(a)  
Lower the elevator carefully to engage the lugs of actuator attachment fitting on the elevator with the actuator ram (12).

 (b)  
Apply a thin layer of grease on the bushings (6).

 (c)  
Install the bushings (6) in the inboard lug of the actuator attachment fitting.

 (d)  
Apply a thin layer of grease on the bolt assembly (11).

 (e)  
Install the bolt assembly (11), with the bolt head outboard.

 NOTE: Do not remove the bushing (6) in the inboard lug.
____
 (f)  
Install the outer nut (7), washer (8), and inner nut (9) on the bolt assembly.

 (g)  
Use the spanner wrench socket to tighten the outer nut (7) to 1000-1100 pound-inches plus run-on torque.

 (h)  
Tighten the inner nut (9) to 800-900 pound-inches plus run-on torque.

 NOTE: Do not tighten the outer nut (7) again after you
____ tightened the inner nut (9).
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 27-31-08
 ALL  ú ú 01 Page 208 ú Jun 18/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400
MAINTENANCE MANUAL

 (3)  S 432-024Remove the caps in the hydraulic lines and ports.
 (4)  S 642-025Apply skydrol assembly lube to the hydraulic fittings.
 S 432-026

 CAUTION: MAKE SURE YOU CONNECT THE HIGH PRESSURE LINE TO PRESSURE PORT
_______ AND THE LOW PRESSURE LINE TO RETURN PORT. IF YOU DO NOT CONNECT THE PRESSURE LINES TO THE CORRECT PORT, DAMAGE TO THE PCP CAN OCCUR.
 (5)  
Connect the hydraulic lines H1 and H2 to the outboard elevator PCP (Fig. 202).

 S 432-027

 (6)  
Install the input control rod:

 (a)  
Align the input control rod end (2) with the PCP summing lever (5).

 (b)  
Install the bolt (13), washer (14), and nut (15) with the bolt head outboard.

 (c)  
Tighten the bolt to 30-40 pound-inches plus run-on torque to turn the bolt into the clevis.

 NOTE: Do not change the adjustment of input control rod
____ while you disconnect it.
 S 092-028
 (7)  
Remove the handling cradle.

 S 862-029

 (8)  
Remove the DO-NOT-CLOSE tags and close these circuit breakers:

 (a)  
P7, Overhead Circuit Breaker Panel 1) 7E7, STAB TRIM L S/O VLV 2) 7E20, STAB TRIM R S/O VLV

 (b)  
P180, DC Power Distribution Panel 1) 180E7, ELEV/RUD VLV SYS 2 2) 180E22, ELEV/RUD VLV SYS 4 3) 180H8, ELEV/RUD VLV SYS 1 4) 180H23, ELEV/RUD VLV SYS 3

 S 862-030
 (9)  Set all FLT CONTROL HYD POWER TAIL switches on the P461, Pilots' Overhead Maintenance Panel in NORM.
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 27-31-08
 ALL  ú ú 01 Page 209 ú Jun 18/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
 S 862-092
 (10)
 Set the STAB TRIM 2 and 3 switches to ON.

 S 832-031

 (11)
 If the adjustment of the input control rod changed while you disconnect it, adjust the outboard elevator PCP (Ref paragraph 4.).

 S 712-032

 (12)
 Do an operational test of the outboard elevator PCP (Ref paragraph 5.).

 TASK 27-31-08-822-109
 4.  Outboard Elevator Power Control Package Adjustment (Fig. 203)__________________________________________________
 A. References
 (1)  
AMM 06-09-06/201, Stabilizer and Elevator Access Doors and Panels

 (2)  
AMM 24-22-00/201, Manual Control

 (3)  
AMM 27-31-07/201, Inboard Elevator Power Control Package

 (4)  
AMM 27-41-00/201, Horizontal Stabilizer Trim Control System

 (5)  
AMM 29-11-00/201, Main Hydraulic Supply System

 (6)  
AMM 34-11-00/201, Pitot Static System

 B.
Access

 (1)  
Location Zone
　
中國航空網 www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：747-400 AMM 飛機維護手冊 飛行操縱 FLIGHT CONTROLS 3(75)