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Hawker Beechcraft Hawker 800XP Pilots Operating Manual

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Table of Contents

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PILOT'S OPERATING MANUAL
P/N 140-590032-0007
for
Applicable to Airplane Serials 258541, 258556, 258567 and After
Equipped with Collins Pro Line 21 Avionics
that have not installed Hawker Beechcraft Winglet Kits.
©
Copyright
2012 Hawker Beechcraft Corporation. All rights reserved.
Hawker and Beechcraft are trademarks of Hawker Beechcraft Corporation.
Original Issue: Feb, 2002
Revision A5: Feb, 2012

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Summary of Contents for Hawker Beechcraft Hawker 800XP

  • Page 1 Equipped with Collins Pro Line 21 Avionics that have not installed Hawker Beechcraft Winglet Kits. © Copyright 2012 Hawker Beechcraft Corporation. All rights reserved. Hawker and Beechcraft are trademarks of Hawker Beechcraft Corporation. Original Issue: Feb, 2002 Revision A5: Feb, 2012...
  • Page 2 Pilot’s Operating Manual Introduction This Pilot’s Operating Manual is applicable to the Hawker 800XP airplane serials 258541, 258556, 258567 and after equipped with Collins Pro Line 21 avionics and is incomplete without the current FAA Approved Airplane Flight Manual, P/N 140-590032-0005.
  • Page 3 LIST OF EFFECTIVE PAGES Pilot’s Operating Manual P/N 140-590032-0007 Revision A5: Feb, 2012 This List of Effective Pages contains all current pages issued to this manual at Revision A5. It should be used to ensure the manual is complete and up to date. Section &...
  • Page 4 Pilot’s Operating Manual LIST OF EFFECTIVE PAGES (continued) Section & Page Revision & Date Section & Page Revision & Date 1-11 Original Issue: Feb, 2002 2-29 Revision A1: Nov, 2002 1-12 Original Issue: Feb, 2002 2-30 Original Issue: Feb, 2002 1-13 Original Issue: Feb, 2002 2-31...
  • Page 5 Pilot’s Operating Manual LIST OF EFFECTIVE PAGES (continued) Section & Page Revision & Date Section & Page Revision & Date Revision A1: Nov, 2002 6-13 Revision A4: Sep, 2010 Revision A1: Nov, 2002 6-14 Revision A4: Sep, 2010 Revision A1: Nov, 2002 6-15 Revision A4: Sep, 2010 Revision A1: Nov, 2002...
  • Page 6 Pilot’s Operating Manual LIST OF EFFECTIVE PAGES (continued) Section & Page Revision & Date Section & Page Revision & Date 8-12 Original Issue: Feb, 2002 9-23 Revision A4: Sep, 2010 8-13 Revision A2: Nov, 2004 9-24 Revision A4: Sep, 2010 8-14 Revision A2: Nov, 2004 Sub-section 10: Environmental...
  • Page 7 Pilot’s Operating Manual LIST OF EFFECTIVE PAGES (continued) Section & Page Revision & Date Section & Page Revision & Date 11-11 Original Issue: Feb, 2002 13-16 Revision A2: Nov, 2004 11-12 Revision A1: Nov, 2002 13-17 Original Issue: Feb, 2002 11-13 Revision A1: Nov, 2002 13-18...
  • Page 8 Pilot’s Operating Manual LIST OF EFFECTIVE PAGES (continued) Section & Page Revision & Date Section & Page Revision & Date 16-2 Original Issue: Feb, 2002 18-3 Revision A2: Nov, 2004 16-3 Revision A1: Nov, 2002 18-4 Revision A2: Nov, 2004 16-4 Original Issue: Feb, 2002 18-5...
  • Page 9 Pilot’s Operating Manual LIST OF EFFECTIVE PAGES (continued) Section & Page Revision & Date Section & Page Revision & Date 2-16 Revision A1: Nov, 2002 2-48 Revision A1: Nov, 2002 2-17 Original Issue: Feb, 2002 2-49 Revision A1: Nov, 2002 2-18 Original Issue: Feb, 2002 2-50...
  • Page 10 Pilot’s Operating Manual LIST OF EFFECTIVE PAGES (continued) Section & Page Revision & Date Section & Page Revision & Date 2-80 Revision A1: Nov, 2002 2-112 Revision A1: Nov, 2002 2-81 Revision A1: Nov, 2002 2-113 Revision A1: Nov, 2002 2-82 Revision A1: Nov, 2002 2-114...
  • Page 11 Pilot’s Operating Manual LIST OF EFFECTIVE PAGES (continued) Section & Page Revision & Date Section & Page Revision & Date 2-144 Revision A1: Nov, 2002 2-176 Revision A1: Nov, 2002 2-145 Revision A1: Nov, 2002 2-177 Revision A1: Nov, 2002 2-146 Revision A1: Nov, 2002 2-178...
  • Page 12 Pilot’s Operating Manual LIST OF EFFECTIVE PAGES (continued) Section & Page Revision & Date Section & Page Revision & Date Revision A1: Nov, 2002 Original Issue: Feb, 2002 Revision A1: Nov, 2002 Original Issue: Feb, 2002 Revision A1: Nov, 2002 Original Issue: Feb, 2002 Original Issue: Feb, 2002 Revision A1: Nov, 2002...
  • Page 13 Pilot’s Operating Manual LIST OF EFFECTIVE PAGES (continued) Section & Page Revision & Date Section & Page Revision & Date 4-38 Original Issue: Feb, 2002 Revision A4: Sep, 2010 4-39 Original Issue: Feb, 2002 Revision A4: Sep, 2010 4-40 Original Issue: Feb, 2002 Revision A4: Sep, 2010 4-41 Original Issue: Feb, 2002...
  • Page 14 Pilot’s Operating Manual LIST OF EFFECTIVE PAGES (continued) Section & Page Revision & Date Section & Page Revision & Date 6-34 Revision A5: Feb, 2012 8-16 Revision A3: Apr, 2008 6-35 Revision A5: Feb, 2012 8-17 Revision A3: Apr, 2008 6-36 Revision A5: Feb, 2012 8-18...
  • Page 15 Pilot’s Operating Manual LIST OF EFFECTIVE PAGES (continued) Section & Page Revision & Date Section & Page Revision & Date 1-14 Revision A4: Sep, 2010 2-20 Revision A2: Nov, 2004 1-15 Revision A4: Sep, 2010 2-21 Revision A1: Nov, 2002 1-16 Revision A4: Sep, 2010 2-22...
  • Page 16 Pilot’s Operating Manual LIST OF EFFECTIVE PAGES (continued) Section & Page Revision & Date Section & Page Revision & Date 1-10 Revision A4: Sep, 2010 2-21 Revision A2: Nov, 2004 1-11 Revision A4: Sep, 2010 2-22 Revision A2: Nov, 2004 1-12 Revision A4: Sep, 2010 2-23...
  • Page 17 Pilot’s Operating Manual LIST OF EFFECTIVE PAGES (continued) Section & Page Revision & Date Section & Page Revision & Date 2-53 Revision A2: Nov, 2004 Revision A1: Nov, 2002 2-54 Revision A2: Nov, 2004 Revision A1: Nov, 2002 2-55 Revision A2: Nov, 2004 Revision A1: Nov, 2002 2-56 Revision A2: Nov, 2004...
  • Page 18 Pilot’s Operating Manual Intentionally left blank Page 16 of 16 P/N 140-590032-0007 Revision A5: Feb, 2012...
  • Page 19 LOG OF TEMPORARY CHANGES Issue Date: September 22, 2010 Serials 258541, 258556, 258567 and After Pilot’s Operating Manual P/N 140-590032-0007 AIRPLANES EQUIPPED WITH COLLINS PRO LINE 21 AVIONICS Active Temporary Changes must be inserted into this manual. Part Number Subject Date 140-590032-0007TC1 (Incorporated into POM at Revision A2)
  • Page 20 Pilot’s Operating Manual Intentionally left blank Page 2 of 2 P/N 140-590032-0007LOTC September 22, 2010...
  • Page 21 LOG OF REVISIONS Pilot’s Operating Manual P/N 140-590032-0007 Revision A5: Feb, 2012 NOTE: Revision bars in the margin of a revision page indicate the addition, deletion or revision of pertinent or technical data only. Pages replaced in a revision that do not have revision bars are replaced for pagination, formatting or editorial reasons only with no pertinent or technical data changes.
  • Page 22 Intentionally left blank P/N 140-590032-0007A5 Page 2 of 2 Log Of Revisions...
  • Page 23 Pages 1 and 2 Log of Revisions Provided new Log of Revisions for Revision A4. Pages 1 thru 4 Section III - SYSTEMS Revised headers to Hawker Beechcraft format and footers for DESCRIPTION Revision A4. Sub-section 3 - Fuel System...
  • Page 24 SECTION & PAGES DESCRIPTION Sub-section 9 - Electrical Revised headers to Hawker Beechcraft format and footers for Power Revision A4. Pages 9-1 thru 9-24 Page 9-5 Figure 1, removed a green bar connecting the Starter Busbar to the PS2 Busbar.
  • Page 25 SECTION & PAGES DESCRIPTION Section V - FLIGHT Revised headers to Hawker Beechcraft format and footers for HANDLING Revision A4. Sub-section 1 - Normal Handling Pages 1-1 thru 1-26 Pages 1-1 and 1-2 Revised Table of Contents for Revision A4 additions and page shifts.
  • Page 26 SECTION & PAGES DESCRIPTION Sub-section 1 - Ground ENGINE START, revised "Motor" to "motor". Handling (continued) Page 1-12 Page 4 of 4...
  • Page 27 SECTION & PAGES DESCRIPTION Title and Logo Pages Revised Title Page to include Hawker Beechcraft and Hawker Beechcraft Corporation logos. Moved introduction paragraph to Logo Page. Updated footers for Revision A3. Added text and NOTE to Logo Page.
  • Page 28 Hawker 800XP Pro Line 21 Pilot’s Operating Manual LOG OF REVISIONS Airplane Serial Nos. 258541, 258556, 258567 and After Pilot’s Operating Manual P/N 140-590032-0007 Revision A2: November 2004 AIRPLANES EQUIPPED WITH COLLINS PRO LINE 21 AVIONICS SECTION & PAGE DESCRIPTION Pages replaced in this Revision A2 which do not have revision bars are replaced for pagination, formatting and editorial reasons only with no technical changes.
  • Page 29 Hawker 800XP Pro Line 21 Pilot’s Operating Manual SECTION & PAGE (Continued) DESCRIPTION (Continued) Sub-section 2 - ENGINES Page 2-19 Moved Figure 4 title above footer line. (no technical change) Page 2-20 Updated company header (no technical change). Page 2-35 Added anti-icing information.
  • Page 30 Hawker 800XP Pro Line 21 Pilot’s Operating Manual SECTION & PAGE (Continued) DESCRIPTION (Continued) Sub-section 7 - STALL WARNING/IDENTIFICATION Page 7-1 Added Figure 1- Stall Valve Annunciators Updated Figure numbers. Added Figure 4 - Stall System Pitot Static Block Diagram.
  • Page 31 Hawker 800XP Pro Line 21 Pilot’s Operating Manual SECTION & PAGE (Continued) DESCRIPTION (Continued) Pages 7-9 Pagination only (no technical change). Pages 7-10 Added two headers of SYSTEM ANNUNCIATORS and SYSTEM POWER SUPPLIES. Pages 7-11 Re-formatted Figure 6 to a foldout page.
  • Page 32 Hawker 800XP Pro Line 21 Pilot’s Operating Manual SECTION & PAGE (Continued) DESCRIPTION (Continued) Page 10-6 Updated company header (no technical change). Page 10-7 Removed text referencing "dolls eye" indicator. Page 10-8 Updated company header (no technical change). Page 10-17 Moved Figure 2 title above footer line and inserted Key above color provisions.
  • Page 33 Hawker 800XP Pro Line 21 Pilot’s Operating Manual SECTION & PAGE (Continued) DESCRIPTION (Continued) Page 17-10 Edited text for an optional ACP. Moved Figure 5 to Page 17-11. Incorporated Temporary Change TC1, HF Radio Transmissions. Page 17-11 Re-located Audio Control Panel from Page 17-10 and provided an optional installation with Figure 5.
  • Page 34 Hawker 800XP Pro Line 21 Pilot’s Operating Manual SECTION & PAGE (Continued) DESCRIPTION (Continued) Page 2-14 Removed the word "where" from text. Page 2-19 Removed the word "best" from text. Page 2-20 Updated company header (no technical change). Page 2-23 Editorial change only, added period after "if applicable"...
  • Page 35 Hawker 800XP Pro Line 21 Pilot’s Operating Manual SECTION & PAGE (Continued) DESCRIPTION (Continued) Page 1-15 Revised Figure references. Page 1-16 Re-located thrust reverser locking pins illustration. Page 1-17 Updated company header (no technical change). Pages 1-18 Added the word "Mooring" to Procedure.
  • Page 36 Hawker 800XP Pro Line 21 Pilot’s Operating Manual SECTION & PAGE (Continued) DESCRIPTION (Continued) Page 2-15 Added RAC Service Bulletin SB 24-3641 information for Refueling Control and Indication. Added reference of FIgure 8 to Water Draining. Added the word "FOLLOWING" to the CAUTION: Page 2-16 Added Service Bulletin information.
  • Page 37 Hawker 800XP Pro Line 21 Pilot’s Operating Manual SECTION & PAGE (Continued) DESCRIPTION (Continued) Pages 2-47 thru 2-55 Updated company header (no technical change). Page 2-56 Added adapter to equipment listing in Table 7. Changed "diagrams" to read "graphs" in NOTE 1.
  • Page 38 Pages 1 thru 9 Updated for Revision A1. Section I - General Page 3 Changed ’Hawker 800XP’ to read ’Hawker 800XP Pro Line 21’. Indented notes. Page 4 Changed ’Hawker 800XP’ to read ’Hawker 800XP Pro Line 21’. Was ’Co-pilot’, now ’Copilot’.
  • Page 39 SECTION & PAGE (Continued) DESCRIPTION (Continued) Sub-section 2 - Engines Page 2-5 Was ’de-icing’, now ’deicing’. Indent bullets. Pages 2-7, 2-12, 2-13, 2-15, 2-16, 2-18, Indent bullets and notes. For conformity, changed 2-21, 2-22, 2-23, 2-25, 2-26, 2-29, 2-33, temperature callouts, ex: 103° C or 98° F. 2-35, 2-38, 2-40 and 2-41 Page 2-9 Add parenthesis close ’)’...
  • Page 40 SECTION & PAGE (Continued) DESCRIPTION (Continued) Pages 6-3 and 6-17 Changed Co-pilot’s to Copilot’s for conformity in manual. Indent bullets. Pages 6-4, 6-6, 6-7, 6-8, 6-11, 6-13, Reprint for improved graphics. 6-16 and 6-18 Pages 6-5, 6-12, 6-19 and 6-20 Indent bullets and notes.
  • Page 41 SECTION & PAGE (Continued) DESCRIPTION (Continued) Page 9-19 Was ’BUSTIE’, now ’BUS TIE’, to correct annuncia- tor call out. Changed ’No’ to ’No.’ and add a space where needed, to correctly identify as a number. Indent notes. Pages 9-20 and 9-21 Changed XS1, XS2, INV1 and INV2 to XS 1, XS 2, INV 1 and INV 2, to correctly identify annunciators.
  • Page 42 SECTION & PAGE (Continued) DESCRIPTION (Continued) Pages 13-3 and 13-15 Add piece of art for locator. Pages 13-7, 13-11, 13-12, 13-13 and Indent bullets and notes. 13-18 Page 13-14 Changed black and white art to colored art. Sub-section 14 - Equipment and Furnishings Page 14-7 Changed art to show correct annunciator location.
  • Page 43 SECTION & PAGE (Continued) DESCRIPTION (Continued) Page 1-4 Reprint for improved graphics. Page 1-6 Add note. Sub-section 2 - Preflight Pages 2-3, 2-19, 2-20, 2-21, 2-35, 2-36, Indent bullets and notes. 2-97 and 2-159 Pages 2-9, 2-10, 2-11, 2-13, 2-15, 2-16, For conformity, changed temperature callouts, 2-37, 2-38, 2-41 thru 2-44, 2-47 thru ex: 103°...
  • Page 44 SECTION & PAGE (Continued) DESCRIPTION (Continued) Page 4-59 Indent notes. Sub-section 6 - Single Engine Pages 6-1, 6-3, 6-10 thru 6-13 and 6-16 For conformity, changed temperature callouts, thru 6-19 ex: 103° C or 98° F. Indent bullets. Page 6-4 Add period at end of sentence.
  • Page 45 Add EQUIPMENT NECESSARY to TOC. Page 1-2 Additional information caused text shift. Page 1-3 Was ’Hawker 800XP’, Now ’Hawker 800XP Pro Line 21. Was ’PRECATIONS’, Now ’PRECAU- TIONS’. For conformity, changed temperature call- outs, ex: 103° C or 98° F.
  • Page 46 SECTION & PAGE (Continued) DESCRIPTION (Continued) Page 2-51 Add standard US values. For conformity, changed temperature callouts, ex: 103° C or 98° F. Indent notes and bullets. Changed spacing for conformity. Section VII - SAFETY INFORMATION Pages 1 thru 4, 11 thru 16, 19, 21, 25, Align text frame with header and footer.
  • Page 47 LOG OF REVISIONS Serial Nos. 258541, 258556, 258567 and After Pilot’s Operating Manual P/N 140-590032-0007 Original Issue - February 2002 AIRPLANES EQUIPPED WITH COLLINS PRO LINE 21 AVIONICS SECTION & PAGE DESCRIPTION All Sections and Pages Original Issue, Refer to the List Of Effective Pages. Page 1 of 1...
  • Page 48 Pro Line 21 Section - I GENERAL Table of Contents Page MANUAL INTRODUCTION ................3 REVISIONS and TEMPORARY CHANGES ..........3 SUPPLEMENTS ..................3 CONTENTS ....................4 AIRPLANE GENERAL ................... 4 Figure 1 - General Dimensions ..............6 DIMENSIONAL DATA.................. 7 TERMS and DEFINITIONS ................
  • Page 49 Hawker 800XP Pro Line 21 Section I - GENERAL Intentionally left blank Pilot’s Operating Manual Page 2 Original Issue: Feb, 2002...
  • Page 50 REVISIONS and TEMPORARY CHANGES Revisions Revisions are issued periodically and affect all Hawker 800XP Pro Line 21 POM’s. Revisions are issued as replacement pages to the main manual and provide the revision date in the footer of the page with revision bars in the margin of the page indicating additional, deleted or revised technical data.
  • Page 51 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"...
  • Page 52 Hawker 800XP Pro Line 21 Section I - GENERAL Electric heating is provided for the following: • Rudder bias struts • Windshields • Engine intake temperature and pressure sensors: • Pitot heads (a) Pt • Static plates • Auxiliary pitot head (b) Tt •...
  • Page 53 Hawker 800XP Pro Line 21 Section I - GENERAL Figure 1 General Dimensions Pilot’s Operating Manual Page 6 Original Issue: Feb, 2002...
  • Page 54 Hawker 800XP Pro Line 21 Section I - GENERAL DIMENSIONAL DATA Wing Span ..........51 ft 4 1/2 in ......15.66 m Aspect Ratio ........7.06 Gross wing area ....... 374 sq ft ........34.75 sq m Fuselage Overall length (including tail) ..... 51 ft 1.64 in ......15.59 m Cabin Length (including vestibule) ....
  • Page 55 Hawker 800XP Pro Line 21 Section I - GENERAL Minimum Turning Radius Using Nosewheel Steering Inside Wheel ........15 ft 9 in ........ 4.80 m Outside Wingtip ......... 47 ft 2 in ........ 14.38 m Mainwheel Tire size..........23 X 7.00-12, 12 Ply Tubeless Tire pressure ........
  • Page 56 Hawker 800XP Pro Line 21 Section I - GENERAL TERMS and DEFINITIONS The following terms and definitions are used in this POM when describing locations or functions of equipment or systems (see Figure 2). Terms Definitions Pilot The left side of the airplane looking towards the nose.
  • Page 57 Hawker 800XP Pro Line 21 Section I - GENERAL CAPTAIN'S PILOT FIRST OFFICER'S COPILOT (NO. 1) SIDE (NO. 2) SIDE FLIGHT COMPARTMENT OUTWARD OPENING DOOR WITH INTEGRAL STAIRS VESTIBULE AREA PASSENGER CABIN TOILET COMPARTMENT PRESSURE DOME M6365_0 NO. 1 SIDE NO.
  • Page 58 Pro Line 21 Section - II OPERATING LIMITATIONS Table of Contents Page GENERAL ..................... 3 Pilot’s Operating Manual Page 1 Original Issue: Feb, 2002...
  • Page 59 Hawker 800XP Pro Line 21 Section II - OPERATING LIMITATIONS Intentionally left blank Pilot’s Operating Manual Page 2 Original Issue: Feb, 2002...
  • Page 60 Hawker 800XP Pro Line 21 Section II - OPERATING LIMITATIONS GENERAL For operating limitations, refer to the FAA approved Airplane Flight Manual, P/N 140-590032-0005 Section 2 - LIMITATIONS Pilot’s Operating Manual Page 3 Original Issue: Feb, 2002...
  • Page 61 Hawker 800XP Pro Line 21 Section II - OPERATING LIMITATIONS Intentionally left blank Pilot’s Operating Manual Page 4 Original Issue: Feb, 2002...
  • Page 62 Pro Line 21 Section - III SYSTEMS DESCRIPTION Table of Contents Page Sub-section 1 - MASTER WARNING SYSTEM ..........1-1 Sub-section 2 - ENGINES ...................2-1 Sub-section 3 - FUEL SYSTEM ................3-1 Sub-section 4 - FIRE PROTECTION..............4-1 Sub-section 5 - HYDRAULICS ................5-1 Sub-section 6 - FLIGHT CONTROLS..............6-1 Sub-section 7 - STALL WARNING/IDENTIFICATION ........7-1 Sub-section 8 - LANDING GEAR ................8-1...
  • Page 63 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION Intentionally left blank Page 2 Pilot’s Operating Manual Revision A2: Nov, 2004...
  • Page 64 Pro Line 21 Section - III SYSTEMS DESCRIPTION Sub-section 1 MASTER WARNING SYSTEM Table of Contents Page GENERAL .......................1-3 ANNUNCIATOR TYPES .................1-3 MWS ARRANGEMENT ..................1-3 REPEATER ANNUNCIATORS ...............1-3 Figure 1 - Master Warning Annunciations and Controls ......1-4 SYSTEM OPERATION ...................1-5 ACKNOWLEDGEMENT .................1-5 ANNUNCIATION SEQUENCE................1-6 Table 1: Annunciation Sequence .............1-6...
  • Page 65 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION Intentionally left blank Sub-section 1 Page 1-2 Pilot’s Operating Manual MASTER WARNING SYSTEM Original Issue: Feb, 2002...
  • Page 66 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION GENERAL A master warning system (MWS) consisting of annunciation logic, displays and associated controls is provided to alert or advise the crew to the status of the airplane systems. ANNUNCIATOR TYPES...
  • Page 67 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION REFUEL ENG 1 ENG 2 BATT 1 FUEL FUEL CNTCTR AUX FUEL WING FUEL REAR BAY BATT 2 XFD/TFR DOOR CNTCTR FUEL 1 FUEL 2 GEN 1 BUS TIE GEN 2...
  • Page 68 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION SYSTEM OPERATION When a system status change or fault condition occurs, the appropriate annunciator illuminates at maximum intensity. In the event of a red warning, both MWS red master warning lamps will flash and if the red annunciator is located on the overhead roof panel, the associated repeater annunciator illuminates with a steady intensity.
  • Page 69 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION ANNUNCIATION SEQUENCE Table 1: Annunciation Sequence Annunciator state and Annunciator Annunciator intensity level when first Attention Event Location Color illuminated AMBER REPEATER Illuminates steady at maximum intensity Flashes at maximum...
  • Page 70 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION TESTING Pushing the ANNUN test button on the overhead roof panel results in the following: • All of the overhead and MWS panel annunciators, including white, illuminate at maximum intensity.
  • Page 71 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION ANNUNCIATORS WITH ASSOCIATED MWS REPEATERS ELECTRICAL Overhead Roof Panel BATT 1 CNTCTR BATT 2 CNTCTR GEN 2 BUS TIE GEN 1 FAIL FAIL OPEN DC Power Section XS 1 XS 2...
  • Page 72 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION ICE PROTECTION Overhead Roof Panel L SCREEN R SCREEN ALTR 2 ALTR 1 OVHT OVHT FAIL FAIL L VANE R VANE SIDE SCRN DETECTED HTR FAIL HTR FAIL OVHT L PITOT...
  • Page 73 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION FUEL Overhead Roof Panel Overhead Roof Panel AUX FUEL WING FUEL ENG 1 ENG 2 REFUEL XFD/TFR FUEL FUEL FUEL 1 FUEL 2 LO PRESS LO PRESS The illumination of any of the above fuel...
  • Page 74 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION ENGINE FIRE WARNING Overhead Roof Panel Forward Extension ENG 1 ENG 2 FIRE FIRE The illumination of either of the above fire warning annunciators on the Overhead Roof Panel Forward...
  • Page 75 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION MWS ANNUNCIATORS - WITHOUT A REPEATER Table 2: MWS Annunciators - Without a Repeater Red Annunciators Location Amber Annunciators Location M W S panel M W S panel REVERSER (if installed)
  • Page 76 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION Table 2 continued: MWS Annunciators - Without a Repeater Amber or White Red Annunciator Location Location Annunciators ENT DOOR M W S panel UNLOCKED RUDDER M W S panel BIAS...
  • Page 77 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION Intentionally left blank Sub-section 1 Page 1-14 Pilot’s Operating Manual MASTER WARNING SYSTEM Original Issue: Feb, 2002...
  • Page 78 Pro Line 21 Section - III SYSTEMS DESCRIPTION Sub-section 2 ENGINES Table of Contents Page GENERAL.......................2-5 DESCRIPTION....................2-6 Figure 1 - Engine Cutaway View ..............2-6 FAN ......................2-6 COMPRESSOR SECTION ................2-6 Low Pressure Spool N .................2-7 High Pressure Spool N ................2-7 COMBUSTION CHAMBER................2-7 TURBINE SECTION ..................2-7 ACCESSORY DRIVE...................2-7 OPERATION....................2-8...

  • Page 79: Table Of Contents

    Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION Page IGNITION ....................2-22 Ignition Unit ..................2-22 Igniter Plugs and Leads ..............2-22 Ignition Switches ................. 2-22 FUEL CONTROL ..................2-23 Fuel Pump................... 2-23 Anti-ice Valve................... 2-25 Filter Bypass..................2-25 Figure 5 - Engine-Driven Fuel Pump Assembly........
  • Page 80 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION Page THRUST REVERSERS ................2-39 DESCRIPTION...................2-39 CONTROLS and INDICATORS..............2-39 ARM ....................2-39 OFF .....................2-40 UNLCK ....................2-40 REVRS ....................2-40 REVERSER ASSEMBLY and OPERATION..........2-40 Initiate....................2-40 Deploy ....................2-41 Stow ....................2-41 Autostow....................2-42 Automatic Thrust Lever Retard/Autostow System .......2-42 SYSTEM SAFETY ..................2-42...
  • Page 81 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION Intentionally left blank Sub-section 2 Page 2-4 Pilot’s Operating Manual Original Issue: Feb, 2002 ENGINES...
  • Page 82 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.
  • Page 83 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION DESCRIPTION The engine is a two-spool-transonic-stage-compressor, front fan jet engine. It is a light weight modular design for ease of maintenance. The simplicity of the design eliminates the need for variable geometry inlet guide vanes.
  • Page 84 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION Low Pressure Spool N The LP N spool consists of a four stage, low pressure, axial flow compressor and a three stage, low pressure turbine. Both the compressor and the turbines are mounted on a common shaft.
  • Page 85 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION OPERATION When the engine is operating, the single-stage fan draws air through the nacelle inlet duct. The outer diameter of the fan accelerates a moderately large air mass at a low velocity into the full-length bypass duct.
  • Page 86 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION ENGINE INDICATING SYSTEM (EIS) The EIS provides full time displays of engine Fan RPM N , ITT and a part time, pop-up or pilot-selectable display of engine RPM N , fuel flow, oil pressure and oil temperature on the left MFD.
  • Page 87 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION RPM DISPLAYS The N indication provides engine RPM measured against a fixed 100% value and shares the same scale with the ITT indication. Normal scale range for the N portion of the scale is 20 to 100% with an overlimit scale to 110%. Gray tick marks are at 20, 40, 60, 80 and 110%.
  • Page 88 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION REFERENCE DISPLAYS The N reference consists of a single digital N REF read-out and individual N REF bugs on each N scale. N REF may be set manually by the pilot using the REFS menu or it may be provided by the FMS.
  • Page 89 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION The triangular N REF bug is positioned on the perimeter of each N scale with the apex of the triangle at the point that corresponds with the N REF digital read-out. The bug is the same color as the digital read-out and is removed when the read-out does not appear.
  • Page 90 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION OPERATING NORMAL LIMIT REDLINE LIMIT CONDITION (Green) (Red) ITT ≤ 978 ° C ITT ≥ 980 ° C START ITT ≤ 968 ° C ITT ≥ 970 ° C ITT ≤ 978 ° C ITT ≥...
  • Page 91 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION FUEL FLOW DISPLAYS Fuel flow appears below the N display in the top right corner of the MFD. The fuel flow display consists of digital read-outs for each engine and a FF legend. The gray FF legend separates the left and right digital read-outs.
  • Page 92 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION OIL TEMPERATURE DISPLAYS Oil temperature for each engine appears below oil pressure for each engine in the top right corner of the MFD. The oil temperature display is a digital read-out for each engine with a gray TEMP legend, placed below the gray OIL legend.
  • Page 93 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION ENGINE SYSTEMS and COMPONENTS • ENGINE OIL • IGNITION • FUEL CONTROL • POWER CONTROLS ENGINE OIL (Figure 3) Oil under pressure lubricates the engine bearings and the transfer, accessory and planetary gearboxes.
  • Page 94 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION VENT No 4 and 5 No 6 BEARINGS BEARING BREATHER PRESSURIZING VALVE TRANSFER GEARBOX ACCESSORY GEARBOX ANTI-SYPHON ORIFICE PLANETARY GEARS Nos 1, 2 and 3 BEARINGS OIL TANK TEMPERATURE CONTROL & BYPASS...
  • Page 95 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION Oil Filter A filter is provided to remove impurities from the oil. The oil filter consists of a disposable element enclosed in a metal housing on the right side of the accessory drive gearbox.
  • Page 96 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION ALTERNATOR COOLING AIR EXHAUST Outboard View of No. 2 Engine Outboard View of No. 1 Engine ALTERNATOR COOLING AIR EXHAUST Inboard View of No. 1 Engine Inboard View of No. 2 Engine...
  • Page 97 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION Intentionally left blank Sub-section 2 Page 2-20 Pilot’s Operating Manual Revision A2: Nov, 2004 ENGINES...
  • Page 98 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION Fuel/Oil Cooler The fuel/oil cooler (oil temperature regulator) uses airplane fuel to maintain the oil at a constant temperature and consists of a temperature control valve and a heat exchanger. Fuel constantly flows through the unit and oil only flows through the unit if it is above a set temperature.

  • Page 99: Ignition

    Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION IGNITION Each engine has an independent ignition system that consists of: • Ignition Unit • Igniter Plugs and Leads • ENG IGNITION Switches • IGN ON Annunciators Ignition Unit An ignition unit on the upper left side of the fan bypass housing is a high voltage, capacitor discharge, radio noise-suppressed, intermittent sparking type unit that uses a 10 to 30 VDC power supply.

  • Page 100: Fuel Control

    Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION FUEL CONTROL The engine fuel control system consists of: • Fuel Pump Assembly (Figure 5) • Hydro-mechanical Fuel Control Unit (FCU) • Digital Electronic Engine Control (DEEC) • Fuel Flow Divider Assembly •...

  • Page 101: Fuel Control Unit

    Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION FUEL CONTROL LEGEND UNIT PUMP SUPPLY DISCHARGE LOW-PRESSURE FUEL FEED PUMP HYDRO- HIGH-PRESSURE MECHANICAL COLLECTOR PUMP FUEL TANK METERING UNIT ENG 1 ENG 2 ENG 1 and/or FUEL FUEL FUEL ∆...

  • Page 102: Inlet Pressure And Temperature Sensor

    Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION Filter Clogged If the filter begins to clog, the following events will occur: ∆ • At 6 to 8 psi p the amber annunciator will illuminate on the MWS. ∆...

  • Page 103: Digital Electronic Engine Control (Fuel Computer)

    Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION Digital Electronic Engine Control (Fuel Computer) Two Digital Electronic Engine Controls (DEECs) are located in the rear equipment bay. Each DEEC controls the engine acceleration and deceleration. Separate ENG CMPTR switches on the flight compartment overhead roof panel allow automatic (AUTO) or overspeed protection (OVSPD PROT) mode selection.
  • Page 104 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION The DEEC MANUAL/NORMAL switch must be in the NORMAL position and the ENG CMPTR switch must be in the AUTO position for the system to function. If the electronic engine control malfunctions, the FCU on the engine automatically switches to the manual mode and the respective ENG CMPTER annunciator will illuminate.

  • Page 105: Surge Bleed Valve

    Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION Surge Bleed Valve Under certain conditions, gas turbine engines tend to surge and stall. For each compressor RPM, there is a relationship between the amount of air flow and the pressure gradient; a disturbance results in the engine surging.

  • Page 106: Fuel Flow Indicating

    Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION Fuel Flow Indicating Each engine fuel flow indicating system consists of: • Fuel Flow Transmitter • Data Concentrator Unit (DCU) • Flow Rate Indication The transmitter is a turbine-driven motor that rotates and generates an AC electrical signal as fuel flows past it.

  • Page 107: Power Controls

    Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION POWER CONTROLS Engine Thrust Levers Each thrust lever on the center control pedestal mechanically connects through cables and a teleflex control to a fuel control unit. Movement of the thrust lever directly drives the fuel control unit from idle to full power.
  • Page 108 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION STOP BOLTS COCK (FULL) (IDLE) LEVER MICROSWITCH THROTTLE LEVER TO COCK LEVER LINKAGE based on V2079 Figure 7 Fuel Controls Sub-section 2 Pilot’s Operating Manual Page 2-31 ENGINES Revision A1: Nov, 2002...

  • Page 109: Engine Synchronizer

    Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION Engine Synchronizer The engine synchronizer provides synchronization of the engines. Using the three position ENG SYNC switch, synchronization of either the low pressure fan N or the high pressure turbine N speeds can be selected in the cockpit.

  • Page 110: Bleed Air And Ventilation

    Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION BLEED AIR and VENTILATION Air is bled from two stages of the engine compressor to provide supplies for: • Nacelle Inlet Cowl Anti-icing • Airplane Services Ram air is used to ventilate the area of the cowling surrounding the engine compressor stages between the front and rear firewalls.
  • Page 111 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION PE BUSBAR MWS DIM BUS ICE PROT SELECTED ENG ANTICE TO ENGINE DIGITAL COMPUTER IDLE 2 SEC SCHEDULE DELAY TO Pt and Tt HEATING CIRCUITS ENG 1 A/ICE PRESSURE 6 PSI...

  • Page 112: Power Supplies

    Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION The ENG ANTICE switches for the engine intake ice protection system may be selected ON at any engine speed including the use of maximum take-off thrust for takeoff and go-around.

  • Page 113: Airplane Services

    Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION AIRPLANE SERVICES Each engine has two bleed ports used for the airplane services • One low pressure (LP) bleed port on the inboard side of each engine takes bleed air aft of the last stage of the axial compressor.
  • Page 114 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION PE 2 BUS DIM BUS OVRD SWITCH SWITCH INDICATION INDICATION RELAY 2 RELAY 1 ARMED AUTO SYNCHRONIZER SWITCH DISARMED ENGINE RPM OVRD ARMED APR/SYNCHRONIZER CONTROLLER FUEL FUEL COMPUTER COMPUTER ENGINE 1...

  • Page 115: Operation

    Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION OPERATION In both automatic and manual modes the engine fuel computers limit maximum takeoff power to the APR rating although under normal conditions, the APR control unit electrically trims down the settings to the lower normal ratings.

  • Page 116: Thrust Reversers

    Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION THRUST REVERSERS DESCRIPTION The thrust reverser assembly consists of clamshell type doors which, when stowed, form the final section of the engine exhaust nozzle. The reverser doors are held in the stowed positions by a latching system until released by the sequenced actuation of a series of switches and relays.

  • Page 117: Off

    Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION Power to the thrust reverser system is OFF and indicated by the illumination of this white annunciator. UNLCK An amber annunciator which illuminates if one or more thrust reverser door latches are not locked and when the doors are moving or deployed.

  • Page 118: Deploy

    Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION Deploy Initially the stow and latch isolation solenoids are simultaneously energized, which directs pressure to the stow side of the primary actuators, the latch actuators and the thrust lever retard actuator.

  • Page 119: Autostow

    Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION Autostow The stow sequence (autostow) will always be activated when at least one pair of door latches on the same side of the reverser is not locked and a valid deploy signal is not present, irrespective of the position of the POWER switch.

  • Page 120: Deploy

    Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION PRESSURE SWITCH T/R ACCUMULATOR LATCH ISOLATION HYDRAULIC PRESSURE STOW LINE FROM CONTROL AIRPLANE (SELECTOR) TO OPPOSITE SYSTEM THERMAL PRESSURE VALVE T/R SYSTEM RELIEF RELEASE VALVE VALVE HYDRAULIC RETURN LINE TO AIRPLANE...
  • Page 121 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION Intentionally left blank Page 2-44 Sub-section 2 Pilot’s Operating Manual Original Issue: Feb, 2002 ENGINES...
  • Page 122 Pilot’s Operating Manual Section III SYSTEMS DESCRIPTION Sub-section 3 FUEL SYSTEM Table of Contents Page GENERAL.......................3-3 WING TANKS ....................3-3 Figure 1 - Wing Tank Crossfeed and Transfer..........3-4 FUEL TANK VENTING ................3-4 DRAIN VALVES ...................3-4 REFUEL/DEFUEL FILLER POINTS ............3-4 Figure 2 - Fuel Feed System ..............3-5 Figure 3 - Refuel/Defuel System .............3-6 Gravity Filler ..................3-7 Pressure Refueling................3-7...
  • Page 123 Pilot’s Operating Manual Intentionally left blank Section III Sub-section 3 Page 3-2 P/N 140-590032-0007 FUEL SYSTEM Revision A4: Sep, 2010...
  • Page 124 Pilot’s Operating Manual GENERAL The fuel storage system consists of three fuel tanks: • Two integral fuel tanks, one in each wing • A ventral fuel tank under the lower aft fuselage (if installed) The system has both a wing tank to wing tank transfer capability, and a crossfeed capability from either wing tank to one or both of the engines.
  • Page 125 Pilot’s Operating Manual Figure 1 Wing Tank Crossfeed and Transfer FUEL TANK VENTING Each fuel tank is vented to the atmosphere through the vent surge tank in the wing tip. Each vent tank incorporates a NACA intake that pressurizes the vent system. Fuel that spills into the vent surge tank syphons back into the wing tanks as the tank level falls.
  • Page 126 Pilot’s Operating Manual During operation of the wing transfer valve (1) WING FUEL the WING FUEL XFD TFR annunciator will Valves XFD TFR Pipe lines illuminate on the overhead roof panel. 1. WING TRANSFER FEED FROM WING 2. No 1 LOW PRESSURE WING TRANSFER 3.
  • Page 127 Pilot’s Operating Manual Figure 3 Refuel/Defuel System Page 3-6 Section III Sub-section 3 P/N 140-590032-0007 Revision A4: Sep, 2010 FUEL SYSTEM...
  • Page 128 Pilot’s Operating Manual Gravity Filler A flush mounted fuel filler assembly is located on the upper surface of each wing near the outboard leading edge. The assembly includes a wing skin adaptor, flap valve, lockable cap and a lanyard that attaches the cap to the wing.
  • Page 129 Copilot Instrument Panel Pilot Instrument Panel PILOT'S CENTER Center Instrument INSTRUMENT PANEL HAWKER 800XP Panel INSTRUMENT PANEL FUEL 2000 FUEL 2000...
  • Page 130 Pilot’s Operating Manual ENGINE FUEL FEED SYSTEM FUEL PUMPS Two electrically operated fuel pumps, one per wing tank, located in the fuel reservoir (compartment No. 1), supply fuel to their respective engines and also provide motive flow fuel to its associated jet pumps.
  • Page 131 Pilot’s Operating Manual FUEL PRESSURE SWITCH A pressure switch in each fuel line, upstream of the engine driven pumps, monitors fuel pressure. The pressure switch illuminates the FUEL 1 LO PRESS or FUEL 2 LO PRESS annunciators on the overhead roof when the pressure drops below 6.5 (± .5) psi and extinguishes the annunciators when the fuel pressure increases.
  • Page 132 Pilot’s Operating Manual AUXILIARY TANK TRANSFER The AUX FUEL TRANSFER lever is located on the center control pedestal and mechanically actuates the ventral tank transfer valve. Moving the lever to the down position opens the transfer valve and the white AUX FUEL TFR annunciator on the overhead roof panel will illuminate. AUX FUEL With both fuel pumps operating, fuel transfers from the ventral tank to both wing tanks with jet pump operation in approximately 10 minutes.
  • Page 133 A flow transmitter on each engine sends a signal through the Engine Indicating System and displays the fuel flow figures on the Pilot’s MFD. Copilot Instrument Panel Pilot Instrument Panel PILOT'S CENTER Center Instrument INSTRUMENT PANEL Panel HAWKER 800XP INSTRUMENT PANEL 84.7 84.7 FUEL 2000 2000 QTY LBS...
  • Page 134 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION Section - III SYSTEMS DESCRIPTION Sub-section 4 FIRE PROTECTION Table of Contents Page GENERAL ......................4-3 Figure 1 - Engine Fire Detection and Warning System Component Locations.............4-3 CONTROLS and INDICATIONS..............4-4 ENGINE FIRE DETECTION SYSTEM ............4-4 OVERHEAT....................4-4...
  • Page 135 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION Intentionally left blank Sub-section 4 Page 4-2 Pilot’s Operating Manual FIRE PROTECTION Original Issue: Feb, 2002...
  • Page 136 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION GENERAL Each engine is divided into two zones for fire detection purposes. Each zone is equipped with a fire or overheat detection element connected to a responder. When a fire or overheat is detected in a zone, an audible and visual warning is initiated.
  • Page 137 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION CONTROLS and INDICATIONS Overhead Roof Panel Fire Warning Test Switches FIRE FIRE ENG 1 EXT ENG 2 EXT ENG 1 ENG 2 FIRE FIRE BELL CANCEL BELL BELL CNCLD CNCLD...
  • Page 138 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION FIRE The hydrogen-filled core in the sensor releases large quantities of gas whenever a small section of the tube is heated to a pre-set temperature, by flame or a local hot spot. The hydrogen gas triggers the alarm switch in the responder.
  • Page 139 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION ENGINE FIRE EXTINGUISHING SYSTEM Engine fire extinguishant is supplied from two dual-head, single-shot extinguisher bottles located in the rear equipment bay. The extinguishant is distributed from the bottles by tubing connected to twin high- rate discharge nozzles mounted one on each engine pylon wall and located to discharge into the associated engine bay.
  • Page 140 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION FIRE ENG 1 EXT ENG 2 EXT ENG 1 ENG 2 FIRE FIRE BELL CANCEL BELL BELL CNCLD CNCLD EXT 2 EXT 1 FIRED FIRED ENGINE 1 - SHOT 2...
  • Page 141 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION BCF PORTABLE FIRE EXTINGUISHER A single portable hand-operated extinguisher, stowed on the flight compartment left bulkhead, provides BCF extinguishant for fighting fires in the interior of the fuselage. A second BCF extinguisher is located in the passenger cabin in a location determined by the cabin layout.
  • Page 142 Pro Line 21 Section - III SYSTEMS DESCRIPTION Sub-section 5 HYDRAULICS Table of Contents Page GENERAL.......................5-3 MAIN HYDRAULIC SYSTEM...............5-3 AUXILIARY HYDRAULIC SYSTEM.............5-3 MAIN SYSTEM ....................5-4 FLUID STORAGE ..................5-4 POWER GENERATION................5-5 High Pressure Relief ................5-5 Low Pressure Indication ................5-5 Hand Pump ...................5-5 MAINTAINED PRESSURE PATHS .............5-5 Thrust Reversers...................5-5 Wheel Brakes Emergency Path ............5-6...
  • Page 143 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION Intentionally left blank Sub-section 5 Page 5-2 Pilot’s Operating Manual HYDRAULICS Original Issue: Feb, 2002...
  • Page 144 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION GENERAL Hydraulic power is provided by independent Main and Auxiliary systems for operation of the following services: MAIN HYDRAULIC SYSTEM • Normal extension and retraction of the landing gear • Normal and emergency operation of the wheel brakes •...
  • Page 145 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION MAIN SYSTEM Table 1: Indicators and Annunciators Item Location Parameter Combined BRAKES (2) Center instrument panel Brakes: 2000 and SUPPLY indicator Supply: 3000 Hydraulic fluid overheat warning 90 ° C...
  • Page 146 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION POWER GENERATION Fluid is supplied from the reservoir through a suction filter to the two variable-delivery engine driven pumps, one per engine. An on/off valve in each suction line is interconnected to the related HP cock lever. Isolation of the hydraulic fluid supply is therefore simultaneous with engine shut-down.
  • Page 147 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION Wheel Brakes Emergency Path Main system pressure is distributed through a check valve to the emergency brake accumulator and the emergency brake reducing valve. Should the main system pressure fail, the check valve retains the pressure stored in the emergency brakes accumulator.
  • Page 148 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION ISOLATION VALVE STALL IDENT UNIT ISOLATION VALVE AIR BRAKE ACTUATOR AIR BRAKE ACTUATOR Figure 1 Main Hydraulic System Components Pilot’s Operating Manual Sub-section 5 Page 5-7 Revision A2: Nov, 2004...
  • Page 149 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION KEY TO FIGURE 2 Pipeline Colors Component Identification Air ........1. Capacitor Suction ......2. Pressure switch and snubber Pressure ......3. Full flow relief valves Return ....... 4. Ground servicing hand pump Emergency Brakes ....
  • Page 150 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION No. 1 ENGINE PRESSURE PRESSURE No. 2 ENGINE GAUGE BLEED AIR REDUCING BLEED AIR VALVE MAIN RESERVOIR GROUND AIR SUCTION CONNECTION FILTER HYD OVHT No. 1 HP TEMP No. 2 HP...
  • Page 151 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION AUXILIARY SYSTEM The auxiliary hydraulic system provides an alternative source of hydraulic power for landing gear lowering and flaps operation. The system is hand-operated, and when selected, is independent of the main system.
  • Page 152 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION MWS PANEL LANDING AUX HYD GEAR LO LEVEL SELECTOR ON/OFF VALVE LEVEL DUMP INDICATOR VALVE RESERVOIR FILTER FLAP CONTROL UNIT MAIN SYSTEM SHUTTLE VALVE NOSE GEAR ACTUATOR AUXILIARY SYSTEM SHUTTLE...
  • Page 153 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION CONTROLS and INDICATIONS CONTROL LOCATION Left side of center instrument panel, AUX HYD SYSTEM PULL selector handle adjacent to FMS No. 1 display EMERG HYD PUMP operating handle socket Pilot’s floorboard, adjacent to the center pedestal...
  • Page 154 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION Manual operation of the hand pump draws fluid from the auxiliary reservoir. The fluid is delivered via the check valve and the shuttle valves to the down side of the main and nose gear jacks. Fluid from the check valve is also delivered to the flap control unit.
  • Page 155 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION RESETTING THE MAIN SYSTEM Following use of the auxiliary system, the main system must be reset before normal operation of the landing gear. NOTES: 1. With the main system pressurized normally, the setting of the AUX HYD SYSTEM PULL control lever has no effect on flaps operation.
  • Page 156 Pilot’s Operating Manual Section III SYSTEMS DESCRIPTION Sub-section 6 FLIGHT CONTROLS Table of Contents Page GENERAL ...................... 6-3 PRIMARY CONTROLS .................. 6-3 AILERON CONTROL SYSTEM..............6-3 Figure 1 - Aileron Control System ............6-4 Aileron Trim Tabs.................. 6-5 Aileron Out-Of-Trim Warning ..............6-5 RUDDER CONTROL SYSTEM ..............
  • Page 157 Pilot’s Operating Manual Intentionally left blank Section III Sub-section 6 Page 6-2 P/N 140-590032-0007 FLIGHT CONTROLS Revision A4: Sep, 2010...
  • Page 158 Pilot’s Operating Manual GENERAL The aileron, elevator and rudder are primary controls operated manually by cable-activated circuits from dual ram’s-horn type control columns and adjustable rudder pedals. Trim tabs are installed on the rudder, elevator and left aileron. The elevator trim tab may also be operated by a servo motor which is controlled by the pilot using the electric trim switches or by the autopilot and mach trim system.
  • Page 159 Pilot’s Operating Manual Figure 1 Aileron Control System Section III Sub-section 6 Page 6-4 P/N 140-590032-0007 FLIGHT CONTROLS Revision A4: Sep, 2010...
  • Page 160 Pilot’s Operating Manual Aileron Trim Tabs Each aileron has a servo-action geared tab mounted on its trailing edge. The tab is connected to the aileron by twin connecting rods, and moves in the opposite sense to the aileron to lighten the aerodynamic loads on the pilot’s handwheel.
  • Page 161 Pilot’s Operating Manual RUDDER CONTROL SYSTEM (Figure 2) The rudder is hinged from the rear of the vertical stabilizer and extends upwards from the rear cone of the fuselage to just below the under-surface of the horizontal stabilizer. Movement of the rudder pedals is transmitted by connecting rods and a bell crank to a pulley drum under the flight compartment floor.
  • Page 162 Pilot’s Operating Manual Rudder Trim Tabs (Figure 3) Two separate tabs are hinged at the trailing edge of the rudder. The upper tab is linked to the rudder by a connecting rod, the lower tab is linked by rods to a screw trim actuator unit. Figure 3 Rudder Trim System Section III Sub-section 6...
  • Page 163 Pilot’s Operating Manual Both tabs provide an anti-servo action while the position of the lower tab may be controlled manually by the rudder trim handwheel mounted on the center control pedestal, immediately above the aileron trim handwheel. RUDDER TRIM Center Control Pedestal Top View Rudder Trim Handwheel Top View...
  • Page 164 Pilot’s Operating Manual Fuel Temp Switch PUSH Upper Left Area A RUDDER BIAS B Center Control Pedestal RUDDER BIAS MWS Panel Annunciator (Switches shown with guard open) Electric Heating An electric heater muff on each strut makes sure ice will not prevent operation of the strut or solenoid valve.
  • Page 165 Pilot’s Operating Manual Figure 4 Rudder Bias System Section III Sub-section 6 Page 6-10 P/N 140-590032-0007 FLIGHT CONTROLS Revision A4: Sep, 2010...
  • Page 166 Pilot’s Operating Manual ELEVATOR CONTROL SYSTEM (Figure 5) The elevator control surfaces are hinged from the rear of the horizontal stabilizer and each is installed with a mass balance weight to prevent flutter and a horn balance to reduce the aerodynamic loads felt by the pilot.
  • Page 167 Pilot’s Operating Manual Elevator Trim System (Figure 6) A trim tab is installed on each elevator and is manually controlled from an elevator trim handwheel, located on the left side of the central control pedestal. Operation of the elevator moves the trim tab to give servo action. The autopilot servo motor is used to provide pitch trim, mach trim and electric trim functions.
  • Page 168 Pilot’s Operating Manual Figure 6 Elevator Trim System Section III Sub-section 6 P/N 140-590032-0007 Page 6-13 FLIGHT CONTROLS Revision A4: Sep, 2010...
  • Page 169 Pilot’s Operating Manual Mach Trim The Mach trim system is incorporated into the Integrated Avionics Processor System (IAPS) and uses the same pitch trim servomotor as the manual electric trim and the auto electric trim systems. The Mach trim system receives Mach number data from the air data computers and computes trim tab deflection to increase longitudinal stability at Mach numbers above 0.75 Mach when the autopilot is not engaged.
  • Page 170 Pilot’s Operating Manual SECONDARY CONTROLS FLAP SYSTEM Interconnected slotted flaps are hydraulically powered from a single flap control unit and transmission shafting. The flap control unit is normally supplied from the main hydraulic system but an independent fluid supply from the auxiliary hydraulic system is available in the event of a main system failure. Flap Control System (Figure 7) The flap selector lever is connected by a cable to an input lever on the flap control unit.
  • Page 171 Pilot’s Operating Manual Figure 7 Flap Control System Section III Sub-section 6 Page 6-16 P/N 140-590032-0007 FLIGHT CONTROLS Revision A4: Sep, 2010...
  • Page 172 Flap position is displayed on the Copilot’s Multifunction Display (MFD). This indication also provides the lift dump position. Co-pilot’s Instrument Panel Pilot’s Instrument Panel Pilot Instrument Panel Copilot Instrument Panel PILOT'S CENTER Center Instrument Center Instrument INSTRUMENT PANEL HAWKER 800XP Panel Panel INSTRUMENT PANEL FUEL 2000 2000 QTY LBS FLAPS VENTRAL...
  • Page 173 Pilot’s Operating Manual A baulk, at the 15° slot, prevents inadvertent selection of the up, approach or landing positions. The baulk is released by pushing the selector lever into the 15° slot in the gate. Additional movement of the flaps downwards from the landing position to a lift dump position, is controlled by the airbrake selector lever.
  • Page 174 Pilot’s Operating Manual Figure 8 Airbrake Control System A system of cables run from the AIRBRAKE selector lever to a hydraulic selector valve mounted on each airbrake actuator. Main hydraulic system pressure is utilized to operate the airbrakes through a hydraulic actuator in each wing.
  • Page 175 Pilot’s Operating Manual Lift Dump The AIRBRAKE selector is interconnected with the input lever to the flap control unit. Selection of airbrake between the SHUT and OPEN positions does not affect the flap position. During the landing run, and the flaps selected to the 45° (Land) position, lifting the AIRBRAKE selector and then moving it rearwards into the DUMP position automatically lowers the flaps from the 45°...
  • Page 176 Pro Line 21 Section - III SYSTEMS DESCRIPTION Sub-section 7 STALL WARNING/IDENTIFICATION Table of Contents Page GENERAL ..................... 7-3 SYSTEM LOGIC..................7-3 CONTROLS and ANNUNCIATIONS ............7-3 OPERATION ....................7-4 STALL WARNING SYSTEM............... 7-4 STALL IDENTIFICATION SYSTEM ............7-4 Figure 1 - Stall Valve Annunciators ............7-4 Figure 2 - Variation of Stall Identification Angle With Rate of Increase of Vane Angle ..........
  • Page 177 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION Intentionally left blank Sub-section 7 Page 7-2 Pilot’s Operating Manual STALL WARNING/IDENTIFICATION Revision A2: Nov, 2004...
  • Page 178 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION GENERAL NOTE: This section applies to 800XP Pro Line 21 airplanes prior to Serial No. 258675. For airplanes Serial Nos. 258675 and subsequent, refer to Section VIII SUPPLEMENTS for Supplement P/N 140-590032-0041.
  • Page 179 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION OPERATION STALL WARNING SYSTEM The stall warning system uses an electrically driven stick shaker on each control column to provide a physical warning of an approaching stall to the pilots.
  • Page 180 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION FLAP 0° IDENT FLAP > 0° IDENT FLAP 0° WARN FLAP 15/25° WARN FLAP 45° WARN VANE RATE - DEGREES/SECOND NOTE: HFD is the Horizontal Fuselage Datum. Figure 2 Variation of Stall Identification Angle with Rate of Increase of Vane Angle Sub-section 7 Pilot’s Operating Manual...
  • Page 181 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION THIRD STALL IDENTIFICATION CHANNEL A third channel for stall identification is provided by a pitot/static system which uses pitot pressure (P2) from the right pitot head, static pressure (S6) from the forward static vents and a vent pressure (V) from left and right stall vents.
  • Page 182 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION Right Forward Static Vent Plate Left Forward Static Vent Plate Stall Ident (Autopilot Disconnected) Right Pitot Stall Head Detector Pitot Isolation Valve Stall Detector Stall Ident 3rd Channel Right Left...
  • Page 183 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION SYSTEM FAULTS and ANNUNCIATIONS The duplication of the stall warning system makes sure a single passive fault cannot prevent a stick shake occurring. Should an active fault develop, the faulty system can be isolated via the appropriate circuit breaker.
  • Page 184 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION FLAP ASYMMETRY If asymmetry between the left and right flap positions exists for more than 2 seconds, then the FLAP annunciator (Pilot’s group only) will illuminate. WEIGHT-ON-WHEELS ASYMMETRY If asymmetry between the positions of the left and right weight-on-wheels relays exists for more than 4 seconds, then a SQUAT annunciator (Copilot’s group only) will illuminate.
  • Page 185 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION SYSTEM ANNUNCIATORS Table 1: Summary of Annunciators Function Annunciator MWS Panel Airflow angle sensor left or VANE HTR FAIL # VANE right vane heating L (R) HTR FAIL PROT malfunction...
  • Page 186 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION STALL WARNING and IDENTIFICATION LOGIC (Figure 6) START ANGLE OF ATTACK CONTINUES TO INCREASE ANGLE OF ATTACK MONITORED BY AIRFLOW ANGLE SENSOR STALL WARNING TRIGGER POINT & STALL IDENTIFICATION TRIGGER...
  • Page 187 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION Intentionally left blank Pilot’s Operating Manual Page 7-12 Sub-section 7 Revision A2: Nov, 2004 STALL WARNING/IDENTIFICATION...
  • Page 188 Pro Line 21 Section - III SYSTEMS DESCRIPTION Sub-section 8 LANDING GEAR Table of Contents Page GENERAL ...................... 8-3 CONTROLS - ANNUNCIATORS - INDICATORS.......... 8-3 GEAR POSITIONS ..................8-3 Gear Locked Down ................8-3 Gear Unlocked ..................8-3 Gear Locked Up..................8-3 STANDBY INDICATIONS................
  • Page 189 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION Page Figure 8 - Combined Hydraulic Pressure Indicator and Emergency Wheel Brake Annunciators........ 8-17 Emergency System Operation with Main System Pressure Exhausted ............. 8-17 POWER SUPPLIES .................. 8-18 NOSE WHEEL STEERING................8-18 OPERATION .....................
  • Page 190 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION GENERAL The airplane has a hydraulically-powered retractable landing gear incorporating nitrogen charged shock absorber struts and nose wheel steering. Each main gear has two wheels and retracts inboard into wheel wells in the fuselage. Each main wheel well has a fairing attached to the landing gear and a hydraulically-operated door.
  • Page 191 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION STANDBY INDICATIONS Main Gear Standby main gear downlock indication is provided by an independent circuit connected to green L GEAR and R GEAR annunciators located on the right side console.
  • Page 192 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION WARNING HORN A warning horn sounds if the gear is not locked down when the flaps are extended beyond the 15 ° position. In this instance, the warning horn cannot be cancelled.
  • Page 193 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION LANDING GEAR SELECTOR and BAULK OVERRIDE A LANDING GEAR selector lever is provided to control the normal raising and lowering of the landing gear. The lever operates in a two-gated slot in the center instrument panel and is connected to a hydraulic selector valve located in the nose gear bay.
  • Page 194 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION RETRACTION and EXTENSION (Figure 2) With the weight of the airplane off the wheels, selecting LANDING GEAR up allows main hydraulic system pressure into the gear up pipelines. This pressure operates hydraulic jacks, one on each main gear, and one on the nose gear.
  • Page 195 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION TO RETURN MAIN SYSTEM PRESSURE DIAGRAM SHOWS: LANDING GEAR SELECTED ‘UP’ FILTER GEAR ‘UP’ PIPELINES PRESSURIZED RESTRICTOR AND LANDING GEAR ‘DOWN’ PIPELINES IN-LINE FILTERS GEAR VENTED TO RETURN SELECTOR DOOR ACTUATORS RETRACTED...
  • Page 196 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION MAIN GEAR (Figure 3) Each main oleo-pneumatic leg retracts inwards into a wheel well in the wing. The well is covered with the gear up by a fairing hinged to the wing, and linked to the gear. Additional fairing is provided by a wheel well door, hydraulically-actuated to shut when the gear locks up.
  • Page 197 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION HYDRAULIC RETRACTION ACTUATOR DOOR ACTUATOR Figure 3 Main Landing Gear Sub-section 8 Page 8-10 Pilot’s Operating Manual LANDING GEAR Revision A2: Nov, 2004...
  • Page 198 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION HYDRAULIC RETRACTION ACTUATOR STEERING DISCONNECT PIN (REMOVED WHEN TOWING AIRPLANE) STEERING ACTUATOR Figure 4 Nose Landing Gear Sub-section 8 Pilot’s Operating Manual Page 8-11 LANDING GEAR Original Issue: Feb, 2002...
  • Page 199 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION Figure 5 Nose Gear Doors Release Strut POWER SUPPLIES DC power distribution is as follows: PE Busbar Normal landing gear position annunciators (6) Warning horn control and warning horn PS1 Busbar...
  • Page 200 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION AUXILIARY HYDRAULIC SYSTEM (Figure 6) The auxiliary hydraulic system is selected by pulling the AUX HYD SYSTEM handle. This action dumps any pressure in the normal landing gear system lines to the reservoir and isolates the auxiliary system from the main system return line.
  • Page 201 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION MWS PANEL AUX HYD LO LEVEL LANDING GEAR SELECTOR ON/OFF VALVE LEVEL DUMP INDICATOR VALVE RESERVOIR FILTER FLAP CONTROL UNIT MAIN SYSTEM SHUTTLE VALVE NOSE GEAR ACTUATOR SHUTTLE VALVES MAIN...
  • Page 202 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION WHEELS and BRAKES LOCATION of CONTROLS and INDICATORS Item Location WHEEL BRAKE lever (Figure 7) Right side of center control pedestal BRAKES (2) and SUPPLY combined hydraulic pressure Center instrument panel below the...
  • Page 203 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION Further rearward movement of the WHEEL BRAKE lever into the PARK BRAKE range progressively applies the brakes and at 1000 psi, the white WHEEL BRAKE EMERG annunciators illuminate. Full parking pressure is applied when the WHEEL BRAKE lever is in the PARK BRAKE position.
  • Page 204 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION A combined hydraulic pressure indicator shows the BRAKE pressures (upper indication) applied to the left and right brake units during normal operation. The BRAKE indications are electrically operated from pressure transmitters connected into the normal supply lines to the brake units.
  • Page 205 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION POWER SUPPLIES DC power distribution is as follows: PE Busbar WHEEL BRAKE EMERG annunciators PS1 Busbar BRAKES applied pressure indicators NOSEWHEEL STEERING (Figure 9) CAUTION: A STEERING DISCONNECT PIN MUST BE REMOVED BEFORE TOWING THE AIRPLANE.
  • Page 206 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION Figure 9 Nose Gear Steering System Sub-section 8 Pilot’s Operating Manual Page 8-19 LANDING GEAR Original Issue: Feb, 2002...
  • Page 207 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION Intentionally left blank Sub-section 8 Page 8-20 Pilot’s Operating Manual LANDING GEAR Original Issue: Feb, 2002...
  • Page 208 Pilot’s Operating Manual Section III SYSTEMS DESCRIPTION Sub-section 9 ELECTRICAL POWER Table of Contents Page GENERAL ...................... 9-3 CONTROLS and INDICATIONS..............9-3 EXTERNAL POWER ................... 9-3 BATTERY SUPPLIES.................. 9-4 AMMETERS ....................9-4 Figure 1 - DC Electrical System - De-energized........9-5 VOLTMETER....................
  • Page 209 Pilot’s Operating Manual Page AC POWER DISTRIBUTION ..............9-22 Figure 8 - Inverter System Busbars - Simplified........9-22 ALTERNATOR POWER SUPPLY ............9-23 Section III Sub-section 9 Page 9-2 140-590032-0007 ELECTRICAL POWER Revision A4: Sep, 2010...
  • Page 210 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.
  • Page 211 Pilot’s Operating Manual CAUTION: NO. 1 BATTERY MAY BE EXCESSIVELY DISCHARGED AND DAMAGED IF THE ROOF SWITCH ON PANEL DA AND THE ENTRY LIGHT SWITCH ON THE FORWARD CABIN BULKHEAD ARE LEFT ON FOR LONG PERIODS WHILE EXTERNAL POWER IS APPLIED. THE VESTIBULE ROOF LIGHT AND THE ENTRY LIGHT ARE CONNECTED VIA THEIR SWITCHES DIRECTLY TO NO.
  • Page 212 Pilot’s Operating Manual Figure 1 DC Electrical System De-energized Section III Sub-section 9 140-590032-0007 Page 9-5 ELECTRICAL POWER Revision A4: Sep, 2010...
  • Page 213 Pilot’s Operating Manual VOLTMETER A 0-40V voltmeter and selector switches are provided in the flight compartment on the overhead roof panel. The voltmeter scale has a red segment between 32V and 40V. The voltmeter may display, by selection on the switches, the voltage of the batteries (1 thru 6), busbars PE, PS1 or PS2. The positions on the switches are labelled B1, PS1, PE, PS2, B2, XFER and B3, B4, B5, B6, OFF.
  • Page 214 Pilot’s Operating Manual EXTERNAL POWER CONTACTOR ENG 2 ENG 1 No. 2 No. 1 STARTER STARTER STARTER OPERATING OPERATING APU START GEN LINE GEN LINE STARTER BUSBAR APU GEN GEN 1 CONTACTOR GEN 2 CONTACTOR FAIL FAIL No. 2 FAIL No.
  • Page 215 Pilot’s Operating Manual BATT EMERG-ON-OFF switch With no generators or external power supplying the busbars, selection of the BATT switch to ON will connect both batteries in parallel to busbar PE via the emergency contactors. When any generator comes on-line both emergency contactors remain closed. The generator fed PS busbar is connected to its related battery to commence charging, by closure of the associated battery contactor.
  • Page 216 Pilot’s Operating Manual BATT ISOLATE BATT 1-NORM-BATT 2 switch NORM selection closes both battery contactors to permit batteries to charge when the generators come on line, or external power is available. Selecting the switch to either BATT 1 or BATT 2 will open the associated battery contactor, to isolate the battery from its charge source.
  • Page 217 Pilot’s Operating Manual EXTERNAL POWER CONTACTOR ENG 2 No. 2 ENG 1 No. 1 STARTER STARTER STARTER OPERATING OPERATING APU START GEN LINE GEN LINE APU GEN GEN 2 STARTER BUSBAR GEN 1 CONTACTOR CONTACTOR FAIL FAIL FAIL No. 2 No.
  • Page 218 Pilot’s Operating Manual BUS TIE CLOSE-OPEN switch Following an abnormal electrical condition, selecting the BUS TIE switch to OPEN splits the busbar system into two single-channel busbars. Overhead Roof Panel BUS TIE CLOSE BUS TIE OPEN OPEN selection - annunciator illuminated OPEN CLOSE selection - annunciator extinguished GEN 1 and GEN 2 CLOSE-TRIP switches...
  • Page 219 Pilot’s Operating Manual EXTERNAL POWER CONTACTOR ENG 2 No. 2 ENG 1 No. 1 STARTER STARTER STARTER OPERATING OPERATING APU START GEN LINE APU GEN GEN LINE STARTER BUSBAR CONTACTOR CONTACTOR FAIL No. 2 No. 1 GEN SHUNT APU GEN GEN SHUNT No.
  • Page 220 Pilot’s Operating Manual ENGINE START USING EXTERNAL POWER Selecting the EXT PWR switch to ON with a suitable external power supply unit will energize all busbars including the start busbar providing that internal start power has not been previously selected. Operation of the START PWR push switch illuminates the PWR ON/PUSH FOR ABORT annunciator and brings the start circuit to a state of readiness for ENGINE START switch selection.
  • Page 221 Pilot’s Operating Manual EXTERNAL POWER CONTACTOR ENG 2 ENG 1 No. 2 No. 1 STARTER STARTER STARTER OPERATING OPERATING APU START GEN LINE GEN 2 GEN LINE GEN 1 STARTER BUSBAR CONTACTOR APU GEN FAIL CONTACTOR FAIL No. 2 FAIL No.
  • Page 222 Pilot’s Operating Manual ENGINE START USING BATTERY POWER (Figure 5) Selecting the BATT switch to ON energizes PE busbar and makes the battery power available at the internal start contactor. Operation of the START PWR energizes the internal start contactors which connect both batteries to the start busbar and brings the system to a state of readiness for ENGINE START.
  • Page 223 Pilot’s Operating Manual In the event of reverse current, overvoltage, or over excitation faults being detected, the GCU will signal the GLC to open, thereby removing the faulty system from the busbars and illuminating the relevant GEN FAIL annunciator. NOTE: An attempt to reinstate an off-line generator can be made using the GEN CLOSE-TRIP switch.
  • Page 224 Pilot’s Operating Manual EXTERNAL POWER CONTACTOR ENG 2 ENG 1 No. 2 No. 1 STARTER STARTER STARTER OPERATING OPERATING APU START GEN LINE GEN LINE STARTER BUSBAR APU GEN GEN 1 CONTACTOR CONTACTOR FAIL FAIL No. 2 No. 1 GEN SHUNT APU GEN GEN SHUNT No.
  • Page 225 Pilot’s Operating Manual EXTERNAL POWER CONTACTOR ENG 2 ENG 1 No. 2 No. 1 STARTER STARTER STARTER OPERATING OPERATING APU START GEN LINE GEN LINE GEN 2 STARTER BUSBAR APU GEN GEN 1 CONTACTOR CONTACTOR FAIL FAIL FAIL No. 2 No.
  • Page 226 Pilot’s Operating Manual APU GENERATOR (if APU installed) The generator driven by the APU is rated at 28 VDC at 250 AMPS. When the APU is running, operating the APU GEN switch, located on the APU control panel - vestibule panel inner face, to CLOSE and held for 5 seconds causes the APU generator contactor to close.
  • Page 227 Pilot’s Operating Manual AC POWER AC power is supplied from two sources: • DC driven static inverters • Engine driven alternators CONTROLS and INDICATIONS All controls and indicators, with the exception of the ELECT repeater annunciator on the MWS panel, are located on the AC POWER section of the overhead roof panel.
  • Page 228 Pilot’s Operating Manual STATIC INVERTERS Two 1500VA, 115V, 400 Hz. main static inverters, designated No. 1 and No. 2, are installed in the rear equipment bay. Under normal operating conditions, these main inverters provide power to the airplane’s AC busbars. A 250VA, 115V, 400Hz. standby inverter is installed in the rear equipment bay to power essential AC services in the event of failure of both main inverters.
  • Page 229 Pilot’s Operating Manual AC POWER DISTRIBUTION Two main busbars XS 1 and XS 2 and an essential busbar XE are provided. During normal operation, busbars XS 1 and XE are fed by No. 1 inverter and XS 2 by No. 2 inverter. In the event of a single main inverter failure, the remaining main inverter output will be automatically switched to supply all three busbars.
  • Page 230 Pilot’s Operating Manual ALTERNATOR POWER SUPPLY The AC generated power is supplied from two 208V, frequency wild, three phase alternators, one driven by each engine. This supply is used to power the windscreen and side screen heating and the vane heaters.
  • Page 231 Pilot’s Operating Manual Intentionally left blank Section III Sub-section 9 Page 9-24 140-590032-0007 ELECTRICAL POWER Revision A4: Sep, 2010...
  • Page 232 Pro Line 21 Section - III SYSTEMS DESCRIPTION Sub-section 10 ENVIRONMENTAL Table of Contents Page GENERAL ....................10-3 BLEED AIR SYSTEM................. 10-3 ENGINE AIR BLEED ................10-3 MIXING VALVE ..................10-3 MAIN AIR VALVE..................10-3 PRESSURE REGULATOR and SHUT-OFF VALVE......... 10-4 AIR CYCLE MACHINE................
  • Page 233 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION Intentionally left blank Sub-section 10 Page 10-2 Pilot’s Operating Manual ENVIRONMENTAL Original Issue: Feb, 2002...
  • Page 234 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION GENERAL Bleed air is tapped from both engines and conditioned to acceptable temperature levels by an air conditioning pack incorporating a three-wheel air cycle machine. Conditioned air is ducted to the flight compartment and passenger cabin to provide ventilation, heating and pressurization.
  • Page 235 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION MAIN AIR VLV Overhead Roof Panel OPEN CLOSE Time delay units are incorporated in the open circuit of the MAVs to prevent an initial surge of air to the cabin. The No. 1 MAV has a staggered open/delay logic control, and takes approximately 20 seconds to reach the fully open position.
  • Page 236 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION Figure 1 Air Supply and Distrubution Page 10-5 Pilot’s Operating Manual Sub-section 10 Revision A2: Nov, 2004 ENVIRONMENTAL...
  • Page 237 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION Intentionally left blank Pilot’s Operating Manual Page 10-6 Sub-section 10 Revision A2: Nov, 2004 ENVIRONMENTAL...
  • Page 238 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION OVERSPEED PROTECTION A pressure switch downstream of the PRSOV, protects the ACM from overspeed should the PRSOV fail. The pressure switch operates on a rising pressure of 40 psi to signal the No. 2 MAV to close.
  • Page 239 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION LOW LIMIT TEMPERATURE CONTROL SYSTEM The air temperature at the inlet to the water separator is limited by a control circuit to a minimum temperature of about 2°C to prevent freezing and subsequent blockage of the water separator. Warm air is routed from the primary heat exchanger outlet via the Low Limit Temperature Control Valve (LLTCV) to the inlet of the water separator.
  • Page 240 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION CABIN TEMPERATURE CONTROL SYSTEM Temperature of the air delivered to the cabin may be varied by the flight crew via selections on the CABIN TEMP AUTO-MANUAL/COOL-HOT temperature selector. AUTO or MANUAL are the two modes of operation for the cabin temperature system.
  • Page 241 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION CAUTION: THE FAN FOR THE TEMPERATURE INDICATOR BULB AND THE CABIN TEMPERATURE SENSOR IS INOPERATIVE WHEN MANUAL IS SELECTED. THE DUCT TEMPERATURE SHOULD BE MONITORED TO CHECK THE CABIN AIR...
  • Page 242 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION AUXILIARY HEATING SYSTEM The auxiliary heating system supplies the flight compartment with a variable supply of hot air via a heat augmentor in the main supply system. Control of the auxiliary system valve is by the F/DK VLV switch on the overhead roof panel.
  • Page 243 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION REAR EQUIPMENT BAY VENTILATION A tapping is taken from the dorsal fin air intake to provide an air supply for rear equipment bay ventilation. There are no controls or indications for this supply.
  • Page 244 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION PRESSURIZATION CONTROL SYSTEM INDICATOR A triple pointer CABIN pressure indicator is located on the copilot’s instrument panel at the lower right of the PFD. The three pointers are: • An "A" pointer which displays cabin altitude.
  • Page 245 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION AUTOMATIC CONTROL Cabin pressure is controlled by two outflow/safety valves on the rear pressure bulkhead. During normal operation both valves are automatically controlled, but in the event of system malfunction, manual control of one outflow/safety valve is available.
  • Page 246 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION Pneumatic Relay Each pneumatic relay senses cabin pressure changes as referenced by the pressure controller. These pressure changes cause the associated outflow valve to operate via an absolute pressure regulator.
  • Page 247 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION CABIN ALTITUDE (Roof Panel Test Area) HORN HORN ISOLATE FLAPS 15 ° CABIN ALTITUDE Normal Datum Pressure Switch 9300 ft ± 300 ft CABIN HIGH DATUM High Datum Pressure Switch 14,000 ft ±...
  • Page 248 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION Pressure Cabin Shell PRESSN OVRD Cabin Pressure Pressurization Controller Weight Air Jet Override Pressure Pump Auxiliary Wheels Port AUTO Tank Switch Volume Tank Vacuum Valve Engine Bleed Pressure Fan Venturi Tube...
  • Page 249 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION Intentionally left blank Page 10-18 Pilot’s Operating Manual Sub-section 10 Revision A2: Nov, 2004 ENVIRONMENTAL...
  • Page 250 Pro Line 21 Section - III SYSTEMS DESCRIPTION Sub-section 11 ICE PROTECTION SYSTEM Table of Contents Page GENERAL ....................11-3 SYSTEM OPERATION................11-3 ROTARY-CUTTER ICE DETECTOR ............11-4 WING SPOTLIGHTS ................11-4 Figure 1 - Ice Detection Components ..........11-5 FLUID STORAGE..................11-6 Warning Annunciators..............11-6 POWER SUPPLIES................11-6 Figure 2 - Airframe Ice Protection System........
  • Page 251 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION Intentionally left blank Sub-section 11 Page 11-2 Pilot’s Operating Manual ICE PROTECTION Original Issue: Feb, 2002...
  • Page 252 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION GENERAL An airframe fluid ice protection system is provided for the leading edges of the wings and the horizontal stabilizers. The system is controlled by a single timer switch. An audio warning is given when the system switches off.
  • Page 253 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION De-icing fluid is drawn from the tank through a suction filter to the pump, and then via a pressure filter and check valve to the head compensating valve. The head compensating valve ensures equal fluid pressure at the wings and horizontal stabilizers proportioning units.
  • Page 254 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION ICE DETECTION SPOTLIGHT (Same Right Side) ROTARY-CUTTER ICE DETECTOR Overhead Roof Panel DETECTED ICE DET MWS Panel AUTO LOGO/ICE PROT Figure 1 OVRD Ice Detection Components Sub-section 11 Pilot’s Operating Manual...
  • Page 255 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION FLUID STORAGE De-icing fluid for the system is stored in a tank with an approximate capacity of 10.04 gallons (38 liters). For a tank indicating full, priming and protection for at least 85 minutes is provided. The fluid contents indicator on the right side console reads FULL above 8.19 gallons (31 liters), and reads EMPTY when...
  • Page 256 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION Figure 2 Airframe Ice Protection System Sub-section 11 Pilot’s Operating Manual Page 11-7 ICE PROTECTION Original Issue: Feb, 2002...
  • Page 257 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION ENGINE BLEED AIR ANTI-ICING Air is bled from two stages of the engine compressor to provide supplies for: • Nacelle inlet cowl anti-icing • Airplane services An ENG ANTICE ON-OFF switch, located on the roof panel ice protection section, is provided for each engine.
  • Page 258 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION PE BUSBAR MWS DIM BUS ICE PROT SELECTED ENG ANTICE TO ENGINE DIGITAL COMPUTER IDLE 2 SEC SCHEDULE DELAY TO Pt and Tt HEATING CIRCUITS ENG 1 A/ICE PRESSURE 6 PSI...
  • Page 259 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION ICE PROTECTION - WINDSCREENS The two forward facing curved windscreens ('A' screens) and the left and right forward sidescreens ('B' screens) are anti-iced and anti-misted by electrical heating. ELECTRICAL HEATING SYSTEM Power for windscreen and sidescreen heating is supplied from two 208V, frequency wild, three phase alternators, one driven from each main engine.
  • Page 260 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION Figure 4 Windscreen Electrical Heating Sub-section 11 Pilot’s Operating Manual Page 11-11 ICE PROTECTION Original Issue: Feb, 2002...
  • Page 261 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION POWER SUPPLIES Power distribution to the equipment is as follows: PE busbar supplies: • ALTR 1 (2) FAIL annunciators. • L (R) SCREEN OVHT annunciators. • SIDE SCRN OVHT annunciator MWS ICE PROT repeater annunciator SCREEN HEAT L ON/OFF control PS2 busbar supplies.
  • Page 262 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION PITOT, STATIC, RUDDER BIAS STRUT and AIRFLOW ANGLE SENSOR HEATING Ice protection in the form of electrical heating is provided for the following: • Two pitot heads, one located each side of the forward fuselage.
  • Page 263 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION Overhead Roof Panel PITOT AMPS PITOT/VANE HEAT R VANE L VANE HTR FAIL HTR FAIL R PITOT L PITOT MWS Panel HTR FAIL HTR FAIL PROT POWER SUPPLIES DC power supplies to the pump and chime unit are taken from busbar PS2. Supplies to the ANTICE LO PRESS, ANTICE LO QTY annunciators and the MWS ICE PROT repeater annunciator is taken from busbar PE.
  • Page 264 Pro Line 21 Section - III SYSTEMS DESCRIPTION Sub-section 12 OXYGEN SYSTEM Table of Contents Page GENERAL ....................12-3 Figure 1 - Oxygen Cylinder Assembly ..........12-3 Figure 2 - Oxygen System ..............12-4 SERVICING ....................12-5 Figure 3 - Oxygen Box Assembly ............12-5 OPERATION .....................
  • Page 265 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION Intentionally left blank Sub-section 12 Page 12-2 Pilot’s Operating Manual OXYGEN SYSTEM Original Issue: Feb, 2002...
  • Page 266 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION GENERAL Two 750 liter oxygen cylinders (with provision for a third 750 liter cylinder) are mounted in the rear equipment bay between frames 24 and 25. The cylinders are charged to 1800 psi and normally supply oxygen to two quick-release sockets in the flight compartment, two therapeutic outlets and eight drop- out mask units in the passenger cabin and one drop-out mask unit in the toilet compartment.
  • Page 267 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION 750 LITER OXYGEN CYLINDERS 750 LITER OXYGEN CYLINDERS NOTE: A blanking plug is installed if an optional cylinder is not installed. Figure 2 Oxygen System Sub-section 12 Page 12-4 Pilot’s Operating Manual...
  • Page 268 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION SERVICING The oxygen cylinders are charged through a charging valve in the oxygen box assembly which is situated in the right hand rear fuselage between frames 24 and 25. A contents indicator is mounted next to the charging valve. The charging supply passes through a line filter and bursting disc assembly before joining the pipeline from the cylinders to the automatic shut-off valve.
  • Page 269 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION OPERATION Oxygen from the storage cylinders is fed to the master SUPPLY valve on the flight compartment oxygen panel on the left console. Opening the master SUPPLY valve allows oxygen to flow to the contents indicator and the pressure regulator, then, at 70 psi to the combined mask-regulators, therapeutic outlets and the baromatic valve.
  • Page 270 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION PORTABLE OXYGEN SMOKE SET The Puritan-Zep portable oxygen smoke set comprises a single 312 liter capacity oxygen cylinder and a smoke mask. The cylinder rests in a fixture secured to the rear of the flight compartment right console.
  • Page 271 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION FLIGHT CREW SUPPLY Mask-Regulator Under normal flight conditions the mask-regulator is selected to the — N“ position. At this setting the ratio of oxygen to air increases with an increase in altitude until at approximately 30,000 feet, when 100% oxygen is supplied.
  • Page 272 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION Goggles Combined smoke goggles and mask-regulators are provided for the flight crew with the goggles stowed in the flight compartment left and right side consoles. NOTE: Headsets and hats must be removed before donning oxygen masks.
  • Page 273 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION PASSENGER SUPPLY The emergency drop-out passenger mask unit consists of a mask and hose assembly and an emergency mask stowage. The emergency mask stowage boxes are provided in the airplane ceiling structure above the passengers' heads and supply oxygen to the single face masks.
  • Page 274 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION Figure 9 Oxygen Mask Folding and Stowage Sub-section 12 Pilot’s Operating Manual Page 12-11 OXYGEN SYSTEM Original Issue: Feb, 2002...
  • Page 275 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION Intentionally left blank Sub-section 12 Page 12-12 Pilot’s Operating Manual OXYGEN SYSTEM Original Issue: Feb, 2002...
  • Page 276 Pro Line 21 Section - III SYSTEMS DESCRIPTION Sub-section 13 LIGHTING SYSTEMS Table of Contents Page GENERAL ....................13-3 ENTRANCE LIGHTING................13-3 Figure 1 - Main Entry Doorway Lighting and Controls ......13-3 FLIGHT COMPARTMENT LIGHTING ............13-4 INSTRUMENT and PANEL LIGHTING ..........13-4 Figure 2 - Flight Compartment Lighting ..........
  • Page 277 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION Page Figure 6 - Interior Lighting Control Panel .......... 13-15 EXTERIOR LIGHTING................13-16 NAVIGATION LIGHTS ................13-16 ANTI-COLLISION BEACONS ............... 13-16 LANDING and TAXI LIGHTS ..............13-16 WING ICE-INSPECTION SPOTLIGHTS ..........13-16 Figure 7 - Exterior Lighting Control Panel .........
  • Page 278 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION GENERAL Particular lighting installations may vary from the standard installation. This section provides a typical installation of interior and exterior lighting. ENTRANCE LIGHTING Entrance lighting is provided by a step light mounted on the rear face of the forward cabinet and a twin light assembly mounted in the vestibule roof.
  • Page 279 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION FLIGHT COMPARTMENT LIGHTING INSTRUMENT and PANEL LIGHTING (Figure 2) Circuit control for the electroluminescent display panels, instruments and the pedestal lighting is provided by a “successive action” LTS MASTER push button switch on the overhead roof panel and the dimming controls on the overhead roof panel and the left and right glareshields.
  • Page 280 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION NOTE: FOR INDIVIDUAL INSTRUMENT PANEL ARRANGEMENTS MIKE INCLUDING ELECTROLUMINESCENT MIKE PANELS REFER TO CHAPTER 31 FD BARS GLARESHIELD PANEL FD BARS ANNUN GLARESHIELD PANEL INSTRUMENT PANEL DISPLAYS PANELS INST INSTRUMENT PANEL...
  • Page 281 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION CHART/WANDER LIGHT SWITCH WANDER LIGHT SOCKET STORM LIGHT SPOTLIGHT SWITCH PANEL DA Looking Aft SPOTLIGHT (DA PANEL LIGHTING) Figure 3 Flight Compartment Bulkhead Lighting WANDER LIGHT (Figure 3) A CHART/WANDER LIGHT three position switch plus a wander light socket is located on the upper inward face of panel DA.
  • Page 282 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION STANDBY LIGHTING Electrical power for standby lighting is available when the PE busbar is energized. The following lights are connected to the PE busbar, and are switched by their normal operating switches to provide standby lighting.
  • Page 283 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION PRINCIPAL DIMMER CONTROLS Table 2 Dimmer Supply Panel Lighting Service (voltage) Busbar Overhead Roof Panel *INSTR DIM Overhead roof panel (5 VDC) instrument integral lighting *PANEL DIM E2B compass lighting...
  • Page 284 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION Dimmer Supply Panel Lighting Service (voltage) Busbar Right Glareshield Right pad light (28 VDC) *GLARESHIELD PANEL Right glareshield side and (5 VDC) upper electroluminescent panel *INSTRUMENT PANEL Right electroluminescent PANELS...
  • Page 285 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION GALLEY LIGHTING (Figure 4) An incandescent light strip is installed on the back of the upper shelf of the upper galley section and controlled by the GALLEY UP LIGHTS switch on the galley switch panel. The galley work lighting is provided by a twin fluorescent light assembly to illuminate the working surface and controlled by the GALLEY WORK LIGHTS switch on the galley switch panel.
  • Page 286 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION PASSENGER CABIN LIGHTING GENERAL LIGHTING NOTE: For the position of lights and switches refer to Figure 1 or Figure 3 and for details of power supplies refer to Table 1.
  • Page 287 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION CABIN LIGHTING POWER SOURCES Table 3 PE Busbar Cabin standby lights Toilet standby lights PS1 Busbar Cabin floor lights (left-hand inverter) Reading lights (left-hand inverter) PS2 Busbar Cabin flood lights (right-hand inverter)
  • Page 288 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION EMERGENCY LIGHTING (if installed) The emergency lighting system is powered by a forward and aft battery supply and provides emergency cabin and exterior lighting automatically whenever PE power is interrupted or lost with the capability to be manually overridden.
  • Page 289 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION TOILET COMPARTMENT LIGHTING (Figure 5) The toilet compartment is illuminated by six fluorescent tubes mounted in the roof trim to provide a concealed lighting effect when the main airplane power is turned on. Additional lighting is controlled by switching on the toilet lighting control panel located above the mirror.
  • Page 290 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION AFT BAGGAGE COMPARTMENT LIGHTING A roof-mounted twin-bulb tube is installed in the aft baggage compartment and is controlled by the BAGGAGE LIGHTS switch on the toilet lighting control panel. One bulb of the aft baggage compartment light is illuminated whenever the main toilet lights are on, the other is illuminated together with the toilet bulb whenever the main cabin lights are on.

  • Page 291: Exterior Lighting

    Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION EXTERIOR LIGHTING NAVIGATION LIGHTS (Figures 7 and 8) These lights give a high-intensity red (left wingtip), green (right wingtip), and white (tail unit) light. All three lights are controlled by a single switch labelled NAV-OFF on flight compartment overhead roof panel forward extension.
  • Page 292 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION NAVIGATION LIGHT (GREEN) STROBE LIGHT LANDING LIGHTS RIGHT LOGO TAXI LIGHT FLOOD LIGHT (if installed) LANDING LIGHT LEFT LOGO LANDING LIGHT FLOOD LIGHT TAXI LIGHT (if installed) STROBE NAVIGATION LIGHT (RED)

  • Page 293: Strobe Lights

    Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION STROBE LIGHTS (Figures 7 & 8) Strobe lighting provides additional airplane identification to the standard airplane position light presentations. The strobe lighting system consists of three flashing white condenser discharge strobe lights, three power supply units (PSU's 1, 2 and 3) and a STROBE light control switch.
  • Page 294 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION EXTERIOR LIGHTING POWER SOURCES Table 4 PE Busbar Navigation lights Left wing landing light Left wing taxi light Vestibule/ground lights PS1 Busbar Left and right wing inspection spotlights Strobe lights...
  • Page 295 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION Intentionally left blank Sub-section 13 Page 13-20 Pilot’s Operating Manual LIGHTING SYSTEMS Original Issue: Feb, 2002...
  • Page 296 Pro Line 21 Section - III SYSTEMS DESCRIPTION Sub-section 14 EQUIPMENT and FURNISHINGS Table of Contents Page GENERAL ....................14-3 FLIGHT COMPARTMENT .................14-3 CREW SEATS ..................14-3 Figure 1 - Crew Seat ................14-4 3rd CREW MEMBER SEAT ..............14-5 Figure 2 - 3rd Crew Member Seat ............14-5 CREW CABINET AREA ................14-5 Figure 3 - Flight Compartment ............14-6 Figure 4 - Flight Compartment Main Instrument Panels......14-7...
  • Page 297 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION Intentionally left blank Sub-section 14 Page 14-2 Pilot’s Operating Manual EQUIPMENT and FURNISHINGS Original Issue: Feb, 2002...
  • Page 298 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION GENERAL Due to individual customer requirements, the equipment and furnishings may vary from the standard installation. This Sub-section provides the typical installation of a flight compartment, vestibule area, passenger cabin, galley, toilet compartment and cargo and accessory compartments.
  • Page 299 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION Armrests When the control knob is turned, a screw adjuster increases or decreases the distance between the armrest drive plate and the pivot block via a drive shaft, thereby raising or lowering the armrest. The inboard armrest can be stowed by rotating the arm to the rear of the seat.
  • Page 300 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION 3rd CREW MEMBER SEAT The 3rd crew member seat is an additional seat which can be attached to the inboard rails of each crew seat. A three point inertia reel harness is anchored to the seat frame and the luggage compartment upper shelf structure.
  • Page 301 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION ROOF PANEL `CG` CREW SERVICES OVERHEAD (MAIN SECTION) PANEL ROOF PANEL OVERHEAD ROOF PANEL `CG` ROOF PANEL CONTROL DISPLAY UNIT (FWD SECTION) FWD EXTENTION PANEL `CT` GLARE SHIELD CENTER INSTRUMENT...
  • Page 302 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION STANBY HORIZON PUSH TO INHIB STALL IDENT PUSH TO INHIB STALL IDENT HORIZON FAULT FAULT WARN STALL IDENT 1 IDENT 2 IDENT 3 STALL STALL STALL IDENT 1 IDENT 2...
  • Page 303 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION TEST F/DK VLV OPEN CABIN STALL HP AIR ANNUN OVHT SELCAL FIRE EGPWS STOP ISOLATE EXT BATT EXT PWR EMERG BATT ALTERNATOR ENGINE START CHG ON EMERG BATT 1 EMERG...
  • Page 304 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION V8636_1.AI Figure 6 Flight Compartment (looking aft) Sub-section 14 Pilot’s Operating Manual Page 14-9 EQUIPMENT and FURNISHINGS Original Issue: Feb, 2002...
  • Page 305 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION AIR OUTLET AIR OUTLET AUDIO SELECTOR PANEL AUDIO SELECTOR PANEL NAV / COMM CVR-120 CONTROLLER CONTROLLER DE-ICING FLUID OXYGEN PANEL CONTENTS RIGHT-HAND CONSOLE LEFT-HAND CONSOLE MANUAL CABIN PRESSURIZATION CONTROL ALTITUDE CONTROL...
  • Page 306 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION THRUST NOSE GEAR HORN ISOLATE REVERSER MECHANICAL PUSH BUTTON LEVERS INDICATOR THRUST DUMP VALVE LEVERS THROTTLES AUXILIARY HYDRAULIC SYSTEM SELECTOR HANDLE AIR BRAKES SMOKE WHEEL BRAKE PUSH FUEL TEMP SOCKET FOR...
  • Page 307 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION GALLEY The galley is located on the left side of the airplane aft of the entry door and consists of liquid containers, hot cup, decanter rack, drain dish, ice drawer, glasses drawer, cold food box, hot meal oven, waste bin and various drawers and cupboards.
  • Page 308 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION PASSENGER CABIN Figure 10 Typical Interior Layout Sub-section 14 Pilot’s Operating Manual Page 14-13 EQUIPMENT and FURNISHINGS Revision A1: Nov, 2002...
  • Page 309 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION SEATING ARRANGEMENTS The seating arrangements comprise individual forward or aft facing seats with side consoles for entertainment control and a three seat divan. Each individual seat position is provided with a lap type safety belt.
  • Page 310 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION CARGO and ACCESSORY COMPARTMENTS LUGGAGE COMPARTMENT A luggage compartment is installed in the vestibule area of all airplanes, with luggage retained within the compartment by a zip fastened nylon net. The compartment is normally enclosed by a folding slat type curtain.
  • Page 311 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION Figure 13 Cargo and Accessory Compartments Sub-section 14 Page 14-16 Pilot’s Operating Manual EQUIPMENT and FURNISHINGS Original Issue: Feb, 2002...
  • Page 312 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION TOILET COMPARTMENT The typical toilet compartment consists of a console assembly, flushing toilet with a fore and aft positioned toilet services bulkhead. Access is provided to the rear baggage compartment and the avionics compartment from within the toilet compartment.
  • Page 313 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION Intentionally left blank Sub-section 14 Page 14-18 Pilot’s Operating Manual EQUIPMENT and FURNISHINGS Original Issue: Feb, 2002...
  • Page 314 Pro Line 21 Section - III SYSTEMS DESCRIPTION Sub-section 15 EMERGENCY EQUIPMENT Table of Contents Page GENERAL ....................15-3 EQUIPMENT LOCATION................15-3 FLIGHT COMPARTMENT..............15-3 VESTIBULE .................... 15-3 PASSENGER CABIN ................15-3 TOILET COMPARTMENT ..............15-3 EMERGENCY LOCATOR TRANSMITTER (ELT)........15-4 PROTECTIVE BREATHING EQUIPMENT (PBE) ........
  • Page 315 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION Intentionally left blank Sub-section 15 Page 15-2 Pilot’s Operating Manual EMERGENCY EQUIPMENT Original Issue: Feb, 2002...
  • Page 316 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION GENERAL Emergency equipment is stored in the following compartments: • Flight compartment • Crew Cabinet • Passenger cabin • Toilet compartment EQUIPMENT LOCATION The location, number of and composition of the emergency equipment varies according to the furnishing options chosen and the floorplan.
  • Page 317 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION EMERGENCY LOCATOR TRANSMITTER (ELT) The ELT is a compact self powered emergency locating transmitter designed to activate automatically under disabling emergency conditions, or manually from the cabin to summon assistance in other than a disabling emergency condition.
  • Page 318 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION PROTECTIVE BREATHING EQUIPMENT (PBE) The PBE is installed for use by crew members in the event of fire or smoke from cabin furnishings or equipment, other than from electrical/electronic sources, producing burning dripping plastic with toxic fumes.
  • Page 319 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION Intentionally left blank Sub-section 15 Page 15-6 Pilot’s Operating Manual EMERGENCY EQUIPMENT Original Issue: Feb, 2002...
  • Page 320 Pro Line 21 Section - III SYSTEMS DESCRIPTION Sub-section 16 WATER/WASTE Table of Contents Page GENERAL ....................16-3 WATER SYSTEM..................16-3 LAVATORY WATER TANK ..............16-3 LAVATORY WATER PUMP ..............16-3 GALLEY WATER..................16-4 Figure 1 - Galley Master Switch and Typical Galley ......16-4 WASTE SYSTEM ..................
  • Page 321 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION Intentionally left blank Sub-section 16 Page 16-2 Pilot’s Operating Manual WATER and WASTE Initial Issue: Feb, 2002...
  • Page 322 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION GENERAL The water and waste system consists of a basin with heated running water located in a lavatory at the rear of the passenger cabin and an electrically flushing toilet with external servicing facilities.
  • Page 323 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION GALLEY WATER (Figure 1) The galley water system, depending on options selected, has either a heated 2.23 gallon water tank, an unheated 2.07 gallon water tank or both. With the heated water tank, the water temperature is thermostatically controlled to approximately 100°...
  • Page 324 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION WASTE SYSTEM TOILET (Figures 2 & 3) An electrical flushing toilet (Monogram 4620-17) with external servicing facilities is installed at the rear of the passenger cabin. The toilet is a self-contained removable unit consisting of a tank, motor, pump and a filter.
  • Page 325 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION DRAIN VALVE ASSEMBLY ELECTRICAL CONNECTION BOWL MOTOR-PUMP -FILTER CARTRIDGE ASSEMBLY GROUND FLUSH INLET M6360_0 HA03C 014659AA.AI Figure 3 Typical Toilet with External Servicing Facility Sub-section 16 Page 16-6 Pilot’s Operating Manual...
  • Page 326 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION DETAIL Figure 4 Toilet Ground Servicing Sub-section 16 Pilot’s Operating Manual Page 16-7 WATER and WASTE Initial Issue: Feb, 2002...
  • Page 327 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION Intentionally left blank Sub-section 16 Page 16-8 Pilot’s Operating Manual WATER and WASTE Initial Issue: Feb, 2002...
  • Page 328 Pilot’s Operating Manual Section III SYSTEMS DESCRIPTION Sub-section 17 AVIONICS Table of Contents Page GENERAL ....................17-3 SYSTEMS and CONTROLS ..............17-3 Figure 1 - Push-To-Test Panel ............17-3 ELECTRONIC FLIGHT INSTRUMENT SYSTEM (EFIS) ....17-3 DISPLAY CONTROL PANELS (DCP) ..........17-4 FLIGHT GUIDANCE PANEL (FGP) ............
  • Page 329 Pilot’s Operating Manual Page ENHANCED GROUND PROXIMITY WARNING SYSTEM (EGPWS) with WINDSHEAR ............. 17-14 EGPWS Features ................17-14 Figure 6 - Terrain Clearance Floor Alert Envelope ...... 17-15 Figure 7 - Improved Terrain Clearance Floor Envelope....17-15 Self Test..................17-16 Switches/Annunciators ..............
  • Page 330 Pilot’s Operating Manual GENERAL The Hawker 800XP Collins Pro Line 21 avionics system is an intricate network of subsystems interconnected and managed by the Integrated Avionics Processor System (IAPS). This Sub-section provides general information of the systems with expanded information on the Enhanced Ground Proximity Warning System (EGPWS).
  • Page 331 Pilot’s Operating Manual Each MFD can be used to present a variety of information, including: Present Position Map; TCAS; FMS based textual data; Navigation Data; Weather Radar and EGPWS. Engine data is typically presented on the Pilot’s MFD. The Copilot’s MFD can present fuel gauging data, the flap display and the electronic checklist.
  • Page 332 Pilot’s Operating Manual STANBY HORIZON PUSH TO INHIB STALL IDENT PUSH TO INHIB STALL IDENT HORIZON FAULT WARN FAULT STALL STALL IDENT 1 IDENT 2 IDENT 3 IDENT 1 IDENT 2 IDENT 3 STALL STALL SQUAT VALVE A VALVE B FIRE VALVE A VALVE B...
  • Page 333 Pilot’s Operating Manual ENGINE REFS NAV / BRG RADAR BARO MENU ADV TILT RANGE PUSH PUSH PUSH MENU AUTO TILT Collins DISPLAY CONTROL PANEL MIKE FD BARS GLARESHIELD PANEL INSTRUMENT PANEL PANELS INST DISPLAYS CONSOLE PANEL DIGIT IDENT PANEL LTS FLOOD EMERG STORM...
  • Page 334 Pilot’s Operating Manual FLIGHT GUIDANCE SYSTEM (FGS) The FGS provides autopilot and dual flight guidance functions by utilizing two identical computers, three primary servos, a pitch trim servo and a flight guidance panel. The Flight Guidance Computers (FGC) receive Attitude Heading System (AHS) data directly from the Attitude Heading Computer (AHC) to provide independent flight guidance computation while operating together to provide 3-axis autopilot, pitch trim, Mach trim and yaw damper functions.
  • Page 335 Pilot’s Operating Manual WEATHER RADAR SYSTEM The Weather Radar System is a fully integrated system that detects precipitation, moisture-based turbulence and ground feature returns in front of the airplane which can be displayed on the Primary Flight Displays (PFDs) or the Multifunction Flight Displays (MFDs) and features the following operating modes: Mode Description...
  • Page 336 Pilot’s Operating Manual COMPONENT LOCATIONS Figure 4 Component Locations P/N 140-590032-0007 Section III Sub-section 17 Page 17-9 Revision A4: Sep, 2010 AVIONICS...
  • Page 337 PE busbar through the AUDIO 1 CTL and AUDIO 2 CTL circuit breakers. HF Radio Transmissions Hawker Beechcraft Corporation considers the following indication fluctuations to be normal and acceptable providing that the indications return to a normal reading when the HF radio transmission...
  • Page 338 Pilot’s Operating Manual SELCAL MIC SELECT VHF1 VHF2 VHF2 VOR/ILS VHF1 Standard ACP Installation NORM EMERG BOOM-MIC NORM PHONE AUTOCOM TONE SPKR- OXY-MIC PHONE M8504_0.AI SELCAL MIC SELECT VHF1 VHF2 VHF2 Optional ACP installation VOR/ILS VHF1 based on requested Optional Customer Equipment NORM (ACP shown with HF 2 and ADF 2 EMERG...
  • Page 339 Pilot’s Operating Manual ACP Operation Control Function A SELCAL lamp is located above each respective SELCAL indicator lamps transceiver and illuminates when a ground to air SELCAL signal is received or SELCAL is tested. VHF 1, VHF 2, HF 1, and HF 2 (if option installed) TRANSCEIVER switches/volumes receiver switch functions and volume controls.
  • Page 340 Pilot’s Operating Manual Control Function BOOM-MIC position - Sets the BOOM mic input as the microphone input to the audio control panel. OXY-MIC position - Sets the OXY mic input as the BOOM-MIC/OXY-MIC switch microphone input to the ACP. Also turns ON the following digital amplifier functions: INPH Hot switch, INPH to SPKR switch and Speaker switch.

  • Page 341: Enhanced Ground Proximity Warning System (Egpws) With Windshear

    Pilot’s Operating Manual ENHANCED GROUND PROXIMITY WARNING SYSTEM (EGPWS) with WINDSHEAR The EGPWS provides voice and visual predictive warnings to the flight crew alerting them to the proximity of possible terrain hazards by presenting PULL UP and GND PROX annunciations on the PFD, graphical representations of terrain and peaks elevation value on the PFD/MFD.
  • Page 342 Pilot’s Operating Manual 1/2 RUNWAY LENGTH ENVELOPE BIAS FACTOR 15NM 12NM M6914_0 TCF ALERT ENVELOPE HA00C 016398AA Figure 6 Terrain Clearance Floor Alert Envelope 245 FT BIAS FACTOR 45§ 700' AGL 400' AGL RUNWAY TERRAIN TERRAIN 4 NM 12 NM 15 NM 245 FT IMPROVED TCF ENVELOPE...

  • Page 343: Self Test

    Pilot’s Operating Manual The EGPWS Terrain video is inhibited by pushing the TERR INHIB switch. If the EGPWS terrain video is showing, pushing the TERR INHIB switch makes the video stop and TERR is shown in amber. NOTE: The basic EGPWS modes 1-6 and windshear mode 7 remain active when the Terrain Awareness Alerting is manually inhibited.
  • Page 344 Pilot’s Operating Manual 5.0NM (OUTER LIMIT) (1.5 + KRF) NM RFCF CEILING (300 FT. ABOVE FIELD) FIELD RFCF ELEVATION ALERT AREA RUNWAY (NO LOWER LIMIT) RFCF ALERT ENVELOPE 5500 5000 4500 4000 3500 RFCF ALERT ENVELOPE 3000 2500 2000 TCF ENVELOPE 1500 DISTANCE TO CENTER OF RUNWAY (NM) M6916_0...

  • Page 345: Egpws Operating Modes

    Pilot’s Operating Manual EGPWS Operating Modes There are 7 modes of operations: Mode Operational Envelope MODE 1 This mode is active for all phases of flight when the radio altimeter Excessive Descent Rate indicates between 10 and 2450 ft AGL. The mode envelope identifies Alert/Warning the minimum radio altitude permitted based on a given descent rate.
  • Page 346 Pilot’s Operating Manual Mode Operational Envelope MODE 3 This mode is active when the radio altimeter indicates between 30 and Alert To Descent 1500 ft AGL, either the landing gear or flaps are UP, and the EGPWS is After Takeoff in the takeoff mode (enabled by a successful landing previous to the current takeoff).
  • Page 347 Pilot’s Operating Manual Mode Operational Envelope MODE 5 This mode is active when the following conditions are present: Alert To • A valid glideslope signal is present. Descent Below Glideslope • The EGPWS is in the approach mode or the flaps are in the landing configuration.
  • Page 348 Pilot’s Operating Manual Mode Operational Envelope MODE 6 This mode is active for all phases of flight and airplane configurations. Altitude Callouts/Bank Angle Mode 6 gives voice altitude callouts and indications. The standard callouts will be Menu 76 with smart callout: •...
  • Page 349 Pilot’s Operating Manual Mode Operational Envelope MODE 6 If the airplane bank angle exceeds the maximum allowable bank angle Altitude Callouts/Bank below 150 ft AGL, the "BANK ANGLE BANK ANGLE" voice warning Angle (continued) sounds with no pause between the warnings. On rolling back below the maximum allowable bank angle, the voice messages stop.
  • Page 350 Pro Line 21 Section - III SYSTEMS DESCRIPTION Sub-section 18 PITOT-STATIC SYSTEM Table of Contents Page GENERAL ....................18-3 PITOT HEADS..................18-3 STATIC VENT PLATES ................18-3 STATIC VENTS..................18-3 EQUIPMENT ISOLATION ..............18-4 STALL VENTS ..................18-4 Figure 1 - Pitot Static System Block Diagram........18-5 Pilot’s Operating Manual Page 18-1 Revision A2: Nov, 2004...
  • Page 351 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION Intentionally left blank Sub-section 18 Page 18-2 Pilot’s Operating Manual PITOT STATIC SYSTEM Revision A2: Nov, 2004...
  • Page 352 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION GENERAL The pitot-static system supplies the source pressure for the No. 1 and No. 2 Air Data Computers, an Electronic Standby Instrument System Air Data Unit, the Stall Warning and Identification System, and the Airplane Cabin Differential Pressure Indicator.
  • Page 353 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION EQUIPMENT ISOLATION A PITOT ISOLATION valve, located on the copilot’s side console, provides isolation of the stall detectors and any additional equipment from the Air Data Computer No. 2 and the ESIS Air Data Unit.
  • Page 354 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION Right Forward Static Vent Plate Left Forward Static Vent Plate Copilot Cabin Pressure Instrument Panel Controller No. 1 No. 2 Air Data Left Right Air Data Computer Computer Pitot Pitot...
  • Page 355 Hawker 800XP Pro Line 21 Section III - SYSTEMS DESCRIPTION Intentionally left blank Sub-section 18 Page 18-6 Pilot’s Operating Manual PITOT STATIC SYSTEM Revision A2: Nov, 2004...
  • Page 356 Pilot’s Operating Manual Section - IV FLIGHT PLANNING DATA Table of Contents Page SUB-SECTION 1 - GENERAL................1-1 SUB-SECTION 2 - PREFLIGHT................2-1 SUB-SECTION 3 - CLIMB.................3-1 SUB-SECTION 4 - CRUISE EN-ROUTE............4-1 SUB-SECTION 5 - NORMAL DESCENT ............5-1 SUB-SECTION 6 - SINGLE ENGINE ..............6-1 SUB-SECTION 7 - UNFACTORED LANDING..........7-1 SUB-SECTION 8 - GEAR DOWN PERFORMANCE ........8-1 SUB-SECTION 9 - EXTENDED RANGE OPERATIONS (Non-ETOPS) ..9-1...
  • Page 357 Pilot’s Operating Manual Intentionally left blank Section - IV Page 2 P/N 140-590032-0007 Revision A3: Apr, 2008 FLIGHT PLANNING DATA...
  • Page 358 Pro Line 21 Section - IV FLIGHT PLANNING DATA Sub-section 1 GENERAL Table of Contents Page INTRODUCTION ..................1-3 SPEED and TEMPERATURE RELATIONSHIPS........1-4 DETERMINATION OF TEMPERATURES RELATIVE TO ISA ....1-4 Figure 1 - ISA Temperatures ..............1-4 DETERMINATION OF SPEED and TEMPERATURE CORRECTION .............
  • Page 359 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA Intentionally left blank Page 1-2 Sub-section 1 Pilot’s Operating Manual Original Issue: Feb, 2002 GENERAL...
  • Page 360 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA INTRODUCTION This Sub-section contains general speed and atmospheric data. It also contains ceiling data giving the relationship between maximum altitude and maximum weight. It also contains relationships between true Mach number, true airspeed and true outside air temperature with indicated values of airspeed, altitude and temperature.
  • Page 361 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA SPEED and TEMPERATURE RELATIONSHIPS DETERMINATION OF TEMPERATURES RELATIVE TO ISA Relationship to ISA conditions can be determined by entering the chart with a known altitude and temperature. TRUE OUTSIDE AIR TEMPERATURE - M7015_0.AI...
  • Page 362 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA DETERMINATION OF SPEED and TEMPERATURE CORRECTION Figure 2 allows true values of Mach number, airspeed, and outside air temperature to be determined from indicated values of airspeed, altitude and temperature.
  • Page 363 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA NOTE: Refer to the Airplane Flight Manual for maximum altitude limitation. Figure 2 Speed and Temperature Correction Page 1-6 Sub-section 1 Pilot’s Operating Manual Revision A1: Nov, 2002 GENERAL...
  • Page 364 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA CEILING DATA Table 1 MAXIMUM CRUISE ALTITUDE ° TEMPERATURE RELATIVE TO ISA WEIGHT lb MAXIMUM CRUISE ALTITUDE ft 27,000 40,600 40,400 39,800 39,100 38,300 37,400 36,400 34,300 26,000 41,000...
  • Page 365 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA CEILING DATA Table 3 MAXIMUM TAKE-OFF WEIGHT for CRUISE ALTITUDE ° TEMPERATURE RELATIVE TO ISA CRUISE MAXIMUM TAKE-OFF WEIGHT lb ALTITUDE ft 35,000 28,000 36,000 27,100 37,000 27,500 25,600...
  • Page 366 Pro Line 21 Section - IV FLIGHT PLANNING DATA Sub-section 2 PREFLIGHT Table of Contents Page INTRODUCTION ..................2-3 Figure 1 - Definitions and Terms for Various Phases of Flight ..... 2-5 FUEL LOADING PLAN and WORKED EXAMPLE........2-6 FUEL LOADING PLAN ................2-6 WORKED EXAMPLE................
  • Page 367 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA Intentionally left blank Page 2-2 Sub-section 2 Pilot’s Operating Manual Original Issue: Feb, 2002 PREFLIGHT...
  • Page 368 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA INTRODUCTION The data in this Sub-section allows the determination of total time and fuel required, using one of the three standard procedures: • High speed • Intermediate • Long Range Definitions and terms used for referring to the various phases of the flight are illustrated on Figure 1.
  • Page 369 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA Intentionally left blank Page 2-4 Sub-section 2 Pilot’s Operating Manual Original Issue: Feb, 2002 PREFLIGHT...
  • Page 370 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA DESCENT CRUISE CLIMB Figure 1 Definitions and Terms for Various Phases of Flight Page 2-5 Pilot’s Operating Manual Sub-section 2 Original Issue: Feb, 2002 PREFLIGHT...
  • Page 371 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA FUEL LOADING PLAN and WORKED EXAMPLE FUEL LOADING PLAN A fuel loading plan is an essential aid to flight planning. The following plan, recommended by Raytheon Aircraft Company, is provided together with a worked example illustrating its use in pre-flight planning.
  • Page 372 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA FUEL LOADING PLAN Trip Date: From: Destination: Alternate: ..................................... Part 1 PERMISSIBLE WEIGHTS lb Part 3B FLIGHT PLAN Weights lb Part 4 FUEL SUMMARY (from AFM)
  • Page 373 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA Intentionally left blank Sub-section 2 Page 2-8 Pilot’s Operating Manual PREFLIGHT Initial Issue: Feb, 2002...
  • Page 374 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA WORKED EXAMPLE The pages that follow contain a worked example using the FUEL LOADING PLAN. The example is based on the flight profile in Figure 1. The reader is progressively guided through the Parts of the FUEL LOADING PLAN with text describing each Part before moving to the next Part.
  • Page 375 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA CALCULATION Part 1 - PERMISSIBLE WEIGHTS (from AFM) Permissible Take-off Weight Temperature ° C = 5 ( ° F -32) = 19° C Since there are no obstacles the permissible take-off weight will be the lowest of: 1.
  • Page 376 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA Permissible Landing Weight at Alternate Temperature........86 ° F = 30° C. Maximum Landing Weight ....23,350 lb. WAT Limitation ........ 25,930 lb. Field Length Limitation (wet)... 22,350 lb.
  • Page 377 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA Part 2 - ZERO FUEL WEIGHT Data for this part is obtained from Section 6 (Weight and Balance) of the Airplane Flight Manual. Operating Weight A typical Operating Weight is defined in the Weight and Balance section of the AFM and consists of the...
  • Page 378 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA Part 3A - FLIGHT PLAN DISTANCES If there is a headwind or tailwind component, then an Equivalent Still Air Distance (ESAD) must be estimated for the sector from the departure airfield to the destination, and for diversion from the destination to the alternate airfield.
  • Page 379 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA Part 3A of the FUEL LOADING PLAN may now be completed. Part 3A - FLIGHT PLAN DISTANCES Sector Diversion 1900 Distance nm Distance nm Still Air Time - minutes Still Air Time - minutes Mean Still Air Speed kts.
  • Page 380 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA Part 3B FLIGHT PLAN Fuels and Times The total fuel quantity required is built up starting at the zero fuel weight and moving through the flight profile (Figure 1) in the reverse direction adding fuel for each phase until a take-off weight is obtained.
  • Page 381 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA For the required arrival weight of 18,329 lb the values will be: Time = 257 min. Fuel = 6815 lb NOTE: This fuel may be reduced by 30 lb because the departure airfield is at 2000 ft altitude.
  • Page 382 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA Part 4 - FUEL SUMMARY 100 lb Approach 50 lb Taxi-in 711 lb Diversion 568 lb Holding Additional Reserves (if required) 6785 lb Sector 100 lb Taxi-out 8314 lb...
  • Page 383 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA Intentionally left blank Page 2-18 Sub-section 2 Pilot’s Operating Manual Original Issue: Feb, 2002 PREFLIGHT...
  • Page 384 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA EQUIVALENT STILL AIR DISTANCE (ESAD) ALLOWANCES and RESERVE FUEL When a Sector or Diversion is to be flown in other than zero wind conditions it will be necessary to estimate an Equivalent Still Air distance (ESAD) for purposes of determining the fuel required.
  • Page 385 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA END ALLOWANCES The following fuel allowances may be used: • Engine start ....20 lb for both engines. • Taxi........ 10 lb per minute pre takeoff or post landing.
  • Page 386 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA Additional Holding Allowance On some routes an additional holding allowance will be needed at the destination. EN ROUTE ALLOWANCE A contingency allowance, usually in the form of a percentage of sector fuel, may be added to the reserves.
  • Page 387 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA EQUIVALENT STILL AIR DISTANCE Tabulated Data 350 kt TAS Sector Distance 50 - 1200 nm HEADWIND kt SECTOR DIST 1013 917 1105 1000 913 1197 1083 989 1289 1167 1065 980...
  • Page 388 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA EQUIVALENT STILL AIR DISTANCE Tabulated Data 350 kt TAS Sector Distance 50 - 1200 nm TAILWIND kt SECTOR DIST 100 120 292 285 286 275 778 745 1000 1050...
  • Page 389 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA EQUIVALENT STILL AIR DISTANCE Tabulated Data 350 kt TAS Sector Distance 1250 - 2500 nm HEADWIND kt SECTOR DIST 1250 2303 2083 1902 1750 1683 1620 1563 1509 1458 1411 1367 1326 1287...
  • Page 390 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA EQUIVALENT STILL AIR DISTANCE Tabulated Data 350 kt TAS Sector Distance 1250 - 2500 nm TAILWIND kt SECTOR DIST 100 120 1215 1182 1151 1122 1094 1067 1042 1017 994...
  • Page 391 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA EQUIVALENT STILL AIR DISTANCE Tabulated Data 400 kt TAS Sector Distance 50 - 1350 nm HEADWIND kt SECTOR DIST 118 114 176 171 235 229 294 286 353 343...
  • Page 392 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA EQUIVALENT STILL AIR DISTANCE Tabulated Data 400 kt TAS Sector Distance 50 - 1350 nm TAILWIND kt SECTOR DIST 100 120 1000 1050 1024 1000 977 1073 1048 1023 1000 978...
  • Page 393 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA EQUIVALENT STILL AIR DISTANCE Tabulated Data 400 kt TAS Sector Distance 1400 - 3000 nm HEADWIND kt SECTOR DIST 1400 2333 2154 2000 1867 1806 1750 1697 1647 1600 1556 1514 1474 1436...
  • Page 394 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA EQUIVALENT STILL AIR DISTANCE Tabulated Data 400 kt TAS Sector Distance 1400 - 3000 nm TAILWIND kt SECTOR DIST 100 120 1400 1366 1333 1302 1273 1244 1217 1191 1167 1143 1120 1077 1037 1000...
  • Page 395 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA EQUIVALENT STILL AIR DISTANCE Tabulated Data 450 kt TAS Sector Distance 50 - 1350 nm HEADWIND kt SECTOR DIST 1009 944 1086 1016 955 1164 1089 1023 964 1241 1161 1091 1029 1000 973...
  • Page 396 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA EQUIVALENT STILL AIR DISTANCE Tabulated Data 450 kt TAS Sector Distance 50 - 1350 nm TAILWIND kt SECTOR DIST 100 120 118 114 158 153 197 191 237 229...
  • Page 397 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA EQUIVALENT STILL AIR DISTANCE Tabulated Data 450 kt TAS Sector Distance 1400 - 3000 nm HEADWIND kt SECTOR DIST 1400 2172 2032 1909 1800 1750 1703 1658 1615 1575 1537 1500 1465 1432...
  • Page 398 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA EQUIVALENT STILL AIR DISTANCE Tabulated Data 450 kt TAS Sector Distance 1400 - 3000 nm TAILWIND kt SECTOR DIST 100 120 1400 1370 1340 1313 1286 1260 1235 1212 1189 1167 1145 1105 1068 1033...
  • Page 399 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA Intentionally left blank Page 2-34 Sub-section 2 Pilot’s Operating Manual PREFLIGHT Original Issue: Feb, 2002...
  • Page 400 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA SECTOR TIME and FUEL INTRODUCTION Sector time and fuel are tabulated against air distance and cruise altitude. The tables cover a range of arrival weights and en-route temperatures with data provided for three procedures as follows: •...
  • Page 401 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA SECTOR TIME and FUEL - HIGH SPEED PROCEDURE INTRODUCTION High Speed Procedure is defined as follows: • Normal Climb. • Cruise at V or Maximum Cruise Thrust whichever is slower.
  • Page 402 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA HIGH SPEED PROCEDURE ISA - 15 C Low Altitude Arrival Weight 17,000 lb ALTITUDE 8000 ft 10,000 ft 15,000 ft 19,000 ft SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME...
  • Page 403 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA HIGH SPEED PROCEDURE ISA - 15 C Low Altitude Arrival Weight 17,000 lb 21,000 ft 23,000 ft 25,000 ft 27,000 ft ALTITUDE SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME...
  • Page 404 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA HIGH SPEED PROCEDURE ISA - 15 C Low Altitude Arrival Weight 20,000 lb ALTITUDE 8000 ft 10,000 ft 15,000 ft 19,000 ft SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME...
  • Page 405 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA HIGH SPEED PROCEDURE ISA - 15 C Low Altitude Arrival Weight 20,000 lb 21,000 ft 23,000 ft 25,000 ft 27,000 ft ALTITUDE SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME...
  • Page 406 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA HIGH SPEED PROCEDURE ISA - 15 C Low Altitude Arrival Weight 23,000 lb ALTITUDE 8000 ft 10,000 ft 15,000 ft 19,000 ft SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME...
  • Page 407 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA HIGH SPEED PROCEDURE ISA - 15 C Low Altitude Arrival Weight 23,000 lb 21,000 ft 23,000 ft 25,000 ft 27,000 ft ALTITUDE SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME...
  • Page 408 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA HIGH SPEED PROCEDURE ISA - 15 C High Altitude Arrival Weight 17,000 lb ALTITUDE 29,000 ft 31,000 ft 33,000 ft 35,000 ft SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME...
  • Page 409 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA HIGH SPEED PROCEDURE ISA - 15 C High Altitude Arrival Weight 17,000 lb 37,000 ft 39,000 ft 41,000 ft ALTITUDE SECTOR SECTOR SECTOR TIME FUEL TIME FUEL TIME FUEL...
  • Page 410 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA HIGH SPEED PROCEDURE ISA - 15 C High Altitude Arrival Weight 20,000 lb ALTITUDE 29,000 ft 31,000 ft 33,000 ft 35,000 ft SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME...
  • Page 411 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA HIGH SPEED PROCEDURE ISA - 15 C High Altitude Arrival Weight 20,000 lb 37,000 ft 39,000 ft 41,000 ft ALTITUDE SECTOR SECTOR SECTOR TIME FUEL TIME FUEL TIME FUEL...
  • Page 412 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA HIGH SPEED PROCEDURE ISA - 15 C High Altitude Arrival Weight 23,000 lb ALTITUDE 29,000 ft 31,000 ft 33,000 ft 35,000 ft SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME...
  • Page 413 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA HIGH SPEED PROCEDURE ISA - 15 C High Altitude Arrival Weight 23,000 lb 37,000 ft 39,000 ft 41,000 ft ALTITUDE SECTOR SECTOR SECTOR TIME FUEL TIME FUEL TIME FUEL...
  • Page 414 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA HIGH SPEED PROCEDURE ISA - 10 C Low Altitude Arrival Weight 17,000 lb ALTITUDE 8000 ft 10,000 ft 15,000 ft 19,000 ft SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME...
  • Page 415 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA HIGH SPEED PROCEDURE ISA - 10 C Low Altitude Arrival Weight 17,000 lb 21,000 ft 23,000 ft 25,000 ft 27,000 ft ALTITUDE SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME...
  • Page 416 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA HIGH SPEED PROCEDURE ISA - 10 C Low Altitude Arrival Weight 20,000 lb ALTITUDE 8000 ft 10,000 ft 15,000 ft 19,000 ft SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME...
  • Page 417 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA HIGH SPEED PROCEDURE ISA - 10 C Low Altitude Arrival Weight 20,000 lb 21,000 ft 23,000 ft 25,000 ft 27,000 ft ALTITUDE SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME...
  • Page 418 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA HIGH SPEED PROCEDURE ISA - 10 C Low Altitude Arrival Weight 23,000 lb ALTITUDE 8000 ft 10,000 ft 15,000 ft 19,000 ft SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME...
  • Page 419 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA HIGH SPEED PROCEDURE ISA - 10 C Low Altitude Arrival Weight 23,000 lb 21,000 ft 23,000 ft 25,000 ft 27,000 ft ALTITUDE SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME...
  • Page 420 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA HIGH SPEED PROCEDURE ISA - 10 C High Altitude Arrival Weight 17,000 lb ALTITUDE 29,000 ft 31,000 ft 33,000 ft 35,000 ft SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME...
  • Page 421 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA HIGH SPEED PROCEDURE ISA - 10 C High Altitude Arrival Weight 17,000 lb 37,000 ft 39,000 ft 41,000 ft ALTITUDE SECTOR SECTOR SECTOR TIME FUEL TIME FUEL TIME FUEL...
  • Page 422 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA HIGH SPEED PROCEDURE ISA - 10 C High Altitude Arrival Weight 20,000 lb ALTITUDE 29,000 ft 31,000 ft 33,000 ft 35,000 ft SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME...
  • Page 423 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA HIGH SPEED PROCEDURE ISA - 10 C High Altitude Arrival Weight 20,000 lb 37,000 ft 39,000 ft 41,000 ft ALTITUDE SECTOR SECTOR SECTOR TIME FUEL TIME FUEL TIME FUEL...
  • Page 424 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA HIGH SPEED PROCEDURE ISA - 10 C High Altitude Arrival Weight 23,000 lb ALTITUDE 29,000 ft 31,000 ft 33,000 ft 35,000 ft SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME...
  • Page 425 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA HIGH SPEED PROCEDURE ISA - 10 C High Altitude Arrival Weight 23,000 lb 37,000 ft 39,000 ft 41,000 ft ALTITUDE SECTOR SECTOR SECTOR TIME FUEL TIME FUEL TIME FUEL...
  • Page 426 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA HIGH SPEED PROCEDURE Low Altitude Arrival Weight 17,000 lb ALTITUDE 8000 ft 10,000 ft 15,000 ft 19,000 ft SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME FUEL TIME FUEL TIME...
  • Page 427 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA HIGH SPEED PROCEDURE Low Altitude Arrival Weight 17,000 lb 21,000 ft 23,000 ft 25,000 ft 27,000 ft ALTITUDE SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME FUEL TIME FUEL TIME...
  • Page 428 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA HIGH SPEED PROCEDURE Low Altitude Arrival Weight 20,000 lb ALTITUDE 8000 ft 10,000 ft 15,000 ft 19,000 ft SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME FUEL TIME FUEL TIME...
  • Page 429 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA HIGH SPEED PROCEDURE Low Altitude Arrival Weight 20,000 lb 21,000 ft 23,000 ft 25,000 ft 27,000 ft ALTITUDE SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME FUEL TIME FUEL TIME...
  • Page 430 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA HIGH SPEED PROCEDURE Low Altitude Arrival Weight 23,000 lb ALTITUDE 8000 ft 10,000 ft 15,000 ft 19,000 ft SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME FUEL TIME FUEL TIME...
  • Page 431 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA HIGH SPEED PROCEDURE Low Altitude Arrival Weight 23,000 lb 21,000 ft 23,000 ft 25,000 ft 27,000 ft ALTITUDE SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME FUEL TIME FUEL TIME...
  • Page 432 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA HIGH SPEED PROCEDURE High Altitude Arrival Weight 17,000 lb ALTITUDE 29,000 ft 31,000 ft 33,000 ft 35,000 ft SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME FUEL TIME FUEL TIME...
  • Page 433 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA HIGH SPEED PROCEDURE High Altitude Arrival Weight 17,000 lb 37,000 ft 39,000 ft 41,000 ft ALTITUDE SECTOR SECTOR SECTOR TIME FUEL TIME FUEL TIME FUEL AIR DIST 1365 1288...
  • Page 434 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA HIGH SPEED PROCEDURE High Altitude Arrival Weight 20,000 lb ALTITUDE 29,000 ft 31,000 ft 33,000 ft 35,000 ft SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME FUEL TIME FUEL TIME...
  • Page 435 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA HIGH SPEED PROCEDURE High Altitude Arrival Weight 20,000 lb 37,000 ft 39,000 ft 41,000 ft ALTITUDE SECTOR SECTOR SECTOR TIME FUEL TIME FUEL TIME FUEL AIR DIST 1413 1342...
  • Page 436 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA HIGH SPEED PROCEDURE High Altitude Arrival Weight 23,000 lb ALTITUDE 29,000 ft 31,000 ft 33,000 ft 35,000 ft SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME FUEL TIME FUEL TIME...
  • Page 437 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA HIGH SPEED PROCEDURE High Altitude Arrival Weight 23,000 lb 37,000 ft 39,000 ft 41,000 ft ALTITUDE SECTOR SECTOR SECTOR TIME FUEL TIME FUEL TIME FUEL AIR DIST 1041 1022...
  • Page 438 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA HIGH SPEED PROCEDURE ISA + 10 C Low Altitude Arrival Weight 17,000 lb ALTITUDE 8000 ft 10,000 ft 15,000 ft 19,000 ft SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME...
  • Page 439 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA HIGH SPEED PROCEDURE ISA + 10 C Low Altitude Arrival Weight 17,000 lb 21,000 ft 23,000 ft 25,000 ft 27,000 ft ALTITUDE SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME...
  • Page 440 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA HIGH SPEED PROCEDURE ISA + 10 C Low Altitude Arrival Weight 20,000 lb ALTITUDE 8000 ft 10,000 ft 15,000 ft 19,000 ft SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME...
  • Page 441 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA HIGH SPEED PROCEDURE ISA + 10 C Low Altitude Arrival Weight 20,000 lb 21,000 ft 23,000 ft 25,000 ft 27,000 ft ALTITUDE SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME...
  • Page 442 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA HIGH SPEED PROCEDURE ISA + 10 C Low Altitude Arrival Weight 23,000 lb ALTITUDE 8000 ft 10,000 ft 15,000 ft 19,000 ft SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME...
  • Page 443 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA HIGH SPEED PROCEDURE ISA + 10 C Low Altitude Arrival Weight 23,000 lb 21,000 ft 23,000 ft 25,000 ft 27,000 ft ALTITUDE SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME...
  • Page 444 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA HIGH SPEED PROCEDURE ISA + 10 C High Altitude Arrival Weight 17,000 lb ALTITUDE 29,000 ft 31,000 ft 33,000 ft 35,000 ft SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME...
  • Page 445 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA HIGH SPEED PROCEDURE ISA + 10 C High Altitude Arrival Weight 17,000 lb 37,000 ft 39,000 ft 41,000 ft ALTITUDE SECTOR SECTOR SECTOR TIME FUEL TIME FUEL TIME FUEL...
  • Page 446 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA HIGH SPEED PROCEDURE ISA + 10 C High Altitude Arrival Weight 20,000 lb ALTITUDE 29,000 ft 31,000 ft 33,000 ft 35,000 ft SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME...
  • Page 447 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA HIGH SPEED PROCEDURE ISA + 10 C High Altitude Arrival Weight 20,000 lb 37,000 ft 39,000 ft 41,000 ft ALTITUDE SECTOR SECTOR SECTOR TIME FUEL TIME FUEL TIME FUEL...
  • Page 448 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA HIGH SPEED PROCEDURE ISA + 10 C High Altitude Arrival Weight 23,000 lb ALTITUDE 29,000 ft 31,000 ft 33,000 ft 35,000 ft SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME...
  • Page 449 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA HIGH SPEED PROCEDURE ISA + 10 C High Altitude Arrival Weight 23,000 lb 37,000 ft 39,000 ft 41,000 ft ALTITUDE SECTOR SECTOR SECTOR TIME FUEL TIME FUEL TIME FUEL...
  • Page 450 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA HIGH SPEED PROCEDURE ISA + 20 C Low Altitude Arrival Weight 17,000 lb ALTITUDE 8000 ft 10,000 ft 15,000 ft 19,000 ft SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME...
  • Page 451 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA HIGH SPEED PROCEDURE ISA + 20 C Low Altitude Arrival Weight 17,000 lb 21,000 ft 23,000 ft 25,000 ft 27,000 ft ALTITUDE SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME...
  • Page 452 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA HIGH SPEED PROCEDURE ISA + 20 C Low Altitude Arrival Weight 20,000 lb ALTITUDE 8000 ft 10,000 ft 15,000 ft 19,000 ft SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME...
  • Page 453 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA HIGH SPEED PROCEDURE ISA + 20 C Low Altitude Arrival Weight 20,000 lb 21,000 ft 23,000 ft 25,000 ft 27,000 ft ALTITUDE SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME...
  • Page 454 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA HIGH SPEED PROCEDURE ISA + 20 C Low Altitude Arrival Weight 23,000 lb ALTITUDE 8000 ft 10,000 ft 15,000 ft 19,000 ft SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME...
  • Page 455 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA HIGH SPEED PROCEDURE ISA + 20 C Low Altitude Arrival Weight 23,000 lb 21,000 ft 23,000 ft 25,000 ft 27,000 ft ALTITUDE SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME...
  • Page 456 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA HIGH SPEED PROCEDURE ISA + 20 C High Altitude Arrival Weight 17,000 lb ALTITUDE 29,000 ft 31,000 ft 33,000 ft 35,000 ft SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME...
  • Page 457 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA HIGH SPEED PROCEDURE ISA + 20 C High Altitude Arrival Weight 17,000 lb 37,000 ft 39,000 ft 41,000 ft ALTITUDE SECTOR SECTOR SECTOR TIME FUEL TIME FUEL TIME FUEL...
  • Page 458 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA HIGH SPEED PROCEDURE ISA + 20 C High Altitude Arrival Weight 20,000 lb ALTITUDE 29,000 ft 31,000 ft 33,000 ft 35,000 ft SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME...
  • Page 459 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA HIGH SPEED PROCEDURE ISA + 20 C High Altitude Arrival Weight 20,000 lb 37,000 ft 39,000 ft 41,000 ft ALTITUDE SECTOR SECTOR SECTOR TIME FUEL TIME FUEL TIME FUEL...
  • Page 460 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA HIGH SPEED PROCEDURE ISA + 20 C High Altitude Arrival Weight 23,000 lb ALTITUDE 29,000 ft 31,000 ft 33,000 ft 35,000 ft SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME...
  • Page 461 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA HIGH SPEED PROCEDURE ISA + 20 C High Altitude Arrival Weight 23,000 lb 37,000 ft 39,000 ft 41,000 ft ALTITUDE SECTOR SECTOR SECTOR TIME FUEL TIME FUEL TIME FUEL...
  • Page 462 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA SECTOR TIME and FUEL - INTERMEDIATE PROCEDURE INTRODUCTION Intermediate Procedure is defined as follows: • Normal Climb. • Cruise at 280 KIAS/0.75 IMN or Maximum Cruise Thrust, whichever is slower.
  • Page 463 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA INTERMEDIATE PROCEDURE ISA - 15 C Low Altitude Arrival Weight 17,000 lb ALTITUDE 5000 ft 10,000 ft 15,000 ft 19,000 ft SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME FUEL...
  • Page 464 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA INTERMEDIATE PROCEDURE ISA - 15 C Low Altitude Arrival Weight 17,000 lb 21,000 ft 23,000 ft 25,000 ft 27,000 ft ALTITUDE SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME FUEL...
  • Page 465 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA INTERMEDIATE PROCEDURE ISA - 15 C Low Altitude Arrival Weight 20,000 lb ALTITUDE 5000 ft 10,000 ft 15,000 ft 19,000 ft SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME FUEL...
  • Page 466 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA INTERMEDIATE PROCEDURE ISA - 15 C Low Altitude Arrival Weight 20,000 lb 21,000 ft 23,000 ft 25,000 ft 27,000 ft ALTITUDE SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME FUEL...
  • Page 467 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA INTERMEDIATE PROCEDURE ISA - 15 C Low Altitude Arrival Weight 23,000 lb ALTITUDE 5000 ft 10,000 ft 15,000 ft 19,000 ft SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME FUEL...
  • Page 468 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA INTERMEDIATE PROCEDURE ISA - 15 C Low Altitude Arrival Weight 23,000 lb 21,000 ft 23,000 ft 25,000 ft 27,000 ft ALTITUDE SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME FUEL...
  • Page 469 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA INTERMEDIATE PROCEDURE ISA - 15 C High Altitude Arrival Weight 17,000 lb ALTITUDE 29,000 ft 31,000 ft 33,000 ft 35,000 ft SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME FUEL...
  • Page 470 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA INTERMEDIATE PROCEDURE ISA - 15 C High Altitude Arrival Weight 17,000 lb 37,000 ft 39,000 ft 41,000 ft ALTITUDE SECTOR SECTOR SECTOR TIME FUEL TIME FUEL TIME FUEL AIR DIST...
  • Page 471 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA INTERMEDIATE PROCEDURE ISA - 15 C High Altitude Arrival Weight 20,000 lb ALTITUDE 29,000 ft 31,000 ft 33,000 ft 35,000 ft SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME FUEL...
  • Page 472 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA INTERMEDIATE PROCEDURE ISA - 15 C High Altitude Arrival Weight 20,000 lb 37,000 ft 39,000 ft 41,000 ft ALTITUDE SECTOR SECTOR SECTOR TIME FUEL TIME FUEL TIME FUEL AIR DIST...
  • Page 473 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA INTERMEDIATE PROCEDURE ISA - 15 C High Altitude Arrival Weight 23,000 lb ALTITUDE 29,000 ft 31,000 ft 33,000 ft 35,000 ft SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME FUEL...
  • Page 474 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA INTERMEDIATE PROCEDURE ISA - 15 C High Altitude Arrival Weight 23,000 lb 37,000 ft 39,000 ft 41,000 ft ALTITUDE SECTOR SECTOR SECTOR TIME FUEL TIME FUEL TIME FUEL AIR DIST...
  • Page 475 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA INTERMEDIATE PROCEDURE ISA - 10 C Low Altitude Arrival Weight 17,000 lb ALTITUDE 5000 ft 10,000 ft 15,000 ft 19,000 ft SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME FUEL...
  • Page 476 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA INTERMEDIATE PROCEDURE ISA - 10 C Low Altitude Arrival Weight 17,000 lb 21,000 ft 23,000 ft 25,000 ft 27,000 ft ALTITUDE SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME FUEL...
  • Page 477 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA INTERMEDIATE PROCEDURE ISA - 10 C Low Altitude Arrival Weight 20,000 lb ALTITUDE 5000 ft 10,000 ft 15,000 ft 19,000 ft SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME FUEL...
  • Page 478 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA INTERMEDIATE PROCEDURE ISA - 10 C Low Altitude Arrival Weight 20,000 lb 21,000 ft 23,000 ft 25,000 ft 27,000 ft ALTITUDE SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME FUEL...
  • Page 479 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA INTERMEDIATE PROCEDURE ISA - 10 C Low Altitude Arrival Weight 23,000 lb ALTITUDE 5000 ft 10,000 ft 15,000 ft 19,000 ft SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME FUEL...
  • Page 480 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA INTERMEDIATE PROCEDURE ISA - 10 C Low Altitude Arrival Weight 23,000 lb 21,000 ft 23,000 ft 25,000 ft 27,000 ft ALTITUDE SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME FUEL...
  • Page 481 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA INTERMEDIATE PROCEDURE ISA - 10 C High Altitude Arrival Weight 17,000 lb ALTITUDE 29,000 ft 31,000 ft 33,000 ft 35,000 ft SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME FUEL...
  • Page 482 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA INTERMEDIATE PROCEDURE ISA - 10 C High Altitude Arrival Weight 17,000 lb 37,000 ft 39,000 ft 41,000 ft ALTITUDE SECTOR SECTOR SECTOR TIME FUEL TIME FUEL TIME FUEL AIR DIST...
  • Page 483 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA INTERMEDIATE PROCEDURE ISA - 10 C High Altitude Arrival Weight 20,000 lb ALTITUDE 29,000 ft 31,000 ft 33,000 ft 35,000 ft SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME FUEL...
  • Page 484 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA INTERMEDIATE PROCEDURE ISA - 10 C High Altitude Arrival Weight 20,000 lb 37,000 ft 39,000 ft 41,000 ft ALTITUDE SECTOR SECTOR SECTOR TIME FUEL TIME FUEL TIME FUEL AIR DIST...
  • Page 485 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA INTERMEDIATE PROCEDURE ISA - 10 C High Altitude Arrival Weight 23,000 lb ALTITUDE 29,000 ft 31,000 ft 33,000 ft 35,000 ft SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME FUEL...
  • Page 486 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA INTERMEDIATE PROCEDURE ISA - 10 C High Altitude Arrival Weight 23,000 lb 37,000 ft 39,000 ft 41,000 ft ALTITUDE SECTOR SECTOR SECTOR TIME FUEL TIME FUEL TIME FUEL AIR DIST...
  • Page 487 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA INTERMEDIATE PROCEDURE Low Altitude Arrival Weight 17,000 lb ALTITUDE 5000 ft 10,000 ft 15,000 ft 19,000 ft SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME FUEL TIME FUEL TIME FUEL...
  • Page 488 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA INTERMEDIATE PROCEDURE Low Altitude Arrival Weight 17,000 lb 21,000 ft 23,000 ft 25,000 ft 27,000 ft ALTITUDE SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME FUEL TIME FUEL TIME FUEL...
  • Page 489 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA INTERMEDIATE PROCEDURE Low Altitude Arrival Weight 20,000 lb ALTITUDE 5000 ft 10,000 ft 15,000 ft 19,000 ft SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME FUEL TIME FUEL TIME FUEL...
  • Page 490 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA INTERMEDIATE PROCEDURE Low Altitude Arrival Weight 20,000 lb 21,000 ft 23,000 ft 25,000 ft 27,000 ft ALTITUDE SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME FUEL TIME FUEL TIME FUEL...
  • Page 491 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA INTERMEDIATE PROCEDURE Low Altitude Arrival Weight 23,000 lb ALTITUDE 5000 ft 10,000 ft 15,000 ft 19,000 ft SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME FUEL TIME FUEL TIME FUEL...
  • Page 492 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA INTERMEDIATE PROCEDURE Low Altitude Arrival Weight 23,000 lb 21,000 ft 23,000 ft 25,000 ft 27,000 ft ALTITUDE SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME FUEL TIME FUEL TIME FUEL...
  • Page 493 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA INTERMEDIATE PROCEDURE High Altitude Arrival Weight 17,000 lb ALTITUDE 29,000 ft 31,000 ft 33,000 ft 35,000 ft SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME FUEL TIME FUEL TIME FUEL...
  • Page 494 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA INTERMEDIATE PROCEDURE High Altitude Arrival Weight 17,000 lb 37,000 ft 39,000 ft 41,000 ft ALTITUDE SECTOR SECTOR SECTOR TIME FUEL TIME FUEL TIME FUEL AIR DIST 1214 1185 1168...
  • Page 495 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA INTERMEDIATE PROCEDURE High Altitude Arrival Weight 20,000 lb ALTITUDE 29,000 ft 31,000 ft 33,000 ft 35,000 ft SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME FUEL TIME FUEL TIME FUEL...
  • Page 496 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA INTERMEDIATE PROCEDURE High Altitude Arrival Weight 20,000 lb 37,000 ft 39,000 ft 41,000 ft ALTITUDE SECTOR SECTOR SECTOR TIME FUEL TIME FUEL TIME FUEL AIR DIST 1302 1280 1271...
  • Page 497 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA INTERMEDIATE PROCEDURE High Altitude Arrival Weight 23,000 lb ALTITUDE 29,000 ft 31,000 ft 33,000 ft 35,000 ft SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME FUEL TIME FUEL TIME FUEL...
  • Page 498 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA INTERMEDIATE PROCEDURE High Altitude Arrival Weight 23,000 lb 37,000 ft 39,000 ft 41,000 ft ALTITUDE SECTOR SECTOR SECTOR TIME FUEL TIME FUEL TIME FUEL AIR DIST 1026 1023 1391...
  • Page 499 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA INTERMEDIATE PROCEDURE ISA + 10 C Low Altitude Arrival Weight 17,000 lb ALTITUDE 5000 ft 10,000 ft 15,000 ft 19,000 ft SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME FUEL...
  • Page 500 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA INTERMEDIATE PROCEDURE ISA + 10 C Low Altitude Arrival Weight 17,000 lb 21,000 ft 23,000 ft 25,000 ft 27,000 ft ALTITUDE SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME FUEL...
  • Page 501 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA INTERMEDIATE PROCEDURE ISA + 10 C Low Altitude Arrival Weight 20,000 lb ALTITUDE 5000 ft 10,000 ft 15,000 ft 19,000 ft SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME FUEL...
  • Page 502 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA INTERMEDIATE PROCEDURE ISA + 10 C Low Altitude Arrival Weight 20,000 lb 21,000 ft 23,000 ft 25,000 ft 27,000 ft ALTITUDE SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME FUEL...
  • Page 503 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA INTERMEDIATE PROCEDURE ISA + 10 C Low Altitude Arrival Weight 23,000 lb ALTITUDE 5000 ft 10,000 ft 15,000 ft 19,000 ft SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME FUEL...
  • Page 504 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA INTERMEDIATE PROCEDURE ISA + 10 C Low Altitude Arrival Weight 23,000 lb 21,000 ft 23,000 ft 25,000 ft 27,000 ft ALTITUDE SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME FUEL...
  • Page 505 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA INTERMEDIATE PROCEDURE ISA + 10 C High Altitude Arrival Weight 17,000 lb ALTITUDE 29,000 ft 31,000 ft 33,000 ft 35,000 ft SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME FUEL...
  • Page 506 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA INTERMEDIATE PROCEDURE ISA + 10 C High Altitude Arrival Weight 17,000 lb 37,000 ft 39,000 ft 41,000 ft ALTITUDE SECTOR SECTOR SECTOR TIME FUEL TIME FUEL TIME FUEL AIR DIST...
  • Page 507 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA INTERMEDIATE PROCEDURE ISA + 10 C High Altitude Arrival Weight 20,000 lb ALTITUDE 29,000 ft 31,000 ft 33,000 ft 35,000 ft SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME FUEL...
  • Page 508 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA INTERMEDIATE PROCEDURE ISA + 10 C High Altitude Arrival Weight 20,000 lb 37,000 ft 39,000 ft 41,000 ft ALTITUDE SECTOR SECTOR SECTOR TIME FUEL TIME FUEL TIME FUEL AIR DIST...
  • Page 509 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA INTERMEDIATE PROCEDURE ISA + 10 C High Altitude Arrival Weight 23,000 lb ALTITUDE 29,000 ft 31,000 ft 33,000 ft 35,000 ft SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME FUEL...
  • Page 510 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA INTERMEDIATE PROCEDURE ISA + 10 C High Altitude Arrival Weight 23,000 lb 37,000 ft 39,000 ft 41,000 ft ALTITUDE SECTOR SECTOR SECTOR TIME FUEL TIME FUEL TIME FUEL AIR DIST...
  • Page 511 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA INTERMEDIATE PROCEDURE ISA + 20 C Low Altitude Arrival Weight 17,000 lb ALTITUDE 5000 ft 10,000 ft 15,000 ft 19,000 ft SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME FUEL...
  • Page 512 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA INTERMEDIATE PROCEDURE ISA + 20 C Low Altitude Arrival Weight 17,000 lb 21,000 ft 23,000 ft 25,000 ft 27,000 ft ALTITUDE SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME FUEL...
  • Page 513 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA INTERMEDIATE PROCEDURE ISA + 20 C Low Altitude Arrival Weight 20,000 lb ALTITUDE 5000 ft 10,000 ft 15,000 ft 19,000 ft SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME FUEL...
  • Page 514 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA INTERMEDIATE PROCEDURE ISA + 20 C Low Altitude Arrival Weight 20,000 lb 21,000 ft 23,000 ft 25,000 ft 27,000 ft ALTITUDE SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME FUEL...
  • Page 515 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA INTERMEDIATE PROCEDURE ISA + 20 C Low Altitude Arrival Weight 23,000 lb ALTITUDE 5000 ft 10,000 ft 15,000 ft 19,000 ft SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME FUEL...
  • Page 516 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA INTERMEDIATE PROCEDURE ISA + 20 C Low Altitude Arrival Weight 23,000 lb 21,000 ft 23,000 ft 25,000 ft 27,000 ft ALTITUDE SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME FUEL...
  • Page 517 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA INTERMEDIATE PROCEDURE ISA + 20 C High Altitude Arrival Weight 17,000 lb ALTITUDE 29,000 ft 31,000 ft 33,000 ft 35,000 ft SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME FUEL...
  • Page 518 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA INTERMEDIATE PROCEDURE ISA + 20 C High Altitude Arrival Weight 17,000 lb 37,000 ft 39,000 ft 41,000 ft ALTITUDE SECTOR SECTOR SECTOR TIME FUEL TIME FUEL TIME FUEL AIR DIST...
  • Page 519 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA INTERMEDIATE PROCEDURE ISA + 20 C High Altitude Arrival Weight 20,000 lb ALTITUDE 29,000 ft 31,000 ft 33,000 ft 35,000 ft SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME FUEL...
  • Page 520 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA INTERMEDIATE PROCEDURE ISA + 20 C High Altitude Arrival Weight 20,000 lb 37,000 ft 39,000 ft 41,000 ft ALTITUDE SECTOR SECTOR SECTOR TIME FUEL TIME FUEL TIME FUEL AIR DIST...
  • Page 521 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA INTERMEDIATE PROCEDURE ISA + 20 C High Altitude Arrival Weight 23,000 lb ALTITUDE 29,000 ft 31,000 ft 33,000 ft 35,000 ft SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME FUEL...
  • Page 522 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA INTERMEDIATE PROCEDURE ISA + 20 C High Altitude Arrival Weight 23,000 lb 37,000 ft 39,000 ft 41,000 ft ALTITUDE SECTOR SECTOR SECTOR TIME FUEL TIME FUEL TIME FUEL AIR DIST...
  • Page 523 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA Intentionally left blank Sub-section 2 Page 2-158 Pilot’s Operating Manual PREFLIGHT Original Issue: Feb, 2002...
  • Page 524 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA SECTOR TIME and FUEL - LONG RANGE PROCEDURE INTRODUCTION Long Range Procedure is defined as follows: • Normal Climb • Cruise at 230/220 KIAS/0.70 IMN or Maximum Cruise Thrust, whichever is slower.
  • Page 525 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA LONG RANGE PROCEDURE ISA - 15 C High Altitude Arrival Weight 17,000 lb ALTITUDE 29,000 ft 31,000 ft 33,000 ft 35,000 ft SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME...
  • Page 526 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA LONG RANGE PROCEDURE ISA - 15 C High Altitude Arrival Weight 17,000 lb 37,000 ft 39,000 ft 41,000 ft ALTITUDE SECTOR SECTOR SECTOR TIME FUEL TIME FUEL TIME FUEL...
  • Page 527 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA LONG RANGE PROCEDURE ISA - 15 C High Altitude Arrival Weight 20,000 lb ALTITUDE 29,000 ft 31,000 ft 33,000 ft 35,000 ft SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME...
  • Page 528 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA LONG RANGE PROCEDURE ISA - 15 C High Altitude Arrival Weight 20,000 lb 37,000 ft 39,000 ft 41,000 ft ALTITUDE SECTOR SECTOR SECTOR TIME FUEL TIME FUEL TIME FUEL...
  • Page 529 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA LONG RANGE PROCEDURE ISA - 15 C High Altitude Arrival Weight 23,000 lb ALTITUDE 29,000 ft 31,000 ft 33,000 ft 35,000 ft SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME...
  • Page 530 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA LONG RANGE PROCEDURE ISA - 15 C High Altitude Arrival Weight 23,000 lb 37,000 ft 39,000 ft 41,000 ft ALTITUDE SECTOR SECTOR SECTOR TIME FUEL TIME FUEL TIME FUEL...
  • Page 531 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA LONG RANGE PROCEDURE ISA - 10 C High Altitude Arrival Weight 17,000 lb ALTITUDE 29,000 ft 31,000 ft 33,000 ft 35,000 ft SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME...
  • Page 532 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA LONG RANGE PROCEDURE ISA - 10 C High Altitude Arrival Weight 17,000 lb 37,000 ft 39,000 ft 41,000 ft ALTITUDE SECTOR SECTOR SECTOR TIME FUEL TIME FUEL TIME FUEL...
  • Page 533 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA LONG RANGE PROCEDURE ISA - 10 C High Altitude Arrival Weight 20,000 lb ALTITUDE 29,000 ft 31,000 ft 33,000 ft 35,000 ft SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME...
  • Page 534 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA LONG RANGE PROCEDURE ISA - 10 C High Altitude Arrival Weight 20,000 lb 37,000 ft 39,000 ft 41,000 ft ALTITUDE SECTOR SECTOR SECTOR TIME FUEL TIME FUEL TIME FUEL...
  • Page 535 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA LONG RANGE PROCEDURE ISA - 10 C High Altitude Arrival Weight 23,000 lb ALTITUDE 29,000 ft 31,000 ft 33,000 ft 35,000 ft SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME...
  • Page 536 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA LONG RANGE PROCEDURE ISA - 10 C High Altitude Arrival Weight 23,000 lb 37,000 ft 39,000 ft 41,000 ft ALTITUDE SECTOR SECTOR SECTOR TIME FUEL TIME FUEL TIME FUEL...
  • Page 537 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA LONG RANGE PROCEDURE High Altitude Arrival Weight 17,000 lb ALTITUDE 29,000 ft 31,000 ft 33,000 ft 35,000 ft SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME FUEL TIME FUEL TIME...
  • Page 538 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA LONG RANGE PROCEDURE Arrival Weight 17,000 lb High Altitude 37,000 ft 39,000 ft 41,000 ft ALTITUDE SECTOR SECTOR SECTOR TIME FUEL TIME FUEL TIME FUEL AIR DIST 1163 1154...
  • Page 539 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA LONG RANGE PROCEDURE High Altitude Arrival Weight 20,000 lb ALTITUDE 29,000 ft 31,000 ft 33,000 ft 35,000 ft SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME FUEL TIME FUEL TIME...
  • Page 540 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA LONG RANGE PROCEDURE High Altitude Arrival Weight 20,000 lb 37,000 ft 39,000 ft 41,000 ft ALTITUDE SECTOR SECTOR SECTOR TIME FUEL TIME FUEL TIME FUEL AIR DIST 1255 1248...
  • Page 541 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA LONG RANGE PROCEDURE High Altitude Arrival Weight 23,000 lb ALTITUDE 29,000 ft 31,000 ft 33,000 ft 35,000 ft SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME FUEL TIME FUEL TIME...
  • Page 542 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA LONG RANGE PROCEDURE High Altitude Arrival Weight 23,000 lb 37,000 ft 39,000 ft 41,000 ft ALTITUDE SECTOR SECTOR SECTOR TIME FUEL TIME FUEL TIME FUEL AIR DIST 1017 1022...
  • Page 543 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA LONG RANGE PROCEDURE ISA +10 C High Altitude Arrival Weight 17,000 lb ALTITUDE 29,000 ft 31,000 ft 33,000 ft 35,000 ft SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME FUEL...
  • Page 544 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA LONG RANGE PROCEDURE ISA +10 C High Altitude Arrival Weight 17,000 lb 37,000 ft 39,000 ft 41,000 ft ALTITUDE SECTOR SECTOR SECTOR TIME FUEL TIME FUEL TIME FUEL AIR DIST...
  • Page 545 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA LONG RANGE PROCEDURE ISA +10 C High Altitude Arrival Weight 20,000 lb ALTITUDE 29,000 ft 31,000 ft 33,000 ft 35,000 ft SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME FUEL...
  • Page 546 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA LONG RANGE PROCEDURE ISA +10 C High Altitude Arrival Weight 20,000 lb 37,000 ft 39,000 ft 41,000 ft ALTITUDE SECTOR SECTOR SECTOR TIME FUEL TIME FUEL TIME FUEL AIR DIST...
  • Page 547 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA LONG RANGE PROCEDURE ISA +10 C High Altitude Arrival Weight 23,000 lb ALTITUDE 29,000 ft 31,000 ft 33,000 ft 35,000 ft SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME FUEL...
  • Page 548 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA LONG RANGE PROCEDURE ISA +10 C High Altitude Arrival Weight 23,000 lb 37,000 ft 39,000 ft 41,000 ft ALTITUDE SECTOR SECTOR SECTOR TIME FUEL TIME FUEL TIME FUEL AIR DIST...
  • Page 549 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA LONG RANGE PROCEDURE ISA +20 C High Altitude Arrival Weight 17,000 lb ALTITUDE 29,000 ft 31,000 ft 33,000 ft 35,000 ft SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME FUEL...
  • Page 550 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA LONG RANGE PROCEDURE ISA +20 C High Altitude Arrival Weight 17,000 lb 37,000 ft 39,000 ft 41,000 ft ALTITUDE SECTOR SECTOR SECTOR TIME FUEL TIME FUEL TIME FUEL AIR DIST...
  • Page 551 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA LONG RANGE PROCEDURE ISA +20 C High Altitude Arrival Weight 20,000 lb ALTITUDE 29,000 ft 31,000 ft 33,000 ft 35,000 ft SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME FUEL...
  • Page 552 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA LONG RANGE PROCEDURE ISA +20 C Arrival Weight 20,000 lb High Altitude 37,000 ft 39,000 ft 41,000 ft ALTITUDE SECTOR SECTOR SECTOR TIME FUEL TIME FUEL TIME FUEL AIR DIST...
  • Page 553 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA LONG RANGE PROCEDURE ISA + 20 C High Altitude Arrival Weight 23,000 lb ALTITUDE 29,000 ft 31,000 ft 33,000 ft 35,000 ft SECTOR SECTOR SECTOR SECTOR TIME FUEL TIME...
  • Page 554 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA LONG RANGE PROCEDURE ISA + 20 C High Altitude Arrival Weight 23,000 lb 37,000 ft 39,000 ft 41,000 ft ALTITUDE SECTOR SECTOR SECTOR TIME FUEL TIME FUEL TIME FUEL...
  • Page 555 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA Intentionally left blank Sub-section 2 Page 2-190 Pilot’s Operating Manual PREFLIGHT Original Issue: Feb, 2002...
  • Page 556 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA DIVERSION TIME and FUEL INTRODUCTION This Sub-section contains tabulated data for diversion times and fuels versus diversion distance and diversion cruise altitude. The tables cover a range of arrival weights for ISA conditions however, they also may be used for other temperatures since the effect of temperature on diversion times and fuel is negligible.
  • Page 557 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA DIVERSION TIME and FUEL Arrival Weight 17,000 lb ALTITUDE 5000 ft 10,000 ft 15,000 ft 19,000 ft DIVERSION DIVERSION DIVERSION DIVERSION TIME FUEL TIME FUEL TIME FUEL TIME FUEL...
  • Page 558 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA DIVERSION TIME and FUEL Arrival Weight 17,000 lb 21,000 ft 23,000 ft 25,000 ft 27,000 ft ALTITUDE DIVERSION DIVERSION DIVERSION DIVERSION TIME FUEL TIME FUEL TIME FUEL TIME FUEL...
  • Page 559 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA DIVERSION TIME and FUEL Arrival Weight 20,000 lb ALTITUDE 5000 ft 10,000 ft 15,000 ft 19,000 ft DIVERSION DIVERSION DIVERSION DIVERSION TIME FUEL TIME FUEL TIME FUEL TIME FUEL...
  • Page 560 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA DIVERSION TIME and FUEL Arrival Weight 20,000 lb 21,000 ft 23,000 ft 25,000 ft 27,000 ft ALTITUDE DIVERSION DIVERSION DIVERSION DIVERSION TIME FUEL TIME FUEL TIME FUEL TIME FUEL...
  • Page 561 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA DIVERSION TIME and FUEL Arrival Weight 23,000 lb ALTITUDE 5000 ft 10,000 ft 15,000 ft 19,000 ft DIVERSION DIVERSION DIVERSION DIVERSION TIME FUEL TIME FUEL TIME FUEL TIME FUEL...
  • Page 562 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA DIVERSION TIME and FUEL Arrival Weight 23,000 lb 21,000 ft 23,000 ft 25,000 ft 27,000 ft ALTITUDE DIVERSION DIVERSION DIVERSION DIVERSION TIME FUEL TIME FUEL TIME FUEL TIME FUEL...
  • Page 563 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA Intentionally left blank Sub-section 2 Page 2-198 Pilot’s Operating Manual PREFLIGHT Original Issue: Feb, 2002...
  • Page 564 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA HOLDING FUEL FLOW INTRODUCTION This Sub-section provides tabulated data for holding fuel flow versus weight and holding altitude. The data is provided for engine antice off and engine antice on. The fuel flows are calculated with the assumption that the holding is accomplished while flying circuits with 25 °...
  • Page 565 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA HOLDING FUEL FLOW ENGINE ANTICE OFF 1500 5000 10,000 15,000 20,000 25,000 30,000 35,000 ALTITUDE ft TOTAL FUEL FLOW lb/hr WEIGHT lb KIAS 16,000 1038 1010 17,000 1086 1057...
  • Page 566 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA HOLDING FUEL FLOW ENGINE ANTICE ON 1500 5000 10,000 15,000 20,000 25,000 30,000 35,000 ALTITUDE ft TOTAL FUEL FLOW lb/hr WEIGHT lb KIAS 16,000 1163 1131 1088 1051 1007...
  • Page 567 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA Intentionally left blank Sub-section 2 Page 2-202 Pilot’s Operating Manual PREFLIGHT Original Issue: Feb, 2002...
  • Page 568 Pro Line 21 Section - IV FLIGHT PLANNING DATA Sub-section 3 CLIMB Table of Contents Page INTRODUCTION ..................3-3 NORMAL CLIMB..................3-4 ISA -15° C....................3-4 ISA -10° C....................3-6 ISA ......................3-8 ISA +5° C....................3-10 ISA +10° C....................3-12 ISA +15°...
  • Page 569 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA Intentionally left blank Sub-section 3 Page 3-2 Pilot’s Operating Manual CLIMB Original Issue: Feb, 2002...
  • Page 570 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA INTRODUCTION Climb fuel, distance and time are tabulated versus take-off weight and altitude at top of climb. Fuel and time for takeoff and initial climb to 160 KIAS at 1000 ft are included. The data is presented for temperatures in the range from ISA -15°...
  • Page 571 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA NORMAL CLIMB TABLE UNITS ISA - 15° C Take-off Weight (TOW) ....pounds FUEL ..........pounds DIST ..........nautical miles TIME ..........minutes ALTITUDE (x 1000 ft) AT TOP OF CLIMB...
  • Page 572 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA NORMAL CLIMB TABLE UNITS ISA - 15° C Take-off Weight (TOW)....pounds FUEL..........pounds DIST ..........nautical miles TIME ..........minutes ALTITUDE (x 1000 ft) AT TOP OF CLIMB...
  • Page 573 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA NORMAL CLIMB TABLE UNITS ISA - 10° C Take-off Weight (TOW) ....pounds FUEL ..........pounds DIST ..........nautical miles TIME ..........minutes ALTITUDE (x 1000 ft) AT TOP OF CLIMB...
  • Page 574 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA NORMAL CLIMB TABLE UNITS ISA - 10° C Take-off Weight (TOW)....pounds FUEL..........pounds DIST ..........nautical miles TIME ..........minutes ALTITUDE (x 1000 ft) AT TOP OF CLIMB...
  • Page 575 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA NORMAL CLIMB TABLE UNITS Take-off Weight (TOW) ....pounds FUEL ..........pounds DIST ..........nautical miles TIME ..........minutes ALTITUDE (x 1000 ft) AT TOP OF CLIMB FUEL 19,000...
  • Page 576 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA NORMAL CLIMB TABLE UNITS Take-off Weight (TOW) ....pounds FUEL..........pounds DIST..........nautical miles TIME ..........minutes ALTITUDE (x 1000 ft) AT TOP OF CLIMB FUEL 19,000 DIST TIME FUEL 20,000 DIST TIME...
  • Page 577 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA NORMAL CLIMB TABLE UNITS ISA + 5° C Take-off Weight (TOW) ....pounds FUEL ..........pounds DIST ..........nautical miles TIME ..........minutes ALTITUDE (x 1000 ft) AT TOP OF CLIMB...
  • Page 578 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA NORMAL CLIMB TABLE UNITS ISA + 5° C Take-off Weight (TOW) ....pounds FUEL ..........pounds DIST ..........nautical miles TIME ..........minutes ALTITUDE (x 1000 ft) AT TOP OF CLIMB...
  • Page 579 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA NORMAL CLIMB TABLE UNITS ISA + 10° C Take-off Weight (TOW) ....pounds FUEL ..........pounds DIST ..........nautical miles TIME ..........minutes ALTITUDE (x 1000 ft) AT TOP OF CLIMB...
  • Page 580 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA NORMAL CLIMB TABLE UNITS ISA + 10° C Take-off Weight (TOW)....pounds FUEL..........pounds DIST ..........nautical miles TIME ..........minutes ALTITUDE (x 1000 ft) AT TOP OF CLIMB...
  • Page 581 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA NORMAL CLIMB TABLE UNITS ISA + 15° C Take-off Weight (TOW) ....pounds FUEL ..........pounds DIST ..........nautical miles TIME ..........minutes ALTITUDE (x 1000 ft) AT TOP OF CLIMB...
  • Page 582 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA NORMAL CLIMB TABLE UNITS ISA + 15° C Take-off Weight (TOW)....pounds FUEL..........pounds DIST ..........nautical miles TIME ..........minutes ALTITUDE (x 1000 ft) AT TOP OF CLIMB...
  • Page 583 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA NORMAL CLIMB TABLE UNITS ISA + 20° C Take-off Weight (TOW) ....pounds FUEL ..........pounds DIST ..........nautical miles TIME ..........minutes ALTITUDE (x 1000 ft) AT TOP OF CLIMB...
  • Page 584 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA NORMAL CLIMB TABLE UNITS ISA + 20° C Take-off Weight (TOW) ....pounds FUEL..........pounds DIST..........nautical miles TIME ..........minutes ALTITUDE (x 1000 ft) AT TOP OF CLIMB 1038 FUEL 19,000 DIST...
  • Page 585 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA OPTIMUM TIME-TO-HEIGHT CLIMB TABLE UNITS ISA -15° C Take-off Weight (TOW) ....pounds FUEL ..........pounds DIST ..........nautical miles TIME ..........minutes ALTITUDE (x 1000 ft) AT TOP OF CLIMB...
  • Page 586 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA OPTIMUM TIME-TO-HEIGHT CLIMB TABLE UNITS ISA -15° C Take-off Weight (TOW) ....pounds FUEL..........pounds DIST..........nautical miles TIME ..........minutes ALTITUDE (x 1000 ft) AT TOP OF CLIMB FUEL 19,000 DIST TIME...
  • Page 587 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA OPTIMUM TIME-TO-HEIGHT CLIMB TABLE UNITS ISA -10° C Take-off Weight (TOW) ....pounds FUEL ..........pounds DIST ..........nautical miles TIME ..........minutes ALTITUDE (x 1000 ft) AT TOP OF CLIMB...
  • Page 588 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA OPTIMUM TIME-TO-HEIGHT CLIMB TABLE UNITS ISA -10° C Take-off Weight (TOW)....pounds FUEL..........pounds DIST ..........nautical miles TIME ..........minutes ALTITUDE (x 1000 ft) AT TOP OF CLIMB...
  • Page 589 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA OPTIMUM TIME-TO-HEIGHT CLIMB TABLE UNITS Take-off Weight (TOW) ....pounds FUEL ..........pounds DIST ..........nautical miles TIME ..........minutes ALTITUDE (x 1000 ft) AT TOP OF CLIMB FUEL...
  • Page 590 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA OPTIMUM TIME-TO-HEIGHT CLIMB TABLE UNITS Take-off Weight (TOW)....pounds FUEL..........pounds DIST ..........nautical miles TIME ..........minutes ALTITUDE (x 1000 ft) AT TOP OF CLIMB FUEL 19,000 DIST...
  • Page 591 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA OPTIMUM TIME-TO-HEIGHT CLIMB TABLE UNITS ISA +10° C Take-off Weight (TOW) ....pounds FUEL ..........pounds DIST ..........nautical miles TIME ..........minutes ALTITUDE (x 1000 ft) AT TOP OF CLIMB...
  • Page 592 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA OPTIMUM TIME-TO-HEIGHT CLIMB TABLE UNITS ISA +10° C Take-off Weight (TOW)....pounds FUEL..........pounds DIST ..........nautical miles TIME ..........minutes ALTITUDE (x 1000 ft) AT TOP OF CLIMB...
  • Page 593 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA OPTIMUM TIME-TO-HEIGHT CLIMB TABLE UNITS ISA +15° C Take-off Weight (TOW) ....pounds FUEL ..........pounds DIST ..........nautical miles TIME ..........minutes ALTITUDE (x 1000 ft) AT TOP OF CLIMB...
  • Page 594 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA OPTIMUM TIME-TO-HEIGHT CLIMB TABLE UNITS ISA +15° C Take-off Weight (TOW)....pounds FUEL..........pounds DIST ..........nautical miles TIME ..........minutes ALTITUDE (x 1000 ft) AT TOP OF CLIMB...
  • Page 595 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA OPTIMUM TIME-TO-HEIGHT CLIMB TABLE UNITS ISA +20° C Take-off Weight (TOW) ....pounds FUEL ..........pounds DIST ..........nautical miles TIME ..........minutes ALTITUDE (x 1000 ft) AT TOP OF CLIMB...
  • Page 596 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA OPTIMUM TIME-TO-HEIGHT CLIMB TABLE UNITS ISA +20° C Take-off Weight (TOW)....pounds FUEL..........pounds DIST ..........nautical miles TIME ..........minutes ALTITUDE (x 1000 ft) AT TOP OF CLIMB...
  • Page 597 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA PRESSURE RATE OF CLIMB Figure 1 Normal Procedure Pressure Rate of Climb - Antice Off Sub-section 3 Page 3-30 Pilot’s Operating Manual CLIMB Revision A1: Nov, 2002...
  • Page 598 Pro Line 21 Section - IV FLIGHT PLANNING DATA Sub-section 4 CRUISE EN-ROUTE Table of Contents Page INTRODUCTION ..................4-3 HIGH SPEED CRUISE ................4-5 5000 ft....................... 4-5 7000 ft....................... 4-6 9000 ft....................... 4-7 11,000 ft....................4-8 13,000 ft....................4-9 15,000 ft....................
  • Page 599 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA Page INTERMEDIATE CRUISE (Continued) 33,000 ft ....................4-37 35,000 ft ....................4-38 37,000 ft ....................4-39 39,000 ft ....................4-40 41,000 ft ....................4-41 LONG RANGE CRUISE ................4-43 230 KIAS ....................
  • Page 600 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA INTRODUCTION Cruise true airspeed, fuel flow and indicated airspeed are tabulated in this Sub-section for a range of temperatures from ISA -10° C to ISA + 20° C , for three procedures: •...
  • Page 601 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA Intentionally left blank Sub-section 4 Page 4-4 Pilot’s Operating Manual CRUISE - ENROUTE Original Issue: Feb, 2002...
  • Page 602 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA HIGH SPEED CRUISE 5000 ft TEMPERATURE RELATIVE TO ISA C CRUISE WEIGHT AMBIENT TEMP C IOAT C KTAS TOTAL FUEL FLOW 18,000 1802 1824 1849 1873 1896 1919 1942 1965...
  • Page 603 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA HIGH SPEED CRUISE 7000 ft TEMPERATURE RELATIVE TO ISA C CRUISE WEIGHT AMBIENT TEMP C IOAT C KTAS TOTAL FUEL FLOW 18,000 1775 1798 1820 1844 1867 1890 1913 1936...
  • Page 604 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA HIGH SPEED CRUISE 9000 ft TEMPERATURE RELATIVE TO ISA C CRUISE WEIGHT AMBIENT TEMP C IOAT C KTAS TOTAL FUEL FLOW 18,000 2351 2381 2413 2444 2475 2506 2536 2566...
  • Page 605 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA HIGH SPEED CRUISE 11,000 ft TEMPERATURE RELATIVE TO ISA C CRUISE WEIGHT AMBIENT TEMP C IOAT C KTAS TOTAL FUEL FLOW 18,000 2329 2360 2393 2425 2456 2487 2517 2547...
  • Page 606 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA HIGH SPEED CRUISE 13,000 ft TEMPERATURE RELATIVE TO ISA C CRUISE WEIGHT AMBIENT TEMP C IOAT C KTAS TOTAL FUEL FLOW 18,000 2291 2322 2355 2388 2420 2449 2479 2510...
  • Page 607 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA HIGH SPEED CRUISE 15,000 ft TEMPERATURE RELATIVE TO ISA C CRUISE WEIGHT AMBIENT TEMP C IOAT C KTAS TOTAL FUEL FLOW 18,000 2232 2263 2295 2328 2358 2388 2418 2449...
  • Page 608 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA HIGH SPEED CRUISE 17,000 ft TEMPERATURE RELATIVE TO ISA °C CRUISE WEIGHT AMBIENT TEMP °C IOAT °C KTAS TOTAL FUEL FLOW 2176 2206 2238 2269 2299 2328 2360 2390...
  • Page 609 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA HIGH SPEED CRUISE 19,000 ft TEMPERATURE RELATIVE TO ISA °C CRUISE WEIGHT AMBIENT TEMP °C IOAT °C KTAS TOTAL FUEL FLOW 2122 2153 2184 2214 2245 2273 2304 2334...
  • Page 610 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA HIGH SPEED CRUISE 21,000 ft TEMPERATURE RELATIVE TO ISA °C CRUISE WEIGHT AMBIENT TEMP °C IOAT °C KTAS TOTAL FUEL FLOW 2074 2107 2137 2166 2195 2224 2255 2287...
  • Page 611 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA HIGH SPEED CRUISE 23,000 ft TEMPERATURE RELATIVE TO ISA °C CRUISE WEIGHT AMBIENT TEMP °C IOAT °C KTAS TOTAL FUEL FLOW 2039 2070 2100 2129 2157 2188 2220 2249...
  • Page 612 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA HIGH SPEED CRUISE 25,000 ft TEMPERATURE RELATIVE TO ISA °C CRUISE WEIGHT AMBIENT TEMP °C IOAT °C KTAS TOTAL FUEL FLOW 2030 2058 2086 2118 2151 2181 2209 2228...
  • Page 613 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA HIGH SPEED CRUISE 27,000 ft TEMPERATURE RELATIVE TO ISA °C CRUISE WEIGHT AMBIENT TEMP °C IOAT °C KTAS TOTAL FUEL FLOW 2064 2094 2133 2168 2198 2223 2228 2112...
  • Page 614 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA HIGH SPEED CRUISE 29,000 ft TEMPERATURE RELATIVE TO ISA °C CRUISE WEIGHT AMBIENT TEMP °C IOAT °C KTAS TOTAL FUEL FLOW 2211 2255 2290 2331 2299 2201 2100 1993...
  • Page 615 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA HIGH SPEED CRUISE 31,000 ft TEMPERATURE RELATIVE TO ISA °C CRUISE WEIGHT AMBIENT TEMP °C IOAT °C KTAS TOTAL FUEL FLOW 2076 2116 2154 2192 2155 2062 1970 1873...
  • Page 616 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA HIGH SPEED CRUISE 33,000 ft TEMPERATURE RELATIVE TO ISA °C CRUISE WEIGHT AMBIENT TEMP °C IOAT °C KTAS TOTAL FUEL FLOW 1920 1963 1997 2035 2017 1927 1843 1754...
  • Page 617 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA HIGH SPEED CRUISE 35,000 ft TEMPERATURE RELATIVE TO ISA °C CRUISE WEIGHT AMBIENT TEMP °C IOAT °C KTAS TOTAL FUEL FLOW 1798 1835 1871 1902 1875 1788 1712 1630...
  • Page 618 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA HIGH SPEED CRUISE 37,000 ft TEMPERATURE RELATIVE TO ISA °C CRUISE WEIGHT AMBIENT TEMP °C IOAT °C KTAS TOTAL FUEL FLOW 18,000 1717 1751 1782 1817 1732 1646 1576...
  • Page 619 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA HIGH SPEED CRUISE 39,000 ft TEMPERATURE RELATIVE TO ISA °C CRUISE WEIGHT AMBIENT TEMP °C IOAT °C KTAS TOTAL FUEL FLOW 18,000 1658 1684 1711 1653 1561 1486 1423...
  • Page 620 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA HIGH SPEED CRUISE 41,000 ft TEMPERATURE RELATIVE TO ISA °C CRUISE WEIGHT AMBIENT TEMP °C IOAT °C KTAS TOTAL FUEL FLOW 1579 1609 1541 1483 1405 1335 1273 1207...
  • Page 621 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA Intentionally left blank Sub-section 4 Page 4-24 Pilot’s Operating Manual CRUISE - ENROUTE Original Issue: Feb, 2002...
  • Page 622 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA INTERMEDIATE CRUISE 9000 ft TEMPERATURE RELATIVE TO ISA °C CRUISE WEIGHT AMBIENT TEMP °C IOAT °C KTAS TOTAL FUEL FLOW 1746 1768 1791 1814 1837 1860 1884 1906 18,000...
  • Page 623 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA INTERMEDIATE CRUISE 11,000 ft TEMPERATURE RELATIVE TO ISA °C CRUISE WEIGHT AMBIENT TEMP °C IOAT °C KTAS TOTAL FUEL FLOW 18,000 1719 1741 1764 1787 1810 1833 1856 1879...
  • Page 624 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA INTERMEDIATE CRUISE 13,000 ft TEMPERATURE RELATIVE TO ISA °C CRUISE WEIGHT AMBIENT TEMP °C IOAT °C KTAS TOTAL FUEL FLOW 1694 1715 1738 1762 1785 1808 1831 1854 18,000...
  • Page 625 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA INTERMEDIATE CRUISE 15,000 ft TEMPERATURE RELATIVE TO ISA °C CRUISE WEIGHT AMBIENT TEMP °C IOAT °C KTAS TOTAL FUEL FLOW 1667 1689 1713 1736 1760 1783 1806 1829 18,000...
  • Page 626 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA INTERMEDIATE CRUISE 17,000 ft TEMPERATURE RELATIVE TO ISA °C CRUISE WEIGHT AMBIENT TEMP °C IOAT °C KTAS TOTAL FUEL FLOW 1643 1666 1690 1712 1736 1759 1783 1806 18,000...
  • Page 627 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA INTERMEDIATE CRUISE 19,000 ft TEMPERATURE RELATIVE TO ISA °C CRUISE WEIGHT AMBIENT TEMP °C IOAT °C KTAS TOTAL FUEL FLOW 1619 1642 1667 1689 1713 1737 1760 1784 18,000...
  • Page 628 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA INTERMEDIATE CRUISE 21,000 ft TEMPERATURE RELATIVE TO ISA °C CRUISE WEIGHT AMBIENT TEMP °C IOAT °C KTAS TOTAL FUEL FLOW 1597 1620 1646 1669 1692 1716 1740 1764 18,000...
  • Page 629 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA INTERMEDIATE CRUISE 23,000 ft TEMPERATURE RELATIVE TO ISA °C CRUISE WEIGHT AMBIENT TEMP °C IOAT °C KTAS TOTAL FUEL FLOW 1576 1600 1625 1648 1671 1695 1718 1743 18,000...
  • Page 630 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA INTERMEDIATE CRUISE 25,000 ft TEMPERATURE RELATIVE TO ISA °C CRUISE WEIGHT AMBIENT TEMP °C IOAT °C KTAS TOTAL FUEL FLOW 1560 1585 1609 1632 1654 1679 1703 1728 18,000...
  • Page 631 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA INTERMEDIATE CRUISE 27,000 ft TEMPERATURE RELATIVE TO ISA °C CRUISE WEIGHT AMBIENT TEMP °C IOAT °C KTAS TOTAL FUEL FLOW 1557 1582 1606 1631 1656 1680 1704 1729 18,000...
  • Page 632 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA INTERMEDIATE CRUISE 29,000 ft TEMPERATURE RELATIVE TO ISA °C CRUISE WEIGHT AMBIENT TEMP °C IOAT °C KTAS TOTAL FUEL FLOW 1565 1589 1617 1643 1667 1691 1720 1748 18,000...
  • Page 633 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA INTERMEDIATE CRUISE 31,000 ft TEMPERATURE RELATIVE TO ISA °C CRUISE WEIGHT AMBIENT TEMP °C IOAT °C KTAS TOTAL FUEL FLOW 1589 1612 1637 1659 1689 1722 1751 1776 18,000...
  • Page 634 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA INTERMEDIATE CRUISE 33,000 ft TEMPERATURE RELATIVE TO ISA °C CRUISE WEIGHT AMBIENT TEMP °C IOAT °C KTAS TOTAL FUEL FLOW 1475 1496 1518 1539 1564 1597 1627 1654 18,000...
  • Page 635 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA INTERMEDIATE CRUISE 35,000 ft TEMPERATURE RELATIVE TO ISA °C CRUISE WEIGHT AMBIENT TEMP °C IOAT °C KTAS TOTAL FUEL FLOW 1366 1392 1412 1434 1457 1491 1521 1550 18,000...
  • Page 636 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA INTERMEDIATE CRUISE 37,000 ft TEMPERATURE RELATIVE TO ISA °C CRUISE WEIGHT AMBIENT TEMP °C IOAT °C KTAS TOTAL FUEL FLOW 1273 1302 1323 1342 1370 1402 1430 1454 18,000...
  • Page 637 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA INTERMEDIATE CRUISE 39,000 ft TEMPERATURE RELATIVE TO ISA °C CRUISE WEIGHT AMBIENT TEMP °C IOAT °C KTAS TOTAL FUEL FLOW 1197 1223 1244 1267 1295 1325 1348 1349 18,000...
  • Page 638 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA INTERMEDIATE CRUISE 41,000 ft TEMPERATURE RELATIVE TO ISA °C CRUISE WEIGHT AMBIENT TEMP °C IOAT °C KTAS TOTAL FUEL FLOW 1149 1168 1196 1224 1247 1269 1273 1207 18,000...
  • Page 639 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA Intentionally left blank Sub-section 4 Page 4-42 Pilot’s Operating Manual CRUISE - ENROUTE Original Issue: Feb, 2002...
  • Page 640 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA LONG RANGE CRUISE 230 KIAS TEMPERATURE RELATIVE TO ISA °C ALTITUDE ft KTAS 31,000 TOTAL FUEL FLOW 1184 1204 1222 1243 1263 1283 1305 1327 lb/hr KTAS 29,000 TOTAL FUEL FLOW...
  • Page 641 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA LONG RANGE CRUISE 230 KIAS TEMPERATURE RELATIVE TO ISA °C ALTITUDE ft KTAS 15,000 TOTAL FUEL FLOW 1335 1348 1364 1381 1398 1416 1433 1451 lb/hr KTAS 13,000 TOTAL FUEL FLOW...
  • Page 642 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA LONG RANGE CRUISE 33,000 ft TEMPERATURE RELATIVE TO ISA °C CRUISE WEIGHT AMBIENT TEMP °C IOAT °C KTAS TOTAL FUEL FLOW 1115 1136 1154 1172 1192 1211 1232 1254...
  • Page 643 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA LONG RANGE CRUISE 35,000 ft TEMPERATURE RELATIVE TO ISA °C CRUISE WEIGHT AMBIENT TEMP °C IOAT °C KTAS TOTAL FUEL FLOW 1120 1143 1161 1176 1198 1221 1243 1264...
  • Page 644 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA LONG RANGE CRUISE 37,000 ft TEMPERATURE RELATIVE TO ISA °C CRUISE WEIGHT AMBIENT TEMP °C IOAT °C KTAS TOTAL FUEL FLOW 1056 1076 1096 1113 1135 1156 1175 1195...
  • Page 645 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA LONG RANGE CRUISE 39,000 ft TEMPERATURE RELATIVE TO ISA °C CRUISE WEIGHT AMBIENT TEMP °C IOAT °C KTAS TOTAL FUEL FLOW 1048 1065 1092 1113 1132 1148 1175 1200...
  • Page 646 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA LONG RANGE CRUISE 41,000 ft TEMPERATURE RELATIVE TO ISA °C CRUISE WEIGHT AMBIENT TEMP °C IOAT °C KTAS TOTAL FUEL FLOW 1004 1027 1047 1064 1079 1105 1128 1147...
  • Page 647 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA Intentionally left blank Sub-section 4 Page 4-50 Pilot’s Operating Manual CRUISE - ENROUTE Original Issue: Feb, 2002...
  • Page 648 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA CRUISE AIR MILES per lb of FUEL Figure 1 CRUISE AIR MILES per lb of FUEL - 20,000 ft ISA Sub-section 4 Page 4-51 Pilot’s Operating Manual CRUISE - ENROUTE...
  • Page 649 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA CRUISE AIR MILES per lb of FUEL Figure 2 CRUISE AIR MILES per lb of FUEL - 25,000 ft ISA Sub-section 4 Page 4-52 Pilot’s Operating Manual CRUISE - ENROUTE...
  • Page 650 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA CRUISE AIR MILES per lb of FUEL Figure 3 CRUISE AIR MILES per lb of FUEL - 31,000 ft ISA Sub-section 4 Page 4-53 Pilot’s Operating Manual CRUISE - ENROUTE...
  • Page 651 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA CRUISE AIR MILES per lb of FUEL Figure 4 CRUISE AIR MILES per lb of FUEL - 33,000 ft ISA Sub-section 4 Page 4-54 Pilot’s Operating Manual CRUISE - ENROUTE...
  • Page 652 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA CRUISE AIR MILES per lb of FUEL Figure 5 CRUISE AIR MILES per lb of FUEL - 35,000 ft ISA Sub-section 4 Page 4-55 Pilot’s Operating Manual CRUISE - ENROUTE...
  • Page 653 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA CRUISE AIR MILES per lb of FUEL Figure 6 CRUISE AIR MILES per lb of FUEL - 37,000 ft ISA Sub-section 4 Page 4-56 Pilot’s Operating Manual CRUISE - ENROUTE...
  • Page 654 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA CRUISE AIR MILES per lb of FUEL Figure 7 CRUISE AIR MILES per lb of FUEL - 39,000 ft ISA Sub-section 4 Page 4-57 Pilot’s Operating Manual CRUISE - ENROUTE...
  • Page 655 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA CRUISE AIR MILES per lb of FUEL Figure 8 CRUISE AIR MILES per lb of FUEL - 41,000 ft ISA Sub-section 4 Page 4-58 Pilot’s Operating Manual CRUISE - ENROUTE...
  • Page 656 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA EN ROUTE FUEL CHECK INSTRUCTIONS FOR USE OF TABLE ALTITUDE ft PRESENT WEIGHT thousands of lb The numbers in the instructions below refer to the stage numbers shown on the table.
  • Page 657 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA Intentionally left blank Page 4-60 Sub-section 4 Pilot’s Operating Manual Original Issue: Feb, 2002 CRUISE - ENROUTE...
  • Page 658 Pro Line 21 Section - IV FLIGHT PLANNING DATA Sub-section 5 NORMAL DESCENT Table of Contents Page INTRODUCTION ..................5-3 NORMAL DESCENT ISA................5-4 Pilot’s Operating Manual Page 5-1 Original Issue: Feb, 2002...
  • Page 659 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA Intentionally left blank Sub-section 5 Page 5-2 Pilot’s Operating Manual NORMAL DESCENT Original Issue: Feb, 2002...
  • Page 660 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA INTRODUCTION Descent Fuel, Distance and Time are tabulated in this Sub-section against Arrival Weight. The data is presented for a descent at 0.76 IMN/285/250 KIAS in ISA conditions. The descent procedure specifies a constant 1000 ft/min rate of descent down to 37,000 ft, where the thrust is reduced to idle for the remainder of the descent to 1500 ft.
  • Page 661 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA NORMAL DESCENT TABLE UNITS Arrival Weight ......... pounds FUEL ..........pounds DIST ..........nautical miles TIME ..........minutes ALTITUDE (x 1000 ft) AT TOP OF DESCENT ARRIVAL WEIGHT FUEL...
  • Page 662 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA NORMAL DESCENT TABLE UNITS Arrival Weight ......... pounds FUEL ..........pounds DIST ..........nautical miles TIME ..........minutes ALTITUDE (x 1000 ft) AT TOP OF DESCENT ARRIVAL WEIGHT FUEL...
  • Page 663 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA Intentionally left blank Sub-section 5 Page 5-6 Pilot’s Operating Manual NORMAL DESCENT Original Issue: Feb, 2002...
  • Page 664 Pilot’s Operating Manual Section IV FLIGHT PLANNING DATA Sub-section 6 SINGLE ENGINE Table of Contents Page INTRODUCTION ..................6-3 SINGLE ENGINE CEILING ..............6-3 SINGLE ENGINE DRIFT DOWN.............. 6-3 SINGLE ENGINE CRUISE ............... 6-4 SINGLE ENGINE MAXIMUM CONTINUOUS THRUST FOR DESCENT AND CRUISE..............6-4 SINGLE ENGINE..................
  • Page 665 Pilot’s Operating Manual Page SINGLE ENGINE HIGH SPEED DESCENT..........6-30 SINGLE ENGINE MAXIMUM CONTINUOUS THRUST CRUISE ..... 6-32 10,000 ft ....................6-32 11,000 ft ....................6-33 13,000 ft ....................6-34 15,000 ft ....................6-35 17,000 ft ....................6-36 19,000 ft ....................6-37 21,000 ft ....................
  • Page 666 Pilot’s Operating Manual INTRODUCTION This Sub-section contains one engine inoperative data. SINGLE ENGINE CEILING This Sub-section provides the following data: A summary of single engine ceilings for a range of weights and temperatures, at: • En-route climb speed. • Minimum cruise speed. •...
  • Page 667 Pilot’s Operating Manual SINGLE ENGINE CRUISE This Sub-section contains data tables for (SINGLE ENGINE LONG RANGE CRUISE). If an engine fails, the cruise altitude is reduced, with a subsequent reduction in air miles per lb. To minimize the loss of range, the thrust on the operative engine should be increased to maximum continuous thrust and the speed reduced to the recommended single engine cruise speed (refer to the table for Long Range Cruise Speed) and allow the airplane to drift down to its new cruise altitude.
  • Page 668 Pilot’s Operating Manual SINGLE ENGINE SINGLE ENGINE MINIMUM CRUISE SPEED and MAXIMUM CRUISE ALTITUDE ° TEMPERATURE RELATIVE TO ISA MINIMUM SPEED CRUISE MAXIMUM CRUISE ALTITUDE ft KIAS WEIGHT lb 26,000 25,800 25,200 23,900 22,500 21,400 20,300 18,800 16,700 25,000 26,800 26,200 25,100 23,700 22,500 21,600 20,100 18,300 24,000 27,800 27,400 26,300 25,000 23,800 22,800 21,400 19,900 23,000...
  • Page 669 Pilot’s Operating Manual SINGLE ENGINE SINGLE ENGINE MAXIMUM CRUISE WEIGHT ° TEMPERATURE RELATIVE TO ISA CRUISE MAXIMUM CRUISE WEIGHT lb ALTITUDE ft 17,000 25,800 19,000 25,800 24,600 21,000 26,300 25,400 24,300 23,200 23,000 25,600 24,600 23,800 22,700 21,700 25,000 26,200 25,100 23,900 22,900 22,000 21,000 19,900 27,000 24,800 24,300 23,400 22,400 21,300 20,400 19,300 18,500 29,000...
  • Page 670 Pilot’s Operating Manual SUMMARY of SINGLE ENGINE CEILINGS SINGLE ENGINE CEILING ft AT TEMPERATURES RELATIVE TO ° ENGINE WEIGHT lb SPEED KIAS ANTICE EN ROUTE CLIMB 0% 24,450 21,450 19,300 15,850 EN ROUTE CLIMB 1.1% 20,800 17,150 14,500 11,100 26,000 MINIMUM CRUISE 25,800 22,500 20,300 16,700 LONG RANGE CRUISE...
  • Page 671 Pilot’s Operating Manual OBSTACLE CLEARANCE Cruise Ceiling for Zero En Route Net Gradient ° TEMPERATURE RELATIVE TO ISA MAXIMUM CRUISE ALTITUDE ft CRUISE WEIGHT lb 17,300 16,300 15,100 13,800 12,500 10,900 9100 7100 29,000 11,000 9600 8200 7000 5500 3200 18,600 17,500 16,200 14,900 13,600 12,600 10,400 8500 28,000 12,300 11,100 9700...
  • Page 672 Pilot’s Operating Manual RANGE AFTER ENGINE FAILURE Figure 1 Range After Engine Failure P/N 140-590032-0007 Section IV Sub-section 6 Page 6-9 Revision A4: Sep, 2010 SINGLE ENGINE...
  • Page 673 Pilot’s Operating Manual SINGLE ENGINE DRIFT DOWN ISA -15° C These ceilings are based on average performance at Maximum Continuous Thrust and a constant drift down KIAS (minimum cruise speed at start of drift down weight). To check obstacle clearance use the EN ROUTE NET GRADIENT in the Airplane Flight Manual which will give a lower ceiling than the final drift down altitudes below.
  • Page 674 Pilot’s Operating Manual SINGLE ENGINE DRIFT DOWN ISA -15° C These ceilings are based on average performance at Maximum Continuous Thrust and a constant drift down KIAS (minimum cruise speed at start of drift down weight). To check obstacle clearance use the EN ROUTE NET GRADIENT in the Airplane Flight Manual which will give a lower ceiling than the final drift down altitudes below.
  • Page 675 Pilot’s Operating Manual SINGLE ENGINE DRIFT DOWN ISA -10° C These ceilings are based on average performance at Maximum Continuous Thrust and a constant drift down KIAS (minimum cruise speed at start of drift down weight). To check obstacle clearance use the EN ROUTE NET GRADIENT in the Airplane Flight Manual which will give a lower ceiling than the final drift down altitudes below.
  • Page 676 Pilot’s Operating Manual SINGLE ENGINE DRIFT DOWN ISA -10° C These ceilings are based on average performance at Maximum Continuous Thrust and a constant drift down KIAS (minimum cruise speed at start of drift down weight). To check obstacle clearance use the EN ROUTE NET GRADIENT in the Airplane Flight Manual which will give a lower ceiling than the final drift down altitudes below.
  • Page 677 Pilot’s Operating Manual SINGLE ENGINE DRIFT DOWN These ceilings are based on average performance at Maximum Continuous Thrust and a constant drift down KIAS (minimum cruise speed at start of drift down weight). To check obstacle clearance use the EN ROUTE NET GRADIENT in the Airplane Flight Manual which will give a lower ceiling than the final drift down altitudes below.
  • Page 678 Pilot’s Operating Manual SINGLE ENGINE DRIFT DOWN These ceilings are based on average performance at Maximum Continuous Thrust and a constant drift down KIAS (minimum cruise speed at start of drift down weight). To check obstacle clearance use the EN ROUTE NET GRADIENT in the Airplane Flight Manual which will give a lower ceiling than the final drift down altitudes below.
  • Page 679 Pilot’s Operating Manual SINGLE ENGINE DRIFT DOWN ISA +10° C These ceilings are based on average performance at Maximum Continuous Thrust and a constant drift down KIAS (minimum cruise speed at start of drift down weight). To check obstacle clearance use the EN ROUTE NET GRADIENT in the Airplane Flight Manual which will give a lower ceiling than the final drift down altitudes below.
  • Page 680 Pilot’s Operating Manual SINGLE ENGINE DRIFT DOWN ISA +10° C These ceilings are based on average performance at Maximum Continuous Thrust and a constant drift down KIAS (minimum cruise speed at start of drift down weight). To check obstacle clearance use the EN ROUTE NET GRADIENT in the Airplane Flight Manual which will give a lower ceiling than the final drift down altitudes below.
  • Page 681 Pilot’s Operating Manual SINGLE ENGINE DRIFT DOWN ISA +20° C These ceilings are based on average performance at Maximum Continuous Thrust and a constant drift down KIAS (minimum cruise speed at start of drift down weight). To check obstacle clearance use the EN ROUTE NET GRADIENT in the Airplane Flight Manual which will give a lower ceiling than the final drift down altitudes below.
  • Page 682 Pilot’s Operating Manual SINGLE ENGINE DRIFT DOWN ISA +20° C These ceilings are based on average performance at Maximum Continuous Thrust and a constant drift down KIAS (minimum cruise speed at start of drift down weight). To check obstacle clearance use the EN ROUTE NET GRADIENT in the Airplane Flight Manual which will give a lower ceiling than the final drift down altitudes below.
  • Page 683 Pilot’s Operating Manual SINGLE ENGINE LONG RANGE CRUISE 11,000 ft ° TEMPERATURE RELATIVE TO ISA CRUISE WEIGHT ° AMBIENT TEMP ° IOAT KTAS TOTAL FUEL FLOW 18,000 1002 1015 1029 1043 1056 1069 lb/hr KIAS KTAS TOTAL FUEL FLOW 20,000 1070 1086 1101...
  • Page 684 Pilot’s Operating Manual SINGLE ENGINE LONG RANGE CRUISE 13,000 ft ° TEMPERATURE RELATIVE TO ISA CRUISE WEIGHT ° AMBIENT TEMP ° IOAT KTAS TOTAL FUEL FLOW 18,000 1007 1021 1035 1048 1062 lb/hr KIAS KTAS TOTAL FUEL FLOW 20,000 1062 1078 1093 1108...
  • Page 685 Pilot’s Operating Manual SINGLE ENGINE LONG RANGE CRUISE 15,000 ft ° TEMPERATURE RELATIVE TO ISA CRUISE WEIGHT ° AMBIENT TEMP ° IOAT KTAS TOTAL FUEL FLOW 18,000 1012 1026 1040 1054 lb/hr KIAS KTAS TOTAL FUEL FLOW 20,000 1053 1069 1084 1098 1113...
  • Page 686 Pilot’s Operating Manual SINGLE ENGINE LONG RANGE CRUISE 17,000 ft ° TEMPERATURE RELATIVE TO ISA CRUISE WEIGHT ° AMBIENT TEMP ° IOAT KTAS TOTAL FUEL FLOW 18,000 1004 1017 1031 1045 lb/hr KIAS KTAS TOTAL FUEL FLOW 20,000 1044 1059 1075 1089 1103...
  • Page 687 Pilot’s Operating Manual SINGLE ENGINE LONG RANGE CRUISE 19,000 ft ° TEMPERATURE RELATIVE TO ISA CRUISE WEIGHT ° AMBIENT TEMP ° IOAT KTAS TOTAL FUEL FLOW 18,000 1009 1022 1037 lb/hr KIAS KTAS TOTAL FUEL FLOW 20,000 1038 1053 1068 1081 1095 1114...
  • Page 688 Pilot’s Operating Manual SINGLE ENGINE LONG RANGE CRUISE 21,000 ft ° TEMPERATURE RELATIVE TO ISA CRUISE WEIGHT ° AMBIENT TEMP ° IOAT KTAS TOTAL FUEL FLOW 18,000 1002 1019 1034 lb/hr KIAS KTAS TOTAL FUEL FLOW 20,000 1037 1050 1064 1081 1098 1115...
  • Page 689 Pilot’s Operating Manual SINGLE ENGINE LONG RANGE CRUISE 23,000 ft ° TEMPERATURE RELATIVE TO ISA CRUISE WEIGHT ° AMBIENT TEMP ° IOAT KTAS TOTAL FUEL FLOW 18,000 1008 1024 1038 lb/hr KIAS KTAS TOTAL FUEL FLOW 20,000 1043 1059 1076 1095 1111 1128...
  • Page 690 Pilot’s Operating Manual SINGLE ENGINE LONG RANGE CRUISE 25,000 ft ° TEMPERATURE RELATIVE TO ISA CRUISE WEIGHT ° AMBIENT TEMP ° IOAT KTAS TOTAL FUEL FLOW 18,000 1008 1023 1042 1056 lb/hr KIAS KTAS TOTAL FUEL FLOW 20,000 1065 1082 1101 1121 1138...
  • Page 691 Pilot’s Operating Manual SINGLE ENGINE LONG RANGE CRUISE 27,000 ft ° TEMPERATURE RELATIVE TO ISA CRUISE WEIGHT ° AMBIENT TEMP ° IOAT KTAS TOTAL FUEL FLOW 18,000 1003 1022 1041 1060 1030 lb/hr KIAS KTAS TOTAL FUEL FLOW 20,000 1082 1103 1117 1139...
  • Page 692 Pilot’s Operating Manual SINGLE ENGINE HOLDING - FUEL FLOW ENGINE ANTICE OFF ALTITUDE ft 1500 5000 10,000 15,000 20,000 25,000 30,000 35,000 WEIGHT lb KIAS TOTAL FUEL FLOW lb/hr 16,000 17,000 18,000 19,000 1022 1000 20,000 1071 1048 1017 1000 1045 21,000 1118...
  • Page 693 Pilot’s Operating Manual SINGLE ENGINE HIGH SPEED DESCENT Single Engine High Speed Descent 0.70 M/300 KIAS Units: FUEL- LB, DIST - NM, TIME - MIN Top of Descent Wt - ALTITUDE (x1000) AT TOP OF DESCENT - FT FUEL 17,000 DIST TIME FUEL...
  • Page 694 Pilot’s Operating Manual SINGLE ENGINE HIGH SPEED DESCENT Single Engine High Speed Descent 0.70 M/300 KIAS Units: FUEL- LB, DIST - NM, TIME - MIN Top of ALTITUDE(x1000) AT TOP OF DESCENT - FT Descent Wt - FUEL DIST 17,000 TIME FUEL DIST...
  • Page 695 Pilot’s Operating Manual SINGLE ENGINE MAXIMUM CONTINUOUS THRUST CRUISE 10,000 ft TEMPERATURE RELATIVE TO ISA ºC CRUISE WEIGHT AMBIENT TEMP ºC KTAS TOTAL FUEL FLOW 2016 2043 1992 1917 1833 1754 1671 1592 18,000 lb/hr KIAS KTAS TOTAL FUEL FLOW 20,000 2017 2044...
  • Page 696 Pilot’s Operating Manual SINGLE ENGINE MAXIMUM CONTINUOUS THRUST CRUISE 11,000 ft TEMPERATURE RELATIVE TO ISA ºC CRUISE WEIGHT AMBIENT TEMP ºC KTAS TOTAL FUEL FLOW 1989 2004 1939 1864 1784 1707 1627 1551 18,000 lb/hr KIAS KTAS TOTAL FUEL FLOW 20,000 1988 2004...
  • Page 697 Pilot’s Operating Manual SINGLE ENGINE MAXIMUM CONTINUOUS THRUST CRUISE 13,000 ft TEMPERATURE RELATIVE TO ISA ºC CRUISE WEIGHT AMBIENT TEMP ºC KTAS TOTAL FUEL FLOW 18,000 1939 1905 1829 1758 1685 1614 1539 1466 lb/hr KIAS KTAS TOTAL FUEL FLOW 20,000 1938 1903...
  • Page 698 Pilot’s Operating Manual SINGLE ENGINE MAXIMUM CONTINUOUS THRUST CRUISE 15,000 ft TEMPERATURE RELATIVE TO ISA ºC CRUISE WEIGHT AMBIENT TEMP ºC KTAS TOTAL FUEL FLOW 1868 1792 1718 1649 1583 1519 1449 1380 18,000 lb/hr KIAS KTAS TOTAL FUEL FLOW 20,000 1865 1790...
  • Page 699 Pilot’s Operating Manual SINGLE ENGINE MAXIMUM CONTINUOUS THRUST CRUISE 17,000 ft TEMPERATURE RELATIVE TO ISA ºC CRUISE WEIGHT AMBIENT TEMP ºC KTAS TOTAL FUEL FLOW 1759 1692 1620 1555 1502 1449 1386 1321 18,000 lb/hr KIAS KTAS TOTAL FUEL FLOW 20,000 1757 1690...
  • Page 700 Pilot’s Operating Manual SINGLE ENGINE MAXIMUM CONTINUOUS THRUST CRUISE 19,000 ft TEMPERATURE RELATIVE TO ISA ºC CRUISE WEIGHT AMBIENT TEMP ºC KTAS TOTAL FUEL FLOW 18,000 1656 1589 1522 1459 1417 1375 1318 1261 lb/hr KIAS KTAS TOTAL FUEL FLOW 20,000 1654 1586...
  • Page 701 Pilot’s Operating Manual SINGLE ENGINE MAXIMUM CONTINUOUS THRUST CRUISE 21,000 ft TEMPERATURE RELATIVE TO ISA ºC CRUISE WEIGHT AMBIENT TEMP ºC KTAS TOTAL FUEL FLOW 18,000 1560 1501 1433 1374 1337 1302 1249 1196 lb/hr KIAS KTAS TOTAL FUEL FLOW 20,000 1556 1498...
  • Page 702 Pilot’s Operating Manual SINGLE ENGINE MAXIMUM CONTINUOUS THRUST CRUISE 23,000 ft TEMPERATURE RELATIVE TO ISA ºC CRUISE WEIGHT AMBIENT TEMP ºC KTAS TOTAL FUEL FLOW 18,000 1471 1423 1357 1301 1265 1231 1180 1129 lb/hr KIAS KTAS TOTAL FUEL FLOW 20,000 1465 1418...
  • Page 703 Pilot’s Operating Manual SINGLE ENGINE MAXIMUM CONTINUOUS THRUST CRUISE 25,000 ft TEMPERATURE RELATIVE TO ISA ºC CRUISE WEIGHT AMBIENT TEMP ºC KTAS TOTAL FUEL FLOW 18,000 1379 1341 1281 1227 1191 1158 1107 1058 lb/hr KIAS KTAS TOTAL FUEL FLOW 20,000 1370 1334...
  • Page 704 Pilot’s Operating Manual SINGLE ENGINE MAXIMUM CONTINUOUS THRUST CRUISE 27,000 ft TEMPERATURE RELATIVE TO ISA ºC CRUISE WEIGHT AMBIENT TEMP ºC KTAS TOTAL FUEL FLOW 18,000 1273 1253 1205 1163 1121 1086 1035 lb/hr KIAS KTAS TOTAL FUEL FLOW 20,000 1264 1245 1199...
  • Page 705 Pilot’s Operating Manual Intentionally left blank Page 6-42 Section IV Sub-section 6 P/N 140-590032-0007 Revision A4: Sep, 2010 SINGLE ENGINE...
  • Page 706 Pro Line 21 Section - IV FLIGHT PLANNING DATA Sub-section 7 UNFACTORED LANDING Table of Contents Page INTRODUCTION ..................7-3 INSTRUCTIONS FOR USE OF THE CHART ..........7-4 Figure 1 - Unfactored Landing Distance Required ....... 7-5 Pilot’s Operating Manual Page 7-1 Original Issue: Feb, 2002...
  • Page 707 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA Intentionally left blank Sub-section 7 Page 7-2 Pilot’s Operating Manual UNFACTORED LANDING Original Issue: Feb, 2002...
  • Page 708 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA INTRODUCTION Figure 1 shows the unfactored landing distance required from 50 feet (15.24m) to stop on a dry, wet or slippery surface. The associated conditions are the same as those given for landing field length in Sub- section 5.50 of the Airplane Flight Manual.
  • Page 709 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA INSTRUCTIONS FOR USE OF THE CHART The broken arrowed line illustrates the use of Figure 1. • Enter with landing weight and go up to the airfield altitude. • Move right to the reference line of the wind correction grid.
  • Page 710 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA Figure 1 Unfactored Landing Distance Required Page 7-5 Pilot’s Operating Manual Sub-section 7 Revision A2: Nov, 2004 UNFACTORED LANDING...
  • Page 711 Hawker 800XP Pro Line 21 Section IV - FLIGHT PLANNING DATA Intentionally left blank Sub-section 7 Page 7- 6 Pilot’s Operating Manual Revision A2: Nov, 2004 UNFACTORED LANDING...
  • Page 712 Pilot’s Operating Manual Section - IV FLIGHT PLANNING DATA Sub-section 8 GEAR DOWN PERFORMANCE Table of Contents Page INTRODUCTION ..................8-3 GEAR DOWN CLIMB 160 KIAS / 210 KIAS ISA -15° C ....................8-4 ISA -10° C ....................8-5 ISA -5° C ....................8-6 ISA ......................
  • Page 713 Pilot’s Operating Manual Intentionally left blank Section IV - Sub-section 8 P/N 140-590032-0007 Page 8-2 Revision A3: Apr, 2008 GEAR DOWN PERFORMANCE...
  • Page 714 Pilot’s Operating Manual INTRODUCTION This Sub-section provides gear down flight planning data for climb, cruise and descent and is for use in planning abnormal operations only. Normal operations require landing gear retraction capability to meet AFM takeoff and climb performance. Data is provided up to the maximum permissible altitude of 20,000 feet with the landing gear extended.
  • Page 715 Pilot’s Operating Manual GEAR DOWN CLIMB 160 KIAS/210 KIAS ISA -15° C TABLE UNITS Take-off Weight (TOW)…… pounds FUEL………………………… pounds DIST…………………………… nautical miles TIME………………………… minutes ALTITUDE (x 1000 ft) AT TOP OF CLIMB FUEL 19,000 DIST TIME FUEL 20,000 DIST TIME FUEL 21,000...
  • Page 716 Pilot’s Operating Manual GEAR DOWN CLIMB 160 KIAS/210 KIAS ISA -10° C TABLE UNITS Take-off Weight (TOW)…… pounds FUEL………………………… pounds DIST…………………………… nautical miles TIME………………………… minutes ALTITUDE (x 1000 ft) AT TOP OF CLIMB FUEL DIST 19,000 TIME FUEL DIST 20,000 TIME FUEL DIST...
  • Page 717 Pilot’s Operating Manual GEAR DOWN CLIMB 160 KIAS/210 KIAS ISA -5° C TABLE UNITS Take-off Weight (TOW)…… pounds FUEL………………………… pounds DIST…………………………… nautical miles TIME………………………… minutes ALTITUDE (x 1000 ft) AT TOP OF CLIMB FUEL DIST 19,000 TIME FUEL DIST 20,000 TIME FUEL DIST...
  • Page 718 Pilot’s Operating Manual GEAR DOWN CLIMB 160 KIAS/210 KIAS TABLE UNITS Take-off Weight (TOW)…… pounds FUEL………………………… pounds DIST…………………………… nautical miles TIME………………………… minutes ALTITUDE (x 1000 ft) AT TOP OF CLIMB FUEL DIST 19,000 TIME FUEL DIST 20,000 TIME FUEL DIST 21,000 TIME FUEL...
  • Page 719 Pilot’s Operating Manual GEAR DOWN CLIMB 160 KIAS/210 KIAS ISA +5° C TABLE UNITS Take-off Weight (TOW)…… pounds FUEL………………………… pounds DIST…………………………… nautical miles TIME………………………… minutes ALTITUDE (x 1000 ft) AT TOP OF CLIMB FUEL DIST 19,000 TIME FUEL DIST 20,000 TIME FUEL DIST...
  • Page 720 Pilot’s Operating Manual GEAR DOWN CLIMB 160 KIAS/210 KIAS ISA +10° C TABLE UNITS Take-off Weight (TOW)…… pounds FUEL………………………… pounds DIST…………………………… nautical miles TIME………………………… minutes ALTITUDE (x 1000 ft) AT TOP OF CLIMB FUEL DIST 19,000 TIME FUEL DIST 20,000 TIME FUEL DIST...
  • Page 721 Pilot’s Operating Manual GEAR DOWN CLIMB 160 KIAS/210 KIAS ISA +15° C TABLE UNITS Take-off Weight (TOW)…… pounds FUEL………………………… pounds DIST…………………………… nautical miles TIME………………………… minutes ALTITUDE (x 1000 ft) AT TOP OF CLIMB FUEL DIST 19,000 TIME FUEL DIST 20,000 TIME FUEL DIST...
  • Page 722 Pilot’s Operating Manual GEAR DOWN CLIMB 160 KIAS/210 KIAS ISA +20° C TABLE UNITS Take-off Weight (TOW)…… pounds FUEL………………………… pounds DIST…………………………… nautical miles TIME………………………… minutes ALTITUDE (x 1000 ft) AT TOP OF CLIMB FUEL DIST 19,000 TIME FUEL DIST 20,000 TIME FUEL DIST...
  • Page 723 Pilot’s Operating Manual GEAR DOWN CRUISE 1,000 ft TEMPERATURE RELATIVE TO ISA ºC CRUISE WEIGHT AMBIENT TEMP ºC KTAS TOTAL FUEL FLOW 18,000 1886 1908 1932 1955 1979 2003 2027 2050 lb/hr KIAS KTAS TOTAL FUEL FLOW 20,000 1916 1939 1963 1987 2012...
  • Page 724 Pilot’s Operating Manual GEAR DOWN CRUISE 3,000 ft TEMPERATURE RELATIVE TO ISA ºC CRUISE WEIGHT AMBIENT TEMP ºC KTAS TOTAL FUEL FLOW 18,000 1858 1880 1904 1929 1952 1974 1997 2019 lb/hr KIAS KTAS TOTAL FUEL FLOW 20,000 1888 1911 1936 1961 1983...
  • Page 725 Pilot’s Operating Manual GEAR DOWN CRUISE 5,000 ft TEMPERATURE RELATIVE TO ISA ºC CRUISE WEIGHT AMBIENT TEMP ºC KTAS TOTAL FUEL FLOW 18,000 1830 1853 1875 1898 1921 1944 1967 1990 lb/hr KIAS KTAS TOTAL FUEL FLOW 20,000 1860 1883 1906 1929 1953...
  • Page 726 Pilot’s Operating Manual GEAR DOWN CRUISE 7,000 ft TEMPERATURE RELATIVE TO ISA ºC CRUISE WEIGHT AMBIENT TEMP ºC KTAS TOTAL FUEL FLOW 18,000 1804 1826 1848 1871 1894 1917 1939 1961 lb/hr KIAS KTAS TOTAL FUEL FLOW 20,000 1834 1856 1879 1902 1924...
  • Page 727 Pilot’s Operating Manual GEAR DOWN CRUISE 9,000 ft TEMPERATURE RELATIVE TO ISA ºC CRUISE WEIGHT AMBIENT TEMP ºC KTAS TOTAL FUEL FLOW 18,000 1778 1799 1823 1845 1867 1889 1912 1935 lb/hr KIAS KTAS TOTAL FUEL FLOW 20,000 1807 1829 1853 1876 1899...
  • Page 728 Pilot’s Operating Manual GEAR DOWN CRUISE 11,000 ft TEMPERATURE RELATIVE TO ISA ºC CRUISE WEIGHT AMBIENT TEMP ºC KTAS TOTAL FUEL FLOW 18,000 1755 1777 1799 1821 1844 1867 1890 1913 lb/hr KIAS KTAS TOTAL FUEL FLOW 20,000 1784 1806 1829 1852 1876...
  • Page 729 Pilot’s Operating Manual GEAR DOWN CRUISE 13,000 ft TEMPERATURE RELATIVE TO ISA ºC CRUISE WEIGHT AMBIENT TEMP ºC KTAS TOTAL FUEL FLOW 18,000 1732 1755 1778 1800 1824 1847 1869 1892 lb/hr KIAS KTAS TOTAL FUEL FLOW 20,000 1762 1785 1808 1831 1855...
  • Page 730 Pilot’s Operating Manual GEAR DOWN CRUISE 15,000 ft TEMPERATURE RELATIVE TO ISA ºC CRUISE WEIGHT AMBIENT TEMP ºC KTAS TOTAL FUEL FLOW 18,000 1707 1730 1753 1776 1799 1823 1847 1870 lb/hr KIAS KTAS TOTAL FUEL FLOW 20,000 1737 1760 1784 1807 1832...
  • Page 731 Pilot’s Operating Manual GEAR DOWN CRUISE 17,000 ft TEMPERATURE RELATIVE TO ISA ºC CRUISE WEIGHT AMBIENT TEMP ºC KTAS TOTAL FUEL FLOW 18,000 1684 1706 1729 1754 1778 1801 1825 1847 lb/hr KIAS KTAS TOTAL FUEL FLOW 20,000 1713 1736 1761 1786 1811...
  • Page 732 Pilot’s Operating Manual GEAR DOWN CRUISE 19,000 ft TEMPERATURE RELATIVE TO ISA ºC CRUISE WEIGHT AMBIENT TEMP ºC KTAS TOTAL FUEL FLOW 18,000 1662 1685 1710 1735 1759 1783 1806 1829 lb/hr KIAS KTAS TOTAL FUEL FLOW 20,000 1692 1717 1743 1768 1791...
  • Page 733 Pilot’s Operating Manual GEAR DOWN CRUISE 20,000 ft TEMPERATURE RELATIVE TO ISA ºC CRUISE WEIGHT AMBIENT TEMP ºC KTAS TOTAL FUEL FLOW 18,000 1653 1677 1702 1727 1751 1773 1796 1820 lb/hr KIAS KTAS TOTAL FUEL FLOW 20,000 1685 1709 1734 1759 1783...
  • Page 734 Pilot’s Operating Manual GEAR DOWN DESCENT 210 KIAS TABLE UNITS Arrival Weight……….pounds FUEL………………………pounds DIST……………………….nautical miles TIME……………………….minutes ARRIVAL ALTITUDE (x 1000 ft) AT TOP OF DESCENT WEIGHT FUEL 17,000 DIST TIME FUEL 18,000 DIST TIME FUEL 19,000 DIST TIME FUEL 20,000 DIST TIME FUEL...
  • Page 735 Pilot’s Operating Manual Intentionally left blank Section IV - Sub-section 8 P/N 140-590032-0007 Page 8-24 Revision A3: Apr, 2008 GEAR DOWN PERFORMANCE...
  • Page 736 Pilot’s Operating Manual Section - IV FLIGHT PLANNING DATA Sub-section 9 EXTENDED RANGE OPERATIONS (Non-ETOPS) Table of Contents Page INTRODUCTION ..................9-3 EXTENDED RANGE OPERATIONS (Non-ETOPS) ........9-3 P/N 140-590032-0007 Page 9-1 Revision A5: Feb, 2012...
  • Page 737 Pilot’s Operating Manual Intentionally left blank Page 9-2 Section IV - Sub-section 9 P/N 140-590032-0007 Revision A5: Feb, 2012 EXTENDED RANGE OPERATIONS (Non-ETOPS)
  • Page 738 Pilot’s Operating Manual INTRODUCTION This section presents information for Hawker 800XP Part 135 operators to conduct flights without requiring FAA Extended Operations (ETOPS) approval. EXTENDED RANGE OPERATIONS (Non-ETOPS) The Hawker 800XP's 180 minute distance is 1027 nm. Any flight that remains within 1027 nm of an adequate airport at all times does not require the Part 135 certificate holder to have ETOPS authorization.
  • Page 739 Pilot’s Operating Manual The 180 minute distance of 1027 nm was calculated as follows: • From the Single Engine High Speed Descent data: Top Of Descent Descent Bottom Of Descent Altitude Weight Fuel Distance Time Altitude Weight (ft) (lb) (lb) (nm) (min) (ft)
  • Page 740 Pro Line 21 Section - V FLIGHT HANDLING Table of Contents Page Sub-section 1 - NORMAL HANDLING ...............1-1 Sub-section 2 - ABNORMAL HANDLING ............2-1 Pilot’s Operating Manual Page 1 Original Issue: Feb, 2002...
  • Page 741 Hawker 800XP Pro Line 21 Section V - FLIGHT HANDLING Intentionally left blank Page 2 Pilot’s Operating Manual- Original Issue: Feb, 2002...
  • Page 742 Pilot’s Operating Manual Section V FLIGHT HANDLING Sub-section 1 NORMAL HANDLING Table of Contents Page TAKEOFF AND DEPARTURE ................1-3 TAXI ......................1-3 THRUST REVERSERS (T/Rs) ..............1-3 ENGINE COMPUTER, RUDDER BIAS AND T/R CHECKS......1-3 ENGINE COMPUTERS ................1-3 RUDDER BIAS ..................1-4 T/Rs ......................1-4 TYPE OF RUNWAY SURFACE..............1-4 WET RUNWAY..................1-4 SLIPPERY RUNWAY ................1-5...
  • Page 743 Pilot’s Operating Manual Page TECHNIQUES FOR STALLS ..............1-16 STALL CHARACTERISTICS ..............1-16 AVIONICS AND NAVIGATION ..............1-17 FLIGHT MANAGEMENT SYSTEM (FMS)..........1-17 DURATION OF OXYGEN SUPPLY FOR PRIVATE CATEGORY AIRPLANES ............1-18 Table 3 - DURATION OF OXYGEN SUPPLY - PRIVATE CATEGORY ............
  • Page 744 Pilot’s Operating Manual TAKEOFF AND DEPARTURE TAXI The airplane may be taxied on normal hard areas. Directional control is normally exercised by nosewheel steering but differential wheel braking is available in the event of nosewheel steering failure. Figure 1 provides minimum turning radii. CAUTION: THE NOSEWHEEL STEERING SHOULD NOT BE MOVED WHILE THE AIRPLANE IS STATIONARY.
  • Page 745 Pilot’s Operating Manual Rudder Bias RUDDER BIAS switches A & B........OFF RUDDER BIAS annunciator..........Illuminated Left Thrust Lever.............. Advance to approximately 85% N Verify no movement of rudder pedals due to rudder bias input. RUDDER BIAS switch A ..........ON Verify rudder pedals deflect to the left.
  • Page 746 Pilot’s Operating Manual Slippery Runway A slippery runway is one which is either covered by compacted snow or is expected to have very low braking action due to the presence of wet ice. The coefficient of friction is: μ = 0.05 NOTE: A runway referred to as slippery, under these conditions, is extremely more slippery than a wet runway.
  • Page 747 Pilot’s Operating Manual Figure 1 Minimum Turn Radii Page 1-6 Section V Sub-section 1 P/N 140-590032-0007 Revision A4: Sep, 2010 NORMAL HANDLING...
  • Page 748 Pilot’s Operating Manual WHEEL BRAKES The normal wheel brake system incorporates Maxaret anti-skid units which automatically reduce the brake pressure should a wheel tend to skid. NOTE: The Maxaret unit does not operate until the wheel is revolving, therefore the brakes must not be applied before touchdown.
  • Page 749 Pilot’s Operating Manual NOTE: There is a fuel penalty when the engine antice systems are in use. Whether in icing conditions or not, the SCREEN HEAT L and R and the PITOT/VANE HEAT L and R should be selected ON in flight. The ICE DET switch should normally be set to AUTO, but before taxiing in icing conditions, it should be set to OVRD.
  • Page 750 Pilot’s Operating Manual TAKEOFF THRUST Initial take-off thrust is obtained when the thrust levers are set fully forward, the MAIN AIR VLVs and F/DK VLV closed with the annunciators on the MWS extinguished and APR armed. Compensated fan speed (N ) provides the indication of thrust and the Airplane Flight Manual Figures 5.05.1 (ENG ANTICE OFF) or 5.05.2 (ENG ANTICE ON) shows the value of N ) for...
  • Page 751 Pilot’s Operating Manual Figure 2 Flight Profile - Normal Takeoff Page 1-10 Section V Sub-section 1 P/N 140-590032-0007 Revision A4: Sep, 2010 NORMAL HANDLING...
  • Page 752 Pilot’s Operating Manual CLIMB Refer to Figure 3 for a Flight Profile of Climb, Cruise, and Descent. For the following procedures, refer to Section IV - FLIGHT PLANNING DATA. Climb fuel, distance and time are tabulated versus take-off weight and altitude at top of climb. The data is presented for temperatures in the range from ISA -15°C to ISA +20°C.
  • Page 753 Pilot’s Operating Manual Table 1 REFERENCE VALUES FOR MAXIMUM CLIMB ENGINE ANTI-ICING OFF - SYNC ON TEMPERATURE °C ALTITUDE -55 -50 -45 -40 -35 -30 -25 -20 -15 -10 -5. 10 15 20 25 30 35 40 98.7 99.8 100.0 100.0 100.0 99.7 98.8 98.0 97.1 41,000 98.7 99.8 100.0 100.0 100.0 100.0 99.0 98.3 97.4 96.5 40,000...
  • Page 754 Pilot’s Operating Manual Figure 3 Flight Profile - Climb, Cruise and Descent P/N 140-590032-0007 Section V Sub-section 1 Page 1-13 Revision A4: Sep, 2010 NORMAL HANDLING...
  • Page 755 Pilot’s Operating Manual CRUISE Refer to Figure 3 for a Flight Profile of Climb, Cruise, and Descent. The maximum cruising speed is limited by V , or maximum cruise rating. The recommended Intermediate cruising speed is: • 280 KIAS up to 29,000 ft. •...
  • Page 756 Pilot’s Operating Manual The airplane may require a small but increasing amount of lateral trim, particularly when changing airspeeds above 0.6 mach number. Care should be taken to monitor the trim indicator throughout the flight. NOTE: Center the trim indicator before disconnecting the autopilot. RUDDER CONTROL FORCE A load is imposed on the rudder control by a spring strut.
  • Page 757 Pilot’s Operating Manual Technique For Stalls The stalling technique is as follows: 1. All stalls are to be made in straight (wings level) flight. 2. Stalls with flaps retracted and in the take-off configuration should be carried out at idle thrust. To reduce altitude loss with approach or landing flaps, thrust should be adjusted not to exceed 77% N Once thrust is set it should not be reduced during the approach to the stall and recovery.
  • Page 758 Pilot’s Operating Manual Stall Characteristics (continued) It is acceptable for stick pusher operation to be coincident with the natural stall, provided that any rolling tendency can be restrained to within 20° of bank angle by normal use of ailerons. Some aerodynamic buffet may occur briefly at the point of stall.
  • Page 759 Pilot’s Operating Manual DURATION OF OXYGEN SUPPLY FOR PRIVATE CATEGORY AIRPLANES This table provides the oxygen duration times for complete depletion of the usable oxygen contents for emergency descent from altitude, followed by continued cruise at 15,000 feet. Oxygen is supplied to 2 crew members and all passengers NOTE: The crew regulator will be on 100% during the emergency descent and a 2 minutes period at 15,000 feet, then switched to the NORMAL mode.
  • Page 760 Pilot’s Operating Manual DURATION OF OXYGEN SUPPLY FOR COMPLIANCE WITH 14 CFR 91.211 This table provides the oxygen duration times for an emergency descent and continued cruise at 15,000 feet. After the given period, the airplane is required to descend to 12,500 feet. The oxygen supply to the passengers is stopped at this altitude by closing the passenger isolation valve.
  • Page 761 Pilot’s Operating Manual DURATION OF OXYGEN SUPPLY FOR COMPLIANCE WITH 14 CFR 135.157 This table provides the oxygen duration times for an emergency descent and continued cruise at 15,000 feet. Oxygen supply to the passengers is reduced to 10% ten minutes after oxygen initiation. After the given period, the airplane is required to descend to 10,000 feet.
  • Page 762 Pilot’s Operating Manual DESCENT and HOLDING DESCENT Descent procedures are based on the requirement that cabin rate of descent should not exceed approximately 300 feet per minute. The following table shows the minimum time to descend: Table 6 - Time Of Descent Cruising Altitude Feet Minimum Time Of Descent To 1500 Feet 41,000...
  • Page 763 Pilot’s Operating Manual HOLDING Holding, in normal conditions, is carried out with the airplane in a clean configuration. Holding speeds are given in Section IV - FLIGHT PLANNING DATA. Refer to Figures 4 and 5 for Flight Profiles of ILS and Non-Precision Approaches with holding anticipated.
  • Page 764 Pilot’s Operating Manual Figure 5 Flight Profile - Non-Precision Approach P/N 140-590032-0007 Section V Sub-section 1 Page 1-23 Revision A4: Sep, 2010 NORMAL HANDLING...
  • Page 765 Pilot’s Operating Manual APPROACH AND LANDING (Figures 4, 5 and 6) APPROACH Refer to Figures 4, 5 and 6 for ILS, Non-Precision and VFR Normal approaches. NORMAL LANDING Before the airplane descends below 200 feet, the MAIN AIR VLVs must be selected to CLOSE and the APR armed.
  • Page 766 Pilot’s Operating Manual Figure 6 Flight Profile - VFR Approach Normal P/N 140-590032-0007 Section V Sub-section 1 Page 1-25 Revision A4: Sep, 2010 NORMAL HANDLING...
  • Page 767 Pilot’s Operating Manual Intentionally left blank Page 1-26 Section V Sub-section 1 P/N 140-590032-0007 Revision A4: Sep, 2010 NORMAL HANDLING...
  • Page 768 Pro Line 21 Section - V FLIGHT HANDLING Sub-section 2 ABNORMAL HANDLING Table of Contents Page SLIPPERY RUNWAYS ................2-3 LANDING....................2-3 OPERATION IN HIGH SURFACE TAILWINDS ......... 2-3 REJECTED TAKEOFF BEFORE V ............2-3 CONTINUED TAKEOFF (ENGINE FAILURE AFTER V )......
  • Page 769 Hawker 800XP Pro Line 21 Section V - FLIGHT HANDLING Page Figure 4 - Symmetric Microburst ............2-15 Figure 5 - Asymmetric Microburst ............2-15 Figure 6 - Dry Microburst ..............2-15 DIAGRAM OF FLIGHT CREW ACTION ..........2-16 LESSONS LEARNED FROM WINDSHEAR ENCOUNTERS....2-16 STANDARD OPERATING TECHNIQUES..........
  • Page 770 Hawker 800XP Pro Line 21 Section V - FLIGHT HANDLING SLIPPERY RUNWAYS The following information is provided for operation on runways which are either: (a) Covered by compacted snow. (b) Expected to have very low braking action due to the presence of wet ice.
  • Page 771 Hawker 800XP Pro Line 21 Section V - FLIGHT HANDLING CONTINUED TAKEOFF (ENGINE FAILURE AFTER V The APR system should automatically apply APR power which will be indicated by the APR green ON legend being illuminated and, unless on the flat rating, a rise of N If the APR green ON legend remains extinguished, immediately push the APR OVRD switch.
  • Page 772 Hawker 800XP Pro Line 21 Section V - FLIGHT HANDLING Figure 1 Flight Profile Takeoff: Engine Failure After V with APR-High and Low Performance Profiles Sub-section 2 Pilot’s Operating Manual Page 2-5 ABNORMAL HANDLING Original Issue: Feb, 2002...
  • Page 773 Hawker 800XP Pro Line 21 Section V - FLIGHT HANDLING CRUISE WITH ONE ENGINE INOPERATIVE Performance data for Single Engine Operation can be found in Section IV - FLIGHT PLANNING DATA Sub-section 6. If an engine fails, thrust may be increased up to maximum continuous on the operating engine, to minimize the loss of speed and altitude.
  • Page 774 Section V - FLIGHT HANDLING ICING CONDITIONS The Hawker 800XP is approved for flight in icing conditions, however, good airmanship dictates that icing conditions must be avoided whenever possible, due to the following reasons: • Ice and snow accumulation will reduce the aerodynamic efficiency of the airplane by increasing drag and diminishing lift due to airfoil deformation.
  • Page 775 Hawker 800XP Pro Line 21 Section V - FLIGHT HANDLING BEFORE TAKE-OFF Prime the airframe ice protection system by setting the WING/TAIL ANTICE time switch to run the pump for two minutes. Check that priming is complete before start of takeoff.
  • Page 776 Hawker 800XP Pro Line 21 Section V - FLIGHT HANDLING NOTES: CONTINUED 3. This is a recommended speed. However, if it is necessary to take advantage of the full range of airspeeds permitted for flight in icing conditions and if other conditions permit, the airspeed may be adjusted to within the limits given in Figure 2.
  • Page 777 Hawker 800XP Pro Line 21 Section V - FLIGHT HANDLING NOTES: 1. The procedural use of flap 15° for descent is not permitted in icing conditions. 2. In icing conditions, ice may accumulate on the unprotected areas between the TKS panels on the leading edges of the wings.
  • Page 778 Hawker 800XP Pro Line 21 Section V - FLIGHT HANDLING LEAVING ICING CONDITIONS ENG ANTICE 1 and 2............OFF ENG IGNITION 1 and 2 ............OFF WING/TAIL ANTICE time switch .......... Zero SEVERE ICING CONDITIONS WARNING: SEVERE ICING MAY RESULT FROM ENVIRONMENTAL CONDITIONS OUTSIDE OF THOSE FOR WHICH THE AIRPLANE IS CERTIFIED.
  • Page 779 Hawker 800XP Pro Line 21 Section V - FLIGHT HANDLING PROCEDURES FOR EXITING SEVERE ICING CONDITIONS These procedures are applicable to all flight phases from takeoff to landing. Monitor the ambient air temperature. While severe icing may form at temperatures as cold as -18° C, increased vigilance is warranted at temperatures near freezing with visible moisture present.
  • Page 780 Hawker 800XP Pro Line 21 Section V - FLIGHT HANDLING CLEAR AIR and NON-STORM TURBULENCE Airspeed need not be reduced except for reasons of passenger comfort. If it is changed, it is recommended that an airspeed of 230 knots IAS or 0.7 M be used.
  • Page 781 Hawker 800XP Pro Line 21 Section V - FLIGHT HANDLING OPERATION IN WINDSHEAR AND MICROBURST CONDITIONS CONVECTIVE WEATHER This term is taken to mean highly active areas of weather energy such as thunderstorms, rainstorms, virga, extreme turbulence, or tornadoes due to local heating/cooling effects.
  • Page 782 Hawker 800XP Pro Line 21 Section V - FLIGHT HANDLING Figure 4 Symmetric Microburst An airplane transiting this type of microburst would experience equal headwinds and tailwinds. Figure 5 Asymmetric Microburst An airplane transiting the microburst from left to right would experience a small headwind followed by a large tailwind.
  • Page 783 Hawker 800XP Pro Line 21 Section V - FLIGHT HANDLING DIAGRAM OF FLIGHT CREW ACTION Due to the serious threat imposed by infrequent windshear encounters, an orderly set of actions is necessary to increase flight crew awareness of weather conditions that produce windshear.
  • Page 784 Hawker 800XP Pro Line 21 Section V - FLIGHT HANDLING These additional lessons are: • Recognition is difficult and is usually complicated by marginal weather. • Time available for recognition and recovery is short (as little as 5 seconds). • Aircrew co-ordination is essential for prompt windshear recognition and recovery.
  • Page 785 Hawker 800XP Pro Line 21 Section V - FLIGHT HANDLING Avoid Known Windshear The importance of avoiding severe windshear and microbursts cannot be over-emphasized. Microburst windshears exist which are beyond the capability of even the largest of airplanes and the most highly skilled pilots.
  • Page 786 Hawker 800XP Pro Line 21 Section V - FLIGHT HANDLING A Key To the Previous Information Is: HIGH Probability • Critical attention to be given to this observation. • A decision to avoid should be made. MEDIUM Probability • Consideration should be given to avoiding.
  • Page 787 The choice also involves consideration of exposure to obstacles after lift off and crosswind and tailwind limitations. Take-off Flap Selection No recommendations have been determined for the use of specific flap settings on takeoff for the Hawker 800XP Pro Line 21 series airplane. Increased Rotation Airspeed 1. Determine V , and V speeds for actual airplane gross weight and flap setting.
  • Page 788 Hawker 800XP Pro Line 21 Section V - FLIGHT HANDLING Windshear effect may force rotation at speed below V . Rotation should begin no later than 2,000 ft from end of usable runway. Figure 7 Windshear Effects on Rotation Decision Approach Precautions 1.
  • Page 789 Hawker 800XP Pro Line 21 Section V - FLIGHT HANDLING Microburst reduces airspeed and lift at normal attitude which results in pitch down tendency to regain airspeed. Figure 8 Windshear Effects on Flight Path During Approach Thrust Management Rather than immediately compensating for an airspeed increase by reducing thrust, a brief pause to evaluate speed trends is prudent.
  • Page 790 Hawker 800XP Pro Line 21 Section V - FLIGHT HANDLING Flight Director and Autopilot During approach it is desirable to utilize the flight director and autopilot to the maximum extent practical. However, use of autoflight systems only provide benefits in terms of decreased workload if this allows the aircrew more time to monitor instruments and weather conditions.
  • Page 791 Hawker 800XP Pro Line 21 Section V - FLIGHT HANDLING Aircrew Co-ordination Pilot Flying: Should focus attention on flying, taking appropriate action in response to call-outs in a windshear encounter. Pilot Not Flying: Should focus attention on: • Airspeed • Vertical speed •...
  • Page 792 Hawker 800XP Pro Line 21 Section V - FLIGHT HANDLING Recovery Technique 1. Thrust - immediately apply full power. 2. Pitch - At normal V rotate toward 12° at normal pitch rate (but no later than 2000 ft of usable runway remaining, even if below V ).
  • Page 793 Hawker 800XP Pro Line 21 Section V - FLIGHT HANDLING REPORT THE ENCOUNTER Report the encounter as soon as possible after recovery. Use the following format: 1. Maximum loss or gain of airspeed. 2. Altitude at which shear was encountered.
  • Page 794 OPERATION IN AREAS CONTAMINATED BY VOLCANIC ASH Operation of the Hawker 800XP airplane, both in flight and on the ground, in areas contaminated by volcanic ash or dust must be avoided. However, the following information is offered should volcanic ash be unavoidably encountered.
  • Page 795 Hawker 800XP Pro Line 21 Section V - FLIGHT HANDLING APPROACH AND LANDING (ONE ENGINE INOPERATIVE) Refer to Figure 9 for a Flight Profile of Non - Precision Approach (Single Engine) Refer to Figure 10 for a Flight Profile of ILS Approach (Single Engine)
  • Page 796 Hawker 800XP Pro Line 21 Section V - FLIGHT HANDLING LANDING ABOVE WAT LIMIT WITH ONE OR BOTH ENGINES OPERATING Refer to Figure 13 for a Flight Profile of ILS Approach - Landing Above WAT Limit If a landing has to be made shortly after takeoff at a weight at or close to the maximum given in the Airplane Flight Manual Figure 5.15.1, where the required approach climb gross gradient of 2.1% cannot...
  • Page 797 Hawker 800XP Pro Line 21 Section V - FLIGHT HANDLING LANDING BY USE OF TRIM SYSTEM Should failure of any one of the primary flying controls occur, the following landing technique is recommended. Maneuvering in the traffic pattern should be made at approximately 160 KIAS with flaps 15° and the landing gear down.
  • Page 798 Hawker 800XP Pro Line 21 Section V - FLIGHT HANDLING Figure 9 Flight Profile - Non-Precision Approach-Single Engine Sub-section 2 Pilot’s Operating Manual Page 2-31 ABNORMAL HANDLING Original Issue: Feb, 2002...
  • Page 799 Hawker 800XP Pro Line 21 Section V - FLIGHT HANDLING Figure 10 Flight Profile - ILS Approach-Single Engine Sub-section 2 Page 2-32 Pilot’s Operating Manual ABNORMAL HANDLING Original Issue: Feb, 2002...
  • Page 800 Hawker 800XP Pro Line 21 Section V - FLIGHT HANDLING Figure 11 Flight Profile - VFR Approach-Single Engine Sub-section 2 Pilot’s Operating Manual Page 2-33 ABNORMAL HANDLING Original Issue: Feb, 2002...
  • Page 801 Hawker 800XP Pro Line 21 Section V - FLIGHT HANDLING Figure 12 Flight Profile - VFR No Flap Approach Sub-section 2 Page 2-34 Pilot’s Operating Manual ABNORMAL HANDLING Original Issue: Feb, 2002...
  • Page 802 Hawker 800XP Pro Line 21 Section V - FLIGHT HANDLING Figure 13 Flight Profile - ILS Approach-Landing Above WAT Limit Sub-section 2 Pilot’s Operating Manual Page 2-35 ABNORMAL HANDLING Original Issue: Feb, 2002...
  • Page 803 They contain the best available advice, being based largely on model ditching tests on the British Royal Air Force Dominie and general ditching procedures of other airplane (reference R & M No. 2917). These recommendations are not based on tests made with a Hawker 800XP. No such tests have been carried out.
  • Page 804 Hawker 800XP Pro Line 21 Section V - FLIGHT HANDLING Depressurization • Depressurize cabin by 1500 ft above sea level. • Close MAIN AIR VALVES 1 and 2 and check that the dump valve is closed. During Descent • Switch on all external lights to aid location of the airplane.
  • Page 805 Hawker 800XP Pro Line 21 Section V - FLIGHT HANDLING Intentionally left blank Sub-section 2 Page 2-38 Pilot’s Operating Manual ABNORMAL HANDLING Revision A2: Nov, 2004...
  • Page 806 Pro Line 21 Section - VI GROUND OPERATIONS Table of Contents Page Sub-section 1 - GROUND HANDLING ..............1-1 Sub-section 2 - GROUND SERVICING .............2-1 Pilot’s Operating Manual Page 1 Original Issue: Feb, 2002...
  • Page 807 Hawker 800XP Pro Line 21 Section VI - GROUND OPERATIONS Intentionally left blank Page 2 Pilot’s Operating Manual- Original Issue: Feb, 2002...
  • Page 808 Pilot’s Operating Manual Section VI GROUND OPERATIONS Sub-section 1 GROUND HANDLING Table of Contents Page INTRODUCTION ................... 1-3 AIRPLANE DE-ICING .................. 1-3 EQUIPMENT NECESSARY ................. 1-3 SNOW REMOVAL ..................1-4 FROZEN SNOW AND ICE FILMS..............1-5 FROST REMOVAL ..................1-5 ICE REMOVAL .....................
  • Page 809 Pilot’s Operating Manual Page PARKING and MOORING (Continued) Figure 3 - Thrust Reverser Locking Pins..........1-16 COVERS AND BLANKS ................1-17 Installation of Engine Covers..............1-17 Figure 4 - Covers and Blanks..............1-17 MOORING....................1-18 Mooring Procedure................1-18 Figure 5 - Airplane Mooring..............1-18 Figure 6 - Main and Nose Landing Gear Mooring........
  • Page 810 Pilot’s Operating Manual INTRODUCTION This Sub-section contains information for the ground handling of the Hawker 800XP Pro Line 21 airplane. The procedures are provided for pilots who may be required to accomplish their own ground handling. AIRPLANE DE-ICING CAUTION: DO NOT OPERATE THE APU (IF INSTALLED) WHILE DE-ICING IS IN PROGRESS.
  • Page 811 Holdover time tables, obtained from www.faa.gov, search "HOLDOVER TIME TABLES", shall only be used as part of an approved ground-deicing program. When the website cannot be accessed or questions arise, contact FAA Flight Standards, Washington D.C. at 202-267-8166 or Hawker Beechcraft Corporation at 1-800-429-5372 or 316-676-3140.
  • Page 812 Pilot’s Operating Manual If ice has formed under the snow, clear by spraying with de-icing fluid. Special attention should be given to all vents, openings, static ports, control surfaces, hinge points, and the wing, tail, and fuselage surfaces for obstructions or accumulations of snow. Check the exterior of the airplane for damage to external components that may have occurred during the snow removal operations.
  • Page 813 Pilot’s Operating Manual Control surfaces should be moved to confirm full and free movement. The landing gear mechanism, doors, wheel wells, uplocks and microswitches should be checked for ice deposits that may impair function. NOTE: When the airplane is hangared to melt ice, any melted ice may freeze again if the airplane is subsequently moved into freezing temperatures.
  • Page 814 Pilot’s Operating Manual REMOVAL OF SALT OR CHEMICAL AGENTS CAUTION: DO NOT USE HIGH PRESSURE WATER AS DAMAGE MAY RESULT TO ELECTRICAL EQUIPMENT AND LUBRICATED COMPONENTS. Where contamination has occurred on the structure after landing at airfields where snow and ice had been dispersed with salt or chemical agents, carry out the following: •...
  • Page 815 Pilot’s Operating Manual COLD WEATHER PROCEDURES (Snow, Slush and Ice) PREFLIGHT INSPECTION Make sure that the tires are not frozen to the ramp, and that the brakes are free of ice contamination. De-icing or anti-icing solutions may be used on the tires and brakes if they are frozen. Solutions which contain a lubricant, such as oil, must not be used as they will decrease the effectiveness of the brakes.
  • Page 816 Pilot’s Operating Manual TAKEOFF Allow additional take-off distance when snow or slush is on the runway. Extra cycling of the landing gear when above 500 feet AGL may help clear any contamination from the gear system. LANDING Braking and steering are less effective on slick runways. Also, at higher speeds, hydroplaning may occur under wet runway conditions.
  • Page 817 Pilot’s Operating Manual COLD SOAK CONDITIONS INTRODUCTION This section provides information for operation of the airplane into and out of airfields where the local ambient temperature is predominantly below -20° C and the airplane cannot be housed in a heated hangar.
  • Page 818 Holdover time tables, obtained from www.faa.gov, search "HOLDOVER TIME TABLES", shall only be used as part of an approved ground-deicing program. When the website cannot be accessed or questions arise, contact FAA Flight Standards, Washington D.C. at 202-267-8166 or Hawker Beechcraft Corporation at 1-800-429-5372 or 316-676-3140.
  • Page 819 Pilot’s Operating Manual ENGINE START Check the following are free of ice and snow: • Engine Intakes • Fan Blades • Spinners and Cowlings • Vents • Inlets • Drains • Jet Exhausts To assist satisfactory starts, approximately 10 minutes before start, motor each engine for 30 seconds with the fuel off.
  • Page 820 Pilot’s Operating Manual GROUND MANEUVERING TOWING Towbar 25-6Y1647 uses the steering disconnect pin 25-8UN357 as a towing pin. The shear pins for the towbar are: • Pt. No. 25-6Y1659 for side loads • Pt. No. 25-6Y1661 for push/pull loads Towing Procedure 1.
  • Page 821 Pilot’s Operating Manual CAUTION: MAKE SURE THE QUICK RELEASE PIN IS PROPERLY INSTALLED. Figure 1 Towbar Installation Page 1-14 Section VI Sub-section 1 P/N 140-590032-0007 Revision A4: Sep, 2010 GROUND HANDLING...
  • Page 822 Pilot’s Operating Manual PARKING and MOORING PARKING Parking Procedure 1. Position the airplane nose into wind and center the nose gear wheels. 2. Place the WHEELBRAKE lever fully to the PARK position. 3. Install the landing gear locking pins (Figure 2). If required, the nose gear doors can be opened manually.
  • Page 823 Pilot’s Operating Manual STOWED POSITION DEPLOYED POSITION Figure 3 Thrust Reverser Locking Pins Page 1-16 Section VI Sub-section 1 P/N 140-590032-0007 Revision A4: Sep, 2010 GROUND HANDLING...
  • Page 824 Pilot’s Operating Manual COVERS AND BLANKS (Figure 4) Covers and blanks should be used to protect the following: • Stall Warning Vents • Cold Air Unit Exhaust • Static Vents • Engine Intake and Exhaust • Pitot Heads • APU (if installed) Intake, Exhaust and Generator Cooling •...
  • Page 825 Pilot’s Operating Manual MOORING CAUTION: ATTACH MOORING ROPES ONLY TO THE PARTS OF THE STRUCTURE SHOWN IN FIGURES 5 AND 6. Mooring Procedure 1. Provided the airplane is headed into wind and the parking brakes are used in conjunction with chocks front and rear of the main and nose gear wheels, no mooring is necessary in winds of less than 40 knots.
  • Page 826 Pilot’s Operating Manual 60 to 80 KNOTS If the airplane cannot be flown out or hangared: • Airplane headed into wind • Fueled • Brakes on • Wheel chocks lashed • Main wheels moored with additional turns • Nose wheel moored MAIN GEAR NOSE GEAR Figure 6...
  • Page 827 Pilot’s Operating Manual GUST LOCKS INSTALLATION OF AILERONS and ELEVATOR GUST LOCK (Figure 7) 1. Release the gust lock from the stowage clip. Set the control column fully forward and fully left. Swing the lock around, and with the handwheel in the neutral position, attach the claws on the handwheel. 2.
  • Page 828 Pilot’s Operating Manual INSTALLATION OF RUDDER GUST LOCK (Figure 8) 1. Remove the gust lock from the stowage. 2. Set the rudder pedals at the neutral position. 3. Lift the cover in the floor and insert the gust lock through the gust lock lever and bracket. REMOVAL OF RUDDER GUST LOCK 1.
  • Page 829 Pilot’s Operating Manual Intentionally left blank Page 1-22 Section VI Sub-section 1 P/N 140-590032-0007 Revision A4: Sep, 2010 GROUND HANDLING...
  • Page 830 Pro Line 21 Section - VI GROUND OPERATIONS Sub-section 2 GROUND SERVICING Table of Contents Page INTRODUCTION ..................... 2-3 ENGINE GROUND RUNNING ................ 2-3 ENGINE START ................... 2-3 Figure 1 - Engine Danger Zones .............. 2-4 ENGINE SHUTDOWN.................. 2-4 ENGINE OIL SERVICING ................2-5 Table 1: Engine Oil Capacities ..............
  • Page 831 Hawker 800XP Pro Line 21 Section VI - GROUND OPERATIONS Page HYDRAULIC SYSTEM ................. 2-41 TANK CAPACITIES ................... 2-41 Table 4: Capacities of Reservoirs ............2-41 CHECK HYDRAULIC PRESSURE ............2-41 RELEASE HYDRAULIC PRESSURE ............2-41 CHECK MAIN HYDRAULIC SYSTEM RESERVOIR ......... 2-41 Table 5: Equipment and Materials ............
  • Page 832 Hawker 800XP Pro Line 21 Section VI - GROUND OPERATIONS INTRODUCTION This Sub-section contains information for the ground servicing of the Hawker 800XP Pro Line 21 airplane. The procedures are provided for pilots who may be subjected to completing their own ground servicing.
  • Page 833 Hawker 800XP Pro Line 21 Section VI - GROUND OPERATIONS FULL THROTTLE Velocity falls below 15 MPH FULL THROTTLE Temperature ° below 30 16 ft Radius 75 ft 150 ft Area to be cleared prior to engine start. Area to be cleared if take-off power is to be used.
  • Page 834 Hawker 800XP Pro Line 21 Section VI - GROUND OPERATIONS ENGINE OIL SERVICING WARNING: SYNTHETIC OIL CAN BE TOXIC, AVOID PROLONGED CONTACT WITH THE SKIN. CAUTION: DO NOT ALLOW OIL TO CONTAMINATE THE AIRPLANE OR EXTERIOR OF THE ENGINE. Table 1 - Engine Oil Capacities Measurements U.S.
  • Page 835 Hawker 800XP Pro Line 21 Section VI - GROUND OPERATIONS Replenish Engine Oil via the Oil Tank (Right Side of Engine - Figure 3) 1. Open the cowling lower door to get access to the oil tank on the right side of the engine.
  • Page 836 Hawker 800XP Pro Line 21 Section VI - GROUND OPERATIONS INBOARD LEFT ENGINE OUTBOARD RIGHT ENGINE Figure 2 Engine Oil Contents Viewing Ports Sub-section 2 Pilot’s Operating Manual Page 2-7 GROUND SERVICING Revision A2: Nov, 2004...
  • Page 837 Hawker 800XP Pro Line 21 Section VI - GROUND OPERATIONS Figure 3 Engine Oil System Replenishment Details Sub-section 2 Page 2-8 Pilot’s Operating Manual GROUND SERVICING Revision A2: Nov, 2004...
  • Page 838 Hawker 800XP Pro Line 21 Section VI - GROUND OPERATIONS THRUST REVERSERS WARNING: MAKE SURE THE THRUST REVERSER SYSTEM IS DISABLED BEFORE ANY WORK IS COMPLETED ON THE SYSTEM OR ANY OTHER SYSTEM WHICH IS OPERATED BY ELECTRICAL AND/OR HYDRAULIC POWER.
  • Page 839 Hawker 800XP Pro Line 21 Section VI - GROUND OPERATIONS FUEL SYSTEM GENERAL Fuel is stored in integral tanks in each wing and in a ventral tank beneath the rear fuselage, as shown in Figure 5. All tanks can be pressure refuelled and defueled, through a coupling which is accessible through a door on the right side of the ventral tank rear fairing, or alternatively, all tanks can be gravity filled through a filler neck in each tank.
  • Page 840 Hawker 800XP Pro Line 21 Section VI - GROUND OPERATIONS APPROVED FUEL SPECIFICATIONS Aviation Kerosene to the current approved issue of specifications • British ......DEF STAN 91-87 D.E.R.D. 2453 DEF STAN 91-91 D.E.R.D. 2494 • American ..... ASTM D1655/JET A...
  • Page 841 Hawker 800XP Pro Line 21 Section VI - GROUND OPERATIONS VENT COLLECTOR VENTRAL TANK BOND POINT TANK DRAIN VALVE REAR WALL (FAIRING REMOVED) FUEL DRAIN VALVE ENG 2 REFUEL FUEL GRAVITY REFUEL BONDING WING FUEL REAR BAY POINT (ACCESS SPIGOT...
  • Page 842 Hawker 800XP Pro Line 21 Section VI - GROUND OPERATIONS OPERATION OF THE PRESSURE REFUELING COUPLING (Figure 7) To Remove The Cover From The Airplane Coupling 1. Open the access door. 2. Slide the finger hole towards the center to release the handle.
  • Page 843 Hawker 800XP Pro Line 21 Section VI - GROUND OPERATIONS Figure 7 Pressure Refueling Coupling Sub-section 2 Page 2-14 Pilot’s Operating Manual GROUND SERVICING Revision A2: Nov, 2004...
  • Page 844 Hawker 800XP Pro Line 21 Section VI - GROUND OPERATIONS PRESSURE and GRAVITY FUELING The airplane provides for pressure refueling through a coupling at the rear of the ventral tank (Figure 6) or by gravity refueling through a filler cap in each outer wing (Figure 9) and the left side of the ventral tank rear wall (Figure 10).
  • Page 845 Hawker 800XP Pro Line 21 Section VI - GROUND OPERATIONS Figure 8 Water Drain Tool To Drain Water From The Wing Center Tanks, Use This Release Tool With The Extension Blade. 1. Insert the blade of the release tool in the slot of the drain valve spindle.
  • Page 846 Hawker 800XP Pro Line 21 Section VI - GROUND OPERATIONS PRESSURE REFUELING and DEFUELING Pressure Refueling Before starting the procedure, operators of airplanes equipped with a ventral tank must read the refueling instructions given in 25-8PF315 AIRPLANES WITH VENTRAL TANK. This document is located in the manual stowage area in the airplane.
  • Page 847 Hawker 800XP Pro Line 21 Section VI - GROUND OPERATIONS Test Refuel Control System Before Refuel (continued) (c) Push the RIGHT OVER FLOW PRESS TO TEST and check: • OVER FLOW is indicated. • MASTER VALVE indicates SHUT. • All three REFUEL VALVES indicate SHUT.
  • Page 848 Hawker 800XP Pro Line 21 Section VI - GROUND OPERATIONS Connect and Disconnect the Refuel Hose (Figures 6). To remove the cover from the airplane coupling: (a) Open the access door. (b) Push the finger hole towards the center to release the handle, then turn the handle counter-clockwise to remove the cover.
  • Page 849 Hawker 800XP Pro Line 21 Section VI - GROUND OPERATIONS Preparation for Pressure Refueling Specific preparations are provided below for airplanes which have Service Bulletin SB 24-3641 incorporated or do not have Service Bulletin SB 24-3641 incorporated: I. Airplane Serial No. 258670 and subsequent, or airplanes with Raytheon Aircraft Company...
  • Page 850 Hawker 800XP Pro Line 21 Section VI - GROUND OPERATIONS Preparation for Pressure Refueling (continued) II. Airplanes prior to airplane Serial No. 258670 which do not have Raytheon Aircraft Company Service Bulletin SB 24-3641 incorporated and pressure refueling with the airplane batteries only: Calculate the fuel load required.
  • Page 851 Hawker 800XP Pro Line 21 Section VI - GROUND OPERATIONS Preparation for Pressure Refueling (continued) (5) If the wings are to be only partially filled, check the wing FUEL contents displayed on the CDU and make sure the indication shows the correct current fuel state.
  • Page 852 Hawker 800XP Pro Line 21 Section VI - GROUND OPERATIONS Pressure Refueling Procedure (continued) (7) Partial filling of wing tanks only - Select each wing tank REFUEL switch to OFF when tank content is: Contents Required for Each Wing lb (kg)
  • Page 853 Hawker 800XP Pro Line 21 Section VI - GROUND OPERATIONS Defueling Preparation for Suction Defueling Specific preparations are provided below for airplanes which have Service Bulletin SB 24-3641 incorporated or do not have Service Bulletin SB 24-3641 incorporated: I. Airplane Serial No. 258670 and subsequent, or airplanes with Raytheon Aircraft Company...
  • Page 854 Hawker 800XP Pro Line 21 Section VI - GROUND OPERATIONS Preparation for Suction Defueling (continued) II. Airplanes prior to airplane Serial No. 258670 which do not have Raytheon Aircraft Company Service Bulletin SB 24-3641 incorporated and suction defueling with the airplane batteries only: Calculate the fuel quantity to be off-loaded.
  • Page 855 Hawker 800XP Pro Line 21 Section VI - GROUND OPERATIONS Suction Defueling Procedure CAUTION: DO NOT EXCEED MAXIMUM DEFUEL SUCTION OF 11.0 psi (0.759 bar). (1) Bond the refuel vehicle or hydrant to the airplane. (2) Open the fuel coupling access door, remove protective covers, connect bonding lead of hose coupling to airplane grounding point, connect refuel/defuel hose to the airplane coupling (Figures 6 &...
  • Page 856 Hawker 800XP Pro Line 21 Section VI - GROUND OPERATIONS GRAVITY REFUELING and DEFUELING Gravity Refueling Wing Tanks Preparation for Gravity Refueling Wing Tanks Specific preparations are provided below for airplanes which have Service Bulletin SB 24-3641 incorporated or do not have Service Bulletin SB 24-3641 incorporated: I.
  • Page 857 Hawker 800XP Pro Line 21 Section VI - GROUND OPERATIONS Preparation for Gravity Refueling Wing Tanks (continued) (5) If the wings are to be only partially filled, check the wing FUEL contents displayed on the pilot’s CDU and make sure the indication shows the correct current fuel state.
  • Page 858 Hawker 800XP Pro Line 21 Section VI - GROUND OPERATIONS Preparation for Gravity Refueling Wing Tanks (continued) III. All airplanes gravity refueling wing tanks when external power or the APU is available: Calculate the fuel quantity to be off-loaded. CAUTION: INVESTIGATE ANY CONTAMINATION, OTHER THAN WATER, OF THE FOLLOWING DRAINED SAMPLE.
  • Page 859 Hawker 800XP Pro Line 21 Section VI - GROUND OPERATIONS Gravity Refueling Wing Tanks Procedure (continued) (8) Remove the refuel nozzle, install and lock the filler cap, disconnect nozzle bonding lead. (a) Engage the cap into the skin adapter with the arrow on the cap pointed forward.
  • Page 860 Hawker 800XP Pro Line 21 Section VI - GROUND OPERATIONS Gravity Refueling Ventral Tank Preparation for Gravity Refueling Ventral Tank Specific preparations are provided below for airplanes which have Service Bulletin SB 24-3641 incorporated or do not have Service Bulletin SB 24-3641 incorporated: I.
  • Page 861 Hawker 800XP Pro Line 21 Section VI - GROUND OPERATIONS Preparation for Gravity Refueling Ventral Tank (continued) II. Airplanes prior to airplane Serial No. 258670 which do not have Raytheon Aircraft Company Service Bulletin SB 24-3641 incorporated and gravity refueling ventral tank with the airplane batteries only: Calculate the fuel load required.
  • Page 862 Hawker 800XP Pro Line 21 Section VI - GROUND OPERATIONS Gravity Refuel Ventral Tank Procedure (1) Check the VENTRAL tank contents legend on the CDU displays EMPTY. (2) Check the AUX FUEL TRANSFER valve is shut (lever up). (3) Bond the refuel vehicle or hydrant to the airplane.
  • Page 863 Hawker 800XP Pro Line 21 Section VI - GROUND OPERATIONS Equipment Required: • Gravity Defuel Drain Adapter P/N 25Y867A (Figure 11). • Suction Defuel Drain Adapter P/N 25Y635A. NOTES: 1. 25Y867A is a sub-assembly of 25Y635A and can be obtained separately.
  • Page 864 Hawker 800XP Pro Line 21 Section VI - GROUND OPERATIONS To Remove the Filler Cap 1. Lift the handle from the recess. 2. Rotate the handle to release the cap. 3. Withdraw the cap from the skin adapter. To Reinstall the Filler Cap 1.
  • Page 865 Hawker 800XP Pro Line 21 Section VI - GROUND OPERATIONS Figure 10 Ventral Tank Filler Cap Sub-section 2 Page 2-36 Pilot’s Operating Manual GROUND SERVICING Revision A2: Nov, 2004...
  • Page 866 Hawker 800XP Pro Line 21 Section VI - GROUND OPERATIONS WING LEADING EDGE FUEL DRAIN ADAPTER 25Y-867A M8009_0.AI Figure 11 Gravity Defueling Drain Adaptor Sub-section 2 Page 2-37 Pilot’s Operating Manual GROUND SERVICING Revision A2: Nov, 2004...
  • Page 867 Hawker 800XP Pro Line 21 Section VI - GROUND OPERATIONS ELECTRICAL SYSTEM CAUTION: IF IT IS INTENDED TO PARK THE AIRPLANE IN AMBIENT TEMPERATURES BELOW -10° C FOR A PERIOD OF 12 HOURS OR MORE, THE AIRPLANE BATTERIES MUST BE REMOVED TO A WARMER ENVIRONMENT.
  • Page 868 Hawker 800XP Pro Line 21 Section VI - GROUND OPERATIONS APU (if installed) Running at Governed Speed Ground Supply Generator Check the APU MASTER, BATTERY, EXT POWER and external On the APU control panel, ground supply switches are selected OFF.
  • Page 869 Hawker 800XP Pro Line 21 Section VI - GROUND OPERATIONS Figure 13 External Ground Power Receptacle Pilot’s Operating Manual Page 2-40 Sub-section 2 Revision A2: Nov, 2004 GROUND SERVICING...
  • Page 870 Hawker 800XP Pro Line 21 Section VI - GROUND OPERATIONS HYDRAULIC SYSTEM TANK CAPACITIES Table 4 - Capacities of Reservoirs Reservoir U.S. Pints Liters Main 19.22 9.10 Auxiliary 6.01 2.84 CHECK HYDRAULIC PRESSURE 1. Energize the DC busbars. 2. Read the pressure indication on the hydraulic main system gauge on the triple indicator (Figure 14).
  • Page 871 Hawker 800XP Pro Line 21 Section VI - GROUND OPERATIONS REPLENISH MAIN RESERVOIR (Figure 15 & 16) CAUTION: BEFORE REPLENISHMENT, MAKE SURE THE FILTER IN THE FILLER NECK IS IN POSITION AND UNDAMAGED. ALWAYS USE A CLEAN CONTAINER AND CLEAN FLUID.
  • Page 872 Hawker 800XP Pro Line 21 Section VI - GROUND OPERATIONS 5. If necessary, charge the accumulators through the charging valves with a supply of dry nitrogen. CAUTION: APPLY NITROGEN SLOWLY TO PREVENT DAMAGE TO THE ACCUMULATORS AND TO PREVENT FALSE READINGS DUE TO OVERHEATING.
  • Page 873 Hawker 800XP Pro Line 21 Section VI - GROUND OPERATIONS LEVEL INDICATOR FILLER CAP FULL THREE LARGE ACCS EMPTY FULL ONE LEVEL INDICATOR FILLER CAP LARGE ACC 3000 PSI AUXILIARY RESERVOIR FULL TWO LARGE ACCS 3000 PSI FULL THREE LARGE ACCS...
  • Page 874 Hawker 800XP Pro Line 21 Section VI - GROUND OPERATIONS Figure 16 Main Hydraulic Reservoir Sub-section 2 Pilot’s Operating Manual Page 2-45 GROUND SERVICING Revision A2: Nov, 2004...
  • Page 875 Hawker 800XP Pro Line 21 Section VI - GROUND OPERATIONS LANDING GEAR TIRE PRESSURES Tire Inflation Gauge NT62604MSB Tire Inflation Trolley Local Supply The following pressures may be used, up to maximum take-off weight, for general operation from normal runway surfaces. These values are with Weight-On-Wheels.
  • Page 876 Hawker 800XP Pro Line 21 Section VI - GROUND OPERATIONS Figure 17 Variation of Minimum Nosewheel Tire Pressure with Take-off and Landing Weights Sub-section 2 Pilot’s Operating Manual Page 2-47 GROUND SERVICING Revision A2: Nov, 2004...
  • Page 877 Hawker 800XP Pro Line 21 Section VI - GROUND OPERATIONS Figure 18 Variation of Minimum Mainwheel Tire Pressure with Take-off and Landing Weights Sub-section 2 Page 2-48 Pilot’s Operating Manual GROUND SERVICING Revision A2: Nov, 2004...
  • Page 878 Hawker 800XP Pro Line 21 Section VI - GROUND OPERATIONS WHEEL REMOVAL Special tools are required for wheel removal and installation, therefore, reference must be made to the Airplane Maintenance Manual. TREAD WEAR CHECK 1. Unless otherwise stated by the appropriate Airworthiness Authority, reject a tire when it is fully worn as defined by the following.
  • Page 879 Hawker 800XP Pro Line 21 Section VI - GROUND OPERATIONS REINFORCING TREAD CORD BREAKERS, IF INCORPORATED SIDEWALL RUBBER CASING PLIES, LAYERS OF CORD BEAD BEAD CHAFER STEEL WIRE CHAFER BEAD HEEL CORE OVERLAP BEAD BEAD BASE BEAD BEAD APEX WRAPPER...
  • Page 880 Hawker 800XP Pro Line 21 Section VI - GROUND OPERATIONS PERMISSIBLE DAMAGE FOR TIRES (Figures 20 & 20A) 1. Refer to Figure 20, example (2) Superficial cuts affecting tread and/or sidewall rubber not exposing the breakers or the cords of the casing plies.
  • Page 881 Hawker 800XP Pro Line 21 Section VI - GROUND OPERATIONS UNEVEN WEAR TYPICAL FLINT CUT SIDEWALL SPLITS SIDEWALL CRACKING Figure 20 Permissible Tire Damage Sub-section 2 Page 2-52 Pilot’s Operating Manual GROUND SERVICING Revision A2: Nov, 2004...
  • Page 882 Hawker 800XP Pro Line 21 Section VI - GROUND OPERATIONS EXCESSIVE WEAR ON SHOULDER SKID BURN OR SCALD SIDEWAYS SCRUBBING Figure 20A Permissible Tire Damage (continued) Sub-section 2 Pilot’s Operating Manual Page 2-53 GROUND SERVICING Revision A2: Nov, 2004...
  • Page 883 Hawker 800XP Pro Line 21 Section VI - GROUND OPERATIONS WORN TIRES and NON-PERMISSIBLE TIRE DAMAGE (Figure 21) 1. Refer to Figure 21, example (1) Bulges in the crown area or other extensive rubber damage. 2. Refer to Figure 21, example (2) Open tread joints or other extensive cuts.
  • Page 884 Hawker 800XP Pro Line 21 Section VI - GROUND OPERATIONS BULGES IN THE CROWN AREA OPEN TREAD JOINT SIDEWALL CREASING OR BUCKLING SPLITTING AT BASE OF TREAD GROVE TIRE SCUFFED EXPOSING OR CUTTING CASING CORDS Figure 21 Non-Permissible Tire Damage Sub-section 2 Pilot’s Operating Manual...
  • Page 885 Hawker 800XP Pro Line 21 Section VI - GROUND OPERATIONS GEAR ASSEMBLIES NITROGEN INFLATION Table 7 - Material Required Equipment - Material Part - Item Number Turner Inflation Adapter Turner 772 Gauge (0-600 psi) Turner F29/24/600 Gauge (0-1500 psi) Turner F29/24/1500...
  • Page 886 Hawker 800XP Pro Line 21 Section VI - GROUND OPERATIONS NITROGEN INFLATION (continued) CAUTION: WHEN ADDING PRESSURIZED NITROGEN TO THE GEAR CHARGING POINTS, FILL WITH NITROGEN SLOWLY TO PREVENT TEMPERATURE INCREASE AND INCORRECT PRESSURE INDICATIONS. 4. Inflate as necessary with nitrogen until pressure/extension is within limits given.
  • Page 887 Hawker 800XP Pro Line 21 Section VI - GROUND OPERATIONS Figure 23 Main Gear - Pressure/Extension Graph Sub-section 2 Page 2-58 Pilot’s Operating Manual GROUND SERVICING Revision A2: Nov, 2004...
  • Page 888 Hawker 800XP Pro Line 21 Section VI - GROUND OPERATIONS Figure 24 Nose Gear - Pressure/Extension Graph Sub-section 2 Pilot’s Operating Manual Page 2-59 GROUND SERVICING Revision A2: Nov, 2004...
  • Page 889 Hawker 800XP Pro Line 21 Section VI - GROUND OPERATIONS OXYGEN SYSTEM CHECK OXYGEN CONTENTS (Figure 25) WARNING: THE MASTER SUPPLY VALVE MUST BE FULLY OPEN OR CLOSED, FINGER TIGHT ONLY. DO NOT ATTEMPT TO STOP A LEAK BY OVER-TIGHTENING.
  • Page 890 Hawker 800XP Pro Line 21 Section VI - GROUND OPERATIONS REPLENISH OXYGEN SYSTEM (Figure 26) WARNING: OXYGEN FORMS AN EXPLOSIVE MIXTURE WITH OIL, GREASE, FUEL OR METAL DUST. USE DEGREASED TOOLS AND CLEAN HANDS. WARNING: MAKE SURE NO ELECTRICAL OR MOTOR DRIVEN GROUND EQUIPMENT IS CONNECTED TO THE AIRPLANE.
  • Page 891 Hawker 800XP Pro Line 21 Section VI - GROUND OPERATIONS REPLENISH OXYGEN SYSTEM continued 2. Connect the oxygen charging rig to the airplane charging valve as follows: WARNING: BEFORE BONDING THE OXYGEN CHARGING RIG TO THE AIRPLANE, MAKE SURE BOTH THE RIG AND THE AIRPLANE ARE INDIVIDUALLY BONDED TO GROUND.
  • Page 892 Hawker 800XP Pro Line 21 Section VI - GROUND OPERATIONS AIRFRAME ICE PROTECTION SYSTEM (Figure 27) REPLENISH SYSTEM TANK The recommended fluids are: • TKS fluid R 328. • TKS fluid 80. • De-icing fluid to specification DTD 406B. The tank capacity is 8.45 gallons (38 liters).
  • Page 893 Hawker 800XP Pro Line 21 Section VI - GROUND OPERATIONS DE-ICE FLUID TANK CONTENTS GAUGE ON RIGHT HAND CONSOLE VENT COVER DETECTED ANTICE ANTICE LO PRESS LO QTY ICE DET WING / TAIL ANTICE MAIN RISING AUTO MINS VENT PIPE...
  • Page 894 Pro Line 21 Section - VII SAFETY INFORMATION Table of Contents Page INTRODUCTION .....................3 GENERAL .......................3 SOURCES OF INFORMATION..............3 FAA APPROVED AIRPLANE FLIGHT MANUAL AND PILOT’S OPERATING MANUAL..............3 RAYTHEON AIRCRAFT COMPANY SERVICE PUBLICATIONS ....4 FEDERAL AVIATION REGULATIONS............5 AIRWORTHINESS DIRECTIVES..............5 AERONAUTICAL INFORMATION MANUAL..........5 ADVISORY INFORMATION .................6 FAA ADVISORY CIRCULARS ..............6 FAA GENERAL AVIATION NEWS ...............8...
  • Page 895 Hawker 800XP Pro Line 21 Section VII - SAFETY INFORMATION Page FLIGHT OPERATIONS (CONTINUED) Stalls, Slow Flight and Training ............21 Spins ....................21 Vortices - Wake Turbulence ..............23 Takeoff and Landing Conditions............23 MEDICAL FACTS FOR PILOTS ..............24 General....................

  • Page 896: Introduction

    Hawker 800XP Pro Line 21 Section VII - SAFETY INFORMATION INTRODUCTION Raytheon Aircraft Company has developed this special summary of safety information to refresh pilots’ and owner’s knowledge of safety related subjects. Topics in this section are dealt with in more detail in FAA Advisory Circulars and other publications pertaining to the subject of safe flying.

  • Page 897: Raytheon Aircraft Company Service Publications

    Hawker 800XP Pro Line 21 Section VII - SAFETY INFORMATION RAYTHEON AIRCRAFT COMPANY SERVICE PUBLICATIONS Raytheon Aircraft Company publishes a wide variety of manuals, service letters, service instructions, service bulletins, safety communiques and other publications for the various models of Raytheon Aircraft Company airplanes.

  • Page 898: Federal Aviation Regulations

    Hawker 800XP Pro Line 21 Section VII - SAFETY INFORMATION FEDERAL AVIATION REGULATIONS 14 CFR Part 91, General Operating and Flight Rules, is a document of law governing operation of airplanes and the owner’s and pilot’s responsibilities. Some of the subjects covered are: •...

  • Page 899: Advisory Information

    Hawker 800XP Pro Line 21 Section VII - SAFETY INFORMATION • Airport Operations • Wake Turbulence - Vortices • Clearances and Separations • Medical Facts for Pilots • Preflight • Bird Hazards • Departures - IFR • Good Operating Practices •...
  • Page 900 Hawker 800XP Pro Line 21 Section VII - SAFETY INFORMATION 20-35 ..... Tie-Down Sense 20-43 ..... Aircraft Fuel Control 20-93 ..... Flutter Due to Ice or Foreign Substance on or in Aircraft Control Surfaces 20-105 ....Engine Power-Loss Accident Prevention 21-4 .......

  • Page 901: Faa General Aviation News

    Hawker 800XP Pro Line 21 Section VII - SAFETY INFORMATION FAA GENERAL AVIATION NEWS FAA General Aviation News is published by the FAA in the interest of flight safety. The magazine is designed to promote safety in the air by calling the attention of general aviation airmen to current technical, regulatory and procedural matters affecting the safe operation of airplanes.

  • Page 902: General Information On Specific Topics

    Hawker 800XP Pro Line 21 Section VII - SAFETY INFORMATION • VFR Pilot Exam-O-Grams • Impossible Turn • Windshear • Estimating Inflight Visibility • Is the Aircraft Ready for Flight • Tips on Mountain Flying • Tips on Desert Flying •...

  • Page 903: Hazards Of Unapproved Modifications

    Hawker 800XP Pro Line 21 Section VII - SAFETY INFORMATION Airplanes operated for Air Taxi or other than normal operation, and airplanes operated in humid tropics, or cold and damp climates, etc., may need more frequent inspections for wear, corrosion and/or lack of lubrication.

  • Page 904: Passenger Safety Procedures Guides

    Hawker 800XP Pro Line 21 Section VII - SAFETY INFORMATION The pilot must be completely familiar with the performance of the airplane and performance data in the Checklist and FAA Approved Airplane Flight Manual. The resultant effect of temperature and pressure altitude must be taken into account in performance.

  • Page 905: Autopilot

    Hawker 800XP Collins Pro Line 21 Avionics System Pilot’s Guide, P/N 523-0780409- 001117. Prior to flight, each pilot must command a full understanding of the methods of engagement and disengagement of the autopilot system, particularily disengagement.

  • Page 906: Turbulent Weather

    Hawker 800XP Pro Line 21 Section VII - SAFETY INFORMATION decrease, if airspeed is reduced; (2) remain constant, if airspeed is held constant and no failures occur; or (3) increase to the point of self-destruction, especially if airspeed is high and/or is allowed to increase.

  • Page 907: Windshear

    Hawker 800XP Pro Line 21 Section VII - SAFETY INFORMATION The National Weather Service classifies turbulence as follows: Class of Turbulence Effect Aircraft is violently tossed about and is practically impossible to control. Extreme May cause structural damage. Aircraft may be momentarily out of control. Occupants are thrown Severe violently against the belts and back into the seat.

  • Page 908: Flight In Icing Conditions

    Hawker 800XP Pro Line 21 Section VII - SAFETY INFORMATION Windshears are rapid, localized changes in wind direction, which can occur vertically as well as horizontally. Windshear can be very dangerous to all airplanes, large and small, particularly on approach to landing when airspeeds are slow.
  • Page 909 Hawker 800XP Pro Line 21 Section VII - SAFETY INFORMATION equipped for IFR flight, cannot be flown safely into conditions such as thunderstorms, tornadoes, hurricanes or other phenomena likely to produce severe turbulence, airplanes equipped for flight in icing conditions cannot be expected to cope with “severe” icing conditions as defined by the National Weather Service.

  • Page 910: Weather Radar

    Hawker 800XP Pro Line 21 Section VII - SAFETY INFORMATION For any owner or pilot whose use pattern of an airplane exposes it to icing encounters, the following references are required reading for safe flying: • The airplane’s FAA Approved Airplane Flight Manual and Pilot’s Operating Manual, especially the sections on Normal Procedures, Emergency Procedures, Abnormal Procedures, Systems Description and Safety Information.

  • Page 911: Mountain Flying

    Hawker 800XP Pro Line 21 Section VII - SAFETY INFORMATION 1. Don’t land or take off in the face of an approaching thunderstorm. Sudden gust front low level turbulence could cause loss of control. 2. Don’t attempt to fly under a thunderstorm even if you can see through to the other side. Turbulence and windshear under the storm could be disastrous.

  • Page 912: Vfr At Night

    Hawker 800XP Pro Line 21 Section VII - SAFETY INFORMATION Mountain wave turbulence can, of course, occur in dry air and the absence of such clouds should not be taken as assurance that mountain wave turbulence will not be encountered. A mountain wave downdraft may exceed the climb capability of your airplane.

  • Page 913: Flight With One Engine Inoperative

    Hawker 800XP Pro Line 21 Section VII - SAFETY INFORMATION Excessive speed accidents occur at airspeeds greatly in excess of two operating limitations which are specified in the manuals (maximum maneuvering speed and the "red line" or maximum operating speed). Such speed limits are set to protect the structure of an airplane. For example, flight controls are designed to be used to their fullest extent only below the airplane’s maximum maneuvering speed.

  • Page 914: Basic Single Engine Procedures

    Hawker 800XP Pro Line 21 Section VII - SAFETY INFORMATION However, sudden engine failures rarely occur with all factors listed above, and therefore, the actual under any particular situation may be a little slower than listed in the LIMITATIONS section of the AFM.
  • Page 915 Hawker 800XP Pro Line 21 Section VII - SAFETY INFORMATION This airplane has not been tested for spin recovery characteristics and intentional spins are prohibited. The pilot of an airplane placarded against intentional spins should assume that the airplane may become uncontrollable in a spin, since its performance characteristics beyond certain limits specified in the FAA regulations may not have been tested and are unknown.

  • Page 916: Vortices - Wake Turbulence

    Hawker 800XP Pro Line 21 Section VII - SAFETY INFORMATION • Recognize that under some conditions of weight, density altitude, and airplane configuration, a twin engine airplane cannot climb or accelerate on a single engine. Hence a single engine go-around is impossible and the airplane is committed to a landing.

  • Page 917: Medical Facts For Pilots

    Hawker 800XP Pro Line 21 Section VII - SAFETY INFORMATION MEDICAL FACTS FOR PILOTS General When entering the airplane, the pilot becomes an integral part of the man-machine system and is just as essential to a successful flight as the control surfaces. To ignore the pilot in preflight planning would be as senseless as failing to inspect the integrity of the control surfaces or any other vital part of the machine.

  • Page 918: Hyperventilation

    Hawker 800XP Pro Line 21 Section VII - SAFETY INFORMATION Should symptoms occur that cannot definitely be identified as either hypoxia or hyperventilation, try three or four deep breaths of oxygen. The symptoms should improve markedly if the condition was hypoxia (recovery from hypoxia is rapid).

  • Page 919: Alcohol

    Hawker 800XP Pro Line 21 Section VII - SAFETY INFORMATION Alcohol Common sense and scientific evidence dictate that you must not fly as a crew member while under the influence of alcohol. Alcohol, even in small amounts, produces (among other things): •...

  • Page 920: Drugs

    Hawker 800XP Pro Line 21 Section VII - SAFETY INFORMATION (b) Except in an emergency, no pilot of a civil aircraft may allow a person who appears to be intoxicated or who demonstrates by manner or physical indications that the individual is under the influence of drugs (except a medical patient under proper care) to be carried in that aircraft.

  • Page 921: A Final Word

    Hawker 800XP Pro Line 21 Section VII - SAFETY INFORMATION A FINAL WORD Airplanes are truly remarkable machines. They enable us to shrink distance and time, and to expand our business and personal horizons in ways that, not too many years ago, were virtually inconceivable.
  • Page 922 Any information pending foreign regulatory agency approval will be listed in the description. Raytheon Aircraft Company, which has been renamed Hawker Beechcraft Corporation, is now owned by Hawker Beechcraft, Inc. Neither Hawker Beechcraft, Inc. nor Hawker Beechcraft Corporation are affiliated any longer with Raytheon Company. Any Raytheon marks contained in this document are owned by Raytheon Company and are employed pursuant to a limited license granted by Raytheon Company.
  • Page 923 LOG OF SUPPLEMENTS Pilot’s Operating Manual P/N 140-590032-0007 August 2, 2006 AIRPLANES EQUIPPED WITH COLLINS PRO LINE 21 AVIONICS Supplements, or supplement revisions, incorporated into this manual which have not been approved by Raytheon Aircraft Company, must be recorded on a separate Log of Supplements. Supplement Title Date...

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