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JetSuiteX EMB145 > Systems > Flashcards

Systems Flashcards

1
Q

ADC#1 Fail

A

Loss of Airspeed, Altitude and VSI. QRH NAP-29

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2
Q

Flap Speeds

A

QRH (Performance Data) PD-2

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3
Q

DC-Bus #2 Fails

A

MFD#1, PFD#2,

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4
Q

IC-600#1 and IC-600#2 powered from

A

Essential DC#1 and DC#2

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5
Q

nose wheel static wick

A

must be capable of touching

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6
Q

ADC#1 and ADC#2

A

ADC#1: Pitot#1 and Static Ports 1 and 4

ADC#2: Pitot#2 and Static Ports 2 and 3

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7
Q

Flight Data Recorder

A

Red BCN turns on FDR on ground, or FDR turns on automatically if airborne.
FDR: 25 hours solid state memory

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8
Q

CVR

A

Records for 2 hours solid state memory.

CVR test; LED lights up for 1 second.

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9
Q

T/O Config Check

A

Flaps, Spoiler, Trim, and Brakes

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10
Q

ICAS Inhibition Logic

A

Takeoff: from V2-15 until 400’
Landing: from 200’ AGL until WOW plus 3 sec or 60 sec from passing 200’

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11
Q

FLC - Flight Level Change Mode

A

Holds Speed 240 KIAS (<10,000) - 270 KIAS M0.65 (>10,000)

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12
Q

Digital Audio Panel - EMRG Button

A

Ties to COM#1 on PIC side or COM#2 on SIC side

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13
Q

AC BUS

A

115v 400hz, powers EGWPS/WINDSHEAR and TCAS

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14
Q

GPU Connected

A

All buses powered, batteries are NOT being charged

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15
Q

How many Batteries

A

Batt #1 and Batt #2 are interchangeable 24v; 44 amp hr Ni-Cads.
Batt #3 - 24v 5 amp Lead Acid (provides stabilized power for GCU)

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16
Q

Fire Suppression System, Baggage Compartment

A

Two bottles: one high rate and one metering for 50 mins

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17
Q

of GENs for SHED BUSES to be AUTO

A

3 or more

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18
Q

4 or 5 GENs ON

A

Two isolated left and right electrical networks with all buses energized

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19
Q

3 GENs ON

A

Both electrical networks interconnected (one network) through Bus Tie Contactors with all buses energized

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20
Q

1 or 2 GEN’s ON

A

Both electrical networks interconnected (one network) through Bus Tie Contactors with shed buses deeergized

21
Q

Loss of all GEN’s

A

Batteries to supply the Essential Buses (in-flight condition only)

22
Q

Power Loss to Essential DC Bus

A

Emergency Lights come on

23
Q

Accessory Gearbox

A 
H-ydraulic Pumps
O-il Pump
T-urbine (pneumatic starter)
F-uel Pump and Metering Unit (FPMU)
A-lternator (PMA)
G-enerators x2
24
Q

Fuel Pumps - Power Source

A

A and B pumps - Essental DC Buses

C pump - Main DC Bus

25
Q

ATTCS

A

Automatic Takeoff Thrust Control System

26
Q

Starting Engines

A

> 3 sec will abort start
RUN Position 3 sec
START Position 1 sec

27
Q

Engine Driven Hydraulic Pumps PSI

A

3000 PSI

28
Q

Electric Hydraulic Pumps PSI

A

2900 PSI +/- 200

Automatic Mode: <1600 PSI or N2 drops <56.4%

29
Q

Priority Valve

A

Hydraulic System 1: The Priority Valve will provide minimum flow to the landing gear system and give priority to the flight control services.

30
Q

Hydraulic System 1 - Liters

A

6L reservoir
1L Amber Range
<1600 PSI DC Pumps ON

31
Q

HYD SYS 1 (2) FAIL

A

ON CHECKRIDE

32
Q

Brake Overheat

A

> 420º, Temp in Amber range NO T/O

33
Q

Nose Wheel Steering

A

Electronically controlled and hydraulically operated. Pedals only 5º, steering handle only 71º, handle and pedals 76º

34
Q

Brake System: Touchdown Protection

A

Brake actuation will be allowed only after 3 seconds from the latest touchdown or after the wheels have spun-up to >50 kts.

35
Q

Brake System: Locked Wheel Protection

A

For wheel speeds below 30 kt, the locked wheel protection is deactivated and the brake system actuates without the wheel speed comparator. For wheel speeds below 10 kt, the anti-skid protection is deactivated, allowing the pilot to lock and pivot on a wheel.

36
Q

Landing Gear: Electrical Override

A

Bypasses the LGEU (Landing Gear Electronic Unit) and actuates directly the Landing Gear Electrovalve and the Nose Gear Doors Solenoid Valve.

37
Q

Landing Gear: Free-Fall Extension

A

Mechanically actuates the Free-Fall Selector Valve and unlocks 3 gear uplocks. Hydraulic fluid is sent back to reservoir.

38
Q

When Engine Fire Extinguishing Handle is pulled, what is cut off?

A

H - Hydraulics
A - Bleed Air
L - Lip Anti-Icing
F - Fuel at wing root

39
Q

Pitot/Static Tube 3 supplies

A

Total air pressure to the stby Airspeed Indicator, and static pressure to the stby Airspeed Indicator and stby Altimeter. Pitot/Static tube 3 supplies static pressure to the Cabin Pressure Acquisition Module (CPAM)

40
Q

Data Acquisition Units (DAU’s)

A

DAU#1 Left Engine and Forward Aircraft Systems
DAU#2 Right Engine and Rear Aircraft Systems
Each DAU has a Primary and Secondary channel. If a failure is detected the DAU will switch to the secondary channel.

41
Q

IC-600#1, IC-600#2 control which displays?

A

IC-600#1 - PFD#1, MFD#1, EICAS

IC-600#2- PFD#2, MFD#2

42
Q

Power source for PFD#1, MFD#1, EICAS MFD#2, PFD#2

A 
PFD#1 - DC1
MFD#2 - DC2
EICAS - Essential DC Bus#1
MFD#2 - DC1
PFD#2 - DC2
43
Q

Power source for IC-600#1, IC-600#2

A

IC-600#1 - Essential DC Bus#1

IC-600#2 - DC2

44
Q

Power Source RMU-1, RMU-2, backup RMU-3

A

RMU-1 - Essential DC Bus #1
RMU-2 - Essential DC Bus #2
RMU-3 (backup) - DC Bus #2

45
Q

Turn WX on ground

A

STB x 4 < 3 sec

46
Q

Electrical System - In normal duel network, 4 generators or greater, which bus tie contactor is open?

A

Bus tie contactor #1 - (BTC 1)

47
Q

EGPWS Escape Maneuver

A

Max Thrust
Pitch Up 20 degrees
Climb to MSA

48
Q

BLD 1(2) OVTEMP

A

Associated pre-cooler downstream temperature above 305 degrees C

JetSuiteX EMB145 (3 decks)

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