(a)
Put the splice as near as you can to the end of the shaft.
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(b) Make sure there is sufficient clearance between the through bolts and the adjacent structure when you install the shaft.
(2) S 228-007Cut the shaft.
(3) S 228-015Measure the inner diameter with a micrometer.
(4) S 328-008Make the splice torque tube (Fig. 801).
(5) S 358-009Find and drill the bolt holes.
(6) S 378-010Apply the alodine to the inner diameter of the torque tube.
(7) S 378-018Do this task if the material of the splice torque tube is aluminum: "Apply the Alodine 1200 Solution" (Ref 51-21-04/701).
(8) S 438-011Install the splice torque tube with the wet primer.
(9) S 438-012Install the through bolts and nuts.
S 438-016
(10)
Tighten the nuts to 15-20 pound-inches more than the run-on torque.
S 228-013
(11)
Make sure the shaft is straight.
NOTE: The maximum permitted eccentricity is 0.005 inch TIR for each
____ foot of length.
S 378-014
(12) Apply the alodine to the open metal of the drive shaft outer diameter.
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S 378-017
(13) Apply two layers of the primer on all the repair area.
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KRUEGER FLAPS ROTARY ACTUATOR - REMOVAL/INSTALLATION
____________________________________________________
1. General
_______
A. There are two tasks in this procedure. There is one task for the removal and one task for the installation of the Krueger flap rotary actuator (referred to as the rotary actuator). The procedure has these parts:
(1)
The installation of the safety locks
(2)
The removal of the rotary actuator
(3)
The installation of the rotary actuator
(4)
A check of the flap profile
(5)
A check of the retract stop clearance.
B.
Each Krueger flap is operated by two rotary actuators. Each actuator has a gear reduction of 60 to 1. The gears are in a housing that attaches to the wing structure. The input shaft extends through the actuator and has splines at each end.
C.
The removal and installation procedure of all the rotary actuators is the same.
TASK 27-81-06-004-001
2. Krueger Flap Rotary Actuator Removal
____________________________________
A. Special Tools and Equipment
(1)
17MIT65B04017 Leading Edge Flap Drive Unit Lock
(2)
G27013-9 Inboard Krueger Flap No. 11 thru 16 Rigging Set (Preferred)
(3)
12MIT65B04017 Krueger Flap Rigging Tool (Optional)
B.
References
(1)
AMM 24-22-00/201, Manual Control
(2)
AMM 27-81-00/201, Leading Edge Flap System
(3)
AMM 29-11-00/201, Main Hydraulic Supply System
(4)
AMM 36-00-00/201, Pneumatic System
(5)
AIPC 27-81-01, Fig. 1
(6)
AIPC 27-81-01, Fig. 5
(7)
AIPC 27-81-01, Fig. 10
(8) 中国航空网 www.aero.cn 航空翻译 www.aviation.cn 本文链接地址：747-400 AMM 飞机维护手册 飞行操纵 FLIGHT CONTROLS 7(130)
