Delta A320 > S-LOD > Flashcards

S-LOD Flashcards

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1
Q

[Aircraft General] ACGEN_002 — TAXIING Recall the minimum theoretical pavement width for a 180-degree turn.

A
  • 75 feet.
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2
Q

[Aircraft General] ACGEN_003 — TAXIING Describe the relationship of the wingtip, tail, and nose during a turn.

A
  • The wingtip and tail swing the largest arc, followed by the nose. Therefore, the wingtip and tail
    determine the minimum obstruction clearance path during a turn.
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3
Q

[Aircraft General] ACGEN_004 — CABIN SLIDING WINDOWS Recall the location of Cabin Doors, Overwing Emergency Exits and Flight Deck emergency exits.

A
  • There are 4 cabin passenger doors (2 on each side of the cabin), identified as 1L, 1R, 2L, and 2R.
  • Cabin doors are each equipped with an interior and exterior control handle which allow for opening
    and closing from either the interior or exterior of the aircraft.
  • There are 4 overwing emergency exits (2 on each side of the aircraft) which are always armed. When
    the handle cover is removed the SLIDE ARMED light illuminates. When the handle is pulled, the exit
    opens inwards.
  • Two (2) flightdeck sliding windows can be used as emergency exits by the flight crew.
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4
Q

[Aircraft General] ACGEN_006 — DOOR/OXY SD PAGE Describe the DOOR/OXY SD page indications.

A
  • Cabin, Cargo, and Avionics Doors:
    • Green box – door is closed and locked.
    • Solid amber box with label – door is not locked.
    • Amber X – the information is not valid.
  • Overwing Emergency Exits:
    • Green box – exit is closed and locked.
    • Solid amber box with amber EMER EXIT – exit is not locked.
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5
Q

[Aircraft General] ACGEN_007 — DOOR/OXY SD PAGE Recall the DOOR/OXY SD page indications of the emergency escape slides being armed.

A

The word SLIDE (white) appears next to the respective cabin door or overwing exit.

NOTE: Only one emergency escape slide is installed per wing.

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6
Q

[Aircraft General] ACGEN_008 — GENERAL Recall the number of full-face quick-donning oxygen masks on the flight deck.

A
  • There are 4 crew oxygen masks, one at each crewmember seat.
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7
Q

[Aircraft General] ACGEN_010 — OVERHEAD PANEL Explain the controls and indicators on the overhead OXYGEN panel.

A
  • MASK MAN ON pb:
    • AUTO (guarded) – The mask doors open automatically
      when the cabin altitude exceeds 14,000 feet.
    • Pressed (guard lifted) - The oxygen mask doors open.
  • PASSENGER SYS ON light:
    • Illuminates white when control (either automatic or
      manual) for the oxygen mask doors is activated.
  • CREW SUPPLY pb: controls the solenoid valve for low pressure oxygen to the crew masks:
    • ON (light out) – the valve is open; low pressure oxygen is supplied to the crew masks. Normal
      position in flight.
    • OFF (white) – the valve is closed.
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8
Q

[Aircraft General] ACGEN_011 — DOOR/OXY PAGE Recall the crew oxygen system indications on the DOOR/OXY SD page.

A
  • OXY Pressure indication
    • The number is Green when the pressure is ≥ 400 PSI
    • The number is Amber when the pressure is < 400 PSI
  • REGUL LO PR
    • If amber, pressure on the low-pressure circuit (supply line to crew
      oxygen masks) is low.
  • OXY indication: Normally Green. Becomes Amber when:
    • Pressure is below a predetermined value
    • Low oxygen pressure is detected
    • The OXYGEN CREW SUPPLY pb is off
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9
Q

[Aircraft General] ACGEN_012 — CONTROLS AND INDICATIONS Recall the function of each position of the EMER EXIT LT switch.

A
  • ON – Turns on all cabin emergency lights, which include:
    • Overhead emergency lights
    • EXIT signs
    • Proximity emergency escape path marking system
  • OFF – Turns off all cabin emergency lights. The amber
    OFF light comes on.
  • ARM – All cabin emergency lights come on when their normal electrical power is lost.
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10
Q

[Aircraft General] ACGEN_014 — OVERHEAD PANEL Recall the effect on the Cabin EXIT signs when the NO SMOKING switch is placed in the AUTO position:

A
  • Cabin EXIT signs:
    • Illuminate when the landing gear is extended.
    • Extinguish when the landing gear is retracted.
  • NO SMOKING signs are always illuminated, regardless of
    switch position.
    P 87T 3#y
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11
Q

[Air Systems] AIR_002 — OVERHEAD PANEL Recall the function of each position of the X BLEED selector.

A
  • AUTO:
    • Crossbleed valve is open if the APU bleed valve is open.
    • Crossbleed valve is closed if the APU bleed valve is closed.
    • Crossbleed valve closes if an air leak in the wing, pylon, or fuselage (APU)
      is detected.
  • OPEN:
    • Crossbleed valve is open.
  • SHUT:
    • Crossbleed valve is closed.
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12
Q

[Air Systems] AIR_004 — BLEED PAGE Recall the indications of external high pressure air being applied to the pneumatic system.

A
  • With no internal air source being provided (i.e. no APU or engine bleed air), if a PSI value is displayed
    on the left side of the BLEED SD page, by default, the air source must be an external high-pressure air
    cart.
  • The GND indication appears on the ground only, indicating it is possible to connect the high pressure
    ground air supply. It does NOT mean that HP ground air is connected.
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13
Q

[Air Systems] AIR_005 — BLEED PAGE Recall the indications of the Engine Bleed Valves and HP (High Pressure) valves on the ECAM BLEED SD page.

A
  • Engine bleed valves are depicted next to the respective engine’s number (1
    and 2) on the lower portion on the page.
  • HP valves are depicted on the lower portion of the page next to the white HP
    designator.
    NOTE: IP (Intermediate Pressure) check valves are not specifically
    depicted but are represented by a white IP designator.
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14
Q

[Air Systems] AIR_008 — OVERHEAD PANEL, ECAM BLEED PAGE, MEMO DISPLAY Recall the indications when APU bleed air is in use.

A
  • APU bleed valve indicates open on the BLEED SD page.
  • APU BLEED memo is displayed in green on the E/WD.
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15
Q

[Air Systems] AIR_009 — LEAK DETECTION Recall the areas of the aircraft where a bleed air leak can be detected.

A
  • Wings: each wing’s bleed air duct
  • Engine pylons: area from the engine to the respective wing bleed duct
  • Fuselage: area surrounding the APU bleed air duct
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16
Q

[Air Systems] AIR_016 — ECAM COND PAGE Recall which cargo compartment is heated and ventilated and where the temperature of the aft cargo compartment can be monitored.

A
  • Only the aft cargo compartment is temperature controlled, using the controls located on the overhead
    CARGO HEAT panel.
  • Temperature of the aft cargo compartment can be monitored by referencing the COND SD page.
  • Temperature control of the forward cargo compartment is NOT installed.
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17
Q

[Air Systems] AIR_017 — GENERAL ECAM CAB PRESS PAGE Recall how many Cabin Pressure Controllers (CPCs) are installed and where the active system is displayed.

A
  • There are two Cabin Pressure Controllers (CPC) installed.
  • Designated as SYS 1 and SYS 2, the active system appears in green on the CAB PRESS SD page.
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18
Q

[Air Systems] AIR_019 — OVERHEAD PANEL AUTOMATIC OPERATION Describe the function of the LDG ELEV selector.

A
  • AUTO position:
    • The pressurization system uses FMGS data, including landing field elevation, to
      create an optimized pressure schedule.
  • Other positions:
    • Landing field elevation is set manually.
    • Used when both FMGCs have failed, when landing airport is not in the FMS
      database, or FMGS data is not available.
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19
Q

[Air Systems] AIR_020 — OVERHEAD PANEL ECAM CRUISE PAGE ECAM CAB PRESS PAGE Describe the function of the manual pressurization controls.

A
  • MODE SEL pb:
    • Selecting MAN (white light on) enables the use of the MAN V/S CTL toggle switch to manually
      control the outflow valve.
    • Allows manual control of pressurization.
  • MAN V/S CTL toggle switch with the MODE SEL pb in MAN:
    • UP commands the outflow valve open, reducing cabin pressure – increasing cabin altitude.
    • DN commands the outflow valve closed, increasing cabin pressure – decreasing cabin altitude.
      NOTE: Pressurization system performance can be monitored on either the CAB PRESS or CRUISE
      SD page.
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20
Q

[Air Systems] AIR_022 — 21-20-30 DITCHING 21-20-10 GENERAL Describe the function of the DITCHING pb.

A
  • Placing the DITCHING pb to ON commands the following openings to close:
    • Outflow valve
    • Emergency Ram Air Inlet
    • Avionics ventilation inlet and extract valves
    • Pack flow control valves
      NOTE: Each valve listed above is located below the aircraft’s flotation line.
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21
Q

[Ice and Rain Protection] ICE_001 — DESCRIPTION DESCRIPTION Recall which areas of the wings and engines receive ice protection.

A
  • Wings – three outboard slats (Slats 3, 4, and 5).
  • Engines – engine nacelle leading edge.
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22
Q

[Ice and Rain Protection] ICE_005 — OVERHEAD PANEL MEMO DISPLAY Describe the indications and actions when engine anti-ice is selected ON.

A
  • ON (blue) illuminates on the respective ENG 1(2) pb.
  • Continuous Ignition is automatically selected.
  • ENG A.ICE and IGNITION (green) appear on the ECAM memo section.
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23
Q

[Ice and Rain Protection] ICE_006 — OVERHEAD PANEL MEMO DISPLAY Describe the indications when wing anti-ice is selected ON.

A
  • ON (blue) illuminates on the WING pb.
  • WING A. ICE (green) appears on the ECAM memo section.
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24
Q

[Ice and Rain Protection] ICE_009 — OVERHEAD PANEL OVERHEAD PANEL Recall the meaning of the amber FAULT light in the WING and ENG 1(2) ANTI ICE pbs.

A
  • Appears briefly as the valves transit.
  • Represents disagreement between the selected position and actual valve position.
  • The FAULT light on the WING pb also indicates low bleed air pressure is being detected.
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25
[Ice and Rain Protection] ICE_010 — OVERHEAD PANEL Recall the operation of the PROBE/WINDOW HEAT pb.
- AUTO (light out) - On the ground, with at least one engine running, all probes and windows are heated, except TAT probes, which are not heated until in flight. - In flight, all probes and windows are heated. - ON - Light illuminates blue. - All probes and windows are heated permanently, except TAT probes, which are only heated in flight.
26
[Auto Flight] AUTO_006 — FMA DISPLAY Recall the organization of the Flight Mode Annunciator (FMA).
- Column 1: autothrust modes and messages - Column 2: auto flight vertical mode - Column 3: auto flight lateral mode - Column 4: approach capabilities and minimums - Column 5: auto flight status
27
[Auto Flight] AUTO_007 — A/THR Explain the color convention of FMA annunciations.
- Green – engaged mode - Blue – armed mode - Magenta – altitude constraints (if vertical path includes a level segment). - White – approach capabilities, certain autothrust modes, and auto flight system status. - Amber – thrust and/or flight control system caution messages. - Red – significant flight control system degradation.
28
[Auto Flight] AUTO_008 — AP-A/THR CONTROL AREA MANUAL DISENGAGEMENT Recall how to engage and disengage the autopilot.
- To engage: select either the AP1 or AP2 pb on the Flight Control Unit (FCU). - To disengage: - Press the autopilot disconnect pb on either sidestick (preferred method). - Select the illuminated AP1or AP2 pb on the FCU. - Displace either sidestick or rudder pedals.
29
[Auto Flight] AUTO_009 — Recall the autopilot related indications displayed on the top line of column 5 of the FMA.
- With autopilot disengaged: line 1 will be blank. - Autopilot 1 engaged: AP1 - Autopilot 2 engaged: AP2 - Both Autopilots engaged: AP1+2
30
[Auto Flight] AUTO_010 — AUTOMATIC ENGAGEMENT MANUAL ENGAGEMENT CONTROL PANEL ENGAGEMENT Recall how to engage and disengage the flight directors.
- The Flight Director system is automatically engaged (powered) when electrical power is established on the aircraft. - A respective FD pb, located on each Electronic Flight Instrument System (EFIS) control panel, can be used to manually engage or disengage its respective FD. - A green light within the pb indicates that the respective FD is engaged.
31
[Auto Flight] AUTO_011 — DISENGAGEMENT ANNUNCIATION Recall the various Flight Director indications on the second line of column 5 of the FMA.
- Both Flight Directors OFF: the second line will be blank. - Both Flight Directors ON: 1FD2 will be displayed. - CA’s Flight Director selected OFF; FO’s is ON: -FD2 will be displayed. - FO’s Flight Director selected OFF; CA’s is ON: 1FD- will be displayed. - If FMGC 1 or FD1 has failed: 2FD2 is displayed. - If FMGC 2 or FD 2 has failed: 1FD1 is displayed.
32
[Auto Flight] AUTO_012 — A/THR (ARMED) A/THR (ACTIVATED) GENERAL MANFLXXX MANTOGA A/THR ACTIVATION THRUST LEVERS A/THR ARMING Describe the FMA and FCU indications of the Autothrust System.
- OFF (DISCONNECTED): - FMA Column 1 and the bottom row of Column 5 are blank - A/TH pb on FCU is extinguished. NOTE: Engine thrust is controlled by manually positioning the thrust levers. - ARMED: - MAN FLX or MAN TOGA appears in column 1 and A/THR in blue in column 5 of the FMA. - Engine thrust corresponds to thrust lever position of FLX or TOGA . NOTE: Inflight, when thrust levers are placed in the TOGA detent, TOGA thrust is provided and, if in CONF 1 or greater, the go-around phase activated. MAN TOGA appears in column 1 and A/TH in blue in column 5 of the FMA. - ACTIVE: - FMA column 1 displays the current mode, and the bottom row of Column 5 displays A/THR (white).  The active range for two engine operation is any position between the CLB detent and just above the idle detent.  During single engine operation, the active range increases to include the MCT detent. - When Active, autothrust can automatically change from one mode to another to meet vertical path requirements. NOTE: Regardless of mode, the thrust levers never automatically move. The pilot must always reference the FMA for awareness of the autothrust system’s operating mode.
33
[Auto Flight] AUTO_013 — A/THR ARMING A/THR ACTIVATION A/THR DISCONNECTION Explain how the Autothrust System is normally armed, activated, and disconnected.
- Armed: - The system is normally armed at takeoff when the thrust levers are placed in either the FLX or TOGA detent when both engines are running. - Activated: - The system is normally activated when the thrust levers are moved to the CLB detent when the A/THR is armed. - Disconnected (Turned Off): - The system is normally disconnected by bringing the thrust levers to the idle detent at touch down. - Pressing the Instinctive Disconnect pb on either thrust lever. - Pressing the illuminated A/THR pb on the FCU panel.
34
[Auto Flight] AUTO_016 — GENERAL Explain the difference between the Thrust mode and Speed/Mach mode.
- Thrust Mode: - A specific thrust level is maintained, and the target airspeed is achieved through pitch changes. - Used during climbs and descents when no specific rate is required. - Speed/Mach Mode: - Thrust output varies to maintain the target airspeed or mach. - Used during level flight, or during climbs/descents when a specific rate must be maintained.
35
[Auto Flight] AUTO_017 — THRUST MODE GENERAL SPEED/MACH MODE Recall the FMA column 1 indications of Thrust mode and Speed/Mach mode.
- Thrust Mode: - MAN TOGA, MAN FLX, MCT, THR CLB, THR IDLE - Speed/Mach Mode: - SPEED or MACH
36
[Auto Flight] AUTO_018 — SPEED/MACH MODE Recall the Autothrust System’s default operating mode with Autopilots and Flight Directors off.
- Defaults to Speed/Mach mode.
37
[Auto Flight] AUTO_019 — ALPHA FLOOR ALPHA-FLOOR PROTECTION Explain the autothrust Alpha Floor feature.
- Commands automatic application of TOGA thrust. - Is available in Normal Law from lift-off down to 100ft RA. - Functions regardless of thrust lever position or autothrust status. - If off, autothrust will self-activate.  Aircraft must be in Normal Law with a functional autothrust system. - Once the condition causing Alpha Floor is resolved, thrust remains at TOGA (TOGA LK) until pilot intervention.
38
[Auto Flight] AUTO_020 — ALPHA FLOOR Recall the indications associated with Alpha Floor.
- A. FLOOR (green) surrounded by an amber box in column 1 of the FMA. - A. FLOOR (amber) above the N1 displays on the E/WD. - Engine thrust automatically accelerates to TOGA. - Once the condition which caused Alpha Floor no longer exists: - TOGA Lock engages. - TOGA LK (green) replaces the A. FLOOR indications on FMA.
39
[Auto Flight] AUTO_022-1 — GENERAL PHILOSOPHY VERTICAL CONTROL AREA ENGAGEMENT CONDITIONS GENERAL Describe SELECTED guidance of the Auto Flight System.
- Pulling the SPD/MACH knob selects a specific target airspeed. - Pulling the HDG/TRK knob selects a specific heading. - Pulling the altitude knob engages an open climb or open descent. - Pulling the V/S / FPA knob selects a specific vertical speed or flight path angle climb or descent. NOTE: SELECTED guidance always takes priority over MANAGED guidance.
40
[Auto Flight] AUTO_022-2 — GENERAL PHILOSOPHY VERTICAL CONTROL AREA Describe MANAGED guidance of the Auto Flight System.
- Allows the auto flight system to follow commands generated by the FMS. - Auto flight system complies with the lateral, vertical and target airspeed profiles defined by the FMGCs and constraints entered by the pilot. - MANAGED guidance is engaged or armed by momentarily pushing the respective knob on the FCU: NOTE: Pushing the V/S / FPA knob does not result in activating a MANAGED mode. This action would result in the aircraft immediately leveling off (V/S 0).
41
[Auto Flight] AUTO_023 — FMA DISPLAY 30 DISENGAGEMENT CONDITIONS INDICATORS Explain what a momentary flashing white box indicates within an FMA column.
- It indicates a new annunciation/recent change in the respective column. NOTE: In addition to a white box, a triple click aural warning is provided whenever there is an automatic disengagement of a managed Lateral or Vertical mode of the FMGS. This is referred to as a “Mode Reversion”.
42
[Auto Flight] AUTO_024-2 — 20-ENGAGEMENT CONDITIONS 20-ENGAGEMENT CONDITIONS Recall when SRS (Speed Reference System) becomes active.
- At takeoff when thrust levers are placed in either FLX or TOGA. - During a go-around when the thrust levers are placed in TOGA and CONF 1 (Flaps 1) or greater has been selected
43
[Auto Flight] AUTO_028 — CHARACTERISTIC SPEEDS AIRSPEED GENERAL Describe VLS and its relationship with the Autothrust System.
- VLS is defined as the “Lowest Selectable Speed”. It is an airspeed calculated by the FACs based on aircraft gross weight and configuration. - It is intended to advise the pilot of the lowest airspeed that should be selected in the current configuration. NOTE: The pilot can select an airspeed below VLS. - VLS is displayed on the airspeed indicator with an amber hook at the top of the amber strip. It is displayed regardless of Flight Control Law or the status of autothrust. NOTE: The position of the amber hook is not fixed and will adjust as the result of changes to aircraft configuration (flaps, spoilers, and landing gear). - When autothrust is active and the aircraft is in Normal Law, thrust will automatically increase to prevent the airspeed from decreasing below VLS. The pilot selected airspeed, if lower than VLS, will be ignored.
44
[Communications] COMM_002 — FLIGHT INTERPHONE INTRODUCTION INTRODUCTION Describe the Flight, Cabin, and Service Interphone systems.
- Flight Interphone System - INT - Permits communication between members of the flight deck, and also between the flight deck and personnel at the External Power Panel near the nose gear: - Requires the use of the INT (Transmission key & Reception knob) controls on the Audio Control Panel (ACP). - Cabin Interphone System - CAB - Permits communication between the flight deck and cabin. - Requires the use of the CAB (Transmission key & Reception knob) controls on the Audio Control Panel (ACP). - Service Interphone System - CAB - Permits communication between the flight deck and exterior Service Interphone Jacks (excluding the External Power Panel near the nose gear.) - Requires the use of the CAB (Transmission key & Reception knob) controls on the Audio Control Panel (ACP).
45
[Communications] COMM_003-1 — RADIO MANAGEMENT PANEL UTILIZATION DESCRIPTION Recall the purpose of the Radio Management Panels (RMPs).
- Used to select and tune all communication radios, SELCAL and standby navigation radios.
46
[Communications] COMM_003-2 — AUDIO MANAGEMENT SYSTEM AUDIO CONTROL PANEL UTILIZATION Recall the purpose of the Audio Control Panels (ACPs).
- Selection of radios and interphone system for transmission and reception - Control of reception volume - Transmission on the Passenger (Public) Address (PA) system
47
[Communications] COMM_003-3 — AUDIO CONTROL PANEL Recall the function of each position of the INT/RAD switch.
- INT – allows hands-free (“hot mic”) transmission on only the Flight Interphone system through a headset boom or oxygen mask microphone. Remains in the INT position until moved. - Off (Neutral) – the switch is in the off position. - RAD (Spring-Loaded) – allows push-to-talk transmission for the selected transmission key through a headset boom or oxygen mask microphone. Must be held in position. When released, returns to the off position.
48
[Communications] COMM_004 — AUDIO SWITCHING Recall the function of the AUDIO SWITCHING selector.
- Permits selection of ACP 3 by either pilot in the event their respective ACP has failed. - When CAPT 3 or F/O 3 has been selected, “AUDIO 3 XFRD” appears on the memo section of the E/WD. NOTE: Use of ACP 3 does not affect either RMP’s operation
49
[Communications] COMM_005 — AUDIO CONTROL PANEL Recall the indications when receiving a transmission from SELCAL, Ground Crew, or Cabin Crew.
- SELCAL: - CALL flashes in amber in the respective transmission keys (HF 1/2). - Buzzer sounds on flightdeck. - Ground Crew: Call from ground crew at the External Power Panel to flight deck. - MECH flashes in amber in the INT transmission key. - Buzzer sounds on flight deck. - Cabin Crew: - ATT flashes in amber within the CAB transmission keys. - Buzzer sound on the flightdeck. NOTE: Pressing the RESET key on the ACP will extinguish a flashing CALL, MECH, or ATT light.
50
[Communications] COMM_006 — AUDIO MANAGEMENT SYSTEM STOWAGE BOX Recall how many flight deck oxygen mask microphones are available, and how they are de-activated.
- Oxygen mask microphones are available only for the Captain’s, First Officer’s, and 3rd occupant’s oxygen masks. - De-activation/Cut Off: - Occurs by closing the respective compartment’s left-hand door, and then pressing the RESET/TEST control slide. This cuts off the oxygen and the mask microphone.
51
[Communications] COMM_007 — DESCRIPTION CONTROLS AND INDICATORS Describe the two methods of making a Passenger (Public) Announcement (PA).
- Using the handset mounted at rear of the center pedestal. - Pressing and holding the PA transmission key on the ACP, and speaking into a headset boom or oxygen mask microphone.
52
[Communications] COMM_008 — CABIN CALL SYSTEM GROUND MECHANIC CALL SYSTEM Explain the controls on the overhead CALLS panel.
- ATTND ADV pb: not used by DAL - MECH pb: - COCKPIT CALL light illuminates on the external power panel near the nose gear. - External horn sounds at the nose of the aircraft. - FWD pb: - High/low chime sounds at the forward section of the cabin and CAPTAIN CALL appears at the forward Flight Attendant Indication Panel. - AFT pb: - High/low chime sounds at the aft section of the cabin and CAPTAIN CALL appears at the aft Flight Attendant Indication Panel. - EMER pb: - ON in white and CALL in amber flash within the pb. - High/Low chime sounds three times throughout the cabin. - EMERGENCY CALL appears on all Flight Attendant Indication Panels.
53
[Communications] COMM_009 — CONTROLS AND INDICATORS Explain the function of the controls on the RCDR panel.
- GND CTL pb: - ON (blue) - Cockpit Voice Recorder (CVR) and Digital Flight Data Recorder (DFDR) are actively recording. - AUTO (lights out) - the CVR & DFDR automatically start recording with first engine start. After engine start, the ON light goes out automatically. - CVR ERASE button - Erases the CVR tape if the button is pressed for a brief time provided: - Aircraft is on the ground. - Parking brake is on. - CVR TEST button - Tests the CVR when the following conditions are met: - GND CTL pb is selected ON. - Parking brake is set. NOTE: a Low frequency tone is heard through the flight deck loudspeaker indicationg a successful test.
54
[Electrical] ELEC_002 — GENERAL DSC 24-10-20-AC GENERATORS IN FLIGHT FAILURE OF AC BUS 1 Recall the power sources for the AC Buses during normal operating conditions.
- AC Buses 1 & 2: - Respective Engine Generator (IDG 1 or 2). - External power. - APU generator. - AC ESS Bus: - Normally powered by AC Bus 1. - AC Bus 2 manually, when AC ESS FEED pb is selected to ALTN. - AC Bus 2 automatically, via the auto switching logic.
55
[Electrical] ELEC_003 — GENERAL OVERHEAD PANEL Describe the electrical system’s power priority with the BUS TIE pb in AUTO (light out).
- 1st Respective engine generator, GEN 1 OR GEN 2 - 2nd External power (If selected ON) - 3rd APU generator - 4th Opposite engine generator
56
[Electrical] ELEC_004 — OVERHEAD PANEL GENERAL Recall the functions of the BUS TIE pb.
- Two bus tie contactors automatically open or close to maintain power to both AC BUS 1 and 2, maintaining power priority logic. - AUTO (light out) – One or both contactors close depending on the electrical configuration. - OFF – Both bus tie contactors are open.  AC Bus 1 and 2 can only be powered by their respective engine generator.
57
[Electrical] ELEC_005 — FAILURE OF AC BUS 1 OVERHEAD PANEL Recall the purpose of the AC ESS FEED pb.
- The AC ESS FEED pb is used to manually command AC Bus 2 to power the AC ESS Bus. - When in the “light out” normal configuration: - AC Bus 1 powers AC ESS Bus. This the normal configuration. - If AC Bus 1 fails, AC Bus 2 automatically powers AC ESS BUS. - When selected to ALTN: - AC Bus 2 is commanded to power AC ESS Bus regardless of the status of AC Bus 1. - ALTN appears only when the pb is selected.
58
[Electrical] ELEC_007 — ELEC PAGE Explain the information displayed on the ECAM ELEC SD page.
- GEN 1, GEN 2, and APU GEN: - Load (percentage of output) - Voltage - Frequency - EXT PWR: - Voltage - Frequency NOTE: The EXT PWR indication appears whenever external power is available. Voltage and Frequencies appear in green when normal.
59
[Electrical] ELEC_008 — ELEC PAGE Recall the display on the ECAM ELEC SD page of a shed (unpowered) AC or DC ESS SHED Bus.
- The word SHED (amber) appears under AC ESS or DC ESS buses when the respective SHED Bus has automatically shed. - AC and DC ESS SHED busses do not appear on the ELEC SD page when they are powered.
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[Electrical] ELEC_009 — ELEC PAGE FAILURE OF ONE ENGINE GENERATOR OVERHEAD PANEL Explain the meaning of GALLEY SHED on the ECAM ELEC SD page and function of the GALLEY pb on the Overhead Panel.
- In flight, with one generator operating, GALLEY SHED indicates that the main galley has shed. However, the secondary galley remains powered unless the Galley pb is selected OFF. NOTE: On the ground, with one engine running and the APU GEN available, all galleys remain powered. - When the GALLEY pb is selected OFF, GALLEY SHED indicates that the main and secondary galleys are not supplied (not powered).
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[Electrical] ELEC_010 — OVERHEAD PANEL Recall the cautions associated with selecting the guarded IDG 1 and IDG 2 pbs.
- To avoid damage to the IDG disconnect mechanism DO NOT: - Disconnect unless the engine is running or windmilling. - Push the pb(s) for more than three (3) seconds.
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[Electrical] ELEC_011 — CIRCUIT BREAKERS (C/BS) Explain the color-coding of the circuit breakers.
- Green: - Circuit breaker is monitored. - C/B TRIPPED message appears on ECAM when CB is out for more than 1 minute. - Black: - Circuit breaker is not monitored, therefore no “C/B TRIPPED” message is generated. - The system which the circuit breaker supports may be monitored by the FWCs and generate a message. - Yellow: - Must be pulled when flying on batteries only. - Red: - The Wing Tip Brake (WTB) circuit breakers have red caps to prevent them from being reset.
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[Electrical] ELEC_012 — OVERHEAD PANEL (CONT’D) SMOKE CONFIGURATION Recall how Generator 1 is affected when the GEN 1 LINE pb is selected OFF.
- Generator 1 line contactor opens, isolating it from the rest of the aircraft’s electrical system. - AC BUS 1 is powered from GEN 2. - Generator 1 still powers one fuel pump in each wing tank.
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[Electrical] ELEC_013 — GENERAL EMERGENCY GENERATION AFTER LOSS OF ALL MAIN GENERATORS OVERHEAD PANEL (CONT’D) Describe the two methods of activating the emergency generator.
- Automatically: - Loss of power to AC Bus 1 and 2 in flight (speed greater than 100kts) will automatically deploy the Ram Air Turbine (RAT) and activate the emergency generator. - Manually: - Selecting the red guarded MAN ON pb on the EMER ELEC PWR panel will manually deploy the Ram Air Turbine (RAT) and activate the emergency generator. NOTE: Selecting the RAT MAN ON pb on the HYD panel will deploy the RAT but will not activate the emergency generator.
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[Electrical] ELEC_014 — EMERGENCY GENERATION AFTER LOSS OF ALL MAIN GENERATORS OVERHEAD PANEL (CONT’D) Explain the configuration called “Emergency Generation After Loss of All Main Generators”.
- It means that AC Buses 1 and 2 are unpowered and the Emergency Generator is powering: - AC ESS Bus - DC ESS Bus, through the ESS TR - AC and DC ESS SHED buses through their ESS Buses NOTE: The ECAM message for this configuration is: ELEC EMER CONFIG NOTE: A red FAULT light illuminates on the EMER ELEC PWR panel when AC Buses 1 and 2 are unpowered and the RAT is deployed but the emergency generator is not supplying power.
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[Electrical] ELEC_015 — EMERGENCY GENERATION AFTER LOSS OF ALL MAIN GENERATORS OVERHEAD PANEL (CONT’D) Explain what occurs to the emergency generator when the landing gear is lowered on the A320.
- The emergency generator is automatically deactivated, and the aircraft batteries become the sole source of electrical power. NOTE: A red FAULT light illuminates on the EMER ELEC PWR panel when AC Buses 1 and 2 are unpowered and the RAT is deployed but the emergency generator is not supplying power. #y
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[Engines/APU] ENG_004 — DISPLAY OVERHEAD PANEL APU PAGE DISPLAY Recall the indications when the APU can supply electrical power and bleed air to the aircraft systems (“on speed”).
- AVAIL appears (in green) on the: - APU START pb - APU SD page - APU AVAIL appears in ECAM Memo Display - APU BLEED appears in ECAM Memo Display if: - The APU is available, and - The APU BLEED pb is ON.
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[Engines/APU] ENG_005 — OVERHEAD PANEL Recall the indications of the APU MASTER SW pb.
- Light out – The APU is off or in the shutdown sequence. NOTE: When pressed, initiates APU operation and ON light illuminates. - ON - The APU is in the starting sequence or is operating. NOTE: Selecting the APU MASTER SW to OFF (light out) will accomplish a normal shutdown sequence. - FAULT– an automatic shutdown has occurred.
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[Engines/APU] ENG_007 — GENERAL OVERHEAD PANEL APU PAGE Recall the function of the APU BLEED pb and APU GEN pb.
- APU BLEED pb: - ON – commands the APU bleed valve open. APU bleed air supplies the pneumatic system. Opens the crossbleed valve and closes the engine bleed automatically. The APU bleed air valve on the ECAM APU SD shows Inline Green – not closed. - APU GEN pb: - Light out – APU generator will automatically energize once the APU is available (on speed) and will connect to the electrical system automatically. This is the normal position. - OFF light illuminated - APU generator is de-energized and not able to supply power.
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[Engines/APU] ENG_008 — GENERAL Recall the uses of APU bleed air.
- APU bleed air can be used for: - Engine starts: on the ground and in flight - Air conditioning system: on the ground and in flight - During takeoff it can supply bleed air for air conditioning, when optimum aircraft performance is required.
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[Engines/APU] ENG_015 — CONTINUOUS IGNITION MEMO DISPLAY Recall how Continuous Ignition can be manually activated.
- Following an engine start, cycle the ENG MODE selector from NORM back to IGN/START. NOTE: appears in the memo section of the E/WD whenever continuous ignition is active. This is the only indication that the system is active.
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[Engines/APU] ENG_017 — ENG SD PAGE IGNITION FOR STARTING Recall the engine igniter displays on the ECAM ENGINE SD page.
- Engine igniters are displayed as A and B. - During engine start, A or B appears at the lower portion of the ECAM ENGINE SD page, indicating the active igniter. - AB indicates that both igniters are being used for that engine’s start, or continuous ignition is active. NOTE: The FADEC automatically alternates which igniter is used with each start. For example, if igniter A was used for the first start, igniter B would be used for the next start on the same engine.
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[Engines/APU] ENG_019 — E/WD Recall the E/WD N1 gauge’s indications.
NOTE: slight variations are possible depending on the aircraft variant. - Green – current N1 in normal range, displayed numerically and as a green line. - Amber tick mark – N1 Limit. - Red – N1 Red Limit (beginning of Red Line), N1 Exceedance (the highest NI value reached) and N1 Red Line (between the N1 red limit and end of the scale.) - Circle – current thrust lever position. - Transient N1 - the 4 green arcs indicate the difference between the N1 command and the current N1, when the A/THR is active. - Green REV – the thrust reverser system is fully deployed. - Amber REV – the thrust reverser system is unlocked, but not fully deployed.
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[Engines/APU] ENG_020 — E/WD Recall the meaning of the grey box on the N2 display on the E/WD.
- An engine start sequence is in progress. It will disappear once the start sequence is complete.
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[Engines/APU] ENG_021 — AUTOMATIC STARTING SEQUENCE ENG MODE SELECTOR AND ENG MASTER LEVERS Recall the functions of the controls and indicators on the ENG panel.
- ENG MASTER 1(2) switches (levers): - ON – initiates the automatic start sequence when ENG MODE selector is set to IGN/START. - OFF – shuts down the engine or aborts the start sequence. - ENG MODE selector: - NORM – normal mode of operation following engine start. - IGN/START – selected prior to all engine starts:  Displays the ENG SD page  Activates FADEC and all engine parameters become available to view on ENG SD  Commands both pack valves to close  Following an engine start, continuous ignition is activated when cycled from the NORM position - CRANK – selected to Dry Crank / Ventilate an engine after an aborted start.  Displays the ENG SD page  Activates FADEC and all engine parameters become available to view on ENG SD - FIRE – illuminates when an engine fire has been detected. - FAULT – illuminates when: - Automatic start has been aborted (FADEC start fault) - The position of the HP fuel shutoff valve is abnormal NOTE: There is no relationship between the FIRE and FAULT indications. They are separate indications.
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[Engines/APU] ENG_022 — MANUAL STARTING ENG MAN START PANEL ENGINE VENTILATION Explain what occurs when an ENG MAN START pb is selected ON.
- If the ENG MODE selector is in IGN/START: - The manual start sequence is initiated and FADEC opens the respective engine start valve. - If the ENG MOD selector is set to CRANK: - The dry crank process is initiated and FADEC opens the respective engine start valve.
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[Engines/APU] ENG_023 — IGNITION FOR STARTING Describe igniter behavior during automatic versus manual starts on the ground.
- Automatic starts – engine igniters alternate between starts (A or B.) - The FADEC automatically controls the ignition. NOTE: FADEC automatically alternates which igniter is used with each automatic start. For example, if igniter A was used for the first start, then igniter B would be used for the next start. - Manual starts – both igniters are activated (AB) only after the ENG MASTER lever (switch) has been selected on. #y
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[Fire Protection] FIRE_005 — EXTINGUISHING FIRE EXTINGUISHING Recall the number of fire extinguisher bottles available for each engine, the APU, and the cargo compartments.
- Each engine has 2 fire extinguisher bottles. - The APU has 1 fire extinguisher bottle. - The Forward and Aft cargo compartments share 1 fire extinguisher bottle.
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[Fire Protection] FIRE_004 — EXTINGUISHING Describe the APU’s automatic fire protection function.
- When an APU fire is detected on the ground, the APU automatically shuts down, and the extinguisher bottle discharges automatically. NOTE: APU automatic shutdown and fire bottle discharge due to a fire is only available when the aircraft is on the ground.
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[Fire Protection] FIRE_014 — SMOKE DETECTION Recall the type of smoke detection available in the avionics compartment.
- The avionics compartment is equipped with one smoke detector, which only senses particulates. - Heat/temperature sensing is not available and there are no cockpit temperature indications.
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[Fire Protection] FIRE_009 — ECAM COND PAGE Recall where the Aft Cargo compartment’s temperature is displayed and can be monitored.
- Aft Cargo compartment temperature is displayed and can be monitored from the ECAM COND SD page:
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[Fire Protection] FIRE_011 — EXTERNAL POWER PANEL EMER ELEC PWR PANEL Recall the exterior aircraft indications of an APU fire on the ground.
- External warning horn sounds. - Red APU FIRE light illuminates on the External Power Panel.
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[Flight Controls] FCTRL_002 — COMPUTERS PITCH CONTROL ROLL CONTROL Describe the roles of the Elevator Aileron Computers (ELAC 1 and ELAC 2).
- Provide control of the Elevators, Ailerons, and Trimmable Horizontal Stabilizer (THS). - Determine requirement for and activate spoiler assist during rolls, and rudder input for yaw. - Both ELACs are normally active. ELAC 1 controls roll and ELAC 2 controls pitch. - If one fails, the remaining ELAC automatically assumes all ELAC-related functions.
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[Flight Controls] FCTRL_003 — FLIGHT AUGMENTATION COMPUTER YAW CONTROL RUDDER TRAVEL LIMITATION CHARACTERISTIC SPEEDS GENERAL Describe the roles of the Flight Augmentation Computers (FAC 1 and FAC 2).
- Provide control of the Rudder to include: - Turn coordination - Yaw damping - High/Low speed rudder travel limit - Rudder trim - Compute data for characteristic speeds on the PFD. - Only one FAC is active at a time, with the other serving as a backup.
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[Flight Controls] FCTRL_004 — COMPUTERS PITCH CONTROL Describe the roles of the Spoiler Elevator Computers (SEC 1, SEC 2 and SEC 3).
- SECs are responsible for a specific pair, or pairs, of spoiler panels. - SEC 1 and SEC 2 can provide backup control of the Elevators and THS in the event of a dual ELAC failure.
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[Flight Controls] FCTRL_006 — GENERAL ALTERNATE LAW DIRECT LAW ABNORMAL ATTITUDE LAWS MECHANICAL BACK-UP COMPUTERS Describe the Flight Control Laws.
- Normal Law: - Defines the Flight Control Computers’ logic of the aircraft’s pitch, roll, and yaw limits during normal operations. - All protections are available in order to prevent the aircraft from exceeding its designed flight envelope. Active when all, or nearly all, systems are functioning correctly. - Alternate Law: - Defines the Flight Control Computers’ logic of the aircraft’s pitch, roll, and yaw limits in response to multiple failures involving a Flight Control computer, Hydraulic, or Navigation system/s (ADIRS). - Maintains a high level of capability, though some flight control characteristics change, and some protections are lost. - Direct Law: - Typically occurs as the result of the landing gear lowered while in Alternate Law, but can also be the result of more significant system failures. - Flight control feel and response is like a conventional aircraft due to direct stick-to-elevator relationship, and all protections are lost. - Mechanical Backup Law: - Occurs when all flight control computers have failed or there has been a total loss of electrical power. - Side sticks are inoperative, and the aircraft can only be controlled by manual pitch trim, rudder pedals and engine thrust. - Abnormal Attitude Law: - Provides sufficient control to recover from unusual attitudes as the result of extraordinary external event. - Is a subset of Alternate Law.
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[Flight Controls] FCTRL_008 — FLIGHT MODE Describe Load Factor Demand.
- Available in Normal and Alternate Law. - Flight control computers interpret pitch change commands as G-load changes, or load factor changes: - Climb commands (Stick aft) result in a positive G-Load change - Descent commands (Stick forward) result in negative G-Load change - Neutral stick results in zero G-Load change
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[Flight Controls] FCTRL_009 — FLIGHT MODE Describe Automatic Pitch Trim during a roll.
- Automatic pitch trim is provided by the ELACs in Normal and Alternate Law. - Pitch trim is automatically provided for bank angles up to and including 33 degrees.
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[Flight Controls] FCTRL_010 — PROTECTIONS Describe Load Factor (Maneuver) Protection.
- Available in Normal and Alternate Law. - Restricts flight control surface movement that would cause the aircraft to exceed its designed structural G-load limits, overstressing the aircarft: - Clean configuration (Flaps and Slats retracted): -1.0g to +2.5g - Slats extended, and Flaps retracted: -1.0g to +2.5g - Slats and Flaps extended: 0.0g to +2.0g
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[Flight Controls] FCTRL_011 — PROTECTIONS Describe Pitch Protection.
- Available only in Normal Law. - Prevents excessive nose-up and nose-down attitudes. - ELACs will not allow attitudes greater than 30º nose-up or 15º nose-down, even if the sidestick is held full aft/forward.
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[Flight Controls] FCTRL_012 — PROTECTIONS Describe High Speed Protection.
- Available only in Normal Law. - Attempts to prevent aircraft from exceeding VMO/MMO. - Autopilot automatically disengages when High Speed Protection becomes active. - Flight Control Computers automatically pitch the aircraft up to limit further acceleration, even if the sidestick is held full forward. - Represented by two green bars near VMO (=)
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[Flight Controls] FCTRL_014 — PROTECTIONS AIRSPEED Describe Angle of Attack Protection (Alpha Prot) and its indication on the airspeed indicator.
- Available only in Normal Law. - Flight control computers prevent the aircraft’s angle of attack (AOA) from exceeding a predetermined threshold at low airspeeds. - Autopilot automatically disengages and speed brakes, if deployed, automatically retract. - Flight control computers logic changes from Load Factor Demand to AOA Demand. - Alpha Prot is represented by the position of the top of the amber and black band. - It can be overridden with aft side stick movement.
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[Flight Controls] FCTRL_015 — PROTECTIONS AIRSPEED Describe Alpha Max and its indication on the airspeed indicator.
- Alpha Max is the highest angle of attack (AOA) that the flight control computers will allow: - Available only in Normal Law. - It cannot be overridden by the pilot, even with full aft sidestick pressure. - It is represented by the top of the red band on the airspeed indicator.
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[Flight Controls] FCTRL_017 — BANK ANGLE PROTECTION Describe Bank Angle Hold and Positive Spiral Static Stability.
- Both are only available in Normal Law. - Bank Angle Hold - At commanded bank angles of less than or equal to 33 degrees, the bank angle is maintained with automatic pitch trim when sidestick is released. - Positive Spiral Static Stability - At commanded bank angles of greater than 33 degrees, if the sidestick is released, bank angle returns to and maintains 33 degrees. Continuous pressure must be applied to the sidestick to hold bank angles exceeding 33 degrees as well as pitch.
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[Flight Controls] FCTRL_019 — BANK ANGLE PROTECTION Describe the role of Automatic Pitch Trim during turns.
- Available in Normal and Alternate Law. - At bank angles less than or equal to 33º, the ELACs automatically introduce the necessary back pressure through automatic pitch trim. - At bank angles above 33º, this feature becomes inhibited, and aft sidestick will be necessary to maintain a level turn.
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[Flight Controls] FCTRL_020 — BANK ANGLE PROTECTION Describe Bank Angle Protection.
- Available only in Normal Law. - ELACs restrict bank angle to a maximum of 67º, even if full left or right sidestick is maintained.
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[Flight Controls] FCTRL_021 — ATTITUDE DATA PROTECTIONS BANK ANGLE PROTECTION Recall the indications of Normal Law on the PFD.
- Green equal signs displayed at: - 67º bank angle limit. - +30º and -15º pitch attitude limits. - High speed protection limit.
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[Flight Controls] FCTRL_022 — GENERAL FLIGHT MODE FLARE MODE Describe the 3 modes of Normal Law: Ground, Flight, and Flare (Landing).
- Ground Mode: - Active when aircraft is on the ground. - Direct relationship between the sidesticks and flight control surfaces. - Permits pilot to perform a flight control check and rotate the aircraft on takeoff. - Flight Mode: - Active shortly after takeoff. - All flight control computer protections and flight characteristics take effect. - Flare (Landing) Mode: - Becomes active as the aircraft descends through 50 ft RA, at which point the ELACs “memorize” the aircraft’s pitch attitude. - Beginning at 30 ft RA, the ELACs add a gentle nose down pitch command; approximately 2 degrees nose down over 8 seconds. - Instinctively, the pilot counters this nose-down action with aft sidestick input, resulting in a landing flare maneuver much like a conventional aircraft. - Shortly after landing, the aircraft returns to ground mode, and the THS resets to 0.
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[Flight Controls] FCTRL_025 — ALTERNATE LAW Describe High and Low Speed Stabilities in Alternate Law.
- High Speed Stability: - Becomes active near VMO/MMO - Flight control computers command the elevators to increase the aircraft’s pitch, attempting to prevent an increase in speed. NOTE: High Speed Stability can be overridden by pilot sidestick input from the pilot. - Low Speed Stability: - Becomes active at airspeed slightly higher than stall warning speed. - Flight control computers command the elevators to decrease aircraft’s pitch, attempting to increase airspeed. NOTE: Low Speed Stability can be overridden by sidestick input from the pilot.
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[Flight Controls] FCTRL_029 — DIRECT LAW ATTITUDE DATA GENERAL Recall the indications of Alternate Law and Direct Law.
- The green equal signs on the PFD are replaced with amber Xs in both Alternate and Direct Law. In Alternate Law: - F/CTL ALTN LAW (PROT LOST) message in E/WD memo section. In Direct Law: - F/CTL DIRECT LAW (PROT LOST) message in the E/WD memo section. - USE MAN PITCH TRIM on the PFD.
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[Flight Controls] FCTRL_030 — MECHANICAL BACK-UP Describe Mechanical Backup.
- Provides mechanical control of the aircraft in the event all flight control computers have failed, or there is total electrical failure. - It is intended to be used only for as long as it takes to restore flight control computers or electrical power.
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[Flight Controls] FCTRL_031 — MECHANICAL BACK-UP Recall which flight control surfaces are operational when in Mechanical Backup.
- Rudder - Trimmable Horizontal Stabilizer (THS) - Mechanical (cable) connections to these flight controls permit use only if hydraulic power to the respective servos is available.
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[Flight Controls] FCTRL_032 — MECHANICAL BACK-UP Recall the PFD indications of Mechanical Backup.
- Amber Xs present in Alternate and Direct Law remain. - MAN PITCH TRIM ONLY appears on the PFD. NOTE: PFD displays are only available if electrical power being is available.
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[Flight Controls] FCTRL_033 — ABNORMAL ATTITUDE LAWS Describe Abnormal Attitude Law.
- Ensures flight characteristics and protections associated with Normal Law do not interfere with recovery from an abnormal flight attitude. - After the recovery has been made, abnormal attitude law disengages and the aircraft enters and remains in Alternate Law for the remainder of the flight. NOTE: Law will NOT degrade to Direct Law once the landing gear is extended.
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[Flight Controls] FCTRL_034 — ECAM F/CTL PAGE Describe the Rudder and Rudder Trim displays on the ECAM F/CTL SD page.
- The rudder is depicted in green and represents actual rudder position. - Rudder trim is represented by the cyan (blue) tick mark.
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[Flight Controls] FCTRL_035 — ALPHA/SPEED LOCK FUNCTION (SLATS) ECAM UPPER DISPLAY Recall the meaning of a pulsing A-LOCK (blue) on the E/WD.
- A-LOCK is displayed as an indication that leading-edge slat retraction has been inhibited due to excessively low airspeed or high angle of attack. Only the slats are inhibited; not the flaps. - Once airspeed and/or angle of attack corrections have been made, the slats will respond to flap lever commands and retract, and A-LOCK indication disappears.
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[Flight Controls] FCTRL_036 — GLARESHEILD LATERAL CONSOLES Describe the sidestick priority system.
- The sidestick priority system allows either pilot’s sidestick to have sole control of the aircraft in the event of an opposing sidestick’s failure. - Pressing and holding the autopilot disconnect/sidestick priority pb: - Disengages the autopilot/s, if engaged. - Temporarily deactivates the opposite sidestick. - Generates respective “Priority Left” or “Priority Right” voice message - A red arrow illuminates only on the SIDE STICK PRIORITY indicator of the pilot whose sidestick has been deactivated. - If the deactivated sidestick is sensed not to be in the neutral position, CAPT or F/O (both green) illuminates only on the SIDE STICK PRIORITY indicator of the pilot who has taken priority. - After 40 seconds of pressing the sidestick autopilot disconnect/sidestick priority pb, it may be released, and the opposing sidestick will remain deactivated, until the other pilot presses their sidestick priority pb. NOTE: If both pilots press their sidestick pb, the last pilot to press it will have priority.
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[Flight Controls] FCTRL_037 — LATERAL CONSOLES Explain what occurs when both sidesticks are simultaneously moved.
- “Dual Input” is heard over the flightdeck loudspeakers. - If moved in the same direction:  ELACs will sum their inputs, up to a maximum of one sidestick’s full deflection. - If moved in opposite directions:  ELACs cancels both inputs
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[Flight Controls] FCTRL_038 — 27-20-30-ECAM F/CTL PAGE Describe the indications on the ECAM F/CTL SD page of hydraulic system power sources.
- G indicates controls powered by the Green hydraulic system. - Y indicates controls powered by the Yellow hydraulic system. - B indicates controls powered by the Blue hydraulic system. NOTE: The system’s letter appears in amber if the respective hydraulic system has failed.
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[Flight Controls] FCTRL_039 — 27-20-30-ECAM F/CTL PAGE Describe the indications of the Flight Control Computers on the ECAM F/CTL SD page.
- The two ELACs and the three SECs are depicted. - The respective computer’s number is shown in green when functioning normally. - If a flight control computer fails or has been selected OFF, the computer’s number and the half-box surrounding it both turn amber. NOTE: The two FACs are not depicted on the ECAM F/CTL SD page.
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[Flight Controls] FCTRL_040 — 27-20-30-ECAM F/CTL PAGE Describe the indications of Pitch Trim on the ECAM F/CTL SD page.
- A digital readout for PITCH TRIM is presented on the F/CTL SD page: - It displays the angle of the THS for nose UP or nose DN trimming. - For example:  0.6º UP indicates the THS is set at -0.6º for aircraft nose up trimming.  1.2º DN indicates the THS is set at 1.2º for aircraft nose down trimming. NOTE: Pitch trim must be manually set for takeoff. Once airborne, pitch trim is automatically positioned per Flight Control Computer logic.
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[Flight Controls] FCTRL_044 — ECAM F/CTL PAGE ECAM WHEEL PAGE Recall the methods of monitoring Speed Brake and Ground Spoiler deployment.
- Vertical arrows (green) appear on both ECAM F/CTL and WHEEL SD pages. - On landing, the ground spoilers are monitored on the WHEEL SD page, which is automatically displayed with landing gear extension.
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[Flight Controls] FCTRL_046 — SPEED BRAKES AND GROUND SPOILERS Recall the requirements for automatic Ground Spoilers deployment during landing or rejected takeoff.
- Main gear wheel speed must be at 72 knots or greater. - If the spoilers are ARMED:  Spoilers deploy when both thrust levers are placed to IDLE. - If the spoilers are NOT ARMED:  Spoilers deploy when at least one thrust lever is in the REV range and the other is at IDLE. P 88T 4#y
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[Indicating/Recording Systems] INDREC_001 — INTRODUCTION DSC- 31-05-20 COCKPIT ARRANGEMENT Describe the organization of the Electronic Instrument System (EIS).
- Six identical cathode ray tube Display Units (DUs) in two parts: - Electronic Flight Instrument System (EFIS):  Two Primary Flight Displays (PFDs) – normally displayed on the outboard DU.  Two Navigation Displays (NDs) – normally displayed on the inboard DU. - Electronic Centralized Aircraft Monitor (ECAM):  Engine/Warning Display (E/WD) – normally displayed on the Upper ECAM.  System Display (SD) – normally displayed on the Lower ECAM
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[Indicating/Recording Systems] INDREC_005 — GENERAL ADIRS SCHEMATIC Describe the components of the Air Data Inertial Reference System (ADIRS).
- Three Air Data Inertial Reference Units (ADIRUs), each divided into two parts: - Air Data Reference (ADR) Unit – processes pitot-static information. - Inertial Reference (IR) Unit – processes attitude, positional, and heading data. - ADIRU 1 supplies information to the CA’s PFD and ND. - ADIRU 2 supplies information to the FO’s PFD and ND. - ADIRU 3 serves as a backup.
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[Indicating/Recording Systems] INDREC_006 — GENERAL Describe the general displays of the E/WD.
- Upper Portion: - Engine parameters - N1, N2, EGT and Fuel Flow - Fuel on Board (FOB) - Slat/Flap position - Lower Portion - Bottom left  Normal and non-normal operations, including checklists.  Class 1 ECAM messages – Warning and Caution messages. - Bottom right  Secondary failures  Memos
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[Indicating/Recording Systems] INDREC_008 — CODE Explain the color-coding on the E/WD.
- Green – normal operation. - White – remarks and guidance for procedures. - Blue – ECAM action steps or limitations. - Amber - failure or configuration needing crew awareness, but not immediate action. - Red – a failure or configuration requiring immediate crew action. - Magenta - informational messaging, such as inhibition messages. - Amber XX – information not available.
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[Indicating/Recording Systems] INDREC_009 — RECONFIGURA TION PFDU/NDU RECONFIGURATION Recall the EFIS Display Unit (DU) priority.
- The PFD takes priority over the ND. - If the outer DU is turned off or fails, the PFD automatically transfers to the inner DU.
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[Indicating/Recording Systems] INDREC_010 — FAILURE OF UPPER ECAM DU Recall the ECAM Display Unit (DU) priority.
- The E/WD (upper ECAM display) takes priority over the SD (Lower ECAM display). - If the upper ECAM DU is turned off or fails, the E/WD automatically transfers to the lower ECAM DU.
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[Indicating/Recording Systems] INDREC_011 — EFIS CONTROLS Recall the functions of the ND Brightness Control Knob.
- The Inner knob is used to control the general brightness of the ND symbols and turn it on and off. (Controls brightness of items inside the aircraft) - Rotating this knob all the way counterclockwise turns off the ND. - The Outer knob controls the brightness of these displays: (Controls brightness of items outside the aircraft) - Weather Radar displays - EGPWS Terrain displays
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[Indicating/Recording Systems] INDREC_012 — RECONFIGURING THE DMC Explain the functions of the three Display Management Computers (DMCs).
- The DMCs process signals received from the sensors and computers within the aircraft for display on the DUs. - DMC 1 provides information to the CA’s PFD, ND, and the E/WD. - DMC 2 provides information to the FO’s PFD, ND, and the SD. - DMC 3 serves as a standby/backup to either DMC 1 or DMC 2.
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[Indicating/Recording Systems] INDREC_016 — OF FAILURES PRIMARY AND SECONDARY FAILURE Recall the types of failure messages.
- Independent – A failure that affects an isolated system or item without degrading the performance of others. - Presented in the left column of the E/WD memo section. - Affected system is underlined. Example: – F/CTL, HYD, ELEC - Specific failure follows the affected system. Example: F/CTL ELAC 1 FAULT - Primary – A failure that affects the use of other systems or components: - Presented in the left column of the E/WD memo section as a “Boxed Title”. - Secondary – Systems or components affected as the result of a Primary failure: - Presented in the right column of the E/WD memo section in amber with a * in front of the title.
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[Indicating/Recording Systems] INDREC_019 — HYD PAGE FUEL PAGE BLEED PAGE Describe the indications of pumps and valves on the related Systems Display (SD) pages.
- Pumps – depicted as a square: Inline green – green vertical line indicates the pump is on and pump pressure is normal. Crossline green – green line indicates the pump is off in accordance with automatic logic. Crossline amber – amber line indicates the pump has been manually selected OFF. LO amber – indicates the pump is on, but pump pressure is low. - Valves – depicted as a circle: Inline green – green line connecting to system indicates the valve is open. Crossline green – green line NOT connecting to the system line indicates the valve is closed. Crossline amber – the valve is stuck closed when it is being commanded to open. Inline amber – the valve is stuck open when it has been commanded to close. Diagonal amber – diagonal line indicates that the valve is in transit.
124
[Indicating/Recording Systems] INDREC_020 — PAGE Explain the location and function of the STATUS page.
- Located on the SD (Systems Display). - Provides an operational summary of the state of the aircraft. - Displayed by: - Pressing the STS pb on the ECAM control panel. - Automatically as part of the ECAM Procedure; it is displayed when the last ECAM alert is cleared. - Automatically when CONF 1 (FLAPS 1) has been selected for approach and the Status page is not empty. - The STS REMINDER (a white boxed STS) appears at the lower portion of the E/WD whenever the STATUS page is not empty; whenever information is present on the STATUS page. It does NOT go away after the STATUS page has been viewed.
125
[Indicating/Recording Systems] INDREC_021 — PEDASTAL GENERAL Describe the functions of the SWITCHING panel.
- ATT HDG – selects IRU 3 for attitude and heading information when IRU 1 or 2 fails. - AIR DATA – selects ADR 3 for pitot-static information when ADR 1 or 2 fails. - EIS DMC – selects DMC 3 when DMC 1 or 2 fails. - ECAM/ND XFR – transfers the SD (lower ECAM) information to the CA’s or FO’s ND. NOTE: ND screen information cannot be transferred to the SD (lower ECAM)
126
[Indicating/Recording Systems] INDREC_022 — CONTROL PANEL Describe the function of the CLR, RCL, and T.O. CONFIG pbs on the ECAM Control Panel.
- CLR pbs - Used to clear failure messages and sequence through the SD pages during an ECAM procedure. - With multiple failure messages displayed, pressing the CLR pb will remove (clear) the first message and all of its associated action steps. - RCL pb - Used to recall ECAM messages (alerts) previously cleared by the CLR pbs that are still active. - If there is no ECAM message to recall, “NORMAL” appears on the E/WD. - If held for more than 3 seconds, the E/WD displays any alerts (CAUTION failure messages) that were canceled by the EMER CANC pb. - TO CONFIG pb - Used to test the Takeoff Warning system. - Simulates the application of takeoff power. - Generates all warnings associated with the aircraft not correctly configured for takeoff.
127
[Indicating/Recording Systems] INDREC_023 — CONTROL PANEL PAGE Describe the effects of using the EMER CANC pb in response to ECAM WARNINGS or CAUTIONS. The EMER CANC pb should be used to suppress spurious or nuisance MASTER CAUTIONS or WARNINGS. The EMER CANC pb should not be used in place of a CLR pb when performing an ECAM Procedure.
- Warnings: - Cancels (stops) the aural warning (CRC) for as long as the failure condition continues. - Extinguishes the MASTER WARNING lights. - Does not affect the ECAM message display (MASTER WARNING message remains in view). - Cautions: - Extinguishes the MASTER CAUTION lights. - Cancels (stops) the aural warning (Single chime) for as long as the failure condition continues. - Cancels ECAM message display for the remainder of the flight. The CAUTION message is moved to the STATUS page under CANCELLED CAUTION. - Cancelled MASTER CAUTION messages may be recalled (restored) by pressing the RCL pb for 3 seconds. P 48 T 5#y
128
[Flight Management] FMGT_005 — GENERAL DUAL MODE SINGLE MODE INDEPENDENT MODE AND MESSAGES Describe the operating modes of the Flight Management and Guidance System (FMGS).
- Dual: - Normal mode of operation - Both FMGCs are synchronized, meaning all data entered into any Multi-Function Control and Display Unit (MCDU) is transferred to both FMGCs through a crosstalk bus. - Single: - FMGS operating mode when one FMGC has failed. - Both Flight Directors are driven by the same (operative) FMGC. - Any entry on either MCDU is sent to the operative FMGC. - Indications of a failed FMGC include:  1FD1 (FMGC #2 has failed) or 2FD2 (FMGC #1 has failed) in Column 5 of the FMAs, indicating that both flight directors are driven by the same FMGC.  OPP FMGC IN PROCESS message in MCDU scratchpad.  SELECT OFFSIDE RNG/MODE and MAP NOT AVAIL messages on the failed side’s ND - Independent: - Degraded mode caused by a significant difference between the two databases (database validity). - FMGCs work independently and there is no synchronization of data between the FMGCs. - Each MCDU transmits data it receives from its onside FMGC. - INDEPENDENT OPERATION message is displayed in both MCDU scratchpads. IND annunciator on the top of the MCDU is lit.
129
[Flight Management] FMGT_009 — 28-RADIO NAV PAGE GENERAL NAVIGATION MODES Describe the FMGS autotune function.
- Automatically tunes VOR stations for approach and enroute position updating. - Automatically tunes the ILS frequency when an ILS approach has been loaded into the flight plan, or if an ILS is associated with the departure runway.
130
[Flight Management] FMGT_012 — MODES TRAJECTORY DEVIATION Recall how VOR and ILS information is displayed.
- VOR information is displayed on the NDs: - When respective EFIS VOR/ADF selector switch is in the VOR 1 or 2 position. - ILS information, including deviation scales, is displayed on the PFDs: - When respective EFIS (I)LS pb is selected
131
[Flight Management] FMGT_014 — 30-RMP MODES Explain the function of the STBY NAV key on the RMP.
- When selected: - Activates the STBY NAV (ILS, VOR and ADF) selector keys of the respective RMP. Used when both FMGCs or MCDUs fail. - Engages radio navigation backup mode. - Takes away auto and manual navaid tuning capability from both FMGCs. - The MCDU RAD NAV page is unusable. - A green light illuminates next to the key, indicating activation. - An R appears next to the tuned VOR frequency on the ND.
132
[Flight Management] FMGT_015 — MODES Explain the indications of a tuned VOR on the NDs.
- If a station has been autotuned by the FMGCs, it will only contain the station’s three letter identifier, no M or R. - If a station has been manually tuned via the MCDU’s RAD NAV page, an underlined M appears next to the station’s three-letter identifier. - If a station has been manually tuned via an RMP’s Standby NAV keys, an underlined R appears next to the station’s three-letter identifier.
133
[Flight Management] FMGT_016 — 20-OVERHEAD PANEL 10-GENERAL Explain the function of the IR Mode Selector Positions.
- The IR mode selector switch is used to control the function of its respective ADIRU. - OFF – Depowered. Both ADR and IR data unavailable. - NAV – Normal operation, initiates IR alignment, provides Inertial Reference data. - ATT – Provides only Attitude and Heading information (if entered by flight crew.) Used when navigation data is not available. - From left to right is selector ADIRU 1 (CA), ADIRU 3 (STBY), and ADIRU 2 (FO). #3 is in the center.
134
[Flight Management] FMGT_017 — Recall the time required for FULL (normal) and FAST IR alignments.
- A FULL (normal) alignment takes 10 minutes. - A FAST alignment takes 30 seconds.
135
[Flight Management] FMGT_020 — 20-OVERHEAD PANEL 20-ADIRS OPERATIONS STATUS MESSAGES ALIGNMENT Explain the operational difference between steady versus flashing IR ALIGN lights.
- Steady – Indicates the respective ADIRU is operating normally in the alignment mode. - Flashing – Indicates an alignment fault has occurred, caused by one of the following: - Excessive motion. - A present position has not been entered in the MCDU with approximately 1 minute remaining. - The position stored at shutdown differs from the present position entered in the MCDU.
136
[Flight Management] FMGT_021 — 20-OVERHEAD PANEL Recall the meaning of the ON BAT light on the ADIRS panel.
- Illuminates when one or more ADIRU is operating on aircraft battery power. - Appears for a few seconds at the beginning of a Full (normal) alignment process, when an ADIRU Mode Selector is placed from OFF to NAV. This indicates that the respective ADIRU is capable of operating on battery power when required. NOTE: The ON BAT light will not illuminate during a FAST alignment.
137
[Flight Management] FMGT_031 — 30-CONTROL PANEL Recall the functions of each of the radar’s MODE selector knob positions.
- WX – Displays only precipitation returns: - Black – minimum/no intensity - Green – low intensity - Amber – moderate intensity - Red – highest intensity - WX+T – Displays both precipitation returns and turbulence: - Magenta represents turbulence areas. - TURB – Displays only areas of turbulence in magenta. NOTE: The ND only displays turbulence areas within 40 NM. - MAP – Ground mapping mode: - Black – water - Green – ground returns - Amber – cities and mountains. P 609T 6#y
138
[Fuel] FUEL_001 — TANKS Recall the aircraft’s fuel tank configuration.
- Each wing tank is divided into an Inner and Outer tank (also called cell.) - A Center tank located in the center of the fuselage. (Example of ECAM FUEL SD page displaying each tank at full capacity, totaling approx. 42,000 lbs.) - Surge vent tanks, located outboard of each outer tank, are not displayed on the ECAM FUEL SD page.
139
[Fuel] FUEL_003 — TANKS Explain the normal fuel loading sequence and approximate tank capacities.
- Outer Wing Tanks are filled to capacity, followed by the inner tanks. - Total Wing Tank capacity is approximately 27,500lbs. (approx. 13,750 lbs per wing – 1500 outer and 12,000 inner). - Center Tank is filled, as required, once Wing Tanks are full. Approximate capacity is 14,500 lbs. NOTE: The Center Tank is normally not filled without first having full wing tanks.
140
[Fuel] FUEL_006 — OVERHEAD PANEL ENGINE FEED MAIN COMPONENTS Recall the number and location of the fuel pumps.
- A total of 6 electrically powered fuel pumps. - 2 in each wing inner tank. - 2 in the center tank
141
[Fuel] FUEL_007 — MAIN COMPONENTS FUEL FEED SEQUENCE OVERHEAD PANEL With fuel in the Center Tank, explain the normal (automatic) fuel feed priority and the function of the MODE SEL pb.
- With flaps/slats retracted: center tank fuel is preferentially consumed first, followed by wing tank fuel. - The wing tank pumps are equipped with pressure relief valves. - Pressure relief valves allow center tank pumps to preferentially supply the respective engine. - With flaps extended: center tank pumps automatically shut off, per auto logic, allowing wing tank fuel to be consumed. - AUTO (light out) – if CTR TK PUMP pbs are selected on (lights out), the center tank pumps will be automatically controlled by automated logic. - MAN (white) – automatic control logic is off. Center tank pumps must be manually controlled.
142
[Fuel] FUEL_008 — FUEL PAGE OVERHEAD PANEL Recall the function and indications of the L & R TK PUMPS pbs.
- L(R) TK PUMPS pbs are used to manually control their respective Wing Tank pumps: - On (light out) – pump runs until pb is selected OFF. Inline green on FUEL SD. - OFF (white) – pump is off and remains off until pb is selected. Crossline amber on FUEL SD. NOTE: Wing tank pumps are not equipped with auto logic. Pump operation must always be manually controlled.
143
[Fuel] FUEL_011 — FUEL PAGE DISPLAY Recall the indications when Center Tank fuel is being consumed.
- CTR TK FEEDG appears in the E/WD memo section. - On the ECAM FUEL page, the center tank pump indications will be inline green. NOTE: When the center pumps are commanded off, per computer logic, pump indications will be crossline green.
144
[Fuel] FUEL_013 — FUEL FEED SEQUENCE Recall when the transfer valves will automatically open, allowing outer cell fuel to gravity feed into the respective inner cell.
- Both transfer valves automatically open when either wing tank inner cell fuel level reaches approximately 1,650lbs.
145
[Fuel] FUEL_014 — FUEL PAGE DISPLAY Recall the indications of the transfer valves on the ECAM FUEL SD.
- Transfer valve indications on the ECAM FUEL SD appear vertical when closed and horizontal when open. - OUTR TK FUEL XFRD (green) appears on the E/WD memo section when open. NOTE: While the valves are in transit, they appear as diagonal lines.
146
[Fuel] FUEL_015 — USED Recall when the F. USED indications reset to zero.
- Automatically, when the engine is started on the ground.
147
[Fuel] FUEL_016 — FUEL PAGE Recall the location of valve indications on the ECAM FUEL SD page.
- Cross feed (X Feed) valve appears directly above the CTR text. - APU fuel valve appears under the white APU. - Engine Low Pressure fuel valves (LP Valves) appear directly below the engine’s fuel used quantity number.
148
[Fuel] FUEL_017 — FUEL PAGE Recall the location of fuel temperature indications.
on the ECAM FUEL SD page. - Outer and Inner tank fuel temperatures are displayed directly below the respective compartment on the ECAM FUEL SD. NOTE: Fuel temperature readings are not provided for the center tank.
149
[Fuel] FUEL_018 — FUEL PAGE OVERHEAD PANEL DISPLAY Recall the controls and indications of the Fuel X Feed (cross feed) Valve.
- The fuel cross feed valve is controlled with the X FEED pb: - lights out (off)– valve is closed - ON (white) – valve has been commanded open - OPEN (green) valve is fully open - When the cross feed is open: - FUEL X FEED (green) appears on E/WD memo section. - On ECAM FUEL SD, the cross feed valve appears as in-line green. NOTE: While in transit, the valve indication appears as an amber circle with a diagonal line.
150
[Fuel] FUEL_019 — FUEL PAGE UPPER DISPLAY Recall the indications of a degraded or inaccurate Fuel Quantity Indication (FQI) system.
- Amber dashes cover the last two digits of fuel quantity displays of the: - FOB indication on the E/WD - The individual fuel tank quantities on the ECAM FUEL SD
151
[Fuel] FUEL_020 — UPPER DISPLAY Recall the meaning of an amber half box surrounding the FOB indication on the E/WD.
- There are three possible causes, all the result of not usable (trapped) fuel: - Both center tank pumps have failed (with usable fuel in tank). - Both center tank pumps have been turned off (with usable fuel in tank). - A wing tank transfer valve (intercell transfer valve) has failed. P 749T 7#y
152
[Hydraulics] HYD_002 — GREEN SYSTEM PUMP BLUE SYSTEM PUMPS YELLOW SYSTEM PUMPS RAM AIR TURBINE (RAT) POWER TRANSFER UNIT (PTU) Recall the power sources of each hydraulic system.
- Green: - Engine-driven pump powered by engine 1 (primary). - Power Transfer Unit (PTU) (alternate). - Blue: - Electrically powered pump (primary). - Ram Air Turbine (RAT) (alternate). - Yellow: - Engine-driven pump powered by engine 2 (primary). - Power Transfer Unit (PTU) (alternate). - Electrically powered pump (alternate). - Hand pump – capable only of providing pressure for cargo door operation (Not displayed on HYD SD page).
153
[Hydraulics] HYD_003 — HYD PAGE Describe the hydraulic system’s reservoir indications on the ECAM HYD SD page.
- The pointer is displayed in green when fluid level is in normal range. - The pointer is displayed in amber if fluid level goes below the warning level. - LO AIR PRESS appears in amber if the air pressure in the reservoir drops below normal. - OVHT appears in amber if the temperature of the hydraulic fluid is above normal.
154
[Hydraulics] HYD_004 — OVERHEAD PANEL Explain the operation of the BLUE ELEC PUMP when its pb is selected AUTO (lights out).
- On the ground - pump is automatically activated and runs continuously with first engine start. - In-flight - pump operates continuously regardless of engine operation as long as AC power is available.
155
[Hydraulics] HYD_005 — HYD PAGE FIRE SHUTOFF VALVES Describe Fire Shutoff valve indications on the ECAM HYD SD page.
- Green and Yellow system Fire Shutoff valves are depicted below the engine pump depictions. - Controlled by the respective ENG 1(2) FIRE pb.
156
[Hydraulics] HYD_006 — HYD PAGE Recall which pumps are depicted on the ECAM HYD SD page.
- Green ENG 1 PUMP - Blue ELEC PUMP - Yellow ENG 2 PUMP - Yellow ELEC Pump - PTU (Power Transfer Unit) - Ram Air Turbine (RAT)
157
[Hydraulics] HYD_008 — HYD PAGE OVERHEAD PANEL Recall the indications when the Yellow Electric Pump is selected ON.
- ON (white) appears on the YELLOW ELEC PUMP pb. - The triangle on the ECAM HYD SD page next to the white ELEC indication turns solid green.
158
[Hydraulics] HYD_009 — POWER TRANSFER UNIT (PTU) Explain the function of the Power Transfer Unit (PTU).
- The PTU is a bidirectional hydraulic power transfer unit which provides an alternate power source to either the Green or Yellow hydraulic systems, and enables the Yellow system to pressurize the Green system and vice versa. NOTE: The PTU transfers pressure, and not fluid, between the Green and Yellow systems.
159
[Hydraulics] HYD_011 — HYD PAGE Describe the PTU indications on the ECAM HYD SD page.
- Green arrows pointing away from the white PTU label indicate that the PTU is armed and not operating. - Amber arrows indicate the PTU pb has either been selected OFF or inhibited. - Solid green arrows pointing to the left indicate that the PTU is supplying pressure to the Green hydraulic system. - Solid green arrows pointing to the right indicate that the PTU is supplying pressure to the Yellow hydraulic system.
160
[Hydraulics] HYD_012 — DISPLAY Recall the indication on the E/WD memo when the PTU is operating.
- HYD PTU appears
161
[Hydraulics] HYD_013 — TO OPERATE THE FORWARD AND AFT CARGO DOOR OVERHEAD PANEL PROXIMITY DETECTORS ON SHOCK ABSORBERS Describe the conditions that will automatically inhibit PTU operation.
- When ENG MASTER switches are in opposite positions (one ON, one OFF), and either: - Parking brake is on, or - Nose wheel steering is disconnected by the towing lever on the nose gear. - When the Yellow Electric pump is activated through either cargo door’s operation.
162
[Hydraulics] HYD_014 — OVERHEAD PANEL Recall the meaning of the FAULT light in the PTU pb.
- Illuminates as the result of the following in either the Green or Yellow hydraulic system reservoirs: - Hydraulic fluid overheat - Low air pressure - Low fluid level NOTE: The FAULT light does not represent the status or condition of the PTU.
163
[Hydraulics] HYD_015 — OVERHEAD PANEL RAM AIR TURBINE (RAT) Explain the function of the RAT MAN ON pb on the HYD Overhead Panel.
- Used to manually deploy the Ram Air Turbine (RAT), which provides alternate power to pressurize the Blue hydraulic system. - The emergency generator is not energized with use of this pb. - The RAT will not automatically deploy with a failure of the Blue Electric pump.
164
[Hydraulics] HYD_016 — DISPLAY HYD PAGE Recall the indications when the RAT is deployed.
- RAT OUT (green) appears on the E/WD memo section when the RAT is deployed or not fully stowed. - The white hollow triangle next to the white RAT indication on the ECAM HYD SD page turns solid green, and a line connects it to the rest of the Blue system indications. P 873T 8#y
165
[Landing Gear] LGEAR_003 — WHEEL SD PAGE LANDING GEAR INDICATOR PANEL Recall the indications of landing gear detected downlocked.
- Forward set of triangles on the ECAM WHEEL SD page appear in green. - NOTE: only one green triangle on each gear is sufficient to confirm that the gear is downlocked. - Three green triangles appear on the landing gear indicator panel. - LDG GEAR DN appears in green on the E/WD.
166
[Landing Gear] LGEAR_004 — LANDING GEAR INDICATOR PANEL Recall the meaning of a red UNLK light on the Landing Gear Indicator Panel.
- Indicates that a specific gear is not locked in the selected position.
167
[Landing Gear] LGEAR_006 — LANDING GEAR SELECTOR LEVER Recall what is indicated by the illumination of the red arrow on the Landing Gear Selector Lever.
- The aircraft is in the landing configuration and the landing gear is not downlocked.
168
[Landing Gear] LGEAR_008 — LANDING GEAR GRAVITY EXTENSION Recall the operation of GRAVITY GEAR EXTN hand crank.
- Lift/pull the handle into position. - Turn clockwise three (3) turns.
169
[Landing Gear] LGEAR_010 — MEMO DISPLAY Recall what is indicated by the NW STRG DISC memo on the E/WD.
- The towing control lever has been placed in the towing position by the ground crew, inhibiting nose wheel steering from the flight deck, normally in preparation for pushback. - Appears in green when both engines are not running. - Appears in amber when at least one engine is running. NOTE: NW STRG DISC is not displayed when the A/SKID & N/W STRG switch is placed to OFF.
170
[Landing Gear] LGEAR_011 — DESCRIPTION Recall the controls for Nose Wheel Steering.
- Tillers (steering hand wheels) on the CA’s and FO’s side consoles - Rudder pedals - Autopilot during auto landings
171
[Landing Gear] LGEAR_012 — CENTER INSTRUMENT PANEL BRAKING MODES Recall the possible Anti-Skid braking configurations.
- Normal brakes with antiskid (Green hydraulic pressure). - Alternate brakes with antiskid (Yellow hydraulic pressure). NOTE: In the event of total BSCU failure or failure of both Green and Yellow hydraulic systems, Alternate brakes without antiskid is available, powered by Yellow system accumulator.
172
[Landing Gear] LGEAR_013 — CENTER INSTRUMENT PANEL BRAKING MODES Recall what is indicated on ACCU-PRESS and BRAKES indicator.
- ACCU-PRESS – Indicates the pressure in the yellow brake accumulator. The Green Band represents a full charge. - BRAKES - Indicates yellow system pressure being applied to the respective brake. This includes Parking Brake application pressure. - Green Arcs - Represent the safe application pressure range, at or below 1,000 PSI, when brakes are being manually applied and anti-skid is not available. The pilot must modulate brake pressure at or below 1.000 PSI to avoid wheel locking. NOTE: Indications are only related to the YELLOW hydraulic system and not associated with Normal Braking or the Green hydraulic system.
173
[Landing Gear] LGEAR_014 — WHEEL SD PAGE Recall the meaning of these brake temperature indications on the ECAM WHEEL SD page.
- Green arc appears over the wheel with hottest brake temperature over 100ºC. - Arc becomes amber if a brake temperature exceeds 300ºC.
174
[Landing Gear] LGEAR_015 — WHEEL SD PAGE Recall the meaning of the Release Indicators on the ECAM WHEEL SD page.
- The horizontal green lines appear: - Temporarily after the landing gear is lowered to indicate that the antiskid function is armed/ready. - Reappear after touchdown, along with REL, when anti-skid is active.
175
[Landing Gear] LGEAR_017 — AUTO BRAKE PANEL Recall the function of each Autobrake pb selection.
- LO – Sends progressive brake pressure to the brakes 4 seconds after the spoilers deploy. - MED – Sends progressive brake pressure to the brakes 2 seconds after the spoilers deploy. NOTE: LO or MED is normally selected for landing. - MAX – Sends maximum pressure to the brakes immediately after the spoilers deploy. NOTE: MAX selection is only authorized for takeoff.
176
[Landing Gear] LGEAR_018 — AUTO BRAKE PANEL Recall the meaning of the DECEL (green) indication on an AUTO BRK pb.
- Indicates the actual deceleration rate is 80% of the selected rate.
177
[Landing Gear] LGEAR_019 — MEMO DISPLAY CENTER INSTRUMENT PANEL BRAKING MODES Recall the indications of the Parking Brake being applied.
- PARK BRK appears in the E/WD memo section. - The ACCU-PRESS/BRAKES indicator (triple indicator) displays approximately 2,000lbs psi application pressure on the left and right brakes. NOTE: The source of the application pressure can only be from either the active Yellow system or the Yellow system’s accumulator. P 98 T 9#y
178
[Surveillance] SURV_001 — 40-OVERHEAD PANEL 10-OVERVIEW Recall the function of the GPWS TERR pb and SYS pb, when selected OFF.
- TERR pb selected OFF: - Inhibits only the terrain warning mode of the GPWS system. This is based on a GPWS database to display terrain information. The basic modes remain operational. - SYS pb selected OFF: - Inhibits all basic modes of the GPWS system. The terrain warning mode remains operational.
179
[Surveillance] SURV_002 — 40-OVERHEAD PANEL Describe the function of the G/S MODE, FLAP MODE, and LDG FLAP 3 pbs on the GPWS panel.
- G/S MODE: - Inhibits the excessive deviation below glideslope warning “GLIDESLOPE” - Used for approaches with glideslope out of service, or LDA/LOC approaches. - FLAP MODE: - Inhibits “TOO LOW FLAPS” aural warning. - Used in conjunction with a flap malfunction. - LDG FLAP 3: - Configures the GPWS to expect FLAPS 3 as the final flap setting for landing. - Inhibits “TOO LOW FLAPS” aural warning. - Landing memo displays FLAPS 3 instead of FLAPS FULL.
180
[Surveillance] SURV_003 — 40-INSTRUMENT PANELS Explain the manual and automatic operation of the of GPWS Terrain feature.
- Manual operation: - A TERR ON ND pb has been selected ON (green) - Terrain is continuously displayed on the respective ND. - Automatic operation: - Respective TERR ON ND pb is deselected (light out) and terrain data does not appear on the ND. - Terrain is automatically displayed on both NDs as the result of a caution or warning. - Both TERR ON ND pbs illuminate ON (green). - To remove the terrain display, the pb on the respective side must be deselected (lights out). NOTE: Terrain displays take priority over weather radar displays.
181
[Surveillance] SURV_005 — EGPWS 30-WEATHER RADAR INDICATION ON ND Recall the details of the Terrain and Weather indications on the NDs.  When terrain is being displayed, TERR (blue) appears in the lower right corner of the ND.  When weather radar is on, TILT (blue) with the corresponding tilt angle appears in the lower right corner of the ND.
182
[Surveillance] SURV_006 — EGPWS Recall the meaning of the number value displayed with the Terrain display.
- Appears only when the respective ND is set in the ARC mode. - Represents the highest elevation of an obstacle that is within the respective ND’s range setting. Example: 081 is read as 8,100ft.
183
[Surveillance] SURV_007 — 35-TERRAIN AWARENESS AND DISPLAY Recall the indications associated with a Terrain Caution and a Terrain Warning.
- Terrain Caution - Both GPWS lights (amber) illuminate on the forward instrument panel. - Aural “TERRAIN AHEAD” warning sounds. - Terrain displays automatically appear on both NDs. - Amber TERR AHEAD message appears on the NDs. - Terrain Warning - Both PULL UP lights (red) illuminate on the forward instrument panel. - Aural “TERRAIN AHEAD, PULL UP” warning sounds. - Terrain displays automatically appear on both NDs. - Red TERR AHEAD message appears on the NDs.
184
[Surveillance] SURV_008 — 20-ATC/TCAS PANEL 20-CONTROL PANELS Describe the function of the controls and meaning of the indications on the ATC/TCAS Control Panel.
- ABV/N/BLW Select Knob - ABV (Above) sets TCAS display from 9900 ft above to 2700 ft below aircraft. - N (Normal) sets TCAS display from 2700 ft above to 2700 ft below aircraft. - BLW (Below) sets TCAS display from 2700 ft above to 9900 ft below aircraft. - ATC FAIL Indicator – Illuminates when the selected transponder fails. Does not illuminate when STBY mode is selected. - ADS-B Fail Annunciator – Illuminates with loss of GPS signal or ADS-B system failure. - Mode Select Knob – Rotate to enable transponder, altitude reporting, and TCAS functions. - Transponder SYS Select Knob – Rotate to select ATC system 1 or ATC system 2. - IDENT (Identification) Button – Push to ID aircraft to ATC. - TRAFFIC Knob – Rotate to select traffic display mode to “THRT” to display only threats, or “ALL” to display all traffic.
185
[Surveillance] SURV_011 — EGPWS 20-ND INDICATIONS GENERAL Recall which ND mode cannot display GPWS, TCAS, or Weather Radar returns.
- PLAN mode.
186
[Surveillance] SURV_013 — WINDSHEAR DETECTION FUNCTION Recall the indications of Windshear warnings.
- WINDSHEAR (red) message appears on the PFDs. - Aural “WINDSHEAR” “WINDSHEAR” “WINDSHEAR” warning sounds (3 times.) NOTE: The A320 Windshear system is a reactive system only, not predeictive. - Warnings will only function: - When aircraft is configured at FLAPS 1 (CONF 1) or greater. - At low altitudes during takeoff and landing.
187
[Surveillance] SURV_015 — ALTITUDE ALERT Describe the Altitude Alert system indications.
- Designed to alert the pilot of altitude deviations. The aural portion of the alert (C chord) is inhibited when the autopilot is engaged. - During a climb or descent, when within 750ft of the FCU altitude:  A short duration aural C-chord sound.  PFD altitude window border pulses until within 250ft of the FCU altitude. - In level flight, if aircraft deviates more than 250ft of the FCU altitude:  Short duration aural C-chord sounds.  PFD altitude window border pulses. P 0 T 0#y
Delta A320
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