ASA CRJ Flight Deck [PDF]

Zitiervorschau

CRJ 200 Flight Deck Picture Book

Revision 1

Published by: Atlantic Southeast Airlines Flight Training Department

THIS DOCUMENT IS FOR TRAINING PURPOSES ONLY.

No part of this publication may be reproduced or transmitted in any form or by any means, electronic or mechanical, including photocopy, recording, or any information storage and retrieval system, without prior permission in writing from ASA. All rights reserved. ©2008, Atlantic Southeast Airlines, Inc.

Contents Overhead Panel Electrical Panel Fire Detection Panel External Lights Panel Landing Lights Panel Fuel Panel Bleed Air Panel APU Panel Start / Ignition Panel Hydraulic Panel ELT / Oxygen Panel Pressurization Panel Air Conditioning Panel Anti-Ice Panel Miscellaneous Lights Panel Emergency Lights Panel

Standby Compass

1 Glareshield Panel 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17

Left Glareshield Flight Control Panel Right Glareshield

Side Panels Wipers / Stall Protection / Nose Wheel Steering Lighting Panel Display Control Panel Air Data Reference Panel Display Reversionary Panel Selector Valves Clocks

18

19 21 22 23

25 27 28 29 30 31 32 33

Instrument Panel Instrument Panel Primary Flight Display Multi-Function Display FMS Map Format HSI Format NAV Sector Format FMS Plan Map Format TCAS Format Radar Format EICAS Display 1 Primary Page EICAS Display 2 Status Page ECS Synoptic Page Hydraulic Synoptic Page Electrical Synoptic Page (AC) Electrical Synoptic Page (DC) Fuel Synoptic Page

35 37 38 39 39 40 41 42 43 44 45 45 46 46 47 48 49 50 51

Flight Control Synoptic Page Anti-Ice Synoptic Page Doors Synoptic Page EICAS Menu Page Standby Instruments - Analog Standby Instruments - Digital Cockpit Voice Recorder

Center Pedestal Flight Management System (FMS) Landing Gear Panel Miscellaneous Test Panel Ground Prox. Panel Pitch / Roll Disconnect Flight Spoiler Lever Thrust Levers Flap Lever Spoilers / Thrust Reversers Radio Tuning Unit

52 53 54 55 56 57 58

59 61 62 63 64 65 66 67 68 69 70

Audio Control Panel Radar Panel Backup Tuning Panel Stabilizer Trim Panel Avionics Cooling Panel Compass Control Panel Parking Brake Engine Control Panel EICAS Control Panel Aileron / Rudder Trim Panel Lighting Panel Yaw Damper Panel Interphone Panel Source Selector Panel Landing Gear Emergency Extension ADG Manual Deploy Handle ACARS Printer Cargo Fire Extinguishing Panel ADG Auto Deploy Panel

71 72 73 74 75 76 77 78 79 80 81 82 83 84 85 85 86 87 88

Glossary

89

Overhead Panel 1

2

DC SERVICE ON: Power the DC SERVICE bus from the battery when it has no other power source.

BATTERY MASTER ON: Power the BATTERY bus from both batteries.

EXTERNAL POWER DC, AC PRESSED IN: Enable use of associated external power. AVAIL: Associated external power is available for use. IN USE: Associated external power is being used.

AC ESS XFR PRESSED IN: Power the AC ESS BUS from AC BUS 2. ALTN: The AC ESS BUS is not being powered from AC BUS 1.

IDG DISCONNECT IDG1, IDG2 FAULT: High oil temperature or low oil pressure (HOTLOP) in the CSD. DISC: The IDG has disconnected from the accessory gear box. PUSH: Manually disconnect the IDG from the accessory gear box. Note: Once disconnected, the IDG can only be re-connected by maintenance.

GENERATOR CONTROL GEN1, APU, GEN2 ON: The generator is enabled. The GCU determines usage according to generator auto-transfer logic. OFF/RESET: The generator is removed from the electrical system and GCU faults are cleared.

AUTOTRANSFER 1, 2 FAIL: A GCU has disabled generator auto-transfer due to a bus fault. PRESSED IN/OFF: Generator auto-transfer has been manually disabled for the associated main AC bus.

DC POWER TIES TIE1, TIE2, ESS TIE PRESSED IN: Manually close the associated DC TIE. CLOSED: The associated DC tie has been closed.

Electrical Panel

3

LOOP TOGGLE SWITCHES L ENG, L JET, APU, R JET, R ENG BOTH: Both loops A and B are used for fire/overheat detection. (Normal operation). A: Only loop A is used for fire/overheat detection. B: Only loop B is used for fire/overheat detection.

ENGINE BOTTLE CARGO BOTTLE

1&2 (Spring loaded to NORM) TEST: Test the associated engine bottle squib circuits.

APU BOTTLE (Spring loaded to NORM) TEST: Test the APU bottle squib circuits.

4

TEST (Spring loaded to center) WARN: Simulates a fire. Tests loop continuity and the ability to detect a fire on all engine loops, all jet pipe loops, and the APU loops. FAIL: Simulates a short. Tests the short discriminator circuit on all engine loops, all jet pipe loops, and the APU loops.

Fire Detection Panel

(Spring loaded to NORM) TEST1: Simulates smoke on cargo smoke detector 1. TEST2: Simulates smoke on cargo smoke detector 2.

EXTERNAL LIGHTING SWITCHES ON: Associated lights are on. OFF: Associated lights are off. NAV: BEACON: STROBE: LOGO: WING INSP:

Navigation lights Red beacon Strobe lights Tail logo lights (disabled) Wing Inspection lights.

External Lights Panel

5

EXTERNAL LIGHTING SWITCHES ON: Associated lights are on. OFF: Associated lights are off. LEFT: NOSE: RIGHT: RECOG TAXI:

6

Left landing light Nose landing light Right landing light. Recognition / Taxi lights.

Landing Lights Panel

GRAVITY CROSSFLOW

BOOST PUMPS L,R ON: The boost pump is operating. INOP: The associated boost pump has not been armed, or has failed. PRESSED IN: Both boost pumps will operate if the associated main ejector loses pressure. PRESSED OUT: A loss of pressure at the associated main ejector will not cause the boost pumps to operate.

PRESSED IN/OPEN: The gravity crossflow valve is open. PRESSED OUT: Command the gravity crossflow valve to close. FAIL: The gravity crossflow valve is not in the commanded position.

MANUAL CROSSFLOW SWITCHES CROSSFLOW AUTO OVERRIDE PRESSED IN/MAN: The fuel crossflow system is in manual mode. PRESSED OUT: The fuel crossflow system is in automatic mode.

Fuel Panel

L,R PRESSED IN/ON: With the crossflow in manual mode, the respective crossflow SOV opens and the XFLOW/APU pump is energized. FAIL: The crossflow SOV is not in the commanded position.

7

14th STAGE BLEED VALVES L,R PRESSED IN: The associated engine bleed valve is commanded open. PRESSED OUT/CLOSED: The associated engine bleed valve is closed. DUCT FAIL: A leak has been detected in the ductwork on the associated side of the 14th stage bleed air manifold.

14th STAGE ISOLATION VALVE PRESSED IN: The isolation valve is commanded open. PRESSED OUT: The isolation valve is commanded closed. OPEN: The isolation valve is open.

DUCT MON (Spring loaded to NORM) NORM: Normal operation of the bleed leak detection loops. TEST: Test all bleed leak detection loops for continuity and the ability to detect a leak. LOOP A: Isolate 10th stage loop A. LOOP B: Isolate 10th stage loop B.

10th STAGE BLEED VALVES

APU LOAD CONTROL VALVE PRESSED IN: Command the APU LCV to open. PRESSED OUT: Command the APU LCV to close. OPEN: The APU LCV is open. FAIL: The APU LCV is not in the commanded position.

8

10th STAGE ISOLATION VALVE PRESSED IN: The isolation valve is commanded open. PRESSED OUT: The isolation valve is commanded closed. OPEN: The isolation valve is open.

Bleed Air Panel

L,R PRESSED IN: Command the associated engine bleed valve to open. PRESSED OUT: Command the associated engine bleed valve to close. CLOSED: The associated engine bleed valve is closed. DUCT FAIL: A leak has been detected in the duct work on the associated side of the 10th stage bleed air manifold.

POWER/FUEL PRESSED IN: The APU ECU is powered, APU fuel SOV opens, APU door opens, APU gauges appear on EICAS. PRESSED OUT: The APU door closes, APU fuel SOV closes, APU ECU is off, APU gauges disappear from EICAS. PUMP FAIL: The APU/CROSSFLOW pump has failed. SOV FAIL: The APU fuel SOV has failed.

START / STOP PRESSED IN: Start the APU. PRESSED OUT: Shutdown the APU. START: The APU starter is engaged. AVAIL: The APU is available for pneumatic loading. Note: ASA policy is to delay pneumatic loading for 2 minutes after APU start.

APU Panel

9

ENGINE STARTER (START) L,R PUSH: Engage air turbine starter on the associated engine. START: The associated engine air turbine starter is engaged.

CONTINUOUS IGNITION PRESSED IN/ON: Both engine ignition systems operate continuously. PRESSED OUT: Continuous ignition is disabled.

ENGINE STARTER (STOP) L,R PUSH: Manually disengage air turbine starter on the associated engine.

10

ENGINE IGNITION A,B PRESSED IN/ARM: Respective ignition system is armed. PRESSED OUT: Respective ignition system is disarmed. ON: Respective ignition system is active.

Start / Ignition Panel

ELECTRIC HYDRAULIC PUMP CONTROL ON: (Ground) Selected electric hydraulic pump will operate as long as any AC power source is available. (Flight) Selected electric hydraulic pump will operate as it’s power source is available. Pumps 1B and 2B require that the cross-side IDG is operating. OFF: Selected electric hydraulic pump is disabled. AUTO: Selected electric hydraulic pump will operate automatically when the flaps are not retracted and it’s power source is available. Pumps 1B and 2B require that the cross-side IDG is operating. 123A 3B -

Hydraulic pump 1B Hydraulic pump 2B Hydraulic pump 3A Hydraulic pump 3B

Hydraulic Panel

11

COCKPIT VOICE RECORDER MICROPHONE

EMERGENCY LOCATOR TRANSMITTER ARM/RESET: ELT is armed. ON: ELT is on.

12

ELT / Oxygen Panel

PASSENGER OXYGEN PRESSED IN/ON: Deploy passenger oxygen masks. PRESSED OUT: Normal operation.

MANUAL CABIN ALTITUDE DIRECTION LANDING ELEVATION TURN: Turn to set destination field elevation.

UP/DOWN/CENTER: Select to specify whether the cabin should climb, descend, or maintain altitude in manual pressurization mode.

EMERGENCY DEPRESS PRESSED IN/ON: Both outflow valves fully open until the cabin altitude reaches the cabin altitude limiter.

PRESSURIZATION CONTROL PRESSED IN/MAN: Select manual pressurization mode. PRESSED OUT: Select automatic pressurization mode. FAULT: Both cabin pressure controllers have failed.

MANUAL CABIN ALTITUDE RATE TURN: Turn to adjust cabin altitude rate of climb/descent in manual pressurization mode.

Pressurization Panel

13

PACKS L,R PRESSED IN: Associated PACK is turned on. PRESSED OUT/OFF: Associated PACK is off. FAULT: Associated PACK has shutdown due to over-temperature or over-pressure.

RAM-AIR PRESSED IN/OPEN: The RAM AIR valve is open. PRESSED OUT: The RAM AIR valve is closed.

PACK TEMPERATURE CONTROL

PACK TEMPERATURE CONTROL MODE

L, R (Spring loaded to center) HOT/COLD: Move toggle switch to manually adjust associated PACK output temperature while in manual temperature control mode.

L,R PRESSED IN/MAN: Associated PACK is in manual temperature control mode. PRESSED OUT: Associated PACK is in automatic temperature control mode.

CARGO AIR CONDITIONING OFF: Cargo air conditioning is disabled. FAN: The cargo compartment is conditioned with recirculated cabin air. COND AIR: The cargo compartment is conditioned with PACK air and an electric heater.

14

Air Conditioning Panel

PACK TEMPERATURE CONTROL COCKPIT, CABIN TURN: Turn knob to adjust cockpit or cabin temperature while in automatic temperature control mode.

WING ANTI-ICE

COWL ANTI-ICE

OFF: Wing anti-ice system is off. NORM: Wing anti-ice is on in normal mode. STBY: Wing anti-ice is on in standby mode.

L,R OFF: Respective engine cowl anti-ice is off. ON: Respective engine cowl anti-ice is on.

WING OVERHEAT SWITCH

ICE DETECTORS

PUSH: Test the wing overheat detection system. OVHT: A wing overheat condition has been detected. DUCT FAIL: A leak has been detected in a wing or fuselage anti-ice duct.

ICE: Ice has been detected and the aircraft antiice system is not configured correctly. PRESSED IN: Perform an ice detector system test.

WINDSHIELD HEAT OFF/RESET: Windshield heat is off and the temperature controller is reset. LOW: Windshield heat is set to low heat. HI: Windshield heat is set to high heat.

PROBE HEAT L,R OFF: Probe heat is off on the ground. In flight probes will operate. ON: Probe heat is on.

Anti-Ice Panel

15

COCKPIT DOME LIGHT OFF: Dome light is off. DIM: Dome light is on dim. ON: Dome light is on bright.

OVERHEAD PANEL BACKLIGHTING TURN: Adjust brightness of overhead panel integral lighting.

STANDBY COMPASS LIGHT OFF: Standby compass backlight is off. DIM: Standby compass backlight is on dim. ON: Standby compass backlight is on bright.

16

Miscellaneous Lights Panel

EMERGENCY LIGHTING STATUS OFF: Emergency lighting system is disabled.

EMERGENCY LIGHTS ON: Emergency lighting is on. OFF: Emergency lighting is disabled. ARM: Emergency lighting is armed and will illuminate if either essential bus loses power.

PASSENGER SIGNS ON: Respective sign is on. OFF: Respective sign is off. AUTO: Respective sign is off, but will turn on automatically in the event of a loss of cabin pressure or gear/flap extension.

Emergency Lights Panel

17

COMPASS CORRECTION CARD

ROTATING COMPASS DIAL

18

Standby Compass

Glareshield Panel 19

20

STALL Illuminates when stick pusher activates. PUSH: On ground push to test the stall protection system.

SPOILERONS CONTROL Used to select which yoke controls spoilerons after a roll disconnect. ROLL SEL: Illuminates after a roll disconnect. PRESSED IN/PLT ROLL: Captain’s yoke controls both spoilerons. Automatically selected during right aileron PCU runaway.

MASTER WARNING Flashes with any new EICAS warning message. PUSH: to cancel warning.

LEFT ENGINE FIRE PUSH Illuminates with left engine fire indication. PRESSED IN: Closes left bleed, hydraulic, and fuel shut-off valves. Turns off left IDG. Arms squibs on both engine fire bottles.

FIRE BOTTLE 1 Illuminates when fire bottle squibs are armed. PUSH: Fire bottle discharges into the engine that has its FIRE PUSH switch pressed in.

MASTER CAUTION

GROUND PROXIMITY WARNING

Flashes with any new EICAS caution SYSTEM message. PULL UP: Flashes during GPWS PULL UP PUSH: to cancel caution. warnings. GND PROX: Flashes during GPWS cautionary alerts. PUSH: (Ground) Initiates GPWS system test. (Flight) Cancels glideslope deviation alerts.

Left Glareshield

21

XFR PUSH: Push to select which FCC provides flight director guidance.

COURSE KNOBS

AP ENG PUSH: Push to engage or disengage autopilot.

1,2 TURN: Turn to adjust associated CDI needle. PUSH: Push to set CDI needle to direct course.

FLIGHT DIRECTOR MODE SELECTORS SPEED, APPR, B/C, HDG, NAV, ALT, VS PUSH: Push to put flight director in respective mode.

AP DISC

SPEED KNOB

HEADING KNOB

PULL DOWN: Pull down TURN: Turn to adjust speed to disengage autopibucket. lot. Autopilot cannot PUSH: Push to toggle between be re-engaged until indicated and MACH airbar is pushed back up. speed.

TURB PUSH: Push to toggle turbulence mode (reduced autopilot gain).

22

TURN: Turn to adjust heading bug. PUSH: Push to set heading bug to current heading.

ALTITUDE KNOB TURN: Turn to adjust altitude selector. PUSH: Push to cancel altitude deviation alerts.

1/2 BANK PUSH: Push to toggle 1/2 bank turns.

Flight Control Panel

FD BUTTONS x2 PUSH: Removes flight director from one or both PFD’s.

PITCH WHEEL ROTATE: to adjust selected pitch attitude (when in PITCH mode) or vertical speed (when in VS mode).

RIGHT ENGINE FIRE PUSH Illuminates with right engine fire indication. PRESSED IN: Closes right bleed, hydraulic, and fuel shut-off valves. Turns off right IDG. Arms squibs on both engine fire bottles.

APU FIRE PUSH Illuminates with APU fire indication. PRESSED IN: Closes LCV and fuel shutoff valve. Turns off APU generator. Arms APU fire bottle squibs.

SPOILERONS CONTROL Used to select which yoke controls spoilerons after a roll disconnect. ROLL SEL: Illuminates after a roll disconnect. PRESSED IN/CPLT ROLL: First Officer’s yoke controls both spoilerons. Automatically selected during left aileron PCU runaway.

APU FIRE BOTTLE Illuminates when fire bottle squibs are armed. PUSH: Fire bottle discharges into the APU compartment.

FIRE BOTTLE 2

GROUND PROXIMITY WARNING SYSTEM

PULL UP: Flashes during GPWS PULL UP Illuminates when fire bottle warnings. squibs are armed. GND PROX: Flashes during GPWS cautionary PUSH: Fire bottle discharges alerts. into the engine that has PUSH: (Ground) Initiates GPWS system test. its FIRE PUSH switch (Flight) Cancels glideslope deviation pressed in. alerts.

STALL Illuminates when stick pusher activates. PUSH: On ground push to test the stall protection system.

MASTER WARNING Flashes with any new EICAS warning message. PUSH: to cancel warning.

MASTER CAUTION Flashes with any new EICAS caution message. PUSH: to cancel caution.

Right Glareshield

23

24

Side Panels 25

26

NOSE WHEEL STEERING ARMED: Nose wheel steering is activated on the ground. OFF: Nose wheel steering is off. Nose wheel will free castor.

STALL PROTECTION

WINDSHIELD WIPERS OFF/PARK: Wipers are off. SLOW: Wipers operate at low speed. FAST: Wipers operate at high speed.

(Stick Pusher) ON: Stick pusher is armed. OFF: Stick pusher is disabled.

NOTE: The windshield wipers will operate at the faster of the captain’s and first officer’s wiper speed selection.

NOTE: Both captain and first officer STALL PROTECTION pusher switches must be on to enable the stick pusher.

Wipers / Stall Protection / Nose Wheel Steering

27

FLOOR LIGHTING ON/OFF: Control floor level lighting.

DISPLAY LIGHTING TURN: Adjust brightness of PFD and MFD.

28

INTEGRAL LIGHTING

FLOOD LIGHTING

TURN: Adjust brightness of side panel back lighting.

TURN: Adjust brightness of side panel flood lighting.

Lighting Panel

MFD FORMAT / RANGE TURN OUTER: Select MFD format. TURN INNER: Select MFD range.

BEARING POINTERS

NAV SOURCE TURN: Select navigation source for associated HSI needle. (FMS, on-side VOR/LOC, cross-side VOR/LOC. PUSH: Enable display of cross-side navigation information. Works only in HSI and NAV SECTOR MFD formats.

PUSH: Enable/disable display of bearing pointers on the EFIS. Single arrow pointers use captain’s side or FMS NAV sources. Double arrow pointers use F/O side NAV sources.

TRAFFIC

RADAR / TERRAIN PUSH: Control overlay of radar and EGPWS information on the MFD. Cycles between radar, terrain, and no overlay.

PUSH: (MFD range 40 miles) Display TCAS format on MFD

Display Control Panel

29

DH / MDA TURN OUTER: Select between DH (radar) and MDA (barometric) minimums. TURN INNER: Adjust selected minimums value. PUSH INNER: Toggle display of minimums on the associated PFD.

HPA / IN PUSH: Switch between hectopascals and inches for altimeter setting.

SEL PUSH: Switch between V1 VR and V2 when SPEED REFS knob is set to VSPDS.

SPEED REFS TURN OUTER: Select TGT to set VT. Select VSPDS to set V1 VR and V2. TURN INNER: Turn to adjust selected speed. PUSH INNER: Toggle display of selected speed on the associated PFD.

30

RADAR ALTIMETER TEST PUSH: Initiate radar altimeter test.

Air Data Reference Panel

BARO TURN: Adjust altimeter setting on associated PFD. PUSH: Set altimeter setting to 29.92.

DISPLAY REVERSION NORM: Associated MFD operates normally. PFD: Associated PFD is disabled. PFD information is displayed on the MFD. EICAS: EICAS status page is displayed on the associated MFD. The EICAS control panel can be used to display other EICAS pages.

Display Reversionary Panel

31

PITOT SELECTOR VALVE

STATIC SELECTOR VALVE

PUSH DOWN: to close the pitot system selector valve. This removes the on-side mach transducer from the pitot system.

PUSH DOWN: to close the static system selector valve. This removes the on-side mach transducer from the static system.

NOTE:

32

Selector valves are not installed on aircraft with electronic standby instruments. The select valve switches are connected together. The pitot and static valves must be opened or closed together.

Selector Valves

CHRONOMETER PUSH: Start/Stop/Reset chronometer.

MODE SELECTOR Change display mode. DATE: Display date LOC: Display local time GMT: Display UTC time. SET: Set time and date.

CHRONOMETER PUSH: Start/Stop/Reset chronometer.

Note: There are two types of clocks installed on ASA aircraft. They are used interchangeably.

Clocks

33

34

Instrument Panel 35

36

STANDBY INSTRUMENTS

EICAS DISPLAY 1 (ED1)

PRIMARY FLIGHT DISPLAY (PFD)

EICAS DISPLAY 2 (ED2)

MULTI-FUNCTION DISPLAY (MFD)

MULTI-FUNCTION DISPLAY (MFD)

Instrument Panel

PRIMARY FLIGHT DISPLAY (PFD)

37

38

Primary Flight Display

Multi-Function Display

FMS Map Format

39

40

HSI Format

NAV Sector Format

41

42

FMS Plan Map Format

TCAS Format

43

44

Radar Format

EICAS Display 1

Primary Page

45

46

EICAS Display 2

Status Page

ECS Synoptic Page

47

48

Hydraulic Synoptic Page

Electrical Synoptic Page (AC)

49

50

Electrical Synoptic Page (DC)

Fuel Synoptic Page

51

52

Flight Control Synoptic Page

Anti-Ice Synoptic Page

53

54

Doors Synoptic Page

EICAS Menu Page

55

56

Standby Instruments - Analog

Standby Instruments - Digital

57

TEST BUTTON & LIGHT PUSH: Push and hold test button for 5 seconds to test CVR. The test light illuminates while the test button is held to indicate a successful test.

58

Cockpit Voice Recorder

ERASE BUTTON PUSH: Push to erase CVR.

Center Pedestal 59

60

Flight Management System (FMS)

61

GEAR HORN MUTE

BTMS OVERHEAT RESET PUSH: Push to reset BTMS indicators to green after a brake overheat.

PRESSED IN/MUTED: The landing gear warning horn is muted in some, but not all, configurations.

ANTI-SKID ARMED: The anti-skid system is armed. OFF: The anti-skid system is disabled.

LANDING GEAR HANDLE UP/DN: Select to extend or retract the landing gear.

ANTI-SKID TEST (Spring loaded) TEST: Perform a test of the anti-skid system. Parking brake must be off for a successful test.

MLG BAY OVERHEAT WARNING TEST (Spring loaded) OVHT: Simulate an overheat in the main landing gear overheat detection loop.

62

MLG BAY OVERHEAT FAIL TEST (Spring loaded) FAIL: Simulate a short in the main landing gear overheat detection loop.

Landing Gear Panel

DOWNLOCK RELEASE LIFT: Lift to override the solenoid that prevents the landing gear handle from being raised on the ground.

OVERSPEED TEST (Spring loaded to center) 1: Test overspeed clacker for air data computer 1. 2: Test overspeed clacker for air data computer 2.

FDR EVENT PUSH: Push to insert marker on FDR recording.

LAMP TEST (Spring loaded to center) 1: Test switch-lights using DCU1. 2: Test switch-lights using DCU2.

INDICATOR LIGHTS BRIGHTNESS BRT: Illuminate switch-lights using high intensity. DIM: Illuminate switch-lights using low intensity.

AURAL WARNING TEST (Spring loaded to center) 1: Press up to start aural warning test using DCU1. Press up again to stop the test. 2: Press down to start aural warning test using DCU2. Press down again to stop the test.

Miscellaneous Test Panel

63

TERRAIN

FLAP

PRESSED IN/OFF: Press in to disable terrain floor EGPWS warnings. Used when landing on a runway that is not in the terrain database.

PRESSED IN/OVRD: Press in to disable “too low flap” warnings. Used when landing at a flap setting other than 45 degrees.

GROUND CREW CALL PUSH: Push to call ground crew. CALL light illuminates on external services panel. CALL: Ground crew is attempting to contact flight crew using external services panel.

64

Ground Prox. Panel

ROLL DISCONNECT

PITCH DISCONNECT PULL and TURN EITHER DIRECTION: to disconnect pitch control torque tube.

PULL and TURN EITHER DIRECTION: to disconnect roll control torque tube.

Pitch / Roll Disconnect

65

66

Flight Spoiler Lever

Thrust Levers

67

68

Flap Lever

GROUND LIFT DUMPING AUTO: The ground lift dumping system will arm automatically during the takeoff roll. MAN ARM: The ground lift dumping system is manually armed and will deploy when the aircraft is on the ground. MAN DISARM: The ground lift dumping system is disabled.

THRUST REVERSER EMERGENCY STOW

THRUST REVERSERS

L/R UNLK: The respective thrust reverser is unlocked. PUSH: Stow the unlocked thrust reverser.

L/R ARMED: The respective thrust reverser is armed and will deploy on pilot command. OFF: The respective thrust reverser is disabled.

Spoilers / Thrust Reversers

69

LINE SELECT KEYS

ATC IDENT DME HOLD CROSS SIDE TUNING

TUNING KNOB

LINE SELECT KEYS 70

Radio Tuning Unit

TRANSMIT KNOB TURN: to select transmitter.

VHF COMM RADIOS

INTERCOM

1&2 PRESSED IN: to enable audio. PRESSED OUT: to disable audio. TURN: to adjust volume.

PRESSED IN: to enable audio. PRESSED OUT: to disable audio. TURN: to adjust volume.

DME 1&2 PRESSED IN: to enable audio. PRESSED OUT: to disable audio. TURN: to adjust volume.

ADF RADIOS 1&2 PRESSED IN: to enable audio. PRESSED OUT: to disable audio. TURN: to adjust volume.

NAV RADIOS 1&2 PRESSED IN: to enable audio. PRESSED OUT: to disable audio. TURN: to adjust volume.

MARKER BEACONS 1&2 PRESSED IN: to enable audio. PRESSED OUT: to disable audio. TURN: to adjust volume.

PTT SWITCH R/T: Transmit on device selected by the transmit knob. I/C: Transmit over the intercom circuit (hot mic). CENTER: Microphone is off.

VOICE/ID BOTH: Both voice and ident code is heard on NAV radios. VOICE: Voice only is heard on NAV radios.

EMERGENCY

SPEAKER

MIC SELECT

MASK: Oxygen mask microPRESSED IN: to enable speaker. phone is selected. PRESSED OUT: to disable speaker. BOOM: Headset microphone is TURN: to adjust volume. selected.

Audio Control Panel

NORM: Normal operation. EMER: (Captains Side) Captain’s headset connected to COM1 NAV1 only. (F/O’s Side) First Officer’s headset connected to COM2 NAV2 only. (Observer) Switch is inoperative.

71

SECTOR SCAN PUSH: to toggle scan between 60 and 120 degrees.

TRANSFER PUSH: to select which pilot controls radar range.

STABILIZATION PUSH: to enable/disable antenna stabilization.

GAIN ADJUSTMENT TURN: to adjust receiver gain. PUSH: to enable ground clutter suppression.

72

MODE SELECTOR

TILT

OFF: Radar is off. TEST: Radar is in self-test mode. Transmitter is disabled. MAP: Radar is on in ground mapping mode. WX: Radar is on in weather mode.

TURN: to adjust antenna tilt. PUSH: to enable/disable antenna auto-tilt. When enabled tilt will automatically adjust with altitude changes.

Radar Panel

RTU INHIBITS 1&2 PRESSED OUT: Normal RTU operation. PRESSED IN: Respective RTU is disabled. Opposite RTU can be used to tune cross-side radios.

COM1 / NAV1 FREQUENCY DISPLAY

COM/NAV SWITCH COM: COM frequency can be changed using tuning knob. NAV: NAV frequency can be changed using tuning knob.

FMS TUNE INHIBIT UP: Normal operation. All radios can be tuned from FMS RADIO page. INHIBIT: The FMS is prevented from tuning all radios.

TRANSPONDER SELECTOR STBY: Transponders are off. 1: Transponder 1 is on. 2: Transponder 2 is on.

TUNING KNOB MODE SELECTOR

TURN: to adjust COM1 or NAV1 as selected by COM/NAV switch.

OFF: Backup tuning unit is off. STBY: Backup tuning unit is on in standby mode. Frequencies are viewable but cannot be tuned using the backup tuning unit. ON: Backup tuning unit is on and can be used to tune COM1 and NAV1.

Backup Tuning Panel

73

STABILIZER TRIM CHANNELS 1 & 2 PUSH: to enable respective channel of the Horizontal Stabilizer Trim Control Unit (HSTCU).

74

MACH TRIM PUSH: to enable/disable MACH trim.

Stabilizer Trim Panel

DISPLAY FAN

ARINC FAN

NORM: Display cooling fans operate normally. GND ALTN: The ground alternate fan (i.e. the fan normally used in flight) is used for display cooling at all times. FLT ALTN: The flight alternate fan (i.e. the fan normally used on the ground) is used for display cooling at all times. STDBY: The standby cooling fan is used for display cooling.

NORM: Avionics cooling fans operate normally. GND ALTN: The ground alternate fan (i.e. the fan normally used in flight) is used for avionics cooling at all times. FLT ALTN: The flight alternate fan (i.e. the fan normally used on the ground) is used for avionics cooling at all times.

Avionics Cooling Panel

75

SLEW

COMPASS MODE CONTROL MAG: Magnetic flux detectors are used to correct for gyro precession. DG: Magnetic flux detectors are disabled.

76

+/-: Manually slew AHRS heading in selected direction.

Compass Control Panel

PARKING BRAKE PULL and TURN EITHER DIRECTION while holding toe brakes to set parking brake.

Parking Brake

77

APR TEST (Spring loaded to OFF) TEST 1: APR is tested using DCU1. TEST 2: APR is tested using DCU1.

APR ARM: APR operates normally and will ARM during takeoff. OFF: APR is disabled.

ENGINE VIBRATION MONITOR (Spring loaded to OFF) TEST: Initiate test of vibration monitor system. OFF: Vibration monitor operates normally.

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Engine Control Panel

ENGINE SPEED SWITCHES LH & RH ON: Respective engine’s electronic control unit (ECU) is enabled. Fuel is metered electronically above 79% N1. OFF: Respective engine’s electronic control unit (ECU) is disabled. Fuel is metered mechanically at all times.

STAT BUTTON PUSH: to page through and box status messages.

PAGE SELECT BUTTONS PUSH: to display respective page on the EICAS.

STEP BUTTON PUSH: to sequence through EICAS pages one at a time.

CAS BUTTON PUSH: to page through and box caution messages.

SEL, UP & DOWN BUTTONS PUSH: to navigate through items on the EICAS MENU page.

Note: Caution messages can be boxed only when a generator is on-line.

EICAS Control Panel

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AILERON TRIM (Split Switch) PUSH: both switches simultaneously to adjust aileron trim.

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RUDDER TRIM TURN: to adjust rudder trim.

Aileron / Rudder Trim Panel

DISPLAY LIGHTING TURN: to adjust brightness of EICAS displays, RTU’s, and FMS.

INTEGRAL LIGHTING TURN: to adjust brightness of pedestal backlighting.

FLOOD LIGHTING TURN: to adjust brightness of flood lighting under glareshield.

Lighting Panel

CIRCUIT BREAKER PANEL LIGHTING TURN: to adjust brightness of circuit breaker panel integral lighting.

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DISCONNECT PUSH: to disengage both yaw dampers.

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Yaw Damper Panel

ENGAGE YD1 & YD2 PUSH: to engage respective yaw damper.

PASSENGER ADDRESS PUSH: to enable PA system. Transmit knob on Audio Control Panel must also be set to PA.

CHIME PUSH: to sound HI/LO chime in cabin.

CALL PUSH: to call flight attendant. Transmit knob on Audio Control Panel must be set to PA.

Interphone Panel

EMERGENCY CALL PUSH: to call flight attendant. A cabin light will indicate to flight attendant that the call is urgent. The Transmit Knob on the Audio Control Panel must be set to PA.

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ATTITUDE / HEADING NORM: Both PFD’s use their on-side AHRS computer. 1: Both PFD’s use AHRS1. 2: Both PFD’s use AHRS2.

EICAS NORM: ED1 and ED2 operate normally. 1: ED1 is used for all EICAS information. ED2 is disabled. The EICAS Control Panel can be used to control ED1. 2: ED2 is used for all EICAS information. ED1 is disabled. The EICAS Control Panel can be used to control ED2.

DISPLAY CONTROLLER

AIR DATA NORM: Both PFD’s use their on-side Air Data Computers. 1: Both PFD’s use Air Data Computer 1. 2: Both PFD’s use Air Data Computer 2.

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NORM: Each EFIS is controlled by it’s on-side Display Control Panel. 1: Captain’s Display Control Panel controls all EFIS screens. 2: First Officer’s Display Control Panel controls all EFIS screens.

Source Selector Panel

LANDING GEAR EMERGENCY EXTENSION PULL: to manually release landing gear uplocks.

Landing Gear Emergency Extension

ADG MANUAL DEPLOY HANDLE PULL: to manually deploy Air Driven Generator (ADG).

ADG Manual Deploy Handle

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ACARS Printer

CARGO SMOKE Normal & Standby Both illuminate when smoke is detected by either cargo smoke detector. PRESS IN: to arm squibs on both cargo fire bottles.

CARGO BOTTLE

CARGO BOTTLE

NORMAL Armed by normal CARGO SMOKE button.

STANDBY Armed by standby CARGO SMOKE button.

PUSH: to discharge both cargo fire bottles.

PUSH: to discharge both cargo fire bottles.

Cargo Fire Extinguishing Panel

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POWER TRANSFER OVERRIDE

ADG TEST (Spring loaded to center) LAMP: Test green TEST lamp bulb. UNIT: Perform test of ADG transfer contactors and squib. Green TEST lamp illuminates momentarily to indicate a successful test.

PUSH: to transfer the AC ESS bus from the ADG to a normal power source.

Note: At least two generators must be online for a successful UNIT test.

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ADG Auto Deploy Panel

Glossary

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A ACMP ADC ADG AFCS AHRS APR APU ARINC ARP

D AC Motor Pump (Hydraulic) Air Data Computer Air Driven Generator Automatic Flight Control System Attitude Heading Reference System Automatic Power Reserve Auxiliary Power Unit Aeronautical Radio Incorporated Air Data Reference Panel

B B/C BITE BTMS

Back Course Built-in Test Equipment Brake Temperature Monitoring System

C CAS CDL CSD

DCP DCU DH DR DRP

Display Control Panel Data Concentrator Unit Decision Height Dead Reckoning Display Reversionary Panel

E ECS ECU ED EFIS EGPWS EICAS

Environmental Control System Electronic Control Unit EICAS Display Electronic Flight Instrument System Enhanced Ground Proximity Warning System Engine Instrumentation & Crew Alerting System

F Crew Alerting System Configuration Deviation List Constant Speed Drive

FCC FCP FD

Flight Control Computer Flight Control Panel Flight Director 91

FMA

Flight Mode Annunciator

G

MFD

Multi-Function Display

P

GCS GPWS

Ground Clutter Suppression Ground Proximity Warning System

H HSTCU

PBA PDU PFD PRSOV PSEU

Pushbutton Annunciator Power Drive Unit Primary Flight Display Pressure Regulating Shut-off Valve Proximity Sensing Electronic Unit

Horizontal Stabilizer Trim Control Unit

R

I I/C IAPS IDG ITT

Intercom Integrated Avionics Processing System Integrated Drive Generator Inter-Turbine Temperature

R/T REF RPM RTU

Radio Transmit Reference Speed Revolutions Per Minute Radio Tuning Unit

S

M MDA MEL

Minimum Descent Altitude Minimum Equipment List 92

SAT SOV

Static Air Temperature Shut-off Valve

T TAS TAT TCAS TRU

True Airspeed Total Air Temperature Traffic Collision Avoidance System Transformer Rectifier Unit

U UTC

Universal Time

W WOW

Weight on Wheels

X XFER

Transfer

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