Flight Controls Chapter 9

Transcription

1 Flight Controls Chapter 9 Table of Contents Section Flight Controls-Table of Contents Controls and Indicators Pitch and Stabilizer Trim Systems Control Wheel and Column Stabilizer Trim System Stabilizer Trim Lights Aileron and Rudder Trim Controls Aileron Trim Indicator Aileron and Rudder Trim Rudder System Rudder/Brake Pedals EICAS Status Display Yaw Damper Switches Rudder System Light Flight Control Shutoff Switches Speedbrakes Speedbrake Lever Speedbrake Lights Flap System Flap Controls Flap Position Indicator/Alternate Flaps Selector System Description Introduction Pilot Controls Flight Control Surfaces Flight Control Surface Locations Pitch Control Elevator Actuator Control Hydraulic Power Distribution Stabilizer Trim Control D632N00-200R 9.TOC.0.

2 Flight Controls - Table of Contents Electric Trim Alternate Trim Automatic Trim Non normal Operation Roll Control Ailerons Yaw Control Rudder Rudder Ratio Yaw Damping Spoilers Spoiler Speedbrake Operation Flaps and Slats Flap and Slat Sequencing Flap Load Relief Autoslats Flap/Slat Non Normal Operation Alternate Flap Operation Leading Edge Disagreement Leading Edge Asymmetry Trailing Edge Disagreement Trailing Edge Asymmetry Load Relief Inoperative EICAS Messages Flight Controls EICAS Messages TOC.0.2 D632N00-200R

3 Flight Controls Chapter 9 Controls and Indicators Section Flight Controls-Controls and Indicators Pitch and Stabilizer Trim Systems Control Wheel and Column 2 3 CONTROL WHEEL Pitch Trim Switches Spring loaded to neutral. Push (both switches) electrically signals stabilizer movement. 2 Control Wheel Rotate deflects the ailerons and spoilers in the desired direction. Moves and remains displaced with aileron trim. 3 Control Column Push/Pull deflects the elevator movement opposing stabilizer trim stops trimming May 0, 2002 D632N00-200R 9.0.

4 Flight Controls - Controls and Indicators Stabilizer Trim System APL NOSE DN 2 3 APL NOSE DN S T A B T R I M APL NOSE UP O F APL NOSE UP ALTN STAB TRIM NORM CUT OUT 4 C STAB TRIM R CONTROL STAND Alternate Stabilizer Trim (ALTN STAB TRIM) Switches Spring loaded to neutral. Push (both switches) electrically signals stabilizer movement neutralizes conflicting trim commands 2 Stabilizer Trim (STAB TRIM) Indicator indicates stabilizer position in units of trim the green bands indicate the allowable takeoff trim range 3 Stabilizer Trim OFF Flag Trim indicator inoperative. 4 Stabilizer Trim (STAB TRIM) Cut Out Switches NORM hydraulic power is supplied to the related stabilizer trim control module. CUT OUT shuts off the respective center or right hydraulic system power to the related stabilizer trim control module D632N00-200R May 0, 2002

5 Stabilizer Trim Lights Flight Controls - Controls and Indicators STAB TRIM MACH SPD TRIM 3 2 UNSCHED STAB TRIM OVERHEAD PANEL Stabilizer Trim (STAB TRIM) Light Illuminated (amber) stabilizer trim rate is one half the normal control wheel stabilizer trim switch rate. 2 Unscheduled Stabilizer Trim (UNSCHED STAB TRIM) Light Illuminated (amber) uncommanded stabilizer motion detected. 3 Mach Speed Trim (MACH SPD TRIM) Light Illuminated (amber) the mach/speed trim system is inoperative. Aileron and Rudder Trim Controls Aileron Trim Indicator AILERON TRIM CONTROL WHEEL AILERON TRIM Indicator Indicates units of aileron trim. November 23, 2005 D632N00-200R 9.0.3

6 U U Flight Controls - Controls and Indicators Aileron and Rudder Trim RUDDER TRIM NOSE LEFT UNITS NOSE RIGHT LEFT WING DOWN AILERON RIGHT WING DOWN NOSE LEFT R U D D E R NOSE RIGHT 2 3 AFT AISLE STAND RUDDER TRIM Indicator Indicates units of rudder trim. 2 AILERON Trim Switches Spring loaded to neutral. Push (both switches) moves the control wheel, ailerons, and spoilers in the desired direction. 3 RUDDER Trim Control Spring loaded to neutral. Rotate moves the rudder pedals and rudder in the desired direction. Rudder System Rudder/Brake Pedals U D632N00-200R

7 Rudder Pedals Adjustment Crank Pull and Rotate adjusts rudder pedals forward or aft. Flight Controls - Controls and Indicators 2 Rudder Pedals Push deflects the rudder in the desired direction. Refer to Chapter 4, Landing Gear, for brakes and nosewheel steering description. EICAS Status Display STATUS DISPLAY Rudder, Aileron, and Elevator (RUD, AIL, ELEV) Position Indicates rudder, aileron, and elevator flight control surface deflection. Yaw Damper Switches YAW DAMPER L R 2 ON INOP ON INOP OVERHEAD PANEL YAW DAMPER Switches ON the yaw damper is commanded on. Off (ON not visible) the yaw damper is commanded off. 2 Yaw Damper Inoperative (INOP) Lights Illuminated (amber) the yaw damper is inoperative. D632N00-200R 9.0.5

8 Flight Controls - Controls and Indicators Rudder System Light RUDDER RATIO OVERHEAD PANEL RUDDER RATIO Light Illuminated (amber) the rudder ratio system is failed. Flight Control Shutoff Switches FLT CONTROL SHUTOFF ON ON ON 2 OFF OFF OFF L C R ACCESSORY PANEL Flight (FLT) CONTROL SHUTOFF Switches ON the flight control valve is commanded open. Off (ON not visible) the flight control valve is commanded closed. 2 Flight Control Shutoff OFF Lights Illuminated (amber) the flight control valve is closed D632N00-200R May 6, 200

9 Flight Controls - Controls and Indicators Speedbrakes Speedbrake Lever DOWN ARMED UP CONTROL STAND Speedbrake Lever DOWN (detent) all spoiler panels are retracted. ARMED the auto speedbrake system is armed after landing, the speedbrake lever automatically moves to UP and the spoiler panels extend UP the required spoiler panels extend to their maximum in flight or on ground position (intermediate positions can be selected). On the ground: the speedbrake lever moves to DOWN and all spoiler panels retract if either thrust lever is advanced to the takeoff thrust position the speedbrake lever moves to UP and all spoiler panels extend if either reverse thrust lever is raised to the reverse idle detent Speedbrake Lights SPEED BRAKES CENTER FORWARD PANEL 2 3 SPOILERS AUTO SPDBRK OVERHEAD PANEL D632N00-200R 9.0.7

10 Flight Controls - Controls and Indicators SPEED BRAKES Light Illuminated (amber) the speedbrakes are extended when: the flaps are in a landing position, or radio altitude is 800 feet or below 2 SPOILERS Light Illuminated (amber) one or more spoiler pairs are inoperative. 3 Auto Speedbrake (AUTO SPDBRK) Light Illuminated (amber) a fault is detected in the automatic speedbrake system. Note: Light may illuminate momentarily when the Speedbrake handle is moved to the DOWN position after automatic deployment. Flap System Flap Controls FLAP 2 CONTROL STAND Flap Lever Positions the slats and flaps hydraulically. UP the slats and flaps are retracted D632N00-200R November 9, 2003

11 Flight Controls - Controls and Indicators the slats extend to the midrange position the flaps extend to 5, 5, and 20 the slats remain in the midrange position the flaps extend to the commanded position 25 the slats extend to the fully extended position the flaps extend to the slats remain in the fully extended position the flaps extend to 30 the flap load relief system arms 2 Flap Gates prevents inadvertent retraction of the slats. 20 prevents inadvertent retraction of the flaps past the go around position. November 9, 2003 D632N00-200R 9.0.9

12 Flight Controls - Controls and Indicators Flap Position Indicator/Alternate Flaps Selector 2 LEADING EDGE TRAILING EDGE 240K FLAP LIMIT (IAS) 220K 20K UP FLAPS 30 62K 25 ALTN FLAPS K 95K 4 UP 20 NORM LE 30 TE 25 5 ALTN ALTN CENTER FORWARD PANEL TRAILING EDGE Light Illuminated (amber) a flap disagree exists a flap asymmetry exists the flap load relief system is not operating when required 2 LEADING EDGE Light Illuminated (amber) a slat disagree exists a slat asymmetry exists D632N00-200R

13 Flight Controls - Controls and Indicators 3 Flap Position Indicator Indicates flap position. UP the slats and flaps are retracted. Between UP and the slats are between the retracted and midrange position the flaps are between the retracted and position to 30 the flaps are in the indicated position. 4 Alternate (ALTN FLAPS) Flaps Selector NORM normal flap operation, alternate system not in use. UP the slats and flaps are retracted. the slats extend to the midrange position the flaps extend to 5 and 5 the slats remain in the midrange position the flaps extend to the commanded position 20 the slats extend to the fully extended position the flaps extend to 20 Alternate flaps switches must be in ALTN for the slats and flaps to move. 5 Alternate (ALTN) Flaps Switches ALTN arms the selected LE slat or TE flap alternate drive unit shuts off hydraulic power to both the flap and slat drive systems Off (ALTN not visible) alternate flaps and slats command inactive. D632N00-200R 9.0.

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15 Flight Controls Chapter 9 System Description Section Flight Controls-System Description Introduction The primary flight controls are elevators, ailerons, and rudders. The control column, control wheel, and rudder pedals control these flight control surfaces. The primary flight controls are powered by redundant hydraulic systems; there is no manual reversion. Secondary flight controls include a moveable horizontal stabilizer, spoilers, and leading and trailing edge flaps. Spoilers operate differentially to assist ailerons for roll control and symmetrically as speedbrakes. There are three guarded flight control shutoff switches that control hydraulic power to the stabilizer, elevators and rudder. The flight control shutoff OFF light illuminates and the EICAS advisory message L, C, or R FLT CONT HYD displays when a flight control valve is closed. If two or more OFF lights illuminate the EICAS advisory message FLT CONT VALS displays. Pilot Controls The pilot controls consist of: two control columns two control wheels two pairs of rudder pedals control wheel stabilizer trim switches the speedbrake lever the flap lever aileron trim switches rudder trim switch alternate stabilizer trim switches The columns and wheels are connected through jam override mechanisms. If a jam occurs in a column or wheel, the pilots can maintain control by applying force to the other column or wheel to overcome the jam.when a restricted portion of the flight controls are bypassed, some control effectiveness may be lost. The rudder pedals are rigidly connected between the two sides. The speedbrake lever allows manual or automatic symmetric actuation of the spoilers. D632N00-200R 9.20.

16 Flight Controls - System Description Flight Control Surfaces Pitch control is provided by: two elevators a movable horizontal stabilizer Roll control is provided by: two ailerons ten spoilers Yaw control is provided by a single rudder. Flaps and slats provide high lift for takeoff, approach, and landing. Symmetric spoilers are used as speedbrakes. Flight Control Surface Locations Spoilers Leading Edge Slats Rudder Aileron Trailing Edge Flaps Stabilizer Elevator Pitch Control The pitch control surfaces consist of two elevators and a stabilizer. A Mach speed trim system operates the stabilizer to improve speed stability. Elevator Moving the control column signals hydraulic actuators to move the elevators. Elevator positions are shown on the EICAS status display. Separate pointers indicate the left and right elevator deflection. A full scale indication corresponds to the maximum elevator deflection D632N00-200R

17 Flight Controls - System Description If one control column should jam, applying significant forward or aft force to the other causes the two columns to override. Pitch control is then available using the free control column path. Two elevator feel systems provide artificial feel forces to the pilots control columns. Mechanical springs provide feel following a loss of the center and right hydraulic systems. D632N00-200R

18 Flight Controls - System Description Actuator Control Hydraulic Power Distribution Hydraulic System Source Left, Center, or Right. Outboard Spoilers Inboard Spoilers GROUND USE ONLY Aileron Stabilizer Elevator Rudder D632N00-200R May 0, 2002

19 Stabilizer Trim Control Flight Controls - System Description The stabilizer is powered by the center and right hydraulic systems. Stabilizer position commands are sent to the stabilizer trim control modules, which control hydraulic power to the stabilizer. There are two modules, one for each stabilizer hydraulic source. Stabilizer position is displayed on two stabilizer position indicators located on the control stand. Green bands indicate the normal trim settings for takeoff. There are three modes of stabilizer trim control: electric alternate automatic Electric Trim Dual electric pitch trim switches located on the control wheel must be pushed simultaneously to command trim changes. To set Stabilizer Trim less than 3 units, requires use of Alternate Trim system. Alternate Trim Alternate trim control is provided by the alternate stabilizer trim switches on the control stand. Pushing both switches simultaneously commands trim changes and provides an increased range of stabilizer travel. The signals neutralize any other conflicting trim inputs. Automatic Trim The stabilizer is controlled automatically by the autopilot or by a Mach speed trim system when the autopilots are not engaged. The Mach speed trim system improves speed stability by trimming the stabilizer as airspeed changes. Electric, backup, or autopilot trimming inhibits the Mach speed trim system. Automatic stabilizer trim uses only one trim control module and trims at one-half the electric or alternate trim rate. Non normal Operation If a single autopilot is engaged, electric trimming causes the autopilot to disengage. If multiple autopilots are engaged, the electric trim switches are inhibited. Alternate trimming does not cause autopilot disengagement. The UNSCHED STAB TRIM light illuminates and the EICAS caution message UNSCHD STAB TRIM displays when uncommanded stabilizer motion is detected. The light and message also occur if alternate trim is used with an autopilot engaged. May 25, 2004 D632N00-200R

20 Flight Controls - System Description The center and right stabilizer cutout switches control hydraulic power to the respective stabilizer trim control module. Placing both switches in the CUT OUT position removes all hydraulic power from the stabilizer. The control column can be used to interrupt stabilizer trim commands. This feature allows the pilot to quickly stop uncommanded trim changes. The stabilizer trim commands are interrupted if the control column is displaced in the opposing direction. The STAB TRIM light illuminates and the EICAS advisory message STAB TRIM displays when the stabilizer trim rate is one half of the normal control wheel stabilizer trim switch rate. If the malfunction is unique to the electric trim control, full trim rate is available by using alternate trim. The MACH SPD TRIM light illuminates and the EICAS advisory message MACH/SPD TRIM displays when the Mach speed trim system is inoperative. Roll Control An aileron is located on each wing on either side of the outboard trailing edge flap. Aileron surface deflections are proportional to control wheel displacement. Spoilers begin to extend to augment roll control after several degrees of control wheel rotation. Control wheel forces increase as control displacement increases. The control wheels are connected so that, if one control wheel jams, using significant force causes the control wheels to override. Roll control is then available using the free control wheel. Ailerons Aileron positions are shown on the EICAS status display. A full scale indication corresponds to maximum aileron deflection. Dual aileron trim switches located on the aft aisle stand must be pushed simultaneously to command trim changes. Hydraulic power from one of the three hydraulic systems is necessary to accurately set aileron trim. The amount of aileron trim is indicated on a scale on the top of each control column. Note: If the flight crew inadvertently activates aileron trim while an autopilot is engaged, the repositioning of the aileron neutral point is not apparent to the crew. When the autopilot is disengaged, the control wheels and ailerons move to the new (possibly undesired) neutral point and the airplane will roll proportional to the amount of trim input D632N00-200R

21 Flight Controls - System Description Yaw Control Yaw control is provided by a single rudder. Two yaw dampers operate through the rudder control system to improve directional stability. Rudder Rudder position is shown on the EICAS status display. On the ground, a full scale indication corresponds to the maximum rudder deflection. The rudder trim control can be used to command trim changes. The rudder trim indicator shows the units of rudder trim that are commanded. Rudder Ratio The control commands from the rudder pedals and trim control are modified by a rudder ratio changer. As airspeed increases the ratio changer desensitizes these commands from the pilot to reduce the rudder deflection. The ratio changer receives air data computer airspeed inputs and provides control commands to an actuator powered by the left hydraulic system. The actuator then dampens the pilots inputs to the rudder. The RUDDER RATIO light illuminates and the EICAS advisory message RUDDER RATIO displays to indicate the rudder ratio system is failed. Rudder structural protection is provided by automatic depressurization of the left hydraulic system actuator which limits rudder displacement at high airspeeds. However, abrupt rudder pedal input should be avoided at high airspeeds. At low airspeeds the two remaining rudder actuators provide sufficient control for full rudder displacement. If the left hydraulic system is providing normal pressure to the ratio changer, a fault may result in limited displacement of the rudder at all airspeeds. This requires that crosswind and auto land limitations be observed. Yaw Damping The yaw damper systems improve turn coordination and dutchroll damping. The yaw damper INOP light illuminates and the EICAS advisory message L or R YAW DAMPER displays, when a yaw damper is inoperative. Spoilers There are six spoiler panels located on the upper wing surface of each wing. Spoilers on opposing wings are symmetrically paired. Spoiler panels are used as speedbrakes to increase drag and reduce lift, both in flight and on the ground. The spoilers also supplement roll control in response to control wheel commands. D632N00-200R

22 Flight Controls - System Description Spoiler Speedbrake Operation The speedbrakes are controlled by the speedbrake lever located on the control stand. The speedbrake lever has three marked positions: DOWN ARMED UP The speedbrake lever can be placed in intermediate positions between ARMED and UP. In the ARMED position, when the landing gear is fully on the ground (not tilted) and the thrust levers are at idle, the speedbrake lever is driven aft to the UP position and the spoiler panels are fully extended. On the ground when either reverse thrust lever is moved to the reverse idle detent, the speedbrake lever is driven aft to the UP position and the spoiler panels are fully extended. The speedbrake lever does not need to be in the ARMED position. The EICAS caution message SPEEDBRAKES EXT displays and the SPEEDBRAKES light illuminates if speedbrakes are extended when: the flaps are in a landing position radio altitude is 800 feet or below The AUTO SPDBRK light illuminates and the EICAS advisory message AUTO SPEEDBRAKE displays to indicate a fault is detected in the automatic speedbrake system which may result in the loss of automatic speedbrake extension. If the speedbrake lever is armed, the message and light indicate a fault which may result in an inadvertent speedbrake extension in flight. The speedbrake lever should be returned to the DOWN position. The speedbrakes can still be operated manually. The AUTO SPDBRK light may illuminate and the EICAS advisory message AUTO SPEEDBRAKE may display momentarily when the speedbrake lever is moved to the DOWN position after the speedbrakes have been deployed automatically. Both the light and the message will extinguish when the panels are retracted. The SPOILERS light illuminates and the EICAS advisory message SPOILERS displays to indicate that one or more spoiler pairs are inoperative. Flaps and Slats The trailing edge flaps and leading edge slats are high lift devices that increase wing lift and decrease stall speed during takeoff, approach, and landing. Flap and slat positions are indicated by two pointers in the flap position indicator. There are L and R pointers for the left and right wing flaps and slats. The right pointer is normally hidden from view by the left pointer D632N00-200R November 9, 2003

23 Flight Controls - System Description In the flaps position, the flaps and slats move. Flaps, 5, 5, 20 are takeoff flap positions. Flaps 25 and 30 are landing flaps positions. Flaps 20 is used for some non-normal landing conditions. Flap and Slat Sequencing When the flap lever is in the UP detent, all flaps and slats are commanded retracted and the flap position indicator points to UP. Moving the flap lever aft allows selection of flap detent positions, 5, 5, 20, 25, and 30. Starting from flaps UP, selection of flaps commands the slats to move to the midrange position. The flaps extend to. The position indicator pointers move mid way between UP and when the flaps and slats are in transit. The pointers move to the indication when all slats are in the midrange position and flaps reach position. Selection of the flaps 5, 5, or 20 positions commands the flaps to move to the position selected. The slats remain in the midrange position. The position indicator provides only trailing edge flap position indications for all flap settings greater than. Selection of flaps 25 commands both the flaps and slats to move to landing positions. Selection of flaps 30 commands the flaps to extend to the primary landing position. During retraction flap and slat sequencing is reversed. The flap gate at the flaps 20 detent prevents inadvertent retraction of the flaps past the go around position. The flap gate at flaps prevents inadvertent retraction of the slats. Flap Load Relief The flap load relief system protects the flaps from excessive airloads. If the flap airspeed placard limit is exceeded with the flaps in the 30 position, the flaps automatically retract to position 25. When airspeed is reduced, the flaps automatically re extend. Autoslats The autoslat system enhances airplane stall characteristics. Upon receiving a signal from the stall warning system, the slats automatically extend from the midrange position to the fully extended landing position. The slats retract a few seconds after the signal is removed. November 9, 2003 D632N00-200R

24 Flight Controls - System Description Flap/Slat Non Normal Operation Alternate Flap Operation The alternate mode allows direct manual operation of the flaps and slats through electric motors. The alternate flaps switches: disable normal control arm the alternate mode engage the electric motors the flap lever no longer controls flaps/slats The alternate flaps selector extends and retracts the flaps and slats. Alternate mode flap and slat extension is limited to flaps 20. Trailing edge flap asymmetry protection, autoslats, and flap load relief are not available in the alternate mode. Because autoslats are unavailable, the slats are fully extended at flaps 20 to improve stall handling characteristics. Slat and flap operation time in the alternate mode is greatly increased. Leading Edge Disagreement The LEADING EDGE light illuminates and the EICAS caution message LE SLAT DISAGREE displays when the leading edge slat positions disagree with commanded position. The disagree indicates that the slats are not driving toward their new commanded position. Hydraulic power to both slats and flaps is automatically shut off. Leading Edge Asymmetry The LEADING EDGE light illuminates and the EICAS caution message LE SLAT ASYM displays when the leading edge slats are not symmetrically extended. Hydraulic power to both slats and flaps is automatically shut off. Trailing Edge Disagreement The TRAILING EDGE light illuminates and the EICAS caution message TE FLAP DISAGREE displays when the trailing edge flap positions disagree with commanded position. The disagree indicates that the flaps are not driving toward their new commanded position. Hydraulic power to both slats and flaps is automatically shut off. A TE FLAP DISAGREE may also occur if the flap lever is not in a detent for an extended period of time. In this case, the light and message can be removed by moving the flap lever to the desired detent D632N00-200R

25 Trailing Edge Asymmetry Flight Controls - System Description The TRAILING EDGE light illuminates and the EICAS caution message TE FLAP ASYM displays when the trailing edge flaps are not symmetrically extended. Hydraulic power to both slats and flaps is automatically shut off. Load Relief Inoperative The TRAILING EDGE light illuminates and the EICAS advisory message FLAP LD RELIEF displays when the flap load relief system fails to operate when required. D632N00-200R 9.20.

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27 Flight Controls Chapter 9 EICAS Messages Section Flight Controls-EICAS Messages Flight Controls EICAS Messages Note: Configuration warning messages are covered in Chapter 5, Warning Systems. The following EICAS messages can be displayed. Message Level Light Aural Condition AUTO SPEEDBRAKE Advisory AUTO SPDBRK A fault is detected in the automatic speedbrake system. FLAP LD RELIEF Advisory TRAILING EDGE The flap load relief system fails to operate when required. C FLT CONT HYD L FLT CONT HYD R FLT CONT HYD Advisory OFF The flight control valve is closed. FLT CONT VALS Advisory OFF Two or more flight control valves are closed. LE SLAT ASYM Caution LEADING EDGE Beeper The leading edge slats are not symmetrically extended. LE SLAT DISAGREE Caution LEADING EDGE Beeper The leading edge slat positions disagree with commanded position. MACH/SPD TRIM Advisory MACH SPD TRIM RUDDER RATIO Advisory RUDDER RATIO The Mach speed trim system is inoperative. The rudder ratio system is failed. SPEEDBRAKES EXT Caution SPEED BRAKES Beeper The speedbrake lever is extended when the flaps are in a landing position, or when radio altitude is 800 feet or below. SPOILERS Advisory SPOILERS One or more spoiler pairs are inoperative. May 8, 2005 D632N00-200R 9.30.

28 Flight Controls - EICAS Messages Message Level Light Aural Condition STAB TRIM Advisory STAB TRIM TE FLAP ASYM Caution TRAILING EDGE TE FLAP DISAGREE UNSCHD STAB TRIM L YAW DAMPER R YAW DAMPER Caution Caution TRAILING EDGE UNSCHED STAB TRIM Beeper Beeper Beeper The stabilizer trim rate is one half of the normal control wheel stabilizer trim switch rate. The trailing edge flaps are not symmetrically extended. The trailing edge flap positions disagree with commanded position. Uncommanded stabilizer motion is detected. Advisory INOP The yaw damper is inoperative D632N00-200R November 23, 2005