Hawker 800 XP, Pilot Training Manual

Page: 121 / 504

MASTER WARNING SYSTEM
The master warning system (MWS) panel is
located on the center instrument panel. Ice
protection, fuel, and electrical system an-
nunciators are grouped on the roof panel. Roof
and MWS panel annunciators are red, amber,
and white. Red warnings are those which re-
quire immediate crew action. Amber and white
annunciators denote faults or system condi-
tions of less urgency to the crew. Test buttons
are provided to test all annunciator filaments
and warning circuits.
FUEL SYSTEM
The Hawker 800 XP fuel system includes one
integral (wet) fuel tank in each wing and a
metal ventral tank in the lower aft fuselage.
The system has both a wing tank-to-tank trans-
fer capability and a crossfeed capability from
either wing tank to one or both engines. One
electric boost pump in each wing tank deliv-
ers fuel under pressure to its respective engine
during normal operating conditions. Each
boost pump operates two jet pumps for trans-
fer of fuel from outer portions of the same
tanks and from the opposite wing tanks and
ventral tank. The fuel system has both grav-
ity- and pressure-refueling/defueling capa-
bilities. All tanks can be pressure-refueled or
defueled simultaneously.
AUXILIARY POWER UNIT
The APU is a self-sufficient unit installed in
the rear equipment bay that renders the airplane
independent of ground service equipment.
Both the Garrett Turbine Engine Company
(AiResearch) and Solar Turbines Incorporated,
(Turbomach) manufacture power units in-
stalled in the Hawker 800 XP. Its function is
to drive a DC generator to power the aircraft
electrical system, charge the aircraft batteries,
and provide bleed air to the air conditioning
system for heating and cooling.
POWERPLANT
The aircraft is propelled by two Garrett AiResearch
Model TFE 731-5BR turbofan engines installed
in pods mounted on pylons; one on each side of,
and integral with, the rear fuselage.
Firewalls divide each pod into two fire zones
which are ventilated by ram air; both zones in-
corporate a fire/overheat warning system. The
two-shot fire extinguishing system discharges
only into zone 1, the forward zone.
Hot air is bled from the engine to pressurize
and air condition the aircraft, to operate the
rudder bias system and for engine anti-icing.
Each engine has a combined starter/generator and
can be started from either the aircraft batteries
or a ground power supply. Each engine has an
AC generator for the pilot’s windshield de-icing.
Engine power and fuel shutoff controls for
each engine are operated by separate throttle
and high pressure cock levers on the pilot’s
central control pedestal.
Engine starting, ignition and anti-ice controls
are located on the flight compartment roof
panel. Instruments (i.e. N
1
, N
2
rpm, ITT, oil
pressure and temperature indicators) are lo-
c a t e d i n t h e c e n t e r i n s t r u m e n t p a n e l .
Annunciators associated with the engine are
on the main MWS and roof panel.
The Hawker 800 XP airplanes are equipped
w i t h a D e e H o w a r d T R 5 0 0 0 BA T h r u s t
Reverser System. The system includes a thrust
reverser assembly at the rear of each engine
nacelle and various controls and indicators
located within the cockpit.
FIRE PROTECTION
The Hawker 800 XP fire protection system in-
cludes the detection and warning of fire and
overheat conditions in each engine and within
the APU. Overheat detection capability is also
provided for the rear equipment bay. Fire ex-
tinguishers are installed to extinguish engine
and APU fires. The engine fire extinguishing
system is a two-shot system; if an engine fire
is not extinguished with actuation of the first
bottle, the second bottle is available for dis-
charge into the same engine. The engine fire bot-
tles are located in the rear equipment bay. The
APU has independent fire detection, warning,
and extinguishing systems. A portable hand-
held extinguisher is located in the cockpit.
Revision 1 1-17
FOR TRAINING PURPOSES ONLY
HAWKER 800 XP PILOT TRAINING MANUAL
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