AA. With hydraulic pressure applied, recheck upper and lower trailing edge gaps and mismatches
and readjust, if required (Section A-A). AB. Fully extend slats. AC. Remove system A hydraulic power (Ref 27-81-0). AD. Install detent arm torque adjustment bolts (Fig. 402). AE. Check as follows:
(1)
With slats fully extended, check that trailing edge gap is as shown in Fig. 403. If gaps are not within limits, retract slats to intermediate position and adjust per step X. to obtain required gap in intermediate and full extend positions. After adjustment, tighten bolts 45 to 65 pound-inches. Install cotter pins.
(2)
Check that top of detent arm ramp is 0.72 +0.13/-0.08 inch above track surface and that bottom of detent in detent arm is above track lower surface. Reposition detent arm upstop to meet both requirements.
AF. At each detent arm, pull arm down until top of ramp is even with track lower surface (within 0.03 inch). Apply force at detent of detent arm. Check that force required to deflect each detent arm is 70 to 85 pounds and that forces at both arms are equal within 3 pounds. Adjust detent arm torque adjustment bolt as required to adjust forces. Lockwire bolt.
AG. Install access door and seal on slat at actuator rod end.
AH. Install fixed wing leading edge lower surface access panels.
AI. Remove all leading edge slat actuator locks.
AJ. Provide system A hydraulic power (Ref 27-81-0).
AK. Position flap control lever to FLAP UP detent to retract flaps and slats.
AL. Adjust aerodynamic seals on slat ends.
(1) Gap between blade type seal and adjacent structure is 0.00 to 0.03 inches.
(2) Bulb type seal must be compressed 0.03 to 0.2 inches. AM. Check that actuator door and thermal anti-icing duct door firmly contact structure on all edges.
If not, adjust to obtain firm contact. AN. Remove system A hydraulic power if no longer required (Ref 27-81-0).
531
Jun 20/85 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-81-21 Page 409
T52507
Leading Edge Slat Gap Adjustment 531
27-81-21 Figure 403 Feb 1/95
Page 410
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
513 Leading Edge Slat Installation
Jun 20/91 Figure 404 27-81-21
Page 411
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
Actuator Switch Lead Clamp Installation 513
27-81-21 Figure 405 Jun 20/90
Page 412
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
LEADING EDGE SLATS -INSPECTION/CHECK
1. General
A. This data consists of illustrations and wear limit charts. This section gives no procedures for gaining access to or removing the components, or for replacing them after inspection for wear . Refer to component removal/Installation for this information.
2. Leading Edge Slats - Surface Conditions
A. Check that leading edge roughness is less than that of 240 grit sandpaper. Symmetry between left and right wing should be maintained. Refer to Structural Repair Manual 57-50-3 for leading edge erosion repair if roughness is exceeded.
B. Check for dents in nonhoneycomb structure.
NOTE: For allowable dents in the wing thermal anti-ice area refer to the Structural Repair Manual.
(1)
Maximum depth of dent damage (Y) must not exceed Y=0.10.
(2)
Maximum Y/A ratio (A=diameter of dent) must not exceed 0.03 inch per inch.
C. Check for dents on honeycomb structure.
(1)
Maximum depth of dent damage must not exceed Y=0.10.
(2)
Maximum A/Y value must be greater than 10.
D. Refer to Structural Repair Manual, 57-50-3 Wing Leading Edge Slat-Skin Repair for repair instructions for dents that fall within the allowable limits.
3. Leading Edge Slats -Wear Limits
G42747
501 Leading Edge Slat Auxiliary Track Wear Limits
Jun 20/84 Figure 601 (Sheet 1) 27-81-21
Page 601
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
G43085G43118 G43140
Leading Edge Slats Auxiliary Track Wear Limits 501
27-81-21 Figure 601 (Sheet 2) Aug 15/73
Page 602
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
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