Sabado

1. - If the temperature controller for the cabin fails, what setting on the AIR-CONDITIONING control panel is selected to maintain compartment temperature?. Ram air. Right manual Switchlight. Cabin temperature control.

Why must the temperature of the pack be monitored on the ECS page if manual temperature operation has been selected?. In case the automatic temperature control fails. There is no upper or lower temperature limit in manual mode. All of the above.

Under normal conditions, which pack provides air to the flight deck?. Left pack. Right pack. Both.

If smoke is detected in the cargo bay, the... The right air conditioning pack is closed. Airflow is stopped by turning the fan in the AIRCONDITIONING control panel OFF. Airflow to the cargo bay is automatically stopper.

On the ground, with only battery power available, why is operating time limited?. Fans that cool the displays operate at a reduced flow. Fan operation is unpredictable on DC power. Fans that cool the displays are not powered.

What functions are automatically activated by the CPAM?. Seat belt and no smoking signs illuminate and oxygen masks drop down. Seat belt signs and emergency exits signs illuminate. All of the above.

The primary function of the IAPS circuitry is to: Provide a common data bus from which the aircraft computers communicate with other aircraft electronic components. Provide the power source for the air data computers. All of the above.

The CRJ-200 aircraft is equipped with two independent flight directors, which provide: Provide visual representation of the commands generated by the flight control computer. Flight guidance in the event of loss of all DC power. Manual input to the AFCS for pitch and heading commands only.

With the XFER pushbutton on the FCP panel selected: Flight director 1 is disabled and flight director 2 needs to be selected by either pilot. Flight director 2 is used as the active flight director. Flight director 1 is disables and flight director 2 needs to be selected by either pilot.

What information is displayed by the flight mode annunciator (FMA)?. Altitude preselected. Flight management computer initialization modes. Flight director modes.

Select the statement that best describes the active FMA area. Left field, lateral mode displayed above vertical mode. Modes selected but not yet captured by the flight control computer. Modes used by the flight director to compute the guidance commands.

Indications of mode engagement are: Green FCC status indicator lights on the FCP and a red line through the FMA. Green active mode in the FMA and green FCC status indicator lights on the FCP. Only the FMA presents active.

Controls for vertical mode are: Pitch wheel, FD pushbuttons, CRS 1 and CRS 2 knobs. Speed knob, VS, HDG knob, speed pushbutton. Speed pushbutton, speed knob, VS, pitch wheel, ALT pushbutton.

After selection of approach mode (APPR), which modes will be captured?. Autopilot turbulence and lateral go-around. Localizer and glideslope. Glideslope and half bank.

Prior to providing power to hydraulic system 3 the following precaution must be taken: System 1 and 2 must also be powered. Nose gear area must be clear. Passanger door must be in the closed position.

The FMA will display ALT to indicate: Preselected altitude armed. Preselected altitude captured. Altitude hold mode selected at FCP.

17. - The IDGs and APU generator are nominally rated for: 35 kva. 25 kva. 30 kva.

An acceptable quality of AC external power source is indicated by: IN USE on the AC switchlight. AVAIL on the AC switchlight. APU GEN switch in the ON position.

During normal conditions, in flight, AC essential bus is powered by. APU generator. Ac bus 1. TRU 1.

You are climbing with APU running and generator switched on, generator 1 fails. Which AC source will automatically power the affected buses?. Generator 2. ADG. APU GENERATOR.

When a generator drops off line due to a main AC bus fault, the automatic transfer inhibit system is activated…. To load shed a failed generator. To prevent the faulted bus from being re- powered. To allow the pilot to manually control.

In flight, when will the AC utility buses automatically load shed?. When only one generator is operating. When either AC main bus overloaded. When the APU generator is not operating.

The main purpose of the enclosure containing APU is to: Protect the APU from damage. Reduce the noise level in the cabin. Create a fire containment zone.

Under normal conditions, where are the APU OIL indications displayed?. No indications are displayed. Status Page. Primary page.

What is the alternative fuel source available to maintain APU operations?. Left engine fuel feed manifold. Right engine fuel feed manifold. Left booster pump.

Where is the APU exhaust gas temperature (EGT) data displayed for the pilots?. ECS page. Primary page. Status page.

What is the minimum battery voltage required to start the APU?. 24 volts. 22 volts. 28 volts.

The APU is supplying both electrical and pneumatic power simultaneously. As EGT increases and enters the amber range which of the following will occur?. APU shutdown. Left and right air conditioning packs close. LCV modulated towards close.

For normal APU shutdown, the controls used are: APU Shutoff button and L/R XFLOW switchlights. APU START/STOP switchlight and PWR/FUEL switchlight. APU START/STOP switchlight and APU GEN button.

What are the N1 and N2 sections of the CRJ-200 Engines?. High pressure turbines connected to the fan of the left and right engine. A single stage fan rotor N1 connected to a low pressure turbine and a compressor. N1 is the Power section and N2 is the accessory gearbox.

What type of airflow does the engine produce?. N1 fan airflow and N2 core airflow produce forward and reverse thrust. N2 section produces core and reverse thrust airflow. N2 section produces core airflow, N1 produces forward and reverse thrust airflow.

During normal operations, where are the oil temperature indications presented?. Primary page and status page. Status Page. Primary page.

The automatic performance reserve (APR) system when selected to ARM: Provides increased thrust is autopilot is engaged. B) Provides increased thrust during takeoff if a single engine failure occurs. Monitors N2 performance.

Where are normal engine fuel indications presented?. Primary and status pages. Status page onl. Fuel synoptic and primary pages.

The 10th stage Bleed air system provides air for: Engine starting and air conditioning. Engine starting and thrust reverses. Wing and cowl anti – icing.

The purpose of the 10th stage isolation valve is to: Modulate the pressure between the left and right sides of the manifold. Supply air for wing anti-icing and cowl anti- icing. Allow 10th stage air from any source to supply either or both.

What are the requirements to open the 10th stage isolation valve?. Pneumatic pressure from the engines or APU. DC electrical power from the 10th stage ISOL switchlight on the BLEED AIR control panel. DC electrical power from the 10th stage ISOL switchlight, and pneumatic pressure.

The ECS page displays: The 10th stage Bleed Air system. All Pneumatic systems. The 14th stage Bleed air systems.

What does the APU fuel feed and fuel crossflow have in common?. Both provide fuel balance between wing tanks. Fuel movement for both is provided by the XFLOW/APU pump. In the event of a main ejector failure, both provide an alternative source of fuel.

If the APU fuel pump fails, an alternative fuel source for the APU is: The right engine fuel feed manifold. Gravity feed. Not available.

Fuel quantity readouts are provided on: Fuel Synoptic page only. Primary page, fuel synoptic page and magnetic level indicators. Status page and fuel menu page.

The pilot’s control wheel, column and pedals provide independent control of the: Left aileron, left elevator, left spoileron. Left aileron, left elevator, rudder. All secondary flight control.

When a single hydraulic actuator (PCU) for an elevator is jammed: The jam tolerant mechanism causes a message to be displayed on the primary page. The pitch disconnect system is used to split the controls and regain use of the elevators. The jam tolerant mechanism ensures that the failed PCU is overpowered by the remaining two operable hydraulics actuators.

A failed elevator or aileron flutter damper is indicated to the pilots by: The master caution switchlight and an amber message on the primary page. A status message and a half circle symbol for the failed system on the flight controls page. A status message only.

How are the yaw dampers controlled?. Automatically by the ADC. By yaw damper actuators engaged through pushbuttons on the yaw damper control panel. By the autopilot when both yaw damper computer channels failed.

During flight with the ROLL DISC handle pulled and the amber ROLL SEL switchlights illuminated the pilot’s control wheel commands: Left Aileron and right spoileron. Right aileron and both spoilerons. Right aileron and right spoileron.

Which pages display by default on ED1?. Status, menu. Primary only. Primary sinoptic.

What do the data concentrator units do?. Concentrate and control displays of EFIS data. Allow pilot selection of synoptic pages. Process and relay data to the proper component or EICAS display.

What messages are associated with the single chime?. Status. Warning. Caution.

Which button on the EICAS control panel remains active if the ECP computer fails?. STEP, STAT, MENU. STEP, CAS, STAT, PRI. STAT, STEP, CAS.