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BOMBARDIER Challenger 601-3A CL-600-2B16, Pilot Training Manual

The BOMBARDIER Challenger 601-3A CL-600-2B16 is a powerful and sophisticated private jet, renowned for its exceptional performance and luxurious amenities. To ensure you have all the necessary knowledge and skills to fly this aircraft, we provide a comprehensive Pilot Training Manual available for free download on our website manualshive.com.

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1.

Hydraulic systems No. 1 and No. 2 each
have:

A. One engine-driven pump and one elec-

trically driven pump

B. Two electrically driven pumps
C. One engine-driven pump only
D. One electrically driven pump only

2.

The hydraulic reservoirs are:

A. Unpressurized
B. Pressurized by engine bleed air
C. Pressurized by a bootstrap system
D. Pressurized by a nitrogen precharge

3.

Motor-operated firewall shutoff valves
are installed in the:

A. Suction lines to all hydraulic pumps
B. Suction lines to all electrically driven

pumps

C. Pressure lines of the two engine-

driven pumps

D. S u c t i o n   l i n e s   o f   t h e   t wo   e n g i n e -

driven pumps

4.

The 3B pump operates:

A. Only when the ADG is deployed
B. Only when switched on with the NO.

3 ELECT PUMP switch

C. Automatically when the ADG is de-

ployed, or when switched on with the
NO.3B ELECT PUMP switch

D. When the ADG is deployed and the

N O . 3   E L E C T   P U M P   s w i t c h   i s
placed on

5.

Fluid filtration occurs:

A. Only in the pressure system
B. Only in the return system
C. Only in the bypass system
D. In the pressure system, the return sys-

tem, and the case drain system

6.

If the left generator fails in flight, B
pump(s):

A. In the No. 2 system will be inoperative
B. In the No. 1 system will be inoperative
C. In both the No. 1 and No. 2 systems

will be inoperative

D. In the No. 3 system will be inoperative

7.

The three hydraulic systems are:

A. Always hydraulically interconnected
B. Never hydraulically interconnected
C. Interconnected under certain condi-

tions

D. None of the above

8.

In flight, when a No. 1 and No. 2 gener-
ator failure occurs while the APU is not
operating, hydraulic pressure in system
No. 3 is provided by:

A. The 3B pump
B. The 3A and 3B pumps
C. Engine-driven pumps
D. None of the above

FlightSafety Canada 

L t é e
L t d .

CL-600-2B16 PILOT TRAINING MANUAL

13-10

CL 601-3A/R

FOR TRAINING PURPOSES ONLY

QUESTIONS

Summary of Contents for Challenger 601-3A CL-600-2B16

Page 1: ...gin A vertical line adjacent to blank space means that material has been delet ed In addition each revised page is marked Revision 01 in the lower left or right corner The changes made in this revision will be further explained at the appropriate time in the training course FlightSafety international COURSEWARE SUPPORT HURST 8900 Trinity Blvd Hurst Texas 76053 817 276 7500 Fax 817 276 7501 the bes...

Page 2: ... Dorval Quebec Canada H9P 1A2 800 573 4025 www flightsafety com Canadair CHALLENGER CL 601 3A R MODEL CL 600 2B16 PILOT TRAINING MANUAL VOLUME 2 AIRCRAFT SYSTEMS FlightSafety CanadaLtee Ltd FlightSafety CanadaLtee Ltd ...

Page 3: ...anada H9P 1A2 800 573 4025 Fax 514 631 2263 FlightSafety Texas Houston Learning Center 7525 Fauna Street Houston TX 77061 800 927 1521 Fax 713 644 2118 FlightSafety International Tucson Learning Center 1071 E Aero Park Blvd Tucson AZ 85706 800 203 5627 Fax 602 889 9619 Copyright 2003 by FlightSafety International Inc All rights reserved Printed in the United States of America ...

Page 4: ...ation 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 or the FAA that of the manufacturer or the FAA shall take precedence We at FlightSafety want you to have the best training possible We welcome any suggestions you might have for improving this manual...

Page 5: ...WER 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 SYSTEMS Chapter 14 LANDING GEAR AND BRAKES Chapter 15 FLIGHT CONTROLS Chapter 16 AVIONICS Chapter 17 MISCELLANEOUS SYSTEMS WALKAROUND APPENDIX ANNUNCIATOR PANEL INSTRUMENT PANEL POSTER ...

Page 6: ...ollowing chapters are specifically affected by differences between models please take the indicated actions to make your manual correspond to the model of your aircraft Chapters Affected Action Chapter 2 Electrical Pages 2 21 through 2 29 Discard Appropriate Pages Chapter 5 Fuel System Discard Appropriate Pages Chapter 7 Powerplant Discard Appropriate Pages Chapter 9 Pneumatics Discard Appropriate...

Page 7: ...osition SYL 7 Curriculum Title SYL 7 Curriculum Prerequisites SYL 7 Course Objectives SYL 10 Training Schedule Typical SYL 10 Simulator and Flight Training SYL 13 Completion Standards SYL 13 AIRCRAFT GROUND TRAINING CURRICULUM SEGMENT SYL 14 Curriculum Segment Outline SYL 14 Training Module Outlines SYL 15 FOR TRAINING PURPOSES ONLY FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL ...

Page 8: ...RRICULUM SEGMENT SYL 21 Training Hours SYL 21 Flight Training Module Outlines SYL 21 Completion Standards SYL 25 FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL SYL ii CL 601 3A R FOR TRAINING PURPOSES ONLY ...

Page 9: ...IONS Figure Title Page SYL 1 Montreal Facility Floor Plan SYL 2 SYL 2 Houston Facility Floor Plan SYL 3 SYL 3 Tucson Facility Floor Plan SYL 5 FOR TRAINING PURPOSES ONLY FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL ...

Page 10: ...rnational Airport 1071 E Aero Park Blvd Tucson AZ 85706 DESCRIPTION OF TRAINING FACILITY Each classroom and briefing room is adequately heated lighted and ventilated to conform to local building sanitation and health codes The building construction prevents any distractions from instruction conducted in other rooms or by flight operations and maintenance operations on the airport Classrooms are eq...

Page 11: ... MAINTENANCE MAINTENANCE INSTRUCTOR S AREA LOUNGE WOMEN MEN CLASSROOM 4 CLASSROOM 5 CLASSROOM 6 CLASSROOM 7 SELF STUDY ROOM STAIRS DOWN STAIRS DOWN EXIT DOWN EXIT EXIT EXIT EXIT STAIRS UP PUBS OFFICE EXIT STORAGE OFFICE RECEPTION AREA EXIT EXIT UTILITY ROOM EXIT FlightSafety Canada Ltee Ltd Canadair Challenger Learning Center BR 3 O2 LEGEND O2 EMERGENCY OXYGEN EQUIPMENT FIRST AID KIT LOCATIONS BAS...

Page 12: ...141 ROOM 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 RECEPTIONIST MANAGER DOS DOT TECH LIBRARY MAIN ENTRANCE SIMULATOR SUPPORT INSTRUCTORS FAUNA STREET MARKETING FALCON 20 MU 2 G I KING AIR AUDIO VISUAL H 700 CUSTOMER SERVICE CUSTOMER SERVICE 2 7525 ...

Page 13: ...G ROOM TRAINING ROOM TRAINING ROOM 3 OFFICE MEN OFFICE TRAINING ROOM OVERFLOW BRIEFING ROOM EXIT DIRECTOR OF STANDARDS OFFICE OFFICE ATR 42 72 BRIEFING ROOM CUSTOMER SUPPORT LOUNGE COMPUTER ROOM POWER ROOM EXIT EXIT CHALLENGER C601 3A ATR 42 72 B737 300 MEN WOMEN COFFEE SHOP EMB 120 BAe 800 OFFICE B737 300 FALCON 50 CHALLENGER BREIFING ROOM BREIFING ROOM BREIFING ROOM BREIFING ROOM BREIFING ROOM T...

Page 14: ...118 MEN WOMEN EXERCISE ROOM 103 MARKETING 104 CUST SUPPORT MGR 106 ASS T MGR 107 CUSTOMER SUPPORT REPRESENTATIVE 105 MANAGER 109 AD M IN 108 DOT 102 TOILET STORAGE 101 STORAGE CPM 119 CPM 137 BRIEF 136 CPM 122 BRIEF 123 CPM 134 MAINTENANCE 125 LOBBY CONFERENCE ROOM 110 DOMT 115 INSTRUCTORS 114 INSTRUCTORS 111 PROGRAM MGRS 112 VEST FIRST FLOOR Learjet Learning Center Tucson Arizona FlightSafety int...

Page 15: ...CLASSROOM 213 CLASSROOM 212 CLASSROOM 211 CLASSROOM 210 CLASSROOM 209 CLASSROOM 207 CLASSROOM 205 MAINT LAB 204 CLASSROOM 17 203 SELF LEARNING 202 LIBRARY 201 VEND 206 LOUNGE COFFEE CLASSROOM 224 CLASSROOM 223 CLASSROOM 222 CLASSROOM 221 CLASSROOM 220 CLASSROOM 219 CLASSROOM 218 STORAGE 217 MEN WOMEN STORAGE 208 TELE TELE SECOND FLOOR Learjet Learning Center Tucson Arizona FlightSafety internation...

Page 16: ...ht simulator in flight in a CL 600 Series airplane if the pilot 1 Holds a private pilot certificate with an airplane rating 2 Holds an instrument rating or concurrently completes the instrument course 3 Has a minimum of 1 000 hours flight experience in airplanes as a pilot May be waived at the discretion of the Center Manager 4 Holds a MEL category rating without centerline thrust limitation 61 15...

Page 17: ...th a CL 600 type rating Completion Methods The completion methods are as follows 1 100 Flight Simulator with no Limitations 2 100 Flight Simulator with 15 hours SOE Limitation 3 100 Flight Simulator with 25 hours SOE Limitation 4 Combination of Flight Simulator and Aircraft with no Limitation 100 Flight Simulator with No Limitations A pilot may complete all of the practical test required for a CL ...

Page 18: ...uisites listed above the pilot may be eligible to complete 100 in the flight simulator and receive a certificate with the following limitations A pilot who qualifies under this subparagraph may not act as PIC of a CL 600 Series airplane and will be issued a CL 600 type rating or an ATP certificate with a CL 600 type rating as ap propriate with the limitation This certificate is subject to 25 hour ...

Page 19: ... the applicable standards prior to the start of any training or evaluation session The required standards will be discussed with the pilot being trained COURSE OBJECTIVES Upon the completion of this course the pilot will have the necessary knowledge and skills to demonstrate that he she is the master of the aircraft with the successful outcome of a proce dure or maneuver never in doubt and to meet...

Page 20: ...and Rain Protection Systems Air Conditioning System Pressurization Oxygen Systems Day 8 Classroom 7 0 Entire System Review Examination Day 9 Classroom 6 0 Airplane Flight Manual Flight Planning Performance Weight and Balance Day 10 Classroom 6 0 3A R Avionics FMS Systems Integration Day 11 Classroom 6 0 3A R Avionics FMS Systems Integration FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MA...

Page 21: ...imulator Pre Post Briefings 1 5 Flight Simulator Period Five 4 0 Day 17 Briefing Room Oral and Pre Post Briefings 2 5 Flight Simulator Period Six Simulator Practical Test 4 0 Aircraft Preflight Inspection 2 0 Day 18 Simulator Pre Post Briefings 1 5 Flight Simulator Period Seven LOFT 2 5 or Aircraft Flight Training if required 1 5 Day 19 Aircraft Practical Test if required 1 0 NOTE Flight time may ...

Page 22: ... doubtful that the pilot will become proficient Further training shall be given only after review by the Center Manager Discussed D This designation indicates that the item was discussed and not performed in the simulator or aircraft The discussion revealed a satisfactory knowledge of the ap propriate procedure aircraft system etc Trained T Trained in maneuvers for procedures only no flight traini...

Page 23: ...y Administration General Operational Subjects Modules A Weight and Balance B Performance C Flight Planning D Approved Flight Manual E Windshear optional F High Altitude Training if required Aircraft Systems Modules A Aircraft General B Electrical Power C Lighting D Master Warning E Fuel F APU G Powerplant H Thrust Reversers I Fire Protection J Pneumatics K Ice and Rain Protection L Air Conditionin...

Page 24: ...icate holder and to the aircraft in which the training is being conducted Training in general operational sub jects are not conducted by FlightSafety unless specifically pertinent to this course A Weight and Balance Module 1 General Elements a Principles and Methods of Weight and Balance Determination 2 Limitation Elements 3 Operational Elements B Aircraft Performance Module 1 General Elements a U...

Page 25: ...ment of Wind Models 4 Model of Flight Crew Actions a Evaluate the Weather b Avoid Known Windshear c Consider Precautions 1 Takeoff Precautions 2 Approach Precautions d Follow Established Standard Operating Techniques e Windshear Recovery Techniques 1 Encounter During Takeoff After Lift off 2 Encounter on Approach 3 Encounter During Takeoff On Runway F High Altitude Training IAW 61 31 f l i as requ...

Page 26: ... and Components c Annunciators d Miscellaneous 2 Operational Elements 3 Limitations Elements 4 Emergency Abnormal Procedure Elements C Lighting Module 1 General Elements a System Description b Controls and Components c Miscellaneous 2 Operational Elements 3 Limitation Elements 4 Emergency Abnormal Procedure Elements D Warning Systems Module 1 General Elements 2 Operational Elements 3 Limitations E...

Page 27: ...tors 2 Operational Elements 3 Limitation Elements 4 Emergency Abnormal Procedure Elements H Thrust Reversers Module 1 General Elements 2 Operational Elements 3 Limitation Elements 4 Emergency Abnormal Procedure Elements I Fire Protection Module 1 General Elements 2 Operational Elements 3 Limitation Elements 4 Emergency Abnormal Procedure Elements J Pneumatics Module 1 General Elements 2 Operationa...

Page 28: ...ments 2 Operational Elements 3 Limitation Elements 4 Emergency Abnormal Procedure Elements N Hydraulics Module 1 General Elements a System Description b Controls and Components c Indicators Indications d Annunciators 2 Operational Elements 3 Limitation Elements 4 Emergency Abnormal Procedure Elements O Landing Gear and Brakes Module 1 General Elements a System Description b Controls and Components...

Page 29: ...eview Module 1 Written Examination with a Passing Grade of 70 Corrected to 100 Systems Integration Modules Systems Integration provides the pilot with instruction on aircraft systems interrelationships with respect to normal abnormal and emergency procedures Pilots will be introduced to and will exercise in the elements of crew resource management as part of the integration process including but n...

Page 30: ...lot training as a single crew member are specified in subsequent tables FLIGHT TRAINING MODULE OUTLINES Flight Training Curriculum Segment A Objective With the use of an approved flight simulator cockpit checklist and appropri ate instrument approach and airport charts the pilot will be able to accomplish the Normal and Emergency Abnormal checklists perform selected maneuvers and procedures and im...

Page 31: ...ls 5 Enroute a Steep Turns b Approach to Stall Enroute Configuration c Approach to Stall Takeoff and Approach Flaps d Approach to Stall Landing Configuration e Unusual Attitude f In flight Powerplant Shutdown g In flight Powerplant Restart h High Speed Handling Characteristics 6 Descent a Normal Descent b Rapid Decompression c Emergency Descent 7 Approaches Instrument Arrivals a Navigation Equipme...

Page 32: ...nding b Landing from a Precision Approach c Crosswind d Maneuver to Landing with Powerplant Failure e Landing with an Engine Out Full Stop f Rejected Landing to a Missed Approach g Landing from a Circling Approach h Zero Flap Landing i After Landing Procedures j Parking and Securing 9 Other Flight Procedures a ATC Procedures Phraseology b Ice Accumulation on Airframe c Windshear d Emergency Evacua...

Page 33: ...ction j Flap Systems k Flight Controls l Flight Instrument System m FMS Automatic or Other Approach and Landing Systems n Fuel o Hydraulics p Landing Gear q Navigation Systems r Pneumatics s Powerplant t Pressurization u Stall Warning Devices 11 Human Factors a CRM b Attitude c Judgement d Checklist QRH FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL SYL 24 CL 601 3A R FOR TRAINING P...

Page 34: ...nd Arrival a Altitude 100 Feet b Heading 10 c Airspeed 10 KIAS 3 Steep Turns a Altitude 100 Feet b Rollout Heading 10 c Bank Angle 5 d Airspeed 10 KIAS 4 Approach to Stall a Recognize Perceptible Stall or Stall Warning b Recover at First Indication of Stall c Strive for Minimum Altitude Loss 5 IFR Approaches Prior to Final Approach a Nonprecision Approach 1 Altitude 100 Feet 2 Heading 5 3 Airspeed...

Page 35: ...cling 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 100 Feet b Heading 5 c Airspeed 5 KIAS 9 Landing a Final Airspeed 5 0 KIAS 10 Powerplant Failure Multiengine Aircraft a Altitude 100 Feet b Heading 10 5 c Airspeed 10 KIAS 5 KIAS During Takeoff FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL SYL 26 CL 601 3...

Page 36: ...S 1 14 Electrical System 1 14 Lighting 1 15 Warning Systems 1 15 Fuel System 1 15 Auxiliary Power Unit 1 16 Powerplants 1 16 Fire Protection 1 16 Pneumatic System 1 16 Ice and Rain Protection 1 17 Air Conditioning 1 17 Pressurization 1 17 Hydraulic Power Systems 1 18 Landing Gear and Brakes 1 18 FOR TRAINING PURPOSES ONLY FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL ...

Page 37: ...Flight Controls 1 18 Avionics 1 19 Oxygen System 1 19 1 ii CL 601 3A R FOR TRAINING PURPOSES ONLY FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL ...

Page 38: ... 1 7 Nose Landing Gear Assembly 1 8 1 8 Passenger Compartment Typical 1 8 1 9 Engine and Pylon 1 9 1 10 Vertical and Horizontal Stabilizers 1 9 1 11 Passenger and Crew Door 1 10 1 12 Overwing Emergency Exit 1 11 1 13 Baggage Compartment Door 1 12 1 14 Rear Equipment Bay Door 1 13 1 15 Winglet 1 13 1 16 Landing Gear Locking Pins 1 14 FOR TRAINING PURPOSES ONLY FlightSafety CanadaLtée Ltd CL 600 2B1...

Page 39: ...uent changes in airplane appearance or system operation will be covered during aca demic training and in subsequent revisions to this manual GENERAL The airplane is manufactured by Canadair Limited It is a sweptwing twin engine mono plane designed to accommodate a crew of 3 and a maximum of from 8 to 19 passengers in spacious comfort The airplane is powered by two General Elec tric CF 34 turbofan ...

Page 40: ...earances of the airplane 1 2 CL 601 3A R FOR TRAINING PURPOSES ONLY FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL Figure 1 1 Canadair Challenger Figure 1 2 Dimensions and Ground Clearances Sheet 1 of 2 3 FT 1 IN 5 FT 4 IN 61 FT 7 IN 60 FT 0 IN No Tail Tank 68 FT 5 IN 20 FT 8 IN ...

Page 41: ...IN 10 FT 5 IN 12 FT 2 IN 9 FT 4 IN STATIC GROUND LINE 8 FT 10 IN 20 FT 4 IN 27 FT 8 IN 13 FT 1 IN 4 FT 2 IN CABIN INTERIOR DIMENSIONS LENGTH WIDTH MAX DIA HEADROOM FLOOR TO MAX HEIGHT VOLUME FLOOR AREA FLOOR WIDTH 28 FT 3 IN 8 FT 2 IN 6 FT 1 IN 1 150 CU FT 202 5 SQ FT 7 FT 2 IN Figure 1 2 Dimensions and Ground Clearances Sheet 2 of 2 ...

Page 42: ...00 2B16 PILOT TRAINING MANUAL MAXIMUM STEERING ANGLE 8 IN MINIMUM TURNING RADII USING NOSEWHEEL STEERING MAXIMUM STEERING ANGLE 52 TO 55 46 FT 26 FT 15 FT 33 FT 40 FT 53 FT NOTE LESSER STEERING ANGLES REQUIRE WIDER TAXI STRIP FOR 180 DEGREE TURN THEORETICAL TURNING POINT WITH NOSEWHEEL AT 52 TO 55 61 FOOT MINIMUM TAXI STRIP WIDTH FOR 180 DEGREE TURN 52 TO 55 26 FT 3 3 F T 38 FT NOTE MINIMUM TURNIN...

Page 43: ...RPOSES ONLY MAXIMUM THRUST IDLE THRUST 18 FT MAXIMUM THRUST IDLE THRUST 180 170 160 150 140 130 120 110 100 90 80 70 60 50 40 30 20 10 0 FEET 180 170 160 150 140 130 120 110 100 90 80 70 60 50 40 30 20 10 0 FEET 532 C 990 F 393 C 740 F 60 C 140 F 27 C 80 F 227 C 440 F 60 C 140 F 27 C 80 F 400 FT SEC 800 FT SEC 200 FT SEC 200 FT SEC 150 FT SEC 100 FT SEC 50 FT SEC 30 FT SEC 100 FT SEC 50 FT SEC 18 ...

Page 44: ...vided by the flight compartment floor into upper and lower halves The upper half comprises the flight compartment and forward avionics bay The flight compartment Figure 1 5 contains the airplane instruments caution warning lights controls circuit breaker panels two crew seats control columns and pedals On the center windshield post there is a pilot s eye locator to enable seat adjustment for optim...

Page 45: ...IVEN GENERATOR COMPARTMENT NOSE GEAR REAR DOOR NOSE LANDING GEAR FLIGHT COMPARTMENT FLOOR UNDERFLOOR AVIONICS BAY PRESSURIZED FWD AUX TANK PASSENGER CABIN FLOOR AFT AUXILIARY TANK REAR PRESSURE BULKHEAD REAR FUSELAGE UNDER FLOOR AREA PRESSURIZED MAIN LANDING GEAR WHEEL BAY AFT EQUIPMENT BAY UNPRESSURIZED TAIL CONE RUDDER HORIZONTAL STABILIZER ELEVATORS VERTICAL STABILIZER VERTICAL STABILIZER REAR ...

Page 46: ...single level floor into the pressurized passenger com partment cabin area Figure 1 8 and the un derfloor area The passenger compartment incorporates the passenger crew entrance door and the baggage door on the left side an over wing 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 t...

Page 47: ... side of the passenger compartment The passenger crew door is downward opening with the stairs incorporated in the door structure 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 airplane outer skin when closed Passenger Crew Door The entrance door is electrically or manually operated and downward open...

Page 48: ...ition Once the switch is released the door can still be operated manually The door unlocks from the outside by the op eration of a pushbutton in the handle itself which releases the T handle from its recess To unlatch the door the T handle is turned 45 degrees counterclockwise A pullout handle is also provided to assist the operator in open ing and closing the door from the outside When the door i...

Page 49: ...IN FLAP PUSH DOOR INWARD Baggage Compartment Door The baggage compartment door is located on the left side of the airplane immediately aft of the passenger compartment The door opens inward and upward on two sets of tracks attached to the structure It is assisted during opening by balance springs with cable attachments to the door and structure The door is held closed by two plungers which are ope...

Page 50: ...hat recess The handle flush hold lock is released by operation of an integral pushbutton on the handle When released the handle moves out of its recess under spring force and can then be turned to release the locking plungers and open the door Figure 1 13 Rear Equipment Bay Door The rear equipment bay door located at the bot tom of the rear fuselage Figure 1 14 provides access to the APU air condi...

Page 51: ...r Kevlar to save weight and to facilitate repairs The Challenger CL 600 2B16 employs winglets Figure 1 15 Fuel for the airplane is stored in three tank areas The deep section of the airfoil on each side is used as a main tank and the center sec tion is used as an auxiliary tank A fuel tight bulkhead each side of the center section sepa rates the tanks and all tanks are compartmented to ensure a co...

Page 52: ...nstalled as illustrated in Figure 1 16 AIRPLANE SYSTEMS ELECTRICAL SYSTEM The Challenger was the first executive jet to use AC power as its primary electrical system Its DC requirements are met through the use of transformer rectifier units which convert 115 VAC to 28 VDC A single nickel cad mium battery is used for starting the APU and as an emergency DC backup AC System The AC system is divided ...

Page 53: ...on both externally and in ternally throughout the airplane The exterior lighting includes four landing lights and two taxi recognition lights two rotating red bea cons standard red green and white navigation lights wing ice inspection lights and anticol lision strobe lights The interior lighting in cludes boarding and dome lights to illuminate the passenger door area service compartment lights and...

Page 54: ...rom a comparable turbojet while consuming the same amount of fuel This significantly in creases the range capability of the airplane At sea level on a standard day the CF 34 de livers 8 729 pounds of thrust at takeoff power with 9 220 pounds of thrust available through an automatic power reserve system Thrust reversers are installed for ground use FIRE PROTECTION The fire protection system provide...

Page 55: ...e aft equipment bay Air drawn through a ram air intake at the base of the ver tical stabilizer is ducted through the units as a cooling agent A ducting system associated with each air conditioning unit is responsible for delivering conditioned air to the cabin area from the right ACU and to the flight deck and cabin area from the left ACU Cabin and flight compartment temperature is controlled from...

Page 56: ...ES The Challenger employs three retractable land ing gear assemblies each fitted with dual wheels and an oleopneumatic shock strut The main landing gear retracts inward into recesses in the wing and center fuselage The nose landing gear retracts forward Normal extension and retraction is electrically con trolled and hydraulically operated For emer gency landing gear operation the gear may be exten...

Page 57: ...ally hinged inboard and outboard slotted flap panels which are mounted on the wing trailing edges The panels are electrically selected and electri cally driven A flap control lever quadrant on the center pedestal has detents at the 0 20 30 and 45 positions Aileron and rudder trim are actuated electri cally There are no trim tabs Pitch trim inputs are electromechanically applied to an actua tor whi...

Page 58: ... 2 6 Emergency AC System 2 8 AC Power Distribution 2 9 Control and Monitoring 2 12 DC SYSTEM 2 13 DC Static Conversion 2 14 Battery System 2 16 Battery Overload 2 16 Battery Contactor 2 16 External DC 2 17 Control and Monitoring 2 19 CIRCUIT BREAKER PANEL LOCATIONS 2 21 QUESTIONS 2 29 FOR TRAINING PURPOSES ONLY FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL ...

Page 59: ...ator Location 2 8 2 11 Ram Air Turbine 2 9 2 12 Total AC Power 2 10 2 13 Essential AC Power Panel 2 11 2 14 ADG Controls 2 11 2 15 Electrical Control Panel 2 12 2 16 DC System Components Locations 2 13 2 17 Primary DC Power Feed Normal Operation 2 14 2 18 Primary DC Power Feed TRU No 2 INOP 2 15 2 19 Primary DC Power Feed ESS TRU No 1 INOP 2 15 2 20 Battery Master Switch OFF All Power Off 2 16 2 2...

Page 60: ... CBP A Battery Bus 2 23 2 30 CBP B Main AC and DC Bus 2 2 24 2 31 CBP B Battery Bus 2 25 2 32 CBP C AC Essential Bus 2 26 2 33 CBP D DC Essential Bus 2 27 2 34 CBP E Battery Direct Bus 2 28 TABLES Table Title Page 2 1 Generator Trip Levels 2 3 2 2 Circuit Breaker Panels 2 21 2 iv CL 601 3A R FOR TRAINING PURPOSES ONLY FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL ...

Page 61: ...ectrical system consists of two engine driven AC generators one APU driven AC generator one ram air turbine driven AC gen erator four transformer rectifier units one nickel cadmium battery plus devices for in terconnection and control Control is exer cised primarily through the electrical control panel located on the center console Provision is made to connect both AC and DC ex ternal power throug...

Page 62: ... 2 1 Integrated Drive Generators IDG Each IDG Figure 2 2 is made up of a con stant speed drive CSD and an AC generator that are assembled into one unit Constant Speed Drive CSD The CSD provides the mechanical interface be tween the engine accessory gearbox and the generator The CSD uses a self contained oil supply as an operating medium Through a series of hydromechanical devices the vari able eng...

Page 63: ...sted in Table 2 1 are exceeded Generator Line Contactor GLC Each generator line contactor is responsible for supplying its own main bus with power from Its own generator through a generator line contact or A secondary source through a trans fer contactor The secondary source is used only when the pri mary is unavailable If power is not available at either contact the main bus is not powered and th...

Page 64: ...or at 12 000 rpm to maintain the out put frequency at 400 Hz A self contained oil system supplies oil for adapter and generator lubrication and cooling The adapter oil is cooled by APU fuel through a heat exchanger The auxiliary power system GCU provides the same functions as the primary system GCU The auxiliary power system GCU pro vides the same functions as the primary sys tem GCU The auxiliary...

Page 65: ...CU GCU IDG 2 IDG 2 GCU GCU APU GEN APU GEN GCU GCU GLC 2 GLC 1 GTC 2 GTC 1 AP EP CONT MAIN AC BUS 1 MAIN AC BUS 2 LEGEND IDG 1 POWER UNPOWERED POWERED BUS IDG 2 POWER IDG 1 IDG 1 GCU GCU IDG 2 IDG 2 GCU GCU APU GEN APU GEN GCU GCU GLC 2 GLC 1 GTC 2 GTC 1 AP EP CONT MAIN AC BUS 1 MAIN AC BUS 2 Figure 2 4 Main AC Power APU Feed Figure 2 5 Main AC Power Normal GEN Feed ...

Page 66: ...d panel Provided no other airplane generator is on line movement of the G PWR switch to the ON position extinguishes the AVAIL light and illuminates the amber IN USE light This indicates that external AC power is now connected to the airplane buses If the APU generator or any main generator is brought on line external power automatically reverts to an available status 2 6 CL 601 3A R FOR TRAINING ...

Page 67: ...ES ONLY Figure 2 7 AC External Power Connector LEGEND EXTERNAL AC POWER UNPOWERED POWERED BUS IDG 1 IDG 1 GCU GCU IDG 2 IDG 2 GCU GCU APU GEN APU GEN GCU GCU EXT AC EXT AC MONITOR MONITOR GLC 2 GLC 1 GTC 2 GTC 1 AP EP CONT MAIN AC BUS 1 MAIN AC BUS 2 Figure 2 8 External AC Power Feed All GENs INOP ...

Page 68: ...upport leg The ram air tur bine is a two bladed 19 inch propeller Figure 2 11 with a variable pitch mechanism that is used to achieve the constant speed necessary to operate the generator at a constant frequency The AC generator is similar in construction and operation to the other three generators but is rated at 15 kva It is air cooled and therefore subject to lower temperature restrictions 2 8 ...

Page 69: ...us 1 2 AC bus 2 3 AC essential bus 4 ADG bus 5 26 volt AC bus 2 6 26 volt AC essential bus 7 AC utility bus 1 8 AC utility bus 2 AC Bus 1 and AC Bus 2 Normal AC electrical power is distributed from the two main AC buses AC bus 1 and AC bus 2 In flight each main bus is normally supplied by its own IDG Generator No 1 sup plies AC bus 1 and generator No 2 supplies AC bus 2 Either bus may be powered b...

Page 70: ...th main AC buses are unpowered in flight and both IDGs are off line the ADG is deployed automatically Within four seconds of deployment the ADG starts producing 115 200 volt 3 phase 400 Hz power The power is automatically routed to the AC essential bus hydraulic pump 3B and the voltage and frequency meters of the electrical control panel If automatic deployment fails the ADG may be deployed manual...

Page 71: ... flaps selected to 0 and any single source of AC power available 2 With airplane airborne and any two generators on line Automatic load shedding of both utility buses occurs in flight anytime only one generator is on line ADG Control Unit Checks the following two functional tests Lamp Test When selected will indicate that the BATT DI RECT BUS is powered Unit Check Continuity of the UPLOCK Squib Ci...

Page 72: ...nerator is not switched on has no output is out of frequency tolerance or is out of voltage tolerance OVLD Light The overload OVLD light illuminates when the generator load exceeds 34 5 kva Generator Control Switch Each generator is controlled by its own gen erator control switch which has three posi tions ON OFF RESET and TEST When in the center OFF RESET position the switch in hibits the generat...

Page 73: ...quency Metering A rotary selector allows for the monitoring of AC voltage and frequency on separate meters The rotary selector positions are labeled EXT PWR GEN 1 APU GEN 2 and ADG DC SYSTEM DC supply can be subdivided into two systems static conversion and battery In normal op eration primary DC power is derived from the AC system through the use of four trans former rectifier units TRU located i...

Page 74: ... to DC buses 1 and 2 except the utility buses Figure 2 17 can be main tained by energizing DC bus ties which cross connect the outputs of TRU 1 and TRU 2 These bus ties are controlled by switchlights on the electrical control panel labeled BUS TIE CLOSED Both BUS TIE CLOSED switchlights would have to be illuminated to replace either TRU 1 or TRU 2 Figure 2 15 When a DC tie relay is closed the resp...

Page 75: ...END IDG 2 POWER TRU 1 POWER TRU 2 POWER ESSENTIAL TRU 1 POWER ESSENTIAL TRU 2 POWER ESS DC BUS BATT BUS MAIN AC BUS 1 DC BUS 1 ESS DC BUS DC UTILITY BUS 1 DC BUS 2 MAIN AC BUS 2 TRU 1 A17 C2 A69 A68 DC TIE CONT D10 EMER DC 1 TC D5 D4 D7 B69 B68 D8 D9 B29 B17 DC TIE CONT ESS TRU 2 ESS TRU 1 TRU 2 UNPOWERED POWERED BUS IDG 1 POWER LEGEND IDG 2 POWER TRU 1 POWER TRU 2 POWER ESSENTIAL TRU 1 POWER ESSE...

Page 76: ...the battery bus the battery re mote control circuit breaker RCCB trips and takes the battery off line The RCCB trips at 50 amps to protect the battery from a short cir cuit on the battery contactor or the battery bus Figure 2 20 The RCCB is physically lo cated in the aft equipment bay When it trips it also trips the BATT RCCB CONT circuit breaker on the DC essential bus in the cock pit Resetting t...

Page 77: ...ing and for starting the APU The external DC power replaces the bat tery as a source of power Whenever the ex ternal contactor is energized the battery is disconnected and external DC is connected to the battery direct bus and to the APU start ing circuit It also supplies a ground which causes the IN USE light on the overhead panel to illuminate Figure 2 21 DC External Power Connector MAIN AC BUS ...

Page 78: ... EMER DC 1 TC D10 D5 ESS TRU 1 EXT DC UNPOWERED POWERED BUS EXTERNAL DC POWER LEGEND BATT BUS MAIN AC BUS 2 ESS DC BUS BATT DIR BUS BATT CHGR B32 MAIN BATT ESS TRU 2 D9 D8 D7 D4 EMER DC 2 TC W OFF W E8 EXT DC TC D6 BATTERY MASTER SENSOR RELAY BATTERY CONT EMER DC 1 TC D10 D5 ESS TRU 1 EXT DC UNPOWERED POWERED BUS IDG 2 POWER LEGEND BATTERY POWER BATTERY CHARGER BATT BUS Figure 2 23 External DC Bat...

Page 79: ... is not available for use by the bat tery bus possibly due to one of the following conditions The BATTERY MASTER switch is in the OFF position The battery has failed Figure 2 27 shows the total electrical system in simplified form and illustrates AC and DC system interconnection Figures 2 28 through 2 34 show the circuit breaker panels and locations FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TR...

Page 80: ...GCU EXT AC MONITOR GLC 2 GLC 1 A23 B23 C5 C2 A47 A17 A69 B69 A68 B68 E8 D6 RCCB EXT DC TC EMER DC 2 TC W OFF W EMER DC 1 TC DC TIE CONT DC TIE CONT BATTERY MASTER BATTERY CONT SENSOR RELAY D5 D4 EMERG AC TC ESS PWR TC GTC 2 GTC 1 AP EP CONT D9 D10 ADG BUS D8 D7 B29 B17 B32 B47 DC UTIL BUS 2 DC UTIL BUS 1 ESS TRU 1 TRU 1 TRU 2 BATT CHGR MAIN BATT EXT DC ESS TRU 2 3B ESS AC BUS MAIN AC BUS 1 ESS 26 ...

Page 81: ...attery AC Essential Bus Just forward of the pilot s side console 26 VAC Essential Bus DC Essential Bus Just forward of the copilot s side console Main Bus 1 AC and DC Inboard on the bulkhead behind the pilot s seat Utility Bus 1 AC and DC Main Bus 2 AC and DC Utility Bus 2 AC and DC Inboard on the bulkhead behind the copilot s seat 26 VAC Bus 2 Battery Bus Two panels one electrical bus one outboar...

Page 82: ...FOR TRAINING PURPOSES ONLY FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL 2 22 CL 601 3A Figure 2 28 CBP A Main AC and DC Bus 1 ...

Page 83: ...FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL FOR TRAINING PURPOSES ONLY CL 601 3A 2 23 Figure 2 29 CBP A Battery Bus ...

Page 84: ...FOR TRAINING PURPOSES ONLY FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL 2 24 CL 601 3A Figure 2 30 CBP B Main AC and DC Bus 2 ...

Page 85: ...FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL FOR TRAINING PURPOSES ONLY CL 601 3A 2 25 Figure 2 31 CBP B Battery Bus ...

Page 86: ...FOR TRAINING PURPOSES ONLY FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL 2 26 CL 601 3A Figure 2 32 CBP C AC Essential Bus ...

Page 87: ...lightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL FOR TRAINING PURPOSES ONLY CL 601 3A 2 27 1 1 1 1 NOTE RED IDENTIFICATION COLLAR INSTALLED POST SB 601 0379 Figure 2 33 CBP D DC Essential Bus ...

Page 88: ...FOR TRAINING PURPOSES ONLY FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL 2 28 CL 601 3A Figure 2 34 CBP E Battery Direct Bus ...

Page 89: ...lass D Monitoring a light 6 While on the ground AC power can be supplied by the engines or by a n A APU generator B External DC connector C ADG D CSD 7 A source of emergency in flight AC power is A IDG B CSD C ADG D TRU 8 If the ADG is inadvertently deployed it can be retracted A By depressing the reset switch B With a manual crank C By holding the deploy button down for 3 seconds D Only on the gr...

Page 90: ...attery AC Essential Bus Just forward of the pilot s side console 26 VAC Essential Bus DC Essential Bus Just forward of the copilot s side console Main Bus 1 AC and DC Inboard on the bulkhead behind the pilot s seat Utility Bus 1 AC and DC Main Bus 2 AC and DC Utility Bus 2 AC and DC Inboard on the bulkhead behind the copilot s seat 26 VAC Bus 2 Battery Bus Two panels one electrical bus one outboar...

Page 91: ...FOR TRAINING PURPOSES ONLY FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL 2 22 CL 601 3R Figure 2 28 CBP A Main AC and DC Bus 1 ...

Page 92: ...FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL FOR TRAINING PURPOSES ONLY CL 601 3R 2 23 Figure 2 29 CBP A Battery Bus ...

Page 93: ...FOR TRAINING PURPOSES ONLY FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL 2 24 CL 601 3R Figure 2 30 CBP B Main AC and DC Bus 2 ...

Page 94: ...FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL FOR TRAINING PURPOSES ONLY CL 601 3R 2 25 Figure 2 31 CBP B Battery Bus ...

Page 95: ...FOR TRAINING PURPOSES ONLY FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL 2 26 CL 601 3R Figure 2 32 CBP C AC Essential Bus ...

Page 96: ...lightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL FOR TRAINING PURPOSES ONLY CL 601 3R 2 27 1 1 1 1 NOTE RED IDENTIFICATION COLLAR INSTALLED POST SB 601 0379 Figure 2 33 CBP D DC Essential Bus ...

Page 97: ...DETECT RESET DS5KJ DS4KJ LH ENG IGN B ENG OIL CONT BYPASS IND ENG OIL POWER BATT SHUNT FUSES RH BAT BUS BATTERY DIRECT BUS BATTERY DIRECT BUS 20 3 10 50 5 3 3 3 3 3 5 5 7 5 7 5 75 3 E7 E6 E9 BOARD BAT CONT EXT AC PWR CONT ESS PWR CONT AUTO APR CONT FUEL DE FUEL APU BACKUP PWR CONT IND APU START MAN ADG DEPLOY CONT SERV LIGHTS CBP E Figure 2 34 CBP E Battery Direct Bus ...

Page 98: ... gage C Viewing a sight glass D Monitoring a light 6 While on the ground AC power can be supplied by the engines or by a n A APU generator B External DC connector C ADG D CSD 7 A source of emergency in flight AC power is A IDG B CSD C ADG D TRU 8 If the ADG is inadvertently deployed it can be retracted A By depressing the reset switch B With a manual crank C By holding the deploy button down for 3...

Page 99: ...Compartment Lights 3 4 Service Lights 3 4 EXTERIOR LIGHTS 3 4 Landing and Taxi Recognition Lights 3 5 Wing Ice Inspection Lights 3 6 Navigation Lights 3 6 Anticollision Strobe Lights and Beacon Lights 3 6 EMERGENCY LIGHTS 3 6 QUESTIONS 3 7 FOR TRAINING PURPOSES ONLY FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL ...

Page 100: ...hts Control 3 4 3 3 Ordinance Lights Controls 3 4 3 4 Exterior Lighting Locations 3 5 3 5 Landing and Taxi Recognition Lights Controls 3 5 3 6 External Lighting Control Panel 3 6 3 7 Emergency Lighting Control 3 6 FOR TRAINING PURPOSES ONLY FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL ...

Page 101: ...es GENERAL Included in the interior lighting groups are boarding and dome lights to illuminate the passenger door area service compartment lights and cockpit lighting Exterior lighting consists of one recogni tion taxi light and one landing light in the leading edge of each wing and two landing lights in the radome for approach and ground visibility standard red green and white nav igation lights ...

Page 102: ...ng and fluorescent and integral panel lighting Figure 3 1 illustrates interior light ing controls and their locations OFF ON OFF ON OFF ON OFF ON OFF ON OFF ON OFF ON OFF ON OFF ON OFF ON MISC LTS BOARDING DOME STBY COMP SERVICE DIM OFF ON OFF ON LANDING LTS EXTERNAL LTS LEFT NOSE RIGHT OFF BRT RECOG TAXI LT NAV WING ANTI COLL OVERHD PANEL WARN LTS FLOOD LTS TEST OFF BRIGHT DIM WARN LTS FLOOD LTS ...

Page 103: ...he pilot s floodlights is supplied from the DC essential bus The copilot s flood lights are powered from the battery bus Integral lighting includes edge lit panel light ing and instrument lighting The integral lighting in the cockpit is con trolled in two individual areas Overhead panel Center pedestal Integral lighting is supplied with up to 5 VAC by incandescent lamp dimmers controlled from the ...

Page 104: ... selected both signs illuminate whenever 1 cabin altitude is above 10 400 feet 2 the landing gear is selected down or 3 the test button on the LDG GEAR control panel is pressed The FASTEN SEAT BELT sign also illumi nates if the flaps are not at 0 SERVICE LIGHTS Service lights are located in the nosewheel bay the avionics bay and the rear equipment bay All service lights are powered by the battery ...

Page 105: ...ht panel Figure 3 5 Positioning a landing light switch to ON causes both the landing and the taxi recognition lights on the side selected to il luminate Positioning the RECOG TAXI LT switch to ON causes both taxi lights to illu minate The left lights are powered by AC bus 1 and the right lights by AC bus 2 EMERGENCY LIGHT NAVIGATION AND STROBE LIGHTS ROTATING BEACON OPTIONAL NAVIGATION LIGHT TAXI ...

Page 106: ...ncy lights are provided to illu minate escape routes during emergency evac uation There are three lights in the fuselage above the right wing and one light on the left side just forward of the main entrance door Two battery packs independently supply power Emergency lighting is controlled from the emergency lighting panel on the copilot s side console Figure 3 7 The switch labeled EMERGENCY LIGHTI...

Page 107: ...D Both B and C 5 When the ordinance sign switches are in AUTO the seat belt and no smoking signs illuminate A When cabin altitude is above 10 400 feet B When the landing gear is selected down C When LDG GEAR test is initiated D All the above 6 The nosewheel bay service light control is located A On the overhead panel B Near the entrance door C In the avionics compartment D In the nosewheel bay 7 I...

Page 108: ... 4 1 GENERAL 4 1 MASTER CAUTION SYSTEM 4 2 General 4 2 Components 4 4 Lamp Test Switches 4 4 Illumination Causes 4 5 AURAL WARNING SYSTEM 4 13 General 4 13 Components 4 13 QUESTIONS 4 16 FOR TRAINING PURPOSES ONLY FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL ...

Page 109: ...tatus Annunciators 4 12 4 5 Landing Gear MUTE HORN Button 4 13 4 6 Aural Warning System 4 15 TABLES Table Title Page 4 1 Caution Annunciators 4 5 4 2 Miscellaneous Annunciators 4 10 4 3 Warning Annunciators 4 11 4 4 Nondimmable Annunciators 4 12 4 5 Aural Warnings 4 14 FOR TRAINING PURPOSES ONLY FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL ...

Page 110: ...and white lights indicate conditions which are normal when in use The two basic central warning systems are 1 the master caution system and 2 the aural warning system The master caution system provides the crew with up to 18 visual annun ciators for airplane system malfunctions Ad ditional information on the specific malfunction may then be found on the associated system con trol panel The master ...

Page 111: ...MASTER CAUTION lights are switch lights designed to draw attention to the sys tem annunciators They also function as a means of canceling or resetting the master caution system The system provides power to the various cau tion advisory and warning lights located throughout the cockpit An annunciator light in conjunction with the flashing MASTER CAUTION lights illumi nates to indicate a malfunction...

Page 112: ...lluminated and cannot be reset as long as the malfunction exists This is not a memory system it will not recall a system annunciator where no faults con tinue to exist ELECTRONIC CIRCUIT BREAKER BOX TEST RECALL SWITCH AIRPLANE SYSTEMS ILLUMINATE WHEN MALFUNCTION EXISTS OR WHEN LIGHTS ARE BEING TESTED AMBER MALFUNCTION LIGHT RED WARNING LIGHTS GREEN STATUS LIGHTS WHITE STATUS LIGHTS AMBER STATUS LI...

Page 113: ... the annun ciator light to extinguish if the ECB is suc cessful in reestablishing power to that circuit Dimming Modules The dimming modules provide interface be tween the airplane systems and the annunci ator panels These modules are located under the consoles in the cockpit Each module is powered by a separate channel of the elec tronic circuit breaker and routes this power to the associated ligh...

Page 114: ...ng anti ice system has failed The wing anti ice sensor has failed Indicated cowl anti ice system has failed Indicated windshield heat has failed The ADS heater has failed Indicated pitot heat has failed Indicated ice detector system has failed HTR FAIL DUCT FAIL SENSOR FAIL ANNUNCIATOR ASSOCIATED ANNUNCIATOR CAUSE FOR ILLUMINATION R FAIL L FAIL FAIL FAIL PITOT HEAT PITOT HEAT ON FAIL ON FAIL The A...

Page 115: ... voltage less than required for IRS operation The main landing gear bay overheat detection system has failed INBD FAIL INBD TEST OUTBD FAIL OUTBD TEST Indicated hydraulic system electric pump pressure is below 1 800 psi with the flaps selected or pump pressure is below 1 800 psi with switch selected ON Hydraulic system 1 2 or 3 overtemped ELEC PUMP Indicates hydraulic No 1 system pressure is below...

Page 116: ...EC PASS DR UNLKD BAG DOOR UNSAFE Indicated generator is not operating Indicated generator has overloaded GEN OFF OVLD Indicated automatic bus tie is switched off Indicated automatic bus tie has failed Main AC bus 1 or DC bus 1 is not powered AUTO OFF FAIL MAIN BUS 1 OFF Main AC bus 2 or DC bus 2 is not powered MAIN BUS 2 OFF The DC essential bus is off 1 OFF 2 OFF ESS BUS OFF The battery bus is of...

Page 117: ...enge ejector fuel pump is inoperative Indicated main ejector fuel pump is inoperative The aileron PCU control valve has jammed or one hydraulic system is unpressurized The elevator PCU control valve has jammed The rudder PCU has jammed or one hydraulic system is unpressurized Mach trim is not engaged The flaps have failed Tail tank system not armed for auto transfer Tail tank system has switched t...

Page 118: ...ottle has low pressure ANNUNCIATOR ASSOCIATED ANNUNCIATOR CAUSE FOR ILLUMINATION FIRE FAULT WOW Indicated fire warning system has failed FIRE WARN FAIL LOW PRESS Indicates a disagreement between various WOW outputs or if either channel power source fails The emergency light is off or the flight recorder is malfunctioning EMER LTS OFF HIGH VIB WOW O P FAIL WOW I P FAIL EMER LGT FLT REC ...

Page 119: ...ECTRONIC CIRCUIT BREAKER BOX AIRPLANE SYSTEMS WARNING LIGHTS DIMMING MODULE 1 OF 32 D 41 DC ESS BUS B 161 BATT BUS B 87 DC BUS 2 NOTE THE ABOVE ONLY APPLIES TO RED ANNUNCIATORS THAT ARE POWERED FROM DIMMING MODULES BRT DIM SWITCH WARN LIGHTS TEST SWITCHES 1 OF 40 POWER OUTPUTS POWER SUPPLY Figure 4 3 System Warning Annunciators Nosewheel steering is inoperative ANNUNCIATOR CAUSE FOR ILLUMINATION N...

Page 120: ...ing modules The parking brake is engaged Dimming modules The landing gear is in transit or is not locked in the position selected or the LDG GEAR TEST button is pressed Landing gear control unit Indicated engine or APU has a fire Fire detection unit Ice has been detected but the anti icing systems for wing and engines are not turned on Ice detection units The main landing gear bay has an overheat ...

Page 121: ...UIT BREAKER BOX D 41 DC ESS BUS B 161 BATT BUS B 87 DC BUS 2 Figure 4 4 System Status Annunciators Table 4 4 NONDIMMABLE ANNUNCIATORS ANNUNCIATOR ASSOCIATED SYSTEM External AC DC L R Engine Start Switch ASSOCIATED SYSTEM Jet Pipe Pylon Overheat Detection Firex Bottles 1 2 APU Landing Gear Control Handle Main Landing Gear Bay Overheat Detection Ice Detection Fire Detection ANNUNCIATOR Stall Protect...

Page 122: ...lume ad justment and a press to mute switch This allows the flight crew to test the individual tone generators and also to mute those tones which can be muted Operation of the rotary selec tor switch applies an input to generate one of the eight aural warnings With the selector switch in the FIRE or FLAP OVSPD posi tions the tone can be muted by pressing the press to mute switch which then illumin...

Page 123: ...or HF2 Landing gear configuration Horn As long as hazard exists As long as hazard exists Landing gear not down and locked with flaps greater than 30 Landing gear not down and locked with either throttle at idle may be muted by switch on landing gear control lever panel Landing gear control unit Altitude alert C chord One second At 1 000 ft from the altitude selected on vertical navigation computer...

Page 124: ...RE DETECTION UNIT THROTTLE LEVERS LANDING GEAR CONTROL UNIT AIR DATA COMPUTER 1 AND 2 VERTICAL NAV COMPUTER CONTROLLER HORIZONTAL STABILIZER UNIT SPOILER PROXIMITY SWITCHES SELCAL DECODER UNIT LH ENGINE FIRE DETECTION UNIT APU FIRE DETECTION UNIT STALL WARNING COMPUTER STALL FLAP CONTROL UNIT AURAL WARNING TEST PANEL AURAL WARNING VOLUME CONTROL PRESS TO MUTE TONE MUTED TONE TEST STALL FLAP OVSPD ...

Page 125: ...is pushed D Anytime except when a red annun ciator is illuminated steady 3 Which of the following systems are rep resented on the 8 and 10 channel annun ciators A Electronic circuit breaker B Weight on wheels C Emergency lights D All the above 4 The color light that indicates a situation requiring attention but not immediate action is A Red warning B Amber caution C White advisory D Green test 5 W...

Page 126: ...sfer Ejectors 5 3 Standby Electric Pumps 5 3 Engine Driven Pumps 5 3 Crossflow Valve 5 3 Powered Crossfeed Valve 5 3 APU FUEL SYSTEM 5 8 FUEL CONTROLS AND INDICATORS 5 9 General 5 9 Fuel Control Panel 5 9 Fuel Quantity 5 11 VENT SYSTEM 5 12 REFUELING 5 13 General 5 13 Pressure Refueling 5 13 FOR TRAINING PURPOSES ONLY FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL ...

Page 127: ... TAIL TANK 5 17 General 5 17 Normal Transfer 5 17 Fuel Jettison 5 18 Refueling and Defueling 5 18 QUESTIONS 5 20 FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL 5 ii CL 601 3A FOR TRAINING PURPOSES ONLY ...

Page 128: ...rt without Powered Crossfeed 5 7 5 7 Fuel Distribution Engine Start with Powered Crossfeed Service Bulletin 601 0225 5 7 5 8 APU Fuel System Normal Operation 5 8 5 9 APU Fuel System Negative G Condition 5 9 5 10 Fuel Controls and Indicators with Powered Crossfeed Service Bulletin 601 0225 5 10 5 11 Vent System 5 12 5 12 Pressure Refueling System 5 13 5 13 Exterior Fueling Components 5 14 5 13 Refu...

Page 129: ... pounds due to the addition of a tail tank Fuel is supplied to the engines from two collector tanks Fuel is delivered from each collector tank to its respective engine by a main ejector pump located within the tank Additional scavenge and transfer ejector pumps are located within the main and auxiliary tanks to ensure proper fuel distribution Electrically operated standby fuel pumps are pro vided ...

Page 130: ...ated on the upper outboard wing surface The auxiliary tank encompasses the entire center section of the wing There are access panels in the lower wing surface The auxil iary tank gravity filler port is located in the right wing root just aft of the leading edge Contained within the auxiliary tank are two collector tanks which are extensions of each main tank They incorporate the main fuel ejectors...

Page 131: ...el flow to its own engine through firewall shutoff valves Flow to the opposite engine is not pos sible because of one way check valves in the feed lines Failure of a main ejector will cause illumination of an amber caution light in the cockpit and will activate both standby elec tric pumps Figure 5 4 or 5 5 TRANSFER EJECTORS When main tank fuel quantity drops below the 93 full level float valves o...

Page 132: ...ossflow valve see Figure 5 2 or 5 3 which connects both main tanks and both collector tanks Balance is achieved through gravity flow only To avoid a serious imbalance which might occur if the wings are not level the crossflow should not be left open when the airplane is on the ground POWERED CROSSFEED VALVE When depressing the LEFT TO RIGHT or RIGHT TO LEFT switchlight the associated powered cross...

Page 133: ...DBY PUMPS FLAPPER VALVE SCAVENGE EJECTOR OVERFLOW PRESSURE MOTIVE FLOW PRESSURE LEGEND MAIN EJECTOR PRESSURE GRAVITY FLOW LINES FLOAT VALVE FLAPPER VALVES SCAVENGE EJECTOR TO ENGINE TO ENGINE FIREWALL LOW PRESSURE SWITCH LOW PRESSURE SWITCH TO APU FIREWALL SOV APU SOV OVERFLOW LINE POWERED CROSSFEED SHUTOFF VALVE POWERED CROSSFEED SHUTOFF VALVE MAIN EJECTOR CROSSFLOW VALVE MAIN EJECTOR OVERFLOW LI...

Page 134: ...NDBY PUMP PRESSURE Figure 5 4 Fuel Distribution Abnormal Operation Main Ejector Fail without Power Crossfeed GRAVITY FLOW LINES FLOAT VALVE FLAPPER VALVES SCAVENGE EJECTOR TO ENGINE TO ENGINE FIREWALL LOW PRESSURE SWITCH LOW PRESSURE SWITCH TO APU FIREWALL SOV APU SOV OVERFLOW LINE POWERED CROSSFEED SHUTOFF VALVE POWERED CROSSFEED SHUTOFF VALVE MAIN EJECTOR CROSSFLOW VALVE MAIN EJECTOR OVERFLOW LI...

Page 135: ...N EJECTOR PRESSURE STANDBY PUMP PRESSURE Figure 5 6 Fuel Distribution Engine Start without Powered Crossfeed GRAVITY FLOW LINES FLOAT VALVE FLAPPER VALVES SCAVENGE EJECTOR TO ENGINE TO ENGINE FIREWALL LOW PRESSURE SWITCH LOW PRESSURE SWITCH TO APU FIREWALL SOV APU SOV OVERFLOW LINE POWERED CROSSFEED SHUTOFF VALVE POWERED CROSSFEED SHUTOFF VALVE MAIN EJECTOR CROSSFLOW VALVE MAIN EJECTOR OVERFLOW LI...

Page 136: ...failure fuel can be supplied from the left engine feed line to the APU Figure 5 9 This line has a differential pressure one way check valve which opens whenever the main APU supply pressure drops 10 psi lower than the pressure in the left en gine fuel feed line Fuel from the left engine feed line cannot flow to the right tank or to any heat exchanger because of a check valve in stalled in the main...

Page 137: ...an amber INOP legend which illuminates to in dicate that the associated pump is not selected on or that the pump is not operating properly A third switchlight labeled X FLOW con trols operation of the crossflow valve The green OPEN light illuminates to indicate that FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL CL 601 3A 5 9 FOR TRAINING PURPOSES ONLY RIGHT MAIN TANK APU FUEL PUMP ...

Page 138: ...P X FLOW E J C T F E E D L E F T E N G F U E L E N G F U E L FUEL CONTROL SCAV MAIN VALVE CLOSED FILTER LOW PRESS VALVE CLOSED FILTER LOW PRESS SCAV MAIN ON INOP ON INOP OPEN LEFT TO RIGHT RIGHT TO LEFT E J C T F E E D R I G H T 70 20 20 40 0 70 20 20 60 40 0 FUEL C L R 60 Figure 5 10 Fuel Controls and Indicators with Powered Crossfeed Service Bulletin 601 0225 ...

Page 139: ... FILTER light illuminates to indicate an impending fuel filter bypass or a clogged filter This condition is covered in Chapter 7 Powerplant The amber LOW PRESS light illumi nates if fuel pressure at the inlet side of the engine driven pump falls below a predetermined value A fuel temperature indicator in the cen ter of the fuel control panel indicates the temperature of the fuel as it leaves the f...

Page 140: ... during flight due to ram air effect There are no valves or screens in the vent lines so dirt or ice accumulation does not nor mally occur Any trapped fuel or moisture in the vent lines is continuously purged from the low points by a bleed line connected to each scavenge ejector During pressure fueling the fuel tank vent lines are augmented with special vent valves which will be described later un...

Page 141: ... two way check valve three shutoff valves SOV associated with three float operated full level control valves and three vent valves that can be tested during the refueling process and are utilized as backup to normal pressure relief during refueling The adapter and manifold can accept a flow rate of up to 250 gpm at a pressure of from 20 to 55 psi The pressure fueling process is con trolled from th...

Page 142: ...6 PILOT TRAINING MANUAL 5 14 CL 601 3A FOR TRAINING PURPOSES ONLY AUXILIARY TANK GRAVITY REFUELING PORT PRESSURE REFUEL DEFUEL CONTROL PANEL MAIN TANK GRAVITY REFUELING PORT PRESSURE REFUELING ADAPTER Figure 5 13 Exterior Fueling Components ...

Page 143: ...ithin 30 seconds After 30 40 seconds the SOV CLosed light will illuminate and the OPen light will extinguish indicating that the au tomatic level control system is working properly Test other SOVs and VVs individually for other tanks to be filled Rotate the MODE selector to FUEL Check that all three VV OPEN lights extinguish Ensure that the tank FUEL DEF switches of the tanks to be filled are in t...

Page 144: ...hen the tanks are empty the valves will close by spring pressure The tanks may be selectively defueled using the refuel defuel control panel in the DEFUEL mode as follows Move the power switch Figures 5 14 and 5 15 to ON and check that the green POWER ON light illuminates Connect the defueling nozzle from the tender to the single point adapter Open the nozzle valve and check for a maximum negative...

Page 145: ...at the rate of approximately 25 pounds per minute When only unusable fuel approx imately 1 3 U S gallons is left the shutoff valve closes and the fuel transfer pump stops If the ARMED OFF switch is set to OFF while there is still usable fuel in the tail tank the NOT ARMED light illuminates If fuel in the auxiliary tank reaches the level of the No 2 auxiliary tank level switch the NOT ARMED light f...

Page 146: ...per minute NOTE Fuel jettison must only be carried out with flaps set at 0 If an imme diate landing is required the fuel jettison procedure should be initi ated immediately However if it is not possible to complete the jetti son procedure a landing may be made with fuel in the tail cone tank Do not jettison fuel in known light ning conditions REFUELING AND DEFUELING Refueling can only be accomplis...

Page 147: ...EL SWITCH FWD AUX TANK PRIMARY AUX TANK REAR AUX TANK TAIL TANK LEFT MAIN TANK RIGHT MAIN TANK FUELING ADAPTER AND MANIFOLD ROTORBURST ZONE TRANSFER LINE TRANSFER SOV WATER DRAIN FULL LEVEL SWITCH NO 1 TAIL TANK LEVEL SWITCH NO 2 TAIL TANK LEVEL SWITCH JETTISON SOV RAM AIR SECONDARY TRANSFER PUMP SECONDARY TRANSFER SOV PRESSURIZED SHROUD FUELING LINE FLOW SENSOR Figure 5 18 Tail Tank Flow Schemati...

Page 148: ...in tanks prevent A Reverse flow of fuel from the main tanks to the auxiliary tank B Reverse flow of fuel from the auxil iary tank to the main tanks C Gravity flow of fuel from the out board main tank sections to the inboard main tank section D Reverse flow of fuel from the inboard main tank sections to the outboard main tank sections 6 Fuel for the APU is normally supplied by A The left scavenge e...

Page 149: ... more than A 3 000 pounds B 4 000 pounds C 3 000 gallons D 4 000 gallons 13 The maximum negative pressure allowed for single point defueling is A 6 psi B 8 psi C 10 psi D 12 psi 14 During flight the maximum imbalance al lowed between the main tanks is A 800 pounds B 1 836 pounds C 2 500 pounds D 2 836 pounds 15 The Tail Tank system amber NOT ARMED light if on steady A Indicated no fuel in the tank...

Page 150: ...sfer Ejectors 5 4 Standby Electric Pumps 5 5 Engine Driven Pumps 5 6 Crossflow Valve 5 7 Powered Crossfeed Valve 5 7 APU FUEL SYSTEM 5 7 FUEL CONTROLS AND INDICATORS 5 8 General 5 8 Fuel Control Panel 5 8 Fuel Quantity 5 10 VENT SYSTEM 5 10 REFUELING 5 11 General 5 11 Pressure Refueling 5 11 FOR TRAINING PURPOSES ONLY FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL ...

Page 151: ...Normal Transfer 5 15 Tail Tank Amber Warning Lights Versus Master Caution 5 16 Fuel Jettison 5 16 Refueling and Defueling 5 16 QUESTIONS 5 19 FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL 5 ii CL 601 3R FOR TRAINING PURPOSES ONLY ...

Page 152: ... System Normal Operation 5 7 5 6 APU Fuel System Negative G Condition 5 7 5 7 Fuel Controls and Indicators 5 9 5 8 Vent System 5 10 5 9 Exterior Fueling Components 5 12 5 10 Pressure Refueling System 5 13 5 11 Refuel Defuel Control Panel 5 13 5 12 Tail Tank Quantity Panel 5 15 5 13 Tail Tank Fuel Transfer Panel 5 16 5 14 Tail Tank Flow Schematic 5 17 FOR TRAINING PURPOSES ONLY FlightSafety CanadaL...

Page 153: ...o its respective engine by a main ejector pump located within the tank Addi tional scavenge and transfer ejector pumps are located within the main and auxiliary tanks to ensure proper fuel distribution Electrically operated standby fuel pumps are provided These pumps are operated during engine starting or following a main ejector pump failure A fuel imbalance between the main tanks may be correcte...

Page 154: ...n the upper outboard wing surface The auxiliary tank encompasses the entire center section of the wing There are access panels in the lower wing surface The auxil iary tank gravity filler port is located in the right wing root just aft of the leading edge Contained within the auxiliary tank are two collector tanks which are extensions of each main tank They incorporate the main fuel ejectors and f...

Page 155: ... caution light in the cockpit Motive flow for operation of a scavenge ejec tor comes from the high pressure side of the two stage engine driven fuel pump Figure 5 2 Ejectors have no moving parts Each op erates on the venturi principle to convert FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL CL 601 3R 5 3 FOR TRAINING PURPOSES ONLY GRAVITY FLOW LINES FLOAT VALVE FLAPPER VALVES SCAVE...

Page 156: ...ain tank fuel quantity drops below the 93 full level float valves open allow ing the transfer ejectors to draw fuel from the auxiliary tank to the inboard sections of the main tanks Motive flow for the transfer ejec tors is provided by the output of the associated main ejector No cockpit indication of fuel transfer or transfer ejector failure is provided FlightSafety CanadaLtée Ltd CL 600 2B16 PIL...

Page 157: ... enough motive flow to operate the main ejectors The left electric pump is powered by the bat tery bus while the right pump receives power from DC bus No 2 FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL CL 601 3R 5 5 FOR TRAINING PURPOSES ONLY GRAVITY FLOW LINES FLOAT VALVE FLAPPER VALVES SCAVENGE EJECTOR TO ENGINE TO ENGINE FIREWALL LOW PRESSURE SWITCH LOW PRESSURE SWITCH TO APU FI...

Page 158: ...nk by the transfer ejectors when in flight or the fuel boost pumps via the transfer ejec tors when on the ground NOTE Maximum imbalance is 800 pounds APU FUEL SYSTEM The APU is normally supplied with fuel from the right main tank by an electric fuel pump The pump is identical to the standby electric pumps described previously The APU fuel pump operates whenever it is se lected on by a switch on th...

Page 159: ...VE RESTRICTOR CHECK VALVE CHECK VALVE FUEL CONTROL UNIT SHUTOFF VALVE PRESSURE SWITCH CENTER TANK LEGEND Figure 5 5 APU Fuel System Normal Operation RIGHT MAIN TANK APU FUEL PUMP STANDBY PUMPS FROM LEFT MAIN EJECTOR TO LEFT ENGINE APU NEGATIVE G CHECK VALVE STANDBY PUMP PRESSURE MAIN EJECTOR PRESSURE APU NEGATIVE G SHUTOFF VALVE APU FUEL FEED SHUTOFF VALVE FUEL CONTROL UNIT TO PNEUMATIC SYSTEM APU...

Page 160: ...nk fuel levels develop and gravity equalizing with the crossflow valve not be possible the transfer is possible by de pressing the appropriate switchlight The de pressed switchlight will illuminate steady and will start flashing after eight minutes as a reminder An interlock prevents simultane ous operation of both switchlights The remaining five lights for each engine pro vide information as foll...

Page 161: ...P AT 0 FLAPS ONLY DUMP X FER ARMED OFF TAIL TANK PUSH ON OFF PUMP PUMP X FLOW E J C T F E E D L E F T E N G F U E L E N G F U E L FUEL CONTROL SCAV MAIN VALVE CLOSED FILTER LOW PRESS VALVE CLOSED FILTER NOT ARMED SEC TRANS LOW PRESS SCAV MAIN ON INOP ON INOP OPEN LEFT TO RIGHT RIGHT TO LEFT E J C T F E E D R I G H T DUMP SW ARMED 120 80 40 0 40 R TOTAL FUEL QUANTITY LB AUX L MAIN R MAIN TAIL ...

Page 162: ...and TAIL DC bus 1 The fuel quantity indicators are powered via the SDC as follows RH LH AUX TAIL DC essential bus TOTALIZER battery bus If power to the probes is lost the affected quantity indicator will read zero and the amount of fuel remaining in that tank will be subtracted from the total VENT SYSTEM Each tank is vented at two different points through a series of vent lines which allow air to ...

Page 163: ... level is not known Fuel in excess of 4 000 pounds will spew from the filler if opened PRESSURE REFUELING The pressure refueling system Figure 5 10 consists of a single point adapter a pressure manifold containing a two way check valve three shutoff valves SOV associated with three float operated full level control valves and three vent valves that can be tested during the refueling process and ar...

Page 164: ...6 PILOT TRAINING MANUAL 5 12 CL 601 3R FOR TRAINING PURPOSES ONLY Figure 5 9 Exterior Fueling Components AUXILIARY TANK GRAVITY REFUELING PORT PRESSURE REFUEL DEFUEL CONTROL PANEL MAIN TANK GRAVITY REFUELING PORT PRESSURE REFUELING ADAPTER ...

Page 165: ...S ONLY TANK SOV LEVEL CONTROL VALVE VENT TEST VALVE VENT RELIEF VALVE VENT TEST VALVES FUEL MANIFOLD SINGLE POINT ADAPTER TWO WAY CHECK VALVE VENT LINES REFUELING PRESSURE LEGEND NOTE ENERGIZED CLOSED DURING FUELING ONLY Figure 5 10 Pressure Refueling System Figure 5 11 Refuel Defuel Control Panel ...

Page 166: ...be only partially filled tank levels must be monitored from the cockpit quantity panel For this AC electrical power must be provided usually from the APU or external AC unit DEFUELING The airplane may be completely defueled without the use of electrical power via the single point adapter Fuel tender suction of negative 8 psi max imum at the manifold will open the tank shutoff valves and withdraw f...

Page 167: ...the tail tank fuel transfer panel see Figure 5 7 set to ARMED the fuel transfers automatically to the auxiliary tank at the rate of approximately 25 pounds per minute When only unusable fuel approximately 1 3 U S gallons is left the shutoff valve closes and the fuel transfer pump stops If the ARMED OFF switch is set to OFF while there is still usable fuel in the tail tank the NOT ARMED light illum...

Page 168: ...ms the DUMP SELECT DUMP OPEN guarded switchlight Once armed pressing the green DUMP OPEN switchlight causes it to illuminate and opens the jettison valve Fuel discharges at a rate of 100 pounds per minute NOTE Fuel jettison must only be carried out with flaps set at 0 If an imme diate landing is required the fuel jettison procedure should be initi ated immediately However is is not possible to com...

Page 169: ...EL SWITCH FWD AUX TANK PRIMARY AUX TANK REAR AUX TANK TAIL TANK LEFT MAIN TANK RIGHT MAIN TANK FUELING ADAPTER AND MANIFOLD ROTORBURST ZONE TRANSFER LINE TRANSFER SOV WATER DRAIN FULL LEVEL SWITCH NO 1 TAIL TANK LEVEL SWITCH NO 2 TAIL TANK LEVEL SWITCH JETTISON SOV RAM AIR SECONDARY TRANSFER PUMP SECONDARY TRANSFER SOV PRESSURIZED SHROUD FUELING LINE FLOW SENSOR Figure 5 14 Tail Tank Flow Schemati...

Page 170: ...n tanks prevent A Reverse flow of fuel from the main tanks to the auxiliary tank B Reverse flow of fuel from the auxil iary tank to the main tanks C Gravity flow of fuel from the out board main tank sections to the in board main tank section D Reverse flow of fuel from the inboard main tank sections to the outboard main tank sections 6 Fuel for the APU is normally supplied by A The left scavenge e...

Page 171: ... more than A 3 000 pounds B 4 000 pounds C 3 000 gallons D 4 000 gallons 13 The maximum negative pressure allowed for single point defueling is A 6 psi B 8 psi C 10 psi D 12 psi 14 During flight the maximum imbalance al lowed between the main tanks is A 800 pounds B 1 836 pounds C 2 500 pounds D 2 836 pounds 15 The Tail Tank system amber NOT ARMED light if on steady A Indicated no fuel in the tank...

Page 172: ...tions 6 2 APU SYSTEMS 6 4 Lubricating System 6 4 Fuel System 6 4 Ignition System 6 5 Instrumentation 6 5 Bleed Air Control System 6 6 APU Protection System 6 6 APU Starting System 6 8 APU Cold Weather Starting 6 8 APU Normal Shutdown 6 9 QUESTIONS 6 10 FOR TRAINING PURPOSES ONLY FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL ...

Page 173: ... APU Air Intake 6 3 6 4 APU Exhaust Outlet 6 4 6 5 APU Control Panel 6 5 6 6 APU Remote Indicating Panel 6 7 6 7 Auxiliary Battery Panel 6 8 6 8 Auxiliary Battery Panel SB 601 0418 6 9 6 9 Electrical Control Panel 6 9 FOR TRAINING PURPOSES ONLY FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL ...

Page 174: ...nated GTCP 36 100 E The APU is equipped with self contained oil fuel and ignition systems During starting and operation the APU is monitored by an electronic control unit ECU If any primary parameters are exceeded the ECU will auto matically shut down the APU Separate fire protection consisting of a mon itored fire detection system and a fire extin guishing system is provided for the APU The APU s...

Page 175: ...n air inlet to the compressor is located around the waist of the APU The air intake is shrouded and connected by a rectangular duct to a flush screened inlet figure 6 3 at the top of the rear fuselage compartment Compressor The compressor is a single stage centrifugal type which induces air through the intake compresses the air and directs the airflow for cooling combustion and bleed air extractio...

Page 176: ...ILOT TRAINING MANUAL CL 601 3A R 6 3 FOR TRAINING PURPOSES ONLY DC STARTER MOTOR DRIVE PADS FUEL CONTROL TURBINE IGNITER COMBUSTOR EXHAUST LOAD CONTROL VALVE COMPRESSOR AIR INTAKE GEARBOX Figure 6 2 APU Engine Cutaway Figure 6 3 APU Air Intake ...

Page 177: ...egral part of the APU It converts high turbine rpm to the speeds required for the APU accessories which include APU lubricating pump APU fuel control unit AC generator adapter unit APU SYSTEMS The APU systems consist of the following Lubricating system Fuel system Ignition system Instrumentation Bleed air control system APU protection system ECU APU starting system LUBRICATING SYSTEM The APU lubri...

Page 178: ...meter located within the APU enclosure in the rear fuselage compartment The rpm gage is calibrated in percentage of design 100 rpm from 0 to 110 The rpm signal is generated by a monopole sen sor installed on the planetary gearbox The monopole transmits the rpm signal to the elec tronic control unit which in turn supplies the RPM indicator The EGT indicator is calibrated from 0 to 10 in degrees Cel...

Page 179: ...gine 10th stage bleed air switchlight and the bleed air ISOL switchlight are both pushed in An amber FAILED light works through the electrical interlock circuit The FAILED light will illuminate after a five second time delay if the load control valve has not closed and one of the following conditions exists The left engine 10th stage bleed air switchlight is pushed in The right engine 10th stage b...

Page 180: ...tion flags the remote indicating panel has two push button switches one labeled INDicator RESET and the other labeled APU STOP Pushing the INDicator RESET button with power on the battery bus will reset any tripped flags even if the fault has not been corrected The APU STOP pushbutton when pushed in troduces a false overspeed signal to the ECU and the APU automatically shuts down NOTE When a remot...

Page 181: ...he green STARTER light will extinguish Acceleration will continue at 95 rpm the ECU will deactivate the ignition arm the load control valve the ADaPTeR the APU LO PRESSure and HI TEMPerature lights and il luminate the APU GENerator OFF light Figure 6 7 Four seconds later the green APU ReaDY light will illuminate The rpm and EGT will stabilize at the steady state no load values The APU is now fully...

Page 182: ...ure a successful start APU NORMAL SHUTDOWN The APU is normally shut down by 1 First turning off the APU generator switch Figure 6 9 and without fur ther delay 2 Push the START STOP switchlight Figure 6 5 The APU spooldown should be monitored on the rpm indica tor until it reaches zero The spooldown should be smooth 3 Press out APU BLEED AIR switchlight 4 Press out APU POWER FUEL ON OFF switchlight...

Page 183: ...and annun ciators on the APU control panel B Start the APU fuel boost pump and arm the START STOP switchlight C Open the APU fuel supply valve and the APU negative G fuel supply valve D Both B and C are correct 2 APU ignition is activated when the A APU rpm reaches 10 during starting B PWR FUEL switchlight is pushed in C START STOP switchlight is pushed in D APU fuel boost pump pressure switch ope...

Page 184: ... System 7 7 Ignition System 7 10 Engine Power Control 7 13 Engine Instrumentation 7 15 Engine Starting 7 17 Engine Speed Control and APR Systems 7 21 Engine Vibration Monitoring System 7 25 THRUST REVERSERS 7 26 General 7 26 Control 7 26 Indication 7 28 Protection 7 28 Operation 7 29 QUESTIONS 7 30 FOR TRAINING PURPOSES ONLY FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL ...

Page 185: ...anel 7 16 7 14 Bleed Air Control Panel 7 17 7 15 External Air Supply Adapter 7 19 7 16 Bleed Air Sources First Engine Start Schematic 7 19 7 17 Cross Bleed Start Left Engine from Right Engine Schematic 7 19 7 18 Maximum Allowable Start Time and Time to Stabilize Idle Seconds 7 20 7 19 Airstart Envelope 7 21 7 20 APR Control Panel 7 21 7 21 APR Engine Speed Schematic 7 24 7 22 Engine Vibration Moni...

Page 186: ...he engines are modular in design to facilitate maintenance and reduce airplane downtime Each engine incorporates self contained oil fuel and ignition systems in addition to a fire and or overheat detection system A fire ex tinguishing system is common to both en gines Pneumatically operated cascade thrust reversers are standard equipment Each engine is monitored during takeoff by an electronically...

Page 187: ...ter the engine will be discussed under seven major sections 1 Air inlet section 2 Fan section 3 Compressor 4 Combustor 5 Turbine 6 Exhaust 7 Accessory gear Air Inlet Section The nacelle fairing forms the main air inlet at the front of the engine fan section Fan Section The single stage fan and integral two piece nose cone are installed in the front frame The fan is basically the low pressure LP co...

Page 188: ...mpera ture compensating system to maintain the required variable geometry accuracy through out the normal fuel temperature range The variable geometry module in the FCU will di rect HP fuel to two variable geometry actua tors to operate the inlet and stator vanes A feedback system relays the position of the vanes to the FCU at all times When the en gine is static and during steady state operation ...

Page 189: ...me The gearbox is driven by a tower shaft and bevel gear assembly from the main HP spool rotor shaft The following accessories are driven by the accessory gearbox N1 speed control alternator Integrated drive generator Oil pump Fuel pumps and FCU Hydraulic pump In addition to these accessories an air turbine starter is mounted on the accessory gearbox to provide engine cranking through a clutch OPE...

Page 190: ...gh the replenish ment system in the rear equipment bay Control An oil replenishing control panel powered from the battery direct bus Figure 7 3 con tains a power switch a green power ON light and two green oil full switchlights labeled LH FULL and RH FULL These two lights have a press to test feature A three position man ual selector valve labeled L OFF and R is located adjacent to the control pan...

Page 191: ...o two outputs and transmits them to alternate fiber optic segments that form the vertical analog scales of the oil pressure and oil temperature indi cators Figure 7 5 The fiber optic segments are color coded red yellow and green these colors are also painted on the instrument face outboard of the analog scales A blue light at the bottom of each vertical scale indicates a power on condition The oil...

Page 192: ...ressor stator vanes to provide engine stall surge protection Major Components The major components of the fuel system include an engine driven LP pump heat exchanger a by pass filter a dual element HP pump an inte grated hydromechanical electronic fuel control unit FCU a fuel flow distributor and 18 fuel nozzles in the combustor system LP Engine Driven Pump The LP engine driven pump receives inlet...

Page 193: ...CTRICAL SUMP VENT REGULATOR B SUMP A SUMP FAN BEARINGS COMPRESSOR BEARINGS S S S RESTRICTOR BYPASS VALVE PRESSURE TRANSDUCER AND LOW PRESSURE WARNING SWITCH CHIP DETECTOR CHIP DETECTOR CHIP DETECTORS ACCESSORY GEARBOX OIL PUMP ASSEMBLY DEAERATOR OIL TANK RELIEF VALVE CHIP DETECTOR FILTER FUEL IN FUEL OUT OIL COOLER IMPENDING BYPASS INDICATOR RELIEF VALVE S S S S S P COMPRESSOR BEARINGS TURBINE BEA...

Page 194: ...sor inlet temperature T2C The FCU has a fail safe schedule in the event of loss of T2C input In this case the variable geometry and the acceleration schedules will revert to a fixed temperature reference If high thrust is set at the time of failure a minor de crease in thrust may result If failure occurs at idle thrust possible compressor damage can result if an attempt is made to accelerate the e...

Page 195: ...w for main and scavenge ejector operation The metering section of the FCU in response to the computing section signals me ters fuel through the flowmeter to the fuel man ifold From the fuel manifold fuel is supplied in precisely equal amounts through the 18 noz zles in the combustor During this operation the variable geometry section of the FCU operating in response to inputs representing N2 rpm a...

Page 196: ...NLET GUIDE VANES STATOR VANES JET PUMP MOTIVE FLOW FUEL ECOLOGY TANK LP PUMP FUEL HEATER AIR OUT 14TH STAGE AIR IN FILTER BYPASS BYPASS FUEL TEMP INDICATOR PUMP BYPASS TORQUE MOTOR HP PUMP N1 T2 N2 AMPLIFIER TRANSDUCER THROTTLE LEVER VARIABLE GEOMETRY ACTUATORS DRAIN VALVE 18 FUEL HOSES FUEL FLOW DISTRIBUTOR BYPASS BYPASS VALVE OIL OUT OIL COOLER OIL IN P3 T2C N2 FUEL FLOW COMBUSTOR SUPPLY LP PUMP...

Page 197: ...he appro priate STOP switchlight In flight Ignition In flight ignition is separate for each engine It is designed to provide dual ignition for wind milling relights or during single engine operation Control and Indication The in flight ignition system is controlled by a switchlight Figure 7 8 for each engine la beled IN FLIGHT START Pushing in one of these switchlights will il luminate the green I...

Page 198: ... ignition of the duration of stall warning regardless of the position of all other ignition switches ENGINE POWER CONTROL General Engine power control is provided on a quad rant located on the center pedestal Thrust Levers The individual engine thrust levers Figure 7 9 operate in quadrant slots from a full aft po sition labeled SHUT OFF to a full forward position labeled MAX POWER An inter mediate...

Page 199: ...NG PURPOSES ONLY Figure 7 10 Ignition System Schematic AC ESSENTIAL BUS BATTERY BUS A IGNITER POWER LEGEND B IGNITER POWER FROM STALL PROTECTION STATIC INVERTER FROM STALL PROTECTION SYSTEM STATIC INVERTER AC ESSENTIAL BUS C 28 BATTERY BUS B 169 B A A B LEFT ENGINE IGNITION CONTROL RELAY ...

Page 200: ...ovide for safe green cau tion yellow and warning red indications The bottom segment in each vertical scale is power indicator that will show blue if power is available to the scale Power Sources The engine instruments are powered from a signal data converter SDC The SDC is sup plied DC power from the battery bus and the essential DC bus The SDC processes the in puts from the various engine paramet...

Page 201: ...ertical scale will illuminate if the ITT reaches 871 C These lights also illuminate during the in strument test A two position switch labeled DGT OFF Figure 7 11 located at the bottom of the ITT panel allows the crew to extinguish all engine parameter digital displays which might be an noying on extended nighttime operations N2 RPM N2 rpm Figure 7 11 is supplied by an alter nator driven by the acc...

Page 202: ... switchlight Figure 7 8 to arm an ignition system and check that the ap plicable green light illuminates Push and hold the appropriate START switch light for 2 seconds The green START light will illuminate as will the ON light in the selected ignition switchlight The ISOLation valve OPEN light will also illuminate The left and right en gine BLEED CLOSED lights will extinguish Verify engine rotatio...

Page 203: ...rt using a cross bleed air supply are similar to those for APU bleed or external air source except that the APU bleed air Figure 7 13 must be off Push the BLEED AIR switch Figure 7 14 of the operating engine and check that the bleed air pressure is 45 psi minimum then continue as for APU bleed air start Figure 7 17 illustrates the availability of bleed air during a cross bleed start of the left en...

Page 204: ...D AIR SOV RIGHT ENGINE 10TH STAGE BLEED AIR APU BLEED AIR LEGEND Figure 7 16 Bleed Air Sources First Engine Start Schematic LEFT ENGINE ATS ATS APU 10TH STAGE BLEED AIR LEFT START VALVE LEFT BLEED AIR SOV EXTERNAL AIR LCV ISOLATION VALVE RIGHT START VALVE RIGHT BLEED AIR SOV RIGHT ENGINE 10TH STAGE BLEED AIR 10TH STAGE BLEED AIR LEGEND Figure 7 17 Cross Bleed Start Left Engine from Right Engine Sc...

Page 205: ...ra tures below 15 C 59 F the start sequence may exceed 60 seconds Figure 7 18 Before attempting another start dry motor the engine with both ignition systems off and the affected thrust lever at SHUT OFF NOTE The air turbine duty cycle for normal engine start is 3 consecutive cycles with 5 minutes cooling be tween additional cycles For dry motoring the ATS duty cycle is 90 seconds with a 5 minute ...

Page 206: ... lights will illuminate Advance the thrust lever to IDLE and moni tor all engine related instruments until the en gine is stabilized Then push the IN FLighT START switchlight again The green light and the IGN A and B ON lights will extinguish then complete the After Start checklist ENGINE SPEED CONTROL AND APR SYSTEMS General The automatic performance reserve APR is a solid state system which cons...

Page 207: ...d The serviceable engine s response to an APR trigger produces less than 2 N1 rpm increase within 2 seconds The ECU input voltages are outside ac ceptable limits The monitoring system detects failure of the microcomputer or the two inter nal power supplies Either or both N1 input signals are out of limits Battery input voltage fails The two WOW inputs disagree A unwarranted APR command is triggere...

Page 208: ...illuminate accompanied by the MASTER CAUTION light Operation Before takeoff the static and dynamic tests are performed and determined as valid both en gine speed control switches are on and the APR switch is at ARM The green READY light will illuminate after 79 N1 The amber APR light and the green L ON and R ON lights and the TEST light are extinguished Figure 7 21 illustrates an APR trigger Both ...

Page 209: ...EL FLOW BATTERY POWER N1 INPUT LEGEND N2 INPUT APR TRIGGER T2 INPUT POWER LEVER ANGLE FEEDBACK APR CONTROLLER FLAPS 45 WOW BATTERY DIRECT BUS N1 DESIRED N1 ACTUAL N1 T2 N2 PLA POWER FEEDBACK APR MV FCU FUEL CONTROL AMPLIFIER ECU TM N1 DESIRED N1 ACTUAL N1 T2 N2 PLA POWER FEEDBACK METERED FUEL TO COMBUSTOR MV METERING VALVE TM TORQUE MOTOR APR MV FCU APR OPERATING LEFT ENGINE ...

Page 210: ...ator and flash ing MASTER CAUTION lights NOTE The test system does not test the en gine mounted transducers or cable circuitry The indicator needle re sponse following engine starting in dicates proper operation of the system Components AC 5105 and Subsequent A transducer mounted on the compressor cas ing of each engine generates an electrical sig nal proportional to the intensity of the engine vi...

Page 211: ...ors to lie flat and form part of the fan airflow exit nozzle NOTE Only fan airflow is reversed The re verser system does not affect the core engine airflow which continues on its normal path to the atmosphere CONTROL The thrust reversers are controlled by levers Figure 7 9 piggyback mounted on the thrust levers The thrust reverser levers are latched in the fully forward position The latch must be ...

Page 212: ...y CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL CL 601 3A 7 27 FOR TRAINING PURPOSES ONLY Figure 7 24 Thrust Reversers NORMAL OPERATION BYPASS AIRFLOW BYPASS AIRFLOW CORE AIRFLOW REVERSER DEPLOYED CORE AIRFLOW ...

Page 213: ...sys tem with the UNSAFE TO ARM light illumi nated could result in immediate deployment of that thrust reverser at touchdown On the ground this light will illuminate if the asso ciated reverser was not armed and the thrust reverser lever is actuated The amber REVERSER UNLOCKED light Figure 7 26 will illuminate if 1 the trans lating sleeve is not stowed 2 the pneumatic brake is released 3 the mechan...

Page 214: ...Do not arm a thrust reverser in flight if the UNSAFE TO ARM light is illuminated After touchdown when weight on wheels or wheel spin up is being sensed and the thrust lever at idle unlatch and raise the thrust re versers levers and hold gently against the solenoid stops Check that both amber RE VERSER UNLOCKED lights illuminate fol lowed in approximately 2 seconds by both green REVERSER THRUST lig...

Page 215: ...he variable geometry system B Jump and rate system in the FCU C FCU governor D Speed control ECU on the FCU 6 Electrical power for engine ignition is supplied by the A Battery bus and essential AC bus B Essential DC bus C AC bus 1 and AC bus 2 D Self contained exciters on each engine 7 Prior to engine starting ITT is indicating 150 C the starting procedure is A Select Ignition A or B but not both ...

Page 216: ... System 7 7 Ignition System 7 11 Engine Power Control 7 14 Engine Instrumentation 7 14 Engine Starting 7 16 Engine Speed Control and APR Systems 7 21 Engine Vibration Monitoring System 7 24 THRUST REVERSERS 7 24 General 7 24 Control 7 25 Indication 7 26 Protection 7 26 Operation 7 27 QUESTIONS 7 28 FOR TRAINING PURPOSES ONLY FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL ...

Page 217: ...nt Control Panel 7 15 7 13 APU Control Panel 7 17 7 14 Bleed Air Control Panel 7 17 7 15 External Air Supply Adapter 7 18 7 16 Bleed Air Sources First Engine Start Schematic 7 18 7 17 Cross Bleed Start Left Engine from Right Engine Schematic 7 18 7 18 Maximum Allowable Start Time and Time to Stabilize Idle Seconds 7 20 7 19 Airstart Envelope 7 20 7 20 APR Control Panel 7 21 7 21 APR Engine Speed S...

Page 218: ...he engines are modular in design to facilitate maintenance and reduce airplane downtime Each engine incorporates self contained oil fuel and ignition systems in addition to a fire and or overheat detection system A fire ex tinguishing system is common to both en gines Pneumatically operated cascade thrust reversers are standard equipment Each engine is monitored during takeoff by an electronically...

Page 219: ...r the engine will be discussed under seven major sections 1 Air inlet section 2 Fan section 3 Compressor 4 Combustor 5 Turbine 6 Exhaust 7 Accessory gear Air Inlet Section The nacelle fairing forms the main air inlet at the front of the engine fan section Fan Section The single stage fan and integral two piece nose cone are installed in the front frame The fan is basically the low pressure LP comp...

Page 220: ...mpera ture compensating system to maintain the required variable geometry accuracy through out the normal fuel temperature range The variable geometry module in the FCU will di rect HP fuel to two variable geometry actua tors to operate the inlet and stator vanes A feedback system relays the position of the vanes to the FCU at all times When the en gine is static and during steady state operation ...

Page 221: ...ame The gearbox is driven by a tower shaft and bevel gear assembly from the main HP spool rotor shaft The following accessories are driven by the accessory gearbox N1 speed control alternator Integrated drive generator Oil pump Fuel pumps and FCU Hydraulic pump In addition to these accessories an air turbine starter is mounted on the accessory gearbox to provide engine cranking through a clutch OP...

Page 222: ...gh the replenish ment system in the rear equipment bay Control An oil replenishing control panel powered from the battery direct bus Figure 7 3 con tains a power switch a green power ON light and two green oil full switchlights labeled LH FULL and RH FULL These two lights have a press to test feature A three position man ual selector valve labeled L OFF and R is located adjacent to the control pan...

Page 223: ...coded red yellow and green These colors are also painted on the instrument face outboard of the analog scales A blue light at the bottom of each vertical scale indicates a power on condition The oil pressure indicators are calibrated in psi The oil temperature indicators are calibrated in degrees Celsius Low oil pressure is sensed by a switch on the pressure pump output line When the switch closes...

Page 224: ...ting conditions In addition the fuel system operates the vari able geometry system of the compressor to po sition inlet guide vanes and compressor stator vanes to provide engine stall surge protection Major Components The major components of the fuel system include an engine driven LP pump heat exchanger a by pass filter a dual element HP pump an inte grated hydromechanical electronic fuel control...

Page 225: ...YPASS VALVE PRESSURE TRANSDUCER AND LOW PRESSURE WARNING SWITCH CHIP DETECTOR CHIP DETECTOR CHIP DETECTORS ACCESSORY GEARBOX OIL PUMP ASSEMBLY DEAERATOR OIL TANK RELIEF VALVE CHIP DETECTOR FILTER FUEL IN FUEL OUT OIL COOLER IMPENDING BYPASS INDICATOR RELIEF VALVE S S S S S P COMPRESSOR BEARINGS TURBINE BEARINGS C SUMP 40 0 150 155 OIL TEMP 163 L R 90 60 30 120 0 25 115 130 OIL PRESS L R 60 80 40 3...

Page 226: ...nd the acceleration schedules will revert to a fixed temperature reference If high thrust is set at the time of failure a minor decrease in thrust may result If failure occurs at idle thrust possible compressor damage can result if an at tempt is made to accelerate the engine Core engine overspeed in limited three ways 1 the N2 governor in the FCU 2 the com puter section therefore if the FCU gover...

Page 227: ... FIREWALL SOV S LEFT COLLECTOR TANK INLET GUIDE VANES STATOR VANES JET PUMP MOTIVE FLOW FUEL LP PUMP FUEL HEATER FILTER BYPASS FUEL TEMP INDICATOR PUMP BYPASS TORQUE MOTOR HP PUMP N1 T2 N2 AMPLIFIER TRANSDUCER THROTTLE LEVER VARIABLE GEOMETRY ACTUATORS P3 T2C N2 FUEL FLOW COMBUSTOR SUPPLY LP PUMP PRESSURE HP PUMP PRESSURE LEGEND SIGNAL CONTROL OIL AIR ELECTRICAL MECHANICAL 0 200 3500 4000 3000 200...

Page 228: ...he design full open position permitting maxi mum airflow through the core engine IGNITION SYSTEM General The CF34 3A1 series engine has a dual high energy capacitor discharge type ignition The ignition system for each engine consists of an ignitor plug A and an ignitor plug B in the combustor with each ignitor powered through its own exciter Operation of either ignitor is sufficient to pro vide fo...

Page 229: ...only if either ignition A and or ignition B has been armed The green CONT IGN legend the green IGN legend and the white ON leg ends of the selected ignition system will all il luminate during operation of the continuous ignition system Automatic Stall Protection Ignition The automatic or stall protection ignition sys tem provides anti flameout protection during periods of engine inlet turbulence c...

Page 230: ...LY CL 601 3R 7 13 Figure 7 9 Ignition System Schematic AC ESSENTIAL BUS BATTERY BUS A IGNITER POWER LEGEND B IGNITER POWER FROM STALL PROTECTION STATIC INVERTER FROM STALL PROTECTION SYSTEM STATIC INVERTER AC ESSENTIAL BUS C 28 BATTERY BUS B 169 B A A B LEFT ENGINE IGNITION CONTROL RELAY ...

Page 231: ...go around mode Switches are mounted in the throttle quadrant slots to provide 1 takeoff configuration warning for flaps spoilers and horizontal stabilizer 2 pressur ization ground control mode and 3 landing configuration warning landing gear not down and locked at landing power settings Quadrant Friction Control A single friction adjustment twist knob Figure 7 10 is located on the quadrant aft of ...

Page 232: ...displays When compared with the nonlinear analog readout the digital indicators provide a more accurate indication Automatic Dimming A photoelectric cell Figure 7 12 is provided on the engine instrument control panel to pro vide for automatic engine instrument dim ming as ambient light conditions change A rheostat on the same panel allows the crew to set brilliancy to personal preferences Instrume...

Page 233: ... flow indicators The analog scales are calibrated in pounds of fuel per hour from 0 to 4 000 The digital dis plays are in pounds per hours times 10 ENGINE STARTING General Engine starting is divided into ground starts starter assisted airstarts and windmilling airstarts Starter The engine starter is an electrically controlled air turbine starter ATS Starter output is ap plied through a clutch to t...

Page 234: ...faulty T2C input an IDLE FLOOR STOP is provided to prevent N2 from decreasing below 56 9 If idle speed stabilizes at approxi mately 57 N2 the engine must be shut down immediately and the con dition reported to maintenance Do not attempt to increase idle N2 by advancing the thrust lever because it can result in serious damage to the first stage compressor blades Ground Start External Air The proced...

Page 235: ...D AIR SOV RIGHT ENGINE 10TH STAGE BLEED AIR APU BLEED AIR LEGEND Figure 7 16 Bleed Air Sources First Engine Start Schematic LEFT ENGINE ATS ATS APU 10TH STAGE BLEED AIR LEFT START VALVE LEFT BLEED AIR SOV EXTERNAL AIR LCV ISOLATION VALVE RIGHT START VALVE RIGHT BLEED AIR SOV RIGHT ENGINE 10TH STAGE BLEED AIR 10TH STAGE BLEED AIR LEGEND Figure 7 17 Cross Bleed Start Left Engine from Right Engine Sc...

Page 236: ...f starter operation continues for more than 60 seconds the time delay relay will cause the STOP light to illuminate At temperatures above 15 C 59 F the start should be aborted by pushing the STOP switchlight anytime up to 55 N2 rpm The thrust lever should then be moved to SHUT OFF then wait one minute before attempting another start At tempera tures below 15 C 59 F the start sequence may exceed 60...

Page 237: ...ust lever to IDLE and moni tor all engine related instruments until the en gine is stabilized Then push the IN FLighT FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL 7 20 CL 601 3R FOR TRAINING PURPOSES ONLY AIRSTART ALTITUDE LIMIT 21 10 0 0 10 13 N2 RPM 55 WINDMILL START 10 000 21 000 FT STARTER ASSIST BELOW 21 000 FT WINDMILL START BELOW 10 000 FT Figure 7 19 Airstart Envelope WARN...

Page 238: ...ystem The TEST RESET position is spring loaded to the off position and is used for testing A split legend green light labeled L ON and R ON will illuminate following an APR trigger activating to confirm proper response N1 increase on the serviceable engine A green light labeled READY forms the upper part of a dual legend light which illu minates to confirm APR readiness above 79 N1 if the system i...

Page 239: ...dicated N1 above 83 note the READY light came on at 79 N1 The APR controller samples the fan rpm continuously to determine if they are stable that is fan rpm does not vary more than a pre determined amount The dynamic test initiates an APR trigger to both APR amplifiers which causes both engines to accelerate slightly If the test is valid the TEST light will momen tarily flash If outside the permi...

Page 240: ...EL FLOW BATTERY POWER N1 INPUT LEGEND N2 INPUT APR TRIGGER T2 INPUT POWER LEVER ANGLE FEEDBACK APR CONTROLLER FLAPS 45 WOW BATTERY DIRECT BUS N1 DESIRED N1 ACTUAL N1 T2 N2 PLA POWER FEEDBACK APR MV FCU FUEL CONTROL AMPLIFIER ECU TM N1 DESIRED N1 ACTUAL N1 T2 N2 PLA POWER FEEDBACK METERED FUEL TO COMBUSTOR MV METERING VALVE TM TORQUE MOTOR APR MV FCU APR OPERATING LEFT ENGINE ...

Page 241: ...the respective amber CORE and FAN lights will illuminate accompanied by an Engine M C light NOTE The test system does not test the en gine mounted transducers or cable circuitry The indicator needle re sponse following engine starting in dicates proper operation of the system THRUST REVERSERS GENERAL The Canadair Challenger is equipped with electrically energized pneumatically oper ated thrust rev...

Page 242: ...en the thrust reverser lever is unlatched then moved upward and aft a solenoid is en gaged to prevent more than 20 of lever travel while the air motor operates the ballscrew jacks to drive the translating sleeve aft ex posing the cascade vanes and closing the 10 blocker doors in the bypass duct At this point a microswitch is operated to release the thrust reverser lever lock solenoid Further aft m...

Page 243: ... position or 2 the de ploy stow switch is faulty possibly giving a permanent deploy command Arming the sys tem with the UNSAFE TO ARM light illumi nated could result in immediate deployment of that thrust reverser at touchdown On the ground this light will illuminate if the asso ciated reverser was not armed and the thrust reverser lever is actuated The amber REVERSER UNLOCKED light Figure 7 25 wi...

Page 244: ...Do not arm a thrust reverser in flight if the UNSAFE TO ARM light is illuminated After touchdown when weight on wheels or wheel spin up is being sensed and the thrust lever at idle unlatch and raise the thrust re versers levers and hold gently against the solenoid stops Check that both amber RE VERSER UNLOCKED lights illuminate fol lowed in approximately 2 seconds by both green REVERSER THRUST lig...

Page 245: ...is the A N1 rpm B ITT C N2 rpm D Fuel flow 5 Fan rpm limiting is a sole function of the A Position of the variable geometry sys tem B Jump and rate system in the FCU C FCU governor D Speed control ECU on the FCU 6 Electrical power for engine ignition is supplied by the A Battery bus and essential AC bus B Essential DC bus C AC bus 1 and AC bus 2 D Self contained exciters on each en gine 7 Prior to...

Page 246: ...INGUISHING 8 4 General 8 4 Engine Fire Extinguishing 8 4 APU Fire Extinguishing 8 7 Operation 8 10 Portable Extinguisher 8 11 MAIN LANDING GEAR BAY OVERHEAT DETECTION 8 12 Operation 8 12 Test 8 13 ENGINE JET PIPE PYLON OVERHEAT DETECTION 8 14 Operation 8 15 Test 8 15 QUESTIONS 8 16 FOR TRAINING PURPOSES ONLY FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL ...

Page 247: ...System 8 7 8 6 APU Firex Bottle Installation 8 8 8 7 APU Fire Extinguishing System 8 9 8 8 Portable Fire Extinguisher 8 11 8 9 MLG Bay Overheat Detection Components 8 12 8 10 MLG Bay Overheat Detection System 8 13 8 11 Engine Jet Pipe Pylon Detection Components 8 14 8 12 Engine Jet Pipe Pylon Overheat Detection System 8 15 FOR TRAINING PURPOSES ONLY FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TR...

Page 248: ... from the cockpit The two engine fire bottles are interconnected so that both bottles may be used for either engine The main landing gear bay is provided with a similar detection system that senses an overheat condition and provides a cockpit indication The jet pipe pylon overheat detection system gives the crew a visual indication of an overheat or fire in the jet pipe exhaust and pylon areas of ...

Page 249: ...d will usually advise the flight crew if a loop resistance falls to zero instantaneously such as might happen for a short circuit COMPONENTS The fire detection system components Figure 8 1 include sensing loops detection control units FIRE lights a fire bell and the FIRE WARN FAIL lights on the fire warning test panel Fire Loops and Detection Units Each fire sensing loop Figure 8 2 is a coax ial e...

Page 250: ...ELEMENT ENGINE COMBUSTION ZONE SENSING ELEMENT APU SENSING ELEMENT APU FIRE PUSH BOTTLE ARMED PUSH TO DISCH Figure 8 1 Engine and APU Fire Detection Components OUTER CONDUCTOR GROUNDED INSULATOR RESISTANCE VALUE DECREASES PROPORTIONALLY TO RISE IN TEMPERATURE INNER CONDUCTOR FORMS LOOP TO FIRE DETECTION UNIT Figure 8 2 Fire Sensing Loop ...

Page 251: ...one muted continue to operate as long as a fire overheat condition exists If a fire and overheat detection control unit detects a false warning signal caused by a short in a sensing cable it powers the appropriate FIRE WARN FAIL light on the fire warning test panel and automatically isolates the defective fire circuit The master caution lights flash when a FIRE WARN FAIL light illuminates SYSTEM T...

Page 252: ... a tee type check valve This valve prevents one bottle from discharging its contents into the other bottle if it is empty The left ports are connected to the left engine in the same manner The left and right ports are operated by ex plosive squibs electrically activated from the cockpit Each port contains a squib with dual firing cartridges for redundancy When fired a bullet penetrates a frangible...

Page 253: ...nate when either ENG FIRE light is depressed If either bottle has pressure below 275 psi its associated light will not illuminate Depressing an illuminated BOTTLE ARMED light fires the appropriate squib and causes the Firex bottle to discharge its contents into the engine associated with the ENG FIRE switch light pushed Once the bottle contents have discharged the associated BOTTLE ARMED light ext...

Page 254: ...le is charged with Halon 1301 fire extinguishing agent and pressurized by dry nitrogen at 600 to 625 psi The electrically operated port is connected by tub ing to the APU compartment and contains a squib with dual firing cartridges for redundancy The thermal discharge port operates when the pressure in the bottle exceeds 1 400 psi and dis charges the bottle contents into the area sur rounding the ...

Page 255: ...FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL 8 8 CL 601 3A R FOR TRAINING PURPOSES ONLY APU FIREX BOTTLE Figure 8 6 APU Firex Bottle Installation ...

Page 256: ...and arms the APU Firex bottle squib circuit NOTE If the FIRE switchlight is depressed without being illuminated the APU will shut down BOTTLE ARMED Light This switchlight located adjacent to the FIRE light illuminates whenever the FIRE light is depressed and the Firex bottle has sufficient pressure Depressing the BOTTLE ARMED switchlight when illuminated fires the APU bottle squib and discharges t...

Page 257: ...switchlight caus ing bottle 1 left port squib to fire The contents of bottle 1 are discharged into left engine The bottle 1 pressure drops causing the green BOTTLE 1 ARMED light to ex tinguish and the amber BOTTLE 1 LOW PRESS light to illuminate accompa nied by the FIRE FAULT light and the flashing master caution lights The fire in the left engine extinguishes causing the red LH ENG FIRE light to ...

Page 258: ...ge position and squeezing a spring loaded lever on the extinguisher operating head The lever can be released at any time to stop the dis charge The charge pressure of the extin guishing agent allows the extinguisher to be used at a safe distance from very hot fires or fires generating a dangerous amount of smoke FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL CL 601 3A R 8 11 FOR TRA...

Page 259: ... the top of each main wheel well bin The OVHT and OVHT WARN FAIL switchlights are located below the landing gear control panel OPERATION The detection loops are similar to those of the engine and APU fire detection systems They are connected in series Figure 8 10 and will give a cockpit warning when they detect a temperature in excess of 320 F 160 C When the temperature exceeds this trip level the...

Page 260: ... in the fire detection warn test When the red OVHT light illuminates it indicates that The lamp is serviceable The loops have continuity The overheat detection circuit is ser viceable Pressing the OVHT WARN FAIL switchlight grounds the loops as in the fire detection fault test causing illumination of the OVHT WARN FAIL switchlight along with the ap propriate master caution system reaction This tes...

Page 261: ...ngine jet pipe pylon panel is located on the top right corner of the center instrument panel It incorporates four press to test switch lights two labeled OVHT and two labeled OVHT WARN FAIL The detection loops are similar to the ones on the engine and APU fire detection system One detection loop is located around the tailpipe section of the engine The other is lo cated in the area where the engine...

Page 262: ...d the engine system light indicating that a true overheat cannot be detected TEST Pressing the OVHT switchlight grounds the loop as in the fire detection warning test The red OVHT light illuminates to indicate the detection system is serviceable Pressing the OVHT WARN FAIL switchlight grounds the loop also This causes illumination of the OVHT WARN FAIL light along with an appropriate master cautio...

Page 263: ...lumination of a BOTTLE ARMED light B Ringing of a fire bell C Illumination of an OVHT light D Sounding of a horn 5 If during the warn test operation the APU BOTTLE ARMED switchlight fails to illuminate it indicates A The APU is not operating B The APU squib is unserviceable C The APU Firex bottle pressure is low D The fire detection loop is grounded 6 The number of Firex bottles that can be discha...

Page 264: ...on 9 2 Operation 10th Stage 9 4 BLEED AIR VALVES 14TH STAGE 9 8 Control and Indication 9 8 Operation 14th Stage 9 8 FOOTWARMER AND DEMIST SYSTEM 9 9 General 9 9 Normal Source 9 9 Standby Source 9 9 Control 9 9 BLEED AIR LEAK DETECTION 9 11 General 9 11 Indication 9 11 Testing 9 11 QUESTIONS 9 13 FOR TRAINING PURPOSES ONLY FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL ...

Page 265: ...leed Air Supply APU Operating 9 6 9 6 External Air Supply Adapter 9 7 9 7 Bleed Air Supply External Air Source 9 7 9 8 14th Stage Bleed Air System 9 8 9 9 Copilot s Fascia Panel Footwarmer Demist Knobs 9 9 9 10 Footwarmer and Demisting Normal Operation 9 10 9 11 Bleed Air Leak Annunciator 9 11 9 12 Total Pneumatic System 9 12 FOR TRAINING PURPOSES ONLY FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT...

Page 266: ...ic system has four sources of air 1 the left engine high pressure compressor 2 the right engine high pressure compressor 3 the auxiliary power unit and 4 external air There are bleed ports on the 10th and 14th stages of the CF34 engine Two ports on each engine are interconnected by a Y duct on the 10th stage and a single port on the 14th stage A flow limiter limits air extraction to a spe cific pe...

Page 267: ...owl anti ice SOV are fail safe open if loss of electrical power occurs BLEED AIR VALVES 10TH STAGE The 10th stage bleed air manifold supply is controlled by three identical valves called the left engine and right engine bleed air shutoff valves and the isolation valve The engine bleed air shutoff valves permit flow in both di rections and are primarily used to control bleed air extraction from the...

Page 268: ...sh The isolation valve will open and the green OPEN legend will illuminate The bleed air shutoff valves and the isolation valve will au tomatically close at the termination of start the BLEED CLOSED lights will illuminate and the ISOL OPEN light will extinguish During start these valves are powered by the battery bus Automatic closing of an engine bleed air shutoff valve will also occur if 1 the a...

Page 269: ...ne to the right ACU pres sure regulating and shutoff valve and the right footwarmer demist shutoff valve The pressurization jet pump is supplied from up stream of the right engine bleed air shutoff valve Both sides of the manifolds can be pressurized from one engine by opening the isolation valve FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL 9 4 CL 601 3A FOR TRAINING PURPOSES ONLY...

Page 270: ...tart both engines Prior to selecting an engine start using APU bleed air both engine bleed air switches must be out off because an interlock circuit will automatically close the APU load control valve LCV if switches are positioned in That is if the left bleed air switch alone is selected on in or the right bleed air switch together with the ISOL switch are selected on in the APU LCV will close Fl...

Page 271: ...right side of the bleed air manifold Both en gine bleed air switches must remain off Initiating an engine start either engine while the APU is supplying the manifold will auto matically open both engine bleed air shutoff valves the isolation valve and the selected start valve The four valves will remain open until the start is terminated at approximately 55 N2 FlightSafety CanadaLtée Ltd CL 600 2B...

Page 272: ...ernal supply can also be used for air conditioning and pressurization systems In this case the isolation switch bleed air switches and system switches must be se lected as required FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL CL 601 3A 9 7 FOR TRAINING PURPOSES ONLY ATS ATS APU RIGHT ACU LEFT ACU DEMIST CONTROL KNOB FOOTWARMER CONTROL KNOB PRESSURIZATION JET PUMP FAN HEAT EXCHANGE...

Page 273: ... Before starting the engine the switchlights are selected to the OFF position Since the valves are spring loaded to the open position and there is not air pressure to actuate the valve to the closed position it will be open and the BLEED CLOSED light will be extinguished As the engine rpm increases during the start sequence air pressure from the 14th stage now repositions the shutoff valve to the ...

Page 274: ...ed CKPT HEAT It has three positions NORM OFF and STBY The normal position of the switch energizes the right footwarmer and demist valve The standby position energizes the left foot warmer and demist valve Both valves also re quire pneumatic pressure to operate to the open position NOTE The left footwarmer and demist valve is also electrically energized by the emergency pressurization switch light ...

Page 275: ...n air ground operation pro vides the cooling medium The heat exchanger exhaust valve is modulated by temperature signals from a bulb in the heat exchanger out let duct to determine the cooling airflow and consequently the temperature of the foot warmer and demist air FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL 9 10 CL 601 3A FOR TRAINING PURPOSES ONLY DEMIST CONTROL KNOB FOOTWARM...

Page 276: ...t in one of the engine bleed air switchlights Figure 9 1 or a single red DUCT FAIL light in the wing anti ice system will illuminate to indicate the affected area Additional indication of a bleed air leak lo cation is provided by the BLEED AIR LEAK annunciator panel located behind the copilot Figure 9 11 Each magnetic indicator iden tifies a specific section of the duct to pinpoint a leak Normally...

Page 277: ...GE BLEED AIR SOV PRESSURE XDUCER PRESSURE XDUCER ISOL VALVE LH COWL ANTI ICE VALVE RH COWL ANTI ICE VALVE LH WING ANTI ICE VALVE RH WING ANTI ICE VALVE LOAD CONTROL VALVE LCV RH ACU VALVE LH ACU VALVE ANTI ICE ISOL VALVE T R LH ATS VALVE RH ATS VALVE THRUST REVERSER DUCT SENSOR HEAT EXCHANGER FAN RAM AIR EMER PRESS SOV THRUST REVERSER LEFT ACU EXT AIR RIGHT ACU PRESSURIZATION JET PUMP DEMIST CONTR...

Page 278: ...ist shutoff valve is opened by A Cockpit heat selection to normal B Selecting emergency pressurization C Selecting ACU ON D Pulling on the demist knob 4 The APU bleed air supply is connected to the pressure manifold A Upstream of the right engine bleed air valve B Through the open isolation valve C Upstream of the left engine bleed valve D Between the left engine bleed valve and the isolation valv...

Page 279: ...STAGE 9 2 Control and Indication 9 2 Operation 10th Stage 9 4 BLEED AIR VALVES 14TH STAGE 9 8 Control and Indication 9 8 Operation 14th Stage 9 8 FOOTWARMER AND DEMIST SYSTEM 9 8 BLEED AIR LEAK DETECTION 9 10 General 9 10 Indication 9 11 Testing 9 11 QUESTIONS 9 13 FOR TRAINING PURPOSES ONLY FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL ...

Page 280: ...upply APU Operating 9 6 9 6 External Air Supply Adapter 9 7 9 7 Bleed Air Supply External Air Source 9 7 9 8 14th Stage Bleed Air System 9 8 9 9 Footwarmer and Demisting Normal Operation 9 9 9 10 Temperature Control Panel 9 10 9 11 Copilot s Fascia Panel AIR Knob 9 10 9 12 Bleed Air Leak Annunciator 9 11 9 13 Total Pneumatic System 9 12 FOR TRAINING PURPOSES ONLY FlightSafety CanadaLtée Ltd CL 600...

Page 281: ...eed air sources ducting distribution control indication and duct failure monitoring systems The pneumatic system has four sources of air 1 the left engine high pressure compressor 2 the right engine high pressure compressor 3 the auxiliary power unit and 4 external air There are bleed ports on the 10th and 14th stages of the CF34 engine Two ports on each engine are interconnected by a Y duct on th...

Page 282: ...eed air shutoff valves and the isolation valve The engine bleed air shutoff valves permit flow in both di rections and are primarily used to control bleed air extraction from their associated en gine The isolation valve also provides two way flow and its function is to divide the bleed air manifold into a left and a right sec tion Therefore the isolation valve is nor mally closed in flight CONTROL...

Page 283: ...d 14th stage or 2 if the associated air conditioning unit ACU fails Figure 9 1 because of overpressure and the affected ACU FAIL light illuminates 10th stage only In the latter case if the isolation valve is open it also will automatically close and the green OPEN light will extinguish Pressure Indication 10th Stage The bleed air manifold pressure is sensed by two transducers one on each side of t...

Page 284: ...g the isolation valve Figure 9 4 illustrates the CL 601 normal air borne configuration of the engine bleed air system Bleed air is still available to the pres surization jet pump even with the right en gine bleed air shutoff valve closed Anti icing is not provided from the 10th stage bleed air system and will be discussed separately in Chapter 10 FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAIN...

Page 285: ... load control valve LCV if switches are positioned in That is if the left bleed air switch alone is selected on in or the right bleed air switch together with the ISOL switch are selected on in the APU LCV will close FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL CL 601 3R 9 5 FOR TRAINING PURPOSES ONLY LEFT ACU APU RIGHT ACU ATS ATS LH 10TH STAGE BLEED AIR SOV LH ATS VALVE 10TH STA...

Page 286: ...eed air switches must remain off Initiating an engine start either engine while the APU is supplying the manifold will auto matically open both engine bleed air shutoff valves the isolation valve and the selected start valve The four valves will remain open until the start is terminated at approximately 55 N2 An approved external air supply can be con nected to an adapter Figure 9 6 located in a c...

Page 287: ...nd pressurization systems In this case the isolation switch bleed air switches and system switches must be se lected as required FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL CL 601 3R 9 7 FOR TRAINING PURPOSES ONLY APU ATS ATS 0TH STAGE BLEED AIR PORTS ISOL VALVE PRESSURE XDUCER PRESSURIZATION JET PUMP RH ATS VALVE 10TH STAGE BLEED AIR PORTS RH 10TH STAGE BLEED AIR SOV RH ACU VALV...

Page 288: ...sition Since the valves are spring loaded to the open position and there is not air pressure to actuate the valve to the closed position it will be open and the BLEED CLOSED light will be extinguished As the engine rpm increases during the start sequence air pressure from the 14th stage now repositions the shutoff valve to the closed position and the BLEED CLOSED light illu minates If electrical p...

Page 289: ...Figure 9 10 When selected to ON the electric fan starts the airflow The switch also activates the heating element A duct tem perature sensor mounted on the exhaust of the heater monitors the duct temperature to keep the duct temperature within adequate limits A three position diverter valve installed just downstream of the heater element in the duct ing is manually positioned with a push pull link...

Page 290: ... fatigue could result in catastrophic consequences if leakage occurs The insulation surrounding the bleed air ducts has regularly spaced holes and is clasped at both ends If a crack or other duct failure oc curs the hot air escaping from the holes in the duct insulation impinges on two parallel sens ing loops that are routed along the ducts There are two detection units each monitoring in puts fro...

Page 291: ...black and white triangles An indicator RESET switch is provided to reset any tripped indicator TESTING A SYSTEM TEST button located on the BLEED AIR LEAK annunciator panel when pushed will 1 simultaneously trip all indi cators 2 illuminate the flashing DUCT FAIL light 3 illuminate the DUCT FAIL lights in the engine bleed air switchlights 4 lights and 4 illuminate the DUCT FAIL light on the ANTI IC...

Page 292: ...EED AIR SOV LH 10TH STAGE BLEED AIR SOV PRESSURE XDUCER PRESSURE XDUCER ISOL VALVE LH COWL ANTI ICE VALVE RH COWL ANTI ICE VALVE LH WING ANTI ICE VALVE RH WING ANTI ICE VALVE LOAD CONTROL VALVE LCV RH ACU VALVE LH ACU VALVE ANTI ICE ISOL VALVE T R LH ATS VALVE RH ATS VALVE THRUST REVERSER THRUST REVERSER LEFT ACU EXT AIR RIGHT ACU PRESSURIZATION JET PUMP ATS ATS APU PRESSURE RELIEF VALVE PRESSURE ...

Page 293: ...ess the bleed valves and isolation valve are manually opened 3 The APU bleed air supply is connected to the pressure manifold A Upstream of the right engine bleed air valve B Through the open isolation valve C Upstream of the left engine bleed valve D Between the left engine bleed valve and the isolation valve 4 Loss of the electrical power source will cause 10th stage A Isolation valve to fail op...

Page 294: ...1 ICE DETECTION SYSTEM 10 3 General 10 3 Operation 10 3 Failure Detection 10 4 Test Function 10 4 ANTI ICING SYSTEMS 10 4 Pneumatically Operated Systems 10 4 Electrically Operated Systems 10 8 QUESTIONS 10 13 FOR TRAINING PURPOSES ONLY FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL ...

Page 295: ...s and Indicators 10 5 10 6 Wing Anti icing 10 6 10 7 Wing Anti icing Controls and Indicators 10 7 10 8 Windshield and Side Window Panels 10 8 10 9 Windshield Anti icing Defogging System 10 9 10 10 Windshield Anti icing Controls and Indicators 10 10 10 11 ADS Anti icing Controls and Indicators 10 11 FOR TRAINING PURPOSES ONLY FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL ...

Page 296: ...ntity of ice forms on the probes Pilot action is required to activate the anti icing systems The anti icing systems are divided into two cat egories those which use hot engine bleed air such as wing and engine anti icing and those which use electrical power such as the ADS heaters and windshield anti icing Bleed air is used to provide internal demist ing of the windshield This air is ducted to a d...

Page 297: ...ING MANUAL 10 2 CL 601 3A R FOR TRAINING PURPOSES ONLY TOTAL AIR TEMPERATURE PROBE RIGHT SIDE ONLY PITOT STATIC HEADS WING LEADING EDGES ICE DETECTORS COWL WINDSHIELDS ANGLE OF ATTACK VANES SIDE WINDOWS ALT STATIC PORTS COWL Figure 10 1 Anti iced Areas ...

Page 298: ...ural frequency of 40 kHz When ice ac cumulates on the probe its frequency de creases slightly due to the increase in mass Due to the high frequency of the probe only ice will adhere other materials such as dirt or oil will not During icing conditions an internal micro computer detects probe frequency drops of more than 133 Hz and activates an associated flashing red ICE light amber on Canadian air...

Page 299: ...f the red Canadian amber ICE lights ANTI ICING SYSTEMS PNEUMATICALLY OPERATED SYSTEMS General Hot air for the operation of the cowl and wing anti icing systems is supplied by the 14th stage bleed air system of each engine s compressor The 14th stage shutoff valves are spring loaded open and are energized closed Bleed air is re quired to close these electropneumatic valves After engine start the 14...

Page 300: ...hite ON legend illuminates Pressing the switchlight again energizes the valve s to the closed position and extinguishes the ON legend The amber FAIL legend illuminates if the sys tem is selected on and the pressure switches downstream of the shutoff valve detects in sufficient bleed air pressure When the system is initially selected on the FAIL light illumi nates momentarily until bleed air pressu...

Page 301: ...ght wing The bleed air flow is controlled by a pair of modulating valves one for each wing but operated together The wing anti ice controller modulates the wing anti ice valves when the switch is se lected to the NORMAL position Figure 10 7 An isolation valve in the rear manifold duct separates the left and right halves of the sys tem This valve is normally closed In case of engine failure or the ...

Page 302: ... powered by the battery bus and the DC essential bus Controls and Indicators The NORMAL or STANDBY mode is selected with a WING switch on the upper left of the anti icing control panel The switch has three positions STANDBY OFF and NORMAL In the NORMAL mode both modulating valves open and operate automatically according to signals supplied by the anti icing controller The controller modulates the ...

Page 303: ...ti icing system however is equipped with only a single detection loop instead of two paral lel detection loops When a bleed air leak is detected in the wing anti icing system the red DUCT FAIL light will illuminate the mas ter DUCT FAIL warning light on the center in strument panel will flash and the location of the bleed leak will be displayed on the bleed air leak annunciator panel behind the co...

Page 304: ...ht panels is controlled by two independent anti icing con trollers In addition the temperature in the windshield and side windows is controlled by separate circuits within the controllers The controllers receive temperature signals from sensors embedded in each panel A sec ond sensor is provided in each panel as a spare FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL CL 601 3A R 10 9...

Page 305: ...e anti icing control panel tests both the left and right systems When the button is pressed a signal is sent to override the temperature sen sors and monitor the output current If the system is operating satisfactorily the adja cent green TEST lights illuminate Air Data System ADS Anti icing General Electric heating elements are used to anti ice pitot static probes the angle of attack vanes the to...

Page 306: ...lightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL CL 601 3A R 10 11 FOR TRAINING PURPOSES ONLY HTR FAIL ADS HEATER CONT PUSH TO RESET TAT HTRS OFF ALL ON AOA HTR CURRENT STATIC PITOT POWER METER SELECT R R R L L L LEFT ANGLE OF ATTACK VANE LEFT STATIC PORT RIGHT STATIC PORT LH PITOT STATIC PROBE RIGHT ANGLE OF ATTACK VANE TOTAL AIR TEMP PROBE CONTROL PANEL OVERHEAD PANEL RH PITOT STATIC...

Page 307: ...h each position until the failed heater is detected by reference to the HTR CURRENT meter When the meter pointer falls into the red zone less than 40 it shows that the selected heater is faulty All failure indications except those associ ated with the pitot static probes may be can celed by pressing the HTR FAIL switchlight Failure warning for the pitot static probes can not be canceled Resetting ...

Page 308: ...icing is required D Opened when engine anti icing is re quired and one of the 14th stage bleed air shutoff valves fails to open 6 The wing anti ice HEAT lights illumi nate to indicate that A A minimum acceptable temperature has been reached in the leading edge B The maximum acceptable temperature has been reached in the leading edge C There is both sufficient heat and pres sure for adequate leadin...

Page 309: ...DS anti ice warning system the true one is A Illumination of the HTR FAIL lights is not accompanied by illumination of the ANTI ICE annunciator B The PITOT HEAT lights may be ex tinguished by pressing the RESET switchlight C The PITOT HEAT lights may not be extinguished by pressing the RESET switchlight D The HTR FAIL light may not be ex tinguished by pressing the RESET switchlight FlightSafety Ca...

Page 310: ... 2A TEMPERATURE CONTROL 11 2A General 11 2A Normal Mode 11 3A Standby Mode 11 3A Manual Mode 11 3A VALVES 11 3A General 11 3A Engine Bleed Air Valves 11 3A Isolation Valve 11 3A ACU Valves 11 4A DISTRIBUTION 11 4A OPERATION 11 4A General 11 4A Ground Operation 11 6A In Flight Operation 11 6A FOR TRAINING PURPOSES ONLY FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL ...

Page 311: ...RAM AIR VENTILATION 11 8A General 11 8A Control 11 8A QUESTIONS 11 9A FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL 11 ii CL 601 3A FOR TRAINING PURPOSES ONLY ...

Page 312: ... Bleed Air Panel 11 4A 11 3 Air Conditioning Distribution 11 5A 11 4 APU Control Panel 11 5A 11 5 Air Conditioning Airflow Schematic 11 7A 11 6 Ram Air Inlet 11 8A 11 7 Pressurization Control Panel 11 8A FOR TRAINING PURPOSES ONLY FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL ...

Page 313: ...ditioning is the high pressure compressors of the left and right engines The APU is an al ternate air source and provides heating and cooling of the occupied areas when the airplane is on the ground An approved external air upply can be connected to an adapter to pro vide air conditioning on the ground when the other air sources are not available Two independent air conditioning units ACUs are loc...

Page 314: ...comfortable humidity in the oc cupied areas The water removed from the air flow is sprayed onto the heat exchangers to increase their cooling effectiveness Ice pre vention at the water separator is achieved by a warm air bleed line that maintains the inlet nozzle temperature above the freezing point A pressure operated bypass is incorporated in the water separator in case of blockage TEMPERATURE C...

Page 315: ...ature range in this mode extends from a low of 2 C 35 F to a high of 99 C 210 F Frequent adjustment will be neces sary to maintain a comfortable temperature particularly when altitude or power settings are changing NOTE The manual mode is selected if 1 the normal and standby modes are in operative or 2 the crew wishes to make large and rapid temperature changes When this desired change is achieved...

Page 316: ... extinguish If a problem is caused by overtemperature in the ACU the affected ACU regulating and shutoff valve will close and only the ACU amber FAIL light will illuminate The engine bleed air valve and isolation valve if open will remain open To prevent damage to the ACU if the pressure regulating and shutoff valve fails to close when the ACU is deselected an ACU FAIL light will illuminate In eit...

Page 317: ...ately 50 psi FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL CL 601 3A 11 5 FOR TRAINING PURPOSES ONLY Figure 11 4 APU Control Panel RAM AIR EXHAUST RAM AIR SCOOP SIDE CONSOLE VENT FOOTWARMER DEMIST SIDE PANEL VENT INSTRUMENT COOLING UNDERFLOOR AVIONICS BAY LEFT ACU SUPPLIES COLD AIR FOR CABIN CONDITIONED AIR FOR CABIN AND COCKPIT RIGHT ACU SUPPLIES COLD AIR FOR CABIN AND COCKPIT CON...

Page 318: ...sor where a pressure and tem perature increase occurs Outflow from the ACU compressor is directed through the sec ondary heat exchanger where temperature is reduced but pressure is not This airflow is then directed through the expansion turbine where expansion and cooling occurs The air passes through the water separator and on to the tem perature control system Here mixing of hot air and cold air...

Page 319: ... SWITCH SB601 0141 TEMP SENSOR TEMP CONTROL VALVE TORQUE MOTORS LOW LIMIT VALVE WATER SEPARATOR ACU VALVE EJECTOR VALVE EJECTOR BLEED AIR MANIFOLD PRESSURE SWITCH TEMP SWITCH ASPIRATOR OVHT ANTICIPATOR SWITCH RAM AIR SERVO PRESSURE REGULATOR TURBINE COMPRESSOR DUCT SENSOR CONDITIONED AIR TO CABIN ELECTRICAL SERVO PRESSURE REGULATOR PRECOOLER PRIM HEAT EX TEMP CONTR PANEL SEC HEAT EX LOW LIMIT CONT...

Page 320: ...exchanger and 4 a normally closed ram air valve on the left conditioned air distribution duct CONTROL The ram air ventilation system is controlled by a guarded switchlight labeled RAM AIR VENT on the pressurization control panel Figure 11 7 Raising the guard and pushing the switch illuminates the white ON light and opens the ram air valve to allow ambient air to enter the occupied areas through th...

Page 321: ... CLOSED legend does not illu minate the problem is caused by A A faulty isolation valve B A left ACU overtemperature condition C The left temperature control valve is failed open D Overpressure in the left ACU 5 If the engines are not operating the APU has started the APU READY light is on and the APU fails to deliver air to the bleed air manifold when selected check that or A APU generator is on ...

Page 322: ... 2R TEMPERATURE CONTROL 11 2R General 11 2R Normal Mode 11 3R Standby Mode 11 3R Manual Mode 11 3R VALVES 11 3R General 11 3R Engine Bleed Air Valves 11 3R Isolation Valve 11 3R ACU Valves 11 4R DISTRIBUTION 11 4R OPERATION 11 5R General 11 5R Ground Operation 11 6R In Flight Operation 11 6R FOR TRAINING PURPOSES ONLY FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL ...

Page 323: ...RAM AIR VENTILATION 11 8R General 11 8R Control 11 8R QUESTIONS 11 9R FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL 11 ii CL 601 3R FOR TRAINING PURPOSES ONLY ...

Page 324: ... Bleed Air Panel 11 4R 11 3 Air Conditioning Distribution 11 5R 11 4 APU Control Panel 11 5R 11 5 Air Conditioning Airflow Schematic 11 7R 11 6 Ram Air Inlet 11 8R 11 7 Pressurization Control Panel 11 8R FOR TRAINING PURPOSES ONLY FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL ...

Page 325: ...ditioning is the high pressure compressors of the left and right engines The APU is an al ternate air source and provides heating and cooling of the occupied areas when the airplane is on the ground An approved external air supply can be connected to an adapter to pro vide air conditioning on the ground when the other air sources are not available Two independent air conditioning units ACUs are lo...

Page 326: ...moved from the air flow is sprayed onto the heat exchangers to increase their cooling effectiveness Ice pre vention at the water separator is achieved by a warm air bleed line that maintains the inlet nozzle temperature above the freezing point A pressure operated bypass is incorporated in the water separator in case of blockage A water extractor is also used to prevent ice for mation in the air c...

Page 327: ...e in this mode extends from a low of 2 C 35 F to a high of 99 C 210 F Frequent adjustment will be neces sary to maintain a comfortable temperature particularly when altitude or power settings are changing NOTE The manual mode is selected if 1 the normal and standby modes are in operative or 2 the crew wishes to make large and rapid temperature changes When this desired change is achieved the tempe...

Page 328: ...CLOSED light will illuminate for the affected engine BLEED AIR switchlight and the OPEN light for the ISOL switchlight will extinguish If a problem is caused by overtemperature in the ACU the affected ACU regulating and shutoff valve will close and only the ACU amber FAIL light will illuminate The engine bleed air valve and isolation valve if open will remain open To prevent damage to the ACU if t...

Page 329: ...tSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL CL 601 3R 11 5 FOR TRAINING PURPOSES ONLY Figure 11 4 APU Control Panel RAM AIR EXHAUST RAM AIR SCOOP SIDE CONSOLE VENT FOOTWARMER DEMIST SIDE PANEL VENT INSTRUMENT COOLING UNDERFLOOR AVIONICS BAY LEFT ACU SUPPLIES COLD AIR FOR CABIN CONDITIONED AIR FOR CABIN AND COCKPIT RIGHT ACU SUPPLIES COLD AIR FOR CABIN AND COCKPIT CONDITIONED AIR FOR C...

Page 330: ...am air intake through the precooler and heat exchangers From the precooler the flow will be through the primary heat exchanger and then to the ACU compressor where a pressure and temperature increase occurs Outflow from the ACU compressor is directed through the secondary heat exchanger where temper ature is reduced but pressure is not This air flow is then directed through a water extractor to th...

Page 331: ...COLD AIR TO CABIN ACU THERMAL SAFETY SWITCH SB601 0141 TEMP SENSOR TEMP CONTROL VALVE TORQUE MOTORS LOW LIMIT VALVE WATER SEPARATOR ACU VALVE BLEED AIR SWIRL FILTER EJECTOR VALVE EJECTOR BLEED AIR MANIFOLD PRESSURE SWITCH TEMP SWITCH ASPIRATOR OVHT ANTICIPATOR SWITCH RAM AIR SERVO PRESSURE REGULATOR TURBINE COMPRESSOR DUCT SENSOR CONDITIONED AIR TO CABIN ELECTRICAL PRECOOLER PRIM HEAT EX TEMP CONT...

Page 332: ...controlled by a guarded switchlight labeled RAM AIR VENT on the pressurization control panel Figure 11 7 Raising the guard and pushing the switch illuminates the white ON light and opens the ram air valve to allow ambient air to enter the occupied areas through the con ditioned air ducts if the cabin is unpressurized FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL 11 8 CL 601 3R FOR ...

Page 333: ...egend does not illu minate the problem is caused by A A faulty isolation valve B A left ACU overtemperature condition C The left temperature control valve is failed open D Overpressure in the left ACU 5 If the engines are not operating the APU has started the APU READY light is on and the APU fails to deliver air to the bleed air manifold when selected check that the A The APU generator is on B Th...

Page 334: ... Valves 12 3A Jet Pump 12 3A INDICATIONS 12 4A PROTECTION SYSTEMS 12 4A Normal Differential Control 12 4A Overpressure Limiter 12 4A Altitude Limiter 12 4A Negative Pressure Relief 12 5A Pneumatic Relay 12 5A ASSOCIATED SYSTEM GROUND MODE 12 5A Ground Operation Before Takeoff 12 5A Ground Operation Landing 12 5A FLIGHT MODE 12 6A FOR TRAINING PURPOSES ONLY FlightSafety CanadaLtée Ltd CL 600 2B16 P...

Page 335: ...neral 12 8A Air Source 12 8A Control 12 8A Operation 12 8A Cabin Altitude Control 12 8A EMERGENCY DEPRESSURIZATION 12 10A General 12 10A Control 12 10A QUESTIONS 12 11A FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL 12 ii CL 601 3A FOR TRAINING PURPOSES ONLY ...

Page 336: ... Cabin Altimeter Differential Rate Indicator 12 4A 12 3 Outflow Valve Typical 12 7A 12 4 Pressurization Profile 12 7A 12 5 Emergency Pressurization Schematic 12 9A 12 6 Footwarmer and Demist Controls 12 9A FOR TRAINING PURPOSES ONLY FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL ...

Page 337: ... greatly to passenger comfort GENERAL The fuselage of the Canadair Challenger is sealed from the bulkhead at the forward side of the cockpit to the bulkhead at the aft side of the toilet baggage area These are called the forward and aft pressure bulkheads respec tively The entire structure below the floor is also sealed as the underfloor area with the exception of the center wing section is also p...

Page 338: ... 10th stage bleed air manifold The bleed air from either engine is capable of providing all pressurization requirements if one engine is shut down or if other abnormalities occur See Chapter 9 Pneumatics and Chapter 11 Air Conditioning for bleed air operation The emergency source of air pressurization is the left engine s compressor This air source is available even if the left engine bleed air va...

Page 339: ...ed DECRease and INCRease OUTFLOW VALVES Two outflow valves are located on the rear pressure bulkhead to meter air from the oc cupied areas The left outflow valve is electropneumatic and operates in response to signals from the automatic selector when the MODE selector switch is in the AUTO position The right out flow valve is pneumatic and operates in re sponse to signals from the MANual REGulator...

Page 340: ...ystems incorporated in the pressurization system are Normal differential control Overpressure limiter maximum differ ential Altitude limiter Negative pressure relief NORMAL DIFFERENTIAL CONTROL The normal differential control is an auto matic function of the pressurization controller when operating in the AUTO mode Normal differential pressure for the controller is lim ited to 8 8 psid OVERPRESSUR...

Page 341: ...e automatic mode GROUND OPERATION BEFORE TAKEOFF The pressurization system may be programmed prior to engine starting if electrical power is available and the MODE selector switch is in the AUTOmatic position The cabin will not normally pressurize even if both air condi tioners are selected ON because the WOW weight on wheels system is in the ground mode and the automatic selector controls the lef...

Page 342: ...be necessary throughout the entire operation and especially during descent and before landing The UP DOWN lever is spring loaded to the center which is an off or closed position The lever controls two poppet valves In the DOWN position it opens one poppet valve to move the outflow valve toward the CLOSED position In the UP position it causes the out flow valve to move to a more open position The l...

Page 343: ...RE ALTITUDE LIMITER TO PNEUMATIC OUTFLOW VALVE TRUE STATIC PRESSURE OVERPRESSURE LIMITER CLOSING SPRING DIAPHRAGM CHAMBER Figure 12 3 Outflow Valve Typical 0 50 5 10 15 20 25 30 35 40 45 ALTITUDE X 1 000 RATE DOWN SCHEDULE SCHEDULE TAKEOFF 41 000 30 000 20 000 2 400 6 800 1 000 1 000 LAND AIRCRAFT CABIN 4 200 INCR FAULT LDG ALT X 1000 FT 8 1 2 7 3 6 4 5 10 30 31 29 28 0 9 1 BARO IN NG A B R Figure...

Page 344: ...cockpit and cabin conditioned air ducts The valves re quire pneumatic pressure to actually open The power supply for emergency pressuriza tion control is from the battery bus OPERATION Figure 12 5 illustrates operation of the emer gency pressurization system Notice that all normal bleed air valves are closed An air supply directly from the left engine is routed through the left footwarmer demist v...

Page 345: ...ED AIR PORTS EXT AIR PRESSURE XDUCER LH ACU VALVE PRESSURE XDUCER RH ACU VALVE LOAD CONTROL VALVE LCV RH 10TH STAGE BLEED AIR SOV 10TH STAGE BLEED AIR PORTS ISOL VALVE LH 10TH STAGE BLEED AIR SOV RH FOOT WARMER VALVE NORM LH ATS VALVE ATS APU PRESSURIZATION JET PUMP ATS RH ATS VALVE BLEED AIR COOLED AIR LEGEND RAM AIR RAM AIR EXHAUST LEFT ACU RIGHT ACU Figure 12 5 Emergency Pressurization Schemati...

Page 346: ...n the pressurization control panel Figure 12 1 la beled EMER DEPRESS When pushed an amber ON light in the switch will illuminate and battery bus voltage will be applied to the electro pneumatic left outflow valve Con trol pressure in both outflow valves will dis sipate rapidly Both outflow valves will open and the cabin will depressurize very rapidly At 13 000 500 feet the altitude limiter will ta...

Page 347: ...ergency pressurization is from A AC bus 2 B DC bus 1 C AC bus 1 D The battery bus 4 When the EMERgency DEPRESSuriza tion switchlight is pushed it will A Open the ram air valve and close the engine bleed air valves B Close the engine bleed air valves and both footwarmer and demist valves C Open the ram air valve and the emer gency pressurization valve D Opentheelectropneumaticoutflowvalve 5 During ...

Page 348: ... Valves 12 3R Jet Pump 12 3R INDICATIONS 12 4R PROTECTION SYSTEMS 12 5R Normal Differential Control 12 5R Overpressure Limiter 12 5R Altitude Limiter 12 5R Negative Pressure Relief 12 5R Pneumatic Relay 12 5R ASSOCIATED SYSTEM GROUND MODE 12 6R Ground Operation Before Takeoff 12 6R Ground Operation Landing 12 6R FLIGHT MODE 12 6R FOR TRAINING PURPOSES ONLY FlightSafety CanadaLtée Ltd CL 600 2B16 P...

Page 349: ...ual Mode 12 8R EMERGENCY DEPRESSURIZATION 12 8R General 12 8R Control 12 8R Cabin Altitude Control 12 8R QUESTIONS 12 9R FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL 12 ii CL 601 3R FOR TRAINING PURPOSES ONLY ...

Page 350: ...12 1 Pressurization Control Panel 12 2R 12 2 Cabin Altimeter Differential Rate Indicator 12 4R 12 3 Outflow Valve Typical 12 7R 12 4 Pressurization Profile 12 7R FOR TRAINING PURPOSES ONLY FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL ...

Page 351: ...omfort GENERAL The fuselage of the Canadair Challenger is sealed from the bulkhead at the forward side of the cockpit to the bulkhead at the aft side of the toilet baggage area These are called the forward and aft pressure bulkheads respec tively The entire structure below the floor is also sealed as the underfloor area with the exception of the center wing section is also pressurized Bulkheads ar...

Page 352: ...ation requirements if one engine is shut down or if other abnormalities occur See Chapter 9 Pneumatics and Chapter 11 Air Conditioning for bleed air opera tion MAJOR COMPONENTS The major components of the pressurization system are Automatic selector Manual regulator Outflow valves Jet pump AUTOMATIC SELECTOR The automatic cabin pressure selector Figure 12 1 is located on the overhead panel In the ...

Page 353: ...ead to meter air from the oc cupied areas The left outflow valve is electropneumatic and operates in response to signals from the automatic selector when the MODE selector switch is in the AUTO position The right out flow valve is pneumatic and operates in re sponse to signals from the MANual REGulator Both outflow valves however are pneumati cally interconnected Thus the right outflow valve is sl...

Page 354: ... needle is labeled PSI Both indicate on the same scale The cabin rate of change needle indicates on the left scale and the needle is not labeled An amber light labeled CABIN PRESS LOW on the pressurization control panel Figure 12 1 and Annunciator Panel Section is oper ated from an aneroid switch behind the panel The light will illuminate if the cabin altitude exceeds approximately 10 400 feet In ...

Page 355: ...asing cabin pressure and open the limit valve The outflow valve will close and limit the cabin altitude to approximately 13 000 500 feet NEGATIVE PRESSURE RELIEF A negative pressure relief feature is part of each outflow valve to prevent atmospheric pressure from exceeding cabin pressure In effect one side of each outflow valve di aphragm is exposed to atmospheric pressure while the opposite side ...

Page 356: ...liminate pressure surges after lift off Following lift off the WOW system will go to the flight mode and normal pressurization scheduling will begin GROUND OPERATION LANDING Normal pressurization scheduling for landing is field elevation minus 200 300 feet Therefore the airplane lands slightly pres surized When the WOW system goes to the ground mode the automatic selector sched ules outflow valve ...

Page 357: ...SING SPRING VACUUM LINE TO AIR JET PUMP OUTER DIAPHRAGM TRUE STATIC PRESSURE TO PNEUMATIC OUTFLOW VALVE DIAPHRAGM CHAMBER Figure 12 3 Outflow Valve Typical 0 50 5 10 15 20 25 30 35 40 45 ALTITUDE X 1 000 RATE DOWN SCHEDULE SCHEDULE TAKEOFF 41 000 30 000 20 000 2 400 6 800 1 000 1 000 LAND AIRCRAFT CABIN 4 200 INCR FAULT LDG ALT X 1000 FT 8 1 2 7 3 6 4 5 10 30 31 29 28 0 9 1 BARO IN NG A B R Figure...

Page 358: ...e same rate as the airplane and produce varying de grees of discomfort EMERGENCY DEPRESSURIZATION GENERAL An emergency depressurization system is available to provide rapid decompression of the airplane when an emergency such as air contamination cabin fire or failure of the maximum differential control occurs other situations may also require emer gency depressurization CONTROL The emergency depr...

Page 359: ...ial exceeds the normal limit it will be controlled by the A Overpressure limiter B Pneumatic relay C Altitude limiter D Negative pressure relief valve 3 When the EMERgency DEPRESSuriza tion switchlight is pushed it will A Open the ram air valve and close the engine bleed air valves B Close the engine bleed air valves and both footwarmer and demist valves C Open the ram air valve and the emer gency...

Page 360: ...on 13 2 HYDRAULIC SYSTEM NO 1 13 3 HYDRAULIC SYSTEM NO 2 13 4 HYDRAULIC SYSTEM NO 3 13 4 OPERATING CONDITIONS 13 7 Normal Conditions 13 7 Abnormal Conditions 13 7 Emergency Conditions 13 7 HYDRAULIC SUBSYSTEMS 13 8 QUESTIONS 13 10 FOR TRAINING PURPOSES ONLY FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL ...

Page 361: ...System Schematic 13 5 13 5 No 2 Hydraulic System 13 5 13 6 No 3 Hydraulic System Schematic 13 6 13 7 No 3 Hydraulic System 13 6 13 8 Hydraulic Pressure Generation and Distribution 13 9 TABLES Table Title Page 13 1 Pump Availability 13 7 13 2 Hydraulic Subsystem Chart 13 8 FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL CL 601 3A R 13 iii FOR TRAINING PURPOSES ONLY ...

Page 362: ... primary pump which is pilot controlled by a switch This pump is des ignated as hydraulic pump 3A There is no pilot control of the engine driven pumps except for a motor driven shutoff valve activated by the ENG FIRE PUSH switchlight The backup pumps are all AC electrical pumps and are pilot controlled by switches These pumps are designated as the hydraulic B pumps The hydraulic B pumps are operat...

Page 363: ...ing at the top of the control panel in Figure 13 1 the purpose and operation of the controls and indicators are as follows Pressure Indicators Indicate pressure in the systems Normal operating pres sure is 3 000 150 psi When electrical power is removed the pointers return to 0 psi Temperature Caution Lights Illuminate if fluid temperature in the reservoir exceeds 205 F 96 C ELECT PUMP Switches Pro...

Page 364: ...ock pit indication that bypassing has occurred If system pressure drops to 1 800 psi the amber L ENG PUMP caution light comes on to warn of low pressure If system fluid overheats the amber HI TEMP light illuminates This occurs at 205 F fluid temperature The electric hydraulic 1B pump can be oper ated by placing the NO 1 ELECT PUMP switch to ON providing a supplementary pres sure source for the sys...

Page 365: ...eing supplied by AC bus 1 System components located on the right side of the aft equipment bay are shown in Figure 13 5 HYDRAULIC SYSTEM NO 3 System No 3 is pressurized by two electric pumps 3A and 3B supplied with fluid from one reservoir Each pump operates when switched ON with the applicable ELECT PUMP switch Figure 13 6 The hydraulic 3B pump operates automatically and continually when the ADG ...

Page 366: ...OFF VALVE MOTOR DRIVEN RIGHT ENGINE DRIVEN PUMP ELECTRIC PUMP SWITCH CASE DRAIN FILTER FILTER NO 2 ACCUMULATOR HEAT EXCHANGER FAN PRESSURE RELIEF BLEED VALVE CASE DRAIN FILTER AC BUS 1 RESERVOIR PRESSURE SWITCH PRESSURE SWITCH PRESSURE RELIEF VALVE OFF ON RETURN FILTER AC PUMP 2B P P TO SYSTEMS ELECT PUMP R ENG PUMP HI TEMP RH ENG FIRE PUSH Figure 13 4 No 2 Hydraulic System Schematic Figure 13 5 N...

Page 367: ... PUMP SWITCH CASE DRAIN FILTER FILTER NO 3 ACCUMULATOR PRESSURE RELIEF BLEED VALVE CASE DRAIN FILTER AC BUS 1 RESERVOIR PRESSURE SWITCH PRESSURE SWITCH PRESSURE RELIEF VALVE AIR DRIVEN GENERATOR OFF ON RETURN FILTER AC PUMP 3B P P TO SYSTEMS ELECT PUMP ELECT PUMP HI TEMP ELECTRICAL PUMP PRESSURE SUCTION RETURN NITROGEN Figure 13 6 No 3 Hydraulic System Schematic Figure 13 7 No 3 Hydraulic System ...

Page 368: ... complete electrical power failure occurs on both AC bus 1 and AC bus 2 and the auxiliary power unit APU is not operating the ADG will automatically deploy and provide power for operation of the 3B pump in the No 3 hydraulic system The pump provides sufficient pressure for operation of the landing gear inboard wheel brakes and primary flight controls NOTE A listing of pump availability ac cording ...

Page 369: ...aulic system FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL 13 8 CL 601 3A R FOR TRAINING PURPOSES ONLY SYSTEM 1 SYSTEM 3 SYSTEM 2 LANDING GEAR Normal Extension Normal Retraction LANDING GEAR Downlock Assist FLIGHT SPOILERS BRAKES Outboard BRAKES Inboard FLIGHT CONTROLS One Elevator PCU One Aileron PCU One Rudder PCU FLIGHT CONTROLS One Elevator PCU One Aileron PCU One Rudder PCU FL...

Page 370: ...aLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL CL 601 3A R 13 9 FOR TRAINING PURPOSES ONLY HYDRAULIC SYSTEM NO 1 HYDRAULIC SYSTEM NO 2 HYDRAULIC SYSTEM NO 3 LEGEND Figure 13 8 Hydraulic Pressure Generation and Distribution ...

Page 371: ...UMP switch D When the ADG is deployed and the NO 3 ELECT PUMP switch is placed on 5 Fluid filtration occurs A Only in the pressure system B Only in the return system C Only in the bypass system D In the pressure system the return sys tem and the case drain system 6 If the left generator fails in flight B pump s A In the No 2 system will be inoperative B In the No 1 system will be inoperative C In ...

Page 372: ...ear 14 4 Nose Landing Gear 14 5 Controls and Indicators 14 6 Operation 14 7 NOSEWHEEL STEERING 14 8 General 14 8 Operation 14 8 BRAKES 14 10 General 14 10 Antiskid System 14 11 Brake Operation With Antiskid 14 12 Brake Operation Without Antiskid 14 12 Parking Brakes 14 12 QUESTIONS 14 15 FOR TRAINING PURPOSES ONLY FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL ...

Page 373: ...Gear Doors 14 5 14 8 Landing Gear Control Panel 14 6 14 9 Landing Gear Position Indicator Lights 14 6 14 10 Landing Gear Emergency Extension System 14 9 14 11 Nosewheel Steering Controls 14 10 14 12 Brake Pressure Indicator 14 10 14 13 Measurement of Brake Wear 14 11 14 14 Antiskid System Test 14 12 14 15 Brake System Schematic 14 13 14 16 Parking Brake System 14 14 FOR TRAINING PURPOSES ONLY Flig...

Page 374: ...re through an antiskid system GENERAL Each inward retracting main landing gear uses hydraulic actuators to release the uplocks to extend and retract the landing gear and to disengage the downlocks There is also an ac tuator to assist downlocking during emergency extension The forward retracting nose landing gear also uses hydraulic actuators to release the up locks to extend and retract the nose g...

Page 375: ...ator for reserve pressure in the event of hydraulic system failure An an tiskid system provides optimum braking under all runway conditions LANDING GEAR GENERAL Positioning the cockpit landing gear handle en ergizes solenoid operated selector valves that route hydraulic pressure to open or close the for ward nose gear doors release the uplocks and the downlocks and extend or retract the gear The m...

Page 376: ...nd spoilers Electrical system Air conditioning Cabin pressurization Autopilot Antiskid Intercom Engine Cockpit heat Stall protection test Nosewheel steering Comparator circuitry illuminates the amber WOW I P FAIL light beneath the landing gear control panel Figure 14 3 if a disagreement exists between the WOW proximity switches A 10 to 15 second delay prevents the light from illuminating during a ...

Page 377: ...an be unlocked only with hydraulic pressure on the retract side of the actuator A mechanical uplock engages the gear at retraction it is hydraulically unlocked for gear extension Main Landing Gear Doors When retracted each main gear is partially en closed by a door that is mechanically linked to the main landing gear and actuated by gear movement Figure 14 5 FlightSafety CanadaLtée Ltd CL 600 2B16...

Page 378: ...gaged Nose Landing Gear Doors When retracted the nose gear is enclosed by two forward doors and a rear door Figure 14 7 The forward doors are hydraulically actuated and are closed except when the nose landing gear is in transit On the ground the left forward door can be opened for inspection with a manual re lease lever The rear door is mechanically con nected to the nose landing gear and is close...

Page 379: ...ts above the LDG GEAR control panel indicates landing gear down and locked Figure 14 9 Flashing red lights in the landing gear handle indicate that the landing gear is in transit With the landing gear down and locked the three green position indicator lights will be illuminated and the red handle lights will be extinguished When the gear is up and locked none of these lights are illuminated Flight...

Page 380: ...e muted OPERATION Normal Retraction Moving the landing gear handle to the UP po sition energizes a selector valve to direct No 3 hydraulic system pressure for landing gear retraction The retract sequence of events is as follows The red landing gear handle lights flash The forward nose landing gear doors hydraulically open and the red NOSE DOOR OPEN light illuminates All three landing gear downlock...

Page 381: ...is assured by downlock assist springs see Figure 14 6 When the landing gear is safely down the three green lights will illuminate The nose doors remain open The system linkage is held in the emergency operating position by a ratchet in the LG PULL handle To reset the system press the button on the handle and slowly return it to the stowed position This allows springs to reset the com ponents in th...

Page 382: ...ES ONLY MAIN GEAR DOWNLOCK ASSIST ACTUATORS NO 2 SYSTEM PRESSURE RETURN LEGEND DUMP VALVE FROM GEAR ACTUATORS AND NOSE DOOR ACTUATOR DOWNLOCK ASSIST SELECTOR VALVE NOSE DOOR RELEASE MECHANISM NOSE UPLOCK LEFT MAIN UPLOCK RIGHT MAIN UPLOCK PULL L G Figure 14 10 Landing Gear Emergency Extension System ...

Page 383: ...made BRAKES GENERAL The brakes can be applied by either pilot The system has four multiple disc self adjusting brake assemblies one in each main landing gear wheel Fusible plugs in each main land ing gear wheel prevent fire blowout caused by excessive heat that may result from hard brak ing Outboard brakes are powered by No 2 hy draulic system pressure inboard brakes by the No 3 system A nitrogen ...

Page 384: ...ion pressure again increases at a controlled rate This cycle action may occur as often as 10 times per second depending on runway conditions and brake application by the pilot Touchdown protection is provided to prevent brake application by either pilot prior to touch down When airborne the WOW system en ergizes the antiskid valves dumping braking pressure At touchdown wheel spinup above 35 knots ...

Page 385: ... be set with the PARK ING BRAKE handle Figure 14 16 Fully depress either set of pedals pull the handle and rotate it 90 counter clockwise This mechanically latches the brake metering valves in the open position allowing avail able hydraulic pressure to be applied to the brake assemblies It also closes the return line shutoff valve to prevent the No 3 inboard system antiskid valve leakage from blee...

Page 386: ...KID VALVE ANTI SKID VALVE ANTI SKID VALVE L R L COPILOT S BRAKE PEDALS PILOT S BRAKE PEDALS PARKING SHUTOFF VALVE ACCUMULATOR ACCUMULATOR FUSE FUSE LEFT OUTBOARD BRAKE LEFT INBOARD BRAKE FUSE FUSE RIGHT OUTBOARD BRAKE RIGHT INBOARD BRAKE R HYDRAULIC SYSTEM NO 3 PRESSURE HYDRAULIC SYSTEM NO 2 PRESSURE RETURN LEGEND NITROGEN PRESSURE ELECTRICAL MECHANICAL Figure 14 15 Brake System Schematic ...

Page 387: ...FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL 14 14 CL 601 3A R FOR TRAINING PURPOSES ONLY PARKING BRAKE N W STEER FAIL Figure 14 16 Parking Brake System ...

Page 388: ...ven past 55 the disengaged rack and pinion should be A Reengaged hydraulically B Reengaged without hydraulic power C Disconnected and the nosewheels centered D None of the above 6 Brake pressure is provided by A Both the No 1 and No 3 hydraulic systems B Both the No 1 and No 2 hydraulic systems C Both the No 2 and No 3 hydraulic systems D The No 3 hydraulic system only 7 The brake antiskid system ...

Page 389: ...5 3 Yaw Control System 15 7 Pitch Control System 15 8 Stabilizer Trim 15 9 LIFT MODULATION SYSTEMS 15 10 General 15 10 Flight Spoilers 15 10 Ground Spoilers 15 11 Flaps 15 12 STALL PROTECTION SYSTEM 15 15 General 15 15 Operation 15 16 Testing 15 16 QUESTIONS 15 17 FOR TRAINING PURPOSES ONLY FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL ...

Page 390: ...sition Indicators 15 6 15 6 Servo Monitor Panel 15 6 15 7 Rudder Jam Breakout System 15 6 15 8 Jam Breakout Mechanism 15 7 15 9 Pitch Disconnect 15 8 15 10 Stabilizer Trim System 15 9 15 11 Flight Spoilers and Ground Spoilers Systems 15 11 15 12 Wing Flaps 15 13 15 13 Flaps Controls and Indicators 15 13 15 14 Flap Diagram 15 14 15 15 Stall Protection System 15 15 FOR TRAINING PURPOSES ONLY FlightS...

Page 391: ...s electrically actuated There are no trim tabs on any control surface Trimming is accomplished by varying the loads on the mechanical linkages between the pilot and the control surface A lift modulation system consists of electrically actuated flaps and hydraulically pow ered flight and ground spoilers A stall protection system warns of impending stalls by visual aural and tactile means If no pilo...

Page 392: ...drives all flap segments A proportional flight spoiler on the upper sur face of each wing forward of the outboard flaps provides lift modulation Hydraulic ac tuation of the spoilers is initiated by inputs from a control lever in the cockpit Hydraulically powered ground spoilers for ward of the inboard flaps provide lift dump during the landing roll The ground spoilers are operable only when the we...

Page 393: ... mechanisms that allow both the pilot and the copilot to retain control of the rudder Proximity sensors in the aileron and rudder PCU s detect jammed control valves or loss of hydraulic pressure Elevator PCU sensors de tect jammed control valves only In the event of a control valve jam or loss of hydraulic pressure to a PCU the flight surface remains operative through the other PCU s Since hydraul...

Page 394: ...ere with the normal movement of an operating PCU Aileron load feel is provided by an artificial feel unit Figure 15 3 that forms part of the aft quadrant A spring loaded roller is held into a cam fixed to the aft quadrant Movement of the quadrant and cam causes the roller to ride up the cam Since the cam is fixed to the quad rant quadrant movement is opposed by the spring force which attempts to r...

Page 395: ... the left aileron PCU s and No 2 and No 3 systems pressures to the right aileron PCU s Loss of any one hydraulic system powering the ailerons will not degrade control authority As the ailerons deflect a followup linkage repositions the control valves to neutral stopping and holding the ailerons in the selected position Actual aileron position is constantly displayed on the flight surface position ...

Page 396: ...NLY SEE FIGURE 15 8 CROSS COUPLING RUDDER PEDAL ADJUSTMENT JAM BREAKOUT MECHANISM Figure 15 7 Rudder Jam Breakout System RUDDER L R L R L S U R F A C E R ELEVATOR AILERON FLT SPLR Figure 15 5 Flight Control Surface Position Indicators PITCH YAW ROLL SERVO MONITOR MON SAFE Figure 15 6 Servo Monitor Panel ...

Page 397: ...l linkages is overcome by a breakout mechanism in each linkage If either linkage jams additional rudder pedal force actuated from the jammed or non jammed side will cause the breakout mechanism to adjust the bell crank pivot point on the jammed side This allows full rudder control input through the side that is not jammed The breakout sys tem is shown in Figure 15 7 and the breakout mechanism in F...

Page 398: ...ol valves on the rudder PCUs PCU actuation then deflects the surface as required The amount of trim ap plied is shown on the TRIM position indicator PITCH CONTROL SYSTEM General Two independent hydraulically powered el evators mechanically controlled by control column fore and aft movement provide pitch control Each elevator is powered by two PCUs Elevator travel is limited by PCU travel and mecha...

Page 399: ...e and motor drive direction The two channels of operation are powered by separate buses to prevent loss of trim capability in the event of failure of one bus Automatic as well as pilot transfer of channels is provided Trim commands originate at the trim switch on either the pilot s or copilot s control wheel the autopilot or the Mach trim system Operation To arm the pitch trim system press the CHA...

Page 400: ...nd WOW or wheel spinup occurs The slotted flaps consisting of four panels are actuated by two electric motors driving flexible shafts Airflow is directed over the flaps by fixed and variable position vanes FLIGHT SPOILERS General The flight spoiler on each wing is powered by two PCU s one by the No 1 hydraulic system the other by the No 2 hydraulic system The FLIGHT SPOILER lever on the center ped...

Page 401: ...re hydraulically released for spoiler exten sion Spoiler operation is controlled by a switch on the center pedestal The spoilers are operative only on the ground and have two operating positions retracted and fully ex tended 45 Operation The ground spoilers are armed for operation by the GROUND SPOILER switch which re mains in the OFF position until armed for takeoff Figure 15 11 except for test F...

Page 402: ...SPLR lights extinguish Place the switch momentarily in the OFF position then in the ON position Check that all ground spoiler system lights are extinguished FLAPS General The flap system consists of two inboard and two outboard flaps The inboard flaps have movable flap vanes that automatically extend or retract as the flaps are actuated The out board flaps have fixed vanes When the flaps are exten...

Page 403: ...00 2B16 PILOT TRAINING MANUAL CL 601 3A R 15 13 FOR TRAINING PURPOSES ONLY Figure 15 12 Wing Flaps UP FLAPS FAIL OVHT MOT 1 OVHT MOT 2 DN 40 30 20 10 10 FLAPS DEG 0 0 20 20 30 30 45 45 FLAPS Figure 15 13 Flaps Controls and Indicators ...

Page 404: ...motors are de energized and the brakes on the shafts and on both motors are engaged holding the flaps in position If an asymmetrical condition develops during flap operation rpm detectors on the outboard shafts signal the flap control unit to de energize the motors engage the brakes and illuminate the amber FLAPS FAIL light This will be accompanied by a flight control annunciator and flashing MAST...

Page 405: ...respective stall channel circuit breakers The signal from one of the transducers is routed through the pilot s stall protection test switch Actuation of the switch inter rupts the altitude signal causing a disagree ment that illuminates the ALT COMP FAIL lights Figure 15 15 SPS TEST INDICATOR PROVIDES REFERENCE FOR ALL STALL WARNING STICK PUSHER SEQUENCE BUT IS NOT CALIBRATED TO PROVIDE AOA INDICA...

Page 406: ...ngaged by press ing the AP SP switch on either control wheel When AOA decreases the stick pusher stick shaker and continuous ignition functions cease as their actuation points are passed FAA certificated airplanes incorporate ac celerometer actuated switches that disengage the stick pusher if the airplane reaches 0 5 g preventing entrance into negative g flight TESTING To test the stall protection...

Page 407: ... surface cannot be actuated B The surface is actuated by the re maining PCU C The surface will actuate at half speed D Surface travel is reduced 5 Travel of the primary flight controls is limited by A PCU travel only B Mechanical stops only C Mechanical stops and PCU travel D Airspeed and mechanical stops 6 Stabilizer trim is achieved by A An electric actuator that positions the elevator PCU s B V...

Page 408: ... VHF Navigation 16 12 Distance Measuring Equipment 16 15 Automatic Direction Finder 16 16 Digital Clocks 16 17 Normal EFIS Displays 16 18 EFIS Failure Displays 16 19 DIGITAL AUTOMATIC FLIGHT CONTROL SYSTEM 16 20 Inertial Reference System 16 21 Air Data System 16 27 Electronic Flight Instrument System 16 37 Multifunction Display 16 53 CL 601 3A R 16 i FOR TRAINING PURPOSES ONLY FlightSafety CanadaL...

Page 409: ...TRAINING PURPOSES ONLY Flight Management System 16 58 Flight Guidance System 16 61 Weather Radar System 16 76 Radio Altimeter System 16 80 Avionics Cooling 16 80 FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL ...

Page 410: ...ystem Antennas 16 11 16 11 Navigation System Cockpit Controls 16 12 16 12 VHF NAV Control Unit 16 13 16 13 VHF NAV EFIS Displays 16 14 16 14 DME EHSI Displays 16 15 16 15 ADF Control Unit and EHSI Display 16 16 16 16 Digital Clock 16 17 16 17 Normal EFIS Displays 16 18 16 18 EFIS Failure Displays 16 19 16 19 ASCB Interface 16 20 16 20 IRS Data Flow 16 21 16 21 Mode Select Unit Align and NAV Modes ...

Page 411: ...6 36 16 34 EFIS Components 16 37 16 35 EADI Normal Annunciations 16 38 16 36 EADI Reversion 16 39 16 37 EADI Comparison Monitoring Data Flow 16 40 16 38 EADI Comparison Monitoring 16 41 16 39 EADI Warning and Failure Displays 16 42 16 40 EHSI Full Compass Mode 16 43 16 41 EHSI Arc Mode 16 44 16 42 EHSI Weather Radar and MAP Modes 16 45 16 43 EHSI Reversion Mode 16 46 16 44 EHSI Comparison Monitori...

Page 412: ...ce Controller Vertical Mode Functions 16 65 16 61 Flight Guidance Controller Basic Functions 16 66 16 62 Turn and Pitch Controller 16 68 16 63 Advisory Display 16 69 16 64 Control Wheel Switches 16 72 16 65 Flight Director Couple Arrows 16 73 16 66 Flight Director Command Bars 16 74 16 67 Weather Radar Components 16 76 16 68 Weather Radar Controller 16 78 16 69 Radio Altimeter Display 16 80 16 70 ...

Page 413: ...ic Flight Control System DAFCS consists of the following systems Dual flight director FD Dual autopilot AP CL 601 3A R 16 1 CHAPTER 16 AVIONICS INTRODUCTION The standard factory installed Canadair Challenger CL 600 2B16 model CL 601 3A R avionics package includes communications systems electronic flight instrument sys tems a digital automatic flight control system DAFCS and navigation systems The ...

Page 414: ...mitters for operation and independent position determining systems IPDS which operate independently of ground equipment The basic DPDS on the Challenger include VHF navigation VOR and ILS marker bea con automatic direction finder ADF dis tance measuring equipment DME and ATC transponders The IPDS consist of a weather radar radio altimeter and inertial reference systems 16 2 CL 601 3A R FOR TRAININ...

Page 415: ...V 1 2 1 2 1 2 OFF 1 2 1 2 DME SPKR 1 2 MIC VOL HOT OXY HF 1HF 2 INPH 1 2 MIC OFF BOOM MKR ADF SPKR PHONE HF VHF NAV 1 2 1 2 1 2 OFF 1 2 1 2 DME SPKR 1 2 MIC VOL HOT OXY HF 1HF 2 INPH 1 2 MIC OFF BOOM COCKPIT VOICE RECORDER TEST HEADSET 600 OHMS ERASE GOO D 6 8 4 2 0 1 0 H F MODE FREQ CHAN OPR VOL DSBL SQL CHAN PWR FREQ LD CURSOR VALUE H F MODE FREQ CHAN OPR VOL DSBL SQL CHAN PWR FREQ LD CURSOR VAL...

Page 416: ... DIAGNOSTIC MESSAGES AND MEMORY CHANNEL FREQUENCIES MEM ANNUNCIATOR INDICATES WHEN A STORED FREQUENCY IS DISPLAYED IN THE LOWER DISPLAY VOLUME CONTROL CONTROLS THE RECEIVER AUDIO LEVEL MODE SELECTOR ON AND OFF POSITIONS SWITCH SYSTEM POWER SQ OFF POSITION DISABLES THE RECEIVER SQUELCH AUTOMATIC DISPLAY DIMMER SENSOR AUTOMATICALLY CONTROLS THE DISPLAY BRIGHTNESS ACTIVE FREQUENCY DISPLAY DISPLAYS TH...

Page 417: ...modes provide preset fre quencies for emergency use A test mode provides a self test of the HF system CL 601 3A R 16 5 FOR TRAINING PURPOSES ONLY FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL H F MODE FREQ CHAN OPR VOL DSBL SQL CHAN PWR FREQ LD CURSOR VALUE MODE DISPLAY DISPLAYS THE TYPE OF RF MODE SELECTED BY THE VALUE CONTROL OPR DISPLAY DISPLAYS THE OPERATING MODES OR CONIDITION...

Page 418: ...ination alert the flight crew of a ground station position report request The flight crew depresses the PRESS TO RESET switchlight to extinguish the light and reset the circuit Placing the SELCAL OFF TEST switch to TEST initiates a test of the SELCAL chime and annunciators 16 6 CL 601 3A R FOR TRAINING PURPOSES ONLY FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL SELCAL CONTROL PANEL...

Page 419: ...llowing VHF navigation VHF NAV 1 and 2 Marker beacon MKR 1 and 2 Automatic direction finder ADF 1 and 2 Distance measuring equipment DME 1 and 2 The audio control units provide transmission and listening capabilities for the following VHF 1 and 2 communications HF 1 and 2 communications The audio control units Figure 16 7 allow use from either the headsets or oxygen masks The units also provide ho...

Page 420: ...nnels in the audio electronics unit In this mode the pilot s or copilot s microphone and PTT switch bypasses the audio electronics unit and con nect directly to the associated VHF radio The VHF COM and NAV audio and from the aural warning system connect directly to the pilot s and copilot s headphone and boom MIC 16 8 CL 601 3A R FOR TRAINING PURPOSES ONLY FlightSafety CanadaLtée Ltd CL 600 2B16 P...

Page 421: ...es using the code selector knobs The control unit fea tures an IDENT pushbutton that flashes aircraft information when pressed A test pushbutton initiates a self test of the transponder system CL 601 3A R 16 9 FOR TRAINING PURPOSES ONLY FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL 2 ATC TX Collins A C T 1 IDENT TEST PRE ALT STBY OFF ON MODE SELECTOR OFF REMOVES POWER FROM THE TRAN...

Page 422: ...ng device contains a beacon that trans mits on an ultrasonic frequency when in con tact with water The CVR is tested before flight by pressing the TEST switch and visually observing meter deflections four times into the green band on the CVR test meter 16 10 CL 601 3A R FOR TRAINING PURPOSES ONLY FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL COCKPIT VOICE RECORDER TEST HEADSET 600 ...

Page 423: ...Figure 16 11 shows the location of the cockpit controls Associated controls and displays for the nav igation system consist of the following Normal EFIS displays EFIS failure displays Digital clocks CL 601 3A R 16 11 FOR TRAINING PURPOSES ONLY FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL RADAR 12 INCH FLAT PLATE RADIATOR GLIDE SLOPE VOR LOC ANTENNA ADF LOOP VHF 1 VHF 2 TRANSPONDER...

Page 424: ...A R FOR TRAINING PURPOSES ONLY FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL MEM NAV MEM RMT HLD Collins A C T XFR STO TEST ACT HLD OFF ON V MEM ADF MEM Collins A C T XFR STO TEST ACT TONE ANT OFF ADF V MEM NAV MEM RMT HLD Collins A C T XFR STO TEST ACT HLD OFF ON V MEM ADF MEM Collins A C T XFR STO TEST ACT TONE ANT OFF ADF V ADF 2 ADF 1 DISPLAY CONTROLLER VOR LOC DISPLAYS MKR BEA...

Page 425: ...Y IS CHANGED STAYS ON FLASHING IF THE TUNING IS INCORRECT MEMORY ANNUNCIATOR COMES ON WHEN A PRESET FREQUENCY IS SHOWN IN THE PRESET FREQUENCY DISPLAY RMT ANNUNCIATOR COMES ON WHILE THE DME IS REMOTELY TUNED BY THE FMS POWER AND MODE SELECTOR OFF REMOVES POWER FROM THE DME AND VOR SYSTEMS ON APPLIES POWER TO THE DME AND VOR SYSTEMS HLD HOLDS THE DME ON THE SELECTED FREQUENCY WHILE THE VHF NAV FREQ...

Page 426: ...PLAY IS YELLOW COURSE PRESELECT SOURCE ANNUNCIATOR INDICATES THE SOURCE OF THE COURSE PRE SELECTED INFORMATION DISPLAY IN MAGENTA NO 1 BEARING POINTER INDICATES THE BEARING TO THE SOURCE SELECTED BY THE BRG O CONTROL DISPLAYED IN CYAN BEARING SOURCE ANNUNCIATORS INDICATES THE SELECTED BEARING SOURCE FOR THE ASSOCIATED BEARING POINTER A ADF F FMS V VOR THE COLOR OF THE BEARING SOURCE ANNUNCIATORS C...

Page 427: ...avaid contains a paired DME frequency The VHF control unit pro vides manual frequency selection and the FMS provides automatic frequency selection The DME consists of two transmitter receivers and two antennas The transmitter receiver transmits in the 1025 to 1150 MHz and re ceives in the 962 to 1213 MHz The reception frequency band is designated as x and y chan nels from 1 to 126 The transmitter ...

Page 428: ...RANSFERS ACTIVE AND PRESET FREQUENCIES OR SELECTS PRESET FREQUENCY FOR DISPLAY FREQUENCY SELECTORS SELECTS PRESET AND ACTIVE FREQUENCIES ACTIVE PUSHBUTTON ALLOW FREQUENCY SELECTORS TO DIRECTLY TUNE ADF RECEIVER STO PUSHBUTTON ALLOWS FREQUENCIES TO BE SELECTED AND STORED IN MEMORY TEST PUSHBUTTON INITIATES A SELF TEST ROUTINE AUTUNATIC DISPLAY DIMMER SENSOR AUTOMATICALLY CONTROLS THE DISPLAY BRIGHT...

Page 429: ...DAVTRON RUN E T F T TIME SET UP D B 1hr up PRESS TO RESET PRESS TO RESET PUSHBUTTON ALLOWS FLIGHT TIME RECORDER TO BE RESET TO ZERO WITHOUT TURNING OFF AIRCRAFT ELECTRICAL POWER SET SWITCH UP ADVANCES CLOCK ONE SECOND FOR EACH SECOND HELD D RETARDS CLOCK ONE SECOND FOR EACH SECOND HELD BRIGHT DIM SWITCH B BRIGHTENS DISPLAY DIM DIMS DISPLAY 1 HR UP ADVANCES TIME ONE HOUR WHEN HELD AND RELEASED TIME...

Page 430: ...display using the navigation radios 16 18 CL 601 3A R FOR TRAINING PURPOSES ONLY FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL EADI EHSI HDG VOR ALT AP KIAS M 594 59 280 260 250 240 220 ASEL 24000 20 20 10 10 20 20 10 10 MAG DME 20 0 SRP CRS 110 GSPD 337 HDG 076 V O R 1 V N 3 6 E 12 1 5 S 2 1 2 4 W 3 0 3 3 Figure 16 17 Normal EFIS Displays ...

Page 431: ...ach of the specific failure messages CL 601 3A R 16 19 FOR TRAINING PURPOSES ONLY FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL EADI EHSI MAG DME 20 0 SRP CRS 110 GSPD 337 HDG 076 V O R 1 V N 3 6 E 12 1 5 S 2 1 2 4 W 3 0 3 3 SG FD CAT2 XDTA G S I A S RA ASEL LOC TEST IRS Figure 16 18 EFIS Failure Displays ...

Page 432: ... FGC generate auto matic flight path commands and use attitude and direction from the IRS and FMS air data from the DADC and displays from the EFIS and MFD for aircraft autopilot control The au topilot and associated functions provide sta bilization and control needed to ensure the best performance throughout the aircraft flight profile An avionics standard communications bus ASCB provides the com...

Page 433: ...ATT NO AIR NAV RDY FAULT ALIGN Honeywell LASEREF 1 3 N 2 0 H 5 W 4 E 6 7 9 S 8 SYS DSPL DSPL SEL 2 1 OFF TEST TK GS PPOS HDG STS WIND 3 B R T ENT CLR HDG VOR ALT AP KIAS M 594 59 280 260 250 240 220 ASEL M VTA M 24000 910 DH200 20 20 10 10 20 20 10 10 DH MAG T H FMS 180 SALON 35 DTK 350 TTG 34 5 HDG 340 F M S 1 L O C 1 F V N 3 6 E 12 15 S 21 24 W 30 33 MAG 95 0 040 FMS1 STBY TGT MANZY ETA 1736 DIS...

Page 434: ...Y FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL NAV ALIGN OFF ATT TEST Honeywell LASEREF NAV RDY ALIGN MODE SELECT SWITCH SELECTS THE FOUR BASIC MODES AND THE FOUR SUBMODES NAV POSITION IS DETENTED OFF TURNS OFF THE IRS ALIGN TURNS THE IRS ON AND SELECTS THE ALIGN MODE TO COMPLETE THE ALIGN MODE THE INITIAL POSITION LATITUDE AND LONGITUDE MUST BE ENTERED INTO THE IRS EITHER FROM TH...

Page 435: ...ting an airport identifier waypoint Prior to entering the NAV mode the ALIGN mode accepts any changes to the initialization data without delaying the align ment time The IRS will not complete align ment if the aircraft is moved Make sure that the aircraft is stationary during alignment The ALIGN annunciator flashes and the FAULT annunciator illuminates if the system detects an incorrect aircraft p...

Page 436: ...24 second internal IRS self test that provides three sets of test values The test mode oper ates in the ALGN or NAV mode without af fecting basic IRS functions Groundspeed greater than 20 knots or mode select switch in the ATT position prevents test mode operation 16 24 CL 601 3A R FOR TRAINING PURPOSES ONLY FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL NAV ALIGN OFF ATT TEST Honey...

Page 437: ...S navigation capability by allowing a direct interface between the NDU and each IRS The NDU provides a left right course deviation display either on a stand alone unit or the EFIS EHSI CL 601 3A R 16 25 FOR TRAINING PURPOSES ONLY FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL Honeywell LASERTRAK FAULT ON SYSTEM SELECT TO WPT FROM 1 3 N 2 ENT BCK 0 CLR 5 W 4 E 6 7 9 S 8 BRT DIM M T T...

Page 438: ... PLUG PLUG PLUG SPS NO 1 ALTITUDE TRANSDUCER PILOT S STALL STATIC PRESSURE SELECTOR SALVE COPILOT S STALL STATIC PRESSURE SELECTOR SALVE S P NO 1 DADC STATIC PORT S3 STATIC PORT S3 CABIN DIFFERENTIAL PRESSURE INDICATOR COPILOT S SIDE PANEL CENTER INSTRUMENT PANEL COPILOT S STATIC TUBE SELECTOR VALVE PILOT S STATIC TUBE SELECTOR VALVE STANDBY ASI STANDBY ALT P S NO 2 DADC PILOT S PITOT P1 COPILOT S...

Page 439: ...panel The TAT sensor probe provides temperature sensing for the DADCs The air data system ADS heater control panel con trols the ADS anti icing Pitot static Heads Both pitot static heads Figure 16 25 con sist of three pressure sensors within a probe Ram air pressure sensors correspond to the pilot side as P1 and the copilot side as P2 Two static pressure sensors S1 and S2 cor respond to both pitot...

Page 440: ...atic source selected on the associated STATIC PRESSURE selector valve is provided to the stall transducer Setting a STALL PROTECT selector valve to CLOSED shuts off the selected static source to the stall transducer 16 28 CL 601 3A R FOR TRAINING PURPOSES ONLY FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL STATIC PRESSURE STATIC TUBE SELECTOR VALVE ALTERNATE SOURCE STATIC NORMAL STA...

Page 441: ...mperature SAT and TAT readouts displayed on the advisory dis play The CPL selection on the flight guidance controller determines which DADC is pro viding the SAT TAT indications Air Data System The pitot static system inputs information into the air data system DADCs The DADCs provide the flight guidance computers with altitude hold airspeed vertical speed and Mach number control functions CL 601 ...

Page 442: ...d air data indicators The ADS consists of the following TAS SAT TAT indications Mach airspeed indicator Altimeter Vertical speed indicator NOTE The DADC self test mode is selected by placing the DAFCS ground main tenance test switch to the ON posi tion and then pressing the LAFCS button on the advisory display nine times to select the 21 DADC test menu Then press the reset button to begin the test...

Page 443: ...VMO on an orange background Failures de tected in the IAS primary power airspeed data input or low voltage displays the black OFF flag on an orange background Altimeter The altimeter Figure 16 29 provides a ser voed counter drum pointer display of baro metrically corrected pressure altitude The BARO knob manually controls the barometric pressure in inches of mercury and millibars on baro counters ...

Page 444: ... the failure warning OFF flag The failure warn ing flag appears during loss of 26 VAC ES SENTIAL BUS Standby Flight Instruments The standby pneumatic flight instruments con sists of the following Standby airspeed indicator Standby barometric altimeter 16 32 CL 601 3A R FOR TRAINING PURPOSES ONLY FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL BA 141 ALTIMETER VS 200 VERTICAL SPEED IN...

Page 445: ...ge connected to a differential pressure capsule that responds to changes in pitot pressure Standby Barometric Altimeter The standby altimeter Figure 16 31 receives static pressure from S2 or S3 if the copilot has selected the alternate static source The standby barometric altimeter provides alti tude displays and is provided with a baro metric setting knob Altitude is displayed by a pointer and a ...

Page 446: ...ntained standby horizon indicator provides visual pitch and roll aircraft attitude information Figure 16 31 The indicator contains an electrically driven gyro A me chanical erection system maintains the verti cal attitude The indicator provides continued attitude information for a minimum of nine minutes after a loss of all electrical power With DC power available 28 VDC for the standby horizon in...

Page 447: ...al The 28 VDC integral lighting is supplied from the standby compass circuit breaker on BATT BUS CBP B via the STBY COMP switch on the overhead lighting panel ELECTRONIC FLIGHT INSTRUMENT SYSTEM The EFIS collects and compares DADC inputs to display attitude direction weather flight guidance commands and flight plan informa tion on five interchangeable cathode ray display tubes Figure 16 33 display...

Page 448: ...I EHSI DME ADF NAV RECEIVER WX ET FMS V L MAP FULL ARC GSPD TTG DH TST ADI DIM WX DIM HSI DIM BRG BRG OFF TEST OFF OFF FMS 1 ADF 1 VOR 1 OFF FMS 2 ADF 2 VOR 2 CRS IAS MACH HDG PUSH DCT PUSH CHG PUSH SYNC HDG VOR ALT AP KIAS M 594 59 280 260 250 240 220 ASEL M VTA M 24000 910 DH200 20 20 10 10 20 20 10 10 DH MAG T H FMS 180 SALON 35 DTK 350 TTG 34 5 HDG 340 F M S 1 L O C 1 F V N 3 6 E 1 2 1 5 S 2 1...

Page 449: ...predetermined distance Symbol Generator Three symbol generators SG receive data from both IRSs both FMSs both flight guid ance computers and both DADCs In addition each symbol generator directly receives short range navigation information such as VOR LOC and GS deviations from the on side NAV receiver Each EFIS consists of a symbol gen erator that converts the gathered data to video CL 601 3A R 16...

Page 450: ... The following conditions exist during the reversion process 16 38 CL 601 3A R FOR TRAINING PURPOSES ONLY FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL HDG VOR ALT AP KIAS M 594 59 280 260 250 240 220 ASEL M VTA M 24000 910 DH200 20 20 10 10 20 20 10 10 DH VERTICAL TRACK ALERT ANNUNCIATOR VERTICAL DEVIATION POINTER ROLL ATTITUDE POINTER FD COUPLE ARROW GLIDE SLOPE POINTER AIRCRAFT ...

Page 451: ...compare an amber colored box and text annunciation flashes for ten seconds then turns steady to alert the CL 601 3A R 16 39 FOR TRAINING PURPOSES ONLY FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL SG REV IRS REV IAS REV FD REV HDG VOR ALT AP KIAS M 594 59 280 260 250 240 220 ASEL M VTA M 24000 160 DH200 20 20 10 10 20 20 10 10 IAS REVERSION ANNUNCIATOR IRS REV SWITCH LIGHT WHEN PRE...

Page 452: ...ATT COMPARISON COMPARATOR ADI G S COPILOT S ILS PILOT S ILS GS COMPARISON COMPARATOR ADI I A S COPILOT S IAS PILOT S IAS IAS COMPARISON EFIS SYMBOL GENERATOR TWO THIRDS OF A DOT MISCOMPARE ON LOC AND RA LESS THAN 1 200 FT TWO THIRDS OF A DOT MISCOMPARE AND RA LESS THAN 1 200 FT 5 KNOTS MISCOMPARE FOR MORE THAN 2 SECONDS AND ON SCALE IAS IS 90 KNOTS 3 MISCOMPARE IN PITCH OR ROLL Figure 16 37 EADI C...

Page 453: ...1 dot miscompare on GS data exists with valid on side and cross side ILS data and radio altitude less than 1 200 feet Indicated airspeed IAS comparison 5 knot miscompare for more than two seconds exists with valid on side and cross side IAS and IAS greater than 90 knots on at least one side CL 601 3A R 16 41 FOR TRAINING PURPOSES ONLY FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL L...

Page 454: ...itude preselect failure Removal of the ASEL digits with a red boxed ASEL flag indicates the loss of valid ASEL Cross side data failure A red boxed XDTA flag indicates the loss of valid cross side information Glideslope failure Removal of the scale and pointer with a steady red boxed FS flag during APP mode indicates loss of the valid GS VNAV Localizer failure Removal of the scale and rising runway...

Page 455: ...16 43 FOR TRAINING PURPOSES ONLY FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL MAG MSG FMS 180 SALON 35 DTK 350 TTG 34 5 HDG 340 F M S 1 L O C 1 F H T N 3 6 E 1 2 1 5 S 2 1 2 4 W 3 0 33 COURSE PRESELECT ANNUNCIATOR FMS ONLY BEARING POINTER SOURCE ANNUNCIATOR NAVIGATION SOURCE ANNUNCIATOR BEARING POINTER NO 1 WAYPOINT DME IDENTIFIER WIND VECTOR DISPLAY DISTANCE DISPLAY COURSE DEVIAT...

Page 456: ...RS 020 GSPD 180 TO HDG 016 F M S 1 L O C 1 V N 33 3 COURSE PRESELECT ANNUNCIATOR FMS ONLY BEARING POINTER SOURCE ANNUNCIATOR NAVIGATION SOURCE ANNUNCIATOR FMS APPROACH ANNUNCIATOR WAYPOINT DME IDENTIFIER WIND VECTOR DISPLAY DISTANCE DISPLAY FORE LUBBER LINE HEADING SOURCE ANNUNCIATOR FMS MESSAGE ANNUNCIATOR COURSE SELECT DESIRED TRACK POINTER FMS DRIFT BUG TO FR ANNUNCIATOR AIRCRAFT SYMBOL HEADING...

Page 457: ...M S 1 V N 33 3 MAG T DME 60 RNE 105 CRS 349 GSPD 180 TO 100 WX 1 HDG 016 V O R 1 N 33 3 WX RADAR MAP MODE MODE ANNUNCIATOR TO WAYPOINT CROSS TRACK DISTANCE VOR BEARING RANGE RING RANGE ANNUNCIATOR TO WAYPOINT IDENTIFIER WAYPOINT WAYPOINT LEG WAYPOINT FLIGHT LEVEL TARGET ALERT ANNUNCIATOR WX RETURN DISPLAY YELLOW IF CROSS SIDE NAV SOURCE Figure 16 42 EHSI Weather Radar and Map Mode ...

Page 458: ...ide change to a yellow color during the reversion process NAV source BC Rising runway pointer Vertical deviation pointer CRS DTK arrow and digital display TO FROM display Distance to WPT DME FMS DME Time to go FMS route and WPT VOR DME sym bols Cross track distance display 16 46 CL 601 3A R FOR TRAINING PURPOSES ONLY FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL MAG H DMS 180 RNE 3...

Page 459: ...e same type of heading MAG TRU Figure 16 44 shows a heading miscompare CL 601 3A R 16 47 FOR TRAINING PURPOSES ONLY FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL MAG DMS 180 RNE DTK 349 TTG 34 5 HDG 327 V O R 1 F N 3 6 E 1 2 1 5 S 2 1 2 4 W 3 0 33 I R S HEADING COMPARISON MONITOR AMBER FLASHING 10 SECONDS THEN STEADY Figure 16 44 Comparison Monitoring ...

Page 460: ...e Navigation source failure Removal of the DTK pointer deviation FMS read out and TO FROM display and chang ing the NAV source to a red boxed annunciator indicates the failure Glideslope failure Removal of the scale and pointer and display of a red boxed GS flag indicates glideslope failure 16 48 CL 601 3A R FOR TRAINING PURPOSES ONLY FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL F...

Page 461: ...arning annunciations are similar to normal modes CL 601 3A R 16 49 FOR TRAINING PURPOSES ONLY FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL HDG LOC ALT AP KIAS M 472 270 300 280 260 ASEL M VTA M 10000 1450 DH200 20 20 10 10 20 10 L O C 1 015 T0 025 N 3 33 AUTO PILOT ENGAGE ANNUNCIATOR COURSE DISPLAY MODE ANNUNICATOR MARKER BEACON ANNUNICATOR ALTITUDE PRESELECT DISPLAY GLIDE SLOPE P...

Page 462: ...EADING BUG TO SYNCHRONIZE TO THE AIRCRAFT HEADING HDG PUSH SYNC BUTTON WHEN ROTATED MOVES THE HEADING BUG ON THE COPILOT S HSI WHEN PRESSED CAUSES THE HEADING BUG TO SYNCHRONIZE TO THE AIRCRAFT HEADING ALT SEL CONTROL ROTATING THE ALT SEL CONTROL CAUSES THE ASEL DISPLAYS ON THE PILOT S AND COPILOT S ADI S TO CHANGE IAS MACH PUSH CHG CONTROL SWITCH WHEN ROTATED ADJUSTS THE IAS MACH REFERENCE ON THE...

Page 463: ...E GROUND EFIS AND THE RADIO ALTIMETER ARE CHECKED IN FLIGHT ONLY THE RADIO ALTIMETER IS CHECKED PROVIDED THE GS IS NOT CAPTURED HSI DIM OUTER CONTROL ADJUSTS THE BRIGHTNESS OF THE HSI DISPLAY WHEN SET TO OFF THE ADI DISPLAYS A COMPOSITE ADI AND HSI MAP PUSHBUTTON SELECTS DISPLAY OF ACTIVE WAYPOINTS AND VOR DME GROUND STATION POSITIONS ON PARTIAL COMPASS DISPLAY WX PUSHBUTTON SELECTS WEATHER RADAR ...

Page 464: ...ith their corre sponding logic For the duration of the test an amber TEST is displayed on the EADI The self test is completely inhibited once the FD approach mode is active If the aircraft is on the ground and the TEST function is performed the SG will reset to the power up configuration after the test button is released 16 52 CL 601 3A R FOR TRAINING PURPOSES ONLY FlightSafety CanadaLtée Ltd CL 6...

Page 465: ...HSI if a display tube fails If for example the top EADI display fails the remaining lower dis play can be changed either to a composite for mat combining the essential features of both indicators or to an EADI with the EHSI for mat displayed on the center MFD The weather radar is an X band receiver trans mitter antenna that is EFIS compatible The weather radar controller is used in conjunction wit...

Page 466: ...S OR DECREASES THE RANGE DISPLAY ON THE MFD INDICATOR ENT PUSHBUTTON ENTERS DESIGNATOR AS A WAYPOINT CHECKS OFF A LINE OR SELECTS AN INDEX LINE ITEM FOR DISPLAY APT PUSHBUTTON SELECTS AIRPORTS FOR O DISPLAY ON MFD WX PUSHBUTTON SELECTS THE WEATHER RADAR INFORMATION FOR DISPLAY ON THE MFD INDICATOR JOYSTICK CONTROL POSITIONS WAYPOINT DESIGNATOR OR PERFORMS CHECKLIST PAGE LINE CONTROL VOR PUSHBUTTON...

Page 467: ...RPOSES ONLY FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL MAG 95 0 040 FMS1 STBY TGT MANZY ETA 1736 DIS 100 MANZY 4000 BUENA 3000 KXYZ KABC ARF WAYPT 0 5R 150 E 6 12 AIRPORT SYMBOL AIRPORT IDENTIFIER WAYPOINT DISTANCE AND COURSE TO DESIGNATOR LUBBER LINE TUNED VOR DME TO WAYPOINT IDENTIFICATION WAYPOINT IDENTIFIER ALTITUDE CONSTRAINT WEATHER RADAR MODE DESIRED TRACK LINE ETA TTG IN...

Page 468: ...enerator stores and dis plays 400 to 800 pages of text Each page of text consists of 12 lines with a maximum of 24 character per line The text colors allow sun light readability Figure 16 54 shows typical MFD checklist pages 16 56 CL 601 3A R FOR TRAINING PURPOSES ONLY FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL 75 0 190 FMS1 TRU N STBY TGT RNG 150 MANZY ETA 1736 DIS 100 MANZY 40...

Page 469: ...TE text display occurs at the com pletion of an emergency procedure The SKP RCL PAG and ENT buttons and joy stick control the operation within the check list pages CL 601 3A R 16 57 FOR TRAINING PURPOSES ONLY FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL EMERGENCY PROCEDURES 1 DOUBLE ENGINE FAILURE 2 ENGINE FIRE OR SEVERE ENGINE DAMAGE 3 APU FIRE 4 INADVERTENT THRUST REVERSER DEPLO...

Page 470: ... master caution The CDU displays 9 lines of text 24 charac ters long The top line of the CDU display functions as a title line The bottom line scratchpad area allows pilot input and message display A manual dimming knob controls manual dimming adjustment Ambient light sensors control automatic display brightness adjustments under varying cloud sunlight con ditions The flight management computer FM...

Page 471: ...ation plus airway routes and SIDs STARs procedures The navaids earth reference points and published routes require routine up dating every 28 days NOTE The custom data base memory stores pilot defined waypoints pilot de fined routes and must be manually updated Due to different software configurations available consult the Aircraft Flight Manual AFM and Pilot Operating Manual for the spe cific FMS...

Page 472: ...16 60 CL 601 3A R FOR TRAINING PURPOSES ONLY FlightSafety Canada L tée L td CL 600 2B16 PILOT TRAINING MANUAL Figure 16 57 AFCS Data Flow ...

Page 473: ...ion following an autopi lot disconnect No single failure will prevent the continued normal safe operation of the DAFCS system When a system failure is detected the failed FGC is isolated from the system or the oper ating flight guidance computer may disen gage allowing the alternate FGC to automatically assume control of the aircraft This is accomplished without the loss of the active flight guida...

Page 474: ...Y VNAV ALT VS FLC CPL AP YD CRS HDG ALT SEL PUSH DCT PUSH SYNC CRS IAS MACH HDG PUSH DCT PUSH CHG PUSH SYNC FLIGHT GUIDANCE CONTROLLER PILOT INSTRUMENT REMOTE CONTROLLER ADVISORY DISPLAY TURN PITCH CONTROLLER COPILOT INSTRUMENT REMOTE CONTROLLER CONTROL WHEEL SWITCHES GO AROUND SWITCHES MANUAL PITCH TRIM SWITCH AP SP DISC TCS PUSH TO RESET AP DISC YD OFF COMP MON COOL AIR FAIL PITOT HEAD MACH TRIM...

Page 475: ... commands consist of the following Heading select HDG Navigation NAV Approach APP Backcourse B C CL 601 3A R 16 63 FOR TRAINING PURPOSES ONLY FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL NAV PUSHBUTTON WHEN PRESSED ARMS THE LATERAL GUIDANCE FOR CAPTURE OF THE SELECTED NAVIGATION COURSE DISPLAYED ON THE COUPLED HSI APP PUSHBUTTON WHEN PRESSED ARMS THE LATERAL GUIDANCE FOR LOCALIZER...

Page 476: ...r and attitude commands to the EADI to intercept and track the displayed navigation course on the coupled EHSI This enables precision ILS final approach mode lateral control using a valid tuned VHF localizer frequency The approach mode has an arm and capture phase that allows setup of a path intercept with automatic tran sition into approach capture and track GS is also enabled For precision appro...

Page 477: ...ommands track up or down contin gent upon power setting VSI desired and attitude at engagement Flight Level Change The FLC button selects the airspeed hold mode and overrides all active vertical modes except VNAV Vertical Navigation The VNAV button operates with the FMS ver tical flight profile to select the vertical navi gation mode CL 601 3A R 16 65 FOR TRAINING PURPOSES ONLY FlightSafety Canada...

Page 478: ...uple CPL 16 66 CL 601 3A R FOR TRAINING PURPOSES ONLY FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL BC M TRIM HDG NAV APP BANK CAT 2 STBY VNAV ALT VS FLC CPL AP YD STBY PUSHBUTTON CAT 2 PUSHBUTTON BANK PUSHBUTTON AP PUSHBUTTON AP YD M TRIM AND CPL POINTERS YD PUSHBUTTON CPL PUSHBUTTON MACH TRIM PUSHBUTTON Figure 16 61 Flight Guidance Controller Basic Functions ...

Page 479: ...ect or if an autopilot fault requiring autopilot disengagement occurs Yaw Damper Activation of the YD pushbutton engages the yaw damper function A repeated activation of the YD pushbutton disengages the yaw damper function If the autopilot is engaged at that time this repeated activation of the YD push button disengages the yaw damper and au topilot functions simultaneously The amber YD OFF light ...

Page 480: ... must be in detent center position be fore the autopilot can be engaged Rotation of the TURN knob cancels any lateral flight di rector mode selected 16 68 CL 601 3A R FOR TRAINING PURPOSES ONLY FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL TURN KNOB PROVIDES BANK COMMANDS TO THE AUTOPILOT FGC 1 AND FGC 2 PROPORTIONAL TO KNOB DISPLACEMENT WHEN ROTATED OUT OF DETENT CENTER POSITION T...

Page 481: ... characters wide Messages are generated by the active flight guidance computer and transmitted to the ad visory display over the ASCB The advisory display unit generates both operational and warning caution messages The operational messages consist of SAT TAT TAS display FD lateral and vertical arm modes FD lateral and vertical active modes AFCS status messages CL 601 3A R 16 69 FOR TRAINING PURPO...

Page 482: ...wer Up Test The power up test automatically initiates dur ing power application to the computer This test verifies the computer internal and external hardware interfaces memory and monitors and is automatic it requires no pilot action If no failures are detected the power up test terminates with no messages displayed If a failure condition is detected it is annunci ated as AFCS OFF on the advisory...

Page 483: ...ing navigation source heading error selected course and course error and lateral and vertical deviations The only exception is dual CPL where both EHSIs are coupled to the FGC In dual CPL the ILS data are averaged by the autopilot Dual CPL is defined by NAV receivers tuned to LOC and valid APP selected and LOC GS captured At engagement the system automatically se lects the pilot side L AFCS and il...

Page 484: ... the advisory display The autopi lot then automatically selects the remaining side sensor data for flight guidance computations Once the pilot has acknowl edged the reversion he can clear the caution message by pressing the RESET pushbutton on the advisory display Autopilot Disconnects The autopilot disconnects when the following conditions exist Figure 16 64 16 72 CL 601 3A R FOR TRAINING PURPOSE...

Page 485: ...director guidance sensor data includes NAV data as displayed on the coupled EHSI and DADC data The coupled side is indicated by the arrow lo cated at each side of the CPL button depend ing on the side selection Figure 16 65 In dual CPL both arrows are illuminated A couple arrow is also displayed on each EADI just above the roll attitude index During normal operation all the flight direc tor modes ...

Page 486: ...data from the coupled side The CPL pushbutton selects the sensor data side and displays the computed flight guidance information on the EADI sin gle cue command bars Figure 16 66 As a fail operational system both the DAFCS FGCs synchronize and perform the same com putations The synchronization allows the 16 74 CL 601 3A R FOR TRAINING PURPOSES ONLY FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRA...

Page 487: ...th flight guidance computers monitor sen sor data from both sides of the aircraft and fail safe operation in the event of sensor failures The sensors consist of either basic aircraft dynamics sensors such as IRS and ADC or navigation related sensors such as VOR LOC FMS DME and radio altitude Basic aircraft sensors interface with the flight guidance computers through the ASCB The ASCB provides all ...

Page 488: ...re displayed that enable the pilot to identify coastlines hilly or mountainous re gions cities or large structures The radar system consists of the following Figure 16 67 Receiver transmitter antenna unit Weather radar controller Multifunction display Forced standby mode 16 76 CL 601 3A R FOR TRAINING PURPOSES ONLY FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL MULTIFUNCTION DISPLAY...

Page 489: ...an amber flashing wait displays in the mode field After the period completes warmup the radar automatically stays in SBY WX Selecting weather places the radar system in the weather detection mode The system is fully operational and all internal parameters are set for enroute weather detection If selection of WX oc curs prior to the 45 second RTA warmup period completes the amber flashing WAIT lege...

Page 490: ...ME SELECTED NAV SOURCE WAYPOINT AIRPORT SYMBOL AIRPORT INDENTIFIER RANGE RING DESIGNATOR DISPLACEMENT LINE CROSS TRACK DEVIATION WEATHER RADAR TILT ANGLE DISTANCE TO TO WAYPOINT ETA TTG IN OR IN GMT HR MN TO WAYPOINT IDENTIFICATION AIRCRAFT SYMBOL WAYPOINT IDENTIFIER ALTITUDE CONSTAINT TARGET ALERT WEATHER RADAR MODE DESIRED TRACK LINE VOR DME SYMBOL VOR DME DEM ONLY VOR ONLY STAB PUSHBUTTON ALLOW...

Page 491: ...n autotilt the tilt con trol can fine tune the tilt setting by 2 degrees UP DOWN Arrows The up and down arrows toggle between the six selectable ranges 10 25 50 100 200 and 300 NM TRB Function Pressing the TRB button activates the turbu lence mode with the rotary RADAR mode select switch in WX and the selected range 50 NM or less A green WX T displays in the mode field Selection of the 100 200 or ...

Page 492: ... copilot s EADIs The radio altimeter system consists of a trans mitter receiver transmitter antenna and re ceiver antenna The DH SET control located on the display controller sets the decision height An expanding rising runway comes into view at 200 feet AGL independent of DH setting The green four digit radio altitude display is from 0 to 2 500 feet AGL NOTE DH on both EADIs can be set only from ...

Page 493: ...el and an AVIONICS COOLING annunciator panel on each bulk head behind the pilot s and copilot s seat pro vide a warning and indication of failures Figure 16 70 All fans operate automatically with power ap plied to the aircraft If a cockpit fan fails the vane switch detects a loss of airflow and illu minates the relevant COOL AIR FAIL warn ing light and AVIONICS COOLING panel warning indicator Ther...

Page 494: ... The IRS MSUs B The IRS ISDU C The FMS CDUs D Both B and C 5 The IRS MSU BATT FAIL light illumi nates when A The primary power to the IRU is not available and the auxiliary battery is powering the IRS B The auxiliary battery charger has failed C The auxiliary battery is supplying less than the minimum voltage required by the IRU D Both A and C 6 The EHSI heading select bug is slewed using A The FM...

Page 495: ...s active using both FGCs dual channel D The autopilot and yaw damper are active 12 When the autopilot is engaged the bank limit is set at 24 27 heading select or 30 LNAV If the bank button on the FGC is pressed the bank angle is reduced to A 15 B 16 C 17 D 20 13 If the autopilot fails to engage check A The autopilot status on the FMS CDU B The position of the maintenance test switch C The TURN kno...

Page 496: ...ANEOUS SYSTEMS CONTENTS Page INTRODUCTION 17 1 OXYGEN SYSTEM 17 1 Crew Oxygen System Description and Operation 17 2 LIMITATIONS 17 5 QUESTIONS 17 6 FOR TRAINING PURPOSES ONLY FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL ...

Page 497: ...3 Oxygen Cylinder Assembly 17 3 17 4 Crew Oxygen Pressure Indicator 17 3 17 5 Oxygen Mask Stowage Box 17 4 17 6 Oxygen Mask and Regulator 17 4 17 7 Overboard Discharge Indicator 17 5 17 8 Average Time of Useful Consciousness 17 5 FOR TRAINING PURPOSES ONLY FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL ...

Page 498: ...selage and stores high pressure oxygen for pilot and copilot use it is ground rechargeable through an external filler valve Attached to the cylinder are pres sure reducing and relief valves These valves regulate operating pressure and pro vide for safety relief of excessive pressure Pressure indicators are included to monitor oxygen cylinder pressure in the cockpit and on the ground service panel ...

Page 499: ...r conventional outlets and hose connectors CREW OXYGEN SYSTEM DESCRIPTION AND OPERATION Reference to Figure 17 1 which illustrates the crew oxygen system component locations is helpful in understanding the operation of the complete system FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL 17 2 CL 601 3A R FOR TRAINING PURPOSES ONLY Figure 17 1 Oxygen System ...

Page 500: ...ssure Indicators The ground service pressure indicator Figure 17 2 is located in the ground service panel on the right side of the forward fuselage It indi cates oxygen cylinder pressure and is checked before flight The cockpit oxygen pressure indicator Figure 17 4 is located on the copilot s side panel and indicates oxygen cylinder pressure Oxygen mask stowage boxes Figure 17 5 are provided on th...

Page 501: ... flow is available in three modes and controlled from a manually operated selector with posi tions marked N normal and 100 PUSH and an EMERGENCY ON OFF rotary control with an integral press to test feature N and 100 modes are on demand meaning that oxygen is available only by operator breath ing In the emergency mode a constant flow is available at slightly higher pressure The three modes of opera...

Page 502: ...psi LIMITATIONS The Challenger crew oxygen system has the following limitation Crew oxygen supply must be serviced and quick donning masks must be on board and serviceable prior to each flight Figure 17 8 depicts the average time of use ful consciousness time from onset of hypoxia until loss of effective performance at various cabin altitudes FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING ...

Page 503: ...ST switch 3 The diluter demand quick donning mask delivers oxygen A At all times B Upon inhalation C Upon exhalation D When removed from stowage box 4 The demand regulator on a crew oxygen mask has three positions The position which supplies 100 oxygen at a con stant positive pressure to the mask is A N B 100 C EMERGENCY D AUTO FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL 17 6 CL ...

Page 504: ...orial walkaround 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 The general location photographs do not specify every checklist item However each item is portrayed on the large scale photographs that follow ...

Page 505: ...T FORWARD FUSELAGE 6 WINDSHIELD AND SIDE WINDOW CHECKED 3 ANGLE OF ATTACK COVER REMOVED CHECKED FOR MOVEMENT 5 ICE DETECTOR PROBE CHECKED 2 STATIC PORT COVER REMOVED AND CHECKED 4 PITOT TUBE COVER REMOVED AND CHECKED 1 EMERGENCY LIGHT CHECKED 3 134 2 133 130 128 125 5 7 43 41 39 33 75 29 26 20 22 8 9 15 10 16 11 17 12 18 13 19 14 31 32 30 135 108 126 42 6 28 36 36 67 35 27 24 25 34 76 21 23 1 4 11...

Page 506: ...CTION ACTUATOR CHECK FOR LEAKS 11 BAY DOORS SAFETY NO 3 HYDRAULIC SYSTEM CHECK DOORS LATCHED OPEN 12 REAR DOORS AND STEERING ACTUATOR CHECK FOR LEAKS 9 TIRES CHECK INFLATION TREAD WEAR CUTS AND SLIPPAGE MARKS 10 OLEO EXTENSION CHECKED 8 RADOME CONDITION CHECKED LATCHES SECURE 7 FORWARD AVIONICS BAY LATCHES SECURE NOSE LANDING GEAR BAY ...

Page 507: ...NG PURPOSES ONLY 19 NLG UPLOCK AND PROX SWITCH CHECKED 16 BRAKE ACCUMULATORS CHECKED 750 PSI 18 NOSE DOOR CANNON PLUG CONNECTED IF NO 3 HYD SYSTEM IS DEPRESSURIZED 15 PROXIMITY SWITCHES INTACT 17 ADG SAFETY PIN REMOVED IF NO RESISTANCE FELT 14 WEIGHT ON WHEELS SWITCHES AND HARNESSES INTACT ...

Page 508: ...RPOSES ONLY 26 OXYGEN FRANGIBLE GREEN DISK INTACT 22 FORWARD AVIONICS BAY LATCHES SECURE 23 ADG COMPARTMENT SECURE 25 ICE DETECTOR PROBE CHECKED 21 OXYGEN PANEL OPENED PRESSURE CHECKED SECURE 24 PITOT TUBE COVER REMOVED AND CHECKED 20 AC EXTERNAL POWER SERVICE DOOR SECURE RIGHT FORWARD FUSELAGE ...

Page 509: ... FOR TRAINING PURPOSES ONLY 31 FUEL ADAPTER SERVICE DOOR SECURE 32 WING ICE LIGHT CHECKED 30 PRESSURE FUELING PANEL VALVES CLOSED SWITCH OFF SECURE 28 ANGLE OF ATTACK VANE COVER REMOVED CHECKED FOR MOVEMENT 29 STATIC PORT COVER REMOVED AND CHECKED 27 TAT PROBE CHECKED RIGHT WING ...

Page 510: ... CL 601 3A R W 7 FOR TRAINING PURPOSES ONLY 38 RIGHT MAIN FUEL TANK FILLER CAP SECURE 35 ENGINE INTAKE PLUG REMOVED 37 RIGHT MAIN FUEL DRAIN CHECK FOR LEAKS 34 AUXILIARY FUEL TANK FILLER CAP SECURE 36 EMERGENCY LIGHTS 3 CHECKED 33 TAXI AND LANDING LIGHTS CHECKED ...

Page 511: ...INGES AND VANES CHECK FOR CONDITION AND NO MOVEMENT 41 UNDERSIDE CHECK FOR FUEL LEAKS 42 WINGTIP CHECK CONDITION 43 NAVIGATION LIGHT CHECK FUNCTION 44 STATIC DISCHARGERS CHECK FOR DAMAGE 46 AILERON CHECK FOR LEAKAGE AND CONDITION NO MOVEMENT 40 FUEL VENT VALVE EXHAUST CHECKED 45 WINGLET CHECK CONDITION 39 WING LEADING EDGE CONDITION AND ANTI ICE EXHAUST CHECKED ...

Page 512: ... ACTUATOR CHECK CONDITION LEAKS INTEGRITY PROXIMITY SWITCHES AND DOWNLOCK INDICATOR FLUSH 51 WHEEL WELL BINS CHECK FOR DAMAGE AND SECURITY 52 RIGHT AND LEFT MLG SENSING LOOPS CHECK CONDITION AND CONNECTIONS 50 NO 3 HYDRAULIC SYSTEM ACCUMULATOR CHECK 1500 PSI 49 FUEL NACA VENT COVER REMOVED CHECK CONDITION MAIN LANDING GEAR BAYS ...

Page 513: ...CURITY 60 RIGHT MAIN HYDRAULIC ACTUATOR CHECK CONDITION LEAKS INTEGRITY PROXIMITY SWITCHES AND DOWN LOCK INDICATOR FLUSH 55 LEFT MAIN BRAKES CHECK WEAR INDEX PINS AND LINES FOR LEAKS DAMAGE AND SECURITY 56 LEFT MAIN TIRES CHECK INFLATION TREAD WEAR CUTS AND SLIPPAGE MARKS 57 LEFT MAIN OLEO EXTENSION CHECKED 59 LEFT MAIN UPLOCK AND PROX SWITCH CHECKED 54 DOWNLOCK PIN REMOVED SLIDE DUST PROTECTION R...

Page 514: ...OSED 67 OVERWING EXIT CHECKED FLUSH 66 RIGHT MAIN UPLOCK AND PROX SWITCH CHECKED 64 RIGHT MAIN TIRES CHECK INFLATION TREAD WEAR CUTS AND SLIPPAGE MARKS 65 RIGHT MAIN LANDING GEAR DOOR INSPECT FOR SECURITY 62 RIGHT MAIN BRAKES CHECK WEAR INDEX PIN AND LINES FOR LEAKS DAMAGE AND SECURITY 63 RIGHT MAIN OLEO EXTENSION CHECKED RIGHT REAR FUSELAGE AREA ...

Page 515: ...R TRAINING PURPOSES ONLY 74 RAM AIR INTAKE REMOVE COVER AND CHECK 71 APU EXHAUST REMOVE COVER CHECK CONDITION 73 APU AIR INTAKE REMOVE COVER AND CHECK 70 DC EXTERNAL POWER SERVICE DOOR SECURE 72 RIGHT ACU EXHAUST REMOVE COVER AND CHECK 69 FUEL VENT SHROUD DRAINS INSPECT FOR LEAKAGE ...

Page 516: ...G MANUAL 78 ENGINE PYLON CHECKED 79 ENGINE EXHAUST COVER REMOVED 80 REAR TURBINE BLADES CHECKED 76 UPPER AND LOWER COWLING CHECKED LATCHES SECURE 77 ENGINE DRAIN LINES CHECK FOR LEAKS AND CONDITION 75 COWL ANTI ICE PRESSURE RELIEF VALVE AND EXHAUST LOUVERS CHECKED FLUSH AND CLEAR RIGHT ENGINE AREA ...

Page 517: ...AFT EQUIPMENT BAY 88 SERVICE LIGHT SELECT ON 87 EQUIPMENT BAY DOOR OPEN 86 HYDRAULIC HEAT EXCHANGE EXHAUST CHECK CLEAR 81 RUDDER CHECK FOR LEAKS AND CONDITION 82 HORIZONTAL STABILIZER CHECK POSITION AND CONDITION 83 ELEVATORS CHECK FOR LEAKS AND CONDITION 84 NAVIGATION LIGHTS CHECK FUNCTION 85 ANTENNA CHECK CONDITION ...

Page 518: ...Y DIRECT BUS CHECK CIRCUIT BREAKERS AND FUSES 92 ENGINE FIREX BOTTLES 2 CHECK PRESSURE 600 PSI AND SQUIB CONNECTION 94 BATTERY CHECK CONDITION AND CONNECTIONS 91 PRESSURIZATION OUTFLOW VALVES 2 CHECK CLEAR 93 PNEUMATIC DUCTING CHECK CONDITION 89 APU ENCLOSURE CHECK FOR LEAKS AND CONDITION 90 APU SERVICE DOOR SECURE ...

Page 519: ...ING MANUAL 101 LEFT ACU CHECK 98 RAM AIR DUCTING CHECK CONDITION 100 NO 1 HYDRAULIC SYSTEM CHECK FILTERS LEAKS AND ACCUMULATOR PRESSURE 1500 PSI 97 NO 2 HYDRAULIC SYSTEM CHECK FILTERS LEAKS AND ACCUMULATOR PRESSURE 1500 PSI 99 ENGINE OIL REPLENISHMENT RESERVOIR CHECK CONDITION 96 RIGHT ACU CHECK ...

Page 520: ...ES ONLY FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL 105 EQUIPMENT BAY DOOR CLOSE AND LOCK 103 OIL REPLENISHING SYSTEM CHECKED 104 SERVICE LIGHT SELECT OFF 102 APU FIREX BOTTLE CHECK PRESSURE 600 PSI AND SQUIB CONNECTION ...

Page 521: ...MANUAL 106 ENGINE EXHAUST COVER REMOVED 107 REAR TURBINE BLADES CHECKED 110 UPPER AND LOWER COWLING CHECKED LATCHES SECURE 111 COWL ANTI ICE PRESSURE RELIEF VALVE AND EXHAUST LOUVERS CHECKED FLUSH AND CLEAR 108 ENGINE PYLON CHECKED 109 ENGINE DRAIN LINES CHECK FOR LEAKS AND CONDITION LEFT ENGINE AREA ...

Page 522: ...NUAL 114 CROSSOVER HEAT EXCHANGER EXHAUST REMOVE COVER AND CHECK ONLY CL601 3A 115 APU FAULT PANEL CHECK INDICATORS AND RESET 116 EXTERNAL PNEUMATIC PORT CHECK CONDITION 117 SERVICE DOOR CLOSE AND SECURE 113 LEFT ACU EXHAUST REMOVE COVER AND CHECK 112 ENGINE INTAKE PLUG REMOVED LEFT REAR FUSELAGE AREA ...

Page 523: ...RON CHECK FOR LEAKAGE AND CONDITION NO MOVEMENT 121 FLAPS HINGES AND VANES CHECK FOR CONDITION AND NO MOVEMENT 122 SPOILERS 2 CHECK FOR LEAKAGE AND CONDITION NO MOVEMENT 120 FUEL NACA VENT COVER REMOVED CHECK CONDITION 119 BAGGAGE COMPARTMENT DOOR SECURED LEFT WING 118 APU WITNESS DRAINS INSPECT FOR EXCESSIVE LEAKS ...

Page 524: ... MAIN FUEL TANK DRAIN CHECK FOR LEAKS 128 FUEL VENT VALVE EXHAUST CHECKED 130 WING LEADING EDGE CONDITION AND ANTI ICE EXHAUST CHECKED 127 UNDERSIDE CHECK FOR FUEL LEAKS 129 LEFT MAIN FUEL TANK FILLER CAP SECURE 124 STATIC DISCHARGERS CHECK FOR DAMAGE 125 NAVIGATION LIGHT CHECK FUNCTION 126 WINGTIP CHECK CONDITION ...

Page 525: ...W 22 CL 601 3A R FOR TRAINING PURPOSES ONLY FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL INTENTIONALLY LEFT BLANK ...

Page 526: ...MANUAL 132 AUXILIARY TANK FUEL VENT VALVE EXHAUST CHECKED 133 TAXI AND LANDING LIGHTS CHECKED 134 WING ICE LIGHT CHECKED 135 MAIN ENTRANCE DOOR AREA CHECKED 82 83 82 83 123 124 119 115 116 117 109 87 97 88 98 89 99 90 100 91 101 92 102 93 103 94 104 95 105 96 46 47 72 74 78 71 86 70 79 80 68 69 73 45 113 106 107 110 84 84 85 85 81 48 121 50 51 52 53 54 55 56 57 59 60 61 62 63 64 65 66 58 ...

Page 527: ...LKAROUND CHECKS COCKPIT 2 LEFT FWD FUSELAGE 3 NLG BAY 4 RIGHT FWD FUSELAGE 5 RIGHT MID FUSELAGE WING 6 RIGHT MAIN LANDING GEAR BAY 7 RIGHT AFT FUSELAGE 8 RIGHT ENGINE 9 EMPENNAGE 10 AFT FUSELAGE UNDERSIDE 11 AFT EQUIPMENT BAY 12 LEFT ENGINE 13 LEFT AFT FUSELAGE 14 LEFT MAIN LANDING GEAR BAY 15 LEFT MID FUSELAGE WING 16 MAIN DOOR ENTRANCE PREFLIGHT WALKAROUND SEQUENCE ...

Page 528: ...CL 601 3A APP 1 FOR TRAINING PURPOSES ONLY FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL CL 601 3A R APPENDIX ...

Page 529: ... Exchanger S O V Shutoff Valve ADG Air APR Automatic Performance Reserve APU Auxiliary Power Unit ATS Air Turbine Starter ECU Electronic Control Unit EDP Engine Driven Pump EGT Exhaust Gas Temperature ITT Interturbine Temperature LCV Load Control Valve LOP Low Oil Pressure N1 Fan RPM N2 High Pressure Compressor RPM SDC Signal Data Converter SQUIB Detonating Device Fire Bottles AOA Angle of Attack ...

Page 530: ...G Bearing CAP Capture CB Circuit Breaker COMP Comparator CPL Couple CRS Course DADC Digital Air Data Computer DME Distance Measuring Equipment DG Directional Gyro DH Decision Height DTRK Desired Track EFIS Electronic Flight Instrument System FD Flight Director FGC Flight Guidance Computer FMS Flight Management System GA Go Around GS Glide Slope HDG Heading HSI Horizontal Situation Indicator IRS In...

Page 531: ...NG PURPOSES ONLY FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL AVIONICS AVIONICS VANG Vertical Angle VG Vertical Gyro VMO Maximum Operating Speed VNAV Vertical Navigation VS Vertical Speed WX Weather YD Yaw Damper ...

Page 532: ...CL 601 3A ANN 1 FOR TRAINING PURPOSES ONLY FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL CL 601 3A ANNUNCIATOR PANEL ...

Page 533: ... E 135 S 225 W 315 3 0 3 3 N 3 6 E 1 2 1 5 S 2 1 2 4 W N S O E N MASTER CAUTION PRESS TO RESET STALL PUSH ALT COMP FAIL STALL PROTECT FAIL LH ENG FIRE PUSH REVERSER UNLOCKED REVERSE THRUST REVERSER UNLOCKED REVERSE THRUST LH FLT SPLR LH GND SPUR RH FLT SPLR RH GND SPUR BOTTLE ARMED PUSH TO DISCH RH ENG FIRE PUSH BOTTLE ARMED PUSH TO DSCH APU FIRE PUSH BOTTLE ARMED PUSH TO DISCH MASTER CAUTION PRES...

Page 534: ...HANGE CHAN INBD TEST OUTBD TEST TEST ARM OFF PASS DR NOT RDY PASS DR UNSAFE PASS DR UNLK CABIN SIGNS ON OFF AUTO NO SMKG SEAT BLTS DOOR IND MON SAFE OUTBD FAIL INBD FAIL PASS DR READY OVSP HSI MFD SG HSI SG VOR DAT APT RCL SKP PAG ENT 0 100 110 120 130 350 375 400 425 450 HERTZ AC VOLTS 10 20 25 30 35 DC VOLTS 0 20 40 60 80 100 DC AMPS EXT PWR GEN 1 APU GEN 2 ADG TRU LOAD BUS VOLTS ESS 1 ESS 2 1 2...

Page 535: ...UEL TRANS OFF NOT ARMED SEC TRANS DUMP SW ARMED TOTAL FUEL QUANTITY LB AUX L MAIN R MAIN TAIL PUSH ON OFF PUMP PUMP X FLOW E J C T F E E D L E F T E N G F U E L E N G F U E L FUEL CONTROL SCAV MAIN VALVE CLOSED FILTER LOW PRESS VALVE CLOSED FILTER LOW PRESS SCAV MAIN ON INOP ON INOP OPEN LEFT TO RIGHT RIGHT TO LEFT E J C T F E E D R I G H T 70 20 20 40 0 70 20 20 60 40 0 FUEL C L R 60 OFF SEL CAL ...

Page 536: ...FOR TRAINING PURPOSES ONLY FlightSafety CanadaLtée Ltd CL 600 2B16 PILOT TRAINING MANUAL CL 601 3R ANN 1 CL 601 3R ANNUNCIATOR PANEL ...

Page 537: ...135 S 225 W 315 3 0 3 3 N 3 6 E 1 2 1 5 S 2 1 2 4 W N S O E N MASTER CAUTION PRESS TO RESET STALL PUSH ALT COMP FAIL STALL PROTECT FAIL LH ENG FIRE PUSH REVERSER UNLOCKED REVERSE THRUST REVERSER UNLOCKED REVERSE THRUST LH FLT SPLR LH GND SPUR RH FLT SPLR RH GND SPUR BOTTLE ARMED PUSH TO DISCH RH ENG FIRE PUSH BOTTLE ARMED PUSH TO DSCH APU FIRE PUSH BOTTLE ARMED PUSH TO DISCH MASTER CAUTION PRESS T...

Page 538: ...L R OFF OFF L R CHAN 1 INOP CHAN 2 INOP INBD TEST OUTBD TEST TEST ARM OFF PASS DR NOT RDY PASS DR UNSAFE PASS DR UNLK CABIN SIGNS ON OFF AUTO NO SMKG SEAT BLTS DOOR IND MON SAFE OUTBD FAIL INBD FAIL PASS DR READY ANTI SKID CHANGE CHAN OVSP INC R N G DEC MODE DIM MAP PLAN SRC WX NORM EMER HSI MFD SG HSI SG VOR DAT APT RCL SKP PAG ENT 0 100 110 120 130 350 375 400 425 450 HERTZ AC VOLTS 10 20 25 30 ...

Page 539: ...FIRE WARN FAIL FIRE WARN FAIL LOW PRESS LOW PRESS L SQUIB R SQUIB L SQUIB R SQUIB IRS 1 IRS 2 IRS 3 AUXILIARY BATTERY CHARGER FAIL FIRE WARNING TEST FIREX MONITOR BOTTLE NO 1 APU BOTTLE NO 2 PRESS TO TEST SQUIB WOW O P FAIL WOW I P FAIL NOSE DOOR OPEN DUCT FAIL OVHT OVHT OVHT WARN FAIL FAIL ALTN PRESS TO TRANSFER ESSENTIAL AC POWER PUSH TO TEST MLG OVHT BAY DETECT PUSH TO TEST BLEED AIR LEAK DETEC...

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