Ata Chapter 27 Flight Controls

Dornier 328 DORNIER LUFTFAHRT

TRAINING MANUAL LINE /BASE MAINTENANCE

ATA CHAPTER 27 FLIGHT CONTROLS 27-00 GENERAL

8

GENERAL ................................................................................................................................................ 8 Primary Flight Controls......................................................................................................................... 9 Secondary Flight Controls..................................................................................................................... 9 Spoilers.................................................................................................................................................. 9 Stall Warning and Prevention................................................................................................................ 9 Gust Lock .............................................................................................................................................. 9

27-10 AILERON CONTROLS AND TRIM

10

General ................................................................................................................................................ 10 Aileron Controls.................................................................................................................................. 11 Aileron Trim........................................................................................................................................ 11 INTERFACE TO OTHER SYSTEMS ................................................................................................... 11 Roll Spoiler System............................................................................................................................. 11 Indicating/Recording Systems............................................................................................................. 11 Autoflight ............................................................................................................................................ 11

AILERON CONTROLS

12

FUNCTIONAL DESCRIPTION ............................................................................................................ 12 LH and RH Control Wheels ................................................................................................................ 13 Control Cables..................................................................................................................................... 13 Pulleys ................................................................................................................................................. 14 LH and RH Cable Tension Regulators................................................................................................ 14 LH and RH Transition Units ............................................................................................................... 15 Aileron Disconnect Unit...................................................................................................................... 15 Quadrant Assembly ............................................................................................................................. 16 Levers and Bellcranks ......................................................................................................................... 17 Control Rods........................................................................................................................................ 17 Aileron Disconnect Microswitch 7CW ............................................................................................... 18 LH and RH Aileron Position Transmitters 5CX and 4CX.................................................................. 18 OPERATION(refer to Fig. 3, Fig. 5, Fig. 7)........................................................................................... 18 Power Supplies.................................................................................................................................... 18 Aileron Controls.................................................................................................................................. 18 Flight Compartment Controls.............................................................................................................. 18 Flight Compartment to Upper Center Fuselage Control Run.............................................................. 18 Regulation of Cable Tension in Fuselage Control Run....................................................................... 18 Aileron Controls from Transition Units to Wing Roots...................................................................... 19 Aileron Controls from Wing Root to Aileron ..................................................................................... 19 Effectivity: 328-100 Mod.10

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RH Aileron Servo Tab .........................................................................................................................20 LH Aileron Trim/Servo Tab ................................................................................................................20 SYSTEM INDICATIONS .......................................................................................................................21 Aileron Position Indicating ..................................................................................................................21 Aileron Disconnect Unit Monitoring ...................................................................................................21

AILERON TRIM

23

FUNCTIONAL DESCRIPTION .............................................................................................................23 Aileron Trim Actuator 4CC (refer to Fig. 9) .......................................................................................23 Trim Control Panel 10CC ....................................................................................................................24 Main Aileron Trim Switch 2CC...........................................................................................................24 Standby Aileron Trim Switch 12CC....................................................................................................25 Aileron Trim Reset Switch/Light 17CC ..............................................................................................25 Trim Test Switch 50CC .......................................................................................................................25 OPERATION...........................................................................................................................................25 Power Supplies.....................................................................................................................................25 System Power-Up ................................................................................................................................25 Aileron Trim ........................................................................................................................................28 SYSTEM INDICATIONS .......................................................................................................................31 Standby Trim/Main Lockout Circuit Status.........................................................................................31

27-20 RUDDER CONTROLS AND TRIM

32

GENERAL...............................................................................................................................................32 Rudder Controls ...................................................................................................................................32 Rudder Trim.........................................................................................................................................33 INTERFACE TO OTHER SYSTEMS....................................................................................................33 Navigation System ...............................................................................................................................33 Communications ..................................................................................................................................33 Autoflight.............................................................................................................................................33

RUDDER CONTROLS

34

FUNCTIONAL DESCRIPTION .............................................................................................................34 LH and RH Rudder Pedal Assemblies.................................................................................................35 LH and RH Pedal Adjustment Assemblies..........................................................................................35 LH and RH Forward Quadrant Assemblies .........................................................................................36 Pulleys..................................................................................................................................................36 Control Rods ........................................................................................................................................36 Levers and Bellcranks..........................................................................................................................37 Pressure Bulkhead Fairleads ................................................................................................................37 Aft Quadrant Assembly .......................................................................................................................37 Spring Tab Lever Assembly ................................................................................................................38 Rudder Limiter Actuator 7CL..............................................................................................................38 TEST TAB LOCK Switch/Light 2CL .................................................................................................39 RUD LIMIT Switch/Light 5CL ...........................................................................................................40 Current Detector 16CX ........................................................................................................................40 Rudder Position Transmitter 19CX......................................................................................................40 OPERATION...........................................................................................................................................40 Power Supplies.....................................................................................................................................40 Page: 27-2 Issue: 08/95 ETM/ETX

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Effectivity: 328-100 Mod.10

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System Power-Up................................................................................................................................ 41 Rudder Controls .................................................................................................................................. 41 Electrical Control of Rudder Limiter .................................................................................................. 43 SYSTEM INDICATIONS ...................................................................................................................... 44 Rudder Position Indicating.................................................................................................................. 44 Rudder Limiter Monitoring................................................................................................................. 45

RUDDER TRIM

48

FUNCTIONAL DESCRIPTION ............................................................................................................ 48 Rudder Trim Switch 22CC.................................................................................................................. 48 Trim Test Switch 50CC....................................................................................................................... 49 Rudder Trim Actuator 25CC............................................................................................................... 50 OPERATION .......................................................................................................................................... 50 Power Supplies.................................................................................................................................... 50 System Power-Up................................................................................................................................ 50 Rudder Trim (refer to Fig. 27)............................................................................................................. 51 SYSTEM INDICATIONS ...................................................................................................................... 53 T rim Position Indicating..................................................................................................................... 54 Rudder Trim Selection Status.............................................................................................................. 54

27-30 ELEVATOR CONTROLS AND TRIM

55

GENERAL .............................................................................................................................................. 55 Elevator Controls................................................................................................................................. 56 Elevator Trim ...................................................................................................................................... 56 INTERFACE TO OTHER SYSTEMS ................................................................................................... 56 Indicating/Recording Systems............................................................................................................. 56 Navigation System .............................................................................................................................. 56 Auto Flight System.............................................................................................................................. 56

ELEVATOR CONTROLS

57

FUNCTIONAL DESCRIPTION ............................................................................................................ 57 LH and RH Control Column ............................................................................................................... 58 LH and RH Cable Tension Regulator ................................................................................................. 59 Control Cables..................................................................................................................................... 59 Pulleys ................................................................................................................................................. 59 Control Rods........................................................................................................................................ 59 Levers and Bell cranks ........................................................................................................................ 59 Pressure Bulkhead Fairleads ............................................................................................................... 59 Quadrant Assembly ............................................................................................................................. 60 Elevator Disconnect Unit .................................................................................................................... 61 Elevator Disconnect Micro switch 8CW............................................................................................. 61 LH and RH Elevator Position Transmitters 25CX and 26CX............................................................. 62 OPERATION .......................................................................................................................................... 62 Power Supplies.................................................................................................................................... 62 Elevator Controls................................................................................................................................. 62 Flight Compartment to Vertical Stabilizer Control Run ..................................................................... 62 LH and RH Elevator Tab..................................................................................................................... 63 SYSTEM INDICATIONS ...................................................................................................................... 63 Effectivity: 328-100 Mod.10

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Elevator Position Indicating.................................................................................................................63 Elevator Disconnect Unit Monitoring..................................................................................................63

ELEVATOR TRIM

65

FUNCTIONAL DESCRIPTION .............................................................................................................65 LH (RH) Elevator Trim Actuator 53CC (52CC) .................................................................................66 Main Elevator Trim Switches 33CC....................................................................................................67 Standby Elevator Trim Switch 63CC...................................................................................................68 Elevator Trim Reset Switch/Light 69CC.............................................................................................68 Trim Test Switch 50CC .......................................................................................................................68 OPERATION...........................................................................................................................................68 Power Supplies.....................................................................................................................................68 System Power-Up ................................................................................................................................68 Trim Control ........................................................................................................................................69 Main Trim Control...............................................................................................................................69 Standby Trim Control and Main Trim Lockout...................................................................................69 Actuator Speed Control........................................................................................................................72 Main Trim Runaway Override.............................................................................................................73 Runaway Override Test .......................................................................................................................73 Main Trim Circuit Fault Protection .....................................................................................................74 Standby Trim Circuit Fault Protection.................................................................................................74 Auto-Trim ............................................................................................................................................75 SYSTEM INDICATIONS .......................................................................................................................75 Trim Position Indicating ......................................................................................................................76 Trim Synchronization ..........................................................................................................................76 Trim Speed Mode Indicating ...............................................................................................................77 Standby Trim/Main Lockout Circuit Status.........................................................................................79 Trim Actuator Status............................................................................................................................79

27-33 STALL WARNING AND PREVENTION

80

GENERAL...............................................................................................................................................80 Angle of Attack Information................................................................................................................81 Stall Warning Computing ....................................................................................................................81 Stick Shaker .........................................................................................................................................81 Stick Pusher..........................................................................................................................................81 System Inhibition on Ground and below 100 ft Radar altitude ...........................................................81 Stick Pusher Disarm.............................................................................................................................82 Autopilot Disengagement ....................................................................................................................82 System Test..........................................................................................................................................82 System Monitoring and Indicating.......................................................................................................82 INTERFACE TO OTHER SYSTEMS....................................................................................................83 Auto Flight System (Chapter 22).........................................................................................................83 Communications (Chapter 23).............................................................................................................83 FUNCTIONAL DESCRIPTION .............................................................................................................83 LH (RH) AOA Sensor 2WH (12WH)..................................................................................................84 LH (RH) Stick Shaker 6WH ................................................................................................................85 Stick Pusher 25WH..............................................................................................................................85 LH (RH) Stall Warning Test Switch 7WH (17WH)............................................................................86 Pusher Disarm Switch/Light 22WH ....................................................................................................87 Pusher Reset Switch 24WH .................................................................................................................87 Page: 27-4 Issue: 08/95 ETM/ETX

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Effectivity: 328-100 Mod.10

Dornier 328 DORNIER LUFTFAHRT

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OPERATION .......................................................................................................................................... 87 Power Supplies.................................................................................................................................... 87 System Power-Up................................................................................................................................ 87 Power-Up Test..................................................................................................................................... 89 System Test ......................................................................................................................................... 89 Stall Warning Computing.................................................................................................................... 90 Stick Shaker Operation........................................................................................................................ 91 Stick Pusher Operation........................................................................................................................ 91 SYSTEM INDICATIONS ...................................................................................................................... 93 General ................................................................................................................................................ 93 AOA Sensor Status.............................................................................................................................. 93 AOA Comparison................................................................................................................................ 93 Shaker Status ....................................................................................................................................... 94 Pusher Status ....................................................................................................................................... 94

27-50 FLAPS

97

GENERAL .............................................................................................................................................. 97 INTERFACE TO OTHER SYSTEMS ................................................................................................... 98 Hydraulic Power (Chapter 29) ............................................................................................................ 98 Landing Gear (Chapter 32).................................................................................................................. 98 Navigation (Chapter 34)...................................................................................................................... 98 Indicating/Recording Systems (Chapter 31) ....................................................................................... 98 FUNCTIONAL DESCRIPTION ............................................................................................................ 98 Flap Control Unit 2CG........................................................................................................................ 99 Flap Control Switch 3CG.................................................................................................................. 101 Flap Control Valve Manifold 4CG.................................................................................................... 102 LH and RH Flap Actuators................................................................................................................ 103 LH (RH) Flap Position Feedback Sensor 5CG (6CG) ...................................................................... 103 Torque Shaft...................................................................................................................................... 104 Relay 8CG ......................................................................................................................................... 104 OPERATION ........................................................................................................................................ 104 Electrical Power Supplies.................................................................................................................. 104 Hydraulic Power Supplies................................................................................................................. 104 System Power-Up.............................................................................................................................. 106 Power-Up Test................................................................................................................................... 106 Flap Operation................................................................................................................................... 107 SYSTEM INDICATIONS .................................................................................................................... 108 General .............................................................................................................................................. 108 System Operating Status Monitoring ................................................................................................ 109 System Reset ..................................................................................................................................... 109 Flap Position Indicating..................................................................................................................... 109

27-60 SPOILERS

111

GENERAL ............................................................................................................................................ 111 Ground Spoilers (optional)................................................................................................................ 112 Roll Spoilers...................................................................................................................................... 112 Indications ......................................................................................................................................... 112 INTERFACE TO OTHER SYSTEMS ................................................................................................. 112 Hydraulic Power (Chapter 29) .......................................................................................................... 112

Effectivity: 328-100 Mod.10

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GROUND SPOILERS (OPTIONAL)

113

FUNCTIONAL DESCRIPTION ...........................................................................................................113 Valve Manifold 10CS ........................................................................................................................113 Ground Spoiler Actuators ..................................................................................................................115 Restrictor Relief Valves.....................................................................................................................116 Ground Spoiler Arm/Disarm Switch/Light 2CS................................................................................117 Microswitches 3CS/5CS/7CS/8CS ....................................................................................................117 Proximity Sensors 3CW/5CW (refer to Fig. 64)................................................................................118 OPERATION.........................................................................................................................................118 Electrical Power Supplies ..................................................................................................................118 Hydraulic Power Supplies..................................................................................................................118 System Power-Up ..............................................................................................................................118 System Pre-Takeoff Test....................................................................................................................118 Spoiler Inflight Inhibition ..................................................................................................................119 Landing Gear Circuit .........................................................................................................................119 Power Lever Circuit...........................................................................................................................119 Spoilers Disarm/Arm .........................................................................................................................122 Auto-Deployment on Landing ...........................................................................................................122 Auto-Deploy on Aborted Takeoff......................................................................................................122 Auto-Stow ..........................................................................................................................................122 Spoiler Lockout During Ground Manoeuvring..................................................................................122 SYSTEM INDICATIONS .....................................................................................................................123 Ground Spoiler Position Indicating....................................................................................................123 Spoiler Proximity Sensor Monitoring................................................................................................123 Ground Spoiler not Stowed................................................................................................................123 Ground Spoiler Control Circuit Armed .............................................................................................123

ROLL SPOILERS

125

FUNCTIONAL DESCRIPTION ...........................................................................................................125 LH and RH Roll Spoiler Actuators....................................................................................................125 LH (RH) Roll Spoiler Position Sensor 21CX (22CX).......................................................................127 Double Shuttle Valve.........................................................................................................................127 OPERATION.........................................................................................................................................128 Hydraulic Power Supplies..................................................................................................................129 Roll Spoiler Control...........................................................................................................................129 SYSTEM INDICATIONS .....................................................................................................................130 Spoiler Position Indicating.................................................................................................................130

27-70 GUST LOCK AND DAMPER

132

GENERAL.............................................................................................................................................132 Aileron and Elevator Control Gust Locks..........................................................................................132 Rudder Damper..................................................................................................................................133 FUNCTIONAL DESCRIPTION ...........................................................................................................133 Gust Lock Lever, Flexible Cables and Distribution Box...................................................................133 Aileron Controls Gust Lock...............................................................................................................134 Elevator Controls Gust Lock..............................................................................................................134 Rudder Damper..................................................................................................................................135

Page: 27-6 Issue: 08/95 ETM/ETX

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Effectivity: 328-100 Mod.10

Dornier 328 DORNIER LUFTFAHRT

TRAINING MANUAL LINE /BASE MAINTENANCE

INDEX

137

LIST OF ILLUSTRATIONS

138

Effectivity: 328-100 Mod.10

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27-00 GENERAL GENERAL Rudder Trim Tab Spring Tab

Aileron Servo Tab Roll Spoiler Flap Groundspoiler (Option) Elevator TrimTabs TrimTabs Elevator Groundspoiler (Option) Flap Roll Spoiler Trim/Servo Tab Aileron

Fig. 1 Flight Controls - General Arrangement

Page: 27-8 Issue: 08/95 ETM/ETX

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Effectivity: 328-100 Mod.10

Dornier 328 DORNIER LUFTFAHRT

TRAINING MANUAL LINE /BASE MAINTENANCE

This chapter provides information on those units and components which furnish a means of manually controlling the flight attitude of the aircraft. The chapter is divided into sections containing detailed information on the following flight control subsystems: - Aileron Controls and Trim - Rudder Controls and Trim - Elevator Controls and Trim - Stall Warning and Prevention - Flaps - Spoilers - Ground Spoilers (Option) - Roll Spoilers - Gust Lock and Damper Primary Flight Controls The aircraft primary controls consist of conventional ailerons, elevators and rudder. The primary control surfaces are moved manually by linkage systems consisting of cables, pulleys, levers and rods. Dual controls are installed for the three primary controls. The elevator and aileron control runs are each equipped with a disconnect unit. This allows the captain's and first officer's controls to be disconnected from each other should one control run become jammed. The rudder pedals drive a Flettner-type spring tab on the trailing edge of the rudder. At airspeeds up to 160 knots the rudder is deflected by aerodynamic servo reaction from the tab. The rudder itself is not connected to the rudder pedals directly except at airspeeds above 160 knots. Secondary Flight Controls The secondary flight controls consist of aileron, elevator and rudder trim systems and trailing edge flaps. The aircraft is trimmed in the three axes by electro-mechanical actuators driving trim tabs. Roll trim is achieved by a single actuator driving a tab on the left aileron. Pitch trim is achieved by a tab on each elevator, each tab having its own actuator. Yaw trim is achieved by a single actuator driving a tab on the trailing edge of the rudder. The flaps consist of one flap section on the trailing edge of each wing half. The two sections are mechanically linked and are driven hydraulically. Spoilers For improved performance roll spoilers and ground spoilers are installed. The roll spoilers assist the ailerons. Both sets of spoilers are located on the top surface of the wing and are driven hydraulically. Stall Warning and Prevention A stall warning and prevention system (stick shaker and stick pusher) is installed. Gust Lock The ailerons and elevators can be locked for parking by a lever in the flight compartment. The rudder control system is equipped with a hydraulic gust damper which prevents damage to the structure when the aircraft is parked in gusty conditions

Effectivity: 328-100 Mod.10

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27-10 AILERON CONTROLS AND TRIM General

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Fig. 2 Aileron - General Arrangement This section provides information on that portion of the flight control system which controls the ailerons and the aileron trim tab. Also included are the aileron and trim tab position indicating systems and the aileron disconnect indicating system. The section is divided into subsections containing detailed information on the following aileron and tab subsystems: - Aileron Controls - Aileron Trim

Page: 27-10 Issue: 08/95 ETM/ETX

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Effectivity: 328-100 Mod.10

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Aileron Controls The aircraft is controlled about the roll axis by a conventional aileron control system. Two ailerons are installed, one on the outboard trailing edge of each wing. The ailerons are manually operated by dual control wheels. The linkage from the control wheels to the ailerons is by an arrangement of pulleys, cables, quadrants, push-pull rods, levers and bellcranks. The maximum aileron movement is 30° up and 25° down. The captain's and first officer's aileron control runs are joined by a disconnect unit. This unit allows the two control runs to be separated by the application of higher than normal input forces should one control run become jammed. Aileron Trim The aircraft can be trimmed about the roll axis by a Trim/Servo-tab located on the inboard trailing edge of the left aileron. The tab is driven by an electrically powered linear actuator installed in the trailing edge of the wing. Due to the actuator attachment geometry the tab also functions as a servo tab to provide aerodynamic assistance to flight crew roll commands. The actuator is powered by two separate DC motors and controlled by either a main or a standby aileron trim switch. Override circuits are provided to protect against a trim runaway. Test facilities are provided for the override circuits.

INTERFACE TO OTHER SYSTEMS Roll Spoiler System The roll spoiler control actuators are connected by push-pull rods to the aileron control system. Indicating/Recording Systems The following functions of the aileron and tab subsystem are indicated on the electronic indicating, caution and advisory system EICAS: - the position of each aileron - the status of the aileron disconnect unit - the position of the aileron trim actuator. Autoflight Signals from the automatic flight control system (AFCS) are used to operate the ailerons when the aircraft is flying under automatic control. Refer to (Chapter 22 - AUTO FLIGHT) for further details.

Effectivity: 328-100 Mod.10

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AILERON CONTROLS FUNCTIONAL DESCRIPTION The aileron control subsystem consists of the following components: FIN Component Panel LH and RH control wheels LH and RH cable tension regulators

120

LH and RH fairlead brackets

120

control cables

120 130 210 220 220 530 630 530 630 220

pulleys control rods levers and bellcranks LH and RH transition units

7CW 4CX 5CX

Zone 210

aileron disconnect unit quadrant assembly aileron disconnect microswitch RH aileron position transmitter LH aileron position transmitter

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250

632 532

Access Door 211-FZF 212-EZF 211-LFZ 212-KFZ 221-MFZ 222-EFZ various + furnishing panels various various 251-bt 252-bt furnishing panels 251-bt 252-bt 632-JB 532-JB

Effectivity: 328-100 Mod.10

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LH and RH Control Wheels

Transition Unit

A

Double Pulley

Turnbuckle Control Cable

A

Pulley

Cable Tension Regulator

Fig. 3 Aileron - Control Wheels to Transition Units The control wheels are of the horn type and are mounted with splined shafts on the top of the control columns. Wheel movement is transmitted to the aileron control cable tension regulators beneath the flight compartment floor by cables and pulleys. Control Cables The aileron control cables transmit the movement of the control wheels to the tension regulators and from there to the transition units located on the passenger compartment roof between frames 25 and 26. The cables are 7 x 19 flexible steel wire ropes made from corrosion resistant steel and have a nominal diameter of 3.2 mm (0.13 in.). The LH and RH aileron control runs each consist of eight separate cable sections. Each control wheel is connected to its associated tension regulator by four sections. Each tension regulator is connected to its associated transition unit by a further four sections. Cable sections are joined by turnbuckles and terminated by swaged end fittings. Effectivity: 328-100 Mod.10

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Pulleys The control cables are guided by pulleys equipped with cable guards. The pulleys are made of a phenolic material and run in sealed ball bearings. A double pulley connected to the control wheel at the top of each control column and two single pulleys at the base of the control column guide the cable run from the control wheel to the associated tension regulator. The cable run from each tension regulator to the associated transition unit is guided by a total of fifteen pulleys. LH and RH Cable Tension Regulators

Notch for Aileron Gust Lock (LH Side Only)

Upper Arm Compression Springs Sliding Lever Assembly

Input Pulley Compression Springs

Lower Arm

Fig. 4 Aileron - Cable Tension Regulator The tension of the control cables installed in the flight control system must be maintained within specified tolerances. Temperature effects cause the cables and the aircraft structure to expand and contract. The expansion coefficient of the aluminium structure is higher than that of the steel cables. This means that the cables tighten at high ambient temperatures and slacken at low ambient temperatures. Control cable tension regulators compensate for these effects. A control cable tension regulator is installed below the flight compartment floor in the captain's and first officer's aileron control runs. The two tension regulators are identical in operation. Each regulator automatically regulates the tension of the control cables between the regulator output quadrant and the associated cable termination quadrants in the upper center fuselage. The tension regulator consists of a shaft to which an input pulley and a spring compensator mechanism are firmly attached. An output quadrant with separate upper and lower sections is installed on but not attached to the shaft. The two sections are connected to each other by the compensator mechanism but are otherwise free to rotate on the shaft. The compensator mechanism consists of two compression springs which act on a sliding lever assembly. The sliding lever is connected to the upper and lower sections of the output quadrant by two arms. If the control cables become tight the cables pull the two sections of the output quadrant towards the shaft against the force of the springs. This effectively shortens the length of the cable run. If the cables become slack the springs push the quadrant sections in the other direction to take up the slack. The aileron gust lock engages with a notch in the LH (captain's) tension regulator.

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Effectivity: 328-100 Mod.10

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LH and RH Transition Units The transition units are installed in the roof section of the passenger compartment between frames 25 and 26. The units have two functions: - they act as a connection point between the LH (RH) cable run in the fuselage and the rods in the LH (RH) wing - they act as pressure seals at the point where the control run exits the pressure compartment. Each unit consists of a cable quadrant located in the pressure compartment and an output lever located in the fairing between the fuselage and the wing. The quadrant and the lever are mounted on a common shaft . The shaft bearing is installed in the passenger compartment roof and acts as the pressure seal. The quadrant accepts the control inputs from the fuselage control cables and the lever transmits the movement into the control rod run in the wing. Aileron Disconnect Unit

A

Rod to RH Aileron Control LH/RH Interconnect Rod

A

Autopilot Roll Servo Actuator Cable Quadrant Roll Disconnect Unit

Lever Assembly Quadrant Output Lever Quadrant Assembly

Rod to LH Aileron

Lever Assy Drive Rod Fig. 5 Aileron - Transition Units to the Wingroot Effectivity: 328-100 Mod.10

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Output to RH Aileron Front Half

Transverse Rod to LH Control Circuit

Rear Half

Command Input from RH Control Circuit

Fig. 6 Aileron - Disconnect Unit The captain's and first officer's aileron control cable runs are routed completely separately along the left and right sides of the fuselage respectively. They are joined by an interconnect rod in the wing center section and an aileron disconnect unit located in the trailing edge section of the RH wing root. Under normal circumstances the movement of one control wheel moves both ailerons and the other control wheel. Should one aileron control become jammed the two control circuits can be separated by the application of a higher than normal force to a control wheel. The unit has two halves which are held engaged by a spring and cam arrangement. The front half has levers for two push-pull rods. The lower lever is for the command input from the RH aileron control circuit. The upper lever is for the output rod to the RH aileron. The rear half has a single lever for the interconnect rod that joins the LH and RH control circuits. Under normal operating conditions the two halves of the unit are firmly engaged and move together as a single unit. Should one of the aileron control circuits jam, the two halves can be disconnected from each other by the application of a higher than normal force at a control wheel. The disconnect force is 39 daN (87.7 lb). The applied force causes the cam to override the spring force and move out of its detent. The two halves of the unit are now disengaged, effectively isolating the jammed control circuit. In this situation the captain's control circuit is connected to the left aileron only. The first officer's control circuit is connected to the right aileron only. The aircraft can be controlled about the roll axis using the free control wheel. Once activated, the disconnect unit can only be reset on the ground. The unit has an integral microswitch 7CW which is operated if the disconnect unit is activated. The switch sends a signal to EICAS Quadrant Assembly The quadrant assembly is installed in the trailing edge section of the LH wing root at rib 2. The assembly consists of three levers and a cable quadrant all mounted on a common shaft. The lower lever accepts the control inputs from the LH transition unit. The forward upper lever is the drive lever for the LH aileron control run. The aft upper lever forms the connection point for the LH/RH aileron control interconnect rod. The cable quadrant is the connection point for the autopilot roll servo to the aileron control run. The control cable from the autopilot roll servo is connected to cable arms that extend from the upper and lower sections of the cable quadrant. Because the control cable has no turnbuckles, the arms can be adjusted with screws for setting the cable tension.

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Effectivity: 328-100 Mod.10

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Levers and Bellcranks

A 1 2

7

A LH SIDE SHOWN, RH SIDE SIMILAR.

R0

R3 R4 R5 R6 R7 R8 R9 R 10

6

1. Interconnection Rod 2. Quadrant Assembly 3. Position Transducer 4. Aileron Drive Rod 5. Bellcrank 6. Rollspoiler Drive Rod 7. Disconnect Unit

R 11 R 12

3 R 12 R 13

4 R 14 R 15 R 16 R 17

5

R 18 R 19

R 20

Fig. 7 Aileron - Wing Root to Aileron The control rods in the wing are supported by idler levers and bellcranks running in sealed ball bearings. The connection points for the rod clevis ends are formed by self-aligning sealed ball bearings. Control Rods The aileron control run from the transition units in the upper center fuselage to their associated aileron is formed by a series of aluminium push-pull control rods. Another rod forms the interconnection between the LH (captain's) and RH (first officer's) aileron controls. The Servo-tab on each aileron is also controlled by rods. Rod ends are either of the clevis or eye type. Eye type rod ends are equipped with selfaligning sealed ball bearings. Effectivity: 328-100 Mod.10

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DORNIER LUFTFAHRT

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Aileron Disconnect Microswitch 7CW A microswitch located in the aileron disconnect unit monitors the status of the unit and sends a discrete signal to the EICAS when the disconnect unit is activated. The switch contacts are connected to ground under normal operating conditions and open under aileron disconnect conditions. LH and RH Aileron Position Transmitters 5CX and 4CX An aileron position transmitter is installed for each aileron. The transmitters are installed on their associated wing rear spar between ribs 17 and 18. Each transmitter is driven by a short rod connected to the outboard idler lever in the aileron control run. The transmitters are identical 0 to 10 k Ω three-wire potentiometers whose resistance changes as a function of the aileron position. They send a variable resistance signal to the EICAS for aileron position indicating.

OPERATION(refer to Fig. 3, Fig. 5, Fig. 7) Power Supplies Electrical power is not required for the aileron control system. Power for the indicating part of the system is provided by the EICAS Aileron Controls Note: The LH (captain's) and RH (first officer's) aileron controls from the flight compartment to the upper center fuselage are similar. The operation of the LH side is described. Differences for the RH side are covered in the text or given in brackets. Flight Compartment Controls The Control wheel movement is transmitted through the pulleys by a cable to the cable tension regulator located at frame 9. The tension of this short cable run can be adjusted by turnbuckles. A notch is provided in the aft portion of the LH cable tension regulator between the upper and lower quadrants. The aileron gust lock engages with this notch to lock the aileron controls for gust protection when the aircraft is parked. Flight Compartment to Upper Center Fuselage Control Run From the cable tension regulator, the control movement is continued aft below the flight and passenger compartment floor by control cables and pulleys. The cables pass through guides in some frames under the floor. Cable fairleads equipped with small pulleys are used to guide the cables through the machined part of frame 24. The cable run is virtually straight as far as a point between frames 25 and 26. At this point the cables are routed outboard and then upwards. The cable run now passes between the fuselage skin and the passenger compartment furnishing panels and terminates at a transition unit on the passenger compartment roof just left (right) of the aircraft centerline. Regulation of Cable Tension in Fuselage Control Run The continuous cable run from the cable tension regulators to the cable quadrants on the passenger compartment roof is approximately 9.5 m (31 ft) long. Approximately 6.5 m (21 ft) of this is a virtually straight horizontal run. The expansion coefficient of the aluminium structure is higher than that of the steel cables. This means that the cables tighten at high ambient temperatures and slacken at low ambient temperatures. The control cable tension regulators compensate for these effects.

Page: 27-18 Issue: 08/95 ETM/ETX

- FOR TRAINING PURPOSES ONLY TM-Flight Controls

Effectivity: 328-100 Mod.10

Dornier 328 DORNIER LUFTFAHRT

TRAINING MANUAL LINE /BASE MAINTENANCE

The shaft of the tension regulator (and thus the regulator mechanism) is rotated by flight crew commands acting on the input pulley. The movement is transmitted to the upper and lower sections of the output quadrant by the arms of the regulator mechanism. The control cable is a two-part cable, each part being attached to its associated quadrant section by a nipple. The two sections of the output quadrant are thus allowed to move in relation to each other. Under high ambient temperature conditions the control cables tighten. The cable tension pulls on the two sections of the output quadrant and moves them in opposite directions on the shaft. The movement acts through the arms and pulls the sliding lever assembly towards the shaft against the force of two compression springs. This effectively shortens the length of the cable run. The sliding motion continues until the spring compression is equal to the cable tension. If the ambient temperature is low the cables slacken. The springs push the two sections of the output quadrant in the other direction to take up the slack. Aileron Controls from Transition Units to Wing Roots The shaft of the transition unit on the LH side of the passenger compartment roof exits the fuselage through a pressure tight fitting. A lever is fixed to the shaft out-side the fuselage. A push-pull rod connected to the lever transmits the aileron commands to the quadrant assembly at LH wing station Y 600 (rib 2). A cable quadrant shares a common shaft with three levers on the quadrant assembly. The autopilot roll servo is connected by a control cable to the aileron control run at this quadrant. Two push-pull rods are connected to the upper levers of the quadrant assembly. The aft rod connects to the aileron disconnect unit (at RH wing station Y 600 (rib 2). This rod forms the interconnection between the LH (captain's) and RH (first officer's) aileron controls. The forward rod is the first of six push-pull rods which form the control run from the wing root to the aileron drive bellcrank at LH wing station Y 7345.4 (between ribs 19 and 20). The RH side is similar to the LH. The differences are: - the disconnect unit replaces the quadrant assembly - the control run starts with rod from the disconnect unit - the interface to the autopilot is connected through the disconnect unit. Aileron Controls from Wing Root to Aileron Six push-pull rods - supported at intervals by idler levers and a bellcrank - form the control run from the quadrant assembly in the LH wing root to the LH aileron drive bellcrank. The six rods are routed along the aft face of the rear spar. A further push-pull rod is connected to the idler lever located on the rear spar between ribs 15 and 16. This is the drive rod for the LH roll spoiler actuator. A short push-pull rod connects the aileron drive bellcrank to the aileron control horn. The horn is attached to the underside of the aileron. The aileron position transmitter is driven by the outboard idler lever and indicates the aileron position on the flight control system page on EICAS. The control run in the RH wing starts with rod at the disconnect unit. Otherwise it is similar to the LH wing control run.

Effectivity: 328-100 Mod.10

- FOR TRAINING PURPOSES ONLY TM-Flight Controls

Page: 27-19 Issue: 08/95 ETM/ETX

Dornier 328 TRAINING MANUAL

DORNIER LUFTFAHRT

LINE /BASE MAINTENANCE

RH Aileron Servo Tab

B B Servo Tab Push-Pull Rods Connection to Servo Tab A

Servo Tab Push-Pull Rods

Reduction Lever in Aileron Leading Edge

Connection to Wing Trailing Edge

Fig. 8 Aileron - Servo Tab A Flettner-type servo tab is installed on the inboard trailing edge of the RH aileron. The tab is connected by four short push-pull rods and a reduction lever to the structure of the wing trailing edge at approximately station Y 6880 (just outboard of rib 18). The reduction lever is installed in the leading edge of the aileron. The tab moves in the opposite direction to the aileron to provide aerodynamic assistance for reduced pilot effort. LH Aileron Trim/Servo Tab Trim Tab Drive Rods Reduction Lever in Aileron Leading Edge

Connection to Trim Tab

A

Aileron Trim Actuator

Connection to Wing Trailing Edge

Fig. 9 Aileron - Trim/Servo Tab Page: 27-20 Issue: 08/95 ETM/ETX

- FOR TRAINING PURPOSES ONLY TM-Flight Controls

Effectivity: 328-100 Mod.10

Dornier 328 DORNIER LUFTFAHRT

TRAINING MANUAL LINE /BASE MAINTENANCE

An aileron trim tab is installed on the inboard trailing edge of the LH aileron. The dual-shaft trim actuator is installed in the trailing edge of the wing. The actuator drives the tab through a reduction lever installed in the leading edge of the aileron. The reduction lever is connected to the trim tab by twin push-pull rods. Due to this attachment geometry the trim tab also functions as a Flettner-type servo tab in addition to its function as a trim tab.

SYSTEM INDICATIONS Certain components of the aileron control system send signals to EICAS. The signals are sent to data acquisition units (DAU’s) and are used: - to display the position of the ailerons by synoptics - to indicate the status of the aileron disconnect unit by a synoptic - to display a caution message if the aileron disconnect unit is activated. The position of the ailerons and the status of the disconnect unit are displayed on the FLIGHT CONTROL page. The caution message is displayed on the CAS field of the primary EICAS page and on the FLIGHT CONTROL page. Aileron Position Indicating An aileron position transmitter is installed for each aileron. Each transmitter is a three-wire potentiometer whose resistance changes as a function of the aileron position. The LH transmitter sends resistance signal to DAU 1 in the EICAS system for processing. The RH transmitter sends an identical signal DAU 2. The resistance values correspond to the following aileron deflections: - 0.5 kΩ corresponds to an aileron up deflection of -30° - 5 kΩ corresponds to aileron neutral - 9.5 kΩ corresponds to an aileron down deflection of +25°. The position of each aileron is indicated by a blue synoptic on the FLIGHT CONTROL page of the EICAS. If the transmitter signal is invalid, the blue synoptic is replaced by an amber X. Under normal operating conditions the LH and RH aileron synoptics are joined by a white bar. The bar changes to amber if the aileron disconnect unit is activated below. Aileron Disconnect Unit Monitoring A micro switch 7CW in the aileron disconnect unit monitors the status of the unit. It sends a discrete ground or open signal to DAU 1 for processing. The signal line is connected to ground under normal operating conditions and open circuit if the disconnect unit is activated. If the captain's and first officer's aileron control runs are disconnected: - an amber AIL DISCONNECT caution message is displayed on the CAS field of the primary EICAS page and on the FLIGHT CONTROL page - on the FLIGHT CONTROL page the white bar which connects the LH and RH aileron synoptics changes to amber. CAS FIELD Indication MFD PAGE Indication Fault or Condition AMBER

AMBER

AIL DISCONNECT

AIL DISCONNECT

-

white pointer against white aileron scale

Effectivity: 328-100 Mod.10

Aileron disconnect unit activated

AMBER Bar blue Indicates position of Aileron LH (RH) aileron synoptic Invalid synoptic replaced by an amber X RH aileron similar white pointer against white Indicates aileron trim settings aileron scale

- FOR TRAINING PURPOSES ONLY TM-Flight Controls

Page: 27-21 Issue: 08/95 ETM/ETX

Dornier 328 TRAINING MANUAL

DORNIER LUFTFAHRT

LINE /BASE MAINTENANCE Honeywell

LH

RH ELEVATOR ELEV DISCONNECT RUDDER LIMITED AIL DISCONNECT

RUDDER AILERON

TRIM

E L E V

AIL RUD ROLL

NU TRIM SPEED FAST

ND ROLL

FLAP ASYM FLAPS 12 0 °

0 °

20 32

SYSTEM 1 / 3 FLIGHT CONTROL

HYDR

ENGINE

FUEL

NEXT

Fig. 10 Aileron - EICAS Indications - MFD System Page

Page: 27-22 Issue: 08/95 ETM/ETX

- FOR TRAINING PURPOSES ONLY TM-Flight Controls

Effectivity: 328-100 Mod.10

Dornier 328 DORNIER LUFTFAHRT

TRAINING MANUAL LINE /BASE MAINTENANCE

AILERON TRIM FUNCTIONAL DESCRIPTION The aileron trim subsystem consists of the following components: FIN Component Panel 1CC/11CC circuit breaker 12VE 1CX circuit breaker 18VE 2CC main aileron trim switch 10CC 4CC aileron trim actuator 5CC trim runaway interlock relay LH 23VE 6CC trim runaway override relay LH 23VE 7CC trim runaway override relay RH 23VE 8CC trim runaway interlock relay RH 23VE 9CC aileron trim test relay 23VE 10CC trim control panel 12CC standby aileron trim switch 10CC 14CC diodes 10CC 15CC 16CC standby aileron trim control relay 23VE 17CC aileron trim reset switch/light 10CC 50CC trim test switch 30VE LH

Zone 210 210 210 532 210 210 210 210 210 210 210 210

Access Door

532-JB

210 210 210

Aileron Trim Actuator 4CC (refer to Fig. 9) The aileron trim actuator is installed in the left wing trailing edge at approximately station Y 6880 (just outboard of rib 18). The actuator has two separate DC motors (main and standby). The main motor is controlled by the main trim switch 2CC and the standby motor by the standby trim switch 12CC. Only one motor can operate at a time. An external electrical lockout circuit prevents the main motor from operating when the standby motor is active. Internal limit switches for both motors stop actuator movement before the mechanical limits are reached. The rotary output of each motor is converted in a reduction gearbox to a dual shaft linear output. Total shaft travel between the electrical limits is 26.8 mm (1.05 in.). The twin shafts of the actuator are connected to a reduction lever arrangement in the leading edge of the aileron. Two push-pull rods connected to the output side of the reduction lever transmit the actuator movement to the tab. An integral synchro-type position transmitter in the actuator sends an aileron trim position indicating signal to the EICAS.

Effectivity: 328-100 Mod.10

- FOR TRAINING PURPOSES ONLY TM-Flight Controls

Page: 27-23 Issue: 08/95 ETM/ETX

Dornier 328 TRAINING MANUAL

DORNIER LUFTFAHRT

LINE /BASE MAINTENANCE

Trim Control Panel 10CC

TRIM TEST

NH OVSP TEST ENG LH FI TEST

LH

ENG RH 1

PLA FI

MADC

2

OFF PLA FI SSEC DISABLE

LH

AIL

RH

RESET

LH

AIL

RH

STBY

LH

RH

AIL

S T B Y

PRESS TO RESET

T R I M

RUD STBY OFF

ELEV

UP

ELEV

DN UP

Fig. 11 Aileron Trim Controls - Trim Control The trim control panel is installed in the aft LH section of the center pedestal. The panel interfaces with the aileron, rudder and elevator trim circuits and has the following switches: - main aileron trim switch 2CC - standby aileron trim switch 12CC - aileron trim reset switch/light 17CC - rudder trim switch - rudder trim on/off switch/light - elevator trim reset switch/light - standby elevator trim switch Main Aileron Trim Switch 2CC The main aileron trim switch is installed in the forward LH section of the trim control panel. The switch is labelled LH AIL RH and contains two three-position center biased rocker switches. Both rocker switches must be activated together to operate the aileron trim actuator. The two switches have a total of eight sets of contacts (four per switch). Each contact of one rocker switch is connected in either series or parallel with a contact in the other switch, making a total of four contact pairs.

Page: 27-24 Issue: 08/95 ETM/ETX

- FOR TRAINING PURPOSES ONLY TM-Flight Controls

Effectivity: 328-100 Mod.10

Dornier 328 DORNIER LUFTFAHRT

TRAINING MANUAL LINE /BASE MAINTENANCE

Standby Aileron Trim Switch 12CC The standby aileron trim switch is installed in the forward RH section of the trim control panel. The switch is labelled LH AIL RH and is identical to the main trim switch 2CC. It controls the standby motor of the aileron trim actuator. A lockout circuit is activated when the standby trim switch is operated. This circuit disables the main motor of the aileron trim actuator. The main motor remains disabled until the reset switch/light 17CC is pressed. Aileron Trim Reset Switch/Light 17CC A lockout circuit disables the main trim motor when the standby trim motor is operated. The lockout circuit remains active even after the trim operation has been completed. The main trim motor can be reenabled by pressing an aileron trim reset switch/light. The switch is labelled PRESS TO RESET and is installed in the trim control panel between the two aileron trim switches . A white STBY AIL annunciator in the front face of the switch comes on to indicate when the standby trim circuit - and thus the lockout circuit - is active. The switch is guarded by a transparent spring-loaded cover. Trim Test Switch 50CC The trim test push switch is installed in the LH engine/propeller test panel 30VE located in the forward LH section of the center pedestal. The switch is labelled TRIM TEST and is used to test the trim runaway override circuits of the following systems: - aileron trim actuator main motor - rudder trim system - elevator trim system To test the aileron trim runaway override circuit, press and hold the TRIM TEST switch and then press the main aileron trim switch to LH and then RH. If the runaway override circuits of the actuator main motor are serviceable, the actuator will operate in the reverse direction to that commanded. When the test switch is released the motor will start again in the commanded direction.

OPERATION Power Supplies The aileron trim subsystem is supplied with 28 VDC and 26 VAC electrical power as follows: Component

BUS

circuit breaker

trim actuator main motor control and power circuit trim actuator standby control and power circuit trim actuator position indicating circuit

ESSENTIAL BUS 3PP

AIL TRIM 1CC

BUS 1 2PP

STBY AIL TRIM 11CC

AC BUS 4XP

AIL TRIM IND 1CX

No.

System Power-Up The trim tab control and indicating circuits are energized when 28 VDC and 26 VAC are applied to the aircraft bus system.

Effectivity: 328-100 Mod.10

- FOR TRAINING PURPOSES ONLY TM-Flight Controls

Page: 27-25 Issue: 08/95 ETM/ETX

Dornier 328 TRAINING MANUAL

DORNIER LUFTFAHRT

LINE /BASE MAINTENANCE

ESS BUS-3PP 3A AIL TRIM

1CC

A1

A5 Electrical Schematic for:

A3

2CC

B1

7

Main Trim Switch 2CC and Stby Trim Switch 12CC

AIL TRIM LH

AIL TRIM RH

1

2

6

5

3

4

8

7

1

2

6

5

3

4

8

7

B5

2CC

A3

A2

50CC

A

B3

A7

A1 TRIMM TEST

B7

B

A2

8CC

A2 (9)

A3

B2

9CC

(11)

A3

A1

A1

C2

8CC

B3

B1

C3

A3

A1

A1

7CC

(5)

(4)

C1

A2

X1

X1 X2

B2

5CC

A3

A1

B2

9CC

B3

B1

B3

C2

5CC B1

(3)

C3

C1

B2 X1

16CC (18)

6CC X2

A2

A2

A2 5CC

A3

6CC

A1

7CC

A3

B1

X1

B3

X2

X1

9CC

8CC

X2

X2

G2

G3

50CC G1

B

R

B2

B8

4CC 2CC

B4

A2

AIL TRIM ACTR

AIL TRIM LH

LH

FILTER

RH AIL TRIM RH

M NORMAL OPERATION

Br

A4

1

2

C = closes O = opens T = change over(transition)

B6

2CC

A8

A6

3 C O T 8 9 11

4

5

6

7

CO T 6

8

9

C O T 5

C O T 1 3 4

10

11

12 C O T 2 10

Fig. 12 Aileron Trim - Electrical Diagram (Sheet 1 of 3)

Page: 27-26 Issue: 08/95 ETM/ETX

- FOR TRAINING PURPOSES ONLY TM-Flight Controls

Effectivity: 328-100 Mod.10

Dornier 328 DORNIER LUFTFAHRT

TRAINING MANUAL LINE /BASE MAINTENANCE

BUS 1-2PP 3A

11CC

STBY AIL TRIM

A1

A3

12CC

B1

A5

A7 AIL TRIM STBY B5 RH

AIL TRIM STBY LH

12CC

B7

B3

C2

E

D2

16CC

D/N

E2 C3

C1

D3

D1

16CC E3

E1

2LF

16CC

X1 X2

B LH

LAMP TEST

R

FILTER

RH

3CX

6CX

2CX

STBY AIL

M STBY OPERATION

4CC B2

17CC

B8

A3

RESET

12CC

B4

A2

B6 AIL TRIM STBY A8 RH

AIL TRIM STBY LH

A4

13

12CC

A2

A1

A6

14

15

16

17

18

19

20

C O T 5 6 14 15 18

Fig. 13 Aileron Trim - Electrical Diagram (Sheet 2 of 3)

Effectivity: 328-100 Mod.10

- FOR TRAINING PURPOSES ONLY TM-Flight Controls

Page: 27-27 Issue: 08/95 ETM/ETX

Dornier 328 TRAINING MANUAL

DORNIER LUFTFAHRT

LINE /BASE MAINTENANCE

26VAC-BUS-6XP 1A

1CX

AIL TRIM IND

R

1TU

11TU

DAU 1

SIGN 34 H

S2 R1

W

SIGN 609

L

L

H

4CC

CCW 5CX CW AIL POSIT POTI LH

H

W

L

S1

R2 S3 BK/W ACTR POSIT SENSOR

21

SIGN 41

DAU 2

22

W

23

24

W CCW 4CX CW AIL POSIT POTI RH

25

26

27

Fig. 14 Aileron Trim - Electrical Diagram (Sheet 3 of 3) Aileron Trim Main Trim Circuit The main motor of the aileron trim actuator is controlled by the main aileron trim switch 2CC. If both rockers of the switch are held to LH (left wing down), the following contacts operate: - series contacts A1/A3 and B1/B3 close and supply 28 VDC to the left wing down circuit - parallel contacts A2/A4 and B2/B4 open and remove the ground from the right wing down circuit. 28 VDC is now supplied to the left wing down side of the motor through: Page: 27-28 Issue: 08/95 ETM/ETX

- FOR TRAINING PURPOSES ONLY TM-Flight Controls

Effectivity: 328-100 Mod.10

Dornier 328 DORNIER LUFTFAHRT

TRAINING MANUAL LINE /BASE MAINTENANCE

- contacts A3/A2 of relay 7CC - contacts A2/A3 of relay 16CC - the contacts of the actuator LH internal limit switch. The ground circuit for the motor is provided by either: - the contacts of the actuator RH internal limit switch (and then direct to ground if the actuator is at its maximum RH travel)or by the following series circuit: - the contacts of the RH internal limit switch - contacts B3/B2 of relay 16CC - contacts A2/A3 of relay 6CC - contacts B2/B3 of relay 9CC - the parallel contacts B8/B6 and A8/A6 of the main trim switch 2CC. The motor runs in the commanded direction (drives the trim tab down) until either the trim switch is released or until the LH internal limit switch operates. The operation sequence is similar in reverse when right wing down is commanded. Main Trim Runaway Override Circuits An electrical fault in the actuator control circuitry, such as sticking contacts in the main trim switch, could cause a trim runaway. Override circuits ensure that a main trim motor runaway can be stopped and reversed by instinctive operation of the main trim switch in the opposite direction to the runaway. The following example describes the operation of the circuit in the event of a runaway towards left wing down. Relay 5CC is the LH trim runaway interlock relay. It is energized when the main trim switch is held to the LH position. If contacts A1/A3 and B1/B3 of the main trim switch 2CC stick closed when the switch is released, the trim actuator will run uncommanded towards left wing down and relay 5CC will remain energized. The relay has three sets of contacts: - contacts C2/C1 close and arm the test circuit - contacts B2/B3 open and disable the coil circuit of relay 8CC (8CC is the RH trim runaway interlock relay) - contacts A2/A1 close and arm the coil circuit of the trim runaway override relay 7CC. The trim runaway will be indicated to the flight crew by the continuing left roll and by the aileron trim position indicator on the EICAS. The runaway can be stopped and reversed by holding the main trim switch to the RH position. This action energizes relay 7CC through contacts A2/A1 of 5CC. The contacts of 7CC replace the 28 VDC power supply to the left wing down side of the main trim motor with a ground connection. 28 VDC is now supplied to the right wing down side of the motor through: - contacts A5/A7 and B5/B7 of the main trim switch 2CC - contacts A3/A2 of relay 6CC - contacts B2/B3 of relay 16CC - the contacts of the actuator RH internal limit switch. The ground circuit for the motor is provided by either: - the contacts of the actuator LH internal limit switch (and then direct to ground if the actuator is at its maximum LH travel) or by the following series circuit: - the contacts of the LH internal limit switch - contacts A3/A2 of relay 16CC - contacts A2/A1 of relay 7CC. The motor drives the trim tab up (right wing down) until either the trim switch is released or until the RH internal limit switch operates. If the fault still exists on the main trim switch when the switch is released, the actuator will again run uncommanded towards left wing down. The main motor can be disabled by momentarily operating the standby trim switch 12CC to LH or RH . The operation sequence is similar in reverse if the trim runaway is to the right.

Effectivity: 328-100 Mod.10

- FOR TRAINING PURPOSES ONLY TM-Flight Controls

Page: 27-29 Issue: 08/95 ETM/ETX

Dornier 328 TRAINING MANUAL

DORNIER LUFTFAHRT

LINE /BASE MAINTENANCE

Runaway Override Test Circuit The TRIM TEST push switch 50CC is used to test the trim runaway override circuits of the following systems: - aileron trim actuator main motor - rudder trim system - elevator trim system To test the aileron trim runaway override circuit, press and hold the TRIM TEST switch and then press the main aileron trim switch 2CC to LH and then RH. If the runaway override circuits of the actuator main motor are serviceable, the actuator will operate in the reverse direction to that commanded. When the test switch is released the motor will start again in the commanded direction. The following example describes the operation of the circuit when the test switch is pressed and the main aileron trim switch held to LH. When the TRIM TEST switch is held pressed the trim test relay 9CC energizes. Relay 9CC has two sets of contacts, one for the LH circuit and one for the RH. If the main trim switch is now held to the L position, relay 5CC energizes. The RH trim runaway override relay 7CC energizes through the following series circuit: - contacts C2/C1 of relay 5CC - contacts B1/B2 of relay 9CC - contacts A2/A1 of relay 5CC. The contacts of 7CC remove the 28 VDC power supply from the left wing down side of the main trim motor and replace it with a ground connection. The actuator stops. 28 VDC is now supplied to the right wing down side of the motor through: - the same circuit as the coil of relay 7CC (see above) - contacts A3/A2 of relay 6CC - contacts B2/B3 of relay 16CC - the contacts of the actuator RH internal limit switch. The ground circuit for the motor is provided by either: - the contacts of the actuator LH internal limit switch (and then direct to ground if the actuator is at its maximum LH travel)or by the following series circuit: - the contacts of the LH internal limit switch - contacts A3/A2 of relay 16CC - contacts A2/A1 of relay 7CC. The motor now starts in the reverse direction and trims the aileron tab up (right wing down) until either: - the TRIM TEST switch 50CC is released or - the main aileron trim switch 2CC is released or - the RH internal limit switch operates. The test sequence is similar in reverse when the main trim switch is held to RH. Main Trim Motor Lockout Circuit If for any reason the aileron main trim circuit is unserviceable, it can be disabled. This is done by momentarily pressing the standby trim switch 12CC to either LH or RH. The standby aileron trim control relay 16CC energizes and self-latches through its contacts E2/E1. The ground circuit for the relay coil is provided through the RESET switch/light 17CC. In addition to the contacts for the self-latching circuit, relay 16CC has four other sets of contacts. Contacts C and D complete the circuits to the left and right wing down sides of the standby trim motor. Contacts A and B disable the left and right wing down sides of the main trim motor . The main motor is thus locked out until relay 16CC is de-energized by pressing the RESET switch/light. This re-enables the main motor and disables the standby motor. A white STBY AIL annunciator in the aileron trim reset switch/light indicates when the standby aileron trim subsystem is active. The annunciator is controlled by contacts E2/E1 of relay 16CC .

Page: 27-30 Issue: 08/95 ETM/ETX

- FOR TRAINING PURPOSES ONLY TM-Flight Controls

Effectivity: 328-100 Mod.10

Dornier 328 DORNIER LUFTFAHRT

TRAINING MANUAL LINE /BASE MAINTENANCE

Standby Trim Circuit The standby motor of the aileron trim actuator is controlled by the standby aileron trim switch 12CC. If both rockers of the switch are held to LH (left wing down), the following contacts operate: - series contacts A1/A3 and B1/B3 close and supply 28 VDC to the left wing down circuit - parallel contacts A2/A4 and B2/B4 open and remove the ground from the right wing down circuit. The standby aileron trim control relay 16CC energizes and latches, disabling the main trim circuit and switching on the STBY AIL annunciator as previously described. 28 VDC is now supplied to the left wing down side of the motor through: - contacts C2/C1 of relay 16CC - the contacts of the actuator LH internal limit switch. The ground circuit for the motor is provided by: - the contacts of the actuator RH internal limit switch (and then direct to ground if the actuator is at its maximum RH travel) or by the following series circuit: - the contacts of the RH limit switch - contacts D1/D2 of relay 16CC - the parallel contacts B8/B6 and A8/A6 of the standby trim switch 12CC. The motor runs in the commanded direction until either the trim switch is released or until the LH internal limit switch operates. The operation sequence is similar in reverse when right wing down is commanded.

SYSTEM INDICATIONS The aileron trim actuator has an integral synchro-type position transmitter. The transmitter sends an aileron trim position signal to data acquisition unit 1 (DAU 1) in the EICAS system for processing. The aileron trim setting is indicated by a white pointer against an analogue scale on the primary and FLIGHT CONTROL pages of the EICAS. CAS FIELD Indication

MFD PAGE Indication white pointer against white white pointer against aileron scale white aileron scale Scale has white tic marks Scale has white tic every 25%. marks every 25%.

Fault or Condition Indicates aileron trim settings

Standby Trim/Main Lockout Circuit Status A STBY AIL annunciator in the front face of the RESET switch/light 17CC indicates when the standby trim circuit and the main trim lockout circuit are active.

Effectivity: 328-100 Mod.10

- FOR TRAINING PURPOSES ONLY TM-Flight Controls

Page: 27-31 Issue: 08/95 ETM/ETX

Dornier 328 TRAINING MANUAL

DORNIER LUFTFAHRT

LINE /BASE MAINTENANCE

27-20 RUDDER CONTROLS AND TRIM GENERAL

Rudder Trim Actuator

° 20

Rudder Position Transmitter

-24°

Spring Tab Drive Mechanism Quadrant Assembly Spring Tab Lock Actuator Autopilot Servo

Cable Quadrants

Rudder Pedal Assemblies

Fig. 15 Rudder - General Arrangement This section provides information on that portion of the flight control system which controls the position and movement of the rudder and the rudder trim tab. Also included are the indicating systems for the rudder position, the rudder limiter status and the trim tab position. The section is divided into subsections containing detailed information on the following rudder and tab subsystems: - Rudder Controls - Rudder Trim Rudder Controls The aircraft is controlled about the yaw axis by a rudder control system. At airspeeds below 160 knots the dual rudder pedal assemblies are connected to a Flettner-type tab on the lower trailing edge of the rudder through a torsion bar and lever assembly. Movement of the rudder pedals drives the tab in the opposite sense to the yaw command and aerodynamic effects from the tab move the rudder in the commanded sense.

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Effectivity: 328-100 Mod.10

Dornier 328 DORNIER LUFTFAHRT

TRAINING MANUAL LINE /BASE MAINTENANCE

At speeds above 160 knots the lever assembly is locked by an actuator controlled by micro air data computers 1 and 2. The pedal assemblies are then effectively connected directly to the rudder and flight crew commands are not assisted by the tab. This limits the rudder deflection at high airspeeds and prevents structural overload conditions. The tab can be unlocked and the limiter actuator disabled by manually operating a switch in the flight compartment. A facility is provided for testing the actuator. The linkage from the pedal assemblies to the rudder and tab is by an arrangement of pulleys, cables, quadrants, push-pull rods, levers and bellcranks. The control cables exit the pressure compartment through pressure fairleads at the rear pressure bulkhead. Maximum rudder deflection is 24° right and 20° left. Rudder Trim The aircraft can be trimmed about the yaw axis by a trim tab located on the trailing edge of the rudder immediately above the spring tab. The tab is driven by an electrically powered linear actuator installed in the leading edge of the rudder. The actuator is powered by a DC motor and controlled by a rudder trim switch in the flight compartment. Override circuits are provided to protect against a trim runaway. Test facilities are provided for the override circuits. The rudder trim actuator can be disabled and re-enabled by a switch/light in the flight compartment.

INTERFACE TO OTHER SYSTEMS Navigation System The micro air data computers MADC 1 and 2 send discrete airspeed signals to the rudder limiter control circuit. Communications An amber RUDDER LIMITED caution message is displayed on page 2 of the radio management unit (RMU) if the rudder limiter is active at airspeeds lower than 155 knots. Indicating /Recoording System The following functions of the rudder and tab subsystem are indicated on EICAS: - the position of the rudder - the status of the rudder limiter - the position of the rudder trim actuator. Autoflight Signals from the automatic flight control system (AFCS) are used to operate the rudder when the aircraft is flying under automatic control. Refer to (Chapter 22 - AUTO FLIGHT) for further details.

Effectivity: 328-100 Mod.10

- FOR TRAINING PURPOSES ONLY TM-Flight Controls

Page: 27-33 Issue: 08/95 ETM/ETX

Dornier 328 TRAINING MANUAL

DORNIER LUFTFAHRT

LINE /BASE MAINTENANCE

RUDDER CONTROLS FUNCTIONAL DESCRIPTION The rudder control subsystem consists of the following components: FIN Component Panel Zone LH (RH) rudder pedal assemblies 210, 120

Access Door 123-AL, 211-FZF, 211GFZ, (122-AR, 212EFZ, 212-FZF) LH (RH) pedal adjustment assemblies 210,120 123-AL, 211FZF, (122-AR, 212-FZF) LH (RH) forward quadrant assemblies 120 211-LZF, (212-KFZ control rods 120, 320 various control cables 120, 130, various 140, 310 levers and bellcranks 120, 310 various pulleys 120, 140, various 310 pressure bulkhead fairleads 230 231-EFZ LH (RH) fairlead brackets 130 221-FZF, (222-FZF) aft quadrant assembly 310 312-AL, 324-AL spring tab lever assembly 324 312-CL, 324-DL torsion bar 324 324-AL, 324-DL 7CL rudder limiter actuator 324 324-DL 2CL TEST TAB LOCK switch/light 30VE (RH) 210 5CL RUD LIMIT switch/light 32VE 210 3CL, 4CL 160 knot relay 22VE 210 6CL manual rudder unlimit relay 22VE 210 9CL stby motor inhibit relay 22VE 210 16CX current detector 22VE 210 1CL, 8CL circuit breakers 12VE 210 19CX rudder position transmitter 322 322-BL

Page: 27-34 Issue: 08/95 ETM/ETX

- FOR TRAINING PURPOSES ONLY TM-Flight Controls

Effectivity: 328-100 Mod.10

Dornier 328 DORNIER LUFTFAHRT

TRAINING MANUAL LINE /BASE MAINTENANCE

LH and RH Rudder Pedal Assemblies Rudder Pedal Pedal Pivot for Wheel Brakes Pedal Adjust Handle Rudder Pedal

Brake Actuating Rod Rods to NWS Rudder Command Potentiometer

Pedal Ajustment Assembly

Push/Pull Rods to Quadrant Assembly

Fig. 16 Rudder Components - Pedal Assembly The rudder pedal assembly is a conventional pedestal mounted unit. Rudder commands are transmitted from the pedals to the forward quadrant assembly beneath the flight compartment floor by two push-pull rods and an idler lever. The idler lever of the LH (captain's) pedal assembly has a connection for the nose wheel steering potentiometer. The pedals are mounted on pivots for controlling the wheel brakes. Brake actuating rods are connected to a lever at the pivot point. A pedal spring is connected between the brake operating mechanism of each pedal and the aircraft structure. The spring ensures that the brakes release when toe pressure is removed from the pedal. LH and RH Pedal Adjustment Assemblies A pedal adjustment assembly allows the rudder pedals to be adjusted to cater for the individual requirements of pilots. The pedals are adjusted by pulling a handle and allowing the pedals to move back under spring pressure or pushing the pedals forward. When the handle is released the pedals lock in the selected position. The handle is installed on a cover between the two rudder pedals.

Effectivity: 328-100 Mod.10

- FOR TRAINING PURPOSES ONLY TM-Flight Controls

Page: 27-35 Issue: 08/95 ETM/ETX

Dornier 328 TRAINING MANUAL

DORNIER LUFTFAHRT

LINE /BASE MAINTENANCE

LH and RH Forward Quadrant Assemblies Pressure Bulkhead Fairleads

Cable Faileads

er ly dd Ru ssem m fro dal A Pe

forward Quadrant Assembly

Control Cables

Fig. 17 Rudder - forward Quadrant to Pressure Bulkhead A quadrant assembly is installed below the flight compartment floor in the captain's and first officer's rudder control run. Each assembly consists of a single cable quadrant and an input lever on a common shaft. The push-pull rod from the associated rudder pedal assembly connects to the input lever. The assemblies form the starting point for the LH and RH control cable runs to the rear fuselage. Control Cables The rudder control cables transmit the flight crew rudder commands from the forward quadrant assemblies to the aft quadrant assembly at frame 49. The cables are 7 x 19 flexible steel wire ropes made from corrosion resistant steel and have a nominal diameter of 3.2 mm (0.13 in.). The LH and RH cable runs each consist of four separate cable sections. Cable sections are joined by turnbuckles and terminated by swaged end fittings. Pulleys The control cables are guided by pulleys equipped with cable guards. The pulleys are made of a phenolic material and run in sealed ball bearings. The complete cable run from the forward quadrant to the associated cable quadrant in the rear fuselage is guided by a total of twelve pulleys. Control Rods Each rudder pedal assembly is connected to its associated forward quadrant assembly by two aluminium push-pull control rods. Two rods connect the aft quadrant assembly at frame 49 to the spring tab lever assembly in the rudder, and a further two rods connect the lever assembly to the spring tab. Page: 27-36 Issue: 08/95 ETM/ETX

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Effectivity: 328-100 Mod.10

Dornier 328 DORNIER LUFTFAHRT

TRAINING MANUAL LINE /BASE MAINTENANCE

Levers and Bellcranks The two control rods connecting each rudder pedal assembly to the associated forward quadrant assembly are supported by an idler lever. A bellcrank connects the two rods between the aft quadrant assembly at frame 49 and the spring tab lever assembly in the rudder. Levers and bellcranks run in sealed ball bearings. The connection points for the rod clevis ends are formed by self-aligning sealed ball bearings. Pressure Bulkhead Fairleads The rudder control cables exit the pressure compartment through special fairleads at the rear pressure bulkhead. Each fairlead consists of a ball headed cable sleeve sandwiched between two plates. The plates are fixed to a bracket installed on and sealed to the lower part of the pressure bulkhead. The cable passes through the sleeve which acts as a cable seal. Aft Quadrant Assembly Bellcrank Assembly

Rudder Drive Rod

Push-Pull Rod

LH Quadrant

RH Quadrant

Aft Quadrant Assembly

Autopilot Yaw Servo

from

cen

ter

fus

ela

ge Fig. 18 Rudder - from Pressure Bulkhead to Spring Tab

Effectivity: 328-100 Mod.10

- FOR TRAINING PURPOSES ONLY TM-Flight Controls

Page: 27-37 Issue: 08/95 ETM/ETX

Dornier 328 TRAINING MANUAL

DORNIER LUFTFAHRT

LINE /BASE MAINTENANCE

The aft quadrant assembly is installed on the upper forward face of frame 49. It forms the interconnection between the LH (captain's) and RH (first officer's) rudder controls. The assembly consists of a LH and a RH cable quadrant and an output lever on a common shaft. The LH quadrant has two functions: - it terminates the cable run from the captain's rudder pedals - it forms the connection point for the control cable from the autopilot yaw servo. The RH quadrant terminates the cable run from the first officer's rudder pedals. The output lever is the connection point for a push-pull rod that continues the rudder commands into the vertical stabilizer. Spring Tab Lever Assembly Connection to Rudder Spring Tab Connection

upper Torsion Bar

Spring Tab Drive Rods

Output Lever

Coupling Link Input Lever Spring Tab Locking Lever

Command Input Rod

Actuator Connection to Rudder

Spring Tab Lock Actuator lower Torsion Bar

Connection to Rudder

Fig. 19 Spring Tab Lever Assembly The spring tab lever assembly is installed in the lower leading edge section of the rudder. The assembly consists mainly of an input lever, a coupling link, an output lever and an upper and lower torsion bar. The input lever shares the same pivot axis as the rudder and acts through the coupling link on the output lever. The output lever is supported between the torsion bars and the rudder structure and has two functions: - it drives the spring tab up to 160 knots as Flettner-Type (unlocked or not limited). - it drives the rudder directly at airspeeds above 160 knots (locked or limited). Rudder Limiter Actuator 7CL The rudder limiter actuator is installed in the lower leading edge section of the rudder. The actuator has two separate (normal and standby) DC motors whose output shafts are mechanically connected to each other. The rotary output of the motors is converted in a reduction gearbox to a dual-shaft linear output. The output shafts of the actuator are connected to the rudder structure. The actuator body is connected to a locking lever. When the actuator is energized it moves the locking lever and either unlocks or locks the spring tab lever assembly. When the assembly is locked the rudder pedal assemblies are effectively connected directly to the rudder. Page: 27-38 Issue: 08/95 ETM/ETX

- FOR TRAINING PURPOSES ONLY TM-Flight Controls

Effectivity: 328-100 Mod.10

Dornier 328 DORNIER LUFTFAHRT

TRAINING MANUAL LINE /BASE MAINTENANCE

The control circuits for the two motors are mutually exclusive (external interlock circuits disable one motor when the other motor is enabled). The normal motor is controlled by signals from micro air data computers 1 and 2. The motor is driven automatically in either direction as follows: - to retract the actuator and lock the spring tab above 160 knots (increasing airspeed) - to extend the actuator and unlock the spring tab below 155 knots (decreasing airspeed). The standby motor is controlled by the RUD LIMIT switch/light 5CL. The purpose of this motor is to drive the actuator to the tab unlock position on a manual command from the flight crew. The standby motor cannot drive the actuator to the tab lock position. Internal limit switches for both motors stop actuator movement before the mechanical travel limits are reached. The actuator has an integral position transmitter. The transmitter is a three wire potentiometer whose resistance changes as a function of the actuator position. The transmitter signal is used in conjunction with the signals from the air data computers for indicating the status of the rudder limiter. TEST TAB LOCK Switch/Light 2CL

A

A

B

Test Tab Lock Switch/Light 2CL

3

4

3

4

ACTR GO

TEST TAB LOCK AUX PUMP

RH

LH

B

ENG-TRIM

ENG LH

ENG RH

Rudder Limit Switch/Light 5CL TRENDR

IMTREC

REFUEL QTY QTY

+

ARM

EXCEED

REC/FDR

-

OFF

R U D

UNLIMIT

L I M I T

Fig. 20 Rudder - Limiter Controls The TEST TAB LOCK switch is a press-to-test switch/light used to test the lock/unlock circuit of the normal motor of the rudder limiter actuator. It is installed in the RH engine/propeller test panel 30VE located in the forward RH section of the center pedestal.

Effectivity: 328-100 Mod.10

- FOR TRAINING PURPOSES ONLY TM-Flight Controls

Page: 27-39 Issue: 08/95 ETM/ETX

Dornier 328 TRAINING MANUAL

DORNIER LUFTFAHRT

LINE /BASE MAINTENANCE

To test the lock circuit, press and hold the TEST TAB LOCK switch. If the circuit is serviceable, the actuator runs to the lock position. This is indicated by an ACTR GO caption which comes on in the front face of the switch. When the switch is released the actuator returns to the unlock position and the caption goes out. RUD LIMIT Switch/Light 5CL The RUD LIMIT switch is a press in/press out switch/light. It is installed in control panel 32VE located in the aft LH section of the center pedestal. The switch is used to manually unlock the spring tab (switch off the rudder limiter) should the flight crew consider this necessary. Under normal operating conditions the switch/light is pressed in and the rudder limiter circuit is armed. At the discretion of the flight crew the switch can be pressed out to drive the rudder limiter circuit prior to the airspeed reaching 160 knots to unlocked the spring tab assembly. When the switch is pressed out an UNLIMIT caption in the front face of the switch comes on to indicate that the rudder limiter is inoperative. The switch also sends a signal to the EICAS for processing. The signal is used to indicate that the rudder limiter is manually disabled. Current Detector 16CX The current detector consists of a shunt, an amplifier and a relay. The shunt is connected in series with the normal motor of the rudder limiter actuator and thus senses motor current. The amplifier is connected across the shunt and controls the ground circuit of the relay. The relay has two sets of contacts and energizes when the normal motor is operating (in either direction). One set of contacts is connected in the actuator test circuit. The other set disables the actuator's standby motor is open when the normal motor is operating. Rudder Position Transmitter 19CX

Bracket

A

Rudder position transmitter

A

Rod Lever

Fig. 21 Rudder Components - Position Transmitter A rudder position transmitter is installed on a bracket in the trailing edge of the vertical stabilizer at rib 3. A short rod attached to a lever in the leading edge of the rudder drives the transmitter. The unit is a threewire potentiometer whose resistance changes as a function of the rudder position. It sends a 0 to 10 kΩ variable resistance signal to the EICAS for rudder position indicating.

OPERATION Power Supplies Component BUS Circuit Breaker No. rudder limiter actuator (normal operating) ESSENTIAL BUS 3PP RUD LIMIT 1CL rudder limiter actuator (standby operating) BUS 1 2PP STBY RUD LIMIT 8CL Page: 27-40 Issue: 08/95 ETM/ETX

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Effectivity: 328-100 Mod.10

Dornier 328 DORNIER LUFTFAHRT

TRAINING MANUAL LINE /BASE MAINTENANCE

System Power-Up The control and status indicating circuits for the rudder limiter actuator are energized when 28 VDC is applied to the aircraft bus system. Rudder Controls Flight Compartment to Vertical Stabilizer Control Run Rudder pedal movement is transmitted by two push-pull rods and an idler lever to the forward quadrant assembly located at frame 9. The idler lever in the LH control run has a connection point for the nose wheel steering potentiometer From the forward quadrant assembly, the movement is continued aft below the flight and passenger compartment floor by control cables and pulleys. The cables pass through guides in some frames under the floor. Cable fairleads equipped with small pulleys are used to guide the cables through the machined parts of frames 24 and 26. The cable run is virtually straight as far as a point between frames 33 and 35. At this point the cables are routed inboard and then upwards to follow the contour of the fuselage. The cables exit the pressure compartment through sealed fairleads at the rear pressure bulkhead. The cable run terminates at the aft quadrant assembly on the forward face of frame 49. The aft quadrant assembly forms the interconnection between the LH (captain's) and RH (first officer's) rudder controls. The assembly has two cable quadrants and an output lever on a common shaft. The LH quadrant terminates the cable run from the captain's rudder pedals. The autopilot yaw servo is connected by a cable to the rudder control run at the LH quadrant. The RH quadrant terminates the cable run from the first officer's rudder pedals. The output lever serves as the connection point for a push-pull rod which continues the rudder commands into the vertical stabilizer. The push-pull rod exits the fuselage immediately forward of the vertical stabilizer rear spar. The rod connects to a bellcrank assembly installed on the forward face of the rear spar between vertical stabilizer ribs 2 and 3. A short push-pull rod is connected to the output side of the bellcrank. This rod is the command input rod for the spring tab lever assembly Spring Tab Lever Assembly Flight crew yaw commands act through the input rod directly on the input lever. The movement is transmitted by the coupling link to the output lever which is installed between the upper and lower torsion bars and the rudder structure. The output lever is connected directly to the spring tab by the tab drive rods which deflect the tab in the opposite sense to the yaw command. Aerodynamic effects from the tab deflect the rudder in the correct sense. Rudder deflection at airspeeds below 160 knots is thus a function of rudder pedal movement and airspeed and the deflection angle is only limited by mechanical stops. At 160 knots micro air data computers (MADC) 1 and 2 send a signal to the control circuit of the rudder limiter actuator. The actuator moves the locking lever into a position which locks the spring tab lever assembly to the rudder structure. This effectively connects the rudder pedals directly to the rudder and prevents the spring tab from moving in relation to the rudder. Yaw commands from the flight crew now receive no assistance from the tab and rudder deflection is limited by aerodynamic forces.

Effectivity: 328-100 Mod.10

- FOR TRAINING PURPOSES ONLY TM-Flight Controls

Page: 27-41 Issue: 08/95 ETM/ETX

11TU

ESS BUS-3PP

DAU 2

SIGN 653

SIGN 647

RUDDER LIMIT 160kt=GND

BUS 1-2PP

1 1CL

5A

1 8CL

5A STBY RUD LIMIT

2

2

160kt=GND

11TU

DAU 2

A1

SIGN 621

CD X2

X2

X1

X1

3CL

4CL

A2

A1

A3

UNLIMIT NORM

- FOR TRAINING PURPOSES ONLY -

TM-Flight Controls

Fig. 22 Rudder Limiter - Electrical Diagram

RUD LIMIT

B2

B1

C2

C1 D1

5CL

B3

LO

16CX

W

HI

X2

C3 A3 D2

A1

B3

3CL

B1

A2

D1

B2

16CX A3

B2 A1

A2

B1

A3

B2

C1

2CL

B3

C2 TEST LAB LOCK

C3

A1

B3

4CL

B1

A2 A1

B2

A3

B1

6CL

A2

B3

B2

C1

C3

C2

SIGN 660 A3

A2

1TU

16CX C3

DAU 1

2LF

DIMMER

ON

OFF

7CL

TEST +28V

STBY OPERATING

FILTER

FILTER

M

M

LOCK ACTR

X1

17CX

1CW

ACTR GO

X1

9CL

X2

X2

UNLIMIT

TEST LAB LOCK

STANDBY D3

Effectivity: 328-100 Mod.10

1

2 C O T 13 15

3 C O T 13 15

4

5

6

7 C O T 13 15 16 18

8

9

10 C O T 19

11

12

13

14 C O T 4 10

15

16

17

D1

A3

A1

6CL

9CL

D2

A2

18

19

20

21

22 C = closes O = opens T = change over(transition)

23

DORNIER LUFTFAHRT

6CL

ON

OFF

NORMAL OPERATING

Dornier 328

ADC 2

TRAINING MANUAL

11FA

LINE /BASE MAINTENANCE

Page: 27-42 Issue: 08/95 ETM/ETX

1FA ADC 1

Dornier 328 DORNIER LUFTFAHRT

TRAINING MANUAL LINE /BASE MAINTENANCE

Electrical Control of Rudder Limiter Automatic Control of Rudder Limiter Actuator The ground circuits for the coils of relays 3CL and 4CL are controlled by micro air data computers (MADC) 1 and 2. At airspeeds below 160 knots the ground circuits are open. Relays 3CL and 4CL are de-energized and their contacts A and B connect 28 VDC to the unlock (limiter off) circuit of the rudder limiter actuator. The actuator is in the unlocked position and the rudder limiter is inactive. At 160 knots the signals lines from MADC 1 and 2 switch to ground and relays 3CL and 4CL energize. 28 VDC is supplied to the lock (limiter on) circuit of the actuator's normal motor through: - terminals A1/D1 of the current detector 16CX - contacts B1/B2 of relay 3CL - contacts B1/B2 of relay 4CL - contacts B3/B2 of relay 6CL - the contacts of the normal motor's "on" limit switch. The ground circuit for the actuator is formed through: - the contacts of the normal motor's "off" limit switch (and then direct to ground until the actuator starts to move) and by the following series circuit after the actuator has moved from its off position: - the contacts of the actuator internal off limit switch - contacts A2/A3 of relay 6CL - contacts A2/A1 of relay 4CL. The actuator runs to the lock (limiter on) position until the internal "on" limit switch operates. The spring tab lever assembly is now mechanically locked and the rudder limiter is active. The operation sequence is similar in reverse when the airspeed drops below 155 knots. Note that the airspeed signals from MADC 1 and 2 are also sent to a data acquisition unit (DAU 2) in the EICAS system for processing. The signals are used in the logic that generates certain rudder limiter condition messages. Normal and Standby Motor Mutual Exclusion When the normal motor of the actuator is operating in any direction, the relay of current detector 16CX energizes. Contacts D3/B2 of 16CX energize relay 9CL, the contacts of which remove the ground circuit from the standby motor. This provides an interlock circuit which prevents the standby motor from operating at the same time as the normal motor. Should the flight crew opt to manually disable the rudder limiter by pressing out the RUD LIMIT switch/light 5CL, relay 6CL energizes. Contacts A and B of the relay open and interrupt the 28 VDC and ground lines to the normal motor of the actuator. Rudder Limiter Disable The rudder limiter can be disabled at the discretion of the flight crew. The disable function is controlled by the RUD LIMIT switch/light 5CL. The switch/light has three banks of contacts. When the switch/light is pressed out to disable the rudder limiter: - contacts A2/A3 switch on a RUD UNLIMIT caption in the front face of the switch - contacts B2/B3 energize relay 6CL - contacts C2/C3 send a ground signal to data acquisition unit 1 (DAU 1) in the EICAS system for processing. The signal is used to display a blue RUDDER MAN UNLIMIT message on the EICAS. When relay 6CL energizes: - contacts A and B interrupt the power and ground circuits for the normal motor of the rudder limiter actuator - contacts C1/C2 connect 28 VDC to the unlock (limiter off) circuit of the standby motor of the actuator.

Effectivity: 328-100 Mod.10

- FOR TRAINING PURPOSES ONLY TM-Flight Controls

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Dornier 328 TRAINING MANUAL

DORNIER LUFTFAHRT

LINE /BASE MAINTENANCE

The ground circuit for the standby motor is formed through: - the conta cts of the standby motor's "on" limit switch (and then direct to ground until the actuator starts to move) and then through contacts D1/D2 of relay 6CL (a parallel ground connection is also provided by contacts A3/A2 of relay 9CL). If the actuator is in the lock (limiter on) position when the RUD LIMIT switch/light is pressed out, it will run to the unlock (limiter off) position until the internal "off" limit switch operates. The spring tab lever assembly is now mechanically unlocked and the rudder limiter is disabled. If the actuator is already in the unlock position when the switch/light is pressed out, the normal motor of the actuator is isolated and the rudder limiter remains disabled until the switch/light is pressed in. When the switch/light is pressed in, relay 6CL de-energizes. This disables the standby motor and re-enables the normal motor. Rudder Limiter Actuator Test The rudder limiter actuator and the associated limiter control circuit can be tested. The test circuit is controlled by the TEST TAB LOCK switch/light 2CL. The switch/light has three sets of contacts. When the switch is pressed and held: - contacts A and B simulate the 160 knots ground signals from air data computers 1 and 2 respectively. Relays 3CL and 4CL energize and the actuator moves to the lock (limiter on) position. - contacts C1/C3 close. When the actuator starts to move, the relay of the current detector 16CX energizes. This connects 28 VDC to the ACTR GO caption in the front face of the TEST TAB LOCK switch and energizes relay 9CL. The ground circuit for the ACTR GO caption is provided through contacts C2/C3 of relay 6CL and A1/A2 of relay 9CL. When the TEST TAB LOCK switch is released, relays 3CL and 4CL de-energize and the actuator returns to the unlock position. Note that the test can only be performed when the RUD LIMIT switch/light 5CL is pressed in (rudder limiter control circuit enabled).

SYSTEM INDICATIONS Certain components of the rudder control system send signals to EICAS. The signals are sent to data acquisition units (DAU’s) and are used: - to display the position of the rudder by a synoptic - to indicate correct operation of the rudder limiter by blue status messages - to indicate a malfunction in the rudder limiter system by amber caution messages. Rudder Position Indicating The rudder position transmitter is a three-wire potentiometer whose resistance changes as a function of the rudder position. It sends a variable resistance signal DAU 1. The resistance values correspond to the following rudder deflections: - 0.5 kΩ corresponds to a full left deflection - 5 kΩ corresponds to rudder neutral - 9.5 kΩ corresponds to a full right deflection. The position of the rudder is indicated by a blue synoptic on the FLIGHT CONTROL page of the EICAS. If the transmitter signal is invalid, the blue synoptic is replaced by an amber X.

Page: 27-44 Issue: 08/95 ETM/ETX

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Effectivity: 328-100 Mod.10

Dornier 328 DORNIER LUFTFAHRT

TRAINING MANUAL LINE /BASE MAINTENANCE

Rudder Limiter Monitoring General The operation of the rudder limiting system is monitored within the EICAS by a logic arrangement. The inputs to the logic arrangement are derived as follows: - airspeed signals sent from micro air data computers (MADC) 1 and 2. The MADC’s send discrete signals to DAU 2. The signal lines are open circuit at airspeeds below 160 knots and grounded at airspeeds above 160 knots. - from the position transmitter in the rudder limiter actuator. The signal has a value of 0.5 kΩ when the actuator is in the fully extended (rudder unlimited) position and 9.5 k Ω in the fully retracted (rudder limited) position. These values are converted to percentage values for logic evaluation purposes within the EICAS (0.5 kΩ = 0% and 9.5 kΩ = 100%). - from the RUD LIMIT switch/light 5CL. The signal line is open circuit when the switch/light is pressed in (rudder limiter not disabled) and grounded when the switch/light is pressed out (rudder limiter disabled). These four signals are evaluated in the logic circuits to produce caution and status messages relating to the operation of the rudder limiter. Correct Rudder Limiter Function Below 155 Knots (Limiter Inactive) If both MADC’s report an airspeed below 155 knots and the rudder limiter is inactive, then: - a blue RUDDER NOT LIMITED status message is displayed on the FLIGHT CONTROL page of the EICAS. Incorrect Rudder Limiter Function Below 155 Knots (Limiter Active) If both MADC’s report an airspeed below 155 knots and the rudder limiter is active, then: - an amber RUDDER LIMITED caution message is displayed on the CAS field of the primary EICAS page, on the FLIGHT CONTROL page and on page 2 of the radio management unit (RMU). Correct Rudder Limiter Function Above 160 Knots (Limiter Active) If both MADC’s report an airspeed above 160 knots and the rudder limiter is active, then: - a blue RUDDER LIMITED status message is displayed on the FLIGHT CONTROL page of the EICAS. Incorrect Rudder Limiter Function Above 160 Knots (Limiter Inactive) If both MADC’s report an airspeed above 160 knots and the rudder limiter is inactive, then: - an amber RUDDER NOT LIMITED caution message is displayed on the CAS field of the primary EICAS page and on the FLIGHT CONTROL page. MADC 1 and MADC 2 Report Different Airspeeds If one MADC reports an airspeed below 155 knots and the other MADC reports an airspeed above 160 knots, then: - an amber RUDDER LIMIT FAIL caution message is displayed on the CAS field of the primary EICAS page and on the FLIGHT CONTROL page. This message is inhibited if the airspeed reported by both MADC’S is between 155 and 165 knots. Rudder Limiter Actuator Fails in Intermediate Position If MADC 1 and MADC 2 both report an airspeed above 160 knots or below 155 knots and the actuator has not moved to the lock or unlock position respectively after 1 second, then: - an amber RUDDER LIMIT FAIL caution message is displayed on the CAS field of the primary EICAS page and on the FLIGHT CONTROL page. Rudder Limiter Manually Disabled by Flight Crew If the RUD LIMIT switch/light 5CL is pressed out to manually disable the rudder limiter, then: Effectivity: 328-100 Mod.10

- FOR TRAINING PURPOSES ONLY TM-Flight Controls

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Dornier 328 TRAINING MANUAL

DORNIER LUFTFAHRT

LINE /BASE MAINTENANCE

- a blue RUDDER MAN UNLIMIT status message replaces all other rudder limiter messages on the CAS field of the primary EICAS page and on the FLIGHT CONTROL page. CAS FIELD Indication -

MFD PAGE Indication BLUE

Fault or Condition Rudder not limited (speed 160 & rudder limiter not activated.

BLUE

Rudder limited (speed >155 kts) MADC 2 & 1 report >155 & rudder limiter activated.

RUDDER LIMITED

AMBER

AMBER

RUDDER LIMITED

RUDDER LIMITED

AMBER

AMBER

RUDDER LIMIT FAIL

RUDDER LIMIT FAIL

BLUE

-

Rudder limited (speed 200 kts Relay 55CC energized and MADC 1 report >200 kts Elevator trim speed slow at airspeed 3°). Flap control FLAP ASYM FLAP ASYM circuit locked out (failed passive) BLUE BLUE Indicates the actual flap position. LH/RH position LH/RH position When actual position matches selected position synoptic against white synoptic against white (blue flap synoptic and white digits). scale scale When actual and selected position: If flap position signal is If flap position signal is - synoptic and digit in amber invalid flap synoptic is invalid flap synoptic is - selected position is indicated by an amber line replaced by an amber X replaced by an amber X Effectivity: 328-100 Mod.10

- FOR TRAINING PURPOSES ONLY TM-Flight Controls

Page: 27-109 Issue: 08/95 ETM/ETX

Honeywell

FLAP CRTL FAIL FLAP ASYM END

97.0

97.0

LH

RH ELEVATOR

TQ

ELEV DISCONNECT RUDDER LIMITED

RUDDER

80.2

80.2

AILERON

Fig. 60 Flaps - EICAS Indications

TM-Flight Controls

- FOR TRAINING PURPOSES ONLY -

NP

800

TRIM

E L E V

AIL RUD ROLL

800

NU

ITT

TRIM SPEED FAST 80.3

ND

80.3

ROLL

FLAP ASYM FLAP CRTL FAIL FLAPS

18 °

20

NU

500 2870

OIL TEMP OIL PRSS FF LBS / HR FQ LBS

ND 500 2870

ENGINE

12 °

MAIN

SYSTEM 1 / 3 HYDR

12 °

FUEL

NEXT

CAPT REF SYSTEM DATA

COPY

AHRS

F/O SYSTEM

MSG

Effectivity: 328-100 Mod.10

DORNIER LUFTFAHRT

32

FLIGHT CONTROL

2000 FT 0 FPM

NH

12 14 °

CAB ALT V/S

Dornier 328

TRAINING MANUAL

LINE /BASE MAINTENANCE

Page: 27-110 Issue: 08/95 ETM/ETX

Honeywell

Dornier 328 DORNIER LUFTFAHRT

TRAINING MANUAL LINE /BASE MAINTENANCE

27-60 SPOILERS GENERAL

RH ROLL SPOILER

RH GROUND SPOILERS

LH GROUND SPOILERS

LH ROLL SPOILER

Fig. 61 Spoilers - General Arrangement This section provides information on that portion of the flight control system which controls the position and movement of the ground and roll spoilers. Also included are the systems which indicate the position of the ground and roll spoilers. The section is divided into subsections containing detailed information on the following spoiler subsystems: - Ground Spoilers - Roll Spoilers

Effectivity: 328-100 Mod.10

- FOR TRAINING PURPOSES ONLY TM-Flight Controls

Page: 27-111 Issue: 08/95 ETM/ETX

Dornier 328 TRAINING MANUAL

DORNIER LUFTFAHRT

LINE /BASE MAINTENANCE

Ground Spoilers (optional) The aircraft can be equipped with a ground spoiler system consisting of four hydraulically operated spoiler panels. Two spoilers are located on the upper surface of the LH wing forward of the flaps and two in a corresponding location on the RH wing. When deployed the spoiler panels protrude into the airflow above the wing, dumping lift and assisting other braking systems in reducing the landing run. The operation of the spoilers is controlled electrically. The spoilers deploy automatically shortly after the aircraft touches down and stow automatically when engine power is reduced on completion of the landing roll. The spoilers will also deploy automatically if a takeoff is aborted. Spoiler deployment is inhibited when the aircraft is airborne. At the discretion of the flight crew the spoiler control circuit can be disabled by a switch in the flight compartment. Each of the four spoiler panels is hinge mounted on five brackets attached to the wing rear spar. The inboard spoilers extend from wing station Y 969.71 to Y 3193 and the outboard spoilers from Y 3193 to Y 5469. Each spoiler panel is driven by a hydraulic actuator powered by the main hydraulic system. Spoiler deflection is 69.6° relative to the wing chord line. Roll Spoilers The aircraft is equipped with a roll spoiler system consisting of two hydraulically operated spoiler panels. The LH spoiler is located on the upper surface of the LH wing forward of the outboard section of the flap. The RH spoiler is in a corresponding location on the RH wing. Only one spoiler operates at a time. The LH spoiler deflects upwards in response to a left roll command. The RH spoiler deflects upwards in response to a right roll command. The spoilers assist the ailerons and generate additional rolling moments at low airspeeds. The command inputs to the roll spoiler actuators are formed by mechanical connections to the aileron control linkage. Each spoiler panel is hinge mounted on four brackets attached to the wing rear spar. The spoilers extend from wing station Y 5469 to Y 6797. Each spoiler is driven by a hydraulic actuator powered by the main hydraulic system. A priority arrangement in the hydraulic system maintains the hydraulic power supply to the roll spoilers if the fluid level in the main hydraulic reservoir is low. The operation of the spoilers is controlled by roll command inputs to the aileron control linkage. The amount of spoiler deflection is a function of aileron deflection. Maximum spoiler deflection is 68° relative to the wing chord line at maximum aileron deflection. Indications The following functions of the ground and roll spoiler subsystems are indicated on the electronic indicating, caution and advisory system EICAS : - the position of the ground spoilers - the status of the ground spoilers and their control circuit - the position of the roll spoilers.

INTERFACE TO OTHER SYSTEMS Hydraulic Power (Chapter 29) The ground and roll spoilers are supplied with hydraulic power from the main hydraulic power system. The microswitch 9DX in the double shuttle valve is a component of the hydraulic indicating system. The switch is used to indicate the position of the priority valve in the main hydraulic power system. Indicating/Recording Systems (Chapter 31) The position sensor in each roll spoiler actuator sends signals to the EICAS. The signals are used to display the roll spoiler position by synoptics on the EICAS FLIGHT CONTROL page.

Page: 27-112 Issue: 08/95 ETM/ETX

- FOR TRAINING PURPOSES ONLY TM-Flight Controls

Effectivity: 328-100 Mod.10

Dornier 328 DORNIER LUFTFAHRT

TRAINING MANUAL LINE /BASE MAINTENANCE

GROUND SPOILERS (OPTIONAL) This section provides information on that portion of the flight control system which controls the operation of the ground spoilers. Also included is the ground spoiler indicating system.

FUNCTIONAL DESCRIPTION The ground spoiler system consists of the following components: FIN Component Panel 2CS ground spoiler arm/disarm switch/light 32VE 3CS LH power lever microswitch 9VE 4CS ground spoiler auto-deploy relay 32VE 5CS RH power lever microswitch 9VE 6CS ground spoiler auto-deploy relay 23VE 7CS LH condition lever microswitch 9VE 8CS RH condition lever microswitch 9VE 9CS ground spoiler auto-stow relay 23VE 10CS valve manifold 13CS spoilers armed indicating relay 23VE 3CW LH inboard spoiler proximity sensor 3CW RH inboard spoiler proximity sensor 5CW LH outboard spoiler proximity sensor 5CW RH outboard spoiler proximity sensor LH inboard actuator LH outboard actuator RH inboard actuator RH outboard actuator LH relief restrictor valve RH relief restrictor valve 1CS circuit breaker 12VE

Zone 210 210 210 210 210 210 210 210 250 210 530 630 530 630 530 530 630 630 530 630 210

Access Door

251-BT, 252-BT 531-BB 631-BB 531-EB 631-EB 531-BB 531-EB 631-BB 631-EB 531-DB 631-DB

Valve Manifold 10CS

Control Valve Manifold

R3

Return Port

FW

D

R3

Solenoid Valve Wiring Coonector

Retract Port Extend Port

Pressure Port

Solenoid Valve

Fig. 62 Ground Spoiler Valve Manifold Effectivity: 328-100 Mod.10

- FOR TRAINING PURPOSES ONLY TM-Flight Controls

Page: 27-113 Issue: 08/95 ETM/ETX

Dornier 328 TRAINING MANUAL

DORNIER LUFTFAHRT

LINE /BASE MAINTENANCE

The valve manifold is the hydraulic control element of the ground spoiler control system. The manifold is installed in the upper fuselage fairing on the LH side below wing rib 3. It controls the hydraulic pressure and return lines to the spoiler actuators and consists of a housing with the following components: - two solenoid valves - two control valves - a hydraulic pressure port and a port for the hydraulic return line - pressure line filter. - a extend port and a retract port for the hydraulic supply to the spoiler actuators. - wiring connector. SOLENOID VALVE I

SOLENOID WIRING VALVE II CONNECTOR

PRESSURE RETURN CONTROL

RETURN PORT EXTEND PORT

RETRACT PORT

PRESS. LINE FILTER

CONTROL VALVES

PRESSURE PORT

Fig. 63 Ground Spoilers Valve Manifold - Hydraulic Diagram The solenoid valves are controlled by electrical signals from the spoiler control circuit. When the ground spoilers are stowed, both solenoid valves are de-energized. The valves are energized by the deploy signals from the spoiler control circuit. Both valves must energize to deploy the spoilers. The solenoid valves control the supply of hydraulic pressure to the spools of two control valves. The main hydraulic pressure and return lines to the spoiler actuators are connected in cascade through the two control valves. This means that the spools of both control valves must be in the same position before the spoilers can deploy. When both the solenoid valves are de-energized, hydraulic pressure is prevented from reaching the control valve spools. Each spool is held by a spring in a position which holds the pressure and return lines to the four actuators open in the stow direction. Hydraulic pressure is thus constantly applied to the actuators to maintain the spoilers in the stowed position. When both solenoid valves are energized, hydraulic pressure moves the spools of both control valves down to the deploy position. This reverses the hydraulic pressure and return lines to the actuators. The actuators extend and deploy the spoilers. As long as the solenoid valves are energized, hydraulic pressure is constantly applied to maintain the spoilers in the deployed position.

Page: 27-114 Issue: 08/95 ETM/ETX

- FOR TRAINING PURPOSES ONLY TM-Flight Controls

Effectivity: 328-100 Mod.10

Dornier 328 DORNIER LUFTFAHRT

TRAINING MANUAL LINE /BASE MAINTENANCE

Ground Spoiler Actuators A

B

89

10

A R 12 R 11

R6

A R3

A

R3 R6

6 1

11

B

R 11 R 12

A FW

8

D

7 6

1 2 3 4 5 6 7 8 9 10 11

5

2 4

Retract Line Extend Line Indicator Pin Plunger Housing Connection Point to Wing Spoiler Actuator Connection Point on Spoiler Proximity Sensor Target Spoiler Panel Flap

3

Fig. 64 Ground Spoilers Actuators Each spoiler panel is driven by its own hydraulic actuator. The four identical actuators are installed between connection points on the wing rear spar.

Extending

Retracted

Fig. 65 Ground Spoilers Actuator - Internal View The following description applies to all actuators.

Effectivity: 328-100 Mod.10

- FOR TRAINING PURPOSES ONLY TM-Flight Controls

Page: 27-115 Issue: 08/95 ETM/ETX

Dornier 328 TRAINING MANUAL

DORNIER LUFTFAHRT

LINE /BASE MAINTENANCE

The ground spoiler actuator is a double-acting hydraulic cylinder. The unit has two ports for the extend and retract lines for connecting the hydraulic lines. In the retracted position the actuator piston is mechanically locked by a spring-loaded plunger. The plunger mechanism has an indicator pin that protrudes from the plunger housing when the actuator is unlocked. When the spoiler deploy signal is received the plunger is moved by hydraulic pressure in the actuator's extension chamber and disengages from the piston. The piston starts to extend. At the same time the pressure controlled check valve is opened by the extension pressure and allows the return fluid from the retraction chamber to flow through the restrictor back to the extension chamber. This gives an extremely rapid actuator extension time (and therefore fast ground spoiler deployment). Return fluid from the retraction chamber is prevented from returning to the hydraulic system by the check valve. A damper at the end of the extension stroke prevents the piston from hitting the end stop. When the actuator retracts the pressure controlled check valve is closed and fluid from the extension chamber is returned to the hydraulic system through the extend port. Restrictor Relief Valves

A R 12 R 11

R6 R3

Retract Line

A

Extend Line

FW

D

R3 R6

to Actuator Restrictor Relief Valve

to Actuator

R 11 R 12

A

Fig. 66 Ground Spoilers Restrictor Relief Valve Two identical relief restrictor valves are installed. The valves are installed immediately inboard of the LH and RH outboard ground spoiler actuators. Each valve is connected between the retract line and the extend line to the ground spoiler actuators immediately inboard of the outboard actuators. The cracking pressure of the valve is 2828 ± 72 psi. The valve cracks when pressure is applied to the retract port of the actuator and diverts the excess pressure into the extend line through a relief line. This allows a restricted flow of fluid to bypass the actuator, to bleed the hydraulic line and to hold fluid temperature in operating limits.

Page: 27-116 Issue: 08/95 ETM/ETX

- FOR TRAINING PURPOSES ONLY TM-Flight Controls

Effectivity: 328-100 Mod.10

Dornier 328 DORNIER LUFTFAHRT

TRAINING MANUAL LINE /BASE MAINTENANCE

Ground Spoiler Arm/Disarm Switch/Light 2CS

A

TRENDR

IMTREC

REFUEL QTY QTY

+

ARM

EXCEED

REC/FDR

-

OFF

R U D

UNLIMIT

L I M I T

Fig. 67 Ground Spoilers Switch/Light 2CS The GND SPOILER switch/light is a press in/press out switch. It is installed in control panel 32VE located in the aft LH section of the center pedestal and must be pressed in to arm the ground spoiler control circuit. Provided that the landing gear is down and the condition levers set to above 95%, the armed status is indicated by an ARM caption in the front face of the switch. The switch can be pressed out at the discretion of the flight crew to disable the ground spoilers. This is indicated by an OFF caption in the switch. Microswitches 3CS/5CS/7CS/8CS

Microswitch 8CS

Microswitch 3CS

Microswitch 7CS

Microswitch 5CS

Fig. 68 Ground Spoilers Condition- and Powerlever Microswitches

Effectivity: 328-100 Mod.10

- FOR TRAINING PURPOSES ONLY TM-Flight Controls

Page: 27-117 Issue: 08/95 ETM/ETX

Dornier 328 TRAINING MANUAL

DORNIER LUFTFAHRT

LINE /BASE MAINTENANCE

These microswitches are installed in the center pedestal. Microswitches 3CS and 5CS are operated by the LH and RH engine power levers respectively. Their contacts are closed below the flight idle (FI) setting and open above the FI setting. The microswitches control (in conjunction with the PSEU weight-on-wheels circuit) the auto-deploy relays 4CS and 6CS. Microswitches 7CS and 8CS are operated by the LH and RH engine condition levers respectively. At power settings below 95% the contacts control the auto-stow relay 9CS. At power settings above 95% they control the ARM caption in the GND SPOILER switch/light 2CS. Proximity Sensors 3CW/5CW (refer to Fig. 64) A proximity sensor is installed for each spoiler. The four identical sensors are installed in the trailing edge section of the wing immediately inboard of their associated spoiler actuator. The target for each sensor is attached to the spoiler. The sensors send spoiler position information to a proximity switch electronic unit (PSEU). The PSEU processes the position information and sends it to EICAS. The EICAS uses the information to display system status and spoiler position. The PSEU is a component of the landing gear position and warning system.

OPERATION Electrical Power Supplies Component

Bus

Circuit Breaker

No.

ground spoiler control system

ESSENTIAL BUS 3PP

GND SPOILER 1CS

Hydraulic Power Supplies When the main hydraulic system is energized hydraulic power is supplied to the pressure and return ports of the valve manifold 10CS. System Power-Up The ground spoiler control circuit is energized when 28 VDC is applied to the aircraft bus system. System Pre-Takeoff Test The ground spoiler system is tested during the normal procedure for applying engine power for takeoff. With the engine power levers at ground idle and the GND SPOILER switch/light 2CS pressed out (system disarmed), the condition levers are advanced above 85%. This actuates the microswitch 7CS and 8CS and ensures that the auto-stow relay 9CS cannot energize when the system is armed. The GND SPOILER switch/light is now pressed in to arm the system for takeoff. This has the following effect: - the ARM caption in the switch/light comes on to indicate the armed status - auto-deploy relays 4CS and 6CS energize through the series circuits formed by the switch/light and the power lever microswitches 3CS and 5CS - solenoid valves I and II in the valve manifold energize through the series circuits formed by the contacts of relays 4CS, 6CS and 9CS - hydraulic pressure is applied to the extend ports of all four ground spoiler actuators and the spoilers deploy simultaneously - relay 13CS energizes and sends a discrete open line signal to the EICAS. The signal switches on a GND SPOILER ARMED message on the EICAS. Note that relay 13CS checks the integrity of the GND SPOILER circuit breaker 1CS. If the circuit breaker is not closed when the system is armed, the EICAS message will not appear. Page: 27-118 Issue: 08/95 ETM/ETX

- FOR TRAINING PURPOSES ONLY TM-Flight Controls

Effectivity: 328-100 Mod.10

Dornier 328 DORNIER LUFTFAHRT

TRAINING MANUAL LINE /BASE MAINTENANCE

When the power levers are advanced through the flight idle position for takeoff, the microswitches 3CS and 5CS are actuated and de-energize the auto-deploy relays 4CS and 6CS. This interrupts the 28 VDC power and ground lines to both spoiler control solenoid valves. The valves de-energize. Hydraulic pressure is applied to the retract ports of all four ground spoiler actuators and the spoilers stow simultaneously. When the gear is retracted after take-off, relay 36GA de-energizes and switches off the ARM caption in the GND SPOILER switch/light. Relay 36GA is a component of the landing gear position and warning system. Spoiler Inflight Inhibition Spoiler deployment is inhibited when the aircraft is airborne. As previously described in, both solenoid valves in the valve manifold must energize before the spoilers can deploy. The auto-deploy relays 4CS and 6CS each control one solenoid valve. Relay 4CS controls solenoid valve I and relay 6CS controls solenoid valve II. Both relays are prevented from energizing when the aircraft is airborne by the following independent circuits: Landing Gear Circuit

Fig. 69 Ground Spoiler System - Logic Diagram - EQ #21 and #22 The LH and RH main gear weight-on-wheels (WOW) proximity sensors send landing gear status information to the PSEU. The PSEU evaluates the information and generates two discrete signals that are the result of two logic equations (#21 and #22). The discrete signal lines are connected in the ground lines of the coils of relays 4CS and 6CS. Until both main gears are loaded (aircraft on the ground), the signals derived from equations #21 and #22 are open circuit and relays 4CS and 6CS cannot energize. Power Lever Circuit During all normal flight operations both engine power levers are set to at least flight idle (FI). At these settings the contacts of the LH and RH power lever micro switches 3CS and 5CS are open. The contacts of 3CS and 5CS control the 28 VDC power lines of relays 4CS and 6CS respectively. Neither relay can energize, therefore, until its associated power lever is retarded to below FI. Effectivity: 328-100 Mod.10

- FOR TRAINING PURPOSES ONLY TM-Flight Controls

Page: 27-119 Issue: 08/95 ETM/ETX

1 3A GND SPOILER

1CS 2

OPEN= GROUND SPOIL ARMED GND = NO INDICATION SIGNAL 315

ARM OFF

A3 RH INBORD GND SPOILER

RH OUTBORD GND SPOILER

3CW

5CW

3CW

5CW

D3 2CS

A1

A2

B1

B2

A1

GROUND SPOILER

A2

D1

D2

ARM OFF

LH OUTBORD GND SPOILER

A3

B1 7CS C F.I. 3CS

< F.I.

36GA

>85%

>F.I. 5CS

D3

A3

A1 4CS A2

A3

8CS 85%

A1 6CS

10CS

VALVE BLOCK I II

A2 LAMP TEST

A1

A3

9CS A2

X1 4CS

X1

X2

DIMMER 2LF

X1

6CS

9CS X2

X2

9CS

02

03

01

ARM OFF

ARM

B3

OFF

B1

9CS B2 X1 13CS X2

GND MODE=GND AIR MODE=OPEN

6GA

Effectivity: 328-100 Mod.10

1

PROXIMITY SWITCH ELECTRONIC

2

3

4

5

6

7

8

9

10

S O W 12 20

S O W 12 22

11

12

13 S O W 12 14 21

14 S O W 18

15

16

17

18

19

20

21

22

DORNIER LUFTFAHRT

Fig. 70 Ground Spoiler - Electrical Schematic

TM-Flight Controls

- FOR TRAINING PURPOSES ONLY -

LH INBORD GND SPOILER

B3

Dornier 328

TRAINING MANUAL

LINE /BASE MAINTENANCE

Page: 27-120 Issue: 08/95 ETM/ETX

ESS-BUS-3PP

LG WOW 1 RG WOW 1 Timedelay

&

LG WOW 2 RG WOW 2 Timedelay

&

1

LH Inboard GND Spoiler Actuator

1

RH Inboard GND Spoiler Actuator

1

1

RH Outboard GND Spoiler Actuator

1

GND SPOILER

OFF

AUTO-DEPLOY Conditionlever > 95% and Powerlever below FI

ARINC 429

Ext. Port

Retr. Port GND Spoiler Valve Manifold

EICAS

LH Outboard GND Spoiler Actuator LG WOW 1 RG WOW 1 Timedelay

&

LG WOW 2 RG WOW 2 Timedelay

&

PSEU

1

LH Inboard GND Spoiler Actuator

1

RH Inboard GND Spoiler Actuator

GND SPOILER ARM OFF

Ext. Port

Retr. Port

EICAS

Pressure Main Return Main 1 Proximity Sensor

Dornier 328

GND Spoiler Valve Manifold

LINE /BASE MAINTENANCE

AUTO-DEPLOY Conditionlever < 95% or Powerlever above FI

TRAINING MANUAL

Page: 27-121 Issue: 08/95 ETM/ETX

ARINC 429

Fig. 71 Ground Spoiler - Hydraulic Schematic

- FOR TRAINING PURPOSES ONLY -

RH Outboard GND Spoiler Actuator

ARM

PSEU

TM-Flight Controls

1

DORNIER LUFTFAHRT

Effectivity: 328-100 Mod.10

LH Outboard GND Spoiler Actuator

Dornier 328 TRAINING MANUAL

DORNIER LUFTFAHRT

LINE /BASE MAINTENANCE

Spoilers Disarm/Arm At the discretion of the flight crew the ground spoiler control circuit can be disarmed by pressing out the GND SPOILER switch/light 2CS. This removes electrical power from the spoiler control circuit and deenergizes all relays and solenoid valves. If the spoilers are deployed when the circuit is disarmed they will immediately stow. An OFF caption on the front face of the switch comes on to indicate that the system is disarmed. The ground spoilers are armed for automatic deployment when the GND SPOILER switch/light is pressed in. This switches off the OFF caption in the switch/light and connects 28 VDC power to the spoiler control circuit. The armed status is indicated by: - a GND SPOILER ARMED message on the EICAS - an ARM caption on the front face of the switch/light. Auto-Deployment on Landing During all normal flight operations, including the approach, the engine power and condition levers are set as follows: - both power levers at flight idle (FI) or higher - both condition levers at 85% or higher. When both main landing gears are loaded on touchdown, the LH and RH main gear WOW sensors tell the PSEU to complete the ground circuits for the auto-deploy relays 4CS and 6CS. The condition levers remain above 85% for reverse thrust. When the landing is assured after touchdown, both power levers are retarded to reverse. The contacts of the power lever micro switches 3CS and 5CS now complete the 28 VDC power supply to relays 4CS and 6CS. The relays energize. The solenoid valves I and II in the valve manifold energize and hydraulic pressure is applied to the extend ports of all four ground spoiler actuators. The spoilers deploy simultaneously. The ARM caption in the GND SPOILER switch/light goes out when the condition levers are retarded. Auto-Deploy on Aborted Takeoff If a takeoff is aborted the spoilers deploy automatically when the power levers are retarded. This occurs through the power lever micro switches 3CS and 5CS in the same way as described in the previous paragraph. Auto-Stow On completion of the landing roll both condition levers are retarded to below 85% power. The contacts of the condition lever micro switches 7CS and 8CS now complete the 28 VDC power supply to the autostow relay 9CS. The relay energizes and its B and C contacts interrupt the ground circuits for the solenoid valves I and II respectively. Both solenoid valves de-energize. Hydraulic pressure is applied to the retract ports of all four ground spoiler actuators and the spoilers stow simultaneously. Once the spoilers have stowed automatically, a lockout circuit prevents them from deploying during applications of engine power during ground manoeuvring. Spoiler Lockout During Ground Manoeuvring When manoeuvring the aircraft on to the ramp it may be necessary to apply power by advancing the power lever above FI (Flight Idle). The spoilers are prevented from deploying during such manoeuvres by a lockout circuit. The lockout circuit is activated when both condition levers are below 85% and the power levers are below FI. The auto-stow relay 9CS is energized by a series circuit formed by the A contacts of the auto-deploy relays 4CS and 6CS and the A contacts of relay 9CS. Note that because the condition lever are not used for ground manoeuvring and remain in the MIN position, relays 9CS stay energized.

Page: 27-122 Issue: 08/95 ETM/ETX

- FOR TRAINING PURPOSES ONLY TM-Flight Controls

Effectivity: 328-100 Mod.10

Dornier 328 DORNIER LUFTFAHRT

TRAINING MANUAL LINE /BASE MAINTENANCE

SYSTEM INDICATIONS The information from the ground spoiler proximity sensors is registered as part of the takeoff configuration test. If a ground spoiler is not stowed for takeoff the T/O configuration warning is triggered. The following signals are sent from the ground spoiler system to EICAS. - proximity sensors signals (indirectly through the PSEU) - discrete signal from the GND SPOILER switch/light to DAU 1. The signals are used to: - indicate deployed ground spoilers by synoptics - indicate a failed spoiler proximity sensor by an amber caution message and synoptics - indicate when the ground spoiler control circuit is armed by a blue status message - indicate if a ground spoiler is not stowed when it should be by an amber status message. Ground Spoiler Position Indicating The position (deployed or stowed) of each ground spoiler is registered by a proximity sensor at each spoiler location. The sensors indicate spoiler position information to a PSEU. After processing, the position information is sent on an ARINC bus to the EICAS. The following ground spoiler position information is displayed on the EICAS: - on the primary page: Blue LH and RH ground spoiler synoptics on the upper side of the flap bar. - on the FLIGHT CONTROL page: Blue LH/RH inboard and LH/RH outboard ground spoiler synoptics on the upper side of the flap bar. The synoptics only appear when the spoilers are deployed. They disappear when the spoilers are stowed. Spoiler Proximity Sensor Monitoring The integrity of the four spoiler proximity sensors is monitored by a logic arrangement in the PSEU. A failed sensor is reported on the ARINC bus to the EICAS and indicated by: - an amber PROXI GNDSPLR FAIL on the CAS field of the primary EICAS page and - an amber X in place of the associated ground spoiler synoptic on the FLIGHT CONTROL page - an amber X in place of the LH or RH spoiler group on the primary page if both LH or both RH proximity sensors fail. Ground Spoiler not Stowed If a ground spoiler is not stowed when the aircraft is in a weight-off wheels (WOFW) condition an amber GND SPOIL NOT STOW caution message is displayed on the CAS field of the primary EICAS page. The message is generated by a logic equation in the PSEU. The logic is as follows: - any spoiler not stowed and - LH or RH main gear WOFW. Ground Spoiler Control Circuit Armed A blue GND SPOIL ARMED status message on the CAS field of the primary EICAS page indicates when the ground spoilers control circuit is armed. The message is generated by a discrete signal from the GND SPOILER switch/light. The signal line is open circuit when the control circuit is armed (switch/light pressed in) and grounded when the circuit is disarmed. Note that the message is only displayed when two conditions are fulfilled: - the GND SPOILER circuit breaker 1CS is closed (relay 13CS checks the integrity of the circuit breaker) and - the GND SPOILER switch/light 2CS is pressed in. An OFF caption in the GND SPOILER switch/light indicates when the system is disarmed. Effectivity: 328-100 Mod.10

- FOR TRAINING PURPOSES ONLY TM-Flight Controls

Page: 27-123 Issue: 08/95 ETM/ETX

Dornier 328 TRAINING MANUAL LINE /BASE MAINTENANCE

CAS FIELD Indication AMBER

MSG

DORNIER LUFTFAHRT

F/O SYSTEM

AMBER

0° 0°

32

AHRS COPY CAPT REF SYSTEM DATA NEXT FUEL

ND

GND SPOIL NOT STOW

MAIN SYSTEM 1 / 3

NU NH

PROXI GNDSPLR FAIL

800

500 2870 500 2870

0 ° 20

800

- FOR TRAINING PURPOSES ONLY TM-Flight Controls

Effectivity: 328-100 Mod.10

MFD PAGE Fault or Condition Indication synoptic At least one spoiler not stowed and at least one MLG WOW proximity sensor report OFF WHEEL amber X One or more proximity sensors/interface failed on the failed sensor GND SPOILER switch/light 2CS pressed in and circuit breaker 1CS closed. LH outboard/inboard Shows stowed/deployed status of spoilers or failed spoiler synoptic proximity sensors. RH outboard/inboard spoiler synoptic

NP

Fig. 72 Ground Spoilers - EICAS Indications

AILERON

BLUE

Page: 27-124 Issue: 08/95 ETM/ETX

12

OIL TEMP OIL PRSS FF LBS / HR FQ LBS

0 °

ENGINE HYDR FLIGHT CONTROL

TQ

ELEVATOR

2000 FT 0 FPM

RUD

ROLL

FLAP ASYM FLAP CRTL FAIL FLAPS ROLL

TRIM SPEED FAST AIL

97.0 97.0

CAB ALT V/S 80.3 80.3

ND

ITT

NU

E L E V TRIM

80.2

RUDDER

GND SPOIL ARMED

RH LH

80.2

ELEV DISCONNECT RUDDER LIMITED

GND SPOIL NOT STOW PROXI GNDSPLR FAIL GNDSPOIL ARMED END

LH and RH spoiler group synoptic

Honeywell Honeywell

Dornier 328 DORNIER LUFTFAHRT

TRAINING MANUAL LINE /BASE MAINTENANCE

ROLL SPOILERS FUNCTIONAL DESCRIPTION FIN

21CX 22CX

Component LH roll spoiler actuator RH roll spoiler actuator LH roll spoiler position sensor (integral part of LH actuator) RH roll spoiler position sensor (integral part of RH actuator) double shuttle valve Restrictor Relief Valves

Panel

Zone 530 630

Access Door 532-EB 632-EB

250

215-BT, 252-BT, 253-BT

LH and RH Roll Spoiler Actuators

A

B

R 15 R 16 R 17 R 18 R 19

A

R 20

Command Input Rod from Aileron Control Linkage

Hydraulic Pressure Port

B

Hydraulic Return Port

Lockout Device

Actuator Attach Fitting

Piston Rod

Command Input Lever

Bellcrank

Feedback Linkage

Spoiler Drive Rod

Fig. 73 Roll Spoilers Actuator Effectivity: 328-100 Mod.10

- FOR TRAINING PURPOSES ONLY TM-Flight Controls

Page: 27-125 Issue: 08/95 ETM/ETX

Dornier 328 TRAINING MANUAL

DORNIER LUFTFAHRT

LINE /BASE MAINTENANCE

Each spoiler panel is driven by its own hydraulic actuator. The two identical actuators are installed between an attach fitting and bellcrank on the wing rear spar. The following description applies to both actuators. The roll spoiler actuator is a double-acting hydraulic cylinder. The unit has one pressure port with an integral filter and one return port. The actuator piston rod is connected to the roll spoiler by a bellcrank and rod such that the spoiler extends when the piston rod retracts. A position sensor is installed in the actuator piston rod. A spool-type control valve is an integral part of the actuator. The valve spool is positioned by a closed loop system consisting of: - mechanical commands from the command input rod. This rod is connected to an idler lever in the aileron control linkage between ribs 15 and 16 and drives a command input lever. The mechanical connection to the aileron control linkage is designed such that the actuator start to deflect its spoiler until the associated aileron deflection reach 4°. Above 4° aileron deflection the roll spoiler moves proportional to the aileron up to its maximum deflection of 68°. and - mechanical position feedback signals acting through a feedback linkage from the actuator piston rod. The closed loop ensures that spoiler deflection is synchronized to aileron deflection. Roll Spoiler

Feedback Linkage

Aileron Down End Command Stop

LVDT

Input Lever Retract Chamber

End Stop

Aileron Up Command

Piston Pressure Line Filter Return Line

Extend Chamber

Spool Valve

Fig. 74 Roll Spoilers Actuator - Hydraulic Schematic The spool controls the direction of hydraulic fluid flow to the extend and retract chambers of the actuator. Depending on the position of the valve the actuator piston rod either extends or retracts, or is hydraulically locked in a required position. Roll commands act on the command input lever and thus on the control valve. Depending on the direction of the command the valve spool either connects hydraulic pressure to the extend or retract chamber. The movement of the piston rod drives the spoiler in the required direction and is fed back to the valve spool. As the spoiler approaches its required deflection angle the spool closes off the hydraulic supply to the piston chambers. At the required deflection the mechanical signals from the input and feedback levers are nulled. The actuator is now hydraulically locked until the next roll command. Page: 27-126 Issue: 08/95 ETM/ETX

- FOR TRAINING PURPOSES ONLY TM-Flight Controls

Effectivity: 328-100 Mod.10

Dornier 328 DORNIER LUFTFAHRT

TRAINING MANUAL LINE /BASE MAINTENANCE

Fig. 75 Roll Spoiler Actuator Breakout Device The actuator is equipped with a breakout-out device. The device allows the command input lever to move freely after application of an overriding force should the control valve jam. This ensures that the aileron controls are not jammed by a jammed control valve. The movement of the input lever is limited by end stops. The end stop at the aileron down end is adjustable. LH (RH) Roll Spoiler Position Sensor 21CX (22CX) The LH and RH roll spoiler position sensors are installed in their associated actuators. The two sensors are identical. This description applies to both sensors. Each sensor is a three-wire potentiometer whose resistance changes as a function of the actuator position. The sensor is integrated into the piston rod of the actuator and sends a 0 to 10 kΩ variable resistance signal to the EICAS for spoiler position indicating. Double Shuttle Valve

A B A

Electrical Connector Offloading Valve

B Standby Pressure

Standby Return Actuator Return Line

Main System Pressure Main System Return

Actuator Pressure Line

Fig. 76 Roll Spoilers - Double Shuttle Valve Effectivity: 328-100 Mod.10

- FOR TRAINING PURPOSES ONLY TM-Flight Controls

Page: 27-127 Issue: 08/95 ETM/ETX

Dornier 328 TRAINING MANUAL

DORNIER LUFTFAHRT

LINE /BASE MAINTENANCE

The double shuttle valve is installed in the upper fuselage fairing immediately to the left of the aircraft centerline. It connects the primary or standby hydraulic lines of the main hydraulic power system to the roll spoiler actuators. Depending on the status of the priority valve in the main hydraulic system, hydraulic pressure is supplied to either the primary or standby pressure port. Under normal operating conditions hydraulic pressure from the primary subsystem is routed to the actuators. Return fluid from the actuators flows into the hydraulic system primary return line. If the priority valve energizes: - the primary pressure line to the shuttle valve is closed off. - pressure from the standby subsystem is routed through the standby pressure port of the shuttle valve to the roll spoiler actuators. - the primary return line in the shuttle valve is closed off mechanically. - the standby return line in the shuttle valve is opened mechanically. The shuttle valve has an integral offload valve. The valve cracks at 2900 psi and resets at 2755 psi. The valve opens and allows hydraulic fluid to bypass the roll spoiler actuators if: - the priority valve is activated and - the DC standby hydraulic pump is running in the continuous mode and - there is no hydraulic demand from the roll spoiler actuators. The position of the double shuttle valve depends on whether the priority valve is activated or not. A microswitch 9DX in the double shuttle valve is used to indirectly monitor the position of the priority valve.

OPERATION LH Roll Spoiler Actuator

RH Roll Spoiler Actuator

7

Aileron Control (LH)

EICAS

Aileron Control (RH)

Mainsystem Accumulator 10/11

7 Microswitch Double Shuttle Valve

Return MAIN

Return STBY

Supply Priority

Supply Normal Priority Valve 13/11

Hydraulic System (refer to ATA 29)

(Continuous Supply MAIN/STBY)

Pressure Main Pressure Stby Return Main Return Stby Extend Retract Mechanical Linkage Electrical Lines

Fig. 77 Roll Spoiler - Hydraulic Schematic

Page: 27-128 Issue: 08/95 ETM/ETX

- FOR TRAINING PURPOSES ONLY TM-Flight Controls

Effectivity: 328-100 Mod.10

Dornier 328 DORNIER LUFTFAHRT

TRAINING MANUAL LINE /BASE MAINTENANCE

Hydraulic Power Supplies When the main hydraulic system is energized, hydraulic power is available at either: - the primary pressure and return ports of the double shuttle valve if the priority valve is not activated or - the standby pressure and return ports of the double shuttle valve if the priority valve is activated. Roll Spoiler Control When the aileron controls are at neutral: - the control valve spool of each actuator is in a neutral position. Hydraulic pressure is standing by at the control valves. - the actuators are fully extended at their mechanical end stops - the roll spoilers are retracted flush with the upper surface of the wing. Any roll input commands move the actuator input levers through the aileron control linkage. The lever movement is transmitted to the control valve spool. A left roll command: - connects the hydraulic pressure and return lines to the retract and extend chamber respectively of the LH actuator - maintains the pressure and return lines to the extend and retract chambers respectively of the RH actuator. The actuator piston rod of the LH actuator retracts and deflects the LH spoiler into the airflow above the wing. The RH spoiler does not move. A right roll command reverses the above operation. The following example describes the operation of the LH actuator when a LH roll command is received and when the aileron controls are subsequently neutralized. The operation of the RH actuator is similar for a RH roll command. When a left roll command is received from the aileron control linkage the input lever of the LH spoiler actuator moves the control valve spool down. When the LH aileron reaches 4° up deflection the valve connects: - the hydraulic pressure line to the retract chamber of the LH actuator - the hydraulic return line to the extend chamber of the LH actuator. The piston rod starts to retract, deflecting the LH spoiler and moving the feedback linkage. The feedback linkage repositions the valve spool. When the spoiler deflection reaches the angle required for the aileron deflection the mechanical signals from the input and feedback levers are nulled. The spool closes off both chambers of the actuator. Spoiler movement stops and the actuator is hydraulically locked in its current position. When the aileron controls are returned to neutral, the input lever of the LH actuator moves the control valve spool up. The valve connects hydraulic pressure to the extend chamber of the actuator and the hydraulic return line to the retract chamber. The piston rod starts to extend, retracting the LH spoiler and moving the feedback linkage. The feedback linkage repositions the valve spool. When the spoiler has fully retracted the control valve spool closes off both chambers of the actuator. This means that with the aileron controls at neutral: - both spoiler actuators are fully extended and hydraulically locked in this position - both roll spoilers are retracted flush with the upper surface of the wing.

Effectivity: 328-100 Mod.10

- FOR TRAINING PURPOSES ONLY TM-Flight Controls

Page: 27-129 Issue: 08/95 ETM/ETX

Dornier 328 TRAINING MANUAL

DORNIER LUFTFAHRT

LINE /BASE MAINTENANCE

SYSTEM INDICATIONS Spoiler Position Indicating RACK LH

RACK RH

DAU1

DAU2

1 TU

11 TU

SIGN 197 LO

W

SIGN 198 HI

LO

W

HI

REAR SPAR LH

1

2

REAR SPAR RH

1

3

3

W

W EXT

2

EXT

RETR

21CX

RETR

22CX RH POSIT SENSOR

LH POSIT SENSOR

Fig. 78 Roll Spoiler - Electrical Schematic The position of each roll spoiler is registered by a position sensor in each spoiler actuator. The LH sensor 21CX sends a 0 to 10 k Ω variable resistance signal to DAU 1 for processing. The RH sensor 22CX sends an identical signal to DAU 2 for processing. The position of each roll spoiler is displayed EICAS. The roll spoilers are depicted only on the flight control page as a LH and RH blue synoptic on the upper side of the flap bar. The bar serves as the reference line for the flaps, ground spoilers and roll spoilers. The synoptic for each spoiler is only visible when the respective spoiler is deflected above the wing. If a position sensor signal is invalid, the blue synoptic is replaced by an amber X. CAS FIELD Indication MFD PAGE Indication Fault or Condition blue Indicates position of LH LH (RH) Roll Spoiler synoptic (RH) Roll Spoiler Note: If signal from position sensor is invalid, synoptic is replaced by an amber X

Page: 27-130 Issue: 08/95 ETM/ETX

- FOR TRAINING PURPOSES ONLY TM-Flight Controls

Effectivity: 328-100 Mod.10

Dornier 328 DORNIER LUFTFAHRT

TRAINING MANUAL LINE /BASE MAINTENANCE

Honeywell

LH

RH ELEVATOR ELEV DISCONNECT RUDDER LIMITED AIL DISCONNECT

RUDDER AILERON

TRIM

E L E V

AIL RUD ROLL

NU TRIM SPEED FAST

ND ROLL

FLAP ASYM FLAPS 12 0 °

0 °

20 32

SYSTEM 1 / 3 FLIGHT CONTROL

HYDR

ENGINE

FUEL

NEXT

Fig. 79 Roll Spoilers - EICAS Indications

Effectivity: 328-100 Mod.10

- FOR TRAINING PURPOSES ONLY TM-Flight Controls

Page: 27-131 Issue: 08/95 ETM/ETX

Dornier 328 TRAINING MANUAL

DORNIER LUFTFAHRT

LINE /BASE MAINTENANCE

27-70 GUST LOCK AND DAMPER GENERAL The aircraft is equipped with devices which protect the primary flight controls and their adjacent structural parts from wind damage when the aircraft is parked. These devices are: - aileron controls gust lock - elevator controls gust lock - rudder damper. The aileron and elevator gust locks are engaged by a single lever located between the engine power levers on the center pedestal. The rudder and its adjacent structure is protected by a hydraulic damper installed between the rudder and the vertical stabilizer. Aileron and Elevator Control Gust Locks

RH Elevator Cable Tensioner Elevator Gust Lock

LH Aileron Cable Tensioner Aileron Gust Lock

Gust Lock Lever Center Pedestal Push-Pull Cable Cable Distribution Box

Elevator Gust Lock Push-Pull Cable

Aileron Gust Lock Push-Pull Cable

Fig. 80 Gust Lock System - General Arrangement Page: 27-132 Issue: 08/95 ETM/ETX

- FOR TRAINING PURPOSES ONLY TM-Flight Controls

Effectivity: 328-100 Mod.10

Dornier 328 DORNIER LUFTFAHRT

TRAINING MANUAL LINE /BASE MAINTENANCE

The aileron and elevator controls can be locked by gust locks which engage in a control cable tensioner of the associated control run. The aileron gust lock engages in the cable tensioner of the captain's (LH) aileron control run. The elevator gust lock engages in the cable tensioner of the first officer's (RH) elevator control run. The locks are engaged by a gust lock lever located between the engine power levers on the center pedestal. The gust lock lever is connected to the locks by a push-pull cable arrangement and a cable distribution box. Three conditions must be fulfilled before the gust locks can be engaged: - the control wheels must be centered (ailerons neutral) - the control columns must be pushed forward (elevators down) - the engine power levers must be set to less than flight idle (FI). The engine power levers cannot be advanced above the flight idle position when the gust locks are engaged. Rudder Damper When the aircraft is parked a double-acting hydraulic damper prevents wind gusts from swinging the rudder violently on to the end stops. The damper is connected between the vertical stabilizer structure and the rudder.

FUNCTIONAL DESCRIPTION The gust lock and damper system consists of the following components: FIN Component Panel Zone Access Door gust lock lever 210 211-DZW flexible cables 120, 210 211-DZW, 211-LZF, 212-KFZ cable distribution box 120 211-LZF aileron controls gust lock 120 211-LZF elevator controls gust lock 120 212-KFZ rudder damper 310 324-DL Gust Lock Lever, Flexible Cables and Distribution Box The gust lock lever assembly is installed in the center pedestal between the LH and RH engine power levers. The lever moves forward and aft in a quadrant. Each end position of the lever is biased by a spring into a detent at each end of the quadrant. The forward position is marked OFF (unlocked) and the rear position ON (locked). Before the lever can be moved it must be lifted out of its current detent position against the force of the spring. A mechanical interlock is installed between the gust lock lever assembly and the engine power levers. The interlock prevents: - the gust lock lever from being set to the lock position if either engine power lever is set at or higher than flight idle. This ensures that the gust locks cannot be engaged in flight. - the power levers from being advanced above flight idle when the gust locks are engaged. This ensures that the aircraft cannot take off with the flight controls locked. Lever movement is transmitted by a flexible push-pull cable to a cable distribution box. The distribution box is installed below the flight compartment floor and is simply a one-in/two-out adapter for the flexible push-pull cables to the aileron and elevator gust locks.

Effectivity: 328-100 Mod.10

- FOR TRAINING PURPOSES ONLY TM-Flight Controls

Page: 27-133 Issue: 08/95 ETM/ETX

Dornier 328 TRAINING MANUAL

DORNIER LUFTFAHRT

LINE /BASE MAINTENANCE

Aileron Controls Gust Lock The aileron control gust lock is installed below the flight compartment floor. It is in line with and immediately aft of the cable tensioner in the captain's (LH) aileron control run. The unit consists of a housing with an outer and inner plunger. When the aileron controls are unlocked the outer plunger is held in the unlocked position by an unlocking spring. When the gust lock lever in the flight compartment is pulled back to the ON position, the push-pull cable acts on a rack and pinion mechanism and moves the outer and inner plungers forward against the force of the unlocking spring. If the aileron controls are not centered when the gust lock lever is moved to ON, the notch in the cable tensioner quadrant is not aligned with the gust lock. The inner plunger moves forward until it contacts the cable quadrant. The outer plunger continues moving and loads the inner plunger locking spring. If the controls are centered when the gust lock lever is moved to ON, the notch is aligned with the gust lock and the outer plunger acts on the locking spring to drive the inner plunger into the quadrant notch. The aileron controls are now locked. The gust lock is disengaged when the gust lock lever is pushed forward into the OFF position. This action withdraws the outer plunger (assisted by the unlocking spring) together with the inner plunger from the cable tension regulator notch. Elevator Controls Gust Lock 1 2

4 7

A

3

GUST LOCK LEVER IN "OFF" POSITION INNER AND OUTER PLUNGERS WITHDRAWN FROM CONTROL CABLE TENSIONER BY UNLOCKING SPRING. CONTROLS UNLOCKED.

6 5

B GUST LOCK LEVER IN "ON" POSITION. AILERON CONTROLS NOT CENTRALIZED (NOTCH IN CABLE TENSIONER NOT ALIGNED WITH PLUNGER ASSEMBLY). INNER PLUNGER PUSHED BACK INTO OUTER PLUNGER WHEN CABLE TENSIONER IS CONTACTED. CONTROLS WILL LOCK WHEN CONTROLS ARE CENTRALIZED.

C GUST LOCK LEVER IN "ON" POSITION. AILERON CONTROLS CENTRALIZED. INNER PLUNGER PUSHED FORWARD BY LOCKING SPRING INTO CABLE TENSIONER NOTCH. CONTROLS LOCKED.

1 Control Cable Tensioner 2 Outer Plunger 3 Unlocking Spring 4 Rack and Pinion 5 Push-Pull Cable 6 Locking Spring 7 Inner Plunger

Fig. 81 Gust Lock System - Functional Schematic Page: 27-134 Issue: 08/95 ETM/ETX

- FOR TRAINING PURPOSES ONLY TM-Flight Controls

Effectivity: 328-100 Mod.10

Dornier 328 DORNIER LUFTFAHRT

TRAINING MANUAL LINE /BASE MAINTENANCE

The elevator control gust lock is identical to the aileron control gust lock. When engaged by the gust lock lever the plunger engages with a cut-out in the cable tension regulator (of the RH (first officer's) elevator control run. Note that the operation of the elevator gust lock differs slightly from that of the ailerons. The ailerons must be centered to engage the lock; the elevators must be down (control column pushed) before the gust lock can engage. Rudder Damper Damper Attach Fitting on Rudder

A A

Rudder Damper

Accumulator

Indicator Damper Attach Fitting on Vertical Stabilizer Fig. 82 Gust Damper A double-acting hydraulic damper prevents wind gusts from swinging the rudder violently on to the end stops when the aircraft is parked. The aft end of the damper is connected to an attach fitting on the lower leading edge of the rudder just forward and to the right of the rudder hinge axis. The forward end of the damper is connected to an attach fitting on the LH side of the vertical stabilizer rear spar. Integral end stops in the damper serve as stops for the rudder.

Effectivity: 328-100 Mod.10

- FOR TRAINING PURPOSES ONLY TM-Flight Controls

Page: 27-135 Issue: 08/95 ETM/ETX

Dornier 328 TRAINING MANUAL

DORNIER LUFTFAHRT

LINE /BASE MAINTENANCE

The damper is equipped with a spring-loaded accumulator/reservoir which has three functions: - it maintains a general pressure of approximately 7.25 psi in the damper - it holds an adequate fluid volume for damper operation - it accommodates changes in the fluid volume caused by temperature variations. An indicator on the accumulator housing provides an indication of the fluid volume in the accumulator. The indicator protrudes from the accumulator housing and has green and red painted marks on its barrel. The red area is not visible when the fluid volume is adequate. Damping action is an exponential function of rudder deflection speed. The higher the deflection speed the greater the damping action. In flight, little resistance is offered to normal rudder commands from the flight compartment. If, however, the rudder starts to move quickly due to a wind gust, the damping action increases. Maximum damping effect is reached just before the rudder reaches full deflection.

Page: 27-136 Issue: 08/95 ETM/ETX

- FOR TRAINING PURPOSES ONLY TM-Flight Controls

Effectivity: 328-100 Mod.10

Dornier 328 DORNIER LUFTFAHRT

TRAINING MANUAL LINE /BASE MAINTENANCE

INDEX Aft Quadrant Assembly (Rudder) ....................................37 Aileron Controls (Operation) ........................................... 18 Aileron Controls Gust Lock ........................................... 134 Aileron Disconnect Microswitch 7CW ............................18 Aileron Disconnect Unit................................................... 15 Aileron Disconnect Unit Monitoring................................21 Aileron Position Indicating ..............................................21 Aileron Position Transmitters ..........................................18 Aileron Servo Tab ............................................................20 Aileron Trim (Operation) ................................................. 28 Aileron Trim Actuator 4CC..............................................23 Aileron Trim Reset Switch/Light 17CC........................... 25 Aileron Trim/Servo Tab ................................................... 20 AOA Comparison............................................................. 93 AOA Sensor......................................................................84 AOA Sensor Status........................................................... 93 Control Column................................................................58 Current Detector 16CX ....................................................40 Double Shuttle Valve ..................................................... 127 Electrical Control of Rudder Limiter ............................... 43 Elevator Controls (Operation) ..........................................62 Elevator Controls Gust Lock..........................................134 Elevator Disconnect Micro switch 8CW..........................61 Elevator Disconnect Unit ................................................. 61 Elevator Disconnect Unit Monitoring ..............................63 Elevator Position Indicating ............................................. 63 Elevator Position Transmitters ......................................... 62 Elevator Trim Actuator ....................................................66 Elevator Trim Reset Switch/Light....................................68 Flap Actuators ................................................................103 Flap Control Switch 3CG ............................................... 101 Flap Control Unit 2CG ..................................................... 99 Flap Control Valve Manifold ......................................... 102 Flap Operation................................................................107 Flap Position Feedback Sensor ......................................103 Gnd Splr Arm/Disarm Switch/Light ..............................117 Ground Spoiler (Operation)............................................118 Ground Spoiler Actuators............................................... 115 Ground Spoiler Control Circuit Armed..........................123 Ground Spoiler not Stowed ............................................123 Ground Spoiler Position Indicating................................123 Gust Lock Lever ............................................................. 133 Hydraulic Power Supplies (Roll SPLR) ......................... 129 LH and RH Control Wheels ............................................. 13 LH and RH Transition Units ............................................15 Main Aileron Trim Switch 2CC ....................................... 24

Effectivity: 328-100 Mod.10

Main Elevator Trim Switches ..........................................67 Pedal Adjustment Assemblies..........................................35 Pusher Disarm Switch/Light ............................................87 Pusher Reset Switch......................................................... 87 Pusher Status ....................................................................94 Quadrant Assemblies (Rudder) ........................................36 Quadrant Assembly (aileron) ........................................... 16 Quadrant Assembly (Elevator)......................................... 60 Restrictor Relief Valves ................................................. 116 Roll Spoiler Actuators....................................................125 Roll Spoiler Control ....................................................... 129 Roll Spoiler Position Sensor ..........................................127 RUD LIMIT Switch/Light 5CL ....................................... 40 Rudder Controls (Operation) ........................................... 41 Rudder Damper ..............................................................135 Rudder Limiter Actuator 7CL ..........................................38 Rudder Pedal Assemblies................................................. 35 Rudder Position Indicating............................................... 44 Rudder Position Transmitter 19CX..................................40 Rudder Trim (Operation) ................................................. 51 Rudder Trim Actuator 25CC............................................50 Rudder Trim Selection Status ..........................................54 Rudder Trim Switch 22CC............................................... 48 Shaker Status ....................................................................94 Spoiler Position Indicating............................................. 130 Spoiler Proximity Sensor Monitoring ............................123 Spring Tab Lever Assembly............................................. 38 Stall Warning (Operation) ................................................87 Stall Warning Test Switch ............................................... 86 Standby Aileron Trim Switch 12CC ................................25 Standby Elevator Trim Switch ......................................... 68 Stick Pusher......................................................................85 Stick Shaker ..................................................................... 85 Tension Regulator (Elevator)........................................... 59 Tension Regulators (Aileron)........................................... 14 TEST TAB LOCK Switch/Light 2CL ............................. 39 Torque Shaft................................................................... 104 Trim Actuator Status ........................................................79 Trim Control (Operation)................................................. 69 Trim Control Panel 10CC ................................................24 Trim Position Indicating............................................. 54; 76 Trim Speed Mode Indicating ........................................... 77 Trim Synchronization....................................................... 76 Trim Test Switch..............................................................68 Trim Test Switch 50CC ............................................. 25; 49 Valve Manifold (Gnd Splr) ............................................113

- FOR TRAINING PURPOSES ONLY TM-Flight Controls

Page: 27-137 Issue: 08/95 ETM/ETX

Dornier 328 TRAINING MANUAL

DORNIER LUFTFAHRT

LINE /BASE MAINTENANCE

LIST OF ILLUSTRATIONS Fig. 1 Flight Controls - General Arrangement .......................................................................................................................................................8 Fig. 2 Aileron - General Arrangement .................................................................................................................................................................10 Fig. 3 Aileron - Control Wheels to Transition Units............................................................................................................................................13 Fig. 4 Aileron - Cable Tension Regulator............................................................................................................................................................14 Fig. 5 Aileron - Transition Units to the Wingroot................................................................................................................................................15 Fig. 6 Aileron - Disconnect Unit ..........................................................................................................................................................................16 Fig. 7 Aileron - Wing Root to Aileron .................................................................................................................................................................17 Fig. 8 Aileron - Servo Tab....................................................................................................................................................................................20 Fig. 9 Aileron - Trim/Servo Tab ..........................................................................................................................................................................20 Fig. 10 Aileron - EICAS Indications - MFD System Page ..................................................................................................................................22 Fig. 11 Aileron Trim Controls - Trim Control .....................................................................................................................................................24 Fig. 12 Aileron Trim - Electrical Diagram (Sheet 1 of 3)....................................................................................................................................26 Fig. 13 Aileron Trim - Electrical Diagram (Sheet 2 of 3)....................................................................................................................................27 Fig. 14 Aileron Trim - Electrical Diagram (Sheet 3 of 3)....................................................................................................................................28 Fig. 15 Rudder - General Arrangement................................................................................................................................................................32 Fig. 16 Rudder Components - Pedal Assembly ...................................................................................................................................................35 Fig. 17 Rudder - forward Quadrant to Pressure Bulkhead ...................................................................................................................................36 Fig. 18 Rudder - from Pressure Bulkhead to Spring Tab.....................................................................................................................................37 Fig. 19 Spring Tab Lever Assembly.....................................................................................................................................................................38 Fig. 20 Rudder - Limiter Controls........................................................................................................................................................................39 Fig. 21 Rudder Components - Position Transmitter.............................................................................................................................................40 Fig. 22 Rudder Limiter - Electrical Diagram .......................................................................................................................................................42 Fig. 23 Rudder - RMU .........................................................................................................................................................................................46 Fig. 24 Rudder - EICAS .......................................................................................................................................................................................47 Fig. 25 Rudder Trim Controls - Trim Control Panel............................................................................................................................................48 Fig. 26 Rudder - Trim Actuator............................................................................................................................................................................50 Fig. 27 Rudder Trim - Electrical Diagram (Sheet 1 of 2) ....................................................................................................................................51 Fig. 28 Rudder Trim - Electrical Diagram (Sheet 2 of 2) ....................................................................................................................................54 Fig. 29 Elevator - General Arrangement ..............................................................................................................................................................55 Fig. 30 Elevator - Control Column to Pressure Bulkhead....................................................................................................................................58 Fig. 31 Elevator - Pressure Bulkhead to Vertical Stabilizer.................................................................................................................................60 Fig. 32 Elevator Disconnect Unit.........................................................................................................................................................................61 Fig. 33 Elevator Controls - EICAS Indications....................................................................................................................................................64 Fig. 34 Elevator Trim Actuators ..........................................................................................................................................................................66 Fig. 35 Elevator Trim - Controls ..........................................................................................................................................................................67 Fig. 36 Elevator Trim - Electrical Schematic (Sheet 1 of 3)................................................................................................................................70 Fig. 37 Elevator Trim - Electrical Schematic (Sheet 2 of 3)................................................................................................................................71 Fig. 38 Elevator Trim - Electrical Schematic (Sheet 3 of 3)................................................................................................................................72 Fig. 39 Elevator Trim Controls - Position Indicating...........................................................................................................................................76 Fig. 40 Elevator Trim Indications ........................................................................................................................................................................78 Fig. 41 Elevator Trim Indications SYS MAINT page .........................................................................................................................................79 Fig. 42 Stall Warning and Prevention - Diagram.................................................................................................................................................80 Fig. 43 AOA Sensors............................................................................................................................................................................................84 Fig. 44 Stick Shaker .............................................................................................................................................................................................85 Fig. 45 Stick Pusher .............................................................................................................................................................................................85 Fig. 46 Stall Warning and Prevention Controls - RH Miscellaneous Panel.........................................................................................................86 Fig. 47 Stall Warning and Prevention Controls - Pusher Reset Switch ...............................................................................................................87 Fig. 48 Stall Warning and Prevention - Electrical Diagram.................................................................................................................................88 Fig. 49 Stall Warning and Prevention - RMU Indications Indications ................................................................................................................95 Fig. 50 Stall Warning and Prevention - EICAS/PFD Indications........................................................................................................................96 Fig. 51 Flaps - General Arrangement ...................................................................................................................................................................97 Fig. 52 Flap Control Unit .....................................................................................................................................................................................99 Fig. 53 Flap Control Switch ...............................................................................................................................................................................101 Fig. 54 Flap Control Manifold ...........................................................................................................................................................................102 Fig. 55 Flap Actuators ........................................................................................................................................................................................103 Fig. 56 Flaps - Controls - Torque Shaft..............................................................................................................................................................104 Fig. 57 Flaps - Wiring Diagram .........................................................................................................................................................................105 Fig. 58 Flaps - Hydraulic Schematic..................................................................................................................................................................106 Fig. 59 Flaps - Control Valve Manifold - Hydraulic Schematic ........................................................................................................................107 Fig. 60 Flaps - EICAS Indications .....................................................................................................................................................................110 Fig. 61 Spoilers - General Arrangement ............................................................................................................................................................111 Fig. 62 Ground Spoiler Valve Manifold ............................................................................................................................................................113 Fig. 63 Ground Spoilers Valve Manifold - Hydraulic Diagram ........................................................................................................................114 Fig. 64 Ground Spoilers Actuators.....................................................................................................................................................................115 Fig. 65 Ground Spoilers Actuator - Internal View .............................................................................................................................................115

Page: 27-138 Issue: 08/95 ETM/ETX

- FOR TRAINING PURPOSES ONLY TM-Flight Controls

Effectivity: 328-100 Mod.10

Dornier 328 DORNIER LUFTFAHRT

TRAINING MANUAL LINE /BASE MAINTENANCE

Fig. 66 Ground Spoilers Restrictor Relief Valve ...............................................................................................................................................116 Fig. 67 Ground Spoilers Switch/Light 2CS........................................................................................................................................................117 Fig. 68 Ground Spoilers Condition- and Powerlever Microswitches ................................................................................................................117 Fig. 69 Ground Spoiler System - Logic Diagram - EQ #21 and #22 .................................................................................................................119 Fig. 70 Ground Spoiler - Electrical Schematic...................................................................................................................................................120 Fig. 71 Ground Spoiler - Hydraulic Schematic ..................................................................................................................................................121 Fig. 72 Ground Spoilers - EICAS Indications....................................................................................................................................................124 Fig. 73 Roll Spoilers Actuator............................................................................................................................................................................125 Fig. 74 Roll Spoilers Actuator - Hydraulic Schematic.......................................................................................................................................126 Fig. 75 Roll Spoiler Actuator Breakout Device .................................................................................................................................................127 Fig. 76 Roll Spoilers - Double Shuttle Valve.....................................................................................................................................................127 Fig. 77 Roll Spoiler - Hydraulic Schematic .......................................................................................................................................................128 Fig. 78 Roll Spoiler - Electrical Schematic........................................................................................................................................................130 Fig. 79 Roll Spoilers - EICAS Indications .........................................................................................................................................................131 Fig. 80 Gust Lock System - General Arrangement ............................................................................................................................................132 Fig. 81 Gust Lock System - Functional Schematic ............................................................................................................................................134 Fig. 82 Gust Damper ..........................................................................................................................................................................................135

Effectivity: 328-100 Mod.10

- FOR TRAINING PURPOSES ONLY TM-Flight Controls

Page: 27-139 Issue: 08/95 ETM/ETX

Dornier 328

Rudder Trim Tab Spring Tab

Aileron Servo Tab Roll Spoiler Flap Groundspoiler (Option) Elevator TrimTabs

TrimTabs Elevator Groundspoiler (Option) Flap Roll Spoiler Trim/Servo Tab Aileron

Primary Flight Controls Secondary Flight Controls Spoilers

Flight Controls - General Arrangement Effectivity: 328-100 Mod.10

- FOR TRAINING PURPOSES ONLY TA-27-Hcol1.1

Issue: 01/95 D1-TAKL-27-0001

Dornier 328

A

A

Upper Arm Notch for Aileron Gust Lock (LH Side Only)

Compression Springs Sliding Lever Assembly

Input Pulley Compression Springs

Lower Arm

Aileron - Cable Tension Regulator Effectivity: 328-100 Mod.10

- FOR TRAINING PURPOSES ONLY TA-27-Hcol1.2

Issue: 01/95 D1-TAKL-27-0004

Dornier 328

A

A Spring Tab Connection Torsion Bar Connection to Rudder Torsion Bar Spring

Spring Tab Drive Rods

Spring Tab Locking Lever

Rudder Drive Rod (Input)

Actuator Connection to Rudder

Spring Tab Lock Actuator

Torsion Bar Connection to Rudder

Spring Tab Lever Assembly Effectivity: 328-100 Mod.10

- FOR TRAINING PURPOSES ONLY TA-27-Hcol1.5

Issue: 01/95 D1-TAKL-27-0016

Dornier 328 Honeywell

Elevator Trim Status

E L E V

NU

ND

E L E V

NU

E L E V

ND

100% 75% 50% 25% 0% -50% -65%

NU

ND

Rudder Limiter Status LH

RH ELEVATOR ELEV DISCONNECT RUDDER LIMITED ELEV DISCONNECT

RUDDER AILERON

RUDDER LIMITED RUDDER NOT LIMITED RUDDER LIMITED RUDDER NOT LIMITED

Trim Speed Status

Flap and Ground Spoiler Status ROLL

TRIM SPEED FAST TRIM SPEED SLOW TRIM SPEED FAST TRIM SPEED SLOW

ROLL

TRIM

FLAPS

E L E V

AIL 12 0 °

20

0 °

RUD

32

ROLL

ROLL

ND ROLL

Aileron and Elevator Disconnect Status

FLAPS

FLAPS

ELEVATOR

12

12 20

TRIM SPEED FAST

FLAP ASYM FLAP CRTL FAIL

ROLL

9 °

NU

14 °

9 °

18 °

20

32

AILERON

32

ROLL

SYSTEM 1 / 3

ROLL

FLIGHT CONTROL

FLAPS

HYDR

ENGINE

FUEL

NEXT

12 32 °

20

32 °

32

Flight Control System Page - Indications Effectivity: 328-100 Mod.10

- FOR TRAINING PURPOSES ONLY-

Issue: 01/95 D1-TAHA-27-0002

er

ni

or

D

End of ATA Chapter 27 Flight Controls