Pinnacle Systems Written Practice Test

Front 1

T/F
The APU bleed air directly feeds the right side of the 10th stage manifold to feed the right pack.

Back 1

FALSE, it supplies the Left pack

Front 2

In case of failure of both packs, _ _ can be used as the sole source of ventilation.

Back 2

Ram Air

Front 3

The Left pack primarily supplies the flight compartment _% and supplements the flow to the passenger cabin _%.

Back 3

70/30

Front 4

T/F
In the Air Conditioning system the dual bypass valves modulate as necessary to blend bypassed hot air with cooled air cycle machine air to achieve the selected temperature.

Back 4

TRUE

Front 5

Pack Fault Light indicates a(n) _ or _ condition has been detected.

Back 5

Overpressure/Over Temperature

Front 6

If live cargo is being transported at high ambient temperatures, the cargo switch should be only be set to _ _ after takeoff.

Back 6

COND AIR

Front 7

T/F
The CPKT and CABIN temp control knobs adjust the temp setting for the related compartment.

Back 7

TRUE

Front 8

Rotation of the V/S pitch wheel changes the pitch reference value by _ degrees per click.

Back 8

1/2

Front 9

The vertical takeoff mode generates a _ degree pitch up flight director command. Loss of an engine limits the pitch up command to _ degrees.

Back 9

15, 10

Front 10

Go-Around mode generates a _ degree pitch up command.

Back 10

10

Front 11

Automatic switchover from IAS to Mach occurs when climbing through _ feet.

Back 11

31,600 (AFM)

Front 12

T/F
The square HDG push button on the FCP selects or deselects the heading mode.

Back 12

TRUE

Front 13

When a pilot selects a HDG change > _ degrees, the aircraft will initiate a roll in the direction of the selected heading change.

Back 13

180

Front 14

Aircraft limitations prohibit the use of ___ submode during approach (either FD or autopilot coupled).

Back 14

DES

Front 15

Automatic transition to half-bank mode occurs when climbing above _ feet (PA) or if the airplane is above half-bank transition altitude when the flight director is engaged.

Back 15

31,600

Front 16

Half bank mode reduces the maximum command bank angle to _ degrees.

Back 16

15

Front 17

The yellow ROLL comparator flag is displayed when a difference of _ degrees (in level flight) or 3 degrees (during approach) is detected between AHRS roll data.

Back 17

?

Front 18

Traffic advisories (TA) indicate the relative positions of intruding airplanes that are about _ seconds from the closest point of approach (CPA) and may require a later resolution advisory.

Back 18

40

Front 19

The TCAS resolution advisory programs are based on the pilot initiating the RA maneuver within approx _ seconds.

Back 19

5

Front 20

Pitch-Limit Indicator (PLI) (yellow)-displayed during windshear warning or alert for a minimum of _ seconds- it displays the maximum pitch attitude that can be made before encountering the stall angle-of-attack.

Back 20

60

Front 21

For aircraft equipped with Mach transducers, each Mach transducer supplies primary Mach compensation data to the _ _ computer.

Back 21

Stall Protection

Front 22

The radio altimeter provides absolute altitude in a range of 0 to _ feet.

Back 22

2500

Front 23

The AUTO X FLOW INHIB- EICAS message will remain if the fueler leaves the power switch on the Refuel/Defuel control panel selected ON.

Back 23

TRUE, will be manual & not able to do automatically

Front 24

The green low speed awareness indicator bar indicates _ times the computed stall speed.

Back 24

1.27

Front 25

An _ knot range on the airspeed scale is always in view.

Back 25

80

Front 26

_ 100 amp, Transformer Rectifier Units convert the AC supply to 28volts DC, and power the airplane's buses.

Back 26

5

Front 27

The ADG (Air Driven Generator) is automatically deployed if there is a complete _ _ failure.

Back 27

AC Power

Front 28

The ADG is pushed into the airstream, where _ _ turns the turbine.

Back 28

Ram Air

Front 29

The main generators are _, 115 VAC, three phase, 400Hz, integrated drive generators.

Back 29

30KVa

Front 30

Power to the AC service bus is supplied directly from the _ _ _ or the _ _.

Back 30

External Power Receptacle / APU Generator.

Front 31

The AC service bus is supplies power to those circuits necessary for _ _ _, without having to energize the remainder of the electrical system.

Back 31

Ground Servicing Operations

Front 32

Bus priority for AC bus #2 is:

Back 32

IDG2 - APU - IDG1 - External Ground Power

Front 33

The EXT AC PUSH green AVIAL light in the external service panel illuminates when the connected AC power _ voltage and frequency are correct.

Back 33

Phase

Front 34

During AFCE operation, trim rate is determined by _ movement.

Back 34

Flap

Front 35

During an aileron mistrim condition, and with the autopilot engaged, the yellow aileron mistrim indicator appears on the _.

Back 35

PFD

Front 36

Some CRJ 200's have _ flap detent positions, while some CRJ 200's have _.

Back 36

5/4

Front 37

There are _ spoiler panels on each wing.

Back 37

4

Front 38

Ground flight spoilers are retracted in flight, or deploy to _ degrees after landing.

Back 38

45

Front 39

Flight spoilers can be extended from 0 to _ degrees.

Back 39

50

Front 40

T/F
Operation of the flap system is controlled by HYD system #3.

Back 40

False

Front 41

T/F
The ground lift dump system is fully automated?

Back 41

True

Front 42

T/F
Operations of mobile transceivers in close proximity to the smoke detectors may cause a false alarm.

Back 42

True

Front 43

Slow metering of the cargo fire ext. system last approx 30 min, but will give protection for _ minutes.

Back 43

45

Front 44

The CARGO BTL LO caution message may take up to _ minutes before it extinguishes, as the cargo FIREX bottle gradually discharges.

Back 44

20

Front 45

The airplane has _ portable fire extinguishers.

Back 45

3

Front 46

T/F
The main landing gear overheat detection consists of a dual loop overheat detection?

Back 46

False

Front 47

The Cargo compartment extinguisher system uses _ firex bottles.

Back 47

2

Front 48

_ smoke detector(s) monitor the cargo compartment.

Back 48

2

Front 49

_ heat sensitive fusible plugs are in each wheel.

Back 49

4

Front 50

The APU receives fuel directly from the _ tanks by the crossover/APU pump.

Back 50

Main

Front 51

The fuel temperature is continuously monitored by a fuel temp sensor in the _ wing.

Back 51

Left

Front 52

If one wing fuel quantity is less than _ pounds, that wing's quantity readout turns amber.

Back 52

450

Front 53

When left or right wing tank drops below _% full, the fuel system computer activates fuel transfer until the respective tank fuel level is 97/100% of it's capacity.

Back 53

94

Front 54

Automatic fuel crossflow is maintained until a fuel imbalance of _ pounds is reached in each tank selected for crossflow ( "low wing" )

Back 54

+50

Front 55

The fuel tanks are vented and slightly pressurized by a _ scoop.

Back 55

NACA

Front 56

T/F
Fuel boost pumps, when armed, serve as a backup to the main ejectors.

Back 56

True

Front 57

Maximum zero fuel weight is _ pounds.

Back 57

44,000

Front 58

Each hydraulic system operates at _ PSI.

Back 58

3,000

Front 59

Overall length of the CRJ is _'_".

Back 59

87/10

Front 60

T/F
There is no EICAS caution or warning for the crew escape hatch.

Back 60

True

Front 61

Maximum landing weight is _ pounds.

Back 61

47,000

Front 62

If IDG2 is disconnected, hydraulic pump _ is shed.

Back 62

1B

Front 63

The heat exchanger cools hydraulic fluid in the _ and _ hydraulic systems through ram air flow.

Back 63

#1/#2

Front 64

ACMP 2B provides backup to the right engine driven fuel pump and is supplied power from _ _ _.

Back 64

AC Bus #1

Front 65

A(n) _ _ augments air flow through the heat exchanger for hydraulics on the ground.

Back 65

Electric fan

Front 66

AC motor pumps _ and _ do not automatically start during or after and engine failure.

Back 66

1B/2B

Front 67

The respective AC hydraulic pump operates in AUTO when _ and associated generator is online.

Back 67

Flaps are out of the 0 degree position

Front 68

The windshield wiper switch on the pilot and co-pilot side simultaneously controls _ wiper(s).

Back 68

Both

Front 69

T/F
The CRJ has three independent ice detection systems.

Back 69

False

Front 70

If bleed air is not supplied from one engine, the opposite engine can supply bleed air to both wings by the _ _.

Back 70

ISOL Valve

Front 71

With the landing gear not in the down and locked position, the warning horn cannot be muted if flaps are selected to _ degrees or more.

Back 71

30

Front 72

There are _ brake wear pins on each brake assembly.

Back 72

2

Front 73

In the event of a failure of _ or _ hyd systems, accumulators in both hyd systems provide reserve pressure for six brake applications with the anit-skid off.

Back 73

#2/#3

Front 74

Loss of _ or _ hydraulic systems leaves the aircraft with 50% symmetric braking capability with full anti-skid control to the working brakes.

Back 74

#2/#3

Front 75

During initial, final takeoff, and landing phases, the _(s) process inhibit logic to minimize distracting warning or caution messages.

Back 75

DCU (Data Concentrator Unit)

Front 76

Inboard and outboard brake pressure caution message display if the system is less than _ PSI.

Back 76

1030

Front 77

There should be a _ minute delay between cranking attempts to allow for cooling of the APU starter and drainage.

Back 77

2

Front 78

The recognition/taxi lights illuminate automatically when the associated _ _ is selected on.

Back 78

Landing Lights

Front 79

If a fire extinguisher is discharged in the _ compartment, all flight crew must wear oxygen masks with the EMER selected to 100%.

Back 79

Flight

Front 80

The chemical oxygen generator supplies approx _ minutes to each mask.

Back 80

13

Front 81

T/F
The N2 rotor is a 16 stage axial flow compressor.

Back 81

False

Front 82

_ _ switches on the thrust reverser panel drive the TR equipment to the stow position, should the automatic system fail.

Back 82

EMER STOW

Front 83

_ _ gauges replace the oil pressure gauges when oil level is normal.

Back 83

Fan Vib

Front 84

T/F
18 dual orifice fuel injectors are on each engine.

Back 84

True

Front 85

IGN-B, on both engines, is powered from a static inverter on the _ _ bus.

Back 85

DC Battery

Front 86

With the APU armed and engines operating in N1 mode, a drop to _% N1 on either engine causes the APR system to command N1 speed increase on both engines.

Back 86

67.6

Front 87

A minimum of _ PSI and 24V DC are required for engine starts.

Back 87

40

Front 88

The CPAM automatically deploys the passenger cabin oxygen masks when cabin altitude reaches _ feet, and illumination of the seat belt/no smoking sign when cabin altitude reaches _ feet.

Back 88

14,000/10,000

Front 89

If the airplane maintains an altitude of _ feet or less above takeoff airport elevation, and then begins a descent at 1,000FPM or more, the system assumes the landing elevation is the departure airport.

Back 89

6,000

Front 90

T/F
The pressurization system includes two outflow valves.

Back 90

True

Front 91

The pressurization system has _ identical and redundant cabin pressure controllers when operating in automatic mode.

Back 91

2

Front 92

Cabin altitude rate of change is limited to _ FPM climbing and _ FPM on descent.

Back 92

500/300

Front 93

Advisory messages are set in _ at the top of the stack of messages on ED2.

Back 93

Green

Front 94

T/F
Advisory messages can not be removed from view, unless the applicable system or switch has been deselected or deactivated.

Back 94

True

Front 95

T/F
Warning messages can not be removed from view, unless the applicable failure is rectified.

Back 95

True

Front 96

Caution messages appear in _.

Back 96

Amber

Front 97

The lavatory wash water system uses a _ gallon water tank.

Back 97

5

Front 98

The galley potable water system contains a _ gallon water tank.

Back 98

8