Page 2-5
Pilot’s Operating Manual
Revision A1: Nov, 2002
Sub-section 2
ENGINES
Hawker 800XP Pro Line 21
Section III - SYSTEMS DESCRIPTION
GENERAL
The airplane is powered by two Garrett AiResearch Model TFE 731-5BR-1H turbofan engines installed
in pods mounted on pylons; one 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 incorporate a
fire/overheat warning system. The two shot fire extinguishing system discharges only into zone 1, the
forward zone.
For more information on the engine fire protection system refer to Sub-section 4, FIRE PROTECTION.
Hot air is bled from the engine to pressurize and air condition the airplane, 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 airplanes batteries or an external power supply. Each engine has an AC alternator which
provides deicing to the pilot’s windshields.
The engine consists of five major components:
• Fan
• Low Pressure (LP) Spool
• High Pressure (HP) Spool
• Annular Combustion Chamber
• Transfer and Accessory Gearboxes
Engine power and fuel shut off controls for each engine are operated by separate thrust and high
pressure (HP) cock levers on the pilot’s central control pedestal with engine starting, ignition and antice
controls being located on the flight compartment overhead roof panel.
Indications of N
1
, N
2
, ITT, oil pressure, oil temperature and fuel flow are displayed on the pilot’s Multi
Function Display. Annunciators associated with the engine are on the main MWS and overhead roof
panel.