S 286-229

 (4)  
External access is from under the wing.

 S 286-230

 (5)  
Find the external leak point.

 (a)  
Remove the aerodynamic gap seal in areas of suspected leak paths to find the external leak point.

 (b)  
Remove the aerodynamic seal in the gap between the two wing skins inboard and outboard from the wet location until you see dry surface.

 S 286-231
 (6)
After you find the external leak point, drain and purge the tank.

 S 286-232

 (7)  
Use the Backblowing procedure and Fig. 638 to help find the internal leak point.

 S 286-233

 (8)  
The internal leak point can be at one of these locations (Fig. 640):

 (a)  
At a fastener fillet seal.

 (b)  
At a fastener self sealing collar.

 (c)  
At the fillet seal between the stiffener and any part that is attached to the stiffener.

 (d)  
At the fillet seal between stiffener and wing skin. 1) The leak can occur anywhere along the length of the

________ stiffener.
 V. External- No. 1 or No. 2 Tank - Along the Lower Stiffener S-5
 S 286-234
 (1)  
Leaks can occur from the No. 1 or No. 2 tank anywhere along the lower stiffener S-5.

 S 286-235

 (2)  
Internal access to the area of the No. 1 or No. 2 tank is through any wing access panel between the wing ribs (AMM 28-11-11/401).

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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
RIB
LOWER WING SKIN
FILLET SEAL
LOWER STIFFENER S-9 FILLET SEAL
FWD RIB
OUTBD
STIFFENER S-9
FASTENER
FILLET SEAL FILLET SEAL
LOWER WING SKIN LOWER WING SKIN AERODYNAMIC SEALANT
Internal View - No. 1 Tank - Stiffener S-9 Between Ribs Figure 637
F83608
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
 (3)  S 286-236Leaks from this area can occur when the No. 1 or No. 2 tank has a small quantity or more of fuel when the airplane is parked and level.
 (4)  S 286-237External access is from under the wing.
 (5)  S 286-238Find the external leak point with fuel in the tank. (a) Remove the aerodynamic gap seal in the area of suspected leak paths to find the external leak point. (b) Remove the aerodynamic gap seal between the two wing skins inboard and outboard from the wet location until you see dry surface.
 (6)  S 286-239After you find the external leak point, drain and purge the tank.
 (7)  S 286-240Use the Backblowing procedure and Fig. 639 to find the internal leak point.
 (8)  S 286-241The internal leak point can be at one of these locations (Fig. 640): (a) At a fastener fillet seal. (b) At a fastener self-sealing collar. (c) At the fillet seal between the stiffener and any part that is attached to the stiffener. (d) At the fillet seal between stiffener and wing skin (Fig. 640). 1) The leak can occur anywhere along the length of the________ stiffener.

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 28-11-00
 ALL  ú ú 02 Page 680T ú Mar 12/02
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
FUEL DOOR CUTOUT
LOWERRIB WING SKIN
FILLET SEAL
LOWER STIFFENER S-5
FILLET SEAL
FWD
RIB
OUTBD
STIFFENER S-5
FASTENERS
FILLET SEAL FILLET SEAL
LOWER WING SKIN LOWER WING SKIN AERODYNAMIC SEALANT
Internal View - No. 1 -Tank Stiffener S-5 Between Ribs Figure 638
　
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