.
(4) Remove cotter pin (39), nut (38), washer (37), spacing washers (34, 35 and 36) and bolt (33).
NOTE: Avoid changing toe-in adjustment. Note location of each torque link attaching part for
reassembly.
(5) Remove bushings (30 and 31) from torque links.
C. Piston Removal (Refer to Figure 1002).
(1) Push bearing (79) and retainer (83) into cylinder enough to free lock ring (85). Remove lock ring (85) from cylinder.
(2) Remove piston assembly from cylinder.
D. Piston Disassembly (Refer to Figure 1002).
(1) Remove four setscrews (46) from bearing (45).
(2) Unscrew and remove bearing (45) from top of piston assembly.
(3) Remove retainer (43) and orifice (41) from bearing (45).
(4) Remove spacer (75) from barrel of piston assembly.
(5) Slide phenolic bearing block (79), scraper (81), scraper retainer (83) and lock ring (85) from piston assembly barrel.
(6) Remove packing (76) and backup retainer (77) from bearing block (79).
(7) Remove polypack seal (80) (or packing and seal cap, if installed) from inner channel of bearing block (79).
(8) Extract isolation piston (110), spring (113), stop (114) and retainer (115) from piston assembly barrel.
NOTE: A hole has been drilled and tapped (10-32 UNF 3B) in the center of the isolation piston to
facilitate removal.
(9) Compress spring (113) to remove retainer (115). Remove retainer (115), spring (113) and stop (114) from isolation
piston (110).
(10) Remove upper and lower Teflon packings (111) and center packing (108) from isolation piston (110).
E. Axle Removal (Refer to Figure 1002).
NOTE: Do not remove axle unless inspection reveals that replacement is necessary. If axle is cracked or
damaged, inspect barrel and forging assembly before removing axle.
(1) Remove the safety wire and drive out the pin (106) securing the axle to the piston. Discard the pin.
(2) Using an arbor press, support the piston on a wooden block centered over a 2.25 inch (57.15 mm) diameter hole in
the block. Press out the axle using care to prevent damage to the piston.
(3) Remove expansion plug (105) from axle (103).

Copyright © Textron Aviation Inc. Page 1 of 2

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 13:08:08 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
32-10-00-3 (Rev 14)

F. Trunnion and Cylinder Disassembly (Refer to Figure 1001).

NOTE: It is not necessary to disassemble the trunnion and the cylinder to prevent corrosion if they were
assembled with Loctite 609.
(1) Remove two aft bolts (85), washers, bushings and nuts.
(2) Remove two forward bolts (81), washers and nuts.
(3) Remove cylinder from trunnion.

Copyright © Textron Aviation Inc. Page 2 of 2

MAIN GEAR ASSEMBLY - CLEANING

1. Cleaning
A. Tools and Equipment.
NOTE: Equivalent substitutes may be used for the listed items:
NAME NUMBER MANUFACTURER USE
Methyl n-Propyl Ketone Clean metal and phenolic
parts.
Naptha MIL-PRF-680 (Type Commercially Available Metal parts cleaning that
III) require soak cleaning.
Paint Stripper T-6776 LO Turco Products, Inc. Strip paint from metal parts
Westminster 92684 prior to inspection.
CA
Protective Oil Oakite Special Oakite Products Inc. Protect metal surfaces that
Protective Oil 50 Valley Road have had paint removed.
Berkeley Heights, NJ 07922
Hydraulic Assembly MCS 352 Aviation Fluids Service Co. Protect surfaces normally in
Lubricant St. Louis, MO 63166 contact with hydraulic fluid.
B. Cleaning.
WARNING: Use cleaning solvents only in well ventilated areas. Avoid inhaling solvent vapors. Keep solvent
and solvent containers away from spark or open flame.
(1) Clean metal parts and phenolic bearings with approved solvent. Remove stubborn deposits by hand-rubbing with
nonabrasive pads or material. Apply approved solvent under pressure to all lubrication fittings, channels and other
internal cavities to ensure cleanness. Thoroughly dry all parts with filtered, dry, compressed air and a lint-free cloth or
lint-free disposable tissue.
(2) Labels or identification plates which are attached by adhesive shall be removed by lifting the corner and pulling free.
Remove adhesive with clean cloth dipped in cleaning solvent.
CAUTION: Do not allow paint stripper to contact high heat treated steel pins such as pins attaching landing
gear components. Paint strippers may induce hydrogen embrittlement in high heat treated steel.
(3) Before stripping paint, thoroughly mask off or remove high heat treated steel pins such as pins attaching landing gear
components.
WARNING: All paint strippers are harmful to eyes and skin. Operators shall wear goggle-type glasses, rubber
gloves, aprons and boots. In case of contact with skin, flush with water. In case of contact with
eyes, flush eyes thoroughly with water and consult a physician immediately. Paint stripping shall
be done in a well ventilated area. Follow manufacturer's instructions carefully to release pressure
before opening paint stripper storage containers.
(4) Apply a suitable paint stripper on painted parts. Allow the first application to work from 5 to 45 minutes or as advised
by manufacturer's instructions. If necessary, scrub softened areas with brush to loosen paint. Rinse with water.
Repeat as necessary to remove all paint. After paint is completely removed, rinse part thoroughly with water spray.
Dry part with filtered, dry, compressed air and a lint-free cloth or lint-free disposable tissue.
(5) After drying, coat all parts, that would normally come in contact with hydraulic fluid during operation, with clean
hydraulic fluid or hydraulic assembly lubricant. External metal surfaces or other parts not coming in contact with
hydraulic fluid during operation of the strut need not be coated. However, highly machined surfaces may be coated
with hydraulic fluid or other suitable protective coating.
(6) If checking and repair procedures do not immediately follow cleaning, coat all surfaces that have had paint removed
with a suitable protective oil.

Copyright © Textron Aviation Inc. Page 1 of 1

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 13:08:09 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
32-10-00-5 (Rev 7)

MAIN GEAR ASSEMBLY - CHECK

1. Check
A. Tools and Equipment.
NOTE: Equivalent substitutes may be used for the following item:
NAME NUMBER MANUFACTURER USE
Cupric Sulfate Commercially Available Chrome surface check.
Sulfuric Acid Concentrated (18N) Commercially Available Chrome surface check.
B. Recommended Checking Methods.
(1) Consult Table 501 to determine the recommended method of checking each component.
(2) Check all parts visually under strong light for surface cracks, flaws, burrs, pitting, scoring or any other wear.
(3) Replace all parts showing cracks or flaws under dye penetrant, magnetic particle or visual inspection.
(4) Check all friction surfaces and machined holes for wear beyond tolerances given in Fits and Clearances.
(5) Check all bolts, nuts and screw threads, both external and internal, for evidence of stripping or scoring. Replace all
parts that have stripped threads.
(6) Check shafts and pins for ovaling, or other signs of wear.
C. Checking Chrome Plating.
CAUTION: When mixing solutions, always add acid to water; never add water to acid.
(1) Check the chrome surfaces of the shock strut assembly for scratches, scores, blisters, and nicks. All suspected
defects should be tested to determine if the base metal has been exposed. To test, apply liberally to the suspected
areas a copper sulfate solution consisting of 100 grams cupric sulfate, five (5) milliliters sulfuric acid and one (1) liter
of water. Wipe off excess liquid and inspect, using a strong light and a magnifying lens. If the chrome plating has been
penetrated, a copper coating will adhere to the ferrous metal. Clean the area thoroughly using solvent. If the chrome
plating has been penetratedin the sealing area, the part shall not be returned to airplane use. If the chrome plating on
the piston below the sealing surface is penetrated but no damage to the steel is detectable, then the chrome damage
may be repaired by cleaning and applying epoxy primer. After this repair is complete the piston may be returned to
service. Defects that have not penetrated the chrome plating should be polished to remove sharp edges that could
damage seals. A honing stone or crocus cloth may be used for this purpose.
D. Table 501 contains Recommended Inspection (Refer to Illustrated Parts List, Figure 1001 andFigure 1002 for Reference).
Nomenclature Item Number Same as Method of Check For Requirement
Illustrated Parts List Number Checking
Cylinder (105) (Reference Figure 1001) Visual Wear, damage No damage or wear that would
endanger structure or interfere with
function.
Cracks No cracks.
Air valve (160) Visual Damage, stripped No damage or stripped threads.
threads
Plug (165) Visual Stripped threads No stripped threads.
Piston (96A) (Reference Figure 1002) Visual Wear, damage inner No wear or damage that would
diameter finish prevent function.
Magnetic particle Cracks No cracks.
Ultrasonic Cracks No voids or cracks in brazed joints.
Retainers (43, 115 and 83) Visual Wear, Damage No wear or damage that would
prevent function.
Bearings (45 and 79) Visual Wear, Damage No obvious wear or damage.

Copyright © Textron Aviation Inc. Page 1 of 2

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 13:08:10 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
32-10-00-5 (Rev 7)

Isolation piston (110) Visual Wear, Damage No wear or damage that would
prevent function or sealing
capability.
Dye penetrant No cracks.
Cracks
Shafts (19) (Reference Figure 1002) Visual Ovaling or other Must meet dimensions given in
damage Fits and Clearances.
Magnetic particle Cracks No cracks.
Upper and lower torque links (24 and 25) Visual Out of round bearing Holes must meet tolerances given
holes, wear or other in Fits and Clearances. No wear or
damage other damage that would endanger
structure or prevent function.
Dye penetrant Cracks No cracks.
Spacer (75) Visual Damage or wear No obvious wear or damage.
Axle (103) Visual Stripped threads, No damage.
damage
Magnetic particle Cracks No cracks.
Piston (96A) Visual Corrosion Check for corrosion in areas
described in Main Gear Assembly
- Repairs. If corrosion is detected,
repair as indicated. If corrosion is
detected in areas other than those
described for repairs, contact
Citation Customer Services
Department for disposition.

Copyright © Textron Aviation Inc. Page 2 of 2

MAIN GEAR ASSEMBLY - REPAIR

1. Repair
NOTE: It is recommended that superseded parts be replaced in lieu of repair.
A. Tools and Equipment.
NOTE: Equivalent substitutes may be used for the following items.
NAME NUMBER MANUFACTURER USE
Wet or dry sandpaper 400 Commercially Available Remove corrosion from gear
strut.
Emery Cloth 320 grit 400 grit Commercially Available Remove corrosion and final
finishing of axle and piston axle
adaptor.
Color Chemical Film Alodine 1132 Henkel (Parker Amchem) Protective treatment of
Treatment 32100 Stephenson Highway aluminum
Madison Heights, MI 48071
Color Chemical Film Alodine 1203 Henkel (Parker Amchem) Protective treatment of
Treatment aluminum
Chemical Film Iridite No. 15 Witco Corporation Protective treatment of
Treatment 400 Midland Ave. magnesium
Highland Park, MI
Pretreatment primer DOD-P-15328 Sherwin-Williams Inc. Pretreatment primer
Base 728-014 16116 E. 13th Street
Reducer 728-013 Wichita, KS
Waterborne Corrosion U-4800/U-4801 Sterling Laquer Manufacturing Co. Corrosion protection primer
Resistant Primer MIL- 3150 Brannon St.
PRF-85582 St. Louis, MO 63139
Waterborne Corrosion W9100- U.S. Paint Corp. Corrosion protection primer
Resistant Primer MIL- K11/W3100 831 South 21st St.
PRF-85582 St. Louis, MO 63130
Waterborne Corrosion 10PW20-4 Akxo Nobel Aerospace Corrosion protection primer
Resistant Primer MIL- East Water Street
PRF-85582 Waukegan, IL 60085
Waterborne Corrosion 44-GN-60/ 44-GN- Deft, Inc. Corrosion protection primer
Resistant Primer 60 CATA 17151 Von Karman Ave.
Irvine, CA 92714
Polyurethane paint, 7400 (Color Name: U.S. Paint Corp. Finish paint.
medium gray Pewter)
Corrosion Resistant U-1201F/ U-1202F Sterling Lacquer Mfg. Corrosion protection primer.
Primer MIL-PRF-
23377G or later
Adhesive RTV-154 General Electric Co. Bond filling instructions placard
Silicone Products Dept. to strut.
Waterford, NY 12188
Clear enamel AA92-C-21C U.S. Paint Corp. Cover filling instructions
placard.
Catalyst AA92-C-22B U.S. Paint Corp. Cover filling instructions
placard.

Copyright © Textron Aviation Inc. Page 1 of 13

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 13:08:11 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
32-10-00-6 (Rev 17)

Flexible drive Shaft Commercially Available To hone piston assembly inner

with 1/4 inch chuck barrel.
Hone CF63 or CF68 Snap-On Tools To hone piston assembly inner
3150 Terrace barrel.
Kansas City, MO 64111
Honing oil Sun Concentrate Sun Oil Company To oil stones while honing.
1501 P.O. Box 2039
Tulsa, OK 74102
Hydraulic assembly MCS 352 Aviation Fluids Service Co. To lubricate piston assembly
lubricant St. Louis, MO 63166 inner barrel.
Stones - 2 2-inch fine JT63-24 Snap-On Tools Used with CF63 or CF68
(400 grit) hones to hone piston assembly
inner barrel.
B. Replacement of Damaged Parts.
(1) Replace all parts that show visual wear, cracks or flaws.
(2) Replace all parts that show cracks under visual or dye penetrant inspection.
(3) Replace all parts indicating cracks or flaws under ultrasonic, X-ray, or magnetic particle inspection.
(4) Replace all parts that have machined holes that are worn beyond tolerance limits.
C. Chrome Surface Repair.
CAUTION: When buffing or polishing out scratches on chrome surfaces, extreme caution must be taken not
to penetrate the chrome plating or create low spots by too much localized buffing or polishing.
(1) Scratches or nicks that have not penetrated the chrome plating of the piston and axle assembly or the upper cylinder
assembly may be honed and polished to remove sharp edges that could damage the seals. A honing stone or crocus
cloth may be used for this purpose. In the areas not subject to seal travel, scratches, pits and scoring that do not
penetrate the chrome plating are relatively unimportant. The sharp edges of the nicks should be removed by honing
and polishing. The presence of defects in this area, if properly repaired, are considered acceptable.
D. Piston Assembly (96A) inner Diameter Finish Rework (Refer to Figure 1002).
NOTE: The inner barrel of the piston assembly is phosphate coated. This coating may be rough, causing
premature wear to the seals causing fluid to leak from the strut assembly. The following procedure
provides a method for smoothing this coating.
NOTE: This procedure is not intended to be performed after each overhaul. Perform this procedure only
once.
(1) Using a micrometer, check inside diameter of piston assembly to ensure it is within tolerance.
(2) Check inside of piston assembly for pitting. If pitted, replace the piston assembly.
(3) Hone the inside diameter of the piston assembly to remove a minimal amount of phosphate coating and to achieve a
smooth finish.
(a) Remove air charge valve assembly (160) and packing (161). Refer to Figure 1001.
(b) Assemble hone, stones, flexible shaft with chuck and a variable speed drill.
NOTE: Install a piece of plastic, rubber hose or other suitable material over the chuck on flexible
shaft to prevent chuck from striking piston bore during honing.
(c) Adjust the hone and install into the end of piston assembly; expand hone assembly until stones are resting
against inner diameter of piston assembly. Apply honing oil as required.
CAUTION: Do not allow stones to get dry during honing; use honing oil freely while operating hone.
Allowing stones to get dry will result in scratching the inner diameter finish of the piston
assembly.
(d) Hone the piston assembly at a maximum speed of 600 RPM, one continuous stroke the length of bore and out,
keeping the hone moving through piston at all times until phosphate is removed.
(e) Thoroughly clean piston assembly after honing. Refer to Main Gear Assembly - Cleaning, for material.

Copyright © Textron Aviation Inc. Page 2 of 13

(f)Using a micrometer, check inside diameter of piston assembly to ensure honing did not exceed the 2.253
inches (57.226 mm) diameter.
(g) Install air charge valve assembly (160) and new packing (161). Refer to Figure 1001.
(4) If piston assembly is not being reassembled, coat inside diameter with hydraulic assembly lubricant MCS 352.
E. Painting.
(1) Preliminary.
(a) Verify areas to be painted are free of dirt, oil, grease and/or corrosion.
(b) Do not paint tires, strut air valves, data plates, bearings, polished pistons, switches, wire bundles, clamps,
hydraulic hoses, wheels, axle spindle area within the wheels or contacting areas of the lower to upper torque
links.
(c) Retreat and paint removed wheels in accordance with Goodyear Wheel and Brake Components Maintenance
Manual.
(2) Pretreatment.
(a) Apply DOD-P-15328 pretreatment primer in accordance with manufacturer's instructions.
(3) Corrosion Resistant Primer.
(a) Mix and apply MIL-PRF-23377 corrosion resistant primer in accordance with manufacturer's instructions.
(4) Top Coat.
(a) Mix and apply top coat in accordance with manufacturer’s instructions.
F. Install Service Placard.
(1) Bond Filling Instruction Placard to upper cylinder with RTV-154 adhesive. Prepare and apply adhesive in accordance
with manufacturers instructions.
(2) Apply two coats of clear polyurethane over the placard after installation. Prepare and apply polyurethane top coat in
accordance with manufacturers instructions.
G. Piston Axle Adaptor and Axle External Corrosion Inspection, Removal and Prevention.
NOTE: This procedure applies to the external areas of the piston axle adaptor and axle in the areas where
the brake assembly makes contact.
(1) Inspection of Piston Axle Adaptor and Axle.
(a) Inspect the piston axle adaptor and axle in the areas shown for damage to the finish and corrosion. Refer to
Figure 601. If the finish is not damaged and no corrosion exists, no further action is required. If corrosion is
present on the piston axle adaptor and/or axle, proceed to paragraph G, step (2), Rework of Piston Axle
Adaptor and Axle. If the finish is damaged, but no corrosion exists, proceed to paragraph G, step (5), Finish
Application.
(2) Rework of Piston Axle Adaptor and Axle.
(a) Determine if the axle can be reworked as described. Refer to Figure 601.
1 Using a steel wire brush, remove the loose corrosion from the axle in the area between the piston axle
adaptor and the area where the inboard wheel bearing and seal were located. Clean the axle with
approved solvent to remove all grease and dirt. Using a vernier micrometer, measure the diameter of the
axle and determine the average axle diameter.
NOTE: Average axle diameter is determined by measuring the axle at four different locations,
oriented 45 degrees apart, and averaging the four measurements.
a If the average axle diameter is less than 1.8000 inches (45.72 mm), the axle must be replaced. Refer
to Main Gear Assembly - Assembly, Axle Installation.
b If the average axle diameter is 1.8000 inches (45.72 mm) or greater, proceed with reworking
instructions.
NOTE: If the axle surface contains pits which remain after corrosion removal and it is
estimated that upon removal of these pits, the axle may not meet the absolute
minimum average diameter of 1.8000 inches (45.72 mm), it may not be feasible to
attempt to rework the axle since it is possible that the axle may require

Copyright © Textron Aviation Inc. Page 3 of 13

replacement.
(b) Determine if the piston axle adaptor can be reworked as described. Refer to Figure 601.
(3) Using a steel wire brush, remove the loose corrosion from the piston axle adaptor in the area shown. Clean the piston
axle adaptor with approved solvent to remove all grease and dirt. Using a vernier micrometer, measure the diameter
of the piston axle adaptor and determine the piston axle adaptor average diameter.
NOTE: Piston axle adaptor average diameter is determined by measuring the piston axle diameter at
four different locations, oriented 45 degrees apart (as shown in Figure 601, View B-B), and
averaging the four measurements.
(a) If the axle adaptor average diameter is less than 2.490 inches (63.246 mm), there is an optional repair available
that uses a Cessna controlled process. This process can remove the corrosion and build up the axle adaptor
with hard chrome plating. For more details, contact Cessna Customer Services - Structures.
NOTE: Small local areas of the piston axle adaptor may indicate as small as 2.4850 inches (63.119
mm) diameter at any one location, but the piston axle adaptor average diameter must still
be a minimum of 2.4900 inches (63.246 mm).
(b) If the piston axle adaptor average diameter is 2.4900 inches (63.246 mm) or greater, the piston axle adaptor
does not require replacement and must have a finish applied. Refer to Step G. (5), Finish Application.
NOTE: If it is determined that either the axle or piston axle adaptor require replacement, it may be
desirable to replace the piston and axle assembly (which includes both the piston and
axle).
(4) Rework of Piston Axle Adaptor and Axle.
(a) Wrap a piece of thin (0.012 or 0.016) aluminum sheet, 5.70 X 1.0 inch (144.78 X 25.4 mm), around the axle and
secure in place with a worm-type hose clamp to protect the portion of the axle where the inboard bearing and
seal were located.
CAUTION: It is very important to preserve the axle radius at the inboard edge of the rework area. When
using the emery cloth, do not allow the edge of the emery cloth to form a groove in the radius;
instead, allow the emery cloth to ride up into the radius.
(b) Using a 0.75 inch (19.05 mm) wide strip of 320 grit (aluminum oxide) emery cloth, remove all corrosion on the
axle (between the piston axle adaptor and protected area). All corrosion, including any pitting of the metal, must
be removed. After all pits are removed, apply a final finish to the axle with 400 grit emery cloth (aluminum oxide).
(c) Remove the aluminum sheet protecting the axle and ensure all corrosion is removed up to the area where the
bearing seal was making contact with the axle. Remove any remaining corrosion with 400 grit emery cloth but
use minimum pressure when sanding over the seal area.
(d) Clean the area with approved solvent and measure the diameter of the axle in the reworked area at four
locations oriented 45 degrees apart and determine the average axle diameter. If the average axle diameter is
less than 1.8000 inches (45.72 mm), the axle must be replaced. Refer to Main Gear Assembly - Disassembly
and Main Gear Assembly - Assembly, for axle replacement instructions. If the average axle diameter is 1.8000
(45.72 mm) or greater, proceed with application of finish. Refer to paragraph G. step (5), Finish Application.
NOTE: Small local areas of the axle may indicate as small as 1.7950 inch (45.593 mm) diameter at
any one location, but the average axle diameter must still be a minimum of 1.8000 inch
(45.72 mm) diameter.
(e) Remove all corrosion from the piston axle adaptor in the same manner as utilized for the axle. Upon removal of
all pits, measure the piston axle adaptor diameter at four locations oriented 45 degrees apart and average
together to determine the piston axle adaptor average diameter.
NOTE: Small local areas of the piston axle adaptor may indicate as small as 2.4850 inches (63.119
mm) diameter at any one location, but the piston axle adaptor average diameter must still
be a minimum of 2.4900 inches (63.246 mm).
1
If the piston axle adaptor average diameter is 2.4900 inches (63.246 mm) or greater, the piston axle
adaptor does not require replacement and must have a finish applied. Refer to paragraph G. step (5),
Finish Application.
(5) Finish Application.

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NOTE: MIL-PRF-23377 corrosion resistant primer must be applied to clean surfaces within 30 minutes
of completion of sanding procedure. An oxide film which provides minimal adhesion for
primer begins to form immediately after working. Poorly adhered corrosion resistant primer
will result in accelerated corrosion.
(a) Clean the piston axle adaptor and/or axle with approved solvent and wipe dry.
(b) Mask off areas of the piston not reworked.
(c) Mask off the outboard portion of the axle from the inboard wheel bearing seal. Ensure masking covers the
inboard wheel bearing seal contact point so that the seal does not ride on the MIL-PRF-23377 corrosion
resistant primer.
(d) Apply MIL-PRF-23377 corrosion resistant primer to the piston axle adaptor and/or the axle. For application and
mixing instructions for MIL-PRF-23377 corrosion resistant primer, refer to the manufacturer’s instructions.
(e) Apply a thin film of wheel bearing grease to the outer surface of axle as a corrosion preventative treatment.
H. Axle Internal Corrosion Inspection, Removal, Modification and Prevention
(1) Inspection of Axle
NOTE: This procedure applies to the internal areas of the axle from the outboard end to a point 1.63
inches (41.402 mm) inboard.
(a) If corrosion exists in the outboard (1.63 inches (41.402 mm)) end of the axle internal bore the corrosion must be
removed by mechanical means. If corrosion is light and is removed by the use of 320 grit emery cloth (aluminum
oxide) with no remaining pits, measure the bore diameter. If the bore diameter is larger than 1.378, or pits
remain after the use of emery cloth, the bore will require machining to enlarge the bore to 1.4105 inches, +0.003
or -0.003 inches (35.826 mm, +0.076 or -0.076 mm). If corrosion was removed by the use of emery cloth and the
bore diameter was 1.378 inches (35.001 mm) or less, then no machining is required. Proceed to paragraph H.
step (2) (c) for finish application to prevent corrosion. If machining is required to enlarge the bore, proceed to
paragraph H. step (2), Axle Rework, for machining requirements.
(2) Axle Rework.
NOTE: This procedure must be performed by a machinist using standard practices and techniques
for machining a precision bore in the axle (material 4340 steel).
(a) Refer to Main Gear Assembly - Disassembly and Main Gear Assembly - Assembly, for axle removal
procedures.
(b) Enlarge the bore diameter to 1.4105 inches, +0.003 or -0.003 inches (35.826 mm, +0.076 or -0.076 mm).
Maintain a surface finish of 125 microinches. Maintain a 0.005 inch (0.127 mm) radius and a 0.062 inch (1.574
mm) chamfer at the transition point from the larger diameter bore to the smaller diameter bore 1.63 inches
(41.402 mm) inboard from the outboard end of the axle. Establish a 1.510 inches (38.354 mm) diameter 30
degrees chamfer at the outboard end of the bore.
NOTE: MIL-PRF-23377 corrosion primer must be applied to clean surfaces within 30 minutes of
completion of sanding procedure. An oxide film which provides minimal adhesion for MIL-
PRF-23377 corrosion primer begins to form immediately after working. Poorly adhered
MIL-PRF-23377 corrosion primer will result in accelerated corrosion.
(c) Clean the bore diameter and apply primer. For mixing and application of MIL-PRF-23377 corrosion primer,
refer to the manufacturer’s instructions.
1 Fabricate a stainless steel shim from sheet stock as shown (Refer to Figure 602). Deburr all edges.
Abrade one surface of the shim using 320 grit emery cloth (aluminum oxide).
2 Roll shim to 1.41 inch (35.814 mm) diameter with abraded surface to the outside. Clean outer surface of
shim with approved solvent.
3 Bond shim in the axle with the joint at the top using EA9309.3NA adhesive. Insert antiskid transducer
(coated with wax and then wrapped with one layer of thin plastic, such as Saran Wrap, to act as a parting
agent) to hold the shim in position.
4 Allow adhesive to cure, then remove the antiskid transducer.
5 Reinstall axle. Refer to Main Gear Assembly - Assembly, for axle installation procedures.
I. Outer Cylinder Lower Bearing Area Corrosion Inspection, Removal, Modification and Prevention.

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(1) Inspection of the outer cylinder lower bearing area.

(a) Inspect the outer cylinder lower bearing area as shown for damage to the finished surface due to corrosion.
Refer to Figure 603. If the finished surface is not damaged and no corrosion exists, proceed to step (3). If
corrosion is present on the outer cylinder lower bearing surface area, proceed to step (2).
(2) Preliminary rework of outer cylinder lower bearing surface area.
(a) Determine if the outer cylinder lower bearing surface area can be reworked (Refer to Figure 603):
1 Verify that no corrosion exists on the uppermost 0.5 inch (12.7 mm) of the bearing surface. If corrosion is
found in this area, contact Citation Customer Service Department for disposition.
2 Using a stainless steel wire brush or glass bead peening, remove the corrosion from the outer cylinder
lower bearing area. Glass bead peening may be used to remove corrosion from the pits which were not
removed with the stainless steel wire brush.
3 Clean the outer cylinder bearing area with approved solvent to remove all grease and dirt.
4 Using a dial micrometer with a pointed tip, measure the inner diameter of the outer cylinder lower bearing
area and determine the average bearing surface diameter to include the depth of pit.
NOTE: Average bearing surface diameter is determined by measuring the inner diameter at a
minimum of four different locations, starting at the most damaged location and
rotating 45 degrees either side, plus one additional location and averaging the four
measurements.
(b) If the average bearing surface diameter is greater than 3.405 inches (86.487 mm), or the maximum pit depth is
greater than 0.015 inch (0.381 mm), contact Citation Customer Service Department.
(c) If the average bearing surface diameter is less than 3.405 inches (86.487 mm), proceed to step 3.
NOTE: If the outer cylinder lower bearing surface contains pits which remain after corrosion
removal, and it is estimated that upon removal of these pits the outer cylinder lower
bearing surface may not meet the absolute maximum average diameter of 3.405 inches
(86.487 mm) or the maximum pit depth is greater than 0.015 inches (0.381 mm), it may not
be feasible to rework the outer cylinder. The outer cylinder may require replacement.
(3) Rework of outer cylinder lower bearing surface area.
(a) Place a 3.00 inches (76.2 mm) diameter plug at the lower end (just past the bearing surface) of the outer
cylinder bore.
(b) Use a rotary stainless steel wire brush or glass bead peening to remove all corrosion from the bearing and
retainer ring areas. Glass bead penning may be used to remove corrosion from the pits which were not removed
with the stainless steel wire brush. Insure that all corrosion is removed prior to proceeding.
(c) Clean the lower bearing surface and the retainer ring areas with approved solvent, to remove all grease and dirt.
Wipe off solvent with a clean absorbent rag. Do not allow solvent to dry on the surface, remove all solvent
residue.
(d) Mask the machined step at the top edge of the lower bearing surface and a 0.50 inch (12.7 mm) band of the
upper portion of the lower bearing surface area, to prevent MIL-PRF-23377 corrosion resistant primer from
being applied to these surfaces.
(e) Reclean the unmasked portion of the lower bearing surface with approved solvent. Wipe off solvent with a clean
absorbent rag. Do not allow solvent to dry on the surface, remove all solvent residue.
(f) Immediately prime the abraded area with MIL-PRF-23377 corrosion resistant primer, refer to the manufacturer’s
instructions for mixing, application and cure times.
J. Outer Cylinder and Piston Weld Assembly Torque Link Lug Inner Diameter Corrosion Inspection, Removal, Modification
and Prevention.
(1) Inspection
(a) Inspect the 0.751 inch (19.075 mm) diameter hole in the respective torque link lug for corrosion damage. Refer
to Figure 603 and Figure 604. If the inner bore finish is not damaged, proceed to step (2)(c). If corrosion
damage is present, proceed to step (2).
(2) Preliminary rework of the torque link lug pin hole.

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(a) Determine if the overall diameter of the torque link lug hole except in the locally corroded area is within tolerance
of (0.751 inch +0.001 or -0.001 inch (19.075 mm, +0.025 or -0.025 mm)) after the removal of all corrosion.
1 Using a stainless steel wire brush, remove corrosion from the torque link lug pin hole. Glass bead penning
may be used to remove corrosion from the pits which were not removed with the stainless steel wire brush.
Insure that all corrosion is removed prior to finishing.
2 Clean the torque link lug hole with approved solvent to remove all grease and dirt. Wipe off solvent with a
clean absorbent rag. Do not allow solvent to dry on the surface, remove all solvent residue.
(b) Using a dial micrometer, measure the lug hole and determine the average hole diameter:
NOTE: Measure the diameter of the hole at a minimum of four different locations in the same
vertical plane. Start at the most damaged location and measure 15 degrees on either side
of this location, plus one additional location and average the four measurements.
1 If the average lug hole diameter at the corroded point is greater than 0.780 inch (19.812 mm) or the
maximum pit depth is greater than 0.015 inch, proceed to Rework Torque Link Lug Hole Bushing Required.
2 If the average lug hole diameter is less than 0.780 inch (19.812 mm) at the corroded point, proceed to the
next step.
(c) Reclean the torque link lug hole with approved solvent to remove all grease and dirt. Wipe off solvent with a
clean absorbent rag. Do not allow solvent to dry on the surface, remove all solvent residue.
(d) Option 1: Immediately apply MIL-PRF-23377 corrosion resistant primer to inside of the hole area with a
thickness of 0.6 to 0.9 mil. For mixing and application of MIL-PRF-23377 corrosion resistant primer, refer to the
manufacturer’s instructions.
NOTE: MIL-PRF-23377 corrosion resistant primer must be applied to clean surfaces within 30
minutes of completion of brushing procedure. An oxide film which provides minimal
adhesion for MIL-PRF-23377 corrosion primer begins to form immediately after working.
Poorly adhered MIL-PRF-23377 corrosion resistant primer will result in accelerated
corrosion.
(e) Cure MIL-PRF-23377 corrosion resistant primer in accordance with the manufacturer’s instructions.
NOTE: MIL-PRF-23377 corrosion resistant primer must be completely cured to have phosphate
ester hydraulic fluid resistance.
(f)
Option 2: Immediately coat inside of the hole area with Type 1 Class B2 sealer. Install the torque link pin and
wipe off all excess sealer.
(3) Rework Torque Link Lug Hole Bushing Required.
(a) Ream the hole to 0.850 inch (21.59 mm) diameter.
(b) Fabricate from 4340 steel, heat treated to 180-200 KSI, a 2.498 inches (63.449 mm) long bushing to press fit
into the 0.850 inch (21.59 mm) hole. The interference fit of the outer diameter of the bushing shall be 0.001 to
0.002 inch (0.025 to 0.050 mm).
(c) Coat the inside surface of the 0.850 inch (21.59 mm) diameter oversized hole with Type 1 Class B2 sealer prior
to installation of the bushing.
(d) Use liquid nitrogen to cool the bushing prior to pressing into the torque link lug.
(e) After pressing the bushing into the 0.850 inch (21.59 mm) hole, ream the bore of the bushing inner diameter to
0.751 inch, +0.001 or -0.001 inch (19.075 mm, +0.025 or -0.025 mm) diameter. Finish the 0.751 inch (19.075
mm) inner diameter of the bushing as described in preliminary rework of the torque link pin hole, utilizing either
Option 1 or Option 2.
K. Piston Weld Assembly Lightening Hole Corrosion Inspection, Removal, Modification and Prevention.
(1) With the axle removed from the piston weld assembly, inspect the lower lightening hole for corrosion. Refer to Figure
604.
(a) Inspect the axle adaptor lightening hole for damage due to corrosion. If the finished surface is not damaged,
proceed to step (3). If corrosion damage is present proceed to Step (2).
(2) Rework axle adaptor lightening hole area.
(a) Determine if the piston weld assembly can be reworked as follows:

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1 Using a stainless steel wire brush or glass bead peening, remove the corrosion from the lightening hole
area. Glass bead peening may be used to remove corrosion from the pits which were not removed with the
stainless wire brush. Insure that all corrosion is removed.
2 Clean the lightening hole area with approved solvent to remove all grease and dirt.
3 Using a dial micrometer, measure the inner diameter of the lightening hole and determine the average hole
diameter.
NOTE: The average hole diameter is determined by measuring the inner diameter at a
minimum of four different locations, starting at the most damaged location and
rotating 45 degrees either side all on the same horizontal plane, plus one additional
location and averaging the four measurements.
a If the average hole diameter on the 5541101 or 5541108 piston assembly is greater than 1.53 inches
(38.862 mm), or the maximum pit depth is greater than 0.015 inch (0.381 mm), the piston weld
assembly must be replaced with a new like part.
b If the hole diameter is less than 1.53 inches (38.862 mm) and the maximum pit depth is less than
0.015 inch (0.381 mm), proceed with the rework instructions.
NOTE: If the 1.50 inch (38.1 mm) diameter hole inner surface contains pits which remain
after corrosion removal and it is estimated that upon removal of these pits the
hole diameter will not meet the absolute maximum average diameter of 1.530 mm
(38.862 mm) or if the maximum pit depth is greater than 0.015 inch (0.381 mm), it
may not be feasible to rework the axle adaptor. The piston weld assembly may
require replacement.
c If the average hole diameter on the 5541330 or 6541100 piston assembly is greater than 1.37 inches
(34.798 mm), or the maximum pit depth is greater than 0.015 inch, the piston weld assembly must be
replaced with a new like part.
d If the hole diameter is less than 1.37 inches and the maximum pit depth is less than 0.015 inch,
proceed with the rework instructions.
NOTE: If the 1.37 inch (34.798 mm) diameter hole inner surface contains pits which
remain after corrosion removal and it is estimated that upon removal of these
pits the hole diameter will not meet the absolute maximum average diameter of
1.370 inch (34.798 mm) or if the maximum pit depth is greater than 0.015 inch, it
may not be feasible to rework the axle adaptor. The piston weld assembly may
require replacement.
(3) Rework the axle adaptor lightening hole.
(a) Using a rotary stainless steel wire brush or glass bead peening, remove surface corrosion from the inner surface
of the lightening hole.
(b) Clean the hole inner surface with approved solvent to remove all grease and dirt just prior to reinstallation of the
axle. Wipe off solvent with a clean absorbent rag. Do not allow solvent to dry on the surface. Remove all solvent
residue.
(c) Immediately coat the axle adaptor lightening hole with Grade 1 Material MIL-C-16173 Royco 103 just prior to
pressing the axle into the axle adaptor. Do not coat the axle adaptor where the axle presses into the axle
adaptor with the Royco 103 material.

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Figure 601 : Sheet 1 : Main Landing Gear Piston Axle Adaptor and Axle Inspection

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Figure 601 : Sheet 2 : Main Landing Gear Piston Axle Adaptor and Axle Inspection

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Figure 602 : Sheet 1 : Axle Inside Diameter Corrosion Removal

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Figure 603 : Sheet 1 : Cylinder Repairs

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Figure 604 : Sheet 1 : Piston Assembly Corrosion Repairs

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MAIN GEAR ASSEMBLY - ASSEMBLY

1. Assembly
A. Tools and Equipment (Refer to Illustrated Parts List, Figure 1001 and Figure 1002).
NOTE: Equivalent substitutes may be used for the following items.
NAME NUMBER MANUFACTURER USE
Safety Wire Monel 0.020 inch Commercially Available Safety air valve and cylinder
(0.508 mm) plug.
diameter
Hydraulic Assembly MCS 352 Aviation Fluids Service Company Lubricate and protect surfaces
Lubricant St. Louis, MO 63166 in contact with hydraulic fluid or
prevent entry of water.
Loctite 609 Loctite Corporation Fill and seal trunnion to cylinder
705 N. Mountain Road and install bushings in torque
Newington, CT 06111 links.
Teflon O-Ring CJMD132-003 Cessna Aircraft Co. To install Teflon seals on
Installation Tool Citation Marketing Div. isolation piston.
Department 579
P.O. Box 7706
Wichita, KS 67277
Drill Bit Letter D Commercially Available
Reamer 0.250 inch (6.350 Commercially Available
mm) diameter with
a pilot 0.128 inch
(3.251 mm)
diameter and 0.375
inch (9.525 mm)
length
NOTE: Drill bit must have a 0.128 inch (3.251 mm) diameter pilot that is 0.375 inch (9.525 mm) in length.
NOTE: A reamer such as a Cleveland 4001 reamer, Number 25513 would be satisfactory. The pilot must be
machined onto the Cleveland reamer.
B. Axle Installation (Refer to Figure 1002).
(1) Install the expansion plug (105) into the inboard end of the new axle using MIL-PRF-23377 corrosion resistant primer
and 1000 pounds, +500 or -000 pounds (4448.22 N, +2224.11 or -2224.11 N) of force.
(2) Wipe out the hole in the piston with approved solvent, refer to Main Gear Assembly - Cleaning.
(3) Prepare the arbor press to install the axle (103) in the piston using the wooden block used when pressing the axle out
of the piston.
(4) Coat the hole in the piston and the portion of the axle that makes contact with the piston with MIL-PRF-23377
corrosion resistant primer and press the axle in position while primer is wet. Make sure that the keyway in a new axle
(the threaded area of the axle) is oriented up, or on a reinstalled axle, the keyhole must be oriented 60 degrees from
the original keyway up position on the axle.
NOTE: 60 degrees deviation from original up position is required on installed axle.
(5) Using a 0.250 OD. × 0.128 I.D. drill bushing in the hole in the side of the piston and a number 30 (0.128 inch (3.251
mm) diameter) drill bit, drill a hole through (one side only) of the axle to match the existing hole in the piston. Remove
the drill bushing and enlarge the hole using a letter D (0.246 inch diameter) drill bit with a 0.128 inch (3.251 mm)
diameter pilot. Ream the hole using a 0.250 inch (6.35 mm) diameter pilot. Ream the hole using a 0.250 inch (6.35
mm) diameter reamer with a 0.246 (6.248 mm) inch diameter pilot.
(6) Deburr the hole and install new pin (106) flush with the outside surface of the piston and secure with safety wire.
C. Torque Link Bushing Installation.

Copyright © Textron Aviation Inc. Page 1 of 6

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 13:08:29 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
32-10-00-7 (Rev 14)

(1) Remove paint, grease, dust or other contaminating substances from bushings and torque links.
WARNING: Use solvent in well ventilated area, avoid breathing fumes.
(2) Use a clean rag saturated with approved solvent and clean bushings and torque links.
(3) Apply Loctite 609, to bushings (30 and 31) and torque links.
(4) Prior to installation, align lubrication holes in bushing (31) with lubrication fitting on torque link and press bushings (30
and 31) in place.
NOTE: Bushings (30) do not require alignment with lubrication fitting prior to installation.
WARNING: Use solvent in a well ventilated area. Avoid breathing fumes.
(5) Excess Loctite may be removed with a rag moistened with approved solvent.
(6) Clean Loctite from lubrication holes.
(7) Cure time for Loctite on the bushings is 24 hours.
NOTE: When new torque link bushings are installed, it may be necessary to mill and ream bushings
(30) to dimensions shown in Main Gear Assembly - Fits and Clearances.
D. Piston Assembly (Refer to Figure 1002).
WARNING: Long exposure to phosphate ester base fluids can cause skin dehydration and chapping.
(1) Immerse packings and seals in phosphate ester base hydraulic fluid.
(2) Install packing (108) and two Teflon packings (111) on isolation piston (110) as follows (refer to Figure 701,
(a) Place the -8 holding fixture with the narrow end down in the center of an arbor press base plate. Place the upper
Teflon packing in the center of the holding fixture upper surface.
(b) Position the -7 expansion cone with point down through the center of the packing and into the holding fixture.
(c) Invert the isolation piston and center over the upper portion of the expansion cone.
(d) Place the -10 holding fixture over the isolation piston shaft.
CAUTION: Ensure Teflon packing is centered on the holding fixture and expands uniformly as pressure
is applied to expansion cone.
(e) Smoothly compress the stack with the arbor press until the Teflon packing slips into the first annular groove of
the inverted isolation piston.
(f) Disassemble the tools from the isolation piston.
(g) Place the -10 holding fixture on the arbor press base plate with the small end down. Center the lower Teflon
packing on the upper surface of the holding fixture and place the -9 expansion cone through the center of the
Teflon packing.
CAUTION: Ensure Teflon packing is centered on the holding fixture and expands uniformly as pressure
is applied to expansion cone.
(h) Insert the isolation piston through the expansion cone and into the holding fixture. Place the -12 ram over the
isolation piston and compress until Teflon packing slips into annular groove.
(i) Disassemble the tools from the isolation piston.
(j) Place the -11 contraction cylinder on the arbor press base plate with the smallest inside diameter end down.
(k) Center isolation piston on contraction cylinder with piston shaft pointing down.
CAUTION: Spacer height or hole diameter on the arbor press base plate must be sufficient to allow the
piston to be pressed completely through the contraction cylinder without obstruction.
(l) Center -12 ram on the isolation piston and press through contraction cylinder.
(m) Install the O-ring packing in the middle groove in the normal manner.
(3) Install spring (113) and stop (114) on end of isolation piston (110). Secure with retainer (115).
(4) Coat the inner barrel of piston (96A) with a thin layer of hydraulic fluid or hydraulic assembly lubricant.
(5) Use threaded rod or long bolt screwed into face of isolation piston (110) and insert isolation piston (110), spring
(113) and stop (114) into barrel of piston assembly (96A). Push piston into barrel until stop seats against bottom.
(6) Install orifice (41) into top of bearing (45) and attach with retainer (43).

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(7) Install polypak seal (80) into inner channel in phenolic bearing (79).
NOTE: Install polypak seal with expander ring edge upwards towards fluid.
(8) Install backup retainer (77) and packing (76) on phenolic bearing (79).
CAUTION: Do not allow retainers to scratch the chrome surface of the piston assembly.
(9) Slide lock ring (85), scraper retainer (83), scraper (81), phenolic bearing (79) and spacer (75) over barrel of piston
assembly (96A).
CAUTION: Set screws must be recessed below bearing surface. Make sure resistance is felt when installing
setscrews to ensure self-locking capability. Replace setscrews not indicating locking capabilities.
(10) Install bearing (45) on top of piston assembly and secure with four self-locking setscrews (46). Torque setscrews 60
to 70 inch-pounds.
E. Piston Installation. (Refer to Figure 1001 and Figure 1002)
(1) Pack area all around bearing (79) with hydraulic assembly lubricant (MCS-352) to resist entry of water about bearing
interface with strut cylinder collar. Refer to Figure 1002.
(2) Carefully slide piston assembly into cylinder assembly. Seat phenolic bearing (79) into cylinder and install scraper
(81), scraper retainer (83) and lock ring (85). Refer to Figure 1002.
NOTE: Make sure lock ring is seated in the lock ring groove, then extend strut piston assembly until
scraper retainer locks the lock ring in place.
F. Assemble Trunnion to Cylinder.
WARNING: Solvent is toxic and flammable; use in well ventilated area. Avoid breathing fumes and keep away
from flames.
(1) Clean inside diameter of trunnion and outside diameter of cylinder with solvent.
(2) Apply Loctite 609 to inside diameter of trunnion and outside diameter of cylinder using a clean brush.
NOTE: Apply sufficient amount of Loctite 609 to assure complete fill and seal.
(3) Press-fit cylinder into trunnion.
NOTE: Remove excess Loctite immediately and before subsequent exterior finishing.
(4) Install two forward bolts (81), washers (82 and 83) and nut (84). Refer to Figure 1001.
(5) Install two aft bolts (85), washers (82), bushings (88), washers (86) and nuts (87). Refer to Figure 1001.
G. Torque Link Installation. Refer to Figure 1002.
(1) Install upper and lower torque links (24 and 25), shafts (19) and shaft retainer pins (20 and 21).
(2) Install torque link interconnect bolt (33), toe-in adjustment washers (34, 35 and 36), flat washer (37), nut (38) and
cotter pin (39). Add or remove washers until a gap of 0.004 inch to 0.019 inch (0.102 to 0.4826 mm) is obtained.
NOTE: Torque link interconnect parts should be assembled exactly as disassembled to maintain toe-
in adjustment.
H. Service Fittings Installation. Refer to Figure 1001.
(1) Install packing (155) and air valve assembly (154). Torque valve assembly from 100 to 110 inch-pounds (11.30 to
12.43 N-m). Safety wire large nut (0.75 inch (19.05 mm)) to forging. Use double twist method of installing safety wire.
NOTE: If new air valve assembly is being installed, discard packing and replace with a phosphate
ester base fluid resistant packing, Part Number NAS1611-015.
(2) Install plug (159) and seal (160) in top of cylinder assembly. Safety wire plug to trunnion bolt using double twist
method.
2. Storage
A. Recommended Storage Procedure.
(1) Release air from air valve. Refer to Main Gear Assembly - Disassembly.
(2) Remove plug from top of cylinder assembly and drain hydraulic oil from cylinder. Replace plug.
(3) Collapse strut assembly. Coat exposed chromed surface of piston assembly with protective oil.
(4) Wrap collapsed strut in grease-proof paper, then kraft paper and pack in rigid container.
(5) Container shall be stored in a cool, dry, well ventilated area on a noncorrosive base.

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Figure 701 : Sheet 1 : Isolation Piston Teflon Packing Installation

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Figure 701 : Sheet 2 : Isolation Piston Teflon Packing Installation

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Figure 701 : Sheet 3 : Isolation Piston Teflon Packing Installation

Copyright © Textron Aviation Inc. Page 6 of 6

MAIN GEAR ASSEMBLY - FITS AND CLEARANCES

1. Fits and Clearances
A. Cylinder 5541100-1, -2, -3, -4, -5, -6, 5541107-1, -2, -4

(1) 3.000 inch, +0.002 or -0.000 inch (76.20 mm, +0.05 or -0.00 mm) diameter
(2) 3.0312 inch, +0.0012 or -0.0000 inch (76.992 mm, +0.030 or -0.000 mm) diameter
(3) 3.2068 inch, +0.0000 or -0.0014 inch (81.452 mm, +0.036 or -0.000 mm) diameter
(4) 0.751 inch, +0.001 or -0.000 inch (19.08 mm, +0.03 or -0.00 mm) diameter
(5) 0.751 inch, +0.001 or -0.000 inch (19.08 mm, +0.03 or -0.00 mm) diameter (lug hole)
(6) 2.498 inch, +0.000 or -0.002 inch (63.45 mm, +0.00 or -0.05 mm) diameter
B. Cylinder 5541109-1, -2, -5, -6,

(1) 3.000 inch, +0.002 or -0.000 inch (76.20 mm, +0.05 or -0.00 mm) diameter
(2) 2.90 inch, +0.03 or -0.03 inch (73.7 mm, +0.8 or -0.8 mm) diameter
(3) 3.2068 inch, +0.0000 or -0.0014 inch (81.452 mm, +0.036 or -0.000 mm) diameter
(4) 3.012 inch, +0.005 or -0.001 inch (76.50 mm, +0.13 or -0.03 mm) diameter
(5) 0.751 inch, +0.001 or -0.000 inch (19.08 mm, +0.03 or -0.00 mm) diameter
C. Cylinder 5541320-1, -2, -3, -4, -5, -6

Copyright © Textron Aviation Inc. Page 1 of 6

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 13:08:39 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
32-10-00-8 (Rev 17)

(1) 3.000 inch, +0.002 or -0.000 inch (76.20 mm, +0.05 or -0.00 mm) diameter
(2) 2.1598 inch, +0.0100 or -0.0000 inch (54.860 mm, +0.254 or -0.000 mm) diameter
(3) 3.2068 inch, +0.0000 or -0.0014 inch (81.452 mm, +0.036 or -0.000 mm) diameter
(4) 3.012 inch, +0.005 or -0.001 inch (76.50 mm, +0.13 or -0.03 mm) diameter
(5) 0.751 inch, +0.001 or -0.000 inch (19.08 mm, +0.03 or -0.00 mm) diameter
D. Piston 5541101-1, -2

(1) 2.250 inch, +0.003 or -0.000 inch (57.15 mm, +0.80 or -0.00 mm) diameter
(2) 2.4365 inch, +0.0000 or -0.0020 inch (61.89 mm, +0.000 or -0.000 mm) diameter
(3) 2.750 inch, +0.000 or -0.002 inch (69.85 mm, +0.00 or -0.05 mm) diameter
(4) 0.005 inch, (0.03 mm) maximum TIR (Total Indicator Reading)
(5) 0.751 inch, +0.001 or -0.000 inch (19.08 mm, +0.03 or -0.00 mm) diameter (lug hole)
(6) 2.498 inch, +0.000 or -0.002 inch (63.45 mm, +0.00 or -0.05 mm) diameter
E. Piston 5541108-1, -2, -3, -4, -5, -6

Copyright © Textron Aviation Inc. Page 2 of 6

(1) 2.250 inch, +0.003 or -0.000 inch (57.15 mm, +0.80 or -0.00 mm) diameter
(2) 2.4365 inch, +0.0000 or -0.0020 inch (61.89 mm, +0.000 or -0.000 mm) diameter
(3) 2.750 inch, +0.000 or -0.002 inch (69.85 mm, +0.00 or -0.05 mm) diameter
(4) 0.005 inch, (0.03 mm) maximum TIR (Total Indicator Reading)
(5) 0.751 inch, +0.001 or -0.000 inch (19.08 mm, +0.03 or -0.00 mm) diameter (lug hole)
(6) 4.380 inch, +0.010 or -0.010 inch (111.25 mm, +0.03 or -0.00 mm) diameter
(7) 0.125 inch, (3.18 mm) radius
(8) 2.498 inch, +0.000 or -0.002 inch (63.45 mm, +0.00 or -0.05 mm) diameter
NOTE: Items (6) and (7) are dimensions after rework to prevent brake interference.
F. Piston 6541100-1, -2

Copyright © Textron Aviation Inc. Page 3 of 6

(7) 0.250 inch, ( mm) radius

NOTE: Items (6) and (7) are dimensions after rework to prevent brake interference.
(8) 2.498 inch, +0.000 or -0.002 inch (63.45 mm, +0.00 or -0.05 mm) diameter
G. Piston 5541330-1, -2, -3, -4

Copyright © Textron Aviation Inc. Page 4 of 6

(1) 0.9375 inch, +0.0008 or -0.0000 inch (23.85 mm, +0.020 or -0.000 mm) diameter
(2) 0.7500 inch, +0.0007 or -0.0000 inch (19.05 mm, +0.018 or -0.000 mm) diameter
(3) 0.6250 inch, +0.0015 or -0.0000 inch (15.88 mm, +0.038 or -0.000 mm) diameter
(4) 0.839 inch, +0.000 or -0.000 inch (21.31 mm, +0.00 or -0.00 mm) diameter
(5) 2.500 inch, +0.000 or -0.003 inch (63.50 mm, +0.00 or -0.08 mm) diameter
NOTE: Dimension (5) is measured between faces of bushings. Machine bushings after installation.
I. Shaft, Torque Link 6541212-2 (supercedes 5541212-1, -3

(1) 0.750 inch, +0.000 or -0.001 inch (19.05 mm, +0.00 or -0.03 mm) diameter
(2) 0.250 inch, +0.006 or -0.000 inch (6.35 mm, +0.15 or -0.00 mm) diameter
J. Torque Link End Bushing 5541202-3

Copyright © Textron Aviation Inc. Page 5 of 6

(1) 0.090 inch, (2.29 mm) radius

(2) 0.125 inch, +0.004 or -0.001 inch (3.18 mm, +0.10 or -0.00 mm) diameter
(3) 0.9393 inch, +0.0000 or -0.0010 inch (23.860 mm, +0.000 or -0.003 mm) diameter
(4) 0.7505 inch, +0.0010 or -0.0010 inch (19.06 mm, +0.003 or -0.000 mm) diameter after installation and line
reaming.

Copyright © Textron Aviation Inc. Page 6 of 6

MAIN LANDING GEAR ASSEMBLY

NOMENCLATURE EFFECTIVITY UNITS
PER
ITEM PART NUMBER 1 2 3 4 5 6 7 FROM TO ASSY
- MAIN LANDING GEAR ASSEMBLY
- 1 5541000-3 . LANDING GEAR ASSY-LH A 01
- 2 5541000-4 . LANDING GEAR ASSY-RH B 01
- 3 5541000-9 . LANDING GEAR ASSY-LH C 01
- 4 5541000-10 . LANDING GEAR ASSY-RH D 01
- . LANDING GEAR ASSY-LH
5 5541000-11 E NP
FSO 6541000-37

- . LANDING GEAR ASSY-RH

6 5541000-12 F NP
FSO 6541000-38

- . GEAR STRUT-LH REFER

7 5541000-17 G 01 R
TO NOTE 1
GEAR STRUT-RH REFER
- 8 5541000-18 . H 01 R
TO NOTE 1
- . LANDING GEAR ASSY-LH
9 6541000-3 J NP
FSO 6541000-37

- . LANDING GEAR ASSY-RH

10 6541000-4 K NP
FSO 6541000-38

- . LANDING GEAR ASSY-LH

11 6541000-11 L NP
FSO 6541000-37
LANDING GEAR ASSY-LH
- 11A 6541000-11 . M NP R
FSO 6541000-37

- . LANDING GEAR ASSY-RH

12 6541000-12 N NP R
FSO 6541000-38
LANDING GEAR ASSY-RH
- 12A 6541000-12 . P NP R
FSO 6541000-38

- . LANDING GEAR ASSY-LH

12B 6541000-27 Q NP R
FSO 6541000-37

- . LANDING GEAR ASSY-LH

12C 6541000-27 R NP R
FSO 6541000-37

- . LANDING GEAR ASSY-RH

12D 6541000-28 S NP R
FSO 6541000-38
LANDING GEAR ASSY-RH
- 12E 6541000-28 . T NP R
FSO 6541000-38
- 12F 6541000-33 . LANDING GEAR ASSY-LH U 01 R
- 12G 6541000-34 . LANDING GEAR ASSY-RH V 01 R
- 12H 6541000-37 . LANDING GEAR ASSY-LH W 01 R
- 12J 6541000-37 . LANDING GEAR ASSY-LH X 01 R
- 12K 6541000-38 . LANDING GEAR ASSY-RH Y 01 R
- 12L 6541000-38 . LANDING GEAR ASSY-RH Z 01 R

Copyright © Textron Aviation Inc. Page 1 of 9

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 13:08:51 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
32-10-00-1001 (Rev 14)

WHEEL AND TIRE

ASSY REFER TO
13 . . AIRPLANE PARTS RF
CATALOG FOR
DETAILS
PLACARD-TIRE
INFLATION
. . INSTRUCTION REFER
14 RF
TO AIRPLANE PARTS
CATALOG FOR
DETAILS
HUBCAP REFER TO
. . AIRPLANE PARTS
15 RF
CATALOG FOR
DETAILS
BRAKE ASSY-LH AND
RH REFER TO
16 . . AIRPLANE PARTS RF
CATALOG FOR
DETAILS
- 17 TA41A716WD8SR . . CLAMP-LH STRUT V84971 A,C & E 02
18 TA41A12C59WD8EP . . CLAMP-STRUT V84971 E,J THRU Z 02 R
19 TA732D55EP . . CLAMP-STRUT V84971 J THRU Z 02 R
ATTACHING
PARTS
20 MS27039-1-10 . . SCREW 01
---*---
21 5541217-1 . . BLOCK-LH 02
ATTACHING
PARTS
22 MS27039-1-08 . . SCREW 02
23 MS21045L3 . . NUT 02
---*---
24 P39920 . . ROD END V57606 01
25 MS16562-49 . . PIN 01
26 AN315-3R . . JAMNUT 01
PLATE-
- 27 5540001-5 . . IDENTIFICATION FSO A THRU F NP
5540001-13
PLATE-
28 5540001-13 . . G THRU Z 01 R
IDENTIFICATION
NOTE 1: AIRPLANES INCORPORATING SB32-1 R
NOMENCLATURE EFFECTIVITY UNITS
PER
ITEM PART NUMBER 1 2 3 4 5 6 7 FROM TO ASSY
- MAIN LANDING GEAR ASSEMBLY

Copyright © Textron Aviation Inc. Page 2 of 9

TRUNNION ASSY-LH
- 75 5541000-7 . . A&C NP
FSO 5541000-15
- . . TRUNNION ASSY-RH
76 5541000-8 B&D NP
FSO 5541000-16
- 77 5541000-15 . . TRUNNION ASSY-LH E&G 01
- 78 5541000-16 . . TRUNNION ASSY-RH F&H 01
- 79 6541000-7 . . TRUNNION ASSY-LH J 01
- 80 6541000-8 . . TRUNNION ASSY-RH K 01
- . . TRUNNION ASSY-LH
80A 6541000-15 L NP
FSO 6541000-29
TRUNNION ASSY-RH
- 80B 6541000-16 . . M NP
FSO 6541000-30
- 80C 6541000-29 . . TRUNNION ASSY-LH N&P 01 R
- 80D 6541000-30 . . TRUNNION ASSY-RH Q&R 01 R
- 80E 6541000-31 . . TRUNNION ASSY-LH S&T 01 R
- 80F 6541000-32 . . TRUNNION ASSY-RH U&V 01 R
- 80G 6541000-35 . . TRUNNION ASSY-LH W&X 01 R
- 80H 6541000-36 . . TRUNNION ASSY-RH Y& Z 01 R
81 NAS464P8A72 . . . BOLT-FORWARD 02
82 5541225-1 . . . WASHER-LOWER 04
83 NAS1149F0832P . . . WASHER-UPPER 02
DELETED-NOT
- 83A . . .
USED
84 MS21083N8 . . . NUT 02
BOLT-AFT MADE
85 5541224-1 . . . FROM NAS464P8- 02
51
86 NAS1149F0632P . . . WASHER 02
DELETED-NOT
- 86A . . .
USED
87 MS21042L6 . . . NUT 02
88 NAS77-6-20 . . . BUSHING-AFT 02
- . . . TRUNNION FSO
89 5541306-1 A THRU D NP
5541306-2
TRUNNION FSO
- 90 5541306-2 . . . E THRU K NP
5541306-3
- . . . TRUNNION FSO
91 5541306-3 E THRU K NP
5541306-5
TRUNNION FSO
91A 5541306-4 . . . L THRU V NP R
5541306-5
- 91B 5541306-5 . . . TRUNNION W THRU Z 01 R
BRACE-DRAG FSO
- 92 5541308-1 . . . A&B NP
5541308-2

Copyright © Textron Aviation Inc. Page 3 of 9

- . . . BRACE FSO
93 5541308-2 A THRU D NP
6541300-1
. . . DRAG BRACE FSO
94 6541300-1 E THRU R NP R
6541300-2
- 94A 6541300-2 . . .
DRAG BRACE S THRU Z 01 R
ATTACHING
PARTS
95 NAS464P6A28 . . . BOLT-UPPER 01
96 NAS1149F0632P . . . WASHER-UPPER 02
- . . . DELETED-NOT
96A
USED
97 MS21042L6 . . . NUT-UPPER 01
98 NAS464P9A16 . . . BOLT-LOWER 01
99 NAS1149F0932P . . . WASHER-LOWER 02
- . . . DELETED-NOT
99A
USED
100 MS21245L9 . . . NUT-LOWER 01
- . . . NUT-LOWER ALT
100A NAS1291-9 01
FOR MS21245L9
---*---
- . . . BARREL-LH FSO
101 5541100-1 A&C NP
5541320-203
- . . . CYLINDER ASSY-LH
102 5541100-3 A&C NP
FSO 5541320-203
CYLINDER ASSY-LH
- 103 5541100-5 . . . A&C NP
FSO 5541320-203
- . . . CYLINDER ASSY-LH
104 5541107-1 C,E & G NP
FSO 5541320-203
- . . . CYLINDER ASSY-LH
105 5541109-5 NP
FSO 5541320-203
CYLINDER ASSY-LH
- 106 5541109-1 . . . NP
FSO 5541320-203
- . . . CYLINDER ASSY-LH
106A 5541320-1 NP
FSO 5541320-203
. . . CYLINDER ASSY-LH
106B 5541320-3 L,N,P,S & T NP R
FSO 5541320-203
CYLINDER ASSY-LH
- 106C 5541320-5 . . . S,T,W & X NP R
FSO 5541320-203
- 106D 5541320-203 . . . CYLINDER ASSY-LH 01
- . . . BARREL-RH FSO
107 5541100-2 B&D NP
5541320-202
CYLINDER ASSY-
- 108 5541100-4 . . . RH FSO 5541320- B&D NP
202

Copyright © Textron Aviation Inc. Page 4 of 9

CYLINDER ASSY-
- 109 5541100-6 . . . RH FSO 5541320- B&D NP
202
CYLINDER ASSY-
- 110 5541107-2 . . . RH FSO 5541320- F&H NP
202
CYLINDER ASSY-
- 111 5541107-4 . . . RH FSO 5541320- F&H NP
202
CYLINDER ASSY-
- 112 5541109-6 . . . RH FSO 5541320- NP
202
CYLINDER ASSY-
- 113 5541109-2 . . . RH FSO 5541320- NP
202
CYLINDER ASSY-
- 113A 5541320-2 . . . RH FSO 5541320- NP
202
CYLINDER ASSY-
- . . . M,Q,R,U &
113B 5541320-4 RH FSO 5541320- NP R
V
202
CYLINDER ASSY-
- 113C 5541320-6 . . . RH FSO 5541320- U,V,Y & Z NP R
202
- . . . CYLINDER ASSY-
113D 5541320-202 01
RH

NOMENCLATURE EFFECTIVITY UNITS

PER
ITEM PART NUMBER 1 2 3 4 5 6 7 FROM TO ASSY
- MAIN LANDING GEAR ASSEMBLY
STUD-ACTUATOR
150 . . ATTACH REFER TO RF
NOTE 2
- . . PLACARD-FILLING
151 5540001-3 A THRU D 01
INSTRUCTIONS
PLACARD-FILLING
. . E,F,G,H,L,N,
152 5540001-11 INSTRUCTIONS 01 R
Q,S,W & Y
REFER TO NOTE 3
- . . PLACARD-FILLING J,K,M,P,R,T,
153 5540001-16 01 R
INSTRUCTIONS U,V,X & Z
. . VALVE VALVE ASSY-
154 AN6287-1 01
AIR CHARGE
155 NAS1611-015 . . O-RING SEE NOTE 1 01
156 MS21258C28 . . WASHER-HUB 01
157 MS21025-28 . . NUT-HUB 01
158 MS24665-429 . . COTTER PIN A THRU F 01
159 AN814-4L . . PLUG 01

Copyright © Textron Aviation Inc. Page 5 of 9

160 NAS1612-4 . . O-RING SEE NOTE 1 01

NOTE 1: THIS PART MAY BE ORDERED AS PART OF MAIN LANDING GEAR SEAL KIT NUMBER CPD2
NOTE 2: REFER TO ILLUSTRATED PARTS CATALOG FOR STUD, WASHER SET AND NUT
NOTE 3: USED ON LANDING GEAR ASSEMBLIES 6541000-27,-28,-37,-38 INSTALLED ON MODEL 500
- Item Not Illustrated

Copyright © Textron Aviation Inc. Page 6 of 9

Figure 1001 : Sheet 1 : MAIN LANDING GEAR ASSEMBLY

Copyright © Textron Aviation Inc. Page 7 of 9

Figure 1001 : Sheet 2 : MAIN LANDING GEAR ASSEMBLY

Copyright © Textron Aviation Inc. Page 8 of 9

Figure 1001 : Sheet 3 : MAIN LANDING GEAR ASSEMBLY

Copyright © Textron Aviation Inc. Page 9 of 9

MAIN LANDING GEAR STRUT ASSEMBLY

NOMENCLATURE EFFECTIVITY UNITS
PER
ITEM PART NUMBER 1 2 3 4 5 6 7 FROM TO ASSY
- MAIN LANDING GEAR STRUT ASSEMBLY
- 1 5541000-3 . LANDING GEAR ASSY-LH A 01
- 2 5541000-4 . LANDING GEAR ASSY-RH B 01
- 3 5541000-9 . LANDING GEAR ASSY-LH C 01
- 4 5541000-10 . LANDING GEAR ASSY-RH D 01
- . LANDING GEAR ASSY-LH
5 5541000-11 E NP
FSO 6541000-37

- . LANDING GEAR ASSY-RH

6 5541000-12 F NP
FSO 6541000-38

- . LANDING GEAR ASSY-LH

7 6541000-3 G NP
FSO 6541000-37
LANDING GEAR ASSY-RH
- 8 6541000-4 . H NP
FSO 6541000-38
- . LANDING GEAR ASSY-LH
8A 6541000-11 J NP
FSO 6541000-37

- . LANDING GEAR ASSY-RH

8B 6541000-12 K NP
FSO 6541000-38
- 8C 5541000-17 . LANDING GEAR ASSY-LH L 01
- 8D 5541000-18 . LANDING GEAR ASSY-RH M 01
LANDING GEAR ASSY-LH
- 8E 6541000-27 . N NP
FSO 6541000-37

- . LANDING GEAR ASSY-RH

8F 6541000-28 P NP
FSO 6541000-38
- 8G 6541000-33 . LANDING GEAR ASSY-LH Q 01
- 8H 6541000-34 . LANDING GEAR ASSY-RH R 01
- 8J 6541000-37 . LANDING GEAR ASSY-LH S 01
- 8K 6541000-38 . LANDING GEAR ASSY-RH T 01
TORQUE LINK-LH
- 9 5541304-1 . . UPPER FSO 5541304- A NP
11
TORQUE LINK-LH
- 10 5541304-3 . . UPPER FSO 5541304- A NP
11
- 11 5541304-9 . . TORQUE LINK-LH A,C,E,G,J
01
UPPER L,N,Q,S
- 12 5541304-11 . . TORQUE LINK-LH A,C,E,G,J
01
UPPER L,N,Q,S
TORQUE LINK-RH
- 13 5541304-2 . . UPPER AND LOWER B,F,K,M,P NP
FSO 5541304-6

- . . TORQUE LINK-RH
14 5541304-6 B,D,F 02
UPPER AND LOWER

Copyright © Textron Aviation Inc. Page 1 of 7

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 13:09:04 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
32-10-00-1002 (Rev 14)

- . . TORQUE LINK-RH
15 5541304-6 F,H,K,M,P,R,T 01
LOWER
TORQUE LINK-RH
- 16 5541304-10 . . UPPER AIRPLANES F,H,K,M,P,R,T 01
WITH THRUST
REVERSER
ATTACHING
PARTS

- . . SHAFT FSO 5541212-

17 5541212-1 A THRU D NP
3

- . . SHAFT FSO 6541212-

18 5541212-3 E,F,L,M NP
2
19 6541212-2 . . SHAFT-TORQUE LINK E THRU T 02
20 MS16562-65 . . PIN LOWER 01
21 MS16562-66 . . PIN UPPER 01
---*---

- . . . TORQUE LINK-LH
22 5541304-5 A 01
UPPER
- . . . TORQUE LINK-LH
23 5541304-7 A 01
LOWER
. . . TORQUE LINK-LH A,C,E,G,J
24 5541304-13 01
UPPER L,N,Q,S

Copyright © Textron Aviation Inc. Page 2 of 7

WASHER-TOE IN
35 AN960-1016 . . AR
ADJUST
WASHER
- 35A NAS1149F1063P . . ALTERNATE FOR AR
AN960-1016
. . WASHER-TOE IN
36 AN960C1016L AR
ADJUST
WASHER
- 36A NAS1149C1032R . . ALTERNATE FOR AR
AN960C1016L
37 5541216-2 . . WASHER 01
38 MS17825-8 . . NUT 01
39 MS24665-287 . . COTTER PIN 01
- 40 5541206-1 . . ORIFICE-POPPET A THRU D 01
41 5541206-2 . . ORIFICE-POPPET E THRU T 01
ATTACHING
PARTS
- 42 RSN75 . . RING-RETAINING V80756 A THRU D 01
43 321C8 . . RETAINING RING V72800 E THRU T 01
---*---
- 44 5541310-2 . . BEARING-PISTON A THRU D 01
BEARING ASSY-
45 5541310-3 . . E THRU T 01
PISTON
46 NAS1081-4B4 . . SETSCREW 04

NOMENCLATURE EFFECTIVITY UNITS

PER
ITEM PART NUMBER 1 2 3 4 5 6 7 FROM TO ASSY
- MAIN LANDING GEAR STRUT
ASSEMBLY
75 5541208-1 . . SPACER 01
. . O-RING REFER TO
76 NAS1611-337 01
NOTE 1
RETAINER-BACKUP
77 MS28774-337 . . 01
REFER TO NOTE 1
BEARING-LOWER
- 78 5541309-2 . . A THRU D 01
SLEEVE
. . BEARING-LOWER
79 5541309-7 E THRU T 01
SLEEVE
POLY PAK SEAL
80 P81A5849-04207 . . V30781 01
REFER TO NOTE 1
SCRAPER REFER TO
81 MS28776M2-27 . . 01
NOTE 1
- . . RETAINER FSO
82 5541210-1 NP
5541210-2
83 5541210-2 . . RETAINER 01

Copyright © Textron Aviation Inc. Page 3 of 7

- . . A THRU
84 CM2690H21 LOCKRING 01
F,L,M
. . LOCKRING ALT FOR G,H,J,K
85 CM2690C21 01
CM2690H21 N,P,Q,R,S,T
- . . PISTON ASSY-LH
86 5541000-5 A,C NP
FSO 5541000-13
PISTON ASSY-RH
- 87 5541000-6 . . B,D NP
FSO 5541000-14
- 88 5541000-13 . . PISTON ASSY-LH E,L 01
- 89 5541000-14 . . PISTON ASSY-RH F,M 01
- . . PISTON AND AXLE
90 6541000-5 G 01
ASSY-LH
PISTON AND AXLE
- 91 6541000-6 . . H 01
ASSY-RH
- . . PISTON AND AXLE
91A 6541000-41 G,J,N,Q,S 01
ASSY-LH
- . . PISTON AND AXLE
91B 6541000-42 H,K,P,R.T 01
ASSY-RH
- 92 5541101-1 . . . PISTON ASSY-LH A,C NP
FSO 5541108-3
- . . . PISTON ASSY-RH
93 5541101-2 B,D NP
FSO 5541108-2
- . . . PISTON ASSY-LH
94 5541108-1 E,L NP
FSO 5541108-3
- 95 5541108-3 . . . PISTON ASSY-LH E,L 01
- 96 5541108-5 . . . PISTON ASSY-LH E,L 01
. . . PISTON ASSY-LH
96A 5541330-3 E,G,J,L,N,Q,S NP R
FSO 5541330-203
PISTON ASSY-LH
- 96B 5541330-203 . . . FOR SPARES E,G,J,L,N,Q,S 01 R
ONLY
PISTON ASSY-RH
- 97 5541108-2 . . . F,M NP
FSO 5541108-4
PISTON ASSY-RH
- 98 5541108-4 . . . ALT FOR F,M 01
5541108-6
- 99 5541108-6 . . . PISTON ASSY-RH F,M 01
PISTON ASSY-RH
- 99A 5541330-4 . . . F,H,J,M,P,R,T NP R
FSO 5541330-202
PISTON ASSY-RH
- 99B 5541330-202 . . . FOR SPARES F,H,J,M,P,R,T 01 R
ONLY
- 100 6541100-1 . . . PISTON ASSY-LH G 01
- 101 6541100-2 . . . PISTON ASSY-RH H 01
- . . . AXLE FSO
102 5541214-4 A THRU D NP R
6541200-200

Copyright © Textron Aviation Inc. Page 4 of 7

AXLE FSO
103 6541200-2 . . . E THRU T NP R
6541200-200
- . . . AXLE FOR
103A 6541200-200 A THRU T 01 R
SPARES ONLY
- . . . PLUG- A THRU
104 MS9176-29 01
EXPANSION F,L,M
PLUG-
105 5514350-17 . . . EXPANSION FSO G,H,J,K N,P NP
5514350-22
- . . . PLUG- G,H,J,K
105A 5514350-22 01
EXPANSION N,P,Q,R,S,T
106 NAS561P8-8 . . . PIN 01
END PLUG-MAIN
. . G,H,J,K
107 5541321-1 LANDING GEAR 01
N,P,Q,R,S,T
CYLINDER
O-RING-MAIN
- . . LANDING GEAR G,H,J,K
107A NAS1612-28 01
CYLINDER END N,P,Q,R,S,T
PLUG
O-RING REFER TO
108 NAS1611-328 . . 01
NOTE 1
PISTON-ISOLATION
- 109 5541000-205 . . USED WITH 5541108- A THRU F 01
1 AND 5541108-2
PISTON-ISOLATION
USED WITH 5541108-
110 6541000-200 . . 3, 5541108-4, G THRU T 01
5541108-5 &
5541108-6
O-RING TEFLON
111 S2672-31 . . . REFER TO NOTE 02
1
O-RING ALT FOR
- 112 R513-328 . . . V07060 02
S2672-31
113 5541400-1 . . SPRING 01
114 5541209-1 . . STOP 01
ATTACHING
PARTS
115 CM2689-5 . . RETAINER 01
---*---
NOTE 1: THIS PART MAY BE ORDERED AS PART OF CPD2 MAIN LANDING GEAR SEAL KIT
- Item Not Illustrated

Copyright © Textron Aviation Inc. Page 5 of 7

Figure 1002 : Sheet 1 : MAIN LANDING GEAR STRUT ASSEMBLY

Copyright © Textron Aviation Inc. Page 6 of 7

Figure 1002 : Sheet 2 : MAIN LANDING GEAR STRUT ASSEMBLY

Copyright © Textron Aviation Inc. Page 7 of 7

MAIN GEAR ASSEMBLY - ILLUSTRATED PARTS LIST

1. Illustrated Parts List
A. Introduction.
(1) The Illustrated Parts List will help the customer to order, keep, and supply the main landing gear components. It will
also identify new and reclaimed parts. It is not approved for any other purpose.
(2) The main gear assembly part numbers that follow are covered in this parts list:
6641000-3 6641000-4 6641000-19 6641000-20 6541001-3
6541001-4 6541001-7 6541001-8 6541001-13 6541001-14
6541001-21 6541001-22
(3) The indention system used in the detailed parts list of this catalog shows the relationship of one part to another. For a
given item, the indention code shows a general heading at the extreme left position and continues with indented
columns until the end detail is reached as follows:
A18017
1234567
Installation
Detail Parts for Installation
Assembly
Attaching Parts for Assembly
Detail Parts for Assembly
Subassembly
Attaching Parts for Subassembly
Detail Parts for Subassembly
Sub−Subassembly
Attaching Parts for Sub−Subassembly
Detail Parts for Sub−Subassembly

Basic Number Dash Number

(Drawing Identification
Only)

Copyright © Textron Aviation Inc. Page 1 of 1

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 13:09:13 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
32-10-01-0 (Rev 14)

MAIN GEAR ASSEMBLY - DESCRIPTION AND OPERATION

1. Description
A. The main gear assembly is designed and assembled to permit maneuverability of the airplane on the ground and to retract
into the wing when airborne. It is designed to absorb shock during airplane takeoffs, landings and taxiing. The main gear
assembly consists of a trunnion, shock strut, axle and torque links. Refer to Figure 1 and Figure 2.
(1) The trunnion is connected to the shock strut and is mounted in the wing wheel well with trunnion pins to allow the gear
assembly to retract into the wing.
(2) The shock strut consists of a cylinder assembly, a piston assembly and an isolation piston which floats within the
piston assembly. The chamber above the isolation piston is filled with hydraulic fluid. The chamber below the isolation
piston is charged with dry air or nitrogen. O-ring packings are used on the isolation piston to prevent leakage of
air/nitrogen or hydraulic fluid around the isolation piston.
(3) The axle is connected to the bottom of the strut piston; press fitted and secured with a pin.
(4) Torque links enable adjustment of the gear toe-in and toe-out. The upper torque link is connected at the shock strut
cylinder and the lower torque link connected to the shock strut piston. The upper and lower torque links are connected
together to permit piston vertical movement in the cylinder and prevent piston rotation in the cylinder.
(5) These main gear assembly part numbers are affected by this Section:
6641000-3 6641000-4 6641000-19 6641000-20 6541001-3
6541001-4 6541001-7 6541001-8 6541001-13 6541001-14
6541001-21 6541001-22
2. Operation
A. As weight of the airplane is applied to the main gear assembly, the piston assembly is forced to slide into the cylinder
assembly. This movement forces hydraulic fluid to flow from the cylinder chamber through an orifice in the top of the piston
into the piston chamber against the isolation piston. The restricted fluid flow and the resistance of the compressed
air/nitrogen below the isolation piston dampens the movement of the piston assembly and absorbs compression shocks.
As the weight of the airplane is removed from the main gear assembly, the compressed air/nitrogen forces the isolation
piston toward the top of the piston chamber. The hydraulic fluid is forced into the cylinder chamber and the piston assembly
extends. Refer to Figure 3.
3. Personnel Safety Precautions - Hydraulic Fluid
A. The main gear assembly contains phosphate ester base hydraulic fluid. Before performing maintenance or any operation
on the main gear shock strut assembly, personnel should read and thoroughly understand the following.
WARNING: Observe the following safety precautions when working on systems containing phosphate ester
base fluid. Prolonged exposure to the fluid can cause skin dehydration and chapping.
(1) Wash hands thoroughly with soap and water before starting work; apply barrier cream (silicone hand cream) to
hands, wrists and forearms. Rub cream under fingernails and into creases of skin.
(2) Wear eye goggles when pressure testing components or systems or anytime there is a possibility of hydraulic fluid
spraying/splashing in the eyes.
(3) If hydraulic fluid enters the eyes, treat eyes immediately by irrigating thoroughly with clear, cold water.
(4) Wash hands, wrists and forearms with soap and warm water after contacting hydraulic fluid.
(5) If clothing becomes soaked with hydraulic fluid, remove the clothing as soon as possible. Wash hydraulic fluid
exposed skin with soap and warm water. Wash hydraulic fluid contaminated clothes before wearing.
4. Technical Safety Precautions - Hydraulic Fluid
A. Because the main gear strut contains phosphate ester base hydraulic fluid, improper maintenance practices can be
damaging to gear components and other equipment. Before performing maintenance or any operation on the main gear
shock strut assembly, personnel should read and thoroughly understand the following technical precautions.
CAUTION: Phosphate ester base hydraulic fluid will damage and/or deteriorate a wide range of materials,
including rubber, copper, various plastics and paints.
(1) Make sure that hydraulic fluid does not come in contact with any part of the component outside of the main gear
shock strut. Keep spillage to an absolute minimum. Clean up spilled hydraulic fluid immediately to prevent

Copyright © Textron Aviation Inc. Page 1 of 5

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 13:09:14 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
32-10-01-0 (Rev 14)

contamination of non-hydraulic components and to avoid false hydraulic leak detections. If spillage occurs, wipe up
the fluid with a dry cloth and wash area with naphtha MIL-PRF-680, (Type III).
(2) When gear components are disassembled, provide suitable protection for preventing entry of foreign material by
using caps and/or covers.
(3) Always check angle and position of components prior to disassembly to ensure proper alignment and placement of
components and hardware during assembly or replacement.
(4) Use naphtha MIL-PRF-680 (Type III) or Methyl n-Propyl Ketone when washing metal parts prior to assembly. Make
sure all traces of the cleaning agent are removed before assembly.
(5) Use only clean hydraulic fluid for flushing or testing hydraulic components.
(6) Do not unpack seals, O-rings/packings until they are required and ensure that only correct and approved seals, O-
rings/packings are used.
CAUTION: Take special care not to contaminate seals, o-rings/ packings after lubrication.
CAUTION: Prevent contamination of phosphate ester base hydraulic fluid with other hydraulic fluids, oil, water
or dirt.
(7) When assembling the gear shock strut hydraulic seals and O-rings/packings, lubricate only with phosphate ester
base hydraulic fluid. Always lubricate seals, O-rings/packings immediately before installation. Threaded fittings
should be assembled without the use of lubricants whenever possible. If a lubricant is required to prevent galling or to
otherwise ease installation, use phosphate ester base hydraulic fluid or VV-P-236 Petrolatum.

Copyright © Textron Aviation Inc. Page 2 of 5

Figure 1 : Sheet 1 : Main Gear Assembly

A83874

Trunnion

Strut Drag Brace

Torque Links

Axle

5641T1065

Copyright © Textron Aviation Inc. Page 3 of 5

Figure 2 : Sheet 1 : Main Gear Strut Assembly

Copyright © Textron Aviation Inc. Page 4 of 5

Figure 3 : Sheet 1 : Main Gear Strut Assembly Operation

Copyright © Textron Aviation Inc. Page 5 of 5

MAIN GEAR ASSEMBLY - TESTING

1. Testing
A. Service Main Gear Strut for Test.
WARNING: Do not stand in front of valve assembly while releasing air/nitrogen pressure. Do not turn 0.75 inch
hex nut while releasing air/nitrogen pressure. Removing air filler valve without releasing
air/nitrogen pressure first can cause bodily injury.
(1) Position and maintain strut in an upright position to expel any fluid collected in the air chamber.
(a) Entry of fluid in the air chamber occurs as the oil film seeps by the seal during strut operation. A nominal amount
of oil seepage on a strut is approximately one drop per 100 hours of operation; however, some struts may have
more or less seepage and still be serviceable.
(b) Fluid accumulation in the strut air chamber with little or no piston movement requires additional inspection and
maintenance to correct oil from leaking into the air chamber.
(2) Rotate outer 0.625 inch hex nut on the air filler valve (AN6287-1) counterclockwise (CCW), to lift internal valve poppet.
Then attach a valve core depressor or remove valve core to release any trapped air/nitrogen and/or fluid.
(3) Remove plug (MS24391-8L) from the top of the strut and replace with a reducer (MS24399-11) and gasket
(NAS1612-8).
(4) Attach hose from a hand pump containing clean hydraulic fluid (Skydrol 500B or equivalent), and operate pump until
the strut is partially extended, but not to the stop limit.
CAUTION: Do not exceed 300 PSIG applied pressure.
(5) Open pump check valve and force strut to the collapsed position as trapped air expels into hand pump reservoir.
(6) Repeat pump cycling of strut until no air/nitrogen is being discharged from the fluid chamber.
(7) Discontinue pump cycling of the strut with the strut in the collapsed position. Remove hose, fitting (union) and gasket.
(8) Keep full of fluid and do not disturb strut from the collapsed position until plug and new gasket has been installed in
the top of the strut and tightened. The fluid chamber is to be entirely free of air/nitrogen. Safety wire plug to trunnion
attach nut using the double-twist method of installing safety wire.
NOTE: Strut assembly to be charged/serviced with nitrogen only.
WARNING: Servicing the strut with air before strut is properly serviced with hydraulic fluid could result in
blowing strut apart causing damage to equipment and/or injury to personnel.
(9) Install nitrogen filler valve core (if previously removed). Connect nitrogen source with pressure gage and charge strut
by turning 0.625 inch hex nut a maximum of 1-1/2 turns counterclockwise. Charge strut with nitrogen as follows:
(a) Charge strut to 300 PSIG with strut fully extended. Bleed pressure down to 280 PSIG.
(10) Tighten 0.625 inch hex nut 50 to 70 inch-pounds.
B. Test.
(1) After accomplishing Testing, paragraph A., leave strut assembly charged for a one hour period. No fluid leakage or
loss of nitrogen pressure as indicated on the pressure gage is permissible.
WARNING: Do not stand in front of filler valve assembly when releasing nitrogen pressure. Do not turn 0.75
inch hex nut while releasing pressure. Removing nitrogen filler valve without releasing nitrogen
pressure first can cause bodily injury.
(2) Release all nitrogen from the strut through the filler valve. If fluid is noted coming through the filler valve, consult
troubleshooting procedure.
2. Troubleshooting
A. The main gear assembly may be tested as outlined in Testing, for determining fluid or nitrogen leakage. Testing results,
visual checking and/or a review of information received with the gear assembly may be utilized in conjunction with the
following while troubleshooting.
B. Troubleshooting.
TROUBLE PROBABLE CAUSE REMEDY

Copyright © Textron Aviation Inc. Page 1 of 2

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 13:09:21 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
32-10-01-1 (Rev 5)

OIL LEAK AROUND PISTON Damaged packings or seals on Replace packings and seals.
lower bearing
Damaged scraper Replace scraper.
Cracked bearing Replace bearing.
Piston cut or nicked Polish out cut or nick.
Flat spot on piston Replace piston.
STRUT DOES NOT EXTEND WHEN Damaged or worn packings isolation Replace packings.
WEIGHT REMOVED AND/OR OIL piston
PRESENT WHEN NITROGEN VALVE
OPENED
Stuck isolation piston Free isolation piston and check
damage.
Isolation piston damaged Replace isolation piston.
Low nitrogen pressure Check for leaky nitrogen valve and
replace if leaking, then recharge strut.
Piston wall damaged Hone piston inside diameter or replace
piston.

Copyright © Textron Aviation Inc. Page 2 of 2

MAIN GEAR ASSEMBLY - DISASSEMBLY

1. Disassembly
NOTE: Review Safety Precautions in Main Gear Assembly - Description and Operation before beginning
disassembly.
A. Preparation for Disassembly (Refer to Illustrated Parts List).
(1) Rotate 0.625 inch hex nut on air valve (23) counterclockwise one and one-half turns to lift internal valve poppet, then
release any trapped gas or liquid by depressing valve core.
WARNING: Do not stand in front of valve assembly while releasing gas pressure. Do not turn 0.75 inch hex nut
while releasing gas pressure. Removing air valve without releasing compressed gas can cause
bodily injury.
(2) Ensure that gas is released by sliding piston in and out of cylinder.
(3) Cut lockwire and remove air valve (23) and packing (24) from piston assembly.
(4) Remove plug (25) and packing (26) from top of cylinder assembly (11).
(5) Drain hydraulic fluid by inverting strut assembly.
B. Torque Link Removal (Refer to Illustrated Parts List).
(1) Remove squat switch and attaching hardware.
(2) Remove upper and lower torque link shaft attach pins (104).
(3) Remove upper and lower torque link shafts (103). Note shaft positions for reassembly.
(4) Remove torque links (99 and 100) from strut assembly before further disassembly.
(5) Remove cotter pin (108), nut (107), washer (106), spacing washers (109, 110 and 111) and bolt (105).
NOTE: Avoid changing toe-in adjustment. Note location of spacing washers and of each torque link
attaching part for reassembly.
(6) Remove bearings (101 and 102) from torque links.
C. Piston Removal (Refer to Illustrated Parts List).
(1) Push bearing (91) and scraper (85) into cylinder enough to free retainer (87). Remove retainer (87) from cylinder.
(2) Remove piston assembly from cylinder.
D. Piston Disassembly (Refer to Illustrated Parts List).
(1) Remove two setscrews (98) so that bearing (97) can be unscrewed.
(2) Unscrew and remove bearing (97) from top of piston assembly.
(3) Remove retainer (96) and poppet orifice (95) from bearing (97).
(4) Remove spacer (92) from barrel of piston assembly.
(5) Slide bearing (91), scraper (85), and scraper retainer (86) from piston assembly barrel.
(6) Remove packing (89) and back-up ring (90) from outer surface of bearing (91).
(7) Remove "T" seal (88) from inner channel of bearing (91).
(8) Extract isolation piston (93) from piston assembly barrel.
(9) Remove packing (94) from isolation piston (93).
E. Remove Drag Brace (Refer to Illustrated Parts List).
(1) Remove nut (16), washer (15) and bolt (14).
(2) Remove nut (19), washers (18) and bolt (17); then, remove drag brace (13).
F. Trunnion and Cylinder Disassembly (Refer to Illustrated Parts List).
NOTE: The trunnion and cylinder need not be disassembled if they have previously been assembled
using a sealant to prevent corrosion.
(1) Remove two aft bolts (9), washers and nuts.
(2) Remove two forward bolts (5), washers and nuts.
(3) Remove cylinder from trunnion.

Copyright © Textron Aviation Inc. Page 1 of 2

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 13:09:23 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
32-10-01-3 (Rev 5)

NOTE: The cylinder and trunnion are press-fitted together.

G. Axle Removal (Refer to Illustrated Parts List).
NOTE: Do not remove axle unless inspection reveals that replacement is necessary. If axle is cracked or
damaged, inspect piston (79) before removing axle.
(1) Remove the safety wire and drive out the pin (83) securing the axle to the piston. Discard the pin.
(2) Using an arbor press, support the piston on a wooden block centered over a 2.25 inch diameter hole in the block.
Press out the axle using care to prevent damage to the piston.
(3) Remove expansion plug (84) from axle (81).

Copyright © Textron Aviation Inc. Page 2 of 2

MAIN GEAR ASSEMBLY - CLEANING

1. Cleaning
A. Tools and Equipment.
NAME NUMBER MANUFACTURER USE
Methyl n-Propyl Ketone Clean metal parts.
Solvent Blend Desoclean 110 PRC-DeSoto International Clean metal parts.
5426 San Fernando Rd.
Glendale, CA 91209
Paint Stripper T-6776 LO Turco Products, Inc. Strip paint from metal parts
Westminster 92684 prior to inspection.
CA
Naptha P-D-680 (Type III) Commercially Available Metal parts cleaning that
require soak cleaning.
Protective Oil Oakite Special Oakite Products Inc. Protect metal surfaces that
Protective Oil 50 Valley Road have had paint removed.
Berkeley Heights, NJ 07922
Hydraulic Assembly MCS 352 Aviation Fluids Service Co. Protect surfaces normally in
Lubricant St. Louis, MO 63166 contact with hydraulic fluid.
B. Cleaning.
WARNING: Use cleaning solvents only in well ventilated areas. Avoid inhaling solvent vapors. Keep solvent
and solvent containers away from spark or open flame.
(1) Clean metal parts and phenolic bearings with approved solvent. Remove stubborn deposits by hand-rubbing with
nonabrasive pads or material. Apply solvent under pressure to all lubrication fittings, channels and other internal
cavities to ensure cleanness. Thoroughly dry all parts with filtered, dry, compressed air and a lint-free cloth or lint-free
disposable tissue.
(2) Labels or identification plates which are attached by adhesive shall be removed by lifting the corner and pulling free.
Remove adhesive with clean cloth dipped in cleaning solvent.
CAUTION: Do not allow paint stripper to contact high heat treated steel pins such as pins attaching landing
gear components. Paint strippers may induce hydrogen embrittlement in high heat treated steel.
(3) Before stripping paint, thoroughly mask off or remove high heat treated steel pins such as pins attaching landing gear
components.
WARNING: All paint strippers are harmful to eyes and skin. Operators shall wear goggle-type glasses, rubber
gloves, aprons and boots. In case of contact with skin, flush with water. In case of contact with
eyes, flush eyes thoroughly with water and consult a physician immediately. Paint stripping shall
be done in a well ventilated area. Follow manufacturer's instructions carefully to release pressure
before opening paint stripper storage containers.
(4) Apply paint stripper on painted parts following the recommended manufacturer’s instructions. Allow the first
application to work from 5 to 45 minutes or as advised by manufacturer's instructions. If necessary, scrub softened
areas with brush to loosen paint. Rinse with water. Repeat as necessary to remove all paint. After paint is completely
removed, rinse part thoroughly with water spray. Dry part with filtered, dry, compressed air and a lint-free cloth or lint-
free disposable tissue.
(5) After drying, coat all parts, that would normally come in contact with hydraulic fluid during operation, with clean
hydraulic fluid or hydraulic assembly lubricant. External metal surfaces or other parts not coming in contact with
hydraulic fluid during operation of the strut need not be coated. However, highly machined surfaces may be coated
with hydraulic fluid or other suitable protective coating.
(6) If checking and repair procedures do not immediately follow cleaning, coat all surfaces that have had paint removed
with a suitable protective oil.

Copyright © Textron Aviation Inc. Page 1 of 1

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 13:09:24 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
32-10-01-5 (Rev 12)

MAIN GEAR ASSEMBLY - CHECK

1. Check
A. Tools and Equipment.
NAME NUMBER MANUFACTURER USE
Cupric Sulfate Commercially Available Chrome surface check.
Sulfuric Acid Concentrated (18N) Commercially Available Chrome surface check.
B. Recommended Checking Methods.
(1) Consult Table 501 to determine the recommended method of checking each component.
(2) Check all parts visually under strong light for surface cracks, flaws, burrs, pitting, scoring or any other wear.
(3) Replace all parts showing cracks or flaws under dye penetrant, magnetic particle or visual inspection.
(4) Check all friction surfaces and machined holes for wear beyond tolerances given in Fits and Clearances.
(5) Check all bolts, nuts and screw threads, both external and internal, for evidence of stripping or scoring. Replace all
parts that have stripped threads.
(6) Check shafts and pins for ovaling, or other signs of wear.
C. Checking Chrome Plating.
CAUTION: When mixing solutions, always add acid to water; never add water to acid.
(1) Check the chrome surfaces of the shock strut assembly for scratches, scores, blisters, and nicks. All suspected
defects should be tested to determine if the base metal has been exposed. To test, apply liberally to the suspected
areas a copper sulfate solution consisting of 100 grams cupric sulfate, five (5) milliliters sulfuric acid and one (1) liter
of water. Wipe off excess liquid and inspect, using a strong light and a magnifying lens. If the chrome plating has been
penetrated, a copper coating will adhere to the ferrous metal. Clean the area thoroughly using approved solvent, refer
to Main Gear Assembly - Cleaning. If the chrome plating has been penetrated in the sealing area, the part shall not be
returned to airplane use. If the chrome plating on the piston below the sealing surface is penetrated but no damage to
the steel is detectable, then the chrome damage may be repaired by cleaning and applying MIL-PRF-23377
corrosion resistant primer. After this repair is complete the piston may be returned to service. Defects that have not
penetrated the chrome plating should be polished to remove sharp edges that could damage seals. A honing stone
or crocus cloth may be used for this purpose.
Table 501. Recommended Inspection (Refer to Illustrated Parts List for Reference).
Nomenclature Item Method of Checking Check For Requirement
Number Same as
Illustrated Parts List
Number
Cylinder (11) Visual Wear, damage No damage or wear that would endanger
structure or interfere with function.
Magnetic particle Cracks No cracks.
Air valve (23) Visual Damage, stripped threads No damage or stripped threads.
Plug (25) Visual Stripped threads No stripped threads.
Piston (75) Visual Wear, damage inner No wear or damage that would prevent
diameter finish function.
Magnetic particle Cracks No cracks.
Ultrasonic Cracks No voids or cracks in brazed joints.
Retainers (86, 87, and Visual Wear, damage No wear or damage that would prevent
96) function.
Bearings (97 and 91) Visual Wear, damage No obvious wear or damage.

Copyright © Textron Aviation Inc. Page 1 of 2

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 13:09:25 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
32-10-01-5 (Rev 12)

Isolation piston (93) Visual Wear, damage No wear or damage that would prevent
(NOTE) function or sealing capability.
Shafts (103) Visual Ovaling or other damage Must meet dimensions given in Main Gear
Assembly - Fits and Clearances.
Magnetic particle Cracks No cracks.
Upper and lower Visual Out of round bearing holes, Holes must meet tolerances given in Fits
torque links (99 and wear or other damage to and Clearances. No wear or other
100) bearing or teflon lining. damage that would endanger structure or
prevent function.
Dye penetrant Cracks No cracks.
Spacer (92) Visual Damage or wear No obvious wear or damage.
Axle (81) Visual Stripped threads, damage No damage.
Magnetic particle Cracks No cracks.
Piston (79) Visual Corrosion Check for corrosion in areas described in
Main Gear Assembly - Repairs. If
corrosion is detected, repair as indicated.
If corrosion is detected in areas other than
those described for repairs, contact
Citation Customer Services Department
for disposition.
NOTE 1: The isolation piston has a teflon-impregnated hard coat anodized finish and should show little or
no wear.

Copyright © Textron Aviation Inc. Page 2 of 2

MAIN GEAR ASSEMBLY - REPAIR

1. Repair
NOTE: It is recommended that superseded parts be replaced in lieu of repair.
A. Tools and Equipment.
NOTE: Equivalent substitutes may be used for the listed items:
NAME NUMBER MANUFACTURER USE
Wet or dry sandpaper 400 Commercially Available Remove corrosion from gear
strut.
Emery Cloth 320 grit 400 grit Commercially Available Remove corrosion and final
finishing of axle and piston axle
adaptor.
Pretreatment primer Base 728-014 Shewin-Williams Inc. Pretreatment primer
DOD-P-15328 Reducer 728-013 16116 E. 13th Street
Andover, KS 67002
Fuel and Corrosion 10-P1-4 Base 10- Akzo Nobel Aerospace Corrosion protection primer for
Resistant Primer P1-4 Catalyst EC- One East Water st. integral fuel tanks
108 Thinner TR-19 Waukegan, IL 60085
Waterborne Corrosion U-4800/U-4801 Sterling Lacquer Manufacturing Co. Corrosion protection primer
Resistant Primer MIL- 3150 Brannon St.
PRF-85582 St. Louis, MO 63139
Waterborne Corrosion W9100- U.S. Paint Corp. Corrosion protection primer
Resistant Primer MIL- K11/W3100 831 South 21st St.
PRF-85582 St. Louis, MO 63130
Waterborne Corrosion 10PW20-4 Akzo Nobel Aerospace Corrosion protection primer
Resistant Primer MIL-
PRF-85582
Waterborne Corrosion 44-GN-60 /44-GN- Deft, Inc. Corrosion protection primer
Resistant Primer 60 CATA 17151 Von Karman Ave.
Irvine, CA 92714
Corrosion Resistant 02-Y-40 02-4-40 DEFT, Inc. Corrosion protection primer.
Primer MIL-PRF- CATA
23377G or later
Corrosion Resistant U-1201F/ U-1202F Sterling Lacquer Mfg. Corrosion protection primer.
Primer MIL-PRF-
23377G or later
Corrosion Resistant R4001-K14MAX U.S. Paint Corp. Corrosion protection primer.
Primer MIL-PRF- COR
23377G or later
Polyurethane paint, 7400 (Color Name: U.S. Paint Corp. Finish paint.
medium gray Pewter)
Adhesive RTV-154 General Electric Co. Bond filling instructions placard
Silicone Products Dept. to strut.
Waterford, NY 12188
Clear enamel AA92-C-21C U.S. Paint Corp. Cover filling instructions
placard.
Catalyst AA92-C-22B U.S. Paint Corp. Cover filling instructions
placard.

Copyright © Textron Aviation Inc. Page 1 of 12

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 13:09:26 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
32-10-01-6 (Rev 14)

Flexible drive Shaft Commercially Available To hone piston assembly inner

with 1/4 inch chuck barrel.
Hone CF63 or CF68 Snap-On Tools To hone piston assembly inner
3150 Terrace barrel.
Kansas City, MO 64111
Honing oil Sun Concentrate Sun Oil Company To oil stones while honing.
1501 P.O. Box 2039
Tulsa, OK 4102
Hydraulic assembly MCS 352 Aviation Fluids Service Co. To lubricate piston assembly
lubricant St. Louis, MO 63166 inner barrel.
Stones - 2 2-inch fine JT63-24 Snap-On Tools Used with CF63 or CF68
(400 grit) hones to hone piston assembly
inner barrel.
B. Replacement of Damaged Parts.
(1) Replace all parts that show visual wear, cracks or flaws.
(2) Replace all parts that show cracks under visual or dye penetrant inspection.
(3) Replace all parts indicating cracks or flaws under ultrasonic, X-ray, or magnetic particle inspection.
(4) Replace all parts that have machined holes that are worn beyond tolerance limits.
C. Chrome Surface Repair.
CAUTION: When buffing or polishing out scratches on chrome surfaces, extreme caution must be taken not
to penetrate the chrome plating or create low spots by too much localized buffing or polishing.
(1) Scratches or nicks that have not penetrated the chrome plating of the piston and axle assembly or the upper cylinder
assembly may be honed and polished to remove sharp edges that could damage the seals. A honing stone or crocus
cloth may be used for this purpose. In the areas not subject to seal travel, scratches, pits and scoring that do not
penetrate the chrome plating are relatively unimportant. The sharp edges of the nicks should be removed by honing
and polishing. The presence of defects in this area, if properly repaired, are considered acceptable.
D. Piston Assembly (75) Inner Diameter Finish Rework.
NOTE: The inner barrel of the piston assembly is phosphate coated. This coating may be rough, causing
premature wear to the seals causing fluid to leak from the strut assembly. The following procedure
provides a method for smoothing this coating.
NOTE: This procedure is not intended to be performed after each overhaul. Perform this procedure only
once.
(1) Using a micrometer, check inside diameter of piston assembly to ensure it is within tolerance.
(2) Check inside of piston assembly for pitting. If pitted, replace the piston assembly.
(3) Hone the inside diameter of the piston assembly to remove a minimal amount of phosphate coating and to achieve a
smooth finish.
(a) Remove air charge valve assembly (23) and packing (24).
(b) Assemble hone, stones, flexible shaft with chuck and a variable speed drill.
NOTE: Install a piece of plastic, rubber hose or other suitable material over the chuck on flexible
shaft to prevent chuck from striking piston bore during honing.
(c) Adjust the hone and install into the end of piston assembly; expand hone assembly until stones are resting
against inner diameter of piston assembly. Apply honing oil as required.
CAUTION: Do not allow stones to get dry during honing; use honing oil freely while operating hone.
Allowing stones to get dry will result in scratching the inner diameter finish of the piston
assembly.
(d) Hone the piston assembly at a maximum speed of 600 RPM, one continuous stroke the length of bore and out,
keeping the hone moving through piston at all times until phosphate is removed.
(e) Thoroughly clean piston assembly after honing. Refer to Main Gear Assembly - Cleaning, for material.

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(f)Using a micrometer, check inside diameter of piston assembly to ensure honing did not exceed the 2.253
inches (57.226 mm) diameter.
(g) Install air charge valve assembly (23) and new packing (24).
(4) If piston assembly is not being reassembled, coat inside diameter with hydraulic assembly lubricant MCS 352.
E. Painting.
(1) Preliminary.
(a) Verify areas to be painted are free of dirt, oil, grease and/or corrosion.
(b) Do not paint tires, strut air valves, data plates, bearings, polished pistons, switches, wire bundles, clamps,
hydraulic hoses, wheels, axle spindle area within the wheels or contacting areas of the lower to upper torque
links.
(c) Retreat and paint removed wheels in accordance with manufacturer's Component Maintenance Manual.
(2) Pretreatment Primer.
(a) Mix and apply DOD-P-15328 pretreatment primer in accordance with the manufacturer’s instructions.
(3) Corrosion Resistant Primer.
(a) Mix and apply MIL-RF-23377 corrosion resistant primer in accordance with the manufacturer’s instructions.
(4) Top Coat.
(a) Polyurethane paint consists of two compounds; a base and a catalyst. Mix top coat in accordance with the
manufacturer’s instructions.
F. Install Service Placard.
(1) Bond Filling Instruction Placard to upper cylinder with RTV-154 adhesive. Prepare and apply adhesive in accordance
with manufacturers instructions.
(2) Apply two coats of clear polyurethane over the placard after installation. Prepare and apply polyurethane top coat in
accordance with manufacturers instructions.
G. Piston Axle Adaptor and Axle External Corrosion Inspection, Removal and Prevention.
NOTE: This procedure applies to the external areas of the piston axle adaptor and axle in the areas where
the brake assembly makes contact.
(1) Inspection of Piston Axle Adaptor and Axle.
(a) Inspect the piston axle adaptor and axle in the areas shown for damage to the finish and corrosion. Refer to
Figure 601. If the finish is not damaged and no corrosion exists, no further action is required. If corrosion is
present on the piston axle adaptor and/or axle, proceed to paragraph G. step (2), Rework of Piston Axle
Adaptor and Axle. If the finish is damaged, but no corrosion exists, proceed to paragraph G. step (4), Finish
Application.
(2) Rework of Piston Axle Adaptor and Axle.
(a) Determine if the axle can be reworked (Refer to Figure 601):
1 Using a steel wire brush, remove the loose corrosion from the axle in the area between the piston axle
adaptor and the area where the inboard wheel bearing and seal were located. Clean the axle with
approved solvent to remove all grease and dirt. Using a vernier micrometer, measure the diameter of the
axle and determine the average axle diameter.
NOTE: Average axle diameter is determined by measuring the axle at four different locations,
oriented 45 degrees apart, and averaging the four measurements.
a If the average axle diameter is less than 1.8000 inches (45.72 mm), the axle must be replaced. Refer
to Axle Installation section.
b If the average axle diameter is 1.8000 inches (45.72 mm) or greater, proceed with reworking
instructions.
NOTE: If the axle surface contains pits which remain after corrosion removal and it is
estimated that upon removal of these pits, the axle may not meet the absolute
minimum average diameter of 1.8000 inches (45.72 mm), it may not be feasible to
attempt to rework the axle since it is possible that the axle may require

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replacement.
(b) (Refer to Figure 601). Determine if the piston axle adaptor can be reworked as follows:
1 Using a steel wire brush, remove the loose corrosion from the piston axle adaptor in the area shown. Clean
the piston axle adaptor with approved solvent to remove all grease and dirt. Using a vernier micrometer,
measure the diameter of the piston axle adaptor and determine the piston axle adaptor average diameter.
NOTE: Piston axle adaptor average diameter is determined by measuring the piston axle
diameter at four different locations, oriented 45 degrees apart (as shown in Figure
601, View B-B), and averaging the four measurements.
a If the axle adaptor average diameter is less than 2.490 inches (63.246 mm), there is an optional
repair available that uses a Cessna controlled process. This process can remove the corrosion and
build up the axle adaptor with hard chrome plating. For more details, contact Cessna Customer
Services - Structures.
NOTE: Small local areas of the piston axle adaptor may indicate as small as 2.4850
inches (63.119 mm) diameter at any one location, but the piston axle adaptor
average diameter must still be a minimum of 2.4900 inches (63.246 mm).
b If the piston axle adaptor average diameter is 2.4900 inches (63.246 mm) or greater, the piston axle
adaptor does not require replacement and must have a finish applied. Refer to paragraph G. step (4),
Finish Application.
NOTE: If it is determined that either the axle or piston axle adaptor require replacement,
it may be desirable to replace the piston and axle assembly (which includes both
the piston and axle).
(3) Rework of Piston Axle Adaptor and Axle.
(a) Wrap a piece of thin (0.012 or 0.016) aluminum sheet, 5.70 X 1.0 inch (144.78 X 25.4 mm), around the axle and
secure in place with a worm-type hose clamp to protect the portion of the axle where the inboard bearing and
seal were located.
CAUTION: It is very important to preserve the axle radius at the inboard edge of the rework area. When
using the emery cloth, do not allow the edge of the emery cloth to form a groove in the radius;
instead, allow the emery cloth to ride up into the radius.
(b) Using a 0.75 inch (19.05 mm) wide strip of 320 grit (aluminum oxide) emery cloth, remove all corrosion on the
axle (between the piston axle adaptor and protected area). All corrosion, including any pitting of the metal, must
be removed. After all pits are removed, apply a final finish to the axle with 400 grit emery cloth (aluminum oxide).
(c) Remove the aluminum sheet protecting the axle and ensure all corrosion is removed up to the area where the
bearing seal was making contact with the axle. Remove any remaining corrosion with 400 grit emery cloth but
use minimum pressure when sanding over the seal area.
(d) Clean the area with approved solvent and measure the diameter of the axle in the reworked area at four
locations oriented 45 degrees apart and determine the average axle diameter. If the average axle diameter is
less than 1.7950 inches (45.593 mm), the axle must be replaced. Refer to Main Gear Assembly - Disassembly
and Main Gear Assembly - Assembly, for axle replacement instructions. If the average axle diameter is 1.7950
(45.593 mm) or greater, proceed with application of finish. Refer to paragraph G. step (4), Finish Application.
NOTE: Small local areas of the axle may indicate as small as 1.7900 inch diameter at any one
location, but the average axle diameter must still be a minimum of 1.7950 inch diameter.
(e) Remove all corrosion from the piston axle adaptor in the same manner as utilized for the axle. Upon removal of
all pits, measure the piston axle adaptor diameter at four locations oriented 45 degrees apart and average
together to determine the piston axle adaptor average diameter.
1 If the piston axle adaptor average diameter is less than 2.4900 inches (63.246 mm), the piston must be
replaced. Replace the piston in accordance with the Main Gear Assembly - Disassembly and Main Gear
Assembly - Assembly.
NOTE: Small local areas of the piston axle adaptor may indicate as small as 2.4850 inch
(63.119 mm) diameter at any one location, but the piston axle adaptor average
diameter must still be a minimum of 2.4900 inches (63.246 mm).
2 If the piston axle adaptor average diameter is 2.4900 inches (63.246 mm) or greater, the piston axle

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adaptor does not require replacement and must have a finish applied. Refer to paragraph G. step (4),
Finish Application.
(4) Finish Application.
(a) Clean the piston axle adaptor and/or axle with an approved solvent and wipe dry.
(b) Mask off areas of the piston not reworked.
(c) Mask off the outboard portion of the axle from the inboard wheel bearing seal. Ensure masking covers the
inboard wheel bearing seal contact point so that the seal does not ride on the MIL-PRF-23377 corrosion
resistant primer.
NOTE: MIL-PRF-23377 corrosion resistant primer must be applied to clean surfaces within 30
minutes of completion of sanding procedure. An oxide film which provides minimal
adhesion for primer begins to form immediately after working. Poorly adhered MIL-PRF-
23377 corrosion resistant primer will result in accelerated corrosion.
(d) Apply one coat of MIL-PRF-23377 corrosion resistant primer to the piston axle adaptor and/or the axle. Refer to
the Structural Repair Manual, Chapter 51, Protective Treatment of Metal, for application instructions for primer.
(e) Apply a thin film of wheel bearing grease to the outer surface of axle as a corrosion preventative treatment.
H. Axle Internal Corrosion Inspection, Removal, Modification and Prevention.
NOTE: This procedure applies to the internal areas of the axle from the outboard end to a point 1.63
inches (41.402 mm) inboard.
(1) Inspection of Axle.
(a) If corrosion exists in the outboard (1.63 inches (41.402 mm)) end of the axle internal bore the corrosion must be
removed by mechanical means. If corrosion is light and is removed by the use of 320 grit emery cloth (aluminum
oxide) with no remaining pits, measure the bore diameter. If the bore diameter is larger than 1.378, or pits
remain after the use of emery cloth, the bore will require machining to enlarge the bore to 1.4105 inches, +0.003
or -0.003 inches (35.826 mm, +0.076 or -0.076 mm). If corrosion was removed by the use of emery cloth and the
bore diameter was 1.378 inches (35.001 mm) or less, then no machining is required. Proceed to paragraph H.
step (2)(c) for finish application to prevent corrosion. If machining is required to enlarge the bore, proceed to
paragraph H step (2), Axle Rework, for machining requirements.
(2) Axle Rework.
NOTE: This procedure must be performed by a machinist using standard practices and techniques
for machining a precision bore in the axle (material 4340 steel).
(a) Refer to Main Gear Assembly - Disassembly for axle removal procedures.
(b) Enlarge the bore diameter to 1.4105 inches, +0.003 or -0.003 inches (35.826 mm, +0.076 or -0.076 mm).
Maintain a surface finish of 125 microinches. Maintain a 0.005 inch (0.127 mm) radius and a 0.062 inch (1.574
mm) chamfer at the transition point from the larger diameter bore to the smaller diameter bore 1.63 inches
(41.402 mm) inboard from the outboard end of the axle. Establish a 1.510 inch (38.354 mm) diameter 30
degrees chamfer at the outboard end of the bore.
NOTE: Primer must be applied to clean surfaces within 30 minutes of completion of sanding
procedure. An oxide film which provides minimal adhesion for MIL-PRF-23377 corrosion
resistant primer begins to form immediately after working. Poorly adhered primer will
result in accelerated corrosion.
(c) Clean the bore diameter and apply MIL-PRF-23377 corrosion resistant primer; refer to the Structural Repair
Manual, Chapter 51, Protective Treatment of Metal, for application procedures; then apply one coat of epoxy
enamel (medium gray). Refer to Painting.
(d) If airplane is equipped with an antiskid brake system, the axle bore must be shimmed back to 1.377 inches,
+0.001 or -0.001 inches (34.975 mm, +0.025 or -0.025 mm) diameter as follows:
1 Fabricate a stainless steel shim from sheet stock as shown in Figure 602. Deburr all edges. Abrade one
surface of the shim using 320 grit emery cloth (aluminum oxide).
2 Roll shim to 1.41 inch (35.814 mm) diameter with abraded surface to the outside. Clean outer surface of
shim with approved solvent.
3 Bond shim in the axle with the joint at the top using EA9309.3NA adhesive. Insert antiskid transducer

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(coated with wax and then wrapped with one layer of thin plastic, such as Saran Wrap, to act as a parting
agent) to hold the shim in position.
4 Allow adhesive to cure, then remove the antiskid transducer.
5 Reinstall axle. Refer to Main Gear Assembly - Assembly, for axle installation procedures.
I. Outer Cylinder Lower Bearing Area Corrosion Inspection, Removal, Modification and Prevention.
(1) Inspection of the outer cylinder lower bearing area.
(a) Inspect the outer cylinder lower bearing area as shown for damage to the finished surface due to corrosion.
Refer to Figure 603. If the finished surface is not damaged and no corrosion exists, proceed to step (3). If
corrosion is present on the outer cylinder lower bearing surface area, proceed to step (2).
(2) Preliminary rework of outer cylinder lower bearing surface area.
(a) Determine if the outer cylinder lower bearing surface area can be reworked as follows (Refer to Figure 603 ):
1 Verify that no corrosion exists on the uppermost 0.5 inch (12.7 mm) of the bearing surface. If corrosion is
found in this area, contact Citation Customer Service Department for disposition.
2 Using a stainless steel wire brush or glass bead peening, remove the corrosion from the outer cylinder
lower bearing area. Glass bead peening may be used to remove corrosion from the pits which were not
removed with the stainless steel wire brush.
3 Clean the outer cylinder bearing area with an approved solvent to remove all grease and dirt.
4 Using a dial micrometer with a pointed tip, measure the inner diameter of the outer cylinder lower bearing
area and determine the average bearing surface diameter to include the depth of pit.
NOTE: Average bearing surface diameter is determined by measuring the inner diameter at a
minimum of four different locations, starting at the most damaged location and
rotating 45 degrees either side, plus one additional location and averaging the four
measurements.
(b) If the average bearing surface diameter is greater than 3.405 inches (86.487 mm), or the maximum pit depth is
greater than 0.015 inch (0.381 mm), contact Citation Customer Service Department.
(c) If the average bearing surface diameter is less than 3.405 inches (86.487 mm), proceed to step 3.
NOTE: If the outer cylinder lower bearing surface contains pits which remain after corrosion
removal, and it is estimated that upon removal of these pits the outer cylinder lower
bearing surface may not meet the absolute maximum average diameter of 3.405 inches
(86.487 mm) or the maximum pit depth is greater than 0.015 inches (0.381 mm), it may not
be feasible to rework the outer cylinder. The outer cylinder may require replacement.
(3) Rework of outer cylinder lower bearing surface area.
(a) If the average bearing surface diameter is greater than 3.405 inches (86.487 mm), or the maximum pit depth is
greater than 0.015 inch (0.381 mm), contact Citation Customer Service Department.
(b) Use a rotary stainless steel wire brush or glass bead peening to remove all corrosion from the bearing and
retainer ring areas. Glass bead penning may be used to remove corrosion from the pits which were not removed
with the stainless steel wire brush. Insure that all corrosion is removed prior to proceeding.
(c) Clean the lower bearing surface and the retainer ring areas with an approved solvent, to remove all grease and
dirt. Wipe off solvent with a clean absorbent rag. Do not allow solvent to dry on the surface, remove all solvent
residue.
(d) Mask the machined step at the top edge of the lower bearing surface and a 0.50 inch (12.7 mm) band of the
upper portion of the lower bearing surface area, to prevent primer from being applied to these surfaces.
(e) Reclean the unmasked portion of the lower bearing surface with and approved solvent. Wipe off solvent with a
clean absorbent rag. Do not allow solvent to dry on the surface, remove all solvent residue.
(f) Immediately prime the abraded area with primer by one of the following procedures:
NOTE: Apply MIL-PRF-23377 corrosion resistant primer to clean surfaces within 30 minutes of
completion of sanding procedure. An oxide film which provides minimal adhesion for
primer begins to form immediately after working. Poorly adhered primer will result in
accelerated corrosion.

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NOTE: For exact mixing instructions for MIL-PRF-23377 corrosion resistant primer, refer to the
manufacturer’s instructions.
(g) Remove plug and the masking from the cylinder.
NOTE: MIL-PRF-23377 primer must be completely cured to have Phosphate Ester Hydraulic Fluid
resistance.
(h) Cure primer coating in accordance with the manufacturer’s instructions.
J. Outer Cylinder and Piston Assembly Torque Link Lug Inner Diameter Corrosion Inspection, Removal, Modification and
Prevention.
(1) Inspection
(a) Inspect the 0.875 inch (22.225 mm) diameter hole in the respective torque link lug for corrosion damage. Refer
to Figure 603. If the inner bore finish is not damaged, proceed to step (2)(c). If corrosion damage is present,
proceed to step (2).
(2) Preliminary rework of the torque link lug pin hole.
(a) Determine if the overall diameter of the torque link lug hole except in the locally corroded area is within tolerance
of (0.875 inch, +0.001 or -0.001 inch (22.225 mm, +0.025 or -0.025 mm)) after the removal of all corrosion.
1 Using a stainless steel wire brush, remove corrosion from the torque link lug pin hole. Glass bead penning
may be used to remove corrosion from the pits which were not removed with the stainless steel wire brush.
Insure that all corrosion is removed prior to finishing.
2 Clean the torque link lug hole with an approved solvent to remove all grease and dirt. Wipe off solvent with
a clean absorbent rag. Do not allow solvent to dry on the surface, remove all solvent residue.
(b) Using a dial micrometer, measure the lug hole and determine the average hole diameter as follows:
NOTE: Measure the diameter of the hole at a minimum of four different locations in the same
vertical plane. Start at the most damaged location and measure 15 degrees on either side
of this location, plus one additional location and average the four measurements.
1 If the average lug hole diameter at the corroded point is greater than 0.905 inches (22.987 mm) or the
maximum pit depth is greater than 0.015 inch (0.381 mm), proceed to Rework Torque Link Lug Hole-
Bushing Required.
2 If the average lug hole diameter is less than 0.905 inch (22.987 mm) at the corroded point, proceed to the
next step.
(c) Reclean the torque link lug hole with an approved solvent to remove all grease and dirt. Wipe off solvent with a
clean absorbent rag. Do not allow solvent to dry on the surface, remove all solvent residue.
(d) Option 1: Immediately apply MIL-PRF-23377 corrosion resistant primer to inside of the hole area with a
thickness of 0.6 to 0.9 mil. For mixing and application of MIL-PRF-23377 corrosion resistant primer refer to the
manufacturer’s instructions.
NOTE: MIL-PRF-23377 corrosion resistant primer must be applied to clean surfaces within 30
minutes of completion of brushing procedure. An oxide film which provides minimal
adhesion for MIL-PRF-23377 corrosion primer begins to form immediately after working.
Poorly adhered MIL-PRF-23377 corrosion resistant primer will result in accelerated
corrosion.
(e) Cure MIL-PRF-23377 corrosion resistant primer in accordance with the manufacturer’s instructions.
NOTE: MIL-PRF-23377 corrosion resistant primer must be completely cured to have Skydrol
resistance.
(f)
Option 2: Immediately coat inside of the hole area with Type 1 Class B2 sealer. Install the torque link pin and
wipe off all excess sealer.
(3) Rework the Torque Link Lug Hole Bushing Required.
(a) Ream the hole to 0.950 inch (24.13 mm) diameter.
(b) Fabricate from 4340 steel, heat treated to 180-200 KSI, a 2.498 inch (63.449 mm) long bushing to press fit into
the 0.950 inch (24.13 mm) hole. The interference fit of the outer diameter of the bushing shall be 0.001 to 0.002
inch (0.025 to 0.050 mm).

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(c) Coat the inside surface of the 0.950 inch (24.13 mm) (diameter oversized hole with Type 1 Class B2 sealer
prior to installation of the bushing.
(d) Use liquid nitrogen to cool the bushing prior to pressing into the torque link lug.
(e) After pressing the bushing into the 0.950 inch (24.13 mm) hole, ream the bore of the bushing inner diameter to
0.876 inch, +0.001 or -0.001 inch (22.250 mm, +0.025 or -0.025 mm) diameter. Finish the 0.876 inch (22.250
mm) inner diameter of the bushing as described in preliminary rework of the torque link pin hole, utilizing either
Option 1 or Option 2.

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Figure 601 : Sheet 1 : Main Landing Gear Piston Axle Adaptor and Axle Inspection

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Figure 601 : Sheet 2 : Main Landing Gear Piston Axle Adaptor and Axle Inspection

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Figure 602 : Sheet 1 : Axle Inside Diameter Corrosion Removal

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Figure 603 : Sheet 1 : Cylinder and Piston Corrosion Repairs

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MAIN GEAR ASSEMBLY - ASSEMBLY

1. Assembly
A. Tools and Equipment (Refer to Illustrated Parts List).
NOTE: Equivalent substitutes may be used for the listed items.
NAME NUMBER MANUFACTURER USE
Safety Wire Monel 0.020 inch Commercially Available Safety air valve and cylinder
diameter plug.
Hydraulic Assembly MCS 352 Aviation Fluids Service Company Lubricate and protect
Lubricant St. Louis, MO 63166 surfaces in contact with
hydraulic fluid or prevent entry
of water.
Loctite 609 Loctite Corporation Fill and seal trunnion to
705 N. Mountain Road cylinder and install bushings
Newington, CT 06111 in torque links.
Loctite 242 Loctite Corporation For the fasteners thread lock.
705 N. Mountain Road
Newington, CT 06111
Loctite 243 Loctite Corporation For the fasteners thread lock.
705 N. Mountain Road
Newington, CT 06111
Drill Bit Letter D Note 1 Commercially Available
Reamer 0.250 inch diameter Commercially Available
with a pilot 0.128
inch diameter and
0.375 inch length
Note 2
NOTE 1: Drill bit must have a 0.128 inch diameter pilot that is 0.375 inch in length.
NOTE 2: A reamer such as a Cleveland 4001 reamer, Number 25513 would be satisfactory. The pilot must be
machined onto the Cleveland reamer.
B. Axle Installation (Refer to Illustrated Parts List).
(1) Install the expansion plug (84) into the inboard end of the new axle using MIL-PRF-23377 corrosion resistant primer
and 1000 pounds, +500 or -000 pounds of force.
(2) Wipe out the hole in the piston with approved solvent.
(3) Prepare the arbor press to install the axle (81) in the piston using the wooden block used when pressing the axle out
of the piston.
(4) Coat the hole in the piston and the portion of the axle that makes contact with the piston with primer and press the
axle in position while primer is wet. Ensure that the keyway in a new axle (the threaded area of the axle) is oriented
up, or on a reinstalled axle, the keyway shall be oriented 60 degrees from the original keyway up position on the axle.
NOTE: 60 degrees deviation from original up position is required on reinstalled axle.
(5) Using a 0.250 O.D. x 0.128 I.D. drill bushing in the hole in the side of the piston and a number 30 (0.128 inch
diameter) drill bit, drill a hole through (one side only) of the axle to match the existing hole in the piston. Remove the
drill bushing and enlarge the hole using a letter D (0.246 inch diameter) drill bit with a 0.128 inch diameter pilot. Ream
the hole using a 0.250 inch diameter reamer with a 0.246 inch diameter pilot.
(6) Deburr the hole and install new pin (83) flush with the outside surface of the piston and secure with safety wire.
C. Torque Link Bushing Installation (Refer to Illustrated Parts List ).
(1) Clean paint, grease, dust or other contaminating substances from bushings and torque links.
WARNING: Use solvent in well ventilated area, avoid breathing fumes.

Copyright © Textron Aviation Inc. Page 1 of 3

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 13:09:41 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
32-10-01-7 (Rev 14)

(2) Use a clean rag saturated with approved solvent and clean bushings and torque links.
(3) Apply Loctite 609 to bearings (101) and torque links and press bearings (101) in place.
WARNING: Use solvent in a well ventilated area. Avoid breathing fumes.
(4) Excess Loctite may be removed with a rag moistened with approved solvent.
(5) Clean Loctite from lubrication holes.
(6) Cure time for Loctite on the bushings is 24 hours.
NOTE: When new torque link bearings are installed, it may be necessary to mill and ream bearings
(101) to dimensions shown in Main Gear Assembly - Fits and Clearances.
D. Piston Assembly (Refer to Illustrated Parts List).
WARNING: Long exposure to phosphate ester base fluids can cause skin dehydration and chapping.
(1) Immerse packings and seals in phosphate ester base hydraulic fluid.
(2) Install packing (94) on isolation piston (93).
(3) Coat the inner barrel of piston (75) with a thin layer of hydraulic fluid or hydraulic assembly lubricant.
(4) Insert isolation piston (93) into barrel of piston assembly (75). Push piston into barrel until stop seats against bottom.
(5) Install poppet orifice (95) into top of bearing (97) and attach with retainer (96).
(6) Install seal (89) with back-up ring (90) on bearing (91).
(7) Install "T" seal (88) into inner channel in bearing (91).
CAUTION: Do not allow retainers to scratch the chrome surface of the piston assembly.
(8) Slide retainer (86), scraper retainer (87), scraper (85), bearing (91) and spacer (92) over barrel of piston assembly
(75).
(9) Apply primer to threads of bearing (97). Allow to air dry then apply Loctite 242 or Loctite 243 to threads of bearing
(97).
CAUTION: Setscrews must be recessed below bearing surface. Make sure resistance is felt when installing
setscrews to insure self-locking capability. Replace setscrews not indicating locking capabilities.
(10) Screw bearing (97) on piston assembly and secure with two self-locking setscrews (98). Torque setscrews 20 to 30
inch-pounds.
E. Piston Installation (Refer to Illustrated Parts List).
(1) Pack area all around bearing (91) with hydraulic assembly lubricant (MCS-352) to resist entry of water about bearing
interface with strut cylinder collar.
(2) Carefully slide piston assembly into cylinder assembly. Seat bearing (91) into cylinder and install scraper (85),
scraper retainer (87) and retainer (86).
NOTE: Make sure retainer is seated in the lock ring groove, then extend strut piston assembly until
scraper retainer locks the lock ring in place.
F. Assemble Trunnion to Cylinder (Refer to Illustrated Parts List).
WARNING: Solvent is toxic and flammable; use in well ventilated area. Avoid breathing fumes and keep away
from flames.
(1) Clean inside diameter of trunnion and outside diameter of cylinder with approved solvent.
(2) Apply Loctite 609 to inside diameter of trunnion and outside diameter of cylinder using a clean brush.
NOTE: Apply sufficient amount of Loctite 609 to assure complete fill and seal.
(3) Press-fit cylinder into trunnion.
NOTE: Remove excess Loctite immediately and before subsequent exterior finishing.
(4) Install two forward bolts (5), washers (6 and 7) and nut (8).
(5) Install two aft bolts (9), washers (10), washers (7) and nuts (8).
G. Install Drag Brace (Refer to Illustrated Parts List).
(1) Position drag brace (13) in place in trunnion and cylinder.
(2) Install bolt (17), washers (18) and nut (19).

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(3) Install bolt (14), washers (15) and nut (16).

H. Torque Link Installation (Refer to Illustrated Parts List).
(1) Install upper and lower torque links (99 and 100), shafts (103) and shaft retainer pins (104).
(2) Install torque link interconnect bolt (105), toe-in adjustment washers (109, 110 and 111), flat washer (106), nut (107)
and cotter pin (108). Add or remove washers until a gap of 0.004 to 0.019 is obtained.
NOTE: Torque link toe-in adjustment washers and interconnect parts should be assembled exactly as
disassembled to maintain toe-in adjustment.
(3) Install squat switch and attaching hardware.
I. Service Fittings Installation (Refer to Illustrated Parts List).
(1) Install packing (24) and air valve assembly (23). Torque valve assembly 100 to 110 inch-pounds. Safety wire large nut
(0.75 inch) to forging. Use double twist method of installing safety wire.
NOTE: If new air valve assembly is being installed, discard packing and replace with phosphate ester
base fluid resistant packing, Part Number NAS1611-015.
(2) Install plug (25) and seal (26) in top of cylinder assembly. Safety wire plug to trunnion bolt using double twist method.
2. Storage
A. Recommended Storage Procedure.
(1) Release air from air valve; refer to Main Gear Assembly - Disassembly.
(2) Remove plug from top of cylinder assembly and drain hydraulic oil from cylinder. Replace plug.
(3) Collapse strut assembly. Coat exposed chromed surface of piston assembly with protective oil.
(4) Wrap collapsed strut in grease-proof paper, then kraft paper and pack in rigid container.
(5) Container shall be stored in a cool, dry, well ventilated area on a noncorrosive base.

Copyright © Textron Aviation Inc. Page 3 of 3

MAIN GEAR ASSEMBLY - FITS AND CLEARANCES

1. Fits and Clearances
A. Cylinder 6641320-1, -2, -3, -4

(1) 3.000, inch +0.002 or -0.000 inch (76.20 mm, +0.05 or -0.00 mm) diameter
(2) 3.00, inch +0.03 or -0.03 inch (76.2 mm, +0.7 or -0.7 mm) diameter
(3) 3.3600, inch +0.0000 or -0.0014 inch (85.344 mm, +0.036 or -0.000 mm) diameter
(4) 0.876, inch +0.001 or -0.000 inch (22.25 mm, +0.03 or -0.00 mm) diameter
B. Piston 6641330-1, -2

(1) 2.3115, inch +0.000 or -0.0020 inch (58.712 mm, +0.000 or -0.054 mm) diameter
(2) 0.005, inch (0.03 mm) maximum TIR (Total Indicator Reading)
(3) 2.750, inch +0.000 or -0.002 inch (69.85 mm, +0.00 or -0.05 mm) diameter
(4) 0.876, inch +0.001 or -0.000 inch (22.25 mm, +0.03 or -0.00 mm) diameter (lug hole)
(5) 2.497, inch +0.0000 or -0.0020 inch (63.42 mm, +0.000 or -0.054 mm) diameter
C. Torque Link 6641304-1, -2

Copyright © Textron Aviation Inc. Page 1 of 3

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Model 500 Series Component Maintenance Manual (Rev 17)
32-10-01-8 (Rev 9)

(1) 1.0627, inch +0.0008 or -0.0000 inch (26.99 mm, +0.020 or -0.000 mm) diameter
(2) 0.8126, inch +0.0007 or -0.0000 inch (20.640 mm, +0.018 or -0.000 mm) diameter
(3) 0.8765, inch +0.0015 or -0.0000 inch (22.263 mm, +0.038 or -0.000 mm) diameter
(4) 0.6265, inch +0.000 or -0.000 inch (15.913 mm, +0.00 or -0.00 mm) diameter
(5) 2.623, inch +0.000 or -0.0010 inch (66.62 mm, +0.00 or -0.08 mm) diameter
NOTE: Dimension (5) is measured between faces of bushings. Machine bushings after installation.
(6) 0.839, inch +0.000 or -0.003 inch (21.31 mm, +0.00 or -0.00 mm) diameter
D. Shaft, Torque Link 6541212-3

(1) 0.875, inch +0.000 or -0.001 inch (22.23 mm, +0.00 or -0.03 mm) diameter
(2) 0.250, inch +0.006 or -0.000 inch (6.35 mm, +0.15 or -0.00 mm) diameter
E. Torque Link End Bushing M81934/2-14C016

Copyright © Textron Aviation Inc. Page 2 of 3

(1) 0.0625, inch (1.59 mm) radius

(2) 0.8765, inch +0.0000 or -0.0010 inch (22.263 mm, +0.000 or -0.025 mm) diameter
(3) 1.0645, inch +0.0005 or -0.0005 inch (22.990 mm, +0.013 or -0.013 mm) diameter after installation and line
reaming.
F. Isolation Piston 6641307-2

(1) 1.997, inch +0.000 or -0.001 inch (50.72 mm, +0.00 or -0.03 mm) diameter
(2) 1.981, inch +0.000 or -0.001 inch (50.32 mm, +0.03 or -0.03 mm) diameter after installation and line reaming.

Copyright © Textron Aviation Inc. Page 3 of 3

MAIN LANDING GEAR ASSEMBLY

NOMENCLATURE EFFECTIVITY UNITS
PER
ITEM PART NUMBER 1 2 3 4 5 6 7 FROM TO ASSY
- MAIN LANDING GEAR ASSEMBLY

- . LANDING GEAR ASSY-LH

1 6641000-3 A NP
FSO 6641000-19
- 1A 6641000-19 . LANDING GEAR ASSY-LH C 01
LANDING GEAR ASSY-LH
- 1B 6541001-3 . FSO 6541001-21 REFER E NP
TO NOTE 1
- . LANDING GEAR ASSY-LH
1C 6541001-7 G NP
FSO 6541001-21

- . LANDING GEAR ASSY-LH

1D 6541001-13 J NP
FSO 6541001-21
- 1E 6541001-21 . LANDING GEAR ASSY-LH L 01

- . LANDING GEAR ASSY-RH

2 6641000-4 B NP
FSO 6641000-20
- 2A 6641000-20 . LANDING GEAR ASSY-RH D 01
LANDING GEAR ASSY-RH
- 2B 6541001-4 . FSO 6541001-22 REFER F NP
TO NOTE 1

- . LANDING GEAR ASSY-RH

2C 6541001-8 H NP
FSO 6541001-22
- . LANDING GEAR ASSY-RH
2D 6541001-14 K NP
FSO 6541001-22
- 2E 6541001-22 . LANDING GEAR ASSY-RH M 01

- 3 6641000-5 . . TRUNNION AND A,C 01

CYLINDER ASSY-LH
TRUNNION AND
- 3A 6641000-17 . . CYLINDER ASSY-LH E NP
FSO 6641000-25
REFER TO NOTE 2

- . . TRUNNION AND
3B 6641000-25 G,J,L 01
CYLINDER ASSY-LH
TRUNNION AND
- 4 6641000-6 . . B,D 01
CYLINDER ASSY-RH
TRUNNION AND
- . . CYLINDER ASSY-RH
4A 6641000-18 F NP
FSO 6641000-26
REFER TO NOTE 2

- . . TRUNNION AND
4B 6641000-26 H,K,M 01
CYLINDER ASSY-RH
5 NAS464P9A75 . . . BOLT 02
6 AN960-916L . . . WASHER-UPPER 02

Copyright © Textron Aviation Inc. Page 1 of 7

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Model 500 Series Component Maintenance Manual (Rev 17)
32-10-01-1001 (Rev 14)

WASHER
- 6A NAS1149F0932P . . . ALTERNATE FOR 02
AN960-916L
7 AN960-916 . . . WASHER-LOWER 04
WASHER
- 7A NAS1149F0963P . . . ALTERNATE FOR 04
AN960-916
8 MS21083N9 . . . NUT 04
9 6641201-2 . . . BOLT-MLG 02
10 6641202-1 . . . WASHER-UPPER 02
CYLINDER-OUTER
11 6641320-1 . . . A,C NP
LH FSO 6641320-3
- . . . CYLINDER-OUTER
11A 6641320-3 E,G,J,L 01
LH
- . . . CYLINDER-OUTER
12 6641320-2 B,D NP
RH FSO 6641320-4

- . . . CYLINDER-OUTER
12A 6641320-4 F,H,K,M 01
RH
13 6541300-3 . . . DRAG BRACE 01
14 NAS464P10A18 . . . BOLT-LOWER 01
15 AN960-1016L . . . WASHER-LOWER 02
WASHER
- 15A NAS1149F1032P . . . ALTERNATE FOR 02
AN960-1016L
16 MS21083N10 . . . NUT-LOWER 01
17 NAS464P7A28 . . . BOLT-UPPER 01
18 AN960-716L . . . WASHER-UPPER 02
WASHER
- 18A NAS1149F0732P . . . ALTERNATE FOR 02
AN960-716L
19 NAS1291-7 . . . NUT-UPPER 01
TRUNNION ASSY
20 6641306-1 . . . FSO 6641306-5 A,B,C,D,E,F NP
REFER TO NOTE 3
- 20A 6641306-5 . . . TRUNNION ASSY G,H,J,K,L,M 01
BUSHING FSO
21 6641306-4 . . . . 6641000-201 A,B,C,D,E,F NP
REF TO NOTE 4
- 21A 6641306-7 . . . . BUSHING G,H,J,K,L,M 01
BUSHING FSO
22 6641306-3 . . . . 6641000-202 A,B,C,D,E,F NP
REF TO NOTE 4
- 22A 6641306-6 . . . . BUSHING G,H,J,K,L,M 01
VALVE ASSEMBLY-
23 AN6287-1 . . 01
AIR CHARGE
24 NAS1611-015 . . O-RING 01

Copyright © Textron Aviation Inc. Page 2 of 7

25 MS24391-8L . . PLUG 01
26 NAS1612-8 . . O-RING 01
. . PLATE-
27 6640001-4 01
IDENTIFICATION
WHEN INITIALLY REPLACING 6541001-3 OR 6541001-4 WITH 6541001-21 OR 6541001-22
NOTE 1:
ALSO ORDER 1 EACH 5541205-7 & 5541205-8 PINS.
WHEN INITIALLY REPLACING 6641000-17 OR 6641000-18 WITH 6541000-25 OR 6641000-26
NOTE 2:
ALSO ORDER 1 EACH 5541205-7 & 5541205-8 PINS.
WHEN INITIALLY REPLACING 6641306-1 WITH 6641306-5 ALSO ORDER ORDER ONE EACH
NOTE 3:
5541205-7 & 5541205-8 PINS.
6641000-201 & -202 CONSIST OF NEW 6641306-7 & -6 BUSHINGS & 5541205-7 & -8 TRUNNION
NOTE 4:
PINS RESPECTIVELY.
NOMENCLATURE EFFECTIVITY UNITS
PER
ITEM PART NUMBER 1 2 3 4 5 6 7 FROM TO ASSY
- MAIN LANDING GEAR ASSEMBLY
PISTON AND AXLE
75 6641000-23 . . ASSY-LH FSO A,C NP
6641000-33
PISTON AND AXLE
- 75A 6641000-33 . . A,C 01
ASSY-LH
PISTON AND AXLE
- 76 6541001-5 . . ASSY-LH FSO E,G,J NP
6641001-19
- . . PISTON AND AXLE
76A 6541001-19 L 01
ASSY-LH
PISTON AND AXLE
- 77 6641000-24 . . ASSY-RH FSO B,D NP
6641000-34
- . . PISTON AND AXLE
77A 6641000-34 B,D 01
ASSY-RH
PISTON AND AXLE
- 78 6541001-6 . . ASSY-RH FSO F,H,K NP
6641001-20
PISTON AND AXLE
- 78A 6541001-20 . . M 01
ASSY-RH
. . . PISTON-LH FSO
79 6641330-1 A,C,E,G,J,L NP R
6641330-201
- 79A 6641330-201 . . . PISTON-LH A,C,E,G,J,L 01 R
- . . . PISTON-RH FSO
80 6641330-2 B,D,F,H,K,M NP R
6641330-202
- 80A 6641330-202 . . . PISTON-RH B,D,F,H,K,M 01 R
. . . AXLE FSO
81 6641200-5 E,F,G,H,J,K NP
6641200-7
- 81A 6641200-7 . . . AXLE L,M 01

Copyright © Textron Aviation Inc. Page 3 of 7

- . . . AXLE FSO
82 6641200-4 A,B NP R
6641200-200
- . . . AXLE FSO
82A 6641200-6 C,D NP R
6641200-200
- 82B 6641200-200 . . . AXLE A,B,C,D 01 R
83 NAS561P8-8 . . . PIN 01
EXPANSION
84 5514350-22 . . . 01
PLUG
- . . GROMMET-FEED
84A 205A112-3/42 01
THRU
85 MS28776M2-27 . . SCRAPER 01
86 5541210-2 . . RETAINER 01
87 CM2690C21 . . RETAINER 01
. . T-SEAL FSO S2800-
88 601RS335-04183 NP
507
DELTAMOD ROD
- 88A S2800-507 . . SEAL REF RD51-336- 01
E3P-261-C
89 NAS1611-337 . . O-RING 01
90 MS28774-337 . . RING-BACKUP 01
. . BEARING ASSY-
91 5541309-7 01
LOWER
92 5541208-1 . . SPACER 01
93 6641307-2 . . PISTON-ISOLATION 01
94 NAS1611-326 . . O-RING 01
95 5541206-3 . . POPPET-ORIFICE 01
96 321C8 . . RETAINER 01
97 6641310-3 . . BEARING-UPPER 01
98 NAS1081-3B6 . . SET SCREW 02
SCREW-SET
- 98A NAS1081C3B6 . . ALTERNATE FOR 02
NAS1081-3B6
. . TORQUE LINK ASSY
99 6641304-1 01
UPR
. . TORQUE LINK ASSY
100 6641304-2 01
LWR
101 M81934/2-14C016 . . . BEARING 04
102 M81934/1-10C024 . . . BEARING 02
103 6541212-3 . . SHAFT-TORQUE LINK 02
104 MS16562-66 . . PIN 02
105 5541220-2 . . BOLT SHOULDER 01
106 5541216-2 . . WASHER 01
107 MS17825-8 . . NUT 01
108 MS24665-287 . . COTTER PIN 01

Copyright © Textron Aviation Inc. Page 4 of 7

WASHER-TOE ANGLE
109 AN960-1016L . . AR
ADJUST
WASHER
- 109A NAS1149F1032P . . ALTERNATE FOR AR
AN960-1016L
. . WASHER-TOE ANGLE
110 AN960-1016 AR
ADJUST
WASHER
- 110A NAS1149F1063P . . ALTERNATE FOR AR
AN960-1016
. . WASHER-TOE ANGLE
111 AN960C1016L AR
ADJUST
WASHER
- 111A NAS1149C1032R . . ALTERNATE FOR AR
AN960C1016L
- Item Not Illustrated

Copyright © Textron Aviation Inc. Page 5 of 7

Figure 1001 : Sheet 1 : MAIN LANDING GEAR ASSEMBLY

Copyright © Textron Aviation Inc. Page 6 of 7

Figure 1001 : Sheet 2 : MAIN LANDING GEAR ASSEMBLY

Copyright © Textron Aviation Inc. Page 7 of 7

MAIN GEAR ASSEMBLY - ILLUSTRATED PARTS LIST

1. Illustrated Parts List
A. Introduction.
(1) The Illustrated Parts List will help the customer to order, keep, and supply the main landing gear components. It will
also identify new and reclaimed parts. It is not approved for any other purpose.
(2) The main gear assembly part numbers that follow are covered in this parts list:
6641000-15 6641000-16 6641000-27 6641000-28 6641000-35
6641000-36 6641000-37 6641000-38 6641000-39 6641000-40
6641000-41 6641000-42
(3) The indention system used in the detailed parts list of this catalog shows the relationship of one part to another. For a
given item, the indention code shows a general heading at the extreme left position and continues with indented
columns until the end detail is reached as follows:
A18017
1234567
Installation
Detail Parts for Installation
Assembly
Attaching Parts for Assembly
Detail Parts for Assembly
Subassembly
Attaching Parts for Subassembly
Detail Parts for Subassembly
Sub−Subassembly
Attaching Parts for Sub−Subassembly
Detail Parts for Sub−Subassembly

Basic Number Dash Number

(Drawing Identification
Only)

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Model 500 Series Component Maintenance Manual (Rev 17)
32-10-02-0 (Rev 14)

MAIN GEAR ASSEMBLY - DESCRIPTION AND OPERATION

1. Description
A. The main gear assembly is designed and assembled to permit maneuverability of the airplane on the ground and to retract
into the wing when airborne. It is designed to absorb shock during airplane takeoffs, landings and taxiing. The main gear
assembly consists of a trunnion, shock strut, axle and torque links. Refer to Figure 1 and Figure 2.
(1) The trunnion is connected to the shock strut and is mounted in the wing wheel well with trunnion pins to allow the gear
assembly to retract into the wing.
(2) The shock strut consists of a cylinder assembly, a piston assembly and an isolation piston which floats within the
piston assembly. The chamber above the isolation piston is filled with hydraulic fluid. The chamber below the isolation
piston is charged with dry air or nitrogen. O-ring packings are used on the isolation piston to prevent leakage of
air/nitrogen or hydraulic fluid around the isolation piston.
(3) The axle is connected to the bottom of the strut piston; press fitted and secured with a pin.
(4) Torque links enable adjustment of the gear toe-in and toe-out. The upper torque link is connected at the shock strut
cylinder and the lower torque link connected to the shock strut piston. The upper and lower torque links are connected
together to permit piston vertical movement in the cylinder and prevent piston rotation in the cylinder.
(5) The main gear assembly part numbers affected by this Section are:
6641000-15 6641000-16 6641000-27 6641000-28 6641000-35
6641000-36 6641000-37 6641000-38 6641000-39 6641000-40
6641000-41 6641000-42
2. Operation
A. As weight of the airplane is applied to the main gear assembly, the piston assembly is forced to slide into the cylinder
assembly. This movement forces hydraulic fluid to flow from the cylinder chamber through an opening in the top of the
piston past a metering pin of variable diameter into the piston chamber against the isolation piston. The metering pin
restricts the fluid flow between sections of the cylinder to different rates at specific gear extensions. The restricted fluid flow
and the resistance of the compressed air/nitrogen below the isolation piston dampens the movement of the piston
assembly and absorbs compression shocks. As the weight of the airplane is removed from the main gear assembly, the
compressed air/nitrogen forces the isolation piston toward the top of the piston chamber. The hydraulic fluid is forced into
the cylinder chamber and the piston assembly extends. Refer to Figure 3.
3. Personnel Safety Precautions - Hydraulic Fluid
A. The main gear assembly contains phosphate ester base hydraulic fluid. Before performing maintenance or any operation
on the main gear shock strut assembly, personnel should read and thoroughly understand the following.
WARNING: Observe the following safety precautions when working on systems containing phosphate ester
base fluid. Prolonged exposure to the fluid can cause skin dehydration and chapping.
(1) Wash hands thoroughly with soap and water before starting work; apply barrier cream (silicone hand cream) to
hands, wrists and forearms. Rub cream under fingernails and into creases of skin.
(2) Wear eye goggles when pressure testing components or systems or anytime there is a possibility of hydraulic fluid
spraying/splashing in the eyes.
(3) If hydraulic fluid enters the eyes, treat eyes immediately by irrigating thoroughly with clear, cold water.
(4) Wash hands, wrists and forearms with soap and warm water after contacting hydraulic fluid.
(5) If clothing becomes soaked with hydraulic fluid, remove the clothing as soon as possible. Wash hydraulic fluid
exposed skin with soap and warm water. Wash hydraulic fluid contaminated clothes before wearing.
4. Technical Safety Precautions - Hydraulic Fluid
A. Because the main gear strut contains phosphate ester base hydraulic fluid, improper maintenance practices can be
damaging to gear components and other equipment. Before performing maintenance or any operation on the main gear
shock strut assembly, personnel should read and thoroughly understand the following technical precautions.
CAUTION: Phosphate ester base hydraulic fluid will damage and/or deteriorate a wide range of materials,
including rubber, copper, various plastics and paints.
(1) Make sure that hydraulic fluid does not come in contact with any part of the component outside of the main gear

Copyright © Textron Aviation Inc. Page 1 of 5

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Model 500 Series Component Maintenance Manual (Rev 17)
32-10-02-0 (Rev 14)

shock strut. Keep spillage to an absolute minimum. Clean up spilled hydraulic fluid immediately to prevent
contamination of non- hydraulic components and to avoid false hydraulic leak detections. If spillage occurs, wipe up
the fluid with a dry cloth and wash area with naphtha MIL-PRF-680, (Type III).
(2) When gear components are disassembled, provide suitable protection for preventing entry of foreign material by
using caps and/or covers.
(3) Always check angle and position of components prior to disassembly to ensure proper alignment and placement of
components and hardware during assembly or replacement.
(4) Use naphtha MIL-PRF-680 (Type III) or Methyl n- Propyl Ketone, when washing metal parts prior to assembly. Make
sure all traces of the cleaning agent are removed before assembly.
(5) Use only clean hydraulic fluid for flushing or testing hydraulic components.
(6) Do not unpack seals, O-rings/packings until they are required and ensure that only correct and approved seals, O-
rings/packings are used.
CAUTION: Take special care not to contaminate seals, o-rings/ packings after lubrication.
CAUTION: Prevent contamination of phosphate ester base hydraulic fluid with other hydraulic fluids, oil, water
or dirT.
(7) When assembling the gear shock strut hydraulic seals and O-rings/ packings, lubricate only with phosphate ester
base hydraulic fluid. Always lubricate seals, O- rings/packings immediately before installation. Threaded fittings
should be assembled without the use of lubricants whenever possible. If a lubricant is required to prevent galling or to
otherwise ease installation, use phosphate ester base hydraulic fluid or VV-P-236 Petrolatum.

Copyright © Textron Aviation Inc. Page 2 of 5

Figure 1 : Sheet 1 : Main Gear Assembly

A83873

Trunnion

Strut Drag Brace

Torque Links

Axle

5641T1064

Copyright © Textron Aviation Inc. Page 3 of 5

Figure 2 : Sheet 1 : Main Gear Strut Assembly

Copyright © Textron Aviation Inc. Page 4 of 5

Figure 3 : Sheet 1 : Main Gear Strut Assembly Operation

Copyright © Textron Aviation Inc. Page 5 of 5

MAIN GEAR ASSEMBLY - TESTING

1. Testing
A. Service Main Gear Strut for Test.
WARNING: Do not stand in front of valve assembly while releasing air/nitrogen pressure. Do not turn 0.75 inch
hex nut while releasing air/nitrogen pressure. Removing air filler valve without releasing
air/nitrogen pressure first can cause bodily injury.
(1) Position and maintain strut in an upright position to expel any fluid collected in the air chamber.
(a) Entry of fluid in the air chamber occurs as the oil film seeps by the seal during strut operation. A nominal amount
of oil seepage on a strut is approximately one drop per 100 hours of operation; however, some struts may have
more or less seepage and still be serviceable.
(b) Fluid accumulation in the strut air chamber with little or no piston movement requires additional inspection and
maintenance to correct oil from leaking into the air chamber.
(2) Rotate outer 0.625 inch hex nut on the air filler valve (AN6287-1) counterclockwise to lift internal valve poppet. Then
attach a valve core depressor or remove valve core to release any trapped air/nitrogen and/or fluid.
(3) Remove plug (MS24391-4L) from the top of the strut and replace with a union (MS24392-4) and gasket (NAS1612-
4).
NOTE: Plug is installed in head of metering pin. Do not remove metering pin.
(4) Attach hose from a hand pump containing clean hydraulic fluid (Skydrol 500B or equivalent), and operate pump until
the strut is partially extended, but not to the stop limit.
CAUTION: Do not exceed 300 PSIG applied pressure.
(5) Open pump check valve and force strut to the collapsed position as trapped air expels into hand pump reservoir.
(6) Repeat pump cycling of strut until no air/nitrogen is being discharged from the fluid chamber.
(7) Discontinue pump cycling of the strut with the strut in the collapsed position. Remove hose, fitting (union) and gasket.
(8) Keep full of fluid and do not disturb strut from the collapsed position until plug and new gasket has been installed in
the head of the metering pin and tightened. The fluid chamber is to be entirely free of air/nitrogen. Safety wire plug to
trunnion attach nut using the double-twist method of installing safety wire.
NOTE: Strut assembly to be charged/serviced with nitrogen only.
WARNING: Servicing the strut with air before strut is properly serviced with hydraulic fluid could result in
blowing strut apart causing damage to equipment and/or injury to personnel.
(9) Install nitrogen filler valve core (if previously removed). Connect nitrogen source with pressure gage and charge strut
by turning 0.625 inch hex nut a maximum of 1-1/2 turns counterclockwise. Charge strut with nitrogen as follows:
(a) Charge strut to 370 PSIG with strut fully extended. Bleed pressure down to 310 PSIG.
(10) Tighten 0.625 inch hex nut 50 to 70 inch- pounds.
B. Test.
(1) After accomplishing Testing, paragraph A., above, leave strut assembly charged for a one hour period. No fluid
leakage or loss of nitrogen pressure as indicated on the pressure gage is permissible.
WARNING: Do not stand in front of filler valve assembly when releasing nitrogen pressure. Do not turn 0.75
inch hex nut while releasing pressure. Removing nitrogen filler valve without releasing nitrogen
pressure first can cause bodily injury.
(2) Release all nitrogen from the strut through the filler valve. If fluid is noted coming through the filler valve, consult
troubleshooting procedure.
2. Troubleshooting
A. The main gear assembly may be tested as outlined in Testing. above for determining fluid or nitrogen leakage. Testing
results, visual checking and/or a review of information received with the gear assembly may be utilized in conjunction with
the following while troubleshooting.
B. Troubleshooting.
TROUBLE PROBABLY CAUSE REMEDY

Copyright © Textron Aviation Inc. Page 1 of 2

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 13:10:06 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
32-10-02-1 (Rev 5)

OIL LEAK AROUND Damaged packings or seals on lower Replace packings and seals.
PISTON bearing
Damaged scraper Replace scraper.
Cracked bearing Replace bearing.
Piston cut or nicked Polish out cut or nick.
Flat spot on piston Replace piston.
STRUT DOES NOT Damaged or worn packings isolation Replace packings. Free isolation piston and check
EXTEND WHEN piston Stuck isolation piston damage.
WEIGHT REMOVED
AND/OR OIL
PRESENT WHEN
NITROGEN VALVE
OPENED
Isolation piston damaged Replace isolation piston.
Low nitrogen pressure Check for leaky nitrogen valve and replace if leaking,
then recharge strut.
Piston wall damaged. Hone piston inside diameter or replace piston.

Copyright © Textron Aviation Inc. Page 2 of 2

MAIN GEAR ASSEMBLY - DISASSEMBLY

1. Disassembly
NOTE: Review Safety Precautions in Introduction before beginning disassembly.
A. Preparation for Disassembly (Refer to Illustrated Parts List).
(1) Rotate 0.625 inch (15.875 mm) hex nut on air valve (23) counterclockwise one and one-half turns to lift internal valve
poppet, then release any trapped gas or liquid by depressing valve core.
WARNING: Do not stand in front of valve assembly while releasing gas pressure. Do not turn 0.75 inch (19.05
mm) hex nut while releasing gas pressure. Removing air valve without releasing compressed gas
can cause bodily injury.
(2) Ensure that gas is released by sliding piston in and out of cylinder.
(3) Cut lockwire and remove air valve (23) and packing (24) from piston assembly.
(4) Remove plug (25) and packing (26) from metering pin (27).
(5) Remove metering pin (27) and packing (28) from top of cylinder assembly (11). If metering pin is to be replaced,
remove plug (25) from end of metering pin.
(6) Drain hydraulic fluid by inverting strut assembly.
B. Torque Link Removal (Refer to Illustrated Parts List).
(1) Remove squat switch and attaching hardware.
(2) Remove upper and lower torque link shaft attach pins (99).
(3) Remove upper and lower torque link shafts (98). Note shaft positions for reassembly.
(4) Remove torque links (94 and 95) from strut assembly before further disassembly.
(5) Remove cotter pin (103), nut (102), washer (101), spacing washers (104, 105 and 106) and bolt (100).
NOTE: Avoid changing toe-in adjustment. Note location of spacing washers and of each torque link
attaching part for reassembly.
(6) Remove bearings (96 and 97) from torque links.
C. Piston Removal (Refer to Illustrated Parts List).
(1) Push bearing (88) and retainer (82) into cylinder enough to free retainer (84). Remove retainer (84) from cylinder.
(2) Remove piston assembly from cylinder.
D. Piston Disassembly (Refer to Illustrated Parts List).
(1) Remove two setscrews (93) so that bearing (92) can be unscrewed.
NOTE: Bearing (92) is installed using Loctite 242 or Loctite 243 adhesive. To loosen bond, it may be
necessary to apply heat not exceeding 180°F (82.22°C) to joint to soften the adhesive bond.
(2) Unscrew and remove bearing (92) from top of piston assembly.
(3) Remove spacer (89) from barrel of piston assembly.
(4) Slide bearing (88), scraper (82), and scraper retainer (83) from piston assembly barrel.
(5) Remove O-ring (86) and back-up ring (87) from outer surface of bearing (88).
(6) Remove "T" seal (85) from inner channel of bearing (88).
(7) Extract isolation piston (90) from piston assembly barrel.
(8) Remove O-ring (91) from isolation piston (90).
E. Remove Drag Brace (Refer to Illustrated Parts List).
(1) Remove nut (16), washers (15) and bolt (14).
(2) Remove nut (19), washers (18) and bolt (17); then, remove drag brace (13).
F. Trunnion and Cylinder Disassembly (Refer to Illustrated Parts List).
NOTE: The trunnion and cylinder need not be disassembled if they have previously been assembled
using a sealant to prevent corrosion.
(1) Remove two aft bolts (9), washers and nuts.
(2) Remove two forward bolts (5), washers and nuts.

Copyright © Textron Aviation Inc. Page 1 of 2

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 13:10:07 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
32-10-02-3 (Rev 14)

(3) Remove cylinder from trunnion.

NOTE: The cylinder and trunnion are press-fitted together.
G. Axle Removal (Refer to Illustrated Parts List).
NOTE: Do not remove axle unless inspection reveals that replacement is necessary. If axle is cracked or
damaged, inspect piston (77) before removing axle.
(1) Remove the safety wire and drive out the pin (80) securing the axle to the piston. Discard the pin.
(2) Using an arbor press, support the piston on a wooden block centered over a 2.25 inch (57.15 mm) diameter hole in
the block. Press out the axle using care to prevent damage to the piston.
(3) Remove expansion plug (81) from axle (79).

Copyright © Textron Aviation Inc. Page 2 of 2

MAIN GEAR ASSEMBLY - CLEANING

1. Cleaning
A. Tools and Equipment.
NOTE: Equivalent substitutes may be used for the listed items:
NAME NUMBER MANUFACTURER USE
Methyl n-Propyl Ketone Clean metal parts.
Solvent Blend Desoclean 110 PRC-DeSoto International Clean metal parts.
5426 San Fernando Rd.
Glendale, CA 91209
Paint Stripper T-6776 LO Turco Products, Inc. Strip paint from metal parts
Westminster 92684 prior to inspection.
CA
Naptha MIL-PRF-680 (Type Commercially Available Metal parts cleaning that
III) require soak cleaning.
Protective Oil Oakite Special Oakite Products Inc. Protect metal surfaces that
Protective Oil 50 Valley Road have had paint removed.
Berkeley Heights, NJ 07922
Hydraulic Assembly MCS 352 Aviation Fluids Service Co. Protect surfaces normally in
Lubricant St. Louis, MO 63166 contact with hydraulic fluid.
B. Cleaning.
WARNING: Use cleaning solvents only in well ventilated areas. Avoid inhaling solvent vapors. Keep solvent
and solvent containers away from spark or open flame.
(1) Clean metal parts and phenolic bearings with approved solvent. Remove stubborn deposits by hand rubbing with
nonabrasive pads or material. Apply solvent under pressure to all lubrication fittings, channels and other internal
cavities to ensure cleanness. Thoroughly dry all parts with filtered, dry, compressed air and a lint-free cloth or lint-free
disposable tissue.
(2) Labels or identification plates which are attached by adhesive shall be removed by lifting the corner and pulling free.
Remove adhesive with clean cloth dipped in cleaning solvent.
CAUTION: Do not allow paint stripper to contact high heat treated steel pins such as pins attaching landing
gear components. Paint strippers may induce hydrogen embrittlement in high heat treated steel.
(3) Before stripping paint, thoroughly mask off or remove high heat treated steel pins such as pins attaching landing gear
components.
WARNING: All paint strippers are harmful to eyes and skin. Operators shall wear goggle-type glasses, rubber
gloves, aprons and boots. In case of contact with skin, flush with water. In case of contact with
eyes, flush eyes thoroughly with water and consult a physician immediately. Paint stripping shall
be done in a well ventilated area. Follow manufacturer's instructions carefully to release pressure
before opening paint stripper storage containers.
(4) Apply paint stripper on painted parts following the recommended manufacturer’s instructions. Allow the first
application to work from 5 to 45 minutes or as advised by manufacturer's instructions. If necessary, scrub softened
areas with brush to loosen paint. Rinse with water. Repeat as necessary to remove all paint. After paint is completely
removed, rinse part thoroughly with water spray. Dry part with filtered, dry, compressed air and a lint-free cloth or lint-
free disposable tissue.
(5) After drying, coat all parts, that would normally come in contact with hydraulic fluid during operation, with clean
hydraulic fluid or hydraulic assembly lubricant. External metal surfaces or other parts not coming in contact with
hydraulic fluid during operation of the strut need not be coated. However, highly machined surfaces may be coated
with hydraulic fluid or other suitable protective coating.
(6) If checking and repair procedures do not immediately follow cleaning, coat all surfaces that have had paint removed
with a suitable protective oil.

Copyright © Textron Aviation Inc. Page 1 of 1

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 13:10:08 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
32-10-02-5 (Rev 12)

MAIN GEAR ASSEMBLY - CHECK

1. Check
A. Tools and Equipment.
NAME NUMBER MANUFACTURER USE
Cupric Sulfate Commercially Available Chrome surface check.
Sulfuric Acid Concentrated (18N) Commercially Available Chrome surface check.
B. Recommended Checking Methods.
(1) Consult Table 501 to determine the recommended method of checking each component.
(2) Check all parts visually under strong light for surface cracks, flaws, burrs, pitting, scoring or any other wear.
(3) Replace all parts showing cracks or flaws under dye penetrant, magnetic particle or visual inspection.
(4) Check all friction surfaces and machined holes for wear beyond tolerances given in Main Gear Assembly - Fits and
Clearances.
(5) Check all bolts, nuts and screw threads, both external and internal, for evidence of stripping or scoring. Replace all
parts that have stripped threads.
(6) Check shafts and pins for ovaling, or other signs of wear.
C. Checking Chrome Plating.
CAUTION: When mixing solutions, always add acid to water; never add water to acid.
(1) Check the chrome surfaces of the shock strut assembly for scratches, scores, blisters, and nicks. All suspected
defects should be tested to determine if the base metal has been exposed. To test, apply liberally to the suspected
areas a copper sulfate solution consisting of 100 grams cupric sulfate, five (5) milliliters sulfuric acid and one (1) liter
of water. Wipe off excess liquid and inspect, using a strong light and a magnifying lens. If the chrome plating has been
penetrated, a copper coating will adhere to the ferrous metal. Clean the area thoroughly using approved solvent. If the
chrome plating has been penetrated in the sealing area, the part shall not be returned to airplane use. If the chrome
plating on the piston below the sealing surface is penetrated but no damage to the steel is detectable, then the
chrome damage may be repaired by cleaning and applying MIL-PRF-23377 corrosion resistant primer. After this
repair is complete the piston may be returned to service. Defects that have not penetrated the chrome plating should
be polished to remove sharp edges that could damage seals. A honing stone or crocus cloth may be used for this
purpose.
D. Recommended inspection is contained in Table 501 (Refer to Illustrated Parts List).
Table 501. Recommended Inspection
Nomenclature Item Method of Check For Requirement
Number Same as Checking
Illustrated Parts List
Number
Cylinder (11) Visual Wear, damage No damage or wear that would endanger
structure or interfere with function.
Magnetic particle Cracks No cracks.
Air valve (23) Visual Damage, stripped threads No damage or stripped threads.
Plug (25) Visual Stripped threads No stripped threads.
Piston (77, 78) Visual Wear, damage inner diameter No wear or damage that would prevent
finish function.
Magnetic particle Cracks No cracks.
Ultrasonic Cracks No voids or cracks in brazed joints.
Retainers (83, and 84) Visual Wear, damage No wear or damage that would prevent
function.

Copyright © Textron Aviation Inc. Page 1 of 2

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 13:10:09 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
32-10-02-5 (Rev 12)

Bearings (88) and (92) Visual Wear, damage No obvious wear or damage.
Isolation piston (90) Visual Wear, damage No wear or damage that would prevent
(NOTE) function or sealing capability.
Dye penetrant Cracks No cracks.
Shafts (9B) Visual Ovaling or other damage Must meet dimensions given in Fits and
Clearances.
Magnetic particle Cracks No cracks.
Upper and lower torque Visual Out of round bearing holes, Holes must meet tolerances given in Fits
links (94 and 95) wear or other damage to and Clearances. No wear or other
bearing or teflon lining. damage that would endanger structure or
prevent function.
Dye penetrant Cracks No cracks.
Spacer (89) Visual Damage or wear No obvious wear or damage.
Axle (79) Visual Stripped threads, damage No damage.
Magnetic particle Cracks No cracks.
NOTE 1: The isolation piston has a teflon-impregnated hard coat anodized finish and should show little or
no wear.

Copyright © Textron Aviation Inc. Page 2 of 2

MAIN GEAR ASSEMBLY - REPAIR

1. Repair
NOTE: It is recommended that superseded parts be replaced in lieu of repair.
A. Refer to Chapter 20, CONVERSION DATA - Description and Operation, for information on how to convert the United
States (empirical system) to the International System of Units (metric system).
B. Tools and Equipment.
NOTE: Equivalent substitutes may be used for the listed items.
NAME NUMBER MANUFACTURER USE
Wet or dry sandpaper 400 Commercially Available Remove corrosion from gear
strut.
Emery Cloth 320 grit 400 grit Commercially Available Remove corrosion and final
finishing of axle and piston axle
adaptor.
Loctite 7649 Primer N U467019 Loctite Corp. To prime the bearing threads.
705 N. Mountain Road
Nineteen, CT 06111
Locktite 242 Loctite Corporation For the fasteners thread lock.
705 N. Mountain Road
Newington, CT 06111
Loctite 243 Loctite Corporation For the fasteners thread lock.
705 N. Mountain Road
Newington, CT 06111
Fuel and Corrosion 10-P1-4 Base 10- Dexter Crown Metro Corrosion protection primer for
Resistant Primer P1-4 Catalyst EC- One East Water st. integral fuel tanks
108 Thinner TR-19 Waukegan, IL 60085
Waterborne Corrosion U-4800/U-4801 Sterling Lacquer Manufacturing Co. Corrosion protection primer
Resistant Primer MIL- 3150 Brannon St.
P-85582 St. Louis, MO 63139
Waterborne Corrosion W9100- U.S. Paint Corp. Corrosion protection primer
Resistant Primer MIL- K11/W3100 831 South 21st St.
P-85582 St. Louis, MO 63130
Waterborne Corrosion 10-PW20-4 Dexter Crown Metro Corrosion protection primer
Resistant Primer MIL-
P-85582
Waterborne Corrosion 44-GN-60 /44-GN- Deft, Inc. Corrosion protection primer.
Resistant Primer 60 CATA 17151 Von Karman Ave.
Irvine, CA 92714
Corrosion Resistant 02-Y-40 02-4-40 DEFT, Inc. Corrosion protection primer.
Primer MIL-PRF- CATA
23377G or later
Corrosion Resistant U-1201F/ U-1202F Sterling Lacquer Mfg. Corrosion protection primer.
Primer MIL-PRF-
23377G or later
Corrosion Resistant R4001-K14MAX U.S. Paint Corp. Corrosion protection primer.
Primer MIL-PRF- COR
23377G or later

Copyright © Textron Aviation Inc. Page 1 of 12

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 13:10:11 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
32-10-02-6 (Rev 14)

Polyurethane paint, 7400 (Color Name: U.S. Paint Corp. Finish paint.
medium gray Pewter)
Adhesive RTV-154 General Electric Co. Bond filling instructions placard
Silicone Products Dept. to strut.
Waterford, NY 12188
Clear enamel AA92-C-21C U.S. Paint Corp. Cover filling instructions
placard.
Catalyst AA92-C-22B U.S. Paint Corp. Cover filling instructions
placard.
Flexible drive Shaft Commercially Available To hone piston assembly inner
with 1/4 inch chuck barrel.
Hone CF63 or CF68 Snap-On Tools To hone piston assembly inner
3150 Terrace barrel.
Kansas City, MO 64111
Honing oil Sun Concentrate Sun Oil Company To oil stones while honing.
1501 P.O. Box 2039
Tulsa, OK 4102
Hydraulic assembly MCS 352 Aviation Fluids Service Co. To lubricate piston assembly
lubricant St. Louis, MO 63166 inner barrel.
Stones - 2 2-inch fine JT63-24 Snap-On Tools Used with CF63 or CF68
(400 grit) hones to hone piston assembly
inner barrel.
C. Replacement of Damaged Parts.
(1) Replace all parts that show visual wear, cracks or flaws.
(2) Replace all parts that show cracks under visual or dye penetrant inspection.
(3) Replace all parts indicating cracks or flaws under ultrasonic, X-ray, or magnetic particle inspection.
(4) Replace all parts that have machined holes that are worn beyond tolerance limits.
D. Chrome Surface Repair.
CAUTION: When buffing or polishing out scratches on chrome surfaces, extreme caution must be taken not
to penetrate the chrome plating or create low spots by too much localized buffing or polishing.
(1) Scratches or nicks that have not penetrated the chrome plating of the piston and axle assembly or the upper cylinder
assembly may be honed and polished to remove sharp edges that could damage the seals. A honing stone or crocus
cloth may be used for this purpose. In the areas not subject to seal travel, scratches, pits and scoring that do not
penetrate the chrome plating are relatively unimportant. The sharp edges of the nicks should be removed by honing
and polishing. The presence of defects in this area, if properly repaired, are considered acceptable.
E. Piston Assembly (77 and/or 78) Inner Diameter Finish Rework.
NOTE: The inner barrel of the piston assembly is phosphate coated. This coating may be rough, causing
premature wear to the seals causing fluid to leak into the air chamber. The following procedure
provides a method for removing this coating.
NOTE: This procedure is not intended to be performed after each overhaul. Perform this procedure only
once.
(1) Using a micrometer, check inside diameter of piston assembly to ensure it is within tolerance.
(2) Check inside of piston assembly for pitting. If pitted, replace the piston assembly.
(3) Hone the inside diameter of the piston assembly to remove a minimal amount of phosphate coating and to achieve a
smooth finish.
(a) Remove air charge valve assembly (23) and packing (24).
(b) Assemble hone, stones, flexible shaft with chuck and a variable speed drill.

Copyright © Textron Aviation Inc. Page 2 of 12

NOTE: Install a piece of plastic, rubber hose or other suitable material over the chuck on flexible
shaft to prevent chuck from striking piston bore during honing.
(c) Adjust the hone and install into the end of piston assembly; expand hone assembly until stones are resting
against inner diameter of piston assembly. Apply honing oil as required.
CAUTION: Do not allow stones to get dry during honing; use honing oil freely while operating hone.
Allowing stones to get dry will result in scratching the inner diameter finish of the piston
assembly.
(d) Hone the piston assembly at a maximum speed of 600 RPM, one continuous stroke the length of bore and out,
keeping the hone moving through piston at all times until phosphate is removed.
(e) Thoroughly clean piston assembly after honing. Refer to Main Gear Assembly - Cleaning, for material.
(f) Using a micrometer, check inside diameter of piston assembly to ensure honing did not exceed the 2.253 inch
diameter.
(g) Install air charge valve assembly (23) and new packing (24).
(4) If piston assembly is not being reassembled, coat inside diameter with hydraulic assembly lubricant MCS 352.
F. Painting.
(1) Preliminary.
(a) Verify areas to be painted are free of dirt, oil, grease and/or corrosion.
(b) Do not paint tires, strut air valves, data plates, bearings, polished pistons, switches, wire bundles, clamps,
hydraulic hoses, wheels, axle spindle area within the wheels or contacting areas of the lower to upper torque
links.
(c) Retreat and paint removed wheels in accordance with Goodyear Wheel and Brake Components Maintenance
Manual.
(2) Pretreatment Primer.
(a) Apply Loctite 7649 Primer N (material code U467019) to the bearing threads, then apply Loctite 242 or 243 and
assemble.
(3) Corrosion Resistant Primer
(a) Mix and apply MIL-PRF-23377 corrosion resistant primer in accordance with manufacturer's instructions.
(4) Top Coat.
(a) Mix and apply top coat in accordance with manufacturer’s instructions.
G. Install Service Placard.
(1) Bond Filling Instruction Placard to upper cylinder with RTV-154 adhesive. Prepare and apply adhesive in accordance
with manufacturers instructions.
(2) Apply two coats of clear polyurethane over the placard after installation. Prepare and apply polyurethane top coat in
accordance with manufacturers instructions.
H. Outer Cylinder Lower Bearing Area Corrosion Inspection, Removal, Modification and Prevention.
(1) Inspection of the outer cylinder lower bearing area.
(a) Inspect the outer cylinder lower bearing area as shown for damage to the finished surface due to corrosion
(Refer to Figure 601). If the finished surface is not damaged and no corrosion exists, proceed to step (3). If
corrosion is present on the outer cylinder lower bearing surface area, proceed to step (2).
(2) Preliminary rework of outer cylinder lower bearing surface area.
(a) Determine if the outer cylinder lower bearing surface area can be reworked (Refer to Figure 601):
1 Verify that no corrosion exists on the uppermost 0.5 inch (12.7 mm) of the bearing surface. If corrosion is
found in this area, contact Citation Customer Service Department for disposition.
2 Using a stainless steel wire brush or glass bead peening, remove the corrosion from the outer cylinder
lower bearing area. Glass bead peening may be used to remove corrosion from the pits which were not
removed with the stainless steel wire brush.
3 Clean the outer cylinder bearing area with approved solvent to remove all grease and dirt.
4 Using a dial micrometer with a pointed tip, measure the inner diameter of the outer cylinder lower bearing

Copyright © Textron Aviation Inc. Page 3 of 12

area and determine the average bearing surface diameter to include the depth of pit.
NOTE: Average bearing surface diameter is determined by measuring the inner diameter at a
minimum of four different locations, starting at the most damaged location and
rotating 45 degrees either side, plus one additional location and averaging the four
measurements.
(b) If the average bearing surface diameter is greater than 3.405 inches (86.487 mm), or the maximum pit depth is
greater than 0.015 inch (0.381 mm), contact Citation Customer Service Department.
(c) If the average bearing surface diameter is less than 3.405 inches (86.487 mm), proceed to step 3.
NOTE: If the outer cylinder lower bearing surface contains pits which remain after corrosion
removal, and it is estimated that upon removal of these pits the outer cylinder lower
bearing surface may not meet the absolute maximum average diameter of 3.405 inches
(86.487 mm) or the maximum pit depth is greater than 0.015 inches (0.381 mm), it may not
be feasible to rework the outer cylinder. The outer cylinder may require replacement.
(3) Rework of outer cylinder lower bearing surface area.
(a) If the average bearing surface diameter is greater than 3.405 inches, or the maximum pit depth is greater than
0.015 inch (0.381 mm), contact Citation Customer Service Department.
(b) Use a rotary stainless steel wire brush or glass bead peening to remove all corrosion from the bearing and
retainer ring areas. Glass bead peening may be used to remove corrosion from the pits which were not
removed with the stainless steel wire brush. Insure that all corrosion is removed prior to proceeding.
(c) Clean the lower bearing surface and the retainer ring areas with approved solvent, to remove all grease and dirt.
Wipe off solvent with a clean absorbent rag. Do not allow solvent to dry on the surface, remove all solvent
residue.
(d) Mask the machined step at the top edge of the lower bearing surface and an 0.50 inch (12.7 mm) band of the
upper portion of the lower bearing surface area, to prevent primer from being applied to these surfaces.
(e) Reclean the unmasked portion of the lower bearing surface with approved solvent. Wipe off solvent with a clean
absorbent rag. Do not allow solvent to dry on the surface, remove all solvent residue.
(f) Immediately prime the abraded area with MIL-PRF-23377 corrosion resistant primer by one of the following
procedures:
NOTE: Apply MIL-PRF-23377 corrosion resistant primer to clean surfaces within 30 minutes of
completion of sanding procedure. An oxide film which provides minimal adhesion for
primer begins to form immediately after working. Poorly adhered primer will result in
accelerated corrosion.
NOTE: For exact mixing instructions for MIL-PRF-23377 corrosion resistant primer, refer to the
manufacturer’s instructions.
(g) Remove plug and the masking from the cylinder.
NOTE: MIL-PRF-23377 primer must be completely cured to have Skydrol resistance.
(h) Cure MIL-PRF-23377 corrosion resistant primer coating in accordance with the manufacturer’s instructions.
I. Outer Cylinder and Piston Weld Assembly Torque Link Lug Inner Diameter Corrosion Inspection, Removal, Modification
and Prevention.
(1) Inspection
(a) Inspect the 0.875 inch (22.225 mm) diameter hole in the respective torque link lug for corrosion damage. Refer
to Figure 601. If the inner bore finish is not damaged, proceed to step (2)(c). If corrosion damage is present,
proceed to step (2).
(2) Preliminary rework of the torque link lug pin hole.
(a) Determine if the overall diameter of the torque link lug hole except in the locally corroded area is within tolerance
of (0.875 inch, +0.001 or -0.001 inch (22.225 mm, +0.025 or -0.025)) after the removal of all corrosion.
1 Using a stainless steel wire brush, remove corrosion from the torque link lug pin hole. Glass bead peening
may be used to remove corrosion from the pits which were not removed with the stainless steel wire brush.
Insure that all corrosion is removed prior to finishing.
2 Clean the torque link lug hole with approved solvent to remove all grease and dirt. Wipe off solvent with a

Copyright © Textron Aviation Inc. Page 4 of 12

clean absorbent rag. Do not allow solvent to dry on the surface, remove all solvent residue.
(b) Using a dial micrometer, measure the lug hole and determine the average hole diameter as follows:
NOTE: Measure the diameter of the hole at a minimum of four different locations in the same
vertical plane. Start at the most damaged location and measure 15 degrees on either side
of this location, plus one additional location and average the four measurements.
1 If the average lug hole diameter at the corroded point is greater than 0.905 inches (22.987 mm) or the
maximum pit depth is greater than 0.015 inch (0.381 mm), proceed to Rework Torque Link Lug Hole
Bushing Required.
2 If the average lug hole diameter is less than 0.905 inch (22.987 mm) at the corroded point, proceed to the
next step.
(c) Reclean the torque link lug hole with approved solvent to remove all grease and dirt. Wipe off solvent with a
clean absorbent rag. Do not allow solvent to dry on the surface, remove all solvent residue.
(d) Option 1: Immediately apply MIL-PRF-23377 corrosion resistant primer to inside of the hole area with a
thickness of 0.6 to 0.9 mil. For mixing and application of MIL-PRF-23377 corrosion resistant primer refer to the
manufacturer’s instructions.
NOTE: MIL-PRF-23377 corrosion resistant primer must be applied to clean surfaces within 30
minutes of completion of brushing procedure. An oxide film which provides minimal
adhesion for MIL-PRF-23377 corrosion primer begins to form immediately after working.
Poorly adhered MIL-PRF-23377 corrosion resistant primer will result in accelerated
corrosion.
(e) Cure MIL-PRF-23377 corrosion resistant primer in accordance with the manufacturer’s instructions.
NOTE: MIL-PRF-23377 corrosion resistant primer must be completely cured to have Skydrol
resistance.
(f)
Option 2: Immediately coat inside of the hole area with Type 1 Class B2 sealer. Install the torque link pin and
wipe off all excess sealer.
(3) Rework the Torque Link Lug Hole Bushing Required.
(a) Ream the hole to 0.950 inch (24.13 mm) diameter.
(b) Fabricate from 4340 steel, heat treated to 180-200 KSI, a 2.498 inch (63.449 mm) long bushing to press fit into
the 0.950 inch (24.13 mm) hole. The interference fit of the outer diameter of the bushing shall be 0.001 to 0.002
inch (0.025 to 0.050 mm).
(c) Coat the inside surface of the 0.950 inch (24.13 mm) diameter oversized hole with Type 1 Class B2 sealer prior
to installation of the bushing.
(d) Use liquid nitrogen to cool the bushing prior to pressing into the torque link lug.
(e) After pressing the bushing into the 0.950 inch (24.13 mm) hole, ream the bore of the bushing inner diameter to
0.876 inch, +0.001 or -0.001 inch (22.250 mm, +0.025 or -0.025 mm) diameter. Finish the 0.876 inch (22.250
mm) inner diameter of the bushing as described in preliminary rework of the torque link pin hole, utilizing either
Option 1 or Option 2.
J. Axle External Corrosion Inspection, Removal and Prevention.
NOTE: This procedure applies to the external areas of the axle in the areas where the brake assembly
makes contact.
(1) Inspection of Axle.
(a) Inspect the axle in the area shown for damage to the finish and corrosion. If the finish is not damaged and no
corrosion exists, no further action is required. Refer to Figure 602. If corrosion is present on the axle, proceed to
step (2), Rework of Axle. If the finish is damaged, but no corrosion exists, proceed to step (5), Finish
Application.
(2) Rework of Axle.
(a) Determine if the axle can be reworked (refer to Figure 602):
1 Using a steel wire brush, remove the loose corrosion from the axle in the area between the piston axle
adaptor and the area where the inboard wheel bearing and seal were located. Clean the axle with

Copyright © Textron Aviation Inc. Page 5 of 12

approved solvent to remove all grease and dirt. Using a vernier micrometer, measure the diameter of the
axle and determine the average axle diameter.
NOTE: Average axle diameter is determined by measuring the axle at four different locations,
oriented 45 degrees apart, and averaging the four measurements.
a If the average axle diameter is less than 1.8095 inches (45.961 mm), the axle must be replaced. Refer
to Main Gear Assembly - Assembly, Axle Installation.
b If the average axle diameter is 1.8095 inches (45.961 mm) or greater, proceed with reworking
instructions.
NOTE: If the axle surface contains pits which remain after corrosion removal and it is
estimated that upon removal of these pits, the axle may not meet the absolute
minimum average diameter of 1.8020 inches (45.770 mm), it may not be feasible
to attempt to rework the axle since it is possible that the axle may require
replacement.
(3) Rework of Axle.
(a) Wrap a piece of thin (0.012 or 0.016) aluminum sheet, 5.70 X 1.0 inch (144.78 X 25.4 mm), around the axle and
secure in place with a worm-type hose clamp to protect the portion of the axle where the inboard bearing and
seal were located.
CAUTION: It is very important to preserve the axle radius at the inboard edge of the rework area. When
using the emery cloth, do not allow the edge of the emery cloth to form a groove in the radius;
instead, allow the emery cloth to ride up into the radius.
(b) Using an 0.75 inch (19.05 mm) wide strip of 320 grit (aluminum oxide) emery cloth, remove all corrosion on the
axle (between the piston axle adaptor and protected area). All corrosion, including any pitting of the metal, must
be removed. After all pits are removed, apply a final finish to the axle with 400 grit emery cloth (aluminum oxide).
(c) Remove the aluminum sheet protecting the axle and ensure all corrosion is removed up to the area where the
bearing seal was making contact with the axle. Remove any remaining corrosion with 400 grit emery cloth but
use minimum pressure when sanding over the seal area.
(d) Clean the area with solvent and measure the diameter of the axle in the reworked area at four locations oriented
45 degrees apart and determine the average axle diameter. If the average axle diameter is less than 1.8020
inches (45.770 mm), the axle must be replaced. Refer to Main Gear Assembly - Disassembly and Main Gear
Assembly - Assembly, for axle replacement instructions. If the average axle diameter is 1.8020 (45.770 mm) or
greater, proceed with application of finish. Refer to step (5), Finish Application.
NOTE: Small local areas of the axle may indicate as small as 1.8000 inch (45.770 mm) diameter at
any one location, but the average axle diameter must still be a minimum of 1.8020 inch
(45.770 mm) diameter.
(4) (Refer to Figure 602.) Determine if the piston axle adaptor can be reworked as follows:
(a) Using a steel wire brush, remove the loose corrosion from the piston axle adaptor in the area shown. Clean the
piston axle adaptor with approved solvent to remove all grease and dirt. Using a vernier micrometer, measure
the diameter of the piston axle adaptor and determine the piston axle adaptor average diameter. Remove all
corrosion from the piston axle adaptor in the same manner as utilized for the axle. Upon removal of all pits,
measure the piston axle adaptor diameter at four locations oriented 45 degrees apart and average together to
determine the piston axle adaptor average diameter.
NOTE: Piston axle adaptor average diameter is determined by measuring the piston axle
diameter at four different locations, oriented 45 degrees apart (as shown in Figure 602,
View B-B), and averaging the four measurements.
1 If the axle adaptor average diameter is less than 2.490 inches (63.246 mm), there is an optional repair
available that uses a Cessna controlled process. This process can remove the corrosion and build up the
axle adaptor with hard chrome plating. For more details, contact Cessna Customer Services - Structures.
NOTE: Small local areas of the piston axle adaptor may indicate as small as 2.4850 inch
(63.119 mm) diameter at any one location, but the piston axle adaptor average
diameter must still be a minimum of 2.4900 inches (63.246 mm).
2 If the piston axle adaptor average diameter is 2.4900 inches (63.246 mm) or greater, the piston axle

Copyright © Textron Aviation Inc. Page 6 of 12

adaptor does not require replacement and must have a finish applied. Refer to paragraph I. step (5), Finish
Application.
NOTE: If it is determined that either the axle or piston axle adaptor require replacement, it
may be desirable to replace the piston and axle assembly (which includes both the
piston and axle).
(5) Finish Application.
NOTE: MIL-PRF-23377 corrosion resistant primer must be applied to clean surfaces within 30 minutes
of completion of sanding procedure. An oxide film which provides minimal adhesion for MIL-
PRF-23377 corrosion resistant primer begins to form immediately after working. Poorly
adhered MIL-PRF-23377 corrosion resistant primer will result in accelerated corrosion.
(a) Clean the piston axle adaptor and/or axle with approved solvent and wipe dry.
(b) Mask off areas of the piston not reworked.
(c) Mask off the outboard portion of the axle from the inboard wheel bearing seal. Ensure masking covers the
inboard wheel bearing seal contact point so that the seal does not ride on the MIL-PRF-23377 corrosion
resistant primer.
(d) Apply MIL-PRF-23377 corrosion resistant primer to the piston axle adaptor and/or the axle. For application and
mixing instructions for MIL-PRF-23377 corrosion resistant primer, refer to the manufacturer’s instructions.
(e) Apply a thin film of wheel bearing grease to the outer surface of axle as a corrosion preventative treatment.
K. Axle Internal Corrosion Inspection, Removal, Modification and Prevention.
NOTE: This procedure applies to the internal areas of the axle from the outboard end to a point 1.63
inches (41.402 mm) inboard.
(1) Inspection of Axle.
(a) If corrosion exists in the outboard (1.63 inches (41.402 mm)) end of the axle internal bore the corrosion must be
removed by mechanical means. If corrosion is light and is removed by the use of 320 grit emery cloth (aluminum
oxide) with no remaining pits, measure the bore diameter. If the bore diameter is larger than 1.378 inch (35.001
mm), or pits remain after the use of emery cloth, the bore will require machining to enlarge the bore to 1.4105
inches, +0.003 or -0.003 inches (35.826 mm, +0.076 or -0.076 mm). If corrosion was removed by the use of
emery cloth and the bore diameter was 1.378 inches or less, then no machining is required. Proceed to
paragraph J. step (2)(c) for finish application to prevent corrosion. If machining is required to enlarge the bore,
proceed to paragraph K step (2), Axle Rework, for machining requirements.
(2) Axle Rework.
NOTE: This procedure must be performed by a machinist using standard practices and techniques
for machining a precision bore in the axle (material 4340 steel).
(a) Refer to Main Gear Assembly - Disassembly for axle removal procedures.
(b) Enlarge the bore diameter to 1.4105 inches, +0.003 or -0.003 inches (35.826 mm, +0.076 or -0.076 mm).
Maintain a surface finish of 125 microinches. Maintain a 0.005 inch (0.127 mm) radius and a 0.062 inch (1.574
mm) chamfer at the transition point from the larger diameter bore to the smaller diameter bore 1.63 inches
(41.402 mm) inboard from the outboard end of the axle. Establish a 1.510 inch (38.354 mm) diameter 30
degrees chamfer at the outboard end of the bore.
NOTE: MIL-PRF-23377 corrosion resistant primer must be applied to clean surfaces within 30
minutes of completion of sanding procedure. An oxide film which provides minimal
adhesion for MIL-PRF-23377 corrosion resistant primer begins to form immediately after
working. Poorly adhered MIL-PRF-23377 corrosion resistant primer will result in
accelerated corrosion.
(c) Clean the bore diameter and apply MIL-PRF-23377 corrosion resistant primer. For mixing and application of
MIL-PRF-23377 corrosion resistant primer, refer to the manufacturer’s instructions.
(d) If airplane is equipped with an antiskid brake system, the axle bore must be shimmed back to 1.377 inches,
+0.001 or -0.001 inches (34.975, +0.025 or -0.025) diameter as follows:
1 Fabricate a stainless steel shim from sheet stock as shown in Figure 603. Deburr all edges. Abrade one
surface of the shim using 320 grit emery cloth (aluminum oxide).

Copyright © Textron Aviation Inc. Page 7 of 12

2 Roll shim to 1.41 inch (35.814 mm) diameter with abraded surface to the outside. Clean outer surface of
shim with approved solvent.
3 Bond shim in the axle with the joint at the top using EA9309.3NA adhesive. Insert antiskid transducer
(coated with wax and then wrapped with one layer of thin plastic, such as Saran Wrap, to act as a parting
agent) to hold the shim in position.
4 Allow adhesive to cure, then remove the antiskid transducer.
5 Reinstall axle. Refer to Main Gear Assembly - Assembly, for axle installation procedures.

Copyright © Textron Aviation Inc. Page 8 of 12

Figure 601 : Sheet 1 : Cylinder and Piston Corrosion Repairs

Copyright © Textron Aviation Inc. Page 9 of 12

Figure 602 : Sheet 1 : Main Landing Gear Axle Inspection

Copyright © Textron Aviation Inc. Page 10 of 12

Figure 602 : Sheet 2 : Main Landing Gear Axle Inspection

A18131
CAUTION: MAKE SURE THAT YOU KEEP AN
SAFETY WIRE AXLE RADIUS OF 0.38 INCHES AS
(REFERENCE) YOU REMOVE THE CORROSION
NAS561P8−8 FROM THE AXLE. THIS IS DEFINED
PIN IN THE ACCOMPLISHMENT
(REFERENCE) INSTRUCTIONS.

1.16 INCH +0.5 OR−0.05 INCH

B
ALUMINUM SHEET

B
AXLE
WHEEL BEARING (REFERENCE)
AND SEAL AREA
PISTON AXLE
ADAPTER THE MINIMUM AVERAGE
(REFERENCE) DIAMETER IS 2.490 INCHES THE MINIMUM AVERAGE DIAMETER
AFTER THE REWORK IS IS 1.8095 INCHES FOR REWORK.
COMPLETED. (NOTE) THE MIMIMUM AVERAGE DIAMETER IS
1.8020 INCHES AFTER THE REWORK IS
COMPLETED. (NOTE)

VIEWA−A
45 DEGREES

A
D B

C C
NOTE: THE AXLE IS MEASURED AT
FOUR LOCATIONS 45 DEGREES
APART TO FIND THE
AVERAGE AXLE DIAMETER. B D
SEE VIEW B−B. A
VIEWB−B
MEASUREMENT LOCATIONS FOR THE AXLE
AA6541T1017A
BB6541T1017

Copyright © Textron Aviation Inc. Page 11 of 12

Figure 603 : Sheet 1 : Axle Inside Diameter Corrosion Removal

Copyright © Textron Aviation Inc. Page 12 of 12

MAIN GEAR ASSEMBLY - ASSEMBLY

1. Assembly
A. Tools and Equipment (Refer to Illustrated Parts List).
NOTE: Equivalent substitutes may be used for the listed items:
NAME NUMBER MANUFACTURER USE
Safety Wire Monel 0.020 inch Commercially Available Safety air valve and cylinder
diameter plug.
Hydraulic Assembly MCS 352 Aviation Fluids Service Company Lubricate and protect surfaces
Lubricant St. Louis, MO 63166 in contact with hydraulic fluid or
prevent entry of water.
Loctite 7649 Primer N U467019 Loctite Corp. To prime the bearing threads.
705 N. Mountain Road
Nineteen, CT 06111
242 Loctite Corporation For the fasteners thread lock.
Locktite 705 N. Mountain Road
Newington, CT 06111
Loctite 243 Loctite Corporation For the fasteners thread lock.
705 N. Mountain Road
Newington, CT 06111
Loctite 609 Loctite Corporation Fill and seal trunnion to cylinder
705 N. Mountain Road and install bushings in torque
Newington, CT 06111 links.
Drill Bit Letter D Note 1 Commercially Available
Reamer 0.250 inch Commercially Available
diameter with a
pilot 0.128 inch
diameter and 0.375
inch length Note 2
NOTE 1: Drill bit must have a 0.128 inch diameter pilot that is 0.375 inch in length.
NOTE 2: A reamer such as a Cleveland 4001 reamer, Number 25513 would be satisfactory. The pilot must be
machined onto the Cleveland reamer.
B. Axle Installation (Refer to Illustrated Parts List).
(1) Install the expansion plug (81) into the inboard end of the new axle using wet epoxy primer and 1000 pounds, +500 or
-000 pounds of force.
(2) Wipe out the hole in the piston with approved solvent refer to Main Gear Assembly - Cleaning.
(3) Prepare the arbor press to install the axle (79) in the piston using the wooden block used when pressing the axle out
of the piston.
(4) Coat the hole in the piston and the portion of the axle that makes contact with the piston with MIL-PRF-23377
corrosion resistant primer and press the axle in position while primer is wet. Ensure that the keyway in a new axle (the
threaded area of the axle) is oriented up, or on a reinstalled axle, the keyhole shall be oriented 60 degrees from the
original keyway up position on the axle.
NOTE: 60 degrees deviation from original up position is required on installed axle.
(5) Using an 0.250 O.D. x 0.128 I.D. drill bushing in the hole in the side of the piston and a number 30 (0.128 inch
diameter) drill bit, drill a hole through (one side only) of the axle to match the existing hole in the piston. Remove the
drill bushing and enlarge the hole using a letter D (0.246 inch diameter) drill bit with an 0.128 inch diameter pilot.
Ream the hole using an 0.250 inch diameter reamer with an 0.246 inch diameter pilot.
(6) Deburr the hole and install new pin (80) flush with the outside surface of the piston and secure with safety wire.

Copyright © Textron Aviation Inc. Page 1 of 3

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 13:10:22 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
32-10-02-7 (Rev 14)

C. Torque Link Bushing Installation (Refer to Illustrated Parts List).

(1) Clean paint, grease, dust or other contaminating substances from bushings and torque links.
WARNING: Use solvent in well ventilated area, avoid breathing fumes.
(2) Use a clean rag saturated with approved solvent and clean bushings and torque links.
(3) Apply Loctite 609 to bearings (96) and torque links and press bearings (96) in place.
WARNING: Use solvent in a well ventilated area. Avoid breathing fumes.
(4) Excess Loctite may be removed with a rag moistened with approved solvent.
(5) Clean Loctite from lubrication holes.
(6) Cure time for Loctite on the bushings is 24 hours.
NOTE: When new torque link bushings are installed, it may be necessary to mill and ream bearings
(96) to dimensions shown in Main Gear Assembly - Fits and Clearances.
D. Piston Assembly (Refer to Illustrated Parts List).
NOTE: Ensure that phosphate coating has been removed from inner surface of piston assembly, if not
refer to, Main Gear Assembly - Repair, Piston Assembly (77 or 78) Inner Diameter Finish Rework.
WARNING: Long exposure to phosphate ester base fluids can cause skin dehydration and chapping.
(1) Immerse packings and seals in phosphate ester base hydraulic fluid.
(2) Install O-ring (91) on isolation piston (90).
(3) Coat the inner barrel of piston (77 or 78) with a thin layer of hydraulic fluid or hydraulic assembly lubricant.
(4) Insert isolation piston (90) into barrel of piston assembly (77 or 78). Push piston into barrel until it seats against
bottom.
(5) Install O-ring (86) with back-up ring (87) on bearing (88).
(6) Install "T" seal (85) into inner channel in bearing (88).
CAUTION: Do not allow retainers to scratch the chrome surface of the piston assembly.
(7) Slide retainer (83), retainer (84), scraper (82), bearing (88) and spacer (89) over barrel of piston assembly (77 or
78).
(8) Apply Loctite 7649 Primer N (material code U467019) to threads of bearing (92). Allow to air dry then apply Loctite
242 or Loctite 243 to threads of bearing (92).
CAUTION: Setscrews must be recessed below bearing surface. Make sure resistance is felt when installing
setscrews to insure self-locking capability. Replace setscrews not indicating locking capabilities.
(9) Screw bearing (92) on piston assembly and secure with two self-locking setscrews (93). Torque setscrews 20 to 30
inch-pounds.
E. Piston Installation (Refer to Illustrated Parts List).
(1) Pack area all around bearing (88) with hydraulic assembly lubricant (MCS 352) to resist entry of water about bearing
interface with strut cylinder collar.
(2) Carefully slide piston assembly into cylinder assembly. Seat bearing (88) into cylinder and install scraper (82),
retainer (84) and retainer (83).
NOTE: Make sure retainer is seated in the lock ring groove, then extend strut piston assembly until
scraper retainer locks the lock ring in place.
F. Assemble Trunnion to Cylinder (Refer to Illustrated Parts List).
WARNING: Solvent is toxic and flammable; use in well ventilated area. Avoid breathing fumes and keep away
from flames.
(1) Clean inside diameter of trunnion and outside diameter of cylinder with approved solvent.
(2) Apply Loctite 609 to inside diameter of trunnion and outside diameter of cylinder using a clean brush.
NOTE: Apply sufficient amount of Loctite 609 to assure complete fill and seal.
(3) Press fit cylinder into trunnion.
NOTE: Remove excess Loctite immediately and before subsequent exterior finishing.

Copyright © Textron Aviation Inc. Page 2 of 3

(4) Install 2 forward bolts (5), washers (6 and 7) and nuts (8).
(5) Install 2 aft bolts (9), washers (10), washers (7) and nuts (8).
G. Install Drag Brace (Refer to Illustrated Parts List).
(1) Position drag brace (13) in place in trunnion and cylinder.
(2) Install bolt (17), washers (18) and nut (19).
(3) Install bolt (14), washers (15) and nut (16).
H. Torque Link Installation (Refer to Illustrated Parts List).
(1) Install upper and lower torque links (94 and 95), shafts (98) and shaft retainer pins (99).
(2) Install torque link interconnect bolt (100), toe-in adjustment washers (104, 105 and 106), flat washer (101), nut (102)
and cotter pin (103). Add or remove washers until a gap of 0.004 to 0.019 is obtained.
NOTE: Torque link toe-in adjustment washers and interconnect parts should be assembled exactly as
disassembled to maintain toe-in adjustment.
(3) Install squat switch and attaching hardware.
I. Service Fittings Installation (Refer to Illustrated Parts List).
(1) Install packing (24) and air valve assembly (23). Torque valve assembly 100 to 110 inch-pounds. Safety wire large nut
(0.75 inch) to forging. Use double twist method of installing safety wire.
NOTE: If new air valve assembly is being installed, discard packing and replace with phosphate ester
base fluid resistant packing, Part Number NAS1611-015.
(2) Install metering pin (27), plug (25) and seals (26 and 28) in top of cylinder assembly. Safety wire plug to trunnion bolt
using double twist method.
2. Storage
A. Recommended Storage Procedure.
(1) Release air from air valve; refer to Main Gear Assembly - Disassembly.
(2) Remove plug from top of cylinder assembly and drain hydraulic oil from cylinder. Replace plug.
(3) Collapse strut assembly. Coat exposed chromed surface of piston assembly with protective oil.
(4) Wrap collapsed strut in grease proof paper, then kraft paper and pack in rigid container.
(5) Container shall be stored in a cool, dry, well ventilated area on a noncorrosive base.

Copyright © Textron Aviation Inc. Page 3 of 3

MAIN GEAR ASSEMBLY - FITS AND CLEARANCES

1. Fits and Clearances
A. Cylinder 6641320-3, -4

Copyright © Textron Aviation Inc. Page 1 of 3

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 13:10:23 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
32-10-02-8 (Rev 14)

(1) 0.875, inch +0.000 or -0.001 inch (22.23 mm, +0.00 or -0.03 mm) diameter
(2) 0.250, inch +0.006 or -0.000 inch (6.35 mm, +0.15 or -0.00 mm) diameter
E. Torque Link End Bushing M81934/2-14C016

Copyright © Textron Aviation Inc. Page 2 of 3

(1) 0.0625, inch (1.59 mm) radius

(1) 1.997, inch +0.000 or -0.001 inch (50.72 mm, +0.00 or -0.03 mm) diameter
(2) 1.981, inch +0.000 or -0.001 inch (50.32 mm, +0.03 or -0.03 mm) diameter after installation and line reaming.

Copyright © Textron Aviation Inc. Page 3 of 3

MAIN LANDING GEAR ASSEMBLY

NOMENCLATURE EFFECTIVITY UNITS
PER
ITEM PART NUMBER 1 2 3 4 5 6 7 FROM TO ASSY
- MAIN LANDING GEAR ASSEMBLY
- 1 6641000-15 . LANDING GEAR ASSY-LH A 01
- 1A 6641000-27 . LANDING GEAR ASSY-LH C 01
- 1B 6641000-37 . LANDING GEAR ASSY-LH E 01
- 1C 6641000-39 . LANDING GEAR ASSY-LH G 01
- 1D 6641000-41 . LANDING GEAR ASSY-LH J 01
- 1E 6641000-35 . LANDING GEAR ASSY-LH L 01 R
- 2 6641000-16 . LANDING GEAR ASSY-RH B 01
- 2A 6641000-28 . LANDING GEAR ASSY-RH D 01
- 2B 6641000-38 . LANDING GEAR ASSY-RH F 01
- 2C 6641000-40 . LANDING GEAR ASSY-RH H 01
- 2D 6641000-42 . LANDING GEAR ASSY-RH K 01
- 2E 6641000-36 . LANDING GEAR ASSY-RH M 01 R
TRUNNION & CYL
- 3 6641000-17 . . ASSY-LH FSO A NP
6641000-25 REFER TO
NOTE 1

- 3A 6641000-25 . . TRUNNION AND C,E,G,J,L 01 R

CYLINDER ASSY-LH
TRUNNION & CYL
- 4 6641000-18 . . ASSY-RH FSO B NP
6641000-26 REFER TO
NOTE 1
- 4A 6641000-26 . . TRUNNION AND D,F,H,K,M 01 R
CYLINDER ASSY-RH
5 NAS464P9A75 . . . BOLT 02 R
6 NAS1149F0932P . . . WASHER UPPER 02 R
7 NAS1149F0963P . . . WASHER 04 R
8 MS21083N9 . . . NUT 04 R
9 6641201-2 . . . BOLT-MLG 02 R
10 6641202-1 . . . WASHER UPPER 02 R
CYLINDER-OUTER
11 6641320-3 . . . A,C,E,G,J,L 01 R
LH
- . . . CYLINDER-OUTER
12 6641320-4 B,D,F,H,K,M 01 R
RH
13 6541300-3 . . . DRAG BRACE 01 R
BOLT LOWER
14 NAS464P10A18 . . . BRACE ATTACH A,B NP R
FSO S3461-66
- . . . BOLT LOWER
14A S3461-66 C THRU M 01 R
BRACE ATTACH

Copyright © Textron Aviation Inc. Page 1 of 6

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 13:10:29 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
32-10-02-1001 (Rev 14)

. . . WASHER BRACE
15 NAS1149F1032P A,B,C,D 02
ATTACH
. . . NUT LOWER
16 MS21083N10 A,B,C,D 01
BRACE ATTACH
BOLT UPPER
17 NAS464P7A28 . . . BRACE ATTACH A,B NP R
FSO S3461-81
- . . . BOLT UPPER
17A S3461-81 C THRU M 01 R
BRACE ATTACH
. . . WASHER BRACE
18 NAS1149F0732P 02 R
ATTACH

. . . NUT UPPER
19 NAS1291-7 01 R
BRACE ATTACH
TRUNNION ASSY
20 6641306-1 . . . FSO 6641306-5 A,B NP
REFER TO NOTE 2
- 20A 6641306-5 . . . TRUNNION ASSY C THRU M 01 R
21 6641306-4 . . . . BUSHING A,B 01
- 21A 6641306-7 . . . . BUSHING C THRU M 01 R
22 6641306-3 . . . . BUSHING A,B 01
- 22A 6641306-6 . . . .
BUSHING C THRU M 01 R
. . VALVE ASSY-AIR
23 AN6287-1 01
CHARGE
24 NAS1611-015 . . O-RING 01
25 MS24391D4L . . PLUG 01
26 NAS1612-4 . . O-RING 01
27 6641206-1 . . METERING PIN 01
28 NAS1612-8 . . O-RING 01
PLATE-
29 6640001-4 . . 01
IDENTIFICATION
- . . PLATE-
30 6640001-11 E thru M 01 R
IDENTIFICATION
WHEN INITIALLY REPLACING 6641000-17 OR 6641000-18 WITH 6641000-25 OR 6641000-26
NOTE 1:
ALSO ORDER 1 EACH 5541205-7 & 5541205-8 PINS.
WHEN INITIALLY REPLACING 6641306-1 WITH 6641306-5 ALSO ORDER ORDER ONE EACH
NOTE 2:
5541205-7 & 5541205-8 PINS.
NOMENCLATURE EFFECTIVITY UNITS
PER
ITEM PART NUMBER 1 2 3 4 5 6 7 FROM TO ASSY
- MAIN LANDING GEAR ASSEMBLY
PISTON AND AXLE
75 6641000-23 . . ASSY-LH FSO A,C NP
6641000-33

Copyright © Textron Aviation Inc. Page 2 of 6

PISTON AND AXLE

- 75A 6641000-33 . . E,G,J 01
ASSY-LH
PISTON AND AXLE
- 76 6641000-24 . . ASSY-RH FSO B,D NP
6641000-34
- . . PISTON AND AXLE
76A 6641000-34 F,H,K 01
ASSY-RH
PISTON-LH FSO
77 6641330-1 . . . A,C NP R
6641330-201
- 77A 6641330-201 . . . PISTON-LH A,C 01 R
PISTON-RH FSO
- 78 6641330-2 . . . B,D NP R
6641330-202
- 78A 6641330-202 . . . PISTON-RH B,D 01 R
AXLE FSO
79 6641200-4 . . . A,B,C,D NP R
6641200-200
AXLE FSO
- 79A 6641200-6 . . . E,F,G,H,J,K NP R
6641200-200
- 79B 6641200-200 . . . AXLE A THRU K 01 R
80 NAS561P8-8 . . . PIN 01
PLUG-
81 5514350-22 . . . 01
EXPANSION
82 MS28776M2-27 . . SCRAPER 01
83 5541210-2 . . RETAINER 01
84 CM2690C21 . . RETAINER 01
85 601RS-335-04183 . . SEAL-T 01
86 NAS1611-337 . . O-RING 01
87 MS28774-337 . . RING-BACKUP 01
88 5541309-7 . . BEARING-LOWER 01
89 5541208-1 . . SPACER 01
90 6641307-2 . . PISTON-ISOLATION 01
91 NAS1611-326 . . O-RING 01
92 6641311-1 . . BEARING-UPPER 01
93 NAS1081-3B6 . . SCREW-SET 02 R
94 6641304-1 . . LINK-TORQUE UPPER 01
LINK-TORQUE
95 6641304-2 . . 01
LOWER
96 M81934/2-14C016 . . . BEARING 04
97 M81934/1-10C024 . . . BEARING 02
98 6541212-3 . . SHAFT 02
99 MS16562-66 . . PIN 02
100 5541220-2 . . BOLT 01
101 5541216-2 . . WASHER 01
102 MS17825-8 . . NUT 01

Copyright © Textron Aviation Inc. Page 3 of 6

103 MS24665-287 . . PIN-COTTER 01

104 NAS1149F1032P . . WASHER AR
105 NAS1149F1063P . . WASHER AR
. . WASHER-TOE ANGLE
106 NAS70CL640-1188 AR
ADJUST
WASHER
- 106A NAS1149C1016R . . ALTERNATE FOR AR
NAS70CL640-1188
- Item Not Illustrated

Copyright © Textron Aviation Inc. Page 4 of 6

Figure 1001 : Sheet 1 : MAIN LANDING GEAR ASSEMBLY

Copyright © Textron Aviation Inc. Page 5 of 6

Figure 1001 : Sheet 2 : MAIN LANDING GEAR ASSEMBLY

Copyright © Textron Aviation Inc. Page 6 of 6

MAIN GEAR ASSEMBLY - ILLUSTRATED PARTS LIST

1. Illustrated Parts List
A. Introduction
(1) The Illustrated Parts List will help the customer to order, keep, and supply the main gear components. It will also
identify new and reclaimed parts. It is not approved for any other purpose.
(2) This parts list includes the main gear assemblies used on the Citation airplanes. Part numbers:
6541410-1 6541410-2 6541410-3 6541410-4 6541410-5
6541410-6 6541410-7 6541410-8 6541410-9 6541410-10
6541410-11 6541410-12 6541410-13 6541410-14
6541420-1 6541420-4 6541420-7 6541420-8 6541420-200
(3) The indention system used in the detailed parts list of this catalog shows the relationship of one part to another. For a
given item, the indention code shows a general heading at the extreme left position and continues with indented
columns until the end detail is reached as follows:
A18017
1234567
Installation
Detail Parts for Installation
Assembly
Attaching Parts for Assembly
Detail Parts for Assembly
Subassembly
Attaching Parts for Subassembly
Detail Parts for Subassembly
Sub−Subassembly
Attaching Parts for Sub−Subassembly
Detail Parts for Sub−Subassembly

Basic Number Dash Number

(Drawing Identification
Only)

NOTE: Parts that have a dash 400 series stamp are for internal control purposes only and must not be
used by the operator to order or to identify parts. Repair parts available and packaged as a kit
are identified in the parts list with an asterisk (*). Kits may be ordered by the kit part number
located at the end of the parts list.
B. For Vendor names and addresses with Federal Supply Codes, refer to Introduction - Supplier Address List.

Copyright © Textron Aviation Inc. Page 1 of 2

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 13:10:37 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
32-10-03-10 (Rev 14)

Copyright © Textron Aviation Inc. Page 2 of 2

MAIN GEAR ASSEMBLY - DESCRIPTION AND OPERATION

1. Description
A. The main gear assembly is designed and assembled to permit maneuverability of the airplane on the ground and to retract
into the wing when airborne. It is designed to absorb shock during airplane takeoffs, landings and taxiing. The main gear
assembly consists of a trunnion, trailing link, axle and oleo. Refer to Figure 1 and Figure 2.
(1) The trunnion is mounted in the wing wheel well with trunnion pins to allow the gear assembly to retract into the wing.
(2) The oleo consists of an upper and lower barrel with a metering pin and orifice to control the flow of hydraulic fluid from
one chamber to the other during oleo extension and compression. The oleo is filled with hydraulic oil with the oleo
compressed and then charged with compressed dry nitrogen. The fluid and nitrogen are not separated but are
contained in the same chamber.
(3) The axle is installed in the trailing link assembly press fitted and secured with a bolt.
(4) The following main gear assembly and oleo part numbers are affected by this Section are:
6541410-1 6541410-2 6541410-3 6541410-4 6541410-5
6541410-6 6541410-7 6541410-8 6541410-9 6541410-10
6541410-11 6541410-12 6541410-13 6541410-14
6541420-1 6541420-4 6541420-7 6541420-8 6541420-200
2. Operation
A. As weight of the airplane is applied to the main gear assembly, the lower barrel of the oleo assembly is forced to slide into
the upper barrel. This movement forces hydraulic fluid to flow from the upper chamber through an orifice in the bottom of
the upper barrel into the upper barrel. The restricted fluid flow and the resistance of the compressed air/nitrogen in the
upper portion of the barrel dampens the movement of the oleo assembly and absorbs compression shocks. As the weight
of the airplane is removed from the main gear assembly, the compressed air/nitrogen forces the hydraulic fluid back
through the orifice. This expansion and controlled flow of hydraulic fluid causes the oleo to extend. Refer to Figure 3.
3. Personnel Safety Precautions - Hydraulic Fluid
A. The oleo assembly contains phosphate ester base hydraulic fluid. Before performing maintenance or any operation on the
oleo assembly, personnel should read and thoroughly understand this warning.
WARNING: Observe the following safety precautions when working on systems containing phosphate ester
base fluid. Prolonged exposure to the fluid can cause skin dehydration and chapping.
(1) Wash hands thoroughly with soap and water before starting work; apply barrier cream (silicone hand cream) to
hands, wrists and forearms. Rub cream under fingernails and into creases of skin.
(2) Wear eye goggles when pressure testing components or systems or anytime there is a possibility of hydraulic fluid
spraying/splashing in the eyes.
(3) If hydraulic fluid enters the eyes, treat eyes immediately by irrigating thoroughly with clear, cold water.
(4) Wash hands, wrists and forearms with soap and warm water after contacting hydraulic fluid.
(5) !f clothing becomes soaked with hydraulic fluid, remove the clothing as soon as possible. Wash hydraulic fluid
exposed skin with soap and warm water. Wash hydraulic fluid contaminated clothes before wearing.
4. Technical Safety Precautions - Hydraulic Fluid
A. Because the oleo contains phosphate ester base hydraulic fluid, improper maintenance practices can be damaging to
gear components and other equipment. Before performing maintenance or any operation on the oleo assembly, personnel
should read and thoroughly understand the following technical precautions.
CAUTION: Phosphate ester base hydraulic fluid will damage and/or deteriorate a wide range of materials,
including rubber, copper, various plastics and paints.
(1) Ensure that hydraulic fluid does not come in contact with any part of the component outside of the oleo. Keep spillage
to an absolute minimum. Clean up spilled hydraulic fluid immediately to prevent contamination of non-hydraulic
components and to avoid false hydraulic leak detections. If spillage occurs, wipe up the fluid with a dry cloth and wash
area with naptha MIL-PRF-680, (Type III) or Methyl n-Propyl Ketone.
(2) When gear components are disassembled, provide suitable protection for preventing entry of foreign material by
using caps and/or covers.

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Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 13:10:39 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
32-10-03-0 (Rev 14)

(3) Always check angle and position of components prior to disassembly to ensure proper alignment and placement of
components and hardware during assembly or replacement.
(4) Use naptha, Federal Specification P-D-680, (Type III) or Methyl n-Propyl Ketone, when washing metal parts prior to
assembly. Ensure all traces of the cleaning agent are removed before assembly.
(5) Use only clean hydraulic fluid for flushing or testing hydraulic components.
(6) Do not unpack seals, O-rings/packings until they are required and insure that only correct and approved seals, O-
rings/packings are used.
(7) When assembling the gear shock strut hydraulic seals and O-rings/packings, lubricate only with phosphate ester
base hydraulic fluid. Always lubricate seals, O-rings/packings immediately before installation. Threaded fittings
should be assembled without the use of lubricants whenever possible. If a lubricant is required to prevent galling or to
otherwise ease installation, use phosphate ester base hydraulic fluid or VV-P-236 Petrolatum.
CAUTION: Take special care not to contaminate seals, o-rings/ packings after lubrication.
CAUTION: Prevent contamination of phosphate ester base hydraulic fluid with other hydraulic fluids, oil, water
or dirt.

Copyright © Textron Aviation Inc. Page 2 of 5

Figure 1 : Sheet 1 : Main Landing Gear Assembly

A84046

Trunnion

Trailing link

Oleo Assembly

Axle

5541T1014

Copyright © Textron Aviation Inc. Page 3 of 5

Figure 2 : Sheet 1 : Main Landing Gear Oleo Assembly

Copyright © Textron Aviation Inc. Page 4 of 5

Figure 3 : Sheet 1 : Main Landing Gear Oleo Operation

Copyright © Textron Aviation Inc. Page 5 of 5

MAIN GEAR ASSEMBLY - TESTING

1. Testing
A. The main gear oleo strut should be properly filled/serviced with Phosphate Ester hydraulic fluid and charged with nitrogen
prior to conducting test(s).
B. Tools and Equipment.
NAME NUMBER MANUFACTURER USE
Portable hydraulic Commercially available Fill and cycle strut.
pump filled with
Phosphate Ester
hydraulic fluid
C. Main Gear Oleo Servicing.
(1) Refer to Maintenance Manual, Chapter 12, Landing Gear Shock Strut - Servicing.
D. Leak Test.
(1) After filling/servicing oleo in accordance with instructions above, leave oleo charged for a one-hour period. No fluid
leakage or loss of nitrogen is permissible.
WARNING: Do not stand in front of service valve while releasing nitrogen pressure. Do not turn 0.75 inch hex
nut while releasing pressure. Removing air service valve without releasing pressure first can cause
injury.
2. Troubleshooting
A. The main gear oleo may be tested as outlined in Section 1., Testing, to determine nitrogen or fluid leakage. A review of
documented information received with the assembly, visual check and/or test results may be utilized in conjunction with
Paragraph B., Troubleshooting.
B. Troubleshooting.
TROUBLE PROBABLE CAUSE REMEDY
HYDRAULIC FLUID LEAK Damaged seal at lower end of piston. Replace seal.
AROUND PISTON.
Inner wall of barrel worn or damaged beyond Rework or replace barrel.
limits.
Damaged outer surface of upper piston. Rework or replace piston.
OLEO DOES NOT Inadequate nitrogen pressure. Recharge nitrogen pressure.
EXTEND WHEN WEIGHT
IS REMOVED.
Nitrogen pressure leaks. Replace packing on pneumatic valve or
replace valve.
LOOSE BEARING IN Loctite failed or lug damaged. Check inner diameter of hole in lug for
OLEO UPPER OR proper diameter. If in tolerance, reinstall
LOWER LUGS. bearing with Loctite.
LOOSE SPHERICAL Worn nylon ball race. Install new bearing.
BALL IN UPPER OR
LOWER BEARING.
DAMAGED OUTER Foreign objects hitting piston. Rework or replace piston (See
SURFACE ON UPPER Maintenance Manual for rework).
PISTON.
Contaminants between upper piston and upper Clean and replace seal. Check vent in
bearing assembly. bearing assembly; if plugged, replace.

Copyright © Textron Aviation Inc. Page 1 of 1

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Model 500 Series Component Maintenance Manual (Rev 17)
32-10-03-3 (Rev 14)

MAIN GEAR ASSEMBLY - DISASSEMBLY

1. Landing Gear Disassembly
A. Preparation for Disassembly (Refer to Illustrated Parts List).
(1) Rotate 0.625 inch hex nut on air valve (4) counterclockwise one and one-half turns to lift internal valve poppet, then
release any trapped gas or liquid by depressing valve core.
WARNING: Do not stand in front of valve assembly while releasing gas pressure. Do not turn 0.75 inch hex nut
while releasing gas pressure. Removing air valve without releasing compressed gas can cause
bodily injury.
(2) Ensure that gas is released by sliding upper barrel in and out of lower barrel.
B. Disassemble Gear. Refer to Main Landing Gear Assembly, Illustrated Parts List).
(1) Remove oleo assembly (10).
(a) Remove cotter pin (17), nut (16), bolt (11) and washers (13, 14, 15) securing upper end of oleo.
(b) Remove cotter pin (17), nut (16), bolt (12), and washers (13, 14), securing lower end of oleo.
(2) Remove trailing link (85).
(a) Remove cotter pin (83), nut (82), pivot pin (77), thrust bearings (80) and spacer (78) securing trailing link (85) to
trunnion (18).
(3) Remove bushings (79) by pressing out of trunnion.
(4) Remove squat switch support bracket (5) by driving out of bore of trunnion (18).
NOTE: Bracket (5) is secured with Loctite 680.
2. Oleo Disassembly
A. Preparation for Disassembly. Refer to Oleo Assembly - Main Gear, Figure 1002.
(1) Rotate 0.75 inch hex nut on air valve (4) counterclockwise one and one-half turns to lift internal valve poppit, to release
any trapped gas or liquid.
WARNING: Do not stand in front of valve assembly while releasing gas pressure. Do not turn 0.75 inch hex nut
while releasing gas pressure. Removing air valve without releasing compressed gas can cause
bodily injury.
(2) Ensure that gas is released by sliding piston in and out of cylinder.
(3) Cut lockwire and remove air valve (4) and O-ring (5) from piston assembly.
(4) Drain hydraulic fluid by inverting oleo assembly.
B. Disassemble Oleo.
NOTE: Perform only those portions of this disassembly procedure as are necessary to remove the
component which is damaged or requires replacement.
(1) Cut safety wire securing outer bearing (9) to lower barrel (12).
(2) Use a spanner wrench to remove outer bearing (9) from lower barrel (12).
(3) Separate upper (6) and lower barrel (12).
(4) Remove orifice (14) from upper barrel (6).
(5) Secure the lug of the lower cap in a padded vise and remove lower barrel (12) from lower cap (18).
NOTE: Lower cap is installed using Loctite 277 adhesive. To loosen bond, it may be necessary to
apply heat to joint to soften the adhesive bond.
(6) Remove metering pin (13) from lower cap (18).
NOTE: Metering pin is installed using Loctite 242 or Loctite 243 adhesive. To loosen bond, it may be
necessary to apply heat to joint to soften the adhesive bond.
(7) Secure the lug of the upper cap in a padded vise and remove upper cap (3) from the upper barrel (6).
NOTE: Upper cap is installed using Loctite 277 adhesive. To loosen bond, it may be necessary to
apply heat to joint to soften the adhesive bond.
(8) Press bearings (2) out of caps (3) and (18) using a suitable arbor press.

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Model 500 Series Component Maintenance Manual (Rev 17)
32-10-03-4 (Rev 12)

MAIN GEAR ASSEMBLY - CLEANING

1. Cleaning
A. Tools and Equipment.
NOTE: Equivalent substitutes may be used for the listed items.
NAME NUMBER MANUFACTURER USE
Methyl n-Propyl Ketone Clean metal parts.
Solvent Blend Desoclean 110 PRC-DeSoto International Clean metal parts.
5426 San Fernando Rd.
Glendale, CA 91209
Paint Stripper T-6776 LO Turco Products, Inc. Strip paint from metal parts
Westminster 92684 prior to inspection.
CA
Naptha MIL-PRF-680 (Type Commercially Available Metal parts cleaning that
III) require soak cleaning.
Protective Oil Oakite Special Oakite Products Inc. Protect metal surfaces that
Protective Oil 50 Valley Road have had paint removed.
Berkeley Heights, NJ 07922
Hydraulic Assembly MCS 352 Aviation Fluids Service Co. Protect surfaces normally in
Lubricant St. Louis, MO 63166 contact with hydraulic fluid.
B. Cleaning.
WARNING: Use cleaning solvents only in well ventilated areas. Avoid inhaling solvent vapors. Keep solvent
and solvent containers away from spark or open flame.
(1) Clean metal parts with a approved solvent. Remove stubborn deposits by hand-rubbing with nonabrasive pads or
material. Apply solvent under pressure to all lubrication fittings, channels and other internal cavities to ensure
cleanliness. Thoroughly dry all parts with filtered, dry, compressed air; lint-free cloth or lint-free disposable tissue.
(2) Labels or identification plates which are attached by adhesive, shall be removed by lifting the corner and pulling free.
Remove adhesive with clean cloth dipped in cleaning solvent.
(3) Apply paint stripper on painted parts following the recommended manufacturer’s instructions. Allow the first
application to work from 5 to 45 minutes or as advised by manufacturer's instructions. If necessary, scrub softened
areas with brush to loosen paint. Rinse with water. Repeat as necessary to remove all paint. After paint is completely
removed, rinse part thoroughly with water spray. Dry part with filtered, dry, compressed air and a lint-free cloth or lint-
free disposable tissue.
WARNING: All paint strippers are harmful to eyes and skin. Operators shall wear goggle-type glasses, rubber
gloves, aprons and boots. In case of contact with skin, flush with water. In case of contact with
eyes, flush eyes thoroughly with water and consult a physician immediately. Paint stripping shall
be done in a well ventilated area. Follow manufacturer's instructions carefully to release pressure
before opening paint stripper storage containers.
(4) After drying, coat all parts that would normally come in contact with hydraulic fluid during operation, with clean
hydraulic fluid. External metal surfaces or other parts not coming in contact with hydraulic fluid during operation of the
strut need not be coated. However, highly machined surfaces may be coated with hydraulic fluid or other suitable
protective coating.
(5) If checking and repair procedures do not immediately follow cleaning, coat all surfaces that have had paint removed
with a suitable protective oil.

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Model 500 Series Component Maintenance Manual (Rev 17)
32-10-03-5 (Rev 7)

MAIN GEAR ASSEMBLY - CHECK

1. Check
A. Recommended Checking Methods.
(1) Consult Table 501 to determine the recommended method of checking each component.
(2) Check all parts visually under strong light for surface cracks, flaws, burrs, pitting, scoring or any other wear.
(3) Replace all parts showing cracks or flaws under dye penetrant, magnetic particle or visual inspection.
(4) Check all bolts, nuts and screw threads, both external and internal, for evidence of stripping or scoring. Replace all
parts that have stripped threads.
(5) Check shafts and pins for ovaling, or other signs of wear.
Table 501. Recommended Inspection
Nomenclature (Item Method of Check For Requirement
Number Same as Checking
Illustrated Parts List
Number)
Barrel (6), (12) Visual Wear, damage No damage or wear that would
endanger structure or interfere with
function.
Air valve (4) Visual Damage, stripped threads No damage or stripped threads.
Link Pin (77) Visual Ovaling or other damage Must meet dimensions given in Fits and
Clearances.

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Model 500 Series Component Maintenance Manual (Rev 17)
32-10-03-6 (Rev 17)

MAIN GEAR ASSEMBLY - REPAIR

1. Repair
A. Finish.
NAME NUMBER MANUFACTURER USE
Color Chemical Film Alodine 1132 Henkel (Parker Amchem) Protective treatment of
Treatment 32100 Stephenson Highway aluminum
Madison Heights, MI 48071
Color Chemical Film Alodine 1203 Henkel (Parker Amchem) Protective treatment of
Treatment aluminum
(1) For cleaning oleo, refer to Main Gear Assembly - Cleaning; for parts replacement, refer to Main Gear - Assembly.
B. Allowable damage.
(1) Dents or dings in the piston surface, to a maximum of five, may be blended out and refinished if the maximum depth
of penetration does not exceed 0.015 inches (0.381 mm).
(2) Scratches which do not exceed three inches (76 mm) length or 0.015 inches (0.381 mm) depth may be blended out
and refinished.
C. Blending procedure.
(1) Dents or dings must be blended out in a ratio of 5:1 length and width to depth.
6
(2) Surface finish of blended area must be better than 16 microinches RMS (4.06 X 10- m).
D. Axle Adaptor Repair
(1) If the axle adaptor has corrosion that cannot be removed with Scotch Brite, there is an optional repair available that
uses a Cessna controlled process. This process can remove the corrosion and build up the axle adaptor with hard
chrome plating. For more details, contact Cessna Customer Services - Structures.
NOTE: No material is allowed to be removed from the original diameter of 2.497 inches (63.246 mm) on the
trailing link gear due to production shot peening process and design specifications for that area.
The optional repair is the only way to remove corrosion and return the link to service.
NOTE: You can remove the corrosion pits from the axle adaptor area only on the non-trailing link gear
assemblies.
E. Painting.
(1) Preliminary.
(a) Fully clean the dirt, oil, grease, and/or corrosion from the areas before you paint them.
(b) Do not paint the tires, strut air valves, data plates, bearings, polished pistons, switches, wire bundles, clamps,
hydraulic hoses, wheels, axle spindle area in the wheels, or areas that touch the lower to upper torque links.
(c) Prepare and paint the wheels that you remove in accordance with Goodyear Wheel and Brake Components
Maintenance Manual.
(2) Pretreatment Primer.
(a) Mix and apply DOD-P-15328 pretreatment primer in accordance with the manufacturer’s instructions.
(3) Corrosion-Resistant Primer
(a) Mix and apply MIL-PRF-23377 corrosion-resistant primer in accordance with the manufacturer's instructions.
(4) Topcoat.
(a) Mix and apply the topcoat in accordance with the manufacturer’s instructions.
F. Axle External Corrosion Inspection, Removal and Prevention.
NOTE: This procedure applies to the external areas of the axle in the areas where the brake assembly
makes contact.
(1) Inspection of Axle.
(a) Inspect the axle in the area shown for damage to the finish and corrosion. If the finish is not damaged and no
corrosion exists, no further action is required. Refer to Figure 601. If corrosion is present on the axle, proceed to

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Model 500 Series Component Maintenance Manual (Rev 17)
32-10-03-6 (Rev 17)

step (2), Rework of Axle. If the finish is damaged, but no corrosion exists, proceed to step (5), Finish
Application.
(2) Rework of Axle.
(a) Determine if the axle can be reworked (refer to Figure 601):
1 Using a steel wire brush, remove the loose corrosion from the axle in the area between the piston axle
adaptor and the area where the inboard wheel bearing and seal were located. Clean the axle with
approved solvent to remove all grease and dirt. Using a vernier micrometer, measure the diameter of the
axle and determine the average axle diameter.
NOTE: Average axle diameter is determined by measuring the axle at four different locations,
oriented 45 degrees apart, and averaging the four measurements.
a If the average axle diameter is less than 1.8095 inches (45.961 mm), the axle must be replaced.
b If the average axle diameter is 1.8095 inches (45.961 mm) or greater, proceed with reworking
instructions.
NOTE: If the axle surface contains pits which remain after corrosion removal and it is
estimated that upon removal of these pits, the axle may not meet the absolute
minimum average diameter of 1.8020 inches (45.770 mm), it may not be feasible
to attempt to rework the axle since it is possible that the axle may require
replacement.
(3) Rework of Axle.
(a) Wrap a piece of thin (0.012 or 0.016) aluminum sheet, 5.70 X 1.0 inches (144.78 X 25.4 mm), around the axle
and secure in place with a worm-type hose clamp to protect the portion of the axle where the inboard bearing
and seal were located.
CAUTION: It is very important to preserve the axle radius at the inboard edge of the rework area. When
using the emery cloth, do not allow the edge of the emery cloth to form a groove in the radius;
instead, allow the emery cloth to ride up into the radius.
(b) Using an 0.75 inches (19.05 mm) wide strip of 320 grit (aluminum oxide) emery cloth, remove all corrosion on
the axle (between the piston axle adaptor and protected area). All corrosion, including any pitting of the metal,
must be removed. After all pits are removed, apply a final finish to the axle with 400 grit emery cloth (aluminum
oxide).
(c) Remove the aluminum sheet protecting the axle and ensure all corrosion is removed up to the area where the
bearing seal was making contact with the axle. Remove any remaining corrosion with 400 grit emery cloth but
use minimum pressure when sanding over the seal area.
(d) Clean the area with solvent and measure the diameter of the axle in the reworked area at four locations oriented
45 degrees apart and determine the average axle diameter. If the average axle diameter is less than 1.8020
inches (45.770 mm), the axle must be replaced. Refer to Main Gear Assembly - Disassembly and Main Gear
Assembly - Assembly, for axle replacement instructions. If the average axle diameter is 1.8020 (45.770 mm) or
greater, proceed with application of finish. Refer to step (5), Finish Application.
NOTE: Small local areas of the axle may indicate as small as 1.8000 inches (45.770 mm) diameter
at any one location, but the average axle diameter must still be a minimum of 1.8020
inches (45.770 mm) diameter.
(4) Finish Application.
NOTE: MIL-PRF-23377 corrosion resistant primer must be applied to clean surfaces within 30 minutes
of completion of sanding procedure. An oxide film which provides minimal adhesion for MIL-
PRF-23377 corrosion resistant primer begins to form immediately after working. Poorly
adhered MIL-PRF-23377 corrosion resistant primer will result in accelerated corrosion.
(a) Clean the axle with approved solvent and wipe dry.
(b) Mask off areas of the piston not reworked.
(c) Mask off the outboard portion of the axle from the inboard wheel bearing seal. Ensure masking covers the
inboard wheel bearing seal contact point so that the seal does not ride on the MIL-PRF-23377 corrosion
resistant primer.

Copyright © Textron Aviation Inc. Page 2 of 5

(d) Apply MIL-PRF-23377 corrosion resistant primer to the piston axle adaptor and/or the axle. For application and
mixing instructions for MIL-PRF-23377 corrosion resistant primer, refer to the manufacturer’s instructions.
(e) Apply a thin film of wheel bearing grease to the outer surface of axle as a corrosion preventative treatment.

Copyright © Textron Aviation Inc. Page 3 of 5

Figure 601 : Sheet 1 : Main Landing Gear Axle Inspection

A83933

INSPECTION AREA ON AXLE

5641T1068

Copyright © Textron Aviation Inc. Page 4 of 5

Figure 601 : Sheet 2 : Main Landing Gear Axle Inspection

A83982
CAUTION: MAKE SURE THAT YOU KEEP AN
SAFETY WIRE AXLE RADIUS OF 0.38 INCHES AS
(REFERENCE) YOU REMOVE THE CORROSION
NAS561P8-8
PIN FROM THE AXLE. THIS IS DEFINED
(REFERENCE) IN THE ACCOMPLISHMENT
INSTRUCTIONS.

1.16 INCH +0.5 OR -0.05 INCH

B
ALUMINUM SHEET

B
WHEEL BEARING AXLE
AND SEAL AREA (REFERENCE)
PISTON AXLE
ADAPTER
(REFERENCE) THE MINIMUM AVERAGE DIAMETER
IS 1.8095 INCHES FOR REWORK.
THE MIMIMUM AVERAGE DIAMETER IS
1.8020 INCHES AFTER THE REWORK IS
COMPLETED.(NOTE)

VIEWA-A
45Â°

A
D B

C C

B D
NOTE: THE AXLE IS MEASURED AT FOUR
LOCATIONS 45 DEGREES APART TO A
FIND THE AVERAGE AXLE DIAMETER.
SEE VIEW B-B. VIEW B-B
MEASUREMENT LOCATIONS FOR THE AXLE
AA5641T1069
BB5641T1069

Copyright © Textron Aviation Inc. Page 5 of 5

MAIN GEAR ASSEMBLY - ASSEMBLY

1. Landing Gear Assembly
A. Tools and Equipment (refer to `Illustrated Parts List).
NAME NUMBER MANUFACTURER USE
Safety Wire Monel 0.020 inch Commercially available Safety air valve and cylinder.
diameter
Loctite 680 Loctite Corporation Secure squat switch support
705 N. Mountain Road and bearings.
Newington, CT 06111
Loctite 242 Loctite Corporation To assemble the orifice fitting
Loctite 243 Loctite Corporation To assemble the orifice fitting
Loctite 277 Loctite Corporation Assemble oleo.
Locquic Primer T 7471 Loctite Corporation To clean and prepare parts for
an application of thread locking
material.
Loctite Clover Silicon Grade C, 220 Grit Loctite Corporation To deburr threaded
Carbide Grease Mix components
Sealant MIL-S-8802 Type I, PRC-DeSoto International Dissimilar materials protection.
Class B 5454 SanFernando Road
Glendala, CA 91203
Pretreatment Primer 728-013/702-701 Sherwin-Williams Inc Pretreatment primer
DOD-P-15328 16116 E. 13th Street
Andover, KS 67002
Corrosion Resistant 513 x 419/ 910 x PRC-DeSoto International Corrosion protection primer.
Primer MIL-PRF- 942 5426 San Fernando Rd.
23377G or later Glendale, CA 91209
Corrosion Resistant 02-Y-40 02-4-40 Deft, Inc. Corrosion protection primer.
Primer MIL-PRF- CATA 17151 Von Karman Ave.
23377G or later Irvine, CA 92714
Corrosion Resistant U-1201F/ U-1202F Sterling Laquer Manufacturing Co. Corrosion protection primer.
Primer MIL-PRF- 3150 Brannon St.
23377G or later St. Louis, MO 63139
Corrosion Resistant R4001-K14MAX U.S. Paint Corp Corrosion protection primer.
Primer MIL-PRF- COR 831 South 21st St.
23377G or later St. Louis, MO 63130
Polyurethane paint, 7400 (Color Name: U.S. Paint Corp. Finish paint.
medium gray Pewter)
B. Assemble Gear (Refer to Main Landing Gear Assembly, Figure 1001).
(1) Apply Loctite 680 to bore of trunnion (18) and install squat switch support bracket (5).
(2) Install bushings (20), (21) and (79) wet by pressing into trunnion using wet epoxy primer.
(3) Press axle (94) into bore of trailing link (85) using MIL-PRF-23377 corrosion resistant primer, ensuring that the hole
for bolt (95) is properly aligned.
(4) Press bolt (95) into trailing link (85) and axle (94) using MIL-PRF-23377 corrosion resistant primer, and secure with
washer (96) and nut (97).
(5) Install pivot pin (77), thrust bearings (80) spacer (78), to secure trailing link (85) to trunnion (18).
(6) Ensure head of pivot pin (77) is tight against trunnion (18).
(7) Turn nut (82), finger tight against opposite side of trunnion, back nut off to first cotter pin hole and secure with cotter

Copyright © Textron Aviation Inc. Page 1 of 2

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Model 500 Series Component Maintenance Manual (Rev 17)
32-10-03-7 (Rev 14)

pins (83).
(8) Install ramp pin (6) with holding slot parallel to the spacer (78) and secure with washer (7), nut (8) and cotter pin (9).
(9) Install oleo assembly (10).
(a) Install bolt (11) washer (13) under nut, washer (14) under bolt head, washer (15) between oleo bearing and aft
bushing (21), nut (16) and cotter pin (17) to secure upper end of oleo.
(b) Install bolt (12), washer (13) under nut, washer (14) under bolt head, nut (16) and cotter pin (17) to secure lower
end of oleo.
(10) Bond cover (86) in place using MIL-S-8802 Type I Class B sealant.
(11) Bond plug buttons (83) in place using MIL-S-8802 Type I Class B sealant.
2. Oleo Assembly
A. Assemble Oleo. Refer to Oleo Assembly - Main Gear, Figure 1002.
(1) Press bearings (2) into caps (3) and (18) with Loctite 680 and stake bearings in place.
(2) Install a new O-ring (7) in upper cap (3) and then apply Loctite 277 to threads of cap (2).
(3) Secure the lug of the upper cap (3) in a padded vise and install the upper barrel (6) in the cap, torquing to 50 foot-
pounds (67.8 N.m) taking care not to scratch the outer surface of the upper barrel.
(4) Install metering pin (13) in lower cap (18) using Loctite 277 and torque to 125 inch-pounds (14.1 N.m).
(5) Install an new O-ring (17) on lower cap (18) and then apply Loctite 277 to threads of cap (18).
(6) Secure the lug of the lower cap (18) in a padded vise and install the lower barrel (12) in the cap, torquing to 50 foot-
pounds (67.8 N.m).
(7) Install scraper (8) into outer bearing (9).
(8) Verify that filter (10) is installed in outer bearing (9) and is not clogged.
(9) Slip outer bearing (9) and inner bearing (11) onto upper barrel (6).
(10) Temporarily screw the orifice fitting (15) into the lower end of the upper barrel (6).
(a) If the orifice fitting does not turn easily and smoothly, do the following:
1 Apply Loctite Clover Silicon Carbide Grease Mix Grade A, Grit 220 to the threads of the orifice fitting.
2 Install and remove the orifice fitting several times to clean and deburr the threads of the orifice fitting and
upper barrel.
3 Thoroughly clean and dry the orifice fitting and upper barrel to make sure all of the silicon carbide grease is
removed.
4 Screw the orifice fitting into the lower end of the upper barrel to make sure it installs easily and smoothly.
5 Repeat the procedure as needed until the threads install smoothly.
(11) Remove the orifice fitting (15) from the lower end of the upper barrel (6).
(12) Install the T-seal (16) in the groove of the orifice fitting (14).
(13) Install the O-ring (15) at the base of the threads on the orifice fitting (14).
(14) Apply Locquic Primer T 7471 to the threads of the orifice fitting (15), and to the lower end of the upper barrel (6).
(15) Apply Loctite 242 or 243 to threads of orifice fitting (14), and lower end of upper barrel (6).
(16) Immediately screw orifice fitting (14) into lower end of upper barrel (6) and torque to 50 foot-pounds (67.8 N.m).
(17) Use a spanner wrench to install outer bearing (9) to lower barrel (12) and torque to 50 foot-pounds (67.8 N.m).
(18) Safety wire outer bearing (9) to lower barrel (12).
(19) If placards (19, 20, or 21) on Oleo (1) or (99) on trailing link (85) require replacement, bond with MIL-S-8802 Type I
Class B sealant, and overcoat with a minimum of two coats of clear urethane enamel, overlapping the edges of the
placard by a minimum of 0.50 inch (12.7 mm).

Copyright © Textron Aviation Inc. Page 2 of 2

MAIN GEAR ASSEMBLY - FITS AND CLEARANCES

1. Fits and Clearances
A. Link Pivot Pin 6541430-1
A84635

(3) (1)

(2)

6541430

(1) 1.4975 inch, +0.0005 or -0.0005 inch (38.0365 mm, +0.0127 or -0.0127 mm) diameter
(2) 6.639 inch, (168.631 mm) diameter
(3) 0.192 inch, +0.002 or -0.002 inch (4.877 mm, +0.051 or -0.051 mm) diameter
B. Oleo Upper Barrel 6541423-1, -2, -3
A84637

(2) (1) (3)

6541T1055

(1) 3.122 inch, +0.001 or -0.001 inch (79.299 mm, +0.0254 or -0.0254 mm) diameter
(2) 3.145 inch, (79.883 mm) diameter
(3) 2.902 inch, (73.711 mm) diameter
C. Oleo Lower Barrel 6541424-1
A84636

(2) (1) (3)

6541T1054

(1) 3.471 inch, (88.163 mm) diameter

(2) 3.251 inch, +0.001 or -0.001 inch (82.575 mm, +0.0254 or -0.0254 mm) diameter (16 RA surface finish)
(3) 3.630 inch, (92.202 mm) diameter

Copyright © Textron Aviation Inc. Page 1 of 1

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Model 500 Series Component Maintenance Manual (Rev 17)
32-10-03-1001 (Rev 16)

MAIN LANDING GEAR ASSEMBLY

NOMENCLATURE EFFECTIVITY UNITS
PER
ITEM PART NUMBER 1 2 3 4 5 6 7 FROM TO ASSY
- MAIN LANDING GEAR ASSEMBLY
- 1 6541410-1 . GEAR ASSY-LH A 01
- 1A 6541410-3 . GEAR ASSY-LH B 01
- . GEAR ASSY-LH FSO
1B 6541410-5 C NP
6541410-9
- 1C 6541410-7 . GEAR ASSY-LH D 01
- 1D 6541410-9 . GEAR ASSY-LH E 01

- . GEAR ASSY-LH FSO

1E 6541410-11 F NP
6541410-13
- 1F 6541410-13 . GEAR ASSY-LH G 01
- 2 6541410-2 . GEAR ASSY-RH A 01
- 2A 6541410-4 . GEAR ASSY-RH B 01
GEAR ASSY-RH FSO
- 2B 6541410-6 . C NP
6541410-10
- 2C 6541410-8 . GEAR ASSY-RH D 01
- 2D 6541410-10 . GEAR ASSY-RH E 01

- . GEAR ASSY-RH FSO

2E 6541410-12 F NP
6541410-14
- 2F 6541410-14 . GEAR ASSY-RH G 01

3 S3176-2 . . SWITCH-SQUAT LH 01
SG007

- 4 S3176-2 . . SWITCH-SQUAT RH 01
SG007
5 5941164-1 . . BRACKET-SWITCH A 01
- 5A 6641618-11 . . BRACKET-SWITCH B thru F 01
6 5941163-3 . . PIN-LH AND RH 02

7 NAS1149F0332P . . WASHER-LH AND RH 02

UNDER NUT
8 MS17826-3 . . NUT-LH AND RH 02

. . COTTER PIN-LH AND

9 MS24665-134 02
RH
OLEO ASSY-LH AND
10 . . RH REFER TO RF
FIGURE 1002
ATTACHING
PARTS

11 NAS6212-40D . . BOLT-UPPER FSO A NP

S3461-99
- 11A S3461-99 . . BOLT-UPPER B thru F 01

12 NAS6212-26D . . BOLT-LOWER FSO A NP

S3461-96

Copyright © Textron Aviation Inc. Page 1 of 6

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Model 500 Series Component Maintenance Manual (Rev 17)
32-10-03-1001 (Rev 16)

- 12A S3461-96 . . BOLT-LOWER B thru F 01

- 12B 6641640-55 . . SCUFF SHIELD C thru F 02
WASHER-UPPER
13 NAS1149F1290P . . AND LOWER UNDER 02
NUT
WASHER-UPPER
14 NAS1149F1232P . . AND LOWER UNDER 02
BOLT HEAD
WASHER-UPPER
. . BETWEEN OLEO
15 NAS1149F1232P 01
BEARING AND
BUSHING
. . NUT-UPPER AND
16 MS17826-12 02
LOWER

. . COTTER PIN-UPPER
17 MS24665-357 02
AND LOWER
---*---

. . TRUNNION-LH FSO
18 6541460-1 NP R
6594022-1
TRUNNION-LH FOR
- 18A 6594022-1 . . A thru G 01 R
SPARES ONLY
- . . TRUNNION-RH FSO
19 6541460-2 NP R
6594022-2
- . . TRUNNION-RH FOR
19A 6594022-2 A thru G 01 R
SPARES ONLY
20 NAS77-12-045 . . BUSHING-LH AND RH 02
21 NAS77-12-065 . . BUSHING-UPPER 02

NOMENCLATURE EFFECTIVITY UNITS

PER
ITEM PART NUMBER 1 2 3 4 5 6 7 FROM TO ASSY
- MAIN LANDING GEAR ASSEMBLY
- 75 6541435-1 . . TRAILING LINK ASSY- A,B,C NP
LH FSO 6541435-205
- . . TRAILING LINK ASSY-
75A 6541435-9 D,E,F NP
LH FSO 6541435-205
TRAILING LINK ASSY-
- 75B 6541435-11 . . A THRU G NP
LH FSO 6541435-205
- . . TRAILING LINK ASSY-
75C 6541435-203 A THRU G NP
LH FSO 6541435-205
- . . TRAILING LINK ASSY-
75D 6541435-205 A THRU G 01
LH FOR SPARES ONLY
TRAILING LINK ASSY-
- 76 6541435-2 . . A,B,C NP
RH FSO 6541435-206

Copyright © Textron Aviation Inc. Page 2 of 6

Copyright © Textron Aviation Inc. Page 3 of 6

. . . SWITCH STRIKE
90 6541435-6 02
PLATE-LH AND RH
91 MS17826-6 . . . NUT-LH AND RH 02
. . . COTTER PIN-LH
92 MS24665-283 02
AND RH
BUSHING-LH AND
93 NAS77-12-020 . . . 02
RH
. . . AXLE-LH AND RH
94 6541417-1 NP
FSO 6541417-201
- . . . AXLE-LH AND RH
94A 6541417-201 02
FOR SPARES ONLY
ATTACHING
PARTS
95 S3461-89 . . . BOLT MPI 01
96 NAS1149F0563P . . . WASHER 01
97 MS17826-5 . . . NUT 01
98 MS24665-134 . . . COTTER PIN 01
---*---
PLUG-AXLE
- 98A 6541400-5 . . . 01
EXPANSION
99 6541435-7 . . . PLATE-S/N 01
- Item Not Illustrated

Copyright © Textron Aviation Inc. Page 4 of 6

Figure 1001 : Sheet 1 : MAIN LANDING GEAR ASSEMBLY

Copyright © Textron Aviation Inc. Page 5 of 6

Figure 1001 : Sheet 2 : MAIN LANDING GEAR ASSEMBLY

Copyright © Textron Aviation Inc. Page 6 of 6

MAIN LANDING GEAR OLEO ASSEMBLY

NOMENCLATURE EFFECTIVITY UNITS
PER
ITEM PART NUMBER 1 2 3 4 5 6 7 FROM TO ASSY
- MAIN LANDING GEAR OLEO ASSEMBLY

- . OLEO ASSY FSO

1 6541420-1 A NP R
6541420-200
- . OLEO ASSY FSO
1A 6541420-4 B NP R
6541420-200
OLEO ASSY FSO
- 1B 6541420-7 . C NP R
6541420-200
- . OLEO ASSY FSO
1C 6541420-8 D NP R
6541420-200
- 1D 6541420-200 . OLEO ASSY A,B,C,D 01 R

2 MS14102-12 . . BEARING-UPPER A 02
AND LOWER
3 6541421-1 . . UPPER CAP, OLEO A 01
- 3A 6541421-2 . . CAP ASSY-UPPER B,C 01
- 3B MS14102-12 . . . BEARING B,C,D 01
- 3B 6541421-4 . . CAP ASSY-UPPER D 01

4 HF2003 . . VALVE REFER TO V13899 01

NOTE 1

5 NAS1611-015 . . O-RING REFER TO V80205 01

NOTE 1

6 6541423-1 . . UPPER BARREL, A,B 01

OLEO

- 6A 6541423-2 . . UPPER BARREL, C 01

OLEO

- 6B 6541423-3 . . UPPER BARREL, D 01

OLEO
7 NAS1611-235 . . O-RING 01
8 S33829-338H1 . . SCRAPER V09257 A 01
- 8A S33829-338H29 . . SCRAPER V09257 B,C,D 01

. . OUTER BEARING
9 6541425-2 A 01
ASSY
OUTER BEARING
- 9A 6541425-6 . . ASSY REFER TO B,C 01
NOTE 2

- . . OUTER BEARING
9B 6541425-13 D 01
ASSY
OUTER BEARING
- 9C 6541425-15 . . ASSY-USED WITH A,B,C,D 01 R
6541420-200
10 FCR2030-2-2 . . . FILTER DISC V13778 A,B,C 01
11 6541425-1 . . INNER BEARING A 01

Copyright © Textron Aviation Inc. Page 1 of 3

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Model 500 Series Component Maintenance Manual (Rev 17)
32-10-03-1002 (Rev 14)

. . LOWER BARREL,
12 6541424-1 01
OLEO
13 6541427-1 . . METERING PIN A 01
- . . METERING PIN
13A 6541427-2 B,C,D 01
REFER TO NOTE 2
14 6541428-1 . . ORIFICE FITTING A,B 01
- 14A 6541428-2 . . ORIFICE FITTING C 01
- 14B 6541428-3 . . ORIFICE FITTING D 01
15 NAS1611-036 . . O-RING 01
16 7336MS952T . . T-SEAL V5F573 A,B 01
- 16A 733F6MS-954-T . . T-SEAL V5F573 C,D 01
17 NAS1611-236 . . O-RING 01
18 6541422-1 . . LOWER CAP, OLEO A 01
- 18A 6541422-3 . . CAP ASSY-LOWER B,C,D 01

. . PLACARD- FILLING
19 6541420-2 A 01
INSTR

- . . PLACARD- FILLING
19A 6541420-6 B,C,D 01
INSTR
. . PLACARD-P/N & S/N
20 6541420-3 01
PLATE
. . PLACARD-
21 6340002-10 01
VENT,OLEO
VALVE IS SUPPLIED WITH 0-RING. PART NUMBER IS PROVIDED IF REPLACEMENT OF O-
NOTE 1:
RING ONLY IS REQUIRED.
NOTE 2: AIRPLANES -0875 AND ON AND AIRLANES -0801 THRU -0874 INCORPORATING SB550-32-35
- Item Not Illustrated

Copyright © Textron Aviation Inc. Page 2 of 3

Figure 1002 : Sheet 1 : MAIN LANDING GEAR OLEO ASSEMBLY

Copyright © Textron Aviation Inc. Page 3 of 3

MAIN GEAR ASSEMBLY - ILLUSTRATED PARTS LIST

1. Illustrated Parts List
A. Introduction.
(1) The Illustrated Parts List will help the customer to order, keep, and supply the main landing gear components. It will
also identify new and reclaimed parts. It is not approved for any other purpose.
(2) This parts list includes the main landing gear assembly used on the Citation airplanes. Part numbers:
6541510-1 6541510-2 6541510-3 6541510-4
6541520-2 6541520-3 6541520-4 6541520-5
(3) The indention system used in the detailed parts list of this catalog shows the relationship of one part to another. For a
given item, the indention code shows a general heading at the extreme left position and continues with indented
columns until the end detail is reached as follows:
A18017
1234567
Installation
Detail Parts for Installation
Assembly
Attaching Parts for Assembly
Detail Parts for Assembly
Subassembly
Attaching Parts for Subassembly
Detail Parts for Subassembly
Sub−Subassembly
Attaching Parts for Sub−Subassembly
Detail Parts for Sub−Subassembly

Basic Number Dash Number

(Drawing Identification
Only)

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Model 500 Series Component Maintenance Manual (Rev 17)
32-10-04-0 (Rev 14)

MAIN GEAR ASSEMBLY - DESCRIPTION AND OPERATION

1. Description
A. The main gear assembly is designed and assembled to permit maneuverability of the airplane on the ground and to retract
into the wing when airborne. It is designed to absorb shock during airplane takeoffs, landings and taxiing. The main gear
assembly consists of a trunnion, trailing link, axle and oleo. Refer to Figure 1 and Figure 2.
(1) The trunnion is mounted in the wing wheel well with trunnion pins to allow the gear assembly to retract into the wing.
(2) The oleo consists of an upper and lower barrel with a metering pin and orifice to control the flow of hydraulic fluid from
one chamber to the other during oleo extension and compression. The oleo is filled with hydraulic oil with the oleo
compressed and then charged with compressed dry nitrogen. The fluid and nitrogen are not separated but are
contained in the same chamber.
(3) The axle is installed in the trailing link assembly press fitted and secured with a bolt.
(4) The following main gear assembly part numbers are affected by this Section are:
6541510-1 6541510-2 6541510-3 6541510-4
6541520-2 6541520-3 6541520-4 6541520-5
2. Operation
A. As weight of the airplane is applied to the main gear assembly, the lower barrel of the oleo assembly is forced to slide into
the upper barrel. This movement forces hydraulic fluid to flow from the upper chamber through an orifice in the bottom of
the upper barrel into the upper barrel. The restricted fluid flow and the resistance of the compressed air/nitrogen in the
upper portion of the barrel dampens the movement of the oleo assembly and absorbs compression shocks. As the weight
of the airplane is removed from the main gear assembly, the compressed air/nitrogen forces the hydraulic fluid back
through the orifice. This expansion and controlled flow of hydraulic fluid causes the oleo to extend. Refer to Figure 3.
3. Personnel Safety Precautions - Hydraulic Fluid
A. The oleo assembly contains phosphate ester base hydraulic fluid. Before performing maintenance or any operation on the
oleo assembly, personnel should read and thoroughly understand this warning.
WARNING: Observe the following safety precautions when working on systems containing phosphate ester
base fluid. Prolonged exposure to the fluid can cause skin dehydration and chapping.
(1) Wash hands thoroughly with soap and water before starting work; apply barrier cream (silicone hand cream) to
hands, wrists and forearms. Rub cream under fingernails and into creases of skin.
(2) Wear eye goggles when pressure testing components or systems or anytime there is a possibility of hydraulic fluid
spraying/splashing in the eyes.
(3) If hydraulic fluid enters the eyes, treat eyes immediately by irrigating thoroughly with clear, cold water.
(4) Wash hands, wrists and forearms with soap and warm water after contacting hydraulic fluid.
(5) !f clothing becomes soaked with hydraulic fluid, remove the clothing as soon as possible. Wash hydraulic fluid
exposed skin with soap and warm water. Wash hydraulic fluid contaminated clothes before wearing.
4. Technical Safety Precautions - Hydraulic Fluid
A. Because the oleo contains phosphate ester base hydraulic fluid, improper maintenance practices can be damaging to
gear components and other equipment. Before performing maintenance or any operation on the oleo assembly, personnel
should read and thoroughly understand the following technical precautions.
CAUTION: Phosphate ester base hydraulic fluid will damage and/or deteriorate a wide range of materials,
including rubber, copper, various plastics and paints.
(1) Make sure that hydraulic fluid does not come in contact with any part of the component outside of the oleo. Keep
spillage to an absolute minimum. Clean up spilled hydraulic fluid immediately to prevent contamination of non-
hydraulic components and to avoid false hydraulic leak detections. If spillage occurs, wipe up the fluid with a dry cloth
and wash area with naptha MIL-PRF-680, (Type III) or Methyl n-Propyl Ketone.
(2) When gear components are disassembled, provide suitable protection for preventing entry of foreign material by
using caps and/or covers.
(3) Always check angle and position of components prior to disassembly to ensure proper alignment and placement of
components and hardware during assembly or replacement.

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Model 500 Series Component Maintenance Manual (Rev 17)
32-10-04-0 (Rev 14)

(4) Use naptha MIL-PRF-680, (Type III) or Methyl n-Propyl Ketone, when washing metal parts prior to assembly. Make
sure all traces of the cleaning agent are removed before assembly.
(5) Use only clean hydraulic fluid for flushing or testing hydraulic components.
(6) Do not unpack seals, O-rings/packings until they are required and make sure that only correct and approved seals, O-
rings/packings are used.
(7) When assembling the gear shock strut hydraulic seals and O-rings/packings, lubricate only with phosphate ester
base hydraulic fluid. Always lubricate seals, O-rings/packings immediately before installation. Threaded fittings
should be assembled without the use of lubricants whenever possible. If a lubricant is required to prevent galling or to
otherwise ease installation, use phosphate ester base hydraulic fluid or VV- P-236 Petrolatum.
CAUTION: Take special care not to contaminate seals, o-rings/ packings after lubrication.
CAUTION: Prevent contamination of phosphate ester base hydraulic fluid with other hydraulic fluids, oil, water
or dirt.

Copyright © Textron Aviation Inc. Page 2 of 5

Figure 1 : Sheet 1 : Main Landing Gear Assembly

A84049

Trunnion

Link Assembly
Oleo Assembly

Axle

5541T1017

Copyright © Textron Aviation Inc. Page 3 of 5

Figure 2 : Sheet 1 : Main Landing Gear Oleo Assembly

Copyright © Textron Aviation Inc. Page 4 of 5

Figure 3 : Sheet 1 : Main Landing Gear Oleo Operation

Copyright © Textron Aviation Inc. Page 5 of 5

MAIN GEAR ASSEMBLY - TESTING

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Model 500 Series Component Maintenance Manual (Rev 17)
32-10-04-3 (Rev 14)

MAIN GEAR ASSEMBLY - DISASSEMBLY

1. Landing Gear Disassembly
A. Preparation for Disassembly (Refer to Illustrated Parts List).
(1) Rotate 0.625 inch hex nut on air valve (4) counterclockwise one and one-half turns to lift internal valve poppet, then
release any trapped gas or liquid by depressing valve core.
WARNING: Do not stand in front of valve assembly while releasing gas pressure. Do not turn 0.75 inch hex nut
while releasing gas pressure. Removing air valve without releasing compressed gas can cause
bodily injury.
(2) Ensure that gas is released by sliding upper barrel in and out of lower barrel.
B. Disassemble Gear. Refer to Main Landing Gear Assembly, Figure 1001.
(1) Remove oleo assembly (31).
(a) Remove cotter pin (30), nut (29), bolt (26) and washers (27) securing upper end of oleo.
(b) Remove cotter pin (35), nut (34), bolt (32), and washers (33), securing lower end of oleo.
(2) Remove trailing link (75).
(a) Remove cotter pins (81), nut (80), pivot pin (77), thrust bearings (78) and spacer (82) securing trailing link (75) to
trunnion (16A).
(3) Remove bushings (79) by pressing out of trunnion.
(4) Remove squat switch support bracket (18) by driving out of bore of trunnion (16A).
NOTE: Bracket (18) is secured with Loctite 680.
2. Oleo Disassembly
A. Preparation for Disassembly. Refer to Oleo Assembly - Main Gear, Figure 1002.
(1) Rotate 0.75 inch hex nut on air valve (4) counterclockwise one and one-half turns to lift internal valve poppit, to release
any trapped gas or liquid.
WARNING: Do not stand in front of valve assembly while releasing gas pressure. Do not turn 0.75 inch hex nut
while releasing gas pressure. Removing air valve without releasing compressed gas can cause
bodily injury.
(2) Ensure that gas is released by sliding piston in and out of cylinder.
(3) Cut lockwire and remove air valve (4) and O-ring (5) from piston assembly.
(4) Drain hydraulic fluid by inverting oleo assembly.
B. Disassemble Oleo.
NOTE: Perform only those portions of this disassembly procedure as are necessary to remove the
component which is damaged or requires replacement.
(1) Cut safety wire securing outer bearing (9) to lower barrel (13).
(2) Use a spanner wrench to remove outer bearing (9) from lower barrel (13).
(3) Separate upper (6) and lower barrel (13).
(4) Remove orifice (15) from upper barrel (6).
(5) Secure the lug of the lower cap (19) in a padded vise and remove lower barrel (13) from lower cap (19).
NOTE: Lower cap is installed using Loctite 277 adhesive. To loosen bond, it may be necessary to
apply heat to joint to soften the adhesive bond.
(6) Remove metering pin (14) from lower cap (19).
NOTE: Metering pin is installed using Loctite 242 or Loctite 243 adhesive. To loosen bond, it may be
necessary to apply heat to joint to soften the adhesive bond.
(7) Secure the lug of the upper cap (3) in a padded vise and remove upper cap from the upper barrel (6).
NOTE: Upper cap is installed using Loctite 277 adhesive. To loosen bond, it may be necessary to
apply heat to joint to soften the adhesive bond.
(8) Press bearings (2) out of caps (3) and (19) using a suitable arbor press.

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Model 500 Series Component Maintenance Manual (Rev 17)
32-10-04-4 (Rev 12)

MAIN GEAR ASSEMBLY - CLEANING

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Model 500 Series Component Maintenance Manual (Rev 17)
32-10-04-5 (Rev 9)

MAIN GEAR ASSEMBLY - CHECK

1. Check
A. Recommended Checking Methods.
(1) Consult Table 501 to determine the recommended method of checking each component.
(2) Check all parts visually under strong light for surface cracks, flaws, burrs, pitting, scoring or any other wear.
(3) Replace all parts showing cracks or flaws under dye penetrant, magnetic particle or visual inspection.
(4) Check all bolts, nuts and screw threads, both external and internal, for evidence of stripping or scoring. Replace all
parts that have stripped threads.
(5) Check shafts and pins for ovaling, or other signs of wear.
Table 501. Recommended Inspection
Nomenclature (Item Method of Check For Requirement
Number Same as Checking
Illustrated Parts List
Number)
Barrel (6), (13) Visual Wear, damage No damage or wear that would
endanger structure or interfere with
function.
Air valve (4) Visual Damage, stripped threads No damage or stripped threads.
Link Pin (77) Visual Ovaling or other damage Must meet dimensions given in Fits and
Clearances.

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Model 500 Series Component Maintenance Manual (Rev 17)
32-10-04-6 (Rev 17)

MAIN GEAR ASSEMBLY - REPAIR

1. Repair
A. Finish.
NAME NUMBER MANUFACTURER USE
Color Chemical Film Alodine 1132 Henkel (Parker Amchem) Protective treatment of
Treatment 32100 Stephenson Highway aluminum
Madison Heights, MI 48071
Color Chemical Film Alodine 1203 Henkel (Parker Amchem) Protective treatment of
Treatment aluminum
(1) For cleaning oleo, refer to Main Gear Assembly - Cleaning; for parts replacement, refer to Main Gear - Assembly.
B. Allowable damage.
(1) A maximum of five dents or dings in the piston surface may be blended out and refinished.
(a) The maximum depth of penetration must not exceed 0.015 inches (0.381 mm).
(2) Scratches which do not exceed three inches (76 mm) length or 0.015 inches (0.381 mm) depth may be blended out
and refinished.
C. Blending procedure.
(1) Dents or dings must be blended out in a ratio of 5:1 length and width to depth.
6
(2) Surface finish of blended area must be better than 16 microinches RMS (4.06 X 10- m).
D. Phenolic Scuff Shield Replacement
(1) Heat the area using a heat gun to soften the adhesive.
(2) Scrape phenolic from surface using a blunt scraper.
(3) Smooth the remaining adhesive using aluminum oxide paper. Do not attempt to remove all adhesive from the trailing
link lugs.
(4) Apply a thin layer of EA9309.3NA adhesive to the phenolic scuff shield, and apply the shield to the trailing link lug.
(5) Allow the adhesive to cure.
(6) Remove any squeezed out adhesive.
E. Axle External Corrosion Inspection, Removal and Prevention.
NOTE: This procedure applies to the external areas of the axle in the areas where the brake assembly
makes contact.
(1) Inspection of Axle.
(a) Inspect the axle in the area shown for damage to the finish and corrosion. If the finish is not damaged and no
corrosion exists, no further action is required. Refer to Figure 601. If corrosion is present on the axle, proceed to
step (2), Rework of Axle. If the finish is damaged, but no corrosion exists, proceed to step (5), Finish
Application.
(2) Rework of Axle.
(a) Determine if the axle can be reworked (refer to Figure 601):
1 Using a steel wire brush, remove the loose corrosion from the axle in the area between the piston axle
adaptor and the area where the inboard wheel bearing and seal were located. Clean the axle with
approved solvent to remove all grease and dirt. Using a vernier micrometer, measure the diameter of the
axle and determine the average axle diameter.
NOTE: Average axle diameter is determined by measuring the axle at four different locations,
oriented 45 degrees apart, and averaging the four measurements.
a If the average axle diameter is less than 1.8095 inches (45.961 mm), the axle must be replaced.
b If the average axle diameter is 1.8095 inches (45.961 mm) or greater, proceed with reworking
instructions.
NOTE: If the axle surface contains pits which remain after corrosion removal and it is

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Model 500 Series Component Maintenance Manual (Rev 17)
32-10-04-6 (Rev 17)

estimated that upon removal of these pits, the axle may not meet the absolute
minimum average diameter of 1.8020 inches (45.770 mm), it may not be feasible
to attempt to rework the axle since it is possible that the axle may require
replacement.
(3) Rework of Axle.
(a) Wrap a piece of thin (0.012 or 0.016) aluminum sheet, 5.70 X 1.0 inches (144.78 X 25.4 mm), around the axle
and secure in place with a worm-type hose clamp to protect the portion of the axle where the inboard bearing
and seal were located.
CAUTION: It is very important to preserve the axle radius at the inboard edge of the rework area. When
using the emery cloth, do not allow the edge of the emery cloth to form a groove in the radius;
instead, allow the emery cloth to ride up into the radius.
(b) Using an 0.75 inches (19.05 mm) wide strip of 320 grit (aluminum oxide) emery cloth, remove all corrosion on
the axle (between the piston axle adaptor and protected area). All corrosion, including any pitting of the metal,
must be removed. After all pits are removed, apply a final finish to the axle with 400 grit emery cloth (aluminum
oxide).
(c) Remove the aluminum sheet protecting the axle and ensure all corrosion is removed up to the area where the
bearing seal was making contact with the axle. Remove any remaining corrosion with 400 grit emery cloth but
use minimum pressure when sanding over the seal area.
(d) Clean the area with solvent and measure the diameter of the axle in the reworked area at four locations oriented
45 degrees apart and determine the average axle diameter. If the average axle diameter is less than 1.8020
inches (45.770 mm), the axle must be replaced. Refer to Main Gear Assembly - Disassembly and Main Gear
Assembly - Assembly, for axle replacement instructions. If the average axle diameter is 1.8020 (45.770 mm) or
greater, proceed with application of finish. Refer to step (5), Finish Application.
NOTE: Small local areas of the axle may indicate as small as 1.8000 inches (45.770 mm) diameter
at any one location, but the average axle diameter must still be a minimum of 1.8020
inches (45.770 mm) diameter.
(4) Finish Application.
NOTE: MIL-PRF-23377 corrosion resistant primer must be applied to clean surfaces within 30 minutes
of completion of sanding procedure. An oxide film which provides minimal adhesion for MIL-
PRF-23377 corrosion resistant primer begins to form immediately after working. Poorly
adhered MIL-PRF-23377 corrosion resistant primer will result in accelerated corrosion.
(a) Clean the piston axle adaptor and/or axle with approved solvent and wipe dry.
(b) Mask off areas of the piston not reworked.
(c) Mask off the outboard portion of the axle from the inboard wheel bearing seal. Ensure masking covers the
inboard wheel bearing seal contact point so that the seal does not ride on the MIL-PRF-23377 corrosion
resistant primer.
(d) Apply MIL-PRF-23377 corrosion resistant primer to the piston axle adaptor and/or the axle. For application and
mixing instructions for MIL-PRF-23377 corrosion resistant primer, refer to the manufacturer’s instructions.
(e) Apply a thin film of wheel bearing grease to the outer surface of axle as a corrosion preventative treatment.
F. Axle Adaptor Repair
(1) there is an optional repair available that uses a Cessna controlled process. This process can remove corrosion and
build up the axle adaptor with hard chrome plating. For more details, contact Cessna Customer Services –
Structures.
NOTE:
No material is allowed to be removed from the original diameter of 2.497 inches (63.246 mm) on
the trailing link gear due to production shot peening process and design specifications for
that area. The optional repair is the only way to remove corrosion and return the link to
service.
2. Modify Outer Bearing
NOTE: This modification installs a larger breather vent which can be replaced more easily and does not
become clogged as quickly.

NOTE: This modification upgrades the 6541425-6 and -11 outer bearing to the functional equivalent of a
6541425-13 bearing.
A. Modification.
CAUTION: Locate the position of the hole carefully. Putting it too high on the bearing will result in less than
minimum edge distance.
(1) Lay out, drill and tap a hole for a MS21209F1-15 Helicoil insert following the required instructions provided in
NASM33537 for a 0.190-32 UNF-3B insert. Refer to Figure 602.
(a) Remove all burrs.
(b) Remove all chips and other metallic debris.
(2) Apply color chemical film to only the threads formed in the bearing. Refer to the Structural Repair Manual, Chapter 51.
Protective Treatment of Metal.
(3) Insert the Helicoil insert so the outer end is 0.75 to 1.5 turns below the outer surface of the bearing.
(4) Break off the drive tang of the Helicoil.
(5) Apply N7649 primer to the threads of the QSB-5-SS breather vent.
(6) Apply 242 anaerobic adhesive to the threads of the breather vent.
(7) Install the breather vent in the Helicoil.
(8) Add a suffix "A" after the oleo serial number on the identification placard.

Figure 601 : Sheet 1 : Main Landing Gear Axle Inspection

A83932

INSPECTION AREA ON AXLE

5641T1066

Figure 601 : Sheet 2 : Main Landing Gear Axle Inspection

A83983
CAUTION: MAKE SURE THAT YOU KEEP AN
SAFETY WIRE AXLE RADIUS OF 0.38 INCHES AS
(REFERENCE) YOU REMOVE THE CORROSION
NAS561P8-8
PIN FROM THE AXLE. THIS IS DEFINED
(REFERENCE) IN THE ACCOMPLISHMENT
INSTRUCTIONS.

1.16 INCH +0.5 OR -0.05 INCH

B
ALUMINUM SHEET

VIEWA-A
45Â°

A
D B

C C

NOTE: THE AXLE IS MEASURED AT FOUR B D

LOCATIONS 45 DEGREES APART TO A
FIND THE AVERAGE AXLE DIAMETER.
SEE VIEW B-B.
VIEW B-B
MEASUREMENT LOCATIONS FOR THE AXLE
AA5641T1067
BB5641T1067

Figure 602 : Sheet 1 : Modification of Outer Bearing

A27708

(NOTE)

A
EXISTING
FILTER DISC

OUTER
A BEARING

NOTE: HOLE DRILLED FOR NEW BREATHER VENT

IS ON THE OPPOSITE SIDE OF THE
BEARING AS THE EXISTING FILTER DISC

OUTER
BEARING

0.190-32 UNF-3B HELICAL

COIL INSERT
THREAD THRU EXISTING
PER MS33537 FILTER DISC
(DO NOT REMOVE)

1.198 INCH
(30.43 mm)

VIEW A-A
6641T1029
AA6641T1030

MAIN GEAR ASSEMBLY - ASSEMBLY

1. Landing Gear Assembly
A. Tools and Equipment
NAME NUMBER MANUFACTURER USE
Safety Wire Monel 0.020 inch Commercially available To safety the air valve and
diameter cylinder
Loctite 680 Loctite Corporation To secure the squat switch
705 N. Mountain Road support and bearings
Newington, CT 06111
Loctite 242 Loctite Corporation To assemble the orifice fitting
Loctite 243 Loctite Corporation To assemble the orifice fitting
Loctite 277 Loctite Corporation To assemble the oleo
Locquic Primer T 7471 Loctite Corporation To clean and prepare parts for
an application of thread locking
material.
Loctite Clover Silicon Grade C, 220 Grit Loctite Corporation To deburr threaded
Carbide Grease Mix components
Adhesive EA9309.3NA Loctite Aerospace To bond placards
2850 Willow Pass Road
Bay Point, CA 94565
Sealant MIL-S-8802 Type I, PRC-DeSoto International Dissimilar materials protection.
Class B 5454 SanFernando Road
Glendala, CA 91203
Pretreatment Primer 728-013/702-701 Sherwin-Williams Inc. Pretreatment primer
DOD-P-15328 16116 E. 13th Street
Andover, KS 67002
Corrosion Resistant 513 x 419/ 910 x PRC-DeSoto International Corrosion protection primer
Primer MIL-PRF- 942 5426 San Fernando Rd.
23377G or later Glendale, CA 91209
Corrosion Resistant 02-Y-40 02-4-40 Deft, Inc. Corrosion protection primer
Primer MIL-PRF- CATA 17151 Von Karman Ave.
23377G or later Irvine, CA 92714
Corrosion Resistant U-1201F/ U-1202F Sterling Laquer Manufacturing Co. Corrosion protection primer
Primer MIL-PRF- 3150 Brannon St.
23377G or later St. Louis, MO 63139
Corrosion Resistant R4001-K14MAX U.S. Paint Corp Corrosion protection primer
Primer MIL-PRF- COR 831 South 21st St.
23377G or later St. Louis, MO 63130
Polyurethane paint, 7400 (Color Name: U.S. Paint Corp. Finish paint
medium gray Pewter)
2. Main Gear Assembly
A. Assemble Gear (Refer to Main Gear Assembly, Figure 1001).
(1) Apply Loctite 680 to bore of trunnion (16A) and install squat switch support bracket (18).
(2) Install bushings (25), (28) and (79) wet by pressing into trunnion using wet epoxy primer.
(3) Press axle (96) into bore of trailing link (75) using MIL-PRF-23377 corrosion resistant primer, ensuring that the hole
for blind fastener (97) is properly aligned.
(4) Install blind fastener (97) into trailing link (75) and axle (96).

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 13:11:23 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
32-10-04-7 (Rev 14)

(5) Install pivot pin (77), thrust bearings (78) spacer (82), ensuring ramp of spacer is against squat switch, to secure
trailing link (75) to trunnion (16A).
(6) Ensure head of pivot pin (77) is tight against trunnion (16A).
(7) Turn nut (80), finger tight against opposite side of trunnion, back nut off to first cotter pin hole and secure with cotter
pins (81).
(8) With ramp against squat switch, install bolt (19) through spacer (82) and pivot pin (77) and secure with bracket (20)
washer (21), nut (22) and cotter pin (23).
(9) Verify phenolic scuff shields (94) are bonded in place. Refer to Main Gear Assembly - Repair.
(10) Install oleo assembly (31).
(a) Install bolt (26) washers (27) under nut, under bolt head, and between oleo bearing and forward bushing (21), nut
(29) and cotter pin (30) to secure upper end of oleo.
(b) Install bolt (32), washers (33) under nut and under bolt head, nut (34) and cotter pin (35) to secure lower end of
oleo.
(11) Use MIL-S-8802 Type I Class B sealant to bond the end cap (84) on the trailing link (75).
(a) Make sure to apply a sufficient quantity of sealant to completely seal around the circumference of the end cap to
keep moisture out of the upper bore of the trailing link (75).
(12) Use MIL-S-8802 Type I Class B sealant to bond the button plug (83) on the trailing link (75).
3. Oleo Assembly
A. Assemble Oleo (Refer to Oleo Assembly - Main Gear Assembly, Figure 1002).
(1) Press bearings (2) into caps (3) and (19) with Loctite 680 and stake bearings in place.
(2) Install a new O-ring (7) in upper cap (3) and then apply Loctite 277 to threads of cap (3).
(3) Secure the lug of the upper cap (3) in a padded vise and install the upper barrel (6) in the cap, torquing to 50 foot-
pounds (67.8 N-m) taking care not to scratch the outer surface of the upper barrel.
(4) Install metering pin (14) in lower cap (19) using Loctite 277 and torque to 125 inch-pounds (14.1 N-m).
(5) Install an new O-ring (18) on lower cap (19) and then apply Loctite 277 to threads of cap (19).
(6) Secure the lug of the lower cap (19) in a padded vise and install the lower barrel (13) in the cap, torquing to 50 foot-
pounds (67.8 N-m).
(7) Install scraper (12) into outer bearing (9).
(8) Verify that filter (11) is installed in outer bearing (9) and is not clogged.
(9) Slip outer bearing (9) onto upper barrel (6).
(10) Temporarily screw the orifice fitting (15) into the lower end of the upper barrel (6).
(a) If the orifice fitting does not turn easily and smoothly, do the following:
1 Apply Loctite Clover Silicon Carbide Grease Mix Grade A, Grit 220 to the threads of the orifice fitting.
2 Install and remove the orifice fitting several times to clean and deburr the threads of the orifice fitting and
upper barrel.
3 Thoroughly clean and dry the orifice fitting and upper barrel to make sure all of the silicon carbide grease is
removed.
4 Screw the orifice fitting into the lower end of the upper barrel to make sure it installs easily and smoothly.
5 Repeat the procedure as needed until the orifice fitting turns smoothly when installed in the upper barrel.
(11) Remove the orifice fitting (15) from the lower end of the upper barrel (6).
(12) Install the T-seal (17) in the groove of the orifice fitting (15).
(13) Install the O-ring (16) at the base of the threads on the orifice fitting (15).
(14) Apply Locquic Primer T 7471 to the threads of the orifice fitting (15), and to the lower end of the upper barrel (6).
(15) Apply Loctite 242 or 243 to threads of orifice fitting (15), and lower end of upper barrel (6).
(16) Immediately screw orifice fitting (15) into lower end of upper barrel (6) and torque to 50 foot-pounds (67.8 N-m).
(17) Use a spanner wrench to install outer bearing (9) to lower barrel (13) and torque to 50 foot-pounds (67.8 N-m).

(18) Safety wire outer bearing (9) to lower barrel (13).

(19) If placards (20 or 21) on Oleo (1) or (98) on trailing link (75) require replacement, bond with EA9309.3NA adhesive,
and overcoat with a minimum of two coats of clear urethane enamel, overlapping the edges of the placard by a
minimum of 0.50 inch (12.7 mm).

MAIN LANDING GEAR ASSEMBLY - FITS AND CLEARANCES

1. Fits and Clearances (Oleo)
A. Upper Barrel 6541423-1, 6541423-2 and 6541423-3
A84463

(1)

6641T1053

(1) 3.122 Inch, +0.001 or -0.001 (79.298 mm, +0.025 or -0.025 mm) surface finish 16 microinches.
B. Lower Barrel 6541424-1
A84464

(1)

6641T1054

(1) 3.251 Inch, +0.001 or -0.001 (82.575 mm, +0.025 or -0.025 mm) surface finish 16 microinches.
C. Orifice 6541428-1, 6541428-2 and 6541428-3
A84465

(1)

6641T1055

(1) 3.2460 Inch, +0.0005 or -0.0005 (82.448 mm, +0.012 or -0.012 mm) diameter.
D. Upper Barrel Cap 6541521-2 and 6541521-3

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 13:11:24 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
32-10-04-8 (Rev 14)

A84466
(1)

5614T1586

(1) 1.3745 Inch, +0.001 or -0.001(34.9123 mm, +0.012 or -0.012 mm) diameter.
E. Lower Barrel Cap 6541422-1
A84467

(1)

6641T1057

(1) 1.3745 Inch, +0.0005 or -0.0005 (34.9123 mm, +0.012 or -0.012 mm) diameter.
F. Outer Bearing 6541425-2, 6541425-7 and 6541425-14
A84468

(1)

6641T1058

(1) 3.125 Inch, +0.001 or -0.001 (79.375 mm, +0.025 or -0.025 mm) diameter.
G. Metering Pin 6541527-1

A84469
(10) (9) (8) (7) (6) (5)
(4)
(3)
(2)

(1)

5614T1587

(1) 0.56 Inch, +0.001 or -0.001 (14.224 mm, +0.0254, or -0.0254 mm) diameter.
(2) 0.430 Inch, +0.001 or -0.001 (10.922 mm, +0.0254, or -0.0254 mm) diameter.
(3) 0.470 Inch, +0.001 or -0.001 (11.938 mm, +0.0254, or -0.0254 mm) diameter.
(4) 0.233 Inch, +0.001 or -0.001 (5.918 mm, +0.0254, or -0.0254 mm) diameter.
(5) 0.280 Inch, +0.001 or -0.001 (7.112 mm, +0.0254, or -0.0254 mm) length.
(6) 0.600 Inch, +0.001 or -0.001 (15.24 mm, +0.0254, or -0.0254 mm) length.
(7) 1.000 Inch, +0.001 or -0.001 (25.4 mm, +0.0254, or -0.0254 mm) length.
(8) 3.600 Inch, +0.001 or -0.001 (91.44 mm, +0.0254, or -0.0254 mm) length.
(9) 7.880 Inch, +0.001 or -0.001 (200.152 mm, +0.0254, or -0.0254 mm) length.
(10) 11.026 Inch, +0.001 or -0.001 (280.060 mm, +0.0254, or -0.0254 mm) length.

MAIN LANDING GEAR ASSEMBLY

NOMENCLATURE EFFECTIVITY UNITS
PER
ITEM PART NUMBER 1 2 3 4 5 6 7 FROM TO ASSY
- MAIN LANDING GEAR ASSEMBLY
GEAR ASSY-MAIN
- 1 6541510-1 . LANDING LH FSO 6541510- A NP
3
GEAR ASSY-MAIN
- 2 6541510-2 . LANDING RH FSO B NP
6541510-4
- . GEAR ASSY-MAIN
2A 6541510-3 C 01
LANDING LH
GEAR ASSY-MAIN
- 2B 6541510-4 . D 01
LANDING RH

3 6541525-1 . . PIN-SIDEBRACE 01
ATTACH
4 S3461-55 . . BOLT 01
5 NAS1149F0463P . . WASHER 01
6 MS17825-4 . . NUT 01
7 MS24665-153 . . COTTER PIN 01
8 NAS1149F1232P . . WASHER 02
9 NAS1149F1290P . . WASHER 01
10 S1450-6N16-063 . . WASHER 01
11 MS17826-6 . . NUT 01
12 MS24665-300 . . COTTER PIN 01
13 6641331-1 . . BOLT 01
14 NAS1149F1232P . . WASHER 01
15 MS17826-12 . . NUT 01
16 MS24665-357 . . COTTER PIN 01
TRUNNION ASSY-MAIN
16A 6541550-1 . . LANDING GEAR LH E NP
FSO 6541550-9
TRUNNION ASSY-MAIN
- 16B 6541550-3 . . LANDING GEAR LH F NP
FSO 6541550-9
TRUNNION ASSY-MAIN
- 16C 6541550-5 . . LANDING GEAR LH G NP
FSO 6541550-9
TRUNNION ASSY-MAIN
- 16D 6541550-7 . . LANDING GEAR LH H NP
FSO 6541550-9
- . . TRUNNION ASSY-MAIN
16E 6541550-9 J 01
LANDING GEAR LH

- . . TRUNNION ASSY-MAIN
16F 6541550-11 K 01
LANDING GEAR LH

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 13:11:26 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
32-10-04-1001 (Rev 16)

- . . TRUNNION ASSY-MAIN
16G 6541550-13 L 01
LANDING GEAR LH

- . . TRUNNION ASSY-MAIN
16H 6541550-15 M 01
LANDING GEAR LH
TRUNNION ASSY-MAIN
- 16J 6541550-19 . . LANDING GEAR LH N NP
FSO 6541550-17
TRUNNION ASSY-MAIN
- 16K 6541550-17 . . LANDING GEAR LH P NP R
FSO 6594021-1
TRUNNION ASSY-MAIN
- 16L 6594021-1 . . LANDING GEAR LH E THRU P 01 R
FOR SPARES ONLY
TRUNNION ASSY-MAIN
- 16M 6541550-2 . . LANDING GEAR RH E NP R
FSO 6541550-10
TRUNNION ASSY-MAIN
- 16N 6541550-4 . . LANDING GEAR RH F NP R
FSO 6541550-10
TRUNNION ASSY-MAIN
- 16P 6541550-6 . . LANDING GEAR RH G NP R
FSO 6541550-10
TRUNNION ASSY-MAIN
- 16Q 6541550-8 . . LANDING GEAR RH H NP R
FSO 6541550-10
- . . TRUNNION ASSY-MAIN
16R 6541550-10 J 01 R
LANDING GEAR RH
TRUNNION ASSY-MAIN
- 16S 6541550-12 . . K 01 R
LANDING GEAR RH
- . . TRUNNION ASSY-MAIN
16T 6541550-14 L 01 R
LANDING GEAR RH
TRUNNION ASSY-MAIN
- 16U 6541550-16 . . M 01 R
LANDING GEAR RH
TRUNNION ASSY-MAIN
- 16V 6541550-20 . . LANDING GEAR RH N NP R
FSO 6541550-18
TRUNNION ASSY-MAIN
- 16W 6541550-18 . . LANDING GEAR RH P NP R
FSO 6594021-2
TRUNNION ASSY-MAIN
- 16X 6594021-2 . . LANDING GEAR RH E THRU P 01 R
FOR SPARES ONLY
17 S3176-2 . . . SWITCH-SQUAT 01
BRACKET ASSY-
18 6541530-2 . . . MAIN LANDING E 01
GEAR SWITCH
BRACKET ASSY-
- 18A 6541530-9 . . . MAIN LANDING F THRU P 01
GEAR SWITCH

19 AN3-21 . . . BOLT 01
20 MS9592-050 . . . BRACKET 01
21 NAS1149F0363P . . . WASHER 01
22 MS17826-3 . . . NUT 01
23 MS24665-134 . . . COTTER PIN 01
BUSHING-MAIN
24 6641618-5 . . . LANDING GEAR 01
TRUNNION
25 NAS77-12-068 . . . BUSHING 01
26 S3461-124 . . . BOLT 01
27 NAS1149F1232P . . . WASHER 03
28 NAS77-12-065 . . . BUSHING 02
29 MS17826-12 . . . NUT 01
COTTER PIN PIN-
30 MS24665-357 . . . 01
COTTER
OLEO ASSY REFER
31 . . . TO 32-10-04 RF
FIGURE 1002
ATTACHING
PARTS
32 S3461-96 . . . BOLT 01
33 NAS1149F1290P . . . WASHER 02
34 MS17826-12 . . . NUT 01
. . . COTTER PIN PIN-
35 MS24665-357 01
COTTER
---*---
ANCHOR ASSY-
36 6318015-14 . . . MAIN LANDING 01
GEAR TRUNNION

NOMENCLATURE EFFECTIVITY UNITS

PER
ITEM PART NUMBER 1 2 3 4 5 6 7 FROM TO ASSY
- MAIN LANDING GEAR ASSEMBLY
TRAILING LINK ASSY-
MAIN LANDING GEAR
- 75 6541535-1 . . . A THRU G NP
TRUNNION LH FSO
6541535-5
TRAILING LINK ASSY-
MAIN LANDING GEAR
- 75A 6541535-3 . . . H THRU P NP
TRUNNION LH FSO
6541535-5

UPLOCK ROLLER
SPACER-MAIN
91 6541530-6 . . . . LANDING GEAR 01
TRAILING LINK
AND AXLE
92 MS17826-6 . . . . NUT 01
93 MS24665-283 . . . . COTTER PIN 01
SCUFF SHIELD-
. . . . MAIN LANDING
94 6641640-55 02
GEAR TRAILING
LINK AND AXLE
95 NAS77-12-020 . . . . BUSHING 02
AXLE-MAIN
96 6541517-1 . . . . LANDING GEAR A THRU N NP
FSO 6541517-2
- . . . . AXLE-MAIN
96A 6541517-2 P 01
LANDING GEAR
97 MS90354U1215 . . . . FASTENER-BLIND 01
- Item Not Illustrated

Figure 1001 : Sheet 1 : MAIN LANDING GEAR ASSEMBLY

A27449

16
15
14
30
27 29
26 27 28 27 28

36
4
14
13 9
25

24 12
5
6 11
16A 8 10
3
7
31

18
32 17
33
33
19 34
20 35

212223

5641T1036

Figure 1001 : Sheet 2 : MAIN LANDING GEAR ASSEMBLY

A27450

81
80
81
78

78
79

95 77

94
83
82
84
87 88 96
97
91 90
88
92 85 89
93
5641T1036

MAIN LANDING GEAR OLEO ASSEMBLY

NOMENCLATURE EFFECTIVITY UNITS
PER
ITEM PART NUMBER 1 2 3 4 5 6 7 FROM TO ASSY
- MAIN LANDING GEAR OLEO ASSEMBLY

. OLEO ASSY FSO

1 6541520-2 A NP R
6541520-5
- . OLEO ASSY FSO
1A 6541520-3 B NP R
6541520-5
OLEO ASSY FSO
- 1B 6541520-4 . C NP R
6541520-5
- . OLEO ASSY-FOR
1C 6541520-5 A,B,C 01 R
SPARES ONLY

. . BEARING-UPPER
2 MS14102-12 02
AND LOWER
3 6541521-2 . . OLEO CAP UPPER A,B 01
- 3A 6541521-3 . . OLEO CAP UPPER C 01
4 HF2003 . . VALVE V13899 01

5 NAS1611-015 . . . O-RING REFER TO 01

NOTE 1
UPPER BARREL
6 6541423-1 . . A NP
OLEO FSO 6541423-3

- . . UPPER BARREL
6A 6541423-2 B NP
OLEO FSO 6541423-3

- . . UPPER BARREL
6B 6541423-3 C 01
OLEO
7 NAS1611-235A . . O-RING 01
OUTER BEARING
- 8 6541425-6 . . A,B 01
ASSY

- . . OUTER BEARING
8A 6541425-13 C 01
ASSY

- . . OUTER BEARING
8B 6694615-1 D 01 R
ASSY
OUTER BEARING
- 8C 6541425-15 . . ASSY-USED WITH A,B,C 01 R
6541520-5
9 6541425-7 . . . OUTER BEARING D 01 R
- 9A 6541425-14 . . . OUTER BEARING E 01 R
- 9B 6694615-2 . . . OUTER BEARING D 01 R
- 10 6541425-8 . . . BEARING LINER E 01 R
11 FCR2030-2-2 . . . FILTER DISC V13778 01
12 S33829-338H29 . . . SCRAPER V09257 01
- . . . SCRAPER-USED
12A WXMF0A0129 A,B,C 01 R
WITH 6541425-15
- 12B MS21209F1-15 . . . INSERT A,B,C 01 R

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 13:11:28 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
32-10-04-1002 (Rev 14)

- 12C QSB-5-SS . . . BREATHER VENT V59023 A,B,C 01 R

13 6541424-1 . . BARREL-LOWER 01
14 6541527-1 . . METERING PIN 01
. . ORIFICE FITTING FSO
15 6541428-1 A NP
6541428-2
- 15A 6541428-2 . . ORIFICE FITTING B 01
- 15B 6541428-3 . . ORIFICE FITTING C 01
16 NAS1611-036A . . O-RING 01

. . T-SEAL FSO
17 7336MS-952-T V5F573 A NP
733F6MS-954-T
- 17A 733F6MS-954-T . . T-SEAL V5F573 B,C 01
18 NAS1611-236A . . O-RING 01
19 6541422-1 . . LOWER CAP OLEO 01
PLACARD-OLEO
20 6340002-10 . . 01
VENT
. . PLACARD-MLG OLEO
21 6540502-2 A,B,C 01 R
FILL
OLEO SERVICING
- 22 6940002-1 . . PLACARD-USED A,B,C 01 R
WITH 6541520-5
VALVE IS SUPPLIED WITH O-RING. PART NUMBER IS PROVIDED IF REPLACEMENT OF O-
NOTE 1:
RING ONLY IS REQUIRED.
- Item Not Illustrated

Figure 1002 : Sheet 1 : MAIN LANDING GEAR OLEO ASSEMBLY

A27464

5
4

7
21
6 1
13

12
14
9 20

11
18
16
19
15
17
2

5641T1035

NOSE LANDING GEAR ASSEMBLY - ILLUSTRATED PARTS LIST

1. Illustrated Parts List
A. Introduction.
(1) The Illustrated Parts List will help the customer to order, keep, and supply the nose gear assembly components. It will
also identify new and reclaimed parts. It is not approved for any other purpose.
(2) This parts list includes the nose landing gear assembly used on the Cessna Citation, Citation I and Citation II
airplanes. Part numbers:
5542000-4 5542000-7 5542000-9 5542000-200
5542000-203 5542000-205
(3) The indention system used in the detailed parts list of this catalog shows the relationship of one part to another. For a
given item, the indention code shows a general heading at the extreme left position and continues with indented
columns until the end detail is reached as follows:
A18017
1234567
Installation
Detail Parts for Installation
Assembly
Attaching Parts for Assembly
Detail Parts for Assembly
Subassembly
Attaching Parts for Subassembly
Detail Parts for Subassembly
Sub−Subassembly
Attaching Parts for Sub−Subassembly
Detail Parts for Sub−Subassembly

Basic Number Dash Number

(Drawing Identification
Only)

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 13:11:29 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
32-20-00-0 (Rev 14)

NOSE GEAR ASSEMBLY - DESCRIPTION AND OPERATION

1. Description
A. The nose gear assembly is designed and assembled to permit maneuverability of the airplane on the ground and to retract
into the nose wheel well when airborne. It is designed to absorb shock during airplane takeoffs, landings and taxiing and is
equipped with nose wheel steering. The principal sub-assemblies of the nose gear are the trunnion assembly, shock strut
assembly, fork and torque links. Refer to Figure 1 and Figure 2.
(1) The cylinder, piston and an isolation piston are the shock absorbing portion of the nose gear assembly. The isolation
piston floats within the piston assembly. The chamber above the isolation piston contains hydraulic fluid and the
chamber below the isolation piston is charged with dry air or nitrogen. O-ring type packings are used on the isolation
piston to separate the hydraulic fluid and air/nitrogen. The cylinder assembly is supported within the trunnion by
bearings and retainers which permit rotation around the centerline of the cylinder.
(2) The trunnion is connected to the shock strut and attaches to the sides of the wheel well with trunnion pins to allow the
gear assembly to be retracted into the nose wheel well by a hydraulic actuator.
(3) The fork is press fitted to the bottom of the piston assembly and should not be separated unless warranted by
unserviceable conditions such as cracks or material flaws.
(4) Torque links prevent the piston and fork from rotating within the cylinder assembly. The upper torque link is connected
to the bottom of the cylinder and the lower torque link is connected to the piston-fork assembly. Mounted on the aft
side of the strut, the torque links are connected together to permit piston vertical movement in the cylinder.
B. The nose gear is equipped with a shimmy damper. Refer to Shimmy Damper, Description and Operation for information
concerning component operation and maintenance of the nose wheel shimmy damper.
C. The nose gear wheel is steerable and actuated by a bungee and cables connected to the rudder pedals. Refer to the
airplane maintenance manual for operation and maintenance of the nose wheel steering.
D. These nose gear assembly part numbers are affected by this individual component maintenance manual:
5542000-4 5542000-7 5542000-9
(1) Other nose gear assembly part numbers included as spares are: 5542000-200, 5542000-203 and5542000-205.
(2) Nose gear P/N 5542000-200 is the same as P/N 5542000-4 less tire, wheel and attaching parts.
(3) Nose gear P/N 5542000-203 is the same as P/N 5542000-7 less tire, wheel and attaching parts.
(4) Nose gear P/N 5542000-205 is the same as P/N 5542000-7 less tire, wheel and attaching parts.
2. Operation
A. As weight of the airplane is applied to the nose gear assembly, the piston assembly is forced to slide into the cylinder
assembly. This movement causes a tapered metering pin, mounted at the top of the cylinder and protruding through a fixed
orifice in the top of the piston, to increasingly restrict hydraulic fluid flow through the orifice. The restricted fluid flow on the
top of the isolation piston and the compressed air/nitrogen below the isolation piston dampens the movement of the piston
assembly and absorbs compression shocks. As weight of the airplane is removed from the nose gear assembly, the
compressed air/nitrogen forces the isolation piston toward the top of the piston chamber. The hydraulic fluid is forced
through the fixed orifice at the top of the piston that is becoming increasingly unrestricted as the tapered metering pin is
withdrawn from the fixed orifice and the piston assembly extends. Refer to Figure 3.
3. Personnel Safety Precautions - Hydraulic Fluid
A. The nose gear assembly contains phosphate ester base hydraulic fluid. Before performing maintenance or any operation
on the nose gear shock strut assembly, personnel should read and thoroughly understand the following.
WARNING: Observe the following safety precautions when working on systems containing phosphate ester
base fluid. Prolonged exposure to the fluid can cause skin dehydration and chapping.
(1) Wash hands thoroughly with soap and water before starting work; apply barrier cream (silicone hand cream) to
hands, wrists and forearms. Rub cream under fingernails and into creases of skin.
(2) Wear eye goggles when pressure testing components or systems or anytime there is a possibility of hydraulic fluid
splashing into eyes.
(3) If hydraulic fluid enters the eyes, treat eyes immediately by irrigating thoroughly with clear, cold water.
(4) Wash hands, wrists and forearms with soap and warm water after contacting hydraulic fluid.

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 13:11:31 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
32-20-00-0 (Rev 14)

(5) If clothing becomes soaked with hydraulic fluid, remove the contaminated clothing as soon as possible. Wash skin
exposed to hydraulic fluid with soap and warm water. Wash hydraulic fluid contaminated clothing before wearing.
4. Technical Safety Precaution - Hydraulic Fluid
A. Because the nose gear strut contains phosphate ester base hydraulic fluid, improper maintenance practices can be
damaging to gear components and other equipment. Before performing maintenance or any operation on the nose gear
shock strut assembly, personnel should read and thoroughly understand the following technical precautions.
CAUTION: Phosphate ester base hydraulic fluid will damage and/or deteriorate a wide range of materials;
including rubber, copper, various plastics and paints.
(1) Make sure that hydraulic fluid does not come in contact with any part of the component outside of the nose gear
shock strut. Keep spillage to an absolute minimum. Clean up spilled hydraulic fluid immediately to prevent
contamination of non-hydraulic components and to avoid false hydraulic leak detections. Should spillage occur, wipe
up the fluid with a dry cloth and wash area with naphtha MIL-PRF-680 (Type III).
(2) When gear components are disassembled, provide suitable protection for preventing entry of foreign material by
using caps and/or covers.
(3) Always check angle and position of components prior to disassembly to ensure proper alignment and placement of
components and hardware during assembly or replacement.
(4) Use naphtha MIL-PRF-680 (Type III) or methyl n-propyl ketone, when washing metal parts prior to assembly. Make
sure all traces of the cleaning agent are removed before assembly.
(5) Use only clean hydraulic fluid for flushing or testing hydraulic components.
(6) Do not unpack seals, O-rings/packings until they are required and make sure that only correct, compatible and
approved seals, O-rings/packings are used.
(7) When assembling the gear shock strut hydraulic seals, O-rings/packings, lubricate only with phosphate ester base
hydraulic fluid. Always lubricate seals, O-ring/packings immediately before installation. Threaded fittings should be
assembled without the use of lubricants whenever possible. If a lubricant is required to prevent galling or to otherwise
ease installation, use phosphate ester base hydraulic fluid or VV-P-236 Petrolatum.
CAUTION: Take special care not to contaminate seals, o-rings/ packings after lubrication.
CAUTION: Prevent contamination of phosphate ester base hydraulic fluid with other hydraulic fluids, oils,
water or dirt.

Figure 1 : Sheet 1 : Nose Gear Assembly - Description

A84047

Trunnion

Piston

Fork

Torque Links

5542T1032

Figure 2 : Sheet 1 : Nose Gear Strut Assembly - Description

Figure 3 : Sheet 1 : Nose Gear Strut Assembly - Operation

NOSE GEAR ASSEMBLY - TESTING

1. Testing
A. The nose gear shock strut should be properly filled/serviced with phosphate ester base hydraulic fluid and charged with dry
air/nitrogen prior to conducting test(s).
B. Tools and Equipment.
NOTE: Equivalent substitutes may be used for the listed items:
NAME NUMBER MANUFACTURER USE
Hydraulic Service Unit, CMJD112-001 Cessna Aircraft Co. Fill and cycle strut.
Portable Citation Marketing Div.
Department 579
P.O. Box 7706
Wichita, KS 67277
Magnetic Vee Base Measure piston deflection.
Nine Inch Horizontal
Gage Holding Rod,
Dial Indicator
Hunter Spring Gage Type D100 Ametek/Hunter Spring Measure pull force.
Hatfield, PA 19440
C. Shock Strut Filling Instructions.
(1) Position and maintain strut in upright position to expel any fluid that may have collected in the air chamber.
(2) Attach a valve core depressor to, or remove valve core from the air filler valve assembly. Rotate 0.625 inch hex nut
counterclockwise to lift internal poppet to release any trapped air/nitrogen.
WARNING: Do not stand in front of the valve assembly while releasing air/nitrogen pressure. Do not turn 0.75
inch hex nut while releasing pressure. Removing the air filler valve without releasing air/nitrogen
pressure can cause injury.
(3) Remove metering pin from top of cylinder and install reducer (AN919-3) or union (AN815-5) with gasket (NAS1612-
5).
(4) Attach hose from portable hydraulic service unit containing phosphate ester base hydraulic fluid and pump until strut
is fully extended.
(5) Open pump check valve and force strut to collapsed position as trapped air is expelled into hand pump reservoir.
(6) Repeat pumping, cycling strut until no air is noted coming from the strut fluid chamber.
(7) Discontinue pump cycling of the strut with the strut in the collapsed position. Remove hose and fitting.
(8) Keep fluid chamber full and do not disturb strut from the collapsed position until the metering pin has been installed
and tightened against its gasket. Safety wire metering pin.
WARNING: Servicing the strut with air before strut is properly serviced with hydraulic fluid could result in
blowing strut apart causing damage to equipment and/or injury to personnel.
(9) Install air filler valve core (replace with new valve core if necessary) and charge strut air chamber with the 0.625 inch
hex nut turned a maximum of one and one-half turns counterclockwise to 5 PSI above service placard instruction
pressure.
NOTE: Charge strut with dry air or nitrogen.
(10) Bleed air/nitrogen to service placard pressure.
(11) Tighten 0.625 inch hex nut to 50 to 70 inch-pounds.
D. Leak Test.
(1) After filling/servicing nose gear shock strut in accordance with instructions above, leave strut assembly charged for a
one hour period. No fluid leakage or loss of air/nitrogen is permissible.
(2) Release air/nitrogen from the air filler valve. If fluid is noted coming through the air filler valve, consult Troubleshooting
procedure.

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 13:11:39 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
32-20-00-1 (Rev 5)

WARNING: Do not stand in front of filler valve while releasing air/nitrogen pressure. Do not turn 0.75 inch hex
nut while releasing pressure. Removing air filler valve without releasing pressure first can cause
injury.
E. Piston Bearing Wear Test (Refer to Figure 101).
(1) Place nose gear in a suitable stand to hold the trunnion assembly solid.
(2) Attach magnetic vee base and dial indicator.
(3) Set and record dial indicator reading. Apply a 30-pound, 90-degree forward pull with spring scale at the axle area of
the fork. Note and record dial indicator reading.
(4) Apply a 30-pound, 90-degree aft pull with spring scale at the axle area of the fork. Note and record dial reading.
(5) If the deflection exceeds the maximum allowable wear of 0.078 TIR, replace bearing(s).
2. Troubleshooting
A. The nose gear assembly may be tested as outlined in Testing, to determine air or fluid leakage. A review of documented
information received with the assembly, visual check and/or test results may be utilized in conjunction with the following
troubleshooting.
B. Troubleshooting.
TROUBLE PROBABLE CAUSE REMEDY
OIL LEAK AROUND Damaged packings or seals on lower Replace packings and seals. Hone piston.
PISTON bearing.
Cracked bearing. Replace bearing.
Piston surface cut or nicked. Polish out cut or nick.
Excessive polishing on piston surface has Replace piston.
created low or flat spots that packings are
unable to seal.
STRUT DOES NOT Damaged packings on isolation piston. Replace packings.
EXTEND WHEN
WEIGHT IS REMOVED
Leaking air valve. Replace air valve
OIL PRESENT WHEN Isolation piston damaged. Replace isolation piston.
AIR VALVE IS OPENED
Piston wall damaged. Replace piston.
STEERING DIFFICULT Damaged upper or lower cylinder support Replace bearings.
bearings.
INCREASED NOSE Loose torque links. Check torque link attach points.
WHEEL SHIMMY

Figure 101 : Sheet 1 : Piston Bearing Wear Test

NOSE GEAR ASSEMBLY - DISASSEMBLY

1. Disassembly
NOTE: Determine extent of disassembly required by reviewing documentation accompanying the nose gear
assembly, or discrepancies noted during test, troubleshooting, checks and other maintenance
accomplished.
NOTE: Review personnel and technical safety precautions in Nose Gear Assembly - Description and
Operation, concerning handling phosphate ester base hydraulic fluid.
A. Preparation for Disassembly (Refer to Illustrated Parts List).
(1) Place nose gear strut in upright position.
(2) Rotate 0.625 inch hex nut on air valve (260) counterclockwise 1-1/2 turns to lift internal valve poppet and release
air/nitrogen pressure by depressing valve core.
WARNING: Do not stand in front of air filler valve while releasing pressure. Do not turn 0.75 inch hex nut while
releasing pressure. Removal of the air filler valve prior to releasing pressure can cause injury.
(3) Cut safety wire and remove air valve (260) and packing (259) from bottom end of piston assembly.
(4) Cut safety wire and remove metering pin (225) and packing (226) from top of cylinder.
(5) Drain hydraulic fluid from upper piston chamber.
B. Torque Links Removal.
(1) Separate upper and lower torque links (154 and 155) by removing cotter pin (167), nut (166), washers (165), bolt
(163) and spacer (164).
(2) Remove pins (158 and 159) and shafts (156) attaching torque links to cylinder and piston assemblies.
(3) Press bushings (160) from upper and lower torque links (154 and 155).
C. Cylinder Assembly Removal.
(1) Remove lower retainer (229) and slide cylinder assembly (231) out of trunnion (9).
(2) Remove upper retainer (227) and bearing (228) from cylinder assembly (231).
D. Piston - Cylinder Disassembly.
(1) Push bearing (246) and retainer (250) into cylinder enough to free lock ring (252). Remove lock ring (252).
(2) Pull piston and fork assembly from cylinder (231).
(3) Remove two setscrews (234) and unscrew bearing (233) from top of piston (257).
(4) Slide spacer (242), bearing (246), scraper (248) and retainer (250) from piston (257).
(5) Remove polypak seal (247) from Inner groove of phenolic bearing (246).
(6) Remove packing (243) and backup retainer (244) from outside of phenolic bearing (246).
(7) Remove Isolation piston (238), spring (239) and stop (240) from piston (257).
NOTE: A 10-32 UNF 3B hole has been drilled in the center of the Isolation piston to facilitate removal.
If setscrews (234) have dimpled the piston so that removal of the isolation piston Is difficult,
remove metal with an adjustable cylinder hone. Remove only the high spots from inside the
piston barrel.
(8) Compress spring (239) to remove retainer (241). Remove stop (240) and spring (239) from Isolation piston (238).
(9) Remove teflon packings (235) and rubber packing (237) from isolation piston (238).
E. Fork Removal.
NOTE: Do not remove fork from piston unless inspection reveals cracks, flaws or other unserviceable
conditions. Inspect piston for damage before removing fork.
(1) Remove uplock roller assembly.
(a) Remove cotter pins (176) and nuts (175). Pull bolts (170 and 171) allowing brackets (168 and 169), washers
(172 and 173) and spacers (174) to drop from fork.
(2) Using an arbor press and suitable mandrel, press piston (257) from fork (258).

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 13:11:43 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
32-20-00-4 (Rev 12)

NOSE GEAR ASSEMBLY - CLEANING

1. Cleaning
A. Tools and Equipment.
NOTE: Equivalent substitutes may be used instead of the listed items:
NAME NUMBER MANUFACTURER USE
Methyl n-Propyl Ketone Clean metal parts.
Solvent Blend Desoclean 110 PRC-DeSoto International Clean metal parts.
5426 San Fernando Rd.
Glendale, CA 91209
Paint Stripper T-6776 LO Turco Products, Inc. Strip paint from metal parts
Westminster 92684 prior to inspection.
CA
Naptha MIL-PDF-680 Commercially Available Metal parts cleaning that
(Type III) require soak cleaning.
Protective Oil Oakite Special Oakite Products Inc. Protect metal surfaces that
Protective Oil 50 Valley Road have had paint removed.
Berkeley Heights, NJ 07922
Hydraulic Assembly MCS 352 Aviation Fluids Service Co. Protect surfaces normally in
Lubricant St. Louis, MO 63166 contact with hydraulic fluid.
B. Cleaning Procedure.
(1) Clean metal parts and phenolic bearing with approved solvent. Remove stubborn deposits by hand rubbing with
nonabrasive pads or material. Apply solvent under pressure to all lubrication pads or material. Apply solvent under
pressure to all lubrication fittings, channels and other internal cavities to ensure cleanliness. Thoroughly dry all parts
with filtered, dry, compressed air, lint free cloth or lint free disposable tissue.
WARNING: Use cleaning solvents only in well ventilated areas. Avoid inhaling solvent vapors. Keep solvent
and solvent containers away from spark or open flame.
(2) Labels or identification plates which are attached by adhesive, shall be removed by lifting the corner and pulling free.
Remove adhesive with clean cloth dipped in cleaning solvent.
WARNING: All paint strippers are harmful to eyes and skin. Operators shall wear goggle type eye glasses,
rubber gloves, aprons and boots. In case of contact with skin, flush with water. In case of contact
with eyes, flush eyes thoroughly with water and consult a physician immediately. Paint stripping
shall be done in a well ventilated area. Follow manufacturer's instructions carefully to relieve
pressure before opening paint stripper storage containers.
(3) Apply a suitable paint stripper on painted parts. Allow the first application to work from 5 to 45 minutes or as advised
by manufacturer's instructions. If necessary, scrub softened areas with brush to loosen paint. Rinse with water.
Repeat as necessary to remove all paint. After paint is completely removed, rinse part thoroughly with water spray.
Dry part with filtered, dry, compressed air, lint free cloth or lint free disposable tissue.
(4) After drying, coat all parts that would normally come in contact with hydraulic fluid during operation with clean hydraulic
fluid or hydraulic assembly lubricant. External metal surfaces or other parts not coming in contact with hydraulic fluid
during operation of the strut need not be coated. However, highly machined surfaces may be coated with hydraulic
fluid or other suitable protective coating.
(5) If inspection and repair procedures do not immediately follow cleaning, coat all surfaces that have had paint removed
with a suitable protective oil.

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 13:11:44 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
32-20-00-5 (Rev 12)

NOSE GEAR ASSEMBLY - CHECK

1. Checking Nose Gear Assembly
A. Tools and Equipment.
NOTE: Equivalent substitutes may be used instead of the listed items:
NAME NUMBER MANUFACTURER USE
Cupric sulfate Commercially Available Chrome surface check.
Sulfuric acid Concentrated (18N) Commercially Available Chrome surface check.
B. Recommended Checking Methods.
(1) Consult Table 501 to determine the recommended method of checking for each component.
(2) Check all parts visually under strong light for surface cracks, flaws, burrs, pitting, scoring or any other wear.
(3) Replace all parts showing cracks or flaws under dye penetrant, magnetic particle or visual inspection.
(4) Check all friction surfaces and machined holes for wear beyond tolerances given in Nose Gear Assembly - Fits and
Clearances.
(5) Check all bolts, nuts and screw threads, both external and internal, for evidence of stripping or scoring. Replace all
parts that have stripped threads.
C. Checking Chrome Plating.
CAUTION: When mixing solutions, always add acid to water; never add water to acid.
(1) Check the chrome surfaces of the shock strut assembly for scratches, scores, blisters, and nicks. All suspected
defects should be tested to determine if the base metal has been exposed. To test, apply liberally to the suspected
areas a copper sulfate solution consisting of 100 grams cupric sulfate, five (5) milliliters sulfuric acid and one (1) liter
of water. Wipe off excess liquid and inspect, using a strong light and a magnifying lens. If the chrome plating has been
penetrated, a copper coating will adhere to the ferrous metal. Clean the area thoroughly using solvent. If the chrome
plating has been penetrated in the sealing area, the part shall not be returned to airplane use. If the chrome plating on
the piston below the sealing surface is penetrated but no damage to the steel is detectable, then the chrome damage
may be repaired by cleaning and applying MIL-PRF-23377 corrosion resistant primer. After this repair is complete
the piston may be returned to service. Defects that have not penetrated the chrome plating should be polished to
remove sharp edges that could damage seals. A honing stone or crocus cloth may be used for this purpose.
D. Table 501 contains recommended checks (Refer to Illustrated Parts List for item reference).
Table 501. Recommended Checks
NOMENCLATURE METHOD OF CHECK FOR REQUIREMENT
AND ITEM NUMBER CHECKING
Trunnion (9) Visual Wear, Damage No damage or wear that would
endanger structure or interfere with
function.
Dye Penetrant Cracks No Cracks.
Valve Assembly (260) Visual Damage, Stripped Threads No damage or stripped threads.
Metering Pin (225) Visual Stripped Threads No stripped threads.
Cylinder (231) Visual Wear, Damage No wear or damage that would
prevent function.
Magnetic Particle Cracks No cracks.
Retainers (227, 229, Visual Wear, Damage No wear or damage that would
241 and 250) prevent function.
Bearing (233) Visual Wear, Damage No wear or damage.
Isolation Piston (238) Visual Wear, Damage No wear or damage that would
prevent function or sealing capability.

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 13:11:45 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
32-20-00-5 (Rev 12)

Dye Penetrant Cracks No cracks.

Shafts (156) Visual Ovaling or Other Damage Must meet dimensions given in Fits
and Clearances.
Dye Penetrant Cracks No cracks.
Upper and Lower Visual Out of Round Holes - Wear or Other Holes must meet tolerances given in
Torque Links (154 Damage Fits and Clearances.
and 155)
No wear or other damage that would
endanger structure or prevent
function.
Dye Penetrant Cracks No cracks.
Spacer (164) Visual Damage or Wear No wear or damage.
Piston (257) Visual Wear, Damage to Bearing Surfaces No wear or damage that would
Inner Diameter Finish prevent function.
Dye Penetrant Cracks No cracks.
Ultrasonic Braze Joints No voids or cracks.

NOSE GEAR ASSEMBLY - REPAIR

1. Repair
A. Tools and Equipment.
NOTE: Equivalent substitutes may be used for the listed items:
NAME NUMBER MANUFACTURER USE
Wet or dry sandpaper 400 Commercially Available Remove corrosion from gear
strut.
Wet or dry sandpaper 180 grit Commercially Available Blending damaged nose gear
fork at upper torque take - out
lugs.
Emery Cloth 320 grit 400 grit Commercially Available Remove corrosion and final
finishing of axle and piston axle
adaptor.
Pretreatment primer Base 728-014
Sherwin-Williams Inc. Pretreatment primer
DOD-P-15328 Reducer 728-013
16116 E. 13th Street
Andover, KS 67002
Corrosion Resistant 513 x 419/910 x PRC-DeSoto International Corrosion protection primer.
Primer MIL-PRF- 942 5426 San Fernando Rd.
23377G or later Glendale, CA 91209
Polyurethane paint, 7400 (Color Name: U.S. Paint Corp. Finish paint.
medium gray Pewter) 831 South 21st St.
St. Louis, MO 63130
Waterborne Corrosion 44-GN-60 /44-GN- Deft, Inc. Corrosion protection primer
Resistant Primer 60 CATA 17151 Von Karman Ave.
Irvine, CA 92714
Adhesive RTV-154 General Electric Co. Bond filling instructions placard
Silicone Products Dept. to strut.
Waterford, NY 12188
Clear enamel AA92-C-21C U.S. Paint Corp. Cover filling instructions
placard.
Catalyst AA92-C-22B U.S. Paint Corp. Cover filling instructions
placard.
Flexible drive Shaft with Commercially Available To hone piston assembly inner
1/4 inch chuck barrel.
Hone CF63 or CF68 Snap-On Tools To hone piston assembly inner
3150 Terrace barrel.
Kansas City, MO 64111
Honing oil Sun Concentrate Sun Oil Company To oil stones while honing.
1501 P.O. Box 2039
Tulsa, OK 74102
Hydraulic assembly MCS 352 Aviation Fluids Service Co. To lubricate piston assembly
lubricant St. Louis, MO 63166 inner barrel.
Sealant Class B-2 PRC-DeSoto International To attach washers to reworked
nose gear fork upper torque
take - out lugs.
Stones - 2 2-inch fine JT63-24 Snap-On Tools Used with CF63 or CF68
(400 grit) hones to hone piston assembly
inner barrel.

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 13:11:46 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
32-20-00-6 (Rev 15)

B. Replacement of Damaged Parts.

(1) Replace all parts that show visual wear, cracks or flaws.
(2) Replace all parts that show cracks visual or dye penetrant inspection.
(3) Replace all parts not listed in Table 501, Recommended Checking Methods, before reassembly.
(4) Replace all parts that have machined surfaces or holes that have worn beyond tolerance limits or repair limits
described in this section.
C. Chrome Surface Repair.
CAUTION: When buffing or polishing out scratches on chrome surfaces, extreme caution must be taken not
to exceed drawing tolerances or create low spots by too much localized buffing or polishing.
(1) Scratches or nicks that have not penetrated the chrome plating of the piston and fork assembly or the upper cylinder
assembly may be honed and polished to remove sharp edges that could cause damage to seals. A honing stone or
crocus cloth may be used for this purpose. In the areas not subject to seal travel, scratches, pits and scoring that do
not penetrate the chrome plating are relatively unimportant. The sharp edges of the nicks should be removed by
honing and polishing. The presence of defects in this area, if properly repaired, are considered acceptable.
D. Piston Assembly (257) Inner Diameter Finish Rework.
NOTE: The inner barrel of the piston assembly is phosphate coated. This coating may be rough, causing
premature wear to the seals causing fluid to leak into the air chamber. The following procedure
provides a method for removing this coating.
NOTE: This procedure is not intended to be performed after each overhaul. Perform this procedure only
once.
(1) Using a micrometer, check inside diameter of piston assembly to ensure it is within tolerance.
(2) Check inside of piston assembly for pitting. If pitted, replace the piston assembly.
(3) Hone the inside diameter of the piston assembly to remove a minimal amount of phosphate coating and to achieve a
smooth finish.
(a) Remove air charge valve assembly (260) and packing (259).
(b) Assemble hone, stones, flexible shaft with chuck and a variable speed drill.
NOTE: Install a piece of plastic, rubber hose or other suitable material over the chuck on flexible
shaft to prevent chuck from striking piston bore during honing.
(c) Adjust the hone and install into the end of piston assembly; expand hone assembly until stones are resting
against inner diameter of piston assembly. Apply honing oil as required.
CAUTION: Do not allow stones to get dry during honing; use honing oil freely while operating hone.
Allowing stones to get dry will result in scratching the inner diameter finish of the piston
assembly.
(d) Hone the piston assembly at a maximum speed of 600 RPM, one continuous stroke the length of bore and out,
keeping the hone moving through piston at all times until phosphate is removed.
(e) Thoroughly clean piston assembly after honing. Refer to Nose Gear Assembly - Cleaning.
(f) Using a micrometer, check inside diameter of piston assembly to ensure honing did not exceed the 1.878 inch
diameter.
(g) Install air charge valve assembly (260) and new packing (259).
(4) If piston assembly is not being reassembled, coat inside diameter with hydraulic assembly lubricant MCS 352.
E. Exterior Surface Repair.
(1) Scratches and nicks that have been repaired on forgings by sanding or polishing must be pretreated with DOD-P-
15328 pretreatment primer.
F. Nose Gear Trunnion Repair, Elongated Hole at Shimmy Damper Push-Pull Rod Attach Boss (Refer to Figure 601).
(1) Criterion.
(a) Permissible to rework elongated holes on the trunnion clevis fitting that attaches the shimmy damper push rod.
The elongation shall be removed when holes are line reamed to 0.2492 inch, +0.0005 or -0.0000 inch diameter.
If the elongation exceeds the reamed hole diameter or the wall thickness (edge distance) after reaming is less

than 0.15 inch, replace the trunnion.

(2) Rework.
(a) Jack airplane and remove nose gear assembly from the airplane, refer to the Maintenance Manual.
(b) Remove cotter pin, nut, washers, bolt and spacer attaching shimmy damper push rod to trunnion attach boss.
Discard attaching hardware.
(c) Measure the elongated holes in the trunnion attach boss, if the elongated hole length exceeds the diameter of
the hole after reaming, replace the trunnion.
(d) Ream elongated attach boss holes.
NOTE: The trunnion shall be secured (clamped) to drill press or table to provide accurate
alignment for reaming.
1
Use a 0.2188 inch straight reamer with 0.1895 inch pilot and ream the 3/16 inch elongated holes. After
reaming, check for elimination of elongation and wall thickness and determine if it is feasible to perform the
final reaming step that follows.
2 Use a 0.2495 inch straight reamer with 0.2188 inch pilot and ream 7/32 inch holes to provide a close
tolerance fit (0.2492 inch, +0.0005 or -0.0000 inch diameter hole) for a NAS464P4-11 bolt.
(e) Measure wall thickness (edge thickness). If the wall thickness Is less than 0.15 inch, replace the trunnion.
(f) Attach shimmy damper push rod to trunnion attach boss with the following: install spacer (5542204-200) in the
shimmy damper push rod; install bolt (NAS464P4-11), washer (AN960-416L) each side of push rod, nut
(AN320-4) and cotter pin (MS24665-132).
G. Nose Gear Fork Repair for Cracks at Intersection of Fork and Strut Socket (Refer to Figure 602).
(1) This repair may be performed when inspection indicates cracks have developed. However, if material removed will
require removing material outside of material removal envelope defined in Figure 602, Detail A, the fork must be
replaced.
(2) Preferred Repair.
(a) Remove the fork assembly from the nose gear and machine an undercut in the socket boss observing the
limitations of the material removal envelope in Figure 602, Detail A.
(b) Break all corners, giving particular attention to the forward and aft corners. Forward and aft corners are to be
blended into socket boss with 0.30 inch minimum radius.
(c) Polish entire machined area using progressively finer wet or dry sandpaper with a final polish using 600 grit
paper. Ensure that all machining marks are removed. Refer to Figure 602, Detail B for polish direction.
(d) Perform a dye penetrant inspection to ensure complete crack removal.
(e) Finish area by applying chemical film treatment followed by painting, refer to Painting below. For application of
chemical film treatment refer to the 500 Series Structural Repair Manual, Chapter 51, Protective Treatment of
Metal.
(3) Alternate repair (may be performed without removing gear from the airplane).
(a) Remove uplock assembly from gear.
(b) Locate center of cutout radius and center punch.
(c) Drill a small (Number 30) longitudinal (fore and aft) hole at the radius centerline (center punch).
(d) Drill out the Number 30 drilled hole using progressively larger bits and final ream to 0.25 inch diameter.
(e) Saw out remaining material and file smooth.
(f) Break all corners, giving particular attention to the forward and aft corners. Forward and aft corners are to be
blended into socket boss with 0.30 inch minimum radius.
(g) Polish entire machined area using progressively finer wet or dry sandpaper with a final polish using 600 grit
paper. Ensure that all machining marks are removed. Refer to Figure 602, Detail B for polish direction.
(h) Perform a dye penetrant inspection to ensure complete crack removal.
(i) Finish area by applying chemical film treatment followed by painting, refer to Painting below. For application of
chemical film treatment refer to the 500 Series Structural Repair Manual, Chapter 51, Protective Treatment of
Metal.

H. Painting.
(1) Preliminary.
(a) Verify areas to be painted are free of dirt, oil, grease and/or corrosion.
(b) Do not paint tires, strut air valves, data plates, bearings, polished pistons, switches, wire bundles, clamps,
hydraulic hoses, wheels, axle spindle area within the wheels or contacting areas of the lower to upper torque
links.
(2) Pretreatment Primer.
(a) Mix and apply DOD-P-15328 pretreatment primer in accordance with the manufacturer’s instructions.
(3) Corrosion Resistant Primer.
(a) Mix and apply MIL-PRF-23377 corrosion resistant primer in accordance with manufacturer's instructions.
(4) Top Coat.
(a) Polyurethane paint consists of two components; a base and a catalyst. Mix top coat in accordance with the
manufacturer’s instructions.
I. Outer Cylinder Lower Bearing Area Corrosion Inspection, Removal, Modification and Prevention.
(1) Inspection of the outer cylinder lower bearing area.
(a) Inspect the outer cylinder lower bearing area as shown for damage to the finished surface due to corrosion.
Refer to Figure 603. If the finished surface is not damaged and no corrosion exists, proceed to step (3). If
corrosion is present on the outer cylinder lower bearing surface area, proceed to step (2).
(2) Preliminary rework of outer cylinder lower bearing surface area.
(a) Determine if the outer cylinder lower bearing surface area can be reworked (Refer to Figure 603):
1 Verify that no corrosion exists on the uppermost 0.5 inch of the bearing surface. If corrosion is found in this
area, contact Citation Customer Service Department for disposition.
2 Using a stainless steel wire brush or glass bead peening, remove the corrosion from the outer cylinder
lower bearing area. Glass bead peening may be used to remove corrosion from the pits which were not
removed with the stainless steel wire brush.
3 Clean the outer cylinder bearing area with an approved solvent to remove all grease and dirt.
4 Using a dial micrometer with a pointed tip, measure the inner diameter of the outer cylinder lower bearing
area and determine the average bearing surface diameter to include the depth of pit.
NOTE: Average bearing surface diameter is determined by measuring the inner diameter at a
minimum of four different locations, starting at the most damaged location and
rotating 45 degrees either side, plus one additional location and averaging the four
measurements.
(b) If the average bearing surface diameter is greater than 2.908 inches, or the maximum pit depth is greater than
0.015 inch, contact Citation Customer Service Department.
(c) If the average bearing surface diameter is less than 2.908 inches, proceed to step (3).
NOTE: If the outer cylinder lower bearing surface contains pits which remain after corrosion
removal, and it is estimated that upon removal of these pits the outer cylinder lower
bearing surface may not meet the absolute maximum average diameter of 2.908 inches or
the maximum pit depth is greater than 0.015 inches, it may not be feasible to rework the
outer cylinder. The outer cylinder may require replacement.
(3) Rework of outer cylinder lower bearing surface area.
(a) If the average bearing surface diameter is greater than 2.908 inches, or the maximum pit depth is greater than
0.015 inch, contact Citation Customer Service Department.
(b) Use a rotary stainless steel wire brush or glass bead peening to remove all corrosion from the bearing and
retainer ring areas. Glass bead penning may be used to remove corrosion from the pits which were not removed
with the stainless steel wire brush. Ensure that all corrosion is removed prior to proceeding.
(c) Clean the lower bearing surface and the retainer ring areas with an approved solvent to remove all grease and
dirt. Wipe off solvent with a clean absorbent rag. Do not allow solvent to dry on the surface, remove all solvent
residue.

(d) Mask the machined step at the top edge of the lower bearing surface and a 0.50 inch band of the upper portion
of the lower bearing surface area, to prevent epoxy primer from being applied to these surfaces.
(e) Reclean the unmasked portion of the lower bearing surface with approved solvent. Wipe off solvent with a clean
absorbent rag. Do not allow solvent to dry on the surface, remove all solvent residue.
(f) Immediately prime the abraded area with MIL-PRF-23377 corrosion resistant primer by one of the following
procedures:
NOTE: Primer must be applied to clean surfaces within 30 minutes of completion of sanding
procedure. An oxide film which provides minimal adhesion for primer begins to form
immediately after working. Poorly adhered primer will result in accelerated corrosion.
NOTE: For exact mixing instructions for MIL-PRF-23377 corrosion resistant primer, refer to the
manufacturer’s instructions.
(g) Cure MIL-PRF-23377 corrosion resistant primer coating in accordance with the manufacturer’s instructions.
J. Repair of Nose Gear Fork at Upper Torque Take - Out Lugs.
(1) This repair may be performed when inspection indicates gouge, chafe, and corrosion damage on the surfaces of the
Torque Take - Out Lugs on the upper portion of the nose landing gear fork. The gouge damage is caused by the
protruding shoulders of the torque link bushings. The gouge damage is a circular ridge that has approximately the
same diameter as the shoulder bushing.
(2) Do the Repair of the Nose Gear Fork at Upper Torque Take - Out Lugs.
(a) Measure the diameters of both lug holes, noting the minimum and maximum dimensions and the clocking of
those measurements. If the maximum diameter exceeds 0.5006 inch (12.7152 mm) or if the difference between
the maximum and minimum diameters exceeds 0.0015 inch (0.0381 mm), contact Citation Customer Service by
telephone (316) 517-6221 or fax (316) 517-8500.
(b) Blend smooth the outer surface(s) of the damaged lug(s) using 180 grit sandpaper. Remove only as much
material as is necessary to eliminate all evidence of surface anomalies. Refer to Figure 604, Detail A for blend
area. Rework surface(s) flat and perpendicular with the lug bores. If the dimension "D" shown in Figure 604,
Detail B is greater than 1.888 inch (47.955 mm), no further rework of the lug is required and installation of the
washers is not necessary. Proceed to step (d) and skip step (g). If dimension "D" is less than 1.814 inches
(46.076 mm), the fork must be replaced.
(c) Installation of two washers, one on each lug outer face, will be required. Rework both lug surfaces by blending
flat and perpendicular to the lug bore until dimensiion "D", as shown in Figure 604, Detail B equals 1.819,
+0.005 or -0.005 inches (46.203, +0.127 or -0.127 mm).
NOTE: The final dimension as measured from washer outer surface to washer outer surface
must be maintained to ensure a proper fit with the mating torque link assembly. Refer to
Figure 604, Detail C.
(d) Smooth and polish the reworked areas to a RMS 63 or smoother finish and provide a gentle and consistent
transition between reworked and no-reworked areas (0.125 inch (3.175 mm) minimum transition radius).
(e) Surface eddy current inspect the reworked areas for cracks per Model 500 Series Non Destructive Testing
Manual. If any anomalies or a crack is found, contact Citation Customer Service by telephone (316) 517-6221 or
fax (316) 517-8500.
(f) Chemically clean, epoxy prime and then apply polyurethane topcoat to the fork surfaces requiring paint.
(g) Procure two NAS1149C-0832B washers and attach one to each of the fork lug reworked surfaces using Class
B-2 sealer, refer to Figure 604, Detail C. These washers will take up the space at the fork-to-link interface when
the fork is installed on the aircraft.
NOTE: The final dimension of the lug plus the B-2 sealer and washer stack-up must be as shown
in Figure 604, Detail C to make sure that a proper fit with the mating torque assembly. A
dimension of 0.005 inch (0.127 mm) is assumed for the thickness of the B-2 sealer.
K. Service Placards.
(1) Bond filling instruction placard to trunnion with RTV-154. Prepare and apply adhesive in accordance with
manufacturer’s instructions.

Figure 601 : Sheet 1 : Nose Gear Trunnion Repair, Elongated Hole at Shimmy Damper Push-Pull Rod Attach Boss

Figure 602 : Sheet 1 : Nose Gear Fork Assembly Repair

Figure 602 : Sheet 2 : Nose Gear Fork Assembly Repair

Figure 602 : Sheet 3 : Nose Gear Fork Assembly Repair

Figure 603 : Sheet 1 : Cylinder and Piston Corrosion Repairs

Figure 604 : Sheet 1 : Repair of Nose Gear Fork at Upper Torque Take - Out Lugs

Figure 604 : Sheet 2 : Repair of Nose Gear Fork at Upper Torque Take - Out Lugs
A96633

NOSE LANDING GEAR FORK

P/N 5542300

BLEND DIMENSION "D"

VIEWB−B

1.893, +0.005 or −0.005 INCHES B−2 SEALER

(40.082, +0.127 or −0.127 mm)

NAS1149C−0832B
(2 PLACES)

NOSE LANDING GEAR FORK

P/N 5542300

TWO (2) WASHER INSTALLATION, ONE (1) WASHER PER LUG FACE
VIEWC−C
BB5542T300−1
CC5542T300−1

NOSE GEAR ASSEMBLY - ASSEMBLY

1. Assembly
A. Tools and Equipment (Refer to Illustrated Parts List).
NOTE: Equivalent substitutes may be used for the listed items:
NAME NUMBER MANUFACTURER USE
Hydraulic assembly MCS 352 Aviation Fluids Service Co. Lubricate and protect surfaces
lubricant St. Louis, MO 63166 normally in contact with
hydraulic fluid and prevent entry
of water.
Oakite special Oakite Products, Inc. Protection of machined
protective oil 50 Valley Road surfaces during storage.
Berkeley Heights, NJ 07922
Pretreatment Primer 728-013701-702 Sherwin-Williams Inc Lubricate press-fit trunnion
DOD-P-15328 16116 E. 13th Street bearings during installation.
Andover, KS 67002
Corrosion Resistant 513 x 419/910 x 942 PRC-DeSoto International Corrosion protection primer.
Primer MIL-PRF- 5426 San Fernando Rd.
23377G or later Glendale, CA 91209
Corrosion Resistant 02-Y-4002-4-40 Deft, Inc. Corrosion protection primer.
Primer MIL-PRF- CATA 17151 Von Karman Ave.
23377G or later Irvine, CA 92714
Teflon O-ring CJMD 132-003 Cessna Aircraft Co. To install Teflon seals on
Installation Tool Citation Marketing Div. isolation piston.
Department 579
P.O. Box 7706
Wichita, KS 67277
B. Trunnion Assembly (Refer to Illustrated Parts List).
(1) Press new pivot bearings (11) into trunnion (9) with MIL-PRF-23377 corrosion resistant primer and stake in place.
(2) Press bearings (10) with MIL-PRF-23377 corrosion resistant primer, into trunnion.
CAUTION: Do not press against inner bearing race. Use a suitable arbor and mandrel to prevent damage to
bearings.
(3) Press bearing (12) with MIL-PRF-23377 corrosion resistant primer, into trunnion.
C. Piston and Fork Assembly (Refer to Illustrated Parts List).
NOTE: Ensure that phosphate coating has been removed from inner surface of piston assembly, if not
refer to, Nose Gear Assembly - Repair, Piston Assembly (257) Inner Diameter Finish Rework.
(1) If fork has been removed from piston, coat mating surfaces of piston and fork with MIL-PRF-23377 corrosion
resistant primer and press piston into fork socket.
NOTE: Valve hole and attach holes in piston barrel and fork must be aligned when installing piston.
(2) Install uplock roller assembly.
(a) Install bolt (171) through washer (173), left brackets (168 and 169), fork, right brackets (168 and 169), washer
(173) and nut (175). Do not tighten nut completely.
(b) Install bolt (170) through washer (172), left bracket (168), spacer (174), left bracket (169), fork, right bracket
(168), spacer (174), right bracket (169), washer (173) and nut (175). Do not tighten nut completely.
NOTE: Washer (172) is thinner than washers (173).
NOTE: Bolts (170, 171 and 177) are not interchangeable. Bolt (177) must be marked (NAS464) on
the head.
NOTE: Nut (179) is thinner than nuts (175).

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 13:12:07 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
32-20-00-7 (Rev 17)

(c) Tighten nuts (175) and install cotter pins (176).

(3) Immerse all packings and seals in hydraulic oil.
(4) Install one rubber packing (237) and two Teflon packings (235) on isolation piston (238) (refer to Figure 701).
(a) Place the -2 holding fixture with the narrow end down in the center of an arbor press base plate. Place the upper
Teflon packing in the center of the holding fixture upper surface.
(b) Position the -1 expansion cone with point down through the center of the packing and into the holding fixture.
(c) Invert the isolation piston and center over the upper portion of the expansion cone.
(d) Place the -4 holding fixture over the isolation piston shaft.
CAUTION: Ensure teflon packing is centered on the holding fixture and expands uniformly as pressure is
applied to expansion cone.
(e) Smoothly compress the stack with the arbor press until the Teflon packing slips into the first annular groove of
the inverted isolation piston.
(f) Disassemble the tools from the isolation piston.
(g) Place the -4 holding fixture on the arbor press base plate with the small end down. Center the lower Teflon
packing on the upper surface of the holding fixture and place the -3 expansion cone through the center of the
Teflon packing.
CAUTION: Ensure teflon packing is centered on the holding fixture and expands uniformly as pressure is
applied to expansion cone.
(h) Insert the isolation piston through the expansion cone and into the holding fixture. Place the -6 Ram over the
isolation piston and compress until Teflon packing slips into annular groove.
(i) Disassemble the tools from the isolation piston.
(j) Place the -5 contraction cylinder on the arbor press base plate with the smallest inside diameter end down.
(k) Center isolation piston on contraction cylinder with piston shaft pointing down.
CAUTION: Spacer height or hole diameter on the arbor press base plate must be sufficient to allow the
piston to be pressed completely through the contraction cylinder without obstruction.
(l) Center -6 ram on the isolation piston and press through contraction cylinder.
(m) Install the O-ring packing in the middle groove in the normal manner.
(5) Install spring (239) and stop (240) on isolation piston (238) and secure with retainer (241).
(6) Coat the inner wall of the piston and fork assembly barrel with a thin layer of hydraulic fluid or hydraulic assembly
lubricant.
(7) Insert isolation piston (238) into piston (257) and push to bottom of barrel.
NOTE: Install isolation piston with stop (240) toward bottom of piston (257).
(8) Cover outside surface of piston with a thin coat of hydraulic fluid.
(9) Slide lock ring (252), scraper retainer (250) and scraper (248) onto piston (257).
(10) Install polypak seal (247) into inner groove in bearing (246).
NOTE: Install polypak seal with expander ring edge upwards towards fluid.
(11) Install back retainer (244) and packing (243) onto outside groove in bearing (246).
(12) Slide bearing assembly (246) onto piston barrel.
NOTE: Install bearing assembly with outside packing groove toward the top of piston barrel.
(13) Slide spacer (242) onto piston barrel.
CAUTION: Setscrews must be recessed below bearing surface. Make sure resistance is felt when installing
screws to ensure self-locking capability. Replace screws not indicating self-locking capability.
(14) Screw bearing (233) onto piston until setscrew holes align with holes in piston and secure with four setscrews (234).
Torque setscrews to 10-20 inch-pounds.
NOTE: When a new bearing (233) is required to be installed, it is possible that the setscrew holes will
not align with the recesses in the piston. It is permissible to drill a new set of recesses in the
piston for alignment. However, this procedure is only acceptable for three bearing

replacements (four sets of recesses in the piston).

D. Piston and Fork Installation (Refer to Illustrated Parts List).
(1) Pack area all around bearing (246) with hydraulic assembly lubricant (MCS 352) to resist entry of water about
bearing interface with strut cylinder collar.
(2) Cover inside of cylinder with a thin coat of hydraulic fluid.
(3) Slide piston assembly into cylinder (231) and install scraper (248), scraper retainer (250) and lock ring (252).
CAUTION: Make certain lock ring is seated in the cylinder groove and the retainer is then extended to lock it in
place.
E. Cylinder Installation (Refer to Illustrated Parts List ).
(1) Slide retainer (229) over cylinder (231).
(2) Install bearing (228) on cylinder (231) and secure with retainer (227).
(3) Slide cylinder into trunnion (9) and secure with retainer (229).
F. Assembly and Installation of Torque Links (Refer to Illustrated Parts List).
(1) Coat bushings (160 and 162) with MIL-PRF-23377 corrosion resistant primer and press into upper torque link (154).
(2) Coat bushings (160) with MIL-PRF-23377 corrosion resistant primer and press into lower torque link (155).
NOTE: When new torque link bushings are installed, it may be necessary to mill and ream bushings
(160) to dimensions shown in Nose Gear Assembly - Fits and Clearances.
CAUTION: Install torque links as shown in Figure 1001, or damage could result.
(3) Install upper and lower torque links (154 and 155) with shafts (156) and secure shafts with pins (158 and 159).
(4) Install torque link interconnect bolt (163), washers (165), spacer (164), nut (166) and cotter pin (167).
G. Valve and Plug Installation (Refer to Illustrated Parts List ).
(1) Install air valve (260) and packing (259).
NOTE: If new air valve is being installed, discard packing and replace with phosphate ester base fluid
resistant packing, Part Number NAS1611-015.
(2) Lock wire air valve to piston using double twist method.
(3) Install metering pin (225) and packing (226).
H. Lubrication (Refer to Illustrated Parts List).
(1) Grease torque link lubrication points with grease per MIL-PRF-23827.
2. Storage
A. Storage Procedure.
(1) Release air from air valve, refer to Nose Gear Assembly - Disassembly.
(2) Remove metering pin from cylinder top and drain hydraulic oil from cylinder. Replace plug.
(3) Collapse strut assembly. Coat exposed surface of piston with protective oil.
(4) Wrap collapsed strut in grease proof paper, then kraft paper and pack in rigid container.
(5) Container shall be stored in a cool, dry, well ventilated area on a noncorrosive base.

Figure 701 : Sheet 1 : Isolation Piston Teflon Packing Installation

Figure 701 : Sheet 2 : Isolation Piston Teflon Packing Installation

Figure 701 : Sheet 3 : Isolation Piston Teflon Packing Installation

NOSE GEAR ASSEMBLY - FITS AND CLEARANCES

1. Fits and Clearances
A. Trunnion Assembly 5542301-5
A3834
8 3
2

7
5

1
6342T1028

(1) 3.875 inch, +0.001 Or -0.000 inch (98.42 mm, +0.03 or -0.00 mm ) diameter
(2) 2.8096 inch, +0.0015 Or -0.0000 inch (71.364 mm, +0.038 or -0.000 mm ) diameter
(3) 1.7476 inch, +0.0010 Or -0.0000 inch (44.389 mm, +0.025 or -0.000 mm ) diameter
(4) 0.8125 inch, +0.0010 Or -0.0000 inch (20.638 mm, +0.025 or -0.000 mm ) diameter
(5) 0.7500 inch, +0.0005 Or -0.0000 inch (19.050 mm, +0.013 or -0.000 mm ) diameter
(6) 0.6250 inch, +0.0007 Or -0.0000 inch (15.875 mm, +0.018 or -0.000 mm ) diameter
(7) 0.2500 inch, +0.0035 Or -0.0000 inch (6.350 mm, +0.089 or -0.000 mm ) diameter
(8) 0.1895 inch, +0.0005 Or -0.0000 inch (4.813 mm, +0.003 or -0.000 mm ) diameter
B. Cylinder Assembly 5542100-2, -3
A3838

2 1

6342T1029

(1) 0.4991 inch, +0.0015 or -0.0000 inch (12.677 mm, +0.038 or -0.000 mm ) diameter
(2) 0.156 inch, +0.004 or -0.000 inch (4.813 mm, +0.10 or -0.000 mm ) diameter
C. Piston Assembly 5542101-1, 5542105-1, -2, -3
A4097

1
6342T1029

(1) 1.875 inch, +0.003 or -0.000 inch (47.63 mm, 0.08 or -0.00 mm) diameter
D. Fork 5542300-1

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 13:12:17 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
32-20-00-8 (Rev 15)

(1) 0.4991 inch, +0.0015 or -0.0000 inch (12.677 mm, 0.038 or -0.000 mm) diameter
(2) 0.156 inch, +0.004 or -0.000 inch (3.96 mm, 0.10 or -0.00 mm) diameter
(3) 0.250 inch, +0.003 or -0.000 inch (6.35 mm, 0.08 or -0.00 mm) diameter
(4) 1.376inch, +0.002 or -0.000 inch (34.95 mm, 0.05 or -0.00 mm) diameter
(5) 1.875 inch (47.62 mm) diameter x 0.250 inch (6.35 mm) deep
(6) 1.898 inch, +0.000 or -0.005 inch (48.209, +0.000 or -0.127 mm)
E. Bearing 6642307-6

(1) 2.284 inch, +0.005 or -0.000 inch (58.01 mm, 0.13 or -0.00 mm) diameter
(2) 2.252 inch, +0.003 or -0.000 inch (57.23 mm, 0.08 or -0.00 mm) diameter
(3) Uniform taper from 2.282 to 2.252 inch (58.01 to 57.25 mm) diameter
(4) 2.874, +0.000 or -0.002 inch (73.00 mm, 0.00 or-0.05 mm) diameter
F. Bearing 5542308-7
A3842

1
6342T1029

(1) 2.497, +0.000 or -0.003 inch (63.42 mm, 0.00 or -0.08 mm) diameter
G. Torque Link - Upper 5542302-1

A96652
4

2 3

6342T1027

(1) 0.4997 inch, +0.0004 or -0.0000 inch (12.692 mm, 0.102 or -0.000 mm) diameter
(2) 0.1250 inch, +0.0015 or -0.0000 inch (3.175 mm, 0.038 or -0.000 mm) diameter
(3) 0.6250 inch, +0.0005 or -0.0000 inch (15.875 mm, 0.013 or -0.000 mm) diameter
(4) 1.9025 inch, +0.0025 or -0.0025 inch (48.3235, +0.06350 or -0.06350 mm)
H. Shaft - Torque Link Attach 5542208-1, -3

(1) 0.4988 inch, +0.0002 or -0.0004 inch (12.670 mm, 0.005 or -0.010 mm) diameter
(2) 0.156 inch, +0.004 or -0.000 inch (3.96 mm, 0.10 or -0.00 mm) diameter
I. Torque Link - Lower 5542302-2
A96653
4

2 3

6342T1027

(1) 0.2495 inch, +0.0010 or -0.0000 inch (6.337 mm, 0.025 or -0.000 mm) diameter
(2) 0.1250 inch, +0.0015 or -0.0000 inch (3.175 mm, 0.038 or -0.000 mm) diameter
(3) 0.6250 inch, +0.0005 or -0.0000 inch (15.875 mm, 0.013 or -0.000 mm) diameter
(4) 1.9025 inch, +0.0025 or -0.0025 inch (48.3235, +0.06350 or -0.06350 mm)
J. Torque Link End Bushing 5041017-2
A3846
1

5 3

4 2
6342T1029

(1) 0.060 inch, +0.010 or -0.010 inch (1.52 mm, 0.25 or -0.25 mm)
(2) 0.12 inch (6.4 mm) radius
(3) 0.5000 inch, +0.0010 or -0.0000 inch (12.700 mm, 0.025 or -0.000 mm) diameter
(4) 0.094 inch, +0.010 or -0.010 inch (2.39 mm, 0.03 or -0.03 mm) diameter hole
(5) 0.6255 inch, +0.0005 or -0.0000 inch (15.888 mm, 0.013 or -0.000 mm) diameter
K. Spacer 5542209-1
A3849

5594T1054

(1) 0.625 inch, +0.001 or -0.001 inch (15.88 mm, 0.03 or -0.03 mm) diameter
(2) 0.2500 inch, +0.0005 or -0.0005 inch (6.350 mm, 0.013 or -0.013 mm) diameter
(3) 0.3730 inch, +0.0004 or -0.0004 inch (9.474 mm, 0.010 or -0.010 mm) diameter
L. Bushing NAS77A6-22
A4328

NAS77A6−022

(1) 0.3730 inch, +0.0004 or -0.0004 inch (9.474 mm, 0.010 or -0.010 mm) diameter
(2) 0.5013 inch, +0.0000 or -0.0007 inch (12.733 mm, 0.000 or -0.018 mm) diameter

NOSE LANDING GEAR ASSEMBLY

NOMENCLATURE EFFECTIVITY UNITS
PER
ITEM PART NUMBER 1 2 3 4 5 6 7 FROM TO ASSY
- NOSE LANDING GEAR ASSEMBLY
- 1 5542000-4 . GEAR ASSY A 01
- . GEAR ASSY SPARE
2 5542000-200 A 01
REFER TO NOTE 1
- 3 5542000-7 . GEAR ASSY B 01
- . GEAR ASSY SPARE
4 5542000-203 B 01
REFER TO NOTE 2
5 5542000-9 . GEAR ASSY C 01
GEAR ASSY SPARE
- 5A 5542000-205 . D 01
REFER TO NOTE 7
- 6 5542301-3 . . TRUNNION ASSY A 01
7 5542301-5 . . TRUNNION ASSY A THRU C 01
- 7A 5542301-18 . . TRUNNION ASSY D 01
- 8 5542301-4 . . . TRUNNION A 01
9 5542301-6 . . . TRUNNION B,C 01
- 9A 5542301-17 . . . TRUNNION D 01
10 MS27642-16 . . . BEARING 02

11 MS21240-10C016 . . . SLEEVE- 02
BEARING OUTER
BEARING-INNER
11A . . . REFER TO NOTE RF
6
12 MS27642-33 . . . BEARING 01
SHIMMY DAMPER
- 13 5543001-1 . . FSO 5543001-8 A NP
REFER TO NOTE 3
SHIMMY DAMPER
14 5543001-3 . . FSO 5543001-8 B,C NP
REFER TO NOTE 3
SHIMMY DAMPER
- 14A 5543001-5 . . FSO 5543001-8 A,B,C NP
REFER TO NOTE 3

- . . SHIMMY DAMPER
14B 5543001-8 A,B,C 01
REFER TO NOTE 3
ATTACHING
PARTS

15 NAS464P3-11 . . BOLT REFER TO 01

NOTE 4
- 16 NAS464P4-11 . . BOLT REFER TO 01
NOTE 5

. . WASHER REFER TO
17 NAS1149F0332P 02 R
NOTE 4

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 13:12:20 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
32-20-00-1001 (Rev 13)

- . . WASHER REFER TO
18 NAS1149F0432P 02 R
NOTE 5

. . SPACER REFER TO
19 5542204-1 01
NOTE 4
- . . SPACER REFER TO
20 5542204-200 01
NOTE 5
. . NUT REFER TO NOTE
21 AN320-3 01
4

- . . NUT REFER TO NOTE

22 AN320-4 01
5

. . COTTER PIN REFER

23 MS24665-134 01
TO NOTE 4
- . . COTTER PIN REFER
24 MS24665-132 01
TO NOTE 5
25 NAS1149F1232P . . WASHER AR
26 RSN75SK . . RETAINER V80756 01
---*---
NOTE 1: 5542000-200 IS THE SAME AS 5542000-4 LESS WHEEL AND TIRE ASSY AND
NOTE 2: 5542000-203 IS THE SAME AS 5542000-7 LESS WHEEL AND TIRE ASSY AND
NOTE 3: REFER TO SHIMMY DAMPER COMPONENT PARTS MANUAL FOR DETAILS
NOTE 4: SPARE EXCEPT FOR REWORKED TRUNNION
SPARE WHEN SHIMMY DAMPER ATTACH BOSS REPAIR HAS BEEN PERFORMED. REFER
NOTE 5:
TO REPAIR SECTION
NOTE 6: REFER TO PARTS CATALOG FOR CORRECT INNER BEARING.
NOTE 7: 5542000-205 IS THE SAME AS 5542000-7
NOMENCLATURE EFFECTIVITY UNITS
PER
ITEM PART NUMBER 1 2 3 4 5 6 7 FROM TO ASSY
- NOSE LANDING GEAR ASSEMBLY
. . GEAR ASSY-
75 5542214-1 A 01
STEERING
GEAR ASSY-
- 75A 5542214-3 . . B,C,D 01
STEERING
ATTACHING
PARTS
76 AN4H10A . . BOLT 06
77 NAS1149F0432P . . WASHER 06
---*---
78 ATLF12-111 . . . BEARING V15860 01
79 5542401-1 . . COVER-FORWARD 01
COVER-REAR FSO
- 80 5542401-2 . . A NP
5542401-3
81 5542401-3 . . COVER-REAR B,C,D 01

ATTACHING
PARTS
82 MS35266-60 . . SCREW 02
83 NAS1149F0332P . . WASHER 02
---*---
84 5542215-2 . . GEAR-STEERING 01
ATTACHING
PARTS
85 NAS561P10-22 . . PIN-SLOTTED UPPER 01
---*---
86 AN4-20A . . BOLT-STOP 02
87 5542219-1 . . SPACER 02
88 NAS1149F0432P . . WASHER 02
89 MS21083N4 . . NUT 02
- . . SHAFT FSO 5542216-
90 5542216-2 A,B NP
3
91 5542216-3 . . SHAFT C,D 01
92 5542303-2 . . FORK-UPPER 01
ATTACHING
PARTS
93 NAS561P10-24 . . PIN-SLOTTED LOWER 01
---*---
94 5542221-2 . . SHAFT 02
95 MJHT891 . . BEARING V60380 02
96 MS16625-1075 . . RETAINER 02
97 5542306-1 . . CROSS-STEERING 01
98 5542221-1 . . SHAFT 01
99 NAS464P3-50 . . BOLT 01
100 AN970-3 . . WASHER 02
101 AN320-3 . . NUT 01
102 MS24665-132 . . COTTER PIN 01
FORK ASSY-
- 103 5542304-3 . . 01
STEERING LOWER
104 5542304-4 . . . FORK 01
105 JHTT89C . . . BEARING V60380 02

NOMENCLATURE EFFECTIVITY UNITS

PER
ITEM PART NUMBER 1 2 3 4 5 6 7 FROM TO ASSY
- NOSE LANDING GEAR ASSEMBLY
PLACARD-SHOCK
- 150 5540001-4 . . STRUT FILLING A 01
INSTRUCTIONS

PLACARD-SHOCK
151 5540001-12 . . STRUT FILLING B,C,D 01
INSTRUCTIONS
WHEEL AND TIRE
- 152 5542103-2 . . ASSY ALT FOR A,B 01
5542103-4
WHEEL AND TIRE
153 5542103-4 . . C 01
ASSY
154 5542302-1 . . LINK ASSY-UPPER 01
155 5542302-2 . . LINK ASSY-LOWER 01
ATTACHING
PARTS

156 5542208-1 . . SHAFT FSO 5542208- A,B NP

3
- 157 5542208-3 . . SHAFT C,D 02
158 MS16562-43 . . PIN-SLOTTED UPPER 01
. . PIN-SLOTTED
159 MS16562-45 01
LOWER
---*---
160 5041017-2 . . . BUSHING 04
161 NAS516-1A . . . FITTING-GREASE 05
162 NAS77A6-22 . . . BUSHING 02
163 AN174-13 . . BOLT 01
164 5542209-1 . . SPACER 01
165 NAS1149F0432P . . WASHER 02
166 AN310-4 . . NUT 01
167 MS24665-134 . . COTTER PIN 01
BRACKET-UPLOCK
168 5542402-2 . . LH OUTBOARD RH 02
INBOARD
BRACKET-UPLOCK
169 5542402-1 . . LH INBOARD RH 02
OUTBOARD
ATTACHING
PARTS
170 AN4-46 . . BOLT-FORWARD 01
171 AN4-41 . . BOLT-REAR 01
172 NAS1149F0432P . . WASHER 01
173 NAS1149F0463P . . WASHER 03
. . SPACER-FORWARD
174 NAS43DD4-46 02
BOLT
175 AN310-4 . . NUT 02
176 MS24665-134 . . COTTER PIN 02
---*---

177 NAS464P4-71 . . BOLT 01

178 NAS1149F0463P . . WASHER 02
179 AN320-4 . . NUT 01
180 MS24665-134 . . COTTER PIN 01
. . SPACER
181 5542218-2 02
SOUTBOARD
182 5542218-1 . . SPACER-CENTER 01
183 MS21240-06C022 . . BEARING-UPLOCK 03
184 NAS75-6-029 . . BUSHING 02
185 AN5-55 . . BOLT 01
186 0842000-37 . . BUCKET-AXLE 02
. . SPACER-AXLE
187 5542223-1 02
REFER TO NOTE 1
SPACER-AXLE
- 187A 5542223-2 . . 02
REFER TO NOTE 2
188 0842000-36 . . TUBE 01
189 NAS1149F0532P . . WASHER 01
190 AN310-5 . . NUT 01
191 MS24665-230 . . COTTER PIN 01
PLACARD-NOSE
192 5540001-8 . . 01
WHEEL INFLATION
5542223-1 SPACERS ARE USED WITH ALL WHEEL ASSEMBLIES EXCEPT GOODYEAR
NOTE 1: WHEEL ASSEMBLIES WITH TIMKEN BEARING CUPS (13621) AND TIMKEN BEARING CONES
(13600LA902A1).
5542223-2 SPACERS ARE USED WITH GOODYEAR WHEEL ASSEMBLIES WITH TIMKEN
NOTE 2: BEARING CUPS (13621) AND TIMKEN BEARING CONES (13600LA902A1) AND MAY BE USED
AS AN ALTERNATE TO 5542223-1 TO ACHIEVE A SLIP FIT.
NOMENCLATURE EFFECTIVITY UNITS
PER
ITEM PART NUMBER 1 2 3 4 5 6 7 FROM TO ASSY
- NOSE LANDING GEAR ASSEMBLY
225 5542225-1 . . METERING PIN 01
226 NAS1612-5 . . PACKING-O RING 01
227 RST293CD . . RETAINER V80756 01
228 MS27642-47 . . BEARING 01
229 RRT387CD . . RETAINER V80756 01
- 230 5542100-2 . . CYLINDER ASSY A 01
231 5542100-3 . . CYLINDER ASSY B,C,D 01
- . . BEARING ASSY FSO
232 5542308-3 A NP
5542308-7
. . BEARING AND
233 5542308-7 B,C,D 01
ORIFICE ASSY
234 NAS1081-4B4 . . SETSCREW 04

. . O-RING TEFLON
235 R513-325 V07060 02
REFER TO NOTE 1
- 236 . . DELETED-NOT USED
. . O-RING REFER TO
237 NAS1611-325 01
NOTE 1
. . PISTON ASSY-
238 5542000-204 01
ISOLATION
239 5541400-1 . . SPRING 01
240 5541209-1 . . STOP 01
241 CM2689-5 . . RETAINER 01
242 5542206-1 . . SPACER 01
. . O-RING REFER TO
243 NAS1611-333 01
NOTE 1
RETAINER-PACKING
244 MS28774-333 . . 01
REFER TO NOTE 1
- . . BEARING ASSY FSO
245 5542307-3 A NP
6642307-1
. . BEARING ASSY FSO
246 5542307-6 B,C NP
6642307-1
- 246A 6642307-1 . . BEARING ASSY 01
T SEAL POLYPAK
247 P77A5450 . . V30781 01
REFER TO NOTE 1
. . SCRAPER REFER TO
248 S11065-23T V09257 A,B,C,D 01 R
NOTE 1 AND 2
SCRAPER ALT FOR
- 248A S11065-23 . . S11065-23T REFER V09257 A,B,C,D 01 R
TO NOTE 1 AND 2
- 248B MS28776M2-23 . . SCRAPER E 01 R
- . . RETAINER FSO
249 5542207-1 A,B NP
5542207-2
250 5542207-2 . . RETAINER-SCRAPER C,D 01
- . . LOCK RING FSO
251 CM2690-17 A NP
CM2690H17
252 CM2690H17 . . LOCK RING B,C,D 01
- . . LOCK RING ALT FOR
253 CM2690C17 01
CM2690H17
- . . FORK & PISTON
254 5542000-3 01
ASSY
- 255 5542101-1 . . . PISTON ASSY NP
FSO 5542105-2
- . . . PISTON ASSY
256 5542105-1 NP
FSO 5542105-2
. . . PISTON ASSY
257 5542105-2 NP
FSO 5542105-3
- 257A 5542105-3 . . . PISTON ASSY 01

258 5542300-1 . . . FORK 01

FORK
ALTERNATE FOR
5542300-1 NOT
- 258A 5542300-3 . . . 01
USED WITH
GRAVEL RUNWAY
KIT OPTION
. . PACKING-O RING
259 NAS1611-015 01
REFER TO NOTE 1
260 AN6287-1 . . VALVE-AIR CHARGE 01
IDENTIFICATION
- 261 5540001-5 . . PLATE FSO 5541001- A NP
13

262 5540001-13 . . IDENTIFICATION B,C,D 01

PLATE
ATTACHING
PARTS
263 MS21318-14 . . SCREW-DRIVE 02
---*---
NOTE 1: THIS PART MAY BE ORDERED AS PART OF LANDING GEAR SEAL KIT NUMBER CPD3.
THE MS28776M2-23 METAL SCRAPER RING CAN BE USED BY OPERATORS EXPERIENCING
NOTE 2:
ICE INDUCED SEAL DAMAGE
- Item Not Illustrated

Figure 1001 : Sheet 1 : NOSE LANDING GEAR ASSEMBLY

Figure 1001 : Sheet 2 : NOSE LANDING GEAR ASSEMBLY

Figure 1001 : Sheet 3 : NOSE LANDING GEAR ASSEMBLY

Figure 1001 : Sheet 4 : NOSE LANDING GEAR ASSEMBLY

NOSE LANDING GEAR ASSEMBLY - ILLUSTRATED PARTS LIST

1. Illustrated Parts List
A. Introduction.
(1) The Illustrated Parts List will help the customer to order, keep, and supply the nose landing gear components. It will
also identify new and reclaimed parts. It is not approved for any other purpose.
(2) This parts list includes the nose landing gear assembly used on the Citation airplanes. Part numbers:
6642000-2 6642000-5 6642000-6 6642000-8 6642000-10
6642000-11 6642000-13 6642000-14 6642000-15 6642000-18
6642000-19 6642000-24 6642000-25 6642000-26 6642000-27
6642000-28 6642000-29 6642000-201 6642000-202 6642000-204
6642000-205 6642000-34 6642000-35 6642000-44 6642000-45
6642000-48 6642000-49 6642000-52 6642000-53 6642000-54
6642000-55 6642000-63 6642000-64 6642000-65 6642000-66
6642000-73 6642000-74 6642000-79
(3) The indention system used in the detailed parts list of this catalog shows the relationship of one part to another. For a
given item, the indention code shows a general heading at the extreme left position and continues with indented
columns until the end detail is reached as follows:
A18017
1234567
Installation
Detail Parts for Installation
Assembly
Attaching Parts for Assembly
Detail Parts for Assembly
Subassembly
Attaching Parts for Subassembly
Detail Parts for Subassembly
Sub−Subassembly
Attaching Parts for Sub−Subassembly
Detail Parts for Sub−Subassembly

Basic Number Dash Number

(Drawing Identification
Only)

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 13:12:37 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
32-20-01-10 (Rev 14)

NOSE GEAR ASSEMBLY - DESCRIPTION AND OPERATION

1. Description
A. The nose gear assembly is designed and assembled to permit maneuverability of the airplane on the ground and to retract
into the nose wheel well when airborne. It is designed to absorb shock during airplane takeoffs, landings and taxiing and is
equipped with nose wheel steering. The principal sub-assemblies of the nose gear are the trunnion assembly, shock strut
assembly, fork and torque links.
(1) The cylinder, piston and an isolation piston are the shock absorbing portion of the nose gear assembly. The isolation
piston floats within the piston assembly. The chamber above the isolation piston contains hydraulic fluid and the
chamber below the isolation piston is charged with dry air or nitrogen. O-ring type packings are used on the isolation
piston to separate the hydraulic fluid and air/nitrogen. The cylinder assembly is supported within the trunnion by
bearings and retainers which permit rotation around the centerline of the cylinder.
(2) The trunnion is connected to the shock strut and attaches to the sides of the wheel well with trunnion pins to allow the
gear assembly to be retracted into the nose wheel well by a hydraulic actuator.
(3) The fork is press fitted to the bottom of the piston assembly and should not be separated unless warranted by
unserviceable conditions such as cracks or material flaws.
(4) Torque links prevent the piston and fork from rotating within the cylinder assembly. The upper torque link is connected
to the bottom of the cylinder and the lower torque link is connected to the piston-fork assembly. Mounted on the aft
side of the strut, the torque links are connected together to permit piston vertical movement in the cylinder.
B. The nose gear is equipped with a shimmy damper. Refer to Shimmy Damper - Description for information concerning
component operation and maintenance of the nose wheel shimmy damper.
C. The nose gear wheel is steerable and actuated by a bungee and cables connected to the rudder pedals. Refer to the
airplane maintenance manual for operation and maintenance of the nose wheel steering.
D. These nose gear assembly part numbers are affected by this section:
6642000-2 6642000-5 6642000-6 6642000-8 6642000-10
6642000-11 6642000-13 6642000-14 6642000-15 6642000-18
6642000-19 6642000-24 6642000-25 6642000-26 6642000-27
6642000-28 6642000-29 6642000-201 6642000-202 6642000-204
6642000-205 6642000-34 6642000-35 6642000-44 6642000-45
6642000-48 6642000-49 6642000-52 6642000-53 6642000-54
6642000-55 6642000-63 6642000-64 6642000-65 6642000-66
6642000-73 6642000-74 6642000-79
2. Operation
A. As weight of the airplane is applied to the nose gear assembly, the piston assembly is forced to slide into the cylinder
assembly. This movement causes a tapered metering pin, mounted at the top of the cylinder and protruding through a fixed
orifice in the top of the piston, to regulate the restriction of the hydraulic fluid flow through the orifice. The restricted fluid flow
on the top of the isolation piston and the compressed air/nitrogen below the isolation piston dampens the movement of the
piston assembly and absorbs compression shocks. As weight of the airplane is removed from the nose gear assembly,
the compressed air/nitrogen forces the isolation piston toward the top of the piston chamber. The hydraulic fluid is forced
through the fixed orifice at the top of the piston and is regulated by the tapered metering pin being withdrawn from the fixed
orifice as the piston assembly extends. Refer to Figure 1 and Figure 2 and Figure 3.
3. Personnel Safety Precautions - Hydraulic Fluid
A. The nose gear assembly contains phosphate ester base hydraulic fluid. Before performing maintenance or any operation
on the nose gear shock strut assembly, personnel should read and thoroughly understand the following.
WARNING: Observe the following safety precautions when working on systems containing phosphate ester
base fluid. Prolonged exposure to the fluid can cause skin dehydration and chapping.
(1) Wash hands thoroughly with soap and water before starting work; apply barrier cream (silicone hand cream) to
hands, wrists and forearms. Rub cream under fingernails and into creases of skin.

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 13:12:38 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
32-20-01-0 (Rev 14)

(2) Wear eye goggles when pressure testing components or systems or anytime there is a possibility of hydraulic fluid
splashing into eyes.
(3) If hydraulic fluid enters the eyes, treat eyes immediately by irrigating thoroughly with clear, cold water.
(4) Wash hands, wrists and forearms with soap and warm water after contacting hydraulic fluid.
(5) If clothing becomes soaked with hydraulic fluid, remove the contaminated clothing as soon as possible. Wash skin
exposed to hydraulic fluid with soap and warm water. Wash hydraulic fluid contaminated clothing before wearing.
4. Technical Safety Precaution - Hydraulic Fluid
A. Because the nose gear strut contains phosphate ester base hydraulic fluid, improper maintenance practices can be
damaging to gear components and other equipment. Before performing maintenance or any operation on the nose gear
shock strut assembly, personnel should read and thoroughly understand the following technical precautions.
CAUTION: Phosphate ester base hydraulic fluid will damage and/or deteriorate a wide range of materials;
including rubber, copper, various plastics and paints.
(1) Make sure that hydraulic fluid does not come in contact with any part of the component outside of the nose gear
shock strut. Keep spillage to an absolute minimum. Clean up spilled hydraulic fluid immediately to prevent
contamination of non-hydraulic components and to avoid false hydraulic leak detections. Should spillage occur, wipe
up the fluid with a dry cloth and wash area with naphtha MIL-PRF-680 (Type III).
(2) When gear components are disassembled, provide suitable protection for preventing entry of foreign material by
using caps and/or covers.
(3) Always check angle and position of components prior to disassembly to ensure proper alignment and placement of
components and hardware during assembly or replacement.
(4) Use naphtha MIL-PRF-680 (Type III) or Methyl n-Propyl Ketone when washing metal parts prior to assembly. Make
sure all traces of the solvent are removed before assembly.
(5) Use only clean hydraulic fluid for flushing or testing hydraulic components.
(6) Do not unpack seals, O-rings/packings until they are required and ensure that only correct, compatible and approved
seals, O-rings/packings are used.
CAUTION: Take special care not to contaminate seals, o-rings/packings after lubrication.
CAUTION: Prevent contamination of phosphate ester base hydraulic fluid with other hydraulic fluids, oils,
water or dirt.
(7) When assembling the gear shock strut hydraulic seals, O-rings/packings, lubricate only with phosphate ester base
hydraulic fluid. Always lubricate seals, O-ring/packings immediately before installation. Threaded fittings should be
assembled without the use of lubricants whenever possible. If a lubricant is required to prevent galling or to otherwise
ease installation, use phosphate ester base hydraulic fluid or VV-P-236 Petrolatum.

Figure 1 : Sheet 1 : Nose Gear Assembly - Description

A84048

Trunnion

Piston

Fork

Torque Links

5542T1031

Figure 2 : Sheet 1 : Nose Gear Strut Assembly - Description

Figure 3 : Sheet 1 : Nose Gear Strut Assembly - Operation

NOSE GEAR ASSEMBLY - TESTING

1. Testing
A. The nose gear shock strut should be properly filled/serviced with phosphate ester base hydraulic fluid and charged with dry
air/nitrogen prior to conducting test(s).
B. Tools and Equipment.
NOTE: Equivalent substitutes may be used for the listed items:
NAME NUMBER MANUFACTURER USE
Hydraulic Service Unit, CMJD112-001 Cessna Aircraft Co. Fill and cycle strut.
Portable Citation Marketing Div.
Department 579
P.O. Box 7706
Wichita, KS 67277
Magnetic Vee Base Measure piston deflection.
Nine Inch Horizontal
Gage Holding Rod,
Dial Indicator
Hunter Spring Gage Type D100 Ametek/Hunter Spring Measure pull force.
Hatfield, PA 19440
C. Shock Strut Filling Instructions.
(1) Position and maintain strut in upright position to expel any fluid that may have collected in the air chamber.
WARNING: Do not stand in front of the valve assembly while releasing air/nitrogen pressure. Do not turn 0.75
inch hex nut while releasing pressure. Removing the air filler valve without releasing air/nitrogen
pressure can cause injury.
(2) Attach a valve core depressor to, or remove valve core from the air filler valve assembly. Rotate 0.625 inch hex nut
counterclockwise to lift internal poppet to release any trapped air/nitrogen.
(3) Remove metering pin from top of cylinder and install reducer (AN919-3) or union (AN815-5) with gasket (NAS1612-
5).
(4) Attach hose from portable hydraulic service unit containing phosphate ester base hydraulic fluid and pump until strut
is fully extended.
(5) Open pump check valve and force strut to collapsed position as trapped air is expelled into hand pump reservoir.
(6) Repeat pumping, cycling strut until no air is noted coming from the strut fluid chamber.
(7) Discontinue pump cycling of the strut with the strut in the collapsed position. Remove hose and fitting.
(8) Keep fluid chamber full and do not disturb strut from the collapsed position until the metering pin has been installed
and tightened against its gasket. Safety wire metering pin.
WARNING: Servicing the strut with air before strut is properly serviced with hydraulic fluid could result in
blowing strut apart causing damage to equipment and/or injury to personnel.
(9) Install air filler valve core (replace with new valve core if necessary) and charge strut air chamber with the 0.625 inch
hex nut turned a maximum of 1-1/2 turns counterclockwise to 5 PSI above service placard instruction pressure.
NOTE: Charge strut with dry air or nitrogen.
(10) Bleed air/nitrogen to service placard pressure.
(11) Tighten 0.625 inch hex nut 50 to 70 inch-pounds.
D. Leak Test.
(1) After filling/servicing nose gear shock strut in accordance with instructions above, leave strut assembly charged for a
one hour period. No fluid leakage or loss of air/nitrogen is permissible.
WARNING: Do not stand in front of filler valve while releasing air/nitrogen pressure. Do not turn 0.75 inch hex
nut while releasing pressure. Removing air filler valve without releasing pressure first can cause
injury.

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 13:12:46 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
32-20-01-1 (Rev 5)

(2) Release air/nitrogen from the air filler valve. If fluid is noted coming through the air filler valve, consult Troubleshooting
procedure.
2. Troubleshooting
A. The nose gear assembly may be tested as outlined in Testing. above to determine air or fluid leakage. A review of
documented information received with the assembly, visual check and/or test results may be utilized in conjunction with the
following troubleshooting.
B. Troubleshooting.
TROUBLE PROBABLE CAUSE REMEDY
OIL LEAK AROUND Damaged packings or seals on lower Replace packings and seals.
PISTON bearing.
Cracked bearing. Replace bearing.
Piston surface cut or nicked. Polish out cut or nick.
Excessive polishing on piston surface has Replace piston.
created low or flat spots that packings are
unable to seal.
O-ring does not seal with isolation piston. Replace isolation piston. (Spares have
improved O-ring groove.)
STRUT DOES NOT Damaged packings on isolation piston. Replace packings.
EXTEND WHEN WEIGHT
IS REMOVED AND/OR
OIL PRESENT WHEN AIR
VALVE IS OPENED
Low nitrogen pressure. Check air valve for leaks.
Leaking air valve. Replace air valve
Stuck isolation piston. Free isolation piston; check for damage.
Isolation piston damaged. Replace isolation piston.
Piston wall damaged. Replace piston.
STEERING DIFFICULT Damaged upper or lower cylinder support Replace bearings.
bearings.
INCREASED NOSE Loose torque links. Check torque link attach points.
WHEEL SHIMMY

NOSE GEAR ASSEMBLY - DISASSEMBLY

1. Disassembly
NOTE: Determine extent of disassembly required by reviewing documentation accompanying the nose gear
assembly, or discrepancies noted during test, troubleshooting, checks and other maintenance
accomplished.
NOTE: Review personnel and technical safety precautions in Nose Gear Assembly - Description and Operation
concerning handling phosphate ester base hydraulic fluid.
A. Preparation for Disassembly (Refer to Illustrated Parts List).
(1) Place nose gear strut in upright position.
(2) Rotate 0.625 inch hex nut on air valve (175) counterclockwise one and one-half turns to lift internal valve poppet and
release air/nitrogen pressure by depressing valve core.
WARNING: Do not stand in front of air filler valve while releasing pressure. Do not turn 0.75 inch hex nut while
releasing pressure. Removal of the air filler valve prior to releasing pressure can cause injury.
(3) Cut safety wire and remove air valve (175) and packing (176) from bottom end of piston assembly.
(4) Cut safety wire and remove metering pin (150) and packing (152) from top of cylinder.
(5) Drain hydraulic fluid from upper piston chamber.
B. Torque Links Removal.
(1) Separate upper and lower torque links (226 and 227) by removing cotter pin (237), nut (236), washers (234), bolt
(233) and spacer (235).
(2) Remove pins (229) and shafts (228) attaching torque links to cylinder and piston assemblies.
(3) Press bushings (232) from upper and lower torque links (226 and 227).
C. Cylinder Assembly Removal.
(1) Remove lower retainer (155) and slide cylinder assembly (156) out of trunnion (16).
(2) Remove upper retainer (153) and bearing (154) from cylinder assembly (156).
D. Piston - Cylinder Disassembly.
(1) Push bearing (164) and retainer (167) into cylinder enough to free lock ring (168). Remove lock ring (168).
(2) Pull piston and fork assembly from cylinder (156).
(3) Remove two setscrews (157) and unscrew bearing (159) from top of piston (173).
(4) Slide spacer (161), phenolic bearing (164), scraper (166) and retainer (167) from piston (173).
(5) Remove "T" seal (165) from inner groove of bearing (164).
(6) Remove packing (162) and backup retainer (163) from outside of bearing (164).
(7) Remove isolation piston (160) from piston (173).
NOTE: It may be necessary to hold piston assembly (173) upside down in a bucket (or other suitable
container) containing rags and then, apply a very low air pressure to the air chamber to
remove isolation piston.
(8) Remove packing (169) from isolation piston (160).
E. Fork Removal.
NOTE: Do not remove fork from piston unless inspection reveals cracks, flaws or other unserviceable
conditions. Inspect piston for damage before removing fork.
(1) Remove uplock roller assembly.
(a) Remove cotter pins (243) and nuts (242). Pull bolts (240 and 244) allowing brackets (238 and 239), washers
(241 and 245) and spacers (246) to drop from fork.
(2) Using an arbor press and suitable mandrel, press piston (173) from fork (174).

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 13:12:47 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
32-20-01-4 (Rev 9)

NOSE GEAR ASSEMBLY - CLEANING

1. Cleaning
A. Tools and Equipment.
NOTE: Equivalent substitutes may be used instead of the listed items:
NAME NUMBER MANUFACTURER USE
Methyl n-Propyl Ketone Clean metal parts.
Solvent Blend Desoclean 110 PRC-DeSoto International Clean metal parts.
5426 San Fernando Rd.
Glendale, CA 91209
Paint Stripper T-6776 LO Turco Products, Inc. Strip paint from metal parts
Westminster 92684 prior to inspection.
CA
Naptha P-D-680 (Type III) Commercially Available Metal parts cleaning that
require soak cleaning.
Protective Oil Oakite Special Oakite Products Inc. Protect metal surfaces that
Protective Oil 50 Valley Road have had paint removed.
Berkeley Heights, NJ 07922
Hydraulic Assembly MCS 352 Aviation Fluids Service Co. Protect surfaces normally in
Lubricant St. Louis, MO 63166 contact with hydraulic fluid.
B. Cleaning Procedure.
(1) Clean metal parts and phenolic bearing with approved solvent. Remove stubborn deposits by hand rubbing with
nonabrasive pads or material. Apply solvent under pressure to all lubrication fittings, channels and other internal
cavities to insure cleanliness. Thoroughly dry all parts with filtered, dry, compressed air, lint free cloths or lint free
disposable tissue.
WARNING: Use cleaning solvents only in well ventilated areas. Avoid inhaling solvent vapors. Keep solvent
and solvent containers away from spark or open flame.
(2) Labels or identification plates which are attached by adhesive, shall be removed by lifting the corner and pulling free.
Remove adhesive with clean cloth dipped in cleaning solvent.
WARNING: All paint strippers are harmful to eyes and skin. Operators shall wear goggle type eye glasses,
rubber gloves and boots. In case of contact with skin, flush with water. In case of contact with
eyes, flush eyes thoroughly with water and consult a physician immediately. Paint stripping shall
be done in a well ventilated area. Follow manufacturer's instructions carefully to relieve pressure
before opening paint stripper storage containers.
(3) Apply paint stripper on painted parts following the recommended manufacturer’s instructions. Allow the first
application to work from 5 to 45 minutes or as advised by manufacturer's instructions. If necessary, scrub softened
areas with brush to loosen paint. Rinse with water. Repeat as necessary to remove all paint. After paint is completely
removed, rinse part thoroughly with water spray. Dry part with filtered, dry, compressed air and a lint-free cloth or lint-
free disposable tissue.
(4) After drying, coat all parts that would normally come in contact with hydraulic fluid during operation with clean hydraulic
fluid or hydraulic assembly lubricant. External metal surfaces or other parts not coming in contact with hydraulic fluid
during operation of the strut need not be coated. However, highly machined surfaces may be coated with hydraulic
fluid or other suitable protective coating.
(5) If inspection and repair procedures do not immediately follow cleaning, coat all surfaces that have had paint removed
with a suitable protective oil.

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 13:12:48 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
32-20-01-5 (Rev 17)

NOSE GEAR ASSEMBLY - CHECK

1. Check
A. Tools and Equipment.
NOTE: Equivalent substitutes may be used for the listed items:
NAME NUMBER MANUFACTURER USE
Cupric Sulfate Commercially Available Chrome surface check.
Sulfuric Acid Concentrated (18N) Commercially Available Chrome surface check.
B. Recommended Checking Methods.
(1) Consult Table 501 to determine the recommended method of checking each component.
(2) Check all parts visually under strong light for surface cracks, flaws, burrs, pitting, scoring or any other wear.
(3) Replace all parts showing cracks or flaws under dye penetrant, magnetic particle or visual inspection.
(4) Check all friction surfaces and machined holes for wear beyond tolerances given in Fits and Clearances.
(5) Check all bolts, nuts and screw threads, both external and internal, for evidence of stripping or scoring. Replace all
parts that have stripped threads.
(6) Check shafts and pins for ovaling, or other signs of wear.
C. Checking Chrome Plating.
CAUTION: When mixing solutions, always add acid to water; never add water to acid.
(1) Check the chrome surfaces of the shock strut assembly for scratches, scores, blisters, and nicks. All suspected
defects should be tested to determine if the base metal has been exposed. To test, apply liberally to the suspected
areas a copper sulfate solution consisting of 100 grams cupric sulfate, five (5) milliliters sulfuric acid and one (1) liter
of water. Wipe off excess liquid and inspect, using a strong light and a magnifying lens. If the chrome plating has been
penetrated, a copper coating will adhere to the ferrous metal. Clean the area thoroughly using approved solvent. If the
chrome plating has been penetrated in the sealing area, the part shall not be returned to airplane use. If the chrome
plating on the piston below the sealing surface is penetrated but no damage to the steel is detectable, then the
chrome damage may be repaired by cleaning and applying MIL-PRF-23377 corrosion resistant primer. After this
repair is complete the piston may be returned to service. Defects that have not penetrated the chrome plating should
be polished to remove sharp edges that could damage seals. A honing stone or crocus cloth may be used for this
purpose.
D. Table 501 contains recommended inspection (Refer to Illustrated Parts List).
Table 501. Recommended Inspection
NOMENCLATURE METHOD OF CHECK FOR REQUIREMENT
AND ITEM NUMBER CHECKING
SAME AS
ILLUSTRATED
PARTS LIST NO.
Trunnion (16) Visual Wear, Damage No damage or wear that would
endanger structure or interfere with
function.
Dye Penetrant Cracks No cracks.
Valve Assembly (175) Visual Damage, stripped Threads No damage or stripped threads.
Metering Pin (150) Visual Stripped Threads No stripped threads.
Cylinder (156) Visual Wear, Damage No wear or damage that would
prevent function.
Ultrasonic Cracks or voids No voids or cracks in braze joints.
Magnetic Particle Cracks No cracks.

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 13:12:50 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
32-20-01-5 (Rev 17)

Retainers (153, 155 Visual Wear, Damage No wear or damage that would
and 167) prevent function.
Bearing (159) Visual Wear, Damage No wear or damage.
Isolation Piston (160) Visual Wear, Damage No wear or damage that would
NOTE prevent function or sealing
capability.
Dye Penetrant Cracks No cracks.
Shafts (228) Visual Ovaling or Other Damage Must meet dimensions given in
Fits and Clearances.
Dye Penetrant Cracks No cracks.
Upper and Lower Visual Out of Round Holes, Wear or Other Holes must meet tolerances given
Torque Links (226 and Damage in Fits and Clearances.
227)
No wear or other damage that
would endanger structure or
prevent function.
Dye Penetrant Cracks No cracks.
Spacer (235) Visual Damage or Wear No wear or damage.
Piston (173) Visual Wear, Damage to Bearing Surfaces No wear or damage that would
Inner Diameter Finish, Deformation prevent function. Deformation can
from Bearing Set Screws be successfully removed.
Dye Penetrant Cracks No cracks.
Ultrasonic Cracks or Voids No voids or cracks in weld joints.
NOTE 1: The isolation piston has a teflon impregnated hard coat anodized finish and should show little or
no wear.

NOSE GEAR ASSEMBLY - REPAIR

1. Repair
A. Tools and Equipment.
NOTE: Equivalent substitutes may be used for the listed items:
NAME NUMBER MANUFACTURER USE
Wet or dry sandpaper 400 Commercially Available Remove corrosion from gear
strut.
Wet or dry sandpaper 180 grit Commercially Available Blending damaged nose gear
fork at upper torque take - out
lugs.
Emery Cloth 320 grit 400 grit Commercially Available Remove corrosion and final
finishing of axle and piston axle
adaptor.
Pretreatment primer Base 728-014
Sherwin-Williams Inc. Pretreatment primer
DOD-P-15328 Reducer 728-013
16116 E. 13th Street
Andover, KS 67002
Corrosion Resistant 513 x 419/910 x PRC-DeSoto International Corrosion protection primer.
Primer MIL-PRF- 942 5426 San Fernando Rd.
23377G or later Glendale, CA 91209
Corrosion Resistant 2 Part Epoxy P/N Akzo Nobel Corrosion protection primer.
Primer 10P4-2 P/N EC- East Water Street
117 Waukegan, IL 60085
Polyurethane paint, 7400 (Color Name: U.S. Paint Corp. Finish paint.
medium gray Pewter) 831 South 21st St.
St. Louis, MO 63130
Waterborne Corrosion 44-GN-60 /44-GN- Deft, Inc. Corrosion protection primer
Resistant Primer 60 CATA 17151 Von Karman Ave.
Irvine, CA 92714
Adhesive RTV-154 General Electric Co. Bond filling instructions placard
Silicone Products Dept. to strut.
Waterford, NY 12188
Clear enamel AA92-C-21C U.S. Paint Corp. Cover filling instructions
placard.
Catalyst AA92-C-22B U.S. Paint Corp. Cover filling instructions
placard.
Flexible drive Shaft with Commercially Available To hone piston assembly inner
1/4 inch chuck barrel.
Hone CF63 or CF68 Snap-On Tools To hone piston assembly inner
3150 Terrace barrel.
Kansas City, MO 64111
Honing oil Sun Concentrate Sun Oil Company To oil stones while honing.
1501 P.O. Box 2039
Tulsa, OK 74102
Hydraulic assembly MCS 352 Aviation Fluids Service Co. To lubricate piston assembly
lubricant St. Louis, MO 63166 inner barrel.
Sealant Class B-2 PRC-DeSoto International To attach washers to reworked
nose gear fork upper torque
take - out lugs.

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 13:12:51 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
32-20-01-6 (Rev 17)

Stones - 2 2-inch fine JT63-24 Snap-On Tools Used with CF63 or CF68
(400 grit) hones to hone piston assembly
inner barrel.
B. Replacement of Damaged Parts.
(1) Replace all parts that show visual wear, cracks or flaws.
(2) Replace all parts that show cracks under visual or dye penetrant inspection.
(3) Replace all parts indicating cracks or flaws under ultrasonic, X-ray, or magnetic particle inspection.
(4) Replace all parts that have machined holes that are worn beyond tolerance limits.
C. Chrome Surface Repair.
CAUTION: When buffing or polishing out scratches on chrome surfaces, extreme caution must be taken not
to penetrate the chrome plating or create low spots by too much localized buffing or polishing.
(1) Scratches or nicks that have not penetrated the chrome plating of the piston and axle assembly or the upper cylinder
assembly may be honed and polished to remove sharp edges that could damage the seals. A honing stone or crocus
cloth may be used for this purpose. In the areas not subject to seal travel, scratches, pits and scoring that do not
penetrate the chrome plating are relatively unimportant. The sharp edges of the nicks should be removed by honing
and polishing. The presence of defects in this area, if properly repaired, are considered acceptable.
D. Piston Assembly (173) Inner Diameter Deformation From the Set Screws on the Bearing (159).
(1) Use a small peen hammer to lightly tap the piston assembly where the set screw contacts the piston to restore the
original contour of the surface and remove any deformation that may damage the seals upon reassembly.
E. Piston Assembly (173) Inner Diameter Finish Rework.
NOTE: The inner barrel of the piston assembly is phosphate coated. This coating may be rough, causing
premature wear to the seals causing fluid to leak from the strut assembly. The following procedure
provides a method for smoothing this coating.
NOTE: This procedure is not intended to be performed after each overhaul. Perform this procedure only
once.
(1) Using a micrometer, check inside diameter of piston assembly to ensure it is within tolerance.
(2) Check inside of piston assembly for pitting. If pitted, replace the piston assembly.
(3) Hone the inside diameter of the piston assembly to remove a minimal amount of phosphate coating and to achieve a
smooth finish.
(a) Remove air charge valve assembly (175) and packing (176).
(b) Assemble hone, stones, flexible shaft with chuck and a variable speed drill.
NOTE: Install a piece of plastic, rubber hose or other suitable material over the chuck on flexible
shaft to prevent chuck from striking piston bore during honing.
(c) Adjust the hone and install into the end of piston assembly; expand hone assembly until stones are resting
against inner diameter of piston assembly. Apply honing oil as required.
CAUTION: Do not allow stones to get dry during honing; use honing oil freely while operating hone.
Allowing stones to get dry will result in scratching the inner diameter finish of the piston
assembly.
(d) Hone the piston assembly at a maximum speed of 600 RPM, one continuous stroke the length of bore and out,
keeping the hone moving through piston at all times until phosphate is removed.
(e) Thoroughly clean piston assembly after honing. Refer to Nose Gear Assembly - Cleaning.
(f) Using a micrometer, check inside diameter of piston assembly to ensure honing did not exceed the 1.815 inch
diameter.
(g) Install air charge valve assembly (175) and new packing (176).
(4) If piston assembly is not being reassembled, coat inside diameter with hydraulic assembly lubricant MCS 352.
F. Exterior Surface Repair.
(1) Scratches and nicks that have been repaired on forgings by sanding or polishing must be pretreated with wash
primer.

G. Nose Gear Trunnion Repair, Elongated Hole at Shimmy Damper Push- Pull Rod Attach Boss (Refer to Figure 601).
(1) Criterion.
(a) Permissible to rework elongated holes on the trunnion clevis fitting that attaches the shimmy damper push rod.
The elongation shall be removed when holes are line reamed to 0.2492 inch, +0.0005 or -0.0000 inch diameter.
If the elongation exceeds the reamed hole diameter, or the wall thickness (edge distance) after reaming is less
than 0.15 inch, replace the trunnion.
(2) Rework.
(a) Jack airplane and remove nose gear assembly from the airplane; refer to the Maintenance Manual.
(b) Remove cotter pin, nut, washers, bolt and spacer attaching shimmy damper push rod to trunnion attach boss.
Discard attaching hardware.
(c) Measure the elongated holes in the trunnion attach boss. If the elongated hole length exceeds the diameter of
the hole after reaming, replace the trunnion.
(d) Ream elongated attach boss holes.
NOTE: The trunnion shall be secured (clamped) to drill press or table to provide accurate
alignment for reaming.
1Use a 0.2188 inch straight reamer with 0.1895 inch pilot and ream the 3/16 inch elongated holes. After
reaming, check for elimination of elongation and wall thickness and determine if it is feasible to perform the
final reaming step that follows.
2 Use a 0.2495 inch straight reamer with 0.2188 inch pilot and ream 7/32 inch holes to provide a close
tolerance fit (0.2492 inch, +0.0005 or -0.0000 inch diameter hole) for a (NAS464P4-11 bolt).
(e) Measure wall thickness (edge thickness). If the wall thickness is less than 0.15 inch, replace the trunnion.
(f) Attach shimmy damper push rod to trunnion attach boss with the following: install spacer (5542204-200) in the
shimmy damper push rod; install bolt (NAS464P4-11), washer (AN960-416L) each side of push rod, nut
(AN320-4) and cotter pin (MS24665-132).
H. Painting.
(1) Preliminary.
(a) Verify areas to be painted are free of dirt, oil, grease and/or corrosion.
(b) Do not paint tires, strut air valves, data plates, bearings, polished pistons, switches, wire bundles, clamps,
hydraulic hoses, wheels, axle spindle area within the wheels or contacting areas of the lower to upper torque
links.
(2) Pretreatment Primer.
(a) Apply DOD-P-15328 pretreatment primer in accordance with manufacturer's instructions.
(3) Corrosion Resistant Primer.
(a) Mix and apply MIL-PRF-23377 corrosion resistant primer in accordance with manufacturer's instructions.
(4) Top Coat.
(a) Polyurethane paint consists of two components; a base and a catalyst. Mix top coat in accordance with the
manufacturer's instructions.
I. Outer Cylinder Lower Bearing Area Corrosion Inspection, Removal, Modification and Prevention.
(1) Inspection of the outer cylinder lower bearing area.
(a) Inspect the outer cylinder lower bearing area as shown for damage to the finished surface due to corrosion. If the
finished surface is not damaged and no corrosion exists, proceed to step (3). If corrosion is present on the outer
cylinder lower bearing surface area, proceed to step (2).
(2) Preliminary rework of outer cylinder lower bearing surface area.
(a) Determine if the outer cylinder lower bearing surface area can be reworked:
1 Verify that no corrosion exists on the uppermost 0.5 inch of the bearing surface. If corrosion is found in this
area, contact Citation Customer Service Department for disposition.
2 Using a stainless steel wire brush or glass bead peening, remove the corrosion from the outer cylinder
lower bearing area. Glass bead peening may be used to remove corrosion from the pits which were not

removed with the stainless steel wire brush.

3 Clean the outer cylinder bearing area with an approved solvent to remove all grease and dirt.
4 Using a dial micrometer with a pointed tip, measure the inner diameter of the outer cylinder lower bearing
area and determine the average bearing surface diameter to include the depth of pit.
NOTE: Average bearing surface diameter is determined by measuring the inner diameter at a
minimum of four different locations, starting at the most damaged location and
rotating 45 degrees either side, plus one additional location and averaging the four
measurements.
(b) If the average bearing surface diameter is greater than 2.908 inches, or the maximum pit depth is greater than
0.015 inch, contact Citation Customer Service Department.
(c) If the average bearing surface diameter is less than 2.908 inches, proceed to step (3).
NOTE: If the outer cylinder lower bearing surface contains pits which remain after corrosion
removal, and it is estimated that upon removal of these pits the outer cylinder lower
bearing surface may not meet the absolute maximum average diameter of 2.908 inches or
the maximum pit depth is greater than 0.015 inches, it may not be feasible to rework the
outer cylinder. The outer cylinder may require replacement.
(3) Rework of outer cylinder lower bearing surface area.
(a) If the average bearing surface diameter is greater than 2.908 inches, or the maximum pit depth is greater than
0.015 inch, contact Citation Customer Service Department.
(b) Use a rotary stainless steel wire brush or glass bead peening to remove all corrosion from the bearing and
retainer ring areas. Glass bead penning may be used to remove corrosion from the pits which were not removed
with the stainless steel wire brush. Ensure that all corrosion is removed prior to proceeding.
(c) Clean the lower bearing surface and the retainer ring areas with approved solvent to remove all grease and dirt.
Wipe off solvent with a clean absorbent rag. Do not allow solvent to dry on the surface, remove all solvent
residue.
(d) Mask the machined step at the top edge of the lower bearing surface and a 0.50 inch band of the upper portion
of the lower bearing surface area, to prevent primer from being applied to these surfaces.
(e) Reclean the unmasked portion of the lower bearing surface with approved solvent. Wipe off solvent with a clean
absorbent rag. Do not allow solvent to dry on the surface, remove all solvent residue.
(f) Immediately prime the abraded area with DOD-P-15328 pretreatment primer by one of the following
procedures:
NOTE: Apply DOD-P-15328 pretreatment primer to clean surfaces within 30 minutes of
completion of sanding procedure. An oxide film which provides minimal adhesion for
primer begins to form immediately after working. Poorly adhered primer will result in
accelerated corrosion.
NOTE: Mix primer in accordance with the manufacturer’s instructions.
1
Pour thinned primer onto the side and rotate the gear until the entire surface of the repair area is coated
with primer. Stand the gear up and allow the excess primer to drain.
a If applied primer is too thick or has heavy runs, sags or tears, etc., wipe off immediately with approved
solvent, dry and reapply.
2 Brush on to a thickness of 0.6 to 0.9 mil. At this thickness, the metal may be visible through the primer.
(g) Remove plug and the masking from the cylinder.
NOTE: This primer must be completely cured to have phosphate ester hydraulic fluid resistance.
(h) Cure coating by using the manufacturer’s instructions.
J. Repair of Nose Gear Fork at Upper Torque Take - Out Lugs.
(1) This repair may be performed when inspection indicates gouge, chafe, and corrosion damage on the surfaces of the
Torque Take - Out Lugs on the upper portion of the nose landing gear fork. The gouge damage is caused by the
protruding shoulders of the torque link bushings. The gouge damage is a circular ridge that has approximately the
same diameter as the shoulder bushing.

(2) Do the Repair of the Nose Gear Fork at Upper Torque Take - Out Lugs.
(a) Measure the diameters of both lug holes, noting the minimum and maximum dimensions and the clocking of
those measurements. If the maximum diameter exceeds 0.5006 inch (12.7152 mm) or if the difference between
the maximum and minimum diameters exceeds 0.0015 inch (0.0381 mm), contact Citation Customer Service by
telephone (316) 517-6221 or fax (316) 517-8500.
(b) Blend smooth the outer surface(s) of the damaged lug(s) using 180 grit sandpaper. Remove only as much
material as is necessary to eliminate all evidence of surface anomalies. Refer to Figure 604, Detail A for blend
area. Rework surface(s) flat and perpendicular with the lug bores. If the dimension "D" shown in Figure 604,
Detail B is greater than 1.888 inch (47.955 mm), no further rework of the lug is required and installation of the
washers is not necessary. Proceed to step (d) and skip step (g). If dimension "D" is less than 1.814 inches
(46.076 mm), the fork must be replaced.
(c) Installation of two washers, one on each lug outer face, will be required. Rework both lug surfaces by blending
flat and perpendicular to the lug bore until dimensiion "D", as shown in Figure 604, Detail B equals 1.819,
+0.005 or -0.005 inches (46.203, +0.127 or -0.127 mm).
NOTE: The final dimension as measured from washer outer surface to washer outer surface
must be maintained to ensure a proper fit with the mating torque link assembly. Refer to
Figure 604, Detail C.
(d) Smooth and polish the reworked areas to a RMS 63 or smoother finish and provide a gentle and consistent
transition between reworked and no-reworked areas (0.125 inch (3.175 mm) minimum transition radius).
(e) Surface eddy current inspect the reworked areas for cracks per Model 500 Series Non Destructive Testing
Manual. If any anomalies or a crack is found, contact Citation Customer Service by telephone (316) 517-6221 or
fax (316) 517-8500.
(f) Chemically clean, epoxy prime and then apply polyurethane topcoat to the fork surfaces requiring paint.
(g) Procure two NAS1149C-0832B washers and attach one to each of the fork lug reworked surfaces using Class
B-2 sealer, refer to Figure 604, Detail C. These washers will take up the space at the fork-to-link interface when
the fork is installed on the aircraft.
NOTE: The final dimension of the lug plus the B-2 sealer and washer stack-up must be as shown
in Figure 604, Detail C to make sure that a proper fit with the mating torque assembly. A
dimension of 0.005 inch (0.127 mm) is assumed for the thickness of the B-2 sealer.
K. Service Placards.
(1) Bond filling instruction placard to trunnion with RTV-154. Prepare and apply adhesive in accordance with
manufacturer’s instructions.

Figure 601 : Sheet 1 : Nose Gear Trunnion Repair, Elonged Hole at Shimmy Damper Push-Pull Rod Attach Boss

Figure 602 : Sheet 1 : Repair of Nose Gear Fork at Upper Torque Take - Out Lugs

Figure 602 : Sheet 2 : Repair of Nose Gear Fork at Upper Torque Take - Out Lugs
A96635

NOSE LANDING GEAR FORK

P/N 5542300

BLEND DIMENSION "D"

VIEWB−B

1.893, +0.005 or −0.005 INCHES B−2 SEALER

(40.082, +0.127 or −0.127 mm)

NAS1149C−0832B
(2 PLACES)

NOSE LANDING GEAR FORK

P/N 5542300

TWO (2) WASHER INSTALLATION, ONE (1) WASHER PER LUG FACE
VIEWC−C
BB5542T300−1
CC5542T300−1

NOSE GEAR ASSEMBLY - ASSEMBLY

1. Assembly
A. Tools and Equipment (Refer to Illustrated Parts List).
NOTE: Equivalent substitutes may be used for the listed items:
NAME NUMBER MANUFACTURER USE
Hydraulic assembly MCS 352 Aviation Fluids Service Co. Lubricate and protect surfaces
lubricant St. Louis, MO 63166 normally in contact with
hydraulic fluid and prevent entry
of water.
Oakite special Oakite Products, Inc. Protection of machined
protective oil 50 Valley Road surfaces during storage.
Berkeley Heights, NJ 07922
Pretreatment Primer 728-013701-702 Sherwin-Williams Inc. Lubricate press-fit trunnion
DOD-P-15328 16116 E. 13th Street bearings during installation.
Andover, KS 67002
Corrosion Resistant 513 x 419/910 x 942 PRC-DeSoto International Corrosion protection primer.
Primer MIL-PRF- 5426 San Fernando Rd.
23377G or later Glendale, CA 91209
Corrosion Resistant 02-Y-4002-4-40 Deft, Inc. Corrosion protection primer.
Primer MIL-PRF- CATA 17151 Von Karman Ave.
23377G or later Irvine, CA 92714
Locktite 222 Loctite Corporation For the fasteners thread lock.
705 N. Mountain Road
Newington, CT 06111
B. Trunnion Assembly (Refer to Illustrated Parts List).
(1) Press new pivot bearings (19) into trunnion (16) with MIL-PRF-23377 corrosion resistant primer and stake in place.
(2) Press bearings (18), wet with MIL-PRF-23377 corrosion resistant primer, into trunnion.
CAUTION: Do not press against inner bearing race. Use a suitable arbor and mandrel to prevent damage to
bearings.
(3) Press bearing (17), wet with MIL-PRF-23377 corrosion resistant primer, into trunnion.
C. Piston and Fork Assembly (Refer to Illustrated Parts List).
(1) If fork has been removed from piston, coat mating surfaces of piston and fork with MIL-PRF-23377 corrosion
resistant primer and press piston into fork socket.
NOTE: Valve hole and attach holes in piston barrel and fork must be aligned when installing piston.
(2) Install uplock roller assembly.
(a) Install bolt (240) through washer (241), left brackets (238 and 239), fork, right brackets (238 and 239), washer
(241) and nut (242). Do not tighten nut completely.
(b) Install bolt (244) through washer (245), left bracket (238), spacer (246), left bracket (239), fork, right bracket
(238), spacer (246), right bracket (239), washer (241) and nut (242). Do not tighten nut completely.
NOTE: Washer (245) is thinner than washers (241).
NOTE: Bolts (240, 244 and 247) are not interchangeable. Bolt (247) must be marked (NAS464) on
the head.
NOTE: Nut (252) is thinner than nuts (242).
(c) Tighten nuts (242) and install cotter pins (243).
(3) Immerse all packings and seals in hydraulic oil.
(4) Install rubber packing (169) on isolation piston (160).

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 13:12:59 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
32-20-01-7 (Rev 17)

(5) Coat the inner wall of the piston and fork assembly barrel with a thin layer of hydraulic fluid or hydraulic assembly
lubricant.
(6) Insert isolation piston (160) into piston (173) and push to bottom of barrel.
(7) Cover outside surface of piston with a thin coat of hydraulic fluid.
(8) Slide lock ring (168), scraper retainer (167) and scraper (166) onto piston (173).
(9) Install polypak seal (165) into inner groove in bearing (164).
NOTE: Install polypak seal with expander ring edge upwards towards fluid.
(10) Install back retainer (163) and packing (162) onto outside groove in bearing (164).
(11) Slide bearing assembly (164) onto piston barrel.
NOTE: Install bearing assembly with outside packing groove toward the top of piston barrel.
(12) Slide spacer (161) onto piston barrel.
(13) Apply Locquic primer/activator to threads of bearing (159). Allow to air dry then apply Loctite 222 to threads of
bearing (159).
CAUTION: Setscrews must be recessed below bearing surface. Make sure resistance is felt when installing
screws to insure self-locking capability. Replace screws not indicating self-locking capability.
(14) Screw bearing (159) onto piston until it bottoms. Apply Loctite 222 to setscrews (157) and secure bearing with two
setscrews (157). Torque setscrews 10 to 20 inch-pounds.
D. Piston and Fork Installation (Refer to Illustrated Parts List).
(1) Pack area all around bearing (164) with MCS 352 hydraulic assembly lubricant to resist entry of water about bearing
interface with strut cylinder collar.
(2) Cover inside of cylinder with a thin coat of hydraulic fluid.
CAUTION: Make certain lock ring is seated in the cylinder groove and the retainer is then extended to lock it in
place.
(3) Slide piston assembly into cylinder (156) and install scraper (166), scraper retainer (167) and lock ring (168).
E. Cylinder Installation (Refer to Illustrated Parts List).
(1) Slide retainer (155) over cylinder (156).
(2) Install bearing (154) on cylinder (156) and secure with retainer (153).
(3) Slide cylinder into trunnion (16) and secure with retainer (155).
F. Assembly and Installation of Torque Links (Refer to Illustrated Parts List).
(1) Coat bushings (231 and 232) with MIL-PRF-23377 corrosion resistant primer and press into upper torque link (226).
(2) Coat bushings (231) with MIL-PRF-23377 corrosion resistant primer and press into lower torque link (227).
NOTE: When new torque link bushings are installed, it may be necessary to mill and ream bushings
(231) to dimensions shown in Fits and Clearances.
CAUTION: Install torque links as shown in Figure 1001, or damage could result.
(3) Install upper and lower torque links (226 and 227) with shafts (228) and secure shafts with pins (229).
(4) Install torque link interconnect bolt (233), washers (234), spacer (235), nut (236) and cotter pin (237).
G. Valve and Plug Installation (Refer to Illustrated Parts List).
(1) Install air valve (175) and packing (176).
NOTE: If new air valve is being installed, discard packing and replace with phosphate ester base fluid
resistant packing, Part Number (NAS1611-015).
(2) Lock wire air valve to piston using double twist method.
(3) Install metering pin (150) and packing (152).
H. Lubrication (Refer to Illustrated Parts List).
(1) Grease torque link lubrication points with grease per MIL-PRF-23827.
2. Storage
A. Storage Procedure.

(1) Release air from air valve, refer to Disassembly.

(2) Remove metering pin from cylinder top and drain hydraulic oil from cylinder. Replace plug.
(3) Collapse strut assembly. Coat exposed surface of piston with protective oil.
(4) Wrap collapsed strut in grease proof paper, then kraft paper and pack in rigid container.
(5) Container shall be stored in a cool, dry, well ventilated area on a noncorrosive base.

NOSE GEAR ASSEMBLY - FITS AND CLEARANCES

1. Fits and Clearances
A. Trunnion Assembly 5542301-9
A3834
8 3
2

7
5

1
6342T1028

(1) 3.875 inch, +0.001 or -0.000 inch (98.42 mm, +0.03 or -0.00 mm ) diameter
(2) 2.8096 inch, +0.0015 or -0.0000 inch (71.364 mm, +0.038 or -0.000 mm ) diameter
(3) 1.7476 inch, +0.0010 or -0.0000 inch (44.389 mm, +0.025 or -0.000 mm ) diameter
(4) 0.8125 inch, +0.0010 or -0.0000 inch (20.638 mm, +0.025 or -0.000 mm ) diameter
(5) 0.7500 inch, +0.0005 or -0.0000 inch (19.050 mm, +0.013 or -0.000 mm ) diameter
(6) 0.6250 inch, +0.0007 or -0.0000 inch (15.875 mm, +0.018 or -0.000 mm ) diameter
(7) 0.2500 inch, +0.0035 or -0.0000 inch (6.350 mm, +0.089 or -0.000 mm ) diameter
(8) 0.1895 inch, +0.0005 or -0.0000 inch (4.813 mm, +0.003 or -0.000 mm ) diameter
B. Cylinder Assembly 5542100-3
A3838

2 1

6342T1029

(1) 0.4991 inch, +0.0015 or -0.0000 inch (12.677 mm, +0.038 or -0.000 mm ) diameter
(2) 0.156 inch, +0.004 or -0.000 inch (4.81 mm, +0.10 or -0.00 mm ) diameter
C. Piston Assembly 6642100-2
A4097

1
6342T1029

(1) 1.812 inch, +0.003 or -0.000 inch (46.02 mm, 0.08 or -0.00 mm) diameter
D. Fork 5542300-2

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 13:13:00 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
32-20-01-8 (Rev 15)

(1) 0.4991 inch, +0.0015 or -0.0000 inch (12.677 mm, 0.038 or -0.000 mm) diameter
(2) 0.156 inch, +0.004 or -0.000 inch (3.96 mm, 0.10 or -0.00 mm) diameter
(3) 0.250 inch, +0.003 or -0.000 inch (6.35 mm, 0.08 or -0.00 mm) diameter
(4) 1.376 inch, +0.002 or -0.000 inch (34.95 mm, 0.05 or -0.00 mm) diameter
(5) 1.875 inch (47.62 mm) diameter x 0.250 inch (6.35 mm) deep
(6) 1.898 inch, +0.000 or -0.005 inch (48.209, +0.000 or -0.127 mm)
E. Bearing 6642307-1

1
6342T1029

(1) 2.497, +0.000 or -0.003 inch (63.42 mm, 0.00 or -0.08 mm) diameter
G. Torque Link - Upper 5542302-1

A96655
4

2 3

6342T1027

(1) 0.4988 inch, +0.0002 or -0.0004 inch (12.670 mm, 0.005 or -0.010 mm) diameter
(2) 0.156 inch, +0.004 or -0.000 inch (3.96 mm, 0.10 or -0.00 mm) diameter
I. Torque Link - Lower 5542302-2
A96656
4

2 3

6342T1027

5 3

4 2
6342T1029

(1) 1.810 inch, +0.000 or -0.002 inch (45.97 mm, 0.00 or -0.05 mm) diameter
(2) 1.443 inch, +0.000 or -0.004 inch (36.65 mm, 0.00 or -0.10 mm) diameter (-1)
(3) 1.457 inch, +0.000 or -0.004 inch (37.01 mm, 0.00 or -0.10 mm) diameter (-2)
L. Spacer 5542209-1
A3849

5594T1054

NAS77A6−022

(1) 0.3730 inch, +0.0004 or -0.0004 inch (9.474 mm, 0.010 or -0.010 mm) diameter
(2) 0.5013 inch, +0.0000 or -0.0007 inch (12.733 mm, 0.000 or -0.018 mm) diameter

NOSE LANDING GEAR ASSY

NOMENCLATURE EFFECTIVITY UNITS
PER
ITEM PART NUMBER 1 2 3 4 5 6 7 FROM TO ASSY
- NOSE LANDING GEAR ASSY

. NOSE GEAR STRUT

1 6642000-2 A NP
ASSY FSO 6642000-204
- . NOSE GEAR STRUT
2 6642000-201 B NP
ASSY FSO 6642000-204
NOSE GEAR STRUT
- 2A 6642000-204 . V 01
ASSY
- . NOSE GEAR STRUT
3 6642000-6 C NP
ASSY FSO 6642000-205

- . NOSE GEAR STRUT

4 6642000-202 D NP
ASSY FSO 6642000-205

- . NOSE GEAR STRUT

4A 6642000-205 W 01
ASSY
- . NOSE GEAR STRUT
5 6642000-10 E NP
ASSY FSO 6642000-65

- . NOSE GEAR STRUT

5A 6642000-14 F NP
ASSY FSO 6642000-65

- . NOSE GEAR STRUT

5B 6642000-18 G NP
ASSY FSO 6642000-65

- . NOSE GEAR STRUT

5C 6642000-26 R NP
ASSY FSO 6642000-65

- . NOSE GEAR STRUT

5D 6642000-34 Y NP
ASSY FSO 6642000-65
NOSE GEAR STRUT
- 5E 6642000-48 . Z NP
ASSY FSO 6642000-65

- . NOSE GEAR STRUT

5F 6642000-54 AD NP
ASSY FSO 6642000-65
- . NOSE GEAR STRUT
5G 6642000-65 AJ 01
ASSY

- . NOSE GEAR STRUT

6 6642000-11 H NP
ASSY FSO 6642000-66
NOSE GEAR STRUT
- 6A 6642000-15 . J NP
ASSY FSO 6642000-66
- . NOSE GEAR STRUT
6B 6642000-19 K NP
ASSY FSO 6642000-66
- . NOSE GEAR STRUT
6C 6642000-27 S NP
ASSY FSO 6642000-66

- . NOSE GEAR STRUT

6D 6642000-35 X NP
ASSY FSO 6642000-66
NOSE GEAR STRUT
- 6E 6642000-49 . AA NP
ASSY FSO 6642000-66
- . NOSE GEAR STRUT
6F 6642000-55 AE NP
ASSY FSO 6642000-66

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 13:13:04 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
32-20-01-1001 (Rev 14)

- . NOSE GEAR STRUT

6G 6642000-66 AK 01
ASSY

- . NOSE GEAR STRUT

7 6642000-73 AF 01
ASSY
- . NOSE GEAR STRUT
8 6642000-74 AG 01
ASSY
- . NOSE GEAR STRUT
8A 6642000-79 AL 01 R
ASSY

- . NOSE GEAR STRUT

9 6642000-5 L 01
ASSY GRAVEL RUNWAY

- . NOSE GEAR STRUT

10 6642000-8 M 01
ASSY GRAVEL RUNWAY
- . NOSE GEAR STRUT
11 6642000-13 Q 01
ASSY GRAVEL RUNWAY
NOSE GEAR STRUT
- 12 6642000-25 . ASSY GRAVEL RUNWAY P NP
FSO 6642000-63
NOSE GEAR STRUT
- 12A 6642000-28 . ASSY GRAVEL RUNWAY U NP
FSO 6642000-63
NOSE GEAR STRUT
- 12B 6642000-44 . ASSY GRAVEL RUNWAY AB NP
FSO 6642000-63
NOSE GEAR STRUT
- 12C 6642000-52 . ASSY GRAVEL RUNWAY AD NP
FSO 6642000-63
- . NOSE GEAR STRUT
12D 6642000-63 AH 01
ASSY GRAVEL RUNWAY
NOSE GEAR STRUT
- 13 6642000-24 . ASSY GRAVEL RUNWAY N NP
FSO 6642000-64
NOSE GEAR STRUT
- 13A 6642000-29 . ASSY GRAVEL RUNWAY T NP
FSO 6642000-64
NOSE GEAR STRUT
- 13B 6642000-45 . ASSY GRAVEL RUNWAY AC NP
FSO 6642000-64
NOSE GEAR STRUT
- 13C 6642000-53 . ASSY GRAVEL RUNWAY AE NP
FSO 6642000-64
NOSE GEAR STRUT
- 13D 6642000-64 . AI 01
ASSY GRAVEL RUNWAY
- . . A thru H,J,K
15 5542301-9 TRUNNION ASSY 01
N,P,R,S
- 15A 5542301-14 . . TRUNNION ASSY T thru AK 01
. . . A thru H,J,K
16 5542301-10 TRUNNION 01
N,P,R,S
- 16A 5542301-13 . . . TRUNNION T thru AK 01

17 MS27642-33 . . . BEARING 01
18 MS27642-16 . . . BEARING 02
19 M81934/1-10C018 . . . BEARING-OUTER 02
BEARING-INNER NOT
- 20 5542224-3 . . INCLUDED IN 02
TRUNNION
21 5542401-3 . . COVER-GEAR 01
SCREW-COVER
22 MS35266-60 . . 02
ATTACH
WASHER-COVER
23 NAS1149F0332P . . 02
ATTACH
24 5542215-2 . . GEAR-STEERING 01
PIN SLOTTED-GEAR
25 NAS561P10-22 . . 01
ATTACH
26 5542401-1 . . COVER-GEAR 01
BOLT-COVER
27 AN4H10A . . 06
ATTACH
. . WASHER-COVER
28 NAS1149F0432P 06
ATTACH
GEAR ASSY-
29 5542214-3 . . 01
STEERING
BOLT-GEAR ASSY
30 AN4-20A . . 02
ATTACH
. . SPACER-GEAR ASSY
31 5542219-1 02
ATTACH
WASHER-GEAR
32 NAS1149F0432P . . 02
ASSY ATTACH
. . NUT-GEAR ASSY
33 MS21083N4 02
ATTACH
34 ATLF12-111 . . . BEARING V15860 01

NOMENCLATURE EFFECTIVITY UNITS

PER
ITEM PART NUMBER 1 2 3 4 5 6 7 FROM TO ASSY
- NOSE LANDING GEAR ASSY
SHIMMY DAMPENER
A,C,E,F,H J
75 5543001-3 . . ASSY FSO 5543001- NP R
L,M,P
12
SHIMMY DAMPENER
B,D,G,K,N
- 76 5543001-5 . . ASSY FSO 5543001- NP R
Q
12
SHIMMY DAMPENER
- 76A 5543001-7 . . ASSY FSO 5543001- R,S NP R
12
SHIMMY DAMPENER
- 76B 5543001-8 . . ASSY FSO 5543001- T thru AC NP
11

- . . SHIMMY DAMPENER
76C 5543001-11 AD thru AK 01
ASSY
- . . SHIMMY DAMPENER
76D 5543001-12 AL 01 R
ASSY
ATTACHING
PARTS
77 NAS1149F1232P . . WASHER 01
78 RSN75SK . . RETAINING RING V80756 01
79 NAS464P3-11 . . BOLT 01
80 NAS1149F0332P . . WASHER 02
81 5542204-1 . . SPACER 01
82 AN320-3 . . NUT 01
83 MS24665-132 . . COTTER PIN 01
---*---
84 5542216-3 . . SHAFT 01
. . FORK-UPPER
85 5542303-2 01
STEERING
ATTACHING
PARTS
86 NAS561P10-24 . . PIN-SLOTTED 01
---*---
87 5542306-1 . . CROSS-STEERING 01
ATTACHING
PARTS
88 5542221-2 . . SHAFT 02
89 MJHT891 . . BEARING V60380 A THRU Y NP
- 89A S3273-1 . . BEARING 02
89B 6642000-43 . . SPACER Z THRU AK 02
90 MS16625-1075 . . RETAINER 02
---*---
- 91 5542304-3 . . FORK ASSY-LOWER 01
ATTACHING
PARTS
92 NAS464P3-50 . . BOLT 01
93 AN970-3 . . WASHER 02
94 5542221-1 . . SHAFT 01
95 AN320-3 . . NUT 01
96 MS24665-132 . . COTTER PIN 01
---*---
97 5542304-4 . . FORK STEERING 01
98 JHTT89 . . BEARING V60380 02

NOMENCLATURE EFFECTIVITY UNITS

PER
ITEM PART NUMBER 1 2 3 4 5 6 7 FROM TO ASSY
- NOSE LANDING GEAR ASSY
METERING PIN
150 5542225-2 . . WITHOUT GRAVEL 01
RUNWAY
METERING PIN WITH
- 151 5542225-3 . . 01
GRAVEL RUNWAY
152 NAS1612-5 . . O-RING 01
153 RST293CD . . RETAINER V80756 01
154 MS27642-47 . . BEARING 01
155 RRT387CD . . RETAINER V80756 01
156 5542100-3 . . CYLINDER ASSY 01
- 156A 6542001-1 . . STEERING CYLINDER AF,AG 01 R
. . SCREW-SET REFER
157 NAS1081-3B4 02
TO NOTE 1
SCREW-SET
- 158 NAS1081C3B4 . . ALTERNATE FOR 02
NAS1081-3B4
. . BEARING REFER TO
159 6642308-3 01
NOTE 1
160 6642217-2 . . PISTON-ISOLATION 01
161 5542206-1 . . SPACER 01
162 NAS1611-333A . . O-RING 01
163 MS28774-333 . . RETAINER 01
164 6642307-1 . . BEARING 01
165 P77A5450 . . SEAL POLYPAK V30781 01
- . . T-SEAL ALT FOR
165A 601RS331-04183 V30781 01
P77A5450
. . SCRAPER REFER TO
166 S11065-23T V09257 A THRU AE 01
NOTE 2
- 166A MS28776M2-23 . . SCRAPER AF THRU AK 01
167 5542207-2 . . RETAINER-SCRAPER 01
168 CM2690H17 . . LOCK RING 01
169 NAS1611-324A . . O-RING 01
- . . PISTON AND FORK
170 6642000-3 01
ASSY
171 AN4-41 . . . BOLT 01
172 AN310-4 . . . NUT 01
173 6642100-3 . . . PISTON ASSY 01
PISTON ASSY
- 173A 6642100-2 . . . ALTERNATE FOR 01
6642100-3

174 5542300-2 . . . FORK 01

VALVE ASSY-AIR
175 AN6287-1 . . 01
CHARGE
176 NAS1611-015A . . O-RING 01
. . PLATE-
177 6640001-4 01
IDENTIFICATION
178 MS21318-14 . . SCREW-DRIVE 02
PLACARD-FILLING
179 6640001-1 . . A,B,L,Q,V 01
INSTRUCTIONS
- . . PLACARD-FILLING
180 6640001-8 C,D,M,W 01
INSTRUCTIONS
E,F,G,P,R,U
- . . PLACARD-FILLING
181 6640001-12 Y,Z,AB,AD,AF 01
INSTRUCTIONS
AG,AH,AJ
H,J,K,N,S,T
- . . PLACARD-FILLING
182 6640001-14 X,AA,AC,AE 01
INSTRUCTIONS
AI,AK
WHEN INITIALLY ORDERING NAS1081-3B4 SET SCREW OR 6642308-3 BEARING, BOTH
NOTE 1:
PARTS MUST BE ORDERED.
THE MS28776M2-23 METAL SCRAPER RING CAN BE USED BY OPERATORS EXPERIENCING
NOTE 2:
ICE INDUCED SEAL DAMAGE.
NOMENCLATURE EFFECTIVITY UNITS
PER
ITEM PART NUMBER 1 2 3 4 5 6 7 FROM TO ASSY
- NOSE LANDING GEAR ASSY
. . PLACARD-NOSE
225 6640001-3 01
WHEEL INFLATION
226 5542302-1 . . LINK ASSY-UPPER 01
227 5542302-2 . . LINK ASSY-LOWER 01
ATTACHING
PARTS
228 5542208-3 . . SHAFT 02
229 MS16562-43 . . PIN-SLOTTED 02
---*---
FITTING-
230 NAS516-1A . . . 05
LUBRICATION
231 NAS77A6-22 . . . BUSHING-UPPER 02
232 5041017-2 . . . BUSHING 04
233 S3461-4 . . BOLT 01
234 NAS1149F0432P . . WASHER 02
235 5542209-1 . . SPACER 01
236 AN310-4 . . NUT 01
237 MS24665-134 . . COTTER PIN 01
238 5542402-4 . . BRACKET-UPLOCK 02

239 5542402-3 . . BRACKET-UPLOCK 02

240 AN4-41 . . BOLT-REAR 01
241 NAS1149F0463P . . WASHER 05
242 AN310-4 . . NUT 02
243 MS24665-134 . . COTTER PIN 03
244 AN4-46 . . BOLT-CENTER 01
245 NAS1149F0432P . . WASHER 01
246 NAS43DD4-46FC . . SPACER-CENTER 02
SPACER-CENTER
- 246A NAS43DD4-46N . . ALT FOR NAS43DD4- 02
46FC
247 NAS464P4-71 . . BOLT-FORWARD 01
248 M81934/1-06C022 . . BEARING 03
249 NAS75-6-029 . . BUSHING 02
250 5542218-2 . . SPACER 02

251 5542218-1 . . SPACER-FORWARD 01

CENTER
252 AN320-4 . . NUT 01
253 AN5-55 . BOLT 01
254 0842000-37 . BUCKET-AXLE 02
. SPACER REFER TO
255 5542223-1 02
NOTE 1
- . SPACER REFER TO
256 5542223-2 02
NOTE 2
257 0842000-36 . TUBE AXLE 01
258 NAS1149F0532P . WASHER 01
259 MS17825-5 . NUT 01
260 MS24665-231 . COTTER PIN 01

. WHEEL ASSY REFER TO

261 RF
PARTS CATALOG
5542223-1 SPACERS ARE USED WITH ALL WHEEL ASSEMBLIES EXCEPT GOODYEAR
NOTE 1: WHEEL ASSEMBLIES WITH TIMKEN BEARING CUPS (13621) AND TIMKEN BEARING CONES
(13600LA902A1).
5542223-2 SPACERS ARE USED WITH GOODYEAR WHEEL ASSEMBLIES WITH TIMKEN
NOTE 2: BEARING CUPS (13621) AND TIMKEN BEARING CONES (13600LA902A1) AND MAY BE USED
AS AN ALTERNATE TO 5542223-1 TO ACHIEVE A SLIP FIT.
- Item Not Illustrated

Figure 1001 : Sheet 1 : NOSE LANDING GEAR ASSY

Figure 1001 : Sheet 2 : NOSE LANDING GEAR ASSY

Figure 1001 : Sheet 3 : NOSE LANDING GEAR ASSY

Figure 1001 : Sheet 4 : NOSE LANDING GEAR ASSY

SHIMMY DAMPER - DESCRIPTION

1. Description
A. The nose wheel shimmy damper is a hydraulic unit designed to absorb and dampen nose wheel shimmy during airplane
takeoff, landing and taxiing. The damper cylinder and piston is mounted on a rotating steering gear at the top of the landing
gear strut assembly. The piston rod is bolted to a fixed arm on the landing gear trunnion. Refer to Figure 1.
B. The damper consists of a fluid filled cylinder that moves on a fixed piston. An orifice permits fluid to flow through the piston
as the cylinder moves with the steering gear. Seals, packings and scrapers prevent fluid leakage.
C. These shimmy damper part numbers are affected by this individual component maintenance manual.
5543001-1 5543001-3 5543001-5 5543001-7 5543001-8
DDA55146-1 5543001-11 5543001-12
2. Operation
A. Nose wheel shimmy is transmitted through the shock strut to a steering gear mounted on top of the strut assembly. As the
steering gear turns, the barrel of the shimmy damper slides left or right along the piston rod. The fluid within the barrel is
forced through an orifice in the piston. The restricted fluid flow through the orifice absorbs and dampens the movement of
the barrel, steering gear and nose gear wheel.
3. Personnel Safety Precautions - Hydraulic Fluid
A. The shimmy damper contains phosphate ester base hydraulic fluid. Before performing maintenance or any operation on
the shimmy damper, personnel should read and thoroughly understand the following:
WARNING: Observe the following safety precautions when working on systems containing phosphate ester
base fluid. Prolonged exposure to the fluid can cause skin dehydration and chapping.
(1) Wash hands thoroughly with soap and water before starting work; apply barrier cream (silicone hand cream) to
hands, wrists and forearms. Rub cream under fingernails and into creases of skin.
(2) Wear eye goggles when pressure testing components or systems or anytime there is a possibility of hydraulic fluid
splashing into eyes.
(3) If hydraulic fluid enters the eyes, treat eyes immediately by irrigating thoroughly with clear, cold water.
(4) Wash hands, wrists and forearms with soap and warm water after contacting hydraulic fluid.
(5) If clothing becomes soaked with hydraulic fluid, remove the contaminated clothing as soon as possible. Wash skin
exposed to hydraulic fluid with soap and warm water. Wash hydraulic fluid contaminated clothing before wearing.
4. Technical Safety Precaution - Hydraulic Fluid
A. Because the shimmy damper contains phosphate ester base hydraulic fluid, improper maintenance practices can be
damaging to gear components and other equipment. Before performing maintenance or any operation on the shimmy
damper personnel should read and thoroughly understand the following technical precautions:
CAUTION: Phosphate ester base hydraulic fluid will damage and/or deteriorate a wide range of materials;
including rubber, copper, various plastics and paints.
(1) Ensure that hydraulic fluid does not come in contact with any part of the component outside of the shimmy damper.
Keep spillage to an absolute minimum. Clean up spilled hydraulic fluid immediately to prevent contamination of non-
hydraulic components and to avoid false hydraulic leak detections. Should spillage occur, wipe up the fluid with a dry
cloth and wash area with naphtha, MIL-PRF-680 (Type III).
(2) When shimmy damper is disassembled, provide suitable protection for preventing entry of foreign material by using
caps and/or covers.
(3) Always check position of components prior to disassembly to ensure proper alignment and placement of components
and hardware during assembly or replacement.
(4) Use naphtha, MIL-PRF-680 (Type III) or Methyl n-Propyl Ketone when washing metal parts prior to assembly. Ensure
all traces of the cleaning agent are removed before assembly.
(5) Use only clean hydraulic fluid for flushing or testing hydraulic components.
(6) Do not unpack seals, O-rings/packings until they are required and ensure that only correct, compatible and approved
seals, O-rings/packings are used.
CAUTION: Take special care not to contaminate seals, o-rings/ packings after lubrication.

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 13:13:21 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
32-20-02-0 (Rev 16)

CAUTION: Prevent contamination of phosphate ester base hydraulic fluid with other hydraulic fluids, oils,
water or dirt.
(7) When assembling the Shimmy damper hydraulic seals, O-rings/packings, lubricate only with phosphate ester base
hydraulic fluid. Always lubricate seals, O- ring/packings immediately before installation. Threaded fittings should be
assembled without the use of lubricants whenever possible. If a lubricant is required to prevent galling or to otherwise
ease installation, use phosphate ester base hydraulic fluid or VV-P-236 Petrolatum.

Figure 1 : Sheet 1 : Shimmy Damper Assembly

SHIMMY DAMPER - TESTING

1. Testing
A. Function.
(1) Cycle the shimmy damper piston rod several times by hand. While cycling the piston. check for the following:
(a) No roughness in operation as the piston (inside) travels the length of the housing barrel.
(b) Resistance to quick movement.
(c) No leaks.
B. Pressure Test.
(1) Remove cap retainer and spring from the unit.
(2) Insert proof test slug 0.670 inch, +0.010 or -0.010 inch diameter by 0.38 inch in cylinder and reinstall cap retainer.
(3) Remove cap from reducer fitting; connect hand pump with gage to fitting.
(4) With hand pump apply 1500 PSIG for one minute. There shall be no leaks.
(5) Reduce hand pump pressure.
(6) Remove retainer cap and remove proof test plug.
(7) Reinstall spring and retainer cap.
NOTE: If fluid pressure is too great for installation of spring and retainer cap, bleed fluid at bleed
screw.
(8) Apply fluid flow from hand pump until fluid flows from retainer cap hole.
(9) Stop hand pump and check depth through spring to makeup piston.
(10) Remove bleed screw and observe that spring drives makeup piston inward to 5.00 inch depth while expelling fluid at
bleed screw hole.
(11) Replace seal washer and screw before the makeup piston bottoms at approximately 5.75 inches depth.
(12) Service shimmy damper, refer to assembling procedure.
2. Troubleshooting
A. General.
(1) Refer to Table 101 for aid in determining and correcting causes of shimmy damper malfunction.
(2) Make necessary repairs or replacement and repeat test to ensure that corrective action was successful.
NOTE: Evidence of severe damage, such as broken parts, warrants replacement of the entire
assembly.
B. Table 101 contains troubleshooting information.
Table 101. Troublshooting
TROUBLE PROBABLE CAUSE REMEDY
ROUGH OPERATION Damaged barrel in housing. Replace housing.
Damaged Piston. Replace piston.
Contaminated hydraulic fluid. Drain oil; clean chamber; refill with
clean fluid.
FLUID LEAKAGE Damaged or improperly installed Replace packings.
packings.
Worn parts. Replace worn parts.
NO OPERATION Broken parts. Replace assembly.
Internal seals damaged. Replace seals.

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 13:13:27 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
32-20-02-3 (Rev 7)

SHIMMY DAMPER - DISASSEMBLY

1. Disassembly
A. Tools and Equipment.
NOTE: Equivalent substitutes may be used for the listed items:
NAME NUMBER MANUFACTURER USE
Extraction Tool Set CUTA1870104CE The Lee Company To remove orifice and check
2 Pettipaug Road valve assemblies.
Westbrook, CT 06498
Extraction Tool Set CUTA2180103BA The Lee Company To remove plug assembly.
Extraction Tool Set CUTA2S00103BA The Lee Company To remove plug assembly.
Extraction Tool Set CUTA2810114CD The Lee Company To remove pressure relief
assembly.
Extraction Tool Set CUTA3430103BA The Lee Company To remove the plug which is
behind the pressure relief
assembly.
B. Disassemble Shimmy Damper (Refer to Illustrated Parts List).
NOTE: To remove the shimmy damper from the airplane, refer to the Maintenance Manual.
(1) Pull on rod eye of piston rod assembly (11) until piston (20) stops against head bearing (16).
(2) Position housing assembly vertically with the eye end of the piston rod assembly up
(3) Remove the retaining ring (12) and head bearing (16) from housing (45).
(4) Drain fluid from housing (45).
(5) Remove the retaining ring (25) and slide head bearing (29) from rod (11).
(6) Remove packing (26) from outside groove of head bearing (29).
(7) Remove lock ring (27) and scraper ring (28) from head bearing (29).
(8) Remove seal (33) from head bearing (29).
(9) Pull piston rod from housing (45).
(10) Remove seal (24) and packing (23) from piston (20).
(11) Remove roll pin (22) and slide piston (20) from rod (11).
(12) Slide head bearing (16) from rod (11).
(13) Remove seal (19), lock ring (4), scraper ring (15) and packing (13) from head bearing (16).
(14) Remove self-locking screw (78) and sealing washer (76) from housing (45).
(15) Press or drive bearing (9) from rod (11).
(16) Remove retainer cap (79), spring (88) and makeup piston (87) from housing (45).
(17) Remove packing (84) and backup retainer (85) from makeup piston (87).
(18) Remove cap (79), reducer fitting (82), packing (83) from housing (45).
(19) Remove check valve assembly (81) from reducer fitting (82) in accordance with Figure 301.
(20) Remove plug assembly and check valve assembly (46) from housing (45) in accordance with Figure 301.
(21) Remove plug assembly and pressure relief valve assembly (49) from housing (45) inaccordance with Figure 301.
(22) Remove plug assembly (50) from housing (45) in accordance with Figure 301.

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 13:13:28 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
32-20-02-3 (Rev 7)

Figure 301 : Sheet 1 : Extraction Tool Usage Example

Figure 301 : Sheet 2 : Extraction Tool Usage Example

SHIMMY DAMPER - CLEANING

1. Cleaning
WARNING: Chemicals and solvents shall be used only in well ventilated areas, avoid inhaling vapors. Chemicals
and solvents are harmful to eyes and skin. In case of contact with eyes, flush eyes thoroughly with
water and consult a physician immediately.
A. Tools and Equipment.
NOTE: Equivalent substitutes may be used for the listed items:
NAME NUMBER MANUFACTURER USE
Methyl n-Propyl Ketone Clean metal parts.
Solvent Blend Desoclean 110 PRC-DeSoto International Clean metal parts.
5426 San Fernando Rd.
Glendale, CA 91209
Naptha MIL-PRF-680 (Type Commercially Available Metal parts cleaning that
III) require soak cleaning.
Protective Oil Oakite Special Oakite Products Inc. Protect metal surfaces that
Protective Oil 50 Valley Road have had paint removed.
Berkeley Heights, NJ 07922
Hydraulic Assembly MCS 352 Aviation Fluids Service Co. Protect surfaces normally in
Lubricant St. Louis, MO 63166 contact with hydraulic fluid.
B. Chemical Cleaning.
(1) Aluminum parts are chemically cleaned and deoxidized before the chemical color film pretreatment.
C. Solvent Cleaning.
(1) Aluminum parts are cleaned with approved solvent prior to painting.

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 13:13:35 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
32-20-02-5 (Rev 17)

SHIMMY DAMPER - CHECK

1. Checking Shimmy Damper
A. Recommended Check Methods.
(1) Consult Table 501 to determine the recommended method of check for each component.
(2) Replace all worn or damaged parts.
(3) Replace all parts that show cracks or flaws under dye penetration check.
B. Inspection of Chrome Plating.
CAUTION: When mixing solution, always add acid to water; never add water to acid.
(1) Inspect the chrome surface of the piston rod for scratches, scores, blisters and nicks. All suspected defects should be
tested to determine if the base metal has been exposed. To test, apply liberally to the suspected areas of copper
sulfate solution consisting of 100 grams cupric sulfate, 5 milliliters sulfuric acid and 1 liter of water. Wipe off excess
liquid and check, using a strong light and a magnifying lens. If the chrome plating has been penetrated, a copper
coating will adhere to the ferrous metal. Clean the area thoroughly using solvent. If the chrome plating has been
penetrated, the part shall not be returned to airplane use. Defects that have not penetrated the chrome plating should
be polished to remove sharp edges.
C. Table 501 contains recommended checks.
NOTE: The item numbers called out in this table are identical to the item numbers in Illustrated Parts List.
Table 501. Recommended Check
NOMENCLATURE METHOD OF CHECK FOR REQUIREMENT
AND ITEM CHECK
NUMBER
Housing (45) Visual Wear, Damage No damage or wear that would
endanger the structure or prevent
effective sealing. If scratches are
present in the bore(s), see repair
chapter.
Dye Penetrant Cracks No cracks.
Go-No Go Tool Proper Bore Alignment Alignment is within specification.
CJMDL32-012
Retainer (12 and 25) Visual Wear, Damage No burrs or cuts in retainer.
Lock Ring (14 and Visual Wear, Damage No burrs or cuts in lock ring.
27)
Piston (20) Visual Wear No wear that exceeds limits given
in Fits and Clearances.
Dye Penetrant Cracks No Cracks.
Rod (11) Visual Wear Test chrome surface for defects
(refer to Paragraph B).
Magnetic Particle Cracks No cracks.

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 13:13:36 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
32-20-02-6 (Rev 17)

SHIMMY DAMPER - REPAIR

1. Repair
A. Tools and Equipment.
NOTE: Equivalent substitutes may be used for the listed items
NAME NUMBER MANUFACTURER USE
Wet or dry sandpaper 400 Commercially Available Remove corrosion from gear
strut.
Emery Cloth 320 grit 400 grit Commercially Available Remove corrosion and final
finishing of axle and piston axle
adaptor.
Scotch-Brite Pad Red or White Commercially Available Remove corrosion from
Shimmy Damper components.
Pretreatment primer Base 728-014 Sherwin-Williams Inc. Pretreatment primer
DOD-P-15328 Reducer 728-013 16116 E. 13th Street
Andover, KS 67002
Corrosion Resistant 513 x 419/910 x PRC-DeSoto International Corrosion protection primer.
Primer MIL-PRF- 942 5426 San Fernando Rd.
23377G or later Glendale, CA 91209
Polyurethane paint, 7400 (Color Name: U.S. Paint Corp. Finish paint.
medium gray Pewter) 831 South 21st St.
St. Louis, MO 63130
Waterborne Corrosion 44-GN-60 /44-GN- Deft, Inc. Corrosion protection primer
Resistant Primer 60 CATA 17151 Von Karman Ave.
Irvine, CA 92714
Hydraulic assembly MCS 352 Aviation Fluids Service Co. To lubricate piston assembly
lubricant St. Louis, MO 63166 inner barrel.
B. Barrel.
(1) Light scratches or sharp edges on the bore/s can be polished with red or white Scotch-Brite pad.
NOTE: Do not remove more material than necessary to remove sharp edges that may damage seals.
(2) External nicks or gouges shall be sanded and pretreated with chemical film treatment. For application of chemical
film treatment refer to the 500 Series Structural Repair Manual, Chapter 51, Protective Treatment of Metal.
(3) External polyurethane painted surfaces can be stripped using approved stripper. Water rinse housing immediately
following the removal of polyurethane paint.
C. Painting.
(1) Preliminary.
(a) Verify areas to be painted are free of dirt, oil, grease and/or corrosion. Use only an approved solvent. Refer to
Shimmy Damper - Cleaning.
(2) Pretreatment Primer.
(a) Mix and apply DOD-P-15328 pretreatment primer in accordance with the manufacturer’s instructions.
(3) Corrosion Resistant Primer.
(a) Mix and apply MIL-PRF-23377 corrosion resistant primer in accordance with the manufacturer’s instructions.
D. Piston Rod Assembly.
(1) A corrosion resistant steel TFE lined sleeve bearing is press fit into the eye of the piston rod. The Installed bearing
can be pressed or driven from the piston rod eye. The installed bearing shall be centered +0.005 or -0.005 in the
piston rod eye.
(2) The external surface of the piston rod has a 0.0003 to 0.0008 thick chrome plating. With no evidence of nicks the

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 13:13:38 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
32-20-02-6 (Rev 17)

piston rod can be rechromed. Minor surface roughness may be polished out with metal polish.
E. Repair Procedure.
(1) Replace all parts that have visual cracks or flaws.
(2) Replace all parts that show cracks under dye penetrant or magnetic particle inspection.
(3) Replace all parts that are worn beyond the limits given in Shimmy Damper - Fits and Clearances.
(4) Replace all packings, seals, sealing washers, and backup retainers during assembly of the shimmy damper.

SHIMMY DAMPER - ASSEMBLY

1. Assembly
A. Tools and Equipment.
NOTE: Equivalent substitutes may be used for the listed items:
NAME NUMBER MANUFACTURER USE
Proof Test Slug 0.670 inch, +0.010 Fabricate Locally To proof test damper the unit.
or -0.010 inch
diameter x 0.38
(aluminum alloy)
Hydraulic Assembly MCS 352 Solutia To lubricate the packings and
Lubricant St. Louis, MO 63166 gaskets.
B. Housing Assembly (Refer to Illustrated Parts List).
(1) Install plug assembly (50) into housing (45).
(2) Install pressure relief assembly (49) and plug assembly (48) into housing (45).
(3) Install check valve assembly (46) and plug assembly (47) into housing (45).
(4) Install check valve assembly (81) into reducer fitting (82).
C. Piston Rod Assembly.
(1) Press bearing (9) into rod (11).
NOTE: The bearing shall be centered in the rod end within +0.005 or -0.005 inch.
D. Assemble Shimmy Damper.
NOTE: Lubricate all packings, seals, and grooves liberally with MCS 352 lubricant before installing
packing into groove.
(1) Lubricate large and small bores of housing (45) with MCS 352 lubricant.
(2) Install packing (83) and reducer fitting (82) in housing (45).
(3) Assemble backup retainer (85) and packing (84) in makeup piston (87).
(4) Insert makeup piston (87) and a proof test slug (0.670 inch, +0.010 or -0.010 inch diameter by 0.38 inch) and retainer
cap (89) in housing.
NOTE: Do not install the make-up piston spring.
(5) Install scraper ring (15) in head bearing (16). Secure scraper ring (15) with lock ring (14).
(6) Install seal (33) in head bearing (29) with backup ring side out (away from fluid).
(7) Install scraper ring (28) and lock ring (27) into head bearing (29). Install O-ring (26) in groove on head bearing (29).
NOTE: Ensure packings are lubricated with MCS 352 lubricant.
(8) Install seal (19) in head bearing (16) with backup ring side out (away from fluid).
(9) Install O-ring packing (13) on head bearing (16).
(10) Slide head bearing (16) on rod (11) to eye end of rod.
(11) Slide piston (20) on rod (11). Align piston attaching hole with rod attaching hole and install roll pin (22) flush with
groove outside diameter.
NOTE: Press roll pin to equal depth at both sides of piston.
(12) Install O- ring (23) and seal (24) on piston (20).
NOTE: O-ring (23) is installed under seal (24) between the flanges of piston (20).
(13) Place a 1-1/4 Inch hose clamp (with shims to protect against damaging seal) over seal (24) on piston (20) and tighten
clamp down to compress seal. Maintain clamp pressure for approximately five to ten minutes.
(14) Remove hose clamp from piston (20) and insert piston and rod assembly into housing (45).
NOTE: Ensure packing and seal are lubricated with MCS 352.
(15) Position a drip pan under housing (45)

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 13:13:39 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
32-20-02-7 (Rev 17)

CAUTION: Skydrol proof gloves should be worn during fill and stroking procedure as hydraulic fluid will
overflow and be on many surfaces.
(16) Position piston (20) to midstroke position in housing (45) and add approximately 1/8 pint of phosphate esther base
hydraulic fluid (fill entire chamber) to eye end of housing large bore.
(17) Seat head bearing (16) and install snap ring (12).
(18) Clamp rod (11) (eye end) in smooth jawed vise with housing (45) upward.
(19) Temporarily install sealing washer (76) and screw (78) into housing
(20) While constantly pumping a trickle of phosphate esther base hydraulic fluid into fitting (82), stroke the housing (45)
downward until fluid rises just above the counterbore for head bearing (29). Repeat stroking five or six times.
(21) Remove screw (78) and sealing washer (76) from housing (45).
(22) Continue pumping fluid into fitting (82) and stroking housing (45) up and down until all air is expelled from all
chambers.
(23) Slide head bearing (29) down the rod (11) until it enters the counterbore on the housing (45).
(24) Press head bearing (29) firmly into housing counterbore and secure with retainer ring (25).
(25) Fully stroke the damper unit while slowly overflowing at bleed screw hole with slow flow from hand pump.
NOTE: Ensure no air is allowed to enter screw (78) hole by keeping constant flow of fluid from pump.
(26) Replace sealing washer (76) and screw (78) in housing (45).
(27) Completely wipe all hydraulic fluid from exterior surface of housing.
(28) Proof pressure test damper unit to 1500 PSIG for one minute.
(29) Reduce hand pump pressure.
(30) Remove retainer cap (89).
CAUTION: Hydraulic fluid will spurt from screw hole as pressure is released. Cover with rags while opening.
(31) Release pressure from shimmy damper at screw (78).
(32) Remove proof test slug from housing (45).
(33) Install makeup piston spring (87) into housing (45).
(34) Reinstall retainer cap (89).
NOTE: If fluid pressure is too great for installation of spring and retainer cap, bleed fluid at screw (78).
(35) Apply fluid flow from hand pump not to exceed 100 PSI until fluid flows from retainer cap hole.
(36) Stop hand pump and check depth through spring to makeup piston. Exercise care that measuring probe is not
inserted into threaded hole in piston.
NOTE: Depth is checked through the hole in the retainer cap (89) to the flat surface of the makeup
piston surrounding the threaded hole.
(37) Loosen slowly with screw covered with a rag, screw (78) and observe that spring (88) drives makeup piston (87)
inward to 5.00 inch depth while expelling fluid at bleed screw hole.
(38) Tighten screw (78) and sealing washer (76) before the makeup piston bottoms at approximately 5.75 inches.
(39) Fill the shimmy damper until the make-up piston (87) measures between 4.5 inches (114.3 mm) and 4.6 inches
(116.8 mm) from the end of the retainer cap (89).
NOTE: Temperature affects the dimension to which the makeup piston should be set. Refer to Table
701for the final dimension.
NOTE: Measurement is taken through the hole in the retainer cap (89).
Table 701. Shimmy Damper Service Dimension Temperature vs. Inches
TEMPERATURE SERVICE DIMENSION MAXIMUM MINIMUM
(NOM)
°F INCHES
30 4.28 4.33 4.23

40 4.35 4.40 4.30

50 4.41 4.46 4.36
60 4.48 4.53 4.43
70 4.55 4.60 4.50
80 4.61 4.66 4.56
90 4.68 4.73 4.63
100 4.74 4.79 4.69
110 4.81 4.86 4.76
120 4.88 4.93 4.83
(40) Disconnect hand pump from reducer fitting (82) and install cap (79) to reducer fitting.
(41) To service the shimmy damper, refer to Chapter 12 of the appropriate Model 500 series maintenance manual.
2. Storage
A. Preparation for Storage.
(1) Refer to Disassembly and remove head bearing from shimmy damper.
(2) Drain hydraulic fluid from shimmy damper cylinder.
(3) Refer to Assembly and install head bearing.
(4) Coat exposed surfaces of piston rod and exposed areas of head bearings with a suitable protective oil.
(5) Wrap assembly in grease proof paper, then kraft paper and pack in rigid container.
(6) Store container in a cool, dry, well ventilated area on a noncorrosive base.

SHIMMY DAMPER - FITS AND CLEARANCES

1. Fits and Clearances
A. Housing 5543301

(1) 1.253 inch (31.83 mm) maximum diameter

(2) 1.440 inch (36.60 mm) maximum diameter
(3) 0.7485 inch (19.01 mm) maximum diameter
(4) 1.471 inch (37.36 mm) maximum diameter
NOTE: This dimension applies to only one end of 55148-1 housing only as a substitute for
dimension (2).
B. Piston 5543207-1
A3850

55942018

(1) 0.5015 inch (12.751 mm) maximum diameter

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 13:13:40 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
32-20-02-8 (Rev 9)

C. Rod 5543200-8, -10

A4332
1
2

3 55942018

(1) 0.5009 inch (12.723 mm) maximum diameter

(2) 0.498 inch (12.649 mm) minimum diameter
(3) Chrome plating - no scratches/bare spots (surface finish between 8 and 16 rms)
D. Head Bearing 5543208-1
A3852

1 2

55942018

(1) 0.505 inch (12.27 mm) maximum diameter

(2) 1.434 inch (36.40 mm) minimum diameter
E. Head Bearing 55147-1
A3852

1 2

55942018

(1) 0.505 inch (12.27 mm) maximum diameter

(2) 1.463 inch (37.16 mm) minimum diameter
F. Makeup Piston 5543209-1
A4334

50942018

(1) 0.684 inch (17.37 mm) minimum diameter

G. Makeup Piston 5543209-2
A4334

50942018

(1) 0.682 inch (17.63 mm) minimum diameter

SHIMMY DAMPER - ILLUSTRATED PARTS LIST

1. Illustrated Parts List
A. Introduction.
(1) The Illustrated Parts List has been prepared to assist customer personnel in requisitioning, storing and issuing the
replaceable shimmy damper components and in identifying new and reclaimed parts.
(2) This parts list covers the nose landing gear shimmy damper assembly used on the Cessna Citation, Citation II,
Citation II Bravo, Citation S/II and Citation V airplanes. These part numbers are covered:
5543001-1 5543001-3 5543001-5 5543001-7 5543001-8
DDA55146-1 5543001-11 5543001-12
(3) The indention system used in the detailed parts list shows the relationship of one part to another. For a given item, the
indention code shows a system, installation or general heading starting at the extreme left position continuing on
down into the succeeding columns until the end detail is reached. Example:
A18017
1234567
Installation
Detail Parts for Installation
Assembly
Attaching Parts for Assembly
Detail Parts for Assembly
Subassembly
Attaching Parts for Subassembly
Detail Parts for Subassembly
Sub−Subassembly
Attaching Parts for Sub−Subassembly
Detail Parts for Sub−Subassembly

(4) The quantities given in the UNITS PER ASSY column of the Illustrated Parts List are, in the case of assemblies, the
total used at the indicated location. For component parts indented under the assemblies, the quantities are those
used In the assembly. The quantities specified, therefore, are not necessarily the total used per installation.
(5) Effectivity for detail parts of assemblies covered by this technical manual are listed in the Effect column. The code A,
B, C, etc., listed for the assembly Is the code for the detail parts peculiar to that assembly. If no code appears in the
Effect column, that detail part is used in all assemblies listed.
(6) When a part of later design is not interchangeable with the part it replaces, both parts applicable to the particular
usage are listed. The individual part usage is listed in the Effect column. Care should be exercised in determining
proper usage when ordering to ensure receipt of the correct part.
(7) When a part of later design is completely interchangeable with the part it replaces, both parts will be serialized and
the notation FSO (for spares order) will be entered following the listing of the earlier design part. FSO means that the
earlier design part is not available and the later design part must be used.
(8) The basic number identifies the Cessna drawing only. Each installation, assembly or detail part is assigned a part
number which consists of the drawing number and an appropriate dash number. Example:
A12537
EXAMPLE:
Part Number
6707005 − 7

Basic Number Dash Number

(Drawing Identification
Only)

NOTE: Parts stamped with a dash 400 series are for internal control purposes only and should not be
used by the operator for ordering/ identifying purposes.
NOTE: Repair parts available and packaged as a kit are identified in the parts list with an asterisk (*).

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 13:13:44 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
32-20-02-10 (Rev 16)

Kits may be ordered by the kit part number located at the end of the parts list.
B. For Vendor names and addresses with Federal Supply Codes, refer to Introduction - Supplier Address List.

SHIMMY DAMPER ASSEMBLY

NOMENCLATURE EFFECTIVITY UNITS
PER
ITEM PART NUMBER 1 2 3 4 5 6 7 FROM TO ASSY
- SHIMMY DAMPER ASSEMBLY

- . SHIMMY DAMPER ASSY

1 5543001-1 A NP
FSO 5543001-11
- . SHIMMY DAMPER ASSY
2 DDA055146-1 B NP R
FSO 5543001-11
SHIMMY DAMPER ASSY
- 3 5543001-3 . C NP
FSO 5543001-12
- . SHIMMY DAMPER ASSY
4 5543001-5 D NP
FSO 5543001-12

- . SHIMMY DAMPER ASSY

5 5543001-7 E NP
FSO 5543001-12

- . SHIMMY DAMPER ASSY

6 5543001-8 F NP
FSO 5543001-11
- 6A 5543001-11 . SHIMMY DAMPER ASSY G 01
- 6B 5543001-12 . SHIMMY DAMPER ASSY H 01

- 7 5543200-7 . . ROD ASSY-PISTON A,B,C NP

FSO 5543200-10

- 8 5543200-9 . . ROD ASSY-PISTON D,E,F NP

FSO 5543200-11
- 8A 5543200-11 . . ROD ASSY-PISTON G 01

9 MS21240-06C010 . . . BEARING REFER 01

TO NOTE 1
- 10 5543200-8 . . . ROD A THRU C 01

11 5543200-10 . . . ROD FSO D,E,F 01

5543200-12
- 11A 5543200-12 . . . ROD G 01

12 MS16625-4143 . . RING-RETAINING 01
REFER TO NOTE 1

13 NAS1611-217 . . O-RING REFER TO 01

NOTE 1

14 CM2690-00 . . LOCK RING REFER 01

TO NOTE 1

. . RING-SCRAPER
15 S11065-01T V09257 01
REFER TO NOTE 1
16 5543208-1 . . BEARING-HEAD 01
RETAINER FSO 233-
- 17 MS28774-112 . . 11251-952-0190 V5F573 A THRU D NP
REFER TO NOTE 1
O-RING FSO 233-
- 18 NAS1611-112 . . 11251-952-0190 A THRU D NP
REFER TO NOTE 1

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 13:13:45 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
32-20-02-1001 (Rev 16)

. . SEAL REF S2800-220

19 233-11251-952-0190 V5F573 E,F 01
REFER TO NOTE 1
20 5543207-1 . . PISTON 01
PIN-ROLL REFER TO
- 21 MS16562-138 . . NOTE 1 FSO NP
6343001-4
. . PIN REFER TO NOTE
22 6343001-4 01
1

. . O-RING REFER TO
23 NAS1611-214 01
NOTE 1

. . SEAL REFER TO
24 S13201-214N V09257 01
NOTE 1
. . RING-RETAINER
25 MS16625-4143 01
REFER TO NOTE 1
. . O-RING REFER TO
26 NAS1611-217 01
NOTE 1

. . LOCK RING REFER

27 CM2690-00 01
TO NOTE 1
. . RING-SCRAPER
28 S11065-01T V09257 01
REFER TO NOTE 1
29 5543208-1 . . BEARING-HEAD A,C,D,E,F 02
- 29A 5543208-2 . . BEARING-HEAD G 02
- 30 55147-1 . . BEARING-HEAD B 01
RETAINER FSO
- 31 MS28774-112 . . S2800-220 REFER TO A THRU D NP
NOTE 1
O-RING FSO S2800-
- 32 NAS1611-112 . . 220 REFER TO NOTE A THRU D NP
1
. . SEAL REFER TO
33 233-11251-952-0190 V5F573 E,F 01
NOTE 1
- 34 5543001-2 . . HOUSING ASSY A 01
- 35 55146-2 . . HOUSING ASSY B 01
HOUSING ASSY FS0
- 36 5543001-4 . . C NP
5543001-6
- 37 5543001-6 . . HOUSING ASSY D,E 01
HOUSING ASSY FSO
- 38 5543001-9 . . F NP
5543001-10
- 38A 5543001-10 . . HOUSING ASSY G 01
- 39 5543301-1 . . . HOUSING A 01
- 40 5543301-2 . . . HOUSING A 01
- 41 55148-1 . . . HOUSING B 01
- 42 5543301-4 . . . HOUSING C 01
- 43 5543301-6 . . . HOUSING C,D,E 01

HOUSING ALT
- 44 5543301-5 . . . FOR 5543301-4 C,D,E 01
AND 5543301-6
HOUSING FSO
45 5543301-8 . . . F NP
5543301-9
- 45A 5543301-9 . . . HOUSING G 01
VALVE ASSY-
46 CKFA1876005A . . . V92555 01
CHECK
47 S1221-6 . . . PLUG ASSY 01
48 S1221-8 . . . PLUG ASSY 01
PRESSURE
49 PRRA2812120D . . . V92555 01
RELIEF ASSY
50 S1221-5L . . . PLUG ASSY 01
NOTE 1: THIS PART MAY BE ORDERED AS PART OF CPD5 SHIMMY DAMPER SEAL KIT
NOMENCLATURE EFFECTIVITY UNITS
PER
ITEM PART NUMBER 1 2 3 4 5 6 7 FROM TO ASSY
- SHIMMY DAMPER ASSEMBLY
- 75 NAS1598-08N . . WASHER-SEALING A THRU E 01
REFER TO NOTE 1
. . WASHER REFER TO
76 AN960-8L F 01
NOTE 1
WASHER ALT FOR
- 76A NAS1149FN816P . . F 01
AN960-8L
O-RING REFER TO
77 NAS1611-007 . . F 01
NOTE 1
. . SCREW REFER TO
78 MS27039-0806 01
NOTE 1
79 AN929-4 . . CAP 01
- . . FITTING ASSY-
80 5543211-1 01
CHECK VALVE
VALVE ASSY-
81 CKFA1876005A . . . V92555 01
CHECK
FITTING-
82 5543211-2 . . . 01
REDUCER
. . PACKING-GASKET
83 NAS1612-8 01
REFER TO NOTE 1
84 NAS1611-112 . . PACKING NP
85 MS28774-112 . . RETAINER NP
- . . PISTON-MAKEUP
86 5543209-1 A THRU E NP
FSO 5543209-3
87 5543209-3 . . PISTON-MAKEUP F 01
. . SPRING-MAKEUP
88 5543401-1 01
PISTON
89 5543210-1 . . CAP-RETAINER 01

NOTE 1: THIS PART MAY BE ORDERED AS PART OF CPD5 SHIMMY DAMPER SEAL KIT
- Item Not Illustrated

Figure 1001 : Sheet 1 : SHIMMY DAMPER ASSEMBLY

Figure 1001 : Sheet 2 : SHIMMY DAMPER ASSEMBLY

A18203

78
76
77

79
81
82
83

84
85
87

5542T3021A

UNLOCK AND SEQUENCE ACTUATOR - ILLUSTRATED PARTS LIST

1. Illustrated Parts List
A. Introduction.
(1) The Illustrated Parts List has been prepared to assist customer personnel in requisitioning, storing and issuing the
replaceable shimmy damper components and in identifying new and reclaimed parts.
(2) This parts list covers the unlock and sequence actuator assemblies used on the Cessna Citation airplanes. These
part numbers are covered:
5527504-1 5525504-2 5525504-3 5527534-1 6527304-1
(3) The indention system used in the detailed parts list shows the relationship of one part to another. For a given item, the
indention code shows a system, installation or general heading starting at the extreme left position continuing on
down into the succeeding columns until the end detail is reached. Example:
A18017
1234567
Installation
Detail Parts for Installation
Assembly
Attaching Parts for Assembly
Detail Parts for Assembly
Subassembly
Attaching Parts for Subassembly
Detail Parts for Subassembly
Sub−Subassembly
Attaching Parts for Sub−Subassembly
Detail Parts for Sub−Subassembly

(4) The quantities given in the UNITS PER ASSY column of the Illustrated Parts List are, in the case of assemblies, the
total used at the indicated location. For component parts indented under the assemblies, the quantities are those
used in the assembly. The quantities specified, therefore, are not necessarily the total used per installation.
(5) Effectivity for detail parts of assemblies covered by this technical manual are listed in the Effect column. The code A,
B, C, etc., listed for the assembly is the code for the detail parts peculiar to that assembly. If no code appears in the
Effect column, that detail part is used in all assemblies listed.
(6) When a part of later design is not interchangeable with the part it replaces, both parts applicable to the particular
usage are listed. The individual part usage is listed in the Effect column. Care should be exercised in determining
proper usage when ordering to ensure receipt of the correct part.
(7) When a part of later design is completely interchangeable with the part it replaces, both parts will be serialized and
the notation FSO (for spares order) will be entered following the listing of the earlier design part. FSO means that the
earlier design part is not available and the later design part must be used.
(8) The basic number identifies the Cessna drawing only. Each installation, assembly or detail part is assigned a part
number which consists of the drawing number and an appropriate dash number.
A12537
EXAMPLE:
Part Number
6707005 − 7

Basic Number Dash Number

(Drawing Identification
Only)

NOTE: Parts stamped with a dash 400 series are for internal control purposes only and should not be
used by the operator for ordering/Identifying purposes.
B. For Vendor names and addresses with Federal Supply Codes, refer to Introduction - Supplier Address List.

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 13:13:50 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
32-30-05-0 (Rev 12)

UPLOCK AND SEQUENCE ACTUATOR - DESCRIPTION AND OPERATION

1. Description
A. The uplock and sequence actuator consists of a barrel and valve body, piston and rod assembly, ball valve and associated
fittings. The purpose of the uplock and sequence actuator is to release landing gear uplock hooks prior to allowing
hydraulic pressure to the gear actuators.
B. These uplock and sequence actuator part numbers are affected by this individual component maintenance manual:
5527504-1 5527504-2 5527504-3 5527534-1 6527504-1
2. Operation
A. Landing gears are held in the retracted position by mechanical hooks that must be released prior to applying hydraulic flow
to the gear actuators. The uplock and sequence actuator has a controllable check valve to prevent passage of fluid until the
uplock hook is fully released and then the valve is unseated. For gear retraction, hydraulic flow unseats the check valve to
allow passage of fluid. Refer to Figure 1.
3. Personnel Safety Precautions - Hydraulic Fluid
A. The uplock and sequence actuator contains phosphate ester base hydraulic fluid. Before performing any operation on the
uplock and sequence actuator, personnel should read and thoroughly understand these instructions:
WARNING: Observe the following safety precautions when working on systems containing phosphate ester
base fluid. Prolonged exposure to this fluid can cause skin dehydration and chapping.
(1) Wash hands thoroughly with soap and water before starting work.
(2) Apply barrier cream (silicone hand cream) to hands, wrists and forearms. Rub cream under fingernails and into
creases of skin.
(3) Wear eye goggles when pressure testing components of system or anytime there is possibility of hydraulic fluid
splashing into eyes.
(4) If hydraulic fluid splashes into eyes, treat eyes immediately by irrigating thoroughly with clear, cold water.
(5) Wash hands, wrists and forearms with soap and hot water after contacting hydraulic fluid.
(6) If clothing becomes soaked with hydraulic fluid, remove the contaminated clothing as soon as possible. Wash skin
exposed to hydraulic fluid with soap and warm water. Wash hydraulic fluid contaminated clothing before wearing.
4. Technical Safety Precautions - Hydraulic Fluid
A. Because the uplock and sequence actuator contains phosphate ester base hydraulic fluid, improper maintenance
practices can be damaging to gear components and other equipment. Before performing maintenance or any operation
on the uplock and sequence actuator, personnel should read and thoroughly understand these technical precautions:
CAUTION: Phosphate ester base hydraulic fluid will damage and/or deteriorate a wide range of materials;
including rubber, copper, various plastics and paints.
(1) Make sure that hydraulic fluid does not come in contact with any part of the component outside of the uplock and
sequence actuator. Keep spillage to an absolute minimum. Clean up spilled hydraulic fluid immediately to prevent
contamination of non-hydraulic components and to avoid false hydraulic leak detections. Should spillage occur, wipe
up the fluid with a dry cloth and wash area with naphtha MIL-PRF-680 (Type I).
(2) When components are disassembled, provide suitable protection for preventing entry of foreign material by using
caps and/or covers.
(3) Always check angle and position of components prior to disassembly to ensure proper alignment and placement of
components and hardware during assembly or replacement.
(4) Use naphtha MIL-PRF-680 (Type I) or methyl n-propyl ketone when washing metal parts prior to assembly. Ensure all
traces of the cleaning agent are removed before assembly.
(5) Use only clean hydraulic fluid for flushing or testing hydraulic components.
(6) Do not unpack seals, O-rings/packings until they are required and make sure that only correct, compatible and
approved seals, O-rings/ packings are used.
CAUTION: Take special care not to contaminate seals, o-rings/ packings after lubrication.
CAUTION: Prevent contamination of phosphate ester base hydraulic fluid with other hydraulic fluids, oils,
water or dirt.

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 13:13:51 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
32-30-05-0 (Rev 12)

(7) When assembling the uplock and sequence actuator hydraulic seals, O-rings/packings, lubricate only with phosphate
ester base hydraulic fluid. Always lubricate seals, O-ring/packings immediately before installation. Threaded fittings
should be assembled without the use of lubricants whenever possible. If a lubricant is required to prevent galling or to
otherwise ease installation, use phosphate ester base hydraulic fluid or VV-P-236 Petrolatum.

Figure 1 : Sheet 1 : Uplock and Sequence Actuator - Description and Operation

UPLOCK AND SEQUENCE ACTUATOR - TESTING

1. Testing
A. Functional Test.
(1) With piston rod restrained to travel not more than 0.656 inch from full extended position, apply 1500 PSIG (maximum)
pressure to inlet valve fitting. Refer to Figure 101 for suggested test setup.
(2) Leakage from opposite port shall not exceed 5 drops per minute.
(3) Leakage at the piston rod or past the piston seal shall not exceed one drop in 25 cycles.
(4) There shall be no leakage at fittings.

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 13:13:56 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
32-30-05-1 (Rev 5)

Figure 101 : Sheet 1 : Actuator Test Setup

UPLOCK AND SEQUENCE ACTUATOR - DISASSEMBLY

1. Disassembly
A. Disassemble actuator (Refer to Illustrated Parts List).
(1) Remove valve fitting (6) from body (4).
(2) Remove spring (9), ball (10) and ball (11).
(3) Cut safety wire and remove plug fitting (24) and spring (21) from body.
(4) Remove piston and rod assembly (19) from body.
(5) Remove and discard packings and backup rings from piston and body.

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 13:14:00 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
32-30-05-4 (Rev 9)

UPLOCK AND SEQUENCE ACTUATOR - CLEANING

1. Cleaning
A. Tools and Equipment.
NOTE: Equivalent substitute may be used for the listed item:
NAME NUMBER MANUFACTURER USE
Methyl n-Propyl Ketone Commercially Available Clean metal parts.
B. Cleaning.
(1) Clean metal parts with solvent. Apply solvent under pressure to all channels to ensure cleanness. Thoroughly dry all
parts with filtered, dry, compressed air, lint free cloth or lint free disposable tissue.
WARNING: Use cleaning solvents only in a well ventilated area. Avoid inhaling solvent vapors. Keep solvent
and solvent containers away from sparks or open flame.

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 13:14:01 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
32-30-05-5 (Rev 5)

UPLOCK AND SEQUENCE ACTUATOR - CHECK

1. Checking Uplock and Sequence Actuator
A. Always discard packings and packing backup rings and install new parts.
B. Do not attempt to repair damaged or worn parts of the actuator assembly. Discard all defective items and install a new
parts during assembly.
C. Check parts:
(1) Check all parts visually, preferably under magnification, for stripped threads, cracks, deep nicks and dents.
(2) Check ball seats for scratches or dents.
(3) Check applicable parts for dimensional conformity to Uplock and Sequence Actuator - Fits and Clearances.

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 13:14:03 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
32-30-05-6 (Rev 9)

UPLOCK AND SEQUENCE ACTUATOR - REPAIR

1. Repair
A. Tools and Equipment.
NOTE: Equivalent substitutes may be used for the listed items:
NAME NUMBER MANUFACTURER USE
Wet-or-Dry Sandpaper 400 grit Commercially Available Remove corrosion from gear
strut.
Wash Primer MIL-C-8514 Commercially Available Pretreatment.
Pretreatment primer Base 728-014 Sherwin-Williams Inc. Pretreatment primer
DOD-P-15328 Reducer 728-013 16116 E. 13th Street
Andover, KS 67002
Corrosion Resistant 513 x 419/910 x PRC-DeSoto International Corrosion protection primer.
Primer MIL-PRF- 942 5426 San Fernando Rd.
23377G or later Glendale, CA 91209
Polyurethane paint, 7400 (Color Name: U.S. Paint Corp. Finish paint.
medium gray Pewter) 831 South 21st St.
St. Louis, MO 63130
Adhesive RTV-154 General Electric Bond placard to valve body.
Silicone Products Dept.
Waterford, NY
Clear Enamel AA92-C-21C U.S. Paint Cover placard.
Catalyst AA92-C-22B
B. Repair Procedures.
(1) Replace all parts that have visual cracks or flaws.
(2) Replace all parts that show cracks under dye penetrant or magnetic particle inspection.
(3) Replace all parts that are worn beyond the limits given in Uplock and Sequence Actuator - Fits and Clearances.
(4) Replace all packings, seals and backup retainers with new parts.
(5) Repair housing external surface scratches and nicks by sanding or polishing followed by pretreatment.
C. Installation of Nameplate.
(1) Bond nameplate to actuator with RTV-154 adhesive. Prepare and apply adhesive in accordance with manufacturer's
instructions.
(2) Apply two coats of clear polyurethane top coat over the nameplate after installation. Prepare and apply top coat in
accordance with manufacturer's instructions.

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 13:14:04 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
32-30-05-7 (Rev 5)

UPLOCK AND SEQUENCE ACTUATOR - ASSEMBLY

1. Assembly
A. Tools and Equipment.
NOTE: Equivalent substitute may be used for the listed item:
NAME NUMBER MANUFACTURER USE
Safety Wire Monel 0.032 inch Commercially Available Safety plug fitting.
diameter
B. Assemble Actuator (Refer to Illustrated Parts List).
(1) Install packing (13) and backup ring (12) into recess of body (4).
NOTE: Lubricate packings and backup rings in phosphate ester base hydraulic fluid immediately
before installation.
(2) Install packing (18) and backup ring (17) into groove in piston and rod assembly (19) and install packing (20) on
piston.
(3) Insert piston and rod assembly (19) into body (4).
(4) Install packing (22) on plug fitting (24). Install fitting and spring (21) into body (4). Torque to standard torque value and
secure with 0.032 safety wire.
(5) Install ball (11) and ball (10) into recess of body (4).
(6) Install packing (8) on valve fitting (6). Install fitting and spring into body (4). Torque fitting to standard torque value. On
5527534-1 assembly, secure valve fitting (6) with safety wire.
C. Storage.
(1) Drain hydraulic fluid from valve body.
(2) Cap open ports.
(3) Wrap in moisture proof material (plastic bag or grease proof paper).
(4) Pack in rigid container and store in cool, dry, ventilated area.

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 13:14:05 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
32-30-05-8 (Rev 9)

UPLOCK AND SEQUENCE ACTUATOR - FITS AND CLEARANCES

1. Fits and Clearances
A. Barrel and Valve Body

(1) 0.375 inch, +0.002 or -0.000 inch (9.53 mm, +0.05 or -0.00 mm)
(2) 0.750 inch, +0.002 or -0.000 inch (19.05 mm, +0.05 or -0.00 mm)
B. Barrel and Valve Body
A4336
2

3 55941028

(1) 0.748 inch, +0.000 or -0.002 inch (19.00 mm, +0.00 or -0.05 mm)
(2) 0.374 inch, +0.000 or -0.002 inch (9.50 mm, +0.00 or -0.05 mm)
(3) 0.125 inch, +0.004 or -0.000 inch (3.18 mm, +0.10 or -0.00 mm)

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 13:14:06 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
32-30-05-1001 (Rev 13)

UP LOCK AND SEQUENCE ACTUATOR-LANDING GEAR

NOMENCLATURE EFFECTIVITY UNITS
PER
ITEM PART NUMBER 1 2 3 4 5 6 7 FROM TO ASSY
- UP LOCK AND SEQUENCE ACTUATOR-
LANDING GEAR

- 1 5527504-1 . ACTUATOR ASSY FSO A NP

5527504-2
- 2 5527504-2 . ACTUATOR ASSY B 01
- 2A 5527504-3 . ACTUATOR ASSY E 01
- 3 5527534-1 . ACTUATOR ASSY C 01
- 3A 5527304-3 . ACTUATOR ASSY D 01
- 3B 6527504-1 . ACTUATOR ASSY F 01
4 5527215-1 . . BODY A,B,D,E,F 01
- 5 5527245-1 . . BODY C 01
6 5527218-1 . . VALVE FITTING A&B 01
- 7 5527248-1 . . VALVE FITTING C 01
- 7A 6327504-3 . . VALVE FITTING D,E 01
7B 6327504-3 . . VALVE FITTING F 01
8 NAS1612-4 . . PACKING-O RING 01
9 5527404-3 . . SPRING-VALVE 01
10 S272-11 . . BALL 01
11 S272-5 . . BALL 01
12 S1121-389 . . RING-BACKUP 01

- . . RING-BACKUP ALT
12A 8-2043E652-90 V02697 A,B,C,D,E 01
FOR S1121-389
13 00363139E515CT . . O-RING V02697 01

- . . O-RING ALT FOR

13A NAS1611-204 A,B,C,D,E 01
00363139E515CT
- 14 5527405-1 . . NAMEPLATE A 01
15 5527405-3 . . NAMEPLATE B 01
- 16 5527405-2 . . NAMEPLATE C 01
- 16A 5527405-4 . . NAMEPLATE D,E 01
- 16B 6527405-1 . . NAMEPLATE F 01
17 S1121-207 . . RING-BACKUP 01
- . . RING-BACKUP ALT
17A 8-106E652-90 V02697 A,B,C,D,E 01
FOR S1121-207
18 00181103E515CT . . O-RING V02697 01
- . . O-RING ALT FOR
18A NAS1611-106 A,B,C,D,E 01
00181103E515CT
19 5527216-1 . . PISTON AND ROD 01
20 NAS1611-113 . . O-RING 01

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 13:14:08 CDT 2018
Model 500 Series Component Maintenance Manual (Rev 17)
32-30-05-1001 (Rev 13)

- . . O-RING ALT FOR

20A NAS1611-113A 01
NAS1611-113
21 5527404-1 . . SPRING-OUTER 01
22 NAS1612-10 . . O-RING 01
- . . O-RING ALT FOR
22A NAS1612-10A 01
NAS1612-10
- 23 5527217-2 . . PLUG FITTING ASSY A 01
24 5527217-3 . . PLUG FITTING ASSY B&C 01
- 25 6527217-1 . . PLUG FITTING ASSY F 01
- Item Not Illustrated

Figure 1001 : Sheet 1 : UP LOCK AND SEQUENCE ACTUATOR-LANDING GEAR

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Sun Aug 26 13:14:08 CDT 2018

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