Navigation/Auto Flight

通報

問題一覧

What does it mean when the ADR fault light illuminates steady on then ADIRS CDU?

A fault is detected in air data reference

On the pedestal mounted switching panel, the ATT HDG and AIR DATA selectors are at NORM, meaning:

ADIRU 1 supplies data to PFD1, ND1 and DDRMI. ADIRU 2 supplies data to PFD2, ND2

Tuning of VOR/DME and ILS is provided by:

Automatic tuning, manual tuning, backup tuning

In case of failure of FMGC 1 and 2:

RMP1 controls VOR, ILS DME and ADF receivers 1 RMP2 controls VOR, ILS DME and ADF receivers 2

The ALIGN light flashes:

During the alignment phase in case of IRS alignment fault

The FMGS consist of the following main components:

2 FMGS – 2 MCDU – 2 FAC – 1 FCU control panel

Normal electrical power supplies the A/C and the MCDU CRT is dark, without any other warning. It means:

The MCDU "BRT" knob is dimmed

On the ground, when electrical power is initially supplied to the A/C, the MCDU will automatically display:

A/C Status page

You press the "ALIGN IRS" prompt on INIT A page. On the ADIRS CDU the ALIGN lights flash but no message is displayed on the CDU:

Make a second "present position" entry

These messages appear on copilot side ND: SELECT OFF SIDE RANGE/MODE and MAP NOT AVAILABLE:

Single FMGC operation and the two EFIS control panels aren’t set at the same range and mode

Engines running, ready to taxi. This message appears: CHECK GW. Access to INIT B page is no longer available, on which page is it possible to insert the correct GW:

Fuel prediction page

Aircraft on RWY centerline, ready for take-off. To preset a HDG of 233°:

Turn HDG knob, set 233° pull HDG knob when ATC clears you to turn to 233°

One of the SRS disengagement conditions is not true:

Disengages by setting a new FCU altitude

Control of the A/C can be automatic or manual. Guidance of the A/C can be managed or selected.. How do you understand this situation? Managed guidance - manual control - selected speed:

FMGC computes and sends steering orders for navigation purposes. The pilot flies through the sidestick. Speed is adjusted in the FCU window

A hold has been entered in the F-PLN. Speed and NAV are managed . You want to leave this hold:

Activate IMM EXIT prompt

For A/C position determination, FMGC uses data from:

Both (DME, VOR or ILS systems) and (3 ADIRS)

In flight, following a manual position up-dating of the FMGC:

An IRS cannot be up-dated during A/C motion

The Expedite mode is active. To disengage it, one of these statements is not correct:

Press again the EXPD PB to cancel this mode

What are the basic modes of the FD:

HDG and V/S

The engagement of both autopilots is possible:

After APPR pb switch is pressed and illuminates

Can you read the HDG on the PFD:

Yes

A/C is in clean configuration and in Normal Law. When the FAC detects a too high angle of attack:

Alpha floor function operates

During ILS approach, LAND 3 Fail Passive (also called CAT 3 single), one engine fails below 100 feet RA: This causes a landing capability downgrading and you must go around:

False

During an ILS approach the NAV mode will be deactivated at:

Localizer capture (LOC*)

Can you display FD bars and FPV at the same time, for cross-checking on different PFDs;

Certified FMGS limitations. Max wind conditions for CAT III automatic approach performed in managed speed guidance with A/THR: Headwind - Tailwind - Crosswind

30 KT - 10 KT - 20 KT

The continuous cavalry charge audio identifies only one of the following:

Autopilot disengaged

Setting the thrust levers at idle will disengage the A/THR mode. A/THR will re engage:

When A/THR pb is pressed on the FCU

In one of the cases listed below, A/THR does not disengage:

When the aural warning announces "RETARD!"

The LOC pushbutton on the FCU is pressed to arm LOC mode. This is used for:

Approaching on an ILS with no G/S

What does an aural triple click mean during an ILS approach:

Landing capability down grading warning

The active F-PLN is erased when:

The A/C has been on groun for 30 seconds following the landing

Following a dual engine generator failure, emergency generator supplies the A/C:

Only FMGC 1 is available (NAV function only)

In which case are AP/FD, A/THR and auto landing capabilities totally lost?

2 IRS failure or 2 ADRs failures

The mandatory parameter used by the alpha floor detection is:

A/C angle attack

Rudder travel limitation is a function of:

FAC only

When the two YAW damper functions are engaged:

YAW damper 1 has priority, YAW damper actuator 2 is slaved

The safety tests are automatically performed:

On ground, at computer power up

When the two rudder trim functions are engaged:

Rudder trim 1 controls its motor, rudder trim 2 is in standby

The FMGC functions are:

Flight management and flight guidance

The trim function of the FAC is:

A Rudder Trim

In flight, in case of temporary loss of electrical power on FAC 2, FAC 2 pb "FAULT" comes on and:

It can be manually reset and the safety tests are not performed

The AFS (Auto Flight System) main computers are:

FMGC and FAC

With AP1 and AP2 not engaged and FD1 engaged:

FMGC1 is master

The autopilot does not disengaged in case of override on: in flight

A rudder pedal deflection less than 10° out of trim

In normal operation with the two MCDU’s showing the same page, a modification made by the pilot on MCDU 1 is sent to MCDU 2:

Via FMGC 1 and FMGC 2

The flight guidance function are:

Autopilot, Flight director, Auto-thrust

The position of the aircraft, used in the flight plan is computed by:

FM part of the FMGC

The Flight Director is engaged:

Automatically at system power up

With autopilot engaged, the rudder is normally controlled by:

The FAC

The normal FMGC operation is:

FMGCs operate according to master/slave principle

The FCU allows:

Selection of FG function modes

In cruise, lateral AP orders are executed by:

Ailerons, spoilers and rudder

With the aircraft in flight, AP engaged and A/THR active, the A/THR mode:

Depends on the AP longitudinal mode

With the aircraft in flight, A/THR not engaged, thrust levers in CLB gate, an ALPHA-FLOOR is detected:

A/THR automatically engages and controls the engine with TO/GA thrust.

The FAC computes rudder travel limit:

At any time

With AP engaged in LAND mode, the YAW damper actuator is controlled by:

An AP yaw order computed by the FMGC, via the FAC

On the FMA, on the second line of the longitudinal zone (FMA Column 2):

ALT in cyan indicates that ALT mode is armed

With the thrust levers in the CLB gate, A/THR disengages. The engine thrust:

Is frozen at the existing thrust

When TAKE-OFF mode is engaged (Thrust levers at the FLX or TOGA detent):

A/THR automatically engages but is not active

ADIRU 3 can supply information to:

DMC 1, DMC 2 and DMC 3

Air data modules (ADM) supply pressure information to the ADIRUs from:

All pilot probes and static ports

ADIRU 3 receives TAT information from:

The captain's TAT sensor

The baro correction or reference selected is sent to each ADIRU from:

The FCU

Each ADIRU receives two analogue inputs. They are:

Angle of Attack (AOA) and Total Air Temperature (TAT)

In normal operation the ADIRUs aligned using information from:

The MCDU

If ADIRU 2 fails, the correct action is:

Set ATT HDG and AIR DATA selectors to F/O 3

In normal operation, ADIRU 1 supplies information to:

The captain's PFD and ND

In ROSE NAV mode with VOR 1 selected, the ND displays what VOR information?

Bearing pointer only

In ROSE ILS mode, the ND displays what ILS information?

Deviation bar, selected course, G/S and LOC scales

In the event of no ADF1 reception, with ADF1 selected on ND:

The bearing pointer goes out of view and station ID may be replaced by frequency

In ROSE VOR mode, in the event of VOR receiver failure:

The VOR information flashes and the course pointer disappears

During Take-Off and Go Around with managed speed, the speed window on the FCU displays:

Dashes and the light is illuminated: managed speed such as V2 or memorized VAPP are automatically used by the FMGS

The following AP/FD lateral modes are managed:

NAV, APPR, LOC, RWY, RWY TRK, GA TRK

On approach, LAND illuminates green on FMA when radio altitude is:

400 feet

On the ground, the engagement of the autothrust function:

Is performed automatically at the engagement of the takeoff mode

Climbs and descents are always limited:

By the altitude manually selected on the FCU

In flight, the FMGS radio position is updated:

Automatically with the DMEs through the auto tuning function

On the ND, in the event of VOR receiver failure:

The VOR bearing and the course pointer disappear

In flight, the FMGS position is automatically updated:

By the DMEs through the autotuning function

The IR FAULT light flashes:

When an IR fault has occurred, however attitude and heading information may be recovered in ATT mode

The aircraft has ___ ATC transponders which are controlled by a dual control box on the center pedestal.

Two

The G/S warning may be canceled by selecting the G/S pushbutton OFF:

True

The TCAS predicts the flight path of the other aircraft based on their ATC transponder replies. When will the TCAS alert the flight crew with a Traffic Advisory?

When a tracked aircraft enters the caution area, 40 sec from the collision area

The Weather Radar picture is displayed on the ND:

In all ND modes except PLAN

TCAS STBY appears in green when:

All options

What are the two types of guidance?

Selected and managed

What is the minimum height for AP use on a non-precision approach?

MDA

How many legs can a flight plan contain?

200

In SRS mode, what speed does the aircraft maintain with 2 engines operative and with 1 engine operative?

V2 + 10 knots / Highest of V2 or current speed (Maximum V2 + 15 knots)

What unit is used for short-term interface?

FCU

Which of the following units are part of the Flight Management System (FMGS)?

Two Flight Management Guidance Computers (FMGC) and Two Multipurpose Control and Display Units (MCDU) and One Flight Control Unit (FCU) and Two Flight Augmentation Computers (FAC)

What is the normal mode for the FMGCs?

Dual mode

How many GPS receivers are connected to the IR part of the Air Data Inertial Reference Unit (ADIRU)?

Two independent receivers

Below what height do the Flight Warning Computer (FWC) generate height announcements?

2500 feet

With the Predictive Windshear (PWS) switch in AUTO, below what height is data displayed on the ND?

1500 ft RA

How long must the RESET p/b on the Integrated Standby Instrument System (ISIS) be pressed to reset the attitude indication?

At least 2 seconds

If ALL/N is selected on the ATC/TCAS panel, what is the altitude range of intruders that are displayed?

2700 feet above / 2700 feet below the aircraft

With AP1 and AP2 not engaged, FD1 and FD2 engaged and A/THR active:

FMGC1 controls both engines

B777 - Part 8

B777 - Part 8

B777 - Part 3

B777 - Part 3

B777 - Part 6

B777 - Part 6

B777 - Part 4

B777 - Part 4

B777 - Part 1

B777 - Part 1

B777 - Part 7

B777 - Part 7

B777 - Part 9

Angelo Ortiz · 28問 · 3年前

B777 - Part 9

28問 • 3年前

B777 - Part 2

B777 - Part 2

B777 - Part 5

B777 - Part 5

Angelo Ortiz · 100問 · 2年前

AIA - VUL

AIA - VUL

100問 • 2年前

Underwriting

Angelo Ortiz · 66問 · 2年前

Underwriting

66問 • 2年前

Airplanes and Aerodynamics

Angelo Ortiz · 49問 · 2年前

Airplanes and Aerodynamics

49問 • 2年前

Airplane Instruments, Engines and Systems

Angelo Ortiz · 77問 · 2年前

Airplane Instruments, Engines and Systems

77問 • 2年前

Airport, ATC and Airspace

Angelo Ortiz · 88問 · 2年前

Airport, ATC and Airspace

88問 • 2年前

Angelo Ortiz · 100問 · 2年前

Federal Aviation Regulations - Part 1

Federal Aviation Regulations - Part 1

100問 • 2年前

Federal Aviation Regulations - Part 2

Angelo Ortiz · 89問 · 2年前

Federal Aviation Regulations - Part 2

89問 • 2年前

Airplane Weight and Balance

Angelo Ortiz · 10問 · 2年前

Airplane Weight and Balance

10問 • 2年前

Medical Factors and Decision Making

Angelo Ortiz · 25問 · 2年前

Medical Factors and Decision Making

25問 • 2年前

Weather and Services

Angelo Ortiz · 87問 · 2年前

Weather and Services

87問 • 2年前

Navigation

Angelo Ortiz · 30問 · 2年前

Navigation

30問 • 2年前