(2)
Position quadrant over stop with sloping face up and engage splines.
NOTE: Shaft has blind spline at both ends to ensure correct assembly.
(3)
Secure quadrant segment to shaft using bolt, washer, and locknut. While tightening bolt 90 to 110 pound-inches, apply a 20- to 50-pound upwards load on shaft and downwards load on quadrant segment to seat shaft in bearings.
27-51-191 Oct 20/86 Page 402
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
G23812
500 Flap Control Quadrant Installation
Nov 15/67 Figure 401 27-51-191
Page 403
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
E. Connect WFA and WFB cables to quadrant. Secure cables with cotter pin. Remove tags and cable clamps.
F. Lubricate control cable with grease in area which contacts quadrant.
G. Ensure that quadrant stops are free of foreign particles.
H. Connect WFA and WFB cables at turnbuckles. Remove tags and cable clamps.
I. Lift flap control lever and clamp so that index dog is disengaged from detent plate.
J. Adjust WFA and WFB turnbuckles so that flap control lever springs back to rigging position shown in figure 402. Adjust so that cable tension is within (+ 10) pounds of that specified in temperature-tension chart when lever is in rigging position.
NOTE: Ensure that flap control quadrant stops contact when flap control lever is in rigging position.
K. Install turnbuckle locking clips.
L. Remove clamp from flap control lever.
M. Install flap control unit. See Flap Control Unit - Removal/Installation, 27-51-201.
N. Test flap control quadrant per flap control unit test. See Flap Control Unit - Adjustment/Test, 27-51-201.
6. Restore Airplane to Normal Configuration
A. If required, install and seal floor panel. See Passenger Cabin Floors, Chapter 53.
B. If required, install carpets and interior equipment. See Carpets, Chapter 25.
C. If required, install aft cargo compartment ceiling panel. See Cargo Compartment Ceiling Lining, Chapter 25.
D. Close lower nose compartment access door.
27-51-191 Nov 15/67 Page 404
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
G23769
5C1 Flap Control Lever Rigging Position
Feb 20/89 Figure 402 27-51-191
Page 405
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
FLAP CONTROL UNIT - REMOVAL/INSTALLATION
1. General
A. The flap control unit includes the leading edge flap control valve, the trailing edge flap control valve, control actuating linkage, follow-up linkage and flap limit switch actuating cams. The flap limit switches are mounted on the flap control unit and may be removed with the flap control unit, however they are not part of the replacement control unit assembly.
2. Equipment and Materials
A. Corrosion Preventive Compound - MIL-C-11796, class 3 (AMM 20-30-21/201)
B. Pressure Sealant - BMS 5-19, class A (AMM 20-30-11/201)
C. Primer - BMS 10-11, Type 1 (AMM 20-30-41/201)
D. Grease - MIL-G-23827 (AMM 20-30-21/201)
E. Rigging Pin - F-1, 0.311 +0.000/-0.002 inch diameter, 2.35 +0.06 inches long (MS20392-4)
NOTE: Rigging pin is a part of kit F70207-61, or -84.
F. Wrench Set - F80197-5 (Preferred) or -1 (Optional)
G. Bonding Meter (Ref 20-22-01)
3. Prepare Flap Control Unit for Removal
A. Provide system A hydraulic power (AMM 27-51-0/201).
B. Position flap control lever in FLAP UP detent.
C. Remove system A hydraulic power (AMM 27-51-0/201).
D. Remove lower pan from flap control unit (Fig. 401).
E. Remove switch cover from flap control unit.
4. Remove Flap Control Unit
A. Use wrench set to remove limit switches (Fig. 401). Identify each switch so that it may be easily matched with proper mounting hole at installation. Retaining nuts and roller guides remain with each switch.
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