Primary Flight Controls
- Rudder
- Elevator
- Ailerons (Spoilers assists the aileron for roll control)
Secondary Flight Controls
- Flaps
Powered Flight Control Surfaces (PFCS)
- Elevators, Spoilers and Rudder
- Hydraulically powered
- PFCS positions are shown on the pilot’s Multi-Function Display (MFD) in the Permanent Systems Data Area at the bottom portion of the display
Flight Control Electronic Control Unit (FCECU)
- Location
- Description
- Channel 1 (left channel) is powered by the
- Channel 2 (right channel) is powered by the
- Located under the passenger cabin floor
- Is a single electronic unit divided into two channels; 1 and 2 (also referred to a left and right channels)
- Two channels function separately from each other throughout the entire system
- The left and right channels of the FCECU send electrical outputs to primary and secondary flight control systems
- Channel 1 (left channel) is powered by the “LEFT Essential DC bus”
- Channel 2 (right channel) is powered by the “RIGHT Essential DC bus”
Elevator Pitch Control
• Pitch control of the airplane is maintained by
• Elevators are attached to the
• Both control columns are connected to each other by a
• Left control column operates the ___ elevator and the right control column operates the ___ elevator
• Movement of the control columns is transferred through
- Pitch control of the airplane is maintained by two mechanically controlled, and hydraulically powered elevators
- Elevators are attached to the trailing edge of the left and right horizontal stabilizers
- Both control columns are connected to each other by a “Pitch Disconnect” system so that they both operate together for normal operations
- Left control column operates the left elevator and the right control column operates the right elevator
- Movement of the control columns is transferred through two fully independent cable and pulley control circuits to the elevator Power Control Units (PCUs)
Elevator Pitch Control
- How many PCUs for each elevator surface and which are active and stanby
- Which hydraulic systems control which PCUs
- Where is the PCU compensator located and what is it’s purpose
• 3 identical hydraulic PCUs for each elevator surface (outboard, center, and inboard PCU)
o “Outboard” and “Center” PCUs on each elevator are active at all times
o Inboard PCUs serve as standby control units
• #1 hydraulic system supplies power to the left and right outboard PCUs
• #2 hydraulic system supplies power to the left and right center PCUs
• #3 hydraulic system supplies power to the left and right inboard PCUs in the event that the #1 and/or #2 hydraulic systems fail
• PCU compensator is installed in the return line of the #3 hydraulic system:
o Purpose of the compensator is to maintain positive pressure on the elevators for gust lock protection when there is no system pressure available (e.g. when the aircraft is parked)
o Also provides elevator flutter suppression in flight should there be a loss of system pressure
Elevator System Malfunctions
• A loss of #1 and/or #2 Hydraulic System will result in
• Automatic activation is confirmed in the cockpit by an indication of
• #3 Hydraulic system can be activated manually by pushing
- A loss of #1 and/or #2 Hydraulic System will result in the automatic activation of the No. 3 hydraulic system to supply pressure to the inboard elevator PCUs
- Automatic activation is confirmed in the cockpit by an indication of “#3 HYD” system pressure on MFD 2
- # 3 Hydraulic system can be activated manually by pushing the HYD #3 ISOL VLV switchlight
Flap Auto Pitch Trim / Pitch Trim
- When does the AFCS supplie automatic pitch trim commands to the elevator control system and why
- Autopilot pitch trim signals, based on flap position, are sent to the ___ which then gives trim command signals to the pitch trim actuators
- Pitch trim signals from the elevator trim switches or from the autopilot, are prioritized by the ___ in the following order: (3)
• During flap extension or retraction (15° to 35° only) AFCS supplies automatic pitch trim commands to the elevator control system to reduce the pitch trim forces felt on the control columns
• Autopilot pitch trim signals, based on flap position, are sent to the FCECU which then gives trim command signals to the pitch trim actuators
• Pitch trim signals from the elevator trim switches or from the autopilot, are prioritized by the FCECU in the following order:
o Pilot trim switch inputs
o Copilot trim switch inputs
o Autopilot trim inputs
• The trim signal with the highest priority controls the pitch trim actuator
Flap Auto Pitch Trim / Pitch Trim
• Flap Auto Pitch Trim system is active when all of the following conditions exist: (4)
• A “Clacker” audio tone will sound when either of the 2 following conditions are met:
• Flap Auto Pitch Trim system is active when all of the following conditions exist:
o Flaps are selected from 15° to 35° or 35° to 15°, and
o Autopilot is not engaged, and
o Airspeed is
Flap Auto Pitch Trim / Pitch Trim
• Flap Auto Pitch Trim is deactivated when any of the following conditions exist: (7)
• Flap Auto Pitch Trim is deactivated when any of the following conditions exist:
o Airplane is on the ground (Weight On Wheels), or
o Airspeed is > 200 KIAS, or
o Autopilot is engaged, or
o Flaps are not in transitioning from 15° to 35° or 35° to 15°, or
o Manual pitch trim is commanded by either the pilot or copilot, or
o Pitch commands are in excess of the pitch limits, or
o Flight control system failures or failures within the AFCS occur
Rudder/Yaw Control
- Yaw control is provided by a
- Rudder consists of two sections; a fore section and an aft section
- Fore section is attached to the ___ and operated by two PCUs; an ___ PCU and a ___ PCU
o __ Hydraulic system powers the lower PCU
o __ Hydraulic system powers the upper PCU
o If either hydraulic system fails, how will it the rudder be controlled
- Aft section of the rudder is attached to ___
o Aft section of the rudder deflects ___
o Full deflection of the aft section of the rudder can be up to __ degrees off center
- Yaw control is provided by a mechanically controlled, hydraulically powered rudder
- Rudder consists of two sections; a fore section and an aft section
- Fore section is attached to the vertical stabilizer and operated by two PCUs; an upper PCU and a lower PCU
o #1 Hydraulic system powers the lower PCU
o #2 Hydraulic system powers the upper PCU
o If either hydraulic system fails, the remaining PCU will provide normal rudder control - Aft section of the rudder is attached to the fore section by push rods and deflects mechanically with movement of the fore rudder
o Aft section of the rudder deflects twice as far as the fore section
o Full deflection of the aft section of the rudder can be up to 36o off center
Rudder/Yaw Control
- A mechanical rudder input restrictor mechanism limits rudder pedal travel with
- Flap selector lever is mechanically linked to the
- Full rudder travel of __° left or right of center is available when the Flap selector lever is moved out of the __° flap detent position
- Rudder travel is limited to approximately __° left or right of center when the Flap selector lever is in the __° flap detent position
- Yaw damper authority is approximately __° maximum of rudder deflection either side of center
- A mechanical rudder input restrictor mechanism limits rudder pedal travel with Flap selector lever operation
- Flap selector lever is mechanically linked to the copilot’s rudder forward quadrant
- Full rudder travel of 18° left or right of center is available when the Flap selector lever is moved out of the 0° flap detent position
- Rudder travel is limited to approximately 12° left or right of center when the Flap selector lever is in the 0° flap detent position
- Yaw damper authority is approximately 4.5° maximum of rudder deflection either side of center
Rudder Malfunctions
• If a mechanical jam occurs in the ___ rudder PCU, the “RUD 1” switchlight (alternate action) located on the center glareshield panel illuminates
• If a mechanical jam occurs in the ___ rudder PCU, the RUD 2 switchlight (alternate action) on the center glareshield panel illuminates
• Pushing the RUD 1 switchlight depressurizes the ___ rudder PCU and results in the illumination of the RUD 1 HYD caution light
• Pushing off the RUD 2 switchlight depressurizes the ___ rudder PCU and results in the illumination of the #2 RUD HYD Caution light
- If a mechanical jam occurs in the lower rudder PCU, the “RUD 1” switchlight (alternate action) located on the center glareshield panel illuminates
- If a mechanical jam occurs in the upper rudder PCU, the RUD 2 switchlight (alternate action) on the center glareshield panel illuminates
- Pushing the RUD 1 switchlight depressurizes the LOWER rudder PCU and results in the illumination of the RUD 1 HYD caution light
- Pushing off the RUD 2 switchlight depressurizes the UPPER rudder PCU and results in the illumination of the #2 RUD HYD Caution light
Ailerons & Spoilers/Roll Control
- Roll control is provided by the ___ which are assisted by ___
- Ailerons are ___ controlled and operated
- Spoilers are ___ controlled and ___ powered
- Captain’s wheel controls ___
- F/O wheel controls ___
- Each wing has ___ aileron and ___ flight spoilers (inboard & outboard)
- Roll control is provided by the ailerons which are assisted by roll spoilers
- Ailerons are mechanically controlled and operated
- Spoilers are mechanically controlled and hydraulically powered
- Captain’s wheel controls the flight spoilers
- F/O wheel controls the ailerons
- Each wing has one aileron and two flight spoilers (inboard & outboard)
Spoilers
- There is an ___ and ___ roll spoiler panel on each wing
- Roll spoilers operate in conjunction with the ailerons to ___
- Each roll spoiler panel is extended and retracted by ___
- Roll spoiler position is indicated on ___
- There are three modes of spoiler operation:
- There is an inboard and outboard roll spoiler panel on each wing
- Roll spoilers operate in conjunction with the ailerons to assisting with roll control of the airplane in flight
- Each roll spoiler panel is extended and retracted by a hydraulically powered PCU
- Roll spoiler position is indicated on the “PFCS” display located at the bottom of MFD 1
- There are three modes of spoiler operation:
o Flight Mode
o Ground Mode
o Taxi Mode
Spoilers
Flight Mode Operation
- Spoilers extend in proportion to ___
- #1 hydraulic system powers the ___
- #2 hydraulic system powers the ___
- Outboard spoiler operation is deactivated at airspeeds > ___ KIAS
- FCECU disables the outboard spoilers above __ KIAS by shutting off ___ pressure to the outboard system
- Spoilers extend in proportion to the up going aileron to provide roll control
- # 1 hydraulic system powers the inboard spoilers
- # 2 hydraulic system powers the outboard spoilers
- Outboard spoiler operation is deactivated at airspeeds > 170 KIAS
- FCECU disables the outboard spoilers above 170 KIAS by shutting off extension pressure to the outboard system
Spoilers
Ground Mode Operation
- Two ___ in the inboard spoiler system and two in the outboard spoiler system control the ground operation of the spoilers
- Both valves open ___ to allow the spoilers to extend on the ground
- In order for the spoilers to extend in the ground mode on landing, the FCECU and PSEU must confirm the following conditions: (3)
- Two ground extension advisory lights, ___ and ___, located adjacent to the Flight /Taxi switch, illuminate when the inboard and outboard spoiler extend in the ground mode at touch down
- Two lift-dump valves in the inboard spoiler system and two in the outboard spoiler system control the ground operation of the spoilers
- Both valves open together to allow the spoilers to extend on the ground
- In order for the spoilers to extend in the ground mode on landing, the FCECU and PSEU must confirm the following conditions:
o “FLIGHT/TAXI” switch (left glareshield) is in the FLIGHT (up) position and
o Both power levers are at or aft of the FLIGHT IDLE gate and
o PSEU is receiving a Weight-On-Wheels signal from the left and right main landing gear - Two ground extension advisory lights, ROLL INBD and ROLL OUTBD, located adjacent to the Flight /Taxi switch, illuminate when the inboard and outboard spoiler extend in the ground mode at touch down
Spoilers
Taxi Mode Operation
• After landing, all spoiler panels can be retracted for taxiing by ___
• Switch is spring loaded to ___ position but must be manually selected to the ___ position
• Switch is magnetically held in the __ position by a hold-in solenoid
• When both power levers are advanced ahead of ___, the solenoid is de-energized and the switch automatically flips up to the ___ position
• FLIGHT/TAXI switch is manually selected to the ___ position prior to advancing the power levers for take-off
- After landing, all spoiler panels can be retracted for taxiing by selecting the FLIGHT/TAXI switch to TAXI (down) position
- Switch is spring loaded to FLIGHT position but must be manually selected to the TAXI position
- Switch is magnetically held in the TAXI position by a hold-in solenoid
- When both power levers are advanced ahead of FLIGHT IDLE, the solenoid is de-energized and the switch automatically flips up to the FLIGHT position
- FLIGHT/TAXI switch is manually selected to the FLIGHT position prior to advancing the power levers for take-off
Roll Control / Spoiler Malfunctions
• If a PCU linkage jam develops on any of the four spoiler PCUs it will ___
• Pushing the “SPLR 1” switchlight shuts off pressure to the ___ spoiler PCUs and results in the illumination of the ROLL ___ Caution light. This allows the ___ spoilers to retract
• Pushing the “SPLR 2” switchlight shuts off pressure to the ___ spoiler PCUs and results in the illumination of the ROLL ___ caution lights This allows the ___ spoilers to retract
• Left Control Wheel Free (aileron system jam); ONLY the ___ are operational
• Right Control Wheel Free (roll spoiler system jam); ONLY the ___ are operational
o If the right control wheel is rotated more than __° left or right from neutral position, it will result in the continuous illumination of both SPLR 1 and SPLR 2 switchlights
• If a PCU linkage jam develops on any of the four spoiler PCUs it will be eliminated due to the design of the system
• Pushing the “SPLR 1” switchlight shuts off pressure to the inboard spoiler PCUs and results in the illumination of the ROLL “SPLR INBD HYD” Caution light. This allows the inboard spoilers to retract
• Pushing the “SPLR 2” switchlight shuts off pressure to the outboard spoiler PCUs and results in the illumination of the ROLL “SPLR OUTBD HYD” caution lights This allows the outboard spoilers to retract
• Left Control Wheel Free (aileron system jam); ONLY the roll spoilers are operational
• Right Control Wheel Free (roll spoiler system jam); ONLY the ailerons are operational
o If the right control wheel is rotated more than 50° left or right from neutral position, it will result in the continuous illumination of both SPLR 1 and SPLR 2 switchlights
Flaps
- Type of flaps
- How do the flaps operate
- What hydraulic system supplies pressure
- Describe the rudder restrictor
- What activates the PTU and when
- Fowler Type Flaps
- Hydro-mechanical Flap Power Unit (FPU) is electrically activated by a Flap Control Unit (FCU) to operate the flap drive system and move the flaps to their selected positions
- # 1 hydraulic system supplies pressure to the FPU
- Flap selector lever is mechanically connected to a rudder restrictor on the right rudder fore quadrant, mechanically limiting rudder travel when the lever is in the 0° position
- Flap Control Until (FCU) automatically activates the Standby Hydraulic Pump and the PTU when the Flap Selector lever is moved out of 0° position
Flaps
- Describe the “FLAP POWER” Caution light
- Describe the “FLAP DRIVE” Caution light
- Describe the “FLAP LANDING GPWS” switch
NOTE: Do not operate flaps until both engines are stabilized (condition levers ___). Hydraulic pressure needs to build prior to the activation of the Standby & PTU hydraulic pump
NOTE: Takeoff warning horn will sound when both power levers are advanced for takeoff (engine torque exceeds __%) if flaps are set greater than __° or less than __°
- “FLAP POWER” Caution light illuminated, the FCU inhibits further flap movement and the flaps will lock in the last position reached prior to failure
- “FLAP DRIVE” Caution light illuminated, the flaps may still be operable in some instances only with reduced performance. The type fault is automatically reset if the condition goes away
- “FLAP LANDING GPWS” switch – An audio warning tone of “TOO LOW FLAPS” will be heard if the flap lever and the “FLAP LANDING GPWS” switch do not match (i.e. flap lever selected to 35 and switch selected to 15)
NOTE: Do not operate flaps until both engines are stabilized (condition levers 660). Hydraulic pressure needs to build prior to the activation of the Standby & PTU hydraulic pump
NOTE: Takeoff warning horn will sound when both power levers are advanced for takeoff (engine torque exceeds 50%) if flaps are set greater than 20° or less than 3.5°
Stall Protection System
- Uses ___ type of power
- What calculates when the aircraft is approaching a stall
- Stall Protection System operates when the conditions that follow are met: (3)
• AC Powered (115vAC)
• 2 Stall Protection Modules (SPM 1 and SPM 2) calculate when the aircraft is approaching a stall
• Stall Protection System operates when the conditions that follow are met:
o Calibrated airspeed (true) is less than 215 knots
o Altitude is more than 200 feet AGL
o Stick pusher “SHUT OFF” switchlight is not pushed to the OFF position
Stall Protection System
• SPM1 and SPM2 use the following parameters to determine an approaching stall condition: (5)
• SPM1 and SPM2 use the following parameters to determine an approaching stall condition:
o Average of two Angle of Attack (AOA) inputs
o Flap position – input from Flap Position Indication Unit
o Mach number – input from ADU 1 & 2
o Engine torque
o Icing status – input from the REF SPEEDS switch
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Q400 Limitations Oil, APU, Powerplant56
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Q400 General Limitations49
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Q400 NNBM Limitations22
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Q400 Memory Items22
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Electrical System40
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Fuel System24
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Fire Detection/Protection25
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APU5
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Hydraulics14
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Air Conditioning and Pressurization19
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Ice & Rain Protection16
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Powerplant28
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Flight Controls23
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Landing Gear & Brakes11
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Pneumatics7
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Aircraft General26
