Flight Controls¶
Flight Controls: 1 General¶
The flight control system includes movable surfaces, control systems, associated indications, and alerting systems. Primary and secondary flight controls permit to control the aircraft on the three axes. Primary flight controls include: - One aileron equipped with spring tab and one spoiler on each wing for roll axis - Two elevators equipped with balance tab for pitch axis - One rudder equipped with spring tab for yaw axis. Secondary flight control for lift augmentation is achieved with two flaps on each wing, one inboard and one outboard. Ailerons, elevators, and rudder are mechanically actuated. Spoilers and flaps are hydraulically actuated by the blue hydraulic system. Wind protection is achieved on ground by: - A locking mechanism on pitch and roll axes - A damping unit on yaw axis limiting excessive rudder travel speed.
AILERON SPRING TAB SPOILER ELEVATOR INBOARD FLAP OUTBOARD FLAP SPRING TAB & TRIM RUDDER SPRING TAB TAB (BALANCE & TRIM)
Flight Controls: 1 DESCRIPTION¶
Flight Controls: 1.1 Description¶
The two control wheels operate mechanically the two ailerons and the two spoilers’ hydraulic valve blocks. Spoiler deflection starts after 2.5 ° of aileron deflection. Wheel travel is ± 65 °. Aileron travel is 14 ° UP / 14 ° DOWN. A spring tab provides a flexible compensation that automatically increases with the aerodynamic loads applied on the ailerons. This ensures a reduction in the pilot’s efforts. Roll Aileron trim function is performed by varying the neutral position of the LH aileron tab. The trim function is electrically controlled from a twin control switch through an electrical actuator. Trim tab travel displayed on the roll trim position indicator is added to the automatic tab travel. LH Aileron trim controlled tab travel: 6.7 ° UP / 6.7 ° DOWN. Full roll trim travel requires about 15 s.
RIGHT SPOILER SPOILER SPRING TAB CONTROL WHEELS SPOILER ACTUATOR SPLR FLT CTL TRIM 110VU AIL AIL WING DN R WING L I A AILERON TRIM INDICATOR AILERON SPOILER VALVE BLOCK AP ROLL ACTUATOR TORQUE TUBE CABLE TENSION REGULATOR FLIGHT DATA RECORDER FLIGHT DATA AQUISITION UNIT AILERON PROXIMITY SWITCH POSITION TRANSMITTER SPRING TAB POSITION TRANSMITTER TRIM ACTUATOR POSITION TRANSMITTER SPOILER INDICATOR LIGHT
Flight Controls: 2 CONTROLS¶
Flight Controls: 2.1 Spoiler Position Indicator¶
SPLR
When green light comes on, each one indicates that the associated spoiler is not in the retracted position.
Flight Controls: 2.2 Roll Trim Position Indicator¶
EWD L R L R L R L R L R L R L R
Aileron trim symbol indicates the aileron trim tab travel. Aileron trim symbol is: - White when AP is engaged - Cyan either when AP is not engaged or when AP is engaged and generates a RETRIM ROLL message on FMA - Amber when AP is engaged and generates a AILERON MISTRIM message on FMA.
Moreover when AP is engaged and generates a RETRIM ROLL message on FMA, a cyan arrow appears above the aileron trim symbol to indicate the trim direction request (opposite trim command is inhibited).
Flight Controls: 2.3 Roll Trim Control Switch¶
L WING DN R WING DN AIL AIL TRIM 110VU Controls the roll trim actuator. For operation, both switches must be moved and held in the same direction (L WING DN or R WING DN) to energize the system (safety reasons).
Flight Controls: 3 ELECTRICAL SUPPLY¶
Flight Controls: 3.1 Electrical Supply¶
EQUIPMENT DC BUS SUPPLY (C/B) AC BUS SUPPLY (C/B) Spoiler position indication DC BUS 1 (on lateral panel C/B SPLR IND) NIL Roll trim DC EMER BUS (on lateral panel C/B AIL TRIM) NIL Roll (pitch, yaw) Trim position indication NIL 26 VAC STBY BUS (C/B FLT CTL/TRIM POS IND)
Flight Controls: 4 SYSTEM MONITORING¶
Flight Controls: 4.1 Retrim Roll L(R) Wing DN¶
CONDITION VISUAL AURAL When the trim threshold limit is exceeded and a trim control is required. - RETRIM ROLL L(R) WING DN amber message on FMA - Aileron trim indicator becomes cyan on EWD - Cyan arrow appears NIL
Flight Controls: 4.2 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
Flight Controls: 1 DESCRIPTION¶
Flight Controls: 1.1 Description¶
Each control column mechanically drives the associated elevator and, through a pitch coupling mechanism, the other elevator and the opposite control column. In case of jamming, pitch control will be recovered by applying on both control columns a differential force (520 N) disengaging the pitch coupling system. The non affected channel enables the aircraft to be operated safely. System recoupling has to be performed on ground. Pitch uncoupling generates PITCH DISCONNECT red alert. Control column travel: 11.25 ° up, 6.75 ° down. Elevators travel: 23 ° up, 13 ° down. Elevators automatic tab travel: 50 % of the pitch control course. Pitch trim is performed by off setting both tabs neutral position. Normal trim (control column) and STBY trim (pedestal) supply appropriate part of each actuator. Each trim tab is activated by a dedicated actuator. The two actuators are synchronized by a flexible shaft. In case of pitch tabs desynchronization: - An alert is generated by the FWS - Normal and STBY pitch trim control are inoperative - AP disconnects. Trim tab travel, displayed on the pitch trim position indicator, is added to the automatic tab travel. Elevators trim controlled tab travel: 5 ° up, 1.5 ° down. Full pitch trim travel requires about 30 s in normal and in STBY control. A stick pusher and a stick shaker are provided, preventing the aircraft from reaching a critical angle of attack. When the detected incidence becomes too high, the MFC sends a signal to an electric actuator which shakes the control column at stall alert thresholds. If angle of attack keeps increasing a further threshold is reached and the MFC activates the stick pusher. The complete pitch control linkage assembly is pushed forward. Note 1) There are two stick shakers, one for each control column but only one stick pusher actuator located on the captain pitch channel. In case of pitch uncoupling when the pusher triggering angle of attack is reached, only the captain control column is pushed forward 2) Loss of stick pusher does not lead to stick shaker loss 3) Left and right stick shaker operations are segregated.
Flight Controls: 2 CONTROLS¶
Flight Controls: 2.1 Pitch Trim Rocker Switches¶
DOWN ROCKER SWITCHES UP
ROCKER SWITCHES COVER On each control wheel, two pitch trim rocker switches are installed. It is necessary to operate both rocker switches to activate the normal electrical motor of each trim actuator and to control nose up or down. Both pitch trim rocker switches are protected by a cover to avoid not intentional in-flight operation. The switches are spring loaded to neutral position. If both switches are operated simultaneously but in opposite direction, trimming action stops. If normal trim actuator is actuated during more than 1 s, an aural whooler is generated by the FWS. Note If the AP is engaged, manual trim operation of the rocker switches disengages the AP.
Flight Controls: 2.2 Pitch Trim Position Indicator¶
EWD
UP 2 0 DN UP 3.0 E L E V 3 1 2 Indicates the right trim actuator controlled tab travel. 1 Pointer Pitch trim pointer associated with a numerical value. Pointer color: - Green associated with a numerical value when AP is engaged - Cyan associated with a numerical value in manual mode - Amber associated with a numerical value in case of: o Pitch Trim ASYM o Pitch Mistrim or Pitch Trim failed with AP engaged o Pointer outside of green band in pre takeoff condition (TAKEOFF CONFIG).
2 Green Sector TO trim sector (from 0 ° DN to 2.5 ° UP) Identifies the takeoff range. If takeoff (or takeoff CONFIG test) is performed with pitch trim out of this range, CONFIG warning will be generated by the FWS. 3 Magenta Bug Magenta bug Indicates the managed pitch trim objective.
Flight Controls: 2.3 STBY Pitch Control Switch¶
NOSE UP NOSE DN STBY PITCH This guarded switch controls the electrical motors of each trim actuator. Action on this switch disengages the AP. CAUTION Simultaneous action on a normal rocker switch and the STBY PITCH sw is not recommended.
Flight Controls: 2.4 Stick Pusher Pushbutton¶
FAULT OFF PUSHER STICK
FAULT Light (amber) Indicates a stick pusher or stick shaker failure. CAUTION STALL WARNING aural alert (cricket) is also lost. OFF Position Enables the flight crew to switch off the stick pusher and the stick shaker system. Note STALL WARNING aural alert (cricket) is still active.
Flight Controls: 2.5 Stick Pusher Indication¶
Stick Pusher Annunciator The stick pusher is controlled by the MFC and is a function of signals sent by the angle-of- attack probes. The triggering values for the secondary alarms (stick pusher) depend on the aircraft configuration. A green STICK PUSHER indication is triggered on the FMA to indicate that the stick pusher is operating.
FMA
STICK PUSHER
Flight Controls: 3 ELECTRICAL SUPPLY¶
Flight Controls: 3.1 Electrical Supply¶
EQUIPMENT DC BUS SUPPLY (C/B) AC BUS SUPPLY (C/B) Normal pitch control DC EMER BUS (on lateral panel FLT CTL / R NORM PITCH TRIM) NIL Right standby pitch control DC BUS 2 (on lateral panel FLT CTL / R STBY PITCH TRIM) NIL Left standby pitch control DC EMER BUS (on lateral panel FLT CTL / L NORM & STBY PITCH TRIM & RUD TLU MAN CTL) NIL Pitch (roll, yaw, trim position indicator) NIL 26 VAC STBY BUS (on lateral panel FLT CTL / TRIM POS IND) Stick pusher PWR DC BUS 1 (on lateral panel FLT CTL / STICK PUSHER / PWR SPLY) NIL Stick pusher CTL DC BUS 1 (on lateral panel FLT CTL / STICK PUSHER & CAPT STICK SHAKER) NIL Left stick shaker DC BUS 1 (on lateral panel FLT CTL / STICK PUSHER / CTL & CAPT STICK SHAKER) NIL Right stick shaker DC BUS 2 (on lateral panel FLT CTL / F/O STICK SHAKER & RUD TLU AUTO CTL) NIL ELEVATOR CLUTCH DC ESS (on lateral panel FLT CTL / ELEVATOR CLUTCH PWR SPLY) NIL
Flight Controls: 4 SYSTEM MONITORING¶
Flight Controls: 4.1 TO Configuration¶
CONDITION VISUAL AURAL Pitch trim out of the takeoff range (0 ° DN to 2.5 ° UP) when PL at TO position or simulated so by the TO CONFIG TEST - MW light flashing red - CONFIG red message on EWD - FLT CTL amber message on EWD (only during TO CONFIG TEST) - Pitch trim pointer is displayed amber CRC
Flight Controls: 4.2 Pitch Trim Run Away¶
CONDITION VISUAL AURAL Normal trim actuator actuated during more than 1 s - OR - STBY trim actuator actuated during more than 1 s NIL Whooler
Flight Controls: 4.3 PITCH DISCONNECT-Alert Coupling Mechanism¶
CONDITION VISUAL AURAL Pitch coupling mechanism disconnected. - MW light flashing red - PITCH DISC red message on EWD CRC
Flight Controls: 4.4 PITCH DISCONNECT - Alert Control Column Travel¶
PITCH DISCONNECT - Alert Control Column Travel CONDITION VISUAL AURAL In case of both control columns travel not synchronized. NIL NIL
Flight Controls: 4.5 STICK PUSHER-SHAKER FAULT-Alert¶
CONDITION VISUAL AURAL Stick pusher / shaker fault - MC light flashing amber - FLT CTL PUSHER amber message on EWD - STICK PUSHER FAULT amber light in STICK PUSHER / SHAKER pb SC
Flight Controls: 4.6 PITCH TRIM ASYM-Alert¶
CONDITION VISUAL AURAL Pitch tabs desynchronisation - MC light flashing amber - PITCH TRIM ASYM amber message on EWD SC
Flight Controls: 4.7 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
Flight Controls: 4.8 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
Flight Controls: 5 LATERAL MAINTENANCE PANEL¶
Flight Controls: 5.1 Pitch Trim¶
A PTT pb is provided on RH lateral maintenance panel to test the pitch tabs shift detection unit.
PTT PITCH TRIM COMPT Test Procedure - DC electrical power available - Press and hold test button: o MC light come on amber o PITCH TRIM ASYM amber message on EWD o Pitch trim pointer is displayed amber o Aural alert is SC o Disconnection of AP if engaged.
Flight Controls: 5.2 Elevator Clutch¶
ELEV CLUTCH R E A R M
Enables to reconnect both elevators in case of declutch (Refer to FLIGHT CONTROLS). Reconnection conditions: - Aircraft on ground - Gust lock ON.
Flight Controls: 6 SCHEMATIC¶
Flight Controls: 6.1 Schematic¶
FUNCTIONAL ABSTRACTION - pitch controls
CONTROL COLUMN L/R -> cable-tension regulators -> pitch cable runs
| | |
| +--> stick shaker +--> elevator mechanisms
| +--> stick pusher +--> elevator tabs
| +--> pitch disconnect
|
+--> AP pitch actuator / AP computer
NORMAL PITCH TRIM SWITCHES --> trim actuator --> flexible shaft --> trim actuators
STBY PITCH CONTROL ----------> standby trim path
FWS/FDAU <-------------------- position and control-status transmitters
Flight Controls: 1 DESCRIPTION¶
Flight Controls: 1.1 Description¶
Yaw controls system consists of rudder pedals, TLU, RCU, rudder damper, and trim. Rudder pedals mechanically act on a spring tab and through it on the rudder itself.
Flight Controls: 1.2 Spring Tab¶
A spring tab provides a flexible compensation which automatically increases with the aerodynamic loads applied on the rudder, therefore ensuring a reduction of the flight crew’s efforts when really needed (engine failure).
- Fig. 1 : Neutral Position - Without airload on the surface (V = 0), when rudder pedals are moved to full deflection, the spring tab stays in line with the rudder until the rudder reaches its stops, above that point it moves the tab.
- Fig. 2 : Without Aerodynamic Force -
With airload on the surface (V ≠ 0), the spring tab has a travel in the opposite direction of the rudder which generates a compensating moment. Spring travel increases with airspeed. Low V1 Low B1 Spring slightly loaded
V1 B1 - Fig. 3 : Low Aerodynamic Force - V2 B2 High V2 High B2 Spring strongly loaded Greater force from the rudder pedals
- Fig. 4 : High Aerodynamic Force -
Flight Controls: 1.3 Travel Limitation Unit (TLU)¶
The travel limitation unit is fitted on the aircraft to limit pedals travel in order to prevent any damaging rudder travel when flying at high speed.
FAULT ADC 1 CAC 1 MFC 1A AUTO LO SPD HI SPD TLU SWITCH ADC 2 CAC 2 MFC 2A RUDDER TRAVEL LIMITATION UNIT The TLU automatic control is done through ADC 1/2, via CAC 1/2, when reaching 185 kt during an acceleration and when reaching 180 kt during a deceleration. The TLU setting (high speed or low speed) may also be performed manually in case of ADC or CAC’s failure.
Flight Controls: 1.4 Releasable Centering Unit (RCU)¶
A releasable centering unit is provided between the rudder and the linkage to the flight crew pedals to enable rudder position stabilization when no action is applied on the pedals. The RCU position change with trim setting. As soon as the yaw trim control lever is moved to the left or to the right, the releasable centering unit is disengaged to enable trim setting. It will be re-engaged at the new position when the yaw control switches are released. The rudder trim levers control the RCU centering process. Any action on the levers is sufficient to declutch the RCU. When the levers are returned to neutral, the RCU is re-engaged in the new position and the rudder cam is centered.
Flight Controls: 1.5 Damper¶
The rudder is linked to the aircraft structure by a damper: - In flight this damper regulates rudder travel speed - On ground it limits excessive movement generated by gusts and avoids damaging the structural stops.
DAMPER TAB LINKAGE TO PILOTS PEDALS TRIM = VARIATION OF SPRING TAB ZERO POSITION RELEASABLE CENTERING UNIT
Flight Controls: 1.6 Yaw Trim¶
It is performed by off setting the spring tab zero position. Yaw trim is electrically controlled from a twin rudder selector or from the autopilot, through a trim actuator. Units of trim motor displacement are displayed on the yaw trim position IND. Maximum values are ±3 dots. Full yaw trim travel requires about 15 s.
Flight Controls: 2 CONTROLS¶
Flight Controls: 2.1 TLU Control and Indication¶
FAULT TLU LO SPD HI SPD AUTO FLT CTL
- TLU switch :
- This is a guarded switch.
- AUTO
-
- Normal position in flight.
- HI SPD / LO SPD
- Used based on IAS after FAULT lights on. FLT CTL FAULT light : Comes on amber when a system failure is detected : - System disagreement - Both ADC failure - Speed disagreement between the two ADC - TLU position synchro failure
Flight Controls: 2.2 TLU LO Speed Label¶
A TLU LO SPEED green label appears on EWD when the TLU is in Full authority position.
EWD
TLU LO SPEED
Flight Controls: 2.3 Yaw Trim Position Indicator¶
Indicates units of trim motor displacement.
EWD
YAW TRIM POINTER YAW TRIM SCALE RETRIM NOSE INDICATION
L R R U D L R R U D L R R U D Pointer color is: - Cyan in normal configuration - Green in case of yaw AUTO trim activation - Amber in case of yaw mistrim, or yaw AUTO trim failure, with YD engaged.
Flight Controls: 2.4 Yaw Trim Control Switches¶
RUD RUD NOSE LH NOSE RH Controls the yaw trim actuator. As a safety device both levers must be moved and held in the same direction (NOSE LH or NOSE RH) to energize the system and trim the aircraft.
Flight Controls: 3 ELECTRICAL SUPPLY¶
Flight Controls: 3.1 Electrical Supply¶
EQUIPMENT DC BUS SUPPLY (C/B) AC BUS SUPPLY (C/B) Yaw trim DC EMER BUS (on lateral panel C/B RUD) NIL Yaw (pitch, roll) Trim position indicator NIL 26 VAC STBY BUS (C/B FLT CTL / TRIM POS IND) Travel Limitation Unit control power (AUTO CONTROL) DC BUS 2 (on lateral panel C/B TLU CTL) NIL Travel Limitation Unit control power (MANUAL CONTROL) DC EMER BUS NIL Travel Limitation Unit monitoring NIL 26 VAC STBY BUS
Flight Controls: 4 SYSTEM MONITORING¶
Flight Controls: 4.1 TLU FAULT-Alert¶
CONDITION VISUAL AURAL System disagree (target vs actual TLU position) - OR - ADC 1+ 2 FAILURE - OR - TLU position synchro failure - MC light flashing amber - FLT CTL TLU amber message on EWD - TLU FAULT amber light on overhead panel SC
Flight Controls: 4.2 DUTCH ROLL TENDENCY-RUDDER RELEASABLE CENTERING UNIT¶
FAIL-Alert CONDITION VISUAL AURAL Dutch roll oscillation tendency (releasable centering unit clutch energized more than 60 s with Y/D off) - MC light flashing amber - FLT CTL RUD RCU amber message on EWD SC
Flight Controls: 4.3 AP Rudder Out of Trim¶
CONDITION VISUAL AURAL Trim threshold limit exceed. - RETRIM A/C NOSE L amber message on FMA - RETRIM A/C NOSE R amber message on FMA - Cyan arrow on EWD rudder trim indicator. NIL
Flight Controls: 4.4 RETRIM A-C Nose L(R)¶
CONDITION VISUAL AURAL Trim threshold limit exceed. - RETRIM A/C NOSE L amber message on FMA - RETRIM A/C NOSE R amber message on FMA - Cyan arrow on EWD rudder trim indicator. NIL
Flight Controls: 4.5 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
Flight Controls: 5 SCHEMATIC¶
Flight Controls: 5.1 Schematic¶
TO BRAKE CONTROL FORCE DETECTOR ROD PEDAL POSITION ADJUSTER AP YAW ACTUATOR TRIM ACTUATOR RUDDER RUDDER DAMPER TRAVEL LIMITER UNIT RELEASABLE CENTERING UNIT POSITION TRANSMITTER SPRING TRIM TAB L R R U D YAW TRIM POINTER YAW TRIM SCALE NOSE LH RUD NOSE RH RUD
FUNCTIONAL ABSTRACTION - yaw controls
RUDDER PEDALS -> force detector rod -> travel limiter unit -> rudder linkage
| | |
+--> pedal-position adjuster +--> AP yaw actuator |
+--> rudder damper |
+--> trim actuator --+
+--> position transmitter
Trim command/position -> yaw-trim panel and yaw-trim indication.
Brake-control input is taken from the pedal assembly.
Flight Controls: 1 DESCRIPTION¶
Flight Controls: 1.1 Description¶
Refer to DSC.27.5.6.1 Schematic Two flaps on each wing achieve the lift augmentation, one inboard and one outboard, linked mechanically with a fail safe design. The FLAPS control lever has three distinct positions: 0°, 15°, and 30°. The flight crew cannot select an intermediate position. The lever and the flaps positions electrically control the flap valve which hydraulically actuates the four flaps actuators. Possible asymmetry is sensed by two flaps position transmitters and detected by the MFC when an angle of 6.7 ° is reached. Then the electrical supply to the flap control system is isolated: - The flaps stay in their present position - The control lever has no effect on the system up to a maintenance action. A FLAP UNLK alert is provided to inform the flight crew of flaps spurious retraction. The alert is triggered if spurious retraction of more than 4 ° occurs. Note When wing flaps are extended, the VMO alert (clacker) operates at VFE. VFE FLAPS 15 = 185 kt VFE FLAPS 30 = 150 kt
Flight Controls: 1.2 Flaps Hydraulic Power Supply¶
14, 0, 4, 3 V13.2 L_CB_00000000_0000000_000_00_00
BLUE GREEN BLUE PUMP GREEN PUMP FLAP VALVE BLOCK AUX PUMP M M M X FEED OUTBOARD FLAP INBOARD FLAP FLAP ACTUATORS OUTBOARD FLAP INBOARD FLAP FLAP ACTUATORS
Flight Controls: 2 CONTROLS¶
Flight Controls: 2.1 Flaps Control Lever¶
30° FLAPS 0° 15° 30° 0° 15°
Controls the flaps operation. Distinct positions correspond to FLAPS 0°, 15°, 30°. To change flaps position, pull up the lever, move it to the selected position (an amber strip at the bottom of the lever is visible as long as the lever is not in one of the three distinct positions) and release the lever.
Flight Controls: 2.2 Flaps Position Indicator¶
The flaps position indication on flight control part of EWD page is the mean value of left and right sides flaps position. In case of loss of right or left flaps position, the valid flap position is used for flap position display. If both right and left flap position are not available, flap position is not displayed.
Selected flap position is indicated below Flap indicator by “SEL: xx°“ label. A flap position bullet corresponding to flaps command is filled in: - Cyan when difference between flap position and flap command is higher than 1 ° - Green when difference between flap position and flap command is lower than 1 °. Flaps position color is: - White when flap position is at 0 ° - Green when the difference between flap command and position is lower than 1 ° (except at 0 °) - Cyan when the flaps extend or retract - Amber when: Flap asymmetry is detected or flap jam is detected or flap command failure is detected - Amber and crossed when both flaps position are invalid - Red when flap unlocked is detected.
EWD
SEL 0° SEL 30° SEL 30° SEL 30° SEL 30° Note Repeated appearance in flight of the cyan flap position while wing flaps have reached the selected position reveals a leakage in the hydraulic lock incorporated in the valve block.
Flight Controls: 3 ELECTRICAL SUPPLY¶
Flight Controls: 3.1 Electrical Supply¶
EQUIPMENT DC BUS SUPPLY (C/B) AC BUS SUPPLY (C/B) Flaps control and asymmetry detection DC STBY BUS (on lateral panel C/B CTL) NIL Flaps position indicator NIL 26 VAC BUS 1 (on lateral panel C/B POS IND)
Flight Controls: 4 SYSTEM MONITORING¶
Flight Controls: 4.1 FLAPS UNLK - Alert¶
CONDITION VISUAL AURAL Flaps untimely retraction when flaps extended. - MW light flashing red - FLAPS UNLK red message on EWD CRC
Flight Controls: 4.2 TO Configuration¶
CONDITION VISUAL AURAL Flaps not in appropriate TO position when PL at TO position or simulated so by the TO CONFIG TEST. - MW light flashing red - CONFIG red message on EWD - FLT CTL amber message on EWD (only during TO CONFIG TEST) - Flap position indication is amber light on the flaps indicator. CRC
Flight Controls: 4.3 FLAPS ASYM-Alert¶
CONDITION VISUAL AURAL Flaps asymmetry of more than 6.7 ° during flaps actuation. - MC light flashing amber - FLAPS ASYM amber message on EWD - Flap symbol amber on flaps position indicator on EWD SC
Flight Controls: 4.4 Flaps Jam¶
CONDITION VISUAL AURAL This alert informs that flaps have not reached the selected position. - OR - The CACs compare the half sum of RH and LH Flap position to the selected position. - OR - If the difference is higher than 1° during more than 30 seconds : - MC light flashing amber - FLAPS JAM amber message on EWD - Flap position indication is amber light on the flaps indicator. SC
Flight Controls: 5 LATERAL MAINTENANCE PANEL¶
Flight Controls: 5.1 Flaps Unlock Test¶
UNLK PTT FLAPS CAUTION FLAPS RET On RH lateral maintenance panel, a pushbutton is provided, for maintenance purpose only, to test flaps unlock alarm relays. Test Procedure - DC electrical power available - Hydraulic power available - Flaps extended to other than 0° position - Press and hold test button. The flaps retract as long as the button is held and FLAPS UNLK red message comes on the EWD each time the flap position passes over a selectable position. - Button released: flaps come back to selected position.
Flight Controls: 5.2 Flaps ASYM Test¶
A periodic test to ensure correct operation of asymmetry detection system is provided on ground. Pressing ASYM PTT pb introduces a 10 ° difference between values read by transmitters. It simulates an asymmetry of more than 6.7 °: - Operation of control lever does not cause any flap extension or retraction - Appearance of FLAP ASYM alert and associated procedure on EWD page. This test is inhibited in flight by a flight/on ground condition.
FLAPS
ASYM PTT
Flight Controls: 6 SCHEMATIC¶
Flight Controls: 6.1 Schematic¶
FLAP CONTROL LEVER --> [FLAP CONTROL SWITCH UNIT] --> [MFC 1 / MFC 2]
|
AP ---------------------------------------------+
v
[FLAP VALVE BLOCK]
|
+------------------------+------------------------+
v v
LEFT FLAP ACTUATORS -- torque shaft -- RIGHT FLAP ACTUATORS
| |
position transmitters --------------------------> CAC/FDAU
MFC monitoring inputs: flap unlock, flap asymmetry, lever reference and
left/right flap positions. Electrical supply is from standby AC/DC buses.
Flight Controls: 1 DESCRIPTION¶
Flight Controls: 1.1 Description¶
A gust lock system is provided to protect the pitch and roll flight controls on ground and to limit the PL travel slightly below FI. This system includes an elevator mechanical locking device and one aileron electrical-mechanical locking device. This system provides protection against takeoff with gust lock engaged, or too high power setting when in hotel mode.
Flight Controls: 1.2 Elevator Mechanical Locking Device¶
The system locks the control column in pitch and therefore control surfaces. This device is controlled by a control lever on the pedestal and mechanically operated through cables and gears.
Flight Controls: 1.3 Aileron Electro Mechanical Locking Device¶
The system is composed of two electro-mechanical locking devices locking one aileron each. Each locking device is electrically actuated through switches installed on the GUST LOCK lever. ELEVATOR LOCKING DEVICE GUST LOCK LEVER AIL LOCK MFC AILERON LOCKING DEVICE
Note Ailerons can be locked slightly beyond the neutral position. Therefore the control wheel can be tilted (+/-5 °), according to the actual position of ailerons.
Flight Controls: 2 CONTROLS¶
Flight Controls: 2.1 Gust Lock Lever¶
GI FI 35 40 45 50 55 60 65 70 75 75 70 65 60 55 50 45 40 ON POWER POWER GUST LOCK OFF OFF 902VU 35 MAX PWR MAX PWR 80 80 85 85 2 1 R E V R E V When the gust lock is engaged, the PL travel is limited slightly below FI to provide protection against takeoff and too high power setting when in hotel mode. The gust lock handle can be put into the locking notch whatever the position of the flight controls is but these controls must be brought to neutral to positively engage the locking devices.
Flight Controls: 3 ELECTRICAL SUPPLY¶
Flight Controls: 3.01 Electrical Supply¶
EQUIPMENT DC BUS SUPPLY (C/B) AC BUS SUPPLY (C/B) Aileron lock indicator DC EMER BUS (on lateral panel C/B AIL TRIM & AIL LOCK WARN) NIL Aileron lock CTL DC ESS BUS (on lateral panel C/B GUST LOCK AIL) NIL
Flight Controls: 4 SYSTEM MONITORING¶
Flight Controls: 4.1 AIL LOCK LIT-Alert Gust Lock Disagree¶
CONDITION VISUAL AURAL Disagree between aileron locking actuators and gust lock control (temporized alert 8 s) - MC light flashing amber - AIL LOCK LIT amber message on EWD SC
Flight Controls: 4.2 AIL LOCK LIT-Alert CONFIG¶
CONDITION VISUAL AURAL Aileron locking actuators not fully retracted and PL on TO position - OR - Disagree between aileron locking actuators and gust lock control during TO CONFIG test - MW light flashing red - CONFIG red message on EWD - AIL LOCK LIT amber message on EWD (only during TO CONFIG TEST) - FLT CTL amber message on EWD (only during TO CONFIG TEST) CRC
Flight Controls: 4.3 TO Configuration¶
CONDITION VISUAL AURAL Aileron locking actuators not fully retracted and PL on TO position - OR - Disagreement between aileron locking actuators and gust lock control during the TO CONFIG TEST - MW light flashing red - CONFIG red message on EWD - FLT CTL amber message on EWD (only during TO CONFIG TEST) - AIL LOCK LIT amber message on EWD (only during TO CONFIG TEST) CRC