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| Max takeoff/landing altitude |
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| Maximum Cabin Differential (takeoff and landing) |
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10,643 lbs Each Wing
16,422 lbs Center |
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| Main tanks Must be full if.. |
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| center contains >1,000 lbs |
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Rudder controlled over 60 knots
Steering wheel under 60 knots |
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| Wheel Speed Sensors detect Rotation Speed and are Modulated by Computer system, Temperature sensitive, Thermal Plug Sensor Brakes must be cool enough to operate or aircraft cannot GO. Prevents tire lock-up, skidding and longer stopping distances. |
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| : Freon charged, 2 for Main Engines(Located in Landing Gear Well) can feed either Engine, 1 By APU, 4 pairs of detectors(2 loops, 4 detectors each) for each Engine, 1 in Wheel well, 1 by APU |
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| APU Max operating altitude |
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| 3 Tanks, 2 Main Tanks @ 10,643 Lbs. Each, 1 Center Tank @ 16,422 Lbs., 8 Fuel Pumps, 2 Electric Pumps in each tank, 1 gear driven pump on each Engine Cross feed valve feeds both engines from either Wing Tank, Must use Center Tank first, Scavenger Pump in Center Tank Pumps last 1,000 Lbs. of fuel into #1 Wing Tank, APU is fed from #1 Wing Tank, Fuel Temperature Gauge in #1 Wing Tank, Fueling & De-Fueling Valves on #2 Wing Tank |
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| Hydraulic systems (how many what psi) |
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| Gear driven with electric A/C motor backup |
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| Same as A, operates auto-slats, flaps, and leading edge devices |
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| Hydraulic A and B Operate |
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| Rudders, ailerons, elevator, landing gear |
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| Thrust reverser, auto pilot-a, ground spoilers, inboard flight spoilers, alternate brakes |
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| Thrust reverser, auto pilot=b, outboard flight spoilers, yaw damper, normal brakes, trailing edge flaps |
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| Standby System operations |
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| Rudder, thrust reverser, flaps, auto-slats, leading edge devices |
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| Powered by System A to Pressurize System B and to operate Flaps, Auto-Slats, Leading Edge Devices |
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| in Hydraulic Tanks to keep enough fluid for Secondary Pumps in case the #1 Pump fails or leak |
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| Hydraulic System Description |
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| 2 Main Systems and a standby, Each main System is driven with an Engine and an Electrical pump as a backup, Standby System is Electric Only, System A operates Ailerons, Elevator, Rudder, Landing Gear, AutoPilot A, Thrust Reversers, B System operates the Ailerons, Elevator, Rudder, Landing Gear, AutoPilot B, Thrust Reversers, as well as Flaps, Auto Slats and Leading Edge Devices, Standby System operates the Rudder, Thrust Reversers, Flaps, Auto Slats, Leading Edge Devices. The System contains a Power Transfer Unit operated by the A system, which pressurizes the B system to operate the Flaps and Leading Edge Devices |
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| Generator and APU volts and hz |
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| Generator buses cross feed to |
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| transfer buses (fuel pumps) |
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| 3 Transformer rectifier units operate at Volts, etc |
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| 115v A/C to 28v D/C to 2 D/C buses |
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| Describe electrical system |
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| 3 Generators, 3 Transformer/Rectifiers, 2 Generator Buses, 2 Main Buses, 2 D/C Buses, 2 Transfer Buses, 1 Battery, 1 Battery Charger, 1 Inverter, T/R's Convert 115 v A/C to 28 v D/C, Inverter Converts 28 v D/C to 115 v A/C |
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| Air conditioning system description |
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| Hot Air from 5th and 9th stages of each Engine and/or the APU (Pre conditioned air from ground source straight into Mix Manifold when at terminal), Hot Air goes to 2 A/C packs to be conditioned, and trim air system, Left Pack to Cockpit and Mix Manifold, Right Pack to Mix Manifold Only, which feeds the Main Cabin(Forward and Aft), Trim Air Feeds Hot Air into each cabin mix line to adjust temperature. Re-circulating Fans(in forward cargo hold) pump air back to Mix Manifold to re-condition and re-circulate air back into cabin. |
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| Hot Air goes to Primary Heat Exchanger to be cooled, to the Air Cycle Machine and gets compressed(gets hot again), to the Secondary Heat Exchanger, to the High Pressure Water Separator and back to the Air Cycle Machine(Turbine Portion) and back through the Water Separator and then to the Mix Manifold. |
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| Flows Hot Air into the Cabin Mix Lines(after Mix Manifold) and can be regulated to control Cabin Temperature. |
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| Describe APU (auxiliary power unit) |
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| Located in the tail end of aircraft, provides backup electrical and additional bleed air, is started with a battery, and drains 200-300 lbs of fuel per hour from #1 fuel tank |
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| What is the standard pressure in cabin |
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| Releases excess cabin pressure |
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| Allows pressure into aircraft below 8,000 |
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| What emergency equipment is standard? |
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| Megaphone, First Aid Kit, Crash Axe, CO2 Extinguisher, Water Extinguisher, Dry Chemical Extinguisher, BCF Extinguisher, Smoke Hood, Life Vests, Flashlights |
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| What are the three classes (types) of fire extinguishers |
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A-Combustibles
B-Flammable liquids
D-Live electcal |
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| Takeoff weight determined by |
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| Weight at Brake Release- Determined by Runway Length, Temperature, Altitude, Tire Speed Limits, Brake Energy Limits, Obstacle Clearance, Enroute Clearance, & Operating Requirements |
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| 3° = 48' per Nautical Mile |
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| Cards by Stealth//typhoon5150@hotmail.com Say thanks |
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