567  Outboard Midflap Carriage Spindle Bearing Installation 
Feb 20/85  Figure 801 (Sheet 2)  27-51-81 
Page 803 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

(4)  
Install washer and nut and tighten nut 40 to 200 pound-inches (1.18 inch long bearing).

(5)  
If locking holes in nut and spindle do not align with nut tightened as required, install thin washer under nut and retighten. Install clevis pin and lockwire.

(6)  
Clean excess corrosion preventive compound from forward end of bearing and spindle.

(7)  
Apply fillet of BMS 5-95 sealant between bearing and spindle on forward end per Detail B.

(8)  
Apply grease liberally around slotted hole in carriage bearing support and on bearing periphery.

B.  On airplanes with bearing and bearing inner race, install bearing as follows:
(1)  
Apply primer to spindle and bore of bearing inner race (Detail B) and install bearing inner race on spindle with wet primer.

(2)  
Install bearing on inner race.

(3)  
Clean excess primer from aft end of inner race and spindle.

(4)  
Apply fillet of BMS 5-95 sealant between aft face of inner race and spindle before installing washer.

(5)  
Install washer and nut and tighten 150 to 300 pound-inches. Remove excess sealant from moveable bearing.

(6)  
If locking holes in nut and spindle do not align with nut tightened as required, install thin washer under nut and retighten. Install clevis pin and lockwire.

(7)  
Clean excess primer from forward end of bearing inner race and spindle.

(8)  
Apply fillet of BMS 5-95 sealant between forward face of inner race and spindle.

(9)  
Apply grease liberally around slotted hole in carriage bearing support and on bearing periphery.

C.  Install carriage bearing support, together with all shims which were tagged with correct thickness and location and when bearing was removed. Tighten 3/8-inch nut 160 to 190 pound-inches and 5/16-inch nut 100 to 140 pound-inches.
NOTE:  If thickness and location of shims are unknown, refer to 27-51-72, A/T, to determine shim requirements.
If carriage bearing support interferes with flap structure, install support fitting in unison with bearing or before installing bearing on aft end of carriage spindle.
D.  Apply BMS 5-79 sealant to carriage access panel and midflap faying surface and install access panel above carriage spindle.
E.  Provide system A hydraulic power (Ref 27-51-0, MP), retract flaps and remove system A hydraulic power (Ref 27-51-0, MP).
5A6 
27-51-81 Page 804  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Feb 20/85 

OUTBOARD AFT FLAP - REMOVAL/INSTALLATION
1.  Equipment and Materials
A.  Corrosion Preventive Compound - MIL-C-11796, Class 3 (AMM 20-30-41/201)
B.  Outboard Flap Rigging Tools:
(1)  
Outboard Flap Rigging Beam - F80209-2 (Preferred)

NOTE: F80209-2 is contained in the F80209-1 Beam Set.

(2)  
Outboard Flap Rigging Tool - TE65-73720-1 and -2 (Optional)

C.  Sealant - BMS 5-79, Class C (Ref 20-30-11)
2.  Prepare Outboard Aft flap for Removal
A.  Pressurize hydraulic system A (AMM 27-51-0/201).
B.  Position flap control lever to FLAP DOWN detent.
C.  Depressurize hydraulic system A (AMM 27-51-0/201).
D.  Remove four aft flap track access panels from midflap upper trailing edge.
3.  Remove Outboard Aft flap
A.  Remove bolts connecting pushrods to aft flap (Fig. 401).
B.  Remove bolt attaching bottom flight rollers to roller support fitting.
C.  Roll flap aft, lift trailing edge and remove from flap tracks.
D.  Attach bottom flight rollers to roller support fitting.
4.  Install Outboard Aft flap
A.  If existing bushings and bolts are to be used, check allowable wear (AMM 27-51-91/601).
B.  Remove bolt attaching bottom flight rollers to roller support fitting (Fig. 401).
C.  Lift flap onto tracks and install bolt attaching bottom flight rollers to roller support. Tighten the thinner nut 30 to 40 pound-inches. (Ref .282 Thickness)
NOTE: Tighten the thicker nut to 60 to 85 pound-inches. (Ref .329 Thickness).
D. Check that forward and aft deadweight rollers are contacting aft flap track flanges and that
0.000 to 0.025 inch gap exists between aft flap track and forward and aft flight rollers.
　
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