BOEING 737 NG INSTRUMENT AND INDICATING SYSTEM / NAV

With the CONTROL PANEL select switch on the DISPLAYS Source Panel in the BOTH ON 2 position: The First Officer's EFIS Control Panel is supplying identical inputs to the captain's & First Officer's displays. Both pilots displays are using the No.2 symbol generator. DEU 2 controls all six display units. ADIRU inputs for both the L & R ADIRU are being received from the First Officer's pitot probe.

The Slip/Skid indication of the Attitude Indicator will turn amber if bank angle is 35 degrees or more. True. False.

The Glide Slope Pointer is not displayed when the track and the front course on the Mode Control Panel differ by more than 90 degrees (backcourse). True. False.

The standby radio magnetic indicator (RMI) displays magnetic heading & VOR/ADF bearing to the station. The RMI is powered by: The AC transfer bus 2. The AC standby bus. The DC standby bus. The TR3.

Concerning Navigation Display Information, Heading is supplied by Air Data Inertial Reference System (ADIRS) & Track is supplied by the FMC during normal operation. True. False.

If you select the 'BOTH ON 1' switch of the CONTROL PANEL: The Left EFIS control panel controls both pilots' outboard & inboard display units. The Right EFIS control panel controls both pilots' outboard & inboard display units. The Left ADIRS controls both pilots' outboard & inboard display units. The Right ADIRS controls both pilots' outboard & inboard display units.

The Mach digital counter indicates current Mach number & it is displayed when airspeed increases above Mach. 0.30. 0.40. 0.50. 0.60.

The display SOURCE selector also allows the crew to manually select either DEU1 or DEU2 for all 6 display units. If the displays are automatically or manually switched to a single DEU source, a 'DSLPY SOURCE' annunciation illuminates above both pilot's altimeters. True. False.

If the Upper Display fails: The engine display automatically moves to the Inboard display and the Upper display blanks. The engine display automatically moves to the Outboard display and the Upper display blanks. The engine display automatically moves to the Lower display and the Upper display blanks. The engine display automatically moves to the Inboard or Outboard display and the Upper display blanks.

What is the purpose of the Air Data Modules (ADMs)?. The ADMs convert pneumatic pressure to electrical signals and send these data to the ADIRUs. The ADMs provide only pitot & static pressure to the standby instruments. The ADMs provide inertial position & track data to the displays thru the ADIRUs. The ADMs measure thru the Alpha vanes the airplane angle-of-attack.

The Weather Radar Annunciation 'WXR ATT' indicates: The Weather radar has failed. The Weather radar Attitude calibration has been lost. The Attitude stabilization for antenna has been lost. The Display unit cooling has been lost or an overheat condition has occurred.

The ND Wind direction/speed and wind arrow is: Displayed in only in ND MAP mode. Blanked if wind speed becomes less than 6 knots. Displayed if wind speed is greater than 6 knots. Displayed only in ILS mode.

During an ILS approach the Captain observes his BARO minimum reference/ altitude turns from green to flashing amber for three second. What does it mean?. Radio altitude data is unreliable. The aircraft has descended below the Captain's selected minimum altitude (DA). A windshear has been encountered. The aircraft has descended below 1000 feet.

The decision height (DH) display on the CDS is set: Automatically when APPROACH is selected on the MCP panel. Independently by each pilot using his/her EFIS control panel. By entering the desired DH on the FMC CDU APPROACH REFERENCE page. By using the DH selector knob on the forward instrument panel.

The aircraft is on the ground and the Flight Recorder Switch is in NORMAL: The Flight Recorder operates anytime electrical power is available. The Flight Recorder operates when electrical power is available and either engine is operating. The Flight Recorder operates whenever the Battery Switch is ON. The Flight Recorder operates anytime electrical power is available and start switch in GROUND position.

The First Officer observes the word PITCH displayed in amber in the lower portion of the PFD during an ILS approach. What does it mean?. The autopilot has defaulted to CWS pitch. Glide slope is not being tracked. The Captain's and First Officer's pitch displays differ by 5 degrees or more. The First Officer's pitch display is more than 3 degrees in error.

An amber DSPLY SOURCE annunciation below each speed tape indicates: The altimeter is receiving inputs from a source other than the ADIRU and should be considered unreliable unless verified by another source. A single DEU has been manually or automatically selected to drive all six display units. A non-dispatchable CDS fault has occurred. A single EFIS control panel has been manually or automatically selected as the source for all six display units.

If an outboard display unit fails, the PFD is automatically displayed: Never. It can only be displayed manually with the MAIN PANEL DU selectors. On the ENGINE PRIMARY display. On the ENGINE SECONDARY display. On the inboard display unit.

An amber CDS FAULT annunciation below each speed tape indicates: The altimeter is receiving inputs from a source other than the ADIRU and should be considered unreliable unless verified by another source. A single DEU has been manually selected to drive all six display units. A non-dispatchable CDS fault has occurred. Single EFIS control panel has been manually or automatically selected as the source for all six display units.

The Air Data Inertial Reference System (ADIRS) produces following flight data: Position and speed only. Attitude and speed only. Altitude and speed only. Position, attitude, altitude and speed.

When Max range is selected on the EFIS Control Panel, weather radar returns are limited to: 80 NM. 160 NM. 320 NM. 640 NM.

With the weather radar in WX/TURB mode, turbulence will be shown within: 160 NM. 120 NM. 80 NM. 40 NM.