J. Apply a thin film of corrosion preventive compound to actuator rod end attachment bolt and spacers and connect actuator to slat with bolt and washer on each side. Install locknut and tighten 220 to 360 pound-inches.
K. Reconnect actuator switch leads at electrical connector.
L. Remove all leading edge slat actuator locks.
M. Install access panel and seal on slat at actuator rod end.
N. Install leading edge slat actuator door and seal door strap angles on actuator.
(1)
Align holes in leading edge slat actuator door, seal door strap angles, and actuator and loosely install bolts. Ensure that rod end seal is attached to clips under door.
(2)
Pull door down as far as slotted and oversize holes will permit. Tighten bolts just tight enough to maintain position after being tapped into position.
O. Provide system A hydraulic power (Ref 27-81-0 MP).
P. Retract slats and lightly tap slat actuator door up into faired position. Adjust door forward and aft to obtain a gap of 0.12 +0.03 inch at aft edge of door.
Q. Extend slats to 1-unit detent.
R. Depressurize hydraulic systems (Ref 27-81-0 MP).
S. Check that each strap is properly positioned in adjustment slot of strap angle to ensure smooth operation and alignment of seal door.
T. Tighten slat actuator door attachment bolts.
U. Pressurize hydraulic system A (Ref 27-81-0 MP).
V. Cycle slats between 1-unit and UP positions of flap lever several times to bleed air from system. End cycling at 1-unit detent.
W. Position flap lever to fully extend slats. Ensure that slat extends from intermediate to full extend position.
X. Examine hydraulic fittings on actuator for leakage.
Y. Repeat steps (V) through (X) with standby hydraulic system power.
NOTE: Retract slats with hydraulic system A power as necessary.
Z. Position flap control lever to FLAP UP detent to retract slats.
AA. Remove hydraulic power if no longer required (Ref 27-81-0 MP).
AB. Install access panels adjacent to actuator and panel aft of actuator door.
AC. Check hydraulic reservoirs and service if required (Ref Chapter 12, Hydraulic Servicing).
531
27-81-41 Page 404 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. May 01/98
LEADING EDGE SLAT ACTUATOR - INSPECTION CHECK
1. General
A. This data consists of illustrations and wear limit charts. There wil1 be no procedure given for gaining access to the component, for removing it, or for replacing it after inspection for wear. Refer to Leading Edge Slat Actuator - Removal/Installation for this information.
2. Leading Edge Slat Actuator Wear Limits (Fig. 601)
G42940 G42963
504 Leading Edge Slat Actuator Wear Limits
Jun 20/83 Figure 601 (Sheet 1) 27-81-41
Page 601
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
Leading Edge Slat Actuator Wear Limits 504
27-81-41 Figure 601 (Sheet 2) Jun 20/83
Page 602
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
LEADING EDGE SLAT AERODYNAMIC SEAL - REMOVAL/INSTALLATION
1. General
A. The wing leading edge aerodynamic seal's function is to prevent airflow through cutouts provided in the wing fixed leading edge skin for attachment, actuation, and heating of leading edge slats.
2. Equipment and Materials
A. Leading Edge Slat Actuator Locks - F80048-57, -58, -59 (737-100); -58, -59, -60 (737-200); -57, -79 (on advanced and aircraft with retrofit Hi-Lift system)
3. Remove Leading Edge Slat Aerodynamic Seal (Fig. 401)
A. Provide system A hydraulic power (AMM 27-81-0/201).
B. Position flap control lever to 40-unit detent to fully extend leading edge devices. Tag or placard flap control lever DO NOT OPERATE.
C. Install leading edge slat locks on extended leading edge slat actuators (AMM 27-81-0/201).
D. Depressurize hydraulic system A (AMM 27-81-0/201).
E. Remove access panels and open access doors as required.
F. Slat main track seal curtain assembly (Detail A).
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