(2)
Torque Control Tool -"HERBIE", P/N VST 15-50,
Commercially available
(Voi-Shan, Culver City CA 90230) or similar
B. Consumable Materials
(1) A00247 Sealant, BMS 5-95 Class B-1/2
C. References
(1)
27-61-00/201 Spoiler Control System
(2)
27-62-00/201 Speedbrake Control System
(3)
27-81-00/201, Leading Edge Slats
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737-300/400/500MAINTENANCE MANUAL
D. Access
(1) Location Zones
500 Left Nacelle
600 Right Nacelle
E. Procedure
S 944-007-B00
CAUTION: MAKE SURE THE WING COMPARTMENT IS FREE OF TOOLS, LOOSE
_______ MATERIALS, AND CONTAMINATION. DAMAGE TO THE WING COULD OCCUR.
(1)
Before you install the fairing panel, remove, all tools, loose material, and contamination from the wing.
S 424-008-B00
(2)
Do these steps to install the aft fairing panel (Fig. 401):
(a) Apply BMS 5-95 sealant along the bottom edge of the fairing panel before you install the panel.
NOTE: The sealant will keep water and moisture away from
____ the inner part of the wing where it can freeze and damage the fairing.
(b)
Apply BMS 5-95 sealant to the two mating sufaces, the skate angle and the lower surface of the fairing panel. 1) Obey the manufacturer's instructions for the sealant.
(c)
Install bolts into the fairing that have an equal diameter to the bolts you removed.
(d)
Put the fairing assembly on the wing and make sure it aligns with the nutplates before you tighten the bolts.
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.
(e) Use a torque control tool to attach the bolts to the fairing. 1) Tighten the bolts to the values in Table 401.
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~............................................................................... | Table 401 | ................................................................................. | BOLT SIZE | TORQUE VALUE | | (DIAMETER IN INCHES) | (POUND-INCHES) | ................................................................................. | 3/16 | 25-30 | ................................................................................. | 1/4 | 70-80 | 2.......................................….......................................1
F. Put the Airplane To Its Usual Condition
S 444-010-B00
(1) Do the activation procedure for the Spoiler and Speedbrake Control Systems (Ref 27-61-00/201 & 27-62-00/201).
(2) S 444-011-B00Do the activation procedure for the leading edge slats (Ref 27-81-00/201).
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ATTACH FITTINGS - DESCRIPTION AND OPERATION
___________________________________________
1. General_______
A. Fittings used as a means of connection between main structural parts are listed here.
(1)
Wing terminal fittings.
(a) These are heavy three-flanged forged fittings. Refer to 57-41-00 for a detailed description. 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 机翼 WINGS(25)
