S 215-054
S 585-056
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
32-33-00
ALL ú ú 01 Page 501 ú Jun 18/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400
MAINTENANCE MANUAL
S 865-057
(7)
Provide system No. 1 hydraulic power (AMM 29-11-00/201).
S 095-058
(8)
Remove body gear ground locks (AMM 09-11-00/201).
D.
Test Body Gear Extension and Retraction
S 865-072
WARNING: CLEAR MAIN LANDING GEAR WHEEL WELL AREAS OF EQUIPMENT AND
_______
PERSONNEL BEFORE OPERATING GEAR.
(1)
Place landing gear control handle in UP position and note gear retraction time.
S 715-061
(2)
Place control handle in OFF position for 15 seconds, then place handle in DN position.
S 715-062
(3)
Check that both gear extend and doors close within times shown and as measured in step (2).
S 215-063
(4)
Check that control handle in DN position.
S 215-064
(5)
Check that gear is in down and locked position.
E.
Restore Airplane to Normal
S 495-065
(1)
Install body gear ground locks (AMM 09-11-00/201).
S 865-067
(2)
Remove system No. 1 hydraulic power if no longer required
(AMM 29-11-00/201).
(3)
Lower airplane and remove jacks (AMM 07-11-01/201).
(4)
Remove grounding cables from airplane.
(5)
Remove nose gear door locks (AMM 32-00-30/201).
S 585-068
S 215-069
S 495-070
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
32-33-00
ALL ú ú 01 Page 502 ú Jun 18/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
TASK 32-33-00-735-043
2. System Test - Body Gear and Door Extension and Retraction
_________________________________________________________
NOTE: It is satisfactory if the "CONFIG GEAR" message appears while you are
____
doing the test.
A. General
(1)
The purpose of this test is to provide a system test of the mechanical and electrical functions of the body landing gear normal actuation system.
(2)
This test does not serve as a system test for the landing gear control system rigging. If the landing gear control system was rerigged then do the landing gear control system test in addition to this test (AMM 32-31-00/501).
(3)
If a complete system test of all (or several) landing gears and the landing gear control system is required then do the landing gear extension and retraction system test instead of this test or the landing gear control system test (AMM 32-31-00/501).
(4)
The following hardware must be functional and operating for the body landing gear system test:
-Electronic Interface Unit (EIU)
-Engine Indication and Crew Alerting System (EICAS)
-Proximity Switch Electronic Unit (PSEU)
(5)
Monitor hydraulic fluid temperature during testing. Fluid temperature shall not exceed 100°C (212°F). If the SYS FAULT light on the overhead panel illuminates, and HYD OVHT appears on EICAS, then discontinue testing and allow fluid to cool before continuing.
B.
References
(1)
AMM 07-11-01/201, Jacking Airplane
(2)
AMM 09-11-00/201, Towing
(3)
AMM 20-41-01/201, Static Grounding
(4)
AMM 24-22-00/201, Manual Control
(5)
AMM 29-11-00/201, Main Hydraulic Supply System
(6)
AMM 32-00-30/201, Landing Gear Door Locks
(7)
AIPC 32-13-01 Fig. 1, AIPC 32-13-67 Fig. 1, AIPC 32-14-01 Fig. 2, AIPC 32-14-02 Fig. 2, AIPC 32-14-05 Fig. 1, AIPC 32-14-06 Fig. 1
C.
Access
(1)
Location Zone
137 Body Landing Gear Wheel Well, LH
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