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Page 11-3

Pilot’s Operating Manual
Revision A1: Nov, 2002

Sub-section 11

ICE PROTECTION

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. Location of components in the vestibule area is shown in Figure 2.

Hot air is used to keep the main engine air intake and starter/generator cooling air intake free of ice with
electric heating provided for windscreens, pitot heads, forward static plates and stall vanes, rudder bias
struts and engine inlet temperature and pressure sensors Pt

2

and Tt

2

.

SYSTEM OPERATION

A WING/TAIL ANTICE timer switch controls an electrically-operated pump for up to 10 minutes. When
initially selected, the first minute of operation is at a high flow rate, after which, the system reverts to
normal flow. If icing conditions still prevail or are expected, and therefore a further period of operation
is required, this should be selected before the timer switch reaches zero.

Using this procedure the system will remain on the normal flow rate, without first delivering a high rate
flow and therefore fluid will be conserved. When the timer switch returns to zero, the pump is de-
energized and a warning chime sounds via the airplane audio system.

NOTE: At very low temperatures (-28° C or less) ice crystals can exist in the atmosphere, but do not

present a hazard. If the airframe ice protection system is used at these low temperatures, the
water/alcohol content of the fluid will evaporate, leaving solidified glycol which together with
the impinging ice crystals can give the appearance of ice. Use of the airframe ice protection
system, under these conditions, is not advisable.

Therefore, operation of the WING/TAIL ANTICE timer switch should be limited to the priming
procedures, and additional use in flight only when weather conditions warrant.

MINS

10

0

ANTICE

LO PRESS

ANTICE

LO QTY

ICE

PROT

MWS Panel

Overhead Roof Panel

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Содержание Hawker 800XP

Страница 1: ...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 Corpora...

Страница 2: ...in this Pilot s Operating Manual may depict optional equipment not installed in all airplanes Published By Hawker Beechcraft Corporation P O Box 85 Wichita Kansas 67201 U S A The export of these comm...

Страница 3: ...ru 9 Revision A1 Nov 2002 LOG OF REVISIONS Pages 1 of 1 Original Issue Feb 2002 Section I GENERAL 1 Original Issue Feb 2002 2 Original Issue Feb 2002 3 Revision A1 Nov 2002 4 Revision A1 Nov 2002 5 Re...

Страница 4: ...2 2 24 Original Issue Feb 2002 2 25 Revision A1 Nov 2002 2 26 Revision A1 Nov 2002 2 27 Original Issue Feb 2002 2 28 Original Issue Feb 2002 Section Page Revision Date 2 29 Revision A1 Nov 2002 2 30 O...

Страница 5: ...on A4 Sep 2010 6 9 Revision A4 Sep 2010 6 10 Revision A4 Sep 2010 6 11 Revision A4 Sep 2010 6 12 Revision A4 Sep 2010 Section Page Revision Date 6 13 Revision A4 Sep 2010 6 14 Revision A4 Sep 2010 6 1...

Страница 6: ...ep 2010 9 19 Revision A4 Sep 2010 9 20 Revision A4 Sep 2010 9 21 Revision A4 Sep 2010 9 22 Revision A4 Sep 2010 Section Page Revision Date 9 23 Revision A4 Sep 2010 9 24 Revision A4 Sep 2010 Sub secti...

Страница 7: ...Nov 2002 13 12 Revision A1 Nov 2002 13 13 Revision A1 Nov 2002 13 14 Revision A1 Nov 2002 13 15 Revision A2 Nov 2004 Section Page Revision Date 13 16 Revision A2 Nov 2004 13 17 Original Issue Feb 200...

Страница 8: ...0 17 21 Revision A4 Sep 2010 17 22 Revision A4 Sep 2010 Sub section 18 Pitot Static System 18 1 Revision A2 Nov 2004 18 2 Revision A2 Nov 2004 Section Page Revision Date 18 3 Revision A2 Nov 2004 18 4...

Страница 9: ...ion A1 Nov 2002 2 43 Revision A1 Nov 2002 2 44 Revision A1 Nov 2002 2 45 Revision A1 Nov 2002 2 46 Revision A1 Nov 2002 2 47 Revision A1 Nov 2002 Section Page Revision Date 2 48 Revision A1 Nov 2002 2...

Страница 10: ...2002 2 108 Revision A1 Nov 2002 2 109 Revision A1 Nov 2002 2 110 Revision A1 Nov 2002 2 111 Revision A1 Nov 2002 Section Page Revision Date 2 112 Revision A1 Nov 2002 2 113 Revision A1 Nov 2002 2 114...

Страница 11: ...ion A1 Nov 2002 2 172 Original Issue Feb 2002 2 173 Original Issue Feb 2002 2 174 Revision A1 Nov 2002 2 175 Revision A1 Nov 2002 Section Page Revision Date 2 176 Revision A1 Nov 2002 2 177 Revision A...

Страница 12: ...Feb 2002 4 3 Revision A1 Nov 2002 4 4 Original Issue Feb 2002 4 5 Original Issue Feb 2002 Section Page Revision Date 4 6 Original Issue Feb 2002 4 7 Original Issue Feb 2002 4 8 Original Issue Feb 2002...

Страница 13: ...Feb 2002 5 3 Original Issue Feb 2002 5 4 Original Issue Feb 2002 5 5 Original Issue Feb 2002 5 6 Original Issue Feb 2002 Sub section 6 Single Engine 6 1 Revision A4 Sep 2010 Section Page Revision Dat...

Страница 14: ...8 11 Revision A3 Apr 2008 8 12 Revision A3 Apr 2008 8 13 Revision A3 Apr 2008 8 14 Revision A3 Apr 2008 8 15 Revision A3 Apr 2008 Section Page Revision Date 8 16 Revision A3 Apr 2008 8 17 Revision A3...

Страница 15: ...15 Original Issue Feb 2002 2 16 Revision A1 Nov 2002 2 17 Revision A1 Nov 2002 2 18 Revision A1 Nov 2002 2 19 Revision A2 Nov 2004 Section Page Revision Date 2 20 Revision A2 Nov 2004 2 21 Revision A1...

Страница 16: ...16 Revision A2 Nov 2004 2 17 Revision A2 Nov 2004 2 18 Revision A2 Nov 2004 2 19 Revision A2 Nov 2004 2 20 Revision A2 Nov 2004 Section Page Revision Date 2 21 Revision A2 Nov 2004 2 22 Revision A2 No...

Страница 17: ...on A1 Nov 2002 4 Revision A1 Nov 2002 5 Revision A1 Nov 2002 6 Revision A1 Nov 2002 7 Revision A1 Nov 2002 8 Revision A1 Nov 2002 9 Revision A1 Nov 2002 10 Revision A1 Nov 2002 11 Revision A1 Nov 2002...

Страница 18: ...Page 16 of 16 P N 140 590032 0007 Revision A5 Feb 2012 Pilot s Operating Manual Intentionally left blank...

Страница 19: ...Changes must be filed in the front of this POM immediately in front of the Log of Revisions pages This page replaces any Log of Temporary Changes dated prior to the issue date near the top of this pa...

Страница 20: ...Page 2 of 2 Pilot s Operating Manual P N 140 590032 0007LOTC September 22 2010 Intentionally left blank...

Страница 21: ...ht and updated for Revision A5 List of Effective Pages Pages 1 thru 16 Updated for Revision A5 Log of Revisions Pages 1 thru 2 Provided for changes made in Revision A5 Section IV FLIGHT PLANNING DATA...

Страница 22: ...Page 2 of 2 P N 140 590032 0007A5 Log Of Revisions Intentionally left blank...

Страница 23: ...and 2 Provided new Log of Temporary Changes for Revision A4 Log of Revisions Pages 1 thru 4 Provided new Log of Revisions for Revision A4 Section III SYSTEMS DESCRIPTION Sub section 3 Fuel System Pag...

Страница 24: ...17 22 MODE 7 revised WINDHEAR to WINDSHEAR Section IV FLIGHT PLANNING DATA Sub section 6 Single Engine Pages 6 1 thru 6 42 Revised headers to Hawker Beechcraft format and footers for Revision A4 Page...

Страница 25: ...r trim Pages 1 15 and 1 16 Incorporated Temporary Change 2 and shifted data Page 1 17 Added FMS to Flight Management System heading Page 1 19 Revised 14 CFR 91 32 to 14 CFR 91 211 in three places Sect...

Страница 26: ...Page 4 of 4 SECTION PAGES DESCRIPTION Sub section 1 Ground Handling continued Page 1 12 ENGINE START revised Motor to motor A4...

Страница 27: ...itle 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 List Of Effect...

Страница 28: ...agination formatting and editorial reasons only with no technical changes Title Page New Title page for Revision A2 Logo Page New Logo page for Revision A2 List of Effective Pages Pages 1 thru 16 Upda...

Страница 29: ...Updated company header no technical change Page 3 3 Added if installed to ventral tank information Page 3 4 Updated company header no technical change Page 3 5 Changed wording of Legend to read Key P...

Страница 30: ...tem consist of added information to listing Added words of pitot and static to the 7th bullet Deleted reference to EGPWS from text Added the word located to text Page 7 4 Added Figure 1 reference Chan...

Страница 31: ...unciator to plural annunciators Provided new illustration of gear annunciators Page 8 4 Updated company header no technical change Page 8 9 Added gear annunciators illustration Page 8 10 Updated compa...

Страница 32: ...d illustration for clarity no technical change Page 13 16 Updated company header no technical change Sub section 14 EQUIPMENT and FURNISHINGS Page 14 7 Moved Figure 4 title above footer line no techni...

Страница 33: ...numbered for pagination only and updated company headers no technical change Sub section 18 PITOT STATIC SYSTEM Pages 18 1 thru 18 6 Addition of PITOT STATIC SYSTEM Section IV FLIGHT PLANNING DATA Su...

Страница 34: ...rms of First Officer and Captain to read copilot and pilot Page 2 37 Changed terms of Captain and First Officer to read Pilot and Copilot Page 2 38 Updated company header no technical change Section V...

Страница 35: ...change Sub section 2 GROUND SERVICING Page 2 1 Changed PRESSURE REFUELING DEFUELING to read PRESSURE REFUELING and DEFUELING Added GRAVITY REFUELING and DEFUELING Deleted Figure 12A Page 2 2 Reversed...

Страница 36: ...Figure reference Pages 35 36 Updated company header no technical change Page 2 37 Replaced Figure 11 for clarity of ground operation Page 2 38 Updated company header no technical change Page 2 39 Re f...

Страница 37: ...Page 2 60 Added Figure 25 reference to CHECK OXYGEN CONTENTS and updated step text Provided Figure 25 Flight Compartment Oxygen Services Panel Page 2 61 Changed heading of REPLENISH SYSTEM to read RE...

Страница 38: ...Restated Export Statement List of Effective Pages Pages 1 thru 16 Updated for Revision A1 Log of Revisions Pages 1 thru 9 Updated for Revision A1 Section I General Page 3 Changed Hawker 800XP to read...

Страница 39: ...dd space between No and 1 Page 3 12 Changed lettering style in graphics from BOLD to PLAIN Sub section 4 Fire Protection Pages 4 4 4 5 and 4 8 Indent bullets and notes Page 4 6 Add space between No an...

Страница 40: ...Page 8 13 Center page text box Indent bullets For confor mity made panel callout black Sub section 9 Electrical Power Pages 9 3 9 8 and 9 16 Was BUSTIE now BUS TIE to correct annuncia tor call out In...

Страница 41: ...ndent bullets For conformity made panel callout black Page 10 14 Clarified language now will provide a For confor mity made panel callout black Page 10 16 Changed No 2 to No 2 to properly identify as...

Страница 42: ...TCHES ANNUNCIATORS page to TOC Pages 17 3 17 14 and 17 16 Reprint for improved graphics Pages 17 4 17 17 and 17 18 Indent bullets Page 17 5 Changed art to show correct annunciator location Page 17 6 C...

Страница 43: ...49 2 154 2 155 2 156 2 157 2 162 2 163 2 168 2 169 2 180 2 181 and 2 186 For conformity changed temperature callouts ex 103 C or 98 F Add comma to numbers 10 000 and greater Pages 2 63 2 64 2 69 2 124...

Страница 44: ...Correct the subscript text size Page 1 10 For conformity changed temperature callouts ex 103 C or 98 F Indent bullets and notes Page 1 11 Changed 5 to 5 in upper table Sub section 2 Abnormal Handling...

Страница 45: ...ted comma For conformity changed temperature callouts ex 103 C or 98 F Indent bullets and notes Page 1 22 Add paragraph heading Sub section 2 Ground Servicing Page 2 1 Corrected Table of Contents Head...

Страница 46: ...er and footer Pages 5 6 8 9 10 17 20 22 and 23 Indent bullets and notes Align text frame with header and footer Pages 7 and 26 Add periods Indent bullets Align text frame with header and footer Page 1...

Страница 47: ...After Pilot s Operating Manual P N 140 590032 0007 Original Issue February 2002 for AIRPLANES EQUIPPED WITH COLLINS PRO LINE 21 AVIONICS SECTION PAGE DESCRIPTION All Sections and Pages Original Issue...

Страница 48: ...ro 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...

Страница 49: ...Hawker 800XP Pro Line 21 Page 2 Pilot s Operating Manual Original Issue Feb 2002 Section I GENERAL Intentionally left blank...

Страница 50: ...sion a new List Of Effective Pages LOEP will be issued listing all the pages and dates for the current standard of the Pilot s Operating Manual The LOEP does not include Temporary Changes or pages int...

Страница 51: ...APS Avionics information can be found in this Pilot s Operating Manual SECTION III Sub section 17 and the Collins Pro Line 21 Avionics System Pilot s Guide P N 523 0780409 001117 Each turbofan engine...

Страница 52: ...at detection is provided for the rear equipment bay Engine bleed air is tapped from the engines for the pressurization air conditioning rudder bias systems and hydraulic reservoir pressure A gas turbi...

Страница 53: ...Hawker 800XP Pro Line 21 Page 6 Pilot s Operating Manual Original Issue Feb 2002 Section I GENERAL Figure 1 General Dimensions...

Страница 54: ...y Door Height 4 ft 3 in 1 30 m Width 2 ft 3 in 0 68 m Average height of door sill above ground 3 ft 6 in 1 07 m Windows Height 1 ft 2 1 2 in 0 36 m Width 10 in 0 25 m Emergency Exit Height 3 ft 0 in 0...

Страница 55: ...ng 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 135 lb sq in Nosewheel Tire size 18 X 4 25 10 6 P...

Страница 56: ...etween the rear bulkhead of the passenger cabin and the rear pressure bulkhead The area contains toilet and washbasin facilities on the rear pressure bulkhead and an avionics rack and rear baggage com...

Страница 57: ...Section I GENERAL M6365_0 HA00C 014725AA AI FIRST OFFICER S NO 2 SIDE FLIGHT COMPARTMENT OUTWARD OPENING DOOR WITH INTEGRAL STAIRS CAPTAIN S NO 1 SIDE NO 2 SIDE NO 1 SIDE VESTIBULE AREA PASSENGER CAB...

Страница 58: ...Page 1 Pilot s Operating Manual Original Issue Feb 2002 Pro Line 21 Section II OPERATING LIMITATIONS Table of Contents Page GENERAL 3...

Страница 59: ...Hawker 800XP Pro Line 21 Page 2 Pilot s Operating Manual Original Issue Feb 2002 Section II OPERATING LIMITATIONS Intentionally left blank...

Страница 60: ...ating Manual Original Issue Feb 2002 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 Se...

Страница 61: ...Hawker 800XP Pro Line 21 Page 4 Pilot s Operating Manual Original Issue Feb 2002 Section II OPERATING LIMITATIONS Intentionally left blank...

Страница 62: ...Sub section 6 FLIGHT CONTROLS 6 1 Sub section 7 STALL WARNING IDENTIFICATION 7 1 Sub section 8 LANDING GEAR 8 1 Sub section 9 ELECTRICAL POWER 9 1 Sub section 10 ENVIRONMENTAL 10 1 Sub section 11 ICE...

Страница 63: ...Hawker 800XP Pro Line 21 Page 2 Pilot s Operating Manual Revision A2 Nov 2004 Section III SYSTEMS DESCRIPTION Intentionally left blank...

Страница 64: ...Annunciations and Controls 1 4 SYSTEM OPERATION 1 5 ACKNOWLEDGEMENT 1 5 ANNUNCIATION SEQUENCE 1 6 Table 1 Annunciation Sequence 1 6 TESTING 1 7 DIM CONTROL FAILURE 1 7 MWS MASTER WARNING LAMP FAILURE...

Страница 65: ...Page 1 2 Pilot s Operating Manual Original Issue Feb 2002 Sub section 1 MASTER WARNING SYSTEM Hawker 800XP Pro Line 21 Section III SYSTEMS DESCRIPTION Intentionally left blank...

Страница 66: ...the glareshield one in front of each pilot Additional annunciators are arranged in groups in the system areas of the overhead roof panel An ANNUN test button is located in the test section of the over...

Страница 67: ...DOOR UNLOCKED RUDDER BIAS APU ON ICE PROT SELECTED STALL IDENT FUEL XFD TFR AIR BRAKE Figure 1 Master Warning Annunciations and Controls Overhead Roof Panel ENG 1 FIRE ENG 2 FIRE ENG 1 FUEL ENG 2 FUE...

Страница 68: ...iators will increase in brightness ACKNOWLEDGEMENT Either pilot can acknowledge the warning by pushing either MWS red master warning lamp on the glareshield with the following results The MWS red mast...

Страница 69: ...illuminated Attention Event Overhead Roof Panel Illuminates steady at maximum intensity Flashes at maximum intensity Illuminates steady at dimmed intensity as set on MWS DIM control None MWS Main Pan...

Страница 70: ...the MWS panel The flight crew should set the NORM DIM OVRD switch to the DIM OVRD position This causes the warning annunciator to illuminate at maximum intensity and the MWS DIM FAIL annunciator will...

Страница 71: ...FD Copilot Instrument Panel Pilot Instrument Panel Center Instrument Panel GEN 1 FAIL GEN 2 FAIL BATT 1 BATT 2 CNTCTR CNTCTR BUS TIE OPEN XS 1 FAIL XS 2 FAIL XE FAIL INV 1 FAIL INV 2 FAIL ELECT The il...

Страница 72: ...rs on the Overhead Roof Panel will be accompanied by the illumination of the associated MWS repeater shown below MFD MFD PFD PFD Copilot Instrument Panel Pilot Instrument Panel Center Instrument Panel...

Страница 73: ...2 FUEL FUEL 1 LO PRESS FUEL 2 LO PRESS REFUEL ON WING FUEL XFD TFR AUX FUEL TFR FUEL XFD TFR The illumination of any of the above fuel annunciators on the Overhead Roof Panel will be accompanied by th...

Страница 74: ...The illumination of either of the above fire warning annunciators on the Overhead Roof Panel Forward Extension will be accompanied by the illumination of the respective MWS repeater shown below DUCT...

Страница 75: ...iators Location Amber Annunciators Location MWS panel if installed MWS panel MWS panel MWS panel MWS panel MWS panel MWS panel MWS panel MWS panel MWS panel MWS panel MWS panel MWS panel MWS panel MWS...

Страница 76: ...S Annunciators Without a Repeater Red Annunciator Location Amber or White Annunciators Location MWS panel MWS panel MWS panel Overhead panel MWS panel if installed MWS panel Flight Compartment Overhea...

Страница 77: ...Page 1 14 Pilot s Operating Manual Original Issue Feb 2002 Sub section 1 MASTER WARNING SYSTEM Hawker 800XP Pro Line 21 Section III SYSTEMS DESCRIPTION Intentionally left blank...

Страница 78: ...Operation 2 8 ENGINE INDICATING SYSTEM EIS 2 9 N1 RPM DISPLAYS 2 10 N1 REFERENCE DISPLAYS 2 11 ITT DISPLAYS 2 12 N2 RPM DISPLAYS 2 13 FUEL FLOW DISPLAYS 2 14 OIL PRESSURE DISPLAYS 2 14 OIL TEMPERATURE...

Страница 79: ...Engine Interface 2 27 Surge Bleed Valve 2 28 Fuel Flow Divider Assembly 2 28 Fuel Atomizers 2 28 Fuel Heating 2 28 Fuel Flow Indicating 2 29 Additional Fuel System Components 2 29 POWER CONTROLS 2 30...

Страница 80: ...9 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 Re...

Страница 81: ...Page 2 4 Pilot s Operating Manual Original Issue Feb 2002 Sub section 2 ENGINES Hawker 800XP Pro Line 21 Section III SYSTEMS DESCRIPTION Intentionally left blank...

Страница 82: ...lane to operate the rudder bias system and for engine anti icing Each engine has a combined starter generator and can be started from either the airplanes batteries or an external power supply Each en...

Страница 83: ...and provides a cool skin concept for the external surfaces of the turbine section FAN The fan is an axial flow unit that moves large quantities of air into the bypass and core inlets The bypass secti...

Страница 84: ...ixed with atomized fuel supplied by twelve duplex fuel nozzles The twelve duplex fuel nozzles consists of primary nozzles used for starting and secondary nozzles used in conjunction with the primary n...

Страница 85: ...essor and directed to the HP compressor where the air pressure is further increased and ducted aft to the combustor A precise amount of this air enters the reverse flow combustor where fuel is injecte...

Страница 86: ...tton removes the parameters provided that all read outs are within normal operating limits The last change by either pilot controls the EIS on all currently enabled displays Declutter is not allowed w...

Страница 87: ...pointer icon to the left of the N1 indication The N1 digital display has a range of 0 to 110 The normal limit for N1 is 100 and the N1 pointer and digital read out are green when N1 is within 100 If...

Страница 88: ...cyan colored text The N1 REF value can now be changed using the MENU ADV knob on the DCP The second push of the N1 REF line select key removes the flashing box and places a solid box around the FMS M...

Страница 89: ...ow pressure turbine These thermocouples measure the Interstage Turbine Temperature ITT and send signals to the Engine Data Concentrator EDC and the fuel computer The ITT display indicates the temperat...

Страница 90: ...nsient limit and red when N2 is in the redline Four yellow dashes and a decimal point replace the N2 read out if all sources of N2 are flagged or missing The following lists the normal transient and r...

Страница 91: ...low in the top right corner of the MFD The oil pressure display can appear up to 3 digits for each engine A gray OIL PRESS legend with OIL placed below PRESS appears between the left and right digital...

Страница 92: ...econds CLIMB ANNUNCIATION Maximum Climb Thrust is set by adjusting the thrust levers until the green CLIMB annunciation appears at the lower center of the N1 ITT scales CLIMB shares the display locati...

Страница 93: ...box accessory gearbox and the front fan planetary gear assembly Oil Pump Assembly An oil pump assembly is located on the accessory drive gearbox It contains a single oil pressure pump and four scaveng...

Страница 94: ...X ACCESSORY VENT BREATHER PRESSURIZING VALVE PLANETARY GEARS CHIP DETECTOR PRESSURE REGULATOR FILTER FUEL FUEL FUEL HEATER FUEL FUEL OIL PUMPS BYPASS COOLER IN OUT LEGEND INLET OIL HIGH PRESSURE OIL S...

Страница 95: ...ngine Figure 4 Fuel Heater An externally mounted fuel heater is located on the left side of the engine The fuel heater provides oil to fuel heat exchanging to prevent ice formation in the fuel system...

Страница 96: ...II SYSTEMS DESCRIPTION Pilot s Operating Manual Revision A2 Nov 2004 Outboard View of No 1 Engine Inboard View of No 1 Engine Outboard View of No 2 Engine Inboard View of No 2 Engine ALTERNATOR COOLIN...

Страница 97: ...Hawker 800XP Pro Line 21 Section III SYSTEMS DESCRIPTION Page 2 20 Pilot s Operating Manual Revision A2 Nov 2004 Sub section 2 ENGINES Intentionally left blank...

Страница 98: ...awn back to the engine oil reservoir by the scavenge pumps Oil Venting Vent lines interconnect the oil sumps to the oil tank assembly and the breather pressurizing valve The breather pressurizing valv...

Страница 99: ...nual operation of the ignition unit is through the ENG IGNITION switch in the ON position If required the unit can be operated continuously Igniter Plugs and Leads The igniter plugs on the annular com...

Страница 100: ...el control system The pump assembly consists of Booster Pump Element Fuel Filter Filter Bypass Valve High Pressure Pump Element Relief Valve FCU attached to the rear of the pump Anti Ice Valve An anti...

Страница 101: ...ICE VALVE PUMP RELIEF VALVE BOOST FILTER FILTER COLLECTOR TANK INTERSTAGE PRESSURE TAP SAFETY CAPPED OIL FUEL HEATER HIGH PUMP BYPASS RETURN LEGEND SUPPLY LOW PRESSURE PUMP HIGH PRESSURE PUMP PUMP BY...

Страница 102: ...r if the fuel computer is operative A hydro mechanical control when the fuel computer is inoperative An operating fuel computer DEEC electrically controls fuel flow scheduling by setting the FCU meter...

Страница 103: ...ts to each computer are Engine Inlet Pressure Pt2 Engine Inlet Temperature Tt2 Interstage Turbine Temperature ITT N2 speed N1 speed Thrust Lever Position Each DEEC provides appropriate output current...

Страница 104: ...tions the FCU on the engine automatically switches to the manual mode and the respective ENG CMPTER annunciator will illuminate The DEEC compensates the engine operating parameters for different fuel...

Страница 105: ...d the fuel atomizers During the engine start the divider routes fuel at a reduced pressure to the primary atomizers As the start sequence continues and the RPM increases the fuel flow and pressure dif...

Страница 106: ...AC voltage passes through a converter where DC voltage is supplied to the Data Concentrator Unit DCU which supplies the data to the MFD for the fuel flow indications The fuel flow indicating system us...

Страница 107: ...m shaft Reducing power below 65 N1 RPM with the landing gear not locked down below 150 kts completes a circuit that sounds a warning horn Increasing power with the air brakes extended while the landin...

Страница 108: ...nual Revision A1 Nov 2002 Sub section 2 ENGINES Hawker 800XP Pro Line 21 Section III SYSTEMS DESCRIPTION STOP BOLTS FULL IDLE HP COCK LEVER THROTTLE LEVER TO COCK LEVER HP LINKAGE MICROSWITCH based on...

Страница 109: ...authority and can occur only when speed differential is within the authority range The maximum authority range is 2 5 N2 at thrust setting midrange authority range decreases as engine speed increases...

Страница 110: ...Services Ram air is used to ventilate the area of the cowling surrounding the engine compressor stages between the front and rear firewalls ANTI ICING An ENG ANTICE ON OFF switch located on the overhe...

Страница 111: ...21 Section III SYSTEMS DESCRIPTION ANTI ICING VALVE PE BUSBAR 6 PSI PICCOLO TUBE 2 SEC DELAY MWS DIM BUS ICE PROT SELECTED ENG 1 A ICE Figure 9 Engine Anti icing System TO Pt2 and Tt2 HEATING CIRCUIT...

Страница 112: ...ngine When the air pressure is low the switch operates and illuminates ENG 1 or 2 A ICE annunciator on the MWS panel The anti icing valve is energized to the closed position with busbar energized and...

Страница 113: ...ERVE APR When armed the APR system allows an automatic increase in engine performance in the event of an engine failure or transient fault during takeoff or during a go around following a single engin...

Страница 114: ...Section III SYSTEMS DESCRIPTION ARM SWITCH DISARMED ARMED ENGINE 1 ENGINE 2 SYNCHRONIZER SWITCH DIM BUS FUEL 2 OFF N 2 N 1 PE 2 BUS COMPUTER OVRD SWITCH OVRD AUTO FUEL 1 COMPUTER MASTER SLAVE INDICAT...

Страница 115: ...nction with the engine synchronizer system Manual Mode When armed to cater for an auto mode malfunction the system may also be triggered by manual selection of APR OVRD NOTE There is a penalty in term...

Страница 116: ...imit the thrust obtainable at the full reverse thrust position CONTROLS and INDICATORS An electrical control panel located on the lower section of the center instrument panel provides L H and R H THRU...

Страница 117: ...lever is increased to its maximum thrust position An automatic engine thrust lever retard system is incorporated in the event of a stow or deploy malfunction REVERSER ASSEMBLY and OPERATION Each thrus...

Страница 118: ...ust may be commanded by pulling the levers toward maximum reverse A mechanical stop is set at a predetermined thrust setting A deploy command inhibits operation of rudder bias to prevent rudder moveme...

Страница 119: ...h in turn activates the thrust lever retard system to force the engine thrust lever to move to the idle position SYSTEM SAFETY A reverse thrust selector installed to each engine thrust lever is operab...

Страница 120: ...AULIC RETURN LINE TO AIRPLANE SYSTEM TO OPPOSITE T R SYSTEM ISOLATION PRESSURE SWITCH LATCH INBOARD OUTBOARD DOOR LATCH ASSEMBLY STOW DEPLOY FAN FLAP ACTUATOR FAN FLAP ACTUATOR PRIMARY ACTUATOR POSITI...

Страница 121: ...Page 2 44 Pilot s Operating Manual Original Issue Feb 2002 Sub section 2 ENGINES Hawker 800XP Pro Line 21 Section III SYSTEMS DESCRIPTION Intentionally left blank...

Страница 122: ...Defuel System 3 6 Gravity Filler 3 7 Pressure Refueling 3 7 Table 1 Pressure Refueling Quantities 3 7 FUEL PROBES and FLOAT SWITCHES 3 7 FUEL QUANTITY INDICATIONS 3 8 REFUEL DEFUEL CONTROL and INDICAT...

Страница 123: ...Page 3 2 P N 140 590032 0007 Revision A4 Sep 2010 Section III Sub section 3 FUEL SYSTEM Pilot s Operating Manual Intentionally left blank...

Страница 124: ...uel reservoir With the fuel pumps operating and the appropriate transfer selection made fuel can be transferred between the wing tanks and from the ventral tank to the wing tanks NOTE The engines cann...

Страница 125: ...during in flight maneuvering The ventral tank vents into the left wing tank through two vent float valves non return valves a pipe and a wing stringer DRAIN VALVES One fuel drain valve and one water d...

Страница 126: ...nd APU if installed WATER DRAIN CHECK VALVE PRESS SWITCH JET PUMP colored as pipe P FUEL PUMP VENTRAL TANK SUCTION FEED STRAINER P P PRESS SWITCH FUEL 2 LO PRESS FUEL 1 LO PRESS XFD TFR WING FUEL Duri...

Страница 127: ...Page 3 6 P N 140 590032 0007 Revision A4 Sep 2010 Section III Sub section 3 FUEL SYSTEM Pilot s Operating Manual Figure 3 Refuel Defuel System...

Страница 128: ...f the airplane The airplane fuel system accepts a maximum refueling supply pressure of 50 psi Incorporated into the fuel system is a pressure reducing valve that reduces the refueling pressure within...

Страница 129: ...ric fuel pump in the rear center wing section to the engine driven pump in the engine fuel control The wing tank transfer system allows fuel balancing between the wing fuel tanks in flight and on the...

Страница 130: ...fuel pumps fail fuel still gravity feeds into the fuel reservoir of each wing so that the engine driven pumps can draw the fuel for operation under suction feed Warning of pump failure is provided by...

Страница 131: ...down respectively To operate lift a hinged guard installed above the control levers before the levers are moved to the closed down position The LP COCK levers also incorporate a spring loaded knob to...

Страница 132: ...made with fuel in the ventral tank Moving the AUX FUEL TRANSFER lever to the up position closes the ventral tank transfer valve and the white AUX FUEL TFR annunciator will extinguish Auxiliary fuel tr...

Страница 133: ...el flow figures on the Pilot s MFD FUEL TEMPERATURE INDICATOR A temperature bulb in the left engine fuel supply line is electrically connected to the outside air fuel temperature indicator on the uppe...

Страница 134: ...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 FIRE 4 5 WARNINGS 4 5 TESTING 4 5 ENGINE FIRE EX...

Страница 135: ...Hawker 800XP Pro Line 21 Page 4 2 Pilot s Operating Manual Original Issue Feb 2002 Section III SYSTEMS DESCRIPTION Sub section 4 FIRE PROTECTION Intentionally left blank...

Страница 136: ...r 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 initia...

Страница 137: ...ore material The sensor has two sensing functions Overheat sensing of average temperature increase Fire sensing of discrete temperatures caused by impinging flame or hot gases OVERHEAT The sensor acts...

Страница 138: ...shield An associated ENG 1 or ENG 2 FIRE repeater annunciator MWS panel FIRE legend in the lower center of the applicable N1 ITT scale An associated HP cock red fire warning lamp directly above the HP...

Страница 139: ...xtinguisher bottle 1 has been used shot 1 The second bottle is still available for use either in No 1 engine shot 2 or in No 2 engine shot 1 should the need arise Two pressure relief discharge indicat...

Страница 140: ...ES CHECK VALVES TWIN NOZZLES TWIN NOZZLES ENGINE 1 SHOT 1 ENGINE 1 SHOT 2 ENGINE 2 SHOT 2 ENGINE 2 SHOT 1 EXTINGUISHER BOTTLE FIRED EXTINGUISHER BOTTLE UNUSED Figure 2 Engine Fire Extinguisher System...

Страница 141: ...lic fluid and similar Electrical fires The early stages of fires involving freely burning materials such as wood paper and cloth The extinguishant is a charge of 1 5 kg of BCF Halon 1211 propelled by...

Страница 142: ...and Pump 5 5 MAINTAINED PRESSURE PATHS 5 5 Thrust Reversers 5 5 Wheel Brakes Emergency Path 5 6 Accumulators 5 6 NON MAINTAINED PRESSURE PATHS 5 6 Figure 1 Main Hydraulic System Components 5 7 KEY TO...

Страница 143: ...Page 5 2 Pilot s Operating Manual Original Issue Feb 2002 Sub section 5 HYDRAULICS Hawker 800XP Pro Line 21 Section III SYSTEMS DESCRIPTION Intentionally left blank...

Страница 144: ...el brakes Nosewheel steering Normal operation of the flaps Operation of the airbrakes Stall identification stick push Operation of the thrust reversers AUXILIARY HYDRAULIC SYSTEM Emergency extension o...

Страница 145: ...ard relief valve as well as a pressure gauge Table 1 Indicators and Annunciators Item Location Parameter Combined BRAKES 2 and SUPPLY indicator Center instrument panel psi Brakes 2000 Supply 3000 Main...

Страница 146: ...ove 3750 psi the relief valve operates to pass fluid into the return line Low Pressure Indication The low pressure switch operates if the pump pressure falls to 1500 psi A time delay prevents the asso...

Страница 147: ...w pressure below 2250 psi in the path or accumulator is indicated by the illumination of the EMRG BRK LO PRESS annunciator on the main MWS panel Accumulators Three piston type accumulators each instal...

Страница 148: ...Hawker 800XP Pro Line 21 Section III SYSTEMS DESCRIPTION Pilot s Operating Manual Revision A2 Nov 2004 Figure 1 Main Hydraulic System Components ISOLATION VALVE ISOLATION VALVE STALL IDENT UNIT AIR B...

Страница 149: ...ir Suction Pressure Return Emergency Brakes Maintained Pressure Component Identification 1 Capacitor 2 Pressure switch and snubber 3 Full flow relief valves 4 Ground servicing hand pump 5 Emergency br...

Страница 150: ...RESSURE FILTER EMERGENCY BRAKE ACCUMULATOR STALL IDENT N STICK PUSH MAIN ACCUMULATOR SPEED CONTROL RESTRICTOR SYSTEM PRESSURE GAUGE 5 6 TO BRAKE UNITS PRESS SWITCH GROUND AIR CONNECTION lubrication lo...

Страница 151: ...f the setting of the landing gear selector lever but the flaps must be selected to the required setting 2 When using the auxiliary system lowering of the landing gear always occurs before operation of...

Страница 152: ...PTION ON OFF VALVE LANDING GEAR SELECTOR DUMP VALVE RESERVOIR FILTER KEY AUXILIARY SYSTEM MAIN SYSTEM SUCTION RETURN CIRCUIT SHOWN WITH SELECTOR HANDLE PULLED MAIN SYSTEM FLAP CONTROL UNIT AUX HYD LO...

Страница 153: ...no pressure in the auxiliary system the shuttle valves close the auxiliary system supply ports on the landing gear jacks allowing main system pressure to operate the jacks With the lever in the normal...

Страница 154: ...after the commencement of emergency lowering hand pump resistance decreases when the gear uplocks release and the AUX HYD LO LEVEL annunciator is illuminated Continued operation of the hand pump lock...

Страница 155: ...te or exercise the auxiliary system operation of the flaps will be from the main system To reset the system first make sure the LANDING GEAR selector lever is in the down position then push the AUX HY...

Страница 156: ...igure 3 Rudder Trim System 6 7 Rudder Bias System 6 8 Electric Heating 6 9 Figure 4 Rudder Bias System 6 10 ELEVATOR CONTROL SYSTEM 6 11 Figure 5 Elevator Control System 6 11 Elevator Trim System 6 12...

Страница 157: ...Page 6 2 P N 140 590032 0007 Revision A4 Sep 2010 Section III Sub section 6 FLIGHT CONTROLS Pilot s Operating Manual Intentionally left blank...

Страница 158: ...ng stick shake and identification system stick push is also provided Refer to Sub section 7 STALL WARNING IDENTIFICATION Internal gust locks are provided to lock the control surfaces when the airplane...

Страница 159: ...Page 6 4 P N 140 590032 0007 Revision A4 Sep 2010 Section III Sub section 6 FLIGHT CONTROLS Pilot s Operating Manual Figure 1 Aileron Control System...

Страница 160: ...trim actuator is connected by a cable system to a trim handwheel mounted on the center control pedestal immediately below the rudder trim handwheel Aileron Out Of Trim Warning A warning of the ailero...

Страница 161: ...ting rods and a bell crank to a pulley drum under the flight compartment floor Cables transmit the movement of the pulley drum to a quadrant installed at the bottom of the rudder torque tube A spring...

Страница 162: ...LIGHT CONTROLS 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 ta...

Страница 163: ...solenoid valve installed in each strut The solenoid valves are normally in the closed position when the RUDDER BIAS selector switches A and B are set to their ON positions Accidental operation of the...

Страница 164: ...re supplied separately from the L and R PITOT VANE HEAT switches on the overhead roof panel Each switch controls the power supply to one heating element of each strut Pitot Vane Switch Busbar Circuit...

Страница 165: ...Page 6 10 P N 140 590032 0007 Revision A4 Sep 2010 Section III Sub section 6 FLIGHT CONTROLS Pilot s Operating Manual Figure 4 Rudder Bias System...

Страница 166: ...left control circuit to provide acceptable stick force characteristics A stick shaker motor is attached to each control column and is operated by the stall warning system A stick pusher unit is conne...

Страница 167: ...ns are described more extensively in Sub section 17 AVIONICS If necessary these functions can be overridden by arresting the movement of the elevator trim handwheel which turns as the automatic system...

Страница 168: ...Page 6 13 P N 140 590032 0007 Revision A4 Sep 2010 Section III Sub section 6 FLIGHT CONTROLS Pilot s Operating Manual Figure 6 Elevator Trim System...

Страница 169: ...ab deflection to increase longitudinal stability at Mach numbers above 0 75 Mach when the autopilot is not engaged Faults which render the system inoperative fail passive will result in a warning give...

Страница 170: ...he transmission shafting to move the flaps in the selected direction The motor is stopped automatically should a control cable failure occur When the flaps reach the selected position the hydraulic pr...

Страница 171: ...Page 6 16 P N 140 590032 0007 Revision A4 Sep 2010 Section III Sub section 6 FLIGHT CONTROLS Pilot s Operating Manual Figure 7 Flap Control System...

Страница 172: ...laps are selected to the 25 or 45 positions when the landing gear is not locked down The flaps are controlled by a selector lever located on the right side of the center control pedestal The lever mov...

Страница 173: ...set position from 0 to 45 Lift dump and airbrakes are not available The emergency flap selection is made using the normal flap control lever Position indication is still available as long as PS1 a bu...

Страница 174: ...valve mounted on each airbrake actuator Main hydraulic system pressure is utilized to operate the airbrakes through a hydraulic actuator in each wing To allow for control system failure the selector...

Страница 175: ...tion automatically lowers the flaps from the 45 setting to 75 and also opens the airbrakes further to provide maximum drag Annunciations and Warnings The airbrake system has a white system status annu...

Страница 176: ...n of Stall Identification Angle With Rate of Increase of Vane Angle 7 5 THIRD STALL IDENTIFICATION CHANNEL 7 6 Figure 3 Stall Warning and Identification 7 6 Figure 4 Stall System Pitot Static Block Di...

Страница 177: ...Page 7 2 Pilot s Operating Manual Revision A2 Nov 2004 Sub section 7 STALL WARNING IDENTIFICATION Hawker 800XP Pro Line 21 Section III SYSTEMS DESCRIPTION Intentionally left blank...

Страница 178: ...stall identification sensor Annunciators and test switches SYSTEM LOGIC 1 It is impossible for a stick push to occur before a stall warning stick shake 2 No single active fault of an SSU or relay can...

Страница 179: ...em pressure backed by the main accumulator the rate of operation being controlled by a fluid restrictor Control of the hydraulic pressure to the stick pusher is via two independent stall valves A and...

Страница 180: ...1 Section III SYSTEMS DESCRIPTION 0 1 2 3 4 5 14 16 18 20 22 VANE RATE DEGREES SECOND 24 26 6 7 9 28 FLAP 0 WARN FLAP 15 25 WARN FLAP 45 WARN FLAP 0 IDENT FLAP 0 IDENT VANE ANGLE to HFD Degrees Figure...

Страница 181: ...o produce an output at a point between the settings for the stall warning and identification signals from the SSUs The output from the third channel sensor energizes a relay which connects the stall i...

Страница 182: ...t Static Block Diagram Left Forward Static Vent Plate 6 Right Forward Static Vent Plate 6 S6 P S Stall Detector Right Pitot Head P2 Pitot Isolation Valve Stall Ident Autopilot Disconnected S6 P S P2 S...

Страница 183: ...lve is routed via the identification relay of one channel and the warning relay of the other channel A monitoring circuit will cause an IDENT 1 or IDENT 2 annunciator depending on the channel at fault...

Страница 184: ...e than 4 seconds then a SQUAT annunciator Copilot s group only will illuminate SSU SELF TEST A built in test within the SSU detects the following faults Loss of 26 VDC supply Loss of internal power or...

Страница 185: ...ight On Wheels asymmetry SQUAT Stall valve A B operating STALL VLV A B OPEN Table 2 Power Supplies Panel Location Row Column Circuit Breaker Circuit or Equipment Busbar DA D B 1 STALL IDENT 1 26 VAC i...

Страница 186: ...TALL AND INITIATES A WARNING SIGNAL WARNING SIGNAL FROM EITHER CHANNEL DISCONNECTS AUTOPILOT AND OPERATES ANGLE OF ATTACK INCREASING NO YES PREVENTIVE ACTION TAKEN BY PILOT ANGLE OF ATTACK STALL IDENT...

Страница 187: ...Section III SYSTEMS DESCRIPTION Page 7 12 Pilot s Operating Manual Revision A2 Nov 2004 Hawker 800XP Pro Line 21 Sub section 7 STALL WARNING IDENTIFICATION Intentionally left blank...

Страница 188: ...r Selector and Baulk Override 8 6 RETRACTION and EXTENSION 8 7 Figure 2 Landing Gear Hydraulic System 8 8 MAIN GEAR 8 9 WEIGHT ON WHEELS SWITCHES 8 9 NOSE GEAR 8 9 NOSE GEAR BAY DOORS 8 9 Figure 3 Mai...

Страница 189: ...ine 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...

Страница 190: ...n hydraulic system for the normal lowering and retraction of the gear An auxiliary hydraulic system is provided for lowering the gear should the main hydraulic system or landing gear selection control...

Страница 191: ...ependent circuit connected to green L GEAR and R GEAR annunciators located on the right side console Nose Gear As the nose gear locks down a mechanical post indicator extends from the top left of the...

Страница 192: ...to obtain between 60 and 70 N1 RPM nominal with IAS below 150 kts In this case the warning horn can be cancelled by a switch on the forward side of the LH thrust lever The audible warning is repeated...

Страница 193: ...owing the selector lever to be moved away from the LANDING GEAR DOWN position The pawl re engages when the airplane lands The airplane has a LANDING GEAR BAULK OVRD PUSH button located next to the LAN...

Страница 194: ...equence is as follows Main gear wheel well doors open Nosewheel steering isolated nose wheel self centers Nose gear doors open Nose gear locks up and doors shut Main gear locks up Wheel well doors shu...

Страница 195: ...For Auxiliary Hydraulic System See Figure 6 LANDING GEAR SELECTOR DUMP VALVE MAIN GEAR ACTUATOR MAIN GEAR ACTUATOR SEQUENCE VALVE SEQUENCE VALVE DOOR ACTUATOR DOOR ACTUATOR DIAGRAM SHOWS LANDING GEAR...

Страница 196: ...the landing gear completes the closure of the bay when the gear is retracted The oleo pneumatic leg is attached to a fitting on each side of the nose gear bay and is stabilized in the down position by...

Страница 197: ...8 10 Pilot s Operating Manual Revision A2 Nov 2004 Sub section 8 LANDING GEAR Section III SYSTEMS DESCRIPTION Hawker 800XP Pro Line 21 HYDRAULIC ACTUATOR RETRACTION DOOR ACTUATOR Figure 3 Main Landing...

Страница 198: ...Original Issue Feb 2002 Sub section 8 LANDING GEAR Hawker 800XP Pro Line 21 Section III SYSTEMS DESCRIPTION Figure 4 Nose Landing Gear HYDRAULIC RETRACTION ACTUATOR STEERING ACTUATOR STEERING DISCONNE...

Страница 199: ...ection III SYSTEMS DESCRIPTION POWER SUPPLIES DC power distribution is as follows PE Busbar Normal landing gear position annunciators 6 Warning horn control and warning horn PS1 Busbar Landing gear le...

Страница 200: ...and the gear extends The main gear uplocks are released the wheel well doors are unlocked and the main gear extends pushing the doors open As the nose gear locks down the mechanical linkage closes th...

Страница 201: ...TION ON OFF VALVE LANDING GEAR SELECTOR DUMP VALVE RESERVOIR LEVEL INDICATOR FILTER MAIN GEAR ACTUATORS SHUTTLE VALVE KEY AUXILIARY SYSTEM MAIN SYSTEM SUCTION RETURN NOSE GEAR ACTUATOR CIRCUIT SHOWN W...

Страница 202: ...mal and emergency operation With the WHEEL BRAKE lever fully forward main hydraulic system pressure backed by the main accumulator passes to a brake control valve via a main reducing valve The control...

Страница 203: ...KE EMERG annunciators illuminate Full parking pressure is applied when the WHEEL BRAKE lever is in the PARK BRAKE position Pressure supplied by the emergency brake accumulator is maintained at the bra...

Страница 204: ...l supply so that the modulator units and Maxaret units are inoperative With the emergency system selected the BRAKE indications continue to show normal system pressure to the brakes provided there is...

Страница 205: ...steering actuator The nose gear is turned in the required direction by the steering actuator When the required degree of turn has been reached feedback through linkage connected to the landing gear mo...

Страница 206: ...Page 8 19 Pilot s Operating Manual Original Issue Feb 2002 Sub section 8 LANDING GEAR Hawker 800XP Pro Line 21 Section III SYSTEMS DESCRIPTION Figure 9 Nose Gear Steering System...

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Страница 208: ...EN switch 9 11 GEN 1 AND GEN 2 CLOSE TRIP switch 9 11 Figure 4 Normal Flight Conditions 9 12 ENGINE START USING EXTERNAL POWER 9 13 ABORT START 9 13 Figure 5 Internal Start with No 2 Engine Selected 9...

Страница 209: ...590032 0007 Revision A4 Sep 2010 Section III Sub section 9 ELECTRICAL POWER Pilot s Operating Manual Page AC POWER DISTRIBUTION 9 22 Figure 8 Inverter System Busbars Simplified 9 22 ALTERNATOR POWER...

Страница 210: ...parallel A start busbar links the start power source either the ground supply contactor or the internal start contactor with the individual engine 1 and 2 start contactor or the APU start contactor A...

Страница 211: ...ddition to the main battery supplies three 24 VDC 4 ampere hour sealed lead acid batteries Nos 3 4 and 5 are located in the rear equipment bay These batteries provide electrical power for the emergenc...

Страница 212: ...1 PE 2 No 2 STARTER GEN PS1 BUSBAR PS2 BUSBAR GROUND POWER CONTACTOR BATT SHUNT 1 BATT SHUNT 2 ENG 2 ENG 1 SHUNT INT START CONTACTOR APU GEN CONTACTOR APU START CONTACTOR GEN LINE CONTACTOR 1 GEN LIN...

Страница 213: ...is charged from the PS1 busbar and No 2 battery is charged from the PS2 As a generator comes on line the associated battery contactor closes automatically and the charge begins The batteries may also...

Страница 214: ...No 1 PE BUSBAR BATT 1 BATT 2 INTERNAL START CONTACTOR EMERGENCY CONTACTORS PE 2 GEN SHUNT No 1 GEN SHUNT No 2 APU GEN SHUNT EXTERNAL POWER CONTACTOR TO PS2 a and PS2 b BUSBARS TO PS1 a and PS1 b BUSB...

Страница 215: ...tactors remain closed The generator fed PS busbar is connected to its related battery to commence charging by closure of the associated battery contactor Both batteries may be charged from one generat...

Страница 216: ...wer 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 The relevant BATT CNTCTR annunciator will illu...

Страница 217: ...R No 1 PE BUSBAR BATT 1 BATT 2 INTERNAL START CONTACTOR EMERGENCY CONTACTORS PE 2 GEN SHUNT No 1 GEN SHUNT No 2 APU GEN SHUNT EXTERNAL POWER CONTACTOR TO PS2 a AND PS2 b BUSBARS TO PS1 a AND PS1 b BUS...

Страница 218: ...t Operated momentarily to the TRIP position it will disconnect its associated generator from the busbars and isolate its field circuit and illuminate the following annunciators Operated to the CLOSE p...

Страница 219: ...ACTOR No 2 GEN LINE CONTACTOR No 1 PE BUSBAR BATT 1 BATT 2 INTERNAL START CONTACTOR EMERGENCY CONTACTORS PE 2 GEN SHUNT No 1 GEN SHUNT No 2 APU GEN SHUNT EXTERNAL POWER CONTACTOR TO PS2 a AND PS2 b BU...

Страница 220: ...then its generator is used as detailed below At ENGINE START switch operation ENG 1 or 2 the Generator Control Unit GCU initiates the start cycle Illumination of the OPERATING annunciator indicates c...

Страница 221: ...E CONTACTOR PE BUSBAR BATT 1 BATT 2 INTERNAL START CONTACTOR EMERGENCY CONTACTORS PE 2 GEN SHUNT No 1 GEN SHUNT No 2 APU GEN SHUNT EXTERNAL POWER CONTACTOR TO PS2 a AND PS2 b BUSBARS TO PS1 a AND PS1...

Страница 222: ...e driven from each engine serve as the primary source of power for the airplane The generators are self exciting and each produce a rated power output of 9 kW when the engine reaches self sustaining s...

Страница 223: ...r feeds busbars PS1 and PS2 as well as PE DOUBLE GENERATOR FAILURE Figure 7 Following a double generator failure both generator contactors open Both battery contactors also open to prevent the batteri...

Страница 224: ...RT GEN LINE CONTACTOR No 2 GEN LINE CONTACTOR PE BUSBAR BATT 1 BATT 2 INTERNAL START CONTACTOR EMERGENCY CONTACTORS PE 2 GEN SHUNT No 1 GEN SHUNT No 2 APU GEN SHUNT EXTERNAL POWER CONTACTOR TO PS2 a A...

Страница 225: ...GEN LINE CONTACTOR PE BUSBAR BATT 1 BATT 2 INTERNAL START CONTACTOR EMERGENCY CONTACTORS PE 2 GEN SHUNT No 1 GEN SHUNT No 2 APU GEN SHUNT EXTERNAL POWER CONTACTOR TO PS2 a AND PS2 b BUSBARS TO PS1 a...

Страница 226: ...RVOLTAGE PROTECTION The GCU overvoltage protection circuit operates when the generator terminal voltage rises above 32 5 VDC This opens the generator field and signals the GLC to open disconnecting th...

Страница 227: ...E FAIL annunciator will also result in the red flashing MWS master warning lamps on the glareshield to operate The ELECT repeater annunciator will flash when any of the following annunciators illumina...

Страница 228: ...operate Annunciator INV 2 will remain illuminated Starting No 2 inverter With the No 1 inverter on line momentarily selecting the INV 2 switch to START causes the following actions Energizes No 2 inv...

Страница 229: ...f a single main inverter failure the remaining main inverter output will be automatically switched to supply all three busbars If failure of both main inverters should occur essential services supplie...

Страница 230: ...alternators one driven by each engine This supply is used to power the windscreen and side screen heating and the vane heaters Each alternator is controlled by an ALTERNATOR 1 or 2 ON OFF switch loca...

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Страница 232: ...10 7 COLD AIR UNIT CAU 10 7 LOW LIMIT TEMPERATURE CONTROL SYSTEM 10 8 DUCT TEMPERATURE 10 8 CABIN TEMPERATURE CONTROL SYSTEM 10 9 AUTO MODE 10 9 MANUAL MODE 10 9 FLOOD AIR CONTROL 10 10 AUXILIARY HEAT...

Страница 233: ...Page 10 2 Pilot s Operating Manual Original Issue Feb 2002 Sub section 10 ENVIRONMENTAL Hawker 800XP Pro Line 21 Section III SYSTEMS DESCRIPTION Intentionally left blank...

Страница 234: ...r Valves MAV are selected open High Pressure HP air is ducted from a flow limiting venturi to a solenoid operated shut off valve then to the mixing valve MIXING VALVE The mixing valve regulates HP air...

Страница 235: ...d then via a common duct to a pressure regulator and shut off valve unit PRSOV and a pressure reducing and flow restricting venturi to an air cycle machine AIR CYCLE MACHINE The air cycle machine ACM...

Страница 236: ...Hawker 800XP Pro Line 21 Section III SYSTEMS DESCRIPTION Page 10 5 Sub section 10 ENVIRONMENTAL Pilot s Operating Manual Revision A2 Nov 2004 Figure 1 Air Supply and Distrubution...

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Страница 238: ...NIT CAU The CAU consists of a fan a compressor and a turbine mounted on a common shaft Bleed Air from the venturi enters the ACM via the primary heat exchanger which cools the air to an acceptable lev...

Страница 239: ...llow continued flow The operation of the LLTCV is controlled by a low limit control sensor in the duct downstream of the water separator The low limit temperature control system operates independently...

Страница 240: ...is required Resulting signals from the controller cause the cabin temperature control valve to open or close accordingly A CABIN TEMP indicator on the overhead roof panel is connected to a temperatur...

Страница 241: ...the unlikely event that freezing would occur at the water separator due to high humidity at these cold temperatures the bypass valve in the water separator would open and allow continued flow FLOOD AI...

Страница 242: ...sed until selected manually open RAM AIR Ram air from the dorsal air intake is used primarily as a cooling medium for the heat exchanger but it can also be introduced into an unpressurized cabin for v...

Страница 243: ...ols or indications for this supply CABIN RECIRCULATED AIR SUPPLY An electrically operated fan draws air from the rear of the cabin and recirculates it via individual controllable outlets on each passe...

Страница 244: ...ressure 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 A plain white pointer which indicates cab...

Страница 245: ...dial with an outer and an inner scale Both scales show ALTitude graduated in FT x 1000 The outer displays the selected CABIN altitude With a CABIN altitude set the inner scale shows the associated air...

Страница 246: ...a venturi in the forward luggage bay Rotating the MANUAL CABIN ALTITUDE CONTROL valve between INCREASE and DECREASE adjusts the pressure differential required to operate the outflow valve and allows a...

Страница 247: ...essure switch is controlled by an illuminated push button switch labelled CABIN HIGH DATUM on the copilot s instrument panel When the button is pushed and illuminated the high altitude datum pressure...

Страница 248: ...ssure Regulators Air Jet Pump Outflow Safety Valve Outflow Safety Valve True Static Atmosphere Atmosphere Bleed Port Cabin Air Venturi Atmosphere Port Low Pressure Port MANUAL CABIN Air Filter Assembl...

Страница 249: ...Section III SYSTEMS DESCRIPTION Page 10 18 Pilot s Operating Manual Revision A2 Nov 2004 Hawker 800XP Pro Line 21 Sub section 10 ENVIRONMENTAL Intentionally left blank...

Страница 250: ...etection Components 11 5 FLUID STORAGE 11 6 Warning Annunciators 11 6 POWER SUPPLIES 11 6 Figure 2 Airframe Ice Protection System 11 7 ENGINE BLEED AIR ANTI ICING 11 8 Warning Annunciators 11 8 Figure...

Страница 251: ...Page 11 2 Pilot s Operating Manual Original Issue Feb 2002 Sub section 11 ICE PROTECTION Hawker 800XP Pro Line 21 Section III SYSTEMS DESCRIPTION Intentionally left blank...

Страница 252: ...m reverts to normal flow If icing conditions still prevail or are expected and therefore a further period of operation is required this should be selected before the timer switch reaches zero Using th...

Страница 253: ...operation on the ground Power supplies to the ice detector are fed through the weight on wheels switch relay system and controlled by an ICE DET AUTO OVRD switch With the switch selected to AUTO the d...

Страница 254: ...ion 11 ICE PROTECTION Hawker 800XP Pro Line 21 Section III SYSTEMS DESCRIPTION ICE DETECTION SPOTLIGHT Same Right Side ROTARY CUTTER ICE DETECTOR ICE DETECTED ICE PROT Figure 1 Ice Detection Component...

Страница 255: ...below the tank filler should be pushed for 10 seconds to bleed the pump NOTE The vent valve must not be operated while the pump is running Warning Annunciators With the pump running system low pressur...

Страница 256: ...Page 11 7 Pilot s Operating Manual Original Issue Feb 2002 Sub section 11 ICE PROTECTION Hawker 800XP Pro Line 21 Section III SYSTEMS DESCRIPTION Figure 2 Airframe Ice Protection System...

Страница 257: ...compressor and ducted forward to anti ice the nacelle inlet cowl Electrical power is supplied via the fuel computer switch when set to AUTO to the Pt2 and Tt2 sensor probe heaters located in the inle...

Страница 258: ...Line 21 Section III SYSTEMS DESCRIPTION ENG ANTICE 1 2 OFF PE BUSBAR PICCOLO TUBE 2 SEC MWS DIM BUS ON ICE PROT SELECTED ENG 1 A ICE Figure 3 Engine Anti icing System TO Pt2 and Tt2 HEATING CIRCUITS T...

Страница 259: ...rnator failure is indicated by the illumination of an associated ALTR FAIL 1 2 annunciator and the MWS ICE PROT repeater annunciator The two forward facing panels of the windshield each incorporate a...

Страница 260: ...Page 11 11 Pilot s Operating Manual Original Issue Feb 2002 Sub section 11 ICE PROTECTION Hawker 800XP Pro Line 21 Section III SYSTEMS DESCRIPTION Figure 4 Windscreen Electrical Heating...

Страница 261: ...es 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 SCREEN HEAT R ON OFF control No...

Страница 262: ...ith PITOT VANE HEAT switched ON for at least 1 minute readings of between 5 and 10 amps indicate satisfactory operation of the pitot heaters only Actual power consumption depends on the ambient temper...

Страница 263: ...S ANTICE LO QTY annunciators and the MWS ICE PROT repeater annunciator is taken from busbar PE The fluid contents indicator is supplied from busbar PE when the airplane is on the ground and busbar PS2...

Страница 264: ...mbly 12 5 OPERATION 12 6 Figure 4 Flight Compartment Oxygen Panel on Left Console 12 6 PORTABLE OXYGEN SMOKE SET 12 7 Figure 5 Portable Oxygen Smoke Set 12 7 FLIGHT CREW SUPPLY 12 8 Mask Regulator 12...

Страница 265: ...Page 12 2 Pilot s Operating Manual Original Issue Feb 2002 Sub section 12 OXYGEN SYSTEM Hawker 800XP Pro Line 21 Section III SYSTEMS DESCRIPTION Intentionally left blank...

Страница 266: ...vestibule cabinet for a third crew member a drop out mask in the vestibule and for additional drop out mask units in the passenger cabin depending on the number of seats Cylinder pressure is reduced t...

Страница 267: ...e Feb 2002 Sub section 12 OXYGEN SYSTEM 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...

Страница 268: ...alve 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 The automatic shut off valve is also loc...

Страница 269: ...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 regu...

Страница 270: ...inder rests in a fixture secured to the rear of the flight compartment right console Pre Mod 252939 The top of the cylinder is secured to the forward face of panel DA by a toggle fastener Post Mod 252...

Страница 271: ...n is supplied Between 35 000 and 41 000 feet 100 oxygen at a positive pressure is automatically maintained However 100 oxygen is available at any altitude when the mask regulator is selected to the 10...

Страница 272: ...ust be removed before donning oxygen masks THERAPEUTIC SUPPLY Oxygen for therapeutic use is available at two self sealing outlets in the passenger cabin These outlets incorporate a check valve spring...

Страница 273: ...ns automatically or manually and allows the mask to drop into the half hang position during an emergency The mask has a lightweight molded face piece which can be held against the face with one hand M...

Страница 274: ...Page 12 11 Pilot s Operating Manual Original Issue Feb 2002 Sub section 12 OXYGEN SYSTEM Hawker 800XP Pro Line 21 Section III SYSTEMS DESCRIPTION Figure 9 Oxygen Mask Folding and Stowage...

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Страница 276: ...7 EMERGENCY LIGHTING 13 7 AUXILIARY POWER UNIT PANEL LIGHTING if installed 13 7 FLIGHT COMPARTMENT LIGHTING POWER SOURCES Table 1 13 7 PRINCIPAL DIMMER CONTROLS Table 2 13 8 ANNUNCIATORS 13 9 GALLEY L...

Страница 277: ...ontrol 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 Pa...

Страница 278: ...light mounted on the rear face of the forward cabinet and a twin light assembly mounted in the vestibule roof Lights are installed in the main entry doorway top and bottom step risers Switching is by...

Страница 279: ...ight glareshield side control panels and labelled PANEL LTS FLOOD The emergency lights are controlled by a three position switch on the left and right glareshield side control panels and labelled PANE...

Страница 280: ...LIGHT ANNUN TEST PAD LAMP PAD LAMP MASTER LIGHT SW STANDBY COMPASS INTEGRAL LAMP PANEL DIM INSTR DIM STORM LAMP STORM LAMP S F L A N D I N G G E A R DIGIT FD BARS GLARESHIELD PANEL PAD PANELS INST DIS...

Страница 281: ...ed on the inward face of the right bulkhead panel DA The CHART WANDER LIGHT switch will override the dimmer controls and turn both lights to full intensity Electrical power is supplied to the chart li...

Страница 282: ...by the STORM OFF EMERG switches mounted on the left and right glareshields when selected to EMERG AUXILIARY POWER UNIT PANEL LIGHTING if APU installed The translucent APU panel is illuminated from be...

Страница 283: ...1 GLARESHIELD PANEL 5 VDC Left glareshield side and upper electroluminescent panels PS1 INSTRUMENT PANEL PANELS 5 VDC Left electroluminescent panels Center electroluminescent panels PS2 INSTRUMENT PAN...

Страница 284: ...DIM OVRD switch may be selected to the OVRD position this effectively bypasses the dimming circuit and connects a 28 VDC supply direct to the annunciators Both power supplies are taken from the PE bus...

Страница 285: ...light assembly to illuminate the working surface and controlled by the GALLEY WORK LIGHTS switch on the galley switch panel The circuit breaker panel is located in the galley circuit breaker compartme...

Страница 286: ...interior lighting is provided by a twin light assembly positioned in the wardrobe upper section The lights are connected in parallel supplied from the PS2 busbar and controlled by an illuminated push...

Страница 287: ...r Reading lights left hand inverter PS2 Busbar Cabin flood lights right hand inverter Toilet lights FWD and rear luggage bay lights Reading lights right hand PSU s Battery 1 in flight Vestibule roof l...

Страница 288: ...lights and the R H two middle overhead reading lights An amber EMERG LTS OFF annunciator adjacent to the emergency light switch will illuminate anytime the switch is in the OFF position and PE is pow...

Страница 289: ...tment 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 o...

Страница 290: ...y to give general area lighting and power supply for a plug in wander light Control of the switch is by manual selection to ON or OFF and automatic selection to OFF when the door is closed Two pillar...

Страница 291: ...drain holes in the lens cover forward and aft of the attachment bosses LANDING and TAXI LIGHTS Figures 7 and 8 Mounted together in each wing leading edge these lights are sealed beam units controlled...

Страница 292: ...xterior Lighting NAVIGATION LIGHT GREEN STROBE LIGHT LANDING LIGHTS TAXI LIGHT LANDING LIGHT LANDING LIGHT TAXI LIGHT LEFT LOGO FLOOD LIGHT if installed RIGHT LOGO FLOOD LIGHT if installed NAVIGATION...

Страница 293: ...controlled by a single LOGO ICE OFF switch located on the EXTERIOR LIGHTS section of the flight compartment overhead roof panel forward extension BOARDING LIGHT Figure 8 The ground area and bottom st...

Страница 294: ...TING 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 Right nos...

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Страница 296: ...ight Compartment Overhead Roof Panels 14 8 Figure 6 Flight Compartment looking aft 14 9 Figure 7 Flight Compartment Side Consoles 14 10 Figure 8 Flight Compartment Center Pedestal 14 11 GALLEY 14 12 F...

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Страница 298: ...erride When the thigh support adjustment control knob is turned two bevel gears mounted on the cross shaft are rotated which in turn rotate a threaded drive shaft under each thigh pad The rotating dri...

Страница 299: ...raised to an almost vertical position where it will be held by a friction clutch until returned to the horizontal position by the occupant Back Cushion Lumbar Support The seat back cushion is adjustab...

Страница 300: ...he seat is installed by engaging the seat slides with the crew seat rails then locating the locking pin holes in the seat rails and the seat slides and then locking the pins into position CREW CABINET...

Страница 301: ...EW SERVICES PANEL CENTER INSTRUMENT PANEL CC ROOF PANEL CG MAIN SECTION ROOF PANEL CG FWD SECTION LEFT SIDE CONSOLE RIGHT SIDE CONSOLE LEFT HAND INSTRUMENT PANEL CA CONTROL PEDESTAL PANEL RIGHT HAND I...

Страница 302: ...Compartment Center Instrument Panel Pilot Instrument Panel M5880_0 HA00B 995511AA AI MFD PFD CABIN PRESSURE CONTROL L A N D I N G G E A R MODE AHRS NORM SLEW CABIN ALTITUDE DIFF PRESSURE RATE OF CLIM...

Страница 303: ...FUEL 1 LO PRESS FUEL 2 LO PRESS IGN ON OPERATING PWR ON PUSH FOR ABORT OPERATING ALTR 2 FAIL ICE DETECTED ANTICE LO QTY ALTR 1 FAIL SIDE SCRN OVHT ANTICE LO PRESS SCREEN HEAT PITOT VANE HEAT ENG ANTIC...

Страница 304: ...MASK MIC SOCKETS HEADSET OXYGEN MASK MIC SOCKETS FIRE EXTINGUISHER FLASHLIGHT LIFE JACKET STOWAGE LIFE JACKET STOWAGE WARNING HORN SUN VISORS STOWAGE RADIO AND ELECTRONIC EQUIPMENT RUDDER GUST LOCK A...

Страница 305: ...INCREASE DECREASE L GEAR R GEAR ISOLATE PITOT ISOLATION DEPRESS TO OPERATE MANUAL CABIN ALTITUDE CONTROL NORMAL NORMAL PRESSURIZATION CONTROL TEST GROUND RIGHT HAND CONSOLE LEFT HAND CONSOLE OXYGEN P...

Страница 306: ...R EMERGENCY HYDRAULIC HAND PUMP EMERGENCY HYDRAULIC HAND PUMP HANDLE GUST LOCK BAR STOWAGE ON RH SEAT SUPPORT STRUCTURE L P COCKS H P COCKS FIRE WARNING LIGHTS FLAPS L P COCKS GUARD AUXILIARY FUEL TRA...

Страница 307: ...and refreshment cabinet light The drain dish is connected to an overboard drain A heater is attached to the drain pipe immediately inboard of the drain exit from the fuselage Control of the galley fun...

Страница 308: ...ge 14 13 Pilot s Operating Manual Revision A1 Nov 2002 Sub section 14 EQUIPMENT and FURNISHINGS Hawker 800XP Pro Line 21 Section III SYSTEMS DESCRIPTION PASSENGER CABIN Figure 10 Typical Interior Layo...

Страница 309: ...n comprises a base assembly with seat cushions back cushions and a safety lap shoulder belt assembly at each seat position The base assembly is attached to the floor and sidewall seat rails The two ou...

Страница 310: ...seat structure Luggage Compartment The radio compartment under the luggage compartment is concealed by trim panels which can be removed for maintenance purposes Wing Fairing Equipment in the wing fai...

Страница 311: ...Page 14 16 Pilot s Operating Manual Original Issue Feb 2002 Sub section 14 EQUIPMENT and FURNISHINGS Hawker 800XP Pro Line 21 Section III SYSTEMS DESCRIPTION Figure 13 Cargo and Accessory Compartments...

Страница 312: ...ashbasin console is installed on the right side and incorporates washing facilities provision for toilet requisites and the filling point for the wash water tank The toilet service s bulkhead forms th...

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Страница 314: ...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 TRA...

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Страница 316: ...r BCF TYPE 34H Secured to left bulkhead behind the pilot seat Axe Secured to left bulkhead behind the pilot seat Flashlight Secured to left bulkhead behind the pilot seat Combination Oxygen Mask and G...

Страница 317: ...by setting the ARM OFF ON switch to the ON position This should be done with the antenna connected and only within the first 5 minutes of an hour for a maximum of three pulses see FAA Advisory Circula...

Страница 318: ...life support pack The PBE unit is stored in a sealed fire retardent polyethylene case which is located in the underfloor document compartment between the crew seats When the Pull To Actuate ring is r...

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Страница 320: ...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 16 5 TOILET 16 5 Fig...

Страница 321: ...Page 16 2 Pilot s Operating Manual Initial Issue Feb 2002 Sub section 16 WATER and WASTE Hawker 800XP Pro Line 21 Section III SYSTEMS DESCRIPTION Intentionally left blank...

Страница 322: ...llows The high level switch contacts are closed when the tank is full and open immediately the float starts to fall The low level switch contacts open when the minimum water level just above the eleme...

Страница 323: ...ol panel is pushed the galley busbar is connected to the PE busbar and indicated by the illumination of a small LED in the top left corner of the switch This provides a power supply via circuit breake...

Страница 324: ...OF STEP LIGHT switch forward vestibule cabinet rear face to ON connects a battery No 1 supply to the coil of the entry lights relay Operating the PRESS TO FLUSH timer button will connect the power sup...

Страница 325: ...ion 16 WATER and WASTE Hawker 800XP Pro Line 21 Section III SYSTEMS DESCRIPTION M6360_0 HA03C 014659AA AI BOWL GROUND FLUSH INLET ELECTRICAL CONNECTION MOTOR PUMP FILTER CARTRIDGE ASSEMBLY DRAIN VALVE...

Страница 326: ...Page 16 7 Pilot s Operating Manual Initial Issue Feb 2002 Sub section 16 WATER and WASTE Hawker 800XP Pro Line 21 Section III SYSTEMS DESCRIPTION A DETAIL A Figure 4 Toilet Ground Servicing...

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Страница 328: ...igure 3 Glareshield Control Panels 17 6 FLIGHT GUIDANCE SYSTEM FGS 17 7 ATTITUDE HEADING SYSTEM AHS 17 7 FLIGHT MANAGEMENT SYSTEM FMS 17 7 AIR DATA SYSTEM ADS 17 7 ENGINE INDICATING SYSTEM EIS 17 7 WE...

Страница 329: ...NCED 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...

Страница 330: ...ce system annunciations and navigation data on a single integrated display The PFD also provides engine or fuel and flaps display information when selected in reversionary mode The upper region of the...

Страница 331: ...ums Barometric Altitude based Minimum Descent Altitude and RA Minimums Radio Altitude based Decision Height Minimums FLIGHT GUIDANCE PANEL FGP Figure 3 The FGP is used to control the Flight Guidance S...

Страница 332: ...RS ARM OFF M5880_0 HA00B 995511AA AI MFD PFD CABIN PRESSURE CONTROL L A N D I N G G E A R MODE AHRS NORM SLEW CABIN ALTITUDE DIFF PRESSURE RATE OF CLIMB GEAR OVRD DIM OVRD DIM CPWS CANCEL STANBY HORIZ...

Страница 333: ...GLARESHIELD PANEL PAD PANELS INST DISPLAYS PANEL MIC KEY FLOOD EMERG STORM OFF PANEL LTS ATC IDENT CONSOLE INSTRUMENT PANEL ENGINE FD VNAV VS CRS1 DOWN UP FLC NAV HDG APPR ALT YD AP FD CRS2 YD AP DIS...

Страница 334: ...Gyro DG mode FLIGHT MANAGEMENT SYSTEM FMS The Flight Management System provides flight plan management multisensor navigation and radio tuning The FMS consists of two Flight Management Computers FMC...

Страница 335: ...stem advises the pilot when to climb descend or maintain altitude to avoid passing too close to the threat aircraft Resolution maneuvers between aircraft equipped with TCAS II are automatically co ord...

Страница 336: ...Page 17 9 Pilot s Operating Manual P N 140 590032 0007 Revision A4 Sep 2010 Section III Sub section 17 AVIONICS COMPONENT LOCATIONS Figure 4 Component Locations...

Страница 337: ...on is provided reference Figure 5 on the following page The power supply for No 1 ACP is provided by the PE busbar through the AUDIO 1 CTL circuit breaker The power supply for No 2 ACP is provided by...

Страница 338: ...HF2 HF2 HF1 HF1 PA PA VHF2 VHF2 VHF1 VHF1 MIC SELECT NORM BOOM MIC Figure 5 Audio Control Panel ACP M8504_0 AI 1 2 HF VHF ADF 1 2 PA MKR 1 2 DME NORM TONE SPKR PHONE OFF AUTOCOM PHONE I C 1 2 VOR ILS...

Страница 339: ...TT is pushed NORM EMERG switch When switched to EMERG this feature is designed to allow the operator to switch transmit and interphone functions to the cross side audio control panel This feature allo...

Страница 340: ...s regardless of the speaker selection on the audio panels The flight compartment unmuted audio system has an emergency bypass circuit between the ACP and VHF COMM NAV which will produce aural warning...

Страница 341: ...ion of the warning messages EGPWS Features The EGPWS system has 7 operating modes all of which are controlled by switching logic based upon radio altitude airspeed vertical speed landing gear flap pos...

Страница 342: ...ENTIONAL TCF CONVENTIONAL TCF IMPROVED TCF ENVELOPE PLAN VIEW IMPROVED TCF ENVELOPE 45 BIAS FACTOR 4 NM 12 NM 400 AGL 700 AGL 15 NM TERRAIN TERRAIN BIAS FACTOR M6914_0 HA00C 016398AA ENVELOPE BIAS FAC...

Страница 343: ...ude based on the GPS altitude which is designed to reduce or eliminate altitude errors resulting from temperature extremes non standard pressure altitude conditions and altimeter miss sets Self Test T...

Страница 344: ...T AREA NO LOWER LIMIT RFCF ALERT ENVELOPE 2 1 0 1 2 3 4 5 6 7 RFCF CEILING 300 FT ABOVE FIELD 5 0NM OUTER LIMIT 1 5 KRF NM FIELD ELEVATION RUNWAY END KRF MINIMUM RUNWAY FIELD CLEARANCE FT RWY RFCF ALE...

Страница 345: ...and has two sub modes Mode 2A is active when the flaps are in any position other than landing and the airplane is not on the glideslope centerline Mode 2B is active when the flaps are in the landing p...

Страница 346: ...e and approach Mode 4C alerts the flight crew to insufficient terrain clearance during takeoff or go around Mode 4A is active when the landing gear is UP and the EGPWS is in the approach mode If the a...

Страница 347: ...0 ft AGL or less than 30 ft AGL or a non ILS frequency is selected The Mode 5 alert envelope is enabled by glideslope deviations over 1 3 dots and radio altitudes between 300 and 1000 ft AGL typical T...

Страница 348: ...INIMUMS based on the Decision Height Some airplanes will have menu 14 ONE THOUSAND at 1000 ft AGL FIVE HUNDRED at 500 ft AGL MINIMUMS based on the Decision Height BANK ANGLE Mode 6 excessive bank angl...

Страница 349: ...7 Windshear Detection This mode is active for windshear detection during takeoff mode from rotation to 1500 ft AGL or if the airplane is reconfigured for landing The mode is also active for windshear...

Страница 350: ...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...

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Страница 352: ...dent supplies of pitot pressure to the following Left Pitot Head P1 Air Data Computer No 1 Right Pitot Head P2 Air Data Computer No 2 Standby Airspeed Indicator Stall Detectors Additional equipment co...

Страница 353: ...ir Data Computer No 2 and the ESIS Air Data Unit WiththevalveintheNORMALposition P2pitotpressureissuppliedfromtherightpitotheadtoallrelevant instruments and equipment Operating the valve from NORMAL t...

Страница 354: ...S Stall Detector Left Pitot Head Right Pitot Head 9 8 S9 S9 Pitot Isolation Valve Connections for Additional Equipment Stall Ident Autopilot Disconnected S6 Left Rear Static Vents Right Rear Static V...

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Страница 356: ...ents 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...

Страница 357: ...Section IV FLIGHT PLANNING DATA P N 140 590032 0007 Revision A3 Apr 2008 Page 2 Pilot s Operating Manual Intentionally left blank...

Страница 358: ...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 1 5 Figure 2 Speed and Temper...

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Страница 360: ...rature with indicated values of airspeed altitude and temperature The true Mach number on the graph differs slightly from the indicated Mach number by the magnitude of the position error given in Sub...

Страница 361: ...ES RELATIVE TO ISA Relationship to ISA conditions can be determined by entering the chart with a known altitude and temperature M7015_0 AI ALTITUDE thousands of feet TRUE OUTSIDE AIR TEMPERATURE C 60...

Страница 362: ...itude and temperature The true Mach number obtained will differ from indicated Mach number by the magnitude of the position error given in Sub section 5 05 of the Aircraft Flight Manual The chart assu...

Страница 363: ...ng Manual Revision A1 Nov 2002 Sub section 1 GENERAL Hawker 800XP Pro Line 21 Section IV FLIGHT PLANNING DATA NOTE Refer to the Airplane Flight Manual for maximum altitude limitation Speed and Tempera...

Страница 364: ...300 26 000 41 000 41 000 40 600 39 900 39 000 38 100 37 100 35 400 25 000 41 000 41 000 41 000 40 700 39 800 38 700 37 700 36 400 24 000 41 000 41 000 41 000 41 000 40 600 39 500 38 400 37 100 23 000...

Страница 365: ...41 000 ft or by a 200 ft min rate of climb limit at M 0 7 MAXIMUM TAKE OFF WEIGHT for CRUISE ALTITUDE TEMPERATURE RELATIVE TO ISA C 15 10 5 0 5 10 15 20 CRUISE ALTITUDE ft MAXIMUM TAKE OFF WEIGHT lb...

Страница 366: ...ERVE FUEL 2 19 END ALLOWANCES 2 20 OPERATION FROM and INTO HIGH ALTITUDE AIRFIELDS 2 20 RESERVE FUEL 2 20 DIVERSION 2 20 HOLDING 2 20 EN ROUTE ALLOWANCE 2 21 ICING CONDITIONS 2 21 EQUIVALENT STILL AIR...

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Страница 368: ...ne 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 A method for pre flight...

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Страница 370: ...HIGH SPEED INTERMEDIATE OR LONG RANGE PROCEDURE START and TAXI OUT TAKEOFF and CLIMB CRUISE DESCENT HOLD DIVERSION APPROACH and LAND TAXI IN FUEL END ALLOWANCES CLIMB CRUISE 1500 ft 1000 ft 1500 ft 10...

Страница 371: ...gether with a worked example illustrating its use in pre flight planning The fuel loading plan is arranged in five Parts 1 Permissible weights 2 Zero fuel weight 3 Flight plan 4 Fuel summary 5 Loading...

Страница 372: ...min and fuels lb Zero Fuel Weight Approach fuel Taxi in fuel Diversion Arrival Weight Diversion fuel Weight at end of Hold Holding fuel for min at altitude Additional fuel Reserves if required Destina...

Страница 373: ...Section IV FLIGHT PLANNING DATA Page 2 8 Pilot s Operating Manual Initial Issue Feb 2002 Sub section 2 PREFLIGHT Hawker 800XP Pro Line 21 Intentionally left blank...

Страница 374: ...w Departure Airfield Elevation 2000 ft Runway Length 5800 ft dry Runway Slope Zero No Clearway Stopway or Obstacles Temperature 66 F Wind Component Zero Distance to Destination 1900 nm En Route Wind 2...

Страница 375: ...section 5 20 From AFM Sub section 5 15 for departure airfield it can be seen that the WAT and tire speed limits at both flap settings are greater than 28 000 lb From AFM Sub section 5 20 assuming Flap...

Страница 376: ...350 lb WAT Limitation 25 930 lb Field Length Limitation wet 22 350 lb Permissible Landing Weight at Alternate 22 350 lb Maximum Zero Fuel Weight from AFM Section 2 18 450 lb Part 1 of the FUEL LOADING...

Страница 377: ...lowance is 170 lb per passenger 4 x 170 680 lb Baggage weight may be weighed or estimated 120 lb Zero Fuel Weight the sum of Operating Weight Passengers and baggage 16 900 lb This is less than the Max...

Страница 378: ...ives a Sector time for 1900 nm of about 270 minutes at the highest achievable cruise altitude of 39 000 ft Mean Sector speed is thus 60 x 1900 422 kt 270 and the ESAD from this section is 1814 nm by i...

Страница 379: ...the FUEL LOADING PLAN may now be completed Part 3A FLIGHT PLAN DISTANCES Sector Distance nm 1900 Diversion Distance nm 120 Still Air Time minutes 270 Still Air Time minutes 28 Mean Still Air Speed kts...

Страница 380: ...ion fuel required 711lb Weight at end of Holding 17 761 lb Holding fuel flow at 5000 ft ISA at mean weight of say 18 100 lb equals 1110 lb per hour antice off Add 25 lb per hour for ISA 5 C 1135 lb Th...

Страница 381: ...Weights lb Times min and Fuels lb Zero Fuel Weight 16 900 Approach Fuel 100 Taxi in Fuel 50 Diversion Arrival Weight 17 050 Diversion Fuel 711 Weight at End of Hold 17 761 Holding fuel for 30 min at 5...

Страница 382: ...ired 0 Sector 6785 lb Taxi out 100 lb TOTAL FUEL REQUIRED 8314 lb Part 5 LOADING CHECK optional Zero Fuel Weight 16 900 Values must not exceed Total Fuel required 8314 RAMP WEIGHT 25 214 28 120 lb Tax...

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Страница 384: ...n give ESAD values over a range of sector distances for headwinds and tailwinds of up to 160 knots Data is provided for true air speed values of 350 400 and 450 knots Cruise true air speeds may be det...

Страница 385: ...sector distance Landing at a high altitude airfield has no significant effect on sector fuel RESERVE FUEL DIVERSION Diversion fuel can be read from the tables Diversion Time and Fuel of this Sub secti...

Страница 386: ...gh guide Total NBAA IFR reserve fuel including 200 nm diversion and 35 minutes holding at 5000 ft will be 1500 lb for a Zero Fuel Weight of approximately 17 500 lb ICING CONDITIONS Climb The effect of...

Страница 387: ...7 463 500 921 833 761 700 673 648 625 603 583 565 547 530 515 550 1013 917 837 770 740 713 688 664 642 621 602 583 566 600 1105 1000 913 840 808 778 750 724 700 677 656 636 618 650 1197 1083 989 910 8...

Страница 388: ...414 404 394 384 375 366 358 350 335 321 309 450 486 473 461 449 438 427 417 407 398 389 372 357 343 500 535 520 507 494 481 470 458 448 438 428 410 393 377 550 583 568 553 538 525 512 500 488 477 467...

Страница 389: ...5 2052 1983 1919 1859 1803 1750 1750 3224 2917 2663 2450 2356 2269 2188 2112 2042 1976 1914 1856 1801 1800 3316 3000 2739 2520 2423 2333 2250 2172 2100 2032 1969 1909 1853 1850 3408 3083 2815 2590 249...

Страница 390: ...1322 1266 1214 1167 1700 1701 1655 1612 1571 1531 1494 1458 1424 1392 1361 1303 1250 1201 1750 1750 1703 1658 1615 1575 1537 1500 1465 1432 1400 1340 1286 1235 1800 1799 1750 1704 1660 1619 1579 1542...

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Страница 394: ...00 1952 1907 1864 1822 1783 1745 1708 1673 1640 1577 1519 1464 2050 2049 2000 1953 1909 1867 1826 1787 1750 1714 1680 1615 1556 1500 2100 2098 2048 2000 1955 1911 1870 1830 1792 1755 1720 1654 1593 15...

Страница 395: ...619 604 589 576 563 600 931 871 818 771 750 730 711 692 675 659 643 628 614 650 1009 944 886 836 813 791 770 750 731 713 696 680 665 700 1086 1016 955 900 875 851 829 808 788 768 750 733 716 750 1164...

Страница 396: ...538 527 516 505 495 485 476 467 458 450 434 419 406 550 587 574 563 551 540 529 519 509 500 491 474 458 443 600 636 622 609 597 585 574 563 552 542 532 513 496 480 650 685 670 656 643 630 618 606 594...

Страница 397: ...50 3181 2976 2795 2636 2563 2493 2428 2365 2306 2250 2196 2145 2097 2100 3259 3048 2864 2700 2625 2554 2487 2423 2363 2305 2250 2198 2148 2150 3336 3121 2932 2764 2688 2615 2546 2481 2419 2360 2304 22...

Страница 398: ...05 1963 1922 1883 1845 1809 1774 1741 1708 1677 1618 1564 1512 2050 2054 2011 1969 1929 1890 1853 1817 1783 1750 1718 1658 1602 1549 2100 2103 2059 2016 1974 1935 1897 1861 1825 1792 1759 1697 1640 15...

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Страница 400: ...section Holding fuel flows are tabulated in Holding Fuel Flow of this Sub section The climb procedures are defined in Sub section 3 CLIMB and descent procedures are defined in Sub section 5 NORMAL DE...

Страница 401: ...ECTOR TIME and FUEL HIGH SPEED PROCEDURE INTRODUCTION High Speed Procedure is defined as follows Normal Climb Cruise at VMO MMO or Maximum Cruise Thrust whichever is slower Normal Descent The Sector T...

Страница 402: ...51 1787 50 1658 400 71 2711 69 2612 66 2367 64 2187 500 88 3378 86 3255 82 2946 79 2717 600 104 4047 102 3899 97 3525 94 3246 700 121 4722 118 4548 113 4107 109 3776 800 138 5397 135 5197 128 4692 12...

Страница 403: ...475 75 2467 500 93 3122 91 3021 90 2951 88 2942 600 107 3629 105 3509 104 3427 102 3418 700 122 4139 120 3999 117 3903 116 3893 800 136 4652 134 4495 131 4386 129 4375 900 151 5166 148 4990 145 4870 1...

Страница 404: ...2644 67 2402 65 2224 500 88 3429 86 3296 82 2987 80 2759 600 105 4108 102 3951 98 3576 95 3297 700 122 4788 119 4605 113 4164 109 3836 800 138 5468 135 5259 129 4752 124 4376 900 155 6156 152 5918 14...

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Страница 461: ...CTOR TIME min FUEL lb TIME min FUEL lb TIME min FUEL lb AIR DIST nm 100 200 51 1462 52 1470 300 65 1822 66 1806 400 80 2179 80 2139 500 94 2540 95 2484 600 108 2900 110 2827 700 122 3260 124 3156 800...

Страница 462: ...IME 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 Normal Descent The S...

Страница 463: ...5 76 2116 72 1967 500 107 3224 100 2904 94 2626 89 2434 600 128 3860 120 3473 112 3136 106 2901 700 149 4510 139 4048 130 3646 123 3368 800 170 5160 159 4633 148 4164 140 3835 900 190 5809 178 5218 16...

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Страница 507: ...130 3878 131 3713 132 3571 1000 146 4305 143 4297 144 4111 145 3955 1100 160 4724 157 4716 158 4510 159 4338 1200 174 5144 171 5134 172 4909 173 4721 1300 188 5565 184 5553 185 5308 187 5104 1400 202...

Страница 508: ...3001 121 2894 800 132 3447 133 3347 136 3218 900 146 3818 147 3694 149 3558 1000 160 4188 161 4040 161 3895 1100 174 4558 175 4389 176 4217 1200 188 4928 189 4742 191 4550 1300 202 5298 203 5094 205 4...

Страница 509: ...53 90 2751 91 2665 92 2599 700 106 3180 104 3178 105 3075 105 2995 800 120 3608 117 3605 118 3485 119 3391 900 133 4043 131 4041 132 3900 133 3790 1000 147 4478 144 4477 146 4318 147 4196 1100 161 491...

Страница 510: ...0 64 1797 65 1756 66 1706 400 78 2169 79 2109 81 2038 500 92 2545 94 2463 96 2367 600 106 2925 108 2817 111 2688 700 120 3306 122 3198 125 3039 800 134 3687 135 3586 136 3486 900 148 4073 150 3949 100...

Страница 511: ...651 76 2388 72 2170 69 2021 500 101 3301 95 2972 89 2693 84 2503 600 120 3955 113 3555 106 3217 100 2984 700 140 4620 131 4146 123 3740 116 3466 800 160 5286 149 4744 140 4274 132 3948 900 179 5951 16...

Страница 512: ...2629 600 113 3344 111 3226 108 3118 105 3042 700 129 3806 126 3669 122 3543 119 3455 800 144 4276 141 4115 137 3969 133 3868 900 160 4750 156 4569 151 4405 147 4287 1000 175 5224 171 5024 166 4842 16...

Страница 513: ...101 3380 95 3041 89 2763 85 2573 600 121 4055 113 3648 106 3305 101 3066 700 140 4729 132 4255 123 3851 117 3567 800 160 5404 150 4862 140 4397 133 4067 900 180 6092 168 5470 157 4943 149 4568 1000 1...

Страница 514: ...9 3207 106 3134 700 130 3919 126 3777 123 3650 120 3566 800 145 4400 141 4238 138 4093 134 3998 900 161 4881 156 4700 152 4537 148 4430 1000 176 5361 171 5162 167 4980 162 4862 1100 191 5850 186 5625...

Страница 515: ...38 1144 300 62 2111 59 1907 56 1752 54 1647 400 82 2793 77 2521 73 2303 70 2151 500 101 3475 95 3135 90 2857 86 2661 600 121 4168 114 3753 107 3411 102 3170 700 141 4861 132 4377 124 3970 118 3682 800...

Страница 516: ...0 84 2574 82 2493 80 2423 79 2382 500 99 3062 97 2961 95 2874 93 2822 600 115 3550 112 3429 110 3324 107 3262 700 130 4045 127 3901 124 3777 121 3703 800 146 4540 142 4375 139 4233 135 4147 900 161 50...

Страница 517: ...73 115 3224 116 3099 900 130 3804 127 3774 128 3603 129 3458 1000 144 4213 141 4177 142 3981 143 3817 1100 157 4630 154 4590 155 4367 156 4176 1200 171 5048 167 5003 169 4760 170 4547 1300 184 5465 18...

Страница 518: ...1613 62 1565 63 1525 400 76 1951 76 1880 77 1816 500 89 2289 90 2194 91 2108 600 103 2626 103 2509 105 2401 700 116 2964 117 2826 119 2693 800 130 3301 131 3145 133 2990 900 143 3644 145 3464 147 3286...

Страница 519: ...942 129 3909 130 3759 131 3612 1000 145 4366 142 4327 143 4157 145 3989 1100 158 4791 156 4746 157 4555 159 4367 1200 172 5215 169 5164 170 4953 173 4744 1300 186 5641 182 5582 184 5351 186 5121 1400...

Страница 520: ...63 78 1999 79 1934 500 91 2412 92 2323 94 2232 600 105 2761 106 2648 108 2531 700 119 3113 121 2976 123 2831 800 133 3465 135 3310 137 3142 900 147 3816 148 3641 150 3464 1000 160 4169 162 3966 1100 1...

Страница 521: ...1 2761 92 2679 93 2603 700 105 3222 104 3183 105 3080 107 2985 800 119 3655 118 3606 119 3481 121 3368 900 132 4093 131 4031 133 3883 135 3750 1000 146 4531 145 4456 146 4288 149 4136 1100 160 4969 15...

Страница 522: ...ECTOR TIME min FUEL lb TIME min FUEL lb TIME min FUEL lb AIR DIST nm 100 200 51 1460 51 1462 300 65 1822 66 1806 400 80 2181 81 2146 500 94 2541 95 2486 600 108 2899 110 2823 700 122 3260 124 3156 800...

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Страница 524: ...HT 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 sl...

Страница 525: ...3609 174 3483 169 3381 164 3306 1100 197 3951 191 3811 185 3696 180 3613 1200 215 4308 208 4146 202 4012 196 3919 1300 232 4666 225 4489 218 4344 212 4237 1400 250 5023 242 4832 235 4675 228 4560 150...

Страница 526: ...74 160 3089 160 3010 1000 181 3465 176 3370 175 3282 1100 197 3757 191 3652 191 3554 1200 212 4048 207 3933 206 3826 1300 228 4358 222 4225 222 4112 1400 244 4668 238 4529 237 4414 1500 260 4978 253 4...

Страница 527: ...00 197 4150 192 4007 186 3898 180 3816 1200 215 4515 209 4359 202 4238 196 4149 1300 233 4880 226 4710 219 4578 212 4481 1400 250 5246 243 5061 235 4919 228 4814 1500 268 5616 260 5412 252 5259 244 51...

Страница 528: ...6 176 3623 176 3608 1100 197 4008 192 3944 192 3927 1200 213 4331 207 4264 207 4246 1300 229 4653 223 4585 223 4566 1400 245 4975 238 4905 238 4885 1500 261 5298 254 5225 254 5204 1600 277 5625 269 55...

Страница 529: ...7 2667 800 145 3211 141 3125 137 3056 133 3011 900 163 3587 158 3487 153 3407 149 3355 1000 180 3972 175 3857 170 3764 165 3704 1100 198 4357 192 4229 186 4126 181 4061 1200 215 4742 209 4602 203 4489...

Страница 530: ...15 2637 700 133 2960 130 2961 130 2978 800 149 3299 146 3301 146 3320 900 165 3639 161 3641 161 3675 1000 181 3994 177 3999 177 4032 1100 197 4349 192 4358 192 4389 1200 213 4705 208 4717 204 4749 130...

Страница 531: ...8 3623 172 3497 167 3408 162 3335 1100 195 3966 189 3826 183 3726 178 3645 1200 212 4324 206 4162 200 4045 193 3954 1300 230 4682 223 4507 216 4379 209 4276 1400 247 5040 239 4851 232 4713 225 4602 15...

Страница 532: ...99 158 3115 158 3040 1000 179 3492 174 3399 173 3314 1100 194 3786 189 3683 189 3589 1200 210 4081 204 3967 204 3863 1300 226 4393 220 4263 219 4158 1400 242 4706 235 4571 235 4460 1500 257 5019 250 4...

Страница 533: ...1100 195 4162 189 4028 184 3928 178 3853 1200 213 4528 206 4381 200 4271 194 4189 1300 230 4895 223 4735 216 4614 210 4525 1400 247 5261 240 5088 233 4957 226 4861 1500 265 5632 257 5442 249 5300 241...

Страница 534: ...9 174 3666 174 3637 1100 195 4045 190 3990 189 3958 1200 211 4370 205 4314 205 4280 1300 226 4696 220 4637 220 4602 1400 242 5022 236 4961 235 4924 1500 258 5348 251 5285 251 5249 1600 274 5682 266 56...

Страница 535: ...726 116 2694 800 143 3223 139 3141 135 3079 132 3043 900 161 3601 156 3504 152 3431 147 3392 1000 178 3987 173 3876 168 3791 163 3746 1100 196 4374 190 4249 184 4155 179 4107 1200 213 4760 207 4623 20...

Страница 536: ...647 113 2667 700 132 2996 129 2991 129 3011 800 148 3338 144 3334 144 3358 900 164 3683 160 3680 159 3716 1000 179 4041 175 4042 175 4075 1100 195 4399 190 4405 187 4435 1200 211 4757 206 4768 197 482...

Страница 537: ...4 3658 169 3539 164 3443 159 3367 1100 191 4005 185 3871 180 3764 174 3679 1200 208 4367 202 4212 196 4086 189 3990 1300 225 4729 218 4560 211 4422 205 4315 1400 242 5092 234 4909 227 4758 220 4645 15...

Страница 538: ...94 900 159 3246 155 3179 155 3070 1000 175 3543 170 3468 170 3345 1100 190 3840 185 3758 185 3633 1200 205 4141 200 4047 200 3933 1300 221 4459 215 4352 215 4233 1400 236 4778 230 4664 230 4533 1500 2...

Страница 539: ...100 191 4211 186 4074 180 3961 175 3898 1200 208 4581 202 4430 196 4306 190 4238 1300 225 4952 219 4786 212 4651 205 4577 1400 242 5323 235 5142 228 4996 221 4917 1500 259 5701 251 5499 244 5341 236 5...

Страница 540: ...00 175 3787 171 3728 170 3707 1100 191 4118 186 4058 185 4026 1200 206 4450 201 4387 200 4353 1300 222 4781 216 4716 215 4695 1400 237 5112 231 5046 230 5037 1500 252 5443 246 5375 245 5379 1600 268 5...

Страница 541: ...117 2751 114 2734 800 141 3259 137 3172 133 3107 129 3086 900 158 3641 153 3537 149 3463 145 3437 1000 175 4032 170 3912 165 3826 160 3794 1100 192 4422 186 4289 181 4194 175 4159 1200 209 4813 203 46...

Страница 542: ...79 600 114 2699 111 2703 111 2728 700 129 3045 126 3054 125 3081 800 145 3392 141 3406 136 3449 900 160 3743 156 3761 150 3813 1000 176 4106 171 4130 165 4191 1100 191 4470 186 4498 179 4568 1200 207...

Страница 543: ...000 171 3711 165 3594 160 3496 156 3433 1100 187 4063 182 3931 176 3821 171 3750 1200 204 4430 198 4277 192 4149 186 4068 1300 220 4797 214 4630 207 4491 201 4399 1400 237 5164 230 4982 223 4832 216 4...

Страница 544: ...2641 123 2574 800 141 3012 138 2932 137 2858 900 156 3314 152 3223 152 3151 1000 171 3617 167 3515 167 3445 1100 186 3920 182 3825 181 3739 1200 201 4227 196 4135 196 4032 1300 217 4549 211 4446 211 4...

Страница 545: ...6 3625 1100 188 4270 182 4135 177 4034 171 3969 1200 204 4644 198 4496 192 4385 186 4313 1300 221 5019 214 4858 208 4735 202 4657 1400 238 5394 230 5219 223 5086 217 5001 1500 254 5778 247 5581 239 54...

Страница 546: ...172 138 3153 900 157 3521 153 3497 153 3474 1000 172 3858 168 3821 165 3801 1100 187 4194 182 4146 175 4132 1200 202 4531 197 4483 189 4473 1300 217 4867 212 4827 203 4833 1400 232 5204 226 5171 217 5...

Страница 547: ...2812 112 2789 800 138 3310 134 3230 131 3174 127 3145 900 155 3696 150 3602 146 3535 142 3501 1000 171 4090 166 3983 162 3904 157 3864 1100 188 4484 183 4364 177 4276 172 4234 1200 205 4878 199 4745...

Страница 548: ...744 400 82 2073 81 2079 78 2093 500 97 2413 95 2423 92 2448 600 112 2767 110 2775 106 2797 700 127 3121 126 3115 123 3132 800 142 3475 145 3453 148 3434 900 157 3835 160 3810 164 3789 1000 173 4205 17...

Страница 549: ...000 167 3767 162 3655 158 3574 153 3514 1100 184 4124 178 3996 173 3905 168 3837 1200 200 4496 194 4349 188 4239 183 4160 1300 216 4867 210 4707 204 4587 197 4499 1400 233 5239 226 5065 219 4934 212 4...

Страница 550: ...400 80 1851 78 1830 78 1799 500 94 2157 92 2127 92 2085 600 109 2463 107 2424 107 2372 700 124 2769 121 2722 121 2660 800 139 3075 135 3030 135 2951 900 153 3381 150 3337 150 3243 1000 168 3699 164 36...

Страница 551: ...4 3729 1100 184 4339 179 4219 174 4127 169 4082 1200 201 4719 195 4586 189 4484 183 4435 1300 217 5099 210 4954 204 4840 198 4787 1400 233 5478 226 5321 219 5196 213 5140 1500 250 5870 242 5692 235 55...

Страница 552: ...00 95 2316 93 2300 91 2301 600 110 2638 108 2621 105 2628 700 125 2972 122 2947 118 2942 800 139 3306 138 3251 135 3229 900 154 3640 157 3526 160 3400 1000 169 3973 172 3833 1100 184 4314 187 4157 120...

Страница 553: ...116 2926 113 2891 110 2890 800 136 3372 132 3303 128 3258 125 3256 900 152 3765 148 3681 144 3626 140 3622 1000 168 4165 164 4068 159 4001 155 3996 1100 185 4564 179 4454 174 4380 169 4373 1200 201 49...

Страница 554: ...CTOR TIME min FUEL lb TIME min FUEL lb TIME min FUEL lb AIR DIST nm 100 200 51 1465 51 1472 300 66 1810 66 1804 400 81 2159 82 2144 500 96 2511 97 2493 600 109 2880 110 2857 700 122 3275 119 3306 800...

Страница 555: ...Page 2 190 Pilot s Operating Manual Original Issue Feb 2002 Sub section 2 PREFLIGHT Hawker 800XP Pro Line 21 Section IV FLIGHT PLANNING DATA Intentionally left blank...

Страница 556: ...hts for ISA conditions however they also may be used for other temperatures since the effect of temperature on diversion times and fuel is negligible Diversion times and fuels have been calculated usi...

Страница 557: ...48 49 1141 46 1070 240 61 1496 57 1355 53 1236 50 1157 260 66 1615 62 1462 58 1332 54 1244 280 71 1735 66 1569 62 1427 58 1331 300 76 1854 71 1675 66 1522 62 1418 320 81 1973 75 1782 70 1618 66 1505 3...

Страница 558: ...220 49 1124 48 1094 47 1065 46 1045 240 53 1207 52 1173 50 1140 49 1118 260 57 1290 55 1252 54 1215 53 1190 280 61 1373 59 1332 58 1291 56 1262 300 65 1456 63 1411 61 1366 60 1335 320 69 1539 67 1490...

Страница 559: ...57 1405 54 1289 51 1212 260 66 1668 62 1515 58 1387 55 1301 280 71 1790 66 1625 62 1486 59 1391 300 76 1913 71 1735 66 1584 63 1480 320 81 2035 76 1845 71 1682 67 1570 340 86 2158 80 1955 75 1780 71 1...

Страница 560: ...1107 240 53 1265 52 1231 51 1202 50 1182 260 57 1350 56 1313 54 1279 53 1256 280 61 1436 59 1395 58 1357 57 1331 300 65 1521 63 1477 62 1435 60 1406 320 69 1607 67 1558 65 1513 64 1480 340 73 1692 71...

Страница 561: ...57 1458 54 1337 51 1266 260 66 1729 62 1571 58 1438 55 1358 280 71 1856 67 1684 62 1539 59 1450 300 76 1984 71 1798 66 1640 63 1542 320 81 2112 76 1912 71 1741 67 1634 340 86 2240 80 2027 75 1842 71...

Страница 562: ...54 1324 52 1292 51 1264 50 1247 260 57 1412 56 1377 55 1345 53 1325 280 61 1500 60 1461 58 1425 57 1402 300 65 1588 64 1545 62 1505 60 1479 320 69 1676 67 1629 66 1585 64 1557 340 73 1764 71 1714 69...

Страница 563: ...Page 2 198 Pilot s Operating Manual Original Issue Feb 2002 Sub section 2 PREFLIGHT Hawker 800XP Pro Line 21 Section IV FLIGHT PLANNING DATA Intentionally left blank...

Страница 564: ...L 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...

Страница 565: ...6 1025 995 978 967 20 000 185 1236 1204 1153 1111 1068 1038 1022 1011 21 000 190 1288 1250 1197 1154 1111 1080 1065 1054 22 000 194 1339 1297 1243 1197 1156 1125 1109 1098 23 000 198 1387 1343 1287 12...

Страница 566: ...1182 1137 1103 1085 1072 20 000 185 1392 1356 1298 1251 1203 1169 1151 1138 21 000 190 1449 1406 1347 1298 1250 1215 1198 1186 22 000 194 1532 1484 1422 1369 1322 1287 1269 1256 23 000 198 1587 1536...

Страница 567: ...Page 2 202 Pilot s Operating Manual Original Issue Feb 2002 Sub section 2 PREFLIGHT Hawker 800XP Pro Line 21 Section IV FLIGHT PLANNING DATA Intentionally left blank...

Страница 568: ...s 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 C 3 14 ISA 20 C 3 16 OPTIMUM TIME TO HEIGHT CLIMB 3 18 ISA 15 C 3 18 ISA 10 C 3 20 ISA 3 22...

Страница 569: ...Page 3 2 Pilot s Operating Manual Original Issue Feb 2002 Sub section 3 CLIMB Hawker 800XP Pro Line 21 Section IV FLIGHT PLANNING DATA Intentionally left blank...

Страница 570: ...and accelerate to 250 KIAS at 5000 ft NORMAL CLIMB Reference the charts on pages 3 4 through 3 17 From 5000 ft the normal climb continues at 250 KIAS to 32 000 ft at which IMN 0 70 The final part of...

Страница 571: ...15 17 20 TIME 1 2 2 3 3 4 4 4 5 5 6 FUEL 75 117 157 186 213 239 266 293 320 348 376 23 000 DIST 0 2 4 6 8 9 11 13 16 18 21 TIME 1 2 2 3 3 4 4 5 5 5 6 FUEL 78 123 164 195 223 251 279 307 336 365 395 2...

Страница 572: ...436 468 502 539 580 616 657 705 765 FUEL 24 28 32 37 43 50 57 65 77 92 DIST 23 000 7 7 8 9 10 11 12 13 15 17 TIME 426 458 492 528 567 611 649 694 749 818 FUEL 25 29 34 39 45 53 60 70 82 100 DIST 24 0...

Страница 573: ...15 18 21 TIME 1 2 2 3 3 4 4 4 5 5 6 FUEL 75 118 158 188 216 243 270 298 326 355 384 23 000 DIST 0 2 4 6 8 10 12 14 16 19 22 TIME 1 2 3 3 3 4 4 5 5 6 6 FUEL 78 124 166 197 226 255 283 312 342 372 403 2...

Страница 574: ...447 480 516 555 599 636 678 729 791 FUEL 25 29 34 39 45 53 60 69 81 96 DIST 23 000 7 7 8 9 10 11 12 14 15 18 TIME 436 469 505 543 585 631 671 717 774 847 FUEL 26 31 35 41 48 56 64 73 86 105 DIST 24 0...

Страница 575: ...2 15 18 21 24 TIME 1 2 2 3 3 4 4 5 5 6 6 FUEL 75 120 162 193 223 252 281 312 342 374 407 23 000 DIST 0 2 4 6 8 11 13 16 19 22 26 TIME 1 2 3 3 3 4 4 5 6 6 7 FUEL 78 126 170 203 234 264 295 327 360 393...

Страница 576: ...TIME 442 478 516 558 603 654 699 752 816 899 FUEL 30 35 40 47 55 64 73 85 100 122 DIST 23 000 8 8 9 10 12 13 14 16 18 22 TIME 465 503 544 588 636 691 740 797 870 973 FUEL 32 37 43 49 58 68 78 91 108 1...

Страница 577: ...6 20 23 27 TIME 1 2 3 3 3 4 4 5 6 6 7 FUEL 75 122 166 199 230 260 292 324 356 390 425 23 000 DIST 0 2 5 7 9 12 14 17 21 24 29 TIME 1 2 3 3 4 4 5 5 6 7 7 FUEL 78 127 174 208 241 273 306 340 374 410 447...

Страница 578: ...TIME 462 501 542 588 639 697 748 808 883 988 FUEL 33 39 45 53 62 73 84 97 116 144 DIST 23 000 8 9 10 11 13 14 16 18 21 25 TIME 486 527 572 620 674 737 793 859 947 1080 FUEL 35 41 48 56 65 78 89 104 1...

Страница 579: ...22 26 30 TIME 1 2 3 3 4 4 5 5 6 7 8 FUEL 75 123 170 205 238 270 304 338 373 410 447 23 000 DIST 0 2 5 8 10 13 16 20 23 28 32 TIME 1 2 3 3 4 4 5 6 6 7 8 FUEL 78 129 178 215 250 284 319 356 393 431 471...

Страница 580: ...5 17 19 22 27 TIME 486 529 575 626 685 753 813 882 975 1116 FUEL 38 44 51 60 71 84 98 114 137 177 DIST 23 000 9 10 11 13 14 16 18 20 24 30 TIME 512 557 607 662 725 798 864 942 1052 1247 FUEL 40 46 54...

Страница 581: ...5 29 35 TIME 1 2 3 3 4 5 5 6 7 8 8 FUEL 75 125 174 211 247 282 318 355 393 433 474 23 000 DIST 0 2 6 9 11 15 18 22 26 31 37 TIME 1 2 3 3 4 5 5 6 7 8 9 FUEL 78 131 182 222 259 296 334 374 414 456 500 2...

Страница 582: ...9 11 12 13 15 18 20 23 27 34 TIME 518 565 617 678 750 837 915 1001 1121 FUEL 43 50 59 70 84 103 121 142 174 DIST 23 000 10 11 13 14 16 19 22 25 29 TIME 546 596 652 717 796 892 978 1076 1225 FUEL 45 5...

Страница 583: ...39 TIME 1 2 3 4 4 5 6 6 7 8 9 FUEL 75 128 179 219 257 295 334 374 416 459 505 23 000 DIST 0 3 6 10 13 16 20 25 30 35 42 TIME 1 2 3 4 4 5 6 7 8 9 10 FUEL 78 134 188 230 270 310 351 394 438 484 532 24...

Страница 584: ...205 DIST 22 000 10 12 13 15 18 21 24 28 34 TIME 553 607 667 738 827 943 1050 1170 1342 FUEL 49 58 68 82 100 127 152 183 232 DIST 23 000 11 12 14 16 19 23 26 31 38 TIME 584 641 706 783 881 1011 1134 1...

Страница 585: ...7 9 11 13 15 17 20 TIME 1 2 2 3 3 4 4 4 5 5 6 FUEL 75 117 157 186 213 239 266 293 320 348 376 23 000 DIST 0 2 4 6 8 9 11 13 16 18 21 TIME 1 2 2 3 3 4 4 5 5 5 6 FUEL 78 123 164 195 223 251 279 307 336...

Страница 586: ...2 13 15 TIME 405 436 468 497 525 554 586 624 670 728 FUEL 24 28 32 36 40 45 51 59 69 83 DIST 23 000 7 7 8 9 9 10 11 12 14 17 TIME 426 458 492 523 552 583 618 660 713 781 FUEL 25 29 33 38 42 48 54 63 7...

Страница 587: ...9 11 13 15 18 21 TIME 1 2 2 3 3 4 4 4 5 5 6 FUEL 75 118 158 188 216 243 270 298 326 355 384 23 000 DIST 0 2 4 6 8 10 12 14 16 19 22 TIME 1 2 2 3 3 4 4 5 5 6 6 FUEL 78 124 166 197 226 255 284 313 342...

Страница 588: ...14 16 TIME 415 447 480 511 540 570 603 643 691 750 FUEL 25 29 33 38 42 48 54 62 72 87 DIST 23 000 7 7 8 9 10 11 12 13 15 17 TIME 436 469 505 537 568 601 637 680 734 805 FUEL 26 31 35 40 45 50 57 66 7...

Страница 589: ...6 8 10 12 15 18 21 24 TIME 1 2 2 3 3 4 4 5 5 6 6 FUEL 75 120 162 193 223 252 282 312 343 375 408 23 000 DIST 0 2 4 6 8 11 13 16 19 22 26 TIME 1 2 3 3 3 4 4 5 5 6 7 FUEL 78 126 170 203 233 264 296 327...

Страница 590: ...18 TIME 442 478 516 551 584 619 657 701 756 826 FUEL 30 34 40 45 51 57 64 74 86 103 DIST 23 000 8 8 9 10 11 12 13 15 17 20 TIME 465 503 543 580 615 653 694 744 806 892 FUEL 31 36 42 48 54 60 68 79 93...

Страница 591: ...12 15 18 22 26 30 TIME 1 2 3 3 4 4 5 5 6 7 8 FUEL 75 123 169 204 237 270 303 337 372 408 445 23 000 DIST 0 2 5 8 10 13 16 19 23 27 32 TIME 1 2 3 3 4 4 5 6 6 7 8 FUEL 78 129 177 214 249 283 318 354 391...

Страница 592: ...4 15 17 19 23 TIME 484 526 571 614 654 696 742 797 868 969 FUEL 37 43 50 57 65 73 82 94 111 137 DIST 23 000 9 10 11 12 13 15 16 18 21 25 TIME 510 555 603 648 691 736 787 849 933 1064 FUEL 39 46 53 61...

Страница 593: ...17 21 25 30 35 TIME 1 2 3 3 4 5 5 6 7 8 8 FUEL 75 125 174 212 247 282 318 355 394 433 474 23 000 DIST 0 2 6 9 11 15 18 22 26 31 37 TIME 1 2 3 3 4 5 5 6 7 8 9 FUEL 78 131 183 222 260 297 335 374 415 45...

Страница 594: ...13 15 16 18 20 23 27 TIME 517 564 617 668 716 767 820 883 969 1106 FUEL 43 50 59 68 77 87 99 113 134 172 DIST 23 000 10 11 13 14 15 17 19 21 25 31 TIME 546 596 652 706 759 814 873 945 1049 1249 FUEL...

Страница 595: ...24 28 34 40 TIME 1 2 3 4 4 5 6 6 7 8 9 FUEL 75 128 179 219 257 295 334 375 417 460 505 23 000 DIST 0 3 6 10 13 16 20 25 30 36 42 TIME 1 2 3 4 4 5 6 7 8 9 10 FUEL 78 134 188 230 270 311 352 395 439 485...

Страница 596: ...0 10 12 13 15 17 19 21 23 27 33 TIME 554 607 668 728 786 847 912 988 1096 1299 FUEL 49 58 69 80 92 105 119 138 166 225 DIST 23 000 11 13 14 16 18 20 22 25 30 39 TIME 585 642 707 772 836 902 975 1065 1...

Страница 597: ...0 Pilot s Operating Manual Revision A1 Nov 2002 Sub section 3 CLIMB Hawker 800XP Pro Line 21 Section IV FLIGHT PLANNING DATA PRESSURE RATE OF CLIMB Normal Procedure Pressure Rate of Climb Antice Off F...

Страница 598: ...ft 4 8 13 000 ft 4 9 15 000 ft 4 10 17 000 ft 4 11 19 000 ft 4 12 21 000 ft 4 13 23 000 ft 4 14 25 000 ft 4 15 27 000 ft 4 16 29 000 ft 4 17 31 000 ft 4 18 33 000 ft 4 19 35 000 ft 4 20 37 000 ft 4 21...

Страница 599: ...00 ft 4 41 LONG RANGE CRUISE 4 43 230 KIAS 4 43 33 000 ft 4 45 35 000 ft 4 46 37 000 ft 4 47 39 000 ft 4 48 41 000 ft 4 49 CRUISE AIR MILES per lb of FUEL 4 51 Figure 1 20 000 ft ISA 4 51 Figure 2 25...

Страница 600: ...o ISA 20 C for three procedures High speed Cruise VMO MMO Maximum Cruise Thrust Intermediate Cruise 280 KIAS 0 75 IMN Long Range Cruise 230 220 KIAS 0 70 IMN Graphical charts of nautical air miles per...

Страница 601: ...Page 4 4 Pilot s Operating Manual Original Issue Feb 2002 Sub section 4 CRUISE ENROUTE Hawker 800XP Pro Line 21 Section IV FLIGHT PLANNING DATA Intentionally left blank...

Страница 602: ...1872 1896 1919 1942 1965 1989 KIAS 280 280 280 280 280 280 280 280 KTAS 288 290 293 296 298 301 304 306 22 000 TOTAL FUEL FLOW lb hr 1852 1875 1900 1923 1947 1971 1994 2018 KIAS 280 280 280 280 280 28...

Страница 603: ...843 1866 1890 1913 1937 1960 KIAS 280 280 280 280 280 280 280 280 KTAS 296 299 301 304 307 310 312 315 22 000 TOTAL FUEL FLOW lb hr 1825 1847 1871 1895 1918 1942 1966 1990 KIAS 280 280 280 280 280 280...

Страница 604: ...2458 2489 2520 2550 2580 KIAS 335 335 335 335 335 335 335 335 KTAS 363 366 370 373 377 380 384 387 22 000 TOTAL FUEL FLOW lb hr 2382 2413 2445 2476 2508 2538 2569 2599 KIAS 335 335 335 335 335 335 335...

Страница 605: ...39 2470 2500 2531 2561 KIAS 335 335 335 335 335 335 335 335 KTAS 373 377 381 384 388 391 395 398 22 000 TOTAL FUEL FLOW lb hr 2358 2389 2423 2455 2487 2516 2547 2578 KIAS 335 335 335 335 335 335 335 3...

Страница 606: ...2 2432 2463 2493 2524 KIAS 334 334 334 334 334 334 334 334 KTAS 382 386 390 394 398 401 405 409 22 000 TOTAL FUEL FLOW lb hr 2319 2350 2384 2417 2449 2478 2509 2540 KIAS 334 334 334 334 334 334 334 33...

Страница 607: ...2342 2372 2402 2433 2464 KIAS 331 331 331 331 331 331 331 331 KTAS 391 395 399 402 406 410 414 418 22 000 TOTAL FUEL FLOW lb hr 2260 2291 2324 2356 2386 2417 2448 2479 KIAS 331 331 331 331 331 331 331...

Страница 608: ...283 2313 2343 2373 2405 KIAS 328 328 328 328 328 328 328 328 KTAS 399 403 407 411 415 419 423 427 22 000 TOTAL FUEL FLOW lb hr 2204 2234 2266 2297 2327 2358 2389 2420 KIAS 328 328 328 328 328 328 328...

Страница 609: ...2228 2260 2288 2319 2349 KIAS 325 325 325 325 325 325 325 325 KTAS 407 411 415 420 424 428 432 436 22 000 TOTAL FUEL FLOW lb hr 2151 2182 2213 2243 2275 2303 2334 2365 KIAS 325 325 325 325 325 325 325...

Страница 610: ...2180 2210 2239 2271 2301 KIAS 322 322 322 322 322 322 322 322 KTAS 416 420 424 429 433 437 442 446 22 000 TOTAL FUEL FLOW lb hr 2104 2137 2167 2196 2226 2255 2289 2319 KIAS 322 322 322 322 322 322 32...

Страница 611: ...114 2143 2171 2204 2235 2264 KIAS 319 319 319 319 319 319 319 319 KTAS 424 429 433 438 442 447 451 456 22 000 TOTAL FUEL FLOW lb hr 2071 2102 2132 2160 2190 2223 2254 2283 KIAS 319 319 319 319 319 319...

Страница 612: ...2134 2167 2196 2224 2226 KIAS 316 316 316 316 316 316 316 314 KTAS 433 438 443 448 452 457 462 463 22 000 TOTAL FUEL FLOW lb hr 2063 2091 2118 2155 2188 2216 2244 2224 KIAS 316 316 316 316 316 316 31...

Страница 613: ...2186 2216 2241 2226 2110 KIAS 313 313 313 313 313 313 311 305 KTAS 443 448 452 457 462 467 468 463 22 000 TOTAL FUEL FLOW lb hr 2100 2138 2175 2209 2238 2268 2224 2107 KIAS 313 313 313 313 313 313 31...

Страница 614: ...8 2371 2296 2198 2097 1990 KIAS 308 308 308 308 306 303 299 294 KTAS 450 455 461 465 466 466 466 461 22 000 TOTAL FUEL FLOW lb hr 2296 2337 2373 2391 2293 2194 2094 1986 KIAS 308 308 308 308 305 302 2...

Страница 615: ...7 2232 2152 2059 1967 1869 KIAS 296 296 296 296 293 290 287 282 KTAS 447 452 457 461 462 462 462 458 22 000 TOTAL FUEL FLOW lb hr 2188 2223 2265 2248 2148 2054 1963 1863 KIAS 296 296 296 295 292 289 2...

Страница 616: ...59 2098 2013 1922 1839 1748 KIAS 283 283 283 283 280 277 274 270 KTAS 443 448 453 456 457 457 457 452 22 000 TOTAL FUEL FLOW lb hr 2057 2093 2128 2106 2008 1917 1833 1740 KIAS 283 283 283 282 279 276...

Страница 617: ...TOTAL FUEL FLOW lb hr 1874 1911 1941 1973 1870 1783 1706 1622 KIAS 270 270 270 270 267 264 261 256 KTAS 439 444 449 452 452 452 451 445 22 000 TOTAL FUEL FLOW lb hr 1959 1990 2026 1969 1865 1777 1699...

Страница 618: ...20 000 TOTAL FUEL FLOW lb hr 1802 1830 1867 1829 1726 1640 1569 1489 KIAS 258 258 258 257 254 251 248 242 KTAS 436 441 445 447 447 447 443 437 22 000 TOTAL FUEL FLOW lb hr 1882 1916 1877 1824 1721 163...

Страница 619: ...0 KTAS 436 442 444 446 446 445 442 435 20 000 TOTAL FUEL FLOW lb hr 1733 1767 1703 1649 1556 1477 1410 1339 KIAS 247 247 245 243 240 237 232 225 KTAS 434 438 440 441 440 437 431 421 22 000 TOTAL FUEL...

Страница 620: ...2 443 445 445 444 440 432 TOTAL FUEL FLOW lb hr 1579 1609 1541 1483 1405 1335 1273 1207 KIAS 235 235 233 231 228 225 220 213 KTAS 433 438 439 440 437 435 428 416 20 000 TOTAL FUEL FLOW lb hr 1586 1598...

Страница 621: ...Page 4 24 Pilot s Operating Manual Original Issue Feb 2002 Sub section 4 CRUISE ENROUTE Hawker 800XP Pro Line 21 Section IV FLIGHT PLANNING DATA Intentionally left blank...

Страница 622: ...TAL FUEL FLOW lb hr 1768 1790 1813 1837 1860 1884 1907 1930 KIAS 280 280 280 280 280 280 280 280 KTAS 304 307 310 313 316 319 322 324 22 000 TOTAL FUEL FLOW lb hr 1796 1818 1842 1865 1889 1913 1936 19...

Страница 623: ...AL FUEL FLOW lb hr 1741 1763 1786 1810 1833 1856 1879 1902 KIAS 280 280 280 280 280 280 280 280 KTAS 313 316 319 322 325 328 331 334 22 000 TOTAL FUEL FLOW lb hr 1768 1791 1815 1839 1862 1886 1909 193...

Страница 624: ...TAL FUEL FLOW lb hr 1715 1737 1761 1785 1808 1831 1854 1878 KIAS 280 280 280 280 280 280 280 280 KTAS 322 326 329 332 335 338 341 344 22 000 TOTAL FUEL FLOW lb hr 1743 1766 1790 1814 1838 1861 1885 19...

Страница 625: ...TAL FUEL FLOW lb hr 1689 1712 1736 1760 1783 1806 1830 1854 KIAS 280 280 280 280 280 280 280 280 KTAS 332 336 339 342 346 349 352 355 22 000 TOTAL FUEL FLOW lb hr 1718 1741 1765 1789 1813 1837 1861 18...

Страница 626: ...TAL FUEL FLOW lb hr 1665 1689 1713 1736 1760 1784 1807 1831 KIAS 280 280 280 280 280 280 280 280 KTAS 342 346 349 353 356 359 363 366 22 000 TOTAL FUEL FLOW lb hr 1694 1718 1742 1766 1790 1815 1839 18...

Страница 627: ...OTAL FUEL FLOW lb hr 1641 1664 1689 1712 1736 1760 1784 1807 KIAS 280 280 280 280 280 280 280 280 KTAS 353 356 360 364 367 371 374 378 22 000 TOTAL FUEL FLOW lb hr 1670 1694 1719 1743 1767 1792 1816 1...

Страница 628: ...OTAL FUEL FLOW lb hr 1617 1641 1667 1690 1714 1738 1762 1786 KIAS 280 280 280 280 280 280 280 280 KTAS 363 367 371 375 379 383 386 390 22 000 TOTAL FUEL FLOW lb hr 1644 1669 1695 1719 1743 1767 1792 1...

Страница 629: ...TOTAL FUEL FLOW lb hr 1596 1620 1646 1669 1692 1716 1741 1766 KIAS 280 280 280 280 280 280 280 280 KTAS 375 379 383 387 391 395 399 402 22 000 TOTAL FUEL FLOW lb hr 1623 1647 1673 1697 1720 1745 1769...

Страница 630: ...TOTAL FUEL FLOW lb hr 1581 1605 1630 1653 1676 1701 1725 1750 KIAS 280 280 280 280 280 280 280 280 KTAS 387 391 395 399 404 408 412 416 22 000 TOTAL FUEL FLOW lb hr 1609 1633 1658 1681 1706 1730 1754...

Страница 631: ...TOTAL FUEL FLOW lb hr 1579 1604 1628 1654 1679 1703 1728 1752 KIAS 280 280 280 280 280 280 280 280 KTAS 399 403 408 412 417 421 425 430 22 000 TOTAL FUEL FLOW lb hr 1608 1632 1658 1685 1709 1733 1760...

Страница 632: ...TOTAL FUEL FLOW lb hr 1588 1615 1642 1667 1691 1717 1748 1775 KIAS 280 280 280 280 280 280 280 280 KTAS 412 416 421 426 430 435 439 444 22 000 TOTAL FUEL FLOW lb hr 1620 1648 1675 1699 1722 1753 1783...

Страница 633: ...TOTAL FUEL FLOW lb hr 1619 1641 1665 1686 1722 1754 1782 1805 KIAS 279 279 279 279 279 279 279 279 KTAS 423 428 432 437 442 447 452 456 22 000 TOTAL FUEL FLOW lb hr 1655 1677 1699 1728 1763 1794 1821...

Страница 634: ...TOTAL FUEL FLOW lb hr 1511 1532 1554 1574 1606 1638 1668 1693 KIAS 267 267 267 267 267 267 267 267 KTAS 419 424 429 434 438 443 448 453 22 000 TOTAL FUEL FLOW lb hr 1554 1574 1595 1622 1655 1687 1714...

Страница 635: ...TOTAL FUEL FLOW lb hr 1409 1434 1454 1476 1507 1540 1570 1596 KIAS 254 254 254 254 254 254 254 254 KTAS 415 420 425 430 435 440 444 445 22 000 TOTAL FUEL FLOW lb hr 1455 1479 1499 1528 1559 1592 1620...

Страница 636: ...20 000 TOTAL FUEL FLOW lb hr 1319 1346 1365 1391 1421 1453 1479 1489 KIAS 243 243 243 243 243 243 243 242 KTAS 413 418 423 428 433 437 442 437 22 000 TOTAL FUEL FLOW lb hr 1374 1400 1424 1453 1484 15...

Страница 637: ...30 KTAS 413 418 423 428 433 437 441 435 20 000 TOTAL FUEL FLOW lb hr 1251 1275 1300 1327 1356 1385 1410 1338 KIAS 232 232 232 232 232 232 232 225 KTAS 413 418 423 428 433 437 431 421 22 000 TOTAL FUEL...

Страница 638: ...hr 1149 1168 1196 1224 1247 1269 1273 1207 KIAS 221 221 221 221 221 221 220 213 KTAS 413 418 423 428 433 435 428 416 20 000 TOTAL FUEL FLOW lb hr 1215 1243 1271 1302 1332 1321 1258 1191 KIAS 221 221...

Страница 639: ...Page 4 42 Pilot s Operating Manual Original Issue Feb 2002 Sub section 4 CRUISE ENROUTE Hawker 800XP Pro Line 21 Section IV FLIGHT PLANNING DATA Intentionally left blank...

Страница 640: ...25 000 KTAS 320 324 327 331 334 338 341 344 TOTAL FUEL FLOW lb hr 1224 1240 1258 1276 1294 1313 1333 1353 23 000 KTAS 310 314 317 320 323 327 330 333 TOTAL FUEL FLOW lb hr 1245 1261 1279 1297 1315 13...

Страница 641: ...1497 9000 KTAS 251 253 256 258 260 263 265 267 TOTAL FUEL FLOW lb hr 1400 1415 1431 1448 1466 1484 1503 1522 7000 KTAS 243 246 248 250 253 255 257 259 TOTAL FUEL FLOW lb hr 1421 1437 1453 1471 1489 1...

Страница 642: ...TOTAL FUEL FLOW lb hr 1147 1170 1187 1204 1224 1246 1268 1289 KIAS 230 230 230 230 230 230 230 230 KTAS 365 369 374 378 382 386 390 395 22 000 TOTAL FUEL FLOW lb hr 1182 1204 1221 1238 1259 1283 1305...

Страница 643: ...TOTAL FUEL FLOW lb hr 1154 1178 1196 1213 1238 1259 1281 1303 KIAS 230 230 230 230 230 230 230 230 KTAS 378 382 387 391 396 400 405 409 22 000 TOTAL FUEL FLOW lb hr 1190 1214 1235 1255 1278 1298 1320...

Страница 644: ...20 000 TOTAL FUEL FLOW lb hr 1091 1111 1132 1154 1175 1194 1213 1240 KIAS 220 220 220 220 220 220 220 220 KTAS 376 381 385 390 394 399 403 407 22 000 TOTAL FUEL FLOW lb hr 1132 1154 1182 1203 1222 124...

Страница 645: ...7 KTAS 387 392 397 402 406 411 415 420 20 000 TOTAL FUEL FLOW lb hr 1083 1111 1136 1154 1172 1198 1225 1248 KIAS 217 217 217 217 217 217 217 217 KTAS 387 392 397 402 406 411 415 420 22 000 TOTAL FUEL...

Страница 646: ...147 KIAS 207 207 207 207 207 207 207 207 KTAS 388 392 397 402 406 411 415 416 20 000 TOTAL FUEL FLOW lb hr 1062 1083 1101 1118 1146 1169 1188 1192 KIAS 207 207 207 207 207 207 207 205 KTAS 388 392 397...

Страница 647: ...Page 4 50 Pilot s Operating Manual Original Issue Feb 2002 Sub section 4 CRUISE ENROUTE Hawker 800XP Pro Line 21 Section IV FLIGHT PLANNING DATA Intentionally left blank...

Страница 648: ...s Operating Manual Original Issue Feb 2002 Sub section 4 CRUISE ENROUTE 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 FUE...

Страница 649: ...s Operating Manual Original Issue Feb 2002 Sub section 4 CRUISE ENROUTE 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 FUE...

Страница 650: ...s Operating Manual Original Issue Feb 2002 Sub section 4 CRUISE ENROUTE 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 FUE...

Страница 651: ...s Operating Manual Original Issue Feb 2002 Sub section 4 CRUISE ENROUTE 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 FUE...

Страница 652: ...s Operating Manual Original Issue Feb 2002 Sub section 4 CRUISE ENROUTE 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 FUE...

Страница 653: ...s Operating Manual Original Issue Feb 2002 Sub section 4 CRUISE ENROUTE 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 FUE...

Страница 654: ...s Operating Manual Original Issue Feb 2002 Sub section 4 CRUISE ENROUTE 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 FUE...

Страница 655: ...s Operating Manual Original Issue Feb 2002 Sub section 4 CRUISE ENROUTE 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 FUE...

Страница 656: ...40 4350 4440 4570 4660 4730 4790 4870 4970 5030 5110 5260 1200 1280 1360 1440 1520 1600 1680 1760 1840 1920 2000 4560 4670 4760 4910 5000 5080 5140 5220 5320 5390 5480 5630 1275 1360 1445 1530 1615 17...

Страница 657: ...Section IV FLIGHT PLANNING DATA Page 4 60 Pilot s Operating Manual Original Issue Feb 2002 Sub section 4 CRUISE ENROUTE Hawker 800XP Pro Line 21 Intentionally left blank...

Страница 658: ...Page 5 1 Pilot s Operating Manual Original Issue Feb 2002 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...

Страница 659: ...Page 5 2 Pilot s Operating Manual Original Issue Feb 2002 Sub section 5 NORMAL DESCENT Hawker 800XP Pro Line 21 Section IV FLIGHT PLANNING DATA Intentionally left blank...

Страница 660: ...e 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 idl...

Страница 661: ...2 4 5 6 7 8 8 9 9 10 FUEL 0 19 35 43 51 60 67 72 77 82 87 21 000 DIST 0 6 14 18 22 27 32 35 39 43 47 TIME 0 2 4 5 6 7 8 8 9 10 10 FUEL 0 19 36 44 52 61 68 73 79 84 89 22 000 DIST 0 6 14 18 22 28 32 3...

Страница 662: ...TIME 92 97 102 107 111 114 118 123 158 191 FUEL 51 55 59 63 67 70 73 77 92 106 DIST 21 000 11 12 12 13 13 14 14 15 17 19 TIME 94 99 104 109 114 117 122 126 162 196 FUEL 52 56 61 65 69 72 76 80 94 109...

Страница 663: ...Page 5 6 Pilot s Operating Manual Original Issue Feb 2002 Sub section 5 NORMAL DESCENT Hawker 800XP Pro Line 21 Section IV FLIGHT PLANNING DATA Intentionally left blank...

Страница 664: ...NE MINIMUM CRUISE SPEED and MAXIMUM CRUISE ALTITUDE 6 5 SINGLE ENGINE MAXIMUM CRUISE WEIGHT 6 6 SINGLE ENGINE LONG RANGE CRUISE SPEED 6 6 SUMMARY of SINGLE ENGINE CEILINGS 6 7 OBSTACLE CLEARANCE 6 8 R...

Страница 665: ...Sep 2010 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...

Страница 666: ...ince they do not contain any margin they must not be used for checking obstacle clearance Where obstacle clearance after engine failure is relevant it should be checked using the en route net gradient...

Страница 667: ...an instantaneous loss of height from two engine to single engine altitude If in the particular case it is practicable to do the gradual drift down mentioned above there will be a savings of approxima...

Страница 668: ...000 210 25 800 25 200 23 900 22 500 21 400 20 300 18 800 16 700 25 000 206 26 800 26 200 25 100 23 700 22 500 21 600 20 100 18 300 24 000 202 27 800 27 400 26 300 25 000 23 800 22 800 21 400 19 900 23...

Страница 669: ...00 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 22 700 22 500 21 700 20 900 19 800 18 900 1...

Страница 670: ...00 23 850 21 550 18 800 EN ROUTE CLIMB 1 1 172 OFF 22 700 19 450 17 200 13 750 MINIMUM CRUISE 202 OFF 27 800 25 000 22 800 19 900 LONG RANGE CRUISE 230 OFF 25 500 21 400 19 200 14 800 LONG RANGE CRUIS...

Страница 671: ...700 11 500 9800 8100 5800 24 000 23 000 22 000 21 000 19 700 18 300 16 800 15 200 13 400 17 500 16 300 15 100 13 800 12 500 11 000 9300 7300 23 000 24 200 23 200 22 100 21 000 19 700 18 200 16 700 14...

Страница 672: ...Page 6 9 Pilot s Operating Manual P N 140 590032 0007 Revision A4 Sep 2010 Section IV Sub section 6 SINGLE ENGINE RANGE AFTER ENGINE FAILURE Figure 1 Range After Engine Failure...

Страница 673: ...t 31 510 31 150 30 280 29 390 28 470 27 560 26 640 25 720 37 000 CONSTANT KIAS 185 189 194 198 202 206 210 214 IOAT AT START C 62 62 61 61 60 60 60 59 TIME min 35 36 38 41 43 44 46 47 DISTANCE nm 172...

Страница 674: ...USED lb 165 355 485 580 660 735 805 FINAL ALTITUDE ft 30 820 30 070 29 210 28 320 27 430 26 520 25 610 29 000 CONSTANT KIAS 198 202 206 210 214 IOAT AT START C 49 49 49 48 48 TIME min 7 21 27 31 35 DI...

Страница 675: ...t 31 410 31 060 30 190 29 230 28 220 27 190 26 160 25 120 37 000 CONSTANT KIAS 185 189 194 198 202 206 210 214 IOAT AT START C 57 56 56 56 55 55 54 54 TIME min 35 37 38 42 45 47 49 51 DISTANCE nm 176...

Страница 676: ...5 380 525 635 725 815 895 FINAL ALTITUDE ft 30 960 30 750 29 980 29 040 28 050 27 050 26 030 25 010 29 000 CONSTANT KIAS 198 202 206 210 214 IOAT AT START C 44 44 44 43 43 TIME min 12 24 30 35 39 DIST...

Страница 677: ...27 380 26 100 24 820 23 590 22 440 37 000 CONSTANT KIAS 185 189 194 198 202 206 210 214 IOAT AT START C 46 46 45 45 45 44 44 43 TIME min 44 44 48 51 53 56 58 59 DISTANCE nm 222 223 245 261 275 288 299...

Страница 678: ...1065 FINAL ALTITUDE ft 29 750 29 560 28 420 27 190 25 940 24 680 23 470 22 330 29 000 CONSTANT KIAS 194 198 202 206 210 214 IOAT AT START C 34 34 33 33 33 32 TIME min 22 31 37 42 45 48 DISTANCE nm 10...

Страница 679: ...S 185 189 194 198 202 206 210 214 IOAT AT START C 36 35 35 35 34 34 33 33 TIME min 49 51 53 56 58 61 64 66 DISTANCE nm 246 258 270 283 298 313 328 342 FUEL USED lb 790 850 910 980 1060 1140 1225 1310...

Страница 680: ...8 202 206 210 214 IOAT AT START C 25 24 24 23 23 23 22 22 TIME min 23 32 37 42 46 50 53 57 DISTANCE nm 112 154 183 207 228 248 265 284 FUEL USED lb 400 555 670 775 875 975 1065 1165 FINAL ALTITUDE ft...

Страница 681: ...25 24 24 23 TIME min 56 59 61 64 67 DISTANCE nm 278 291 306 321 338 FUEL USED lb 875 955 1030 1115 1205 FINAL ALTITUDE ft 26 580 24 580 23 430 22 250 21 030 35 000 CONSTANT KIAS 185 189 194 198 202 2...

Страница 682: ...14 14 13 13 13 12 12 12 TIME min 37 44 49 52 56 61 66 72 DISTANCE nm 179 213 235 255 276 299 326 352 FUEL USED lb 620 760 855 955 1055 1175 1320 1470 FINAL ALTITUDE ft 26 340 24 430 23 280 22 110 20 9...

Страница 683: ...00 200 200 200 KTAS 236 238 241 243 245 247 250 252 20 000 TOTAL FUEL FLOW lb hr 1070 1086 1101 1116 1131 1145 1159 1173 KIAS 210 210 210 210 210 210 210 210 KTAS 247 250 252 254 257 259 261 264 22 00...

Страница 684: ...255 257 260 20 000 TOTAL FUEL FLOW lb hr 1062 1078 1093 1108 1123 1137 1151 1166 KIAS 210 210 210 210 210 210 210 210 KTAS 254 257 260 262 265 267 269 272 22 000 TOTAL FUEL FLOW lb hr 1163 1180 1196 1...

Страница 685: ...63 266 268 20 000 TOTAL FUEL FLOW lb hr 1053 1069 1084 1098 1113 1127 1142 1157 KIAS 210 210 210 210 210 210 210 210 KTAS 262 265 268 270 273 276 278 281 22 000 TOTAL FUEL FLOW lb hr 1153 1170 1185 12...

Страница 686: ...6 269 271 274 276 20 000 TOTAL FUEL FLOW lb hr 1044 1059 1075 1089 1103 1118 1134 1149 KIAS 210 210 210 210 210 210 210 210 KTAS 270 273 276 279 281 284 287 289 22 000 TOTAL FUEL FLOW lb hr 1146 1162...

Страница 687: ...272 275 278 280 283 286 20 000 TOTAL FUEL FLOW lb hr 1038 1053 1068 1081 1095 1114 1129 1144 KIAS 210 210 210 210 210 210 210 210 KTAS 279 282 285 288 290 293 296 298 22 000 TOTAL FUEL FLOW lb hr 114...

Страница 688: ...0 KTAS 275 278 281 284 287 289 292 295 20 000 TOTAL FUEL FLOW lb hr 1037 1050 1064 1081 1098 1115 1129 1144 KIAS 210 210 210 210 210 210 210 210 KTAS 288 291 294 297 300 303 303 292 22 000 TOTAL FUEL...

Страница 689: ...AS 200 200 200 200 200 200 200 200 KTAS 284 287 290 293 296 299 302 297 20 000 TOTAL FUEL FLOW lb hr 1043 1059 1076 1095 1111 1128 1147 1122 KIAS 210 210 210 210 210 210 210 205 KTAS 297 300 304 307 3...

Страница 690: ...991 1008 1023 1042 1056 KIAS 200 200 200 200 200 200 200 200 KTAS 294 297 300 303 306 308 296 280 20 000 TOTAL FUEL FLOW lb hr 1065 1082 1101 1121 1138 1146 1096 1044 KIAS 210 210 210 210 210 209 199...

Страница 691: ...305 298 285 TOTAL FUEL FLOW lb hr 966 983 1003 1022 1041 1060 1030 983 KIAS 200 200 200 200 200 200 193 183 KTAS 303 306 310 313 305 292 20 000 TOTAL FUEL FLOW lb hr 1082 1103 1117 1139 1109 1069 KIAS...

Страница 692: ...000 175 974 952 923 903 890 890 917 19 000 180 1022 1000 970 951 941 943 979 20 000 185 1071 1048 1017 1000 993 999 1045 21 000 190 1118 1094 1064 1048 1043 1055 22 000 194 1165 1141 1112 1099 1096 1...

Страница 693: ...233 269 296 20 000 DIST 0 11 29 44 55 66 74 TIME 0 2 5 7 9 10 12 FUEL 0 53 132 191 236 273 301 21 000 DIST 0 11 29 44 56 67 76 TIME 0 2 5 7 9 11 12 FUEL 0 53 133 193 239 276 305 22 000 DIST 0 11 30 44...

Страница 694: ...IST 20 000 13 14 15 17 18 20 22 23 TIME 325 351 377 404 429 453 476 495 FUEL 83 92 102 112 122 133 144 154 DIST 21 000 13 14 16 17 19 20 22 23 TIME 330 356 383 409 434 459 481 500 FUEL 85 94 103 113 1...

Страница 695: ...315 346 1990 308 340 1915 300 333 1831 291 325 1753 282 317 1669 272 308 1590 261 22 000 KTAS TOTAL FUEL FLOW lb hr KIAS 344 2017 313 348 2045 313 344 1988 306 338 1912 298 330 1829 288 322 1750 279 3...

Страница 696: ...311 346 1936 304 340 1862 296 333 1782 287 326 1706 278 317 1625 268 308 1549 257 22 000 KTAS TOTAL FUEL FLOW lb hr KIAS 346 1988 310 349 2004 309 343 1934 302 337 1859 293 330 1780 284 322 1703 275 3...

Страница 697: ...303 345 1826 294 339 1755 286 332 1682 278 325 1611 269 316 1536 259 307 1464 249 22 000 KTAS TOTAL FUEL FLOW lb hr KIAS 351 1936 306 349 1900 301 343 1824 292 336 1752 283 329 1679 274 321 1608 265 3...

Страница 698: ...293 344 1715 284 337 1646 276 331 1580 268 323 1515 259 315 1446 250 306 1378 240 22 000 KTAS TOTAL FUEL FLOW lb hr KIAS 354 1863 299 348 1787 290 340 1711 281 333 1642 273 326 1576 264 319 1511 255 3...

Страница 699: ...283 342 1617 274 336 1551 266 330 1498 259 324 1445 251 316 1383 243 307 1318 234 22 000 KTAS TOTAL FUEL FLOW lb hr KIAS 352 1753 288 346 1686 280 338 1613 271 331 1547 262 325 1493 255 319 1441 247 3...

Страница 700: ...7 1586 273 340 1519 264 333 1454 255 328 1412 249 323 1371 243 316 1314 235 308 1258 227 22 000 KTAS TOTAL FUEL FLOW lb hr KIAS 349 1649 277 343 1583 269 335 1514 260 328 1449 251 323 1408 245 318 136...

Страница 701: ...270 345 1498 262 337 1428 253 330 1369 245 326 1332 239 321 1298 234 314 1245 226 307 1193 219 22 000 KTAS TOTAL FUEL FLOW lb hr KIAS 345 1550 266 340 1493 258 332 1424 249 324 1365 241 320 1328 235...

Страница 702: ...EL FLOW lb hr KIAS 347 1465 259 342 1418 252 334 1352 243 327 1296 235 323 1260 230 318 1226 224 311 1175 216 303 1125 208 22 000 KTAS TOTAL FUEL FLOW lb hr KIAS 341 1458 254 337 1412 248 329 1347 239...

Страница 703: ...05 1058 203 20 000 KTAS TOTAL FUEL FLOW lb hr KIAS 343 1370 247 339 1334 241 332 1276 233 324 1223 225 319 1186 219 314 1153 213 304 1101 204 292 1051 194 22 000 KTAS TOTAL FUEL FLOW lb hr KIAS 337 13...

Страница 704: ...321 1121 213 315 1086 207 305 1035 198 295 989 189 20 000 KTAS TOTAL FUEL FLOW lb hr KIAS 336 1264 234 335 1245 230 328 1199 223 321 1158 216 312 1115 207 304 1079 199 288 1024 186 22 000 KTAS TOTAL F...

Страница 705: ...Page 6 42 Section IV Sub section 6 SINGLE ENGINE P N 140 590032 0007 Revision A4 Sep 2010 Pilot s Operating Manual Intentionally left blank...

Страница 706: ...al Original Issue Feb 2002 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 Unfactore...

Страница 707: ...Page 7 2 Pilot s Operating Manual Original Issue Feb 2002 Sub section 7 UNFACTORED LANDING Hawker 800XP Pro Line 21 Section IV FLIGHT PLANNING DATA Intentionally left blank...

Страница 708: ...ow operation to 14 CFR Part 121 standards and where a lower standard of safety is acceptable to the operator and to the Airworthiness Authority Figure 1 shows the shortest achievable landing distance...

Страница 709: ...d directly in the grids but when a landing is to be made into a headwind greater than 40 knots the chart is to be read at 40 knots 2 Figure 1 is based on ISA temperature conditions as required by the...

Страница 710: ...Page 7 5 Sub section 7 UNFACTORED LANDING Hawker 800XP Pro Line 21 Section IV FLIGHT PLANNING DATA Pilot s Operating Manual Revision A2 Nov 2004 Figure 1 Unfactored Landing Distance Required...

Страница 711: ...Section IV FLIGHT PLANNING DATA Page 7 6 Pilot s Operating Manual Revision A2 Nov 2004 Sub section 7 UNFACTORED LANDING Hawker 800XP Pro Line 21 Intentionally left blank...

Страница 712: ...age 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 8 7 ISA 5 C 8 8 ISA 10 C 8 9 ISA 15 C 8 10 ISA 20 C 8 11 GEAR DOWN CRUISE 1000 ft 8 12 3000 ft 8 13 500...

Страница 713: ...Page 8 2 Section IV Sub section 8 GEAR DOWN PERFORMANCE Pilot s Operating Manual P N 140 590032 0007 Revision A3 Apr 2008 Intentionally left blank...

Страница 714: ...are tabulated versus take off weight and altitude at the top of the climb The gear down climb speed profile commences at 160 KIAS at 1000 feet and accelerates to 210 KIAS at 5000 feet maintaining airs...

Страница 715: ...1 4 322 14 5 357 16 6 394 19 6 414 21 7 23 000 FUEL DIST TIME 75 0 1 119 2 2 163 4 3 199 6 3 234 8 4 269 10 4 303 12 5 339 14 5 377 17 6 416 20 7 437 22 7 24 000 FUEL DIST TIME 78 0 1 125 2 2 171 4 3...

Страница 716: ...2 5 329 14 5 366 17 6 405 20 7 425 22 7 23 000 FUEL DIST TIME 75 0 1 120 2 2 164 4 3 202 6 3 238 8 4 273 10 4 310 12 5 347 15 5 386 18 6 428 22 7 449 23 7 24 000 FUEL DIST TIME 78 0 1 126 2 2 173 4 3...

Страница 717: ...3 5 340 15 5 380 18 6 421 22 7 444 24 7 23 000 FUEL DIST TIME 75 0 1 121 2 2 166 4 3 205 6 3 243 8 4 280 11 4 319 13 5 359 16 6 401 20 6 445 24 7 469 26 8 24 000 FUEL DIST TIME 78 0 1 127 2 2 175 4 3...

Страница 718: ...13 5 352 17 6 395 20 6 440 24 7 464 27 8 23 000 FUEL DIST TIME 75 0 1 122 2 2 169 4 3 209 6 3 248 9 4 287 11 4 329 14 5 372 18 6 417 21 7 466 26 8 492 28 8 24 000 FUEL DIST TIME 78 0 1 128 2 2 177 5 3...

Страница 719: ...369 18 6 415 22 7 464 27 8 490 30 9 23 000 FUEL DIST TIME 75 0 1 124 2 2 173 5 3 215 7 3 257 10 4 299 12 5 343 16 6 389 19 6 439 24 7 491 29 9 520 32 9 24 000 FUEL DIST TIME 78 0 1 130 2 2 181 5 3 226...

Страница 720: ...20 7 438 25 8 491 30 9 520 33 9 23 000 FUEL DIST TIME 75 0 1 126 2 2 177 5 3 222 8 4 267 11 4 312 14 5 360 17 6 410 22 7 464 27 8 521 32 9 552 36 10 24 000 FUEL DIST TIME 78 0 1 132 2 2 186 5 3 234 8...

Страница 721: ...3 7 469 29 8 529 35 10 561 38 11 23 000 FUEL DIST TIME 75 0 1 129 3 2 184 6 3 233 9 4 281 12 5 331 16 6 383 20 7 438 25 8 498 31 9 562 37 10 597 41 11 24 000 FUEL DIST TIME 78 0 1 135 3 2 193 6 3 246...

Страница 722: ...8 510 34 10 578 41 11 615 45 12 23 000 FUEL DIST TIME 75 0 1 133 3 2 192 6 3 246 10 4 300 14 5 354 18 6 412 23 7 475 29 9 543 36 10 617 44 12 657 48 13 24 000 FUEL DIST TIME 78 0 1 139 3 2 203 7 3 26...

Страница 723: ...2059 210 217 2082 210 22 000 KTAS TOTAL FUEL FLOW lb hr KIAS 204 1952 210 206 1975 210 208 2000 210 210 2025 210 212 2050 210 213 2073 210 215 2097 210 217 2120 210 24 000 KTAS TOTAL FUEL FLOW lb hr K...

Страница 724: ...2029 210 223 2052 210 22 000 KTAS TOTAL FUEL FLOW lb hr KIAS 210 1924 210 212 1948 210 214 1973 210 216 1997 210 218 2020 210 220 2044 210 221 2067 210 223 2090 210 24 000 KTAS TOTAL FUEL FLOW lb hr K...

Страница 725: ...1999 210 230 2021 210 22 000 KTAS TOTAL FUEL FLOW lb hr KIAS 216 1895 210 218 1919 210 220 1943 210 222 1966 210 224 1990 210 226 2013 210 228 2037 210 230 2060 210 24 000 KTAS TOTAL FUEL FLOW lb hr K...

Страница 726: ...1971 210 237 1994 210 22 000 KTAS TOTAL FUEL FLOW lb hr KIAS 222 1870 210 224 1892 210 227 1916 210 229 1940 210 231 1963 210 233 1986 210 235 2010 210 237 2033 210 24 000 KTAS TOTAL FUEL FLOW lb hr K...

Страница 727: ...1944 210 244 1967 210 22 000 KTAS TOTAL FUEL FLOW lb hr KIAS 229 1843 210 231 1866 210 233 1890 210 236 1913 210 238 1937 210 240 1960 210 242 1983 210 244 2007 210 24 000 KTAS TOTAL FUEL FLOW lb hr K...

Страница 728: ...921 210 252 1945 210 22 000 KTAS TOTAL FUEL FLOW lb hr KIAS 236 1821 210 238 1842 210 241 1867 210 243 1890 210 245 1914 210 247 1937 210 250 1960 210 252 1984 210 24 000 KTAS TOTAL FUEL FLOW lb hr KI...

Страница 729: ...902 210 260 1925 210 22 000 KTAS TOTAL FUEL FLOW lb hr KIAS 243 1799 210 246 1822 210 248 1846 210 250 1869 210 253 1893 210 255 1918 210 257 1942 210 260 1965 210 24 000 KTAS TOTAL FUEL FLOW lb hr KI...

Страница 730: ...1880 210 268 1903 210 22 000 KTAS TOTAL FUEL FLOW lb hr KIAS 251 1774 210 253 1797 210 256 1821 210 258 1847 210 261 1871 210 263 1896 210 266 1920 210 268 1944 210 24 000 KTAS TOTAL FUEL FLOW lb hr K...

Страница 731: ...1858 210 276 1882 210 22 000 KTAS TOTAL FUEL FLOW lb hr KIAS 258 1750 210 261 1774 210 264 1801 210 266 1826 210 269 1851 210 271 1875 210 274 1899 210 276 1923 210 24 000 KTAS TOTAL FUEL FLOW lb hr K...

Страница 732: ...1839 210 286 1863 210 22 000 KTAS TOTAL FUEL FLOW lb hr KIAS 266 1733 210 269 1757 210 272 1783 210 275 1809 210 278 1832 210 280 1857 210 283 1881 210 286 1905 210 24 000 KTAS TOTAL FUEL FLOW lb hr K...

Страница 733: ...1830 210 290 1855 210 22 000 KTAS TOTAL FUEL FLOW lb hr KIAS 271 1725 210 274 1749 210 277 1775 210 279 1800 210 282 1825 210 285 1849 210 288 1873 210 290 1897 210 24 000 KTAS TOTAL FUEL FLOW lb hr...

Страница 734: ...0 5 50 23 6 56 26 6 59 27 7 21 000 FUEL DIST TIME 0 0 0 5 2 1 13 5 1 19 8 2 26 11 3 33 14 4 39 17 5 46 20 5 52 24 6 58 27 7 61 28 7 22 000 FUEL DIST TIME 0 0 0 6 2 1 13 5 1 20 8 2 27 11 3 34 15 4 40 1...

Страница 735: ...Page 8 24 Section IV Sub section 8 GEAR DOWN PERFORMANCE Pilot s Operating Manual P N 140 590032 0007 Revision A3 Apr 2008 Intentionally left blank...

Страница 736: ...90032 0007 Revision A5 Feb 2012 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 OPERAT...

Страница 737: ...Page 9 2 P N 140 590032 0007 Revision A5 Feb 2012 Pilot s Operating Manual Section IV Sub section 9 EXTENDED RANGE OPERATIONS Non ETOPS Intentionally left blank...

Страница 738: ...000 lb Climb to 39 000 ft per the Normal Climb profile Level off and cruise per the High Speed Cruise procedure Engine failure at 1027 nm from the departure airport weight 23 524 lb Descent to 15 000...

Страница 739: ...st unit Adding the fuel distance and time from the Single Engine High Speed Descent to 15 000 ft and the Single Engine Maximum Continuous Thrust MCT Cruise at 15 000 ft the following results were obta...

Страница 740: ...Page 1 Pilot s Operating Manual Original Issue Feb 2002 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...

Страница 741: ...Page 2 Pilot s Operating Manual Original Issue Feb 2002 Hawker 800XP Pro Line 21 Section V FLIGHT HANDLING Intentionally left blank...

Страница 742: ...7 ICE PROTECTION BEFORE TAKEOFF 1 7 TAKEOFF PROCEDURES 1 8 TAKEOFF THRUST 1 9 NOISE ABATEMENT PROCEDURES 1 9 TAKEOFF THRUST PROCEDURES 1 9 BEFORE TAKEOFF 1 9 TAKEOFF 1 9 UP TO 80 KIAS 1 9 ABOVE 80 KI...

Страница 743: ...ORY 1 18 DURATION OF OXYGEN SUPPLY FOR COMPLIANCE WITH 14 CFR 91 211 1 19 Table 4 DURATION OF OXYGEN SUPPLY 14 CFR 91 32 1 19 DURATION OF OXYGEN SUPPLY FOR COMPLIANCE WITH 14 CFR 135 157 1 20 Table 5...

Страница 744: ...e or not serviceable it must be disabled and locked in the forward thrust position The thrust reversers should be armed ARM annunciator illuminated before each flight unless the system is inoperative...

Страница 745: ...procedure using the right Thrust Lever T Rs RUDDER BIAS switches A B ON RUDDER BIAS annunciator Extinguished Left Thrust Lever Advance to approximately 85 N2 Verify rudder pedals deflect to the left L...

Страница 746: ...e wheels but large stones may cause dents If possible the pilot should inspect the runway surface before using it Tire wear will increase if heavy braking is used particularly on gravel surfaces Even...

Страница 747: ...Page 1 6 Pilot s Operating Manual Section V Sub section 1 NORMAL HANDLING P N 140 590032 0007 Revision A4 Sep 2010 Figure 1 Minimum Turn Radii...

Страница 748: ...ver less than five minutes in each circuit Landings with light braking may be repeated at intervals of not less than fifteen minutes After a landing with heavy braking one or more touch and go circuit...

Страница 749: ...start takeoff may be made when runway length is not limiting brakes being released before setting the thrust levers for takeoff Where field length is limiting the takeoff should be commenced from a s...

Страница 750: ...will normally prevent the engine limitations being exceeded but if this should occur fuel is cut off automatically by the computer if N1 or N2 exceeds predetermined values 107 N1 or 109 N2 Noise Abate...

Страница 751: ...Page 1 10 Pilot s Operating Manual Section V Sub section 1 NORMAL HANDLING P N 140 590032 0007 Revision A4 Sep 2010 Figure 2 Flight Profile Normal Takeoff...

Страница 752: ...justing the thrust levers until the green CLIMB annunciation appears in the N1 ITT gage located at the lower center of the N1 ITT scales on the pilot s MFD NOTE When using the CLIMB annunciation in th...

Страница 753: ...82 9 83 8 84 8 85 8 86 7 87 7 88 6 89 5 90 4 91 3 92 2 93 1 93 9 94 8 94 9 94 1 93 2 92 2 91 0 89 8 Sea Level 77 6 78 5 79 4 80 3 81 2 82 1 83 0 83 8 84 7 85 5 86 4 87 2 88 0 88 8 89 6 90 4 91 2 92 0...

Страница 754: ...Pilot s Operating Manual P N 140 590032 0007 Revision A4 Sep 2010 Page 1 13 Section V Sub section 1 NORMAL HANDLING Figure 3 Flight Profile Climb Cruise and Descent...

Страница 755: ...ed the cruise may be started at a speed below 220 KIAS or 0 70 MIND and the airplane may be allowed to accelerate as weight decreases maintaining maximum cruising thrust until the desired speed is rea...

Страница 756: ...ne may not be evident from flight characteristics alone Before takeoff check the RUDDER BIAS switches are selected ON and check the RUDDER BIAS annunciator is off NOTE Rudder bias is inhibited when th...

Страница 757: ...The red STALL VLV OPEN annunciators will illuminate The airplane should be allowed to pitch nose down until the stick push has cancelled and should then be recovered to normal controlled flight Any te...

Страница 758: ...ta insertions including ramp co ordinates previously inserted into the Flight Management System should be recalled and verified preferably by another member of the aircrew The verification should incl...

Страница 759: ...5 000 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...

Страница 760: ...NOTE The barometric control valve can only be reset below 11 000 feet For times quoted less than 30 minutes this procedure allows 30 minutes minimum supplementary oxygen supply to 2 crew members as st...

Страница 761: ...ven period the airplane is required to descend to 10 000 feet The oxygen supply is completely stopped to the passengers at this altitude For times quoted less than 120 minutes this procedure allows 12...

Страница 762: ...e the descent procedure used is 0 76 MIND down to 31 000 ft and 285 KIAS below decelerating to 250 KIAS by 10 000 ft Adequate supply of air to the cabin is obtained with engines idling and both MAIN A...

Страница 763: ...n A4 Sep 2010 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 Fl...

Страница 764: ...Pilot s Operating Manual P N 140 590032 0007 Revision A4 Sep 2010 Page 1 23 Section V Sub section 1 NORMAL HANDLING Figure 5 Flight Profile Non Precision Approach...

Страница 765: ...drag the rate of descent will be increased unless thrust is added When nearing the runway thrust should be reduced so that the airplane crosses the threshold at VREF The yaw damper should be disengag...

Страница 766: ...Pilot s Operating Manual P N 140 590032 0007 Revision A4 Sep 2010 Page 1 25 Section V Sub section 1 NORMAL HANDLING Figure 6 Flight Profile VFR Approach Normal...

Страница 767: ...Page 1 26 Pilot s Operating Manual Section V Sub section 1 NORMAL HANDLING P N 140 590032 0007 Revision A4 Sep 2010 Intentionally left blank...

Страница 768: ...AXIMUM PERMISSIBLE SPEED 2 6 FLIGHTS IN EXCESS OF MMO VMO 2 6 ICING CONDITIONS 2 7 ICING GENERAL 2 7 AIRFRAME ICING 2 7 WING TAIL ANTICE FLUIDS 2 7 BEFORE TAKE OFF 2 8 IN FLIGHT 2 8 CLIMB 2 9 CRUISE 2...

Страница 769: ...ASH 2 27 GROUND OPERATION 2 27 PRE START 2 27 TAXI 2 27 TAKEOFF 2 27 CRUISE 2 27 LANDING 2 27 APPROACH and LANDING ONE ENGINE INOPERATIVE 2 28 GO AROUND ONE ENGINE INOPERATIVE 2 28 EMERGENCY OVERWEIGH...

Страница 770: ...and runway gradient are shown in the Airplane Flight Manual Combinations of wind and gradient lying in the shaded area are not permitted Reverse thrust should be used if available but forward idle thr...

Страница 771: ...help minimize deviation Rotate at VR In a continued takeoff after engine failure where field length or obstacle clearance is limiting it is important that airspeed rise during transition is kept to a...

Страница 772: ...rating Manual Original Issue Feb 2002 Sub section 2 ABNORMAL HANDLING Hawker 800XP Pro Line 21 Section V FLIGHT HANDLING Figure 1 Takeoff Engine Failure After V1 with APR High and Low Performance Prof...

Страница 773: ...the minimum cruising speed The airplane will then drift down to the single engine cruise ceiling When a satisfactory cruise altitude is established allow the speed to rise to the Long Range KIAS or h...

Страница 774: ...ICING GENERAL If ice has formed on the airframe prior to approach or icing conditions exist the flight speeds for use on approach are provided in Figure 2 AIRFRAME ICING The airplane must be clear of...

Страница 775: ...IGNITION 1 and 2 to off when conditions permit 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...

Страница 776: ...switch ON an ITT increase of 20 to 50 C can be expected and special care must be taken not to exceed the ITT limitations Appropriate performance tables must be used when the ENG ANTICE switch is selec...

Страница 777: ...In icing conditions ice may accumulate on the unprotected areas between the TKS panels on the leading edges of the wings Descent should be made at 230 KIAS or as required in accordance with Figure 2 T...

Страница 778: ...be determined by the following visual cues If one or more of these visual cues exists immediately request priority handling from Air Traffic Control to facilitate a route or an altitude change to exi...

Страница 779: ...ponse or uncommanded roll control movement is observed reduce the angle of attack 6 Do not extend flaps during prolonged operations in icing conditions Operation with flaps extended can result in a re...

Страница 780: ...3 should be observed for that part of the flight where severe turbulence is expected in order to avoid the possibility of encountering heavy buffet The airplane should be stabilized at 230 KIAS or 0 7...

Страница 781: ...potentially serious hazard to airplanes during landing and takeoff but may also be experienced in thunderstorm areas when penetrating weather fronts low level jet streams mountain waves and thermals O...

Страница 782: ...irplane transiting this type of microburst would experience equal headwinds and tailwinds An airplane transiting the microburst from left to right would experience a small headwind followed by a large...

Страница 783: ...ay to day operations to make sure such actions are available and easily recalled when needed LESSONS LEARNED FROM WINDSHEAR ENCOUNTERS The primary lesson learned is that the best defense against winds...

Страница 784: ...ter The SOTs fall into two general headings of air crew awareness and air crew co ordination The aircrew should be prepared to change to windshear recovery techniques as soon as the SOTs indicate the...

Страница 785: ...ive Weather Near Intended Flight Path Observation Windshear Probability With localized strong winds Tower reports or observed dust rings tornado like features etc HIGH With heavy precipitation Observe...

Страница 786: ...ng but can be interpreted to mean that conditions are right for windshear activity A number of precautionary techniques have been developed which aircrews can take to lessen the effects of an inadvert...

Страница 787: ...mit maximum weight and corresponding VR for selected runway 4 If field length limit VR is greater than actual gross weight VR use the higher VR up to 20 knots in excess of actual gross weight VR for t...

Страница 788: ...ed below VR Rotation should begin no later than 2 000 ft from end of usable runway Figure 7 Windshear Effects on Rotation Decision Approach Precautions 1 Stabilize approach no later than 1000 ft ARTE...

Страница 789: ...nt In the absence of a tailwind shear this procedure may result in a higher than normal approach speed which may have to be accounted for in landing distance Landing Flap Selection Use flaps 45 If the...

Страница 790: ...limb rates Airspeed build up 2 Know use all engine initial climb attitude 3 Make continuous rotation at normal rate 4 Cross check flight director commands if applicable 5 Minimize pitch attitude reduc...

Страница 791: ...e recognition and action cannot be stressed enough The criteria for windshear recognition and recovery decision are Takeoff 1 15 knots sudden variation of airspeed 2 500 fpm sudden variation of vertic...

Страница 792: ...ncreases the performance of the airplane increasing performance shear a normal go around rather than the recovery maneuver may be accomplished Recovery Technique 1 THRUST Immediately apply full power...

Страница 793: ...presence of windshear is recognized by the pilots even if the windshear alerting system has not yet given a CAUTION or a WARNING An amber Windshear Caution is annunciated for an increasing performanc...

Страница 794: ...rolling takeoff by advancing the thrust levers smoothly to take off power CRUISE NOTE If an area contaminated by volcanic ash is encountered during cruise the aircrew must don oxygen masks If engines...

Страница 795: ...the remainder of the approach and in the event of a subsequent go around Reverse thrust on the operative engine may be used on the ground and it is recommended that the reverser on the inoperative en...

Страница 796: ...MPUTER INOPERATIVE When landing with either or both engines in the manual mode special care must be taken due to slow engine s acceleration Depending on conditions acceleration time will be greatly in...

Страница 797: ...that the rudder be used for lateral control However it may be possible to use the aileron trim control depending on the type of failure Unless the left aileron itself has jammed normal use of the trim...

Страница 798: ...age 2 31 Pilot s Operating Manual Original Issue Feb 2002 Sub section 2 ABNORMAL HANDLING Hawker 800XP Pro Line 21 Section V FLIGHT HANDLING Figure 9 Flight Profile Non Precision Approach Single Engin...

Страница 799: ...Page 2 32 Pilot s Operating Manual Original Issue Feb 2002 Sub section 2 ABNORMAL HANDLING Hawker 800XP Pro Line 21 Section V FLIGHT HANDLING Figure 10 Flight Profile ILS Approach Single Engine...

Страница 800: ...Page 2 33 Pilot s Operating Manual Original Issue Feb 2002 Sub section 2 ABNORMAL HANDLING Hawker 800XP Pro Line 21 Section V FLIGHT HANDLING Figure 11 Flight Profile VFR Approach Single Engine...

Страница 801: ...Page 2 34 Pilot s Operating Manual Original Issue Feb 2002 Sub section 2 ABNORMAL HANDLING Hawker 800XP Pro Line 21 Section V FLIGHT HANDLING Figure 12 Flight Profile VFR No Flap Approach...

Страница 802: ...ge 2 35 Pilot s Operating Manual Original Issue Feb 2002 Sub section 2 ABNORMAL HANDLING Hawker 800XP Pro Line 21 Section V FLIGHT HANDLING Figure 13 Flight Profile ILS Approach Landing Above WAT Limi...

Страница 803: ...imize roll Transmit a warning of possible ditching as soon as the emergency arises and while altitude remains The transmission can be cancelled later if danger is averted If possible the ditching shou...

Страница 804: ...Use landing lights unless mist causes reflected glare Under such conditions when the sea may not be seen clearly before impact control the rate of descent at approximately 200 ft per minute until the...

Страница 805: ...Page 2 38 Pilot s Operating Manual Revision A2 Nov 2004 Sub section 2 ABNORMAL HANDLING Hawker 800XP Pro Line 21 Section V FLIGHT HANDLING Intentionally left blank...

Страница 806: ...Page 1 Pilot s Operating Manual Original Issue Feb 2002 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...

Страница 807: ...Page 2 Pilot s Operating Manual Original Issue Feb 2002 Hawker 800XP Pro Line 21 Section VI GROUND OPERATIONS Intentionally left blank...

Страница 808: ...E LANDING GEAR 1 6 REMOVAL OF SALT OR CHEMICAL AGENTS 1 7 COLD WEATHER PROCEDURES Snow Slush and Ice 1 8 PREFLIGHT INSPECTION 1 8 TAXIING 1 8 BEFORE TAKEOFF 1 8 TAKEOFF 1 9 LANDING 1 9 SHUTDOWN AND SE...

Страница 809: ...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 1 19 GUST LOCKS 1 20 INSTALLATION OF...

Страница 810: ...S ARE TOXIC AVOID CONTACT WITH SKIN AND EYES WEAR GOGGLES AND PROTECTIVE CLOTHING CAUTION DO NOT APPLY HOT SPRAY DIRECTLY ONTO WINDOW PANEL OR SEALS During these operations the surfaces will be very s...

Страница 811: ...frost and snow from the airplane s exterior after it has formed Anti icing is a means of keeping the surface clear of subsequent accumulations of ice snow and frost Removal of these accumulations is n...

Страница 812: ...in breaking up the deposits and to retain the fluid on the deposit When all frozen deposits have been removed give a final light spray of de icing fluid FROST REMOVAL Frost that may form on the wing f...

Страница 813: ...CAUTION AFTER SPRAYING EXAMINE SURFACE THOROUGHLY TO MAKE SURE CONTAMINATION IS REMOVED AS ICE FORMED BY FREEZING RAIN IS DIFFICULT TO SEE UNDER THE DE ICING FLUID Spray with undiluted fluid hot if po...

Страница 814: ...ime or conditions prevent removal of the contamination at out stations this must be noted in the Technical Log so that the appropriate action can be taken to remove it at base Airplanes operating on r...

Страница 815: ...or icing conditions the rotor blades should be turned by hand in the direction of normal rotation to make sure they are free to rotate prior to starting engines The removal of frozen deposits by chip...

Страница 816: ...runways Also at higher speeds hydroplaning may occur under wet runway conditions Use the rudder to maintain directional control until the tires make solid contact with the runway surface Selecting re...

Страница 817: ...PON ARRIVAL 1 Drain the water system and toilet unit 2 If the airplane cannot be housed in a heated hanger remove the airplane main batteries and store in a warm environment NOTE The removal of the ai...

Страница 818: ...r 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 PREPARATION FOR FLIGHT WARNING IN ACCORDANCE WITH THE L...

Страница 819: ...successful use ground hot air supply if available to warm the engine prior to the next attempt Before takeoff the minimum oil temperature for thrust settings above idle is 30 C IMMEDIATELY BEFORE TAKE...

Страница 820: ...mpetent brake operator in the flight compartment and position an observer at each wing tip and at the rear of the airplane if it is to be pushed 7 Establish a suitable communication between the brake...

Страница 821: ...1 14 Pilot s Operating Manual Section VI Sub section 1 GROUND HANDLING P N 140 590032 0007 Revision A4 Sep 2010 Figure 1 Towbar Installation CAUTION MAKE SURE THE QUICK RELEASE PIN IS PROPERLY INSTAL...

Страница 822: ...trol gust locks Figures 7 and 8 6 Check that a pressure of 2000 psi minimum is indicated on the emergency brake accumulator gauge in the rear equipment bay If necessary top up the system by operating...

Страница 823: ...Page 1 16 Pilot s Operating Manual Section VI Sub section 1 GROUND HANDLING P N 140 590032 0007 Revision A4 Sep 2010 DEPLOYED POSITION Figure 3 Thrust Reverser Locking Pins STOWED POSITION...

Страница 824: ...ee from all contaminates before installing and do not drag the cover over the screen Installation of Engine Covers a Position the intake exhaust covers over the engine pod intake and exhaust with the...

Страница 825: ...unction with chocks front and rear of the main and nose gear wheels no mooring is necessary in winds of less than 40 knots 2 When winds are expected to exceed 40 knots moor the airplane as shown in Fi...

Страница 826: ...VI Sub section 1 GROUND HANDLING 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 moo...

Страница 827: ...in the neutral position attach the claws on the handwheel 2 Close the spigots on the claws into the handwheel bushes by pushing the knurled ring down and turning clockwise Make sure the plunger engage...

Страница 828: ...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 RUDD...

Страница 829: ...Page 1 22 Pilot s Operating Manual Section VI Sub section 1 GROUND HANDLING P N 140 590032 0007 Revision A4 Sep 2010 Intentionally left blank...

Страница 830: ...2 10 GENERAL 2 10 Figure 5 Fuel Tanks and Compartments 2 10 FUEL CAPACITIES 2 10 Table 3 Fuel Capacities 2 10 APPROVED FUEL SPECIFICATIONS 2 11 FUEL LOADING 2 11 Figure 6 Fuel System Servicing Points...

Страница 831: ...ith Take off and Landing Weights 2 48 WHEEL REMOVAL 2 49 TREAD WEAR CHECK 2 49 TIRE INSPECTION 2 49 Figure 19 Construction of a Typical Tire 2 50 PERMISSIBLE DAMAGE FOR TIRES 2 51 Table 6 Maximum Perm...

Страница 832: ...spilt fuel and or oil so that all buildings etc will be clear of the Engine Danger Zones Figure 1 2 Center the nose gear and chock all wheels 3 Remove all covers and blanks and make sure the engine in...

Страница 833: ...of less than 60 seconds Upon completion of the engine run the cowling doors and the rear equipment bay door should be closed and secured Area to be cleared if take off power is to be used Area to be...

Страница 834: ...sumption Table 2 Engine Oil Consumption NOTE Consumption is measured over a 15 hour period Approved Engine Oils For Approved Engine Oils refer to the Airplane Flight Manual Section 2 LIMITATIONS Check...

Страница 835: ...sh down and turn 90 clockwise to secure Do not use excessive force 6 Record the quantity required to fill the system 7 Close the cowling lower access door and secure Replenish Engine Oil via the Fille...

Страница 836: ...ot s Operating Manual Revision A2 Nov 2004 Sub section 2 GROUND SERVICING Hawker 800XP Pro Line 21 Section VI GROUND OPERATIONS Figure 2 Engine Oil Contents Viewing Ports INBOARD LEFT ENGINE OUTBOARD...

Страница 837: ...Page 2 8 Pilot s Operating Manual Revision A2 Nov 2004 Sub section 2 GROUND SERVICING Hawker 800XP Pro Line 21 Section VI GROUND OPERATIONS Figure 3 Engine Oil System Replenishment Details...

Страница 838: ...CIALLY IMPORTANT WHEN WORKING NEAR THE THRUST REVERSER DOORS MAKE SURE ALL OF THE FOLLOWING PRECAUTIONS ARE COMPLETED BEFORE STARTING ANY MAINTENANCE WORK 1 Make sure the electrical power is off 2 Pin...

Страница 839: ...ral tank filler neck is through a door on the left side of the tank rear fairing FUEL CAPACITIES Capacities quoted in Table 3 are achieved following gravity refueling NOTE Contents indicators register...

Страница 840: ...anadian CAN CGSB 3 22 JET B Russian GOST 10227 86 T2 Fuel Additives Anti Static STADIS 450 additive may be used in concentrations not exceeding 3 parts per million ppm by volume SIGBOL additive TU38 1...

Страница 841: ...0 0 0 0 0 0 0 0 0 0 N1 ITT N2 0 22 1 22 PRESS TEMP C OIL OIL 0 0 FUEL FLOW 1940 LBS 2020 QTY FUEL EMPTY VENTRAL C A D E B ON OFF POWER BOND POINT BLANKING CAP ON LANYARD VENTRAL TANK REAR FAIRING BOND...

Страница 842: ...ng of the HEPC into engagement with the airplane coupling 4 Rotate the HEPC clockwise to the limit of its travel approximately 40 5 Connect the HEPC ground clip to the grounding point 6 Move the valve...

Страница 843: ...Page 2 14 Pilot s Operating Manual Revision A2 Nov 2004 Sub section 2 GROUND SERVICING Hawker 800XP Pro Line 21 Section VI GROUND OPERATIONS Pressure Refueling Coupling Figure 7...

Страница 844: ...OWER switch on the refuel control panel a For Airplane Serial No 258670 and subsequent or for airplanes with SB 24 3641 embodied The refuel control panel POWER switch also energizes the left CDU and t...

Страница 845: ...f the refuel control panel POWER switch to ON Selecting the airplane batteries to ON for these airplanes is not required To Drain Water From The Wing Center Tanks Use This Release Tool With The Extens...

Страница 846: ...WARNING THE APU MUST NOT BE USED IF THE AIRPLANE CONTAINS OR WILL BE REFUELLED WITH A WIDE CUT FUEL E G JP4 WARNING DO NOT START THE APU WHILE A REFUEL IS IN PROGRESS Limitations Maximum refuel press...

Страница 847: ...ns are the same as those at the end of step 2 g Push the L WING PRESS TO TEST and check FULL is indicated VALVE indication changes from OPEN to SHUT h Push the R WING PRESS TO TEST and check FULL is i...

Страница 848: ...the HEPC up and put its nose coupling into engagement with the airplane coupling turn the HEPC clockwise to the limit of its travel approximately 40 d Connect the HEPC grounding clip to the grounding...

Страница 849: ...ng I Airplane Serial No 258670 and subsequent or airplanes with Raytheon Aircraft Company Service Bulletin SB 24 3641 incorporated and pressure refueling with the airplane batteries only 1 Calculate t...

Страница 850: ...her CDU push and release the IDX button b On the CDU push and release R LSK2 The Engine Fuel data page will be displayed on the CDU 6 If the wings are to be only partially filled check the wing FUEL c...

Страница 851: ...nect the hose to airplane refuel coupling 3 Bond the hose coupling to the airplane NOTE A refuel vehicle with either hose end or on board pressure regulation may be used 4 Open the refuel vehicle deli...

Страница 852: ...g lead uncouple the refueling hose and disconnect the vehicle bonding lead Install the blanking cap to the airplane coupling and close the coupling access door 13 If necessary de energize the DC busba...

Страница 853: ...subsequent or airplanes with Raytheon Aircraft Company Service Bulletin SB 24 3641 incorporated and suction defueling with the airplane batteries only 1 Calculate fuel quantity to be off loaded NOTE F...

Страница 854: ...displayed on the CDU 5 If the wings are to be only partially defueled check the wing FUEL contents displayed on the CDU and make sure the indication shows the correct current fuel state 6 Comply with...

Страница 855: ...FUEL switch to DEFUEL and check the ventral tank VALVE magnetic indicator displays OPEN c Defuel the ventral tank until the CDU legend displays EMPTY d Check the ventral tank VALVE magnetic indicator...

Страница 856: ...ing on the configuration of the airplane refer to the appropriate steps under I II or III to prepare for Gravity Refueling Wing Tanks I Airplane Serial No 258670 and subsequent or airplanes with Rayth...

Страница 857: ...ng tanks with the airplane batteries only 1 Calculate the fuel load required CAUTION INVESTIGATE ANY CONTAMINATION OTHER THAN WATER OF THE FOLLOWING DRAINED SAMPLE 2 Drain all water from the tanks Fig...

Страница 858: ...ts displayed on the CDU and make sure the indication shows the correct current fuel state 5 Comply with local refueling safety precautions 6 Refer below to Gravity Refueling Wing Tanks Procedure and c...

Страница 859: ...ointed forward b Turn the handle to lock and the seal cap c Lower the handle into the recess 9 Disconnect the refuel vehicle or hydrant bonding lead 10 Remove the wing skin protection mat from the win...

Страница 860: ...0 and subsequent or airplanes with Raytheon Aircraft Company Service Bulletin SB 24 3641 incorporated and gravity refuel ventral tank with the airplane batteries only NOTE If the ventral tank is to be...

Страница 861: ...a On either CDU push and release the IDX button b On the CDU push and release R LSK2 The Engine Fuel data page will be displayed on the CDU 6 If the wings are to be only partially filled check the wi...

Страница 862: ...ller cap from the tank 8 Pump fuel into the tank until full and withdraw the nozzle 9 Check the filler cap is serviceable install and secure the cap to the tank Disconnect the bonding lead and close t...

Страница 863: ...ER THAN WATER IN THE FOLLOWING DRAINED SAMPLE 2 Drain all water from the tanks 3 Comply with local refueling safety precautions 4 Bond the refuel vehicle hydrant or container to the airplane 5 Place a...

Страница 864: ...e 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 Insert the cap into the skin adapter wi...

Страница 865: ...Page 2 36 Pilot s Operating Manual Revision A2 Nov 2004 Sub section 2 GROUND SERVICING Hawker 800XP Pro Line 21 Section VI GROUND OPERATIONS Figure 10 Ventral Tank Filler Cap...

Страница 866: ...erating Manual Revision A2 Nov 2004 Sub section 2 GROUND SERVICING Hawker 800XP Pro Line 21 Section VI GROUND OPERATIONS M8009_0 AI FUEL DRAIN ADAPTER 25Y 867A WING LEADING EDGE Figure 11 Gravity Defu...

Страница 867: ...otection 2 For external starts a ground power unit capable of supplying 28 VDC with a minimum output of 42 kW short term capability of 28 volts x 1500 AMPS having a limiter operating at 1100 AMPS must...

Страница 868: ...itor the battery voltage on B1 B2 and PE by using the voltmeter selector switch ESSENTIAL DC BUSBAR PE Power Diode When the BATTERY switch is selected to EMERG No 1 and No 2 batteries are connected in...

Страница 869: ...Section VI GROUND OPERATIONS Page 2 40 Pilot s Operating Manual Revision A2 Nov 2004 Hawker 800XP Pro Line 21 Sub section 2 GROUND SERVICING Figure 13 External Ground Power Receptacle...

Страница 870: ...foot brake pedals until the emergency brake accumulator pressure gauge reads 950 to 1000 psi CHECK MAIN HYDRAULIC SYSTEM RESERVOIR Figure 15 16 Table 5 Equipment and Materials 1 Make sure the landing...

Страница 871: ...ck the velcro secured fabric cover on the forward bulkhead and gain access to the auxiliary reservoir 3 Check the fluid level in the tank level indicator tube and replenish the reservoir as necessary...

Страница 872: ...of dry nitrogen CAUTION APPLY NITROGEN SLOWLY TO PREVENT DAMAGE TO THE ACCUMULATORS AND TO PREVENT FALSE READINGS DUE TO OVERHEATING 6 After charging check the charging valves for leaks OFF 2 2 1 1 0...

Страница 873: ...RELEASE CONNECTION 3 OFF NORMAL BRAKE PRESSURE RELEASE VALVE THRUST REVERSER ACCUMULATOR GAUGE CAPACITORS MAIN SYSTEM RESERVOIR AND ACCUMULATORS EMERGENCY ACCUMULATOR MAIN ACCUMULATOR EMERGENCY BRAKE...

Страница 874: ...Page 2 45 Pilot s Operating Manual Revision A2 Nov 2004 Sub section 2 GROUND SERVICING Hawker 800XP Pro Line 21 Section VI GROUND OPERATIONS Figure 16 Main Hydraulic Reservoir...

Страница 875: ...0 psi is recommended for pressures quoted above or Figures 17 and 18 With the airplane standing on its wheels check the tire pressures with an inflation gauge pressure range 0 260 psi and a screw on...

Страница 876: ...s Operating Manual Revision A2 Nov 2004 Sub section 2 GROUND SERVICING Hawker 800XP Pro Line 21 Section VI GROUND OPERATIONS Figure 17 Variation of Minimum Nosewheel Tire Pressure with Take off and L...

Страница 877: ...l Revision A2 Nov 2004 Sub section 2 GROUND SERVICING Hawker 800XP Pro Line 21 Section VI GROUND OPERATIONS TIRE PRESSURE POUNDS PER SQUARE INCH Figure 18 Variation of Minimum Mainwheel Tire Pressure...

Страница 878: ...groove s NOTE A tire worn beyond the above defined limit cannot normally be retreaded TIRE INSPECTION 1 Examine the tire tread as previously defined in Tread Wear Check and reject a tire which is full...

Страница 879: ...ATIONS CROWN SHOULDER SIDE WALL BEAD Tire Terminology Chine Type Nose Wheel Tire CHINE REINFORCING CORD TREAD SIDEWALL RUBBER BEAD CHAFER BEAD HEEL BEAD BASE PLY OVERLAP BEAD APEX STRIP BEAD FILLERS B...

Страница 880: ...the cords of the casing plies are not exposed 3 Refer to Figure 20 example 1 and Figure 20A example 5 Unevenly worn tires or tires worn on the shoulder until worn to the base of the tread pattern or...

Страница 881: ...ting Manual Revision A2 Nov 2004 Sub section 2 GROUND SERVICING Hawker 800XP Pro Line 21 Section VI GROUND OPERATIONS Figure 20 Permissible Tire Damage UNEVEN WEAR 1 TYPICAL FLINT CUT 2 SIDEWALL SPLIT...

Страница 882: ...Manual Revision A2 Nov 2004 Sub section 2 GROUND SERVICING Hawker 800XP Pro Line 21 Section VI GROUND OPERATIONS Figure 20A Permissible Tire Damage continued EXCESSIVE WEAR ON SHOULDER 5 SKID BURN OR...

Страница 883: ...er damage 2 Refer to Figure 21 example 2 Open tread joints or other extensive cuts 3 Refer to Figure 21 example 3 The sidewall of the tire must be clear of creasing or buckling 4 Refer to Figure 21 ex...

Страница 884: ...GROUND SERVICING Hawker 800XP Pro Line 21 Section VI GROUND OPERATIONS BULGES IN THE CROWN AREA 1 OPEN TREAD JOINT 2 SIDEWALL CREASING OR BUCKLING 3 SPLITTING AT BASE OF TREAD GROVE 4 TIRE SCUFFED EXP...

Страница 885: ...ND FREE FROM OIL OR GREASE WARNING IF A LEAK OCCURS AT THE CHARGING VALVE ADAPTER THE ADAPTER MUST NOT BE OVER TIGHTENED CLOSE THE CHARGING VALVE AND CHARGING CART STOP VALVE AND DEPRESSURIZE THE HOSE...

Страница 886: ...N 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 limit...

Страница 887: ...Page 2 58 Pilot s Operating Manual Revision A2 Nov 2004 Sub section 2 GROUND SERVICING Hawker 800XP Pro Line 21 Section VI GROUND OPERATIONS Figure 23 Main Gear Pressure Extension Graph...

Страница 888: ...Page 2 59 Pilot s Operating Manual Revision A2 Nov 2004 Sub section 2 GROUND SERVICING Hawker 800XP Pro Line 21 Section VI GROUND OPERATIONS Figure 24 Nose Gear Pressure Extension Graph...

Страница 889: ...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 1 Open the master SUPPLY valve on the o...

Страница 890: ...EQUIPMENT IS CONNECTED TO THE AIRPLANE WARNING MAKE SURE A CARBON DIOXIDE FIRE EXTINGUISHER IS IMMEDIATELY AVAILABLE WARNING ONLY OXYGEN THAT CONFORMS TO THE CORRECT SPECIFICATION MUST BE USED TO REP...

Страница 891: ...valve WARNING DO NOT OPEN VALVES OR INCREASE PRESSURE RAPIDLY 3 Open the rig delivery valve and set the regulator valve to charge the system slowly to approximately 1900 psi 4 Close the rig delivery v...

Страница 892: ...sbar Figure 12 2 Make sure the contents indicator on the copilot s side console is at a minimum of 1 4 3 Push the vent valve adjacent to the tank filler cap for at least 10 seconds 4 Set the WING TAIL...

Страница 893: ...ME 6 TANK CONTENTS GAUGE ON RIGHT HAND CONSOLE DE ICE FLUID ICE DETECTED ANTICE LO PRESS ANTICE LO QTY ICE DET AUTO OVRD WING TAIL ANTICE MINS 0 10 E F 1 4 1 2 3 4 DE ICING FLUID TANK CONTENTS TRANSMI...

Страница 894: ...AL AVIATION NEWS 8 FAA ACCIDENT PREVENTION PROGRAM 8 ADDITIONAL INFORMATION 8 GENERAL INFORMATION ON SPECIFIC TOPICS 9 MAINTENANCE 9 HAZARDS OF UNAPPROVED MODIFICATIONS 10 FLIGHT PLANNING 10 PASSENGER...

Страница 895: ...CONTINUED Stalls Slow Flight and Training 21 Spins 21 Vortices Wake Turbulence 23 Takeoff and Landing Conditions 23 MEDICAL FACTS FOR PILOTS 24 General 24 Fatigue 24 Hypoxia 24 Hyperventilation 25 Al...

Страница 896: ...e manuals which accompany the airplane that FAA requirements for ratings certifications and review be scrupulously complied with and that only persons who are properly licensed and rated and thoroughl...

Страница 897: ...we can not make changes in the name or address furnished by the FAA The owner must contact the FAA regarding any changes to name or address Their address is FAA Aircraft Registration Branch AAC250 P...

Страница 898: ...h an Airworthiness Directive issued by the FAA applies except in accordance with the requirements of that Airworthiness Directive Airworthiness Directives AD s are not issued by the manufacturer They...

Страница 899: ...n regulatory material of interest Advisory Circulars contain a wealth of information with which the prudent pilot should be familiar A complete list of current FAA Advisory Circulars is published in A...

Страница 900: ...Intentional Spinning 61 84 Role of Preflight Preparation 67 2 for sale Medical Handbook for Pilots 90 23 Wake Turbulence 90 42 Traffic Advisory Practices at Nontower Airports 90 48 Pilot s Role in Co...

Страница 901: ...The FAA conducts seminars and workshops and distributes invaluable safety information under this program Usually the airport manager the FAA Flight Service Station FSS or Fixed Base Operator FBO will...

Страница 902: ...that proper maintenance records are kept Use only genuine Raytheon Aircraft Company approved parts obtained from Raytheon Aircraft Company approved sources in conjunction with the maintenance and repa...

Страница 903: ...conflict with other STC s that have already been installed Because approval of an STC is obtained by the individual STC holder based upon modification of the original type design it is possible for S...

Страница 904: ...and severe spinal injuries can occur to occupants Prior to flight pilots should assure that articles are not stowed beneath seats that would restrict seat pan energy absorption or penetrate the seat i...

Страница 905: ...d have the system repaired by a qualified service agency If field service advice or assistance is necessary contact Raytheon Aircraft Company Customer Support Department The preflight check must be co...

Страница 906: ...erience in properly maintaining that make and model of airplane The owner should make certain that control cable tension inspections are performed as outlined in the applicable Raytheon Aircraft Compa...

Страница 907: ...un the risk of structural damage or failure on the other hand if your airspeed is too low the airplane may stall If turbulence is encountered reduce speed to the turbulent air penetration speed or to...

Страница 908: ...operable equipment needed for flight in icing conditions In addition they must ascertain from the same source the limits of approval or certification of their airplane for flight in icing conditions...

Страница 909: ...ress to the point where the airplane is no longer capable of flying Therefore the pilot operating even a fully equipped airplane in sustained icing conditions must remain sensitive to any indication s...

Страница 910: ...r is as its name implies for avoiding severe weather not for penetrating it Whether to fly into an area of radar echoes depends on echo intensity and shape spacing between the echoes and the capabilit...

Страница 911: ...ects and inform your passengers 2 Plan and hold your course to take you through the storm in minimum time 3 To avoid the most critical icing establish a penetration altitude below the freezing level o...

Страница 912: ...flight procedures can an airplane be operated safely in a low visibility environment Flying in fog dense haze or dust cloud banks or very low visibility with strobe lights or rotating beacons turned o...

Страница 913: ...ed by at least 80 Single engine climb performance depends on four factors Loss of thrust on one engine creates yaw due to asymmetric thrust Yaw forces must be balanced with the rudder In addition yaw...

Страница 914: ...RUST LEVER MOVEMENT THEN SECURE Engine Failure During Takeoff If an engine fails before attaining V1 the only proper action is to discontinue the takeoff Stalls Slow Flight and Training The stall warn...

Страница 915: ...verted during the onset of a spinning motion Once the airplane has been permitted to progress beyond the stall and is allowed to reach the rapid rolling and yawing condition the pilot must then immedi...

Страница 916: ...nter roll obtainable in a light airplane The turbulent areas may remain for as long as three minutes or more depending on wind conditions and may extend several miles behind the airplane Plan to fly s...

Страница 917: ...you are not getting enough oxygen It is impossible to predict when or where hypoxia will occur during a given flight or how it will manifest itself Some of the common symptoms of hypoxia are increase...

Страница 918: ...ith significant circulatory or lung disease may need to use supplemental oxygen at lower altitudes than specified by these regulations Pilots of pressurized airplanes should receive physiological trai...

Страница 919: ...hat pilots commit major errors of judgment and procedure at blood alcohol levels substantially less than the minimum legal levels of intoxication for most states These tests further show a continuatio...

Страница 920: ...feet Carbon Monoxide and Night Vision The presence of carbon monoxide results in hypoxia which will affect night vision in the same manner and extent as hypoxia from high altitudes Even small levels...

Страница 921: ...losion in capability of avionics systems is even more remarkable Radar FMS GPS sophisticated autopilots EFIS and other devices which just a few years ago were too large and prohibitively expensive for...

Страница 922: ...r the supplement part number Any information pending foreign regulatory agency approval will be listed in the description Raytheon Aircraft Company which has been renamed Hawker Beechcraft Corporation...

Страница 923: ...the manual Supplements marked with an asterisk will not be supplied with Pilot s Operating Manuals due to their limited applicability If a document is required for your airplane please order it throu...

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