(2)
Make sure that the door is smooth with the outer surface of the forward fairing.
(a)
A maximum distance of |0.025 inch (|0.64 mm) at the forward edge is permitted.
(b)
If the door is not in the limits, adjust the door as follows: 1) Do this procedure: Remove the Pressure Relief Doors. 2) Remove or add the shims between the hinges and the door. 3) Make sure the door is smooth with the outer surface of the
forward fairing. 4) Apply the primer to all shims which do not have the primer applied to them (AMM 70-10-01/201).
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
54-33-01
ALL ú ú B01 Page 210 ú Jul 15/97
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
5) Do this procedure: Install the Pressure Relief Door.
S 222-035-B00
(3) Make sure the door has no free play when the latch is fully locked.
TASK 54-33-01-822-036-B00
8. Latch Free Play Adjustment__________________________
A. References
(1) AMM 54-31-01/401, Nacelle Strut Access Panels
B. Access
(1)
Location Zones
500 Left Nacelle
600 Right Nacelle
(2)
Access Panels 5741 Pressure Relief Door/Pressure Relief Structure - Left Nacelle
5841 Pressure Relief Door/Pressure Relief Structure - Right Nacelle
C. Procedure
S 012-037-B00
(1)
Open the pressure relief door (AMM 54-31-01/401).
S 822-038-B00
(2)
Add or remove the shims between the striker and the sill to prevent the free play.
S 412-039-B00
(3)
Close the pressure relief door (AMM 54-31-01/401).
S 222-040-B00
(4)
Make sure the distances between the inboard, outboard, aft edges, and the other skin edges are between 0.03-0.09 inch (0.76-2.3 mm).
S 222-041-B00
(5)
Make sure the distance between the door forward edge and the skin edge is 0.07-0.10 inch (1.8-2.5 mm).
(a) If the distance is less than the limits, remove the material from the applicable edge until the distance is in the limits.
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
54-33-01
ALL ú ú B01 Page 211 ú Jul 15/97
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
ENGINE ATTACH FITTINGS - DESCRIPTION AND OPERATION
__________________________________________________
1. General_______
A. The engines are attached to the nacelle struts at the forward and aft end. These mounts, in conjunction with the mounts on the engine, are designed to absorb engine thrust, vertical and side loads, and to allow axial and radial growth due to thermal expansion.
(1) On some engines, each thrust reverser is attached to the side of the nacelle strut at three hinge fittings. The forward and center hinge fittings have removable vibration isolators.
B. The strut is attached to the wing as follows: an upper link connects a fitting on the strut upper spar with a fitting on the wing front spar. Two strut midspar fittings connect directly with wing lower surface fittings. Braces connect a fitting on the strut lower spar with a wing lower surface fitting. In addition, midspar assembly side braces connect the strut with the wing. Structural fuse pins at the attach points will shear in the event of a severe engine seizure.
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
54-42-00
ALL ú ú B03 Page 1 ú Mar 15/89
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
UPPER LINK
MOUNT AFT ENGINE SIDE BRACE (2)
LINK FITTING MOUNT
Attach Fittings
Figure 1
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú 中国航空网 www.aero.cn 航空翻译 www.aviation.cn 本文链接地址：737-300 400 500 AMM 飞机维护手册 NACELLES/PYLONS(41)
