- the outer wall of the exhaust nozzle.
This outer wall contains an inner cowl forming the inner wall of the
exhaust nozzle.
The fan thrust reverser assembly is hinged to the pylon and clamped to
the engine fan frame.
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Exhaust - General
Figure 001
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Fan Thrust Reverser Pivoting Doors
Figure 002
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Fan Thrust Reverser
Figure 003
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Exhaust Modes
Figure 004
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C. Thrust Reverser System (Ref. 78-30-00) (Ref. Fig. 004) The fan thrust reverser assembly uses part of engine exhaust power to provide additional aerodynamic braking during aircraft landing. The fan thrust reverser assembly is hydraulically actuated by the hydraulic pump mounted on the associated engine. It is controlled by a lever hinged to the corresponding throttle control lever from the cockpit through two redundant and segregated circuits. The first one is EIU/ECU/HCU, the second one being SEC/static relay/SOV.
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HOT EXHAUST - DESCRIPTION AND OPERATION
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1. General
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The hot exhaust consists of a center body and a conical primary nozzle.
The nozzle directs the primary exhaust gas aft and regulates the gas stream
flow.
A. Core Nozzle (or Primary Nozzle)
(1) Description
R **ON A/C 001-049, 051-099, 101-149, 151-199, 201-299, 401-499,
(Ref. Fig. 001)
**ON A/C 301-399,
(Ref. Fig. 001A)
**ON A/C ALL
The primary nozzle is composed of a forward flange for attachement to the engine outer primary exhaust frame (A6 flange) with 16 bolts, a conventional stiffened sheet metal inner and outer skin, and a forward bulkhead. A spring seal is attached to the outer barrel which interfaces with the pylon. The outer barrels are of skin and frame construction. The primary nozzle structural assembly is a riveted conventional sheet metal structure.
(2) Drainage is provided by holes located in both the inner and outer skins. The inner skin has one 0.312 in. diameter hole located at the lowest point in the skin contour. The outer skin has five 0.312 in. diameter holes located aft of each stiffener at engine center line.
B. Center Body
(1) Description
R **ON A/C 001-049, 051-099, 101-149, 151-199, 201-299, 401-499,
(Ref. Fig. 001)
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Core Nozzle/Center Body (Config 1)
Figure 001
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R Core Chevron Nozzle/Center Body (Config 2) R Figure 001A
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R **ON A/C 301-399,
R (Ref. Fig. 001A)
R **ON A/C ALL
The centerbody is composed of a forward flange for attachment to the engine inner primary exhaust frame (A7 flange) with 16 bolts and a stiffened sheet metal formed section with an open aft end for the engine center vent system.
(2) Drainage is provided by four 0.25 in. diameter holes located at engine center line. The first hole is at STA 265.1 and the remaining holes are located just aft of each frame.
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NOZZLE - CORE - REMOVAL/INSTALLATION
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本文链接地址：A320飞机维护手册 AMM EXHAUST 1(13)
