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S 624-085-C00
 (11) Fill space between the temperature sensors and the inlet cowl with sealant.
 (a)  Cut the sealant smooth with the surface.
 (b)  Let the sealant cure for 4 hours.
 NOTE:____ Four hour cure time is based on standard conditions of
 77 |2°F (25 |1°C) and 50 |5% relative humidity.  Cure
 time will change at other conditions.

 S 414-086-C00
 (12) Close the fan cowl panels (AMM 71-11-02/201).
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INLET COWL - INSPECTION/CHECK
_____________________________
 1. General
_______
 A. This procedure has the one task to examine the inlet cowl for damage.
 TASK 71-11-01-206-003-C00
 2. Inlet Cowl Inspection
_____________________
 A. References
 (1)
AMM 71-11-02/201, Fan Cowl Panels

 B.
Access

 (1)  
Location Zones
 506 Engine No. 1 - Inlet Cowl
 606 Engine No. 2 - Inlet Cowl

LIP SKIN
Inlet Cowl Inspection Figure 601
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RUBSTRIP
A-A

Inlet Cowl Rubstrip Inspection/Check
Figure 602

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(2)  
Access Panels
 5737/5746 Engine No. 1 - Fan Cowl Panels
 5837/5846 Engine No. 2 - Fan Cowl Panels

 C.
Procedure

 S 016-001-C00
 (1)  
Open the fan cowl panels (AMM 71-11-02/201).

 S 216-002-C00

 (2)
Examine the inlet cowl (Fig. 601) for the damage that follows:

 NOTE: If you find damage, refer to the Structural Repair Manual
____
 (SRM 54-10-01) for the permitted limits.

 (a)  
Cracks

 (b)  
Nicks, gouges, scratches, and corrosion

 (c)  
Dents

 (d)  
Holes and punctures

 (e)  
Delamination (on the inner or outer skin)

 (f)  
Erosion (on the lip skin)

 (g)  
Missing/loose fasteners on the lip skin 1) Replace the fastener. 2) It is permitted to operate the airplane with one missing

 fastener to get to a maintenance base for the correct fastener installation.

 (h)  
Measure the thickness of the aft inlet chord at the strut/inlet interface. 1) The minimum permitted thickness of the chord is 0.06 inches

 (1.52 mm).
 S 216-004-C00
 (3)  INLET COWLS WITH THE RUBSTRIPS BETWEEN THE INLET AFT CHORD AND THE STRUT FAIRING; Make an inspection of the rubstrips as follows:
　
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