Auto Flight

2026-07-07

Auto Flight: 1 DESCRIPTION

Auto Flight: 1.1 General

The aircraft is provided with an Automatic Flight Control System (AFCS). It achieves: - Autopilot (AP) function with automatic pitch trim, rudder autotrim, Yaw Damper (YD), and turn coordination - Flight Director (FD) function - Altitude alert. Main components are: - Two Core Avionics Cabinet (CAC 1 which controls the autopilot functions, and CAC 2 which monitors the autopilots functions) - Three control panel : one Flight Guidance and Control Panel (FGCP) and two Index Control Panel (ICP) - Two Flight Mode Annunciator (FMA), one on each PFD upper part - Three identical servo actuators on the three axes (pitch, roll, yaw) - Two Power Trim Box (to interface with the pitch trim actuator and yaw trim actuator). The computers (CAC 1/2) receive data from the Air Data Computers (ADC), the Attitude and Heading Reference Systems (AHRS), the radio-altimeter, the NAV 1/2 , the FMS, and from some sensors. The CAC 1 generates commands to the flight control actuator and CAC 2 monitors the system.

Auto Flight: 1.2 Component Layout

14, 0, 4, 3 V13.2 L_CB_00000000_0000000_000_00_00

1 3 2 1 FMA, FGCP, ICP, computers, pitch, and yaw trim boxes (Cockpit and electronic rack). 2 Yaw and pitch servo actuators. 3 Roll servo actuator.

Auto Flight: 2 CONTROLS

Auto Flight: 2.1 Go-Around pb

The go-around pb are on the external side of each Power lever.

2 GI FI 35 40 45 50 55 60 65 70 75 80 80 75 70 65 60 55 50 ON POWER POWER GUST LOCK OFF OFF 1 85 85 MAX PWR MAX PWR GI R E V R E V When pressing these pb: - The autopilot is disengaged - All flight director modes except LNAV (if engaged before GA) are cancelled, they are replaced by: o HDG HOLD for the lateral mode o GA for the vertical mode. - If missed approach is defined in the FMS FPLN, the missed approach procedure is activated.

Auto Flight: 2.2 Control Wheel

2 3 1 ON THE BACK SIDE OF THE CONTROL WHEEL 1 AP Quick Disconnect pb Enables to disconnect AP when pressed once. When pressed again clears the AP OFF alarm. 2 Normal Pitch Trim Rocker Switches Used to adjust the pitch trim. Note If the AP is engaged, manual trim operation of the rocker switches disengages the AP.

3 Touch Control Steering (TCS) pb On the back side of the control wheel. The TCS pushbutton enables the flight crew to temporarily take manual control of the aircraft without AP disengagement. Press the TCS pb with a basic AP mode engaged Changes AP pitch and roll references. The reference attitude will become the aircraft's new pitch and roll attitude (within limits) at the time the TCS pb is released. If the TCS pb is released with: - A pitch attitude: o In the -11°/+15° limits, the AP reference pitch attitude becomes the current aircraft's pitch attitude o Out of the -11°/+15° limits, below 25°: the aircraft returns in the -11°/+15° limits and the AP maintains the limit o Above 25°: the AP disengages. - A bank angle: o Below 6°: the AP levels the wings and, when wings are level, maintains the current heading o Between 6° and 35°: the AP maintains the current bank angle o Above 35°: the aircraft returns to 35° and the AP maintains 35°. Press the TCS pb with VS HOLD mode or PITCH HOLD mode engaged Resynchronizes the air data command reference without disengagement of the mode. Press the TCS pb in all other modes Enables the flight crew to take manual control of the aircraft without mode disengagement.

Auto Flight: 2.3 STBY Pitch Trim SW

14, 0, 4, 3 V13.2 L_CB_00000000_0000000_000_00_00

NOSE UP NOSE DN STBY PITCH STBY PITCH TRIM sw will disengage the AP.

Auto Flight: 2.4 Flight Guidance and Control Panel (FGCP)

(Applies: 1096-1283) 14, 0, 4, 3 V13.2 L_CB_00000000_0000000_000_00_00

HDG PUSH SYNC NAV SOURCE ALT SEL COURSE V/ILS 1 V/ILS 2 FM 1 FM 2 NAV SOURCE COURSE V/ILS 2 V/ILS 1 FM 2 FM 1 NOSE UP NOSE DN 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 9 8 5 FD AP YD SPD HLD CPL FD ALT IAS VS VNAV HDG APP BC STBY NAV

1 AP pb Action on the AP pb engages AP and YD functions simultaneously. All four associated arrows come on green. Pressing the pb again disengages only the AP function. 2 YD pb Action on the YD pb engages the YD function. Both associated arrows come on green. Pressing the pb again disengages the YD function (and the AP if engaged). 3 SPEED HLD pb This function is not implemented. A yellow “SPD HLD INHIB” message comes on, on the FMA. It is displayed steady for 7 s, then disappears. 4 CPL pb Enables selection of the side (CAPT or F/O) to be coupled to the AP/YD computers. Coupled side is indicated: - By green arrow light on, on side of the pb - By the arrow on FMA. At power up, selected side is CAPT side. 5 Vertical Modes Pushbuttons Enable selection of vertical modes: IAS HOLD, VS HOLD, ALT HOLD. Pressing the pb again disengages these functions to return in basic mode (PITCH HOLD). Note VNAV function is not activated. When VNAV pb is pressed, a yellow message “VNAV INHIB” is displayed on FMA. For further details, Refer to VERTICAL MODES. 6 Pitch Wheel (PW) In VS mode, operating the PW will change the VS value without disengaging the VS mode In pitch Hold mode, operating the PW will change the pitch target value without disengaging the pitch Hold mode. Note PW is inhibited in GS, IAS HOLD, ALT SEL CAPTURE, and ALT HOLD modes. 7 STBY pb Cancels all AP and FD Upper Modes (Armed, Captured, or active modes). Resets them to basic modes. 8 Lateral Modes Pushbuttons Enable the selection of lateral modes: HDG SEL, NAV, APP, BC. Pressing the pb again disengages these functions to return in basic mode (HDG HLD or ROLL HLD) and in case of Flux valve failure the WING LVL replaces HDG HLD basic mode. For further details, Refer to LATERAL MODES.

9 FD pb Action on the FD pb displays the FD command bars. Each bar (Horizontal Bar and Vertical Bar ) will be displayed in: - Upper mode - Basic mode, only if AP is engaged. (Pressing the pb again clears the display of the FD command bars). 10 HDG knob Sets the heading used as reference by the FGS. The selected heading is displayed on both CAPT and F/O on PFD and/or ND depending on display configuration. Pushing the knob permit to synchronize the heading bug with the actual heading. 11 CRS knob CAPT Side Sets the course on CAPT PFD and/or ND depending on display configuration. 12 CRS knob F/O Side Sets the course on F/O PFD and/or ND depending on display configuration. 13 NAV SOURCE selector CAPT Side Selects the source of navigation data displayed on CAPT ND and PFD: - FM 1 for navigation data from FMS 1 - V/ILS 1 for navigation data from VOR 1 or ILS 1 - V/ILS 2 for navigation data from VOR 2 or ILS 2 - FM 2 for navigation data from FMS 2. Note In normal use, it is recommended to select the NAV SOURCE FM 1 or V/ILS 1 on CAPT side. 14 NAV SOURCE selector F/O Side Selects the source of navigation data displayed on F/O ND and PFD: - FM 1 for navigation data from FMS 1 - V/ILS 1 for navigation data from VOR 1 or ILS 1 - V/ILS 2 for navigation data from VOR 2 or ILS 2 - FM 2 for navigation data from FMS 2. Note In normal use, it is recommended to select the NAV SOURCE FM 2 or V/ILS 2 on F/O side. 15 ALT SEL knob Controls the preselected altitude which is shown above the PFD altimeter scale.

(Applies: 1054) 14, 0, 4, 3 V13.2 L_CB_00000000_0000000_000_00_00

HDG PUSH SYNC NAV SOURCE ALT SEL COURSE V/ILS 1 V/ILS 2 FM 1 FM 2 NAV SOURCE COURSE V/ILS 2 V/ILS 1 FM 2 FM 1 NOSE UP NOSE DN 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 9 8 5 FD HDG NAV APP STBY ALT VS AP YD SPD HLD CPL FD IAS BC 1 AP pb Action on the AP pb engages AP and YD functions simultaneously. All four associated arrows come on green. Pressing the pb again disengages only the AP function. 2 YD pb Action on the YD pb engages the YD function. Both associated arrows come on green . Pressing the pb again disengages the YD function (and the AP if engaged). 3 SPEED HLD pb This function is not implemented. A yellow “SPD HLD INHIB“ message comes on, on the FMA. It is displayed steady for 7 s, then disappears. 4 CPL pb Enables selection of the side (CAPT or F/O) to be coupled to the AP/YD computers. Coupled side is indicated: - By green arrow light on, on side of the pb - By the arrow on FMA. At power up, selected side is CAPT side.

5 Vertical Modes Pushbuttons Enable selection of vertical modes: IAS HOLD, VS HOLD, ALT HOLD. Pressing the pb again disengages these functions to return in basic mode (PITCH HOLD). For further details, Refer to VERTICAL MODES. 6 Pitch Wheel (PW) In VS mode, operating the PW will change the VS value without disengaging the VS mode Note PW is inhibited in GS, IAS HOLD, ALT SEL CAPTURE, and ALT HOLD modes. 7 STBY pb Cancels all AP and FD Upper Modes (Armed, Captured, or active modes). Resets them to basic modes. 8 Lateral Modes Pushbuttons Enable the selection of lateral modes: HDG SEL, NAV, APP, BC. Pressing the pb again disengages these functions to return in basic mode (HDG HLD or ROLL HLD) and in case of Flux valve failure the WING LVL replaces HDG HLD basic mode. For further details, Refer to LATERAL MODES. 9 FD pb Action on the FD pb displays the FD command bars. Each bar (Horizontal Bar and Vertical Bar) will be displayed in: - Upper mode - Basic mode, only if AP is engaged. (Pressing the pb again clears the display of the FD command bars). 10 HDG knob Sets the heading used as reference by the FGS. The selected heading is displayed on both CAPT and F/O on HSI and/or ND depending on display configuration. Pushing the knob permit to synchronize the heading bug with the actual heading. 11 CRS knob CAPT Side Sets the course on CAPT PFD and/or ND depending on display configuration. 12 CRS knob F/O Side Sets the course on F/O PFD and/or ND depending on display configuration. 13 NAV SOURCE selector CAPT Side Selects the source of navigation data displayed on CAPT ND and PFD: - FM 1 for navigation data from FMS 1 - V/ILS 1 for navigation data from VOR 1 or ILS 1 - V/ILS 2 for navigation data from VOR 2 or ILS 2 - FM 2 for navigation data from FMS 2. Note In normal use, it is recommended to select the NAV SOURCE FM 1 or V/ILS 1 on CAPT side.

14 NAV SOURCE selector F/O Side Selects the source of navigation data displayed on F/O ND and PFD: - FM 1 for navigation data from FMS 1 - V/ILS 1 for navigation data from VOR 1 or ILS 1 - V/ILS 2 for navigation data from VOR 2 or ILS 2 - FM 2 for navigation data from FMS 2. Note In normal use, it is recommended to select the NAV SOURCE FM 2 or V/ILS 2 on F/O side. 15 ALT SEL knob Controls the preselected altitude which is shown above the PFD altimeter scale.

Auto Flight: 2.5 Index Control Panel (ICP)

14, 0, 4, 3 V13.2 L_CB_00000000_0000000_000_00_00

SEL AUTO/MAN SPD TGT BARO SET PUSH STD DH MDA

1 2 3 4 SPD TGT (upper part) 1 AUTO/MAN SEL pb Selects the source of the IAS target between: - MAN mode: the IAS target is the value manually selected by the flight crew through the knob 2 . Manual IAS target bug and value are displayed in cyan on speed scale of both PFD. - AUTO mode: the IAS target is managed by the FMS. FMS IAS target bug and value are displayed in magenta on speed scale of both PFD. For details about IAS, Refer to FMS.02.80.4.2 IAS. Note At power on, the manual speed target mode (MAN) is engaged. 2 SPD TGT knob Selects the IAS target when the MAN mode is selected. BARO SET (lower part) 3 BARO SET/PUSH STD knob Selects the barometric reference. Push the knob to set standard barometric reference (29.92 inHg / 1 013.25 hPa).

4 DH/MDA knob Outer knob permits to select between DH (Decision Height) or MDA (Minimum Descent Altitude). Inner knob is used to set DH or MDA values, depending on the outer knob position. DH or MDA values are displayed in cyan on ADI area of PFD. 14 Flight Mode Annunciator (FMA) General FMA

HOLD ROLL LO ICING DGD PERF CAT1 AP FD DUAL CHECK NAV VOR ALT SEL TCS 3 5 6 7 8 SRC 4 1 2 15 14 13 11 12 9 10 FD SINGLE CH PITCH HOLD RETRIM WING DN ROLL R The FMA, in the upper part of the PFD, has: - Four columns dedicated to annunciation of: o Icing Status Information o Lateral Modes o Vertical Modes o Engagement Status of the autopilot. - A messages line.

Modes Symbols CYAN GREEN GREEN GREEN MODE ARM MODE HOLD MODE CAPTURE () MODE CHANGE (BOXED FOR 7s) DISPLAY DESCRIPTION

Lateral Modes Lateral Modes 1 Lateral armed mode (cyan) 2 Lateral Capture and Hold mode (green) 3 Bank Angle (green) Depending on the speed: - Low Bank (LO) (15 ° MAX), if IAS < VmHB or Rad Alt < 1 000 ft - High Bank (27 ° MAX), in all the other cases.

DESCRIPTION HDG HOLD MODE (BASIC MODE) 2 MODE CHANGE 1 3 ROLL HOLD MODE (BASIC MODE) HDG HOLD ROLL HOLD HDG HOLD ROLL HOLD "LO" or " " "LO" or " " ARM + 7 S BANK ANGLE WING LVL MODE (BASIC MODE) WING LVL WING LVL "LO" or " " HDG SEL (UPPER MODE) HDG SEL HDG SEL "LO" or " "

C 1 DESCRIPTION NAV MODE ASSOCIATED WITH A VOR (UPPER MODE) 2 MODE CHANGE 1 3 NAV MODE ASSOCIATED WITH A LOC (UPPER MODE) APP MODE ASSOCIATED WITH AN ILS (COMMON UPPER MODE) CAPTURE (GREEN) VOR LOC VOR LOC VOR LOC VOR LOC "LO" or " " "LO" or " " ARM (CYAN) + 7 S HOLD (GREEN) BANK ANGLE (GREEN) APP MODE ASSOCIATED WITH A GPS L-LOC L-LOC L-LOC L-LOC "LO" or " " NAV MODE ASSOCIATED WITH A FMS (UPPER MODE) BC BACK COURSE OF THE LOC (UPPER MODE) --> BC LNAV BC BC BC LNAV "LO" or " " "LO" or " "

Vertical Modes

(Applies: 1054;1237-1283) Vertical Modes 4 Vertical Armed mode (cyan) 5 Vertical Capture and Hold mode (green)

DESCRIPTION PITCH HOLD MODE (BASIC MODE) 5 MODE CHANGE 4 IAS MODE (UPPER MODE) PITCH HOLD IAS PITCH HOLD IAS + 7 S VS MODE (UPPER MODE) VS VS ARM

DESCRIPTION ALT MODE (UPPER MODE) 5 MODE CHANGE 4 APP MODE ASSOCIATED WITH AN ILS (COMMON UPPER MODE) ALT GS ALT GS ALT GS ARM + 7 S HOLD ALT SEL GS

DESCRIPTION 5 MODE CHANGE 4 CAPTURE (GREEN) ARM (CYAN) + 7 S HOLD (GREEN) APP MODE ASSOCIATED WITH A GPS L-GS L-GS L-GS L-GS

(Applies: 1096-1160) Vertical Modes 4 Vertical Armed mode (cyan) 5 Vertical Capture and Hold mode (green)

DESCRIPTION PITCH HOLD MODE (BASIC MODE) 5 MODE CHANGE 4 IAS MODE (UPPER MODE) PITCH HOLD IAS PITCH HOLD IAS + 7 S VS MODE (UPPER MODE) VS VS ARM

DESCRIPTION ALT MODE (UPPER MODE) 5 MODE CHANGE 4 APP MODE ASSOCIATED WITH AN ILS (COMMON UPPER MODE) ALT GS ALT GS ALT GS ARM + 7 S HOLD ALT SEL GS

C 1 DESCRIPTION 5 MODE CHANGE 4 CAPTURE (GREEN) ARM (CYAN) + 7 S HOLD (GREEN) APP MODE ASSOCIATED WITH A GPS L-GS L-GS L-GS L-GS VNAV ALT MODE ENGAGED IF A/C IS IN CAPTURE CONDITIONS OF FMS TARGET ALTITUDE. VNAV ALT VNAV ALT VNAV ALT VNAV ALT VNAV IAS MODE ENGAGED TO HOLD AN IAS IN CLIMB. VNAV IAS VNAV IAS VNAV IAS VNAV IAS VNAV VS MODE ENGAGED TO HOLD A VERTICAL SPEED IN DESCENT. VNAV VS VNAV VS VNAV VS VNAV PATH MODE ENGAGED TO ALLOW THE AIRCRAFT TO JOIN AND FOLLOW THE FMS VERTICAL PROFILE. VNAV PATH VNAV PATH VNAV PATH V-FP MODE ENGAGED 2 NM prior TO FAF. V-FP V-FP V-FP V-FP

Common Modes Common Modes 1 2 4 5 - APP (GS & LOC) - GA. APP MODE COMMON MODE GA GS 5 MODE CHANGE + 7 s DESCRIPTION GA GS 4 ARM GA MODE COMMON MODE HDG HOLD LOC 2 MODE CHANGE 1 ARM HOLD GS + 7 s HDG HOLD LOC HOLD LOC LOC GS

AP or YD Engagement 6 AP or YD Engagement

ENGAGEMENT OF THE AP/YD ON THE FGCP (< AP > AND < YD >) ENGAGEMENT OF THE YD ON THE FGCP (< YD >) DISPLAY DESCRIPTION AP YD ITEM 6

FD Bars Display 7 FD Bars Display

FLIGHT DIRECTOR COMMAND BARS DISPLAYED ON THE PFD DISPLAY DESCRIPTION FD ITEM 7 Coupling Selection 8 Coupling Selection

COUPLING ON CAPT SIDE WITH THE CPL P/B ON THE FGCP (< CPL) COUPLING ON F/O SIDE WITH THE CPL P/B ON THE FGCP (CPL >) DISPLAY DESCRIPTION ITEM 8 DUAL COUPLING IN CAT 2 APPROACH (< CPL >) DUAL

TCS Activation 9 TCS Activation

3 ACTIVATION OF THE TCS PUSH BUTTON DISPLAY DESCRIPTION TCS ITEM 9 AP-YD Disengagement, Approach Category Retrogression, AFCS Internal Failure AP/YD Disengagement, Approach Category Retrogression, AFCS Internal Failure 10 AP/YD Disengagement, Approach Category Retrogression, AFCS Internal Failure Message+7S Message Aural alert Display logic Comments AP DISENG Cavalry Charge Red message, reverse video flashing. Reset by the Quick Disconnect P/B. The AP/YD can be disengaged either automatically or manually. YD DISENG YD DISENG Amber message, reverse video flashing. Reset by the Quick Disconnect P/B. The AP/YD can be disengaged either automatically or manually. AP/YD INVALID AP INVALID Amber message, reverse video flashing. When an AFCS Internal failure inhibits AP/YD or YD engagement. Yellow message, steady for 7 seconds. When AP or YD engagement are attempted and an AFCS External failure or condition inhibits AP engagement. Yellow message, steady for 7 seconds. When speed hold engagement are attempted and an AFCS External failure or condition inhibits speed hold engagement. CHECK SPD HLD CHECK SPD HLD Amber message, reverse video flashing. When speed hold is unable to maintain target speed. FD SINGLE CH Amber message, reverse video flashing for 7 seconds, then steady until failure is cleared. When one (and only one) FD channel is lost. FD SINGLE SRC FD SINGLE SRC Amber permanent steady message. When "single AHRS" and/or "single ADC" configuration is active. After an AHRS or ADC failure, the "single AHRS" and/or "single ADC" configuration is selected on the switching control panel. CAT2 INVALID Amber message, reverse video flashing for 7 seconds, then desappears. Loss of CAT2 valid requirements during a CAT2 approach. Triple clicks CAT3 INVALID Amber message, reverse video flashing for 7 seconds, then desappears. Loss of CAT3 valid requirements during a CAT3 approach. Triple clicks

AP DISENG AP/YD DISENG AP/YD DISENG FD SINGLE CH AP INHIBIT YD INHIBIT SPD HLD INHIBIT

Approach Category

(Applies: 1054-1096;1237-1283) 11 Approach Category ILS CAT 1 APPROACH DISPLAY DESCRIPTION ITEM 11 CAT 1 ILS CAT 2 APPROACH CAT 2 LPV APPROACH LPV

3 LP APPROACH LP

(Applies: 1124-1160) 11 Approach Category ILS CAT 1 APPROACH DISPLAY DESCRIPTION ITEM 11 CAT 1 ILS CAT 2 APPROACH CAT 2 LPV APPROACH LPV

3 LP APPROACH LP RNP AR operations: approach, missed approach and departures RNP AR

Unexpected Mode Change, or Problem in Navigation Parameters

(Applies: 1237-1283) 12 Unexpected Mode Change, or Problem in Navigation Parameters

Message+7S Message Aural alert Display logic Comments CHECK NAV SRC Yellow message flashing for 7 s then disappears If the crew try to engage a NAV mode whereas the wrong nav source is selected, or if the navigation source is lost. CHECK NAV SRC Amber message, reverse video flashing for 7 seconds, then steady until failure is cleared by trying to engage another FD mode, or by pressing STBY pb. - If an armed or engaged nav mod dropped off following a nav source change. - If a VOR/LOC nav frequency change induces the current mode loss. - In case of coupling change. Amber message, reverse video flashing for 7 seconds, then steady. If VCP Icing selection disagrees with the actual icing conditions. ADC INVALID Yellow message, flashing for 7 seconds, then disappears. - In case of ADC data miscomparison, the AP/YD is disengaged (disengagement only for discrepancy on CAS and TAS). After clearing the AP/YD DISENG ADC INVALID warning, the FMA displays , associated with CHECK ALT CHECK IAS or on the PFD. - Or in case of loss of ADC redundant sensor indicated by a flag, the AP/YD is disengaged. After clearing the warning, the FMA displays AP/YD DISENG ADC INVALID. ATT INVALID Yellow message, flashing for 7 seconds, then disappears. - In case of AHRS data miscomparison, the AP/YD is disengaged (disengagement only for discrepancy on attitude parameter). After clearing the warning, the FMA displays , associated with AP/YD DISENG ATT INVALID CHECK ATT on PFD if Roll or Pitch angles are not coherent. - Or in case of loss of AHRS redundant sensor indicated by a flag, the AP/YD is disengaged. After clearing the warning, the FMA displays AP/YD DISENG ATT INVALID. HDG INVALID Yellow message, flashing for 7 seconds, then disappears. - In case of AHRS data miscomparison, the FMA displays , HDG INVALID associated with on the PFD & ND, if magnetic headings CHECK HDG are not coherent (No AP/YD disengagement). - Or in case of loss of AHRS redundant sensor indicated by a flag. NAV INVALID Yellow message, flashing for 7 seconds, then disappears. In case of loss of NAV redundant sensor indicated by a flag. SPD AUTO INOP Amber message, reverse video flashing for 7 seconds, then disappears. If AUTO is selected with the "AUTO/MAN" SEL P/B and the speed target from both FMS is not valid. The AUTO speed mode is not available and the speed is automatically switched to MAN (Cyan Speed Target Bug). The Speed Target Bug is automatically synchronized to the current value of A/C speed. SPD AUTO INOP Yellow message flashing for 7 s then disappears. When the ICP AUTO/MAN push-button is pressed while MAN is selected and IAS target from the selected FMS is invalid. EXCESS DEV Red message, reverse video flashing for 7 seconds then steady amber. Excessive deviation on the GS or the LOC. The message on the FMA is associated with the GS or the LOC deviation scale flashing amber to indicate a flight path excusion. Amber message, reverse video flashing for 7 seconds, then steady until failure is cleared by changing AHRS source selection, or by selecting another FD mode, or by pressing STBY pb. When an AHRS failure ( or ) leads to the FD ATT INVALID HDG INVALID mode cancellation. ALT OFF Amber message, reverse video flashing for 7 seconds, then disappears. During Altitude Capture, - When the selected altitude is changed (transition to basic pitch). - When baro correction is changed (transition to basic pitch). STEEP APP Green message steady. When steep approach is selected. AFCS TEST Amber flashing. During the AFCS test (maintenance operation). CHECK NAV SRC CHECK T/O SPEED CHECK T/O SPEED EXCESS DEV FD MODE CHG FD MODE CHG REDUCE SPD Amber message, reverse video flashing for 7 seconds, then steady. High speed protection: see DSC-AUTO FLGHT-SPEED PROTECTION REDUCE SPD MONITOR SPD Amber message, reverse video flashing for 7 seconds, then steady. Low speed protection: see DSC-AUTO FLGHT-SPEED PROTECTION MONITOR SPD Triple click Triple click if Prot Level is activated SPEED SPEED Flashing permanently. Complementary low speed alerting: see DSC-AUTO FLGHT-SPEED PROTECTION Triple click

Message+7S Message Aural alert Display logic Comments VNAV INHIB VNAV INHIB upon any VNAV mode engagement attempted and VNAV option not installed. Yellow message flashing for 7 s then disappears.

Message+7S Message Aural alert Display logic Comments APP INVALID APP INVALID if GPS data failure or loss of LPV capability leads to FD mode engagement inhibition. Yellow message flashing for 7 s then disappears. SELECT VTF SELECT VTF in HDG SEL mode on an attempt to arm LPV modes (P/B APP) before activating the VTF Yellow message flashing for 7 s then disappears.

(Applies: 1096-1160) 12 Unexpected Mode Change, or Problem in Navigation Parameters

Message+7S Message Aural alert Display logic Comments CHECK NAV SRC Yellow message flashing for 7 s then disappears If the crew try to engage a NAV mode whereas the wrong nav source is selected, or if the navigation source is lost. CHECK NAV SRC Amber message, reverse video flashing for 7 seconds, then steady until failure is cleared by trying to engage another FD mode, or by pressing STBY pb. - If an armed or engaged nav mod dropped off following a nav source change. - If a VOR/LOC nav frequency change induces the current mode loss. - In case of coupling change. Amber message, reverse video flashing for 7 seconds, then steady. If VCP Icing selection disagrees with the actual icing conditions. ADC INVALID Yellow message, flashing for 7 seconds, then disappears. - In case of ADC data miscomparison, the AP/YD is disengaged (disengagement only for discrepancy on CAS and TAS). After clearing the AP/YD DISENG ADC INVALID warning, the FMA displays , associated with CHECK ALT CHECK IAS or on the PFD. - Or in case of loss of ADC redundant sensor indicated by a flag, the AP/YD is disengaged. After clearing the warning, the FMA displays AP/YD DISENG ADC INVALID. ATT INVALID Yellow message, flashing for 7 seconds, then disappears. - In case of AHRS data miscomparison, the AP/YD is disengaged (disengagement only for discrepancy on attitude parameter). After clearing the warning, the FMA displays , associated with AP/YD DISENG ATT INVALID CHECK ATT on PFD if Roll or Pitch angles are not coherent. - Or in case of loss of AHRS redundant sensor indicated by a flag, the AP/YD is disengaged. After clearing the warning, the FMA displays AP/YD DISENG ATT INVALID. HDG INVALID Yellow message, flashing for 7 seconds, then disappears. - In case of AHRS data miscomparison, the FMA displays , HDG INVALID associated with on the PFD & ND, if magnetic headings CHECK HDG are not coherent (No AP/YD disengagement). - Or in case of loss of AHRS redundant sensor indicated by a flag. NAV INVALID Yellow message, flashing for 7 seconds, then disappears. In case of loss of NAV redundant sensor indicated by a flag. SPD AUTO INOP Amber message, reverse video flashing for 7 seconds, then disappears. If AUTO is selected with the "AUTO/MAN" SEL P/B and the speed target from both FMS is not valid. The AUTO speed mode is not available and the speed is automatically switched to MAN (Cyan Speed Target Bug). The Speed Target Bug is automatically synchronized to the current value of A/C speed. SPD AUTO INOP Yellow message flashing for 7 s then disappears. When the ICP AUTO/MAN push-button is pressed while MAN is selected and IAS target from the selected FMS is invalid. EXCESS DEV Red message, reverse video flashing for 7 seconds then steady amber. Excessive deviation on the GS or the LOC. The message on the FMA is associated with the GS or the LOC deviation scale flashing amber to indicate a flight path excusion. Amber message, reverse video flashing for 7 seconds, then steady until failure is cleared by changing AHRS source selection, or by selecting another FD mode, or by pressing STBY pb. When an AHRS failure ( or ) leads to the FD ATT INVALID HDG INVALID mode cancellation. When APP mode is not armed 2Nm before FAF during a LPV approach, LNAV mode is disengaged. ALT OFF Amber message, reverse video flashing for 7 seconds, then disappears. During Altitude Capture, - When the selected altitude is changed (transition to basic pitch). - When baro correction is changed (transition to basic pitch). STEEP APP Green message steady. When steep approach is selected. AFCS TEST Amber flashing. During the AFCS test (maintenance operation). CHECK NAV SRC CHECK T/O SPEED CHECK T/O SPEED EXCESS DEV FD MODE CHG FD MODE CHG REDUCE SPD Amber message, reverse video flashing for 7 seconds, then steady. High speed protection: see DSC-AUTO FLGHT-SPEED PROTECTION REDUCE SPD MONITOR SPD Amber message, reverse video flashing for 7 seconds, then steady. Low speed protection: see DSC-AUTO FLGHT-SPEED PROTECTION MONITOR SPD Triple click Triple click if Prot Level is activated SPEED SPEED Flashing permanently. Complementary low speed alerting: see DSC-AUTO FLGHT-SPEED PROTECTION Triple click

Message+7S Message Aural alert Display logic Comments Triple Clicks Amber message flashing for 7 s then disappears. VNAV OFF if VNAV mode is lost because ALT SEL is changed above A/C altitude while in VNAV descent mode OR ALT SEL is changed below A/C altitude while in VNAV climb mode OR FMS target level off changes by more than 60ft due to barometric correction change while VNAV ALT is engaged OR step descent is in progress and ALT SEL is modified after TOD-5min. SELECT LNAV SELECT LNAV on an attempt of arming / engaging VNAV without LNAV engaged or arming / engaging V-FP without LNAV armed/ engaged. VNAV OFF Yellow message flashing for 7 s then disappears. APP INVALID APP INVALID if VNAV flight path mode cannot be engaged due to FMS Selected approach type data failure or due to selected FMS Flight area data failure Yellow message flashing for 7 s then disappears. APP INHIB APP INHIB upon VNAV flight path mode attempted and approach is not enabled by FMS (no FAF in active flight plan) OR inconsistent FMS flight phase Yellow message flashing for 7 s then disappears.

E 1 Message+7S Message Aural alert Display logic Comments Yellow message flashing for 7 s then disappears. - If the crew wants to descend manually, VS mode can be used - If the crew wants to descend automatically, wait until entering in new TOD -5'area then use VNAV pushbutton or perform a Vertical direct to any waypoint (available upon vertical revision on MCDU). This action will recompute a new vertical profil and upon VNAV pushbutton press may allow engaging VNAV PATH Mode. NAV INVALID CHECK ALT SEL CHECK ALT SEL if VNAV descent mode cannot be engaged because ALT SEL is above A/C, OR VNAV climb mode cannot be engaged because ALT SEL is below A/C, OR ALT capture is in progress Yellow message flashing for 7 s then disappears.

Message+7S Message Aural alert Display logic Comments APP INVALID APP INVALID if GPS data failure or loss of LPV capability leads to FD mode engagement inhibition. Yellow message flashing for 7 s then disappears. SELECT VTF SELECT VTF in HDG SEL mode on an attempt to arm LPV modes (P/B APP) before activating the VTF Yellow message flashing for 7 s then disappears.

(Applies: 1054) 12 Unexpected Mode Change, or Problem in Navigation Parameters

Message+7S Message Aural alert Display logic Comments CHECK NAV SRC Yellow message flashing for 7 s then disappears If the crew try to engage a NAV mode whereas the wrong nav source is selected, or if the navigation source is lost. CHECK NAV SRC Amber message, reverse video flashing for 7 seconds, then steady until failure is cleared by trying to engage another FD mode, or by pressing STBY pb. - If an armed or engaged nav mod dropped off following a nav source change. - If a VOR/LOC nav frequency change induces the current mode loss. - In case of coupling change. Amber message, reverse video flashing for 7 seconds, then steady. If VCP Icing selection disagrees with the actual icing conditions. ADC INVALID Yellow message, flashing for 7 seconds, then disappears. - In case of ADC data miscomparison, the AP/YD is disengaged (disengagement only for discrepancy on CAS and TAS). After clearing the AP/YD DISENG ADC INVALID warning, the FMA displays , associated with CHECK ALT CHECK IAS or on the PFD. - Or in case of loss of ADC redundant sensor indicated by a flag, the AP/YD is disengaged. After clearing the warning, the FMA displays AP/YD DISENG ADC INVALID. ATT INVALID Yellow message, flashing for 7 seconds, then disappears. - In case of AHRS data miscomparison, the AP/YD is disengaged (disengagement only for discrepancy on attitude parameter). After clearing the warning, the FMA displays , associated with AP/YD DISENG ATT INVALID CHECK ATT on PFD if Roll or Pitch angles are not coherent. - Or in case of loss of AHRS redundant sensor indicated by a flag, the AP/YD is disengaged. After clearing the warning, the FMA displays AP/YD DISENG ATT INVALID. HDG INVALID Yellow message, flashing for 7 seconds, then disappears. - In case of AHRS data miscomparison, the FMA displays , HDG INVALID associated with on the PFD & ND, if magnetic headings CHECK HDG are not coherent (No AP/YD disengagement). - Or in case of loss of AHRS redundant sensor indicated by a flag. NAV INVALID Yellow message, flashing for 7 seconds, then disappears. In case of loss of NAV redundant sensor indicated by a flag. SPD AUTO INOP Amber message, reverse video flashing for 7 seconds, then disappears. If AUTO is selected with the "AUTO/MAN" SEL P/B and the speed target from both FMS is not valid. The AUTO speed mode is not available and the speed is automatically switched to MAN (Cyan Speed Target Bug). The Speed Target Bug is automatically synchronized to the current value of A/C speed. SPD AUTO INOP Yellow message flashing for 7 s then disappears. When the ICP AUTO/MAN push-button is pressed while MAN is selected and IAS target from the selected FMS is invalid. EXCESS DEV Red message, reverse video flashing for 7 seconds then steady amber. Excessive deviation on the GS or the LOC. The message on the FMA is associated with the GS or the LOC deviation scale flashing amber to indicate a flight path excusion. Amber message, reverse video flashing for 7 seconds, then steady until failure is cleared by changing AHRS source selection, or by selecting another FD mode, or by pressing STBY pb. When an AHRS failure ( or ) leads to the FD ATT INVALID HDG INVALID mode cancellation. When APP mode is not armed 2Nm before FAF during a LPV approach, LNAV mode is disengaged. ALT OFF Amber message, reverse video flashing for 7 seconds, then disappears. During Altitude Capture, - When the selected altitude is changed (transition to basic pitch). - When baro correction is changed (transition to basic pitch). STEEP APP Green message steady. When steep approach is selected. AFCS TEST Amber flashing. During the AFCS test (maintenance operation). CHECK NAV SRC CHECK T/O SPEED CHECK T/O SPEED EXCESS DEV FD MODE CHG FD MODE CHG REDUCE SPD Amber message, reverse video flashing for 7 seconds, then steady. High speed protection: see DSC-AUTO FLGHT-SPEED PROTECTION REDUCE SPD MONITOR SPD Amber message, reverse video flashing for 7 seconds, then steady. Low speed protection: see DSC-AUTO FLGHT-SPEED PROTECTION MONITOR SPD Triple click Triple click if Prot Level is activated SPEED SPEED Flashing permanently. Complementary low speed alerting: see DSC-AUTO FLGHT-SPEED PROTECTION Triple click

Message+7S Message Aural alert Display logic Comments APP INVALID APP INVALID if GPS data failure or loss of LPV capability leads to FD mode engagement inhibition. Yellow message flashing for 7 s then disappears. SELECT VTF SELECT VTF in HDG SEL mode on an attempt to arm LPV modes (P/B APP) before activating the VTF Yellow message flashing for 7 s then disappears.

Message+7S Message Aural alert Display logic Comments VNAV INHIB VNAV INHIB upon any VNAV mode engagement attempted and VNAV option not installed. Yellow message flashing for 7 s then disappears. Trim Status 13 Trim Status COMMENTS AP PITCH TRIM FAIL MESSAGE AP PITCH TRIM FAIL MESSAGE +7 S AURAL ALERT DISPLAY LOGIC DISPLAYED WHEN THE AFCS IS NOT ABLE TO COMMAND THE PITCH TRIM AND THE AP IS ENGAGED YAW AUTO TRIM FAIL YAW AUTO TRIM FAIL DISPLAYED WHEN THE AFCS IS NOT ABLE TO COMMAND THE YAW TRIM AND THE AP IS ENGAGED (ONLY IF RUDDER AUTOTRIM) PITCH MISTRIM PITCH MISTRIM WHEN THE PITCH SERVO MOTOR REACHES A TORQUE VALUE THRESHOLD RETRIM R WING DN RETRIM R WING DN RETRIM L WING DN RETRIM L WING DN WHEN THE AILERON SERVO MOTOR REACHES A FIRST TORQUE VALUE THRESHOLD AILERON MISTRIM AILERON MISTRIM WHEN THE AILERON SERVO MOTOR REACHES A SECOND TORQUE VALUE THRESHOLD RUDDER MISTRIM RUDDER MISTRIM WHEN THE RUDDER SERVO MOTOR REACHES A SECOND TORQUE VALUE THRESHOLD SGL CHIME AMBER MESSAGE, REVERSE VIDEO FLASHING 7 SECONDS, THEN STEADY NIL SGL CHIME

3 NOTE: IN CASE OF YAW AUTO TRIM FAILURE THE ALERT MESSAGE WILL BE DISPLAYED APM Message 14 APM Message Refer to DSC.30.8.2.1 APM Indications Icing 15 Icing Refer to DSC.30.2.2.1 Ice Detector Panel

Auto Flight: 2.6 Primary Flight Display (PFD)

8 2 1 MDA 000 HDG SEL LO ICING DGD PERF HLD SPD PITCH HOLD 2 1 6 6 2 1 RNG WX WAIT 40.5 012 CRS VOR2 29.20 / NM TA ONLY BELOW ° ADF2 1250.5 A ILS1 VOR1_ID 40.5 NM M 999 15315 FL 20 157 60 40 80M 20 AHRS1 DEGRADED 20 10 10 DH 900 10 10 TCS GS RETRIM ROLL R WING DN CAT1 SPD AUTO INOP FD SINGLE CH 010 G 1013 AHRS1 ADC1 I 99 DH TAS 250 GS 200 000° HDG °/ 80 355 MSG TERM A H OFST 110.30 H +10.3 ° T TERR ON XPDR2 STBY -10 -9 2750 G-VAR 20 20 2 3 7 5 6 7 3 6 4 4 AP FD DUAL 200 220 240 180 195 206 C H E C K I A S FR V2 F 141 1 Flight Director Command bars (Green) Display computed commands to capture and maintain a desired flight path. 2 Speed bug & speed read out - Cyan bug when selected manually. On ICP, the SPD TGT has to be in MAN and selection is done with the speed knob. - Magenta bug when managed by the FMS On ICP, the SPD TGT has to be in AUTO, and the speed is computed by the FMS. 3 ALT Bug & Altitude Read Out On the FGCP, the cyan bug and the readout is set with the ALT SEL knob. The numeric ALT SEL readout is permanently displayed. 4 VS Bug & VS Read Out On the FGCP, the cyan bug and read out are set with the Pitch wheel when the VS mode is selected.

5 HDG Bug & HDG Read Out On the FGCP, the cyan bug is set with the heading knob. 6 NAV Course Pointer/Deviation & Readout - Cyan course when selected manually. (Mode NAV and APP) On the FGCP, when the NAV source selector is on V/ILS 1 or 2, the course pointer is set with the CRS knob. - Magenta course when managed by the FMS (Mode LNAV) On the FGCP, when the NAV source selector is on FMS 1 or 2, the desired track indication is computed by the FMS. 7 Minimum Descent Altitude (MDA) The MDA is set with the ICP. This MDA is displayed by two horizontal amber lines directly on the altimeter scale. At MDA + 80 ft, the "Approaching Minimum" aural alert is generated. At MDA, the "Minimum, Minimum" aural alert is generated. 8 Decision Height (DH) - (CAT II) Linked to the radioaltimeter information, an aural and visual alert inform the crew that the decision height is reached. A DH alert is displayed on the PFD, associated with the following auto callouts: - “APPROACHING DECISION HEIGHT”, at DH + 100 ft - “DECISION HEIGHT”, at DH. Note For more information about MDA/DH callouts Refer to DSC.34.12.1.2.1.6 Mode 6.

DH on PFD PFD

99 MDA 10 20 10 20 10 10 I DH 900 DH 1

Auto Flight: 3 ELECTRICAL SUPPLY

Auto Flight: 3.01 Electrical Supply

EQUIPMENT DC BUS SUPPLY (C/B) AC BUS SUPPLY (C/B) Autopilot Servo Motor (Roll, Yaw, Pitch) DC STBY BUS (on overhead panel C/B PITCH SERVO, C/B YAW SERVO, C/B ROLL SERVO) NIL FGCP (Channel 1 & 2) DC EMER BUS (on overhead panel C/B FGCP CHAN1/IOM-AP1) DC ESS BUS (on overhead panel C/B FGCP CHAN2/IOM-AP2) NIL Index Control Panel F/O DC BUS 2 (Flight SPLY) (on overhead panel C/B ADC 2 FLT SPLY / ICP F/O FLT SPLY) DC EMER BUS (Ground SPLY) (on overhead panel C/B ADC 2 FLT SPLY / ICP F/O GND SPLY) NIL Index Control Panel CAPT DC EMER BUS (on overhead panel C/B ADC 1 ICP CAPT EMER SPLY) NIL Yaw Dynamometric Rod DC EMER BUS NIL Quick release DC EMER BUS (on lateral panel C/B L NORM & STBY PITCH TRIM & C/B RUD TLU MAN CTL) NIL FCTL Power Trim Box DC EMER BUS (on lateral panel C/B L NORM & STBY PITCH TRIM C/B RUD TLU MAN CTL) NIL CAC 2 DC ESS BUS (CAC Card: CPM2) (on overhead panel C/B CPM 2 / IOM--S 2) DC ESS BUS (CAC Card : IOM-AP2) (on overhead panel C/B FGCP CHAN2/IOM-AP2) NIL

EQUIPMENT DC BUS SUPPLY (C/B) AC BUS SUPPLY (C/B) CAC 1 DC EMER BUS (CAC Card : CPM1) (on overhead panel C/B CPM 1 / IOM-S 1) (CAC Card : IOM-AP1) (on overhead panel C/B FGCP CHAN1/IOM--AP1) NIL

Auto Flight: 4 SYSTEM MONITORING

Auto Flight: 4.1 AILERON MISTRIM-Alert

CONDITION VISUAL AURAL When aileron servo motor reaches a second torque value threshold - OR - Not appropriate ROLL trim input - OR - Excessive YAW trim input - MC light flashing amber - AILERON MISTRIM amber message on EWD - AILERON MISTRIM amber message on FMA (Amber message, reverse video flashing 7 seconds, then steady) - Cyan arrow appears on EWD SC

Auto Flight: 4.2 EXCESSIVE LATERAL TRIM REQUIRED-Alert

CONDITION VISUAL AURAL Excessive lateral trim required NIL NIL

Auto Flight: 4.3 ABNORMAL FLIGHT CHARACTERISTICS IN ROLL-Alert

CONDITION VISUAL AURAL When aileron servo motor reaches a second torque value threshold - OR - Not appropriate ROLL trim input - OR - Excessive YAW trim input - MC light flashing amber - AILERON MISTRIM amber message on EWD - AILERON MISTRIM amber message on FMA (Amber message, reverse video flashing 7 seconds, then steady) SC

Auto Flight: 4.4 PITCH MISTRIM-Alert

CONDITION VISUAL AURAL AP trim threshold limit is exceeded - MC light flashing amber - PITCH MISTRIM amber message on EWD - PITCH MISTRIM amber message on FMA (Amber message, reverse video flashing 7 seconds, then steady) - The pointer of the Pitch Trim Position Indicator becomes amber on EWD SC

Auto Flight: 4.5 AP PITCH TRIM FAIL-Alert

CONDITION VISUAL AURAL AFCS PITCH Autotrim function failure - MC light flashing amber - AP PITCH TRIM amber message on EWD - AP PITCH TRIM FAIL amber message on FMA (Amber message, reverse video flashing 7 seconds, then steady) SC

Auto Flight: 4.6 RUDDER MISTRIM-Alert

CONDITION VISUAL AURAL When rudder servo motor reaches a second torque value threshold - MC light flashing amber - RUDDER MISTRIM amber message on EWD - RUDDER MISTRIM amber message on FMA (Amber message, reverse video flashing 7 seconds, then steady) - The pointer of the Yaw Trim Position Indicator becomes amber on EWD SC

Auto Flight: 4.7 YAW AUTOTRIM FAILURE-Alert

CONDITION VISUAL AURAL AFCS YAW Autotrim function failure. - MC light flashing amber - YAW AUTOTRIM amber message on EWD - YAW AUTO TRIM FAIL amber message on FMA (Amber message, reverse video flashing 7 seconds, then steady) - The pointer of the Yaw Trim Position Indicator becomes amber on EWD SC

Auto Flight: 4.8 FGCP SINGLE CHANNEL-Alert

CONDITION VISUAL AURAL One FGCP channel is lost. - MC light flashing amber - FGCP SGL CH amber message on EWD SC

Auto Flight: 4.9 FGCP LOSS-Alert

CONDITION VISUAL AURAL All FGCP channel are lost. - MC light flashing amber - FGCP LOSS amber message on EWD SC

Auto Flight: 4.10 YAW DAMPER SINGLE SOURCE-Alert

CONDITION VISUAL AURAL AHRS or ADC in single source and IAS is below 160 kt. - MC light flashing amber - YD DEGRADED amber message on EWD SC

Auto Flight: 4.11 ENHANCED LOC CAPTURE DEGRADED POSITION-Alert

CONDITION VISUAL AURAL The enhanced LOC capture mode is not available because the accuracy of the aircraft estimated position error (EPE) is not sufficient. - MC light flashing amber - ENHANCED LOC* amber message on EWD SC

Auto Flight: 4.12 ENHANCED LOC CAPTURE INCORRECT COURSE-Alert

CONDITION VISUAL AURAL FGCP course and FMS NAV database course value mismatche. - MC light flashing amber - ENHANCED LOC* amber message on EWD SC

Auto Flight: 4.13 ENHANCED BC CAPTURE DEGRADED POSITION-Alert

CONDITION VISUAL AURAL The enhanced BC capture mode is not available because the accuracy of the aircraft estimated position error (EPE) is not sufficient. - MC light flashing amber - ENHANCED BC* amber message on EWD SC

Auto Flight: 4.14 ENHANCED BC CAPTURE INCORRECT COURSE-Alert

CONDITION VISUAL AURAL FGCP course and FMS NAV database course value mismatches. - MC light flashing amber - ENHANCED BC* amber message on EWD SC

Auto Flight: 5 LATERAL MAINTENANCE PANEL

Auto Flight: 5.01 LH Maintenance Panel

Not applicable

Auto Flight: 6 SCHEMATICS

Auto Flight: 6.01 Schematics

(Applies: 1096-1283) PFD 1 MFD 1 MFD 2 PFD 2 SEL AUTO/MAN SPD TGT BARO SET IN HG HPA PUSH STD DH MDA ICP 1 SEL AUTO/MAN SPD TGT BARO SET IN HG HPA PUSH STD DH MDA ICP 2 CAC 1 CAC 2 GPS 1 NAV 1 AHRS 1 ADC 1 EEC 1 MCDU 1 GPS 2 NAV 2 AHRS 2 ADC 2 EEC 2 MCDU 2 FGCP FMA FMA APAU PITCH APAU ROLL AYAU PITCH TRIM BOX AFDX YAW TRIM BOX

 [ICP 1]   [PFD 1] [MFD 1] [MFD 2] [PFD 2]   [ICP 2]
    |         |       |       |       |          |
    +---------+-------+-- AFDX / display network-+
                          |
                    +-----+-----+
                    |           |
                  [CAC 1]     [CAC 2]
                    |  \       /  |
 ADC 1 / AHRS 1 / NAV 1      ADC 2 / AHRS 2 / NAV 2
                    |           |
               MCDU 1/2, AP pitch actuator, AP yaw actuator,
               pitch-trim and yaw-trim backup/control paths

Auto Flight: 1 Purpose

The Yaw Damper (YD) provides yaw damping, turn coordination and rudder trim function. To achieve these functions, AFCS computers (CAC 1/2) and AP yaw actuator are used. The AP provides the following: - Stabilizing the aircraft around its center of gravity while holding pitch attitude and heading, wing level, or bank angle (AP in basic mode) - Flying automatically any upper or basic mode or any mode except GO AROUND mode which must be flown manually only.

Auto Flight: 2 Autopilot Engagement

When the AP is engaged, the pitch, roll, and yaw actuators are connected to the flight controls, the pitch AUTO trim and yaw AUTO trim function are activated. - Engagement with no vertical upper mode selected: The AP flies current pitch attitude. This is the basic vertical mode (PITCH HOLD, displayed in green). Pitch wheel and TCS can be used to modify the pitch attitude. - Engagement with no lateral upper mode selected: Depending of the conditions at engagement, the AP levels wings and then maintains wing level (WING LVL, displayed in green), or maintains the current heading (HDG HOLD, displayed in green), or maintains the current bank angle (ROLL HOLD, displayed in green). These are the basic lateral mode. TCS pb may be used (Refer to Control Wheel). - Engagement with a lateral or vertical armed upper mode selected: the AP flies basic mode until the armed mode becomes active - Engagement with a lateral and/or vertical active upper mode selected: the AP maneuvers to fly to zero the FD command bars - If AP is engaged while the vertical FD orders are not followed, the reversion is done in pitch hold mode (AP basic mode).

Auto Flight: 3 Autopilot Disengagement

AP can be disengaged manually or automatically. Manual disengagement is achieved by action on one of the following devices: - Quick disconnect pb on control wheel - Action on pitch trim (normal or STBY) - AP pb on FGCP - YD pb on FGCP - GA pb on PL - Force of pilot on the pedals over 300 N (66 lb) - Force of pilot on the control column (pitch axis) over 100 N (22 lb)

Automatic disengagement occurs when: - One of the engagement conditions of the AP and/or YD is no longer met - Stall warning indicator threshold is achieved Note AP and FD displays and active modes are disengaged automatically upon stall warning activation. - There is a disagreement between the two AHRS, or between the two ADCs - There is a mismatch between the two pitch trims - There is a failure of one AHRS, or one ADC.

Auto Flight: 4 Manual Disengagement

• Action on the AP pb on the FGCP, or quick disconnect pb on each control column, or GA mode activation, or STBY or NORMAL pitch trim sw activation or effort on control column disengage the AP function without disengaging the YD function. The AP green arrows turn off, AP DISENG is displayed on FMA (white on red message reverse video) and the “cavalry charge” aural warning is generated
• Action on the quick disconnect pb (second time) clears the aural warning and message Note If a failure occurs, the PITCH TRIM FAIL, PITCH MISTRIM, AILERON MISTRIM, RUDDER MISTRIM, or YAW AUTO TRIM message is displayed on the FMA. The flight crew must disengage AP and manually fly the aircraft.
• Action on the YD pb on the FGCP, or an effort on pedals disengages the AP and YD (if engages together). AP and YD green arrow turn off. AP/YD DISENG is displayed on FMA (displayed in white on red message reverse video) and the “cavalry charge” aural warning is generated. Action on the quick disconnect pb (second time) clears the aural warning and message
• The YD (if only engaged). The YD green arrows turn off. YD DISENG is displayed on FMA (displayed in black on amber message reverse video). Action on the quick disconnect pb (second time) clears the message.

Auto Flight: 5 Automatic Disengagement

The warnings and messages are the same as those which occur in case of manual disengagement but the AP DISENG, AP/YD DISENG or YD DISENG messages are flashing. Action on quick disconnect pb clears warnings and messages. Note If EWD displays PITCH TRIM ASYM, AP automatically disengages and cannot be reengaged.

Auto Flight: 6 AP-YD Monitoring Recovery

When a monitored failure is detected, AP and/or YD is disengaged. If the flight crew clears messages displayed on FMA (by using quick disconnect pb) the AP computer will attempt a “monitor recovery”. The AP/YD can be again engaged. If initial failure condition still exists, AP/YD is disengaged again.

Auto Flight: 1 Function

The purpose of the FD is to provide information to the flight crew through the command bars on the PFD to enable a manual guidance of the aircraft: - In pitch axis if a vertical active mode is selected - In roll axis if a lateral active mode is selected. The FD commands are satisfied when the FD bars remain centered on the PFD. If no vertical active mode is engaged, the corresponding command bar will revert to PITCH HOLD. If no lateral active mode is engaged, the corresponding command bar will according to situation revert to HDG HOLD, ROLL HOLD or WING LVL. In addition, the two bars can be removed by acting on the FD pb on the FGCP. The following modes are available: - Vertical modes: ALT SEL, ALT, VS, IAS, VNAV (if VNAV capability available) - Lateral modes: HDG SEL, NAV, BC - Common modes: APP (lateral and vertical guidance for approach) GA. Some modes have an initial arm status before becoming active. Their active phase is divided into a capture phase followed by a track or hold phase. When AP is engaged, it automatically follows the FD commands. If no FD active mode is selected, the system flies basic AP mode (Refer to YAW DAMPER).

Auto Flight: 2 Mode Selection

Mode selection is achieved by action on the corresponding pb on the FGCP except for ALT SEL mode and GO AROUND mode: - ALT SEL mode is automatically armed - Relevant VNAV modes are activated as soon as VNAV pb (on FGCP) is pressed (if VNAV capability available) - Concerning GO AROUND mode, Refer to DSC.22.4.2.5.4 Go-around Mode (FD Mode Only). Note Simultaneous armed status modes is limited to one lateral mode and two vertical modes: one primary vertical mode and ALT SEL as a secondary vertical mode.

Auto Flight: 3 Activation of Armed Modes

Only one lateral and one vertical mode can be activated simultaneously. If two vertical modes are armed, the first which meets the capture conditions becomes first active. The second remains armed.

Auto Flight: 4 Mode Disengagement

Action on the pb of an armed or active mode on the FGCP disengages that mode. Action on either GA pb on the PL’s disengages all other armed or active mode (except LNAV if engaged before GA). Action on the STBY pb on the FGCP disengages all armed and active modes. ALT SEL mode will rearm automatically only if AP is engaged or if a FD mode is selected again and if aircraft flies toward the selected altitude. When a vertical (or lateral) mode becomes active, the previously active vertical (or lateral) mode is automatically disengaged. FD display and active modes are disengaged automatically upon stall warning activation.

Auto Flight: 5 Flight Guidance Displays and Annunciations

• The HSI / ND displays navigation information: The FD uses information from the coupled HSI/ND which is selected through the CPL pb on the FGCP
• Heading bug: The heading bug is controlled by the single HDG knob. The heading error between actual heading and selected heading as displayed on the coupled HSI/ND is sent to the FD
• Course pointer: The course pointer of each HSI/ND is controlled by the associated COURSE knob (except LNAV mode). The course error as displayed on the coupled HSI / ND is sent to the FD
• Deviations: Deviations displayed on the coupled HSI/ND and used by the FD are as follows, depending on the selected navigation source: o In lateral: VOR, LOC, LNAV or, L-LOC (if LPV capability available) o In vertical: GS, VNAV or L-GS (if VNAV or LPV capability available).
• The ADI displays guidance information through the pitch and roll command bars
• The FMA provides mode status annunciations : o Lateral armed mode status is displayed in cyan (VOR, NAV, BC) o Vertical armed mode status is displayed in cyan (ALT SEL, GS, VNAV IAS, VNAV ALT, ALT SEL/V-FP, V-FP, LGS)) o Lateral active mode status is displayed in green (VOR, LOC, BC, LNAV, HDG SEL, HGD HOLD, ROLL HOLD, WING LVL, L-LOC) o Vertical active mode status is displayed in green (IAS, VS, ALT, GS, PITCH HOLD, VNAV IAS, VNAV ALT, VNAV VS, VNAV PATH, V-FP, L-GS, PROT LEVEL) o At mode change, the mode annunciation is surrounded with a green box for 7 s o During capture phase, a star is added to the mode annunciation on FMA.

Auto Flight: 1 SYSTEM OPERATION

Auto Flight: 1.1 AFCS Coupling

(Applies: 1124-1160) CAC 1 & CAC 2 (AFCS computers) receive data from both ADC and both AHRS. The Autopilot and Yaw damper functions use data from both ADC and both AHRS, and the FD use data from the selected sources. This selection is achieved by the CPL pb on the FGCP. At power up, left side is coupled. The coupled side is indicated by lighting of the corresponding arrow at each side of the CPL pb and displayed in green on the FMA (“<-- -- “, “-- -->“). In case of failure on either side despite of the coupling (AHRS or ADC failed, AHRS’s or ADC’s miscomparison), AP/YD are disengaged. In this case the AP/YD can be reengaged with a “single AHRS” or “single ADC” by selecting the operative source, with the dedicated switching source pb on the switching control panel. During ILS approach only: DUAL CPL automatically occurs after LOC and GS track phase has begun if both NAV receivers are tuned to ILS. In DUAL CPL both arrows come on, “DUAL” is on FMA, and both NAV receivers are coupled to the AFCS computers which uses average data for guidance computation. When the APP mode is manually cancelled, the FD remains coupled to the side selected prior to dual coupling. Excess DEV monitoring uses ILS data from both sources (CAT II approach). During RNP AR procedures (Departure, approach and missed approach): DUAL CPL automatically occurs before RNP AR operations. In DUAL CPL arrows come on, “DUAL” is on FMA, and both FMS are coupled to the AFCS computers which uses average data for guidance computation. When the RNP AR operations end, the FD remains coupled to the side selected prior to dual coupling.

(Applies: 1054-1096;1237-1283) CAC 1 & CAC 2 (AFCS computers) receive data from both ADC and both AHRS. The Autopilot and Yaw damper functions use data from both ADC and both AHRS, and the FD use data from the selected sources. This selection is achieved by the CPL pb on the FGCP. At power up, left side is coupled. The coupled side is indicated by lighting of the corresponding arrow at each side of the CPL pb and displayed in green on the FMA (“<-- -- “, “-- -->“). In case of failure on either side despite of the coupling (AHRS or ADC failed, AHRS’s or ADC’s miscomparison), AP/YD are disengaged. In this case the AP/YD can be reengaged with a “single AHRS” or “single ADC” by selecting the operative source, with the dedicated switching source pb on the switching control panel. During ILS approach only: DUAL CPL automatically occurs after LOC and GS track phase has begun if both NAV receivers are tuned to ILS (same frequency), both identical courses and RA below 1 200 ft. In

DUAL CPL both arrows are lighted, DUAL is displayed on FMA, and both NAV receivers are coupled to the AFCS computers which uses average data for guidance computation. When the APP mode is manually cancelled, the FD remains coupled to the side selected prior to dual coupling. Excess DEV monitoring uses ILS data from both sources (CAT II approach).

Auto Flight: 2 AUTO PILOT - FLIGHT DIRECTOR MODES

Auto Flight: 2.1 GENERAL

Auto Flight: 2.1.01 General

(Applies: 1054-1096;1237-1283) 1) Reduced Bank Angle Function In all lateral modes, this function selects automatically the bank angle limit (High or Low bank). Selection of either value is made by the AFCS computer by comparison between current aircraft speed and VmHB. LO BANK is selected if IAS < VmHB or RA < 1 000 ft HI BANK is selected if IAS > VmHB + 5 and RA > 1 100 ft The selected bank angle is displayed on the FMA by the green message “LO". - If nothing is displayed: bank angle maximum value 27 ° - If “LO" is displayed: bank angle maximum value 15 °. This limit bank angle is also displayed on the ADI by two green ticks: - For LO BANK:

20 20 - For HI BANK:

20 20

(Applies: 1124-1160) 1) Reduced Bank Angle Function In all lateral modes, this function selects automatically the bank angle limit (High or Low bank). Selection of either value is made by the AFCS computer by comparison between current aircraft speed and VmHB. LO BANK is selected if IAS < VmHB or RA < 1 000 ft HI BANK is selected if IAS > VmHB + 5 and RA > 1 100 ft The selected bank angle is displayed on the FMA by the green message “LO". - If nothing is displayed: bank angle maximum value 27 ° - If “LO" is displayed: bank angle maximum value 15 °. This limit bank angle is also displayed on the ADI by two green ticks: - For LO BANK:

20 20 - For HI BANK:

20 20 2) Additional information on PBN operations Specific logics for LO/HI bank angle management are implemented for RNP AR procedures. LO BANK is selected if IAS < VmHB or RA < 400 ft HI BANK is selected if IAS > VmHB + 5 and RA > 500 ft

Auto Flight: 2.2 BASIC MODES

Auto Flight: 2.2.01 Basic Modes

The basic modes are engaged by the AP pb on the FGCP, if no FD mode is active before AP engagement. The autopilot basic modes are: - Pitch hold (PITCH HOLD green on FMA) on vertical axis - Heading hold (HDG HOLD green on FMA), Wing level (WING LVL, green on FMA), and Roll hold (ROLL HOLD green on FMA) on lateral axis. Note If AP engaged in basic mode only, the Flight Director cross bars will be displayed. Vertical Basic Mode Pitch hold (PITCH HOLD green on FMA). The pitch basic mode enables to maintain the pitch attitude at engagement or bring it back to +15 ° or -11 ° limit value. Then the pitch value, can be changed and held within the limits, with the TCS or the pitch wheel. Lateral Basic Mode - If the roll angle is less than 3 ° for more than 10 s, at mode activation, the current heading is maintained (HDG HOLD green on FMA) despite of the heading bug - If the roll angle is inferior to 6 ° at mode activation: the aircraft returns to null bank angle with activation of the wing level basic mode (WING LVL, green on FMA), then when bank angle is less than 3 ° confirmed for 10 s, the heading hold basic mode (HDG HOLD, green on FMA) is activated. - If roll angle is superior to 6 ° at activation, the autopilot holds the current bank angle (ROLL HOLD green on FMA) - If roll angle is superior to the limit (+/-15 ° or +/-27 ° depending on the speed – –> Low bank/ High bank), the aircraft returns and holds the limit bank angle (ROLL HOLD green on FMA). The bank angle can be changed and hold with the TCS, within the limits of +/-50 °, the autopilot is automatically disengaged if bank angle is greater than 50 °.

HDG HOLD FGCP FMA NOTE: ITALIC TEXT INDICATES THE REAL COLORS 33 N 3 6 30 W E 24 12 21 15 S ALT IAS VS YD SPD HLD CPL FD ALT SEL NAV SOURCE COURSE V/ILS 2 V/ILS 1 FM 2 FM 1 AP HEADING 270° HOLD AT AP ENGAGEMENT ON THE FGCP, THE AUTOPILOT HOLDS THE CURRENT HEADING DESPITE OF THE HEADING BUG. HDG HOLD MODE IS ACTIVATED. HDG HOLD ROLL HOLD FGCP FMA (GREEN BOXED) ALT IAS VS YD SPD HLD CPL FD ALT SEL NAV SOURCE COURSE V/ILS 2 V/ILS 1 FM 2 FM 1 AP ROLL HOLD AT AP ENGAGEMENT, AS THE BANK ANGLE IS BETWEEN 6° AND 27°, THE ROLL HOLD MODE IS ACTIVATED. ROLL HOLD (GREEN) AFTER 7s 10 10 10 20 20 30 30 10 6°< BANK ANGLE < 27° WING LEVEL FGCP FMA (GREEN BOXED) ALT IAS VS YD SPD HLD CPL FD ALT SEL NAV SOURCE COURSE V/ILS 2 V/ILS 1 FM 2 FM 1 AP WING LEVEL / HDG HOLD WING LEVEL (GREEN) AFTER 7s 10 10 10 10 20 20 30 30 BANK ANGLE < 6° HDG HOLD FMA (GREEN BOXED) HDG HOLD (GREEN) AFTER 7s 10 10 10 10 20 20 30 30 BANK ANGLE < 3° AT AP ENGAGEMENT, AS THE BANK ANGLE IS LESS THAN 6°, THE WING LEVEL MODE IS ACTIVATED. THEN WHEN BANK ANGLE IS LESS THAN 3° CONFIRMED FOR 10s, THE HDG HOLD MODE IS ACTIVATED. PITCH HOLD FGCP FMA (GREEN BOXED) ALT IAS VS YD SPD HLD CPL FD ALT SEL NAV SOURCE COURSE V/ILS 2 V/ILS 1 FM 2 FM 1 AP PITCH HOLD PITCH HOLD (GREEN) AFTER 7s AT AP ENGAGEMENT, THE CURRENT PITCH ANGLE (BETWEEN ± 15°) IS MAINTAINED. THE PITCH HOLD MODE IS ACTIVATED. 10 10 10 10 20 20 -15° < PITCH ANGLE < 15° 20 20 30 30 LATERAL MODE VERTICAL MODE 20 20 20 20 20 20 (GREEN BOXED) HDG HOLD (GREEN) AFTER 7s

Auto Flight: 2.3 VERTICAL MODES

Auto Flight: 2.3.1 Altitude Select Mode

ALT SEL mode is automatically armed when the aircraft is climbing or is descending toward the selected altitude except after action on the STBY pb. In this case, ALT SEL mode rearms only if AP is engaged or if a FD mode is selected, in addition to the previous conditions. ARM PHASE 1 4 The ALT SEL armed mode is annunciated by: - A cyan ALT SEL message on the FMA - A cyan bug and an altitude selected read out on the PFD altimeter. VS HOLD, IAS HOLD or PITCH HOLD modes can be used to fly to the selected altitude. This altitude is selected by means of the ALT SEL knob on the FGCP. CAPTURE PHASE 2 When approaching the preselected altitude, the system automatically switches to the ALT SEL CAPTURE mode and the previous vertical mode is cancelled. A command is generated to a symptomatically capture the selected altitude. ALT SEL CAPTURE is annunciated by: - A green and boxed ALT (the box for mode change and the star for capture) - A green ALT after 7 s. Note The ALT OFF amber message appears during Altitude Capture. - When the selected altitude is changed (transition to basic PITCH HOLD mode) - When BARO correction is changed (transition to basic PITCH HOLD mode). HOLD PHASE 3 When the desired altitude is reached, the ALT SEL CAPTURE mode is automatically cancelled and ALT HOLD mode is automatically selected. The ALT HOLD mode is annunciated on the FMA by a green ALT. During the three phases (ALT SEL ARM, ALT SEL CAPTURE, ALT HOLD), a GS capture overrides the altitude mode.

1 2 4 3 FGCP ALT FMA (GREEN BOXED) IAS ALT FMA (GREEN) NOTE: ITALIC TEXT INDICATES THE REAL COLORS 5 6 IAS FL180 ALT IAS FL200 FL220 IAS VS AP YD SPD HLD CPL FD ALT SEL NAV SOURCE COURSE V/ILS 2 V/ILS 1 FM 2 FM 1 ALT FGCP IAS FMA (CYAN) VS AP YD SPD HLD CPL FD ALT SEL NAV SOURCE COURSE V/ILS 2 V/ILS 1 FM 2 FM 1 ALT IAS (GREEN) ALT SEL ALT (GREEN) FMA (CYAN) ALT (GREEN BOXED) (GREEN) ALT SEL FGCP VS AP YD SPD HLD CPL FD ALT SEL NAV SOURCE COURSE V/ILS 2 V/ILS 1 FM 2 FM 1 ALT IAS PFD 166 00 80 170 165 20 FL180 FMA FMA PFD 180 00 80 20 FL180 PFD 177 00 80 180 175 20 FL180 PFD 180 00 80 20 FL220 PFD 200 00 80 20 FL200 PASSING 1000 ft BEFORE THE ALT SELECTION THE ALTITUDE FRAME IS FLASHING ASSOCIATED WITH C CHORD

Auto Flight: 2.3.2 Altitude Hold Mode

5 6 Activation of the ALT pb on the FGCP selects the ALT HOLD mode and overrides all active FD vertical modes. Any lateral mode existing at engagement is maintained. The ALT HOLD mode is annunciated on FMA by a green ALT and the bug & readout are displayed on the PFD. In the ALT HOLD mode, all armed FD vertical modes are authorized, but a GS capture overrides the ALT HOLD mode.

1 2 4 3 FGCP ALT FMA (GREEN BOXED) IAS ALT FMA (GREEN) NOTE: ITALIC TEXT INDICATES THE REAL COLORS 5 6 IAS FL180 ALT IAS FL200 FL220 IAS VS AP YD SPD HLD CPL FD ALT SEL NAV SOURCE COURSE V/ILS 2 V/ILS 1 FM 2 FM 1 ALT FGCP IAS FMA (CYAN) VS AP YD SPD HLD CPL FD ALT SEL NAV SOURCE COURSE V/ILS 2 V/ILS 1 FM 2 FM 1 ALT IAS (GREEN) ALT SEL ALT (GREEN) FMA (CYAN) ALT * (GREEN BOXED) (GREEN) ALT SEL FGCP VS AP YD SPD HLD CPL FD ALT SEL NAV SOURCE COURSE V/ILS 2 V/ILS 1 FM 2 FM 1 ALT IAS PFD 166 00 80 170 165 20 FL180 FMA FMA PFD 180 00 80 20 FL180 PFD 177 00 80 180 175 20 FL180 PFD 180 00 80 20 FL220 PFD 200 00 80 20 FL200 PASSING 1000 ft BEFORE THE ALT SELECTION THE ALTITUDE FRAME IS FLASHING ASSOCIATED WITH C CHORD

Auto Flight: 2.3.3 Vertical Speed Hold Mode

1 Action on the VS pb on the control panel selects the VS hold mode and overrides all active FD vertical modes. VS existing at engagement is maintained. The VS mode is annunciated by: - A green VS message on the FMA - A cyan bug and a selected VS readout on the PFD VSI. 2 When the VS is stabilized, the VSI pointer is in front of the bug. 7 s after the selection the VS is annunciated by a green VS message on the FMA. 3 Activation of the PW will set a new vertical speed reference. 3 When the new VS is stabilized, the VSI pointer is in front of the bug. Pressing and holding the TCS pb enables the flight crew to maneuver the aircraft to a new vertical speed reference without disengaging the mode. In VS hold mode any other vertical mode may be armed, and when captured will override VS hold mode.

1 VS (GREEN) NOTE: ITALIC TEXT INDICATES THE REAL COLORS VS HOLD FGCP VS SYNC VS HOLD 1 2 HDG NAV APP BC STBY ALT IAS VS NOSE UP NOSE DN -20 6 2 1 6 2 1 PFD VS (GREEN BOXED) FGCP HDG NAV APP BC STBY ALT IAS NOSE UP NOSE DN 0 6 2 1 6 2 1 PFD VS 0 0 -20 6 2 1 6 2 1 PFD 0 -10 6 2 1 6 2 1 0 FMA PFD FMA VS (GREEN) FMA 3 4 -20 -20 -10 -10

Auto Flight: 2.3.4 Indicated Airspeed Hold Mode

1 Action on the IAS pb on the control panel selects the IAS hold mode and overrides all active FD vertical modes. The IAS target speed (MAN or AUTO) is acquired and hold. The IAS mode is annunciated by: - A green boxed IAS message on the FMA - A cyan bug and the selected IAS readout on the PFD ASI. After 7 s, a green IAS message is displayed on the FMA. Manual Speed (MAN) 2 Actuation of the SPD TGT knob will set a new IAS reference without disengaging the mode. The speed bug (cyan) is manually operated by the flight crew. 3 When the new IAS is stabilized, the ASI pointer is in front of the bug. In IAS hold mode, any other vertical mode may be armed, and when captured will override IAS hold mode. Automatic Speed (AUTO) The speed bug (magenta) is managed by the FMS. For further information, Refer to IAS.

1 IAS NOTE: ITALIC TEXT INDICATES THE REAL COLORS FMA 180 160 170 (GREEN BOXED) FGCP VS AP YD SPD HLD CPL FD ALT SEL NAV SOURCE COURSE V/ILS 2 V/ILS 1 FM 2 FM 1 ALT IAS IAS HOLD 2 IAS FMA (GREEN) ICP AUTO/MAN SPD TGT SEL PFD PFD 3 IAS FMA (GREEN) PFD IAS SYNC IAS HOLD 150 170 180 160 170 150 180 190 170 180 160 180

5 VNAV Mode VNAV Mode Introduction

(Applies: 1096-1160) VNAV mode uses FMS data and barometric data to provide a vertical guidance along the FPLN vertical path. The VNAV mode is used in climb, in descent and during approach (except for LOC, ILS, LP and LPV approaches). The VNAV mode is engaged with VNAV pb on FGCP for climb or descent and with APP pb on FGCP for approach. The mode is available only when LNAV mode is active. The VNAV mode includes 5 VNAV submodes, used in accordance with the following flight phases: Flight Phase GROUND / TAKEOFF CLIMB / GO- AROUND CRUISE until TOD-5’ CRUISE after TOD-5’ / DESCENT APPROACH VNAV SUBMODE VNAV IAS Arm only Climb to ALT SEL Or ALT Constraint N/A VNAV ALT N/A Capture level- off N/A VNAV VS N/A Descent to ALT SEL N/A VNAV PATH N/A Descent along profile V-FP N/A Arm only Approach procedure VNAV Modes Summary

Typical flight profiles with associated VNAV sub mode: - Start of descent after TOD minus 5 min:

VNAV IAS VNAV IAS VNAV PATH V-FP VNAV ALT ALT TOD-5 TOD Press on VNAV pb Climb Phase with VNAV Mode Descent Phase with VNAV Mode Final Approach Cruise VNAV - Start of descent before TOD minus 5 min:

VNAV Path VNAV VS V-FP ALT ALT TOD-5 TOD Final Approach Press on VNAV pb Press on VNAV pb VNAV VNAV

VNAV IAS Submode

(Applies: 1096-1160) VNAV IAS submode guides the aircraft during climb. The VNAV IAS targets a speed target (AUTO or MAN) during the climb, when a vertical constraint that requires a level off is reached, the VNAV IAS mode is then replaced by VNAV ALT submode. 1 An action on the FGCP VNAV pb will engaged VNAV mode with VNAV IAS submode if: - The current selected altitude is 250 ft above the current aircraft altitude - The LNAV mode is engaged. The autopilot targets the IAS speed target (MAN or AUTO). Note - On ground, an action on VNAV pb will arm the VNAV IAS mode if LNAV is armed and the current Selected Altitude is at least 250 ft above current aircraft altitude. - The VNAV IAS submode is annunciated by a ”VNAV IAS” green boxing on the FMA during 7 s. If there is an altitude constraint requiring a level off before to reach the selected altitude: - The VNAV ALT submode is armed. - The constraint altitude value is displayed in magenta above the altitude scale on the PFD. 2 3 If there is an altitude constraint requiring a level off before to reach the selected altitude: - 1 000 ft before the level off, the C-Chord sound is triggered. - 250 ft before the level off, VNAV ALT submode is engaged during altitude capture and VNAV IAS submode is armed. Note The VNAV ALT submode is annunciated by a ”VNAV ALT*” green boxing on the FMA during 7 s. After altitude capture, VNAV ALT is engaged. 4 5 When aircraft is cleared from the altitude constraint, the climb is resumed with VNAV IAS submode. Note The VNAV IAS submode is annunciated by a ”VNAV IAS” green boxing on the FMA during 7 s. The Vertical Path Change Alert (VPCA) is raised 10 s before the pitch change at level off exit (flashing of the altitude constraint value displayed above the altitude scale). If there is no additional altitude constraint requiring a level off, the ALT mode is armed. If there is another altitude constraint requiring a level off, the VNAV ALT submode is armed again and the associated altitude constraint value is displayed in magenta above the altitude scale. 6 Capture of the selected altitude. ALT mode is engaged. Note VNAV IAS is automatically disengaged 5 min before TOD.

FL180 FL 220 PASSING 1000 ft BEFORE THE FMS LEVEL OFF. C CHORD V N A V A L T * V N A V I A S L N A V FL180 FL 220 160 VNAV ALT FL180 FL 220 VNAV ALT VNAV IAS FL 220 FL180 VPCA (FMS LEVEL OFF INDICATION FLASHING) FL 220 VNAV IAS ALT SEL 190 FL 220 220 VNAV ALT

VNAV ALT Submode

(Applies: 1096-1160) VNAV ALT mode guides the aircraft on FMS level-offs. It is equivalent to the ALT mode but targets the FMS altitude constraint rather than the Selected Altitude. VNAV ALT mode is automatically armed when the aircraft is climbing toward a FMS level off in VNAV IAS mode. Refer to DSC.22.4.2.3.2 VNAV IAS Submode for a level off sequence description.

VNAV VS Submode

(Applies: 1096-1160) VNAV VS submode guides the aircraft during descent. VNAV VS submode is engaged when: - VNAV pb is pushed earlier than 5 min before the TOD - The selected altitude is below the current aircraft altitude - The LNAV mode is engaged. VNAV VS submode guides the aircraft with a -1 500 ft/min vertical speed target until the selected altitude. 1 2 An action on the FGCP VNAV pb will engage VNAV mode with VNAV VS submode ( providing that previous condition are satisfied ). The ALT mode is armed. The autopilot targets -1 500 ft/min vertical speed target. Note The VNAV VS submode is annunciated by a green boxed ”VNAV VS” message on the FMA during 7 s. A magenta Vertical speed bug and Vertical speed target value ( at -1 500 ft/min) are displayed on VSI. 3 Approaching selected altitude: - 1 000 ft before the selected altitude, C-Chord sound is triggered. - During the selected altitude capture, ALT mode is engaged during altitude capture. - After altitude capture, ALT mode is engaged. Note The ALT mode is annunciated by a green boxed ” ALT*” message on the FMA during 7 s.

FL 160 VNAV VS 160 FL 160 FL 160 VNAV VS FL 180

-15 -15 2 1 2 1 0 VNAV VS ALT SEL FL 160 PASSING 1000 ft ABOVE THE ALT SELECTION THE ALTITUDE FRAME IS FLASHING ASSOCIATED WITH C CHORD

VNAV PATH Submode

(Applies: 1096-1160) The VNAV PATH Mode is used to guide the aircraft along the FMS vertical profile in descend. The FMS vertical profile is computed 5 min before TOD (For further information, Refer to FMS.02.80.3.5 Vertical Profile Computation for Descent). VNAV PATH submode is engaged when: - VNAV pb is pushed later than 5 min before the TOD - The selected altitude is below the current aircraft altitude - The LNAV mode is engaged. 1 Aircraft is in ALT and LNAV modes. 5 min before the TOD, the vertical deviation indicator is displayed on PFD. 2 1 min before TOD, the flight crew is informed by the VTA (Vertical Track Alert, flashing of the selected altitude value above altitude speed scale) that the TOD will be reached in 5 min. 3 An action on the FGCP VNAV pb will engage VNAV mode with VNAV PATH submode (providing that the previous conditions are satisfied). Note The VNAV PATH mode engagement is annunciated by: - A “VNAV PATH” green boxing on the FMA during 7 s. - If there is an ALT constraint, the ALT constraint value is displayed above the altitude scale in magenta. - The ALT SEL mode is automatically armed. - The VS target that is required to follow the vertical profile is displayed in cyan on the VS indicator.

FL 160 160 1 MINUTE BEFORE TOD VTA 3000 VNAV PATH 3000 160 160 FL 160 TOD VNAV PATH ALT SEL FAF 3000 ft

FL 160

Start of descent between TOD-5 and TOD Note If descent is started before TOD-5, VNAV VS Mode will be activated. Refer to DSC.22.4.2.3.4 VNAV VS Submode. If VNAV pb is pushed between TOD-5 and TOD, the VNAV PATH submode will guide the aircraft along a new vertical profile: The FMS recomputes a new vertical profile. The new vertical profile is a direct trajectory from the current aircraft position to: - The first constraining altitude constraint. After this altitude constraint, the vertical profile is computed in accordance with all other vertical constraints defined in the arrival procedure. - The MAP if there is no constraining altitude constraint.

TOD-5 TOD VNAV Action on VNAV pb TOD VNAV Path

Start of descent after TOD If VNAV pb is pushed after TOD, the VNAV PATH will guide initially the aircraft on a descent with a 5.5 ° FPA, until it joins the initial descent profile.

FMS Vertical Profile ALT Mode ALT Mode VNAV Path 5.5° FPA Descent TOD VNAV Action on VNAV pb Note If an ALT constraint of the FPLN cannot be respected during the descent with a 5.5 ° FPA, an ALT constraint missed will be displayed. On ND, a purple circle shows the intersection between FPLN profile and the 5.5 ° FPA descent trajectory.

Use of VNAV mode when the aircraft is below the cruise level When VNAV pb is pushed later than 5 min before the TOD and the aircraft is below the FMS cruise altitude, there are two possible descent trajectories: - If the aircraft is above all AT and AT OR ABOVE altitude constraints of the arrival: The VNAV PATH submobe will guide the aircraft along a new vertical profile. The new vertical profile is a direct trajectory from the current aircraft position to: o The first constraining altitude constraint. After this altitude constraint, the vertical profile is computed in accordance with all other vertical constraints defined in the arrival procedure. Example (with and without new constraining altitude constraint):

Cruise Altitude Cruise Altitude TOD TOD o The MAP if there is no constraining altitude constraint.

TOD MAP Runway

• If the aircraft is below an AT and AT OR ABOVE altitude constraints of the arrival: The VNAV PATH submobe will guide the aircraft on a level off trajectory until to join the vertical profile.

TOD Cruise Altitude

V-FP Submode

(Applies: 1096-1160) The V-FP submode is the vertical guidance mode dedicated to final approaches. It is similar to VNAV PATH with the difference that it ignores the Selected Altitude. The V-FP submode is used for following approaches: - LNAV/VNAV - VOR - NDB. V-FP submode is engaged with FGCP APP pb. VNAV PATH submode is engaged when: - A LNAV/VNAV, VOR or NDB approach is set in the FPLN - The V-FP submode is armed 2 Nm before FAF. For further information, Refer to DSC.22.4.2.5.3 LNAV-VNAV Approach Mode.

Auto Flight: 2.4 LATERAL MODES

Auto Flight: 2.4.1 Heading Select Mode

1 2 Heading selection is made by the HDG knob and is displayed on both HSI / ND. 3 Action on the HDG pb on the FGCP, selects the Heading Select mode and overrides any active lateral FD mode. The heading Select mode is annunciated on the FMA by a green boxed HDG SEL at the lateral active location. 4 The aircraft turn to the selected heading and after 7 s a green HDG SEL is displayed on the FMA. Selection of turns greater than 180 ° will lead the system to order a turn as short as possible if selection has been made before HDG mode being engaged. If selection is made after HDG mode engagement, turning command will occur by the side selected by the flight crew. CAUTION Before takeoff, aircraft lined up with the runway heading, the vertical command bar has to be checked and centered (if necessary).

2 3 4 FD HDG NAV BC STBY HDG PUSH SYNC NAV SOURCE COURSE V/ILS 1 V/ILS 2 FM 1 FM 2 NOSE UP NOSE DN APP HDG SEL FGCP 3 HEADING SEL ENGAGE NOTE: ITALIC TEXT INDICATES THE REAL COLORS HDG HOLD FMA (GREEN) HEADING HOLD (GREEN BOXED) HEADING HOLD HDG SEL FMA (GREEN) 33 N 3 6 30 W E 24 12 21 15 S FD HDG NAV BC STBY HDG PUSH SYNC NAV SOURCE COURSE V/ILS 1 V/ILS 2 FM 1 FM 2 NOSE UP NOSE DN APP HDG HOLD FGCP FMA 2 HEADING BUG SETTING (GREEN) 4 FMA 33 N 3 6 30 W E 24 12 21 15 S 33 N 3 6 30 W E 24 12 21 15 S 1

Auto Flight: 2.4.2 Navigation Mode

NAV pb on the FGCP enables to arm the following lateral guidance mode: - VOR when VOR frequency is tuned and NAV source is V/ILS 1 or V/ILS 2 on coupled side - LOC when LOC frequency is tuned and NAV source is V/ILS 1 or V/ILS 2 on coupled side - LNAV when active FLPN is inserted in FMS and NAV source is FM1 or FM2 on coupled side. VOR Navigation Mode The arming and activation sequence of the VOR navigation mode is: 1 Selection of the NAV SOURCE V/ILS 1 or V/ILS 2 on the FGCP, tuning of the frequency with the MCP or RMS (via the MCDU), set of the requested course on the FGCP COURSE knob. 2 When the NAV pb is pressed, the VOR arming is annunciated on the FMA by a cyan VOR message. HDG SELECT, HDG HOLD modes can be used to steer during the VOR arm phase. 3 At VOR capture, the previous active lateral mode is cancelled and VOR CAPTURE is annunciated on FMA by: - A green boxed VOR (the box for mode change and the star for capture) - A green VOR after 7 s. 4 VOR TRACK mode is annunciated on the FMA by the green VOR message. 5 AFTER STATION LOC Navigation Mode The arming and activation sequence of LOC navigation mode is identical to VOR NAV navigation mode. The messages displayed on FMA are: LOC (cyan), LOC (green boxed), LOC (green), LOC (green boxed), LOC (green).

1 3 VOR * FMA 3 VOR NOTE: ITALIC TEXT INDICATES THE REAL COLORS (GREEN BOXED) 4 33 N 3 6 30 W E 24 12 21 15 S FD HDG NAV BC STBY HDG PUSH SYNC NAV SOURCE COURSE V/ILS 1 V/ILS 2 FM 1 FM 2 NOSE UP NOSE DN APP FGCP 2 COURSE SETTING VOR TUNED 1 2 3 4 5 6 7 8 9 0 NAV COM ATC ESC ENT HDG SEL (GREEN) FD HDG BC STBY HDG PUSH SYNC NAV SOURCE COURSE V/ILS 1 V/ILS 2 FM 1 FM 2 NOSE UP NOSE DN APP HDG SEL FGCP FMA NAV (GREEN) NAV VOR (CYAN) ENGAGE CAPTURING VOR (GREEN) VOR TRACK FD HDG NAV BC STBY HDG PUSH SYNC NAV SOURCE COURSE V/ILS 1 V/ILS 2 FM 1 FM 2 NOSE UP NOSE DN APP FGCP VOR FMA (GREEN) VOR OVERSTATION VOR FMA (GREEN) VOR AFTER 5 2 4 OVERSTATION 5 33 N 3 6 30 W E 24 12 21 15 S 33 N 3 6 30 W E 24 12 21 15 S 33 N 3 6 30 W E 24 12 21 15 S FMA 1 FMA VOR1 117.70 340 CRS ° VOR1 117.70 015 CRS ° VOR1 117.70 340 CRS ° VOR1 117.70 015 CRS °

LNAV Navigation Mode This mode guides the aircraft along the FMS FPLN lateral flight path. LNAV mode can be armed only if an FMS is selected as the navigation source on the coupled side and a FPLN is defined. While LNAV mode armed, the flight crew can activate another guidance mode to reach position and track near the active FPLN leg and TO waypoint where the LNAV mode could be activated. Armed LNAV automatically activates if aircraft is following the FPLN or when aircraft captures the FPLN leg. 1 The arming and activation sequence of the LNAV navigation mode is: The NAV SOURCE FM 1 or FM 2 is selected on the FGCP and the flight plan is selected on the MCDU. The managed course (HSI) and the leg to the next waypoint (ND) are displayed in magenta. 2 After pressing the NAV pb, the LNAV ARM is annunciated on the FMA by a cyan LNAV message. HDG SELECT, HDG HOLD modes can be used to steer during the LNAV ARM phase. 3 At capture, the previous lateral mode is cancelled. LNAV is annunciated on FMA by a green box (the box for mode change). 4 LNAV track mode is annunciated on the FMA, by a green LNAV message after 7 s. 5 Passing over the waypoint, the LNAV mode sends a roll order to fly to the next way point. LNAV can be manually deactivated by: - Selecting navigation source V/ILS 1 or V/ILS 2 in the coupled side. - Pressing HDG, APP or BC pushbutton on the FGCP to activate another lateral mode. LNAV is automatically deactivated when: - Reaching last active FPLN waypoint or FPLN discontinuity - A FGCP failure is detected. - A failure of the FMS roll target selection is detected. Note A LNAV de-activation automatically de-activates VNAV. LNAV can be manually disarming by selecting navigation source V/ILS 1 or V/ILS 2 in the coupled side. LNAV is automatically disarming when: - One FGCP failure is detected or NAV pb on the FGCP is stuck - No active TO waypoint is detected. For instance when reaching a FPLN discontinuity.

1 3 FMA 3 LNAV CHANGE NOTE: ITALIC TEXT INDICATES THE REAL COLORS (GREEN BOXED) 4 33 N 3 6 30 W E 24 12 21 15 S FD HDG NAV BC STBY HDG PUSH SYNC NAV SOURCE COURSE V/ILS 1 V/ILS 2 FM 1 FM 2 NOSE UP NOSE DN APP FGCP 2 MANAGED COURSE HDG SEL (GREEN) FD HDG BC STBY HDG PUSH SYNC NAV SOURCE COURSE V/ILS 1 V/ILS 2 FM 1 FM 2 NOSE UP NOSE DN APP HDG SEL FGCP FMA NAV (GREEN) NAV LNAV (CYAN) ARMED FMA LNAV (GREEN) LNAV TRACK LNAV FMA (GREEN) OVER WAYPOINT LNAV FMA (GREEN) TO THE NEXT 5 2 4 33 N 3 6 30 W E 24 12 21 15 S WAYPOINT 5 33 N 3 6 30 W E 24 12 21 15 S 33 N 3 6 30 W E 24 12 21 15 S FMA 1 LNAV 1 2 3 4 5 6 7 8 9 0 +/- / SP A B C D E F G H I J K L M N O P Q R S T U V W X Y Z CLR RMS MENU PREV NEXT FPLN DTO PERF MSG EXEC PROG DATA VNA MRK BRT BRT FAIL MSG POS OFST CRS 30° MCDU (MAGENTA)

Auto Flight: 2.4.3 Back Course Mode

The back course mode is set up and flown exactly like a front course localizer approach but selecting BC mode. In this case, glideslope capture is automatically inhibited. - Set the course pointer on the HSI / ND for the inbound published track - Set the heading bug on the HSI / ND for the desired heading to intercept the course. AFCS provides an Enhanced BC capture function. This function uses FMS guidance data to anticipate back course LOC Capture, and then switch to LOC beacon deviation when it can be used. Enhanced BC capture is available while estimated position error remains less than 0.1 Nm (resp. 0.3 Nm) for a distance to localizer antenna of 10 Nm (resp. 25 Nm). Enhanced BC capture is available until 170 ° interception angle. Note if interception angle is greater than 170 °, Enhanced BC capture function is not available. Basic BC mode (without FMS guidance data) remains available. HEADING 340° LOCALIZER RUNWAY TX 090° INBOUND COURSE

Auto Flight: 2.5 COMMON MODES

Auto Flight: 2.5.1 ILS Approach Mode

1 2 Action on the APP pb on FGCP selects LOC and GS ARM modes provided the coupled NAV receiver is tuned to an ILS frequency. LOC ARM is annunciated on the FMA by a cyan LOC message. HDG SELECT, HDG HOLD modes can be used to steer during the LOC ARM phase. GS ARM is annunciated on the FMA by a cyan GS message. Any vertical mode is allowed during GS ARM phase. 3 4 At LOC CAPTURE the previous lateral mode used to fly is cancelled. LOC CAPTURE is annunciated on the FMA by: - A green boxed LOC (the box for mode change and the star for capture) - A green LOC after 7 s. AFCS provides an Enhanced LOC capture function. This function uses FMS guidance data to anticipate LOC capture, and then switch to LOC deviation when it can be used. Enhanced LOC capture is available while estimated position error remains less than 0.1 Nm (resp 0.3 Nm) for a distance to localizer antenna of 10 Nm (resp 25 Nm). Enhanced LOC capture is available until 170 ° interception angle. Note if interception angle is greater than 170 °, Enhanced LOC capture function is not available. Basic LOC capture (without FMS guidance data) remains available. 5 LOC TRACK is annunciated on the FMA by the green LOC message. Glideslope capture is interlocked such that the localizer must be captured before glideslope capture. The GS capture overrides all vertical modes which were previously engaged. GS CAPTURE is annunciated on the FMA by : - A green boxed GS* (the box for mode change and the star for capture) - A green GS after 7 s. GS TRACK is annunciated on the FMA by the green GS message. Flight crew is advised if all aircraft CAT II conditions are met by a CAT 2 message displayed on the FMA. If not, a CAT I message is displayed. If CAT II conditions are lost during approach, a CAT 2 INVALID amber message is displayed on the FMA. In addition, a TRIPLE CLIC aural alert is generated. Note EXCESS DEV monitoring is enabled when CAT II conditions are met. This monitoring is available below 300 ft RA. When an excessive deviation occurs, the LOC or/and GS scales are flashing amber and EXCESS DEV (white on red reverse video) is flashing on the FMA, then after 7 s EXCESS DEV is becoming steady amber.

HDG SEL ALT 1 2 3 4 5 6 7 8 9 0 NAV COM ATC ESC ENT ILS1 110.30 (GREEN) FD HDG NAV BC STBY HDG PUSH SYNC NAV SOURCE COURSE V/ILS 1 V/ILS 2 FM 1 FM 2 NOSE UP NOSE DN APP HDG SEL ALT LOC GS FGCP FMA APP ENGAGE LOC * ALT FMA CAPTURING LOC GS ARMED (GREEN BOXED) (CYAN) LOC ALT GS FMA LOC TRACK GS ARMED (GREEN) (CYAN) GS LOC FMA CAPTURING GS LOC TRACK (GREEN) GS* (GREEN) LOC GS FMA (GREEN) LOC TRACK GS TRACK NOTE: ITALIC TEXT INDICATES THE REAL COLORS FMA 2 3 5 6 4 2 3 4 5 (GREEN BOXED) ALT HOLD HEADING SEL ILS TUNED 1 LOCALIZER GLIDE SLOPE 6 (CYAN) (GREEN) (GREEN) 1

Auto Flight: 2.5.2 LPV Approach Mode

1) LPV Approach Mode Without VTF 1 An LPV approach is selected in the flight plan and LNAV mode is engaged. 2 Action on the FGCP APP pb selects L-LOC and L-GS ARM modes: - L-LOC ARM is annunciated on the FMA by a cyan “L-LOC" message. - L-GS ARM is annunciated on the FMA by a cyan “L-GS" message. 3 L-LOC CAPTURE mode engages when LNAV mode is engaged and aircraft reaches 2 Nm before the FAF. L-LOC CAPTURE is annunciated on the FMA by: - A green boxed “L-LOC" (the box for mode change and the star for capture) - A green "L-LOC" after 7 s. Note LPV approach category is displayed in green on FMA. 4 L-LOC TRACK mode engages when aircraft is established on LPV localizer. L-LOC TRACK is annunciated on the FMA by the green “L-LOC" message. - A green boxed “L-LOC" - A green “L-LOC" after 7 s. 5 LPV glideslope capture is interlocked so that the LPV localizer must be captured before LPV glideslope capture. The L-GS capture overrides all vertical modes which were previously engaged. L-GS CAPTURE is annunciated on the FMA by: - A green boxed "L-GS" (the box for mode change and the star for capture) - A green "L-GS" after 7 s. 6 GS TRACK mode engages when aircraft is established on LPV glideslope. GS TRACK is annunciated on the FMA by the green GS message. - A green boxed “L-GS" - A green “L-GS" after 7 s.

6 FD HDG NAV BC STBY HDG PUSH SYNC NAV SOURCE COURSE V/ILS 1 V/ILS 2 FM 1 FM 2 NOSE UP NOSE DN APP LNAV ALT L-GS FGCP FMA APP ENGAGE LPV FMA LPV FMA LPV L-LOC FMA 2 4 LPV-LOCALIZER LPV-GLIDE SLOPE 1 LNAV ALT FMA 1 L-GS 3 4 FAF L-LOC * ALT 2 L-LOC L-GS ARMED CAPTURING L-LOC L-LOC ALT L-GS L-GS ARMED L-LOC TRACK 5 ARRIVAL LFBO TO L5 L6 L4 L3 L2 L1 R5 R6 R4 R3 R2 R1 LPV MCDU LPV FMA 5 L-LOC L-LOC TRACK CAPTURING L-GS L-GS * 6 L-GS TRACK L-LOC TRACK L-GS

APPROACH WITHOUT VTF 2) LPV Approach Mode With VTF 1 An LPV approach is selected in the flight plan and LNAV mode is engaged. 2 Action on the FGCP HDG pb selects the HDG mode (LNAV mode is automatically cancelled before VTF). 3 The flight crew selects VTF on the MCDU. All waypoints between current aircraft position and FAF are removed. A 30 Nm leg is created from FAF. LPV mode armament is inhibited if VTF is not selected. Note If the flight crew try to arm LPV modes (L-LOC and L-GS) before VTF selection on MCDU, SELECT VTF yellow message will flash 7 s in FMA. 4 Action on the FGCP APP pb selects L-LOC and L-GS ARM modes: - L-LOC ARM is annunciated on the FMA by a cyan “L-LOC" message. - L-GS ARM is annunciated on the FMA by a cyan “L-GS" message.

5 L-LOC CAPTURE mode engages when the aircraft intercepts the desired LPV lateral beam. AFCS provides an Enhanced LPV L-LOC function. The principle of Enhanced L-LOC Capture is to use GNSS SBAS linear deviation to anticipate L-LOC Capture. L-LOC CAPTURE is annunciated on the FMA by: - A green boxed “L-LOC" (the box for mode change and the star for capture) - A green "L-LOC" after 7 s. Note LPV approach category is displayed in green on FMA. 6 L-LOC TRACK mode engages when aircraft is established on LPV localizer. L-LOC TRACK is annunciated on the FMA by the green “L-LOC" message. - A green boxed “L-LOC" - A green “L-LOC" after 7 s. 7 LPV glideslope capture is interlocked so that the LPV localizer must be captured before LPV glideslope capture. The L-GS capture overrides all vertical modes which were previously engaged. L-GS CAPTURE is annunciated on the FMA by: - A green boxed "L-GS" (the box for mode change and the star for capture) - A green "L-GS" after 7 s. 8 GS TRACK mode engages when aircraft is established on LPV glideslope. GS TRACK is annunciated on the FMA by the green GS message. - A green boxed “L-GS" - A green “L-GS" after 7 s.

1 LNAV ALT FMA MCDU ARRIVAL LFBO TO L5 L6 L4 L3 L2 L1 R5 R6 R4 R3 R2 R1 LPV HDG SEL ALT FGCP FMA 2 FD HDG NAV BC STBY HDG PUSH SYNC NAV SOURCE COURSE V/ILS 1 V/ILS 2 FM 1 FM 2 NOSE UP NOSE DN APP HDG SEL ALT FMA MCDU 3 L5 L6 L4 L3 L2 L1 R5 R6 R4 R3 R2 R1 VTF ACTIVATION 1 HDG SEL VS ALT SEL/L-GS FGCP FMA APP ENGAGE 4 L-LOC FD HDG NAV BC STBY HDG PUSH SYNC NAV SOURCE COURSE V/ILS 1 V/ILS 2 FM 1 FM 2 NOSE UP NOSE DN APP LPV-LOCALIZER LPV-GLIDE SLOPE LPV L-LOC FMA L-GS 8 L-GS TRACK L-LOC TRACK LPV FMA 7 L-LOC L-LOC TRACK CAPTURING L-GS L-GS * LPV FMA 6 L-LOC ALT L-GS L-GS ARMED L-LOC TRACK LPV FMA L-LOC * ALT L-GS ARMED CAPTURING L-LOC L-GS 5 2 3 4 5 6 7 8 APPROACH WITH VTF

FAF

Auto Flight: 2.5.3 LNAV-VNAV Approach Mode

(Applies: 1096-1160) 1 2 Action on the FGCP APP pb selects V-FP mode provided a LNAV/VNAV approach is selected on the FMS flight plan. V-FP ARM is annunciated on the FMA by a cyan ”V-FP” message. 3 4 5 . 2 Nm before the FAF, V-FP mode engages and is annunciated on the FMA by: - A green boxed ”V-FP” - A green ”V-FP” after 7 s. While V-FP is engaged, the aircraft will descend toward the MDA along the vertical profile provided by the FMS. Aircraft will ignore the selected altitude. 1 2 3 4 5 LOCALIZER GLIDE SLOPE LNAV VNAV PATH ALT SEL FMA 1 FD HDG NAV BC STBY HDG PUSH SYNC NAV SOURCE COURSE V/ILS 1 V/ILS 2 FM 1 FM 2 NOSE UP NOSE DN APP LNAV VNAV PATH ALT SEL/V-FP FGCP FMA APP ENGAGE 2 ALT V-FP 3 LNAV FMA 2 NM BEFORE FAF V-FP 4 LNAV V-FP FMA FAF

Auto Flight: 2.5.4 Go-around Mode (FD Mode Only)

(Applies: 1054;1237-1283) Action on the GA pb selects the GO AROUND mode and cancels all armed and active FD modes. The AP disengages and the FD gives commands to fly predetermined minimum safe pitch attitude and to maintain heading followed at GA engagement. The GO AROUND mode is annunciated on the FMA by a GA message as vertical mode and HDG HOLD message as lateral mode. The GO AROUND mode is cancelled when one of the following events occurs : - any other vertical mode is activated - the AP is engaged - FD STBY mode is selected - the FGCP is not valid after GO AROUND mode has been engaged for at least 0.9 s - stall warning is active.

HDG HOLD GA FMA LOC GS FMA FMA 3 2 3 1 1 HDG HOLD GA 2

(Applies: 1096) Action on the GA pb selects the GO AROUND mode and cancels all armed and active FD modes. The AP disengages and the FD gives commands to fly predetermined minimum safe pitch attitude and to maintain heading followed at GA engagement. The GO AROUND mode is annunciated on the FMA by a GA message as vertical mode and HDG HOLD message as lateral mode. The GO AROUND mode is cancelled when one of the following events occurs: - any other vertical mode is activated - the AP is engaged - FD STBY mode is selected - the FGCP is not valid after GO AROUND mode has been engaged for at least 0.9 s - stall warning is active. Note If LNAV is engaged when pressing the GA pb, LNAV remains engaged to provide guidance along the missed approach procedure.

HDG HOLD GA FMA LOC GS FMA FMA 3 2 3 1 1 HDG HOLD GA 2

GA LNAV GA FMA LNAV V-FP FMA FMA 3 2 3 1 1 LNAV GA 2

(Applies: 1124-1160) Action on the GA pb selects the GO AROUND mode and cancels all armed and active FD modes. The AP disengages and the FD gives commands to fly predetermined minimum safe pitch attitude and to maintain heading followed at GA engagement. The GO AROUND mode is annunciated on the FMA by a GA message as vertical mode and HDG HOLD message as lateral mode. The GO AROUND mode is cancelled when one of the following events occurs: - any other vertical mode is activated - the AP is engaged - FD STBY mode is selected - the FGCP is not valid after GO AROUND mode has been engaged for at least 0.9 s - stall warning is active. In addition, when RNP-AR Dual CPL submode is not active, the GO AROUND mode is cancelled when one of the following events occurs: - the ADC or ATT/HDG selection is changed with CAPT / F/O reversion switches - CAS or TAS or MACH data from the selected ADC is not valid - an attitude data from the selected AHRS is not valid. Note If LNAV is engaged when pressing the GA pb, LNAV remains engaged to provide guidance along the missed approach procedure.

HDG HOLD GA FMA LOC GS FMA FMA 3 2 3 1 1 HDG HOLD GA 2

GA LNAV GA FMA LNAV V-FP FMA FMA 3 2 3 1 1 LNAV GA 2

Auto Flight: 01 Altitude Alert

(Applies: 1054;1237-1283) The purpose of the altitude alert function is to alert the flight crew by activation of a visual signal and an aural signal when the aircraft is reaching or leaving the preselected altitude. Preselection is displayed with a bug and a read out above the PFD altimeter scale: - In cyan selected through the ATL SEL knob. The visual signal consists of a flashing amber surrounding the altitude readout, above the PFD altitude scale, when altitude is between H + 250 ft and H + 1 000 ft, or between H - 250 ft and H - 1 000 ft. The aural signal consists in a “C chord” signal of 1 s duration which is activated each time the aircraft enters one of the two altitude zones defined above.

1 sec

H +250 ft

1 sec

1 sec

1 sec

1 sec

1 sec

AURAL WARNING SOUNDS FOR 1 SECOND. THE WARNING SHALL BE CANCELLED BY

NEW ALTITUDE SELECTION UNTIL THE NEW VALUE IS STABLE DURING 1 sec.

H -250 ft

H -1000 ft

H -1100 ft

H +1000 ft

H +1100 ft

VISUAL WARNING (ALTITUDE ALERT DISCRETE FOR EIS). IT SHALL BE CANCELLED BY NEW ALTITUDE SELECTION UNTIL THE NEW VALUE IS STABLE DURING 1 sec. H SELECTED ALTITUDE

Altitude alert (visual and audio signals) is inhibited when a final approach mode is engaged (GS, GS, L-GS, L-GS or V-FP).

(Applies: 1096-1160) The purpose of the altitude alert function is to alert the flight crew by activation of a visual signal and an aural signal when the aircraft is reaching or leaving the preselected altitude. Preselection is displayed with a bug and a read out above the PFD altimeter scale: - In cyan selected through the ATL SEL knob - In magenta when managed by the FMS. The visual signal consists of a flashing amber surrounding the altitude readout, above the PFD altitude scale, when altitude is between H + 250 ft and H + 1 000 ft, or between H - 250 ft and H - 1 000 ft. The aural signal consists in a “C chord” signal of 1 s duration which is activated each time the aircraft enters one of the two altitude zones defined above.

1 sec

H +250 ft

1 sec

1 sec

1 sec

1 sec

1 sec

AURAL WARNING SOUNDS FOR 1 SECOND. THE WARNING SHALL BE CANCELLED BY

NEW ALTITUDE SELECTION UNTIL THE NEW VALUE IS STABLE DURING 1 sec.

H -250 ft

H -1000 ft

H -1100 ft

H +1000 ft

H +1100 ft

VISUAL WARNING (ALTITUDE ALERT DISCRETE FOR EIS). IT SHALL BE CANCELLED BY NEW ALTITUDE SELECTION UNTIL THE NEW VALUE IS STABLE DURING 1 sec. H SELECTED ALTITUDE Altitude alert (visual and audio signals) is inhibited when a final approach mode is engaged (GS, GS, L-GS, L-GS or V-FP). 1) VTA Vertical Track Alert is used to prompt the flight crew that ALT SEL should be modified to follow the FMS flight plan. When VNAV is engaged, VTA is raised 1 min before: - The beginning of a step - The Top of Descent (TOD). VTA ends as soon as ALT SEL has been modified by the flight crew or TOD is sequenced.

2) VPCA With VNAV mode engaged, Vertical Path Change Alert indicates that aircraft pitch will change due to VNAV guidance. VPCA is raised 10 s before the pitch change. - In climb, VPCA is raised when a constraining altitude constraint will be sequenced (pitch change from level off to climb). There is no VPCA when aircraft reaches an altitude constraint (pitch change from climb to level off is indicated by FMS audio alert). When VPCA is raised, FMS level off constraint indications on PFD flashes. - In descent, VPCA is raised for an aircraft on path when aircraft reaches the end of current vertical segment. When VPCA is raised, FMS VS Target indications on PFD flashes.

Auto Flight: 1 Flight Path Angle Protection

(Applies: 1054;1237-1283) The purpose of the Flight Path Angle (FPA) protection is to prevent aircraft from stopping climb, during significant evolutions of IAS target (e.g. after flaps configuration change) or significant downdrafts. When active, AFCS takes over pitch guidance order. Flight path angle protection is available: - in IAS mode, 180 s after liftoff - in GA mode, 180 s after a go-around performed under 500 ft (or performed with RA failed). If FPA reaches +0.5°, and respecting IAS target would result in a FPA decrease, AFCS longitudinal guidance order will be maintained at a +0.5° FPA target. Previous guidance target is no longer followed as long as the protection is active. If the FPA protection is continuously active during 20 s, and aircraft speed is lower than VmHB, the active vertical mode is replaced by PITCH HOLD mode (initially resynchronized with the +0.5° FPA target). At PITCH HOLD mode engagement: - Triple click audio alert is triggered, - PITCH HOLD mode is displayed on FMA and is boxed during 7 s. Note As with every reversion to basic modes, aircraft short-term stability is ensured to allow flight crew to consider the best sequence of actions (e.g. engaging ALT hold mode to retrieve acceleration capability). As PITCH HOLD mode benefits from low speed protection (Refer to Low Speed Protection), flight path angle protection may be followed by low speed protection, and then complementary low speed alerting, if the conditions remain challenging for aircraft performance.

(Applies: 1096-1160) The purpose of the Flight Path Angle (FPA) protection is to prevent aircraft from stopping climb, during significant evolutions of IAS target (e.g. after flaps configuration change) or significant downdrafts. When active, AFCS takes over pitch guidance order. Flight path angle protection is available: - in IAS mode, 180 s after liftoff - in GA mode, 180 s after a go-around performed under 500 ft (or performed with RA failed) - in VNAV IAS mode. If FPA reaches +0.5°, and respecting IAS target would result in a FPA decrease, AFCS longitudinal guidance order will be maintained at a +0.5° FPA target. Previous guidance target is no longer followed as long as the protection is active.

If the FPA protection is continuously active during 20 s, and aircraft speed is lower than VmHB, the active vertical mode is replaced by PITCH HOLD mode (initially resynchronized with the +0.5° FPA target). At PITCH HOLD mode engagement: - Triple click audio alert is triggered, - PITCH HOLD mode is displayed on FMA and is boxed during 7 s. Note As with every reversion to basic modes, aircraft short-term stability is ensured to allow flight crew to consider the best sequence of actions (e.g. engaging ALT hold mode to retrieve acceleration capability). As PITCH HOLD mode benefits from low speed protection (Refer to Low Speed Protection), flight path angle protection may be followed by low speed protection, and then complementary low speed alerting, if the conditions remain challenging for aircraft performance.

Auto Flight: 1 High Speed Protection

The purpose of the high speed protection is to prevent the aircraft from exceeding Vmax. The high speed protection lowers the descent rate, possibly down to Vz = 0 ft/min. When protection is activated, AFCS takes over pitch guidance order and alerts the flight crew. High speed protection is available if: - VNAV PATH, VNAV VS, VS, ALT* or PITCH HOLD modes are engaged in descent (Vz < 0 ft/min),and - In clean or FLAPS 15 configuration, and - AP is engaged. If IAS increases toward Vmax -2.5 kt in FLAPS 0 or Vmax -5 kt in FLAPS 15: - AFCS vertical guidance order will target: o Vmax -2.5 kt in FLAPS 0 o Vmax -5 kt in FLAPS 15. - REDUCE SPD message is displayed on FMA if protection is active during more than: o 6 s in FLAPS 0 o 3 s in FLAPS 15. FD AP VS LNAV REDUCE SPD FD AP VS LNAV REDUCE SPD

• Triple click audio alert is triggered if protection is active during more than: o 6 s in FLAPS 0 o 3 s in FLAPS 15. Note Due to the priority order of aural alerts, triple click can be drowned out by whooler (Refer to DSC.31.12.1.7 Aurals for aural alert priority order). Vertical mode pitch target is no longer followed as long as the protection is active. Note
• In PITCH HOLD mode, Nose Down pitch wheel modifications are inhibited if IAS > Vmax or if high speed protection is active
• In V/S mode, V/S target reduction with the pitch wheel is inhibited if IAS > Vmax or if high speed protection is active.

1) AP Disengagement Behavior When high speed protection is active and VS, ALT*, VNAV PATH or VNAV VS mode is active, if AP is disengaged: - The active vertical mode is disengaged, and - REDUCE SPD message is displayed during 7 s, and - If an upper lateral mode is active, FD remains engaged and PITCH HOLD mode is engaged, or - If a basic lateral mode is active, FD is disengaged.

Auto Flight: 2 Low Speed Protection

The purpose of the low speed protection is to prevent the aircraft from decreasing significantly below Vmin OPS. When active, AFCS takes over pitch guidance order and alerts the flight crew. Low speed protection is available if: - VNAV ALT, ALT, VS and PITCH HOLD modes are engaged in climb (Vz > 0 ft/min), and - In clean, FLAPS 15 configurations, and - AP is engaged. If IAS reaches Vmin OPS: - AFCS vertical guidance order will target Vmin OPS, and - “MONITOR SPD” message is displayed on FMA if protection is active during more than 3 s. FD AP VS LNAV MONITOR SPD FD AP VS LNAV MONITOR SPD

Vertical mode pitch target is no longer followed as long as the protection is active. When V/S reaches 0 ft/min while low speed protection is active, active vertical mode is replaced by a PROT LEVEL mode. PROT LEVEL mode maintains V/S = 0 ft/min. At PROT LEVEL mode engagement: - "MONITOR SPD” message blinks during 7 s then is displayed steady - Triple click audio alert is triggered. Note Due to the priority order of aural alerts, triple click can be drowned out by whooler (Refer to DSC.31.12.1.7 Aurals for aural alert priority order).

FD AP PROT LEVEL LNAV MONITOR SPD PROT LEVEL mode can be disengaged manually by pressing STBY or selecting another vertical mode or by automatic engagement of an armed vertical mode. 1) AP Disengagement Behavior When MONITOR SPD is displayed and VS, ALT or VNAV ALT mode is active, if AP is disengaged before PROT LEVEL engagement: - The active vertical mode is disengaged, and - “MONITOR SPD” message remains displayed during at least 7 s after AP disengagement, and - If an upper lateral mode is active, FD remains engaged and PITCH HOLD mode is engaged, or - If a basic lateral mode is active, FD is disengaged. Note - In PITCH HOLD mode, Nose Up pitch wheel modifications are inhibited if IAS < VminOPS or if low speed protection is active - In V/S mode, V/S target increase with the pitch wheel is inhibited if IAS < VminOPS or if low speed protection is active. When PROT LEVEL mode is engaged, if AP is disengaged: - PROT LEVEL mode remains engaged and provides vertical FD guidance.

Auto Flight: 3 Complementary Low Speed Alerting

The purpose of the complementary low speed alerting is to alert the flight crew that the aircraft speed decreases significantly below Vmin OPS. Complementary low speed alerting is available in flight, above 80 ft. In Clean or FLAPS 15 configurations, if IAS decreases until Vmin OPS -5 kt and if PROT LEVEL is not engaged: - “SPEED SPEED” Message is displayed on FMA, and - Triple click audio alert is triggered. Note Due to the priority order of aural alerts, triple click can be drowned out by whooler (Refer to DSC.31.12.1.7 Aurals for aural alert priority order). “SPEED SPEED” Message disappears when IAS > Vmin OPS.

In FLAPS 30 configuration, if IAS decreases under Vmin OPS - 3 kt and if PROT LEVEL is not engaged: - “SPEED SPEED” Message is displayed on FMA, and - Triple click audio alert is triggered. Note Due to the priority order of aural alerts, triple click can be drowned out by whooler (Refer to DSC.31.12.1.7 Aurals for aural alert priority order). “SPEED SPEED” message disappears when IAS > VminOPS.

FD AP ALT LNAV SPEED SPEED Note When PROT LEVEL mode is already engaged, “SPEED SPEED” Message is displayed and triple click is triggered when IAS is below Vmin OPS +1 kt. “SPEED SPEED” Message disappears when IAS > Vmin OPS +10 kt.

FD AP PROT LEVEL LNAV SPEED SPEED