1900 Tech Exam

Question 1

Maximum ITT for takeoff is

Answer 1

800 degrees for 5 minutes.

Question 2

Minimum battery voltage for an external power start is

Answer 2

20 VDC.

Question 3

In cruise flight at 3200 ft/lbs and 1550 RPM a propeller lever cable break will result in

Answer 3

the propeller governing at 1700 RPM.

Question 4

During an engine start if no ITT is observed

Answer 4

a clearing start is required.

Question 5

With respect to certification, the maximum landing weight may be limited by

Answer 5

brake energy.

Question 6

Moving the pressurization switch to the dump position does what?

Answer 6

It energizes the dump solenoid and de-energizes the ram air vent lock, to allow vacuum air to open the valve.

Question 7

Engine anti ice is required

Answer 7

before entering visible moisture with an OAT of 10 degrees Celsius or less.

Question 8

Asymmetric flap protection is provided by

Answer 8

a switch between adjacent flap segments.

Question 9

Maximum pressure differential is

Answer 9

5.0 to 5.2 psi.

Question 10

The landing gear safety switch

Answer 10

interrupts power to the landing gear motor on the ground.

Question 11

The vacuum/pneumatic system is driven by

Answer 11

P3 air from the compressor regulated to 18 psi.

Question 12

When the engine auto ignition is armed the

Answer 12

igniters operate when torque falls below 750 ft/lbs.

Question 13

After starting the engine, the condition lever should be moved to high,

Answer 13

after the engine has stabilized and N1 is 65%.

Question 14

With the gen ties switch in NORM,

Answer 14

both ties close when the line contactor closes.

Question 15

The ram vent air is

Answer 15

available only when the dump solenoid is engaged.

Question 16

The minimum N1 allowed for putting a generator online is

Answer 16

72%.

Question 17

Annunciators associated with a loss of power to the left generator bus are,

Answer 17

L DC GEN, L GEN TIE OPEN and

R ENVIRO FAIL.

Question 18

Va is

Answer 18

178 knots.

Question 19

The primary governor’s operating range is

Answer 19

1200-1700 RPM.

Question 20

The stand by boost pump is energized

Answer 20

when the IGNITION AND ENGINE START switches are in the ON position and/or fuel is being transferred.

Question 21

If the engine driven high pressure fuel pump fails

Answer 21

the engine will fail.

Question 22

The fuel topping governor

Answer 22

utilizes inputs from fly weights and pneumatic bellows to meter fuel.

Question 23

With an oil pressure indication of less than 90 psi

Answer 23

a maximum torques of 2000 ft/lbs must be observed.

Question 24

ITT limits for engine start are

Answer 24

not more than 870-1000 degrees for more than 5 seconds.

Question 25

Failure of the stand by pump results in

Answer 25

a loss of fuel transfer capability.

Question 26

26) The R ENVIR FAIL annunciator illuminated means

Answer 26

the pre cooler and shut off valve regulator valves are closed and the switch is OPEN.

Question 27

27) Vacuum for the wing de ice system is provided by

Answer 27

a bleed air ejector.

Question 28

28) Maximum N1 for the PT6-67D is

Answer 28

104%.

Question 29

29) The engine intake lip is heated

Answer 29

continuously by exhaust air.

Question 30

With 17,000 set on the aircraft scale of the pressure controller, you begin a descent to 15,000 feet.

Answer 30

The cabin differential will decrease.

Question 31

Fault protection for the triple fed bus is provided by

Answer 31

three 60 amp current limiters.

Question 32

Min Flow is

Answer 32

50% N1.

Question 33

The fuel control units receive inputs from

Answer 33

a pneumatic bellows, N1 governor, the power lever and the condition lever.

Question 34

A completely blank or black EFIS tube is most likely

Answer 34

a failure of the tube.

Question 35

When the IGNITION AND ENGINE START switches are in the full ON position

Answer 35

the starter turns the engine, the ignitors are on and the stand by pump is on.

Question 36

The starter limits are

Answer 36

20 seconds on, 30 seconds off, 20 seconds on, 60 seconds off, 20 seconds on, 5 minutes off.

Question 37

After a failure of the triple fed bus

Answer 37

the pilot will notice that COM 1 and the engine instruments will lose power

Question 38

) A vacuum source failure will be indicated by

Answer 38

zero or very low suction, and a pressurization loss/cabin descent.

Question 39

The 0 flap Vref at 14,000 lbs is

Answer 39

124 knots

Question 40

The HED’s protect their respective buses by

Answer 40

opening its associated bus tie if excessive current is sensed.

Question 41

The L DC GEN annunciator will illuminate when

Answer 41

the line contactor is open and the starter switch is in the STARTER ONLY position.

Question 42

The balked landing climb gradient is

Answer 42

3.3%

Question 43

A compressor bleed valve that is stuck open will result in

Answer 43

high ITT and low torque.

Question 44

A wet runway

Answer 44

has no effect on V1 for the Beech 1900

Question 45

The hydraulic power pack shuts off

Answer 45

during gear extension when the 3 actuator down lock pins are engaged or the 16 second switch is energized.

Question 46

With the landing gear up

Answer 46

the hydraulic power pack comes on at 2320 psi and cuts out when the pressure switch detects 2775 psi or the timer switch hits 16 seconds.

Question 47

For the MAN COOL mode to function,

Answer 47

the ACM bypass valve must be closed and the OAT must be 45 degrees Fahrenheit or greater

Question 48

A XDTA annunciator on the first officer’s side means

Answer 48

the f/o can not receive data from the captains side.

Question 49

Placing bleed air switches in the ENVIR OFF position

Answer 49

de-energizes the enviro valves closed but the pneumatic valve stays open.

Question 50

A squat switch

Answer 50

energizes the dump solenoid open and prevents aircraft pressurization on the ground.

Question 51

While taxiing, the firewall fuel valve light comes on

Answer 51

The pilots should visually confirm the fire, and then blow the extinguisher bottle.

Question 52

The hydraulic accumulator

Answer 52

assists in maintaining system pressure to hold the landing gear up

Question 53

A squat switch

Answer 53

energizes the dump solenoid open and prevents aircraft pressurization on the ground.

Question 54

While taxiing, the firewall fuel valve light comes on

Answer 54

The pilots should visually confirm the fire, and then blow the extinguisher bottle.

Question 55

The hydraulic accumulator

Answer 55

assists in maintaining system pressure to hold the landing gear up