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BOMBARDIER BD-100-1A10 Operating Manual

BOMBARDIER BD-100-1A10 Operating Manual

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FLIGHT CREW

OPERATING MANUAL

CSP 100-6

Oct 31/2008

Revision 11

VOLUME 2

MODEL BD-100-1A10

CUSTOMER SUPPORT PUBLICATION No. 100-6

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Summary of Contents for BOMBARDIER BD-100-1A10

Page 1 FLIGHT CREW OPERATING MANUAL CSP 100-6 Oct 31/2008 Revision 11 VOLUME 2 MODEL BD-100-1A10 CUSTOMER SUPPORT PUBLICATION No. 100-6...
Page 3 Production Modification Data ....................00-02-02 Addresses ........................... 00-02-02 Abbreviations and Acronyms....................00-02-03 Conversion Factors ......................00-02-12 Temperature Conversion Table ................... 00-02-13 Index ........................... 00-03-01 Systems Description......................00-04-01 REV 1 Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 00-00-01...
Page 5 The List of Effective Pages establishes the current effective date of each page in the Flight Crew Operating Manual and may be used as an instruction sheet for incorporating the latest Numbered Change into the Flight Crew Operating Manual.
Page 6 On the internet at www.cic.bombardier.com, then select User Comment from the Technical Publications heading. A user name and password are required to use this option. REV 1 Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 00-02-02...
Page 7 Command Cowl Anti-Ice CMPS Compass Calibrate CMPTR Computer Capture Carbon Dioxide Calibrated Airspeed COMP Compressor, Comparator REV 1 Crew Alerting System COND Condition, Continued Category CONN Connection Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 00-02-03...
Page 8 (2) Electronic Control Unit Electronic Display Engine Indicating System Engine Driven Pump ELEC Electrical Engine Electronic Controller Emergency Locator Transmitter EFIS Electronic Flight EMER Emergency Instrument System Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 00-02-04...
Page 9 Flight Management Computer FADEC Full Authority Digital Engine Flight Management System Control Flight Control Computer Foreign Object Damage FCOM Flight Crew Operating Manual Feet Per Minute Flight Control Unit Flap Power Unit Flight Data Recorder FREQ Frequency FECU Flap Electronic Control Unit...
Page 10 KTAS Kilo Pascal True Airspeed Kilo Watts LAT/LONG Latitude/Longitude LNDG Landing Altitude L/G or LG Landing Gear Localizer Left Compass Locator at Outer Marker Lavatory Low Pressure Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 00-02-06...
Page 11 Master Wheel Disconnect Mega Hertz (freq range) Miles To Go Mach indicated MTOW Maximum Take Off Weight Minimum Reception Altitude MZFW Maximum Zero Fuel Weight REV 1 Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 00-02-07...
Page 12 Pounds Per Square Inch Gauge Pilot Proximity Sensor System Position Push To Talk Pounds Per Hour Priority Valve PRI, or PRIM Primary PRI PRV Primary Pressure Regulating Valve Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 00-02-08...
Page 13 Sensitivity, Sensor SUPPL Supply SERV, SVCE Service Servo Standard Instrument Departure SW(s) Switches SMKG Smoking Synchronize Shut-Off Valve SYNC Synchronization, Synchronous SP, SPD Speed System REV 1 Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 00-02-09...
Page 14 Rough Air Penetration speed Operating Speed Minimum Control Speed Air Reference Velocity Minimum Control Speed Ground Stalling Speed or the Minimum Steady Flight Speed Obtained in a Specific Configuration Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 00-02-10...
Page 15 XFR or XFER Transfer XPNDR Transponder XBLEED Cross Bleed Cross Track XFLOW Cross Flow Cross Wind Component XMIT Transmit YD or Y/D Yaw Damper Zero Fuel Weight Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 00-02-11...
Page 16 29.574 U.S. gal 3.7854 liters U.S. gal/min 3.7854 liters/min 6.8948 0.3048 30.48 0.4536 lb/min 0.4536 kg/min 4.4482 lbf in 0.1130 lbf ft 1.3558 in Hg 3.3864 Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 00-02-12...
Page 17 -63.4 -47.2 26.6 -19.4 116.6 206.6 36.1 296.6 63.9 -61.6 -46.7 28.4 -18.9 118.4 208.4 36.7 298.4 64.4 -59.8 -46.1 30.2 -18.3 120.2 210.2 37.2 300.2 65.0 Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 00-02-13...
Page 19: Table Of Contents
APU Fuel Feed.......................12-01-05 APU Fuel Shutoff Valve (SOV) ................12-01-07 APU Fuel Supply ....................05-01-06 REV 7 APU/Engine Bleed Switching .................02-02-05 APU/Engine Bleed Switching Sequence ..............02-02-05 APU Schematic ......................05-01-03 (Continued) Dec 05/2006 Flight Crew Operating Manual Volume 2 REV 7 CSP 100-6 00-03-01...
Page 20 Bleed Air Management...................02-02-05 Bleed Air Manifold ....................02-02-03 Bleed Air System....................02-02-01 Bleed Leak Detection System ................14-01-03 Bleed Valve ......................05-01-08 Bleed Valve Modulation/Bleed Air Loads ...............05-01-08 Brake Control System ....................15-01-13 Volume 2 Flight Crew Operating Manual Dec 05/2006 REV 7 CSP 100-6 00-03-02...
Page 21 Control Switches and Function................14-01-09 Control Wheel......................01-04-13 Control Wheel TX and INPH Switches ..............06-01-02 Conversion Factors ....................00-02-12 Course Display ....................... 11-01-19 Course Pointer ....................... 11-01-19 Crew Oxygen Mask ....................08-01-07 (Continued) Dec 05/2006 Flight Crew Operating Manual Volume 2 REV 7 CSP 100-6 00-03-03...
Page 22 Electric Fuel Pumps ....................12-01-05 Electrical Control Panel ..................07-01-16 Electrical Pneumatic Actuating Valve (EPAV)............08-01-09 Electrical Power......................18-01-05 Electrical Control Panel ..................05-01-11 Electrical Summary Page ..................07-01-15 Electrical Synoptic Page..................05-01-12 (Continued) Volume 2 Flight Crew Operating Manual Dec 05/2006 REV 7 CSP 100-6 00-03-04...
Page 23 External Aircraft Lighting ..................16-01-12 External Ground Air Connector ................02-02-03 External Lights......................16-01-08 External Power .......................07-01-03 External Power Control Panel ................05-01-09 External Power Control Panel ................07-01-14 Eye Locator — Seat Adjustment ................01-04-02 Dec 05/2006 Flight Crew Operating Manual Volume 2 REV 7 CSP 100-6 00-03-05...
Page 24 Flight Compartment Printer (Optional) ..............16-01-16 Flight Compartment Speakers................06-01-04 Flight Control Synoptic Page..................10-02-17 Flight Controls Synoptic Page ................03-04-05 Flight Crew Oxygen Mask and Storage Cup ............08-01-06 Flight Crew Oxygen Mask Cold Weather Storage..........08-01-06 Flight Deck Emergency Equipment ................ 08-01-11 Flight Director Command Bars ................04-01-02 Flight Director Command Bars ................
Page 25 HF Coupler ......................06-01-09 HF Radio Communication (Optional) ..............06-01-09 High Pressure Valves .....................02-02-03 High-Level Sensors ....................12-01-08 High-Power Amplifier....................06-01-12 Honeywell AS907 Engine Module Breakdown ............18-01-02 Horizon Line ......................11-01-04 (Continued) Dec 05/2006 Flight Crew Operating Manual Volume 2 REV 7 CSP 100-6 00-03-07...
Page 26 Left and Right Hydraulic System ................13-01-01 Left and Right Hydraulic System Cooling...............13-01-04 Left Cockpit Lights Panel..................16-01-03 Left Displays......................11-01-27 Left Displays Reversion Switch ................03-02-09 Left Hydraulic System Schematic................13-01-05 Left MFD.........................03-02-08 (Continued) Volume 2 Flight Crew Operating Manual Dec 05/2006 REV 7 CSP 100-6 00-03-08...
Page 27 Navigation Alert Flags .................... 11-01-20 Navigation Data ...................... 11-01-19 Navigation Displays....................11-01-19 Navigation Source Indicator ................... 11-01-19 NEXRAD Image ..................... 11-02-15 Normal Extension and Retraction................15-01-09 Normal-Rated Takeoff N Indications (TO).............18-01-08 (Continued) Dec 05/2006 Flight Crew Operating Manual Volume 2 REV 7 CSP 100-6 00-03-09...
Page 28 Pressurization Schedule — Descent and Hold (<25 000 ft) ........02-04-04 Primary Flight Controls...................10-01-02 Primary Flight Display (PFD).................. 11-01-34 Primary Flight Displays................... 11-01-03 Production Modification Data .................00-02-02 (Continued) EV 7 Volume 2 Flight Crew Operating Manual Dec 05/2006 REV 7 CSP 100-6 00-03-10...
Page 29 Secondary Flight Controls ..................10-02-01 Secondary Power Centers ..................07-01-06 SELCAL System (Optional)..................06-01-11 Selected Heading Reference ................. 11-01-18 Service Doors......................01-05-09 SIGMET/AIRMET Reports ..................11-02-26 SIGMET/AIRMET Reports Page ................11-02-26 (Continued) Dec 05/2006 Flight Crew Operating Manual Volume 2 REV 7 CSP 100-6 00-03-11...
Page 30 Takeoff From Airfield Less Than 7850 ft and Landing Field Elevation Above 7850 ft................... 02 - 04- 07 Tank Construction....................12-03-03 TAWS Modes......................17-01-15 Mode 1 ........................17-01-16 (Continued) Volume 2 Flight Crew Operating Manual Dec 05/2006 REV 7 CSP 100-6 00-03-12...
Page 31 Vertical Deviation Display..................11-01-05 Vertical Navigation....................11-01-09 Vertical Speed Field ....................11-01-09 VHF Communication ....................06-01-06 VHF Navigation System ..................17-01-02 Vibration Monitoring System ..................18-01-22 Visual Eye References For Ground Operation ............01-02-06 Dec 05/2006 Flight Crew Operating Manual Volume 2 REV 7 CSP 100-6 00-03-13...
Page 32 Wing Anti-Ice System .....................14-01-03 Wing Anti-Ice System Schematic ................14-01-05 Wing Anti-Icing Valves....................14-01-04 Wing Isolation Valve ....................14-01-04 Wing Overheat .......................14-01-04 Wing Temperature Sensors..................14-01-03 WX Depiction Image....................11-02-17 Yaw Damper......................04-01-23 Yaw Damper......................10-01-06 Volume 2 Flight Crew Operating Manual Dec 05/2006 REV 7 CSP 100-6 00-03-14...
Page 33 FUEL Chapter 12 HYDRAULICS Chapter 13 ICE AND RAIN PROTECTION Chapter 14 LANDING GEAR Chapter 15 LIGHTING Chapter 16 NAVIGATION Chapter 17 POWERPLANT Chapter 18 REV 1 Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 00-04-01...
Page 35 Aft Equipment Bay Door Annunciation............... 01-05-11 Door Warning System ......................01-05-12 Description ......................... 01-05-12 Components And Operation ..................01-05-12 EICAS Messages ........................ 01-05-13 REV 4 REV 1 REV 1 Sep 14/2005 Flight Crew Operating Manual Volume 2 REV 4 CSP 100-6 01-00-01...
Page 37: Introduction
Aircraft air-conditioning systems which include an air-cycle machine, provide heating, cooling, and pressurization for the cockpit, passenger compartment, and lavatory. REV 1 Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 01-02-01...
Page 38: Aircraft Dimension Schematic
(7.24 m) (8.56 m) 25% CHORD LINE 3 ft 9 in OTHER DIMENSIONS (1.14 m) WING AREA 522 ft (48.5 m ) WING BASE 27.8 ft (8.5 m) Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 01-02-02...
Page 39 (18.62 m) 68 ft 8 in (20.92 m) NOTES Measurement at manufacturer empty weight. 23.7 ft (7.7 m) 16.5 ft (5.0 m) 28.6 ft (8.7 m) REV 1 Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 01-02-03...
Page 40 1.55 m WIDTH CENTERLINE 7 ft 2 in 2.18 m HEIGHT 6 ft 1 in 1.85 m 896 ft VOLUME 25.37 m 146 ft 13.5 m FLOOR AREA Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 01-02-04...
Page 41: Antenna Location Schematic
Personnel should not stand nearby and in front of the radar antenna when it is transmitting. When the antenna is not scanning, the danger increases. WEATHER RADAR GLIDESLOPE Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 01-02-05...
Page 42: Visual Eye References For Ground Operation
MAXIMUM 139° VISION AFT WITH HEAD ROTATED 1.8 ft PILOT'S EYE (0.54 m) POSITION WITH HEAD MOVED 0.3 ft (91 mm) OUTBOARD 51° 51° 17° 17° 20° 20° 32° 32° Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 01-02-06...
Page 43: Steering And Turning Radii
OF SAFETY. NOTE MAXIMUM STEERING SYMMETRICAL AND IDLE THRUST NO DIFFERENTIAL BRAKING 65° STEERING ANGLE 3° SLIP DRY RUNWAY SLOW CONTINUOUS TURN MAX A/C WEIGHT AFT CG Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 01-02-07...
Page 44: Danger Areas
SHOWN FOR IDLE RPM. VALUES APPROXIMATELY DOUBLE FOR TAKEOFF APU EXHAUST RPM. 500 °F (260 °C) 19 ft (5.8 m) 200 ft (60.9 m) FROM TAILPIPE 200 °F (93.3 °C) Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 01-02-08...
Page 45: Airplane Jacking
Gear jacking points are also provided for tire/wheel/brake changes. Jacking procedures are located in the Aircraft Maintenance Manual (Chapter 7). SUPPORT BEAM JACKING POINT JACK NYLON PLUG TYPICAL JACK LEGEND JACK REAR FUSELAGE SUPPORT REAR FUSELAGE SUPPORT REV 1 Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 01-03-01...
Page 46: Towing
For further towing information refer to the Aircraft Maintenance Manual (Chapter 9). TOWING BAR ATTACHMENT TOW BAR ASSEMBLY REV 7 Volume 2 Flight Crew Operating Manual Dec 05/2006 REV 7 CSP 100-6 01-03-02...
Page 47: Mooring
Mooring procedures are located in the Aircraft Maintenance Manual (Chapter 10). MOORING ATTACHMENT POINTS MOORING MAIN AND NOSE AREAS ADAPTER PLATE JACKING 45° 45° TIE DOWN TAIL AREA RING 30.25° 30.25° Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 01-03-03...
Page 49: Crew Seat Assembly
SEAT BASE SEAT BACK VERTICAL ADJUSTMENT CONTROL TRASH BAG HOOK SHOULDER STRAP RESTRAINT LOCK / UNLOCK HANDLE SEATBACK FRAME FORE/AFT ADJUSTMENT CONTROL LUMBAR ADJUSTMENT HANDWHEEL REV 1 Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 01-04-01...
Page 50: Eye Locator - Seat Adjustment
- All flight controls are unrestricted throughout full travel - Flight instruments and warning lights visible, without being obstructed - Out-of-cockpit visibility unobstructed - Seat position comfortable Volume 2 Flight Crew Operating Manual May 06/2005 REV 2 CSP 100-6 01-04-02...
Page 51: Cockpit Layout
AIRPLANE GENERAL COCKPIT LAYOUT Flight Deck (typical) Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 01-04-03...
Page 52: Left Side Console
AIRPLANE GENERAL COCKPIT LAYOUT (Cont) LEFT SIDE CONSOLE COCKPIT LIGHTS GSHLD/L SIDE PEDESTAL ANNUN PFD - Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 01-04-04...
Page 53: Right Side Console
AIRPLANE GENERAL COCKPIT LAYOUT (Cont) RIGHT SIDE CONSOLE COCKPIT LIGHTS GSHLD/R SIDE DOME PFD - CB PANELS REV 1 Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 01-04-05...
Page 54: Center Pedestal
21. FLAP LEVER 22. MFD CONTROL PANEL (MCP) PULL 23. ENGINE PANEL 24. APU SWITCH 25. LANDING GEAR MANUAL RELEASE HANDLE 26. PAX OXYGEN PANEL Center Pedestal (Typical) Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 01-04-06...
Page 55: Instrument Panel
AIR OUTLET LEFT PRIMARY FLIGHT DISPLAY (PFD) LEFT MULTI FUNCTION DISPLAY (MFD) TAWS WARNING PANEL LANDING GEAR HANDLE RIGHT MULTI FUNCTION DISPLAY (MFD) RIGHT PRIMARY FLIGHT DISPLAY (PFD) Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 01-04-07...
Page 56: Circuit Breaker Panels
ANTI ICE L AOA L WINDSHIELD L PROBE L ICE L STBY L WING L ENG CTRL L PITOT STATIC CTRL BLD LK VANE CASE REV 2 Volume 2 Flight Crew Operating Manual May 06/2005 REV 2 CSP 100-6 01-04-08...
Page 57: Cb 2 Copilot Circuit Breaker Panel (Typical)
R AOA R PROBE R WING R STBY STBY R ICE CTRL EMER DOME R ENG BLD LK CTRL VANE STATIC PITOT R PITOT CASE REV 2 May 06/2005 Flight Crew Operating Manual Volume 2 REV 2 CSP 100-6 01-04-09...
Page 58: Cb 3 Left Side Equipment Rack Circuit Breaker Panel (Typical)
LIGHTS IAPS LIGHTNING L CKPT CABIN WING MAP/ BCN/ COM 3 /PED SIGNS INSP STOW STROBE ENTRY INDICATING/RECORDING DISPLAYS L PFD L MFD CLOCK CLOCK REV 7 Volume 2 Flight Crew Operating Manual Dec 05/2006 REV 7 CSP 100-6 01-04-10...
Page 59: Cb 4 Right Side Equipment Rack Circuit Breaker Panel (Typical)
CTRL WARM MAST HTR PAX 2 LIGHTS CABIN NOSE GEAR WING R CKPT LOGO CABIN TAXI STROBE /CBP CTRL INDICATING/RECORDING R MFD R PFD ADDRESS REV 7 Dec 05/2006 Flight Crew Operating Manual Volume 2 REV 7 CSP 100-6 01-04-11...
Page 60: Cb 5 Left Dc Power Center Circuit Breaker Panel (Typical)
SEC STAB SATCOM HYD SOL MOTOR R LDG ELECTRICAL REFUEL DEFUEL L DCPC R DCPC R SPC ESS BUS ESS BUS BAT BUS CTRL VALVES REV 2 Volume 2 Flight Crew Operating Manual May 06/2005 REV 2 CSP 100-6 01-04-12...
Page 61: Control Wheel
DOUBLE ACTING SYNCHRONIZATION PITCH/ROLL AND SWITCH TRIM ARMING MASTER CHECKLIST LINE DISCONNECT ADVANCE SWITCH SWITCH TRANSPONDER ID SWITCH (LOCATED BEHIND) MICROPHONE SWITCH INPH (LOCATED BEHIND) REV 1 Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 01-04-13...
Page 63: Passenger Door
The passenger door is normally closed electrically using an inside or outside switch. The door can be opened or closed man- ually. PASSENGER DOOR (INSIDE) SWITCH DOOR SEAL (OUTSIDE) DOOR HANDLE SUPPORT STRUT HANDRAIL (OUTSIDE) AIRSTAIR SWITCH SUPPORT STRUT (INSIDE) REV 1 DOOR LEVER Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 01-05-01...
Page 64 The door seal also keeps water out of the fuselage if ditching occurs. (INSIDE) SWITCH DOOR SEAL PULLEY HAND-OPERATED CABLE ASSEMBLY (OUTSIDE) DOOR SWITCH PANEL ACTUATOR HANDRAIL HINGE POINT LIFTING CABLE HANDRAIL STABILIZER Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 01-05-02...
Page 65 To lock the door, rotate the inside handle downward until it stops. When the door is closed, a green flag indicator shows through the window in the handle. Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1...
Page 66: Door Latching Mechanism
- The aircraft is on the ground with the left engine run switch in the On position - The aircraft is in flight and the passenger door rollers are not fully engaged into the fitting guides REV 1 Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6...
Page 67: Emergency Exit
Place the hatch clear of the exit to allow passage. SECURITY PIN LOCKING PINS LATCH HANDLE HAND HOLD HINGES REV 1 Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 01-05-05...
Page 68: Emergency Exit Annunciations
- Switch panels for cabin lighting and entertainment system - 115V 60 Hz electrical outlet and fax/modem port (location depending on cabin layout) - VIP switch (location depending on cabin layout) Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6...
Page 69 NORMAL to PURGE. This opens a solenoid valve allowing overboard draining of the water system. The switch is REV 2 located behind the facial tissue dispenser on the upper vanity cabinet. Refer to the Cabin Handbook for further description. May 06/2005 Flight Crew Operating Manual Volume 2 REV 2 CSP 100-6...
Page 70: Cargo Bay Door
A CARGO DOOR (C) CAS message is displayed if the aircraft is on the ground and the left engine run switch is selected REV 7 ON. Otherwise, CARGO DOOR (S) CAS message is illuminated. Volume 2 Flight Crew Operating Manual Dec 05/2006 REV 7 CSP 100-6...
Page 71: Service Doors
CONTROL-PANEL GROUND-POWER DOOR DOOR LAVATORY- WASTE SERVICE DOOR REFUEL/DEFUEL DOOR PASSENGER DOOR SWITCH PANEL COMMUNICATION PANEL DOOR OUTFLOW VALVE DOOR BATTERY DOOR GROUND-AIR SERVICING DOOR REV 1 Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 01-05-09...
Page 72 The ground-air servicing door is located right of the centerline toward the rear of the fuselage, and allows access to the ground air servicing connection. REV 1 Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 01-05-10...
Page 73: Service Doors
LEVER AFT EQUIPMENT BAY DOOR ANNUNCIATION An AFT EQPT BAY DOOR (C) CAS message is displayed if the aft equipment bay door is not closed. REV 1 Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 01-05-11...
Page 74: Door Warning System
A magnet with an electronic proximity sensor is mounted at each door. The proximity sensors interface with the proximity sensor electronic unit (PSEU), data concentrator unit (DCU), and the multifunction display. The flight crew receives a sin- gle chime and a visual CAS annunciation if a door is not in the correct position under specific conditions. For the specific conditions, refer to the annunciation description for each door in this section.
Page 75: Eicas Messages
The electronic proximity sensor is indicating that PASSENGER DOOR TO/LAND the passenger door is not in the correct position position when the airplane is in on the ground REV 4 Sep 14/2005 Flight Crew Operating Manual Volume 2 REV 4 CSP 100-6 01-05-13...
Page 76 Challenger 300 Flight Crew Operating Manual - Volum REVISION 1...
Page 77 Automatic Pressurization Modes ................02-04-02 Manual Pressurization Mode ..................02-04-03 Pressurization Schedule — Climb and Cruise ............02-04-04 Pressurization Schedule — Descent and Hold (<25 000 ft)........02-04-04 REV 1 Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 02-00-01...
Page 78 Takeoff and Return to Base ..................02-04-08 Takeoff from Airfield Above 7850 ft and Landing Field Elevation Less Than 7850 ft ..........02-04-08 ECS Synoptic Page ....................02-04-09 EICAS Messages ........................ 02-04-10 Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 02-00-02...
Page 79: Rev 1
Aircraft pressurization is accomplished by regulating the overboard discharge of the conditioned air. Ventilation is provided for the electronic equipment on the flight deck and avionics racks. REV 1 Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6...
Page 81: Bleed Air System
(IASC) which processes the information for display on the EICAS. CONDITIONING BLEED SYSTEM SYSTEM (IP) GROUND ENGINE SOURCES STARTING BLEED ANTI-ICING ENGINES SYSTEM SYSTEM (HP) INTEGRATED EICAS AIR SYSTEM CONTROLLER DISTRIBUTION INDICATING SUPPLY REV 1 Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 02-02-01...
Page 82: Bleed Air Distribution
15 °C to 35 °C in normal mode and 10 °C to 70 °C in manual mode. AIR COND / BLEED CABIN COCKPIT MAN TEMP COLD COLD AIR SOURCE NORM RAM AIR PACK ONLY TRIM AIR ONLY L BLEED R BLEED XBLEED Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 02-02-02...
Page 83 - Power is lost to valves - Associated ENG FIRE switch is selected - Bleed air valves are selected closed at the ANTI-ICE control panel via the WING switch. Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6...
Page 84 BLEED AIR SYSTEM FROM/TO BLEED DIFFUSER SYSTEMS STARTER MOTOR FROM/TO AIRCRAFT SYSTEMS GENERATOR LOW OIL-PRESSURE SWITCH PUMP FUEL CONTROL UNIT AIR INLET INLET AIR BLEED AIR ELECTRICAL CIRCUITS Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 02-02-04...
Page 85: Bleed Air Management
APU. When the load control valve is open, the ECU adjusts the butterfly plate position to supply the correct quantity of bleed air. These adjustments are controlled by the required quantity of the bleed air load and the APU exhaust gas temperature. Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6...
Page 86: Bleed Air Leak Detection System
The bleed air ducts are constructed of stainless steel, titanium or aluminum and wrapped with insulation. A series of vent holes in the duct covers direct escaping bleed air to the sensing loops in the event of a bleed air leak. Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1...
Page 87: Trim Air System
Channel B is dedicated to wing anti-ice control and monitoring, bleed leak detection and limited backup control of the air conditioning system. IASC 1 channel B also has a backup cabin pressure sensor. REV 1 Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6...
Page 88 (ATS) receive sufficient airflow for starter operation. When the start valve closes, the air source returns to the previous selection. DUAL HEAT EXCHANGER WATER EXTRACTOR REHEATER/ CONDENSER PLENUM AIR CYCLE MACHINE TEMPERATURE CONTROL VALVE Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 02-03-02...
Page 89 Controls for the air conditioning system are located at the AIR COND/BLEED panel on the center pedestal. AIR COND / BLEED CABIN COCKPIT MAN TEMP COLD COLD AIR SOURCE NORM RAM AIR PACK ONLY TRIM AIR ONLY L BLEED R BLEED XBLEED Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 02-03-03...
Page 90 10 000 ft, selecting the guarded RAM AIR switch to ON opens the ram air valve to provide air flow into the aircraft. RAM AIR — Used to provide ambient air to ventilate the cockpit and cabin, in the event of PACK and RAM AIR TRIM AIR failure. Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 02-03-04...
Page 91 Cockpit exhaust air to the under-floor area and outflow valve is ensured through holes in the cockpit floor and center pedestal. Air circulation is also provided at the back of the cockpit displays through specially designed grilles. Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6...
Page 92 Intermediate Pressure Bleed Aair Ram Air 1- Flow Control Valves 2- Pack Valve Conditioned Air 3- Precooler Crossover Valve Cold Air Precooled Air 4- Trim Air Valve Volume 2 Flight Crew Operating Manual May 06/2005 REV 2 CSP 100-6 02-03-06...
Page 93 UPPER DISTRIBUTION DUCT LOWER DISTRIBUTION DUCT FROM PACK COCKPIT DISTRIBUTION DUCT CABIN DISTRIBUTION SYSTEM SIDE VIEW CABIN LAVATORY CARGO ENTRY WAY COCKPIT GASPERS FROM PACK REV 1 Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 02-03-07...
Page 94 PATH CABIN CABIN SUPPLY SUPPLY DUCTS DUCTS COCKPIT SUPPLY DUCT COCKPIT AND CABIN GASPERS SUPPLY COCKPIT CONDITIONED AIR SUPPLY CABIN CONDITIONED AIR SUPPLY EXHAUST PATH EV 2 Volume 2 Flight Crew Operating Manual May 06/2005 REV 2 CSP 100-6 02-03-08...
Page 95 IASC 2 is activated and the avionics fan is turned on. If the fan has failed, then the avionics valve opens. AVIONICS EXHAUST TO AVIONICS VALVE TO OVERFLOW VALVE CABIN DISPLAY DOOR UNITS DISPLAYS AVIONICS RACK COCKPIT OUTFLOW CHECK VALVE VALVE AVIONICS REV 1 VALVE Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 02-03-09...
Page 96: Cabin And Cockpit Air Distribution System
CABIN and COCKPIT AIR DISTRIBUTION SYSTEM RAM AIR GROUND TO OUTFLOW INLET CONNECT VALVE PACK FROM RAM AIR EXHAUST AVIONICS COOLING COCKPIT SUPPLY FLOOR DISTRIBUTION TOP DISTRIBUTION GASPERS REV 2 Volume 2 Flight Crew Operating Manual May 06/2005 REV 2 CSP 100-6 02-03-10...
Page 97 If a negative pressure condition develops (ambient pressure is greater than cabin pressure), the safety valves automatically open to equalize cabin pressure. REV 1 Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 02-04-01...
Page 98 After landing or after an aborted takeoff, the cabin will depressurize at a rate of 500 sea level feet to equalize cabin, then OFV will go to full open and remain in that configuration while on ground. Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1...
Page 99 1 psid (maximum allowed for landing). AFTER LANDING After landing, depressurize the aircraft by adjusting the MAN RATE switch toward the UP position until field elevation is attained. Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 02-04-03...
Page 100 13 000 31 000 3873 14 000 1022 32 000 4291 Note: For holding above 25 000 ft following descent, the pressurization schedule for Climb and Cruise applies. Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 02-04-04...
Page 101 The sequence activates automatically, and is inhibited above 15 000 ft. NOTE: The ditching function is not available in manual mode. To close the outflow valve, turn the MAN RATE knob to max down. Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6...
Page 102 The warning and caution thresholds will continue to decrease at a rate of -300 fpm until the caution threshold of 8500 ft and the warning threshold reaches 9400 ft. Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6...
Page 103 LANDING ELEVATION 7850 ft MAX > - 7850 ft CABIN ALTITUDE TIME CABIN CLIMB RATE TAKEOFF ACCORDING TO ELEVATION CLIMB SCHEDULE < - 7850 ft CABIN PREPRESSURIZED Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 02-04-07...
Page 104 500 ft MIN THROTTLES FOR > 10 SEC ADVANCED TIME 7850 ft MAX CABIN ALTITUDE TAKEOFF LANDING ELEVATION ELEVATION 10 000 ft 7000 ft DESCENT RATE 300 fpm Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 02-04-08...
Page 105 118.000 108.00 7777 1799.5 118.000 118.000 2.0000 STBY 2.0000 118.000 118.000 108.00 190.0 118.000 AUTO PLAN SKIP SHLDR SIDE CKLST FRMT TR/WX SUMRY ENTER FUEL A/ICE ELEC Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 02-04-09...
Page 106 + 650 ft with a maximum limit of 14 300 ft Either the pressure sensor has failed or cabin CABIN PRESS FAULT TO/LAND altitude limiter function has failed Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 02-04-10...
Page 107 The RAM AIR ventilation valve has failed to RAM AIR FAIL TO/LAND move to the commanded position AIR COND MAN TEMP The air conditioning temperature control is in manual mode REV 4 Sep 14/2005 Flight Crew Operating Manual Volume 2 REV 4 CSP 100-6 02-04-11...
Page 108 The AIR SOURCE switch is in the TRIM AIR ONLY position, resulting in all air conditioning TRIM AIR ONLY bleed air being routed through the trim air sys- tem. The air will be warm Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 02-04-12...
Page 109 ECS Synoptic Page ....................03-04-03 Electrical Synoptic Page .................... 03-04-04 Flight Controls Synoptic Page..................03-04-05 Fuel Synoptic Page....................03-04-06 Hydraulic Synoptic Page.................... 03-04-07 EICAS Messages ........................ 03-05-01 REV 1 Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 03-00-01...
Page 111 The maintenance diagnostic computer (MDC) is used to record engine and line replaceable unit (LRU) status and param- eters. MDC data can be downloaded for system diagnosis and fault identification. REV 1 Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6...
Page 113: Engine Indicating And Crew Alerting System (Eicas)
- Green — Normal operation for digital values. Normal flow, energy or pressure in flowlines - White — Normal status of component (pump, valve, etc.) or no flow through the flowline - Magenta — Invalid or unknown data Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6...
Page 114 - FIRE DET — tests the fire detection and extinguishing (FIREX) system - TAWS — tests the terrain avoidance warning system SYSTEMS TEST ANNUN A ANNUN B PUSH TAWS PROBES TEST STALL/RUD LIM FIRE DET ICE DET Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 03-02-02...
Page 115 AURAL/VISUAL ALERTS ENGINE INDICATING AND CREW ALERTING SYSTEM (EICAS) (Cont) Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 03-02-03...
Page 116 These should only be used if problems with the aural warning system is encountered, or as directed by AFM procedure AURAL WARNING DCU A DCU B Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 03-02-04...
Page 117 ELEC L/R TOGGLE The L/R toggle switch allows the flight crew to select control to the left or right MFDs. Pressing the CAS switch once removes the caution, advisory, and status messages, and a white MSGS icon will display. Pressing the CAS switch a second time causes the messages to reappear.
Page 118 Aileron, horizontal stabilizer and rudder trim indications are green when trims are set in the takeoff range when on the ground and in red for a configuration warning. In flight, the indicators are white. Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1...
Page 119 Caution messages require prompt action and are always accompanied by: - Single chime - Flashing master caution lights Pressing either master caution switch: - Stops the flashing of the master caution lights REV 1 Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 03-02-07...
Page 120 The electrical synoptic page displays the system using a block diagram. FLIGHT CONTROLS The flight control synoptic page displays the positions of the ailerons, elevator, rudder and spoilers. Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6...
Page 121 L-PFD displays compressed format. L-MFD is shut down. NORM L-PFD format is normal. L-MFD format is normal. MFD REV REV 1 L-PFD is shut down. L-MFD displays compressed format. Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 03-02-09...
Page 122 Tuning is normal and can be done through the MFDs or the CDUs as desired. CDU ONLY REV 1 Tuning of the radios enabled only by CDUs. Tuning by the MFD is disabled. Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 03-02-10...
Page 123: Integrated Avionics Processor System (Iaps)
IAPS environment in each half of the IAPS. The IEC has a power supply, two thermostats, two transducer monitor circuits, a two-speed fan, and a heat exchanger. REV 1 Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6...
Page 124: Cockpit Voice Recorder
ON and the hydraulic system is pressurized. To prevent accidental erasures, a time delay circuit makes it necessary to depress the switch for two seconds to start the erasure process. Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6...
Page 125 ROLL DISCONNECT Triple Chime “CONFIGURATION” TRIM AIR LEAK TO/LAND Triple Chime None WING ANTI-ICE LEAK TO/LAND Triple Chime None L (R) WING OVERHEAT Triple Chime None REV 1 Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 03-03-01...
Page 126 TO/LAND ICE DETECTOR FAIL TO/LAND EMER LIGHTS ON TO/LAND L (R) INBD BRAKE FAIL EMERGENCY EXIT TO/LAND INBD BRAKE PRESS LO L (R) ENG ANTI-ICE FAIL TO/LAND Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 03-03-02...
Page 127 L (R) PROBE HEAT OFF TO/LAND WOW FAIL L (R) PYLON LOOP FAIL TO/LAND XBLEED FAIL TO/LAND L (R) REVERSER FAIL YAW DAMPER FAIL TO/LAND ROLL SPOILERS FAIL Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 03-03-03...
Page 128 FIREX BTL 1 (2) FAULT TO/LAND TAWS WINDSHEAR FAIL TO/LAND FIREX BTL 1 (2) LOW TO/LAND WING ANTI-ICE FAULT TO/LAND FLAPS RATE LOW TO/LAND WING SOURCE-XBLEED TO/LAND Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 03-03-04...
Page 129 WING ANTI-ICE ON FUEL XFER OPEN WING/ENG ANTI-ICE ON L (R) GEN OFF WING SOURCE-XBLEED GND SPOILERS OFF YAW DAMPTER OFF HYD PUMP NOT AUTO XBLEED OPEN Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 03-03-05...
Page 130 LEFT (R) INBD BRAKE FAIL TONE INBD BRAKE FAIL TONE INBD BRAKE PRESS LO TONE LEFT (R) FADEC FAIL TONE FIRE SYS FAULT TONE FIREX APU SQUIB FAIL TONE Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 03-03-06...
Page 131 PRI STAB TRIM FAIL TONE LEFT (R) REVERSER FAIL TONE LEFT (R) REVERSER UNSAFE TONE MACH TRIM FAIL TONE ROLL DISCONNECT VOICE MESSAGE ROLL SPOILERS FAIL TONE Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 03-03-07...
Page 132 TONE LEFT (R) STARTER FAIL TONE LEFT (R) STARTER FAIL ON TONE TRIM CLACKER TONE VERTICAL TRACK ALERT TONE WING FUEL TEMP LOW TONE WOW FAIL TONE Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 03-03-08...
Page 133 1200 1799.5 118.000 118.000 2.0000 STBY 118.000 108.00 190.0 2.0000 118.000 118.000 AUTO PLAN CKLST SKIP SHLDR SIDE REV 1 FRMT TR/WX ENTER SUMRY A/ICE ELEC FUEL Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 03-04-01...
Page 134 118.000 108.00 7777 1799.5 118.000 118.000 2.0000 STBY 2.0000 118.000 118.000 108.00 190.0 118.000 AUTO PLAN SKIP SHLDR SIDE CKLST FRMT TR/WX SUMRY ENTER A/ICE ELEC FUEL Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 03-04-02...
Page 135 118.000 108.00 7777 1799.5 118.000 118.000 2.0000 STBY 2.0000 118.000 118.000 108.00 190.0 118.000 AUTO PLAN SKIP SHLDR SIDE CKLST FRMT TR/WX ENTER SUMRY FUEL A/ICE ELEC Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 03-04-03...
Page 136 118.000 108.00 1200 1799.5 118.000 118.000 2.0000 STBY 118.000 108.00 190.0 2.0000 118.000 118.000 AUTO PLAN SKIP SHLDR SIDE CKLST FRMT TR/WX SUMRY ENTER A/ICE ELEC FUEL Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 03-04-04...
Page 137: Flight Controls Synoptic Page
118.000 108.00 1200 1799.5 118.000 118.000 2.0000 STBY 2.0000 118.000 118.000 108.00 190.0 118.000 AUTO PLAN SHLDR SIDE CKLST SKIP FRMT TR/WX SUMRY ENTER A/ICE ELEC FUEL Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 03-04-05...
Page 138 118.000 108.00 1200 1799.5 118.000 118.000 2.0000 STBY 2.0000 118.000 118.000 108.00 190.0 118.000 AUTO PLAN SKIP SHLDR SIDE CKLST FRMT TR/WX ENTER SUMRY FUEL A/ICE ELEC Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 03-04-06...
Page 139 118.000 108.00 1200 1799.5 118.000 118.000 2.0000 STBY 2.0000 118.000 118.000 108.00 190.0 118.000 AUTO PLAN SKIP CKLST SHLDR SIDE FRMT TR/WX SUMRY ENTER A/ICE ELEC FUEL Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 03-04-07...
Page 141 The respective AURAL WARNING DCU A or AURAL WARN A (B) DCU B switch has been selected, muting all MUTED warnings through that channel REV 1 Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 03-05-01...
Page 143 Autopilot Takeoff Configuration Warning..............04-01-23 Yaw Damper........................04-01-23 Description ......................... 04-01-23 Controls and Indications...................... 01-01-24 Description ......................... 01-01-24 PFD Messages........................04-01-25 EICAS Messages ........................ 04-01-27 REV 2 May 06/2005 Flight Crew Operating Manual Volume 2 REV 2 CSP 100-6 04-00-01...
Page 145 The automatic flight control system (AFCS) provides a means of automatically controlling the aircraft flight path. The AFCS reduces the flight crew workload by providing steering commands through the flight director or automatically flying the aircraft through the autopilot. The main functions of the AFCS are:...
Page 146 DESCRIPTION The flight directors display flight guidance cues on the attitude indicators, thereby assisting the flight crew in maintaining a specified flight path. The flight guidance cues are displayed in the form of flight director command bars. The crew can choose to hand fly the aircraft with "raw data"...
Page 147: Cross-Pointer Command Bars
Active modes are displayed in green on the top line and armed modes are displayed in white on the bottom line. ROLL AP YD PITCH ALTS 16000 11 : 42 ° C 29.92 IN ° C May 06/2005 Flight Crew Operating Manual Volume 2 REV 2 CSP 100-6 04-01-03...
Page 148: Flight Guidance Panel (Fgp)
FLC (flight level change) button — Depressing the FLC button engages the flight level change mode, which sycronizes on engagement to the current airspeed/mach. The speed reference can then be changed with the SPEED knob. Pushing the FLC switch again disengages the mode. Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6...
Page 149 YD. XFR (transfer) button — Selects the desired flight director (left or right) to command the autopilot. Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6...
Page 150: Flight Director Synchronization
FD is off. AUTOPILOT SYNCHRONIZATION SWITCH INPH TAKE-OFF/GO AROUND (TO/GA) SWITCH THRUST REVERSER LEVER IDLE IDLE TO/GA TO/GA TOGA SWITCH (2) L ENGINE R ENGINE EV 2 Volume 2 Flight Crew Operating Manual May 06/2005 REV 2 CSP 100-6 04-01-06...
Page 151: Flight Director Lateral Modes
ROLL mode is annunciated by a green ROLL in the active lateral field of the PFD. ROLL AP YD PTCH ALTS 16000 11 : 42 4200 ° C 29.92 IN ° C May 06/2005 Flight Crew Operating Manual Volume 2 REV 2 CSP 100-6 04-01-07...
Page 152 Heading mode is indicated by a green HDG in the active lateral field of the PFD. AP YD PTCH 16000 11 : 42 4200 ° C 29.92 IN ° C Volume 2 Flight Crew Operating Manual May 06/2005 REV 2 CSP 100-6 04-01-08...
Page 153 FMS is the selected NAV source. LNV 1 AP YD 16000 11 : 42 4200 ° C 29.92 IN ° C REV 2 May 06/2005 Flight Crew Operating Manual Volume 2 REV 2 CSP 100-6 04-01-09...
Page 154: Autopilot Engagement
Selection of GA causes the flight directors to operate independently. Selection of GA mode disengages the autopilot (but not the Yaw Damper), and clears all other existing modes. ALTS 16000 11 : 42 4200 ° C 29.92 IN ° C EV 2 Volume 2 Flight Crew Operating Manual May 06/2005 REV 2 CSP 100-6 04-01-10...
Page 155 The capture point is independently determined for each FGC. 1/2 Bank mode is automatically deselected when APPR mode is selected. APPR VOR1 AP YD 16000 11 : 42 4200 ° C 29.92 IN ° C Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 04-01-11...
Page 156 NAV source and also green in the lateral arm field, which identifies the armed NAV source (B/C1 or B/C2). APPR B/C 2 AP YD ALTS 16000 11 : 42 4200 ° C 29.92 IN ° C Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 04-01-12...
Page 157: Flight Director Vertical Modes
Vertical modes are armed or activated by switches or a UP/DOWN wheel on the flight guidance panel or TOGA switches on the thrust levers. Disabling the active vertical mode is accomplished by pushing the active FGP push button or by selecting another vertical mode. REV 2 May 06/2005 Flight Crew Operating Manual Volume 2 REV 2 CSP 100-6 04-01-13...
Page 158 Pitch Mode is annunciated by PTCH in green in the vertical capture field. ROLL PTCH 16000 11 : 42 4200 ° C 29.92 IN ° C Volume 2 Flight Crew Operating Manual May 06/2005 REV 2 CSP 100-6 04-01-14...
Page 159 In addition to altitude preselect being set with the altitude preselect knob, a FMS flight path target altitude can be programmed for use with VNAV. In the VNAV glide path capture mode, capturing the preselected altitude is prohibited. May 06/2005 Flight Crew Operating Manual Volume 2 REV 2 CSP 100-6...
Page 160 - ALTV in green color in the vertical capture field — track ALTS AP YD VS 2000 16000 11 : 42 4200 ° C 29.92 IN ° C Volume 2 Flight Crew Operating Manual May 06/2005 REV 2 CSP 100-6 04-01-16...
Page 161 - Rotating the UP/DOWN wheel, which selects Pitch Hold The GA Mode generates a 10° pitch up command. This mode is annunciated by a green GA in the lateral and vertical capture field. REV 1 Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 04-01-17...
Page 162 - Selecting TO or GA mode - Changing the source of the active VNAV data - By pressing the VNAV mode button on the FGP EV 2 Volume 2 Flight Crew Operating Manual May 06/2005 REV 2 CSP 100-6 04-01-18...
Page 163 - Changing the XFR side when APPR is armed. - The FDs are turned off while the AP disengages. Glideslope arm is annunciated by the white GS message in the vertical (arm) field on the PFD. May 06/2005 Flight Crew Operating Manual Volume 2 REV 2 CSP 100-6...
Page 164 PFD. Glide path capture is annunciated by the green GP in the vertical capture field on the PFD. AP YD PTCH APPR LOC2 ALTV FLC 16000 11 : 42 4200 ° C 29.92 IN ° C Volume 2 Flight Crew Operating Manual May 06/2005 REV 2 CSP 100-6 04-01-20...
Page 165 When an out-of-trim condition is sensed in the pitch axis, the FGC signals the horizontal stabilizer trim control unit to re- position the horizontal stabilizer. May 06/2005 Flight Crew Operating Manual Volume 2 REV 2 CSP 100-6...
Page 166 AUTOMATIC FLIGHT CONTROL SYSTEM AUTOPILOT (Cont) Volume 2 Flight Crew Operating Manual May 06/2005 REV 2 CSP 100-6 04-01-22...
Page 167: Yaw Damper
The AP/YD DISC switch, YD switch and control wheel disconnect switches will disengage the yaw damper. When a yaw damper channel fails or disconnects, the amber YAW DAMPER FAIL CAS message is displayed. May 06/2005 Flight Crew Operating Manual Volume 2 REV 2...
Page 168 SWITCH TRIM ARMING MASTER CHECKLIST LINE DISCONNECT ADVANCE SWITCH SWITCH TRANSPONDER ID SWITCH (LOCATED BEHIND) MICROPHONE SWITCH INPH (LOCATED BEHIND) ROLL AP YD PITCH ALTS EV 5 Volume 2 Flight Crew Operating Manual Feb 22/2006 REV 5 CSP 100-6 04-01-24...
Page 169 Flight level change mode (on the vertical capture field) Green Lateral Go-Around Mode (in lateral capture field) EV 4 Green Vertical Go-Around Mode (in vertical capture field) Sep 14/2005 Flight Crew Operating Manual Volume 2 REV 4 CSP 100-6 04-01-25...
Page 170 (the line is drawn through the active lateral tion symbol(s) mode annunciation) A required data source is invalid, for the active vertical outer loop (the line is drawn through the active vertical mode annunciation) Volume 2 Flight Crew Operating Manual Sep 14/2005 REV 4 CSP 100-6 04-01-26...
Page 171 TO/LAND The yaw damper has failed FD 1 FAIL The respective flight director has failed TO/LAND FD 2 FAIL accompanied by an FD flag on the PFD May 06/2005 Flight Crew Operating Manual Volume 2 REV 2 CSP 100-6 04-01-27...
Page 172 TO/LAND The yaw damper has failed FD 1 FAIL The respective flight director has failed TO/LAND FD 2 FAIL accompanied by an FD flag on the PFD Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 04-01-28...
Page 173 Air Cond/Bleed Control Panel ..................05-01-10 Electrical Control Panel....................05-01-11 Electrical Synoptic Page .................... 05-01-12 ECS Synoptic Page ....................05-01-13 REV 2 Fuel Synoptic Page....................05-01-14 EICAS Messages ........................ 05-01-15 May 06/2005 Flight Crew Operating Manual Volume 2 REV 2 CSP 100-6 05-00-01...
Page 175 The APU-driven air-cooled DC generator also has a NACA inlet for cooling air flow. The air is pulled through the generator and dumped in the APU compartment. This air is then exhausted overboard via the APU exhaust eductor. LOCATION REV 1 Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 05-01-01...
Page 176 AUXILIARY POWER UNIT APU ACCESS PANEL LOCATIONS SIDE ACCESS PANEL BOTTOM ACCESS PANEL Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 05-01-02...
Page 177 FROM/TO BLEED DIFFUSER SYSTEMS STARTER MOTOR FROM/TO AIRCRAFT SYSTEMS GENERATOR LOW OIL-PRESSURE SWITCH PUMP FUEL CONTROL UNIT AIR INLET INLET AIR BLEED AIR ELECTRICAL CIRCUITS REV 2 May 06/2005 Flight Crew Operating Manual Volume 2 REV 2 CSP 100-6 05-01-03...
Page 178: Power Section And Gearbox
- Fuel control unit and high-pressure pump The APU gearbox also serves as a sump for the lubrication system and incorporates the oil gravity fill cap and quantity sightglass. Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6...
Page 179: Air Intake And Exhaust
COMPONENTS AND OPERATION The oil pump directs filtered oil under pressure to the APU bearings, gearbox, and generator bearings. Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 05-01-05...
Page 180 No Acceleration (during start)* Loss of EGT Signal* Overspeed Low Oil Pressure* Emergency Fire High Oil Temperature* Internal ECU Failure Overtemperature* Loss of Overspeed Protection Circuit No Flame (during start)* Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 05-01-06...
Page 181: Start And Ignition
R BATT to the R ESS BUS on the Electrical synoptic page is depicted in white. The ignition system is energized at 5% APU rpm and stays energized until 95% rpm. REV 2 May 06/2005 Flight Crew Operating Manual Volume 2 REV 2 CSP 100-6...
Page 182: Pneumatic Supply
For the ECU to energize the bleed-air supply system, the APU must be more than 95% of its maximum speed. BLEED AIR LIMITATIONS Refer to the Approved Airplane Flight Manual for bleed air limitations. Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6...
Page 183 APU system operation and fault presentation is provided on the EICAS pages. The FUEL, ECS, ELECTRICAL synoptic pages monitor the APU system and services. START EXTERNAL POWER CONTROL PANEL Lamp APU Shutdown Service EXT DC Test AVAIL IN USE EXTERNAL POWER CONTROL PANEL Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 05-01-09...
Page 184 AIR COND / BLEED CABIN COCKPIT MAN TEMP COLD COLD AIR SOURCE NORM RAM AIR PACK ONLY TRIM AIR ONLY L BLEED R BLEED XBLEED REV 1 Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 05-01-10...
Page 185 AVAIL STBY HYD GEN INST BUS TIE L ESS R ESS L MAIN L AUX R MAIN R AUX L GEN APU GEN R GEN REV 2 May 06/2005 Flight Crew Operating Manual Volume 2 REV 2 CSP 100-6 05-01-11...
Page 186 118.000 108.00 1200 1799.5 118.000 118.000 2.0000 STBY 118.000 108.00 190.0 2.0000 118.000 118.000 AUTO PLAN SHLDR SIDE CKLST SKIP TR/WX FRMT ENTER SUMRY A/ICE ELEC FUEL Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 05-01-12...
Page 187 118.000 108.00 7777 1799.5 118.000 118.000 2.0000 STBY 118.000 118.000 108.00 190.0 2.0000 118.000 AUTO PLAN CKLST SKIP SHLDR SIDE TR/WX FRMT ENTER SUMRY A/ICE ELEC FUEL Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 05-01-13...
Page 188 118.000 108.00 1200 1799.5 118.000 118.000 2.0000 STBY 118.000 108.00 190.0 2.0000 118.000 118.000 AUTO PLAN SKIP SHLDR SIDE CKLST TR/WX FRMT ENTER SUMRY A/ICE ELEC FUEL Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 05-01-14...
Page 189 APU electronic control unit - Reverse flow has been detected The auxiliary power unit electronic control unit APU SHUTDOWN TO/LAND has shut down the APU for protective reasons Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 05-01-15...
Page 191 CVR Control Panel..................... 06-01-14 Area Microphone......................06-01-15 Recorder Unit......................06-01-15 Emergency Locator Transmitter ..................06-01-16 Description ......................... 06-01-16 Cabin Communication System (Optional) ................06-01-16 REV 1 Description ......................... 06-01-16 Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 06-00-01...
Page 192 Flight Data Recorder (FDR) (Optional)................06-01-17 Description ......................... 06-01-17 Components and Operation..................06-01-17 Recorder Unit......................06-01-17 Underwater Locator Device (ULD)................06-01-17 Tri-Axial Accelerometer....................06-01-17 EICAS Messages ........................ 06-01-18 Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 06-00-02...
Page 193 The EMER/NORM is a two position locking toggle switch. In the NORM position, the audio system operation is normal. In the EMER position, the audio is routed directly to the headphones. Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1...
Page 194 The pilot and copilot’s control wheels are equipped with TX/INPH momentary switches. The TX position allows transmitting on the selected radio. The INPH position allows intercom transmissions when the in- terphone is selected off on the ACP. INPH Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 06-01-02...
Page 195 HEADSET JACK PLUGS Headset panels are available at the two flight deck positions to connect the headsets to the audio system. HDPH PILOT AND COPILOT HEADPHONE JACK PANEL Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 06-01-03...
Page 196 Two speakers are located overhead in the flight compartment. The speaker volume can be adjusted by rotating the SPKR knob. The speaker can be selected off by pressing the SPKR knob in. FLIGHT COMPARTMENT LOUDSPEAKER (2) Volume 2 Flight Crew Operating Manual May 06/2005 REV 2 CSP 100-6...
Page 197 - Left side of the aircraft in the nose compartment area (accessible behind the communication access door - Left side of the aft equipment compartment NOSE-COMPARTMENT SERVICE-INTERPHONE UNIT AFT-COMPARTMENT SERVICE-INTERPHONE UNIT Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 06-01-05...
Page 198: Vhf Communication
NOTE: The menu is automatically removed 20 seconds after the last activity of the MENU, DATA, or PUSH SELECT knob, or when another menu or list button is pushed. Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6...
Page 199 DATA mode is selected, the squelch annunciation, squelch status, transfer arrow, frequency selections 8.33 and 25, and TEST selection do not show on the COM 3 CONTROL menu REV 1 Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6...
Page 200 4. To return to the TUNE page from a CONTROL submenu, push the line select key for the radio or push the TUN key. Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6...
Page 201: Tuning Reversion
This minimizes the tuning times for frequently used frequencies. HF ANTENNA The HF antenna is classified as a conformal-type antenna in that it is an integral part of the leading edge of the vertical stabilizer. Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 06-01-09...
Page 202 6. To return to the TUNE page from a submenu, push the line select key for the radio or push the TUN key. Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6...
Page 203: Selcal System (Optional)
(AFIS), that provides data on aircraft conditions, departure time, arrival time, or flight delay time). The GES can also trans- mit telephone communications (such as voice, fax, and PC modem data). Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1...
Page 204: Data Link (Optional)
Data link operation is via the VHF, HF, or SATCOM and is controllable from the FMS CDU. The system utilizes the same data loading unit as the FMS with air-ground-air and air-to-air capabilities. Crew advisory messages are displayed on the CDU scratch pad. Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6...
Page 205: Static Wicks
Static wicks are installed to discharge static electricity, thereby reducing radio interference. They are installed at the fol- lowing locations: - Winglets/wingtips and ailerons - Elevators, rudder, vertical stabilizer, horizontal stabilizer and tail cone STATIC WICK Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 06-01-13...
Page 206: Cockpit Voice Recorder (Cvr)
When the erase button is pushed, all recorded information will be erased as long as the aircraft is on the ground, the hy- draulic systems are pressurized and the parking brake is set. COCKPIT VOICE RECORDER HOLD 5 SEC TEST HEADSET ERASE EV 1 Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 06-01-14...
Page 207 The unit is equipped with a battery having a life expectancy of 6 years. Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1...
Page 208: Emergency Locator Transmitter
An ELT buzzer is installed in the rear fuselage section near a venting cutout. It is installed so that the buzzer alarm will not distract the flight crew, but will be audible during ground operations and servicing when the engines are not operating.
Page 209 The tri-axial accelerometer is used for acceleration measurements. It contains three separate seismic sensors that measure vertical, lateral, and longitudinal acceleration near the center of gravity of the aircraft. This data is sent to the DCUs where it is formatted for the FDR. Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6...
Page 210 2, or 3 SELCAL VHF 3 The SELCAL code has been received on SELCAL DATALINK TO/LAND “SELCAL” DATALINK ELT ON Pilot status that ELT is transmitting EV 1 Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 06-01-18...
Page 211 Controls and Indications...................... 07-01-14 External Power Control Panel..................07-01-14 Electrical Summary Page................... 07-01-15 Electrical Control Panel....................07-01-16 Electrical Synoptic Page .................... 07-01-17 EICAS Messages....................... 07-01-18 REV 2 May 06/2005 Flight Crew Operating Manual Volume 2 REV 2 CSP 100-6 07-00-01...
Page 213 The electrical system incorporates a split, multiple bus system for power distribution interconnected by contactors, fuses, and circuit breakers. These react automatically to isolate a malfunctioning circuit. REV 1 Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6...
Page 214 DC CONTROL RIGHT CIRCUIT POWER CENTER PANEL BREAKER PANEL LEFT CIRCUIT GENERATOR LEFT SECONDARY BREAKER PANEL POWER CENTER LEFT DC RIGHT POWER CENTER BATTERY LEFT LEFT BATTERY GENERATOR Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 07-01-02...
Page 215: Electrical System
The GPU may be deselected with the same switch. The bus tie contactor automatically closes when a GPU is connected and selected ON. The entire DC system is powered, assuming the EXT PWR is selected ON. May 06/2005 Flight Crew Operating Manual Volume 2 REV 2 CSP 100-6...
Page 216 AVAIL STBY HYD GEN INST BUS TIE L ESS R ESS L AUX L MAIN R MAIN R AUX L GEN APU GEN R GEN EV 2 Volume 2 Flight Crew Operating Manual May 06/2005 REV 2 CSP 100-6 07-01-04...
Page 217 - Distribute the electrical power to secondary power centers located in the front fuselage of the aircraft - Protect distribution cables from short circuit Additionally, there is an Auxiliary Power Center for the APU Generator. REV 2 May 06/2005 Flight Crew Operating Manual Volume 2 REV 2 CSP 100-6 07-01-05...
Page 218: Secondary Power Centers
The pilot’s floor heater is connected to the left equipment rack circuit breaker panel, and the copilot’s floor heater is con- nected to the right equipment rack circuit breaker panel. Volume 2 Flight Crew Operating Manual May 06/2005 REV 2...
Page 219 DC PUMP PWR2 ANTI ICE L AOA L WINDSHIELD L PROBE L STBY L ICE L WING L ENG CTRL L PITOT STATIC CASE CTRL BLD LK VANE May 06/2005 Flight Crew Operating Manual Volume 2 REV 2 CSP 100-6 07-01-07...
Page 220 R WINDSHIELD R AOA STBY R PROBE R WING R ICE R STBY PITOT R PITOT CTRL EMER DOME R ENG BLD LK CTRL CASE VANE STATIC Volume 2 Flight Crew Operating Manual May 06/2005 REV 2 CSP 100-6 07-01-08...
Page 221 L CKPT CABIN WING MAP/ BCN/ COM 3 /PED SIGNS INSP STOW STROBE ENTRY INDICATING/RECORDING COMM DISPLAYS L PFD L MFD CLOCK R AUDIO CLOCK PWR 2 May 06/2005 Flight Crew Operating Manual Volume 2 REV 2 CSP 100-6 07-01-09...
Page 222 CABIN NOSE GEAR WING R CKPT LOGO TAXI CABIN STROBE /CBP CTRL INDICATING/RECORDING COMM COMPASS R MFD R PFD L AUDIO ADDRESS LIGHT PHONE PWR2 REV 2 Volume 2 Flight Crew Operating Manual May 06/2005 REV 2 CSP 100-6 07-01-10...
Page 223 ELECTRICAL REFUEL DEFUEL ENVIRONMENT L DCPC R DCPC R SPC BAG COMP HTR ESS BUS ESS BUS BATT BUS CTRL VALVES PWR 1 PWR 2 REV 2 May 06/2005 Flight Crew Operating Manual Volume 2 REV 2 CSP 100-6 07-01-11...
Page 224 ELECTRICAL DIRECT CURRENT SYSTEM (DC) DC ELECTRICAL SYSTEM Volume 2 Flight Crew Operating Manual May 06/2005 REV 2 CSP 100-6 07-01-12...
Page 225: Dc Primary Architecture
ESS BUS MAIN BUS AUX BUS RIGHT ESS BUS 1013.2 hPa STANDBY INSTRUMENT BATTERY CONTACTOR M. 47 29.92 in CAGE BARO FUSE STBY INST CIRCUIT SENSOR REV 1 Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 07-01-13...
Page 226 ELECTRICAL CONTROLS AND INDICATIONS EXTERNAL POWER CONTROL PANEL Lamp Service APU Shutdown EXT DC Test AVAIL IN USE EXTERNAL POWER CONTROL PANEL Volume 2 Flight Crew Operating Manual May 06/2005 REV 2 CSP 100-6 07-01-14...
Page 227: Electrical Summary Page
ELECTRICAL CONTROLS AND INDICATIONS (Cont) ELECTRICAL SUMMARY PAGE AUTO PLAN SKIP SHLDR SIDE CKLST TR/WX FRMT ENTER SUMRY A/ICE FUEL ELEC REV 1 Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 07-01-15...
Page 228 AVAIL STBY HYD GEN INST BUS TIE L ESS R ESS L AUX L MAIN R MAIN R AUX L GEN APU GEN R GEN REV 2 Volume 2 Flight Crew Operating Manual May 06/2005 REV 2 CSP 100-6 07-01-16...
Page 229 1200 1799.5 118.000 118.000 2.0000 STBY 118.000 108.00 190.0 2.0000 118.000 118.000 AUTO PLAN SKIP SHLDR SIDE CKLST FRMT TR/WX ENTER SUMRY A/ICE ELEC FUEL REV 1 Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 07-01-17...
Page 230 L (R) AUX BUS OFF TO/LAND Respective AUX BUS is selected off An electrical system fault occurred, resulting in ELECTRICAL FAULT TO/LAND loss of redundancy in the display of electrical indications Volume 2 Flight Crew Operating Manual Sep 14/2005 REV 4 CSP 100-6 07-01-18...
Page 231 The optional hydraulic motor driven generator ELEC HYD GEN ON (HMDG) has been activated L (R) GEN OFF The affected engine generator switch has been selected OFF REV 4 Sep 14/2005 Flight Crew Operating Manual Volume 2 REV 4 CSP 100-6 07-01-19...
Page 233 Overboard Discharge Indicator .................. 08-01-04 Oxygen Service Panel ....................08-01-05 Smoke Goggles ......................08-01-06 Flight Crew Oxygen Mask and Storage Cup.............. 08-01-06 Flight Crew Oxygen Mask Cold Weather Storage ............. 08-01-06 Crew Oxygen Mask....................08-01-07 Passenger Oxygen System....................08-01-09 Description ......................... 08-01-09 Components and Operation..................
Page 235 The following equipment is provided to deal with specific emergencies: Smoke goggles, personal breathing equipment, life vests, crash axe, flashlights, first aid kit and portable fire extinguishers. REV 1 Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6...
Page 236 TRANSDUCER TO THERAPEUTIC CIRCUIT OVERBOARD DISCHARGE INDICATOR OXYGEN CYLINDER 77 CU FT FILLER VALVE PRESSURE GAUGE OXYGEN PIPELINE ELECTRICAL SIGNAL LINE ELECTRICAL POWER LINE PNEUMATIC SIGNAL LINE Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 08-01-02...
Page 237: Oxygen System — Optional Configuration
DISCHARGE INDICATOR OXYGEN OXYGEN CYLINDER CYLINDER 77 CU FT 115 CU FT FILLER VALVE PRESSURE GAUGE OXYGEN PIPELINE ELECTRICAL SIGNAL LINE ELECTRICAL POWER LINE PNEUMATIC SIGNAL LINE Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 08-01-03...
Page 238 Should the contents be discharged overboard, the green overboard discharge indicator located above the oxygen servicing panel on the right side of the of the aircraft will be ruptured or missing. Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6...
Page 239 Replenishment of the oxygen system is a maintenance function. OXYGEN FILLER VALVE OXYGEN SERVICE OXYGEN PANEL DOOR SERVICE PANEL 1000 1500 2000 OXYGEN SUPPLY PRESSURE OXYGEN USE NO OIL PRESSURE MADE IN USA GAUGE Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 08-01-05...
Page 240 SMOKE GOGGLES Smoke goggles provided for both flight crew members and are designed to be used in conjunction with the EROS crew oxygen mask. The goggles are equipped with a vent-valve, and provide smoke and toxic gas protection for crew members.
Page 241 When the tabs are released, the harness deflates and the mask holds tightly against the operator’s face. CONTROL KNOB REGULATOR SMOKE GOGGLES REV 1 CREW OXYGEN MASK Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 08-01-07...
Page 242 When the O2 MASK/NORM switch on the associated audio control panel is selected to O2 MASK, the microphone in the mask is activated. INFLATABLE HARNESS MASK VENT LEVER HARNESS MANUAL INFLATION CONTROL OXYGEN LINE Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 08-01-08...
Page 243: Passenger Oxygen System
There is also a mask container in the lavatory located on the bulkhead. The latch mechanism can be operated manually or electrically. When the latch mechanism is released, the door opens and the masks drop down. Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6...
Page 244: Passenger Masks
The mask must be placed over the nose and mouth and is held in place with an elastic strap. ELASTIC STRAP OXYGEN VALVE (LANYARD OPERATED) OXYGEN MASK LANYARD COVER (OPEN) OXYGEN MASK RESERVOIR Volume 2 Flight Crew Operating Manual May 06/2005 REV 2 CSP 100-6 08-01-10...
Page 245: Emergency Equipment
ON position, the extinguisher is fully discharged in 10 seconds. WARNING: If a fire extinguisher is discharged in the flight compartment, all flight crew must wear oxygen masks with EMERGENCY selected (100% oxygen). Crew exposure to high levels of Halon vapor may result in diz- ziness, impaired coordination, and reduced mental sharpness.
Page 246 OXYGEN AND EMERGENCY EQUIPMENT EMERGENCY EQUIPMENT (Cont) DISCHARGE LEVER NYLON LOCKING DISCHARGE NOZLE NORMAL CHARGE HALON 1211 PRESSURE GUAGE CLASP Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 08-01-12...
Page 247 PBE. Pull the PBE straight out of the bag. If necessary hold the bag with the opposite hand. REV 2 STEP 2 A25-1031 Volume 2 May 06/2005 Flight Crew Operating Manual Volume 2 08-01-13 REV 2 CSP 100-6 08-01-13...
Page 248 6. With the straps still in hand and head bent forward, pull backward to secure the oronasal mask cone high on the nose for a tight seal. STEP 6 Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6...
Page 249 Disposal The expended PBE still contains unreacted oxidizing material and strong alkali materials. At the completion of flight, it must be turned over to maintenance for authorized disposal. Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6...
Page 250 If the condition persists, or there is evidence of a tear in the neckseal, the user should go quickly to a safe area and don alternate breathing equipment if required. Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6...
Page 251 LIFE VEST Life vests are provided for crew and passengers. Flight crew life vests are located under the pilot and copilot’s seats. The passenger life vests are located in a compartment under each passenger seat. The life vests are inflated by pulling the red release tabs.
Page 252 7. SHOULD IT BECOME NECESSARY, pass the straps between legs, fasten hooks. LIFE VEST CAN BE ORALLY Inflate only one chamber. INFLATED BY BLOWING INTO ORAL INFLATION TUBES. Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 08-01-18...
Page 253 CREW CLOSET CONTROLS AND INDICATIONS PASSENGER OXYGEN CONTROL PANEL OXYGEN THERAPEUTIC AUTO DEPLOY PLACARDS HALON FIRE OXYGEN EXTINGUISHER CYLINDER CREW MEMBER LIFE-VEST UNDER SEAT FIRST AID KIT Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 08-01-19...
Page 254 The passenger oxygen switch has been selected PAX OXYGEN OFF Pressure has been detected in the passenger PAX OXYGEN ON oxygen lines. Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 08-01-20...
Page 255 Description ......................... 09-01-11 Components and Operation..................09-01-11 Smoke Detectors ....................... 09-01-11 Controls and Indications...................... 09-01-12 Systems Test......................09-01-12 Description ......................... 09-01-12 EICAS Messages ........................ 09-01-13 REV 2 May 06/2005 Flight Crew Operating Manual Volume 2 REV 2 CSP 100-6 09-00-01...
Page 257 The detection and extinguishing systems are tested and monitored from the flight deck. POWER PLANT FIRE DETECTION/ EXTINGUISHING APU FIRE DETECTION/ EXTINGUISHING SYSTEM MAIN LANDING GEAR OVERHEAT DETECTION REV 1 Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 09-01-01...
Page 258 INDICATION FIRE- INTEGRATING APU FIRE- AND CREW DETECTION-AND- SYSTEM ALERTING DETECTION EXTINGUISHING SYSTEM SYSTEM (FIREX) (EICAS) CONTROL UNIT MAIN LANDING GEAR (MLG) OVERHEAT- DETECTION SYSTEM EV 2 Volume 2 Flight Crew Operating Manual May 06/2005 REV 2 CSP 100-6 09-01-02...
Page 259: Fire Protection System Overview Schematic
108.00 108.00 190.0 190.0 118.000 118.000 FIREX LEFT GEAR RIGHT GEAR CONTROL UNIT AFFECTED AFFECTED AREA AREA AFFECTED AFFECTED AREA AREA APU COMPARTMENT LH ENGINE RH ENGINE Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 09-01-03...
Page 260: Engine Fire Detection
The check tee prevents extinguishing agent from the second discharged bottle from back filling into the bottle that was discharged first. Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6...
Page 261 1- BLEED AIR VALVE 2- FUEL SHUTOFF VALVE 3- HYDRAULIC SHUTOFF VALVE 4- APU BLEED SHUTOFF VALVE 5- APU FUEL SHUTOFF VALVE LEGEND 6- TWO WAY CHECK VALVE ENGINE DISCHARGE Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 09-01-05...
Page 262: Engine Fire Protection
R ENG FIRE APU FIRE FIRE FIRE FIRE FIRE EXT EVENT ARMED ARMED AUTO AUTO APR MACH HOLD SYNC L STARTER R STARTER IGNITION CRANK START CRANK START Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 09-01-06...
Page 263 Minimum/Maximum FIREX Bottle Pressure (4.3 lb nominal weight) Gage reading (psig) Temp °C Minimum Maximum 1096 1032 1165 1100 1235 1168 1305 1235 1375 1303 1445 1371 1515 1439 1585 Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 09-01-07...
Page 264: Auxiliary Power Unit Fire Protection
In flight, when a fire condition is detected and the APU FIRE switch is pushed, the APU shuts down and arms the discharge cartridge on the number 2 container. The flight crew must discharge the bottle by pushing the FIRE EXT 2 switch.
Page 265 APU FIRE FIRE FIRE FIRE FIRE EXT EVENT ARMED ARMED AUTO AUTO APR MACH HOLD SYNC L STARTER R STARTER IGNITION CRANK START CRANK START REV 1 Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 09-01-09...
Page 266: Main Landing Gear Overheat Detection
FIREX system. FIRE DETECTION/EXTINGUISHING SYSTEM CONTROL UNIT OVERHEAT WARNING OVERHEAT EICAS DETECTION FAIL OVERHEAT DETECTION DATA CONCENTRATOR UNIT OVERHEAT DETECTOR MAIN LANDING GEAR BAY OVERHEAT DETECTION LOOPS Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 09-01-10...
Page 267: Cargo Bay Fire Protection
CARGO SMOKE (W) CAS message illuminates. NOTE: Operation of mobile transceivers in close proximity to the smoke detectors or exhaust fumes from ground handling equipment may cause a false alarm. Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6...
Page 268: Systems Test
The test takes approximately 10 seconds to complete. SYSTEMS TEST ANNUN A ANNUN B PUSH TAWS PROBES TEST STALL/RUD LIM FIRE DET ICE DET REV 7 Volume 2 Flight Crew Operating Manual Dec 05/2006 REV 7 CSP 100-6 09-01-12...
Page 269 The fire detect test system is conducting the FIRE SYS IN TEST manually activated system test The fire detect test system has passed the sys- FIRE SYS TEST OK tem test REV 1 Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 09-01-13...
Page 271 Controls and Indications...................... 10-02-16 Flap Control Lever ..................... 10-02-16 EICAS Trim Status Display ..................10-02-16 Flight Control Synoptic Page ..................10-02-17 REV 1 EICAS Messages ........................ 10-02-18 Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 10-00-01...
Page 273 The elevator and rudder has a manual reversion capability in the event of a dual hydraulic failure. ELEVATORS HORIZONTAL STABILIZER RUDDER FLAPS AILERON GROUND MULTI-FUNCTION SPOILERS SPOILERS Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 10-01-01...
Page 274: Primary Flight Controls
When the gust lock is engaged, the throttles are physically prevented from being moved above idle. Aileron position is dis- played on the EICAS FLIGHT CONTROL synoptic page. A full-scale deflection of the AIL position indicator corresponds to maximum aileron deflection. Volume 2 Flight Crew Operating Manual Sep 14/2005 REV 4 CSP 100-6...
Page 275 ROLL DISCONNECT The roll disconnect allows the flight crew to isolate the left control wheel from the aileron control system. The roll discon- nect mechanism is mounted on the left control wheel. It is comprised of a lever, a shaft, a stud roller, a cam, and two torsion springs.
Page 276 The horizon- tal-stabilizer-trim electronic-control unit (HST ECU) controls the movement of the rudder travel limiter-actuator. Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1...
Page 277 INPUT MECHANICAL FGC 1 FGC 2 INPUT CABLE INPUT RUDDER LIMITER RUDDER TRIM/YAW DAMPER POWER CONTROL UNIT RUDDER (POSITION TO EICAS ELEVATOR ELEVATOR FLIGHT CONTROL PAGE) RUDDER Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 10-01-05...
Page 278 - Provides a positive means of disengagement. The switch is manually positioned and the YD cannot engage when the bar is in the down (disconnect) position When the yaw damper channel fails or disconnects, an amber YAW DAMPER FAIL (C) CAS message is displayed. Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6...
Page 279 POWER CONTROL UNIT PITCH FEEL UNITS ELEVATOR SURFACE AFT QUADRANT AUTOPILOT PITCH SERVO STICK-PUSHER CABLES ACTUATOR CONTROL COLUMN FORWARD QUADRANT REV 1 Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 10-01-07...
Page 280 A PITCH DISCONNECT (W) CAS message will also be illuminated on the MFD. PITCH DISC PULL & TURN PITCH DISC LEVER Volume 2 Flight Crew Operating Manual May 06/2005 REV 2 CSP 100-6 10-01-08...
Page 281 SERVO AUTOPILOT PITCH FEEL PITCH SERVO UNITS HORIZONTAL STABILIZER POWER CONTROL LEGEND ELEVATORS UNIT ELECTRICAL INPUT ELEVATOR ELEVATOR RUDDER MECHANICAL INPUT CABLE INPUT FLIGHT CONTROL SYNOPTIC PAGE Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 10-01-09...
Page 283: Secondary Flight Controls
SECU. Position indicators for the secondary control surfaces are located on the MFD and the FLIGHT CONTROLS synoptic page. HORIZONTAL STABILIZER AILERON TRIM SINGLE FOWLER FLAP GROUND SPOILERS MULTI-FUNCTION SPOILERS REV 1 Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 10-02-01...
Page 284 RUDDER TRIM Rudder trim is provided through an electromechanical rudder trim actuator. Rudder trim is activated by the flight crew by means of a RUD TRIM switch on the pedestal. Trimming of the rudder is done directly with the rudder surface. There are no trim tabs on the rudder.
Page 285 Likewise, decreasing aircraft speed from a trimmed condition results in Mach trim inputting slight nose down trim. The Mach trim system is continuously monitored and any fault detected is displayed on the EICAS display. Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6...
Page 286 CONFIG AILERON TRIM MULTI-FUNCTION SPOILERS LEFT AILERON BALANCE (POSITION TO EICAS FLIGHT CONTROLS PAGE) TRIM STAB LEGEND ELECTRICAL INPUT MECHANICAL INPUT MECHANICAL INPUT CABLE INPUT GEAR FLAPS TRIM MOTOR Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 10-02-04...
Page 287 CHANNEL 1 RELAY RELAY CHANNEL 2 HORZONTAL STABILIZER BRAKE 1 BRAKE 3 BRAKE 2 BRAKE 4 MOTOR MOTOR COMM COMM HSTA GEARBOX HORIZONTAL NO BACK STABILIZER TRIM ACTUATOR Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 10-02-05...
Page 288 The flap position alerting system is monitored by airspeed, flap position, spoiler, gear position, and altitude. An overspeed warning horn is activated if flaps are extended above the following speed: 210 kt — 10° 210 kt — 20° 175 kt — 30° Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 10-02-06...
Page 289 This circuit allows the arming solenoid valve within the flap power unit to energize open for 75 sec- onds and then de-energize. FLAPS FLAP POSITION INDICATION Flap position is shown in a digital display on the (EICAS) and flight control synoptic page. Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 10-02-07...
Page 290: Spoiler System
The ground spoilers have only two positions: fully retracted during flight or fully deployed after landing. The inboard and outboard ground spoilers, when tied together with the multifunction spoilers, comprise the ground spoilers system. Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1...
Page 291: Spoiler Electronic Control Unit (Secu)
FLIGHT SPOILERS EMER PITCH DISC PULL & TURN REV 2 May 06/2005 Flight Crew Operating Manual Volume 2 REV 2 CSP 100-6 10-02-09...
Page 292 Pressing the switch again, reengages the roll assist function and extinguishes the CAS message PILOT COPILOT CONTROL CONTROL ROLL SPOILERS WHEEL WHEEL ROLL DISCONNECT SWITCH RVDT RVDT SECU1 SECU2 COMMAND MONITOR COMMAND MONITOR ARINC 429 Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 10-02-10...
Page 293 SWITCHES GND SPOILERS AUTO MANUAL LEFT MAIN 28 VDC SECU1 SECU2 ARINC 429 COMMAND MONITOR COMMAND MONITOR LEFT MAIN 28 VDC OUTBD INBD INBD OUTBD GSSV1 GSSV2 Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 10-02-11...
Page 294 Inboard and outboard ground spoilers are limited to two positions, either up or down. The spoilers are continuously monitored and any fault detected is displayed on the appropriate EICAS screen. Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1...
Page 295: Takeoff Configuration Warning System
STALL PROTECTION SYSTEM DESCRIPTION The stall protection system (SPS) provides the flight crew with aural, visual, and tactile (stick shaker) indications of an impending stall. If the pilot does not take corrective action, the system activates the stick pusher mechanism.
Page 296 This prevents the aircraft’s pitching momentum from carrying it through the stall warning/stick pusher sequence to deep into the stall. RH ANGLE OF ATTACK SENSOR LH ANGLE OF ATTACK SENSOR ANGLE OF ATTACK SENSOR (TYPICAL) EV 2 Volume 2 Flight Crew Operating Manual May 06/2005 REV 2 CSP 100-6 10-02-14...
Page 297 Should the SPS incorrectly activate the stick pusher, the stick pusher may be disabled by selecting the STALL PUSHER switch to OFF. TRIM MASTER DISCONNECT STAB SWITCH FOR AP, TRIM & STALL PUSHER STALL PUSHER REV 2 May 06/2005 Flight Crew Operating Manual Volume 2 REV 2 CSP 100-6 10-02-15...
Page 298 FLIGHT CONTROLS CONTROLS AND INDICATIONS FLAP CONTROL LEVER FLAPS EICAS TRIM STATUS DISPLAY TRIM STAB Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 10-02-16...
Page 299: Flight Controls
118.000 108.00 1200 1799.5 118.000 118.000 2.0000 STBY 118.000 108.00 190.0 2.0000 118.000 118.000 AUTO PLAN SKIP SHLDR SIDE CKLST TR/WX FRMT ENTER SUMRY A/ICE ELEC FUEL Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 10-02-17...
Page 300 All flight spoilers have failed FLT SPOILERS Either the inboard or outboard spoilers have FAULT failed GND SPLRS NOT The ground spoilers are not armed and not ARMED selected OFF Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 10-02-18...
Page 301 The flap extension and retraction rates are slower than normal. This message will illumi- FLAPS RATE LOW TO/LAND nate when the right engine is shutdown, or if the engine driven pump is shutdown Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 10-02-19...
Page 302 The STAB TRIM switch is in the off position. STAB TRIM OFF The autopilot will be inoperative The stall pusher has been manually deacti- STALL PUSHER OFF vated Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 10-02-20...
Page 303 Heading Display ........................11-01-18 Description ......................... 11-01-18 Components and Operation..................11-01-18 Heading Indicators ..................... 11-01-18 Selected Heading Reference ..................11-01-18 Attitude and Heading Flags..................11-01-18 REV 1 Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 11-00-01...
Page 304 Standby Instrument Functions ................... 11-01-33 Clock/Chronometer ......................11-01-33 Description ......................... 11-01-33 Components and Operation..................11-01-33 Flight Time (FLT/RST)....................11-01-33 Chronograph (CHR)....................11-01-33 GPS/MAN Mode ......................11-01-33 REV 7 Volume 2 Flight Crew Operating Manual Dec 05/2006 REV 7 CSP 100-6 11-00-02...
Page 305 Airport IDENTS Overlay..................... 11-02-30 SIGMET Overlay......................11-02-31 Database Functions ......................11-02-32 Status Page........................ 11-02-32 Database Effectivity Page ..................11-02-33 Chart Subscription Page .................... 11-02-34 File Server Configuration page .................. 11-02-35 Dec 05/2006 Flight Crew Operating Manual Volume 2 REV 7 CSP 100-6 11-00-03...
Page 307 CO-PILOT PILOT PILOT CO-PILOT RIGHT MFD LEFT MFD RIGHT PFD LEFT PFD CDU 2 CDU 1 (OPTION) MFD CONTROL REV 7 (EFIS Display typical) Dec 05/2006 Flight Crew Operating Manual Volume 2 REV 7 CSP 100-6 11-01-01...
Page 308: Flight Instruments
(OPTION) CABIN PRESS (OPTION) SPOILER BRAKES SATCOM NOSE WHEEL STEER HF DATALINK (OPTION) HYDRAULICS HF COUPLER (OPTION) HF COM PROXIMITY SENSING (OPTION) (OPTION) FLIGHT CONTROLS EV 1 Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 11-01-02...
Page 309: Primary Flight Displays
° C HDG 340 FMS1 DTK 340 KCID TTG 15:01 95.0 NM SOURCE ANOSA FMS1 NEBOR KCID LOC1 111.30 FMS2 126.80 VOR2 TR / / LX 180N FMS2 Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 11-01-03...
Page 310 5 degrees and small line markings every 2.5 degrees. Red warning chevrons appear during maneuvers of excessive pitch attitude pointing toward the zero degree position. Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1...
Page 311 There is a diamond for glideslope data and a star for VNAV data. GLIDESLOPE FLAG During an ILS, with invalid glideslope information, a red boxed GS flag is displayed, replacing the pointer and scale. Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6...
Page 312 - Heading indication - FCC transfer indicator When the pitch and roll limits are restored, the PFD resumes displaying all information. Example of decluttered EADI in excessive roll Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 11-01-06...
Page 313 FLIGHT INSTRUMENTS PRIMARY FLIGHT DISPLAYS (Cont) Example of decluttered EADI in excessive pitch Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 11-01-07...
Page 314 1000 feet and small rectangles for 500 feet. The barometric altitude readout ranges from -1000 feet to 50 000 feet. The digital readout in the fixed altitude window indicates the actual altitude. 16000 4200 29.92 IN Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 11-01-08...
Page 315 Selected VS shows on the VS scale as a reference bug, and as a digital readout on the automatic flight control system (AFCS) mode field above the attitude ball. Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6...
Page 316: Radio Altitude Display
AIR DATA FLAGS When ADC airspeed, altitude or vertical speed data is invalid, red air data flags are presented to replace the affected systems information. REV 2 Volume 2 Flight Crew Operating Manual May 06/2005 REV 2 CSP 100-6 11-01-10...
Page 317: Air Data System
The airspeed trend vector originates from the tail of the indicated airspeed arrow. The magenta trend vector moves verti- cally in response to the aircraft acceleration or deceleration indicating the speed predicted in the next 10 seconds. Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1...
Page 318 )/maximum mach number (M - Baro correction - Barometric corrected altitude - Static air temperature - Total air temperature - True AIRSPEED - Temperature difference from standard (ISA) Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 11-01-12...
Page 319: Pitot Static System
Chapter 14, Ice and Rain Protection. TAT PROBE RIGHT PITOT/ STATIC PROBE LEFT PITOT/ STATIC PROBE STANDBY PITOT PROBE RIGHT STANDBY LEFT STANDBY STATIC PORT STATIC PORT REV 5 Feb 22/2006 Flight Crew Operating Manual Volume 2 REV 5 CSP 100-6 11-01-13...
Page 320: Total Air Temperature Probe
-S3 is the static input to the integrated standby instrument STANDBY P2 S1 S2 STATIC STANDBY INSTRUMENT MANIFOLD STANDBY P1 S1 S2 STBY STATIC LEGEND PITOT STATIC Volume 2 Flight Crew Operating Manual Feb 22/2006 REV 5 CSP 100-6 11-01-14...
Page 321: Attitude And Heading Reference System (Ahrs)
Initialization and operation of the AHRS occurs automatically when electrical power is established and the aircraft is sta- tionary. Initialization takes approximately 40 seconds in MAG mode and 4.5 minutes in DG mode. REV 1 Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6...
Page 322 When the switch is selected to 1, all displays receive data from AHRS 1 only. An amber AHS1 message is displayed on both PFDs. When the switch is selected to 2, all displays receive data from AHRS 2 only. An amber AHS2 message is displayed on both PFDs. Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 11-01-16...
Page 323 If an airborne alignment occurs due to power interruption, the system will take 40 seconds to realign. During the in-flight alignment process, the aircraft must remain in a straight and level unaccelerated flight. ATT/HDG ALIGNING Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6...
Page 324: Heading Display
A red boxed heading flag HDG is displayed when the heading source is invalid. When the flag is in view, it replaces the heading readout, the compass rose (or arc) is rotated to north-up, and the lubber line around the digital heading is removed. Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1...
Page 325: Navigation Displays
The track pointer is positioned on the compass rose or compass tape at the current aircraft track over the earth. The track pointer is a green open circle shape. The difference between the track pointer position and the lubber line is the drift angle. Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1...
Page 326 The horizontal situation indicator (HSI) represents the compass card, which incorporates selectable navaids, bearing and course pointers. HSI indications include: - Course pointer - Lateral deviation bar - Lateral deviation scale - To/from indicator Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 11-01-20...
Page 327 This provides a vertical menu on the left side of the PFD, with three pages of menus. Rotating the MENU/DAT knob scrolls through the various options and on the third page, the VBAR or XPNTR is selected by toggling the PUSH/SELECT button in the MENU/DATA knob on the DCP. Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6...
Page 328 / LX 270 / 150 CONTROL T-1.5A COM1 NAV1 ATC1/TCAS ADF1 COM3 COM2 118.000 108.00 1200 1799.5 118.000 118.000 2.0000 STBY 2.0000 118.000 118.000 108.00 190.0 118.000 Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 11-01-22...
Page 329 The ENTER switch is associated with the joystick and enters the PPOS waypoint or selects the current menu item in the top half of the MFD. SUMRY The SUMRY switch is used to display the EICAS summary display on the MFD. (Continued) REV 1 Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 11-01-23...
Page 330 The UPR MENU button is used to present or remove an upper menu. The content depends on the format. Each push of the ESC button moves up one level through the menu tree until the top level is reached on the display. REV 7 (Continued) Volume 2 Flight Crew Operating Manual Dec 05/2006 REV 7 CSP 100-6 11-01-24...
Page 331 (Red), may be hidden by paging through all existing messages to a blank page. New messages will then appear on this blank page. All messages can be retrieved by subsequently pressing the CAS button on the MFD control. (Continued) Dec 05/2006 Flight Crew Operating Manual Volume 2 REV 7 CSP 100-6...
Page 332 The ZOOM feature is operated by a rocker switch with + and - markings. Pushing the + expands the view, pushing the - returns the chart to normal scaling. (Continued) Volume 2 Flight Crew Operating Manual Dec 05/2006 REV 7 CSP 100-6...
Page 333 When the SHLDR view is displayed, the viewing angle is 22° lateral and 75° vertical, relative to the inbound course. SIDE Selecting SIDE view on the 3D display will provide the pilot with 90° lateral and 90° vertical viewing angles, relative to the inbound course. Dec 05/2006 Flight Crew Operating Manual Volume 2 REV 7 CSP 100-6 11-01-27...
Page 334 The tune knob is a rotary control used for MFD radio tuning. The larger and smaller knobs change the most significant and least significant digits of the frequency respectively. The up down arrow button in the center of the TUNE knob swaps the recall and the active frequencies. Volume 2 Flight Crew Operating Manual Dec 05/2006 REV 7 CSP 100-6...
Page 335 DISPLAY CONTROL PANEL WARNING FLAG A display control panel (DCP) failure results in the display of an amber boxed DCP flag. This flag will appear on the PFD and MFD displays. Dec 05/2006 Flight Crew Operating Manual Volume 2 REV 7 CSP 100-6...
Page 336 MFD. When either MFD is off, it is recommended that the EICAS switch is set to BOTH PFDS, otherwise EICAS is not displayed. Volume 2 Flight Crew Operating Manual Dec 05/2006 REV 7 CSP 100-6...
Page 337 Tuning of the radios by the CDU is disabled, tuning enabled only by MFD. Position — NORM Tuning is normal. Position — CDU ONLY Tuning of the radios by the MFD is disabled. Tuning is enabled only by CDU. Dec 05/2006 Flight Crew Operating Manual Volume 2 REV 7 CSP 100-6 11-01-31...
Page 338 COMPONENTS AND OPERATION STANDBY INDICATOR The indicator supplies the flight crew with displays of aircraft speed, attitude, slip/skid, and glideslope/localizer data as long as 28 vdc power is available. The localizer and glideslope data come from the VHF navigation receiver 1. The localizer and glideslope pointers and scales are not in view until an ILS frequency is selected.
Page 339 LOC (local time) and date displays. By pressing and holding the mode button for more than two seconds, the chronometer will enter the UTC, LOC and date mode. GPS/MAN 1 : 23 MONTH MODE 43 : 33 Dec 05/2006 Flight Crew Operating Manual Volume 2 REV 7 CSP 100-6 11-01-33...
Page 340: Standby Compass
FLIGHT INSTRUMENTS STANDBY COMPASS DESCRIPTION The standby compass supplies the flight crew with the magnetic heading data. This system is in constant operation and is used as an auxiliary display. COMPONENT AND OPERATION The standby compass is installed in a bracket on the center post of the windshield, above the flight guidance panel. The compass is aligned with the aircraft longitudinal axis.
Page 341 STANDBY COMPASS WITH ALL RADIOS ON SWUNG / / BY TO FLY 210 240 300 330 120 150 STEER CENTER INDEX MARK BRACKET COMPENSATORS ADJUSTMENT SCREW COMPASS DIAL LIGHT UNIT REV 7 Dec 05/2006 Flight Crew Operating Manual Volume 2 REV 7 CSP 100-6 11-01-35...
Page 342: Primary Flight Display (Pfd)
HDG 340 FMS1 DTK 340 KCID TTG 15:01 95.0 NM SOURCE ANOSA FMS1 NEBOR KCID LOC1 111.30 FMS2 VOR2 126.80 TR / / LX 180N FMS2 REV 7 Volume 2 Flight Crew Operating Manual Dec 05/2006 REV 7 CSP 100-6 11-01-36...
Page 343: Multifunction Displays (Mfd)
/ LX 270 / 150 CONTROL T-1.5A NAV1 ADF1 COM1 ATC1/TCAS COM3 COM2 118.000 108.00 1200 1799.5 118.000 118.000 2.0000 STBY 118.000 108.00 190.0 2.0000 118.000 118.000 Dec 05/2006 Flight Crew Operating Manual Volume 2 REV 7 CSP 100-6 11-01-37...
Page 344: Mfd Control Panel (Mcp)
SKIP A/ICE ELEC MENU TR/WX FUEL SUMRY FRMT ENTER DISPLAY CONTROL PANEL (DCP) DME/H NAVSRC FRMT TR/WX TUNE MENU DATA TILT RANGE AUTO RADIO BRGSRC REFS RADAR Volume 2 Flight Crew Operating Manual Dec 05/2006 REV 7 CSP 100-6 11-01-38...
Page 345 ONLY LEFT ONLY RIGHT DISPLAYS DISPLAYS COM 1 NORM NORM 121.50 ATT/HDG AIR DATA NORM NORM OPTIONAL STANDBY INSTRUMENT 1013.2 hPa M. 47 29.92 in CAGE BARO Dec 05/2006 Flight Crew Operating Manual Volume 2 REV 7 CSP 100-6 11-01-39...
Page 346: Multi-Function/Primary Flight Display Visual Annunciations
Indicates when VNAV data from the FMS is missing or invalid Indicates in place of the vertical speed scale when vertical speed data from the air data com- puter is missing or invalid Volume 2 Flight Crew Operating Manual Dec 05/2006 REV 7 CSP 100-6 11-01-40...
Page 347 Channel A or B of the remote data concentrator RDC FAULT TO/LAND has failed with no loss of functionality Dec 05/2006 Flight Crew Operating Manual Volume 2 REV 7 CSP 100-6 11-01-41...
Page 349 Multifunction Controls and two MFDs. The FSU provides the processing and storage for all IFIS functions including E- Charts, Enhanced Maps, and GWX. INTEGRATED FLIGHT INFORMATION SYSTEM (IFIS) BLOCK DIAGRAM MFD CONTROLS MFD CONTROLS XM RECEIVER GWX-3000 COMMUNICATION VHF3/DATALINK MANAGEMENT GWX-5000 UNIT REV 7 Dec 05/2006 Flight Crew Operating Manual Volume 2 REV 7 CSP 100-6 11-02-01...
Page 350 The symbol is displayed as a green aircraft with a white circle/slash when the chart in view is not geograph- ically-referenced. The moving aircraft symbol displays the current aircraft position latitude and longitude as determined by the same side Global Positioning System (GPS). (Continued) Volume 2 Flight Crew Operating Manual Dec 05/2006 REV 7 CSP 100-6 11-02-02...
Page 351 - OUT OF DATE - CHECK DATE - CHART FAULT The menus are divided into the following areas: - Chart Main Index - Chart Type Menu - Chart List. Dec 05/2006 Flight Crew Operating Manual Volume 2 REV 7 CSP 100-6 11-02-03...
Page 352 1. With an E-Chart displayed, push the UPR or LWR MENU button on the MFD control. 2. If the Chart Type, Chart List, or NOTAM menu is in view, push the ESC button on the MFD control. (Continued) Volume 2 Flight Crew Operating Manual Dec 05/2006 REV 7 CSP 100-6...
Page 353 1. Push the UPR or LWR MENU or ESC button on the MFD control to exit the Chart Main Index and show the E- Chart that was previously in view. Dec 05/2006 Flight Crew Operating Manual Volume 2 REV 7...
Page 354 1. Push the UPR or LWR MENU button on the MFD control to show the Chart Main Index. 2. Turn the MENU ADV knob to position the menu cursor around the desired chart. Push the PUSH SELECT button to select the chart for display. Volume 2 Flight Crew Operating Manual Dec 05/2006 REV 7 CSP 100-6...
Page 355 Approach, Airport, Departure, Airspace, Arrival, and Noise. 2. Push the PUSH SELECT button on the MFD control to select the chart type. (Continued) Dec 05/2006 Flight Crew Operating Manual Volume 2 REV 7 CSP 100-6 11-02-07...
Page 356 - The chart is to be deleted and its effectivity date has passed - The chart is the early cycle of a mid-cycle revision and the current date/time is the late cycle of the database. (Continued) Volume 2 Flight Crew Operating Manual Dec 05/2006 REV 7 CSP 100-6...
Page 357 EXIT CHART LIST 1. Push the UPR or LWR MENU or ESC button on the MFD control to exit the Chart List and show the chart previ- ously in view. Dec 05/2006 Flight Crew Operating Manual Volume 2 REV 7 CSP 100-6...
Page 358 FLIGHT INSTRUMENTS ELECTRONIC CHARTS (OPTIONAL) (Cont) CHART NOTAMS MENU DISPLAY (Continued) REV 7 Volume 2 Flight Crew Operating Manual Dec 05/2006 REV 7 CSP 100-6 11-02-10...
Page 359 Push the ESC button on the MFD control to exit the NOTAM page and show the Chart Main Index. b. Push the UPR or LWR MENU button on the MFD control to exit the NOTAM page and show the Display Chart format. Dec 05/2006 Flight Crew Operating Manual Volume 2 REV 7 CSP 100-6...
Page 360 When an image of this nature is encountered and you suspect the data is in error, wait until the next image update cycle, request a new image, and verify the test pattern is removed. Volume 2 Flight Crew Operating Manual Dec 05/2006 REV 7...
Page 361 The CDU also displays the message RCVD just beside the requested image. As long as images in the entry list have not been viewed, the message RCVD continues to be displayed on the CDU. (Continued) Dec 05/2006 Flight Crew Operating Manual Volume 2 REV 7 CSP 100-6...
Page 362 Each datalinked GWX image is paired with a corresponding geopolitical background image. The geopolitical background images shows geographic and political borders. The borders are displayed in white with a black background. (Continued) Volume 2 Flight Crew Operating Manual Dec 05/2006 REV 7 CSP 100-6...
Page 363 NEXRAD images to represent areas of precipitation and the relative intensity: Precipitation Intensity Color 20 < Green dBZ < 30 30 < Yellow dBZ < 40 > 40 Dec 05/2006 Flight Crew Operating Manual Volume 2 REV 7 CSP 100-6 11-02-15...
Page 364 The following table lists the colors used on TOPS/MOVEMENTS images to represent areas of precipitation and the relative intensity: Precipitation Intensity Color 20 < dBZ < 30 Green 30 < dBZ < 40 Yellow dBZ > 40 Volume 2 Flight Crew Operating Manual Dec 05/2006 REV 7 CSP 100-6 11-02-16...
Page 365 WX DEPICTION is based on a finite number of reporting stations. For finer weather detail, refer to other sources such as NEXRAD OR TAF reports. The following table list the colors used on WX DEPICTION images: Precipitation Intensity Color Sky Blue Marginal VFR Green Yellow Low IFR Dec 05/2006 Flight Crew Operating Manual Volume 2 REV 7 CSP 100-6 11-02-17...
Page 366 The head points to the wind direction. The temperatures are depicted next to the grid points in degrees Celsius. Miss- ing wind is represented as M. HEAD 50 kts PENNANT BARB 10 kts 5 kts HALF BARB TAIL Volume 2 Flight Crew Operating Manual Dec 05/2006 REV 7 CSP 100-6 11-02-18...
Page 367 34, 39, 45, and 53. The following table lists the colors used on TURBULENCE images to represent areas of likely turbu- lence: Turbulence Probability Color Low probability Light Magneta Moderate probability Medium Magenta High probability Dark Magenta Dec 05/2006 Flight Crew Operating Manual Volume 2 REV 7 CSP 100-6 11-02-19...
Page 368 GWX format is active. The specified altitudes available for icing images (x 1000 ft) are: 0, 5, 10, 18, 24, and 30. Icing Potential Color Trace rime Light Blue Trace clear - light rime or clear Medium Blue Light or greater mixed ice Dark Blue Volume 2 Flight Crew Operating Manual Dec 05/2006 REV 7 CSP 100-6 11-02-20...
Page 369 < 30 Light Blue dBZ < 30 Green dBZ < 40 Medium Magenta dBZ < 40 Medium Blue dBZ < 40 Yellow Dark Blue Dark Magenta Dec 05/2006 Flight Crew Operating Manual Volume 2 REV 7 CSP 100-6 11-02-21...
Page 370 When the GWX format is selected, the OVERLAYS menu will display a list of overlays that may be displayed on the MFD. OVERLAY LEGENDS The OVERLAY LEGENDS page displays all the symbology used on the overlays to assist the operator with interpreting the information display on the overlay. Volume 2 Flight Crew Operating Manual Dec 05/2006 REV 7 CSP 100-6 11-02-22...
Page 371 To exit the OVERLAY LEGENDS page, push the ESC button on the MFD Control panel. 2. With the cursor positioned on the overlay selection, push the PUSH SELECT button on the MFD Control panel to turn the selected overlay ON or OFF. Dec 05/2006 Flight Crew Operating Manual Volume 2 REV 7 CSP 100-6...
Page 372: Taf/Metar Reports
METAR reports for that airport. 3. Turn the DATA knob on the MFD Control panel to select the TAF reports page with the current TAF for that airport. Volume 2 Flight Crew Operating Manual Dec 05/2006 REV 7 CSP 100-6...
Page 373 3. When more than one SIGMET or AIRMET report is available, turn the DATA knob to view all reports. Each turn of the DATA knob selects the next report page. Dec 05/2006 Flight Crew Operating Manual Volume 2 REV 7...
Page 374: Sigmet/Airmet Reports
When graphical SIGMET data is available, the message NO GRAPHICAL SIGMET appears in the upper right corner of the SIGMET Report page. A maximum of 50 active SIGMET reports and 75 active AIRMET reports can be presented. Volume 2 Flight Crew Operating Manual Dec 05/2006 REV 7 CSP 100-6...
Page 375 Overlays Menu is used to control the following: - NEXRAD - Echo Tops - METARS - Airport Idents - SIGMETs Once an overlay is selected for display it remains on until selected OFF. Dec 05/2006 Flight Crew Operating Manual Volume 2 REV 7 CSP 100-6 11-02-27...
Page 376 FLIGHT INSTRUMENTS OVERLAYS (Cont) OVERLAY LEGENDS The OVERLAY LEGENDS page displays all the symbology used in the graphical weather overlays. Volume 2 Flight Crew Operating Manual Dec 05/2006 REV 7 CSP 100-6 11-02-28...
Page 377 1000 < Ceiling < 3000 ft and/or 3 < Visibility < 5 miles 500 < Ceiling < 1000 ft and/or 1 < Visibility < 3 miles Low IFR Ceiling < 500 ft and/or Visibility < 1 mile Dec 05/2006 Flight Crew Operating Manual Volume 2 REV 7 CSP 100-6 11-02-29...
Page 378 The AIRPORT ICONS depicts airports and reporting stations that are within the currently displayed image. The AIRPORT ICONS consist of a small circle with the ICAO identifier for the airport above the circle. Volume 2 Flight Crew Operating Manual Dec 05/2006 REV 7...
Page 379 The SIGMET consists of a point, line, or unfilled polygon that defines the geographic extent of the report and its identifier. The following illustration displays the SIGMET condition and the associated color. Dec 05/2006 Flight Crew Operating Manual Volume 2 REV 7...
Page 380: Database Functions
The STAT button on the MFD Control is used to display a menu of lesser used menus. They are displayed when a Status Format Window is selected. The STAT menu includes the following formats: - Database Effectivity - Chart Subscription (Example shown above) - File Server Configuration Volume 2 Flight Crew Operating Manual Dec 05/2006 REV 7 CSP 100-6 11-02-32...
Page 381 If in a Dual FSU configuration, the MFD displays database information from the same side FSU. The left MFD displays data from the left FSU and the right MFD displays data from the right FSU. Dec 05/2006 Flight Crew Operating Manual Volume 2 REV 7...
Page 382 Regions are added to the list by entering temporary access codes. Both the subscription number and access codes are obtained from Jeppesen. The Chart Subscription page can only be modified on the ground. Volume 2 Flight Crew Operating Manual Dec 05/2006 REV 7...
Page 383 Options Part number, Function and Status of installed software is displayed. Part numbers and access codes (provided by Rockwell Collins Inc.) are entered on this page to load optional software. Dec 05/2006 Flight Crew Operating Manual Volume 2 REV 7...
Page 385 Fuel Control Panel ..................... 12-01-10 REV 1 Fuel Display ....................... 12-01-11 Fuel Temperature Readouts ..................12-01-11 Fuel Quantity Indications ................... 12-01-11 Fuel Synoptic Page....................12-01-12 EICAS Messages ........................ 12-01-13 Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 12-00-01...
Page 387 The fuel computer controls automatic refueling, powered cross- flow, fuel transfer, measurement of fuel quantity and temperature. Fuel system data is presented on the EICAS and synoptic pages. REV 1 Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 12-01-01...
Page 388: Fuel Tank System
† Based on a fuel density of 6.75 lb/USG (0.809 kg/litre), rounded to the nearest 50 lb or 25 kg. Fuel Mass is provided for reference only and should not be considered limit- ing. Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6...
Page 389 COMPONENTS AND OPERATIONS TANK CONSTRUCTION The wing tanks are integral type fuel tanks that use a wet wing design and are sealed with a fuel resistant sealant. REV 1 Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 12-01-03...
Page 390 If contamination is suspected all tanks should be drained until the fuel is clear of water or other contaminates. WATER DRAIN WATER DRAIN Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 12-01-04...
Page 391 The scavenge ejectors are operated by motive flow created by the high-pressure output of the engine-driven fuel pumps. The two ejectors are located at the lowest inboard point of each wing tank. The ejectors transfer fuel from the wing tanks to the collector tanks. Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6...
Page 392 The fuel filter assembly is mounted just aft of the oil tank on the engine. The filters are monitored for contamination by an impending bypass switch. If the fuel pressure parameters are exceeded, a signal is sent to the EICAS. REV 1 Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6...
Page 393 REFUELING MANUAL MODE The manual mode allows refueling personnel to direct fuel to a specific tank by selecting the appropriate shutoff valve open or closed. REV 1 Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 12-01-07...
Page 394 WARNING: Gravity filler caps for the wing tanks are located below the maximum pressure refueling level. Never re- move the gravity filler caps if the wing tanks are full or fuel quantity is unknown. Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1...
Page 395: Fuel Indication And Control
S.O.V. ENGINE OIL LEVEL TEST FUEL FULL MANUAL FUEL AUTO H. LEVEL DETECTOR CHECK OIL RIGHT LEFT PRESS. TOTAL QTY POWER INC. LEFT RIGHT FUEL QTY DEC. Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 12-01-09...
Page 396 FUEL CONTROL PANEL L (R) PUMP, GRAVITY XFLOW, and XFER are selected on the FUEL control panel. FUEL GRAVITY XFLOW R PUMP L PUMP AUTO AUTO XFER Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 12-01-10...
Page 397: Fuel Display
This indication shows the amount of fuel used since the counter was reset. The reset is carried out automatically on powerup by the FADEC. Magenta dashes indicate the input data is invalid. REV 2 May 06/2005 Flight Crew Operating Manual Volume 2 REV 2 CSP 100-6...
Page 398 118.000 108.00 1200 1799.5 118.000 118.000 2.0000 STBY 118.000 108.00 190.0 2.0000 118.000 118.000 AUTO PLAN SKIP SHLDR SIDE CKLST TR/WX FRMT ENTER SUMRY A/ICE ELEC FUEL Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 12-01-12...
Page 399 The wing fuel gravity crossflow valve is not fully TO/LAND FAIL opened or closed as commanded The respective electric fuel pump has been L (R) FUEL PUMP ON automatically turned on REV 4 Sep 14/2005 Flight Crew Operating Manual Volume 2 REV 4 CSP 100-6 12-01-13...
Page 400 L (R) FUEL PUMP OFF The respective fuel pump is OFF L (R) FUEL PUMP ON The respective fuel pump is ON FUEL XFER OPEN The fuel transfer valve is open Volume 2 Flight Crew Operating Manual Sep 14/2005 REV 4 CSP 100-6 12-01-14...
Page 401 Auxiliary Hydraulic System Schematic............... 13-01-11 Controls and Indications...................... 13-01-12 Description ......................... 13-01-12 Hydraulic Control Panel ..................... 13-01-12 Hydraulic Synoptic Page.................... 13-01-13 EICAS Messages ........................ 13-01-14 REV 5 Feb 22/2006 Flight Crew Operating Manual Volume 2 REV 5 CSP 100-6 13-00-01...
Page 402 Instruction Sheet Challenger 300 Flight Crew Operating Manual - Volume 2 REVISION 1 1/04 Sep 13/2004 Flight Crew Operating Manual Volume 2 CSP 100-6...
Page 403 In addition, roll assist with roll spoilers will be lost. The ailerons are strictly manually controlled through cables and pulleys. Due to the loss of flaps, thrust reversers, and lift dumping devices, the aircraft landing distances will be significantly increased. REV 2 May 06/2005 Flight Crew Operating Manual Volume 2 REV 2 CSP 100-6 13-01-01...
Page 404: Left And Right Hydraulic System
SPOILERS LANDING GEAR, RIGHT STEERING AND DCMP AUXILIARY BRAKING DCMP HEAT EXCHANGERS LEFT THRUST LEFT DCMP REVERSERS FLAPS LEGEND LEFT HYDRAULIC SYSTEM RIGHT HYDRAULIC SYSTEM AUXILIARY SYSTEM Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 13-01-02...
Page 405 3000 psi. The EDPs operate any time the engines are turning. Pressure switches located in the pump outflow lines provide low-pressure indications to the flight crew. The discharge, suction and case drains ports of the pump include quick-disconnect fittings and are connected directly to the aircraft systems through hoses. The case drain port is located on the top side of the pump near the mounting flange for maximum case drain cooling of pump components.
Page 406: Ecology Bottle
The DCMP will also automatically continue providing hydraulic pressure to other systems after the EDP stops functioning. No action is required of the flight crew, as the above procedures are automatic. LEFT AND RIGHT HYDRAULIC SYSTEM COOLING The left and right hydraulic systems require cooling due to heat generated by the EDPs and other heat sources within the engine nacelle.
Page 407 HYDRAULICS LEFT AND RIGHT HYDRAULIC SYSTEM (Cont) LEFT HYDRAULIC SYSTEM SCHEMATIC May 06/2005 Flight Crew Operating Manual Volume 2 REV 2 CSP 100-6 13-01-05...
Page 408 HYDRAULICS LEFT AND RIGHT HYDRAULIC SYSTEM (Cont) RIGHT HYDRAULIC SYSTEM SCHEMATIC Volume 2 Flight Crew Operating Manual May 06/2005 REV 2 CSP 100-6 13-01-06...
Page 409: Auxiliary Hydraulic System
100% of all contaminants larger than 15 microns and is a non-cleanable type. The auxiliary system pressure filter and the case drain filter element used on the filter manifolds of the left and right systems are identical, and interchangeable. May 06/2005 Flight Crew Operating Manual Volume 2 REV 2...
Page 410: Power Transfer Unit
The auxiliary system filler has a quick-disconnect to add hydraulic fluid to the auxiliary reservoir. The quick disconnects are installed on panels near the system access doors. Volume 2 Flight Crew Operating Manual May 06/2005 REV 2 CSP 100-6...
Page 411 HYDRAULICS HYDRAULIC SERVICING (Cont) HYDRAULIC SERVICING PANEL LEFT SYSTEM PRESSURE RIGHT SYSTEM PRESSURE LEFT SYSTEM RETURN RIGHT SYSTEM HYDRAULIC SERVICING PANEL RETURN May 06/2005 Flight Crew Operating Manual Volume 2 REV 2 CSP 100-6 13-01-09...
Page 412 HYDRAULICS HYDRAULIC SERVICING (Cont) AUXILIARY ACCUMULATOR SERVICING AUXILLARY ACCUMULATOR SERVICING Volume 2 Flight Crew Operating Manual May 06/2005 REV 2 CSP 100-6 13-01-10...
Page 413 HYDRAULICS AUXILIARY HYDRAULIC SYSTEM SCHEMATIC May 06/2005 Flight Crew Operating Manual Volume 2 REV 2 CSP 100-6 13-01-11...
Page 414: Hydraulic Control Panel
The Engine Indicating and Crew Alerting System (EICAS) monitors and displays the hydraulic system informa- tion. HYDRAULIC CONTROL PANEL HYDRAULIC L SOV R SOV CLOSED CLOSED L PUMP R PUMP AUTO AUTO AUTO ALTN PUMP FLAPS AUTO Volume 2 Flight Crew Operating Manual May 06/2005 REV 2 CSP 100-6 13-01-12...
Page 415 118.000 108.00 1200 1799.5 118.000 118.000 2.0000 STBY 118.000 108.00 190.0 2.0000 118.000 118.000 AUTO PLAN SKIP CKLST SHLDR SIDE FRMT TR/WX SUMRY ENTER A/ICE ELEC FUEL May 06/2005 Flight Crew Operating Manual Volume 2 REV 2 CSP 100-6 13-01-13...
Page 416 At least one of HYDRAULIC PUMP (L,R, PTU, HYD PUMP NOT AUTO or AUX) switch is not in the AUTO position L (R) HYD SOV The respective hydraulic shutoff valve is closed CLOSED Volume 2 Flight Crew Operating Manual May 06/2005 REV 2 CSP 100-6 13-01-14...
Page 417 Control Switches and Function .................. 14-01-08 Controls and Indications...................... 14-01-09 Description ......................... 14-01-09 Anti-Ice Control Panel ....................14-01-09 Anti-Ice Synoptic Page ......................14-01-10 EICAS Messages ........................ 14-01-11 REV 2 May 06/2005 Flight Crew Operating Manual Volume 2 REV 2 CSP 100-6 14-00-01...
Page 419 Anti-icing of the aircraft tail surface is not required. Two ice detectors provide indication to the flight crew of icing conditions. The anti-ice protection system (AIPS) is controlled by the integrated air system controllers (IASC) with indications dis- played on the EICAS.
Page 420: Ice Detection System
To initiate a test of the system, select ICE DET on the SYSTEMS TEST panel and push the test switch. During the test sequence, an internal check of the electronics, probe heater, and CAS messages will be performed. ELECTRICAL STRUT CONNECTOR VIBRATING MOUNTING PROBE FLANGE Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 14-01-02...
Page 421: Wing Anti-Ice System
The inboard sensor supplies the temperature data used to modulate the wing anti-icing valves. The sensor also monitors the wing for overheat and will display L (R) WING OVHT (W) CAS message if the condition exists. Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1...
Page 422 When the FROM R is selected, the left wing anti-ice and high pressure valves are closed and the crossbleed valve opens allowing bleed-air from the right engine to anti-ice both wings. EV 2 Volume 2 Flight Crew Operating Manual May 06/2005 REV 2 CSP 100-6...
Page 423: Wing Anti-Ice System Schematic
WING CROSS-BLEED COWL COWL VALVE ANTI-ICE ANTI-ICE VALVE VALVE WING ANTI-ICE VALVES HIGH HIGH PRESSURE PRESSURE VALVE VALVE EICAS DISPLAY STALL PROTECTION COMPUTER REV 1 CHANNEL CHANNEL Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 14-01-05...
Page 424: Engine Anti-Ice
The engine spinner is a two-piece, aluminum forging with a conical shape to provide a surface that sheds ice in icing con- ditions and operates without the need for anti-icing heat. EV 2 Volume 2 Flight Crew Operating Manual May 06/2005 REV 2 CSP 100-6...
Page 425: Air Data And Sensors Anti-Ice
PROBES switch. TOTAL AIR TEMPERATURE PROBE (TAT) One total air temperature sensor is located in the right side of the aircraft. The TAT heater operates in flight only. May 06/2005 Flight Crew Operating Manual Volume 2 REV 2 CSP 100-6...
Page 426: Windshield Ice And Rain Protection
Selecting the L (R) WSHLD/WINDOW off de-energizes the applicable windshield and window and resets the temperature controller. SIDE WINDOW SENSING SIDE WINDOW ELEMENTS SENSING ELEMENTS BARS SENSING ELEMENTS BARS Volume 2 Flight Crew Operating Manual May 06/2005 REV 2 CSP 100-6 14-01-08...
Page 427 Anti-ice system operation and fault presentation is provided on the ANTI-ICE synoptic display. The ANTI-ICE synoptic display monitors the pneumatically-operated anti-icing and ice detection systems. ANTI-ICE CONTROL PANEL ANTI-ICE WING SOURCE WING PROBES NORM FROM FROM WSHLD/WINDOW May 06/2005 Flight Crew Operating Manual Volume 2 REV 2 CSP 100-6 14-01-09...
Page 428 7777 1799.5 118.000 118.000 2.0000 STBY 2.0000 118.000 118.000 108.00 190.0 118.000 AUTO PLAN CKLST SKIP SHLDR SIDE FRMT TR/WX SUMRY ENTER FUEL A/ICE ELEC REV 2 Volume 2 Flight Crew Operating Manual May 06/2005 REV 2 CSP 100-6 14-01-10...
Page 429 Both detection loops failed. This is only checked FAIL during power up self-test L (R) WING A/I PRESS High pressure has been sensed in the wing anti- TO/LAND ice system REV 4 Sep 14/2005 Flight Crew Operating Manual Volume 2 REV 4 CSP 100-6 14-01-11...
Page 430 WING/ENG ANTI-ICE The wing and both engine anti-ice systems are WING SOURCE Either FROM L or FROM R has been selected XBLEED on the ANTI-ICE WING SOURCE switch Volume 2 Flight Crew Operating Manual Sep 14/2005 REV 4 CSP 100-6 14-01-12...
Page 431 WING/ENG ANTI-ICE The wing and both engine anti-ice systems are WING SOURCE Either FROM L or FROM R has been selected XBLEED on the ANTI-ICE WING SOURCE switch Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 14-01-13...
Page 433 Landing Gear (Up) ..................... 15-01-19 Landing Gear (Down)....................15-01-20 NWS Switch ....................... 15-01-21 Nosewheel Steering Tiller ..................15-01-21 Landing Gear Indication..................... 15-01-21 EICAS Messages ........................ 15-01-22 REV 1 Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 15-00-01...
Page 435 - Manual Release System - Steering Control System - Proximity Sensing System - EICAS Messages and Audio Alerts - Brake System NOSE LANDING GEAR MAIN LANDING GEAR Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 15-01-01...
Page 436 The logic driving the mutable and non-mutable warnings are designed to ensure adequate time to either lock the gear down or perform a go-around. REV 1 Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 15-01-02...
Page 437: Landing Gear
The main landing gear is held in the up-and-locked position by mechanical uplocks. With the gear extended, locking mech- anisms in the side-brace keeps lock the gear in the down position. On the ground, locking pins can be inserted into the side strut actuator. Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6...
Page 438 SHOCK STRUT UPLOCK ROLLER (ON THE PIVOT OF MECHANICAL THE MAIN FITTING DOOR LINKAGE AND TRAILING ARM) TRAILING ARM BRAKE ASSEMBLY BRAKE WEAR INDICATOR (TWO PER ASSEMBLY) Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 15-01-04...
Page 439 A downlock safety pin at the end of the side brace assembly, secures each of the main landing gear in position while on the ground. GROUND LOCKING PIN Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6...
Page 440 When the nose gear is retracted, the mechanisms pull the two forward doors to the fully closed position. When the nose gear is down, the forward doors and aft door will remain open. Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6...
Page 441 MANUAL RELEASE ASSEMBLY DOOR RETRACTION ACTUATOR NOSE GEAR FORWARD DOOR DOOR UPLOCK UPPER DRAG DOOR BRACE LOWER DRAG BRACE DOWNLOCK STEERING ACTUATOR UPLOCK SHOCK STRUT TORQUE LINKS Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 15-01-07...
Page 442 NOSE GEAR DOWNLOCK SAFETY PIN A downlock safety pin, within the drag brace assembly, secures the nose landing gear in position while on ground. GROUND LOCKING DOWNLOCK ASSIST SPRING Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 15-01-08...
Page 443 UP, this restrictor will decrease hydraulic fluid flow which decreases the retraction speed and allows the NLG to retract smoothly and with less noise. Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1...
Page 444 However, landing gear retraction will only be initiated when the landing gear handle is moved to the UP position. After an actual gear failure situation, the manual release handle should be stowed only after landing and the gear pins are installed. PUSH PULL STOW Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 15-01-10...
Page 445: Tires And Brakes
NOTE: The brake wear indicator pins must be checked with the brakes applied and the left and right hydraulic systems pressurized. REV 1 Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 15-01-11...
Page 446 The emergency/parking brake valve meters hydraulic system pressure to all four main wheel brakes as commanded by the flight crew through the handle. Hydraulic pressure from the emergency/parking brake valve is connected to each of the main wheel brakes by shuttle valves. Differential braking is not possible with PARK/EMER BRAKE handle, and does not provide anti-skid protection.
Page 447: Brake Control System
VALVE SYSTEM FUSE PRESSURE TRANSDUCER WHEEL SPEED TRANSDUCER BRAKE SHUTTLE LEGEND VALVE HYDRAULIC SYSTEM EMERGENCY AND BRAKE PRESSURE PARKING BRAKE VALVE (REF) HYDRAULIC RETURN ELECTRICAL REV 1 Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 15-01-13...
Page 448 The main and park/emergency brake accumulators are located on the aft side of the underwing fairing support frame. The parking/emergency brake accumulator is connected to a gauge and charge valve that is located in the rear fuselage battery compartment. BRAKE ACCUMULATOR PARK/EMERGENCY BRAKE ACCUMULATOR Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 15-01-14...
Page 449: Nosewheel Steering
- Left hydraulic system is pressurized - Nose landing gear is down - The locked and a weight-on-wheels signal is present - NWS selected on REV 1 Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 15-01-15...
Page 450: Steering Control System
SYSTEM STEERING MAINFOLD PSEU NOSE LANDING STEERING TO EICAS GEAR DOWN CONTROL UNIT AND LOCKED RUDDER PEDALS NOSEWHEEL STEERING SWITCH STEERING HANDWHEEL PILOT'S SIDE PANEL REV 1 Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 15-01-16...
Page 451: Landing Gear Indications
GEAR IN TRANSIT AND GEAR DISAGREE AND NO GEAR WARNING GEAR IN TRANSIT AND GEAR WARNING DATA FROM BOTH PSS SUBSYSTEMS NOT AVAILABLE OR INVALID REV 1 Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 15-01-17...
Page 452 Flight deck controls activate normal gear extension and retraction, emergency extension, nosewheel steering, and warning horn mute. The EICAS presents indications of landing gear operation. TAWS WARN TERRAIN FLAPS LANDING GEAR VLO 200 VLO 250 VLE 250 REV 1 Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 15-01-18...
Page 453 LANDING GEAR CONTROLS AND INDICATIONS (Cont) LANDING GEAR (UP) REV 1 Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 15-01-19...
Page 454 LANDING GEAR CONTROLS AND INDICATIONS (Cont) LANDING GEAR (DOWN) REV 1 Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 15-01-20...
Page 455: Nws Switch
TRIM TRIM STAB STAB GEAR GEAR GEAR FLAPS FLAPS SPOILERS SPOILERS GEAR DOWN CAB ALT CAB ALT 7300 7300 CAB RATE CAB RATE 1000 1000 REV 1 Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 15-01-21...
Page 456 There may be damage to the NLG EXCEEDED feedback link L (R) OUTBD BRAKE The respective (left or right but not both) out- FAIL board normal system brake has failed Volume 2 Flight Crew Operating Manual Sep 14/2005 REV 4 CSP 100-6 15-01-22...
Page 457 The nose wheel steering has been selected NWS OFF PARK/EMER BRAKE Park brake pressure is sensed while on the ground REV 2 May 06/2005 Flight Crew Operating Manual Volume 2 REV 2 CSP 100-6 15-01-23...
Page 459 Components and Operation..................16-01-09 Airstair Lighting........................16-01-10 Cargo and Service Compartments Lighting ................ 16-01-11 Components and Operation..................16-01-11 External Aircraft Lighting ..................... 16-01-12 EICAS Messages ........................ 16-01-13 REV 2 May 06/2005 Flight Crew Operating Manual Volume 2 REV 2 CSP 100-6 16-00-01...
Page 461: Aircraft Lighting
The switch for this light is activated by the stowage door, so that the light illuminates only when the door is open. Two flight crew reading lights are provided to illuminate the pilot and copilot’s lap area. They are recessed in the headliner on each side of the cockpit, to avoid head impact to the pilots.The light can be rotated up to + 30°.
Page 462 GSHLD/L SIDE DIMMER GSHLD/R SIDE INSP STROBE BELTS PEDESTAL DOME ZONE 2 LANDING EMER LTS N LDG/TAXI ANNUN CB PANELS DIMMER ZONE 4 ZONE 4 CB PANELS Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 16-01-02...
Page 463 This push button switch controls the brightness of the other switches from DIM to BRT as well as off. PFD/MFD Display units have internal lighting, and the intensity is controlled through the PFD/MFD potentiometer. Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6...
Page 464 Display units have internal lighting, and the intensity is controlled by the MFD/PFD potentiometer. CB PANELS CB PANELS This potentiometer controls the intensity of lighting to the pilot and copilot circuit breaker panels. Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 16-01-04...
Page 465: Standby Instrument Lighting
These standby instruments are as follows: - Standby compass - Standby instrument - Clock LIGHT UNIT STANDBY COMPASS 1013 hPa GPS/ MONTH MODE 29.92 in CAGE BARO STANDBY INSTRUMENT CLOCK Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 16-01-05...
Page 466 Flashlights are installed in holders behind the pilot’s and copilot’s seats, below the circuit breaker panels. Flashlights are also located in the lavatory area of the cabin. FLIGHT COMPARTMENT FLASHLIGHT Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 16-01-06...
Page 467: Emergency Lighting
LIGHT EMERGENCY EXIT SIGN CABIN FLOOR EXTERIOR TRACK EMERGENCY LIGHTING LIGHT FLOOR TRACK FLOOR LEVEL LIGHTING EMERGENCY EXIT SIGN EXIT FLOOR TRACK EMERGENCY EXIT LIGHTING EXIT SIGN Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 16-01-07...
Page 468: External Lights
The L and R LANDING switches, located on the LIGHTING control panel, activates the left and/or right HID landing lights respectfully. LIGHTING WING SMKG/ STROBE INSP BELTS LANDING EMER LTS N LDG/TAXI Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 16-01-08...
Page 469: Entrance And Cabin Lighting
Control of the SMKG/BELTS is through a switch on the LIGHTING control panel, located on the center pedestal. The three-position switch is labeled OFF, BELTS, SMKG/BELTS. SMKG/ BELTS PAX SIGNS ELECTRONIC CHIME REV 2 May 06/2005 Flight Crew Operating Manual Volume 2 REV 2 CSP 100-6 16-01-09...
Page 470: Airstair Lighting
LIGHTING AIRSTAIR LIGHTING STAIR LIGHT MICROSWITCH Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 16-01-10...
Page 471: Cargo And Service Compartments Lighting
The auto shut-off box may be switched from the normal operation to standby operation via two quick clicks. AFT COMP LIGHT SWITCH BAG EXT LIGHT SWITCH AUTO-SHUTOFF DEVICE BAGGAGE-COMPARTMENT EXTERNAL LIGHT AFT EQUIPMENT- COMPARTMENT LIGHT Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 16-01-11...
Page 472: External Aircraft Lighting
WING LANDING BEACON INSPECTION LIGHT LIGHT TAXI-LANDING LANDING WING LIGHTS NAV/ANTI-COLLISION LIGHT INSPECTION LIGHTS LIGHT NAV/ANTI-COLLISION LIGHTS NAV/ANTI-COLLISION LIGHTS NAV/ANTI-COLLISION LIGHTS BEACON LANDING LIGHT TAXI-LANDING LIGHTS BEACON Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 16-01-12...
Page 473 MEANING WARNING The cabin emergency lights are off when they EMER LIGHTS OFF should be armed EMER LIGHTS ON The cabin emergency lights are on REV 2 May 06/2005 Flight Crew Operating Manual Volume 2 REV 2 CSP 100-6 16-01-13...
Page 474 MESSAGE INHIBITS MEANING WARNING The cabin emergency lights are off when they EMER LIGHTS OFF should be armed EMER LIGHTS ON The cabin emergency lights are on Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 16-01-14...
Page 475 Terrain Clearance Floor (TCF) ................... 17-01-29 Annunciations ......................17-01-30 Weather Radar ........................17-01-31 Description ......................... 17-01-31 Components and Operation..................17-01-31 Weather Radar Operational Modes ................17-01-31 Radar Antenna......................17-01-32 REV 2 May 06/2005 Flight Crew Operating Manual Volume 2 REV 2 CSP 100-6 17-00-01...
Page 476 Global Positioning System (GPS) ................17-01-34 Predicted RAIM......................17-01-35 Required Navigation Performance (RNP)..............17-01-35 Satellite Deselect ....................... 17-01-35 Controls and Indications...................... 17-01-36 Navigation Components..................... 17-01-36 EICAS Messages ........................ 17-01-37 Volume 2 Flight Crew Operating Manual May 06/2005 REV 2 CSP 100-6 17-00-02...
Page 477 They receive inputs from TAWS and TCAS and distribute digital audio signals from the audio control panels (ACPs). REV 1 Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6...
Page 478: Vhf Navigation System
(BFO) signal. VHF NAVIGATION RECEIVERS Two VHF navigation receivers (NAV 1 and NAV 2) provide VHF omnirange (VOR), localizer (LOC), glideslope (GS) and marker beacon (MKR) signals to the navigation systems and flight crew. System Frequency Range Channel Spacing 108.00 to 117.9 MHz...
Page 479 -Turn the MENU knob to move the selection box to the TEST control. -Turn the DATA knob or push the PUSH SELECT button to select the TEST mode. Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6...
Page 480 -Turn the MENU knob to move the selection box to the TEST control -Turn the DATA knob or push the PUSH SELECT button to select the TEST mode Volume 2 Flight Crew Operating Manual May 06/2005 REV 2 CSP 100-6...
Page 481 4. To return to the TUNE page from a CONTROL page, push the line select key for the radio or push the TUN key. Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1...
Page 482 Hz output tone when a carrier is present, in addition to the residual audio/noise from the detected carrier. A data-load option may be included so that the BFO audio output will be “clean”, i.e., contain no noise, even under low signal strength conditions. Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6...
Page 483: Mode S Transponder System
ATC transponder does not reply to other aircraft TCAS interrogations. Also, mode C is not reported when interrogated by ATC. Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1...
Page 484 35 seconds from the closest point of approach and may, a short time later require a resolution advisory (RA). The TA provides the flight crew with the opportunity to visually acquire the intruding aircraft.
Page 485 When ON is selected all traffic is displayed - Transponder selection is on TRANSPONDER/TCAS radio sub menu. When ATC1 or ATC2 is the active transpon- der, the selected transponder is enlarged Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6...
Page 486 A traffic advisory (TA) is issued when an intruding aircraft penetrating the 35 second TCAS surveillance area and is con- sidered by the TCAS computer to be a possible threat. The traffic advisory provides the flight crew with an opportunity to use the TCAS page on the MFD to assist in visually locating the intruding aircraft.
Page 487 Clear Of Conflict Reposition to assigned altitude Maintain Vertical Speed, Maintain Maintain climb or descent rate Maintain Vertical Speed, Crossing Maintain climb rate Maintain Traffic, Traffic Traffic Advisory Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 17-01-11...
Page 488 All RA’s inhibited. (TA ONLY) and TA Aural message inhibited Below 1100 ft climbing Below 1000 ft AGL descending “DESCEND RA” inhibited Below 1200 ft climbing Below 1450 ft AGL “INCREASE DESCENT” inhibited Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 17-01-12...
Page 489: Terrain Awareness Warning System (Taws)
The primary purpose of the terrain awareness warning system (TAWS) is to provide alerts and warnings to avoid controlled flight into terrain (CFIT) and to provide detected windshear warning. The system provides the flight crew with aural alert messages and visual annunciations and displays in the event that the boundaries of any alerting envelopes are exceeded.
Page 490 A/ICE ELEC DISPLAY CONTROL PANEL (DCP) DME/H NAVSRC FRMT TR/WX MENU DATA TILT RANGE TUNE AUTO RADIO BRGSRC REFS RADAR TAWS WARN PANEL TAWS WARN FLAPS TERRAIN Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 17-01-14...
Page 491 BELOW GLIDESLOPE "DON'T SINKI" "TOO LOW-GEAR" "GLIDESLOPE" "TOO LOW-FLAPS" MODE 6 MODE 7 EXCESSIVE BANK ANGLE WINDSHEAR CAUTION/WARNING "BANK ANGLEI" "WINDSHEAR, WINDSHEAR" ALTITUDE CALL-OUTS "WINDSHEAR" "...FIVE HUNDRED..." Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 17-01-15...
Page 492 “PULL UP” warning. The aural warning is annunciated continuously until the condition is rectified. 2500 2000 "SINKRATE" 1500 "PULL UP!" "PULL UP!" 1000 2000 4000 6000 8000 DESCENT RATE (FEET/MINUTE) Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 17-01-16...
Page 493 PFD and generate an aural “PULL UP” warning. The aural and visual warning are annunciated continuously until the condition is rectified. 2500 "TERRAIN "PULL UP!" SPEED TERRAIN" EXPANSION 2000 1500 1000 "PULL UP!" 2000 4000 6000 8000 10000 TERRAIN CLOSURE RATE (FEET/MINUTE) Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 17-01-17...
Page 494 2B warning envelope is inhibited at an altitude below 30 feet AGL. 2500 "PULL UP!" "TERRAIN 2000 TERRAIN" 1500 1000 "PULL UP!" 2000 4000 6000 8000 10000 TERRAIN CLOSURE RATE (FEET/MINUTE) Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 17-01-18...
Page 495 This condition will remain until the airplane regains the initial altitude value. Mode 3 is inhibited for radio altitude values in excess of 1500 feet. 2500 2000 1500 1000 "DON'T SINK" "DON'T SINK" ALTITUDE LOSE (FEET) Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 17-01-19...
Page 496 WARNING AREA TOO LOW TERRAIN WARNING AREA "TOO LOW COMPUTED AIRSPEED (KTS) TERRAIN" AIRCRAFT SLOWED TO LESS THAN 190 KTS "TOO LOW TERRAIN" "TOO LOW GEAR" RUNWAY Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 17-01-20...
Page 497 "TOO LOW FLAPS" RUNWAY NOTE: Aural “TOO LOW FLAPS” warning can be silenced by selecting OFF on the FLAPS switch, which is located on the TAWS WARN panel. Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 17-01-21...
Page 498 1800 1600 WARNING AREA (>250 KTS) 1400 1200 WARNING AREA 1000 (<190 KTS) "TOO LOW 2800 1200 1600 2000 2400 TERRAIN" RADIO ALTITUDE (FEET) "TOO LOW TERRAIN" Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 17-01-22...
Page 499 SOFT ALERT AREA HARD ALERT AREA RUNWAY NOTE: The “GLIDESLOPE” aural warning can be muted by selecting the GS switch OFF, which is located on the TAWS WARN panel. Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 17-01-23...
Page 500 ±2 dots of either the glideslope or localizer. The callout is also generated during a backcourse approach. "FIVE HUNDRED" "MINIMUMS- MINIMUMS" RUNWAY Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 17-01-24...
Page 501 55°. The alert will be annunciated until the bank angle is decreased below said value. EXCESSIVE BANK ANGLE 1200 WARNING "BANK ANGLE BANK ANGLE" 150 FT 50 FT 30 FT ±10 ±20 ±30 ±40 ±50 ROLL ANGLE (±DEG) Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 17-01-25...
Page 502 INCREASING 1000 HEADWIND HEADWIND (KTS PER SEC) (KTS PER SEC) 2000 3000 WINDSHEAR WARNING DOWNDRAFT (FEET PER MIN) WINDSHEAR AREA CAUTION LAMP MICROBURST "WINDSHEAR WINDSHEAR WINDSHEAR" RUNWAY Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 17-01-26...
Page 503: Terrain Awareness Alerting
2. SOLID AMBER— Areas of terrain that satisfy the terrain caution alert criteria. 3. GREEN, AMBER, RED DOT PATTERN — Areas of terrain that are significantly close to the aircraft but do not satisfy warning alert or caution alert criteria. Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6...
Page 504 NOTE: When landing at an airport that is not in the database, TERRAIN functions can be in- hibited by selecting the TERRAIN switch OFF. The switch is located on the TAWS WARN panel. Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6...
Page 505 The amber GND PROX remains displayed until the airplane exits the alert envelope. "TOO LOW TERRAIN" 4 NM 12 NM 15 NM RUNWAY Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 17-01-29...
Page 506 2. SOLID AMBER— Areas of terrain that satisfy the terrain caution alert criteria. 3. GREEN, AMBER, RED DOT PATTERN — Areas of terrain that are significantly close to the aircraft but do not satisfy warning alert or caution alert criteria. Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6...
Page 507: Weather Radar
Light levels of thunderstorm cells (1-4 strikes) are yellow, medium level cells 5- 9 strikes) are red, and heavy level cells (over 9 strikes) are magenta. Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1...
Page 508 The antenna tilt is adjusted between -15 degrees (down) and + 15 degrees (up). The antenna maintains its stabilization with respect to the horizon regardless of the airplane attitude (within -15 to +15 degrees). ANTENNA Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6...
Page 509 Included in the operator’s guide is their website to obtain the latest performance database updates from Rockwell Collins Inc. CONTROL DISPLAY UNIT (CDU) EXEC FPLN LEGS PERF PREV NEXT MENU DATA P Q R Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 17-01-33...
Page 510: Dead Reckoning (Dr)
Pre-departure verification of GPS availabil- ity is required for GPS as a primary means of navigation before each flight. EV 2 Volume 2 Flight Crew Operating Manual May 06/2005 REV 2 CSP 100-6...
Page 511 Individual satellites can be deselected from use by entering the identifier for the satellite in the FMS. This function would be used if a satellite is NOTAM’d under test. When deselected, the FMS ignores the data from the satellite. May 06/2005 Flight Crew Operating Manual Volume 2 REV 2...
Page 512 P Q R S V W X Y Z CONTROL DISPLAY UNIT DME/H NAVSRC FRMT TR/WX TUNE MENU DATA TILT RANGE RADIO BRGSRC REFS RADAR DISPLAY CONTROL PANEL Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 17-01-36...
Page 513 TAWS GS WARN OFF awareness warning system has been selected The terrain warning function of the terrain aware- TAWS TERR OFF ness warning system has been selected OFF Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 17-01-37...
Page 515 Engine Starting System ....................... 18-01-14 Description ......................... 18-01-14 Components and Operation..................18-01-15 Starter Control Valve ....................18-01-15 Air Turbine Starter (ATS).................... 18-01-15 Start Sequence ......................18-01-15 Engine Motoring......................18-01-16 REV 2 May 06/2005 Flight Crew Operating Manual Volume 2 REV 2 CSP 100-6 18-00-01...
Page 516 Thrust Lever Quadrant and Engine Control Panel............. 18-01-23 Engine Start Controls ....................18-01-24 Air Cond/Bleed Control Panel ..................18-01-24 EICAS Display ......................18-01-25 EICAS Messages ........................ 18-01-25 Volume 2 Flight Crew Operating Manual May 06/2005 REV 2 CSP 100-6 18-00-02...
Page 517 SPINNER CENTER BODY COVER RING ASSEMBLY INNER RING ASSEMBLY EXHAUST HIGH PRESSURE MIXER LOW PRESSURE COMPRESSOR NOZZLE TURBINE ASSEMBLY FAN STATOR ASSEMBLY VANE ASSEMBLY ACCESSORY GEABOX ASSEMBLY Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 18-01-01...
Page 518: Engine Construction
TURBINE AIR INLET COMPRESSOR COMBUSTION SECTION SECTION SECTION SECTION EXHAUST BY-PASS SECTION SECTION ACCESSORY DRIVES LEGEND COLD BYPASS AIRFLOW HOT EXHAUST GASES Volume 2 Flight Crew Operating Manual May 06/2005 REV 2 CSP 100-6 18-01-02...
Page 519 The PMA is considered to be the primary source of ECU pow- er, with 28 VDC from the aircraft being the backup source. Aircraft 28 VDC power is required for starting and shutdown. May 06/2005 Flight Crew Operating Manual Volume 2 REV 2...
Page 520: Engine Fuel System
The L (R) ENGINE FIRE switches control the SOVs. At the engine, the fuel is pressurized, heated, filtered, metered, and distributed to the combustion chamber. All fuel sched- uling is controlled by the FADEC. Volume 2 Flight Crew Operating Manual May 06/2005 REV 2 CSP 100-6...
Page 521: Engine Control System
FLIGHT IDLE Flight idle refers to the idle setting used when the thrust lever is set to idle while airborne (weight-off-wheels). May 06/2005 Flight Crew Operating Manual Volume 2 REV 2 CSP 100-6 18-01-05...
Page 522: Engine Condition And Fault Reporting (Ecfr)
The system is integrated into the FADEC of each engine. ECFR EVENT SWITCH The EVENT switch is located on the engine control panel. The switch allows the flight crew to manually initiate data col- lection to the ECFR.
Page 523: Thrust Calculations
The programmed normal-rated takeoff thrust value is displayed on the MFD by the following indications: - Cyan caret - Cyan N digital reference - Cyan TO thrust mode annunciation for takeoff thrust May 06/2005 Flight Crew Operating Manual Volume 2 REV 2 CSP 100-6 18-01-07...
Page 524: Climb Thrust (Clb)
When the thrust levers are in any of the detents and a new bleed air demand is placed on the engines, the N target rpm may change to compensate for the new bleed-air demands. Volume 2 Flight Crew Operating Manual May 06/2005 REV 2 CSP 100-6...
Page 525: Engine Synchronization
R ENG FIRE APU FIRE FIRE FIRE FIRE FIRE EXT EVENT AUTO APR ARMED ARMED AUTO SYNC MACH HOLD L STARTER R STARTER IGNITION CRANK START CRANK START May 06/2005 Flight Crew Operating Manual Volume 2 REV 2 CSP 100-6 18-01-09...
Page 526: Mach Hold
L (R) ENG OIL PRESS HIGH (C). An imminent bypass of the oil filter is annunciated by a L (R) ENGINE OIL BYPASS (A) CAS message. REV 5 Volume 2 Flight Crew Operating Manual Feb 22/2006 REV 5 CSP 100-6...
Page 527: Engine Oil Level And Replenishment System
ENGINE NACELLE OIL LEVEL SIGHT GAGE REFUEL DEFUEL CONTROL PANEL ENGINE OIL TEMPERATURE Excessively high engine oil temperatures are displayed as L (R) ENG OIL TEMPERATURE HIGH (C) CAS message. REV 4 Sep 14/2005 Flight Crew Operating Manual Volume 2 REV 4 CSP 100-6 18-01-11...
Page 528: Engine Lubrication Schematic
AGB OIL LAST-CHANCE REDUCTION NOZZLES SCREEN ORIFICE TANK TEMPERATURE DRAIN PLUG TRANSDUCER SUMP SUPPLY OIL PRESSURE FORWARD TRANSDUCER SUMP SUPPLY (DUAL SWITCH) DE-OIL VALVE LEGEND VENT FUEL Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 18-01-12...
Page 529: Engine Bleed Air System
The nacelle bleed-air ducts are monitored for bleed-air leakage by the engine fire detection system. Refer to Chapter 2, Air Conditioning and Pressurization, and Chapter 14, Ice and Rain Protection for more discussion on the bleed air system. Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6...
Page 530: Engine Starting System
FIRE FIRE EXT EVENT ARMED ARMED AUTO APR AUTO MACH HOLD SYNC INTEGRATED L STARTER R STARTER CRANK START CRANK START IGNITION SYSTEM (IAS) ENGINE CONTROL PANEL Volume 2 Flight Crew Operating Manual May 06/2005 REV 2 CSP 100-6 18-01-14...
Page 531: Starter Control Valve
If the start valve fails to close after achieving 50% N , a L (R) STARTER FAIL ON (C) CAS message is shown Refer to the Airplane Flight Manual for starter limits. May 06/2005 Flight Crew Operating Manual Volume 2 REV 2 CSP 100-6...
Page 532: Engine Motoring
When the affected engine’s ENGINE RUN switch is placed in the OFF position, the L (R) ENGINE FLAMEOUT caution message is replaced by the L (R) ENGINE SHUTDOWN (S) message. Volume 2 Flight Crew Operating Manual May 06/2005 REV 2...
Page 533: Thrust Levers
The reverse thrust setting is for ground use only. May 06/2005 Flight Crew Operating Manual Volume 2 REV 2...
Page 534 LEVER THRUST IDLE IDLE IDLE IDLE FORWARD THRUST IDLE REVERSE TO/GA TO/GA THRUST TOGA SWITCH (2) MAX REV MAXIMUM L ENGINE R ENGINE REVERSE FRICTION THRUST KNOB Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 18-01-18...
Page 535: Thrust Reverser System
- Maintenance test switch — allows thrust reverser operation without engine operating UPPER DOOR UPPER ACTUATOR UPPER TERTIARY LOCK ELECTRO-HYDRAULIC PRIMARY LOCK HYDRAULIC PRIMARY LOCK LOWER TERTIARY LOCK LOWER DOOR LOWER ACTUATOR Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 18-01-19...
Page 536 THRUST REVERSER STOWED FORWARD THRUST ACTUATOR UPPER DOOR EXHAUST UNIT FIXED STRUCTURE THRUST REVERSER DEPLOYED REVERSE THRUST EXHAUST NOZZLE EXHAUST LOWER DOOR CONE ACTUATOR THRUST REVERSER DEPLOYED REVERSE THRUST Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 18-01-20...
Page 537: Reverse Thrust Operation
As the aircraft decelerates, the maximum N is reduced which limits thrust reverser authority and also helps prevent thrust reverser controllability problems. Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 18-01-21...
Page 538: Vibration Monitoring System
CAS message. STANDARD WIRING LOW NOISE CABLE EICAS ENGINE CONTROL UNIT AIRFRAME LEFT ENGINE RIGHT ENGINE SPEED SPEED PROBE PROBE SPEED SPEED PROBE PROBE VIBRATION VIBRATION TRANSDUCER TRANSDUCER Volume 2 Flight Crew Operating Manual Sep 13/2004 REV 1 CSP 100-6 18-01-22...
Page 539: Controls And Indications
FIRE EXT EVENT AUTO APR TO/GA TO/GA ARMED ARMED AUTO SYNC MACH HOLD L STARTER R STARTER L ENGINE R ENGINE IGNITION CRANK START CRANK START REV 2 May 06/2005 Flight Crew Operating Manual Volume 2 REV 2 CSP 100-6 18-01-23...
Page 540: Engine Start Controls
R BLEED XBLEED EICAS DISPLAY 85.0 MCT 85.0 MCT 93.0 61.0 MACH HOLD 84.7 84.7 OIL PRESS OIL TEMP 7300 FF PPH 7300 APU RPM APU EGT Volume 2 Flight Crew Operating Manual May 06/2005 REV 2 CSP 100-6 18-01-24...
Page 541: Eicas Messages
The respective engine oil pressure is high HIGH L (R) ENGINE A higher than normal level of vibration has been VIBRATION TO/LAND sensed in the respective engine REV 4 Sep 14/2005 Flight Crew Operating Manual Volume 2 REV 4 CSP 100-6 18-01-25...
Page 542 The respective engine oil filter is impending TO/LAND BYPASS bypass ENGINE SYNC FAIL TO/LAND The engine sync mode has failed L (R) ENG VIBRATION TO/LAND Loss of vibration signal from affected engine FAIL Volume 2 Flight Crew Operating Manual Sep 14/2005 REV 4 CSP 100-6 18-01-26...
Page 543 RUN switch OFF or the respective FIRE switch SHUTDOWN pushed The respective thrust reverser is inoperative L (R) REVERSER INOP and is mechanically pinned, hydraulically and electrically isolated Sep 14/2005 Flight Crew Operating Manual Volume 2 REV 4 CSP 100-6 18-01-27...
Page 544 Instruction Sheet Challenger 300 Flight Crew Operating Manual - Volume 2 REVISION 1 1/04 Sep 13/2004 Flight Crew Operating Manual Volume 2 CSP 100-6...

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Challenger 300