Section - III SYSTEMS DESCRIPTION - SmartCockpit

Page 14-1Pilot’s Operating ManualOriginal Issue: Feb, 2002

Pro Line 21

Section - IIISYSTEMS DESCRIPTION

Sub-section 14EQUIPMENT and FURNISHINGS

Table of Contents

Page

GENERAL ..................................................................................................14-3

FLIGHT COMPARTMENT .........................................................................14-3

CREW SEATS.........................................................................................14-3Figure 1 - Crew Seat ...........................................................................14-4

3rd CREW MEMBER SEAT ....................................................................14-5Figure 2 - 3rd Crew Member Seat .......................................................14-5

CREW CABINET AREA ..........................................................................14-5Figure 3 - Flight Compartment ............................................................14-6Figure 4 - Flight Compartment Main Instrument Panels......................14-7Figure 5 - Flight Compartment Overhead Roof Panels .......................14-8Figure 6 - Flight Compartment (looking aft).........................................14-9Figure 7 - Flight Compartment Side Consoles ..................................14-10Figure 8 - Flight Compartment Center Pedestal................................14-11

GALLEY ...................................................................................................14-12

Figure 9 - Typical Galley ...................................................................14-12PASSENGER CABIN...............................................................................14-13

Figure 10 - Typical Interior Layout.....................................................14-13SEATING ARRANGEMENTS ...............................................................14-14

Figure 11 - Passenger Right Side Console Control...........................14-14Figure 12 - Typical 3 Seat Divan .......................................................14-14

CARGO and ACCESSORY COMPARTMENT........................................14-15

LUGGAGE COMPARTMENT................................................................14-15MAIN RADIO/AVIONICS COMPARTMENTS .......................................14-15

Figure 13 - Cargo and Accessory Compartments .............................14-16TOILET COMPARTMENT .......................................................................14-17

Figure 14 - Typical Toilet Compartment ............................................14-17

Page 14-2 Pilot’s Operating ManualOriginal Issue: Feb, 2002


Hawker 800XP Pro Line 21

Section III - SYSTEMS DESCRIPTION

Intentionally left blank





GENERAL

Due to individual customer requirements, the equipment and furnishings may vary from the standardinstallation. This Sub-section provides the typical installation of a flight compartment, vestibule area,passenger cabin, galley, toilet compartment and cargo and accessory compartments.

FLIGHT COMPARTMENT

Stowages for miscellaneous flight and airplane equipment are provided in the left and right consolesand on the flight compartment rear bulkheads. A tray is mounted in the structure below the pilot's seatand can be swung out where it spans the area between both pilots' seats.

CREW SEATS

Seat Height Adjustment

Two crew seats, the pilot's and copilot‘s, are installed in the flight compartment and are adjustable forheight, fore and aft travel. Each seat is equipped with Teleflex inertia-reel type shoulder strap assemblyand lap belt. A life-jacket is stowed in a container mounted beneath each seat.

When the seat height adjustment handle is pulled upward, the height lock pins are disengaged from theholes in the height lock plates. Spring tension, supplied by the two bungee cords, causes the seat torise.

When the adjustment handle is released, the height lock pins engage with holes in the height lock platesto retain the seat pan in the required position.

Thigh Pad Position and Override

When the thigh support adjustment control knob is turned, two bevel gears mounted on the cross shaftare rotated, which, in turn, rotate a threaded drive shaft under each thigh pad. The rotating drive shaftcauses crossheads to move towards or away from slide housings thereby raising or lowering the thighpads. The mechanisms are under constant spring tension within the slide housings and support thethigh weight under normal conditions.

When the seat occupant uses the rudder controls of the airplane and thereby applies pressure to thethigh pads, the spring tension is overridden and the crosshead slide tubes are pushed into the slidehousing allowing the thigh pad to move downwards. When the pressure on the thigh pad is relaxed, thepad returns to its pre-set position.

Recline Adjustment Mechanism

When the recline control handle is pulled upward, a spring-loaded latch plate is withdrawn by a cablefrom contact with a coarse threaded nut within the recline unit.

Application of pressure on the backrest rotates the threaded nut and allows the strut to be pushed intothe recline unit. The spring is compressed and the backrest reclines.

When the control handle is released, the spring-loaded latch plate re-engages with the coarse threadednut and the backrest is locked in the required position. If the control handle is again pulled upward, andpressure released from the backrest, the spring, which was compressed by the recline operation, re-asserts itself, causing the threaded nut to rotate in the opposite direction.

The strut pushes on the backrest, which returns to an upright position and is locked upon release of thecontrol handle.





Armrests

When the control knob is turned, a screw adjuster increases or decreases the distance between thearmrest drive plate and the pivot block via a drive shaft, thereby raising or lowering the armrest. Theinboard armrest can be stowed by rotating the arm to the rear of the seat.

A slot in the barrel of the adjuster screw takes up any height adjustment and allows the armrest to alignparallel to the seat back. When fully folded, the armrest is pushed in towards the center of the seat,reducing the seat width. The outboard armrest may be raised to an almost vertical position where it willbe held by a friction clutch until returned to the horizontal position by the occupant.

Back Cushion Lumbar Support

The seat back cushion is adjustable for up-down and in-out lumbar support. Lumbar in-out adjustmentis controlled by a handwheel on the right side of the seat. When the handwheel is rotated, themovement is transmitted through worm and wheel gears to the cross shaft, to which two relay arms areconnected.

As the relay arms rotate, the lumbar cushion moves forward or backward in relation to the spinestructure. The up-down movement of the back cushion is controlled by a handwheel on the left side ofthe seat. When rotated, the worm and wheel assembly causes rotation of a vertical shaft and a screwat the top of this shaft causes the crossbar to be raised or lowered, moving the back cushion to thedesired position.

Figure 1Crew Seat





3rd CREW MEMBER SEAT

The 3rd crew member seat is an additional seat which can be attached to the inboard rails of each crewseat. A three point inertia reel harness is anchored to the seat frame and the luggage compartmentupper shelf structure.

The seat is installed by engaging the seat slides with the crew seat rails, then locating the locking pinholes in the seat rails and the seat slides, and then locking the pins into position.

CREW CABINET AREA

The crew cabinet area is located forward of the main entry door, adjacent to the APU control panel (if installed) and provides a mic socket and volume control for a 3rd crew member. The crew cabinetalso consists of stowage areas for life vests and various pilot manuals. All stowage area doors must beclosed, to clear the flight compartment aisle, for takeoff and landing.

Figure 23rd Crew Member Seat





M5874HA00B995504AA

CREW SERVICESPANEL

CENTER INSTRUMENTPANEL `CC`

ROOF PANEL `CG`(MAIN SECTION)

ROOF PANEL `CG`(FWD SECTION)

LEFT SIDECONSOLE

RIGHT SIDECONSOLE

LEFT HANDINSTRUMENTPANEL `CA`

CONTROLPEDESTAL

PANELRIGHT HANDINSTRUMENTPANEL `CD`

CONTROL DISPLAY UNITPANEL `CT`

GLARE SHIELDPANEL `CY`

S

F

LANDINGGEAR

Figure 3

Flight Compartment

OVERHEADROOF PANEL

FWD EXTENTION

OVERHEADROOF PANEL

Page 14-7Sub-section 14EQUIPMENT and FURNISHINGS

Hawker 800XP Pro Line 21Section III - SYSTEMS DESCRIPTION

Pilot’s Operating ManualRevision A2: Nov, 2004

M5879_1 HA00B 995510AA.AI

BRAKEPRESSURE

RH TRANSFER

EMERGWHEELBRAKE

APR OVRD

APR

RADIO

CPWS

CANCEL

STANBYHORIZON

HORIZONWARN

OAT SMOKE DETECT TEST

FWDPUSH FUEL

TEMP

ON ON ON

OFF OFF OFFA RUDDER BIAS B

LAV AFT

LHIN

RHIN

CAT IIENABLE

HP HP DISABLE

APR ARM

APRARM

L R

REVERSER MACH TRIM FAIL

HP AIR 1 OVHT

APU FIRE

REAR BAY OVHT

HP AIR 2 OVHT

ENG 1 FIRE

CABIN ALTITUDE

ENG 2 FIRE

OIL 1 LO PRESS

ELEV/AIL TRIM

OIL 2 LO PRESS

HYD 1 LO PRESS HYD OVHT

HYD 2 LO PRESS

MAIN AIR VALVE 1

AUX HYD LO LEVEL

MAIN AIR VALVE 2

ENG 1 CMPTER

EMRG BRK LO PRESS

ENG 2 CMPTER

ENG 1 A/ICE

ICE PROT

ENG 2 A/ICE

ELECT FUEL DUCT OVHT

ENT DOOR UNLOCKED

RUDDER BIAS

ICE PROT SELECTED

FUEL XFD TFR

STALL IDENT

AIR BRAKE

APU ON

L/H

ELT

THRUST REVERSER R/H

CPWS

CANCEL

STANBYHORIZON

HORIZONWARN

OVRD

FLAP

GS

INHIB

INHIB

TERR

ALTCALLSINHIB

R GEAR

R GEAR

L GEAR

L GEAR

N GEAR

N GEAR

-// /+ /

U

0

987

654

321

N

G

ZYXWV

TSRQPO

MLKJIH

FEDCBA

-/+ /

U

0

987

654

321

N

G

ZYXWV

TSRQPO

MLKJIH

FEDCBA

CONTROL DISPLAY UNITS (CDU)

POWERUNLCK

REVRS

ARM

OFF

UNLCK

REVRS

ARM

OFF

Flight Compartment

Center Instrument PanelPilot Instrument Panel

M5880_0 HA00B 995511AA.AI

MFD PFD CABINPRESSURECONTROL

LANDING

GEAR

MODEAHRS

+ -NORM

SLEW

CABIN ALTITUDEDIFF PRESSURERATE OF CLIMB

GEAR OVRD

DIM OVRD

DIM

CPWS

CANCEL

STANBYHORIZON

HORIZONWARN

NORM

APR ARM

RH CONSOLE

MWSDIMFAIL

STALLVALVE A

OPEN

STALLVALVE B

OPEN

BAGFIRE

CABINHIGH

DATUM

CABINHIGH

DATUM

CABINTEMP

CPIT CAB

ELT

AIR VENT

SELCALMIC SELECT

VHF2VHF1

PA

OFFPA

HF1

HF2

NORM

EMERGBOOM-MIC

OXY-MIC

CABINI/CPHONENORMV0I

CE TONE SPKR-

PUSHVOX-PUSH

FLT

1 VHF 2 1 HF 2

1 VOR/ILS 2 1 ADF 2

1 DME 2 1 MKR 2

AUDIO CONTROL PANEL (ACP)

NAV/COM CONTROL PANEL

PUSH TO INHIB STALL IDENT

1 2 FAULT 3

IDENT 2

INHIB

IDENT 1

INHIBSQUAT

IDENT 3

INHIB

RH TRANSFERAHS

REV

CDU

REV

PFD MFD

REV REV

ADC

REV

R PFD ENG

SELECT

Copilot Instrument Panel

MFDPFD

BRAKEPRESSURE

PUSH TO INHIB STALL IDENT

1 2

FAULT

STALLVALVE A

OPEN

STALLVALVE B

OPEN

3

MODE + -NORM

SLEW

AHRS RADIOLH TRANSFER

LH CONSOLE

AOA COMPUTERC-87705-4

AHS

REV

CDU

REV

PFD MFD

REV REV

ADC

REV

RADIO 1 ON

RADIO 1 OFF

RADIO 2 ON

FAN FAIL

L RRADIO 2

OFF

M5878_0 HA00B 995509AA.AI

AIR VENT

SELCALMIC SELECT

VHF2VHF1

PA

OFFPA

HF1HF2

NORM

EMERGBOOM-MIC

OXY-MIC

CABINI/CPHONENORMV0ICE TONE SPKR-

PUSHVOX-PUSH

FLT

1 VHF 2 1 HF 2

1 VOR/ILS 2 1 ADF 2

1 DME 2 1 MKR 2

AUDIO CONTROL PANEL (ACP)

COCKPIT VOICE RECORDER (CVR)

IDENT 2

INHIB

IDENT 1

INHIB

SSU

FLAP

IDENT 3

INHIB

Main Instrument Panels

Figure 4


Page 14-8 Pilot’s Operating ManualRevision A2: Nov, 2004


M5873_1 HA00B 995503AA.AI

TEST

DC POWER

ICE PROTECTION FUEL

EXTERIOR LIGHTS FIRE

AIR CONDITIONING

AC POWER

ELECTRICAL

STALL

ENG 1 ENG 2

1 1 1

1

2

3

ANNUNHP AIROVHT

ICEDET

CABINALT EGPWS AOA SELCAL

OFF

OFF

OFF

OFF

LOGO

OFF OFF OFF OFF

OFF

ON

LANDINGLOGO/ICE STROBE NAV BEACON L R ENG 1 EXT ENG 2 EXTENG 1FIRE

ENG 2FIRE

SEATBELTS

EXT 1FIRED

EXT 2FIRED

BELL CANCEL

OFF

N2

EMERG

1 2

1

2

SHOT

TAXI

1

2

SHOT

21

EMERG

OFF

OFF

OVRD

ICE DETAUTO

WING/TAIL ANTICE

AMPS

PITOT AMPS

OFF

LTSMASTER

OVSPD PROT

ENG CMPTRAUTO

OFFOFFOFF

OFF

DC VOLTS AC VOLTS

0-40

AMPS

P

P

AMPS

VOLTS

XS 1FAIL

BATT 1CNCTRBATT 2CNCTR

BUSTIEOPEN

GEN 1FAIL

REAR BAYDOOR

REFUELON

ENG 2FUEL

WING FUELXFD/TFR

ENG 1FUEL

AUX FUELTFR

FUEL 1LO PRESS

FUEL 2LO PRESS

IGN ON

OPERATING

PWR ON

PUSH FOR

ABORT

OPERATING

ALTR 2FAILICE

DETECTED

ANTICELO QTY

ALTR 1FAIL

SIDE SCRNOVHT

ANTICELO PRESS

SCREEN HEAT PITOT/VANE HEAT ENG ANTICE ENG IGNITION ENG SYNCN1

R SCREENOVHT

R VANEHTR FAIL

R PITOTFAIL

L PITOTFAIL

L SCREENOVHT

L VANEHTR FAIL

GEN 2FAIL

XEFAIL

XS 2FAIL

INV 1FAIL

STBV INVON

INV 2FAIL

VOLTS

TRIP STOP OFF STOP ON

OFF

OPEN TRIP

CLOSE CLOSE

OPEN OPEN

OFF AUTO

TEMP

MANUAL

AUTO

XS1XE

XS2B4B5

B6

OFFB3

PS1PE

PS2

B2

XFER

B1

COOL HOTCLOSE

F/DK VLVOPEN

MAIN AIR VLV1 OPEN 2

L ON R L ON R 1 ON 2 1 ON 2

L

ON

R

INSTRDIM

LPON

PANELDIM

CLOSE

DUCT TEMPCABIN TEMP

TEMP

OFF OFF

ON

BATT 2

VMOMMO

22

2 ENGINE STARTBATT

EMERG

GEN 1CLOSE

CABINFLOOD

CABINFLOOR ON

CABINFAN PRESSN

OVRD

INV 1START

STBY INVARM

INV 2START

NO SMKGAUTO

BUSTIECLOSE

GEN 2

CLOSER PUMP

ONL PUMP

ON

EXT BATTCHG ON

EXT PWRON

EMERGMAN

EMERGLTS

EMERGARM

ALTERNATORON

ARM

AMPSBATT

ISOLATEBATT 1

ENGFIRE

CLOSE

STOP

F/DK VLVOPEN

A

DETAIL AS/N 258577 AND AFTER

Figure 5Flight Compartment

Overhead Roof Panels




V8636_1.AI

SIL

ICA

GE

LV

IEW

ING

WIN

DO

WS

HE

AD

SE

TS

TO

WA

GE

HO

OK

ST

ALL

IDE

NT

DIA

GN

OS

TIC

PA

NE

LP

AS

SE

NG

ER

OX

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EN

SU

PP

LYV

ALV

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SIL

ICA

GE

LV

IEW

ING

WIN

DO

WS

HE

AD

SE

T,O

XY

GE

N&

MA

SK

/MIC

SO

CK

ET

SH

EA

DS

ET

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EN

&M

AS

K/M

ICS

OC

KE

TS

FIR

EE

XT

ING

UIS

HE

R

FLA

SH

LIG

HT

LIF

EJA

CK

ET

ST

OW

AG

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LIF

EJA

CK

ET

ST

OW

AG

E

WA

RN

ING

HO

RN

SU

NV

ISO

RS

ST

OW

AG

E

RA

DIO

AN

DE

LEC

TR

ON

ICE

QU

IPM

EN

T

RU

DD

ER

GU

ST

LOC

K/A

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RY

HY

DR

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HA

ND

PU

MP

HA

ND

LES

TO

WA

GE

SU

BP

AN

EL

AS

UB

PA

NE

LD

ST

OR

MLA

MP

WA

ND

ER

LAM

PS

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ND

ER

LAM

PS

OC

KE

T

SP

OT

LAM

P&

SW

ITC

H

CR

AS

HA

XE

MA

NU

AL

ST

OW

AG

E

FIR

E-

WA

RN

ING

BE

LL

TR

AY

EN

TR

YLI

GH

TS

WIT

CH

STO

RM

LIG

HT

WA

ND

ER

LIG

HT

SW

ITC

H

STO

RM

LIG

HT

&S

WIT

CH

WA

ND

ER

LIG

HT

SO

CK

ET

Figure 6Flight Compartment (looking aft)




M5900HA00B995531AA

INCREASE

DECREASE

L GEAR R GEAR

ISOLATE

PITOT ISOLATION

DEPRESSTO OPERATE

MANUAL CABINALTITUDE CONTROL

NORMAL

NORMAL

PRESSURIZATION CONTROL

TEST

GROUND

RIGHT-HAND CONSOLELEFT-HAND CONSOLE

OXYGEN PANEL

CVR-120 CONTROLLER

DE-ICING FLUIDCONTENTS

AIR OUTLETAIR OUTLET

AUDIO SELECTOR PANEL AUDIO SELECTOR PANEL

NAV / COMMCONTROLLER

A

A

Figure 7Flight Compartment Side Consoles




M5851HA00B995480AA

AILERON TRIM

RUDDER TRIM

ELEVATOR TRIMHAND WHEEL

AIR BRAKES

AUXILIARY HYDRAULICSYSTEM SELECTOR

HANDLE

NOSE GEARMECHANICAL

INDICATOR

THRUSTREVERSER

LEVERS

HORN ISOLATEPUSH BUTTON

THROTTLESDUMP VALVE

WHEELBRAKE

SOCKET FOREMERGENCY HYDRAULIC

HAND PUMP

EMERGENCY HYDRAULICHAND PUMP HANDLE

(GUST LOCK BAR)

STOWAGE ON RH SEATSUPPORT STRUCTURE

L.P. COCKS

H.P. COCKS

FIRE WARNINGLIGHTS

FLAPS

L.P. COCKS GUARD

AUXILIARY FUELTRANSFER CONTROL

WING FUELCROSSFEED AND

TRANSFER CONTROL

OATSMOKE

FWDPUSHFUELTEMP

ON ON ON

OFF

SHUT

FLAPS

0

15

o

o

o

o

25

45

PAGE ADV

LINE ADV

CKLSTON/OFF

OPEN

DUMP

AILERON TRIM

RUDDER TRIM

PULL

AUX

HYD

SYSTEM

A

I

R

B

R

A

K

ENOSE UP

OFF OA RUDDER BIAS B

ELEVATORTRIM

NOSE DOWN

T0CG 1/2

3525

15

21

Figure 8Flight Compartment Center Pedestal

STOWAGE BEHINDCOPILOT SEAT

THRUSTLEVERS




GALLEY

The galley is located on the left side of the airplane aft of the entry door and consists of liquid containers,hot cup, decanter rack, drain dish, ice drawer, glasses drawer, cold food box, hot meal oven, waste binand various drawers and cupboards.

Electrical supplies are provided to the oven, hot cup, hot beverage container, drain heater andrefreshment cabinet light. The drain dish is connected to an overboard drain. A heater is attached to thedrain pipe immediately inboard of the drain exit from the fuselage. Control of the galley functions isprovided by a galley switch panel located on the upper left of the galley.

M6356_0HA03C014655AA.

CUSTOM WATER CONTAINER

CUPDISPENSERS

WASTE

COFFEEBREWER

SWITCH PANEL

MICROWAVE

COUNTERSTORAGE

SANDWICHTRAY

DRAWER

UTENSILS

CONDIMENTS

PULL OUT WORK

SURFACE

BOWLS

PLATES

MINIATURES

WINE / SPIRITS STORAGE

MISC.STORAGE

NAPKINS

SODA CANS

ICE / COLD STORAGE

GALLEYUP

LIGHTS

GALLEY SWITCH PANEL

GALLEYWORK

LIGHTS

COFFEEHEAT

WATERHEAT

Figure 9Typical Galley

MISCELLANEOUSSTORAGE

MINIATURES

Page 14-13Pilot’s Operating ManualRevision A1: Nov, 2002



PASSENGER CABIN

Figure 10Typical Interior Layout

Page 14-14 Pilot’s Operating ManualRevision A1: Nov, 2002



SEATING ARRANGEMENTS

The seating arrangements comprise individual forward or aft facing seats with side consoles forentertainment control and a three seat divan. Each individual seat position is provided with a lap typesafety belt.

A three-seat divan comprises a base assembly with seat cushions, back cushions and a safety lap/shoulder belt assembly at each seat position. The base assembly is attached to the floor and sidewallseat rails. The two outer back cushions are attached to the sidewall by velcro tape while the center backcushion can be hinged forward to double as a table. Fixed arm rests are attached at both ends of thebase assembly with a small stowage compartment being provided in the divan base.

Figure 11Passenger Right Side Console Control

Forward

M6357_0HA03C014656AA.AI

LAP/SHOULDER BELT ASSEMBLIES

Figure 12Typical 3 Seat Divan




CARGO and ACCESSORY COMPARTMENTS

LUGGAGE COMPARTMENT

A luggage compartment is installed in the vestibule area of all airplanes, with luggage retained withinthe compartment by a zip fastened nylon net. The compartment is normally enclosed by a folding slattype curtain.

A loading label, giving each compartments capacity and maximum floor loadings, is attached to theinterior trim panels.

MAIN RADIO/AVIONICS COMPARTMENTS

Radio racks and structure for the installation of electronic equipment are provided at various locations,such as under each pilot seat structure, under the luggage compartment, in the wing fairing avionicsrack and in the rear avionics compartment.

Flight Compartment Seats

Access to the compartment under the pilot seat structure is via a grill guard panel. Access to thecompartment under the copilot seat is via a grill guard panel inboard of the seat structure and a panelon the top of the seat structure.

Luggage Compartment

The radio compartment under the luggage compartment is concealed by trim panels which can beremoved for maintenance purposes.

Wing Fairing

Equipment in the wing fairing avionics rack is accessible by removing two panels on the fairingunderside.

Rear Avionics Bay

Access to rear avionics compartment is provided by two doors in the toilet compartment and one doorin the rear luggage bay forward bulkhead.

Nose Equipment Bay

The unpressurized nose equipment bay houses the nose landing gear and various avionics boxes. Thenose equipment bay can be accessed either through the nose cone (after removing the weather radar)or through two access panels located on either side of the nose structure aft of the nose cone. A metalsplash guard protects the equipment in the bay and a shield attached over the bay forward openingsimilarly protects the weather radar scanner.

Rear Equipment Bay

The rear equipment bay is unpressurized and access to the bay, via a hinged door on the underside ofthe fuselage, is only possible with the airplane on the ground. Pipelines forward of the access door, areenclosed by covers secured with quick-release fasteners. A box structure on the left-hand side of thebay houses main hydraulic system components.




Figure 13Cargo and Accessory Compartments




TOILET COMPARTMENT

The typical toilet compartment consists of a console assembly, flushing toilet with a fore and aftpositioned toilet services bulkhead. Access is provided to the rear baggage compartment and theavionics compartment from within the toilet compartment.

The washbasin console is installed on the right side and incorporates washing facilities, provision fortoilet requisites and the filling point for the wash water tank.

The toilet service’s bulkhead forms the mounting structure for a hinged mirror (to provide access to anavionics compartment/baggage compartment), an electric razor stowage socket and switch, an airlouver, mirror lamps and switch.

Electrical supplies to the razor socket are taken via a static inverter mounted in the avionicscompartment behind the hinged mirror. Water is pumped from a heated water tank below the washbasin.

Figure 14

AIR LOUVER

Typical Toilet Compartment




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Section - III SYSTEMS DESCRIPTION - SmartCockpit