Beechjet 400A Self Check

Front 1

A complete description of system operations is available in which aircraft manual

Back 1

Pilot's Operating Manual (POM)

Front 2

What manuals should be in the aircraft during flight?

Back 2

AFM, POM, OH

Front 3

Supplemental equipment operations can be found in?

Back 3

AFM (Supplements in back of AFM)

Front 4

Taxi Radius is?

Back 4

40 Feet

Front 5

Wing span dimensions are?

Back 5

43 Feet 6 Inches

Front 6

Height of tail?

Back 6

13 Feet 11 Inches

Front 7

Each generator is capable of producing how many amps?

Back 7

400 amps

Front 8

Generator power is distributed through?

Back 8

Two main buses

Front 9

The DC electrical power distribution system is divided into four subsystems:

Back 9

Power source distribution
Primary power distribution
Secondary power (load) distribution
Emergency power distribution

Front 10

If the EMER BUS FDR FAIL annunciator comes on, the emergency relay opens and the emergency bus receives power from the?

Back 10

LH load bus

Front 11

The nonessential buses are protected by?

Back 11

Toggle-switch type circuit breaker on main circuit breaker panel

Front 12

To disconnect the LH Main bus from the battery charge bus, pull the:

Back 12

LH BUS TIE RCCB

Front 13

Which position of the battery switch isolates the battery from the start bus?

Back 13

EMER or OFF

Front 14

During normal operation of the AC electrical system, the number 1 inverter powers:

Back 14

Primary 115 VAC & Primary 26 VAC buses
The 115 VAC shed bus
The 26 VAC shed bus

Front 15

If the number 1 inverter fails, the number 2 inverter:

Back 15

Transfers power to the primary buses leaving the secondary buses powerless

Front 16

Maximum generator load with BOTH Gens operating up to 41,000 feet?

Back 16

280 amps

Front 17

The No. 1 inverter is powered from the:

Back 17

LH Load bus

Front 18

Yellow arc of the ITT gauge indicates temperatures between:

Back 18

680 to 700 degrees C

Front 19

How many stages of compression does the low compressor section of the JT15D engine have?

Back 19

Two

Front 20

The high compressor section consists of:

Back 20

One single-stage centrifugal compressor

Front 21

Section controls mixing of fuel and air and contains igniters?

Back 21

Combustion section

Front 22

Description of the turbine section of the JT15D engine:

Back 22

A single-stage high-pressure turbine and a two-stage low-pressure turbine.

Front 23

The high-pressure turbine drives:

Back 23

The high-pressure compressor and the accessory section.

Front 24

Thrust from the engine is delivered by the exhaust section which:

Back 24

Combines bypass air with expanding gases of combustion to provide thrust.

Front 25

What is is driven by the accessory section?

Back 25

Starter-Generator
Oil Pump
N2 Tach
Fuel Pump
Fuel control unit (HMU)
Hydraulic pump

Front 26

Engine oil is cooled by means of:

Back 26

A fuel/oil heat exchanger.

Front 27

Fuel flow to the engine of the Beechjet is controlled by:

Back 27

An electronic control (EFC) working in conjunction with a hydromechanical unit (HMU).

Front 28

The ignition switches are:

Back 28

Three position ON-OFF-STBY switches.

Front 29

The engine thrust levers have four marked positions:

Back 29

OFF, IDLE, NORM T.O. and T. O.

Front 30

The Beechjet utilizes what make and model number engine

Back 30

Pratt & Whitney JT15D-5

Front 31

What are the maximum sea level static thrust and maximum continuous thrust ratings:

Back 31

2,965 LBS and 2,900 LBS

Front 32

Maximum permissible engine operating speeds are:

Back 32

104% N1
96 % N2

Front 33

The maximum permissible ITT during an engine start is:

Back 33

550 C to 600 C = 4 seconds
600 C to 700 C = 2 seconds

Front 34

What is the primary instrument for determining takeoff thrust settings?

Back 34

N1

Front 35

Maximum time for continuous reverse thrust above reverse idle is:

Back 35

30 seconds

Front 36

The maximum stow cycle time after actuation of the reverser lever is:

Back 36

5 seconds

Front 37

The emergency thrust reverser restow flight envelope is (altitude/airspeed):

Back 37

30 Feet or Below 135 KIAS or Below

Front 38

During a generator-assisted start (ground-start), ensure the operating engine is between:

Back 38

52 to 54 % N2

Front 39

A GPU start is recommended at ambient temperature below approximately:

Back 39

Minus 15 degrees C.

Front 40

The engine fire detection system operates based on:

Back 40

A closed loop, semiconductor coaxial cable around the engine

Front 41

The fire detect circuits are powered by their respective

Back 41

Load buses

Front 42

The engine fire bell is powered by the

Back 42

Emergency bus

Front 43

Pushing the LH ENG FIRE PUSH switch light:

Back 43

Closes the left engine fuel valve
Hydraulic shutoff valves
Trips the left generator field
Arms the fire extinguisher bottles

Front 44

Pushing the BOT 1 ARMED PUSH switch light:

Back 44

Discharges the # 1 bottle to the engine corresponding to the last ENGINE FIRE PUSH button pressed

Front 45

The location of engine fire bottles are as follows:

Back 45

Both bottles are located above the rear baggage compartment

Front 46

How many portable fire extinguishers are located on the aircraft?

Back 46

2

Front 47

The fire warning bell will silence after:

Back 47

When the silence button is depressed

Front 48

If the red discharge disk is missing during preflight, the following has occurred?

Back 48

Overheating of the extinguisher bottles causing the bottle fuse to rupture

Front 49

The fuel storage system consists of two independent wing tanks:

Back 49

two forward fuselage tanks, two mid fuselage tanks, and aft fuselage tank and a fuselage fill tank

Front 50

Which tank feeds the left engine during normal operation?

Back 50

The left wing collector tank

Front 51

Refueling of the Beechjet 400A is accomplished through:

Back 51

Three filler ports, one on each wing and one on aft right fuselage.

Front 52

Usable fuel capacity of the Beechjet 400A is:

Back 52

733 gallons

Front 53

During cruise flight, electrical boost pump switches should be selected:

Back 53

AUTO

Front 54

With the electric boost pumps in AUTO, the crew can expect the respective pump to operate:

Back 54

If fuel feed line pressure drops - 5psi
engine start
when collector tank level drops - 11.5 g

Front 55

When an electric boost pump is operating, the crew is informed by means of:

Back 55

A white light above the boost pump switch

Front 56

The jet pump switches are:

Back 56

Two-position switches, labeled NORM and OFF

Front 57

The fuel transfer switches are three position switches labeled:

Back 57

ON, AUTO and RESET

Front 58

The ON position of the fuel transfer pump switch is used:

Back 58

On the ground or as a back up if the automatic system fails.

Front 59

Selecting the FUEL XFEED switch to the L TANK position allows fuel from the left tank to supply:

Back 59

Both engines

Front 60

The fuselage fuel in the Diamond 1/1A should be transferred:

Back 60

in level cruising flight

Front 61

Motive flow for the primary jet pump is supplied by the

Back 61

Engine driven fuel pump

Front 62

Which tanks are foam filled

Back 62

Aft fuselage tank and Aft fuselage fill tank

Front 63

Fuel from the aft filler and aft fuselage tank flows to the mid fuselage tanks by

Back 63

Gravity

Front 64

The purpose of sniffle valves located in the outbaord and middle wing bays and at the gravity refueling port is

Back 64

To provide pressure and vacuum relief

Front 65

How is fuel transferred from the fuselage tanks to the wing tanks

Back 65

Electric fuel transfer pumps located in the mid fuselage tanks

Front 66

How can the fuel shutoff valves be closed

Back 66

Pressing the LH or RH ENG FIRE PUSH switchlight or the R HYD/FUEL VALVE switchlight

Front 67

Illumination okf the L or R WG TK OV PRESS annunciator indicates pressure in the wing tank in excess of 3.5 psid and also causes

Back 67

Respective transfer pump to shut down if selected to ON or AUTO

Front 68

When the trim interrupt switch is engaged

Back 68

The autopilot and yaw damper are disengaged and all trim systems except the emergency pitch trim system are interrupted

Front 69

Control column shaking and angle of attack display on the cockpit indicators warn of

Back 69

Impending stalls

Front 70

As the spoilers on one wing extend, the spoilers on the other wing

Back 70

Move below the upper surface of that wing

Front 71

What are the seletable flap positions

Back 71

Zero, 10, 20, 30

Front 72

Rudder boost must be operable and

Back 72

armed for all operations

Front 73

The hydraulically actuated flight controls consist of

Back 73

Speed brakes, flaps

Front 74

Flap asymmetry protection

Back 74

Stops flap movement if an asymmetric condition of the main flaps is detected

Front 75

The speed brakes will automatically retract when

Back 75

The throttles are advanced approaching takeoff power and the flaps are exteded beyond 10 degrees

Front 76

The auto pilot controls pitch via the

Back 76

Emergency pitch trim motor

Front 77

On takeoff, the pitch trim warning horn sounds. This means

Back 77

The pitch trim is not in the T.O. green band

Front 78

The rudder boost system activates the rudder servo to deflectthe rudder and counteract yaw from asymmetric engine thrust by

Back 78

Comparing engine bleed air pressure

Front 79

Which are considered the primary flight controls

Back 79

Elevators, rudder spoilers

Front 80

Which flight controls are operated via cables

Back 80

Rudder and spolier

Front 81

A hydraulic pressure reading of 1850 PSI would be indicated on the hydraulic pressure gauge at the

Back 81

Red Line

Front 82

The hydraulic reservoir is pressurized with 15psi engine bleed air in order to

Back 82

Prevent foaming of the hydraulic fluid in the reservoir and provide head pressure to pumps

Front 83

The engine driven hydraulic pumps are

Back 83

Variable displacement, rotary plunger type pumps

Front 84

Hydraulic reservoir capacity is

Back 84

1.1 US Gallons

Front 85

Positioning the HYD PRESS switch from NORM to REL

Back 85

Opens the hydraulic bypass valve, directing the fluid back to the reservoir

Front 86

Normal hydraulic system pressure is

Back 86

1350-1550 psi (green arc)

Front 87

Which component does not require hydraulic pressure to operate

Back 87

Nose wheel steering

Front 88

Which is true regarding nosewheel steering

Back 88

Nosewheel steering is disengaged when the gear is retracted.
Rudder pedal deflection allows the nose wheel to travel 25 degrees in each direction.
Assymetric brake application and thrust can result in 45 degrees of nosewhee travel in each direction

Front 89

A rotating-disc-type assembly in each main gear assembly provides

Back 89

Braking force

Front 90

During the n ormal gear retraction cycle, what happens first after raising the gear handle

Back 90

The grar doors open

Front 91

With gear in the UP position, gear and gear doors are held up by

Back 91

Mechanical uplocks

Front 92

The nose wheel steering system is

Back 92

Mechanically actuated

Front 93

In the event both pilots are pressing the toe brakes

Back 93

The pilot who presses harder controls the brakes

Front 94

the parking brake should be

Back 94

Set only from the pilot's side

Front 95

When using the nitrogen system fro braking

Back 95

Anti-skid is unavailable and should make a steady, smooth application of the brakes

Front 96

When the anti-skid activates, which brake does it release

Back 96

both brakes

Front 97

Pressure above_____PSIG or temperature above ______F will close both pressure-regulator and shutoff valves, and ope the emegency pressuraization valve

Back 97

53 psig........400F