500
32-61-0 Page 102 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Nov 15/67
500
Nov 15/67 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 32-61-0 Page 103
500
32-61-0 Page 104 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Nov 15/67
500
Nov 15/67 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 32-61-0 Page 105
LANDING GEAR POSITION INDICATING AND WARNING SYSTEM - ADJUSTMENT/TEST
1. Landing Gear Position Indicating and Warning System Test
A. General
(1)
The landing gear position indicating and warning system should be tested after maintenance has been performed on a component to ensure that the system is functioning properly.
(2)
For tests which require positioning of thrust levers, the thrust lever position is given in approximate degrees from idle stop. This procedure assumes that a rigging check has already been successfully completed, and it is therefore unnecessary to recheck throttle positions accurately.
NOTE: For system rig position, refer to 31-26-11 A/T.
(3)
If it is desirable to use linear dimensions (arc length at control stand cover top) for positioning thrust levers, refer to Chapter 76, Engine Control Cables - MP, for conversion data.
B. Equipment and Materials
(1)
Airplane Jacks (Ref 07-11-11)
(2)
Ground Lock Assemblies (Ref 32-00-01)
(3)
Hydraulic test bench capable of delivering 20 gpm at 3000 psi (optional)
NOTE: You can also use airplane hydraulic power, but you cannot control the hydraulic pressure.
C. Prepare to Test
(1)
Jack airplane until all tires clear ground (Ref 07-11-11).
(2)
Check that external electrical power supply is connected.
(3)
If you use an external source for hydraulic power, connect the source to system A (Ref 29-11-0 MP).
(a)
Do not pressurize the system at this time.
(4)
Check that all circuit breakers on landing gear circuit breaker panel (P6) are closed.
(5)
Check that press-to-test and all indicator lights circuit breakers on circuit breaker panel (P6) are closed.
529
Oct 20/91 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 32-61-0 Page 501/502
D. Test Indicator Light and Warning Horn Responses
(1)
Advance both engine throttles to a position greater than 17 degrees.
(2)
Place landing gear control lever in DN position and check that green indicator light for each gear on pilot's center panel comes on.
(3)
With hydraulic system A depressurized (Ref 29-11-0), place landing gear control lever in UP position. Check that red warning lights on landing gear control panel come on and green indicator lights remain on.
(4)
Place master test switch in DIM position and check that green indicator lights and red warning lights dim.
(5)
Remove ground lock assemblies from all landing gear (Ref 32-00-01).
(6)
Do the steps that follow to retract the landing gear:
(a)
If you use an external hydraulic source, do this step:
1) Supply and control the hydraulic pressure to the hydraulic system A until you get slow gear operation (Ref 29-11-0).
(b)
If you use the hydraulic system on the airplane to supply the hydraulic power, do these steps:
NOTE: Since you cannot control the pressure in the system, the gear will retract and extend faster. You will have to monitor the indicator lights more carefully.
1) Move the control lever for the landing gear to the DN position.
2) Supply hydraulic power to system A (Ref 29-11-0).
3) Move the control lever to the UP position.
(7)
Look at the indicator lights for the landing gear:
(a)
Check that respective green indicator light goes off as each landing gear unlocks.
(b)
Check that respective red warning light goes off as each landing gear retracts to up and locked position.
(8)
Place LIGHTS switch on panel P2 in TEST position. Check that main and nose landing gear green and red lights come on.
(9)
Release LIGHTS switch. Check that main and nose landing gear green and red lights go off.
中國航空網 m.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：737 AMM 飛機維護手冊 起落架 LANDING GEAR(185)
