(c)  Apply the sealant to all the bolt holes.
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 54-32-02
 ALL  ú ú B01 Page 406 ú Mar 15/96
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
 (d)  Put the fairing on the strut and temporarily attach it with three bolts. 1) Attach the fairing with one 3/16 inch (4.76 mm) bolt at the
 top center of the fairing, and two 3/16 inch (4.76 mm) bolts at each of the two corners on the bottom edge.
 NOTE: This will put the fairing in a stable position
____ and make the installation of the other bolts easier.
 2) Attach the remaining 3/16 inch (4.76 mm) bolts to the fairing. 3) Attach the 1/4 inch (6.35 mm) bolts to the fairing as necessary (Fig. 401).
 CAUTION: WHEN YOU TIGHTEN THE BOLTS, USE A TORQUE CONTROL TOOL
_______ TO MAKE SURE THE BOLTS ARE TIGHTENED FULLY. IF THE BOLTS ARE NOT FULLY TIGHTENED, THEY COULD BECOME LOOSE AND FALL FROM THE AIRPLANE.
 4) Tighten the 3/16 inch (4.76 mm) bolts to 25-30 pound-inches (2.8-3.4 Newton meters). 5) Tighten the 1/4 inch (6.35 mm) bolts to 70-80 pound-inches (7.9-9.0 Newton meters).
 (e)  Do a check for aerodynamic smoothness as follows (Ref 54-10-00/501): 1) Make sure the distance between panels is not more than
 0.06|0.03 inch (1.524|0.762 mm).
 S 444-005-B00
 (3)  
Do the activation procedure for the thrust reversers (AMM 78-31-00/201).

 S 444-004-B00

 (4)  
Do the activation procedure for the leading edge slats (AMM 27-81-00/201).

 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 54-32-02
 ALL  ú ú B01 Page 407 ú Nov 15/95
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
 FORWARD FAIRING PRESSURE RELIEF DOOR - MAINTENANCE PRACTICES
____________________________________________________________
 1.  General_______
 A.  There are seven tasks in this procedure:
 (1)  
The first task is the latch release test which can be done in one of two separate procedures:

 (a)  
Torque Adapter and Pivot Support Assembly (Preferred), or

 (b)  
Dial Pull Gage (Alternative).

 (2)  
The second task removes the latch for the pressure relief door

 (3)  
The third task installs the latch for the pressure relief door

 (4)  
The fourth task removes the pressure relief door

 (5)  
The fifth task installs the pressure relief door

 (6)  
The sixth task is the door adjustment.

 (7)  
The seventh task is the adjustment of the latch free play.

 B.  This procedure gives the test of the latches for the pressure relief doors on the forward fairing for correct operation.
 C.  The removal, installation, and adjustment procedures of the pressure relief door and latch are necessary to get the correct aerodynamic smoothness and latch free play.
 TASK 54-33-01-712-001-B00
 2.  The Latch Release Test______________________
 A.  Equipment
 (1)  
B71044-28 - Torque Adaptor Assembly, Load Test (Preferred).

 (2)  
B71044-30 - Torque Adapter, Load Test (alternative)

 (3)  
Gage - Dial Pull, 100 pound (450 N) capacity (Alternative).

 B.  References
 (1)  AMM 54-31-01/401, Nacelle Strut Access Panels
 C.  Access
 (1)  
Location Zone
 500 Left Nacelle
 600 Right Nacelle

 (2)  
Access Panel 5741 Pressure Relief Door/Pressure Relief Structure - Left Nacelle

 5841  Pressure Relief Door/Pressure Relief Structure - Right Nacelle
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
　
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 NACELLES/PYLONS(37)