(2) For a post modification 25268 glazing panel:
(a)
You must replace the glazing panel (Ref. TASK 57-37-12-000-001), (Ref. TASK 57-37-12-400-001) if it has one of these conditions:
-a crack of more than 25 mm (0.9842 in.) in length
-
more than 3 cracks from one bolt hole
-
more than 2 cracks from one bolt hole are in the direction of the panel edge
-
more than 6 bolt holes have cracks
-
more than 2 adjacent bolt holes have cracks
-the glazing is broken.
(b)
If the glazing panel has a crack of more than 12.0 mm (0.4724 in.) and is less than 25 mm (0.9842 in.) in length, do the temporary repair that follows:
NOTE : Cracks that are in the direction of the panel edge must
____
not be stop drilled.
1 Drill a 6.4 mm (0.2519 in.) dia. hole at the end of the crack.
_
2 Clean the surface of the glazing panel with MISCELLANEOUS
_ (Material No. 19-003) made moist with warm soap solution.
3 Dry the surface of the glazing panel with a clean
_ MISCELLANEOUS (Material No. 19-003).
4_ To make a weather seal, apply SEALANTS (Material No. 09-045)
or PR1829 Polysulphide Sealant for Glazings to cover the crack
and stop drilled hole.
5_ Make an entry in the aircraft technical log that the glazing
panel has a temporary repair.
CAUTION : IF YOU DO A TEMPORARY REPAIR TO A CRACK, VISUALLY_______
EXAMINE THE CRACK EACH DAY, OR AT INTERVALS OF TEN
FLIGHT CYCLES.
IF, AFTER FIVE CHECKS, THE DIMENSION OF THE CRACK IS
NOT LARGER, EXAMINE THE CRACK AT INTERVALS OF FIFTY
FLIGHT CYCLES.
6_ Examine temporary repair(s) for an increase in the length of
the crack(s).
(3) For a post modification 28219, 30791 or 30889 glazing panel:
(a)
You must replace the glazing panel (Ref. TASK 57-37-12-000-001), (Ref. TASK 57-37-12-400-001) if it has one of these conditions:
-more than one crack
-
a vertical or longitudinal crack of more than 30 mm (1.1811 in.) in length
-
a crack in the direction of the panel edge
-minimum thickness after polishing is less than 3.33 mm (0.1311 in.)
-broken glazing
-damage to the steel shield.
(b)
If the glazing panel has a vertical or longitudinal crack of 30 mm (1.1811 in.) or less, do the repair that follows:
NOTE : A crack in the direction of the panel edge must not be
____ stop drilled.
1 Drill a 6.4 mm (0.2519 in.) dia. hole at the end of the crack.
_
2 Use fine abrasive paper to make the repair area rough. The
_ repair area is 5.0 mm (0.1968 in.) more than and all around the tape.
3 Clean the surface of the glazing panel with MISCELLANEOUS
_ (Material No. 19-003) made moist with warm soap solution.
4 Dry the surface of the glazing panel with a clean
_ MISCELLANEOUS (Material No. 19-003).
1EFF : ALL 1 33-41-00Page 408 1 1 Feb 01/04R 1 1 1CES 1
5 To make a weather seal, apply SEALANTS (Material No. 09-045)
_ or PR1829 Polysulphide Sealant for Glazings to cover the stop drilled hole.
6 Apply SPECIAL MATERIALS (Material No. 05-065) to cover the
_ crack and the stop drilled hole.
NOTE : Make sure that the tape is installed correctly and has
____ no bubbles, wrinkles or tears in it.
R 7_ Let the tape cure for not less than 15 mins at a minimumR temperature of 15 deg.C (59.00 deg.F). R
8 Make an entry in the aircraft technical log that the glazing
_ panel has a temporary repair.
CAUTION : IF YOU DO A TEMPORARY REPAIR TO A CRACK, VISUALLY
_______ EXAMINE THE CRACK EACH DAY, OR AT INTERVALS OF TEN FLIGHT CYCLES. IF, AFTER FIVE CHECKS, THE DIMENSION OF THE CRACK IS NOT LARGER, EXAMINE THE CRACK AT INTERVALS OF FIFTY FLIGHT CYCLES.
9 Examine the temporary repair for an increase in the length of
_
the crack.
5. Close-up
________
Subtask 33-41-00-865-053
A. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): 1LA, 2LA, 10LV.
Subtask 33-41-00-942-050
中國(guó)航空網(wǎng) www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：A320飛機(jī)維護(hù)手冊(cè) AMM LIGHTS 燈光1(139)
