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R B. Protection of Wing Leading Edge (Ref. Fig. 001)
-------------------------------------------------------------------------------FIN I FUNCTIONAL DESIGNATION I PANELIZONEIACCESS I ATA I I I I DOOR I REF.
-------------------------------------------------------------------------------PANEL - ACCESS, NO. 1, LH 521 521AB 57-41-22 PANEL - ACCESS, NO. 1, RH 621 621AB 57-41-22 PANEL - ACCESS, NO. 2, LH 521 521CB 57-41-22 PANEL - ACCESS, NO. 2, RH 621 621CB 57-41-22 PANEL - ACCESS, NO. 3, LH 521 521EB 57-41-22 PANEL - ACCESS, NO. 3, RH 621 621EB 57-41-22 PANEL - ACCESS, NO. 4, LH 522 522AB 57-41-22 PANEL - ACCESS, NO. 4, RH 622 622AB 57-41-22 PANEL - ACCESS, NO. 5, LH 522 522CB 57-41-22 PANEL - ACCESS, NO. 5, RH 622 622CB 57-41-22
R C. Protection of the Pylons (Ref. Fig. 002, 003)
-------------------------------------------------------------------------------FIN I FUNCTIONAL DESIGNATION I PANELIZONEIACCESS I ATA I I I I DOOR I REF.
-------------------------------------------------------------------------------DOOR-PRESSURE RELIEF, LH 410 413BL 54-52-11 DOOR-PRESSURE RELIEF, LH 410 414BR 54-52-11 DOOR-PRESSURE RELIEF, RH 420 423BL 54-52-11 DOOR-PRESSURE RELIEF, RH 420 424BR 54-52-11 DOOR-PRESSURE RELIEF, LH 471 471BL 54-53-11 DOOR-PRESSURE RELIEF, RH 482 482BR 54-53-11
R D. Protection of the Nacelle (Ref. Fig. 004)
-------------------------------------------------------------------------------FIN I FUNCTIONAL DESIGNATION I PANELIZONEIACCESS I ATA I I I I DOOR I REF.
-------------------------------------------------------------------------------DOOR-PRESSURE RELIEF, LH 438 438BR 71-13-00 DOOR-PRESSURE RELIEF, RH 448 448BR 71-13-00 REVERSER-THRUST, LH 451 451AL 71-00-00 REVERSER/THRUST, RH 452 452AR 71-00-00 REVERSER-THRUST, LH 461 461AL 71-00-00 REVERSER-THRUST, RH 462 462AR 71-00-00
Component Location - Fixed Leading Edge of Underwing
Figure 001
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Pressure Relief Door - Pylon Leading Edge
Figure 002
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Pressure Relief Door - Pylon/Wing Interface
Figure 003
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Pressure Relief Door - Nacelle
Figure 004
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R 3. System Description__________________
R R R R R R R R R A. Ventilation of the Wing Leading Edge The system is installed in the wing leading edge on the left and on the right side. A ram air inlet installed in the lower leading edge structure between slat track 1 and 2 is a NACA-type. It is connected to a duct system of seven piccolo ducts. This system is installed in the wing leading edge above the pneumatic duct between the fuselage and the pylon. In the skin of the lower wing leading edge forward of the frontspar are drainage and bleed holes.
R R The ventilation system of the wing leading edge is not monitored and has no manual control.
R B. Protection of the Wing Leading Edge (Ref. Fig. 005) This system has a protection function of the wing leading edge. It operates when a duct of the pneumatic or anti-icing system bursts or shows major leaks.
It keeps the pressure to a limit when it is too high. This prevents damage to the structure of the wing leading edge and the systems installed.
(1) The access panels prevent on excessive pressure increase. They are located at:
- the applicable bay(s) of the fixed leading edges of the wing, - the leading edge of the fuselage fairing.
(a) The access panels in the fixed leading edge of the wing are also pressure relief panels of the 'blow down' type. There are five panels on each underwing between the fuselage and the anti-icing telescopic duct. Panels 1, 2 and 3 are inboard of the engine pylon. They are a protection against overpressure caused by leaks in the pneumatic duct. Panels 4 and 5 are outboard of the pylon. They are a protection against too much overpressure caused by leaks in the anti-icing duct.
(b) For inboarding leading edge/wing root fairing overpressure relief, a pressure relief valve, with an opening area of 300 cm2 (46.6 in.2) on each side, is installed in the belly fairing. The valve opens at a pressure of 0.15 bar (2.17 psi) (relative) and the pressure is discharged into the main landing gear bay.
Pressure Relief Access Panel Installation Figure 005 中國航空網(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 PNEUMATIC 氣源 2(100)
