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Revision A4: Sep, 2010
Section III Sub-section 9
ELECTRICAL POWER
Pilot’s Operating Manual
GENERAL
The airplane utilizes both DC and AC systems with emergency systems available for certain instrument
and avionics requirements. The 28 VDC system uses a tied-busbar powered from engine driven starter/
generators and backed-up by batteries. A third starter/generator driven from the Auxiliary Power Unit (if
installed) is also available.
Power from the engine-driven generators and the APU generator is distributed by two essential busbar
systems, PS1 and PS2. In normal flight conditions the two PS busbars are tied in parallel by a bus tie
controlled by a BUS TIE switch, selected to CLOSE. Each generator circuit contains a voltage regulator
which stabilizes the busbars at 28
±
0.75 VDC. With a generator on line, selecting the BUS TIE switch
to CLOSE connects the two PS busbars in parallel. A start busbar links the start power source (either
the ground supply contactor or the internal start contactor) with the individual engine 1 and 2 start
contactor or the APU start contactor. AC power is supplied through two systems, one using inverters,
the other engine driven alternators.
CONTROLS and INDICATIONS
EXTERNAL POWER
A standard three pin 28 VDC external power receptacle is located at the right rear fuselage. For external
starts, a ground power unit capable of supplying 28 VDC with a minimum output of 42 kW (short term
capability of 28 VDC x 1500 AMPS) and having a limiter operating at 1100 AMPS must be used.
External power is connected to the airplane busbars through a ground power contactor. Contactor
operation is controlled by the EXT PWR switch supplied from the third pin of the external power
receptacle. With external power available and the EXT PWR switch ON and the EXT BATT CHG switch
OFF, the No. 1 and No. 2 batteries are disconnected from the busbars. Selecting the BATT switch to ON
has no effect.
OFF
ON
EXT PWR
Overhead Roof Panel
External Ground Power Receptacle
Содержание Hawker 800XP
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