System Review PTM CH-01 (Aircraft General) Flashcards

(45 cards)

1
Q

Aircraft Certification Category

A

14 CFR Part 25 and JAR-25

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2
Q

Tail Height

A

20’ 10”

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3
Q

Wing Span

A

72’ 4”

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4
Q

Length

A

62’ 3”

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5
Q

Wheel Track Width

A

10’

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6
Q

What kind of wing does the Latitude have on it?

A

Stretched Delta Wing

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7
Q

Antenna Locations

A

Insert picture

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8
Q

Nose Section Contains the following:

A

Baggage Fire Bottle

Pneumatic bottle and gauge for emergency braking

Pneumatic bottle and gauge for landing gear blow down

Nosewheel steering (NWS) accumulator and gauge

Oxygen Bottle and servicing port

Fan assembly for avionics cooling

ADC 1-2

TCAS

HNS (Hybrid Navigator System) 1-2

DME 1-2

TRU 1-2

Standby Battery

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9
Q

Nose doors

A

4 mechanical switches per door with integral microswitches to monitor the latch position.

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10
Q

Minimum 180 Degree Turn Distance for wingtip clearance

A

83 ft

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11
Q

Door Counterbalance System

A

Attached to the handrail on aft portion of door.
Consists of a nitrogen charged gas spring to assist in opening and closing of the door in the event of door motor failure.

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12
Q

Cabin Entry Door Lift Motor

A

Attached to forward portion of door.

Controlled by external and internal panels.

Provides braking action during opening.

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13
Q

Door Motor Source of Electrical Energy

A

Left Battery Bus.

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14
Q

Door Closing

A

Lift motor holds door in closed position 10 (+/- 2) seconds to allow latching before allowing door to fall.

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15
Q

Pressure Warning LED

A

Indicates the cabin remains pressurized.

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16
Q

Door Open LED

A

Illuminates when Cabin Door Open CAS message displays.

One or more of the door monitoring switches indicate an unsafe condition.

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17
Q

Acoustic Door Curtain

A

Reduces noise during flight. Must be stowed for taxi, takeoff, and landing.

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18
Q

Water Barrier

A

Allows main exit to be used as additional egress route if emergency exit is inaccessible after ditching. It prevents water from rushing into the cabin. Must be installed prior to water landing and before cabin door is opened.

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19
Q

Emergency Exit Hatch

A

Plug type located above toilet on the right side of aircraft. Can be removed from either inside or outside the cabin. Electrically monitored and if unlatched will trigger CAS message.

20
Q

Lavatory Pocket Doors

A

Must be open during taxi, takeoff, and landing to provide access to emergency exit.

21
Q

Lavatory Door Amber CAS

A

Anytime either door is not stowed while on the ground, and inflight below 18,000 ft if either door is not stowed and either main landing gear is down and locked or the flaps are not up.

22
Q

Lavatory Door White CAS

A

Displays inflight anytime below 18,000 ft if either door is not stowed and the landing gear and flaps are up.

23
Q

Toilet Seat for takeoff and landing

A

Not an authorized seat.

24
Q

Baggage Compartment

A

Non-pressurized, non-heated can hold 1000 lbs evenly distributed between forward, aft zones, and coat rod.

25
Baggage Compartment Light
Has 15 minute timer.
26
Baggage Compartment Door
Has seal to enhance baggage fire protection by preventing air (oxygen) from entering and fire suppressant from leaving the baggage compartment.
27
Baggage Door Open Amber CAS
Displays when open or any of the four latches are not secured.
28
Tailcone Service Area
Contains various system components. Electrically monitored with Tailcone Door Open Amber CAS.
29
7 Unmonitored Access Doors
1. Single point refueling door. 2. Left Battery door. 3. Right Battery door. 4. EPU receptacle door. 5. Lavatory service door. 6. Hydraulic service door. 7. Hydraulic reservoir accumulator bleed access door.
30
Lavatory
Externally serviced. Needs interior button on and lav service door closed in order to flush. Without the right battery connected it is only possible to drain the lav. Circuit Breakers for the lavatory are located in the aft cabin J-Box.
31
Lavatory Service Procedure
1. Drain 2. Fill with 3 gallons of water 3. Drain 4. Fill with approximately one gallon of lavatory solution until green service panel light illuminates.
32
Aft Fuselage
Contains an APU. APU provides DC electrical power for the entire aircraft, and bleed-air for most pneumatic systems including air conditioning, pressurization, and service air.
33
Wings
Contain 3 spars. Leading edge swept by 16 degrees.
34
Trim
Is electrically controlled and mechanically actuated.
35
ACM Heat Exchanger Inlet
Located in the base of the vertical stabilizer.
36
Strakes
Two strakes provide for additional lateral stability.
37
Electrical System
Split Bus, with two engine driven generators, an APU generator and two NICAD batteries.
38
AC Power
Provides windshield heating. This power is provided through 2 engine driven alternators.
39
Transformer Rectifier Unit (TRU)
2 TRU are provided to convert AC to DC power in emergency situations.
40
Transformer Rectifier Unit (TRU) Amperage
Provides 100 Amp of DC Power to associated side EMER Bus.
41
Landing Gear & Brakes
Electrically controlled and hydraulically operated.
42
Engines
Pratt & Whitney PW306D1 controlled by dual channel FADEC.
43
Hydraulics
Provided by two engine driven pressure compensating pumps.
44
Hydraulically Powered Items
1. Thrust reversers. 2. Speed brakes 3. Spoilers 4. Landing Gear 5. Wheel brakes 6. Nosewheel steering
45
Electrically Powered Auxiliary Hydraulic Pump
Tied into hydraulic system normally used to set parking brake prior to engine start.