0.71 inch.

(5)  
If dimension checked in (3) and/or (4) is not correct, add or remove shim laminations under side rollers to obtain correct dimension.

(6)  
Tighten side roller mounting bolts to between 30 and 40 pound-inches torque and lockwire bolts to each other.

500 
27-51-21 Page 406  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  May 01/99 

L.  On inboard carriage installation:
(1)  
Mount pulley bracket (11) on top of carriage halves. Dip bolts in primer and install while primer is wet.

(2)  
Adjust position of pulley bracket (11) to align cables with opening in end of midflap. Tighten mounting bolts to maintain pulley bracket position.

M.  Tighten boom cables just enough to remove slack and remove clamping device from cables.
N.  Adjust boom cables as directed in AMM 27-51-61, Aft Flap Actuating Mechanism Boom -Removal/Installation. Check that boom cables do not rub in midflap end rib. If cables rub, loosen cables, reposition pulley bracket, and readjust.
O.  Install inboard trailing edge flap. Refer to AMM 27-51-12, Inboard Trailing Edge Flap -Removal/Installation.
500 
May 15/72  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-51-21 Page 407 

INBOARD MIDFLAP CARRIAGE - INSPECTION/CHECK
1.  General
A.  This data consists of illustrations and wear limits charts. Here will be no procedure iven in this seciton for gaining access to, or removing and replacing the component after inspection for wear. Refer to AMM 27-51-21 Component - Removal/Inspection procedure for this information.
2.  Inboard Midflap Carriage Wear Limits

G12691 G12822
501  Inboard Midflap Carriage Wear Limits 
Feb 01/75  Figure 601 (Sheet 1)  27-51-21 
Page 601 
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Inboard Midflap Carriage -Wear Limits  501 
27-51-21  Figure 601 (Sheet 2)  Feb 01/75 
Page 602 
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INBOARD AFTFLAP - REMOVAL/INSTALLATION
1.  Remove Aftflap
A.  Provide hydraulic system A power (Ref AMM 27-51-0, Maintenance Practices).
NOTE:  If trailing edge flap assembly has been removed from airplane, steps A, B, and C will not apply, however, it will then be necessary to remove rigging pins F-5 and F-6 from boom assembly to allow manual extension of aftflap.
B.  Move flap control lever to FLAP DOWN (40-unit) detent.
C.  Remove hydraulic system A power (Ref AMM 27-51-0).
D.  With aftflap extended, remove midflap trailing edge (Fig. 401).
E.  Remove bottom flight rollers from aftflap carriages.
F.  Disconnect pushrods from leading edge of aftflap.
G.  Roll aftflap aft, lift trailing edge, and remove from flap tracks.
H.  If aftflap will not be immediately reinstalled, install midflap trailing edge. It is not necessary to install or tighten all retaining screws.
CAUTION:  DO NOT RETRACT FLAPS. PUSHRODS MAY DAMAGE OPENINGS IN MIDFLAP REAR SPAR.
2.  Install Aftflap
A.  If existing bushings and bolts are to be used, check allowable wear (Ref AMM 27-51-31, Inspection/Check).
B.  Remove midflap trailing edge, if installed.
C.  If installed, remove bottom flight rollers from each carriage and position aftflap on tracks in midflap (Fig. 401).
500 
Aug 15/73  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-51-31 Page 401 

G12837G12867
Inboard Trailing Edge Aft Flap Installation  500 
27-51-31  Figure 401 Sheet 1)  Nov 15/67 
Page 402 
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500  Inboard Trailing Edge Aft Flap Installation 
Nov 15/67  Figure 401 (Sheet 2)  27-51-31 
Page 403 
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D.  Install bottom flight rollers. Locate two rollers in each carriage and install bolt. Secure with two washers, nut and cotter pin.
E.  With aftflap extended, adjust eccentric bushings so that with flight rollers touching track, dead-weight rollers are against track, as shown in detail A. Tighten nuts on dead-weight rollers at 0 to 5 pound-inches and install cotter pins. If necessary, back off eccentric to first detent to engage lock.
NOTE:  There are four aftflap carriages. Each side of each carriage includes one top dead-weight roller, one top flight roller, one bottom dead-weight roller, and one bottom flight roller.
　
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