Bus Guide 4 Eng Warning Dsply System Display FWD Ins Pnl EIS Switching Pnl ECAM Swtch

• Level 1 - ALERT - Associated with amber E/WD message, no aural signal and requires crew monitoring.
• Level 2 - CAUTION - Associated with the amber MASTER CAUT light, single chime and require crew awareness.
• Level 3 - WARNING - Associated with the red MASTER WARN light, CRC and require immediate action.

A level 3 Warning has priority over a level 2 Caution which has priority over a level 1 Alert.

• Independent - Failure affecting an isolated system/item without degrading other systems/items.
• Primary - Failure of a system/item that affects the use of other systems/items.
• Secondary - Loss of a system/item resulting from a primary failure.

On the lower left portion of the screen.

Secondary failures are displayed on the lower right portion of the E/WD and are preceded by an *.

Information has overflowed off the screen and the pilot must scroll down using the CLR push button on the ECAM panel.

Most warnings and cautions are inhibited to avoid unnecessary distractions during critical phases of flight.

• ENGINE FIRE
• APU FIRE
• ENG FAIL (ENG SHUT DOWN)
• ENG OIL LO PR
• L+R EVEV FAULT
• A/P OFF
• CONFIG
• FWC 1+2 FAULT

• 1 SIDESTICK FAULT (W)
• 2 PITCH TRIM NOT IN T.O RANGE (W)
• 3 SPEED BRAKES NOT RETRACTED (W)
• 4 RUDDER TRIM NOT IN T.O. RANGE (W)
• 5 SLATS/FLAPS NOT IN T.O. RANGE (W)
• 6 DOOR NOT CLOSED (C)
• 7 HOT BRAKES (C)
• 8 PARK BRAKE ON (W)
• 9 FLEX TEMP NOT SET (C) (unless thrust levers in TOGA detent)

• Items 1 - 7 T.O. CONFIG TEST
• Items 1 - 9 T.O. POWER

• 2 minutes after the second engine is started or when the T.O. CONFIG TEST push button is pressed with one engine running.
• TAKEOFF MEMO is removed when takeoff power is applied.

• Below 2,000' RA
• Memo disappears after touchdown (80 knots).

• Relative to the current phase of flight or
• When a system malfunction is detected.

• After a failure is displayed on the SD and all failure items have been cleared.
• Display will reappear when the slats are extended.

• The STATUS page holds messages other than CANCELLED CAUTIONS.
• Flashes after engine shutdown to alert maintenance of any other applicable messages.

• Provides sequencing, operation, monitoring and indications for the landing gear.
• Provides aircraft "In Flight" or "On the Ground" signals to other aircraft systems.

Green

No

Below 750' RA when the aircraft is in the landing configuration and the landing gear is not locked down.

Nothing - A safety valve shuts off hydraulic power to the landing gear system when airpseed is above 260 knots.

The landing gear is not locked in the selected position.

LGCIU

Yes - as long as it is still powered.

The Brake and Steering Control Unit (BSCU).

• Nose wheel steering is deactivated.
• Braking is powered by the Yellow hydraulic system.
• Anti-skid is deactivated.

• Normal brakes - Green
• Alternate brakes - Yellow backed up by a hydraulic accumulator.

Upon ground spoiler deployment.

• LOW - progressive press applied to the brakes 4 secs after ground spoilers deploy to decelerate at 5.6 fps.
• MED - ".........................................................."2 "....................................."9.8 fps.

Actual rate of deceleration is within 80% of the selected rate.

MAX

A/S >72 knots obtained, Thrust Levers moved to IDLE and Ground Spoiler extension (spoilers do not need to be armed with at least one engine in reverse they will autodeploy for RTO).

No - not with the Alternate Brake system.

Yes - if certain conditions are met.

Yes - when at least one engine is in reverse.

Approximately 7 full applications.

300ºC

5-minutes after brake temperature exceeds 300ºC or just before stopping at the gate, whichever occurs first.

• Yellow hydraulic pressure delivered to the left and right brakes.
• Yellow system brake accumulator pressure.

Press the brake pedals to ensure the aircraft slows while verifying brake pressure on the triple indicator is zero indicating the Green hydraulic system has taken over.

3 Display Mgmt Computers (DMC)

• DMC 1 - Cpt PFD, ND upper ECAM DU
• DMC 2 - F/O PFD, ND, lower ECAM DU
• DMC 3 - Backup

"INVALID DATA" will be displayed in the respective EFIS/ECAM display units.

The E/WD automatically replaces the SD on the lower ECAM display.

Select the ECAM/ND switch to CAPT or F/O to transfer the E/WD to either ND.

The E/WD display would automatically transfer to the lower display.

• Press and hold the appropriate system button on the ECAM Control Panel that you wish to view.
• Displayed for 30 seconds.

• Select ECAM / ND XFER switch to CAPT or F/O.
• Press & hold the respective push button on the ECAM Control Panel.

• Displays ALL the system pages successively in 1-second intervals when held down.
• Relase the push button to maintain display of the selected page.

• Recalls warning/caution messages that the activation of the CLR push button or flight phase inhibition may have suppressed.
• Held > 3 secs. the E/WD will show any caution messages suppressed by the EMER CANC push button.

"NORMAL" for 5 seconds.

• EMER CANC
• ALL
• CLR
• STS
• RCL

• Cancels the current Level 1 or 2 warning for the remainder of the flight.
• Cancels the current Level 3 warning for that occurence.

• Eng - oil quantity above 9.5 qts + .5 qts/planned flight hours
• Hyd - hydraulic qty. indexes in normal range
• Door - oxygen pres. - if half boxed in amber, check the MIN FLT CREW OXY CHART (FCOM 3.01.35)

• The system simulates the application of T.O. power and checks certain systems for proper config.
• A warning is displayed if a system is not configured properly.
• "TO CONFIG NORMAL" is displayed in the TO MEMO section if the configuration is correct.