(4)
Apply SPECIAL MATERIALS (Material No. 05-013A) to the mating surface of the static port blanking-plate (3).
(5)
In the middle hole of the laminated shim (4) :
(a)
Fill the space between the laminated shim (4) and the bottom hole of the static port blanking-plate (3) with SEALANTS (Material No. 09-016).
(b)
Apply a bead of SEALANTS (Material No. 09-016) on the inner side of the middle hole of the laminated shim (4).
(c)
Let the sealant become dry.
(d)
Apply SPECIAL MATERIALS (Material No. 05-013A) on the space between the laminated shim (4) and the bottom hole of the static port blanking-plate (3).
(6)
Apply SEALANTS (Material No. 09-016) below the heads of the screws
(1) and (2).
(7)
Let the sealant become dry.
(8)
Apply SPECIAL MATERIALS (Material No. 05-013A) below the heads of the screws (1) and (2).
4. Procedure
_________
(Ref. Fig. 402/TASK 53-19-42-991-003) Subtask 53-19-42-420-050
A. Installation of the Static Port Blanking-Plate
(Ref. Fig. 402/TASK 53-19-42-991-003)
(1)
Put the static port blanking-plate (3) in position on the fuselage structure.
(2)
Install the screws (1) and (2) and tighten them.
R EFF : 106-149, 154-199, 207-299, 301-399, 53-19-42Page 410 401-499, Aug 01/05
CES Subtask 53-19-42-220-050
B. Check of the Clearances
(Ref. Fig. 402/TASK 53-19-42-991-003)
(1)
In zone D, make sure that the out-of-flush dimension A1 is 0.55 -0.25 +0.25 mm (0.0216 -0.0098 +0.0098 in.) between the fuselage structure and the static port blanking-plate (3).
(2)
In zone E, make sure that the out-of-flush dimension A1 is 0.55 -0.35 +0.35 mm (0.0216 -0.0137 +0.0137 in.) between the fuselage structure and the static port blanking-plate (3).
(3)
Make sure that the peripheral clearance J1 between the fuselage structure and the static port blanking-plate (3) is 3.1 -1 +1 mm (0.1220 -0.0393 +0.0393 in.).
5. Close-up
________ Subtask 53-19-42-420-051
A. Installation of the Static Probe 7DA3(8DA3) CAUTION : MAKE SURE THAT NO SEALANT GOES INTO THE MIDDLE HOLES OF THE
_______ BLANKING PLATE. SEALANT IN THE HOLES CAN CAUSE DAMAGE TO THE STATIC PROBE AND CAN CAUSE THE PROBE TO GIVE INCORRECT DATA.
(1) With a non metallic pin 2.5 mm (0.0984 in.) dia., remove the masking tape through the middle holes of the static port blanking-plate (3).
(2) Install the static probe 7DA3(8DA3) (Ref. TASK 34-11-16-400-002). Subtask 53-19-42-865-052
B. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): 2DA3, 3DA3, 4DA3, 5DA3
Subtask 53-19-42-942-050
C. Put the aircraft back to its initial configuration.
(1)
Make sure that the work area is clean and clear of tool(s) and other items.
(2)
Remove the access platform(s).
R EFF : 106-149, 154-199, 207-299, 301-399, 53-19-42Page 411 401-499, Aug 01/05
CES FORWARD FUSELAGE - DESCRIPTION AND OPERATION
____________________________________________
1. General
_______
R **ON A/C 001-049, 051-099, 101-149, 151-199, 201-299, 401-499,
**ON A/C 001-049, 051-099, 101-149, 201-299,
(Ref. Fig. 001)
R **ON A/C 151-199, 401-499,
(Ref. Fig. 001A)
R **ON A/C 001-049, 051-099, 101-149, 151-199, 201-299, 401-499,
A. Location The section 13/14 is the intermediate part of the forward fuselage. It lies between the FR24 and FR35. The upper part contains the front section of the cabin. The lower part contains the forward cargo compartment. The opening for the cargo door is on the right side of the aircraft between FR24A and FR28.
**ON A/C 301-399,
(Ref. Fig. 001B, 002)
A. Location The section 13/14 is the intermediate part of the forward fuselage. It lies between the FR24 and FR35. The upper part contains the front section of the cabin. The lower part contains the forward cargo compartment. The opening for the cargo door is on the right side of the aircraft between FR24A and FR28. The section 14A is the intermediate part of the forward fuselage. It lies between the FR35 and FR35.8. The top part contains the front section of the cabin. The bottom part contains the forward cargo compartment. The opening for the emergency exit door is on each side of the aircraft between FR35.1 and FR35.2A.
EFF : ALL
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