Test 4 - Fire Protection, Auto Pilot, Ice & Rain Protection

1.

1 point

The auto pilot can be disengaged by

Pressing the engage button

Pressing the quick release button

Either a) or b)

2.

1 point

The aural warning "auto-pilot" will occur

Only below 2500 ft

At any altitude

At any altitude but is self cancelling above 2500 ft

3.

1 point

Bleed air for the engine inlet ice protection system comes from

14th stage, irrespective of high stage valve position

Either 9th or 14th stage bleeds

14th stage, dependent upon high stage valve position

4.

1 point

Failure of IC600-1 will cause the loss of

FD and YD functions

All auto pilot and FD functions

Pitch and Turn controller and the three control servos

5.

1 point

Where is the roll mistrim annunciation displayed

On the PFD in digital format

On the EICAS

On the PFD in analogue format

6.

1 point

Does the selected heading bug always appear on the PFD when in arc format

Yes, but only when within 15 deg of present heading

No

Yes

7.

1 point

What aural warning do you get on AP disengagement

Two triple chimes

Double chime

Voice message "Auto-Pilot"

8.

1 point

The vertical default mode is

Pitch hold mode

Speed hold mode

Altitude hold mode

9.

1 point

What indications would you see for AP failure

Red AP in message field (flashing for 5 seconds). Flashing master warning and flashing EICAS warning message AUTOPILOT FAIL.

Flashing caution AUTOPILOT FAIL.

Flash master warning and flashing red message AUTOPILOT FAIL.

10.

1 point

The go-around mode is

A lateral mode

Both vertical and lateral

A vertical mode

11.

1 point

If, when in flight you suspect icing conditions but the system has not been triggered, your first course of action should be

Switch the override switch to all

Don't worry, it's all automatic

Make manual selection using the OHP button switches

12.

1 point

Pressing the fire test button causes

EICAS fire detection messages displayed, fire handles illuminated, baggage fire button illuminated, warning/caution lights flash, fire bell sounds

As above, plus baggage compartment fan shuts down

As in (a) above, but excluding baggage fire button

13.

1 point

All sensors are electrically heated and controlled by ... buttons located on the over head panel

Two

Three

One

14.

1 point

How is low bank mode selected

By pressing the BNK button

By pressing the 1/2 button

By pressing the BNK button and automatically when climbing above 25,000 ft

15.

1 point

What does the green CAT II annunciation on the PFD signify

Transponder function that signifies that the aircraft is cleared for a Category II approach

All approach aids are set for a Category II approach

All conditions for a Category II approach are met

16.

1 point

The windshield heating system is designed to maintain screen temperature between

38 C and 55 C

40 C and 45 C

40 C and 50 C

17.

1 point

The fire protection works on the principle of

Circuit failure

Electrical resistance

Gas expansion

18.

1 point

The engine fire bottles can be utilised

Both bottles to one side if required

Own side only

Opposite side by making a switch

19.

1 point

The EMB 145 is making a Category II approach when the selection of 45 deg of flap is made. The aircraft is below 1000 ft RA. What should the pilot see

The CAT II annunciation flashing and then turning red

The CAT II annunciation flashing amber

Hopefully the runway at approx 200 ft

20.

1 point

Lateral default mode is

Heading hold

Heading

Roll hold

21.

1 point

The yaw damper

Can be engaged at 500 ft RA after takeoff

Can be used without the autopilot

Can only be used with the autopilot engaged

22.

1 point

PFD indications, of Flight Director modes are:

Green for captured, amber for armed

Always green

White for armed, green for captured

23.

1 point

How many separate fire detection circuits are there in the areas of the engines and APU

2

3

5

24.

1 point

Where does the air exiting horizontal stabiliser anti-ice system leave the aircraft

Exit ports adjacent to the elevator horn either side.

Slots on the underside of the stabiliser leading edge

Slots on top of the fin post

25.

1 point

In automatic mode the pitot and static heating is applied

Whenever at least one engine is running

Whenever the aircraft is airborne

Whenever both engines are running

26.

1 point

With the ice protection OVERRIDE switch set at ENG

Engine anti-ice is provided at all times on the ground and in flight

Engine anti-icing is provided as soon as wheel speed rises above 25 kts

Engine anti-icing is provided as long as the APU is running

27.

1 point

The lavatory waste bin extinguisher activates automatically if the temperature in the bin exceeds

70 C

90 C

77 C

28.

1 point

Caution messages are presented on the EICAS to indicate that sensor heating is inoperative. These messages are

Inhibited for takeoff

Are provided whenever triggered for any reason

Inhibited for takeoff and landing phases

29.

1 point

With the aircraft stationary at the holding point and the ice detection override switch set to ALL

Engine and airframe anti-ice will be on

Engine and airframe anti-ice will be off as the aircraft is below 25 kts

Only engine anti-ice will be on

30.

1 point

How are manual inputs made to the auto-pilot

The pitch and turn controller

The guidance controller

By using the control yoke after pressing the quick release

31.

1 point

Speed hold mode is used to maintain airspeed

IAS is used below 25,000 ft and mach number above

Both IAS and Mach number are used at all altitudes

IAS is used for all altitude

32.

1 point

What cockpit indications do you have that the main anti ice system is working

None

OPEN inscriptions on the selector buttons

Hatched light on the selector buttons

33.

1 point

Pulling a fire handle shuts off

Fuel and bleed air only

Fuel, hydraulics, bleed air and engine anti-ice bleed

As in (a) above, and fires the first extinguisher bottle

34.

1 point

Apart from under and over pressure, what other conditions will cause the bleed air systems to trigger their respective caution FAIL messages

Valve failure, switch failure and system activation device failure

As in a) above, but also including asymmetrical degradation of wing systems

As in a) above, but also including duct leakage for wings and stabiliser

35.

1 point

The baggage compartment is equipped with a double bottle system. The second bottle is designed to

Operate over a period of time to provide 50 minutes protection against re-ignition

Operate in unison with the first bottle to give adequate protection

Operate after 60 minutes to give continuing protection

36.

1 point

Where is the switch for the baggage compartment fire extinguisher

Adjacent to the right fire handle

On the control pedestal aft panel

On the O/H panel forward left

37.

1 point

For aircraft equipped with baggage fire extinguishers, if it is necessary to repeat the fire test

No limitation on testing

Wait at least 10 seconds

Wait at least 6 seconds

38.

1 point

The turn control knob will

Should be pulled out to set a constant rate of turn

Remain where it is when released

Return to centre detent when released

39.

1 point

The caution message W/S 1 (2) HEAT FAIL monitors the correct heating of the screens

It will trigger at <50 C and >50 C

It will trigger at <38 C and >55 C

It will trigger whenever outside normal range

40.

1 point

The EICAS message CROSS BLD OPEN will show whenever

Cross bleed start is in progress

Wing anti-ice is operating, cross bleed start is in progress and when the anti-ice system is being tested

As in b) above, but excluding the test function

41.

1 point

What are the possible selections on the wiper switches and what is maximum IAS for use

OFF - SLOW - FAST - 175 kts

PARK - OFF - LO - HI - 170 kts

TIMER - OFF - LOW - HI - 170 kts

42.

1 point

The speed knob of the guidance controller

Is inhibited while the GA mode is selected

Should only be used to increase climb speed with GA mode engaged

May be active whilst the GA mode is selected

43.

1 point

How do you select an altitude and where is your selection displayed

Pressing the ALT button twice, bottom of PFD

Using the push sync knob on GC as altitude is reached. Displayed to side of altitude tape

Using the ASEL knob on the GC, displayed above altitude tape on right side top of PFD

44.

1 point

What activates the air bleed thermal anti-icing system under normal cicumstances

Switches in the OHP selected by the crew upon encountering incing conditions

Automatically through the ice detector activation

Automatically but only when set to the override position

45.

1 point

During CAT II approach how does the lateral deviation scale change with a needle deflection of 2/3 dot to the right

No change

Flashing white, every second

Colour amber, flashing every second

46.

1 point

What is the Category II annunciation and where does it appear

White CAT 2, Top right of PFD

Green CAT 2, Bottom right of PFD

Green CAT 2, Top right of PFD

47.

1 point

The definition of icing conditions applicable to the EMB 145 is

Whenever OAT on the ground, or TAT in flight is 10 C or less with visible moisture

SAT 10 C or less, with visible moisture

OAT of 5 C or less with visible moisture