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END
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.
Continued on next page →
Quick Reference Handbook
REVISION 7 ABNORMAL / EMERGENCY PROCEDURES
May 30/02 Page EE - 11
Yaw Damper Failure, ctd… AFM 3-03-50
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
Quick Reference Handbook
ABNORMAL / EMERGENCY PROCEDURES REVISION 7
Page EE - 12 May 30/02
Notes
Quick Reference Handbook
REVISION 8 ABNORMAL / EMERGENCY PROCEDURES
Oct 11/02 Page EF - 1
Fuel / Hydraulics Index
Hydraulic System Diagram............................................................EF-2
Fuel System Diagram....................................................................EF-3
Dual Hydraulic System Failure ..................................................EF-4
Combined Hydraulic System Failure.............................................EF-5
Flight Hydraulic System Failure.....................................................EF-6
Landing With Standby Electrical Power System Operating ..........EF-6
Master Table Of Hydraulic Component Availability.......................EF-7
Fuel Leak In Flight.......................................................................EF-8
Fuel Boost Pump Failure.............................................................EF-11
Failure of 2 Boost Pumps On 1 Side...........................................EF-11
Permissible Fuel Imbalance For All Flight Operations ................EF-12
Related Topics In QRH
Engine Failure / Shutdown In Flight......................................... EC-6
One (1) Engine Inoperative Landing Procedure.................... EC-10
Yaw Damper Failure ...................................................................EE-10
Quick Reference Handbook
ABNORMAL / EMERGENCY PROCEDURES REVISION 8
Page EF - 2 Oct 11/02
Hydraulic System Diagram
ACCUM
ACCUM
AUX
PUMP
FLT
COMB
AUX
AUX PUMP
OFF/ARM ON
NOT
ARM ON
ELECT CONT
MECH CONT
COMBINED
FLIGHT
AUX
COMB/UTIL
COMB/UTIL/AUX
LEFT
ENG
PUMP
RIGHT
ENG
PUMP
FIRE
HANDLE
DISCH
1 2
FIRE
HANDLE
DISCH
2 1

UTILITY
PUMP MOTOR
UTILITY PUMP
OFF/ARM ON
NOT
ARM ON
GND SPLR SERVO
WING FLAPS
LANDING GEAR
BRAKES
STALL BARRIER
NOSEWHEEL STEERING
CARGO DOOR (ASC 213/354)
MAIN ENTRANCE DOOR
PARKING BRAKES
N2
ACCUM
BOOTSTRAP
BOOTSTRAP
STBY ELEC
ON
HMG
MOTOR
ELEVATORS ELEVATORS
RUDDER RUDDER / YAW DAMP
AILERONS AILERONS
FLIGHT SPOILERS/
SPEED BRAKES
FLIGHT SPOILERS/
SPEED BRAKES
GROUND SPOILERS
COMB OR UTIL OR AUX PRESS
SIGNAL REQ’D FOR FLT USE
GROUND SPOILERS
FLIGHT POWER
SHUT OFF
LEFT
REVERSER
RIGHT
REVERSER
NITROGEN
CHECK VALVE SHUTOFF VALVE
SHUTOFF VALVE (CAA CERT ONLY)
GROUND SERVICE VALVE
Quick Reference Handbook
REVISION 7 ABNORMAL / EMERGENCY PROCEDURES
May 30/02 Page EF - 3
Fuel System Diagram
LOW FUEL LEVEL SENSORS
FUEL QUANTITY PROBES
HYDRAULIC FLUID
HEAT EXCHANGERS
CHECK VALVES
FUEL EJECTORS
APU
FUEL
LEFT
ENG
FUEL
RIGHT
ENG
FUEL
PRESSURE
　
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