28-11-00
ALL ú ú 01 Page 621 ú Sep 20/96
A
757 MAINTENANCE MANUAL
S 366-072
(8)
If leakage was found in the upper surface of the wing center section, you must also repair the secondary fuel barrier (AMM 28-11-00/801) before you release the airplane for flight.
S 366-021
(9)
Permit the sealant to dry for the applicable tack-free time before you close the fuel tank (Fig. 611).
NOTE: You can increase the temperature and the relative
____ humidity to decrease the cure time. Do not increase the temperature to more than 120 degrees Farenheit.
I. Close the Repaired Fuel Tank
S 946-022
(1)
Remove all of the equipment that you put into the tank (for example, tools, solvent containers, plugs, brushes, and other equipment).
S 166-023
(2)
Clean the repaired fuel tank fully to remove unwanted particles and pieces of used sealant.
ST8744
(TO DO A CHECK FOR FASTENERS THAT HAVE A LEAK)
Vacuum Cup
Figure 610
E05467
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28-11-00
ALL ú ú 01 Page 622 ú Sep 20/96
A
757
MAINTENANCE MANUAL
SEALANT CLASS APPLICATION TIME HOURS 1 TIME TACK-FREE HOURS 1 HOURS OUT LIFE SQUEEZE-1 TIME CURING HOURS 1
BMS 5-45 B - 1/2 1/2 8 N/A 24
B - 2 2 24 6 48
BMS 5-26, A - 2 2 36 DNA 72
TYPE II B - 1/2 4 1/2 6 DNA 24
B - 2 2 24 6.0 48
C - 24 5 DNA DNA 24 168
C - 48 5 DNA DNA 48 336
PR-1826 6 B - 1/2 1/2 2.5 DNA 3
B - 1/4 1/4 (15 MINUTES) 1 DNA 2
PROSEAL 860 B - 1/6 1/6 (10 MINUTES) 1.5 2 DNA 4
3
____DNA - DOES NOT APPLY.
NOTE: AT 77`F (25`C) AND 50 PERCENT RELATIVE HUMIDITY AMBIENT CONDITIONS. OTHER TEMPERATURE AND RELATIVE HUMIDITY CONDITIONS WILL CHANGE THE TIME.
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