Situations that can inhibit speedbrake extension or cause them to automatically retract
- Manoeuver Load Alleviation (MLA)
- Low Speed Stability
- Alpha Prot
- Alpha Floor
- 1 thrust lever above MCT
Speedbrakes inhibited in flight
How can they be re-deployed
• Once the inhibiting condition disappears:
- Speedbrake lever stowed
- Wait 5 seconds
- Try again
ECAM EXCESS CAB ALT
At what cabin altitude is it triggered
9,550 ft
Protections for the Flaps/Slats system
- Flap Load relief
- Auto retract
- Alpha Lock
Difference between GPWS and EGPWS
• Enhanced GPWS incorporates basic GPWS functions with added features:
- Terrain Awareness Display (TAD):
Computes a Caution and a Warning Envelope ahead of the flight path using aircraft altitude, range to the nearest runway and its altitude, ground speed, and turn rate.
When these envelopes conflict with terrain memorized in the database, an alert is generated. - Terrain Clearance Floor (TCF)
An Envelope is stored in the database for each runway where terrain data exist, TCF warns of a premature descent below this floor, regardless of the aircraft’s configuration. - Runway Field Clearance Floor (RFCF)
Provides an Envelope protection for runways that are significantly higher than the surrounding terrain.
Computers used by the ECAM
- DMC: Drive Display Units
- SDAC:
Acquire data and send signals to display synoptics
Sends data to the FWCs to generate ECAM msg - FWC:
Acquire data from SDACs and A/C sensors to generate ECAM and aural alerts, flight phases, RA - DH/MDA call outs
Red Warnings are processed directly by FWCs
Amber Cautions are processed by FWCs through SDACs
ECP failure which keys work
CLR, RCL, STS, ALL and EMER CANCEL are hard wired to the FWC/DMC. They are the only one operating if ECP fails
EIVMU failure, what do you lose
• If EIVMU fails, the following functions are lost:
- Manual start
- N1, N2 and N3 Vibration indications
- A/THR on affected engine
- Reverser
- Modulated Idle (only Approach Idle)
- FLX and Derated T/O
Land Recovery
AC LAND RECOVERY and DC LAND RECOVERY buses are recovered. Following equipment is restored:
-LGCIU 1
-SFCC 1
-BSCU Channel 1
-LH windshield anti-ice
-LH landing light
Note: remaining fuel pump will be shed at 260kt (if emer gen powered) or at land recovery selection.
When pb-sw pressed in EMER ELEC, ADR 3 is lost resulting in AP1 lost.
Landing Gear gravity extension, consequences
• Gear doors stay down: - Speed limit 200 kts - NWS not available, Tug needed after landing - Missed approach: . No Gear retraction . Speed selected 200 kts . Keep Flaps 1 for the speed
Emergency Electrical Configuration
Systems remaining with Green powered by 1 EDP or by the RAT ?
• Green Powered by 1 Engine Driven Pump:
- FMGC1, MCDU1, FD1 and AP1 available
- Use Land Recovery:
. FD1, AP1, both RA are lost
. ILS Raw data approach, plan a long final, PM make RA calls
. Full SFCC1 available
. Manoeuvring speeds displayed on PFD
. Gear Gravity extension
. Direct law , USE MAN PITCH TRIM 15 sec after LDG down
• Powered by the RAT:
- FMGC1, MCDU1, AP1, FD1, Pitch and Rudder Trim are lost
- RMP1 RNAV mode to tune VOR1 and DME1
- Use Land Recovery:
. Red Speed Limit on PFD, compute F, S, VApp with QRH
. ILS Raw data approach, plan a long final, PM make RA calls
. SFCC1, Slat channel only, Landing Flaps 0 / Slats 2
. CSM-G disconnects at Slats extension, BAT only
. Gear Gravity extension
. Direct law, no pitch/rudder trim: smooth flying required
Aircraft Gross Weight and CG, how is it computed?
• Before engine start:
- FMGC computes GW and Cg
• After engine start:
- FCMC computes GW and Cg displayed on ECAM SD
- FE computes GW and CG for ECAM warnings
Flap Load Relief System
• FLRS is activated when IAS reaches VFE with Flaps at 2,3 or FULL:
- Flaps automatically retract to next retracted lever position
- PFD VFE displayed remains in accordance with lever position
- “RELIEF” displayed on E/WD Flap/Slat indication
- When IAS decreases below VFE, Flaps extend back
Automatic Retract system
• ARS is activated in Conf 1+F when IAS reaches 200 kts:
- Flaps are automatically retracted to 0
- PFD VFE displayed change from 215 to 240 kts
- If IAS decreases below 200kt, flaps will not extend back to 1+F
Alpha Lock
• Slats Alpha Lock prevent high AOA, low speed slat retraction:
- Flap lever moved from 1 to 0
“A. LOCK” pulses on E/WD Slat indication
- When AOA and speed are normal, Slats retract to 0
• If Alpha Lock function is triggered, accelerate to allow slats retraction.
Air Conditioning, describe the system
- The A330 is separated into 4 different zones
- 1 zone Controller regulates the temperature of each zone by ordering air flow from:
- The Packs via the Pack flow control valve for cold air
- The Trim air valves in each zone duct for hot air
- The Packs and 2 recycling cabin fans supply air to a Mixing Unit.
- The Mixing Unit and the Trim air valve supply each zone.
ADR/IR, what information do they provide
• ADR (Air Data Reference):
- Barometric altitude
- Airspeed
- Mach
- AOA
- Temperature
- Overspeed warnings
• IR (Inertial Reference):
- Attitude
- Flight path vector
- Track
- Heading
- Accelerations
- Angular rates
- Ground speed
- Position
MORA displayed on ND, what terrain does it cover
MORA displayed on ND is the highest MORA value within a circle of 40 nm radius around the aircraft.
Nav Back-Up mode, how do you modify the Flight Plan
• FM NAV data base is lost
• Available revisions : ‐ WPT insertion/deletion ‐ OVERFLY insertion/deletion ‐ DIR TO ‐ CLR waypoints/discontinuities
• Waypoint identification:
- 3 letters (PUD) only if present in the MCDU active F-PLN
- LAT/LONG, IDENT/LAT/LONG coordinates
One Engine Inoperative, Autopilot and Flight Director bank angle limits during takeoff and approach phases
- Speed below maneuvering Speed (F,S,GD) -10 kt : 15°
- Speed above maneuvering speed -3 kt : 25°
- Linear increase from 15 to 25° with speed increasing from maneuvering - 10kt to -3 kt
1 Engine Fails during Climb above ACC ALT, what speed is managed by the FMGEC
• BELOW EO REC MAX
Green Dot: Speed change is gradual to prevent a thrust reduction
• ABOVE EO REC MAX
Engine-Out Long Range Cruise speed at EO REC MAX: Speed change is gradual to prevent a thrust reduction
Basic modes of the EGPWS
- EGPWS generates aural and visual warnings below 2 450ft RA (RA, means EGPWS is available in Cruise)
- 5 basic modes:
- Excessive descent rate: “SINK RATE” “PULL UP”
- Excessive terrain closure rate: “TERRAIN” “PULL UP”
- Altitude loss in take off or Go Around: “DON’T SINK”
- Unsafe terrain clearance: “TOO LOW TERRAIN”, “TOO LOW GEAR”, “TOO LOW FLAPS”
- Excessive deviation below Glide : “GLIDESLOPE”
SRS mode, During Take Off Speed/Pitch target computed by FMGC
• Speed:
- AEO, V2+10
- OEI, IAS at the time of failure (mini V2, maxi V2+15)
• Pitch:
- AEO:
. Pitch to fly V2+10 limited to a maximum of 17.5°
. Pitch to achieve a minimum 0.5º climb gradient limited to 22.5°
SRS mode, During Go Around, Speed target computed by FMGC
• Max of VLS, VAPP, IAS at time of Go Around limited to:
- AEO, VAPP + 25
- OEI, V2 + 15
