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 The pilot disengages A/THR by pushing the A/THR pushbutton on the FCA, or
 The A/THR disconnects due to a failure.
When thrust lock is active:
 “THR LK” flashes amber on the FMA
 ECAM “ENG THRUST LOCKED” flashes every 5 seconds
 ECAM displays “THR LEVERS … MOVE”
 A single chime sounds and the MASTER CAUTION light flashes every 5 seconds. All warnings cease when
the thrust levers are moved out of the detent.
The thrust is locked or frozen at its level prior to disconnection. Moving the thrust levers out of the CL or MCT
detent suppresses thrust lock and allows manual control by means of the thrust levers.
3. What is TOGA Lock?
TOGA thrust is frozen and thrust lever movement will have no effect.
To cancel TOGA LK, disconnect the autothrust.
ALPHA FLOOR protection commands TOGA thrust regardless of the positions of the thrust levers. This protection is
available from lift-off to 100 feet RA on approach.
ALPHA FLOOR calls up the following indications:
 “A FLOOR” in green surrounded by a flashing amber box on the FMA and in amber on the E/WD as long as
 floor conditions are met.
 “TOGA LK” in green surrounded by a flashing amber box on the FMA when the aircraft leaves the  floor
conditions. TOGA thrust is frozen and thrust lever movement will have no effect.
Note: ALPHA FLOOR is inhibited:
 Under alternate or direct flight control law.
 In case of engine failure with flaps extended
4. What should be done if GPS primary is lost during an RNAV approach?
A go-around is mandatory.
2009 – 2010 TGS Study Guide
___________________________________________________________________________________________
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Unofficial Airbus Study Site www.airbusdriver.net
5. When is the predictive windshear detection available?
The Predictive Windshear system operates when the aircraft is below 1,500’ AGL. It scans the airspace within 5
nm forward of the aircraft for windshears. When a windshear is detected, a warning, caution, or advisory message
appears on the PFD and (depending on the range selected on the ND) an icon appears on the ND. Predictive
windshear warning and caution are associated with an aural warning. During takeoff, both warnings and cautions
are available within 3 nm. Alerts are inhibited above 100 knots and up to 50’. During landing, alerts are inhibited
below 50’.
When the WINDSHEAR switch is in AUTO, the Predictive Windshear function is activated. Windshear areas are
detected by the antenna scanning below 2,300’ RA, even if the transceiver selector is set to OFF, and displayed on
the ND if below 1,500’.
Predictive windshear aural alerts have priority over TCAS, EGPWS, and other FWC aural warnings. They are
inhibited by windshear detection by FAC (Reactive) and stall warning aural messages.
The Airbus Reactive Windshear Detection function is available during takeoff from liftoff to 1,300 feet AGL, and
on approach from 1.300 feet AGL to 50 feet AGL, when aircraft configuration is 1 or greater.
When a FAC detects windshear conditions, it triggers a warning:
 “WINDSHEAR” in red on both PFD’s (for at least 15 seconds)
 An aural warning, “WINDSHEAR, WINDSHEAR, WINDSHEAR”
6. How do I confirm that I have actually ARMED the ILS approach for the flight director or autopilot to
capture?
 FMA column 2 (second line): G/S (blue)
 FMA column 3 (second line): LOC (blue)
7. How is the Go Around mode engaged?
When at least one thrust lever is placed in the TOGA detent, the slats/flaps lever is at least in position 1, and:
 the aircraft is airborne or
 the aircraft has been on the ground for less than 30 seconds.
8. Will the G/S mode engage without the LOC mode engaged?
No
9. What is the speed referenced when the FMA displays SRS during a normal takeoff?
Speed Reference System is a vertical mode which controls pitch to maintain a speed defined by SRS guidance
(provided V2 is inserted in the MCDU PERF TO page, the slats are extended, and the aircraft is on the ground). It
engages automatically when the thrust levers are set to TOGA or MCT/FLX detent. It disengages manually when
another vertical mode is engaged, or automatically when the aircraft reaches acceleration altitude or an FCU
selected altitude.
The pitch guidance maintains airspeed at V2 + 10 knots. If an engine failure is detected, pitch guidance maintains
the greater of V2 or current speed. Additionally, the mode protects against high pitch attitude and provides a
　
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