Aircraft Specification & Description (Serial numbers 258717, 258723 and on)

Specification & Description (Serial numbers 258717, 258723 and on)

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Contents

Introduction .................................................................................................................................... 1

1. General Description..................................................................................................................... 2

2. Design Weights and Capacities .................................................................................................... 3

3. Performance................................................................................................................................ 4

4. Structural Design Criteria ............................................................................................................ 4

5. Fuselage...................................................................................................................................... 5

6. Wing ........................................................................................................................................... 6

7. Empennage ................................................................................................................................. 7

8. Landing Gear .............................................................................................................................. 8

9. Powerplants ................................................................................................................................ 8

10. Thrust Reversers ....................................................................................................................... 9

11. Auxiliary Power Unit ................................................................................................................. 9

12. Systems..................................................................................................................................... 9

13. Flight Compartment and Avionics............................................................................................ 13

14. Interior.................................................................................................................................... 20

15. Exterior................................................................................................................................... 22

16. Publications............................................................................................................................. 22

17. Loose Equipment .................................................................................................................... 22

18. Reduced Vertical Separation Minimum (RVSM) Service ......................................................... 23

19. Factory Aircraft Comprehensive Tracking System ................................................................... 23

20. Hawker 800XP New Aircraft Limited Warranty ...................................................................... 24

21. Hawker 800XP Crew Training Agreement............................................................................... 29

Specification & Description (Serial numbers 258717, 258723 and on)

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Introduction

This document is published for the purpose of providing general information for the evaluation of the design, performance and equipment of the Hawker 800XP aircraft. Should more detailed data be required, it can be obtained by contacting:

Hawker Raytheon Aircraft Company P.O Box 85 Wichita, Kansas 67201-0085 Attention: Contracts Administration, Dept. 191

Telephone: 316.676.7111 Fax: 316.676.1910

This document describes only the Hawker 800XP aircraft, serial numbers 258717, 258723 and on, including powerplants and equipment. Also included are the warranties applicable to the Hawker 800XP aircraft, Honeywell TFE 731-5BR engine, Collins avionics equipment as well as the Hawker 800XP crew training agreement. In the event of any conflict or discrepancy between this document and the Aircraft Purchase Agreement to which it may be appended, terms specified in the Aircraft Purchase Agreement shall prevail.

Throughout this document, Raytheon Aircraft Company reserves the right to revise the Specification and Description whenever occasioned by product improvements, government regulations or other good cause, as long as such revisions do not result in a significant reduction in performance standards of the aircraft.

Copyright 2004 Raytheon Aircraft Company. All rights reserved.

Specification & Description (Serial numbers 258717, 258723 and on)

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1. General Description

The Hawker 800XP is an all metal, twin turbofan engine, swept wing executive jet aircraft. Standard seating is for 8 passengers and their baggage, plus a minimum crew of two. A third crew member seat is also provided. The aircraft has optional seating layouts which can accommodate up to 12 passengers.

Powerplants are two Honeywell TFE 731-5BR turbofan engines, pylon mounted on the rear fuselage.

The Hawker 800XP is certified in accordance with CAR.4b BCAR requirements, FAR Part 25 amended, FAR Part 36 noise requirements and meets the airworthiness requirements for RVSM approval.

Approximate Dimensions

Overall Height at Basic Operating Weight ........................................................... 18 ft 1 in (5.51 m) Overall Length .................................................................................................. 51 ft 2 in (15.60 m)

Wing

Span (overall).................................................................................................... 51 ft 4 in (15.66 m) Area.............................................................................................................. 374 sq ft (34.75 sq m) Sweep (at 25% chord)........................................................................................................20.0 deg Dihedral ...............................................................................................................................2.0 deg Aspect Ratio ............................................................................................................................ 7.09 Mean Aerodynamic Chord..................................................................................... 7 ft 11 in (2.4 m)

Horizontal Tail

Span (overall)...................................................................................................... 20 ft 0 in (6.10 m) Area................................................................................................................ 100 sq ft (9.29 sq m) Sweep (at 25% chord)...........................................................................................................20 deg Dihedral ..................................................................................................................................0 deg Aspect Ratio ............................................................................................................................ 4.00

Vertical Tail

Area............................................................................................................... 62.5 sq ft (6.10 sq m) Sweep (at 25% chord)........................................................................................................54.3 deg Aspect Ratio .............................................................................................................................. 1.1

Cabin

Length - Cockpit divider to aft pressure bulkhead................................................ 21 ft 4 in (6.49 m) Height ................................................................................................................... 5 ft 9 in (1.75 m) Width.................................................................................................................... 6 ft 0 in (1.83 m) Width - at floor ..................................................................................................... 4 ft 3 in (1.34 m)

Entrance Door

Height ................................................................................................................... 4 ft 4 in (1.30 m) Width.................................................................................................................... 2 ft 3 in (0.69 m)

Specification & Description (Serial numbers 258717, 258723 and on)

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2. Design Weights and Capacities

Maximum Ramp Weight.................................................................................28,120 lb (12,755 kg) Maximum Take-off Weight ............................................................................28,000 lb (12,700 kg) Maximum Landing Weight .............................................................................23,350 lb (10,591 kg) Basic Operating Weight *.................................................................................16,250 lb (7,370 kg) Fuel Capacity (Useable ) @ 6.7 lb per U.S. gallon ............................................10,000 lb (4,536 kg)

* Basic Operating Weight is an estimate and includes the weight of two crew, unusable fuel, oil and typically selected options.

Specification & Description (Serial numbers 258717, 258723 and on)

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3. Performance

All performance data is based on a standard aircraft and International Standard Atmospheric (ISA) conditions. Take-off and landing lengths are based on level, hard surface, dry runways with zero wind.