NOTE: Access panels No. 13, when fitted with pressure relief valve, will only fit on the inboard surge tank openings.
(2)
If aluminum gasket originally removed is reused, ensure presence of just enough anti-corrosion grease to completely fill the gasket when installed.
NOTE: Insufficient grease could leave voids that can collect moisture and excessive grease could squeeze out on to lower wing surface.
(3)
Apply a thin layer (0.010-0.015 inch) of anticorrosion grease to the flat surface of the wing skin that touches the aluminum gasket (Fig. 401).
(4)
Position gasket and clamp ring and install mounting screws, starting from centerline and working toward ends of panel; removing excess grease from mounting screws.
CAUTION: EXCESS GREASE AHEAD OF MOUNTING SCREWS MAY DAMAGE PANEL BECAUSE OF THE HYDRAULIC PRESSURE GENERATED BY THE GREASE.
(5)
Tighten mounting screws to 35 to 50 pound-inches.
NOTE: Start to tighten the mounting bolts from the centerline to the outboard direction and equally in both directions. (Fig. 402)
500
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May 01/01
503 Fuel Tank Access Panel Installation
Aug 01/94 Figure 401 (Sheet 1) BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 28-11-11 Page 403
H22239 K99498
Fuel Tank Access Panel Installation 502
28-11-11 Page 404 Figure 401 (Sheet 2) BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. May 01/01
500 Fuel Tank Access Panel No. 13 May 01/00 Figure 401 (Sheet 2A) 28-11-11 Page 404A/404B BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
(6) On access panels No. 1, 4, 6, 8, and 10 (Fig. 401) equipped with measuring sticks, push measuring stick in and secure for flight.
CAUTION: MAKE SURE THE ACCESS PANEL IS INSTALLED IN THE CORRECT DIRECTION. IF THE INDEX NOTCH ON THE ACCESS PANEL DOES NOT ALIGN WITH THE INDEX NOTCH IN THE OPENING, A FUEL LEAK CAN OCCUR.
NOTE: The No. 10 panel is 2 inches narrower than the other measuring stick-equipped access panels.
(7) If access panel No. 13 (Fig. 401) with pressure relief valve was installed, check actuation pressure of the relief valve (AMM 28-13-41/601)
3. Removal/Installation of Access Panels No. 14 (Fig. 401)
A. Equipment and Materials
(1)
Aliphatic Naphtha -TT-N-95
(2)
Mild detergent and water
(3)
Air gun with 90 to 100 psig air supply
B. Prepare Fuel Tank Access Panel (No. 14) for Removal
(1) Same as 2.B. (1).
C. Remove Fuel Tank Access Panel (No. 14)
(1)
Support access panel and remove mounting screws.
(2)
Work access panel free of gasket seal, tip panel as required to allow air vent stack to pass out through opening in wing, and remove panel from airplane.
CAUTION: DO NOT PRY ACCESS PANEL LOOSE, IF STUCK, OR CRITICAL SEALING SURFACE MAY BE DAMAGED.
D. Prepare Surge Tank for Access Panel Installation
(1) Same as 2.D.
E. Prepare Fuel Tank Access Panel No. 14 for Installation
(1)
Check screen at top of air vent stack for evidence of foreign matter and clogging. Clean, if necessary, in water and detergent and air dry with compressed air gun.
(2)
Thoroughly clean access panel opening and access panel sealing surface using a clean lint-free cloth moistened with naphtha.
(3)
Check phenolic seal ring gasket for serviceability; especially check condition of molded seal ring inserts. Replace gasket if condition is poor or doubtful.
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