曝光臺 注意防騙 網(wǎng)曝天貓店富美金盛家居專營店坑蒙拐騙欺詐消費者

2. Gear ............................................................. EXTEND NORMALLY
3. Flaps ................................................EXTEND NORMALLY TO 39°
4. Ground Spoilers ..................................................................ARMED
After landing:
On touchdown, the brakes, steering and right thrust reverser operate
normally. The left thrust reverser will NOT deploy.
END
Flight Hydraulic System Failure AFM 3-17-40
With a loss of flight system fluid, the right engine FIRE handle pulled or
flight hydraulic pump failed, will result in loss of the yaw damper
function. Select yaw damper OFF. If the right engine is shut down but
windmilling, yaw damper function may be available. See Yaw Damper
Failure, page EE-10. Observe yaw damper limitations in GIV FM
Section 1, Limitations (also included in Yaw Damper Failure, page EE-
10).
Perform a normal approach and landing using normal procedures. After
landing use brakes, steering and left thrust reverser. The right thrust
reverser is not operational for landing.
END
Landing With Standby Electrical Power System
Operating AFM 3-17-50
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. Emergency Batteries.................................................................. ON
4. Ground Spoilers ........................................................................OFF
Continued on next page →
Quick Reference Handbook
REVISION 8 ABNORMAL / EMERGENCY PROCEDURES
Oct 11/02 Page EF - 7
Landing With Standby Electrical Power System Operating, ctd…
AFM 3-17-50
5. 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.
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 the airplane.
END
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
Ground Spoilers X X1
Rudder X X
Yaw Damper X
Left Thrust Reverser X
Right Thrust Reverser X
Utility Pump Motor X
Wing Flaps X X X
Landing Gear & Doors X X X2
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.
END
Quick Reference Handbook
ABNORMAL / EMERGENCY PROCEDURES REVISION 8
Page EF - 8 Oct 11/02
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 differences
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 13.
If fuel leakage is not visible from wing tank, it must be determined
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 PERFORMANCE
MUST BE TAKEN INTO CONSIDERATION.
　
中國航空網(wǎng) m.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：灣流4快速檢查單QRH GULFSTREAM IV QUICK REFERENCE HANDBOOK 3(45)