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25 Cards in this Set
- Front
- Back
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Danger Zones |
Suction from engine 1 and 2 intake Heat from engine 1 and 2 exhaust Heat from ECS (upper right T section) Heat from APU (upper left T section) Main and tail rotor blades |
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T700-GE-401C |
Front-drive turbo shaft engine Maximum continuous rating of 1662 SHP (shaft horse power) Intermediate rating of 1800 SHP (for 30 minutes) Contingency power rating of 1940 SHP (for 2.5 minutes) |
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5 engine sections |
Inlet Compressor Combustor Turbine Exhaust |
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4 module engine sections |
Accessory section module Cold section module Hit section module Power turbine module |
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Hover infrared suppression system (HIRSS) |
Reduces gas exhaust radiation and line of sight hot surfaces |
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MRH NR (Speed) |
35% NR - centrifugal force pulls anti flap outward 70% NR - centrifugal force pulls drool stops out 50% NR - drop stops seat |
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Tail Rotor |
Canted at 20° Provides 2.5% of lifting force Counteracts torque of mrh to provide directional control |
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Fuel cell main tanks |
Provides 1224 pounds (180 gallons) of fuel storage (each) Completely ballistic tolerant - lower third seals rounds up to 14.2 mm - upper two thirds seals rounds up to 7.62 mm |
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#1 cell |
Single point fueling/defueling and gravity fueling Two high level shut-off valves, two check valves Apu fuel/prime line Sump drain Internal fuel boost pump Vent Fuel pump line |
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#2 cell |
Gravity refueling Two high level shut-off floats Check valve Sump drain Internal fuel boost pump Vent Fuel dump line |
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Fueling operation |
Pre-check valves shall significantly reduce/stop fuel flow to main fuel cells within 5-10 seconds Indicates high level sensors are working |
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Pressure and gravity fueling |
Pressure - port on port side of A/C (aft of cabin) Gravity - #1 fuel cell on starboard, #2 on port |
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Types of fuel |
JP-5 (F-44) - primary fuel JP-8 (F-34) - alternate fuel (flashpoint to low for ship) JP-4 (F-40) - restricted |
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Pneumatic sources for engine start |
External pneumatic power ground source APU Engine cross bleed air |
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Bleed air |
For inlet anti-icing, ECS operation, and cross bleed engine starting |
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Power train 5 main components |
Main transmission module Drive shafts Oil cooler IGB TGB |
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Transmission system primary function |
Take combined power from two engines, reduce the RPM and transfer it to main rotor and tail rotor |
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Transmission system secondary function |
To drive accessory modules and utility hydraulic pump |
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Tail drive shaft |
6 sections with disconnect coupling Shafts are ballistically tolerant and suspended at 4 points by viscous damper bearings |
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IGB |
Transmits torque, reduce shaft speed from MGB to the TGB, and changes angle of drive |
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TGB |
Transmits torque to tail rotor, changes angle of the drive and provides gear reduction Enables pitch change of tail rotor blades via flight controls |
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Metal chip detectors |
Installed in each gearbox Sends signal to cockpit indicating detected chip Equipped with fuzz burn off (immediately burns off chip) |
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Free wheel unit |
Allows the main transmission to spin freely of engines if transmission rotates faster than engine input gear (auto rotation) |
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APU |
Supplies pneumatic power for engine start, provides bleed air to ECS system and limited electrical power for ground operations, in-flight emergencies and back-up pump power Garret and sunstrand |
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Aux tank |
Crashworthy, ballistic tolerant 200 gallon (194 usable) |
