FORWARD ENGINE MOUNT SUPPORT UPPER INBOARD BOLT FRACTURE -MAINTENANCE PRACTICES (CONDITIONAL INSPECTION)

1.  General
A.  Bolt Fracture Condition
(1)  
When this bolt is found fractured for any reason, a structural inspection of the engine mount support structure is necessary.

(2)  
The conditions for a bolt fracture are:

–  
the bolt fractured because of fatigue.

–  
the bolt may have fractured because of the conditions found in MM 5-51-61 or MM 5-51-62, but the fracture may have gone undetected if only the Phase I inspections of these conditions were done.

–  
the fracture of the bolt may have gone undetected during a normal scheduled inspection.

B.  Inspection
(1)  
This inspection has one phase which is the Engine Mount Inspection.

(2)  
This inspection must be done before the next flight.

C.  Repairs and Replacements
(1)  
When this procedure tells you to "examine" a part, remove (if necessary) and look for these conditions:

–  
structure that pulled apart

–  
loose paint (paint flakes)

–  
twisted parts (distortion)

–  
bent parts

–  
fastener holes that became larger or longer

–  
loose fasteners

–  
missing fasteners (fasteners that have pulled out or are gone)

–  
delaminations (a lamination with one or more layers pulled apart)

–  
parts that are not aligned correctly

–
interference (clearance that is not sufficient between two parts) – other signs of damage

(2)  
Replace or repair the components that have one or more of the conditions given above.

(3)  
If fasteners are removed, replace with new fasteners.

500 
Aug 01/95  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  5-51-63 Page 201 

2.  Engine Mount Inspection
A.  Do the Engine Mount Inspection (Fig. 201).
(1)  
Remove the engine (Ref 71-00-00/401).

(2)  
Examine the clevis fitting (2).

(3)  
Remove and examine the bolt (3) that attaches the support fitting of the engine forward mount to the swinging link (outboard side of the engine).

(4)  
Remove and examine the bolt (4) that attaches the swinging link to the bracket installed on the wing front spar.

(5)  
Examine the swinging link (5).

(6)  
Examine the bracket (6) installed on the wing front spar.

(7)  
Remove and examine the two forward (7) and one aft (8) cone bolts.

(8)  
Remove and examine the bolt (9) that attaches the engine aft mount to the flap track.

(9)  
Examine the housing of the vibration isolator (10) for the aft cone bolt.

(10)
Examine the two engine mount rings (forward (11) and aft (12)) adjacent to the cone bolts.

(11)
Remove and examine the four thrust link bolts (13).

(12)
Examine the front spar and wing surface near the forward engine mount connections.

(13)
Examine the thrust link fittings (14) that connect the two thrust links to the wing lower surface.

(14)
Examine the wing surface near the thrust link connections.

(15)
Look for signs of fuel leaks adjacent to all connections to the wing.

500 
5-51-63 Page 202  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Aug 01/95 

F10025 F10078
500  Engine Mount and Cone Bolt Installation 
Aug 01/95  Figure 201 (Sheet 1)  5-51-63 
Page 203 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

Engine Mount and Cone Bolt Installation  500 
5-51-63  Figure 201 (Sheet 2)  Aug 01/95 
Page 204 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

CABIN DEPRESSURIZATION CONDITION - MAINTENANCE PRACTICES (CONDITIONAL INSPECTION)
1.  General
A.  The examination in this subject is applicable after a cabin depressurization caused by unscheduled opening of pressurization outflow valves.
2.  Cabin Depressurization Conditional Inspection
A.  Check for displaced blowout panels and visible lining and insulation damage (Ref Chap 21).
　
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