G09919
Elevator Power Control Unit Installation 551
27-31-101Page 402 Figure 401 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Oct 20/84
G. Disconnect input rod from power control unit input crank.
H. Remove power control unit lower mounting bolt from aft control quadrant mounting bracket.
I. Remove power control unit upper mounting bolt from output torque tube.
J. Remove power control unit from airplane.
K. Install rigging and restraining tool, if required.
NOTE: If both power control units are removed at the same time, install elevator rigging and restraining tool in place of right power control unit.
4. Install Elevator Power Control Unit
A. Remove elevator systems A and B hydraulic power (Ref 27-31-0, MP).
B. Check that rigging pin E-5 is installed in aft control quadrant.
C. Check for allowable wear at elevator power control unit attachment points (Ref 27-31-101, I/C).
D. If installed, remove elevator rigging and restraining tool.
E. Position power control unit in aft compartment and install upper mounting bolt in output torque tube.
(1)
Apply grease to entire shank of bolt.
(2)
Install bolt with head facing inboard.
(3)
Install nut and washer (Fig. 401).
F. Attach power control unit rod end to aft control quadrant mounting bracket as follows:
(1)
Apply grease to entire shank of bolt and install bolt from right to left.
(2)
Install first locknut and tighten 550 to 600 pound-inches.
CAUTION: AFTER TIGHTENING SECOND LOCKNUT, DO NOT ATTEMPT TO RETIGHTEN FIRST LOCKNUT.
(3)
Install second locknut and tighten 225 to 250 pound-inches.
F-1. Move power control unit to fully retracted position. Check for interference between power control unit and reaction link per Fig. 403 and eliminate interference if necessary.
May 01/99 27-31-101 Page 403 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
G. Attach input rod to power control unit input crank as follows:
NOTE: Ensure rod assembly is installed with clevis end up.
(1)
Visually inspect the dual loadpath bolts for damage prior to installation.
(2)
Pre SB 27-1207;
(a)
Apply grease to entire shank of bolt assembly and install bolt assembly with washer under bolthead from left to right through input rod, input crank and into nutplate on input rod.
(b)
Tighten outer bolt to 45-60 pound-inches.
CAUTION: AFTER TIGHTENING LOCKNUT, DO NOT RETIGHTEN OUTER BOLT.
(c)
Install locknut with washer over end of inner bolt and tighten to 15-20 pound-inches.
(3)
Post SB 27-1207;
(a)
Apply grease to entire shank of bolt assembly and install bolt assembly from right to left through input rod and input crank.
(b)
Tighten inner nut to 45-60 pound-inches.
(c)
Tighten outer nut to 15-20 pound-inches.
CAUTION: AFTER TIGHTENING NUT, DO NOT RETIGHTEN INNER NUT.
(d)
Visually inspect for clearance between the control rod dual-loadpath bolts and surrounding structures.
H. Remove protective plugs and caps and connect two flexible hydraulic lines to power control unit.
CAUTION: ENSURE THAT ELECTRICAL CONNECTOR IS INSTALLED IN AN APPROXIMATE VERTICAL POSITION GIVING MAXIMUM CLEARANCE TO ADJACENT STRUCTURE.
I. If installed, attach electrical connector to power control unit receptacle.
J. Remove rigging pin E-5 from aft control quadrant.
K. Restore airplane to normal hydraulic configuration (Ref 27-31-0, MP).
L. Adjust and test elevator power control unit (Ref 27-31-101, A/T).
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：737 AMM 飞机维护手册 飞行操纵 FLIGHT CONTROLS 2(103)
