R R Fan Thrust Reverser Structure - Cut away View Figure 001
F EEFF : E E ECES ALL 『E 78-32-00EEE Page 2 Aug 01/04
R R Fan Thrust Reverser Figure 002
F EEFF : E E ECES ALL 『E EEE 78-32-00 Page 3 Aug 01/04
R R Upper Beam Figure 003
F EEFF : E E ECES ALL 『E EEE 78-32-00 Page 4 Aug 01/04
R R Fan Reverser (stowed) Figure 004
F EEFF : E E ECES ALL 『E 78-32-00EEE Page 5 Aug 01/04
R R Fan Thrust Reverser Structure Figure 005
F EEFF : E E ECES ALL 『E 78-32-00EEE Page 6 Aug 01/04
F 『
E C F M E
E E
E 56-5B E
E E
R The inner barrel is protected by a DARCHEM fire blanket. The blanket
R consists of a back-skin No.3 crimp stainless steel 0.05 mm thick and
R a front skin No.3 crimp stainless steel 0.075mm thick. Internal
R insulation consists of TRITON fibre 9 mm compressed to 8 mm. A
R sufficient quantity of breathers are provided to ensure acceptable
R air flow permeability. The blanket is attached to the inner cowl
R using a hook and latch method.
R The forward section of the inner barrel is protected with MA25 S
R ablative coating.
R (3) Forward frame
R The forward frame supports all the hydraulic system, HCU, latches,
R actuators, the stow switches and the "V" blade which interfaces with
R the fan frame (Ref. 78-36-00) (except the SOV which is on the pylon).
R (4) Ramp
R The ramp serves to deflect the air when the blocker doors are
R deployed. It is a composite honeycomb structure. Graphite composite
R skins are bonded to aluminium honeycomb.
R The ramp fairing considered represent 470 mm of the fan duct zone not
R covered.
R (5) Materials
E E Aug 01/04 E E ECES E
F 『
E C F M E
E E
E 56-5B E
E E
R ------------------------------------------------------------------------------
R COMPONENT MATERIAL
R ------------------------------------------------------------------------------
R Hinge 2024 AL
R
R Inner Barrel 7227 or 7237 AL skins,
R 5052 AL honeycomb core
R
R Outer Barrel Graphite skins, Nomex
R honeycomb core
R
R Blocker Door 7227 or 7237 AL skins,
R 5052 AL honeycomb core
R for inner panel and
R graphite skins, Nomex
R honeycomb core for outer
R panel
R
R Ramps Graphite skins,
R 5052 honeycomb core
R
R Forward Frame 2024 AL
R
R Beams AS7G06 and 2024 AL
R (6) Fire protection R (Ref. Fig. 006) R The thrust reverser is the boundary of 2 designated fire zones. The R fan compartment and the core compartment. R The fan compartment is bounded by the thrust reverser forward frame R and the 6 o'clock engine pipe cavity, which consists of stainless R steel/titanium fireshields. Fireseals are utilized at locations where R the thrust reverser abutts adjacent structure. The core compartment R is bounded by the engine case interfaces forward and aft and the R opposite reverser half at the remaining interfaces. All interfaces R are fireproof. This is obtained by the use of fireproof seals, or due R to the material properties as far as the V-groove and J-ring are R concerned.
R (7) Pressure relief R (Ref. Fig. 007) R The reverser incorporates a pressure relief system which prevents R permanent structural deformation in the event of a single bleed duct R rupture in combination with external air loading throughout the R flight envelope. R It consists of an annular opening between the thrust reverser and the R core compartment.
F 『 EEFF : ALL E Page 878-32-00
E E Aug 01/04 E E ECES E F 『 E C F M E E E E 56-5B E F 『 E C F M E E E E 56-5B E F 『 EEFF : ALL E Page 1178-32-00
R R Thrust Reverser Fire Protection Figure 006
F EEFF : E E ECES ALL 『E 78-32-00EEE Page 9 Aug 01/04
R R Pressure Relief Figure 007
F EEFF : E E ECES ALL 『E EEE 78-32-00 Page 10 Aug 01/04
F 『
E C F M E
E E
E 56-5B E
E E
R (8) Drainage
R Drainage of the core compartment is provided by a dedicated drain
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：A320飞机维护手册 AMM EXHAUST 2(43)
