(2)  
Install access panel on top of wing, if removed.

(3)  
Install engine-to-wing mid fairing (Ref Chapter 54, Engine-to-Wing Mid Fairing).

(4)  
Install fixed fairing (Ref Chapter 71, Fixed Fairing).

(5)  
Install power plant (Ref Chapter 71, Power Plant).

(6)  
Install flap transmission (Ref 27-51-281 R/I).

(7)  
Install trailing edge flap (Ref 27-51-12 R/I).

3.  Inboard Flap Inboard Track - Removal/Installation
A.  Equipment and Materials
(1)  
Primer - BMS 10-11, Type I (Ref 20-30-41)

(2)  
Corrosion Preventive Compound - MIL-C-11796, Class 3 (Ref 20-30-41)

(3)  
Sealant - BMS 5-95, Class B (Ref 20-30-11)

B.  Prepare for Removal
(1)  
Remove trailing edge flap (Ref 27-51-12 R/I).

(2)  
Remove flap transmission (Ref 27-51-281 R/I).

May 01/99 27-51-161 Page 405
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.

G22217
Inboard Flap Inboard Track Installation  513 
27-51-161  Figure 402  Oct 20/87 
Page 406 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

C.  Remove Inboard Flap Inboard Track
(1)  
Remove aft track attach bolts (Fig. 402).

(2)  
Remove bolts attaching track to forward track support fitting and remove track from airplane.

D.  Install Inboard Flap Inboard Track
(1)  
If existing bearings, bushings and bolts are to be used, check allowable wear
(Ref 27-51-161 I/C).

(2)  
Align track with main landing gear beam and install forward bolts (Fig. 402). Coat large diameter bolt with corrosion preventive compound before installation and coat small diameter bolt with sealant and install.

(3)  
Install washers and nuts. Tighten nut on large diameter bolt not to exceed 100 to pound-inches and install cotter pin. Tighten nut on smal1 diameter bolt finger-tight and install cotter pin.

(4)  
Align track with aft track support fitting, with washer on each side of fail safe link. Coat large diameter bolt with corrosion preventive compound and insert through side load link support, track and main link. Dip small diameter bolts in primer and install forward bolt through track and fail safe link, install aft bolt through side load link support and track.

(5)  
Install washers and nuts. Tighten forward nut finger-tight and install cotter pin. Tighten large diameter nut 160 to 240 pound-inches. Tighten aft nut.

E.  Restore Airplane to Normal
(1)  
Install flap transmission (Ref 27-51-281 R/I).

(2)  
Install trailing edge flap (Ref 27-51-12 R/I).

515 
May 01/03  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-51-161 Page 407 

INBOARD FLAP TRACKS - INSPECTION/CHECK
1.  General
A.  This data consists of illustrations and a wear limit chart. There is no procedure given for gaining access to the component for removal or replacement after inspection for wear. Refer to Inboard Flap Tracks - Removal/Installation for this information.
2.  Inboard Flap Tracks Wear Limits (Fig. 601, 602)

G42456
G42456

500  Inboard Flap Outboard Track Wear Limits 
Feb 20/90  Figure 601 (Sheet 1)  27-51-161 
Page 601 

BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.

G22858G22899 G23196G23209 G23490
Inboard Flap Outboard Track Wear Limits  500 
27-51-161  Figure 601 (Sheet 2)  Aug 15/73 
Page 602 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

500  Inboard Flap Inboard Track Wear Limits 
Aug 15/73  Figure 602 (Sheet 1)  27-51-161 
Page 603 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

Inboard Flap Inboard Track Wear Limits  500 
27-51-161  Figure 602 (Sheet 2)  Aug 15/73 
Page 604 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

501  Inboard Flap Inboard Track Wear Limits 
Feb 20/87  Figure 602 (Sheet 3)  27-51-161 
Page 605 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

Inboard Flap Inboard Track Wear Limits  500 
　
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