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Aircraft Systems > Crj 700/900 Reference Manual > Flashcards

Crj 700/900 Reference Manual Flashcards

0
Q

The maximum operating altitude for both aircraft?

A

41,000 feet

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1
Q

The CRJ 900/700 is powered by

A

900: General Electric CF34-8C5
700: General Electric CF34-8C5B1

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2
Q

Noise and exhaust levels

A

The Crj easily meets the FAA’s most stringent rating system for the aircraft noise as defined by FAR part 36 stage 3 requirements. Exceptionally quiet during takeoff and landing. The CRJ has allowed a number of airlines to extend their operating hours at some airports. The engines are highly efficient and clean burning, which leads to very low exhaust emissions and lower fuel consumption

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3
Q

Automatic Flight Control System (AFCS)

A

Provides integration of the Flight Director and Autopilot Systems

The AFCS controls and supplies information to:
Dual independent flight directors.
Two axis autopilot
Automatic pitch trim
Two independent yaw dampeners

When the autopilot is engaged, the AFCS maneuvers the aircraft while the pilot monitors the flight path by observing the flight guidance information presented on the EFIS Displays.

When the autopilot is disengaged, the pilot manually flies the aircraft in response to guidance provided by the command bars on the PFD.

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4
Q

The automatic flight control system (AFCS) consist of the following system components.

A

Flight control panel (FCP)

Flight control. Computers (FCC)

Autopilot servo motors (2)

Yaw dampeners (2)

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5
Q

Integrated avionics information processing (IAPS)

Numerous electronic boxes were required to perform tasks associated with the AFCS, TODAY A SINGLE electronic component (IAPS) provides the interface between the various avionics systems.

Components and operation

A

Internally, the IAPS houses a number of computers and other electronic components. The integrated avionics information processing (IAPS) circuitry allows the computers contained within to communicate both internally and externally with other aircraft electronic components via a COMMON bus.

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6
Q

IAPS (integrated avionics information processing) continued.

Flight control computers (FCC) are mounted inside the IAPS and are the main AFCS microprocessors. The FCCs processes altitude and heading reference (AHRS) and air data computer (adc) information to calculate flight path and flight guidance parameters. The FCCs also receives information via the IAPS from:

A

Flight control panel

EICAS data concentrator units (DCU)

Radio systems

Flight management systems (FMS)

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7
Q

IAPS (integrated avionics information processing) continued.

The FCCs provide INSTRUCTION via the IAPS to:

A

Flight control panel

Flight directors on the PFDs

Yaw dampeners

Autopilot servo motors.

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8
Q

Flight directors (FD)

Description

A

The flight director is the visual representation of the commands generated by the flight control computer. The FD is displayed on the PFD as the command bars. The FD provide GUIDANCE commands to the autopilot and STEERING commands for the pilot when the aircraft is hand flown.

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9
Q

Flight directors (FD) continued

Components and operations.

A

Two independent flight directors, FD1 and FD2.

Most instances on FD provides flight guidance to the primary flight displays.

Other FD acts as standby and provides system redundancy and ensure accuracy of the flight guidance data, the active and standby always crosstalk.

Pilot uses FD1
Copilot uses FD2
Both can’t be active at the same time.

If the active FD fails, a red boxed FD appears on the PFD and a white FD1(2) FAIL EICAS status message is displayed. Selecting the XFR push button on the FCP deselects the failed flight director and allows the standby flight director to become active.

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10
Q

Flight directors (FD) continued

Components and operations.

Both FDs become active and supply guidance instructions to their associated PFD when in the following modes:

A

Takeoff (TOTO) mode

Approach (APPR) mode

Go around (GAGA) mode

When operating independently, flight control computer 1 controls flight director 1 and displays guidance instructions only on PFD 1. FCC2 controls flight director 2 and displays guidance instructions only on PFD 2.

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11
Q

The Crj has the following doors

A 
Passenger door
Galley service door 
Avionics bay door
Forward cargo bay door
Center cargo bay door (CRJ900)
Aft cargo bay door
Aft equipment bay door
Passenger door
Service overhead escape hatch.
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12
Q

How many emergency exits on both CRJ 700 & 900

A

700 has five emergency exits
900 has seven emergency exits

Left and right overwing emergency exits on the 700
Two on left and right overwing emergency exits for 900.

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13
Q

What supplies door position data?

A

All doors except the aft equipment bay door and the overhead escape hatch, are monitored by the proximity sensing electronic unit (PSEU) that supplies door position to the EICAS primary and the door synoptic pages.

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14
Q

Maximum door load for passenger door

A

1000lbs or a maximum of 4 passengers on the stairway at a time.

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15
Q

Components and operation of passenger door

A

The door components consist of : a latch mechanism, a counterbalance mechanism, handrails, steps, and a power assist motor.

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16
Q

Stick pusher is connected to?

A

F/O SIDE

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17
Q

All plug doors are?

A

Emergency overwing exits

Aft cargo bay door

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18
Q

Semi-plug doors on CRJ

A

Forward/center cargo bay doors

Galley door on the right side

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19
Q

The engine indication and crew alerting system (EICAS) provides

A

Automatic system monitoring
Integration of system information
Color logic for presentation of minimum/maximum limits
Aural alert warning messages

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20
Q

The flight data recorder system (FDR)

A

Receives and stores aircraft flight data information for later analysis

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21
Q

FDC is activated when

A

Beacon is turned on.

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22
Q

ED1 and ED2 are powered directly from:

A

Battery bus

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23
Q

When AC power is unavailable, limit ED1 and ED2 operation to

A

Five minutes

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24
Q

Data concentrator unit

A

Heart of the the engine indication crew alerting system (EICAS). Collects data from various aircraft systems, processes the information and relays it to the proper component or display.

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25
Q

Green indication on the EICAS.

A

Normal operations

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26
Q

Amber indication on the EICAS

A

Precautionary range

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27
Q

Red indication on the EICAS

A

Exceed the limits

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28
Q

Crew alerting system (CAS) does?

A

Provides visual and aural alerts when the DCU is alerted of a malfunction.

CAS prioritized messages by order of Occurence and order of importance.

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29
Q

Warning messages cannot be boxed?

A

True

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30
Q

Caution messages can be boxed?

A

True

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31
Q

Advisory messages can be boxed?

A

False

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32
Q

Status messages can be boxed?

A

True

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33
Q

The aircraft engine driven and APU generators are rated at?

A

40KVA

34
Q

The main aircraft generators supply power to how many AC buses?

A

4

35
Q

Power for 28V. DC is supplied by:

A

Transformer Rectifier Units

36
Q

The APU battery is

A

24volts at 43 ampere hours

37
Q

The main battery is:

A

24 volts 17 ampere hours

38
Q

How many Transformer Rectifier units supply power to DC buses

A

4

39
Q

Cranking power for starting the APU is provided.

A

APU BATTERY

40
Q

Cranking power for starting the APU is provided by?

A

APU battery

41
Q

The ADG supplies power to?

A

3B hydraulic pump, ESS AC Bus, slats/flaps and pitch trim.

42
Q

The main and APU batteries are kept in a charged condition by battery chargers powered by?

A

AC BUS No.1 an AC Service bus

43
Q

The External AC power receptacle is located?

A

Forward right side of the airplane

44
Q

Electrical systems warning and caution messages are normally displayed on?

A

EICAS primary page

45
Q

Electrical systems status and advisory messages are normally displayed on?

A

EICAS Status page

46
Q

The Intergrated drive generator (IDG) provides a means of converting

A

Variable engine speed to constant generator speed 12,000 rpm

47
Q

He IDGs May be disconnected from the gearbox by?

A

Disconnect switches located in the cockpit.

48
Q

Once the Intergrated drive generators are disconnected, they can only be reconnected????

A

On the ground with engine shutdown by maintenance

49
Q

Fault protection for each generator is incorporated in each?

A

Generator control unit (GCU).

50
Q

The priority for allowing power to AC Bus 1 would be.

A

Gen1
APU
Gen2
External power source (GPU).

51
Q

IDG 2 normally powers?

A

AC BUS 2, and service bus

52
Q

The ADG can only supply power to?

A

3B hydraulic pump, AC essential, ADG Bus, EICAS, slats, flaps, and pitch trim.

53
Q

115V AC is supplied to TRUs for DC static conversion, and each TRU is rated at?

A

120amps

54
Q

In flight the ADG auto deploy monitors the three main AC generators and the main AC buses for?

A

Complete AC failure

55
Q

An amber IDG fault light/caution light indicates?

A

Low IDG oil pressure and/or high IDG oil temperature.

56
Q

An AUTO XFER fail light (Amber) on the electrical panel indicates?

A

Generator over current or a bus fault

57
Q

An AC ESS XFER light (white) on the electrical indicates?

A

AC essential bus is not being powered by AC Bus 1.

58
Q

What are the generators rated at?

A

40 kVA up to FL410

59
Q

Generator control units?

A

Controls and monitors the generators provides voltage regulation and protection for each generator.

60
Q

ACPC (AC power center)

A

Distributes all power to AC Buses during normal operations.

61
Q

FADEC stands for?

A

Full authority digital electronic control system

62
Q

FADEC controls the operation and performance of the engine through three subsystems?

A

Fuel control, compressor airflow management and engine starting/ignition control.

63
Q

The FADEC has it’s own source of electrical power. When N2 rpm is >50%?

A

A designated accessory gearbox mounted FADEC alternator supplies power to both FADEC channels.

64
Q

When the aircraft’s N2 is below 50% what powers the FADEC system?

A

The aircraft’s electrical power.

65
Q

Bleed air is extracted from the engine compressors to provide; wing anti icing, engine cowl anti ice, air conditioning, and crossbreed engine starts. What stage is the air derived from

A

6th and 10th stage of the engine compressor.

66
Q

Continuous ignition is selected by pressing the CONT switch light on the Start/ignition panel. Both ignition A and B are energized. Continuous ignition must be used when?

A

Takeoffs and landing on contaminated runways
Flight through moderate or heavy intensity rain
Flight through moderate or heavy intensity turbulence
Flight in the vicinity of thunderstorms.

67
Q

What two type of electrical sources does the CRJ use for power?

A

115 volt AC AND 28 Volt DC.

68
Q

AC power Center (ACPC) does what?

A

Distributes power to all AC buses during normal operations.

69
Q

Generator control units (GCU) does what?

A

Controls and monitors the generators and provides voltage protection and regulation for each generator.

70
Q

AC Power sources: primary secondary and emergency?

A

Primary: 2 engine driven Intergrated Drive Generators ( IDG)
40 KVA, 115V, 400 HZ

Secondary: APU Generator
40 KVA, 115v, 400HZ
max altitude FL410, max altitude for start up: FL370, max altitude for bleed air: FL250

Emergency: Air Driven Generator ( ADG )
15 KVA, 115v, 400 HZ

71
Q

Intergrated drive generators (IDG) purpose?

A

To take N2 variable speed and to convert it to constant 12,000 rpm generator speed.

72
Q

Disconnecting IDGs:

Fault light indicates?

A

IDG’s can be disconnected both manually and automatic. Once disconnected the generator will remain lost for the remainder of the flight.

Fault light indicates the generator is running at a high oil temperature or low oil pressure

73
Q

The AC buses are?

A

Bus 1
Bus 2
ESS Bus ( essential bus)
Serv bus (service bus)

74
Q

Single generator operation

A

Any one of the three generators can handle the entire load of the AC system.

75
Q

2 batteries both DC power sources. What are these batteries and the associated function?

A

APU Battery 43 amp hour 24 volt DC.

Main Battery 17 amp hour 24 volt DC.

76
Q

The main battery charger is charged from.

A

AC Bus 1

77
Q

The APU Battery maintains charge from the?

A

AC Service Bus.

78
Q

The electrical direct current (DC) system has how many buses?

A

9 DC Buses:

Bus 1 
Bus 2
Serv bus
ESS bus
Util bus
Batt bus 
APU Direct bus
Batt direct bus
Emergency Bus
79
Q

How many TRU’S and what is there purpose?

A

4 TRU’S located in the nose compartment
Convert 115 volt AC to 28 volt DC
All 4 rated at 120 amps.

80
Q

How many DC tie contactors

A 
Main tie
Cross tie
ESS tie
DC ESS TRU transfer contractor
Service bus contactor
81
Q

AC EXTERNAL POWER

The available switch light for the AC external power is on when what is indicated?

A

Correct voltage, frequency and phase.

82
Q

What are detection loops?

A

Each engine is protected by dual fire/overheat detection loops. The loops are connected to the FIDEEX unit. The loops are constructed of an outer metal sheathing and two internal wires that are separated by an insulating material (thermistor). One of the wires carries electrical current, the other is grounded to the outer sheathing at the control unit. The resistance of the thermistor decreases with an increase in temperature.

83
Q

Fierce detection control unit (FIDEEX)

A

The FIDEEX unit is used to monitor the electrical resistance of the loops. When both loops experience the same decrease in resistance in a preset time, the unit sends a FIRE/OVHT signal to the EICAS. The FIDEEX unit is capable of discriminating between a real fire and a false fire. Each individual control circuit and its related sensing loop is monitored so that in the event of a malfunction of one loop, the second loop maintains the capability of detecting a fire.

Aircraft Systems (7 decks)

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