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ELECTRICAL
AC SYSTEM
AC power is normally supplied by four variable frequency generators (VFG), two on each engine, rated at 115 volt, 40 KVA, 3 phase, 324.596 Hz output.
The generators are brushless, oil cooled and are a three stage machine type generator. The first stage is a permanent magnet generator (PMG), generator excitation function, which provides output power. The second stage is the main exciter which receives its field excitation through the generator control unit (GCU).The GCU will remove the generator from its bus and de-energize the generator, in the event of malfunction. The third stage, is the main alternator, which incorporates current transformers that are used for feeder fault and overcurrent protection.
All VFG output is routed through the AC power center (ACPC), which protects, controls and distributes primary AC power to the main airplane busses. VFG output is then routed through the CCBP to bus feeders 1, 2 and 3 and the AC ESS BUS for power distribution to the 4 transformer rectifier units (TRU) and forward AC loads. Aft AC loads are fed directly from the ACPC. Each generator normally powers its own bus, through a generator line contactor (GLC). Generator #4 also powers AC ESS BUS. In the event of a generator malfunction, the generator transfer contactors (GTC) will automatically switch to an alternate generator, to supply the affected bus. AC bus 2 and 3 are automatically shed during single generator operations.
AC power can also be supplied by the auxiliary power unit (APU) generator. The APU constant frequency generator is rated at 115 volt, 40 KVA, 3 phase, 400 Hz output. The APU generator has a ground power rating of 45 KVA continuous.
External AC power, 115 volt, 3 phase, can also be used to supply power to the AC system.
Enables maintenance personnel to power selected AC loads in the cabin, with AC external power connected.
Volume 2 Flight Crew Operating Manual Rev 3, Apr 25, 2005
ELECTRICAL
AC SYSTEM (CONT'D)
Emergency AC power is supplied by the ram air turbine (RAT) in flight, rated at 115 volts, 9 kVA, 3 phase. With engines running, the RAT will depoy with a 14 second time delay following the loss of all AC power, if the slat/flap handle is at the in/0° position. It will deploy automatically if the slat/flap handle is not at the in/0° position. With a dual-engine failure, the RAT will deploy automatically, regardless of slat/flat handle position. The RAT can also be manually deployed by pulling RAT manual deploy handle, located on the center pedestal. Once deployed, the RAT will power the AC ESS BUS via the ram air turbine line contactor (RATLC).
MANUAL DEPLOY HANDLE
GF0710_004
The RAT also incorporates a hydraulic pump, which powers hydraulic system #3. At approximately 147 KIAS and below, the RAT sheds its electrical output, giving priority to hydraulics.
A ground safety pin is installed in the nose wheel well area to secure the RAT in position while on ground.
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