CHALLENGER 601 - Golden Falcon Aviation · subject bo m bard i er challenger 601 operating manual...

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BO M BARD I ER

CHALLENGER 601 OPERATING MANUAL

PSP 601-6

SECTION 1

AIRCRAFT - GENERAL

TABLE OF CONTENTS

MODEL DESIGNATION AND TYPE

OPERATING ROLE AND DESIGN CONCEPT

STRUCTURE Wing Fuselage

Nose Section Center Section Tail Section

AIRCRAFT DIMENSIONS

AIRCRAFT TURNING RADII

DANGER AREAS

AIRCRAFT PARKING AND MOORING

COVERS AND PLUGS

AIRCRAFT ANTENNAS

DOORS Passenger/Crew Door Emergency Exit Door Baggage Compartment Door Rear Equipment Bay Door Service Doors

SERVICING POINTS

FLIGHT COMPARTMENT Instrument and Control Panels Crew Seats Cabin Sign Controls

LIST OF ILLUSTRATIONS

Figure Number

2

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4

5

Title

Aircraft General Details

Aircraft Basic Dimensions and Ground Clearances

Aircraft Turning Radii

Engine Intake and Exhaust Danger Areas

Aircraft Parking and Mooring

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1 - CONTENTS

Apr 29/2011

B OMBARDIER

CHALLENGER 601

OPERATING MANUAL PSP 601-6

LIST OF ILLUSTRATIONS

Figure Number Title

6 Aircraft Covers and Plugs

7 Aircraft Aitenna Locations

8 Passenger/Crew Door

9 Door Warning Indication

10 Baggage Compartment Door

11 Rear Equipment Bay Door

12 Service Doors and Panels

13 Aircraft Servicing Points

14 Cockpit General Arrangement

15 Cockpit Instrument and Control Panels

16 Center Pedestal Instrument and Control Panels

17 Overhead Instrument and Control Panels

18 Crew Seats

19 Cabin Sign Control Switches

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1 -CONTENTS

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BOMBARD/ £ R

CHALLENGER 601


SECTION 1

AIRCRAFT - GENERAL

1. MODEL DESIGNATION AND TYPE

The Challenger 601 aircraft, manufactured by Bombardier Aerospace, is designated Model CL-601, version 2A12. The aircraft is a swept-wing monoplane powered by two General Electric CF34-1 A Turbofan engines.

2. OPERATING ROLE AND DESIGN CONCEPT

Primarily, the CL 601 is a long range (transcontinental) business aircraft with a crew of two. The design concept is orientated toward carrying up to 19 passengers in spacious comfort over long distances. The combination of an advanced technology supercritical wing, quiet and efficient engines, and a wide body enables the CL 601 to achieve a high standard of performance, economy and passenger comfort.

3. STRUCTURE

A. Wing

The aircraft wing (see Figure 1) is an advanced technology symmetrical airfoil structure, manufactured as a single unit and bolted to the underside of the fuselage. The wing comprises left and right swept-back airfoils connected by a central box structure, and consists of skinned spars and ribs. Ailerons, flaps , spoilers, integral fuel tanks and the support structure for the main landing gear are incorporated into the wing. Wing leading edges are of aluminum alloy and incorporate thermal anti-icing. Each leading edge is made of three removable sections, tapering towards a winglet. Each winglet is constructed from aluminum alloy with a Kevlar leading edge.

Fuel for the aircraft is stored in three tank areas. The deep section airfoil each side is used as a main tank, and the center section is used as the primary auxiliary tank. A fuel-tight bulkhead, each side of the center section, separates the tanks. All tanks are compartmented to ensure a continuous supply of fuel to the engines under all normal flight conditions.

The main landing gear (MLG) assemblies, mounted under the wing left and right airfoils, inboard of the trailing edge flaps, are conventional oleo-pneumatic, shock absorbing struts, each fitted with two wheels. The MLG retracts inward into wheel bins in the underside of the fuselage.

8. Fuselage

The fuselage (see Figure 1) is an all metal, semi-monocoque structure comprising nose, center and tail sections riveted together. The fuselage consists of externally skinned frames, stringers and longerons. The nose section is mainly the flight compartment (cockpit) area, the center section is the passenger cabin area and avionics bay, under which the wing is bolted. The tail section is mainly an equipment bay to which the engines and empennage are attached .

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3. STRUCTURE (CONT'D)

(1) Nose Section

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The nose section is effectively divided by the cockpit floor into upper and lower halves. The upper half comprises the cockpit and forward avionics bay. The lower half comprises compartments for the brake accumulators and brake valve control mechanism, the air-driven generator (ADG), the flight control forward mechanisms and the nose wheel well and mounting structure.

A weather radar antenna pedestal, mounted in front of the upper and lower nose section halves, is enclosed by a cone-shaped radome made from Kevlar. The radome is provided with a system of conductive paths to reduce the risk of, and damage from, lightning strikes.

The nose landing gear (NLG) assembly, mounted on the underside of the nose section lower half, at the rear of a wheel well , is a conventional oleo-pneumatic, shock absorbing strut fitted with two steerable wheels. The NLG retracts forward into the wheel well and is enclosed by hydraulically actuated doors.

(2) Center Section

The center section is divided by a single-level floor into the pressurized passenger compartment (cabin area) and the underfloor area. The passenger compartment incorporates the passenger/crew entrance door and the baggage door on the left side, an overwing emergency exit door on the right side, and six windows on each side, including one in the emergency exit door. The underfloor area is divided by pressure bulkheads into three sections as follows:

• The pressurized avionics bay which houses various electronic components and the forward auxiliary tank

• The unpressurized MLG wheel bay, which is provided with wheel bins to accept the wheels when retracted, and which houses the reservoir and other components of the No. 3 hydraulic system

• The pressurized rear fuselage underfloor area, which contains the rear auxiliary tank.

(3) Tail Section

The unpressurized tail section comprises the rear equipment bay, the vertical stabilizer/rear fuselage frame structure and the tail cone. The rear equipment bay houses the auxiliary power unit (APU), two air conditioning cooling units, the reservoirs and other components of hydraulic system No.1 and No.2 and the aircraft battery. An access door is provided at the bottom of the rear equipment bay, towards the rear of the aircraft.

The engine pylons are secured to the rear equipment bay, above the horizontal centerline on each side. The engines are attached to yoke extensions on each pylon. A pressure bulkhead is built into the front of the rear equipment bay to withstand the pressure in the fuselage center section.

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The vertical stabil izer/rear fuselage frame structure is secured to the rear equipment bay. A fully cantilevered, swept-back, vertical stabilizer projects upward from the rear fuselage structure and is surmounted by a swept-back horizontal stabilizer. A single rudder is hinged to the rear of the vertical stabilizer and an elevator is hinged to each side of the horizontal stabilizer trailing edge. To streaml ine the rear of the fuselage, a tail cone is attached to the rear of the rear fuselage frame structure. •

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3. STRUCTURE (CONT'D)

SOMSAROleR

CHALLENGER 601


PRESSURIZED PASSENGER COMPARTMENT (FUSELAGE CENTRE SECTION>

PILOTS BULKHEAD-----~:.._

FORWARD AVIONICS BAYCUNPRESSURlZEDI

WING CENTRAL BOX STRUCTURE

NOSE LANDING GEAR

WING TO FUSELAGE FRONT FAIRING "'....

Aircraft General Details Figure 1

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BAGGAGE DOOR

BULKHEAD

F.NGINE PYLON

MAIN LANDING GEAR WHEEL SAY

WING TO FUSELAGE REAR FAIRING

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HORIZONTAL STABILIZER

o~ REMOVAB~ LEAOING EDGES/

WINGLET

• 4. AIRCRAFT DIMENSIONS

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CHALLENGER 601


All basic dimensions, including ground clearances, are given in Figure 2 .

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CHALLENGER 601


4. AIRCRAFT DIMENSIONS (CONT'D)

Z7ft9in

t 8ft 10in

l Cabin interior dimensions

length Width lmax dial Headroom (floor to max height) Volume Floor area FJoor width

28ft3in 8ft2in 6ft1in 1150 cu ft 202.5 sq ft 7ft2in

.& Measurement at manufacturers empty weight

& 21 feet elevator up

& Open passenger door ground clearance 4 inches

I r3ft1 in

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0 0 0 0 0

Aircraft Basic Dimensions and Ground Clearances Figure 2

l .20ft 4in

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l 20ttsm&&

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• 5. AIRCRAFT TURNING RADII

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Using the nose gear steering control wheel, the pilot can turn the aircraft, during taxiing, without the use of differential braking. Figure 3 shows the turning radii applicable to the maximum nose wheel steering angle of 55 degrees, the minimum taxi strip width required for a 180 degree turn at the maximum steering angle, and the turning radii for the maximum towing angle of 90 degrees .

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BO M BAROIE:R

CHALLENGER 601 OPERATING MANUAL

PSP 601-6

5. AIRCRAFT TURNING RADII (CONT'D)

NOTE

Lesser steering angles reQuire wider ta>ci stnP for 1ao• tum.

(

MAXIMUM TURNING RADII USING NOSE WHEEL SiEERING CMAXJMUM STEERING ANGLES 52• TO 55°)

MINIMUM TURNING RADII WITH NOSE WHEEL AT 90• CAIRCRAFT MAXIMUM TOWING ANGLE)

Aircraft Turning Radii Figure 3

61 FT M INIMUM TAXI STR" WIDTH FOR 1l!O O!GREE TVRN

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CHALLENGER 601


• 6. DANGER AREAS

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It is essential that persons involved with engine running are aware of the danger areas in front of and to the rear of the engines. Before running an engine, the information shown in Figure 4 must be used to consider the safety of persons, equipment and buildings in the vicinity of the aircraft .

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6. DANGER AREAS (CONT'D)

10!.£ THRUST

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CHALLENGER 6 0 1


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393"C 200 FT/S 174-0"F I '136 MPH) -

20 100 FT/ S (68 MPH

30

40 50 FT / S <34 MPHl

50 FT

60

30 FT/S 10 (20 MPHl

80

90

100 FT

110

120I

130

60°C (140"Fl

Zl"C 180°Fl

18 FT

!OLE THRUST

60°C 1140°FJ

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MAXIMUM THRUST

400 FT/ S <272 M PH!

200 FT/ S (136 MPHI

100 FT/ S (68 MPH)

50 FT/ S (34 MPHI

Engine Intake and Exhaust Danger Areas Figure 4

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CHALLENGER 601


• 7. AIRCRAFT PARKING AND MOORING

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When the aircraft is stationary on the ground, precautions must be taken to ensure safety of personnel and equipment. The extent of safety measures to be observed depends upon the prevailing or expected weather conditions and the expected length of time the aircraft will be stationary. For complete safety, the aircraft should be parked in a hangar but, if this is not possible, the aircraft must be parked or moored into wind, with landing gear locking pins installed, as shown in Figure 5.

Parking the aircraft also entails checking that the flight controls are in neutral, battery switches are off, parking brake is on, doors are closed and that wheels are chocked .

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BOMBARDIER

CHALL£NG£R 601


7. AIRCRAFT PARKING AND MOORING (CONT'D)

0 HOIST RING

NOSE GEAR GROUND LOCKING PIN

0 Aircraft Parking and Mooring

Figure 5

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• 8. COVERS AND PLUGS

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To protect the intakes and exhaust from foreign object ingestion, and to protect sensitive equipment from accidental damage, it is essential to install covers and plugs as shown in Figure 6 .

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CHALLENGER 601


THIS PAGE INTENTIONALLY LEFT BLANK

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CHALLENGI E R ER601

8. COVERS AND PLUGS (CONT'D) OPERATING MANUAL PSP 601-6

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ENGll-E EXHAUST

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STATIC PRESSURE SENSOR

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NOTE Windshield and covers not illust nacelle rated.

MAIN WHEEL

AIR CONDIT EXHAUST l~ONT ING CONTROL & RIGHT!

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• 9. AIRCRAFT ANTENNAS

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CHALLENGER 601


The location and nomenclature of the aircraft antennas are shown in Figure 7 .

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RADAR (18" FLAT PLATE)

SFM601_01 _008

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TRANSPONDER 2 TRANSPONDER 1 OTHER SIDE

VHF 2

VLF ANTENNA (SPACE PROVISION)

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CHALLENGER 601


• 10.DOORS

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The aircraft is provided with a passenger/crew door, a baggage compartment door, a rear equipment bay door, landing gear doors and various small doors which provide access to servicing points. An overwing emergency exit door is provided on the right side of the passenger compartment.

The baggage compartment and emergency exit doors are of the plug type which open inward; all other doors open outward. All doors are flush with the aircraft outer skin when closed.

A. Passenger/Crew Door

The entrance door is manually operated and downward opening with the stairs forming an integral part of the door structure (see Figure 8). Its movement is controlled by a counterbalance system of gas springs.

The latching mechanism is operated by a single-lever inner handle, located on the forward side of the steps, a T-handle which is recessed in a riser of a step, and an external handle with a keylock. A pull-in handle on the rear handrail can be used to reduce the force required to close the door from inside the aircraft.

Once closed, the door is latched from the inside by pushing the inner handle downward. The T-handle is then pulled out of its recess to stow the external handle, which clicks audibly when stowed. Verification that the external handle is stowed can be made by ensuring that the inner handle cannot be pulled up. After this check, the T-handle must then be stowed in the riser of the step.

The door is unlocked from the inside when the inner handle is pulled upward, ejecting the external handle from its pocket. The door is then unlatched by continuing to pull the inner handle upward. As the door opens, the handrails unfold upward.

The door unlocks from the outside by the operation of a PUSH trigger in the external handle, which is ejected from its pocket. To unlatch the door, the external handle is then turned 45 degrees counterclockwise. Pull- out and pull-in handles are also provided to assist the operator in opening or closing the door from outside or inside, respectively. When the door is fully open, a door support leg extends to the ground.

The DOOR INDICATION panel, located on the center pedestal, provides a visual indication to the flight crew of the passenger/crew door and the baggage compartment door status (see Figure 9) .

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DOORS (CONT'D) 10.

\ ..

. . : : . : . : · · ....

INNER HANDLE

RD/ER 1 B 0 ,.. BLAENGER 60 CHAL


C w Door Passenger/ re Figure 8

HANOGRIP

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CHALLENGER 601


• 10. DOORS (CONT'D)

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PASSENGER/ CREW DOOR NOT READY LIGHT

Amber light comes on when the T-handle is not correctly sttiwed.

DOOR @ r-INDICATION 1

PASSENGER/ CREW DOOR READY LIGHT

Green light comes on when the external and internal

handles are stowed.

PASSENGER/ CREW DOOR UNLOCKED LIGHT

Amber light comes on when the door is unlatched, or when the external handle is not stowed.

BAGGAGE COMPARTMENT DOOR UNSAFE LIGHT

Amber light comes on when d()()( locking plungers are not safety engaged.

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Door Warning Indication Figure 9

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10. DOORS (CONT'D)

B. Emergency Exit Door

B OMBARDI E: R

CHALLENGER 601


For details of the emergency exit door, refer to Section 8, EMERGENCY EQUIPMENT.

C. Baggage Compartment Door

The baggage compartment door is located on the left side of the aircraft, immediately aft of the passenger compartment (see Figure 10). The door opens inwards and upwards on two sets of tracks attached to the structure, and is assisted during opening by balance springs with cable attachments to the door and structure. The door is held closed by two plungers which locate inside fittings attached to the door frame, and which are operated by an external handle via levers and push-pull rods.

Two plunger actuated proximity switches are installed to provide an indication in the cockpit, when the door is not safely closed.

The baggage compartment door can be operated from either the inside or the outside by a handle mechanism located near the bottom of the door. The handle stows flush into a pocket in the door outer skin and in this position, acts as a lock for the latching mechanism. The handle has a keylock which unlocks or locks the PUSH trigger. The PUSH trigger, when pushed, ejects the handle, which is then turned to release the locking plungers and open the door.

D. Rear Equipment Bay Door

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The rear equipment bay door (see Figure 11 ), located at the bottom of the rear fuselage, provides access to the APU, engine oil replenishment system, air conditioning units, • replenishment points for No. 1 and No. 2 hydraulic systems, and the aircraft battery. The door opens downward, and is secured at the forward edge by two hinges which are equipped with quick-release pins to facilitate easy door removal.

The rear equipment bay door is held closed by two plungers at the rear edge, and is opened and closed by a handle. Handle operation is the same as for the baggage compartment door, with the exception that the rear equipment bay door must be supported during opening because of the opening direction.

E. Service Doors

Quick-release service doors and panels are provided for easy access to the servicing points throughout the aircraft. Location and nomenclature of these doors and panels is given in Figure 12.

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BALANCE SPP.ING BOXES

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CHALLENGER 601


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Baggage Compartment Door Figure 10

HANDLE _

~~ HAN DLE UNSTOW BUTTON

-... .. ........... r t

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10. DOORS (CONT'D)

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EXTERIOR HANOLE

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CHALLENGER 601


VENTILATION LOUVERS

Rear Equipment Bay Door Figure 11

PLUNGER SOCKET

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REFUELI NG CONTROL

UPPER ELECTRONICS EQUIPM£NT BAY

BRA KE AND STEER ING HYDRAULIC BAY

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CHALLENGER 601

OXYGtN REFILL

FLI GH T COMPARTMENT UNDERFLOOR AND AVIONICS BAY ACCESS


FLIGHT CONTROLS ACCESS APU CONTROL AND GROUND AIR START

• Service Doors and Panels Figure 12

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11. SERVICING POINTS

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CHALLENGER 601


The location and details for all aircraft servicing points are shown in Figure 13.

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CHALLENGI E R ER601 OPERATING MANUAL

PSP 601-6 11. SERVICING POINTS (CONT'D)

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1 BRAKE ACCUM CHARGING PO~N!f TOR AND INTERPHONE S

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PRESSURE REFUEL I DEFUEL p:r- ..:·. . l AND ADAPTER

0 OX)'.GEN SYSTEM VALVE AND G=GING

IT\ NO. J HYDRA ~ CHARG IN ULIC SYSTEMACC

N-0. JHYORAULIC SY5TE G POINT AND PR<SSU~lATOR M RESERVOIR FILLIR UGE CONNECTION

Aircraft Serv· . . icing Points Figure 13

DC EXTERNAL POWER

r

.. FUEL TANK WATER DRAIN ITYPl

NO. z HYDRAULIC SYSTEM

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ACCUMUIJ, TOR PRESSURE GAU /,.... GE ---

APU FAULT PA AIR CONNECT!~~ ANO GROUND

AC EXTERNAL POWER

OVERWING GRAV ITY FUEL FILLER ITYPI

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CHALLENGER 601


• 12. FLIGHT COMPARTMENT

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The flight compartment (cockpit) contains the aircraft instrument, warning light, control and circuit breaker panels, two crew seats and the flight control columns, wheels and pedals. The cockpit structure incorporates the windshield, including a pilots eye locator that enables seat adjustment for optimum field of vision.

Miscellaneous items in the cockpit include a portable fire extinguisher, located behind the copilot's seat on the bulkhead that separates the cockpit from the passenger compartment, two oxygen masks, two cup holders, and storage boxes and pouches for checklists etc.

A. Instrument and Control Panels

For location of panels, controls, switches, lights and instruments refer to Figure 14, Figure 15, Figure 16 and Figure 17.

8. Crew Seats

The pilot's and copilot's seats are identical, except that certain controls are installed on opposite sides; on both seats, inertia reel and forward/rearward controls are located inboard, and lumbar support, height and reclining controls are located outboard (see Figure 18).

C. Cabin Sign Controls

The NO SMOKING and FASTEN SEAT BELT signs in the passenger compartment are controlled manually or automatically through switches located on the center pedestal (see Figure 19) .

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CHALLENGER 601


12. FLIGHT COMPARTMENT (CONT'D)

AURAL WARNING/INTERCOM SPEAKERS

~ ~

PILOT'S INSTRUMENT PANEL

GLARESHIELD

CENTER INSTRUMENT PANEL

__ - ,

COPILOT'S INSTRUMENT PANEL

Cockpit General Arrangement Figure 14

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Al RSPEED LIMITS DECAL RIGHT FLIGHT SPOILER DEPLOYED INDICATOR RIGHT ENGINE FIRE WARNING LIGH '---------. SYSTEM UNLOCKED INDICATOR LEFT ENGINE REVERSE THRUST SYSTEM EMERGENCY STOW PUSH·BUlTON

LEFT ENGINE REVERSE THRUST}

RADIO ALTIMETER LEFT FLIGHT SPOILER OEPLE>YEO 1NOICATOR

/EXTINGUISHER ARM SWITCH LEFT ENGINE REVERSE THRUST

ALTIMETER LEH GROUND SPOILER DEPLOYED INDICATOR

APU FIRE WARNING LIGHT-----. /EXTINGUISHER ARM SWITCH

SYSTEM DEPLOYED INDICATOR

RIGHT ENGINE REVERSE THRUST] ATIITUOE DIRECTOR INDICATOR RIGHT GROUND SPOILER

DEPLOYED INDICATOR MACH/Al RSPEED INDICATOR- FLIGHT DIRECTOR SELECTION

AND ANNUNCIATOR PANEL

BOTILE 2 ARMED PUSH TO DISCHARGE

GYRO FAST ERECT swrrCHJUGHT

PITOT HEAT LIGHT--

STALL PROTECTION SYSTEM TEST INDICATOR

AUTOPILOT FAil iNDiCATORS

AUTOMATIC FLIGHT CONTROL SYSTEM DISENGAGE SWITCH

MASTER CAUTION INDICATOR AND RESET SWITOI

{

AIRWAY

MARKER MIOOtE LIGHTS

OUTER

COMPASS CONTROL PANEL

HIGH/LOW SELECTOH SWll CH

INSTRUMENT COMPARATOR

NOSE WHEEL STEER FAJL LIGHT INDICATOR

PARKING BRAKE OPERAING HANDLE

APU EXTINGUISHER PUSH TO OtSOtARGE

FLIGHT SURFACE TRIM ___ ____ _, INOICATOR

FLIGHT SURFACE POSITION----------' INDICATOll

SYST.EM UNLOCKED INDICATOR RIGHT ENGINE REVERSE THRUSTSYSiEM EMERGENCY STOW PUSH· BUTTON

RIGHT ENGINE REVERSE THRUST STALL PROTECTION SYSTEM SYSTEM DEPLOYED INDICATOR --TEST INDICATOR

ENGINE OIL TEMPERATURE INDICATOR CABIN ALTITUDE AND PRESSURE DIFFERENCE/RATE Of CLIMB

ENGINE OIL PRESSURE INDICATOR

FUEL QUANTITY PANEL

'----FUEL CONTROL PANEL

ENGINE APR AND '------ ENGINE SPEED CONTROL

PANEL

ENGINE INSTRUMENT LIGHTS '---- ---- DIMMING CONTROL PANEL

STATIC SOURCE SELECTOR SWITCHES

---AURAL WARNING TEST PANEL

AUDIO CONTROL PANEL

LIGHTING CONTROL PANEL

OXYGEN PRESSURE INDICATOR

FOOT WARMER CONTROL l<NOH

WINDOW DEMIST CONTROL KNOB

FLAPS FAIL ANO POU MOTOR OVERHEAT WARNING LIGHTS

MLG BAY OVERHEAT WARNINGEBL!:ED AIR LEA" DETECT PANEL

WING FLAPS POSITION INDICATOR

L ANDING GEAR CONTROL - HANDLE ANO INDICATION

FIRE WARNING TEST PANEL OXYGEN MASK

LOCATION VERTICAL NAVIGATION

'---------COMPUTERICONTROLLE~

STANDS~:;.~~~~~ "---------ICE DETECTOR PANEL NLG DOOR

WARNING LIGHT

EMERGENCY LIGHTING PANEL ___ _, OXYGEN MASK LOCATION

VERTICAL SPEED INDICATOR

ENGINE VIBRATION PANEL CME i n SELECTOR SWITCH -----'

FLIGHT DlflECTOR SVlllCltlNG PANEL------"

Cockpit Instrument and Control Panels Figure 15

~~~R~A~ZT~~~~~N ------------l '----------RADAR INDICATOR

PANEL

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WEIGHT-ON·WHE ELS FAIL WARNING LIGHTS

FLIGHT COMPARTMENT AND CABIN _____ _. TEMP CONTROL PANEL

FIRE EXTINGUISHER MONITOR ______ _. PANEL

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FLIGt-:T ANO GROUND SPOILER WAi'WING PANEL

DOOR WARNl~JG LIGHTS ANO ~ABIN SIGNS SWITCH PAN a

NAV 2/COMM2 CONTROL PANEL

AUTOPILOT CONTROL PANEL

AUTOPILOT STATUS PANEL

AOF CONTROL PANEL

LANOINGG~R MANUAL RELEASE HA.NOLE

fi"i"'---- DC METERING ?ANEL

DC POWER MANAGEMEt.T PANEL

Center Pedestal Instrument and Control Panels Figure 16

REVERSE THRUST ARM LIGHTS AND SVllTCHES

NAV 1 CONTROL PANEL

REMOTE COURSE SELECTOR PANE!.

AIR DRIVEN GENERATOR CONTROL PANEL

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BOMBARO I E: R

CHALLENGER 601

OPERA TING MANUAL PSP 601-6


j .......: '~c l-.C- ,.\.T_,

) •w,1 •n 1 • • -c- ~:r:U'

Overhead Instrument and Control Panels Figure 17

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BOMBARDIE:R

CHALL£NG£R 601



QUICK-RELEASE BUCKLE SHOULDER STRAPS

Front of buckle can be turned to simultaneously release shoulder straps, crotch strap and one part of lap belt; buckle remains anached to other part of lap belt. Snap-in attachments are incorPOrated at Strap ends so that safety harness can be easily connee1ed.

LAP BELT

HEIGHT CONTROL LEVER

Releases height lock to allow vertical adjust· ment of seat. Seat locks in selected pQSition when lever is released.

Crew Seats Figure 18 (Sheet 1 of 2)

LUMBAR SUPPORT

ARMREST CONTROL BUTTON

Releases armrest lock to allow angular adjustment of armrestS .

RECLINE CONTROL LEVER

Releases seatback lock to auow adjustment from upright to recline. Seatback locks in position when lever is released.

LUMBAR SUPPORT CONTROL VALVE

Releases air from lumbar support to suit contour of pilot's back.

With pl1ot's back pressed against support, opening valve allows support to match contour of pilot's back, and closing valve aUows support to maintain selected shape. With no pressure on support, ·operling valve allows support to return to original shape.

NOTE C\J

Pilot's seat shown, copilot's seat identical but opposite. ~ I ~

0 I

0 0 <O ~ LI.. CJ)

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CHALL£NG£R 601



INERTIA REE L

INERTIA REEL CONTROL LEVER

When the lever is fully forward the inertia reel allows shoulder strap reel·out until straP acceleration exceeds 19. men the reel locking device operates to prevent reel-out.

When the lever is fully rearward, the inertia reel is locked. thus allowing no reel-out of shoulder straps, and the harness is effectively f ixed.

FORWARD/ REARWARD MOVEMENT CONTROL LEVER Releases seat/track loclt to allow seat forward/ rearward movement. Releasing control lever allows locking pins to engage when aligned with holes in t rack.

Track tock positions are approximately one inch apart.

Crew Seats Figure 18 (Sheet 2 of 2)

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CHALLENGER 601


• 12. FLIGHT COMPARTMENT (CONT'D)

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CABIN SIGNS NO SMKG SEAT BLTS

ON 9 OFF @)

NO SMOKING SIGN SWITCH

When set to ON, the cabin NO SMOKING sign comes on and remains on until set to OFF or AUTO. When set to AUTO, the sign comes on if cabin air pressure is low or the landing gear is down.

AUTO

SEAT BELT SIGN SWITCH

When set 10 ON, the cabin FASTEN SEAT BELT sign comes on and remains on until set to OFF or AUTO. Wt'ten set to AUTO. the sign comes on if cabin air pressure is low, or the landing gear is down, or if the flaps are at any angle other than 0 degrees.

Cabin Sign Control Switches Figure 19

0 C\J 0

I ~

0 I

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0 co ~ u.. (/)

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BOMBARDIER

CHALLENGER 601



SECTION 1 Page 38

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CHALLENGER 601 - Golden Falcon Aviation · subject bo m bard i er challenger 601 operating manual...

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