737-200 Home Study Test Bank

Front 1

The Emergency Exit Lights NOT ARMED indicator light will be illuminated

Back 1

anytime the emergency light switch is not in the ARMED position

Front 2

To combat an electrical fire inside the aircraft, use a ___ fire extinguisher

Back 2

Halon

Front 3

What is the most effective type of fire extinguisher to use on fabric, wood or paper fire?

Back 3

Water

Front 4

The power source for Engine Start Ignition is the ___ bus.

Back 4

Battery

Front 5

How many ADF receivers are installed in the 737-200?

Back 5

2

Front 6

The Radio Altimeter (RA) measures absolute aircraft height above the ground up to

Back 6

2500 feet

Front 7

Which GPWS modes are inoperative when the Radio Altimeter is inoperative?

Back 7

All modes

Front 8

How many Radio Altimeter (RA) indicators are installed in the 737-200?

Back 8

2

Front 9

Both aircraft compass systems operate during standby power operations. (T/F)

Back 9

FALSE

Front 10

The maximum pressure altitude limit for takeoff and landing is ___ feet

Back 10

8300

Front 11

The call system uses lights and aural signals to

Back 11

gain attention of crew members

Front 12

there are ___ Audio Select Panels (ASP) in the cockpit

Back 12

3

Front 13

which types of crew/cabin/ground communications systems are installed on the 737-200?

Back 13

flight interphone, service interphone, passenger address (All of the above)

Front 14

Positioning the thrust reverser override switch to OVERRIDE bypasses the

Back 14

oil pressure switch and the air/ground sensor

Front 15

The yaw dampener may be used with or without the autopilot. (T/F)

Back 15

TRUE

Front 16

The limit for glideslope (GS) capture is ___ dot(s)

Back 16

2

Front 17

The autopilot will only track navigation signals from the number

Back 17

1 VHF NAV radio

Front 18

Which engine indications justify aborting an engine start

Back 18

(1) Fuel flow indication greater than 1100
(2) no oil pressure increases in 30 seconds
(3) no N1 RPM indication by 20% N2 RPM
(4) All of the above

Front 19

The thrust reverser(s) may be activated when the Fire switch is down and

Back 19

(a) engine oil pressure is more than 35 psi
(c) hydraulic pressure is available and Air/Ground safety sensor is in the ground mode
(answers a and c are correct)

Front 20

Selecting the Engine Start switch to GND

Back 20

opens the starter valve and provides ignition to two igniters

Front 21

What does the APU GEN OFF BUS light indicate when illuminated?

Back 21

APU speed is 95% or better and not supplying power to bus

Front 22

Which APU system indicator does NOT result in an automatic APU shutdown?

Back 22

High EGT indication

Front 23

what is the maximum altitude the APU may be operated?

Back 23

35,000 feet

Front 24

What is the maximum altitude the APU may be operated to supply bleed air?

Back 24

17,000 feet

Front 25

What APU action will occur if the Battery Switch is turned OFF during ground operations?

Back 25

The APU will automatically shut down

Front 26

Which of the following actions will not activate the passenger oxygen system?

Back 26

Emergency light switch is selected ON

Front 27

The altitude warning horn will sound when the cabin altitude reaches ___ feet

Back 27

10,000

Front 28

The crew and passenger oxygen systems are connected to the green thermal blowout disc. (T/F)

Back 28

TRUE

Front 29

The passenger oxygen system is composed of chemical oxygen generators and drop-down masks. (T/F)

Back 29

FALSE

Front 30

If the crew oxygen system shutoff valve is closed, oxygen to the crew station

Back 30

is not available

Front 31

During landing or rejected takeoff with the Autobrakes armed, what occurs when the thrust reversers are activated?

Back 31

Brake pressure is reduced to maintain the selected deceleration rate

Front 32

Both 'A' and 'B' hydraulic system pressures indicate normal (green band). The Hydraulic Brake Pressure gage indicates '0' psi. Will the aircraft brakes be available on landing?

Back 32

Yes

Front 33

The minimum pressure (accumulator) of the brake systems during preflight is ___ psi.

Back 33

1000

Front 34

When the landing gear indicator lights are illuminated red it indicates that the

Back 34

(1) gear position is in DISAGREEMENT with the handle position
(2) gear is NOT DOWN and either thrust lever is retarded to (@) IDLE
(3) gear is UNLOCKED
(4) Any of the above

Front 35

Are the inboard leading edge flaps heated?

Back 35

No

Front 36

If a probe heat light is illuminated when the power switch is on it indicates

Back 36

that the affected probe is not heated

Front 37

If an engine Left or Right valve does not open, will the inlet guide vanes receive adequate anti-ice protection?

Back 37

Yes, either valve provides adequate protection

Front 38

How are the TAT probes heated?

Back 38

Electrically, when the power is selected ON

Front 39

When performing a wing anti-ice ground test, the anti-ice valves will close automatically if the duct temperature exceeds a preset limit.

Back 39

TRUE

Front 40

What is the source of electrical power for the engine Overheat and Fire Detection system?

Back 40

Battery Bus

Front 41

How many engine fire bottles are installed on the aircraft?

Back 41

2

Front 42

The engine or APU Fire Switch can be manually activated by simultaneously pressing a button (override) under the Fire Switch and pulling the switch. (T/F)

Back 42

TRUE

Front 43

The affected engine fire BOTTLE DISCHARGE light illuminates when the

Back 43

fire bottle has discharged

Front 44

Pulling the Engine Fire Warning Switch causes the following EXCEPT:

Back 44

B' hydraulic low pressure light is deactivated

Front 45

What is the trim authority for the stabilizer?

Back 45

Manual: 0-17 units
Electrical: 2.6-12.5 units
Autopilot: 2.3-13.0 units
(All of the above)

Front 46

The three ways to turn on the standby hydraulic pump are

Back 46

(AFS)Alternate Flap Switch - Arm
(AFCS) A Flight Control switch - Standby Rudder
(BFCS) B Flight Control switch - Standby Rudder

Front 47

The four actions that will cause the APU to shutdown automatically are

Back 47

APU fire
actual overspeed
high oil temperature
low oil pressure

Front 48

The oxygen masks will deploy when any of the following actions are accomplished, EXCEPT:

Back 48

Cabin rate of climb or descent exceeds 1800 ft/min

Front 49

(Normal operations) Which engine generator powers transformer-rectifier (TR) number 1?

Back 49

Gen #1

Front 50

If Transformer-Rectifier (TR) #3 fails during the flight the battery bus will receive power from

Back 50

the hot battery bus

Front 51

The battery bus is normally powered by TR#3. If TR#3 is not available, the battery bus will be powered by the alternate source - the hot battery bus. (T/F)

Back 51

TRUE

Front 52

(FWD F/A Panel) The Ground Service switch when selected to ON connects external power to the

Back 52

ground service bus

Front 53

The normal and alternate power sources to the hot battery bus are

Back 53

Battery Charger, Battery

Front 54

Where does Transfer Bus 2 receive power from if Generator Bus 2 is inoperative?

Back 54

Gen Bus 1

Front 55

When the STANDBY POWER switch is placed to the BAT position, the following actions occur EXCEPT:

Back 55

All systems are powered for 60 minutes

Front 56

When is a constant speed drive (CSD) disconnect required?

Back 56

Low oil pressure (LOW OIL PRESSURE light illuminated)
High Oil temperature (HIGH OIL TEMP light illuminated)
(Both A and B)

Front 57

Illumination of the GEN OFF BUS light occurs when the associated engine-driven generator is not powering the bus. (T/F)

Back 57

TRUE

Front 58

When a engine-driven generator fails or is disconnected, the following equipment is load shed

Back 58

GALLEY Power
the respective hydraulic system 'B' PUMP
(answers a and b are correct)

Front 59

With only one engine-driven generator operating inflight, can Generator Bus 1 and 2 be powered?

Back 59

NO

Front 60

Can APU electrical power be applied to Gen Bus 1 and Gen Bus 2 inflight?

Back 60

NO

Front 61

Which primary engine instruments are operational during standby power operations?

Back 61

N1
N2
EGT
(All of the above)

Front 62

The power source for the engine and APU fire detection system is the

Back 62

battery bus

Front 63

Where does the standby power system static inverter receive its power from?

Back 63

battery bus

Front 64

Which electrical busses are not powered if Generator #1 is inoperative?

Back 64

Gen bus 1
Main bus 1
(Both a and b)

Front 65

Normal system pressure for each hydraulic system is ___ psi

Back 65

3000

Front 66

When the 'B' hydraulic system LOW QUANTITY light is illuminated it indicates

Back 66

system fluid reservoir is low

Front 67

For cooling purposes, system 'B' fluid is routed through a heat exchanger in

Back 67

main fuel tank #2

Front 68

Pulling an engine Fire Switch closes the hydraulic shutoff valve and

Back 68

deactivates the HYD PRESS LOW light

Front 69

The hydraulic ground interconnect valve can be opened when the

Back 69

aircraft is on the ground and the parking brake is set

Front 70

when is the Standby hydraulic system LOW QUANTITY light armed?

Back 70

The light is armed at all times

Front 71

When is the Standby hydraulic system LOW PRESSURE light armed?

Back 71

When standby hydraulic pump operation is initiated

Front 72

With a loss of hydraulic system 'A' fluid, can the leading edge devices be extended

Back 72

YES

Front 73

if, due to a failure in hydraulic system 'A', the leading edge devices are extended using the Standby hydraulic system, can they be retracted?

Back 73

NO

Front 74

The minimum fuel quantity in main tank #2 for operation of the 'B' hydraulic pumps is

Back 74

1675 lbs

Front 75

Which flight control surface(s) DO NOT receive 'A' hydraulic pressure?

Back 75

(OFS) outboard flight spoilers

Front 76

Which system DOES NOT receive 'B' system hydraulic pressure?

Back 76

Nose wheel steering

Front 77

Which of he following systems does not use Standby hydraulic pressure?

Back 77

(TEF)Trailing edge flaps

Front 78

The minimum required duct pressure for engine start at sea level is ___ psig

Back 78

30

Front 79

The maximum duct pressure for engine start is

Back 79

48

Front 80

The bleed air sources for the aircraft pneumatic systems are the

Back 80

APU, engines and ground air cart

Front 81

An illuminated amber DUAL BLEED light indicates

Back 81

possible APU bleed back pressure

Front 82

The APU bleed air valve is connected to the bleed air duct on the ___ of the system.

Back 82

left side

Front 83

When in the AUTO position, what action will cause the ISOLATION valve to open?

Back 83

Any engine bleed air switch positioned to OFF

Front 84

How is the engine bleed air temperature maintained?

Back 84

A pre-cooler, or heat exchanger, precools the air

Front 85

What does illumination of the BLEED TRIP OFF light indicate?

Back 85

Excessive engine bleed air temperature, the engine bleed air valve has closed

Front 86

How do you reset the engine bleed air valve after a BLEED TRIP OFF light illuminates?

Back 86

Push the TRIP RESET switch

Front 87

The APU bleed valve may be opened prior to APU start by placing the bleed air switch to ON (T/F)

Back 87

FALSE

Front 88

The WING-BODY OVERHEAT detectors are located in the

Back 88

left wing leading edge, aft keel beam, right wing leading edge (all of the above)

Front 89

What does an illuminated WING-BODY OVERHEAT light indicate?

Back 89

Possible bleed air leak in the wing leading edges, Possible bleed air leak in the air conditioning bays, Possible bleed air leak in the APU air duct (all of the above)

Front 90

Which pneumatic valve(s) are AC powered?

Back 90

Engine bleed valves

Front 91

An illuminated BLEED TRIP OFF light indicates that the respective engine bleed valve is stuck open (T/F)

Back 91

FALSE

Front 92

If the FLT/GND switch is left in the GND position during takeoff and climb

Back 92

a bump in pressure pump may be felt on departure, the aircraft will pressurize normally

Front 93

The cabin altitude warning horn sounds when the cabin altitude reaches ___ feet

Back 93

10,000

Front 94

When a PACK TRIP OFF light illuminates the associated air mix valves

Back 94

drive to the full cold position

Front 95

Does the air conditioning pack valve close when the DUCT OVERHEAT light illuminates?

Back 95

NO

Front 96

When a PACK TRIP OFF light illuminates, what actions should be taken to reset the system?

Back 96

Let the pack COOL, select a WARMer temperature, press the trip RESET button (all of the above)

Front 97

When a PACK TRIP OFF light illuminates, does the isolation valve OPEN?

Back 97

NO

Front 98

The normal cabin operating differential pressure is ___ psi

Back 98

7.8

Front 99

The two pressure relief valves limit cabin differential pressure to a maximum of ___ psi

Back 99

8.65

Front 100

The maximum cabin pressure differential for takeoff/landing is ___ psi.

Back 100

0.125

Front 101

the amber AUTO FAIL light (Cabin Pressure Controller) will illuminate when

Back 101

cabin altitude is 13,875 or higher

Front 102

the FLT/GND switch on the Cabin Pressure Controller operates in ___ mode(s)

Back 102

AUTO and STANDBY

Front 103

If the fault has been corrected, the TRIP RESET switch will reset ___ conditions

Back 103

PACK TRIP, BLEED TRIP, DUCT OVERHEAT (All of the above)

Front 104

Which mode(s) of the aircraft pressurization system is AC powered?

Back 104

MANUAL AC, AUTO (both a and b)

Front 105

which of the switches on the pneumatic panel are controlled by DC power?

Back 105

PACK valve and APU

Front 106

The cockpit receives conditioned air from the

Back 106

left pack

Front 107

Which configuration will not cause the takeoff warning horn to sound?

Back 107

Parking brake set

Front 108

What happens if either FLIGHT CONTROL POWER SWITCH is positioned to STBY RUD?

Back 108

Standby hydraulic PUMP is activated
Standby hydraulic rudder actuator VALVE opens
Standby pump low pressure LIGHT is armed
(All of the above)

Front 109

Hydraulic pressure for the yaw dampener is provided by system

Back 109

B

Front 110

The FEEL DIFF PRESS light is disarmed when the

Back 110

flaps are down

Front 111

Illumination of the FEEL DIFF PRESS light indicates

Back 111

possible differential between system A and B hydraulic pressures
possible differential between elevator pitot system pressures
flaps are in UP position
(All of the above)

Front 112

Illumination of the STALL WARNING OFF light indicates

Back 112

Possible HEATER failure of the angle of attack airflow sensor, possible system SIGNAL failure, possible POWER failure (All of the above)

Front 113

the maximum flap extension altitude is ___ feet

Back 113

20,000

Front 114

The STABILIZER OUT OF TRIM light is functional when

Back 114

the autopilot is engaged

Front 115

The yaw dampener will disengage if the 'B' flight control switch is moved to STBY RUDDER. (T/F)

Back 115

TRUE

Front 116

The center tank LOW PRESSURE light is disarmed when the center tank pump switch is OFF. (T/F)

Back 116

TRUE

Front 117

The fuel temperature indicator receives information from the ___ tank.

Back 117

#1 main

Front 118

With a complete loss of electrical power, fuel from ___ is available by suction.

Back 118

#1 and #2 main tanks

Front 119

the purpose of the fuel CROSSFEED valve is to

Back 119

connect engine #1 and engine #2 fuel feed lines

Front 120

In normal flight configuration with fuel in all tanks and all fuel pumps on, where are the engines getting their fuel?

Back 120

Center tank

Front 121

Either illuminated FILTER ICING light indicates an iced or

Back 121

contaminated fuel filter

Front 122

what is the maximum percent RPM for N1 and N2 on the JT8D-17?

Back 122

N1: 102.4, N2: 100.0

Front 123

The 737-200 maximum takeoff gross weight is ___ pounds.

Back 123

117,000

Front 124

the maximum EGT for engine start is:

Back 124

Ground: 550 deg C, Flight 650 deg C

Front 125

What is the 737-200 maximum zero fuel weight?

Back 125

95,000 lbs

Front 126

what is the maximum EGT for the APU?

Back 126

760 deg C

Front 127

The maximum landing weight for the 737-200 aircraft is ___ pounds.

Back 127

105,000

Front 128

the normal engine start starter duty cycle is

Back 128

30 seconds on, 60 seconds off

Front 129

the inflight ignition duty cycle using LOW IGN is

Back 129

continuous -- no limit

Front 130

The engine oil pressure limit range is ___ psi minimum, ___ psi maximum.

Back 130

40, 55

Front 131

When flaps are deployed using alternate extension procedures, limit airspeed to ___ KIAS.

Back 131

210

Front 132

The yaw damper sends signals to the rudder power control unit to

Back 132

help prevent dutch roll

Front 133

A fully charged battery will provide power for a minimum of ___ minutes.

Back 133

30

Front 134

The 737-200 turbulence penetration airspeed is

Back 134

280 KIAS/.70m

Front 135

the OFF SCHED DESCENT light illuminates when the aircraft descends before reaching the planned cruise flight altitude set in the flight altitude indicator. (T/F)

Back 135

TRUE

Front 136

The engine-driven generator maximum amps load is

Back 136

111

Front 137

the 737-200 maximum fuel quantity in each main tank is ___, center tank ___.

Back 137

10,120, 16,351

Front 138

If the CSD has been disconnected inflight, it can be reconnected after the problem is corrected. (T/F)

Back 138

FALSE

Front 139

The maximum allowable CSD oil temperature is ___ deg C.

Back 139

157

Front 140

when the STANDBY PWR OFF light illuminates inflight it indicates

Back 140

the AC standby bus is not powered

Front 141

the maximum external air pressure acceptable from a ground power is ___ psig.

Back 141

60

Front 142

the inflight alternate flap duty cycle limitation is

Back 142

One cycle, 25 minutes off

Front 143

Illumination of the APU Fire Warning Switch causes automatic shutdown and

Back 143

unlocks the APU Fire Warning Switch

Front 144

If an engine Fire Warning Switch or OVERHEAT light remains illuminated after pulling the Fire Switch

Back 144

rotate Fire Switch to the left of right and hold for one second

Front 145

the first action upon discovery of visible fire, smoke or odor from electrical components is

Back 145

Oxygen masks and regulators (if required)… ON, 100%

Front 146

The first action taken in the event of a runaway stabilizer is

Back 146

Control Column … Hold Firmly

Front 147

the APU starter duty cycle is time limited to prevent possible cutout failure and

Back 147

excessive battery drain

Front 148

When checking battery condition, the normal range of battery voltage is ___ volts.

Back 148

22-30

Front 149

The maximum recommended wind for operation of the air stairs is ___ knots.

Back 149

40

Front 150

The emergency Exit Lights are powered by their own NICAD batteries that last approximately

Back 150

20 minutes

Front 151

the maximum takeoff and landing tailwind component is ___ knots.

Back 151

15

Front 152

The alternate flap system requires approximately ___ minutes to extend the flaps to 15 deg.

Back 152

2

Front 153

the engine accessories (oil pump, fuel pump, CSD, starter, etc) are driven by the

Back 153

N2 compressor

Front 154

If the MACH TRIM FAIL light illuminates, limit aircraft speed to ___ Mach

Back 154

0.74

Front 155

Can fuel be transferred between tanks in flight?

Back 155

NO

Front 156

If the LOW OIL QUANTITY light is illuminated during normal APU operation it indicates

Back 156

insufficient oil quantity for extended operation

Front 157

The APU bleed valve should be closed when

Back 157

ground air is connected and the isolation valve is open, engine #1 bleed valve is open, the Isolation valve and engine #2 bleed valve is open (All of the above)

Front 158

the maximum inflight weight (flaps up) of the 737-200 is

Back 158

116,500

Front 159

the maximum fuel temperature allowable is

Back 159

49 deg C

Front 160

the APU generator maximum load on the ground is ___ amps.

Back 160

125

Front 161

the Captain's first step on the Passenger Evacuation checklist is

Back 161

Parking brake … Set

Front 162

the First Officer's first step on the Passenger Evacuation checklist is

Back 162

Flap lever … 40

Front 163

The DUAL BLEED light will be illuminated during engine start using the APU. (T/F)

Back 163

TRUE

Front 164

The Standby Busses are powered when the Standby Power Switch is in the BAT position. (T/F)

Back 164

TRUE

Front 165

Engine ignition must be selected to ___ for takeoff and landing.

Back 165

LOW IGN

Front 166

If the APU DET INOP light illuminates during non-test conditions, it indicates the fire detection system

Back 166

is inoperative and the APU should not be run

Front 167

If the yaw damper is inoperative, the autopilot roll channel may only be used below ___ feet.

Back 167

30,000

Front 168

On taxi-out when fuel tank temperature is ___ deg C or below, position FUEL HEAT switches to ON.

Back 168

0

Front 169

the maximum continuous EGT for JT*D-17 engines is ___ deg C.

Back 169

610

Front 170

The APU LOW OIL PRESSURE light is illuminated during start until the

Back 170

APU oil pressure is normal

Front 171

How many oxygen sytems are installed on the aircraft?

Back 171

2

Front 172

Power for the engine and APU fire warning system comes from the

Back 172

Battery Bus

Front 173

during engine start using ground electrical power, placing the right engine generator on line powers Gen Bus 2, ground power will continue to power Gen Bus 1. (T/F)

Back 173

TRUE