(j)  
Fill the power control package (11) with hydraulic fluid.

 (k)  
Use the hoist and sling assembly to install the power control package in the airplane.

 (l)  
Apply a thin layer of grease to the forward mounting bolt (5), plain bushing (47), and flanged bushing (38).

 CAUTION: MAKE SURE THAT YOU INSTALL THE FLANGED BUSHING CORRECTLY.
_______ IF YOU DO NOT INSTALL THE FLANGED BUSHING CORRECTLY, DAMAGE TO EQUIPMENT CAN OCCUR.
 (m)  
Install the flanged bushing (38), plain bushing (47), bushing (44) and forward mounting bolt (5) (Section B-B).

 (n)  
Install the nuts (45) and (46) but do not tighten.

 (o)  
Measure the nuts (45) and (46) run-on torque with the spanner wrenches.

 (p)  
Tighten the nut (46) to 40-60 pound-inches more than the run-on torque.

 (q)  
Tighten the nut (45) to 40-60 pound-inches more than the run-on torque.

 (r)  
Install the retaining ring (29) on the reaction link bolt (13).

 (s)  
Install the bushing (30), washer (32) and the reaction link bolt (13) (Section A-A).

 (t)  
Install the antirotation plate (28) with bolt (33), washer (26), and nut (27) on the aileron (34).

 (u)  
Use a spanner wrench to measure the run-on torque of the nut (31).

 (v)  
Use the antirotation plate (28)to hold the bolt head.

 (w)  
Tighten the nut (31) to 2850-3050 pound-inches more than the run-on torque.

 (x)  
Remove the hoist equipment.

 (y)  
Install the bushing (24), the actuator attach bolt (14), the washer (36) and the nut (35) (Section A-A).

 (z)  
Install the antirotation plate (25) with bolt (33), washer

 (26), and nut (27) (Section A-A). (aa) Measure the run-on torque of the nut (35).
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 27-11-12
 ALL  ú ú 03 Page 209 ú Feb 15/99
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
 (ab) Tighten the nut (35) to 1850-2050 pound-inches more than the run-on torque. (ac) Install the retaining ring (37).
 CAUTION: BE CAREFUL NOT TO CHANGE THE ADJUSTMENT OF THE INPUT
_______ CONTROL ROD (22). IF THERE IS A CHANGE, A CHECK OF THE AILERON ADJUSTMENT IS THEN NECESSARY TO PREVENT POSSIBLE DAMAGE TO EQUIPMENT.
 (ad) Connect the control linkage (4) to the quadrant input control
 rod (22) with a nut (21), bolt (19), and washer (20). (ae) Tighten the nut (21) to 30-40 pound-inches. (af) On airplanes with a bolt and nut that require a cotter pin,
 install the cotter pin. (ag) Remove the caps from the hydraulic hoses and ports on the power control package (11). (ah) Connect the hydraulic hoses to the pressure and return ports on the power control package. (ai) Remove the inboard aileron lock.
 S 862-012
 (2)  
For the applicable system, remove the DO-NOT-CLOSE tags and close these circuit breakers:

 (a)  
P180 DC Power Distribution Panel
 1) 180H7 LATERAL CONT VALV SYS 1
 2) 180E6 LATERAL CONT VALV SYS 2
 3) 180H22 LATERAL CONT VALV SYS 3
 4) 180E21 LATERAL CONT VALV SYS 4

 S 862-013
 (3)  Set the FLT CONTROL HYD POWER - WING VALVE switches No. 1, 2, 3 and 4 on the P461 Pilot's Overhead Maintenance Panel to NORM.
 S 862-015
 WARNING: MAKE SURE THAT PERSONS AND EQUIPMENT ARE CLEAR OF THE CONTROL
_______ SURFACES BEFORE YOU SUPPLY HYDRAULIC POWER. AILERONS, RUDDERS, ELEVATORS, FLAPS, SPOILERS, LANDING GEAR, AND THRUST REVERSERS CAN MOVE QUICKLY WHEN YOU SUPPLY HYDRAULIC POWER. THIS CAN CAUSE INJURY TO PERSONS OR DAMAGE TO EQUIPMENT.
 (4)  Do this task: "Hydraulic System Pressurization" (Ref 29-11-00/201).
 NOTE: Hydraulic systems No. 1 and 3 for the left power control
____ package. Hydraulic systems No. 2 and 4 for the right power control package.
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

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