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Hawker 800 XP, Руководство по подготовке пилотов

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Rotation of the engine-driven oil pump draws
oil from the reservoir. Oil under pressure
flows through a pressure regulator, filter
and temperature control components to the
engine bearings, the transfer gearbox, ac-
cessory gearbox and the front fan planetary
gear assembly. 

The reservoir has a liquid level sight gage and
a filler cap on the right side of the tank. A filler
tube and cap are located on the left side of the
tank which allows for oil tank replenishing when
access to the right side is restricted.

Oil Pump Assembly

An oil pump assembly is located on the ac-
cessory drive gearbox. It contains a single oil
pressure pump and four scavenge pumps.

The pressure pump draws oil from the reser-
voir and supplies sufficient pressure to force
the oil through the engine components that
require lubricating.

The scavenge pumps collect oil from the plan-
etary gear assembly and the forward engine
bearings, the aft engine bearings, the transfer
gearbox and the mid engine bearings, and the
accessory drive gearbox. A common discharge
line connects the four scavenge pumps to the
engine oil reservoir.

An adjustable pressure regulator in the pumps
helps to provide a constant oil pressure by com-
pensating for changes in the aircraft altitude.

Oil Filter

A filter is provided to remove impurities from
the oil. The oil filter consists of a disposable
element enclosed in a metal housing on the
right side of the accessory drive gearbox.

Oil Tank

A 1.65 U.S. gallon capacity oil reservoir is
located on the right side of the engine fan by-
pass housing.

Engine protection against filter clogging is
provided by an oil filter bypass indicator valve
located adjacent to the oil filter. The valve
opens when the pressure drop across the fil-
ter is excessive to bypass lubricating oil around
the filter.

An integral differential (

∆

P) pressure indica-

tor on the valve visually flags a clogged filter
condition before bypassing occurs. A thermal
lockout device on the 

∆

P indicator prevents ac-

tuation under cold oil conditions although the
bypass valve will bypass oil under these con-
ditions.

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 from clogging
the fuel filter and any other components.

Fuel flow through the fuel heater is thermo-
statically controlled to provide the optimum op-
erating temperature. Excess oil pressure with
cold oil is prevented by a pressure bypass valve.

Air/Oil Cooler

After oil leaves the fuel heater, it passes through
the air/oil coolers in the engine bypass duct. The
air/oil cooler consists of three segments: one
half segments and two quarter segments. 

Each segment is a finned unit with oil lines
running through it. Together the three seg-
ments form the inner surface the fan duct. A
temperature controlled integral bypass valve
directs oil that is hotter than 65° C through the
three segment of the air/oil cooler. Air flow-
ing through the duct cools the oil that passes
through the cooler. Below this temperature, the
valves bypass the oil around the air/oil cooler.

Revision 1

7-7

FOR TRAINING PURPOSES ONLY

HAWKER 800 XP

PILOT TRAINING MANUAL

FlightSafety

international

Содержание 800 XP

Страница 1: ...HAWKER 800 XP PILOT TRAINING MANUAL Volume 2 Aircraft Systems FlightSafety International Inc Marine Air Terminal LaGuardia Airport Flushing New York 11371 718 565 4100 FlightSafety international...

Страница 2: ...Center New Castle County Airport 155 N DuPont Highway New Castle DE 19720 302 328 7548 FlightSafety International Houston Learning Center William P Hobby Airport 7525 Fauna Street Houston TX 77061 71...

Страница 3: ...tion and training purposes only At the time of printing it contained then current information In the event of conflict between data provided herein and that in publications issued by the manufacturer...

Страница 4: ......

Страница 5: ...POWER UNIT Chapter 7 POWERPLANT Chapter 8 FIRE PROTECTION Chapter 9 PNEUMATICS Chapter 10 ICE AND RAIN PROTECTION Chapter 11 AIR CONDITIONING Chapter 12 PRESSURIZATION Chapter 13 HYDRAULIC POWER SYST...

Страница 6: ......

Страница 7: ...Description of Transition Course SYL 11 Course Objectives SYL 12 Training Schedule Typical SYL 12 Simulator and Flight Training SYL 15 Completion Standards SYL 16 Training Materials Aids Devices and...

Страница 8: ...Prohibited Drugs SYL 23 Aircraft Ground Training Curriculum SYL 24 SYSTEMS INTEGRATION SYL 52 CREW RESOURCE MANAGEMENT SYL 53 FLIGHT TRAINING SYL 53 SYL ii FOR TRAINING PURPOSES ONLY HAWKER 800 XP PI...

Страница 9: ...IONS Figure Title Page SYL 1 Houston Facility Floor Plan SYL 2 SYL 2 Greater Philadelphia Wilmington Facility Floor Plan SYL 4 FOR TRAINING PURPOSES ONLY HAWKER 800 XP PILOT TRAINING MANUAL FlightSafe...

Страница 10: ......

Страница 11: ...bby Airport 7525 Fauna at Airport Boulevard Houston Texas 77061 713 644 1521 800 927 1521 Fax 713 644 2118 DESCRIPTION OF TRAINING FACILITY Each classroom and briefing room is adequately heated lighte...

Страница 12: ...140 EXIT FIRE EXIT INSTRUCTORS SHIPPING RECEIVING LOUNGE ROOM 137 ROOM 138 ROOM 139 MEN ROOM 123 ROOM 121 ROOM 117 ROOM 119 LOUNGE MEN ROOM 110 ROOM 107 ELECTRICAL SUPPLY SUPPLY WOMEN FIRE EXIT RECEP...

Страница 13: ...RAINING ROOM TRAINING ROOM TRAINING ROOM TRAINING ROOM TRAINING ROOM TRAINING ROOM 3 OFFICE MEN OFFICE TRAINING ROOM OVERFLOW BRIEFING ROOM EXIT DIRECTOR OF STANDARDS OFFICE OFFICE ATR 42 72 BRIEFING...

Страница 14: ...0 PM H S PM 135 LOBBY MANAGER CUSTOMER SUPPORT ADMIN ASST CUSTOMER SUPPORT MANAGER WORKSPACE M X INSTRUCTO R BRIEF BRIEF BRIEF BRIEF 1 3 8 MAINTENANCE SHOP BRIEF BRIEF BRIEF BRIEF RECPT ADMINISTRATION...

Страница 15: ...SROOM 8 CLASSROOM 10 CLASSROOM 12 CLASSROOM 14 MEN WOMEN CLASSROOM 5 CLASSROOM 6 CLASSROOM 3 CLASSROOM 4 CLASSROOM 2 CLASSROOM 1 GND SIM FLT INSTRUCTORS WW PM ATR PM LOUNGE COFFEE VENDING T T Greater...

Страница 16: ...21 5 19 X 24 12 6 19 X 24 12 7 19 X 24 18 8 19 X 24 18 9 19 X 24 18 10 20 X 24 8 11 19 X 20 8 12 19 X 20 12 13 19 X 20 12 14 19 X 20 12 HOUSTON LEARNING CENTER South Building Classroom Size in Student...

Страница 17: ...the items required in flight in a HS 125 airplane if the pilot 1 Holds a valid Private or Ccommercial Pilot certificate with an Instrument Rating or an Airline Transport Pilot certificate with an Air...

Страница 18: ...powered multiengine airplanes or d Has at least 500 hours of actual flight time in a HS 125 series airplane or e Has at least 1 000 hours of flight time in at least two different airplanes requir ing...

Страница 19: ...of the limitation The PIC limitation is not required if the pilot performs the following on a static airplane or in flight as appropriate 1 Preflight Inspection 2 Normal Takeoff 3 Normal ILS Approach...

Страница 20: ...Oral Exam and Pre Post Briefings for Qualification 3 0 Total Ground Training Hours 57 0 Cockpit Procedure Mockup CPM training may be given in conjunction with the simulator prebriefs Flight Training...

Страница 21: ...Total Ground Training Hours 57 0 Flight Training Flight Training Simulator 10 0 Aircraft Flight Training Typical if necessary 2 0 Flight Training LOFT 4 0 Total Flight Training Hours 18 0 Qualificati...

Страница 22: ...g An Instrument Competency Check as specified in FAR 61 57 Recent Flight Experience as specified in FAR 61 57 c and or 61 57 d provided the candidate meets the requirements of FAA Exemption 5317 as am...

Страница 23: ...nit Powerplant Fire Protection Pneumatics Air Conditioning Day 4 Classroom 6 0 Pressurization Hydraulic Power Systems Landing Gear and Brakes Day 5 Classroom 6 0 Flight Controls Avionics Miscellaneous...

Страница 24: ...Classroom 3 0 Performance Simulator Period No 4 1 0 Day 10 Classroom 3 0 Performance Weight and Balance Day 11 Simulator Period No 5 2 0 Classroom 3 0 Review and Final Exam Day 12 Simulator Period No...

Страница 25: ...ws basic deficiencies such as lack of knowledge skill or ability to perform the required procedures or maneuvers If the present level of per formance or progress is maintained it is doubtful that the...

Страница 26: ...meet the standards of the Airline Transport Pilot and Type Rating Practical Test Standards FAA S 8081 5 TRAINING MATERIALS AIDS DEVICES AND METHODS Listed below are the training tools to implement th...

Страница 27: ...ndicator panel layout of the cockpit It is also used to practice normal and abnonnal emergency procedures Flight Simulator The equipment simulates the operational characteristics of the actual aircraf...

Страница 28: ...ecture facilitator CPM Guided discussion demonstration performance practice Simulator Guided discussion demonstration performance practice Self directed learning Self study program independent study S...

Страница 29: ...ot experience or equivalent served as a ground and or flight instructor for 2 years and have at least two years of college or equivalent Director of Pilot Training The Director of Pilot Training is re...

Страница 30: ...part G and hold a Flight Instructor Certificate with Airplane Instrument and Multiengine Land ratings and an Airline Transport Pilot Certificate with a CE 500 type rating Each Simulator Instructor mus...

Страница 31: ...ting the Chapter 10 syllabus See TAB 7 provided the instructor has piloted the HS 125 Simulator at least 3 hours in the 180 days preceding the date of the FAR 61 58 PIC Check Flight instructors must h...

Страница 32: ...certificate Examiner designation if applicable Pilot Proficiency Examiner PPE authorization if applicable Copies of the following certificates issued by FlightSafety Instructor Certification Academic...

Страница 33: ...tial phase and each recurrent phase of the training re quired by this part TESTING FOR PROHIBITED DRUGS FlightSafety International s drug testing program as mandated by the Federal Aviation Administra...

Страница 34: ...ft systems with operational procedures to sufficiently pre pare them to enter the flight training curriculum segment B FlightSafety Administration C General Operational Subjects Modules if applicable...

Страница 35: ...tique H Completion Standards 1 Systems The pilot must demonstrate adequate knowledge of the aircraft systems by passing an open book written final exam with a score of 70 that is corrected to 100 GROU...

Страница 36: ...conducted by FlightSafety unless specifically pertinent to this course I Aircraft Systems Modules A Aircraft General Master Warning Module 1 General Elements a System Description 1 Structures 2 Airpla...

Страница 37: ...cy 7 Airspeed Limitations 8 Bird Strike Protection B Electrical Module 1 General Elements a System Description 1 General 2 DC Power 3 AC Power 4 Electrical Power Sources 5 Limitations b Controls and C...

Страница 38: ...us f Circuit Breakers 1 XE supplied circuit breakers 2 STBY INV 3 XE Bus Supply c Indicators Indications 1 Battery and Generator Ammeters 2 BATT HOT warning 3 Battery Charge 4 Battery Temperature d An...

Страница 39: ...ystem 3 Limitation Elements a Minimum Battery Voltage b Generator Limits c Ground Power Unit Limits 4 Emergency Abnormal Procedure Elements a Abnormal Voltage b Battery Contactor c Battery Overheat 1...

Страница 40: ...abin Lights 5 Cabin Emergency Lights 6 Cockpit Emergency and Storm Lights 7 Emergency Lights 8 Exterior Lights 9 Instrument Panel Lights 10 Interior Lights 11 Landing Lights 12 Logo Lights 13 Taxi Lig...

Страница 41: ...rottle Below 60 70 rpm 6 Speed Warning 7 Testing 8 Cabin Depressurization 9 Airframe De icing Audible Warning 2 Operational Elements a Master Warning System Operation b Dim Override Test c Smoke Detec...

Страница 42: ...uel Pumps 3 Refuel Panel 2 Operational Elements a Check Battery and Fuel Temperature b Maintain a lateral balance of fuel 3 Limitation Elements a Distribution in Wing Tanks b Transfer from Ventral Tan...

Страница 43: ...ors 1 APU FAULT 2 APU FIRE 3 APU GEN OVERHEAT 4 APU WARN 5 LO OIL PRESS 6 HIGH OIL TEMP 7 APU GEN 8 BLEED AIR VALVE FAIL 9 BLEED AIR ON 10 READY TO LOAD d Servicing Preflight 2 Operational Elements a...

Страница 44: ...ronization 7 Automatic Performance Reserve APR 8 Airstarts 9 Electric Power Sources 10 Power Plant Limitations b Controls and Components 1 APR 2 APR ARM Selector Switch 3 APR O RIDE Selector Switch 4...

Страница 45: ...verser Light d Annunciators 1 ENG 1 CMPTER 2 ENG 2 CMPTER 3 START PWR 4 L R OIL PRESS 5 Green Operating lights 2 Operational Elements a Aurally check ignitor plug operation b Check APR c Check Engine...

Страница 46: ...ure j Immediate Relight k Starter Assisted Relight 1 Windmill Relight m Annunciators from I G I d n High Engine Vibration o Rudder Bias Not Inhibited p Unlock or Arm In Flight q Autostow r Double Engi...

Страница 47: ...matics Module 1 General Elements a System Description 1 Description and Operation 2 Electrical Power Sources 3 Limitations b Controls and Components 1 Flight Deck Heat Valve 2 Main Air Valve c Annunci...

Страница 48: ...rs 1 REAR BAY O HEAT 2 Emergency Abnormal Procedure Elements a Automatic Temperature Control Failure b Duct Overheat c High Pressure Air Overheat d Annunciators from 1 J 1 d K Pressurization Module 1...

Страница 49: ...ferential Pressure b Maximum Allowable Negative Pressure Differential c Safety Valves Setting 4 Emergency Abnormal Procedure Elements a Automatic Pressure Control Failure b Depressurization c Emergenc...

Страница 50: ...s 9 TKS 10 Wing Tail Anti ice Time Switch c Indicators Indications 1 TKS System Chime 2 TKS Gage d Annunciators 1 ALTR 1 FAIL ALTR 2 FAIL 2 ANTICE LOW PRESS 3 ANTICE LOW QUANTITY 4 ENG 1 A ICE ENG 2 A...

Страница 51: ...M Hydraulics Module 1 General Elements a System Description 1 Main Hydraulic System 2 Auxiliary Hydraulic System 3 Hydraulic Subsystems 4 Electrical Power Sources b Controls and Components 1 Auxiliar...

Страница 52: ...Main Hydraulic Failure f EMER Brake Low Pressure g HYD AUX System Low N Thrust Reversers Module 1 General Elements a System Description 1 Thrust Reverser Assembly 2 System Operation 3 Electrical Powe...

Страница 53: ...ding Gear and Brakes Module 1 General Elements a System Description 1 Landing Gear 2 Nosewheel Steering 3 Brakes 4 Electrical Power Sources 5 Limitations b Controls and Components 1 Brake Pedals 2 Bra...

Страница 54: ...Standby Gear Indicator Lights 9 Zero Supply Gage Reading d Annunciators 1 EMERG BRK LO PRESS 2 HYD LO PRES 3 AUX HYD LOW LEVEL e Servicing Preflight 1 Brakes 2 Emergency Accumulator 3 Reservoir Air P...

Страница 55: ...lements a System Description 1 Primary Flight Controls 2 Trim Systems 3 Secondary Flight Controls 4 Stall Warning and Identification 5 Electrical Power Sources 6 Limitations b Controls and Components...

Страница 56: ...dicator 3 Angle of Attack Indicator 4 Airbrake Indicator d Annunciators 1 ELEV AIL TRIM 2 FLAP Fault 3 STALL IDENT 1 2 and 3 4 SQUAT Fault 5 SSU Fault 6 RUDDER BIAS 2 Operational Elements a Operate El...

Страница 57: ...Electric Power Sources 4 Limitations b Controls and Components 1 ADC ADS 1 2 Test Switches 2 ADC ADS 1 2 Transfer Switches 3 AHRS IRS Panels 4 Air Data Transfer Switches 5 Altitude Select 6 AP DISC Bu...

Страница 58: ...r 29 Standby Horizon 30 Transfer Panels Reversionary Mode Panels 31 Transponder 32 Yaw Damper NOTE EFIS items are taught on an AS NEEDED basis in an EFIS FMS Trainer c Indicators Indications 1 Airspee...

Страница 59: ...FCS and Pitch Trim e Check navigation radio reception and bearing information and set for departure f Check resistance to movement of rudder aileron and elevator and appropriate move ment of autopilot...

Страница 60: ...rols and Components 1 Check mask and regulator 2 Crew and Passenger Oxygen System 3 Passenger supply c Indicators Indications 1 Oxygen d Servicing Preflight 1 Check Oxygen Quantity 2 Portable Oxygen B...

Страница 61: ...Gradient 6 2nd 3rd and 4th Segment Gradient 7 Takeoff Flight Path Profile and Charts 8 Maximum Landing Weight 9 TODA vs ASDA 10 TORA vs ASDA 11 Max Takeoff Weight for Value of D 12 Approach Climb Gra...

Страница 62: ...R 61 31 f 1 i 1 General Elements a Respiratory System b Circulation System c Hypoxia Effects Causes Symptoms d Other High Altitude Sicknesses e Causes and Effects of Gas Bubble Formation f Causes and...

Страница 63: ...ncept Workload Assessment and Time Management Briefing Reliance on Automation Decision Making and Judgment Stress FLIGHT TRAINING TRAINING HOURS Each flight simulator period is approximately 2 0 hours...

Страница 64: ...L 14 0 14 0 28 0 1 May vary as necessary TRANSITION TRAINING Left Seat Right Seat Total Time As a Crew Hours Hours Hours Flight Simulator Period No 1 2 0 2 0 4 0 Flight Simulator Period No 2 2 0 2 0 4...

Страница 65: ...TOTAL 16 01 0 0 16 0 1 If required TRANSITION TRAINING Left Seat Right Seat Total Time Not as a Crew Hours Hours Hours Flight Simulator Period No 1 2 0 0 0 2 0 Flight Simulator Period No 2 2 0 0 0 2 0...

Страница 66: ...following outlines indicates an optional training item that is the instructor has the option to review this item as time permits The identi fied items are also noted in Chapter 2 Items identified by t...

Страница 67: ...S Self Test Sperry 8 Air Data Computer Test Honeywell Phase III 9 Thrust Reverser Check 10 Computer and Rudder Bias Check 11 APR Check 12 Brake Checks Taxi Before Landing 13 Periodical Systems Check 1...

Страница 68: ...em Sperry 11 AHRS and O Heat Lights On Sperry 12 Air Data Computer Failure Sperry 3 Flight Training Events a Preparation 1 Prestart Procedures b Surface Operation 1 Starting 2 Taxi 3 Pretakeoff Checks...

Страница 69: ...kload Assessment and Time Management e Briefing Reliance on Automation g Decision Making and Judgement h Stress E Simulator Period No 2 Module 1 Normal Procedure Events a Normal Procedure Checklists 1...

Страница 70: ...ase III 9 Thrust Reverser Check 10 Computer and Rudder Bias Check 11 APR Check 12 Brake Checks Taxi Before Landing 13 Periodical Systems Check 14 Solar APU Garrett APU 2 Abnormal Emergency Procedures...

Страница 71: ...ure 15 Auxiliary Fuel Transfer Failure 16 Fuel Management After One Engine Failure c Avionics EFIS 1 Display Processor Failure Collins 2 Display Control Failure Collins 3 EADI Failure Collins 4 EHSI F...

Страница 72: ...Pretakeoff Checks c Takeoff 1 Normal Takeoff 2 Crosswind Takeoff 3 Instrument Takeoff d Climb 1 Normal e En Route 1 Steep Turns 2 Approach to Stall Clean Configuration 3 Approach to Stall Takeoff Flap...

Страница 73: ...ding 1 Parking j Other Flight Procedures 1 Holding k System Procedures Normal Abnormal Altemate 1 Fuel and Oil 2 Electrical 3 Autopilot 4 Flight Management Guidance Systems and or Automatic or other A...

Страница 74: ...a Normal Procedure Checklists 1 Preliminary Cockpit 2 Thru Flight 3 Before Start External APU or Battery 4 Starting Engines Extemal APU or Battery 5 After Start 6 Taxi 7 Before Takeoff 8 Line Up 9 Imm...

Страница 75: ...nding 13 Solar APU Garrett APU 2 Abnormal Emergency Procedures a Engine APU Fuel 1 Engine Fire Warning Inflight 2 Engine Failure 3 Engine Relight 4 Immediate Relight 5 Relight Envelope 6 Starter Assis...

Страница 76: ...ins 4 EHSI Failure Collins 5 EFIS Fan Failure Collins 6 EFIS Fan Failure Sperry 7 EFIS Fan Fail Lts Illuminated Inflight Sperry 8 Electronic Display Indicator Over temperature Sperry 9 EFIS Display Fa...

Страница 77: ...plant Restart f Descent 1 Normal g Approaches 1 Area Departure and Arrival 2 Holding 3 Precision ILS 4 Precision ILS with an Engine Out 5 Nonprecision VOR 6 Nonprecision NDB 7 Nonprecision with an Eng...

Страница 78: ...edures Normal Abnormal Altemate 1 Fuel and Oil 2 Electrical 3 Hydraulic 4 Autopilot 5 Flight Management Guidance Systems and or Automatic or other Approach and Landing Systems 6 Airborne Weather Radar...

Страница 79: ...a Normal Procedure Checklists 1 Preliminary Cockpit 2 Thru Flight 3 Before Start Extemal APU or Battery 4 Starting Engines External APU or Battery 5 After Start 6 Taxi 7 Before Takeoff 8 Line Up 9 Imm...

Страница 80: ...er Bias Check 11 APR Check 12 Brake Checks Taxi Before Landing 13 Solar APU 2 Abnormal Emergency Procedures a Engine APU Fuel 1 Engine Failure 2 Engine Relight 3 Immediate Relight 4 Relight Envelope 5...

Страница 81: ...ollins 5 EFIS Fan Failure Collins 6 EFIS Fan Failure Sperry 7 EFIS Fan Fail Lts Illuminated Inflight Sperry 8 Electronic Display Indicator Over temperature Sperry 9 EFIS Display Failure 10 Flight Guid...

Страница 82: ...erplant Restart 3 High Speed Handling f Descent 1 Normal 2 Maximum Rate Descent g Approaches 1 Area Departure and Arrival 2 Holding 3 Visual Approach with a Flap Malftunction 4 Precision ILS 5 Precisi...

Страница 83: ...ocedures 1 Holding 2 Ice Accumulation on Airframe 3 Air Hazard Avoidance k System Procedures Normal Abnormal Alternate 1 Pneumatic Pressurization 2 Air Conditioning 3 Fuel and Oil 4 Electrical 5 Hydra...

Страница 84: ...and Time Management e Briefing f Reliance on Automation g Decision Making and Judgment h Stress H Simulator Period No 5 Module 1 Normal Procedure Events a Normal Procedure Checklists 1 Preliminary Coc...

Страница 85: ...Check 10 Computer and Rudder Bias Check 11 APR Check 12 Brake Checks Taxi Before Landing 13 Solar APU Garrett APU 2 Abnormal Emergency Procedures a Electrical 1 Double Generator Failure 2 Single Gener...

Страница 86: ...APU Fire 14 APU Failure 15 Engine Fuel Malfunction 16 Fuel Low Pressure 17 Auxiliary Fuel Transfer Failure 18 Fuel Management After One Engine Failure c Pressurization Pneumatics 1 Depressurization o...

Страница 87: ...Collins 2 Display Control Failure Collins 3 EADI Failure Collins 4 EHSI Failure Collins 5 EFIS Fan Failure Collins 6 EFIS Fan Failure Sperry 7 EFIS Fan Fail Lts Illuminated Inflight Sperry 8 Electroni...

Страница 88: ...owerplant Shutdown 2 Inflight Powerplant Restart f Descent 1 Normal 2 Maximum Rate Descent Emergency Descent g Approaches 1 Area Departure and Arrival 2 Navigation Equipment and Assigned Radials 3 Hol...

Страница 89: ...e 3 Air Hazard Avoidance 4 Windshear Microburst k System Procedures Normal Abnormal Alternate 1 Pneumatic Pressurization 2 Air Conditioning 3 Fuel and Oil 4 Electrical 5 Hydraulic 6 Flight Controls 7...

Страница 90: ...and Time Management e Briefing f Reliance on Automation g Decision Making and Judgment h Stress I Simulator Period No 6 Module 1 Normal Procedure Events a Normal Procedure Checklists 1 Preliminary Coc...

Страница 91: ...erser Check 10 Computer and Rudder Bias Check 11 APR Check 12 Brake Checks Taxi Before Landing 13 Solar APU 2 Abnormal Emergency Procedures a Electrical 1 Double Generator Failure 2 Single Generator F...

Страница 92: ...APU Fire 14 APU Failure 15 Engine Fuel Malfunction 16 Fuel Low Pressure 17 Auxiliary Fuel Transfer Failure 18 Fuel Management After One Engine Failure c Pressurization Pneumatics 1 Depressurization o...

Страница 93: ...ent During Flight 2 Thrust Reverser Malfimctions In Flight 3 Landing with One Thrust Reverser Deployment g Avionics EFIS 1 Display Processor Failure Collins 2 Display Control Failure Collins 3 EADI Fa...

Страница 94: ...ejected Aborted Takeoff 4 Instrument Takeoff 5 Power Failure V1 at or above V1 6 Lower than Standard Minimum Takeoff FAR 135 clients only d Climb 1 Normal e En Route 1 Steep Turns 2 Approach to Stall...

Страница 95: ...s 1 Normal Landing 2 Landing from a Precision Instrument Approach 3 Landing with a Flap Malfunction 4 Crosswind Landing 5 Maneuver to Landing with a Powerplant Failure from a Visual Approach 6 Landing...

Страница 96: ...ctrical Systems 5 Hydraulic Systems 6 Pneumatic Systems 7 Flight Control Systems Malfunction 8 Landing Gear and Flap System Malfunction 4 Crew Resource Management a Situational Awareness and the Error...

Страница 97: ...t b Functional Checks 1 EFIS Ground Test Collins 2 Air Data Computer Check Collins 3 Individual Instrument Test Collins 4 Pre Flight Check Autopilot and Flight Guidance System if applicable 5 Electric...

Страница 98: ...Circling Approach d Landings 1 Normal 2 Simulated Single Engine 3 Crosswind 4 From a Circling Approach K Line Orientated Flight Training Transition 1 LOFT Period No I a LOFT Flight Events 1 Route of F...

Страница 99: ...r flights In all cases it is ex pected that the pilot should strive to meet the tolerances listed below 1 Takeoff a Heading 5 b Airspeed 5 KIAS 2 Departure Cruise Holding and Arrival a Altitude 100 Fe...

Страница 100: ...H 0 Feet Prior to Initiating Missed Approach 4 Airspeed 5 0 KIAS 7 Circling to Land a Altitude 100 0 Feet b Heading 5 c Bank Angle Should Not Exceed 30 d Airspeed 5 KIAS 8 Missed Approach a Altitude 1...

Страница 101: ...Lighting 1 16 Master Warning System 1 17 Fuel System 1 17 Auxiliary Power Unit 1 17 Powerplant 1 17 Fire Protection 1 17 Pneumatics 1 18 Ice and Rain Protection 1 18 Air Conditioning 1 18 Pressurizati...

Страница 102: ...1 ii FOR TRAINING PURPOSES ONLY HAWKER 800 XP PILOT TRAINING MANUAL FlightSafety international Pitot Static System 1 19 Avionics 1 19 Oxygen System 1 19...

Страница 103: ...tment Typical 1 8 1 8 Pilot s Seat 1 7 1 9 Vestibule Arrangement 1 10 1 10 Cabin Arrangement Typical 1 9 1 11 Main Entry Door 1 11 1 12 Escape Hatch 1 12 1 13 Emergency Equipment Locations 1 13 1 14 H...

Страница 104: ......

Страница 105: ...airplane appearance or system operation will be covered during academic train ing and in subsequent revisions to this manual Annunciator panel in this manual displays all light indicators and page AN...

Страница 106: ...is provided by batteries Where AC power is required it is supplied by either engine driven alternators 208 V three phase or static inverters A fluid anti icing system is installed along the leading ed...

Страница 107: ...ternational 1 3 FOR TRAINING PURPOSES ONLY Figure 1 2 Airplane Dimensions 21 FT 0 5 IN 6 41 M WHEELBASE 17 FT 5 IN 5 31 M OVERALL HEIGHT 9 FT 2 IN 2 79 M TRACK 51 FT 4 5 IN 15 66 M WING SPAN 51 FT 1 6...

Страница 108: ...OSES ONLY LEGEND AREA TO BE CLEARED PRIOR TO ENGINE START AREA TO BE CLEARED IF TAKEOFF POWER IS TO BE USED FULL THROTTLE TEMPERATURE BELOW 30 C FULL THROTTLE VELOCITY FALLS BELOW 15 MPH 16 FT RADIUS...

Страница 109: ...lot s transfer panel will illu minate TheEFIS FAULTannunciatorcanbecan celed by pressing the face of the annunciator Pressurized Center Section The pressurized center section extends from the forward...

Страница 110: ...HAWKER 800 XP PILOT TRAINING MANUAL FlightSafety international 1 6 FOR TRAINING PURPOSES ONLY Figure 1 6 Cockpit Layout Typical...

Страница 111: ...l over come the spring loading allowing the pad to move downward When the pressure on the thigh pad is relaxed the pad returns to its pre set condition The recline control handle is pulled upward to a...

Страница 112: ...AGE NOSWHEEL STEERING OXYGEN PASSENGER EMERGENCY SUPPLY SELECTOR KNOB AND CONTENTS INDICATOR CHART AND MAP STOWAGE AUXILIARY HYDRAULIC SYSTEM SELECTOR HANDLE CENTER CONTROL PEDESTAL INSTRUMENT PANELS...

Страница 113: ...ment An upper compartment is used for stowing therapeutic oxygen masks and a first aid kit A lower compartment pro vides stowage for airplane manuals and doc uments On the lower rear face of the cabin...

Страница 114: ...HAWKER 800 XP PILOT TRAINING MANUAL FlightSafety international 1 10 FOR TRAINING PURPOSES ONLY Figure 1 9 Vestibule Arrangement...

Страница 115: ...drail are provided The door is counterbalanced by a spring loaded tensator motor and secured by external and in ternal handles The external handle installed flush with the fuselage and forward of the...

Страница 116: ...ground security latch incorporates a REMOVE FOR FLIGHT flag Emergency Equipment Following is a list of standard and optional emergency equipment available on the Hawker 800 XP Figure 1 13 Hand fire e...

Страница 117: ...HAWKER 800 XP PILOT TRAINING MANUAL FlightSafety international 1 13 FOR TRAINING PURPOSES ONLY Figure 1 13 Emergency Equipment Locations...

Страница 118: ...onnected to a silica gel container at the rear of each win dow Figure 1 15 All cabin windows see note share a common silica gel container mounted in the forward baggage compartment NOTE The window ins...

Страница 119: ...ilon is on the bottom surface of the wing leading edge inboard of the inner end of the row of vor tex generators The stall trigger is attached to the anti icing distributor inboard of the land ing lam...

Страница 120: ...trical system backup power and a power source for internal engine start ing An external power unit can be connected via a three pin plug to energize the bus bars for servicing and engine starting Two...

Страница 121: ...ar fuselage Firewalls divide each pod into two fire zones which are ventilated by ram air both zones in corporate a fire overheat warning system The two shot fire extinguishing system discharges only...

Страница 122: ...oling turbine The bleed air then flows to the three wheel cold air unit where the conditioned air temperature is reg ulated by the amount of air allowed to pass through the turbine The more air that p...

Страница 123: ...ipelines The pitot heads and forward static vent plates are heated to prevent icing AVIONICS Standard avionics includes the EFIS 86 E or SPZ 8000 Electronic Flight Instrument Systems The system consis...

Страница 124: ......

Страница 125: ...19 Ground Power 2 20 Distribution 2 21 Operation 2 21 AC POWER 2 22 Inverters 2 22 Control and Operation 2 23 Distribution 2 23 Operation 2 23 ELECTRICAL POWER SOURCES 2 25 Emergency Battery Supply 2...

Страница 126: ......

Страница 127: ...ower Generation Configuration No 4 2 12 2 12 Power Generation Configuration No 5 2 13 2 13 Power Generation Configuration No 6 2 14 2 14 Power Generation Configuration No 7 2 15 2 15 Power Generation...

Страница 128: ...er System 2 24 TABLES Table Title Page 2 1 Electrical Component Listing 2 4 2 2 Inverter Controls and Locations 2 22 2 iv FOR TRAINING PURPOSES ONLY HAWKER 800 XP PILOT TRAINING MANUAL FlightSafety in...

Страница 129: ...Two additional batteries are also provided one for standby instrument power and the other for emergency avionics power The DC sup ply from the generators and batteries has a positive polarity and use...

Страница 130: ...e the bus tie must be closed to power both PS1 and PS2 Inverters powered from the airplane DC system provide 115 volts AC for the operation of vari ous airplane systems and navigation equipment Each o...

Страница 131: ...Figure 2 3 Main Distribution Panel DA D PANEL TOP ROWS A H DA D PANEL BOTTOM ROWS J S A GENERAL PURPOSE CBs SUBPANEL DA D STORM LAMP AVIONICS CBs SUBPANEL DA D FUSES F1 TO F30 SUBPANEL DA C RELAYS SUB...

Страница 132: ...ternal power source for engine starting Start control circuits are supplied from the main batteries via the PE bus bar See Figure 2 5 Electrical controls indicators and compo nent locations are shown...

Страница 133: ...on line both emergency contactors remain closed and a battery is connected to the bus bar via closure of the appropriate battery contactor When the buses are tied both battery contactors close to con...

Страница 134: ...ernal starting should be used when exter nal power is not available In these conditions pressing the START PWR switch energizes an internal start contactor to connect No 1 and No 2 batteries to a star...

Страница 135: ...No 2 batteries are electrically connected to the indicator via a rotary selec tor switch and a push button switch Figure 2 6 The relevant battery temperature is indicated when the pushbutton is press...

Страница 136: ...ch selection The PE bus bar remains energized during a nor mal internal start For either type of start the starting sequence may be terminated at any time by a second applica tion of the START PWR swi...

Страница 137: ...GEN LINE CONTACTOR NO 1 BATTERY CONTACTOR NO 1 EMERGENCY CONTACTORS BATT 1 CNTCTR BATT 2 CNTCTR BATT 2 BATT 1 BATTERY CONTACTOR NO 2 BUSTIE CONTACTOR PE2 PE BUS GEN LINE CONTACTOR NO 2 GEN SHUNT NO 1...

Страница 138: ...CONTACTOR NO 1 EMERGENCY CONTACTORS BATT 1 CNTCTR BATT 2 CNTCTR BATT 2 BATT 1 BATTERY CONTACTOR NO 2 BUSTIE CONTACTOR PE BUS GEN LINE CONTACTOR NO 2 GEN SHUNT NO 1 GEN SHUNT NO 2 APU GEN SHUNT 500 A...

Страница 139: ...ERY CONTACTOR NO 1 EMERGENCY CONTACTORS BATT 1 CNTCTR BATT 2 CNTCTR BATTERY CONTACTOR NO 2 BUSTIE CONTACTOR PE BUS GEN LINE CONTACTOR NO 2 GEN SHUNT NO 1 GEN SHUNT NO 2 APU GEN SHUNT 500 A 500 A APU G...

Страница 140: ...OR NO 1 EMERGENCY CONTACTORS BATT 1 CNTCTR BATT 2 CNTCTR BATT 2 BATT 1 BATTERY CONTACTOR NO 2 BUSTIE CONTACTOR PE BUS GEN LINE CONTACTOR NO 2 GEN SHUNT NO 1 GEN SHUNT NO 2 APU GEN SHUNT 500 A 500 A AP...

Страница 141: ...MERGENCY CONTACTORS BATT 1 CNTCTR BATT 2 CNTCTR BATT 2 BATT 1 BATTERY CONTACTOR NO 2 BUSTIE CONTACTOR PE BUS GEN LINE CONTACTOR NO 2 GEN SHUNT NO 1 GEN SHUNT NO 2 APU GEN SHUNT 500 A 500 A APU GEN CON...

Страница 142: ...ONTACTORS BATT 1 CNTCTR BATT 2 CNTCTR BATT 2 BATT 1 BATTERY CONTACTOR NO 2 BUSTIE CONTACTOR PE BUS GEN LINE CONTACTOR NO 2 GEN SHUNT NO 1 GEN SHUNT NO 2 APU GEN SHUNT 500 A 500 A APU GEN CONTACTOR STA...

Страница 143: ...OR NO 1 BATTERY CONTACTOR NO 1 EMERGENCY CONTACTORS GPU CONNECTED EXTERNAL POWER SWITCH ON EXTERNAL BATTERY CHARGING SWITCH ON BATT 1 CNTCTR BATT 2 CNTCTR BATTERY CONTACTOR NO 2 BUSTIE CONTACTOR PE2 G...

Страница 144: ...CONTACTOR NO 1 EMERGENCY CONTACTORS BATT 1 CNTCTR BATT 2 CNTCTR BATT 2 BATT 1 BATTERY CONTACTOR NO 2 BUSTIE CONTACTOR PE BUS GEN LINE CONTACTOR NO 2 GEN SHUNT NO 1 GEN SHUNT NO 2 APU GEN SHUNT 500 A...

Страница 145: ...ACTOR NO 1 EMERGENCY CONTACTORS BATT 1 CNTCTR BATT 2 CNTCTR BATT 2 BATT 1 BATTERY CONTACTOR NO 2 BUSTIE CONTACTOR PE BUS GEN LINE CONTACTOR NO 2 GEN SHUNT NO 1 GEN SHUNT NO 2 APU GEN SHUNT 500 A 500 A...

Страница 146: ...rators when the systems are paralleled and serviceable The voltage sensing unit opens the bus tie con tactor automatically when an overvoltage or undervoltage condition occurs on the main bus bar The...

Страница 147: ...ermissible discrepancy be tween readings is 40amperes When the BATT button is pressed the charge rates of No 1 and No 2 batteries are indicated If the battery charge rate cannot be read eas ily on the...

Страница 148: ...upply contactor Contactor operation is controlled by an EXT PWR ON OFF switch supplied from the third pin of the ground supply plug Switching EXT PWR on refer to Figure 2 20 connects the ground power...

Страница 149: ...the rear equipment bay area These panels contain circuits and fuses for certain es sential services A negative ground return is provided through the airplane structure via grounding points below the p...

Страница 150: ...rter feeds XS1 and XE distribution lines and the No 2 inverter feeds XS2 Either in verter is however capable of feeding all dis tribution lines and changeover is achieved automatically if one inverter...

Страница 151: ...rter to XE XS1 and XS2 lines the contactor is deener gized and the failed main inverter shuts off With the changeover complete the XS1 XS2 and XE FAIL annunciators of the serviceable inverter remain o...

Страница 152: ...STBY INV ARM OFF STBY INV ON STANDBY INVERTER INV 2 START STOP INV 2 FAIL NO 2 INVERTER STALL VANE HEAT MAGNETIC CIRCUIT BREAKER MAGNETIC CIRCUIT BREAKER XS1 BUS XS2 FAIL XE FAIL XS1 FAIL NO 2 6 26 VA...

Страница 153: ...ural warning will sound The aural warning may be canceled by depressing the horizon warn cancel pushbut ton adjacent to the standby horizon In addition to the above the standby altime ter and airspeed...

Страница 154: ...tandard three pin 28 VDC external power receptacle is located in the right rear fuselage For external starts a ground power unit ca pable of supplying 28 VDC with a minimum output of 42 kW short term...

Страница 155: ...rs C Positioning the GEN switch to CLOSE then releasing it D Turning the EXT PWR switch to ON 5 The battery charging rate can be moni tored by A Depressing the BATT ammeter push button B Turning off o...

Страница 156: ......

Страница 157: ...4 Emergency Lighting 3 5 Rear Equipment Bay Lighting 3 6 EXTERIOR LIGHTING 3 7 Navigation Lights 3 7 Landing and Taxi Lights 3 7 Anticollision Beacons 3 7 Strobe Lights 3 7 Wing Ice Inspection Spotli...

Страница 158: ......

Страница 159: ...rning Sign Switches 3 4 3 6 Vestibule Lighting Switch 3 4 3 7 Emergency Lighting Controls Cockpit 3 5 3 8 Emergency Light Switch 3 5 3 9 EXIT Light 3 5 3 10 EMERG LTS OFF Light 3 6 3 11 Rear Compartme...

Страница 160: ......

Страница 161: ...he lower canopy rail and under the main instrument panel glareshield The lights are controlled by a dimmer switch on the panel lights section of the left or right glareshields labeled PANEL LTS FLOOD...

Страница 162: ...he tail cone Two wing ice inspection lights INTERIOR LIGHTING COCKPIT LIGHTING The cockpit lighting consists of floodlights edge lighting of panels and internal lighting of instruments Most of the lig...

Страница 163: ...and right glareshields Figure 3 3 Supply is from the PS1 bus bar Storm Lights Three lights are provided to give high inten sity white light to prevent crew flash blindness during lightning conditions...

Страница 164: ...Entrance and vestibule illumination is pro vided by two step lights and a roof mounted twin light assembly One step light mounted on the left side of the entrance and one light of the twin light assem...

Страница 165: ...ormally con trolled by the CTR PANEL dimmer switch on the left glareshield A box containing a number of spare bulbs is fit ted at the base of the main distribution sidewall Passenger Compartment Emerg...

Страница 166: ...o lights on each side of emergency escape hatch Escape hatch external lamp overwing escape route External right wing leading edge to ground area lamp These lights automatically illuminate when elec tr...

Страница 167: ...set by the PS2 bus bar The radome mounted nose taxi lights are powered by PS1 left and PS2 right and will illuminate any time when either the wing landing lights or wing taxi lights are turned ON ANTI...

Страница 168: ...ilable for a logo light system ELECTRICAL POWER SOURCES PE bus bar CB panels spot CB panels wander Chart left and right Instrument panels emer Standby compass Navigation Left landing Left taxi PS1 bus...

Страница 169: ...SMKG switch is positioned to AUTO the NO SMOKING light will il luminate when A A downward force of 1 5 g is felt B The nose gear locks down during ex tension C Cabin altitude reaches 1 500 feet D The...

Страница 170: ......

Страница 171: ...IM FUNCTION 4 5 SYSTEM OPERATION 4 5 AUDIBLE WARNINGS 4 5 Engine Fire Detection 4 6 Landing Gear Horn Warning 4 6 Airbrakes Horn Warning 4 6 Throttles below 50 60 RPM 4 6 Speed Warning 4 7 Testing 4 7...

Страница 172: ......

Страница 173: ...Switch 4 6 4 3 Landing Gear Horn Cancel Button 4 6 TABLES Figure Title Page 4 1 Center Annunciator Panel 4 2 4 2 Ice Protection 4 3 4 3 Fuel 4 4 4 4 DC Power 4 4 4 5 AC Power 4 4 4 6 Engine Fire Ligh...

Страница 174: ......

Страница 175: ...he warning annunciator light to dim If the fault causing the annunciator to illuminate is corrected the annunciator automatically extinguishes Should the fault not be corrected the annun ciator remain...

Страница 176: ...of the duplicated red warning circuits Pressing the face of either light cancels both red flashing lights In normal conditions even when the lights are not illuminated this ac tion also reduces light...

Страница 177: ...ir is not available for anti icing Annunciator Cause for Illumination An annunciator on the ICE PRO TECTION roof panel is illumi nated An annunciator on either DC or AC power roof panels is illumi nat...

Страница 178: ...osition Auxiliary fuel transfer lever is in the open position Wing fuel crossfeed transfer lever is in crossfeed or transfer position Fuel pressure in the supply line to the respective engine is low E...

Страница 179: ...on pressing the MWS red lights has no effect on the intensity of any annunciator SYSTEM OPERATION When a system status change or fault occurs the appropriate individual annunciator illu minates at max...

Страница 180: ...f the down position and start power selected the horn also sounds In either cir cumstance the horn cannot be overridden AIRBRAKES HORN WARNING The horn gives a continuous steady note if the gear is do...

Страница 181: ...ABIN ALTITUDE light on the master warning panel to illuminate at full brilliance The red MWS annunciators on the glareshield to flash NOTE With flaps lowered beyond 15 the cabin altitude warning horn...

Страница 182: ...tem is off C A system malfunction D A system failure 4 The bus bar that powers the master warn ing system is A PS1 B PE C PS2 D XE 5 The master warning lights can be extin guished by A Resetting the M...

Страница 183: ...ank 5 2 Vent System 5 2 Capacities 5 2 FUEL DISTRIBUTION 5 2 CONTROLS AND INDICATORS 5 4 Controls 5 4 Indicators 5 5 REFUELING 5 6 ELECTRICAL POWER SOURCES 5 9 LIMITATIONS 5 10 Fuel Loading 5 10 Fuel...

Страница 184: ......

Страница 185: ...4 Fuel Indicators 5 6 5 5 Ventral Tank Filler Cap 5 7 5 6 Refueling Control Panel 5 7 5 7 Pressure Refuel Defuel Coupling 5 8 5 8 Refueling System and Vent Lines 5 9 TABLE Figure Title Page 5 1 Fuel C...

Страница 186: ......

Страница 187: ...en gine during normal operating conditions Each boost pump operates two jet pumps The jet pumps transfer fuel from the outer portion of the wing tanks and the ventral tank to the fuel sump compartmen...

Страница 188: ...pressure throughout the vent system during flight A water drain is provided for each surge tank The ventral tank vents into the left wing surge tank Refer to Figure 5 8 this chapter CAPACITIES The win...

Страница 189: ...CROSSFEED VALVE NO 1 COMPARTMENTS HIGH PRESSURE SUCTION PRESSURE SWITCH TEMP BULB CHECK VALVE FLAPPER VALVE BOOST PUMP JET PUMP TEMP BULB HAWKER 800 XP PILOT TRAINING MANUAL FlightSafety internationa...

Страница 190: ...emperature bulb permits a fuel tem perature indication to be read from the num ber one engine fuel supply line The fuel in each engine fuel supply line passes through a flowmeter on each engine CONTRO...

Страница 191: ...nate when the fuel pressure in the engine fuel line falls below 7 psi The illumination of either light is repeated by an amber annunciator on the MWS center panel labeled FUEL A white AUX FUEL TFR ann...

Страница 192: ...ntral tank low level float switch maintains a circuit to provide low VMO speed warning at 280 KIAS until ventral tank fuel has been transferred REFUELING The airplane can be gravity refueled through a...

Страница 193: ...HAWKER 800 XP PILOT TRAINING MANUAL FlightSafety international 5 7 FOR TRAINING PURPOSES ONLY Figure 5 6 Refueling Control Panel COVER OPEN Figure 5 5 Ventral Tank Filler Cap...

Страница 194: ...valve Additionally each wing tank and the ventral tank has an electrically operated refuel valve Each tank refuel valve can be mechanically po sitioned in the event of electrical failure Magnetic ind...

Страница 195: ...MANUAL FlightSafety international HIGH LEVEL FLOAT SWITCH VENT FLOAT VALVE VENT SURGE TANK OVERFILL INDICATOR FLOAT SWITCH PRESSURE SWITCH VENTRAL TRANSFER VALVE THERMAL RELIEF VALVE PRESSURE REDUCIN...

Страница 196: ...filled or empty FUEL MANAGEMENT During flight including takeoff and landing the maximum difference in fuel quantity be tween the wing tanks is 500 pounds Fuel carried in the ventral tank shall be tra...

Страница 197: ...lateral imbalance permit ted is A 250 pounds B 500 pounds C 750 pounds D 1 000 pounds 6 With both boost pumps inoperative A Leave the AUX FUEL TRANSFER lever open B Fuel will gravity transfer C Both...

Страница 198: ......

Страница 199: ...nd Indications 6 3 TURBOMACH APU T62T 40 6 8 General 6 8 Major Sections 6 8 Oil System 6 10 Fuel System 6 10 Ignition System 6 10 Control and Indications 6 10 Protection 6 12 APU Starting 6 13 ELECTRI...

Страница 200: ......

Страница 201: ...Garrett APU 6 3 6 2 APU Control Panel 6 4 6 3 Turbomach APU Typical 6 8 6 4 Major Sections Turbomach APU 6 9 6 5 APU Control Panel Turbomach APU 6 11 FOR TRAINING PURPOSES ONLY HAWKER 800 XP PILOT TR...

Страница 202: ......

Страница 203: ...ane may have an APU manufactured by the Garrett Turbine Engine Company GTCP 36 150 or by Solar Turbines Incorporated T62T 40 Some in stallations are approved for in flight use without restrictions Bot...

Страница 204: ...issible electrical load on the Lear Siegler 23080 015 starter generator is 300 amp maximum Shut Down Shut down APU if READY TO LOAD light does not illuminate within 60 seconds of start Do not operate...

Страница 205: ...are as follows DC LOAD Indicator Indicates current being generated by the APU RPM Indicator APU revolutions per minute EGT Indicator APU exhaust gas tem perature EGT F MAIN TEST OVV Switch Tests gen...

Страница 206: ...tiates action to the ECU to shutdown APU Manually discharges fire extinguisher LOW OIL PRESS Annunciator Illuminates amber when oil pressure is less than 35 psig APU shuts down HIGH OIL TEMP Annunciat...

Страница 207: ...auge Monitor start cycle Check a Below 50 RPM Max 760 C to 870 C for 15 sec 870 C to 974 C for 10 sec b Below 95 RPM Loss of acceleration hung start Do not exceed 10 secs 13 APU LOW OIL PRESS Extingui...

Страница 208: ...limits Bleed Air Only Remove Electrical Load 1 GEN switch OFF 2 APU GEN Illuminates 3 Ammeter Check reads zero Electrical Load Only Remove Bleed Load 1 BLEED AIR switch OFF 2 BLEED AIR ON Extinguished...

Страница 209: ...P switch Depress 2 MASTER switch OFF Wait 3 minutes to allow fuel to drain off before attempting another start Emergency Procedures APU Fire In the event of a fire in the APU enclosure the APU FIRE bu...

Страница 210: ...ximum altitude of 15 000 feet emergency only MAJOR SECTIONS The Solar APU Figure 6 4 is a small gas tur bine engine consisting of six major sections 1 Air inlet 2 Compressor 3 Combustor 4 Turbine 5 Ex...

Страница 211: ...from the turbine is reversed to flow aft to the exhaust Exhaust The exhaust consists of an exhaust duct and an exhaust pipe to direct the spent gases to the atmosphere through an outlet on the right...

Страница 212: ...exciter to a single ig niter plug in the combustor Ignition is operational from the initiation of the startup to 90 rpm when it is terminated by a speed sensing switch Electronic Sequence Unit ESU Th...

Страница 213: ...lightSafety international APU D C A B APU MSTR SW ON DETAIL A APU CONTROL PANEL DETAIL D PART OF PANEL ZK DETAIL C HOURMETER DETAIL B MWS CENTER PANEL HOURMETER START COUNTER APU FIRE RESET SWITCH CIR...

Страница 214: ...n light marked GEN ON DC BUS This light will illuminate to indicate that the APU starter generator is supplying DC power to the distribution system The amber GENERATOR OVERHEAT light will come on if t...

Страница 215: ...ease the switch and monitor the EGT gage NOTE EGT will increase when the APU generator is turned on A start inhibit facility prevents APU starting while on external power and the EXT BATT CHG switch l...

Страница 216: ...e 2 If EGT increases or rpm hangs or de creases during a start A Turn off the BLEED AIR switch B Turn off the APU MASTER switch C Discharge the APU fire bottle D Trip the generator 3 Do not operate AP...

Страница 217: ...PONENTS 7 2 DESCRIPTION 7 3 Fan 7 3 Operation 7 5A ENGINE SYSTEMS 7 6 Engine Oil 7 6 Ignition 7 9 FUEL CONTROL 7 10 Introduction 7 10 Fuel Pump 7 10 Fuel Control Unit 7 10 POWER CONTROL 7 15 Introduct...

Страница 218: ...24 THRUST REVERSER SYSTEM 7 24 General 7 24 Thrust Reverser Assembly 7 24 Controls and Indicators 7 26 System Operation 7 28 Automatic Throttle Retard 7 32 Electrical Power 7 33 Normal Condition Manag...

Страница 219: ...l 7 8 7 7 Engine Ignition Switches 7 9 7 8 Fuel System 7 11 7 9 Engine Computer Switches 7 12 7 10 Fuel Computer Engine Interface 7 13 7 11 Engine Fuel Annunciators 7 14 7 12 Fuel Controls 7 16 7 13 E...

Страница 220: ...r System Armed 7 29 7 26 Thrust Reverser System Overstow and Unlatch 7 30 7 27 Thrust Reverser System Deploy 7 30 7 28 Thrust Reverser System Normal Stow Cycle 7 31 7 29 Thrust Reverser System Autosto...

Страница 221: ...HAWKER 800 XP PILOT TRAINING MANUAL FlightSafety international 7 v TABLES Table Title Page 7 1 Engine Operating Conditions 7 35 FOR TRAINING PURPOSES ONLY...

Страница 222: ......

Страница 223: ...actured by Garrett Turbine Engine Company at Phoenix Arizona a division of Allied Signal The engines are designated TFE731 5BR 1H The TFE series engines are lightweight twin spool turbofans The modula...

Страница 224: ...illustrates a typical 731 series engine MAJOR COMPONENTS The engine consists of five major components Fan Low Pressure LP Spool High Pressure HP Spool Annular Combustion Chamber Transfer and Accessor...

Страница 225: ...ties of air into the bypass and core inlets The bypass section consists of the fan spinner support fan rotor assembly fan bypass stator fan duct assembly and the by pass fan support and shaft section...

Страница 226: ...is picked up and accelerated outwards towards the diffuser When the accelerating air reaches the diffuser its velocity is reduced converting kinetic energy into pressure The high pressure spool also...

Страница 227: ...the bypass air before discharging through a convergent di vergent nozzle The high pressure turbine rotor assembly is air cooled to allow an increased turbine inlet temperature A lobed mixer nozzle fit...

Страница 228: ...er instrument panel and this displays the average interstage turbine temperature ITT The indicator displays ITT from 0 C to 1 200 C in 50 C increments with colored bands to indicate different temperat...

Страница 229: ...the single stage fan draws air in through the nacelle inlet duct The outer diameter of the fan accelerates a moderately large air mass at a low velocity into the full length bypass duct At the same t...

Страница 230: ...de Engine Oil Ignition Fuel Control Power Controls Air Bleed Automatic Performance Reserve APR Thrust Reverser ENGINE OIL Oil under pressure lubricates the engine bearings and the transfer accessory a...

Страница 231: ...of the engine fan by pass housing Engine protection against filter clogging is provided by an oil filter bypass indicator valve located adjacent to the oil filter The valve opens when the pressure dro...

Страница 232: ...main sump areas oil then drains by gravity to the lowest point of each sump The scavenge pumps then draw the oil back to the engine oil reservoir Oil Venting Vent lines interconnect the oil sumps to...

Страница 233: ...o the igniter plugs During the engine start cycle a microswitch on each HP fuel lever provides ignition unit activation Once the engine reaches self sus taining speed the relays deenergize to remove p...

Страница 234: ...booster pump to prevent icing of the fuel fil ter element Filter Bypass The filter bypass valve allows fuel to bypass the filter if an excessive pressure drop across the filter occurs An electrical p...

Страница 235: ...NG FUEL TANK ENGINE DRIVEN BOOST PUMP FILTER ANTI ICE VALVE HIGH PRESSURE PUMP ELEMENT 6 5 PSID 88 C PUMP DISCHARGE HYDROMECHANICAL FUEL METERING UNIT BYPASS RETURN FUEL PUMP ASSEMBLY SUPPLY LEGEND PU...

Страница 236: ...e acceleration and provides precise repeatable N1 control for all engine operating regimes This control does not require engine trimming Two digital electronic engine controls DEECs are located in the...

Страница 237: ...IR BYPASS CORE INLET AIR COMPRESSED AIR COMBUSTION AIR EXHAUST AIR COMPUTER OUTPUTS COMPUTER INPUTS N2 PT2 N1 TT2 LOW PRESSURE SPOOL SPEED HIGH PRESSURE SPOOL SPEED ENGINE INLET TOTAL PRESSURE ENGINE...

Страница 238: ...n Fuel Flow Divider Assembly The fuel flow divider is between the fuel con trol unit ant the fuel atomizers During the en gine start the divider routes fuel at a reduced pressure to the primary atomiz...

Страница 239: ...hrottle movements and engine pa rameters the digital electronic engine coontrol DEEC provides an electric signal to the hydro mechanical fuel control unit torque motor The fuel control unit either dec...

Страница 240: ...nal CONTROLS IN PEDESTAL THROTTLE CABLE CONTROL HP FUEL COCK CABLE CONTROL THROTTLE LEVER HP COCK LEVER TELEFLEX HP FUEL COCK LEVER STOP BOLT IDLE THROTTLE HP COCK LEVER LINKAGE HYDRAULIC SHUTOFF COCK...

Страница 241: ...ynchro nization of the engines Using the three posi tion ENG SYNC switch Figure 7 13 synchronization of either the low pressure fan N1 or the high pressure turbine N2 speeds can be selected in the coc...

Страница 242: ...ng events occur The anti icing valve deenergizes open and high pressure air from the HP com pressor and is ducted forward to anti ice the nacelle inlet cowl Electrical power is supplied to PT2 and TT2...

Страница 243: ...or during any subsequent system failure the pressure switch will register a low pressure condition and the appropriate ENG A ICE an nunciator will be lit at the MWS dim pre set level Figure 7 16 The a...

Страница 244: ...gs The rudder bias system receives power from the LP bleed air system only AUTOMATIC PERFORMANCE RESERVE APR INTRODUCTION The APR system when armed allows an au tomatic increase in engine performance...

Страница 245: ...nterstage turbine temperature ITT rising approximately 18 C max Automatic Mode In auto mode the system functions in con junction with the engine synchronizer system When armed APR will be triggered au...

Страница 246: ...ee the Aircraft Maintenance Schedule for further details Therefore override selection of APR should only be made when it is essential to do so To cancel APR mode after override selection both the APR...

Страница 247: ...mode Manual O RIDE is independent of N2 signals An engine fuel computer must be serviceable and selected to AUTO in order to respond to APR Should an engine computer fail or is se lected to manual wi...

Страница 248: ...thrust reverser assembly at the rear of each engine nacelle and various controls and indicators located within the cockpit THRUST REVERSER ASSEMBLY Each thrust reverser assembly Figure 7 21 is an ele...

Страница 249: ...THRUST REVERSER HYDRAULIC ACCUMULATOR FRAME 21 FRAME 22 CONTROL SELECTOR VALVE FAIRING BRACKET LINK BOLT LINK BOLT ATTACHMENT BOLT FAN FLAP FAN FLAP ACTUATOR LATCH BOX ACTUATING ARM DOOR ACTUATING ARM...

Страница 250: ...rom reverse idle to maximum reverse thrust for its respective engine Each throttle has a solenoid operated throttle balk lockout which mechanically prevents selection of reverse thrust until the rever...

Страница 251: ...CTOR LEVER MOVED FROM STOW AND DETENTED AT DEPLOY THROTTLE AT IDLE STOP FACE SPRING STOP ROLLER BALK LINK INTEGRAL SPIGOT SOLENOID OPERATED BALK PAWL REVERSE THRUST SELECTOR LEVER AT FULL REVERSE THRU...

Страница 252: ...loy the reverser doors and extend the fan flaps into the engine bypass airstream The UNLCK and REVRS annun ciators are now illuminated Figure 7 27 After initial deployment the reverse thrust lever bal...

Страница 253: ...ACCUMULATOR PRESSURE GAGE CHECK VALVE TO OPPOSITE TR SYSTEM PRIMARY ACTUATOR FROM AIRPLANE HYDRAULIC SYSTEM Figure 7 24 Thrust Reverser System Deenergized HYDRAULIC PRESSURE RETURN AIR PRESSURE LEGEN...

Страница 254: ...OR PRESSURE GAGE CHECK VALVE TO OPPOSITE TR SYSTEM PRIMARY ACTUATOR FROM AIRPLANE HYDRAULIC SYSTEM Figure 7 26 Thrust Reverser System Overstow and Unlatch HYDRAULIC PRESSURE RETURN AIR PRESSURE LEGEND...

Страница 255: ...LATOR PRESSURE GAGE CHECK VALVE TO OPPOSITE TR SYSTEM PRIMARY ACTUATOR FROM AIRPLANE HYDRAULIC SYSTEM Figure 7 28 Thrust Reverser System Normal Stow Cycle HYDRAULIC PRESSURE RETURN AIR PRESSURE LEGEND...

Страница 256: ...rear of the engine check that fan flaps are retracted Reverser doors can be deployed with out the engines operating If the re verser doors are deployed they must be stowed before engine start One cre...

Страница 257: ...NORMAL CONDITION MANAGEMENT Illumination of Thrust Reverser ARM or UNLCK Annunciator during Flight If the ARM or UNLCK annunciators illuminate in flight singly or in combination the associ ated POWER...

Страница 258: ...uld be rotated by hand through 90 or alternatively a motoring cycle should be carried out to en sure N1 rotation Particular atten tion should then be given to N1 rotation during the subsequent start a...

Страница 259: ...tricted time this is not a normal cruise setting Maximum overspeed 103 103 5 seconds Maximum cruise 100 100 932 C Operating transients 1 006 C 5 seconds 1 016 C 2 seconds Table 7 1 ENGINE OPERATING CO...

Страница 260: ...use below the MIN level on the sight glass and is sufficient for more than 12 hours engine operation at maxi mum oil consumption Approved Engine Oils Mobil Jet II Esso 2380 Castrol 5000 Aero Shell 50...

Страница 261: ...ENTILATION EXIT STARTER GENERATOR COOLING AIR EXIT DRAINS MAST LOWER ACCESS DOOR OIL FILTER BY PASS INDICATOR VIEWING PORT THRUST REVERSER ASSEMBLY BELT AFTERBODY SHOOT BOLTS 2 OFF OIL TANK CONTENTS V...

Страница 262: ...EXIT STARTER GENERATOR COOLING AIR EXIT DRAINS MAST LOWER ACCESS DOOR OIL FILTER BY PASS INDICATOR VIEWING PORT THRUST REVERSER ASSEMBLY BELT AFTERBODY SHOOT BOLTS 2 OFF OIL TANK CONTENTS VIEWING POR...

Страница 263: ...is A 924 C over 30 000 feet for 10 seconds B 952 C until stabilized at idle rpm C 996 C for 10 seconds or 5 seconds in excess of 996 C D 995 for the first 5 minutes of operation 7 The maximum transie...

Страница 264: ......

Страница 265: ...8 3 Rear Equipment Bay Overheat 8 3 FIRE EXTINGUISHING 8 3 Engine Fire Extinguishing 8 3 APU Fire Extinguishing 8 5 APU Fire Detection 8 5 Portable Fuselage Fire Extinguishing 8 6 ELECTRICAL POWER SOU...

Страница 266: ......

Страница 267: ...pment Bay Detection 8 3 8 3 Engine Fire Extinguishing System 8 4 8 4 Pressure Relief Discharge Indicators 8 4 8 5 APU Extinguisher System 8 5 8 6 APU Fire Detection 8 5 8 7 Portable Fire Extinguisher...

Страница 268: ......

Страница 269: ...ine fire extinguishing sys tem is a two shot system if an engine fire is not extinguished with actuation of the first bottle the second bottle is available for dis charge into the same engine The engi...

Страница 270: ...FIRE OVERHEAT DETECTOR ELEMENT ZONE 1 HP COCK ARNING LAMPS BELL PANEL RESPONDER ZONE 1 FIRE OVERHEAT DETECTOR ELEMENT ZONE 1 RESPONDER ZONE 2 RESPONDER ZONE 2 RESPONDER ZONE 1 ROOF PANEL FIRE OVERHEAT...

Страница 271: ...ector circuit has a TEST button also located on the roof panel Pressing either TEST switch illuminates the appropriate ENG FIRE annunciator on the FIRE panel and the re spective ENG FIRE repeater on t...

Страница 272: ...scharge indicators which are located under the left en gine pylon on the fuselage They are green discs A buildup of excess thermal pressure in the bottle will cause the extinguishing agent to discharg...

Страница 273: ...bottle is dis charged due to excessive heat buildup it will blow out the red disc leaving a red indication APU FIRE DETECTION The APU fire detection system comprises three overheat detector switches a...

Страница 274: ...e clamp must be released before the extinguisher can be re moved from the bracket The extinguisher is fitted with a FULL indica tor disc When the extinguisher is operated the disc ejects as soon as di...

Страница 275: ...off the APU MASTER switch 4 The engine fire bottles are discharged as follows A Each bottle can be used only for its re spective engine B When a visual fire warning appears discharge SHOT 1 first If n...

Страница 276: ......

Страница 277: ...INTRODUCTION 9 1 DESCRIPTION AND OPERATION 9 1 General 9 1 Controls and Indicators 9 2 ELECTRICAL POWER SOURCES 9 7 DC Power 9 7 LIMITATIONS 9 7 QUESTIONS 9 8 FOR TRAINING PURPOSES ONLY HAWKER 800 XP...

Страница 278: ......

Страница 279: ...Pheumatic System Control Diagram 9 3 9 3 Main Air Valve Switch LP On Selected HP Valve and Mixing Valve Closed 9 4 9 4 Main Air Valve Switch Open Selected HP Valve Mixing Valve Open 9 5 9 5 Flood Air...

Страница 280: ......

Страница 281: ...ems which are Air conditioning system Pressurization system Rudder bias system Hydraulic reservoir pressurization HP bleed air supplements the LP bleed air at the mixing valve whenever the bleed air p...

Страница 282: ...imum pressure of 18 psi at the valve outlet and limiting the temperature to approximately 200 C The amount of HP air used is dependent on the LP air pressure available When the LP air pressure falls t...

Страница 283: ...P AIR CLOSE CLOSE OPEN 1 OPEN 2 F DK VLV MAIN AIR VLV LP ON LP HP NO 2 ENG LP HP NO 1 ENG PRESS SWITCH HP VALVE HP VALVE MIXING VALVE MAIN AIR VALVE MWS HP AIR 2 OVHT MWS HP AIR 1 OVHT HYD TANK PRESS...

Страница 284: ...P VLAVE CLOSED MIXING VALVE CLOSED HYDRAULIC RESERVOIR AIR JET PUMP MAIN AIR VALVE OPEN 290 C DUCT TEMPERATURE SWITCH CLOSE OPEN LP ON OVERHEAT SENSOR 200 C 27 PSI PRESSURE SWITCH NO 1 ENGINE LEGEND H...

Страница 285: ...E OPEN MIXING VALVE MODULATING HYDRAULIC RESERVOIR AIR JET PUMP MAIN AIR VALVE OPEN 290 C DUCT TEMPERATURE SWITCH CLOSE OPEN LP ON OVERHEAT SENSOR 200 C 27 PSI PRESSURE SWITCH NO 1 ENGINE LEGEND HIGH...

Страница 286: ...w outlet at roof level at the right rear of the passen ger cabin With FLOOD CLOSE selected the air supply to the cabin flood flow outlet is cut off and temperature controlled air is supplied to the ca...

Страница 287: ...unciators MAIN AIR VALVE 1 and 2 annunciators HP bleed on off valve LIMITATIONS Main air valves and flight deck heat valve must be closed prior to takeoff and landing 9 7 FOR TRAINING PURPOSES ONLY HA...

Страница 288: ...1 air valve takes more than A 15 seconds B 10 seconds C 50 seconds D 12 or 45 seconds 3 A pressure switch controls the position ing of an HP bleed air valve The position of the MAIN AIR VLV 1 or 2 sw...

Страница 289: ...RFRAME ANTI ICING SYSTEM 10 5 Description 10 5 Operation 10 5 Warning Annunciators 10 6 WINDSHIELD ANTI ICING SYSTEM 10 7 PITOT VANE HEAT SYSTEM 10 9 ENGINE ANTI ICING SYSTEM 10 10 OPERATING PROCEDURE...

Страница 290: ......

Страница 291: ...ection Controls 10 3 10 4 Airframe Anti icing 10 4 10 5 Airframe Anti icing Fluid Tank 10 5 10 6 Windshield Heat Schematic 10 8 10 7 Engine Anti ice Schematic 10 11 10 8 Powerplant Ventilation 10 12 1...

Страница 292: ......

Страница 293: ...wing fairing for each wing The airframe deicing system uses TKS fluid to anti ice the leading edges of the wings and horizontal stabilizers The left and right windshields and forward side screens are...

Страница 294: ...panel and the left main gear squat switch Selecting the ICE DET switch to AUTO inhibits detector operation on the ground and automatically turns the detector on as the left main gear strut extends dur...

Страница 295: ...a tion activates a microswitch which connects a DC power supply and illuminates the amber ICE DETECTD annunciator on the roof panel and the amber ICE PROT annunciator light on the MWS panel When icing...

Страница 296: ...T WING PROPORTIONING UNIT HORIZONTAL STABILIZER DISTRIBUTOR PANEL ANT ICE LO PRESS ANT ICE LO QTY PUMP AIRFRAME DE ICING FLUID TANK FILTER DISTRIBUTOR PANELS CONTENTS GAGE PANEL CG VENT COVER PROPORTI...

Страница 297: ...oor or behind the pilot s seat Figure 10 5 The FULL EMPTY indicator is located on the copilot s side console and reads FULL at 8 25 U S gallons and EMPTY when there is still 12 minutes protection avai...

Страница 298: ...he water alcohol content of the fluid will evaporate leaving solidified glycol which to gether with the impinging ice crys tals can give the appearance of ice Use of the airframe ice protection system...

Страница 299: ...en The SCREEN HEAT R controls power to the right wind screen and left sidescreen Windshield tem perature control provides two levels of temperature a normal level and a raised level The raised level i...

Страница 300: ...3 A PE RH B SCREEN TEMP CONTROL RH B SCREEN LH A SCREEN TEMP CONTROL LH A SCREEN GCU ALTR 2 FAIL R SCRN OVHT SIDE SCRN OVHT NO 2 INV SCREEN HEAT SW O HEAT NORM STALL VANE HEATER 2 BOTH ALTERNATORS ON...

Страница 301: ...T 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 de pends on the ambient temperature If a PITOT...

Страница 302: ...en and high pressure bleed air is bled from the engine and directed to the inlet cowling In addition with ON selected and the computer switch in AUTO electrical power is supplied to the heating elemen...

Страница 303: ...E ON ON OFF OFF 6 PSI 0 6 PSI D I M AUTO No 2 ENG ANTI ICE FROM No 1 ENG ANTI ICE SQUAT SWITCH BOTH ENGINE CONTROLS BOTH WINDSHIELD HEAT CONTROLS ENGINE INTAKE ANTI ICE VALVE P2T2 HEATER ENG 2 A ICE O...

Страница 304: ...ANTICE and ENG IGNITION switches must be switched on These switches should be switched off when conditions permit NOTE To avoid further throttle adjustments due to slight rise in ITT the ENG ANTICE s...

Страница 305: ...op of descent and if icing conditions are expected preferably for 2 minutes prior to entering icing conditions If icing conditions still prevail or are expected a further period of operation should be...

Страница 306: ...to icing conditions select the airframe ice protection system on for 2 minutes before entering icing approximately 5 000 feet above the cloud With ENG ANTICE selected in flight and the thrust lever at...

Страница 307: ...Revision 1 01 10 15 FOR TRAINING PURPOSES ONLY HAWKER 800 XP PILOT TRAINING MANUAL FlightSafety international Figure 10 9 Speed for Use in Icing Conditions...

Страница 308: ...CE switch ener gized and the computer switch in AUTO electrical power is supplied to heating elements on the P2T2 sensor C When not in icing conditions engine anti icing must not be used for more than...

Страница 309: ...After takeoff power is set C Before takeoff power is set D A minimum of 5 minutes before take off 12 The TKS fluid supply lasts for approxi mately A 30 minutes B 45 minutes C 61 minutes D 108 minutes...

Страница 310: ......

Страница 311: ...e 11 5 CABIN TEMPERATURE CONTROL SYSTEM 11 5 AUTO Mode 11 5 MANUAL Mode 11 5 AIR DISTRIBUTION SYSTEM 11 6 CABIN FLOOD Switch 11 6 Cabin FAN Switch 11 8 CABIN FLOOR Switch 11 8 General System Control 1...

Страница 312: ......

Страница 313: ...ycle Machine ACM 11 3 11 2 Duct Temperature Indication and Overheat Circuits 11 4 11 3 Cabin Temperature Controls 11 6 11 4 Air Distribution Block Diagram 11 7 FOR TRAINING PURPOSES ONLY HAWKER 800 XP...

Страница 314: ......

Страница 315: ...ration unit a cabin temperature control valve a low limit temperature control valve and a water separator The resulting temperatures are de termined by the positions of the valves Bleed air is tapped...

Страница 316: ...ondition However the overpressure condition also triggers a second indication a magnetically latched doll s eye indicator in the rear equipment bay This indication re mains triggered until reset by gr...

Страница 317: ...ED DOOR REAR EQUIP BAY VENT AUX HEAT VALVE RAM AIR VALVE LP HP NO 2 ENG LP HP NO 1 ENG PRESS SWITCH HP VALVE HP VALVE MIXING VALVE MAIN AIR VALVE MWS HP AIR 2 OVHT MWS HP AIR 1 OVHT CAB TEMP CNTL VLV...

Страница 318: ...international D U C T SILENCER WATER SEPARATOR TO LLTCV FROM CABIN TEMPERATURE CONTROL VALVE DUCT OVERHEAT SWITCH 115 C PRESSURE BULKHEAD TO CABIN TEMPERATURE CONTROLLER DUCT OVHT TECH CHECK NRV DUCT...

Страница 319: ...ct overtemperature sensor set at 116 C will cause a DUCT OVHT amber annunciator to be illuminated on the MWS should the temperature be exceeded The overtemperature signal will also cause the cabin tem...

Страница 320: ...air from the No 2 engine can be routed directly to the flight compartment when the auxiliary heating valve is opened CABIN FLOOD SWITCH Temperature controlled air enters the pres sure cabin through a...

Страница 321: ...TIBULE AIR GASPER LH CABIN AIR GASPERS RH CABIN AIR GASPERS LAV AIR GASPER CABIN FAN LAV AIR DUMP RAM AIR AIR CONDITIONING AFT PRESSURE DOME REF MANUAL VALVE OUTLET DUCT COCKPIT LH LOWER SIDE PHL AIR...

Страница 322: ...s cut off A green LED indicator above the switch dis plays the valve position GENERAL SYSTEM CONTROL In cold weather operation the floor ducts should be opened to conditioned air and the cabin fan tur...

Страница 323: ...to permit air from the rear equipment bay to enter the intake and supply the CAU heat exchanger REAR EQUIPMENT BAY VENTILATION A tapping is taken from the dorsal fin air in take to provide an air supp...

Страница 324: ...limiter automatically shuts down the flow control units 4 Cabin delivery air temperature is con trolled by operation of the A No 1 main air valve B No 2 main air valve C Cabin temperature control valv...

Страница 325: ...et Pump 12 4 Pressure Regulators 12 4 Fan operated Venturi 12 4 Controls and Indicators 12 4 OPERATION 12 6 Before Starting Engines 12 6 After Starting Engines 12 6 Takeoff 12 7 After Takeoff 12 7 Dur...

Страница 326: ...AC Power 12 8 LIMITATIONS 12 8 QUESTIONS 12 9 12 ii FOR TRAINING PURPOSES ONLY HAWKER 800 XP PILOT TRAINING MANUAL FlightSafety international...

Страница 327: ...12 4 12 3 HORN ISOLATE Pushbutton 12 5 12 4 CABIN Triple Indicator 12 5 12 5 Manual Pressurization Controls 12 5 12 6 DUMP VALVE Lever 12 6 TABLE Table Title Page 12 1 Cabin Altitude Setting for Landi...

Страница 328: ......

Страница 329: ...reset value The outflow safety valves also provide inward and outward relief for both negative and positive differential conditions in order to protect the airplane s structure A full range of manual...

Страница 330: ...CABIN CONTROLLER pressure con troller Figure 12 1 located on the copilot s instrument panel ensures that the outflow safety valves maintain a selected cabin altitude and that the cabin air pressure ch...

Страница 331: ...N OUTFLOW SAFETY VALVE OPEN CABIN AIR AMBIENT AMBIENT CABIN AIR TRUE STATIC AMBIENT MANUAL CABIN ALTITUDE CONTROL MANUAL SHUTOFF VALVE GROUND PRESS TEST PNEUMATIC RELAY PNEUMATIC RELAY RATE SELECTOR A...

Страница 332: ...es fan running if an engine or APU air valve is open or for approximately 20 seconds after the aircraft has landed With the weight off the wheels in flight the fan stops thus allow ing the cabin to be...

Страница 333: ...he copilot s instrument panel The A pointer displays cabin altitude the plain unmarked pointer indicates cabin altitude rate of change and the red and white barber pole pointer shows cabin differentia...

Страница 334: ...osition and that the MANUAL CABIN ALTITUDE CON TROL is in the full DECREASE position Set the F DK VLV switch to CLOSE CABIN FLOOD switch to CLOSE and the PRESSN switch to AUTO Check that both MAIN AIR...

Страница 335: ...In the event of cabin altitude not being con trolled satisfactorily by the cabin pressure con trol turn the MANUAL CABIN ALTITUDE CONTROL slightly in the INCREASE direc tion The PRESSURIZATION CONTROL...

Страница 336: ...bus bar Recirculating fan control Flood flow valve actuator AC POWER XS2 bus bar Fan operated venturi LIMITATIONS The following limitations pertain to the Hawker 800 XP airplanes pressurization system...

Страница 337: ...maximum allowable negative cabin differential pressure is A 0 5 psi B 8 55 psi C 1 25 psi D 0 025 psi 4 With the airplane on the ground and the air conditioning system on the PRESSN switch prevents ca...

Страница 338: ......

Страница 339: ...13 1 MAIN HYDRAULIC SYSTEM 13 1 General 13 1 Operation 13 4 AUXILIARY HYDRAULIC SYSTEM 13 6 General 13 6 Operation 13 6 HYDRAULIC SUBSYSTEMS 13 6 ELECTRICAL POWER SOURCES 13 8 QUESTIONS 13 9 FOR TRAIN...

Страница 340: ......

Страница 341: ...Indication 13 4 13 4 Main Hydraulic System Components 13 5 13 5 Reservoir Pressure Gage 13 4 13 6 Auxiliary Hydraulic Tank 13 6 13 7 Auxiliary Hydraulic System Schematic 13 7 TABLES Table Title Page...

Страница 342: ......

Страница 343: ...peration GENERAL The output of the variable volume engine driven pumps is manifolded to pressurize the main hydraulic system Either pump is capa ble of actuating all the subsystems A hand pump is prov...

Страница 344: ...the element has an increasing dif ferential pressure caused by clogging and does not have a relief valve The electrically operated DC hydraulic pressure indicator registers main system pressure on the...

Страница 345: ...ION JUNCTION LANDING GEAR FLAPS HIGH PRESS FILTER FULL FLOW RELIEF VALVE FULL FLOW RELIEF VALVE CAP FILTER NOSEWHEEL STEERING SHUTTLE VALVE ON OFF VALVE UP DN SELECTOR DUMP VALVE MAIN SYSTEM PRESSURE...

Страница 346: ...itial delay of 57 seconds to allow the pressure to recover should the low pressure condition be due to system fluctuation rather than a malfunction If both pumps fail or if system fluid is lost both l...

Страница 347: ...TEST QUICK RELEASE CONNECTORS STOW LATCH DEPLOY FORWARD FRAME 21 GROUND SERVICING HAND PUMP THRUST REVERSER CONTROL VALVE RIGHT ENGINE LATCH DEPLOY THRUST REVERSER CONTROL VALVE LEFT ENGINE STOW FRAME...

Страница 348: ...the setting of the land ing gear selector lever but the flaps must be selected to the required setting When using the auxiliary system lowering the landing gear always occurs before opera tion of the...

Страница 349: ...PRESSURE LANDING GEAR SELECTOR DUMP VALVE MAIN GEAR JACK MAIN GEAR JACK SELECTOR HANDLE PULLED FILTER SHUTTLE VALVE HAND PUMP VENT PUMP MWS CENTER PANEL AUX HYD LO LEVEL LEVEL INDICATOR TANK FLAP CON...

Страница 350: ...landing gear the hand pump action must be continued after three greens are achieved until positive resistance is felt to make sure the landing gear is down and locked HYDRAULIC SUBSYSTEMS Landing gear...

Страница 351: ...of the above 4 The first step in operating the auxiliary hydraulic system is A Dump main system pressure B Operate the auxiliary hand pump C Pull the AUX HYD SYSTEM lever D Check that the AUX HYD LO L...

Страница 352: ......

Страница 353: ...rovisions 14 6 Controls and Indicators 14 6 Operation 14 8 NOSEWHEEL STEERING 14 10 General 14 10 Operation 14 10 BRAKES 14 12 General 14 12 Operation 14 12 ELECTRICAL POWER SOURCES 14 14 LIMITATIONS...

Страница 354: ......

Страница 355: ...ver Locking Device 14 7 14 7 Gear Warning Horn Circuit Schematic 14 8 14 8 Nosewheel Steering System 14 10 14 9 Nosewheel Steering System Diagram 14 11 14 10 Normal Brake System 14 13 14 11 Wheel Brak...

Страница 356: ......

Страница 357: ...ted by movement of the gear The main gear inboard doors are hydraulically operated the outboard doors are mechanically operated Gear position indication is provided by six indicator lights on the cent...

Страница 358: ...is mechanically actuated by gear movement the inboard door is hydrauli cally actuated and is closed with the gear ex tended or retracted The maximum permissible airspeed for extending or retracting th...

Страница 359: ...R DOOR ACTUATOR DOOR STOP PLATE DOOR UPLOCK MICROSWITCH SEQUENCE VALVE REAR HINGE DOOR UPLOCK ROLLER EXTENSION LEVER SPRING STRUT DOOR HOOK FAIRING HINGE FAIRING AFT TRUNNION FORWARD TRUNNION TORQUE L...

Страница 360: ...R PIN PLUG BREAK HOOK TO OPEN DOORS UPPER END OF STRUT PIN LEVER ASSEMBLY TO RELEASE SPRING LOADED LATCH ASSEMBLY TO UNLATCH LOWER END OF STRUT MICROSWITCH WHEN MANUALLY CLOSING NOSE GEAR DOORS ENSURE...

Страница 361: ...TCH DOOR OPERATING MECHANISM LEFT SHOWN RIGHT SIMILAR STEERING ON OFF VALVE SPRING STRUT LOCK ROLLER DRAG STAY STEERING JACK STEERING DISCONNECT CHINED TIRE TOWING PIN HOLE MANUAL DOOR RELEASE STRUT S...

Страница 362: ...the pins are stowed in a pouch in the vestibule or under the second step in the main entrance door CONTROLS AND INDICATORS The landing gear is controlled by the LAND ING GEAR selector lever on the ce...

Страница 363: ...ure 14 5 The green annunciators indicate gear down and locked Illumination of red annunciators indicates gear in transit gear unlocked or gear down and locked with the gear selector lever out of the d...

Страница 364: ...isms which lock the gear in both the extended and retracted posi tions Initial movement of the actuator re leases the locks they are engaged by final movement of the actuators Main gear inboard doors...

Страница 365: ...g the handle into the hand pump socket permits pump operation Operation of the handpump draws fluid from the auxiliary tank The pressurized fluid is delivered through a check valve and shuttle valves...

Страница 366: ...l shimmy When the nose gear unlocks prior to retraction a shutoff valve is mechanically closed ren dering the steering system inoperative The steering handwheel must be free from obstruction during ge...

Страница 367: ...N SELECTOR VALVE STEERING SLEEVE HANDWHEEL CHAINS AND SPROCKETS CABLE TENSIONER FIXED BLOCK RIGGING PIN HOLE CABLE DRUM HYDRAULIC RETURN SPRING STRUT HYDRAULIC PRESSURE LINE STEERING ON OFF VALVE TORQ...

Страница 368: ...ven antiskid Maxaret units provide constant antiskid protection by detecting ex cessive wheel deceleration and releasing brak ing pressure as required with wheel rotation Pressure in the brake lines b...

Страница 369: ...TROL VALVE PILOT S MASTER CYLINDER LH LEGEND MAIN SYSTEM PRESSURE REDUCED PRESSURE BRAKING PRESSURE CONTROL PRESSURE RETURN ELECTRICAL TO LEFT BRAKES SHUTTLE VALVE MODULATOR MAXARET UNIT BRAKE UNIT SU...

Страница 370: ...RK LO PRESS annunciator Parking With pressure available from both the main and emergency brake accumulators both brake systems are available for setting the parking brake Movement of the WHEEL BRAKE l...

Страница 371: ...OT S MASTER CYLINDER RH BRAKE CONTROL VALVE PILOT S MASTER CYLINDER LH LEGEND EMERGENCY ACUMULATOR PRESSURE REDUCED PRESSURE BRAKING PRESSURE TO LEFT BRAKE SHUTTLE VALVE BRAKE UNIT CONTROL PRESSURE RE...

Страница 372: ...ESSURE BRAKING PRESSURE SIMILAR TO RIGHT BRAKE SHUTTLE VALVE BRAKE UNIT REDUCED PRESSURE RETURN MECHANICAL ELECTRICAL EMRG BRK LOW PRESS EMERGENCY BRAKE ACCUMULATOR AIR L R EMERG WHEEL BRAKE FROM MAIN...

Страница 373: ...ding or a stop from a rejected takeoff a waiting pe riod should be established to ensure that the brakes are both sufficiently cool and in a ser viceable condition for a further rejected take off crit...

Страница 374: ...ained by the table on the previous page relate to normal operations in which the brakes and tires have time to cool between landings If repeated braked land ings are made for crew training or any othe...

Страница 375: ...below 150 KIAS C The gear is down and locked the LANDING GEAR lever is not se lected down and start power is se lected D All the above 5 An indication of landing gear down and locked 3 green lights ac...

Страница 376: ...tection is available A When braking is from the normal sys tem B When braking is from the emergency system C With a switch on the pedestal during any braking D With a switch on the pedestal during nor...

Страница 377: ...ontrol System 15 5 Gust Lock System 15 8 Elevator Control System 15 11 SECONDARY CONTROLS 15 15 Flap System 15 15 Airbrake Control System 15 16 STALL WARNING AND IDENTIFICATION SYSTEM 15 19 General 15...

Страница 378: ......

Страница 379: ...Switches 15 13 15 12 Mach Trim Circuit Breakers 15 13 15 13 Flap Control System Diagram 15 14 15 14 Flap Selector Lever Position Indication 15 15 15 15 Airbrake Control System 15 17 15 16 Airbrake Sy...

Страница 380: ...25 Stall Identification and Diagnostic Panel 15 27 TABLES Table Title Page 15 1 Electrical Sources PITOT VANE HEAT 15 9 15 2 Electrical Sources Stall Identification System 15 28 15 3 Stall System Annu...

Страница 381: ...evator and left aileron The elevator trim tab may also be servomotor operated by the pilot electric trim the autopilot or the Mach trim system Airbrakes are powered by the main hydraulic system AIRBRA...

Страница 382: ...R 800 XP PILOT TRAINING MANUAL FlightSafety international FORWARD CABLE DRUM GEARED TRIM TAB TRIM JACK GEARED TRIM TAB GEARED TAB AUTOPILOT SWIVEL JOINT FUNCTIONAL DIAGRAM AILERON TRIM CONTROL SYSTEM...

Страница 383: ...links Figure 15 1 Each aileron control surface is fitted with a mass balance weight to prevent flutter and a horn balance to reduce the aerodynamic loads felt by the pilot Primary stops are located at...

Страница 384: ...AUTOPILOT SPRING STRUT RH RUDDER BIAS STRUT BELLCRANK ADJUSTMENT UNIT PULLEY DRUM AIR SUPPLY FROM LH AND RH BLEED AIR DUCTS LH RUDDER BIAS STRUT TECH CHECK 15 4 FOR TRAINING PURPOSES ONLY HAWKER 800 X...

Страница 385: ...e range of movement in both directions Secondary stops are located at each rudder pedal assembly Flow separation triggers have been installed on both sides of the rudder to reduce the pos sibility of...

Страница 386: ...PILOT TRAINING MANUAL FlightSafety international TUMBLER STOP FACE POINTER RUDDER TRIM HANDWHEEL GRADUATED SCALE SCROLL PLATE DOG STOP BRACKET SHAFT CABLE DRUM RUDDER TRIM TRIM JACK RUDDER TRIM HANDW...

Страница 387: ...METRIC THRUST BOTH ENGINES RUNNING RUDDER OPERATION NORMAL SYSTEM FAILURE IN SYSTEM TO LH STRUT LH RUDDER APPLIED A BIAS SWITCH OFF SOLENOID VALVE OPENED RUDDER OPERATION NORMAL LH ENGINE BLEED RH DUC...

Страница 388: ...the RUDDER BIAS switch on the af fected side to OFF equalizes the pressures on both sides of the strut The strut on the good side then maintains a bal ance of forces on the rudder Electric Heating An...

Страница 389: ...le the other throttle is re stricted to a low power setting When the gust lock is removed the baulk is removed free ing both throttle levers The lock must be re moved prior to takeoff To engage the ru...

Страница 390: ...ES ONLY HAWKER 800 XP PILOT TRAINING MANUAL FlightSafety international QUADRANT ELLIPTICAL PULLEY G WEIGHT SPRING BELLCRANK PULLEY DRUM CIRCULAR PULLEY AUTOPILOT SERVOMOTOR ELEVATOR OPERATING LEVER Fi...

Страница 391: ...and is manually controlled from an elevator trim handwheel on the central control pedestal Figure 15 10 Operation of the elevator moves the trim tab to give servo action The autopilot servomotor is u...

Страница 392: ...tric trim is not in use The manual pitch trim handwheel is not being used No Mach trim system failures have been detected Power supplies are correct and available to the system Faults which render the...

Страница 393: ...t switches Figure 15 11 Satisfactory operation will be indicated by the MACH TRIM FAIL annunciator coming on while a switch is operated Electric Power Supplies The ELEV AIL TRIM annunciator is pow ere...

Страница 394: ...ional SPRING STRUT SYNCHRONIZER UNIT AIRBRAKE UNIT INPUT LEVER POSITION INDICATING TRANSMITTER JACK HEAD GEARBOX SYNCHRONIZER LINK FLAP CONTROL UNIT SPRING DRUM SYNCHRONIZER TRANSMITTER AIRBRAKE LEVER...

Страница 395: ...in advertent selection of the up approach or land ing positions The baulk is released by pushing the selector lever into the 15 slot in the gate Additional movement of the flaps downwards from the lan...

Страница 396: ...lure A flap servo baulk stops additional move ment of the flap control unit input lever from the landing position The baulk is released and the lever moved to the lift dump position by an interconnect...

Страница 397: ...TRAINING PURPOSES ONLY SHUT OPEN SELECTOR VALVE LEVER BELLCRANK JACK BAULK RELEASE CABLE BAULK LEVER BAULK LATCH ADJUSTABLE BOBBIN FLAP CONTROL UNIT INPUT LEVER FLAP CONTROL UNIT BAULK MECHANISM LINK...

Страница 398: ...he 45 land position lifting the AIR BRAKE selector and then moving it rearwards into the DUMP position automatically lowers the flaps from the 45 setting to 75 It also opens the airbrakes further to p...

Страница 399: ...wo underwing pressure sensing vents and a stall identification sensor Warning and identification is provided by two stick shaker motors an hydraulically oper ated actuator with two integral electrohy...

Страница 400: ...TALL IDNT IDNT 1 INHIB INHIB FLAP INHIB IDNT 2 SSU IDNT 3 1 2 3 FAULT PUSH TO INHIB STALL IDNT IDNT 1 INHIB INHIB INHIB IDNT 2 SQUAT IDNT 3 1 2 3 FAULT STALL VLV A OPEN STALL VLV B OPEN STALL VLV A OP...

Страница 401: ...amber L and VANE HTR FAIL an nunciators also on the roof panel and by the ICE PROT repeat annunciator on the MWS panel Figure 15 18 There are no control switches The stall warn ing part of the system...

Страница 402: ...s armed and commences to monitor the pitch attitude of the aircraft Stall Identification System The stall identification system uses a hydraulic stick pusher to force the control column for ward pitch...

Страница 403: ...CK MONITORED BY AIRFLOW ANGLE SENSOR ANGLE OF ATTACK INCREASING ANGLE OF ATTACK INCREASING CHANNEL 1 SSU1 CALCULATES APPROACHING STALL AND INITIATES A WARNING SIGNAL CHANNEL 2 SSU2 CALCULATES APPROACH...

Страница 404: ...IFICATION TRIGGER POINT MODIFIED BY RATE OF INCREASE OF ANGLE OF ATTACK SSU1 AND OR SSU2 INITIATE IDENTIFICATION SIGNAL WHEN AIRCRAFT IS AT POINT OF STALL BOTH SSU IDENT SIGNALS OPERATED ONLY ONE SSU...

Страница 405: ...put ceases This ensures that the stick push is maintained until the aircraft has reached nose down attitude well below the stall point and stops the system hunting around the limited hysteresis at the...

Страница 406: ...relay of the other channel A monitoring circuit will cause an IDNT 1 or IDNT 2 annunciator depending on the chan nel at fault to illuminate after a 4 second time delay if an identification signal from...

Страница 407: ...he left and right weight on wheels relays exists for more than 4 seconds then a SQUAT annunci ator copilot s group only will illuminate SSU Self Test A built in test within the SSU detects the fol low...

Страница 408: ...tions PANEL LOCATION ROW COLUMN CIRCUIT BREAKER CIRCUIT OR EQUIPMENT BUSBAR DA D B 1 STALL IDENT 1 26 VAC INPUT TO SSU 1 XS 1 DA D B 4 STALL VLV A 28 VDC TO STALL VALVE 1 AND PS1 a ANNUNCIATORS DA D B...

Страница 409: ...T FLAP SSU FUNCTION ANNUNCIATOR MWS PANEL AIRFLOW ANGLE SENSOR LEFT OR RIGHT VANE HEATING MALFUNCTION L R VANE HTR FAIL FLAP POSITION ASYMMETRY FLAP STALL IDENTIFICATION CHANNEL 1 2 3 FAULT IDNT 1 2 3...

Страница 410: ...e can be advanced to full power 5 The guard is removed from a pitch trim switch A When trim cannot be accomplished using both elements of the switch B During testing to assure that trim ming can be ac...

Страница 411: ...on is integrated with angle of attack signals to determine critical angle of attack of the wing B Flap position is not considered in the determination of critical angle of at tack C Flap position only...

Страница 412: ......

Страница 413: ...age INTRODUCTION 16 1 GENERAL 16 1 PITOT STATIC SYSTEM 16 2 General 16 2 Pitot Heads 16 2 Static Vent Plates 16 2 Equipment Isolation 16 4 Stall Vents 16 4 FOR TRAINING PURPOSES ONLY HAWKER 800 XP PIL...

Страница 414: ......

Страница 415: ...1 Pitot Static and Stall Vent Systems 16 3 16 2 Pitot Head 16 2 16 3 Static Vent Plate 16 2 16 4 Pitot Isolation Valve 16 4 16 5 Wing Stall Vent 16 5 FOR TRAINING PURPOSES ONLY HAWKER 800 XP PILOT TR...

Страница 416: ......

Страница 417: ...s the air data system the autopilot and flight director the electronic flight instrument system the attitude heading reference system and the standby instruments A conventional flight control system w...

Страница 418: ...standby airspeed indicator stall detectors and additional equip ment if connected Both pitot heads are electrically heated Pitot heat is controlled by two PITOT VANE HEAT L and R switches on the roof...

Страница 419: ...NO 1 INSTRUMENTS ARINC BUS OUTPUT FOR NAV SYSTEMS ARINC BUS OUTPUT FOR NAV SYSTEMS FLIGHT GUIDANCE COMPUTER FLIGHT GUIDANCE COMPUTER WARNING HORN 150 KT SPEED SWITCH WARNING HORN 150 KT SPEED SWITCH...

Страница 420: ...s in the ancillary equipment pip ing which may cause the autopilot to become disengaged and the IDNT 3 and MWS STALL IDENT annuncia tors to illuminate In this event press either IDNT 3 annunciator to...

Страница 421: ...ion 16A 12 Operating Limits 16A 13 Emergency Procedures 16A 14 ATTITUDE HEADING AND REFERENCE SYSTEM AHZ 600 16A 14 Description and Operation 16A 14 Normal Operation 16A 16 Abnormal Operation 16A 17 A...

Страница 422: ...odes and Reversions 16A 38 FMZ 800 FLIGHT MANAGEMENT SYSTEM 16A 39 PRIMUS 870 WEATHER RADAR SYSTEM 16A 40 Description and Operation 16A 40 Forced Standby 16A 41 ANGLE OF ATTACK SYSTEM 16A 45 RADIO ALT...

Страница 423: ...16A 13 MC 800 MFD Controller 16A 27 16A 14 MFD MAP Mode With Flight Plan Infomation 16A 30 16A 15 MFD PLAN Mode With Flight Plan Infomation 16A 30 16A 16 MFD With TCAS Display 16A 31 16A 17 MFD With...

Страница 424: ...e Indicator Typical 16A 47 16A 30 Standby Altimeter 16A 47 16A 31 Standby Airspeed Indicator 16A 48 TABLES Table Title Page 16A 1 WX Button Functions 16A 27 16A 2 Weather Detection Calibration Scheme...

Страница 425: ...dance autopilot yaw damper and auto trim functions Subsystems that make up the SPZ 8000 are Dual DFZ 800 Flight Guidance System Dual AZ 600 Attitude Heading Reference System AHRS or optional dual IRS...

Страница 426: ...MFD symbol generator to ED 800 MFD HONEYWELL DFZ 800 DIGITAL AUTOMATIC FLIGHT GUIDANCE SYSTEMS DESCRIPTION AND OPERATION The DFZ 800 Automatic Flight Control Sys tem used in the Hawker 800 XP airplane...

Страница 427: ...HAWKER 800 XP PILOT TRAINING MANUAL FlightSafety international Revision 1 16A 3 FOR TRAINING PURPOSES ONLY Figure 16A 1 SPZ 800 System Flow Diagram...

Страница 428: ...ment and Disengagement The autopilot is engaged by use of the AP pushbutton on the GC 810 autopilot controller The autopilot may be disengaged by one of sev eral methods a Pressing the AP or YD pushbu...

Страница 429: ...di rectly change pitch attitude The amount of pitch change is proportional to the movement of the pitch wheel When the VS HOLD mode is engaged the pitch wheel is used to dial in a new reference which...

Страница 430: ...mode and a pitch command bar will be displayed When the autopilot is engaged this basic mode is annunciated by a green flashing PIT for 5 seconds The reference pitch attitude may be changed via the p...

Страница 431: ...am center The faster the closure rate the farther out the capture point Selection of APP automatically selects the LOC mode Prior to capture the armed GS mode is annunciated in white Upon capture the...

Страница 432: ...acquire the new reference which is also displayed by a solid blue bug on the air speed scale The reference may also be changed by using the TCS button If the airspeed is changed while in the FLC mode...

Страница 433: ...5 seconds to emphasize this transition When the air craft has flared onto the new altitude the sys tem will transition to ALT hold and the ASEL will be replaced by the ALT Note Changing the selected a...

Страница 434: ...f the test by both computers the L FAIL annunciator turns off and the L AFCS annunciator turns on If a failure is de tected in either flight guidance computer the appropriate L R FAIL annunciator latc...

Страница 435: ...mag nitude exists for 20 seconds the amber AIL TRIM L R annunciator will turn on Pitch The elevator servo is monitored to detect a long term load on the servo When this condition is detected the ELEV...

Страница 436: ...FD mode and dis engage the AP and YD DADC The data from the two DADC s are compared in the same manner as the AHRS data Un flagged differences between the data cause the AP and YD to disengage The fli...

Страница 437: ...grees sec LNAV 30 degrees 5 5 degrees sec BC Capture 30 degrees 7 5 degrees sec BC Track 27 degrees 5 5 degrees sec HDG HOLD 13 degrees 5 5 degrees sec ROLL HOLD 35 degrees 5 5 degrees sec MODE PITCH...

Страница 438: ...res The standard system consists of dual attitude and heading reference units dual AHRS controllers and dual flux valves Fig ure 16A 3 Figure 16A 4 and Figure 16A 5 Pitch roll and heading are provided...

Страница 439: ...t entry to the DG mode but the SLAVE annunciator will remain lit Figure 16A 5 Upon exit from the HDG mode the AHRS performs an automatic synchronization of the heading outputs to the present flux valv...

Страница 440: ...EFIS is powered up simulta neously with AHRS the self test on AHRS will not be visible due to the warm up time of the display heads The flags will remain invalid until initializa tion is complete The...

Страница 441: ...Basic mode it will be annunciated on the AHRS controller Normal flight operations may be continued in the Basic mode subject to the limitations of the Flight Manual Following entry into the Basic mode...

Страница 442: ...heading information is an nunciated by a respective red ATT or HDG light in the EADI or EHSI Figure 16A 5 Complete failure of the respective AHRS unit would be annunciated by in the EADI a removing th...

Страница 443: ...rea navigation systems and air data to the cabin display All altitude alerting computation display con trol and output driver are contained in the AZ 810 The set knob on the altitude alert knob provid...

Страница 444: ...s transfer switch 9 Deselectitems7and8andobservethe removal of the ADC 1 or ADC 2 annunciator NOTE During engine start ADC power is transferred to the 4 battery It is normal for a momentary flag to o...

Страница 445: ...ff flag covering the digital portion of the altimeter All three indications would occur simultaneously Figure 16A 9 To allow the opposite ADC to power the failed sides instruments select ADC switchlig...

Страница 446: ...copilot s display system both contain a display controller and a source con troller The display controller provides the means by which the pilot can control the dis play formatting such as full or par...

Страница 447: ...HAWKER 800 XP PILOT TRAINING MANUAL FlightSafety international 16A 23 FOR TRAINING PURPOSES ONLY Figure 16A 10 EDZ 817 818 Electronic Flight Instrument System Block Diagram...

Страница 448: ...ssing the ET button the first time will reset the displayed time to zero The toggling se quence of the ET button is reset start stop VHF Omni Range Localizer V L Button By pressing the V L button VOR...

Страница 449: ...m the EADI display Test TST Button The TST button allows for testing the radio al timeter and EFIS when on the ground or the radio altimeter only when in the air if not in the glide slope capture mode...

Страница 450: ...ckup either of the two EFIS symbol generators or one of the EHSI displays Should one SG fail the pilot can select the MFD symbol generator to take over operation of the failed side s dis plays with al...

Страница 451: ...ather radar configuration on the aircraft Refer to Table 16A 1 Normal NORM Button The NORM button provides entry into the MFD s normal checklist display function The normal checklist is arranged in th...

Страница 452: ...ion at that item If the checklist had previously been com pleted the system forces all items in the checklist to be incomplete and pre sents the first page of the checklist with the active selection a...

Страница 453: ...econd button push will display all air ports within display range up to a max imum of 4 Data DAT Button The DAT button is used to add long range navigation information to the MAP and PLAN displays Fir...

Страница 454: ...to the EFIS WX mode Two range rings are presented at se lected range and half range The other basic mode is WX only This differs from WX with MAP by presenting four range rings with az imuth lines at...

Страница 455: ...ntroller The arrow will not point toward an invalid controller For additional weather radar details refer to the Honeywell Pilot s Operationg Handbook 16A 31 FOR TRAINING PURPOSES ONLY HAWKER 800 XP P...

Страница 456: ...Acceleration Trend IAS MACH Reference Bug and Readout Max Speed Speed Bug from FMS Digital Mach Cat 2 Window Cat 2 Excessive Deviation Reversionary Annunciations Flags Altitude Preselect Readout Compa...

Страница 457: ...HAWKER 800 XP PILOT TRAINING MANUAL FlightSafety international 16A 33 FOR TRAINING PURPOSES ONLY Figure 16A 19 ED 800 EADI Displays and Annunciators Non TCAS II Aircraft...

Страница 458: ...raft Selected Course Desired Track Pointer Selected Course Desired Track Digital Display Course Deviation NAV Source Annunciator TO FROM Pointer FULL Mode TO FROM Annunciator ARC WX MAP or MAP WX Mode...

Страница 459: ...iator Reversionary Source Annunciation Flags and Comparators FMS Alert Message FMS Approach Annunciator WX and MAP WX Modes Only WX Range WX Mode Annunciator WX Return Display Lightning Detection Turb...

Страница 460: ...titude and decision height heading bug on HSI selected AS MACH reference bug and digits Wind Elapsed time bearing pointer 1 selected VS reference Magenta Preselected course arrow digits and annun ciat...

Страница 461: ...y international Revision 1 16A 37 FOR TRAINING PURPOSES ONLY Figure 16A 22 EHSI Compass Display With VOR RMI Needle Overlay Selected Figure 16A 24 EHSI MAP Mode With WX Radar Figure 16A 23 EHSI Arc Mo...

Страница 462: ...SIONS There are several failure modes and rever sions possible with the EFIS system Complete Symbol Generator Failure Both tubes on the respective side go black depending on the nature of the failure...

Страница 463: ...lastly AHRS IRS This po sition is then used to develop area navigation flight plans to any geographical point in the world Routes are defined by the pilot from air craft present position to a destina...

Страница 464: ...he ex piration of the initial R T A warmup period approximately 45 seconds the blue WAIT legend is displayed in the mode field Upon completion of the WAIT period the system automatically switches to s...

Страница 465: ...e riod the system automatically switches to GMAP mode FP Flight Plan Flight plan places the WX transmitter in standby and allows the EHSI or MFD map range to be selected up to 1000 NM TST Test Selects...

Страница 466: ...es within 3 seconds Small antenna mounting misalignments or roll stabilization input offsets can be compensated for electrically See radar pilot s manual SECT Selects sector mode allowing the radar di...

Страница 467: ...nd targest from the display but at the same time it removes some of the weather targets The GCR feature has the following limita tions It does not remove all of the ground and it does remove some of t...

Страница 468: ...ver gain Pushing in on the GAIN switch causes the system to enter the preset calibrated gain mode Calibrated gain is the normal mode and is used for weather avoidance In calibrated gain the rotary por...

Страница 469: ...th airplane flap position converts these inputs into lift infor mation and displays it on a normalized ten gra dation 0 to 1 0 dial Zero lift is at 0 on the dial and the maximum usable lift point as d...

Страница 470: ...Revision 1 16A 46 FOR TRAINING PURPOSES ONLY HAWKER 800 XP PILOT TRAINING MANUAL FlightSafety international Figure 16A 28 Angle of Attack...

Страница 471: ...to main tain the attitude display and internal lighting on the standby horizon The E BAT ON an nunciator on the bottom half of the standby horizon switchlight capsule will illuminate and an aural war...

Страница 472: ...onnected to the right pitot system and the No 8 static air vent In the event of power failure the No 3 battery powers the standby airspeed indicator internal lighting POWER SOURCES EFIS POWER SOURCES...

Страница 473: ...off with one 1 AHRS inoperative or in Basic Mode is permitted only if a third Attitude and Heading Reference source is available for Attitude and Heading dis play in place of failed or degraded AHRS 5...

Страница 474: ......

Страница 475: ...7 1 General 17 1 Oxygen Cylinder Assembly 17 3 Oxygen System Controls 17 3 Crew Oxygen System 17 4 Passenger Oxygen System 17 5 Therapeutic Oxygen Outlets 17 5 Portable Oxygen Smoke Set 17 6 QUESTIONS...

Страница 476: ......

Страница 477: ...17 4 Oxygen System Controls 17 3 17 5 Passenger Supply Valve 17 4 17 6 EROS Oxygen Mask 17 4 17 7 Therapeutic Oxygen Outlet and Mask 17 5 17 8 Portable Oxygen Smoke Set 17 6 TABLE Table Title Page 17...

Страница 478: ......

Страница 479: ...or dual dropout passenger masks in the vestibule the toilet compartment and the passenger cabin Therapeutic outlets are in stalled on the airplane as standard equipment The system includes two oxygen...

Страница 480: ...CLINDERS EXISTING TAIL SECTION 1 100 LTR OPTIONAL CHARGING VALVE CONTENTS INDICATOR DROP MASK UNITS LAVATORY PASSENGER VALVE PRESSURE REGULATOR BAROMATIC VALVE UNREGULATED OXYGEN 1 800 PSI REGULATED O...

Страница 481: ...mati cally closes should there be a break of the sup ply line downstream of the valve OXYGEN SYSTEM CONTROLS The oxygen panel is mounted on the base of the left console Figure 17 4 The panel has a mas...

Страница 482: ...nd a PRESS TO TEST turn for EMERGENCY knob For the mask to op erate it must be plugged into the quick re lease socket The mask is removed from storage by grasping and depressing the red harness contro...

Страница 483: ...ent door allowing the passenger mask to drop out Figure 17 1 When the mask is pulled down for use a retaining clip releases a valve and oxygen flows at a con tinuous rate to the wearer Flow to an indi...

Страница 484: ...Figure 17 8 The cylinder should be pres surized to 1 800 psi which supplies oxygen for approximately 15 minutes The cylinder incorporates an ON OFF control knob and shutoff valve a pressure indicator...

Страница 485: ...MER GENCY valve 6 The passengers constant flow masks de liver oxygen A At all times when the system is acti vated and the mask lanyard is pulled B Upon inhalation only when the system is activated and...

Страница 486: ......

Страница 487: ...alkaround It shows each item called out in the exterior power off preflight inspection The fold out pages at the beginning and end of the walkaround section should be unfolded before starting to read...

Страница 488: ...100 103 7 3 1 8 9 10 11 12 13 109 107 105 104 96 97 106 33 26 31 32 23 22 21 20 19 15 24 35 34 30 29 27 25 18 14 17 16 7 28 WALKAROUND FUSELAGE NOSE LEFT SIDE 1 AIRFLOW ANGLE SENSOR VANE CHECK FREEDO...

Страница 489: ...D HOLES CLEAR 2 PLATES 11 NOSE STEERING PIN INSTALLED 12 NOSE GEAR STRUT CLEAN NO FLUID LEAKS 13 TIRES GENERAL CONDITION 10 NOSE WHEEL WELL DOORS CLOSED AND MANUAL RELEASE SECURE 15 PITOT PROBE COVER...

Страница 490: ...SENSOR VANE CHECK FREEDOM OF MOVEMENT 19 EMERGENCY EXIT CLOSED 20 DORSAL AIR INTAKE COVER REMOVED 21 INTAKE COVER REMOVED NO FOREIGN OBJECT DAMAGE 22 P2T2 SENSOR CLEAN UNDAMAGED SECURE 23 FAN BLADES U...

Страница 491: ...LL STRIP SECURE UNDAMAGED 29 LANDING AND TAXI LIGHTS CONDITION OF LIGHTS COVER CLEAN UNDAMAGED 30 VORTILON SECURE UNDAMAGED 31 FUEL CAP SECURE 32 VORTEX GENERATORS SECURE 34 UNDERSURFACE NO FUEL LEAKS...

Страница 492: ...URE VENTS CLEAR NO LEAKS 50 TURBINE EXHAUST COVER REMOVED CLEAR DRY UNDAMAGED 51 THRUST REVERSER STOWED AND SECURE PIN REMOVED 39 FAIRING AND DOORS SECURE UNDAMAGED 40 WHEEL WELL GENERAL CONDITION NO...

Страница 493: ...55 DOOR OPEN UNDAMAGED 56 AIR DUCTS GENERAL CONDITION 58 HYDRAULIC RESERVOIR CONTENTS APPLICABLE TO ACCUMULATOR PRESSURE NO LEAKS HYDRAULIC TANK PRESSURE GAGE CHECK PRESSURE LH RH ENGINE CHIP DETECTO...

Страница 494: ...8 FOR TRAINING PURPOSES ONLY 62 STICK PUSHER ASSEMBLY GENERAL CONDITION NO LEAKS 63 APU GENERAL CONDITION NO LEAKS 64 ALL LOOSE EQUIPMENT REMOVED 65 DOOR CLOSED AND LOCKED 59 BATTERIES CONNECTED AND...

Страница 495: ...G PURPOSES ONLY REAR FUSELAGE 68 GROUND POWER PROPERLY CONNECTED IF REQUIRED OR DOOR SECURE 66 PRESSURE REFUELING RECEPTACLE DOOR OPEN CAP INSTALLED GENERAL CONDITION 70 TAIL CONE LOCKED SECURE 67 PRE...

Страница 496: ...ATORS INSTALLED 3 LEFT ENGINE 76 VENTRAL TANK CAP SECURE LOCKING LEVER IN PLACE 77 VENTRAL TANK ACCESS DOOR CLOSED 74 TAIL CONE STROBE AND BEACON LIGHTS CHECKED 75 TAIL CONE VENTS UNOBSTRUCTED 72 HORI...

Страница 497: ...CTED 85 FAN BLADES UNDAMAGED 86 P2T2 SENSOR CLEAN UNDAMAGED SECURE 87 INTAKE COVER REMOVED NO FOREIGN OBJECT DAMAGE 89 FAIRING AND DOORS SECURE UNDAMAGED 90 WHEEL WELL GENERAL CONDITION NO EVIDENCE OF...

Страница 498: ...N SECURE UNDAMAGED 105 LANDING AND TAXI LIGHTS CONDITION OF LIGHTS COVER CLEAN UNDAMAGED 106 STALL STRIP SECURE UNDAMAGED 107 TKS PANELS CLEAN UNDAMAGED 108 TOP SURFACE GENERAL CONDITION 98 AIRBRAKES...

Страница 499: ...G MANUAL FlightSafety international FOR TRAINING PURPOSES ONLY HAWKER 800 XP PILOT TRAINING MANUAL FlightSafety international LEFT FUSELAGE 109 WING ICE INSPECTION LIGHT CHECKED 110 ENTRANCE DOOR SEAL...

Страница 500: ......

Страница 501: ...1 FOR TRAINING PURPOSES ONLY HAWKER 800 XP PILOT TRAINING MANUAL FlightSafety international ANNUNCIATORS The following section presents a color representation of all the annunciator lights in the airp...

Страница 502: ......

Страница 503: ...TEST MWS DIM OVRD MWS DIM FAIL L AP SEL R STALL VLV A OPEN STALL VLV B OPEN MWS DIM FAIL BAG FIRE AIR BRAKE RADIO MST APR OVRD WHEEL BRAKE EMERG APR ARM VOICE ADVISORY OFF ADF VOL VOL OPEN NAV 2 TUNE...

Страница 504: ......

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