Hawker Beechcraft Hawker 800XP, Руководство по эксплуатации для пилотов

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Hawker 800XP Pro Line 21
Page 4
Pilot’s Operating Manual
Revision A1: Nov, 2002
Section I - GENERAL
CONTENTS
A table of contents is provided at the front of each section.
SECTION 1 .................................GENERAL
SECTION 2 .................................OPERATING LIMITATIONS
SECTION 3 ................................ SYSTEMS DESCRIPTION (17 Sub-sections)
SECTION 4 .................................FLIGHT PLANNING DATA (7 Sub-sections)
SECTION 5 .................................FLIGHT HANDLING (2 Sub-sections)
SECTION 6 .................................GROUND OPERATIONS (2 Sub-sections)
SECTION 7 .................................SAFETY INFORMATION
SUPPLEMENTS
AIRPLANE GENERAL
The Hawker 800XP Pro Line 21 is a twin turbofan engine, low wing monoplane airplane, certified for
world-wide operation and intercontinental range by day or night.
The airplane is operated by two crew, Pilot and Copilot, and can carry up to fifteen passengers in a
"business express" configuration. The standard layout is an eight-seat executive configuration. A third
crew member may be carried to carry out in-flight attendants duties.
A Collins Pro Line 21 avionics system is installed with an intricate network of subsystems
interconnected and managed by the Integrated Avionics Processor System (IAPS). Avionics
information can be found in this Pilot’s Operating Manual, SECTION III, Sub-section 17 and the Collins
Pro Line 21 Avionics System Pilot’s Guide (P/N 523-0780409-001117).
Each turbofan engine has hydraulically-operated thrust reversers installed and each engine is
controlled by a digital electronic engine control unit backed up by a hydro-mechanical reversionary unit.
A single hydraulic system pressurized by engine driven pumps (one per engine) supplies power for
landing gear and doors, nose-wheel steering, wheel brakes, stall identification system, wing flaps,
airbrakes and thrust reverser functions. Back-up hydraulic supplies are provided to operate the wheel
brakes, stall identification, thrust reversers, lowering landing gear, and retraction or lowering of the flaps.
The main electrical services are supplied with 28 VDC from starter/generators, one starter/generator
installed on each engine. Emergency power is provided by batteries. Where AC power is required, it is
supplied by either engine driven alternators (208V 3-phase) or static inverters. A fluid anti-icing system
is installed along the leading edge of wings and tailplane. Hot air is used to keep the main engine air
intake and starter/generator cooling air intake free of ice.