FLIGHT SPOILER ACTUATOR - REMOVAL/INSTALLATION
1. Equipment and Materials
A. Corrosion Preventive Compound - MIL-C-11796, Class 3 (AMM 20-30-21)
B. Control Surface Protractor - 4MIT65B80307-1 (preferred), F52485-500 (optional)
C. Control Surface Protractor Stand Assembly - F71292-17 (optional)
D. Aileron Control Wheel Protractor Mount - F72790
E. Fire Resistant Hydraulic Fluid -BMS 3-11, or Skydrol Assembly Lube - MCS 352 (AMM 20-30-21)
F. Control Wheel Straightedge - SE 27-0001
G. Sealant - BMS 5-95, Type I, Class B-1/2 (Preferred) (AMM 20-30-11/201)
H. Sealant - BMS 5-26, Type II (Optional) (AMM 20-30-11/201)
I. Solvent - Final Cleaning of Composites Prior to Painting (Series 87) (AMM/SOPM 20-30-87/201).
J. Corrosion Preventive Compound - MIL-C-11796, Class 3 (AMM 20-30-41/201)
2. Remove Flight Spoiler Actuator
A. Provide electrical power.
B. Provide systems A and B hydraulic power (AMM 27-61-0/201).
C. Place flap control lever in FLAP DOWN position to extend trailing edge flaps.
D. Remove electrical power if no longer required.
E. Depressurize hydraulic systems A and B (AMM 27-61-0/201).
F. Disconnect actuator piston rod end from spoiler panel (Fig. 401).
G. Disconnect hydraulic lines from actuator. Provide a container to catch any hydraulic fluid spilled.
H. Remove bolt attaching actuator link to actuator input arm.
May 01/01 27-61-51 Page 401 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
I. Remove four actuator mounting bolts and remove actuator from airplane.
J. Install protective plugs in hydraulic lines.
K. Remove two hydraulic unions from actuator.
L. Install protective caps in open ports.
3. Install Flight Spoiler Actuator
A. Check flight spoiler actuator for wear (AMM 27-61-51/601).
B. Lightly lubricate O-rings with fire resistant hydraulic fluid or Skydrol Assembly Lube. Install O-ring and hydraulic union at each hydraulic port.
C. Remove protective caps from hydraulic lines. Place actuator in airplane and align hydraulic lines.
D. Install four actuator mounting bolts (Fig. 401).
(1) Install bolts with washers on all bolts except shorter of two upper bolts. Do not install washer on short upper bolt.
CAUTION: IF WASHER IS USED ON SHORT UPPER BOLT, ACTUATOR MAY CONTACT BOLT DURING ACTUATION AND BECOME DAMAGED.
NOTE: A spacer is part of the spoiler actuator assembly which is held in place by the upper shorter bolt. The spacer is installed in between the spoiler actuator and the spoiler actuator mount.
(2)
Tighten two upper bolts to 450-550 pound-inches.
(3)
Tighten two lower bolts to 225-275 pound-inches
E. Tighten hydraulic lines.
G35561
Flight Spoiler Actuator Installation 500
27-61-51 Figure 401 (Sheet 1) May 01/01
Page 402
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
G35550
500 Flight Spoiler Actuator Installation
Feb 20/85 Figure 401 (Sheet 2) 27-61-51
Page 403
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
F. Connect actuator link at actuator input arm.
(1)
Install bolt at forward position in input arm with bolthead to left.
(2)
Secure bolt with washer, nut and cotter pin.
G. Connect actuator piston rod end to spoiler panel.
(1)
Position spacer bushing.
(2)
Clean areas around rod end checknut with solvent.
(3)
Coat piston rod end threads with corrosion preventive compound. Install rod end and tighten 350 to 400 pound-inches after adjustment. Install lockwire.
(4)
Install rod end attach bolt with bolthead to left.
(5)
Secure bolt with washer, nut and cotter pin.
(6)
Apply a bead of sealant to the rod end checknut.
H. Provide electrical power.
I. Provide systems A and B hydraulic power. Refer to 27-61-0.
J. Actuate speed brake control lever to bleed spoiler actuators.
K. Place speed brake control lever in UP position to raise all spoiler panels.
NOTE: Raising the spoilers ensures that trailing edge flaps do not strike spoilers during retraction.
L. Check that there is no hydraulic leakage at actuator.
M. Raise trailing edge flaps to full up with jackscrew stops in contact.
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