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5. Ensure that the right throttle lever is at

IDLE and that the R/H ARM annuncia-
tor is illuminated. Repeat the above steps
using the right thrust reverser lever..

Landing

1. After touchdown, with the throttles at

IDLE, lower the nosewheel to the runway.

2. Select lift dump, and use the wheel

brakes in the normal manner.

3. Check that the ARM annunciators are

illuminated.

4. Pull both thrust reverser levers up to the

deploy position.

5. When the UNLCK and REVRS an-

nunciators illuminate and the thrust re-
verser lever balks have released, the
thrust reverser lever position may be se-
lected as required.

NOTE

Reverse thrust must be reduced to
idle by 50 knots.

Engine Shutdown

1. Before parking, place the thrust re-

verser levers to stow.

2. Check that the REVRS and UNLCK

annunciators are extinguished.

3. P r e s s t h e T H RU S T R E V E R S E R

POWER switch, and ensure that the
OFF annunciator is illuminated.

4. Complete the engine shutdown proce-

dures.

ABNORMAL 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 switch(es) must be selected OFF.

Automatic Throttle Retard with
Illumination of ARM, UNLCK,
and MWS REVERSER
Annunciators

If the illumination of the ARM and UNLCK
a n n u n c i a t o r s i s a s s o c i a t e d w i t h t h e R E -
VERSER annunciator and throttle retardation
toward IDLE, the system has been armed au-
tomatically using the “autostow” cycle.

The associated POWER switch should be se-
lected OFF. If indications revert to normal, the
engine may be used as required. If these in-
dications persist, leave the engine at idle for
the remainder of the flight and land as soon as
practicable. Do not use thrust reverse on the
affected engine.

Illumination of MWS
REVERSER Annunciator during
Deploy

If the MWS REVERSER annunciator illumi-
nated during the reverser deploy cycle, the
rudder bias has not been inhibited. Power must
not be increased above reverse idle.

7-33

FOR TRAINING PURPOSES ONLY

HAWKER 800 XP

PILOT TRAINING MANUAL

FlightSafety

international

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Summary of Contents for 800 XP

Page 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...

Page 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...

Page 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...

Page 4: ......

Page 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...

Page 6: ......

Page 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...

Page 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...

Page 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...

Page 10: ......

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

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

Page 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...

Page 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...

Page 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...

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

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 104: ......

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

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

Page 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...

Page 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...

Page 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...

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

Page 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...

Page 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...

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

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 124: ......

Page 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...

Page 126: ......

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 156: ......

Page 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...

Page 158: ......

Page 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...

Page 160: ......

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 170: ......

Page 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...

Page 172: ......

Page 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...

Page 174: ......

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 184: ......

Page 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...

Page 186: ......

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 198: ......

Page 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...

Page 200: ......

Page 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...

Page 202: ......

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 222: ......

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 264: ......

Page 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...

Page 266: ......

Page 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...

Page 268: ......

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 276: ......

Page 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...

Page 278: ......

Page 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...

Page 280: ......

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 290: ......

Page 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...

Page 292: ......

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 310: ......

Page 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...

Page 312: ......

Page 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...

Page 314: ......

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 328: ......

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 338: ......

Page 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...

Page 340: ......

Page 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...

Page 342: ......

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 352: ......

Page 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...

Page 354: ......

Page 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...

Page 356: ......

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 378: ......

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 412: ......

Page 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...

Page 414: ......

Page 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...

Page 416: ......

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

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

Page 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...

Page 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...

Page 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...

Page 474: ......

Page 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...

Page 476: ......

Page 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...

Page 478: ......

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 486: ......

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 500: ......

Page 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...

Page 502: ......

Page 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...

Page 504: ......

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