Subtask 28-12-47-860-050
 B. Aircraft Maintenance Configuration (1) Make sure that the access platform is below the applicable zone 550(650). (2) Make sure that the applicable access panel 550BB(650BB) is removed (Ref. TASK 28-10-00-910-002) (Ref. TASK 57-27-11-000-002). 4. Procedure_________ 
R  **ON A/C 001-049, 051-099, 101-149, 151-199, 201-299, 401-499,
 (Ref. Fig. 401/TASK 28-12-47-991-001) **ON A/C 301-399,
R  (Ref. Fig. 401A/TASK 28-12-47-991-001-A) **ON A/C 001-049, 051-099, 101-149, 151-199, 201-299, 401-499,
 (Ref. Fig. 402/TASK 28-12-47-991-002) **ON A/C 301-399,
R  (Ref. Fig. 402A/TASK 28-12-47-991-002-A) **ON A/C ALL 
R  Subtask 28-12-47-420-052-A 
R R R  A. Preparation for Installation (1) Examine the sealing ring (19) for damage. If necessary, remove and discard it. 
R R R  (2) Install the new sealing ring (19): (a) Remove the used sealant from the groove in the NACA vent intake (14) with a non-metallic scraper.

 NACA Vent Intake Door Installation Details
 Figure 402/TASK 28-12-47-991-002

R 1EFF : 001-049, 051-099, 101-149, 151-199, 1 28-12-47Page 411 1201-299, 401-499, 1Aug 01/05 1 1 1CES 1R NACA Vent Intake Door Installation Details R Figure 402A/TASK 28-12-47-991-002-A

R 1EFF : 301-399, 1 28-12-47Page 412 1 1 May 01/04 1 1 1CES 1 1EFF : ALL 1 28-12-47Page 413 1 1 Aug 01/05 1 1 1CES 1

R R R  (b) Clean the groove in the NACA vent intake (14) with a MISCELLANEOUS (Material No. 19-003) made moist with CLEANING AGENTS (Material No. 11-026). 
R R  (c) Apply a thin layer of SEALANTS (Material No. 09-007) to the groove for the sealing ring (19) in the NACA vent intake (14). 
R  (d) While the SEALANTS (Material No. 09-007) is wet: 
R R  1_  Put the new sealing ring (19) (with the flat edge down) in thegroove in the NACA vent intake (14). 
R R  2_  Remove unwanted SEALANTS (Material No. 09-007) from the faceof the NACA vent intake (14). 
R R R  (3) Clean the component interfaces and the adjacent area with a MISCELLANEOUS (Material No. 19-003) made moist with CLEANING AGENTS (Material No. 11-004). 
R  (4) Do an inspection of the component interface and/or the adjacent area. 
R R  (5) Make sure that the parts retained from the removed component are clean and in the correct condition. 
R R R  (6) Apply a thin layer of SPECIAL MATERIALS (Material No. 05-002) to the bolts (4). Apply to the shank, the threads and below the head of each bolt (4).
 Subtask 28-12-47-420-050
 B. Installation of the NACA Vent Intake
 (1) Assemble the bolt (17), the washer (16), the nut (15) and one end of the bonding strip (4) to the NACA vent intake (14). Put the free end of the bonding strip (4) loosely in the end of the NACA vent intake.
 (2) Apply STORAGE PRESERVATION (Material No. 15-004) to the fastener bolt (18) holes.
 (3) Install the NACA vent intake (14) and secure it loosely with the bolts (18).
 (4) TORQUE the bolts (18) in the sequence A thru AF, in two steps, as follows:
 CAUTION : YOU MUST TIGHTEN AND TORQUE THE BOLTS IN THE CORRECT_______ SEQUENCE TO PREVENT DAMAGE TO THE COMPONENTS.

 (a)
 Firstly to between 25 and 30 lbf.in (0.28 and 0.33 m.daN).

 (b)
 Secondly to between 90 and 100 lbf.in (1.01 and 1.13 m.daN).

 (5)
 Make sure that the NACA vent intake and the aircraft bottom-skin are correctly aligned. The maximum in-to-wind or out-of-wind dimension is:

 -
in areas less than 10 deg from the line of flight, 0.6 mm (0.0236 in.)

 -
in areas greater than 10 deg from the line of flight 0.3 mm (0.0118 in.).

 (6)
 Get access through the hole 550BB (650BB) and remove the free end of the bonding strip (4) from the NACA vent intake (14). Pull the free end of the bonding strip (4) through the duct-hole in RIB23.

 (7)
 Apply FUELS (Material No. 01-001) or COMMON GREASE (Material No. 04-012) to the O-ring seal (3).

 (8)
 Install the new O-ring seal (3) on the elbow-duct assembly (13).

 (9)
 Install the elbow-duct assembly (13) through RIB23 and into the NACA vent intake (14).

 (10)
 Attach the elbow-duct assembly (13) to the aircraft structure with the bolt (2) and the washer (1). Tighten the bolt (2).

 (11)
 Attach the bonding strip (7) to the elbow-duct assembly (13) with the bolt (8) and the nut (6) to bonding method 8 (Ref. TASK 20-28-00-912-006).

 (12)
 Attach the bonding strips (4) and (9) to the elbow-duct assembly (13) with the bolt (5), the washer (10) and the nut (11) to bonding method 8 (Ref. TASK 20-28-00-912-006).
　
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(35)