Quick Reference Handbook

Gulfstream Aerospace Document Number

GAC-AC-GIV-OPS-0003

October 30, 2017

TO: All Gulfstream IV Operators

SUBJECT: GIV Quick Reference Handbook Revision 30, dated
October 30, 2017

This letter to operators introduces the release of GIV Quick Reference

Handbook Revision 30, dated October 30, 2017. This revision
corresponds with GIV FAA Airplane Flight Manual (AFM) Revision 52,
dated October 30, 2017. Specific data in this revision corresponds with
similar data in the current GIV / G400 / G300 Airplane Flight Manuals
(AFM). This revision is applicable to both non-SP GIV aircraft (SN 1000
through 1213, not having ASC 190) and GIV-SP aircraft (SN 1214 and
subs; SN 1000 through 1213, having ASC 190).

The purpose of this revision it to modify procedures related to Nose

Wheel Steering Uncomanded Turns.

To incorporate this revision, remove the superseded pages and

incorporate the new pages in accordance with the Summary of
Revision 30. Please use the List of Effective Pages to ensure the
inclusion of all pages. While incorporating this revision, if you notice
missing pages, please contact Flight Crew Technical Information at
1-800-810-4853 Option 3 (United States) or 1-912-965-4178 Option 3
(International).

In addition, if there are specific issues regarding any of our Flight

Publications (i.e., technical corrections, grammatical errors, etc), we
encourage you to submit a Publications Change Request (PCR) at:
http://surveys.gulfstream.com/s3/pcr-request

(over, please)
Pilot’s Checklist (PCL):
The GIV Pilot’s Checklist (PCL) Basic thru Revision 30 is approved for
use as a companion checklist to the GIV QRH Revision 30.
We, in Flight Crew Technical Information, hope that our commitment to
the timeliness, accuracy, and user-friendliness of your QRH
demonstrates our determination to provide nothing less than absolute
customer satisfaction. Toward that end, we want your advice on how to
make your manuals better with each revision. Please feel free to contact
us at any time using either the Pilot’s Manuals Direct Line form or the
contact information listed at the end of this letter.

Thank you for the opportunity to better serve you.

Flight Crew Technical Information

Gulfstream Aerospace
P.O. Box 2206, M/S SW7 (C-20)
Savannah, GA 31402-2206
800-810-4853, Option 3 (United States)
912-965-4178, Option 3 (International)
912-965-7251 (Fax)
pubs.flight.crew.manager@gulfstream.com
Submitted By: ___________________________ Date: _____________________

Company: ___________________________ Title: _____________________

Address: ___________________________ Phone: (____)______-_________

___________________________ Fax: (____)______-_________

___________________________ E-mail: _____________________

Airplane(s) Production Serial Number(s): ________ / ________ / ________ / ________

Model: GV G350 G450 G500 G550 G650 G650ER Other ______

Manual: AFM OM QRH PCL PH Other ______

Question or Suggestion:

For Technical Issues: For Sales & Distribution Issues:

Flight Crew Technical Information Product Support Business Office
Gulfstream Aerospace Gulfstream Aerospace
P.O. Box 2206, M/S SW7 (C-20) P.O. Box 2206, M/S SW7 (C-20)
Savannah, GA 31402-2206 Savannah, GA 31402-2206
800-810-4853, Option 3 (United States) 800-810-4853, Option 3 (United States)
912-965-4178, Option 3 (International) 912-965-4178, Option 3 (International)
912-965-7251 (Fax) 912-965-7251 (Fax)
pubs.flight.crew.manager@gulfstream.com pubs@gulfstream.com
This page intentionally left blank.
Quick Reference Handbook
Summary of Revision 30, dated Oct 30, 2017
Rev Bar Location Reason For Change
Front Matter Reflects Revision 30

Introduction Reflects Revision 30

Normal Procedures

NE-3 – NE-10 Before Landing: Added Step 8. Deleted a note.

Added a note.
Traffic Pattern: Added Step 13. Revised Step 16.
Added Step 17. Revised Step 29. Renumbered
steps.

Abnormal / Emergency Procedures

EF-9 – EF-12 Combined Hydraulic System Failure – Loss of

Pressure Only: Added Steps 9 and 10.
Flight Hydraulic System Failure – Loss of
Pressure and / or Fluid: Added Steps 8 and 9.
Landing With Standby Electrical Power System
Operating: Added Step 3.

EH-3 – EH-6 Emergency Descent Procedure: Added Steps 11

thru 15.

REVISION 30 FRONT MATTER

Oct 30/17 Page F - 1
 Quick Reference Handbook
Publications Point of Contact
For questions or comments concerning this handbook, please contact:
Flight Crew Technical Information
Gulfstream Aerospace
P.O. Box 2206, M/S SW7 (C-20)
Savannah, GA 31402-2206
800-810-4853, Option 3 (United States)
912-965-4178, Option 3 (International)
912-965-7251 (Fax)
pubs.flight.crew.manager@gulfstream.com

Gulfstream Customer Support

United States: (800) 810-GULF (4853)
International: (912) 965-4178, Option 3

FRONT MATTER REVISION 30

Page F - 2 Oct 30/17
Quick Reference Handbook
List of Effective Pages
Total number of pages in this publication is 598, composed as shown below:

Section Page Rev

Non-SP GIV Performance
Front Matter TOC Page (P) i - ii 24
Data Pages (F) 1-4 30 Data Pages (PA) 1 - 60 24
Introduction Data Pages (PB) 1-2 24
Data Pages (I) 1-2 30 Data Pages (PB) 3 - 14 28
Data Pages (PB) 15 - 18 24
Normal Procedures Data Pages (PC) 1-6 24
Data Pages (PC) 7 - 14 28
TOC Page (N) i -iv 26
Data Pages (PC) 15 - 16 24
Data Pages (NA) 1 - 10 27
Data Pages (NB) 1-2 27
Messages and Annunciations
Data Pages (NB) 3-6 25
Data Pages (NC) 1-4 27 Data Pages (MA) 1-2 29.1
Data Pages (NC) 5-8 28 Data Pages (MA) 3-8 28
Data Pages (ND) 1-4 27 Data Pages (MA) 9 - 10 26
Data Pages (ND) 5-6 29.1 Data Pages (MB) 1-4 24
Data Pages (NE) 1-2 29.1 Data Pages (MB) 5-6 28
Data Pages (NE) 3 - 10 30 Data Pages (MB) 7 - 18 24
Data Pages (NF) 1-4 28 Data Pages (MB) 19 - 20 26
Data Pages (NF) 5-6 24 Data Pages (MB) 21 - 22 28
Data Pages (NG) 1 - 16 24 Data Pages (MB) 23 - 24 24
Data Pages (NG) 17 - 18 28 Data Pages (MB) 25 - 28 28
Data Pages (NG) 19 - 26 24 Data Pages (MB) 29 - 30 24
Data Pages (NH) 1 - 12 26
Data Pages (NI) 1 - 16 24 Data Pages (MC) 1-4 24
Data Pages (MC) 5-6 28
GIV-SP Performance Data Pages (MC) 7 - 18 24
TOC Page (P) i - ii 24 Data Pages (MC) 13 - 14 28
Data Pages (PA) 1 - 60 24 Data Pages (MC) 15 - 18 24
Data Pages (PB) 1-2 24
Data Pages (PB) 3 - 14 28 Abnormal / Emergency Procedures
Data Pages (PB) 15 - 18 24 TOC Pages (E) i - ii 26
Data Pages (PC) 1-6 24 TOC Pages (E) iii - iv 28
Data Pages (PC) 7 - 14 28 TOC Pages (E) v - vi 29.1
Data Pages (PC) 15 - 16 24 TOC Pages (E) vii - viii 26

Data Pages (EA) 1-2 26

Data Pages (EA) 3-6 28
Data Pages (EA) 7-8 24
Data Pages (EA) 9 - 10 27
Data Pages (EA) 11 - 26 24
Data Pages (EA) 27 - 28 26
Data Pages (EA) 29 - 38 24

Continued on next page

REVISION 30 FRONT MATTER

Oct 30/17 Page F - 3
 Quick Reference Handbook

Data Pages (EB) * 1 - 16 24

Data Pages (EB) ** 1-8 24

Data Pages (EC) 1 - 24 28

Data Pages (ED) 1 - 18 28

Data Pages (EE) 1 - 14 28

Data Pages (EF) 1-2 28

Data Pages (EF) 3-6 24
Data Pages (EF) 7-8 26
Data Pages (EF) 9 - 12 30
Data Pages (EF) 13 - 16 28
Data Pages (EF) 17 - 20 24

Data Pages (EG) 1-8 24

Data Pages (EG) 9 - 10 26
Data Pages (EG) 11 - 14 24

Data Pages (EH) 1-2 29.1

Data Pages (EH) 3-6 30
Data Pages (EH) 7-8 24
Data Pages (EH) 9 - 10 28
Data Pages (EH) 11 - 12 24
Data Pages (EH) 13 -14 29

Data Pages (EI) 1-4 26

Data Pages (EI) 5-6 27
Data Pages (EI) 7-8 26

Supplemental Data
Data Pages (S) 1-4 24
Data Pages (S) 5 - 12 28
Data Pages (S) 13 - 40 24
Data Pages (S) 41 – 56 26
Applicable to EB Pages:
* = Brake By Wire
** = HMAB

FRONT MATTER REVISION 30

Page F - 4 Oct 30/17
Quick Reference Handbook
Record of Revisions
Dates of issue for original and changed pages are:
Revision No: Dated: Inserted By: Date:
Revision 13
Dec 8, 2005 Gulfstream Oct 30, 2017
(Re-issue)
Revision 14 June 1, 2006 Gulfstream Oct 30, 2017
Revision 15 July 13, 2006 Gulfstream Oct 30, 2017
Revision 16 Jan 16, 2007 Gulfstream Oct 30, 2017
Revision 17
Feb 1, 2007 Gulfstream Oct 30, 2017
(Re-issue)
Revision 18 May 22, 2007 Gulfstream Oct 30, 2017
Revision 19 July 26, 2007 Gulfstream Oct 30, 2017
Revision 20 Sep 18, 2007 Gulfstream Oct 30, 2017
Revision 21 Dec 21, 2007 Gulfstream Oct 30, 2017
Revision 22 May 13, 2008 Gulfstream Oct 30, 2017
Revision 22.1 Aug 28, 2008 Gulfstream Oct 30, 2017
Revision 23 Nov 20, 2008 Gulfstream Oct 30, 2017
Revision 23.1 Feb 12, 2009 Gulfstream Oct 30, 2017
Revision 24
Mar 17, 2010 Gulfstream Oct 30, 2017
(Re-issue)
Revision 25 Jul 14, 2010 Gulfstream Oct 30, 2017
Revision 26 Oct 5, 2011 Gulfstream Oct 30, 2017
Revision 27 Dec 10, 2012 Gulfstream Oct 30, 2017
Revision 28 May 25, 2016 Gulfstream Oct 30, 2017
Revision 29 May 05, 2017 Gulfstream Oct 30, 2017
Revision 29.1 Aug 07, 2017 Gulfstream Oct 30, 2017
Revision 30 Oct 30, 2017 Gulfstream Oct 30, 2017

© 2017 Gulfstream Aerospace Corporation

All rights reserved, including the right to reproduce this publication. No
part may be reproduced, stored in any retrieval system, or transmitted
in any part or form or by any means, electronic, photo-copying,
microfilm, microfiche, mechanical, or otherwise, without prior written
permission of Gulfstream Aerospace Corporation.

Gulfstream Aerospace Document Number GAC-AC-GIV-OPS-0003

REVISION 30 INTRODUCTION
Oct 30/17 Page I - 1
 Quick Reference Handbook
Owner Information

Name:

Address:

City:

State:

Country:

Postal (ZIP) Code:

Telephone:

E-mail:

Company:

Registration No.:

INTRODUCTION REVISION 30
Page I - 2 Oct 30/17
Quick Reference Handbook

Normal Procedures Index

Preflight
Cockpit Preflight Inspection ..........................................................NA-1
Exterior Preflight Inspection ..........................................................NA-2
Interior Preflight Inspection ...........................................................NA-9
APU Operation
APU Start ......................................................................................NB-1
APU Starting Using External DC Power .......................................NB-2
APU Ground Operation.................................................................NB-4
APU Shutdown .............................................................................NB-4
Engine Starting
Before Starting Engines ............................................................... NC-1
Recommended Elevator Trim Tab Settings For Takeoff ............. NC-5
Before Starting Engines - Thruflight (Reference Only) ................ NC-5
Starting Engines .......................................................................... NC-6
Before Takeoff
After Starting Engines .................................................................. ND-1
Taxi / Before Takeoff ................................................................... ND-3
Taxi Operations With APU Air On ............................................... ND-4
Line Up......................................................................................... ND-5
Inflight
Climb .............................................................................................NE-1
Cruise............................................................................................NE-1
Descent .........................................................................................NE-2
Approach - In Range.....................................................................NE-3
Before Landing .............................................................................NE-3
EGPWS Alerts ..............................................................................NE-4
TCAS II Flight Procedures ............................................................NE-5
All Engines Operating Go Around Procedure ...............................NE-6

REVISION 26 NORMAL PROCEDURES

Oct 5 2011 Page N - i
 Quick Reference Handbook
Normal Procedures Index, ctd…
Inflight, ctd…
Temperature Range For Cowl Anti-Icing ...................................... NE-7
Traffic Pattern ............................................................................... NE-8
After Landing
After Landing ................................................................................ NF-1
Shutdown ...................................................................................... NF-1
Securing ....................................................................................... NF-3
Postflight ....................................................................................... NF-4
Transit Check ............................................................................... NF-4
Flight Fault Summary Check ........................................................ NF-5
Alternate Normal Procedures
Cold Start (Reference Only) ........................................................ NG-2
External Air Start ......................................................................... NG-2
Crossbleed Start .......................................................................... NG-2
Engine Cranking Cycle ................................................................ NG-3
Engine Start - Battery Power Only .............................................. NG-3
Single Engine Taxi....................................................................... NG-5
Battery Charging Using APU or External AC Power ................... NG-6
GIV QFE Operations ................................................................... NG-6
RNP 0.3 RNAV Approach Procedures (RNAV / VNAV)
Approach To A Decision Altitude ............................................. NG-8
High Elevation Airport Operations ............................................... NG-8
Cold Weather Altimeter Setting Procedures ............................. NG-12
Use of The Rudder In Flight ...................................................... NG-13
Thrust Reverser Lockout ........................................................... NG-14
Engine Start - Manual Operation of Start Valve ........................ NG-15
Operational Procedures With Cowl Anti-ice Valve Locked
Open ....................................................................................... NG-21
APU Inflight Operation ............................................................... NG-23
P-RNAV (Precision RNAV) Procedures .................................... NG-24

NORMAL PROCEDURES REVISION 26

Page N - ii Oct 5 2011
Quick Reference Handbook
Normal Procedures Index, ctd…
Supplemental Data
Engine Fuel Grades ..................................................................... NH-1
Hydraulic Fluids ........................................................................... NH-1
Fuel Additives .............................................................................. NH-2
Oil Grades: Engine / Starter / APU .............................................. NH-3
Conversion Tables ....................................................................... NH-4
China RVSM Flight Level Allocation Scheme (FLAS) Table ..... NH-11
Noise Standards ........................................................................ NH-12

Functional Checks
Battery Integrity Check .................................................................. NI-1
Pressurization System Check ........................................................ NI-2
Fuel System Check........................................................................ NI-3
Oxygen Crew Mask / Regulator Preflight Test .............................. NI-4
Cockpit Voice Recorder (CVR) Test .............................................. NI-6
Display Controller Test .................................................................. NI-6
Flight Guidance Panel Test ........................................................... NI-8
Auxiliary Hydraulic Pump / Brake System Check .......................... NI-9
Elevator Trim System Check ....................................................... NI-11
Ground Spoiler System Check .................................................... NI-12
Stall Warning / Stall Barrier System Check ................................. NI-15

REVISION 26 NORMAL PROCEDURES

Oct 5 2011 Page N - iii
 Quick Reference Handbook
Notes

NORMAL PROCEDURES REVISION 26

Page N - iv Oct 5 2011
Quick Reference Handbook
Cockpit Preflight Inspection AFM 2-01-10

WARNING: ENSURE WHEEL WELL AREAS ARE CLEAR OF

PERSONNEL AND/OR DOOR-CONTROL SAFETY PINS ARE
INSTALLED PRIOR TO OPERATION OF THE AUX PUMP.
1. Circuit Breakers – (Pilot / Copilot / Elec. Equip. Area) ........CHECK
2. Standby Attitude Indicator .................................................. CAGED
3. Emergency Power ................................................... ARM / CHECK
4. Standby Engine Instrument and Warning Panel ................... AUTO
5. ESS AC and DC Bus Switches (6) ........................................ AUTO
6. Battery 1 and 2 Switches (Battery Integrity Check: Pg. NI-1) . ON
(22 - 27V)
7. Emergency Power .................................................................... OFF
8. EPMP Power Monitor Switch ....ESS (115V AC / 400 HZ / 22 - 27V)
9. Standby Engine Instrument and Warning Panel .................CHECK
10. Landing Gear Handle ........................................ DOWN / 3 GREEN
11. Pressurization Controls ......... CHECK / OUTFLOW VALVE OPEN
NOTE: Check manual control of outflow valve on first flight of day.
12. Fuel Quantity .......................................................................CHECK
13. Flaps .................... SET (10° RECOMMENDED FOR PREFLIGHT)
14. Parking Brake ............................................................................. ON
15. Brake Accumulator Indicator .............................CHECK / 3000 PSI
NOTE: The correct accumulator precharge pressure (1200 psi) will
increase or decrease 25 psi for each 10°F (5°C) above or below 70° F
(21° C).
16. Brake ECU (Brake-By-Wire) / Skid Control Box (HMAB) ................
........................................................................ CLEAR OF FAULTS
17. Battery 1 and 2 Switches .......................................................... OFF

END

REVISION 27 NORMAL PROCEDURES

Dec 10/12 Page NA - 1
 Quick Reference Handbook
Exterior Preflight Inspection AFM 2-01-20

1. Wheel Well Doors.................................................................. OPEN

WARNING: WITH THE LANDING GEAR DOOR-CONTROL VALVE
SAFETY PINS REMOVED, ANY MANUAL OR AUTOMATIC
ACTIVATION OF THE AUX PUMP MAY CAUSE THE WHEEL WELL
DOORS TO IMMEDIATELY CLOSE. ACTIVATION OF THE
COMBINED HYDRAULIC SYSTEM OR UTILITY PUMP WILL CAUSE
THE WHEEL WELL DOORS TO IMMEDIATELY CLOSE.
WARNING: DO NOT REMOVE NLG DOOR-CONTROL VALVE PIN
FROM INSIDE NOSE WHEEL WELL.
CAUTION: THE DOOR-CONTROL VALVE HANDLE SHOULD NOT
BE ALLOWED TO SNAP BACK UNDER SPRING PRESSURE. THIS
WILL EVENTUALLY AFFECT NORMAL FUNCTIONING OF THE
VALVE.
2. Oxygen Quantity............................... CHECKED / DOOR SECURE
(1800 psi, 1500 psi minimum at 70°F [21°C].)
3. Forward External BATT Switch / Access Door ...... OFF / SECURE
(SN 1156 and subs.)
4. Pitot Covers ...................................................................... REMOVE
5. Radome ............................................................................... CHECK
6. Hydraulic Lines .................................................................... CHECK
7. Nose Gear Uplock ................................................................. OPEN
CAUTION: IF ANY LANDING GEAR UPLOCK IS NOT OPEN, THAT
LANDING GEAR WILL NOT LOCK AFTER RETRACTION.
8.Brake Accumulator Gauge ................. CHECK (1200 PSI PRELOAD)
9. Emergency Air Bottle ...... CHECK (3000 PSI AT 70F (21C) OAT)
10. Nose Gear Ground Lock .................................................. REMOVE
11. Door-Control Valve ..........................................................................
........... FLIGHT POSITION / PIN REMOVED / COVER SECURED
WARNING: WITH THE LANDING GEAR DOOR-CONTROL VALVE
SAFETY PINS REMOVED, ANY MANUAL OR AUTOMATIC
ACTIVATION OF THE AUX PUMP MAY CAUSE THE WHEEL WELL
DOORS TO IMMEDIATELY CLOSE. ACTIVATION OF THE
COMBINED HYDRAULIC SYSTEM OR UTILITY PUMP WILL CAUSE
THE WHEEL WELL DOORS TO IMMEDIATELY CLOSE.
WARNING: DO NOT REMOVE NLG DOOR-CONTROL VALVE PIN
FROM INSIDE NOSE WHEEL WELL.

NORMAL PROCEDURES REVISION 27

Page NA - 2 Dec 10/12
Quick Reference Handbook
CAUTION: THE DOOR-CONTROL VALVE HANDLE SHOULD NOT
BE ALLOWED TO SNAP BACK UNDER SPRING PRESSURE. THIS
WILL EVENTUALLY AFFECT NORMAL FUNCTIONING OF THE
VALVE.
12. Nose Landing Gear (NLG) Wheel Well Area .......................CHECK
13. Cannon Plugs Inside NLG Wheel Well ................................CHECK
Inspect all cannon plugs for condition and security.
14. Nosewheel Strut / Fairing / Electrical Wires ........................CHECK
15. Torque Link .................................................... PINNED / SAFETIED
16. Taxi Lights / Tires ................................................................CHECK
17. TAT Probe ....................................... COVER REMOVED / CHECK
18. Right Angle of Attack Probe ............ COVER REMOVED / CHECK
NOTE: Verify sensing ports are oriented in the direction of flight.
19. Outflow Valve / Safety Valve / Static Ports .......................... CLEAR
20. External DC Power Door .................................. CHECK / SECURE
21. Right Static Ports .............................................................................
....................... COVER REMOVE / CHECK - RVSM NO DAMAGE
22. Antennas ..............................................................................CHECK
23. Right Ice Inspection / Emergency Lights .............................CHECK
24. Right Landing Light ..............................................................CHECK
25. Window Emergency Releases / Windows ........................ SECURE
26. Right Engine Inlet / Cooling Inlets ... COVER REMOVED / CHECK
27. Right Wing Vent ................................................................... CLEAR
28. Pressure Fuel Panel ......................................... CHECK / SECURE
29. Wing Anti-Icing Vent ............................................................ CLEAR
30. Right Sump Drains ........................ CHECK / NOT LEAKING FUEL
31. Anti-Collision Lights .............................................................CHECK
32. Right Pressure Fueling Static Port ...................................... CLEAR
33. Right Wing Leading Edge ....................................................CHECK
34. Right Fuel Tank Vent / Plenum Drain / (VGs: ASC 461) .....CHECK
35. Right Nav Light / Wing Tip ...................................................CHECK
36. Right Winglet .......................................................................CHECK

REVISION 27 NORMAL PROCEDURES

Dec 10/12 Page NA - 3
 Quick Reference Handbook
37. Right Static Wicks ............................................................... CHECK
38. Right Aileron / Flaps / Spoilers / Bungee ............................ CHECK
Check surfaces for damage, security of attach points, condition of
all actuators, aileron bungee free play, plumbing, and cables
forward of the flap. Check condition of flap rollers.

NOTE: To determine if the bungee is normal, move the aileron manually

with one hand and, while holding the bungee with the other hand,
observe if there is any free play in the bungee between the outer cylinder
and the inner cartridge. A normally-operating bungee will not exhibit any
free play when the aileron is moved. Attached to the bungee is what is
referred to as a “slop link” (at the inboard connector to the aileron
actuator) which does have free play per design. Do not confuse that with
free play in the bungee.
39. Right Main Gear Strut / Fairing ........................................... CHECK
40. Right Main Gear Tires / Brakes ........................................... CHECK
NOTE: The PARK/EMER BRAKE must be set to properly check brake
wear indicator reading.
41. Right Tire Flange Retaining Rings (Inboard / Outboard) ..... CHECK
42. Right Main Gear Ground Lock ......................................... REMOVE
43. Right Main Gear Uplock ........................................................ OPEN
CAUTION: IF ANY LANDING GEAR UPLOCK IS NOT OPEN, THAT
LANDING GEAR WILL NOT LOCK AFTER RETRACTION.
44. Right Main Wheel Well Area ............................................... CHECK
45. Cannon Plugs Inside MLG Wheel Well ............................... CHECK
Inspect all cannon plugs for condition and security.
46. Main Fuel Shutoff Valve Position ............................ VERIFY OPEN
NOTE: Verify the main fuel shutoff valve is open by physically checking
that the red valve position indicator is at the “open” mechanical limit
(approximately the seven o’clock position).
47. Fuel Boost Pumps .......................................... CHECK / NO LEAKS
NOTE: Inspect the boost pumps for security and tightness of all
accessible line fittings. Ensure no fuel leakage is present.
48. Right Main Door Control Valve ........................................................
.............................................. FLIGHT POSITION / PIN REMOVED

NORMAL PROCEDURES REVISION 27

Page NA - 4 Dec 10/12
Quick Reference Handbook
WARNING: WITH THE LANDING GEAR DOOR-CONTROL VALVE
SAFETY PINS REMOVED, ANY MANUAL OR AUTOMATIC
ACTIVATION OF THE AUX PUMP MAY CAUSE THE WHEEL WELL
DOORS TO IMMEDIATELY CLOSE. ACTIVATION OF THE
COMBINED HYDRAULIC SYSTEM OR UTILITY PUMP WILL CAUSE
THE WHEEL WELL DOORS TO IMMEDIATELY CLOSE.
CAUTION: THE DOOR-CONTROL VALVE HANDLE SHOULD NOT
BE ALLOWED TO SNAP BACK UNDER SPRING PRESSURE. THIS
WILL EVENTUALLY AFFECT NORMAL FUNCTIONING OF THE VALVE.
49. Service Door ..................................................................... SECURE
50. APU Exhaust ....................................................................... CLEAR
51. Right Engine Fire Extinguisher ............................................CHECK
52. Right Pre-Cooler Exhaust .................................................... CLEAR
53. Right Heat Exchanger Exhaust ........................................... CLEAR
54. Right Engine Cowl / Vents ................................ CHECK / SECURE
55. Right Thrust Reverser ................. CHECK / PROPERLY STOWED
NOTE: If the lower thrust reverser door leading edge is sagged out of
normal contour, report for maintenance action before next flight.
56. Elevator / Rudder / Static Wicks ..........................................CHECK
57. Tail Cone Navigation Light / Static Wick .............................CHECK
58. Horizontal Stabilizer Position ...............................................CHECK
59. Aft Compartment .................................................................CHECK
A. AUX Power Relay Box Circuit Breakers ......................... CHECK
B. Aft Emergency Battery Circuit Breakers ......................... CHECK
C. Converter Failed Fan Indicators ..................................... CHECK
D. APU Fault Indication Box ................................................ CHECK
E. Hydraulic Filter Bypass Indicators (8) ............................. CHECK
F. Thrust Reverser Safety Pins ..................... CHECK / REMOVED
60. APU Fire Extinguisher .........................................................CHECK
61. Aft Compartment Ladder / Door ....................................... SECURE
62. External AC Power Door .................................. CHECK / SECURE
63. Hydraulic Accumulator Pressures .................... CHECK (1000 PSI)

REVISION 27 NORMAL PROCEDURES

Dec 10/12 Page NA - 5
 Quick Reference Handbook
64. Hydraulic Quantities ................ CHECK (DC POWER REQUIRED)
65. Hydraulic Service Door ..................................................... SECURE
66. External Air Door ............................................... CHECK / SECURE
67. Left Hand Exchanger Exhaust ............................................ CLEAR
68. Aft External Batt Switch / Access Door .................. OFF / SECURE
69. Battery Compartment ........................................ CHECK / SECURE
70. Left Engine Fire Extinguisher .............................................. CHECK
71. Left Pre-Cooler Exhaust ...................................................... CLEAR
72. Left Engine Cowl Vents ..................................... CHECK / SECURE
73. Left Thrust Reverser .................... CHECK / PROPERLY STOWED
NOTE: If the lower thrust reverser door leading edge is sagged out of
normal contour, report for maintenance action before next flight.
74. Baggage Door .................................................................. SECURE
75. Service Door ..................................................................... SECURE
76. Left Main Wheel Well Area .................................................. CHECK
77. Cannon Plugs Inside MLG Wheel Well ............................... CHECK
Inspect all cannon plugs for condition and security.
78. Main Fuel Shutoff Valve Position ............................ VERIFY OPEN
NOTE: Verify the main fuel shutoff valve is open by physically checking
that the red valve position indicator is at the “open” mechanical limit
(approximately the seven o’clock position).
79. Fuel Boost Pumps .......................................... CHECK / NO LEAKS
NOTE: Inspect the boost pumps for security and tightness of all
accessible line fittings. Ensure no fuel leakage is present.
80. Left Main Gear Uplock........................................................... OPEN
CAUTION: IF ANY LANDING GEAR UPLOCK IS NOT OPEN, THAT
LANDING GEAR WILL NOT LOCK AFTER RETRACTION.
81. Left Main Gear Ground Lock ............................................ REMOVE
82. Left Main Gear Strut / Fairing .............................................. CHECK
83. Left Main Gear Tires / Brakes ............................................. CHECK
NOTE: The PARK/EMER BRAKE must be set to properly check brake
wear indicator reading.
84. Left Tire Flange Retaining Rings (INBD / OTBD) ............... CHECK

NORMAL PROCEDURES REVISION 27

Page NA - 6 Dec 10/12
Quick Reference Handbook
85. Left Main Door Control Valve ..........................................................
.............................................. FLIGHT POSITION / PIN REMOVED
WARNING: WITH THE LANDING GEAR DOOR CONTROL VALVE
SAFETY PINS REMOVED, ANY MANUAL OR AUTOMATIC
ACTIVATION OF THE AUX PUMP MAY CAUSE THE WHEEL WELL
DOORS TO IMMEDIATELY CLOSE. ACTIVATION OF THE
COMBINED HYDRAULIC SYSTEM OR UTILITY PUMP WILL CAUSE
THE WHEEL WELL DOORS TO IMMEDIATELY CLOSE.
CAUTION: THE DOOR-CONTROL VALVE HANDLE SHOULD NOT
BE ALLOWED TO SNAP BACK UNDER SPRING PRESSURE. THIS
WILL EVENTUALLY AFFECT NORMAL FUNCTIONING OF THE VALVE.
86. Left Flaps / Spoilers / Aileron / Bungee ...............................CHECK
Check surfaces for damage, security of attach points, condition of
all actuators, aileron bungee free play, plumbing, and cables
forward of the flap. Check condition of flap rollers.
NOTE: To determine if the bungee is normal, move the aileron
manually with one hand and, while holding the bungee with the
other hand, observe if there is any free play in the bungee between
the outer cylinder and the inner cartridge. A normally-operating
bungee will not exhibit any free play when the aileron is moved.
Attached to the bungee is what is referred to as a “slop link” (at the
inboard connector to the aileron actuator) which does have free
play per design. Do not confuse that with free-play in the bungee.
87. Left Static Wicks ..................................................................CHECK
88. Left Winglet ..........................................................................CHECK
89. Left Navigation Light / Wing Tip...........................................CHECK
90. Left Fuel Tank Vent / Plenum Drain / (VGs: ASC 461) .......CHECK
91. Left Wing Leading Edge ......................................................CHECK
92. Left Pressure Fueling Static Port ......................................... CLEAR
93. Left Wing Vent ..................................................................... CLEAR
94. Left Sump Drains ........................... CHECK / NOT LEAKING FUEL
95. Window Emergency Release / Windows .......................... SECURE
96. Left Engine Inlet/Cooling Inlets ........ COVER REMOVED / CHECK
97. Left Landing Light ................................................................CHECK
98. Left Ice Inspection / Emergency Lights ...............................CHECK

REVISION 27 NORMAL PROCEDURES

Dec 10/12 Page NA - 7
 Quick Reference Handbook
99. Left Static Ports ...............................................................................
....................... COVER REMOVE / CHECK - RVSM NO DAMAGE
100.Air Stair Door Seal
CHECK
101. Standby Pitot Probes ........................COVER REMOVED / CHECK
102. Left Angle of Attack Probe................COVER REMOVED / CHECK
NOTE: Verify sensing ports are oriented in the direction of flight.
103. Door Pins / Gear Pins / Pitot Covers ................................STOWED
104. Landing Gear Doors ..........................................................CLOSED

END

NORMAL PROCEDURES REVISION 27

Page NA - 8 Dec 10/12
Quick Reference Handbook
Interior Preflight Inspection AFM 2-01-30

1. Baggage Compartment Door ........................... CHECK / SECURE

2. Baggage Door Seal Control Valve Selector ........... NORMAL OPS
(SN 1156 and subs. and SN 1000 thru 1155 with ASC 157.)
3. Windows ........................................................................... SECURE
4. Fuel Tank Caps ................................................................ SECURE
5. SPZ-8000/8400 Shutoff Switch (RH Radio Rack) .................... OFF
(SN 1156 and subs. and SN 1000 thru 1155 with ASC 92.)
6. Wing Vortex Generators ......................................................CHECK
7. Cabin Area ........................................................................ SECURE
8. System Monitor / Test Panel ...............................................CHECK
9. Passenger Briefing ........................................................ CONDUCT
A. Interior Doors Open for Takeoff and Landing
B. Use of Seat Belts / Shoulder Harness
C. Seat Table Position for Taxi, Takeoff, Landing and Turbulence
Encounters
D. Location and Operation of Normal and Emergency Exits
E. Location and Operation of Survival Equipment
F. Use of Oxygen and PELS Smoke Hoods (if installed)
G. Smoking Policy
H. Storage of Loose Articles
I. Use of Portable Electronic Devices
J. Time Enroute and Any Known Delays
K. Enroute and Destination Weather

END

REVISION 27 NORMAL PROCEDURES

Dec 10/12 Page NA - 9
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NORMAL PROCEDURES REVISION 27

Page NA - 10 Dec 10/12
Quick Reference Handbook
APU Start AFM 2-02-10

1. HP Fuel Cocks....................................................................... SHUT

2. Circuit Breakers ...................................................................CHECK
3. Standby Attitude Indicator .................................................. CAGED
4. EPMP Bus Switches (6) ........................................................ AUTO
5. Battery 1 and 2 Switches .................................... ON (22V DC MIN)
6. Exterior Lights ......................................................... AS REQUIRED
7. Electric Master Auxiliary Power ................................................ OFF
8. APU Fire Warning................................................................CHECK
9. APU Air ..................................................................................... OFF
10. APU Master Switch ..................................................................... ON
11. APU Oil Pressure Low Light ............................ ON (10 SECONDS)
For SN 1156 and subs, check the following on first start of day:
A. APU Overspeed Test Switch .......................................... PRESS
B. Overhead Panel Indications ........................................... CHECK
1) APU RPM Indicator ................ MOMENTARILY INCREASES
2) Overspeed LED .................. MOMENTARILY ILLUMINATES
NOTE: The overspeed LED will not illuminate and RPM will not
momentarily increase in airplanes with ASC 465 or SN 1310 and
subs.
3) APU Oil Pressure Low Light ....................... EXTINGUISHED
C. APU Master Switch .............................................................. OFF
D. APU Master Switch ................................................................ ON
E. APU Oil Pressure Low Light ........................ON (10 SECONDS)
NOTE: For airplanes having ASC 465, the APU Electronic Control Unit
(ECU) performs a 12 second Built-In-Test (BIT) after the APU Low Oil
Pressure light illuminates. Expect a delay in starter activation if the APU
Start switch is activated during the APU ECU BIT.
12. Left Main Fuel Boost Pump .......................... ON / MESSAGE OUT
13. APU Start Switch ................................................................. PRESS
14. APU Start Light .............................................. OUT (BEFORE 60%)

REVISION 27 NORMAL PROCEDURES

Dec 10/12 Page NB - 1
 Quick Reference Handbook
15. APU Oil Pressure Low Light ................. OUT (BEFORE 95% RPM)
16. RPM................................................................................ 100% 3%
17. EGT ....................................................... 988C MAXIMUM (0-60%)
821-732C: 60-100% DURING START (LINEAR DECREASE)
732C: MAXIMUM (RUNNING)
For airplanes having ASC 465 (36-150[G] APU):
17. EGT ....................................................... 973C MAXIMUM (0-50%)
973-732C: 51-87% DURING START (LINEAR DECREASE)
732C: 87-100%
732C MAXIMUM (RUNNING)
CAUTION: IF APU FAILS TO COME UP TO SPEED OR START-
SWITCHLIGHT REMAINS ILLUMINATED, DEPRESS OVERSPEED
TEST-SWITCH. IF APU START-SWITCHLIGHT STILL REMAINS
ILLUMINATED, PLACE APU MASTER SWITCH AND BATTERY
SWITCHES 1 AND 2 OFF.
NOTE: For airplanes having ASC 465 (36-150[G] APU), it is acceptable
for the APU EGT synoptic indication to go into the amber or red range
during start. The synoptic indication only reflects running limitations.

END

APU Starting Using External DC Power AFM 2-02-40

CAUTION: ENSURE AC EXTERNAL POWER IS DISCONNECTED.

1. Battery 1 and 2 Switches ......................................................... OFF
2. TRU Circuit Breaker (UNDER “AC RIGHT” ON PDB) ........... PULL
3. DC External Power .........................................................CONNECT
4. Electric Master Auxiliary Power .................................................. ON
5. Battery Voltage ...........................................CHECK (Above 4 volts)
CAUTION: FOR AIRPLANES WITHOUT ASC 54, THE
BATTERIES MUST BE DEEP-CYCLED PRIOR TO FLIGHT IF
BATTERY VOLTAGE IS BELOW 4 VOLTS. IF BATTERY
VOLTAGE IS BETWEEN 4 AND 20 VOLTS PRIOR TO APU
START, THE BATTERIES MUST BE DEEP-CYCLED AT NEXT
AVAILABLE MAINTENANCE FACILITY.

NORMAL PROCEDURES REVISION 27

Page NB - 2 Dec 10/12
Quick Reference Handbook
CAUTION: FOR AIRPLANES WITH ASC 54 AND BATTERY
VOLTAGE BELOW 4 VOLTS, THE BATTERIES MUST BE
DEEP-CYCLED AT NEXT AVAILABLE MAINTENANCE
FACILITY, AFTER USING THIS PROCEDURE.
6. External DC ON Indicator Light .................................................. ON
7. Battery Charger Circuit Breakers 1 and 2 ........................ CLOSED
8. HP Fuel Cocks ....................................................................... SHUT
9. APU Fire Warning ................................................................CHECK
10. APU Air ..................................................................................... OFF
11. APU Master Switch ..................................................................... ON
12. APU Oil Pressure Low Light ........................ ON (ten (10) seconds)
13. Left Main Fuel Boost Pump ........................................................ ON
14. APU Start Button .......................................... PRESS (momentarily)
15. APU Oil Pressure Low Light ......................OUT (before 95% RPM)
16. RPM ...............................................................................100%  3%
17. EGT ....................................................... 988C MAXIMUM (0-60%)
821C -732C: 60-100% DURING START (LINEAR DECREASE)
732C: MAXIMUM (RUNNING)
For airplanes having ASC 465 (36-150[G] APU):
EGT ....................................................... 973C MAXIMUM (0-50%)
973C - 732C: 51-87% DURING START (LINEAR DECREASE)
732C: 87% to 100%
732C: MAXIMUM (RUNNING)
CAUTION: IF APU FAILS TO COME UP TO SPEED OR
START-SWITCH LIGHT REMAINS ILLUMINATED, DEPRESS
OVERSPEED TEST-SWITCH. IF APU START-SWITCH LIGHT
STILL REMAINS ILLUMINATED, PLACE APU MASTER SWITCH
AND BATTERY SWITCHES 1 AND 2 IN “OFF” POSITION.
18. Battery 1 and 2 Switches ............................................................ ON
When battery voltage is above 17 volts:
19. TRU Circuit Breaker ( “AC RIGHT” Section Of PDB) .......... CLOSE

REVISION 25 NORMAL PROCEDURES

Jul 14/10 Page NB - 3
 Quick Reference Handbook
20. Battery Volts / Ammeters................................................ MONITOR
CAUTION: DELAY TAKEOFF UNTIL BATTERY CHARGERS
COMPLETE CHARGE-CYCLES.
NOTE: For airplanes with ASC 54 - If charge current is not indicated for
Battery 1 or 2, turn appropriate battery switch OFF and momentarily turn
the battery override switch on.
NOTE: An undamaged, discharged battery will completely recharge
within approximately seventy-five (75) minutes.
21. Appropriate Battery Switch ......................................................... ON
22. Battery Volts / Ammeter ................................................. MONITOR
23. APU AIR ..................................................................AS REQUIRED
24. DC External Power ...................................................DISCONNECT

END

APU Ground Operation AFM 2-02-20

1. Electric Master Auxiliary Power .................................. ON / CHECK

2. Battery Charger FAIL Lights ..................................................... OUT
3. Battery Amps ................................................................ CHARGING
NOTE: If no charge is indicated on battery immediately after start,
battery charger failure may be indicated.
4. L / R ECS Pack Switches ........................................................... ON
5. APU Air .................................................. ON / CHECK PRESSURE
NOTE: Wait two (2) minute for EGT to stabilize before selecting APU
AIR ON. After six (6) seconds, verify isolation valve is OPEN. Maximum
APU EGT with APU AIR ON is 680 C.

END

APU Shutdown AFM 2-02-30

1. Electrical Master Auxiliary Power ............................................. OFF

2. APU Overspeed Test Button ...........................................................
.......PRESS (MOMENTARILY) NOTE OVERSPEED INDICATION

NORMAL PROCEDURES REVISION 25

Page NB - 4 Jul 14/10
Quick Reference Handbook
3. APU AIR ................................................................................... OFF
NOTE: APU AIR switch position should not be changed just prior to
shutdown. After shutdown, wait until RPM indicates less than 95% before
changing APU AIR switch position.
4. APU MASTER ................................. OFF (RPM LESS THAN 10%)
CAUTION: (FOR AIRPLANES NOT HAVING ASC 465 (36-150[G]
APU)): CYCLING APU MASTER SWITCH DURING SHUTDOWN
WHILE RPM REMAINS ABOVE 10 PERCENT WILL CAUSE
PREMATURE ECU RESET AND LOW ENERGY RESTART
RESULTING IN HIGH EGT INDICATION AND TORCHING FROM APU
TAILPIPE.
NOTE: (For airplanes having ASC 465 (36-150[G] APU)): The amber
APU MASTER WARN CAS message will not be displayed if the APU
MASTER switch is inadvertently left ON after shutdown.
5. Fuel Boost Pumps ........................................ OFF / AS REQUIRED

END

REVISION 25 NORMAL PROCEDURES

Jul 14/10 Page NB - 5
 Quick Reference Handbook
Notes

NORMAL PROCEDURES REVISION 25

Page NB - 6 Jul 14/10
Quick Reference Handbook
Before Starting Engines AFM 2-03-20

= Thruflight Items
1. Preflight Checklists ...................................................... COMPLETE
2. Circuit Breakers ...................................................................CHECK
3. EPMP BUS Switches (6) ....................................................... AUTO
4. ELECTRIC MASTER LEFT PWR / RIGHT PWR Switches ..... OFF
5. BATT 1 / BATT 2 Switches ......................................................... ON
6. Essential AC / DC Bus VOLTS ........................................................
...................................... CHECK 115 V AC / 400 HZ / 22 - 27 VDC
7. STANDBY ELECTRICAL POWER System.............................. OFF
8. HP Fuel Cocks....................................................................... SHUT
9. ELECTRICAL AUX POWER / AIR ............................................. ON
See APU Ground Operation checklist, page NB-4.
10. EMERGENCY POWER ............................................................ OFF
11. DISPLAY Switches (3) ................................................................ ON
12. CABIN / GALLEY / RADIO MASTER Switches .......................... ON
13. Display Controllers (2) ................................................................ ON
(SN 1156 and subs. and SN 1000 thru 1155 with ASC 92.)
14. IRSs .......................................................................................... NAV
15. FMSs ............................................................................. INITIALIZE
16. DISPLAY SWITCHING / SYMBOL GENERATOR CONTROL .........
................................................................................................... NORM
NOTE: Check first flight of month.
17. ENGINE BLEED AIR / TEMP CONTROL .... OFF / AS REQUIRED
NOTE: Selecting ENGINE BLEED AIR switches OFF will help extend
life of the bleed air valves by de-energizing the solenoids.
18. PRESSURIZATION CONTROL (Pressurization System Check:
Pg. NI-2 ......................................................................... CHECK / SET
19. OUTFLOW VALVE ................................................................ OPEN
20. ANTI-ICE Switches (4) ............................................................. OFF
21. FUEL SYSTEM (Fuel System Check: Pg. NI-3) ................CHECK
22. REMOTE FUEL SHUTOFFS (2) ........................................... OPEN

REVISION 27 NORMAL PROCEDURES

Dec 10/12 Page NC - 1
 Quick Reference Handbook
23. ENGINE SYNC ......................................................................... OFF
24. Engine Temperature Control ...................................................... ON
NOTE: Airplanes SN 1320 and subs and SN 1000 through 1319 with
ASC 394 have the engine temperature controls removed.
25. EVM ........................ (WITH ENGINES SHUT DOWN ONLY) TEST
26. ENGINE START Switches (2) .................................................. OFF
27. EXTERIOR LIGHTS ................................................AS REQUIRED
28. ENGINE FIRE TEST / FAULT TEST ...........................COMPLETE
29. Windshield Wipers.................................................................... OFF
30. ANTI ICE HTR Switches .........................................AS REQUIRED
31. UTILITY PUMP ................................................................... ARMED
32. AUX PUMP / Brake System (Auxiliary Hydraulic Pump / Brake
System Check: Pg. NI-9) .............................................. CHECKED
Side Panels:
33. Radar Controls ........................................................AS REQUIRED
34. ICS Panels ..............................................................AS REQUIRED
35. Oxygen Systems ........................................................ ON / CHECK
36. Oxygen Masks (Oxygen Crew Mask / Regulator Preflight Test:
Pg. NI-4) ................................................................................. TEST
37. COCKPIT LIGHTS ..................................................AS REQUIRED
38. Warning Lights .................................................................... CHECK
39. RH Radio Rack Fan .............................................................. AUTO
40. Inertial System Display Unit (ISDU) .................................... CHECK
41. Tone Generator ...................................................................... TEST
NOTE: For SPZ-8400 equipped airplanes, the tone generator test is
performed using the pilot’s display controller TEST menu. Selecting TONE
results in the test tone: a Klaxon (hi-lo-hi-lo) landing gear unsafe tone. In
test mode, the pilot can adjust tone generator volume. Test is completed by
selecting the RETURN prompt to return to the TEST main menu.
42. Landing Gear Emergency Reset ............................. IN / SAFETIED
43. EMER LDG GEAR Handle ...................................... IN / SAFETIED
44. Cockpit Voice Recorder (Cockpit Voice Recorder (CVR) Test:
Pg. NI-6) .............................................................................. CHECK
45. Flight Data Recorder ................................................................ SET
46. Non-Essential Static Control (if installed) .................ON / NORMAL

NORMAL PROCEDURES REVISION 27

Page NC - 2 Dec 10/12
Quick Reference Handbook
47. EMER FLAP Handle ....................................................... NEUTRAL
48. EMERG FLAP Switch ..................................NORMAL / GUARDED
49. Smoke Detector ...................................................................... TEST
50. RH RR FAN AUTO Indicator (SN 1156 and subs) ................ AUTO
Instrument Panel:
51. Clocks ..................................................................................CHECK
52. Display Controllers (Display Controller Test: Pg. NI-6) ....CHECK
53. EFIS ........................................................................................ TEST
54. EICAS ..................................................................................... TEST
55. IRSs ............................................................................. NAV / TEST
56. ELWS Loadmeter (if installed) ...................................... TEST / OFF
57. Standby Engine Instruments ................................................. AUTO
NOTE: Compare static indications with EICAS on first flight of day.
58. Altimeters (s)...........................................SET / CROSS CHECKED
NOTE: In order to conduct operations in RVSM airspace, the pilot and
copilot altimeters must agree within seventy-five (75) feet of known field
elevation and must also agree within seventy-five (75) feet of each other.
59. Flight Guidance Panel (Flight Guidance Panel Test:
Pg. NI-8) ..............................................................................CHECK
60. Thrust Reverser Lights ........................................................CHECK
A. REV ARM .............................................................................. ON
B. REV UNLOCK / DEPLOY .................................................... OUT
NOTE: If either or both UNLOCK or DEPLOY lights are ON,
maintenance is required before flight.
61. Standby Attitude Indicator ............................................. UNCAGED
62. Standby Warning Lights Panel (SPZ-8000 Only) ...... AS DESIRED
63. Fuel Quantity (Normal and Standby) ...................................... TEST
64. DBDIs ..................................................................................... TEST
NOTE: The DBDI will return to standby after TEST unless the
corresponding IRS is in NAV.
65. Cabin Pressurization Controller ................................................ SET
66. Flap Indicator .......................................................................CHECK

REVISION 27 NORMAL PROCEDURES

Dec 10/12 Page NC - 3
 Quick Reference Handbook
67. Landing Gear Handle ........................................ DOWN / 3 GREEN
Center Pedestal:
68. FIRE Handles ............................................................................... IN
69. Power Levers .......................................................................... IDLE
70. GUST LOCK Handle ...............................................AS REQUIRED
71. GND SPLR FLAP ORIDE Switch ............................................. OFF
72. SPEED BRAKE Handle.................................................. RETRACT
73. Elevator Trim (Elevator Trim System Check: Pg. NI-11) .............
................................................................................... CHECK / SET
See next page for recommended elevator trim tab settings.
74. STALL BARRIER Switch ............................................................ ON
75. ANTI SKID Switch ...................................................................... ON
76. GND SPLR Switch ................................................................... OFF
77. T/REV EMER STOW Switch .................................................... OFF
78. NUTCRKR SW TEST Switch ................................. GUARD DOWN
CAUTION: DO NOT DEPRESS THE NUTCRKR SW TEST-SWITCH
WHILE THE AIRPLANE IS ON THE GROUND. DEPRESSING THE
TEST SWITCH SIMULATES THE IN-FLIGHT CONDITION, WHICH
AFFECTS MANY AIRPLANE SYSTEMS, INCLUDING MOMENTARILY
UNLOCKING THE LANDING GEAR HANDLE DOWNLOCK SOLENOID.
79. PARK/EMERG BRAKE Handle .................................................. ON
80. Brake Accumulator Pressure.............................................3000 PSI
81. FLIGHT POWER SHUT OFF Handle .................................. DOWN
82. Radios ...................................................................................... SET
83. TCAS / TCAS MODE / SET UP ................ TEST / TA-RA / ABOVE
84. EGPWS .................................................................................. TEST
85. BTMS / Selector Switch (If Installed) ............................. TEST / ALL
NOTE: SPZ-8000 equipped airplanes SN 1156 and subs and SN 1000
through 1155 having ASC 167. For SPZ-8400 equipped airplanes, BTMS
is incorporated in the BRAKES System page. No test is required and no
selection is available.
86. Rudder and Aileron Trim ..................................................... CHECK
87. EPR / V Speeds / AOA / Radio Altimeter ................................. SET

END

NORMAL PROCEDURES REVISION 27

Page NC - 4 Dec 10/12
Quick Reference Handbook
Recommended Elevator Trim Tab Settings For Takeoff

Fuel
Loading Elevator Trim Tab Position Units
(Lb)
29,000 11 10 9 8 7 6 5 4 3 2
28,000 11 10 9 8 7 6 5 4 3 2
27,000 11 10 9 8 7 7 6 5 4 3
26,000 12 11 10 9 8 7 6 5 4 3
25,000 12 11 10 9 8 7 6 5 4 3
24,000 12 11 10 9 8 7 6 5 4 3
23,000 12 11 10 9 8 7 6 5 4 3
22,000 12 11 10 9 8 7 6 5 4 3
21,000 12 11 10 9 8 7 6 5 4 3
20,000 12 11 10 9 8 7 6 5 4 3
19,000 12 11 10 9 8 7 6 5 4 3
18,000 12 11 10 9 8 7 6 5 4 3
17,000 12 11 10 9 8 7 6 5 3 3
16,000 12 11 10 9 8 7 6 4 3 2
15,000 12 11 10 9 8 6 5 4 3 2
14,000 12 11 10 8 7 6 5 4 3 1
13,000 12 10 9 8 7 6 5 4 2 1
12,000 11 10 9 8 7 5 4 3 2 1
11,000 11 10 9 7 6 5 4 3 1 0
10,000 11 9 8 7 6 5 3 2 1 -1
9,000 10 9 8 6 5 4 3 1 0 -2
8,000 10 8 7 6 5 3 2 1 -1 -3
7,000 9 8 7 5 4 3 1 0 -2 -4
6,000 9 7 6 5 3 2 0 -1 -2 -5
5,000 8 6 5 4 3 1 0 -2 -3 -5
4,000 7 6 5 3 2 0 -1 -3 -4 -6
3,000 7 5 4 2 1 -1 -2 -4 -5 -7
2,000 6 4 3 1 0 -2 -3 -5 -6 -8
1,000 5 3 2 0 -1 -3 -4 -6 -7 -8
36 37 38 39 40 41 42 43 44 45
Zero Fuel Center of Gravity - % MAC

NOTE: A minus sign (-) indicates nose down trim.

Before Starting Engines: Thruflight AFM 2-03-20

Perform boxed items of Before Starting Engines checklist (page NC-1).

END

REVISION 28 NORMAL PROCEDURES

May 25/16 Page NC - 5
 Quick Reference Handbook
Starting Engines AFM 2-03-20

1. Start Page ......................................................................... SELECT

NOTE: When oil temperature is -10 C or less, refer to GIV Operating
Manual 07-01-20: Cold Weather Operations.
2. HP Fuel Cocks .......................................................................SHUT
3. Power Levers .......................................................................... IDLE
4. GUST LOCK............................................................................. OFF
5. Beacon Switch............................................................................ ON
6. APU Air / External Air ............. ON / PRESSURE 25 PSI MINIMUM
NOTE: Normal air pressure from the APU can vary from 25 to 50 psi.
APU air pressure drops during the starting cycle but should not fall below
approximately 20 psi.
7. Fuel Boost Pumps (One Each Side) ............ ON / MESSAGE OUT
8. Electrical Power............................................... CHECK (35% MAX)
NOTE: If using APU, limit APU alternator load (AC AUX PWR) to 35%
during main engine starts. At high elevation airports and/or in high
ambient temperature conditions, limit AUX AC load to 30%.
9. Engine Start Master ................................................................... ON
10. Engine Start Switch ............................................................. PRESS
CAUTION: CONTINUED USE OF THE STARTER IS LIMITED TO
THREE (3) CRANK-CYCLES, WITH A MAXIMUM OF THIRTY (30)
SECONDS PER CYCLE. DELAY THREE (3) MINUTES BETWEEN
START ATTEMPTS. AFTER THREE (3) CYCLES, DELAY USE OF
STARTER FOR AT LEAST FIFTEEN (15) MINUTES.
11. Start Valve and Ignition .............................................................. ON
CAUTION: IF THE SVO INDICATION DOES NOT ILLUMUNATE
DURING START, DISCONTINUE START AND SEEK MAINTENANCE
PRIOR TO DISPATCH. SEE Start Valve Failure, PAGE EC-21.
NOTE: If IGN mnemonic is not displayed on EICAS, the start may be
salvaged by selecting AIR START IGN to ON prior to opening HP fuel
cock.
12. Positive LP RPM ................................................................. CHECK
13. HP Fuel Cock ...................................... OPEN (15% HP MINIMUM)
NOTE: In high tailwind conditions, direction of rotation of LP may initially
be reversed and, if so, the HP fuel cock should not be selected to OPEN
until HP is stabilized. This ensures that LP rotation is positive. Starts with
tailwinds of up to 25 knots have been demonstrated.

NORMAL PROCEDURES REVISION 28

Page NC - 6 May 25/16
Quick Reference Handbook
NOTE: Ignition should occur within ten (10) seconds after selecting HP
fuel cock to OPEN. HP RPM should increase to idling speed 40 seconds
or less on an International Standard Atmosphere (ISA) day or 60
seconds or less on a minus forty degrees (-40°) day.
14. Start Valve and Ignition ............................................................ OFF
NOTE: Start valve should close by 44.5% HP RPM. On SPZ-8000
equipped airplanes, the SVO mnemonic changes from blue to amber
above 42% (44.5% on SPZ-8400 equipped airplanes) and starts flashing.
Check at ground idle HP RPM, and if not closed (SVO still illuminated),
execute Start Valve Failure checklist, page EC-21.

15. TGT.......................................................... MONITOR (700 C MAX)

NOTE: During starting, TGT should not exceed 700 °C. If there is any
evidence of rapid rising TGT and it is anticipated that 700 °C will be
exceeded, select HP fuel cock to SHUT immediately. If TGT has not
exceeded 700°C, a second start may be attempted. If, under normal
starting conditions, TGT exceeds 650°C, this will indicate a fault in the
engine or starting systems. TGT may exceed 650 °C when ambient
conditions cause high density altitudes.
NOTE: Hot Start checklist, if needed, is on page EC-23.
16. Engine RPM.................................. CHECK (46.6% HP MINIMUM)
17. Oil Pressure and Temperature ............................................CHECK
18. EVM .....................................................................................CHECK
NOTE: The EVM system is designed to monitor engine vibrations at idle
and above. During start, the EVM system may occasionally display
momentary EVM values above the ALERT level (0.60) which in turn
causes EVM digits to an amber display momentarily on CAS (SPZ-8400
equipped airplanes). This normally occurs on the first start of the day.
19. SNGL RUDDER LIMIT Message (right engine only running) .... ON
20. Hydraulic Pressure ........................ CHECKED (0 / 3000 / 3000 / 0)
21. FLIGHT REC FAIL Message ..................................... CHECK OUT
22. Second Engine Start ........................ REPEAT STEPS 10 THRU 18
23. SNGL RUDDER LIMIT Message (both engines running) ........OUT
24. Hydraulic Pressure ........................ CHECKED (3000 / 3000 / 0 / 0)

END

REVISION 28 NORMAL PROCEDURES

May 25/16 Page NC - 7
 Quick Reference Handbook
Notes

NORMAL PROCEDURES REVISION 28

Page NC - 8 May 25/16
Quick Reference Handbook
After Starting Engines AFM 2-04-10

1. START MASTER ...................................................................... OFF

2. ELECTRIC MASTER LEFT / RIGHT PWR Switches ................. ON
3. External Electrical Power / Air ............... OFF / CARTS REMOVED
4. Auxiliary Electrical Power / Air / Engine Bleed Air ..... AS DESIRED
NOTE: Only one source of bleed air, either APU or engines, should be
selected after engines are started. This is to prevent thermal transients
on the APU or possible damage to the APU when the power levers are
moved from idle. With engines as source of bleed air, ensure the
isolation valve is CLOSED.
5. Battery Ammeters ................................................................CHECK
6. ESS DC Bus Power Source ... AUTO / LEFT MAIN ILLUMINATED
CAUTION: DO NOT DISPATCH WITH ESS DC BUS POWERED BY
THE BATTERIES.
7. Emergency Power .............................................................. ARMED
8. Doors ................................................................................... CLOSE
NOTE: Check that the orange dot position-indicator on each of the six
locking-pins is visible.
9. Anti-Ice Heat Switches ............................................................... ON
SN 1096 and subs. (5); SN 1000 through 1095 (4).
10. Cowl / Wing Anti-Ice Switches .................CHECK / AS REQUIRED
NOTE: To prevent excessive APU EGT, check or select cowl anti-ice /
wing anti-ice ON using engine bleed air only.
A. L/R Cowl and Wing Anti-Ice ................................................... ON
B. COWL A/I ON Message / WING A/I Message ........DISPLAYED
C. Cowl Anti-Ice Pressure (Overhead Panel) ...................................
................................................ VERIFY GREATER THAN ZERO
D. L/R Cowl and Wing Anti-Ice ................................................. OFF
E. COWL A/I ON Message / WING A/I Message .................... OFF
F. Cowl Anti-Ice Pressure (Overhead Panel) ............VERIFY ZERO
11. Pressurization Control ................................. AUTO / FLIGHT / SET
12. Fuel Boost Pumps / Crossflow Valve ....................... ON / CLOSED
13. Nose Wheel Steering ................................................................ OFF

REVISION 27 NORMAL PROCEDURES

Dec 10/12 Page ND - 1
 Quick Reference Handbook
14. Ground Spoilers (Ground Spoiler System Check: Pg. NI-12)
............................................................................................. CHECK
NOTE: Check on first flight of the day.
15. Stall Barrier (Stall Warning / Stall Barrier System Check:
Pg. NI-15) ............................................................................... TEST
NOTE: Check on first flight of the day. If flight time for the day exceeds
eight (8) hours, a second stall barrier check is required prior to the
second flight of the day.
16. Flight Controls / Bungee / Rudder Torque Limiter .............. CHECK
Check flight controls for freedom and correct movement over full
range of motion while observing Marshaller.
NOTE: While performing the elevator check, pull the yoke aft and then
release. The yoke should slowly fall forward until the elevator surface
reaches its stop. A failed bungee has shown that when the yoke reaches
the forward stop, there is a slight hesitation and the yoke cycles
approximately one inch aft then forward. For a normal bungee, there
should not be any hesitation or aft movement after the yoke is released.
Any windy conditions may invalidate the yoke cycling test.
17. Yaw Damper ............................................................................... ON
18. Nose Wheel Steering ................................................................. ON
19. Pedal Steering Disconnect Switch .................... ON / LIGHTS OUT
20. Auxiliary Hydraulic Pump ................................................... ARMED
21. Brake Test Switch (BITE) / Anti-Skid Test Switch ...........................
................................................................PRESS, THEN RELEASE

END

NORMAL PROCEDURES REVISION 27

Page ND - 2 Dec 10/12
Quick Reference Handbook
Taxi / Before Takeoff AFM 2-04-20

1. Transponder ........................................................... AS REQUIRED

2. Exterior Lights ......................................................... AS REQUIRED
NOTE: Limit ground operation of landing lights to five (5) minutes.
3. Cowl / Wing Anti-Ice ............................................... AS REQUIRED
NOTE: Select cowl / wing anti-ice ON using engine bleed air only.
4. Brakes..................................................................................CHECK
5. Slip Indicators / Compasses / Flight Instruments ...............CHECK
NOTE: For SPZ-8400 equipped airplanes, the external slip indicator is
removed from the PFD and replaced by an electronic slip indication just
below the roll pointer on each PFD ADI.
NOTE: If flight instruments are inoperative, check the AOA indicator. If a
high angle-of-attack is indicated, briefly pressing the respective AOA
TEST button will slew the AOA probe to a lower angle-of-attack, returning
flight instruments to normal operation.
NOTE: If taxi operations are conducted with engine bleed air as source
for ECS pack during warm weather operations, it is recommended that
one throttle be advanced above idle with the isolation valve OPEN and
opposite engine bleed air OFF to provide cooling air flow to the cabin.
6. Thrust Reversers Operational Check (1st Flight of Day) ... COMPLETE
7. Thrust Reverser Lights .......................... CHECK (EVERY FLIGHT)
A. REV ARM ............................................................................. ON
B. REV UNLOCK / REV DEPLOY .......................................... OUT
NOTE: If either or both UNLOCK or DEPLOY lights are ON,
maintenance is required before flight.
8. Fuel Temperature ................................................................CHECK
9. Crew Briefing / EPR / V Speeds .......................................BRIEFED
10. Trim Settings (3) ....................................................................... SET
11. BTMS OVHT / BRAKE OVHT Message (if installed) .....................
.................................................................................. CHECK / OUT
NOTE: SPZ-8000 equipped airplanes SN 1156 and subs and SN 1000
through 1155 having ASC 167. For SPZ-8400 equipped airplanes, BTMS
display is incorporated in the BRAKES system page.
12. Flaps / Stabilizer ..................................................... SET TAKEOFF
13. Engine Instruments ..............................................................CHECK

REVISION 27 NORMAL PROCEDURES

Dec 10/12 Page ND - 3
 Quick Reference Handbook
14. Hydraulic Pressures (COMB / FLT / UTIL / AUX) ...........................
....................................................... CHECKED (3000 / 3000 / 0 / 0)
15. APU ............................................................................AS DESIRED
16. Flight Guidance Panel .............................................................. SET
17. Warn Inhibit ................................................................................ ON

END

Taxi Operations With APU Air On AFM 2-08-70

To achieve better cabin cooling during ground operation, it is recom-

mended that APU be used as the air source for the air conditioning
system.
To preclude APU temperature transients and cabin pressurization
surges, the following procedures are recommended.
Before Taxi:
1. APU Air Switch ........................................................................... ON
2. Engine Bleed Air Switches ....................................................... OFF
3. Taxi Operations .......................................................AS REQUIRED
Before Takeoff:
1. Engine Bleed Air Switches ......................................................... ON
2. APU Air Switch ......................................................................... OFF
3. APU .........................................................................AS REQUIRED

END

NORMAL PROCEDURES REVISION 27

Page ND - 4 Dec 10/12
Quick Reference Handbook
Line Up AFM 2-04-30

CAUTION: DO NOT ATTEMPT TAKEOFF WITH THE PARKING BRAKE

ON (PARKING BRAKE HANDLE NOT FULLY STOWED). TAKEOFF WITH
PARKING BRAKE PRESSURE APPLIED COULD RESULT IN TIRE
FAILURE AND OR OVERHEATED BRAKES.
1. Parking Brake ............................ OFF (HANDLE FULLY STOWED)
NOTE: In addition to the parking brake handle position, on SPZ-8400
equipped airplanes, parking brake pressure (off) can be verified on the
Brakes System Page.
2. Engine Bleed Air Switches ......................................................... ON
3. APU AIR / Isolation Valve ....................................... OFF / CLOSED
4. Exterior Lights ......................................................... AS REQUIRED
5. Ground Spoilers .................................................................. ARMED
NOTE: Advance power levers before arming spoilers. Avoid retarding
power levers to idle to prevent inadvertent ground spoiler deployment.
6. Flight Controls....................................................... CONFIRM FREE
NOTE: At sixty (60) knots, the pilot shall confirm that the elevators are
free and the yoke has reached the neutral position.
NOTE: If the Flight Power Shutoff Handle is pulled at rotation due to a
flight control problem, high pull forces will be required to achieve the takeoff
attitude. There will be a delay in airplane rotation and, once airborne, a
push force will be necessary to maintain the climb attitude. Application of
forward trim will be required shortly after becoming airborne. To avoid
running out of forward trim, reduce speed as necessary.
7. Transponder / TCAS.......................................................... ON / ON
8. Crew Alerting System ..........................................................CHECK
9. Air Start Ignition ...................................................... AS REQUIRED
NOTE: It is recommended that Air Start Ignition be selected ON for
takeoff on a runway with standing water, slush, or snow.
10. Autothrottle ................................. ARM / ENGAGED (IF DESIRED)
NOTE: On SPZ 8000 equipped airplanes, the autothrottle will
annunciate “HOLD” at approximately 60 knots and will maintain power
lever “HOLD” unless selected to another mode after attaining 400 ft.
AGL.
NOTE: On SPZ 8400 equipped airplanes, the autothrottle will maintain
takeoff EPR above 400 ft. AGL unless selected to another mode after
attaining 400 ft. AGL.
11. Departure Runway Alignment ............... BOTH PILOTS CONFIRM
END

REVISION 29.1 NORMAL PROCEDURES

Aug 07/17 Page ND - 5
 Quick Reference Handbook
Notes

NORMAL PROCEDURES REVISION 29.1

Page ND - 6 Aug 07/17
Quick Reference Handbook
Climb AFM 2-05-10

1. Landing Gear .............................................................................. UP

2. Flaps ........................................................................................... UP
Limit bank angle to 15 degrees while the flaps are retracting until
reaching a speed greater than VREF on the speed tape.
3. Flight Guidance Panel .............................................................. SET
4. Exterior Lights ......................................................... AS REQUIRED
5. Ignition ...................................................................................... OFF
6. Ground Spoilers ........................................................................ OFF
7. BTMS OVHT / BRAKE OVHT Message (if installed) .....................
.................................................................................. CHECK / OUT
NOTE: SPZ-8000 equipped airplanes SN 1156 and subs and SN 1000
through 1155 having ASC 167. For SPZ-8400 equipped airplanes, BTMS
display is incorporated in the BRAKES system page.
8. Pressurization ......................................................................CHECK

9. Engine Climb Power / Autothrottle ............... SET / AS REQUIRED

10. Engine Synchronizer .............................................. AS REQUIRED
11. Altimeters (3) ...................................................................................
............ SET & CROSS-CHECKED (AT TRANSITION ALTITUDE)
12. APU ....................................... SHUT DOWN PRIOR TO 30,000 FT
NOTE: Shut down APU prior to reaching 30,000 ft. if not required for
electrical power.
END

Cruise AFM 2-05-20

1. Power................................................................. SET FOR CRUISE

2. Pressurization ......................................................................CHECK
3. Panel Sweep ............................................................... COMPLETE
NOTE: A panel sweep or a check for normal system operation and
indication should be accomplished at top-of-climb, top-of-descent, and at
regular intervals between top-of-climb and top-of-descent.

Continued on next page 

REVISION 29.1 NORMAL PROCEDURES

Aug 07/17 Page NE - 1
 Quick Reference Handbook
4. FMS Fuel Quantity ............................................................ UPDATE
NOTE: The flight crew should perform hourly updates to the FMS fuel
quantity using data from the FQMS. On FMS PERF INT Page 5/5,
perform a delete on line select key 2L. If the difference between gauge
fuel and computed fuel seems unreasonable, consider a possible fuel
leak. See Fuel Leak In Flight, page EF-14.

END

Descent AFM 2-05-30

1. Crew Briefing (VREF / Go-Around Power) ........................ BRIEFED

2. FMS .......................................................................... ARRIVAL SET
3. Flight Instruments ......................................... SET / AS REQUIRED
A. NAV AIDS ....................................... TUNED AND INDENTIFIED
B. Course Selection (using PREVIEW mode) ..................................
................................................................... INBOUND COURSE
C. DH / MDA ..............................................................................SET
D. Marker Beacons ....................................................... SELECTED
4. Pilot / Copilot Seats and Pedals ...................... SET FOR LANDING
Confirm seat and rudder pedals are positioned to provide
capability to apply both full rudder deflection and full brake pedal
actuation.
5. Cowl / Wing Anti-Ice ................................................AS REQUIRED
6. Pressurization ........................................................................... SET
CAUTION: IF ON MANUAL PRESSURE CONTROL, MONITOR
CLOSELY TO ENSURE LANDING UNPRESSURIZED WITH THE
OUTFLOW VALVE FULLY OPEN.
7. Circuit Breakers ................................................................... CHECK
8. Fuel Boost Pumps .............................................................. ALL ON
9. Nosewheel Steering ................................................................... ON
10. Parking Brake / Accumulator .................................. OFF / 3000 PSI

END

NORMAL PROCEDURES REVISION 29.1

Page NE - 2 Aug 07/17
Quick Reference Handbook
Approach - In Range AFM 2-05-40

1. Altimeters (3) ...................................................................................

................... SET & CROSS-CHECKED (AT TRANSITION LEVEL)
2. Engine Synchronizer ................................................................ OFF
3. Flaps ....................................................................... AS REQUIRED
4. VREF / Go-Around Power ............................................... CHECKED
5. Hydraulic Pressure ..............................................................CHECK
6. Exterior Lights ......................................................... AS REQUIRED
7. Auxiliary Hydraulic Pump.................................................... ARMED

END

Before Landing AFM 2-05-50

1. Landing Gear ..................................................... DOWN / 3 GREEN

2. Nutcracker .............................................................................. TEST
CAUTION: DO NOT ARM GROUND SPOILERS IF NUTCRACKER
SWITCH TEST IS UNSUCCESSFUL. REFER TO Nutcracker System
Fails To Shift To Air Mode At Takeoff, PAGE EG-10.
3. Ground Spoilers .................................................................. ARMED
NOTE: If touch and go landing is to be performed, GND SPLR should be
OFF for this maneuver. Manual spoiler landing distance should be taken
into account.
4. Crew Alerting System ..........................................................CHECK
5. Flaps ............................................................... SET FOR LANDING
CAUTION: DO NOT MOVE REVERSE THRUST LEVERS OUT OF
THE FORWARD THRUST POSITION PRIOR TO TOUCHDOWN.
NOTE: Maintain a minimum 67% HP RPM until landing.
6. WARN INHIBIT ........................................................................... ON

Continued on next page 

REVISION 30 NORMAL PROCEDURES

Oct 30/17 Page NE - 3
 Quick Reference Handbook
7. Air Start Ignition .......................................................AS REQUIRED
NOTE: It is recommended that Air Start Ignition be selected ON for
landing on a runway with standing water, slush, or snow.
8. PF Feet Position on Rudder Pedals ............... HEELS OFF FLOOR
NOTE: The pilot flying must position their feet up on the rudder pedals
(heels off the floor) prior to touchdown to provide capability to
immediately apply both full rudder deflection and full brake pedal
actuation.
NOTE: Recommended final approach speed is VREF plus 10 knots. If
gusty wind conditions exist, add ½ of the difference between the steady
state wind and gust (maximum of additional 10 knots of gust additive).
VREF will still be target speed at the threshold.

END

EGPWS Alerts AFM 2-05-60

EGPWS Caution:
When an EGPWS CAUTION occurs, adjust the airplane flight path until
the CAUTION alert ceases.
EGPWS Warning:
If an EGPWS WARNING occurs, follow the escape maneuver steps
below until all alerts cease. Unless operating in Visual Meteorological
Conditions (VMC) and / or the pilot determines based on all available
information, that turning in addition to the vertical escape maneuver is
the safest course of action, only the vertical escape maneuver is
recommended.
CAUTION: THE TERRAIN DISPLAY IS INTENDED TO SERVE AS A
SITUATIONAL AWARENESS TOOL ONLY, AND MAY NOT PROVIDE THE
ACCURACY AND / OR FIDELITY ON WHICH TO SOLELY BASE TERRAIN
AVOIDANCE MANEUVERING DECISIONS.
Vertical Escape Maneuver:
1. Autopilot....................................................................DISCONNECT
2. Power .....................MAXIMUM THRUST (GO-AROUND POWER)
3. Pitch Attitude ................................ ROTATE TO 3 TO 4 DEGREES
PER SECOND TO ATTAIN HIGHEST POSSIBLE VALUE
A pitch attitude of 25 degrees has been demonstrated on the GIV
at maximum landing weight with flaps DOWN (39).

NORMAL PROCEDURES REVISION 30

Page NE - 4 Oct 30/17
Quick Reference Handbook
When stick-shaker is encountered, or as VREF is approached:
4. Pitch Rate / Angle Of Attack ............................................................
............................. REDUCE TO INTERCEPT V2 / VREF -20 KCAS
5. Flaps / Landing Gear .......................................................................
......... DO NOT RETRACT UNTIL SAFE CLIMB-OUT IS ASSURED

END

TCAS II Flight Procedures AFM 2-05-70

Upon initiation of an RA, the pilot flying should focus attention on

flying the commanded maneuver. The airplane should be smoothly
maneuvered to comply with the TCAS command and to promptly
return to ATC clearance when the “CLEAR OF CONFLICT” message
is received.
Compliance with a TCAS II resolution advisory (RA) is necessary
unless the pilot considers it unsafe to do so, or unless the pilot has
better information about the cause of the RA and can maintain safe
separation (e.g., visual acquisition of and safe separation from a
nearby airplane, obvious TCAS system failure, etc.).
WARNING: NON-COMPLIANCE WITH A CROSSING RA BY ONE
AIRPLANE MAY RESULT IN REDUCED VERTICAL SEPARATION;
THEREFORE, SAFE HORIZONTAL SEPARATION MUST ALSO BE
ASSURED BY VISUAL MEANS.

CAUTION: ONCE A NON-CROSSING RA HAS BEEN ISSUED, SAFE

OPERATION COULD BE COMPROMISED IF CURRENT VERTICAL SPEED
IS CHANGED, EXCEPT AS NECESSARY TO COMPLY WITH THE RA.
THIS IS BECAUSE TCAS II-TO-TCAS II COORDINATION MAY BE IN
PROGRESS WITH THE INTRUDER AIRPLANE, AND ANY CHANGE IN
VERTICAL SPEED THAT DOES NOT COMPLY WITH THE RA MAY
NEGATE THE EFFECTIVENESS OF THE OTHER AIRPLANE’S
COMPLIANCE WITH ITS RA.
NOTE: The consequences of not following an RA may result in
additional RAs in which aural alert and visual annunciations may not
agree with each other.

END

REVISION 30 NORMAL PROCEDURES

Oct 30/17 Page NE - 5
 Quick Reference Handbook
All Engines Operating Go Around Procedure AFM 2-05-80

In the event that an approach is discontinued, proceed as

follows:
1. TO / GA Button .................................................................... PRESS
NOTE: The autothrottle, if engaged, automatically advances to go-
around thrust, and the autopilot, if engaged, will disengage.
2. Airspeed ..............................................................VREF +10 KNOTS
NOTE: Recommend final approach speed is VREF +10 knots. If winds
are in excess of 10 knots, or gust conditions are present, add ½ of the
steady state wind above 10 knots plus the full gust value to a maximum
additive of 20 knots (VREF +20) e.g., if winds are reported as “14 gusting
to 20 knots” the total additive to VREF is “+10 +2 +6 = 18”. VREF will still
be target speed at the threshold.
3. Power ............................. GO-AROUND THRUST (IF REQUIRED)
CAUTION: DO NOT ATTEMPT A GO-AROUND WITH LESS THAN
600 LBS OF FUEL INDICATED IN EITHER FUEL TANK.
NOTE: In the event a go-around is performed because of a balked
landing (after touchdown on runway), select GND SPLR – OFF.

4. Flaps ........ 20 ONCE GO-AROUND ATTITUDE IS ESTABLISHED

5. Landing Gear...................................................................................
........ RETRACT WHEN POSITIVE RATE OF CLIMB IS ATTAINED
6. Flaps ...................................... UP WHEN VREF +20 IS ATTAINED
Maintain speed for adequate stall margin.
7. Power ......................................................................AS REQUIRED

END

NORMAL PROCEDURES REVISION 30

Page NE - 6 Oct 30/17
Quick Reference Handbook
Temperature Range for Cowl Anti-Icing AFM 1-30-30

Use of the cowl anti-ice system is required:

• When indicated below in the Temperature Range for Cowl Anti-
Ice chart
• For taxi and takeoff, when static air temperature (as indicated on
FMS, PROGRESS, Page 2, AIR DATA, 1/1) indicates less than
+10C down to -40C and visible moisture or precipitation is
present
• In flight, when visible moisture or precipitation is present, or when
signs of icing are observed. (Ice accretion may be observed on
wings or windshield edges.)

END

REVISION 30 NORMAL PROCEDURES

Oct 30/17 Page NE - 7
 Quick Reference Handbook
Traffic Pattern AFM 2-07-10

Takeoff:
1. Gear ........................................................................................... UP
2. Flaps ........................................................................................... UP
3. Guidance Panel ........................................................................ SET
4. Climb Power ............................................................................. SET
5. GND SPLR ............................................................................... OFF
Pattern:
6. Approach Briefing ............................................... ACCOMPLISHED
7. FMS .......................................................................... ARRIVAL SET
8. Flight Instruments ......................................... SET / AS REQUIRED
9. Flight Observer Seat Position ............................................. CHECK
Landing:
10. Landing Gear ..................................................... DOWN / 3 GREEN
11. Nutcracker .............................................................................. TEST
12. GND SPLR ......................................................................... ARMED
13. Crew Alerting System .......................................................... CHECK
14. Brakes / Hydraulics ........................................................ CHECKED
15. Flaps ................................................................ SET FOR LANDING
16. WARN INHIBIT ........................................................................... ON
17. PF Feet Position on Rudder Pedals ............... HEELS OFF FLOOR
Taxi-Back:
18. GND SPLR ............................................................................... OFF
19. Flaps ............................................................... SET FOR TAKEOFF
20. LDG / STROBE Lights .............................................................. OFF
21. Brake Temps .................................................................. CHECKED
22. Transponder ............................................................AS REQUIRED
23. GPWS / GND SPLR FLAP ORIDE .......................................... OFF

NORMAL PROCEDURES REVISION 30

Page NE - 8 Oct 30/17
Quick Reference Handbook
24. Trim Settings (3) ....................................................................... SET
25. Takeoff Briefing .................................................. ACCOMPLISHED
26. FMS .......................................................................................... SET
27. Flight Instruments ..................................................................... SET
28. Guidance Panel ........................................................................ SET
29. WARN INHIBIT ........................................................................... ON
30. Flight Observer Seat Position ..............................................CHECK
Line Up:
31. COWL ANTI ICE (2) / WING ANTI ICE (2) ............. AS REQUIRED
32. Exterior Lights ........................................................................... SET
32. Transponder ............................................................................... ON
33. Radar ...................................................................... AS REQUIRED
34. GND SPLR ......................................................................... ARMED
35. V-Speeds ........................................................ CHECKED / BOXED
36. EICAS ............................................................................ CHECKED
37. Departure Runway Alignment................ BOTH PILOTS CONFIRM

END

REVISION 30 NORMAL PROCEDURES

Oct 30/17 Page NE - 9
 Quick Reference Handbook
Notes

NORMAL PROCEDURES REVISION 30

Page NE - 10 Oct 30/17
Quick Reference Handbook
After Landing AFM 2-06-10

1. Ignition ...................................................................................... OFF

2. Transponder ........................................................... AS REQUIRED
3. Flaps ....................................................................... AS REQUIRED
4. COWL / WING ANTI-ICE / ANTI ICE HTRS ......... AS REQD / OFF
5. Fuel Boost Pumps .................................... OFF (ONE EACH SIDE)
6. Landing Lights .......................................................................... OFF
7. Ground Spoilers ........................................................................ OFF
8. BTMS OVHT / BRAKE OVHT Message (if installed) .....................
.................................................................................. CHECK / OUT
NOTE: SPZ-8000 equipped airplanes SN 1156 and subs and SN 1000
through 1155 having ASC 167. For SPZ-8400 equipped airplanes, BTMS
display is incorporated in the BRAKES system page.
NOTE: If landing required hard braking, monitor temperatures to ensure
brake temperatures have peaked and are decreasing. Note peak
temperature for use in determining turn around time and brake cooling
requirements. See Brake Kinetic Energy and Carbon Brake Cooling,
page PC-15.
9. APU ........................................................................ AS REQUIRED
10. Auxiliary Power / APU Air / Engine Bleeds ............. AS REQUIRED
NOTE: With APU Alternator selected ON and Yaw Damper selected OFF,
RIGHT Converter may be selected OFF and RIGHT engine may be shut
down for taxi operations. See Single Engine Taxi checklist, page NG-5.
NOTE: If APU air is selected ON after landing, select both engine bleed
air switches to OFF. This will prevent thermal transients on the APU or
possible damage to the APU when the power levers are moved above
idle.
11. Radar (BOTH)................................................................. STANDBY

END

Shutdown AFM 2-06-20

= Quick Turnaround Items

1. Parking Brake / Pressure.......................................... ON / 3000 PSI
2. Transponder ................................................................... STANDBY
3. Emergency Power Switch ......................................................... OFF
4. Radar ........................................................................................ OFF

REVISION 28 NORMAL PROCEDURES

May 25/16 Page NF - 1
 Quick Reference Handbook
5. ELECTRIC MASTER LEFT PWR / RIGHT PWR Switches ..... OFF
6. HP Fuel Cocks .......................................................................SHUT
NOTE: It is required to run the engine(s) at idle for one minute before
shutting down (taxi time may be credited).
7. TGT ................................................................................ MONITOR
8. Radios ...................................................................................... OFF
9. BTMS OVHT / BRAKE OVHT Message (if installed) ......... CHECK
NOTE: SPZ-8000 equipped airplanes SN 1156 and subs and SN 1000
through 1155 having ASC 167. For SPZ-8400 equipped airplanes, BTMS
display is incorporated in the BRAKES system page.
10. IRSs / FMSs ............................................................................. OFF
11. Exterior Lights .........................................................AS REQUIRED
12. Fuel Boost Pumps .................................................................... OFF
13. Cockpit Lights ..........................................................AS REQUIRED
14. Oxygen ..................................................................................... OFF
15. Nose Wheel Steering ............................................................... OFF
16. Display Units ............................................................................ OFF
17. CABIN / GALLEY / RADIO MASTER Switches ....................... OFF
18. ELECTRIC MASTER AUX PWR .............................................. OFF
19. APU ............................................................... OVERSPEED / TEST
20. Standby Attitude Indicator .......................CAGED / AS REQUIRED
21. ENGINE BLEED AIR Switches (2) ........................................... OFF
NOTE: Selecting ENGINE BLEED AIR switches OFF will help extend
life of the bleed air valves by de-energizing the solenoids.
22. APU AIR ................................................................................... OFF
NOTE: APU air switch position should not be changed just prior to
shutdown. After shutdown, wait until RPM indicates less than 95% before
changing APU air switch position.
23. APU MASTER Switch ............. OFF (APU RPM LESS THAN 10%)
NOTE: (For airplanes having ASC 465 (36-150[G] APU)): The amber
APU MASTER WARN CAS message will not be displayed if the APU
MASTER switch is inadvertently left ON after shutdown.
24. Utility Hydraulic Pump Switch ...............................OFF / NOT ARM
25. Aux Hydraulic Pump Switch ..................................OFF / NOT ARM
26. BATT 1 / BATT 2 Switches....................................................... OFF

NORMAL PROCEDURES REVISION 28

Page NF - 2 May 25/16
Quick Reference Handbook
27. GUST LOCK ............................................................................... ON
CAUTION: ENSURE HYDRAULIC PRESSURE IS DEPLETED
PRIOR TO ENGAGING GUST LOCK. IT IS NOT POSSIBLE TO READ
HYDRAULIC PRESSURES AS THE AIRPLANE IS POWERED DOWN.
CYCLE THE CONTROLS WITH THE CONTROL COLUMN, CONTROL
YOKE AND RUDDER PEDALS TO DEPLETE THE RESIDUAL
PRESSURE. FAILURE TO ALLOW HYDRAULIC PRESSURE TO
DISSIPATE PRIOR TO ENGAGING THE GUST LOCK MAY CAUSE
DAMAGE TO THE AIRPLANE STRUCTURE.
28. Chocks ............................................................................. IN PLACE
29. Parking Brake ........................................................................... OFF

END

Securing OM 09-01-30

1. Auxiliary Power Switch ............................................................. OFF

2. APU ........................................................................... OVERSPEED
3. Boost Pumps ............................................................................ OFF
4. APU Air ..................................................................................... OFF
5. APU Master .............................................................................. OFF
6. UTILITY PUMP ................................................................NOT ARM
7. AUX PUMP ......................................................................NOT ARM
8. Cockpit Lights ........................................................................... OFF
9. Both Batteries ........................................................................... OFF
10. Gust Lock.................................................................................... ON
11. IRS “ON BATT” Lights ................................................ CHECK OUT
12. Parking Brake ......................................................... AS REQUIRED

END

REVISION 28 NORMAL PROCEDURES

May 25/16 Page NF - 3
 Quick Reference Handbook
Postflight AFM 2-06-30

1. Engine Oil ............................................................................ CHECK

Check engine oil at the sight glass after the last flight of the day or
at intervals not exceeding eleven (11) hours cumulative flight time.
NOTE: For accurate readings, engine oil must be checked within 30
minutes after engine shutdown.
2. Brakes / Landing Gear ............................................ INSPECT / PIN
3. Thrust Reversers ......................... CHECK / PROPERLY STOWED
NOTE: If the lower thrust reverser door leading edge is sagged out of
normal contour, report for maintenance action before next flight.
4. Exterior ............................................................................. INSPECT
5. Forms And Records .....................................................COMPLETE
6. Interior ................................................................................. CHECK
7. Doors .................................................................................CLOSED

END

Transit Check OM 09-03-80

The transit check is required by the Rolls Royce Tay Maintenance

Manual. It may be performed by a qualified flight crew member. Make
log book entry if required.
After engine shutdown at termination of the last flight of the day
or at intervals not exceeding eleven (11.0) hours cumulative flight
time:
1. Engine Oil ....................... CHECK / REPLENISH AS NECESSARY
NOTE: For accurate readings, engine oil must be checked within 30
minutes after engine shutdown.
2. Oil Filter Differential Pressure Indicator (DPI) ................. EXAMINE
Examine the engine oil filter DPI to determine if oil filter blockage
has occurred.

END

NORMAL PROCEDURES REVISION 28

Page NF - 4 May 25/16
Quick Reference Handbook
Flight Fault Summary Check OM 09-03-70

After the airplane is on the ground and airspeed is less than 50

knots:
1. DO NOT turn off any airplane power (APU can be used for
auxiliary power).
NOTE: DO NOT turn off Electronic Flight Instrument System (EFIS)
display.
2. Select any Maintenance Test (MAINT TEST) switch to ON.
NOTE: MAINT TEST switches are located on both the left and right
hand radio rack system test and monitor panels. On airplanes with ASC
221, a MAINT TEST switch is also located on Copilot's Aft Circuit
Breaker Panel. Only one switch needs to be selected.
3. Disengage yaw damper.
4. On either the Pilot's or Copilot's Display Controller (DC), push the
TEST button to display the TEST menu.
5. From the DC TEST menu, push the line select key adjacent to the
MAINT option. This causes the MAINT TEST menu to be
displayed on the DC.
6. From the DC MAINT TEST menu, push the line select key
adjacent to the AFGCS option. This causes the AFGCS menu to
be displayed on the DC.
7. From the DC AFGCS menu, push the line select key adjacent to
the DOWN option once. This causes the MAINTENANCE TEST
menu page to be displayed on Display Unit (DU) 4. On the
MAINTENANCE TEST menu page, the SYSTEM TEST option is
boxed.
8. From the DC AFGCS menu, push the line select key adjacent to
the SELECT option once. This causes “05 FGC TEST” to be
displayed on DU 4.
9. From the DC AFGCS menu, push the line select key adjacent to
the UP option twice. This causes “50 FLIGHT FAULT SUMMARY”
to be displayed on DU 4.
10. From the DC AFGCS menu, push the line select key adjacent to
the SELECT option once. This causes the Flight Fault Summary
to be displayed on DU 4.

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11. The Flight Fault Summary displayed on DU 4 will be from either
Flight Guidance Computer (FGC) 1 or FGC 2. Record all
characters displayed, including any spaces between character
groups.
12. From the DC AFGCS menu, push the line select key adjacent to
the SELECT option once. This causes the Flight Fault Summary
to be displayed on DU 4 for the other FGC. Again, record all
characters displayed, including any spaces between character
groups.
13. Select MAINT TEST switch to OFF.
14. Shut down airplane power if no longer required.

END

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Alternate Normal Procedures Index

Cold Start (Reference Only) ........................................................ NG-2

External Air Start .......................................................................... NG-2
Crossbleed Start .......................................................................... NG-2
Engine Cranking Cycle ................................................................ NG-3
Engine Start - Battery Power Only............................................... NG-3
Single Engine Taxi ....................................................................... NG-5
Battery Charging Using APU or External AC Power ................... NG-6
GIV QFE Operations .................................................................... NG-6
RNP 0.3 RNAV Approach Procedures (RNAV / VNAV)
Approach To A Decision Altitude .............................................. NG-8
High Elevation Airport Operations ............................................... NG-8
Cold Weather Altimeter Setting Procedures .............................. NG-12
Use of The Rudder In Flight ...................................................... NG-13
Thrust Reverser Lockout ........................................................... NG-14
Engine Start - Manual Operation of Start Valve ........................ NG-15
Operational Procedures With Cowl Anti-ice Valve Locked
Open ....................................................................................... NG-21
APU Inflight Operation ............................................................... NG-23
P-RNAV (Precision RNAV) Procedures .................................... NG-24

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 Quick Reference Handbook
Cold Start AFM 2-08-10

In cold ambient temperatures (when oil temperature is minus 10°C or

less) refer to All Weather Operations and Procedures in the GIV
Operating Manual.
CAUTION: IF DEICING SOLUTION IS INADVERTENTLY SPRAYED
INTO THE ENGINE / APU INLETS OR CONTACTS THE EXHAUST WHEN
ENGINES OR APU ARE OPERATING, POTENTIALLY UNSAFE
CONDITIONS COULD DEVELOP IN THE CABIN. ENGINE / APU BLEEDS
SHOULD BE CLOSED DURING DEICING OPERATIONS TO MINIMIZE THE
RISK OF CABIN ENVIRONMENT CONTAMINATION.

END

External Air Start AFM 2-08-20

1. External Air Source ....................................................CONNECTED

2. Normal Engine Ground Start Procedure ........................ PERFORM
Either engine, or both in turn, may be started from an external air
supply.
NOTE: Depending on the source of external air, the engine start cycle
may take longer than normal. Refer to GIV AFM Section 1, Engine
Starter Duty Limits.

END

Crossbleed Start AFM 2-08-30

After starting one engine from either APU or external air supply:
1. ENGINE BLEED AIR (engine to be started) ............................. OFF
2. ENGINE BLEED AIR (operating engine) .................................... ON
3. Running Engine Power Lever ..........................................................
.................. ADVANCE TO 25 TO 30 PSI BLEED AIR PRESSURE
CAUTION: APPROXIMATELY 85% HP RPM IS REQUIRED FOR
CROSSBLEED STARTING. ENSURE AREA BEHIND AIRPLANE IS
CLEAR BEFORE ATTEMPTING THIS PROCEDURE.
4. Engine Not Running .........................................................................
........... START, USING NORMAL ENGINE-START PROCEDURES
NOTE: See Starting Engines checklist, page NC-6.

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After Starting Other Engine:
5. Power Levers............................................................................ IDLE

END

Engine Cranking Cycle AFM 2-08-40

CAUTION: CONTINUED USE OF THE STARTER IS LIMITED TO

THREE (3) CRANK-CYCLES, WITH A MAXIMUM OF THIRTY (30)
SECONDS PER CYCLE. DELAY THREE (3) MINUTES BETWEEN START-
CYCLES. AFTER THREE (3) START-CYCLES, DELAY USE OF THE
STARTER FOR AT LEAST FIFTEEN (15) MINUTES.
1. HP Fuel Cock ........................................................................ SHUT
2. Power Lever ............................................................................ IDLE
3. APU Air / Bleed Air ..................................................................... ON
4. Boost Pump ................................................................................ ON
5. Engine Crank Master .................................................................. ON
6. Engine Start Switch .................................................................... ON
7. Start Valve Message .................................................................. ON
8. Engine Rotation (LP, HP) ............................................... CONFIRM
9. Oil Pressure ................................................................ INDICATING
10. Engine Crank Master .......................................................................
.................................. OFF (AFTER THIRTY [30] SECONDS MAX)

END

Engine Start - Battery Power Only AFM 2-08-50

Use this checklist in situations where the only electrical source

available is the airplane's batteries and an air source is available from
either APU or external air cart.
The checklist calls for switches to be selected before selecting
batteries ON. The intent is to reduce drain on the batteries while
performing normal checklist functions.
If the APU is the source of air for engine start, expedite steps between
APU start and the first engine start. This reduces drain on batteries.

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 Quick Reference Handbook
Complete all safety checks and as much of Before Starting Engines
checklist (page NC-1) as possible.
1. Chocks ............................................................................ IN PLACE
2. HP Fuel Cocks .......................................................................SHUT
3. Circuit Breakers ................................................................... CHECK
4. EPMP Bus Switches ............................................................. AUTO
5. APU Air ..................................................................................... OFF
6. Beacon ....................................................................................... ON
7. Standby Engine Instruments ............................................ MANUAL
8. Standby Warning Lights Panel ......................................... MANUAL
9. Left Main Boost Pump ................................................................ ON
10. Fuel Crossflow....................................................................... OPEN
11. Engine Temperature Controls .................................................... ON
12. Engine Start Master .................................................................... ON
13. Air Conditioning Packs ............................................................. OFF
14. Electrical Power Master Switch ... ON (ENGINE TO BE STARTED)
15. Gust Lock ................................................................................. OFF
16. Battery 1 and 2 Switches............................................................ ON
17. Engine Fire Test ...........................................................COMPLETE
If APU is used for engine start, continue with Step 18. If external
air is used, proceed to Step 22.
18. APU Fire Warning .................................................................. TEST
19. APU Master Switch .................................................................... ON
20. APU Oil Pressure Low Light ....................................................... ON
21. APU ......................................................................................START
After APU is stabilized one (1) minute:
22. APU AIR / External AIR .............................. ON (25 PSI MINIMUM)
23. Air Start Ignition For Engine To Be Started ................................ ON
24. Engine Start Switch ............................................................. PRESS

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Using standby engine instruments, at 15% HP RPM minimum with
LP RPM indicating an RPM value other than LO:
25. HP Fuel Cock ........................................................................ OPEN
26. TGT............................................................. MONITOR (700° MAX)
NOTE: As engine accelerates to idle, the converter will be operative.
27. Battery Ammeters ................................................................CHECK
28. Air Start Ignition ........................................................................ OFF
29. DUs ............................................................................................. ON
30. EICAS .................................................. CHECK SVO and IGN OUT
31. Remaining Before Starting Engines Checklist Items (pg. NC-1) ....
...................................... COMPLETE AS APPROPRIATE BEFORE
STARTING SECOND ENGINE

END

Single Engine Taxi AFM 2-08-60

Single engine taxi is recommended utilizing the left engine for power
and hydraulics. Additionally, the APU should be running and selected
ON for electrical power in the event of a left alternator/converter failure.
Taxi-Out:
1. Left Engine ..................................................................... RUNNING
2. Left Converter ............................................................................. ON
3. APU ................................................................................ RUNNING
4. AUX Power ................................................................................. ON
5. Yaw Damper ............................................................................. OFF
Before Takeoff:
6. Right Engine ........................................................................ START
Allow one (1) minute for engine to stabilize before takeoff.
7. Right Converter .......................................................................... ON
8. APU Air ..................................................................................... OFF
9. APU ........................................................................ AS REQUIRED
10. Yaw Damper ............................................................................... ON

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 Quick Reference Handbook
Taxi-In:
Allow one (1) minute for cool-down at idle thrust, on right engine, prior
to shutdown.
1. APU ......................................................................................START
2. AUX Power ................................................................................ ON
3. Right Converter ........................................................................ OFF
4. Yaw Damper ............................................................................ OFF
5. Right Engine .............................................................. SHUT DOWN

END

Battery Charging Using APU or External AC Power

1. ELECTRIC MASTER AUX PWR ................................................ ON
NOTE: Battery charging is possible using APU alternator or external AC
power only.
2. BATT 1 or BATT 2 ...................................................................... ON
NOTE: If charging of only one (1) battery is desired, pull appropriate
BATT CHGR circuit breaker on PDB. For airplanes having ASC 54, if
charging of only one (1) battery is desired, select appropriate BATT
switch ON.
3. Battery Ammeter(s) ........................................................ MONITOR
NOTE: The battery chargers may use up to 34 volts for battery charging.
Maximum current for battery charging is limited to 38 amps.

END

GIV QFE Operations AFM 2-08-80

Takeoff:
1. Set pilot’s and copilot’s altimeter settings to QNH (if available). If
QNH is not available, set altimeters to achieve published field
elevation.
2. Perform Takeoff Initialization and verify Takeoff Data to be
correct.
3. On Display Controller, manually "box" takeoff V speeds.

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4. Set desired Flight Level in the AIPLANE / CABIN window along
with the desired rate for cabin rate of change in the RATE LIMIT
window.
5. Set pilot’s and copilot’s altimeter setting to QFE for takeoff.
6. During TAXI checklist, verify that the FLIGHT mode is selected
and that the DFRN PRESS does not exceed 0.30 PSID.
7. Select TERRAIN INHIBIT ON if operating with EGPWS Software
Version –104 -104.
Climb:
1. When clear of traffic pattern, select AUTO V-SPEEDS on Display
Controller.
2. At Transition Altitude, select appropriate altimeter setting (29.92 /
1013).
3. Select TERRAIN INHIBIT to OFF if previously selected ON before
takeoff.
Approach:
1. Set QFE altimeter setting when directed by ATC.
2. Set QNH in the BARO CORR window of Cabin Pressure Selector
Panel.
3. Set published Landing Field Elevation in the LANDING ELEV
window.
4. Set desired RATE in the RATE Limit window.
5. Select TERRAIN INHIBIT to ON if operating EGPWS Software
Version –104-104.
6. Verify CPCS is in Landing mode. Verify DFRN PRESS less than
0.30 PSID prior to landing.

END

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 Quick Reference Handbook
RNP 0.3 Approach Procedures (RNAV/VNAV)
Approach To A Decision Altitude AFM 2-08-90

1. Review the published approach.

2. Select the approach from the database and activate it.
3. Ensure Receiver Autonomous Integrity Monitoring (RAIM) is
available so approach requirements can be met.
4. Set MDA or RAD ALT value to the published DA or reference
radio altitude value.
5. When cleared for the approach, arm the LNAV mode (and VNAV
mode if VNAV guidance is desired for the approach) on the
Guidance Panel and set the Altitude Preselector to the
Touchdown Zone Elevation to ensure continuous vertical
guidance to the runway.
6. When within 2 miles of the Final Approach Fix (FAF), the FMS
Approach light/FMS Approach message will illuminate. This is
clearance to continue the approach to the published DA. If the
FMS Approach light/FMS Approach message does not illuminate,
the approach shall be abandoned.
7. When runway is in sight, disconnect autopilot/autothrottle and
land. If runway not in sight at the DA (or MDA, as appropriate),
execute the published missed approach.

END

High Elevation Airport Operations AFM 2-08-130

Flight Crew Considerations:

Use of oxygen by the flight crew while performing high-workload tasks
at high elevation airports or at field elevations for which the flight crew
is not acclimated is highly recommended.
NOTE: Examine performance data thoroughly to determine the adverse
effects of high density altitude on airplane performance.
Engine Start:
The following topics contain recommended changes to the engine
starting procedures to high elevation airports. During use of these
procedures, the flight crew shall be alert to higher-than-normal TGT
indications or the possibility of a hot start.

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CAUTION: IF THE POWER LEVER IS NOT AT IDLE, THE START WILL
CONTINUE AND THE ENGINE WILL ACCELERATE TO THE THRUST
SELECTED BY THE POWER LEVER. THIS IS NOT RECOMMENDED.
ALWAYS ENSURE THAT POWER LEVERS ARE AT IDLE DURING
STARTING.
CAUTION: CONTINUED USE OF THE STARTER IS LIMITED TO
THREE (3) CRANK-CYCLES, WITH A MAXIMUM OF THIRTY (30)
SECONDS PER CYCLE. DELAY THREE (3) MINUTES BETWEEN START
ATTEMPTS. AFTER THREE (3) START-CYCLES, DELAY USE OF THE
STARTER FOR AT LEAST FIFTEEN (15) MINUTES.
Right Engine Start:
CAUTION: WITH THE UTILITY PUMP OFF, ONLY THE PARKING
BRAKE IS AVAILABLE TO HOLD THE AIRCRAFT. THE USE OF CHOCKS
IS RECOMMENDED.
NOTE: Reduce electrical loads on APU alternator to allow APU to provide
maximum airflow.
The flight crew shall be alert for higher-than-normal TGT indications
or the possibility of a hot start.
1. UTILITY PUMP OFF/ARM ........................................................ OFF
2. Fuel Boost Pumps ................ ONE ON, REMAINING THREE OFF
3. Crossflow Valve (X FLOW).................................................... OPEN
4. RAM AIR .................................................................................. RAM
5. R AIR START IGN (1144 & Subs., Airplanes with ASC 151) ..... ON
6. Maximum Motoring RPM (16-22% HP RPM) ................ ACHIEVED
At maximum motoring RPM:
7. R HP FUEL COCK ................................................................ OPEN
8. TGT................................................................................. MONITOR
After the engine is stabilized at idle:
9. R AIR START IGN (1144 & Subs., Airplanes with ASC 151) ... OFF
10. Utility Pump................................................................................. ON
Left Engine Start:
CAUTION: USE ONLY ONE SOURCE OF BLEED AIR, EITHER APU
BLEED AIR OR CROSSBLEED AIR, TO START ENGINE.
Perform an alternate engine starting procedure as follows:
1. Available Bleed Air (Right Engine, If Required) ............. INCREASE

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 Quick Reference Handbook
2. Maximum Motoring RPM (16-22% HP RPM) ................ ACHIEVED
3. L AIR START IGN (1144 & Subs., Airplanes with ASC 151) ..... ON
At maximum motoring RPM:
4. L HP FUEL COCK ................................................................. OPEN
5. TGT ................................................................................ MONITOR
After the engine is stabilized at idle:
6. L AIR START IGN (1144 & Subs., Airplanes with ASC 151) ......OFF
7. Right Engine ............................................................................ IDLE
8. Utility Pump OFF/ARM ............................................................ ARM
9. RAM Air .................................................................................... OFF
Taxi:
Ground idle speeds may be lower than those required to keep the
alternators on line. It is recommended that the APU be left running
with the APU alternator on line for all ground operations.
CAUTION: USE ONLY ONE SOURCE OF BLEED AIR, EITHER APU
BLEED AIR OR ENGINE BLEED AIR, WHILE TAXIING TO PREVENT
POSSIBLE DAMAGE TO THE APU.
Takeoff:
1. Certain high-elevation airports have preferential runways for
takeoff and landing, i.e., upslope for landing and downslope for
takeoff. Slope, headwind and tailwind conditions should be given
due consideration.
2. Stabilize engine power at 1.5 EPR for 15 seconds and perform a
rolling takeoff. With tailwind conditions, monitor LP RPM limits
when setting final takeoff power, during takeoff run and during
climb out. The Pilot Not Flying (PNF) should be briefed to monitor
LP RPM during takeoff and should be ready to adjust power as
necessary to avoid exceedances. The Pilot Flying (PF) should be
aware that a red “ENGINE EXCEEDANCE” warning CAS
message may occur during takeoff if LP RPM exceeds 95.5%. DO
NOT BE COMPELLED TO ABORT THE TAKEOFF IF THIS
MESSAGE OCCURS. This is especially true when using the
autothrottle.
3. If COWL ANTI ICE or WING ANTI ICE is used for takeoff, select a
minimum of 1.2 EPR or higher before selecting ANTI ICE to ON.
4. Expect slower-than-normal acceleration to 60 knots.

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Descent, Approach and Landing:
1. It may be necessary to increase cabin altitude for landing.
2. If the Landing Field Elevation (LFE) approaches 9,000 ft MSL or
higher, be prepared for a red “CABIN PRESSURE LOW” warning
message to be displayed on CAS.
3. If the LFE approaches 13,000 ft MSL, automatic deployment of
passenger oxygen masks is possible. The passenger masks may
be deployed manually or portable oxygen bottles may be made
available to the passengers to enhance passenger comfort.
4. The cockpit flight crew shall utilize oxygen any time the cabin
altitude is 10,000 ft MSL or higher.
5. On approach, start the APU and select the APU alternator to ON.
6. On approach, landing and rollout, be aware of True Airspeed (TAS)
and Ground Speed (GS). A 145 KCAS approach speed can
translate to 175 KTAS. Ground speed amplified by tailwind
conditions could exceed maximum tire speed on landing.
7. Expect slower than normal thrust reverser spool-up times.
8. Apply brakes at lower ground speeds (runway length permitting) to
avoid excessive brake energy absorption.

END

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 Quick Reference Handbook
Cold Weather Altimeter Setting Procedures AFM 2-08-100

EXTREME CAUTION SHOULD BE EXERCISED WHEN FLYING IN

PROXIMITY TO OBSTRUCTIONS OR TERRAIN IN LOW TEM-
PERATURES. This is especially true in extremely cold temperatures
that cause a large differential between the Standard Day temperature
and actual temperature. This circumstance can cause serious errors
that result in the airplane being significantly lower than the indicated
altitude.
Temperature has an effect on the accuracy of altimeters and your
altitude. The crucial values to consider are standard temperature
versus the ambient (at altitude) temperature. It is this “difference” that
causes the error in indicated altitude. When the air is warmer than
standard, you are higher than your altimeter indicates. Subsequently,
when the air is colder than standard you are lower than indicated. It is
the magnitude of this “difference” that determines the magnitude of
the error. When flying into a cooler air mass while maintaining a
constant indicated altitude, you are losing true altitude. However,
flying into a cooler air mass does not necessarily mean you will be
lower than indicated if the difference is still on the plus side. For
example, while flying at 10,000 feet (where STANDARD temperature
is –5 degrees Celsius (C)), the outside air temperature cools from +5
degrees C to 0 degrees C, the temperature will nevertheless cause
the airplane to be HIGHER than indicated. It is the extreme “cold”
difference that normally would be of concern to the pilot. Also, when
flying in cold conditions over mountainous country, the pilot should
exercise caution in flight planning both in regard to route and altitude
to ensure adequate enroute and terminal area terrain clearance.
The following table derived from ICAO formulas indicates how much
error can exist when the temperature is extremely cold. To use the
table, find the reported temperature in the left column, then read
across the top row to locate the height above the airport/reporting
station (i.e., subtract the airport/reporting elevation from the intended
flight altitude). The intersection of the column and row is how much
lower the airplane may actually be as a result of the possible cold
temperature induced error.
The possible result of the above example should be obvious,
particularly if operating at the minimum altitude or when conducting an
instrument approach. When operating in extreme cold temperatures,
pilots may wish to compensate for the reduction in terrain clearance
by adding a cold temperature correction.
Continued on next page 

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Page NG - 12 Mar 17/10
Quick Reference Handbook
Cold Weather Altimeter Setting Procedures, ctd… AFM 2-08-100

Temp Height Above Airport (Feet)

(°C) 200 300 400 500 600 700 800
+10 10 10 10 10 20 20 20
0 20 20 30 30 40 40 50
-10 20 30 40 50 60 70 80
-20 30 50 60 70 90 100 120
-30 40 60 80 100 120 130 150
-40 50 80 100 120 150 170 190
-50 60 90 120 150 180 210 240
Temp Height Above Airport (Feet)
(°C) 900 1000 1500 2000 3000 4000 5000
+10 20 20 30 40 60 80 90
0 50 60 90 120 170 230 280
-10 90 100 150 200 290 390 490
-20 130 140 210 280 420 570 710
-30 170 190 280 380 570 760 950
-40 220 240 360 480 720 970 1210
-50 270 300 450 590 890 1190 1500

END

Use Of The Rudder In Flight AFM 2-08-110

Flight crews should use caution when operating the rudder in flight.
The rudder limiter design protects the vertical fin of prolonged maxi-
mum rudder inputs in a single direction only. If the rudder is deflected
to maximum deflection then suddenly reversed to the maximum de-
flection in the opposite direction, the vertical fin can be overstressed.
Additionally, the vertical fin can be overstressed by a pilot “walking”
the rudder either abruptly or in small increments in tune with the yaw
response. The issue is magnified at high speed.
There are 3 rules of thumb to follow when using the rudder in flight:
1. Maximum deflection of the rudder in a single direction may be
used to control the airplane when needed such as in the case of
an engine failure at takeoff. Do not return the rudder past neutral
when completing the maneuver.

Continued on next page 

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 Quick Reference Handbook
Use Of The Rudder In Flight, ctd… AFM 2-08-110

2. Do not walk the rudder in tune with the yaw response, either with
abrupt or smooth inputs
3. If you follow the above two rules and continue to fly the airplane
within the published envelope using normal airmanship, you will
not overstress the airplane.
NOTE: Small rudder doublets for the purposes of flight test of yaw
damper effectiveness and response are allowed.

END

Thrust Reverser Lockout OM 09-03-10

1. General:
If a Thrust Reverser (T/R) system malfunction is suspected or if a
failure prevents normal function of either or both T/Rs (including a
no deploy condition), the airplane cannot be dispatched until the
condition is corrected. Gulfstream recommends contacting
Gulfstream Technical Operations, the Operator's Area Field
Service Representative or the Operator's Home Base of
Operations if a T/R system malfunction is suspected or a failure is
detected.
Thrust reverser lockout procedures for the Gulfstream IV
airplane, although available to increase the level of dispatch
capability, are a complex procedure. An improperly locked down
T/R may cause extensive damage to the T/R system, spurious
UNLOCK or DEPLOY warnings to be displayed to the flight crew
or, in the worst case, actual inadvertent deployment of a T/R
door. Therefore, T/R lockout procedures are to be performed only
by properly certificated Airframe and Powerplant Technicians in
accordance with Chapter 78 of the latest approved version of the
Gulfstream Aerospace GIV Aircraft Maintenance Manual.
With one reverser inoperative, the flight crew must be aware of
possible asymmetric braking effects if the operative reverser is
deployed on landing. If desired, lockdown of a properly operating
T/R can be accomplished to avoid possible asymmetric braking
effects. However, Gulfstream does not recommend this in the
event that the operational T/R is needed for any reason during
period the single malfunctioning T/R is locked down.
Continued on next page 

NORMAL PROCEDURES REVISION 24 (RE-ISSUE)

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Quick Reference Handbook
Thrust Reverser Lockout, ctd… OM 09-03-10

2. References:
• GIV Master Minimum Equipment List, System 78
• GIV Airplane Flight Manual, Limitations, Section 01-78-10:
Thrust Reversers
• GIV QRH Section EC (Engines): Thrust Reverser Abnormal
/ Emergency Procedures

END

Engine Start - Manual Operation Of Start Valve

OM 09-03-40

1. General:
Procedures for manually overriding the start-valves on the
Gulfstream IV are included to enable the flight crew to assist and
supervise ramp service personnel when the airplane is away from
its fixed base of operations. The procedures provided in this
section are general in nature and are intended to increase the
level of dispatch capability. Should the procedures presented in
this section conflict with the latest approved version of the
Gulfstream Aerospace GIV Aircraft Maintenance Manual, those
procedures shall take precedence over the procedures presented
in this section in any and all cases.
A. Overview:
This procedure provides an alternate method to start the engine
if the start-valve has failed in the closed position and engine
cannot be started using normal Airplane Flight Manual (AFM)
procedures.
Effective electronic voice communications and coordination
between cockpit and ground crews will be necessary for this
procedure.
If the engine fails to start but IGN and SVO and IGN icons are
displayed, the failed, closed, start-valve may be stuck due to
condensation and/or corrosion. The start-valve indication
comes on with 6° of valve rotation; therefore, the start-valve
open indication (SVO icon) may be displayed but the valve
may be almost fully closed.
Continued on next page 

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Mar 17/10 Page NG - 15
 Quick Reference Handbook
Engine Start - Manual Operation Of Start Valve, ctd… OM 09-03-40

Manually exercising the start valve in accordance with

Paragraph 2.C. may “free up” the start valve, allowing the
engine to be started normally.
If the engine does not start normally after manually exercising
the valve or the IGN and SVO indications are not displayed,
Paragraph 2.D. provides the procedure to start engine with the
valve manually opened.
Normal ground/inflight operation of systems using bleed air is
not affected by this procedure.
CAUTION: IF THE START-VALVE HAS FAILED IN THE OPEN
POSITION, REPLACE VALVE PRIOR TO AIRCRAFT DISPATCH.
B. Applicability:
This procedure is applicable to left engine and right engine
start-valves.
C. References:
• GIV Master Minimum Equipment List, System 80
• GIV Airplane Flight Manual, Limitations, Section 01-80-
10: Starter Duty
• GIV QRH Section EC (Engines): Start-Valve Failure
2. Procedure:
A. Tools and Equipment Needed:

Part Number: Nomenclature: Remarks:

N/A 3/8” wrench or Used to position man-
3/8” socket / ual drive shaft.
breaker bar
combination
DAVID CLARK Headset Used with external
Part No. H3310 communications cord to
or Equivalent establish communi-
cation with cockpit
crewmember.
DAVID CLARK Communication Used with headset to
Part No. C-31-** Cord establish communica-
(where ** is tion with cockpit
length in feet) or crewmember.
equivalent
NOTE: Do not use a ratchet for these procedures.
Continued on next page 

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Quick Reference Handbook
Engine Start - Manual Operation Of Start Valve, ctd… OM 09-03-40

B. Preparation:
When properly configured, the left and right engine start-valves
are normally commanded open when the L ENG START / R
ENG START switches are depressed. This is confirmed by a
blue (HP RPM < 44.5%) or flashing amber (HP RPM ≥ 44.5%)
SVO icon displayed on EICAS adjacent to the respective HP
tachometer. If the start-valve is confirmed as failed closed,
proceed as follows:
(1) Ensure airplane is safe for performing procedure.
(2) Assess situation. See Start Valve Failure, page EC-21.
C. Manual Operation of Start Valve (IGN and SVO Icons
Displayed During First Start Attempt): (See Figure 1)
CAUTION: DO NOT USE A RATCHET TO OPERATE VALVE.
USE A BREAKER BAR, APPROPRIATE SIZE EXTENSION AND
SOCKET TO OPERATE VALVE.
(1) Ensure all sources of air to bleed air manifold are removed.
(2) Ensure L ENG START / R ENG START switches are OFF.
(3) On appropriate engine cowl, open start-valve access panel.
(4) Install socket, extension and breaker bar on start valve
manual wrenching feature.
NOTE: Manual wrenching feature is located with position
indicator switch on start valve.
(5) Rotate valve to OPEN and CLOSED indicated positions
several times. Note any resistance or binding (other than
normal 50 pounds spring tension). If binding is noted,
rotate valve to open and closed positions until valve travel
is smooth.
(6) Ensure valve is in CLOSED indicated position.
(7) Remove tools, check for presence of foreign objects then
close engine cowl start-valve access panel.
(8) Clear area of personnel and foreign objects.
(9) Attempt normal engine start using QRH start procedure. If
engine will not start, perform Paragraph 2.D.
Continued on next page 

REVISION 28 NORMAL PROCEDURES

May 25/16 Page NG - 17
 Quick Reference Handbook
Engine Start - Manual Operation Of Start Valve, ctd… OM 09-03-40

D. Manual Opening and Closing of Start Valve: (See Figure 1)

WARNING: THIS PROCEDURE IS PERFORMED IN THE
VICINITY OF AN OPERATING AIRPLANE ENGINE. REMAIN
CLEAR OF ENGINE AIR INLET AT ALL TIMES. FAILURE TO
COMPLY CAN RESULT IN SERIOUS INJURY OR DEATH.
WARNING: EXTREME CARE MUST BE EXERCISED TO
GUARD AGAINST EMISSION OF HOT EXHAUST GAS FROM THE
STARTER WHEN MANUALLY OPENING OR CLOSING THE
START VALVE. USE A EXTENSION LONG ENOUGH TO ENSURE
A SAFE DISTANCE FROM STARTER VALVE EXHAUST.
CAUTION: DO NOT USE A RATCHET TO OPERATE START-
VALVE. USE A BREAKER BAR, APPROPRIATE SIZE EXTENSION
AND SOCKET TO OPERATE VALVE.
CAUTION: CLOSE START-VALVE AT OR BEFORE 40% HP
RPM. THE STARTER CAN OVERHEAT PAST 40% HP RPM.
CAUTION: DURING MANUAL OPERATION OF START-VALVE,
BLEED AIR PRESSURE ENTERING THE VALVE WILL NOT BE
REGULATED.
CAUTION: CONTINUED USE OF THE STARTER IS LIMITED
TO THREE (3) CRANK-CYCLES WITH A MAXIMUM OF THIRTY
(30) SECONDS PER CYCLE. DELAY THREE (3) MINUTES
BETWEEN START ATTEMPTS. AFTER THREE (3) CYCLES,
DELAY USE OF THE STARTER FOR AT LEAST FIFTEEN (15)
MINUTES.
CAUTION: APU BLEED AIR AND ENGINE START-SWITCHES
MUST BE OFF FOR THIS PROCEDURE.
(1) Position one crewmember in cockpit to perform engine
start and direct opening and closing of valve.
(2) Establish communication between cockpit crewmember
and outside crewmember.
(3) Start opposite engine using normal AFM procedures.
(4) Select APU BLEED AIR off or shut down APU.
(5) Select both L ENG and R ENG BLEED AIR switches to
OFF.
(6) Select both L PACK and R PACK switches to OFF.
Continued on next page 

NORMAL PROCEDURES REVISION 28

Page NG - 18 May 25/16
Quick Reference Handbook
Engine Start - Manual Operation Of Start Valve, ctd… OM 09-03-40

(7) On appropriate engine cowl, open start-valve access

panel.
(8) Using socket, extension and breaker bar on start-valve
manual wrenching feature, position valve to OPEN and
hold.
(9) Start engine using cross bleed starting technique as
follows:
(a) Notify outside crewmember that engine is to be
started.
(b) Increase opposite engine RPM to approximately 75%
HP RPM. This will provide a bleed air manifold
pressure of approximately 30 psi.
(c) Select ISOLATION valve to OPEN.
(d) Select ENG START switch to ON for engine to be
started.
(e) Select BLEED AIR switch to ON for operating engine.
Continue with normal engine start. Using power lever,
maintain 25-30 psi bleed air manifold pressure
throughout engine start-cycle.
(f) Upon attaining 40% HP RPM, select both BLEED AIR
switches to OFF. Remove pressure from manifold.
Notify outside crewmember to position valve to
CLOSED.
(g) Select ENG START switch to OFF.
(10) Remove tools, check for presence of foreign objects then
close engine cowl start-valve access panel.
(11) Close and secure start-valve access door.

END

REVISION 24 (RE-ISSUE) NORMAL PROCEDURES

Mar 17/10 Page NG - 19
 Quick Reference Handbook

Figure 1: Rolls Royce Tay Engine Start Valve

NORMAL PROCEDURES REVISION 24 (RE-ISSUE)

Page NG - 20 Mar 17/10
Quick Reference Handbook
Operational Procedures With Cowl Anti-Ice
Valve Locked Open OM 09-03-50

THIS PROCEDURE IS TO BE USED IN ACCORDANCE WITH GIV

MMEL “M” AND “O” PROCEDURES.
1. Procedure:
A. General:
If a cowl anti-ice valve fails to operate during preflight checkout
and icing conditions are expected during flight, the airplane
may be dispatched with that cowl anti-ice valve manually
locked open.
NOTE: Use of this procedure is intended for extreme circumstances,
where dispatch of the airplane is essential. It is not intended for
routine operation.
B. References:
• GIV Master Minimum Equipment List, System 30
• GIV Airplane Flight Manual, Limitations, Section 01-30-
30: Cowl Anti-Icing
• GIV Aircraft Maintenance Manual, Chapter 30
C. Procedure:
(1) Start engine having operative cowl anti-ice valve using
either APU BLEED AIR or an external air source.
(2) After engine is started, select APU BLEED AIR (or external
air source) OFF. Also select ENG BLEED AIR of that
running engine to OFF. DO NOT RESELECT APU
BLEED AIR ON FOR REMAINDER OF OPERATIONS.
APU BLEED AIR MUST NOT BE SELECTED ON WITH
COWL ANTI-ICE VALVE IN OPEN POSITION.
(3) Manually lock the inoperative cowl anti-ice valve OPEN.
Refer to GIV Aircraft Maintenance Manual, Chapter 30.
(4) Select ENG BLEED AIR of running engine to ON. Ensure
the ISOLATION valve is OPEN by either selecting the
START MASTER switch to ON or the ISOLATION valve
switch to OPEN.
(5) Ensure area behind airplane is clear.

Continued on next page 

REVISION 24 (RE-ISSUE) NORMAL PROCEDURES

Mar 17/10 Page NG - 21
 Quick Reference Handbook
Operational Procedures With Cowl Anti-Ice Valve
Locked Open, ctd… OM 09-03-50

(6) Increase running engine RPM to approximately 80% HP

RPM. This will provide a bleed air manifold pressure of
approximately 30 psi.
NOTE: Time with bleed air manifold pressure at 30 psi before
starting the remaining engine should be kept to a minimum.
(7) Start engine having inoperative cowl anti-ice valve using
normal procedures.
(8) After engine start is complete, retard power lever to idle,
close ISOLATION valve and complete the After Starting
Engines checklist (page ND-1).
(9) The autothrottle will operate normally. With the cowl anti-
ice valve locked OPEN and pressurized, the respective
COWL ANTI ICE switch must be selected ON to ensure
the autothrottle computes proper EPR settings.
(10) For takeoff operations using autothrottle, Takeoff
Initialization (TAKEOFF INIT) must be properly addressed.
COWL ANTI-ICE must be initialized as “ON” for TAKEOFF
INIT and both COWL ANTI ICE switches must be selected
ON whenever the cowl anti-ice valve is locked OPEN for
takeoff. This also applies to Landing Initialization
(LANDING INIT).
(11) With the cowl anti-ice valve locked OPEN and pressurized,
expect COWL ANTI ICE pressure to be approximately 5
psi less than the BLEED AIR pressure supplying the valve.
(12) With the cowl anti-ice valve locked OPEN and pressurized,
expect a nominal 5% decrease in range for long range
flights.
(13) Record the event and ambient temperature at both the
departure and arrival airports in the Airplane Log Book.
(14) After landing and shutdown, manually disengage lock and
return cowl anti-ice valve to the CLOSED position.

END

NORMAL PROCEDURES REVISION 24 (RE-ISSUE)

Page NG - 22 Mar 17/10
Quick Reference Handbook
APU Inflight Operation AFM 2-08-120

NOTE: Maximum altitude for guaranteed APU start is 15,000 ft. The APU
may start between 15,000 ft and 20,000 ft. Slow to a maximum airspeed of
250 KCAS.
1. Left / Right Batteries ................................................................... ON
2. APU Fire Test ................................................................ PERFORM
3. APU Master ................................................................................ ON
4. APU Oil Pressure light ............................................. ILLUMINATED
NOTE: For airplanes having ASC 465, the APU Electronic Control Unit
(ECU) performs a 12 second Built-In-Test (BIT) after the APU Low Oil
Pressure light illuminates. Expect a delay in starter activation if the APU
Start switch is activated during the APU ECU BIT.
5. APU Start ............................................... PRESS (MOMENTARILY)
CAUTION: APU STARTER IS LIMITED TO THREE (3)
CONSECUTIVE START ATTEMPTS OF THIRTY (30) SECONDS EACH
FOLLOWED BY A TWENTY (20) MINUTE COOL DOWN. THREE (3)
ADDITIONAL START ATTEMPTS MAY BE MADE, AFTER WHICH A
ONE (1) HOUR COOL DOWN PERIOD MUST BE OBSERVED
BEFORE THE NEXT FULL STARTER CYCLE IS ATTEMPTED.
When APU reaches operating speed (100 % RPM).
6. Electrical Master Auxiliary Power ............................................... ON
7. Electrical Load ........................................................ AS REQUIRED
Inflight shutdown:
1. Electrical Master Auxiliary Power ............................................. OFF
2. APU STOP ..................................................................... DEPRESS
3. APU MASTER ................................... OFF (RPM LESS THAN 5%)

END

REVISION 24 (RE-ISSUE) NORMAL PROCEDURES

Mar 17/10 Page NG - 23
 Quick Reference Handbook
P-RNAV (Precision RNAV) Procedures AFM 2-08-140

NOTE: These procedures are based on a dual FMS / RNAV capability with
the standard worldwide database installed in the airplane. If dispatching with
a single FMS / RNAV capability, verify that the P-RNAV procedure allows the
procedure to be flown with a single system.

Preflight:
1. Verify database is current and is applicable to the region.
2. Verify RAIM availability for the procedure to be flown.
3. Confirm correct Initial Position has been entered in all FMSs.
4. Check and verify active flight plan (CDU and Map Display) to the
available charts, SID, or other applicable documents.
5. The addition of pilot entered waypoints to the P-RNAV procedure
is prohibited. The procedure may only be altered by radar vectors
or “Direct-To” clearances.
Departure:
1. Prior to takeoff, verify FMS RNAV is available and operating
correctly.
2. Prior to takeoff, update FMS Runway Position. If departing from
an intersection, perform a manual Position Update to the current
GPS position. If GPS is unavailable, depart using conventional
navigation until DME / DME updating is attained and FMS
position is updated. A transition to P-RNAV is then permitted.
3. After takeoff and where feasible, monitor flight progress with
reference to conventional NAVAIDs using the PFD and Map
Display in conjunction with the CDU.
Arrival:
1. Prior to arrival, verify that the correct terminal procedure has been
loaded.
2. Check and verity active flight plan (CDU and Map Display) to the
available charts, SID, or other applicable documents.
3. The addition of pilot entered waypoints to the P-RNAV procedure
is prohibited. The procedure may only be altered by radar vectors
or “Direct-To” clearances.
Continued on next page 

NORMAL PROCEDURES REVISION 24 (RE-ISSUE)

Page NG - 24 Mar 17/10
Quick Reference Handbook
P-RNAV (Precision RNAV) Procedures, ctd… AFM 2-08-140

4. During the procedure, monitor flight progress with reference to

conventional NAVAIDs using the PFD and Map Display in
conjunction with the CDU.
Contingencies:
In the event failure of the RNAV system components including the
autopilot and / or flight director, multiple system failures, navigation
sensors failure, or extended coasting on the IRS position, the flight
crew shall notify ATC of degraded navigation capability.
In the event of lost communications, continue with the P-RNAV
procedure in accordance with the published lost communication
procedure.
In the event of the complete loss of P-RNAV capability, notify ATC
and continue navigation using either the IRS navigation mode of the
FMS or conventional VOR / DME NAVAIDs.

END

REVISION 24 (RE-ISSUE) NORMAL PROCEDURES

Mar 17/10 Page NG - 25
 Quick Reference Handbook
Notes

NORMAL PROCEDURES REVISION 24 (RE-ISSUE)

Page NG - 26 Mar 17/10
Quick Reference Handbook
Engine Fuel Grades AFM 1-12-30

Fuel conforming to any of the following specifications is approved for

use. Fuels conforming to ASTM Specification ES2-74 are also
eligible. Mixing of fuels is permissible.

KEROSENE TYPE
AMERICAN BRITISH CANADIAN
ASTM D1655-89, Jet A DEF STAN 91-87 CAN/CGSB-3.23-M86
ASTM D1655-89, Jet A-1 DEF STAN 91-91
MIL-T-83133A, Grade (JP-8)
FRENCH USSR I.A.T.A.
AIR 3405/C T-1, TS-1, RT (GOST 10277-86) 1988 Kerosene Type
T-7 (GOST 12308-66)
WIDE CUT JP-4 TYPE
AMERICAN BRITISH CANADIAN
ASTM D1655-89, Jet B DEF STAN 91-88 CAN/CGSB-3.22-M86
MIL-T-5624N, Grade JP-4
FRENCH I.A.T.A.
AIR 3407/B 1987 JP-4
HIGH FLASH POINT JP-5 TYPE
AMERICAN BRITISH CANADIAN
MIL-T-5624N, Grade JP-5 DEF STAN 91-86 CAN 3-GP-24Ma
FRENCH
AIR 3404/C

NOTE: The use of Wide Cut fuel as agreed to by the Operator, Rolls-
Royce, and the appropriate Airworthiness Authority may result in a
reduction in HP Fuel Pump Life.

Hydraulic Fluids AFM 1-12-10

The following fire resistant Type IV hydraulic fluids are approved for
use:
• HyJet IV
• HyJet IV-A
• Skydrol LD-4
• Skydrol 500B-4

REVISION 26 NORMAL PROCEDURES

Oct 5 2011 Page NH - 1
 Quick Reference Handbook
Fuel Additives AFM 1-12-40

The following fuel additives (in addition to those included in DEF

STAN Specifications) are approved by Rolls-Royce, subject to
limitations stated:
1. Corrosion Inhibitor/Lubricity Aids:
Concentration Range:
lb/42,035 US Gallons lb/35,000 IMP Gallons
Fuel Additive Minimum Maximum
APOLLO PRI 19 3 (9 mg/liter) 8 (23 mg/liter)
DUPONT DCI-4A 3 (9 mg/liter) 8 (23 mg/liter)
HITEC 580 3 (9 mg/liter) 8 (23 mg/liter)
HITEC 515 4 (11 mg/liter) 7.5 (21 mg/liter)
TOLAD 245 7.5 (21 mg/liter) 12 (34 mg/liter)
NOTE: Minimum requirement is to ensure that sufficient additive is available
when it is required to act as a lubricity aid.
2. Anti-Icing Additive:
DEF STAN 68-252, MIL-I-27686E, or MIL-I-85470 or any direct
equivalent in concentrations not exceeding 0.15 percent by
volume.
3. Static Dissipater Additive:
A. Shell A.S.A. 3 in concentrations of not more than 1.00 part per
million.
B. Stadis 450 maximum concentration not more than 3.00 parts
per million.
4. Anti-Microbiological Additive:
A. Methyl Cellosolve may be used. Refer to GIV Maintenance
Manual, Chapter 28 for additive application procedures.
B. Biobor JF may be used. Refer to GIV Maintenance Manual,
Chapter 28 for additive application procedures.
C. Kathon FP 1.5 may be used. Refer to GIV Maintenance
Manual, Chapter 28 for additive application procedures.
NOTE: Under certain conditions solid matter may be precipitated
from fuel containing Biobor JF or Kathon FP 1.5 during flight. The fuel
differential pressure signals should be carefully monitored in flight
immediately following its use in the airplane tanks. See Rolls Royce
Tay Maintenance Manual M-TAY-1RR for recommended procedures to
be followed when using Biobor JF or Kathon FP 1.5.

NORMAL PROCEDURES REVISION 26

Page NH - 2 Oct 5 2011
Quick Reference Handbook

Oil Grades: Engine / Starter / APU AFM 1-12-50

WARNING: LUBRICATING OIL IS TOXIC TO SKIN, EYES, AND

RESPIRATORY TRACT. SKIN AND EYE PROTECTION IS REQUIRED.
AVOID REPEATED OR PROLONGED CONTACT. USE IN A WELL
VENTILATED AREA.

CAUTION: USE ONLY BRAND NAMES SPECIFICALLY

AUTHORIZED. USE OF ANY UNAPPROVED OIL REQUIRES
AUTHORIZATION OF EQUIPMENT MANUFACTURER.
NOTE: Mixing of oils is not recommended but brands may be mixed if
operationally essential. Complete drainage of one oil and replacement with a
different brand is not considered mixing of oils.
Oil of the brands below, when reclaimed to approved Rolls-Royce
standards for appropriate viscosity grade, are approved for use in the
TAY engine.
The following oils are approved for common usage in the engine and
APU:

3 Centistoke Oils 5 Centistoke Oils

Aeroshell Turbine Oil 390 Royco/Aeroshell Turbine Oil 500
Castrol 3C Gas Turbine Oil Aeroshell Turbine Oil 560
Castrol 325 Gas Turbine Oil Castrol 5000 Gas Turbine Oil
Esso / Exxon Turbo Oil 2389 Esso / Exxon Turbo Oil 2380
Mobil Jet II
Mobil 254

Refer to the following manuals for oils approved for specific usage in
the engine, starter or APU:
• ENGINE: U.K. CAA Approved Rolls-Royce Tay Operating
Instructions (F-TAY-1RR) and associated Service Bulletins
• STARTER: Garrett Starter Maintenance Manual 80-10-53
• APU: Garrett Maintenance Manual No. 49-21-89 for APU
Model No. GTCP36-100(G)

REVISION 26 NORMAL PROCEDURES

Oct 5 2011 Page NH - 3
 Quick Reference Handbook
Conversion Tables

For Length Conversions:

Multiply: By: To Obtain:
Feet 0.3048 Meters
Meters 3.281 Feet
Statute Miles 5,280 Feet
Statute Miles 0.8684 Nautical Miles
Statute Miles 1.609 Kilometers
Nautical Miles 6,076.12 Feet
Nautical Miles 1.1516 Statute Miles
Nautical Miles 1.853 Kilometers
Kilometers 3,281 Feet
Kilometers 0.5396 Nautical Miles
Kilometers 0.6214 Statute Miles
Centimeters 0.3937 Inches
Inches 2.54 Centimeters
For Pressure Conversions:
Multiply: By: To Obtain:
Hectopascals (MB) 0.0295 Inches of Mercury
Inches of Mercury 33.86 Hectopascals (MB)
For Volume Conversions:
Multiply: By: To Obtain:
U.S. Gallons 0.83267 Imperial Gallons
U.S. Gallons 3.785 Liters
Imperial Gallons 1.20095 U.S. Gallons
Imperial Gallons 4.546 Liters
Liters 0.2642 U.S. Gallons
Liters 0.2200 Imperial Gallons
For Weight Conversions:
Multiply: By: To Obtain:
Kilograms 2.205 Pounds
Pounds 0.4536 Kilograms
Metric Tons 2205 Pounds
Metric Tons 1000 Kilograms
For Density Conversions:
Multiply: By: To Obtain:
Kilograms / Liter 5.346 Pounds / Gallon
Pounds / Gallon 0.1198 Kilograms / Liter

NORMAL PROCEDURES REVISION 26

Page NH - 4 Oct 5 2011
Quick Reference Handbook
Conversion Tables, ctd…

For Speed Conversions:

Multiply: By: To Obtain:
Knots 1.151 Statute Miles / Hour
Knots 1.8532 Kilometers / Hour
Knots 0.5147 Meters / Second
Statute Miles / Hour 0.8684 Knots
Statute Miles / Hour 1.6093 Kilometers / Hour
Statute Miles / Hour 26.82 Meters / Second
Kilometers / Hour 0.5396 Knots
Kilometers / Hour 0.6214 Statute Miles / Hour
Kilometers / Hour 0.2778 Meters / Second
Meters / Second 1.943 Knots
Meters / Second 2.237 Statute Miles / Hour
Meters / Second 3.600 Kilometers / Hour

Volume and Weight Equivalents

Liquid Lb / U.S. Gal. Kg / U.S. Gal. Kg / Liter
JP4 6.550 2.9711 0.7847
JP5 6.820 3.0935 0.8170
Kerosene 6.840 3.1026 0.8194
Oil 7.400 3.3566 0.8865
Synthetic Oil 7.740 3.5109 0.9273
Water 8.345 3.7853 1.0000

Converting Hectopascals (Millibars) To Inches of Mercury

Hpa +0 +1 +2 +3 +4 +5 +6 +7 +8 +9
(MB) Inches of Mercury (In Hg)
930 27.46 27.49 27.52 27.55 27.58 27.61 27.64 27.67 27.70 27.73
940 27.76 27.78 27.81 27.84 27.87 27.90 27.93 27.96 27.99 28.02
950 28.05 28.08 28.11 28.14 28.17 28.20 28.23 28.26 28.29 28.32
960 28.35 28.38 28.40 28.43 28.46 28.49 28.52 28.55 28.58 28.61
970 28.64 28.67 28.70 28.73 28.76 28.79 28.82 28.85 28.88 28.91
980 28.94 28.97 29.00 29.03 29.05 29.08 29.11 29.14 29.17 29.20
990 29.23 29.26 29.29 29.32 29.35 29.38 29.41 29.44 29.47 29.50
1000 29.53 29.56 29.59 29.62 29.65 29.67 29.70 29.73 29.76 29.79
1010 29.82 29.85 29.88 29.91 29.94 29.97 30.00 30.03 30.06 30.09
1020 30.12 30.15 30.18 30.21 30.24 30.27 30.29 30.32 30.35 30.38
1030 30.41 30.44 30.47 30.50 30.53 30.56 30.59 30.62 30.65 30.68
1040 30.71 30.74 30.77 30.80 30.83 30.86 30.89 30.91 30.94 30.97
1050 31.00 31.03 31.06 31.09 31.12 31.15 31.18 31.21 31.24 31.27

REVISION 26 NORMAL PROCEDURES

Oct 5 2011 Page NH - 5
 Quick Reference Handbook
Conversion Tables, ctd…

Converting Kilometers to Statute Miles or Nautical Miles

KM 1 2 3 4 5 6 7 8 9 10
SM 0.62 1.24 1.86 2.49 3.11 3.73 4.35 4.97 5.59 6.21
NM 0.53 1.08 1.62 2.16 2.70 3.24 3.78 4.32 4.85 5.40

Converting Millimeters To Inches

+0 +1 +2 +3 +4 +5 +6 +7 +8 +9
MM
Inches
700 27.56 27.60 27.64 27.68 27.72 27.76 27.80 27.83 27.87 27.91
710 27.95 27.99 28.03 28.07 28.11 28.15 28.19 28.23 28.27 28.31
720 28.35 28.39 28.43 28.46 28.50 28.54 28.58 28.62 28.66 28.70
730 28.74 28.78 28.82 28.86 28.90 28.94 28.98 29.02 29.06 29.09
740 29.13 29.17 29.21 29.25 29.29 29.33 29.37 29.41 29.45 29.49
750 29.53 29.57 29.61 29.65 29.68 29.72 29.76 29.80 29.84 29.88
760 29.92 29.96 30.00 30.04 30.08 30.12 30.16 30.20 30.24 30.28
770 30.31 30.35 30.39 30.43 30.47 30.51 30.55 30.59 30.63 30.67
780 30.71 30.75 30.79 30.83 30.87 30.91 30.94 30.98 31.02 31.06
790 31.10 31.14 31.18 31.22 31.26 31.30 31.34 31.38 31.42 31.46

Temperature Conversion
°F -50 -45 -40 -35 -30 -25 -20 -15 -10 -5
°C -45.6 -42.8 -40.0 -37.2 -34.4 -31.7 -28.9 -26.1 -23.3 -20.6
°F 0 5 10 15 20 25 30 35 40 45
°C -17.8 -15.0 -12.2 -9.4 -6.7 -3.9 -1.1 1.7 4.4 7.2
°F 50 55 60 65 70 75 80 85 90 95
°C 10.0 12.8 15.6 18.3 21.1 23.9 26.7 29.4 32.2 35.0
°F 100 105 110 115 120 °F = (°C + 17.8) x 1.80
°C 37.8 40.6 43.3 46.1 48.9 °C = (°F - 32) x 0.5556
NOTE: For interpolation purposes, 1.8°F = 1°C.

NORMAL PROCEDURES REVISION 26

Page NH - 6 Oct 5 2011
Quick Reference Handbook
Conversion Tables, ctd…

Reported Visibility / RVR Cross Reference

Meters 45 46 75 76 90 91
Feet 148 150 246 250 295 300
Meters 150 152 175 182 200 213
Feet 492 500 574 600 656 700
Meters 244 300 305 350 366 402
Feet 800 984 1,000 1,148 1,200 1,320
Miles ---- ---- ---- ---- ---- ¼
Meters 427 488 500 549 550 600
Feet 1,400 1,600 1,640 1,800 1,804 1,969
Miles ---- ---- ---- ---- ---- ----
Meters 610 670 720 731 792 805
Feet 2,000 2,200 2,362 2,400 2,600 2,640
Miles ---- ---- ---- ---- ---- ½
Meters 853 900 914 1,067 1,200 1,207
Feet 2,800 2,953 3,000 3,500 3,937 3,960
Miles ---- ---- ---- ---- ---- ¾
Meters 1,219 1,372 1,500 1,524 1,609 1,676
Feet 4,000 4,500 4,921 5,000 5,280 5,500
Miles ---- ---- ---- ---- 1 ----
Meters 1,829 2,012 2,414 2,816 3,219 3,621
Feet 6,000 6,600 7,920 9,240 10,560 11,880
Miles ---- 1¼ 1½ 1¾ 2 2¼
Meters 4,023 4,426 4,828 NOTE: These values are equivalent
Feet 13,200 14,520 15,840 for operational purposes and are
applicable to both takeoff and
Miles 2½ 2¾ 3 landing minima.

REVISION 26 NORMAL PROCEDURES

Oct 5 2011 Page NH - 7
 Quick Reference Handbook
Conversion Tables, ctd…

Converting Kilograms to Pounds and Pounds to Kilograms

In Pounds Value In Kilos In Pounds Value In Kilos
2.2 1 0.45 1323.0 600 272.16
4.4 2 0.91 1543.5 700 317.52
6.6 3 1.36 1764.0 800 362.88
8.8 4 1.81 1984.5 900 408.24
11.0 5 2.27 2205 1000 454
13.2 6 2.72 4410 2000 907
15.4 7 3.18 6615 3000 1361
17.6 8 3.63 8820 4000 1814
19.8 9 4.08 11025 5000 2268
22.1 10 4.54 13230 6000 2722
44.1 20 9.07 15435 7000 3175
66.2 30 13.61 17640 8000 3629
88.2 40 18.14 19845 9000 4082
110.3 50 22.68 22050 10000 4536
132.3 60 27.22 44100 20000 9072
154.4 70 31.75 66150 30000 13608
176.4 80 36.29 88200 40000 18144
198.5 90 40.82 110250 50000 22680
220.5 100 45.36 132300 60000 27216
441.0 200 90.72 154350 70000 31752
661.5 300 136.08 176400 80000 36288
882.0 400 181.44 198450 90000 40824
1102.5 500 226.80 220500 100000 45360

All values on the above table are additive as demonstrated in the

following example:
To find the value in kilograms for 71,586 pounds, add the values
in the kilos column for:
70,000 (31,752.00)
1,000 (454.00)
500 (226.80)
80 (36.29)
6 (2.72)
71,586 = 32,471.81 kilograms

NORMAL PROCEDURES REVISION 26

Page NH - 8 Oct 5 2011
Quick Reference Handbook
Conversion Tables, ctd…

Meters Feet Meters Feet Meters Feet Meters Feet

15,100 49,500 7,600 24,900 4,900 16,100 2,200 7,200
14,100 46,300 7,500 24,600 4,800 15,700 2,100 6,900
13,100 43,000 7,400 24,300 4,700 15,400 2,000 6,600
12,800 42,000 7,300 24,000 4,600 15,100 1,900 6,200
12,500 41,000 7,200 23,600 4,500 14,800 1,800 5,900
12,200 40,000 7,100 23,300 4,400 14,400 1,700 5,600
12,100 39,700 7,000 23,000 4,300 14,100 1,600 5,200
11,900 39,000 6,900 22,600 4,200 13,800 1,500 4,900
11,600 38,100 6,800 22,300 4,100 13,500 1,400 4,600
11,300 37,100 6,700 22,000 4,000 13,100 1,300 4,300
11,100 36,400 6,600 21,700 3,900 12,800 1,200 3,900
10,900 35,800 6,500 21,300 3,800 12,500 1,100 3,600
10,600 34,800 6,400 21,000 3,700 12,100 1,000 3,300
10,300 33,800 6,300 20,700 3,600 11,800 900 3,000
10,100 33,100 6,200 20,300 3,500 11,500 850 2,800
9,900 32,500 6,100 20,000 3,400 11,200 800 2,600
9,600 31,500 6,000 19,700 3,300 10,800 750 2,500
9,300 30,500 5,900 19,400 3,200 10,500 700 2,300
9,100 29,900 5,800 19,000 3,100 10,200 650 2,100
8,900 29,200 5,700 18,700 3,000 9,800 600 2,000
8,600 28,200 5,600 18,400 2,900 9,500 550 1,800
8,300 27,200 5,500 18,000 2,800 9,200 500 1,600
8,100 26,600 5,400 17,700 2,700 8,900 450 1,500
8,000 26,200 5,300 17,400 2,600 8,500 400 1,300
7,900 25,900 5,200 17,100 2,500 8,200 350 1,100
7,800 25,600 5,100 16,700 2,400 7,900 300 1,000
7,700 25,300 5,000 16,400 2,300 7,500

CAUTION: DO NOT USE FOR APPROACH MINIMA, AS CHART VALUES ARE

ROUNDED TO NEAREST 100 FEET.
Note: Because of rounding differences, most metric flight levels can be satisfied by two
equivalent feet values. Of the two, the closest value in feet is used in this table. Example:
43,000 or 42,900 feet on the altitude pre-selector window will be shown as 13,100 meters
on the PFD.
Note: This chart is not applicable in the People’s Republic of China (PRC). For the PRC,
see Figure 2: China RVSM Flight Level Allocation Scheme (FLAS) Table.

REVISION 26 NORMAL PROCEDURES

Oct 5 2011 Page NH - 9
 Quick Reference Handbook
Conversion Tables, ctd…

Table of U.S. Standard Atmospheres

ALT °F °C IN HG MB ALT °F °C IN HG MB
43,000 -69.7 -56.5 4.82 163 20,000 -12.2 -24.6 13.76 466
42,000 -69.7 -56.5 5.05 171 19,000 -8.7 -22.6 14.35 486
41,000 -69.7 -56.5 5.30 179 18,000 -5.1 -20.6 14.95 506
40,000 -69.7 -56.5 5.56 188 17,000 -1.6 -18.7 15.58 528
39,000 -69.7 -56.5 5.83 197 16,000 2.0 -16.7 16.22 549
38,000 -69.7 -56.5 6.12 207 15,000 5.5 -14.7 16.89 572
37,000 -69.7 -56.5 6.42 217 14,000 9.1 -12.7 17.58 595
36,000 -69.2 -56.2 6.73 228 13,000 12.7 -10.7 18.30 620
35,000 -65.6 -54.2 7.06 239 12,000 16.2 -8.8 19.03 644
34,000 -62.1 -52.3 7.40 251 11,000 19.8 -6.8 19.80 670
33,000 -58.5 -50.3 7.76 263 10,000 23.3 -4.8 20.58 697
32,000 -54.9 -48.3 8.12 275 9,000 26.9 -2.8 21.39 724
31,000 -51.4 -46.3 8.51 288 8,000 30.5 -0.8 22.23 753
30,000 -47.8 -44.3 8.90 301 7,000 34.0 1.1 23.09 782
29,000 -44.3 -42.4 9.31 315 6,000 37.6 3.1 23.98 812
28,000 -40.7 -40.4 9.74 330 5,000 41.2 5.1 24.90 843
27,000 -37.2 -38.4 10.18 345 4,000 44.7 7.1 25.84 875
26,000 -33.6 -36.4 10.64 360 3,000 48.3 9.0 26.82 908
25,000 -30.1 -34.5 11.12 377 2,000 51.9 11.0 27.82 942
24,000 -26.5 -32.5 11.61 393 1,000 55.4 13.0 28.86 977
23,000 -22.9 -30.5 12.12 410 SL 59.0 15.0 29.92 1,013
22,000 -19.4 -28.6 12.65 428 -1,000 62.6 17.0 31.02 1,050
21,000 -15.8 -26.6 13.20 447 -2,000 66.1 18.9 32.15 1,089

NOTE: Values represent Standard Day conditions.

Quick Conversion for JET A Aviation Turbine Fuel

Pounds Liters Imp. Gal. U.S. Gal Pounds Liters Imp. Gal. U.S. Gal
50 28 6 7 4,500 2,557 563 676
100 57 13 16 5,000 2,841 625 751
200 114 25 30 6,000 3,410 750 901
300 170 38 46 7,000 3,978 875 1,051
400 227 50 60 8,000 4,546 1,000 1,201
500 284 63 76 9,000 5,114 1,125 1,351
1,000 568 125 150 10,000 5,683 1,250 1,501
1,500 852 188 226 12,000 6,819 1,500 1,801
2,000 1,137 250 300 14,000 7,956 1,750 2,102
2,500 1,421 313 376 16,000 9,092 2,000 2,402
3,000 1,705 375 450 18,000 10,229 2,250 2,702
3,500 1,989 438 526 20,000 11,365 2,500 3,002
4,000 2,273 500 600

NORMAL PROCEDURES REVISION 26

Page NH - 10 Oct 5 2011
Quick Reference Handbook

China RVSM Flight Level Allocation Scheme (FLAS)

Table

Cleared Select
Meter FL FL in Feet
1550 0 5090 0
1490 0 4890 0
1430 0 4690 0
1370 0 4490 0
1310 0 4300 0
1250 0 41100 41,100
40,100 1220 0 4010 0
1190 0 3910 0 39,100
38,100 1160 0 3810 0
1130 0 3710 0 37,100
36,100 1100 0 3610 0
RVSM airspace 1070 0 3510 0 35,100 RVSM airspace
34,100 1040 0 3410 0
1010 0 3310 0 33,100
32,100 980 0 3210 0
950 0 31100 31,100
30,100 920 0 3010 0
890 0 2910 0 29,100
WESTBOUND (180 - 359 )

EASTBOUND (000 - 179 )

840 0 2760 0
810 0 2660 0
780 0 2560 0
180 to 359 750 0 2460 0 0 to 179
720 0 2360 0
690 0 2260 0
660 0 2170 0
IMPORTANT NOTES 630 0 2070 0
ATC will issue the 600 0 1970 0 The aircraft shall be flown
Flight Level clearance 570 0 1870 0 using the flight level in
in meters 540 0 1770 0 FEET.
510 0 1670 0
Pilots shall use the China 480 0 1570 0 Pilots shou ld be aware
RVSM FLAS table to 450 0 1480 0 that due to the round ing
determine the correspon - 420 0 1380 0 differences, the metric
ding flight level in feet. 390 0 1280 0 readou t of the onboa rd
360 0 1180 0 avionics will not necessarily
330 0 1080 0 correspond to the cleared
300 0 980 0 Flight Level in meters
270 0 890 0 however the difference will
DO NOT USE 240 0 790 0
FOR APPROACH MINIMA, 210 0 690 0 never be more than
AS CHART VALUES 180 0 590 0 30 meters.
ARE ROUNDED TO 150 0 490 0
NEAREST 100 FEET. 120 0 390 0
900 300 0
600 200 0
500 160 0
400 130 0
300 100 0
200 700
100 300 82814 F00

Figure 2

REVISION 26 NORMAL PROCEDURES

Oct 5 2011 Page NH - 11
 Quick Reference Handbook

Noise Standards OM APPENDIX D

The Effective Perceived Noise Levels (EPNL) comply with the

requirement of 14 CFR, Part 36, which are essentially the same as the
requirements of ICAO Annex 16, Volume 1, Chapter 3. Noise levels
established in compliance with 14 CFR, Part 36 are:
Noise Limits
Noise 14 CFR Part 36
Levels ICAO Annex 16
(EPNdB) (EPNdB)
Flyover (Flaps 20) 79.0 89
Lateral (Flaps 20) 87.6 94
Approach (Flaps 39) 93.3 98

No determination has been made by the Federal Aviation

Administration that the noise levels of this airplane are or should be
acceptable or unacceptable for operation at, into, or out of any airport.

END

NORMAL PROCEDURES REVISION 26

Page NH - 12 Oct 5 2011
Quick Reference Handbook

Battery Integrity Check OM 2A-24-00

1. BATT 1 / BATT 2 Switches ............................... DEPRESSED (ON)

2. EPMP .............................................................................. OBSERVE
A. BATT 1 / BATT 2 Switchlights ............................ ILLUMINATED
B. ESS DC BUS BATT Switchlight ........................ ILLUMINATED
C. ESS AC BUS E INV Switchlight ........................ ILLUMINATED
D. ESS Voltmeter Switchlight ........................... DEPRESSED (ON)
E. AC VOLTS / FREQ / DC VOLTS Readings .... 115 / 400 / 22-27
F. CHGR FAIL Lights ............................................. ILLUMINATED
G. BATTERY 1 / 2 Ammeters ................................. DISCHARGING
H. BATTERY 1 / 2 Voltmeters .................. INDICATING VOLTAGE
3. BATT 1 Switch ................................................... EXTENDED (OFF)
4. EPMP .............................................................................. OBSERVE
A. BATT 1 Switchlight .......................................... EXTINGUISHED
B. BATTERY 1 Ammeter .......................................................... 000
C. BATTERY 2 Ammeter ....................................... DISCHARGING
D. BATTERY 2 Voltmeter .................................. 22V DC MINIMUM
5. BATT 1 Switch .................................................. DEPRESSED (ON)
6. BATT 2 Switch ................................................... EXTENDED (OFF)
7. EPMP .............................................................................. OBSERVE
A. BATT 2 Switchlight .......................................... EXTINGUISHED
B. BATTERY 2 Ammeter .......................................................... 000
C. BATTERY 1 Ammeter ....................................... DISCHARGING
D. BATTERY 1 Voltmeter .................................. 22 VDC MINIMUM
8. BATT 2 Switch .................................................. DEPRESSED (ON)
9. EPMP .............................................................................. OBSERVE
A. BATT 1 / BATT 2 Switchlights ............................ ILLUMINATED
B. BATTERY 1 / 2 Ammeters ................................. DISCHARGING
C. BATTERY 1 / 2 Voltmeters .................. INDICATING VOLTAGE

END

REVISION 24 (RE-ISSUE) NORMAL PROCEDURES

Mar 17/10 Page NI - 1
 Quick Reference Handbook
Pressurization System Check OM 2A-21-20

Test Conditions:
1. Main Entrance Door .............................................................. OPEN
2. L ENG / R ENG / APU BLEED AIR .........................AS REQUIRED
3. FLIGHT / LANDING Switch ............................. LANDING (GREEN)
4. AUTO / MANUAL Switch ....................................... AUTO (GREEN)
5. ADC #1 / ADC #2 Switch.................................... ADC #1 (GREEN)
6. Outflow Valve Position Indicator ........................................... OPEN
Procedure:
1. FLIGHT / LANDING Switch ................................ FLIGHT (GREEN)
2. Outflow Valve Position Indicator ..... DRIVING TOWARD CLOSED
When outflow valve position indicator reaches halfway closed:
3. ADC #1 / ADC #2 Switch.................................... ADC #2 (AMBER)
4. Outflow Valve Position Indicator ............ DRIVES FULLY CLOSED
5. FLIGHT / LANDING Switch ............................. LANDING (GREEN)
6. Outflow Valve Position Indicator .......... DRIVING TOWARD OPEN
When outflow valve position indicator reaches halfway closed:
7. ADC #1 / ADC #2 Switch.................................... ADC #1 (GREEN)
8. Outflow Valve Position Indicator ......... DRIVING FURTHER OPEN
Before outflow valve position indicator reaches fully open:
9. AUTO / MANUAL Switch .................................. MANUAL (AMBER)
NOTE: The motor power light (round amber light) will also illuminate.
10. Outflow Valve ..................... POSITION USING MAN HOLD KNOB
11. AUTO / MANUAL Switch ....................................... AUTO (GREEN)
12. Outflow Valve .............................................. VERIFY FULLY OPEN
Final Configuration:
1. FLIGHT / LANDING Switch ............................. LANDING (GREEN)
2. AUTO / MANUAL Switch ....................................... AUTO (GREEN)
3. ADC #1 / ADC #2 Switch.................................... ADC #1 (GREEN)
4. Outflow Valve Position Indicator ........................................... OPEN
5. Motor Power Light (Round Amber Light) ......................... EXTINGUISHED

END

NORMAL PROCEDURES REVISION 24 (RE-ISSUE)

Page NI - 2 Oct 5 2011
Quick Reference Handbook
Fuel System Check OM 2A-28-30

Test Conditions:
1. L / R Remote Fueling Shutoff Switches .......... OPEN (EXTENDED)
2. Crossflow Valve ................................................................ CLOSED
3. L MAIN Boost Pump ................................................................... ON
4. Intertank Valve .................................................................. CLOSED
5. L FUEL PRESS LOW CAS Message ................ NOT DISPLAYED
6. R FUEL PRESS LOW CAS Message ......................... DISPLAYED
Procedure:
1. L / R Remote Fueling Shutoff Switches ...CLOSED (DEPRESSED)
NOTE: Verify CLSD legend illuminates in switches.
2. L / R Remote Fueling Shutoff Switches .......... OPEN (EXTENDED)
3. Crossflow / Intertank Valves ................ OPEN SIMULTANEOUSLY
4. Indications....................................................................... OBSERVE
A. Crossflow Valve Switchlight Bar ......................... ILLUMINATED
B. Intertank Valve Switchlight Bar ........................... ILLUMINATED
C. FUEL XFLOW OPEN CAS Message ..................... DISPLAYED
D. FUEL INT TNK OPEN CAS Message .................... DISPLAYED
5. R FUEL PRESS LOW CAS Message ................ NOT DISPLAYED
6. L MAIN Boost Pump ................................................................. OFF
A. L ALT Boost Pump................................................................. ON
B. L-R FUEL PRESS LOW CAS Messages ...................................
...........DISPLAYED MOMENTARILY, THEN NOT DISPLAYED
7. L ALT Boost Pump ................................................................... OFF
A. R MAIN Boost Pump ............................................................. ON
B. L-R FUEL PRESS LOW CAS Messages ...................................
...........DISPLAYED MOMENTARILY, THEN NOT DISPLAYED
8. R MAIN Boost Pump ................................................................ OFF
A. R ALT Boost Pump ................................................................ ON
B. L-R FUEL PRESS LOW CAS Messages ...................................
...........DISPLAYED MOMENTARILY, THEN NOT DISPLAYED
9. Crossflow / Intertank Valves .............. CLOSE SIMULTANEOUSLY

REVISION 24 (RE-ISSUE) NORMAL PROCEDURES

Mar 17/10 Page NI - 3
 Quick Reference Handbook
10. Indications ...................................................................... OBSERVE
A. Crossflow Valve Switchlight Bar ...................... EXTINGUISHED
B. Intertank Valve Switchlight Bar ....................... EXTINGUISHED
C. FUEL XFLOW OPEN CAS Message .............NOT DISPLAYED
D. FUEL INT TNK OPEN CAS Message ...........NOT DISPLAYED
NOTE: Steps A through D will occur simultaneously.
11. L FUEL PRESS LOW CAS Message ......................... DISPLAYED
12. L MAIN Boost Pump ................................................................... ON
13. L FUEL PRESS LOW CAS Message ................ NOT DISPLAYED
14. R ALT Boost Pump................................................................... OFF
15. R FUEL PRESS LOW CAS Message ......................... DISPLAYED

END

Oxygen Crew Mask / Regulator Preflight Test OM 2A-35-20

NOTE: This procedure allows the flight crew the ability to perform a
complete preflight check without having to remove the mask/regulator from
its stowage compartment.
1. Select the crew oxygen system toggle valve switch to ON.
2. Check the crew oxygen system supply pressure.
3. On the crew mask/regulator stowage compartment, perform the
following based upon the type of crew mask/regulator installed:
A. For the EROS MXP 100, depress the RESET TEST control
lever on the LH door in the direction of the arrow. Oxygen is
then supplied to the mask/regulator assembly.
B. For the EROS MXP 300, depress the PRESS TO TEST AND
RESET control lever on the LH door in the direction of the
arrow. Oxygen is then supplied to the mask/regulator
assembly.
4. MXP 100 only: observe that a white band is visible at the top of
the RESET TEST control lever (LH door).
5. Observe that the flow indicator (blinker) momentarily displays a
yellow cross (+), then returns to black. This indicates the regulator
is leak-tight. If the blinker continuously displays the yellow cross,
a leak in the system should be assumed and investigated.
NORMAL PROCEDURES REVISION 24 (RE-ISSUE)
Page NI - 4 Oct 5 2011
Quick Reference Handbook
6. While holding the MXP 100 RESET TEST control lever (or MXP
300 PRESS TO TEST AND RESET control lever), depress and
hold the red PRESS TO TEST button on the mask regulator for
one (1) second while performing steps A and B below.
A. Observe that the blinker momentarily displays a yellow cross,
then returns to black. This indicates the regulator demand
mechanism is working properly.
B. While holding the MXP 100 RESET TEST control lever (or
MXP 300 PRESS TO TEST AND RESET control lever) and
red PRESS TO TEST button, microphone integrity must be
checked by listening for oxygen flow noise through the
communication set.
7. Release the PRESS TO TEST button on the mask regulator.
8. Release the MXP 100 RESET TEST control lever (or MXP 300
PRESS TO TEST AND RESET control lever):
A. MXP 100 Only: observe the white band (top of RESET TEST
control lever, LH door) disappears.
B. Observe that oxygen flow ceases. Downstream pressure will
be vented to ambient.
9. Select the crew oxygen system toggle valve switch to OFF, if
desired.
NOTE: The MXP 100 RESET TEST control lever (or MXP 300
PRESS TO TEST AND RESET control lever) may also be used
for shutting off the supply to the mask/regulator assembly in the
event of a failure. Prior to depressing the MXP 100 REST TEST
control lever (or MXP 300 PRESS TO TEST AND RESET control
lever), close the door.

END

REVISION 24 (RE-ISSUE) NORMAL PROCEDURES

Mar 17/10 Page NI - 5
 Quick Reference Handbook
Cockpit Voice Recorder (CVR) Test GAC

1. Ensure a COMM radio is tuned to a continuous output frequency,

such as ATIS.
2. Plug headset into CVR headset jack.
3. Ensure ATIS is heard through CVR headset jack.
4. Snap fingers or clap hands near the Cockpit Area Microphone
(CAM); ensure CAM audio is heard through CVR headset jack.
(Some delay will be present.)
5. Push the TEST button; ensure you hear a tone through the CVR
headset jack and ensure the meter needle jumps.

END

Display Controller Test GAC

On the first flight of each day, select the TEST page and perform
the following tests:
1. Check appropriate pages on the display controller to confirm
desired functions have been selected.
2. EFIS (each pilot, respective side) .......................................... TEST
The EFIS test can be initiated using the on-side display controller,
provided airspeed data is valid and less than 60 knots, and the
airplane is on the ground. Selecting EFIS TEST results in the
following annunciations:
• DU 1 / 6 (PFDs):
• IRS – indicates failure
• Air Data (Airspeed / AOA / Altitude / VS) – red X
• Flight Director – amber FD displayed
• Comparison Monitor Annunciators – active, not all shown
• Radio Altitude / Distance Display / Heading – amber dashes
• Vertical Deviation Display – red X (if frequency tuned and
NAV selected for display)
• AOA – removed
• Bearing Pointers – removed (except for ADF / LASERTRAK
/ FMS / NMS)
• ATT FAIL / HDG FAIL messages – displayed
NORMAL PROCEDURES REVISION 24 (RE-ISSUE)
Page NI - 6 Oct 5 2011
Quick Reference Handbook
• DU 2 / 5 (NDs):
• HDG FAIL / VERTICAL ALERT / TRK CHG / OFFSET –
displayed
• HDG / SAT / TAS – amber dashes
• Current GSPD – displayed
3. EICAS ..................................................................................... TEST
Performing an EICAS test causes the three-chime aural warning
to sound and the master warning and caution acknowledgement
switches (MASTER WARN “W” AND “C”) to illuminate. The
adjacent AP OFF amber annunciator light also illuminates.
Selecting EICAS TEST results in the following annunciations:
• DU 3 (Engine Instruments):
Amber dashes will be substituted for digits for the left engine:
• EPR • LP EVM
• TGT • HP EVM
• LP RPM • COMB Hydraulics
• HP RPM • UTIL Hydraulics
• FF • ENG FUEL TEMP
• OIL PRESS • L FUEL QTY
• OIL TEMP • Total FUEL QTY
The following indications will be shown for the right engine:
• EPR – current value • FUEL TEMP – 409°
• TGT – 2047° (red) • R FUEL QTY – 0 (amber)
• LP RPM –163.8 (red) • OIL PRESS – 0
• HP RPM – 163.8 (red) • OIL TEMP – 409°
Actual values will be shown for the following right engine
indications:
• LP EVM • FLIGHT Hydraulics • FF
• HP EVM • AUX Hydraulics • EPR Targets
• EPR Limits • EPR Modes
The following right engine icons will be displayed:
• A/I • SVO (flashing amber
• IGN • EPR
• DU 4 (Crew Alerting System):
All red CAS warning messages will be displayed.

REVISION 24 (RE-ISSUE) NORMAL PROCEDURES

Mar 17/10 Page NI - 7
 Quick Reference Handbook
4. RAD ALT ................................................................................ TEST
Verify “100” is displayed on the ADI portion of the PFD.
5. TONE...................................................................................... TEST
Verify tone is activated. Adjust tone volume at this time, if desired.
(Level is normally no lower than 80.) Select RETURN after
volume has been adjusted to silence tone and end test.

END

Flight Guidance Panel Test GAC

Check the following functions of the flight guidance panel to confirm

selections can be made and the indications are displayed in the
appropriate window:
1. Altitude............ SET IN ALTITUDE WINDOW / VERIFIED ON PFD
2. Heading ...........................................................................................
........ SET / SELECT RUNWAY HEADING IN HEADING WINDOW
3. Speed .......................................... VERIFY V2 (OR APPROPRIATE
SPEED) IS DISPLAYED IN SPEED WINDOW AND ON PFD
4. AT ARM ...................................................................................... ON
5. PFD CMD ...................................................................................... L

END

NORMAL PROCEDURES REVISION 24 (RE-ISSUE)

Page NI - 8 Oct 5 2011
Quick Reference Handbook
Auxiliary Hydraulic Pump / Brake System Check
OM 2A-32-00

General:
The ability to test the brake system is provided in order to:
• Verify automatic operation of the Auxiliary Hydraulic pump
(hereafter referred to as AUX pump)
• Verify proper operation of the wheel brake system after engine
start but prior to taxi (Brake-By-Wire [BBW] airplanes only)
In order to observe applied brake pressure, these checks should be
performed with the HYDRAULICS system page (SPZ-8000 equipped
airplanes) or the BRAKES system page (SPZ-8400 equipped
airplanes) selected for display on DU 4. All checks involve depressing
the brake pedals to three positions:
• Slight deflection, where immediate but low applied brake
pressures are observed
• Half deflection (also known as the “soft stops”), where applied
brake pressures of approximately 600-800 psi are observed
• Full deflection, where applied brake pressures of approximately
3000 ±300 psi are observed
Perform the following procedure during the “AUX Pump / Brake System
Check” step of the Before Starting Engines checklist (page NC-1):
NOTE: When performing this procedure on Hydromechanical Analog
Braking System (HMAB) airplanes, the parking brake must be released.
1. AUX PUMP OFF / ARM Switch ............................................... ARM
2. Pilot’s Brake Pedals ........................................................ DEPRESS
3. Pressure Readings ......................................................... OBSERVE
A. AUX Pump Pressure ........................................ 3000 (±300) PSI
B. Applied Brake Pressure .......APPROPRIATE TO DEFLECTION
4. Pilot’s Brake Pedals .........................................................RELEASE
5. AUX Pump Pressure ............................................. 3000 (±300) PSI
6. AUX PUMP OFF / ARM Switch .......................................NOT ARM
7. Pressure Readings ......................................................... OBSERVE
A. AUX Pump Pressure ........................................................ ZERO
B. Applied Brake Pressure .................................................... ZERO

REVISION 24 (RE-ISSUE) NORMAL PROCEDURES

Mar 17/10 Page NI - 9
 Quick Reference Handbook
8. AUX PUMP OFF / ARM Switch ............................................... ARM
9. Copilot’s Brake Pedals ................................................... DEPRESS
10. Pressure Readings ......................................................... OBSERVE
A. AUX Pump Pressure ........................................ 3000 (±300) PSI
B. Applied Brake Pressure ....... APPROPRIATE TO DEFLECTION
11. Copilot’s Brake Pedals .................................................... RELEASE
12. AUX Pump Pressure ............................................. 3000 (±300) PSI
For BBW airplanes, perform Steps 13 and 14. For HMAB
airplanes, omit Steps 13 and 14 and proceed to Step 15.
NOTE: Airplane speed should be less than 12 knots for this test.
13. BRAKE TEST Switch .................................................... DEPRESS
14. Annunciations ................................................................. OBSERVE
A. Switch Legend (IN TEST)........... ILLUMINATED (3 SECONDS)
B. CAS Messages ........................ DISPLAYED, THEN REMOVED
• ANTISKID FAIL • BRAKE PEDAL
• BRAKE FAIL • BRAKE MAINT REQ’D
For HMAB airplanes, perform Steps 15 and 16:
NOTE: Airplane speed should be less than 12 knots for this test.
NOTE: On HMAB airplanes, the AUX pump must be momentarily de-armed
to stop AUX pump operation.
15. ANTI SKID TEST Switch ........................... DEPRESS AND HOLD
16. Annunciations ................................................................. OBSERVE
A. Switch Legend (IN TEST)........... ILLUMINATED (3 SECONDS)
B. CAS Messages ........................ DISPLAYED, THEN REMOVED
• ANTISKID FAIL • BRAKE MAINT REQ’D
• BRAKE FAIL

END

NORMAL PROCEDURES REVISION 24 (RE-ISSUE)

Page NI - 10 Oct 5 2011
Quick Reference Handbook
Elevator Trim System Check OM 2A-27-20

Located on the pilot's flight panel, the PITCH TRIM ENG / DISENG
switch engages or disengages the electric pitch trim. Pitch trim is also
engaged whenever the autopilot is engaged. With electric pitch trim
engaged (amber DISEN switch legend extinguished), pitch trim can
be adjusted through use of a split-half pitch trim switch installed on
the outboard grip of each control wheel.
Inadvertent actuation of pitch trim, including runaway, is minimized
through the split-half switch design. In order for the pitch trim to be
actuated, both halves of the switch must be simultaneously moved in
the same direction.
During the Before Starting Engines checklist (page NC-1), on the
first flight of the day, run the elevator trim fully up and fully down using
both halves of the switch, simultaneously. Next, attempt to run the
pitch trim using each half of the switch independently. Any movement
resulting from using either half of the switch independently indicates a
malfunction that should be corrected before flight. Finally, set pitch
trim for the takeoff Center of Gravity (CG) condition as determined
using the Recommended Elevator Trim Tab Settings for Takeoff
table, page NC-5.
END

REVISION 24 (RE-ISSUE) NORMAL PROCEDURES

Mar 17/10 Page NI - 11
 Quick Reference Handbook
Ground Spoiler System Check OM 2A-27-70

The ground spoiler system is monitored by a warning circuit that will

detect certain in-flight and on-ground malfunctions within the ground
spoiler system, prompting the following annunciations:
• A red GND SPOILER warning message will be displayed on CAS
and, if installed, the SWLP, should a failure occur within the
ground spoiler system either while airborne or on the ground.
• A red NO GND SPOILERS warning light, located adjacent to the
pilot's AOA indexer on the windshield center post, will illuminate if
the ground spoilers do not automatically extend upon touchdown.
Additionally, a blue GND SPOILER UNARM advisory message is
displayed on CAS anytime the landing gear is down and locked and
the GND SPLR OFF / ARMED switch is not selected to ARMED.
The following ground spoiler system check should be performed
during the After Starting Engines checklist (page ND-1), prior to the
first departure of each day. It provides a complete functional check of
the automatic ground spoiler system and ground spoiler warning
system.
NOTE: When the power lever is advanced, the red GND SPOILER
warning message may be displayed momentarily and then extinguish.
If the message remains extinguished, continue the test.
NOTE: The absence of either the NO GND SPOILERS light or the
GND SPOILER message during Step 8, or any incorrect indication,
constitutes an unsuccessful ground spoiler system check.
NOTE: The ground spoilers cannot always be observed from the
cockpit. The correct GND SPOILER message and NO GND
SPOILERS light indications are sufficient for satisfactory preflight
functional verification.
1. GND SPLR OFF / ARMED Switch ........................................... OFF
2. Power Levers (Both) ................................................................ IDLE
A. Ground Spoilers .......................................................... STOWED
B. NO GND SPOILERS Light .............................. EXTINGUISHED
C. GND SPOILER Message ...............................NOT DISPLAYED
D. GND SPOILER UNARM Message ........................ DISPLAYED

NORMAL PROCEDURES REVISION 24 (RE-ISSUE)

Page NI - 12 Oct 5 2011
Quick Reference Handbook
3. GND SPLR OFF / ARMED Switch ..................................... ARMED
A. Ground Spoilers .......................................................DEPLOYED
B. NO GND SPOILERS Light .........................................................
................ FLASHES MOMENTARILY, THEN EXTINGUISHED
C. GND SPOILER Message .............................. NOT DISPLAYED
D. GND SPOILER UNARM Message ................ NOT DISPLAYED
4. Left Power Lever .................................... ADVANCE OUT OF IDLE
A. Ground Spoilers .......................................................... STOWED
B. NO GND SPOILERS Light .............................. EXTINGUISHED
C. GND SPOILER Message ...........................................................
.............. FLASHES MOMENTARILY, THEN NOT DISPLAYED
5. Right Power Lever .................................. ADVANCE OUT OF IDLE
6. Left Power Lever ............................................... RETURN TO IDLE
A. Ground Spoilers ........................................... REMAIN STOWED
B. NO GND SPOILERS Light .............................. EXTINGUISHED
C. GND SPOILER Message .............................. NOT DISPLAYED
7. GND SPLR OFF / ARMED Switch ........................................... OFF
A. GND SPOILER UNARM Message ......................... DISPLAYED
8. GND SPLR TEST Switch ........................... DEPRESS AND HOLD
A. Ground Spoilers ........................................... REMAIN STOWED
B. GND SPLR TEST Switch Legend ...................... ILLUMINATED
C. NO GND SPOILERS Light ................................. ILLUMINATED
D. GND SPOILER Message ....................................... DISPLAYED
E. GND SPOILER UNARM Message ......................... DISPLAYED
F. GND SPOILER Light (SWLP, If Installed) .......... ILLUMINATED
G. MASTER WARN Lights (Glareshield) ................ ILLUMINATED

REVISION 24 (RE-ISSUE) NORMAL PROCEDURES

Mar 17/10 Page NI - 13
 Quick Reference Handbook
9. GND SPLR TEST Switch ................................................ RELEASE
A. Ground Spoilers ...........................................REMAIN STOWED
B. GND SPLR TEST Switch Legend ................... EXTINGUISHED
C. NO GND SPOILERS Light .............................. EXTINGUISHED
D. GND SPOILER UNARM Message ......................... DISPLAYED
E. GND SPOILER Light (SWLP, If Installed) ....... EXTINGUISHED
F. MASTER WARN Lights (Glareshield) ............. EXTINGUISHED
10. Right Power Lever ................................................................... IDLE
A. NO GND SPOILERS Light .............................. EXTINGUISHED
B. GND SPOILER Message ...............................NOT DISPLAYED
C. GND SPOILER UNARM Message ......................... DISPLAYED

END

NORMAL PROCEDURES REVISION 24 (RE-ISSUE)

Page NI - 14 Oct 5 2011
Quick Reference Handbook
Stall Warning / Stall Barrier System Check OM 2A-27-20

The following stall warning / stall barrier system check should be

performed during the After Starting Engines checklist (page ND-1),
prior to the first departure of each day. If flight time for the day
exceeds eight (8) hours, a second stall barrier check is required prior
to the second flight of the day. This test is performed only on the
ground and cannot be tested in flight.
1. STALL BARRIER Switch ............................................................ ON
2. Display Controllers (Both) ............................ SELECT TEST MENU
3. Sea Level (S/L) Line Select Keys (Both) .........................................
.................................. SIMULTANEOUSLY DEPRESS AND HOLD
Continue holding both S/L line select keys until the normalized
AOA indicator pointer slews. Then verify the following:
A. Stall Warning (Control Column Shaker) .....................................
......................................... OCCURS BETWEEN 0.70 AND 0.80
B. Stall Barrier (Control Column Pusher) ........................................
......................................... OCCURS BETWEEN 0.95 AND 1.07
C. A/P DISC (BARR DISC) Button ..................................................
........................... OVERRIDES PUSHER WHEN DEPRESSED
4. ALT Line Select Keys (Both) ...........................................................
.................................. SIMULTANEOUSLY DEPRESS AND HOLD
Continue holding both ALT line select keys until the normalized
AOA indicator pointer slews. Then verify the following:
A. Stall Warning (Control Column Shaker) .....................................
......................................... OCCURS BETWEEN 0.54 AND 0.65
B. Stall Barrier (Control Column Pusher) ........................................
......................................... OCCURS BETWEEN 0.79 AND 0.90
C. A/P DISC (BARR DISC) Button ..................................................
........................... OVERRIDES PUSHER WHEN DEPRESSED
NOTE: Both pilot's and copilot's sides have to be tested simultaneously in
order to activate the control column pusher.
NOTE: Another momentary push of the TEST function key may be
required to ensure the AOA indicator is in the normal area prior to takeoff.
NOTE: There are two stall warning / stall barrier systems installed in the
airplane. Dispatch with one stall warning / stall barrier system inoperative
is allowed with reference to the MEL.

END

REVISION 24 (RE-ISSUE) NORMAL PROCEDURES

Mar 17/10 Page NI - 15
 Quick Reference Handbook

Notes

NORMAL PROCEDURES REVISION 24 (RE-ISSUE)

Page NI - 16 Oct 5 2011
Quick Reference Handbook
GIV-SP Performance Planning Index
GIV-SP Takeoff Planning
GIV-SP Crosswind Components .................................................. PA-1
GIV-SP Contaminated Runway Operations ................................. PA-2
GIV-SP Takeoff Planning Charts: Flaps 20°, APA Sea Level ...... PA-5
GIV-SP Takeoff Planning Charts: Flaps 20°, 500 Feet ................ PA-7
GIV-SP Takeoff Planning Charts: Flaps 20°, 1000 Feet .............. PA-9
GIV-SP Takeoff Planning Charts: Flaps 20°, 2000 Feet ............ PA-11
GIV-SP Takeoff Planning Charts: Flaps 20°, 4000 Feet ............ PA-13
GIV-SP Takeoff Planning Charts: Flaps 20°, 6000 Feet ............ PA-15
GIV-SP Takeoff Planning Charts: Flaps 20°, 8000 Feet ............ PA-17
GIV-SP Takeoff Planning Charts: Flaps 10°, APA Sea Level .... PA-20
GIV-SP Takeoff Planning Charts: Flaps 10°, 500 Feet .............. PA-22
GIV-SP Takeoff Planning Charts: Flaps 10°, 1000 Feet ............ PA-24
GIV-SP Takeoff Planning Charts: Flaps 10°, 2000 Feet ............ PA-26
GIV-SP Takeoff Planning Charts: Flaps 10°, 4000 Feet ............ PA-28
GIV-SP Takeoff Planning Charts: Flaps 10°, 6000 Feet ............ PA-30
GIV-SP Takeoff Planning Charts: Flaps 10°, 8000 Feet ............ PA-32
GIV-SP Maximum Allowable Takeoff Gross Weight Permitted
By Takeoff Climb Requirements, Flaps 20°, Minimum Grad. .... PA-34
GIV-SP Maximum Allowable Takeoff Gross Weight Permitted
By Takeoff Climb Requirements, Flaps 10°, Minimum Grad. .... PA-35
GIV-SP Maximum Allowable Takeoff Gross Weight Permitted
By Takeoff Climb Requirements, Flaps 20°, SID Departure ...... PA-36
GIV-SP Maximum Allowable Takeoff Gross Weight Permitted
By Takeoff Climb Requirements, Flaps 10°, SID Departure ....... PA-48
GIV-SP SID Climb Performance Conversion Table ................... PA-60

Continued on next page →

REVISION 24 (RE-ISSUE) GIV-SP PERFORMANCE

Mar 17/10 (GIV-SP AIRPLANES ONLY) Page P - i
 Quick Reference Handbook
GIV-SP Performance Planning Index, ctd…

GIV-SP Cruise Planning

GIV-SP Twin Engine Cruise Altitudes, Mach 0.77 ....................... PB-1
GIV-SP Twin Engine Cruise Altitudes, Mach 0.80 ....................... PB-2
GIV-SP Twin Engine Cruise Altitudes, Mach 0.83 ....................... PB-3
GIV-SP Twin Engine Maximum Range Cruise - ISA .................... PB-4
GIV-SP Twin Engine Long Range Cruise - ISA ........................... PB-6
GIV-SP Twin Engine Cruise, Mach 0.77 - ISA ............................. PB-8
GIV-SP Twin Engine Cruise, Mach 0.80 - ISA ........................... PB-10
GIV-SP Twin Engine Cruise, Mach 0.83 - ISA ........................... PB-12
GIV-SP Twin Engine Flight Planning, Mach 0.77 - ISA.............. PB-14
GIV-SP Twin Engine Flight Planning, Mach 0.80 - ISA.............. PB-15
GIV-SP Twin Engine Flight Planning, Mach 0.83 - ISA.............. PB-16
GIV-SP Equal Time Point and Point of No Return ..................... PB-17
GIV-SP Twin Engine Alternate Airport Flight Plan Fuel ............. PB-18
GIV-SP Landing Planning
GIV-SP Landing Field Length: Anti-Skid Operative, Flaps 39° .... PC-1
GIV-SP Landing Speed Schedule ................................................ PC-2
GIV-SP Landing Distance Using Twin-Engine Reverse
Thrust Only (No Braking) .............................................................. PC-6
GIV-SP Aircraft Classification Number (ACN) .............................. PC-8
GIV-SP Equivalent Single Wheel Loading (ESWL) .................... PC-14
GIV-SP Brake Kinetic Energy / Carbon Brake Cooling .............. PC-15
GIV-SP Abnormal Landing Field Length Table .......................... PC-16

GIV-SP PERFORMANCE REVISION 24 (RE-ISSUE)

Page P - ii (GIV-SP AIRPLANES ONLY) Mar 17/10
Quick Reference Handbook
GIV-SP Crosswind Components AFM 5.1

REVISION 24 (RE-ISSUE) GIV-SP PERFORMANCE

Mar 17/10 (GIV-SP AIRPLANES ONLY) Page PA - 1
 Quick Reference Handbook
GIV-SP Contaminated Runway Operations GIV-OIS-2A

RUNWAY SURFACE CONTAMINATION (RSC), CRFI EQUIVALENT

AND ESTIMATED LANDING BRAKING COEFFICIENT
APPROXIMATE
CRFI
RSC PIREP RCR BRAKING
EQUIVALENT
COEFFICIENT
Bare and Dry ³ 0.80
Damp - Less than 0.01 inch of water 0.60 - 0.70 Good ³ 18 0.36 - 0.39
Very light snow patches 0.55 - 0.60
Wet concrete - 0.01 to 0.03 inch of water 0.40 - 0.55
Wet Asphalt - 0.01 to 0.03 inch of water 0.30 - 0.60 Fair 13 - 18 0.25 - 0.35
Compacted snow -- below -15°C 0.40
Sanded, packed snow or ice 0.40 - 0.50
Heavy rain -- 0.03 to 0.10 inch of water 0.28 - 0.30
Snow covered 0.25 - 0.30 Poor 5 - 12 0.13 - 0.25
Compacted snow -- above -15°C 0.20 - 0.25
Cold ice -- below -10°C 0.10 - 0.20
Wet ice -- above -10°C 0.05 - 0.10
Hydroplaning - standing water ³ 0.10 0.05 Nil £5 £ 0.13

CANADIAN RUNWAY FRICTION INDEX

.20 .25 .30 .40 .45 .50 .55 .60 .70 .75

NIL POOR FAIR GOOD

.10 .15 .20 .25 .30 .35

(ICY) (WET) (DRY)
APPROXIMATE BRAKING COEFFICIENT

NOTE: The data presented above is advisory data only and is not FAA
approved. For additional information concerning contaminated runway
operations, refer to the latest approved revision of Operational
Information Supplement GIV-OIS-2A, Contaminated Runway
Operations.

GIV-SP PERFORMANCE REVISION 24 (RE-ISSUE)

Page PA - 2 (GIV-SP AIRPLANES ONLY) Mar 17/10
Quick Reference Handbook
GIV-SP Contaminated Runway Operations, ctd… GIV-OIS-2A

NOTE: The data presented above is advisory data only and is not FAA
approved. For additional information concerning contaminated runway
operations, refer to the latest approved revision of Operational Information
Supplement GIV-OIS-2A, Contaminated Runway Operations.

REVISION 24 (RE-ISSUE) GIV-SP PERFORMANCE

Mar 17/10 (GIV-SP AIRPLANES ONLY) Page PA - 3
 Quick Reference Handbook
GIV-SP Takeoff Planning Charts: Flaps 20° AFM APP. A

The charts in this section provide quick reference planning data for
takeoff planning at the following Airport Pressure Altitudes (APA), for
20° flap configurations:
• Sea Level • 500 Feet • 1000 Feet • 2000 Feet
• 4000 Feet • 6000 Feet • 8000 Feet

These charts are for use for airplanes SN 1214 and subsequent
and SN 1000 thru 1213 with ASC 190 incorporated.

In the interest of safety, the CAUTION and NOTES following each

takeoff planning chart must be observed when using any takeoff
planning chart in this section.

GIV-SP PERFORMANCE REVISION 24 (RE-ISSUE)

Page PA - 4 (GIV-SP AIRPLANES ONLY) Mar 17/10
Quick Reference Handbook
GIV-SP Takeoff Planning: Flaps 20° - APA Sea Level
AFM APP. A

TAKEOFF PLANNING CHART

GIV-SP AIRPORT PRESSURE ALTITUDE = SEA LEVEL TAKEOFF FLAP 20°

74,600 LB MTOGW OAT (°C) 50 45 40 35 30 25 20 15 5 -5 -15
OAT (°F) 122 113 104 95 86 77 68 59 41 23 5
RATED EPR 1.59 1.62 1.64 1.67 1.70 1.70 1.70 1.70 1.69 1.69 1.69
-- 74,600 LB --
VFS = 173 KCAS FLD LNGTH 7,770 7,100 6,580 6,130 5,750 5,660 5,570 5,480 5,350 5,170 4,990
VSE = 180 KCAS V1 KCAS 146 144 142 140 139 139 139 139 140 140 140
VREF = 158 KCAS VR KCAS 146 146 146 146 145 145 145 145 145 145 145
MAX TEMP = 50°C V2 KCAS 150 150 150 150 150 150 150 150 150 150 150
-- 74,000 LB --
VFS = 172 KCAS FLD LNGTH 7,600 6,980 6,470 6,030 5,660 5,570 5,480 5,400 5,270 5,090 4,910
VSE = 179 KCAS V1 KCAS 145 143 141 140 138 138 138 139 139 139 139
VREF = 158 KCAS VR KCAS 145 145 145 145 144 144 144 144 144 144 144
MAX TEMP = 50°C V2 KCAS 149 149 149 149 149 149 149 149 149 149 149
-- 72,000 LB --
VFS = 170 KCAS FLD LNGTH 7,130 6,570 6,110 5,700 5,360 5,280 5,190 5,110 4,990 4,820 4,650
VSE = 177 KCAS V1 KCAS 142 140 139 137 136 136 136 136 136 136 136
VREF = 156 KCAS VR KCAS 143 143 143 143 142 142 142 142 142 142 142
MAX TEMP = 50°C V2 KCAS 147 147 147 147 147 147 147 147 147 147 147
-- 70,000 LB --
VFS = 167 KCAS FLD LNGTH 6,690 6,190 5,760 5,390 5,070 4,990 4,910 4,840 4,720 4,560 4,400
VSE = 174 KCAS V1 KCAS 139 137 136 134 133 133 133 133 134 134 134
VREF = 154 KCAS VR KCAS 141 141 141 140 140 140 140 140 140 140 140
MAX TEMP = 50°C V2 KCAS 145 145 145 145 145 145 145 145 145 145 145
-- 68,000 LB --
VFS = 165 KCAS FLD LNGTH 6,280 5,820 5,430 5,090 4,790 4,710 4,640 4,570 4,460 4,310 4,160
VSE = 171 KCAS V1 KCAS 136 134 133 132 130 130 130 130 131 131 131
VREF = 151 KCAS VR KCAS 139 139 139 138 137 137 137 137 137 137 137
MAX TEMP = 50°C V2 KCAS 143 143 143 143 143 143 143 143 143 143 143
-- 66,000 LB --
VFS = 162 KCAS FLD LNGTH 5,890 5,470 5,120 4,800 4,520 4,450 4,380 4,310 4,200 4,060 3,920
VSE = 169 KCAS V1 KCAS 133 132 130 129 128 128 128 128 128 128 128
VREF = 149 KCAS VR KCAS 137 137 136 135 135 135 135 135 135 135 135
MAX TEMP = 50°C V2 KCAS 141 141 141 141 141 141 141 141 141 141 141
-- 64,000 LB --
VFS = 160 KCAS FLD LNGTH 5,520 5,140 4,820 4,520 4,260 4,190 4,130 4,060 3,960 3,830 3,700
VSE = 166 KCAS V1 KCAS 131 129 128 126 125 125 125 125 125 125 125
VREF = 147 KCAS VR KCAS 135 134 134 133 132 132 132 132 132 132 132
MAX TEMP = 50°C V2 KCAS 139 139 139 139 139 139 139 139 139 139 139
-- 62,000 LB --
VFS = 157 KCAS FLD LNGTH 5,170 4,830 4,530 4,250 4,010 3,950 3,890 3,830 3,730 3,610 3,480
VSE = 164 KCAS V1 KCAS 128 126 125 123 122 122 122 122 122 122 123
VREF = 144 KCAS VR KCAS 132 132 131 131 130 130 130 130 130 130 130
MAX TEMP = 50°C V2 KCAS 137 137 137 137 137 137 137 137 137 137 137
CAUTION: DO NOT REDUCE TAKEOFF EPR BY MORE THAN .15 OR BELOW A MINIMUM VALUE OF 1.56.
NOTES: HEADWIND: Increase available field length 2% for each 5 knots (up to 40 knots).
TAILWIND: Decrease available field length 11% for each 5 knots (up to 10 knots).
UPHILL SLOPE: Decrease available field length 20% for each 1% (up to 2%).
DOWNHILL SLOPE: No adjustments required (up to 2%).
GROUND SPOILERS INOP: Decrease available field length 800 feet.

REVISION 24 (RE-ISSUE) GIV-SP PERFORMANCE

Mar 17/10 (GIV-SP AIRPLANES ONLY) Page PA - 5
 Quick Reference Handbook
GIV-SP Takeoff Planning: Flaps 20° - APA Sea Level, ctd…
AFM APP. A

TAKEOFF PLANNING CHART

GIV-SP AIRPORT PRESSURE ALTITUDE = SEA LEVEL TAKEOFF FLAP 20°

74,600 LB MTOGW OAT (°C) 50 45 40 35 30 25 20 15 5 -5 -15
OAT (°F) 122 113 104 95 86 77 68 59 41 23 5
RATED EPR 1.59 1.62 1.64 1.67 1.70 1.70 1.70 1.70 1.69 1.69 1.69
-- 60,000 LB --
VFS = 155 KCAS FLD LNGTH 4,850 4,530 4,250 4,000 3,770 3,710 3,660 3,600 3,510 3,390 3,280
VSE = 161 KCAS V1 KCAS 125 123 122 120 119 119 119 119 120 120 120
VREF = 142 KCAS VR KCAS 130 129 129 128 127 127 127 127 127 127 127
MAX TEMP = 50°C V2 KCAS 135 135 135 135 135 135 135 135 135 135 135
-- 58,000 LB --
VFS = 152 KCAS FLD LNGTH 4,590 4,300 4,030 3,790 3,600 3,540 3,490 3,440 3,340 3,230 3,120
VSE = 158 KCAS V1 KCAS 123 121 120 118 117 117 117 117 118 118 118
VREF = 140 KCAS VR KCAS 128 128 127 126 126 126 126 126 126 126 126
MAX TEMP = 50°C V2 KCAS 133 133 133 133 133 133 133 133 133 133 133
-- 56,000 LB --
VFS = 150 KCAS FLD LNGTH 4,340 4,070 3,820 3,650 3,540 3,480 3,430 3,380 3,280 3,180 3,070
VSE = 156 KCAS V1 KCAS 121 119 118 117 118 118 118 118 118 118 118
VREF = 137 KCAS VR KCAS 127 126 125 124 124 124 124 124 124 124 124
MAX TEMP = 50°C V2 KCAS 132 132 132 132 132 132 132 132 132 132 132
-- 54,000 LB --
VFS = 147 KCAS FLD LNGTH 4,150 3,890 3,700 3,580 3,480 3,430 3,370 3,320 3,230 3,120 3,020
VSE = 153 KCAS V1 KCAS 119 118 117 117 118 118 118 118 118 118 118
VREF = 135 KCAS VR KCAS 125 125 124 123 123 123 123 123 123 123 123
MAX TEMP = 50°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
-- 52,000 LB --
VFS = 144 KCAS FLD LNGTH 4,010 3,760 3,630 3,520 3,420 3,370 3,320 3,270 3,170 3,070 2,970
VSE = 150 KCAS V1 KCAS 118 117 117 118 118 118 118 118 118 118 119
VREF = 132 KCAS VR KCAS 125 124 124 123 122 122 122 122 122 122 122
MAX TEMP = 50°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
-- 50,000 LB --
VFS = 142 KCAS FLD LNGTH 3,860 3,670 3,560 3,450 3,360 3,310 3,260 3,210 3,120 3,020 2,920
VSE = 147 KCAS V1 KCAS 118 117 117 118 118 118 118 118 119 119 119
VREF = 130 KCAS VR KCAS 125 124 123 122 122 122 122 122 122 122 122
MAX TEMP = 50°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
-- 48,000 LB --
VFS = 139 KCAS FLD LNGTH 3,720 3,600 3,490 3,390 3,300 3,250 3,200 3,150 3,060 2,970 2,870
VSE = 144 KCAS V1 KCAS 117 117 118 118 119 119 119 119 119 119 119
VREF = 127 KCAS VR KCAS 124 124 123 122 121 121 121 121 121 121 121
MAX TEMP = 50°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
-- 46,000 LB --
VFS = 136 KCAS FLD LNGTH 3,640 3,530 3,420 3,330 3,240 3,190 3,140 3,100 3,010 2,910 2,820
VSE = 141 KCAS V1 KCAS 117 118 118 119 119 119 119 119 119 119 120
VREF = 124 KCAS VR KCAS 124 123 122 122 121 121 121 121 121 121 121
MAX TEMP = 50°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
CAUTION: DO NOT REDUCE TAKEOFF EPR BY MORE THAN .15 OR BELOW A MINIMUM VALUE OF 1.56.
NOTES: HEADWIND: Increase available field length 2% for each 5 knots (up to 40 knots).
TAILWIND: Decrease available field length 11% for each 5 knots (up to 10 knots).
UPHILL SLOPE: Decrease available field length 20% for each 1% (up to 2%).
DOWNHILL SLOPE: No adjustments required (up to 2%).
GROUND SPOILERS INOP: Decrease available field length 800 feet.

GIV-SP PERFORMANCE REVISION 24 (RE-ISSUE)

Page PA - 6 (GIV-SP AIRPLANES ONLY) Mar 17/10
Quick Reference Handbook
GIV-SP Takeoff Planning: Flaps 20° - APA 500 Feet
AFM APP. A

TAKEOFF PLANNING CHART

GIV-SP AIRPORT PRESSURE ALTITUDE = 500 FEET TAKEOFF FLAP 20°

74,600 LB MTOGW OAT (°C) 49 45 40 35 30 25 20 15 5 -5 -15
OAT (°F) 120 113 104 95 86 77 68 59 41 23 5
RATED EPR 1.59 1.62 1.64 1.67 1.70 1.71 1.71 1.71 1.70 1.70 1.70
-- 74,600 LB --
VFS = 173 KCAS FLD LNGTH 8,020 7,440 6,870 6,380 5,980 5,810 5,710 5,620 5,480 5,300 5,120
VSE = 180 KCAS V1 KCAS 146 145 143 141 140 139 139 139 140 140 140
VREF = 158 KCAS VR KCAS 146 146 146 146 145 145 145 145 145 145 145
MAX TEMP = 49°C V2 KCAS 150 150 150 150 150 150 150 150 150 150 150
-- 74,000 LB --
VFS = 172 KCAS FLD LNGTH 7,830 7,300 6,750 6,270 5,880 5,710 5,620 5,530 5,400 5,210 5,030
VSE = 179 KCAS V1 KCAS 145 144 142 140 139 139 139 139 139 139 139
VREF = 158 KCAS VR KCAS 145 145 145 145 145 145 145 145 145 145 145
MAX TEMP = 49°C V2 KCAS 149 149 149 149 149 149 149 149 149 149 149
-- 72,000 LB --
VFS = 170 KCAS FLD LNGTH 7,320 6,860 6,360 5,930 5,570 5,410 5,320 5,240 5,110 4,940 4,770
VSE = 177 KCAS V1 KCAS 142 141 139 138 136 136 136 136 136 136 137
VREF = 156 KCAS VR KCAS 143 143 143 143 142 142 142 142 142 142 142
MAX TEMP = 49°C V2 KCAS 147 147 147 147 147 147 147 147 147 147 147
-- 70,000 LB --
VFS = 167 KCAS FLD LNGTH 6,870 6,450 6,000 5,610 5,270 5,120 5,030 4,950 4,830 4,670 4,510
VSE = 174 KCAS V1 KCAS 140 138 136 135 134 133 133 133 134 134 134
VREF = 154 KCAS VR KCAS 141 141 141 141 140 140 140 140 140 140 140
MAX TEMP = 49°C V2 KCAS 145 145 145 145 145 145 145 145 145 145 145
-- 68,000 LB --
VFS = 165 KCAS FLD LNGTH 6,440 6,060 5,650 5,290 4,970 4,830 4,750 4,680 4,560 4,410 4,260
VSE = 172 KCAS V1 KCAS 136 135 134 132 131 131 131 131 131 131 131
VREF = 151 KCAS VR KCAS 139 139 139 138 138 137 137 137 137 137 137
MAX TEMP = 49°C V2 KCAS 143 143 143 143 143 143 143 143 143 143 143
-- 66,000 LB --
VFS = 162 KCAS FLD LNGTH 6,040 5,690 5,320 4,980 4,690 4,560 4,480 4,410 4,310 4,160 4,020
VSE = 169 KCAS V1 KCAS 134 132 131 129 128 128 128 128 128 128 128
VREF = 149 KCAS VR KCAS 137 137 136 136 135 135 135 135 135 135 135
MAX TEMP = 49°C V2 KCAS 141 141 141 141 141 141 141 141 141 141 141
-- 64,000 LB --
VFS = 160 KCAS FLD LNGTH 5,660 5,350 5,000 4,690 4,420 4,300 4,230 4,160 4,060 3,920 3,790
VSE = 166 KCAS V1 KCAS 131 130 128 127 125 125 125 125 125 125 126
VREF = 147 KCAS VR KCAS 135 134 134 133 133 132 132 132 132 132 132
MAX TEMP = 49°C V2 KCAS 139 139 139 139 139 139 139 139 139 139 139
-- 62,000 LB --
VFS = 157 KCAS FLD LNGTH 5,300 5,020 4,700 4,410 4,160 4,050 3,980 3,920 3,820 3,690 3,570
VSE = 164 KCAS V1 KCAS 128 127 125 124 123 122 122 122 123 123 123
VREF = 144 KCAS VR KCAS 132 132 131 131 130 130 130 130 130 130 130
MAX TEMP = 49°C V2 KCAS 137 137 137 137 137 137 137 137 137 137 137
CAUTION: DO NOT REDUCE TAKEOFF EPR BY MORE THAN .15 OR BELOW A MINIMUM VALUE OF 1.56.
NOTES: HEADWIND: Increase available field length 2% for each 5 knots (up to 40 knots).
TAILWIND: Decrease available field length 11% for each 5 knots (up to 10 knots).
UPHILL SLOPE: Decrease available field length 20% for each 1% (up to 2%).
DOWNHILL SLOPE: No adjustments required (up to 2%).
GROUND SPOILERS INOP: Decrease available field length 800 feet.

REVISION 24 (RE-ISSUE) GIV-SP PERFORMANCE

Mar 17/10 (GIV-SP AIRPLANES ONLY) Page PA - 7
 Quick Reference Handbook
GIV-SP Takeoff Planning: Flaps 20° - APA 500 Feet, ctd…
AFM APP. A

TAKEOFF PLANNING CHART

GIV-SP AIRPORT PRESSURE ALTITUDE = 500 FEET TAKEOFF FLAP 20°

74,600 LB MTOGW OAT (°C) 49 45 40 35 30 25 20 15 5 -5 -15
OAT (°F) 120 113 104 95 86 77 68 59 41 23 5
RATED EPR 1.59 1.62 1.64 1.67 1.70 1.71 1.71 1.71 1.70 1.70 1.70
-- 60,000 LB --
VFS = 155 KCAS FLD LNGTH 4,960 4,710 4,410 4,150 3,910 3,810 3,740 3,680 3,590 3,480 3,360
VSE = 161 KCAS V1 KCAS 125 124 122 121 120 119 119 119 120 120 120
VREF = 142 KCAS VR KCAS 130 130 129 128 128 127 127 127 127 127 127
MAX TEMP = 49°C V2 KCAS 135 135 135 135 135 135 135 135 135 135 135
-- 58,000 LB --
VFS = 152 KCAS FLD LNGTH 4,700 4,460 4,190 3,940 3,710 3,620 3,560 3,500 3,410 3,300 3,190
VSE = 158 KCAS V1 KCAS 123 122 120 119 118 117 117 117 118 118 118
VREF = 140 KCAS VR KCAS 128 128 127 127 126 126 126 126 126 126 126
MAX TEMP = 49°C V2 KCAS 133 133 133 133 133 133 133 133 133 133 133
-- 56,000 LB --
VFS = 150 KCAS FLD LNGTH 4,450 4,220 3,970 3,750 3,620 3,550 3,500 3,450 3,350 3,240 3,130
VSE = 156 KCAS V1 KCAS 121 120 118 117 117 117 118 118 118 118 118
VREF = 137 KCAS VR KCAS 127 126 125 125 124 124 124 124 124 124 124
MAX TEMP = 49°C V2 KCAS 132 132 132 132 132 132 132 132 132 132 132
-- 54,000 LB --
VFS = 147 KCAS FLD LNGTH 4,250 4,040 3,810 3,670 3,560 3,490 3,440 3,390 3,290 3,190 3,080
VSE = 153 KCAS V1 KCAS 119 118 117 117 118 118 118 118 118 118 118
VREF = 135 KCAS VR KCAS 126 125 124 124 123 123 123 123 123 123 123
MAX TEMP = 49°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
-- 52,000 LB --
VFS = 144 KCAS FLD LNGTH 4,100 3,900 3,720 3,600 3,500 3,430 3,380 3,330 3,230 3,130 3,030
VSE = 150 KCAS V1 KCAS 119 117 117 117 118 118 118 118 118 118 119
VREF = 132 KCAS VR KCAS 125 125 124 123 123 122 122 122 122 122 122
MAX TEMP = 49°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
-- 50,000 LB --
VFS = 142 KCAS FLD LNGTH 3,950 3,780 3,650 3,540 3,440 3,370 3,320 3,270 3,180 3,080 2,970
VSE = 147 KCAS V1 KCAS 118 117 117 118 118 118 118 118 118 119 119
VREF = 130 KCAS VR KCAS 125 124 124 123 122 122 122 122 122 122 122
MAX TEMP = 49°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
-- 48,000 LB --
VFS = 139 KCAS FLD LNGTH 3,800 3,690 3,580 3,470 3,370 3,310 3,260 3,210 3,120 3,020 2,920
VSE = 144 KCAS V1 KCAS 117 117 117 118 118 119 119 119 119 119 119
VREF = 127 KCAS VR KCAS 124 124 123 122 122 121 121 121 121 121 121
MAX TEMP = 49°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
-- 46,000 LB --
VFS = 136 KCAS FLD LNGTH 3,710 3,610 3,500 3,400 3,310 3,250 3,200 3,150 3,060 2,970 2,870
VSE = 141 KCAS V1 KCAS 117 117 118 118 119 119 119 119 119 119 119
VREF = 124 KCAS VR KCAS 124 123 123 122 121 121 121 121 121 121 121
MAX TEMP = 49°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
CAUTION: DO NOT REDUCE TAKEOFF EPR BY MORE THAN .15 OR BELOW A MINIMUM VALUE OF 1.56.
NOTES: HEADWIND: Increase available field length 2% for each 5 knots (up to 40 knots).
TAILWIND: Decrease available field length 11% for each 5 knots (up to 10 knots).
UPHILL SLOPE: Decrease available field length 20% for each 1% (up to 2%).
DOWNHILL SLOPE: No adjustments required (up to 2%).
GROUND SPOILERS INOP: Decrease available field length 800 feet.

GIV-SP PERFORMANCE REVISION 24 (RE-ISSUE)

Page PA - 8 (GIV-SP AIRPLANES ONLY) Mar 17/10
Quick Reference Handbook
GIV-SP Takeoff Planning: Flaps 20° - APA 1000 Feet
AFM APP. A

TAKEOFF PLANNING CHART

GIV-SP AIRPORT PRESSURE ALTITUDE = 1,000 FEET TAKEOFF FLAP 20°

74,600 LB MTOGW OAT (°C) 48 45 40 35 30 25 20 15 5 -5 -15
OAT (°F) 118 113 104 95 86 77 68 59 41 23 5
RATED EPR 1.60 1.62 1.64 1.66 1.70 1.71 1.71 1.71 1.71 1.71 1.71
-- 74,600 LB --
VFS = 173 KCAS FLD LNGTH 8,290 7,810 7,160 6,650 6,210 5,970 5,850 5,760 5,620 5,430 5,240
VSE = 180 KCAS V1 KCAS 146 145 143 142 140 139 139 140 140 140 140
VREF = 158 KCAS VR KCAS 146 146 146 146 146 145 145 145 145 145 145
MAX TEMP = 48°C V2 KCAS 150 150 150 150 150 150 150 150 150 150 150
-- 74,000 LB --
VFS = 172 KCAS FLD LNGTH 8,090 7,650 7,040 6,540 6,110 5,870 5,760 5,660 5,530 5,340 5,160
VSE = 179 KCAS V1 KCAS 145 144 143 141 139 139 139 139 139 139 139
VREF = 158 KCAS VR KCAS 145 145 145 145 145 145 145 145 145 145 145
MAX TEMP = 48°C V2 KCAS 149 149 149 149 149 149 149 149 149 149 149
-- 72,000 LB --
VFS = 170 KCAS FLD LNGTH 7,520 7,170 6,630 6,170 5,790 5,560 5,450 5,360 5,240 5,060 4,880
VSE = 177 KCAS V1 KCAS 143 142 140 138 137 136 136 136 136 137 137
VREF = 156 KCAS VR KCAS 143 143 143 143 143 142 142 142 142 142 142
MAX TEMP = 48°C V2 KCAS 147 147 147 147 147 147 147 147 147 147 147
-- 70,000 LB --
VFS = 167 KCAS FLD LNGTH 7,060 6,730 6,240 5,830 5,470 5,260 5,160 5,080 4,950 4,790 4,620
VSE = 174 KCAS V1 KCAS 140 139 137 135 134 134 134 134 134 134 134
VREF = 154 KCAS VR KCAS 141 141 141 141 140 140 140 140 140 140 140
MAX TEMP = 48°C V2 KCAS 145 145 145 145 145 145 145 145 145 145 145
-- 68,000 LB --
VFS = 165 KCAS FLD LNGTH 6,610 6,320 5,880 5,500 5,160 4,960 4,870 4,790 4,680 4,520 4,360
VSE = 172 KCAS V1 KCAS 137 136 134 133 131 131 131 131 131 131 131
VREF = 151 KCAS VR KCAS 139 139 139 138 138 138 137 137 137 137 137
MAX TEMP = 48°C V2 KCAS 143 143 143 143 143 143 143 143 143 143 143
-- 66,000 LB --
VFS = 162 KCAS FLD LNGTH 6,190 5,930 5,530 5,180 4,870 4,680 4,590 4,520 4,410 4,260 4,120
VSE = 169 KCAS V1 KCAS 134 133 131 130 129 128 128 128 128 128 128
VREF = 149 KCAS VR KCAS 137 137 137 136 135 135 135 135 135 135 135
MAX TEMP = 48°C V2 KCAS 141 141 141 141 141 141 141 141 141 141 141
-- 64,000 LB --
VFS = 160 KCAS FLD LNGTH 5,800 5,560 5,200 4,870 4,580 4,410 4,330 4,260 4,160 4,020 3,880
VSE = 166 KCAS V1 KCAS 131 130 129 127 126 125 125 125 126 126 126
VREF = 147 KCAS VR KCAS 135 135 134 134 133 133 133 133 133 133 133
MAX TEMP = 48°C V2 KCAS 139 139 139 139 139 139 139 139 139 139 139
-- 62,000 LB --
VFS = 157 KCAS FLD LNGTH 5,430 5,220 4,880 4,580 4,320 4,150 4,080 4,010 3,910 3,780 3,650
VSE = 164 KCAS V1 KCAS 128 127 126 124 123 122 122 122 123 123 123
VREF = 144 KCAS VR KCAS 132 132 132 131 130 130 130 130 130 130 130
MAX TEMP = 48°C V2 KCAS 137 137 137 137 137 137 137 137 137 137 137
CAUTION: DO NOT REDUCE TAKEOFF EPR BY MORE THAN .15 OR BELOW A MINIMUM VALUE OF 1.56.
NOTES: HEADWIND: Increase available field length 2% for each 5 knots (up to 40 knots).
TAILWIND: Decrease available field length 11% for each 5 knots (up to 10 knots).
UPHILL SLOPE: Decrease available field length 20% for each 1% (up to 2%).
DOWNHILL SLOPE: No adjustments required (up to 2%).
GROUND SPOILERS INOP: Decrease available field length 800 feet.

REVISION 24 (RE-ISSUE) GIV-SP PERFORMANCE

Mar 17/10 (GIV-SP AIRPLANES ONLY) Page PA - 9
 Quick Reference Handbook
GIV-SP Takeoff Planning: Flaps 20° - APA 1000 Feet, ctd…
AFM APP. A

TAKEOFF PLANNING CHART

GIV-SP AIRPORT PRESSURE ALTITUDE = 1,000 FEET TAKEOFF FLAP 20°

74,600 LB MTOGW OAT (°C) 48 45 40 35 30 25 20 15 5 -5 -15
OAT (°F) 118 113 104 95 86 77 68 59 41 23 5
RATED EPR 1.60 1.62 1.64 1.66 1.70 1.71 1.71 1.71 1.71 1.71 1.71
-- 60,000 LB --
VFS = 155 KCAS FLD LNGTH 5,080 4,890 4,580 4,310 4,060 3,910 3,830 3,770 3,680 3,560 3,440
VSE = 161 KCAS V1 KCAS 125 124 123 122 120 120 120 120 120 120 120
VREF = 142 KCAS VR KCAS 130 130 129 129 128 128 128 128 128 128 128
MAX TEMP = 48°C V2 KCAS 135 135 135 135 135 135 135 135 135 135 135
-- 58,000 LB --
VFS = 152 KCAS FLD LNGTH 4,820 4,630 4,350 4,080 3,850 3,710 3,640 3,580 3,500 3,380 3,260
VSE = 158 KCAS V1 KCAS 123 122 121 119 118 117 117 117 118 118 118
VREF = 140 KCAS VR KCAS 128 128 127 127 126 126 126 126 126 126 126
MAX TEMP = 48°C V2 KCAS 133 133 133 133 133 133 133 133 133 133 133
-- 56,000 LB --
VFS = 150 KCAS FLD LNGTH 4,560 4,380 4,120 3,870 3,710 3,630 3,570 3,510 3,410 3,300 3,190
VSE = 156 KCAS V1 KCAS 121 120 119 117 117 117 117 118 118 118 118
VREF = 137 KCAS VR KCAS 127 126 126 125 124 124 124 124 124 124 124
MAX TEMP = 48°C V2 KCAS 132 132 132 132 132 132 132 132 132 132 132
-- 54,000 LB --
VFS = 147 KCAS FLD LNGTH 4,350 4,190 3,940 3,760 3,650 3,560 3,510 3,450 3,360 3,250 3,140
VSE = 153 KCAS V1 KCAS 119 119 117 117 117 118 118 118 118 118 118
VREF = 135 KCAS VR KCAS 126 125 125 124 123 123 123 123 123 123 123
MAX TEMP = 48°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
-- 52,000 LB --
VFS = 144 KCAS FLD LNGTH 4,200 4,040 3,830 3,690 3,580 3,500 3,450 3,390 3,300 3,190 3,080
VSE = 150 KCAS V1 KCAS 119 118 117 117 118 118 118 118 118 118 118
VREF = 132 KCAS VR KCAS 125 125 124 124 123 122 122 122 122 122 122
MAX TEMP = 48°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
-- 50,000 LB --
VFS = 142 KCAS FLD LNGTH 4,050 3,900 3,740 3,620 3,520 3,440 3,390 3,330 3,240 3,140 3,030
VSE = 147 KCAS V1 KCAS 118 117 117 117 118 118 118 118 118 118 119
VREF = 130 KCAS VR KCAS 125 125 124 123 122 122 122 122 122 122 122
MAX TEMP = 48°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
-- 48,000 LB --
VFS = 139 KCAS FLD LNGTH 3,900 3,800 3,660 3,550 3,450 3,380 3,320 3,270 3,180 3,080 2,980
VSE = 144 KCAS V1 KCAS 117 117 117 118 118 118 119 119 119 119 119
VREF = 127 KCAS VR KCAS 124 124 123 123 122 122 121 121 121 121 121
MAX TEMP = 48°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
-- 46,000 LB --
VFS = 136 KCAS FLD LNGTH 3,780 3,700 3,590 3,480 3,390 3,320 3,260 3,210 3,120 3,020 2,920
VSE = 141 KCAS V1 KCAS 117 117 117 118 118 119 119 119 119 119 119
VREF = 124 KCAS VR KCAS 124 124 123 122 121 121 121 121 121 121 121
MAX TEMP = 48°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
CAUTION: DO NOT REDUCE TAKEOFF EPR BY MORE THAN .15 OR BELOW A MINIMUM VALUE OF 1.56.
NOTES: HEADWIND: Increase available field length 2% for each 5 knots (up to 40 knots).
TAILWIND: Decrease available field length 11% for each 5 knots (up to 10 knots).
UPHILL SLOPE: Decrease available field length 20% for each 1% (up to 2%).
DOWNHILL SLOPE: No adjustments required (up to 2%).
GROUND SPOILERS INOP: Decrease available field length 800 feet.

GIV-SP PERFORMANCE REVISION 24 (RE-ISSUE)

Page PA - 10 (GIV-SP AIRPLANES ONLY) Mar 17/10
Quick Reference Handbook
GIV-SP Takeoff Planning: Flaps 20° - APA 2000 Feet
AFM APP. A

TAKEOFF PLANNING CHART

GIV-SP AIRPORT PRESSURE ALTITUDE = 2,000 FEET TAKEOFF FLAP 20°

74,600 LB MTOGW OAT (°C) 45 40 35 30 25 20 15 10 0 -10 -19
OAT (°F) 113 104 95 86 77 68 59 50 32 14 -2
RATED EPR 1.62 1.64 1.66 1.69 1.71 1.72 1.72 1.72 1.72 1.72 1.72
-- 74,600 LB --
VFS = 173 KCAS FLD LNGTH 8,720 7,810 7,220 6,730 6,360 6,220 6,080 5,950 5,800 5,610 5,430
VSE = 180 KCAS V1 KCAS 146 145 143 141 140 140 140 140 140 140 140
VREF = 158 KCAS VR KCAS 146 146 146 146 146 146 146 145 145 145 145
MAX TEMP = 45°C V2 KCAS 150 150 150 150 150 150 150 150 150 150 150
-- 74,000 LB --
VFS = 172 KCAS FLD LNGTH 8,510 7,670 7,100 6,620 6,260 6,120 5,980 5,860 5,710 5,520 5,340
VSE = 179 KCAS V1 KCAS 145 144 142 141 140 139 139 139 139 139 140
VREF = 158 KCAS VR KCAS 145 145 145 145 145 145 145 145 145 145 145
MAX TEMP = 45°C V2 KCAS 149 149 149 149 149 149 149 149 149 149 149
-- 72,000 LB --
VFS = 170 KCAS FLD LNGTH 7,870 7,210 6,690 6,260 5,930 5,790 5,660 5,550 5,410 5,220 5,060
VSE = 177 KCAS V1 KCAS 143 141 139 138 137 137 137 136 137 137 137
VREF = 156 KCAS VR KCAS 143 143 143 143 143 143 143 142 142 142 142
MAX TEMP = 46°C V2 KCAS 147 147 147 147 147 147 147 147 147 147 147
-- 70,000 LB --
VFS = 167 KCAS FLD LNGTH 7,350 6,780 6,310 5,910 5,610 5,480 5,360 5,250 5,120 4,940 4,790
VSE = 174 KCAS V1 KCAS 140 138 137 135 134 134 134 134 134 134 134
VREF = 154 KCAS VR KCAS 141 141 141 141 140 140 140 140 140 140 140
MAX TEMP = 46°C V2 KCAS 145 145 145 145 145 145 145 145 145 145 145
-- 68,000 LB --
VFS = 165 KCAS FLD LNGTH 6,880 6,370 5,940 5,570 5,290 5,170 5,060 4,950 4,830 4,670 4,520
VSE = 172 KCAS V1 KCAS 137 135 134 132 132 131 131 131 131 131 132
VREF = 151 KCAS VR KCAS 139 139 139 138 138 138 138 138 138 138 138
MAX TEMP = 46°C V2 KCAS 143 143 143 143 143 143 143 143 143 143 143
-- 66,000 LB --
VFS = 162 KCAS FLD LNGTH 6,440 5,980 5,590 5,250 4,990 4,880 4,770 4,670 4,550 4,400 4,260
VSE = 169 KCAS V1 KCAS 134 132 131 130 129 129 129 128 129 129 129
VREF = 149 KCAS VR KCAS 137 137 136 136 135 135 135 135 135 135 135
MAX TEMP = 46°C V2 KCAS 141 141 141 141 141 141 141 141 141 141 141
-- 64,000 LB --
VFS = 160 KCAS FLD LNGTH 6,030 5,610 5,260 4,940 4,700 4,590 4,490 4,400 4,290 4,150 4,010
VSE = 166 KCAS V1 KCAS 131 130 128 127 126 126 126 126 126 126 126
VREF = 147 KCAS VR KCAS 135 135 134 133 133 133 133 133 133 133 133
MAX TEMP = 46°C V2 KCAS 139 139 139 139 139 139 139 139 139 139 139
-- 62,000 LB --
VFS = 157 KCAS FLD LNGTH 5,640 5,270 4,940 4,650 4,420 4,320 4,230 4,140 4,040 3,900 3,780
VSE = 164 KCAS V1 KCAS 128 127 126 124 123 123 123 123 123 123 123
VREF = 145 KCAS VR KCAS 133 132 132 131 130 130 130 130 130 130 130
MAX TEMP = 46°C V2 KCAS 137 137 137 137 137 137 137 137 137 137 137
CAUTION: DO NOT REDUCE TAKEOFF EPR BY MORE THAN .15 OR BELOW A MINIMUM VALUE OF 1.56.
NOTES: HEADWIND: Increase available field length 2% for each 5 knots (up to 40 knots).
TAILWIND: Decrease available field length 11% for each 5 knots (up to 10 knots).
UPHILL SLOPE: Decrease available field length 20% for each 1% (up to 2%).
DOWNHILL SLOPE: No adjustments required (up to 2%).
GROUND SPOILERS INOP: Decrease available field length 800 feet.

REVISION 24 (RE-ISSUE) GIV-SP PERFORMANCE

Mar 17/10 (GIV-SP AIRPLANES ONLY) Page PA - 11
 Quick Reference Handbook
GIV-SP Takeoff Planning: Flaps 20° - APA 2000 Feet, ctd…
AFM APP. A

TAKEOFF PLANNING CHART

GIV-SP AIRPORT PRESSURE ALTITUDE = 2,000 FEET TAKEOFF FLAP 20°

74,600 LB MTOGW OAT (°C) 45 40 35 30 25 20 15 10 0 -10 -19
OAT (°F) 113 104 95 86 77 68 59 50 32 14 -2
RATED EPR 1.62 1.64 1.66 1.69 1.71 1.72 1.72 1.72 1.72 1.72 1.72
-- 60,000 LB --
VFS = 155 KCAS FLD LNGTH 5,280 4,940 4,640 4,370 4,150 4,060 3,980 3,890 3,800 3,670 3,550
VSE = 161 KCAS V1 KCAS 125 124 123 121 120 120 120 120 120 120 120
VREF = 142 KCAS VR KCAS 130 130 129 128 128 128 128 128 128 128 128
MAX TEMP = 46°C V2 KCAS 135 135 135 135 135 135 135 135 135 135 135
-- 58,000 LB --
VFS = 152 KCAS FLD LNGTH 5,000 4,680 4,400 4,140 3,940 3,860 3,780 3,700 3,610 3,480 3,370
VSE = 158 KCAS V1 KCAS 123 122 121 119 118 118 118 118 118 118 118
VREF = 140 KCAS VR KCAS 129 128 127 127 126 126 126 126 126 126 126
MAX TEMP = 46°C V2 KCAS 133 133 133 133 133 133 133 133 133 133 133
-- 56,000 LB --
VFS = 150 KCAS FLD LNGTH 4,730 4,430 4,170 3,940 3,790 3,730 3,660 3,600 3,490 3,380 3,270
VSE = 156 KCAS V1 KCAS 121 120 118 117 117 117 117 117 117 117 118
VREF = 137 KCAS VR KCAS 127 126 126 125 124 124 124 124 124 124 124
MAX TEMP = 46°C V2 KCAS 132 132 132 132 132 132 132 132 132 132 132
-- 54,000 LB --
VFS = 147 KCAS FLD LNGTH 4,520 4,240 4,000 3,830 3,730 3,660 3,600 3,540 3,430 3,320 3,220
VSE = 153 KCAS V1 KCAS 120 118 117 117 117 117 117 118 118 118 118
VREF = 135 KCAS VR KCAS 126 125 124 124 123 123 123 123 123 123 123
MAX TEMP = 46°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
-- 52,000 LB --
VFS = 144 KCAS FLD LNGTH 4,360 4,090 3,880 3,760 3,660 3,600 3,530 3,470 3,370 3,260 3,160
VSE = 150 KCAS V1 KCAS 119 118 117 117 117 117 118 118 118 118 118
VREF = 132 KCAS VR KCAS 125 125 124 123 123 123 123 123 123 123 123
MAX TEMP = 46°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
-- 50,000 LB --
VFS = 142 KCAS FLD LNGTH 4,200 3,960 3,800 3,690 3,590 3,530 3,470 3,410 3,310 3,200 3,110
VSE = 147 KCAS V1 KCAS 118 117 117 117 118 118 118 118 118 118 118
VREF = 130 KCAS VR KCAS 125 124 124 123 122 122 122 122 122 122 122
MAX TEMP = 46°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
-- 48,000 LB --
VFS = 139 KCAS FLD LNGTH 4,050 3,850 3,730 3,620 3,520 3,460 3,410 3,350 3,250 3,140 3,050
VSE = 144 KCAS V1 KCAS 118 117 117 118 118 118 118 118 118 119 119
VREF = 127 KCAS VR KCAS 125 124 123 123 122 122 122 122 122 122 122
MAX TEMP = 46°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
-- 46,000 LB --
VFS = 136 KCAS FLD LNGTH 3,900 3,770 3,650 3,550 3,460 3,400 3,340 3,290 3,190 3,090 2,990
VSE = 141 KCAS V1 KCAS 117 117 117 118 118 118 119 119 119 119 119
VREF = 124 KCAS VR KCAS 124 123 123 122 122 121 121 121 121 121 121
MAX TEMP = 46°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
CAUTION: DO NOT REDUCE TAKEOFF EPR BY MORE THAN .15 OR BELOW A MINIMUM VALUE OF 1.56.
NOTES: HEADWIND: Increase available field length 2% for each 5 knots (up to 40 knots).
TAILWIND: Decrease available field length 11% for each 5 knots (up to 10 knots).
UPHILL SLOPE: Decrease available field length 20% for each 1% (up to 2%).
DOWNHILL SLOPE: No adjustments required (up to 2%).
GROUND SPOILERS INOP: Decrease available field length 800 feet.

GIV-SP PERFORMANCE REVISION 24 (RE-ISSUE)

Page PA - 12 (GIV-SP AIRPLANES ONLY) Mar 17/10
Quick Reference Handbook
GIV-SP Takeoff Planning: Flaps 20° - APA 4000 Feet
AFM APP. A

TAKEOFF PLANNING CHART

GIV-SP AIRPORT PRESSURE ALTITUDE = 4,000 FEET TAKEOFF FLAP 20°

74,600 LB MTOGW OAT (°C) 40 35 30 25 20 15 10 5 -5 -15 -23
OAT (°F) 104 95 86 77 68 59 50 41 23 5 -9
RATED EPR 1.63 1.66 1.69 1.71 1.72 1.74 1.74 1.74 1.74 1.74 1.74
-- 74,600 LB --
VFS = 174 KCAS FLD LNGTH ****** 8,800 8,070 7,590 7,270 7,000 6,780 6,660 6,410 6,190 6,010
VSE = 181 KCAS V1 KCAS ****** 146 145 144 143 142 142 142 142 142 142
VREF = 159 KCAS VR KCAS ****** 147 147 147 147 147 147 147 147 147 147
MAX TEMP = 37°C V2 KCAS ****** 151 151 151 151 151 151 151 151 151 151
-- 74,000 LB --
VFS = 174 KCAS FLD LNGTH ****** 8,610 7,930 7,460 7,150 6,890 6,670 6,550 6,310 6,090 5,910
VSE = 181 KCAS V1 KCAS ****** 146 144 143 142 142 141 141 141 141 141
VREF = 158 KCAS VR KCAS ****** 146 146 146 146 146 146 146 146 146 146
MAX TEMP = 37°C V2 KCAS ****** 150 150 150 150 150 150 150 150 150 150
-- 72,000 LB --
VFS = 171 KCAS FLD LNGTH 8,910 8,050 7,470 7,040 6,750 6,510 6,310 6,200 5,970 5,760 5,600
VSE = 178 KCAS V1 KCAS 144 143 141 140 139 139 139 139 139 139 139
VREF = 156 KCAS VR KCAS 144 144 144 144 144 144 144 144 144 144 144
MAX TEMP = 41°C V2 KCAS 148 148 148 148 148 148 148 148 148 148 148
-- 70,000 LB --
VFS = 169 KCAS FLD LNGTH 8,260 7,570 7,040 6,640 6,370 6,150 5,960 5,870 5,650 5,450 5,300
VSE = 176 KCAS V1 KCAS 142 140 138 137 137 136 136 136 136 136 136
VREF = 154 KCAS VR KCAS 142 142 142 142 142 142 142 142 142 142 142
MAX TEMP = 42°C V2 KCAS 146 146 146 146 146 146 146 146 146 146 146
-- 68,000 LB --
VFS = 166 KCAS FLD LNGTH 7,670 7,090 6,610 6,250 6,010 5,800 5,630 5,540 5,330 5,140 5,000
VSE = 173 KCAS V1 KCAS 139 137 136 135 134 134 133 133 133 133 133
VREF = 151 KCAS VR KCAS 140 140 140 140 140 139 139 139 139 139 139
MAX TEMP = 42°C V2 KCAS 144 144 144 144 144 144 144 144 144 144 144
-- 66,000 LB --
VFS = 164 KCAS FLD LNGTH 7,170 6,650 6,210 5,890 5,660 5,470 5,300 5,220 5,020 4,850 4,710
VSE = 171 KCAS V1 KCAS 136 134 133 132 131 131 130 130 130 130 130
VREF = 149 KCAS VR KCAS 138 138 138 137 137 137 137 137 137 137 137
MAX TEMP = 42°C V2 KCAS 142 142 142 142 142 142 142 142 142 142 142
-- 64,000 LB --
VFS = 161 KCAS FLD LNGTH 6,700 6,230 5,830 5,540 5,330 5,150 4,990 4,910 4,730 4,570 4,440
VSE = 168 KCAS V1 KCAS 133 131 130 129 128 128 128 128 128 128 128
VREF = 147 KCAS VR KCAS 136 136 135 135 135 134 134 134 134 134 134
MAX TEMP = 42°C V2 KCAS 140 140 140 140 140 140 140 140 140 140 140
-- 62,000 LB --
VFS = 159 KCAS FLD LNGTH 6,270 5,840 5,480 5,200 5,010 4,840 4,700 4,620 4,450 4,300 4,180
VSE = 165 KCAS V1 KCAS 130 129 127 126 126 125 125 125 125 125 125
VREF = 145 KCAS VR KCAS 134 133 133 132 132 132 132 132 132 132 132
MAX TEMP = 42°C V2 KCAS 138 138 138 138 138 138 138 138 138 138 138
CAUTION: DO NOT REDUCE TAKEOFF EPR BY MORE THAN .15 OR BELOW A MINIMUM VALUE OF 1.56.
NOTES: HEADWIND: Increase available field length 2% for each 5 knots (up to 40 knots).
TAILWIND: Decrease available field length 11% for each 5 knots (up to 10 knots).
UPHILL SLOPE: Decrease available field length 20% for each 1% (up to 2%).
DOWNHILL SLOPE: No adjustments required (up to 2%).
GROUND SPOILERS INOP: Decrease available field length 800 feet.

REVISION 24 (RE-ISSUE) GIV-SP PERFORMANCE

Mar 17/10 (GIV-SP AIRPLANES ONLY) Page PA - 13
 Quick Reference Handbook
GIV-SP Takeoff Planning: Flaps 20° - APA 4000 Feet, ctd…
AFM APP. A
TAKEOFF PLANNING CHART

GIV-SP AIRPORT PRESSURE ALTITUDE = 4,000 FEET TAKEOFF FLAP 20°

74,600 LB MTOGW OAT (°C) 40 35 30 25 20 15 10 5 -5 -15 -23
OAT (°F) 104 95 86 77 68 59 50 41 23 5 -9
RATED EPR 1.63 1.66 1.69 1.71 1.72 1.74 1.74 1.74 1.74 1.74 1.74
-- 60,000 LB --
VFS = 156 KCAS FLD LNGTH 5,850 5,470 5,140 4,880 4,700 4,550 4,410 4,340 4,180 4,040 3,920
VSE = 163 KCAS V1 KCAS 127 126 124 123 123 122 122 122 122 122 122
VREF = 142 KCAS VR KCAS 131 131 130 130 130 129 129 129 129 129 129
MAX TEMP = 42°C V2 KCAS 135 135 135 135 135 135 135 135 135 135 135
-- 58,000 LB --
VFS = 154 KCAS FLD LNGTH 5,510 5,150 4,850 4,610 4,440 4,290 4,170 4,100 3,950 3,810 3,700
VSE = 160 KCAS V1 KCAS 125 123 122 121 120 120 119 120 119 120 120
VREF = 140 KCAS VR KCAS 129 129 128 128 128 127 127 127 127 127 127
MAX TEMP = 42°C V2 KCAS 134 134 134 134 134 134 134 134 134 134 134
-- 56,000 LB --
VFS = 151 KCAS FLD LNGTH 5,170 4,850 4,570 4,340 4,180 4,050 3,930 3,870 3,730 3,600 3,500
VSE = 157 KCAS V1 KCAS 122 121 119 119 118 117 117 117 117 117 117
VREF = 137 KCAS VR KCAS 127 127 126 126 125 125 125 125 125 125 125
MAX TEMP = 42°C V2 KCAS 132 132 132 132 132 132 132 132 132 132 132
-- 54,000 LB --
VFS = 148 KCAS FLD LNGTH 4,920 4,620 4,350 4,140 4,020 3,930 3,850 3,790 3,660 3,530 3,440
VSE = 154 KCAS V1 KCAS 120 119 118 117 117 117 117 117 117 117 117
VREF = 135 KCAS VR KCAS 126 126 125 124 124 124 124 124 123 123 123
MAX TEMP = 42°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
-- 52,000 LB --
VFS = 146 KCAS FLD LNGTH 4,750 4,460 4,210 4,040 3,940 3,860 3,780 3,720 3,590 3,470 3,380
VSE = 151 KCAS V1 KCAS 120 118 117 117 117 117 117 117 117 117 118
VREF = 132 KCAS VR KCAS 126 125 125 124 124 123 123 123 123 123 123
MAX TEMP = 42°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
-- 50,000 LB --
VFS = 143 KCAS FLD LNGTH 4,580 4,300 4,080 3,960 3,870 3,780 3,710 3,650 3,520 3,410 3,310
VSE = 148 KCAS V1 KCAS 119 118 117 117 117 117 118 118 118 118 118
VREF = 130 KCAS VR KCAS 125 125 124 124 123 123 123 123 123 123 123
MAX TEMP = 42°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
-- 48,000 LB --
VFS = 140 KCAS FLD LNGTH 4,400 4,160 3,990 3,880 3,790 3,710 3,630 3,580 3,460 3,340 3,250
VSE = 145 KCAS V1 KCAS 118 117 117 117 117 118 118 118 118 118 118
VREF = 127 KCAS VR KCAS 125 124 124 123 123 123 122 122 122 122 122
MAX TEMP = 42°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
-- 46,000 LB --
VFS = 137 KCAS FLD LNGTH 4,230 4,030 3,900 3,800 3,710 3,640 3,560 3,510 3,390 3,280 3,190
VSE = 142 KCAS V1 KCAS 117 117 117 117 118 118 118 118 118 118 119
VREF = 124 KCAS VR KCAS 125 124 123 123 122 122 122 122 122 122 122
MAX TEMP = 42°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
CAUTION: DO NOT REDUCE TAKEOFF EPR BY MORE THAN .15 OR BELOW A MINIMUM VALUE OF 1.56.
NOTES: HEADWIND: Increase available field length 2% for each 5 knots (up to 40 knots).
TAILWIND: Decrease available field length 11% for each 5 knots (up to 10 knots).
UPHILL SLOPE: Decrease available field length 20% for each 1% (up to 2%).
DOWNHILL SLOPE: No adjustments required (up to 2%).
GROUND SPOILERS INOP: Decrease available field length 800 feet.

GIV-SP PERFORMANCE REVISION 24 (RE-ISSUE)

Page PA - 14 (GIV-SP AIRPLANES ONLY) Mar 17/10
Quick Reference Handbook
GIV-SP Takeoff Planning: Flaps 20° - APA 6000 Feet
AFM APP. A

TAKEOFF PLANNING CHART

GIV-SP AIRPORT PRESSURE ALTITUDE = 6,000 FEET TAKEOFF FLAP 20°

74,600 LB MTOGW OAT (°C) 38 35 30 25 20 15 10 5 -5 -15 -25
OAT (°F) 101 95 86 77 68 59 50 41 23 5 -13
RATED EPR 1.64 1.65 1.68 1.71 1.72 1.73 1.74 1.74 1.75 1.75 1.75
-- 74,600 LB --
VFS = 177 KCAS FLD LNGTH ****** ****** ****** 9,280 8,830 8,480 8,160 7,970 7,600 7,340 7,070
VSE = 184 KCAS V1 KCAS ****** ****** ****** 148 147 146 146 146 145 145 146
VREF = 159 KCAS VR KCAS ****** ****** ****** 148 148 148 148 148 148 148 148
MAX TEMP = 29°C V2 KCAS ****** ****** ****** 152 152 152 152 152 152 152 152
-- 74,000 LB --
VFS = 176 KCAS FLD LNGTH ****** ****** ****** 9,090 8,670 8,330 8,020 7,830 7,470 7,210 6,950
VSE = 183 KCAS V1 KCAS ****** ****** ****** 147 146 146 145 145 145 145 145
VREF = 159 KCAS VR KCAS ****** ****** ****** 148 148 148 148 148 148 148 148
MAX TEMP = 29°C V2 KCAS ****** ****** ****** 152 152 152 152 152 152 152 152
-- 72,000 LB --
VFS = 174 KCAS FLD LNGTH ****** ****** 9,170 8,540 8,160 7,850 7,560 7,380 7,050 6,800 6,560
VSE = 181 KCAS V1 KCAS ****** ****** 145 144 143 143 142 142 142 142 142
VREF = 157 KCAS VR KCAS ****** ****** 146 146 146 146 146 146 146 146 146
MAX TEMP = 32°C V2 KCAS ****** ****** 150 150 150 150 150 150 150 150 150
-- 70,000 LB --
VFS = 171 KCAS FLD LNGTH ****** 9,410 8,540 8,030 7,680 7,400 7,130 6,960 6,650 6,410 6,180
VSE = 178 KCAS V1 KCAS ****** 144 143 141 141 140 140 139 139 139 139
VREF = 154 KCAS VR KCAS ****** 144 144 144 144 144 144 144 144 144 144
MAX TEMP = 35°C V2 KCAS ****** 148 148 148 148 148 148 148 148 148 148
-- 68,000 LB --
VFS = 169 KCAS FLD LNGTH 9,260 8,700 7,990 7,530 7,220 6,950 6,710 6,550 6,260 6,040 5,820
VSE = 175 KCAS V1 KCAS 141 141 140 138 138 137 137 136 136 136 137
VREF = 152 KCAS VR KCAS 142 142 142 142 142 141 141 141 141 141 141
MAX TEMP = 38°C V2 KCAS 146 146 146 146 146 146 146 146 146 146 146
-- 66,000 LB --
VFS = 166 KCAS FLD LNGTH 8,470 8,070 7,480 7,060 6,770 6,530 6,310 6,160 5,900 5,690 5,480
VSE = 173 KCAS V1 KCAS 139 138 137 135 135 134 134 134 134 134 134
VREF = 150 KCAS VR KCAS 139 139 139 139 139 139 139 139 139 139 139
MAX TEMP = 38°C V2 KCAS 143 143 143 143 143 143 143 143 143 143 143
-- 64,000 LB --
VFS = 163 KCAS FLD LNGTH 7,890 7,530 7,000 6,620 6,360 6,140 5,930 5,800 5,550 5,350 5,160
VSE = 170 KCAS V1 KCAS 136 135 134 133 132 131 131 131 131 131 131
VREF = 148 KCAS VR KCAS 137 137 137 137 137 137 137 136 136 136 136
MAX TEMP = 38°C V2 KCAS 141 141 141 141 141 141 141 141 141 141 141
-- 62,000 LB --
VFS = 161 KCAS FLD LNGTH 7,350 7,030 6,550 6,210 5,970 5,760 5,570 5,450 5,210 5,030 4,850
VSE = 167 KCAS V1 KCAS 133 132 131 130 129 129 128 128 128 128 128
VREF = 145 KCAS VR KCAS 135 135 135 135 134 134 134 134 134 134 134
MAX TEMP = 38°C V2 KCAS 139 139 139 139 139 139 139 139 139 139 139
CAUTION: DO NOT REDUCE TAKEOFF EPR BY MORE THAN .15 OR BELOW A MINIMUM VALUE OF 1.56.
NOTES: HEADWIND: Increase available field length 2% for each 5 knots (up to 40 knots).
TAILWIND: Not permitted using this data at this pressure altitude.
UPHILL SLOPE: Decrease available field length 20% for each 1% (up to 2%).
DOWNHILL SLOPE: Not permitted using this data at this pressure altitude.
GROUND SPOILERS INOP: Decrease available field length 800 feet.

REVISION 24 (RE-ISSUE) GIV-SP PERFORMANCE

Mar 17/10 (GIV-SP AIRPLANES ONLY) Page PA - 15
 Quick Reference Handbook
GIV-SP Takeoff Planning: Flaps 20° - APA 6000 Feet, ctd…
AFM APP. A

TAKEOFF PLANNING CHART

GIV-SP AIRPORT PRESSURE ALTITUDE = 6,000 FEET TAKEOFF FLAP 20°

74,600 LB MTOGW OAT (°C) 38 35 30 25 20 15 10 5 -5 -15 -25
OAT (°F) 101 95 86 77 68 59 50 41 23 5 -13
RATED EPR 1.64 1.65 1.68 1.71 1.72 1.73 1.74 1.74 1.75 1.75 1.75
-- 60,000 LB --
VFS = 158 KCAS FLD LNGTH 6,850 6,560 6,130 5,820 5,600 5,410 5,230 5,110 4,890 4,720 4,550
VSE = 165 KCAS V1 KCAS 130 129 128 127 126 126 125 125 125 125 125
VREF = 143 KCAS VR KCAS 133 133 133 132 132 132 132 131 131 131 131
MAX TEMP = 38°C V2 KCAS 137 137 137 137 137 137 137 137 137 137 137
-- 58,000 LB --
VFS = 156 KCAS FLD LNGTH 6,370 6,110 5,720 5,440 5,230 5,060 4,890 4,790 4,580 4,420 4,260
VSE = 162 KCAS V1 KCAS 127 126 125 124 123 123 122 122 122 122 122
VREF = 140 KCAS VR KCAS 130 130 130 130 129 129 129 129 129 129 129
MAX TEMP = 38°C V2 KCAS 134 134 134 134 134 134 134 134 134 134 134
-- 56,000 LB --
VFS = 153 KCAS FLD LNGTH 5,920 5,690 5,340 5,080 4,890 4,730 4,570 4,480 4,290 4,140 3,990
VSE = 159 KCAS V1 KCAS 124 123 122 121 120 120 119 119 119 119 119
VREF = 138 KCAS VR KCAS 128 128 127 127 127 126 126 126 126 126 126
MAX TEMP = 38°C V2 KCAS 132 132 132 132 132 132 132 132 132 132 132
-- 54,000 LB --
VFS = 150 KCAS FLD LNGTH 5,600 5,390 5,070 4,820 4,640 4,490 4,350 4,250 4,070 3,930 3,790
VSE = 156 KCAS V1 KCAS 122 121 120 119 118 118 117 117 117 117 117
VREF = 135 KCAS VR KCAS 127 126 126 125 125 125 125 125 124 124 124
MAX TEMP = 38°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
-- 52,000 LB --
VFS = 147 KCAS FLD LNGTH 5,400 5,200 4,890 4,650 4,480 4,340 4,200 4,110 3,950 3,820 3,690
VSE = 153 KCAS V1 KCAS 121 120 119 118 118 117 117 117 117 117 117
VREF = 133 KCAS VR KCAS 126 126 126 125 125 125 124 124 124 124 124
MAX TEMP = 38°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
-- 50,000 LB --
VFS = 145 KCAS FLD LNGTH 5,200 5,010 4,710 4,480 4,320 4,200 4,100 4,020 3,880 3,740 3,610
VSE = 150 KCAS V1 KCAS 120 120 118 117 117 117 117 117 117 117 117
VREF = 130 KCAS VR KCAS 126 126 125 125 124 124 124 124 124 124 124
MAX TEMP = 38°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
-- 48,000 LB --
VFS = 141 KCAS FLD LNGTH 5,000 4,820 4,530 4,320 4,190 4,100 4,010 3,940 3,800 3,670 3,540
VSE = 147 KCAS V1 KCAS 120 119 118 117 117 117 117 117 117 117 118
VREF = 128 KCAS VR KCAS 126 125 125 124 124 124 123 123 123 123 123
MAX TEMP = 38°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
-- 46,000 LB --
VFS = 138 KCAS FLD LNGTH 4,810 4,630 4,360 4,200 4,100 4,010 3,930 3,860 3,720 3,590 3,470
VSE = 144 KCAS V1 KCAS 119 118 117 117 117 117 117 117 117 118 118
VREF = 125 KCAS VR KCAS 125 125 124 124 124 123 123 123 123 123 123
MAX TEMP = 38°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
CAUTION: DO NOT REDUCE TAKEOFF EPR BY MORE THAN .15 OR BELOW A MINIMUM VALUE OF 1.56.
NOTES: HEADWIND: Increase available field length 2% for each 5 knots (up to 40 knots).
TAILWIND: Not permitted using this data at this pressure altitude.
UPHILL SLOPE: Decrease available field length 20% for each 1% (up to 2%).
DOWNHILL SLOPE: Not permitted using this data at this pressure altitude.
GROUND SPOILERS INOP: Decrease available field length 800 feet.

GIV-SP PERFORMANCE REVISION 24 (RE-ISSUE)

Page PA - 16 (GIV-SP AIRPLANES ONLY) Mar 17/10
Quick Reference Handbook
GIV-SP Takeoff Planning: Flaps 20° - APA 8000 Feet
AFM APP. A

TAKEOFF PLANNING CHART

GIV-SP AIRPORT PRESSURE ALTITUDE = 8,000 FEET TAKEOFF FLAP 20°

74,600 LB MTOGW OAT (°C) 34 30 25 20 15 10 5 0 -10 -20 -30
OAT (°F) 93 86 77 68 59 50 41 32 14 -4 -22
RATED EPR 1.66 1.68 1.70 1.71 1.72 1.73 1.74 1.75 1.75 1.75 1.75
-- 74,600 LB --
VFS = 179 KCAS FLD LNGTH ****** ****** ****** ****** ****** 10,130 9,770 9,370 8,950 8,630 8,310
VSE = 186 KCAS V1 KCAS ****** ****** ****** ****** ****** 150 150 149 149 149 150
VREF = 161 KCAS VR KCAS ****** ****** ****** ****** ****** 150 150 150 150 150 150
MAX TEMP = 10°C V2 KCAS ****** ****** ****** ****** ****** 154 154 154 154 154 154
-- 74,000 LB --
VFS = 178 KCAS FLD LNGTH ****** ****** ****** ****** ****** 9,890 9,560 9,190 8,780 8,470 8,160
VSE = 185 KCAS V1 KCAS ****** ****** ****** ****** ****** 149 149 149 148 148 149
VREF = 160 KCAS VR KCAS ****** ****** ****** ****** ****** 149 149 149 149 149 149
MAX TEMP = 12°C V2 KCAS ****** ****** ****** ****** ****** 153 153 153 153 153 153
-- 72,000 LB --
VFS = 176 KCAS FLD LNGTH ****** ****** ****** ****** 9,670 9,240 8,960 8,640 8,260 7,970 7,670
VSE = 183 KCAS V1 KCAS ****** ****** ****** ****** 147 146 146 146 145 145 146
VREF = 158 KCAS VR KCAS ****** ****** ****** ****** 147 147 147 147 147 147 147
MAX TEMP = 19°C V2 KCAS ****** ****** ****** ****** 151 151 151 151 151 151 151
-- 70,000 LB --
VFS = 173 KCAS FLD LNGTH ****** ****** 10,010 9,450 9,040 8,670 8,420 8,130 7,770 7,490 7,220
VSE = 180 KCAS V1 KCAS ****** ****** 145 145 144 144 143 143 143 143 143
VREF = 156 KCAS VR KCAS ****** ****** 145 145 145 145 145 145 145 145 145
MAX TEMP = 25°C V2 KCAS ****** ****** 149 149 149 149 149 149 149 149 149
-- 68,000 LB --
VFS = 171 KCAS FLD LNGTH ****** ****** 9,250 8,820 8,460 8,130 7,900 7,630 7,300 7,040 6,780
VSE = 178 KCAS V1 KCAS ****** ****** 143 142 141 141 140 140 140 140 140
VREF = 154 KCAS VR KCAS ****** ****** 143 143 143 143 143 143 143 143 143
MAX TEMP = 29°C V2 KCAS ****** ****** 147 147 147 147 147 147 147 147 147
-- 66,000 LB --
VFS = 168 KCAS FLD LNGTH ****** 9,230 8,610 8,250 7,920 7,620 7,410 7,150 6,850 6,600 6,360
VSE = 175 KCAS V1 KCAS ****** 141 139 139 138 138 137 137 137 137 137
VREF = 151 KCAS VR KCAS ****** 141 141 141 141 141 141 141 141 141 141
MAX TEMP = 33°C V2 KCAS ****** 145 145 145 145 145 145 145 145 145 145
-- 64,000 LB --
VFS = 166 KCAS FLD LNGTH 9,210 8,560 8,040 7,710 7,420 7,140 6,940 6,710 6,420 6,190 5,960
VSE = 172 KCAS V1 KCAS 138 137 136 136 135 135 134 134 134 134 134
VREF = 149 KCAS VR KCAS 139 139 139 139 139 138 138 138 138 138 138
MAX TEMP = 34°C V2 KCAS 143 143 143 143 143 143 143 143 143 143 143
-- 62,000 LB --
VFS = 163 KCAS FLD LNGTH 8,460 7,960 7,510 7,210 6,940 6,680 6,510 6,290 6,030 5,810 5,600
VSE = 169 KCAS V1 KCAS 136 135 133 133 132 132 131 131 131 131 131
VREF = 147 KCAS VR KCAS 136 136 136 136 136 136 136 136 136 136 136
MAX TEMP = 34°C V2 KCAS 140 140 140 140 140 140 140 140 140 140 140
CAUTION: DO NOT REDUCE TAKEOFF EPR BY MORE THAN .15 OR BELOW A MINIMUM VALUE OF 1.56.
NOTES: HEADWIND: Increase available field length 2% for each 5 knots (up to 40 knots).
TAILWIND: Not permitted using this data at this pressure altitude.
UPHILL SLOPE: Decrease available field length 20% for each 1% (up to 2%).
DOWNHILL SLOPE: Not permitted using this data at this pressure altitude.
GROUND SPOILERS INOP: Decrease available field length 800 feet.

REVISION 24 (RE-ISSUE) GIV-SP PERFORMANCE

Mar 17/10 (GIV-SP AIRPLANES ONLY) Page PA - 17
 Quick Reference Handbook
GIV-SP Takeoff Planning: Flaps 20° - APA 8000 Feet, ctd…
AFM APP. A

TAKEOFF PLANNING CHART

GIV-SP AIRPORT PRESSURE ALTITUDE = 8,000 FEET TAKEOFF FLAP 20°

74,600 LB MTOGW OAT (°C) 34 30 25 20 15 10 5 0 -10 -20 -30
OAT (°F) 93 86 77 68 59 50 41 32 14 -4 -22
RATED EPR 1.66 1.68 1.70 1.71 1.72 1.73 1.74 1.75 1.75 1.75 1.75
-- 60,000 LB --
VFS = 160 KCAS FLD LNGTH 7,860 7,420 7,010 6,730 6,480 6,250 6,090 5,900 5,650 5,450 5,250
VSE = 167 KCAS V1 KCAS 133 131 130 130 129 129 128 128 128 128 128
VREF = 144 KCAS VR KCAS 134 134 134 134 134 134 134 134 133 133 133
MAX TEMP = 34°C V2 KCAS 138 138 138 138 138 138 138 138 138 138 138
-- 58,000 LB --
VFS = 158 KCAS FLD LNGTH 7,290 6,890 6,530 6,270 6,050 5,830 5,690 5,510 5,280 5,090 4,900
VSE = 164 KCAS V1 KCAS 129 128 127 127 126 126 125 125 125 125 125
VREF = 142 KCAS VR KCAS 132 132 132 131 131 131 131 131 131 131 131
MAX TEMP = 34°C V2 KCAS 136 136 136 136 136 136 136 136 136 136 136
-- 56,000 LB --
VFS = 155 KCAS FLD LNGTH 6,750 6,390 6,070 5,840 5,640 5,440 5,300 5,140 4,920 4,750 4,580
VSE = 161 KCAS V1 KCAS 126 125 124 124 123 122 122 122 122 122 122
VREF = 139 KCAS VR KCAS 129 129 129 129 129 128 128 128 128 128 128
MAX TEMP = 34°C V2 KCAS 133 133 133 133 133 133 133 133 133 133 133
-- 54,000 LB --
VFS = 152 KCAS FLD LNGTH 6,350 6,020 5,730 5,520 5,330 5,140 5,010 4,860 4,660 4,490 4,330
VSE = 158 KCAS V1 KCAS 124 123 122 121 121 120 120 120 120 120 120
VREF = 137 KCAS VR KCAS 128 128 127 127 127 127 126 126 126 126 126
MAX TEMP = 34°C V2 KCAS 132 132 132 132 132 132 132 132 132 132 132
-- 52,000 LB --
VFS = 149 KCAS FLD LNGTH 6,070 5,770 5,490 5,290 5,110 4,930 4,810 4,660 4,470 4,310 4,150
VSE = 155 KCAS V1 KCAS 123 122 121 120 120 119 119 119 119 119 119
VREF = 134 KCAS VR KCAS 127 127 127 126 126 126 126 125 125 125 125
MAX TEMP = 34°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
-- 50,000 LB --
VFS = 146 KCAS FLD LNGTH 5,800 5,520 5,250 5,060 4,890 4,720 4,600 4,460 4,280 4,120 3,970
VSE = 152 KCAS V1 KCAS 121 121 120 119 119 118 118 117 117 117 118
VREF = 132 KCAS VR KCAS 127 126 126 125 125 125 125 125 124 124 124
MAX TEMP = 34°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
-- 48,000 LB --
VFS = 143 KCAS FLD LNGTH 5,570 5,300 5,050 4,870 4,700 4,540 4,430 4,290 4,120 3,970 3,830
VSE = 149 KCAS V1 KCAS 121 120 119 118 118 117 117 117 117 117 117
VREF = 129 KCAS VR KCAS 126 126 125 125 125 125 124 124 124 124 124
MAX TEMP = 34°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
-- 46,000 LB --
VFS = 140 KCAS FLD LNGTH 5,350 5,090 4,850 4,680 4,520 4,370 4,280 4,180 4,030 3,890 3,750
VSE = 146 KCAS V1 KCAS 120 119 118 117 117 116 116 117 117 117 117
VREF = 126 KCAS VR KCAS 126 125 125 125 124 124 124 124 124 124 124
MAX TEMP = 34°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
CAUTION: DO NOT REDUCE TAKEOFF EPR BY MORE THAN .15 OR BELOW A MINIMUM VALUE OF 1.56.
NOTES: HEADWIND: Increase available field length 2% for each 5 knots (up to 40 knots).
TAILWIND: Not permitted using this data at this pressure altitude.
UPHILL SLOPE: Decrease available field length 20% for each 1% (up to 2%).
DOWNHILL SLOPE: Not permitted using this data at this pressure altitude.
GROUND SPOILERS INOP: Decrease available field length 800 feet.

GIV-SP PERFORMANCE REVISION 24 (RE-ISSUE)

Page PA - 18 (GIV-SP AIRPLANES ONLY) Mar 17/10
Quick Reference Handbook
GIV-SP Takeoff Planning Charts: Flaps 10° AFM APP. A

The charts in this section provide quick reference planning data for
takeoff planning at the following Airport Pressure Altitudes (APA), for
10° flap configurations:
• Sea Level • 500 Feet • 1000 Feet • 2000 Feet
• 4000 Feet • 6000 Feet • 8000 Feet

These charts are for use for airplanes SN 1214 and subsequent
and SN 1000 thru 1213 with ASC 190 incorporated.

In the interest of safety, the CAUTION and NOTES following each

takeoff planning chart must be observed when using any takeoff
planning chart in this section.

REVISION 24 (RE-ISSUE) GIV-SP PERFORMANCE

Mar 17/10 (GIV-SP AIRPLANES ONLY) Page PA - 19
 Quick Reference Handbook
GIV-SP Takeoff Planning: Flaps 10° - APA Sea Level
AFM APP. A

TAKEOFF PLANNING CHART

GIV-SP AIRPORT PRESSURE ALTITUDE = SEA LEVEL TAKEOFF FLAP 10°

74,600 LB MTOGW OAT (°C) 50 45 40 35 30 25 20 15 5 -5 -15
OAT (°F) 122 113 104 95 86 77 68 59 41 23 5
RATED EPR 1.59 1.62 1.64 1.67 1.70 1.70 1.70 1.70 1.69 1.69 1.69
-- 74,600 LB --
VFS = 173 KCAS FLD LNGTH 8,190 7,570 7,050 6,580 6,170 6,070 5,980 5,880 5,740 5,540 5,350
VSE = 180 KCAS V1 KCAS 151 149 147 146 144 144 144 144 145 145 145
VREF = 158 KCAS VR KCAS 152 151 151 151 150 150 150 150 150 150 150
MAX TEMP = 50°C V2 KCAS 157 157 157 157 157 157 157 157 157 157 157
-- 74,000 LB --
VFS = 172 KCAS FLD LNGTH 8,040 7,440 6,930 6,470 6,070 5,970 5,880 5,790 5,640 5,450 5,260
VSE = 179 KCAS V1 KCAS 150 148 146 145 144 144 144 144 144 144 144
VREF = 158 KCAS VR KCAS 151 151 150 150 150 150 150 150 150 150 150
MAX TEMP = 50°C V2 KCAS 156 156 156 156 156 156 156 156 156 156 156
-- 72,000 LB --
VFS = 170 KCAS FLD LNGTH 7,580 7,030 6,550 6,120 5,750 5,660 5,570 5,480 5,340 5,160 4,990
VSE = 177 KCAS V1 KCAS 147 145 144 142 141 141 141 141 141 141 141
VREF = 156 KCAS VR KCAS 149 149 148 148 147 147 147 147 147 147 147
MAX TEMP = 50°C V2 KCAS 154 154 154 154 154 154 154 154 154 154 154
-- 70,000 LB --
VFS = 167 KCAS FLD LNGTH 7,140 6,630 6,190 5,790 5,440 5,350 5,270 5,180 5,060 4,890 4,720
VSE = 174 KCAS V1 KCAS 144 143 141 139 138 138 138 138 138 138 139
VREF = 154 KCAS VR KCAS 147 146 146 145 145 145 145 145 145 145 145
MAX TEMP = 50°C V2 KCAS 152 152 152 152 152 152 152 152 152 152 152
-- 68,000 LB --
VFS = 165 KCAS FLD LNGTH 6,710 6,240 5,830 5,460 5,130 5,050 4,970 4,890 4,770 4,610 4,450
VSE = 171 KCAS V1 KCAS 141 140 138 137 135 135 135 135 136 136 136
VREF = 151 KCAS VR KCAS 144 144 143 143 143 143 143 143 143 143 143
MAX TEMP = 50°C V2 KCAS 149 149 149 149 149 149 149 149 149 149 149
-- 66,000 LB --
VFS = 162 KCAS FLD LNGTH 6,310 5,870 5,490 5,140 4,840 4,760 4,690 4,610 4,500 4,350 4,200
VSE = 169 KCAS V1 KCAS 138 137 135 134 132 132 132 132 133 133 133
VREF = 149 KCAS VR KCAS 142 141 141 141 140 140 140 140 140 140 140
MAX TEMP = 50°C V2 KCAS 147 147 147 147 147 147 147 147 147 147 147
-- 64,000 LB --
VFS = 160 KCAS FLD LNGTH 5,920 5,510 5,160 4,840 4,560 4,480 4,410 4,340 4,240 4,090 3,950
VSE = 166 KCAS V1 KCAS 135 134 132 131 129 129 129 129 130 130 130
VREF = 147 KCAS VR KCAS 139 139 139 138 138 138 138 138 138 138 138
MAX TEMP = 50°C V2 KCAS 145 145 145 145 145 145 145 145 145 145 145
-- 62,000 LB --
VFS = 157 KCAS FLD LNGTH 5,550 5,180 4,850 4,550 4,290 4,220 4,150 4,090 3,990 3,850 3,720
VSE = 164 KCAS V1 KCAS 132 131 129 128 126 126 126 126 127 127 127
VREF = 144 KCAS VR KCAS 137 137 136 136 135 135 135 135 135 135 135
MAX TEMP = 50°C V2 KCAS 143 143 143 143 143 143 143 143 143 143 143
CAUTION: DO NOT REDUCE TAKEOFF EPR BY MORE THAN .15 OR BELOW A MINIMUM VALUE OF 1.56.
NOTES: HEADWIND: Increase available field length 2% for each 5 knots (up to 40 knots).
TAILWIND: Decrease available field length 11% for each 5 knots (up to 10 knots).
UPHILL SLOPE: Decrease available field length 20% for each 1% (up to 2%).
DOWNHILL SLOPE: No adjustments required (up to 2%).

GIV-SP PERFORMANCE REVISION 24 (RE-ISSUE)

Page PA - 20 (GIV-SP AIRPLANES ONLY) Mar 17/10
Quick Reference Handbook
GIV-SP Takeoff Planning: Flaps 10° - APA Sea Level, ctd…
AFM APP. A

TAKEOFF PLANNING CHART

GIV-SP AIRPORT PRESSURE ALTITUDE = SEA LEVEL TAKEOFF FLAP 10°

74,600 LB MTOGW OAT (°C) 50 45 40 35 30 25 20 15 5 -5 -15
OAT (°F) 122 113 104 95 86 77 68 59 41 23 5
RATED EPR 1.59 1.62 1.64 1.67 1.70 1.70 1.70 1.70 1.69 1.69 1.69
-- 60,000 LB --
VFS = 155 KCAS FLD LNGTH 5,200 4,850 4,550 4,270 4,030 3,970 3,900 3,840 3,750 3,620 3,500
VSE = 161 KCAS V1 KCAS 129 128 126 125 123 123 123 123 124 124 124
VREF = 142 KCAS VR KCAS 135 134 134 133 133 133 133 133 133 133 133
MAX TEMP = 50°C V2 KCAS 140 140 140 140 140 140 140 140 140 140 140
-- 58,000 LB --
VFS = 152 KCAS FLD LNGTH 4,850 4,530 4,250 4,000 3,770 3,710 3,660 3,600 3,510 3,390 3,270
VSE = 158 KCAS V1 KCAS 126 125 123 122 120 120 120 120 120 120 121
VREF = 140 KCAS VR KCAS 132 132 131 131 130 130 130 130 130 130 130
MAX TEMP = 50°C V2 KCAS 138 138 138 138 138 138 138 138 138 138 138
-- 56,000 LB --
VFS = 150 KCAS FLD LNGTH 4,520 4,230 3,970 3,740 3,570 3,520 3,470 3,410 3,320 3,210 3,100
VSE = 156 KCAS V1 KCAS 123 121 120 118 118 118 118 118 118 118 118
VREF = 137 KCAS VR KCAS 129 129 128 128 127 127 127 127 127 127 127
MAX TEMP = 50°C V2 KCAS 136 136 136 136 136 136 136 136 136 136 136
-- 54,000 LB --
VFS = 147 KCAS FLD LNGTH 4,240 3,970 3,740 3,620 3,520 3,460 3,410 3,360 3,260 3,160 3,050
VSE = 153 KCAS V1 KCAS 120 119 117 117 118 118 118 118 118 118 118
VREF = 135 KCAS VR KCAS 127 127 126 126 125 125 125 125 125 125 125
MAX TEMP = 50°C V2 KCAS 134 134 134 134 134 134 134 134 134 134 134
-- 52,000 LB --
VFS = 144 KCAS FLD LNGTH 4,010 3,780 3,660 3,560 3,460 3,410 3,360 3,310 3,210 3,110 3,010
VSE = 150 KCAS V1 KCAS 118 117 117 118 118 118 118 118 118 119 119
VREF = 132 KCAS VR KCAS 126 125 125 124 124 124 124 124 124 124 124
MAX TEMP = 50°C V2 KCAS 132 132 132 132 132 132 132 132 132 132 132
-- 50,000 LB --
VFS = 142 KCAS FLD LNGTH 3,830 3,710 3,600 3,490 3,400 3,350 3,300 3,250 3,160 3,060 2,960
VSE = 147 KCAS V1 KCAS 117 117 118 118 119 119 119 119 119 119 119
VREF = 130 KCAS VR KCAS 124 124 123 123 122 122 122 122 122 122 122
MAX TEMP = 50°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
-- 48,000 LB --
VFS = 139 KCAS FLD LNGTH 3,760 3,640 3,530 3,430 3,340 3,290 3,250 3,200 3,100 3,010 2,910
VSE = 144 KCAS V1 KCAS 117 117 118 118 119 119 119 119 119 119 119
VREF = 127 KCAS VR KCAS 124 123 123 122 122 122 122 122 122 122 122
MAX TEMP = 50°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
-- 46,000 LB --
VFS = 136 KCAS FLD LNGTH 3,680 3,570 3,470 3,370 3,280 3,240 3,190 3,140 3,050 2,950 2,860
VSE = 141 KCAS V1 KCAS 117 118 118 119 119 119 119 119 119 120 120
VREF = 124 KCAS VR KCAS 124 123 123 122 121 121 121 121 121 121 121
MAX TEMP = 50°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
CAUTION: DO NOT REDUCE TAKEOFF EPR BY MORE THAN .15 OR BELOW A MINIMUM VALUE OF 1.56.
NOTES: HEADWIND: Increase available field length 2% for each 5 knots (up to 40 knots).
TAILWIND: Decrease available field length 11% for each 5 knots (up to 10 knots).
UPHILL SLOPE: Decrease available field length 20% for each 1% (up to 2%).
DOWNHILL SLOPE: No adjustments required (up to 2%).

REVISION 24 (RE-ISSUE) GIV-SP PERFORMANCE

Mar 17/10 (GIV-SP AIRPLANES ONLY) Page PA - 21
 Quick Reference Handbook
GIV-SP Takeoff Planning: Flaps 10° - APA 500 Feet
AFM APP. A

TAKEOFF PLANNING CHART

GIV-SP AIRPORT PRESSURE ALTITUDE = 500 FEET TAKEOFF FLAP 10°

74,600 LB MTOGW OAT (°C) 49 45 40 35 30 25 20 15 5 -5 -15
OAT (°F) 120 113 104 95 86 77 68 59 41 23 5
RATED EPR 1.59 1.62 1.64 1.67 1.70 1.71 1.71 1.71 1.70 1.70 1.70
-- 74,600 LB --
VFS = 173 KCAS FLD LNGTH 8,400 7,900 7,340 6,840 6,410 6,230 6,120 6,020 5,880 5,680 5,480
VSE = 180 KCAS V1 KCAS 151 150 148 146 145 145 145 145 145 145 145
VREF = 158 KCAS VR KCAS 152 152 151 151 150 150 150 150 150 150 150
MAX TEMP = 49°C V2 KCAS 157 157 157 157 157 157 157 157 157 157 157
-- 74,000 LB --
VFS = 172 KCAS FLD LNGTH 8,250 7,760 7,220 6,730 6,310 6,130 6,020 5,930 5,780 5,590 5,390
VSE = 179 KCAS V1 KCAS 150 149 147 145 144 144 144 144 144 144 144
VREF = 158 KCAS VR KCAS 151 151 151 150 150 150 150 150 150 150 150
MAX TEMP = 49°C V2 KCAS 156 156 156 156 156 156 156 156 156 156 156
-- 72,000 LB --
VFS = 170 KCAS FLD LNGTH 7,780 7,320 6,820 6,370 5,970 5,800 5,700 5,610 5,480 5,290 5,110
VSE = 177 KCAS V1 KCAS 147 146 144 143 141 141 141 141 141 141 141
VREF = 156 KCAS VR KCAS 149 149 148 148 147 147 147 147 147 147 147
MAX TEMP = 49°C V2 KCAS 154 154 154 154 154 154 154 154 154 154 154
-- 70,000 LB --
VFS = 167 KCAS FLD LNGTH 7,320 6,910 6,440 6,020 5,650 5,490 5,400 5,310 5,180 5,010 4,830
VSE = 174 KCAS V1 KCAS 144 143 142 140 138 138 138 138 139 139 139
VREF = 154 KCAS VR KCAS 147 146 146 146 145 145 145 145 145 145 145
MAX TEMP = 49°C V2 KCAS 152 152 152 152 152 152 152 152 152 152 152
-- 68,000 LB --
VFS = 165 KCAS FLD LNGTH 6,880 6,500 6,060 5,670 5,330 5,180 5,090 5,010 4,890 4,720 4,560
VSE = 172 KCAS V1 KCAS 141 140 139 137 136 135 135 135 136 136 136
VREF = 151 KCAS VR KCAS 144 144 144 143 143 143 143 143 143 143 143
MAX TEMP = 49°C V2 KCAS 149 149 149 149 149 149 149 149 149 149 149
-- 66,000 LB --
VFS = 162 KCAS FLD LNGTH 6,460 6,110 5,700 5,340 5,020 4,880 4,800 4,720 4,610 4,450 4,300
VSE = 169 KCAS V1 KCAS 138 137 136 134 133 132 132 132 133 133 133
VREF = 149 KCAS VR KCAS 142 142 141 141 140 140 140 140 140 140 140
MAX TEMP = 49°C V2 KCAS 147 147 147 147 147 147 147 147 147 147 147
-- 64,000 LB --
VFS = 160 KCAS FLD LNGTH 6,060 5,730 5,360 5,030 4,730 4,600 4,520 4,450 4,340 4,190 4,050
VSE = 166 KCAS V1 KCAS 136 134 133 131 130 129 129 129 130 130 130
VREF = 147 KCAS VR KCAS 140 139 139 138 138 138 138 138 138 138 138
MAX TEMP = 49°C V2 KCAS 145 145 145 145 145 145 145 145 145 145 145
-- 62,000 LB --
VFS = 157 KCAS FLD LNGTH 5,680 5,380 5,040 4,720 4,450 4,320 4,250 4,190 4,080 3,950 3,810
VSE = 164 KCAS V1 KCAS 133 131 130 128 127 126 126 126 127 127 127
VREF = 144 KCAS VR KCAS 137 137 136 136 135 135 135 135 135 135 135
MAX TEMP = 49°C V2 KCAS 143 143 143 143 143 143 143 143 143 143 143
CAUTION: DO NOT REDUCE TAKEOFF EPR BY MORE THAN .15 OR BELOW A MINIMUM VALUE OF 1.56.
NOTES: HEADWIND: Increase available field length 2% for each 5 knots (up to 40 knots).
TAILWIND: Decrease available field length 11% for each 5 knots (up to 10 knots).
UPHILL SLOPE: Decrease available field length 20% for each 1% (up to 2%).
DOWNHILL SLOPE: No adjustments required (up to 2%).

GIV-SP PERFORMANCE REVISION 24 (RE-ISSUE)

Page PA - 22 (GIV-SP AIRPLANES ONLY) Mar 17/10
Quick Reference Handbook
GIV-SP Takeoff Planning: Flaps 10° - APA 500 Feet, ctd…
AFM APP. A

TAKEOFF PLANNING CHART

GIV-SP AIRPORT PRESSURE ALTITUDE = 500 FEET TAKEOFF FLAP 10°

74,600 LB MTOGW OAT (°C) 49 45 40 35 30 25 20 15 5 -5 -15
OAT (°F) 120 113 104 95 86 77 68 59 41 23 5
RATED EPR 1.59 1.62 1.64 1.67 1.70 1.71 1.71 1.71 1.70 1.70 1.70
-- 60,000 LB --
VFS = 155 KCAS FLD LNGTH 5,320 5,040 4,720 4,440 4,180 4,060 4,000 3,930 3,840 3,710 3,580
VSE = 161 KCAS V1 KCAS 130 128 127 125 124 123 123 123 124 124 124
VREF = 142 KCAS VR KCAS 135 134 134 133 133 133 133 133 133 133 133
MAX TEMP = 49°C V2 KCAS 140 140 140 140 140 140 140 140 140 140 140
-- 58,000 LB --
VFS = 152 KCAS FLD LNGTH 4,970 4,710 4,420 4,150 3,910 3,810 3,740 3,680 3,590 3,470 3,350
VSE = 158 KCAS V1 KCAS 126 125 124 122 121 120 120 120 121 121 121
VREF = 140 KCAS VR KCAS 132 132 131 131 130 130 130 130 130 130 130
MAX TEMP = 49°C V2 KCAS 138 138 138 138 138 138 138 138 138 138 138
-- 56,000 LB --
VFS = 150 KCAS FLD LNGTH 4,630 4,390 4,120 3,880 3,670 3,590 3,530 3,480 3,380 3,270 3,160
VSE = 156 KCAS V1 KCAS 123 122 120 119 118 118 118 118 118 118 118
VREF = 137 KCAS VR KCAS 129 129 129 128 128 127 127 127 127 127 127
MAX TEMP = 49°C V2 KCAS 136 136 136 136 136 136 136 136 136 136 136
-- 54,000 LB --
VFS = 147 KCAS FLD LNGTH 4,340 4,130 3,880 3,710 3,600 3,530 3,480 3,420 3,330 3,220 3,110
VSE = 153 KCAS V1 KCAS 121 119 118 117 118 118 118 118 118 118 118
VREF = 135 KCAS VR KCAS 127 127 126 126 125 125 125 125 125 125 125
MAX TEMP = 49°C V2 KCAS 134 134 134 134 134 134 134 134 134 134 134
-- 52,000 LB --
VFS = 144 KCAS FLD LNGTH 4,110 3,900 3,750 3,640 3,540 3,470 3,420 3,370 3,270 3,170 3,060
VSE = 150 KCAS V1 KCAS 118 117 117 118 118 118 118 118 118 118 119
VREF = 132 KCAS VR KCAS 126 125 125 124 124 124 124 124 124 124 124
MAX TEMP = 49°C V2 KCAS 132 132 132 132 132 132 132 132 132 132 132
-- 50,000 LB --
VFS = 142 KCAS FLD LNGTH 3,900 3,800 3,680 3,580 3,480 3,410 3,360 3,310 3,220 3,110 3,010
VSE = 147 KCAS V1 KCAS 116 117 117 118 118 118 118 119 119 119 119
VREF = 130 KCAS VR KCAS 124 124 123 123 122 122 122 122 122 122 122
MAX TEMP = 49°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
-- 48,000 LB --
VFS = 139 KCAS FLD LNGTH 3,820 3,730 3,620 3,510 3,420 3,360 3,310 3,260 3,160 3,060 2,960
VSE = 144 KCAS V1 KCAS 117 117 118 118 118 119 119 119 119 119 119
VREF = 127 KCAS VR KCAS 124 124 123 123 122 122 122 122 122 122 122
MAX TEMP = 49°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
-- 46,000 LB --
VFS = 136 KCAS FLD LNGTH 3,740 3,650 3,550 3,450 3,360 3,300 3,250 3,200 3,110 3,010 2,910
VSE = 141 KCAS V1 KCAS 117 117 118 118 119 119 119 119 119 119 119
VREF = 124 KCAS VR KCAS 124 123 123 122 122 122 122 122 122 122 122
MAX TEMP = 49°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
CAUTION: DO NOT REDUCE TAKEOFF EPR BY MORE THAN .15 OR BELOW A MINIMUM VALUE OF 1.56.
NOTES: HEADWIND: Increase available field length 2% for each 5 knots (up to 40 knots).
TAILWIND: Decrease available field length 11% for each 5 knots (up to 10 knots).
UPHILL SLOPE: Decrease available field length 20% for each 1% (up to 2%).
DOWNHILL SLOPE: No adjustments required (up to 2%).

REVISION 24 (RE-ISSUE) GIV-SP PERFORMANCE

Mar 17/10 (GIV-SP AIRPLANES ONLY) Page PA - 23
 Quick Reference Handbook
GIV-SP Takeoff Planning: Flaps 10° - APA 1000 Feet
AFM APP. A

TAKEOFF PLANNING CHART

GIV-SP AIRPORT PRESSURE ALTITUDE = 1,000 FEET TAKEOFF FLAP 10°

74,600 LB MTOGW OAT (°C) 48 45 40 35 30 25 20 15 5 -5 -15
OAT (°F) 118 113 104 95 86 77 68 59 41 23 5
RATED EPR 1.60 1.62 1.64 1.66 1.70 1.71 1.71 1.71 1.71 1.71 1.71
-- 74,600 LB --
VFS = 173 KCAS FLD LNGTH 8,620 8,230 7,640 7,120 6,670 6,400 6,280 6,180 6,030 5,820 5,620
VSE = 180 KCAS V1 KCAS 151 150 148 147 146 145 145 145 145 145 145
VREF = 158 KCAS VR KCAS 152 152 151 151 151 150 150 150 150 150 150
MAX TEMP = 48°C V2 KCAS 157 157 157 157 157 157 157 157 157 157 157
-- 74,000 LB --
VFS = 172 KCAS FLD LNGTH 8,470 8,090 7,510 7,010 6,560 6,300 6,170 6,080 5,930 5,730 5,530
VSE = 179 KCAS V1 KCAS 150 149 148 146 145 144 144 144 144 144 144
VREF = 158 KCAS VR KCAS 151 151 151 150 150 150 150 150 150 150 150
MAX TEMP = 48°C V2 KCAS 156 156 156 156 156 156 156 156 156 156 156
-- 72,000 LB --
VFS = 170 KCAS FLD LNGTH 7,970 7,630 7,100 6,620 6,210 5,960 5,850 5,750 5,610 5,420 5,230
VSE = 177 KCAS V1 KCAS 147 146 145 143 142 141 141 141 141 142 142
VREF = 156 KCAS VR KCAS 149 149 148 148 148 147 147 147 147 147 147
MAX TEMP = 48°C V2 KCAS 154 154 154 154 154 154 154 154 154 154 154
-- 70,000 LB --
VFS = 167 KCAS FLD LNGTH 7,510 7,190 6,700 6,260 5,870 5,640 5,530 5,440 5,310 5,130 4,950
VSE = 174 KCAS V1 KCAS 144 144 142 141 139 138 138 138 139 139 139
VREF = 154 KCAS VR KCAS 147 147 146 146 145 145 145 145 145 145 145
MAX TEMP = 48°C V2 KCAS 152 152 152 152 152 152 152 152 152 152 152
-- 68,000 LB --
VFS = 165 KCAS FLD LNGTH 7,050 6,760 6,300 5,890 5,530 5,320 5,220 5,130 5,010 4,840 4,670
VSE = 172 KCAS V1 KCAS 142 141 139 138 136 136 136 136 136 136 136
VREF = 151 KCAS VR KCAS 144 144 144 143 143 143 143 143 143 143 143
MAX TEMP = 48°C V2 KCAS 149 149 149 149 149 149 149 149 149 149 149
-- 66,000 LB --
VFS = 162 KCAS FLD LNGTH 6,620 6,350 5,930 5,550 5,210 5,010 4,920 4,840 4,720 4,560 4,400
VSE = 169 KCAS V1 KCAS 139 138 136 135 133 133 133 133 133 133 133
VREF = 149 KCAS VR KCAS 142 142 141 141 140 140 140 140 140 140 140
MAX TEMP = 48°C V2 KCAS 147 147 147 147 147 147 147 147 147 147 147
-- 64,000 LB --
VFS = 160 KCAS FLD LNGTH 6,210 5,960 5,570 5,220 4,910 4,720 4,630 4,560 4,440 4,300 4,150
VSE = 166 KCAS V1 KCAS 136 135 133 132 130 130 130 130 130 130 130
VREF = 147 KCAS VR KCAS 140 139 139 138 138 138 138 138 138 138 138
MAX TEMP = 48°C V2 KCAS 145 145 145 145 145 145 145 145 145 145 145
-- 62,000 LB --
VFS = 157 KCAS FLD LNGTH 5,820 5,590 5,230 4,910 4,610 4,440 4,360 4,290 4,180 4,040 3,900
VSE = 164 KCAS V1 KCAS 133 132 130 129 127 127 127 127 127 127 127
VREF = 144 KCAS VR KCAS 137 137 136 136 136 135 135 135 135 135 135
MAX TEMP = 48°C V2 KCAS 143 143 143 143 143 143 143 143 143 143 143
CAUTION: DO NOT REDUCE TAKEOFF EPR BY MORE THAN .15 OR BELOW A MINIMUM VALUE OF 1.56.
NOTES: HEADWIND: Increase available field length 2% for each 5 knots (up to 40 knots).
TAILWIND: Decrease available field length 11% for each 5 knots (up to 10 knots).
UPHILL SLOPE: Decrease available field length 20% for each 1% (up to 2%).
DOWNHILL SLOPE: No adjustments required (up to 2%).

GIV-SP PERFORMANCE REVISION 24 (RE-ISSUE)

Page PA - 24 (GIV-SP AIRPLANES ONLY) Mar 17/10
Quick Reference Handbook
GIV-SP Takeoff Planning: Flaps 10° - APA 1000 Feet, ctd…
AFM APP. A

TAKEOFF PLANNING CHART

GIV-SP AIRPORT PRESSURE ALTITUDE = 1,000 FEET TAKEOFF FLAP 10°

74,600 LB MTOGW OAT (°C) 48 45 40 35 30 25 20 15 5 -5 -15
OAT (°F) 118 113 104 95 86 77 68 59 41 23 5
RATED EPR 1.60 1.62 1.64 1.66 1.70 1.71 1.71 1.71 1.71 1.71 1.71
-- 60,000 LB --
VFS = 155 KCAS FLD LNGTH 5,450 5,240 4,910 4,600 4,340 4,170 4,090 4,030 3,930 3,800 3,670
VSE = 161 KCAS V1 KCAS 130 129 127 126 124 124 124 124 124 124 124
VREF = 142 KCAS VR KCAS 135 134 134 134 133 133 133 133 133 133 133
MAX TEMP = 48°C V2 KCAS 140 140 140 140 140 140 140 140 140 140 140
-- 58,000 LB --
VFS = 152 KCAS FLD LNGTH 5,090 4,890 4,580 4,310 4,060 3,910 3,830 3,770 3,680 3,560 3,430
VSE = 158 KCAS V1 KCAS 127 126 124 123 121 120 120 120 121 121 121
VREF = 140 KCAS VR KCAS 132 132 131 131 130 130 130 130 130 130 130
MAX TEMP = 48°C V2 KCAS 138 138 138 138 138 138 138 138 138 138 138
-- 56,000 LB --
VFS = 150 KCAS FLD LNGTH 4,740 4,560 4,280 4,020 3,790 3,660 3,600 3,550 3,450 3,330 3,220
VSE = 156 KCAS V1 KCAS 123 122 121 120 118 117 118 118 118 118 118
VREF = 137 KCAS VR KCAS 129 129 129 128 128 128 127 127 127 127 127
MAX TEMP = 48°C V2 KCAS 136 136 136 136 136 136 136 136 136 136 136
-- 54,000 LB --
VFS = 147 KCAS FLD LNGTH 4,450 4,280 4,020 3,820 3,680 3,600 3,540 3,490 3,390 3,280 3,170
VSE = 153 KCAS V1 KCAS 121 120 118 117 117 118 118 118 118 118 118
VREF = 135 KCAS VR KCAS 127 127 127 126 126 125 125 125 125 125 125
MAX TEMP = 48°C V2 KCAS 134 134 134 134 134 134 134 134 134 134 134
-- 52,000 LB --
VFS = 144 KCAS FLD LNGTH 4,210 4,050 3,860 3,730 3,620 3,540 3,490 3,430 3,330 3,230 3,120
VSE = 150 KCAS V1 KCAS 119 118 117 117 118 118 118 118 118 118 119
VREF = 132 KCAS VR KCAS 126 126 125 125 124 124 124 124 124 124 124
MAX TEMP = 48°C V2 KCAS 132 132 132 132 132 132 132 132 132 132 132
-- 50,000 LB --
VFS = 142 KCAS FLD LNGTH 3,980 3,900 3,770 3,660 3,560 3,480 3,430 3,370 3,280 3,170 3,070
VSE = 147 KCAS V1 KCAS 116 117 117 118 118 118 118 118 119 119 119
VREF = 130 KCAS VR KCAS 124 124 124 123 123 122 122 122 122 122 122
MAX TEMP = 48°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
-- 48,000 LB --
VFS = 139 KCAS FLD LNGTH 3,890 3,820 3,700 3,590 3,500 3,420 3,370 3,320 3,220 3,120 3,020
VSE = 144 KCAS V1 KCAS 117 117 117 118 118 119 119 119 119 119 119
VREF = 127 KCAS VR KCAS 124 124 123 123 122 122 122 122 122 122 122
MAX TEMP = 48°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
-- 46,000 LB --
VFS = 136 KCAS FLD LNGTH 3,810 3,740 3,630 3,530 3,430 3,360 3,310 3,260 3,170 3,070 2,960
VSE = 141 KCAS V1 KCAS 117 117 118 118 119 119 119 119 119 119 120
VREF = 124 KCAS VR KCAS 124 124 123 122 122 122 122 122 122 122 122
MAX TEMP = 48°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
CAUTION: DO NOT REDUCE TAKEOFF EPR BY MORE THAN .15 OR BELOW A MINIMUM VALUE OF 1.56.
NOTES: HEADWIND: Increase available field length 2% for each 5 knots (up to 40 knots).
TAILWIND: Decrease available field length 11% for each 5 knots (up to 10 knots).
UPHILL SLOPE: Decrease available field length 20% for each 1% (up to 2%).
DOWNHILL SLOPE: No adjustments required (up to 2%).

REVISION 24 (RE-ISSUE) GIV-SP PERFORMANCE

Mar 17/10 (GIV-SP AIRPLANES ONLY) Page PA - 25
 Quick Reference Handbook
GIV-SP Takeoff Planning: Flaps 10° - APA 2000 Feet
AFM APP. A

TAKEOFF PLANNING CHART

GIV-SP AIRPORT PRESSURE ALTITUDE = 2,000 FEET TAKEOFF FLAP 10°

74,600 LB MTOGW OAT (°C) 45 40 35 30 25 20 15 10 0 -10 -19
OAT (°F) 113 104 95 86 77 68 59 50 32 14 -2
RATED EPR 1.62 1.64 1.66 1.69 1.71 1.72 1.72 1.72 1.72 1.72 1.72
-- 74,600 LB --
VFS = 173 KCAS FLD LNGTH 8,980 8,290 7,720 7,220 6,830 6,670 6,520 6,380 6,230 6,010 5,820
VSE = 180 KCAS V1 KCAS 151 150 148 147 146 145 145 145 145 146 146
VREF = 158 KCAS VR KCAS 152 152 151 151 151 151 151 151 151 151 151
MAX TEMP = 46°C V2 KCAS 157 157 157 157 157 157 157 157 157 157 157
-- 74,000 LB --
VFS = 172 KCAS FLD LNGTH 8,810 8,150 7,590 7,100 6,720 6,570 6,420 6,280 6,120 5,910 5,730
VSE = 179 KCAS V1 KCAS 150 149 147 146 145 145 144 144 145 145 145
VREF = 158 KCAS VR KCAS 151 151 151 150 150 150 150 150 150 150 150
MAX TEMP = 46°C V2 KCAS 156 156 156 156 156 156 156 156 156 156 156
-- 72,000 LB --
VFS = 170 KCAS FLD LNGTH 8,290 7,690 7,170 6,710 6,360 6,210 6,070 5,940 5,800 5,600 5,420
VSE = 177 KCAS V1 KCAS 148 146 145 143 142 142 142 142 142 142 142
VREF = 156 KCAS VR KCAS 149 149 148 148 148 148 148 148 148 148 148
MAX TEMP = 46°C V2 KCAS 154 154 154 154 154 154 154 154 154 154 154
-- 70,000 LB --
VFS = 167 KCAS FLD LNGTH 7,800 7,250 6,760 6,340 6,010 5,870 5,740 5,620 5,480 5,290 5,120
VSE = 174 KCAS V1 KCAS 145 143 142 140 139 139 139 139 139 139 139
VREF = 154 KCAS VR KCAS 147 147 146 146 145 145 145 145 145 145 145
MAX TEMP = 46°C V2 KCAS 152 152 152 152 152 152 152 152 152 152 152
-- 68,000 LB --
VFS = 165 KCAS FLD LNGTH 7,330 6,820 6,370 5,970 5,670 5,540 5,410 5,300 5,170 4,990 4,830
VSE = 172 KCAS V1 KCAS 142 140 139 137 136 136 136 136 136 136 136
VREF = 151 KCAS VR KCAS 145 144 144 143 143 143 143 143 143 143 143
MAX TEMP = 46°C V2 KCAS 149 149 149 149 149 149 149 149 149 149 149
-- 66,000 LB --
VFS = 162 KCAS FLD LNGTH 6,880 6,410 5,990 5,620 5,340 5,220 5,100 5,000 4,870 4,700 4,550
VSE = 169 KCAS V1 KCAS 139 137 136 135 133 133 133 133 133 133 133
VREF = 149 KCAS VR KCAS 142 142 141 141 141 140 140 140 140 140 140
MAX TEMP = 46°C V2 KCAS 147 147 147 147 147 147 147 147 147 147 147
-- 64,000 LB --
VFS = 160 KCAS FLD LNGTH 6,450 6,020 5,630 5,290 5,030 4,910 4,800 4,700 4,590 4,430 4,290
VSE = 166 KCAS V1 KCAS 136 134 133 132 130 130 130 130 130 130 131
VREF = 147 KCAS VR KCAS 140 139 139 138 138 138 138 138 138 138 138
MAX TEMP = 46°C V2 KCAS 145 145 145 145 145 145 145 145 145 145 145
-- 62,000 LB --
VFS = 157 KCAS FLD LNGTH 6,050 5,640 5,290 4,970 4,730 4,620 4,520 4,430 4,310 4,170 4,040
VSE = 164 KCAS V1 KCAS 133 131 130 129 127 127 127 127 127 127 127
VREF = 145 KCAS VR KCAS 137 137 136 136 136 136 135 135 135 135 135
MAX TEMP = 46°C V2 KCAS 143 143 143 143 143 143 143 143 143 143 143
CAUTION: DO NOT REDUCE TAKEOFF EPR BY MORE THAN .15 OR BELOW A MINIMUM VALUE OF 1.56.
NOTES: HEADWIND: Increase available field length 2% for each 5 knots (up to 40 knots).
TAILWIND: Not permitted using this data at this pressure altitude.
UPHILL SLOPE: Decrease available field length 20% for each 1% (up to 2%).
DOWNHILL SLOPE: Not permitted using this data at this pressure altitude.

GIV-SP PERFORMANCE REVISION 24 (RE-ISSUE)

Page PA - 26 (GIV-SP AIRPLANES ONLY) Mar 17/10
Quick Reference Handbook
GIV-SP Takeoff Planning: Flaps 10° - APA 2000 Feet, ctd…
AFM APP. A

TAKEOFF PLANNING CHART

GIV-SP AIRPORT PRESSURE ALTITUDE = 2,000 FEET TAKEOFF FLAP 10°

74,600 LB MTOGW OAT (°C) 45 40 35 30 25 20 15 10 0 -10 -19
OAT (°F) 113 104 95 86 77 68 59 50 32 14 -2
RATED EPR 1.62 1.64 1.66 1.69 1.71 1.72 1.72 1.72 1.72 1.72 1.72
-- 60,000 LB --
VFS = 155 KCAS FLD LNGTH 5,660 5,290 4,960 4,670 4,440 4,340 4,250 4,160 4,050 3,920 3,790
VSE = 161 KCAS V1 KCAS 130 128 127 126 125 124 124 124 124 124 125
VREF = 142 KCAS VR KCAS 135 134 134 134 133 133 133 133 133 133 133
MAX TEMP = 46°C V2 KCAS 140 140 140 140 140 140 140 140 140 140 140
-- 58,000 LB --
VFS = 152 KCAS FLD LNGTH 5,280 4,940 4,640 4,370 4,160 4,060 3,980 3,890 3,800 3,670 3,550
VSE = 158 KCAS V1 KCAS 127 125 124 122 121 121 121 121 121 121 121
VREF = 140 KCAS VR KCAS 132 132 131 131 130 130 130 130 130 130 130
MAX TEMP = 46°C V2 KCAS 138 138 138 138 138 138 138 138 138 138 138
-- 56,000 LB --
VFS = 150 KCAS FLD LNGTH 4,920 4,610 4,330 4,080 3,880 3,800 3,720 3,640 3,550 3,430 3,320
VSE = 156 KCAS V1 KCAS 124 122 121 119 118 118 118 118 118 118 118
VREF = 137 KCAS VR KCAS 130 129 129 128 128 128 128 128 128 128 128
MAX TEMP = 46°C V2 KCAS 136 136 136 136 136 136 136 136 136 136 136
-- 54,000 LB --
VFS = 147 KCAS FLD LNGTH 4,620 4,330 4,070 3,870 3,760 3,700 3,630 3,570 3,470 3,350 3,250
VSE = 153 KCAS V1 KCAS 121 119 118 117 117 117 118 118 118 118 118
VREF = 135 KCAS VR KCAS 127 127 127 126 126 126 126 126 126 126 126
MAX TEMP = 46°C V2 KCAS 134 134 134 134 134 134 134 134 134 134 134
-- 52,000 LB --
VFS = 144 KCAS FLD LNGTH 4,370 4,100 3,910 3,800 3,700 3,630 3,570 3,510 3,410 3,300 3,200
VSE = 150 KCAS V1 KCAS 119 117 117 117 118 118 118 118 118 118 118
VREF = 132 KCAS VR KCAS 126 125 125 125 124 124 124 124 124 124 124
MAX TEMP = 46°C V2 KCAS 132 132 132 132 132 132 132 132 132 132 132
-- 50,000 LB --
VFS = 142 KCAS FLD LNGTH 4,140 3,960 3,840 3,730 3,630 3,570 3,510 3,450 3,350 3,240 3,140
VSE = 147 KCAS V1 KCAS 117 117 117 118 118 118 118 118 118 118 118
VREF = 130 KCAS VR KCAS 124 124 123 123 123 122 122 122 122 122 122
MAX TEMP = 46°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
-- 48,000 LB --
VFS = 139 KCAS FLD LNGTH 4,010 3,890 3,770 3,660 3,570 3,510 3,450 3,390 3,290 3,190 3,090
VSE = 144 KCAS V1 KCAS 117 117 117 118 118 118 118 119 119 119 119
VREF = 127 KCAS VR KCAS 124 124 123 123 122 122 122 122 122 122 122
MAX TEMP = 46°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
-- 46,000 LB --
VFS = 136 KCAS FLD LNGTH 3,930 3,810 3,690 3,590 3,500 3,440 3,390 3,330 3,230 3,130 3,040
VSE = 141 KCAS V1 KCAS 117 117 118 118 118 119 119 119 119 119 119
VREF = 124 KCAS VR KCAS 124 123 123 122 122 122 122 122 122 122 122
MAX TEMP = 46°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
CAUTION: DO NOT REDUCE TAKEOFF EPR BY MORE THAN .15 OR BELOW A MINIMUM VALUE OF 1.56.
NOTES: HEADWIND: Increase available field length 2% for each 5 knots (up to 40 knots).
TAILWIND: Not permitted using this data at this pressure altitude.
UPHILL SLOPE: Decrease available field length 20% for each 1% (up to 2%).
DOWNHILL SLOPE: Not permitted using this data at this pressure altitude.

REVISION 24 (RE-ISSUE) GIV-SP PERFORMANCE

Mar 17/10 (GIV-SP AIRPLANES ONLY) Page PA - 27
 Quick Reference Handbook
GIV-SP Takeoff Planning: Flaps 10° - APA 4000 Feet
AFM APP. A

TAKEOFF PLANNING CHART

GIV-SP AIRPORT PRESSURE ALTITUDE = 4,000 FEET TAKEOFF FLAP 10°

74,600 LB MTOGW OAT (°C) 40 35 30 25 20 15 10 5 -5 -15 -23
OAT (°F) 104 95 86 77 68 59 50 41 23 5 -9
RATED EPR 1.63 1.66 1.69 1.71 1.72 1.74 1.74 1.74 1.74 1.74 1.74
-- 74,600 LB --
VFS = 174 KCAS FLD LNGTH 10,060 9,250 8,620 8,130 7,810 7,530 7,290 7,170 6,900 6,660 6,460
VSE = 181 KCAS V1 KCAS 153 152 150 149 148 148 148 148 147 148 148
VREF = 159 KCAS VR KCAS 154 153 153 153 152 152 152 152 152 152 152
MAX TEMP = 42°C V2 KCAS 158 158 158 158 158 158 158 158 158 158 158
-- 74,000 LB --
VFS = 174 KCAS FLD LNGTH 9,850 9,090 8,470 8,000 7,680 7,400 7,170 7,050 6,780 6,550 6,360
VSE = 181 KCAS V1 KCAS 152 151 149 148 148 147 147 147 147 147 147
VREF = 158 KCAS VR KCAS 153 153 152 152 152 152 151 151 151 151 151
MAX TEMP = 42°C V2 KCAS 157 157 157 157 157 157 157 157 157 157 157
-- 72,000 LB --
VFS = 171 KCAS FLD LNGTH 9,240 8,570 7,990 7,550 7,250 7,000 6,780 6,670 6,410 6,190 6,010
VSE = 178 KCAS V1 KCAS 150 148 147 146 145 144 144 144 144 144 144
VREF = 156 KCAS VR KCAS 151 150 150 150 149 149 149 149 149 149 149
MAX TEMP = 42°C V2 KCAS 155 155 155 155 155 155 155 155 155 155 155
-- 70,000 LB --
VFS = 169 KCAS FLD LNGTH 8,680 8,070 7,540 7,130 6,850 6,610 6,400 6,300 6,060 5,850 5,680
VSE = 176 KCAS V1 KCAS 147 145 144 143 142 141 141 141 141 141 141
VREF = 154 KCAS VR KCAS 148 148 148 147 147 147 147 147 147 147 147
MAX TEMP = 42°C V2 KCAS 153 153 153 153 153 153 153 153 153 153 153
-- 68,000 LB --
VFS = 166 KCAS FLD LNGTH 8,150 7,580 7,090 6,710 6,450 6,230 6,040 5,940 5,720 5,520 5,360
VSE = 173 KCAS V1 KCAS 144 142 141 140 139 139 138 138 138 138 138
VREF = 151 KCAS VR KCAS 146 146 145 145 145 144 144 144 144 144 144
MAX TEMP = 42°C V2 KCAS 151 151 151 151 151 151 151 151 151 151 151
-- 66,000 LB --
VFS = 164 KCAS FLD LNGTH 7,650 7,130 6,670 6,320 6,080 5,870 5,690 5,590 5,390 5,200 5,050
VSE = 171 KCAS V1 KCAS 141 139 138 137 136 136 135 135 135 135 135
VREF = 149 KCAS VR KCAS 143 143 143 142 142 142 142 142 142 142 142
MAX TEMP = 42°C V2 KCAS 148 148 148 148 148 148 148 148 148 148 148
-- 64,000 LB --
VFS = 161 KCAS FLD LNGTH 7,170 6,690 6,270 5,940 5,720 5,520 5,350 5,270 5,070 4,890 4,750
VSE = 168 KCAS V1 KCAS 138 136 135 134 133 133 132 132 132 132 132
VREF = 147 KCAS VR KCAS 141 141 140 140 140 140 139 139 139 139 139
MAX TEMP = 42°C V2 KCAS 146 146 146 146 146 146 146 146 146 146 146
-- 62,000 LB --
VFS = 159 KCAS FLD LNGTH 6,710 6,270 5,880 5,580 5,370 5,190 5,030 4,950 4,770 4,600 4,470
VSE = 165 KCAS V1 KCAS 135 133 132 131 130 130 129 129 129 129 130
VREF = 145 KCAS VR KCAS 139 138 138 137 137 137 137 137 137 137 137
MAX TEMP = 42°C V2 KCAS 144 144 144 144 144 144 144 144 144 144 144
CAUTION: DO NOT REDUCE TAKEOFF EPR BY MORE THAN .15 OR BELOW A MINIMUM VALUE OF 1.56.
NOTES: HEADWIND: Increase available field length 2% for each 5 knots (up to 40 knots).
TAILWIND: Not permitted using this data at this pressure altitude.
UPHILL SLOPE: Decrease available field length 20% for each 1% (up to 2%).
DOWNHILL SLOPE: Not permitted using this data at this pressure altitude.

GIV-SP PERFORMANCE REVISION 24 (RE-ISSUE)

Page PA - 28 (GIV-SP AIRPLANES ONLY) Mar 17/10
Quick Reference Handbook
GIV-SP Takeoff Planning: Flaps 10° - APA 4000 Feet, ctd…
AFM APP. A

TAKEOFF PLANNING CHART

GIV-SP AIRPORT PRESSURE ALTITUDE = 4,000 FEET TAKEOFF FLAP 10°

74,600 LB MTOGW OAT (°C) 40 35 30 25 20 15 10 5 -5 -15 -23
OAT (°F) 104 95 86 77 68 59 50 41 23 5 -9
RATED EPR 1.63 1.66 1.69 1.71 1.72 1.74 1.74 1.74 1.74 1.74 1.74
-- 60,000 LB --
VFS = 156 KCAS FLD LNGTH 6,280 5,880 5,520 5,240 5,040 4,870 4,730 4,650 4,480 4,320 4,200
VSE = 163 KCAS V1 KCAS 132 130 129 128 127 127 126 126 126 126 127
VREF = 142 KCAS VR KCAS 136 136 135 135 135 135 134 134 134 134 134
MAX TEMP = 42°C V2 KCAS 142 142 142 142 142 142 142 142 142 142 142
-- 58,000 LB --
VFS = 154 KCAS FLD LNGTH 5,860 5,480 5,150 4,890 4,710 4,560 4,420 4,350 4,190 4,040 3,930
VSE = 160 KCAS V1 KCAS 129 127 126 125 124 124 123 123 123 123 123
VREF = 140 KCAS VR KCAS 134 133 133 132 132 132 132 132 132 132 132
MAX TEMP = 42°C V2 KCAS 139 139 139 139 139 139 139 139 139 139 139
-- 56,000 LB --
VFS = 151 KCAS FLD LNGTH 5,450 5,110 4,810 4,570 4,400 4,260 4,130 4,060 3,910 3,780 3,670
VSE = 157 KCAS V1 KCAS 125 124 123 121 121 120 120 120 120 120 120
VREF = 137 KCAS VR KCAS 131 130 130 130 129 129 129 129 129 129 129
MAX TEMP = 42°C V2 KCAS 137 137 137 137 137 137 137 137 137 137 137
-- 54,000 LB --
VFS = 148 KCAS FLD LNGTH 5,100 4,780 4,500 4,280 4,130 3,990 3,880 3,820 3,690 3,570 3,470
VSE = 154 KCAS V1 KCAS 123 121 120 119 118 117 117 117 117 117 118
VREF = 135 KCAS VR KCAS 129 128 128 127 127 127 127 127 127 127 127
MAX TEMP = 42°C V2 KCAS 134 134 134 134 134 134 134 134 134 134 134
-- 52,000 LB --
VFS = 146 KCAS FLD LNGTH 4,790 4,500 4,240 4,070 3,980 3,890 3,810 3,750 3,630 3,510 3,410
VSE = 151 KCAS V1 KCAS 120 119 117 117 117 117 117 117 118 118 118
VREF = 132 KCAS VR KCAS 127 126 126 125 125 125 125 125 125 125 125
MAX TEMP = 42°C V2 KCAS 133 133 133 133 133 133 133 133 133 133 133
-- 50,000 LB --
VFS = 143 KCAS FLD LNGTH 4,490 4,260 4,110 4,000 3,910 3,820 3,750 3,690 3,560 3,440 3,350
VSE = 148 KCAS V1 KCAS 117 117 117 117 117 117 118 118 118 118 118
VREF = 130 KCAS VR KCAS 125 124 124 123 123 123 123 123 123 123 123
MAX TEMP = 42°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
-- 48,000 LB --
VFS = 140 KCAS FLD LNGTH 4,340 4,160 4,030 3,920 3,830 3,750 3,680 3,620 3,500 3,380 3,290
VSE = 145 KCAS V1 KCAS 117 117 117 117 118 118 118 118 118 118 118
VREF = 127 KCAS VR KCAS 124 124 123 123 123 123 122 122 122 122 122
MAX TEMP = 42°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
-- 46,000 LB --
VFS = 137 KCAS FLD LNGTH 4,200 4,070 3,950 3,840 3,760 3,680 3,610 3,550 3,430 3,320 3,230
VSE = 142 KCAS V1 KCAS 116 117 117 118 118 118 118 118 118 119 119
VREF = 124 KCAS VR KCAS 124 124 123 123 123 122 122 122 122 122 122
MAX TEMP = 42°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
CAUTION: DO NOT REDUCE TAKEOFF EPR BY MORE THAN .15 OR BELOW A MINIMUM VALUE OF 1.56.
NOTES: HEADWIND: Increase available field length 2% for each 5 knots (up to 40 knots).
TAILWIND: Not permitted using this data at this pressure altitude.
UPHILL SLOPE: Decrease available field length 20% for each 1% (up to 2%).
DOWNHILL SLOPE: Not permitted using this data at this pressure altitude.

REVISION 24 (RE-ISSUE) GIV-SP PERFORMANCE

Mar 17/10 (GIV-SP AIRPLANES ONLY) Page PA - 29
 Quick Reference Handbook
GIV-SP Takeoff Planning: Flaps 10° - APA 6000 Feet
AFM APP. A

TAKEOFF PLANNING CHART

GIV-SP AIRPORT PRESSURE ALTITUDE = 6,000 FEET TAKEOFF FLAP 10°

74,600 LB MTOGW OAT (°C) 38 35 30 25 20 15 10 5 -5 -15 -25
OAT (°F) 101 95 86 77 68 59 50 41 23 5 -13
RATED EPR 1.64 1.65 1.68 1.71 1.72 1.73 1.74 1.74 1.75 1.75 1.75
-- 74,600 LB --
VFS = 177 KCAS FLD LNGTH ****** ****** 10,460 9,840 9,420 9,080 8,750 8,550 8,160 7,880 7,590
VSE = 184 KCAS V1 KCAS ****** ****** 154 153 152 152 151 151 151 151 151
VREF = 159 KCAS VR KCAS ****** ****** 155 155 155 155 154 154 154 154 154
MAX TEMP = 34°C V2 KCAS ****** ****** 160 160 160 160 160 160 160 160 160
-- 74,000 LB --
VFS = 176 KCAS FLD LNGTH ****** 11,220 10,260 9,670 9,260 8,920 8,600 8,400 8,030 7,740 7,460
VSE = 183 KCAS V1 KCAS ****** 155 153 152 152 151 151 150 150 150 151
VREF = 159 KCAS VR KCAS ****** 155 154 154 154 154 154 154 154 154 154
MAX TEMP = 35°C V2 KCAS ****** 159 159 159 159 159 159 159 159 159 159
-- 72,000 LB --
VFS = 174 KCAS FLD LNGTH ****** 10,460 9,660 9,120 8,740 8,420 8,120 7,940 7,580 7,320 7,050
VSE = 181 KCAS V1 KCAS ****** 152 151 150 149 148 148 148 147 148 148
VREF = 157 KCAS VR KCAS ****** 152 152 152 152 152 151 151 151 151 151
MAX TEMP = 37°C V2 KCAS ****** 157 157 157 157 157 157 157 157 157 157
-- 70,000 LB --
VFS = 171 KCAS FLD LNGTH 10,250 9,780 9,090 8,590 8,240 7,940 7,660 7,490 7,160 6,910 6,650
VSE = 178 KCAS V1 KCAS 150 149 148 147 146 146 145 145 145 145 145
VREF = 154 KCAS VR KCAS 150 150 150 150 149 149 149 149 149 149 149
MAX TEMP = 38°C V2 KCAS 155 155 155 155 155 155 155 155 155 155 155
-- 68,000 LB --
VFS = 169 KCAS FLD LNGTH 9,590 9,160 8,540 8,080 7,750 7,480 7,220 7,050 6,740 6,500 6,270
VSE = 175 KCAS V1 KCAS 147 146 145 144 143 143 142 142 142 142 142
VREF = 152 KCAS VR KCAS 148 148 147 147 147 147 147 147 146 146 146
MAX TEMP = 38°C V2 KCAS 152 152 152 152 152 152 152 152 152 152 152
-- 66,000 LB --
VFS = 166 KCAS FLD LNGTH 8,980 8,590 8,020 7,590 7,290 7,030 6,790 6,640 6,340 6,120 5,900
VSE = 173 KCAS V1 KCAS 144 143 142 141 140 140 139 139 139 139 139
VREF = 150 KCAS VR KCAS 146 145 145 145 144 144 144 144 144 144 144
MAX TEMP = 38°C V2 KCAS 150 150 150 150 150 150 150 150 150 150 150
-- 64,000 LB --
VFS = 163 KCAS FLD LNGTH 8,400 8,050 7,520 7,130 6,850 6,610 6,380 6,240 5,970 5,760 5,550
VSE = 170 KCAS V1 KCAS 141 140 139 138 137 137 136 136 136 136 136
VREF = 148 KCAS VR KCAS 143 143 142 142 142 142 142 142 142 142 142
MAX TEMP = 38°C V2 KCAS 148 148 148 148 148 148 148 148 148 148 148
-- 62,000 LB --
VFS = 161 KCAS FLD LNGTH 7,860 7,530 7,050 6,680 6,420 6,200 5,990 5,860 5,600 5,410 5,210
VSE = 167 KCAS V1 KCAS 138 137 136 135 134 134 133 133 133 133 133
VREF = 145 KCAS VR KCAS 141 140 140 140 140 139 139 139 139 139 139
MAX TEMP = 38°C V2 KCAS 145 145 145 145 145 145 145 145 145 145 145
CAUTION: DO NOT REDUCE TAKEOFF EPR BY MORE THAN .15 OR BELOW A MINIMUM VALUE OF 1.56.
NOTES: HEADWIND: Increase available field length 2% for each 5 knots (up to 40 knots).
TAILWIND: Not permitted using this data at this pressure altitude.
UPHILL SLOPE: Decrease available field length 20% for each 1% (up to 2%).
DOWNHILL SLOPE: Not permitted using this data at this pressure altitude.

GIV-SP PERFORMANCE REVISION 24 (RE-ISSUE)

Page PA - 30 (GIV-SP AIRPLANES ONLY) Mar 17/10
Quick Reference Handbook
GIV-SP Takeoff Planning: Flaps 10° - APA 6000 Feet, ctd…
AFM APP. A

TAKEOFF PLANNING CHART

GIV-SP AIRPORT PRESSURE ALTITUDE = 6,000 FEET TAKEOFF FLAP 10°

74,600 LB MTOGW OAT (°C) 38 35 30 25 20 15 10 5 -5 -15 -25
OAT (°F) 101 95 86 77 68 59 50 41 23 5 -13
RATED EPR 1.64 1.65 1.68 1.71 1.72 1.73 1.74 1.74 1.75 1.75 1.75
-- 60,000 LB --
VFS = 158 KCAS FLD LNGTH 7,340 7,040 6,600 6,260 6,020 5,820 5,620 5,500 5,260 5,070 4,890
VSE = 165 KCAS V1 KCAS 135 134 133 132 131 131 130 130 130 130 130
VREF = 143 KCAS VR KCAS 138 138 138 137 137 137 137 137 137 137 137
MAX TEMP = 38°C V2 KCAS 143 143 143 143 143 143 143 143 143 143 143
-- 58,000 LB --
VFS = 156 KCAS FLD LNGTH 6,840 6,560 6,150 5,840 5,620 5,430 5,250 5,140 4,910 4,740 4,570
VSE = 162 KCAS V1 KCAS 132 131 130 129 128 127 127 127 127 127 127
VREF = 140 KCAS VR KCAS 135 135 135 135 134 134 134 134 134 134 134
MAX TEMP = 38°C V2 KCAS 141 141 141 141 141 141 141 141 141 141 141
-- 56,000 LB --
VFS = 153 KCAS FLD LNGTH 6,360 6,110 5,730 5,450 5,240 5,070 4,900 4,790 4,590 4,430 4,270
VSE = 159 KCAS V1 KCAS 128 128 126 125 125 124 124 124 123 123 123
VREF = 138 KCAS VR KCAS 133 133 132 132 132 131 131 131 131 131 131
MAX TEMP = 38°C V2 KCAS 138 138 138 138 138 138 138 138 138 138 138
-- 54,000 LB --
VFS = 150 KCAS FLD LNGTH 5,910 5,680 5,340 5,080 4,890 4,730 4,570 4,470 4,280 4,130 3,980
VSE = 156 KCAS V1 KCAS 125 124 123 122 122 121 120 120 120 120 120
VREF = 135 KCAS VR KCAS 130 130 130 129 129 129 129 129 128 128 128
MAX TEMP = 38°C V2 KCAS 136 136 136 136 136 136 136 136 136 136 136
-- 52,000 LB --
VFS = 147 KCAS FLD LNGTH 5,500 5,290 4,970 4,730 4,560 4,410 4,270 4,170 4,000 3,860 3,720
VSE = 153 KCAS V1 KCAS 122 121 120 119 118 118 117 117 117 117 117
VREF = 133 KCAS VR KCAS 128 127 127 127 126 126 126 126 126 126 126
MAX TEMP = 38°C V2 KCAS 133 133 133 133 133 133 133 133 133 133 133
-- 50,000 LB --
VFS = 145 KCAS FLD LNGTH 5,100 4,910 4,620 4,430 4,320 4,230 4,130 4,060 3,910 3,780 3,650
VSE = 150 KCAS V1 KCAS 119 118 117 116 116 117 117 117 117 117 117
VREF = 130 KCAS VR KCAS 125 125 124 124 124 124 124 123 123 123 123
MAX TEMP = 38°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
-- 48,000 LB --
VFS = 141 KCAS FLD LNGTH 4,910 4,720 4,480 4,340 4,230 4,140 4,050 3,980 3,840 3,710 3,580
VSE = 147 KCAS V1 KCAS 118 117 116 116 117 117 117 117 117 117 118
VREF = 128 KCAS VR KCAS 125 125 124 124 124 123 123 123 123 123 123
MAX TEMP = 38°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
-- 46,000 LB --
VFS = 138 KCAS FLD LNGTH 4,710 4,550 4,360 4,240 4,140 4,060 3,970 3,900 3,760 3,630 3,510
VSE = 144 KCAS V1 KCAS 117 117 116 117 117 117 117 117 118 118 118
VREF = 125 KCAS VR KCAS 125 124 124 124 123 123 123 123 123 123 123
MAX TEMP = 38°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
CAUTION: DO NOT REDUCE TAKEOFF EPR BY MORE THAN .15 OR BELOW A MINIMUM VALUE OF 1.56.
NOTES: HEADWIND: Increase available field length 2% for each 5 knots (up to 40 knots).
TAILWIND: Not permitted using this data at this pressure altitude.
UPHILL SLOPE: Decrease available field length 20% for each 1% (up to 2%).
DOWNHILL SLOPE: Not permitted using this data at this pressure altitude.

REVISION 24 (RE-ISSUE) GIV-SP PERFORMANCE

Mar 17/10 (GIV-SP AIRPLANES ONLY) Page PA - 31
 Quick Reference Handbook
GIV-SP Takeoff Planning: Flaps 10° - APA 8000 Feet
AFM APP. A

TAKEOFF PLANNING CHART

GIV-SP AIRPORT PRESSURE ALTITUDE = 8,000 FEET TAKEOFF FLAP 10°

74,600 LB MTOGW OAT (°C) 34 30 25 20 15 10 5 0 -10 -20 -30
OAT (°F) 93 86 77 68 59 50 41 32 14 -4 -22
RATED EPR 1.66 1.68 1.70 1.71 1.72 1.73 1.74 1.75 1.75 1.75 1.75
-- 74,600 LB --
VFS = 179 KCAS FLD LNGTH ****** ****** ****** ****** ****** 10,650 10,350 9,990 9,560 9,210 8,870
VSE = 186 KCAS V1 KCAS ****** ****** ****** ****** ****** 156 155 155 155 155 155
VREF = 161 KCAS VR KCAS ****** ****** ****** ****** ****** 157 157 157 157 157 157
MAX TEMP = 10°C V2 KCAS ****** ****** ****** ****** ****** 161 161 161 161 161 161
-- 74,000 LB --
VFS = 178 KCAS FLD LNGTH ****** ****** ****** ****** 10,890 10,460 10,170 9,820 9,390 9,050 8,720
VSE = 185 KCAS V1 KCAS ****** ****** ****** ****** 155 155 154 154 154 154 154
VREF = 160 KCAS VR KCAS ****** ****** ****** ****** 156 156 156 156 156 156 156
MAX TEMP = 15°C V2 KCAS ****** ****** ****** ****** 161 161 161 161 161 161 161
-- 72,000 LB --
VFS = 176 KCAS FLD LNGTH ****** ****** 11,160 10,670 10,250 9,850 9,580 9,260 8,860 8,540 8,220
VSE = 183 KCAS V1 KCAS ****** ****** 154 153 152 152 152 151 151 151 151
VREF = 158 KCAS VR KCAS ****** ****** 154 154 154 154 154 154 153 153 153
MAX TEMP = 28°C V2 KCAS ****** ****** 159 159 159 159 159 159 159 159 159
-- 70,000 LB --
VFS = 173 KCAS FLD LNGTH ****** 11,160 10,470 10,030 9,650 9,280 9,030 8,720 8,350 8,050 7,750
VSE = 180 KCAS V1 KCAS ****** 152 151 150 149 149 149 148 148 148 148
VREF = 156 KCAS VR KCAS ****** 152 152 152 152 151 151 151 151 151 151
MAX TEMP = 32°C V2 KCAS ****** 156 156 156 156 156 156 156 156 156 156
-- 68,000 LB --
VFS = 171 KCAS FLD LNGTH 11,130 10,420 9,810 9,420 9,060 8,720 8,480 8,200 7,850 7,570 7,290
VSE = 178 KCAS V1 KCAS 150 149 148 147 146 146 146 145 145 145 145
VREF = 154 KCAS VR KCAS 150 150 149 149 149 149 149 149 149 149 149
MAX TEMP = 34°C V2 KCAS 154 154 154 154 154 154 154 154 154 154 154
-- 66,000 LB --
VFS = 168 KCAS FLD LNGTH 10,340 9,740 9,200 8,830 8,500 8,190 7,970 7,710 7,380 7,110 6,850
VSE = 175 KCAS V1 KCAS 147 146 145 144 144 143 143 142 142 142 142
VREF = 151 KCAS VR KCAS 147 147 147 147 147 146 146 146 146 146 146
MAX TEMP = 34°C V2 KCAS 152 152 152 152 152 152 152 152 152 152 152
-- 64,000 LB --
VFS = 166 KCAS FLD LNGTH 9,650 9,110 8,620 8,280 7,980 7,680 7,480 7,240 6,930 6,680 6,430
VSE = 172 KCAS V1 KCAS 144 143 142 141 141 140 140 139 139 139 139
VREF = 149 KCAS VR KCAS 145 145 144 144 144 144 144 144 144 144 144
MAX TEMP = 34°C V2 KCAS 149 149 149 149 149 149 149 149 149 149 149
-- 62,000 LB --
VFS = 163 KCAS FLD LNGTH 9,010 8,520 8,070 7,760 7,480 7,200 7,020 6,790 6,500 6,270 6,040
VSE = 169 KCAS V1 KCAS 141 140 139 138 138 137 137 136 136 136 136
VREF = 147 KCAS VR KCAS 143 142 142 142 142 142 141 141 141 141 141
MAX TEMP = 34°C V2 KCAS 147 147 147 147 147 147 147 147 147 147 147
CAUTION: DO NOT REDUCE TAKEOFF EPR BY MORE THAN .15 OR BELOW A MINIMUM VALUE OF 1.56.
NOTES: HEADWIND: Increase available field length 2% for each 5 knots (up to 40 knots).
TAILWIND: Not permitted using this data at this pressure altitude.
UPHILL SLOPE: Decrease available field length 20% for each 1% (up to 2%).
DOWNHILL SLOPE: Not permitted using this data at this pressure altitude.

GIV-SP PERFORMANCE REVISION 24 (RE-ISSUE)

Page PA - 32 (GIV-SP AIRPLANES ONLY) Mar 17/10
Quick Reference Handbook
GIV-SP Takeoff Planning: Flaps 10° - APA 8000 Feet, ctd…
AFM APP. A

TAKEOFF PLANNING CHART

GIV-SP AIRPORT PRESSURE ALTITUDE = 8,000 FEET TAKEOFF FLAP 10°

74,600 LB MTOGW OAT (°C) 34 30 25 20 15 10 5 0 -10 -20 -30
OAT (°F) 93 86 77 68 59 50 41 32 14 -4 -22
RATED EPR 1.66 1.68 1.70 1.71 1.72 1.73 1.74 1.75 1.75 1.75 1.75
-- 60,000 LB --
VFS = 160 KCAS FLD LNGTH 8,410 7,970 7,550 7,260 7,000 6,750 6,570 6,360 6,090 5,870 5,660
VSE = 167 KCAS V1 KCAS 138 137 136 135 135 134 134 133 133 133 133
VREF = 144 KCAS VR KCAS 140 140 140 139 139 139 139 139 139 139 139
MAX TEMP = 34°C V2 KCAS 145 145 145 145 145 145 145 145 145 145 145
-- 58,000 LB --
VFS = 158 KCAS FLD LNGTH 7,820 7,410 7,030 6,770 6,530 6,290 6,130 5,940 5,690 5,480 5,280
VSE = 164 KCAS V1 KCAS 134 133 132 132 131 131 131 130 130 130 130
VREF = 142 KCAS VR KCAS 137 137 137 137 136 136 136 136 136 136 136
MAX TEMP = 34°C V2 KCAS 142 142 142 142 142 142 142 142 142 142 142
-- 56,000 LB --
VFS = 155 KCAS FLD LNGTH 7,260 6,890 6,550 6,300 6,080 5,870 5,720 5,540 5,300 5,110 4,930
VSE = 161 KCAS V1 KCAS 131 130 129 129 128 128 127 127 127 127 127
VREF = 139 KCAS VR KCAS 135 134 134 134 134 134 133 133 133 133 133
MAX TEMP = 34°C V2 KCAS 140 140 140 140 140 140 140 140 140 140 140
-- 54,000 LB --
VFS = 152 KCAS FLD LNGTH 6,740 6,400 6,080 5,860 5,660 5,460 5,320 5,150 4,940 4,760 4,590
VSE = 158 KCAS V1 KCAS 128 127 126 125 125 124 124 124 123 124 124
VREF = 137 KCAS VR KCAS 132 132 131 131 131 131 131 131 130 130 130
MAX TEMP = 34°C V2 KCAS 137 137 137 137 137 137 137 137 137 137 137
-- 52,000 LB --
VFS = 149 KCAS FLD LNGTH 6,250 5,940 5,650 5,440 5,260 5,070 4,950 4,790 4,590 4,430 4,270
VSE = 155 KCAS V1 KCAS 125 124 123 122 121 121 121 120 120 120 120
VREF = 134 KCAS VR KCAS 129 129 129 128 128 128 128 128 128 128 128
MAX TEMP = 34°C V2 KCAS 135 135 135 135 135 135 135 135 135 135 135
-- 50,000 LB --
VFS = 146 KCAS FLD LNGTH 5,780 5,500 5,240 5,050 4,880 4,710 4,590 4,450 4,270 4,110 3,960
VSE = 152 KCAS V1 KCAS 121 120 119 119 118 118 117 117 117 117 117
VREF = 132 KCAS VR KCAS 127 126 126 126 126 125 125 125 125 125 125
MAX TEMP = 34°C V2 KCAS 132 132 132 132 132 132 132 132 132 132 132
-- 48,000 LB --
VFS = 143 KCAS FLD LNGTH 5,520 5,250 5,000 4,820 4,660 4,500 4,410 4,310 4,150 4,010 3,870
VSE = 149 KCAS V1 KCAS 120 119 118 117 117 116 116 117 117 117 117
VREF = 129 KCAS VR KCAS 126 126 125 125 125 125 125 124 124 124 124
MAX TEMP = 34°C V2 KCAS 132 132 132 132 132 132 132 132 132 132 132
-- 46,000 LB --
VFS = 140 KCAS FLD LNGTH 5,260 5,010 4,770 4,610 4,500 4,400 4,310 4,220 4,070 3,930 3,790
VSE = 146 KCAS V1 KCAS 119 118 117 116 116 117 117 117 117 117 117
VREF = 126 KCAS VR KCAS 125 125 125 124 124 124 124 124 124 124 124
MAX TEMP = 34°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
CAUTION: DO NOT REDUCE TAKEOFF EPR BY MORE THAN .15 OR BELOW A MINIMUM VALUE OF 1.56.
NOTES: HEADWIND: Increase available field length 2% for each 5 knots (up to 40 knots).
TAILWIND: Not permitted using this data at this pressure altitude.
UPHILL SLOPE: Decrease available field length 20% for each 1% (up to 2%).
DOWNHILL SLOPE: Not permitted using this data at this pressure altitude.

REVISION 24 (RE-ISSUE) GIV-SP PERFORMANCE

Mar 17/10 (GIV-SP AIRPLANES ONLY) Page PA - 33
 Quick Reference Handbook
GIV-SP Takeoff Climb Requirements: Climb Limited
Weights: Flaps 20° - Minimum Gradient AFM 5.3

For airplanes SN 1214 and subsequent and SN 1000 thru 1213

with ASC 190 incorporated.
Conditions:
• For FAA Climb Requirements
• Based on 10 minutes of Maximum Takeoff Thrust in the event of an
engine failure
• Cowl anti-ice ON below 10° C
Takeoff Limited Weight (Pounds) For
Ambient Airport Pressure Altitudes As Shown
Temp: Sea 2000 4000 6000 8000 10000
°C Level Feet Feet Feet Feet Feet
-10 & Below 74600 74600 74600 74600 74600 71900
-5 74600 74600 74600 74600 74600 71300
0 74600 74600 74600 74600 74600 70600
5 74600 74600 74600 74600 74600 69300
10 74600 74600 74600 74600 74600 68500
15 74600 74600 74600 74600 73200 67100
20 74600 74600 74600 74600 71700 65700
25 74600 74600 74600 74600 70200 64300
30 74600 74600 74600 73600 67700 62600
35 74600 74600 74600 70100 - -
40 74600 74600 72000 - - -
45 74600 74000 - - - -
50 74600 - - - - -

GIV-SP PERFORMANCE REVISION 24 (RE-ISSUE)

Page PA - 34 (GIV-SP AIRPLANES ONLY) Mar 17/10
Quick Reference Handbook
GIV-SP Takeoff Climb Requirements: Climb Limited
Weights: Flaps 10° - Minimum Gradient AFM 5.3

For airplanes SN 1214 and subsequent and SN 1000 thru 1213

with ASC 190 incorporated.
Conditions:
• For FAA Climb Requirements
• Based on 10 minutes of Maximum Takeoff Thrust in the event of an
engine failure
• Cowl anti-ice ON below 10° C
Takeoff Limited Weight (Pounds) For
Ambient Airport Pressure Altitudes As Shown
Temp: Sea 2000 4000 6000 8000 10000
°C Level Feet Feet Feet Feet Feet
0 & Below 74600 74600 74600 74600 74600 74600
5 74600 74600 74600 74600 74600 73200
10 74600 74600 74600 74600 74600 72200
15 74600 74600 74600 74600 74600 70600
20 74600 74600 74600 74600 74600 69000
25 74600 74600 74600 74600 74200 67500
30 74600 74600 74600 74600 71200 65500
35 74600 74600 74600 74000 - -
40 74600 74600 74600 - - -
45 74600 74600 - - - -
50 74600 - - - - -

REVISION 24 (RE-ISSUE) GIV-SP PERFORMANCE

Mar 17/10 (GIV-SP AIRPLANES ONLY) Page PA - 35
 Quick Reference Handbook
GIV-SP Takeoff Climb Requirements: Climb Limited
Weights: Flaps 20° - Standard Instrument Departure
GIV-OIS-07

(SN 1214 and subs and SN 1000 thru 1213 with ASC 190)
NOTE: For complete text and examples, see GIV Operating Manual
Section 11-04-40 or Operational Information Supplement number GIV-
OIS-07: Standard Instrument Departure (SID) Climb Performance.
GIV TAKEOFF GROSS WEIGHT LIMITED BY REQUIRED SID CLIMB GRADIENT
1000 FT AGL, FLAPS 20, ONE ENGINE OPERATING
DELTA AIRPORT AIRPORT
ISA AMBIENT PRESS TAKEOFF GROSS WEIGHT (1000 LB)
TEMP TEMP ALTITUDE REQUIRED SID CLIMB GRADIENT (FT/NM)
(DEG C) (DEG C) (FT) 200 300 400 500 600 700 800 900
< -20 15,000 54.6 47.8 NA NA NA NA NA NA
< -18 14,000 56.6 49.6 NA NA NA NA NA NA
< -14 12,000 60.9 53.3 47.4 NA NA NA NA NA
< -10 10,000 65.3 57.2 51.0 45.8 NA NA NA NA
< -5 < -6 8,000 69.9 61.3 54.6 49.2 NA NA NA NA
< -2 6,000 74.6 65.5 58.3 52.6 47.9 NA NA NA
<2 4,000 74.6 70.0 62.3 56.2 51.2 47.0 NA NA
<6 2,000 74.6 73.0 65.0 58.5 53.4 49.1 45.3 NA
< 10 0 74.6 74.6 67.4 60.6 55.2 50.8 46.9 NA
-15 15,000 54.1 47.4 NA NA NA NA NA NA
-13 14,000 56.2 49.2 NA NA NA NA NA NA
-9 12,000 60.4 52.9 47.0 NA NA NA NA NA
-5 10,000 64.8 56.7 50.6 45.5 NA NA NA NA
0 -1 8,000 69.5 60.9 54.2 48.9 NA NA NA NA
3 6,000 74.3 65.1 58.0 52.3 47.6 NA NA NA
7 4,000 74.6 69.6 61.9 55.8 50.9 46.7 NA NA
11 2,000 74.6 73.6 65.5 59.0 53.8 49.4 45.6 NA
15 0 74.6 74.6 67.4 60.6 55.2 50.8 46.9 NA
-10 15,000 53.7 47.0 NA NA NA NA NA NA
-8 14,000 55.7 48.8 NA NA NA NA NA NA
-4 12,000 59.8 52.4 46.6 NA NA NA NA NA
0 10,000 64.0 56.1 50.0 NA NA NA NA NA
5 4 8,000 68.5 60.1 53.5 48.2 NA NA NA NA
8 6,000 73.4 64.3 57.2 51.7 47.0 NA NA NA
12 4,000 74.6 69.5 61.8 55.7 50.8 46.6 NA NA
16 2,000 74.6 72.8 64.8 58.4 53.2 48.9 45.2 NA
20 0 74.6 74.6 67.3 60.6 55.2 50.8 46.9 NA
-5 15,000 52.8 46.1 NA NA NA NA NA NA
-3 14,000 54.7 47.9 NA NA NA NA NA NA
1 12,000 58.6 51.4 45.6 NA NA NA NA NA
5 10,000 62.7 55.0 49.0 NA NA NA NA NA
10 9 8,000 67.2 58.9 52.5 47.3 NA NA NA NA
13 6,000 72.6 63.7 56.7 51.2 46.5 NA NA NA
17 4,000 74.6 68.2 60.7 54.8 50.0 45.8 NA NA
21 2,000 74.6 72.1 64.2 57.8 52.7 48.4 NA NA
25 0 74.6 74.6 67.3 60.6 55.2 50.8 46.9 NA
NOTES: 1. Maximum climb weights are limited by the design MAX TOGW of 74,600 lb for the GIV-SP and
73,200 for the GIV.
2. Increase MAX TOGW by 300 lb for each 10 knots of headwind up to a maximum of 40 knots.
Data not valid for tailwinds.
3. Cowl anti-ice bleeds are assumed ON for temperatures below 10° C; wing anti-ice bleeds
prohibited.

GIV-SP PERFORMANCE REVISION 24 (RE-ISSUE)

Page PA - 36 (GIV-SP AIRPLANES ONLY) Mar 17/10
Quick Reference Handbook
GIV-SP Climb Limited Weights, Flaps 20°, Standard Instrument
Departure, ctd… GIV-OIS-07

GIV TAKEOFF GROSS WEIGHT LIMITED BY REQUIRED SID CLIMB GRADIENT

1000 FT AGL, FLAPS 20, ONE ENGINE OPERATING, ctd…
DELTA AIRPORT AIRPORT
ISA AMBIENT PRESS TAKEOFF GROSS WEIGHT (1000 LB)
TEMP TEMP ALTITUDE REQUIRED SID CLIMB GRADIENT (FT/NM)
(DEG C) (DEG C) (FT) 200 300 400 500 600 700 800 900
0 15,000 51.6 45.0 NA NA NA NA NA NA
2 14,000 53.5 46.8 NA NA NA NA NA NA
6 12,000 57.4 50.3 NA NA NA NA NA NA
10 10,000 61.9 54.3 48.3 NA NA NA NA NA
15 14 8,000 66.4 58.2 51.9 46.7 NA NA NA NA
18 6,000 71.3 62.5 55.7 50.3 45.7 NA NA NA
22 4,000 74.6 67.0 59.6 53.8 49.1 NA NA NA
26 2,000 74.6 71.4 63.5 57.2 52.2 48.0 NA NA
30 0 74.6 74.6 66.9 60.2 54.8 50.4 46.6 NA
5 15,000 50.5 NA NA NA NA NA NA NA
7 14,000 52.3 45.7 NA NA NA NA NA NA
11 12,000 56.6 49.6 NA NA NA NA NA NA
15 10,000 60.7 53.2 47.3 NA NA NA NA NA
20 19 8,000 65.1 57.1 50.9 45.8 NA NA NA NA
23 6,000 69.9 61.3 54.6 49.3 NA NA NA NA
27 4,000 74.6 65.5 58.3 52.7 48.0 NA NA NA
31 2,000 74.6 68.7 61.2 55.2 50.4 46.2 NA NA
35 0 74.6 71.7 63.9 57.6 52.5 48.2 NA NA
10 15,000 49.7 NA NA NA NA NA NA NA
12 14,000 51.6 NA NA NA NA NA NA NA
16 12,000 55.3 48.5 NA NA NA NA NA NA
20 10,000 59.4 52.1 46.3 NA NA NA NA NA
25 24 8,000 63.7 55.9 49.9 NA NA NA NA NA
28 6,000 68.4 60.0 53.5 48.3 NA NA NA NA
32 4,000 71.6 62.8 56.0 50.6 46.0 NA NA NA
36 2,000 74.6 65.5 58.4 52.8 48.1 NA NA NA
40 0 74.6 68.2 60.8 54.9 50.1 45.9 NA NA
15 15,000 48.5 NA NA NA NA NA NA NA
17 14,000 50.4 NA NA NA NA NA NA NA
21 12,000 54.2 47.4 NA NA NA NA NA NA
25 10,000 58.1 51.0 45.2 NA NA NA NA NA
30 29 8,000 62.0 54.4 48.5 NA NA NA NA NA
33 6,000 65.3 57.3 51.1 46.0 NA NA NA NA
37 4,000 68.2 59.9 53.5 48.2 NA NA NA NA
41 2,000 71.0 62.3 55.6 50.2 45.6 NA NA NA
45 0 73.8 64.8 57.8 52.3 47.6 NA NA NA
NOTES: 1. Maximum climb weights are limited by the design MAX TOGW of 74,600 lb for the GIV-SP and
73,200 for the GIV.
2. Increase MAX TOGW by 300 lb for each 10 knots of headwind up to a maximum of 40 knots.
Data not valid for tailwinds.
3. Cowl anti-ice bleeds are assumed ON for temperatures below 10° C; wing anti-ice bleeds
prohibited.

REVISION 24 (RE-ISSUE) GIV-SP PERFORMANCE

Mar 17/10 (GIV-SP AIRPLANES ONLY) Page PA - 37
 Quick Reference Handbook
GIV-SP Climb Limited Weights, Flaps 20°, Standard Instrument
Departure, ctd… GIV-OIS-07

GIV TAKEOFF GROSS WEIGHT LIMITED BY REQUIRED SID CLIMB GRADIENT

2000 FT AGL, FLAPS 20, ONE ENGINE OPERATING
DELTA AIRPORT AIRPORT
ISA AMBIENT PRESS TAKEOFF GROSS WEIGHT (1000 LB)
TEMP TEMP ALTITUDE REQUIRED SID CLIMB GRADIENT (FT/NM)
(DEG C) (DEG C) (FT) 200 300 400 500 600 700 800 900
< -20 15,000 53.7 47.1 NA NA NA NA NA NA
< -18 14,000 55.7 48.9 NA NA NA NA NA NA
< -14 12,000 59.9 52.7 46.9 NA NA NA NA NA
< -10 10,000 64.3 56.5 50.5 45.5 NA NA NA NA
< -5 < -6 8,000 68.8 60.5 54.0 48.8 NA NA NA NA
< -2 6,000 73.6 64.7 57.8 52.2 47.6 NA NA NA
<2 4,000 74.6 69.2 61.7 55.8 51.0 46.8 NA NA
<6 2,000 74.6 72.8 65.0 58.5 53.4 49.1 45.3 NA
< 10 0 74.6 74.6 67.4 60.6 55.2 50.8 46.9 NA
-15 15,000 53.2 46.7 NA NA NA NA NA NA
-13 14,000 55.2 48.5 NA NA NA NA NA NA
-9 12,000 59.4 52.2 46.5 NA NA NA NA NA
-5 10,000 63.8 56.1 50.1 45.1 NA NA NA NA
0 -1 8,000 68.4 60.1 53.7 48.5 NA NA NA NA
3 6,000 73.2 64.3 57.4 52.0 47.4 NA NA NA
7 4,000 74.6 68.8 61.4 55.4 50.7 46.5 NA NA
11 2,000 74.6 73.2 65.3 58.9 53.8 49.4 45.6 NA
15 0 74.6 74.6 67.4 60.6 55.2 50.8 46.9 NA
-10 15,000 52.6 46.1 NA NA NA NA NA NA
-8 14,000 54.8 48.1 NA NA NA NA NA NA
-4 12,000 58.9 51.7 46.1 NA NA NA NA NA
0 10,000 63.1 55.4 49.5 NA NA NA NA NA
5 4 8,000 67.5 59.3 53.0 47.9 NA NA NA NA
8 6,000 72.2 63.5 56.7 51.3 46.7 NA NA NA
12 4,000 74.6 68.6 61.2 55.3 50.5 46.4 NA NA
16 2,000 74.6 72.5 64.7 58.4 53.2 48.9 45.2 NA
20 0 74.6 74.6 67.2 60.6 55.2 50.8 46.9 NA
-5 15,000 51.5 45.1 NA NA NA NA NA NA
-3 14,000 53.8 47.2 NA NA NA NA NA NA
1 12,000 57.7 50.7 45.1 NA NA NA NA NA
5 10,000 61.8 54.3 48.5 NA NA NA NA NA
10 9 8,000 66.1 58.2 52.0 46.9 NA NA NA NA
13 6,000 71.5 62.9 56.1 50.8 46.3 NA NA NA
17 4,000 74.6 67.4 60.1 54.4 49.7 45.6 NA NA
21 2,000 74.6 71.6 63.8 57.7 52.7 48.4 NA NA
25 0 74.6 74.6 66.9 60.4 55.1 50.8 46.9 NA
NOTES: 1. Maximum climb weights are limited by the design MAX TOGW of 74,600 lb for the GIV-SP and
73,200 for the GIV.
2. Increase MAX TOGW by 300 lb for each 10 knots of headwind up to a maximum of 40 knots.
Data not valid for tailwinds.
3. Cowl anti-ice bleeds are assumed ON for temperatures below 10° C; wing anti-ice bleeds
prohibited.

GIV-SP PERFORMANCE REVISION 24 (RE-ISSUE)

Page PA - 38 (GIV-SP AIRPLANES ONLY) Mar 17/10
Quick Reference Handbook
GIV-SP Climb Limited Weights, Flaps 20°, Standard Instrument
Departure, ctd… GIV-OIS-07

GIV TAKEOFF GROSS WEIGHT LIMITED BY REQUIRED SID CLIMB GRADIENT

2000 FT AGL, FLAPS 20, ONE ENGINE OPERATING, ctd…
DELTA AIRPORT AIRPORT
ISA AMBIENT PRESS TAKEOFF GROSS WEIGHT (1000 LB)
TEMP TEMP ALTITUDE REQUIRED SID CLIMB GRADIENT (FT/NM)
(DEG C) (DEG C) (FT) 200 300 400 500 600 700 800 900
0 15,000 50.2 NA NA NA NA NA NA NA
2 14,000 52.6 46.1 NA NA NA NA NA NA
6 12,000 56.5 49.6 NA NA NA NA NA NA
10 10,000 61.0 53.6 47.9 NA NA NA NA NA
15 14 8,000 65.4 57.5 51.4 46.3 NA NA NA NA
18 6,000 70.1 61.7 55.1 49.9 45.4 NA NA NA
22 4,000 74.6 66.1 59.0 53.4 48.8 NA NA NA
26 2,000 74.6 70.6 63.0 56.9 52.0 47.8 NA NA
30 0 74.6 74.6 66.6 60.1 54.8 50.4 46.6 NA
5 15,000 48.7 NA NA NA NA NA NA NA
7 14,000 51.5 45.0 NA NA NA NA NA NA
11 12,000 55.7 48.9 NA NA NA NA NA NA
15 10,000 59.7 52.5 46.8 NA NA NA NA NA
20 19 8,000 64.0 56.4 50.4 45.4 NA NA NA NA
23 6,000 68.8 60.5 54.1 48.9 NA NA NA NA
27 4,000 73.5 64.7 57.8 52.3 47.7 NA NA NA
31 2,000 74.6 68.2 60.9 55.1 50.4 46.2 NA NA
35 0 74.6 71.3 63.7 57.5 52.5 48.2 NA NA
10 15,000 47.9 NA NA NA NA NA NA NA
12 14,000 50.7 NA NA NA NA NA NA NA
16 12,000 54.5 47.8 NA NA NA NA NA NA
20 10,000 58.5 51.4 45.8 NA NA NA NA NA
25 24 8,000 62.7 55.2 49.3 NA NA NA NA NA
28 6,000 67.2 59.2 52.9 47.8 NA NA NA NA
32 4,000 70.9 62.4 55.8 50.5 46.0 NA NA NA
36 2,000 74.0 65.2 58.2 52.7 48.1 NA NA NA
40 0 74.6 67.9 60.6 54.8 50.1 45.9 NA NA
15 15,000 46.4 NA NA NA NA NA NA NA
17 14,000 49.5 NA NA NA NA NA NA NA
21 12,000 53.3 46.7 NA NA NA NA NA NA
25 10,000 57.2 50.3 NA NA NA NA NA NA
30 29 8,000 61.2 53.9 48.1 NA NA NA NA NA
33 6,000 64.6 56.9 50.9 45.9 NA NA NA NA
37 4,000 67.6 59.5 53.3 48.1 NA NA NA NA
41 2,000 70.4 62.0 55.5 50.2 45.6 NA NA NA
45 0 73.2 64.5 57.7 52.3 47.6 NA NA NA
NOTES: 1. Maximum climb weights are limited by the design MAX TOGW of 74,600 lb for the GIV-SP and
73,200 for the GIV.
2. Increase MAX TOGW by 300 lb for each 10 knots of headwind up to a maximum of 40 knots.
Data not valid for tailwinds.
3. Cowl anti-ice bleeds are assumed ON for temperatures below 10° C; wing anti-ice bleeds
prohibited.

REVISION 24 (RE-ISSUE) GIV-SP PERFORMANCE

Mar 17/10 (GIV-SP AIRPLANES ONLY) Page PA - 39
 Quick Reference Handbook
GIV-SP Climb Limited Weights, Flaps 20°, Standard Instrument
Departure, ctd… GIV-OIS-07
GIV TAKEOFF GROSS WEIGHT LIMITED BY REQUIRED SID CLIMB GRADIENT
3000 FT AGL, FLAPS 20, ONE ENGINE OPERATING
DELTA AIRPORT AIRPORT
ISA AMBIENT PRESS TAKEOFF GROSS WEIGHT (1000 LB)
TEMP TEMP ALTITUDE REQUIRED SID CLIMB GRADIENT (FT/NM)
(DEG C) (DEG C) (FT) 200 300 400 500 600 700 800 900
< -20 15,000 52.7 46.3 NA NA NA NA NA NA
< -18 14,000 54.7 48.1 NA NA NA NA NA NA
< -14 12,000 58.9 51.8 46.2 NA NA NA NA NA
< -10 10,000 63.2 55.6 49.7 NA NA NA NA NA
< -5 < -6 8,000 67.7 59.6 53.3 48.1 NA NA NA NA
< -2 6,000 72.4 63.8 57.0 51.6 47.0 NA NA NA
<2 4,000 74.6 68.1 60.9 55.0 50.3 46.2 NA NA
<6 2,000 74.6 71.7 64.1 57.9 52.9 48.7 45.0 NA
< 10 0 74.6 74.6 67.0 60.5 55.2 50.8 46.9 NA
-15 15,000 52.3 45.8 NA NA NA NA NA NA
-13 14,000 54.3 47.7 NA NA NA NA NA NA
-9 12,000 58.4 51.4 45.8 NA NA NA NA NA
-5 10,000 62.7 55.2 49.3 NA NA NA NA NA
0 -1 8,000 67.2 59.1 52.9 47.8 NA NA NA NA
3 6,000 72.0 63.3 56.6 51.3 46.7 NA NA NA
7 4,000 74.6 67.7 60.5 54.7 50.0 45.9 NA NA
11 2,000 74.6 72.1 64.4 58.2 53.2 48.9 45.2 NA
15 0 74.6 74.6 67.0 60.5 55.2 50.8 46.9 NA
-10 15,000 51.5 45.2 NA NA NA NA NA NA
-8 14,000 53.7 47.1 NA NA NA NA NA NA
-4 12,000 57.8 50.9 45.3 NA NA NA NA NA
0 10,000 62.0 54.6 48.8 NA NA NA NA NA
5 4 8,000 66.3 58.4 52.2 47.2 NA NA NA NA
8 6,000 71.1 62.6 55.9 50.6 46.1 NA NA NA
12 4,000 74.6 67.5 60.3 54.6 49.9 45.8 NA NA
16 2,000 74.6 71.4 63.8 57.6 52.7 48.5 NA NA
20 0 74.6 74.6 66.6 60.1 54.9 50.6 46.8 NA
-5 15,000 50.2 NA NA NA NA NA NA NA
-3 14,000 52.5 46.0 NA NA NA NA NA NA
1 12,000 56.7 49.9 NA NA NA NA NA NA
5 10,000 60.8 53.5 47.8 NA NA NA NA NA
10 9 8,000 65.0 57.3 51.2 46.2 NA NA NA NA
13 6,000 70.3 61.9 55.3 50.1 45.6 NA NA NA
17 4,000 74.6 66.3 59.2 53.6 49.0 NA NA NA
21 2,000 74.6 70.5 63.0 56.9 52.0 47.9 NA NA
25 0 74.6 74.1 66.2 59.8 54.6 50.3 46.6 NA
NOTES: 1. Maximum climb weights are limited by the design MAX TOGW of 74,600 lb for the GIV-SP and
73,200 for the GIV.
2. Increase MAX TOGW by 300 lb for each 10 knots of headwind up to a maximum of 40 knots.
Data not valid for tailwinds.
3. Cowl anti-ice bleeds are assumed ON for temperatures below 10° C; wing anti-ice bleeds
prohibited.

GIV-SP PERFORMANCE REVISION 24 (RE-ISSUE)

Page PA - 40 (GIV-SP AIRPLANES ONLY) Mar 17/10
Quick Reference Handbook
GIV-SP Climb Limited Weights, Flaps 20°, Standard Instrument
Departure, ctd… GIV-OIS-07

GIV TAKEOFF GROSS WEIGHT LIMITED BY REQUIRED SID CLIMB GRADIENT

3000 FT AGL, FLAPS 20, ONE ENGINE OPERATING, ctd…
DELTA AIRPORT AIRPORT
ISA AMBIENT PRESS TAKEOFF GROSS WEIGHT (1000 LB)
TEMP TEMP ALTITUDE REQUIRED SID CLIMB GRADIENT (FT/NM)
(DEG C) (DEG C) (FT) 200 300 400 500 600 700 800 900
0 15,000 48.6 NA NA NA NA NA NA NA
2 14,000 51.1 NA NA NA NA NA NA NA
6 12,000 55.5 48.9 NA NA NA NA NA NA
10 10,000 60.0 52.8 47.1 NA NA NA NA NA
15 14 8,000 64.3 56.6 50.6 45.7 NA NA NA NA
18 6,000 68.9 60.7 54.3 49.1 NA NA NA NA
22 4,000 73.9 65.1 58.2 52.7 48.1 NA NA NA
26 2,000 74.6 69.6 62.1 56.2 51.4 47.2 NA NA
30 0 74.6 73.6 65.7 59.4 54.2 50.0 46.2 NA
5 15,000 46.9 NA NA NA NA NA NA NA
7 14,000 49.7 NA NA NA NA NA NA NA
11 12,000 54.8 48.2 NA NA NA NA NA NA
15 10,000 58.7 51.7 46.1 NA NA NA NA NA
20 19 8,000 63.0 55.5 49.6 NA NA NA NA NA
23 6,000 67.6 59.5 53.3 48.2 NA NA NA NA
27 4,000 72.3 63.7 56.9 51.6 47.0 NA NA NA
31 2,000 74.6 67.4 60.2 54.5 49.9 45.8 NA NA
35 0 74.6 70.6 63.1 57.1 52.2 48.0 NA NA
10 15,000 45.9 NA NA NA NA NA NA NA
12 14,000 48.8 NA NA NA NA NA NA NA
16 12,000 53.5 47.0 NA NA NA NA NA NA
20 10,000 57.4 50.6 45.0 NA NA NA NA NA
25 24 8,000 61.7 54.4 48.6 NA NA NA NA NA
28 6,000 66.0 58.2 52.1 47.1 NA NA NA NA
32 4,000 70.1 61.7 55.2 50.0 45.6 NA NA NA
36 2,000 73.2 64.5 57.7 52.3 47.7 NA NA NA
40 0 74.6 67.3 60.1 54.5 49.8 45.7 NA NA
15 15,000 NA NA NA NA NA NA NA NA
17 14,000 47.3 NA NA NA NA NA NA NA
21 12,000 52.4 46.0 NA NA NA NA NA NA
25 10,000 56.3 49.6 NA NA NA NA NA NA
30 29 8,000 60.1 53.0 47.3 NA NA NA NA NA
33 6,000 63.7 56.1 50.3 45.3 NA NA NA NA
37 4,000 66.8 58.9 52.8 47.7 NA NA NA NA
41 2,000 69.7 61.4 55.0 49.8 45.4 NA NA NA
45 0 72.5 63.9 57.2 51.9 47.3 NA NA NA
NOTES: 1. Maximum climb weights are limited by the design MAX TOGW of 74,600 lb for the GIV-SP and
73,200 for the GIV.
2. Increase MAX TOGW by 300 lb for each 10 knots of headwind up to a maximum of 40 knots.
Data not valid for tailwinds.
3. Cowl anti-ice bleeds are assumed ON for temperatures below 10° C; wing anti-ice bleeds
prohibited.

REVISION 24 (RE-ISSUE) GIV-SP PERFORMANCE

Mar 17/10 (GIV-SP AIRPLANES ONLY) Page PA - 41
 Quick Reference Handbook
GIV-SP Climb Limited Weights, Flaps 20°, Standard Instrument
Departure, ctd… GIV-OIS-07

GIV TAKEOFF GROSS WEIGHT LIMITED BY REQUIRED SID CLIMB GRADIENT

4000 FT AGL, FLAPS 20, ONE ENGINE OPERATING
DELTA AIRPORT AIRPORT
ISA AMBIENT PRESS TAKEOFF GROSS WEIGHT (1000 LB)
TEMP TEMP ALTITUDE REQUIRED SID CLIMB GRADIENT (FT/NM)
(DEG C) (DEG C) (FT) 200 300 400 500 600 700 800 900
< -20 15,000 51.9 45.6 NA NA NA NA NA NA
< -18 14,000 53.8 47.3 NA NA NA NA NA NA
< -14 12,000 57.9 51.0 45.5 NA NA NA NA NA
< -10 10,000 62.2 54.8 49.0 NA NA NA NA NA
< -5 < -6 8,000 66.7 58.7 52.6 47.5 NA NA NA NA
< -2 6,000 71.3 62.9 56.2 50.9 46.4 NA NA NA
<2 4,000 74.6 67.2 60.1 54.4 49.7 45.7 NA NA
<6 2,000 74.6 70.7 63.2 57.2 52.3 48.2 NA NA
< 10 0 74.6 74.6 66.8 60.3 55.1 50.8 46.9 NA
-15 15,000 51.6 45.2 NA NA NA NA NA NA
-13 14,000 53.4 46.9 NA NA NA NA NA NA
-9 12,000 57.5 50.6 45.1 NA NA NA NA NA
-5 10,000 61.7 54.4 48.6 NA NA NA NA NA
0 -1 8,000 66.2 58.3 52.2 47.2 NA NA NA NA
3 6,000 70.9 62.5 55.8 50.6 46.1 NA NA NA
7 4,000 74.6 66.8 59.7 54.1 49.4 45.4 NA NA
11 2,000 74.6 71.1 63.5 57.5 52.6 48.4 NA NA
15 0 74.6 74.5 66.6 60.1 54.9 50.7 46.9 NA
-10 15,000 50.8 NA NA NA NA NA NA NA
-8 14,000 52.6 46.2 NA NA NA NA NA NA
-4 12,000 56.9 50.2 NA NA NA NA NA NA
0 10,000 61.1 53.8 48.1 NA NA NA NA NA
5 4 8,000 65.4 57.6 51.6 46.6 NA NA NA NA
8 6,000 70.0 61.7 55.1 50.0 45.5 NA NA NA
12 4,000 74.6 66.5 59.5 53.9 49.2 45.2 NA NA
16 2,000 74.6 70.4 62.9 56.9 52.1 47.9 NA NA
20 0 74.6 74.1 66.2 59.8 54.7 50.4 46.7 NA
-5 15,000 49.5 NA NA NA NA NA NA NA
-3 14,000 51.2 NA NA NA NA NA NA NA
1 12,000 55.8 49.2 NA NA NA NA NA NA
5 10,000 59.9 52.8 47.1 NA NA NA NA NA
10 9 8,000 64.1 56.5 50.6 45.6 NA NA NA NA
13 6,000 69.3 61.0 54.6 49.5 45.0 NA NA NA
17 4,000 74.1 65.3 58.5 53.0 48.4 NA NA NA
21 2,000 74.6 69.5 62.1 56.2 51.4 47.3 NA NA
25 0 74.6 73.4 65.6 59.3 54.2 50.0 46.2 NA
NOTES: 1. Maximum climb weights are limited by the design MAX TOGW of 74,600 lb for the GIV-SP and
73,200 for the GIV.
2. Increase MAX TOGW by 300 lb for each 10 knots of headwind up to a maximum of 40 knots.
Data not valid for tailwinds.
3. Cowl anti-ice bleeds are assumed ON for temperatures below 10° C; wing anti-ice bleeds
prohibited.

GIV-SP PERFORMANCE REVISION 24 (RE-ISSUE)

Page PA - 42 (GIV-SP AIRPLANES ONLY) Mar 17/10
Quick Reference Handbook
GIV-SP Climb Limited Weights, Flaps 20°, Standard Instrument
Departure, ctd… GIV-OIS-07

GIV TAKEOFF GROSS WEIGHT LIMITED BY REQUIRED SID CLIMB GRADIENT

4000 FT AGL, FLAPS 20, ONE ENGINE OPERATING, ctd…
DELTA AIRPORT AIRPORT
ISA AMBIENT PRESS TAKEOFF GROSS WEIGHT (1000 LB)
TEMP TEMP ALTITUDE REQUIRED SID CLIMB GRADIENT (FT/NM)
(DEG C) (DEG C) (FT) 200 300 400 500 600 700 800 900
0 15,000 48.0 NA NA NA NA NA NA NA
2 14,000 49.6 NA NA NA NA NA NA NA
6 12,000 54.7 48.1 NA NA NA NA NA NA
10 10,000 59.1 52.1 46.5 NA NA NA NA NA
15 14 8,000 63.3 55.8 50.0 45.0 NA NA NA NA
18 6,000 67.9 59.9 53.6 48.5 NA NA NA NA
22 4,000 72.7 64.1 57.4 52.0 47.5 NA NA NA
26 2,000 74.6 68.5 61.3 55.5 50.8 46.7 NA NA
30 0 74.6 72.6 64.9 58.7 53.7 49.4 45.7 NA
5 15,000 46.3 NA NA NA NA NA NA NA
7 14,000 47.9 NA NA NA NA NA NA NA
11 12,000 53.9 47.4 NA NA NA NA NA NA
15 10,000 57.8 51.0 45.5 NA NA NA NA NA
20 19 8,000 62.0 54.7 48.9 NA NA NA NA NA
23 6,000 66.5 58.7 52.6 47.5 NA NA NA NA
27 4,000 71.1 62.7 56.1 50.9 46.4 NA NA NA
31 2,000 74.6 66.5 59.5 53.9 49.3 45.2 NA NA
35 0 74.6 70.0 62.6 56.7 51.8 47.7 NA NA
10 15,000 45.4 NA NA NA NA NA NA NA
12 14,000 47.0 NA NA NA NA NA NA NA
16 12,000 52.7 46.3 NA NA NA NA NA NA
20 10,000 56.6 49.9 NA NA NA NA NA NA
25 24 8,000 60.8 53.6 47.9 NA NA NA NA NA
28 6,000 65.0 57.4 51.4 46.4 NA NA NA NA
32 4,000 68.9 60.8 54.4 49.3 NA NA NA NA
36 2,000 72.5 64.0 57.3 52.0 47.4 NA NA NA
40 0 74.6 66.7 59.7 54.1 49.5 45.5 NA NA
15 15,000 NA NA NA NA NA NA NA NA
17 14,000 45.2 NA NA NA NA NA NA NA
21 12,000 51.5 45.2 NA NA NA NA NA NA
25 10,000 55.3 48.8 NA NA NA NA NA NA
30 29 8,000 59.2 52.2 46.6 NA NA NA NA NA
33 6,000 62.8 55.4 49.7 NA NA NA NA NA
37 4,000 66.1 58.3 52.3 47.3 NA NA NA NA
41 2,000 69.0 60.9 54.6 49.5 45.1 NA NA NA
45 0 71.9 63.5 56.9 51.6 47.1 NA NA NA
NOTES: 1. Maximum climb weights are limited by the design MAX TOGW of 74,600 lb for the GIV-SP and
73,200 for the GIV.
2. Increase MAX TOGW by 300 lb for each 10 knots of headwind up to a maximum of 40 knots.
Data not valid for tailwinds.
3. Cowl anti-ice bleeds are assumed ON for temperatures below 10° C; wing anti-ice bleeds
prohibited.

REVISION 24 (RE-ISSUE) GIV-SP PERFORMANCE

Mar 17/10 (GIV-SP AIRPLANES ONLY) Page PA - 43
 Quick Reference Handbook
GIV-SP Climb Limited Weights, Flaps 20°, Standard Instrument
Departure, ctd… GIV-OIS-07

GIV TAKEOFF GROSS WEIGHT LIMITED BY REQUIRED SID CLIMB GRADIENT

5000 FT AGL, FLAPS 20, ONE ENGINE OPERATING
DELTA AIRPORT AIRPORT
ISA AMBIENT PRESS TAKEOFF GROSS WEIGHT (1000 LB)
TEMP TEMP ALTITUDE REQUIRED SID CLIMB GRADIENT (FT/NM)
(DEG C) (DEG C) (FT) 200 300 400 500 600 700 800 900
< -20 15,000 51.6 NA NA NA NA NA NA NA
< -18 14,000 53.0 46.6 NA NA NA NA NA NA
< -14 12,000 56.9 50.2 NA NA NA NA NA NA
< -10 10,000 61.4 53.9 48.2 NA NA NA NA NA
< -5 < -6 8,000 65.7 57.8 51.7 46.7 NA NA NA NA
< -2 6,000 70.2 61.9 55.3 50.1 45.7 NA NA NA
<2 4,000 74.6 66.2 59.2 53.6 49.0 NA NA NA
<6 2,000 74.6 69.6 62.2 56.3 51.5 47.4 NA NA
< 10 0 74.6 73.5 65.7 59.4 54.3 50.0 46.3 NA
-15 15,000 50.9 NA NA NA NA NA NA NA
-13 14,000 52.6 46.2 NA NA NA NA NA NA
-9 12,000 56.9 49.7 NA NA NA NA NA NA
-5 10,000 60.7 53.5 47.8 NA NA NA NA NA
0 -1 8,000 65.4 57.4 51.3 46.4 NA NA NA NA
3 6,000 69.9 61.4 54.9 49.8 45.3 NA NA NA
7 4,000 74.6 65.7 58.8 53.2 48.6 NA NA NA
11 2,000 74.6 70.0 62.5 56.6 51.8 47.6 NA NA
15 0 74.6 73.3 65.5 59.2 54.1 49.9 46.1 NA
-10 15,000 50.8 NA NA NA NA NA NA NA
-8 14,000 51.8 45.5 NA NA NA NA NA NA
-4 12,000 55.8 49.1 NA NA NA NA NA NA
0 10,000 60.5 52.9 47.3 NA NA NA NA NA
5 4 8,000 64.6 56.7 50.7 45.8 NA NA NA NA
8 6,000 68.9 60.7 54.3 49.2 NA NA NA NA
12 4,000 74.5 65.5 58.6 53.1 48.5 NA NA NA
16 2,000 74.6 69.2 61.9 56.0 51.3 47.1 NA NA
20 0 74.6 72.9 65.2 58.9 53.8 49.6 45.9 NA
-5 15,000 48.9 NA NA NA NA NA NA NA
-3 14,000 50.5 NA NA NA NA NA NA NA
1 12,000 54.9 48.0 NA NA NA NA NA NA
5 10,000 58.9 51.9 46.3 NA NA NA NA NA
10 9 8,000 63.4 55.6 49.8 NA NA NA NA NA
13 6,000 68.4 60.1 53.7 48.7 NA NA NA NA
17 4,000 72.9 64.3 57.5 52.1 47.6 NA NA NA
21 2,000 74.6 68.3 61.1 55.3 50.6 46.5 NA NA
25 0 74.6 72.3 64.6 58.4 53.4 49.2 45.5 NA
NOTES: 1. Maximum climb weights are limited by the design MAX TOGW of 74,600 lb for the GIV-SP and
73,200 for the GIV.
2. Increase MAX TOGW by 300 lb for each 10 knots of headwind up to a maximum of 40 knots.
Data not valid for tailwinds.
3. Cowl anti-ice bleeds are assumed ON for temperatures below 10° C; wing anti-ice bleeds
prohibited.

GIV-SP PERFORMANCE REVISION 24 (RE-ISSUE)

Page PA - 44 (GIV-SP AIRPLANES ONLY) Mar 17/10
Quick Reference Handbook
GIV-SP Climb Limited Weights, Flaps 20°, Standard Instrument
Departure, ctd… GIV-OIS-07

GIV TAKEOFF GROSS WEIGHT LIMITED BY REQUIRED SID CLIMB GRADIENT

5000 FT AGL, FLAPS 20, ONE ENGINE OPERATING, ctd…
DELTA AIRPORT AIRPORT
ISA AMBIENT PRESS TAKEOFF GROSS WEIGHT (1000 LB)
TEMP TEMP ALTITUDE REQUIRED SID CLIMB GRADIENT (FT/NM)
(DEG C) (DEG C) (FT) 200 300 400 500 600 700 800 900
0 15,000 47.4 NA NA NA NA NA NA NA
2 14,000 49.0 NA NA NA NA NA NA NA
6 12,000 53.6 46.7 NA NA NA NA NA NA
10 10,000 58.6 51.3 45.7 NA NA NA NA NA
15 14 8,000 62.7 54.9 49.2 NA NA NA NA NA
18 6,000 66.8 58.9 52.7 47.7 NA NA NA NA
22 4,000 71.7 63.1 56.4 51.2 46.7 NA NA NA
26 2,000 74.6 67.4 60.3 54.6 49.9 45.9 NA NA
30 0 74.6 71.5 63.9 57.8 52.9 48.7 45.0 NA
5 15,000 45.7 NA NA NA NA NA NA NA
7 14,000 47.3 NA NA NA NA NA NA NA
11 12,000 52.8 45.9 NA NA NA NA NA NA
15 10,000 56.9 50.2 NA NA NA NA NA NA
20 19 8,000 61.3 53.8 48.1 NA NA NA NA NA
23 6,000 65.7 57.7 51.7 46.7 NA NA NA NA
27 4,000 70.0 61.7 55.2 50.1 45.6 NA NA NA
31 2,000 74.0 65.4 58.5 53.1 48.5 NA NA NA
35 0 74.6 69.1 61.8 55.9 51.2 47.1 NA NA
10 15,000 NA NA NA NA NA NA NA NA
12 14,000 46.4 NA NA NA NA NA NA NA
16 12,000 50.8 NA NA NA NA NA NA NA
20 10,000 55.7 49.1 NA NA NA NA NA NA
25 24 8,000 59.7 52.7 47.1 NA NA NA NA NA
28 6,000 64.0 56.4 50.6 45.6 NA NA NA NA
32 4,000 67.6 59.7 53.5 48.4 NA NA NA NA
36 2,000 71.4 63.2 56.6 51.3 46.8 NA NA NA
40 0 74.3 66.0 59.1 53.6 49.0 NA NA NA
15 15,000 NA NA NA NA NA NA NA NA
17 14,000 NA NA NA NA NA NA NA NA
21 12,000 49.9 NA NA NA NA NA NA NA
25 10,000 54.8 48.0 NA NA NA NA NA NA
30 29 8,000 58.4 51.4 45.8 NA NA NA NA NA
33 6,000 61.7 54.5 48.8 NA NA NA NA NA
37 4,000 64.9 57.5 51.6 46.6 NA NA NA NA
41 2,000 67.6 60.2 54.0 48.9 NA NA NA NA
45 0 70.3 62.8 56.3 51.1 46.6 NA NA NA
NOTES: 1. Maximum climb weights are limited by the design MAX TOGW of 74,600 lb for the GIV-SP and
73,200 for the GIV.
2. Increase MAX TOGW by 300 lb for each 10 knots of headwind up to a maximum of 40 knots.
Data not valid for tailwinds.
3. Cowl anti-ice bleeds are assumed ON for temperatures below 10° C; wing anti-ice bleeds
prohibited.

REVISION 24 (RE-ISSUE) GIV-SP PERFORMANCE

Mar 17/10 (GIV-SP AIRPLANES ONLY) Page PA - 45
 Quick Reference Handbook
GIV-SP Climb Limited Weights, Flaps 20°, Standard Instrument
Departure, ctd… GIV-OIS-07

GIV TAKEOFF GROSS WEIGHT LIMITED BY REQUIRED SID CLIMB GRADIENT

6000 FT AGL, FLAPS 20, ONE ENGINE OPERATING
DELTA AIRPORT AIRPORT
ISA AMBIENT PRESS TAKEOFF GROSS WEIGHT (1000 LB)
TEMP TEMP ALTITUDE REQUIRED SID CLIMB GRADIENT (FT/NM)
(DEG C) (DEG C) (FT) 200 300 400 500 600 700 800 900
< -20 15,000 48.1 NA NA NA NA NA NA NA
< -18 14,000 49.7 45.8 NA NA NA NA NA NA
< -14 12,000 53.1 49.3 NA NA NA NA NA NA
< -10 10,000 56.8 53.0 47.3 NA NA NA NA NA
< -5 < -6 8,000 60.8 56.8 50.9 45.9 NA NA NA NA
< -2 6,000 65.0 60.9 54.4 49.3 NA NA NA NA
<2 4,000 69.4 65.1 58.2 52.8 48.2 NA NA NA
<6 2,000 72.6 68.5 61.2 55.4 50.7 46.6 NA NA
< 10 0 74.6 72.2 64.6 58.4 53.4 49.2 45.5 NA
-15 15,000 47.9 NA NA NA NA NA NA NA
-13 14,000 49.6 45.6 NA NA NA NA NA NA
-9 12,000 52.8 48.9 NA NA NA NA NA NA
-5 10,000 56.5 52.6 47.0 NA NA NA NA NA
0 -1 8,000 60.5 56.4 50.5 45.6 NA NA NA NA
3 6,000 64.7 60.5 54.1 49.0 NA NA NA NA
7 4,000 69.0 64.7 57.8 52.4 47.9 NA NA NA
11 2,000 73.3 68.8 61.5 55.7 51.0 46.9 NA NA
15 0 74.6 72.1 64.4 58.3 53.3 49.1 45.4 NA
-10 15,000 47.5 NA NA NA NA NA NA NA
-8 14,000 49.1 NA NA NA NA NA NA NA
-4 12,000 52.1 48.1 NA NA NA NA NA NA
0 10,000 56.0 52.1 46.4 NA NA NA NA NA
5 4 8,000 59.9 55.8 49.9 45.0 NA NA NA NA
8 6,000 64.0 59.8 53.5 48.4 NA NA NA NA
12 4,000 69.1 64.5 57.7 52.3 47.7 NA NA NA
16 2,000 72.6 68.1 60.9 55.1 50.4 46.4 NA NA
20 0 74.6 71.7 64.1 58.0 53.0 48.8 45.1 NA
-5 15,000 46.4 NA NA NA NA NA NA NA
-3 14,000 47.9 NA NA NA NA NA NA NA
1 12,000 50.7 46.8 NA NA NA NA NA NA
5 10,000 54.9 51.1 45.5 NA NA NA NA NA
10 9 8,000 58.7 54.7 49.0 NA NA NA NA NA
13 6,000 63.4 59.1 52.9 47.9 NA NA NA NA
17 4,000 67.7 63.3 56.6 51.3 46.8 NA NA NA
21 2,000 71.7 67.2 60.1 54.4 49.8 45.7 NA NA
25 0 74.6 71.1 63.5 57.5 52.6 48.4 NA NA
NOTES: 1. Maximum climb weights are limited by the design MAX TOGW of 74,600 lb for the GIV-SP and
73,200 for the GIV.
2. Increase MAX TOGW by 300 lb for each 10 knots of headwind up to a maximum of 40 knots.
Data not valid for tailwinds.
3. Cowl anti-ice bleeds are assumed ON for temperatures below 10° C; wing anti-ice bleeds
prohibited.

GIV-SP PERFORMANCE REVISION 24 (RE-ISSUE)

Page PA - 46 (GIV-SP AIRPLANES ONLY) Mar 17/10
Quick Reference Handbook
GIV-SP Climb Limited Weights, Flaps 20°, Standard Instrument
Departure, ctd… GIV-OIS-07

GIV TAKEOFF GROSS WEIGHT LIMITED BY REQUIRED SID CLIMB GRADIENT

6000 FT AGL, FLAPS 20, ONE ENGINE OPERATING, ctd…
DELTA AIRPORT AIRPORT
ISA AMBIENT PRESS TAKEOFF GROSS WEIGHT (1000 LB)
TEMP TEMP ALTITUDE REQUIRED SID CLIMB GRADIENT (FT/NM)
(DEG C) (DEG C) (FT) 200 300 400 500 600 700 800 900
0 15,000 45.1 NA NA NA NA NA NA NA
2 14,000 46.6 NA NA NA NA NA NA NA
6 12,000 49.3 45.3 NA NA NA NA NA NA
10 10,000 54.3 50.4 NA NA NA NA NA NA
15 14 8,000 58.1 54.1 48.4 NA NA NA NA NA
18 6,000 62.2 58.0 51.9 46.9 NA NA NA NA
22 4,000 66.4 62.0 55.5 50.3 45.9 NA NA NA
26 2,000 70.8 66.3 59.3 53.7 49.1 45.1 NA NA
30 0 74.6 70.4 62.9 56.9 52.1 47.9 NA NA
5 15,000 NA NA NA NA NA NA NA NA
7 14,000 45.1 NA NA NA NA NA NA NA
11 12,000 48.5 NA NA NA NA NA NA NA
15 10,000 53.3 49.4 NA NA NA NA NA NA
20 19 8,000 56.9 53.0 47.4 NA NA NA NA NA
23 6,000 60.9 56.8 50.9 45.9 NA NA NA NA
27 4,000 64.8 60.7 54.4 49.2 NA NA NA NA
31 2,000 68.4 64.3 57.5 52.2 47.6 NA NA NA
35 0 72.3 68.0 60.8 55.1 50.4 46.3 NA NA
10 15,000 NA NA NA NA NA NA NA NA
12 14,000 NA NA NA NA NA NA NA NA
16 12,000 46.9 NA NA NA NA NA NA NA
20 10,000 52.2 48.2 NA NA NA NA NA NA
25 24 8,000 55.6 51.9 46.3 NA NA NA NA NA
28 6,000 59.4 55.5 49.7 NA NA NA NA NA
32 4,000 62.5 58.7 52.7 47.6 NA NA NA NA
36 2,000 65.9 62.1 55.6 50.5 46.0 NA NA NA
40 0 69.2 65.3 58.5 53.0 48.5 NA NA NA
15 15,000 NA NA NA NA NA NA NA NA
17 14,000 NA NA NA NA NA NA NA NA
21 12,000 45.4 NA NA NA NA NA NA NA
25 10,000 51.1 47.1 NA NA NA NA NA NA
30 29 8,000 54.2 50.5 NA NA NA NA NA NA
33 6,000 57.2 53.6 48.0 NA NA NA NA NA
37 4,000 60.1 56.7 50.9 45.9 NA NA NA NA
41 2,000 62.8 59.5 53.4 48.3 NA NA NA NA
45 0 65.4 62.2 55.8 50.6 46.1 NA NA NA
NOTES: 1. Maximum climb weights are limited by the design MAX TOGW of 74,600 lb for the GIV-SP and
73,200 for the GIV.
2. Increase MAX TOGW by 300 lb for each 10 knots of headwind up to a maximum of 40 knots.
Data not valid for tailwinds.
3. Cowl anti-ice bleeds are assumed ON for temperatures below 10° C; wing anti-ice bleeds
prohibited.

REVISION 24 (RE-ISSUE) GIV-SP PERFORMANCE

Mar 17/10 (GIV-SP AIRPLANES ONLY) Page PA - 47
 Quick Reference Handbook
GIV-SP Takeoff Climb Requirements: Climb Limited
Weights: Flaps 10° - Standard Instrument Departure
GIV-OIS-07

(SN 1214 and subs and SN 1000 thru 1213 with ASC 190)
NOTE: For complete text and examples, see GIV Operating Manual
Section 11-04-40 or Operational Information Supplement number GIV-
OIS-07: Standard Instrument Departure (SID) Climb Performance.
GIV TAKEOFF GROSS WEIGHT LIMITED BY REQUIRED SID CLIMB GRADIENT
1000 FT AGL, FLAPS 10, ONE ENGINE OPERATING
DELTA AIRPORT AIRPORT
ISA AMBIENT PRESS TAKEOFF GROSS WEIGHT (1000 LB)
TEMP TEMP ALTITUDE REQUIRED SID CLIMB GRADIENT (FT/NM)
(DEG C) (DEG C) (FT) 200 300 400 500 600 700 800 900
< -20 15,000 60.1 52.0 45.9 NA NA NA NA NA
< -18 14,000 62.3 53.9 47.6 NA NA NA NA NA
< -14 12,000 66.9 57.9 51.1 45.8 NA NA NA NA
< -10 10,000 71.7 62.1 54.8 49.0 NA NA NA NA
< -5 < -6 8,000 74.6 66.4 58.6 52.5 47.6 NA NA NA
< -2 6,000 74.6 70.9 62.6 56.0 50.7 46.6 NA NA
<2 4,000 74.6 74.6 66.8 59.9 54.2 49.6 45.9 NA
<6 2,000 74.6 74.6 69.7 62.4 56.4 51.7 47.7 NA
< 10 0 74.6 74.6 72.2 64.7 58.5 53.5 49.4 45.9
-15 15,000 59.6 51.6 45.5 NA NA NA NA NA
-13 14,000 61.8 53.5 47.2 NA NA NA NA NA
-9 12,000 66.4 57.5 50.7 45.4 NA NA NA NA
-5 10,000 71.1 61.6 54.3 48.7 NA NA NA NA
0 -1 8,000 74.6 65.9 58.2 52.1 47.3 NA NA NA
3 6,000 74.6 70.5 62.2 55.7 50.5 46.3 NA NA
7 4,000 74.6 74.6 66.4 59.5 53.8 49.3 45.6 NA
11 2,000 74.6 74.6 70.2 62.9 56.9 52.0 48.1 NA
15 0 74.6 74.6 72.2 64.7 58.5 53.4 49.3 45.9
-10 15,000 59.1 51.1 45.1 NA NA NA NA NA
-8 14,000 61.3 53.0 46.8 NA NA NA NA NA
-4 12,000 65.7 56.9 50.2 NA NA NA NA NA
0 10,000 70.3 60.8 53.7 48.1 NA NA NA NA
5 4 8,000 74.6 65.1 57.4 51.4 46.7 NA NA NA
8 6,000 74.6 69.6 61.4 55.0 49.8 45.7 NA NA
12 4,000 74.6 74.6 66.3 59.4 53.7 49.2 45.5 NA
16 2,000 74.6 74.6 69.5 62.2 56.3 51.5 47.6 NA
20 0 74.6 74.6 72.2 64.6 58.5 53.4 49.3 45.9
-5 15,000 58.1 50.2 NA NA NA NA NA NA
-3 14,000 60.1 52.0 45.9 NA NA NA NA NA
1 12,000 64.4 55.8 49.2 NA NA NA NA NA
5 10,000 68.8 59.6 52.6 47.2 NA NA NA NA
10 9 8,000 73.6 63.8 56.3 50.4 45.8 NA NA NA
13 6,000 74.6 68.9 60.8 54.5 49.4 45.3 NA NA
17 4,000 74.6 73.7 65.1 58.3 52.8 48.4 NA NA
21 2,000 74.6 74.6 68.8 61.6 55.7 51.0 47.2 NA
25 0 74.6 74.6 72.1 64.6 58.5 53.4 49.3 45.9
NOTES: 1. Maximum climb weights are limited by the design MAX TOGW of 74,600 lb for the GIV-SP and
73,200 for the GIV.
2. Increase MAX TOGW by 300 lb for each 10 knots of headwind up to a maximum of 40 knots.
Data not valid for tailwinds.
3. Cowl anti-ice bleeds are assumed ON for temperatures below 10° C; wing anti-ice bleeds
prohibited.

GIV-SP PERFORMANCE REVISION 24 (RE-ISSUE)

Page PA - 48 (GIV-SP AIRPLANES ONLY) Mar 17/10
Quick Reference Handbook
GIV-SP Climb Limited Weights, Flaps 10°, Standard Instrument
Departure, ctd… GIV-OIS-07

GIV TAKEOFF GROSS WEIGHT LIMITED BY REQUIRED SID CLIMB GRADIENT

1000 FT AGL, FLAPS 10, ONE ENGINE OPERATING, ctd…
DELTA AIRPORT AIRPORT
ISA AMBIENT PRESS TAKEOFF GROSS WEIGHT (1000 LB)
TEMP TEMP ALTITUDE REQUIRED SID CLIMB GRADIENT (FT/NM)
(DEG C) (DEG C) (FT) 200 300 400 500 600 700 800 900
0 15,000 56.8 49.2 NA NA NA NA NA NA
2 14,000 58.8 50.9 NA NA NA NA NA NA
6 12,000 63.0 54.6 48.2 NA NA NA NA NA
10 10,000 68.0 58.9 51.9 46.6 NA NA NA NA
15 14 8,000 72.8 63.0 55.6 49.9 45.3 NA NA NA
18 6,000 74.6 67.6 59.7 53.5 48.5 NA NA NA
22 4,000 74.6 72.4 63.9 57.3 51.9 47.6 NA NA
26 2,000 74.6 74.6 68.1 61.0 55.1 50.5 46.7 NA
30 0 74.6 74.6 71.7 64.2 58.1 53.1 49.0 45.6
5 15,000 55.5 48.1 NA NA NA NA NA NA
7 14,000 57.5 49.8 NA NA NA NA NA NA
11 12,000 62.1 53.8 47.5 NA NA NA NA NA
15 10,000 66.6 57.6 50.9 45.7 NA NA NA NA
20 19 8,000 71.3 61.8 54.6 48.9 NA NA NA NA
23 6,000 74.6 66.3 58.6 52.5 47.7 NA NA NA
27 4,000 74.6 70.7 62.5 56.0 50.8 46.6 NA NA
31 2,000 74.6 74.1 65.5 58.7 53.2 48.8 45.1 NA
35 0 74.6 74.6 68.4 61.3 55.5 50.8 47.0 NA
10 15,000 54.7 47.3 NA NA NA NA NA NA
12 14,000 56.7 49.1 NA NA NA NA NA NA
16 12,000 60.8 52.6 46.5 NA NA NA NA NA
20 10,000 65.1 56.4 49.8 NA NA NA NA NA
25 24 8,000 69.8 60.5 53.4 48.0 NA NA NA NA
28 6,000 74.6 64.9 57.3 51.4 46.7 NA NA NA
32 4,000 74.6 67.8 60.0 53.8 48.8 NA NA NA
36 2,000 74.6 70.7 62.5 56.0 50.9 46.7 NA NA
40 0 74.6 73.6 65.1 58.3 52.9 48.5 NA NA
15 15,000 53.4 46.2 NA NA NA NA NA NA
17 14,000 55.4 47.9 NA NA NA NA NA NA
21 12,000 59.5 51.5 45.6 NA NA NA NA NA
25 10,000 63.7 55.2 48.8 NA NA NA NA NA
30 29 8,000 67.9 58.9 52.0 46.7 NA NA NA NA
33 6,000 71.3 61.9 54.7 49.1 NA NA NA NA
37 4,000 74.4 64.6 57.1 51.3 46.7 NA NA NA
41 2,000 74.6 67.2 59.4 53.3 48.5 NA NA NA
45 0 74.6 69.9 61.9 55.4 50.4 46.3 NA NA
NOTES: 1. Maximum climb weights are limited by the design MAX TOGW of 74,600 lb for the GIV-SP and
73,200 for the GIV.
2. Increase MAX TOGW by 300 lb for each 10 knots of headwind up to a maximum of 40 knots.
Data not valid for tailwinds.
3. Cowl anti-ice bleeds are assumed ON for temperatures below 10° C; wing anti-ice bleeds
prohibited.

REVISION 24 (RE-ISSUE) GIV-SP PERFORMANCE

Mar 17/10 (GIV-SP AIRPLANES ONLY) Page PA - 49
 Quick Reference Handbook
GIV-SP Climb Limited Weights, Flaps 10°, Standard Instrument
Departure, ctd… GIV-OIS-07

GIV TAKEOFF GROSS WEIGHT LIMITED BY REQUIRED SID CLIMB GRADIENT

2000 FT AGL, FLAPS 10, ONE ENGINE OPERATING
DELTA AIRPORT AIRPORT
ISA AMBIENT PRESS TAKEOFF GROSS WEIGHT (1000 LB)
TEMP TEMP ALTITUDE REQUIRED SID CLIMB GRADIENT (FT/NM)
(DEG C) (DEG C) (FT) 200 300 400 500 600 700 800 900
< -20 15,000 59.2 51.3 45.4 NA NA NA NA NA
< -18 14,000 61.3 53.2 47.1 NA NA NA NA NA
< -14 12,000 65.8 57.2 50.6 45.4 NA NA NA NA
< -10 10,000 70.6 61.3 54.2 48.7 NA NA NA NA
< -5 < -6 8,000 74.6 65.6 58.0 52.1 47.4 NA NA NA
< -2 6,000 74.6 70.1 62.0 55.6 50.5 46.4 NA NA
<2 4,000 74.6 74.6 66.2 59.5 53.9 49.4 45.8 NA
<6 2,000 74.6 74.6 69.7 62.4 56.4 51.7 47.7 NA
< 10 0 74.6 74.6 72.2 64.7 58.5 53.5 49.4 45.9
-15 15,000 58.7 50.9 45.0 NA NA NA NA NA
-13 14,000 60.8 52.8 46.7 NA NA NA NA NA
-9 12,000 65.3 56.7 50.2 45.1 NA NA NA NA
-5 10,000 70.0 60.8 53.8 48.3 NA NA NA NA
0 -1 8,000 74.6 65.1 57.6 51.7 47.1 NA NA NA
3 6,000 74.6 69.7 61.7 55.3 50.2 46.1 NA NA
7 4,000 74.6 74.4 65.8 59.1 53.6 49.2 45.5 NA
11 2,000 74.6 74.6 70.0 62.8 56.9 52.0 48.1 NA
15 0 74.6 74.6 72.2 64.7 58.5 53.4 49.3 45.9
-10 15,000 58.0 50.3 NA NA NA NA NA NA
-8 14,000 60.3 52.4 46.3 NA NA NA NA NA
-4 12,000 64.7 56.2 49.7 NA NA NA NA NA
0 10,000 69.2 60.2 53.2 47.8 NA NA NA NA
5 4 8,000 74.0 64.3 56.9 51.0 46.5 NA NA NA
8 6,000 74.6 68.7 60.8 54.6 49.6 45.5 NA NA
12 4,000 74.6 74.2 65.7 58.9 53.5 49.0 45.4 NA
16 2,000 74.6 74.6 69.4 62.2 56.3 51.5 47.6 NA
20 0 74.6 74.6 72.0 64.6 58.5 53.4 49.3 45.9
-5 15,000 56.7 49.2 NA NA NA NA NA NA
-3 14,000 59.2 51.4 45.5 NA NA NA NA NA
1 12,000 63.4 55.1 48.7 NA NA NA NA NA
5 10,000 67.8 58.9 52.1 46.9 NA NA NA NA
10 9 8,000 72.5 63.0 55.8 50.1 45.6 NA NA NA
13 6,000 74.6 68.0 60.2 54.1 49.1 45.1 NA NA
17 4,000 74.6 72.8 64.5 57.9 52.5 48.2 NA NA
21 2,000 74.6 74.6 68.5 61.4 55.7 51.0 47.2 NA
25 0 74.6 74.6 71.8 64.4 58.4 53.4 49.3 45.9
NOTES: 1. Maximum climb weights are limited by the design MAX TOGW of 74,600 lb for the GIV-SP and
73,200 for the GIV.
2. Increase MAX TOGW by 300 lb for each 10 knots of headwind up to a maximum of 40 knots.
Data not valid for tailwinds.
3. Cowl anti-ice bleeds are assumed ON for temperatures below 10° C; wing anti-ice bleeds
prohibited.

GIV-SP PERFORMANCE REVISION 24 (RE-ISSUE)

Page PA - 50 (GIV-SP AIRPLANES ONLY) Mar 17/10
Quick Reference Handbook
GIV-SP Climb Limited Weights, Flaps 10°, Standard Instrument
Departure, ctd… GIV-OIS-07

GIV TAKEOFF GROSS WEIGHT LIMITED BY REQUIRED SID CLIMB GRADIENT

2000 FT AGL, FLAPS 10, ONE ENGINE OPERATING, ctd…
DELTA AIRPORT AIRPORT
ISA AMBIENT PRESS TAKEOFF GROSS WEIGHT (1000 LB)
TEMP TEMP ALTITUDE REQUIRED SID CLIMB GRADIENT (FT/NM)
(DEG C) (DEG C) (FT) 200 300 400 500 600 700 800 900
0 15,000 55.2 47.9 NA NA NA NA NA NA
2 14,000 57.9 50.3 NA NA NA NA NA NA
6 12,000 62.0 53.9 47.7 NA NA NA NA NA
10 10,000 66.9 58.2 51.5 46.3 NA NA NA NA
15 14 8,000 71.6 62.3 55.1 49.5 45.1 NA NA NA
18 6,000 74.6 66.8 59.1 53.1 48.3 NA NA NA
22 4,000 74.6 71.5 63.3 56.8 51.6 47.4 NA NA
26 2,000 74.6 74.6 67.5 60.6 54.9 50.4 46.7 NA
30 0 74.6 74.6 71.4 64.1 58.1 53.1 49.0 45.6
5 15,000 53.7 46.6 NA NA NA NA NA NA
7 14,000 56.6 49.2 NA NA NA NA NA NA
11 12,000 61.2 53.1 47.1 NA NA NA NA NA
15 10,000 65.5 56.9 50.4 45.3 NA NA NA NA
20 19 8,000 70.2 61.0 54.0 48.6 NA NA NA NA
23 6,000 74.6 65.4 58.0 52.0 47.4 NA NA NA
27 4,000 74.6 69.9 61.9 55.6 50.5 46.5 NA NA
31 2,000 74.6 73.7 65.3 58.6 53.2 48.8 45.1 NA
35 0 74.6 74.6 68.2 61.3 55.5 50.8 47.0 NA
10 15,000 52.7 45.8 NA NA NA NA NA NA
12 14,000 55.7 48.5 NA NA NA NA NA NA
16 12,000 59.8 52.0 46.1 NA NA NA NA NA
20 10,000 64.1 55.7 49.4 NA NA NA NA NA
25 24 8,000 68.7 59.8 52.9 47.6 NA NA NA NA
28 6,000 73.5 64.0 56.7 50.9 46.4 NA NA NA
32 4,000 74.6 67.4 59.8 53.7 48.8 NA NA NA
36 2,000 74.6 70.3 62.3 56.0 50.9 46.7 NA NA
40 0 74.6 73.2 64.9 58.3 52.9 48.5 NA NA
15 15,000 51.2 NA NA NA NA NA NA NA
17 14,000 54.4 47.3 NA NA NA NA NA NA
21 12,000 58.5 50.8 45.1 NA NA NA NA NA
25 10,000 62.7 54.5 48.3 NA NA NA NA NA
30 29 8,000 67.0 58.2 51.6 46.5 NA NA NA NA
33 6,000 70.6 61.5 54.5 49.0 NA NA NA NA
37 4,000 73.7 64.2 57.0 51.3 46.7 NA NA NA
41 2,000 74.6 66.8 59.3 53.3 48.5 NA NA NA
45 0 74.6 69.6 61.7 55.4 50.4 46.3 NA NA
NOTES: 1. Maximum climb weights are limited by the design MAX TOGW of 74,600 lb for the GIV-SP and
73,200 for the GIV.
2. Increase MAX TOGW by 300 lb for each 10 knots of headwind up to a maximum of 40 knots.
Data not valid for tailwinds.
3. Cowl anti-ice bleeds are assumed ON for temperatures below 10° C; wing anti-ice bleeds
prohibited.

REVISION 24 (RE-ISSUE) GIV-SP PERFORMANCE

Mar 17/10 (GIV-SP AIRPLANES ONLY) Page PA - 51
 Quick Reference Handbook
GIV-SP Climb Limited Weights, Flaps 10°, Standard Instrument
Departure, ctd… GIV-OIS-07

GIV TAKEOFF GROSS WEIGHT LIMITED BY REQUIRED SID CLIMB GRADIENT

3000 FT AGL, FLAPS 10, ONE ENGINE OPERATING
DELTA AIRPORT AIRPORT
ISA AMBIENT PRESS TAKEOFF GROSS WEIGHT (1000 LB)
TEMP TEMP ALTITUDE REQUIRED SID CLIMB GRADIENT (FT/NM)
(DEG C) (DEG C) (FT) 200 300 400 500 600 700 800 900
< -20 15,000 58.1 50.5 NA NA NA NA NA NA
< -18 14,000 60.3 52.4 46.4 NA NA NA NA NA
< -14 12,000 64.7 56.3 49.8 NA NA NA NA NA
< -10 10,000 69.4 60.4 53.4 48.0 NA NA NA NA
< -5 < -6 8,000 74.2 64.6 57.2 51.4 46.8 NA NA NA
< -2 6,000 74.6 69.1 61.2 54.9 49.9 45.9 NA NA
<2 4,000 74.6 73.7 65.3 58.7 53.3 48.9 45.3 NA
<6 2,000 74.6 74.6 68.7 61.7 56.0 51.3 47.5 NA
< 10 0 74.6 74.6 71.9 64.6 58.5 53.5 49.4 45.9
-15 15,000 57.6 50.0 NA NA NA NA NA NA
-13 14,000 59.7 51.9 46.0 NA NA NA NA NA
-9 12,000 64.2 55.8 49.4 NA NA NA NA NA
-5 10,000 68.8 59.9 53.0 47.7 NA NA NA NA
0 -1 8,000 73.7 64.1 56.8 51.0 46.4 NA NA NA
3 6,000 74.6 68.6 60.8 54.6 49.6 45.6 NA NA
7 4,000 74.6 73.2 64.9 58.3 52.9 48.6 NA NA
11 2,000 74.6 74.6 69.0 62.0 56.2 51.6 47.7 NA
15 0 74.6 74.6 71.9 64.6 58.5 53.4 49.3 45.9
-10 15,000 56.8 49.3 NA NA NA NA NA NA
-8 14,000 59.1 51.3 45.5 NA NA NA NA NA
-4 12,000 63.6 55.3 49.0 NA NA NA NA NA
0 10,000 68.0 59.2 52.4 47.1 NA NA NA NA
5 4 8,000 72.7 63.3 56.1 50.3 45.9 NA NA NA
8 6,000 74.6 67.7 60.0 53.9 49.0 45.0 NA NA
12 4,000 74.6 73.0 64.7 58.1 52.8 48.5 NA NA
16 2,000 74.6 74.6 68.4 61.4 55.7 51.1 47.3 NA
20 0 74.6 74.6 71.4 64.2 58.2 53.3 49.3 45.9
-5 15,000 55.2 48.0 NA NA NA NA NA NA
-3 14,000 57.7 50.2 NA NA NA NA NA NA
1 12,000 62.3 54.2 48.0 NA NA NA NA NA
5 10,000 66.7 58.0 51.4 46.3 NA NA NA NA
10 9 8,000 71.3 62.0 55.0 49.4 NA NA NA NA
13 6,000 74.6 67.0 59.4 53.3 48.5 NA NA NA
17 4,000 74.6 71.7 63.5 57.1 51.8 47.7 NA NA
21 2,000 74.6 74.6 67.5 60.6 55.0 50.5 46.8 NA
25 0 74.6 74.6 71.0 63.8 57.9 53.0 49.0 45.7
NOTES: 1. Maximum climb weights are limited by the design MAX TOGW of 74,600 lb for the GIV-SP and
73,200 for the GIV.
2. Increase MAX TOGW by 300 lb for each 10 knots of headwind up to a maximum of 40 knots.
Data not valid for tailwinds.
3. Cowl anti-ice bleeds are assumed ON for temperatures below 10° C; wing anti-ice bleeds
prohibited.

GIV-SP PERFORMANCE REVISION 24 (RE-ISSUE)

Page PA - 52 (GIV-SP AIRPLANES ONLY) Mar 17/10
Quick Reference Handbook
GIV-SP Climb Limited Weights, Flaps 10°, Standard Instrument
Departure, ctd… GIV-OIS-07

GIV TAKEOFF GROSS WEIGHT LIMITED BY REQUIRED SID CLIMB GRADIENT

3000 FT AGL, FLAPS 10, ONE ENGINE OPERATING, ctd…
DELTA AIRPORT AIRPORT
ISA AMBIENT PRESS TAKEOFF GROSS WEIGHT (1000 LB)
TEMP TEMP ALTITUDE REQUIRED SID CLIMB GRADIENT (FT/NM)
(DEG C) (DEG C) (FT) 200 300 400 500 600 700 800 900
0 15,000 53.5 46.6 NA NA NA NA NA NA
2 14,000 56.2 48.9 NA NA NA NA NA NA
6 12,000 61.0 53.1 47.0 NA NA NA NA NA
10 10,000 65.8 57.3 50.7 45.7 NA NA NA NA
15 14 8,000 70.4 61.3 54.3 48.9 NA NA NA NA
18 6,000 74.6 65.7 58.2 52.3 47.6 NA NA NA
22 4,000 74.6 70.3 62.4 56.0 50.9 46.8 NA NA
26 2,000 74.6 74.6 66.6 59.8 54.3 49.9 46.2 NA
30 0 74.6 74.6 70.5 63.3 57.4 52.6 48.7 45.3
5 15,000 51.7 NA NA NA NA NA NA NA
7 14,000 54.7 47.6 NA NA NA NA NA NA
11 12,000 60.2 52.3 46.4 NA NA NA NA NA
15 10,000 64.4 56.0 49.7 NA NA NA NA NA
20 19 8,000 69.0 60.1 53.2 47.9 NA NA NA NA
23 6,000 74.0 64.4 57.1 51.3 46.8 NA NA NA
27 4,000 74.6 68.8 61.0 54.8 49.9 45.9 NA NA
31 2,000 74.6 72.8 64.6 58.0 52.7 48.5 NA NA
35 0 74.6 74.6 67.6 60.8 55.1 50.6 46.9 NA
10 15,000 50.7 NA NA NA NA NA NA NA
12 14,000 53.7 46.8 NA NA NA NA NA NA
16 12,000 58.8 51.2 45.4 NA NA NA NA NA
20 10,000 63.0 54.8 48.6 NA NA NA NA NA
25 24 8,000 67.6 58.8 52.2 47.0 NA NA NA NA
28 6,000 72.2 62.9 55.8 50.2 45.8 NA NA NA
32 4,000 74.6 66.7 59.2 53.2 48.5 NA NA NA
36 2,000 74.6 69.6 61.8 55.5 50.6 46.5 NA NA
40 0 74.6 72.6 64.4 57.9 52.7 48.4 NA NA
15 15,000 48.9 NA NA NA NA NA NA NA
17 14,000 52.1 45.4 NA NA NA NA NA NA
21 12,000 57.5 50.0 NA NA NA NA NA NA
25 10,000 61.7 53.7 47.7 NA NA NA NA NA
30 29 8,000 65.8 57.3 50.8 45.8 NA NA NA NA
33 6,000 69.6 60.7 53.8 48.5 NA NA NA NA
37 4,000 72.8 63.5 56.4 50.8 46.3 NA NA NA
41 2,000 74.6 66.2 58.8 53.0 48.3 NA NA NA
45 0 74.6 69.0 61.2 55.0 50.2 46.1 NA NA
NOTES: 1. Maximum climb weights are limited by the design MAX TOGW of 74,600 lb for the GIV-SP and
73,200 for the GIV.
2. Increase MAX TOGW by 300 lb for each 10 knots of headwind up to a maximum of 40 knots.
Data not valid for tailwinds.
3. Cowl anti-ice bleeds are assumed ON for temperatures below 10° C; wing anti-ice bleeds
prohibited.

REVISION 24 (RE-ISSUE) GIV-SP PERFORMANCE

Mar 17/10 (GIV-SP AIRPLANES ONLY) Page PA - 53
 Quick Reference Handbook
GIV-SP Climb Limited Weights, Flaps 10°, Standard Instrument
Departure, ctd… GIV-OIS-07

GIV TAKEOFF GROSS WEIGHT LIMITED BY REQUIRED SID CLIMB GRADIENT

4000 FT AGL, FLAPS 10, ONE ENGINE OPERATING
DELTA AIRPORT AIRPORT
ISA AMBIENT PRESS TAKEOFF GROSS WEIGHT (1000 LB)
TEMP TEMP ALTITUDE REQUIRED SID CLIMB GRADIENT (FT/NM)
(DEG C) (DEG C) (FT) 200 300 400 500 600 700 800 900
< -20 15,000 57.3 49.8 NA NA NA NA NA NA
< -18 14,000 59.3 51.6 45.7 NA NA NA NA NA
< -14 12,000 63.7 55.4 49.1 NA NA NA NA NA
< -10 10,000 68.3 59.5 52.7 47.4 NA NA NA NA
< -5 < -6 8,000 73.1 63.7 56.5 50.7 46.2 NA NA NA
< -2 6,000 74.6 68.1 60.4 54.2 49.3 45.4 NA NA
<2 4,000 74.6 72.7 64.5 57.9 52.6 48.4 NA NA
<6 2,000 74.6 74.6 67.8 60.9 55.3 50.8 47.1 NA
< 10 0 74.6 74.6 71.6 64.4 58.4 53.5 49.4 45.9
-15 15,000 56.8 49.4 NA NA NA NA NA NA
-13 14,000 58.8 51.1 45.3 NA NA NA NA NA
-9 12,000 63.2 55.0 48.7 NA NA NA NA NA
-5 10,000 67.7 59.0 52.3 47.1 NA NA NA NA
0 -1 8,000 72.6 63.2 56.0 50.4 45.9 NA NA NA
3 6,000 74.6 67.6 60.0 53.9 49.0 45.1 NA NA
7 4,000 74.6 72.2 64.1 57.6 52.3 48.1 NA NA
11 2,000 74.6 74.6 68.2 61.3 55.6 51.0 47.3 NA
15 0 74.6 74.6 71.4 64.2 58.2 53.4 49.3 45.9
-10 15,000 56.0 48.7 NA NA NA NA NA NA
-8 14,000 57.9 50.4 NA NA NA NA NA NA
-4 12,000 62.6 54.5 48.3 NA NA NA NA NA
0 10,000 67.0 58.4 51.7 46.6 NA NA NA NA
5 4 8,000 71.7 62.5 55.4 49.8 45.4 NA NA NA
8 6,000 74.6 66.8 59.2 53.2 48.4 NA NA NA
12 4,000 74.6 72.0 63.8 57.4 52.1 47.9 NA NA
16 2,000 74.6 74.6 67.5 60.6 55.0 50.6 46.8 NA
20 0 74.6 74.6 71.0 63.8 57.9 53.1 49.1 45.8
-5 15,000 54.5 47.5 NA NA NA NA NA NA
-3 14,000 56.4 49.0 NA NA NA NA NA NA
1 12,000 61.4 53.4 47.4 NA NA NA NA NA
5 10,000 65.7 57.2 50.7 45.7 NA NA NA NA
10 9 8,000 70.2 61.2 54.3 48.8 NA NA NA NA
13 6,000 74.6 66.1 58.6 52.7 48.0 NA NA NA
17 4,000 74.6 70.7 62.7 56.3 51.2 47.1 NA NA
21 2,000 74.6 74.6 66.6 59.9 54.3 49.9 46.3 NA
25 0 74.6 74.6 70.4 63.3 57.4 52.6 48.7 45.4
NOTES: 1. Maximum climb weights are limited by the design MAX TOGW of 74,600 lb for the GIV-SP and
73,200 for the GIV.
2. Increase MAX TOGW by 300 lb for each 10 knots of headwind up to a maximum of 40 knots.
Data not valid for tailwinds.
3. Cowl anti-ice bleeds are assumed ON for temperatures below 10° C; wing anti-ice bleeds
prohibited.

GIV-SP PERFORMANCE REVISION 24 (RE-ISSUE)

Page PA - 54 (GIV-SP AIRPLANES ONLY) Mar 17/10
Quick Reference Handbook
GIV-SP Climb Limited Weights, Flaps 10°, Standard Instrument
Departure, ctd… GIV-OIS-07

GIV TAKEOFF GROSS WEIGHT LIMITED BY REQUIRED SID CLIMB GRADIENT

4000 FT AGL, FLAPS 10, ONE ENGINE OPERATING, ctd…
DELTA AIRPORT AIRPORT
ISA AMBIENT PRESS TAKEOFF GROSS WEIGHT (1000 LB)
TEMP TEMP ALTITUDE REQUIRED SID CLIMB GRADIENT (FT/NM)
(DEG C) (DEG C) (FT) 200 300 400 500 600 700 800 900
0 15,000 52.9 46.1 NA NA NA NA NA NA
2 14,000 54.6 47.6 NA NA NA NA NA NA
6 12,000 60.1 52.3 46.4 NA NA NA NA NA
10 10,000 64.8 56.5 50.1 45.1 NA NA NA NA
15 14 8,000 69.4 60.5 53.6 48.3 NA NA NA NA
18 6,000 74.3 64.8 57.5 51.7 47.1 NA NA NA
22 4,000 74.6 69.3 61.5 55.3 50.3 46.3 NA NA
26 2,000 74.6 74.0 65.7 59.1 53.7 49.3 45.7 NA
30 0 74.6 74.6 69.6 62.6 56.8 52.1 48.2 NA
5 15,000 51.2 NA NA NA NA NA NA NA
7 14,000 52.8 46.0 NA NA NA NA NA NA
11 12,000 59.2 51.6 45.8 NA NA NA NA NA
15 10,000 63.4 55.3 49.1 NA NA NA NA NA
20 19 8,000 67.9 59.2 52.5 47.3 NA NA NA NA
23 6,000 72.8 63.5 56.3 50.7 46.2 NA NA NA
27 4,000 74.6 67.8 60.2 54.1 49.3 45.3 NA NA
31 2,000 74.6 71.8 63.7 57.3 52.1 48.0 NA NA
35 0 74.6 74.6 67.1 60.3 54.8 50.3 46.6 NA
10 15,000 50.2 NA NA NA NA NA NA NA
12 14,000 51.8 45.1 NA NA NA NA NA NA
16 12,000 57.9 50.4 NA NA NA NA NA NA
20 10,000 62.0 54.1 48.0 NA NA NA NA NA
25 24 8,000 66.6 58.0 51.5 46.4 NA NA NA NA
28 6,000 71.1 62.0 55.0 49.6 45.2 NA NA NA
32 4,000 74.6 65.7 58.3 52.5 47.9 NA NA NA
36 2,000 74.6 69.0 61.3 55.1 50.3 46.3 NA NA
40 0 74.6 72.0 64.0 57.5 52.4 48.2 NA NA
15 15,000 48.4 NA NA NA NA NA NA NA
17 14,000 49.9 NA NA NA NA NA NA NA
21 12,000 56.6 49.3 NA NA NA NA NA NA
25 10,000 60.7 52.9 47.0 NA NA NA NA NA
30 29 8,000 64.8 56.5 50.1 45.2 NA NA NA NA
33 6,000 68.7 59.9 53.2 48.0 NA NA NA NA
37 4,000 72.1 63.0 55.9 50.4 46.0 NA NA NA
41 2,000 74.6 65.7 58.4 52.6 48.0 NA NA NA
45 0 74.6 68.5 60.8 54.7 49.9 45.9 NA NA
NOTES: 1. Maximum climb weights are limited by the design MAX TOGW of 74,600 lb for the GIV-SP and
73,200 for the GIV.
2. Increase MAX TOGW by 300 lb for each 10 knots of headwind up to a maximum of 40 knots.
Data not valid for tailwinds.
3. Cowl anti-ice bleeds are assumed ON for temperatures below 10° C; wing anti-ice bleeds
prohibited.

REVISION 24 (RE-ISSUE) GIV-SP PERFORMANCE

Mar 17/10 (GIV-SP AIRPLANES ONLY) Page PA - 55
 Quick Reference Handbook
GIV-SP Climb Limited Weights, Flaps 10°, Standard Instrument
Departure, ctd… GIV-OIS-07

GIV TAKEOFF GROSS WEIGHT LIMITED BY REQUIRED SID CLIMB GRADIENT

5000 FT AGL, FLAPS 10, ONE ENGINE OPERATING
DELTA AIRPORT AIRPORT
ISA AMBIENT PRESS TAKEOFF GROSS WEIGHT (1000 LB)
TEMP TEMP ALTITUDE REQUIRED SID CLIMB GRADIENT (FT/NM)
(DEG C) (DEG C) (FT) 200 300 400 500 600 700 800 900
< -20 15,000 56.3 49.0 NA NA NA NA NA NA
< -18 14,000 58.4 50.8 NA NA NA NA NA NA
< -14 12,000 62.6 54.5 48.3 NA NA NA NA NA
< -10 10,000 67.1 58.5 51.8 46.7 NA NA NA NA
< -5 < -6 8,000 71.9 62.6 55.5 49.9 45.5 NA NA NA
< -2 6,000 74.6 67.0 59.4 53.4 48.6 NA NA NA
<2 4,000 74.6 71.6 63.5 57.0 51.9 47.7 NA NA
<6 2,000 74.6 74.6 66.7 60.0 54.4 50.0 46.4 NA
< 10 0 74.6 74.6 70.5 63.4 57.5 52.7 48.8 45.4
-15 15,000 56.1 48.8 NA NA NA NA NA NA
-13 14,000 57.9 50.4 NA NA NA NA NA NA
-9 12,000 62.1 54.0 47.9 NA NA NA NA NA
-5 10,000 66.6 58.0 51.4 46.3 NA NA NA NA
0 -1 8,000 71.4 62.2 55.1 49.6 45.2 NA NA NA
3 6,000 74.6 66.5 59.0 53.0 48.3 NA NA NA
7 4,000 74.6 71.1 63.0 56.6 51.5 47.4 NA NA
11 2,000 74.6 74.6 67.1 60.3 54.7 50.2 46.6 NA
15 0 74.6 74.6 70.3 63.1 57.3 52.5 48.6 45.3
-10 15,000 55.3 48.1 NA NA NA NA NA NA
-8 14,000 57.1 49.7 NA NA NA NA NA NA
-4 12,000 61.4 53.4 47.4 NA NA NA NA NA
0 10,000 65.9 57.4 50.9 45.8 NA NA NA NA
5 4 8,000 70.5 61.4 54.5 49.0 NA NA NA NA
8 6,000 74.6 65.7 58.3 52.4 47.7 NA NA NA
12 4,000 74.6 70.9 62.9 56.5 51.4 47.2 NA NA
16 2,000 74.6 74.6 66.4 59.7 54.2 49.8 46.1 NA
20 0 74.6 74.6 69.9 62.8 57.0 52.3 48.4 45.1
-5 15,000 53.8 46.8 NA NA NA NA NA NA
-3 14,000 55.6 48.4 NA NA NA NA NA NA
1 12,000 59.9 52.2 46.3 NA NA NA NA NA
5 10,000 64.6 56.3 49.9 NA NA NA NA NA
10 9 8,000 69.2 60.3 53.4 48.1 NA NA NA NA
13 6,000 74.6 65.0 57.7 51.8 47.2 NA NA NA
17 4,000 74.6 69.5 61.7 55.4 50.4 46.4 NA NA
21 2,000 74.6 73.8 65.5 58.9 53.5 49.2 45.5 NA
25 0 74.6 74.6 69.3 62.3 56.5 51.9 48.0 NA
NOTES: 1. Maximum climb weights are limited by the design MAX TOGW of 74,600 lb for the GIV-SP and
73,200 for the GIV.
2. Increase MAX TOGW by 300 lb for each 10 knots of headwind up to a maximum of 40 knots.
Data not valid for tailwinds.
3. Cowl anti-ice bleeds are assumed ON for temperatures below 10° C; wing anti-ice bleeds
prohibited.

GIV-SP PERFORMANCE REVISION 24 (RE-ISSUE)

Page PA - 56 (GIV-SP AIRPLANES ONLY) Mar 17/10
Quick Reference Handbook
GIV-SP Climb Limited Weights, Flaps 10°, Standard Instrument
Departure, ctd… GIV-OIS-07

GIV TAKEOFF GROSS WEIGHT LIMITED BY REQUIRED SID CLIMB GRADIENT

5000 FT AGL, FLAPS 10, ONE ENGINE OPERATING, ctd…
DELTA AIRPORT AIRPORT
ISA AMBIENT PRESS TAKEOFF GROSS WEIGHT (1000 LB)
TEMP TEMP ALTITUDE REQUIRED SID CLIMB GRADIENT (FT/NM)
(DEG C) (DEG C) (FT) 200 300 400 500 600 700 800 900
0 15,000 52.3 45.5 NA NA NA NA NA NA
2 14,000 53.9 47.0 NA NA NA NA NA NA
6 12,000 58.4 50.8 45.1 NA NA NA NA NA
10 10,000 63.8 55.6 49.3 NA NA NA NA NA
15 14 8,000 68.3 59.5 52.8 47.5 NA NA NA NA
18 6,000 73.1 63.7 56.5 50.8 46.4 NA NA NA
22 4,000 74.6 68.2 60.5 54.4 49.5 45.6 NA NA
26 2,000 74.6 72.8 64.6 58.1 52.8 48.6 NA NA
30 0 74.6 74.6 68.6 61.6 55.9 51.3 47.6 NA
5 15,000 50.6 NA NA NA NA NA NA NA
7 14,000 52.2 45.4 NA NA NA NA NA NA
11 12,000 57.5 50.0 NA NA NA NA NA NA
15 10,000 62.4 54.4 48.3 NA NA NA NA NA
20 19 8,000 66.8 58.3 51.7 46.6 NA NA NA NA
23 6,000 71.7 62.5 55.4 49.9 45.5 NA NA NA
27 4,000 74.6 66.7 59.2 53.2 48.5 NA NA NA
31 2,000 74.6 70.6 62.7 56.3 51.3 47.2 NA NA
35 0 74.6 74.6 66.2 59.6 54.1 49.7 46.1 NA
10 15,000 49.6 NA NA NA NA NA NA NA
12 14,000 51.2 NA NA NA NA NA NA NA
16 12,000 55.9 48.7 NA NA NA NA NA NA
20 10,000 61.0 53.2 47.3 NA NA NA NA NA
25 24 8,000 65.4 57.0 50.6 45.7 NA NA NA NA
28 6,000 70.0 61.0 54.2 48.8 NA NA NA NA
32 4,000 73.9 64.5 57.2 51.6 47.0 NA NA NA
36 2,000 74.6 68.2 60.6 54.5 49.7 45.7 NA NA
40 0 74.6 71.3 63.3 56.9 51.8 47.7 NA NA
15 15,000 47.9 NA NA NA NA NA NA NA
17 14,000 49.4 NA NA NA NA NA NA NA
21 12,000 54.3 47.3 NA NA NA NA NA NA
25 10,000 59.7 52.0 46.3 NA NA NA NA NA
30 29 8,000 63.7 55.6 49.4 NA NA NA NA NA
33 6,000 67.5 58.9 52.3 47.2 NA NA NA NA
37 4,000 71.1 62.1 55.1 49.7 45.4 NA NA NA
41 2,000 74.4 65.0 57.7 52.0 47.5 NA NA NA
45 0 74.6 67.8 60.2 54.2 49.5 45.5 NA NA

NOTES: 1. Maximum climb weights are limited by the design MAX TOGW of 74,600 lb for the GIV-SP and
73,200 for the GIV.
2. Increase MAX TOGW by 300 lb for each 10 knots of headwind up to a maximum of 40 knots.
Data not valid for tailwinds.
3. Cowl anti-ice bleeds are assumed ON for temperatures below 10° C; wing anti-ice bleeds
prohibited.

REVISION 24 (RE-ISSUE) GIV-SP PERFORMANCE

Mar 17/10 (GIV-SP AIRPLANES ONLY) Page PA - 57
 Quick Reference Handbook
GIV-SP Climb Limited Weights, Flaps 10°, Standard Instrument
Departure, ctd… GIV-OIS-07

GIV TAKEOFF GROSS WEIGHT LIMITED BY REQUIRED SID CLIMB GRADIENT

6000 FT AGL, FLAPS 10, ONE ENGINE OPERATING
DELTA AIRPORT AIRPORT
ISA AMBIENT PRESS TAKEOFF GROSS WEIGHT (1000 LB)
TEMP TEMP ALTITUDE REQUIRED SID CLIMB GRADIENT (FT/NM)
(DEG C) (DEG C) (FT) 200 300 400 500 600 700 800 900
< -20 15,000 54.3 48.2 NA NA NA NA NA NA
< -18 14,000 56.3 50.0 NA NA NA NA NA NA
< -14 12,000 60.2 53.6 47.5 NA NA NA NA NA
< -10 10,000 64.3 57.5 51.0 45.9 NA NA NA NA
< -5 < -6 8,000 68.7 61.6 54.6 49.1 NA NA NA NA
< -2 6,000 73.2 65.9 58.5 52.5 47.8 NA NA NA
<2 4,000 74.6 70.5 62.5 56.1 51.0 47.0 NA NA
<6 2,000 74.6 74.0 65.7 59.0 53.6 49.3 45.7 NA
< 10 0 74.6 74.6 69.3 62.3 56.5 51.9 48.0 NA
-15 15,000 54.1 47.8 NA NA NA NA NA NA
-13 14,000 56.2 49.7 NA NA NA NA NA NA
-9 12,000 59.8 53.1 47.1 NA NA NA NA NA
-5 10,000 63.9 57.0 50.6 45.5 NA NA NA NA
0 -1 8,000 68.3 61.2 54.2 48.8 NA NA NA NA
3 6,000 72.9 65.5 58.1 52.2 47.5 NA NA NA
7 4,000 74.6 70.0 62.1 55.7 50.7 46.7 NA NA
11 2,000 74.6 74.4 66.0 59.3 53.9 49.5 45.9 NA
15 0 74.6 74.6 69.1 62.1 56.4 51.7 47.9 NA
-10 15,000 53.6 47.3 NA NA NA NA NA NA
-8 14,000 55.4 49.1 NA NA NA NA NA NA
-4 12,000 58.9 52.3 46.4 NA NA NA NA NA
0 10,000 63.3 56.4 50.0 45.1 NA NA NA NA
5 4 8,000 67.6 60.5 53.6 48.3 NA NA NA NA
8 6,000 72.2 64.7 57.4 51.6 47.0 NA NA NA
12 4,000 74.6 69.8 61.9 55.6 50.6 46.5 NA NA
16 2,000 74.6 73.6 65.3 58.7 53.3 49.0 45.4 NA
20 0 74.6 74.6 68.8 61.8 56.1 51.5 47.7 NA
-5 15,000 52.2 46.2 NA NA NA NA NA NA
-3 14,000 53.9 47.8 NA NA NA NA NA NA
1 12,000 57.2 50.9 45.2 NA NA NA NA NA
5 10,000 62.1 55.4 49.1 NA NA NA NA NA
10 9 8,000 66.3 59.3 52.6 47.4 NA NA NA NA
13 6,000 71.5 64.0 56.8 51.0 46.5 NA NA NA
17 4,000 74.6 68.5 60.7 54.6 49.7 45.7 NA NA
21 2,000 74.6 72.6 64.4 57.9 52.7 48.4 NA NA
25 0 74.6 74.6 68.2 61.3 55.6 51.0 47.3 NA
NOTES: 1. Maximum climb weights are limited by the design MAX TOGW of 74,600 lb for the GIV-SP and
73,200 for the GIV.
2. Increase MAX TOGW by 300 lb for each 10 knots of headwind up to a maximum of 40 knots.
Data not valid for tailwinds.
3. Cowl anti-ice bleeds are assumed ON for temperatures below 10° C; wing anti-ice bleeds
prohibited.

GIV-SP PERFORMANCE REVISION 24 (RE-ISSUE)

Page PA - 58 (GIV-SP AIRPLANES ONLY) Mar 17/10
Quick Reference Handbook
GIV-SP Climb Limited Weights, Flaps 10°, Standard Instrument
Departure, ctd… GIV-OIS-07

GIV TAKEOFF GROSS WEIGHT LIMITED BY REQUIRED SID CLIMB GRADIENT

6000 FT AGL, FLAPS 10, ONE ENGINE OPERATING, ctd…
DELTA AIRPORT AIRPORT
ISA AMBIENT PRESS TAKEOFF GROSS WEIGHT (1000 LB)
TEMP TEMP ALTITUDE REQUIRED SID CLIMB GRADIENT (FT/NM)
(DEG C) (DEG C) (FT) 200 300 400 500 600 700 800 900
0 15,000 50.6 NA NA NA NA NA NA NA
2 14,000 52.2 46.4 NA NA NA NA NA NA
6 12,000 55.3 49.4 NA NA NA NA NA NA
10 10,000 61.4 54.7 48.5 NA NA NA NA NA
15 14 8,000 65.5 58.6 51.9 46.8 NA NA NA NA
18 6,000 70.0 62.8 55.7 50.0 45.7 NA NA NA
22 4,000 74.6 67.1 59.5 53.5 48.8 NA NA NA
26 2,000 74.6 71.6 63.5 57.1 52.0 47.8 NA NA
30 0 74.6 74.6 67.5 60.6 55.0 50.5 46.8 NA
5 15,000 48.9 NA NA NA NA NA NA NA
7 14,000 50.4 NA NA NA NA NA NA NA
11 12,000 54.4 48.6 NA NA NA NA NA NA
15 10,000 60.0 53.5 47.5 NA NA NA NA NA
20 19 8,000 64.1 57.4 50.9 45.9 NA NA NA NA
23 6,000 68.5 61.5 54.5 49.1 NA NA NA NA
27 4,000 72.8 65.6 58.2 52.4 47.8 NA NA NA
31 2,000 74.6 69.4 61.6 55.4 50.5 46.5 NA NA
35 0 74.6 73.4 65.2 58.6 53.3 49.0 45.4 NA
10 15,000 48.1 NA NA NA NA NA NA NA
12 14,000 49.5 NA NA NA NA NA NA NA
16 12,000 52.4 46.9 NA NA NA NA NA NA
20 10,000 58.6 52.3 46.5 NA NA NA NA NA
25 24 8,000 62.7 56.1 49.8 NA NA NA NA NA
28 6,000 66.9 60.1 53.3 48.1 NA NA NA NA
32 4,000 70.2 63.5 56.3 50.7 46.3 NA NA NA
36 2,000 73.8 67.0 59.5 53.6 48.9 NA NA NA
40 0 74.6 70.5 62.6 56.3 51.3 47.2 NA NA
15 15,000 46.3 NA NA NA NA NA NA NA
17 14,000 47.7 NA NA NA NA NA NA NA
21 12,000 50.4 45.4 NA NA NA NA NA NA
25 10,000 57.2 51.2 45.5 NA NA NA NA NA
30 29 8,000 60.9 54.7 48.6 NA NA NA NA NA
33 6,000 64.2 58.0 51.5 46.5 NA NA NA NA
37 4,000 67.4 61.2 54.4 49.1 NA NA NA NA
41 2,000 70.4 64.2 57.0 51.5 47.0 NA NA NA
45 0 73.3 67.1 59.6 53.7 49.0 45.0 NA NA
NOTES: 1. Maximum climb weights are limited by the design MAX TOGW of 74,600 lb for the GIV-SP and
73,200 for the GIV.
2. Increase MAX TOGW by 300 lb for each 10 knots of headwind up to a maximum of 40 knots.
Data not valid for tailwinds.
3. Cowl anti-ice bleeds are assumed ON for temperatures below 10° C; wing anti-ice bleeds
prohibited.

REVISION 24 (RE-ISSUE) GIV-SP PERFORMANCE

Mar 17/10 (GIV-SP AIRPLANES ONLY) Page PA - 59
 Quick Reference Handbook
GIV-SP SID Climb Performance Conversion Table
OM 11-04-40

Departure climb requirements are sometimes expressed in units of

degrees and percent climb gradient as well as Ft/NM which is shown
on the SID climb tables. Provided below is a table which can be
used to convert climb requirements in degrees or percent to Ft/NM.
NOTE: Per FAA Terminal Instrument Procedures (TERPs) criteria, SIDs
specified at U.S. civilian airports will ensure that any limiting obstacles will
be cleared by a margin of climb of 48 Ft/NM (0.8% or 0.5 deg). If a
departure climb is specified at a military airport or non-US airport, it is
important to determine if the specified climb requirement provides at least
the same obstacle clearance margin. If uncertainty exists on this point,
add 48 Ft/NM, 0.8% or 0.5 deg to the stated climb requirement before
entering the SID climb tables to determine a maximum allowable takeoff
weight.

Deg % Ft/NM Deg % Ft/NM

1.0 1.7 106 5.0 8.7 532
1.2 2.1 127 5.2 9.1 553
1.4 2.4 148 5.4 9.5 574
1.6 2.8 170 5.6 9.8 596
1.8 3.1 191 5.8 10.2 617
2.0 3.5 212 6.0 10.5 639
2.2 3.8 233 6.2 10.9 660
2.4 4.2 255 6.4 11.2 682
2.6 4.5 276 6.6 11.6 703
2.8 4.9 297 6.8 11.9 725
3.0 5.2 318 7.0 12.3 746
3.2 5.6 340 7.2 12.6 768
3.4 5.9 361 7.4 13.0 789
3.6 6.3 382 7.6 13.3 811
3.8 6.6 404 7.8 13.7 832
4.0 7.0 425 8.0 14.1 854
4.2 7.3 446 8.2 14.4 876
4.4 7.7 468 8.4 14.8 897
4.6 8.0 489 8.6 15.1 919
4.8 8.4 510 8.8 15.5 941

GIV-SP PERFORMANCE REVISION 24 (RE-ISSUE)

Page PA - 60 (GIV-SP AIRPLANES ONLY) Mar 17/10
Quick Reference Handbook
GIV-SP Twin Engine Cruise Altitudes: Mach 0.77 CCM

For airplanes SN 1214 and subsequent and SN 1000 thru 1213

with ASC 190 incorporated.
GROSS WEIGHT - 1000 LB
74 70 66 62 58 54 50 46 42 38
ALT  ISA -20°C to 0°C +20°C
(FT) CEILING
45000 NM/LB **** **** **** **** .1721 .1857 .1982 .2101 .2218 .2326
TWIND **** **** **** **** 3 0 0 0 0 0
43000 NM/LB **** **** **** .1622 .1732 .1834 .1931 .2029 .2119 .2216
TWIND **** **** **** 0 0 6 12 16 21 22
41000 NM/LB **** .1439 .1534 .1621 .1704 .1781 .1864 .1938 .2019 .2089
TWIND **** 2 0 1 7 19 28 37 43 50
39000 NM/LB .1372 .1447 .1518 .1584 .1652 .1716 .1777 .1845 .1904 .1958
TWIND 0 0 5 11 21 36 51 61 73 83
37000 NM/LB .1365 .1421 .1478 .1532 .1584 .1634 .1691 .1740 .1784 .1821
TWIND 2 8 17 26 41 60 76 92 107 122
35000 NM/LB .1329 .1376 .1420 .1462 .1510 .1552 .1591 .1628 .1664 .1687
TWIND 14 23 36 49 65 87 109 129 148 168
33000 NM/LB .1276 .1311 .1351 .1385 .1418 .1450 .1486 .1510 .1529 ****
TWIND 34 41 61 77 99 126 150 175 202 ****
31000 NM/LB .1219 .1247 .1275 .1309 .1335 .1358 **** **** **** ****
TWIND 57 72 92 108 134 166 **** **** **** ****
29000 NM/LB .1162 .1185 .1208 .1234 .1253 **** **** **** **** ****
TWIND 82 101 123 143 174 **** **** **** **** ****
27000 NM/LB .1092 .1110 .1127 .1142 **** **** **** **** **** ****
TWIND 118 140 166 193 **** **** **** **** **** ****
25000 NM/LB .1030 .1043 **** **** **** **** **** **** **** ****
TWIND 154 179 **** **** **** **** **** **** **** ****

NOTES: 1. Values at optimum altitude are shaded.

2. Service Ceilings (100 FPM rate of climb) for selected temperature
conditions are represented on the table by bold lines.
3. Tailwind Factors (TWIND) are the difference in flight level wind
required to equal ground specific range at optimum altitude.

REVISION 24 (RE-ISSUE) GIV-SP PERFORMANCE

Mar 17/10 (GIV-SP AIRPLANES ONLY) Page PB - 1
 Quick Reference Handbook
GIV-SP Twin Engine Cruise Altitudes: Mach 0.80 CCM

For airplanes SN 1214 and subsequent and SN 1000 thru 1213

with ASC 190 incorporated.
GROSS WEIGHT - 1000 LB
74 70 66 62 58 54 50 46 42 38
ALT  ISA -20°C to 0°C +20°C
(FT) CEILING
45000 NM/LB **** **** **** **** .1694 .1816 .1919 .2023 .2126 .2212
TWIND **** **** **** **** 0 0 0 0 0 0
43000 NM/LB **** **** **** .1592 .1688 .1773 .1858 .1944 .2015 .2093
TWIND **** **** **** 0 2 11 15 19 25 26
41000 NM/LB **** .1415 .1498 .1572 .1644 .1711 .1783 .1841 .1907 .1962
TWIND **** 0 0 6 14 28 35 45 53 58
39000 NM/LB .1344 .1407 .1468 .1526 .1587 .1639 .1687 .1742 .1788 .1831
TWIND 0 3 9 20 31 50 63 74 87 95
37000 NM/LB .1321 .1370 .1422 .1467 .1509 .1549 .1595 .1633 .1668 .1697
TWIND 8 15 24 39 56 79 93 110 126 139
35000 NM/LB .1278 .1321 .1356 .1390 .1429 .1461 .1493 .1522 .1548 .1565
TWIND 24 33 48 67 85 112 132 152 172 191
33000 NM/LB .1220 .1249 .1281 .1309 .1336 .1362 .1388 **** **** ****
TWIND 47 62 79 101 125 155 178 **** **** ****
31000 NM/LB .1158 .1182 .1206 .1231 .1252 **** **** **** **** ****
TWIND 75 92 114 138 166 **** **** **** **** ****
29000 NM/LB .1097 .1116 .1134 .1154 **** **** **** **** **** ****
TWIND 107 127 152 180 **** **** **** **** **** ****
27000 NM/LB .1031 .1047 **** **** **** **** **** **** **** ****
TWIND 145 168 **** **** **** **** **** **** **** ****
25000 NM/LB .0971 **** **** **** **** **** **** **** **** ****
TWIND 185 **** **** **** **** **** **** **** **** ****

NOTES: 1. Values at optimum altitude are shaded.

2. Service Ceilings (100 FPM rate of climb) for selected temperature
conditions are represented on the table by bold lines.
3. Tailwind Factors (TWIND) are the difference in flight level wind
required to equal ground specific range at optimum altitude.

GIV-SP PERFORMANCE REVISION 24 (RE-ISSUE)

Page PB - 2 (GIV-SP AIRPLANES ONLY) Mar 17/10
Quick Reference Handbook
GIV-SP Twin Engine Cruise Altitudes: Mach 0.83 CCM

For airplanes SN 1214 and subsequent and SN 1000 thru 1213

with ASC 190 incorporated.
GROSS WEIGHT - 1000 LB
74 70 66 62 58 54 50 46 42 38
ALT  ISA -20°C to 0°C +15°C
(FT) CEILING
45000 NM/LB **** **** **** **** **** **** .1708 .1820 .1911 .1992
TWIND **** **** **** **** **** **** 0 0 0 0
43000 NM/LB **** **** **** **** .1474 .1581 .1674 .1746 .1814 .1871
TWIND **** **** **** **** 0 0 10 20 25 31
41000 NM/LB **** **** **** .1390 .1471 .1546 .1602 .1657 .1705 .1754
TWIND **** **** **** 0 1 11 31 47 57 65
39000 NM/LB **** .1234 .1307 .1370 .1424 .1472 .1518 .1557 .1599 .1637
TWIND **** 0 0 7 17 35 60 80 93 103
37000 NM/LB .1173 .1227 .1273 .1318 .1356 .1395 .1425 .1459 .1492 .1519
TWIND 0 3 13 26 41 63 94 118 134 148
35000 NM/LB .1149 .1185 .1218 .1250 .1277 .1305 .1334 .1360 .1376 .1393
TWIND 10 20 35 54 73 101 134 162 186 206
33000 NM/LB .1104 .1132 .1152 .1178 .1202 .1228 .1240 **** **** ****
TWIND 30 43 65 87 109 139 182 **** **** ****
31000 NM/LB .1051 .1075 .1098 .1108 .1129 .1147 **** **** **** ****
TWIND 57 72 93 124 149 184 **** **** **** ****
29000 NM/LB .0987 .1004 .1022 .1031 .1045 **** **** **** **** ****
TWIND 93 113 132 171 201 **** **** **** **** ****
27000 NM/LB .0942 .0957 .0973 **** **** **** **** **** **** ****
TWIND 122 143 170 **** **** **** **** **** **** ****
25000 NM/LB **** **** **** **** **** **** **** **** **** ****
TWIND **** **** **** **** **** **** **** **** **** ****

NOTES: 1. Values at optimum altitude are shaded.

2. Service Ceilings (100 FPM rate of climb) for selected temperature
conditions are represented on the table by bold lines.
3. Tailwind Factors (TWIND) are the difference in flight level wind
required to equal ground specific range at optimum altitude.

REVISION 28 GIV-SP PERFORMANCE

May 25/16 (GIV-SP AIRPLANES ONLY) Page PB - 3
 Quick Reference Handbook
GIV-SP Maximum Range Cruise - ISA CCM

For airplanes SN 1214 and subsequent and SN 1000 thru 1213

with ASC 190 incorporated.
ALT OAT GROSS WEIGHT - 1000 LB
(FT) (°C) 76 74 72 70 68 66 64 62 60 58
45000 MT **** **** **** **** **** **** **** **** **** 0.778
-56.5 KCAS **** **** **** **** **** **** **** **** **** 209
FF **** **** **** **** **** **** **** **** **** 2590
NAM/LB **** **** **** **** **** **** **** **** **** .1727
43000 MT **** **** **** **** **** **** 0.779 0.774 0.775 0.771
-56.5 KCAS **** **** **** **** **** **** 219 218 218 217
FF **** **** **** **** **** **** 2850 2730 2650 2550
NAM/LB **** **** **** **** **** **** .1570 .1625 .1680 .1731
41000 MT **** **** **** 0.781 0.778 0.775 0.771 0.766 0.761 0.757
-56.5 KCAS **** **** **** 230 229 228 227 225 224 222
FF **** **** **** 3110 3010 2900 2800 2710 2620 2540
NAM/LB **** **** **** .1441 .1484 .1535 .1577 .1622 .1665 .1708
39000 MT 0.776 0.774 0.771 0.767 0.764 0.761 0.757 0.753 0.748 0.744
-56.5 KCAS 239 239 238 237 236 234 233 232 230 229
FF 3340 3240 3150 3040 2960 2870 2790 2710 2640 2570
NAM/LB .1333 .1372 .1407 .1448 .1483 .1520 .1555 .1591 .1627 .1662
37000 MT 0.768 0.763 0.760 0.758 0.752 0.752 0.748 0.743 0.737 0.733
-56.5 KCAS 248 246 245 245 242 243 241 239 237 236
FF 3290 3200 3120 3060 2960 2910 2830 2760 2680 2620
NAM/LB .1337 .1366 .1396 .1425 .1455 .1484 .1514 .1545 .1577 .1610
35000 MT 0.754 0.750 0.747 0.744 0.740 0.736 0.730 0.727 0.721 0.716
-54.3 KCAS 255 253 252 251 250 248 246 245 243 241
FF 3310 3240 3170 3100 3030 2950 2870 2810 2740 2670
NAM/LB .1311 .1336 .1360 .1385 .1411 .1438 .1465 .1492 .1521 .1548
33000 MT 0.737 0.733 0.729 0.724 0.719 0.713 0.707 0.701 0.693 0.684
-50.4 KCAS 260 258 257 255 253 251 249 246 243 240
FF 3370 3300 3220 3150 3080 3000 2920 2850 2770 2680
NAM/LB .1273 .1295 .1317 .1340 .1361 .1384 .1408 .1432 .1458 .1483
31000 MT 0.716 0.710 0.704 0.697 0.690 0.684 0.676 0.668 0.658 0.649
-46.4 KCAS 264 261 259 256 253 251 248 244 241 237
FF 3410 3320 3240 3160 3080 3000 2930 2850 2760 2678
NAM/LB .1234 .1254 .1274 .1294 .1315 .1336 .1357 .1376 .1399 .1422
29000 MT 0.706 0.697 0.687 0.678 0.668 0.657 0.647 0.637 0.625 0.613
-42.5 KCAS 271 268 263 260 256 251 247 243 238 233
FF 3520 3430 3330 3240 3140 3040 2960 2870 2770 2680
NAM/LB .1187 .1205 .1223 .1241 .1259 .1279 .1295 .1314 .1335 .1355
27000 MT 0.671 0.665 0.658 0.651 0.643 0.634 0.625 0.615 0.605 0.594
-38.5 KCAS 268 265 263 260 256 252 249 244 240 236
FF 3500 3420 3340 3260 3170 3090 3000 2910 2820 2730
NAM/LB .1144 .1160 .1176 .1193 .1209 .1227 .1244 .1262 .1281 .1300
25000 MT 0.648 0.641 0.634 0.626 0.617 0.608 0.599 0.590 0.580 0.570
-34.5 KCAS 270 267 263 260 256 252 248 244 240 236
FF 3540 3460 3380 3290 3200 3110 3030 2940 2850 2760
NAM/LB .1101 .1116 .1130 .1145 .1160 .1176 .1192 .1209 .1226 .1243
20000 MT 0.585 0.578 0.570 0.562 0.554 0.546 0.539 0.530 0.522 0.514
-24.6 KCAS 268 265 261 257 254 250 246 242 238 234
FF 3640 3560 3470 3380 3290 3200 3120 3030 2940 2860
NAM/LB .0986 .0998 .1010 .1022 .1035 .1048 .1062 .1076 .1090 .1105

NOTE: See the GIV Operating Manual for procedures to account

for temperature deviation from ISA day and/or wind conditions.

GIV-SP PERFORMANCE REVISION 28

Page PB - 4 (GIV-SP AIRPLANES ONLY) May 25/16
Quick Reference Handbook
GIV-SP Maximum Range Cruise - ISA, ctd… CCM

ALT OAT GROSS WEIGHT - 1000 LB

(FT) (°C) 56 54 52 50 48 46 44 42 40 38
45000 MT 0.776 0.774 0.769 0.767 0.762 0.757 0.750 0.744 0.734 0.725
-56.5 KCAS 208 208 206 206 204 203 200 199 196 193
FF 2490 2390 2300 2220 2140 2060 1980 1910 1830 1750
NAM/LB .1791 .1858 .1921 .1984 .2049 .2110 .2173 .2237 .2304 .2375
43000 MT 0.767 0.763 0.758 0.754 0.749 0.742 0.735 0.728 0.719 0.710
-56.5 KCAS 216 214 213 211 210 208 206 203 201 198
FF 2470 2390 2300 2230 2150 2080 2010 1930 1860 1790
NAM/LB .1787 .1837 .1891 .1942 .1994 .2048 .2104 .2163 .2224 .2282
41000 MT 0.754 0.749 0.744 0.739 0.733 0.727 0.720 0.712 0.702 0.693
-56.5 KCAS 222 220 218 217 215 213 211 208 205 202
FF 2470 2400 2330 2250 2180 2110 2040 1970 1890 1820
NAM/LB .1751 .1794 .1838 .1883 .1930 .1980 .2030 .2079 .2131 .2187
39000 MT 0.739 0.733 0.726 0.720 0.713 0.706 0.697 0.688 0.676 0.665
-56.5 KCAS 227 225 223 221 218 216 213 210 206 202
FF 2500 2420 2340 2270 2200 2130 2060 1980 1900 1830
NAM/LB .1700 .1738 .1779 .1820 .1860 .1902 .1946 .1992 .2039 .2086
37000 MT 0.727 0.721 0.713 0.705 0.696 0.686 0.674 0.662 0.646 0.630
-56.5 KCAS 234 232 229 226 223 219 215 211 206 200
FF 2540 2470 2390 2310 2240 2160 2080 2000 1910 1820
NAM/LB .1644 .1679 .1711 .1747 .1784 .1823 .1861 .1901 .1942 .1985
35000 MT 0.709 0.701 0.690 0.679 0.663 0.648 0.643 0.638 0.596 0.555
-54.3 KCAS 238 235 231 227 222 216 214 212 198 183
FF 2590 2510 2430 2350 2250 2150 2100 2050 1860 1700
NAM/LB .1578 .1608 .1639 .1671 .1704 .1737 .1771 .1801 .1848 .1888
33000 MT 0.675 0.664 0.650 0.635 0.617 0.600 0.583 0.566 0.550 0.535
-50.4 KCAS 236 232 227 221 215 208 202 196 190 185
FF 2600 2510 2420 2330 2220 2120 2020 1920 1821 1740
NAM/LB .1510 .1538 .1566 .1590 .1621 .1652 .1685 .1720 .1756 .1793
31000 MT 0.648 0.628 0.615 0.603 0.589 0.575 0.560 0.545 0.529 0.513
-46.4 KCAS 237 229 224 219 214 209 203 197 191 185
FF 2630 2510 2420 2330 2230 2140 2050 1960 1860 1770
NAM/LB .1446 .1470 .1496 .1522 .1550 .1578 .1608 .1639 .1672 .1705
29000 MT 0.600 0.586 0.572 0.558 0.545 0.532 0.519 0.506 0.496 0.485
-42.5 KCAS 228 222 217 211 206 201 196 191 187 182
FF 2580 2480 2380 2280 2190 2100 2010 1920 1850 1770
NAM/LB .1379 .1400 .1426 .1451 .1477 .1503 .1531 .1560 .1590 .1622
27000 MT 0.584 0.573 0.561 0.550 0.540 0.529 0.517 0.506 0.494 0.483
-38.5 KCAS 231 227 222 217 213 208 204 199 194 190
FF 2640 2550 2460 2370 2290 2200 2120 2040 1950 1870
NAM/LB .1320 .1341 .1363 .1385 .1408 .1432 .1457 .1483 .1510 .1538
25000 MT 0.560 0.550 0.539 0.529 0.519 0.509 0.499 0.488 0.478 0.467
-34.5 KCAS 231 227 222 218 213 209 205 200 196 191
FF 2670 2580 2500 2410 2330 2240 2160 2080 2000 1920
NAM/LB .1262 .1281 .1301 .1322 .1344 .1366 .1389 .1413 .1437 .1463
20000 MT 0.506 0.498 0.490 0.482 0.474 0.466 0.458 0.451 0.444 0.438
-24.6 KCAS 231 227 223 219 216 212 208 205 202 199
FF 2770 2690 2610 2530 2450 2370 2300 2230 2160 2100
NAM/LB .1121 .1137 .1153 .1170 .1188 .1206 .1224 .1242 .1261 .1279

NOTE: See the GIV Operating Manual for procedures to account

for temperature deviation from ISA day and/or wind conditions.

REVISION 28 GIV-SP PERFORMANCE

May 25/16 (GIV-SP AIRPLANES ONLY) Page PB - 5
 Quick Reference Handbook
GIV-SP Long Range Cruise - ISA CCM

For airplanes SN 1214 and subsequent and SN 1000 thru 1213

with ASC 190 incorporated.
OAT GROSS WEIGHT - 1000 LB
ALT
(°C) 76 74 72 70 68 66 64 62 60 58
45000 MT **** **** **** **** **** **** **** **** **** 0.795
-56.5 KCAS **** **** **** **** **** **** **** **** **** 214
FF **** **** **** **** **** **** **** **** **** 2670
NAM/LB **** **** **** **** **** **** **** **** **** 0.1707
43000 MT **** **** **** **** **** **** 0.797 0.792 0.79 0.787
-56.5 KCAS **** **** **** **** **** **** 225 223 223 222
FF **** **** **** **** **** **** 2950 2820 2730 2630
NAM/LB **** **** **** **** **** **** 0.1551 0.1611 0.1665 0.172
41000 MT **** **** **** 0.794 0.793 0.791 0.79 0.787 0.784 0.781
-56.5 KCAS **** **** **** 235 234 234 233 232 231 230
FF **** **** **** 3190 3090 2990 2900 2807 2730 2650
NAM/LB **** **** **** 0.1428 0.1471 0.1521 0.1562 0.1606 0.1648 0.1691
39000 MT 0.792 0.791 0.789 0.788 0.786 0.784 0.781 0.779 0.778 0.775
-56.5 KCAS 245 245 244 244 243 242 241 241 240 239
FF 3440 3330 3240 3150 3070 2990 2910 2840 2770 2700
NAM/LB 0.1322 0.1363 0.1398 0.1434 0.1469 0.1505 0.154 0.1575 0.1611 0.1646
37000 MT 0.788 0.785 0.783 0.782 0.78 0.778 0.775 0.772 0.769 0.766
-56.5 KCAS 255 254 253 253 252 252 251 250 248 247
FF 3420 3330 3250 3190 3110 3040 2970 2900 2830 2770
NAM/LB 0.1322 0.1352 0.1382 0.1409 0.144 0.147 0.1499 0.1529 0.156 0.159
35000 MT 0.779 0.776 0.775 0.773 0.771 0.767 0.763 0.761 0.757 0.753
-54.3 KCAS 264 263 263 262 261 260 258 257 256 255
FF 3460 3380 3320 3250 3180 3110 3030 2980 2900 2830
NAM/LB 0.1298 0.1322 0.1347 0.1371 0.1396 0.1423 0.145 0.1475 0.1504 0.1532
30000 MT 0.749 0.745 0.741 0.737 0.731 0.725 0.717 0.710 0.703 0.695
-44.4 KCAS 283 281 280 278 276 273 270 267 264 261
FF 3685 3615 3540 3470 3390 3310 3216 3135 3055 2965
NAM/LB 0.1199 0.1217 0.1235 0.1253 0.1273 0.1293 0.1315 0.1337 0.1358 0.1379
25000 MT 0.7 0.695 0.688 0.681 0.673 0.665 0.656 0.647 0.638 0.628
-34.5 KCAS 293 290 287 284 280 277 273 269 265 261
FF 3870 3790 3700 3620 3530 3440 3350 3260 3160 3070
NAM/LB 0.109 0.1105 0.1119 0.1134 0.1149 0.1164 0.118 0.1197 0.1213 0.1231
20000 MT 0.641 0.632 0.624 0.615 0.607 0.598 0.59 0.581 0.572 0.563
-24.6 KCAS 295 291 287 283 278 274 270 266 262 258
FF 4030 3930 3830 3740 3640 3540 3450 3350 3260 3160
NAM/LB 0.0976 0.0988 0.1 0.1012 0.1025 0.1038 0.1051 0.1065 0.1079 0.1094
15000 MT 0.575 0.567 0.56 0.552 0.545 0.538 0.53 0.524 0.517 0.51
-14.7 KCAS 291 287 283 279 275 271 267 264 260 257
FF 4133 4031 3931 3831 3735 3641 3550 3463 3375 3290
NAM/LB 0.0872 0.0882 0.0892 0.0903 0.0914 0.0925 0.0936 0.0947 0.0959 0.0971
10000 MT 0.452 0.452 0.452 0.452 0.452 0.452 0.452 0.452 0.452 0.452
-4.8 KCAS 250 250 250 250 250 250 250 250 250 250
FF 3675 3634 3593 3553 3514 3480 3443 3410 3379 3347
NAM/LB 0.0785 0.0794 0.0803 0.0812 0.0821 0.0829 0.0838 0.0846 0.0854 0.0862
5000 MT 0.413 0.413 0.413 0.413 0.413 0.413 0.413 0.413 0.413 0.413
5.1 KCAS 250 250 250 250 250 250 250 250 250 250
FF 3868 3830 3792 3755 3723 3688 3652 3623 3594 3565
NAM/LB 0.0694 0.0701 0.0708 0.0715 0.0721 0.0728 0.0735 0.0741 0.0747 0.0753
0 MT 0.378 0.378 0.378 0.378 0.378 0.378 0.378 0.378 0.378 0.378
15 KCAS 250 250 250 250 250 250 250 250 250 250
FF 4119 4079 4046 4007 3975 3944 3913 3877 3847 3823
NAM/LB 0.0607 0.0613 0.0618 0.0624 0.0629 0.0634 0.0639 0.0645 0.065 0.0654

NOTE: See the GIV Operating Manual for procedures to account

for temperature deviation from ISA day and/or wind conditions.
NOTE: Airspeed restricted to 250 KCAS for altitudes of 10,000 ft
and below.

GIV-SP PERFORMANCE REVISION 28

Page PB - 6 (GIV-SP AIRPLANES ONLY) May 25/16
Quick Reference Handbook
GIV-SP Long Range Cruise - ISA, ctd… CCM

OAT GROSS WEIGHT - 1000 LB

ALT
(°C) 56 54 52 50 48 46 44 42 40 38
45000 MT 0.793 0.791 0.788 0.785 0.782 0.778 0.774 0.77 0.764 0.757
-56.5 KCAS 213 213 212 211 210 209 208 206 205 203
FF 2560 2460 2380 2290 2210 2140 2070 2010 1930 1850
NAM/LB 0.177 0.1845 0.1904 0.1964 0.2029 0.209 0.2145 0.22 0.2275 0.2351
43000 MT 0.785 0.783 0.78 0.776 0.773 0.77 0.765 0.761 0.755 0.75
-56.5 KCAS 221 221 220 218 217 217 215 214 212 210
FF 2550 2470 2390 2320 2250 2180 2110 2050 1970 1900
NAM/LB 0.177 0.1819 0.1872 0.1922 0.1976 0.203 0.2083 0.2135 0.2201 0.2259
41000 MT 0.779 0.777 0.773 0.769 0.765 0.761 0.755 0.749 0.742 0.734
-56.5 KCAS 230 229 228 227 225 224 222 220 218 215
FF 2590 2520 2440 2370 2300 2240 2160 2090 2020 1940
NAM/LB 0.1731 0.177 0.1817 0.1864 0.191 0.1955 0.2007 0.2058 0.2109 0.2165
39000 MT 0.771 0.767 0.763 0.759 0.754 0.748 0.741 0.734 0.726 0.716
-56.5 KCAS 238 236 235 234 232 230 228 225 223 219
FF 2630 2550 2490 2430 2350 2280 2210 2130 2060 1990
NAM/LB 0.1683 0.1721 0.176 0.1798 0.1841 0.1883 0.1927 0.1972 0.2018 0.2065
37000 MT 0.763 0.759 0.752 0.746 0.74 0.734 0.725 0.716 0.705 0.691
-56.5 KCAS 246 245 242 240 238 236 233 230 226 221
FF 2700 2640 2540 2470 2400 2340 2260 2180 2100 2020
NAM/LB 0.162 0.165 0.1694 0.173 0.1767 0.1803 0.1843 0.1882 0.1923 0.1965
35000 MT 0.748 0.743 0.737 0.73 0.723 0.714 0.704 0.687 0.665 0.638
-54.3 KCAS 253 251 248 246 243 240 236 230 222 213
FF 2760 2690 2620 2540 2470 2390 2310 2210 2090 1970
NAM/LB 0.1562 0.1592 0.1623 0.1655 0.1687 0.172 0.1754 0.1791 0.1829 0.1869
30000 MT 0.685 0.675 0.663 0.651 0.637 0.625 0.608 0.593 0.576 0.560
-44.4 KCAS 257 253 248 243 238 233 226 220 214 207
FF 2880 2795 2700 2605 2505 2415 2310 2210 2105 2000
NAM/LB 0.1401 0.1424 0.1448 0.1472 0.1498 0.1524 0.1553 0.1583 0.1614 0.1647
25000 MT 0.618 0.607 0.595 0.584 0.573 0.562 0.551 0.539 0.528 0.517
-34.5 KCAS 256 251 246 241 237 232 227 222 217 212
FF 2980 2880 2780 2690 2590 2500 2410 2320 2230 2150
NAM/LB 0.1249 0.1268 0.1288 0.1309 0.133 0.1352 0.1375 0.1398 0.1423 0.1448
20000 MT 0.554 0.546 0.537 0.528 0.519 0.511 0.503 0.494 0.487 0.48
-24.6 KCAS 254 249 245 241 237 233 229 225 222 218
FF 3070 2980 2890 2800 2710 2630 2550 2470 2400 2330
NAM/LB 0.111 0.1126 0.1142 0.1159 0.1176 0.1194 0.1212 0.123 0.1248 0.1266
15000 MT 0.503 0.497 0.491 0.484 0.478 0.472 0.467 0.461 0.455 0.45
-14.7 KCAS 253 250 247 244 241 237 235 232 229 226
FF 3207 3128 3051 2974 2901 2829 2763 2696 2634 2575
NAM/LB 0.0983 0.0995 0.1007 0.102 0.1033 0.1046 0.1058 0.1071 0.1083 0.1095
10000 MT 0.452 0.452 0.452 0.452 0.452 0.448 0.443 0.438 0.433 0.428
-4.8 KCAS 250 250 250 250 250 247 245 242 239 237
FF 3316 3290 3260 3235 3213 3150 3089 3026 2964 2907
NAM/LB 0.087 0.0877 0.0885 0.0892 0.0898 0.0907 0.0915 0.0924 0.0933 0.0941
5000 MT 0.413 0.413 0.413 0.413 0.413 0.413 0.413 0.413 0.411 0.406
5.1 KCAS 250 250 250 250 250 250 250 250 249 246
FF 3537 3509 3482 3459 3433 3411 3390 3373 3328 3266
NAM/LB 0.0759 0.0765 0.0771 0.0776 0.0782 0.0787 0.0792 0.0796 0.0802 0.0808
0 MT 0.378 0.378 0.378 0.378 0.378 0.378 0.378 0.378 0.378 0.378
15 KCAS 250 250 250 250 250 250 250 250 250 250
FF 3794 3766 3743 3715 3693 3672 3650 3634 3613 3598
NAM/LB 0.0659 0.0664 0.0668 0.0673 0.0677 0.0681 0.0685 0.0688 0.0692 0.0695

NOTE: See the GIV Operating Manual for procedures to account

for temperature deviation from ISA day and/or wind conditions.
NOTE: Airspeed restricted to 250 KCAS for altitudes of 10,000 ft
and below.

REVISION 28 GIV-SP PERFORMANCE

May 25/16 (GIV-SP AIRPLANES ONLY) Page PB - 7
 Quick Reference Handbook
GIV-SP Twin Engine Cruise: Mach 0.77 - ISA CCM

For airplanes SN 1214 and subsequent and SN 1000 thru 1213

with ASC 190 incorporated.
ALT OAT GROSS WEIGHT - 1000 LB
(FT) (°C) 76 74 72 70 68 66 64 62 60 58
45000 MT **** **** **** **** **** **** **** **** **** 0.770
441.6 KCAS **** **** **** **** **** **** **** **** **** 206
FF **** **** **** **** **** **** **** **** **** 2570
-56.5 NAM/LB **** **** **** **** **** **** **** **** **** .1721
43000 MT **** **** **** **** **** **** 0.770 0.770 0.770 0.770
441.6 KCAS **** **** **** **** **** **** 216 216 216 216
FF **** **** **** **** **** **** 2810 2720 2630 2550
-56.5 NAM/LB **** **** **** **** **** **** .1569 .1622 .1679 .1732
41000 MT **** **** **** 0.770 0.770 0.770 0.770 0.770 0.770 0.770
441.6 KCAS **** **** **** 227 227 227 227 227 227 227
FF **** **** **** 3070 2970 2880 2800 2720 2660 2590
-56.5 NAM/LB **** **** **** .1439 .1486 .1534 .1577 .1621 .1663 .1704
39000 MT 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770
441.6 KCAS 238 238 238 238 238 238 238 238 238 238
FF 3310 3220 3140 3050 2980 2910 2850 2790 2730 2670
-56.5 NAM/LB .1333 .1372 .1404 .1447 .1483 .1518 .1551 .1584 .1620 .1652
37000 MT 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770
441.6 KCAS 249 249 249 249 249 249 249 249 249 249
FF 3310 3240 3170 3110 3050 2990 2940 2880 2830 2790
-56.5 NAM/LB .1336 .1365 .1393 .1421 .1448 .1478 .1505 .1532 .1558 .1584
35000 MT 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770
443.8 KCAS 261 261 261 261 261 261 261 261 261 261
FF 3400 3340 3280 3230 3170 3130 3080 3040 2990 2940
-54.3 NAM/LB .1307 .1329 .1354 .1376 .1398 .1420 .1442 .1462 .1483 .1510
33000 MT 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770
447.8 KCAS 273 273 273 273 273 273 273 273 273 273
FF 3560 3510 3460 3420 3360 3310 3270 3230 3200 3160
-50.4 NAM/LB .1258 .1276 .1294 .1311 .1334 .1351 .1368 .1385 .1401 .1418
31000 MT 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770
451.8 KCAS 285 285 285 285 285 285 285 285 285 285
FF 3750 3710 3660 3620 3580 3540 3500 3450 3420 3390
-46.4 NAM/LB .1204 .1219 .1233 .1247 .1261 .1275 .1289 .1309 .1322 .1335
29000 MT 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770
455.7 KCAS 298 298 298 298 298 298 298 298 298 298
FF 3960 3920 3880 3850 3810 3770 3720 3690 3660 3640
-42.5 NAM/LB .1150 .1162 .1173 .1185 .1196 .1208 .1224 .1234 .1244 .1253
27000 MT 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770
459.6 KCAS 311 311 311 311 311 311 311 311 311 311
FF 4250 4210 4170 4140 4110 4080 4050 4020 4000 3980
-38.5 NAM/LB .1082 .1092 .1101 .1110 .1119 .1127 .1135 .1142 .1149 .1156
25000 MT 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770
463.5 KCAS 324 324 324 324 324 324 324 324 324 324
FF 4530 4500 4470 4440 4410 4390 4370 4340 4320 4310
-34.5 NAM/LB .1022 .1030 .1037 .1043 .1050 .1056 .1062 .1067 .1072 .1077
20000 MT **** **** **** **** **** **** **** **** **** ****
473.0 KCAS **** **** **** **** **** **** **** **** **** ****
FF **** **** **** **** **** **** **** **** **** ****
-24.6 NAM/LB **** **** **** **** **** **** **** **** **** ****

NOTE: See the GIV Operating Manual for procedures to account

for temperature deviation from ISA day and/or wind conditions.

GIV-SP PERFORMANCE REVISION 28

Page PB - 8 (GIV-SP AIRPLANES ONLY) May 25/16
Quick Reference Handbook
GIV-SP Twin Engine Cruise - Mach 0.77- ISA, ctd… CCM

ALT OAT GROSS WEIGHT - 1000 LB

(FT) (°C) 56 54 52 50 48 46 44 42 40 38
45000 MT 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770
441.6 KCAS 206 206 206 206 206 206 206 206 206 206
FF 2470 2380 2300 2230 2160 2100 2050 1990 1940 1900
-56.5 NAM/LB .1789 .1857 .1922 .1982 .2045 .2101 .2155 .2218 .2273 .2326
43000 MT 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770
441.6 KCAS 216 216 216 216 216 216 216 216 216 216
FF 2470 2410 2340 2290 2230 2180 2130 2080 2040 1990
-56.5 NAM/LB .1785 .1834 .1885 .1931 .1982 .2029 .2075 .2119 .2163 .2216
41000 MT 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770
441.6 KCAS 227 227 227 227 227 227 227 227 227 227
FF 2530 2480 2420 2370 2320 2280 2240 2190 2150 2110
-56.5 NAM/LB .1744 .1781 .1825 .1864 .1901 .1938 .1974 .2019 .2055 .2089
39000 MT 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770
441.6 KCAS 238 238 238 238 238 238 238 238 238 238
FF 2620 2570 2530 2480 2430 2390 2360 2320 2290 2260
-56.5 NAM/LB .1685 .1716 .1747 .1777 .1815 .1845 .1875 .1904 .1932 .1958
37000 MT 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770
441.6 KCAS 249 249 249 249 249 249 249 249 249 249
FF 2740 2700 2650 2610 2570 2540 2510 2480 2450 2430
-56.5 NAM/LB .1609 .1634 .1666 .1691 .1716 .1740 .1763 .1784 .1804 .1821
35000 MT 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770
443.8 KCAS 261 261 261 261 261 261 261 261 261 261
FF 2900 2860 2820 2790 2760 2730 2700 2670 2650 2630
-54.3 NAM/LB .1531 .1552 .1572 .1591 .1610 .1628 .1644 .1664 .1676 .1687
33000 MT 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770
447.8 KCAS 273 273 273 273 273 273 273 273 273 273
FF 3120 3090 3060 3010 2990 2970 2950 2930 2910 2900
-50.4 NAM/LB .1434 .1450 .1465 .1486 .1498 .1510 .1520 .1529 .1538 .1545
31000 MT 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770
451.8 KCAS 285 285 285 285 285 285 285 285 285 285
FF 3350 3330 3300 3280 3260 3240 3220 3210 3190 3180
-46.4 NAM/LB .1347 .1358 .1369 .1378 .1387 .1394 .1402 .1408 .1415 .1420
29000 MT 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770
455.7 KCAS 298 298 298 298 298 298 298 298 298 298
FF 3610 3590 3570 3560 3540 3520 3510 3500 3490 3480
-42.5 NAM/LB .1261 .1269 .1276 .1282 .1288 .1293 .1298 .1303 .1307 .1311
27000 MT 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770
459.6 KCAS 311 311 311 311 311 311 311 311 311 311
FF 3960 3940 3920 3900 3890 3870 3860 3840 3830 3820
-38.5 NAM/LB .1162 .1167 .1172 .1177 .1182 .1187 .1191 .1195 .1200 .1204
25000 MT 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770
463.5 KCAS 324 324 324 324 324 324 324 324 324 324
FF 4290 4270 4250 4240 4220 4210 4190 4170 4160 4140
-34.5 NAM/LB .1081 .1086 .1090 .1094 .1098 .1102 .1106 .1110 .1114 .1118
20000 MT **** **** **** **** **** **** **** **** **** ****
473.0 KCAS **** **** **** **** **** **** **** **** **** ****
FF **** **** **** **** **** **** **** **** **** ****
-24.6 NAM/LB **** **** **** **** **** **** **** **** **** ****

NOTE: See the GIV Operating Manual for procedures to account

for temperature deviation from ISA day and/or wind conditions.

REVISION 28 GIV-SP PERFORMANCE

May 25/16 (GIV-SP AIRPLANES ONLY) Page PB - 9
 Quick Reference Handbook
GIV-SP Twin Engine Cruise: Mach 0.80 - ISA CCM

For airplanes SN 1214 and subsequent and SN 1000 thru 1213

with ASC 190 incorporated.
ALT OAT GROSS WEIGHT - 1000 LB
(FT) (°C) 76 74 72 70 68 66 64 62 60 58
45000 MT **** **** **** **** **** **** **** **** **** 0.800
458.9 KCAS **** **** **** **** **** **** **** **** **** 216
FF **** **** **** **** **** **** **** **** **** 2710
-56.5 NAM/LB **** **** **** **** **** **** **** **** **** .1694
43000 MT **** **** **** **** **** **** 0.800 0.800 0.800 0.800
458.9 KCAS **** **** **** **** **** **** 226 226 226 226
FF **** **** **** **** **** **** 2970 2880 2790 2720
-56.5 NAM/LB **** **** **** **** **** **** .1543 .1592 .1642 .1688
41000 MT **** **** **** 0.800 0.800 0.800 0.800 0.800 0.800 0.800
458.9 KCAS **** **** **** 237 237 237 237 237 237 237
FF **** **** **** 3240 3160 3060 2980 2920 2850 2790
-56.5 NAM/LB **** **** **** .1415 .1451 .1498 .1537 .1572 .1608 .1644
39000 MT 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800
458.9 KCAS 248 248 248 248 248 248 248 248 248 248
FF 3520 3410 3340 3260 3190 3130 3070 3010 2940 2890
-56.5 NAM/LB .1305 .1344 .1375 .1407 .1436 .1468 .1497 .1526 .1559 .1587
37000 MT 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800
458.9 KCAS 260 260 260 260 260 260 260 260 260 260
FF 3540 3470 3410 3350 3290 3230 3170 3130 3080 3040
-56.5 NAM/LB .1296 .1321 .1346 .1370 .1394 .1422 .1445 .1467 .1489 .1509
35000 MT 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800
461.1 KCAS 272 272 272 272 272 272 272 272 272 272
FF 3660 3610 3540 3490 3440 3400 3360 3320 3280 3230
-54.3 NAM/LB .1258 .1278 .1301 .1321 .1339 .1356 .1374 .1390 .1407 .1429
33000 MT 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800
465.3 KCAS 284 284 284 284 284 284 284 284 284 284
FF 3860 3810 3770 3730 3670 3630 3590 3550 3520 3480
-50.4 NAM/LB .1204 .1220 .1234 .1249 .1268 .1281 .1295 .1309 .1323 .1336
31000 MT 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800
469.4 KCAS 297 297 297 297 297 297 297 297 297 297
FF 4100 4050 4010 3970 3930 3890 3850 3810 3780 3750
-46.4 NAM/LB .1146 .1158 .1170 .1182 .1194 .1206 .1218 .1231 .1242 .1252
29000 MT 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800
473.5 KCAS 311 311 311 311 311 311 311 311 311 311
FF 4350 4320 4280 4240 4210 4170 4130 4100 4080 4050
-42.5 NAM/LB .1087 .1097 .1106 .1116 .1125 .1134 .1146 .1154 .1162 .1169
27000 MT 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800
477.5 KCAS 324 324 324 324 324 324 324 324 324 324
FF 4670 4630 4600 4560 4530 4500 4470 4440 4420 4400
-38.5 NAM/LB .1023 .1031 .1039 .1047 .1054 .1062 .1068 .1075 .1081 .1086
25000 MT 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800
481.6 KCAS 338 338 338 338 338 338 338 338 338 338
FF 4990 4960 4930 4900 4860 4830 4810 4780 4760 4740
-34.5 NAM/LB .0965 .0971 .0977 .0984 .0990 .0997 .1002 .1006 .1011 .1015
20000 MT **** **** **** **** **** **** **** **** **** ****
491.5 KCAS **** **** **** **** **** **** **** **** **** ****
FF **** **** **** **** **** **** **** **** **** ****
-24.6 NAM/LB **** **** **** **** **** **** **** **** **** ****

NOTE: See the GIV Operating Manual for procedures to account

for temperature deviation from ISA day and/or wind conditions.

GIV-SP PERFORMANCE REVISION 28

Page PB - 10 (GIV-SP AIRPLANES ONLY) May 25/16
Quick Reference Handbook
GIV-SP Twin Engine Cruise - Mach 0.80 - ISA, ctd… CCM

ALT OAT GROSS WEIGHT - 1000 LB

(FT) (°C) 56 54 52 50 48 46 44 42 40 38
45000 MT 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800
458.9 KCAS 216 216 216 216 216 216 216 216 216 216
FF 2620 2530 2450 2390 2320 2270 2220 2160 2110 2070
-56.5 NAM/LB .1751 .1816 .1870 .1919 .1974 .2023 .2070 .2126 .2170 .2212
43000 MT 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800
458.9 KCAS 226 226 226 226 226 226 226 226 226 226
FF 2650 2590 2530 2470 2410 2360 2320 2280 2240 2190
-56.5 NAM/LB .1729 .1773 .1817 .1858 .1905 .1944 .1980 .2015 .2050 .2093
41000 MT 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800
458.9 KCAS 237 237 237 237 237 237 237 237 237 237
FF 2730 2680 2620 2570 2530 2490 2450 2410 2370 2340
-56.5 NAM/LB .1679 .1711 .1751 .1783 .1812 .1841 .1871 .1907 .1935 .1962
39000 MT 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800
458.9 KCAS 248 248 248 248 248 248 248 248 248 248
FF 2840 2800 2760 2720 2670 2630 2600 2570 2540 2510
-56.5 NAM/LB .1613 .1639 .1663 .1687 .1718 .1742 .1766 .1788 .1810 .1831
37000 MT 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800
458.9 KCAS 260 260 260 260 260 260 260 260 260 260
FF 3000 2960 2910 2880 2840 2810 2780 2750 2730 2700
-56.5 NAM/LB .1529 .1549 .1576 .1595 .1615 .1633 .1651 .1668 .1684 .1697
35000 MT 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800
461.1 KCAS 272 272 272 272 272 272 272 272 272 272
FF 3190 3160 3120 3090 3060 3030 3010 2980 2960 2950
-54.3 NAM/LB .1446 .1461 .1478 .1493 .1508 .1522 .1534 .1548 .1557 .1565
33000 MT 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800
465.3 KCAS 284 284 284 284 284 284 284 284 284 284
FF 3450 3420 3390 3350 3330 3310 3290 3270 3260 3240
-50.4 NAM/LB .1349 .1362 .1374 .1388 .1398 .1407 .1414 .1422 .1428 .1434
31000 MT 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800
469.4 KCAS 297 297 297 297 297 297 297 297 297 297
FF 3720 3690 3670 3640 3630 3610 3590 3570 3560 3550
-46.4 NAM/LB .1262 .1271 .1280 .1288 .1295 .1301 .1307 .1313 .1318 .1323
29000 MT 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800
473.5 KCAS 311 311 311 311 311 311 311 311 311 311
FF 4030 4010 3990 3980 3960 3950 3930 3920 3910 3900
-42.5 NAM/LB .1175 .1181 .1186 .1191 .1196 .1200 .1204 .1207 .1211 .1214
27000 MT 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800
477.5 KCAS 324 324 324 324 324 324 324 324 324 324
FF 4380 4360 4340 4320 4300 4280 4270 4250 4240 4220
-38.5 NAM/LB .1091 .1096 .1101 .1106 .1111 .1115 .1119 .1123 .1127 .1131
25000 MT 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800
481.6 KCAS 338 338 338 338 338 338 338 338 338 338
FF 4720 4700 4680 4660 4640 4620 4600 4580 4570 4550
-34.5 NAM/LB .1020 .1024 .1029 .1033 .1037 .1042 .1046 .1050 .1055 .1059
20000 MT **** **** **** **** **** **** **** **** **** ****
491.5 KCAS **** **** **** **** **** **** **** **** **** ****
FF **** **** **** **** **** **** **** **** **** ****
-24.6 NAM/LB **** **** **** **** **** **** **** **** **** ****

NOTE: See the GIV Operating Manual for procedures to account

for temperature deviation from ISA day and/or wind conditions.

REVISION 28 GIV-SP PERFORMANCE

May 25/16 (GIV-SP AIRPLANES ONLY) Page PB - 11
 Quick Reference Handbook
GIV-SP Twin Engine Cruise: Mach 0.83 – ISA CCM

For airplanes SN 1214 and subsequent and SN 1000 thru 1213

with ASC 190 incorporated.
ALT OAT GROSS WEIGHT - 1000 LB
(FT) (°C) 76 74 72 70 68 66 64 62 60 58
45000 MT **** **** **** **** **** **** **** **** **** ****
476.1 KCAS **** **** **** **** **** **** **** **** **** ****
FF **** **** **** **** **** **** **** **** **** ****
-56.5 NAM/LB **** **** **** **** **** **** **** **** **** ****
43000 MT **** **** **** **** **** **** **** **** **** 0.830
476.1 KCAS **** **** **** **** **** **** **** **** **** 235
FF **** **** **** **** **** **** **** **** **** 3230
-56.5 NAM/LB **** **** **** **** **** **** **** **** **** .1474
41000 MT **** **** **** **** **** **** 0.830 0.830 0.830 0.830
476.1 KCAS **** **** **** **** **** **** 247 247 247 247
FF **** **** **** **** **** **** 3540 3430 3320 3240
-56.5 NAM/LB **** **** **** **** **** **** .1345 .1390 .1432 .1471
39000 MT **** **** **** 0.830 0.830 0.830 0.830 0.830 0.830 0.830
476.1 KCAS **** **** **** 258 258 258 258 258 258 258
FF **** **** **** 3860 3740 3640 3560 3470 3410 3340
-56.5 NAM/LB **** **** **** .1234 .1273 .1307 .1339 .1370 .1396 .1424
37000 MT 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830
476.1 KCAS 271 271 271 271 271 271 271 271 271 271
FF 4170 4060 3970 3880 3800 3740 3670 3610 3560 3510
-56.5 NAM/LB .1142 .1173 .1200 .1227 .1252 .1273 .1297 .1318 .1337 .1356
35000 MT 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830
478.4 KCAS 283 283 283 283 283 283 283 283 283 283
FF 4240 4160 4110 4040 3980 3930 3880 3830 3780 3750
-54.3 NAM/LB .1128 .1149 .1165 .1185 .1201 .1218 .1234 .1250 .1266 .1277
33000 MT 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830
482.7 KCAS 296 296 296 296 296 296 296 296 296 296
FF 4430 4370 4320 4260 4240 4190 4150 4100 4060 4010
-50.4 NAM/LB .1090 .1104 .1119 .1132 .1138 .1152 .1165 .1178 .1190 .1202
31000 MT 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830
487.0 KCAS 310 310 310 310 310 310 310 310 310 310
FF 4690 4630 4580 4530 4480 4440 4390 4400 4350 4310
-46.4 NAM/LB .1039 .1051 .1063 .1075 .1087 .1098 .1109 .1108 .1118 .1129
29000 MT 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830
491.3 KCAS 323 323 323 323 323 323 323 323 323 323
FF 5020 4980 4930 4890 4850 4810 4800 4760 4730 4700
-42.5 NAM/LB .0978 .0987 .0996 .1004 .1013 .1022 .1024 .1031 .1038 .1045
27000 MT 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830
495.5 KCAS 337 337 337 337 337 337 337 337 337 337
FF 5300 5260 5220 5180 5140 5090 5060 5020 4990 4970
-38.5 NAM/LB .0934 .0942 .0949 .0957 .0965 .0973 .0980 .0986 .0992 .0998
25000 MT **** **** **** **** **** **** **** **** **** ****
499.6 KCAS **** **** **** **** **** **** **** **** **** ****
FF **** **** **** **** **** **** **** **** **** ****
-34.5 NAM/LB **** **** **** **** **** **** **** **** **** ****
20000 MT **** **** **** **** **** **** **** **** **** ****
509.9 KCAS **** **** **** **** **** **** **** **** **** ****
FF **** **** **** **** **** **** **** **** **** ****
-24.6 NAM/LB **** **** **** **** **** **** **** **** **** ****

NOTE: See the GIV Operating Manual for procedures to account

for temperature deviation from ISA day and/or wind conditions.

GIV-SP PERFORMANCE REVISION 28

Page PB - 12 (GIV-SP AIRPLANES ONLY) May 25/16
Quick Reference Handbook
GIV-SP Twin Engine Cruise - Mach 0.83 - ISA, ctd… CCM

ALT OAT GROSS WEIGHT - 1000 LB

(FT) (°C) 56 54 52 50 48 46 44 42 40 38
45000 MT **** **** 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830
476.1 KCAS **** **** 225 225 225 225 225 225 225 225
FF **** **** 2900 2790 2690 2620 2540 2490 2440 2390
-56.5 NAM/LB **** **** .1641 .1708 .1767 .1820 .1874 .1911 .1952 .1992
43000 MT 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830
476.1 KCAS 235 235 235 235 235 235 235 235 235 235
FF 3100 3010 2920 2840 2780 2730 2670 2620 2580 2540
-56.5 NAM/LB .1535 .1581 .1629 .1674 .1710 .1746 .1781 .1814 .1847 .1871
41000 MT 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830
476.1 KCAS 247 247 247 247 247 247 247 247 247 247
FF 3150 3080 3030 2970 2920 2870 2820 2790 2750 2710
-56.5 NAM/LB .1509 .1546 .1572 .1602 .1629 .1657 .1685 .1705 .1730 .1754
39000 MT 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830
476.1 KCAS 258 258 258 258 258 258 258 258 258 258
FF 3290 3230 3180 3140 3100 3060 3020 2980 2940 2910
-56.5 NAM/LB .1449 .1472 .1496 .1518 .1535 .1557 .1578 .1599 .1619 .1637
37000 MT 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830
476.1 KCAS 271 271 271 271 271 271 271 271 271 271
FF 3460 3410 3380 3340 3300 3260 3220 3190 3160 3140
-56.5 NAM/LB .1375 .1395 .1408 .1425 .1442 .1459 .1476 .1492 .1506 .1519
35000 MT 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830
478.4 KCAS 283 283 283 283 283 283 283 283 283 283
FF 3710 3660 3620 3590 3550 3520 3490 3480 3450 3430
-54.3 NAM/LB .1291 .1305 .1320 .1334 .1348 .1360 .1372 .1376 .1385 .1393
33000 MT 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830
482.7 KCAS 296 296 296 296 296 296 296 296 296 296
FF 3970 3930 3890 3890 3860 3840 3810 3790 3770 3750
-50.4 NAM/LB .1215 .1228 .1240 .1240 .1249 .1258 .1266 .1274 .1282 .1289
31000 MT 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830
487.0 KCAS 310 310 310 310 310 310 310 310 310 310
FF 4280 4240 4210 4190 4160 4130 4110 4080 4070 4050
-46.4 NAM/LB .1138 .1147 .1156 .1163 .1171 .1178 .1186 .1192 .1198 .1203
29000 MT 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830
491.3 KCAS 323 323 323 323 323 323 323 323 323 323
FF 4670 4650 4620 4600 4580 4560 4540 4520 4510 4490
-42.5 NAM/LB .1051 .1057 .1063 .1068 .1073 .1078 .1082 .1086 .1090 .1094
27000 MT 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830
495.5 KCAS 337 337 337 337 337 337 337 337 337 337
FF 4940 4910 4880 4850 4830 4810 4790 4770 4750 4730
-38.5 NAM/LB .1004 .1009 .1015 .1021 .1026 .1031 .1035 .1039 .1044 .1048
25000 MT **** **** **** **** **** **** **** **** **** ****
499.6 KCAS **** **** **** **** **** **** **** **** **** ****
FF **** **** **** **** **** **** **** **** **** ****
-34.5 NAM/LB **** **** **** **** **** **** **** **** **** ****
20000 MT **** **** **** **** **** **** **** **** **** ****
509.9 KCAS **** **** **** **** **** **** **** **** **** ****
FF **** **** **** **** **** **** **** **** **** ****
-24.6 NAM/LB **** **** **** **** **** **** **** **** **** ****

NOTE: See the GIV Operating Manual for procedures to account

for temperature deviation from ISA day and/or wind conditions.

REVISION 28 GIV-SP PERFORMANCE

May 25/16 (GIV-SP AIRPLANES ONLY) Page PB - 13
 Quick Reference Handbook
GIV-SP Twin Engine Flight Planning: Mach 0.77 - ISA
CCM

For airplanes SN 1214 and subsequent and SN 1000 thru 1213

with ASC 190 incorporated.

GIV-SP PERFORMANCE REVISION 28

Page PB - 14 (GIV-SP AIRPLANES ONLY) May 25/16
Quick Reference Handbook
GIV-SP Twin Engine Flight Planning: Mach 0.80 - ISA
CCM

For airplanes SN 1214 and subsequent and SN 1000 thru 1213

with ASC 190 incorporated.

REVISION 24 (RE-ISSUE) GIV-SP PERFORMANCE

Mar 17/10 (GIV-SP AIRPLANES ONLY) Page PB - 15
 Quick Reference Handbook
GIV-SP Twin Engine Flight Planning: Mach 0.83 - ISA
CCM

For airplanes SN 1214 and subsequent and SN 1000 thru 1213

with ASC 190 incorporated.

GIV-SP PERFORMANCE REVISION 24 (RE-ISSUE)

Page PB - 16 (GIV-SP AIRPLANES ONLY) Mar 17/10
Quick Reference Handbook
GIV-SP Equal Time Point And Point Of No Return CCM

ETP PNR WIND

GS R1

GS O

GS GS C
R

TRIP DISTANCE = D

DEPARTURE DESTINATION
AIRPORT AIRPORT

The following formula is used to calculate the ground distance from the
departure airport to ETP: (D) (GS )
R
GROUND DISTANCE TO ETP = = NM
GSC + GSR
Where:
D= Total Trip Distance
GSC = Ground Speed To Continue To Destination At Altitude To Be
Flown
GSR = Ground Speed To Departure Airport At Altitude To Be Flown
The following formula is used to calculate the ground distance from the
departure airport to PNR: (Endurance) (GSR1) (GSO)
GROUND DISTANCE TO PNR = = NM
GSO + GSR1

Where:
Total Fuel Quantity
Endurance =
Average Fuel Flow
GSO = Normal Outbound Ground Speed At Cruise Altitude
GSR1 = Return Ground Speed At Normal Cruise Altitude

REVISION 24 (RE-ISSUE) GIV-SP PERFORMANCE

Mar 17/10 (GIV-SP AIRPLANES ONLY) Page PB - 17
 Quick Reference Handbook
GIV-SP Twin Engine Alternate Airport Flight Plan Fuel
CCM

For airplanes SN 1214 and subsequent and SN 1000 thru 1213

with ASC 190 incorporated.
Conditions:
• Standard Day, No Wind
• Zero-Fuel Gross Weight of 44,100 Lb
• 1500 Lb Reserve Fuel Included
• Five (5) Minute Approach Fuel Allowance Included

Distance
To Enroute True Fuel
Alternate Flight Time TAS Mach CAS Quantity
(NM) Level (Hr:Min) (Knots) Number (Knots) (Pounds)
100 230 0:24 329 .542 233 2770
120 250 0:27 338 .562 232 2920
140 310 0:29 378 .645 235 3050
160 350 0:32 412 .715 240 3170
180 370 0:33 427 .745 240 3280
200 410 0:36 437 .762 224 3380
220 430 0:39 442 .770 216 3480
240 450 0:42 442 .770 206 3580
260 450 0:44 442 .770 206 3680
280 450 0:47 442 .770 206 3780
300 450 0:50 442 .770 206 3880
320 450 0:53 442 .770 206 3990
340 450 0:56 442 .770 206 4090
360 450 0:59 442 .770 206 4190
380 450 1:01 442 .770 206 4270
400 450 1:03 442 .770 206 4370
420 450 1:06 442 .770 206 4490
440 450 1:09 442 .770 206 4590
460 450 1:12 442 .770 206 4670
480 450 1:15 442 .770 206 4790
500 450 1:18 442 .770 206 4890
520 450 1:20 442 .770 206 4970
540 450 1:23 442 .770 206 5090
560 450 1:26 442 .770 206 5200
580 450 1:29 442 .770 206 5290
600 450 1:31 442 .770 206 5380

GIV-SP PERFORMANCE REVISION 24 (RE-ISSUE)

Page PB - 18 (GIV-SP AIRPLANES ONLY) Mar 17/10
Quick Reference Handbook
GIV-SP Landing Field Length:
Anti-Skid System Operative - Flaps 39° AFM 5.11

For airplanes SN 1214 and subsequent and SN 1000 thru 1213

with ASC 190 incorporated.
CAUTION: THE GIV-SP MAXIMUM LANDING WEIGHT IS 66,000
POUNDS.
NOTES:
1. ISA day, normal landing configuration.
2. For intended destination wet, multiply landing field lengths below by
1.15.
3. For unfactored landing distances, multiply field lengths below by
0.60.
4. Field lengths seen below are based on no wind or runway slope, but
may be conservatively used with headwinds or uphill runway slopes.
5. For all abnormal landing configurations, see Abnormal Landing
Field Length Table, page PC-16.

Landing Intended Destination Dry Landing Field Length (Feet)

Gross For Airport Pressure Altitudes As Shown
Weight
Sea 2000 4000 6000 8000 10000
(Lb) Level Feet Feet Feet Feet Feet
45000 4340 4470 4600 4760 4950 5260
50000 4570 4710 4860 5040 5260 5600
55000 4800 4950 5120 5310 5550 5930
60000 5030 5200 5380 5600 5860 6270
65000 5260 5440 5640 5880 6160 6610
70000 5500 5690 5910 6160 6480 6940
75000 5730 5940 6170 6440 6770 7270

REVISION 24 (RE-ISSUE) GIV-SP PERFORMANCE

Mar 17/10 (GIV-SP AIRPLANES ONLY) Page PC - 1
 Quick Reference Handbook
GIV-SP Landing Speed Schedule AFM 5.11

For airplanes SN 1214 and subsequent and SN 1000 thru 1213

with ASC 190 incorporated.
The following guidance is provided to assist in the use of the
charts in this section:
Tire speed limits occur when touchdown speeds exceeds 195.5
knots (225 MPH). Tire fuseplug release limits occur when Brake
Kinetic Energy (BKE) for a maximum effort landing (full brake
application at touchdown) exceeds 57 MFP, making fuseplug release
possible. If brake application is delayed following touchdown, the
resulting lower level of BKEs can be determined from GIV Airplane
Flight Manual Appendix C, GIV-SP Brake Kinetic Energy and
Carbon Brake Cooling.
Limits shown in the charts that follow are conservative in nature and
represent a combination of worst-case conditions, i.e., maximum
temperature at a given altitude plus a 2% downhill runway slope.
These limits apply to a nil or headwind condition only.

NOTE: All speeds shown are KCAS.

Weight = 45000 LB Normal Abnormal Abnormal Abnormal

Flaps 39° Flaps 20° Flaps 10° Flaps UP
F39° F39°
Altitude VAPP VREF VAPP VREF VAPP VREF VAPP VREF
Shake Push
0 101 95 133 123 136 126 141 131 149 139
2000 101 95 133 123 136 126 142 132 149 139
4000 101 95 133 123 137 127 143 133 151 141
6000 102 95 134 124 138 128 144 134 152 142
8000 103 96 135 125 139 129 146 136 154 144
10000 104 97 136 126 141 131 147 137 156 146
12000 105 98 137 127 142 132 149 139 158 148
14000 106 99 139 129 143 133 150 140 160 150
15000 107 100 139 129 144 134 151 141 161 151
CAUTION: Fuseplug Release Possible CAUTION: Tire Speed Limit
With Max. Braking

GIV-SP PERFORMANCE REVISION 24 (RE-ISSUE)

Page PC - 2 (GIV-SP AIRPLANES ONLY) Mar 17/10
Quick Reference Handbook
GIV-SP Landing Speed Schedule, ctd… AFM 5.11

NOTES:
1. See the explanatory text presented on page PC-2 of this section.
2. All speeds shown are KCAS.

Weight = 50000 LB Normal Abnormal Abnormal Abnormal

Flaps 39° Flaps 20° Flaps 10° Flaps UP
F39° F39°
Altitude VAPP VREF VAPP VREF VAPP VREF VAPP VREF
Shake Push
0 107 100 140 130 143 133 149 139 157 147
2000 107 100 140 130 143 133 149 139 157 147
4000 107 100 140 130 144 134 150 140 158 148
6000 107 100 140 130 145 135 151 141 160 150
8000 108 101 142 132 147 137 153 143 162 152
10000 109 102 143 133 148 138 155 145 164 154
12000 111 103 144 134 149 139 156 146 166 156
14000 112 104 146 136 151 141 158 148 168 158
15000 112 105 146 136 152 142 159 149 170 160
CAUTION: Fuseplug Release Possible CAUTION: Tire Speed Limit
With Max. Braking

Weight = 55000 LB Normal Abnormal Abnormal Abnormal

Flaps 39° Flaps 20° Flaps 10° Flaps UP
F39° F39°
Altitude VAPP VREF VAPP VREF VAPP VREF VAPP VREF
Shake Push
0 112 105 146 136 149 139 155 145 164 154
2000 112 105 146 136 149 139 155 145 164 154
4000 112 105 146 136 150 140 157 147 166 156
6000 113 105 147 137 152 142 158 148 168 158
8000 114 106 148 138 153 143 160 150 170 160
10000 115 107 149 139 154 144 162 152 172 162
12000 116 108 151 141 156 146 163 153 174 164
14000 117 110 152 142 158 148 165 155 176 166
15000 118 110 153 143 158 148 166 156 177 167
CAUTION: Fuseplug Release Possible CAUTION: Tire Speed Limit
With Max. Braking

REVISION 24 (RE-ISSUE) GIV-SP PERFORMANCE

Mar 17/10 (GIV-SP AIRPLANES ONLY) Page PC - 3
 Quick Reference Handbook
GIV-SP Landing Speed Schedule, ctd… AFM 5.11

NOTES:
1. See the explanatory text presented on page PC-2 of this section.
2. All speeds shown are KCAS.

Weight = 60000 LB Normal Abnormal Abnormal Abnormal

Flaps 39° Flaps 20° Flaps 10° Flaps UP
F39° F39°
Altitude VAPP VREF VAPP VREF VAPP VREF VAPP VREF
Shake Push
0 117 109 152 142 156 146 162 152 171 161
2000 117 109 152 142 156 146 162 152 171 161
4000 117 109 152 142 157 147 163 153 173 163
6000 118 110 153 143 158 148 165 155 175 165
8000 119 111 154 144 160 150 167 157 177 167
10000 120 112 156 146 161 151 168 158 179 169
12000 121 113 157 147 163 153 170 160 181 171
14000 123 114 159 149 164 154 172 162 184 174
15000 123 115 160 150 165 155 173 163 185 175
CAUTION: Fuseplug Release Possible CAUTION: Tire Speed Limit
With Max. Braking

Weight = 65000 LB Normal Abnormal Abnormal Abnormal

Flaps 39° Flaps 20° Flaps 10° Flaps UP
F39° F39°
Altitude VAPP VREF VAPP VREF VAPP VREF VAPP VREF
Shake Push
0 122 114 158 148 162 152 168 158 178 168
2000 122 114 158 148 162 152 168 158 178 168
4000 122 114 158 148 163 153 169 159 179 169
6000 122 114 159 149 164 154 171 161 181 171
8000 124 116 160 150 166 156 173 163 184 174
10000 125 117 162 152 167 157 175 165 186 176
12000 126 118 163 153 169 159 177 167 188 178
14000 128 119 165 155 170 160 179 169 191 181
15000 128 120 166 156 171 161 180 170 192 182
CAUTION: Fuseplug Release Possible CAUTION: Tire Speed Limit
With Max. Braking

GIV-SP PERFORMANCE REVISION 24 (RE-ISSUE)

Page PC - 4 (GIV-SP AIRPLANES ONLY) Mar 17/10
Quick Reference Handbook
GIV-SP Landing Speed Schedule, ctd… AFM 5.11

NOTES:
1. See the explanatory text presented on page PC-2 of this section.
2. All speeds shown are KCAS.

Weight = 70000 LB Normal Abnormal Abnormal Abnormal

Flaps 39° Flaps 20° Flaps 10° Flaps UP
F39° F39°
Altitude VAPP VREF VAPP VREF VAPP VREF VAPP VREF
Shake Push
0 126 118 164 154 167 157 174 164 184 174
2000 126 118 164 154 167 157 174 164 184 174
4000 126 118 164 154 169 159 176 166 186 176
6000 127 119 164 154 170 160 177 167 188 178
8000 128 120 166 156 172 162 179 169 190 180
10000 130 121 167 157 173 163 181 171 193 183
12000 131 122 169 159 175 165 183 173 195 185
14000 132 124 171 161 177 167 185 175 198 188
15000 133 124 172 162 178 168 187 177 199 189
CAUTION: Fuseplug Release Possible CAUTION: Tire Speed Limit
With Max. Braking

Weight = 75000 LB Normal Abnormal Abnormal Abnormal

Flaps 39° Flaps 20° Flaps 10° Flaps UP
F39° F39°
Altitude VAPP VREF VAPP VREF VAPP VREF VAPP VREF
Shake Push
0 131 122 169 159 173 163 180 170 190 180
2000 131 122 169 159 173 163 180 170 190 180
4000 131 122 169 159 174 164 181 171 192 182
6000 132 123 170 160 176 166 183 173 194 184
8000 133 124 171 161 177 167 185 175 197 187
10000 134 125 173 163 179 169 187 177 199 189
12000 136 127 175 165 181 171 190 180 202 192
14000 137 128 176 166 183 173 192 182 204 194
15000 138 129 177 167 183 173 193 183 206 196
CAUTION: Fuseplug Release Possible CAUTION: Tire Speed Limit
With Max. Braking

REVISION 24 (RE-ISSUE) GIV-SP PERFORMANCE

Mar 17/10 (GIV-SP AIRPLANES ONLY) Page PC - 5
 Quick Reference Handbook
GIV-SP Landing Distance Using Twin-Engine Reverse
Thrust Only (No Braking) OM 07-01-80

For airplanes SN 1214 and subsequent and SN 1000 thru 1213

with ASC 190 incorporated.
The table on the following page shows landing distances when using
reverse thrust only to bring the aircraft to a stop. The distances shown
below assume reverse thrust is used to 20 knots with stowage by 10
knots.
Conditions:
• Two-Engine Reverse Thrust Only
• No Slope
• No Wind
• Standard Day Temperature
• AUTO Ground Spoilers
• No Runway Surface Contamination Accumulation
• Full Reverse Thrust To 20 Knots
• Stowage By 10 Knots
• Minimal Braking Below 10 Knots
• Flaps 39°
NOTE: Airplane Flight Manual procedures recommend that cancellation of
thrust reversers be initiated by 70 knots, so as to be completely cancelled by
the time normal taxi speed is achieved. If landing runway conditions will result
in compromised braking performance, this table may be used to provide
additional information for pilot judgment.

GIV-SP PERFORMANCE REVISION 24 (RE-ISSUE)

Page PC - 6 (GIV-SP AIRPLANES ONLY) Mar 17/10
Quick Reference Handbook
GIV-SP Landing Distance Using Twin-Engine Reverse Thrust
Only (No Braking), ctd… OM 07-01-90

Landing Distance (Feet)

ALT Gross Weight (lb)
(Ft) 74,600 73,200 70,000 66,000 65,000 60,000
15,000 15,166 14,850 14,122 13,209 12,985 11,890
14,000 14,346 14,045 13,359 12,501 12,287 11,264
12,000 12,837 12,569 11,960 11,204 11,019 10,112
10,000 11,495 11,255 10,719 10,052 9,886 9,082
8,000 10,524 10,309 9,823 9,215 9,068 8,342
6,000 9,847 9,649 9,199 8,639 8,500 7,831
4,000 9,265 9,081 8,665 8,144 8,015 7,395
2,000 8,771 8,601 8,213 7,727 7,608 7,028
0 8,320 8,161 7,795 7,343 7,230 6,692
Landing Distance (Feet)
ALT Gross Weight (lb)
(Ft) 58,500 55,000 50,000 45,000 40,000
15,000 11,564 10,813 9,787 8,776 7,827
14,000 10,952 10,250 9,282 8,330 7,440
12,000 9,837 9,212 8,359 7,516 6,732
10,000 8,841 8,289 7,532 6,788 6,093
8,000 8,122 7,623 6,940 6,270 5,648
6,000 7,630 7,169 6,541 5,925 5,358
4,000 7,207 6,784 6,204 5,638 5,116
2,000 6,855 6,458 5,920 5,398 4,921
0 6,530 6,160 5,657 5,178 4,744

REVISION 28 GIV-SP PERFORMANCE

May 25/16 (GIV-SP AIRPLANES ONLY) Page PC - 7
 Quick Reference Handbook
GIV-SP Aircraft Classification Number (ACN) GAC

Aircraft Classification Number (ACN) is a number expressing the

relative effect of an aircraft on a pavement for a specified subgrade
category. ACN values are calculated for both flexible and rigid
pavement. If the aircraft gross weight and runway subgrade strength
are known, the ACN value can be determined from the charts on the
following pages.
Pavement Classification Number (PCN) is a number expressing the
bearing strength of a pavement for unrestricted operations. It is
reported in the Jeppesen charts in a format such as 24/F/C/Y/T,
where:
24 is the PCN
F is the type of pavement, where:
R = Rigid
F = Flexible
C is the subgrade strength, where:
D = Ultra Low
C = Low
B = Medium
A = High
Y is the tire pressure, where:
W = Unlimited
X = High, Pressure limited to 254 psi (1.75 MPa)
Y = Medium, Pressure limited to 181 psi (1.25 MPa)
Z = Low, Pressure limited to 73 psi (0.50 MPa)
T is the PCN classification, where:
T = Technical Evaluation
U = Aircraft Experience
ACN values must be less than or equal to the airport PCN for
unrestricted use. ACN input variables are gross weight, percent load
on main wheels, wheel spacing and maximum tire pressure.

GIV-SP PERFORMANCE REVISION 28

Page PC - 8 (GIV-SP AIRPLANES ONLY) May 25/16
Quick Reference Handbook
GIV-SP ACN, ctd… GAC

Example 1:
Given: Gross Weight = 70,000 lb, PCN = 24/F/C/Y/T
Where: PCN = 24
F = Flexible Pavement
ACN = 22 (from charts)
C = Low Subgrade Strength
Y = 181 psi Tire Pressure Limit
T = Technical Evaluation
Thus: ACN less than PCN, but tire pressure becomes a restriction.
Example 2:
Given: Gross Weight = 70,000 lb, PCN = 80/R/B/W/T
Where: PCN = 80
R = Rigid Pavement
ACN = 22 (from charts)
B = Medium Subgrade Strength
W = Unlimited
T = Technical Evaluation
Thus: ACN less than PCN, no tire pressure limit. Suitable runway.

Main Landing Gear Tire Pressure vs. Gross Weight:

1159SCL406-1 Tires

REVISION 28 GIV-SP PERFORMANCE

May 25/16 (GIV-SP AIRPLANES ONLY) Page PC - 9
 Quick Reference Handbook
GIV-SP ACN, ctd… GAC

NOTE: Use of these charts is to be with reference to GIV

Operating Manual Chapter 6: Approach and Landing
Characteristics and Procedures.

GIV-SP PERFORMANCE REVISION 28

Page PC - 10 (GIV-SP AIRPLANES ONLY) May 25/16
Quick Reference Handbook
GIV-SP ACN, ctd… GAC

NOTE: Use of these charts is to be with reference to GIV Operating

Manual Chapter 6: Approach and Landing Characteristics and
Procedures.

REVISION 28 GIV-SP PERFORMANCE

May 25/16 (GIV-SP AIRPLANES ONLY) Page PC - 11
 Quick Reference Handbook
GIV-SP ACN, ctd… GAC

NOTE: Use of these charts is to be with reference to GIV Operating

Manual Chapter 6: Approach and Landing Characteristics and
Procedures.

GIV-SP PERFORMANCE REVISION 28

Page PC - 12 (GIV-SP AIRPLANES ONLY) May 25/16
Quick Reference Handbook
GIV-SP ACN, ctd… GAC

NOTE: Use of these charts is to be with reference to GIV Operating

Manual Chapter 6: Approach and Landing Characteristics and
Procedures.

REVISION 28 GIV-SP PERFORMANCE

May 25/16 (GIV-SP AIRPLANES ONLY) Page PC - 13
 Quick Reference Handbook
GIV-SP Equivalent Single Wheel Loading (ESWL)
OM 06-05-90

Introduction:
One consideration in operating Gulfstream aircraft is the strength of
runway and taxiway pavements in relation to aircraft operating weight.
This can limit operational weights in some airports. One common
method of evaluating an aircraft for a given runway is the Equivalent
Single Wheel Loading (ESWL). ESWL accounts for the extra tire
flotation for multi-wheel landing gear struts such as the dual wheel
struts used on the Gulfstream aircraft. This section provides
information on how to compute ESWL for the G400, G300, GIV-SP and
Non-SP GIV airplanes.

G400, G300, GIV-SP and Non-SP GIV Main Landing Gear

Parameters:
Max
MLG Tire Tire Max Tire Reduction Maximum
Ramp
Size Spacing Pressure Factor ESWL
Weight
(pounds) (inches) (inches) (psi) ---- (pounds)
75,000 34 × 9.5 16.0 190 1.23 27,439

The reduction factor in the table above assumes a rigid pavement with
a radius of equivalent stiffness of 40 inches, roughly equivalent to a
13.5 inch thick concrete slab. Thinner pavements would give higher
reduction factors, so the factors presented are conservative.

ESWL Computation for Lower Operating Weights:

ESWL can be computed for lower operating weights as follows:
ESWL = (Gross Weight) × (0.9) × (0.5) ÷ (Reduction Factor)

GIV-SP PERFORMANCE REVISION 28

Page PC - 14 (GIV-SP AIRPLANES ONLY) May 25/16
Quick Reference Handbook
GIV-SP Brake Kinetic Energy / Carbon Brake Cooling
AFM APP. C

NOTE: Use of these charts is to be with reference to GIV Airplane Flight

Manual Appendix C: Brake Kinetic Energy and Carbon Brake Cooling.

REVISION 24 (RE-ISSUE) GIV-SP PERFORMANCE

Mar 17/10 (GIV-SP AIRPLANES ONLY) Page PC - 15
 Quick Reference Handbook
GIV-SP Abnormal Landing Field Length Table GAC

GIV-SP Abnormal Landing Field Length Table

Reference
Landing Field Corrected, Factored (x 1.67), Dry Runway Landing Field
Length (Feet) Length (Feet) For Abnormal Landing Configuration
39° Flaps 39° 39° 20° 10° 0°
OPERATIVE Anti-Skid OPERATIVE INOP OPERATIVE OPERATIVE OPERATIVE
AUTO Speedbrakes MANUAL AUTO AUTO AUTO AUTO
4200 4620 8660 4320 4510 4700
4400 4860 9190 4530 4740 4950
4600 5090 9720 4740 4970 5210
4800 5330 10250 4950 5200 5460
5000 5570 10790 5160 5430 5710
5200 5810 11320 5370 5660 5970
5400 6050 11850 5580 5890 6220
5600 6290 12380 5790 6120 6480
5800 6530 12910 6000 6350 6730
6000 6770 13440 6210 6580 6980
6200 7000 13970 6420 6810 7240
6400 7240 14510 6630 7040 7490
6600 7480 15040 6840 7270 7750
6800 7720 15570 7050 7510 8000
7000 7960 16100 7260 7740 8260
7200 8200 16630 7470 7970 8510
7400 8440 17160 7680 8200 8760

CAUTION: THE GIV-SP MAXIMUM LANDING WEIGHT IS 66,000 LB

(29,937 KG).
NOTES:
1. Reference Landing Field Length in first column is a FAR 135 factored,
ISA-Day, dry runway distance for a normal landing configuration (Flaps
39°, Anti-Skid operative and Automatic deployment of speed brakes /
ground-spoilers).
2. For intended destination wet, multiply landing field lengths above by 1.15.
3. For unfactored landing distances, multiply field lengths above by 0.60.
4. Field lengths seen above are based on no wind or runway slope, but may
be conservatively used with headwinds or uphill runway slopes.
5. For all abnormal landing flap configurations (0°, 10°, and 20°) with manual
speed brake deployment, increase the flaps 0° landing distance (based on
auto ground spoiler deployment) by 10%.

GIV-SP PERFORMANCE REVISION 24 (RE-ISSUE)

Page PC - 16 (GIV-SP AIRPLANES ONLY) Mar 17/10
Quick Reference Handbook

Non-SP GIV Performance Planning Index

Non-SP GIV Takeoff Planning
Non-SP GIV Crosswind Components ........................................... PA-1
Non-SP GIV Contaminated Runway Operations .......................... PA-2
Non-SP GIV Takeoff Planning Charts: Flaps 20°, APA SL .......... PA-5
Non-SP GIV Takeoff Planning Charts: Flaps 20°, 500 Feet......... PA-7
Non-SP GIV Takeoff Planning Charts: Flaps 20°, 1000 Feet....... PA-9
Non-SP GIV Takeoff Planning Charts: Flaps 20°, 2000 Feet..... PA-11
Non-SP GIV Takeoff Planning Charts: Flaps 20°, 4000 Feet..... PA-13
Non-SP GIV Takeoff Planning Charts: Flaps 20°, 6000 Feet..... PA-15
Non-SP GIV Takeoff Planning Charts: Flaps 20°, 8000 Feet..... PA-17
Non-SP GIV Takeoff Planning Charts: Flaps 10°, APA SL ........ PA-20
Non-SP GIV Takeoff Planning Charts: Flaps 10°, 500 Feet....... PA-22
Non-SP GIV Takeoff Planning Charts: Flaps 10°, 1000 Feet..... PA-24
Non-SP GIV Takeoff Planning Charts: Flaps 10°, 2000 Feet..... PA-26
Non-SP GIV Takeoff Planning Charts: Flaps 10°, 4000 Feet..... PA-28
Non-SP GIV Takeoff Planning Charts: Flaps 10°, 6000 Feet..... PA-30
Non-SP GIV Takeoff Planning Charts: Flaps 10°, 8000 Feet..... PA-32
Non-SP GIV Maximum Allowable Takeoff Gross Weight Permitted
By Takeoff Climb Requirements, Flaps 20°, Minimum Grad. .... PA-34
Non-SP GIV Maximum Allowable Takeoff Gross Weight Permitted
By Takeoff Climb Requirements, Flaps 10°, Minimum Grad. .... PA-35
Non-SP GIV Maximum Allowable Takeoff Gross Weight Permitted
By Takeoff Climb Requirements, Flaps 20°, SID Departure ....... PA-36
Non-SP GIV Maximum Allowable Takeoff Gross Weight Permitted
By Takeoff Climb Requirements, Flaps 10°, SID Departure ....... PA-48
Non-SP SID Climb Performance Conversion Table ................... PA-60

Continued on next page →

REVISION 24 (RE-ISSUE) NON-SP GIV PERFORMANCE

Mar 17/10 (NON-SP GIV AIRPLANES ONLY) Page P - i
 Quick Reference Handbook
Non-SP GIV Performance Planning Index, ctd…
Non-SP GIV Cruise Planning
Non-SP GIV Twin Engine Cruise Altitudes, Mach 0.77 ................ PB-1
Non-SP GIV Twin Engine Cruise Altitudes, Mach 0.80 ................ PB-2
Non-SP GIV Twin Engine Cruise Altitudes, Mach 0.83 ................ PB-3
Non-SP GIV Twin Engine Maximum Range Cruise - ISA ............ PB-4
Non-SP GIV Twin Engine Long Range Cruise - ISA.................... PB-6
Non-SP GIV Twin Engine Cruise, Mach 0.77 - ISA ..................... PB-8
Non-SP GIV Twin Engine Cruise, Mach 0.80 - ISA ................... PB-10
Non-SP GIV Twin Engine Cruise, Mach 0.83 - ISA ................... PB-12
Non-SP GIV Twin Engine Flight Planning, Mach 0.77 - ISA ...... PB-14
Non-SP GIV Twin Engine Flight Planning, Mach 0.80 - ISA ...... PB-15
Non-SP GIV Twin Engine Flight Planning, Mach 0.83 - ISA ...... PB-16
Non-SP GIV Equal Time Point and Point of No Return ............. PB-17
Non-SP GIV Twin Engine Alternate Airport Flight Plan Fuel ..... PB-18
Non-SP GIV Landing Planning
Non-SP GIV Landing Field Length: Anti-Skid Op., Flaps 39° ...... PC-1
Non-SP GIV Landing Speed Schedule ........................................ PC-2
Non-SP GIV Landing Distance Using Twin-Engine Reverse
Thrust Only (No Braking) .............................................................. PC-6
Non-SP GIV Aircraft Classification Number (ACN) ...................... PC-8
Non-SP GIV Equivalent Single Wheel Loading (ESWL) ............ PC-14
Non-SP GIV Brake Kinetic Energy / Carbon Brake Cooling ...... PC-15
Non-SP GIV Abnormal Landing Field Length Table .................. PC-16

NON-SP GIV PERFORMANCE REVISION 24 (RE-ISSUE)

Page P - ii (NON-SP GIV AIRPLANES ONLY) Mar 17/10
Quick Reference Handbook
Non-SP GIV Crosswind Components AFM 5.1

REVISION 24 (RE-ISSUE) NON-SP GIV PERFORMANCE

Mar 17/10 (NON-SP GIV AIRPLANES ONLY) Page PA - 1
 Quick Reference Handbook
Non-SP GIV Contaminated Runway Operations
GIV-OIS-2A

RUNWAY SURFACE CONTAMINATION (RSC), CRFI EQUIVALENT

AND ESTIMATED LANDING BRAKING COEFFICIENT
APPROXIMATE
CRFI
RSC PIREP RCR BRAKING
EQUIVALENT
COEFFICIENT
Bare and Dry ³ 0.80
Damp - Less than 0.01 inch of water 0.60 - 0.70 Good ³ 18 0.36 - 0.39
Very light snow patches 0.55 - 0.60
Wet concrete - 0.01 to 0.03 inch of water 0.40 - 0.55
Wet Asphalt - 0.01 to 0.03 inch of water 0.30 - 0.60 Fair 13 - 18 0.25 - 0.35
Compacted snow -- below -15°C 0.40
Sanded, packed snow or ice 0.40 - 0.50
Heavy rain -- 0.03 to 0.10 inch of water 0.28 - 0.30
Snow covered 0.25 - 0.30 Poor 5 - 12 0.13 - 0.25
Compacted snow -- above -15°C 0.20 - 0.25
Cold ice -- below -10°C 0.10 - 0.20
Wet ice -- above -10°C 0.05 - 0.10
Hydroplaning - standing water ³ 0.10 0.05 Nil £5 £ 0.13

CANADIAN RUNWAY FRICTION INDEX

.20 .25 .30 .40 .45 .50 .55 .60 .70 .75

NIL POOR FAIR GOOD

.10 .15 .20 .25 .30 .35

(ICY) (WET) (DRY)
APPROXIMATE BRAKING COEFFICIENT

NOTE: The data presented above is advisory data only and is not FAA
approved. For additional information concerning contaminated runway
operations, refer to the latest approved revision of Operational
Information Supplement GIV-OIS-2A, Contaminated Runway
Operations.

NON-SP GIV PERFORMANCE REVISION 24 (RE-ISSUE)

Page PA - 2 (NON-SP GIV AIRPLANES ONLY) Mar 17/10
Quick Reference Handbook
Non-SP GIV Contaminated Runway Operations, ctd… GIV-OIS-2A

NOTE: The data presented above is advisory data only and is not FAA
approved. For additional information concerning contaminated runway
operations, refer to the latest approved revision of Operational
Information Supplement GIV-OIS-2A, Contaminated Runway
Operations.

REVISION 24 (RE-ISSUE) NON-SP GIV PERFORMANCE

Mar 17/10 (NON-SP GIV AIRPLANES ONLY) Page PA - 3
 Quick Reference Handbook
Non-SP GIV Takeoff Planning Charts: Flaps 20°
AFM APP. A

The charts in this section provide quick reference planning data for
takeoff planning at the following Airport Pressure Altitudes (APA), for
20° flap configurations:
• Sea Level • 500 Feet • 1000 Feet • 2000 Feet
• 4000 Feet • 6000 Feet • 8000 Feet
In the interest of safety, the CAUTION and NOTES following each
takeoff planning chart must be observed when using any takeoff
planning chart in this section.

NON-SP GIV PERFORMANCE REVISION 24 (RE-ISSUE)

Page PA - 4 (NON-SP GIV AIRPLANES ONLY) Mar 17/10
Quick Reference Handbook
Non-SP GIV Takeoff Planning:
Flaps 20° - APA Sea Level AFM APP. A

TAKEOFF PLANNING CHART

NON-SP GIV AIRPORT PRESSURE ALTITUDE = SEA LEVEL TAKEOFF FLAP 20°
73,200 LB MTOGW OAT (°C) 50 45 40 35 30 25 20 15 5 -5 -15
OAT (°F) 122 113 104 95 86 77 68 59 41 23 5
RATED EPR 1.59 1.62 1.64 1.67 1.70 1.70 1.70 1.70 1.69 1.69 1.69
-- 73,200 LB --
VFS = 171 KCAS FLD LNGTH 7,410 6,810 6,320 5,900 5,540 5,450 5,370 5,280 5,150 4,980 4,810
VSE = 178 KCAS V1 KCAS 144 142 140 139 137 137 137 137 138 138 138
VREF = 157 KCAS VR KCAS 144 144 144 144 143 143 143 143 143 143 143
MAX TEMP = 50°C V2 KCAS 148 148 148 148 148 148 148 148 148 148 148
-- 72,000 LB --
VFS = 170 KCAS FLD LNGTH 7,130 6,570 6,110 5,700 5,360 5,280 5,190 5,110 4,990 4,820 4,650
VSE = 177 KCAS V1 KCAS 142 140 139 137 136 136 136 136 136 136 136
VREF = 156 KCAS VR KCAS 143 143 143 143 142 142 142 142 142 142 142
MAX TEMP = 50°C V2 KCAS 147 147 147 147 147 147 147 147 147 147 147
-- 70,000 LB --
VFS = 167 KCAS FLD LNGTH 6,690 6,190 5,760 5,390 5,070 4,990 4,910 4,840 4,720 4,560 4,400
VSE = 174 KCAS V1 KCAS 139 137 136 134 133 133 133 133 134 134 134
VREF = 154 KCAS VR KCAS 141 141 141 140 140 140 140 140 140 140 140
MAX TEMP = 50°C V2 KCAS 145 145 145 145 145 145 145 145 145 145 145
-- 68,000 LB --
VFS = 165 KCAS FLD LNGTH 6,280 5,820 5,430 5,090 4,790 4,710 4,640 4,570 4,460 4,310 4,160
VSE = 171 KCAS V1 KCAS 136 134 133 132 130 130 130 130 131 131 131
VREF = 151 KCAS VR KCAS 139 139 139 138 137 137 137 137 137 137 137
MAX TEMP = 50°C V2 KCAS 143 143 143 143 143 143 143 143 143 143 143
-- 66,000 LB --
VFS = 162 KCAS FLD LNGTH 5,890 5,470 5,120 4,800 4,520 4,450 4,380 4,310 4,200 4,060 3,920
VSE = 169 KCAS V1 KCAS 133 132 130 129 128 128 128 128 128 128 128
VREF = 149 KCAS VR KCAS 137 137 136 135 135 135 135 135 135 135 135
MAX TEMP = 50°C V2 KCAS 141 141 141 141 141 141 141 141 141 141 141
-- 64,000 LB --
VFS = 160 KCAS FLD LNGTH 5,520 5,140 4,820 4,520 4,260 4,190 4,130 4,060 3,960 3,830 3,700
VSE = 166 KCAS V1 KCAS 131 129 128 126 125 125 125 125 125 125 125
VREF = 147 KCAS VR KCAS 135 134 134 133 132 132 132 132 132 132 132
MAX TEMP = 50°C V2 KCAS 139 139 139 139 139 139 139 139 139 139 139
-- 62,000 LB --
VFS = 157 KCAS FLD LNGTH 5,170 4,830 4,530 4,250 4,010 3,950 3,890 3,830 3,730 3,610 3,480
VSE = 164 KCAS V1 KCAS 128 126 125 123 122 122 122 122 122 122 123
VREF = 144 KCAS VR KCAS 132 132 131 131 130 130 130 130 130 130 130
MAX TEMP = 50°C V2 KCAS 137 137 137 137 137 137 137 137 137 137 137
-- 60,000 LB --
VFS = 155 KCAS FLD LNGTH 4,850 4,530 4,250 4,000 3,770 3,710 3,660 3,600 3,510 3,390 3,280
VSE = 161 KCAS V1 KCAS 125 123 122 120 119 119 119 119 120 120 120
VREF = 142 KCAS VR KCAS 130 129 129 128 127 127 127 127 127 127 127
MAX TEMP = 50°C V2 KCAS 135 135 135 135 135 135 135 135 135 135 135
CAUTION: DO NOT REDUCE TAKEOFF EPR BY MORE THAN .15 OR BELOW A MINIMUM VALUE OF 1.56.
NOTES: HEADWIND: Increase available field length 2% for each 5 knots (up to 40 knots).
TAILWIND: Not permitted using this data at this pressure altitude.
UPHILL SLOPE: Decrease available field length 20% for each 1% (up to 2%).
DOWNHILL SLOPE: Not permitted using this data at this pressure altitude.
GROUND SPOILERS INOP: Decrease available field length 800 feet.

REVISION 24 (RE-ISSUE) NON-SP GIV PERFORMANCE

Mar 17/10 (NON-SP GIV AIRPLANES ONLY) Page PA - 5
 Quick Reference Handbook
Non-SP GIV Takeoff Planning: Flaps 20° - APA Sea Level, ctd…
AFM APP. A

TAKEOFF PLANNING CHART

NON-SP GIV AIRPORT PRESSURE ALTITUDE = SEA LEVEL TAKEOFF FLAP 20°
73,200 LB MTOGW OAT (°C) 50 45 40 35 30 25 20 15 5 -5 -15
OAT (°F) 122 113 104 95 86 77 68 59 41 23 5
RATED EPR 1.59 1.62 1.64 1.67 1.70 1.70 1.70 1.70 1.69 1.69 1.69
-- 58,000 LB --
VFS = 152 KCAS FLD LNGTH 4,590 4,300 4,030 3,790 3,600 3,540 3,490 3,440 3,340 3,230 3,120
VSE = 158 KCAS V1 KCAS 123 121 120 118 117 117 117 117 118 118 118
VREF = 140 KCAS VR KCAS 128 128 127 126 126 126 126 126 126 126 126
MAX TEMP = 50°C V2 KCAS 133 133 133 133 133 133 133 133 133 133 133
-- 56,000 LB --
VFS = 150 KCAS FLD LNGTH 4,340 4,070 3,820 3,650 3,540 3,480 3,430 3,380 3,280 3,180 3,070
VSE = 156 KCAS V1 KCAS 121 119 118 117 118 118 118 118 118 118 118
VREF = 137 KCAS VR KCAS 127 126 125 124 124 124 124 124 124 124 124
MAX TEMP = 50°C V2 KCAS 132 132 132 132 132 132 132 132 132 132 132
-- 54,000 LB --
VFS = 147 KCAS FLD LNGTH 4,150 3,890 3,700 3,580 3,480 3,430 3,370 3,320 3,230 3,120 3,020
VSE = 153 KCAS V1 KCAS 119 118 117 117 118 118 118 118 118 118 118
VREF = 135 KCAS VR KCAS 125 125 124 123 123 123 123 123 123 123 123
MAX TEMP = 50°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
-- 52,000 LB --
VFS = 144 KCAS FLD LNGTH 4,010 3,760 3,630 3,520 3,420 3,370 3,320 3,270 3,170 3,070 2,970
VSE = 150 KCAS V1 KCAS 118 117 117 118 118 118 118 118 118 118 119
VREF = 132 KCAS VR KCAS 125 124 124 123 122 122 122 122 122 122 122
MAX TEMP = 50°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
-- 50,000 LB --
VFS = 142 KCAS FLD LNGTH 3,860 3,670 3,560 3,450 3,360 3,310 3,260 3,210 3,120 3,020 2,920
VSE = 147 KCAS V1 KCAS 118 117 117 118 118 118 118 118 119 119 119
VREF = 130 KCAS VR KCAS 125 124 123 122 122 122 122 122 122 122 122
MAX TEMP = 50°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
-- 48,000 LB --
VFS = 139 KCAS FLD LNGTH 3,720 3,600 3,490 3,390 3,300 3,250 3,200 3,150 3,060 2,970 2,870
VSE = 144 KCAS V1 KCAS 117 117 118 118 119 119 119 119 119 119 119
VREF = 127 KCAS VR KCAS 124 124 123 122 121 121 121 121 121 121 121
MAX TEMP = 50°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
-- 46,000 LB --
VFS = 136 KCAS FLD LNGTH 3,640 3,530 3,420 3,330 3,240 3,190 3,140 3,100 3,010 2,910 2,820
VSE = 141 KCAS V1 KCAS 117 118 118 119 119 119 119 119 119 119 120
VREF = 124 KCAS VR KCAS 124 123 122 122 121 121 121 121 121 121 121
MAX TEMP = 50°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
CAUTION: DO NOT REDUCE TAKEOFF EPR BY MORE THAN .15 OR BELOW A MINIMUM VALUE OF 1.56.
NOTES: HEADWIND: Increase available field length 2% for each 5 knots (up to 40 knots).
TAILWIND: Not permitted using this data at this pressure altitude.
UPHILL SLOPE: Decrease available field length 20% for each 1% (up to 2%).
DOWNHILL SLOPE: Not permitted using this data at this pressure altitude.
GROUND SPOILERS INOP: Decrease available field length 800 feet.

NON-SP GIV PERFORMANCE REVISION 24 (RE-ISSUE)

Page PA - 6 (NON-SP GIV AIRPLANES ONLY) Mar 17/10
Quick Reference Handbook
Non-SP GIV Takeoff Planning:
Flaps 20° - APA 500 Feet AFM APP. A

TAKEOFF PLANNING CHART

NON-SP GIV AIRPORT PRESSURE ALTITUDE = 500 FEET TAKEOFF FLAP 20°
73,200 LB MTOGW OAT (°C) 49 45 40 35 30 25 20 15 5 -5 -15
OAT (°F) 120 113 104 95 86 77 68 59 41 23 5
RATED EPR 1.59 1.62 1.64 1.67 1.70 1.71 1.71 1.71 1.70 1.70 1.70
-- 73,200 LB --
VFS = 171 KCAS FLD LNGTH 7,630 7,120 6,590 6,140 5,760 5,590 5,500 5,410 5,280 5,100 4,930
VSE = 178 KCAS V1 KCAS 144 143 141 139 138 138 138 138 138 138 138
VREF = 157 KCAS VR KCAS 144 144 144 144 144 144 144 144 144 144 144
MAX TEMP = 49°C V2 KCAS 148 148 148 148 148 148 148 148 148 148 148
-- 72,000 LB --
VFS = 170 KCAS FLD LNGTH 7,320 6,860 6,360 5,930 5,570 5,410 5,320 5,240 5,110 4,940 4,770
VSE = 177 KCAS V1 KCAS 142 141 139 138 136 136 136 136 136 136 137
VREF = 156 KCAS VR KCAS 143 143 143 143 142 142 142 142 142 142 142
MAX TEMP = 49°C V2 KCAS 147 147 147 147 147 147 147 147 147 147 147
-- 70,000 LB --
VFS = 167 KCAS FLD LNGTH 6,870 6,450 6,000 5,610 5,270 5,120 5,030 4,950 4,830 4,670 4,510
VSE = 174 KCAS V1 KCAS 140 138 136 135 134 133 133 133 134 134 134
VREF = 154 KCAS VR KCAS 141 141 141 141 140 140 140 140 140 140 140
MAX TEMP = 49°C V2 KCAS 145 145 145 145 145 145 145 145 145 145 145
-- 68,000 LB --
VFS = 165 KCAS FLD LNGTH 6,440 6,060 5,650 5,290 4,970 4,830 4,750 4,680 4,560 4,410 4,260
VSE = 172 KCAS V1 KCAS 136 135 134 132 131 131 131 131 131 131 131
VREF = 151 KCAS VR KCAS 139 139 139 138 138 137 137 137 137 137 137
MAX TEMP = 49°C V2 KCAS 143 143 143 143 143 143 143 143 143 143 143
-- 66,000 LB --
VFS = 162 KCAS FLD LNGTH 6,040 5,690 5,320 4,980 4,690 4,560 4,480 4,410 4,310 4,160 4,020
VSE = 169 KCAS V1 KCAS 134 132 131 129 128 128 128 128 128 128 128
VREF = 149 KCAS VR KCAS 137 137 136 136 135 135 135 135 135 135 135
MAX TEMP = 49°C V2 KCAS 141 141 141 141 141 141 141 141 141 141 141
-- 64,000 LB --
VFS = 160 KCAS FLD LNGTH 5,660 5,350 5,000 4,690 4,420 4,300 4,230 4,160 4,060 3,920 3,790
VSE = 166 KCAS V1 KCAS 131 130 128 127 125 125 125 125 125 125 126
VREF = 147 KCAS VR KCAS 135 134 134 133 133 132 132 132 132 132 132
MAX TEMP = 49°C V2 KCAS 139 139 139 139 139 139 139 139 139 139 139
-- 62,000 LB --
VFS = 157 KCAS FLD LNGTH 5,300 5,020 4,700 4,410 4,160 4,050 3,980 3,920 3,820 3,690 3,570
VSE = 164 KCAS V1 KCAS 128 127 125 124 123 122 122 122 123 123 123
VREF = 144 KCAS VR KCAS 132 132 131 131 130 130 130 130 130 130 130
MAX TEMP = 49°C V2 KCAS 137 137 137 137 137 137 137 137 137 137 137
-- 60,000 LB --
VFS = 155 KCAS FLD LNGTH 4,960 4,710 4,410 4,150 3,910 3,810 3,740 3,680 3,590 3,480 3,360
VSE = 161 KCAS V1 KCAS 125 124 122 121 120 119 119 119 120 120 120
VREF = 142 KCAS VR KCAS 130 130 129 128 128 127 127 127 127 127 127
MAX TEMP = 49°C V2 KCAS 135 135 135 135 135 135 135 135 135 135 135
CAUTION: DO NOT REDUCE TAKEOFF EPR BY MORE THAN .15 OR BELOW A MINIMUM VALUE OF 1.56.
NOTES: HEADWIND: Increase available field length 2% for each 5 knots (up to 40 knots).
TAILWIND: Not permitted using this data at this pressure altitude.
UPHILL SLOPE: Decrease available field length 20% for each 1% (up to 2%).
DOWNHILL SLOPE: Not permitted using this data at this pressure altitude.
GROUND SPOILERS INOP: Decrease available field length 800 feet.

REVISION 24 (RE-ISSUE) NON-SP GIV PERFORMANCE

Mar 17/10 (NON-SP GIV AIRPLANES ONLY) Page PA - 7
 Quick Reference Handbook
Non-SP GIV Takeoff Planning: Flaps 20° - APA 500 Feet, ctd…
AFM APP. A

TAKEOFF PLANNING CHART

NON-SP GIV AIRPORT PRESSURE ALTITUDE = 500 FEET TAKEOFF FLAP 20°
73,200 LB MTOGW OAT (°C) 49 45 40 35 30 25 20 15 5 -5 -15
OAT (°F) 120 113 104 95 86 77 68 59 41 23 5
RATED EPR 1.59 1.62 1.64 1.67 1.70 1.71 1.71 1.71 1.70 1.70 1.70
-- 58,000 LB --
VFS = 152 KCAS FLD LNGTH 4,700 4,460 4,190 3,940 3,710 3,620 3,560 3,500 3,410 3,300 3,190
VSE = 158 KCAS V1 KCAS 123 122 120 119 118 117 117 117 118 118 118
VREF = 140 KCAS VR KCAS 128 128 127 127 126 126 126 126 126 126 126
MAX TEMP = 49°C V2 KCAS 133 133 133 133 133 133 133 133 133 133 133
-- 56,000 LB --
VFS = 150 KCAS FLD LNGTH 4,450 4,220 3,970 3,750 3,620 3,550 3,500 3,450 3,350 3,240 3,130
VSE = 156 KCAS V1 KCAS 121 120 118 117 117 117 118 118 118 118 118
VREF = 137 KCAS VR KCAS 127 126 125 125 124 124 124 124 124 124 124
MAX TEMP = 49°C V2 KCAS 132 132 132 132 132 132 132 132 132 132 132
-- 54,000 LB --
VFS = 147 KCAS FLD LNGTH 4,250 4,040 3,810 3,670 3,560 3,490 3,440 3,390 3,290 3,190 3,080
VSE = 153 KCAS V1 KCAS 119 118 117 117 118 118 118 118 118 118 118
VREF = 135 KCAS VR KCAS 126 125 124 124 123 123 123 123 123 123 123
MAX TEMP = 49°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
-- 52,000 LB --
VFS = 144 KCAS FLD LNGTH 4,100 3,900 3,720 3,600 3,500 3,430 3,380 3,330 3,230 3,130 3,030
VSE = 150 KCAS V1 KCAS 119 117 117 117 118 118 118 118 118 118 119
VREF = 132 KCAS VR KCAS 125 125 124 123 123 122 122 122 122 122 122
MAX TEMP = 49°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
-- 50,000 LB --
VFS = 142 KCAS FLD LNGTH 3,950 3,780 3,650 3,540 3,440 3,370 3,320 3,270 3,180 3,080 2,970
VSE = 147 KCAS V1 KCAS 118 117 117 118 118 118 118 118 118 119 119
VREF = 130 KCAS VR KCAS 125 124 124 123 122 122 122 122 122 122 122
MAX TEMP = 49°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
-- 48,000 LB --
VFS = 139 KCAS FLD LNGTH 3,800 3,690 3,580 3,470 3,370 3,310 3,260 3,210 3,120 3,020 2,920
VSE = 144 KCAS V1 KCAS 117 117 117 118 118 119 119 119 119 119 119
VREF = 127 KCAS VR KCAS 124 124 123 122 122 121 121 121 121 121 121
MAX TEMP = 49°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
-- 46,000 LB --
VFS = 136 KCAS FLD LNGTH 3,710 3,610 3,500 3,400 3,310 3,250 3,200 3,150 3,060 2,970 2,870
VSE = 141 KCAS V1 KCAS 117 117 118 118 119 119 119 119 119 119 119
VREF = 124 KCAS VR KCAS 124 123 123 122 121 121 121 121 121 121 121
MAX TEMP = 49°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
CAUTION: DO NOT REDUCE TAKEOFF EPR BY MORE THAN .15 OR BELOW A MINIMUM VALUE OF 1.56.
NOTES: HEADWIND: Increase available field length 2% for each 5 knots (up to 40 knots).
TAILWIND: Not permitted using this data at this pressure altitude.
UPHILL SLOPE: Decrease available field length 20% for each 1% (up to 2%).
DOWNHILL SLOPE: Not permitted using this data at this pressure altitude.
GROUND SPOILERS INOP: Decrease available field length 800 feet.

NON-SP GIV PERFORMANCE REVISION 24 (RE-ISSUE)

Page PA - 8 (NON-SP GIV AIRPLANES ONLY) Mar 17/10
Quick Reference Handbook
Non-SP GIV Takeoff Planning:
Flaps 20° - APA 1000 Feet AFM APP. A

TAKEOFF PLANNING CHART

NON-SP GIV AIRPORT PRESSURE ALTITUDE = 1,000 FEET TAKEOFF FLAP 20°
73,200 LB MTOGW OAT (°C) 48 45 40 35 30 25 20 15 5 -5 -15
OAT (°F) 118 113 104 95 86 77 68 59 41 23 5
RATED EPR 1.60 1.62 1.64 1.66 1.70 1.71 1.71 1.71 1.71 1.71 1.71
-- 73,200 LB --
VFS = 171 KCAS FLD LNGTH 7,860 7,460 6,870 6,390 5,980 5,740 5,630 5,540 5,410 5,230 5,050
VSE = 178 KCAS V1 KCAS 144 143 141 140 138 138 138 138 138 138 138
VREF = 157 KCAS VR KCAS 145 145 145 144 144 144 144 144 144 144 144
MAX TEMP = 48°C V2 KCAS 149 149 149 149 149 149 149 149 149 149 149
-- 72,000 LB --
VFS = 170 KCAS FLD LNGTH 7,520 7,170 6,630 6,170 5,790 5,560 5,450 5,360 5,240 5,060 4,880
VSE = 177 KCAS V1 KCAS 143 142 140 138 137 136 136 136 136 137 137
VREF = 156 KCAS VR KCAS 143 143 143 143 143 142 142 142 142 142 142
MAX TEMP = 48°C V2 KCAS 147 147 147 147 147 147 147 147 147 147 147
-- 70,000 LB --
VFS = 167 KCAS FLD LNGTH 7,060 6,730 6,240 5,830 5,470 5,260 5,160 5,080 4,950 4,790 4,620
VSE = 174 KCAS V1 KCAS 140 139 137 135 134 134 134 134 134 134 134
VREF = 154 KCAS VR KCAS 141 141 141 141 140 140 140 140 140 140 140
MAX TEMP = 48°C V2 KCAS 145 145 145 145 145 145 145 145 145 145 145
-- 68,000 LB --
VFS = 165 KCAS FLD LNGTH 6,610 6,320 5,880 5,500 5,160 4,960 4,870 4,790 4,680 4,520 4,360
VSE = 172 KCAS V1 KCAS 137 136 134 133 131 131 131 131 131 131 131
VREF = 151 KCAS VR KCAS 139 139 139 138 138 138 137 137 137 137 137
MAX TEMP = 48°C V2 KCAS 143 143 143 143 143 143 143 143 143 143 143
-- 66,000 LB --
VFS = 162 KCAS FLD LNGTH 6,190 5,930 5,530 5,180 4,870 4,680 4,590 4,520 4,410 4,260 4,120
VSE = 169 KCAS V1 KCAS 134 133 131 130 129 128 128 128 128 128 128
VREF = 149 KCAS VR KCAS 137 137 137 136 135 135 135 135 135 135 135
MAX TEMP = 48°C V2 KCAS 141 141 141 141 141 141 141 141 141 141 141
-- 64,000 LB --
VFS = 160 KCAS FLD LNGTH 5,800 5,560 5,200 4,870 4,580 4,410 4,330 4,260 4,160 4,020 3,880
VSE = 166 KCAS V1 KCAS 131 130 129 127 126 125 125 125 126 126 126
VREF = 147 KCAS VR KCAS 135 135 134 134 133 133 133 133 133 133 133
MAX TEMP = 48°C V2 KCAS 139 139 139 139 139 139 139 139 139 139 139
-- 62,000 LB --
VFS = 157 KCAS FLD LNGTH 5,430 5,220 4,880 4,580 4,320 4,150 4,080 4,010 3,910 3,780 3,650
VSE = 164 KCAS V1 KCAS 128 127 126 124 123 122 122 122 123 123 123
VREF = 144 KCAS VR KCAS 132 132 132 131 130 130 130 130 130 130 130
MAX TEMP = 48°C V2 KCAS 137 137 137 137 137 137 137 137 137 137 137
-- 60,000 LB --
VFS = 155 KCAS FLD LNGTH 5,080 4,890 4,580 4,310 4,060 3,910 3,830 3,770 3,680 3,560 3,440
VSE = 161 KCAS V1 KCAS 125 124 123 122 120 120 120 120 120 120 120
VREF = 142 KCAS VR KCAS 130 130 129 129 128 128 128 128 128 128 128
MAX TEMP = 48°C V2 KCAS 135 135 135 135 135 135 135 135 135 135 135
CAUTION: DO NOT REDUCE TAKEOFF EPR BY MORE THAN .15 OR BELOW A MINIMUM VALUE OF 1.56.
NOTES: HEADWIND: Increase available field length 2% for each 5 knots (up to 40 knots).
TAILWIND: Not permitted using this data at this pressure altitude.
UPHILL SLOPE: Decrease available field length 20% for each 1% (up to 2%).
DOWNHILL SLOPE: Not permitted using this data at this pressure altitude.
GROUND SPOILERS INOP: Decrease available field length 800 feet.

REVISION 24 (RE-ISSUE) NON-SP GIV PERFORMANCE

Mar 17/10 (NON-SP GIV AIRPLANES ONLY) Page PA - 9
 Quick Reference Handbook
Non-SP GIV Takeoff Planning: Flaps 20° - APA 1000 Feet, ctd…
AFM APP. A

TAKEOFF PLANNING CHART

NON-SP GIV AIRPORT PRESSURE ALTITUDE = 1,000 FEET TAKEOFF FLAP 20°
73,200 LB MTOGW OAT (°C) 48 45 40 35 30 25 20 15 5 -5 -15
OAT (°F) 118 113 104 95 86 77 68 59 41 23 5
RATED EPR 1.60 1.62 1.64 1.66 1.70 1.71 1.71 1.71 1.71 1.71 1.71
-- 58,000 LB --
VFS = 152 KCAS FLD LNGTH 4,820 4,630 4,350 4,080 3,850 3,710 3,640 3,580 3,500 3,380 3,260
VSE = 158 KCAS V1 KCAS 123 122 121 119 118 117 117 117 118 118 118
VREF = 140 KCAS VR KCAS 128 128 127 127 126 126 126 126 126 126 126
MAX TEMP = 48°C V2 KCAS 133 133 133 133 133 133 133 133 133 133 133
-- 56,000 LB --
VFS = 150 KCAS FLD LNGTH 4,560 4,380 4,120 3,870 3,710 3,630 3,570 3,510 3,410 3,300 3,190
VSE = 156 KCAS V1 KCAS 121 120 119 117 117 117 117 118 118 118 118
VREF = 137 KCAS VR KCAS 127 126 126 125 124 124 124 124 124 124 124
MAX TEMP = 48°C V2 KCAS 132 132 132 132 132 132 132 132 132 132 132
-- 54,000 LB --
VFS = 147 KCAS FLD LNGTH 4,350 4,190 3,940 3,760 3,650 3,560 3,510 3,450 3,360 3,250 3,140
VSE = 153 KCAS V1 KCAS 119 119 117 117 117 118 118 118 118 118 118
VREF = 135 KCAS VR KCAS 126 125 125 124 123 123 123 123 123 123 123
MAX TEMP = 48°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
-- 52,000 LB --
VFS = 144 KCAS FLD LNGTH 4,200 4,040 3,830 3,690 3,580 3,500 3,450 3,390 3,300 3,190 3,080
VSE = 150 KCAS V1 KCAS 119 118 117 117 118 118 118 118 118 118 118
VREF = 132 KCAS VR KCAS 125 125 124 124 123 122 122 122 122 122 122
MAX TEMP = 48°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
-- 50,000 LB --
VFS = 142 KCAS FLD LNGTH 4,050 3,900 3,740 3,620 3,520 3,440 3,390 3,330 3,240 3,140 3,030
VSE = 147 KCAS V1 KCAS 118 117 117 117 118 118 118 118 118 118 119
VREF = 130 KCAS VR KCAS 125 125 124 123 122 122 122 122 122 122 122
MAX TEMP = 48°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
-- 48,000 LB --
VFS = 139 KCAS FLD LNGTH 3,900 3,800 3,660 3,550 3,450 3,380 3,320 3,270 3,180 3,080 2,980
VSE = 144 KCAS V1 KCAS 117 117 117 118 118 118 119 119 119 119 119
VREF = 127 KCAS VR KCAS 124 124 123 123 122 122 121 121 121 121 121
MAX TEMP = 48°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
-- 46,000 LB --
VFS = 136 KCAS FLD LNGTH 3,780 3,700 3,590 3,480 3,390 3,320 3,260 3,210 3,120 3,020 2,920
VSE = 141 KCAS V1 KCAS 117 117 117 118 118 119 119 119 119 119 119
VREF = 124 KCAS VR KCAS 124 124 123 122 121 121 121 121 121 121 121
MAX TEMP = 48°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
CAUTION: DO NOT REDUCE TAKEOFF EPR BY MORE THAN .15 OR BELOW A MINIMUM VALUE OF 1.56.
NOTES: HEADWIND: Increase available field length 2% for each 5 knots (up to 40 knots).
TAILWIND: Not permitted using this data at this pressure altitude.
UPHILL SLOPE: Decrease available field length 20% for each 1% (up to 2%).
DOWNHILL SLOPE: Not permitted using this data at this pressure altitude.
GROUND SPOILERS INOP: Decrease available field length 800 feet.

NON-SP GIV PERFORMANCE REVISION 24 (RE-ISSUE)

Page PA - 10 (NON-SP GIV AIRPLANES ONLY) Mar 17/10
Quick Reference Handbook
Non-SP GIV Takeoff Planning:
Flaps 20° - APA 2000 Feet AFM APP. A

TAKEOFF PLANNING CHART

NON-SP GIV AIRPORT PRESSURE ALTITUDE = 2,000 FEET TAKEOFF FLAP 20°
73,200 LB MTOGW OAT (°C) 45 40 35 30 25 20 15 10 0 -10 -19
OAT (°F) 113 104 95 86 77 68 59 50 32 14 -2
RATED EPR 1.62 1.64 1.66 1.69 1.71 1.72 1.72 1.72 1.72 1.72 1.72
-- 73,200 LB --
VFS = 171 KCAS FLD LNGTH 8,250 7,480 6,940 6,470 6,130 5,990 5,850 5,730 5,590 5,400 5,230
VSE = 178 KCAS V1 KCAS 144 143 141 140 138 138 138 138 138 138 139
VREF = 157 KCAS VR KCAS 145 145 145 144 144 144 144 144 144 144 144
MAX TEMP = 46°C V2 KCAS 149 149 149 149 149 149 149 149 149 149 149
-- 72,000 LB --
VFS = 170 KCAS FLD LNGTH 7,870 7,210 6,690 6,260 5,930 5,790 5,660 5,550 5,410 5,220 5,060
VSE = 177 KCAS V1 KCAS 143 141 139 138 137 137 137 136 137 137 137
VREF = 156 KCAS VR KCAS 143 143 143 143 143 143 143 142 142 142 142
MAX TEMP = 46°C V2 KCAS 147 147 147 147 147 147 147 147 147 147 147
-- 70,000 LB --
VFS = 167 KCAS FLD LNGTH 7,350 6,780 6,310 5,910 5,610 5,480 5,360 5,250 5,120 4,940 4,790
VSE = 174 KCAS V1 KCAS 140 138 137 135 134 134 134 134 134 134 134
VREF = 154 KCAS VR KCAS 141 141 141 141 140 140 140 140 140 140 140
MAX TEMP = 46°C V2 KCAS 145 145 145 145 145 145 145 145 145 145 145
-- 68,000 LB --
VFS = 165 KCAS FLD LNGTH 6,880 6,370 5,940 5,570 5,290 5,170 5,060 4,950 4,830 4,670 4,520
VSE = 172 KCAS V1 KCAS 137 135 134 132 132 131 131 131 131 131 132
VREF = 151 KCAS VR KCAS 139 139 139 138 138 138 138 138 138 138 138
MAX TEMP = 46°C V2 KCAS 143 143 143 143 143 143 143 143 143 143 143
-- 66,000 LB --
VFS = 162 KCAS FLD LNGTH 6,440 5,980 5,590 5,250 4,990 4,880 4,770 4,670 4,550 4,400 4,260
VSE = 169 KCAS V1 KCAS 134 132 131 130 129 129 129 128 129 129 129
VREF = 149 KCAS VR KCAS 137 137 136 136 135 135 135 135 135 135 135
MAX TEMP = 46°C V2 KCAS 141 141 141 141 141 141 141 141 141 141 141
-- 64,000 LB --
VFS = 160 KCAS FLD LNGTH 6,030 5,610 5,260 4,940 4,700 4,590 4,490 4,400 4,290 4,150 4,010
VSE = 166 KCAS V1 KCAS 131 130 128 127 126 126 126 126 126 126 126
VREF = 147 KCAS VR KCAS 135 135 134 133 133 133 133 133 133 133 133
MAX TEMP = 46°C V2 KCAS 139 139 139 139 139 139 139 139 139 139 139
-- 62,000 LB --
VFS = 157 KCAS FLD LNGTH 5,640 5,270 4,940 4,650 4,420 4,320 4,230 4,140 4,040 3,900 3,780
VSE = 164 KCAS V1 KCAS 128 127 126 124 123 123 123 123 123 123 123
VREF = 145 KCAS VR KCAS 133 132 132 131 130 130 130 130 130 130 130
MAX TEMP = 46°C V2 KCAS 137 137 137 137 137 137 137 137 137 137 137
-- 60,000 LB --
VFS = 155 KCAS FLD LNGTH 5,280 4,940 4,640 4,370 4,150 4,060 3,980 3,890 3,800 3,670 3,550
VSE = 161 KCAS V1 KCAS 125 124 123 121 120 120 120 120 120 120 120
VREF = 142 KCAS VR KCAS 130 130 129 128 128 128 128 128 128 128 128
MAX TEMP = 46°C V2 KCAS 135 135 135 135 135 135 135 135 135 135 135
CAUTION: DO NOT REDUCE TAKEOFF EPR BY MORE THAN .15 OR BELOW A MINIMUM VALUE OF 1.56.
NOTES: HEADWIND: Increase available field length 2% for each 5 knots (up to 40 knots).
TAILWIND: Not permitted using this data at this pressure altitude.
UPHILL SLOPE: Decrease available field length 20% for each 1% (up to 2%).
DOWNHILL SLOPE: Not permitted using this data at this pressure altitude.
GROUND SPOILERS INOP: Decrease available field length 800 feet.

REVISION 24 (RE-ISSUE) NON-SP GIV PERFORMANCE

Mar 17/10 (NON-SP GIV AIRPLANES ONLY) Page PA - 11
 Quick Reference Handbook
Non-SP GIV Takeoff Planning: Flaps 20° - APA 2000 Feet, ctd…
AFM APP. A

TAKEOFF PLANNING CHART

NON-SP GIV AIRPORT PRESSURE ALTITUDE = 2,000 FEET TAKEOFF FLAP 20°
73,200 LB MTOGW OAT (°C) 45 40 35 30 25 20 15 10 0 -10 -19
OAT (°F) 113 104 95 86 77 68 59 50 32 14 -2
RATED EPR 1.62 1.64 1.66 1.69 1.71 1.72 1.72 1.72 1.72 1.72 1.72
-- 58,000 LB --
VFS = 152 KCAS FLD LNGTH 5,000 4,680 4,400 4,140 3,940 3,860 3,780 3,700 3,610 3,480 3,370
VSE = 158 KCAS V1 KCAS 123 122 121 119 118 118 118 118 118 118 118
VREF = 140 KCAS VR KCAS 129 128 127 127 126 126 126 126 126 126 126
MAX TEMP = 46°C V2 KCAS 133 133 133 133 133 133 133 133 133 133 133
-- 56,000 LB --
VFS = 150 KCAS FLD LNGTH 4,730 4,430 4,170 3,940 3,790 3,730 3,660 3,600 3,490 3,380 3,270
VSE = 156 KCAS V1 KCAS 121 120 118 117 117 117 117 117 117 117 118
VREF = 137 KCAS VR KCAS 127 126 126 125 124 124 124 124 124 124 124
MAX TEMP = 46°C V2 KCAS 132 132 132 132 132 132 132 132 132 132 132
-- 54,000 LB --
VFS = 147 KCAS FLD LNGTH 4,520 4,240 4,000 3,830 3,730 3,660 3,600 3,540 3,430 3,320 3,220
VSE = 153 KCAS V1 KCAS 120 118 117 117 117 117 117 118 118 118 118
VREF = 135 KCAS VR KCAS 126 125 124 124 123 123 123 123 123 123 123
MAX TEMP = 46°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
-- 52,000 LB --
VFS = 144 KCAS FLD LNGTH 4,360 4,090 3,880 3,760 3,660 3,600 3,530 3,470 3,370 3,260 3,160
VSE = 150 KCAS V1 KCAS 119 118 117 117 117 117 118 118 118 118 118
VREF = 132 KCAS VR KCAS 125 125 124 123 123 123 123 123 123 123 123
MAX TEMP = 46°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
-- 50,000 LB --
VFS = 142 KCAS FLD LNGTH 4,200 3,960 3,800 3,690 3,590 3,530 3,470 3,410 3,310 3,200 3,110
VSE = 147 KCAS V1 KCAS 118 117 117 117 118 118 118 118 118 118 118
VREF = 130 KCAS VR KCAS 125 124 124 123 122 122 122 122 122 122 122
MAX TEMP = 46°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
-- 48,000 LB --
VFS = 139 KCAS FLD LNGTH 4,050 3,850 3,730 3,620 3,520 3,460 3,410 3,350 3,250 3,140 3,050
VSE = 144 KCAS V1 KCAS 118 117 117 118 118 118 118 118 118 119 119
VREF = 127 KCAS VR KCAS 125 124 123 123 122 122 122 122 122 122 122
MAX TEMP = 46°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
-- 46,000 LB --
VFS = 136 KCAS FLD LNGTH 3,900 3,770 3,650 3,550 3,460 3,400 3,340 3,290 3,190 3,090 2,990
VSE = 141 KCAS V1 KCAS 117 117 117 118 118 118 119 119 119 119 119
VREF = 124 KCAS VR KCAS 124 123 123 122 122 121 121 121 121 121 121
MAX TEMP = 46°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
CAUTION: DO NOT REDUCE TAKEOFF EPR BY MORE THAN .15 OR BELOW A MINIMUM VALUE OF 1.56.
NOTES: HEADWIND: Increase available field length 2% for each 5 knots (up to 40 knots).
TAILWIND: Not permitted using this data at this pressure altitude.
UPHILL SLOPE: Decrease available field length 20% for each 1% (up to 2%).
DOWNHILL SLOPE: Not permitted using this data at this pressure altitude.
GROUND SPOILERS INOP: Decrease available field length 800 feet.

NON-SP GIV PERFORMANCE REVISION 24 (RE-ISSUE)

Page PA - 12 (NON-SP GIV AIRPLANES ONLY) Mar 17/10
Quick Reference Handbook
Non-SP GIV Takeoff Planning:
Flaps 20° - APA 4000 Feet AFM APP. A

TAKEOFF PLANNING CHART

NON-SP GIV AIRPORT PRESSURE ALTITUDE = 4,000 FEET TAKEOFF FLAP 20°
73,200 LB MTOGW OAT (°C) 40 35 30 25 20 15 10 5 -5 -15 -23
OAT (°F) 104 95 86 77 68 59 50 41 23 5 -9
RATED EPR 1.63 1.66 1.69 1.71 1.72 1.74 1.74 1.74 1.74 1.74 1.74
-- 73,200 LB --
VFS = 173 KCAS FLD LNGTH ****** ****** ****** 7,290 6,990 6,740 6,520 6,410 6,170 5,960 5,790
VSE = 180 KCAS V1 KCAS ****** ****** ****** 142 141 141 140 140 140 140 140
VREF = 157 KCAS VR KCAS ****** ****** ****** 146 145 145 145 145 145 145 145
MAX TEMP = 25°C V2 KCAS ****** ****** ****** 150 150 150 150 150 150 150 150
-- 72,000 LB --
VFS = 171 KCAS FLD LNGTH ****** 8,050 7,470 7,040 6,750 6,510 6,310 6,200 5,970 5,760 5,600
VSE = 178 KCAS V1 KCAS ****** 143 141 140 139 139 139 139 139 139 139
VREF = 156 KCAS VR KCAS ****** 144 144 144 144 144 144 144 144 144 144
MAX TEMP = 38°C V2 KCAS ****** 148 148 148 148 148 148 148 148 148 148
-- 70,000 LB --
VFS = 169 KCAS FLD LNGTH 8,260 7,570 7,040 6,640 6,370 6,150 5,960 5,870 5,650 5,450 5,300
VSE = 176 KCAS V1 KCAS 142 140 138 137 137 136 136 136 136 136 136
VREF = 154 KCAS VR KCAS 142 142 142 142 142 142 142 142 142 142 142
MAX TEMP = 42°C V2 KCAS 146 146 146 146 146 146 146 146 146 146 146
-- 68,000 LB --
VFS = 166 KCAS FLD LNGTH 7,670 7,090 6,610 6,250 6,010 5,800 5,630 5,540 5,330 5,140 5,000
VSE = 173 KCAS V1 KCAS 139 137 136 135 134 134 133 133 133 133 133
VREF = 151 KCAS VR KCAS 140 140 140 140 140 139 139 139 139 139 139
MAX TEMP = 42°C V2 KCAS 144 144 144 144 144 144 144 144 144 144 144
-- 66,000 LB --
VFS = 164 KCAS FLD LNGTH 7,170 6,650 6,210 5,890 5,660 5,470 5,300 5,220 5,020 4,850 4,710
VSE = 171 KCAS V1 KCAS 136 134 133 132 131 131 130 130 130 130 130
VREF = 149 KCAS VR KCAS 138 138 138 137 137 137 137 137 137 137 137
MAX TEMP = 42°C V2 KCAS 142 142 142 142 142 142 142 142 142 142 142
-- 64,000 LB --
VFS = 161 KCAS FLD LNGTH 6,700 6,230 5,830 5,540 5,330 5,150 4,990 4,910 4,730 4,570 4,440
VSE = 168 KCAS V1 KCAS 133 131 130 129 128 128 128 128 128 128 128
VREF = 147 KCAS VR KCAS 136 136 135 135 135 134 134 134 134 134 134
MAX TEMP = 42°C V2 KCAS 140 140 140 140 140 140 140 140 140 140 140
-- 62,000 LB --
VFS = 159 KCAS FLD LNGTH 6,270 5,840 5,480 5,200 5,010 4,840 4,700 4,620 4,450 4,300 4,180
VSE = 165 KCAS V1 KCAS 130 129 127 126 126 125 125 125 125 125 125
VREF = 145 KCAS VR KCAS 134 133 133 132 132 132 132 132 132 132 132
MAX TEMP = 42°C V2 KCAS 138 138 138 138 138 138 138 138 138 138 138
-- 60,000 LB --
VFS = 156 KCAS FLD LNGTH 5,850 5,470 5,140 4,880 4,700 4,550 4,410 4,340 4,180 4,040 3,920
VSE = 163 KCAS V1 KCAS 127 126 124 123 123 122 122 122 122 122 122
VREF = 142 KCAS VR KCAS 131 131 130 130 130 129 129 129 129 129 129
MAX TEMP = 42°C V2 KCAS 135 135 135 135 135 135 135 135 135 135 135
CAUTION: DO NOT REDUCE TAKEOFF EPR BY MORE THAN .15 OR BELOW A MINIMUM VALUE OF 1.56.
NOTES: HEADWIND: Increase available field length 2% for each 5 knots (up to 40 knots).
TAILWIND: Not permitted using this data at this pressure altitude.
UPHILL SLOPE: Decrease available field length 20% for each 1% (up to 2%).
DOWNHILL SLOPE: Not permitted using this data at this pressure altitude.
GROUND SPOILERS INOP: Decrease available field length 800 feet.

REVISION 24 (RE-ISSUE) NON-SP GIV PERFORMANCE

Mar 17/10 (NON-SP GIV AIRPLANES ONLY) Page PA - 13
 Quick Reference Handbook
Non-SP GIV Takeoff Planning: Flaps 20° - APA 4000 Feet, ctd…
AFM APP. A

TAKEOFF PLANNING CHART

NON-SP GIV AIRPORT PRESSURE ALTITUDE = 4,000 FEET TAKEOFF FLAP 20°
73,200 LB MTOGW OAT (°C) 40 35 30 25 20 15 10 5 -5 -15 -23
OAT (°F) 104 95 86 77 68 59 50 41 23 5 -9
RATED EPR 1.63 1.66 1.69 1.71 1.72 1.74 1.74 1.74 1.74 1.74 1.74
-- 58,000 LB --
VFS = 154 KCAS FLD LNGTH 5,510 5,150 4,850 4,610 4,440 4,290 4,170 4,100 3,950 3,810 3,700
VSE = 160 KCAS V1 KCAS 125 123 122 121 120 120 119 120 119 120 120
VREF = 140 KCAS VR KCAS 129 129 128 128 128 127 127 127 127 127 127
MAX TEMP = 42°C V2 KCAS 134 134 134 134 134 134 134 134 134 134 134
-- 56,000 LB --
VFS = 151 KCAS FLD LNGTH 5,170 4,850 4,570 4,340 4,180 4,050 3,930 3,870 3,730 3,600 3,500
VSE = 157 KCAS V1 KCAS 122 121 119 119 118 117 117 117 117 117 117
VREF = 137 KCAS VR KCAS 127 127 126 126 125 125 125 125 125 125 125
MAX TEMP = 42°C V2 KCAS 132 132 132 132 132 132 132 132 132 132 132
-- 54,000 LB --
VFS = 148 KCAS FLD LNGTH 4,920 4,620 4,350 4,140 4,020 3,930 3,850 3,790 3,660 3,530 3,440
VSE = 154 KCAS V1 KCAS 120 119 118 117 117 117 117 117 117 117 117
VREF = 135 KCAS VR KCAS 126 126 125 124 124 124 124 124 123 123 123
MAX TEMP = 42°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
-- 52,000 LB --
VFS = 146 KCAS FLD LNGTH 4,750 4,460 4,210 4,040 3,940 3,860 3,780 3,720 3,590 3,470 3,380
VSE = 151 KCAS V1 KCAS 120 118 117 117 117 117 117 117 117 117 118
VREF = 132 KCAS VR KCAS 126 125 125 124 124 123 123 123 123 123 123
MAX TEMP = 42°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
-- 50,000 LB --
VFS = 143 KCAS FLD LNGTH 4,580 4,300 4,080 3,960 3,870 3,780 3,710 3,650 3,520 3,410 3,310
VSE = 148 KCAS V1 KCAS 119 118 117 117 117 117 118 118 118 118 118
VREF = 130 KCAS VR KCAS 125 125 124 124 123 123 123 123 123 123 123
MAX TEMP = 42°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
-- 48,000 LB --
VFS = 140 KCAS FLD LNGTH 4,400 4,160 3,990 3,880 3,790 3,710 3,630 3,580 3,460 3,340 3,250
VSE = 145 KCAS V1 KCAS 118 117 117 117 117 118 118 118 118 118 118
VREF = 127 KCAS VR KCAS 125 124 124 123 123 123 122 122 122 122 122
MAX TEMP = 42°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
-- 46,000 LB --
VFS = 137 KCAS FLD LNGTH 4,230 4,030 3,900 3,800 3,710 3,640 3,560 3,510 3,390 3,280 3,190
VSE = 142 KCAS V1 KCAS 117 117 117 117 118 118 118 118 118 118 119
VREF = 124 KCAS VR KCAS 125 124 123 123 122 122 122 122 122 122 122
MAX TEMP = 42°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
CAUTION: DO NOT REDUCE TAKEOFF EPR BY MORE THAN .15 OR BELOW A MINIMUM VALUE OF 1.56.
NOTES: HEADWIND: Increase available field length 2% for each 5 knots (up to 40 knots).
TAILWIND: Not permitted using this data at this pressure altitude.
UPHILL SLOPE: Decrease available field length 20% for each 1% (up to 2%).
DOWNHILL SLOPE: Not permitted using this data at this pressure altitude.
GROUND SPOILERS INOP: Decrease available field length 800 feet.

NON-SP GIV PERFORMANCE REVISION 24 (RE-ISSUE)

Page PA - 14 (NON-SP GIV AIRPLANES ONLY) Mar 17/10
Quick Reference Handbook
Non-SP GIV Takeoff Planning:
Flaps 20° - APA 6000 Feet AFM APP. A

TAKEOFF PLANNING CHART

NON-SP GIV AIRPORT PRESSURE ALTITUDE = 6,000 FEET TAKEOFF FLAP 20°
73,200 LB MTOGW OAT (°C) 38 35 30 25 20 15 10 5 -5 -15 -25
OAT (°F) 101 95 86 77 68 59 50 41 23 5 -13
RATED EPR 1.64 1.65 1.68 1.71 1.72 1.73 1.74 1.74 1.75 1.75 1.75
-- 73,200 LB --
VFS = 175 KCAS FLD LNGTH ****** ****** ****** ****** ****** ****** ****** ****** 7,300 7,050 6,790
VSE = 182 KCAS V1 KCAS ****** ****** ****** ****** ****** ****** ****** ****** 143 144 144
VREF = 158 KCAS VR KCAS ****** ****** ****** ****** ****** ****** ****** ****** 147 147 147
MAX TEMP = 0°C V2 KCAS ****** ****** ****** ****** ****** ****** ****** ****** 151 151 151
-- 72,000 LB --
VFS = 174 KCAS FLD LNGTH ****** ****** ****** ****** ****** ****** ****** 7,380 7,050 6,800 6,560
VSE = 181 KCAS V1 KCAS ****** ****** ****** ****** ****** ****** ****** 142 142 142 142
VREF = 157 KCAS VR KCAS ****** ****** ****** ****** ****** ****** ****** 146 146 146 146
MAX TEMP = 9°C V2 KCAS ****** ****** ****** ****** ****** ****** ****** 150 150 150 150
-- 70,000 LB --
VFS = 171 KCAS FLD LNGTH ****** ****** ****** 8,030 7,680 7,400 7,130 6,960 6,650 6,410 6,180
VSE = 178 KCAS V1 KCAS ****** ****** ****** 141 141 140 140 139 139 139 139
VREF = 154 KCAS VR KCAS ****** ****** ****** 144 144 144 144 144 144 144 144
MAX TEMP = 26°C V2 KCAS ****** ****** ****** 148 148 148 148 148 148 148 148
-- 68,000 LB --
VFS = 169 KCAS FLD LNGTH 9,260 8,700 7,990 7,530 7,220 6,950 6,710 6,550 6,260 6,040 5,820
VSE = 175 KCAS V1 KCAS 141 141 140 138 138 137 137 136 136 136 137
VREF = 152 KCAS VR KCAS 142 142 142 142 142 141 141 141 141 141 141
MAX TEMP = 38°C V2 KCAS 146 146 146 146 146 146 146 146 146 146 146
-- 66,000 LB --
VFS = 166 KCAS FLD LNGTH 8,470 8,070 7,480 7,060 6,770 6,530 6,310 6,160 5,900 5,690 5,480
VSE = 173 KCAS V1 KCAS 139 138 137 135 135 134 134 134 134 134 134
VREF = 150 KCAS VR KCAS 139 139 139 139 139 139 139 139 139 139 139
MAX TEMP = 38°C V2 KCAS 143 143 143 143 143 143 143 143 143 143 143
-- 64,000 LB --
VFS = 163 KCAS FLD LNGTH 7,890 7,530 7,000 6,620 6,360 6,140 5,930 5,800 5,550 5,350 5,160
VSE = 170 KCAS V1 KCAS 136 135 134 133 132 131 131 131 131 131 131
VREF = 148 KCAS VR KCAS 137 137 137 137 137 137 137 136 136 136 136
MAX TEMP = 38°C V2 KCAS 141 141 141 141 141 141 141 141 141 141 141
-- 62,000 LB --
VFS = 161 KCAS FLD LNGTH 7,350 7,030 6,550 6,210 5,970 5,760 5,570 5,450 5,210 5,030 4,850
VSE = 167 KCAS V1 KCAS 133 132 131 130 129 129 128 128 128 128 128
VREF = 145 KCAS VR KCAS 135 135 135 135 134 134 134 134 134 134 134
MAX TEMP = 38°C V2 KCAS 139 139 139 139 139 139 139 139 139 139 139
-- 60,000 LB --
VFS = 158 KCAS FLD LNGTH 6,850 6,560 6,130 5,820 5,600 5,410 5,230 5,110 4,890 4,720 4,550
VSE = 165 KCAS V1 KCAS 130 129 128 127 126 126 125 125 125 125 125
VREF = 143 KCAS VR KCAS 133 133 133 132 132 132 132 131 131 131 131
MAX TEMP = 38°C V2 KCAS 137 137 137 137 137 137 137 137 137 137 137
CAUTION: DO NOT REDUCE TAKEOFF EPR BY MORE THAN .15 OR BELOW A MINIMUM VALUE OF 1.56.
NOTES: HEADWIND: Increase available field length 2% for each 5 knots (up to 40 knots).
TAILWIND: Not permitted using this data at this pressure altitude.
UPHILL SLOPE: Decrease available field length 20% for each 1% (up to 2%).
DOWNHILL SLOPE: Not permitted using this data at this pressure altitude.
GROUND SPOILERS INOP: Decrease available field length 800 feet.

REVISION 24 (RE-ISSUE) NON-SP GIV PERFORMANCE

Mar 17/10 (NON-SP GIV AIRPLANES ONLY) Page PA - 15
 Quick Reference Handbook
Non-SP GIV Takeoff Planning: Flaps 20° - APA 6000 Feet, ctd…
AFM APP. A

TAKEOFF PLANNING CHART

NON-SP GIV AIRPORT PRESSURE ALTITUDE = 6,000 FEET TAKEOFF FLAP 20°
73,200 LB MTOGW OAT (°C) 38 35 30 25 20 15 10 5 -5 -15 -25
OAT (°F) 101 95 86 77 68 59 50 41 23 5 -13
RATED EPR 1.64 1.65 1.68 1.71 1.72 1.73 1.74 1.74 1.75 1.75 1.75
-- 58,000 LB --
VFS = 156 KCAS FLD LNGTH 6,370 6,110 5,720 5,440 5,230 5,060 4,890 4,790 4,580 4,420 4,260
VSE = 162 KCAS V1 KCAS 127 126 125 124 123 123 122 122 122 122 122
VREF = 140 KCAS VR KCAS 130 130 130 130 129 129 129 129 129 129 129
MAX TEMP = 38°C V2 KCAS 134 134 134 134 134 134 134 134 134 134 134
-- 56,000 LB --
VFS = 153 KCAS FLD LNGTH 5,920 5,690 5,340 5,080 4,890 4,730 4,570 4,480 4,290 4,140 3,990
VSE = 159 KCAS V1 KCAS 124 123 122 121 120 120 119 119 119 119 119
VREF = 138 KCAS VR KCAS 128 128 127 127 127 126 126 126 126 126 126
MAX TEMP = 38°C V2 KCAS 132 132 132 132 132 132 132 132 132 132 132
-- 54,000 LB --
VFS = 150 KCAS FLD LNGTH 5,600 5,390 5,070 4,820 4,640 4,490 4,350 4,250 4,070 3,930 3,790
VSE = 156 KCAS V1 KCAS 122 121 120 119 118 118 117 117 117 117 117
VREF = 135 KCAS VR KCAS 127 126 126 125 125 125 125 125 124 124 124
MAX TEMP = 38°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
-- 52,000 LB --
VFS = 147 KCAS FLD LNGTH 5,400 5,200 4,890 4,650 4,480 4,340 4,200 4,110 3,950 3,820 3,690
VSE = 153 KCAS V1 KCAS 121 120 119 118 118 117 117 117 117 117 117
VREF = 133 KCAS VR KCAS 126 126 126 125 125 125 124 124 124 124 124
MAX TEMP = 38°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
-- 50,000 LB --
VFS = 145 KCAS FLD LNGTH 5,200 5,010 4,710 4,480 4,320 4,200 4,100 4,020 3,880 3,740 3,610
VSE = 150 KCAS V1 KCAS 120 120 118 117 117 117 117 117 117 117 117
VREF = 130 KCAS VR KCAS 126 126 125 125 124 124 124 124 124 124 124
MAX TEMP = 38°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
-- 48,000 LB --
VFS = 141 KCAS FLD LNGTH 5,000 4,820 4,530 4,320 4,190 4,100 4,010 3,940 3,800 3,670 3,540
VSE = 147 KCAS V1 KCAS 120 119 118 117 117 117 117 117 117 117 118
VREF = 128 KCAS VR KCAS 126 125 125 124 124 124 123 123 123 123 123
MAX TEMP = 38°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
-- 46,000 LB --
VFS = 138 KCAS FLD LNGTH 4,810 4,630 4,360 4,200 4,100 4,010 3,930 3,860 3,720 3,590 3,470
VSE = 144 KCAS V1 KCAS 119 118 117 117 117 117 117 117 117 118 118
VREF = 125 KCAS VR KCAS 125 125 124 124 124 123 123 123 123 123 123
MAX TEMP = 38°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
CAUTION: DO NOT REDUCE TAKEOFF EPR BY MORE THAN .15 OR BELOW A MINIMUM VALUE OF 1.56.
NOTES: HEADWIND: Increase available field length 2% for each 5 knots (up to 40 knots).
TAILWIND: Not permitted using this data at this pressure altitude.
UPHILL SLOPE: Decrease available field length 20% for each 1% (up to 2%).
DOWNHILL SLOPE: Not permitted using this data at this pressure altitude.
GROUND SPOILERS INOP: Decrease available field length 800 feet.

NON-SP GIV PERFORMANCE REVISION 24 (RE-ISSUE)

Page PA - 16 (NON-SP GIV AIRPLANES ONLY) Mar 17/10
Quick Reference Handbook
Non-SP GIV Takeoff Planning:
Flaps 20° - APA 8000 Feet AFM APP. A

TAKEOFF PLANNING CHART

NON-SP GIV AIRPORT PRESSURE ALTITUDE = 8,000 FEET TAKEOFF FLAP 20°
73,200 LB MTOGW OAT (°C) 34 30 25 20 15 10 5 0 -10 -20 -30
OAT (°F) 93 86 77 68 59 50 41 32 14 -4 -22
RATED EPR 1.66 1.68 1.70 1.71 1.72 1.73 1.74 1.75 1.75 1.75 1.75
-- 73,200 LB --
VFS = 177 KCAS FLD LNGTH ****** ****** ****** ****** ****** ****** ****** ****** ****** ****** 7,960
VSE = 184 KCAS V1 KCAS ****** ****** ****** ****** ****** ****** ****** ****** ****** ****** 148
VREF = 159 KCAS VR KCAS ****** ****** ****** ****** ****** ****** ****** ****** ****** ****** 148
MAX TEMP = -23°C V2 KCAS ****** ****** ****** ****** ****** ****** ****** ****** ****** ****** 152
-- 72,000 LB --
VFS = 176 KCAS FLD LNGTH ****** ****** ****** ****** ****** ****** ****** ****** ****** 7,970 7,670
VSE = 183 KCAS V1 KCAS ****** ****** ****** ****** ****** ****** ****** ****** ****** 145 146
VREF = 158 KCAS VR KCAS ****** ****** ****** ****** ****** ****** ****** ****** ****** 147 147
MAX TEMP = -15°C V2 KCAS ****** ****** ****** ****** ****** ****** ****** ****** ****** 151 151
-- 70,000 LB --
VFS = 173 KCAS FLD LNGTH ****** ****** ****** ****** ****** ****** ****** 8,130 7,770 7,490 7,220
VSE = 180 KCAS V1 KCAS ****** ****** ****** ****** ****** ****** ****** 143 143 143 143
VREF = 156 KCAS VR KCAS ****** ****** ****** ****** ****** ****** ****** 145 145 145 145
MAX TEMP = 0°C V2 KCAS ****** ****** ****** ****** ****** ****** ****** 149 149 149 149
-- 68,000 LB --
VFS = 171 KCAS FLD LNGTH ****** ****** ****** ****** 8,460 8,130 7,900 7,630 7,300 7,040 6,780
VSE = 178 KCAS V1 KCAS ****** ****** ****** ****** 141 141 140 140 140 140 140
VREF = 154 KCAS VR KCAS ****** ****** ****** ****** 143 143 143 143 143 143 143
MAX TEMP = 17°C V2 KCAS ****** ****** ****** ****** 147 147 147 147 147 147 147
-- 66,000 LB --
VFS = 168 KCAS FLD LNGTH ****** 9,230 8,610 8,250 7,920 7,620 7,410 7,150 6,850 6,600 6,360
VSE = 175 KCAS V1 KCAS ****** 141 139 139 138 138 137 137 137 137 137
VREF = 151 KCAS VR KCAS ****** 141 141 141 141 141 141 141 141 141 141
MAX TEMP = 33°C V2 KCAS ****** 145 145 145 145 145 145 145 145 145 145
-- 64,000 LB --
VFS = 166 KCAS FLD LNGTH 9,210 8,560 8,040 7,710 7,420 7,140 6,940 6,710 6,420 6,190 5,960
VSE = 172 KCAS V1 KCAS 138 137 136 136 135 135 134 134 134 134 134
VREF = 149 KCAS VR KCAS 139 139 139 139 139 138 138 138 138 138 138
MAX TEMP = 34°C V2 KCAS 143 143 143 143 143 143 143 143 143 143 143
-- 62,000 LB --
VFS = 163 KCAS FLD LNGTH 8,460 7,960 7,510 7,210 6,940 6,680 6,510 6,290 6,030 5,810 5,600
VSE = 169 KCAS V1 KCAS 136 135 133 133 132 132 131 131 131 131 131
VREF = 147 KCAS VR KCAS 136 136 136 136 136 136 136 136 136 136 136
MAX TEMP = 34°C V2 KCAS 140 140 140 140 140 140 140 140 140 140 140
-- 60,000 LB --
VFS = 160 KCAS FLD LNGTH 7,860 7,420 7,010 6,730 6,480 6,250 6,090 5,900 5,650 5,450 5,250
VSE = 167 KCAS V1 KCAS 133 131 130 130 129 129 128 128 128 128 128
VREF = 144 KCAS VR KCAS 134 134 134 134 134 134 134 134 133 133 133
MAX TEMP = 34°C V2 KCAS 138 138 138 138 138 138 138 138 138 138 138
CAUTION: DO NOT REDUCE TAKEOFF EPR BY MORE THAN .15 OR BELOW A MINIMUM VALUE OF 1.56.
NOTES: HEADWIND: Increase available field length 2% for each 5 knots (up to 40 knots).
TAILWIND: Not permitted using this data at this pressure altitude.
UPHILL SLOPE: Decrease available field length 20% for each 1% (up to 2%).
DOWNHILL SLOPE: Not permitted using this data at this pressure altitude.
GROUND SPOILERS INOP: Decrease available field length 800 feet.

REVISION 24 (RE-ISSUE) NON-SP GIV PERFORMANCE

Mar 17/10 (NON-SP GIV AIRPLANES ONLY) Page PA - 17
 Quick Reference Handbook
Non-SP GIV Takeoff Planning: Flaps 20° - APA 8000 Feet, ctd…
AFM APP. A

TAKEOFF PLANNING CHART

NON-SP GIV AIRPORT PRESSURE ALTITUDE = 8,000 FEET TAKEOFF FLAP 20°
73,200 LB MTOGW OAT (°C) 34 30 25 20 15 10 5 0 -10 -20 -30
OAT (°F) 93 86 77 68 59 50 41 32 14 -4 -22
RATED EPR 1.66 1.68 1.70 1.71 1.72 1.73 1.74 1.75 1.75 1.75 1.75
-- 58,000 LB --
VFS = 158 KCAS FLD LNGTH 7,290 6,890 6,530 6,270 6,050 5,830 5,690 5,510 5,280 5,090 4,900
VSE = 164 KCAS V1 KCAS 129 128 127 127 126 126 125 125 125 125 125
VREF = 142 KCAS VR KCAS 132 132 132 131 131 131 131 131 131 131 131
MAX TEMP = 34°C V2 KCAS 136 136 136 136 136 136 136 136 136 136 136
-- 56,000 LB --
VFS = 155 KCAS FLD LNGTH 6,750 6,390 6,070 5,840 5,640 5,440 5,300 5,140 4,920 4,750 4,580
VSE = 161 KCAS V1 KCAS 126 125 124 124 123 122 122 122 122 122 122
VREF = 139 KCAS VR KCAS 129 129 129 129 129 128 128 128 128 128 128
MAX TEMP = 34°C V2 KCAS 133 133 133 133 133 133 133 133 133 133 133
-- 54,000 LB --
VFS = 152 KCAS FLD LNGTH 6,350 6,020 5,730 5,520 5,330 5,140 5,010 4,860 4,660 4,490 4,330
VSE = 158 KCAS V1 KCAS 124 123 122 121 121 120 120 120 120 120 120
VREF = 137 KCAS VR KCAS 128 128 127 127 127 127 126 126 126 126 126
MAX TEMP = 34°C V2 KCAS 132 132 132 132 132 132 132 132 132 132 132
-- 52,000 LB --
VFS = 149 KCAS FLD LNGTH 6,070 5,770 5,490 5,290 5,110 4,930 4,810 4,660 4,470 4,310 4,150
VSE = 155 KCAS V1 KCAS 123 122 121 120 120 119 119 119 119 119 119
VREF = 134 KCAS VR KCAS 127 127 127 126 126 126 126 125 125 125 125
MAX TEMP = 34°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
-- 50,000 LB --
VFS = 146 KCAS FLD LNGTH 5,800 5,520 5,250 5,060 4,890 4,720 4,600 4,460 4,280 4,120 3,970
VSE = 152 KCAS V1 KCAS 121 121 120 119 119 118 118 117 117 117 118
VREF = 132 KCAS VR KCAS 127 126 126 125 125 125 125 125 124 124 124
MAX TEMP = 34°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
-- 48,000 LB --
VFS = 143 KCAS FLD LNGTH 5,570 5,300 5,050 4,870 4,700 4,540 4,430 4,290 4,120 3,970 3,830
VSE = 149 KCAS V1 KCAS 121 120 119 118 118 117 117 117 117 117 117
VREF = 129 KCAS VR KCAS 126 126 125 125 125 125 124 124 124 124 124
MAX TEMP = 34°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
-- 46,000 LB --
VFS = 140 KCAS FLD LNGTH 5,350 5,090 4,850 4,680 4,520 4,370 4,280 4,180 4,030 3,890 3,750
VSE = 146 KCAS V1 KCAS 120 119 118 117 117 116 116 117 117 117 117
VREF = 126 KCAS VR KCAS 126 125 125 125 124 124 124 124 124 124 124
MAX TEMP = 34°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
CAUTION: DO NOT REDUCE TAKEOFF EPR BY MORE THAN .15 OR BELOW A MINIMUM VALUE OF 1.56.
NOTES: HEADWIND: Increase available field length 2% for each 5 knots (up to 40 knots).
TAILWIND: Not permitted using this data at this pressure altitude.
UPHILL SLOPE: Decrease available field length 20% for each 1% (up to 2%).
DOWNHILL SLOPE: Not permitted using this data at this pressure altitude.
GROUND SPOILERS INOP: Decrease available field length 800 feet.

NON-SP GIV PERFORMANCE REVISION 24 (RE-ISSUE)

Page PA - 18 (NON-SP GIV AIRPLANES ONLY) Mar 17/10
Quick Reference Handbook
Non-SP GIV Takeoff Planning Charts: Flaps 10°
AFM APP. A

The charts in this section provide quick reference planning data for
takeoff planning at the following Airport Pressure Altitudes (APA), for
10° flap configurations:
• Sea Level • 500 Feet • 1000 Feet • 2000 Feet
• 4000 Feet • 6000 Feet • 8000 Feet
In the interest of safety, the CAUTION and NOTES following each
takeoff planning chart must be observed when using any takeoff
planning chart in this section.

REVISION 24 (RE-ISSUE) NON-SP GIV PERFORMANCE

Mar 17/10 (NON-SP GIV AIRPLANES ONLY) Page PA - 19
 Quick Reference Handbook
Non-SP GIV Takeoff Planning:
Flaps 10° - APA Sea Level AFM APP. A

TAKEOFF PLANNING CHART

NON-SP GIV AIRPORT PRESSURE ALTITUDE = SEA LEVEL TAKEOFF FLAP 10°
73,200 LB MTOGW OAT (°C) 50 45 40 35 30 25 20 15 5 -5 -15
OAT (°F) 122 113 104 95 86 77 68 59 41 23 5
RATED EPR 1.59 1.62 1.64 1.67 1.70 1.70 1.70 1.70 1.69 1.69 1.69
-- 73,200 LB --
VFS = 171 KCAS FLD LNGTH ****** 7,280 6,780 6,330 5,940 5,850 5,750 5,660 5,520 5,340 5,150
VSE = 178 KCAS V1 KCAS ****** 147 145 144 142 142 142 142 143 143 143
VREF = 157 KCAS VR KCAS ****** 150 149 149 149 149 149 149 149 149 149
MAX TEMP = 48°C V2 KCAS ****** 155 155 155 155 155 155 155 155 155 155
-- 72,000 LB --
VFS = 170 KCAS FLD LNGTH 7,580 7,030 6,550 6,120 5,750 5,660 5,570 5,480 5,340 5,160 4,990
VSE = 177 KCAS V1 KCAS 147 145 144 142 141 141 141 141 141 141 141
VREF = 156 KCAS VR KCAS 149 149 148 148 147 147 147 147 147 147 147
MAX TEMP = 50°C V2 KCAS 154 154 154 154 154 154 154 154 154 154 154
-- 70,000 LB --
VFS = 167 KCAS FLD LNGTH 7,140 6,630 6,190 5,790 5,440 5,350 5,270 5,180 5,060 4,890 4,720
VSE = 174 KCAS V1 KCAS 144 143 141 139 138 138 138 138 138 138 139
VREF = 154 KCAS VR KCAS 147 146 146 145 145 145 145 145 145 145 145
MAX TEMP = 50°C V2 KCAS 152 152 152 152 152 152 152 152 152 152 152
-- 68,000 LB --
VFS = 165 KCAS FLD LNGTH 6,710 6,240 5,830 5,460 5,130 5,050 4,970 4,890 4,770 4,610 4,450
VSE = 171 KCAS V1 KCAS 141 140 138 137 135 135 135 135 136 136 136
VREF = 151 KCAS VR KCAS 144 144 143 143 143 143 143 143 143 143 143
MAX TEMP = 50°C V2 KCAS 149 149 149 149 149 149 149 149 149 149 149
-- 66,000 LB --
VFS = 162 KCAS FLD LNGTH 6,310 5,870 5,490 5,140 4,840 4,760 4,690 4,610 4,500 4,350 4,200
VSE = 169 KCAS V1 KCAS 138 137 135 134 132 132 132 132 133 133 133
VREF = 149 KCAS VR KCAS 142 141 141 141 140 140 140 140 140 140 140
MAX TEMP = 50°C V2 KCAS 147 147 147 147 147 147 147 147 147 147 147
-- 64,000 LB --
VFS = 160 KCAS FLD LNGTH 5,920 5,510 5,160 4,840 4,560 4,480 4,410 4,340 4,240 4,090 3,950
VSE = 166 KCAS V1 KCAS 135 134 132 131 129 129 129 129 130 130 130
VREF = 147 KCAS VR KCAS 139 139 139 138 138 138 138 138 138 138 138
MAX TEMP = 50°C V2 KCAS 145 145 145 145 145 145 145 145 145 145 145
-- 62,000 LB --
VFS = 157 KCAS FLD LNGTH 5,550 5,180 4,850 4,550 4,290 4,220 4,150 4,090 3,990 3,850 3,720
VSE = 164 KCAS V1 KCAS 132 131 129 128 126 126 126 126 127 127 127
VREF = 144 KCAS VR KCAS 137 137 136 136 135 135 135 135 135 135 135
MAX TEMP = 50°C V2 KCAS 143 143 143 143 143 143 143 143 143 143 143
-- 60,000 LB --
VFS = 155 KCAS FLD LNGTH 5,200 4,850 4,550 4,270 4,030 3,970 3,900 3,840 3,750 3,620 3,500
VSE = 161 KCAS V1 KCAS 129 128 126 125 123 123 123 123 124 124 124
VREF = 142 KCAS VR KCAS 135 134 134 133 133 133 133 133 133 133 133
MAX TEMP = 50°C V2 KCAS 140 140 140 140 140 140 140 140 140 140 140
CAUTION: DO NOT REDUCE TAKEOFF EPR BY MORE THAN .15 OR BELOW A MINIMUM VALUE OF 1.56.
NOTES: HEADWIND: Increase available field length 2% for each 5 knots (up to 40 knots).
TAILWIND: Not permitted using this data at this pressure altitude.
UPHILL SLOPE: Decrease available field length 20% for each 1% (up to 2%).
DOWNHILL SLOPE: Not permitted using this data at this pressure altitude.

NON-SP GIV PERFORMANCE REVISION 24 (RE-ISSUE)

Page PA - 20 (NON-SP GIV AIRPLANES ONLY) Mar 17/10
Quick Reference Handbook
Non-SP GIV Takeoff Planning: Flaps 10° - APA Sea Level, ctd…
AFM APP. A

TAKEOFF PLANNING CHART

NON-SP GIV AIRPORT PRESSURE ALTITUDE = SEA LEVEL TAKEOFF FLAP 10°
73,200 LB MTOGW OAT (°C) 50 45 40 35 30 25 20 15 5 -5 -15
OAT (°F) 122 113 104 95 86 77 68 59 41 23 5
RATED EPR 1.59 1.62 1.64 1.67 1.70 1.70 1.70 1.70 1.69 1.69 1.69
-- 58,000 LB --
VFS = 152 KCAS FLD LNGTH 4,850 4,530 4,250 4,000 3,770 3,710 3,660 3,600 3,510 3,390 3,270
VSE = 158 KCAS V1 KCAS 126 125 123 122 120 120 120 120 120 120 121
VREF = 140 KCAS VR KCAS 132 132 131 131 130 130 130 130 130 130 130
MAX TEMP = 50°C V2 KCAS 138 138 138 138 138 138 138 138 138 138 138
-- 56,000 LB --
VFS = 150 KCAS FLD LNGTH 4,520 4,230 3,970 3,740 3,570 3,520 3,470 3,410 3,320 3,210 3,100
VSE = 156 KCAS V1 KCAS 123 121 120 118 118 118 118 118 118 118 118
VREF = 137 KCAS VR KCAS 129 129 128 128 127 127 127 127 127 127 127
MAX TEMP = 50°C V2 KCAS 136 136 136 136 136 136 136 136 136 136 136
-- 54,000 LB --
VFS = 147 KCAS FLD LNGTH 4,240 3,970 3,740 3,620 3,520 3,460 3,410 3,360 3,260 3,160 3,050
VSE = 153 KCAS V1 KCAS 120 119 117 117 118 118 118 118 118 118 118
VREF = 135 KCAS VR KCAS 127 127 126 126 125 125 125 125 125 125 125
MAX TEMP = 50°C V2 KCAS 134 134 134 134 134 134 134 134 134 134 134
-- 52,000 LB --
VFS = 144 KCAS FLD LNGTH 4,010 3,780 3,660 3,560 3,460 3,410 3,360 3,310 3,210 3,110 3,010
VSE = 150 KCAS V1 KCAS 118 117 117 118 118 118 118 118 118 119 119
VREF = 132 KCAS VR KCAS 126 125 125 124 124 124 124 124 124 124 124
MAX TEMP = 50°C V2 KCAS 132 132 132 132 132 132 132 132 132 132 132
-- 50,000 LB --
VFS = 142 KCAS FLD LNGTH 3,830 3,710 3,600 3,490 3,400 3,350 3,300 3,250 3,160 3,060 2,960
VSE = 147 KCAS V1 KCAS 117 117 118 118 119 119 119 119 119 119 119
VREF = 130 KCAS VR KCAS 124 124 123 123 122 122 122 122 122 122 122
MAX TEMP = 50°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
-- 48,000 LB --
VFS = 139 KCAS FLD LNGTH 3,760 3,640 3,530 3,430 3,340 3,290 3,250 3,200 3,100 3,010 2,910
VSE = 144 KCAS V1 KCAS 117 117 118 118 119 119 119 119 119 119 119
VREF = 127 KCAS VR KCAS 124 123 123 122 122 122 122 122 122 122 122
MAX TEMP = 50°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
-- 46,000 LB --
VFS = 136 KCAS FLD LNGTH 3,680 3,570 3,470 3,370 3,280 3,240 3,190 3,140 3,050 2,950 2,860
VSE = 141 KCAS V1 KCAS 117 118 118 119 119 119 119 119 119 120 120
VREF = 124 KCAS VR KCAS 124 123 123 122 121 121 121 121 121 121 121
MAX TEMP = 50°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
CAUTION: DO NOT REDUCE TAKEOFF EPR BY MORE THAN .15 OR BELOW A MINIMUM VALUE OF 1.56.
NOTES: HEADWIND: Increase available field length 2% for each 5 knots (up to 40 knots).
TAILWIND: Not permitted using this data at this pressure altitude.
UPHILL SLOPE: Decrease available field length 20% for each 1% (up to 2%).
DOWNHILL SLOPE: Not permitted using this data at this pressure altitude.

REVISION 24 (RE-ISSUE) NON-SP GIV PERFORMANCE

Mar 17/10 (NON-SP GIV AIRPLANES ONLY) Page PA - 21
 Quick Reference Handbook
Non-SP GIV Takeoff Planning:
Flaps 10° - APA 500 Feet AFM APP. A

TAKEOFF PLANNING CHART

NON-SP GIV AIRPORT PRESSURE ALTITUDE = 500 FEET TAKEOFF FLAP 10°
73,200 LB MTOGW OAT (°C) 49 45 40 35 30 25 20 15 5 -5 -15
OAT (°F) 120 113 104 95 86 77 68 59 41 23 5
RATED EPR 1.59 1.62 1.64 1.67 1.70 1.71 1.71 1.71 1.70 1.70 1.70
-- 73,200 LB --
VFS = 171 KCAS FLD LNGTH ****** ****** 7,060 6,590 6,170 6,000 5,900 5,800 5,660 5,470 5,280
VSE = 178 KCAS V1 KCAS ****** ****** 146 144 143 143 143 143 143 143 143
VREF = 157 KCAS VR KCAS ****** ****** 150 149 149 149 149 149 149 149 149
MAX TEMP = 43°C V2 KCAS ****** ****** 155 155 155 155 155 155 155 155 155
-- 72,000 LB --
VFS = 170 KCAS FLD LNGTH 7,780 7,320 6,820 6,370 5,970 5,800 5,700 5,610 5,480 5,290 5,110
VSE = 177 KCAS V1 KCAS 147 146 144 143 141 141 141 141 141 141 141
VREF = 156 KCAS VR KCAS 149 149 148 148 147 147 147 147 147 147 147
MAX TEMP = 49°C V2 KCAS 154 154 154 154 154 154 154 154 154 154 154
-- 70,000 LB --
VFS = 167 KCAS FLD LNGTH 7,320 6,910 6,440 6,020 5,650 5,490 5,400 5,310 5,180 5,010 4,830
VSE = 174 KCAS V1 KCAS 144 143 142 140 138 138 138 138 139 139 139
VREF = 154 KCAS VR KCAS 147 146 146 146 145 145 145 145 145 145 145
MAX TEMP = 49°C V2 KCAS 152 152 152 152 152 152 152 152 152 152 152
-- 68,000 LB --
VFS = 165 KCAS FLD LNGTH 6,880 6,500 6,060 5,670 5,330 5,180 5,090 5,010 4,890 4,720 4,560
VSE = 172 KCAS V1 KCAS 141 140 139 137 136 135 135 135 136 136 136
VREF = 151 KCAS VR KCAS 144 144 144 143 143 143 143 143 143 143 143
MAX TEMP = 49°C V2 KCAS 149 149 149 149 149 149 149 149 149 149 149
-- 66,000 LB --
VFS = 162 KCAS FLD LNGTH 6,460 6,110 5,700 5,340 5,020 4,880 4,800 4,720 4,610 4,450 4,300
VSE = 169 KCAS V1 KCAS 138 137 136 134 133 132 132 132 133 133 133
VREF = 149 KCAS VR KCAS 142 142 141 141 140 140 140 140 140 140 140
MAX TEMP = 49°C V2 KCAS 147 147 147 147 147 147 147 147 147 147 147
-- 64,000 LB --
VFS = 160 KCAS FLD LNGTH 6,060 5,730 5,360 5,030 4,730 4,600 4,520 4,450 4,340 4,190 4,050
VSE = 166 KCAS V1 KCAS 136 134 133 131 130 129 129 129 130 130 130
VREF = 147 KCAS VR KCAS 140 139 139 138 138 138 138 138 138 138 138
MAX TEMP = 49°C V2 KCAS 145 145 145 145 145 145 145 145 145 145 145
-- 62,000 LB --
VFS = 157 KCAS FLD LNGTH 5,680 5,380 5,040 4,720 4,450 4,320 4,250 4,190 4,080 3,950 3,810
VSE = 164 KCAS V1 KCAS 133 131 130 128 127 126 126 126 127 127 127
VREF = 144 KCAS VR KCAS 137 137 136 136 135 135 135 135 135 135 135
MAX TEMP = 49°C V2 KCAS 143 143 143 143 143 143 143 143 143 143 143
-- 60,000 LB --
VFS = 155 KCAS FLD LNGTH 5,320 5,040 4,720 4,440 4,180 4,060 4,000 3,930 3,840 3,710 3,580
VSE = 161 KCAS V1 KCAS 130 128 127 125 124 123 123 123 124 124 124
VREF = 142 KCAS VR KCAS 135 134 134 133 133 133 133 133 133 133 133
MAX TEMP = 49°C V2 KCAS 140 140 140 140 140 140 140 140 140 140 140
CAUTION: DO NOT REDUCE TAKEOFF EPR BY MORE THAN .15 OR BELOW A MINIMUM VALUE OF 1.56.
NOTES: HEADWIND: Increase available field length 2% for each 5 knots (up to 40 knots).
TAILWIND: Not permitted using this data at this pressure altitude.
UPHILL SLOPE: Decrease available field length 20% for each 1% (up to 2%).
DOWNHILL SLOPE: Not permitted using this data at this pressure altitude.

NON-SP GIV PERFORMANCE REVISION 24 (RE-ISSUE)

Page PA - 22 (NON-SP GIV AIRPLANES ONLY) Mar 17/10
Quick Reference Handbook
Non-SP GIV Takeoff Planning: Flaps 10° - APA 500 Feet, ctd…
AFM APP. A

TAKEOFF PLANNING CHART

NON-SP GIV AIRPORT PRESSURE ALTITUDE = 500 FEET TAKEOFF FLAP 10°
73,200 LB MTOGW OAT (°C) 49 45 40 35 30 25 20 15 5 -5 -15
OAT (°F) 120 113 104 95 86 77 68 59 41 23 5
RATED EPR 1.59 1.62 1.64 1.67 1.70 1.71 1.71 1.71 1.70 1.70 1.70
-- 58,000 LB --
VFS = 152 KCAS FLD LNGTH 4,970 4,710 4,420 4,150 3,910 3,810 3,740 3,680 3,590 3,470 3,350
VSE = 158 KCAS V1 KCAS 126 125 124 122 121 120 120 120 121 121 121
VREF = 140 KCAS VR KCAS 132 132 131 131 130 130 130 130 130 130 130
MAX TEMP = 49°C V2 KCAS 138 138 138 138 138 138 138 138 138 138 138
-- 56,000 LB --
VFS = 150 KCAS FLD LNGTH 4,630 4,390 4,120 3,880 3,670 3,590 3,530 3,480 3,380 3,270 3,160
VSE = 156 KCAS V1 KCAS 123 122 120 119 118 118 118 118 118 118 118
VREF = 137 KCAS VR KCAS 129 129 129 128 128 127 127 127 127 127 127
MAX TEMP = 49°C V2 KCAS 136 136 136 136 136 136 136 136 136 136 136
-- 54,000 LB --
VFS = 147 KCAS FLD LNGTH 4,340 4,130 3,880 3,710 3,600 3,530 3,480 3,420 3,330 3,220 3,110
VSE = 153 KCAS V1 KCAS 121 119 118 117 118 118 118 118 118 118 118
VREF = 135 KCAS VR KCAS 127 127 126 126 125 125 125 125 125 125 125
MAX TEMP = 49°C V2 KCAS 134 134 134 134 134 134 134 134 134 134 134
-- 52,000 LB --
VFS = 144 KCAS FLD LNGTH 4,110 3,900 3,750 3,640 3,540 3,470 3,420 3,370 3,270 3,170 3,060
VSE = 150 KCAS V1 KCAS 118 117 117 118 118 118 118 118 118 118 119
VREF = 132 KCAS VR KCAS 126 125 125 124 124 124 124 124 124 124 124
MAX TEMP = 49°C V2 KCAS 132 132 132 132 132 132 132 132 132 132 132
-- 50,000 LB --
VFS = 142 KCAS FLD LNGTH 3,900 3,800 3,680 3,580 3,480 3,410 3,360 3,310 3,220 3,110 3,010
VSE = 147 KCAS V1 KCAS 116 117 117 118 118 118 118 119 119 119 119
VREF = 130 KCAS VR KCAS 124 124 123 123 122 122 122 122 122 122 122
MAX TEMP = 49°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
-- 48,000 LB --
VFS = 139 KCAS FLD LNGTH 3,820 3,730 3,620 3,510 3,420 3,360 3,310 3,260 3,160 3,060 2,960
VSE = 144 KCAS V1 KCAS 117 117 118 118 118 119 119 119 119 119 119
VREF = 127 KCAS VR KCAS 124 124 123 123 122 122 122 122 122 122 122
MAX TEMP = 49°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
-- 46,000 LB --
VFS = 136 KCAS FLD LNGTH 3,740 3,650 3,550 3,450 3,360 3,300 3,250 3,200 3,110 3,010 2,910
VSE = 141 KCAS V1 KCAS 117 117 118 118 119 119 119 119 119 119 119
VREF = 124 KCAS VR KCAS 124 123 123 122 122 122 122 122 122 122 122
MAX TEMP = 49°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
CAUTION: DO NOT REDUCE TAKEOFF EPR BY MORE THAN .15 OR BELOW A MINIMUM VALUE OF 1.56.
NOTES: HEADWIND: Increase available field length 2% for each 5 knots (up to 40 knots).
TAILWIND: Not permitted using this data at this pressure altitude.
UPHILL SLOPE: Decrease available field length 20% for each 1% (up to 2%).
DOWNHILL SLOPE: Not permitted using this data at this pressure altitude.

REVISION 24 (RE-ISSUE) NON-SP GIV PERFORMANCE

Mar 17/10 (NON-SP GIV AIRPLANES ONLY) Page PA - 23
 Quick Reference Handbook
Non-SP GIV Takeoff Planning:
Flaps 10° - APA 1000 Feet AFM APP. A

TAKEOFF PLANNING CHART

NON-SP GIV AIRPORT PRESSURE ALTITUDE = 1,000 FEET TAKEOFF FLAP 10°
73,200 LB MTOGW OAT (°C) 48 45 40 35 30 25 20 15 5 -5 -15
OAT (°F) 118 113 104 95 86 77 68 59 41 23 5
RATED EPR 1.60 1.62 1.64 1.66 1.70 1.71 1.71 1.71 1.71 1.71 1.71
-- 73,200 LB --
VFS = 171 KCAS FLD LNGTH ****** ****** ****** 6,850 6,420 6,160 6,040 5,950 5,800 5,610 5,410
VSE = 178 KCAS V1 KCAS ****** ****** ****** 145 144 143 143 143 143 143 143
VREF = 157 KCAS VR KCAS ****** ****** ****** 149 149 149 149 149 149 149 149
MAX TEMP = 37°C V2 KCAS ****** ****** ****** 155 155 155 155 155 155 155 155
-- 72,000 LB --
VFS = 170 KCAS FLD LNGTH ****** 7,630 7,100 6,620 6,210 5,960 5,850 5,750 5,610 5,420 5,230
VSE = 177 KCAS V1 KCAS ****** 146 145 143 142 141 141 141 141 142 142
VREF = 156 KCAS VR KCAS ****** 149 148 148 148 147 147 147 147 147 147
MAX TEMP = 47°C V2 KCAS ****** 154 154 154 154 154 154 154 154 154 154
-- 70,000 LB --
VFS = 167 KCAS FLD LNGTH 7,510 7,190 6,700 6,260 5,870 5,640 5,530 5,440 5,310 5,130 4,950
VSE = 174 KCAS V1 KCAS 144 144 142 141 139 138 138 138 139 139 139
VREF = 154 KCAS VR KCAS 147 147 146 146 145 145 145 145 145 145 145
MAX TEMP = 48°C V2 KCAS 152 152 152 152 152 152 152 152 152 152 152
-- 68,000 LB --
VFS = 165 KCAS FLD LNGTH 7,050 6,760 6,300 5,890 5,530 5,320 5,220 5,130 5,010 4,840 4,670
VSE = 172 KCAS V1 KCAS 142 141 139 138 136 136 136 136 136 136 136
VREF = 151 KCAS VR KCAS 144 144 144 143 143 143 143 143 143 143 143
MAX TEMP = 48°C V2 KCAS 149 149 149 149 149 149 149 149 149 149 149
-- 66,000 LB --
VFS = 162 KCAS FLD LNGTH 6,620 6,350 5,930 5,550 5,210 5,010 4,920 4,840 4,720 4,560 4,400
VSE = 169 KCAS V1 KCAS 139 138 136 135 133 133 133 133 133 133 133
VREF = 149 KCAS VR KCAS 142 142 141 141 140 140 140 140 140 140 140
MAX TEMP = 48°C V2 KCAS 147 147 147 147 147 147 147 147 147 147 147
-- 64,000 LB --
VFS = 160 KCAS FLD LNGTH 6,210 5,960 5,570 5,220 4,910 4,720 4,630 4,560 4,440 4,300 4,150
VSE = 166 KCAS V1 KCAS 136 135 133 132 130 130 130 130 130 130 130
VREF = 147 KCAS VR KCAS 140 139 139 138 138 138 138 138 138 138 138
MAX TEMP = 48°C V2 KCAS 145 145 145 145 145 145 145 145 145 145 145
-- 62,000 LB --
VFS = 157 KCAS FLD LNGTH 5,820 5,590 5,230 4,910 4,610 4,440 4,360 4,290 4,180 4,040 3,900
VSE = 164 KCAS V1 KCAS 133 132 130 129 127 127 127 127 127 127 127
VREF = 144 KCAS VR KCAS 137 137 136 136 136 135 135 135 135 135 135
MAX TEMP = 48°C V2 KCAS 143 143 143 143 143 143 143 143 143 143 143
-- 60,000 LB --
VFS = 155 KCAS FLD LNGTH 5,450 5,240 4,910 4,600 4,340 4,170 4,090 4,030 3,930 3,800 3,670
VSE = 161 KCAS V1 KCAS 130 129 127 126 124 124 124 124 124 124 124
VREF = 142 KCAS VR KCAS 135 134 134 134 133 133 133 133 133 133 133
MAX TEMP = 48°C V2 KCAS 140 140 140 140 140 140 140 140 140 140 140
CAUTION: DO NOT REDUCE TAKEOFF EPR BY MORE THAN .15 OR BELOW A MINIMUM VALUE OF 1.56.
NOTES: HEADWIND: Increase available field length 2% for each 5 knots (up to 40 knots).
TAILWIND: Not permitted using this data at this pressure altitude.
UPHILL SLOPE: Decrease available field length 20% for each 1% (up to 2%).
DOWNHILL SLOPE: Not permitted using this data at this pressure altitude.

NON-SP GIV PERFORMANCE REVISION 24 (RE-ISSUE)

Page PA - 24 (NON-SP GIV AIRPLANES ONLY) Mar 17/10
Quick Reference Handbook
Non-SP GIV Takeoff Planning: Flaps 10° - APA 1000 Feet, ctd…
AFM APP. A

TAKEOFF PLANNING CHART

NON-SP GIV AIRPORT PRESSURE ALTITUDE = 1,000 FEET TAKEOFF FLAP 10°
73,200 LB MTOGW OAT (°C) 48 45 40 35 30 25 20 15 5 -5 -15
OAT (°F) 118 113 104 95 86 77 68 59 41 23 5
RATED EPR 1.60 1.62 1.64 1.66 1.70 1.71 1.71 1.71 1.71 1.71 1.71
-- 58,000 LB --
VFS = 152 KCAS FLD LNGTH 5,090 4,890 4,580 4,310 4,060 3,910 3,830 3,770 3,680 3,560 3,430
VSE = 158 KCAS V1 KCAS 127 126 124 123 121 120 120 120 121 121 121
VREF = 140 KCAS VR KCAS 132 132 131 131 130 130 130 130 130 130 130
MAX TEMP = 48°C V2 KCAS 138 138 138 138 138 138 138 138 138 138 138
-- 56,000 LB --
VFS = 150 KCAS FLD LNGTH 4,740 4,560 4,280 4,020 3,790 3,660 3,600 3,550 3,450 3,330 3,220
VSE = 156 KCAS V1 KCAS 123 122 121 120 118 117 118 118 118 118 118
VREF = 137 KCAS VR KCAS 129 129 129 128 128 128 127 127 127 127 127
MAX TEMP = 48°C V2 KCAS 136 136 136 136 136 136 136 136 136 136 136
-- 54,000 LB --
VFS = 147 KCAS FLD LNGTH 4,450 4,280 4,020 3,820 3,680 3,600 3,540 3,490 3,390 3,280 3,170
VSE = 153 KCAS V1 KCAS 121 120 118 117 117 118 118 118 118 118 118
VREF = 135 KCAS VR KCAS 127 127 127 126 126 125 125 125 125 125 125
MAX TEMP = 48°C V2 KCAS 134 134 134 134 134 134 134 134 134 134 134
-- 52,000 LB --
VFS = 144 KCAS FLD LNGTH 4,210 4,050 3,860 3,730 3,620 3,540 3,490 3,430 3,330 3,230 3,120
VSE = 150 KCAS V1 KCAS 119 118 117 117 118 118 118 118 118 118 119
VREF = 132 KCAS VR KCAS 126 126 125 125 124 124 124 124 124 124 124
MAX TEMP = 48°C V2 KCAS 132 132 132 132 132 132 132 132 132 132 132
-- 50,000 LB --
VFS = 142 KCAS FLD LNGTH 3,980 3,900 3,770 3,660 3,560 3,480 3,430 3,370 3,280 3,170 3,070
VSE = 147 KCAS V1 KCAS 116 117 117 118 118 118 118 118 119 119 119
VREF = 130 KCAS VR KCAS 124 124 124 123 123 122 122 122 122 122 122
MAX TEMP = 48°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
-- 48,000 LB --
VFS = 139 KCAS FLD LNGTH 3,890 3,820 3,700 3,590 3,500 3,420 3,370 3,320 3,220 3,120 3,020
VSE = 144 KCAS V1 KCAS 117 117 117 118 118 119 119 119 119 119 119
VREF = 127 KCAS VR KCAS 124 124 123 123 122 122 122 122 122 122 122
MAX TEMP = 48°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
-- 46,000 LB --
VFS = 136 KCAS FLD LNGTH 3,810 3,740 3,630 3,530 3,430 3,360 3,310 3,260 3,170 3,070 2,960
VSE = 141 KCAS V1 KCAS 117 117 118 118 119 119 119 119 119 119 120
VREF = 124 KCAS VR KCAS 124 124 123 122 122 122 122 122 122 122 122
MAX TEMP = 48°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
CAUTION: DO NOT REDUCE TAKEOFF EPR BY MORE THAN .15 OR BELOW A MINIMUM VALUE OF 1.56.
NOTES: HEADWIND: Increase available field length 2% for each 5 knots (up to 40 knots).
TAILWIND: Not permitted using this data at this pressure altitude.
UPHILL SLOPE: Decrease available field length 20% for each 1% (up to 2%).
DOWNHILL SLOPE: Not permitted using this data at this pressure altitude.

REVISION 24 (RE-ISSUE) NON-SP GIV PERFORMANCE

Mar 17/10 (NON-SP GIV AIRPLANES ONLY) Page PA - 25
 Quick Reference Handbook
Non-SP GIV Takeoff Planning:
Flaps 10°- APA 2000 Feet AFM APP. A

TAKEOFF PLANNING CHART

NON-SP GIV AIRPORT PRESSURE ALTITUDE = 2,000 FEET TAKEOFF FLAP 10°
73,200 LB MTOGW OAT (°C) 45 40 35 30 25 20 15 10 0 -10 -19
OAT (°F) 113 104 95 86 77 68 59 50 32 14 -2
RATED EPR 1.62 1.64 1.66 1.69 1.71 1.72 1.72 1.72 1.72 1.72 1.72
-- 73,200 LB --
VFS = 171 KCAS FLD LNGTH ****** ****** ****** ****** 6,570 6,420 6,280 6,150 5,990 5,790 5,600
VSE = 178 KCAS V1 KCAS ****** ****** ****** ****** 144 144 143 143 144 144 144
VREF = 157 KCAS VR KCAS ****** ****** ****** ****** 149 149 149 149 149 149 149
MAX TEMP = 27°C V2 KCAS ****** ****** ****** ****** 155 155 155 155 155 155 155
-- 72,000 LB --
VFS = 170 KCAS FLD LNGTH ****** ****** 7,170 6,710 6,360 6,210 6,070 5,940 5,800 5,600 5,420
VSE = 177 KCAS V1 KCAS ****** ****** 145 143 142 142 142 142 142 142 142
VREF = 156 KCAS VR KCAS ****** ****** 148 148 148 148 148 148 148 148 148
MAX TEMP = 36°C V2 KCAS ****** ****** 154 154 154 154 154 154 154 154 154
-- 70,000 LB --
VFS = 167 KCAS FLD LNGTH 7,800 7,250 6,760 6,340 6,010 5,870 5,740 5,620 5,480 5,290 5,120
VSE = 174 KCAS V1 KCAS 145 143 142 140 139 139 139 139 139 139 139
VREF = 154 KCAS VR KCAS 147 147 146 146 145 145 145 145 145 145 145
MAX TEMP = 46°C V2 KCAS 152 152 152 152 152 152 152 152 152 152 152
-- 68,000 LB --
VFS = 165 KCAS FLD LNGTH 7,330 6,820 6,370 5,970 5,670 5,540 5,410 5,300 5,170 4,990 4,830
VSE = 172 KCAS V1 KCAS 142 140 139 137 136 136 136 136 136 136 136
VREF = 151 KCAS VR KCAS 145 144 144 143 143 143 143 143 143 143 143
MAX TEMP = 46°C V2 KCAS 149 149 149 149 149 149 149 149 149 149 149
-- 66,000 LB --
VFS = 162 KCAS FLD LNGTH 6,880 6,410 5,990 5,620 5,340 5,220 5,100 5,000 4,870 4,700 4,550
VSE = 169 KCAS V1 KCAS 139 137 136 135 133 133 133 133 133 133 133
VREF = 149 KCAS VR KCAS 142 142 141 141 141 140 140 140 140 140 140
MAX TEMP = 46°C V2 KCAS 147 147 147 147 147 147 147 147 147 147 147
-- 64,000 LB --
VFS = 160 KCAS FLD LNGTH 6,450 6,020 5,630 5,290 5,030 4,910 4,800 4,700 4,590 4,430 4,290
VSE = 166 KCAS V1 KCAS 136 134 133 132 130 130 130 130 130 130 131
VREF = 147 KCAS VR KCAS 140 139 139 138 138 138 138 138 138 138 138
MAX TEMP = 46°C V2 KCAS 145 145 145 145 145 145 145 145 145 145 145
-- 62,000 LB --
VFS = 157 KCAS FLD LNGTH 6,050 5,640 5,290 4,970 4,730 4,620 4,520 4,430 4,310 4,170 4,040
VSE = 164 KCAS V1 KCAS 133 131 130 129 127 127 127 127 127 127 127
VREF = 145 KCAS VR KCAS 137 137 136 136 136 136 135 135 135 135 135
MAX TEMP = 46°C V2 KCAS 143 143 143 143 143 143 143 143 143 143 143
-- 60,000 LB --
VFS = 155 KCAS FLD LNGTH 5,660 5,290 4,960 4,670 4,440 4,340 4,250 4,160 4,050 3,920 3,790
VSE = 161 KCAS V1 KCAS 130 128 127 126 125 124 124 124 124 124 125
VREF = 142 KCAS VR KCAS 135 134 134 134 133 133 133 133 133 133 133
MAX TEMP = 46°C V2 KCAS 140 140 140 140 140 140 140 140 140 140 140
CAUTION: DO NOT REDUCE TAKEOFF EPR BY MORE THAN .15 OR BELOW A MINIMUM VALUE OF 1.56.
NOTES: HEADWIND: Increase available field length 2% for each 5 knots (up to 40 knots).
TAILWIND: Not permitted using this data at this pressure altitude.
UPHILL SLOPE: Decrease available field length 20% for each 1% (up to 2%).
DOWNHILL SLOPE: Not permitted using this data at this pressure altitude.

NON-SP GIV PERFORMANCE REVISION 24 (RE-ISSUE)

Page PA - 26 (NON-SP GIV AIRPLANES ONLY) Mar 17/10
Quick Reference Handbook
Non-SP GIV Takeoff Planning: Flaps 10° - APA 2000 Feet, ctd…
AFM APP. A

TAKEOFF PLANNING CHART

NON-SP GIV AIRPORT PRESSURE ALTITUDE = 2,000 FEET TAKEOFF FLAP 10°
73,200 LB MTOGW OAT (°C) 45 40 35 30 25 20 15 10 0 -10 -19
OAT (°F) 113 104 95 86 77 68 59 50 32 14 -2
RATED EPR 1.62 1.64 1.66 1.69 1.71 1.72 1.72 1.72 1.72 1.72 1.72
-- 58,000 LB --
VFS = 152 KCAS FLD LNGTH 5,280 4,940 4,640 4,370 4,160 4,060 3,980 3,890 3,800 3,670 3,550
VSE = 158 KCAS V1 KCAS 127 125 124 122 121 121 121 121 121 121 121
VREF = 140 KCAS VR KCAS 132 132 131 131 130 130 130 130 130 130 130
MAX TEMP = 46°C V2 KCAS 138 138 138 138 138 138 138 138 138 138 138
-- 56,000 LB --
VFS = 150 KCAS FLD LNGTH 4,920 4,610 4,330 4,080 3,880 3,800 3,720 3,640 3,550 3,430 3,320
VSE = 156 KCAS V1 KCAS 124 122 121 119 118 118 118 118 118 118 118
VREF = 137 KCAS VR KCAS 130 129 129 128 128 128 128 128 128 128 128
MAX TEMP = 46°C V2 KCAS 136 136 136 136 136 136 136 136 136 136 136
-- 54,000 LB --
VFS = 147 KCAS FLD LNGTH 4,620 4,330 4,070 3,870 3,760 3,700 3,630 3,570 3,470 3,350 3,250
VSE = 153 KCAS V1 KCAS 121 119 118 117 117 117 118 118 118 118 118
VREF = 135 KCAS VR KCAS 127 127 127 126 126 126 126 126 126 126 126
MAX TEMP = 46°C V2 KCAS 134 134 134 134 134 134 134 134 134 134 134
-- 52,000 LB --
VFS = 144 KCAS FLD LNGTH 4,370 4,100 3,910 3,800 3,700 3,630 3,570 3,510 3,410 3,300 3,200
VSE = 150 KCAS V1 KCAS 119 117 117 117 118 118 118 118 118 118 118
VREF = 132 KCAS VR KCAS 126 125 125 125 124 124 124 124 124 124 124
MAX TEMP = 46°C V2 KCAS 132 132 132 132 132 132 132 132 132 132 132
-- 50,000 LB --
VFS = 142 KCAS FLD LNGTH 4,140 3,960 3,840 3,730 3,630 3,570 3,510 3,450 3,350 3,240 3,140
VSE = 147 KCAS V1 KCAS 117 117 117 118 118 118 118 118 118 118 118
VREF = 130 KCAS VR KCAS 124 124 123 123 123 122 122 122 122 122 122
MAX TEMP = 46°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
-- 48,000 LB --
VFS = 139 KCAS FLD LNGTH 4,010 3,890 3,770 3,660 3,570 3,510 3,450 3,390 3,290 3,190 3,090
VSE = 144 KCAS V1 KCAS 117 117 117 118 118 118 118 119 119 119 119
VREF = 127 KCAS VR KCAS 124 124 123 123 122 122 122 122 122 122 122
MAX TEMP = 46°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
-- 46,000 LB --
VFS = 136 KCAS FLD LNGTH 3,930 3,810 3,690 3,590 3,500 3,440 3,390 3,330 3,230 3,130 3,040
VSE = 141 KCAS V1 KCAS 117 117 118 118 118 119 119 119 119 119 119
VREF = 124 KCAS VR KCAS 124 123 123 122 122 122 122 122 122 122 122
MAX TEMP = 46°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
CAUTION: DO NOT REDUCE TAKEOFF EPR BY MORE THAN .15 OR BELOW A MINIMUM VALUE OF 1.56.
NOTES: HEADWIND: Increase available field length 2% for each 5 knots (up to 40 knots).
TAILWIND: Not permitted using this data at this pressure altitude.
UPHILL SLOPE: Decrease available field length 20% for each 1% (up to 2%).
DOWNHILL SLOPE: Not permitted using this data at this pressure altitude.

REVISION 24 (RE-ISSUE) NON-SP GIV PERFORMANCE

Mar 17/10 (NON-SP GIV AIRPLANES ONLY) Page PA - 27
 Quick Reference Handbook
Non-SP GIV Takeoff Planning:
Flaps 10° - APA 4000 Feet AFM APP. A

TAKEOFF PLANNING CHART

NON-SP GIV AIRPORT PRESSURE ALTITUDE = 4,000 FEET TAKEOFF FLAP 10°
73,200 LB MTOGW OAT (°C) 40 35 30 25 20 15 10 5 -5 -15 -23
OAT (°F) 104 95 86 77 68 59 50 41 23 5 -9
RATED EPR 1.63 1.66 1.69 1.71 1.72 1.74 1.74 1.74 1.74 1.74 1.74
-- 73,200 LB --
VFS = 173 KCAS FLD LNGTH ****** ****** ****** ****** ****** ****** ****** ****** 6,630 6,400 6,220
VSE = 180 KCAS V1 KCAS ****** ****** ****** ****** ****** ****** ****** ****** 146 146 146
VREF = 157 KCAS VR KCAS ****** ****** ****** ****** ****** ****** ****** ****** 150 150 150
MAX TEMP = 2°C V2 KCAS ****** ****** ****** ****** ****** ****** ****** ****** 156 156 156
-- 72,000 LB --
VFS = 171 KCAS FLD LNGTH ****** ****** ****** ****** ****** ****** 6,780 6,670 6,410 6,190 6,010
VSE = 178 KCAS V1 KCAS ****** ****** ****** ****** ****** ****** 144 144 144 144 144
VREF = 156 KCAS VR KCAS ****** ****** ****** ****** ****** ****** 149 149 149 149 149
MAX TEMP = 11°C V2 KCAS ****** ****** ****** ****** ****** ****** 155 155 155 155 155
-- 70,000 LB --
VFS = 169 KCAS FLD LNGTH ****** ****** ****** 7,130 6,850 6,610 6,400 6,300 6,060 5,850 5,680
VSE = 176 KCAS V1 KCAS ****** ****** ****** 143 142 141 141 141 141 141 141
VREF = 154 KCAS VR KCAS ****** ****** ****** 147 147 147 147 147 147 147 147
MAX TEMP = 27°C V2 KCAS ****** ****** ****** 153 153 153 153 153 153 153 153
-- 68,000 LB --
VFS = 166 KCAS FLD LNGTH 8,150 7,580 7,090 6,710 6,450 6,230 6,040 5,940 5,720 5,520 5,360
VSE = 173 KCAS V1 KCAS 144 142 141 140 139 139 138 138 138 138 138
VREF = 151 KCAS VR KCAS 146 146 145 145 145 144 144 144 144 144 144
MAX TEMP = 42°C V2 KCAS 151 151 151 151 151 151 151 151 151 151 151
-- 66,000 LB --
VFS = 164 KCAS FLD LNGTH 7,650 7,130 6,670 6,320 6,080 5,870 5,690 5,590 5,390 5,200 5,050
VSE = 171 KCAS V1 KCAS 141 139 138 137 136 136 135 135 135 135 135
VREF = 149 KCAS VR KCAS 143 143 143 142 142 142 142 142 142 142 142
MAX TEMP = 42°C V2 KCAS 148 148 148 148 148 148 148 148 148 148 148
-- 64,000 LB --
VFS = 161 KCAS FLD LNGTH 7,170 6,690 6,270 5,940 5,720 5,520 5,350 5,270 5,070 4,890 4,750
VSE = 168 KCAS V1 KCAS 138 136 135 134 133 133 132 132 132 132 132
VREF = 147 KCAS VR KCAS 141 141 140 140 140 140 139 139 139 139 139
MAX TEMP = 42°C V2 KCAS 146 146 146 146 146 146 146 146 146 146 146
-- 62,000 LB --
VFS = 159 KCAS FLD LNGTH 6,710 6,270 5,880 5,580 5,370 5,190 5,030 4,950 4,770 4,600 4,470
VSE = 165 KCAS V1 KCAS 135 133 132 131 130 130 129 129 129 129 130
VREF = 145 KCAS VR KCAS 139 138 138 137 137 137 137 137 137 137 137
MAX TEMP = 42°C V2 KCAS 144 144 144 144 144 144 144 144 144 144 144
-- 60,000 LB --
VFS = 156 KCAS FLD LNGTH 6,280 5,880 5,520 5,240 5,040 4,870 4,730 4,650 4,480 4,320 4,200
VSE = 163 KCAS V1 KCAS 132 130 129 128 127 127 126 126 126 126 127
VREF = 142 KCAS VR KCAS 136 136 135 135 135 135 134 134 134 134 134
MAX TEMP = 42°C V2 KCAS 142 142 142 142 142 142 142 142 142 142 142
CAUTION: DO NOT REDUCE TAKEOFF EPR BY MORE THAN .15 OR BELOW A MINIMUM VALUE OF 1.56.
NOTES: HEADWIND: Increase available field length 2% for each 5 knots (up to 40 knots).
TAILWIND: Not permitted using this data at this pressure altitude.
UPHILL SLOPE: Decrease available field length 20% for each 1% (up to 2%).
DOWNHILL SLOPE: Not permitted using this data at this pressure altitude.

NON-SP GIV PERFORMANCE REVISION 24 (RE-ISSUE)

Page PA - 28 (NON-SP GIV AIRPLANES ONLY) Mar 17/10
Quick Reference Handbook
Non-SP GIV Takeoff Planning: Flaps 10° - APA 4000 Feet, ctd…
AFM APP. A

TAKEOFF PLANNING CHART

NON-SP GIV AIRPORT PRESSURE ALTITUDE = 4,000 FEET TAKEOFF FLAP 10°
73,200 LB MTOGW OAT (°C) 40 35 30 25 20 15 10 5 -5 -15 -23
OAT (°F) 104 95 86 77 68 59 50 41 23 5 -9
RATED EPR 1.63 1.66 1.69 1.71 1.72 1.74 1.74 1.74 1.74 1.74 1.74
-- 58,000 LB --
VFS = 154 KCAS FLD LNGTH 5,860 5,480 5,150 4,890 4,710 4,560 4,420 4,350 4,190 4,040 3,930
VSE = 160 KCAS V1 KCAS 129 127 126 125 124 124 123 123 123 123 123
VREF = 140 KCAS VR KCAS 134 133 133 132 132 132 132 132 132 132 132
MAX TEMP = 42°C V2 KCAS 139 139 139 139 139 139 139 139 139 139 139
-- 56,000 LB --
VFS = 151 KCAS FLD LNGTH 5,450 5,110 4,810 4,570 4,400 4,260 4,130 4,060 3,910 3,780 3,670
VSE = 157 KCAS V1 KCAS 125 124 123 121 121 120 120 120 120 120 120
VREF = 137 KCAS VR KCAS 131 130 130 130 129 129 129 129 129 129 129
MAX TEMP = 42°C V2 KCAS 137 137 137 137 137 137 137 137 137 137 137
-- 54,000 LB --
VFS = 148 KCAS FLD LNGTH 5,100 4,780 4,500 4,280 4,130 3,990 3,880 3,820 3,690 3,570 3,470
VSE = 154 KCAS V1 KCAS 123 121 120 119 118 117 117 117 117 117 118
VREF = 135 KCAS VR KCAS 129 128 128 127 127 127 127 127 127 127 127
MAX TEMP = 42°C V2 KCAS 134 134 134 134 134 134 134 134 134 134 134
-- 52,000 LB --
VFS = 146 KCAS FLD LNGTH 4,790 4,500 4,240 4,070 3,980 3,890 3,810 3,750 3,630 3,510 3,410
VSE = 151 KCAS V1 KCAS 120 119 117 117 117 117 117 117 118 118 118
VREF = 132 KCAS VR KCAS 127 126 126 125 125 125 125 125 125 125 125
MAX TEMP = 42°C V2 KCAS 133 133 133 133 133 133 133 133 133 133 133
-- 50,000 LB --
VFS = 143 KCAS FLD LNGTH 4,490 4,260 4,110 4,000 3,910 3,820 3,750 3,690 3,560 3,440 3,350
VSE = 148 KCAS V1 KCAS 117 117 117 117 117 117 118 118 118 118 118
VREF = 130 KCAS VR KCAS 125 124 124 123 123 123 123 123 123 123 123
MAX TEMP = 42°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
-- 48,000 LB --
VFS = 140 KCAS FLD LNGTH 4,340 4,160 4,030 3,920 3,830 3,750 3,680 3,620 3,500 3,380 3,290
VSE = 145 KCAS V1 KCAS 117 117 117 117 118 118 118 118 118 118 118
VREF = 127 KCAS VR KCAS 124 124 123 123 123 123 122 122 122 122 122
MAX TEMP = 42°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
-- 46,000 LB --
VFS = 137 KCAS FLD LNGTH 4,200 4,070 3,950 3,840 3,760 3,680 3,610 3,550 3,430 3,320 3,230
VSE = 142 KCAS V1 KCAS 116 117 117 118 118 118 118 118 118 119 119
VREF = 124 KCAS VR KCAS 124 124 123 123 123 122 122 122 122 122 122
MAX TEMP = 42°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
CAUTION: DO NOT REDUCE TAKEOFF EPR BY MORE THAN .15 OR BELOW A MINIMUM VALUE OF 1.56.
NOTES: HEADWIND: Increase available field length 2% for each 5 knots (up to 40 knots).
TAILWIND: Not permitted using this data at this pressure altitude.
UPHILL SLOPE: Decrease available field length 20% for each 1% (up to 2%).
DOWNHILL SLOPE: Not permitted using this data at this pressure altitude.

REVISION 24 (RE-ISSUE) NON-SP GIV PERFORMANCE

Mar 17/10 (NON-SP GIV AIRPLANES ONLY) Page PA - 29
 Quick Reference Handbook
Non-SP GIV Takeoff Planning:
Flaps 10° - APA 6000 Feet AFM APP. A

TAKEOFF PLANNING CHART

NON-SP GIV AIRPORT PRESSURE ALTITUDE = 6,000 FEET TAKEOFF FLAP 10°
73,200 LB MTOGW OAT (°C) 38 35 30 25 20 15 10 5 -5 -15 -25
OAT (°F) 101 95 86 77 68 59 50 41 23 5 -13
RATED EPR 1.64 1.65 1.68 1.71 1.72 1.73 1.74 1.74 1.75 1.75 1.75
-- 73,200 LB --
VFS = 175 KCAS FLD LNGTH ****** ****** ****** ****** ****** ****** ****** ****** ****** ****** 7,300
VSE = 182 KCAS V1 KCAS ****** ****** ****** ****** ****** ****** ****** ****** ****** ****** 149
VREF = 158 KCAS VR KCAS ****** ****** ****** ****** ****** ****** ****** ****** ****** ****** 153
MAX TEMP = -24°C V2 KCAS ****** ****** ****** ****** ****** ****** ****** ****** ****** ****** 158
-- 72,000 LB --
VFS = 174 KCAS FLD LNGTH ****** ****** ****** ****** ****** ****** ****** ****** ****** 7,320 7,050
VSE = 181 KCAS V1 KCAS ****** ****** ****** ****** ****** ****** ****** ****** ****** 148 148
VREF = 157 KCAS VR KCAS ****** ****** ****** ****** ****** ****** ****** ****** ****** 151 151
MAX TEMP = -15°C V2 KCAS ****** ****** ****** ****** ****** ****** ****** ****** ****** 157 157
-- 70,000 LB --
VFS = 171 KCAS FLD LNGTH ****** ****** ****** ****** ****** ****** ****** ****** 7,160 6,910 6,650
VSE = 178 KCAS V1 KCAS ****** ****** ****** ****** ****** ****** ****** ****** 145 145 145
VREF = 154 KCAS VR KCAS ****** ****** ****** ****** ****** ****** ****** ****** 149 149 149
MAX TEMP = 0°C V2 KCAS ****** ****** ****** ****** ****** ****** ****** ****** 155 155 155
-- 68,000 LB --
VFS = 169 KCAS FLD LNGTH ****** ****** ****** ****** ****** 7,480 7,220 7,050 6,740 6,500 6,270
VSE = 175 KCAS V1 KCAS ****** ****** ****** ****** ****** 143 142 142 142 142 142
VREF = 152 KCAS VR KCAS ****** ****** ****** ****** ****** 147 147 147 146 146 146
MAX TEMP = 16°C V2 KCAS ****** ****** ****** ****** ****** 152 152 152 152 152 152
-- 66,000 LB --
VFS = 166 KCAS FLD LNGTH ****** ****** 8,020 7,590 7,290 7,030 6,790 6,640 6,340 6,120 5,900
VSE = 173 KCAS V1 KCAS ****** ****** 142 141 140 140 139 139 139 139 139
VREF = 150 KCAS VR KCAS ****** ****** 145 145 144 144 144 144 144 144 144
MAX TEMP = 33°C V2 KCAS ****** ****** 150 150 150 150 150 150 150 150 150
-- 64,000 LB --
VFS = 163 KCAS FLD LNGTH 8,400 8,050 7,520 7,130 6,850 6,610 6,380 6,240 5,970 5,760 5,550
VSE = 170 KCAS V1 KCAS 141 140 139 138 137 137 136 136 136 136 136
VREF = 148 KCAS VR KCAS 143 143 142 142 142 142 142 142 142 142 142
MAX TEMP = 38°C V2 KCAS 148 148 148 148 148 148 148 148 148 148 148
-- 62,000 LB --
VFS = 161 KCAS FLD LNGTH 7,860 7,530 7,050 6,680 6,420 6,200 5,990 5,860 5,600 5,410 5,210
VSE = 167 KCAS V1 KCAS 138 137 136 135 134 134 133 133 133 133 133
VREF = 145 KCAS VR KCAS 141 140 140 140 140 139 139 139 139 139 139
MAX TEMP = 38°C V2 KCAS 145 145 145 145 145 145 145 145 145 145 145
-- 60,000 LB --
VFS = 158 KCAS FLD LNGTH 7,340 7,040 6,600 6,260 6,020 5,820 5,620 5,500 5,260 5,070 4,890
VSE = 165 KCAS V1 KCAS 135 134 133 132 131 131 130 130 130 130 130
VREF = 143 KCAS VR KCAS 138 138 138 137 137 137 137 137 137 137 137
MAX TEMP = 38°C V2 KCAS 143 143 143 143 143 143 143 143 143 143 143
CAUTION: DO NOT REDUCE TAKEOFF EPR BY MORE THAN .15 OR BELOW A MINIMUM VALUE OF 1.56.
NOTES: HEADWIND: Increase available field length 2% for each 5 knots (up to 40 knots).
TAILWIND: Not permitted using this data at this pressure altitude.
UPHILL SLOPE: Decrease available field length 20% for each 1% (up to 2%).
DOWNHILL SLOPE: Not permitted using this data at this pressure altitude.

NON-SP GIV PERFORMANCE REVISION 24 (RE-ISSUE)

Page PA - 30 (NON-SP GIV AIRPLANES ONLY) Mar 17/10
Quick Reference Handbook
Non-SP GIV Takeoff Planning: Flaps 10° - APA 6000 Feet, ctd…
AFM APP. A

TAKEOFF PLANNING CHART

NON-SP GIV AIRPORT PRESSURE ALTITUDE = 6,000 FEET TAKEOFF FLAP 10°
73,200 LB MTOGW OAT (°C) 38 35 30 25 20 15 10 5 -5 -15 -25
OAT (°F) 101 95 86 77 68 59 50 41 23 5 -13
RATED EPR 1.64 1.65 1.68 1.71 1.72 1.73 1.74 1.74 1.75 1.75 1.75
-- 58,000 LB --
VFS = 156 KCAS FLD LNGTH 6,840 6,560 6,150 5,840 5,620 5,430 5,250 5,140 4,910 4,740 4,570
VSE = 162 KCAS V1 KCAS 132 131 130 129 128 127 127 127 127 127 127
VREF = 140 KCAS VR KCAS 135 135 135 135 134 134 134 134 134 134 134
MAX TEMP = 38°C V2 KCAS 141 141 141 141 141 141 141 141 141 141 141
-- 56,000 LB --
VFS = 153 KCAS FLD LNGTH 6,360 6,110 5,730 5,450 5,240 5,070 4,900 4,790 4,590 4,430 4,270
VSE = 159 KCAS V1 KCAS 128 128 126 125 125 124 124 124 123 123 123
VREF = 138 KCAS VR KCAS 133 133 132 132 132 131 131 131 131 131 131
MAX TEMP = 38°C V2 KCAS 138 138 138 138 138 138 138 138 138 138 138
-- 54,000 LB --
VFS = 150 KCAS FLD LNGTH 5,910 5,680 5,340 5,080 4,890 4,730 4,570 4,470 4,280 4,130 3,980
VSE = 156 KCAS V1 KCAS 125 124 123 122 122 121 120 120 120 120 120
VREF = 135 KCAS VR KCAS 130 130 130 129 129 129 129 129 128 128 128
MAX TEMP = 38°C V2 KCAS 136 136 136 136 136 136 136 136 136 136 136
-- 52,000 LB --
VFS = 147 KCAS FLD LNGTH 5,500 5,290 4,970 4,730 4,560 4,410 4,270 4,170 4,000 3,860 3,720
VSE = 153 KCAS V1 KCAS 122 121 120 119 118 118 117 117 117 117 117
VREF = 133 KCAS VR KCAS 128 127 127 127 126 126 126 126 126 126 126
MAX TEMP = 38°C V2 KCAS 133 133 133 133 133 133 133 133 133 133 133
-- 50,000 LB --
VFS = 145 KCAS FLD LNGTH 5,100 4,910 4,620 4,430 4,320 4,230 4,130 4,060 3,910 3,780 3,650
VSE = 150 KCAS V1 KCAS 119 118 117 116 116 117 117 117 117 117 117
VREF = 130 KCAS VR KCAS 125 125 124 124 124 124 124 123 123 123 123
MAX TEMP = 38°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
-- 48,000 LB --
VFS = 141 KCAS FLD LNGTH 4,910 4,720 4,480 4,340 4,230 4,140 4,050 3,980 3,840 3,710 3,580
VSE = 147 KCAS V1 KCAS 118 117 116 116 117 117 117 117 117 117 118
VREF = 128 KCAS VR KCAS 125 125 124 124 124 123 123 123 123 123 123
MAX TEMP = 38°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
-- 46,000 LB --
VFS = 138 KCAS FLD LNGTH 4,710 4,550 4,360 4,240 4,140 4,060 3,970 3,900 3,760 3,630 3,510
VSE = 144 KCAS V1 KCAS 117 117 116 117 117 117 117 117 118 118 118
VREF = 125 KCAS VR KCAS 125 124 124 124 123 123 123 123 123 123 123
MAX TEMP = 38°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
CAUTION: DO NOT REDUCE TAKEOFF EPR BY MORE THAN .15 OR BELOW A MINIMUM VALUE OF 1.56.
NOTES: HEADWIND: Increase available field length 2% for each 5 knots (up to 40 knots).
TAILWIND: Not permitted using this data at this pressure altitude.
UPHILL SLOPE: Decrease available field length 20% for each 1% (up to 2%).
DOWNHILL SLOPE: Not permitted using this data at this pressure altitude.

REVISION 24 (RE-ISSUE) NON-SP GIV PERFORMANCE

Mar 17/10 (NON-SP GIV AIRPLANES ONLY) Page PA - 31
 Quick Reference Handbook
Non-SP GIV Takeoff Planning:
Flaps 10° - APA 8000 Feet AFM APP. A

TAKEOFF PLANNING CHART

NON-SP GIV AIRPORT PRESSURE ALTITUDE = 8,000 FEET TAKEOFF FLAP 10°
73,200 LB MTOGW OAT (°C) 34 30 25 20 15 10 5 0 -10 -20 -30
OAT (°F) 93 86 77 68 59 50 41 32 14 -4 -22
RATED EPR 1.66 1.68 1.70 1.71 1.72 1.73 1.74 1.75 1.75 1.75 1.75
-- 70,000 LB --
VFS = 173 KCAS FLD LNGTH ****** ****** ****** ****** ****** ****** ****** ****** ****** ****** 7,750
VSE = 180 KCAS V1 KCAS ****** ****** ****** ****** ****** ****** ****** ****** ****** ****** 148
VREF = 156 KCAS VR KCAS ****** ****** ****** ****** ****** ****** ****** ****** ****** ****** 151
MAX TEMP = -25°C V2 KCAS ****** ****** ****** ****** ****** ****** ****** ****** ****** ****** 156
-- 68,000 LB --
VFS = 171 KCAS FLD LNGTH ****** ****** ****** ****** ****** ****** ****** ****** 7,850 7,570 7,290
VSE = 178 KCAS V1 KCAS ****** ****** ****** ****** ****** ****** ****** ****** 145 145 145
VREF = 154 KCAS VR KCAS ****** ****** ****** ****** ****** ****** ****** ****** 149 149 149
MAX TEMP = -10°C V2 KCAS ****** ****** ****** ****** ****** ****** ****** ****** 154 154 154
-- 66,000 LB --
VFS = 168 KCAS FLD LNGTH ****** ****** ****** ****** ****** ****** 7,970 7,710 7,380 7,110 6,850
VSE = 175 KCAS V1 KCAS ****** ****** ****** ****** ****** ****** 143 142 142 142 142
VREF = 151 KCAS VR KCAS ****** ****** ****** ****** ****** ****** 146 146 146 146 146
MAX TEMP = 6°C V2 KCAS ****** ****** ****** ****** ****** ****** 152 152 152 152 152
-- 64,000 LB --
VFS = 166 KCAS FLD LNGTH ****** ****** ****** 8,280 7,980 7,680 7,480 7,240 6,930 6,680 6,430
VSE = 172 KCAS V1 KCAS ****** ****** ****** 141 141 140 140 139 139 139 139
VREF = 149 KCAS VR KCAS ****** ****** ****** 144 144 144 144 144 144 144 144
MAX TEMP = 24°C V2 KCAS ****** ****** ****** 149 149 149 149 149 149 149 149
-- 62,000 LB --
VFS = 163 KCAS FLD LNGTH 9,010 8,520 8,070 7,760 7,480 7,200 7,020 6,790 6,500 6,270 6,040
VSE = 169 KCAS V1 KCAS 141 140 139 138 138 137 137 136 136 136 136
VREF = 147 KCAS VR KCAS 143 142 142 142 142 142 141 141 141 141 141
MAX TEMP = 34°C V2 KCAS 147 147 147 147 147 147 147 147 147 147 147
-- 60,000 LB --
VFS = 160 KCAS FLD LNGTH 8,410 7,970 7,550 7,260 7,000 6,750 6,570 6,360 6,090 5,870 5,660
VSE = 167 KCAS V1 KCAS 138 137 136 135 135 134 134 133 133 133 133
VREF = 144 KCAS VR KCAS 140 140 140 139 139 139 139 139 139 139 139
MAX TEMP = 34°C V2 KCAS 145 145 145 145 145 145 145 145 145 145 145
-- 58,000 LB --
VFS = 158 KCAS FLD LNGTH 7,820 7,410 7,030 6,770 6,530 6,290 6,130 5,940 5,690 5,480 5,280
VSE = 164 KCAS V1 KCAS 134 133 132 132 131 131 131 130 130 130 130
VREF = 142 KCAS VR KCAS 137 137 137 137 136 136 136 136 136 136 136
MAX TEMP = 34°C V2 KCAS 142 142 142 142 142 142 142 142 142 142 142
-- 56,000 LB --
VFS = 155 KCAS FLD LNGTH 7,260 6,890 6,550 6,300 6,080 5,870 5,720 5,540 5,300 5,110 4,930
VSE = 161 KCAS V1 KCAS 131 130 129 129 128 128 127 127 127 127 127
VREF = 139 KCAS VR KCAS 135 134 134 134 134 134 133 133 133 133 133
MAX TEMP = 34°C V2 KCAS 140 140 140 140 140 140 140 140 140 140 140
CAUTION: DO NOT REDUCE TAKEOFF EPR BY MORE THAN .15 OR BELOW A MINIMUM VALUE OF 1.56.
NOTES: HEADWIND: Increase available field length 2% for each 5 knots (up to 40 knots).
TAILWIND: Not permitted using this data at this pressure altitude.
UPHILL SLOPE: Decrease available field length 20% for each 1% (up to 2%).
DOWNHILL SLOPE: Not permitted using this data at this pressure altitude.

NON-SP GIV PERFORMANCE REVISION 24 (RE-ISSUE)

Page PA - 32 (NON-SP GIV AIRPLANES ONLY) Mar 17/10
Quick Reference Handbook
Non-SP GIV Takeoff Planning: Flaps 10° - APA 8000 Feet, ctd…
AFM APP. A

TAKEOFF PLANNING CHART

NON-SP GIV AIRPORT PRESSURE ALTITUDE = 8,000 FEET TAKEOFF FLAP 10°
73,200 LB MTOGW OAT (°C) 34 30 25 20 15 10 5 0 -10 -20 -30
OAT (°F) 93 86 77 68 59 50 41 32 14 -4 -22
RATED EPR 1.66 1.68 1.70 1.71 1.72 1.73 1.74 1.75 1.75 1.75 1.75
-- 54,000 LB --
VFS = 152 KCAS FLD LNGTH 6,740 6,400 6,080 5,860 5,660 5,460 5,320 5,150 4,940 4,760 4,590
VSE = 158 KCAS V1 KCAS 128 127 126 125 125 124 124 124 123 124 124
VREF = 137 KCAS VR KCAS 132 132 131 131 131 131 131 131 130 130 130
MAX TEMP = 34°C V2 KCAS 137 137 137 137 137 137 137 137 137 137 137
-- 52,000 LB --
VFS = 149 KCAS FLD LNGTH 6,250 5,940 5,650 5,440 5,260 5,070 4,950 4,790 4,590 4,430 4,270
VSE = 155 KCAS V1 KCAS 125 124 123 122 121 121 121 120 120 120 120
VREF = 134 KCAS VR KCAS 129 129 129 128 128 128 128 128 128 128 128
MAX TEMP = 34°C V2 KCAS 135 135 135 135 135 135 135 135 135 135 135
-- 50,000 LB --
VFS = 146 KCAS FLD LNGTH 5,780 5,500 5,240 5,050 4,880 4,710 4,590 4,450 4,270 4,110 3,960
VSE = 152 KCAS V1 KCAS 121 120 119 119 118 118 117 117 117 117 117
VREF = 132 KCAS VR KCAS 127 126 126 126 126 125 125 125 125 125 125
MAX TEMP = 34°C V2 KCAS 132 132 132 132 132 132 132 132 132 132 132
-- 48,000 LB --
VFS = 143 KCAS FLD LNGTH 5,520 5,250 5,000 4,820 4,660 4,500 4,410 4,310 4,150 4,010 3,870
VSE = 149 KCAS V1 KCAS 120 119 118 117 117 116 116 117 117 117 117
VREF = 129 KCAS VR KCAS 126 126 125 125 125 125 125 124 124 124 124
MAX TEMP = 34°C V2 KCAS 132 132 132 132 132 132 132 132 132 132 132
-- 46,000 LB --
VFS = 140 KCAS FLD LNGTH 5,260 5,010 4,770 4,610 4,500 4,400 4,310 4,220 4,070 3,930 3,790
VSE = 146 KCAS V1 KCAS 119 118 117 116 116 117 117 117 117 117 117
VREF = 126 KCAS VR KCAS 125 125 125 124 124 124 124 124 124 124 124
MAX TEMP = 34°C V2 KCAS 131 131 131 131 131 131 131 131 131 131 131
CAUTION: DO NOT REDUCE TAKEOFF EPR BY MORE THAN .15 OR BELOW A MINIMUM VALUE OF 1.56.
NOTES: HEADWIND: Increase available field length 2% for each 5 knots (up to 40 knots).
TAILWIND: Not permitted using this data at this pressure altitude.
UPHILL SLOPE: Decrease available field length 20% for each 1% (up to 2%).
DOWNHILL SLOPE: Not permitted using this data at this pressure altitude.

REVISION 24 (RE-ISSUE) NON-SP GIV PERFORMANCE

Mar 17/10 (NON-SP GIV AIRPLANES ONLY) Page PA - 33
 Quick Reference Handbook
Non-SP GIV Takeoff Climb Requirements: Climb
Limited Weights: Flaps 20° - Minimum Gradient AFM 5.3

Conditions:
• For FAA Climb Requirements
• Based on 10 minutes of Maximum Takeoff Thrust in the event of an
engine failure
• Cowl anti-ice ON below 10° C
Takeoff Limited Weight (Pounds) For
Ambient Airport Pressure Altitudes As Shown
Temp: °C Sea 2000 4000 6000 8000 10000
Level Feet Feet Feet Feet Feet
-10 & Below 73200 73200 73200 73200 73200 71900
-5 73200 73200 73200 73200 73200 71300
0 73200 73200 73200 73200 73200 70600
5 73200 73200 73200 73200 73200 69300
10 73200 73200 73200 73200 73200 68500
15 73200 73200 73200 73200 73200 67100
20 73200 73200 73200 73200 71700 65700
25 73200 73200 73200 73200 70200 64300
30 73200 73200 73200 73200 67700 62600
35 73200 73200 73200 70100 - -
40 73200 73200 72000 - - -
45 73200 73200 - - - -
50 73200 - - - - -

NON-SP GIV PERFORMANCE REVISION 24 (RE-ISSUE)

Page PA - 34 (NON-SP GIV AIRPLANES ONLY) Mar 17/10
Quick Reference Handbook
Non-SP GIV Takeoff Climb Requirements: Climb
Limited Weights: Flaps 10° - Minimum Gradient AFM 5.3

Conditions:
• For FAA Climb Requirements
• Based on 10 minutes of Maximum Takeoff Thrust in the event of an
engine failure
• Cowl anti-ice ON below 10° C
Takeoff Limited Weight (Pounds) For
Ambient Airport Pressure Altitudes As Shown
Temp: °C Sea 2000 4000 6000 8000 10000
Level Feet Feet Feet Feet Feet
0 & Below 73200 73200 73200 73200 73200 73200
5 73200 73200 73200 73200 73200 73200
10 73200 73200 73200 73200 73200 72200
15 73200 73200 73200 73200 73200 70600
20 73200 73200 73200 73200 73200 69000
25 73200 73200 73200 73200 73200 67500
30 73200 73200 73200 73200 71200 65500
35 73200 73200 73200 73200 - -
40 73200 73200 73200 - - -
45 73200 73200 - - - -
50 73200 - - - - -

REVISION 24 (RE-ISSUE) NON-SP GIV PERFORMANCE

Mar 17/10 (NON-SP GIV AIRPLANES ONLY) Page PA - 35
 Quick Reference Handbook
Non-SP GIV Takeoff Climb Requirements:
Climb Limited Weights:
Flaps 20° - Standard Instrument Departure GIV-OIS-7

NOTE: For complete text and examples, see GIV Operating Manual
Section 11-04-40 or Operational Information Supplement number GIV-
OIS-07: Standard Instrument Departure (SID) Climb Performance.
GIV TAKEOFF GROSS WEIGHT LIMITED BY REQUIRED SID CLIMB GRADIENT
1000 FT AGL, FLAPS 20, ONE ENGINE OPERATING
DELTA AIRPORT AIRPORT
ISA AMBIENT PRESS TAKEOFF GROSS WEIGHT (1000 LB)
TEMP TEMP ALTITUDE REQUIRED SID CLIMB GRADIENT (FT/NM)
(DEG C) (DEG C) (FT) 200 300 400 500 600 700 800 900
< -20 15,000 54.6 47.8 NA NA NA NA NA NA
< -18 14,000 56.6 49.6 NA NA NA NA NA NA
< -14 12,000 60.9 53.3 47.4 NA NA NA NA NA
< -10 10,000 65.3 57.2 51.0 45.8 NA NA NA NA
< -5 < -6 8,000 69.9 61.3 54.6 49.2 NA NA NA NA
< -2 6,000 74.6 65.5 58.3 52.6 47.9 NA NA NA
<2 4,000 74.6 70.0 62.3 56.2 51.2 47.0 NA NA
<6 2,000 74.6 73.0 65.0 58.5 53.4 49.1 45.3 NA
< 10 0 74.6 74.6 67.4 60.6 55.2 50.8 46.9 NA
-15 15,000 54.1 47.4 NA NA NA NA NA NA
-13 14,000 56.2 49.2 NA NA NA NA NA NA
-9 12,000 60.4 52.9 47.0 NA NA NA NA NA
-5 10,000 64.8 56.7 50.6 45.5 NA NA NA NA
0 -1 8,000 69.5 60.9 54.2 48.9 NA NA NA NA
3 6,000 74.3 65.1 58.0 52.3 47.6 NA NA NA
7 4,000 74.6 69.6 61.9 55.8 50.9 46.7 NA NA
11 2,000 74.6 73.6 65.5 59.0 53.8 49.4 45.6 NA
15 0 74.6 74.6 67.4 60.6 55.2 50.8 46.9 NA
-10 15,000 53.7 47.0 NA NA NA NA NA NA
-8 14,000 55.7 48.8 NA NA NA NA NA NA
-4 12,000 59.8 52.4 46.6 NA NA NA NA NA
0 10,000 64.0 56.1 50.0 NA NA NA NA NA
5 4 8,000 68.5 60.1 53.5 48.2 NA NA NA NA
8 6,000 73.4 64.3 57.2 51.7 47.0 NA NA NA
12 4,000 74.6 69.5 61.8 55.7 50.8 46.6 NA NA
16 2,000 74.6 72.8 64.8 58.4 53.2 48.9 45.2 NA
20 0 74.6 74.6 67.3 60.6 55.2 50.8 46.9 NA
-5 15,000 52.8 46.1 NA NA NA NA NA NA
-3 14,000 54.7 47.9 NA NA NA NA NA NA
1 12,000 58.6 51.4 45.6 NA NA NA NA NA
5 10,000 62.7 55.0 49.0 NA NA NA NA NA
10 9 8,000 67.2 58.9 52.5 47.3 NA NA NA NA
13 6,000 72.6 63.7 56.7 51.2 46.5 NA NA NA
17 4,000 74.6 68.2 60.7 54.8 50.0 45.8 NA NA
21 2,000 74.6 72.1 64.2 57.8 52.7 48.4 NA NA
25 0 74.6 74.6 67.3 60.6 55.2 50.8 46.9 NA
NOTES: 1. Maximum climb weights are limited by the design MAX TOGW of 74,600 lb for the GIV-SP and
73,200 for the GIV.
2. Increase MAX TOGW by 300 lb for each 10 knots of headwind up to a maximum of 40 knots.
Data not valid for tailwinds.
3. Cowl anti-ice bleeds are assumed ON for temperatures below 10° C; wing anti-ice bleeds
prohibited.

NON-SP GIV PERFORMANCE REVISION 24 (RE-ISSUE)

Page PA - 36 (NON-SP GIV AIRPLANES ONLY) Mar 17/10
Quick Reference Handbook
Non-SP GIV Climb Limited Weights, Flaps 20°, Standard
Instrument Departure, ctd… GIV-OIS-7

GIV TAKEOFF GROSS WEIGHT LIMITED BY REQUIRED SID CLIMB GRADIENT

1000 FT AGL, FLAPS 20, ONE ENGINE OPERATING, ctd…
DELTA AIRPORT AIRPORT
ISA AMBIENT PRESS TAKEOFF GROSS WEIGHT (1000 LB)
TEMP TEMP ALTITUDE REQUIRED SID CLIMB GRADIENT (FT/NM)
(DEG C) (DEG C) (FT) 200 300 400 500 600 700 800 900
0 15,000 51.6 45.0 NA NA NA NA NA NA
2 14,000 53.5 46.8 NA NA NA NA NA NA
6 12,000 57.4 50.3 NA NA NA NA NA NA
10 10,000 61.9 54.3 48.3 NA NA NA NA NA
15 14 8,000 66.4 58.2 51.9 46.7 NA NA NA NA
18 6,000 71.3 62.5 55.7 50.3 45.7 NA NA NA
22 4,000 74.6 67.0 59.6 53.8 49.1 NA NA NA
26 2,000 74.6 71.4 63.5 57.2 52.2 48.0 NA NA
30 0 74.6 74.6 66.9 60.2 54.8 50.4 46.6 NA
5 15,000 50.5 NA NA NA NA NA NA NA
7 14,000 52.3 45.7 NA NA NA NA NA NA
11 12,000 56.6 49.6 NA NA NA NA NA NA
15 10,000 60.7 53.2 47.3 NA NA NA NA NA
20 19 8,000 65.1 57.1 50.9 45.8 NA NA NA NA
23 6,000 69.9 61.3 54.6 49.3 NA NA NA NA
27 4,000 74.6 65.5 58.3 52.7 48.0 NA NA NA
31 2,000 74.6 68.7 61.2 55.2 50.4 46.2 NA NA
35 0 74.6 71.7 63.9 57.6 52.5 48.2 NA NA
10 15,000 49.7 NA NA NA NA NA NA NA
12 14,000 51.6 NA NA NA NA NA NA NA
16 12,000 55.3 48.5 NA NA NA NA NA NA
20 10,000 59.4 52.1 46.3 NA NA NA NA NA
25 24 8,000 63.7 55.9 49.9 NA NA NA NA NA
28 6,000 68.4 60.0 53.5 48.3 NA NA NA NA
32 4,000 71.6 62.8 56.0 50.6 46.0 NA NA NA
36 2,000 74.6 65.5 58.4 52.8 48.1 NA NA NA
40 0 74.6 68.2 60.8 54.9 50.1 45.9 NA NA
15 15,000 48.5 NA NA NA NA NA NA NA
17 14,000 50.4 NA NA NA NA NA NA NA
21 12,000 54.2 47.4 NA NA NA NA NA NA
25 10,000 58.1 51.0 45.2 NA NA NA NA NA
30 29 8,000 62.0 54.4 48.5 NA NA NA NA NA
33 6,000 65.3 57.3 51.1 46.0 NA NA NA NA
37 4,000 68.2 59.9 53.5 48.2 NA NA NA NA
41 2,000 71.0 62.3 55.6 50.2 45.6 NA NA NA
45 0 73.8 64.8 57.8 52.3 47.6 NA NA NA
NOTES: 1. Maximum climb weights are limited by the design MAX TOGW of 74,600 lb for the GIV-SP and
73,200 for the GIV.
2. Increase MAX TOGW by 300 lb for each 10 knots of headwind up to a maximum of 40 knots.
Data not valid for tailwinds.
3. Cowl anti-ice bleeds are assumed ON for temperatures below 10° C; wing anti-ice bleeds
prohibited.

REVISION 24 (RE-ISSUE) NON-SP GIV PERFORMANCE

Mar 17/10 (NON-SP GIV AIRPLANES ONLY) Page PA - 37
 Quick Reference Handbook
Non-SP GIV Climb Limited Weights, Flaps 20°, Standard
Instrument Departure, ctd… GIV-OIS-7

GIV TAKEOFF GROSS WEIGHT LIMITED BY REQUIRED SID CLIMB GRADIENT

2000 FT AGL, FLAPS 20, ONE ENGINE OPERATING
DELTA AIRPORT AIRPORT
ISA AMBIENT PRESS TAKEOFF GROSS WEIGHT (1000 LB)
TEMP TEMP ALTITUDE REQUIRED SID CLIMB GRADIENT (FT/NM)
(DEG C) (DEG C) (FT) 200 300 400 500 600 700 800 900
< -20 15,000 53.7 47.1 NA NA NA NA NA NA
< -18 14,000 55.7 48.9 NA NA NA NA NA NA
< -14 12,000 59.9 52.7 46.9 NA NA NA NA NA
< -10 10,000 64.3 56.5 50.5 45.5 NA NA NA NA
< -5 < -6 8,000 68.8 60.5 54.0 48.8 NA NA NA NA
< -2 6,000 73.6 64.7 57.8 52.2 47.6 NA NA NA
<2 4,000 74.6 69.2 61.7 55.8 51.0 46.8 NA NA
<6 2,000 74.6 72.8 65.0 58.5 53.4 49.1 45.3 NA
< 10 0 74.6 74.6 67.4 60.6 55.2 50.8 46.9 NA
-15 15,000 53.2 46.7 NA NA NA NA NA NA
-13 14,000 55.2 48.5 NA NA NA NA NA NA
-9 12,000 59.4 52.2 46.5 NA NA NA NA NA
-5 10,000 63.8 56.1 50.1 45.1 NA NA NA NA
0 -1 8,000 68.4 60.1 53.7 48.5 NA NA NA NA
3 6,000 73.2 64.3 57.4 52.0 47.4 NA NA NA
7 4,000 74.6 68.8 61.4 55.4 50.7 46.5 NA NA
11 2,000 74.6 73.2 65.3 58.9 53.8 49.4 45.6 NA
15 0 74.6 74.6 67.4 60.6 55.2 50.8 46.9 NA
-10 15,000 52.6 46.1 NA NA NA NA NA NA
-8 14,000 54.8 48.1 NA NA NA NA NA NA
-4 12,000 58.9 51.7 46.1 NA NA NA NA NA
0 10,000 63.1 55.4 49.5 NA NA NA NA NA
5 4 8,000 67.5 59.3 53.0 47.9 NA NA NA NA
8 6,000 72.2 63.5 56.7 51.3 46.7 NA NA NA
12 4,000 74.6 68.6 61.2 55.3 50.5 46.4 NA NA
16 2,000 74.6 72.5 64.7 58.4 53.2 48.9 45.2 NA
20 0 74.6 74.6 67.2 60.6 55.2 50.8 46.9 NA
-5 15,000 51.5 45.1 NA NA NA NA NA NA
-3 14,000 53.8 47.2 NA NA NA NA NA NA
1 12,000 57.7 50.7 45.1 NA NA NA NA NA
5 10,000 61.8 54.3 48.5 NA NA NA NA NA
10 9 8,000 66.1 58.2 52.0 46.9 NA NA NA NA
13 6,000 71.5 62.9 56.1 50.8 46.3 NA NA NA
17 4,000 74.6 67.4 60.1 54.4 49.7 45.6 NA NA
21 2,000 74.6 71.6 63.8 57.7 52.7 48.4 NA NA
25 0 74.6 74.6 66.9 60.4 55.1 50.8 46.9 NA
NOTES: 1. Maximum climb weights are limited by the design MAX TOGW of 74,600 lb for the GIV-SP and
73,200 for the GIV.
2. Increase MAX TOGW by 300 lb for each 10 knots of headwind up to a maximum of 40 knots.
Data not valid for tailwinds.
3. Cowl anti-ice bleeds are assumed ON for temperatures below 10° C; wing anti-ice bleeds
prohibited.

NON-SP GIV PERFORMANCE REVISION 24 (RE-ISSUE)

Page PA - 38 (NON-SP GIV AIRPLANES ONLY) Mar 17/10
Quick Reference Handbook
Non-SP GIV Climb Limited Weights, Flaps 20°, Standard
Instrument Departure, ctd… GIV-OIS-7

GIV TAKEOFF GROSS WEIGHT LIMITED BY REQUIRED SID CLIMB GRADIENT

2000 FT AGL, FLAPS 20, ONE ENGINE OPERATING, ctd…
DELTA AIRPORT AIRPORT
ISA AMBIENT PRESS TAKEOFF GROSS WEIGHT (1000 LB)
TEMP TEMP ALTITUDE REQUIRED SID CLIMB GRADIENT (FT/NM)
(DEG C) (DEG C) (FT) 200 300 400 500 600 700 800 900
0 15,000 50.2 NA NA NA NA NA NA NA
2 14,000 52.6 46.1 NA NA NA NA NA NA
6 12,000 56.5 49.6 NA NA NA NA NA NA
10 10,000 61.0 53.6 47.9 NA NA NA NA NA
15 14 8,000 65.4 57.5 51.4 46.3 NA NA NA NA
18 6,000 70.1 61.7 55.1 49.9 45.4 NA NA NA
22 4,000 74.6 66.1 59.0 53.4 48.8 NA NA NA
26 2,000 74.6 70.6 63.0 56.9 52.0 47.8 NA NA
30 0 74.6 74.6 66.6 60.1 54.8 50.4 46.6 NA
5 15,000 48.7 NA NA NA NA NA NA NA
7 14,000 51.5 45.0 NA NA NA NA NA NA
11 12,000 55.7 48.9 NA NA NA NA NA NA
15 10,000 59.7 52.5 46.8 NA NA NA NA NA
20 19 8,000 64.0 56.4 50.4 45.4 NA NA NA NA
23 6,000 68.8 60.5 54.1 48.9 NA NA NA NA
27 4,000 73.5 64.7 57.8 52.3 47.7 NA NA NA
31 2,000 74.6 68.2 60.9 55.1 50.4 46.2 NA NA
35 0 74.6 71.3 63.7 57.5 52.5 48.2 NA NA
10 15,000 47.9 NA NA NA NA NA NA NA
12 14,000 50.7 NA NA NA NA NA NA NA
16 12,000 54.5 47.8 NA NA NA NA NA NA
20 10,000 58.5 51.4 45.8 NA NA NA NA NA
25 24 8,000 62.7 55.2 49.3 NA NA NA NA NA
28 6,000 67.2 59.2 52.9 47.8 NA NA NA NA
32 4,000 70.9 62.4 55.8 50.5 46.0 NA NA NA
36 2,000 74.0 65.2 58.2 52.7 48.1 NA NA NA
40 0 74.6 67.9 60.6 54.8 50.1 45.9 NA NA
15 15,000 46.4 NA NA NA NA NA NA NA
17 14,000 49.5 NA NA NA NA NA NA NA
21 12,000 53.3 46.7 NA NA NA NA NA NA
25 10,000 57.2 50.3 NA NA NA NA NA NA
30 29 8,000 61.2 53.9 48.1 NA NA NA NA NA
33 6,000 64.6 56.9 50.9 45.9 NA NA NA NA
37 4,000 67.6 59.5 53.3 48.1 NA NA NA NA
41 2,000 70.4 62.0 55.5 50.2 45.6 NA NA NA
45 0 73.2 64.5 57.7 52.3 47.6 NA NA NA
NOTES: 1. Maximum climb weights are limited by the design MAX TOGW of 74,600 lb for the GIV-SP and
73,200 for the GIV.
2. Increase MAX TOGW by 300 lb for each 10 knots of headwind up to a maximum of 40 knots.
Data not valid for tailwinds.
3. Cowl anti-ice bleeds are assumed ON for temperatures below 10° C; wing anti-ice bleeds
prohibited.

REVISION 24 (RE-ISSUE) NON-SP GIV PERFORMANCE

Mar 17/10 (NON-SP GIV AIRPLANES ONLY) Page PA - 39
 Quick Reference Handbook
Non-SP GIV Climb Limited Weights, Flaps 20°, Standard
Instrument Departure, ctd… GIV-OIS-7

GIV TAKEOFF GROSS WEIGHT LIMITED BY REQUIRED SID CLIMB GRADIENT

3000 FT AGL, FLAPS 20, ONE ENGINE OPERATING
DELTA AIRPORT AIRPORT
ISA AMBIENT PRESS TAKEOFF GROSS WEIGHT (1000 LB)
TEMP TEMP ALTITUDE REQUIRED SID CLIMB GRADIENT (FT/NM)
(DEG C) (DEG C) (FT) 200 300 400 500 600 700 800 900
< -20 15,000 52.7 46.3 NA NA NA NA NA NA
< -18 14,000 54.7 48.1 NA NA NA NA NA NA
< -14 12,000 58.9 51.8 46.2 NA NA NA NA NA
< -10 10,000 63.2 55.6 49.7 NA NA NA NA NA
< -5 < -6 8,000 67.7 59.6 53.3 48.1 NA NA NA NA
< -2 6,000 72.4 63.8 57.0 51.6 47.0 NA NA NA
<2 4,000 74.6 68.1 60.9 55.0 50.3 46.2 NA NA
<6 2,000 74.6 71.7 64.1 57.9 52.9 48.7 45.0 NA
< 10 0 74.6 74.6 67.0 60.5 55.2 50.8 46.9 NA
-15 15,000 52.3 45.8 NA NA NA NA NA NA
-13 14,000 54.3 47.7 NA NA NA NA NA NA
-9 12,000 58.4 51.4 45.8 NA NA NA NA NA
-5 10,000 62.7 55.2 49.3 NA NA NA NA NA
0 -1 8,000 67.2 59.1 52.9 47.8 NA NA NA NA
3 6,000 72.0 63.3 56.6 51.3 46.7 NA NA NA
7 4,000 74.6 67.7 60.5 54.7 50.0 45.9 NA NA
11 2,000 74.6 72.1 64.4 58.2 53.2 48.9 45.2 NA
15 0 74.6 74.6 67.0 60.5 55.2 50.8 46.9 NA
-10 15,000 51.5 45.2 NA NA NA NA NA NA
-8 14,000 53.7 47.1 NA NA NA NA NA NA
-4 12,000 57.8 50.9 45.3 NA NA NA NA NA
0 10,000 62.0 54.6 48.8 NA NA NA NA NA
5 4 8,000 66.3 58.4 52.2 47.2 NA NA NA NA
8 6,000 71.1 62.6 55.9 50.6 46.1 NA NA NA
12 4,000 74.6 67.5 60.3 54.6 49.9 45.8 NA NA
16 2,000 74.6 71.4 63.8 57.6 52.7 48.5 NA NA
20 0 74.6 74.6 66.6 60.1 54.9 50.6 46.8 NA
-5 15,000 50.2 NA NA NA NA NA NA NA
-3 14,000 52.5 46.0 NA NA NA NA NA NA
1 12,000 56.7 49.9 NA NA NA NA NA NA
5 10,000 60.8 53.5 47.8 NA NA NA NA NA
10 9 8,000 65.0 57.3 51.2 46.2 NA NA NA NA
13 6,000 70.3 61.9 55.3 50.1 45.6 NA NA NA
17 4,000 74.6 66.3 59.2 53.6 49.0 NA NA NA
21 2,000 74.6 70.5 63.0 56.9 52.0 47.9 NA NA
25 0 74.6 74.1 66.2 59.8 54.6 50.3 46.6 NA
NOTES: 1. Maximum climb weights are limited by the design MAX TOGW of 74,600 lb for the GIV-SP and
73,200 for the GIV.
2. Increase MAX TOGW by 300 lb for each 10 knots of headwind up to a maximum of 40 knots.
Data not valid for tailwinds.
3. Cowl anti-ice bleeds are assumed ON for temperatures below 10° C; wing anti-ice bleeds
prohibited.

NON-SP GIV PERFORMANCE REVISION 24 (RE-ISSUE)

Page PA - 40 (NON-SP GIV AIRPLANES ONLY) Mar 17/10
Quick Reference Handbook
Non-SP GIV Climb Limited Weights, Flaps 20°, Standard
Instrument Departure, ctd… GIV-OIS-7

GIV TAKEOFF GROSS WEIGHT LIMITED BY REQUIRED SID CLIMB GRADIENT

3000 FT AGL, FLAPS 20, ONE ENGINE OPERATING, ctd…
DELTA AIRPORT AIRPORT
ISA AMBIENT PRESS TAKEOFF GROSS WEIGHT (1000 LB)
TEMP TEMP ALTITUDE REQUIRED SID CLIMB GRADIENT (FT/NM)
(DEG C) (DEG C) (FT) 200 300 400 500 600 700 800 900
0 15,000 48.6 NA NA NA NA NA NA NA
2 14,000 51.1 NA NA NA NA NA NA NA
6 12,000 55.5 48.9 NA NA NA NA NA NA
10 10,000 60.0 52.8 47.1 NA NA NA NA NA
15 14 8,000 64.3 56.6 50.6 45.7 NA NA NA NA
18 6,000 68.9 60.7 54.3 49.1 NA NA NA NA
22 4,000 73.9 65.1 58.2 52.7 48.1 NA NA NA
26 2,000 74.6 69.6 62.1 56.2 51.4 47.2 NA NA
30 0 74.6 73.6 65.7 59.4 54.2 50.0 46.2 NA
5 15,000 46.9 NA NA NA NA NA NA NA
7 14,000 49.7 NA NA NA NA NA NA NA
11 12,000 54.8 48.2 NA NA NA NA NA NA
15 10,000 58.7 51.7 46.1 NA NA NA NA NA
20 19 8,000 63.0 55.5 49.6 NA NA NA NA NA
23 6,000 67.6 59.5 53.3 48.2 NA NA NA NA
27 4,000 72.3 63.7 56.9 51.6 47.0 NA NA NA
31 2,000 74.6 67.4 60.2 54.5 49.9 45.8 NA NA
35 0 74.6 70.6 63.1 57.1 52.2 48.0 NA NA
10 15,000 45.9 NA NA NA NA NA NA NA
12 14,000 48.8 NA NA NA NA NA NA NA
16 12,000 53.5 47.0 NA NA NA NA NA NA
20 10,000 57.4 50.6 45.0 NA NA NA NA NA
25 24 8,000 61.7 54.4 48.6 NA NA NA NA NA
28 6,000 66.0 58.2 52.1 47.1 NA NA NA NA
32 4,000 70.1 61.7 55.2 50.0 45.6 NA NA NA
36 2,000 73.2 64.5 57.7 52.3 47.7 NA NA NA
40 0 74.6 67.3 60.1 54.5 49.8 45.7 NA NA
15 15,000 NA NA NA NA NA NA NA NA
17 14,000 47.3 NA NA NA NA NA NA NA
21 12,000 52.4 46.0 NA NA NA NA NA NA
25 10,000 56.3 49.6 NA NA NA NA NA NA
30 29 8,000 60.1 53.0 47.3 NA NA NA NA NA
33 6,000 63.7 56.1 50.3 45.3 NA NA NA NA
37 4,000 66.8 58.9 52.8 47.7 NA NA NA NA
41 2,000 69.7 61.4 55.0 49.8 45.4 NA NA NA
45 0 72.5 63.9 57.2 51.9 47.3 NA NA NA
NOTES: 1. Maximum climb weights are limited by the design MAX TOGW of 74,600 lb for the GIV-SP and
73,200 for the GIV.
2. Increase MAX TOGW by 300 lb for each 10 knots of headwind up to a maximum of 40 knots.
Data not valid for tailwinds.
3. Cowl anti-ice bleeds are assumed ON for temperatures below 10° C; wing anti-ice bleeds
prohibited.

REVISION 24 (RE-ISSUE) NON-SP GIV PERFORMANCE

Mar 17/10 (NON-SP GIV AIRPLANES ONLY) Page PA - 41
 Quick Reference Handbook
Non-SP GIV Climb Limited Weights, Flaps 20°, Standard
Instrument Departure, ctd… GIV-OIS-7

GIV TAKEOFF GROSS WEIGHT LIMITED BY REQUIRED SID CLIMB GRADIENT

4000 FT AGL, FLAPS 20, ONE ENGINE OPERATING
DELTA AIRPORT AIRPORT
ISA AMBIENT PRESS TAKEOFF GROSS WEIGHT (1000 LB)
TEMP TEMP ALTITUDE REQUIRED SID CLIMB GRADIENT (FT/NM)
(DEG C) (DEG C) (FT) 200 300 400 500 600 700 800 900
< -20 15,000 51.9 45.6 NA NA NA NA NA NA
< -18 14,000 53.8 47.3 NA NA NA NA NA NA
< -14 12,000 57.9 51.0 45.5 NA NA NA NA NA
< -10 10,000 62.2 54.8 49.0 NA NA NA NA NA
< -5 < -6 8,000 66.7 58.7 52.6 47.5 NA NA NA NA
< -2 6,000 71.3 62.9 56.2 50.9 46.4 NA NA NA
<2 4,000 74.6 67.2 60.1 54.4 49.7 45.7 NA NA
<6 2,000 74.6 70.7 63.2 57.2 52.3 48.2 NA NA
< 10 0 74.6 74.6 66.8 60.3 55.1 50.8 46.9 NA
-15 15,000 51.6 45.2 NA NA NA NA NA NA
-13 14,000 53.4 46.9 NA NA NA NA NA NA
-9 12,000 57.5 50.6 45.1 NA NA NA NA NA
-5 10,000 61.7 54.4 48.6 NA NA NA NA NA
0 -1 8,000 66.2 58.3 52.2 47.2 NA NA NA NA
3 6,000 70.9 62.5 55.8 50.6 46.1 NA NA NA
7 4,000 74.6 66.8 59.7 54.1 49.4 45.4 NA NA
11 2,000 74.6 71.1 63.5 57.5 52.6 48.4 NA NA
15 0 74.6 74.5 66.6 60.1 54.9 50.7 46.9 NA
-10 15,000 50.8 NA NA NA NA NA NA NA
-8 14,000 52.6 46.2 NA NA NA NA NA NA
-4 12,000 56.9 50.2 NA NA NA NA NA NA
0 10,000 61.1 53.8 48.1 NA NA NA NA NA
5 4 8,000 65.4 57.6 51.6 46.6 NA NA NA NA
8 6,000 70.0 61.7 55.1 50.0 45.5 NA NA NA
12 4,000 74.6 66.5 59.5 53.9 49.2 45.2 NA NA
16 2,000 74.6 70.4 62.9 56.9 52.1 47.9 NA NA
20 0 74.6 74.1 66.2 59.8 54.7 50.4 46.7 NA
-5 15,000 49.5 NA NA NA NA NA NA NA
-3 14,000 51.2 NA NA NA NA NA NA NA
1 12,000 55.8 49.2 NA NA NA NA NA NA
5 10,000 59.9 52.8 47.1 NA NA NA NA NA
10 9 8,000 64.1 56.5 50.6 45.6 NA NA NA NA
13 6,000 69.3 61.0 54.6 49.5 45.0 NA NA NA
17 4,000 74.1 65.3 58.5 53.0 48.4 NA NA NA
21 2,000 74.6 69.5 62.1 56.2 51.4 47.3 NA NA
25 0 74.6 73.4 65.6 59.3 54.2 50.0 46.2 NA
NOTES: 1. Maximum climb weights are limited by the design MAX TOGW of 74,600 lb for the GIV-SP and
73,200 for the GIV.
2. Increase MAX TOGW by 300 lb for each 10 knots of headwind up to a maximum of 40 knots.
Data not valid for tailwinds.
3. Cowl anti-ice bleeds are assumed ON for temperatures below 10° C; wing anti-ice bleeds
prohibited.

NON-SP GIV PERFORMANCE REVISION 24 (RE-ISSUE)

Page PA - 42 (NON-SP GIV AIRPLANES ONLY) Mar 17/10
Quick Reference Handbook
Non-SP GIV Climb Limited Weights, Flaps 20°, Standard
Instrument Departure, ctd… GIV-OIS-7

GIV TAKEOFF GROSS WEIGHT LIMITED BY REQUIRED SID CLIMB GRADIENT

4000 FT AGL, FLAPS 20, ONE ENGINE OPERATING, ctd…
DELTA AIRPORT AIRPORT
ISA AMBIENT PRESS TAKEOFF GROSS WEIGHT (1000 LB)
TEMP TEMP ALTITUDE REQUIRED SID CLIMB GRADIENT (FT/NM)
(DEG C) (DEG C) (FT) 200 300 400 500 600 700 800 900
0 15,000 48.0 NA NA NA NA NA NA NA
2 14,000 49.6 NA NA NA NA NA NA NA
6 12,000 54.7 48.1 NA NA NA NA NA NA
10 10,000 59.1 52.1 46.5 NA NA NA NA NA
15 14 8,000 63.3 55.8 50.0 45.0 NA NA NA NA
18 6,000 67.9 59.9 53.6 48.5 NA NA NA NA
22 4,000 72.7 64.1 57.4 52.0 47.5 NA NA NA
26 2,000 74.6 68.5 61.3 55.5 50.8 46.7 NA NA
30 0 74.6 72.6 64.9 58.7 53.7 49.4 45.7 NA
5 15,000 46.3 NA NA NA NA NA NA NA
7 14,000 47.9 NA NA NA NA NA NA NA
11 12,000 53.9 47.4 NA NA NA NA NA NA
15 10,000 57.8 51.0 45.5 NA NA NA NA NA
20 19 8,000 62.0 54.7 48.9 NA NA NA NA NA
23 6,000 66.5 58.7 52.6 47.5 NA NA NA NA
27 4,000 71.1 62.7 56.1 50.9 46.4 NA NA NA
31 2,000 74.6 66.5 59.5 53.9 49.3 45.2 NA NA
35 0 74.6 70.0 62.6 56.7 51.8 47.7 NA NA
10 15,000 45.4 NA NA NA NA NA NA NA
12 14,000 47.0 NA NA NA NA NA NA NA
16 12,000 52.7 46.3 NA NA NA NA NA NA
20 10,000 56.6 49.9 NA NA NA NA NA NA
25 24 8,000 60.8 53.6 47.9 NA NA NA NA NA
28 6,000 65.0 57.4 51.4 46.4 NA NA NA NA
32 4,000 68.9 60.8 54.4 49.3 NA NA NA NA
36 2,000 72.5 64.0 57.3 52.0 47.4 NA NA NA
40 0 74.6 66.7 59.7 54.1 49.5 45.5 NA NA
15 15,000 NA NA NA NA NA NA NA NA
17 14,000 45.2 NA NA NA NA NA NA NA
21 12,000 51.5 45.2 NA NA NA NA NA NA
25 10,000 55.3 48.8 NA NA NA NA NA NA
30 29 8,000 59.2 52.2 46.6 NA NA NA NA NA
33 6,000 62.8 55.4 49.7 NA NA NA NA NA
37 4,000 66.1 58.3 52.3 47.3 NA NA NA NA
41 2,000 69.0 60.9 54.6 49.5 45.1 NA NA NA
45 0 71.9 63.5 56.9 51.6 47.1 NA NA NA
NOTES: 1. Maximum climb weights are limited by the design MAX TOGW of 74,600 lb for the GIV-SP and
73,200 for the GIV.
2. Increase MAX TOGW by 300 lb for each 10 knots of headwind up to a maximum of 40 knots.
Data not valid for tailwinds.
3. Cowl anti-ice bleeds are assumed ON for temperatures below 10° C; wing anti-ice bleeds
prohibited.

REVISION 24 (RE-ISSUE) NON-SP GIV PERFORMANCE

Mar 17/10 (NON-SP GIV AIRPLANES ONLY) Page PA - 43
 Quick Reference Handbook
Non-SP GIV Climb Limited Weights, Flaps 20°, Standard
Instrument Departure, ctd… GIV-OIS-7

GIV TAKEOFF GROSS WEIGHT LIMITED BY REQUIRED SID CLIMB GRADIENT

5000 FT AGL, FLAPS 20, ONE ENGINE OPERATING
DELTA AIRPORT AIRPORT
ISA AMBIENT PRESS TAKEOFF GROSS WEIGHT (1000 LB)
TEMP TEMP ALTITUDE REQUIRED SID CLIMB GRADIENT (FT/NM)
(DEG C) (DEG C) (FT) 200 300 400 500 600 700 800 900
< -20 15,000 51.6 NA NA NA NA NA NA NA
< -18 14,000 53.0 46.6 NA NA NA NA NA NA
< -14 12,000 56.9 50.2 NA NA NA NA NA NA
< -10 10,000 61.4 53.9 48.2 NA NA NA NA NA
< -5 < -6 8,000 65.7 57.8 51.7 46.7 NA NA NA NA
< -2 6,000 70.2 61.9 55.3 50.1 45.7 NA NA NA
<2 4,000 74.6 66.2 59.2 53.6 49.0 NA NA NA
<6 2,000 74.6 69.6 62.2 56.3 51.5 47.4 NA NA
< 10 0 74.6 73.5 65.7 59.4 54.3 50.0 46.3 NA
-15 15,000 50.9 NA NA NA NA NA NA NA
-13 14,000 52.6 46.2 NA NA NA NA NA NA
-9 12,000 56.9 49.7 NA NA NA NA NA NA
-5 10,000 60.7 53.5 47.8 NA NA NA NA NA
0 -1 8,000 65.4 57.4 51.3 46.4 NA NA NA NA
3 6,000 69.9 61.4 54.9 49.8 45.3 NA NA NA
7 4,000 74.6 65.7 58.8 53.2 48.6 NA NA NA
11 2,000 74.6 70.0 62.5 56.6 51.8 47.6 NA NA
15 0 74.6 73.3 65.5 59.2 54.1 49.9 46.1 NA
-10 15,000 50.8 NA NA NA NA NA NA NA
-8 14,000 51.8 45.5 NA NA NA NA NA NA
-4 12,000 55.8 49.1 NA NA NA NA NA NA
0 10,000 60.5 52.9 47.3 NA NA NA NA NA
5 4 8,000 64.6 56.7 50.7 45.8 NA NA NA NA
8 6,000 68.9 60.7 54.3 49.2 NA NA NA NA
12 4,000 74.5 65.5 58.6 53.1 48.5 NA NA NA
16 2,000 74.6 69.2 61.9 56.0 51.3 47.1 NA NA
20 0 74.6 72.9 65.2 58.9 53.8 49.6 45.9 NA
-5 15,000 48.9 NA NA NA NA NA NA NA
-3 14,000 50.5 NA NA NA NA NA NA NA
1 12,000 54.9 48.0 NA NA NA NA NA NA
5 10,000 58.9 51.9 46.3 NA NA NA NA NA
10 9 8,000 63.4 55.6 49.8 NA NA NA NA NA
13 6,000 68.4 60.1 53.7 48.7 NA NA NA NA
17 4,000 72.9 64.3 57.5 52.1 47.6 NA NA NA
21 2,000 74.6 68.3 61.1 55.3 50.6 46.5 NA NA
25 0 74.6 72.3 64.6 58.4 53.4 49.2 45.5 NA
NOTES: 1. Maximum climb weights are limited by the design MAX TOGW of 74,600 lb for the GIV-SP and
73,200 for the GIV.
2. Increase MAX TOGW by 300 lb for each 10 knots of headwind up to a maximum of 40 knots.
Data not valid for tailwinds.
3. Cowl anti-ice bleeds are assumed ON for temperatures below 10° C; wing anti-ice bleeds
prohibited.

NON-SP GIV PERFORMANCE REVISION 24 (RE-ISSUE)

Page PA - 44 (NON-SP GIV AIRPLANES ONLY) Mar 17/10
Quick Reference Handbook
Non-SP GIV Climb Limited Weights, Flaps 20°, Standard
Instrument Departure, ctd… GIV-OIS-7

GIV TAKEOFF GROSS WEIGHT LIMITED BY REQUIRED SID CLIMB GRADIENT

5000 FT AGL, FLAPS 20, ONE ENGINE OPERATING, ctd…
DELTA AIRPORT AIRPORT
ISA AMBIENT PRESS TAKEOFF GROSS WEIGHT (1000 LB)
TEMP TEMP ALTITUDE REQUIRED SID CLIMB GRADIENT (FT/NM)
(DEG C) (DEG C) (FT) 200 300 400 500 600 700 800 900
0 15,000 47.4 NA NA NA NA NA NA NA
2 14,000 49.0 NA NA NA NA NA NA NA
6 12,000 53.6 46.7 NA NA NA NA NA NA
10 10,000 58.6 51.3 45.7 NA NA NA NA NA
15 14 8,000 62.7 54.9 49.2 NA NA NA NA NA
18 6,000 66.8 58.9 52.7 47.7 NA NA NA NA
22 4,000 71.7 63.1 56.4 51.2 46.7 NA NA NA
26 2,000 74.6 67.4 60.3 54.6 49.9 45.9 NA NA
30 0 74.6 71.5 63.9 57.8 52.9 48.7 45.0 NA
5 15,000 45.7 NA NA NA NA NA NA NA
7 14,000 47.3 NA NA NA NA NA NA NA
11 12,000 52.8 45.9 NA NA NA NA NA NA
15 10,000 56.9 50.2 NA NA NA NA NA NA
20 19 8,000 61.3 53.8 48.1 NA NA NA NA NA
23 6,000 65.7 57.7 51.7 46.7 NA NA NA NA
27 4,000 70.0 61.7 55.2 50.1 45.6 NA NA NA
31 2,000 74.0 65.4 58.5 53.1 48.5 NA NA NA
35 0 74.6 69.1 61.8 55.9 51.2 47.1 NA NA
10 15,000 NA NA NA NA NA NA NA NA
12 14,000 46.4 NA NA NA NA NA NA NA
16 12,000 50.8 NA NA NA NA NA NA NA
20 10,000 55.7 49.1 NA NA NA NA NA NA
25 24 8,000 59.7 52.7 47.1 NA NA NA NA NA
28 6,000 64.0 56.4 50.6 45.6 NA NA NA NA
32 4,000 67.6 59.7 53.5 48.4 NA NA NA NA
36 2,000 71.4 63.2 56.6 51.3 46.8 NA NA NA
40 0 74.3 66.0 59.1 53.6 49.0 NA NA NA
15 15,000 NA NA NA NA NA NA NA NA
17 14,000 NA NA NA NA NA NA NA NA
21 12,000 49.9 NA NA NA NA NA NA NA
25 10,000 54.8 48.0 NA NA NA NA NA NA
30 29 8,000 58.4 51.4 45.8 NA NA NA NA NA
33 6,000 61.7 54.5 48.8 NA NA NA NA NA
37 4,000 64.9 57.5 51.6 46.6 NA NA NA NA
41 2,000 67.6 60.2 54.0 48.9 NA NA NA NA
45 0 70.3 62.8 56.3 51.1 46.6 NA NA NA
NOTES: 1. Maximum climb weights are limited by the design MAX TOGW of 74,600 lb for the GIV-SP and
73,200 for the GIV.
2. Increase MAX TOGW by 300 lb for each 10 knots of headwind up to a maximum of 40 knots.
Data not valid for tailwinds.
3. Cowl anti-ice bleeds are assumed ON for temperatures below 10° C; wing anti-ice bleeds
prohibited.

REVISION 24 (RE-ISSUE) NON-SP GIV PERFORMANCE

Mar 17/10 (NON-SP GIV AIRPLANES ONLY) Page PA - 45
 Quick Reference Handbook
Non-SP GIV Climb Limited Weights, Flaps 20°, Standard
Instrument Departure, ctd… GIV-OIS-7

GIV TAKEOFF GROSS WEIGHT LIMITED BY REQUIRED SID CLIMB GRADIENT

6000 FT AGL, FLAPS 20, ONE ENGINE OPERATING
DELTA AIRPORT AIRPORT
ISA AMBIENT PRESS TAKEOFF GROSS WEIGHT (1000 LB)
TEMP TEMP ALTITUDE REQUIRED SID CLIMB GRADIENT (FT/NM)
(DEG C) (DEG C) (FT) 200 300 400 500 600 700 800 900
< -20 15,000 48.1 NA NA NA NA NA NA NA
< -18 14,000 49.7 45.8 NA NA NA NA NA NA
< -14 12,000 53.1 49.3 NA NA NA NA NA NA
< -10 10,000 56.8 53.0 47.3 NA NA NA NA NA
< -5 < -6 8,000 60.8 56.8 50.9 45.9 NA NA NA NA
< -2 6,000 65.0 60.9 54.4 49.3 NA NA NA NA
<2 4,000 69.4 65.1 58.2 52.8 48.2 NA NA NA
<6 2,000 72.6 68.5 61.2 55.4 50.7 46.6 NA NA
< 10 0 74.6 72.2 64.6 58.4 53.4 49.2 45.5 NA
-15 15,000 47.9 NA NA NA NA NA NA NA
-13 14,000 49.6 45.6 NA NA NA NA NA NA
-9 12,000 52.8 48.9 NA NA NA NA NA NA
-5 10,000 56.5 52.6 47.0 NA NA NA NA NA
0 -1 8,000 60.5 56.4 50.5 45.6 NA NA NA NA
3 6,000 64.7 60.5 54.1 49.0 NA NA NA NA
7 4,000 69.0 64.7 57.8 52.4 47.9 NA NA NA
11 2,000 73.3 68.8 61.5 55.7 51.0 46.9 NA NA
15 0 74.6 72.1 64.4 58.3 53.3 49.1 45.4 NA
-10 15,000 47.5 NA NA NA NA NA NA NA
-8 14,000 49.1 NA NA NA NA NA NA NA
-4 12,000 52.1 48.1 NA NA NA NA NA NA
0 10,000 56.0 52.1 46.4 NA NA NA NA NA
5 4 8,000 59.9 55.8 49.9 45.0 NA NA NA NA
8 6,000 64.0 59.8 53.5 48.4 NA NA NA NA
12 4,000 69.1 64.5 57.7 52.3 47.7 NA NA NA
16 2,000 72.6 68.1 60.9 55.1 50.4 46.4 NA NA
20 0 74.6 71.7 64.1 58.0 53.0 48.8 45.1 NA
-5 15,000 46.4 NA NA NA NA NA NA NA
-3 14,000 47.9 NA NA NA NA NA NA NA
1 12,000 50.7 46.8 NA NA NA NA NA NA
5 10,000 54.9 51.1 45.5 NA NA NA NA NA
10 9 8,000 58.7 54.7 49.0 NA NA NA NA NA
13 6,000 63.4 59.1 52.9 47.9 NA NA NA NA
17 4,000 67.7 63.3 56.6 51.3 46.8 NA NA NA
21 2,000 71.7 67.2 60.1 54.4 49.8 45.7 NA NA
25 0 74.6 71.1 63.5 57.5 52.6 48.4 NA NA
NOTES: 1. Maximum climb weights are limited by the design MAX TOGW of 74,600 lb for the GIV-SP and
73,200 for the GIV.
2. Increase MAX TOGW by 300 lb for each 10 knots of headwind up to a maximum of 40 knots.
Data not valid for tailwinds.
3. Cowl anti-ice bleeds are assumed ON for temperatures below 10° C; wing anti-ice bleeds
prohibited.

NON-SP GIV PERFORMANCE REVISION 24 (RE-ISSUE)

Page PA - 46 (NON-SP GIV AIRPLANES ONLY) Mar 17/10
Quick Reference Handbook
Non-SP GIV Climb Limited Weights, Flaps 20°, Standard
Instrument Departure, ctd… GIV-OIS-7

GIV TAKEOFF GROSS WEIGHT LIMITED BY REQUIRED SID CLIMB GRADIENT

6000 FT AGL, FLAPS 20, ONE ENGINE OPERATING, ctd…
DELTA AIRPORT AIRPORT
ISA AMBIENT PRESS TAKEOFF GROSS WEIGHT (1000 LB)
TEMP TEMP ALTITUDE REQUIRED SID CLIMB GRADIENT (FT/NM)
(DEG C) (DEG C) (FT) 200 300 400 500 600 700 800 900
0 15,000 45.1 NA NA NA NA NA NA NA
2 14,000 46.6 NA NA NA NA NA NA NA
6 12,000 49.3 45.3 NA NA NA NA NA NA
10 10,000 54.3 50.4 NA NA NA NA NA NA
15 14 8,000 58.1 54.1 48.4 NA NA NA NA NA
18 6,000 62.2 58.0 51.9 46.9 NA NA NA NA
22 4,000 66.4 62.0 55.5 50.3 45.9 NA NA NA
26 2,000 70.8 66.3 59.3 53.7 49.1 45.1 NA NA
30 0 74.6 70.4 62.9 56.9 52.1 47.9 NA NA
5 15,000 NA NA NA NA NA NA NA NA
7 14,000 45.1 NA NA NA NA NA NA NA
11 12,000 48.5 NA NA NA NA NA NA NA
15 10,000 53.3 49.4 NA NA NA NA NA NA
20 19 8,000 56.9 53.0 47.4 NA NA NA NA NA
23 6,000 60.9 56.8 50.9 45.9 NA NA NA NA
27 4,000 64.8 60.7 54.4 49.2 NA NA NA NA
31 2,000 68.4 64.3 57.5 52.2 47.6 NA NA NA
35 0 72.3 68.0 60.8 55.1 50.4 46.3 NA NA
10 15,000 NA NA NA NA NA NA NA NA
12 14,000 NA NA NA NA NA NA NA NA
16 12,000 46.9 NA NA NA NA NA NA NA
20 10,000 52.2 48.2 NA NA NA NA NA NA
25 24 8,000 55.6 51.9 46.3 NA NA NA NA NA
28 6,000 59.4 55.5 49.7 NA NA NA NA NA
32 4,000 62.5 58.7 52.7 47.6 NA NA NA NA
36 2,000 65.9 62.1 55.6 50.5 46.0 NA NA NA
40 0 69.2 65.3 58.5 53.0 48.5 NA NA NA
15 15,000 NA NA NA NA NA NA NA NA
17 14,000 NA NA NA NA NA NA NA NA
21 12,000 45.4 NA NA NA NA NA NA NA
25 10,000 51.1 47.1 NA NA NA NA NA NA
30 29 8,000 54.2 50.5 NA NA NA NA NA NA
33 6,000 57.2 53.6 48.0 NA NA NA NA NA
37 4,000 60.1 56.7 50.9 45.9 NA NA NA NA
41 2,000 62.8 59.5 53.4 48.3 NA NA NA NA
45 0 65.4 62.2 55.8 50.6 46.1 NA NA NA
NOTES: 1. Maximum climb weights are limited by the design MAX TOGW of 74,600 lb for the GIV-SP and
73,200 for the GIV.
2. Increase MAX TOGW by 300 lb for each 10 knots of headwind up to a maximum of 40 knots.
Data not valid for tailwinds.
3. Cowl anti-ice bleeds are assumed ON for temperatures below 10° C; wing anti-ice bleeds
prohibited.

REVISION 24 (RE-ISSUE) NON-SP GIV PERFORMANCE

Mar 17/10 (NON-SP GIV AIRPLANES ONLY) Page PA - 47
 Quick Reference Handbook
Non-SP GIV Takeoff Climb Requirements:
Climb Limited Weights:
Flaps 10° - Standard Instrument Departure GIV-OIS-7

NOTE: For complete text and examples, see GIV Operating Manual
Section 11-04-40 or Operational Information Supplement number GIV-
OIS-07: Standard Instrument Departure (SID) Climb Performance.
GIV TAKEOFF GROSS WEIGHT LIMITED BY REQUIRED SID CLIMB GRADIENT
1000 FT AGL, FLAPS 10, ONE ENGINE OPERATING
DELTA AIRPORT AIRPORT
ISA AMBIENT PRESS TAKEOFF GROSS WEIGHT (1000 LB)
TEMP TEMP ALTITUDE REQUIRED SID CLIMB GRADIENT (FT/NM)
(DEG C) (DEG C) (FT) 200 300 400 500 600 700 800 900
< -20 15,000 60.1 52.0 45.9 NA NA NA NA NA
< -18 14,000 62.3 53.9 47.6 NA NA NA NA NA
< -14 12,000 66.9 57.9 51.1 45.8 NA NA NA NA
< -10 10,000 71.7 62.1 54.8 49.0 NA NA NA NA
< -5 < -6 8,000 74.6 66.4 58.6 52.5 47.6 NA NA NA
< -2 6,000 74.6 70.9 62.6 56.0 50.7 46.6 NA NA
<2 4,000 74.6 74.6 66.8 59.9 54.2 49.6 45.9 NA
<6 2,000 74.6 74.6 69.7 62.4 56.4 51.7 47.7 NA
< 10 0 74.6 74.6 72.2 64.7 58.5 53.5 49.4 45.9
-15 15,000 59.6 51.6 45.5 NA NA NA NA NA
-13 14,000 61.8 53.5 47.2 NA NA NA NA NA
-9 12,000 66.4 57.5 50.7 45.4 NA NA NA NA
-5 10,000 71.1 61.6 54.3 48.7 NA NA NA NA
0 -1 8,000 74.6 65.9 58.2 52.1 47.3 NA NA NA
3 6,000 74.6 70.5 62.2 55.7 50.5 46.3 NA NA
7 4,000 74.6 74.6 66.4 59.5 53.8 49.3 45.6 NA
11 2,000 74.6 74.6 70.2 62.9 56.9 52.0 48.1 NA
15 0 74.6 74.6 72.2 64.7 58.5 53.4 49.3 45.9
-10 15,000 59.1 51.1 45.1 NA NA NA NA NA
-8 14,000 61.3 53.0 46.8 NA NA NA NA NA
-4 12,000 65.7 56.9 50.2 NA NA NA NA NA
0 10,000 70.3 60.8 53.7 48.1 NA NA NA NA
5 4 8,000 74.6 65.1 57.4 51.4 46.7 NA NA NA
8 6,000 74.6 69.6 61.4 55.0 49.8 45.7 NA NA
12 4,000 74.6 74.6 66.3 59.4 53.7 49.2 45.5 NA
16 2,000 74.6 74.6 69.5 62.2 56.3 51.5 47.6 NA
20 0 74.6 74.6 72.2 64.6 58.5 53.4 49.3 45.9
-5 15,000 58.1 50.2 NA NA NA NA NA NA
-3 14,000 60.1 52.0 45.9 NA NA NA NA NA
1 12,000 64.4 55.8 49.2 NA NA NA NA NA
5 10,000 68.8 59.6 52.6 47.2 NA NA NA NA
10 9 8,000 73.6 63.8 56.3 50.4 45.8 NA NA NA
13 6,000 74.6 68.9 60.8 54.5 49.4 45.3 NA NA
17 4,000 74.6 73.7 65.1 58.3 52.8 48.4 NA NA
21 2,000 74.6 74.6 68.8 61.6 55.7 51.0 47.2 NA
25 0 74.6 74.6 72.1 64.6 58.5 53.4 49.3 45.9
NOTES: 1. Maximum climb weights are limited by the design MAX TOGW of 74,600 lb for the GIV-SP and
73,200 for the GIV.
2. Increase MAX TOGW by 300 lb for each 10 knots of headwind up to a maximum of 40 knots.
Data not valid for tailwinds.
3. Cowl anti-ice bleeds are assumed ON for temperatures below 10° C; wing anti-ice bleeds
prohibited.

NON-SP GIV PERFORMANCE REVISION 24 (RE-ISSUE)

Page PA - 48 (NON-SP GIV AIRPLANES ONLY) Mar 17/10
Quick Reference Handbook
Non-SP GIV Climb Limited Weights, Flaps 10°, Standard
Instrument Departure, ctd… GIV-OIS-7

GIV TAKEOFF GROSS WEIGHT LIMITED BY REQUIRED SID CLIMB GRADIENT

1000 FT AGL, FLAPS 10, ONE ENGINE OPERATING, ctd…
DELTA AIRPORT AIRPORT
ISA AMBIENT PRESS TAKEOFF GROSS WEIGHT (1000 LB)
TEMP TEMP ALTITUDE REQUIRED SID CLIMB GRADIENT (FT/NM)
(DEG C) (DEG C) (FT) 200 300 400 500 600 700 800 900
0 15,000 56.8 49.2 NA NA NA NA NA NA
2 14,000 58.8 50.9 NA NA NA NA NA NA
6 12,000 63.0 54.6 48.2 NA NA NA NA NA
10 10,000 68.0 58.9 51.9 46.6 NA NA NA NA
15 14 8,000 72.8 63.0 55.6 49.9 45.3 NA NA NA
18 6,000 74.6 67.6 59.7 53.5 48.5 NA NA NA
22 4,000 74.6 72.4 63.9 57.3 51.9 47.6 NA NA
26 2,000 74.6 74.6 68.1 61.0 55.1 50.5 46.7 NA
30 0 74.6 74.6 71.7 64.2 58.1 53.1 49.0 45.6
5 15,000 55.5 48.1 NA NA NA NA NA NA
7 14,000 57.5 49.8 NA NA NA NA NA NA
11 12,000 62.1 53.8 47.5 NA NA NA NA NA
15 10,000 66.6 57.6 50.9 45.7 NA NA NA NA
20 19 8,000 71.3 61.8 54.6 48.9 NA NA NA NA
23 6,000 74.6 66.3 58.6 52.5 47.7 NA NA NA
27 4,000 74.6 70.7 62.5 56.0 50.8 46.6 NA NA
31 2,000 74.6 74.1 65.5 58.7 53.2 48.8 45.1 NA
35 0 74.6 74.6 68.4 61.3 55.5 50.8 47.0 NA
10 15,000 54.7 47.3 NA NA NA NA NA NA
12 14,000 56.7 49.1 NA NA NA NA NA NA
16 12,000 60.8 52.6 46.5 NA NA NA NA NA
20 10,000 65.1 56.4 49.8 NA NA NA NA NA
25 24 8,000 69.8 60.5 53.4 48.0 NA NA NA NA
28 6,000 74.6 64.9 57.3 51.4 46.7 NA NA NA
32 4,000 74.6 67.8 60.0 53.8 48.8 NA NA NA
36 2,000 74.6 70.7 62.5 56.0 50.9 46.7 NA NA
40 0 74.6 73.6 65.1 58.3 52.9 48.5 NA NA
15 15,000 53.4 46.2 NA NA NA NA NA NA
17 14,000 55.4 47.9 NA NA NA NA NA NA
21 12,000 59.5 51.5 45.6 NA NA NA NA NA
25 10,000 63.7 55.2 48.8 NA NA NA NA NA
30 29 8,000 67.9 58.9 52.0 46.7 NA NA NA NA
33 6,000 71.3 61.9 54.7 49.1 NA NA NA NA
37 4,000 74.4 64.6 57.1 51.3 46.7 NA NA NA
41 2,000 74.6 67.2 59.4 53.3 48.5 NA NA NA
45 0 74.6 69.9 61.9 55.4 50.4 46.3 NA NA
NOTES: 1. Maximum climb weights are limited by the design MAX TOGW of 74,600 lb for the GIV-SP and
73,200 for the GIV.
2. Increase MAX TOGW by 300 lb for each 10 knots of headwind up to a maximum of 40 knots.
Data not valid for tailwinds.
3. Cowl anti-ice bleeds are assumed ON for temperatures below 10° C; wing anti-ice bleeds
prohibited.

REVISION 24 (RE-ISSUE) NON-SP GIV PERFORMANCE

Mar 17/10 (NON-SP GIV AIRPLANES ONLY) Page PA - 49
 Quick Reference Handbook
Non-SP GIV Climb Limited Weights, Flaps 10°, Standard
Instrument Departure, ctd… GIV-OIS-7

GIV TAKEOFF GROSS WEIGHT LIMITED BY REQUIRED SID CLIMB GRADIENT

2000 FT AGL, FLAPS 10, ONE ENGINE OPERATING
DELTA AIRPORT AIRPORT
ISA AMBIENT PRESS TAKEOFF GROSS WEIGHT (1000 LB)
TEMP TEMP ALTITUDE REQUIRED SID CLIMB GRADIENT (FT/NM)
(DEG C) (DEG C) (FT) 200 300 400 500 600 700 800 900
< -20 15,000 59.2 51.3 45.4 NA NA NA NA NA
< -18 14,000 61.3 53.2 47.1 NA NA NA NA NA
< -14 12,000 65.8 57.2 50.6 45.4 NA NA NA NA
< -10 10,000 70.6 61.3 54.2 48.7 NA NA NA NA
< -5 < -6 8,000 74.6 65.6 58.0 52.1 47.4 NA NA NA
< -2 6,000 74.6 70.1 62.0 55.6 50.5 46.4 NA NA
<2 4,000 74.6 74.6 66.2 59.5 53.9 49.4 45.8 NA
<6 2,000 74.6 74.6 69.7 62.4 56.4 51.7 47.7 NA
< 10 0 74.6 74.6 72.2 64.7 58.5 53.5 49.4 45.9
-15 15,000 58.7 50.9 45.0 NA NA NA NA NA
-13 14,000 60.8 52.8 46.7 NA NA NA NA NA
-9 12,000 65.3 56.7 50.2 45.1 NA NA NA NA
-5 10,000 70.0 60.8 53.8 48.3 NA NA NA NA
0 -1 8,000 74.6 65.1 57.6 51.7 47.1 NA NA NA
3 6,000 74.6 69.7 61.7 55.3 50.2 46.1 NA NA
7 4,000 74.6 74.4 65.8 59.1 53.6 49.2 45.5 NA
11 2,000 74.6 74.6 70.0 62.8 56.9 52.0 48.1 NA
15 0 74.6 74.6 72.2 64.7 58.5 53.4 49.3 45.9
-10 15,000 58.0 50.3 NA NA NA NA NA NA
-8 14,000 60.3 52.4 46.3 NA NA NA NA NA
-4 12,000 64.7 56.2 49.7 NA NA NA NA NA
0 10,000 69.2 60.2 53.2 47.8 NA NA NA NA
5 4 8,000 74.0 64.3 56.9 51.0 46.5 NA NA NA
8 6,000 74.6 68.7 60.8 54.6 49.6 45.5 NA NA
12 4,000 74.6 74.2 65.7 58.9 53.5 49.0 45.4 NA
16 2,000 74.6 74.6 69.4 62.2 56.3 51.5 47.6 NA
20 0 74.6 74.6 72.0 64.6 58.5 53.4 49.3 45.9
-5 15,000 56.7 49.2 NA NA NA NA NA NA
-3 14,000 59.2 51.4 45.5 NA NA NA NA NA
1 12,000 63.4 55.1 48.7 NA NA NA NA NA
5 10,000 67.8 58.9 52.1 46.9 NA NA NA NA
10 9 8,000 72.5 63.0 55.8 50.1 45.6 NA NA NA
13 6,000 74.6 68.0 60.2 54.1 49.1 45.1 NA NA
17 4,000 74.6 72.8 64.5 57.9 52.5 48.2 NA NA
21 2,000 74.6 74.6 68.5 61.4 55.7 51.0 47.2 NA
25 0 74.6 74.6 71.8 64.4 58.4 53.4 49.3 45.9
NOTES: 1. Maximum climb weights are limited by the design MAX TOGW of 74,600 lb for the GIV-SP and
73,200 for the GIV.
2. Increase MAX TOGW by 300 lb for each 10 knots of headwind up to a maximum of 40 knots.
Data not valid for tailwinds.
3. Cowl anti-ice bleeds are assumed ON for temperatures below 10° C; wing anti-ice bleeds
prohibited.

NON-SP GIV PERFORMANCE REVISION 24 (RE-ISSUE)

Page PA - 50 (NON-SP GIV AIRPLANES ONLY) Mar 17/10
Quick Reference Handbook
Non-SP GIV Climb Limited Weights, Flaps 10°, Standard
Instrument Departure, ctd… GIV-OIS-7

GIV TAKEOFF GROSS WEIGHT LIMITED BY REQUIRED SID CLIMB GRADIENT

2000 FT AGL, FLAPS 10, ONE ENGINE OPERATING, ctd…
DELTA AIRPORT AIRPORT
ISA AMBIENT PRESS TAKEOFF GROSS WEIGHT (1000 LB)
TEMP TEMP ALTITUDE REQUIRED SID CLIMB GRADIENT (FT/NM)
(DEG C) (DEG C) (FT) 200 300 400 500 600 700 800 900
0 15,000 55.2 47.9 NA NA NA NA NA NA
2 14,000 57.9 50.3 NA NA NA NA NA NA
6 12,000 62.0 53.9 47.7 NA NA NA NA NA
10 10,000 66.9 58.2 51.5 46.3 NA NA NA NA
15 14 8,000 71.6 62.3 55.1 49.5 45.1 NA NA NA
18 6,000 74.6 66.8 59.1 53.1 48.3 NA NA NA
22 4,000 74.6 71.5 63.3 56.8 51.6 47.4 NA NA
26 2,000 74.6 74.6 67.5 60.6 54.9 50.4 46.7 NA
30 0 74.6 74.6 71.4 64.1 58.1 53.1 49.0 45.6
5 15,000 53.7 46.6 NA NA NA NA NA NA
7 14,000 56.6 49.2 NA NA NA NA NA NA
11 12,000 61.2 53.1 47.1 NA NA NA NA NA
15 10,000 65.5 56.9 50.4 45.3 NA NA NA NA
20 19 8,000 70.2 61.0 54.0 48.6 NA NA NA NA
23 6,000 74.6 65.4 58.0 52.0 47.4 NA NA NA
27 4,000 74.6 69.9 61.9 55.6 50.5 46.5 NA NA
31 2,000 74.6 73.7 65.3 58.6 53.2 48.8 45.1 NA
35 0 74.6 74.6 68.2 61.3 55.5 50.8 47.0 NA
10 15,000 52.7 45.8 NA NA NA NA NA NA
12 14,000 55.7 48.5 NA NA NA NA NA NA
16 12,000 59.8 52.0 46.1 NA NA NA NA NA
20 10,000 64.1 55.7 49.4 NA NA NA NA NA
25 24 8,000 68.7 59.8 52.9 47.6 NA NA NA NA
28 6,000 73.5 64.0 56.7 50.9 46.4 NA NA NA
32 4,000 74.6 67.4 59.8 53.7 48.8 NA NA NA
36 2,000 74.6 70.3 62.3 56.0 50.9 46.7 NA NA
40 0 74.6 73.2 64.9 58.3 52.9 48.5 NA NA
15 15,000 51.2 NA NA NA NA NA NA NA
17 14,000 54.4 47.3 NA NA NA NA NA NA
21 12,000 58.5 50.8 45.1 NA NA NA NA NA
25 10,000 62.7 54.5 48.3 NA NA NA NA NA
30 29 8,000 67.0 58.2 51.6 46.5 NA NA NA NA
33 6,000 70.6 61.5 54.5 49.0 NA NA NA NA
37 4,000 73.7 64.2 57.0 51.3 46.7 NA NA NA
41 2,000 74.6 66.8 59.3 53.3 48.5 NA NA NA
45 0 74.6 69.6 61.7 55.4 50.4 46.3 NA NA
NOTES: 1. Maximum climb weights are limited by the design MAX TOGW of 74,600 lb for the GIV-SP and
73,200 for the GIV.
2. Increase MAX TOGW by 300 lb for each 10 knots of headwind up to a maximum of 40 knots.
Data not valid for tailwinds.
3. Cowl anti-ice bleeds are assumed ON for temperatures below 10° C; wing anti-ice bleeds
prohibited.

REVISION 24 (RE-ISSUE) NON-SP GIV PERFORMANCE

Mar 17/10 (NON-SP GIV AIRPLANES ONLY) Page PA - 51
 Quick Reference Handbook
Non-SP GIV Climb Limited Weights, Flaps 10°, Standard
Instrument Departure, ctd… GIV-OIS-7

GIV TAKEOFF GROSS WEIGHT LIMITED BY REQUIRED SID CLIMB GRADIENT

3000 FT AGL, FLAPS 10, ONE ENGINE OPERATING
DELTA AIRPORT AIRPORT
ISA AMBIENT PRESS TAKEOFF GROSS WEIGHT (1000 LB)
TEMP TEMP ALTITUDE REQUIRED SID CLIMB GRADIENT (FT/NM)
(DEG C) (DEG C) (FT) 200 300 400 500 600 700 800 900
< -20 15,000 58.1 50.5 NA NA NA NA NA NA
< -18 14,000 60.3 52.4 46.4 NA NA NA NA NA
< -14 12,000 64.7 56.3 49.8 NA NA NA NA NA
< -10 10,000 69.4 60.4 53.4 48.0 NA NA NA NA
< -5 < -6 8,000 74.2 64.6 57.2 51.4 46.8 NA NA NA
< -2 6,000 74.6 69.1 61.2 54.9 49.9 45.9 NA NA
<2 4,000 74.6 73.7 65.3 58.7 53.3 48.9 45.3 NA
<6 2,000 74.6 74.6 68.7 61.7 56.0 51.3 47.5 NA
< 10 0 74.6 74.6 71.9 64.6 58.5 53.5 49.4 45.9
-15 15,000 57.6 50.0 NA NA NA NA NA NA
-13 14,000 59.7 51.9 46.0 NA NA NA NA NA
-9 12,000 64.2 55.8 49.4 NA NA NA NA NA
-5 10,000 68.8 59.9 53.0 47.7 NA NA NA NA
0 -1 8,000 73.7 64.1 56.8 51.0 46.4 NA NA NA
3 6,000 74.6 68.6 60.8 54.6 49.6 45.6 NA NA
7 4,000 74.6 73.2 64.9 58.3 52.9 48.6 NA NA
11 2,000 74.6 74.6 69.0 62.0 56.2 51.6 47.7 NA
15 0 74.6 74.6 71.9 64.6 58.5 53.4 49.3 45.9
-10 15,000 56.8 49.3 NA NA NA NA NA NA
-8 14,000 59.1 51.3 45.5 NA NA NA NA NA
-4 12,000 63.6 55.3 49.0 NA NA NA NA NA
0 10,000 68.0 59.2 52.4 47.1 NA NA NA NA
5 4 8,000 72.7 63.3 56.1 50.3 45.9 NA NA NA
8 6,000 74.6 67.7 60.0 53.9 49.0 45.0 NA NA
12 4,000 74.6 73.0 64.7 58.1 52.8 48.5 NA NA
16 2,000 74.6 74.6 68.4 61.4 55.7 51.1 47.3 NA
20 0 74.6 74.6 71.4 64.2 58.2 53.3 49.3 45.9
-5 15,000 55.2 48.0 NA NA NA NA NA NA
-3 14,000 57.7 50.2 NA NA NA NA NA NA
1 12,000 62.3 54.2 48.0 NA NA NA NA NA
5 10,000 66.7 58.0 51.4 46.3 NA NA NA NA
10 9 8,000 71.3 62.0 55.0 49.4 NA NA NA NA
13 6,000 74.6 67.0 59.4 53.3 48.5 NA NA NA
17 4,000 74.6 71.7 63.5 57.1 51.8 47.7 NA NA
21 2,000 74.6 74.6 67.5 60.6 55.0 50.5 46.8 NA
25 0 74.6 74.6 71.0 63.8 57.9 53.0 49.0 45.7
NOTES: 1. Maximum climb weights are limited by the design MAX TOGW of 74,600 lb for the GIV-SP and
73,200 for the GIV.
2. Increase MAX TOGW by 300 lb for each 10 knots of headwind up to a maximum of 40 knots.
Data not valid for tailwinds.
3. Cowl anti-ice bleeds are assumed ON for temperatures below 10° C; wing anti-ice bleeds
prohibited.

NON-SP GIV PERFORMANCE REVISION 24 (RE-ISSUE)

Page PA - 52 (NON-SP GIV AIRPLANES ONLY) Mar 17/10
Quick Reference Handbook
Non-SP GIV Climb Limited Weights, Flaps 10°, Standard
Instrument Departure, ctd… GIV-OIS-7

GIV TAKEOFF GROSS WEIGHT LIMITED BY REQUIRED SID CLIMB GRADIENT

3000 FT AGL, FLAPS 10, ONE ENGINE OPERATING, ctd…
DELTA AIRPORT AIRPORT
ISA AMBIENT PRESS TAKEOFF GROSS WEIGHT (1000 LB)
TEMP TEMP ALTITUDE REQUIRED SID CLIMB GRADIENT (FT/NM)
(DEG C) (DEG C) (FT) 200 300 400 500 600 700 800 900
0 15,000 53.5 46.6 NA NA NA NA NA NA
2 14,000 56.2 48.9 NA NA NA NA NA NA
6 12,000 61.0 53.1 47.0 NA NA NA NA NA
10 10,000 65.8 57.3 50.7 45.7 NA NA NA NA
15 14 8,000 70.4 61.3 54.3 48.9 NA NA NA NA
18 6,000 74.6 65.7 58.2 52.3 47.6 NA NA NA
22 4,000 74.6 70.3 62.4 56.0 50.9 46.8 NA NA
26 2,000 74.6 74.6 66.6 59.8 54.3 49.9 46.2 NA
30 0 74.6 74.6 70.5 63.3 57.4 52.6 48.7 45.3
5 15,000 51.7 NA NA NA NA NA NA NA
7 14,000 54.7 47.6 NA NA NA NA NA NA
11 12,000 60.2 52.3 46.4 NA NA NA NA NA
15 10,000 64.4 56.0 49.7 NA NA NA NA NA
20 19 8,000 69.0 60.1 53.2 47.9 NA NA NA NA
23 6,000 74.0 64.4 57.1 51.3 46.8 NA NA NA
27 4,000 74.6 68.8 61.0 54.8 49.9 45.9 NA NA
31 2,000 74.6 72.8 64.6 58.0 52.7 48.5 NA NA
35 0 74.6 74.6 67.6 60.8 55.1 50.6 46.9 NA
10 15,000 50.7 NA NA NA NA NA NA NA
12 14,000 53.7 46.8 NA NA NA NA NA NA
16 12,000 58.8 51.2 45.4 NA NA NA NA NA
20 10,000 63.0 54.8 48.6 NA NA NA NA NA
25 24 8,000 67.6 58.8 52.2 47.0 NA NA NA NA
28 6,000 72.2 62.9 55.8 50.2 45.8 NA NA NA
32 4,000 74.6 66.7 59.2 53.2 48.5 NA NA NA
36 2,000 74.6 69.6 61.8 55.5 50.6 46.5 NA NA
40 0 74.6 72.6 64.4 57.9 52.7 48.4 NA NA
15 15,000 48.9 NA NA NA NA NA NA NA
17 14,000 52.1 45.4 NA NA NA NA NA NA
21 12,000 57.5 50.0 NA NA NA NA NA NA
25 10,000 61.7 53.7 47.7 NA NA NA NA NA
30 29 8,000 65.8 57.3 50.8 45.8 NA NA NA NA
33 6,000 69.6 60.7 53.8 48.5 NA NA NA NA
37 4,000 72.8 63.5 56.4 50.8 46.3 NA NA NA
41 2,000 74.6 66.2 58.8 53.0 48.3 NA NA NA
45 0 74.6 69.0 61.2 55.0 50.2 46.1 NA NA
NOTES: 1. Maximum climb weights are limited by the design MAX TOGW of 74,600 lb for the GIV-SP and
73,200 for the GIV.
2. Increase MAX TOGW by 300 lb for each 10 knots of headwind up to a maximum of 40 knots.
Data not valid for tailwinds.
3. Cowl anti-ice bleeds are assumed ON for temperatures below 10° C; wing anti-ice bleeds
prohibited.

REVISION 24 (RE-ISSUE) NON-SP GIV PERFORMANCE

Mar 17/10 (NON-SP GIV AIRPLANES ONLY) Page PA - 53
 Quick Reference Handbook
Non-SP GIV Climb Limited Weights, Flaps 10°, Standard
Instrument Departure, ctd… GIV-OIS-7

GIV TAKEOFF GROSS WEIGHT LIMITED BY REQUIRED SID CLIMB GRADIENT

4000 FT AGL, FLAPS 10, ONE ENGINE OPERATING
DELTA AIRPORT AIRPORT
ISA AMBIENT PRESS TAKEOFF GROSS WEIGHT (1000 LB)
TEMP TEMP ALTITUDE REQUIRED SID CLIMB GRADIENT (FT/NM)
(DEG C) (DEG C) (FT) 200 300 400 500 600 700 800 900
< -20 15,000 57.3 49.8 NA NA NA NA NA NA
< -18 14,000 59.3 51.6 45.7 NA NA NA NA NA
< -14 12,000 63.7 55.4 49.1 NA NA NA NA NA
< -10 10,000 68.3 59.5 52.7 47.4 NA NA NA NA
< -5 < -6 8,000 73.1 63.7 56.5 50.7 46.2 NA NA NA
< -2 6,000 74.6 68.1 60.4 54.2 49.3 45.4 NA NA
<2 4,000 74.6 72.7 64.5 57.9 52.6 48.4 NA NA
<6 2,000 74.6 74.6 67.8 60.9 55.3 50.8 47.1 NA
< 10 0 74.6 74.6 71.6 64.4 58.4 53.5 49.4 45.9
-15 15,000 56.8 49.4 NA NA NA NA NA NA
-13 14,000 58.8 51.1 45.3 NA NA NA NA NA
-9 12,000 63.2 55.0 48.7 NA NA NA NA NA
-5 10,000 67.7 59.0 52.3 47.1 NA NA NA NA
0 -1 8,000 72.6 63.2 56.0 50.4 45.9 NA NA NA
3 6,000 74.6 67.6 60.0 53.9 49.0 45.1 NA NA
7 4,000 74.6 72.2 64.1 57.6 52.3 48.1 NA NA
11 2,000 74.6 74.6 68.2 61.3 55.6 51.0 47.3 NA
15 0 74.6 74.6 71.4 64.2 58.2 53.4 49.3 45.9
-10 15,000 56.0 48.7 NA NA NA NA NA NA
-8 14,000 57.9 50.4 NA NA NA NA NA NA
-4 12,000 62.6 54.5 48.3 NA NA NA NA NA
0 10,000 67.0 58.4 51.7 46.6 NA NA NA NA
5 4 8,000 71.7 62.5 55.4 49.8 45.4 NA NA NA
8 6,000 74.6 66.8 59.2 53.2 48.4 NA NA NA
12 4,000 74.6 72.0 63.8 57.4 52.1 47.9 NA NA
16 2,000 74.6 74.6 67.5 60.6 55.0 50.6 46.8 NA
20 0 74.6 74.6 71.0 63.8 57.9 53.1 49.1 45.8
-5 15,000 54.5 47.5 NA NA NA NA NA NA
-3 14,000 56.4 49.0 NA NA NA NA NA NA
1 12,000 61.4 53.4 47.4 NA NA NA NA NA
5 10,000 65.7 57.2 50.7 45.7 NA NA NA NA
10 9 8,000 70.2 61.2 54.3 48.8 NA NA NA NA
13 6,000 74.6 66.1 58.6 52.7 48.0 NA NA NA
17 4,000 74.6 70.7 62.7 56.3 51.2 47.1 NA NA
21 2,000 74.6 74.6 66.6 59.9 54.3 49.9 46.3 NA
25 0 74.6 74.6 70.4 63.3 57.4 52.6 48.7 45.4
NOTES: 1. Maximum climb weights are limited by the design MAX TOGW of 74,600 lb for the GIV-SP and
73,200 for the GIV.
2. Increase MAX TOGW by 300 lb for each 10 knots of headwind up to a maximum of 40 knots.
Data not valid for tailwinds.
3. Cowl anti-ice bleeds are assumed ON for temperatures below 10° C; wing anti-ice bleeds
prohibited.

NON-SP GIV PERFORMANCE REVISION 24 (RE-ISSUE)

Page PA - 54 (NON-SP GIV AIRPLANES ONLY) Mar 17/10
Quick Reference Handbook
Non-SP GIV Climb Limited Weights, Flaps 10°, Standard
Instrument Departure, ctd… GIV-OIS-7

GIV TAKEOFF GROSS WEIGHT LIMITED BY REQUIRED SID CLIMB GRADIENT

4000 FT AGL, FLAPS 10, ONE ENGINE OPERATING, ctd…
DELTA AIRPORT AIRPORT
ISA AMBIENT PRESS TAKEOFF GROSS WEIGHT (1000 LB)
TEMP TEMP ALTITUDE REQUIRED SID CLIMB GRADIENT (FT/NM)
(DEG C) (DEG C) (FT) 200 300 400 500 600 700 800 900
0 15,000 52.9 46.1 NA NA NA NA NA NA
2 14,000 54.6 47.6 NA NA NA NA NA NA
6 12,000 60.1 52.3 46.4 NA NA NA NA NA
10 10,000 64.8 56.5 50.1 45.1 NA NA NA NA
15 14 8,000 69.4 60.5 53.6 48.3 NA NA NA NA
18 6,000 74.3 64.8 57.5 51.7 47.1 NA NA NA
22 4,000 74.6 69.3 61.5 55.3 50.3 46.3 NA NA
26 2,000 74.6 74.0 65.7 59.1 53.7 49.3 45.7 NA
30 0 74.6 74.6 69.6 62.6 56.8 52.1 48.2 NA
5 15,000 51.2 NA NA NA NA NA NA NA
7 14,000 52.8 46.0 NA NA NA NA NA NA
11 12,000 59.2 51.6 45.8 NA NA NA NA NA
15 10,000 63.4 55.3 49.1 NA NA NA NA NA
20 19 8,000 67.9 59.2 52.5 47.3 NA NA NA NA
23 6,000 72.8 63.5 56.3 50.7 46.2 NA NA NA
27 4,000 74.6 67.8 60.2 54.1 49.3 45.3 NA NA
31 2,000 74.6 71.8 63.7 57.3 52.1 48.0 NA NA
35 0 74.6 74.6 67.1 60.3 54.8 50.3 46.6 NA
10 15,000 50.2 NA NA NA NA NA NA NA
12 14,000 51.8 45.1 NA NA NA NA NA NA
16 12,000 57.9 50.4 NA NA NA NA NA NA
20 10,000 62.0 54.1 48.0 NA NA NA NA NA
25 24 8,000 66.6 58.0 51.5 46.4 NA NA NA NA
28 6,000 71.1 62.0 55.0 49.6 45.2 NA NA NA
32 4,000 74.6 65.7 58.3 52.5 47.9 NA NA NA
36 2,000 74.6 69.0 61.3 55.1 50.3 46.3 NA NA
40 0 74.6 72.0 64.0 57.5 52.4 48.2 NA NA
15 15,000 48.4 NA NA NA NA NA NA NA
17 14,000 49.9 NA NA NA NA NA NA NA
21 12,000 56.6 49.3 NA NA NA NA NA NA
25 10,000 60.7 52.9 47.0 NA NA NA NA NA
30 29 8,000 64.8 56.5 50.1 45.2 NA NA NA NA
33 6,000 68.7 59.9 53.2 48.0 NA NA NA NA
37 4,000 72.1 63.0 55.9 50.4 46.0 NA NA NA
41 2,000 74.6 65.7 58.4 52.6 48.0 NA NA NA
45 0 74.6 68.5 60.8 54.7 49.9 45.9 NA NA
NOTES: 1. Maximum climb weights are limited by the design MAX TOGW of 74,600 lb for the GIV-SP and
73,200 for the GIV.
2. Increase MAX TOGW by 300 lb for each 10 knots of headwind up to a maximum of 40 knots.
Data not valid for tailwinds.
3. Cowl anti-ice bleeds are assumed ON for temperatures below 10° C; wing anti-ice bleeds
prohibited.

REVISION 24 (RE-ISSUE) NON-SP GIV PERFORMANCE

Mar 17/10 (NON-SP GIV AIRPLANES ONLY) Page PA - 55
 Quick Reference Handbook
Non-SP GIV Climb Limited Weights, Flaps 10°, Standard
Instrument Departure, ctd… GIV-OIS-7

GIV TAKEOFF GROSS WEIGHT LIMITED BY REQUIRED SID CLIMB GRADIENT

5000 FT AGL, FLAPS 10, ONE ENGINE OPERATING
DELTA AIRPORT AIRPORT
ISA AMBIENT PRESS TAKEOFF GROSS WEIGHT (1000 LB)
TEMP TEMP ALTITUDE REQUIRED SID CLIMB GRADIENT (FT/NM)
(DEG C) (DEG C) (FT) 200 300 400 500 600 700 800 900
< -20 15,000 56.3 49.0 NA NA NA NA NA NA
< -18 14,000 58.4 50.8 NA NA NA NA NA NA
< -14 12,000 62.6 54.5 48.3 NA NA NA NA NA
< -10 10,000 67.1 58.5 51.8 46.7 NA NA NA NA
< -5 < -6 8,000 71.9 62.6 55.5 49.9 45.5 NA NA NA
< -2 6,000 74.6 67.0 59.4 53.4 48.6 NA NA NA
<2 4,000 74.6 71.6 63.5 57.0 51.9 47.7 NA NA
<6 2,000 74.6 74.6 66.7 60.0 54.4 50.0 46.4 NA
< 10 0 74.6 74.6 70.5 63.4 57.5 52.7 48.8 45.4
-15 15,000 56.1 48.8 NA NA NA NA NA NA
-13 14,000 57.9 50.4 NA NA NA NA NA NA
-9 12,000 62.1 54.0 47.9 NA NA NA NA NA
-5 10,000 66.6 58.0 51.4 46.3 NA NA NA NA
0 -1 8,000 71.4 62.2 55.1 49.6 45.2 NA NA NA
3 6,000 74.6 66.5 59.0 53.0 48.3 NA NA NA
7 4,000 74.6 71.1 63.0 56.6 51.5 47.4 NA NA
11 2,000 74.6 74.6 67.1 60.3 54.7 50.2 46.6 NA
15 0 74.6 74.6 70.3 63.1 57.3 52.5 48.6 45.3
-10 15,000 55.3 48.1 NA NA NA NA NA NA
-8 14,000 57.1 49.7 NA NA NA NA NA NA
-4 12,000 61.4 53.4 47.4 NA NA NA NA NA
0 10,000 65.9 57.4 50.9 45.8 NA NA NA NA
5 4 8,000 70.5 61.4 54.5 49.0 NA NA NA NA
8 6,000 74.6 65.7 58.3 52.4 47.7 NA NA NA
12 4,000 74.6 70.9 62.9 56.5 51.4 47.2 NA NA
16 2,000 74.6 74.6 66.4 59.7 54.2 49.8 46.1 NA
20 0 74.6 74.6 69.9 62.8 57.0 52.3 48.4 45.1
-5 15,000 53.8 46.8 NA NA NA NA NA NA
-3 14,000 55.6 48.4 NA NA NA NA NA NA
1 12,000 59.9 52.2 46.3 NA NA NA NA NA
5 10,000 64.6 56.3 49.9 NA NA NA NA NA
10 9 8,000 69.2 60.3 53.4 48.1 NA NA NA NA
13 6,000 74.6 65.0 57.7 51.8 47.2 NA NA NA
17 4,000 74.6 69.5 61.7 55.4 50.4 46.4 NA NA
21 2,000 74.6 73.8 65.5 58.9 53.5 49.2 45.5 NA
25 0 74.6 74.6 69.3 62.3 56.5 51.9 48.0 NA
NOTES: 1. Maximum climb weights are limited by the design MAX TOGW of 74,600 lb for the GIV-SP and
73,200 for the GIV.
2. Increase MAX TOGW by 300 lb for each 10 knots of headwind up to a maximum of 40 knots.
Data not valid for tailwinds.
3. Cowl anti-ice bleeds are assumed ON for temperatures below 10° C; wing anti-ice bleeds
prohibited.

NON-SP GIV PERFORMANCE REVISION 24 (RE-ISSUE)

Page PA - 56 (NON-SP GIV AIRPLANES ONLY) Mar 17/10
Quick Reference Handbook
Non-SP GIV Climb Limited Weights, Flaps 10°, Standard
Instrument Departure, ctd… GIV-OIS-7

GIV TAKEOFF GROSS WEIGHT LIMITED BY REQUIRED SID CLIMB GRADIENT

5000 FT AGL, FLAPS 10, ONE ENGINE OPERATING, ctd…
DELTA AIRPORT AIRPORT
ISA AMBIENT PRESS TAKEOFF GROSS WEIGHT (1000 LB)
TEMP TEMP ALTITUDE REQUIRED SID CLIMB GRADIENT (FT/NM)
(DEG C) (DEG C) (FT) 200 300 400 500 600 700 800 900
0 15,000 52.3 45.5 NA NA NA NA NA NA
2 14,000 53.9 47.0 NA NA NA NA NA NA
6 12,000 58.4 50.8 45.1 NA NA NA NA NA
10 10,000 63.8 55.6 49.3 NA NA NA NA NA
15 14 8,000 68.3 59.5 52.8 47.5 NA NA NA NA
18 6,000 73.1 63.7 56.5 50.8 46.4 NA NA NA
22 4,000 74.6 68.2 60.5 54.4 49.5 45.6 NA NA
26 2,000 74.6 72.8 64.6 58.1 52.8 48.6 NA NA
30 0 74.6 74.6 68.6 61.6 55.9 51.3 47.6 NA
5 15,000 50.6 NA NA NA NA NA NA NA
7 14,000 52.2 45.4 NA NA NA NA NA NA
11 12,000 57.5 50.0 NA NA NA NA NA NA
15 10,000 62.4 54.4 48.3 NA NA NA NA NA
20 19 8,000 66.8 58.3 51.7 46.6 NA NA NA NA
23 6,000 71.7 62.5 55.4 49.9 45.5 NA NA NA
27 4,000 74.6 66.7 59.2 53.2 48.5 NA NA NA
31 2,000 74.6 70.6 62.7 56.3 51.3 47.2 NA NA
35 0 74.6 74.6 66.2 59.6 54.1 49.7 46.1 NA
10 15,000 49.6 NA NA NA NA NA NA NA
12 14,000 51.2 NA NA NA NA NA NA NA
16 12,000 55.9 48.7 NA NA NA NA NA NA
20 10,000 61.0 53.2 47.3 NA NA NA NA NA
25 24 8,000 65.4 57.0 50.6 45.7 NA NA NA NA
28 6,000 70.0 61.0 54.2 48.8 NA NA NA NA
32 4,000 73.9 64.5 57.2 51.6 47.0 NA NA NA
36 2,000 74.6 68.2 60.6 54.5 49.7 45.7 NA NA
40 0 74.6 71.3 63.3 56.9 51.8 47.7 NA NA
15 15,000 47.9 NA NA NA NA NA NA NA
17 14,000 49.4 NA NA NA NA NA NA NA
21 12,000 54.3 47.3 NA NA NA NA NA NA
25 10,000 59.7 52.0 46.3 NA NA NA NA NA
30 29 8,000 63.7 55.6 49.4 NA NA NA NA NA
33 6,000 67.5 58.9 52.3 47.2 NA NA NA NA
37 4,000 71.1 62.1 55.1 49.7 45.4 NA NA NA
41 2,000 74.4 65.0 57.7 52.0 47.5 NA NA NA
45 0 74.6 67.8 60.2 54.2 49.5 45.5 NA NA

NOTES: 1. Maximum climb weights are limited by the design MAX TOGW of 74,600 lb for the GIV-SP and
73,200 for the GIV.
2. Increase MAX TOGW by 300 lb for each 10 knots of headwind up to a maximum of 40 knots.
Data not valid for tailwinds.
3. Cowl anti-ice bleeds are assumed ON for temperatures below 10° C; wing anti-ice bleeds
prohibited.

REVISION 24 (RE-ISSUE) NON-SP GIV PERFORMANCE

Mar 17/10 (NON-SP GIV AIRPLANES ONLY) Page PA - 57
 Quick Reference Handbook
Non-SP GIV Climb Limited Weights, Flaps 10°, Standard
Instrument Departure, ctd… GIV-OIS-7

GIV TAKEOFF GROSS WEIGHT LIMITED BY REQUIRED SID CLIMB GRADIENT

6000 FT AGL, FLAPS 10, ONE ENGINE OPERATING
DELTA AIRPORT AIRPORT
ISA AMBIENT PRESS TAKEOFF GROSS WEIGHT (1000 LB)
TEMP TEMP ALTITUDE REQUIRED SID CLIMB GRADIENT (FT/NM)
(DEG C) (DEG C) (FT) 200 300 400 500 600 700 800 900
< -20 15,000 54.3 48.2 NA NA NA NA NA NA
< -18 14,000 56.3 50.0 NA NA NA NA NA NA
< -14 12,000 60.2 53.6 47.5 NA NA NA NA NA
< -10 10,000 64.3 57.5 51.0 45.9 NA NA NA NA
< -5 < -6 8,000 68.7 61.6 54.6 49.1 NA NA NA NA
< -2 6,000 73.2 65.9 58.5 52.5 47.8 NA NA NA
<2 4,000 74.6 70.5 62.5 56.1 51.0 47.0 NA NA
<6 2,000 74.6 74.0 65.7 59.0 53.6 49.3 45.7 NA
< 10 0 74.6 74.6 69.3 62.3 56.5 51.9 48.0 NA
-15 15,000 54.1 47.8 NA NA NA NA NA NA
-13 14,000 56.2 49.7 NA NA NA NA NA NA
-9 12,000 59.8 53.1 47.1 NA NA NA NA NA
-5 10,000 63.9 57.0 50.6 45.5 NA NA NA NA
0 -1 8,000 68.3 61.2 54.2 48.8 NA NA NA NA
3 6,000 72.9 65.5 58.1 52.2 47.5 NA NA NA
7 4,000 74.6 70.0 62.1 55.7 50.7 46.7 NA NA
11 2,000 74.6 74.4 66.0 59.3 53.9 49.5 45.9 NA
15 0 74.6 74.6 69.1 62.1 56.4 51.7 47.9 NA
-10 15,000 53.6 47.3 NA NA NA NA NA NA
-8 14,000 55.4 49.1 NA NA NA NA NA NA
-4 12,000 58.9 52.3 46.4 NA NA NA NA NA
0 10,000 63.3 56.4 50.0 45.1 NA NA NA NA
5 4 8,000 67.6 60.5 53.6 48.3 NA NA NA NA
8 6,000 72.2 64.7 57.4 51.6 47.0 NA NA NA
12 4,000 74.6 69.8 61.9 55.6 50.6 46.5 NA NA
16 2,000 74.6 73.6 65.3 58.7 53.3 49.0 45.4 NA
20 0 74.6 74.6 68.8 61.8 56.1 51.5 47.7 NA
-5 15,000 52.2 46.2 NA NA NA NA NA NA
-3 14,000 53.9 47.8 NA NA NA NA NA NA
1 12,000 57.2 50.9 45.2 NA NA NA NA NA
5 10,000 62.1 55.4 49.1 NA NA NA NA NA
10 9 8,000 66.3 59.3 52.6 47.4 NA NA NA NA
13 6,000 71.5 64.0 56.8 51.0 46.5 NA NA NA
17 4,000 74.6 68.5 60.7 54.6 49.7 45.7 NA NA
21 2,000 74.6 72.6 64.4 57.9 52.7 48.4 NA NA
25 0 74.6 74.6 68.2 61.3 55.6 51.0 47.3 NA
NOTES: 1. Maximum climb weights are limited by the design MAX TOGW of 74,600 lb for the GIV-SP and
73,200 for the GIV.
2. Increase MAX TOGW by 300 lb for each 10 knots of headwind up to a maximum of 40 knots.
Data not valid for tailwinds.
3. Cowl anti-ice bleeds are assumed ON for temperatures below 10° C; wing anti-ice bleeds
prohibited.

NON-SP GIV PERFORMANCE REVISION 24 (RE-ISSUE)

Page PA - 58 (NON-SP GIV AIRPLANES ONLY) Mar 17/10
Quick Reference Handbook
Non-SP GIV Climb Limited Weights, Flaps 10°, Standard
Instrument Departure, ctd… GIV-OIS-7

GIV TAKEOFF GROSS WEIGHT LIMITED BY REQUIRED SID CLIMB GRADIENT

6000 FT AGL, FLAPS 10, ONE ENGINE OPERATING, ctd…
DELTA AIRPORT AIRPORT
ISA AMBIENT PRESS TAKEOFF GROSS WEIGHT (1000 LB)
TEMP TEMP ALTITUDE REQUIRED SID CLIMB GRADIENT (FT/NM)
(DEG C) (DEG C) (FT) 200 300 400 500 600 700 800 900
0 15,000 50.6 NA NA NA NA NA NA NA
2 14,000 52.2 46.4 NA NA NA NA NA NA
6 12,000 55.3 49.4 NA NA NA NA NA NA
10 10,000 61.4 54.7 48.5 NA NA NA NA NA
15 14 8,000 65.5 58.6 51.9 46.8 NA NA NA NA
18 6,000 70.0 62.8 55.7 50.0 45.7 NA NA NA
22 4,000 74.6 67.1 59.5 53.5 48.8 NA NA NA
26 2,000 74.6 71.6 63.5 57.1 52.0 47.8 NA NA
30 0 74.6 74.6 67.5 60.6 55.0 50.5 46.8 NA
5 15,000 48.9 NA NA NA NA NA NA NA
7 14,000 50.4 NA NA NA NA NA NA NA
11 12,000 54.4 48.6 NA NA NA NA NA NA
15 10,000 60.0 53.5 47.5 NA NA NA NA NA
20 19 8,000 64.1 57.4 50.9 45.9 NA NA NA NA
23 6,000 68.5 61.5 54.5 49.1 NA NA NA NA
27 4,000 72.8 65.6 58.2 52.4 47.8 NA NA NA
31 2,000 74.6 69.4 61.6 55.4 50.5 46.5 NA NA
35 0 74.6 73.4 65.2 58.6 53.3 49.0 45.4 NA
10 15,000 48.1 NA NA NA NA NA NA NA
12 14,000 49.5 NA NA NA NA NA NA NA
16 12,000 52.4 46.9 NA NA NA NA NA NA
20 10,000 58.6 52.3 46.5 NA NA NA NA NA
25 24 8,000 62.7 56.1 49.8 NA NA NA NA NA
28 6,000 66.9 60.1 53.3 48.1 NA NA NA NA
32 4,000 70.2 63.5 56.3 50.7 46.3 NA NA NA
36 2,000 73.8 67.0 59.5 53.6 48.9 NA NA NA
40 0 74.6 70.5 62.6 56.3 51.3 47.2 NA NA
15 15,000 46.3 NA NA NA NA NA NA NA
17 14,000 47.7 NA NA NA NA NA NA NA
21 12,000 50.4 45.4 NA NA NA NA NA NA
25 10,000 57.2 51.2 45.5 NA NA NA NA NA
30 29 8,000 60.9 54.7 48.6 NA NA NA NA NA
33 6,000 64.2 58.0 51.5 46.5 NA NA NA NA
37 4,000 67.4 61.2 54.4 49.1 NA NA NA NA
41 2,000 70.4 64.2 57.0 51.5 47.0 NA NA NA
45 0 73.3 67.1 59.6 53.7 49.0 45.0 NA NA
NOTES: 1. Maximum climb weights are limited by the design MAX TOGW of 74,600 lb for the GIV-SP and
73,200 for the GIV.
2. Increase MAX TOGW by 300 lb for each 10 knots of headwind up to a maximum of 40 knots.
Data not valid for tailwinds.
3. Cowl anti-ice bleeds are assumed ON for temperatures below 10° C; wing anti-ice bleeds
prohibited.

REVISION 24 (RE-ISSUE) NON-SP GIV PERFORMANCE

Mar 17/10 (NON-SP GIV AIRPLANES ONLY) Page PA - 59
 Quick Reference Handbook
Non-SP SID Climb Performance Conversion Table
OM 11-04-40

Departure climb requirements are sometimes expressed in units of

degrees and percent climb gradient as well as Ft/NM which is shown
on the SID climb tables. Provided below is a table which can be
used to convert climb requirements in degrees or percent to Ft/NM.
NOTE: Per FAA Terminal Instrument Procedures (TERPs) criteria, SIDs
specified at U.S. civilian airports will ensure that any limiting obstacles will
be cleared by a margin of climb of 48 Ft/NM (0.8% or 0.5 deg). If a
departure climb is specified at a military airport or non-US airport, it is
important to determine if the specified climb requirement provides at least
the same obstacle clearance margin. If uncertainty exists on this point,
add 48 Ft/NM, 0.8% or 0.5 deg to the stated climb requirement before
entering the SID climb tables to determine a maximum allowable takeoff
weight.
Deg % Ft/NM Deg % Ft/NM
1.0 1.7 106 5.0 8.7 532
1.2 2.1 127 5.2 9.1 553
1.4 2.4 148 5.4 9.5 574
1.6 2.8 170 5.6 9.8 596
1.8 3.1 191 5.8 10.2 617
2.0 3.5 212 6.0 10.5 639
2.2 3.8 233 6.2 10.9 660
2.4 4.2 255 6.4 11.2 682
2.6 4.5 276 6.6 11.6 703
2.8 4.9 297 6.8 11.9 725
3.0 5.2 318 7.0 12.3 746
3.2 5.6 340 7.2 12.6 768
3.4 5.9 361 7.4 13.0 789
3.6 6.3 382 7.6 13.3 811
3.8 6.6 404 7.8 13.7 832
4.0 7.0 425 8.0 14.1 854
4.2 7.3 446 8.2 14.4 876
4.4 7.7 468 8.4 14.8 897
4.6 8.0 489 8.6 15.1 919
4.8 8.4 510 8.8 15.5 941

NON-SP GIV PERFORMANCE REVISION 24 (RE-ISSUE)

Page PA - 60 (NON-SP GIV AIRPLANES ONLY) Mar 17/10
Quick Reference Handbook
Non-SP GIV Twin Engine Cruise Altitudes: Mach 0.77
CCM

GROSS WEIGHT - 1000 LB

74 70 66 62 58 54 50 46 42 38
ALT  ISA -20°C to 0°C +20°C
(FT) CEILING
45000 NM/LB **** **** **** **** .1721 .1857 .1982 .2101 .2218 .2326
TWIND **** **** **** **** 3 0 0 0 0 0
43000 NM/LB **** **** **** .1622 .1732 .1834 .1931 .2029 .2119 .2216
TWIND **** **** **** 0 0 6 12 16 21 22
41000 NM/LB **** .1439 .1534 .1621 .1704 .1781 .1864 .1938 .2019 .2089
TWIND **** 2 0 1 7 19 28 37 43 50
39000 NM/LB .1372 .1447 .1518 .1584 .1652 .1716 .1777 .1845 .1904 .1958
TWIND 0 0 5 11 21 36 51 61 73 83
37000 NM/LB .1365 .1421 .1478 .1532 .1584 .1634 .1691 .1740 .1784 .1821
TWIND 2 8 17 26 41 60 76 92 107 122
35000 NM/LB .1329 .1376 .1420 .1462 .1510 .1552 .1591 .1628 .1664 .1687
TWIND 14 23 36 49 65 87 109 129 148 168
33000 NM/LB .1276 .1311 .1351 .1385 .1418 .1450 .1486 .1510 .1529 ****
TWIND 34 41 61 77 99 126 150 175 202 ****
31000 NM/LB .1219 .1247 .1275 .1309 .1335 .1358 **** **** **** ****
TWIND 57 72 92 108 134 166 **** **** **** ****
29000 NM/LB .1162 .1185 .1208 .1234 .1253 **** **** **** **** ****
TWIND 82 101 123 143 174 **** **** **** **** ****
27000 NM/LB .1092 .1110 .1127 .1142 **** **** **** **** **** ****
TWIND 118 140 166 193 **** **** **** **** **** ****
25000 NM/LB .1030 .1043 **** **** **** **** **** **** **** ****
TWIND 154 179 **** **** **** **** **** **** **** ****

NOTES: 1. Values at optimum altitude are shaded.

2. Service Ceilings (100 FPM rate of climb) for selected temperature
conditions are represented on the table by bold lines.
3. Tailwind Factors (TWIND) are the difference in flight level wind
required to equal ground specific range at optimum altitude.

REVISION 24 (RE-ISSUE) NON-SP GIV PERFORMANCE

Mar 17/10 (NON-SP GIV AIRPLANES ONLY) Page PB - 1
 Quick Reference Handbook
Non-SP GIV Twin Engine Cruise Altitudes: Mach 0.80
CCM

GROSS WEIGHT - 1000 LB

74 70 66 62 58 54 50 46 42 38
ALT  ISA -20°C to 0°C +20°C
(FT) CEILING
45000 NM/LB **** **** **** **** .1694 .1816 .1919 .2023 .2126 .2212
TWIND **** **** **** **** 0 0 0 0 0 0
43000 NM/LB **** **** **** .1592 .1688 .1773 .1858 .1944 .2015 .2093
TWIND **** **** **** 0 2 11 15 19 25 26
41000 NM/LB **** .1415 .1498 .1572 .1644 .1711 .1783 .1841 .1907 .1962
TWIND **** 0 0 6 14 28 35 45 53 58
39000 NM/LB .1344 .1407 .1468 .1526 .1587 .1639 .1687 .1742 .1788 .1831
TWIND 0 3 9 20 31 50 63 74 87 95
37000 NM/LB .1321 .1370 .1422 .1467 .1509 .1549 .1595 .1633 .1668 .1697
TWIND 8 15 24 39 56 79 93 110 126 139
35000 NM/LB .1278 .1321 .1356 .1390 .1429 .1461 .1493 .1522 .1548 .1565
TWIND 24 33 48 67 85 112 132 152 172 191
33000 NM/LB .1220 .1249 .1281 .1309 .1336 .1362 .1388 **** **** ****
TWIND 47 62 79 101 125 155 178 **** **** ****
31000 NM/LB .1158 .1182 .1206 .1231 .1252 **** **** **** **** ****
TWIND 75 92 114 138 166 **** **** **** **** ****
29000 NM/LB .1097 .1116 .1134 .1154 **** **** **** **** **** ****
TWIND 107 127 152 180 **** **** **** **** **** ****
27000 NM/LB .1031 .1047 **** **** **** **** **** **** **** ****
TWIND 145 168 **** **** **** **** **** **** **** ****
25000 NM/LB .0971 **** **** **** **** **** **** **** **** ****
TWIND 185 **** **** **** **** **** **** **** **** ****

NOTES: 1. Values at optimum altitude are shaded.

2. Service Ceilings (100 FPM rate of climb) for selected temperature
conditions are represented on the table by bold lines.
3. Tailwind Factors (TWIND) are the difference in flight level wind
required to equal ground specific range at optimum altitude.

NON-SP GIV PERFORMANCE REVISION 24 (RE-ISSUE)

Page PB - 2 (NON-SP GIV AIRPLANES ONLY) Mar 17/10
Quick Reference Handbook
Non-SP GIV Twin Engine Cruise Altitudes: Mach 0.83
CCM

GROSS WEIGHT - 1000 LB

74 70 66 62 58 54 50 46 42 38
ALT  ISA -20°C to 0°C +15°C
(FT) CEILING
45000 NM/LB **** **** **** **** **** **** .1708 .1820 .1911 .1992
TWIND **** **** **** **** **** **** 0 0 0 0
43000 NM/LB **** **** **** **** .1474 .1581 .1674 .1746 .1814 .1871
TWIND **** **** **** **** 0 0 10 20 25 31
41000 NM/LB **** **** **** .1390 .1471 .1546 .1602 .1657 .1705 .1754
TWIND **** **** **** 0 1 11 31 47 57 65
39000 NM/LB **** .1234 .1307 .1370 .1424 .1472 .1518 .1557 .1599 .1637
TWIND **** 0 0 7 17 35 60 80 93 103
37000 NM/LB .1173 .1227 .1273 .1318 .1356 .1395 .1425 .1459 .1492 .1519
TWIND 0 3 13 26 41 63 94 118 134 148
35000 NM/LB .1149 .1185 .1218 .1250 .1277 .1305 .1334 .1360 .1376 .1393
TWIND 10 20 35 54 73 101 134 162 186 206
33000 NM/LB .1104 .1132 .1152 .1178 .1202 .1228 .1240 **** **** ****
TWIND 30 43 65 87 109 139 182 **** **** ****
31000 NM/LB .1051 .1075 .1098 .1108 .1129 .1147 **** **** **** ****
TWIND 57 72 93 124 149 184 **** **** **** ****
29000 NM/LB .0987 .1004 .1022 .1031 .1045 **** **** **** **** ****
TWIND 93 113 132 171 201 **** **** **** **** ****
27000 NM/LB .0942 .0957 .0973 **** **** **** **** **** **** ****
TWIND 122 143 170 **** **** **** **** **** **** ****
25000 NM/LB **** **** **** **** **** **** **** **** **** ****
TWIND **** **** **** **** **** **** **** **** **** ****

NOTES: 1. Values at optimum altitude are shaded.

2. Service Ceilings (100 FPM rate of climb) for selected temperature
conditions are represented on the table by bold lines.
3. Tailwind Factors (TWIND) are the difference in flight level wind
required to equal ground specific range at optimum altitude.

REVISION 28 NON-SP GIV PERFORMANCE

May 25/16 (NON-SP GIV AIRPLANES ONLY) Page PB - 3
 Quick Reference Handbook
Non-SP GIV Maximum Range Cruise - ISA CCM

ALT OAT GROSS WEIGHT - 1000 LB

(FT) (°C) 76 74 72 70 68 66 64 62 60 58
45000 MT **** **** **** **** **** **** **** **** **** 0.778
-56.5 KCAS **** **** **** **** **** **** **** **** **** 209
FF **** **** **** **** **** **** **** **** **** 2590
NAM/LB **** **** **** **** **** **** **** **** **** .1727
43000 MT **** **** **** **** **** **** 0.779 0.774 0.775 0.771
-56.5 KCAS **** **** **** **** **** **** 219 218 218 217
FF **** **** **** **** **** **** 2850 2730 2650 2550
NAM/LB **** **** **** **** **** **** .1570 .1625 .1680 .1731
41000 MT **** **** **** 0.781 0.778 0.775 0.771 0.766 0.761 0.757
-56.5 KCAS **** **** **** 230 229 228 227 225 224 222
FF **** **** **** 3110 3010 2900 2800 2710 2620 2540
NAM/LB **** **** **** .1441 .1484 .1535 .1577 .1622 .1665 .1708
39000 MT 0.776 0.774 0.771 0.767 0.764 0.761 0.757 0.753 0.748 0.744
-56.5 KCAS 239 239 238 237 236 234 233 232 230 229
FF 3340 3240 3150 3040 2960 2870 2790 2710 2640 2570
NAM/LB .1333 .1372 .1407 .1448 .1483 .1520 .1555 .1591 .1627 .1662
37000 MT 0.768 0.763 0.760 0.758 0.752 0.752 0.748 0.743 0.737 0.733
-56.5 KCAS 248 246 245 245 242 243 241 239 237 236
FF 3290 3200 3120 3060 2960 2910 2830 2760 2680 2620
NAM/LB .1337 .1366 .1396 .1425 .1455 .1484 .1514 .1545 .1577 .1610
35000 MT 0.754 0.750 0.747 0.744 0.740 0.736 0.730 0.727 0.721 0.716
-54.3 KCAS 255 253 252 251 250 248 246 245 243 241
FF 3310 3240 3170 3100 3030 2950 2870 2810 2740 2670
NAM/LB .1311 .1336 .1360 .1385 .1411 .1438 .1465 .1492 .1521 .1548
33000 MT 0.737 0.733 0.729 0.724 0.719 0.713 0.707 0.701 0.693 0.684
-50.4 KCAS 260 258 257 255 253 251 249 246 243 240
FF 3370 3300 3220 3150 3080 3000 2920 2850 2770 2680
NAM/LB .1273 .1295 .1317 .1340 .1361 .1384 .1408 .1432 .1458 .1483
31000 MT 0.716 0.710 0.704 0.697 0.690 0.684 0.676 0.668 0.658 0.649
-46.4 KCAS 264 261 259 256 253 251 248 244 241 237
FF 3410 3320 3240 3160 3080 3000 2930 2850 2760 2678
NAM/LB .1234 .1254 .1274 .1294 .1315 .1336 .1357 .1376 .1399 .1422
29000 MT 0.706 0.697 0.687 0.678 0.668 0.657 0.647 0.637 0.625 0.613
-42.5 KCAS 271 268 263 260 256 251 247 243 238 233
FF 3520 3430 3330 3240 3140 3040 2960 2870 2770 2680
NAM/LB .1187 .1205 .1223 .1241 .1259 .1279 .1295 .1314 .1335 .1355
27000 MT 0.671 0.665 0.658 0.651 0.643 0.634 0.625 0.615 0.605 0.594
-38.5 KCAS 268 265 263 260 256 252 249 244 240 236
FF 3500 3420 3340 3260 3170 3090 3000 2910 2820 2730
NAM/LB .1144 .1160 .1176 .1193 .1209 .1227 .1244 .1262 .1281 .1300
25000 MT 0.648 0.641 0.634 0.626 0.617 0.608 0.599 0.590 0.580 0.570
-34.5 KCAS 270 267 263 260 256 252 248 244 240 236
FF 3540 3460 3380 3290 3200 3110 3030 2940 2850 2760
NAM/LB .1101 .1116 .1130 .1145 .1160 .1176 .1192 .1209 .1226 .1243
20000 MT 0.585 0.578 0.570 0.562 0.554 0.546 0.539 0.530 0.522 0.514
-24.6 KCAS 268 265 261 257 254 250 246 242 238 234
FF 3640 3560 3470 3380 3290 3200 3120 3030 2940 2860
NAM/LB .0986 .0998 .1010 .1022 .1035 .1048 .1062 .1076 .1090 .1105

NOTE: See the GIV Operating Manual for procedures to account

for temperature deviation from ISA day and/or wind conditions.

NON-SP GIV PERFORMANCE REVISION 28

Page PB - 4 (NON-SP GIV AIRPLANES ONLY) May 25/16
Quick Reference Handbook
Non-SP GIV Maximum Range Cruise - ISA, ctd… CCM

ALT OAT GROSS WEIGHT - 1000 LB

(FT) (°C) 56 54 52 50 48 46 44 42 40 38
45000 MT 0.776 0.774 0.769 0.767 0.762 0.757 0.750 0.744 0.734 0.725
-56.5 KCAS 208 208 206 206 204 203 200 199 196 193
FF 2490 2390 2300 2220 2140 2060 1980 1910 1830 1750
NAM/LB .1791 .1858 .1921 .1984 .2049 .2110 .2173 .2237 .2304 .2375
43000 MT 0.767 0.763 0.758 0.754 0.749 0.742 0.735 0.728 0.719 0.710
-56.5 KCAS 216 214 213 211 210 208 206 203 201 198
FF 2470 2390 2300 2230 2150 2080 2010 1930 1860 1790
NAM/LB .1787 .1837 .1891 .1942 .1994 .2048 .2104 .2163 .2224 .2282
41000 MT 0.754 0.749 0.744 0.739 0.733 0.727 0.720 0.712 0.702 0.693
-56.5 KCAS 222 220 218 217 215 213 211 208 205 202
FF 2470 2400 2330 2250 2180 2110 2040 1970 1890 1820
NAM/LB .1751 .1794 .1838 .1883 .1930 .1980 .2030 .2079 .2131 .2187
39000 MT 0.739 0.733 0.726 0.720 0.713 0.706 0.697 0.688 0.676 0.665
-56.5 KCAS 227 225 223 221 218 216 213 210 206 202
FF 2500 2420 2340 2270 2200 2130 2060 1980 1900 1830
NAM/LB .1700 .1738 .1779 .1820 .1860 .1902 .1946 .1992 .2039 .2086
37000 MT 0.727 0.721 0.713 0.705 0.696 0.686 0.674 0.662 0.646 0.630
-56.5 KCAS 234 232 229 226 223 219 215 211 206 200
FF 2540 2470 2390 2310 2240 2160 2080 2000 1910 1820
NAM/LB .1644 .1679 .1711 .1747 .1784 .1823 .1861 .1901 .1942 .1985
35000 MT 0.709 0.701 0.690 0.679 0.663 0.648 0.643 0.638 0.596 0.555
-54.3 KCAS 238 235 231 227 222 216 214 212 198 183
FF 2590 2510 2430 2350 2250 2150 2100 2050 1860 1700
NAM/LB .1578 .1608 .1639 .1671 .1704 .1737 .1771 .1801 .1848 .1888
33000 MT 0.675 0.664 0.650 0.635 0.617 0.600 0.583 0.566 0.550 0.535
-50.4 KCAS 236 232 227 221 215 208 202 196 190 185
FF 2600 2510 2420 2330 2220 2120 2020 1920 1821 1740
NAM/LB .1510 .1538 .1566 .1590 .1621 .1652 .1685 .1720 .1756 .1793
31000 MT 0.648 0.628 0.615 0.603 0.589 0.575 0.560 0.545 0.529 0.513
-46.4 KCAS 237 229 224 219 214 209 203 197 191 185
FF 2630 2510 2420 2330 2230 2140 2050 1960 1860 1770
NAM/LB .1446 .1470 .1496 .1522 .1550 .1578 .1608 .1639 .1672 .1705
29000 MT 0.600 0.586 0.572 0.558 0.545 0.532 0.519 0.506 0.496 0.485
-42.5 KCAS 228 222 217 211 206 201 196 191 187 182
FF 2580 2480 2380 2280 2190 2100 2010 1920 1850 1770
NAM/LB .1379 .1400 .1426 .1451 .1477 .1503 .1531 .1560 .1590 .1622
27000 MT 0.584 0.573 0.561 0.550 0.540 0.529 0.517 0.506 0.494 0.483
-38.5 KCAS 231 227 222 217 213 208 204 199 194 190
FF 2640 2550 2460 2370 2290 2200 2120 2040 1950 1870
NAM/LB .1320 .1341 .1363 .1385 .1408 .1432 .1457 .1483 .1510 .1538
25000 MT 0.560 0.550 0.539 0.529 0.519 0.509 0.499 0.488 0.478 0.467
-34.5 KCAS 231 227 222 218 213 209 205 200 196 191
FF 2670 2580 2500 2410 2330 2240 2160 2080 2000 1920
NAM/LB .1262 .1281 .1301 .1322 .1344 .1366 .1389 .1413 .1437 .1463
20000 MT 0.506 0.498 0.490 0.482 0.474 0.466 0.458 0.451 0.444 0.438
-24.6 KCAS 231 227 223 219 216 212 208 205 202 199
FF 2770 2690 2610 2530 2450 2370 2300 2230 2160 2100
NAM/LB .1121 .1137 .1153 .1170 .1188 .1206 .1224 .1242 .1261 .1279

NOTE: See the GIV Operating Manual for procedures to account

for temperature deviation from ISA day and/or wind conditions.

REVISION 28 NON-SP GIV PERFORMANCE

May 25/16 (NON-SP GIV AIRPLANES ONLY) Page PB - 5
 Quick Reference Handbook
Non-SP GIV Long Range Cruise - ISA CCM

OAT GROSS WEIGHT - 1000 LB

ALT
(°C) 76 74 72 70 68 66 64 62 60 58
45000 MT **** **** **** **** **** **** **** **** **** 0.795
-56.5 KCAS **** **** **** **** **** **** **** **** **** 214
FF **** **** **** **** **** **** **** **** **** 2670
NAM/LB **** **** **** **** **** **** **** **** **** 0.1707
43000 MT **** **** **** **** **** **** 0.797 0.792 0.79 0.787
-56.5 KCAS **** **** **** **** **** **** 225 223 223 222
FF **** **** **** **** **** **** 2950 2820 2730 2630
NAM/LB **** **** **** **** **** **** 0.1551 0.1611 0.1665 0.172
41000 MT **** **** **** 0.794 0.793 0.791 0.79 0.787 0.784 0.781
-56.5 KCAS **** **** **** 235 234 234 233 232 231 230
FF **** **** **** 3190 3090 2990 2900 2807 2730 2650
NAM/LB **** **** **** 0.1428 0.1471 0.1521 0.1562 0.1606 0.1648 0.1691
39000 MT 0.792 0.791 0.789 0.788 0.786 0.784 0.781 0.779 0.778 0.775
-56.5 KCAS 245 245 244 244 243 242 241 241 240 239
FF 3440 3330 3240 3150 3070 2990 2910 2840 2770 2700
NAM/LB 0.1322 0.1363 0.1398 0.1434 0.1469 0.1505 0.154 0.1575 0.1611 0.1646
37000 MT 0.788 0.785 0.783 0.782 0.78 0.778 0.775 0.772 0.769 0.766
-56.5 KCAS 255 254 253 253 252 252 251 250 248 247
FF 3420 3330 3250 3190 3110 3040 2970 2900 2830 2770
NAM/LB 0.1322 0.1352 0.1382 0.1409 0.144 0.147 0.1499 0.1529 0.156 0.159
35000 MT 0.779 0.776 0.775 0.773 0.771 0.767 0.763 0.761 0.757 0.753
-54.3 KCAS 264 263 263 262 261 260 258 257 256 255
FF 3460 3380 3320 3250 3180 3110 3030 2980 2900 2830
NAM/LB 0.1298 0.1322 0.1347 0.1371 0.1396 0.1423 0.145 0.1475 0.1504 0.1532
30000 MT 0.749 0.745 0.741 0.737 0.731 0.725 0.717 0.710 0.703 0.695
-44.4 KCAS 283 281 280 278 276 273 270 267 264 261
FF 3685 3615 3540 3470 3390 3310 3216 3135 3055 2965
NAM/LB 0.1199 0.1217 0.1235 0.1253 0.1273 0.1293 0.1315 0.1337 0.1358 0.1379
25000 MT 0.7 0.695 0.688 0.681 0.673 0.665 0.656 0.647 0.638 0.628
-34.5 KCAS 293 290 287 284 280 277 273 269 265 261
FF 3870 3790 3700 3620 3530 3440 3350 3260 3160 3070
NAM/LB 0.109 0.1105 0.1119 0.1134 0.1149 0.1164 0.118 0.1197 0.1213 0.1231
20000 MT 0.641 0.632 0.624 0.615 0.607 0.598 0.59 0.581 0.572 0.563
-24.6 KCAS 295 291 287 283 278 274 270 266 262 258
FF 4030 3930 3830 3740 3640 3540 3450 3350 3260 3160
NAM/LB 0.0976 0.0988 0.1 0.1012 0.1025 0.1038 0.1051 0.1065 0.1079 0.1094
15000 MT 0.575 0.567 0.56 0.552 0.545 0.538 0.53 0.524 0.517 0.51
-14.7 KCAS 291 287 283 279 275 271 267 264 260 257
FF 4133 4031 3931 3831 3735 3641 3550 3463 3375 3290
NAM/LB 0.0872 0.0882 0.0892 0.0903 0.0914 0.0925 0.0936 0.0947 0.0959 0.0971
10000 MT 0.452 0.452 0.452 0.452 0.452 0.452 0.452 0.452 0.452 0.452
-4.8 KCAS 250 250 250 250 250 250 250 250 250 250
FF 3675 3634 3593 3553 3514 3480 3443 3410 3379 3347
NAM/LB 0.0785 0.0794 0.0803 0.0812 0.0821 0.0829 0.0838 0.0846 0.0854 0.0862
5000 MT 0.413 0.413 0.413 0.413 0.413 0.413 0.413 0.413 0.413 0.413
5.1 KCAS 250 250 250 250 250 250 250 250 250 250
FF 3868 3830 3792 3755 3723 3688 3652 3623 3594 3565
NAM/LB 0.0694 0.0701 0.0708 0.0715 0.0721 0.0728 0.0735 0.0741 0.0747 0.0753
0 MT 0.378 0.378 0.378 0.378 0.378 0.378 0.378 0.378 0.378 0.378
15 KCAS 250 250 250 250 250 250 250 250 250 250
FF 4119 4079 4046 4007 3975 3944 3913 3877 3847 3823
NAM/LB 0.0607 0.0613 0.0618 0.0624 0.0629 0.0634 0.0639 0.0645 0.065 0.0654

NOTE: See the GIV Operating Manual for procedures to account

for temperature deviation from ISA day and/or wind conditions.
NOTE: Airspeed restricted to 250 KCAS for altitudes of 10,000 ft
and below.

NON-SP GIV PERFORMANCE REVISION 28

Page PB - 6 (NON-SP GIV AIRPLANES ONLY) May 25/16
Quick Reference Handbook
Non-SP GIV Long Range Cruise - ISA, ctd… CCM
OAT GROSS WEIGHT - 1000 LB
ALT
(°C) 56 54 52 50 48 46 44 42 40 38
45000 MT 0.793 0.791 0.788 0.785 0.782 0.778 0.774 0.77 0.764 0.757
-56.5 KCAS 213 213 212 211 210 209 208 206 205 203
FF 2560 2460 2380 2290 2210 2140 2070 2010 1930 1850
NAM/LB 0.177 0.1845 0.1904 0.1964 0.2029 0.209 0.2145 0.22 0.2275 0.2351
43000 MT 0.785 0.783 0.78 0.776 0.773 0.77 0.765 0.761 0.755 0.75
-56.5 KCAS 221 221 220 218 217 217 215 214 212 210
FF 2550 2470 2390 2320 2250 2180 2110 2050 1970 1900
NAM/LB 0.177 0.1819 0.1872 0.1922 0.1976 0.203 0.2083 0.2135 0.2201 0.2259
41000 MT 0.779 0.777 0.773 0.769 0.765 0.761 0.755 0.749 0.742 0.734
-56.5 KCAS 230 229 228 227 225 224 222 220 218 215
FF 2590 2520 2440 2370 2300 2240 2160 2090 2020 1940
NAM/LB 0.1731 0.177 0.1817 0.1864 0.191 0.1955 0.2007 0.2058 0.2109 0.2165
39000 MT 0.771 0.767 0.763 0.759 0.754 0.748 0.741 0.734 0.726 0.716
-56.5 KCAS 238 236 235 234 232 230 228 225 223 219
FF 2630 2550 2490 2430 2350 2280 2210 2130 2060 1990
NAM/LB 0.1683 0.1721 0.176 0.1798 0.1841 0.1883 0.1927 0.1972 0.2018 0.2065
37000 MT 0.763 0.759 0.752 0.746 0.74 0.734 0.725 0.716 0.705 0.691
-56.5 KCAS 246 245 242 240 238 236 233 230 226 221
FF 2700 2640 2540 2470 2400 2340 2260 2180 2100 2020
NAM/LB 0.162 0.165 0.1694 0.173 0.1767 0.1803 0.1843 0.1882 0.1923 0.1965
35000 MT 0.748 0.743 0.737 0.73 0.723 0.714 0.704 0.687 0.665 0.638
-54.3 KCAS 253 251 248 246 243 240 236 230 222 213
FF 2760 2690 2620 2540 2470 2390 2310 2210 2090 1970
NAM/LB 0.1562 0.1592 0.1623 0.1655 0.1687 0.172 0.1754 0.1791 0.1829 0.1869
30000 MT 0.685 0.675 0.663 0.651 0.637 0.625 0.608 0.593 0.576 0.560
-44.4 KCAS 257 253 248 243 238 233 226 220 214 207
FF 2880 2795 2700 2605 2505 2415 2310 2210 2105 2000
NAM/LB 0.1401 0.1424 0.1448 0.1472 0.1498 0.1524 0.1553 0.1583 0.1614 0.1647
25000 MT 0.618 0.607 0.595 0.584 0.573 0.562 0.551 0.539 0.528 0.517
-34.5 KCAS 256 251 246 241 237 232 227 222 217 212
FF 2980 2880 2780 2690 2590 2500 2410 2320 2230 2150
NAM/LB 0.1249 0.1268 0.1288 0.1309 0.133 0.1352 0.1375 0.1398 0.1423 0.1448
20000 MT 0.554 0.546 0.537 0.528 0.519 0.511 0.503 0.494 0.487 0.48
-24.6 KCAS 254 249 245 241 237 233 229 225 222 218
FF 3070 2980 2890 2800 2710 2630 2550 2470 2400 2330
NAM/LB 0.111 0.1126 0.1142 0.1159 0.1176 0.1194 0.1212 0.123 0.1248 0.1266
15000 MT 0.503 0.497 0.491 0.484 0.478 0.472 0.467 0.461 0.455 0.45
-14.7 KCAS 253 250 247 244 241 237 235 232 229 226
FF 3207 3128 3051 2974 2901 2829 2763 2696 2634 2575
NAM/LB 0.0983 0.0995 0.1007 0.102 0.1033 0.1046 0.1058 0.1071 0.1083 0.1095
10000 MT 0.452 0.452 0.452 0.452 0.452 0.448 0.443 0.438 0.433 0.428
-4.8 KCAS 250 250 250 250 250 247 245 242 239 237
FF 3316 3290 3260 3235 3213 3150 3089 3026 2964 2907
NAM/LB 0.087 0.0877 0.0885 0.0892 0.0898 0.0907 0.0915 0.0924 0.0933 0.0941
5000 MT 0.413 0.413 0.413 0.413 0.413 0.413 0.413 0.413 0.411 0.406
5.1 KCAS 250 250 250 250 250 250 250 250 249 246
FF 3537 3509 3482 3459 3433 3411 3390 3373 3328 3266
NAM/LB 0.0759 0.0765 0.0771 0.0776 0.0782 0.0787 0.0792 0.0796 0.0802 0.0808
0 MT 0.378 0.378 0.378 0.378 0.378 0.378 0.378 0.378 0.378 0.378
15 KCAS 250 250 250 250 250 250 250 250 250 250
FF 3794 3766 3743 3715 3693 3672 3650 3634 3613 3598
NAM/LB 0.0659 0.0664 0.0668 0.0673 0.0677 0.0681 0.0685 0.0688 0.0692 0.0695

NOTE: See the GIV Operating Manual for procedures to account

for temperature deviation from ISA day and/or wind conditions.
NOTE: Airspeed restricted to 250 KCAS for altitudes of 10,000 ft
and below.

REVISION 28 NON-SP GIV PERFORMANCE

May 25/16 (NON-SP GIV AIRPLANES ONLY) Page PB - 7
 Quick Reference Handbook
Non-SP GIV Twin Engine Cruise: Mach 0.77 - ISA CCM

ALT OAT GROSS WEIGHT - 1000 LB

(FT) (°C) 76 74 72 70 68 66 64 62 60 58
45000 MT **** **** **** **** **** **** **** **** **** 0.770
441.6 KCAS **** **** **** **** **** **** **** **** **** 206
FF **** **** **** **** **** **** **** **** **** 2570
-56.5 NAM/LB **** **** **** **** **** **** **** **** **** .1721
43000 MT **** **** **** **** **** **** 0.770 0.770 0.770 0.770
441.6 KCAS **** **** **** **** **** **** 216 216 216 216
FF **** **** **** **** **** **** 2810 2720 2630 2550
-56.5 NAM/LB **** **** **** **** **** **** .1569 .1622 .1679 .1732
41000 MT **** **** **** 0.770 0.770 0.770 0.770 0.770 0.770 0.770
441.6 KCAS **** **** **** 227 227 227 227 227 227 227
FF **** **** **** 3070 2970 2880 2800 2720 2660 2590
-56.5 NAM/LB **** **** **** .1439 .1486 .1534 .1577 .1621 .1663 .1704
39000 MT 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770
441.6 KCAS 238 238 238 238 238 238 238 238 238 238
FF 3310 3220 3140 3050 2980 2910 2850 2790 2730 2670
-56.5 NAM/LB .1333 .1372 .1404 .1447 .1483 .1518 .1551 .1584 .1620 .1652
37000 MT 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770
441.6 KCAS 249 249 249 249 249 249 249 249 249 249
FF 3310 3240 3170 3110 3050 2990 2940 2880 2830 2790
-56.5 NAM/LB .1336 .1365 .1393 .1421 .1448 .1478 .1505 .1532 .1558 .1584
35000 MT 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770
443.8 KCAS 261 261 261 261 261 261 261 261 261 261
FF 3400 3340 3280 3230 3170 3130 3080 3040 2990 2940
-54.3 NAM/LB .1307 .1329 .1354 .1376 .1398 .1420 .1442 .1462 .1483 .1510
33000 MT 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770
447.8 KCAS 273 273 273 273 273 273 273 273 273 273
FF 3560 3510 3460 3420 3360 3310 3270 3230 3200 3160
-50.4 NAM/LB .1258 .1276 .1294 .1311 .1334 .1351 .1368 .1385 .1401 .1418
31000 MT 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770
451.8 KCAS 285 285 285 285 285 285 285 285 285 285
FF 3750 3710 3660 3620 3580 3540 3500 3450 3420 3390
-46.4 NAM/LB .1204 .1219 .1233 .1247 .1261 .1275 .1289 .1309 .1322 .1335
29000 MT 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770
455.7 KCAS 298 298 298 298 298 298 298 298 298 298
FF 3960 3920 3880 3850 3810 3770 3720 3690 3660 3640
-42.5 NAM/LB .1150 .1162 .1173 .1185 .1196 .1208 .1224 .1234 .1244 .1253
27000 MT 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770
459.6 KCAS 311 311 311 311 311 311 311 311 311 311
FF 4250 4210 4170 4140 4110 4080 4050 4020 4000 3980
-38.5 NAM/LB .1082 .1092 .1101 .1110 .1119 .1127 .1135 .1142 .1149 .1156
25000 MT 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770
463.5 KCAS 324 324 324 324 324 324 324 324 324 324
FF 4530 4500 4470 4440 4410 4390 4370 4340 4320 4310
-34.5 NAM/LB .1022 .1030 .1037 .1043 .1050 .1056 .1062 .1067 .1072 .1077
20000 MT **** **** **** **** **** **** **** **** **** ****
473.0 KCAS **** **** **** **** **** **** **** **** **** ****
FF **** **** **** **** **** **** **** **** **** ****
-24.6 NAM/LB **** **** **** **** **** **** **** **** **** ****

NOTE: See the GIV Operating Manual for procedures to account

for temperature deviation from ISA day and/or wind conditions.

NON-SP GIV PERFORMANCE REVISION 28

Page PB - 8 (NON-SP GIV AIRPLANES ONLY) May 25/16
Quick Reference Handbook
Non-SP GIV Twin Engine Cruise - Mach 0.77- ISA, ctd… CCM

ALT OAT GROSS WEIGHT - 1000 LB

(FT) (°C) 56 54 52 50 48 46 44 42 40 38
45000 MT 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770
441.6 KCAS 206 206 206 206 206 206 206 206 206 206
FF 2470 2380 2300 2230 2160 2100 2050 1990 1940 1900
-56.5 NAM/LB .1789 .1857 .1922 .1982 .2045 .2101 .2155 .2218 .2273 .2326
43000 MT 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770
441.6 KCAS 216 216 216 216 216 216 216 216 216 216
FF 2470 2410 2340 2290 2230 2180 2130 2080 2040 1990
-56.5 NAM/LB .1785 .1834 .1885 .1931 .1982 .2029 .2075 .2119 .2163 .2216
41000 MT 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770
441.6 KCAS 227 227 227 227 227 227 227 227 227 227
FF 2530 2480 2420 2370 2320 2280 2240 2190 2150 2110
-56.5 NAM/LB .1744 .1781 .1825 .1864 .1901 .1938 .1974 .2019 .2055 .2089
39000 MT 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770
441.6 KCAS 238 238 238 238 238 238 238 238 238 238
FF 2620 2570 2530 2480 2430 2390 2360 2320 2290 2260
-56.5 NAM/LB .1685 .1716 .1747 .1777 .1815 .1845 .1875 .1904 .1932 .1958
37000 MT 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770
441.6 KCAS 249 249 249 249 249 249 249 249 249 249
FF 2740 2700 2650 2610 2570 2540 2510 2480 2450 2430
-56.5 NAM/LB .1609 .1634 .1666 .1691 .1716 .1740 .1763 .1784 .1804 .1821
35000 MT 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770
443.8 KCAS 261 261 261 261 261 261 261 261 261 261
FF 2900 2860 2820 2790 2760 2730 2700 2670 2650 2630
-54.3 NAM/LB .1531 .1552 .1572 .1591 .1610 .1628 .1644 .1664 .1676 .1687
33000 MT 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770
447.8 KCAS 273 273 273 273 273 273 273 273 273 273
FF 3120 3090 3060 3010 2990 2970 2950 2930 2910 2900
-50.4 NAM/LB .1434 .1450 .1465 .1486 .1498 .1510 .1520 .1529 .1538 .1545
31000 MT 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770
451.8 KCAS 285 285 285 285 285 285 285 285 285 285
FF 3350 3330 3300 3280 3260 3240 3220 3210 3190 3180
-46.4 NAM/LB .1347 .1358 .1369 .1378 .1387 .1394 .1402 .1408 .1415 .1420
29000 MT 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770
455.7 KCAS 298 298 298 298 298 298 298 298 298 298
FF 3610 3590 3570 3560 3540 3520 3510 3500 3490 3480
-42.5 NAM/LB .1261 .1269 .1276 .1282 .1288 .1293 .1298 .1303 .1307 .1311
27000 MT 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770
459.6 KCAS 311 311 311 311 311 311 311 311 311 311
FF 3960 3940 3920 3900 3890 3870 3860 3840 3830 3820
-38.5 NAM/LB .1162 .1167 .1172 .1177 .1182 .1187 .1191 .1195 .1200 .1204
25000 MT 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770 0.770
463.5 KCAS 324 324 324 324 324 324 324 324 324 324
FF 4290 4270 4250 4240 4220 4210 4190 4170 4160 4140
-34.5 NAM/LB .1081 .1086 .1090 .1094 .1098 .1102 .1106 .1110 .1114 .1118
20000 MT **** **** **** **** **** **** **** **** **** ****
473.0 KCAS **** **** **** **** **** **** **** **** **** ****
FF **** **** **** **** **** **** **** **** **** ****
-24.6 NAM/LB **** **** **** **** **** **** **** **** **** ****

NOTE: See the GIV Operating Manual for procedures to account

for temperature deviation from ISA day and/or wind conditions.

REVISION 28 NON-SP GIV PERFORMANCE

May 25/16 (NON-SP GIV AIRPLANES ONLY) Page PB - 9
 Quick Reference Handbook
Non-SP GIV Twin Engine Cruise: Mach 0.80 - ISA CCM

ALT OAT GROSS WEIGHT - 1000 LB

(FT) (°C) 76 74 72 70 68 66 64 62 60 58
45000 MT **** **** **** **** **** **** **** **** **** 0.800
458.9 KCAS **** **** **** **** **** **** **** **** **** 216
FF **** **** **** **** **** **** **** **** **** 2710
-56.5 NAM/LB **** **** **** **** **** **** **** **** **** .1694
43000 MT **** **** **** **** **** **** 0.800 0.800 0.800 0.800
458.9 KCAS **** **** **** **** **** **** 226 226 226 226
FF **** **** **** **** **** **** 2970 2880 2790 2720
-56.5 NAM/LB **** **** **** **** **** **** .1543 .1592 .1642 .1688
41000 MT **** **** **** 0.800 0.800 0.800 0.800 0.800 0.800 0.800
458.9 KCAS **** **** **** 237 237 237 237 237 237 237
FF **** **** **** 3240 3160 3060 2980 2920 2850 2790
-56.5 NAM/LB **** **** **** .1415 .1451 .1498 .1537 .1572 .1608 .1644
39000 MT 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800
458.9 KCAS 248 248 248 248 248 248 248 248 248 248
FF 3520 3410 3340 3260 3190 3130 3070 3010 2940 2890
-56.5 NAM/LB .1305 .1344 .1375 .1407 .1436 .1468 .1497 .1526 .1559 .1587
37000 MT 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800
458.9 KCAS 260 260 260 260 260 260 260 260 260 260
FF 3540 3470 3410 3350 3290 3230 3170 3130 3080 3040
-56.5 NAM/LB .1296 .1321 .1346 .1370 .1394 .1422 .1445 .1467 .1489 .1509
35000 MT 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800
461.1 KCAS 272 272 272 272 272 272 272 272 272 272
FF 3660 3610 3540 3490 3440 3400 3360 3320 3280 3230
-54.3 NAM/LB .1258 .1278 .1301 .1321 .1339 .1356 .1374 .1390 .1407 .1429
33000 MT 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800
465.3 KCAS 284 284 284 284 284 284 284 284 284 284
FF 3860 3810 3770 3730 3670 3630 3590 3550 3520 3480
-50.4 NAM/LB .1204 .1220 .1234 .1249 .1268 .1281 .1295 .1309 .1323 .1336
31000 MT 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800
469.4 KCAS 297 297 297 297 297 297 297 297 297 297
FF 4100 4050 4010 3970 3930 3890 3850 3810 3780 3750
-46.4 NAM/LB .1146 .1158 .1170 .1182 .1194 .1206 .1218 .1231 .1242 .1252
29000 MT 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800
473.5 KCAS 311 311 311 311 311 311 311 311 311 311
FF 4350 4320 4280 4240 4210 4170 4130 4100 4080 4050
-42.5 NAM/LB .1087 .1097 .1106 .1116 .1125 .1134 .1146 .1154 .1162 .1169
27000 MT 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800
477.5 KCAS 324 324 324 324 324 324 324 324 324 324
FF 4670 4630 4600 4560 4530 4500 4470 4440 4420 4400
-38.5 NAM/LB .1023 .1031 .1039 .1047 .1054 .1062 .1068 .1075 .1081 .1086
25000 MT 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800
481.6 KCAS 338 338 338 338 338 338 338 338 338 338
FF 4990 4960 4930 4900 4860 4830 4810 4780 4760 4740
-34.5 NAM/LB .0965 .0971 .0977 .0984 .0990 .0997 .1002 .1006 .1011 .1015
20000 MT **** **** **** **** **** **** **** **** **** ****
491.5 KCAS **** **** **** **** **** **** **** **** **** ****
FF **** **** **** **** **** **** **** **** **** ****
-24.6 NAM/LB **** **** **** **** **** **** **** **** **** ****

NOTE: See the GIV Operating Manual for procedures to account

for temperature deviation from ISA day and/or wind conditions.

NON-SP GIV PERFORMANCE REVISION 28

Page PB - 10 (NON-SP GIV AIRPLANES ONLY) May 25/16
Quick Reference Handbook
Non-SP GIV Twin Engine Cruise - Mach 0.80 - ISA, ctd… CCM

ALT OAT GROSS WEIGHT - 1000 LB

(FT) (°C) 56 54 52 50 48 46 44 42 40 38
45000 MT 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800
458.9 KCAS 216 216 216 216 216 216 216 216 216 216
FF 2620 2530 2450 2390 2320 2270 2220 2160 2110 2070
-56.5 NAM/LB .1751 .1816 .1870 .1919 .1974 .2023 .2070 .2126 .2170 .2212
43000 MT 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800
458.9 KCAS 226 226 226 226 226 226 226 226 226 226
FF 2650 2590 2530 2470 2410 2360 2320 2280 2240 2190
-56.5 NAM/LB .1729 .1773 .1817 .1858 .1905 .1944 .1980 .2015 .2050 .2093
41000 MT 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800
458.9 KCAS 237 237 237 237 237 237 237 237 237 237
FF 2730 2680 2620 2570 2530 2490 2450 2410 2370 2340
-56.5 NAM/LB .1679 .1711 .1751 .1783 .1812 .1841 .1871 .1907 .1935 .1962
39000 MT 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800
458.9 KCAS 248 248 248 248 248 248 248 248 248 248
FF 2840 2800 2760 2720 2670 2630 2600 2570 2540 2510
-56.5 NAM/LB .1613 .1639 .1663 .1687 .1718 .1742 .1766 .1788 .1810 .1831
37000 MT 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800
458.9 KCAS 260 260 260 260 260 260 260 260 260 260
FF 3000 2960 2910 2880 2840 2810 2780 2750 2730 2700
-56.5 NAM/LB .1529 .1549 .1576 .1595 .1615 .1633 .1651 .1668 .1684 .1697
35000 MT 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800
461.1 KCAS 272 272 272 272 272 272 272 272 272 272
FF 3190 3160 3120 3090 3060 3030 3010 2980 2960 2950
-54.3 NAM/LB .1446 .1461 .1478 .1493 .1508 .1522 .1534 .1548 .1557 .1565
33000 MT 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800
465.3 KCAS 284 284 284 284 284 284 284 284 284 284
FF 3450 3420 3390 3350 3330 3310 3290 3270 3260 3240
-50.4 NAM/LB .1349 .1362 .1374 .1388 .1398 .1407 .1414 .1422 .1428 .1434
31000 MT 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800
469.4 KCAS 297 297 297 297 297 297 297 297 297 297
FF 3720 3690 3670 3640 3630 3610 3590 3570 3560 3550
-46.4 NAM/LB .1262 .1271 .1280 .1288 .1295 .1301 .1307 .1313 .1318 .1323
29000 MT 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800
473.5 KCAS 311 311 311 311 311 311 311 311 311 311
FF 4030 4010 3990 3980 3960 3950 3930 3920 3910 3900
-42.5 NAM/LB .1175 .1181 .1186 .1191 .1196 .1200 .1204 .1207 .1211 .1214
27000 MT 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800
477.5 KCAS 324 324 324 324 324 324 324 324 324 324
FF 4380 4360 4340 4320 4300 4280 4270 4250 4240 4220
-38.5 NAM/LB .1091 .1096 .1101 .1106 .1111 .1115 .1119 .1123 .1127 .1131
25000 MT 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800 0.800
481.6 KCAS 338 338 338 338 338 338 338 338 338 338
FF 4720 4700 4680 4660 4640 4620 4600 4580 4570 4550
-34.5 NAM/LB .1020 .1024 .1029 .1033 .1037 .1042 .1046 .1050 .1055 .1059
20000 MT **** **** **** **** **** **** **** **** **** ****
491.5 KCAS **** **** **** **** **** **** **** **** **** ****
FF **** **** **** **** **** **** **** **** **** ****
-24.6 NAM/LB **** **** **** **** **** **** **** **** **** ****

NOTE: See the GIV Operating Manual for procedures to account

for temperature deviation from ISA day and/or wind conditions.

REVISION 28 NON-SP GIV PERFORMANCE

May 25/16 (NON-SP GIV AIRPLANES ONLY) Page PB - 11
 Quick Reference Handbook
Non-SP GIV Twin Engine Cruise: Mach 0.83 - ISA CCM

ALT OAT GROSS WEIGHT - 1000 LB

(FT) (°C) 76 74 72 70 68 66 64 62 60 58
45000 MT **** **** **** **** **** **** **** **** **** ****
476.1 KCAS **** **** **** **** **** **** **** **** **** ****
FF **** **** **** **** **** **** **** **** **** ****
-56.5 NAM/LB **** **** **** **** **** **** **** **** **** ****
43000 MT **** **** **** **** **** **** **** **** **** 0.830
476.1 KCAS **** **** **** **** **** **** **** **** **** 235
FF **** **** **** **** **** **** **** **** **** 3230
-56.5 NAM/LB **** **** **** **** **** **** **** **** **** .1474
41000 MT **** **** **** **** **** **** 0.830 0.830 0.830 0.830
476.1 KCAS **** **** **** **** **** **** 247 247 247 247
FF **** **** **** **** **** **** 3540 3430 3320 3240
-56.5 NAM/LB **** **** **** **** **** **** .1345 .1390 .1432 .1471
39000 MT **** **** **** 0.830 0.830 0.830 0.830 0.830 0.830 0.830
476.1 KCAS **** **** **** 258 258 258 258 258 258 258
FF **** **** **** 3860 3740 3640 3560 3470 3410 3340
-56.5 NAM/LB **** **** **** .1234 .1273 .1307 .1339 .1370 .1396 .1424
37000 MT 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830
476.1 KCAS 271 271 271 271 271 271 271 271 271 271
FF 4170 4060 3970 3880 3800 3740 3670 3610 3560 3510
-56.5 NAM/LB .1142 .1173 .1200 .1227 .1252 .1273 .1297 .1318 .1337 .1356
35000 MT 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830
478.4 KCAS 283 283 283 283 283 283 283 283 283 283
FF 4240 4160 4110 4040 3980 3930 3880 3830 3780 3750
-54.3 NAM/LB .1128 .1149 .1165 .1185 .1201 .1218 .1234 .1250 .1266 .1277
33000 MT 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830
482.7 KCAS 296 296 296 296 296 296 296 296 296 296
FF 4430 4370 4320 4260 4240 4190 4150 4100 4060 4010
-50.4 NAM/LB .1090 .1104 .1119 .1132 .1138 .1152 .1165 .1178 .1190 .1202
31000 MT 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830
487.0 KCAS 310 310 310 310 310 310 310 310 310 310
FF 4690 4630 4580 4530 4480 4440 4390 4400 4350 4310
-46.4 NAM/LB .1039 .1051 .1063 .1075 .1087 .1098 .1109 .1108 .1118 .1129
29000 MT 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830
491.3 KCAS 323 323 323 323 323 323 323 323 323 323
FF 5020 4980 4930 4890 4850 4810 4800 4760 4730 4700
-42.5 NAM/LB .0978 .0987 .0996 .1004 .1013 .1022 .1024 .1031 .1038 .1045
27000 MT 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830
495.5 KCAS 337 337 337 337 337 337 337 337 337 337
FF 5300 5260 5220 5180 5140 5090 5060 5020 4990 4970
-38.5 NAM/LB .0934 .0942 .0949 .0957 .0965 .0973 .0980 .0986 .0992 .0998
25000 MT **** **** **** **** **** **** **** **** **** ****
499.6 KCAS **** **** **** **** **** **** **** **** **** ****
FF **** **** **** **** **** **** **** **** **** ****
-34.5 NAM/LB **** **** **** **** **** **** **** **** **** ****
20000 MT **** **** **** **** **** **** **** **** **** ****
509.9 KCAS **** **** **** **** **** **** **** **** **** ****
FF **** **** **** **** **** **** **** **** **** ****
-24.6 NAM/LB **** **** **** **** **** **** **** **** **** ****

NOTE: See the GIV Operating Manual for procedures to account

for temperature deviation from ISA day and/or wind conditions.

NON-SP GIV PERFORMANCE REVISION 28

Page PB - 12 (NON-SP GIV AIRPLANES ONLY) May 25/16
Quick Reference Handbook
Non-SP GIV Twin Engine Cruise - Mach 0.83 - ISA, ctd… CCM

ALT OAT GROSS WEIGHT - 1000 LB

(FT) (°C) 56 54 52 50 48 46 44 42 40 38
45000 MT **** **** 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830
476.1 KCAS **** **** 225 225 225 225 225 225 225 225
FF **** **** 2900 2790 2690 2620 2540 2490 2440 2390
-56.5 NAM/LB **** **** .1641 .1708 .1767 .1820 .1874 .1911 .1952 .1992
43000 MT 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830
476.1 KCAS 235 235 235 235 235 235 235 235 235 235
FF 3100 3010 2920 2840 2780 2730 2670 2620 2580 2540
-56.5 NAM/LB .1535 .1581 .1629 .1674 .1710 .1746 .1781 .1814 .1847 .1871
41000 MT 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830
476.1 KCAS 247 247 247 247 247 247 247 247 247 247
FF 3150 3080 3030 2970 2920 2870 2820 2790 2750 2710
-56.5 NAM/LB .1509 .1546 .1572 .1602 .1629 .1657 .1685 .1705 .1730 .1754
39000 MT 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830
476.1 KCAS 258 258 258 258 258 258 258 258 258 258
FF 3290 3230 3180 3140 3100 3060 3020 2980 2940 2910
-56.5 NAM/LB .1449 .1472 .1496 .1518 .1535 .1557 .1578 .1599 .1619 .1637
37000 MT 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830
476.1 KCAS 271 271 271 271 271 271 271 271 271 271
FF 3460 3410 3380 3340 3300 3260 3220 3190 3160 3140
-56.5 NAM/LB .1375 .1395 .1408 .1425 .1442 .1459 .1476 .1492 .1506 .1519
35000 MT 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830
478.4 KCAS 283 283 283 283 283 283 283 283 283 283
FF 3710 3660 3620 3590 3550 3520 3490 3480 3450 3430
-54.3 NAM/LB .1291 .1305 .1320 .1334 .1348 .1360 .1372 .1376 .1385 .1393
33000 MT 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830
482.7 KCAS 296 296 296 296 296 296 296 296 296 296
FF 3970 3930 3890 3890 3860 3840 3810 3790 3770 3750
-50.4 NAM/LB .1215 .1228 .1240 .1240 .1249 .1258 .1266 .1274 .1282 .1289
31000 MT 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830
487.0 KCAS 310 310 310 310 310 310 310 310 310 310
FF 4280 4240 4210 4190 4160 4130 4110 4080 4070 4050
-46.4 NAM/LB .1138 .1147 .1156 .1163 .1171 .1178 .1186 .1192 .1198 .1203
29000 MT 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830
491.3 KCAS 323 323 323 323 323 323 323 323 323 323
FF 4670 4650 4620 4600 4580 4560 4540 4520 4510 4490
-42.5 NAM/LB .1051 .1057 .1063 .1068 .1073 .1078 .1082 .1086 .1090 .1094
27000 MT 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830 0.830
495.5 KCAS 337 337 337 337 337 337 337 337 337 337
FF 4940 4910 4880 4850 4830 4810 4790 4770 4750 4730
-38.5 NAM/LB .1004 .1009 .1015 .1021 .1026 .1031 .1035 .1039 .1044 .1048
25000 MT **** **** **** **** **** **** **** **** **** ****
499.6 KCAS **** **** **** **** **** **** **** **** **** ****
FF **** **** **** **** **** **** **** **** **** ****
-34.5 NAM/LB **** **** **** **** **** **** **** **** **** ****
20000 MT **** **** **** **** **** **** **** **** **** ****
509.9 KCAS **** **** **** **** **** **** **** **** **** ****
FF **** **** **** **** **** **** **** **** **** ****
-24.6 NAM/LB **** **** **** **** **** **** **** **** **** ****

NOTE: See the GIV Operating Manual for procedures to account

for temperature deviation from ISA day and/or wind conditions.

REVISION 28 NON-SP GIV PERFORMANCE

May 25/16 (NON-SP GIV AIRPLANES ONLY) Page PB - 13
 Quick Reference Handbook
Non-SP GIV Twin Engine Flight Planning:
Mach 0.77 - ISA CCM

NON-SP GIV PERFORMANCE REVISION 28

Page PB - 14 (NON-SP GIV AIRPLANES ONLY) May 25/16
Quick Reference Handbook
Non-SP GIV Twin Engine Flight Planning:
Mach 0.80 - ISA CCM

REVISION 24 (RE-ISSUE) NON-SP GIV PERFORMANCE

Mar 17/10 (NON-SP GIV AIRPLANES ONLY) Page PB - 15
 Quick Reference Handbook

Non-SP GIV Twin Engine Flight Planning:

Mach 0.83 - ISA CCM

NON-SP GIV PERFORMANCE REVISION 24 (RE-ISSUE)

Page PB - 16 (NON-SP GIV AIRPLANES ONLY) Mar 17/10
Quick Reference Handbook
Non-SP GIV Equal Time Point And Point Of No Return
CCM

ETP PNR WIND

GS R1

GS O

GS GS C
R

TRIP DISTANCE = D

DEPARTURE DESTINATION
AIRPORT AIRPORT

The following formula is used to calculate the ground distance from the
departure airport to ETP:
(D) (GSR)
GROUND DISTANCE TO ETP = = NM
Where: GSC + GSR
D= Total Trip Distance
GSC = Ground Speed To Continue To Destination At Altitude To Be
Flown
GSR = Ground Speed To Departure Airport At Altitude To Be Flown
The following formula is used to calculate the ground distance from the
departure airport to PNR:
(Endurance) (GSR1) (GSO)
GROUND DISTANCE TO PNR = = NM
GSO + GSR1
Where:
Total Fuel Quantity
Endurance =
Average Fuel Flow
GSO = Normal Outbound Ground Speed At Cruise Altitude
GSR1 = Return Ground Speed At Normal Cruise Altitude

REVISION 24 (RE-ISSUE) NON-SP GIV PERFORMANCE

Mar 17/10 (NON-SP GIV AIRPLANES ONLY) Page PB - 17
 Quick Reference Handbook
Non-SP GIV Twin Engine Alternate Airport
Flight Plan Fuel CCM

Conditions:
• Standard Day, No Wind
• Zero-Fuel Gross Weight of 44,100 Lb
• 1500 Lb Reserve Fuel Included
• Five (5) Minute Approach Fuel Allowance Included

Distance
To Enroute True Fuel
Alternate Flight Time TAS Mach CAS Quantity
(NM) Level (Hr:Min) (Knots) Number (Knots) (Pounds)
100 230 0:24 329 .542 233 2770
120 250 0:27 338 .562 232 2920
140 310 0:29 378 .645 235 3050
160 350 0:32 412 .715 240 3170
180 370 0:33 427 .745 240 3280
200 410 0:36 437 .762 224 3380
220 430 0:39 442 .770 216 3480
240 450 0:42 442 .770 206 3580
260 450 0:44 442 .770 206 3680
280 450 0:47 442 .770 206 3780
300 450 0:50 442 .770 206 3880
320 450 0:53 442 .770 206 3990
340 450 0:56 442 .770 206 4090
360 450 0:59 442 .770 206 4190
380 450 1:01 442 .770 206 4270
400 450 1:03 442 .770 206 4370
420 450 1:06 442 .770 206 4490
440 450 1:09 442 .770 206 4590
460 450 1:12 442 .770 206 4670
480 450 1:15 442 .770 206 4790
500 450 1:18 442 .770 206 4890
520 450 1:20 442 .770 206 4970
540 450 1:23 442 .770 206 5090
560 450 1:26 442 .770 206 5200
580 450 1:29 442 .770 206 5290
600 450 1:31 442 .770 206 5380

NON-SP GIV PERFORMANCE REVISION 24 (RE-ISSUE)

Page PB - 18 (NON-SP GIV AIRPLANES ONLY) Mar 17/10
Quick Reference Handbook
Non-SP GIV Landing Field Length:
Anti-Skid System Operative - Flaps 39° AFM 5.11

CAUTION: THE GIV MAXIMUM LANDING WEIGHT IS 58,500 POUNDS.

NOTES:
1. ISA day, normal landing configuration.
2. For intended destination wet, multiply landing field lengths below by
1.15.
3. For unfactored landing distances, multiply field lengths below by
0.60.
4. Field lengths seen below are based on no wind or runway slope, but
may be conservatively used with headwinds or uphill runway slopes.
5. For all abnormal landing configurations, see Abnormal Landing
Field Length Table, page PC-16.

Landing Intended Destination Dry Landing Field Length (Feet)

Gross For Airport Pressure Altitudes As Shown
Weight
Sea 2000 4000 6000 8000 10000
(Lb) Level Feet Feet Feet Feet Feet
45000 4870 5030 5190 5390 5640 6030
50000 5150 5330 5510 5730 6010 6450
55000 5430 5620 5820 6070 6380 6850
60000 5720 5920 6140 6410 6760 7270
65000 5990 6220 6460 6760 7120 7680
70000 6280 6520 6790 7100 7500 8090
75000 6460 6720 6990 7320 7740 8350

REVISION 24 (RE-ISSUE) NON-SP GIV PERFORMANCE

Mar 17/10 (NON-SP GIV AIRPLANES ONLY) Page PC - 1
 Quick Reference Handbook
Non-SP GIV Landing Speed Schedule AFM 5.11

The following guidance is provided to assist in the use of the

charts in this section:
Tire speed limits occur when touchdown speeds exceeds 182.5
knots (210 MPH). Tire fuseplug release limits occur when Brake
Kinetic Energy (BKE) for a maximum effort landing (full brake
application at touchdown) exceeds 40 MFP, making fuseplug release
possible. If brake application is delayed following touchdown, the
resulting lower level of BKEs can be determined from GIV Airplane
Flight Manual Appendix C, GIV Brake Kinetic Energy and Carbon
Brake Cooling.
Limits shown in the charts that follow are conservative in nature and
represent a combination of worst-case conditions, i.e., maximum
temperature at a given altitude plus a 2% downhill runway slope.
These limits apply to a nil or headwind condition only.

NOTE: All speeds shown are KCAS.

Weight = 45000 LB Normal Abnormal Abnormal Abnormal

Flaps 39° Flaps 20° Flaps 10° Flaps UP
F39° F39°
Altitude VAPP VREF VAPP VREF VAPP VREF VAPP VREF
Shake Push
0 101 95 133 123 136 126 141 131 149 139
2000 101 95 133 123 136 126 142 132 149 139
4000 101 95 133 123 137 127 143 133 151 141
6000 102 95 134 124 138 128 144 134 152 142
8000 103 96 135 125 139 129 146 136 154 144
10000 104 97 136 126 141 131 147 137 156 146
12000 105 98 137 127 142 132 149 139 158 148
14000 106 99 139 129 143 133 150 140 160 150
15000 107 100 139 129 144 134 151 141 161 151
CAUTION: Fuseplug Release Possible CAUTION: Tire Speed Limit
With Max. Braking

NON-SP GIV PERFORMANCE REVISION 24 (RE-ISSUE)

Page PC - 2 (NON-SP GIV AIRPLANES ONLY) Mar 17/10
Quick Reference Handbook
Non-SP GIV Landing Speed Schedule, ctd… AFM 5.11

NOTES:
1. See the explanatory text presented on page PC-2 of this section.
2. All speeds shown are KCAS.

Weight = 50000 LB Normal Abnormal Abnormal Abnormal

Flaps 39° Flaps 20° Flaps 10° Flaps UP
F39° F39°
Altitude VAPP VREF VAPP VREF VAPP VREF VAPP VREF
Shake Push
0 107 100 140 130 143 133 149 139 157 147
2000 107 100 140 130 143 133 149 139 157 147
4000 107 100 140 130 144 134 150 140 158 148
6000 107 100 140 130 145 135 151 141 160 150
8000 108 101 142 132 147 137 153 143 162 152
10000 109 102 143 133 148 138 155 145 164 154
12000 111 103 144 134 149 139 156 146 166 156
14000 112 104 146 136 151 141 158 148 168 158
15000 112 105 146 136 152 142 159 149 170 160
CAUTION: Fuseplug Release Possible CAUTION: Tire Speed Limit
With Max. Braking

Weight = 55000 LB Normal Abnormal Abnormal Abnormal

Flaps 39° Flaps 20° Flaps 10° Flaps UP
F39° F39°
Altitude VAPP VREF VAPP VREF VAPP VREF VAPP VREF
Shake Push
0 112 105 146 136 149 139 155 145 164 154
2000 112 105 146 136 149 139 155 145 164 154
4000 112 105 146 136 150 140 157 147 166 156
6000 113 105 147 137 152 142 158 148 168 158
8000 114 106 148 138 153 143 160 150 170 160
10000 115 107 149 139 154 144 162 152 172 162
12000 116 108 151 141 156 146 163 153 174 164
14000 117 110 152 142 158 148 165 155 176 166
15000 118 110 153 143 158 148 166 156 177 167
CAUTION: Fuseplug Release Possible CAUTION: Tire Speed Limit
With Max. Braking

REVISION 24 (RE-ISSUE) NON-SP GIV PERFORMANCE

Mar 17/10 (NON-SP GIV AIRPLANES ONLY) Page PC - 3
 Quick Reference Handbook
Non-SP GIV Landing Speed Schedule, ctd… AFM 5.11

NOTES:
1. See the explanatory text presented on page PC-2 of this section.
2. All speeds shown are KCAS.

Weight = 60000 LB Normal Abnormal Abnormal Abnormal

Flaps 39° Flaps 20° Flaps 10° Flaps UP
F39° F39°
Altitude VAPP VREF VAPP VREF VAPP VREF VAPP VREF
Shake Push
0 117 109 152 142 156 146 162 152 171 161
2000 117 109 152 142 156 146 162 152 171 161
4000 117 109 152 142 157 147 163 153 173 163
6000 118 110 153 143 158 148 165 155 175 165
8000 119 111 154 144 160 150 167 157 177 167
10000 120 112 156 146 161 151 168 158 179 169
12000 121 113 157 147 163 153 170 160 181 171
14000 123 114 159 149 164 154 172 162 184 174
15000 123 115 160 150 165 155 173 163 185 175
CAUTION: Fuseplug Release Possible CAUTION: Tire Speed Limit
With Max. Braking

Weight = 65000 LB Normal Abnormal Abnormal Abnormal

Flaps 39° Flaps 20° Flaps 10° Flaps UP
F39° F39°
Altitude VAPP VREF VAPP VREF VAPP VREF VAPP VREF
Shake Push
0 122 114 158 148 162 152 168 158 178 168
2000 122 114 158 148 162 152 168 158 178 168
4000 122 114 158 148 163 153 169 159 179 169
6000 122 114 159 149 164 154 171 161 181 171
8000 124 116 160 150 166 156 173 163 184 174
10000 125 117 162 152 167 157 175 165 186 176
12000 126 118 163 153 169 159 177 167 188 178
14000 128 119 165 155 170 160 179 169 191 181
15000 128 120 166 156 171 161 180 170 192 182
CAUTION: Fuseplug Release Possible CAUTION: Tire Speed Limit
With Max. Braking

NON-SP GIV PERFORMANCE REVISION 24 (RE-ISSUE)

Page PC - 4 (NON-SP GIV AIRPLANES ONLY) Mar 17/10
Quick Reference Handbook
Non-SP GIV Landing Speed Schedule, ctd… AFM 5.11

NOTES:
1. See the explanatory text presented on page PC-2 of this section.
2. All speeds shown are KCAS.

Weight = 70000 LB Normal Abnormal Abnormal Abnormal

Flaps 39° Flaps 20° Flaps 10° Flaps UP
F39° F39°
Altitude VAPP VREF VAPP VREF VAPP VREF VAPP VREF
Shake Push
0 126 118 164 154 167 157 174 164 184 174
2000 126 118 164 154 167 157 174 164 184 174
4000 126 118 164 154 169 159 176 166 186 176
6000 127 119 164 154 170 160 177 167 188 178
8000 128 120 166 156 172 162 179 169 190 180
10000 130 121 167 157 173 163 181 171 193 183
12000 131 122 169 159 175 165 183 173 195 185
14000 132 124 171 161 177 167 185 175 198 188
15000 133 124 172 162 178 168 187 177 199 189
CAUTION: Fuseplug Release Possible CAUTION: Tire Speed Limit
With Max. Braking

Weight = 73200 LB Normal Abnormal Abnormal Abnormal

Flaps 39° Flaps 20° Flaps 10° Flaps UP
F39° F39°
Altitude VAPP VREF VAPP VREF VAPP VREF VAPP VREF
Shake Push
0 129 121 167 157 171 161 178 168 188 178
2000 129 121 167 157 171 161 178 168 188 178
4000 129 121 167 157 172 162 179 169 190 180
6000 130 121 168 158 174 164 181 171 192 182
8000 131 123 169 159 175 165 183 173 194 184
10000 132 124 171 161 177 167 185 175 197 187
12000 134 125 173 163 179 169 187 177 199 189
14000 135 126 174 164 180 170 190 180 202 192
15000 136 127 175 165 181 171 191 181 203 193
CAUTION: Fuseplug Release Possible CAUTION: Tire Speed Limit
With Max. Braking

REVISION 24 (RE-ISSUE) NON-SP GIV PERFORMANCE

Mar 17/10 (NON-SP GIV AIRPLANES ONLY) Page PC - 5
 Quick Reference Handbook
Non-SP GIV Landing Distance Using Twin-Engine
Reverse Thrust Only (No Braking) OM 07-01-80

The table on the following page shows landing distances when using
reverse thrust only to bring the aircraft to a stop. The distances shown
below assume reverse thrust is used to 20 knots with stowage by 10
knots.
Conditions:
• Two-Engine Reverse Thrust Only
• No Slope
• No Wind
• Standard Day Temperature
• AUTO Ground Spoilers
• No Runway Surface Contamination Accumulation
• Full Reverse Thrust To 20 Knots
• Stowage By 10 Knots
• Minimal Braking Below 10 Knots
• Flaps 39°
NOTE: Airplane Flight Manual procedures recommend that cancellation of
thrust reversers be initiated by 70 knots so as to be completely cancelled by
the time normal taxi speed is achieved. If landing runway conditions will result
in compromised braking performance, this table may be used to provide
additional information for pilot judgment.

NON-SP GIV PERFORMANCE REVISION 24 (RE-ISSUE)

Page PC - 6 (NON-SP GIV AIRPLANES ONLY) Mar 17/10
Quick Reference Handbook
Non-SP GIV Landing Distance Using Twin-Engine Reverse Thrust
Only (No Braking), ctd… OM 07-01-90

Landing Distance (Feet)

ALT Gross Weight (lb)
(Ft) 74,600 73,200 70,000 66,000 65,000 60,000
15,000 15,166 14,850 14,122 13,209 12,985 11,890
14,000 14,346 14,045 13,359 12,501 12,287 11,264
12,000 12,837 12,569 11,960 11,204 11,019 10,112
10,000 11,495 11,255 10,719 10,052 9,886 9,082
8,000 10,524 10,309 9,823 9,215 9,068 8,342
6,000 9,847 9,649 9,199 8,639 8,500 7,831
4,000 9,265 9,081 8,665 8,144 8,015 7,395
2,000 8,771 8,601 8,213 7,727 7,608 7,028
0 8,320 8,161 7,795 7,343 7,230 6,692
Landing Distance (Feet)
ALT Gross Weight (lb)
(Ft) 58,500 55,000 50,000 45,000 40,000
15,000 11,564 10,813 9,787 8,776 7,827
14,000 10,952 10,250 9,282 8,330 7,440
12,000 9,837 9,212 8,359 7,516 6,732
10,000 8,841 8,289 7,532 6,788 6,093
8,000 8,122 7,623 6,940 6,270 5,648
6,000 7,630 7,169 6,541 5,925 5,358
4,000 7,207 6,784 6,204 5,638 5,116
2,000 6,855 6,458 5,920 5,398 4,921
0 6,530 6,160 5,657 5,178 4,744

REVISION 28 NON-SP GIV PERFORMANCE

May 25/16 (NON-SP GIV AIRPLANES ONLY) Page PC - 7
 Quick Reference Handbook
Non-SP GIV Aircraft Classification Number (ACN) GAC

Aircraft Classification Number (ACN) is a number expressing the

relative effect of an aircraft on a pavement for a specified subgrade
category. ACN values are calculated for both flexible and rigid
pavement. If the aircraft gross weight and runway subgrade strength
are known, the ACN value can be determined from the charts on the
following pages.
Pavement Classification Number (PCN) is a number expressing the
bearing strength of a pavement for unrestricted operations. It is
reported in the Jeppesen charts in a format such as 24/F/C/Y/T,
where:
24 is the PCN
F is the type of pavement, where:
R = Rigid
F = Flexible
C is the subgrade strength, where:
D = Ultra Low
C = Low
B = Medium
A = High
Y is the tire pressure, where:
W = Unlimited
X = High, Pressure limited to 254 psi (1.75 MPa)
Y = Medium, Pressure limited to 181 psi (1.25 MPa)
Z = Low, Pressure limited to 73 psi (0.50 MPa)
T is the PCN classification, where:
T = Technical Evaluation
U = Aircraft Experience
ACN values must be less than or equal to the airport PCN for
unrestricted use. ACN input variables are gross weight, percent load
on main wheels, wheel spacing and maximum tire pressure.

NON-SP GIV PERFORMANCE REVISION 28

Page PC - 8 (NON-SP GIV AIRPLANES ONLY) May 25/16
Quick Reference Handbook
Non-SP GIV ACN, ctd… GAC

Example 1:
Given: Gross Weight = 70,000 lb, PCN = 24/F/C/Y/T
Where: PCN = 24
F = Flexible Pavement
ACN = 22 (from charts)
C = Low Subgrade Strength
Y = 181 psi Tire Pressure Limit
T = Technical Evaluation
Thus: ACN less than PCN, but tire pressure becomes a restriction.
Example 2:
Given: Gross Weight = 70,000 lb, PCN = 80/R/B/W/T
Where: PCN = 80
R = Rigid Pavement
ACN = 22 (from charts)
B = Medium Subgrade Strength
W = Unlimited
T = Technical Evaluation
Thus: ACN less than PCN, no tire pressure limit. Suitable runway.

Main Landing Gear Tire Pressure vs. Gross Weight:

1159SCL206-31 and -33 Tires

REVISION 28 NON-SP GIV PERFORMANCE

May 25/16 (NON-SP GIV AIRPLANES ONLY) Page PC - 9
 Quick Reference Handbook
Non-SP GIV ACN, ctd… GAC

NOTE: Use of these charts is to be with reference to GIV Operating Manual

Chapter 6: Approach and Landing Characteristics and Procedures.

NON-SP GIV PERFORMANCE REVISION 28

Page PC - 10 (NON-SP GIV AIRPLANES ONLY) May 25/16
Quick Reference Handbook
Non-SP GIV ACN, ctd… GAC

NOTE: Use of these charts is to be with reference to GIV Operating Manual

Chapter 6: Approach and Landing Characteristics and Procedures.

REVISION 28 NON-SP GIV PERFORMANCE

May 25/16 (NON-SP GIV AIRPLANES ONLY) Page PC - 11
 Quick Reference Handbook
Non-SP GIV ACN, ctd… GAC

NOTE: Use of these charts is to be with reference to GIV Operating Manual

Chapter 6: Approach and Landing Characteristics and Procedures.

NON-SP GIV PERFORMANCE REVISION 28

Page PC - 12 (NON-SP GIV AIRPLANES ONLY) May 25/16
Quick Reference Handbook
Non-SP GIV ACN, ctd… GAC

NOTE: Use of these charts is to be with reference to GIV Operating Manual

Chapter 6: Approach and Landing Characteristics and Procedures.

REVISION 28 NON-SP GIV PERFORMANCE

May 25/16 (NON-SP GIV AIRPLANES ONLY) Page PC - 13
 Quick Reference Handbook
Non-SP GIV Equivalent Single Wheel Loading (ESWL)
OM 06-05-90

Introduction:
One consideration in operating Gulfstream aircraft is the strength of
runway and taxiway pavements in relation to aircraft operating weight.
This can limit operational weights in some airports. One common
method of evaluating an aircraft for a given runway is the Equivalent
Single Wheel Loading (ESWL). ESWL accounts for the extra tire
flotation for multi-wheel landing gear struts such as the dual wheel
struts used on the Gulfstream aircraft. This section provides
information on how to compute ESWL for the G400, G300, GIV-SP and
Non-SP GIV airplanes.

G400, G300, GIV-SP and Non-SP GIV Main Landing Gear

Parameters:
Max
MLG Tire Tire Max Tire Reduction Maximum
Ramp
Size Spacing Pressure Factor ESWL
Weight
(pounds) (inches) (inches) (psi) ---- (pounds)
75,000 34 × 9.5 16.0 190 1.23 27,439

The reduction factor in the table above assumes a rigid pavement with
a radius of equivalent stiffness of 40 inches, roughly equivalent to a
13.5 inch thick concrete slab. Thinner pavements would give higher
reduction factors, so the factors presented are conservative.

ESWL Computation for Lower Operating Weights:

ESWL can be computed for lower operating weights as follows:
ESWL = (Gross Weight) × (0.9) × (0.5) ÷ (Reduction Factor)

NON-SP GIV PERFORMANCE REVISION 28

Page PC - 14 (NON-SP GIV AIRPLANES ONLY) May 25/16
Quick Reference Handbook
Non-SP GIV Brake Kinetic Energy / Carbon Brake
Cooling AFM APP. C

NOTE: Use of these charts is to be with reference to GIV Airplane Flight

Manual Appendix C: Brake Kinetic Energy and Carbon Brake Cooling.

REVISION 24 (RE-ISSUE) NON-SP GIV PERFORMANCE

Mar 17/10 (NON-SP GIV AIRPLANES ONLY) Page PC - 15
 Quick Reference Handbook
Non-SP GIV Abnormal Landing Field Length Table GAC

Non-SP GIV Abnormal Landing Field Length Table

Reference
Landing Field Corrected, Factored (x 1.67), Dry Runway Landing Field
Length (Feet) Length (Feet) For Abnormal Landing Configuration
39° Flaps 39° 39° 20° 10° 0°
OPERATIVE Anti-Skid OPERATIVE INOP OPERATIVE OPERATIVE OPERATIVE
AUTO Speedbrakes MANUAL AUTO or MAN AUTO AUTO AUTO
4800 4800 8000 4620 4800 4960
5000 5000 9000 4800 5000 5200
5200 5200 10000 4990 5210 5440
5400 5400 11000 5180 5420 5680
5600 5600 12000 5360 5630 5920
5800 5800 13000 5550 5840 6160
6000 6000 14000 5740 6040 6400
6200 6200 15000 5920 6250 6640
6400 6400 16000 6110 6460 6880
6600 6600 17000 6300 6670 7120
6800 6800 18000 6480 6880 7360
7000 7000 19000 6670 7080 7600
7200 7200 20000 6860 7290 7840
7400 7400 21000 7040 7500 8080
7600 7600 22000 7230 7710 8320
7800 7800 23000 7420 7920 8560
8000 8000 24000 7600 8120 8800
8200 8200 25000 7790 8330 9040
8400 8400 26000 7970 8540 9280

CAUTION: THE GIV MAXIMUM LANDING WEIGHT IS 58,500 LB (26,535

KG).
NOTES:
1. Reference Landing Field Length in first column is a FAR 135 factored,
ISA-Day, dry runway distance for a normal landing configuration (Flaps
39°, Anti-Skid operative and either Automatic or Manual deployment of
speed brakes/ground-spoilers).
2. For intended destination wet, multiply landing field lengths above by 1.15.
3. For unfactored landing distances, multiply field lengths above by 0.60.
4. Field lengths seen above are based on no wind or runway slope, but may
be conservatively used with headwinds or uphill runway slopes.
5. For all abnormal landing configurations (0°, 10°, and 20°) with manual
speed brake deployment, increase the flaps 0° landing distance (based on
auto ground spoiler deployment) by 10%.

NON-SP GIV PERFORMANCE REVISION 24 (RE-ISSUE)

Page PC - 16 (NON-SP GIV AIRPLANES ONLY) Mar 17/10
Quick Reference Handbook
Warning (Red) Messages and Annunciations Index
Message SWLP Capsule Page
ACFT CONFIGURATION .............ACFT CONFIG .........................MA-2
AFT BAG SMOKE ........................SMOKE DETECT .....................MA-2
AFT EQUIP HOT ..........................AFT EQUIP HOT ......................MA-2
APU FIRE .....................................APU FIRE .................................MA-2
APU LOAD .....................................................................................MA-2
CABIN DFRN - 9.8 .........................................................................MA-2
CABIN PRESSURE LOW ............CAB PRESS LOW....................MA-3
CHECK PFD ...................................................................................MA-3
CHECK PFD 1-2 ............................................................................MA-3
DAU 1-2 MISCMP-MSG .................................................................MA-3
DOOR BAGGAGE ........................CABIN DOORS ........................MA-4
DOOR MAIN .................................CABIN DOORS ........................MA-4
ENGINE EXCEEDANCE ................................................................MA-4
ENG FIRE LOOP ALERT .............FIRE DET LOOP ......................MA-4
ENGINE HOT, L-R .......................L ENGINE HOT ........................MA-5
R ENGINE HOT .......................MA-5
FLAME DETECT ..........................FLAME DETECT ......................MA-5
FUEL FILTER, L-R .......................L FUEL FILTER ........................MA-5
R FUEL FILTER .......................MA-5
FUEL PRESS LOW, L-R ..............L FUEL PRESS ........................MA-5
R FUEL PRESS .......................MA-5
GND SPOILER .............................GND SPOILER .........................MA-6
FWD LAV SMOKE DETECT ..........................................................MA-6
OIL PRESS LOW, L-R .................L OIL PRESS ...........................MA-6
R OIL PRESS ...........................MA-6
PYLON HOT, L-R .........................L PYLON HOT ..........................MA-6
R PYLON HOT .........................MA-6
RADIO RACK SMOKE .................SMOKE DETECT .....................MA-6
REV UNLOCK, L-R ......................REV UNLOCKED .....................MA-7
SMOKE DETECT .........................SMOKE DETECT .....................MA-7
Other Warning Annunciations and Procedures ..............................MA-9

REVISION 29.1 MESSAGES AND ANNUNCIATIONS

Aug 0717 Page MA - 1
 Quick Reference Handbook
Warning (Red) Messages and Annunciations AFM 4A

Message: Cause(s): Corrective Action:

Check handle Correct configuration.
ACFT positions for:
CONFIGURATION  Flap
 Speed Brake
 Landing Gear
Smoke detected in aft See Airplane Interior
AFT BAG SMOKE baggage Fire/Smoke/Fumes, page ED-7.
compartment.
(SPZ 8400 equipped)
SWLP:

SMOKE DETECT

Aft equipment area 1. Identify faulty side by checking

AFT EQUIP HOT temperature above for high TGT, high fuel flow, low
200°F (93°C). EPR or low (abnormal) bleed
Possibility exists that pressure.
SWLP:
high pressure duct 2. Shut off faulty side bleed
has blown or that fire pressure switch.
AFT EQUIP HOT is in progress. 3. Check isolation valve closed.
4. Descend to 41,000 ft.
5. Monitor message.
6. See Aft Equipment Hot, page
ED-16.
APU fire detected. 1. APU Overspeed Test - PRESS
APU FIRE 2. APU Master Switch - OFF.
3. APU fire extinguisher - PRESS.
SWLP: 4. See APU Fire, page ED-6.

APU FIRE

APU electrical load Select CABIN MASTER OFF.

APU LOAD for operations above
30,000 ft. not in limits.
(SPZ 8400 equipped with
ELWS)
Cabin differential 1. Decrease aircraft climb rate,
CABIN DFRN - press approaching maintain level flight or descend
9.8 upper limit (9.8). as required.
2. Raise cabin altitude.
3. Increase rate of climb of cabin.
4. Switch to manual
pressurization control.
5. See Loss of Automatic
Pressurization Control, Page
EH-6.

MESSAGES AND ANNUNCIATIONS REVISION 29.1

Page MA - 2 Aug 0717
Quick Reference Handbook
Warning (Red) Messages and Annunciations, ctd… AFM 4A

Message: Cause(s): Corrective Action:

5 1. Check cabin pressure
CABIN
controls and indications. If the
PRESSURE LOW outflow valve is closed and
SWLP:
cabin altitude is still climbing, a
baggage door seal or main
CABIN PRESS entrance door seal may be
LOW causing the loss of
pressurization.
2. Select COWL ANTI-ICE ON.
Increase bleed air pressure by
selecting COWL ANTI-ICE ON
or by increasing engine power.
Cabin rate-of-climb can be
controlled by selecting COWL
ANTI-ICE ON and /or by
increasing engine power to
maximum continuous setting at
higher altitudes, thereby
increasing available bleed
pressure above 35 psi.
3. Descend as necessary. If
unable to attain 35 psi or
greater, or if selecting cowl ant-
ice ON results in COOL TURB
HOT message, descend to lower
altitude until cabin rate-of-climb is
controllable. Select cowl anti-ice
OFF if COOL TURB HOT
message persists.
4. Use oxygen, as appropriate.

Hazardously Check pitch, roll, airspeed, and

CHECK PFD misleading altitude on both PFDs to verify
information on both information is correct.
CHECK PFD 1-2 PFDs.

(SPZ 8400 equipped

with ELWS)

Miscompare Attempt to identify faulty channel

DAU 1-2
between data then switch to sensor page and
MISCMP-MSG channels of a select good channel of respective
serious nature. DAU.

REVISION 28 MESSAGES AND ANNUNCIATIONS

May 25/16 Page MA - 3
 Quick Reference Handbook
Warning (Red) Messages and Annunciations, ctd… AFM 4A

Message: Cause(s): Corrective Action:

Main or baggage 1. Reduce cabin pressure
DOOR door not locked. differential.
BAGGAGE 2. Check locking handles for
security.
(Deleted by ASC
3. Exercise care when in vicinity
415. Changed to
Amber Message for of doors.
SPZ 8000/8400 4. If main door does not appear
airplanes and 1390 secure, land as soon as
and subs.) possible.
5. If doors appear secure,
DOOR MAIN continue flight.

SWLP:

CABIN DOORS

LP, HP, or TGT Retard throttle(s) to achieve

ENGINE
EXCEEDANCE above limit. power setting within limits. Shut
down engine if exceedance
(SPZ 8400 equipped) persists with throttle at idle.
(Added by ASC 415 for
SPZ 8000 airplanes)
Engine fire loop 1. If fire handle and HP cock are
ENG FIRE LOOP
ALERT senses fire. illuminated, fire warning is
valid – execute engine fire
SWLP: procedure. See Engine Fire
In Flight (page ED-3) or
FIRE DET LOOP Engine Fire On Ground
(page ED-5).
2. If fire handle and HP cock are
not illuminated, check Fire
Detection Fault Panel - per-
form fire test. See Engine
Fire Warning System
Malfunction, page ED-13
and/or Fire Detection
System Fault, page ED-14.
3. If test is good, disable faulty
loop.
4. If test is bad, execute engine
fire procedure. See Engine
Fire In Flight, page ED-3 or
Engine Fire On Ground,
page ED-5.

MESSAGES AND ANNUNCIATIONS REVISION 28

Page MA - 4 May 25/16
Quick Reference Handbook
Warning (Red) Messages and Annunciations, ctd… AFM 4A

Message: Cause(s): Corrective Action:

Engine cooling air See Engine Hot, page ED-15.
ENGINE HOT, L-
R temperature
above 860°F
SWLP: (460°C).

L ENGINE HOT

R ENGINE HOT

Flame in area See Fire / Overheat / Smoke

FLAME DETECT annunciated by Index, page ED-1, for procedure
illuminated corresponding to area in which
SWLP: annunciation. flame is detected.

FLAME DETECT

Fuel filter 1. Retard power lever to 75%

FUEL FILTER, L-
R clogging. HP.
2. Check that fuel temperature
SWLP: increased to above +5°, and
hold this condition for 10
L FUEL FILTER seconds before restoring
engine power.
R FUEL FILTER 3. Shut down engine if operation
becomes erratic.
NOTE: If fault shows on both
engines, apply above procedure
to only one engine at a time.
Land as soon as possible.
Fuel pressure at 1. Check that boost pumps are
FUEL PRESS
LOW, L-R inlet to high ON and functioning.
pressure fuel 2. Check crossflow valve
SWLP: pump is less than position.
15 psi or both fuel 3. Check for erratic fuel flow
L FUEL PRESS boost pumps on indication.
one side have 4. Shut down engine if operation
R FUEL PRESS been turned off becomes erratic.
with crossflow
valve CLOSED.

REVISION 28 MESSAGES AND ANNUNCIATIONS

May 25/16 Page MA - 5
 Quick Reference Handbook
Warning (Red) Messages and Annunciations, ctd… AFM 4A

Message: Cause(s): Corrective Action:

Failure of ground Immediately select ground
GND SPOILER spoiler spoiler arming switch OFF.
component or See Ground Spoiler Failure,
SWLP: deployed ground page EE-7.
spoiler panel.
GND SPOILER

Smoke detected See Airplane Interior

FWD LAV
in FWD LAV area Fire/Smoke/Fumes, page ED-7.
SMOKE DETECT
or radio rack
(SPZ 8400 equipped) area.
Indicated oil 1. Check oil pressure reading.
OIL PRESS LOW,
L-R pressure below Minimum oil pressure 16 psi
16 psi. below 76% HP RPM.
SWLP: 2. Shut down engine if pressure
abnormally low.
L OIL PRESS

R OIL PRESS

Pylon 1. Appropriate bleed air switch

PYLON HOT, L-R temperature is OFF.
above 325°F 2. Check isolation valve closed.
SWLP: (163°C). 3. Descend to 41,000 ft. Monitor
message.
L PYLON HOT
4. Prepare for possible engine
shutdown.
R PYLON HOT 5. If problem persists, land as
soon as possible.
See Pylon Hot, page ED-15.
Smoke detected See Airplane Interior Fire/
RADIO RACK
SMOKE in radio rack area. Smoke/Fumes, page ED-7.

(Added By ASC 415 for

SPZ 8000/8400
airplanes and SN 1390
and subs.)
SWLP:

SMOKE DETECT

MESSAGES AND ANNUNCIATIONS REVISION 28

Page MA - 6 May 25/16
Quick Reference Handbook
Warning (Red) Messages and Annunciations, ctd… AFM 4A

Message: Cause(s): Corrective Action:

Thrust reverser 1. Ensure thrust reverse lever is
REV UNLOCK,
L-R has become stowed and retard affected
unlocked. engine to idle.
SWLP: 2. Reduce airspeed to less than
200 KCAS and depress
REV UNLOCKED T/REV EMERG STOW
switch.
3. See Reverse Thrust Unlock
or Deploy During Flight,
page EC-16.
CAUTION: DO NOT ATTEMPT TO DEPLOY AND RESTOW THE
AFFECTED REVERSER. DAMAGE CAN OCCUR TO AN ACTUATOR’S
PRIMARY LOCK IF IT IS UNLOCKED WITHOUT MAINTAINING STOW
SIDE PRESSURE ABOVE 1200 PSI. THE ACTUATOR COULD BE
DAMAGED, REQUIRING REPLACEMENT AND/OR LOCKDOWN
PROCEDURES MORE RESTRICTIVE THAN THE INITIAL FAILURE
WOULD DICTATE.
Smoke in area See Airplane Interior Fire/
SMOKE DETECT annunciated by Smoke/Fumes, page ED-7.
illuminated
SWLP: indication.

SMOKE DETECT

REVISION 28 MESSAGES AND ANNUNCIATIONS

May 25/16 Page MA - 7
 Quick Reference Handbook
Warning (Red) Messages and Annunciations, ctd… AFM 4A

Annunciation: Cause(s):
MASTER WARNING reset switch A new WARNING (red) message is
"W" legend (red) illuminated on displayed on CAS. The new
Pilot's / Copilot's Master Warning and message will be displayed flashing
Caution Lights Panel. on the top of the WARNING
Triple chime aural tone sounds. messages stack.
Warning horn sounds. Landing gear unsafe.
(SPZ-8000 Equipped Aircraft)
Klaxon (Hi-Lo, Hi-Lo) sounds.
(SPZ-8400 Equipped Aircraft)
Red LOOP A or LOOP B segments An engine fire loop senses fire.
of L ENG or R ENG FIRE TEST
switches illuminated.
Red light in L / R Fire Handle.
Red light in L / R HP FUEL COCK
handle.
Red APU FIRE light on APU control APU fire sensors detect fire.
panel.
Red APU LOAD light above Display APU electrical load for operations
Unit (DU) 2 or 5 above 30,000 ft. not in limits.
(SPZ-8400 Equipped Aircraft)
Red BAG COMPT SMOKE light Smoke detected in baggage
above DU 5. compartment.
(SPZ-8000 Equipped Aircraft)
Red NO GND SPOILERS light on Failure of ground spoiler component
windshield center post. or deployed ground spoiler panel.
Red chevron illuminated on AOA for approach and landing is too
pilot's/copilot's AOA indexer. high.
Red light in landing gear control Landing gear control handle position
handle. does not agree with landing gear
door position or landing gear
position.
White REV UNLOCK light above DU Thrust reverser unlocked.
2 or 5.
White REV DEPLOY light above DU Thrust reverser deployed.
2 or 5.

MESSAGES AND ANNUNCIATIONS REVISION 28

Page MA - 8 May 25/16
Quick Reference Handbook
Warning (Red) Messages and Annunciations, ctd… OM 04-02-20

Annunciation: Cause(s):
Red light illuminated above Cabin differential press approaching
differential pressure indicator. upper limit (9.8) psi.
Red light illuminated above L COWL Associated cowl anti-ice pressure
or R COWL ANTI-ICE pressure has exceeded 60+2 psi.
indicator.

Other Warning Annunciations and Procedures AFM 4A

Annunciation: Cause(s): Corrective Action:

Red fuel tank Fuel tank Do not dispatch or takeoff with
temperature digits temperature is fuel tank temperature at or
on Fuel synoptic +54° C or higher above +54° C.
page. or -40° C or If airborne and fuel tank
lower. temperature is at or below -40°
C, descend to altitude where
SAT is -60° C or warmer.
Remain at this altitude until the
fuel tank temperature increases
by 2 or 3 degrees.

REVISION 26 MESSAGES AND ANNUNCIATIONS

Oct 5 2011 Page MA - 9
 Quick Reference Handbook
Notes

MESSAGES AND ANNUNCIATIONS REVISION 26

Page MA - 10 Oct 5 2011
Quick Reference Handbook
Caution (Amber) Messages and Annunciations Index
Message Page
AC PWR FAIL, L-R .........................................................................MB-5
AHRS COOL FAIL ..........................................................................MB-5
ALT BRG FAIL, L-R ........................................................................MB-5
ALT FUEL FAIL, L-R ......................................................................MB-5
ALT HOT, L-R ................................................................................MB-5
ALT MODE OFF .............................................................................MB-5
ANTI-SKID FAIL ................ (Brake-By-Wire Airplanes) .................MB-6
ANTI-SKID FAIL ................ (HMAB Airplanes) ..............................MB-6
AOA HEAT 1-2 FAIL ......................................................................MB-6
AP OFF...........................................................................................MB-6
AP TRIM FAIL ................................................................................MB-7
APU ALT BRG FAIL .......................................................................MB-7
APU ALT HOT ................................................................................MB-7
APU LOAD .....................................................................................MB-7
APU MASTER WARN ....................................................................MB-7
APU MASTER WARN (ASC 465) ..................................................MB-7
AUX AC POWER FAIL ...................................................................MB-7
AUXILIARY HYD HOT ...................................................................MB-8
BAGGAGE DOOR ..........................................................................MB-8
BATT 1-2 CHGR FAIL ....................................................................MB-8
BATT HOT ......................................................................................MB-8
BATT ON BUS ................... (DC ESS ON BATT Also) ...................MB-8
BATT WARM ..................................................................................MB-8
BLEED AIR HOT, L-R ....................................................................MB-9
BLEED AIR OFF, L-R .....................................................................MB-9
BLEED CONFIG .............................................................................MB-9
BLEED PRESS HI, L-R ..................................................................MB-9
BRAKE FAIL ...................... (Brake-By-Wire Airplanes) .................MB-9
BRAKE FAIL ...................... (HMAB Airplanes) ..............................MB-9
BRAKE OVHT ..............................................................................MB-10
BRAKE PEDAL ................. (Brake-By-Wire Airplanes) ...............MB-10
CABIN DFRN-9.6 .........................................................................MB-10

REVISION 24 (RE-ISSUE) MESSAGES AND ANNUNCIATIONS

Mar 17/10 Page MB - 1
 Quick Reference Handbook
Caution (Amber) Messages and Annunciations Index
Message Page
CABIN OXYGEN ON ................................................................... MB-10
CABIN PRES MANUAL ............................................................... MB-11
CHECK DU 1-2-3-4-5-6 ............................................................... MB-11
CHECK HYD QUANTITY ............................................................. MB-11
CHECK PFD 1-2 .......................................................................... MB-11
CHECK V SPEEDS...................................................................... MB-11
CMB HYD FAIL ............................................................................ MB-12
CONV FAN FAIL, L-R .................................................................. MB-12
CONV HOT, L-R .......................................................................... MB-12
COOL TURB HOT, L-R ................................................................ MB-13
COWL A/I OVHT, L-R .................................................................. MB-13
COWL PRESS LOW, L-R ............................................................ MB-13
CPL DATA INVALID..................................................................... MB-13
CREW OXYGEN OFF.................................................................. MB-13
DAU 1-2 MISCMP ENG ............................................................... MB-13
DAU 1-2 MISCMP MSG ............................................................... MB-14
DC ESS ON BATT ....................(See BATT ON BUS) .................. MB-8
DC POWER FAIL, L-R ................................................................. MB-14
DOOR SEAL PRES LOW ............................................................ MB-14
DOOR SUPPLY HIGH ................................................................. MB-14
DOOR SUPPLY LOW .................................................................. MB-14
DRSL H ........................................................................................ MB-15
DRSL L ......................................................................................... MB-15
DU FAN 1-2 FAIL ......................................................................... MB-16
EL MISTRIM NOSE UP/DN ......................................................... MB-16
ENG FLT LOOP ALRT ................................................................. MB-16
EPMP BATT SW OFF .................................................................. MB-16
EPMP POWER FAIL .................................................................... MB-17
FGC 1-2 FAIL ............................................................................... MB-18
MESSAGES AND ANNUNCIATIONS REVISION 24 (RE-ISSUE)
Page MB - 2 Mar 17/10
Quick Reference Handbook
Caution (Amber) Messages and Annunciations Index
Message Page
FLAP ASYMMETRY .....................................................................MB-18
FLT HYD FAIL ..............................................................................MB-18
FUEL LEVEL LOW, L-R ...............................................................MB-18
FUEL TEMP HOT, L-R .................................................................MB-19
FWD RADIO RACK HOT .............................................................MB-19
HYD QTY LOW ............................................................................MB-19
ICE DETECTED ...........................................................................MB-19
IRS 1-2 ALN FAULT .....................................................................MB-20
IRS 1-2-3 COOL FAIL ..................................................................MB-20
IRS 1-2-3 ON BATTERY ..............................................................MB-20
MACH TRIM LIMIT .......................................................................MB-20
MACH TRIM OFF .........................................................................MB-20
MAIN FUEL FAIL, L-R ..................................................................MB-20
PAX OXYGEN OFF ......................................................................MB-21
PITOT HT FAIL, L-R .....................................................................MB-21
RETRIM L-R WING DOWN..........................................................MB-21
SNGL RUDDER LIMIT .................................................................MB-21
SPD BRAKE EXTENDED ............................................................MB-21
SSEC DISABLED .........................................................................MB-21
STAB-FLAP FAIL .........................................................................MB-21
STALL BARRIER 1-2 ...................................................................MB-22
STALL BARR 1-2 FL ....................................................................MB-22
STALL BARRIER OFF .................................................................MB-22
STBY PITOT HT FAIL ..................................................................MB-22
STEER BY WIRE FAIL .................................................................MB-23
TAT PROBE HT FAIL ...................................................................MB-23
TRIM LIMIT...................................................................................MB-23
TRU FAIL......................................................................................MB-23
TRU HOT......................................................................................MB-24

REVISION 24 (RE-ISSUE) MESSAGES AND ANNUNCIATIONS

Mar 17/10 Page MB - 3
 Quick Reference Handbook
Caution (Amber) Messages and Annunciations Index
Message Page
UNDER FLOOR O’HEAT ............................................................. MB-24
UTILITY HYD OFF ....................................................................... MB-25
WING HOT, L-R ........................................................................... MB-25
WING TEMP LOW, L-R ............................................................... MB-25
YAW DAMPER OFF .................................................................... MB-26
Other Caution Annunciations ....................................................... MB-27

MESSAGES AND ANNUNCIATIONS REVISION 24 (RE-ISSUE)

Page MB - 4 Mar 17/10
Quick Reference Handbook
Caution (Amber) Messages and Annunciations AFM 3A

Message: Cause(s): Corrective Action:

AC output from 1. Check engine idle speed.
AC PWR FAIL,
L-R converter has 2. Select ELECTRIC MASTER --
dropped off LEFT or RIGHT PWR to OFF
line. ten (10) seconds, then ON.
3. If unable to RESET, place
switch to OFF position.
4. See Alternator / Converter
Failure – Single, page EA-8.
AHRS cooling Illuminates when AHRS or IRS 3
AHRS COOL
FAIL fan has failed. is first turned on (5 seconds) and
AHRS / IRS is in self-test. If
(SPZ 8000 equipped) message illuminates at other
times, shut down AHRS / IRS 3.
Alternator main Operation on auxiliary bearing
ALT BRG FAIL,
L-R bearing has can continue for 15 hours at full
failed and is load or 50 hours at no load. Light
operating on will remain illuminated. Time of
auxiliary occurrence should be recorded.
bearing.
Alternate boost See Fuel Boost Pump Failure,
ALT FUEL FAIL,
L-R pump has page EF-17.
failed.
Alternator 1. Select ELECTRIC MASTER --
ALT HOT, L-R temperature is LEFT or RIGHT PWR to OFF.
above 250°F 2. Check EVM.
(121°C). 3. See Alternator Overheat,
page ED-17.
Autopilot pitch Check altitude modes and
ALT MODE OFF wheel has been commands.
moved while in
(Deleted by ASC 415 altitude hold
for SPZ 8000/8400 mode or
airplanes and SN 1390 altitude
and subs.) preselect has
been reset
while in ASEL
CAP mode.
Message will
time out in 5
seconds.

REVISION 28 MESSAGES AND ANNUNCIATIONS

May 25/16 Page MB - 5
 Quick Reference Handbook
Caution (Amber) Messages and Annunciations, ctd… AFM 3A

Message: Cause(s): Corrective Action:

Normal anti- 1. Check that ANTI SKID ON /
ANTI-SKID FAIL skid control OFF switch is ON.
circuit or other 2. If ON, see Anti-Skid Failure
(Brake-By-Wire) failure: system (Brake-By-Wire), page EB-13.
has switched to
open loop
pulsed anti-skid
control. Power
switch selected
OFF.
Miscompare in See Anti-Skid Failure (HMAB),
ANTI-SKID FAIL 28 VDC power page EB-7.
supplies or in
(HMAB) nutcracker
switches.
ANTI SKID
switch OFF or
system circuit
problems.
Auxiliary
system fails to
energize or
pressure fails to
rise within 3
seconds after
brake pedals
are depressed.
Angle-of-attack Check circuit breaker (AOA PRB
AOA HEAT 1-2 probe heater HTR #1: CP, L-14; AOA PRB
FAIL failed. HTR #2: CP, M-14.) If normal,
avoid icing conditions if possible.
If flight in icing conditions is
unavoidable, pull appropriate stall
warning computer circuit breaker
(STALL WARN CMPTR #1: CPO,
A-11; STALL WARN CMPTR #2:
CPO, B-11) and monitor other
system. Full stall barrier
protection is provided by the
operative system.
Autopilot Press autopilot disconnect button
AP OFF disconnected to clear message, or re-engage
by other than autopilot.
normal means.

MESSAGES AND ANNUNCIATIONS REVISION 28

Page MB - 6 May 25/16
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Caution (Amber) Messages and Annunciations, ctd… AFM 3A

Message: Cause(s): Corrective Action:

Autotrim Check pitch trim switch engaged
AP TRIM FAIL function of (light out).
AFGCS has If out:
failed. 1. Grasp yoke securely (expect
out of trim condition), then
2. Disconnect autopilot, then
3. Retrim, then:
4. Attempt to determine problem.
Alternator main 1. Operation on auxiliary bearing
APU ALT BRG
FAIL bearing has can continue for 15 hours at full
failed and the load or 50 hours at no load.
alternator is 2. Light will remain illuminated.
operating on 3. The time of occurrence should
auxiliary be recorded.
bearing.
APU alternator Shut off APU alternator with
APU ALT HOT temperature. ELECTRIC MASTER AUX PWR
above 300° F switch.
(149° C).
APU electrical Adjust electrical load up or down
APU LOAD load for as necessary.
operation
(SPZ 8400 equipped) above 30,000
ft. not in limits.
APU master Turn master switch OFF or start
APU MASTER
WARN switch ON but APU.
APU is not
running.
APU ECU has Log for maintenance action.
APU MASTER
WARN detected a fault.

(ASC 465: 36-150[G]

APU)
Power output 1. Select AUX PWR switch to
AUX AC POWER
FAIL from APU ALT OFF ten (10) seconds, then
has failed or ON.
dropped off 2. If condition remains same, turn
line. AUX PWR switch OFF.

REVISION 24 (RE-ISSUE) MESSAGES AND ANNUNCIATIONS

Mar 17/10 Page MB - 7
 Quick Reference Handbook
Caution (Amber) Messages and Annunciations, ctd… AFM 3A

Message: Cause(s): Corrective Action:

Auxiliary Turn off auxiliary hydraulic
AUXILIARY HYD
HOT hydraulic pump pump, if practicable.
case tem-
perature above
300° F (149° C).
Baggage door Close and lock baggage door as
BAGGAGE is open or required.
DOOR unlocked.

(SN 1000-1389 having

ASC 415, SN 1390 &
subs.)
Battery or Check L/R BATT CHGR circuit
BATT 1-2 CHGR
FAIL battery charger breakers on PDB:
has failed or the 1. If open, close circuit breaker.
input power 2. If light remains on, deactivate
circuit breaker battery charger by pulling CB.
is open. Light will remain ON.
3. See Battery or Battery
Charger Failure, page EA-21.
L or R battery 1. Select hot battery OFF for
BATT HOT temp at or remainder of flight.
above 150°F. 2. Log for maintenance action.

Essential DC See Essential DC Bus On Bat-

BATT ON BUS Bus powered tery Power, page EA-21.
by batteries
DC ESS ON only.
BATT

(SPZ-8000 airplanes
having ASC 415.)
L (or R) battery 1. Monitor battery temperature
BATT WARM temp at or and select OFF if temperature
above 120° F. reaches 140° F.
Message active only if 2. Log for maintenance action.
optional Battery
Temperature Indicator
system is installed.
May be caution or
advisory message
depending on
message module
programming.

MESSAGES AND ANNUNCIATIONS REVISION 24 (RE-ISSUE)

Page MB - 8 Mar 17/10
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Caution (Amber) Messages and Annunciations, ctd… AFM 3A

Message: Cause(s): Corrective Action:

Bleed air 1. Switch appropriate bleed air
BLEED AIR HOT,
L-R temperature is valve OFF.
above 550°F 2. When hot light is extinguished,
(288°C). open isolation valve and
descend to 41,000 ft.
Bleed air is Select bleed air ON as required.
BLEED AIR OFF,
L-R selected OFF.

(SPZ-8400 airplanes
having ASC 422/422A;
SN 1445 & subs.)
Isolation valve 1. Evaluate bleed configuration.
BLEED CONFIG is open with 2. If isolation valve is open for
engine bleed(s) procedural requirements, select
(SPZ-8000 and SPZ- selected ON. engine bleed(s) OFF as
8400 airplanes having required.
ASC 422/422A; SN
1445 & subs.)
Bleed air 1. Switch appropriate bleed air
BLEED PRESS
HI, L-R pressure has valve OFF.
exceeded 75 2. Check isolation valve closed.
psi. 3. Descend to 41,000 ft.
4. When PRESS HI message is
extinguished, open isolation
valve.
Failure of brake See BRAKE FAIL Message
BRAKE FAIL system, BCS (Brake-By-Wire), page EB-8.
cannot provide
(Brake-By-Wire) braking.
Loss of See BRAKE FAIL Message
BRAKE FAIL combined and (HMAB), page EB-4.
auxiliary
(HMAB) pressure.
No braking
available.

REVISION 24 (RE-ISSUE) MESSAGES AND ANNUNCIATIONS

Mar 17/10 Page MB - 9
 Quick Reference Handbook
Caution (Amber) Messages and Annunciations, ctd… AFM 3A

Message: Cause(s): Corrective Action:

One or more See BTMS OVHT Light On or
BRAKE OVHT brake BRAKE OVHT Message (Brake
assemblies By Wire), page EB-11.
exceed
overheat limit: OR:
1. 400° C for
airplanes SN
1156 thru See BTMS OVHT Light On or
1213 and BRAKE OVHT Message
airplanes (HMAB), page EB-5.
with ASC
167.
2. 625° C for
SN 1214 and
subs and
1000 thru
1213 with
ASC 346.
Malfunctioning 1. Verify inoperative pedal by
BRAKE PEDAL brake pedal. using BRAKE NUTCRKR
ORIDE switch and observing
(Brake-By-Wire) applied brake pressure for
each brake pedal.
2. See BRAKE PEDAL Message
(Brake-By-Wire), page EB-8.
Cabin 1. Raise cabin altitude.
CABIN DFRN-9.6 differential 2. Increase cabin rate of climb, if
pressure has required.
reached 9.6 psi. 3. Switch to manual
pressurization control, if
required. See Loss of
Automatic Pressurization
Control, page EH-6.
Passenger 1. No action required if
CABIN OXYGEN
ON oxygen system passengers require cabin
actuated by oxygen mask deployment.
either manual 2. If masks deployed in error,
or automatic repack masks and reset
means. system.

MESSAGES AND ANNUNCIATIONS REVISION 24 (RE-ISSUE)

Page MB - 10 Mar 17/10
Quick Reference Handbook
Caution (Amber) Messages and Annunciations, ctd… AFM 3A

Message: Cause(s): Corrective Action:

Cabin 1. Cycle AUTO/MANUAL switch
CABIN PRES
MANUAL pressurization to AUTO; check system.
controller has 2. If OK, leave switch in AUTO.
been switched 3. If not, switch to MANUAL and
to manual control cabin pressurization
control with MANUAL CONTROL
automatically or knob. See Loss of Automatic
manually. Pressurization Control, page
EH-6.
Information on Verify data on indicated display
CHECK DU 1-2-3-
4-5-6 indicated unit and if incorrect select
display unit different sensor.
may be
incorrect.
Either 1. Select hydraulic synoptic page
CHECK HYD
QUANTITY Combined and verify which quantity is low.
and/or Flight If a leak is evident, expect
(SPZ 8400 equipped) Hydraulic system to fail.
System quantity 2. For loss of Combined Hydraulic
is low. fluid, see Combined Hydraulic
System Failure – Loss of
Pressure and Fluid, page EF-
8.
3. For loss of Flight Hydraulic
fluid, see Flight Hydraulic
System Failure – Loss of
Pressure and / or Fluid, page
EF-11.
4. For loss of both systems, see
Dual Hydraulic System
Failure, page EF-4.
Erroneous in- 1. Check pitch, roll, airspeed and
CHECK PFD 1-2 formation on altitude on both PFDs.
Primary Flight 2. Compare with standby instru-
(SPZ 8400 equipped) Displays ments to verify information is
(PFDs). correct.
The flight man- Compare V-speeds, verify initiali-
CHECK V
SPEEDS agement sys- zation and FMS status for mode
tems have of operation.
computed V-
speeds that are
different.

REVISION 24 (RE-ISSUE) MESSAGES AND ANNUNCIATIONS

Mar 17/10 Page MB - 11
 Quick Reference Handbook
Caution (Amber) Messages and Annunciations, ctd… AFM
3A

Message: Cause(s): Corrective Action:

Failure of Com-
1. Check Combined Hydraulic
CMB HYD FAIL bined Hydraulic
pressure and quantity.
System pres-
2. For loss of Combined Hydraulic
sure. pressure and fluid, see
Combined Hydraulic System
Failure – Loss of Pressure
and Fluid, page EF-8.
3. For loss of Combined Hydraulic
pressure only, see Combined
Hydraulic System Failure –
Loss of Pressure Only, page
EF-10.
CAUTION: STALL BARRIER PROTECTION IS NOT AVAILABLE WITH
LOSS OF COMBINED HYDRAULIC FLUID.
A converter 1. Record time of failure.
CONV FAN FAIL,
L-R cooling fan has 2. Continued operation for
failed. maximum of 25 hours is
permitted.
3. Subsequent takeoffs are
permitted upon verification that
only one cooling fan has failed.
4. Operation with more than one
failed cooling fan may result in
damage to and/or automatic
shutdown of converter.
5. Light will remain illuminated.
NOTE: With ASC 285 incorporated, message will remain displayed. Display
of this message, whether momentary or permanently set, requires a
maintenance action.
Converter 1. Turn ELECTRIC MASTER,
CONV HOT, L-R temperature is LEFT or RIGHT PWR OFF.
above 220°F 2. Light will remain on until
(104°C). temperature reduces to 190°F
(88°C).
3. Try to turn converter back on, if
possible (after light is OFF).
4. Try reducing electrical load on
affected converter.
5. If illumination recurs, turn OFF
and do not reinstate.

MESSAGES AND ANNUNCIATIONS REVISION 24 (RE-ISSUE)

Page MB - 12 Mar 17/10
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Caution (Amber) Messages and Annunciations, ctd… AFM 3A

Message: Cause(s): Corrective Action:

Cooling turbine 1. On ground, ECS system will
COOL TURB
HOT, L-R discharge air automatically shut down.
above 450°F 2. In flight, see Left or Right
(232°C). Cooling Turbine Hot, page
EH-11.
Engine cowl 1. Turn COWL ANTI-ICE OFF.
COWL A/I OVHT,
L-R temperature is 2. If message persists, TURN
above 662°F WING ANTI-ICE OFF.
(350°C). 3. If message persists, turn
associated BLEED AIR OFF.
4. Depart icing conditions.
Cowl anti-ice 1. Check engine power setting.
COWL PRESS
LOW, L-R press. is less 2. Increase thrust setting to
than 10 ±1 psi. extinguish message if cowl
(4 psi ±1 for anti-ice pressure is less than 4
airplanes SN psi.
1190 and subs. 3. If cowl anti-ice pressure gage is
and SN 1000 inoperative, increase thrust to
thru 1189 with extinguish message.
ASC 243).
With FMS as Select any autopilot lateral and
CPL DATA
INVALID coupled NAV vertical mode.
source, airplane
has flown off
end of flight
plan, resulting
in autopilot
reverting to
heading hold
and pitch hold
(If VNAV was
active).
Crew oxygen is 1. Verify bottle is OPEN at the
CREW OXYGEN
OFF shut OFF at the bottle.
bottle. 2. If bottle is OPEN, notify
(SN 1290 & subs) maintenance prior to dispatch.
Engine data Compare engine data displayed
DAU 1-2 MISCMP
ENG miscompare with DAU 'A' and 'B' channels.
between DAU Select good channel.
'A' and 'B'
channels.

REVISION 24 (RE-ISSUE) MESSAGES AND ANNUNCIATIONS

Mar 17/10 Page MB - 13
 Quick Reference Handbook
Caution (Amber) Messages and Annunciations, ctd… AFM
3A

Message: Cause(s): Corrective Action:

EICAS amber Compare amber messages
DAU 1-2 MISCMP
MSG message displayed with DAU 'A' and 'B'
miscompare channels. Select good channel.
between DAU
'A' and 'B'
channels.
DC output from 1. Check engine idle.
DC POWER FAIL,
L-R converter has 2. Select ELECTRIC MASTER --
dropped off LEFT or RIGHT PWR to OFF
line. ten (10) seconds, then ON.
3. If unable to RESET, continue
operation, but monitor condition
frequently.
4. If any unusual condition occurs,
place ELECTRIC MASTER,
LEFT or RIGHT PWR to OFF
position.
5. See Alternator / Converter
Failure - Single, page EA-8.
Main entrance In flight – Check engine power
DOOR SEAL
PRES LOW door seal setting. Increase thrust setting to
and/or baggage extinguish message. If message
(SPZ-8400 equipped door seal does not extinguish, monitor
Airplanes having pressure is less cabin altitude. Check door seals
Advance Warning than 2.5 +/- 0.5 for possible leaks. If leaks
System for the GIV Door psig relative to detected, descend to safe
Seal System.) cabin pressure. altitude. If loss of cabin pressure,
perform emergency descent.
On the ground – Troubleshoot
system and perform maintenance
as required.
Output In flight – Check engine power
DOOR SUPPLY
HIGH pressure from setting. Decrease thrust setting to
door seal extinguish message. If message
(SPZ-8400 equipped regulator is does not extinguish, monitor
Airplanes having greater than 26 cabin altitude. Monitor EICAS for
Advance Warning psig. possible DOOR SEAL PRES
System for the GIV Door LOW annunciation.
Seal System.)
On the ground – Troubleshoot
system and perform maintenance
as required.

MESSAGES AND ANNUNCIATIONS REVISION 24 (RE-ISSUE)

Page MB - 14 Mar 17/10
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Caution (Amber) Messages and Annunciations, ctd… AFM 3A

Message: Cause(s): Corrective Action:

Output In flight – Check engine power
DOOR SUPPLY
LOW pressure from setting. Increase thrust setting to
door seal extinguish message. If message
(SPZ-8400 equipped regulator is less does not extinguish, monitor
Airplanes having than 12 +/- 1.5 cabin altitude. Monitor EICAS for
Advance Warning psig. possible DOOR SEAL PRES
System for the GIV Door LOW annunciation.
Seal System.)
On the ground – Troubleshoot
system and perform maintenance
as required.
Output In flight – Check engine power
DRSL H pressure from setting. Decrease thrust setting to
door seal extinguish message. If message
(SWLP indication for regulator is does not extinguish, monitor
SPZ-8000 equipped greater than 26 cabin altitude. Monitor indication
Airplanes having psig. lights for possible DRSL L
Advance Warning annunciation. If DRSL L
System for the GIV Door
Seal System.)
annunciates, follow Corrective
Action for DRSL L indication as
defined below.
On the ground – Troubleshoot
system and perform maintenance
as required.
Output In flight – Check engine power
DRSL L pressure from setting. Increase thrust setting to
door seal extinguish message. If message
(SWLP indication for regulator is less does not extinguish, monitor
SPZ-8000 equipped than 12 +/- 1.5 cabin altitude. Check door seals
Airplanes having psig and/or for possible leaks. If leaks
Advance Warning main entrance detected, descend to safe
System for the GIV Door
Seal System.)
door seal or altitude. If loss of cabin pressure,
baggage door perform emergency descent.
seal pressure is On the ground – Troubleshoot
less than 2.5 system and perform maintenance
+/- 0.5 psig as required.
relative to cabin
pressure.

REVISION 24 (RE-ISSUE) MESSAGES AND ANNUNCIATIONS

Mar 17/10 Page MB - 15
 Quick Reference Handbook
Caution (Amber) Messages and Annunciations, ctd… AFM 3A

Message: Cause(s): Corrective Action:

Respective 1. Fan No. 1 cools DU 1, 3 and 5.
DU FAN 1-2 FAIL Display Unit 2. Fan No. 2 cools DU 2, 4 and 6.
(DU) cooling 3. If Fan No. 1, consider switching
fan has failed. pilot's side to PFD XFER.
4. If Fan No. 2, consider switching
copilot's side to PFD XFER.
Autopilot 1. No action required for
EL MISTRIM
NOSE UP/DN elevator trim momentary message.
out of trim in 2. If steady message disengage
direction autopilot, retrim, attempt to
indicated. determine problem.
Engine fire 1. Check fire detection fault panel.
ENG FIRE LOOP
ALERT detection loop 2. Identify engine and loop.
fault detector 3. Disable faulty loop with fault
active. switch.
Battery No. 1 1. Depress proper switch.
EPMP BATT SW
OFF and/or No. 2 2. No message indicates that both
switch battery switches are on.
(MASTER) is
OFF.

MESSAGES AND ANNUNCIATIONS REVISION 24 (RE-ISSUE)

Page MB - 16 Mar 17/10
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Caution (Amber) Messages and Annunciations, ctd… AFM 3A

Message: Cause(s): Corrective Action:

Either 1 or all 4 1. Check CBs:
EPMP POWER
FAIL sources of input  EPMP SW PWR # 1: PO, A-5
power supply to  EPMP SW PWR # 2: PO, B-5
EPMP has  EPMP # 1 DC: PO, C-9
failed.  EPMP # 2 DC: PO, D-9
NOTE: If – in 2. If only 1 power supply has
addition to this failed, continue operation as
message – all normal, and if appropriate,
EPMP indica- attempt to reset CB.
tions are lost, it
3. If all power sources have failed
is possible that
(indicated by black-out of
the overhead
EPMP), land as soon as
panel dimming
practical.
rheostat
(OVHD PNL
knob) is in a
position be-
tween fully OFF
(which reverts
the EPMP to
full bright
mode) and the
beginning of
the brightness
controlling
feature. Rota-
tion of the
OVHD PNL
knob may rem-
edy this anom-
aly.

REVISION 24 (RE-ISSUE) MESSAGES AND ANNUNCIATIONS

Mar 17/10 Page MB - 17
 Quick Reference Handbook
Caution (Amber) Messages and Annunciations, ctd… AFM 3A

Message: Cause(s): Corrective Action:

Respective None required. Switchover to
FGC 1-2 FAIL FGC system good flight guidance system is
has failed. automatic.
Cycle appropriate CB if FGC is
hard-failed: (FGC #1: CPO, A-7;
FGC #2: CPO, B-7)
Flap position 1. Select longest available runway
FLAP
asymmetry for landing.
ASYMMETRY
detected. Flaps 2. L/R Airstart Ignition - ON.
(1) (2) have stopped 3. VREF for configuration from
moving toward Performance section.
selected 4. GPWS/GND SPOILER FLAP
position. ORIDE - ON.
CAUTION: DO NOT EXCEED
TIRE SPEED LIMITATIONS.
(1) SPZ 8400 equipped airplanes with ASC 69A or ASC 69B (Flap
Asymmetry Indicator) installation.
(2) SPZ 8000 equipped airplanes with ASC 69A or ASC 69B, an amber
FLAP ASYM indicator light, installed under the FLAP/STAB position
indicator, will illuminate. The CAS message is not incorporated.
Failure of Flight 1. Check Flight Hydraulic
FLT HYD FAIL Hydraulic pressure and quantity.
System 2. For loss of Flight Hydraulic
pressure. pressure and / or fluid, see
Flight Hydraulic System
Failure – Loss of Pressure
and / or Fluid, page EF-11.
Fuel level in 1. Ensure boost pumps are ON.
FUEL LEVEL
LOW, L-R hopper is below 2. Check fuel quantity gauge.
approximately 3. OPEN cross-flow valve.
650 lb (295 kg). 4. If fuel quantity is greater than
650 lb in appropriate tank:
 In flight, level airplane attitude
 On ground, turn boost pumps
on to fill hopper

MESSAGES AND ANNUNCIATIONS REVISION 24 (RE-ISSUE)

Page MB - 18 Mar 17/10
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Caution (Amber) Messages and Annunciations, ctd… AFM 3A

Message: Cause(s): Corrective Action:

FUEL TEMP HOT, Fuel 1. Retard power and monitor

L-R temperature temperature indication.
above 90°C or 2. If indication does not return to
below 0°C. normal, place power lever in
idle position.
OR:
1. Verify oil temperature is within
operating level at engine start.
2. Allow engine to operate at idle
until operating temperature is
reached.
3. Message will extinguish when
engine fuel temperature is
above 0°C.
Radome, left or 1. Attempt to isolate hot
FWD RADIO
RACK HOT right equipment equipment and shut down.
bay tem- 2. Turn off unnecessary
perature has equipment.
exceeded
200°F (93°C).
Either 1. Select HYDRAULICS synoptic
HYD QTY LOW Combined and verify which quantity is low.
and/or Flight If a leak is evident, expect
Hydraulic system to fail.
System quantity 2. For loss of Combined Hydraulic
is low. fluid, see Combined Hydraulic
System Failure – Loss of
Pressure and Fluid, page EF-
8.
3. For loss of Flight Hydraulic
fluid, see Flight Hydraulic
System Failure – Loss of
Pressure and / or Fluid, page
EF-11.
4. For loss of both systems, see
Dual Hydraulic System
Failure, page EF-4.
Ice detected by Select cowl and/or wing anti-ice
ICE DETECTED
probe. on, as appropriate or depart icing
(If Installed) condition.

REVISION 26 MESSAGES AND ANNUNCIATIONS

Oct 5 2011 Page MB - 19
 Quick Reference Handbook
Caution (Amber) Messages and Annunciations, ctd… AFM 3A

Message: Cause(s): Corrective Action:

Improper 1. Check PRESENT POSITION.
IRS 1-2 ALN
FAULT PRESENT 2. If incorrect, re-enter.
POSITION 3. If correct or if excess motion is
entry or excess suspected, turn IRS off for 3
airplane motion seconds then back to ALIGN
while in align and re-enter PRESENT
mode. POSITION.
IRS 1-2-3 COOL Respective IRS Shut down IRS.
FAIL cooling fan has
failed.
(IRS 3 is SPZ 8400
only)
Respective IRS 1. Check normal bus power
IRS 1-2 ON
BATTERY has lost normal source to IRS and restore, if
power source able.
and has 2. Expect limited IRS endurance.
reverted to
battery power.
Elevator trim Retrim or slow airplane.
MACH TRIM
LIMIT has reached
electrical trim
limit while
operating
airplane in
Mach Trim
speed region
(greater than
0.80 Mach).
Pitch trim 1. Check pitch trim switch
MACH TRIM OFF switch OFF or engaged (light out).
electric trim 2. If switch engaged, check STAB
system has AUG SERVO circuit breakers
failed (message (CPO: A-6, B-6.)
inhibited at less 3. Observe mach trim inop speed.
than 0.82 4. See GIV AFM Section 1-22-
Mach). 10: Mach Trim Compensation
/ Electric Elevator Trim.
Main boost 1. Check position of MAIN PUMP
MAIN FUEL FAIL,
L-R pump has CONT circuit breaker on POP.
failed. 2. Select alternate boost pump.
3. Turn failed pump OFF and pull
appropriate CB in PDB.
4. See Fuel Boost Pump
Failure, page EF-17.

MESSAGES AND ANNUNCIATIONS REVISION 26

Page MB - 20 Oct 5 2011
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Caution (Amber) Messages and Annunciations, ctd… AFM 3A

Message: Cause(s): Corrective Action:

Passenger 1. Verify bottle is OPEN at the
PAX OXYGEN oxygen bottle is bottle.
OFF shut OFF at the 2. If bottle is OPEN, notify
(SN 1290 & subs) bottle. maintenance prior to dispatch.
Pitot tube 1. Check PITOT HEAT switch ON
PITOT HT FAIL, heater and circuit breaker(s) – IN (L
L-R elements not PITOT HT CONT: CP, L-12; L
energized. PITOT HT PWR: CP, L-11; R
PITOT HT CONT: CP, M-12; R
PITOT HT PWR: CP, M-11.)
2. If PITOT HEAT illuminates,
expect erroneous indications of
ASI, Air Data System
Computer, Airspeed Warning
Sensor, and Mach Trim
Compensation.
3. Depart icing conditions.
Lateral axis out 1. Grasp control yoke firmly.
RETRIM L-R of trim. 2. Disconnect autopilot and retrim
WING DOWN airplane in direction indicated.
Failure of input Avoid abnormal rudder deflection.
SNGL RUDDER pressure load
LIMIT limiter (with
flight and com-
bined system
pressure nor-
mal).
Speed brakes Retract speed brakes or reduce
SPD BRAKE (flight spoilers) thrust as desired.
EXTENDED are deployed
with throttles
above idle.
Static source Check the appropriate radio rack
SSEC DISABLED error correction DADC test switches.
to DADC has
been disabled.
Flaps UP (0°) 1. Lower flaps to correspond with
STAB-FLAP FAIL and stabilizer stabilizer position to prevent
not UP. running out of longitudinal trim.
2. Maintain airspeed within flap
position limits.
3. See Failure of Stabilizer /
Flap Interconnect, page EE-9.

REVISION 28 MESSAGES AND ANNUNCIATIONS

May 25/16 Page MB - 21
 Quick Reference Handbook
Caution (Amber) Messages and Annunciations, ctd… AFM 3A

Message: Cause(s): Corrective Action:

Stall barrier 1. If either valve light is
STALL BARRIER
1-2 system giving illuminated, check airplane
stall angle attitude, power, and airspeed.
indication. 2. If primary instruments indicate
normal conditions, disable
system by pulling the STALL
WARN CMPTR circuit breaker
(STALL WARN CMPTR #1:
CPO, A-11; STALL WARN
CMPTR #2: CPO, B-11.)
3. Full protection is provided by
operative system.
Stall barrier 1. Check STALL BARRIER and
STALL BARR 1-2
FL failed. It is STALL BARR VALVE circuit
normal for breakers (STALL BARR
STALL VALVE #1: CPO, B-12; STALL
BARRIER 1 FL BARR VALVE #2: CPO, B-9)
to appear any 2. Pull appropriate faulty barrier
time breakers.
EMERGENCY 3. Stall barrier protection is still
FLAPS are available with one system
used and flap operative.
position is
greater than
22°.
Stall barrier 1. Check stall barrier switch ON
STALL BARRIER
OFF switch OFF or ("OFF" light out).
system not 2. If on, check STALL BARRIER
powered. and STALL BARR VALVE
circuit breakers (STALL BARR
VALVE #1: CPO, A-12; STALL
BARR VALVE #2: CPO, B-12;
STALL BARRIER #1: CPO, A-
9; STALL BARRIER #2: CPO,
B-9.)
Standby pitot Check STBY PITOT HEAT switch
STBY PITOT HT
FAIL heater and circuit breaker (STBY PITOT
elements not HT CONT: CP L-13; STBY PITOT
energized. HT PWR: CP M-13.)

MESSAGES AND ANNUNCIATIONS REVISION 28

Page MB - 22 May 25/16
Quick Reference Handbook
Caution (Amber) Messages and Annunciations, ctd… AFM 3A

Message: Cause(s): Corrective Action:

Both steering 1. Check circuit breakers (STEER
STEER BY WIRE
FAIL channels have BY WIRE #1: CPO, C-12;
failed: steering STEER BY WIRE #2: CPO, D-
not available. 12.)
System is in 2. Cycle steering ON/OFF switch.
shimmy damp 3. If message does not clear, use
mode. rudder, brakes, and/or
differential power for steering.
4. If message occurs on ground
with no hydraulic power
available, turn power switch
With ASC 176
OFF until engines are running.
installed, a
5. Reselect power switch ON.
switch position /
system status If message occurs in flight: see
miscompare is Nose Wheel Steering Failure,
detected. page EG-8.
TAT probe 1. TAT inputs to DADC’s may be
TAT PROBE HT
FAIL heater has inaccurate.
failed. 2. DADC outputs and FMS
readouts may be inaccurate.
3. Check circuit breaker (TOTAL
TEMP PROBE HTR: CP, L-10.)
Autopilot Cycle PITCH TRIM switch to
TRIM LIMIT elevator trim DISENGAGE position and
has reached manually trim, as required.
electric trim
limits.
Transformer 1. Check that L or R MAIN AC
TRU FAIL rectifier has no bus is powered.
output. 2. Check that the MAIN DC Bus
EPMP TRU/EXT switchlight is
illuminated.
3. If not, TRU/EXT switch - PUSH.
4. Check both TRU circuit
breakers on Power Distribution
Box.
5. If still no power, reduce load to
below 250 Amps and return
Main DC Bus Switch to AUTO.

REVISION 24 (RE-ISSUE) MESSAGES AND ANNUNCIATIONS

Mar 17/10 Page MB - 23
 Quick Reference Handbook
Caution (Amber) Messages and Annunciations, ctd… AFM 3A

Message: Cause(s): Corrective Action:

Transformer Reduce load on TRU. If warning
TRU HOT rectifier continues after 2 minutes:
temperature. 1. Select other available DC
above 374°F power source(s).
(190°C). 2. Pull TRU (R AC) circuit
breaker.
Bleed air leak 1. If wing anti-ice is on, select
UNDER FLOOR detected under left wing OFF.
O’HEAT cabin floor. 2. If message persists, select
right wing off.
(SN 1280-1327 having
3. Wait 2 minutes.
ASC 415B and ASC
395; SN 1328 and 4. If message persists, depart
subs.) icing conditions.
5. If message extinguishes, re-
establish wing anti-ice using
the anti-ice switch which did
not cause the message to
extinguish.
6. If in doubt, depart icing
conditions.
7. Verify ISOLATION valve
closed.
8. Select left bleed OFF.
9. If message persists:
• Select left bleed ON and
right bleed OFF
• Check floor board
physically for temperature
10. If cool, no action.
11. If hot, descend to 15,000 ft.
or below and select left bleed
off and RAM AIR on.
NOTE: If the condition requires
that a SINGLE (L or R) ENG
BLEED be selected OFF,
descend to 41,000 ft. or below.
If above 41,000 ft. and ENG
BLEED is selected OFF, make
slow deliberate power lever
movements on the affected
engine.

MESSAGES AND ANNUNCIATIONS REVISION 24 (RE-ISSUE)

Page MB - 24 Mar 17/10
Quick Reference Handbook
Caution (Amber) Messages and Annunciations, ctd… AFM 3A

Message: Cause(s): Corrective Action:

Utility hydraulic Turn utility hydraulic pump to
UTILITY HYD
OFF pump has been ON/ARM if desired.
selected off.
Wing anti-icing 1. Turn applicable wing anti-icing
WING HOT, L-R exhaust duct switch to OFF. Wait two (2)
temperature minutes.
above 180°F 2. If message remains ON, assure
(82°C). isolation valve is closed, then
select applicable side BLEED
AIR switch to OFF.
3. If message remains ON,
indication is false and flight
may be continued with normal
use of wing anti-icing. Reselect
applicable BLEED AIR switch
ON.
4. If message goes out in Step 2,
leave applicable BLEED AIR
switch OFF, select applicable
ECS pack OFF, and re-check
isolation valve closed. Descend
to 41,000 ft. Monitor cabin
altitude; descend as required.
NOTE: With Bleed Air switch OFF
and Isolation valve CLOSED, there
is no cowl anti-icing available to that
engine.
5. Monitor wings for icing. Depart
icing conditions as soon as
possible.
Wing anti-icing 1. Increase thrust if flight
WING TEMP
LOW, L-R exhaust duct conditions permit.
temperature 2. If message does not go out,
below 100°F monitor wings for icing and
(38°C). Will not depart icing conditions as soon
illuminate for as possible.
two (2) minutes
after switch ON
(time delay).

REVISION 28 MESSAGES AND ANNUNCIATIONS

May 25/16 Page MB - 25
 Quick Reference Handbook
Caution (Amber) Messages and Annunciations, ctd… AFM 3A

Message: Cause(s): Corrective Action:

Yaw damper 1. Check yaw damper switch ON
YAW DAMPER
OFF switch OFF or (light out).
yaw damper 2. If switch on, check STAB AUG
failure. SERVO circuit breakers (STAB
AUG SERVO #1: CPO, A-6;
STAB AUG SERVO #2: CPO,
B-6.)
3. Observe yaw damper
inoperative speed. See Yaw
Damper Failure, page EE-14.

MESSAGES AND ANNUNCIATIONS REVISION 28

Page MB - 26 May 25/16
Quick Reference Handbook
Caution (Amber) Messages and Annunciations, ctd… OM 04-03-20

Annunciation: Cause(s):
MASTER CAUTION reset switch "C" A new CAUTION (amber) message
legend (amber) illuminated on Pilot's is displayed on CAS. The new
/ Copilot's Master Warning and message will be displayed flashing
Caution Lights Panel. on the top of the CAUTION
"Double Chime" aural tone sounds. messages stack.
"Lo-Lo-Lo" aural tone sounds. Autothrottle disconnected.
"Lo-Hi-Lo" aural tone sounds. Autopilot manually disconnected.
AC RESET light (amber) illuminated AC Bus fault indicated.
on EPMP. A fault on the L or R MAIN AC bus
will result in that bus being
disconnected from all power sources.
No power source light will be
illuminated.
A fault on the ESS AC bus will result
in the AC BPCU cycling bus power
from LEFT to RIGHT to E-INV. The
amber E-INV "ON" switch legend will
also be illuminated.
See Bus Fault - AC or DC RESET
Light on, page EA-14.
DC RESET light (amber) illuminated DC Bus fault indicated.
on EPMP. A fault on the L or R MAIN DC bus
will result in that bus being
disconnected from all power sources.
No power source light will be
illuminated.
A fault on the ESS DC bus will result
in the DC BPCU cycling bus power
from LEFT to RIGHT to BATT. The
amber BATT "ON" switch legend will
also be illuminated.
See Bus Fault - AC or DC RESET
Light on, page EA-14.
BATT 1 or BATT 2 CHGR FAIL light Battery or battery charger has failed,
(amber) illuminated on EPMP. Left Main AC bus or Right Main AC
bus has failed, or input power circuit
breaker is open.
L ALT FAILED BRG light (amber) Left alternator main bearing has
illuminated on overhead panel. failed and alternator is operating on
auxiliary bearing.

REVISION 28 MESSAGES AND ANNUNCIATIONS

May 25/16 Page MB - 27
 Quick Reference Handbook
Caution (Amber) Messages and Annunciations, ctd… OM 04-03-20

Annunciation: Cause(s):
APU ALT FAILED BRG light (amber) APU alternator main bearing has
illuminated on overhead panel. failed and alternator is operating on
auxiliary bearing.
R ALT FAILED BRG light (amber) Right alternator main bearing has
illuminated on overhead panel. failed and alternator is operating on
auxiliary bearing.
L/R ENG IDLE light (amber) Engine idle is in low range when it
illuminated on windshield center post. should be scheduled to high range.
OR:
Engine idle is in high range when it
should be scheduled to low range.
See Approach Idle System Failure,
page EC-19.
Amber chevron illuminated on AOA for approach and landing is too
pilot's/copilot's AOA indexer. low.
AP OFF light (amber) illuminated on Autopilot disconnected.
Pilot's / Copilot's Master Warning and
Caution Lights Panel.
AT OFF light (amber) illuminated on Autothrottle disconnected.
Pilot's / Copilot's Master Warning and
Caution Lights Panel.
LOW FUEL light(s) (amber) Fuel level in respective hopper is
illuminated on standby fuel quantity below approximately 650 lb (295 kg).
indicator.
APU LOAD light (amber) illuminated APU electrical load for operations
above DU 2 or 5. above 30,000 ft. not within limits.
(SPZ-8400 equipped)
ELWS CONFIG light (amber) APU electrical power improperly
illuminated above DU 2 or 5. configured for operations above
(SPZ-8400 equipped) 30,000 ft.
ELWS FAIL light (amber) illuminated APU electrical power unreliable for
above DU 2 or 5. operations above 30,000 ft.
(SPZ-8400 equipped)
N COOL VALVE OPEN light (amber) Nose compartment cooling valve is
illuminated above DU 2 or 5. open.
HORN SILENCE light (amber) Airplane is below 1200 ft. AGL (radio
illuminated on Landing Gear Control altitude), all three landing gear not
Panel. down and locked, flaps less than 22°,
and power lever is retarded below
70%.

MESSAGES AND ANNUNCIATIONS REVISION 28

Page MB - 28 May 25/16
Quick Reference Handbook
Caution (Amber) Messages and Annunciations, ctd… OM 04-03-20

Annunciation: Cause(s):
Amber light illuminated above Cabin differential pressure has
differential pressure indicator. reached 9.6 psi.
Amber light illuminated above APU APU is at 100% speed and EGT has
EGT indicator. exceeded 688°.
Amber light illuminated above APU APU RPM has exceeded 104%.
RPM indicator.
Amber FIRE EXT DISCHD legend APU fire extinguisher has been
illuminated on APU FIRE EXT switch. discharged.

REVISION 24 (RE-ISSUE) MESSAGES AND ANNUNCIATIONS

Mar 17/10 Page MB - 29
 Quick Reference Handbook
Notes

MESSAGES AND ANNUNCIATIONS REVISION 24 (RE-ISSUE)

Page MB - 30 Mar 17/10
Quick Reference Handbook
Advisory (Blue) Messages and Annunciations Index
Message Page
AC EXT POWER ..........................(DC EXT POWER Also) .......... MC-4
AP CTLR SW STUCK ................................................................... MC-4
AP ENGAGE INHIBIT ................................................................... MC-4
APU ALT OFF ............................................................................... MC-4
APU EXCEEDANCE ..................................................................... MC-5
AT ENGAGE INHIBIT .................................................................... MC-5
AT 1-2 FAIL ................................................................................... MC-6
AT NOT IN HOLD .......................................................................... MC-6
BATT WARM ................................................................................. MC-6
BC 1-2-3 TEST FAIL ..................................................................... MC-6
BRAKE MAINT REQ'D ................(Brake-By-Wire Airplanes) ...... MC-7
BRAKE MAINT REQ'D ................(HMAB Airplanes).................... MC-7
BUS CTLR 1-2-3 FL ...................................................................... MC-7
CALL .............................................................................................. MC-7
CDU 1-2 FAIL ................................................................................ MC-7
CHECKLIST MISMATCH .............................................................. MC-7
CMB HYD HOT ............................................................................. MC-8
CONT IGN, L-R ............................................................................. MC-8
COWL A/I ON, L-R ........................................................................ MC-8
CPL DATA INVALID ...................................................................... MC-8
DADC 1-2 FAIL ............................................................................. MC-8
DADC MISCOMPARE ................................................................... MC-9
DAU 1A-1B-2A-2B FL ................................................................... MC-9
DAU 1-2 MISCMP-MSG ................................................................ MC-9
DC CONFIG MISMATCH .............................................................. MC-9
DC EXT POWER ..........................(See AC EXT POWER) ........... MC-4
DISP CTLR 1-2 FAIL ..................................................................... MC-9
DU 1-2-3-4-5-6 HOT ...................................................................... MC-9
E BATT 1-2-3-4 DISCH ............................................................... MC-10
E BATT 1-2-3-4 FAIL ................................................................... MC-10
REVISION 24 (RE-ISSUE) MESSAGES AND ANNUNCIATIONS
Mar 17/10 Page MC - 1
 Quick Reference Handbook
Advisory (Blue) Messages and Annunciations Index
Message Page
ENGINE COWL OPEN ................................................................MC-10
ENGINE EXCEEDANCE..............................................................MC-10
EXCEEDANCE RECORD ............................................................MC-10
EPR 1 - DADC 2 ..........................................................................MC-10
EPR 2 - DADC 1 ..........................................................................MC-10
EXT BATT SWITCH ON ..............................................................MC-10
FGC 1-2 MASTER .......................................................................MC-11
FGC NOT USING IRS 1-2 ...........................................................MC-11
FGC SYSTEM TEST ....................................................................MC-11
FLT HYD HOT ..............................................................................MC-11
FLIGHT REC FAIL .......................................................................MC-11
FUEL INT TANK OPEN ...............................................................MC-11
FUEL XFLOW OPEN ...................................................................MC-11
FWC 1-2 FAIL ..............................................................................MC-12
FWD EXT SW PNL OPN .............................................................MC-12
FWD LAV SVC DR OPN ..............................................................MC-12
GND SPOILER UNARM ..............................................................MC-12
GPWS FAIL ..................................................................................MC-12
IRS 1-2 FAIL ................................................................................MC-12
IRS 1-2 HI LAT ALN .....................................................................MC-12
IRS MISCOMPARE......................................................................MC-12
IRS MONITOR FAIL .....................................................................MC-13
IRS 1-2 NAV READY ...................................................................MC-13
IRS 1-2 ON DC ............................................................................MC-13
ISOLATION VLV OPEN ...............................................................MC-13
MAINT SWITCH ON ....................................................................MC-13
NAV MISCOMP L-R SEL .............................................................MC-13
NZ 1-2 FAIL ..................................................................................MC-14
OIL FILT BPASS, L-R ..................................................................MC-14
MESSAGES AND ANNUNCIATIONS REVISION 24 (RE-ISSUE)
Page MC - 2 Mar 17/10
Quick Reference Handbook
Advisory (Blue) Messages and Annunciations Index
Message Page
PERF 1-2 FAIL ............................................................................ MC-14
PROG MSG 1-2 FAIL .................................................................. MC-14
PROG MSG 1-2 MISMATCH ...................................................... MC-14
RAD ALT 1-2 FAIL ...................................................................... MC-14
RECENTER TURN KNOB .......................................................... MC-14
RUDDER LIMIT ........................................................................... MC-14
RUDDER STRG OFF .................................................................. MC-14
SELECT INHIBIT ......................................................................... MC-15
SERVICE DOORS ...................................................................... MC-15
SG 1-2-3 FAIL ............................................................................. MC-15
SG 1-2-3 HOT ............................................................................. MC-15
SPD BRAKE EXTNDED.............................................................. MC-15
SPD BRAKE SWITCH................................................................. MC-15
T&L >80% FULL .......................................................................... MC-15
TCAS FAIL .................................................................................. MC-15
TERRAIN NOT AVAIL ................................................................. MC-15
TONE GEN FAIL ......................................................................... MC-16
TONE GEN 1-2 FAIL ................................................................... MC-16
UNDER FLOOR O’HEAT ............................................................ MC-16
VHF COMM 1-2-3 FL .................................................................. MC-17
VNAV TRACK CHANGE ............................................................. MC-17
VOICE REC FAIL ........................................................................ MC-17
VOR COURSE ............................................................................ MC-17
WS FAIL ...................................................................................... MC-17
WS UNAVAILABLE ..................................................................... MC-17
WING A / I, L-R ........................................................................... MC-17
Other Advisory Annunciations ..................................................... MC-18

REVISION 24 (RE-ISSUE) MESSAGES AND ANNUNCIATIONS

Mar 17/10 Page MC - 3
 Quick Reference Handbook
Advisory (Blue) Messages and Annunciations AFM 3B

Message: Cause(s): Corrective Action:

External power Remove external power before
AC EXT POWER is connected to taxiing.
airplane.
DC EXT POWER

AP CTLR SW Autopilot Try to pry stuck switch loose.

STUCK guidance panel
switch stuck in,
preventing
other
selections.
An attempt is Correct inhibiting situation and
AP ENGAGE
INHIBIT made to attempt re-engagement.
engage
autopilot under
any of following
conditions:
 Autopilot
disconnect
button active
 GA switch
active
 Airplane on
GND and
airspeed
less than 50
KCAS
 Stick shaker
is active
 TCS switch
active
 Trim up /
down switch
active
APU alternator Select AUX POWER switch ON.
APU ALT OFF is operating but
AUX POWER
switch is not
ON.

MESSAGES AND ANNUNCIATIONS REVISION 24 (RE-ISSUE)

Page MC - 4 Mar 17/10
Quick Reference Handbook
Advisory (Blue) Messages and Annunciations, ctd… AFM 3B

Message: Cause(s): Corrective Action:

APU Fault warning SPZ 8000-equipped airplanes

EXCEEDANCE computer having ASC 415B: message may
(FWC) has be caused by APU fire. Take
recorded an appropriate action and, if
exceedance. necessary, see APU Fire
procedure on ED-6. Recording
may be viewed by selecting
EXCEEDANCES on the
SYSTEMS menu of the Display
Controller.
SPZ 8000 having ASC 415B and
SPZ 8400: message may be
caused by APU RPM or EGT
exceedance. Verify APU auto shut
down and notify maintenance.
Recording may be viewed by
selecting EXCEEDANCES on the
SYSTEMS menu of the Display
Controller.
NOTE: For airplanes S/N 1000 and sub. with ASC 465, a nuisance “APU
EXCEEDANCE” message may occur on second APU start and then on
every other start, unless power is removed/interrupted from the fault
warning computer between starts. The “APU EXCEEDANCE” message
should be considered a nuisance message if cockpit overhead APU panel
and/or APU synoptic page indicate EGT and RPM parameters are within
normal limits.
Attempt is made Correct inhibiting situation and
AT ENGAGE
INHIBIT to engage auto- attempt re-engagement.
throttle under
any of following
conditions:
 A/T discon-
nect button
active
 A/T not armed
on flight
guidance
control panel
 Both engines
not running
 EPR below
1.17
 Isolation valve
open

REVISION 28 MESSAGES AND ANNUNCIATIONS

May 25/16 Page MC - 5
 Quick Reference Handbook
Advisory (Blue) Messages and Annunciations, ctd… AFM 3B

Message: Cause(s): Corrective Action:

Indicated 1. Check appropriate circuit
AT 1-2 FAIL autothrottle has breakers (A/T SERVO #1:
failed, CPO, C-9; A/T SERVO #2:
autothrottle will CPO, D-9.)
disconnect. 2. Select other A/T computer and
re-engage.
Airplane speed Disengage autothrottle and
AT NOT IN HOLD has exceeded manually adjust throttles to
60 KCAS with takeoff EPR.
autothrottle
engaged on
takeoff and
autothrottle
servos are not
in hold.
L (or R) battery 1. Monitor battery temperature
BATT WARM temp at or and select OFF if temperature
above 120° F. reaches 140° F.
Message active only if 2. Log for maintenance action.
optional Battery
Temperature Indicator
system is installed. May
be caution or advisory
message depending on
message module
programming.

BC 1-2-3 TEST BUS controller1. Verify power was applied to

FAIL power-up self BC's and FWCs in normal
test has failed. power-up sequence.
2. Full system capabilities are
maintained on a single BUS
controller.
NOTE: This message is only enabled on ground. BC test will fail if power is
momentarily removed from both FWCs after BC's are powered. If this
condition occurs, fail message can be cleared by reapplying airplane power
in normal power-up sequence or by pulling and resetting all 3 BUS
CONTROLLER circuit breakers (BUS CONT #1: CP, K-2; BUS CONT #2:
CP, L-2; BUS CONT #3: CP, M-2.)

MESSAGES AND ANNUNCIATIONS REVISION 28

Page MC - 6 May 25/16
Quick Reference Handbook
Advisory (Blue) Messages and Annunciations, ctd… AFM 3B

Message: Cause(s): Corrective Action:

BRAKE MAINT If message See Brakes / Anti-Skid (Brake-

REQ'D illuminates By-Wire) Index, page EB-1, for
following gear appropriate anti-skid off braking
(Brake-By-Wire: SN retraction and procedure.
1000 - 1213) extinguishes 5
seconds later,
the auto spin-
down feature
has failed.
If message 1. Notify maintenance to check for
BRAKE MAINT
REQ'D illuminates wheel speed sensor faults or
during takeoff possible dragging brake(s).
(HMAB: SN 1214 or landing 2. If message illuminates
AND SUBS) ground roll or momentarily with gear down
airborne with while airborne, no action
gear extended, required.
a wheel speed
sensor
miscompare
lasting more
than 5 seconds
has been
detected.
BUS CTLR 1-2-3 Indicated bus 1. Check circuit breakers.
FL controller has 2. Full system capabilities are
failed. maintained on a single bus
controller.
3. Cycle CB on failed bus
controller.
Toggled by Answer appropriate caller.
CALL SELCAL,
CABIN/LAV
call, Galley
/Interphone or
telephone.
FMS CDU Verify failure and if failed, use
CDU 1-2 FAIL failed. remaining FMS for navigation.

CHECKLIST Different check- Do not use checklist until correct

MISMATCH list installed in checklists are installed.
FWC 1 and
FWC 2.

REVISION 24 (RE-ISSUE) MESSAGES AND ANNUNCIATIONS

Mar 17/10 Page MC - 7
 Quick Reference Handbook
Advisory (Blue) Messages and Annunciations, ctd… AFM 3B

Message: Cause(s): Corrective Action:

Hydraulic sys- Proceed with flight and
CMB HYD HOT tem fluid temp- investigate after landing.
erature above
220°F (104°C).
Continuous 1. Select OFF if not required.
CONT IGN, L-R ignition is ON. 2. Observe duty cycle limitations
in GIV AFM Section 1,
(SPZ 8400 equipped) Limitations (also presented in
QRH section EC).
COWL A/I ON, L- Cowl anti-ice Turn OFF after exiting icing
R on. conditions.

CPL DATA Lateral or Check validity of coupled source.

INVALID vertical mode Reset appropriate lateral and/or
cannot be vertical mode.
selected or
canceled auto-
matically due to
invalid source
and / or invalid
required
sensors.
Message also
appears any-
time selected
course changes
by greater than
3° when in
LNAV / VOR,
except when
over station.
A DADC has 1. Verify failure and, if failed,
DADC 1-2 FAIL failed. select opposite DADC.
2. Verify DADC selection for
pressurization.

MESSAGES AND ANNUNCIATIONS REVISION 24 (RE-ISSUE)

Page MC - 8 Mar 17/10
Quick Reference Handbook
Advisory (Blue) Messages and Annunciations, ctd… AFM 3B

Message: Cause(s): Corrective Action:

DADC Priority FGC 1. Identify faulty DADC by

MISCOMPARE has detected reference to PFD, ND, standby
an unflagged flight instruments, guidance
miscompare panel, pressure control and
between DADC transponder panel.
1 and DADC 2. 2. Select good DADC to those
panels.
3. Isolate faulty DADC with CB:
(DADC #1: CP, F-3; DADC #2:
CP, G-3.)
4. Check message clear.
5. Re-engage yaw damper and
autopilot if desired.
See DADC Failures, page EA-
36.
DAU 1A-1B-2A- DAU channel Select alternate DAU channel.
2B FL has failed.

DAU 1-2 EICAS blue Compare blue messages

MISCMP-MSG message displayed with DAU 'A' and 'B'
miscompare channels. Select good channel.
between DAU
'A' and 'B'
channel.
DC CONFIG Disagreement Resolve configuration mismatch
MISMATCH between the 2 prior to takeoff. Cannot be
display resolved weight-off wheels.
(SPZ 8400 equipped) controllers’
configuration.
DISP CTLR 1-2 A display No action. Use remaining display
FAIL controller has controller where applicable.
failed.
DU 1-2-3-4-5-6 DU hot (266°F 1. Select DU OFF.
HOT [130°C]). 2. If message clears, select DU
ON.
3. If message returns, select DU
OFF and leave off for
remainder of flight.

REVISION 24 (RE-ISSUE) MESSAGES AND ANNUNCIATIONS

Mar 17/10 Page MC - 9
 Quick Reference Handbook
Advisory (Blue) Messages and Annunciations, ctd… AFM 3B

Message: Cause(s): Corrective Action:

E BATT 1-2-3*-4* Emergency 1. Ensure E BATT is not on.

DISCH battery is 2. If battery is not on, pull and
discharging. reset circuit breaker to attempt
(* if installed) to clear message (AFT EMER
BATT: P, I-13; FWD EMER
BATT: P, H-13.)
3. If message does not clear, no
further action is required.
4. Breaker should be left closed
and system rearmed as
required.
Self Turn off emergency battery.
E BATT 1-2-3*-4*
FAIL explanatory.

(* if installed)
Engine cowl Close door.
ENGINE COWL
OPEN door is open.

Fault warning 1. Check engine instruments.

ENGINE
EXCEEDANCE computer has 2. Reduce thrust by appropriate
recorded an engine(s) within limits.
(Deleted by ASC 415 exceedance. 3. May be caused by engine fire.
[SPZ 8000 airplanes])
4. Take appropriate action.
OR: 5. Recording may be viewed by
EXCEEDANCE selecting EXCEEDANCES on
RECORD SYSTEMS menu of display
controller.
(SPZ 8400 equipped)
DADC Verify status of DADC’s.
EPR 1 - DADC 2 malfunction has
caused
EPR 2 - DADC 1 remaining
DADC to
supply
information to
both EPR
systems.
External battery Turn external battery switch OFF.
EXT BATT
SWITCH ON switch on.

MESSAGES AND ANNUNCIATIONS REVISION 24 (RE-ISSUE)

Page MC - 10 Mar 17/10
Quick Reference Handbook
Advisory (Blue) Messages and Annunciations, ctd… AFM 3B

Message: Cause(s): Corrective Action:

A shift in 1. Check SENSOR page.
FGC 1-2 MASTER controlling FGC 2. Shift back to other FGC, if
has occurred: desired, or leave as is.
indicated FGC
has taken over.
Message times
out
automatically.
IRS data has 1. Check IRS condition / status on
FGC NOT USING
IRS 1-2 been rejected FMS IRS status page.
by FGC due to 2. System performance is same
unflagged with 1 or 2 IRS sources.
miscompare
between IRS
1/2 or flagged
IRS failure.
FGC SYSTEM Maintenance Turn off maintenance switch
TEST switch is on. located in each avionics rack.

Hydraulic 1. If flight system is hot and utility

FLT HYD HOT system fluid pressure is required, utility
temperature hydraulic pump switch must be
above 220° F set to ON.
(104° C). 2. If utility system is not required,
turn utility pump OFF.
FLIGHT REC Flight recorder 1. Check circuit breakers (CP, C-
FAIL has failed. It is 7, C-8, C-9.)
normal for this 2. Pull and reset if necessary.
message to be 3. Check FDR Ground
illuminated until Maintenance Override Switch
an engine is in right hand avionics bay to be
started and 10 in AUTO.
psi oil pressure 4. Check for FDAU and / or DFDR
is attained. fail annunciators and record for
maintenance.
FUEL INT TANK Fuel intertank Select fuel intertank OFF.
OPEN valve is open.

FUEL XFLOW Fuel crossflow Select fuel crossflow OFF.

OPEN is open.

REVISION 24 (RE-ISSUE) MESSAGES AND ANNUNCIATIONS

Mar 17/10 Page MC - 11
 Quick Reference Handbook
Advisory (Blue) Messages and Annunciations, ctd… AFM 3B

Message: Cause(s): Corrective Action:

Fault warning Select other FWC.
FWC 1-2 FAIL computer has
failed.

FWD EXT SW Forward Close door.

PNL OPN external switch
panel door is
open.
FWD LAV SVC Forward Close door.
DR OPN lavatory service
door is open.

GND SPOILER Ground spoilers Check switch; cycle to ARMED.

UNARM not armed.

Ground 1.Check GPWS circuit breaker:

GPWS FAIL Proximity EGPWS AC: CP, D-10 EGPWS
Warning DC: CP, E-10
System 2. Verify at least one radio
(GPWS) has altimeter is available.
failed.
Indicated IRS Verify failure on MSU panel and,
IRS 1-2 FAIL has failed. if being used, select another
sensor.
IRS 1-2 HI LAT IRS is in 1. Use IRS position with caution,
ALN alignment accuracy may be degraded.
status and 2. IRSs should be left in ALIGN
senses a mode for 15 minutes prior to
latitude above selecting NAV mode.
70°.
IRS FGC has 1. If there is no IRS MONITOR
MISCOMPARE detected an FAIL message, FGC will
unflagged automatically note either IRS 1
miscompare or IRS 2 and AP / YD will
fault between remain engaged.
IRS 1/2. 2. If there is IRS MONITOR FAIL
message present, the AP / YD
will automatically disconnect.
3. Re-engagement is possible
only after miscompare
condition is corrected.

MESSAGES AND ANNUNCIATIONS REVISION 24 (RE-ISSUE)

Page MC - 12 Mar 17/10
Quick Reference Handbook
Advisory (Blue) Messages and Annunciations, ctd… AFM 3B

Message: Cause(s): Corrective Action:

IRS MONITOR FGC has 1. AHRS / IRS 3 must be in NAV

FAIL detected failure mode when YD is engaged for
of comparison monitor test to pass.
monitor located 2. If message is present and
in AHRS / IRS unflagged IRS miscompare
3. occurs, AP / YD will
disconnect.
3. To eliminate message, switch
from current FGC to opposite
FGC and back, e.g., FGC 1 to
FGC 2 to FGC 1.
IRS 1-2 NAV Indicated IRS Select NAV on MSU panel
READY has completed selector.
alignment but
MSU panel
selector is still
in ALIGN.
Airplane AC 1. Check appropriate airplane AC
IRS 1-2 ON DC power supply power supply.
has failed. 2. IRS will continue to operate
normally.
ISOLATION VLV Isolation valve Select isolation valve CLOSED.
OPEN is open.

MAINT SWITCH Maintenance Select maintenance switch off

ON switch is on. (located in each avionics rack).

FGC has None. Switchover is automatic.

NAV MISCOMP
L-R SEL sensed
difference in NOTE: Message is active only in
navigation ILS dual coupled mode.
receiver
information and
selected a
single receiver
as NAV source.

REVISION 28 MESSAGES AND ANNUNCIATIONS

May 25/16 Page MC - 13
 Quick Reference Handbook
Advisory (Blue) Messages and Annunciations, ctd… AFM 3B

Message: Cause(s): Corrective Action:

Indicated 1. Check appropriate CB (CP: D-
NZ 1-2 FAIL navigation 8, E-8.)
computer has 2. Associated FMS CDU will be
failed. blank or display PERF INDEX.
OIL FILT BPASS, Engine oil filter 1. Monitor engine oil pressure.
L-R has clogged. 2. If pressure falls below limits,
see Engine Failure / Shut-
down In Flight, page EC-8.
Indicated 1. Check appropriate CB (CPO:
PERF 1-2 FAIL performance C-11, D-11.)
computer has 2. Performance information and
failed. autothrottle computer will not
be available.

PROG MSG 1-2 Programmable Notify maintenance for corrective

FAIL message action.
modules have
(SPZ 8400 equipped) failed.

PROG MSG 1-2 Programmable Notify maintenance for corrective

MISMATCH message action.
modules do not
(SPZ 8400 equipped) contain same
messages.
RAD ALT 1-2 Radar altimeter Select opposite radar altimeter.
FAIL has failed.

TURN knob is Re-center TURN knob.

RECENTER
TURN KNOB not centered.
Autopilot
cannot be
engaged.
Rudder None.
RUDDER LIMIT actuator torque
limiter is in
operation.
RUDDER STRG With ASC 302A None required if this is desired
OFF installed HAND mode. If not, select NORMAL
WHEEL ONLY mode.
is selected.

MESSAGES AND ANNUNCIATIONS REVISION 28

Page MC - 14 May 25/16
Quick Reference Handbook
Advisory (Blue) Messages and Annunciations, ctd… AFM 3B

Message: Cause(s): Corrective Action:

An attempt is Determine cause of FGC fault.
SELECT INHIBIT made to
manually select
invalid FGC.
One or more of Close service doors.
SERVICE DOORS service doors is
open.
Indicated Switch appropriate symbol
SG 1-2-3 FAIL symbol generator to "ALT" and
generator has momentarily select a different
failed. mode on the navigation display.
Symbol 1. Check avionics rack ventilation.
SG 1-2-3 HOT generator hot. 2. Select alternate symbol
generator and pull hot SG CB:
(SYM GEN #1: CP, K-3; SYM
GEN #2, CP, L-3; SYM GEN
#3, CP, M-3.)
Speed brakes Retract speed brakes.
SPD BRAKE
EXTNDED are extended.

FWC and FGC Check adjustment of speed brake

SPD BRAKE
SWITCH disagree on extended signal to DAU and FGC
position of at next maintenance opportunity.
speed brakes.
FWC memory Download and erase FWC
T&L >80% FULL is greater than memory at next convenient
80% full. maintenance period.
(Added by ASC 415 for
SPZ 8000 airplanes.)
Traffic Alert and 1. Check TCAS circuit breaker
TCAS FAIL Collision (TCAS: CP, D-11.)
Avoidance 2. Verify transponder and altitude
System (TCAS) reporting is selected ON.
has failed.
Terrain 1. Check circuit breakers:
TERRAIN NOT
AVAIL awareness is EGPWS AC: CP, D-10
not available. EGPWS DC: CP, E-10
2. Verify at least one (1) radio
altimeter is available.

REVISION 24 (RE-ISSUE) MESSAGES AND ANNUNCIATIONS

Mar 17/10 Page MC - 15
 Quick Reference Handbook
Advisory (Blue) Messages and Annunciations, ctd… AFM 3B

Message: Cause(s): Corrective Action:

Aural warning 1. Check circuit breakers.
TONE GEN FAIL tone generator 2. Reset if required.
OR: has failed. 3. Proceed with flight.
TONE GEN 1-2 4. No aural tones will be available.
FAIL
(SPZ 8400 equipped)
Bleed air leak 1. If wing anti-ice is on, select
UNDER FLOOR
O’HEAT detected under left wing OFF.
cabin floor. 2. If message persists, select
(SN 1280-1327 having right wing off.
ASC 415B and ASC 3. Wait 2 minutes.
395; SN 1328 and
subs.) 4. If message persists, depart
icing conditions.
5. If message extinguishes, re-
establish wing anti-ice using
the anti-ice switch which did
not cause the message to
extinguish.
6. If in doubt, depart icing
conditions.
7. Verify ISOLATION valve
closed.
8. Select left bleed OFF.
9. If message persists:
• Select left bleed ON and
right bleed OFF
• Check floor board
physically for temperature
10. If cool, no action.
11. If hot, descend to 15,000 ft.
or below and select left bleed
off and RAM AIR on.
NOTE: If the condition requires
that a SINGLE (L or R) ENG
BLEED be selected OFF,
descend to 41,000 ft. or below.
If above 41,000 ft. and ENG
BLEED is selected OFF, make
slow deliberate power lever
movements on the affected
engine.

MESSAGES AND ANNUNCIATIONS REVISION 24 (RE-ISSUE)

Page MC - 16 Mar 17/10
Quick Reference Handbook
Advisory (Blue) Messages and Annunciations, ctd… AFM 3B

Self explanatory. Check status of VHF radio.

VHF COMM 1-2-
3 FL

One minute prior No action.

VNAV TRACK
CHANGE to vertical
navigation track
change.
Self No action.
VOICE REC
FAIL explanatory.

Autopilot has If desired, course selector may

VOR COURSE sensed being now be changed more than 3°
over station without dropping LNAV
while coupled (VOR/TCN) mode.
to LNAV
(VOR/TCN).
Windshear 1. Check circuit breakers:
WS FAIL function of EGPWS AC: CP, D-10
GPWS has EGPWS DC: CP, E-10
failed. 2. Verify at least one (1) radio
altimeter is available.
Windshear 1. Check circuit breakers:
WS
UNAVAILABLE function of EGPWS AC: CP, D-10
GPWS not EGPWS DC: CP, E-10
available. 2. Verify at least one (1) radio
altimeter is available.
Wing anti-ice Turn OFF wing anti-ice after
WING A / I, L-R On. departing icing conditions.

REVISION 24 (RE-ISSUE) MESSAGES AND ANNUNCIATIONS

Mar 17/10 Page MC - 17
 Quick Reference Handbook
Advisory (Blue) Messages and Annunciations, ctd… OM 04-04-20

Annunciation: Cause(s):
"Single Chime" aural tone sounds. A new ADVISORY (blue) message is
displayed on CAS. The new
message will be displayed flashing
on the top of the ADVISORY
messages stack. The aural tone will
then automatically cease and
message will automatically revert to
steady display.
"Cricket" aural tone sounds. Airplane Overspeed
"Beep" aural tone sounds. Altitude Alert
LEFT/RIGHT WING WARM light Wing anti-ice plenum in wing leading
(blue) illuminated on overhead panel. edges has reached minimum opera-
ting temperature of 100° F (38° C).
EXT BATT SW light (blue) External battery switch on.
illuminated on overhead panel.
AC EXT PWR light (blue) illuminated AC external power applied.
on overhead panel.
DC EXT PWR light (blue) illuminated DC external power applied.
on overhead panel.
LEFT/RIGHT FRONT/SIDE Windshield heat operating.
WINDOW light (green) illuminated on
overhead panel.
REV ARM light (green) illuminated Parameters satisfied for thrust
above Display Unit (DU) 2 or 5. reverser deployment.
LH RR FAN FAIL light (blue) Left hand radio rack cooling fan has
illuminated on copilot's side panel. failed.
(1)
RH RR FAN FAIL light (blue) Right hand radio rack cooling fan has
illuminated on copilot's side panel. failed.
(1)
RH RR FAN AUTO light (blue) Right hand radio rack cooling fan
illuminated on copilot's side panel. operating automatically.
(1)
RH RR FAN MAN ON light (blue) Right hand radio rack cooling fan
illuminated on copilot's side panel. operating manually.
(1)
SPEED BRAKE handle illuminated SPEED BRAKE handle not in
(pale blue). RETRACT detent.
(1) SN 1156 and subs.

MESSAGES AND ANNUNCIATIONS REVISION 24 (RE-ISSUE)

Page MC - 18 Mar 17/10
Quick Reference Handbook

Abnormal / Emergency Procedures Master Index

Avionics / Electrics / APU Index ............................... EA-1

Electrical Power System Diagram ................................................ EA-2
Alternator / Converter Failure - Dual ........................................ EA-3
Essential DC Bus Power Failure ............................................... EA-6
Electrical System - Battery Only Operation ............................. EA-7
Alternator / Converter Failure - Single.......................................... EA-8
Electrical Load Warning System - ELWS ..................................... EA-9
Flight With One Electrical System Inoperative ........................... EA-10
Operational Procedures With Converter / Alternator
Inoperative - ELWS Installed ................................................. EA-11
Bus Fault - AC or DC RESET Light On ...................................... EA-14
Battery or Battery Charger Failure ............................................. EA-21
Essential DC Bus On Battery Power .......................................... EA-21
Master Table Of Electrical Component Availability .................... EA-23
Components Powered By The Emergency Batteries ................. EA-26
APU Inflight Operation - Alternate Electrical Source .................. EA-27
APU Inflight Operation - ELWS (Loadmeter) /
ASC 420 Procedures .............................................................. EA-28
APU Alternator Failure ............................................................... EA-30
Suspected Erroneous / Unreliable Airspeed Indications ..... EA-30
Display Unit Failure .................................................................... EA-33
Symbol Generator Failure .......................................................... EA-35
Traffic and Collision Avoidance System (TCAS) Failure ............ EA-35
Enhanced Ground Proximity Warning Sys. (EGPWS) Failure ..... EA-36
DADC Failures ........................................................................... EA-36

REVISION 26 ABNORMAL / EMERGENCY PROCEDURES

Oct 5 2011 Page E - i
 Quick Reference Handbook
Brakes / Anti-Skid (Brake By Wire) Index .................EB-1
Hydraulic System Diagram .......................................................... EB-2
Emergency Brakes (Brake-By-Wire) ........................................ EB-3
Wheel Brake Failure (Brake-By-Wire).......................................... EB-3
Brake Confidence Check - Inflight (Brake-By-Wire) .................... EB-4
Uncommanded Applied Brake Pressure -
Inflight (Brake-By-Wire)............................................................. EB-4
Landing With Applied Brake Pressure
Indicated (Brake-By-Wire) ........................................................ EB-6
Uncommanded Brake Pressure During Landing
Rollout (Brake-By-Wire) .............................................................EB-6
BRAKE FAIL Message (Brake-By-Wire) .......................................EB-8
BRAKE PEDAL Message (Brake-By-Wire) ..................................EB-8
Multiple Brake Failure Messages (Brake-By-Wire) .......................EB-9
BTMS OVHT Light On or BRAKE OVHT
Message (Brake-By-Wire) .......................................................EB-11
Anti-Skid Failure (Brake-By-Wire) .............................................. EB-13
Anti-Skid Off Braking (Brake-By-Wire: Without ASC 190/266) ..... EB-14
Anti-Skid Off Braking (Brake-By-Wire: With ASC 190/266) ....... EB-15

Brakes / Anti-Skid (HMAB) Index ..............................EB-1

Hydraulic System Diagram .......................................................... EB-2
Emergency Brakes (HMAB) ...................................................... EB-3
Wheel Brake Failure (HMAB) ....................................................... EB-3
Auxiliary Braking (HMAB) .............................................................EB-4
BRAKE FAIL Message (HMAB) ....................................................EB-4
BRAKE MAINT REQ’D Message (HMAB) ....................................EB-5
BTMS OVHT Light On or BRAKE OVHT Message (HMAB) ........EB-5
Anti-Skid Failure (HMAB) ............................................................. EB-7
Anti-Skid Off Braking (HMAB) ...................................................... EB-8

ABNORMAL / EMERGENCY PROCEDURES REVISION 26

Page E - ii Oct 5 2011
Quick Reference Handbook
Engines Index ............................................................ EC-1
Engine Failure Below V1 ............................................................ EC-2
Engine Failure Above V1 ........................................................... EC-3
Dual Engine Flameout................................................................ EC-5
Dual Engine Out Speeds For Maximum Range ....................... EC-7
Dual Engine Out Approach and Landing ................................. EC-7
Engine Failure / Shutdown In Flight ......................................... EC-8
Engine Out Driftdown – ISA, 76,000 to 58,000 pounds......... EC-10
Engine Out Driftdown – ISA, 56,000 to 38,000 pounds......... EC-11
Airstart - Immediate.................................................................. EC-12
Airstart - Normal ....................................................................... EC-12
One (1) Engine Inoperative Landing Procedure .................... EC-14
One (1) Engine Inoperative Go-Around Procedure ............... EC-14
Reverse Thrust Unlock or Deploy During Takeoff ................ EC-15
Reverse Thrust Unlock or Deploy During Flight ................... EC-16
Reverse Thrust Unlock Light Illuminated On The Ground... EC-17
Thrust Reverser Locking Procedure .......................................... EC-17
Engine Synchronizer Failure ...................................................... EC-18
Approach Idle System Failure .................................................... EC-19
Engine Vibration ......................................................................... EC-19
Ice Shedding Procedure ............................................................. EC-20
Engine Failure To Start .............................................................. EC-20
Start Valve Failure ...................................................................... EC-21
Start Valve Open (SVO) Indication In Flight .............................. EC-22
Hot Start ..................................................................................... EC-23
Continuous (Airstart) Ignition Limitations ................................... EC-23
Airstart Envelope ........................................................................ EC-24

REVISION 28 ABNORMAL / EMERGENCY PROCEDURES

May 25/16 Page E - iii
 Quick Reference Handbook
Fire / Overheat / Smoke Index ................................... ED-1
Fire Extinguishing System Diagram ............................................. ED-2
Engine Fire In Flight .................................................................. ED-3
Engine Fire On Ground ............................................................. ED-5
APU Fire ...................................................................................... ED-6
Airplane Interior Fire / Smoke / Fumes .................................... ED-7
Fire / Smoke / Fumes in Cockpit, Cabin, or Baggage
Compartment ........................................................................ ED-8
Smoke From Air Conditioning Outlets ................................. ED-9
Electrical Fire / Smoke Source Unknown ........................... ED-10
Smoke and Fumes Evacuation............................................ ED-12
Engine Fire Warning System Malfunction ............................. ED-13
Tailpipe Fire .............................................................................. ED-14
Fire Detection System Fault ....................................................... ED-14
Engine Hot ................................................................................ ED-15
Pylon Hot .................................................................................. ED-15
Aft Equipment Hot.................................................................... ED-16
Converter Overheat ................................................................. ED-17
Alternator Overheat ................................................................. ED-17
Under Floor Overheat ................................................................ ED-18

Flight Controls / Autoflight Index.............................. EE-1

Hydraulic System Diagram .......................................................... EE-2
General Guidance .......................................................................EE-3
Flight Controls Runaway To Hardover Position ......................EE-3
Immovable Flight Controls .........................................................EE-4
Stall Barrier Malfunction ............................................................EE-6
Ground Spoiler Failure ...............................................................EE-7

ABNORMAL / EMERGENCY PROCEDURES REVISION 28

Page E - iv May 25/16
Quick Reference Handbook
Flight Controls / Autoflight Index, ctd…
Runaway Electric Pitch Trim ........................................................ EE-7
Frozen Pitch Trim ......................................................................... EE-8
Failure of Stabilizer / Flap Interconnect........................................ EE-9
Flaps - Alternate Operation ........................................................ EE-10
Partial or Jammed Flaps Landings ............................................. EE-11
Uncommanded Flap Movement ................................................. EE-11
Flaps Lock Up While Moving / Fail To Move .............................. EE-12
Autopilot Malfunction .................................................................. EE-12
Autothrottle Malfunction ............................................................. EE-13
AFGCS Failure ........................................................................... EE-13
Mach Trim Compensation Failure .............................................. EE-13
Yaw Damper Failure................................................................... EE-14
Fuel / Hydraulics Index............................................... EF-1
Hydraulic System Diagram ........................................................... EF-2
Fuel System Diagram ................................................................... EF-3
Dual Hydraulic System Failure ................................................. EF-4
Combined Hydraulic System and Auxiliary Hydraulic System
Loss of Fluid ............................................................................... EF-6
Combined Hydraulic System Failure – Loss of Pressure and Fluid .....
..................................................................................................... EF-8
Combined Hydraulic System Failure – Loss of Pressure Only .. EF-10
Flight Hydraulic System Failure – Loss of Pressure and / or Fluid ......
................................................................................................ EF-11
Landing With Standby Electrical Power System Operating ....... EF-12
Master Table Of Hydraulic Component Availability .................... EF-13
Fuel Leak In Flight .................................................................... EF-14
Fuel Boost Pump Failure ............................................................ EF-17
Failure of Two Boost Pumps on One Side ................................. EF-18
Permissible Fuel Imbalance for All Flight Operations ................ EF-19

REVISION 29.1 ABNORMAL / EMERGENCY PROCEDURES

Aug 07/17 Page E - v
 Quick Reference Handbook
Landing Gear Index ................................................... EG-1
Hydraulic System Diagram .......................................................... EG-2
Abnormal Gear Condition - Emergency Landing ................... EG-3
Landing Gear Failure To Retract ................................................. EG-5
Landing Gear Failure To Extend .................................................. EG-6
Landing Gear Retraction Following Alternate Extension ............. EG-7
Nose Wheel Steering Failure ....................................................... EG-8
Nutcracker System Fails To Shift To Ground Mode At
Touchdown ............................................................................... EG-9
Nutcracker System Fails To Shift To Air Mode At Takeoff ........ EG-10
‘G’ Monitor System ..................................................................... EG-11
‘G’ Monitor Versus Airplane Gross Weight Charts ..................... EG-12

Pneumatics / ECS Index ............................................ EH-1

Bleed Air / ECS System Diagram ................................................ EH-2
Loss of Pressurization .............................................................. EH-3
Emergency Descent Procedure ................................................ EH-4
Loss of Automatic Pressurization Control .................................... EH-6
Pressurization System - Rate Limiting ......................................... EH-7
Bleed Air System Failure ............................................................. EH-8
Unpressurized Flight .................................................................. EH-10
Air Conditioning System Shut Down or Inoperative ................... EH-10
Air Conditioning System Airflow Hot or Uncontrollable .............. EH-11
Left or Right Cooling Turbine Hot .............................................. EH-11
Oxygen System Quantity Shortage............................................ EH-13

ABNORMAL / EMERGENCY PROCEDURES REVISION 29.1

Page E - vi Aug 07/17
Quick Reference Handbook
Miscellaneous Index .................................................... EI-1
Windshield Failure ....................................................................... EI-2
Cabin Window Cracked ............................................................... EI-3
Overweight Landing ..................................................................... EI-3
Ditching ......................................................................................... EI-4
Immediate Return for Landing .................................................... EI-6
Main Entrance Door Not Secure .................................................... EI-6
Planned Airplane Evacuation ......................................................... EI-7

REVISION 26 ABNORMAL / EMERGENCY PROCEDURES

Oct 5 2011 Page E - vii
 Quick Reference Handbook
General Guidance AFM 4-00-10

Should any emergency occur, the following shall apply:

1. Maintain control of the airplane.
2. Other than retracting the landing gear and silencing aural
warnings, take no action until above 400 ft. AGL.
3. Analyze the situation and take appropriate action. Resetting
“popped” circuit breakers is not recommended unless the affected
system is required for continued safe flight and landing.
4. Land as soon as conditions permit.

Circuit breaker location is identified using the following acronyms:

• P - Pilot's Circuit Breaker Panel (Behind Seat)
• CP - Copilot's Circuit Breaker Panel (Behind Seat)
• PO - Pilot's Overhead Circuit Breaker Panel
• CPO - Copilot's Overhead Circuit Breaker Panel
Both Abnormal and Emergency Procedures are combined in this
chapter and are presented by system or event. To differentiate
between the type of procedure, Emergency Procedure titles have a
red border; Abnormal Procedure titles have an amber border. When
possible, Emergency Procedures will be presented before Abnormal
Procedures within each section.

ABNORMAL / EMERGENCY PROCEDURES REVISION 26

Page E - viii Oct 5 2011
Quick Reference Handbook
Avionics / Electrics / APU Index
Electrical Power System Diagram ................................................ EA-2
Alternator / Converter Failure - Dual ........................................ EA-3
Essential DC Bus Power Failure ............................................... EA-6
Electrical System - Battery Only Operation ............................. EA-7
Alternator / Converter Failure - Single.......................................... EA-8
Electrical Load Warning System - ELWS ..................................... EA-9
Flight With One Electrical System Inoperative ........................... EA-10
Operational Procedures With Converter / Alternator
Inoperative - ELWS Installed ................................................. EA-11
Bus Fault - AC or DC RESET Light On ...................................... EA-14
Battery or Battery Charger Failure ............................................. EA-21
Essential DC Bus On Battery Power .......................................... EA-21
Master Table Of Electrical Component Availability .................... EA-23
Components Powered By The Emergency Batteries ................. EA-26

APU Inflight Operation - Alternate Electrical Source .................. EA-27

APU Inflight Operation - ELWS (Loadmeter) /
ASC 420 Procedures .............................................................. EA-28
APU Alternator Failure ............................................................... EA-30
Suspected Erroneous / Unreliable Airspeed Indications ..... EA-30
Display Unit Failure .................................................................... EA-33
Symbol Generator Failure .......................................................... EA-35
Traffic and Collision Avoidance System (TCAS) Failure ............ EA-35
Enhanced Ground Proximity Warning Sys. (EGPWS) Failure ..... EA-36
DADC Failures ........................................................................... EA-36
Related Topics In QRH
Airplane Interior Fire / Smoke / Fumes .................................... ED-7
Landing With Standby Electrical Power System Operating .......... EF-12
Circuit Breakers Listed By Bus and Group ................................... S-13
Alphabetical List of Circuit Breakers ............................................. S-31
Battery Charging Using APU or External AC Power .................... NG-6

REVISION 26 ABNORMAL / EMERGENCY PROCEDURES

Oct 5 2011 Page EA - 1
 Quick Reference Handbook
Electrical Power System Diagram

EXT AC
L AUX AC APU R
ALT ALT ALT

L CONV R CONV
LAC 2 RAC 2
DC AC AC DC

LAC 1 RAC 1
AC ESS 1
L MAIN AC R MAIN AC

AC ESS 2 E
INV
E INV
ON RLY
ESS AC
TRU 1

STBY GEN AC DC
ABEX
AC PWR RLY

HYD
TRU
SYS
AUX DC
EXT
DC

LDC 2 RDC 2

LDC 1 RDC 1
DC ESS 1
L MAIN DC R MAIN DC

DC ESS 2

ESS DC
NO. 1 NO. 2
BATTERY BATTERY
NO. 1 BATT TIE NO. 2
BATT BUS BUS BATT BUS
NO. 1 BATT BATT NO. 2
CHGR CHGR CONT CONT CHGR CHGR
CONT RLY RLY CONT
RLY RLY

ABNORMAL / EMERGENCY PROCEDURES REVISION 26

Page EA - 2 Oct 5 2011
Quick Reference Handbook
Alternator / Converter Failure - Dual AFM 4-07-10

After verifying that neither Alternator / Converter can be regained

by use of "Alternator / Converter Failure - Single" checklist
proceed as follows:
1. Crossflow ............................................................................... OPEN
2. Fuel Boost Pump (One Main only) ........ ON (ALL OTHERS - OFF)
3. L or R FUEL PRESS LOW Messages ..................... CHECK / OUT
If combined hydraulic pressure and the Standby Electrical Power
system are available, proceed as follows. If not, proceed to Step
13.
NOTE: Approximately twenty (20) minutes of electrical power is available if
both batteries are fully charged and Standby Electrical Power System cannot
be used.
4. AC / DC RESET Switches ..................................................... PUSH
If no Help:
5. All Normal Electrical Power Sources (except batteries) ........... OFF
6. Standby Electrical Power Switch ................................................ ON
7. Standby Electrical E-INVERT Switch ......................................... ON
8. Standby Electrical TRU Switch ................................................... ON
9. Emergency Battery Switch ...................................................... ARM
CAUTION: UNLOAD ELECTRICAL SYSTEM TO STAY AT OR
UNDER 100% AC AND DC POWER AS INDICATED ON STANDBY
ELECTRICAL POWER PANEL. TURN OFF DC ITEMS IF AC
PERCENTAGE IS OVERRANGE, AND VICE VERSA.
NOTE: Speed Brakes may be used, however, operation should be slow
(approximately five [5] seconds for full range movement).
10. Utility Pump .................................................. OFF / AS REQUIRED
NOTE: The Utility Pump, if left in the ARM position, will run continuously.
If both FGCs indicate FAILED, to regain FGC 1:
11. FGC 1 and 2 Circuit Breakers (CPO: A-7, B-7) ...................... PULL
12. FGC 1 Circuit Breaker Only (CPO: A-7) .............................. RESET

Continued on next page 

REVISION 28 ABNORMAL / EMERGENCY PROCEDURES

May 25/16 Page EA - 3
 Quick Reference Handbook
Alternator / Converter Failure – Dual, ctd… AFM 4-07-10

NOTE: The Standby Electrical Power system is powered by a hydraulically

driven motor and is therefore sensitive to hydraulic pressure changes. As long
as the limitations in GIV AFM Section 1 are observed, the Standby Electrical
Power system should operate normally. If the system drops off line, as result of
hydraulic pressure transients, it will be necessary to cycle Standby Electrical
Power switch from ON to OFF and back to ON.
NOTE: The Standby Electrical monitor panel indicates percent power from the
source. The airplane subsystem takes standby AC power and converts it to DC
through the TRU. Standby DC power is converted through the "E" inverter to
AC power. Thus, airplane DC load is displayed on standby AC load monitor
and airplane AC load is displayed on the standby DC load monitor. When
operating on the standby system, electrical load (both AC and DC ) should be
reduced to less than 100% on the standby monitor panel to avoid excessive
use of battery power.
All essential AC and DC Bus-powered equipment is available when
using Standby Electrical Power System. Among the items available:
Pilot's PFD Standby Engine Instruments
DU 3 (SG 2 and 3 - ALT) Standby Warning Panel
COMM No. 1 (or No. 3, as bused) Standby Fuel Qty Indicator
NAV No. 1 and DME No. 1 Wing / Cowl Anti-ice
ADF No. 1 Pressurization
ATC No. 1 (Transponder) Cockpit / Cabin Temp Control
(SN 1120 & subs. and airplanes with ASC 170)
Display Controller No. 1 Main Fuel Boost Pumps
FMS No. 1 and IRS No. 1 Cross Flow Valve
Both DBDIs Intertank Valve
Both Clocks Tone Generator
ISDU (or 3rd Nav Unit) Pilot's and Standby Pitot Heat
DADC No. 1 Air Start Ignition
FGC-1 (Turn Knob Inop) Fire Detection / Protection
Flight Director Both FWCs (FWC 1 only: SPZ 8000 airplanes)
Pitch Trim AOA No. 1
Yaw Damper Aux Hydraulic Pump
All Bus Controllers Flaps and Flap / Stab Indicator
Left Windshield Wiper

Upon descent for approach and landing, replace Standby

Electrical Power with APU/Auxiliary Power, when altitude permits,
as follows:
NOTE: Normal hydraulic landing gear operation and landing with the
standby electrical power system as a source of electrical power is
approved as long as the auto ground spoilers and thrust reversers are
NOT used. See Landing With Standby Electrical Power System
Operating, page EF-12.

Continued on next page 

ABNORMAL / EMERGENCY PROCEDURES REVISION 28

Page EA - 4 May 25/16
Quick Reference Handbook
Alternator / Converter Failure – Dual, ctd… AFM 4-07-10

13. Descend to 15,000 ft. or lower; slow to a maximum speed of 250

KCAS.
NOTE: To ensure sufficient battery strength, it is recommended that
descent to 15,000 ft. and start of the APU be accomplished within ten
(10) minutes, if the Standby Electrical Power system cannot be used
during the descent.
14. APU Fire Warning ................................................................CHECK
15. APU Master ................................................................................ ON
16. APU Oil Press Light .................................................................... ON
17. APU Start Button ................................................................... PUSH
CAUTION: A MAXIMUM OF TWO (2) THIRTY (30) SECOND APU
START ATTEMPTS WILL ENSURE TWENTY (20) MINUTES OF
BATTERY-ONLY OPERATION. ADDITIONAL START ATTEMPTS WILL
REDUCE BATTERY-ONLY OPERATING TIME. IF UNABLE TO START
APU AND STANDBY ELECTRICAL POWER SYSTEM IS NOT
AVAILABLE, SEE ELECTRICAL SYSTEM - BATTERY ONLY
OPERATION, PAGE EA-7.
CAUTION: IF APU CANNOT BE STARTED OR APU ALTERNATOR
CANNOT BE USED TO POWER THE BUSES, REMAIN ON STANDBY
ELECTRICAL POWER THROUGHOUT DESCENT AND APPROACH.
DO NOT CONTINUE CHECKLIST. AT CREW’S DISCRETION, THE
LANDING MAY BE ACCOMPLISHED BY TURNING OFF STANDBY
ELECTRICAL POWER AND USING BATTERY POWER ONLY FOR
LANDING OR THE CREW MAY ELECT TO LAND WITH STANDBY
ELECTRICAL POWER OPERATING.
NOTE: For airplanes having ASC 465 (36-150[G] APU), it is acceptable
for the APU EGT synoptic indication to go into the amber or red range
during start. The synoptic indication only reflects running limitations.
18. Auxiliary Power ........................................................................... ON
19. Essential AC Bus AUTO Switch ............................................ PUSH
20. Standby Electrical Power E-INVERT Switch ............................ OFF
21. Essential DC Bus AUTO Switch ............................................ PUSH
22. Standby Electrical Power TRU Switch ..................................... OFF
23. EPMP Auxiliary AC and DC Percent Loads ........................CHECK
24. Fuel Boost Pumps (Both MAINS) ............................................... ON
25. Crossflow .......................................................................... CLOSED
Continued on next page 

REVISION 28 ABNORMAL / EMERGENCY PROCEDURES

May 25/16 Page EA - 5
 Quick Reference Handbook
Alternator / Converter Failure – Dual, ctd… AFM 4-07-10

26. Standby Electrical Power Switch .............................................. OFF

NOTE: If the 100% load limit is exceeded on the APU alternator
(AUX PWR on the EPMP) or on the transformer-rectifier (AUX PWR
on EPMP), turn off equipment as required to bring loads within limits.
See the appropriate APU procedure in this section.
27. Utility Pump ................................................. ARM / AS REQUIRED

END

Essential DC Bus Power Failure AFM 4-07-20

NOTE: Steps 1 thru 4 cause DU 2 to be unpowered, DU 6 to Red X and

the copilots PFD to automatically transfer to DU 5 (SPZ 8400 only).
Selecting NORM-ALT-ALT on the SG reversionary panel will restore the
copilot's displays to normal. DU 2 will remain unpowered for remainder of
flight.
1. Essential DC Bus Power Source............................................ BATT
2. L / R MAIN DC SENSE CBs (P: H-14, I-14)........................... PULL
3. Standby Electrical Power Switch ................................................ ON
4. Standby Electrical Power TRU Switch ....................................... ON
5. Battery Ammeters............................................................................
.... MONITOR FOR INDICATION AND LOAD-SHED IF REQUIRED
For Approach and Landing:
NOTE: If standby electrical power is interrupted during the following
steps, cycle Standby Electrical Power switch OFF then ON.
6. Gear Handle ......................................................................... DOWN
7. Flaps ................................................................ SET FOR LANDING
8. Emergency Batteries .................................................................. ON
9. Ground Spoilers ....................................................................... OFF
10. HP RPM.............. MAINTAIN 67% HP RPM UNTIL TOUCHDOWN
NOTE: Once the airplane is on the ground, there is no need to continue
to maintain 67% HP RPM. The standby electrical system will stay on line
during normal taxi maneuvers. If standby electrical power is interrupted,
cycle the Standby Electrical Power Switch OFF then ON to regain power.
Continued on next page 
ABNORMAL / EMERGENCY PROCEDURES REVISION 28
Page EA - 6 May 25/16
Quick Reference Handbook
Essential DC Bus Power Failure, ctd… AFM 4-07-20

11. Reverse Thrust .......................................................... DO NOT USE

On touchdown:
12. Flight Spoilers ............................................... MANUALLY DEPLOY
AT A SLOW RATE (APPROXIMATELY 5 SECONDS)
13. Normal Braking ..................................... USE TO STOP AIRPLANE

END

Electrical System - Battery Only Operation AFM 4-07-30

CAUTION: WHEN ANY ELECTRICAL CONDITION REQUIRES

OPERATION ON BATTERIES ONLY, LAND AT NEAREST SUITABLE
AIRPORT.
1. Essential DC Bus Battery Switch ............................................... ON
2. Battery 1 and 2 Switches ............................................................ ON
3. Crossflow ............................................................................... OPEN
4. Fuel Boost Pumps (One Main Only) ...... ON (ALL OTHERS - OFF)
5. L or R FUEL PRES LOW Message ......................... CHECK / OUT
CAUTION: IMMEDIATE DESCENT TO APU START ENVELOPE
(15,000 FT / 250 KCAS) SHOULD BE INITIATED. ATTEMPT MAXIMUM
OF TWO (2) THIRTY (30) SECOND APU START ATTEMPTS. IF APU
START IS UNSUCCESSFUL, MAINTAIN 15,000 FT MSL OR BELOW
(MSA PERMITTING) AND TURN OFF LAST FUEL BOOST PUMP.
6. Left Power, Right Power and Auxiliary Power .......................... OFF
7. All Non-Essential Items ............................................................ OFF
NOTE: Two (2) DUs will be powered with batteries only. Consideration
should be given to turning one or both OFF if the situation permits .
8. Utility Pump .................................................... OFF/AS REQUIRED
NOTE: The utility pump, if left in the ARM position, will run continuously
when only battery essential power is available to airplane .

END

REVISION 24 (RE-ISSUE) ABNORMAL / EMERGENCY PROCEDURES

Mar 17/10 Page EA - 7
 Quick Reference Handbook
Alternator / Converter Failure - Single AFM 3-07-40

1. Appropriate Converter AC and DC Loads/Voltage ............. CHECK

2. Electric Master LEFT or RIGHT Power ...........................................
.........................................................................................................
OFF, WAIT TEN (10) SECONDS THEN ON
If voltage is produced, automatic transfer back to this source will
occur.
If voltage is not produced or reading is unusual, or if converter
trips off again:
3. Electric Master LEFT or RIGHT Power ...........................................
.........................................................................................................
OFF FOR REMAINDER OF FLIGHT
If below 15,000 ft., it is recommended that the APU be started as
source of supplemental electrical power. See APU Inflight Operation
– Alternate Electrical Source, page EA-27.
Failure of a portion of a converter may be indicated by one or more
failure messages as follows:
• L AC POWER FAIL • L DC POWER FAIL
• R AC POWER FAIL • R DC POWER FAIL
If any one of these failure messages illuminate, proceed as
follows:
1. Appropriate Converter AC and DC Loads/Voltage ............. CHECK
2. Electric Master LEFT or RIGHT Power ...........................................
.........................................................................................................
OFF, WAIT TEN (10) SECONDS THEN ON
If voltage is produced, automatic transfer back to this source will
occur.
If DC voltage is not produced and L-R DC POWER FAIL
message remains, converter operation may be continued. If AC
voltage is not produced and L-R AC POWER FAIL message
remains, turn converter OFF.

END

ABNORMAL / EMERGENCY PROCEDURES REVISION 24 (RE-ISSUE)

Page EA - 8 Mar 17/10
Quick Reference Handbook
Electrical Load Warning System - ELWS AFM 3-07-50

In the event APU electrical load is observed in low amber range,

proceed as follows:
1. CABIN MASTER ......................................................................... ON
If condition persists:
2. GALLEY MASTER ...................................................................... ON
In the event APU electrical load is observed in high amber range,
proceed as follows:
1. GALLEY MASTER .................................................................... OFF
If condition persists:
2. CABIN MASTER ....................................................................... OFF

END

REVISION 27 ABNORMAL / EMERGENCY PROCEDURES

Dec 10/12 Page EA - 9
 Quick Reference Handbook
Flight With One Electrical System Inoperative
AFM 3-07-60

APU Alternator Failure or APU Flameout:

1. Essential AC and DC buses will automatically transfer to operative
converter.
2. Main AC and DC buses powered by APU will be unpowered ..... at
time of failure due to configuration of EPMP bus switches.
3. Power to failed buses may be regained by selecting AUTO on
EPMP panel for those buses.
4. Remaining converter will be capable of powering airplane for
remainder of flight.
5. If APU has flamed out, the pilot may elect to descend to 15,000 ft.,
restart APU, return to cruise altitude, and monitor APU electrical
load.
6. Allow time during descent for windshield heat to defog windows.
Alternator / Converter Failure:
NOTE: GIV airplane SNs 1000 through 1155 without APU Cooling /
Venting Enhancements (ASC 390A, ASC 427 or ASC 470) or 36-150[G]
APU (ASC 465A) is limited to 30,000 ft.
1. Essential AC and DC buses will automatically transfer to APU
alternator and TRU.
2. Main AC and DC buses powered by Converter will be unpowered
at time of failure due to configuration of EPMP bus switches.
3. DO NOT attempt to repower failed buses by switching their power
source to APU unless airplane altitude is 35,000 ft. or less. APU
alternator is not capable of powering entire airplane above 35,000
ft.
4. On descent for approach and landing, power to failed buses may
be regained by Selecting AUTO on EPMP panel for those buses.
Accomplish this at or below 35,000 ft.
5. Allow time during descent for windshield heat to defog windows.

END

ABNORMAL / EMERGENCY PROCEDURES REVISION 27

Page EA - 10 Dec 10/12
Quick Reference Handbook
Operational Procedures With Converter / Alternator
Inoperative - ELWS Installed OM 09-03-60

THIS PROCEDURE IS TO BE USED IN ACCORDANCE WITH GIV

MMEL “M” AND “O” PROCEDURES.
For departure operations with one (1) converter / alternator
inoperative, complete the following steps:
After Starting Engines:
1. START MASTER ...................................................................... OFF
If LEFT converter / alternator is inoperative, complete Steps 2
through 7, omit Steps 8 through 13 and proceed to Step 14. If
RIGHT converter / alternator is inoperative, proceed to Step 8.
If LEFT converter / alternator is inoperative:
2. ELECTRICAL MASTER RIGHT PWR ........................................ ON
3. ELECTRICAL MASTER AUX PWR............................................ ON
4. LEFT MAIN AC APU / EXT .................. ON (MANUALLY SELECT)
5. R MAIN AC RIGHT ............................... ON (MANUALLY SELECT)
6. L MAIN DC TRU / EXT ......................... ON (MANUALLY SELECT)
7. R MAIN DC RIGHT ............................... ON (MANUALLY SELECT)
If RIGHT converter / alternator is inoperative:
8. ELECTRIC MASTER LEFT PWR............................................... ON
9. ELECTRIC MASTER AUX PWR ................................................ ON
10. LEFT MAIN AC LEFT ........................... ON (MANUALLY SELECT)
11. R MAIN AC APU / EXT ......................... ON (MANUALLY SELECT)
12. L MAIN DC LEFT .................................. ON (MANUALLY SELECT)
13. R MAIN DC TRU / EXT ........................ ON (MANUALLY SELECT)
For EITHER converter / alternator inoperative, proceed as follows:
14. ESS AC AUTO............................................................................ ON
15. ESS DC AUTO ........................................................................... ON

Continued on next page 

REVISION 24 (RE-ISSUE) ABNORMAL / EMERGENCY PROCEDURES

Mar 17/10 Page EA - 11
 Quick Reference Handbook
Operational Procedures With Converter / Alternator Inoperative –
ELWS Installed, ctd… OM 09-03-60

16. APU Bleed Air .........................................................AS REQUIRED

17. Battery Ammeters................................................................ CHECK
18. Emergency Power ................................................................... ARM
19. Doors ................................................................................... CLOSE
20. Anti Ice Heaters .......................................................................... ON
21. Cowl / Wing Anti-Ice ................................ CHECK / AS REQUIRED
22 CABIN PRESSURE CONTROL ................................FLIGHT / SET
23. Fuel Boost Pumps / Crossflow Valve .......................... ON / CLOSE
24. Nose Wheel Steering ............................................................... OFF
25. Flight Controls ..................................................................... CHECK
26. Ground Spoilers .................................................................. CHECK
27. Stall Barrier ............................................................................. TEST
28. Yaw Damper ............................................................................... ON
29. ELWS Loadmeter ............... ON / CHECK LOAD IN GREEN BAND
30. Windshield Heat ................... OFF TWO (2) SECONDS, THEN ON
NOTE: ELWS FAIL light will illuminate momentarily while windshield
heat is being cycled.
31. Nose Wheel Steering ................................................................. ON
32. AUX Pump .......................................................................... ARMED
33. Brake Test Switch (BITE) .......................PRESS, THEN RELEASE
After Landing:
1. Ignition ...................................................................................... OFF
2. Transponder ................................................................... STANDBY
3. Flaps ...........................................................................AS DESIRED
4. ANTI ICE / Anti Ice Heaters...................................................... OFF
NOTE: ELWS CONFIG light will illuminate when windshield heat is
selected OFF.

Continued on next page 

ABNORMAL / EMERGENCY PROCEDURES REVISION 24 (RE-ISSUE)

Page EA - 12 Mar 17/10
Quick Reference Handbook
Operational Procedures With Converter / Alternator Inoperative -
ELWS Installed, ctd… OM 09-03-60

5. Fuel Boost Pumps .................................... OFF (ONE EACH SIDE)

NOTE: The amber (or red) APU LOAD light may illuminate when
fuel boost pumps are selected OFF. This is normal.
6. Landing Lights .......................................................................... OFF
7. Ground Spoilers ........................................................................ OFF
8. BTMS / OVHT Light .................................................. CHECK / OUT
For airplanes with Brake Temperature Monitoring System (BTMS)
installed.
NOTE: If landing required hard braking, monitor temperatures to
ensure brake temperatures have peaked and are decreasing.
9. Radar .............................................................................. STANDBY
Shutdown:
1. Parking Brake ............................................................................. ON
2. Emergency Power .................................................................... OFF
3. Radar ........................................................................................ OFF
4. ELWS Loadmeter ..................................................................... OFF
5. EPMP Bus Switches (6) ........................................................ AUTO
6. ELECTRIC MASTER LEFT (or RIGHT) PWR .......................... OFF
7. HP Fuel Cocks ....................................................................... SHUT
8. TGT................................................................................. MONITOR
9. Radios....................................................................................... OFF
10. BTMS ............................................................ CHECK / LIGHT OUT
For airplanes with Brake Temperature Monitoring System (BTMS)
installed.
11. IRSs .......................................................................................... OFF
12. Exterior Lights ......................................................... AS REQUIRED
13. Fuel Boost Pumps .................................................................... OFF
14. Cockpit Lights ............................................................ AS DESIRED
15. Oxygen ..................................................................................... OFF
Continued on next page 

REVISION 24 (RE-ISSUE) ABNORMAL / EMERGENCY PROCEDURES

Mar 17/10 Page EA - 13
 Quick Reference Handbook
Operational Procedures With Converter / Alternator Inoperative -
ELWS Installed, ctd… OM 09-03-60

16. Display Units ............................................................................ OFF

17. ELECTRIC MASTER AUX PWR .............................................. OFF
18. APU ............................................................... OVERSPEED / TEST
19. Standby Attitude Indicator ...................................................CAGED
20. APU MASTER Switch ............. OFF (APU RPM LESS THAN 10%)
NOTE: (For airplanes having ASC 465 (36-150[G] APU)): the amber
APU MASTER WARN CAS message will not be displayed if the APU
MASTER switch is inadvertently left ON after shutdown.
21. BATT 1 / BATT 2 Switches....................................................... OFF
22. Gust Lock ................................................................................... ON
NOTE: Ensure hydraulic pressure is depleted prior to engaging gust
lock.
23. Chocks............................................................................. IN PLACE
24. Parking Brake ........................................................................... OFF

END

Bus Fault - AC or DC RESET Light On AFM 3-07-70

When RESET switchlight is pushed, one of three events will occur:

• RESET light will extinguish and remain out.
• RESET light will extinguish, the relevant BPCU will cycle the bus
through its possible power sources, then the RESET light will re-
illuminate.
• RESET light will not extinguish but, instead, remains illuminated.
Specific procedures for Essential DC Bus Fault, Essential AC Bus
Fault, Main AC Bus fault and Main DC Bus Fault follow in blue.
NOTE: The MASTER and RESET Switches should not be cycled more
than once every ten (10) seconds.

Continued on next page 

ABNORMAL / EMERGENCY PROCEDURES REVISION 24 (RE-ISSUE)

Page EA - 14 Mar 17/10
Quick Reference Handbook
Bus Fault - AC or DC RESET Light On, ctd… AFM 3-07-70

Essential DC Bus Fault Indicated:

ESS DC BUS

DC SEL ON
RESET AUTO
LEFT RIGHT
BATT
MAIN MAIN

ON ON

BATT 1 BATT 2

1. DC RESET Switchlight .......................................................... PUSH

If RESET light extinguishes and remains out:
A. Essential DC Bus AUTO Switchlight ....................... CHECK ON
B. Verify electrical power is on L MAIN DC bus (source light
illuminated) and Essential DC L MAIN switchlight is ON.
C. Voltage .............................MONITOR REMAINDER OF FLIGHT
2. If RESET light extinguishes momentarily while the bus cycles
through possible power sources, then re-illuminates:
A. Essential DC Bus BATT Switch ........................................ PUSH
B. ESSENTIAL DC BUS FEEDER Circuit Breakers (On PDB) ......
............................................................. PULL (ONE AT A TIME)
C. DC RESET Switchlight ...............................................................
....PUSH (ONCE, FOR EACH CIRCUIT BREAKER PULLED)
CAUTION: PULL ONLY ONE (1) CIRCUIT BREAKER AT A TIME
AND, IF PROBLEM CONTINUES, RESET CB BEFORE PULLING
THE NEXT CIRCUIT BREAKER.
D. After fault isolation, leave applicable feeder breaker pulled
(OPEN).
E. Essential DC Bus AUTO Switchlight ....................... CHECK ON
3. If RESET light remains illuminated:
A. Essential DC Bus Battery Switchlight ............................... PUSH
B. Battery Amperage ........................................................... CHECK
If the Main DC buses are powered, turn off both Main Boost
Pumps. If the Main DC busses are not powered, open
Crossflow and turn off Right Main Boost Pump.
If battery amperage exceeds negative three (-3) amps
discharge, consideration should be given to descending below
15,000 ft. and turning off all boost pumps to conserve battery
life.
Continued on next page 

REVISION 24 (RE-ISSUE) ABNORMAL / EMERGENCY PROCEDURES

Mar 17/10 Page EA - 15
 Quick Reference Handbook
Bus Fault - AC or DC RESET Light On, ctd… AFM 3-07-70
Essential AC Bus Fault Indicated:
ESS AC BUS

AC SEL ON
RESET AUTO
LEFT RIGHT E
MAIN MAIN INV

1. AC RESET Switchlight ............................................................ PUSH

If RESET light extinguishes and remains out:
A. Essential AC Bus AUTO Switchlight ......................... CHECK ON
B. Verify electrical power is on L MAIN AC BUS (source light
illuminated) and that Essential AC L MAIN switchlight is ON.
C. Monitor voltage and frequency for remainder of flight.
2. If RESET light extinguishes momentarily while the bus cycles
through possible power sources, then re-illuminates:
A. Essential AC Bus AUTO Switchlight ......................... CHECK ON
B. Check Essential AC bus voltage and frequency:
1) If indications are normal:
a. PILOT/COPILOT PHASE B and C CBs
("AC ESS" Section on PDB) ................................. PULL
b. AC RESET Switchlight......................................... PUSH
c. RESET PILOT/COPILOT PHASE B and C CBs one at
a time. Allow sufficient time for fault to reoccur. AC
RESET switchlight will illuminate.
d. After fault isolation, leave applicable circuit breaker
pulled (OPEN).
e. AC RESET Switchlight......................................... PUSH
2) If indications are abnormal (voltage and frequency drop):
a. Essential AC Bus E INV Switch .......................... PUSH
b. PILOT/COPILOT PHASE A and ACCESS CBs
(“AC ESS” Section on PDB) ................................. PULL

Continued on next page 

ABNORMAL / EMERGENCY PROCEDURES REVISION 24 (RE-ISSUE)

Page EA - 16 Mar 17/10
Quick Reference Handbook
Bus Fault - AC or DC RESET Light On, ctd… AFM 3-07-70
Essential AC Bus Fault Indicated, ctd…
c. Manual Pressurization ................................... SELECT
CAUTION: PULLING PILOT'S PHASE A CIRCUIT
BREAKER CAUSES LOSS OF AUTOMATIC PRESSUR-
IZATION CONTROL; ONLY MANUAL PRESSURIZATION
WILL BE AVAILABLE.
d. AC RESET Switchlight ....................................... PUSH
e. Reset PILOT/COPILOT PHASE A and ACCESS CBs
one at time. Allow sufficient time for fault to reoccur.
f. After fault isolation, leave applicable circuit breaker
pulled (OPEN).
g. Essential AC Bus AUTO Switchlight .................. PUSH
NOTE: If Pilot's Phase A is not the fault, reset
pressurization to AUTO.
3. If RESET light remains on:
A. Power .................. VERIFY AVAILABLE ON LEFT MAIN AC BUS
B. Essential AC Bus L Main Switchlight ................................ PUSH
C. AC RESET Switchlight ..................................................... PUSH
If AC RESET switchlight extinguishes, monitor voltage and
frequency for remainder of flight.
If AC RESET switchlight does NOT extinguish:
D. Power ............. VERIFY AVAILABLE ON RIGHT MAIN AC BUS
E. Essential AC Bus R Main Switchlight ............................... PUSH
F. AC RESET Switchlight ..................................................... PUSH
If AC RESET switchlight extinguishes, monitor voltage and
frequency for remainder of flight.
If AC RESET switchlight does NOT extinguish, continue:
G. Essential AC Bus E INV Switch ........................................ PUSH
H. Monitor voltage and frequency for remainder of flight.
NOTE: All B and C Phase Essential AC Bus power is not
available.

Continued on next page 

REVISION 24 (RE-ISSUE) ABNORMAL / EMERGENCY PROCEDURES

Mar 17/10 Page EA - 17
 Quick Reference Handbook
Bus Fault - AC or DC RESET Light On, ctd… AFM 3-07-70
Main AC Bus Fault Indicated:
ESS AC BUS

CHGR AC SEL ON
FAIL RESET AUTO
LEFT RIGHT E
MAIN MAIN INV

NOTE: With a MAIN AC BUS unpowered, the corresponding CHGR FAIL

warning light will illuminate.
If RIGHT MAIN AC BUS is unpowered:
1. Essential AC BUS ................................................................. AUTO
If LEFT MAIN AC BUS is unpowered:
1. Essential AC BUS RIGHT MAIN Switchlight ........................ PUSH
2. AC RESET Light.................................................................... PUSH
3. If RESET light extinguishes and power is restored to the bus:
A. If fault indication was the LEFT BUS, then:
Essential AC Bus AUTO Switchlight .................................. PUSH
B. Monitor loads for remainder of flight.
4. If RESET light extinguishes momentarily, while bus cycles
through available sources, then re-illuminates:
A. Relevant AC Main Feeder Circuit Breakers (PDB) ............PULL
B. AC RESET Switchlight ......................................................PUSH
C. RESET Main Feeder circuit breakers one at a time. Allow
sufficient time for fault to recur.
D. After fault isolation, then:
Applicable Circuit Breaker .................. LEAVE PULLED (OPEN)
E. AC RESET Switchlight ......................................................PUSH
F. If fault was the LEFT BUS, then:
Essential AC Bus AUTO Switchlight .................................PUSH
5. If RESET light remains ON:
A. Verify availability of power for failed bus by selecting Volt/Freq.
Meter to LEFT, RIGHT, and, if APU is running, AUX.
Continued on next page 

ABNORMAL / EMERGENCY PROCEDURES REVISION 24 (RE-ISSUE)

Page EA - 18 Mar 17/10
Quick Reference Handbook
Bus Fault - AC or DC RESET Light On, ctd… AFM 3-07-70
Main AC Bus Fault Indicated, ctd…
B. If failed bus is LEFT AC BUS, then:
As Available, LEFT MAIN, RIGHT MAIN, or AUX ............ PUSH
C. If failed bus is RIGHT AC BUS, then:
As Available, RIGHT MAIN, LEFT MAIN, or AUX ............ PUSH
D. AC RESET Switchlight ..................................................... PUSH
E. If RESET Switchlight extinguishes, then:
Loads ...................... MONITOR FOR REMAINDER OF FLIGHT
F. If RESET Switchlight remains ON, then:
Loss Of Equipment Powered By Dead Bus ...................... NOTE
Main DC Bus Fault Indicated:
ESS DC BUS

DC SEL ON
RESET AUTO
LEFT RIGHT
BATT
MAIN MAIN

If RIGHT MAIN DC BUS is unpowered:

1. Essential DC BUS ................................................................. AUTO
If LEFT MAIN DC BUS is unpowered:
1. Essential DC BUS RIGHT Switchlight .................................. PUSH
2. DC RESET Light ................................................................... PUSH
3. If RESET light extinguishes and power is restored to the bus:
A. If fault indication was LEFT BUS, then:
Essential DC Bus AUTO Switchlight .................................. PUSH
B. Monitor loads for remainder of flight.

Continued on next page 

REVISION 24 (RE-ISSUE) ABNORMAL / EMERGENCY PROCEDURES

Mar 17/10 Page EA - 19
 Quick Reference Handbook
Bus Fault - AC or DC RESET Light On, ctd… AFM 3-07-70
Main DC Bus Fault Indicated, ctd…
4. If RESET Light extinguishes momentarily, while the bus
cycles through available sources, then re-illuminates:
A. Relevant DC Main Feeder Circuit Breakers (PDB) ............PULL
B. DC RESET Switchlight ......................................................PUSH
C. RESET Main Feeder circuit breakers one at a time. Allow
sufficient time for fault to recur.
D. After fault isolation, then:
Applicable Circuit Breaker .................. LEAVE PULLED (OPEN)
E. DC RESET Switchlight ......................................................PUSH
F. If fault indication was LEFT BUS, then:
Essential DC Bus AUTO Switchlight .................................PUSH
5. If RESET Light remains ON:
A. Verify availability of power for faulty bus by selecting Volt/Freq.
Meter to LEFT, RIGHT; and, if APU is running, AUX.
B. If faulty bus is LEFT DC BUS, then:
As available, LEFT MAIN, TRU, or RIGHT MAIN .............PUSH
C. If faulty bus is RIGHT DC BUS, then:
As available, RIGHT MAIN, TRU, or LEFT MAIN .............PUSH
D. DC RESET Switchlight ......................................................PUSH
E. If RESET Switchlight extinguishes, then:
Loads ...................... MONITOR FOR REMAINDER OF FLIGHT
F. If RESET Switchlight remains ON, then:
Loss Of Equipment Powered By Dead Bus ......................NOTE

END

ABNORMAL / EMERGENCY PROCEDURES REVISION 24 (RE-ISSUE)

Page EA - 20 Mar 17/10
Quick Reference Handbook
Battery Or Battery Charger Failure AFM 3-07-80

CHGR FAIL warning light illuminated:

1. Appropriate Main AC Bus Power .........................................CHECK
2. Affected Battery Current/Voltage .................................... OBSERVE
If meter reading is abnormal:
3. BATT CHGR CB (PDB) .......................................................... PULL
CHRG FAIL warning light will remain ON.
4. After 3 - 5 minutes, BATT CHGR CB (PDB) ....................... RESET
If battery does not charge:
5. BATT CHGR CB (PDB) .......................................................... PULL
6. Battery Switch On Affected Side .............................................. OFF
NOTE: OFF only if battery is discharging. Re-instate if battery power is
required.

END

Essential DC Bus On Battery Power AFM 3-07-90

NOTE: If the ESS DC BUS AUTO, LEFT MAIN, and BATT switch capsules
are illuminated without the BATT 1 and 2 switches illuminated or the “BATT ON
BUS” message (SPZ 8400)/capsule (SPZ 8000) illuminated, the K20/K22 relay
experienced a failure of one of the two relay-poles. Report for maintenance
action.
If DC Reset Light is ON, see Bus Fault - AC Or DC RESET Light
On, page EA-14. If DC Reset Light is NOT ON:
1. Left and/or Right Main DC Bus ...................... VERIFY POWERED
A. If buses are not powered, determine reason and re-power
the buses.
B. If buses are powered, verify ESS DC Bus switch selection on
EPMP is AUTO.
C. DC Reset Switch ......................................................... PRESS
D. Hard select ESS DC to Left, then Right, then back to AUTO.
Pause between each step to determine if power to ESS DC
BUS is switched from BATT to either Left or Right Main Bus.
2. If EPMP switch selection is correct, check Battery Ammeters for
discharge.
Continued on next page 

REVISION 24 (RE-ISSUE) ABNORMAL / EMERGENCY PROCEDURES

Mar 17/10 Page EA - 21
 Quick Reference Handbook
Essential DC Bus On Battery Power, ctd… AFM 3-07-90

If Battery Ammeters indicate that batteries are discharging:

A. Load shed as necessary (one or both main boost pumps
may be sufficient).
CAUTION: DO NOT ATTEMPT TO START THE APU OR USE
THE AUX HYDRAULIC PUMP.
OR:
B. Power Source For ESS DC Bus ..................... SELECT BATT
C. L / R MAIN DC SENSE CBs (P: H-14, I-14) ...................PULL
D. Standby Electrical Power Switch ....................................... ON
E. Standby Electrical Power TRU Switch ............................... ON
F. Monitor Battery Ammeters. Load shed if required.
NOTE: Steps 2B thru 2F cause DU 2 to be unpowered, DU 6 to
RED X and copilot's PFD to auto-transfer to DU 5 (SPZ 8400 only).
Selecting NORM-ALT-ALT on SG reversionary panel will restore
the co-pilot's displays to normal. DU 2 will remain unpowered.
G. Maintain minimum of 67% HP RPM while in this configuration.
H. For Approach and Landing:
NOTE: The crew may elect to land with "batteries only" powering
the essential bus provided there is power to the main buses from the
converters. Load shedding of the MAIN boost pumps and opening
the cross flow valve prior to landing should be sufficient to preserve
batteries.
1) Gear Handle ............................................................ DOWN
2) Flaps .................................................. SET FOR LANDING
3) Emergency Batteries ..................................................... ON
4) Ground Spoilers ........................................................... OFF
5) Maintain 67% HP RPM until touchdown.
NOTE: Once the airplane is on the ground, there is no need to
continue to maintain 67% HP RPM. The Standby Electrical
System will stay on line during normal taxi maneuvers. If
Standby Electrical Power is interrupted, cycle the Standby
Electrical Power Switch OFF then ON to regain power.
6) DO NOT use Reverse Thrust.
7) On touchdown, manually deploy the flight spoilers at a
slow rate (approximately 5 seconds).
8) Use normal braking to stop airplane.

END

ABNORMAL / EMERGENCY PROCEDURES REVISION 24 (RE-ISSUE)

Page EA - 22 Mar 17/10
Quick Reference Handbook
Master Table Of Electrical Component Availability GAC

AC BUSSES DC BUSSES

BATT
COMPONENT L MN R MN ESS AC L MN R MN ESS DC BUS
AC AC BUS DC DC BUS #1,
BUS BUS BUS BUS #2
ADF #2 NO #1 NO
1000- 1000-
1017. 1017.
OK OK
1018 & 1018 &
SUB. SUB.
AHRS OK IF L OK IF L
MAIN MAIN
DC OK AC OK
AIR START NO
IGNITION
AOA HEAT #2 NO #1 NO
AOA STALL #2 NO #1 NO
BARRIER
APU ENG NO NO
START START
AUX HYD NO NO
PUMP
BATT CHGRS #1 NO #2 NO NO
BOOST NO NO
PUMPS ALTNS MAINS
CDU #2 NO #1 NO
COWL-WING NO
ANTI-ICE
CPT/CABIN *FULL NO
TEMP CONT COLD
DADC #2 NO #1 NO
DAU #1B NO #2A NO #1A
NO,
#2B NO
DDRMI 1 #1, #2
(DBDI) OK IF
E-
BATTS
ON

*SNs 1120 and Subsequent or ASC 170 - CPT/CAB TEMP CONT is normal.

Continued on next page 

REVISION 24 (RE-ISSUE) ABNORMAL / EMERGENCY PROCEDURES

Mar 17/10 Page EA - 23
 Quick Reference Handbook
Master Table Of Electrical Component Availability, ctd… GAC

AC BUSSES DC BUSSES

BATT
COMPONENT L MN R MN ESS AC L MN R MN ESS DC BUS
AC AC BUS DC DC BUS #1,
BUS BUS BUS BUS #2
DISP. CONT. #2 NO #1 NO
DME #2 NO #1 NO
DU #5 NO #2, #4, #1, #3
#6 NO NO
E INVERTER OK IF
SEPS
IS ON
ECS UNABLE
PACKS TO
CLOSE
ENG IDLE LEFT = RIGHT
67% = 67%
MIN MIN
ENGINE NO STBY
INSTRU- EPR OK IF
MENTS E-
BATTS
ON
FGC #2 NO #1 NO
SPZ 8000
FGC #1 & #2
SPZ 8400 NO
FIRE DET NO
PROT
FLAPS NO
FLIGHT OK IF R OK IF L
GUIDANCE MAIN MAIN
PANEL DC OK DC OK
FWC #2 NO #1 NO
GROUND NO NO
SPOILERS
HF #1 NO #2 NO
IRU #1 OK #2 OK
IF L IF R
MAIN MAIN
AC OK AC OK
ISOLATION FROZEN FROZEN
VALVE
LDG GEAR IND OK
IF E-
BATTS
ON
NAV COMP #2 NO #1 NO
NAV RCVR #2 NO #1 NO

Continued on next page 

ABNORMAL / EMERGENCY PROCEDURES REVISION 24 (RE-ISSUE)

Page EA - 24 Mar 17/10
Quick Reference Handbook
Master Table Of Electrical Component Availability, ctd… GAC

AC BUSSES DC BUSSES

BATT
COMPONENT L MN R MN ESS AC L MN R MN ESS DC BUS
AC AC BUS DC DC BUS #1,
BUS BUS BUS BUS #2
NOSE STEER OK IF OK IF R
ESS DC MAIN
OK DC OK
PERF COMP #1 NO #2 NO
PITCH/MACH #2 NO #1 NO
TRIM
PITOT HEAT NO NO NO NO
RIGHT LEFT RIGHT LEFT
NO NO
STBY STBY
PRESSUR- NO ZERO
IZATION AUTO OFF
RAD ALT #1 NO #2 NO
REVERSERS NO
SYM GEN #3 NO #2 NO #1 NO
TOE BRAKES OK IF
E-
BATTS
ON
TONE GEN NO
TRANS- #2 NO #1 OK
PONDER IF E-
TDR/CAD BATTS
ON
VHF #2 NO #1 OK
IF E-
BATTS
ON
WIPERS NO NO
RIGHT LEFT
WX RADAR PILOTS CO-
RDR PILOTS
CONT RDR
NO CONT
NO
X FLOW / FROZEN
INTERTANK
YAW DAMPER #2 NO #1 NO

END

REVISION 24 (RE-ISSUE) ABNORMAL / EMERGENCY PROCEDURES

Mar 17/10 Page EA - 25
 Quick Reference Handbook
Components Powered By The Emergency Batteries
OM 2A-24-30

Battery Function No. 1 Battery No. 2 Battery

Inboard Anti-skid Outboard Anti-skid
(HMAB) (HMAB)
No. 1 Clock No. 2 Clock
No. 1 Standby No. 2 Standby
DDRMI / DBDI DDRMI / DBDI
No. 1 COMM Standby Horizon
No. 1 COMM Cont. Left Fuel Qty. Ind.
Emergency Buses No. 1 Audio Right Fuel Qty. Ind.
No. 1 TDR / CAD Left Stby. Eng. Inst.
Stby. Mach/AS Ind. Right Stby. Eng.
Inst.
Stby. Altimeter Cockpit Lights Cont.
Stby. Elec. Pwr. Pnl. Landing Gr. Pos.
Lts.
BCS Channel 1 Flap / Horiz. Stab.
Position Indicator
Exterior Emergency Exterior Emergency
Lights (8 ea.) Lights (8 ea.)
No. 1 COMM No. 2 COMM
No. 1 TDR / CAD No. 1 TDR / CAD
Memory Keep Alive No. 1 NAV No. 2 NAV
No. 1 DME No. 2 DME
No. 1 ADF No. 2 ADF

NOTE FOR SN 1467 AND SUBS

Emergency Batteries No. 3 and No. 4 are added. The No. 3 Battery
powers the interior emergency lighting. The No. 4 Battery powers
the main entrance door emergency lighting (if main entrance door is
open).

END

ABNORMAL / EMERGENCY PROCEDURES REVISION 24 (RE-ISSUE)

Page EA - 26 Mar 17/10
Quick Reference Handbook
APU Inflight Operation - Alternate Electrical Source
AFM 3-04-20

For SN 1000 thru 1155 without APU Loadmeter (includes

airplanes having ASC 465 (36-150[G] APU)).
In the event supplemental electrical power is required in flight due to
failure of an engine or alternator / converter system, the APU
alternator may be used as a source.
To start APU in flight:
1. Altitude/Airspeed ....15,000 FT OR BELOW / 250 KCAS OR LESS
2. Battery 1 and 2 Switches ............................................................ ON
3. APU Fire Warning................................................................CHECK
4. APU Master Switch..................................................................... ON
5. APU Start Button ................................................................... PUSH
CAUTION: APU STARTER IS LIMITED TO THREE (3)
CONSECUTIVE START ATTEMPTS THIRTY (30) SECONDS ON,
FOLLOWED BY TWENTY (20) MINUTE COOL-DOWN PERIOD. THEN,
THREE (3) ADDITIONAL START ATTEMPTS MAY BE MADE, AFTER
WHICH A ONE (1) HOUR COOL-DOWN PERIOD MUST BE
OBSERVED.
NOTE: For airplanes having ASC 465 (36-150[G] APU), it is acceptable
for the APU EGT synoptic indication to go into the amber or red range
during start. The synoptic indication only reflects running limitations.

When APU is up to speed (100% 3%):

6. Electric Master Auxiliary Power .................................................. ON
7. Auxiliary Power Loadings ............................................... OBSERVE
With the APU operating and auxiliary power selected ON,
constant frequency AC power is available to power the Main AC
busses; either automatically, if the respective Main AC Bus
AUTO switch is selected, or manually, if the respective APU /
EXT switch is selected. See the limitations that follow.
APU Operating Envelope (SN 1000 through 1155 without APU
Loadmeter):
Starting: 15,000 ft and below / 250 KCAS maximum

Continued on next page 

REVISION 26 ABNORMAL / EMERGENCY PROCEDURES

Oct 5 2011 Page EA - 27
 Quick Reference Handbook
APU Inflight Operation - Alternate Electrical Source, ctd…
AFM 3-04-20

Running: 35,000 ft and below / VMO/MMO maximum

Load: SL to 22,000 ft: 100% (30 KVa)
22,000 to 30,000 ft: linear decrease to 50% (15 KVa)
END

APU Inflight Operation -

ELWS (Loadmeter) / ASC 420 Procedures AFM 3-04-30

For airplanes SN 1156 and subs; airplanes SN 1000 thru SN 1155

with APU loadmeter installed or removed by ASC 420; SN 1430
and subs.
To start APU in flight:
1. Descend to 15,000 ft. or below and reduce airspeed to 250 KCAS
or less.
2. Battery 1 and 2 Switches ........................................................... ON
3. APU Fire Warning ............................................................... CHECK
4. APU Master Switch .................................................................... ON
5. APU Start Button .................................................................... PUSH
CAUTION: APU STARTER IS LIMITED TO THREE (3)
CONSECUTIVE START ATTEMPTS, THIRTY (30) SECONDS ON,
FOLLOWED BY TWENTY (20) MINUTE COOL-DOWN PERIOD. THEN,
THREE (3) ADDITIONAL START ATTEMPTS MAY BE MADE, AFTER
WHICH A ONE (1) HOUR COOL-DOWN PERIOD MUST BE OBSERVED.
When APU is up to speed (100% +3%):
6. Electric Master Auxiliary Power ................................................. ON
7. Auxiliary Power Loadings ............................................... OBSERVE
See the limitations at end of this procedure.
NOTE: If flight is continued above 30,000 ft., the following steps must be
accomplished to ensure continuous APU operation.
If the Left Converter / Alternator is inoperative, complete Steps 8
through 12.
8. Electric Master RIGHT Power .................................................... ON
9. Left AC Main APU / EXT ...................... ON (MANUALLY SELECT)
Continued on next page 
ABNORMAL / EMERGENCY PROCEDURES REVISION 26
Page EA - 28 Oct 5 2011
Quick Reference Handbook
APU Inflight Operation - ELWS (Loadmeter) / ASC 420
Procedures, ctd… AFM 3-04-30

10. Right AC Main RIGHT .......................... ON (MANUALLY SELECT)

11. Left DC Main TRU / EXT ...................... ON (MANUALLY SELECT)
12. Right DC Main RIGHT .......................... ON (MANUALLY SELECT)
If Right Converter / Alternator is inoperative, complete Steps 13
through 17.
13. Electric Master LEFT Power ................. ON (MANUALLY SELECT)
14. Left AC Main LEFT ............................... ON (MANUALLY SELECT)
15. Right AC Main APU / EXT .................... ON (MANUALLY SELECT)
16. Left DC Main LEFT ............................... ON (MANUALLY SELECT)
17. Right DC Main TRU / EXT .................... ON (MANUALLY SELECT)
For either Converter / Alternator inoperative, continue:
18. Essential AC AUTO .................................................................... ON
19. Essential DC AUTO .................................................................... ON
20. Electrical Loadmeter (If Installed) ............................................... ON
21. Electrical Loadmeter (If Installed) Green Arc ......................CHECK
For airplanes SN 1430 and subs, and airplanes with ASC 420:
22. Windshield Heat ..................................................... AS REQUIRED
A. Left Converter Failed .......................................... RF/LS – OFF
B. Right Converter Failed ....................................... LF/RS – OFF
APU Operating Envelope (SN 1156 and subs; SN 1000 through
1155 with APU Loadmeter installed (or removed by ASC 420), SN
1430 and subs, ASC 465 (36-150[G] APU):
Starting: 15,000 ft and below / 250 KCAS maximum
Running: 35,000 ft and below / VMO/MMO maximum
Load: Sea level to 15,000 ft.*: 100% (30 kVA)
15,000 ft. to 30,000 ft..: 75% (22.5 kVA)
30,000 to 35,000 ft.: 50% (15 kVA)
Load-shedding may be required.
* 20,000 ft. if airspeed is kept below 300 KIAS

END

REVISION 24 (RE-ISSUE) ABNORMAL / EMERGENCY PROCEDURES

Mar 17/10 Page EA - 29
 Quick Reference Handbook
APU Alternator Failure AFM 3-04-40

An APU alternator failure (as indicated by lack of AUX PWR on

Electrical Master Panel and / or AUX AC POWER FAIL amber caution
message on CAS) will have no effect as long as both engine driven
Alternator / Converters continue to function. Backup power for
Alternator / Converter failures, however, has been lost.
1. Auxiliary Power Switch ... CYCLE OFF (10 SECONDS), THEN ON
If condition remains same:
2. Auxiliary Power Switch ............................................................. OFF

END

Suspected Erroneous / Unreliable Airspeed

Indications AFM 4-18-60

If one or more airspeed indications (including standby airspeed)

is erroneous or unreliable (with or without DADC failures),
stabilize pitch, power setting (fuel flow), and normalized angle of
attack on the AOA indicator, as appropriate to the phase of flight.
1. Clean Configuration: 0.50 or Lower .............................ESTABLISH
2. Flaps 10, 20, or 39: 0.59 or Lower Until on Approach ............. SET
If an overspeed condition is displayed or the overspeed aural
warning is generated, check pitch, power setting, and AOA.
Maintain AOA between 0.30 and 0.50.
CAUTION: IF THE OVERSPEED CONDITION PERSISTS, REDUCE
POWER SETTING AND INCREASE AOA TO MAINTAIN LEVEL FLIGHT. DO
NOT USE AN AOA HIGHER THAN 0.50.
3. Autopilot and Autothrottle .........................................DISCONNECT
4. Flight Path Angle (FPA) (SPZ-8400) ........ SELECT FOR DISPLAY
5. Pitot and Standby Pitot Heaters ................................... VERIFY ON
6. Pitot and Standby Pitot HTR CB’s ..................... CHECK / PUSH IN
7. Icing Conditions ...................... DEPART AS SOON AS POSSIBLE

Continued on next page 

ABNORMAL / EMERGENCY PROCEDURES REVISION 24 (RE-ISSUE)

Page EA - 30 Mar 17/10
Quick Reference Handbook
Suspected Erroneous / Unreliable Airspeed
Indications, ctd… AFM 4-18-60

8. ATC........................................... ADVISE AS SOON AS POSSIBLE

9. Airplane............................................................................................
.......... PROCEED TO NEAREST SUITABLE AIRPORT AND LAND
CRUISE:
In cruise, maintain the current attitude, power setting (fuel flow), and
normalized AOA. If available, use the HUD symbology, or select FPA
or the HUD Flight Director CUE on the PFD. Align the Flight Path
Marker with the zero-pitch line.
1. KIAS and Predicted Airspeed (from AOM or Cruise
Control Manual) ............................................................. COMPARE
2. IRS or GPS ground speed ........................................................ USE
Predicted ground speed from computerized flight plan may also
be used.
3. Airspeed Source for Continued Flight .............................................
................................................ DETERMINE IF ONE IS SUITABLE
Continue to monitor pitch, power setting (fuel flow), and AOA.
CLIMB, if necessary:
1. Power Levers ........................................... SET TO CLIMB POWER
2. Pitch Attitude ............. ADJUST TO APPROXIMATELY 5° NOSE UP
3. Flight Path Marker (SPZ-8400) ...........................................................
................................... ADJUST TO APPROXIMATELY 3° NOSE UP
4. AOA Between 0.30 and 0.50............................................. MAINTAIN
Be alert for greatly reduced air-noise or lightening of control
forces. If these conditions occur:
5. Pitch Attitude ............................... ADJUST DOWN AS NECESSARY
DESCENT:
1. Power Levers ............................................................. SET TO IDLE
Above 35,000 feet:
2. Pitch Attitude........................................ SET TO 0-1° NOSE DOWN

Continued on next page 

REVISION 24 (RE-ISSUE) ABNORMAL / EMERGENCY PROCEDURES

Mar 17/10 Page EA - 31
 Quick Reference Handbook
Suspected Erroneous / Unreliable Airspeed
Indications, ctd… AFM 4-18-60

3. Flight Path Marker (SPZ-8400) ...........................................................

................................... SET TO APPROXIMATELY 3° NOSE DOWN
Below 35,000 feet:
4. Pitch Attitude ................................. ADJUST TO 0-2° NOSE DOWN
Be alert for increasing air-noise or Mach rumble over the canopy.
If these conditions occur:
5. Pitch Attitude ..................................... ADJUST UP AS NECESSARY
APPROACH AND LANDING:
1. ILS or RNAV Approach With an Electronic Glidepath ........................
.................................................................... UTILIZE, IF AVAILABLE
2. Landing............................... ESTABLISH CONFIGURATION EARLY
3. Approach ................................................................ FLY AT 0.59 AOA
4. Normal Landing................................................................. PERFORM
CONDITIONS/CAUSES FOR PITOT-STATIC ICING/BLOCKAGE:
• Airspeed and altitude information is not consistent with pitch attitude
and thrust setting
• Airspeed / Mach failure-flags are visible
• Airspeed is fluctuating
• A variation exists between pilot and co-pilot airspeed indications
• Overspeed indications exist
• Simultaneous overspeed and stall warnings exist
• The radome has been lost or damaged

END

ABNORMAL / EMERGENCY PROCEDURES REVISION 24 (RE-ISSUE)

Page EA - 32 Mar 17/10
Quick Reference Handbook
Display Unit Failure AFM 3-18-10

For SPZ 8000-equipped airplanes:

1. Affected DU Circuit Breaker (CB) ........................................ CHECK
DU #1, CP: E-6 DU #4, CP: H-6
DU #2, CP: F-6 DU #5, CP: I-6
DU #3, CP: G-6 DU #6, CP: J-6
In the event of a Display Unit failure, the following switching
options are available:
1. NORM - Normal presentation.
2. PFD XFER - Display of PFD info. on DU normally used as ND.
3. ND OFF - Blanks the ND.
EICAS switching options are:
1. NORM - Normal presentation.
2. TOP CMPT - "Compacted" display of both engine
instrumentation and flight crew alerting messages on DU 3.
3. BOT CMPT - "Compacted" display of both engine
instrumentation and flight crew alerting messages on DU 4.

Continued on next page 

REVISION 24 (RE-ISSUE) ABNORMAL / EMERGENCY PROCEDURES

Mar 17/10 Page EA - 33
 Quick Reference Handbook
Display Unit Failure, ctd… AFM 3-18-10

For SPZ 8400-equipped airplanes:

1. Affected DU Circuit Breaker (CB) .......................................... CHECK
DU #1, CP: E-6 DU #4, CP: H-6
DU #2, CP: F-6 DU #5, CP: I-6
DU #3, CP: G-6 DU #6, CP: J-6
In the event of Display Unit failure, automatic switching of
displays occurs to the next available DU.
Manual switching is also available with the following options:
PILOT DISPLAY (PFD and ND):
1. NORM - Normal presentation.
2. PFD - Display of PFD information on DU 2.
3. ENG / EICAS:
- With DU 3 failed, engine data is displayed on DU 2.
- With both DU 3 and 4 inop, compact display of engine
instruments and CAS messages is displayed on DU 2.
COPILOT DISPLAY (PFD and ND):
1. NORM - Normal presentation.
2. PFD - Display of PFD information on DU 5.
3. CAS / EICAS:
- With DU 4 inop, normal CAS display is displayed on DU 5.
- With both DU 3 and 4 inop, compact display of engine
instruments and CAS messages is displayed on DU 5.
Manual reversion with all six DUs operative results in the blanking of
the DU from which information has been transferred and display of
that data on the appropriate DU.

END

ABNORMAL / EMERGENCY PROCEDURES REVISION 24 (RE-ISSUE)

Page EA - 34 Mar 17/10
Quick Reference Handbook
Symbol Generator Failure AFM 3-18-20

1. Display System Control Selector (For Failed Display) .................ALT

2. Display .............................................................................. MONITOR

The following table summarizes the Symbol Generator (SG) selection

possibilities:
Control Switch and Position Symbol Generator Used
PILOT EICAS COPILOT PILOT EICAS COPILOT
NORM NORM NORM 1 3 2
ALT NORM NORM 3 3 2
ALT ALT NORM 2 2 2R
 ALT  ALT  ALT Red X Red X Red X
 ALT  ALT  ALT 1 3 2
ALT NORM ALT 3 3 3R
NORM NORM ALT 1 3 3
NORM ALT NORM 1 2 2
NORM ALT ALT 1 1 1R
NORM = Normal
ALT = Alternate
R = Repeater of source in use by opposite side
 = SPZ-8000 equipped airplanes
 = SPZ-8400 equipped airplanes

END

Traffic And Collision Avoidance System (TCAS)

Failure AFM 3-18-30

1. Equipment Failure:
Should TCAS fail, a TCAS FAIL blue advisory message will be
displayed on EICAS.
2. Circuit Protection:
TCAS components are protected by the TCAS circuit breaker on
the copilot’s aft circuit breaker panel (TCAS, D-11).

END

REVISION 24 (RE-ISSUE) ABNORMAL / EMERGENCY PROCEDURES

Mar 17/10 Page EA - 35
 Quick Reference Handbook
Enhanced Ground Proximity Warning System
(EGPWS) Failure AFM 3-18-40

EGPWS components are protected by EGPWS circuit breakers on

the copilot’s overhead circuit breaker panel (EGPWS AC, D-10;
EGPWS DC, E-10).

END

DADC Failures AFM 3-18-50

“Flagged” DADC Failures

A “flagged” DADC failure is one where the failure is readily apparent,
because of the DADC 1 (or 2) FAIL CAS message, and red “X's”
through all four air data scales (airspeed, altitude, AOA, and vertical
speed) of the PFD using the failed DADC as its air data source, as
selected on the display controllers. Other confirmation of failure is as
follows:
• Transponder indications
• AOA indexer failure
• Automatic cabin pressurization control problems and faulty
guidance panel indications (if operating on the failed DADC)
• EICAS message indicating that EPR is receiving pressure
information from the opposite DADC (EPR 1 - DADC 2 or EPR 2
- DADC 1)
If a “flagged” DADC failure has occurred:
1. Opposite (Good) DADC ................ SELECT AS DATA SOURCE ON
DISPLAY CONTROLLERS, GUIDANCE PANEL, CABIN PRES-
SURE CONTROL PANEL, ETC.

Continued on next page 

ABNORMAL / EMERGENCY PROCEDURES REVISION 24 (RE-ISSUE)

Page EA - 36 Mar 17/10
Quick Reference Handbook
DADC Failures, ctd… AFM 3-18-50

“Unflagged” DADC Failures

An “unflagged” DADC failure will produce a DADC MISCOMPARE
CAS message. The failure may not be readily apparent, but the
following can be expected to occur:
• The autopilot and yaw damper will disconnect and will not re-
engage until the faulty DADC has been identified and isolated by
pulling its circuit breaker
• Pitch trim will remain operative
If an “unflagged” DADC failure is suspected:
1. Faulty DADC ............................................................. ATTEMPT TO
IDENTIFY USING PFD COMPARATOR “IAS/ALT” WARNINGS
To determine which system is correct,
2. Independent Data Source (Standby Flight Instrumentation) ...........
..................................................................................... ESTABLISH
With reference to independent data source established:
3. Other DADC Outputs (Pressurization System, AOA Indexers,
Transponders) .................................................................................
................ CHECK FOR INDICATIONS OF FAULTY OPERATION
If observation leads to a determination of which DADC is faulty:
4. Opposite (Good) DADC .............. SELECT AS DATA SOURCE ON
DISPLAY CONTROLLERS, GUIDANCE PANEL, CABIN PRES-
SURE CONTROL PANEL, ETC.
5. Faulty DADC ...... ISOLATE BY PULLING ITS CIRCUIT BREAKER
(DADC #1: CP, F-3; DADC #2: CP, G-3)
When at least one (1) minute has elapsed since pulling the faulty
DADC circuit breaker:
6. Autopilot ..................................................................... RE-ENGAGE

END

REVISION 24 (RE-ISSUE) ABNORMAL / EMERGENCY PROCEDURES

Mar 17/10 Page EA - 37
 Quick Reference Handbook
Notes

ABNORMAL / EMERGENCY PROCEDURES REVISION 24 (RE-ISSUE)

Page EA - 38 Mar 17/10
Quick Reference Handbook
Brakes / Anti-Skid (Brake By Wire) Index
Hydraulic System Diagram ........................................................... EB-2
Emergency Brakes (Brake-By-Wire)......................................... EB-3
Wheel Brake Failure (Brake-By-Wire) .......................................... EB-3
Brake Confidence Check - Inflight (Brake-By-Wire)..................... EB-4
Uncommanded Applied Brake Pressure -
Inflight (Brake-By-Wire) ............................................................. EB-4
Landing With Applied Brake Pressure
Indicated (Brake-By-Wire) ......................................................... EB-6
Uncommanded Brake Pressure During Landing
Rollout (Brake-By-Wire) ............................................................ EB-6
BRAKE FAIL Message (Brake-By-Wire) ...................................... EB-8
BRAKE PEDAL Message (Brake-By-Wire) .................................. EB-8
Multiple Brake Failure Messages (Brake-By-Wire) ...................... EB-9
BTMS OVHT Light On or BRAKE OVHT
Message (Brake-By-Wire) ....................................................... EB-11
Anti-Skid Failure (Brake-By-Wire) .............................................. EB-13
Anti-Skid Off Braking (Brake-By-Wire: Without ASC 190/266) .. EB-14
Anti-Skid Off Braking (Brake-By-Wire: With ASC 190/266) ....... EB-15

Related Topics In QRH

Brake Kinetic Energy and Carbon Brake Cooling Chart ............ PC-15

REVISION 24 (RE-ISSUE) ABNORMAL / EMERGENCY PROCEDURES

Mar 17/10 (BRAKE BY WIRE) Page EB - 1
 Quick Reference Handbook
Hydraulic System Diagram

ABNORMAL / EMERGENCY PROCEDURES REVISION 24 (RE-ISSUE)

Page EB - 2 (BRAKE BY WIRE) Mar 17/10
Quick Reference Handbook
Emergency Brakes (Brake-By-Wire) AFM 4-05-10

In the event of loss of Combined, Utility, and Auxiliary System

pressure, the wheel brakes may be operated by brake accumulator
pressure through use of the PARK/EMERG brake handle, which by-
passes pedal control. A fully charged brake accumulator allows
approximately 5 to 6 applications of the PARK/EMERG handle before
the pressure is depleted.
There is a noticeable delay in pressure rise when using the parking
brake handle to meter pressure. Grasp the handle with fingertips only
and rest the thumb near the base of the speed brake handle slot.
Raise the handle carefully in ¼ inch increments to avoid excessive
pressure.
CAUTION: ANTI-SKID PROTECTION IS NOT AVAILABLE WHEN
USING THE EMERGENCY BRAKE SYSTEM. USE OF THE EMERGENCY
BRAKE SYSTEM WHILE THE AIRPLANE IS MOVING IS STRICTLY AN
EMERGENCY PROCEDURE. THE EMERGENCY BRAKE PRESSURE CAN
BE METERED. CAUTION SHOULD BE USED NOT TO EXTEND HANDLE
BEYOND THE POSITION WHERE BRAKING IS FIRST FELT (¼ TO ½ INCH
[0.635 TO 1.27 CM]). AS THE AIRPLANE DECELERATES,
REPOSITIONING (METERING) OF HANDLE (EASING IN) MIGHT BE
NECESSARY TO PREVENT SUDDEN STOPPING OR TIRE SKIDDING.

END

Wheel Brake Failure (Brake-By-Wire) AFM 3-05-30

If the Combined System engine-driven pump fails, the Utility System

will automatically provide power to operate brakes. If the Combined
and Utility systems fail, the Auxiliary Hydraulic Pump may be utilized
to operate the brakes. Anti-skid protection is available when using
Combined, Utility, or Auxiliary System pressure.
CAUTION: TAKEOFF IS NOT PERMITTED WITH EITHER SINGLE OR
DUAL CHANNEL FAILURE OF BRAKE-BY-WIRE SYSTEM.

END

REVISION 24 (RE-ISSUE) ABNORMAL / EMERGENCY PROCEDURES

Mar 17/10 (BRAKE BY WIRE) Page EB - 3
 Quick Reference Handbook
Brake Confidence Check - Inflight (Brake-By-Wire)
AFM 3-05-40

1. ANTI-SKID ................................................................................. ON
2. BRAKE NUTCRCKR ORIDE Switch .......... DEPRESS AND HOLD
Depress and hold the BRAKE NUTCRCKR ORIDE switch for the
duration of this check. Wait a minimum of ten (10) seconds.
After a minimum of ten (10) seconds has passed:
3. Left And Right Brake Pedals (Pilot Or Copilot) ...............................
.............................................................. INDIVIDUALLY DEPRESS
A. Confirm applied brake pressure proportionally tracks brake
pedal deflection.
B. Confirm brake pedal deflection does not cause applied
pressure on opposite brake.
4. BRAKE NUTCRCKR ORIDE Switch ............................... RELEASE
If check is satisfactory, proceed with normal landing.

END

Uncommanded Applied Brake Pressure - Inflight

(Brake-By-Wire) AFM 3-05-50

1. Brake System Test (BITE) ...............PERFORM SEVERAL TIMES

IN ATTEMPT TO CLEAR UNCOMMANDED PRESSURE
If pressure returns to normal, perform Brake Confidence Check
- Inflight (Brake-By-Wire), page EB-4.
If pressure remains, proceed as follows:
2. BCS CHL #1 Circuit Breaker (CPO, A-2) ............................... PULL
The ANTI-SKID FAIL message will illuminate on CAS. Apply
brake pressure for thirty (30) seconds. Open-loop pulsed (BANG-
BANG) braking will occur. Release brake pedals.
If brake pressure returns to normal:
A. Reset BCS CHL #1 circuit breaker. If pressure remains
normal, perform Brake Confidence Check - Inflight
(Brake-By-Wire), page EB-4.

Continued on next page 

ABNORMAL / EMERGENCY PROCEDURES REVISION 24 (RE-ISSUE)

Page EB - 4 (BRAKE BY WIRE) Mar 17/10
Quick Reference Handbook
Uncommanded Applied Brake Pressure – Inflight (Brake-By-
Wire), ctd… AFM 3-05-50

If applied pressure remains:

B. PULL BCS CHL #2 circuit breaker (CPO, B-2.) All four (4)
brake system messages will illuminate on CAS.
If brake pressure returns to normal:
C. Leave BCS CHL #2 circuit breaker out and perform Brake
Confidence Check - Inflight (Brake-By-Wire), page EB-4.
If Brake Confidence Check is satisfactory, land with BCS
CHL #2 circuit breaker out.
If uncommanded pressure remains:
D. BCS CHL #2 Circuit Breaker (CPO, B-2) .................... RESET
3. ANTI-SKID ................................................................................ OFF
Cycle the affected brake pedal(s) in an attempt to clear the
uncommanded pressure.
If pressure returns to normal:
A. If pressure returns to normal, land using the applicable
ANTI-SKID OFF BRAKING procedure (see page EB-14 or
EB-15).
If uncommanded applied brake pressure remains:
4. ANTI-SKID .................................................................................. ON
Assume uncommanded applied brake pressure will be present
during landing. See Landing With Applied Brake Pressure
Indicated (Brake-By-Wire), page EB-6.

END

REVISION 24 (RE-ISSUE) ABNORMAL / EMERGENCY PROCEDURES

Mar 17/10 (BRAKE BY WIRE) Page EB - 5
 Quick Reference Handbook
Landing With Applied Brake Pressure Indicated
(Brake-By-Wire) AFM 3-05-60

1. ANTI-SKID .................................................................................. ON
2. Brake Accumulator Pressure ............................................3000 PSI
3. AUX Pump............................................ ARMED (NOT RUNNING)
On Touchdown:
4. Reverse Thrust ........................................APPLY AS NECESSARY
5. Rudder and/or Nose Wheel Steering ..............................................
..............................USE TO MAINTAIN DIRECTIONAL CONTROL
6. DO NOT attempt to use brakes.
7. When ground speed is less than 80 knots, use the metering
parking brake to stop airplane.
CAUTION: ANTI-SKID PROTECTION IS NOT AVAILABLE.
SEE THE APPROPRIATE BRAKES SYSTEM PROCEDURE IN
THIS SECTION.
A. Pull parking brake handle up approximately 1/4 - 1/2 inch.
B. Wait for braking action to commence. Increase brake handle
travel as required.
C. As the airplane decelerates, modulate (meter) the parking
brake pressure as required to prevent sudden stopping or
tire skidding.

END

Uncommanded Brake Pressure During Landing

Rollout (Brake-By-Wire) AFM 3-05-70

1. Reverse Thrust ........................................APPLY AS NECESSARY

2. Rudder and/or Nose Wheel Steering ..............................................
..............................USE TO MAINTAIN DIRECTIONAL CONTROL
3. Discontinue any attempt to apply brakes - FEET OFF THE
BRAKE PEDALS.
4. REAPPLY brake pressure after one (1) second.

Continued on next page 

ABNORMAL / EMERGENCY PROCEDURES REVISION 24 (RE-ISSUE)

Page EB - 6 (BRAKE BY WIRE) Mar 17/10
Quick Reference Handbook
Uncommanded Brake Pressure During Landing Rollout (Brake-
By-Wire), ctd… AFM 3-05-70

5. If the uncommanded or undesired Brake Pressure is still present

and airplane cannot be controlled, DISCONTINUE BRAKE
APPLICATION.
6. When ground speed is less than 80 knots, use the metering
parking brake to stop airplane.
CAUTION: ANTI-SKID PROTECTION IS NOT AVAILABLE.
SEE THE APPROPRIATE BRAKES SYSTEM PROCEDURE IN
THIS SECTION.
A. Pull parking brake handle up approximately 1/4 - 1/2 inch.
B. Wait for braking action to commence. Increase brake handle
travel as required.
C. As the airplane decelerates, modulate (meter) the parking
brake pressure as required to prevent sudden stopping or
tire skidding.

END

REVISION 24 (RE-ISSUE) ABNORMAL / EMERGENCY PROCEDURES

Mar 17/10 (BRAKE BY WIRE) Page EB - 7
 Quick Reference Handbook
BRAKE FAIL Message (Brake-By-Wire) AFM 3-06-10

1. ANTI-SKID .................................................................... CHECK ON

2. Applied Brake Pressure Display......................... SELECT ON DU 4
If airborne:
3. BRAKE NUTCRKR ORIDE Switch ................................ DEPRESS
Hold for 10 seconds and continue holding while performing Step 4.
4. Brake Pedals .................................................................. DEPRESS
INDIVIDUALLY AND CHECK APPLIED BRAKE PRESSURE
5. BRAKE NUTCRKR ORIDE Switch ................................. RELEASE
6. If both left and right brake pressure is not available, see
Emergency Brakes (Brake-By-Wire), page EB-3.
7. If braking is available on one strut, stopping airplane with oper-
ative nosewheel steering on a dry runway is possible if braking is
begun from lower speeds. Expect longer landing distances.
8. If left and right brake pressure is available, the BRAKE FAIL
message is erroneous. Use normal braking.

END

BRAKE PEDAL Message (Brake-By-Wire) AFM 3-06-40

Use the following procedure for fault isolation of the brake pedals:
1. ANTI-SKID .................................................................... CHECK ON
2. Applied Brake Pressure Display......................... SELECT ON DU 4
If airborne:
3. BRAKE NUTCRKR ORIDE Switch ................................ DEPRESS
Hold 10 seconds and continue holding while performing Step 4.
4. Brake Pedals .................................................................. DEPRESS
INDIVIDUALLY AND CHECK APPLIED BRAKE PRESSURE
NOTE: A malfunctioning brake pedal is indicated by zero (0) or lower
than normal brake pressure.
5. BRAKE NUTCRKR ORIDE Switch ................................. RELEASE

Continued on next page 

ABNORMAL / EMERGENCY PROCEDURES REVISION 24 (RE-ISSUE)

Page EB - 8 (BRAKE BY WIRE) Mar 17/10
Quick Reference Handbook
BRAKE PEDAL Message (Brake-By-Wire), ctd… AFM 3-06-40
6. Malfunctioning Brake Pedal(s) .................................. DO NOT USE
7. If no brake pressure is available from any pedal, see Emergency
Brakes (Brake By Wire), page EB-3.

END

Multiple Brake Failure Messages (Brake-By-Wire)

AFM 3-06-50

In case of multiple failure messages or if brake system status is

unknown:
1. Brake ECU ........ ATTEMPT RESET FOLLOWED BY BRAKE BITE
Allow thirty (30) seconds after the BITE for failure to recur.
2. ANTI-SKID Switch ........................................................ CHECK ON
3. Select Applied Brake Pressure Display on DU 4.
If airborne:
4. BRAKE NUTCRKR ORIDE Switch ................................. DEPRESS
Hold for 10 seconds and continue holding while performing Step 5.
5. Brake Pedals (Pilot or Copilot) ....................................... DEPRESS
INDIVIDUALLY AND VERIFY APPLIED BRAKE PRESSURE IS
APPROPRIATE FOR PEDAL DEFLECTION
6. BRAKE NUTCRKR ORIDE Switch ..................................RELEASE
7. If brake pressure indications are normal, use CAUTION in normal
braking.
8. If abnormal or no brake pressure indications occur:
ANTI-SKID Switch .................................................................... OFF
9. Brake Pedals (Pilot or Copilot) ....................................... DEPRESS
INDIVIDUALLY AND VERIFY APPLIED BRAKE PRESSURE IS
APPROPRIATE FOR PEDAL DEFLECTION
10. If brake pressure indications are normal, see appropriate ANTI-
SKID OFF BRAKING (Brake-By-Wire) procedure, page EB-14 or
EB-15.

Continued on next page 

REVISION 24 (RE-ISSUE) ABNORMAL / EMERGENCY PROCEDURES

Mar 17/10 (BRAKE BY WIRE) Page EB - 9
 Quick Reference Handbook
Multiple Brake Failure Messages (Brake-By-Wire), ctd… AFM 3-06-50
11. If abnormal or no brake pressure indications occur:
BCS CHL #1 Circuit Breaker (CPO, A-2) ............................... PULL
12. Brake Pedals (Pilot or Copilot) ....................................... DEPRESS
INDIVIDUALLY AND VERIFY APPLIED BRAKE PRESSURE IS
APPROPRIATE FOR PEDAL DEFLECTION
13. If brake pressure indications are normal, see appropriate ANTI-
SKID OFF BRAKING (Brake-By-Wire) procedure, page EB-14 or
EB-15.
14. If abnormal or no brake pressure indications occur:
BCS CHL #1 Circuit Breaker (CPO, A-2) ............................ RESET
15. ANTI-SKID Switch ...................................................................... ON
16. BCS CHL #2 Circuit Breaker (CPO, B-2) ............................... PULL
NOTE: Pulling this circuit breaker causes three (3) amber brake
messages and one (1) blue brake message to illuminate on EICAS.
17. Brake Pedals (Pilot or Copilot) ....................................... DEPRESS
INDIVIDUALLY AND VERIFY APPLIED BRAKE PRESSURE IS
APPROPRIATE FOR PEDAL DEFLECTION
18. If brake pressure indications are normal, use CAUTION in normal
braking.
19. If abnormal brake pressure indications occur, see Landing With
Applied Brake Pressure Indicated (Brake-By-Wire), page EB-
6.
20. If NO brake pressure indications occur, see Emergency Brakes
(Brake-By-Wire), page EB-3.

END

ABNORMAL / EMERGENCY PROCEDURES REVISION 24 (RE-ISSUE)

Page EB - 10 (BRAKE BY WIRE) Mar 17/10
Quick Reference Handbook

BTMS OVHT Light On or BRAKE OVHT Message

(Brake-By-Wire) AFM 3-06-60

ON THE GROUND:
If the OVHT light on the BTMS display and the BRAKE OVHT CAS
message illuminates during ground operations:
1. Determine which brake is causing the OVHT light by slowly
rotating the BTMS selector switch through each position and
checking for brake temperatures exceeding:
NOTE: For SPZ 8400 equipped airplanes, BTMS display is available
only on BRAKES system page. All four (4) brake temperatures are
displayed simultaneously on the BRAKES system page.
A. 400° ±10° C (Non-ASC 190/Non-ASC 266 airplanes SN
1000 thru 1213 with ASC 167).
B. 625° ±25° C (ASC 190/ASC 266 airplanes SN 1000 thru
1213 with ASC 346 and SN 1214 and subs.).
2. Avoid using the brake(s) that exceed the OVHT limit. Use reverse
thrust as necessary to assist in stopping the airplane if required.
NOTE: For airplanes 1000 thru 1143 without ASC 166: Use of thrust
reversers is limited to one (1) minute every thirty (30) minutes.
3. If possible, expeditiously move the airplane to an uncongested
area clear of other airplane and active taxiways/runways.
4. DO NOT SET THE PARKING BRAKE. Chock the nose gear tire if
possible.
5. Monitor temperature of all brakes for trend information:
A. If temperatures continue to rise or remain above the OVHT
limit for more than five (5) minutes, expect wheel fuse plugs
to release. EVACUATE all personnel and remain clear of the
main landing gear area for a minimum of thirty (30) minutes.
CAUTION: DO NOT ATTEMPT TO TAKEOFF WITH THE
BRAKE OVHT LIGHT ON. THERE MAY NOT BE SUFFICIENT
BRAKE KINETIC ENERGY AVAILABLE IN THE EVENT OF A
REJECTED TAKEOFF OR TIRE FAILURE MAY OCCUR DURING
TAKEOFF ROLL.
NOTE: A visual inspection of the overheated wheels, tires, and
brakes should be accomplished prior to the next flight.

Continued on next page 

REVISION 24 (RE-ISSUE) ABNORMAL / EMERGENCY PROCEDURES

Mar 17/10 (BRAKE BY WIRE) Page EB - 11
 Quick Reference Handbook
BTMS OVHT Light On or BRAKE OVHT Message (Brake-By-Wire),
ctd… AFM 3-06-60

B. If the temperatures have peaked and the OVHT light

extinguishes, the tires should be inspected for proper
inflation and the brakes inspected for obvious damage
before continuing the departure.
NOTE: The flight crew should consider brake energy requirements
for subsequent departures with elevated brake temperatures. Refer
to GIV AFM Appendix C for Brake Kinetic Energy and Carbon
Brake Cooling chart data. (Chart shown on QRH page PC-15.)
IN FLIGHT:
1. Altitude ...... 20,000 FT OR BELOW (DESCEND IF NECESSARY)
2. Airspeed ................................................................. 225 KCAS MAX
3. Landing Gear..................................................................... EXTEND
4. Airspeed ................................................................. 250 KCAS MAX
5. BTMS ............................................................................. MONITOR
NOTE: Landing gear should remain extended until the brake
temperature decreases below 200°C.
6. Airspeed ................................................................. 225 KCAS MAX
7. Landing Gear.................................................................. RETRACT
8. BTMS / OVHT Light............................................. CHECKED / OUT
NOTE: An inspection of overheated wheels, tires, brakes, and wheel
speed sensors should be accomplished before next flight. Refer to GIV
AFM Appendix C for Brake Kinetic Energy and Carbon Brake Cooling
chart data. (Chart shown on QRH page PC-15.)

END

ABNORMAL / EMERGENCY PROCEDURES REVISION 24 (RE-ISSUE)

Page EB - 12 (BRAKE BY WIRE) Mar 17/10
Quick Reference Handbook
Anti-Skid Failure (Brake-By-Wire) AFM 3-02-10

Takeoff:
During takeoff with anti-skid inoperative or selected OFF, wheel
spindown function will be disabled.
Perform the following steps for takeoff with the anti-skid inoperative or
OFF:
1. ANTI-SKID Switch .................................................................... OFF
2. Applied Brake Pressure Display ........................ SELECT ON DU 4
3. Before gear retraction after lift-off, momentarily apply light brake
pressure (300 to 400 psi).
Approach and landing:
If anti-skid is selected OFF, braking should be performed using the
appropriate ANTI-SKID OFF BRAKING procedure, this section.
If anti-skid is not selected OFF, braking in the open loop pulsed mode
(BANG - BANG) should be performed using the following procedure:
1. ANTI-SKID .................................................................... CHECK ON
2. Applied Brake Pressure Display ........................ SELECT ON DU 4
3. Maximum Reverse Thrust ....................................................APPLY
4. Braking ..................... USE AS REQUIRED AT HIGHER SPEEDS
5. ANTI-SKID ...................... OFF AT APPROXIMATELY 100 KNOTS
NOTE: At speeds below 100 knots, the pulsing of open loop
pulsed anti-skid causes braking action to be jerky.
6. ANTI-SKID OFF BRAKING Procedure ........................... CONSULT
NOTE: An increase in landing distance will result if landing rollout is
made with anti-skid completely inoperative or under open loop pulsed
anti-skid control. For landing distances with anti-skid inoperative, refer to
Landing Field Length, Anti-Skid Inoperative charts in Performance
section of GIV AFM. Use of reverse thrust reduces landing distances.

END

REVISION 24 (RE-ISSUE) ABNORMAL / EMERGENCY PROCEDURES

Mar 17/10 (BRAKE BY WIRE) Page EB - 13
 Quick Reference Handbook
Anti-Skid Off Braking
(Brake-By-Wire: Without ASC 190/266) AFM 3-02-20

FOR AIRPLANES SN 1000 THRU 1213 WITHOUT ASC 190/266

Takeoff:
During takeoff with anti-skid inoperative or selected OFF, wheel
spindown function will be disabled.
Perform the following Steps for takeoff with ANTI-SKID
inoperative or OFF:
1. ANTI-SKID Switch .................................................................... OFF
2. Applied Brake Pressure Display......................... SELECT ON DU 4
3. Before gear retraction after lift-off, momentarily apply light brake
pressure (300 to 400 psi).
Approach and landing:
Use the following procedure when braking with anti-skid selected
off:
1. ANTI-SKID Switch .................................................................... OFF
2. Applied Brake Pressure Display......................... SELECT ON DU 4
3. Maximum Reverse Thrust .................................................... APPLY
4. Allow speed to decrease to approximately 100 knots before
applying light braking. Gradually increase to moderate braking as
speed decreases.
NOTE: An increase in landing distance will result if landing rollout is
made with anti-skid completely inoperative. For landing distances with
anti-skid inoperative, refer to Landing Field Length, Anti-Skid Inoperative
charts in Performance section of GIV AFM. Use of reverse thrust
reduces landing distances.

END

ABNORMAL / EMERGENCY PROCEDURES REVISION 24 (RE-ISSUE)

Page EB - 14 (BRAKE BY WIRE) Mar 17/10
Quick Reference Handbook
Anti-Skid Off Braking
(Brake-By-Wire: With ASC 190/266) AFM 3-02-30

FOR AIRPLANES SN 1000 THRU 1213 WITH ASC 190/266

Takeoff:
During takeoff with the anti-skid inoperative or selected OFF, the
wheel spindown function will be disabled. Perform the following steps
for takeoff with the anti-skid inoperative or OFF:
1. ANTI-SKID Switch .................................................................... OFF
2. Applied Brake Pressure Display ........................ SELECT ON DU 4
3. Prior to gear retraction after lift-off, momentarily apply light brake
pressure (300-400 psi).
Approach and landing:
Use the following procedure when braking with anti-skid selected
off:
1. ANTI-SKID Switch .................................................................... OFF
2. Applied Brake Pressure Display ........................ SELECT ON DU 4
3. Maximum Reverse Thrust ....................................................APPLY
4. The pilot should smoothly apply brakes to approximately 300 psi
as advised by the copilot. In an anti-skid inoperative situation, the
pilot should devote his attention to airplane control and the copilot
should monitor applied brake pressure and advise the pilot of
corrections needed to maintain 300 psi.
CAUTION: IT IS NORMAL FOR DECELERATION TO INCREASE
AS THE STOP PROGRESSES. IT IS EXTREMELY IMPORTANT TO
MAINTAIN 300 PSI TO AVOID LOCKED WHEELS AND BLOWN TIRES.
THERE WILL BE A SIGNIFICANT INCREASE IN LANDING DISTANCE
WITH ANTI-SKID INOPERATIVE.
NOTE: An increase in landing distance will result if landing rollout is
made with anti-skid inoperative. For landing distances with anti-skid
inoperative, refer to Landing Field Length, Anti-Skid Inoperative charts in
Performance section of GIV AFM. Use of reverse thrust reduces
landing distances.

END

REVISION 24 (RE-ISSUE) ABNORMAL / EMERGENCY PROCEDURES

Mar 17/10 (BRAKE BY WIRE) Page EB - 15
 Quick Reference Handbook
Notes

ABNORMAL / EMERGENCY PROCEDURES REVISION 24 (RE-ISSUE)

Page EB - 16 (BRAKE BY WIRE) Mar 17/10
Quick Reference Handbook
Brakes / Anti-Skid (HMAB) Index
Hydraulic System Diagram ........................................................... EB-2
Emergency Brakes (HMAB) ....................................................... EB-3
Wheel Brake Failure (HMAB) ....................................................... EB-3
Auxiliary Braking (HMAB) ............................................................. EB-4
BRAKE FAIL Message (HMAB) ................................................... EB-4
BRAKE MAINT REQ’D Message (HMAB) ................................... EB-5
BTMS OVHT Light On or BRAKE OVHT Message (HMAB) ........ EB-5
Anti-Skid Failure (HMAB) ............................................................. EB-7
Anti-Skid Off Braking (HMAB) ...................................................... EB-8

Related Topics In QRH

Brake Kinetic Energy and Carbon Brake Cooling Chart ............. PC-15

REVISION 24 (RE-ISSUE) ABNORMAL / EMERGENCY PROCEDURES

Mar 17/10 (HMAB) Page EB - 1
 Quick Reference Handbook
Hydraulic System Diagram

ABNORMAL / EMERGENCY PROCEDURES REVISION 24 (RE-ISSUE)

Page EB - 2 (HMAB) Mar 17/10
Quick Reference Handbook
Emergency Brakes (HMAB) AFM 4-05-20

FOR AIRPLANES SN 1183, SN 1214 AND SUBSEQUENT WITH

HYDROMECHANICAL ANALOG BRAKE (HMAB) SYSTEM
INCORPORATED
CAUTION: ANTI-SKID PROTECTION IS NOT AVAILABLE WHEN
USING THE EMERGENCY BRAKE SYSTEM. USE OF THE EMERGENCY
BRAKE SYSTEM WHILE THE AIRPLANE IS MOVING IS STRICTLY AN
EMERGENCY PROCEDURE. THE EMERGENCY BRAKE PRESSURE CAN
BE METERED. CAUTION SHOULD BE USED NOT TO EXTEND HANDLE
BEYOND THE POSITION WHERE BRAKING IS FIRST FELT (1/4 TO 1/2
INCH [0.635 TO 1.27 CM]). AS THE AIRPLANE DECELERATES,
REPOSITIONING (METERING) OF HANDLE (EASING IN) MIGHT BE
NECESSARY TO PREVENT SUDDEN STOPPING OR TIRE SKIDDING.
The following procedure should be used to stop the airplane with
emergency brakes:
1. Parking Brake .................................................................... SELECT
2. Anti-Skid ................................................................................... OFF
3. AUX Pump .................................................................................. ON
CAUTION: DO NOT EXCEED 300 PSI INDICATED BRAKE
PRESSURE WHEN APPLYING PARK / EMERG BRAKES.
4. Parking Brake ..................................... AS REQUIRED TO 300 PSI

END

Wheel Brake Failure (HMAB) AFM 3-05-30

If the Combined System engine-driven pump fails, the Utility System

will automatically provide power to operate brakes. If the Combined
and Utility systems fail, the Auxiliary Hydraulic Pump may be utilized
to operate the brakes. Anti-skid protection is available when using
Combined, Utility, or Auxiliary System pressure.
CAUTION: TAKEOFF IS NOT PERMITTED WITH EITHER SINGLE OR
DUAL CHANNEL FAILURE OF BRAKE SYSTEM.

END

REVISION 24 (RE-ISSUE) ABNORMAL / EMERGENCY PROCEDURES

Mar 17/10 (HMAB) Page EB - 3
 Quick Reference Handbook
Auxiliary Braking (HMAB) AFM 3-05-80

FOR AIRPLANES SN 1183, SN 1214 AND SUBS AND AIRPLANES

SN 1000 THRU 1213 WITH ASC 307
1. HYDRAULIC SYSTEM Display ......................................... SELECT
Select HYDRAULIC SYSTEM display on EICAS to show applied
brake pressure.
2. Auxiliary Hydraulic Pump ........................................................... ON
3. Braking ....................................................................AS REQUIRED

END

BRAKE FAIL Message (HMAB) AFM 3-06-20

FOR AIRPLANES SN 1183, 1214 AND SUBS. WITH THE HYDRO-

MECHANICAL ANALOG BRAKE SYSTEM INCORPORATED
If warning occurs in flight:
1. Applied Brake Pressure Display......................... SELECT ON DU 4
2. Hydraulic Pressures ............................................................ CHECK
If combined pressure is normal:
3. Auxiliary Hydraulic Pump ......................................................... OFF
4. Anti-Skid Switch ....................................................................... OFF
5. Brakes .................................................................................. APPLY
If applied brake pressure indicates normal, the message was
false. Proceed with Steps 6, 9 and 10.
6. Auxiliary Hydraulic Pump ................................................... ARMED
If combined system has failed:
7. Auxiliary Hydraulic Pump ........................................... ARMED / ON
8. Brakes .................................................................................. APPLY
If applied brake pressure indicates normal, see Auxiliary Braking
(HMAB), this page.
9. Anti-Skid Switch ......................................................................... ON
10. INBD ANTI-SKID, OTBD ANTI-SKID Circuit Breakers (CPO: A-2,
B-2) ............................................................................................... IN
Continued on next page 

ABNORMAL / EMERGENCY PROCEDURES REVISION 24 (RE-ISSUE)

Page EB - 4 (HMAB) Mar 17/10
Quick Reference Handbook
BRAKE FAIL Message (HMAB), ctd… AFM 3-06-20
If warning occurs during landing:
11. Park / Emergency Brake ......................................... AS REQUIRED
See Emergency Brakes (HMAB), page EB-3.

END

BRAKE MAINT REQ’D Message (HMAB) AFM 3-06-30

For airplanes SN 1183, 1214 and subs:

A wheel speed miscompare lasting more than five (5) seconds will
illuminate the BRAKE MAINTENANCE REQ’D message.
If the message occurs in flight, investigate after landing. This
message may appear if the landing gear is left down after takeoff and
there is a difference in wheel spindown rates.
If message occurs on the ground, limited troubleshooting can be
accom-plished by performing an anti-skid test at a speed of 10 knots or
less.
On ground only:
If the ANTI-SKID FAIL message illuminates during the test, a fault
exists which can be isolated by performing a system test on the Skid
Control Box (SCB).
END

BTMS OVHT Light On or BRAKE OVHT Message

(HMAB) AFM 3-06-60

ON THE GROUND:
If the OVHT light on the BTMS display and the BRAKE OVHT CAS
message illuminates during ground operations:
1. Determine which brake is causing the OVHT light by slowly
rotating the BTMS selector switch through each position and
checking for brake temperatures exceeding:
NOTE: For SPZ 8400-equipped airplanes, BTMS display is available
only on BRAKES system page. All four (4) brake temperatures are
displayed simultaneously on the BRAKES system page.

Continued on next page 

REVISION 24 (RE-ISSUE) ABNORMAL / EMERGENCY PROCEDURES

Mar 17/10 (HMAB) Page EB - 5
 Quick Reference Handbook
BTMS OVHT Light On or BRAKE OVHT Message (HMAB), ctd…
AFM 3-06-60
A. 400° ±10° C (Non-ASC 190/Non-ASC 266 airplanes SN 1000
thru 1213 with ASC 167.)
B. 625° ±25° C (ASC 190/ASC 266 airplanes SN 1000 thru 1213
with ASC 346 and SN 1214 and subs.).
2. Avoid using the brake(s) that exceed the OVHT limit. Use reverse
thrust as necessary to assist in stopping the airplane if required.
NOTE: For airplanes 1000 thru 1143 without ASC 166: Use of thrust
reversers is limited to one (1) minute every thirty (30) minutes.
3. If possible, expeditiously move the airplane to an uncongested
area clear of other airplane and active taxiways/runways.
4. DO NOT SET THE PARKING BRAKE. Chock the nose gear tire if
possible.
5. Monitor temperature of all brakes for trend information:
A. If temperatures continue to rise or remain above the OVHT
limit for more than five (5) minutes, expect wheel fuse plugs to
release. EVACUATE all personnel and remain clear of the
main landing gear area for a minimum of thirty (30) minutes.
CAUTION: DO NOT ATTEMPT TO TAKEOFF WITH THE
BRAKE OVHT LIGHT ON. THERE MAY NOT BE SUFFICIENT
BRAKE KINETIC ENERGY AVAILABLE IN THE EVENT OF A
REJECTED TAKEOFF OR TIRE FAILURE MAY OCCUR DURING
TAKEOFF ROLL.
NOTE: A visual inspection of the overheated wheels, tires, and
brakes should be accomplished prior to the next flight.
B. If the temperatures have peaked and the OVHT light
extinguishes, the tires should be inspected for proper inflation
and the brakes inspected for obvious damage before
continuing the departure.
NOTE: The flight crew should consider brake energy requirements
for subsequent departures with elevated brake temperatures. Refer
to GIV AFM Appendix C for Brake Kinetic Energy and Carbon
Brake Cooling chart data. (Chart shown on QRH page PC-15.)

IN FLIGHT:
1. Altitude ...... 20,000 FT OR BELOW (DESCEND IF NECESSARY)
2. Airspeed ................................................................. 225 KCAS MAX
Continued on next page 

ABNORMAL / EMERGENCY PROCEDURES REVISION 24 (RE-ISSUE)

Page EB - 6 (HMAB) Mar 17/10
Quick Reference Handbook
BTMS OVHT Light On or BRAKE OVHT Message (HMAB), ctd…
AFM 3-06-60

3. Landing Gear .....................................................................EXTEND

4. Airspeed ................................................................ 250 KCAS MAX
5. BTMS .............................................................................. MONITOR
NOTE: Landing gear should remain extended until the brake
temperature decreases below 200° C.
6. Airspeed ................................................................ 225 KCAS MAX
7. Landing Gear .................................................................. RETRACT
8. BTMS / OVHT Light ............................................. CHECKED / OUT
NOTE: An inspection of overheated wheels, tires, brakes, and wheel
speed sensors should be accomplished before next flight. Refer to GIV
AFM Appendix C for Brake Kinetic Energy and Carbon Brake Cooling
chart data. (Chart shown on QRH page PC-15.)

END

Anti-Skid Failure (HMAB) AFM 3-02-40

FOR AIRPLANES SN 1183, 1214 AND SUBS

A failure occurring in the brake system which renders the anti-skid
inoperative will be indicated by illumination of the ANTI-SKID FAIL
message on the EICAS.
There is no automatic reversion to auxiliary braking unless the
combined/utility hydraulic system fails.
If the anti-skid switch is left ON there may still be anti-skid protection on
one pair of wheels (inboard or outboard). With the anti-skid switch OFF
all anti-skid protection is disabled.
Braking with the ANTI-SKID FAIL message illuminated should be
performed using the Anti-Skid Off Braking procedure in this section.

END

REVISION 24 (RE-ISSUE) ABNORMAL / EMERGENCY PROCEDURES

Mar 17/10 (HMAB) Page EB - 7
 Quick Reference Handbook
Anti-Skid Off Braking (HMAB) AFM 3-02-50

FOR AIRPLANES SN 1183, 1214 AND SUBS

During takeoff with anti-skid inoperative or selected OFF, wheel
spindown function will be functional.
Takeoff with the anti-skid inoperative or selected OFF:
1. ANTI-SKID Switch .................................................................... OFF
2. Applied Brake Pressure Display ......................... SELECT ON DU 4
Approach and landing with anti-skid inoperative:
1. ANTI-SKID Switch ...................................................................... ON
2. Applied Brake Pressure Display ......................... SELECT ON DU 4
3. Maximum Reverse Thrust .................................................... APPLY
4. Immediately upon landing or at takeoff abort, the pilot should
smoothly apply brakes to approximately 300 psi as advised by the
copilot. In an anti-skid inoperative situation, the pilot should devote
his attention to airplane control and the copilot should monitor
applied brake pressure and advise the pilot of corrections needed
to maintain 300 psi.
CAUTION: IT IS NORMAL FOR DECELERATION TO INCREASE AS
THE STOP PROGRESSES. IT IS EXTREMELY IMPORTANT TO
MAINTAIN 300 PSI TO AVOID LOCKED WHEELS AND BLOWN TIRES.
THERE WILL BE A SIGNIFICANT INCREASE IN LANDING DISTANCE
WITH ANTI-SKID INOPERATIVE.
NOTE: Brake pedal position in relation to brake pressure can be
observed and practiced airborne with the anti-skid system selected OFF,
and the landing gear up or down.
NOTE: An increase in landing distance will result if landing rollout is
made with anti-skid completely inoperative. For landing distances with
anti-skid inoperative, refer to Landing Field Length, Anti-Skid Inoperative
charts in Performance section of GIV AFM. Use of reverse thrust reduces
landing distances.

END

ABNORMAL / EMERGENCY PROCEDURES REVISION 24 (RE-ISSUE)

Page EB - 8 (HMAB) Mar 17/10
Quick Reference Handbook
Engines Index
Engine Failure Below V1 ............................................................ EC-2
Engine Failure Above V1 ........................................................... EC-3
Dual Engine Flameout................................................................ EC-5
Dual Engine Out Speeds For Maximum Range ....................... EC-7
Dual Engine Out Approach and Landing ................................. EC-7
Engine Failure / Shutdown In Flight ......................................... EC-8
Engine Out Driftdown – ISA, 76,000 to 58,000 pounds......... EC-10
Engine Out Driftdown – ISA, 56,000 to 38,000 pounds......... EC-11
Airstart - Immediate.................................................................. EC-12
Airstart - Normal ....................................................................... EC-12
One (1) Engine Inoperative Landing Procedure .................... EC-14
One (1) Engine Inoperative Go-Around Procedure ............... EC-14
Reverse Thrust Unlock or Deploy During Takeoff ................ EC-15
Reverse Thrust Unlock or Deploy During Flight ................... EC-16
Reverse Thrust Unlock Light Illuminated On The Ground ..... EC-17
Thrust Reverser Stowing Procedure .......................................... EC-17
Engine Synchronizer Failure ...................................................... EC-18
Approach Idle System Failure .................................................... EC-19
Engine Vibration ......................................................................... EC-19
Ice Shedding Procedure ............................................................. EC-20
Engine Failure To Start .............................................................. EC-20
Start Valve Failure ...................................................................... EC-21
Start Valve Open (SVO) Indication In Flight .............................. EC-22
Hot Start ..................................................................................... EC-23
Continuous (Airstart) Ignition Limitations ................................... EC-23
Airstart Envelope ........................................................................ EC-24

Continued on next page 

REVISION 28 ABNORMAL / EMERGENCY PROCEDURES

May 25/16 Page EC - 1
 Quick Reference Handbook
Related Topics In QRH
Shutdown ..................................................................................... NF-1
Engine Cranking Cycle ................................................................ NG-3
Engine Start - Battery Power Only ............................................... NG-3
Single Engine Taxi ....................................................................... NG-5
Landing Planning Data ............................................... PC-1 thru PC-16
APU Inflight Operation - Alternate Electrical Source ................. EA-27
APU Inflight Operation - ELWS (Loadmeter) /
ASC 420 Procedures .............................................................. EA-28

Engine Failure Below V1 AFM 4-09-20

1. Power Levers .......................................................................... IDLE

NOTE: Autothrottle will disconnect.
2. Maximum Anti-Skid Braking ....................................AS REQUIRED
3. Speed Brakes .......................................... DEPLOY IMMEDIATELY
NOTE: Ground spoilers should deploy automatically when the power
levers are closed during an aborted takeoff. Speed brake deployment is a
required backup procedure.
4. Thrust Reversers .....................................................AS REQUIRED
NOTE: During a rejected takeoff, reverse thrust may be used to bring
the airplane to a stop (zero ground speed). If reverse thrust is used
during a rejected takeoff down to zero ground speed, report the
occurrence for maintenance.
5. Tower.................................................................................. NOTIFY
When clear of the runway:
6. Appropriate Abnormal / Emergency Checklist .............COMPLETE
7. AFTER LANDING Checklist (Pg. NF-1) ......................COMPLETE

END

ABNORMAL / EMERGENCY PROCEDURES REVISION 28

Page EC - 2 May 25/16
Quick Reference Handbook
Engine Failure Above V1 AFM 4-09-30

1. Directional Control .......................................................... MAINTAIN

NOTE: Autothrottle will disconnect.
2. VR Speed ...........................................................................ROTATE
3. V2 Speed ...............................................ATTAIN AFTER LIFT-OFF
NOTE: Additional rudder input will be required when nose wheel lifts off.
4. Landing Gear ...................................................................................
.......... UP AFTER POSITIVE RATE OF CLIMB IS ESTABLISHED
NOTE: If gear does not retract normally, manually select utility pump ON.
NOTE: If engine failure should occur after passing V 2 on takeoff, it is
recommended that the speed at the time of engine failure (up to V 2 +10
knots) be maintained. A speed of V2 +10 knots in single-engine takeoff
configuration will produce the maximum climb gradient available.
Continue climb at V2 to 1500 ft above airport level, accelerate to
V2 +10, then:
NOTE: For an obstacle above 1500 feet AGL or a SID that requires a
climb to more than 1500 feet AGL, continue climbing at V2 speed with
flaps in the takeoff position until the obstacle is cleared or the SID has
been satisfied. Refer to AFM Section 5.6 Obstacle Clearance Limited
Performance to determine if an increased level-off altitude is required.
5. Flaps ..............UP AFTER V2 +10 ATTAINED AT 1500 FT ABOVE
AIRPORT LEVEL
NOTE: If the flaps do not retract normally, manually select Utility and
AUX Pumps ON.
6. Airspeed .............................. CONTINUE ACCELERATION TO VSE
7. Operating Engine Power Lever ................................. MCT POWER
NOTE: Takeoff power may be maintained for ten (10) minutes during
single engine operations as needed. Power should then be reduced to
MCT.
Engine Shutdown in Flight:
8. Operating Engine Power Lever ......................................... ADJUST
NOTE: Autothrottle will disengage.
9. Engine Synchronizer ................................................................ OFF

Continued on next page 

REVISION 28 ABNORMAL / EMERGENCY PROCEDURES

May 25/16 Page EC - 3
 Quick Reference Handbook
Engine Failure Above V1, ctd… AFM 4-09-30

10. Power Lever (Failed Engine) ................................................... IDLE

WARNING: VERIFY PROPER ENGINE (LEFT OR RIGHT).
11. HP Fuel Cock (Failed Engine) ................................................SHUT
12. Tone Warning ................................................................... SILENCE
13. Fuel Boost Pumps (Failed Engine) .......................................... OFF
14. Airstart Ignition (Failed Engine) ................................................ OFF
15. Electric Master Power (Failed Engine) ..................................... OFF
16. Electrical Load .................................................CHECK / MONITOR
NOTE: APU may be used as an alternate source of Electrical Power, if
desired. See APU Inflight Operation – Alternate Electrical Source,
page EA-27.
If an engine is shut down due to extreme vibration, consideration
should be given to pulling the FIRE handle to shut off fuel and
hydraulic fluid to the engine.
17. Bleed Air (Failed Engine) ......................................................... OFF
18. Isolation Valve ....................................................................... OPEN
19. Utility Hydraulic Pump (if Left Engine Failed) ........ .....................ON
20. Auxiliary Hydraulic Pump (if Left Engine Failed) ..................... ARM
21. TCAS ................................................................................TA ONLY
22. Fuel Balance .............................................. MONITOR / MAINTAIN
One Engine Inoperative Landing:
23. Normal BEFORE LANDING Checklist .........................COMPLETE
24. Airspeed.......................................VREF FOR 20° FLAPS +10 KCAS
At Final Approach Fix:
25. Flaps.............................................................................................39°
NOTE: If the flight crew elects to land at flaps 20°, fly the approach at
VREF for 20° flaps +10 knots. See Landing Planning – PC for landing
distance in the flaps 20° configuration. Engines do not go to high idle at
flaps 20°. See Partial or Jammed Flaps Landing, page EE-11.

Continued on next page 

ABNORMAL / EMERGENCY PROCEDURES REVISION 28

Page EC - 4 May 25/16
Quick Reference Handbook
Engine Failure Above V1, ctd… AFM 4-09-30

26. Airspeed.....................................VREF FOR 39° FLAPS +10 KNOTS

NOTE: If strong winds are present, add to VREF ½ of the steady state
wind plus the full gust to a maximum additive of 20 knots.
After Landing:
27. Operating Engine Thrust Reverser...........................AS REQUIRED

END

Dual Engine Flameout AFM 4-09-40

If flameout is the result of volcanic ash encounter, an immediate

relight is not recommended. Reverse course to clear ash cloud
and proceed to Step 4.
1. Crew Oxygen Mask (100%) .................................................... DON
2. Power Levers ........................................................................... IDLE
3. Airstart Ignition ............................................................................ ON
4. Airspeed................. DESCEND AT VMO/MMO TO 25,000 FT THEN
SLOW TO 210 KCAS
If engines fail to relight:
5. Passenger Oxygen Masks ..................... DEPLOY (IF REQUIRED)
6. Power Levers ........................................................................... IDLE
7. HP Fuel Cocks....................................................................... SHUT
If below 28,000 ft., proceed to Step 15, otherwise:
8. Airstart Ignition .......................................................................... OFF
9. Battery Switches 1 and 2 ........................................... ON (VERIFY)
10. Essential AC / DC Buses ........................... E INV / BATT (VERIFY)
11. Electric Master Power Switches ............................. OFF (L AND R)
12. Crossflow / Boost Pumps ........................ OPEN / ONE MAIN - ON
13. Electrical Load ....................... REDUCE AS SITUATION PERMITS
14. Bleed Air Switches .................................................................... OFF

Continued on next page 

REVISION 28 ABNORMAL / EMERGENCY PROCEDURES

May 25/16 Page EC - 5
 Quick Reference Handbook
Dual Engine Flameout, ctd… AFM 4-09-40

15. Symbol Generators 2 and 3 ...................................... ALTERNATE

16. EICAS Display ............................... TOP COMPACT (IF DESIRED)
When within airstart envelope (Below 25,000 ft., 200-324 KCAS):
17. Fire Handles ................................................................................. IN
18. Crossflow / Boost Pumps .........................OPEN / ONE MAIN - ON
19. Airstart Ignition .......................................................................... ON
20. Engine RPM (HP and LP) ...........................................INDICATING
21. HP Fuel Cocks (One at a Time) ......................................................
................................................. OPEN (CHECK FOR FUEL FLOW)
NOTE: Use clock to time measurements of thirty (30) second airstart
attempts and engine drain time cycles.
22. Engine Parameters......................................................... MONITOR
CAUTION: ENGINE DAMAGE MAY RESULT IF RPM IS NOT
ALLOWED TO STABILIZE AT IDLE BEFORE ADVANCING POWER
LEVERS.
If engine does not relight within thirty (30) seconds or if engine
does not reach idle:
23. HP Fuel Cocks .......................................................................SHUT
24. Airstart Ignition ........................................................................ OFF
Allow engines to drain for thirty (30) seconds.
25. Begin airstart procedure with Step 17.
After relight of one or both engines occurs:
26. Electrical Power .......................................................AS REQUIRED
27. Bleed Air Switches / Isolation Valve ........................AS REQUIRED
NOTE: With both engines running the configuration is BOTH BLEEDS -
ON, BOTH ECS PACKS - ON, and ISOLATION VALVE - CLOSED.
NOTE: With one engine running the configuration is OPERATING
ENGINE BLEED - ON, BOTH ECS PACKS - ON, and ISOLATION
VALVE - OPEN.
28. Pressurization ........................................... RESET AS REQUIRED
29. “E” Batts................................................................................... ARM

Continued on next page 

ABNORMAL / EMERGENCY PROCEDURES REVISION 28

Page EC - 6 May 25/16
Quick Reference Handbook
Dual Engine Flameout, ctd… AFM 4-09-40

30. Airstart Ignition .......................................................................... OFF

31. Cowl / Wing Anti-Ice ............................................... AS REQUIRED
32. Windshield Heat ................................................. CYCLE OFF / ON
33. Fuel Balance ................................................................... MONITOR
34. APU ........................................................... START - IF REQUIRED

END

Dual Engine Out Speeds For Maximum Range CCM

Weight 75,000 70,000 65,000 60,000 55,000 50,000 45,000

KIAS 203 196 188 181 173 164 155
Glide Ratio = Approximately 15:1

Dual Engine Out Approach and Landing AFM 4-09-50

1. APU (If Available) ........................ START (ONE ATTEMPT ONLY)

2. Starting Point ...................................................................................
...................... ESTABLISH 5,000 FT AGL OVER LANDING AREA
3. Flaps .......................................... 10° (EXTEND WITH AUX PUMP)
4. Airspeed .................................... VREF FOR 10° FLAPS +20 KCAS
5. 180° Position .............................................. BANK TO ESTABLISH
A 25 degree bank will bring the airplane to a 180-degree position
at about 2,500 ft. AGL.
6. Flaps .......................................... 20° (EXTEND WITH AUX PUMP)
7. Bank Angle ..........................................MAINTAIN TO HIGH FINAL
The bank angle should be held at 25 degrees or as necessary for
turning to high final, depending on winds.
8. Airspeed..........................................................175 KCAS OR LESS
9. Emergency Landing Gear T-Handle....................................... PULL
NOTE: Ensure landing gear handle is DOWN for proper gear position
indication and nose wheel steering operation. Operation of emergency
system is not predicated on position of the selector handle.
Continued on next page 

REVISION 28 ABNORMAL / EMERGENCY PROCEDURES

May 25/16 Page EC - 7
 Quick Reference Handbook
Dual Engine Out Approach and Landing, ctd… AFM 4-09-50

10. With Landing Gear Down and Locked ......... OBSERVE LANDING
GEAR EXTENDED SPEED LIMITATION (250 KCAS / 0.7 MT)
11. Final Approach Turn ........................................ 800 to 1000 FT AGL
12. AUX PUMP ....................................................... ON FOR LANDING
13. Flaps ........................................................................................... 20°
NOTE: As airspeed is reduced on final, for landing, hydraulic fluid flow
decreases and flight controls may become less responsive. Do not use
speed brakes if possible, as this could hasten loss of hydraulic pressure.
14. Brakes ................................................. AS NECESSARY TO STOP
15. Emergency Brakes .................. PREPARE TO USE IF REQUIRED

END

Engine Failure / Shutdown In Flight AFM 4-10-10

1. Operating Engine Power Lever ......................................... ADJUST

NOTE: Autothrottle will disengage.
2. Engine Synchronizer ................................................................ OFF
3. Power Lever (Failed Engine) .................................................. IDLE
WARNING: VERIFY PROPER ENGINE (LEFT OR RIGHT).
4. HP Fuel Cock (Failed Engine) ............................................... SHUT
5. Tone Warning ................................................................... SILENCE
6. Fuel Boost Pumps (Failed Engine) .......................................... OFF
7. Airstart Ignition (Failed Engine) ............................................... OFF
8. Electric Master Power (Failed Engine) .................................... OFF
9. Electrical Load ................................................. CHECK / MONITOR
NOTE: The APU may be used as an alternate source of electrical
power, if desired. See the appropriate APU Inflight Operation procedure
in the Avionics / Electrics / APU Index, page EA-1.
NOTE: If an engine is shut down due to extreme vibration, consideration
should be given to pulling the FIRE handle to shut off fluids.
Continued on next page 

ABNORMAL / EMERGENCY PROCEDURES REVISION 28

Page EC - 8 May 25/16
Quick Reference Handbook
Engine Failure / Shutdown In Flight, ctd… AFM 4-10-10

10. Bleed Air Switch (Failed Engine) ............................................. OFF

11. Isolation Valve ....................................................................... OPEN
12. Utility Hydraulic Pump (Left Engine Failed) ................................ ON
13. Auxiliary Hydraulic Pump (Left Engine Failed) ........................ ARM
14. TCAS ................................................................................ TA ONLY
15. Fuel Balance ............................................... MONITOR / MAINTAIN
NOTE: See One (1) Engine Inoperative Landing Procedure, page
EC-14.
One Engine Inoperative Landing:
16. Normal BEFORE LANDING Checklist ........................ COMPLETE
17. Airspeed..................................... VREF FOR 20° FLAPS +10 KCAS
At Final Approach Fix:
18. Flaps ........................................................................................... 39°
NOTE: If the flight crew elects to land at flaps 20°, fly the approach at
VREF for 20° flaps +10 knots. See Landing Planning – PC for landing
distance in the flaps 20° configuration. Engines do not go to high idle at
flaps 20°. See Partial or Jammed Flaps Landing, page EE-11.
19. Airspeed................................... VREF FOR 39° FLAPS +10 KNOTS
NOTE: If strong winds are present, add to VREF ½ of the steady state
wind plus the full gust to a maximum additive of 20 knots.
After Landing:
20. Operating Engine Thrust Reverser ......................... AS REQUIRED

END

REVISION 28 ABNORMAL / EMERGENCY PROCEDURES

May 25/16 Page EC - 9
 Quick Reference Handbook
Engine Out Driftdown - ISA, 76,000 to 58,000 Pounds
CCM

ENGINE OUT DRIFTDOWN

ISA
INITIAL ALT INITIAL DRIFTDOWN WEIGHT - 1000 LB
OAT (°C) 76 74 72 70 68 66 64 62 60 58
SPEED KCAS **** **** **** 246 243 241 238 236 233 230
45000 TIME MIN **** **** **** 51 50 49 48 48 46 46
-56.5 FUEL LB **** **** **** 2400 2310 2206 2122 2074 1948 1916
DISTANCE NM **** **** **** 318 313 306 302 300 290 290
FINAL ALT FT **** **** **** 21300 22300 23200 24200 25000 26100 27000
SPEED KCAS **** 250 247 246 243 241 239 236 233 230
43000 TIME MIN **** 53 52 51 50 48 47 47 45 45
-56.5 FUEL LB **** 2567 2470 2388 2296 2189 2087 2052 1920 1884
DISTANCE NM **** 324 319 314 309 301 294 294 282 281
FINAL ALT FT **** 19600 20600 21300 22300 23200 24100 25000 26100 27000
SPEED KCAS 252 250 248 246 243 241 239 236 233 230
41000 TIME MIN 53 52 50 50 49 47 46 45 43 43
-56.5 FUEL LB 2657 2547 2427 2363 2266 2155 2049 2009 1875 1835
DISTANCE NM 326 319 310 307 301 292 283 282 269 268
FINAL ALT FT 18700 19600 20500 21300 22300 23200 24100 25000 26100 27000
SPEED KCAS 252 250 248 246 243 241 238 237 233 230
39000 TIME MIN 52 51 49 48 47 45 45 43 41 41
-56.5 FUEL LB 2620 2507 2383 2316 2215 2102 2057 1938 1813 1770
DISTANCE NM 317 309 299 296 288 279 277 266 254 252
FINAL ALT FT 18700 19600 20500 21300 22300 23200 24100 24900 26100 27000
SPEED KCAS 252 250 248 246 243 241 238 237 233 230
37000 TIME MIN 51 49 47 46 45 43 43 41 40 38
-56.5 FUEL LB 2564 2448 2322 2253 2149 2033 1985 1864 1781 1686
DISTANCE NM 304 296 286 282 274 264 261 250 243 234
FINAL ALT FT 18700 19600 20500 21300 22300 23200 24100 24900 26000 27000
SPEED KCAS 252 250 248 246 243 241 239 237 233 231
35000 TIME MIN 49 47 45 44 43 41 40 38 37 35
-54.2 FUEL LB 2493 2375 2247 2174 2066 1947 1881 1769 1678 1568
DISTANCE NM 290 281 271 266 257 247 242 232 223 212
FINAL ALT FT 18700 19600 20500 21300 22300 23200 24000 24900 26000 26900
SPEED KCAS 252 250 248 246 243 241 239 237 234 231
33000 TIME MIN 46 45 44 42 40 39 37 36 33 31
-50.3 FUEL LB 2408 2287 2209 2078 1964 1890 1767 1696 1537 1423
DISTANCE NM 274 265 260 249 239 234 222 216 199 187
FINAL ALT FT 18700 19600 20400 21300 22300 23100 24000 24800 25900 26900
SPEED KCAS 252 250 248 246 243 241 240 237 234 232
31000 TIME MIN 44 43 41 40 38 36 33 32 29 26
-46.3 FUEL LB 2306 2235 2096 2012 1889 1755 1614 1540 1363 1224
DISTANCE NM 257 253 241 235 224 212 198 191 172 156
FINAL ALT FT 18700 19500 20400 21200 22200 23100 23900 24800 25900 26800
SPEED KCAS 252 250 248 246 244 242 240 238 235 233
29000 TIME MIN 42 40 38 36 34 31 30 27 24 20
-42.4 FUEL LB 2239 2105 1958 1865 1719 1574 1477 1326 1166 988
DISTANCE NM 244 233 220 213 199 185 176 160 142 121
FINAL ALT FT 18600 19500 20400 21200 22100 23000 23800 24700 25700 26600
SPEED KCAS 252 251 249 247 245 242 240 238 235 233
27000 TIME MIN 39 36 34 32 29 27 24 21 16 10
-38.4 FUEL LB 2085 1925 1770 1665 1503 1390 1211 1065 822 520
DISTANCE NM 222 208 194 185 169 158 139 123 95 58
FINAL ALT FT 18600 19400 20300 21100 22000 22900 23800 24600 25600 26500
SPEED KCAS 253 251 249 248 245 243 241 240 213 210
25000 TIME MIN 34 33 30 26 24 20 16 11 **** ****
-34.4 FUEL LB 1870 1769 1592 1402 1261 1044 846 613 **** ****
DISTANCE NM 195 186 170 151 137 115 93 66 **** ****
FINAL ALT FT 18500 19300 20200 21000 21900 22800 23600 24300 25000 25000

27602C00

ABNORMAL / EMERGENCY PROCEDURES REVISION 28

Page EC - 10 May 25/16
Quick Reference Handbook
Engine Out Driftdown- ISA, 56,000 to 38,000 Pounds
CCM

ENGINE OUT DRIFTDOWN

ISA
INITIAL ALT INITIAL DRIFTDOWN WEIGHT - 1000 LB
OAT (°C) 56 54 52 50 48 46 44 42 40 38
SPEED KCAS 228 225 219 216 215 213 211 207 203 199
45000 TIME MIN 44 43 42 40 38 36 34 31 30 29
-56.5 FUEL LB 1783 1712 1631 1526 1411 1338 1219 1116 1048 982
DISTANCE NM 277 272 266 254 241 233 217 203 195 186
FINAL ALT FT 28000 29000 30400 31500 32400 33300 34300 35400 36400 37400
SPEED KCAS 228 225 219 216 215 212 211 207 203 200
43000 TIME MIN 42 41 40 38 36 34 31 29 28 26
-56.5 FUEL LB 1748 1673 1586 1478 1362 1289 1165 1057 983 914
DISTANCE NM 267 260 253 240 226 218 201 186 176 166
FINAL ALT FT 28000 29000 30400 31500 32400 33400 34300 35400 36400 37300
SPEED KCAS 228 225 219 216 215 213 211 207 204 200
41000 TIME MIN 40 39 38 36 33 32 29 26 24 23
-56.5 FUEL LB 1697 1619 1527 1415 1297 1217 1091 975 896 842
DISTANCE NM 253 246 237 224 209 200 182 165 154 146
FINAL ALT FT 28000 29000 30400 31500 32400 33300 34300 35400 36300 37200
SPEED KCAS 228 225 220 217 215 213 211 207 204 201
39000 TIME MIN 39 38 35 33 30 28 26 23 20 17
-56.5 FUEL LB 1674 1590 1442 1327 1207 1120 1022 889 788 675
DISTANCE NM 243 235 218 204 189 178 164 144 129 110
FINAL ALT FT 27900 28900 30300 31400 32400 33300 34200 35300 36200 37100
SPEED KCAS 228 225 221 218 215 213 211 208 205 200
37000 TIME MIN 37 35 32 29 27 25 21 17 12 6
-56.5 FUEL LB 1585 1494 1331 1207 1117 1014 859 697 537 321
DISTANCE NM 224 215 195 179 168 154 131 106 79 40
FINAL ALT FT 27900 28900 30200 31300 32300 33200 34200 35200 36100 36900
SPEED KCAS 229 226 221 217 216 214 212 208 175 171
35000 TIME MIN 33 31 29 25 22 18 13 6 **** ****
-54.2 FUEL LB 1460 1360 1224 1075 919 780 601 326 **** ****
DISTANCE NM 201 190 173 154 132 112 84 39 **** ****
FINAL ALT FT 27800 28800 30100 31300 32200 33100 34000 34900 35000 35000
SPEED KCAS 229 226 222 218 216 212 182 179 175 172
33000 TIME MIN 29 26 23 19 14 6 **** **** **** ****
-50.3 FUEL LB 1301 1178 1003 837 635 331 **** **** **** ****
DISTANCE NM 174 159 136 114 85 38 **** **** **** ****
FINAL ALT FT 27800 28800 30000 31100 32000 32900 33000 33000 33000 33000
SPEED KCAS 230 227 223 217 183 183 183 180 176 173
31000 TIME MIN 23 21 15 6 **** **** **** **** **** ****
-46.3 FUEL LB 1078 956 693 336 **** **** **** **** **** ****
DISTANCE NM 139 124 88 37 **** **** **** **** **** ****
FINAL ALT FT 27700 28600 29800 30900 31000 31000 31000 31000 31000 31000
SPEED KCAS 230 228 198 195 192 188 185 182 178 175
29000 TIME MIN 17 11 **** **** **** **** **** **** **** ****
-42.4 FUEL LB 814 542 **** **** **** **** **** **** **** ****
DISTANCE NM 99 64 **** **** **** **** **** **** **** ****
FINAL ALT FT 27500 28400 29000 29000 29000 29000 29000 29000 29000 29000
SPEED KCAS 206 202 199 196 193 189 186 182 179 176
27000 TIME MIN **** **** **** **** **** **** **** **** **** ****
-38.4 FUEL LB **** **** **** **** **** **** **** **** **** ****
DISTANCE NM **** **** **** **** **** **** **** **** **** ****
FINAL ALT FT 27000 27000 27000 27000 27000 27000 27000 27000 27000 27000
SPEED KCAS 207 204 201 198 195 191 188 184 181 177
25000 TIME MIN **** **** **** **** **** **** **** **** **** ****
-34.4 FUEL LB **** **** **** **** **** **** **** **** **** ****
DISTANCE NM **** **** **** **** **** **** **** **** **** ****
FINAL ALT FT 25000 25000 25000 25000 25000 25000 25000 25000 25000 25000

27603C00

REVISION 28 ABNORMAL / EMERGENCY PROCEDURES

May 25/16 Page EC - 11
 Quick Reference Handbook
Airstart - Immediate AFM 4-10-20

1. Power Lever ............................................................................ IDLE

2. Air Start Ignition .......................................................................... ON
NOTE: Successful relight is indicated by RPM stabilizing at idle. Allow
engine(s) to stabilize prior to advancing power lever(s). Check that
engine(s) responds normally and monitor TGT prior to advancing power
lever.
After Relight:
3. Airstart Ignition ......................................................................... OFF
If engine fails to relight within twenty (20) seconds, close the HP
fuel cock. Wait at least one (1) minute and perform the AIRSTART
– NORMAL procedure that follows.

END

Airstart - Normal AFM 4-10-30

1. Airspeed ................................................................ 200 - 324 KCAS

2. Altitude ....................................................... 25,000 FT OR BELOW
3. HP Fuel Cock .........................................................................SHUT
4. Bleed Air (Affected Engine) / ISOL VLV ...................... OFF / OPEN
5. Fire Handle ................................................................................... IN
6. Power Lever ............................................................................ IDLE
7. Fuel Boost Pumps ...............................................................ALL ON
8. Cowl / Wing Anti-Ice (Affected Side) ........................................ OFF
9. Airstart Ignition .......................... ON (CHECK IGN MESSAGE ON)
10. Engine RPM (HP and LP) ...........................................INDICATING
11. HP Fuel Cock .......................... OPEN (CHECK FOR FUEL FLOW)
CAUTION: DO NOT ATTEMPT TO METER HP FUEL COCK LEVER
AT INTERMEDIATE POSITIONS.
12. RPM / TGT ..................................................................... MONITOR
13. Oil Temperature / Pressure ................................................. CHECK
Continued on next page 

ABNORMAL / EMERGENCY PROCEDURES REVISION 28

Page EC - 12 May 25/16
Quick Reference Handbook
Airstart - Normal, ctd… AFM 4-10-30

14. Hydraulic Pressure ..............................................................CHECK

15. Airstart Ignition ................................................ OFF (AT IDLE RPM)
16. Electric Master Power ................................................. ON / CHECK
17. ISOL VLV .......................................................................... CLOSED
18. Bleed Air ..................................................................................... ON
19. Cowl / Wing Anti-Ice (Affected Side) ...................... AS REQUIRED
NOTE: At high true airspeeds, it may be necessary to advance power
lever slightly to assist engine RPM acceleration. On advancing the power
lever, HP RPM should steadily increase toward idle. Monitor TGT.
NOTE: The engine should normally light up within ten (10) seconds and
reach idling RPM in approximately forty-five (45) seconds. When the
engine runs satisfactorily, select Airstart Ignition OFF (IGN Message
OUT). Advance power lever slowly to desired RPM.
If the engine fails to relight after airstart ignition has been
energized for thirty (30) seconds, or if it appears unlikely that the
engine will accelerate to idle, proceed as follows:
1. HP Fuel Cock ........................................................................ SHUT
2. Airstart Ignition .....................................OFF (IGN MESSAGE OUT)
3. Power Lever ............................................................................ IDLE
Before attempting another relight, allow engine to drain for at
least thirty (30) seconds. Try again at lower altitude.

END

REVISION 28 ABNORMAL / EMERGENCY PROCEDURES

May 25/16 Page EC - 13
 Quick Reference Handbook
One (1) Engine Inoperative Landing Procedure
AFM 4-10-40

1. Normal Before Landing Checklist (Page NE-3) .........COMPLETE

2. Airspeed .................................. VREF (FOR 20° FLAPS) +10 KCAS
At Final Approach Fix:
3. Flaps ........................................................................................... 39°
NOTE: If the flight crew elects to land at flaps 20°, fly the approach at
VREF for 20° flaps + 10 knots. See the Performance section for landing
distance in the flaps 20° configuration. Engines do not go to high idle at
flaps 20°. See Partial or Jammed Flaps Landings, page EE-11.
4. Airspeed .......................................... VREF 39° FLAPS + 10 KNOTS
NOTE: If strong winds are present, add to VREF ½ of the steady state
wind plus the full gust to a maximum additive of 20 knots.
After Landing:
5. Operating Engine Thrust Reverser .........................AS REQUIRED

END

One (1) Engine Inoperative Go-Around Procedure

AFM 4-10-50

1. Power Lever ...... GO-AROUND POWER ON OPERATING ENGINE

2. Flaps ........................................................................................... 20°
3. Airspeed ..........................................................................................
APPROACH CLIMB SPEED (VREF FOR 39° FLAPS + 10 KNOTS)
4. Landing Gear (After Positive Rate Of Climb Established) ......... UP
5. Altitude ............ CLIMB TO 1,500 FEET ABOVE AIRPORT LEVEL
6. Flaps ............................... UP AT VREF FOR 20° FLAPS +20 KCAS
7. Airspeed ............... MAINTAIN FOR ADEQUATE STALL MARGIN
8. Operating Engine Power Lever .......................................................
................................................ MAXIMUM CONTINUOUS POWER
NOTE: Final segment climb performance is based on setting maximum
continuous power on operating engine.

END

ABNORMAL / EMERGENCY PROCEDURES REVISION 28

Page EC - 14 May 25/16
Quick Reference Handbook
Reverse Thrust Unlock or Deploy During Takeoff
AFM 4-24-10

If below V1:
1. Takeoff ................................................................................. ABORT
2. Engine Failure Below V1 Checklist ................................ PERFORM
NOTE: See Engine Failure Below V1, page EC-2.
If above V1:
3. Affected Engine Power Lever .................................................. IDLE
4. Takeoff .............. CONTINUE AS SINGLE ENGINE INOPERATIVE
5. Airspeed........................................... DO NOT EXCEED 200 KCAS
6. T/REV Emergency Stow Switch .......................................... PRESS
If warning message and lights extinguish:
7. Airplane...................................... LAND AS SOON AS PRACTICAL
8. Reverse Thrust .......................................................... DO NOT USE
NOTE: Both engines will be available for landing.
If T/R doors are believed to be actually deployed:
9. Airplane ..................................... LAND AS SOON AS PRACTICAL
10. Reverse Thrust .......................................................... DO NOT USE
11. Affected Power Lever ............................................. LEAVE IN IDLE
12. Flaps ................................................................................ LIMIT 20°
NOTE: See Landing Planning, Section PC.
13. GPWS / GND SPLR FLAP ORIDE ............................................. ON
CAUTION: IN ANY SITUATION WHERE A REVERSER WILL NOT
RESTOW, THE AFFECTED ENGINE SHOULD BE SHUT DOWN ONLY
IF REQUIRED TO MAINTAIN LEVEL FLIGHT. UNDER CERTAIN
GROSS WEIGHT AND ATMOSPHERIC CONDITIONS, A
SUCCESSFUL GO-AROUND MAY NOT BE POSSIBLE.

END

REVISION 28 ABNORMAL / EMERGENCY PROCEDURES

May 25/16 Page EC - 15
 Quick Reference Handbook
Reverse Thrust Unlock or Deploy During Flight
AFM 4-24-30

NOTE: The REV UNLOCK light may illuminate at high power settings if
hydraulic system pressure is lost.
1. Reverse Levers ...................................................... VERIFY DOWN
2. Affected Engine Power Lever .................................................. IDLE
3. Airspeed ...........................................DO NOT EXCEED 200 KCAS
4. T/REV Emergency Stow Switch .......................................... PRESS
If warning message and lights extinguish:
5. Airplane ..................................... LAND AS SOON AS PRACTICAL
6. Reverse Thrust .......................................................... DO NOT USE
NOTE: Both engines will be available for landing.
If T/R doors are believed to be actually deployed:
7. Airplane ..................................... LAND AS SOON AS PRACTICAL
8. Reverse Thrust .......................................................... DO NOT USE
9. Affected Power Lever .............................................................. IDLE
10. Flaps ................................................................................. LIMIT 20°
NOTE: See Landing Planning, Section PC.
11. GPWS / GND SPLR FLAP ORIDE ............................................ ON
CAUTION: IN ANY SITUATION WHERE A REVERSER WILL NOT
RESTOW, THE AFFECTED ENGINE SHOULD BE SHUT DOWN ONLY
IF REQUIRED TO MAINTAIN LEVEL FLIGHT. UNDER CERTAIN
GROSS WEIGHT AND ATMOSPHERIC CONDITIONS, A
SUCCESSFUL GO-AROUND MAY NOT BE POSSIBLE.

END

ABNORMAL / EMERGENCY PROCEDURES REVISION 28

Page EC - 16 May 25/16
Quick Reference Handbook
Reverse Thrust Unlock Light Illuminated On The
Ground AFM 4-24-40

CAUTION: DO NOT ATTEMPT TO DEPLOY AND RESTOW THE

AFFECTED REVERSER. DAMAGE CAN OCCUR TO AN ACTUATOR’S
PRIMARY LOCK IF IT IS UNLOCKED WITHOUT MAINTAINING STOW
SIDE PRESSURE ABOVE 1200 PSI. THE ACTUATOR COULD BE
DAMAGED REQUIRING REPLACEMENT AND/OR LOCK DOWN
PROCEDURES MORE RESTRICTIVE THAN THE INITIAL FAILURE
WOULD INDICATE.
Return for maintenance action prior to next takeoff.

END

Thrust Reverser Stowing Procedure AFM 3-24-20

NOTE: Use this procedure when a T/R is inadvertently deployed during

engine shutdown. If a malfunction is suspected, refer to GIV Maintenance
Manual, Chapter 78, for T/R lockdown information.
1. For left T/R unlock, open WARN LTS PWR # 4 CB (P, F-4). For
right T/R unlock, open WARN LTS PWR # 8 CB (P, G-3 or G-4).
Affected T/R unlock light should extinguish.
NOTE: If BOTH left and right T/R are unlocked, both the WARN LTS
PWR # 4 CB and WARN LTS PWR # 8 CB must be opened in order to
perform engine cranking cycle.
CAUTION: OBSERVE STARTER DUTY CYCLE.
CAUTION: DO NOT ATTEMPT TO START ENGINE IF T/R DOORS
ARE NOT ENGAGED BY THE SECONDARY LOCK LATCH. PERFORM
NEXT STEP IF T/R DOORS ARE NOT ENGAGED.
2. With reverse thrust lever in stow position, perform Engine
Cranking Cycle, page NG-3. T/R doors will engage secondary
lock latch.
NOTE: Engine cranking cycle will not lock T/R actuator.
3. With reverse thrust lever in stow position, perform Starting
Engines checklist, page NC-6.
4. Close circuit breaker(s) after engine reaches idle. T/R unlock and
deploy lights should be extinguished.

Continued on next page 

REVISION 28 ABNORMAL / EMERGENCY PROCEDURES

May 25/16 Page EC - 17
 Quick Reference Handbook
Thrust Reverser Locking Procedure, ctd… AFM 3-24-20

NOTE: As an alternate method to the engine crank cycle, the T/R doors
may be brought through secondary lock latch as follows:
1. Remove electrical and hydraulic power from airplane.
2. Cycle all flight controls to remove residual hydraulic pressure from
systems.
3. Apply hand pressure to lower door until secondary lock latch engages
T/R doors.

END

Engine Synchronizer Failure AFM 3-08-10

Failure of the engine synchronizer will be evident by left engine failing

to maintain synchronization with the right on either low pressure or
high pressure speed. Should this occur, select the synchronizer OFF.
The synchronizer has also failed if, when selecting the system OFF,
the operating light fails to extinguish after fifteen (15) seconds. Should
this occur, pull the ENG SYNC circuit breaker (P, K-9). If the synchro-
nizer has failed, power lever stagger and asymmetric reverse thrust
may be expected but should not present control problems. With the
synchronizer in the failed mode, the approach idle system will not limit
the engine to minimum approach RPM of 67 % HP RPM. This RPM
must be monitored on approach.
On SN 1214 and subsequent and airplanes with drawing
1159SB40761/1159SB40762 incorporated, the engine synchronizer
function is controlled by the autothrottle. The engine synchronizer
function is only available when the autothrottle is engaged and in the
speed control mode, e.g., CRUISE, V/S mode, V PATH mode, or
PITCH HOLD mode. The engine synchronizer function is enabled with
the autothrottle engaged by using the ON/OFF and LP/HP selector
switches on the overhead panel.

END

ABNORMAL / EMERGENCY PROCEDURES REVISION 28

Page EC - 18 May 25/16
Quick Reference Handbook
Approach Idle System Failure AFM 3-08-20

1. Illumination of amber "ENG IDLE" light:

In Flight:
A. If flaps are less than 39°, minimum idle for corresponding
engine may increase to 67% HP RPM.
B. If flaps are at 39, the flight crew must manually maintain
minimum engine RPM to 67% HP RPM on approach.
On Ground:
A. Minimum idle for the corresponding engine may increase to
67% HP RPM.
2. Approach Idle System Failure - Amber "ENG IDLE" light does not
illuminate:
In Flight:
A. If flaps are at 39°, the flight crew must manually maintain
minimum engine RPM to 67% HP RPM on approach.

END

Engine Vibration AFM 3-08-30

If EVM exceeds 0.60 LP and/or 0.60 HP:

1. Power Lever.....................................................................................
.........................................................................................................
RETARD UNTIL EVM RETURNS TO NORMAL LEVEL
CAUTION: EVM INDICATIONS ALONE SHOULD NOT BE USED AS
CRITERIA FOR ENGINE SHUTDOWN. IN ICING CONDITIONS,
VIBRATIONS MAY EXCEED THE ALERT LEVEL WITHOUT OTHER
ABNORMAL INDICATIONS AND ARE CONSIDERED NORMAL.
If vibration is accompanied by other failure indication:
2. Affected Engine ......................................................... SHUT DOWN
If in flight, see Engine Failure / Shutdown In Flight, page EC-8.
If on ground, see Shutdown, page NF-1.

END

REVISION 28 ABNORMAL / EMERGENCY PROCEDURES

May 25/16 Page EC - 19
 Quick Reference Handbook
Ice Shedding Procedure AFM 3-08-40

In Flight:
To assist in shedding ice, if high vibration occurs and operational cir-
cumstances permit, one engine at a time may be retarded to idle, held
there for five (5) seconds, and then accelerated to 85% LP RPM. The
power lever may then be returned to its original position.
On Ground:
When taxiing or holding on the ground at low power in temperatures
less than 1°C, engine operation at 85% LP for one (1) minute is
recommended just prior to takeoff and at intervals of not more than
sixty (60) minutes under these temperature and moisture conditions.
This is dependent on taxiway and/or runway conditions and proximity to
other airplanes.

END

Engine Failure To Start AFM 3-11-10

Failure of engine to start or reach idling speed may be caused by:

1. No engine rotation.
2. No fuel or no ignition of fuel.
Failure of the engine to rotate can be the result of electrical or
pneumatic malfunctions. Check the engine instruments display for the
Start Valve Open (SVO) mnemonic. If not present, see Start Valve
Failure, page EC-21.
NOTE: For airplanes SN 1144 and subs. and SN 1000 thru 1143 with ASC
151, engine failure to start may be the result of a failed igniter. Check EICAS for
IGN mnemonic. If not present, the start may be salvaged by selecting Air Start
Ignition - ON prior to moving the HP cock from OFF to OPEN. See MEL for
dispatch.
NOTE: Check for fuel flow / pressure to engine. If there is no fuel flow /
pressure verify FIRE handle is FULLY IN.
Auto ignition should occur when the ENGINE START switch is
depressed and its availability will be indicated by the Ignition (IGN)
mnemonic on the engine instruments display. If auto ignition is not
indicated, check for proper selection of the START switch instead of
the CRANK switch. If the CRANK switch has been inadvertently
selected, the start may be salvaged by selecting the proper AIR
START IGNITION switch to ON; or the start may be terminated, the
proper selections made and a second attempt initiated.
Continued on next page 

ABNORMAL / EMERGENCY PROCEDURES REVISION 28

Page EC - 20 May 25/16
Quick Reference Handbook
Engine Failure To Start, ctd… AFM 3-11-10

Fuel ignition should result within five (5) to ten (10) seconds after
opening the HP fuel cock.
If there is no indication of ignition:
1. HP Fuel Cock ........................................................................ SHUT
2. Start Master Switch .................................................................. OFF

END

Start Valve Failure AFM 3-11-20

START VALVE FAIL TO OPEN OR INDICATE OPEN ON ENGINE

START:
1. Start Attempt ........................................................... DISCONTINUE
2. Engine Start Circuit Breaker (P, K-6). .................................CHECK
3. APU Air / External Air ....................................... ON / CONNECTED
4. Bleed Air Pressure ............................... CHECK (25 PSI MINIMUM)
If air is available and pressure is adequate:
5. Another Start .................................................................. ATTEMPT
If start valve does NOT open:
6. Start ............................................................................... ABANDON
The start valve can be manually opened and closed through an
access port in the engine cowling. See Engine Start – Manual
Operation of Start Valve, page NG-15 or refer to GIV
Maintenance Manual, Chapter 80, for procedure.
FAILURE TO CLOSE AFTER ENGINE START:
If the start valve indicator ("SVO") is still illuminated (start valve
not closed) by ground idle HP RPM, proceed as follows:
1. Start Master Switch ......................... PRESS / CHECK LIGHT OUT
2. Both Bleed Air Switches ........................................................... OFF
3. APU Air (or External Air)........................................................... OFF

Continued on next page 

REVISION 28 ABNORMAL / EMERGENCY PROCEDURES

May 25/16 Page EC - 21
 Quick Reference Handbook
Start Valve Failure, ctd… AFM 3-11-20

When bleed air pressure stabilizes at minimum value (minimum 30

seconds):
4. Engine ....................................................................... SHUT DOWN
5. Notify maintenance before further start attempt.

END

Start Valve Open (SVO) Indication - In Flight AFM 3-11-30

In the event the amber SVO indication is displayed on EICAS in

flight:
1. Isolation Valve ...................................................................CLOSED
2. Affected Engine Bleed Air Switch ............................................. OFF
3. Affected Bleed Air Manifold Pressure .............................. ZERO (0)
If not zero, reduce affected engine power to idle.
4. Altitude ...................................................... 41,000 FEET OR LESS
5. Engine Parameters and EVM levels ................................... CHECK
If parameters and levels are normal:
6. Malfunction .................................INVESTIGATE AFTER LANDING
CAUTION: EVM INDICATIONS ALONE SHOULD NOT BE USED AS
CRITERIA FOR ENGINE SHUTDOWN. SEE ENGINE VIBRATION,
PAGE EC-19.
If parameters and levels are abnormal:
7. Engine ........................................................................ SHUT DOWN
See Engine Failure / Shutdown In Flight, page EC-8.

END

ABNORMAL / EMERGENCY PROCEDURES REVISION 28

Page EC - 22 May 25/16
Quick Reference Handbook
Hot Start AFM 3-11-40

If engine exceeds maximum start temperature (700°C):

1. HP Fuel Cock (Affected Engine) ........................................... SHUT
2. Affected Engine ....... CONTINUE TO MOTOR FOR 30 SECONDS
Continue to motor the affected engine for a maximum of thirty
(30) seconds to reduce TGT.
After a maximum of thirty (30) seconds:
3. START MASTER ...................................................................... OFF
Prior to the next attempt to start, check that the fuel boost pump is
ON, fuel pressure is normal, an air source is available and its
pressure is adequate. Check wind direction and attempt to start
directly into the wind; move the airplane if required. If a second
attempt produces a hot start, shut down the affected engine. DO NOT
attempt a restart.

END

Continuous (Airstart) Ignition Limitations AFM 1-74-10

For airplanes SN 1000 through 1249 without ASC 304:

The duty cycle time for continuous (airstart) ignition without ASC 304
is five (5) minutes ON and thirty (30) minutes OFF for cooling. There
is no limitation on the ignition when used in a thirty (30) seconds ON,
thirty (30) seconds OFF cycle.
For airplanes SN 1250 and subs and SN 1000 through 1249 with
ASC 304:
There is no duty-cycle time-limitation for continuous (airstart) ignition
with ASC 304 installed.

END

REVISION 28 ABNORMAL / EMERGENCY PROCEDURES

May 25/16 Page EC - 23
 Quick Reference Handbook
Airstart Envelope AFM FIG 1-10

ABNORMAL / EMERGENCY PROCEDURES REVISION 28

Page EC - 24 May 25/16
Quick Reference Handbook
Fire / Overheat / Smoke Index
Fire Extinguishing System Diagram ............................................. ED-2
Engine Fire In Flight ................................................................... ED-3
Engine Fire On Ground .............................................................. ED-5
APU Fire ...................................................................................... ED-6
Airplane Interior Fire / Smoke / Fumes .................................... ED-7
Fire / Smoke / Fumes in Cockpit, Cabin, or Baggage
Compartment ........................................................................... ED-8
Smoke From Air Conditioning Outlets ................................. ED-9
Electrical Fire / Smoke Source Unknown ........................... ED-10
Smoke and Fumes Evacuation ............................................ ED-12
Engine Fire Warning System Malfunction ............................. ED-13
Tailpipe Fire .............................................................................. ED-14
Fire Detection System Fault ....................................................... ED-14
Engine Hot ................................................................................ ED-15
Pylon Hot ................................................................................... ED-15
Aft Equipment Hot .................................................................... ED-16
Converter Overheat .................................................................. ED-17
Alternator Overheat.................................................................. ED-17
Under Floor Overheat................................................................. ED-18

Related Topics In QRH

Master Table Of Electrical Component Availability .................... EA-23
APU Inflight Operation - Alternate Electrical Source .................. EA-27
APU Inflight Operation - ELWS (Loadmeter) /
ASC 420 Procedures .............................................................. EA-28

REVISION 28 ABNORMAL / EMERGENCY PROCEDURES

May 25/16 Page ED - 1
 Quick Reference Handbook
Fire Extinguishing System Diagram
2.5 LB HALON APU
APU 1301/600 PSI N2
FIRE EXT
ENCLOSURE
FIRE
GAUGE EXT ESS
DISCHD APU DC BUS
FIRE EXT
(PILOT, I-10)

5.6 LB HALON
5.6 LB HALON
1301/600 PSI N2 1301/600 PSI N2

LEFT RIGHT
BOTTLE BOTTLE

GAUGE GAUGE

THERMAL THERMAL
DISCHARGE DISCHARGE

DISCH DISCH

1 2 2 1
LEFT ESS RIGHT
ENGINE DC BUS ENGINE
FUEL , FUEL ,

R
HYDRAUL IC HYDRAUL IC

L
FL UID, FL UID,
GENERAT OR GENERAT OR
AND T HRUST AND T HRUST
REVE RSE R REVE RSE R
DISABL ED DISABL ED
W HEN FIRE EXT W HEN
PUL L ED SHOT #2 PUL L ED
(PILOT, H-8)

ESS
FIRE EXT DC BUS
SHOT #1
(PILOT, G-8)

LEFT RIGHT
ENGINE ENGINE

LEGEND
LEFT BOT TL E
RI G HT BO T T L E
COMMON LINE
APU SHOT

ABNORMAL / EMERGENCY PROCEDURES REVISION 28

Page ED - 2 May 25/16
Quick Reference Handbook
Engine Fire In Flight AFM 4-12-10

For an engine fire warning (red ENG FIRE LOOP ALRT with
warning tone, accompanied by FIRE handle red lights ON, and
lights in the associated HP fuel cock), proceed as follows:
1. Warning Tone ................................................................... SILENCE
2. Affected Engine ........................................................... IDENTIFIED
3. Affected Engine’s Power Lever ............................................... IDLE
4. Affected Engine’s HP FUEL COCK ....................................... SHUT
5. Affected Engine’s Fire Handle ................................................ PULL
6. Affected Engine’s Fire Extinguisher ................................................
...................................DISCH 1 (TURN TO EXTREME POSITION)
NOTE: When it is necessary to discharge a fire bottle, ALWAYS use
DISCHARGE 1 first.
If fire warning indications are no longer present:
7. Fire Warning Circuit Test ............................................... PERFORM
If fire warning circuit test is satisfactory, complete the ENGINE
FAILURE / SHUTDOWN IN FLIGHT checklist (page EC-8). If fire
warning circuit test is not satisfactory, or if fire warning
indications persist for 30 seconds:
8. Affected Engine’s Fire Extinguisher ................................................
...................................DISCH 2 (TURN TO EXTREME POSITION)
If fire warning circuit test is satisfactory or after discharge of fire
bottle(s):
Engine Shutdown in Flight:
9. Operating Engine Power Lever ......................................... ADJUST
NOTE: Autothrottle will disengage.
10. Engine Synchronizer ................................................................ OFF
11. Fuel Boost Pumps (Failed Engine) ........................................... OFF
12. Airstart Ignition (Failed Engine) ................................................. OFF
13. Electric Master Power (Failed Engine) ...................................... OFF

Continued on next page 

REVISION 28 ABNORMAL / EMERGENCY PROCEDURES

May 25/16 Page ED - 3
 Quick Reference Handbook
Engine Fire In Flight, ctd… ................................................ AFM 4-12-10
14. Electrical Load ................................................. CHECK / MONITOR
NOTE: APU may be used as an alternate source of Electrical Power, if
desired. See APU Inflight Operation – Alternate Electrical Source,
page EA-27.
If an engine is shut down due to extreme vibration, consideration
should be given to pulling the FIRE handle to shut off fuel and
hydraulic fluid to the engine.
15. Bleed Air (Failed Engine) .......................................................... OFF
16. Isolation Valve........................................................................ OPEN
17. Utility Hydraulic Pump (if Left Engine Failed) ............................. ON
18. Auxiliary Hydraulic Pump (if Left Engine Failed) ..................... ARM
19. TCAS ................................................................................ TA ONLY
20. Fuel Balance ................................................MONITOR / MAINTAIN
One Engine Inoperative Landing:
21. Normal BEFORE LANDING Checklist ..........................COMPLETE
22. Airspeed........................................VREF FOR 20° FLAPS +10 KCAS
At Final Approach Fix:
23. Flaps ..... .....................................................................................39°
NOTE: If the flight crew elects to land at flaps 20°, fly the approach at
VREF for 20° flaps +10 knots. See Landing Planning – PC for landing
distance in the flaps 20° configuration. Engines do not go to high idle at
flaps 20°. See Partial or Jammed Flaps Landing, page EE-11.
24. Airspeed ................................... VREF FOR 39° FLAPS +10 KNOTS
NOTE: If strong winds are present, add to VREF ½ of the steady state
wind plus the full gust to a maximum additive of 20 knots.
After Landing:
25. Operating Engine Thrust Reverser ..........................AS REQUIRED

END

ABNORMAL / EMERGENCY PROCEDURES REVISION 28

Page ED - 4 May 25/16
Quick Reference Handbook
Engine Fire On Ground AFM 4-12-20

1. Airplane ................................................................................. STOP

2. Both Power Levers .................................................................. IDLE
3. Parking Brake ........................................................................... SET
4. Both HP Fuel Cocks .............................................................. SHUT
5. Affected Engine ........................................................... IDENTIFIED
6. Affected Engine’s FIRE Handle .............................................. PULL
If fire warning indications are no longer present:
7. Fire Warning Circuit Test ............................................... PERFORM
If light(s) test satisfactorily, proceed to Step 11. If fire warning
circuit does not test properly, or if fire light remains illuminated
for 30 seconds:
8. Affected Engine’s Fire Extinguisher .................................................
...................................DISCH 1 (TURN TO EXTREME POSITION)
If fire warning indications are no longer present:
9. Fire Warning Circuit Test ............................................... PERFORM
If fire warning light(s) extinguish:
10 Fire Warning Circuit ................................................................ TEST
If light(s) test is satisfactory, proceed to Step 11. If fire warning
circuit does not test properly, or if fire light remains illuminated
for thirty (30) seconds:
11. Affected Engine’s Fire Extinguisher ................................................
...................................DISCH 2 (TURN TO EXTREME POSITION)
If fire warning light(s) test is satisfactory, or warning ceases after
discharge of fire bottle(s).
12. APU MASTER Switch......................................PRESS/LIGHT OUT
After Ten (10) Seconds:
13. Battery 1 and 2 Switches .......................................................... OFF
14. Airplane......................................................................... EVACUATE

END

REVISION 28 ABNORMAL / EMERGENCY PROCEDURES

May 25/16 Page ED - 5
 Quick Reference Handbook
APU Fire AFM 4-12-30

1. APU Overspeed Test Button ............................................... PRESS

2. APU Master Switch .................................................................. OFF
NOTE: After the APU MASTER switch has been turned off, RPM and
EGT indication will continue for thirty (30) seconds or until the RPM
decreases below 10% (on airplanes SN 1041 and subs. and airplanes
SN 1000 thru 1040 with ASC 46).
3. APU Fire Extinguisher ......................................................... PRESS
NOTE: Allow one (1) minute after release of extinguisher for warnings to
cancel.
4. APU Fire Test ...................................................................... PRESS
If the APU fire detection system tests properly, it may be
assumed that the APU fire has been extinguished. In flight, an
expeditious descent and landing should be considered for
assessment of any damage caused by the APU.
If warnings have not cancelled or system does not test after
warnings have cancelled, it must be assumed that the APU fire
has NOT been extinguished.
In Flight:
5. Emergency Descent ................................................AS REQUIRED
6. Nearest Suitable Airport ......................................................... LAND
On Ground:
7. Airplane ......................................... STOP / SET PARKING BRAKE
8. Engines ..................................................................... SHUT DOWN
9. Fuel Boost Pumps ............................................................. ALL OFF
10. Airplane ............................................ EVACUATE IF NECESSARY

END

ABNORMAL / EMERGENCY PROCEDURES REVISION 28

Page ED - 6 May 25/16
Quick Reference Handbook
Airplane Interior Fire / Smoke / Fumes AFM 4-12-40

WARNING: DO NOT DELAY DESCENT OR DIVERSION TO FIND THE

SMOKE SOURCE. REGARDLESS OF WHETHER A FIRE HAS BEEN
EXTINGUISHED OR SMOKE HAS CLEARED, CONSIDERATION SHOULD
BE GIVEN TO LANDING THE AIRPLANE AT THE NEAREAST SUITABLE
AIRPORT, WITHOUT DELAY.
WARNING: CONSIDER ALL SMOKE AND/OR FUMES TO BE TOXIC.
1. Crew Oxygen Masks (100%) and Smoke Goggles .................. DON
2. NO SMOKE / SEAT BELT .......................................................... ON
WARNING: EXERCISE EXTREME CAUTION WHEN USING
OXYGEN NEAR OPEN FLAME.
3. Passenger Oxygen Mask .............. MANUALLY DEPLOY / VERIFY
NOTE: Visually confirm that an oxygen mask has deployed for each
passenger. Advise passengers to DON oxygen masks.
4. Galley / Cabin Master Switches ................................................. OFF
5. Emergency Power ...................................................................... ON
6. Rapid Descent (if possible) ................................................... BEGIN
Use of autopilot and autothrottles is recommended. Set altitude
pre-selector to desired safe altitude.
NOTE: See Emergency Descent Procedure, page EH-4.
Proceed to the appropriate section to complete checklist:
 Fire / Smoke / Fumes in Cockpit, Cabin, or Baggage
Compartment (page ED-8) ........................................... Section A
 Smoke From Air Conditioning Outlets
(page ED-9) ................................................................... Section B
 Electrical Fire / Smoke Source Unknown
(page ED-10) .................................................................... Section C
 Smoke and Fumes Evacuation
(page ED-12) .................................................................... Section D
Continued on next page 

REVISION 28 ABNORMAL / EMERGENCY PROCEDURES

May 25/16 Page ED - 7
 Quick Reference Handbook
Airplane Interior Fire / Smoke / Fumes, ctd… ................. AFM 4-12-40

Section A: Fire / Smoke / Fumes in Cockpit, Cabin, or

Baggage Compartment
WARNING: MOST GAS-TYPE FIRE EXTINGUISHERS USE HALON
AS THE EXTINGUISHING AGENT. AFTER THE FIRE IS EXTINGUISHED,
REDUCE CONCENTRATION OF HALON AND RESIDUAL FUMES BY
ALLOWING ADEQUATELY VENTILATED AIR TO ENTER THE CABIN.
1. Smoke Mask, Goggles, and Portable Oxygen
(Investigating Crew Member) .................................................. DON
2. FLIGHT/LANDING Switch .................................................. FLIGHT
If the source of Fire/Smoke/Fumes is in the baggage
compartment, go to Step 4.
3. Fire/Smoke/Fumes.....................LOCATE/EXTINGUISH/ELIMNATE
Proceed to Section D: Smoke and Fumes Evacuation, page
ED-12.
4. Internal Baggage Door ......................................... OPEN SLIGHTLY
NOTE: If the airplane is unpressurized, select the pressurization system
to MANUAL, and fully close the outflow valve.
5. Baggage Door Seal Depressurization:
A. Baggage Door Handle ............................... OPEN 45 DEGREES
(for airplanes s/n 1000 through 1155, without ASC 157)
NOTE: Crew member is required to enter baggage compartment to
accomplish Step 5A. Once door handle is rotated 45 degrees, do not
open baggage door. Doing so will impair smoke evacuation.
B. Baggage Door Seal Selector Valve .................... EVAC SMOKE
(for airplanes s/n 1000 through 1155, with ASC 157, and
airplanes s/n 1156 and subsequent)
NOTE: As cabin altitude increases, cabin rate of climb can be
controlled by increasing available bleed pressure above 35 psi. Bleed
pressure can be increased by increasing power to maximum
continuous setting, or by selecting COWL ANTI-ICE ON at higher
altitudes. If unable to attain 35 psi or greater, or if selecting COWL
ANTI-ICE ON results in COOL TUB HOT message, descend to lower
altitude until cabin rate of climb is controllable. Select COWL ANTI-
ICE OFF if COOL TURB HOT message persists.
6. Baggage Compartment .......................................................... ENTER
Continued on next page 

ABNORMAL / EMERGENCY PROCEDURES REVISION 28

Page ED - 8 May 25/16
Quick Reference Handbook
Airplane Interior Fire / Smoke / Fumes, ctd… AFM 4-12-40

7. Fire/Smoke/Fumes ............... LOCATE / EXTINGUISH / ELIMINATE

8. Cabin Pressurization May Be Returned to Normal:
A. Baggage Door Handle ......................................................CLOSE
(for airplanes s/n 1000 through 1155, without ASC 157)
NOTE: Crew member is required to enter baggage compartment to
accomplish Step 8.
B. Baggage Door Seal Selector Valve .................... NORMAL OPS
(for airplanes s/n 1000 through 1155, with ASC 157, and
airplanes s/n 1156 and subsequent)
9. Internal Baggage Door ......................................................... CLOSED
10. Proceed to nearest suitable airport and land. Proceed to
Section D: Smoke and Fumes Evacuation, page ED-12.

Section B: Smoke From Air Conditioning Outlets

To isolate smoke source to an Environmental Control System
(ECS) pack or Engine Bleed Air System:
1. Isolation Valve .................................................................. CLOSED
2. Left Engine BLEED AIR ............................................................ OFF
If smoke appears to have stopped, proceed to nearest suitable
airport and land. Proceed to Section D: Smoke and Fumes
Evacuation, page ED-12.
If smoke continues:
3. Left Engine BLEED AIR .............................................................. ON
4. Right Engine BLEED AIR ......................................................... OFF
If smoke appears to have stopped, proceed to nearest suitable
airport and land. Proceed to Section D: Smoke and Fumes
Evacuation, page ED-12.
If smoke continues:
CAUTION: WITH L AND R BLEEDS OFF, THE AIRPLANE WILL
DEPRESSURIZE AND CABIN ALTITUDE WILL RISE RAPIDLY.
5. Left Engine BLEED AIR ............................................................ OFF
Continued on next page 

REVISION 28 ABNORMAL / EMERGENCY PROCEDURES

May 25/16 Page ED - 9
 Quick Reference Handbook
Airplane Interior Fire / Smoke / Fumes, ctd. AFM 4-12-40

6. RAM AIR.................................................................................. RAM

7. OUTFLOW VALVE ............................... OPEN (TO VENT SMOKE)
If source of smoke or fumes cannot be positively located and
isolated, even though smoke has dissipated, consider
performing the steps in Section A (page ED-8) or Section C (page
ED-10). Proceed to nearest suitable airport and land.

Section C: Electrical Fire / Smoke Source Unknown

1. Boost Pumps ...................................................................... ALL ON
2. Cross Flow............................................................................. OPEN
3. Battery Switches .............................................................. BOTH ON
4. Essential AC Bus .............................. E INV (MANUALLY SELECT)
5. Essential DC Bus.............................. BATT (MANUALLY SELECT)
6. Electric Masters (Left, Right, AUX Power Switches) ................ OFF
7. ‘E’ BATTS ................................................................................. OFF
If smoke stops, complete steps 8 through 11. Proceed to Section
D: Smoke and Fumes Evacuation, page ED-12. If smoke
continues, go to step 12.
8. FGC 2 Circuit Breaker ............................................................ PULL
9. STBY Electrical Power Switch, E INV, TRU ............................... ON
10. Symbol Generator 2 and 3 Control Switches ............................ ALT
(Top Compact – If Desired)
11. Utility Pump Switch ................................................................... OFF
NOTE: STBY Electrical Power Switch, E INV, TRU should be
turned off for approach and landing.
If smoke continues:
12. Electrical Masters (Left, Right, AUX Power) .............................. ON
13. ESS AC and DC Busses ....................................................... AUTO
14. Pressurization Control ...................................................... MANUAL
Continued on next page 

ABNORMAL / EMERGENCY PROCEDURES REVISION 28

Page ED - 10 May 25/16
Quick Reference Handbook
Airplane Interior Fire / Smoke / Fumes, ctd… AFM 4-12-40

At Power Distribution Box (PDB):

CAUTION: DO NOT ATTEMPT TO RESET ANY POPPED
CIRCUIT BREAKERS.
15. ESS AC and DC Circuit Breakers ...............PULL ONE AT A TIME
Allow sufficient time (approximately thirty (30) seconds) for smoke to
stop between each PULL and RESET.
CAUTION: PULLING ESS DC BUS PILOT CIRCUIT BREAKER
2 WILL DISABLE MANUAL CONTROL OF PRESSURIZATION
SYSTEM. RESELECT AUTO MODE IF PULLING THIS CIRCUIT
BREAKER STOPS SMOKE.
NOTE: Refer to MASTER TABLE, Section 4, for Electrical Component
Availability, to assist in determining inoperative items with a specific
breaker.
16. Yaw Damper and/or Mach Trim Limits ........................... OBSERVE
17. Pressurization Control ........................................................... AUTO
If available, pilot’s Phase A Circuit Breaker, ESS AC Section.
18. Windshield Heat ................... OFF TWO (2) SECONDS, THEN ON
19. FGC CB’s .................. PULL AND / OR RESET (AS NECESSARY)
If smoke continues:
20. Electrical System .......... RETURN TO NORMAL CONFIGURATION
21. Windshield Heat...................... OFF TWO (2) SECONDS, THEN ON
22. FGC CB’s .................... PULL AND / OR RESET (AS NECESSARY)
23. Proceed to nearest suitable airport for landing. Proceed to
Section D: Smoke and Fumes Evacuation, page ED-12.

Continued on next page 

REVISION 28 ABNORMAL / EMERGENCY PROCEDURES

May 25/16 Page ED - 11
 Quick Reference Handbook
Airplane Interior Fire / Smoke / Fumes, ctd… AFM 4-12-40

Section D: Smoke and Fumes Evacuation

WARNING: MOST GAS-TYPE FIRE EXTINGUISHERS USE
HALON AS THE EXTINGUISHING AGENT. AFTER THE FIRE IS
EXTINGUISHED, REDUCE CONCENTRATION OF HALON AND
RESIDUAL FUMES BY ALLOWING ADEQUATELY VENTILATED
AIR TO ENTER THE CABIN.
To remove residual smoke / fumes from the cockpit or cabin
areas:
1. FLIGHT / LANDING Switch ................................................ FLIGHT
2. Cockpit and Cabin Air Gaspers ............................................. OPEN
3. Cabin Altitude ................................................ RAISE TO 10,000 FT
4. Cabin Rate ...........................................................Select 1,000 FPM
If smoke/fumes cannot be eliminated, consider repeating Section
A, B, or C of this procedure.
5. Emergency Power (E-Batts) .................................................... ARM
6. Proceed to nearest suitable airport and land.
Operational Considerations:
 Immediate Return for Landing – see Immediate Return for
Landing, page EI-6
 Overweight Landing – see Overweight Landing, page EI-3
 Ditching – see Ditching, page EI-4
 Emergency Airplane Evacuation – see Emergency Airplane
Evacuation, page S-56

END

ABNORMAL / EMERGENCY PROCEDURES REVISION 28

Page ED - 12 May 25/16
Quick Reference Handbook
Engine Fire Warning System Malfunction AFM 4-13-10

In the event of a single FIRE TEST LOOP light:

1. Lighted Fire Test Switchlight ............................................... PRESS
If warnings illuminate:
A. Fire Test Switch ....................................................... RELEASE
B. Faulty Loop With Fault Switch On FIRE DETECTION Panel ...
.................................................................................. DISABLE
If warnings DO NOT illuminate:
A. Fire Test Switch ....................................................... RELEASE
B. Engine Fire In Flight Checklist, page ED-3 or
Engine Fire On Ground Checklist, page ED-5
(As Applicable) .................................................... COMPLETE

END

REVISION 28 ABNORMAL / EMERGENCY PROCEDURES

May 25/16 Page ED - 13
 Quick Reference Handbook
Tailpipe Fire AFM 4-12-50

In the event of a tailpipe fire:

1. Affected Engine ........................................................... IDENTIFIED
2. Both Power Levers .................................................................. IDLE
3. Affected Engine HP Fuel Cock ................................................. OFF
4. APU BLEED AIR (If APU Running) ............................................ ON
5. Isolation Valve ....................................................................... OPEN
6. Master Crank .............................................................................. ON
7. Affected Engine ENG START .................................................... ON
8. SVO ..................................................................................... CHECK
9. Crank Cycle ................................. CONTINUE UNTIL FIRE IS OUT
10. Emergency Crew .............................................................NOTIFIED
11. Remaining Engine ..................................................... SHUT DOWN

END

Fire Detection System Fault AFM 3-13-20

Each of the two (Loop A and Loop B) fire detection loops of each
engine is provided with a fault discriminator circuit. Fault indicators
and a single test button to test all four loops are located in the
ENGINE CONTROL section of the overhead panel.
If a fire detection loop develops a fault, the associated amber fault
light will illuminate and an ENG FLT LOOP ALRT message with the
associated tone will be generated. Since both loops must sense a fire
or overheat in order to trigger an engine fire warning, the faulty loop
will preclude that capability until it has been isolated from the system.
The faulty loop is isolated and fire detection system is restored to
normal operation by pressing the amber FAULT switchlight, at which
time the OFF portion of the switchlight will illuminate.

END

ABNORMAL / EMERGENCY PROCEDURES REVISION 28

Page ED - 14 May 25/16
Quick Reference Handbook
Engine Hot AFM 4-21-10

For engine hot (L-R ENGINE HOT message on CAS and associated
warning tone), proceed as follows:
1. Affected Engine Bleed Air ........................................................ OFF
2. Affected Power Lever ....................................................... RETARD
If engine hot message is extinguished, continue operating with
reduced engine power.
If light persists, immediately proceed as follows:
3. Affected Engine HP Fuel Cock .............................................. SHUT
NOTE: If HP fuel cock lever is jammed and cannot be closed, pull FIRE
handle.
4. Power and Trim ...................................................... AS REQUIRED
5. Gear and Flaps ....................................................... AS REQUIRED
6. Engine Failure / Shutdown In Flight Checklist (Page EC-8) .........
..................................................................................... COMPLETE
CAUTION: FIRE EXTINGUISHER SHOULD NOT BE USED FOR
ENGINE HOT WARNING ALONE. IF SUBSEQUENT FIRE WARNING
RESULTS, INITIATE ENGINE FIRE PROCEDURE. AN ENGINE MUST
NOT BE RESTARTED AFTER AN OVERHEAT WARNING. CLOSELY
OBSERVE APPROPRIATE ENGINE FIRE WARNING LIGHT.
NOTE: If HP fuel cock was closed, but visual, aural, or TGT / RPM
checks indicate a condition that could lead to further damage, the FIRE
handle should be pulled.

END

Pylon Hot AFM 4-21-20

A PYLON HOT message indicates a pylon temperature which may

result in damage to the pylon. Accomplish the following checklist:
1. Affected Engine Bleed Air ........................................................ OFF
2. Affected Engine ECS Pack ....................................................... OFF
3. Isolation Valve .....................................................CHECK CLOSED
4. Altitude ............................... DESCEND TO 41,000 FT OR BELOW

Continued on next page 

REVISION 28 ABNORMAL / EMERGENCY PROCEDURES

May 25/16 Page ED - 15
 Quick Reference Handbook
Pylon Hot, ctd… AFM 4-21-20

If message persists or returns:

5. Affected Engine ......................................................... SHUT DOWN
See Engine Failure / Shutdown In Flight, page EC-8.

END

Aft Equipment Hot AFM 4-21-30

The AFT EQUIPMENT HOT message indicates high temperatures

exist in the tail compartment which may be caused by a ruptured
pneumatic duct or fire.
1. Affected Engine ....................................... ATTEMPT TO IDENTIFY
NOTE: High TGT, high fuel flow, low EPR, or abnormal (low) bleed
pressure may indicate faulty side.
2. Affected Engine Bleed Air ........................................................ OFF
3. Isolation Valve ..................................................... CHECK CLOSED
4. Altitude ............................... DESCEND TO 41,000 FT OR BELOW
If message persists or returns:
5. Emergency Descent ................................................... COMMENCE
See Emergency Descent Procedure, page EH-4.
6. Crew Oxygen Masks ..................................... DON (IF REQUIRED)
7. Passenger Oxygen Masks ..................... DEPLOY (IF REQUIRED)
8. Opposite Engine Bleed Air ........................................................ OFF
NOTE: This will result in loss of cabin pressurization. Cabin altitude will
climb at the cabin leak rate.
9. If message persists, land airplane as soon as possible.

END

ABNORMAL / EMERGENCY PROCEDURES REVISION 28

Page ED - 16 May 25/16
Quick Reference Handbook
Converter Overheat AFM 4-21-40

Illumination of "L or R CONV HOT" amber caution message with

associated tone:
1. ELECTRIC MASTER LEFT or RIGHT POWER ....................... OFF
If message extinguishes:
2. ELECTRIC MASTER LEFT or RIGHT POWER ......................... ON
NOTE: Converter operation should be monitored for remainder of
flight. At any sign of unusual operation or heavy load, turn
ELECTRIC MASTER LEFT or RIGHT PWR - OFF.
NOTE: The light will remain ON until the temperature of the converter is
reduced. If overheat condition recurs, turn the overheated converter OFF
for remainder of flight and perform Alternator / Converter Failure –
Single, page EA-8.
NOTE: If below 15,000 ft., it is recommended that the APU be started as
a source of supplemental electrical power. See the Avionics / Electrics /
APU Index, page EA-1, for the appropriate APU Inflight Operation
procedure.

END

Alternator Overheat AFM 4-21-50

Illumination of L or R ALT HOT message with associated tone:

1. ELECTRIC MASTER LEFT or RIGHT POWER ....................... OFF
If the message extinguishes and was not accompanied by engine
vibration or unusual EVM indications:
2. ELECTRIC MASTER LEFT or RIGHT POWER ......................... ON
Monitor alternator operation for remainder of flight. If indications
are erratic or HOT message re-illuminates, select appropriate
ELECTRIC MASTER switch to OFF.
NOTE: If below 15,000 ft., it is recommended that the APU be started as
a source of supplemental electrical power. See the Avionics / Electrics
/ APU Index, page EA-1, for the appropriate APU Inflight Operation -
Alternate Electrical Source procedure.

END

REVISION 28 ABNORMAL / EMERGENCY PROCEDURES

May 25/16 Page ED - 17
 Quick Reference Handbook
Under Floor Overheat AFM 3-21-60

1. If wing anti-ice is ON, select left wing OFF.

2. Wait two (2) minutes.
3. If message persists, select right wing OFF.
4. If message persists, depart icing conditions.
5. Verify isolation valve is closed.
6. Select left bleed OFF.
7. If message persists, select left bleed ON and right bleed OFF.
8. If message persists, check floor board physically for temperature.
9. If cool, no action.
10. If hot, descend to 15,000 ft. or below and select left bleed OFF
and RAM AIR ON.

END

ABNORMAL / EMERGENCY PROCEDURES REVISION 28

Page ED - 18 May 25/16
Quick Reference Handbook
Flight Controls / Autoflight Index
Hydraulic System Diagram ........................................................... EE-2
General Guidance ....................................................................... EE-3
Flight Control Runaway To Hardover Position ....................... EE-3
Immovable Flight Controls ........................................................ EE-4
Stall Barrier Malfunction ............................................................ EE-6
Ground Spoiler Failure .............................................................. EE-7
Runaway Electric Pitch Trim ........................................................ EE-7
Frozen Pitch Trim ......................................................................... EE-8
Failure of Stabilizer / Flap Interconnect........................................ EE-9
Flaps - Alternate Operation ........................................................ EE-10
Partial or Jammed Flaps Landings ............................................. EE-11
Uncommanded Flap Movement ................................................. EE-11
Flaps Lock Up While Moving / Fail To Move .............................. EE-12
Autopilot Malfunction .................................................................. EE-12
Autothrottle Malfunction ............................................................. EE-13
AFGCS Failure ........................................................................... EE-13
Mach Trim Compensation Failure .............................................. EE-13
Yaw Damper Failure................................................................... EE-14

REVISION 28 ABNORMAL / EMERGENCY PROCEDURES

May 25/16 Page EE - 1
 Quick Reference Handbook
Hydraulic System Diagram

ABNORMAL / EMERGENCY PROCEDURES REVISION 28

Page EE - 2 May 25/16
Quick Reference Handbook
General Guidance AFM 4-15-10

CAUTION: DO NOT PULL THE FLIGHT POWER SHUTOFF HANDLE

WITH THE SPEED BRAKES EXTENDED, AS ASYMMETRICAL SPOILER
BLOWDOWN MAY CAUSE AIRPLANE ROLL. SHOULD THE FLIGHT
POWER SHUTOFF HANDLE INADVERTENTLY BE PULLED WITH SPEED
BRAKES EXTENDED, IMMEDIATELY MOVE THE SPEED BRAKE HANDLE
TO THE FULL RETRACTED POSITION.

END

Flight Control Runaway To Hardover Position

AFM 4-15-20

Rudder Control (Yaw):

1. Flight Power Shutoff Handle ................................................... PULL
Aileron Control (Roll):
2. Check GND SPOILER message. If extinguished:
Flight Power Shutoff Handle ................................................... PULL
Elevator Control (Pitch):
3. Verify runaway electric trim or stall barrier is not the problem, then:
Flight Power Shutoff Handle .................................................. PULL
NOTE: If the Flight Power Shutoff Handle is pulled at rotation due to a
flight control problem, high pull forces will be required to achieve the
takeoff attitude. There will be a delay in airplane rotation and, once
airborne, a push force will be necessary to maintain the climb attitude.
Application of forward trim will be required shortly after becoming
airborne. To avoid running out of forward trim, reduce speed as
necessary.
NOTE: If Yaw Damper disengages as result of pulling Flight Power
Shutoff Handle, do not attempt to reengage.
Continue flight to nearest suitable airport and land.
NOTE: Select a runway that is at least 7,000 feet long and 150 feet
wide. Minimize crosswind component to less than 5 knots.
NOTE: If the flight crew elects to land at flaps 20°, fly the approach at
VREF for 20° flaps +10 knots. See Section 5, Performance for landing
distance in the flaps 20° configuration. Engines do not go to high idle at
flaps 20°.
Continued on next page 

REVISION 28 ABNORMAL / EMERGENCY PROCEDURES

May 25/16 Page EE - 3
 Quick Reference Handbook
Flight Control Runaway To Hardover Position, ctd… AFM 4-15-20

For Approach and Landing, plan a wide, power-on approach.

Once established:
4. Flaps ........................................................................................... 20°
5. GPWS / GND SPLR FLAP ORIDE ............................................ ON
6. Airstart Ignition ........................................................................... ON
7. Landing Gear ..................................................... DOWN / 3 GREEN
8. Nutcracker .............................................................................. TEST
9. WARN INHIBIT ........................................................................... ON
10. Flap Position ................................................................. VERIFY 20°
11. VREF ................................. APPROPRIATE TO CONFIGURATION
Landing:
NOTE: Left and right thrust reversers, nose wheel steering and normal
antiskid braking will be available. Speed brakes and ground spoilers will
not be available.
12. Thrust Reversers ................................... DEPLOY / AS REQUIRED
13. Braking ....................................................................AS REQUIRED

END

Immovable Flight Controls AFM 4-15-30

Rudder Control (Yaw):

1. Flight Power Shutoff Handle ................................... DO NOT PULL
UNLESS COUPLED WITH SINGLE-ENGINE EMERGENCY
Aileron Control (Roll):
2. Flight Power Shutoff Handle................................................... PULL

Continued on next page 

ABNORMAL / EMERGENCY PROCEDURES REVISION 28

Page EE - 4 May 25/16
Quick Reference Handbook
Immovable Flight Controls, ctd… ...................................... AFM 4-15-30
Elevator Control (Pitch):
3. Flight Power Shutoff Handle ................................................... PULL
NOTE: If the Flight Power Shutoff Handle is pulled at rotation due to a
flight control problem, high pull forces will be required to achieve the
takeoff attitude. There will be a delay in airplane rotation and, once
airborne, a push force will be necessary to maintain the climb attitude.
Application of forward trim will be required shortly after becoming
airborne. To avoid running out of forward trim, reduce speed as
necessary.
NOTE: Use only lateral and longitudinal trim after pulling Flight Power
Shutoff Handle. Disengage yaw damper. Return directional trim to the
neutral position prior to restoring hydraulic boost to flight control. If control
is not regained in manual mode, return hydraulic boost to flight controls.
NOTE: If yaw damper disengages as result of pulling Flight Power
Shutoff Handle, do not attempt to re-engage it until hydraulic pressure
has been restored to flight controls.
Continue flight to nearest suitable airport and land.
NOTE: Select a runway that is at least 7,000 feet long and 150 feet
wide. Minimize crosswind component to less than 5 knots.
NOTE: If the flight crew elects to land at flaps 20°, fly the approach at
VREF for 20° flaps +10 knots. See Section 5, Performance for landing
distance in the flaps 20° configuration. Engines do not go to high idle at
flaps 20°.
For Approach and Landing, plan a wide, power-on approach.
Once established:
4. Flaps ........................................................................................... 20°
5. GPWS / GND SPLR FLAP ORIDE ............................................. ON
6. Airstart Ignition ............................................................................ ON
7. Landing Gear ..................................................... DOWN / 3 GREEN
8. Nutcracker .............................................................................. TEST
9. WARN INHIBIT ........................................................................... ON
10. Flap Position ................................................................. VERIFY 20°
11. VREF .................................. APPROPRIATE TO CONFIGURATION

Continued on next page 

REVISION 28 ABNORMAL / EMERGENCY PROCEDURES

May 25/16 Page EE - 5
 Quick Reference Handbook
Immovable Flight Controls, ctd… ..................................... AFM 4-15-30
Landing:
NOTE: Left and right thrust reversers, nose wheel steering and normal
antiskid braking will be available. Speed brakes and ground spoilers will
not be available.
12. Thrust Reversers ................................... DEPLOY / AS REQUIRED
13. Braking ....................................................................AS REQUIRED

END

Stall Barrier Malfunction AFM 4-15-40

In the event of unwanted stall barrier actuation:

1. Autopilot Disengage Button ............................. PRESS AND HOLD
2. Stall Barrier Switch ................................................................... OFF
3. Autopilot Disengage Button ............................................. RELEASE
4. Determine failed stall barrier system and disable by pulling the
appropriate STALL WARN CMPTR circuit breaker (#1: CPO, A-
11; #2: CPO, B-11.)
5. Stall Barrier Switch ........................ON (PROCEED WITH FLIGHT)

END

ABNORMAL / EMERGENCY PROCEDURES REVISION 28

Page EE - 6 May 25/16
Quick Reference Handbook
Ground Spoiler Failure AFM 4-15-50

IN FLIGHT:
If the GND SPOILER message illuminates:
1. Ground Spoiler Arming Switch ................................................. OFF
2. GND SPOILER Circuit Breaker (CPO, C-6) ........................... PULL
DURING LANDING:
If NO GND SPOILER light illuminates (remains ON) after landing
touchdown (GND SPOILERS ARMED):
1. Speed Brakes .......................................... DEPLOY IMMEDIATELY
NOTE: ACFT CONFIGURATION message may illuminate and warning
tone may sound momentarily.
NOTE: NO GND SPOILER light may light momentarily after touchdown,
and then go out again, in less than one (1) second. This is the normal
sequence of events as the ground spoilers go through their automatic
deployment process. Wheel spin up logic should preclude this occurrence.
If light remains ON after touchdown, the above procedure applies.

END

Runaway Electric Pitch Trim AFM 3-15-60

In the event of runaway electric pitch trim:

1. Autopilot Disconnect Button ............................ PRESS AND HOLD
If electric trim is disabled while switch is held:
2. Electric Pitch Trim ....................................................... DISENGAGE
3. Autopilot Disconnect Button ............................................RELEASE
4. Manual Pitch Trim Wheel .................................... USE TO RETRIM
NOTE: Subsequent attempts to engage the autopilot will result in
automatic re-engagement of electric trim.
Alternate Procedure:
1. Manual Pitch Trim Wheel ................................ GRASP AND HOLD
2. Electric Pitch Trim ....................................................... DISENGAGE
NOTE: Subsequent attempts to engage the autopilot will result in
automatic re-engagement of electric trim.

END

REVISION 28 ABNORMAL / EMERGENCY PROCEDURES

May 25/16 Page EE - 7
 Quick Reference Handbook
Frozen Pitch Trim AFM 3-15-70

NOTE: If either or both FGCs have “hard failed” due to frozen trim, pull and
reset both FGC CBs (FGC #1: CPO, A-7; FGC #2: CPO, B-7).
If frozen pitch trim is suspected:
1. Autopilot Disconnect Button ............................ PRESS AND HOLD
2. Electric Pitch Trim ...................................................... DISENGAGE
3. Attempt to free trim with firm application of fore and aft pressures
on the pitch trim wheel.
CAUTION: DO NOT USE EXCESSIVE FORCE AS THE PITCH
TRIM SYSTEM IS PROTECTED BY A SHEAR PIN DESIGNED TO
BREAK IF EXCESSIVE FORCE IS APPLIED. IF THE PIN IS SHEARED,
FUTURE USE OF PITCH TRIM WILL NOT BE POSSIBLE.
If the pitch trim cannot be freed and descent to warmer altitude is
not feasible:
4. Maintain current trimmed airspeed while in cruise flight. If climbs
or descents are necessary, disconnect autopilot and manually fly
the airplane to new altitude. Determine trim airspeed for new
altitude, adjust power as required. Engage autopilot if desired.
5. If possible, descend to warmer altitude before attempting any
configuration changes.
When below 20,000 ft. MSL:
6. Attempt to free trim using electric pitch trim switches. If unable,
turn pitch trim OFF and re-attempt to free trim using firm pressure
on pitch trim wheel.
If trim cannot be freed, plan to approach and land with current trim
setting. Normal cruise trim is approximately zero (0) units while
approach trim is typically 12 to 14 units nose up. Yoke pull force is
not excessive with pitch trim at zero (0) and the airplane in
landing configuration. Speed and configuration should be
adjusted to give the best balance of approach speed and control
forces for airport and weather conditions.
CAUTION: CARE SHOULD BE TAKEN WHEN CHANGING
CONFIGURATION TO AVOID RAPID CONTROL FORCE BUILD-UP.

END

ABNORMAL / EMERGENCY PROCEDURES REVISION 28

Page EE - 8 May 25/16
Quick Reference Handbook

Failure of Stabilizer / Flap Interconnect AFM 3-14-10

1. Further Flap Movement ......................................................... STOP

2. Land as soon as practicable; if further flight is necessary, match
flaps to stabilizer position and observe appropriate placard speed.
3. GPWS / GND SPLR FLAP ORIDE ............................................. ON
4. For Landing:
STABILIZER FAILED AT 20° or 39° POSITION:
Match flaps to stabilizer position. If appropriate, see Partial or
Jammed Flaps Landings, page EE-11. If runway length is
limited and the stabilizer is in 20° position, then 39° flaps may be
used for landing. In that condition, use full nose up elevator trim
as required and expect heavy pull forces on final approach and
during landing.
STABILIZER FAILED AT 0° or 10° POSITION
Match flaps to stabilizer position. See Partial or Jammed Flaps
Landings, page EE-11. If runway length is limited, 20° flaps may
be used for landing. In that condition, use full nose up elevator
trim as required and expect heavy pull forces on final approach
and during landing.

END

REVISION 28 ABNORMAL / EMERGENCY PROCEDURES

May 25/16 Page EE - 9
 Quick Reference Handbook
Flaps - Alternate Operation AFM 3-14-20

CAUTION: IF OPERATING (COMBINED OR UTILITY) HYDRAULIC

PRESSURE READS ZERO IMMEDIATELY AFTER SELECTING FLAPS,
PULL BOTH THE FLAP CONT (CPO, B-1) AND THE MANUAL FLAP CONT
(CPO, A-1) CIRCUIT BREAKERS BEFORE TURNING ON AUXILIARY
HYDRAULIC PUMP. THIS WILL ENSURE THAT AUXILIARY SYSTEM
FLUID WILL BE AVAILABLE FOR BRAKING AFTER LANDING.
NOTE: When using the emergency flap control, the AOA indication on the
PFDs will be invalid (Red X). The stall barrier system (shake and push) will
continue to function normally (two systems). When 39° flaps is selected, the
"STALL BARR 1 FL" message will be displayed on CAS. Pull the STALL
WARN CMPTR CB (CPO, A-11). The stall barrier system will be single
system operation with the operative stall warning computer providing normal
shake and push functions.
To use the Emergency Flap Control, proceed as follows:
1. Flap Lever ...............................................................AS REQUIRED
2. Auxiliary Hydraulic Pump ............................... ON (IF REQUIRED)
NOTE: Do NOT engage autopilot when using emergency flaps unless
flap deflection is 10° or greater.
3. Emergency Flap Switch ..................................................... EMERG
NOTE: Activating the Emergency Flap switch will cause a FLAP INPUT
INVALID message on the FMS CDU, the speed target will become
invalid, VREF will no longer be displayed on the display controller or PFD
speed tape and the autothrottle will disengage.
4. Emergency Flap Control .................................................................
.................................... PUSH OR PULL (EXTEND OR RETRACT)
When flaps attain desired position:
5. Emergency Flap Control .................................................NEUTRAL
CAUTION: IN ORDER TO GUARD AGAINST THE REMOTE
POSSIBILITY OF ASYMMETRY PROTECTION FAILURE WHEN USING
EMERGENCY FLAP CONTROL, OBSERVE THAT NO AIRPLANE
ROLL IS PRESENT INDICATING FLAP ASYMMETRY. IF ASYMMETRY
IS INDICATED, RETURN FLAPS TO THEIR PREVIOUSLY SELECTED
POSITION.

END

ABNORMAL / EMERGENCY PROCEDURES REVISION 28

Page EE - 10 May 25/16
Quick Reference Handbook
Partial Or Jammed Flaps Landings AFM 3-14-30

If landing at a reduced flap setting is unavoidable, plan a wide

approach, select Airstart Ignition ON, and select the longest
available runway.
Once established:
1. VREF.................................. APPROPRIATE TO CONFIGURATION
Observe VREF speed appropriate to configuration as shown in
Performance Section for landing distance.
2. GPWS/GND SPLR FLAP ORIDE ............................................... ON
NOTE: Set FLAP ORIDE switch to prevent nuisance message.
Landing with less than full flaps negates ground spoiler deployment
as result of wheel spin-up unless the GPWS / GND SPLR FLAP
ORIDE switch is selected ON before landing. Ground spoiler
deployment as result of weight-on-wheels should be normal.
3. Air Start Ignitions ........................................................................ ON
4. Touchdown Ground Speed ........................ 182 KNOTS MAXIMUM
CAUTION: TIRE SPEED LIMITATIONS WILL BE EXCEEDED IF
TOUCHDOWN IS MADE IN EXCESS OF 182 KNOTS GROUND
SPEED. (195 KNOTS GROUND SPEED SN 1214 AND SUBS., AND SN
1000 THRU 1213 WITH ASC 190.)
NOTE: If landing at less than 39° flaps, See Performance for landing
distances.

END

Uncommanded Flap Movement AFM 3-14-40

In the event of uncontrolled flap movement:

1. Emergency Flap Switch ...................................................... EMERG
2. Emergency Flap Control ..................................................................
.................................... PUSH OR PULL (EXTEND OR RETRACT)
3. MANUAL FLAP CONT Circuit Breaker (CPO, A-1) ............... PULL
NOTE: With MANUAL FLAP CONT circuit breaker pulled, flaps are
inoperative. Emergency flap control may be regained by resetting MANUAL
FLAP CONT circuit breaker and operating the Emergency Flap Control.

END

REVISION 28 ABNORMAL / EMERGENCY PROCEDURES

May 25/16 Page EE - 11
 Quick Reference Handbook
Flaps Lock Up While Moving / Fail To Move AFM 3-14-50

In the event that flaps stop moving while in motion or flaps fail to
move when commanded, proceed as follows:
1. Speed ............................... REDUCE AT LEAST 10 KNOTS FROM
SPEED AT TIME OF LOCKUP; MAINTAIN AT LEAST 10 KNOTS
BELOW VFE FOR SELECTED / DESIRED FLAP SETTING
2. Flaps .................................................................................. SELECT
BACK TO PREVIOUS SETTING (REVERSE DIRECTION)
3. Normal Flap Operation ....................................................................
............... RESUME ONCE FLAPS REACH SELECTED SETTING
4. Flap Limit Speed (VFE) ................................................... OBSERVE
If flaps fail to respond:
5. Partial Flaps Landing..................................................... PERFORM
See Partial or Jammed Flaps Landings, page EE-11.

END

Autopilot Malfunction AFM 3-03-10

If the autopilot malfunctions, disengage autopilot as follows:

1. Autopilot Disengage Button (Either Pilot’s Control Wheel) .............
............................................................... PRESS (MOMENTARILY)
The autopilot may also be disengaged by any of the following:
2. Autopilot "ON" Capsule (Guidance Panel) .......................... PRESS
3. Electric Elevator Trim Switch...........................................ACTUATE
4. Either Go-Around (G/A) Button ........................................... PRESS
CAUTION: THE AUTOTHROTTLE, IF ENGAGED WHEN THE G/A
BUTTON IS PRESSED, WILL INCREASE POWER TO G/A EPR.
If a flight guidance computer fails, the second computer will
continue to control airplane. A failure of the second computer will
disconnect the autopilot.
In the event that above methods fail, the autopilot may be
overpowered by the pilot.

END

ABNORMAL / EMERGENCY PROCEDURES REVISION 28

Page EE - 12 May 25/16
Quick Reference Handbook
Autothrottle Malfunction AFM 3-03-20

Disengage the autothrottle as follows:

1. Activating either momentary action engage/disengage thumb
lever located on the power levers.
2. Activating either mechanical disengagement button located on the
front of the power lever knobs.
3. Deselecting the autothrottle ARM button on the guidance panel.

END

AFGCS Failure AFM 3-03-30

Fail Operational: If monitors detect a failure condition within a flight

guidance computer, the failed computer will be shut down and control
of the airplane will be transferred to the remaining computer.
Fail Passive: If the airplane is being controlled by the second flight
guidance computer, after a single failure, and that computer fails, the
autopilot will disengage.

END

Mach Trim Compensation Failure AFM 3-03-40

1. Pitch Trim Switch ........................................................ DISENGAGE

NOTE: Since electric elevator trim is not available, the manual
trim wheel must be used.
2. MMO .................................................................... LIMIT TO 0.75 MT
CAUTION: WHEN OBSERVING MMO OF 0.75 MT, CLOSELY
MONITOR AIRSPEED TO AVOID EXCEEDING 0.75 MT.

END

REVISION 28 ABNORMAL / EMERGENCY PROCEDURES

May 25/16 Page EE - 13
 Quick Reference Handbook
Yaw Damper Failure AFM 3-03-50

The yaw damper is powered by the flight hydraulic system. If the right
engine has failed but is windmilling, flight system hydraulic pressure
will remain at approximately 3000 psi and will power the yaw damper.
Should the right engine failure prevent windmilling, the yaw damper
should be selected OFF. The YAW DAMPER OFF message
illuminates if the yaw damper is OFF.
If the yaw damper fails in flight:
With the yaw damper inoperative, maintain at least 220 KCAS above
18,000 ft.
Below 18,000 ft., maintain airspeed, as function of fuel quantity, at or
above that shown in the following table until ready to configure the
airplane for approach and landing.

Fuel Quantity - 1000 lb 8 10 12 14 16 18 20 22 24 26 28 30

Min. Airspeed - KCAS 96 107 117 126 135 143 151 158 165 172 178 184

When yaw damper failure is coupled with failure of mach trim

compensation, observe speed limitations for both failures and limit
altitude to 41,000 ft.
NOTE: If practical, land at fuel weight of less than 9,000 lb (4,082 kg).
Landing at lower fuel weights will improve dutch roll stability. Avoid flight into
known areas of moderate or greater turbulence.
If the yaw damper fails on the ground:
If the yaw damper fails on the ground, maximum fuel quantity
permitted for takeoff is 9,000 lb (4,082 kg).

END

ABNORMAL / EMERGENCY PROCEDURES REVISION 28

Page EE - 14 May 25/16
Quick Reference Handbook
Fuel / Hydraulics Index
Hydraulic System Diagram ........................................................... EF-2
Fuel System Diagram ................................................................... EF-3
Dual Hydraulic System Failure ................................................. EF-4
Combined Hydraulic System and Auxiliary Hydraulic System
Loss of Fluid ............................................................................... EF-6
Combined Hydraulic System Failure – Loss of Pressure and Fluid .......
..................................................................................................... EF-8
Combined Hydraulic System Failure – Loss of Pressure Only .... EF-10
Flight Hydraulic System Failure – Loss of Pressure and / or Fluid ........
................................................................................................ EF-11
Landing With Standby Electrical Power System Operating ....... EF-12
Master Table Of Hydraulic Component Availability .................... EF-13
Fuel Leak In Flight .................................................................... EF-14
Fuel Boost Pump Failure ............................................................ EF-17
Failure of Two Boost Pumps on One Side ................................. EF-18
Permissible Fuel Imbalance for All Flight Operations ................ EF-19

Related Topics In QRH

Engine Failure / Shutdown In Flight ......................................... EC-8
One (1) Engine Inoperative Landing Procedure .................... EC-14
Yaw Damper Failure................................................................... EE-14

REVISION 28 ABNORMAL / EMERGENCY PROCEDURES

May 25/16 Page EF - 1
 Quick Reference Handbook
Hydraulic System Diagram

ABNORMAL / EMERGENCY PROCEDURES REVISION 28

Page EF - 2 May 25/16
Quick Reference Handbook
Fuel System Diagram

REVISION 24 (RE-ISSUE) ABNORMAL / EMERGENCY PROCEDURES

Mar 17/10 Page EF - 3
 Quick Reference Handbook

Dual Hydraulic System Failure AFM 4-17-10

Continue flight to nearest suitable airport and land.

1. Altitude .................................. ESTABLISH 25,000 FT OR BELOW
2. Airspeed ................................ MAINTAIN 250 KCAS OR SLOWER
3. Yaw Damper............................................................................. OFF
NOTE: This action disengages the autopilot if previously engaged.
For approach and landing, plan a wide, power-on approach. Once
established:
4. AUX Pump .................................................................................. ON
5. Flaps ........................................................................................... 20°
6. Airstart Ignition ........................................................................... ON
7. Landing Gear Handle ........................................................... DOWN
8. Airspeed ..................................... MAINTAIN 175 KCAS MAXIMUM
9. EMER Landing Gear T-Handle .............................................. PULL
CAUTION: DO NOT RESET EMER GEAR HANDLE OR
DUMP VALVE FOR REMAINDER OF FLIGHT.
10. Landing Gear ..................................................... DOWN / 3 GREEN
11. Flaps Position ............................................................... VERIFY 20°
12. VREF ................................. APPROPRIATE TO CONFIGURATION
13. GPWS / GND SPLR FLAP ORIDE ............................................ ON
Select the ORIDE switch to ON if landing with flaps less than 22
degrees. This prevents the nuisance “TOO LOW FLAPS” aural
alerts and provides backup capability to deploy the ground
spoilers with wheel spin-up.
NOTE: During approach and landing, the GROUND SPOILER message
may be displayed on the CAS during flap extension. This is due to spoiler
float and is considered normal.

Continued on next page 

ABNORMAL / EMERGENCY PROCEDURES REVISION 24 (RE-ISSUE)

Page EF - 4 Mar 17/10
Quick Reference Handbook
Dual Hydraulic System Failure, ctd… AFM 4-17-10

Prior To Touchdown:
CAUTION: ENSURE THAT THE FLAPS HAVE REACHED THE 20°
POSITION PRIOR TO TOUCHDOWN. IF FLAPS ARE STILL IN TRANSIT,
DELAY THE LANDING UNTIL THE FLAP MOVEMENT HAS STOPPED. IF
UNABLE TO DELAY THE LANDING, PULL THE MANUAL FLAP CONT
CIRCUIT BREAKER (CPO, A-1) TO STOP FLAP MOVEMENT. LANDING WITH
THE FLAPS IN MOTION DRIVEN BY THE AUXILIARY HYDRAULIC PUMP
WILL CAUSE A LOSS OF BRAKES DURING THE LANDING ROLLOUT.
Landing:
NOTE: Thrust reversers and ground spoilers will be inoperative after
touchdown.
14. Brakes and Rudder ............. MAINTAIN DIRECTIONAL CONTROL
With both hydraulic systems failed, braking pressure will be
supplied by the AUX hydraulic system. If AUX hydraulic system
pressure is lost, the PARK / EMERG brake must be used. Antiskid
will be inoperative when using the PARK / EMERG brake. See
Anti-Skid Off Braking (HMAB), page EB-8 and Emergency
Brakes (HMAB), page EB-3.
15. Landing Gear Safety Pins ..................................................INSTALL
CAUTION: GEAR PINS SHALL BE INSTALLED PRIOR TO
RESETTING DUMP-VALVE.

END

REVISION 24 (RE-ISSUE) ABNORMAL / EMERGENCY PROCEDURES

Mar 17/10 Page EF - 5
 Quick Reference Handbook
Combined Hydraulic System and Auxiliary Hydraulic
System Loss of Fluid AFM 4-17-70

Continue flight to the nearest suitable airport and land.

CAUTION: TO VERIFY THE AVAILABILITY OF THE AUXILIARY
SYSTEM FLUID, SELECT THE AUX PUMP ON FOR A MINIMUM OF 30
SECONDS AND CHECK FOR AUXILIARY SYSTEM PRESSURE. IF
PRESSURE CAN BE MAINTAINED, ASSUME THAT THE AUXILIARY
SYSTEM IS AVAILABLE AND PROCEED TO Combined Hydraulic System
Failure – Loss of Pressure and Fluid, PAGE EF-8.
CAUTION: STALL BARRIER PROTECTION IS NOT AVAILABLE WITH
LOSS OF COMBINED HYDRAULIC SYSTEM FLUID.
In case of complete fluid loss to the Combined Hydraulic System
and the Auxiliary Hydraulic System, proceed as follows:
1. Utility Pump ..................................................................... NOT ARM
2. AUX PUMP ..................................................................CHECK OFF
Approach:
Select a runway that is at least 7000 feet long and 150 feet wide.
Minimize crosswind component to less than 5 knots if possible. If
crosswind is present, plan the landing on the downwind side, as the
airplane will weather vane into the wind as rudder effectiveness is lost.
Plan a shallow approach to land within the first 1000 feet of the runway.
3. GPWS / GND SPLR FLAP ORIDE ................. ON / AS REQUIRED
Select the ORIDE switch to ON if landing with flaps less than 22
degrees. This prevents the nuisance “TOO LOW FLAPS” aural
alerts.
4. NWS POWER ........................................................................... OFF
5. Airspeed .......................................................... 175 KCAS OR LESS
6. Landing Gear Handle ............................................................ DOWN
7. Emergency Landing Gear Handle ...........................................PULL
8. Landing Gear Position ....................................... DOWN / 3 GREEN
9. Anti-Skid.................................................................................... OFF
10. Ground Spoiler .......................................................................... OFF
Continued on next page 

ABNORMAL / EMERGENCY PROCEDURES REVISION 24 (RE-ISSUE)

Page EF - 6 Mar 17/10
Quick Reference Handbook
Combined Hydraulic System and Auxiliary Hydraulic System Loss
of Fluid, ctd… ...................................................................... AFM 4-17-70
11. Brakes System Page (SPZ 8400)...................................... SELECT
12. VREF ............................... APPROPRIATE FOR CONFIGURATION
Observe VREF speed appropriate to configuration as shown in
GIV AFM Section 5.11 Final Approach and Landing:
Approach Speed For Landing Distance (VREF).
Landing:
After landing, deploy the right thrust reverser as required to slow the
airplane, maintaining aerodynamic directional control with the rudder.
Aerodynamic control will not be available below 60 knots and will
begin diminishing around 80 knots. Depending on winds, runway
crown, etc, the airplane may veer as rudder effectiveness is lost. The
right thrust reverser may mitigate a veer to the left. A slight thrust
increase on the right engine (forward thrust) may mitigate a veer to
the right but with a corresponding increase in landing roll. In
either case, cautious application of reverse or forward thrust (if
required) should only be considered if a runway departure is likely.
13. Speed Brakes .............................................................. EXTENDED
14. Right Thrust Reverser ...........................DEPLOY / AS REQUIRED
CAUTION: IT IS NORMAL FOR DECELERATION TO INCREASE AS
THE STOP PROGRESSES. THIS MAY RESULT IN LOCKED WHEELS
AND BLOWN TIRES. REDUCE PRESSURE AS REQUIRED TO MAIN-
TAIN CONSTANT DECELERATION. THERE WILL BE A SIGNIFICANT
INCREASE IN LANDING DISTANCE WITH ANTI-SKID INOPERATIVE.
15. Park / Emergency Brake ... AS REQUIRED TO MAINTAIN 400 PSI
Slowly apply Park / Emergency Brake, increasing pressure to 400
PSI. However, it may be necessary to exceed this pressure in
order to stop the airplane on the runway. The pilot should devote
his attention to airplane control and brake application, while the
copilot should monitor applied brake pressure, advising the pilot
of corrections required to maintain optimum brake pressure.
After Landing:
16. Landing Gear Safety Pins ..................................................INSTALL
CAUTION: GEAR PINS SHALL BE INSTALLED PRIOR TO
RESETTING DUMP VALVE.

END

REVISION 26 ABNORMAL / EMERGENCY PROCEDURES

Oct 5 2011 Page EF - 7
 Quick Reference Handbook
Combined Hydraulic System Failure – Loss of
Pressure and Fluid AFM 3-17-30

Continue flight to the nearest suitable airport and land.

CAUTION: TO VERIFY THE AVAILABILITY OF THE AUXILIARY
SYSTEM FLUID, SELECT THE AUX PUMP ON FOR A MINIMUM OF 30
SECONDS AND CHECK FOR AUXILIARY SYSTEM PRESSURE. IF
PRESSURE CANNOT BE MAINTAINED, ASSUME THAT THE AUXILIARY
SYSTEM IS NOT AVAILABLE AND PROCEED TO Combined Hydraulic
System and Auxiliary Hydraulic System Loss of Fluid, PAGE EF-6.
CAUTION: STALL BARRIER PROTECTION IS NOT AVAILABLE WITH
LOSS OF COMBINED HYDRAULIC SYSTEM FLUID.
1. Hydraulic Synoptic / Quantity ........................... DISPLAY / CHECK
2. Utility Pump .................................................................... NOT ARM
If a hydraulic leak in the flaps system is not suspected, proceed
to Step 4. Otherwise, disable flaps by performing Step 3:
3. Manual Flap Control CB (CPO A-1) ....................................... PULL
4. AUX PUMP Switch ..................... SELECT ON FOR 30 SECONDS
The only way to verify availability of Auxiliary System fluid is to
select the AUX pump on and observe that pressure can be
maintained.
If loss of Combined System fluid and Auxiliary System fluid is
suspected or has occurred, see Combined Hydraulic System and
Auxiliary Hydraulic System Loss of Fluid, page EF-6.
For approach and landing:
5. AUX Pump.................................................................................. ON
6. Flap Handle (If CBs Not Pulled In Step 3) ................................. 20°
20° flaps should be planned for approach and landing.
NOTE: Flap extension from UP (0°) to 20° will take at least one
(1) minute.
7. Airstart Ignition ........................................................................... ON
8. Landing Gear Handle ........................................................... DOWN
9. Airspeed ......................................................... 175 KCAS OR LESS
10. EMER Landing Gear Handle .................................................. PULL
CAUTION: DO NOT RESET EITHER THE EMER GEAR HANDLE OR
DUMP VALVE PRIOR TO LANDING.
Continued on next page 

ABNORMAL / EMERGENCY PROCEDURES REVISION 26

Page EF - 8 Oct 5 2011
Quick Reference Handbook
Combined Hydraulic System Failure – Loss of Pressure and
Fluid, ctd… AFM 3-17-30

11. Landing Gear ..................................................... DOWN / 3 GREEN

12. Flap Position (If Available) ............................................ VERIFY 20°
13. VREF .................................. APPROPRIATE TO CONFIGURATION
Plan a wide approach and observe VREF speed appropriate to
configuration as shown in GIV AFM Section 5.11 Final
Approach and Landing: Approach Speed For Landing
Distance (VREF).
Prior to touchdown:
CAUTION: ENSURE THAT THE FLAPS HAVE REACHED THE 20°
POSITION PRIOR TO TOUCHDOWN. IF FLAPS ARE STILL IN TRANSIT,
DELAY THE LANDING UNTIL THE FLAP MOVEMENT HAS STOPPED. IF
UNABLE TO DELAY THE LANDING, PULL THE MANUAL FLAP CONT
CIRCUIT BREAKER TO STOP FLAP MOVEMENT. LANDING WITH THE
FLAPS IN MOTION DRIVEN BY THE AUXILIARY HYDRAULIC PUMP WILL
CAUSE A LOSS OF BRAKES DURING THE LANDING ROLLOUT.
14. GPWS/GND SPLR FLAP ORIDE ............................................... ON
Select the ORIDE switch to ON if landing with flaps less than 22
degrees. This prevents the nuisance “TOO LOW FLAPS” aural
alerts and provides backup capability to deploy the ground
spoilers with wheel spin-up.
15. Nutcracker ................................................................................. Test
16. Ground Spoilers ................................................................... ARMED
CAUTION: TIRE SPEED LIMITATIONS WILL BE EXCEEDED
IF TOUCHDOWN IS MADE IN EXCESS OF 182 KNOTS (SN 1000-1213
W/O ASC 190) OR 195 KNOTS GROUND SPEED.
Landing:
17. Brakes / Rudder ................................................................................
............... AS REQUIRED TO MAINTAIN DIRECTIONAL CONTROL
18. Right Thrust Reverser ............................................ AS REQUIRED
NOTE: The left thrust reverser will not deploy.
19. Landing Gear Safety Pins ..................................................INSTALL
CAUTION: GEAR PINS SHALL BE INSTALLED PRIOR TO
RESETTING DUMP VALVE.

END

REVISION 30 ABNORMAL / EMERGENCY PROCEDURES

Oct 30/17 Page EF - 9
 Quick Reference Handbook
Combined Hydraulic System Failure – Loss of
Pressure Only AFM 3-17-40

Continue flight to the nearest suitable airport and land.

1. Hydraulic Synoptic / Quantity ........................... DISPLAY / CHECK
2. UTILITY HYD PUMP Switch ........................................... NOT ARM
For approach and landing:
3. UTILITY HYD PUMP Switch ...................................................... ON
NOTE: For gear and flap operation after takeoff or during approach,
operate one system at a time allowing completion of cycle before
operating system, for example:
 Raise gear first, then retract flaps after gear is up after takeoff.
 Allow flaps to reach 20° before lowering gear for approach and landing.
4. Aux Hydraulic Pump ................................................................... ON
5. Flaps ........................................................................................... 20°
6. Landing Gear ..................................................... DOWN / 3 GREEN
7. Flaps ........................................................................................... 39°
8. Ground Spoiler ................................................................... ARMED
9. Crew Alerting System .......................................................... CHECK
10. PF Feet Position on Rudder Pedals ............... HEELS OFF FLOOR
Landing
11. Brakes / Steering .............................................................................
..............AS REQUIRED TO MAINTAIN DIRECTIONAL CONTROL
12. Right Thrust Reverser .............................................AS REQUIRED
NOTE: The left thrust reverser will not deploy.

END

ABNORMAL / EMERGENCY PROCEDURES REVISION 30

Page EF - 10 Oct 30/17
Quick Reference Handbook
Flight Hydraulic System Failure – Loss of Pressure
and / or Fluid AFM 3-17-50

Continue flight to the nearest suitable airport and land.

With a loss of Flight Hydraulic System fluid, the right engine shut
down, the right engine FIRE handle pulled or right (flight) hydraulic
pump failed, there is little degradation of performance. The only
component not available is the right thrust reverser.
In the event of flight system failure:
1. YAW DAMPER ......................................................................... OFF
NOTE: This action disengages the autopilot if previously
engaged.
2. UTILITY HYD PUMP Switch............................................NOT ARM
For approach and landing:
3. AUX PUMP ................................................................................. ON
NOTE: For gear and flap operation after takeoff or during approach,
operate one system at a time allowing completion of cycle before
operating system, for example:
 Raise gear first, then retract flaps after gear is up after takeoff.
 Allow flaps to reach 20° before lowering gear for approach and landing.
4. Approach and Landing ................. ALLOW FLAPS TO REACH 20°
BEFORE SELECTING LANDING GEAR DOWN
5. Landing Gear ..................................................... DOWN / 3 GREEN
6. Flaps ........................................................................................... 39°
7. Ground Spoilers .................................................................. ARMED
8. Crew Alerting System ..........................................................CHECK
9. PF Feet Position on Rudder Pedals ...............HEELS OFF FLOOR
Landing:
10. Brakes / Steering ............................................................................
............ AS REQUIRED TO MAINTAIN DIRECTIONAL CONTROL
11. Left Thrust Reverser ............................................. AS REQUIRED
NOTE: The right thrust reverser will not deploy.

END

REVISION 30 ABNORMAL / EMERGENCY PROCEDURES

Oct 30/17 Page EF - 11
 Quick Reference Handbook

Landing With Standby Electrical Power System

Operating AFM 3-17-60

NOTE: If standby electrical power is interrupted during the following steps,

cycle the STANDBY ELECTRICAL POWER switch OFF, then ON.
1. Landing Gear........................................................................ DOWN
2. Flaps ................................................................ SET FOR LANDING
3. PF Feet Position on Rudder Pedals ............... HEELS OFF FLOOR
4. Emergency Batteries .................................................................. ON
5. Ground Spoilers ....................................................................... OFF
6. HP RPM ............ MAINTAIN 67% HP RPM UNTIL TOUCHDOWN
NOTE: Once the airplane is on the ground, there is no need to continue
to maintain 67% HP RPM. The standby electrical system should stay on
line during normal taxi maneuvers. If standby electrical power is
interrupted, cycle the STANDBY ELECTRICAL POWER switch OFF,
then ON to regain power.
7. DO NOT use reverse thrust.
8. On touchdown, manually deploy the flight spoilers at a slow rate
(approximately 5 seconds).
9. Use normal braking to stop the airplane.

END

ABNORMAL / EMERGENCY PROCEDURES REVISION 30

Page EF - 12 Oct 30/17
Quick Reference Handbook
Master Table Of Hydraulic Component Availability GAC

System/Component: Hydraulic System:

COMB FLT UTIL AUX
Elevators X X
Stall Barrier X X
Ailerons X X
Speed Brakes X X
Flight Spoilers X X
1
Ground Spoilers X X
Rudder X X
Yaw Damper X
Left Thrust Reverser X
Right Thrust Reverser X
Utility Pump Motor X
Wing Flaps X X X
2
Landing Gear & Doors X X X
Nosewheel Steering X X
Brakes X X X
SEP System Motor X
Parking Brake Pressure X
Main Entrance Door X
1
If servo pressure signal from COMB, UTIL or AUX is present.
2
Ground use only, using ground service valve.

REVISION 28 ABNORMAL / EMERGENCY PROCEDURES

May 25/16 Page EF - 13
 Quick Reference Handbook
Fuel Leak In Flight AFM 4-16-10

A suspected fuel leak will most likely manifest itself as an increasing

difference in fuel quantity that cannot be explained by normal differ-
ences in fuel flows between engines. It can also be identified by fuel
smell in the cabin, abnormally high fuel flow or fuel flow out of range
“dashed” indications on one of the engines, or lateral trim changes.
CAUTION: DO NOT PERFORM THIS PROCEDURE ON THE BASIS
OF ERRATIC FUEL GAUGE INDICATIONS ONLY OR DURING
ASYMMETRIC TRIM REQUIREMENTS FELT DURING ACCELERATING
PHASES OF FLIGHT SUCH AS INITIAL CLIMB OR NOSE HIGH OR NOSE
LOW PITCH ATTITUDES.
1. Fuel Crossflow Valve .........................................................CLOSED
2. Fuel Intertank Valve ..........................................................CLOSED
3. FMS Single Engine Performance / Range .......................... CHECK
Monitor fuel tank quantities and lateral trim requirements. Identify leak
by observing one wing fuel tank quantity decreasing faster than the
other, and or slowly increasing lateral trim force.
If fuel leakage is visible from wing tank, proceed to Step 15.
If fuel leakage is not visible from wing tank, it must be deter-
mined if the fuel leak is coming from the wing tank or from the
engine/ engine feed system. Descend to 15,000 feet and proceed
as follows:
WARNING: THIS PROCEDURE MAY RESULT IN ENGINE FAILURE.
TERRAIN CLEARANCE AND AIRCRAFT SINGLE ENGINE PERFOR-
MANCE MUST BE TAKEN INTO CONSIDERATION.
Prepare airplane for possible engine failure but DO NOT SHUT
DOWN THE ENGINE. See Engine Failure / Shutdown In Flight,
page EC-8.
4. Non-Affected Side’s Power Lever .................. SET AS REQUIRED
5. Steady Flight ...........................................................ESTABLISHED
6. Affected Side’s Power Lever ................................................... IDLE
NOTE: The APU is fed by the boost pump manifold on the left wing
tank only. If boost pumps on left side are turned off, APU performance
may be erratic, and or not meet maximum altitude starting performance.
Continued on next page 

ABNORMAL / EMERGENCY PROCEDURES REVISION 28

Page EF - 14 May 25/16
Quick Reference Handbook
Fuel Leak In Flight, ctd… AFM 4-16-10

7. Affected Side’s MAIN and ALT Boost Pumps .......................... OFF

Wait two minutes. If the engine continues to run, the leak should be
assumed to be in the affected side wing fuel tank. Proceed to Step 15.
If the engine fails, runs erratically, or continues to run with extremely
high fuel flow or “dashed” fuel flow indications, the leak should be as-
sumed to be in the fuel feed system, somewhere between the boost
pumps and the engine. Proceed to Step 6.
8. Affected Engine’s HP FUEL COCK ....................................... SHUT
9. Affected Engine’s FIRE Handle (Do Not Rotate) .................... PULL
10. Engine Failure / Shutdown In Flight Checklist (Steps 5
and Subsequent – see page EC-8) ............................. COMPLETE
WARNING: DO NOT RESTART FAILED ENGINE, AS A
HIGH PROBABILITY OF ENGINE FIRE EXISTS.
11. Failed Side’s MAIN and ALT Boost Pumps ....... RECONFIRM OFF
12. Fuel Crossflow Valve ................................. RECONFIRM CLOSED
13. Fuel Intertank Valve ................................................ AS REQUIRED
Balance fuel by using the intertank valve and establishing a small
sideslip (approximately ½ trapezoid or ball width). Move the
rudder trim arrow in the direction of the tank from which you
desire to transfer fuel. This will create a slight wing-down
condition toward the tank to which you desire to transfer fuel.
14. Nearest Suitable Airport .........................................................LAND
See One (1) Engine Inoperative Landing Procedure, page EC-
14, if required.
Fuel Tank Leak:
15. Affected Side’s MAIN and ALT Boost Pumps ............................ ON
The flight crew must now evaluate the fuel loss rate and distance
to nearest suitable landing airfield. Consideration should be given
but is not limited to the following: two-engine vs. single-engine
climb to altitude in order to achieve greater range, maximum
transfer of fuel to good tank vs. lateral controllability, and affected
side engine failure due to fuel starvation.
NOTE: Up to 4000 lb. of fuel imbalance between tanks in flight has
been safely demonstrated while under abnormal conditions. For
approach and landing with abnormal fuel imbalance and an engine shut
down, be prepared to use full rudder and aileron as necessary.
Continued on next page 

REVISION 28 ABNORMAL / EMERGENCY PROCEDURES

May 25/16 Page EF - 15
 Quick Reference Handbook
Fuel Leak In Flight, ctd… AFM 4-16-10

16. Fuel Crossflow Valve ...............................................AS REQUIRED

17. Intertank Valve ........................................................AS REQUIRED
WARNING: IF INTERTANK VALVE IS USED FOR MAXIMUM FUEL
TRANSFER RATES, ENSURE PROPER SIDESLIP IS MAIN-TAINED TO
PREVENT FUEL FROM FLOWING BACK INTO LEAKING TANK.
18. Fuel Transfer to Good Side .....................INITIATE AS REQUIRED
19. Autopilot....................................................................DISCONNECT
20. Airspeed ..... AS REQUIRED TO MAINTAIN LATERAL CONTROL
CAUTION: IF IT BECOMES APPARENT THAT, PRIOR TO
LANDING, ENGINE ON LEAKING SIDE WILL FAIL DUE TO FUEL
STARVATION, SHUT DOWN ENGINE (SEE Engine Failure /
Shutdown In Flight, PAGE EC-8). OBSERVE AFM MAXIMUM FUEL
IMBALANCE LIMITS PRIOR TO LANDING (SEE Permissible Fuel
Imbalance For All Flight Operations, PAGE EF-19).
21. Nearest Suitable Airport ......................................................... LAND
See One (1) Engine Inoperative Landing Procedure, page EC-
14, if required.
WARNING: DO NOT USE THRUST REVERSERS ON LANDING.
END

ABNORMAL / EMERGENCY PROCEDURES REVISION 28

Page EF - 16 May 25/16
Quick Reference Handbook
Fuel Boost Pump Failure AFM 3-16-20

NOTE: Check position of circuit breakers on POP.

For a L (or R) ALT FUEL FAIL, or L (or R) MAIN FUEL FAIL
message on CAS:
1. Same Side Operative Fuel Boost Pump..................................... ON
2. Check fuel boost pump switch for "CB" indication.
3. If "CB" indication is not illuminated:
A. Fuel Boost Pump Switch ..................................................... OFF
B. Fuel BOOST PUMP Circuit Breaker (PDB) ....................... PULL
4. If "CB" indication is illuminated:
A. Fuel Boost Pump Switch ..................................................... OFF
B. Fuel BOOST PUMP Circuit Breaker (PDB) .................... RESET
CAUTION: RESET CB ONLY IF USE OF PUMP IN QUESTION
IS REQUIRED FOR CONTINUED SAFE FLIGHT AND LANDING.
5. If "CB" indication clears, continue normal operation and monitor
CAS. If the message repeats, switch inoperative fuel boost pump
OFF and verify that circuit breaker is open.

END

REVISION 24 (RE-ISSUE) ABNORMAL / EMERGENCY PROCEDURES

Mar 17/10 Page EF - 17
 Quick Reference Handbook
Failure Of Two Boost Pumps On One Side AFM 3-16-30

If two (2) fuel boost pumps on same side are inoperative, fuel can
be delivered under pressure to each engine as follows:
1. Crossflow............................................................................... OPEN
2. Operative Fuel Boost Pumps ..............................................ALL ON
CAUTION: FLYING UNDER THESE CONDITIONS WILL
PRODUCE A GRADUALLY INCREASING FUEL UNBALANCE, AS
FUEL FROM ONLY ONE TANK WILL BE USED.
CAUTION: THE ENGINE WILL RUN ON SUCTION FUEL FEED
ONLY AT OR BELOW 20,000 FEET. ABOVE 20,000 FEET, THE
ENGINE WILL RUN ERRATICALLY AND FLAME OUT IF THE
CROSSFLOW IS NOT OPEN WITH AT LEAST ONE BOOST PUMP
ON.
When fuel balancing is required:
3. Inter Tank .............................................................................. OPEN
4. Sideslip ..... TRIM RUDDER TO ESTABLISH LIGHT WING DOWN
When fuel balancing is complete:
5. Inter Tank ...........................................................................CLOSED
6. Normal Trim ...................................................... RE-ESTABLISHED
NOTE: For additional information on fuel balancing, refer to GIV AFM
Section 1-28-10: Usable Fuel Capacities. For quick reference
purposes, data from this AFM section has been added to Permissible
Fuel Imbalance For All Flight Operations, page EF-19.

END

ABNORMAL / EMERGENCY PROCEDURES REVISION 24 (RE-ISSUE)

Page EF - 18 Mar 17/10
Quick Reference Handbook
Permissible Fuel Imbalance For All Flight Operations
AFM 1-28-10

From GIV AFM Limitations, Section 1-28-10: Usable Fuel

Capacities:
See the figure below for maximum unbalanced fuel. Before the
imbalance exceeds that shown, proceed with fuel balancing.

REVISION 24 (RE-ISSUE) ABNORMAL / EMERGENCY PROCEDURES

Mar 17/10 Page EF - 19
 Quick Reference Handbook
Permissible Fuel Imbalance For All Flight Operations, ctd…
AFM 1-28-10
Continued from GIV AFM Limitations, Section 1-28-10: Usable
Fuel Capacities:
1. Fuel load balancing may be accomplished by using the crossflow
valve or intertank valve.
2. When balancing fuel through use of the crossflow valve, ensure
that boosted fuel pressure is always available to the engines.
CAUTION: THE ENGINE WILL RUN ON SUCTION FUEL FEED
ONLY AT OR BELOW 20,000 FEET. ABOVE 20,000 FEET, THE
ENGINE WILL RUN ERRATICALLY AND FLAME OUT IF THE
CROSSFLOW IS NOT OPEN WITH AT LEAST ONE BOOST PUMP ON.
3. Balancing fuel by using the intertank valve requires the airplane to
be placed in a sideslip condition. Adjusting the rudder trim in the
direction of the “heavy” tank will create a wing down condition and
allow fuel to flow toward the “light” tank.

END

ABNORMAL / EMERGENCY PROCEDURES REVISION 24 (RE-ISSUE)

Page EF - 20 Mar 17/10
Quick Reference Handbook
Landing Gear Index
Hydraulic System Diagram ........................................................... EG-2
Abnormal Gear Condition - Emergency Landing .................... EG-3
Landing Gear Failure To Retract .................................................. EG-5
Landing Gear Failure To Extend .................................................. EG-6
Landing Gear Retraction Following Alternate Extension ............. EG-7
Nose Wheel Steering Failure ....................................................... EG-8
Nutcracker System Fails To Shift To Ground Mode At
Touchdown ................................................................................ EG-9
Nutcracker System Fails To Shift To Air Mode At Takeoff ......... EG-10
‘G’ Monitor System ..................................................................... EG-11
‘G’ Monitor Versus Airplane Gross Weight Charts ..................... EG-12

REVISION 24 (RE-ISSUE) ABNORMAL / EMERGENCY PROCEDURES

Mar 17/10 Page EG - 1
 Quick Reference Handbook
Hydraulic System Diagram

ABNORMAL / EMERGENCY PROCEDURES REVISION 24 (RE-ISSUE)

Page EG - 2 Mar 17/10
Quick Reference Handbook
Abnormal Gear Condition - Emergency Landing
AFM 4-19-10

NOSE GEAR RETRACTED BOTH MAIN GEAR DOWN AND

LOCKED PROCEDURE:
If contamination of the uplocks due to ice and snow is suspected,
consider flying to an area where melting can occur. If fully retracted,
attempt to release from uplocks by applying positive “g” loading (not to
exceed 2.5 g’s flaps up). If partially extended but not locked down,
perform a normal approach and firmly “bump” the main wheels on
runway in an attempt to shake the nose gear down and locked.
Execute a go-around. Consideration should be given to flying faster
than normal in order to increase elevator effectiveness and the nose
falling through on touchdown.
Landing Procedure:
1. GPWS / GND SPLR FLAP ORIDE ............................................. ON
2. Touchdown ............................................. RUNWAY CENTERLINE
3. Wheel Brakes ......................................................... USE MINIMUM
4. Nose ............................................................. FLY ONTO RUNWAY
Relieve weight with elevator after runway contact.
5. Brakes ............................................................AS REQUIRED FOR
DIRECTIONAL CONTROL AND STOPPING
ONE MAIN GEAR AND NOSE GEAR DOWN AND LOCKED,
OPPOSITE MAIN GEAR RETRACTED PROCEDURE:
If fully retracted, attempt to release from uplocks by applying positive
“g” loading not to exceed 2.5 g’s flaps up.
If partially extended, yaw airplane to apply spanwise air load to force
the affected gear outboard (left rudder for left main gear, right rudder
for right main gear). Attempt to lock unsafe gear down. At normal
approach speeds, touch affected gear on runway with slight SKID to
force the faulty gear outboard. Execute a go-around.
Landing Procedure:
1. GPWS Voice Override ................................................................ ON
2. Touchdown .......................SIDE OF RUNWAY WITH SAFE GEAR
3. Speed Brakes .................................... EXTEND (AS NECESSARY)

Continued on next page 

REVISION 24 (RE-ISSUE) ABNORMAL / EMERGENCY PROCEDURES

Mar 17/10 Page EG - 3
 Quick Reference Handbook
Abnormal Gear Condition – Emergency Landing, ctd… AFM 4-19-10
4. Thrust Reversers .......... USE MAXIMUM INITIALLY, GRADUALLY
DECREASING ON FAILED GEAR SIDE FOR
DIRECTIONAL CONTROL
5. Brakes ................................................................. AS NECESSARY
FOR DIRECTIONAL CONTROL AND STOPPING
6. Unsafe Gear ....................................................................................
RELIEVE WEIGHT WITH AILERONS AND THRUST REVERSERS
ONE MAIN GEAR ONLY DOWN AND LOCKED PROCEDURE:
If only one main gear is extended, retract gear and perform an all-
gear-up landing. Follow steps below for all-gear-up landing.
BOTH MAIN GEAR RETRACTED NOSE GEAR DOWN AND
LOCKED PROCEDURE:
If unable to extend and lock down both main gear, retract nose and
perform all-gear-up landing. Follow steps below for all-gear-up
landing.
ALL-GEAR-UP LANDING PROCEDURE:
NOTE: Do not deploy spoilers for this procedure.
1. Burn off fuel to 2000 pounds remaining before attempting a
planned wheels-up landing.
2. GPWS Voice Override ............................................................... ON
3. FOR SPZ 8400 EQUIPPED AIRPLANES: Silence landing gear
warning horn by pulling FWC #1 circuit breaker. FOR SPZ 8000
EQUIPPED AIRPLANES: Silence landing gear warning horn by
pulling TONE WARN #1 circuit breaker.
4. For final approach, set flaps to 39°.
5. Use final approach speed of VREF or as slow as possible at all
planned wheels up landing weights and fly a very shallow
approach angle.
6. Set elevator trim to develop maximum nose up moment. A slight
control column push may be required to maintain proper pitch
attitude.
7. Target low sink rate at touchdown.
8. Flap segments are likely to break clean away from the wing at
touchdown.
Continued on next page 

ABNORMAL / EMERGENCY PROCEDURES REVISION 24 (RE-ISSUE)

Page EG - 4 Mar 17/10
Quick Reference Handbook
Abnormal Gear Condition – Emergency Landing, ctd… AFM 4-19-10
9. Touch down on runway centerline.
10. When aft fuselage contacts runway surface, immediately shut
down both engines with FIRE handles.
11. APU MASTER ........................................................................... OFF
12. BATTERIES .............................................................................. OFF
13. Pull control column to the full aft position during the remainder of
the ground run to maintain a nose-high attitude. Maintain
directional control with rudder.
14. When airplane stops, evacuate immediately.

END

Landing Gear Failure To Retract AFM 3-19-20

If landing gear handle will not move:

1. Ground Spoiler ......................................................................... OFF
2. Lock Release Button ............................................................. PUSH
If landing gear handle moves but landing gear fails to retract:
3. Ground Spoiler ......................................................................... OFF
4. COMBINED SYS Quantity / Pressure ................................... Check
If either COMBINED SYS quantity or pressure is not indicated, see
Combined Hydraulic System Failure – Loss of Pressure and
Fluid, page EF-8.
CAUTION: USE OF THE LANDING GEAR EMERGY RESET (D-RING) IN
AN ATTEMPT TO RETRACT THE GEAR IS NOT RECOMMENDED.
If landing gear still fails to retract:
5. Landing Gear Handle ........................................................... DOWN
NOTE: Should landing gear fail to retract and all attempts are
unsuccessful, the landing gear handle should be returned to the
DOWN position, and the airplane should return for landing and
troubleshooting.

END

REVISION 24 (RE-ISSUE) ABNORMAL / EMERGENCY PROCEDURES

Mar 17/10 Page EG - 5
 Quick Reference Handbook
Landing Gear Failure To Extend AFM 3-19-30

If normal operation of the landing gear does not result in a proper

down-and-locked condition, alternate extension will be required. A
loss of the Combined Hydraulic System (COMB SYS) fluid will also
require alternate extension since the utility System will be inoperative,
and step 2 and 3 may be omitted.
Landing gear extension is accomplished as follows:
1. Landing Gear Handle ........................................................... DOWN
2. Emergency Landing Gear T-Handle ...............................................
.............................. PUSH (DOWN, TO ASSURE FULLY SEATED)
Wait a minimum of thirty (30) seconds after reseating the T-
handle. After 30 seconds:
3. Dump Valve D-Ring ................................................................ PULL
NOTE: Handle must be pulled up fully, held for ten (10) seconds,
and then restowed.
If this procedure does not result in proper gear position and
indication, proceed as follows:
CAUTION: A FULLY CHARGED NITROGEN BOTTLE (3000 PSI AT
70°F/21°C) WILL ALLOW ONLY ONE (1) EXTENSION OF LANDING
GEAR.
4. Airspeed ...................................................... 175 KCAS (OR LESS)
5. Emergency Landing Gear T-Handle ...................................... PULL
NOTE: Ensure landing gear handle is DOWN for proper gear
position indication and nose wheel steering operation. Operation
of emergency system is not predicated on position of the selector
handle.
6. With Landing Gear Down and Locked .............................................
OBSERVE LANDING GEAR EXTENDED SPEED LIMITATION
(250 KCAS/0.7 MT)

END

ABNORMAL / EMERGENCY PROCEDURES REVISION 24 (RE-ISSUE)

Page EG - 6 Mar 17/10
Quick Reference Handbook
Landing Gear Retraction Following Alternate
Extension AFM 3-19-40

WARNING: A FULLY CHARGED NITROGEN BOTTLE (3000 PSI AT

70° F (21° C) ALLOWS ONLY ONE EXTENSION OF THE LANDING GEAR.
RETRACTION FOLLOWING ALTERNATE EXTENSION COULD RESULT
IN A GEAR UP LANDING.

CAUTION: THIS RESET / RETRACTION PROCEDURE IS PROVIDED

FOR USE IF GREATER OR COMPOUNDED EMERGENCY CONDITIONS
EXIST AND IS NOT TO BE CONSIDERED AUTHORIZATION TO RECYCLE
LANDING GEAR AFTER ROUTINE MAINTENANCE OR TRAINING USE OF
THE BLOW DOWN SYSTEM.
Extension of the landing gear using the preceding procedures
actuates valves to isolate the hydraulic system from the nitrogen
pressure of the emergency extension system. Should conditions
necessitate landing gear retraction, the system must be reset to the
normal configuration. Retraction will not be possible if Combined
System fluid was lost.
To retract the landing gear following an alternate extension,
proceed as follows:
1. Landing Gear Handle ........................................................... DOWN
2. Emergency Landing Gear T-Handle ....................... PUSH (DOWN)
Wait a minimum of thirty (30) seconds after reseating T-handle to
allow pressure to bleed off. After 30 seconds:
3. Dump Valve D-ring ................................................................. PULL
NOTE: Handle must be pulled fully, held for ten (10) seconds,
and then restowed.
4. Landing Gear Handle ................................................................. UP
NOTE: There is no back-up method for retracting landing gear.

END

REVISION 24 (RE-ISSUE) ABNORMAL / EMERGENCY PROCEDURES

Mar 17/10 Page EG - 7
 Quick Reference Handbook
Nose Wheel Steering Failure AFM 3-19-50

If the STEER BY WIRE FAIL message illuminates on CAS, proceed

as follows:
For airplanes SN 1000 thru SN 1143 without ASC 176:
1. Nose Wheel Steering Switch .................................. OFF, THEN ON
2. If Message Stays On: Nose Wheel Steering Switch ................ OFF
3. Use brakes, rudder, and/or Differential Power for Directional
Control.
NOTE: Normal shimmy damping will be available with nose wheel
steering OFF.
IF AIRBORNE:
For airplanes SN 1144 and subs. or airplanes with ASC 176:
NOTE: Message will only illuminate with landing gear extended.
After Takeoff:
1. Nose Wheel Steering Switch .................................................... OFF
If the nose steering wheel is NOT centered, leave landing gear
DOWN and land as soon as practical.
If the nose steering wheel is centered, remove feet from rudder
pedal(s) and hands-off nose steering wheel.
2. Landing Gear.................................................................. RETRACT
On Approach:
1. Nose Wheel Steering Switch .................................................... OFF
After Landing:
1. Rudder and Differential Brakes .............. USE FOR DIRECTIONAL
........................................................ CONTROL UNTIL REACHING
A SLOW TAXI SPEED OR STOPPED
2. Nose Wheel Steering Switch ...................................................... ON
A. If message extinguishes, expect normal nose wheel steering
output.
B. If message remains ON, use brakes, rudder, and / or
differential power for directional control.

END

ABNORMAL / EMERGENCY PROCEDURES REVISION 24 (RE-ISSUE)

Page EG - 8 Mar 17/10
Quick Reference Handbook
Nutcracker System Fails To Shift To Ground Mode At
Touchdown AFM 3-19-60

For airplanes with ASC 166:

1. REV UNLOCK message will illuminate with the use of thrust
reversers. Thrust reversers will stow at low ground speed.
2. Ground spoilers will deploy with wheel spin-up, but will retract at
low ground speed.
3. Anti-skid system may not operate normally. Be prepared to turn
anti-skid off at low ground speed if you lose brakes.
4. Engine idle will go to 67% HP at low ground speed.
5. APU air is inoperative.
6. Pressurization outflow valve will not open automatically. Switch to
manual and open outflow valve.
7. Stick shaker and pusher remain armed.
8. Landing gear handle is not safe (safety solenoid energized).
9. Engines cannot be restarted.
For airplanes without ASC 166:
1. Thrust reversers are inoperative.
2. If speed brakes are used, a ACFT CONFIG message will illuminate.
3. Ground spoilers will deploy with wheel spin-up, but will stow at
low ground speed.
4. Anti-skid system may not operate normally. Be prepared to turn
anti-skid off at low ground speed if brakes are lost.
5. Engine idle will go to 67% HP on landing.
6. Pressurization outflow valve will not open automatically. Switch to
manual and open outflow valve.
7. APU air is inoperative.
8. Stick shaker and pusher remain armed.
9. Landing gear handle is not safe (safety solenoid energized).
10. Engines cannot be restarted.
If nutcracker has failed to air mode:
1. Cabin Pressure Control AUTO / MANUAL ....................... MANUAL
2. Cabin Press Control Man Hold ........................ ROTATE TO OPEN
3. Differential Braking .............................................. AS NECESSARY

END

REVISION 26 ABNORMAL / EMERGENCY PROCEDURES

Oct 5 2011 Page EG - 9
 Quick Reference Handbook
Nutcracker System Fails To Shift To Air Mode At
Takeoff AFM 3-19-80

WARNING: THRUST REVERSERS ARE OPERATIVE IN FLIGHT IF

POWER LEVERS ARE RETARDED TO IDLE.

WARNING: GROUND SPOILERS WILL DEPLOY IF POWER LEVERS

ARE RETARDED TO GROUND IDLE AND GND SPLR OFF/ARMED
SWITCH IS ARMED.
NOTE: With the nutcracker system not in the AIR mode after takeoff,
pressurization will remain at 0.25 psi differential and cabin altitude will climb at
approximately the same rate as the airplane. Manual control is still available. If
cabin rate of climb exceeds 3,000 feet per minute, rate limiting will occur,
driving the outflow valve fully closed.
NOTE: Stick shaker and stick pusher are inoperative if the nutcracker system
is not in the AIR mode after takeoff.
1. GND SPLR OFF/ARMED Switch ............................................. OFF
2. NUTCRKR SW TEST Switch ..................... DEPRESS AND HOLD
3. Landing Gear.............................................................................. UP
4. NUTCRACKER Circuit Breaker (CPO A-13, B-13, C-13) ...... PULL
5. NUTCRACKER BAT PWR Circuit Breaker (CPO, D-13) ....... PULL
(For airplanes having ASC 242.)
6. NUTCRKR SW TEST Switch .......................................... RELEASE
NOTE: On airplanes SN 1000 through 1320 having ASC 381 and
airplanes SN 1321 and subsequent, wing anti ice air is exhausted into the
main landing gear wheel well area. If slush or ice is the suspected cause
of nutcracker failure, selecting WING ANTI ICE ON may correct the
problem. After heating the wheel well area for a period of time, the flight
crew may then elect to reset the nutcracker system to determine if the
problem is corrected.
To restore the nutcracker system to the ground for landing:
7. NUTCRACKER Circuit Breakers (as pulled) ...................................
..................................... RESET SHORTLY AFTER TOUCHDOWN
8. Speed Brakes ............................................... MANUALLY EXTEND
Automatic deployment of ground spoilers will not be available.

END

ABNORMAL / EMERGENCY PROCEDURES REVISION 26

Page EG - 10 Oct 5 2011
Quick Reference Handbook
‘G’ Monitor System OM 2A-31-32

Airplanes SN 1034, 1156 and subsequent and airplanes SN 1000

through 1155 with ASC 118 incorporated have a gravity force ('G')
monitor system to record the maximum vertical acceleration
experienced by the airplane during landing. Data collected by this
system is used to assist in determining the requirement for either
overweight or hard landing inspections.
The monitoring system is activated during approach at 50 ft radio
altitude with the landing gear extended. The system is active until the
nose gear nutcracker signals weight-on-wheels. The maximum
acceleration sensed, while the system is active, is recorded by the
computer. Once deactivated by nutcracker logic, the system remains
deactivated until the subsequent approach and landing, when
activation criteria are again satisfied.
The recorded acceleration will be affected by normal occurrences
experienced between main gear touchdown and nose gear nutcracker
ground mode logic. These occurrences include but are not limited to:
• Ground spoiler deployment
• Rough, bumpy runways
• Travel through runway intersections
• Travel across arresting cable hardware housing
The above items can add 0.2 to 0.3 'G' to the touchdown acceleration
and are considered valid loads on the airplane structure. Normal
landing 'G' readings may vary from 1.3 to 1.6 'G'.
The established limit to determine the requirement for the hard landing
inspection for airplane weights up to and including maximum landing
weight is 2.0 'G' (2.3 'G' for airplanes SN 1214 and subsequent and
airplanes SN 1000 thru 1213 with ASC 190). The limit to determine the
requirement for an overweight landing inspection for airplane weights
exceeding maximum landing weight decreases on a linear scale from
2.0 'G' to 1.6 'G' (2.3 'G' to 1.7 'G' for airplanes SN 1214 and
subsequent and airplanes SN 1000 thru 1213 with ASC 190). The limit
depends on actual airplane weight and assumes that extremely high
side-loads were not encountered during landing touchdown. If the
actual 'G' recorded for the landing is within limits and no extremely high
side loads were encountered at touchdown, no inspection is required. If
extremely high side loads were encountered at touchdown, or the 'G'
limit is exceeded, the flight crew shall log the event for maintenance
action. For additional information, refer to Chapters 5 and 31 of the GIV
Maintenance Manual.

END

REVISION 24 (RE-ISSUE) ABNORMAL / EMERGENCY PROCEDURES

Mar 17/10 Page EG - 11
 Quick Reference Handbook
‘G’ Monitor Versus Airplane Gross Weight OM 2A-31-32

ABNORMAL / EMERGENCY PROCEDURES REVISION 24 (RE-ISSUE)

Page EG - 12 Mar 17/10
Quick Reference Handbook
‘G’ Monitor Versus Airplane Gross Weight, ctd… OM 2A-31-32

REVISION 24 (RE-ISSUE) ABNORMAL / EMERGENCY PROCEDURES

Mar 17/10 Page EG - 13
 Quick Reference Handbook
Notes

ABNORMAL / EMERGENCY PROCEDURES REVISION 24 (RE-ISSUE)

Page EG - 14 Mar 17/10
Quick Reference Handbook
Pneumatics / ECS Index
Bleed Air / ECS System Diagram ................................................. EH-2
Loss of Pressurization ............................................................... EH-3
Emergency Descent Procedure ................................................ EH-4
Loss of Automatic Pressurization Control .................................... EH-6
Pressurization System - Rate Limiting ......................................... EH-7
Bleed Air System Failure .............................................................. EH-8
Unpressurized Flight .................................................................. EH-10
Air Conditioning System Shut Down or Inoperative ................... EH-10
Air Conditioning System Airflow Hot or Uncontrollable .............. EH-11
Left or Right Cooling Turbine Hot ............................................... EH-11
Oxygen System Quantity Shortage ............................................ EH-13

REVISION 29.1 ABNORMAL / EMERGENCY PROCEDURES

Aug 07/17 Page EH - 1
 Quick Reference Handbook
Bleed Air / ECS System Diagram

ABNORMAL / EMERGENCY PROCEDURES REVISION 29.1

Page EH - 2 Aug 07/17
Quick Reference Handbook
Loss Of Pressurization AFM 4-22-10

If cabin pressurization is lost, proceed as follows:

1. Crew Oxygen Masks ............................................................... DON
2. Emergency Descent Procedure (page EH-4) ............... INITIATE
3. Passenger Oxygen Masks ........................... MANUALLY DEPLOY
NOTE: Ensure sufficient lighting is available to visually confirm mask
deployment and the donning of masks. Advise passengers to don masks.
4. Passenger Oxygen Masks........................ VERIFY DEPLOYMENT
5. Pressurization ................................................................. RESTORE
See Loss of Automatic Pressurization Control, page EH-6.
THE FOLLOWING STEPS MAY BE HELPFUL IF IT IS SUSPECTED
THAT A TORN MAIN ENTRANCE DOOR SEAL OR TORN
BAGGAGE DOOR SEAL MAY BE THER CAUSE OF THE LOSS OF
PRESSURIZATION:
6. Cabin Pressure Controls and Indications ............................CHECK
If the outflow valve is closed and cabin altitude is still climbing, a
baggage door seal or main entrance door seal may be causing
the loss of pressurization.
7. COWL ANTI-ICE ........................................................................ ON
Increase bleed air pressure by selecting COWL ANTI-ICE ON or
by increasing engine power. Cabin rate-of-climb can be controlled
by selecting COWL ANT-ICE ON and / or by increasing engine
power to maximum continuous setting at higher altitudes, thereby
increasing available bleed pressure above 35 psi.
8. Altitude .............................................. DESCEND AS NECESSARY
If unable to attain 35 psi or greater, or if selecting cowl anti-ice ON
results in COOL TURB HOT message, descend to lower altitude
until cabin rate-of-climb is controllable. Select cowl ant-ice OFF if
COOL TURB HOT message persists.
9. Oxygen .................................................... USE AS APPROPRIATE

END

REVISION 30 ABNORMAL / EMERGENCY PROCEDURES

Oct 30/17 Page EH - 3
 Quick Reference Handbook
Emergency Descent Procedure AFM 4-22-20

The following procedure assumes structural integrity of airplane.

If airplane structural integrity is in doubt, limit speed as much as
possible and avoid high maneuvering loads.
1. Power Levers .......................................................................... IDLE
2. Airspeed .................................................... ESTABLISH MMO / VMO
NOTE: An initial pitch attitude of 8 to 10 nose down is recommended
to commence descent. As speed approaches MMO / VMO, adjust pitch
attitude as necessary to avoid an overspeed condition.
3. Speed Brakes .................................................................... EXTEND
4. Airspeed .......................................................MAINTAIN MMO / VMO
NOTE: It is recommended that the emergency descent be flown
manually in order to achieve maximum descent rate.
5. SEAT BELT / NO SMOKING Signs ........................................... ON
6. Transponder Code .......................................................... SET 7700
7. Air Traffic Control (ATC) ..................................................... NOTIFY
8. Level Off ..........................................................................................
.........................................................................................................
15,000 FT OR MINIMUM ENROUTE ALTITUDE, IF HIGHER
Approach and Landing:
9. Normal Approach .......................................................... PERFORM
10. Gear .................................................................. DOWN / 3 GREEN
11. Nutcracker…………………………………………….…………TEST
12. Ground Spoilers……………………………………………..ARMED
13. Crew Alerting System……………………………………….CHECK
14. Flaps…………………………………………....SET FOR LANDING
15. PF Feet Position on Rudder Pedals………...HEELS OFF FLOOR

Continued on next page

ABNORMAL / EMERGENCY PROCEDURES REVISION 30

Page EH - 4 Oct 30/17
Quick Reference Handbook
Emergency Descent Procedure, ctd… AFM 4-22-20

If unable to get gear down for landing and a gear-up landing is

planned:
16. GPWS Voice Override ................................................................ ON
NOTE: FOR SPZ 8400 EQUIPPED AIRPLANES: Silence landing gear
warning horn by pulling FWC #1 circuit breaker. FOR SPZ 8000
EQUIPPED AIRPLANES: Silence landing gear warning horn by pulling
TONE WARN #1 circuit breaker.
17. Pressurization ................................................................... MANUAL
18. Outflow Valve......................................................................... OPEN
19. Final Approach .............................................................. FLAPS 39°
20. Landing .......................................... PERFORM UNPRESSURIZED
21. Use final approach speed at VREF or as slow as possible at all
planned wheels up landing weights and fly a very shallow
approach.
22. Set elevator trim to develop maximum nose up movement. A
slight control column push may be required to maintain proper
pitch attitude.
23. Target low sink rate at touchdown.
24. Flap segments are likely to break clean away from the wing at
touchdown.
25. Touchdown on runway centerline.
26. When aft fuselage contacts runway surface, gently lower nose to
runway. Pull aft on control column to keep the weight as light as
possible once the nose has contacted the runway.
27. Both Engines ...................................................................................
.................... IMMEDIATELY SHUT DOWN WITH FIRE HANDLES
28. APU MASTER .......................................................................... OFF
29. Batteries .................................................................................... OFF
30. Directional Control ............................... MAINTAIN WITH RUDDER
See Abnormal Gear Condition – Emergency Landing, page
EG-3.
END

REVISION 30 ABNORMAL / EMERGENCY PROCEDURES

Oct 30/17 Page EH - 5
 Quick Reference Handbook
Loss Of Automatic Pressurization Control AFM 3-22-30

1. AUTO / MANUAL Switch .................................................. MANUAL

2. DADC Selector Switch ............ OPPOSITE DADC (DADC 1 OR 2)
3. AUTO / MANUAL Switch ....................................................... AUTO
If automatic pressurization control is not regained:
4. AUTO / MANUAL Switch .................................................. MANUAL
5. Rate of Climb .................... MANUALLY CONTROL TO ±500 FPM
CAUTION: CLOSELY MONITOR CABIN DIFFERENTIAL PRESS-
URE. DO NOT ALLOW IT TO EXCEED 9.8 PSID.
NOTE: When operating in manual, the rate of change should be
monitored to maintain a maximum of 500 feet per minute UP or 300 feet
per minute DOWN. Care should also be taken to land unpressurized with
the outflow valve indicator in the full OPEN position.
If manual pressurization control is not successful and if cabin
differential pressure will exceed 9.8 PSID:
6. RAM AIR Switch ...................................................................... RAM
WARNING: SELECTING RAM WILL SHUT OFF BLEED AIR FOR
PRESSURIZATION AND THE AIRPLANE WILL DEPRESSURIZE.
7. Crew Oxygen Masks ............................................................... DON
8. Altitude .................................... DESCEND TO A SAFE ALTITUDE
9. Passenger Oxygen Masks ........................... MANUALLY DEPLOY
NOTE: Ensure sufficient lighting is available to visually confirm mask
deployment and the donning of masks. Advise passengers to don masks.
Upon reaching a safe altitude, attempt to regain control of the
pressurization system:
10. RAM AIR Switch ....................................................................... OFF
11. AUTO or MANUAL Control..................... ATTEMPT TO RESTORE
NOTE: Avoid excessive throttle movements while attempting to regain
control of the pressurization system.

END

ABNORMAL / EMERGENCY PROCEDURES REVISION 30

Page EH - 6 Oct 30/17
Quick Reference Handbook
Pressurization System - Rate Limiting AFM 3-22-40

The following procedure is recommended to return to automatic

operation:
1. AUTO / MANUAL Selector Switch .................................. MANUAL
Manually control system. (Rate should not exceed 500 ft. per
minute up or down.) Observe position of outflow valve on
indicator.
2. AUTO / MANUAL Selector Switch ....................................... AUTO
If rate-of-change switch is retriggered, PLACE the AUTO /
MANUAL Switch in MANUAL and continue flight. Cabin rate-of-
change should be monitored to maintain maximum of 500 ft. per
minute, up or down.
CAUTION: WHEN OPERATING IN MANUAL, MONITOR CABIN
ALTITUDE CLOSELY, ESPECIALLY IN DESCENT, TO ENSURE THAT
CABIN ALTITUDE DOES NOT DECREASE TO LESS THAN LANDING
FIELD ELEVATION.
NOTE: Opposite cabin pressure reference switch position DADC 2 may
be selected and procedure repeated, if necessary.
Care must be taken to land unpressurized with outflow valve in
the full OPEN position.

END

REVISION 24 (RE-ISSUE) ABNORMAL / EMERGENCY PROCEDURES

Mar 17/10 Page EH - 7
 Quick Reference Handbook
Bleed Air System Failure AFM 3-22-50

In the event a bleed air system failure occurs, the following steps
apply:
1. Affected Bleed Air Switch ......................................................... OFF
2. Affected BLEED AIR Circuit Breaker .................................. CHECK
(L BLEED AIR: PO, A-10; R BLEED AIR: PO, B-10)
NOTE: If the circuit breaker is popped, wait 5 minutes to allow for circuit
cooling prior to resetting the circuit breaker.
For SN 1000 thru 1201 without ASC 298:
If the right system circuit breaker is popped, the ISOLATION VLV
OPEN message will be present on EICAS. Even though the message
is present, the isolation valve is closed.
NOTE: The isolation valve must be manually opened from the tail
compartment in order to start the left engine.
1. Right Bleed Switch ................................................................... OFF
2. Right BLEED AIR Circuit Breaker ..................... ATTEMPT RESET
If CB resets:
1. Isolation Valve ....................................................................... OPEN
2. Altitude ............................... DESCEND TO 41,000 FT OR BELOW
3. Flight Into Known Icing Conditions ....................................... AVOID
If CB will not reset:
1. Right ECS Pack Switch ............................................................ OFF
2. Altitude ............................... DESCEND TO 41,000 FT OR BELOW
3. Flight Into Known Icing Conditions ....................................... AVOID
For all other bleed air system failures:
If the affected system circuit breaker is not popped, pull and reset
the circuit breaker.
If resetting the circuit breaker solves the problem, continue flight
in normal configuration.

Continued on next page 

ABNORMAL / EMERGENCY PROCEDURES REVISION 24 (RE-ISSUE)

Page EH - 8 Mar 17/10
Quick Reference Handbook
Bleed Air System Failure, ctd… AFM 3-22-50

If resetting the circuit breaker does not solve problem or if circuit

breaker does not reset:
For Left Bleed Air System:
1. Left Bleed Air Switch ................................................................ OFF
2. Isolation Valve ....................................................................... OPEN
3. Altitude ............................................................................ MAINTAIN
41,000 FT OR BELOW FOR REMAINDER OF FLIGHT
4. Flight Into Known Icing Conditions ....................................... AVOID
For Right Bleed Air System:
1. Right Bleed Air Switch .............................................................. OFF
2. Isolation Valve ....................................................................... OPEN
3. Altitude ............................................................................ MAINTAIN
41,000 FT OR BELOW FOR REMAINDER OF FLIGHT
4. Flight Into Known Icing Conditions ....................................... AVOID

END

REVISION 28 ABNORMAL / EMERGENCY PROCEDURES

May 25/16 Page EH - 9
 Quick Reference Handbook
Unpressurized Flight AFM 3-22-60

If dispatching unpressurized to comply with MMEL requirements,

proceed as follows:
1. AUTO / MANUAL Switch .................................................. MANUAL
2. MANUAL HOLD Knob .....................................................................
................................. POSITION OUTFLOW VALVE FULLY OPEN
3. RAM AIR ................................................................................. RAM
4. Maximum Cruise Altitude ........................................... 10,000 FEET
NOTE: The 60 HZ power supply for cabin entertainment may shut down
automatically if the cabin altitude exceeds 8,000 feet.
If smoke is detected in the aft baggage compartment:
5. MANUAL HOLD Knob .....................................................................
............................ POSITION OUTFLOW VALVE FULLY CLOSED
NOTE: Position the outflow valve fully closed will create a slight
pressure differential in the cabin. This will help prevent smoke migration
into the cabin and allow the smoke to be evacuated. See Airplane
Interior Fire / Smoke / Fumes, page ED-7.

END

Air Conditioning System Shut Down Or Inoperative

AFM 3-01-10

At altitudes above 41,000 feet with either air conditioning system

selected to OFF or inoperative, the respective engine COWL ANTI
ICE must be selected ON and the BLEED AIR ISOLATION valve
selected to CLOSED.
From GIV AFM, Bleed Air System Limitations: Do not operate above
41,000 feet without both engine bleeds ON and each engine being
bled by either the air conditioning system or engine COWL ANTI ICE.
1. Associated Pack Switch ........................................................... OFF
2. Operational Pack Bleed Source ......................................................
....................................... VERIFY COMPENSATION TO 30 ±3 PSI

END

ABNORMAL / EMERGENCY PROCEDURES REVISION 28

Page EH - 10 May 25/16
Quick Reference Handbook
Air Conditioning System Airflow Hot Or Uncontrollable
AFM 3-01-20

If cool air is not produced in either AUTO, MANUAL, or OFF

mode:
1. Affected Air Conditioning PACK Switch ................................... OFF
If cool air is not produced in either AUTO, MANUAL or OFF
mode, the water separator may be frozen, preventing cool air
from flowing through it. To determine whether the water separator
is frozen or the Air Cycle Machine (ACM) is developing a
problem, select the affected Air Conditioning PACK switch to
OFF.
Allow ten (10) minute time period to elapse, then:
2. Affected Air Conditioning PACK Switch ...........RESELECT TO ON
If cool airflow is present, the water separator is most likely the
problem.
If cool airflow is present:
3. Temperature Setting ...................... SELECT SLIGHTLY WARMER
Select a slightly warmer temperature to preclude water separator
from re-freezing.
If warm or hot airflow returns:
4. Malfunctioning Pack ............................................... AS REQUIRED
BY FLIGHT CONDITIONS / MISSION REQUIREMENTS
If warm or hot airflow returns, the ACM is developing a problem.
Depending on flight conditions or mission requirements, the
malfunctioning air conditioning pack should be managed as
required. See Air Conditioning System Shut Down Or
Inoperative, page EH-10, for bleed air requirements with the air
conditioning packs shut off.

END

Left or Right Cooling Turbine Hot AFM 3-01-30

On ground only:
1. Air conditioning flow control and shutoff valve will automatically
close.
2. Associated Air Conditioning Pack Switch ................................. OFF

Continued on next page 

REVISION 24 (RE-ISSUE) ABNORMAL / EMERGENCY PROCEDURES

Mar 17/10 Page EH - 11
 Quick Reference Handbook
Left or Right Cooling Turbine Hot, ctd… AFM 3-01-30

In flight:
1. Current Bleed Air Configuration ........................................ ASSESS
If COWL and/or WING ANTI ICE is selected ON, see
Temperature Range for Cowl Anti-Icing chart, page NE-7, to
determine whether the use of anti-ice is required.
If COWL and/or WING ANTI-ICE is required, consider departing
icing conditions before proceeding to Step 2 OR if COWL and /
or WING ANTI-ICE is ON but is not required:
2. Appropriate COWL / WING ANTI-ICE...................................... OFF
3. Temperature Control Selector Switch (Affected Pack) ...................
............................................................... SELECT WARMER TEMP
4. One (1) Minute ............................................... ALLOW TO ELAPSE
If COOL TURB HOT message remains displayed:
5. Affected (L or R) Pack Switch ................................................. OFF
CAUTION: DO NOT TURN OFF BOTH PACK SWITCHES AT
HIGH ALTITUDE.
If both air conditioning packs are affected, select only one pack
switch OFF.
If COWL ANTI-ICE is required or if airplane altitude is above
41,000 feet:
6. COWL ANTI-ICE ........................................................................ ON
Same bleed air system with pack shut down.
If COOL TURB HOT message persists for second pack:
7. Descent To Lower Altitude ......................................... COMMENCE
8. Crew Oxygen Masks / Regulators .................................... ON/100%
9. Passenger Oxygen Masks ..............................................................
........................................... MANUALLY DEPLOY (IF REQUIRED)
10. Second Pack Switch ................................................................. OFF
(If COOL TURB HOT message is still displayed.)
11. Proceed to nearest suitable airport and land.

END

ABNORMAL / EMERGENCY PROCEDURES REVISION 24 (RE-ISSUE)

Page EH - 12 Mar 17/10
Quick Reference Handbook

Oxygen System Quantity Shortage AFMS

To maximize the amount of oxygen available to the flight crew when

prolonged use of oxygen by the flight crew is required:
1. THERAPEUTIC OXYGEN Switch.(If Installed)………………... OFF
2. Passenger Oxygen Control Panel Rotary Knob ....................... OFF

WARNING: PERFORMING THIS ACTION TERMINATES FLOW

OF OXYGEN TO THE CABIN. CONSIDERATION SHALL BE GIVEN
TO DESCENDING TO 15,000 FEET OR BELOW FOR THE
REMAINDER OF THE FLIGHT. AVAILABLE PORTABLE OXYGEN
BOTTLE(S) SHALL BE DISTRIBUTED TO PASSENGERS REQUIRING
OXYGEN ASSISTANCE.

NOTE: For additional information, refer to the applicable Airplane Flight

Manual Supplement (AFMS) Oxygen Section.

END

REVISION 29 ABNORMAL / EMERGENCY PROCEDURES

May 05/17 Page EH - 13
 Quick Reference Handbook

NOTES

ABNORMAL / EMERGENCY PROCEDURES REVISION 29

Page EH - 14 May 05/17
Quick Reference Handbook
Miscellaneous Index
Windshield Failure ....................................................................... EI-2
Cabin Window Cracked ............................................................... EI-3
Overweight Landing ..................................................................... EI-3
Ditching ......................................................................................... EI-4
Immediate Return for Landing .................................................... EI-6
Main Entrance Door Not Secure .................................................... EI-6
Planned Airplane Evacuation ......................................................... EI-7

Related Topics In QRH

Landing Planning Data .............................................. PC-1 thru PC-16
“G” Monitor System .................................................................... EG-11
“G” Monitor Versus Airplane Gross Weight Charts .................... EG-12

REVISION 26 ABNORMAL / EMERGENCY PROCEDURES

Oct 5 2011 Page EI - 1
 Quick Reference Handbook
Windshield Failure AFM 3-25-10

If windshield heat failure is detected, cycle the windshield heat control

OFF, then ON. If windshield heat can not be regained, flight may be
continued, but flight into icing conditions should be avoided. If failure
involves a front window, pull appropriate circuit breaker:
• L FRONT POWER (or L FRONT POWER or L FRONT WSHLD):
CP, J-8
• R FRONT POWER (or R FRONT POWER or R FRONT WSHLD):
CP, K-8
• L SIDE PWR (or L SIDE WSHLD): CP, J-10
• R SIDE PWR (or R SIDE WSHLD): CP, K-10
Windshield crack(s):
1. Upon detection of a crack in outer heating / protective windshield
ply, immediately turn windshield heat OFF on affected panel by
pulling the appropriate circuit breaker listed above and observe
icing restrictions.
2. Upon detection of a crack in either main structural windshield ply,
a reduction of cabin pressure differential to 7.5 psi is
recommended for remainder of flight.
3. Maintain current airspeed / mach or slower for remainder of flight.
4. Refer to GIV AFM Configuration Deviation List - Appendix B
for subsequent takeoff considerations.
WARNING: IF CRACKING IS TO THE INNER GLASS PLY, IT
IS RECOMMENDED THAT THE PILOT ADJACENT TO THE
CRACK AREA WEAR EYE PROTECTION SUCH AS SMOKE
GOGGLES.

END

ABNORMAL / EMERGENCY PROCEDURES REVISION 26

Page EI - 2 Oct 5 2011
Quick Reference Handbook
Cabin Window Cracked AFM 3-25-20

If the airplane is equipped with the optional cabin window heat

system, the middle pane that acts as the battery element may be
cracked.
If the middle pane is cracked:
1. Appropriate Cabin Window Heat Circuit Breaker ................... PULL
2. Report for maintenance action.
WARNING: IT IS RECOMMENDED THAT PASSENGER SEATS
ADJACENT TO THE CRACKED WINDOW BE VACATED.
3. Select an 8,000 ft cabin altitude on the cabin pressure selector
panel.
4. Descend to 35,000 ft or below.
5. Maintain cabin pressure differential. Maintain at 7.5 PSID or less.

END

Overweight Landing AFM 4-20-10

If landing at a weight in excess of maximum landing weight is

unavoidable, proceed as follows:
1. Longest Available Runway ................................................. UTILIZE
See Landing Planning Data (pages PC-1 thru PC-16) for
landing field length requirements.
CAUTION: TIRE SPEED LIMITATIONS WILL BE EXCEEDED IF
TOUCHDOWN IS MADE IN EXCESS OF 182 KNOTS GROUND
SPEED. (195 KNOTS GROUND SPEED WITH ASC 190 AND SN 1214
AND SUBSEQUENT).
2. Sink Rate and Crab Angle ................ MINIMIZE AT TOUCHDOWN
NOTE: Overweight landings are predicted data and have not been
verified by field performance test.
3. Maximum Reverse Thrust ....................................................APPLY
4. Report overweight landing for appropriate maintenance
inspections.
NOTE: For airplanes SN 1156 and subs., and airplanes SN 1000
through 1155 with ASC 118, the overweight landing inspection may not
be required if the recorded landing vertical acceleration is within limits.
See ‘G’ Monitor System, page EG-11, for additional information.

END

REVISION 26 ABNORMAL / EMERGENCY PROCEDURES

Oct 5 2011 Page EI - 3
 Quick Reference Handbook
Ditching AFM 4-20-20

No tests or actual ditching have been made. The following procedures

will improve the chances of a successful ditching.
1. Distress Message .......................................................... TRANSMIT
2. Fuel Load ........................................................................ MINIMUM
3. Cabin and Passengers ................................................... PREPARE
4. Heading ......................................................... PARALLEL SWELLS
5. Emergency Power ...................................................................... ON
6. Landing Gear .............................................................................. UP
NOTE: FOR SPZ 8400 EQUIPPED AIRPLANES: Silence landing gear
warning horn by pulling FWC #1 circuit breaker. FOR SPZ 8000
EQUIPPED AIRPLANES: Silence landing gear warning horn by pulling
TONE WARN #1 circuit breaker.
7. Flaps ........................................................................................... 39°
8. GPWS Voice Override ............................................................... ON
9. RAM AIR.................................................................................. RAM
NOTE: If RAM air is inoperative, select BOTH ECS PACKS – OFF.
10. Cabin Pressure Control .................................................... MANUAL
11. Outflow Valve ...................................................................... CLOSE
12. Differential Pressure .............................................................. ZERO
13. Stall Barrier ............................................................................... OFF
14. Final Approach Speed ............................................................ VREF
15. Descent Rate ..................................... APPROXIMATELY 200 FPM
16. Touchdown Configuration ............................................ESTABLISH
NOTE: Power levers should be closed, airplane rotated to normal
landing attitude (airspeed approximately 1.25 Vs), slightly nose up, and
contact made with water at minimum forward speed and minimum sink
rate. At water entry, expect airplane attitude to be approximately 7 to 8
degrees up. Airspeed at water entry should be just above stall speed.
This is to minimize structural damage following water contact.
17. Fire Handles .......................................................................... PULL
18. Life Rafts ......................................................................... REMOVE
19. Airplane .........................................................................ABANDON
Continued on next page 

ABNORMAL / EMERGENCY PROCEDURES REVISION 26

Page EI - 4 Oct 5 2011
Quick Reference Handbook
Ditching, ctd… AFM 4-20-20

CREW DUTIES FOLLOWING DITCHING:

Captain:
1. Emergency Exit Lights ................................................................ ON
2. Remove life raft #1 from stowed position. Tie life raft mooring line
to fastened seatbelt at forward exit window, either left or right
side.
3. Remove forward exit window and deploy life raft #1 out window.
4. Exit window and follow mooring line to life raft. Board life raft.
5. Direct passengers to follow mooring line to life raft. Assist
passengers into life raft.
First Officer:
1. Emergency Exit Lights ................................................................ ON
2. ELT ............................................................................................. ON
3. Remove life raft #2 from stowed position. Tie life raft mooring line
to fastened seatbelt at aft exit window - same side as raft #1.
4. Remove aft exit window and deploy life raft #2 out window.
5. Exit window and follow mooring line to life raft #2. Board raft.
6. Direct passengers to follow mooring line to life raft. Assist
passengers into life raft.
Cabin Crewmember (If Onboard):
1. Assist Captain and First Officer in obtaining life rafts #1 and #2
from stowed position.
2. Assist Captain and First Officer with securing life rafts by tying life
raft mooring line to fastened seatbelt at exit windows.
3. Direct Captain and First Officer to open exit windows and deploy
life rafts.
NOTE: For passenger accountability, life rafts go out same side of
airplane.
4. Have Captain and First Officer follow life raft mooring lines to rafts
and board.
5. Continue to direct evacuation from inside airplane. Assist
passengers.
Continued on next page 
REVISION 27 ABNORMAL / EMERGENCY PROCEDURES
Dec 10/12 Page EI - 5
 Quick Reference Handbook
Ditching, ctd… AFM 4-20-20

6. If time permits, gather first aid kit, blankets, food, garbage bags,
etc., to take to life rafts.
7. Depart via exit window and board life raft.

END

Immediate Return for Landing AFM 4-20-50

NOTE: If an immediate return to the departure airport is required for any

reason, the landing should be accomplished using 39° flaps (if available) and
the longest runway available. If less than 39° flaps are to be used for landing,
the flight crew should consider runway length requirements, brake energy
requirements, and tire-speed limitations. If there is any doubt, the flight crew
should consider diversion to an airport with a longer runway or delaying
landing until a lower airplane weight is attained.
NOTE: If the airplane is over max gross landing weight refer to overweight
landing procedure in this section.
1. Final Approach Speed ............................................................. VREF
If landing with flaps less than 39°, perform Step 2. If landing with
flaps 39°, proceed to Step 3.
2. GPWS / GND SPLR FLAP ORIDE ............................................ ON
3. Landing Area ..............................FIRST 1,000 FEET OF RUNWAY
4. Sink Rate / Crab Angle .......... MINIMIZE PRIOR TO TOUCHDOWN
5. Maximum Reverse Thrust .................................................... APPLY
6. Brake Temperatures .......................................................................
...................................... MONITOR AFTER LANDING (if available)

END

Main Entrance Door Not Secure AFM 4-25-10

WARNING: DO NOT TOUCH THE SECONDARY LATCH HANDLE OR

THE DOOR RELEASE HANDLE.
1. Door Locking Handles and Bayonet Notches .. VISUALLY CHECK

ABNORMAL / EMERGENCY PROCEDURES REVISION 27

Page EI - 6 Dec 10/12
Quick Reference Handbook
Main Entrance Door Not Secure, ctd… AFM 4-25-10

If main door appears to be secure and the locked (extended)

position of the Bayonet Latches can be confirmed visually.
2. Flight ............................................................................. CONTINUE
If main door does not appears to be secure:
3. Cabin Pressure Differential (DFRN PRESS) .................... REDUCE
4. Airplane........................................ LAND AS SOON AS POSSIBLE

END

Planned Airplane Evacuation OM 5-20-50

During evacuation, all occupants should stay as close to the floor as

possible to enhance visibility and maximize breathable air. If the
external baggage compartment door is used, advise the passengers
that the door is approximately seven feet above the ground with
landing gear extended. Once out of the airplane, direct passengers to
a safe location upwind of the airplane. Order passengers to remain in
a group and not to smoke.
1. Airplane.................................................................................. STOP
2. Parking Brake ........................................................................... SET
3. Ground Spoilers ........................................................................ OFF
4. Speed Brakes ....................................................................... STOW
5. Flaps ..................................................................................... DOWN
6. CABIN PRESSURE CONTROL ....................................... MANUAL
7. Outflow Valve............................................................... FULL OPEN
8. ATC..................................................................................... NOTIFY
9. L / R FUEL COCKS .................................................................. OFF
10. APU MASTER .......................................................................... OFF
11. L / R FIRE Handles ................................................................. PULL
12. L / R FIRE Handles .........ROTATE FULLY TO DISCH 1 / DISCH 2
13. BATTERIES 1 and 2 ................................................................. OFF
14. Passengers / Crew ....................................................... EVACUATE

END

REVISION 26 ABNORMAL / EMERGENCY PROCEDURES

Oct 5 2011 Page EI - 7
 Quick Reference Handbook
Notes

ABNORMAL / EMERGENCY PROCEDURES REVISION 26

Page EI - 8 Oct 5 2011
Quick Reference Handbook
Supplemental Procedures / Data Index
Windshear / Microburst ................................................................... S-2
Volcanic Ash Encounter .................................................................. S-4
Heavy Rain / Hail Encounter ........................................................... S-5
Turbulence Penetration / Severe Gust Encounter .......................... S-7
Bird Ingestion .................................................................................. S-9
Lightning Strike .............................................................................. S-10
Circuit Breaker Listing Disclaimer ................................................. S-12
Circuit Breakers Listed By Bus and Group ................................... S-13
Alphabetical List of Circuit Breakers ............................................. S-31
Emergency Airplane Evacuation ............................................... S-56

REVISION 24 (RE-ISSUE) SUPPLEMENTAL PROCEDURES / DATA

Mar 17/10 Page S - 1
 Quick Reference Handbook
Windshear / Microburst AFM APP E

Low-level windshear, microburst, or downburst may develop within an

unstable air mass, during frontal passage, and in the vicinity of
thunderstorms. These conditions can create rapidly changing wind
directions and velocities. An even more dangerous condition can
result from high velocity down flows that can force the aircraft into
ground impact unless very prompt and drastic actions are taken.
Severe microbursts may occur with greater frequency than originally
believed. However, they are of short duration, two (2) to five (5)
minutes, about two(2) miles in diameter, and can have a down flow in
center of as much as 6000to 7000 feet per minute.
INCREASING PERFORMANCE CONDITIONS:
Significant airspeed and altitude gain may be caused by increasing
headwind, decreasing tailwind and updrafts.
Takeoff:
When the amber WS caution annunciator (if installed) illuminates
during takeoff, or the crew recognizes the signs of increasing
performance conditions, the following procedures should be
followed:
1. The flight crew should be alerted to the possibility that the
increased performance could be followed by decreasing
performance conditions.
2. Attitude and power (thrust) corrections should be minor, in order to
minimize any “fall-off” in performance when the proverse windshear
event ends.
Approach / Landing:
When the amber WS caution annunciator (if installed) illuminates
during final approach, or the crew recognizes the signs of
increasing performance conditions, the following procedures
should be followed:
1. The flight crew should be alerted to the possibility of decreasing
performance conditions. Coupled with other weather factors,
initiating a go-around as early as possible should be considered.
2. Wind and gust allowances should be added to the approach speed,
increasing thrust if necessary. It may be necessary to disengage
autopilot/autothrottle.
Continued on next page 

SUPPLEMENTAL PROCEDURES / DATA REVISION 24 (RE-ISSUE)

Page S - 2 Mar 17/10
Quick Reference Handbook
Windshear / Microburst. ctd… AFM APP E

3. Avoid sinking below the approach glidepath or letting the power

levers remain at flight idle for extended periods of time.
DECREASING PERFORMANCE CONDITIONS:
Significant airspeed and altitude loss may be caused by decreasing
headwind, increasing tailwind and downdrafts.
When conditions exist where low-level windshear, microburst, or
downburst may be present, the pilot should consider diversion to an
alternate airport or delay takeoff or landing until the risk of an
encounter is minimized. If the condition is unavoidable or
unexpectedly encountered, the flight crew may expect a rapid decay
in airspeed and/or an increase in sink rate.
Takeoff:
When the audible "WIND SHEAR--WIND SHEAR--WIND SHEAR"
WARNING occurs, and the red WS WARN annunciator (if
installed) is illuminated during takeoff, or the flight crew
recognizes the signs of decreasing performance conditions, the
following procedures should be followed:
1. The flight crew should be alerted to the possibility of subsequent
decreasing performance conditions.
2. Disconnect the Autopilot and apply Go-Around Power.
3. Rotate at 3 to 4 degrees per seconds to increase pitch attitude to
the highest possible value.
4. When stick shaker is encountered, or as V2 / VREF is approached,
reduce pitch rate/angle of attack to intercept V2 / VREF -20 KCAS.
5. Engine overboost should be avoided unless the airplane
continues to descend and airplane safety is in doubt. When
airplane safety has been assured, adjust thrust to maintain engine
parameters within approved limits.
6. DO NOT retract flaps or landing gear until safe climb-out is
assured.

Continued on next page 

REVISION 24 (RE-ISSUE) SUPPLEMENTAL PROCEDURES / DATA

Mar 17/10 Page S - 3
 Quick Reference Handbook
Windshear / Microburst. ctd… AFM APP E

Approach / Landing:
When the audible "WIND SHEAR--WIND SHEAR--WIND SHEAR"
WARNING occurs, and the red WS WARN annunciator (if
installed) is illuminated during final approach, or the flight crew
recognizes the signs of decreasing performance conditions, the
following procedures should be followed:
1. The flight crew should be alerted to the possibility of subsequent
decreasing performance conditions.
2. Disconnect the Autopilot and apply Go-Around Power.
3. Rotate at 3 to 4 degrees per seconds to increase pitch attitude to
the highest possible value.
4. When stick shaker is encountered, or as V2/VREF is approached,
reduce pitch rate/angle of attack to intercept V2/VREF -20 KCAS.
5. Engine overboost should be avoided unless the airplane continues
to descend and airplane safety is in doubt. When airplane safety
has been assured, adjust thrust to maintain engine parameters
within approved limits.
6. DO NOT retract flaps or landing gear until safe climb-out is
assured.

END

Volcanic Ash Encounter AFM APP E

Flight through volcanic ash should be avoided. If volcanic ash is

encountered, reverse course to clear the ash cloud and inform ATC.
The autothrottle should be disconnected. A low power setting is
recommended (idle is preferred), with airstart ignition OFF.
Volcanic ash may be difficult to detect, however, flight crews have
reported the following indications:
• Smoke and dust with acrid odor, similar to electrical smoke,
appearing in cockpit.
• Engine malfunction, e.g., a surge condition with increasing TGT
and/or flameout.

Continued on next page 

SUPPLEMENTAL PROCEDURES / DATA REVISION 24 (RE-ISSUE)

Page S - 4 Mar 17/10
Quick Reference Handbook
Volcanic Ash Encounter, ctd… AFM APP E

• At night, St. Elmo's fire and/or static discharge may be seen

around the windshield. (If static discharge is observed, select the
windshield heat OFF.)
If one or both engines flame out, an immediate relight is not
recommended until clear of ash cloud.
If both engines flame out and as RPM is decreasing, perform the
following steps IMMEDIATELY:
1. Reverse course to clear the ash cloud and inform ATC or
encounter and course change.
2. Altitude / Airspeed ................................... DESCEND AT VMO/MMO
TO 25,000 FT, THEN SLOW TO 210 KCAS
NOTE: Use of speed brakes is not recommended. Use of the Standby
Electrical Power System (ABEX) generator is not possible with a
windmilling engine.
CAUTION: MANEUVERS SHOULD BE LIMITED TO THE MINIMUM
NECESSARY BANK AND PITCH ANGLES, SINCE HYDRAULIC
BOOST WILL BE LOST AS RPM DECAYS.
WARNING: ENGINE DAMAGE MAY RESULT IF RPM IS NOT
ALLOWED TO STABILIZE AT IDLE BEFORE ADVANCING POWER
LEVERS.
3. Descent To Airstart Envelope .. CONTINUE / CLEAR ASH CLOUD
(Sea Level to 25,000 ft and 200 KCAS to 324 KCAS)
4. Dual Engine Flameout Procedure (Page EC-5) ........... CONSULT

END

Heavy Rain / Hail Encounter AFM APP E

The Tay engine is tolerant of water ingestion rates normally

encountered in flight. During flight through heavy rain or hail, it is
possible that there may be fluctuations in engine parameters, in
particular, a noticeable drop in indicated TGT.
The following general procedures are recommended if heavy rain or
hail is encountered:
• Avoid rapid power adjustments, if possible.
• Select Airstart Ignition (L / R AIR START IGN) to ON.

Continued on next page 

REVISION 28 SUPPLEMENTAL PROCEDURES / DATA

May 25/16 Page S - 5
 Quick Reference Handbook
Heavy Rain / Hail Encounter, ctd… AFM APP E

• Select autothrottle to OFF.

• Maintain as high a power setting as possible.
Engine parameters should return to normal immediately on leaving
the area of heavy rain.
If both engines flame out, an immediate relight is recommended.
As engine RPM is decreasing, perform the following steps
IMMEDIATELY:
1. Power Levers .......................................................................... IDLE
2. Airstart Ignition (L / R AIR START IGN) ..................................... ON
3. Altitude / Airspeed ................................... DESCEND AT VMO/MMO
TO 25,000 FT, THEN SLOW TO 210 KCAS
NOTE: Use of speed brakes is not recommended. Use of the Standby
Electrical Power System (ABEX) generator is not possible with a
windmilling engine.
CAUTION: MANEUVERS SHOULD BE LIMITED TO THE MINIMUM
NECESSARY BANK AND PITCH ANGLES, SINCE HYDRAULIC
BOOST WILL BE LOST AS RPM DECAYS.
CAUTION: FOR AIRPLANES SN 1000 THROUGH 1249 WITHOUT
ASC 304: THE DUTY CYCLE FOR CONTINUOUS (AIRSTART)
IGNITION WITHOUT ASC 304 IS FIVE (5) MINUTES ON AND THIRTY
(30) MINUTES OFF FOR COOLING. THERE IS NO LIMITATION ON
THE IGNITION WHEN USED IN A THIRTY (30) SECONDS ON, THIRTY
(30) SECONDS OFF CYCLE.
CAUTION: FOR AIRPLANES SN 1250 AND SUBSEQUENT, AND
SN 1000 THROUGH 1249 WITH ASC 304: THERE IS NO DUTY
CYCLE TIME LIMITATION FOR CONTINUOUS (AIRSTART) IGNITION
WITH ASC 304.
CAUTION: ENGINE DAMAGE MAY RESULT IF RPM IS NOT
ALLOWED TO STABILIZE AT IDLE BEFORE ADVANCING POWER
LEVERS.
If engine(s) DO NOT relight:
1. Descent To Airstart Envelope .......................................CONTINUE
(Sea Level to 25,000 ft and 200 KCAS to 324 KCAS)
2. Airplane ..... PROCEED TO NEAREST SUITABLE LANDING SITE
3. Dual Engine Flameout Procedure (Page EC-5) ........... CONSULT

END

SUPPLEMENTAL PROCEDURES / DATA REVISION 28

Page S - 6 May 25/16
Quick Reference Handbook
Turbulence Penetration / Severe Gust Encounter
AFM APP E

Turbulence penetration procedures apply to flying at altitude and

should not be confused with the low altitude wind shear precautions
recommended for the traffic pattern and landing approach phase of
the mission.
If possible, flight through turbulence should be avoided. Flying the
recommended speeds at reduced altitudes produces greater buffet
margins for the same intensity of turbulence.
Continued use of the autopilot will reduce pilot workload. However,
use of the Flight Director (FD) vertical modes is not advised in severe
turbulence. The basic pitch attitude and heading hold autopilot modes
will reduce excessive control surface motion and attitude changes in
severe turbulence. Airplane pitch motions and ride qualities are
aggravated when FD vertical modes are engaged during these flight
conditions.
The following general procedures are recommended if SEVERE gust
turbulence is encountered:
• Avoid rapid power adjustments, if possible.
• Select Airstart Ignition (L / R AIR START IGN) to ON.
• Select autothrottle to OFF.
If both engines flame out, an immediate relight is recommended.
As engine RPM is decreasing, perform the following steps
IMMEDIATELY:
1. Power Levers ........................................................................... IDLE
2. Airstart Ignition (L / R AIR START IGN) ..................................... ON
3. Altitude / Airspeed .......DESCEND AT 270 KCAS / 0.75 MT UNTIL
OUT OF TURBULENCE, THEN DESCEND AT V MO/MMO TO
25,000 FEET
NOTE: Use of speed brakes is not recommended. Use of the Standby
Electrical Power System (ABEX) generator is not possible with a
windmilling engine.
CAUTION: MANEUVERS SHOULD BE LIMITED TO THE MINIMUM
NECESSARY BANK AND PITCH ANGLES, SINCE HYDRAULIC
BOOST WILL BE LOST AS RPM DECAYS.
CAUTION: FOR AIRPLANES SN 1000 THROUGH 1249 WITHOUT
ASC 304: THE DUTY CYCLE FOR CONTINUOUS (AIRSTART)
IGNITION WITHOUT ASC 304 IS FIVE (5) MINUTES ON AND THIRTY
(30) MINUTES OFF FOR COOLING. THERE IS NO LIMITATION ON
THE IGNITION WHEN USED IN A THIRTY (30) SECONDS ON, THIRTY
(30) SECONDS OFF CYCLE.
Continued on next page 

REVISION 28 SUPPLEMENTAL PROCEDURES / DATA

May 25/16 Page S - 7
 Quick Reference Handbook
Turbulence Penetration / Severe Gust Encounter, ctd… AFM APP E

CAUTION: FOR AIRPLANES SN 1250 AND SUBSEQUENT, AND

SN 1000 THROUGH 1249 WITH ASC 304: THERE IS NO DUTY
CYCLE TIME LIMITATION FOR CONTINUOUS (AIRSTART) IGNITION
WITH ASC 304.
CAUTION: ENGINE DAMAGE MAY RESULT IF RPM IS NOT
ALLOWED TO STABILIZE AT IDLE BEFORE ADVANCING POWER
LEVERS.
If engine(s) DO NOT relight:
1. Descent To Airstart Envelope .......................................CONTINUE
(Sea Level to 25,000 ft and 200 KCAS to 324 KCAS)
2. Airplane ..... PROCEED TO NEAREST SUITABLE LANDING SITE
3. Dual Engine Flameout Procedure (Page EC-5) ........... CONSULT
Airspeed Parameters:
1. Recommended turbulence penetration airspeed is 270 KCAS /
0.75 MT, whichever is lower.
2. A minimum speed of 1.5 VS is recommended to maintain
adequate buffet margins.
3. Severe turbulence will cause large and often rapid variations in
indicated airspeed.
CAUTION: DO NOT CHASE AIRSPEED.
Attitude Parameters:
1. Maintain the desired pitch attitude and keep wings level.
2. Large and sudden control and power changes should be avoided.
Passenger Warning:
1. ST BELT and/or NO SMOK/ST BELT Switch ............................ ON
If Autopilot is ON:
1. Use of the basic autopilot ATTITUDE and HEADING HOLD
modes is recommended.
2. Avoid use of flight director VERTICAL modes.
3. Pilot inputs should be made using the turn and pitch controller, if
installed.
Continued on next page 

SUPPLEMENTAL PROCEDURES / DATA REVISION 28

Page S - 8 May 25/16
Quick Reference Handbook
Turbulence Penetration / Severe Gust Encounter, ctd… AFM APP E

4. Avoid using touch control steering in severe turbulence.

5. Severe conditions may cause the autopilot to disengage.
If Autopilot is OFF or Disengaged:
1. Hand-flying the airplane again requires basic attitude control.
2. Pitch and roll may best be controlled with the control yoke only.
3. Use of rudder is not recommended and may actually aggravate
the situation.
Yaw Damper:
WARNING: DO NOT FLY INTO AREAS OF KNOWN SEVERE
TURBULENCE WITH A FAILED YAW DAMPER.
1. The yaw damper should be engaged at all times.
2. If in turbulence with yaw damper inoperative or disengaged, avoid
chasing airplane motion with rudder. Attempt to hold rudder
pedals stationary and wings level.

END

Bird Ingestion AFM APP E

If both engines flame out, an immediate relight is recommended.

As engine RPM is decreasing, perform the following steps
IMMEDIATELY:
1. Power Levers ........................................................................... IDLE
2. Airstart Ignition (L / R AIR START IGN) ..................................... ON
3. Altitude / Airspeed .................................. DESCEND AT 210 KCAS
If at low altitude and unable to achieve immediate relight, prepare for
a dual engine out landing. See Engines Index, page EC-1, for
procedures as appropriate.
NOTE: Use of speed brakes is not recommended. Use of the Standby
Electrical Power System (ABEX) generator is not possible with a
windmilling engine.
CAUTION: MANEUVERS SHOULD BE LIMITED TO THE MINIMUM
NECESSARY BANK AND PITCH ANGLES, SINCE HYDRAULIC
BOOST WILL BE LOST AS RPM DECAYS.
Continued on next page 

REVISION 28 SUPPLEMENTAL PROCEDURES / DATA

May 25/16 Page S - 9
 Quick Reference Handbook
Bird Ingestion, ctd…. AFM APP E

CAUTION: FOR AIRPLANES SN 1000 THROUGH 1249 WITHOUT

ASC 304: THE DUTY CYCLE FOR CONTINUOUS (AIRSTART)
IGNITION WITHOUT ASC 304 IS FIVE (5) MINUTES ON AND THIRTY
(30) MINUTES OFF FOR COOLING. THERE IS NO LIMITATION ON
THE IGNITION WHEN USED IN A THIRTY (30) SECONDS ON, THIRTY
(30) SECONDS OFF CYCLE.
CAUTION: FOR AIRPLANES SN 1250 AND SUBSEQUENT, AND
SN 1000 THROUGH 1249 WITH ASC 304: THERE IS NO DUTY
CYCLE TIME LIMITATION FOR CONTINUOUS (AIRSTART) IGNITION
WITH ASC 304.
CAUTION: ENGINE DAMAGE MAY RESULT IF RPM IS NOT
ALLOWED TO STABILIZE AT IDLE BEFORE ADVANCING POWER
LEVERS.
If engine(s) DO NOT relight:
1. Descent To Airstart Envelope .......................................CONTINUE
(Sea Level to 25,000 ft and 200 KCAS to 324 KCAS)
2. Airplane ..... PROCEED TO NEAREST SUITABLE LANDING SITE
3. Dual Engine Flameout Procedure (Page EC-5) ......... CONSULT

END

Lightning Strike AFM APP E

The theory that lightning strikes will be avoided if thunderstorms are

avoided, or radar-indicated precipitation is avoided by greater than
twenty (20) miles, is false. Research and experience has shown that
airplanes have been struck by lightning in clear air (especially at
higher altitudes), at distances of up to 50 miles from thunderstorms
and radar-indicated precipitation – the proverbial “Bolt From The
Blue”. Electrical activity generated by thunderstorms may exist even
after the thunderstorm cell has decayed.
Research and experience has also shown that flight through
precipitation, volcanic ash or heavily polluted air can cause an
airplane to experience electrostatic discharge or “triggered” lightning.
The probability of a lightning strike to an airplane flying in or near a
thunderstorm increases from a minimum at the thunderstorm base to
a maximum at the 36,000 to 40,000 foot level.
Continued on next page 

SUPPLEMENTAL PROCEDURES / DATA REVISION 28

Page S - 10 May 25/16
Quick Reference Handbook
Lightning Strike, ctd… AFM APP E

Lightning strikes at high altitude generally result in greater total

charge transfers, and damage is usually worse for large total current
transfers. The entire surface of the airplane may be susceptible to
lightning attachment. However, strikes are more probable to particular
areas such as the airplane's extremities (nose, wingtips, tail) and
composite surfaces.
If both engines flame out, an immediate relight is recommended.
As engine RPM is decreasing, perform the following steps
IMMEDIATELY:
1. Power Levers ........................................................................... IDLE
2. Airstart Ignition (L / R AIR START IGN) ..................................... ON
3. Altitude / Airspeed ................................... DESCEND AT VMO/MMO
TO 25,000 FT, THEN SLOW TO 210 KCAS
NOTE: Use of speed brakes is not recommended. Use of the Standby
Electrical Power System (ABEX) generator is not possible with a
windmilling engine.
CAUTION: MANEUVERS SHOULD BE LIMITED TO THE MINIMUM
NECESSARY BANK AND PITCH ANGLES, SINCE HYDRAULIC
BOOST WILL BE LOST AS RPM DECAYS.
CAUTION: FOR AIRPLANES SN 1000 THROUGH 1249 WITHOUT
ASC 304: THE DUTY CYCLE FOR CONTINUOUS (AIRSTART)
IGNITION WITHOUT ASC 304 IS FIVE (5) MINUTES ON AND THIRTY
(30) MINUTES OFF FOR COOLING. THERE IS NO LIMITATION ON
THE IGNITION WHEN USED IN A THIRTY (30) SECONDS ON, THIRTY
(30) SECONDS OFF CYCLE.
CAUTION: FOR AIRPLANES SN 1250 AND SUBSEQUENT, AND
SN 1000 THROUGH 1249 WITH ASC 304: THERE IS NO DUTY
CYCLE TIME LIMITATION FOR CONTINUOUS (AIRSTART) IGNITION
WITH ASC 304.
CAUTION: ENGINE DAMAGE MAY RESULT IF RPM IS NOT
ALLOWED TO STABILIZE AT IDLE BEFORE ADVANCING POWER
LEVERS.
If engine(s) DO NOT relight:
1. Descent To Airstart Envelope ....................................... CONTINUE
(Sea Level to 25,000 ft and 200 KCAS to 324 KCAS)
2. Airplane..... PROCEED TO NEAREST SUITABLE LANDING SITE
3. Dual Engine Flameout Procedure (Page EC-5) ........... CONSULT

END

REVISION 28 SUPPLEMENTAL PROCEDURES / DATA

May 25/16 Page S - 11
 Quick Reference Handbook
Circuit Breaker Listing Disclaimer GAC

Disclaimer
The circuit breaker listings in this section are based on the production
airplane. Differences will exist from these lists when systems or
functionality were added during the completion phase or post entry-
into-service by another mod center prior to the same items being
incorporated as part of the production airplane.

SUPPLEMENTAL PROCEDURES / DATA REVISION 28

Page S - 12 May 25/16
Quick Reference Handbook
Essential DC Bus Circuit Breakers
Circuit Breaker Name Panel Loc. Control
PILOT 1 PDB
AC EXT PWR PO A-8 PILOT 1
AFT EMER BATT P I-13 PILOT 1
AIR INLET DOOR PO C-11 PILOT 1
APU FIRE EXT P I-10 PILOT 1
BATT AMMETER PO A-7 PILOT 1
BATT CHGR CONT PO A-6 PILOT 1
BOT A/C LT GND OPER P E-6* PILOT 1
BOT A/C LT GND OPER P F-9* PILOT 1
CABIN PRESS IND PO A-12 PILOT 1
CKPT TEMP CONT PO B-13 PILOT 1
CKPT/CABIN TEMP IND PO A-11 PILOT 1
ELWS #1 PO A-9 PILOT 1
ENGINE START P K-6 PILOT 1
EPMP SW PWR #1 PO A-5 PILOT 1
ESS DC VM P D-13 PILOT 1
FUEL PUMP IND PO A-4 PILOT 1
FUEL X FLOW V PO D-2 PILOT 1
FWD IMPACT P J-13 PILOT 1
L #1 IGN P I-8 PILOT 1
L AIR COND PO C-13 PILOT 1
L BLEED AIR PO A-10 PILOT 1
L FIRE DET LOOP B P G-6 PILOT 1
L FUEL S/O PO A-2 PILOT 1
L FUELING S/O PO A-3 PILOT 1
L SEC LOCK P G-7 PILOT 1
L T/REV CONTROL P I-7 PILOT 1
MAIN PUMP CONT PO A-1 PILOT 1
R #1 IGN P I-9 PILOT 1
R BLEED AIR IND PO C-12 PILOT 1
SGL PACK PO C-14 PILOT 1
WARN LTS PWR #1 P F-1 PILOT 1
WARN LTS PWR #2 P F-2 PILOT 1
WARN LTS PWR #3 P F-3 PILOT 1
WARN LTS PWR #4 P F-4 PILOT 1
WARN LTS PWR #5 P F-5 PILOT 1
WARN LTS PWR #6 P G-1* PILOT 1
WARN LTS PWR #6 P G-2* PILOT 1
WARN LTS PWR #7 P G-2* PILOT 1
WARN LTS PWR #7 P G-3* PILOT 1
WHEEL WELL LTS P F-6* PILOT 1
WHEEL WELL LTS P F-10* PILOT 1
* Depending on effectivity. Continued on next page 

REVISION 24 (RE-ISSUE) SUPPLEMENTAL PROCEDURES / DATA

Mar 17/10 Page S - 13
 Quick Reference Handbook
Essential DC Bus Circuit Breakers, ctd…

Circuit Breaker Name Panel Loc. Control

PILOT 2 PDB
#2 STANDBY WARN PWR P B-1 PILOT 2
AFT IMPACT P K-13 PILOT 2
ANN LTS CONT STBY P B-3* PILOT 2
ANN LTS CONT STBY P C-3* PILOT 2
APU START P H-10 PILOT 2
BACKUP CONT PWR PO B-7 PILOT 2
BATT CHGR FAIL ANNUN PO B-6 PILOT 2
CABIN PRESS 28V PO B-11 PILOT 2
CABIN TEMP CONT PO D-14 PILOT 2*
DOME LT P B-6 PILOT 2
ELWS #2 PO B-9 PILOT 2
EPMP SW PWR #2 PO B-5 PILOT 2
FIRE BELL P B-4* PILOT 2
FIRE BELL P B-5* PILOT 2
FIRE BELL P C-4* PILOT 2
FIRE EXT SHOT #2 P H-8 PILOT 2
FLAP/STAB WARN P D-3 PILOT 2
FUEL INTERTANK V PO B-4 PILOT 2
FUEL LOW LEVEL PO B-1 PILOT 2
FWD EMER BATT P H-13 PILOT 2
L BLEED AIR IND PO B-12 PILOT 2
OVHD ANN LTS PWR #4 P A-4* PILOT 2
OVHD ANN LTS PWR #4 P C-4* PILOT 2
OVHD ANN LTS PWR #5 P A-5* PILOT 2
OVHD ANN LTS PWR #5 P C-5* PILOT 2
OVHD PNL PRI P B-9 PILOT 2
PED ANN LTS PWR P D-2 PILOT 2
R AIR COND PO D-13 PILOT 2
R BLEED AIR PO B-10 PILOT 2
R CKPT ANN LTS PWR P B-2* PILOT 2
R CKPT ANN LTS PWR P C-2* PILOT 2
R ENG O'HT P H-9 PILOT 2
R FIRE DET LOOP B P H-6 PILOT 2
R FUEL S/O PO B-2 PILOT 2
R FUELING S/O PO B-3 PILOT 2
R SEC LOCK P H-7 PILOT 2
SPD BRAKE/FLAP ALARM P D-4 PILOT 2
STBY PWR CONT P H-12 PILOT 2
UTILITY LTS P D-9* PILOT 2
UTILITY LTS P E-9* PILOT 2
WARN LTS PWR #10 P G-5* PILOT 2
WARN LTS PWR #10 P H-3* PILOT 2
WARN LTS PWR #11 P H-3* PILOT 2
WARN LTS PWR #11 P H-4* PILOT 2
* Depending on effectivity. Continued on next page 
SUPPLEMENTAL PROCEDURES / DATA REVISION 24 (RE-ISSUE)
Page S - 14 Mar 17/10
Quick Reference Handbook
Essential DC Bus Circuit Breakers, ctd…
Circuit Breaker Name Panel Loc. Control
PILOT 2, ctd… PDB
WARN LTS PWR #12 P H-4* PILOT 2
WARN LTS PWR #12 P H-5* PILOT 2
WARN LTS PWR #13 P H-5* PILOT 2
WARN LTS PWR #13 P I-4* PILOT 2
WARN LTS PWR #14 P I-4* PILOT 2
WARN LTS PWR #14 P I-5* PILOT 2
WARN LTS PWR #15 P I-5* PILOT 2
WARN LTS PWR #15 P J-5* PILOT 2
WARN LTS PWR #8 P G-3* PILOT 2
WARN LTS PWR #8 P G-4* PILOT 2
WARN LTS TEST P B-4* PILOT 2
WARN LTS TEST P J-5* PILOT 2
PILOT 3 PDB
#1 STANDBY WARN PWR P A-1 PILOT 3
ANN LTS CONT MAIN P A-3* PILOT 3
ANN LTS CONT MAIN P B-3* PILOT 3
APU FIRE WARN P A-4* PILOT 3
APU FIRE WARN P B-4* PILOT 3
APU PWR #3 P L-10 PILOT 3
ENGINE OILER P G-10* PILOT 3
ENGINE OILER P L-9* PILOT 3
FIRE EXT SHOT #1 P G-8 PILOT 3
FLOOD LTS OVERRIDE P A-6 PILOT 3
L #2 IGN P J-8 PILOT 3
L CKPT ANN LTS PWR P A-2* PILOT 3
L CKPT ANN LTS PWR P B-2* PILOT 3
L ENG O'HT P G-9 PILOT 3
L FIRE DET LOOP A P I-6 PILOT 3
L FLT PNL/GSHLD P A-7 PILOT 3
L T/R EMER STOW P K-7* PILOT 3
L T/R EMER STOW P L-7* PILOT 3
LDG WARN HORN P E-4 PILOT 3
OVHD ANN LTS PWR #1 P A-1* PILOT 3
OVHD ANN LTS PWR #1 P C-1* PILOT 3
OVHD ANN LTS PWR #2 P A-2* PILOT 3
OVHD ANN LTS PWR #2 P C-2* PILOT 3
OVHD ANN LTS PWR #3 P A-3* PILOT 3
OVHD ANN LTS PWR #3 P C-3* PILOT 3
R #2 IGN P J-9 PILOT 3
R FIRE DET LOOP A P J-6 PILOT 3
R T/R EMER STOW P L-7 PILOT 3
R T/REV CONTROL P J-7 PILOT 3
T/R EMER STOW P K-7 PILOT 3
TONE WARN #1 P A-5 PILOT 3
* Depending on effectivity. Continued on next page 

REVISION 24 (RE-ISSUE) SUPPLEMENTAL PROCEDURES / DATA

Mar 17/10 Page S - 15
 Quick Reference Handbook
Essential DC Bus Circuit Breakers, ctd…

Circuit Breaker Name Panel Loc. Control

COPILOT 1 PDB
AOA PRB HTR #1 CP L-14 COPILOT 1
BUS CONT #1 CP K-2 COPILOT 1
BUS CONT #3 CP M-2 COPILOT 1
CKPT VOICE RECORDER CP D-13 COPILOT 1*
COMB HYD PRESS CPO A-3 COPILOT 1
COMB HYD QTY CPO A-4 COPILOT 1
DAU #1A CP A-14 COPILOT 1
DBDI #1 CP F-4* COPILOT 1
DDRMI #1 CP F-4* COPILOT 1
DISPLAY UNIT #1 CP E-6 COPILOT 1
FGC #1 CPO A-7 COPILOT 1
FLT HYD PRESS CPO C-4 COPILOT 1
FWC #1 CP A-13 COPILOT 1
IRU #1 DC SEC CP J-5 COPILOT 1
L HYD S/O CPO A-5 COPILOT 1
L NUTCRACKER CPO A-13 COPILOT 1
L PITOT HT CONT CP L-12 COPILOT 1
MANUAL FLAP CONT CPO A-1 COPILOT 1
SHAKER #1 CPO A-10 COPILOT 1
STAB AUG SERVO #1 CPO A-6 COPILOT 1
STALL BARR DUMP VALVE CPO A-8 COPILOT 1
STALL BARR VALVE #1 CPO A-12 COPILOT 1
STALL BARRIER #1 CPO A-9 COPILOT 1
STALL WARN CMPTR #1 CPO A-11 COPILOT 1
STBY PITOT HT CONT CP L-13 COPILOT 1
SYM GEN #1 CP K-3 COPILOT 1
UTILITY HYD PUMP OFF CPO C-3 COPILOT 1

COPILOT 2 PDB
A/P SERVO #1 CPO C-8 COPILOT 2
APPLIED BRAKE PRESS CPO D-6 COPILOT 2
AUX HYD PRESS CPO D-4 COPILOT 2
AUX HYD PUMP CPO D-5 COPILOT 2
BCS CHL #2 CPO B-2 COPILOT 2
BUS CONT #2 CP L-2 COPILOT 2
CVR SHUTDOWN CP E-13 COPILOT 2
DADC #1 CP F-3 COPILOT 2
DAU #2B CP D-14 COPILOT 2
DBDI #2 CP G-4* COPILOT 2
DDRMI #2 CP G-4* COPILOT 2
DISPLAY CONT #1 CP F-5 COPILOT 2
DISPLAY MASTER #2 CP J-2 COPILOT 2
DISPLAY UNIT #3 CP G-6 COPILOT 2
DISPLAYS FAN #1 CP D-5 COPILOT 2*
* Depending on effectivity. Continued on next page 
SUPPLEMENTAL PROCEDURES / DATA REVISION 24 (RE-ISSUE)
Page S - 16 Mar 17/10
Quick Reference Handbook
Essential DC Bus Circuit Breakers, ctd…

Circuit Breaker Name Panel Loc. Control

COPILOT 2, ctd… PDB
DOOR CONT/WARN CPO B-8 COPILOT 2
FDR CONT #1 CP C-8 COPILOT 2
FLAP CONT CPO B-1 COPILOT 2
FLT GDNC PNL #1 CPO C-7 COPILOT 2
FLT HYD QTY CPO B-4 COPILOT 2
NAV/DME CONT # 1 CP D-9 COPILOT 2
NUTCRACKER CPO B-13 COPILOT 2
R COWL A/I PRESS CP K-12 COPILOT 2
R COWL ANTI-ICE CP K-13 COPILOT 2
R HYD S/O CPO B-5 COPILOT 2
R NUTCRACKER CPO C-13 COPILOT 2
R WING ANTI-ICE CP K-14 COPILOT 2
RH RR FAN CONT CP I-1 COPILOT 2
STEER BY WIRE #1 CPO C-12 COPILOT 2
UTILITY HYD PRESS CPO B-3 COPILOT 2
WHEEL BRK ACCUM PRESS CPO D-3 COPILOT 2
COPILOT 3 PDB
ADF #1 CP F-11 COPILOT 3
ADF CONT #1 CP F-12 COPILOT 3
CDU #1 CP D-7 COPILOT 3
CKPT AUDIO #2 CP I-8 COPILOT 3
DAU #1B CP C-14 COPILOT 3
DAU #2A CP B-14 COPILOT 3
DME #1 CP F-10 COPILOT 3
FWC #2 CP B-13 COPILOT 3
G-METER CP C-13 COPILOT 3
L COWL A/I PRESS CP J-12 COPILOT 3
L COWL ANTI-ICE CP J-13 COPILOT 3
L WING ANTI-ICE CP J-14 COPILOT 3
L WSHLD WIPER CP J-11 COPILOT 3
L/H RR COOL FAN CP K-1 COPILOT 3
NAV CMPTR #1 CP D-8 COPILOT 3
NAV RCVR #1 CP F-9 COPILOT 3*
SMOKE DET CP E-14 COPILOT 3
ACCESS PDB
L CONV PDB
R CONV PDB
L MAIN BOOST PUMP PDB
R MAIN BOOST PUMP PDB
E INV PDB
EXT PWR PDB
TRU PDB
* Depending on effectivity.

REVISION 24 (RE-ISSUE) SUPPLEMENTAL PROCEDURES / DATA

Mar 17/10 Page S - 17
 Quick Reference Handbook
Left Main DC Bus Circuit Breakers
Circuit Breaker Name Panel Loc. Control
PILOT 1 PDB
AC-BPCU PWR #1 PO C-5 PILOT 1
ADC XFER PO D-15 PILOT 1
AFT PED PWR SUPPLY P E-3* PILOT 1
AFT PED PWR SUPPLY #2 P E-3* PILOT 1
DC-BPCU PWR #1 PO C-6 PILOT 1
FUEL PUMP LOGIC PO C-4 PILOT 1
L CONSOLE PWR SUPPLY P D-1 PILOT 1
L ENG IDLE P K-8 PILOT 1
L MAIN DC SENSE P H-14 PILOT 1
L MAIN DC VM P E-13 PILOT 1
PEDESTAL P A-8 PILOT 1
R CONSOLE PWR SUPPLY P E-1 PILOT 1
SIGN LTS P B-1* PILOT 1
SIGN LTS P D-5* PILOT 1
TAXI LTS CONT P C-9 PILOT 1

PILOT 2 PDB
L CONSOLE FLOOD P A-10 PILOT 2
L ENG ACU SOL P J-11 PILOT 2
L LDG LT CONT P E-6* PILOT 2
L LDG LT CONT P D-7* PILOT 2
NAV/INSP LTS CONT P D-8 PILOT 2
OVHD/PED FLOOD LTS P A-9 PILOT 2

COPILOT 1 PDB
A/T SERVO #1 CPO C-9 COPILOT 1
DATA LOADER CP I-7 COPILOT 1
DISPLAY UNIT #5 CP I-6 COPILOT 1
FLT HYD CONT CPO C-5 COPILOT 1
GND SPOILER CPO C-6 COPILOT 1
IRU #1 DC PRI CP K-5 COPILOT 1
RADIO ALTM #1 CP I-4 COPILOT 1
W RDR CONT #1 CP F-14 COPILOT 1
W RDR R/T CP F-13 COPILOT 1

COPILOT 2 PDB
PERF #1 CPO C-11 COPILOT 2
WHEELSPEED CPO C-10 COPILOT 2**
**AFT E-BAT on HMAB airplanes

COPILOT 3 PDB
#1 HF MIC ADAPTOR CP F-8 COPILOT 3
AHRS DC CP M-5 COPILOT 3
EGPWS DC CP E-10 COPILOT 3
HF CONT #1 CP D-12 COPILOT 3
HF RT CPLR #1 CP D-11 COPILOT 3
* Depending on effectivity. Continued on next page 

SUPPLEMENTAL PROCEDURES / DATA REVISION 24 (RE-ISSUE)

Page S - 18 Mar 17/10
Quick Reference Handbook
Left Main DC Bus Circuit Breakers, ctd…

Circuit Breaker Name Panel Loc. Control

COPILOT 3, ctd… PDB
IRS BATT CHGR #1 CP H-13 COPILOT 3
SYM GEN #3 CP M-3 COPILOT 3

ACCESS PDB

Right Main DC Bus Circuit Breakers

Circuit Breaker Name Panel Loc. Control
PILOT 1 PDB
AC-BPCU PWR #2 PO D-5 PILOT 1
AFT PED PWR SUPPLY #1 P E-2 PILOT 1
ALT PUMP CONT PO D-4 PILOT 1
BOT A/C LT P D-6* PILOT 1
BOT A/C LT P F-7* PILOT 1
DC-BPCU PWR #2 PO D-6 PILOT 1
ENG SYNC P K-9 PILOT 1
F E-BATT ALT PWR P J-14 PILOT 1
R ENG IDLE P L-8 PILOT 1
R FLT PNL/GSHLD P B-7 PILOT 1
WARN LTS PWR #9 P G-4* PILOT 1
WARN LTS PWR #9 P G-5* PILOT 1

PILOT 2 PDB
A E-BAT ALT PWR P K-14 PILOT 2
CABIN TEMP CONT PO D-14 PILOT 2*
CAM DC (EVS) CP AUX A-6* PILOT 2
COOL VLV (EVS) CP AUX D-6* PILOT 2
HTR (EVS) CP AUX C-6* PILOT 2
PROC (EVS) CP AUX B-5* PILOT 2
R CONSOLE FLOOD P B-10 PILOT 2
R ENG ACU SOL P K-11 PILOT 2
R LDG LT CONT P F-7 PILOT 2
R MAIN DC SENSE P I-14 PILOT 2
R MAIN DC VM P F-13 PILOT 2
STROBE LTS CONT P E-7* PILOT 2
STROBE LTS CONT P F-8* PILOT 2
TONE WARN #2 P B-5 PILOT 2

COPILOT 1 PDB
A/P SERVO #2 CPO D-8* COPILOT 1
CDU #2 CP E-7 COPILOT 1
DADC #2 CP G-3 COPILOT 1
DISPLAY UNIT #2 CP F-6 COPILOT 1
DISPLAY UNIT #6 CP J-6 COPILOT 1
FGC #2 CPO B-7 COPILOT 1
* Depending on effectivity. Continued on next page 

REVISION 24 (RE-ISSUE) SUPPLEMENTAL PROCEDURES / DATA

Mar 17/10 Page S - 19
 Quick Reference Handbook
Right Main DC Bus Circuit Breakers, ctd…

Circuit Breaker Name Panel Loc. Control

COPILOT 1, ctd… PDB
FLT GDNC PNL #2 CPO D-7 COPILOT 1
IRU #2 DC CP L-5 COPILOT 1
NAV CMPTR #2 CP E-8 COPILOT 1
NAV/DME CONT # 2 CP E-9 COPILOT 1
R PITOT HT CONT CP M-12 COPILOT 1
RADIO ALTM #2 CP J-4 COPILOT 1
SPZ-8000 SHUTDN CP L-4 COPILOT 1
STAB AUG SERVO #2 CPO B-6 COPILOT 1
STALL BARR VALVE #2 CPO B-12 COPILOT 1
STALL WARN CMPTR #2 CPO B-11 COPILOT 1
SYM GEN #2 CP L-3 COPILOT 1
TOTAL TEMP VALVE CP M-10 COPILOT 1
W RDR CONT #2 CP G-14 COPILOT 1

COPILOT 2 PDB
A/T SERVO #2 CPO D-9* COPILOT 2
BTMS* CP D-10 COPILOT 2
HUD CMPTR CP AUX C-4* COPILOT 2
HUD OVHD UNIT CP AUX D-4* COPILOT 2
NOSE COMPT COOL VLV CP L-1 COPILOT 2
PERF #2 CPO D-11 COPILOT 2
R WSHLD WIPER CP K-11 COPILOT 2
SHAKER #2 CPO B-10 COPILOT 2
STALL BARRIER #2 CPO B-9 COPILOT 2
STEER BY WIRE #2 CPO D-12 COPILOT 2

COPILOT 3 PDB
#2 HF MIC ADAPTOR CP G-8 COPILOT 3
ADF #2 CP G-11 COPILOT 3
ADF CONT #2 CP G-12 COPILOT 3
AOA PRB HTR #2 CP M-14 COPILOT 3
DISPLAY CONT #2 CP G-5 COPILOT 3
DISPLAY UNIT #4 CP H-6 COPILOT 3
DISPLAYS FAN #2 CP D-6 COPILOT 3*
DME #2 CP G-10 COPILOT 3
HF CONT #2 CP E-12 COPILOT 3
HF RT CPLR #2 CP E-11 COPILOT 3
IRS BATT CHGR #2 CP I-13 COPILOT 3
NAV RCVR #2 CP G-9 COPILOT 3*
NOSE COMPT COOL FAN CP M-1 COPILOT 3
PED COOL FAN CP J-1 COPILOT 3
R STBY ENG INST CP B-11 COPILOT 3
TDR/CAD #2 CP I-11* COPILOT 3
TDR/CAD CONT #2 CP I-12 COPILOT 3
VHF COMM #2 CP I-9 COPILOT 3
VHF COMM CONT #2 CP I-10 COPILOT 3
XPNDR #2 CP I-11* COPILOT 3
* Depending on effectivity. Continued on next page 

SUPPLEMENTAL PROCEDURES / DATA REVISION 24 (RE-ISSUE)

Page S - 20 Mar 17/10
Quick Reference Handbook
Right Main DC Bus Circuit Breakers, ctd…

Circuit Breaker Name Panel Loc. Control

ACCESS PDB
L ALTN BOOST PUMP PDB
R ALTN BOOST PUMP PDB

Essential AC Bus Circuit Breakers

Circuit Breaker Name Panel Loc. Control
PILOT Φ A PDB
BLEED AIR ISO S/O V PO D-12 PILOT Φ A
CABIN PRESS 115V PO D-11 PILOT Φ A
ESS AC PH A VM P A-13 PILOT Φ A
L TEMP CONT AC P H-11 PILOT Φ A
R TEMP CONT AC P I-11 PILOT Φ A

PILOT Φ B PDB
ESS AC PH B VM P B-13 PILOT Φ B

PILOT Φ C PDB
ESS AC PH C VM P C-13 PILOT Φ C

COPILOT Φ A PDB
#1 26VAC XFMR CP A-10 COPILOT Φ A
#2 26 VAC XFMR CP B-10 COPILOT Φ A
CKPT VOICE RECORDER CP D-13 COPILOT Φ A*
DISPLAYS FAN #1 CP D-5 COPILOT Φ A*
ELEC TRIM EXC #1 CPO C-1 COPILOT Φ A
ELEC TRIM EXC #2 CPO D-1 COPILOT Φ A
FDR/FDAU CP C-7 COPILOT Φ A
L ENG OIL PRESS CP A-12 COPILOT Φ A
L EPR 115V CP A-9 COPILOT Φ A
L PITOT HT PWR CP L-11 COPILOT Φ A
PLA EXC #1 CPO C-2 COPILOT Φ A
PLA EXC #2 CPO D-2 COPILOT Φ A
POSN SNSRS CP C-10 COPILOT Φ A
R EPR 115V CP B-9 COPILOT Φ A
STBY PITOT HT PWR CP M-13 COPILOT Φ A
R ENG OIL PRESS CP B-12 COPILOT Φ A

COPILOT Φ B PDB
ILS # 1 CP I-3 COPILOT Φ B

COPILOT Φ C PDB
CKPT VOICE RECORDER CP D-13 COPILOT Φ C

ACCESS PDB
* Depending on effectivity.

REVISION 24 (RE-ISSUE) SUPPLEMENTAL PROCEDURES / DATA

Mar 17/10 Page S - 21
 Quick Reference Handbook
Left Main AC Bus Circuit Breakers
Circuit Breaker Name Panel Loc. Control
PILOT Φ A PDB
L LDG LT PWR P C-7 PILOT Φ A
L MAIN AC PH A VM P A-11 PILOT Φ A
NAV LTS P C-8* PILOT Φ A
NAV LTS P E-8* PILOT Φ A
NAV/INSP LTS XFMR P C-6* PILOT Φ A
NAV/INSP LTS XFMR P C-8* PILOT Φ A
WING INSP LTS P C-9* PILOT Φ A
WING INSP LTS P E-9* PILOT Φ A

PILOT Φ B PDB
L MAIN AC PH B VM P C-11 PILOT Φ B

PILOT Φ C PDB
L MAIN AC PH C VM P E-11 PILOT Φ C

COPILOT Φ A PDB
#1 HF COMM CP C-10* COPILOT Φ A
ENG VIB MONITOR CP B-8 COPILOT Φ A
L SIDE PWR* CP J-10* COPILOT Φ A*
L SIDE WSHLD* CP J-10* COPILOT Φ A*
R FRONT PWR* CP L-8* COPILOT Φ A*
R FRONT WSHLD* CP L-8* COPILOT Φ A*

COPILOT Φ B PDB
#1 HF COMM CP C-11* COPILOT Φ B*
AHRS AC CP M-6 COPILOT Φ B
R FRONT PWR* CP L-8* COPILOT Φ B*

COPILOT Φ C PDB
#1 HF COMM CP C-12* COPILOT Φ C*
EGPWS AC* CP D-10 COPILOT Φ C
IRU #1 AC CP K-6 COPILOT Φ C
TCAS CP D-11 COPILOT Φ C

ACCESS Φ A PDB
ACCESS Φ B PDB
ACCESS Φ C PDB
L BATT CHGR PDB
* Depending on effectivity.

SUPPLEMENTAL PROCEDURES / DATA REVISION 24 (RE-ISSUE)

Page S - 22 Mar 17/10
Quick Reference Handbook
Right Main AC Bus Circuit Breakers
Circuit Breaker Name Panel Loc. Control
PILOT Φ A PDB
R MAIN AC PH A VM P B-11 PILOT Φ A
STROBE LTS P F-9* PILOT Φ A
STROBE LTS P E-8* PILOT Φ A

PILOT Φ B PDB
CTR TAXI LT PWR P D-10 PILOT Φ B
L TAXI LT PWR P C-10 PILOT Φ B*
R LDG LT PWR P D-7* PILOT Φ B
R LDG LT PWR P E-7* PILOT Φ B
R MAIN AC PH B VM P D-11 PILOT Φ B
R TAXI LT PWR P E-10 PILOT Φ B
TAXI LTS XFMR P D-6* PILOT Φ B
TAXI LTS XFMR P F-10* PILOT Φ B

PILOT Φ C PDB
BCN LTS P C-6* PILOT Φ C
R MAIN AC PH C VM P F-11 PILOT Φ C
TOP A/C LT P C-6* PILOT Φ C
TOP A/C LT P F-8* PILOT Φ C

COPILOT Φ A PDB
#2 HF COMM CP E-10* COPILOT Φ A*
CAM AC (EVS) CP AUX A-7* COPILOT Φ A
R PITOT HT PWR CP M-11 COPILOT Φ A

COPILOT Φ B PDB
#2 HF COMM CP E-11* COPILOT Φ B*
DISPLAYS FAN #2 CP D-6 COPILOT Φ B*
ILS # 2 CP J-3 COPILOT Φ B
L FRONT PWR* CP J-8* COPILOT Φ B
L FRONT WSHLD* CP J-8* COPILOT Φ B*
NOSE COMPT COOL FAN CP M-1 COPILOT Φ B*
TOTAL TEMP PROBE HTR CP L-10 COPILOT Φ B

COPILOT Φ C PDB
#2 HF COMM CP E-12* COPILOT Φ C*
IRU #2 AC CP L-6 COPILOT Φ C
L FRONT PWR* CP J-8* COPILOT Φ C
L FRONT WSHLD* CP J-8* COPILOT Φ C*
LOGO LTS P C-5 COPILOT Φ C
R SIDE PWR* CP K-10 COPILOT Φ C
R SIDE WSHLD* CP K-10 COPILOT Φ C
RR ENG TEST CP G-13 COPILOT Φ C
* Depending on effectivity. Continued on next page 

REVISION 24 (RE-ISSUE) SUPPLEMENTAL PROCEDURES / DATA

Mar 17/10 Page S - 23
 Quick Reference Handbook
Right Main AC Bus Circuit Breakers, ctd…

Circuit Breaker Name Panel Loc. Control

ACCESS Φ A PDB
ACCESS Φ B PDB
ACCESS Φ C PDB
R BATT CHGR PDB
TRU PDB

Battery Bus 1 Circuit Breakers

Circuit Breaker Name Panel Loc. Bus
APU CONT P G-10* BATT BUS 1*
APU PWR #1 P J-10 BATT BUS 1

BATT #1 CONT AUX PWR RLY BOX BATT BUS 1

BATT #1 ON PO C-7 BATT BUS 1
BATT #1 VM PO C-8 BATT BUS 1

DISPLAY MASTER #1 CP I-2 BATT BUS 1

EPMP #1 AFT AUX PWR RLY BOX BATT BUS 1

EPMP #1 DC PO C-9 BATT BUS 1

FDR CONT #2 CP C-9 BATT BUS 1

NUTCRACKER BAT PWR** CPO D-13 BATT BUS 1

* Depending on effectivity. ** ASC 242

Battery Bus 2 Circuit Breakers

Circuit Breaker Name Panel Loc. Bus
APU CONT P L-9* BATT BUS 2*
APU PWR #2 P K-10 BATT BUS 2

BATT #2 CONT AUX PWR RLY BOX BATT BUS 2

BATT #2 ON PO D-7 BATT BUS 2
BATT #2 VM PO D-8 BATT BUS 2
BATT AIR CIRCULATOR AUX PWR RLY BOX N/A
BATT PWR DC BPCU PO B-8 BATT BUS

EPMP #2 AFT AUX PWR RLY BOX BATT BUS 2

EPMP #2 DC PO D-9 BATT BUS 2
* Depending on effectivity.

SUPPLEMENTAL PROCEDURES / DATA REVISION 24 (RE-ISSUE)

Page S - 24 Mar 17/10
Quick Reference Handbook
Forward Emergency Battery Bus Circuit Breakers
Circuit Breaker Name Panel Loc. Bus
AIU #1 CP F-8 FWD E-BAT

BCS CHL #1 CPO A-2 FWD E-BAT

CKPT AUDIO #1 CP H-8 FWD E-BAT

CLOCK #1 CP H-14 FWD E-BAT

E DBDI #1 CP H-5 FWD E-BAT

E DDRMI #1 CP H-5 FWD E-BAT
INBD ANTI-SKID CPO A-2 FWD E-BAT
NAV RCVR #1 CP F-9 FWD E-BAT*
RTU #1 CP F-7 FWD E-BAT
STBY ALTM VIB CP H-3* FWD E-BAT
STBY ALTM VIB CP H-4* FWD E-BAT
STBY PWR DISPLAY P I-12 FWD E-BAT
TDR/CAD #1 CP H-11 FWD E-BAT
TDR/CAD CONT #1 CP H-12 FWD E-BAT
VHF COMM #1 CP H-9 FWD E-BAT
VHF COMM CONT #1 CP H-10 FWD E-BAT
XPNDR #1 CP H-11 FWD E-BAT
* Depending on effectivity.

Aft Emergency Battery Bus Circuit Breakers

Circuit Breaker Name Panel Loc. Bus
CLOCK #2 CP I-14 AFT E-BAT
E DBDI #2 CP I-5 AFT E-BAT
E DDRMI #2 CP I-5 AFT E-BAT
FLAP/STAB POS CP E-5 AFT E-BAT
L FUEL QTY PO C-1 AFT E-BAT
L STBY ENG INST CP A-11 AFT E-BAT
LDG GEAR POS IND P B-5* AFT E-BAT
LDG GEAR POS IND P E-5* AFT E-BAT
NAV RCVR #2 CP G-9 AFT E-BAT*
* Depending on effectivity. Continued on next page 

REVISION 24 (RE-ISSUE) SUPPLEMENTAL PROCEDURES / DATA

Mar 17/10 Page S - 25
 Quick Reference Handbook
Aft Emergency Battery Bus Circuit Breakers, ctd…
Circuit Breaker Name Panel Loc. Bus
OTBD ANTI-SKID CPO B-2 AFT E-BAT
R FUEL QTY PO D-1 AFT E-BAT
STBY ENG INSTR P B-8 AFT E-BAT
STBY HORZN CP E-4 AFT E-BAT
STBY INSTR P B-8 AFT E-BAT
WHEELSPEED CPO C-10 AFT E-BAT**
** L MAIN DC bus on Brake-By-Wire airplanes.

Miscellaneous Circuit Breakers

Circuit Breaker Name Panel Loc. Bus
STBY DC VM P K-12 S E PWR DC
STBY AC VM P J-12 ST GEN RLY

Power Distribution Box Circuit Breakers

Essential DC Bus L Main DC Bus R Main DC Bus
PILOT 1 PILOT 1 PILOT 1
PILOT 2 PILOT 2 PILOT 2
PILOT 3 COPILOT 1 COPILOT 1
COPILOT 1 COPILOT 2 COPILOT 2
COPILOT 2 COPILOT 3 COPILOT 3
COPILOT 3 ACCESS ACCESS
ACCESS L ALTN BOOST PUMP
L CONV R ALTN BOOST PUMP
R CONV
TRU
E INV
EXT PWR
L MAIN BOOST PUMP
R MAIN BOOST PUMP
Essential AC Bus L Main AC Bus R Main AC Bus
PILOT Φ A PILOT Φ A PILOT Φ A
PILOT Φ B PILOT Φ B PILOT Φ B
PILOT Φ C PILOT Φ C PILOT Φ C
COPILOT Φ A COPILOT Φ A COPILOT Φ A
COPILOT Φ B COPILOT Φ B COPILOT Φ B
COPILOT Φ C COPILOT Φ C COPILOT Φ C
ACCESS ACCESS Φ A ACCESS Φ A
BATT CHGR ACCESS Φ B ACCESS Φ B
ACCESS Φ C ACCESS Φ C
L BATT CHGR R BATT CHGR
TRU

SUPPLEMENTAL PROCEDURES / DATA REVISION 24 (RE-ISSUE)

Page S - 26 Mar 17/10
Quick Reference Handbook
Warning Lights Power Circuit Breakers
Circuit Breaker Panel Loc. Bus

WARN LTS PWR #1 P F-1 ESS DC

Stall Barrier
Cabin Pressure Control

WARN LTS PWR #2 P F-2 ESS DC

Bleed Air Control
Ground Spoilers

WARN LTS PWR #3 P F-3 ESS DC

Electronic Display System
AC Power
DC Power
Engine Start
Engine Fire Detection
Audible Tone Generator
Cowl Anti Ice
Wing Anti-Ice (SN 1129 & subs)
Landing Gear Indication (SN 1096 & subs)

WARN LTS PWR #4 P F-4 ESS DC

Left Thrust Reverser
Door Warning and Control
AFGCS
Bleed Air Manual Pressure Indication
Hydraulic Control

WARN LTS PWR #5 P F-5 ESS DC

Fuel Low Level
Fuel Quantity
Engine Starting
Speed Brake / Flap Alarm
Wing Anti-Ice (SN 1000 - 1128)

WARN LTS PWR #6 P G-1 or G-2* ESS DC

Fuel Low Level
Engine Starting
Door Warning and Control
Wing Anti-Ice (SN 1000 - 1128)
Landing Gear Indication (SN 1000 - 1095)
* Depending on effectivity. Continued on next page 

REVISION 24 (RE-ISSUE) SUPPLEMENTAL PROCEDURES / DATA

Mar 17/10 Page S - 27
 Quick Reference Handbook
Warning Lights Power Circuit Breakers, ctd…

Circuit Breaker Panel Loc. Bus

WARN LTS PWR #7 P G-2 or G-3* ESS DC

Audible Tone Generator
Electronic Display System
VHF Navigation
Stall Barrier
Engine Starting
Engine Fire Protection
Engine Idle Handling
Cowl Anti-Ice
Wing Anti-Ice (SN 1129 & subs)

WARN LTS PWR #8 P G-3 or G-4* ESS DC

Transponder
Bleed Air Manual Pressure Indication
Engine Idle Handling
Right Thrust Reverser
AFGCS
Ground Spoilers
Airflow Control
Equipment Overheat
EICAS

WARN LTS PWR #9 P G-4 or G-5* R MAIN DC

Ground Spoilers

WARN LTS PWR #10 P G-5 or H-3* ESS DC

WARN LTS PWR #11 P H-3 or H-4* ESS DC
WARN LTS PWR #12 P H-4 or H-5* ESS DC
WARN LTS PWR #13 P H-5 or I-4* ESS DC
Equipment Overheat

WARN LTS PWR #14 P I-4 or I-5* ESS DC

WARN LTS PWR #15 P I-5 or J-5* ESS DC
Hydraulic Control
Cowl Anti-Ice
Equipment Overheat
Engine Overheat
Oil Pressure Warning & Indication
Fuel Pressure Warning
Fuel Filter / Oil Filter Warning
* Depending on effectivity.

SUPPLEMENTAL PROCEDURES / DATA REVISION 24 (RE-ISSUE)

Page S - 28 Mar 17/10
Quick Reference Handbook
Annunciator Lights Power Circuit Breakers
Circuit Breaker Panel Loc. Bus

L CKPT ANN LTS PWR P A-2 or B-2* ESS DC

Engine Idle Handling
Thrust Reversers
Ground Spoilers
Cooling Fan
FMS
DADC
EICAS
AFGCS

PED ANN LTS PWR P D-2* ESS DC

Stall Barrier
Landing Gear Nutcracker
Speed Brake / Flap Alarm
Engine Idle Handling
Thrust Reversers
Ground Spoilers
Brake-By-Wire

R CKPT ANN LTS PWR P B-2 or C-2* ESS DC

FMS
Thrust Reversers
EICAS
Cooling Fans
Fuel Quantity

OVHD ANN LTS PWR #1 P A-1 or C-1* ESS DC

Utility Lights
Fire Extinguishing
Power Source
Bleed Air
DC Power
APU Fire Detection
Engine Fire Detection
Windshield Wipers
Air Flow
Fuel Control
Windshield Heat
Engine Starting
* Depending on effectivity. Continued on next page 

REVISION 24 (RE-ISSUE) SUPPLEMENTAL PROCEDURES / DATA

Mar 17/10 Page S - 29
 Quick Reference Handbook
Annunciator Lights Power Circuit Breakers, ctd…

Circuit Breaker Panel Loc. Bus

OVHD ANN LTS PWR #2 P A-2 or C-2* ESS DC

APU Fire Detection
APU Control
Hydraulic Control
Fuel Control
Engine Starting
Cabin Pressure Control
Stall Barrier
Engine Fire Detection
Exterior Lights
Fuel Shutoff and Crossflow Control
Cowl Anti-Ice

OVHD ANN LTS PWR #3 P A-3 or C-3* ESS DC

APU Control
Auxiliary Hydraulic Pump
Wing Anti-Ice
Pitot Heat
TGT and Overtemperature Control
Engine Fire Detection
Engine Starting
Power Source

OVHD ANN LTS PWR #4 P A-4 or C-4* ESS DC

Pitot Heat
Air Flow
Engine Synchronization
Electronic Display
Exterior Lights
Windshield Heat
Landing and Taxi Lights

OVHD ANN LTS PWR #5 P A-5 or C-5* ESS DC

Landing and Taxi Lights
Sign Lights
Windshield Wipers
Engine Vibration Monitor
Exterior Lights
Windshield Heat
Pitot Heat
* Depending on effectivity.

SUPPLEMENTAL PROCEDURES / DATA REVISION 24 (RE-ISSUE)

Page S - 30 Mar 17/10
Quick Reference Handbook
Alphabetical List of Circuit Breakers
Circuit Breaker Name Panel Loc. Bus
#1 26VAC XFMR CP A-10 ESS AC
#1 HF COMM CP C-10* L MAIN AC
#1 HF COMM CP C-11* L MAIN AC
#1 HF COMM CP C-12* L MAIN AC
#1 HF MIC ADAPTOR CP F-8 L MAIN DC
#1 STANDBY WARN PWR P A-1 ESS DC
#2 26 VAC XFMR CP B-10 ESS AC
#2 HF COMM CP E-10* R MAIN AC
#2 HF COMM CP E-11* R MAIN AC
#2 HF COMM CP E-12* R MAIN AC
#2 HF MIC ADAPTOR CP G-8 R MAIN DC
#2 STANDBY WARN PWR P B-1 ESS DC
A E-BAT ALT PWR P K-14 ESS DC
A/P SERVO #1 CPO C-8 ESS DC
A/P SERVO #2 CPO D-8 R MAIN DC
A/T SERVO #1 CPO C-9 L MAIN DC
A/T SERVO #2 CPO D-9 R MAIN DC
AC EXT PWR PO A-8 ESS DC
AC-BPCU PWR #1 PO C-5 L MAIN DC
AC-BPCU PWR #2 PO D-5 R MAIN DC
ACCESS PDB AC ESS ESS AC
ACCESS PDB DC ESS ESS DC
ADC XFER PO D-15 L MAIN DC
ADF #1 CP F-11 ESS DC
ADF #2 CP G-11 R MAIN DC
ADF CONT #1 CP F-12 ESS DC
ADF CONT #2 CP G-12 R MAIN DC
AFT EMER BATT P I-13 ESS DC
AFT IMPACT P K-13 ESS DC
AFT PED PWR SUPPLY P E-3* L MAIN DC
AFT PED PWR SUPPLY #1 P E-2 R MAIN DC
AFT PED PWR SUPPLY #2 P E-3* L MAIN DC
AHRS AC CP M-6 L MAIN AC
AHRS DC CP M-5 L MAIN DC
AIR INLET DOOR PO C-11 ESS DC
AIU #1 CP F-8 FWD E-BAT
AIU #2 CP G-8 ESS DC
ALT PUMP CONT PO D-4 R MAIN DC
ANN LTS CONT MAIN P A-3* ESS DC
ANN LTS CONT MAIN P B-3* ESS DC
ANN LTS CONT STBY P B-3* ESS DC
ANN LTS CONT STBY P C-3* ESS DC
AOA PRB HTR #1 CP L-14 ESS DC
AOA PRB HTR #2 CP M-14 R MAIN DC
* Depending on effectivity. Continued on next page 

REVISION 24 (RE-ISSUE) SUPPLEMENTAL PROCEDURES / DATA

Mar 17/10 Page S - 31
 Quick Reference Handbook
Alphabetical List of Circuit Breakers. ctd…
Circuit Breaker Name Panel Loc. Bus
APPLIED BRAKE PRESS CPO D-6 ESS DC
APU CONT P G-10* BATT BUS 1
APU CONT P L-9* BATT BUS 2
APU FIRE EXT P I-10 ESS DC
APU FIRE WARN P A-4* ESS DC
APU FIRE WARN P B-4* ESS DC
APU PWR #1 P J-10 BATT BUS 1
APU PWR #2 P K-10 BATT BUS 2
APU PWR #3 P L-10 ESS DC
APU START P H-10 ESS DC
AUX HYD PRESS CPO D-4 ESS DC
AUX HYD PUMP CPO D-5 ESS DC
BACKUP CONT PWR PO B-7 ESS DC
BATT #1 CONT AUX PWR RLY BOX BATT BUS 1
BATT #1 ON PO C-7 BATT BUS 1
BATT #1 VM PO C-8 BATT BUS 1
BATT #2 CONT AUX PWR RLY BOX BATT BUS 2
BATT #2 ON PO D-7 BATT BUS 2
BATT #2 VM PO D-8 BATT BUS 2
BATT AIR CIRCULATOR AUX PWR RLY BOX N/A
BATT AMMETER PO A-7 ESS DC
BATT CHGR CONT PO A-6 ESS DC
BATT CHGR FAIL ANNUN PO B-6 ESS DC
BATT PWR DC BPCU PO B-8 BATT BUS
BCN LTS P C-6* R MAIN AC
BCS CHL #1 CPO A-2 FWD E-BAT
BCS CHL #2 CPO B-2 ESS DC
BLEED AIR ISO S/O V PO D-12 ESS AC
BOT A/C LT P D-6* R MAIN DC
BOT A/C LT P F-7* R MAIN DC
BOT A/C LT GND OPER P E-6* ESS DC
BOT A/C LT GND OPER P F-9* ESS DC
BTMS* CP D-10 R MAIN DC
BUS CONT #1 CP K-2 ESS DC
BUS CONT #2 CP L-2 ESS DC
BUS CONT #3 CP M-2 ESS DC
CABIN PRESS 115V PO D-11 ESS AC
CABIN PRESS 28V PO B-11 ESS DC
CABIN PRESS IND PO A-12 ESS DC
CABIN TEMP CONT PO D-14 R MAIN DC*
CAM AC (EVS) CP AUX A-7* R MAIN AC
CAM DC (EVS) CP AUX A-6* R MAIN DC
CDU #1 CP D-7 ESS DC
CDU #2 CP E-7 R MAIN DC
* Depending on effectivity. Continued on next page 
SUPPLEMENTAL PROCEDURES / DATA REVISION 24 (RE-ISSUE)
Page S - 32 Mar 17/10
Quick Reference Handbook
Alphabetical List of Circuit Breakers, ctd…
Circuit Breaker Name Panel Loc. Bus
CKPT AUDIO #1 CP H-8 FWD E-BAT
CKPT AUDIO #2 CP I-8 ESS DC
CKPT TEMP CONT PO B-13 ESS DC
CKPT VOICE RECORDER CP D-13 ESS AC*
CKPT/CABIN TEMP IND PO A-11 ESS DC
CLOCK #1 CP H-14 FWD E-BAT
CLOCK #2 CP I-14 AFT E-BAT
COMB HYD PRESS CPO A-3 ESS DC
COMB HYD QTY CPO A-4 ESS DC
COOL VLV (EVS) CP AUX D-6* R MAIN DC
COPILOT Φ A PDB AC ESS ESS AC
COPILOT Φ B PDB AC ESS ESS AC
COPILOT Φ C PDB AC ESS ESS AC
COPILOT 1 PDB DC ESS ESS DC
COPILOT 2 PDB DC ESS ESS DC
COPILOT 3 PDB DC ESS ESS DC
CTR TAXI LT PWR P D-10 R MAIN AC
CVR SHUTDOWN CP E-13 ESS DC
DADC #1 CP F-3 ESS DC
DADC #2 CP G-3 R MAIN DC
DATA LOADER CP I-7 L MAIN DC
DAU #1A CP A-14 ESS DC
DAU #1B CP C-14 ESS DC
DAU #2A CP B-14 ESS DC
DAU #2B CP D-14 ESS DC
DBDI #1 CP F-4 ESS DC
DBDI #2 CP G-4 ESS DC
DC-BPCU PWR #1 PO C-6 L MAIN DC
DC-BPCU PWR #2 PO D-6 R MAIN DC
DDRMI #1 CP F-4 ESS DC
DDRMI #2 CP G-4 ESS DC
DISPLAY CONT #1 CP F-5 ESS DC
DISPLAY CONT #2 CP G-5 R MAIN DC
DISPLAYS FAN #1 CP D-5 ESS DC*
DISPLAYS FAN #2 CP D-6 R MAIN DC*
DISPLAY MASTER #1 CP I-2 BATT BUS 1
DISPLAY MASTER #2 CP J-2 ESS DC
DISPLAY UNIT #1 CP E-6 ESS DC
DISPLAY UNIT #2 CP F-6 R MAIN DC
DISPLAY UNIT #3 CP G-6 ESS DC
DISPLAY UNIT #4 CP H-6 R MAIN DC
DISPLAY UNIT #5 CP I-6 L MAIN DC
DISPLAY UNIT #6 CP J-6 R MAIN DC
DME #1 CP F-10 ESS DC
DME #2 CP G-10 R MAIN DC
* Depending on effectivity. Continued on next page 
REVISION 24 (RE-ISSUE) SUPPLEMENTAL PROCEDURES / DATA
Mar 17/10 Page S - 33
 Quick Reference Handbook
Alphabetical List of Circuit Breakers, ctd..
Circuit Breaker Name Panel Loc. Bus
DOME LT P B-6 ESS DC
DOOR CONT/WARN CPO B-8 ESS DC
E DBDI #1 CP H-5 ESS DC
E DBDI #2 CP I-5 AFT E-BAT
E DDRMI #1 CP H-5 FWD E-BAT
E DDRMI #2 CP I-5 AFT E-BAT
EGPWS AC* CP D-10 L MAIN AC
EGPWS DC CP E-10 L MAIN DC
E INV PDB DC ESS ESS DC
ELEC TRIM EXC #1 CPO C-1 ESS AC
ELEC TRIM EXC #2 CPO D-1 ESS AC
ELEV TRIM TAB ACTR HEAT CP L-9 L MAIN AC
ELWS #1 PO A-9 ESS DC
ELWS #2 PO B-9 ESS DC
ENG SYNC P K-9 R MAIN DC
ENG VIB MONITOR CP B-8 L MAIN AC
ENGINE OILER P G-10* ESS DC
ENGINE OILER P L-9* ESS DC
ENGINE START P K-6 ESS DC
EPMP #1 AFT AUX PWR RLY BOX BATT BUS 1
EPMP #2 AFT AUX PWR RLY BOX BATT BUS 2
EPMP #1 DC PO C-9 BATT BUS 1
EPMP #2 DC PO D-9 BATT BUS 2
EPMP SW PWR #1 PO A-5 ESS DC
EPMP SW PWR #2 PO B-5 ESS DC
ESS AC PH A VM P A-13 ESS AC
ESS AC PH B VM P B-13 ESS AC
ESS AC PH C VM P C-13 ESS AC
ESS DC VM P D-13 ESS DC
EXT PWR PDB DC ESS ESS DC
F E-BATT ALT PWR P J-14 ESS DC
FDR CONT #1 CP C-8 ESS DC
FDR CONT #2 CP C-9 BATT BUS 1
FDR/FDAU CP C-7 ESS AC
FGC #1 CPO A-7 ESS DC
FGC #2 CPO B-7 R MAIN DC
FIRE BELL P B-4* ESS DC
FIRE BELL P B-5* ESS DC
FIRE BELL P C-4* ESS DC
FIRE EXT SHOT #1 P G-8 ESS DC
FIRE EXT SHOT #2 P H-8 ESS DC
FLAP CONT CPO B-1 ESS DC
FLAP POS CP K-4 ESS DC
FLAP/STAB POS CP E-5 AFT E-BAT
* Depending on effectivity. Continued on next page 

SUPPLEMENTAL PROCEDURES / DATA REVISION 24 (RE-ISSUE)

Page S - 34 Mar 17/10
Quick Reference Handbook
Alphabetical List of Circuit Breakers, ctd..
Circuit Breaker Name Panel Loc. Bus
FLAP/STAB WARN P D-3 ESS DC
FLOOD LTS OVERRIDE P A-6 ESS DC
FLT GDNC PNL #1 CPO C-7 ESS DC
FLT GDNC PNL #2 CPO D-7 R MAIN DC
FLT HYD CONT CPO C-5 L MAIN DC
FLT HYD PRESS CPO C-4 ESS DC
FLT HYD QTY CPO B-4 ESS DC
FUEL INTERTANK V PO B-4 ESS DC
FUEL LOW LEVEL PO B-1 ESS DC
FUEL PUMP IND PO A-4 ESS DC
FUEL PUMP LOGIC PO C-4 L MAIN DC
FUEL X FLOW V PO D-2 ESS DC
FWC #1 CP A-13 ESS DC
FWC #2 CP B-13 ESS DC
FWD EMER BATT P H-13 ESS DC
FWD IMPACT P J-13 ESS DC
G-METER CP C-13 ESS DC
GND SPOILER CPO C-6 L MAIN DC
GPS #1 CP D-9 ESS DC
GPS #2 CP E-9 R MAIN DC
HF CONT #1 CP D-12 L MAIN DC
HF CONT #2 CP E-12 R MAIN DC
HF RT CPLR #1 CP D-11 L MAIN DC
HF RT CPLR #2 CP E-11 R MAIN DC
HTR (EVS) CP AUX C-6* R MAIN DC
HUD CMPTR CP AUX C-4* R MAIN DC
HUD OVHD UNIT CP AUX D-4* R MAIN DC
ILS # 1 CP I-3 ESS AC
ILS # 2 CP J-3 ESS AC
INBD ANTI-SKID CPO A-2 FWD E-BAT
IRS BATT CHGR #1 CP H-13 L MAIN DC
IRS BATT CHGR #2 CP I-13 R MAIN DC
IRU #1 AC CP K-6 L MAIN AC
IRU #1 DC PRI CP K-5 L MAIN DC
IRU #1 DC SEC CP J-5 ESS DC
IRU #2 AC CP L-6 R MAIN AC
IRU #2 DC CP L-5 R MAIN DC
L #1 IGN P I-8 ESS DC
L #2 IGN P J-8 ESS DC
L AIR COND PO C-13 ESS DC
L ALTN BOOST PUMP PDB R DC R MAIN DC
L BATT CHGR PDB L AC L MAIN AC
* Depending on effectivity. Continued on next page 

REVISION 24 (RE-ISSUE) SUPPLEMENTAL PROCEDURES / DATA

Mar 17/10 Page S - 35
 Quick Reference Handbook
Alphabetical List of Circuit Breakers, ctd..
Circuit Breaker Name Panel Loc. Bus
L BLEED AIR PO A-10 ESS DC
L BLEED AIR IND PO B-12 ESS DC
L CKPT ANN LTS PWR P A-2* ESS DC
L CKPT ANN LTS PWR P B-2* ESS DC
L CONSOLE FLOOD P A-10 L MAIN DC
L CONSOLE PWR SUPPLY P D-1 L MAIN DC
L CONV PDB DC ESS ESS DC
L COWL A/I PRESS CP J-12 ESS DC
L COWL ANTI-ICE CP J-13 ESS DC
L ENG ACU SOL P J-11 L MAIN DC
L ENG IDLE P K-8 L MAIN DC
L ENG O'HT P G-9 ESS DC
L ENG OIL PRESS CP A-12 ESS AC
L EPR 115V CP A-9 ESS AC
L FIRE DET LOOP A P I-6 ESS DC
L FIRE DET LOOP B P G-6 ESS DC
L FLT PNL/GSHLD P A-7 ESS DC
L FRONT PWR* CP J-8 R MAIN AC
L FRONT WSHLD* CP J-8 R MAIN AC
L FUEL QTY PO C-1 AFT E-BAT
L FUEL S/O PO A-2 ESS DC
L FUELING S/O PO A-3 ESS DC
L HYD S/O CPO A-5 ESS DC
L LDG LT CONT P E-6* L MAIN DC
L LDG LT CONT P D-7* L MAIN DC
L LDG LT PWR P C-7 L MAIN AC
L MAIN AC PH A VM P A-11 L MAIN AC
L MAIN AC PH B VM P C-11 L MAIN AC
L MAIN AC PH C VM P E-11 L MAIN AC
L MAIN BOOST PUMP PDB DC ESS ESS DC
L MAIN DC SENSE P H-14 L MAIN DC
L MAIN DC VM P E-13 L MAIN DC
L NUTCRACKER CPO A-13 ESS DC
L PITOT HT CONT CP L-12 ESS DC
L PITOT HT PWR CP L-11 ESS AC
L SEC LOCK P G-7 ESS DC
L SIDE PWR* CP J-10 L MAIN AC
L SIDE WSHLD* CP J-10 L MAIN AC
L STBY ENG INST CP A-11 AFT E-BAT
L T/R EMER STOW P K-7* ESS DC
L T/R EMER STOW P L-7* ESS DC
L T/REV CONTROL P I-7 ESS DC
L TAXI LT PWR P C-10 R MAIN AC
L TEMP CONT AC P H-11 ESS AC
L WING ANTI-ICE CP J-14 ESS DC
L WSHLD WIPER CP J-11 ESS DC
* Depending on effectivity. Continued on next page 

SUPPLEMENTAL PROCEDURES / DATA REVISION 24 (RE-ISSUE)

Page S - 36 Mar 17/10
Quick Reference Handbook
Alphabetical List of Circuit Breakers, ctd..
Circuit Breaker Name Panel Loc. Bus
L/H RR COOL FAN CP K-1 ESS DC
LDG GEAR POS IND P B-5* AFT E-BAT
LDG GEAR POS IND P E-5* AFT E-BAT
LDG WARN HORN P E-4 ESS DC
LOGO LTS P C-5 R MAIN AC
MAIN PUMP CONT PO A-1 ESS DC
MANUAL FLAP CONT CPO A-1 ESS DC
NAV CMPTR #1 CP D-8 ESS DC
NAV CMPTR #2 CP E-8 R MAIN DC
NAV LTS P C-8* L MAIN AC
NAV LTS P E-8* L MAIN AC
NAV RCVR #1 CP F-9 FWD E-BAT*
NAV RCVR #2 CP G-9 AFT E-BAT*
NAV/DME CONT # 1 CP D-9 ESS DC
NAV/DME CONT # 2 CP E-9 R MAIN DC
NAV/INSP LTS CONT P D-8 L MAIN DC
NAV/INSP LTS XFMR P C-6* L MAIN AC
NAV/INSP LTS XFMR P C-8* L MAIN AC
NOSE COMPT COOL FAN CP M-1 R MAIN DC*
NOSE COMPT COOL VLV CP L-1 R MAIN DC
NUTCRACKER CPO B-13 ESS DC
NUTCRACKER BAT PWR** CPO D-13 BATT BUS 1
OTBD ANTI-SKID CPO B-2 AFT E-BAT
OVHD ANN LTS PWR #1 P A-1* ESS DC
OVHD ANN LTS PWR #1 P C-1* ESS DC
OVHD ANN LTS PWR #2 P A-2* ESS DC
OVHD ANN LTS PWR #2 P C-2* ESS DC
OVHD ANN LTS PWR #3 P A-3* ESS DC
OVHD ANN LTS PWR #3 P C-3* ESS DC
OVHD ANN LTS PWR #4 P A-4* ESS DC
OVHD ANN LTS PWR #4 P C-4* ESS DC
OVHD ANN LTS PWR #5 P A-5* ESS DC
OVHD ANN LTS PWR #5 P C-5* ESS DC
OVHD PNL PRI P B-9 ESS DC
OVHD/PED FLOOD LTS P A-9 L MAIN DC
PED ANN LTS PWR P D-2 ESS DC
PED COOL FAN CP J-1 R MAIN DC
PEDESTAL P A-8 L MAIN DC
PERF #1 CPO C-11 L MAIN DC
PERF #2 CPO D-11 R MAIN DC
PILOT Φ A PDB AC ESS ESS AC
PILOT Φ B PDB AC ESS ESS AC
* Depending on effectivity. ** ASC 242 Continued on next page 

REVISION 24 (RE-ISSUE) SUPPLEMENTAL PROCEDURES / DATA

Mar 17/10 Page S - 37
 Quick Reference Handbook
Alphabetical List of Circuit Breakers, ctd..
Circuit Breaker Name Panel Loc. Bus
PILOT Φ C PDB AC ESS ESS AC
PILOT 1 PDB DC ESS ESS DC
PILOT 2 PDB DC ESS ESS DC
PILOT 3 PDB DC ESS ESS DC
PLA EXC #1 CPO C-2 ESS AC
PLA EXC #2 CPO D-2 ESS AC
POSN SNSRS CP C-10 ESS AC
PROC (EVS) CP AUX B-6* R MAIN DC
PYLON LT P D-5 ESS AC
R #1 IGN P I-9 ESS DC
R #2 IGN P J-9 ESS DC
R AIR COND PO D-13 ESS DC
R ALTN BOOST PUMP PDB R DC R MAIN DC
R BATT CHGR PDB L AC R MAIN AC
R BLEED AIR PO B-10 ESS DC
R BLEED AIR IND PO C-12 ESS DC
R CKPT ANN LTS PWR P B-2* ESS DC
R CKPT ANN LTS PWR P C-2* ESS DC
R CONSOLE FLOOD P B-10 R MAIN DC
R CONSOLE PWR SUPPLY P E-1 L MAIN DC
R CONV PDB DC ESS ESS DC
R COWL A/I PRESS CP K-12 ESS DC
R COWL ANTI-ICE CP K-13 R MAIN DC
R ENG ACU SOL P K-11 R MAIN DC
R ENG IDLE P L-8 R MAIN DC
R ENG O'HT P H-9 R MAIN DC
R ENG OIL PRESS CP B-12 ESS AC
R EPR 115V CP B-9 ESS AC
R FIRE DET LOOP A P J-6 ESS DC
R FIRE DET LOOP B P H-6 ESS DC
R FLT PNL/GSHLD P B-7 R MAIN DC
R FUEL S/O PO B-2 ESS DC
R FUELING S/O PO B-3 ESS DC
R FUEL QTY PO D-1 AFT E-BAT
R FRONT PWR* CP L-8 L MAIN AC
R FRONT WSHLD* CP L-8 L MAIN AC
R HYD S/O CPO B-5 ESS DC
R LDG LT CONT P F-7 R MAIN DC
R LDG LT PWR P D-7* R MAIN AC
R LDG LT PWR P E-7* R MAIN AC
R MAIN AC PH A VM P B-11 R MAIN AC
R MAIN AC PH B VM P D-11 R MAIN AC
R MAIN AC PH C VM P F-11 R MAIN AC
R MAIN BOOST PUMP PDB DC ESS ESS DC
R MAIN DC SENSE P I-14 R MAIN DC
* Depending on effectivity. Continued on next page 
SUPPLEMENTAL PROCEDURES / DATA REVISION 24 (RE-ISSUE)
Page S - 38 Mar 17/10
Quick Reference Handbook
Alphabetical List of Circuit Breakers, ctd..
Circuit Breaker Name Panel Loc. Bus
R MAIN DC VM P F-13 R MAIN DC
R NUTCRACKER CPO C-13 ESS DC
R PITOT HT CONT CP M-12 R MAIN DC
R PITOT HT PWR CP M-11 R MAIN AC
R SEC LOCK P H-7 ESS DC
R SIDE PWR* CP K-10 R MAIN AC
R SIDE WSHLD* CP K-10 R MAIN AC
R STBY ENG INST CP B-11 R MAIN DC
R T/R EMER STOW P L-7 ESS DC
R TAXI LT PWR P E-10 R MAIN AC
R TEMP CONT AC P I-11 ESS AC
R WING ANTI-ICE CP K-14 ESS DC
R WSHLD WIPER CP K-11 R MAIN DC
RADIO ALTM #1 CP I-4 L MAIN DC
RADIO ALTM #2 CP J-4 R MAIN DC
RADIO RACK COOLING DC CP I-1 ESS DC
RH RR COOL FAN CP H-2 ESS DC
RH RR FAN CONT CP I-1 ESS DC
RR ENG TEST CP G-13 R MAIN AC
RTU #1 CP F-7 FWD E-BAT
RTU #2 CP G-7 ESS DC
SGL PACK PO C-14 ESS DC
SHAKER #1 CPO A-10 ESS DC
SHAKER #2 CPO B-10 R MAIN DC
SIGN LTS P B-1* L MAIN DC
SIGN LTS P D-5* L MAIN DC
SMOKE DET CP E-14 ESS DC
SPD BRAKE/FLAP ALARM P D-4 ESS DC
SPZ-8000 SHUTDN CP L-4 R MAIN DC
STAB AUG SERVO #1 CPO A-6 ESS DC
STAB AUG SERVO #2 CPO B-6 R MAIN DC
STALL BARR DUMP VALVE CPO A-8 ESS DC
STALL BARR VALVE #1 CPO A-12 ESS DC
STALL BARR VALVE #2 CPO B-12 R MAIN DC
STALL BARRIER #1 CPO A-9 ESS DC
STALL BARRIER #2 CPO B-9 R MAIN DC
STALL WARN CMPTR #1 CPO A-11 ESS DC
STALL WARN CMPTR #2 CPO B-11 R MAIN DC
STBY AC VM P J-12 ST GEN RLY
STBY ALTM VIB CP H-3* FWD E-BAT
STBY ALTM VIB CP H-4* FWD E-BAT
STBY DC VM P K-12 S E PWR DC
STBY ENG INSTR P B-8 AFT E-BAT
STBY HORZN CP E-4 AFT E-BAT
STBY INSTR P B-8 AFT E-BAT
* Depending on effectivity. Continued on next page 
REVISION 24 (RE-ISSUE) SUPPLEMENTAL PROCEDURES / DATA
Mar 17/10 Page S - 39
 Quick Reference Handbook
Alphabetical List of Circuit Breakers, ctd..
Circuit Breaker Name Panel Loc. Bus
STBY PWR DISPLAY P I-12 FWD E-BAT
STBY PITOT HT CONT CP L-13 ESS DC
STBY PITOT HT PWR CP M-13 ESS AC
STBY PWR CONT P H-12 ESS DC
STEER BY WIRE #1 CPO C-12 ESS DC
STEER BY WIRE #2 CPO D-12 R MAIN DC
STROBE LTS P E-8* R MAIN AC
STROBE LTS P F-9* R MAIN AC
STROBE LTS CONT P E-7* R MAIN DC
STROBE LTS CONT P F-8* R MAIN DC
SYM GEN #1 CP K-3 ESS DC
SYM GEN #2 CP L-3 R MAIN DC
SYM GEN #3 CP M-3 L MAIN DC
T/R EMER STOW P K-7 ESS DC
TAXI LTS CONT P C-9 L MAIN DC
TAXI LTS XFMR P D-6* R MAIN AC
TAXI LTS XFMR P F-10* R MAIN AC
TCAS CP D-11 L MAIN AC
TDR/CAD #1 CP H-11 FWD E-BAT
TDR/CAD #2 CP I-11 R MAIN DC
TDR/CAD CONT #1 CP H-12 FWD E-BAT
TDR/CAD CONT #2 CP I-12 R MAIN DC
TONE WARN #1 P A-5 ESS DC
TONE WARN #2 P B-5 R MAIN DC
TOP A/C LT P C-6* R MAIN AC
TOP A/C LT P F-8* R MAIN AC
TOTAL TEMP PROBE HTR CP L-10 R MAIN AC
TOTAL TEMP VALVE CP M-10 R MAIN DC
TRU PDB AC RT R MAIN AC
TRU PDB DC ESS ESS DC
UTILITY HYD PRESS CPO B-3 ESS DC
UTILITY HYD PUMP OFF CPO C-3 ESS DC
UTILITY LTS P D-9* ESS DC
UTILITY LTS P E-9* ESS DC
VHF COMM #1 CP H-9 FWD E-BAT
VHF COMM #2 CP I-9 R MAIN DC
VHF COMM CONT #1 CP H-10 FWD E-BAT
VHF COMM CONT #2 CP I-10 R MAIN DC
W RDR CONT #1 CP F-14 L MAIN DC
W RDR CONT #2 CP G-14 R MAIN DC
W RDR R/T CP F-13 L MAIN DC
* Depending on effectivity. Continued on next page 

SUPPLEMENTAL PROCEDURES / DATA REVISION 24 (RE-ISSUE)

Page S - 40 Mar 17/10
Quick Reference Handbook
Alphabetical List of Circuit Breakers, ctd..
Circuit Breaker Name Panel Loc. Bus
WARN LTS PWR #1 P F-1 ESS DC
WARN LTS PWR #2 P F-2 ESS DC
WARN LTS PWR #3 P F-3 ESS DC
WARN LTS PWR #4 P F-4 ESS DC
WARN LTS PWR #5 P F-5 ESS DC
WARN LTS PWR #6 P G-1* ESS DC
WARN LTS PWR #6 P G-2* ESS DC
WARN LTS PWR #7 P G-2* ESS DC
WARN LTS PWR #7 P G-3* ESS DC
WARN LTS PWR #8 P G-3* ESS DC
WARN LTS PWR #8 P G-4* ESS DC
WARN LTS PWR #9 P G-4* R MAIN DC
WARN LTS PWR #9 P G-5* R MAIN DC
WARN LTS PWR #10 P G-5* ESS DC
WARN LTS PWR #10 P H-3* ESS DC
WARN LTS PWR #11 P H-3* ESS DC
WARN LTS PWR #11 P H-4* ESS DC
WARN LTS PWR #12 P H-4* ESS DC
WARN LTS PWR #12 P H-5* ESS DC
WARN LTS PWR #13 P H-5* ESS DC
WARN LTS PWR #13 P I-4* ESS DC
WARN LTS PWR #14 P I-4* ESS DC
WARN LTS PWR #14 P I-5* ESS DC
WARN LTS PWR #15 P I-5* ESS DC
WARN LTS PWR #15 P J-5* ESS DC
WARN LTS TEST P B-4* ESS DC
WARN LTS TEST P J-5* ESS DC
WHEEL BRK ACCUM PRESS CPO D-3 ESS DC
WHEEL WELL LTS P F-6* ESS DC
WHEEL WELL LTS P F-10* ESS DC
WHEELSPEED CPO C-10 ESS DC**
WING INSP LTS P C-9* L MAIN AC
WING INSP LTS P E-9* L MAIN AC
XPNDR #1 CP H-11 FWD E-BAT
XPNDR #2 CP I-11 R MAIN DC
* Depending on effectivity. ** L MAIN DC bus on Brake-By-Wire airplanes.

REVISION 26 SUPPLEMENTAL PROCEDURES / DATA

Oct 5 2011 Page S - 41
 Quick Reference Handbook
Air Conditioning System Circuit Breakers – ATA 21
Circuit Breaker Name Panel Loc. Bus
ADC XFER PO D-15 L MAIN DC
CABIN PRESS 115V PO D-11 ESS AC
CABIN PRESS 28V PO B-11 ESS DC
CABIN PRESS IND PO A-12 ESS DC
CABIN TEMP CONT PO D-14 R MAIN DC*
CKPT TEMP CONT PO B-13 ESS DC
CKPT/CABIN TEMP IND PO A-11 ESS DC
DISPLAYS FAN #1 CP D-5 ESS DC*
DISPLAYS FAN #2 CP D-6 R MAIN DC*
L AIR COND PO C-13 ESS DC
L/H RR COOL FAN CP K-1 ESS DC
NOSE COMPT COOL FAN CP M-1 R MAIN DC*
NOSE COMPT COOL VLV CP L-1 R MAIN DC
PED COOL FAN CP J-1 R MAIN DC
R AIR COND PO D-13 ESS DC
RH RR COOL FAN CP H-2 ESS DC
RH RR FAN CONT CP I-1 ESS DC
SGL PACK PO C-14 ESS DC

Autoflight System Circuit Breakers – ATA 22

Circuit Breaker Name Panel Loc. Bus
A/P SERVO #1 CPO C-8 ESS DC
A/P SERVO #2 CPO D-8 R MAIN DC
A/T SERVO #1 CPO C-9 L MAIN DC
A/T SERVO #2 CPO D-9 R MAIN DC
ELEC TRIM EXC #1 CPO C-1 ESS AC
ELEC TRIM EXC #2 CPO D-1 ESS AC
FGC #1 CPO A-7 ESS DC
FGC #2 CPO B-7 R MAIN DC
FLT GDNC PNL #1 CPO C-7 ESS DC
FLT GDNC PNL #2 CPO D-7 R MAIN DC
PERF #1 CPO C-11 L MAIN DC
PERF #2 CPO D-11 R MAIN DC
PLA EXC #1 CPO C-2 ESS AC
PLA EXC #2 CPO D-2 ESS AC
STAB AUG SERVO #1 CPO A-6 ESS DC
STAB AUG SERVO #2 CPO B-6 R MAIN DC

SUPPLEMENTAL PROCEDURES / DATA REVISION 26

Page S - 42 Oct 5 2011
Quick Reference Handbook
Communications System Circuit Breakers – ATA 23
Circuit Breaker Name Panel Loc. Bus
#1 HF COMM CP C-10* L MAIN AC
#1 HF COMM CP C-11* L MAIN AC
#1 HF COMM CP C-12* L MAIN AC
#1 HF MIC ADAPTOR CP F-8 L MAIN DC
#2 HF COMM CP E-10* R MAIN AC
#2 HF COMM CP E-11* R MAIN AC
#2 HF COMM CP E-12* R MAIN AC
#2 HF MIC ADAPTOR CP G-8 R MAIN DC
AIU #1 CP F-8 FWD E-BAT
AIU #2 CP G-8 ESS DC
CKPT AUDIO #1 CP H-8 FWD E-BAT
CKPT AUDIO #2 CP I-8 ESS DC
CKPT VOICE RECORDER CP D-13 ESS AC*
CVR SHUTDOWN CP E-13 ESS DC
HF CONT #1 CP D-12 L MAIN DC
HF CONT #2 CP E-12 R MAIN DC
HF RT CPLR #1 CP D-11 L MAIN DC
HF RT CPLR #2 CP E-11 R MAIN DC
RTU #1 CP F-7 FWD E-BAT
RTU #2 CP G-7 ESS DC
VHF COMM #1 CP H-9 FWD E-BAT
VHF COMM #2 CP I-9 R MAIN DC
VHF COMM CONT #1 CP H-10 FWD E-BAT
VHF COMM CONT #2 CP I-10 R MAIN DC

Electrical Power System Circuit Breakers – ATA 24

Circuit Breaker Name Panel Loc. Bus
ACCESS PDB AC ESS ESS AC
ACCESS PDB DC ESS ESS DC
#1 26VAC XFMR CP A-10 ESS AC
#2 26 VAC XFMR CP B-10 ESS AC
A E-BAT ALT PWR P K-14 ESS DC
AC EXT PWR PO A-8 ESS DC
AFT EMER BATT P I-13 ESS DC
AFT IMPACT P K-13 ESS DC
BACKUP CONT PWR PO B-7 ESS DC
BATT AMMETER PO A-7 ESS DC
BATT CHGR CONT PO A-6 ESS DC
BATT CHGR FAIL ANNUN PO B-6 ESS DC
E INV PDB DC ESS ESS DC
EXT PWR PDB DC ESS ESS DC
EPMP SW PWR #1 PO A-5 ESS DC
EPMP SW PWR #2 PO B-5 ESS DC
ESS AC PH A VM P A-13 ESS AC

REVISION 26 SUPPLEMENTAL PROCEDURES / DATA

Oct 5 2011 Page S - 43
 Quick Reference Handbook
ESS AC PH B VM P B-13 ESS AC
ESS AC PH C VM P C-13 ESS AC
ESS DC VM P D-13 ESS DC
F E-BATT ALT PWR P J-14 ESS DC
FWD EMER BATT P H-13 ESS DC
FWD IMPACT P J-13 ESS DC
L CONV PDB DC ESS ESS DC
R CONV PDB DC ESS ESS DC
STBY PWR CONT P H-12 ESS DC

Left Main AC Bus:

Circuit Breaker Name Panel Loc. Bus
L BATT CHGR PDB L AC L MAIN AC
L MAIN AC PH A VM P A-11 L MAIN AC
L MAIN AC PH B VM P C-11 L MAIN AC
L MAIN AC PH C VM P E-11 L MAIN AC
NAV/INSP LTS XFMR P C-6* L MAIN AC
NAV/INSP LTS XFMR P C-8* L MAIN AC

Right Main AC Bus:

Circuit Breaker Name Panel Loc. Bus
R BATT CHGR PDB L AC R MAIN AC
R MAIN AC PH A VM P B-11 R MAIN AC
R MAIN AC PH B VM P D-11 R MAIN AC
R MAIN AC PH C VM P F-11 R MAIN AC
TAXI LTS XFMR P D-6* R MAIN AC
TAXI LTS XFMR P F-10* R MAIN AC
TRU PDB AC RT R MAIN AC

Left Main DC Bus:

Circuit Breaker Name Panel Loc. Bus
AC-BPCU PWR #1 PO C-5 L MAIN DC
DC-BPCU PWR #1 PO C-6 L MAIN DC
L MAIN DC SENSE P H-14 L MAIN DC
L MAIN DC VM P E-13 L MAIN DC

Right Main DC Bus:

Circuit Breaker Name Panel Loc. Bus
AC-BPCU PWR #2 PO D-5 R MAIN DC
DC-BPCU PWR #2 PO D-6 R MAIN DC
R MAIN DC SENSE P I-14 R MAIN DC
R MAIN DC VM P F-13 R MAIN DC

SUPPLEMENTAL PROCEDURES / DATA REVISION 26

Page S - 44 Oct 5 2011
Quick Reference Handbook

Essential AC Bus:
Circuit Breaker Name Panel Loc. Bus
COPILOT Φ A PDB AC ESS ESS AC
COPILOT Φ B PDB AC ESS ESS AC
COPILOT Φ C PDB AC ESS ESS AC
PILOT Φ A PDB AC ESS ESS AC
PILOT Φ B PDB AC ESS ESS AC
PILOT Φ C PDB AC ESS ESS AC

Essential DC Bus:
Circuit Breaker Name Panel Loc. Bus
COPILOT 1 PDB DC ESS ESS DC
COPILOT 2 PDB DC ESS ESS DC
COPILOT 3 PDB DC ESS ESS DC
PILOT 1 PDB DC ESS ESS DC
PILOT 2 PDB DC ESS ESS DC
PILOT 3 PDB DC ESS ESS DC
TRU PDB DC ESS ESS DC

Fire Protection System Circuit Breakers – ATA 26

Circuit Breaker Name Panel Loc. Bus
APU FIRE EXT P I-10 ESS DC
APU FIRE WARN P A-4* ESS DC
APU FIRE WARN P B-4* ESS DC
FIRE BELL P B-4* ESS DC
FIRE BELL P B-5* ESS DC
FIRE BELL P C-4* ESS DC
FIRE EXT SHOT #1 P G-8 ESS DC
FIRE EXT SHOT #2 P H-8 ESS DC
L ENG O'HT P G-9 ESS DC
L FIRE DET LOOP A P I-6 ESS DC
L FIRE DET LOOP B P G-6 ESS DC
R ENG O'HT P H-9 R MAIN DC
R FIRE DET LOOP A P J-6 ESS DC
R FIRE DET LOOP B P H-6 ESS DC
SMOKE DET CP E-14 ESS DC

REVISION 26 SUPPLEMENTAL PROCEDURES / DATA

Oct 5 2011 Page S - 45
 Quick Reference Handbook
Flight Controls’ System Circuit Breakers – ATA 27
Circuit Breaker Name Panel Loc. Bus
AOA PRB HTR #1 CP L-14 ESS DC
AOA PRB HTR #2 CP M-14 R MAIN DC
ELEV TRIM TAB ACTR HEAT CP L-9 L MAIN AC
FLAP CONT CPO B-1 ESS DC
FLAP/STAB POS CP E-5 AFT E-BAT
FLAP POS CP K-4 ESS DC
FLAP/STAB WARN P D-3 ESS DC
GND SPOILER CPO C-6 L MAIN DC
MANUAL FLAP CONT CPO A-1 ESS DC
SHAKER #1 CPO A-10 ESS DC
SHAKER #2 CPO B-10 R MAIN DC
SPD BRAKE/FLAP ALARM P D-4 ESS DC
STALL BARR DUMP VALVE CPO A-8 ESS DC
STALL BARR VALVE #1 CPO A-12 ESS DC
STALL BARR VALVE #2 CPO B-12 R MAIN DC
STALL BARRIER #1 CPO A-9 ESS DC
STALL BARRIER #2 CPO B-9 R MAIN DC
STALL WARN CMPTR #1 CPO A-11 ESS DC
STALL WARN CMPTR #2 CPO B-11 R MAIN DC

Fuel System Circuit Breakers – ATA 28

Circuit Breaker Name Panel Loc. Bus

ALT PUMP CONT PO D-4 R MAIN DC

FUEL INTERTANK V PO B-4 ESS DC
FUEL LOW LEVEL PO B-1 ESS DC
FUEL PUMP IND PO A-4 ESS DC
FUEL PUMP LOGIC PO C-4 L MAIN DC
FUEL X FLOW V PO D-2 ESS DC
L FUEL QTY PO C-1 AFT E-BAT
L FUEL S/O PO A-2 ESS DC
L FUELING S/O PO A-3 ESS DC
L ALTN BOOST PUMP PDB RDC R MAIN DC
L MAIN BOOST PUMP PDB DC ESS ESS DC
MAIN PUMP CONT PO A-1 ESS DC
R FUEL S/O PO B-2 ESS DC
R FUELING S/O PO B-3 ESS DC
R FUEL QTY PO D-1 AFT E-BAT
R ALTN BOOST PUMP PDB RDC R MAIN DC
R MAIN BOOST PUMP PDB DC ESS ESS DC

SUPPLEMENTAL PROCEDURES / DATA REVISION 26

Page S - 46 Oct 5 2011
Quick Reference Handbook
Hydraulic Power System Circuit Breakers – ATA 29
Circuit Breaker Name Panel Loc. Bus
APPLIED BRAKE PRESS CPO D-6 ESS DC
AUX HYD PRESS CPO D-4 ESS DC
AUX HYD PUMP CPO D-5 ESS DC
COMB HYD PRESS CPO A-3 ESS DC
COMB HYD QTY CPO A-4 ESS DC
FLT HYD CONT CPO C-5 L MAIN DC
FLT HYD PRESS CPO C-4 ESS DC
FLT HYD QTY CPO B-4 ESS DC
L HYD S/O CPO A-5 ESS DC
R HYD S/O CPO B-5 ESS DC
UTILITY HYD PRESS CPO B-3 ESS DC
UTILITY HYD PUMP OFF CPO C-3 ESS DC
WHEEL BRK ACCUM PRESS CPO D-3 ESS DC

Ice and Rain Protection System Circuit Breakers –

ATA 30
Circuit Breaker Name Panel Loc. Bus
L COWL A/I PRESS CP J-12 ESS DC
L COWL ANTI-ICE CP J-13 ESS DC
L FRONT PWR* CP J-8 R MAIN AC
L FRONT WSHLD* CP J-8 R MAIN AC
L PITOT HT CONT CP L-12 ESS DC
L PITOT HT PWR CP L-11 ESS AC
L SIDE PWR* CP J-10 L MAIN AC
L SIDE WSHLD* CP J-10 L MAIN AC
L WING ANTI-ICE CP J-14 ESS DC
L WSHLD WIPER CP J-11 ESS DC
R COWL A/I PRESS CP K-12 ESS DC
R COWL ANTI-ICE CP K-13 R MAIN DC
R FRONT PWR* CP L-8 L MAIN AC
R FRONT WSHLD* CP L-8 L MAIN AC
R PITOT HT CONT CP M-12 R MAIN DC
R PITOT HT PWR CP M-11 R MAIN AC
R SIDE PWR* CP K-10 R MAIN AC
R SIDE WSHLD* CP K-10 R MAIN AC
R WING ANTI-ICE CP K-14 ESS DC
R WSHLD WIPER CP K-11 R MAIN DC
STBY PITOT HT CONT CP L-13 ESS DC
STBY PITOT HT PWR CP M-13 ESS AC
TOTAL TEMP PROBE HTR CP L-10 R MAIN AC
TOTAL TEMP VALVE CP M-10 R MAIN DC

REVISION 26 SUPPLEMENTAL PROCEDURES / DATA

Oct 5 2011 Page S - 47
 Quick Reference Handbook
Indicating & Recording System Circuit Breakers –
ATA 31
Circuit Breaker Name Panel Loc. Bus
BUS CONT #1 CP K-2 ESS DC
BUS CONT #2 CP L-2 ESS DC
BUS CONT #3 CP M-2 ESS DC
CLOCK #1 CP H-14 FWD E-BAT
CLOCK #2 CP I-14 AFT E-BAT
DAU #1A CP A-14 ESS DC
DAU #1B CP C-14 ESS DC
DAU #2A CP B-14 ESS DC
DAU #2B CP D-14 ESS DC
DISPLAY CONT #1 CP F-5 ESS DC
DISPLAY CONT #2 CP G-5 R MAIN DC
DISPLAY MASTER #1 CP I-2 BATT BUS 1
DISPLAY MASTER #2 CP J-2 ESS DC
DISPLAY UNIT #1 CP E-6 ESS DC
DISPLAY UNIT #2 CP F-6 R MAIN DC
DISPLAY UNIT #3 CP G-6 ESS DC
DISPLAY UNIT #4 CP H-6 R MAIN DC
DISPLAY UNIT #5 CP I-6 L MAIN DC
DISPLAY UNIT #6 CP J-6 R MAIN DC
FDR CONT #1 CP C-8 ESS DC
FDR CONT #2 CP C-9 BATT BUS 1
FDR/FDAU CP C-7 ESS AC
FWC #1 CP A-13 ESS DC
FWC #2 CP B-13 ESS DC
G-METER CP C-13 ESS DC
POSN SNSRS CP C-10 ESS AC
RADIO RACK COOLING DC CP I-1 ESS DC
SPZ-8000 SHUTDN CP L-4 R MAIN DC
SYM GEN #1 CP K-3 ESS DC
SYM GEN #2 CP L-3 R MAIN DC
SYM GEN #3 CP M-3 L MAIN DC
TONE WARN #1 P A-5 ESS DC
TONE WARN #2 P B-5 R MAIN DC
WARN LTS PWR #1 P F-1 ESS DC
WARN LTS PWR #2 P F-2 ESS DC
WARN LTS PWR #3 P F-3 ESS DC
WARN LTS PWR #4 P F-4 ESS DC
WARN LTS PWR #5 P F-5 ESS DC
WARN LTS PWR #6 P G-1* ESS DC
WARN LTS PWR #6 P G-2* ESS DC
WARN LTS PWR #7 P G-2* ESS DC
WARN LTS PWR #7 P G-3* ESS DC
WARN LTS PWR #8 P G-3* ESS DC
WARN LTS PWR #8 P G-4* ESS DC
WARN LTS PWR #9 P G-4* R MAIN DC

SUPPLEMENTAL PROCEDURES / DATA REVISION 26

Page S - 48 Oct 5 2011
Quick Reference Handbook
WARN LTS PWR #9 P G-5* R MAIN DC
WARN LTS PWR #10 P G-5* ESS DC
WARN LTS PWR #10 P H-3* ESS DC
WARN LTS PWR #11 P H-3* ESS DC
WARN LTS PWR #11 P H-4* ESS DC
WARN LTS PWR #12 P H-4* ESS DC
WARN LTS PWR #12 P H-5* ESS DC
WARN LTS PWR #13 P H-5* ESS DC
WARN LTS PWR #13 P I-4* ESS DC
WARN LTS PWR #14 P I-4* ESS DC
WARN LTS PWR #14 P I-5* ESS DC
WARN LTS PWR #15 P I-5* ESS DC
WARN LTS PWR #15 P J-5* ESS DC

Landing Gear System Circuit Breakers – ATA 32

Circuit Breaker Name Panel Loc. Bus
BCS CHL #1 CPO A-2 FWD E-BAT
BCS CHL #2 CPO B-2 ESS DC
BTMS* CP D-10 R MAIN DC
INBD ANTI-SKID CPO A-2 FWD E-BAT
L NUTCRACKER CPO A-13 ESS DC
LDG GEAR POS IND P B-5* AFT E-BAT
LDG GEAR POS IND P E-5* AFT E-BAT
LDG WARN HORN P E-4 ESS DC
NUTCRACKER CPO B-13 ESS DC
OTBD ANTI-SKID CPO B-2 AFT E-BAT
R NUTCRACKER CPO C-13 ESS DC
STEER BY WIRE #1 CPO C-12 ESS DC
STEER BY WIRE #2 CPO D-12 R MAIN DC
WHEELSPEED CPO C-10 ESS DC**

REVISION 26 SUPPLEMENTAL PROCEDURES / DATA

Oct 5 2011 Page S - 49
 Quick Reference Handbook
Lights System Circuit Breakers – ATA 33
Circuit Breaker Name Panel Loc. Bus
#1 STANDBY WARN PWR P A-1 ESS DC
#2 STANDBY WARN PWR P B-1 ESS DC
AFT PED PWR SUPPLY P E-3* L MAIN DC
AFT PED PWR SUPPLY #1 P E-2 R MAIN DC
AFT PED PWR SUPPLY #2 P E-3* L MAIN DC
ANN LTS CONT MAIN P A-3* ESS DC
ANN LTS CONT MAIN P B-3* ESS DC
ANN LTS CONT STBY P B-3* ESS DC
ANN LTS CONT STBY P C-3* ESS DC
BCN LTS P C-6* R MAIN AC
BOT A/C LT P D-6* R MAIN DC
BOT A/C LT P F-7* R MAIN DC
BOT A/C LT GND OPER P E-6* ESS DC
BOT A/C LT GND OPER P F-9* ESS DC
CTR TAXI LT PWR P D-10 R MAIN AC
DOME LT P B-6 ESS DC
FLOOD LTS OVERRIDE P A-6 ESS DC
L CKPT ANN LTS PWR P A-2* ESS DC
L CKPT ANN LTS PWR P B-2* ESS DC
L CONSOLE FLOOD P A-10 L MAIN DC
L CONSOLE PWR SUPPLY P D-1 L MAIN DC
L FLT PNL/GSHLD P A-7 ESS DC
L LDG LT CONT P E-6* L MAIN DC
L LDG LT CONT P D-7* L MAIN DC
L LDG LT PWR P C-7 L MAIN AC
L TAXI LT PWR P C-10 R MAIN AC
LOGO LTS P C-5 R MAIN AC
NAV LTS P C-8* L MAIN AC
NAV LTS P E-8* L MAIN AC
NAV/INSP LTS CONT P D-8 L MAIN DC
OVHD ANN LTS PWR #1 P A-1* ESS DC
OVHD ANN LTS PWR #1 P C-1* ESS DC
OVHD ANN LTS PWR #2 P A-2* ESS DC
OVHD ANN LTS PWR #2 P C-2* ESS DC
OVHD ANN LTS PWR #3 P A-3* ESS DC
OVHD ANN LTS PWR #3 P C-3* ESS DC
OVHD ANN LTS PWR #4 P A-4* ESS DC
OVHD ANN LTS PWR #4 P C-4* ESS DC
OVHD ANN LTS PWR #5 P A-5* ESS DC
OVHD ANN LTS PWR #5 P C-5* ESS DC
OVHD PNL PRI P B-9 ESS DC
OVHD/PED FLOOD LTS P A-9 L MAIN DC
PED ANN LTS PWR P D-2 ESS DC
PEDESTAL P A-8 L MAIN DC
PYLON LT P D-5 ESS AC
R CKPT ANN LTS PWR P B-2* ESS DC

SUPPLEMENTAL PROCEDURES / DATA REVISION 26

Page S - 50 Oct 5 2011
Quick Reference Handbook
R CKPT ANN LTS PWR P C-2* ESS DC
R CONSOLE FLOOD P B-10 R MAIN DC
R CONSOLE PWR SUPPLY P E-1 L MAIN DC
R FLT PNL/GSHLD P B-7 R MAIN DC
R LDG LT CONT P F-7 R MAIN DC
R LDG LT PWR P D-7* R MAIN AC
R LDG LT PWR P E-7* R MAIN AC
R TAXI LT PWR P E-10 R MAIN AC
SIGN LTS P B-1* L MAIN DC
SIGN LTS P D-5* L MAIN DC
STBY ENG INSTR P B-8 AFT E-BAT
STROBE LTS P E-8* R MAIN AC
STROBE LTS P F-9* R MAIN AC
STROBE LTS CONT P E-7* R MAIN DC
STROBE LTS CONT P F-8* R MAIN DC
TAXI LTS CONT P C-9 L MAIN DC
TOP A/C LT P C-6* R MAIN AC
TOP A/C LT P F-8* R MAIN AC
UTILITY LTS P D-9* ESS DC
UTILITY LTS P E-9* ESS DC
WARN LTS TEST P B-4* ESS DC
WARN LTS TEST P J-5* ESS DC
WHEEL WELL LTS P F-6* ESS DC
WHEEL WELL LTS P F-10* ESS DC
WING INSP LTS P C-9* L MAIN AC
WING INSP LTS P E-9* L MAIN AC

Navigation System Circuit Breakers – ATA 34

Circuit Breaker Name Panel Loc. Bus
ADF #1 CP F-11 ESS DC
ADF #2 CP G-11 R MAIN DC
ADF CONT #1 CP F-12 ESS DC
ADF CONT #2 CP G-12 R MAIN DC
AHRS AC CP M-6 L MAIN AC
AHRS DC CP M-5 L MAIN DC
BATT AIR CIRCULATOR AUX PWR NA NA
RLY BOX
CAM AC (EVS) CP AUX A-7* R MAIN AC
CDU #1 CP D-7 ESS DC
CDU #2 CP E-7 R MAIN DC
COOL VLV (EVS) CP AUX D-6* R MAIN DC
DADC #1 CP F-3 ESS DC
DADC #2 CP G-3 R MAIN DC
DATA LOADER CP I-7 L MAIN DC
DBDI #1 CP F-4 ESS DC
DBDI #2 CP G-4 ESS DC
DDRMI #1 CP F-4 ESS DC
DDRMI #2 CP G-4 ESS DC

REVISION 26 SUPPLEMENTAL PROCEDURES / DATA

Oct 5 2011 Page S - 51
 Quick Reference Handbook
DME #1 CP F-10 ESS DC
DME #2 CP G-10 R MAIN DC
E DBDI #1 CP H-5 ESS DC
E DBDI #2 CP I-5 AFT E-BAT
E DDRMI #1 CP H-5 FWD E-BAT
E DDRMI #2 CP I-5 AFT E-BAT
EGPWS AC* CP D-10 L MAIN AC
EGPWE DC CP E-10 L MAIN DC
GPS #1 CP D-9 ESS DC
GPS #2 CP E-9 R MAIN DC
HTR (EVS) CP AUX C-6* R MAIN DC
HUD CMPTR CP AUX C-4* R MAIN DC
HUD OVHD UNIT CP AUX D-4* R MAIN DC
ILS # 1 CP I-3 ESS AC
ILS # 2 CP J-3 ESS AC
IRS BATT CHGR #1 CP H-13 L MAIN DC
IRS BATT CHGR #2 CP I-13 R MAIN DC
IRU #1 AC CP K-6 L MAIN AC
IRU #1 DC PRI CP K-5 L MAIN DC
IRU #1 DC SEC CP J-5 ESS DC
IRU #2 AC CP L-6 R MAIN AC
IRU #2 DC CP L-5 R MAIN DC
NAV CMPTR #1 CP D-8 ESS DC
NAV CMPTR #2 CP E-8 R MAIN DC
NAV RCVR #1 CP F-9 FWD E-BAT*
NAV RCVR #2 CP G-9 AFT E-BAT*
NAV/DME CONT # 1 CP D-9 ESS DC
NAV/DME CONT # 2 CP E-9 R MAIN DC
PROC (EVS) CP AUX B-6* R MAIN DC
RADIO ALTM #1 CP I-4 L MAIN DC
RADIO ALTM #2 CP J-4 R MAIN DC
TCAS CP D-11 L MAIN AC
TDR/CAD #1 CP H-11 FWD E-BAT
TDR/CAD #2 CP I-11 R MAIN DC
TDR/CAD CONT #1 CP H-12 FWD E-BAT
TDR/CAD CONT #2 CP I-12 R MAIN DC
W RDR CONT #1 CP F-14 L MAIN DC
W RDR CONT #2 CP G-14 R MAIN DC
W RDR R/T CP F-13 L MAIN DC
STBY HORIZON CP E-4 AFT - BAT
STBY ALTM VIB CP H-3* FWD E-BAT
STBY ALTM VIB CP H-4 FWD E-BAT
STBY INSTR CP B-8 AFT E-BAT
XPNDR #1 CP H-11 FWD E-BAT
XPNDR #2 CP I-11 R MAIN DC

SUPPLEMENTAL PROCEDURES / DATA REVISION 26

Page S - 52 Oct 5 2011
Quick Reference Handbook
Oxygen System Circuit Breakers – ATA 35
Circuit Breaker Name Panel Loc. Bus
CAM DC (EVS) CP AUX A-6* R MAIN DC

Pneumatic System Circuit Breakers – ATA 36

Circuit Breaker Name Panel Loc. Bus
BLEED AIR ISO S/O V PO D-12 ESS AC
L BLEED AIR PO A-10 ESS DC
L BLEED AIR IND PO B-12 ESS DC
R BLEED AIR PO B-10 ESS DC
R BLEED AIR IND PO C-12 ESS DC

Airborne Auxiliary Power System Circuit Breakers –

ATA 49
Circuit Breaker Name Panel Loc. Bus
AIR INLET DOOR PO C-11 ESS DC
APU PWR #3 P L-10 ESS DC
APU START P H-10 ESS DC
APU CONT P G-10* BATT BUS 1
APU CONT P L-9* BATT BUS 2
APU PWR #1 P J-10 BATT BUS 1
APU PWR #2 P K-10 BATT BUS 2
ELWS #1 PO A-9 ESS DC
ELWS #2 PO B-9 ESS DC

Doors System Circuit Breakers – ATA 52

Circuit Breaker Name Panel Loc. Bus
DOOR CONT/WARN CPO B-8 ESS DC

Engine Fuel and Control System Circuit Breakers –

ATA 73
Circuit Breaker Name Panel Loc. Bus
L ENG ACU SOL P J-11 L MAIN DC
L ENG IDLE P K-8 L MAIN DC
L TEMP CONT AC P H-11 ESS AC
R ENG ACU SOL P K-11 R MAIN DC
R ENG IDLE P L-8 R MAIN DC
R TEMP CONT AC P I-11 ESS AC

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 Quick Reference Handbook
Engine Controls System Circuit Breakers – ATA 76
Circuit Breaker Name Panel Loc. Bus
ENG SYNC P K-9 R MAIN DC

Engine Indicating System Circuit Breakers – ATA 77

Circuit Breaker Name Panel Loc. Bus
ENG VIB MONITOR CP B-8 L MAIN AC
L ENG OIL PRESS CP A-12 ESS AC
L EPR 115V CP A-9 ESS AC
L STBY ENG INST CP A-11 AFT E-BAT
R ENG OIL PRESS CP B-12 ESS AC
R EPR 115V CP B-9 ESS AC
RR ENG TEST CP G-13 R MAIN AC
R STBY ENG INST CP B-11 R MAIN DC

Exhaust System Circuit Breakers – ATA 78

Circuit Breaker Name Panel Loc. Bus
L SEC LOCK P G-7 ESS DC
L T/R EMER STOW P K-7* ESS DC
L T/R EMER STOW P L-7* ESS DC
L T/REV CONTROL P I-7 ESS DC
R SEC LOCK P H-7 ESS DC
R T/R EMER STOW P L-7 ESS DC
T/R EMER STOW P K-7 ESS DC

Oil System Circuit Breakers – ATA 79

Circuit Breaker Name Panel Loc. Bus
ENGINE OILER P G-10* ESS DC
ENGINE OILER P L-9* ESS DC

Starting System Circuit Breakers – ATA 80

Circuit Breaker Name Panel Loc. Bus
ENGINE START P K-6 ESS DC
L #1 IGN P I-8 ESS DC
L #2 IGN P J-8 ESS DC
R #1 IGN P I-9 ESS DC
R #2 IGN P J-9 ESS DC

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REVISION 26 SUPPLEMENTAL PROCEDURES / DATA

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 Quick Reference Handbook
Emergency Airplane Evacuation AFM 4-20-30

1. Parking Brake ........................................................................... SET

2. L/R FUEL COCKS .................................................................... OFF
3. APU MASTER .......................................................................... OFF
4. L/R FIRE Handles .................................................................. PULL
5. L/R FIRE Handles .............ROTATE FULLY TO DISCH 1 / DISCH 2
6. CABIN PRESS CONTROL............................................... MANUAL
7. OUTFLOW VALVE ...................................................... FULL OPEN
8. BATTERIES 1 and 2 ................................................................ OFF
9. Passengers / Crew ............................. EVACUATE IMMEDIATELY
NOTE: See Emergency Escape Routes (AFM 4-20-40) figure below.

END

SUPPLEMENTAL PROCEDURES / DATA REVISION 26

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