A320飞机维护手册 AMM FIRE PROTECTION 防火2(10)

 Distribution Line
 Figure 503/TASK 26-21-00-991-003- 22 (SHEET 2)
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 -disconnect the line (3) from the discharge head (4) and move the bottle (8) to get access to the line (3),
 -remove the 4 screws and washers which attach the forward fire-extinguisher bottle (12),
 -disconnect the line (2) from the discharge head (7) and move the bottle (12) to get access to the line (2).
 (b)
 Install the manifold adapter (10) TOOLING TEST - ENGINE FIRE EXTINGUISHING SYSTEM (98D26203000124), the clamp (9) and the flexible pipe (8) on the outlet B (detail F).

 (c)
 Connect the manifold assembly TOOLING TEST - ENGINE FIRE EXTINGUISHING SYSTEM (98D26203000100) to the flexible pipe (8).

 (d)
 Connect a compressed air source (up to 2.07 bars (30 psi)) to the manifold assembly.

 (e)
 Open the compressed air source and make sure that the air flows from the outlets A, C, D, E, F and G (detail B) and H and J (detail C).

 (f)
 Close the compressed air source.

 (2) Leak Test
R (a) Install the plug assy (13) TOOLING TEST - ENGINE FIRE R EXTINGUISHING SYSTEM (98D26203000130) on the outlets H and J of R the lines (2) and (3) (details C and D).
 (b)
 Install the pipe blanks (11) TOOLING TEST - ENGINE FIRE EXTINGUISHING SYSTEM (98D26203000114) on the outlets E and F (detail E).

 (c)
 Install the blanks (5) TOOLING TEST - ENGINE FIRE EXTINGUISHING SYSTEM (98D26203001102) on the outlets A, D and C (detail G).

 (d)
 Install the blank (6) TOOLING TEST - ENGINE FIRE EXTINGUISHING SYSTEM (98D26203000126) on the outlet G (detail E).

 (e)
 Pressurize the line to 2.07 bars (30 psi).

 (f)
 Close the valve of the manifold assembly to isolate the extinguishing line.

 (g)
 During 5 minutes, make sure that there is no leakage: pressure must not decrease more than 0.13 bar (1.88 psi).

 (h)
 Close the compressed air source.

 (i)
 Open the drain valve to depressurize the extinguishing line.

 (j)
 Disconnect the compressed air source.

 (k)
 Disconnect the manifold assembly from the line.

R (l) Remove the blanks (5), the pipe blanks (11), the blank (6) and R the plug assy (13).
 (m) Remove the clamp (9), the flexible pipe (8) and the manifold
 adapter (10). R
 5. Close-up
________
 Subtask 26-21-00-860-058

 A. Put the aircraft back to its initial configuration.
 (1)
 If the bottles were not installed, install them (Ref. TASK 26-21-41-400-001) and go to the step B.

 (2)
 Connect the lines (2) and (3) to the discharge heads (7) and (4) (Ref. TASK 26-21-41-400-001).

 (3)
 Install the 4 screws and washers which attach the aft fire-extinguisher bottle (8).

 (4)
 Install the 4 screws and washers which attach the forward fire-extinguisher bottle (12).

 Subtask 26-21-00-865-068
 B. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): 1WE1, 1WE2, 2WE1, 2WE2 Subtask 26-21-00-410-060

 C. Close Access
 (1)
 Make sure that the work area is clean and clear of tool(s) and other items.

 (2)
 On the left engine pylon, install the access doors:
 415BL, 415BR

 (3)
 On the right engine pylon, install the access doors:
 425BL, 425BR

 (4)
 Close the left thrust reverser halves :
 (Ref. TASK 78-36-00-410-040)

 (a)
 For engine 1,
 452AR

 (b)
 For engine 2,
 462AR

 Subtask 26-21-00-440-053
 D. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041) Subtask 26-21-00-410-061
 E. Close Access
 (1) Close the fan cowls:
 (Ref. TASK 71-13-00-410-040)

 (a)
 For engine 1,
 437AL, 438AR

 (b)
 For engine 2,
 447AL, 448AR

 Subtask 26-21-00-942-060
 F. Put the aircraft back to its initial configuration.
 Remove the warning notice(s).
 Remove the access platform(s).

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