-------------------------------------------------------------------------------REFERENCE DESIGNATION
-------------------------------------------------------------------------------
57-17-11-000-001 Removal of the Covers 147AZ (148AZ)
57-17-11-400-001 Installation of the Covers 147AZ (148AZ)
28-12-45-991-001 Fig. 401
28-12-45-991-002 Fig. 402
3. Job Set-up
__________ Subtask 28-12-45-941-053
A. Safety Precautions WARNING : OBEY THE SAFETY PROCEDURES WHEN YOU DO WORK IN A FUEL TANK.
_______
(1)
You must obey the fuel safety procedures (Ref. TASK 28-00-00-910-001) when you do work on the fuel system.
(2)
Make sure that the safety barriers are in position.
(3)
Make sure that the ground safety locks are installed on the landing gear (Ref. TASK 32-00-00-481-001).
Subtask 28-12-45-860-051
B. Aircraft Maintenance Configuration
(1)
Make sure that the fuel has been drained from the applicable vent surge tank (Ref. TASK 28-25-00-650-003).
(2)
Make sure that the access platform is below the applicable access panel:
-
for the left wing, below 550CB
-
for the right wing, below 650CB.
1EFF : ALL 1 28-12-45Page 406 1 1 Aug 01/05R 1 1 1CES 1
4. Procedure
_________
(Ref. Fig. 401/TASK 28-12-45-991-001, 402/TASK 28-12-45-991-002) Subtask 28-12-45-420-051
A. Preparation for Installation
(1)
Examine the sealing ring (2) for damage, if necessary replace the sealing ring (2) as follows:
(a)
Remove and discard the sealing ring (2).
(b)
Remove the sealant from the sealing ring groove of the access panel (3) with a non metallic scraper.
(c)
Clean the access panel (3), its interfaces and the adjacent areas with a MISCELLANEOUS (Material No. 19-003) made moist with CLEANING AGENTS (Material No. 11-026).
(d)
Do an inspection of the component interface and/or the adjacent area.
(e)
Apply a thin layer of SEALANTS (Material No. 09-007) to the sealing ring groove of the access panel (3).
(f)
While the sealant is wet install, flat edge down, the new sealing ring (2) in the groove of the access panel (3).
(g)
Remove unwanted sealant from the access panel (3).
(2)
Clean the component interface and/or the adjacent area with a MISCELLANEOUS (Material No. 19-003) made moist with CLEANING AGENTS (Material No. 11-026).
(3)
Do an inspection of the component interface and/or the adjacent area.
(4)
Make sure that the parts retained from the removed component are clean and in the correct condition.
(5)
Remove the cover from the overpressure protector (1).
1EFF : ALL 1 28-12-45Page 407 1 1 Aug 01/05R 1 1 1CES 1
In-to-Wind and Out-of-Wind Dimensions Figure 402/TASK 28-12-45-991-002
1EFF : 1 1R 1CES ALL 1 11 1 28-12-45 Page 408 Aug 01/05
R Subtask 28-12-45-420-052-A
R B. Installation of the Panel Assembly 550CB(650CB)
R (1) Make sure that all of the bonding straps are correctly installed and
R attached (Ref. TASK 20-28-00-912-002), before you install the access
R panel (3).
R (2) Apply a thin layer of SPECIAL MATERIALS (Material No. 05-002) to the
R bolts (4). Apply to the shank, the threads and below the head of each
R bolt (4).
R (3) Put the access panel (3) in position and loosely install the bolts
R (4).
R (4) TORQUE the bolts in the sequence A thru X, in two steps, to these
R values:
R (a) Firstly, to between 25 and 30 lbf.in (0.28 and 0.33 m.daN).
R (b) Secondly, to between 90 and 100 lbf.in (1.01 and 1.13 m.daN).
R (5) Do a bonding check between the access panel (3) and the wing skin (5)
R (Ref. TASK 20-28-00-912-004). Make sure that the electrical
R resistance is less than 10 milliohms.
R (6) Make sure that the DIM 'X' is between 0.5 mm (0.0196 in.) and 2.5 mm
R (0.0984 in.).
R (Ref. Fig. 402/TASK 28-12-45-991-002)
R (7) Make sure that the maximum in-to-wind or out-of-wind dimensions are
R as follows:
R - along the long axis, between +/- 3.0 mm (0.1181 in.)
R - along the short axis, for a distance of approximately 100 mm
中國航空網 www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：A320飛機維護手冊 AMM FUEL 燃油2(24)
