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737-300/400/500MAINTENANCE MANUAL
 (b)  
At the faying surface between the terminal fitting which is on the inside of the tank and rear spar web.

 (c)  
At the faying surface between the rear spar web and the rear spar chord.

 (d)  
At the faying surface between the rear spar chord and the wing skin.

 (e)  
At the faying surface between the rear spar chord and the chord splice fitting.

 (f)  
At the faying surface between the rear spar web and the bulkhead fitting body stations 663.

 S 286-146
 (6)  After you find the external leak point, use Fig. 623 to help you find the internal leak point.
 NOTE: It can help to make sure you found the external leak
____
 point if you remove the external sealant.

 I. No. 1 or No. 2 Internal Tank - Aft Inboard Upper Corner
 S 286-147
 (1)  
Leaks can occur in the aft inboard upper corner of the No. 1 or No. 2 tank.

 S 286-148

 (2)  
Internal access to the aft inboard upper corner of the No. 1 or No. 2 tank is through the No. 1 access panel between wing rib WBL 114 and wing rib WBL 135.5 (AMM 28-11-11/401) and through an access hole through wing rib WBL 114 and Wing Rib WBL 92.5.

 (a)  When the center tank is drained and purged, access to the aft inboard upper corner of the No. 1 or No. 2 tank can be through the center tank access panel under the left air conditioning door (AMM 28-11-31/401) and through the access panel in wing rib WBL 70.85 (AMM 28-11-51/401).

 (3)  
External access is through the main wheel well.

 S 286-149
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A 737-300/400/500MAINTENANCE MANUAL

UPPER REAR SPAR SPLICE

A
External View - Upper Rear Spar Splice
Figure 622 (Sheet 1)

F42091
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737-300/400/500MAINTENANCE MANUAL
STRINGER 18A STRAP
UPPER TRAILING EDGE PANEL
REAR SPAR WEB OUTBD
External View - Rear Spar Upper Splice Figure 622 (Sheet 2)
BULKHEAD FITTING
BODY STATION 663

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737-300/400/500MAINTENANCE MANUAL
 S 286-150
 (4)  
Leaks from this area can occur when the No. 1 or No. 2 tank has 1500 kg (3300 pounds) or more of fuel and when the airplane is parked and level.

 S 286-151

 (5)  
Find the external leak point.

 (a)  
After you find the external leak point, use the Backblowing procedure to find the leak path.

 (b)  
Use Fig. 624 to help you find the internal leak point.

 S 286-152
 (6)  The internal leak point can be at one of these locations:
 (a)  
At a fastener fillet seal.

 (b)  
At a fastener self sealing collar.

 (c)  
At a fillet seal at the terminal fitting and rear spar web.

 (d)  
At a fillet seal at the rear spar web and the rear spar chord.

 (e)  
At a fillet seal at the rear spar chord and the wing skin.

 (f)  
At a fillet seal at the rear spar chord and the chord splice plate.

 (g)  
At a fillet seal at the seal pan and wing structure.
　
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