CHECK THAT GROUND LOCK ASSEMBLIES ARE INSTALLED IN MAIN LANDING GEAR TO PREVENT INADVERTENT OPERATION OF GEAR. INJURY TO PERSONNEL AND/OR DAMAGE TO EQUIPMENT COULD RESULT IF GEAR RETRACTS.
CAUTION: DO NOT TURN STEERING WHEEL WITH NOSE GEAR SHOCK STRUT FULLY
_______ EXTENDED TO PREVENT POSSIBLE DAMAGE TO SHOCK STRUT CENTERING CAMS.
G. Use override trigger and place landing gear control lever in UP position to retract nose gear, then move control lever to OFF position.
H. Depressurize hydraulic system A (Ref 29-15-00, MP) and proceed trouble shooting with pressure off.
I. Following trouble shooting, restore airplane to normal.
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
32-35-00
ALL ú ú 01 Page 101 ú Jun 25/87
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
3. Trouble Shooting Charts_______________________
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
32-35-00
ALL ú ú 01 Page 102 ú Jun 25/84
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
NOSE GEAR MANUAL EXTENSION SYSTEM - ADJUSTMENT/TEST
___________________________________________________
1. General_______
A. This procedure has three tasks:
(1)
An adjustment of the manual extension system for the nose gear to get the correct cable tension.
(2)
A test of the manual extension system for the nose gear (airplane on jacks).
(3)
A test of the manual extension system for the nose gear (airplane on the ground).
TASK 32-35-00-825-001
2. Nose Gear Manual Extension System Adjustment (Fig. 501)____________________________________________
A. Standard Tools and Equipment
(1) Pin - Rigging; 0.311 +0.000/-0.002 inch diameter x 5.00 inches long, Type MS20392-4C
NOTE: The rigging pin is part of F70207-69 or F70207-78.
____
B. References
(1)
20-10-10/401, Clips - Turnbuckle Locking - Removal/Installation
C.
Access
(1)
Location Zone
101, Control Cabin - Left
102, Control Cabin - Right
203, Nose Wheel Well
D.
Adjustment
(1)
Align the rigging pin holes.
(2)
Install the rigging pin through the torque tube and the bracket.
(3)
Remove the cabin floor panel.
S 825-002
S 495-010
S 015-003
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
32-35-00
ALL ú ú 02 Page 501 ú Jul 12/00
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
Nose Gear Manual Extension System
Figure 501 (Sheet 1)
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
32-35-00
ALL ú ú 01 Page 502 ú Feb 20/84
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500
MAINTENANCE MANUAL
RIGGING PIN HOLE
TORQUE TUBE
RETURN SPRING BRACKET
NOSE GEAR WHEEL WELL AFT BULKHEAD
TORQUE TUBE FWD INBDRIGGING PIN QUADRANT
NOSE GEAR WHEEL WELL RIGHT SIDE BULKHEAD
TORQUE TUBE AND BRACKET ASSEMBLY
B
MANUAL EXTENSION ACCESS DOOR
CABLE MNGEA
CABLE MLGEA (R)
中國航空網 www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：737-300 400 500 AMM 飛機維護手冊 起落架 LANDING GEAR 2(141)
