(4)
Back off each cone bolt nut 1/8 turn.
(5)
Tighten nuts in increments of 200 pound-inches to a torque range of 1000 to 1100 pound-inches, using the sequence specified in step (1).
CAUTION: IMPROPER TIGHTENING OF CONE BOLTS MAY CAUSE BREAKAGE. REFER TO 20-50-11 FOR PROPER USE OF TORQUE WRENCH ADAPTERS.
H. Install the link assembly.
(1)
NON-ENERGY ABSORBING CABLE SECONDARY SUPPORT LINKS; Install the link cable assembly and keeper cable retainer (AMM 71-21-11/401).
(2)
ENERGY ABSORBING SECONDARY SUPPORT LINKS WITH CRUSHABLE SPACER; Install the link crushable spacer and nut (AMM 71-20-0/601).
(a) Tighten the nut until it touches the spacer (do not torque over 65 pound-inches [AMM 71-21-11/401]).
CAUTION: IMPROPER TIGHTENING OF LINK NUT MAY CAUSE DAMAGE TO ENERGY ABSORBING HONEYCOMB MATERIAL AND/OR CRUSHABLE SPACER. REFER TO 20-50-11 FOR PROPER USE OF TORQUE WRENCH ADAPTERS.
NOTE: 1. A minimum of two threads must be above nut when bolt is tightened.
2. If unable to obtain two exposed threads on bolt when installing nut, delete as required. Delete washers as follows:
a.
Remove plain washers (if any) from under head of bolt.
b.
Remove countersunk washer from under head of bolt.
c. Remove plain washer from under nut. Remove only those washers required to expose two full bolt threads while maintaining 0.06 inch minimum clearance at top end of bolt.
500
Aug 01/94 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 71-00 Page 417
(3) ENERGY ABSORBING SECONDARY SUPPORT LINKS WITHOUT CRUSHABLE SPACER; Install the link, chamfered washer, washer assembly and nut in the retainer (AMM 71-21-11/401).
(a)
Tighten the nut until the link cannot be turned by hand, then tighten another half turn.
(b)
Make sure the washer assembly under the link head is engaged in the countersunk hole.
I. Slack off the chain hoists and remove ball lockpins and remove hoist assembly.
507
71-00 Page 418 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. May 01/00
J. Remove the engine support beams and the transportation dolly.
K. Remove lock collar (if installed), then remove loadcell assemblies by pushing upward and rotating 60 degrees to disengage from engine hoist receptacles.
NOTE: Load cell assemblies must be rotated counterclockwise for removal from receptacles with torsion springs. For removal from other receptacles, rotation may be in either direction.
L. Install access panels.
M. Couple the thrust reverser push-pull cable at quick-disconnect as follows (Fig. 406):
(1)
Join cable ends together.
(2)
Manually close jaws of coupling assembly over mating flange on connector terminal on aft conduit. Notch at aft end of both jaws must engage circular flange on terminal.
NOTE: End of forward conduit can be moved fore and aft in bulkhead fitting as necessary to make this connection.
(3)
While holding jaws in place with one hand, release outer sleeve of disconnect from forward holding position with other hand.
(4)
Push outer sleeve fully aft to secure connection.
CAUTION: CHECK THAT THE GAP BETWEEN AFT END OF OUTER SLEEVE AND AFT CONNECTOR TERMINAL IS LESS THAN 1/16 INCH. A LARGER GAP COULD INDICATE THAT THE COUPLING ASSEMBLY JAWS ARE NOT ENGAGED WITH THE CONNECTOR TERMINAL FLANGE.
N. Connect hydraulic reservoir pneumatic pressurizing line (5), (Fig. 402) at disconnect bracket.
O. Connect aft strut drain line (6) at disconnect bracket.
P. Position the engine control cables in the grooves of the lower spacer block at approximately the 10 o'clock position on the engine. The start control cable should be forward of the thrust control cable. Install the top spacer block and secure with washers and locknuts.
Q. Position the two engine control support brackets on the two bolts of the fixed bracket at approximately the 8 o'clock position on the engine. The engine thrust control bracket should be on top of the engine start control bracket. Install the washers and locknuts.
R. Connect engine start push-pull cable support clamp to bracket at 9 o'clock position on engine flange using bolt, washer, and locknut.
S. Install idle rigging pins at fuel control thrust crank and at thrust drum in strut. Check that start lever on control stand is in cutoff detent and install rigging pin through start crank extension at engine cross-shaft.
May 01/00 71-00 Page 418A/418B BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
中國航空網(wǎng) www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：737 AMM 飛機(jī)維護(hù)手冊 動(dòng)力裝置 POWER PLANT(9)
