R R  Fan Thrust Reverser Structure - Cut away View Figure 001
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R R  Fan Thrust Reverser Figure 002
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R R  Upper Beam Figure 003
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R R  Fan Reverser (stowed) Figure 004
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R R  Fan Thrust Reverser Structure Figure 005
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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

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R COMPONENT MATERIAL
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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.
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R R  Thrust Reverser Fire Protection Figure 006
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R R  Pressure Relief Figure 007
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R  (8) Drainage 
R  Drainage of the core compartment is provided by a dedicated drain 
　
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