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Dornier 328DORNIER LUFTFAHRT TRAINING MANUAL
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TM-Flight Controls
ATA CHAPTER 27 FLIGHT CONTROLS
27-00 GENERAL 8GENERAL
................................................................................................................................................
8
Primary Flight
Controls.........................................................................................................................
9Secondary Flight
Controls.....................................................................................................................
9Spoilers..................................................................................................................................................
9Stall Warning and
Prevention................................................................................................................
9Gust Lock
..............................................................................................................................................
9
27-10 AILERON CONTROLS AND TRIM 10General
................................................................................................................................................
10Aileron
Controls..................................................................................................................................
11Aileron
Trim........................................................................................................................................
11
INTERFACE TO OTHER SYSTEMS
...................................................................................................
11Roll Spoiler
System.............................................................................................................................
11Indicating/Recording
Systems.............................................................................................................
11Autoflight
............................................................................................................................................
11
AILERON CONTROLS 12FUNCTIONAL DESCRIPTION
............................................................................................................
12
LH and RH Control Wheels
................................................................................................................
13Control
Cables.....................................................................................................................................
13Pulleys
.................................................................................................................................................
14LH and RH Cable Tension
Regulators................................................................................................
14LH and RH Transition Units
...............................................................................................................
15Aileron Disconnect
Unit......................................................................................................................
15Quadrant Assembly
.............................................................................................................................
16Levers and Bellcranks
.........................................................................................................................
17Control
Rods........................................................................................................................................
17Aileron Disconnect Microswitch
7CW...............................................................................................
18LH and RH Aileron Position Transmitters 5CX and
4CX..................................................................
18
OPERATION(refer to Fig. 3, Fig. 5, Fig.
7)...........................................................................................
18Power
Supplies....................................................................................................................................
18Aileron
Controls..................................................................................................................................
18Flight Compartment
Controls..............................................................................................................
18Flight Compartment to Upper Center Fuselage Control
Run..............................................................
18Regulation of Cable Tension in Fuselage Control
Run.......................................................................
18Aileron Controls from Transition Units to Wing
Roots......................................................................
19Aileron Controls from Wing Root to Aileron
.....................................................................................
19
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RH Aileron Servo Tab
.........................................................................................................................20LH
Aileron Trim/Servo Tab
................................................................................................................20
SYSTEM
INDICATIONS.......................................................................................................................21Aileron
Position Indicating
..................................................................................................................21Aileron
Disconnect Unit Monitoring
...................................................................................................21
AILERON TRIM 23FUNCTIONAL
DESCRIPTION.............................................................................................................23
Aileron Trim Actuator 4CC (refer to Fig. 9)
.......................................................................................23Trim
Control Panel 10CC
....................................................................................................................24Main
Aileron Trim Switch
2CC...........................................................................................................24Standby
Aileron Trim Switch
12CC....................................................................................................25Aileron
Trim Reset Switch/Light 17CC
..............................................................................................25Trim
Test Switch 50CC
.......................................................................................................................25
OPERATION...........................................................................................................................................25Power
Supplies.....................................................................................................................................25System
Power-Up
................................................................................................................................25Aileron
Trim
........................................................................................................................................28
SYSTEM
INDICATIONS.......................................................................................................................31Standby
Trim/Main Lockout Circuit
Status.........................................................................................31
27-20 RUDDER CONTROLS AND TRIM
32GENERAL...............................................................................................................................................32
Rudder Controls
...................................................................................................................................32Rudder
Trim.........................................................................................................................................33
INTERFACE TO OTHER
SYSTEMS....................................................................................................33Navigation
System...............................................................................................................................33Communications
..................................................................................................................................33Autoflight.............................................................................................................................................33
RUDDER CONTROLS 34FUNCTIONAL
DESCRIPTION.............................................................................................................34
LH and RH Rudder Pedal
Assemblies.................................................................................................35LH
and RH Pedal Adjustment
Assemblies..........................................................................................35LH
and RH Forward Quadrant Assemblies
.........................................................................................36Pulleys..................................................................................................................................................36Control
Rods
........................................................................................................................................36Levers
and
Bellcranks..........................................................................................................................37Pressure
Bulkhead Fairleads
................................................................................................................37Aft
Quadrant Assembly
.......................................................................................................................37Spring
Tab Lever Assembly
................................................................................................................38Rudder
Limiter Actuator
7CL..............................................................................................................38TEST
TAB LOCK Switch/Light 2CL
.................................................................................................39RUD
LIMIT Switch/Light
5CL...........................................................................................................40Current
Detector
16CX........................................................................................................................40Rudder
Position Transmitter
19CX......................................................................................................40
OPERATION...........................................................................................................................................40Power
Supplies.....................................................................................................................................40
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Dornier 328DORNIER LUFTFAHRT TRAINING MANUAL
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TM-Flight Controls
System
Power-Up................................................................................................................................
41Rudder Controls
..................................................................................................................................
41Electrical Control of Rudder Limiter
..................................................................................................
43
SYSTEM INDICATIONS
......................................................................................................................
44Rudder Position
Indicating..................................................................................................................
44Rudder Limiter
Monitoring.................................................................................................................
45
RUDDER TRIM 48FUNCTIONAL DESCRIPTION
............................................................................................................
48
Rudder Trim Switch
22CC..................................................................................................................
48Trim Test Switch
50CC.......................................................................................................................
49Rudder Trim Actuator
25CC...............................................................................................................
50
OPERATION
..........................................................................................................................................
50Power
Supplies....................................................................................................................................
50System
Power-Up................................................................................................................................
50Rudder Trim (refer to Fig.
27).............................................................................................................
51
SYSTEM INDICATIONS
......................................................................................................................
53T rim Position
Indicating.....................................................................................................................
54Rudder Trim Selection
Status..............................................................................................................
54
27-30 ELEVATOR CONTROLS AND TRIM 55GENERAL
..............................................................................................................................................
55
Elevator
Controls.................................................................................................................................
56Elevator Trim
......................................................................................................................................
56
INTERFACE TO OTHER SYSTEMS
...................................................................................................
56Indicating/Recording
Systems.............................................................................................................
56Navigation System
..............................................................................................................................
56Auto Flight
System..............................................................................................................................
56
ELEVATOR CONTROLS 57FUNCTIONAL DESCRIPTION
............................................................................................................
57
LH and RH Control Column
...............................................................................................................
58LH and RH Cable Tension Regulator
.................................................................................................
59Control
Cables.....................................................................................................................................
59Pulleys
.................................................................................................................................................
59Control
Rods........................................................................................................................................
59Levers and Bell cranks
........................................................................................................................
59Pressure Bulkhead Fairleads
...............................................................................................................
59Quadrant Assembly
.............................................................................................................................
60Elevator Disconnect Unit
....................................................................................................................
61Elevator Disconnect Micro switch
8CW.............................................................................................
61LH and RH Elevator Position Transmitters 25CX and
26CX.............................................................
62
OPERATION
..........................................................................................................................................
62Power
Supplies....................................................................................................................................
62Elevator
Controls.................................................................................................................................
62Flight Compartment to Vertical Stabilizer Control Run
.....................................................................
62LH and RH Elevator
Tab.....................................................................................................................
63
SYSTEM INDICATIONS
......................................................................................................................
63
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Elevator Position
Indicating.................................................................................................................63Elevator
Disconnect Unit
Monitoring..................................................................................................63
ELEVATOR TRIM 65FUNCTIONAL
DESCRIPTION.............................................................................................................65
LH (RH) Elevator Trim Actuator 53CC (52CC)
.................................................................................66Main
Elevator Trim Switches
33CC....................................................................................................67Standby
Elevator Trim Switch
63CC...................................................................................................68Elevator
Trim Reset Switch/Light
69CC.............................................................................................68Trim
Test Switch 50CC
.......................................................................................................................68
OPERATION...........................................................................................................................................68Power
Supplies.....................................................................................................................................68System
Power-Up
................................................................................................................................68Trim
Control
........................................................................................................................................69Main
Trim
Control...............................................................................................................................69Standby
Trim Control and Main Trim
Lockout...................................................................................69Actuator
Speed
Control........................................................................................................................72Main
Trim Runaway
Override.............................................................................................................73Runaway
Override Test
.......................................................................................................................73Main
Trim Circuit Fault Protection
.....................................................................................................74Standby
Trim Circuit Fault
Protection.................................................................................................74Auto-Trim
............................................................................................................................................75
SYSTEM
INDICATIONS.......................................................................................................................75Trim
Position Indicating
......................................................................................................................76Trim
Synchronization
..........................................................................................................................76Trim
Speed Mode Indicating
...............................................................................................................77Standby
Trim/Main Lockout Circuit
Status.........................................................................................79Trim
Actuator
Status............................................................................................................................79
27-33 STALL WARNING AND PREVENTION
80GENERAL...............................................................................................................................................80
Angle of Attack
Information................................................................................................................81Stall
Warning Computing
....................................................................................................................81Stick
Shaker
.........................................................................................................................................81Stick
Pusher..........................................................................................................................................81System
Inhibition on Ground and below 100 ft Radar altitude
...........................................................81Stick
Pusher
Disarm.............................................................................................................................82Autopilot
Disengagement
....................................................................................................................82System
Test..........................................................................................................................................82System
Monitoring and
Indicating.......................................................................................................82
INTERFACE TO OTHER
SYSTEMS....................................................................................................83Auto
Flight System (Chapter
22).........................................................................................................83Communications
(Chapter
23).............................................................................................................83
FUNCTIONAL
DESCRIPTION.............................................................................................................83LH
(RH) AOA Sensor 2WH
(12WH)..................................................................................................84LH
(RH) Stick Shaker
6WH................................................................................................................85Stick
Pusher
25WH..............................................................................................................................85LH
(RH) Stall Warning Test Switch 7WH
(17WH)............................................................................86Pusher
Disarm Switch/Light 22WH
....................................................................................................87Pusher
Reset Switch
24WH.................................................................................................................87
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Dornier 328DORNIER LUFTFAHRT TRAINING MANUAL
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Effectivity: - FOR TRAINING PURPOSES ONLY - Page: 27-5328-100
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TM-Flight Controls
OPERATION
..........................................................................................................................................
87Power
Supplies....................................................................................................................................
87System
Power-Up................................................................................................................................
87Power-Up
Test.....................................................................................................................................
89System Test
.........................................................................................................................................
89Stall Warning
Computing....................................................................................................................
90Stick Shaker
Operation........................................................................................................................
91Stick Pusher
Operation........................................................................................................................
91
SYSTEM INDICATIONS
......................................................................................................................
93General
................................................................................................................................................
93AOA Sensor
Status..............................................................................................................................
93AOA
Comparison................................................................................................................................
93Shaker Status
.......................................................................................................................................
94Pusher Status
.......................................................................................................................................
94
27-50 FLAPS 97GENERAL
..............................................................................................................................................
97INTERFACE TO OTHER SYSTEMS
...................................................................................................
98
Hydraulic Power (Chapter 29)
............................................................................................................
98Landing Gear (Chapter
32)..................................................................................................................
98Navigation (Chapter
34)......................................................................................................................
98Indicating/Recording Systems (Chapter 31)
.......................................................................................
98
FUNCTIONAL DESCRIPTION
............................................................................................................
98Flap Control Unit
2CG........................................................................................................................
99Flap Control Switch
3CG..................................................................................................................
101Flap Control Valve Manifold
4CG....................................................................................................
102LH and RH Flap
Actuators................................................................................................................
103LH (RH) Flap Position Feedback Sensor 5CG (6CG)
......................................................................
103Torque
Shaft......................................................................................................................................
104Relay
8CG.........................................................................................................................................
104
OPERATION
........................................................................................................................................
104Electrical Power
Supplies..................................................................................................................
104Hydraulic Power
Supplies.................................................................................................................
104System
Power-Up..............................................................................................................................
106Power-Up
Test...................................................................................................................................
106Flap
Operation...................................................................................................................................
107
SYSTEM INDICATIONS
....................................................................................................................
108General
..............................................................................................................................................
108System Operating Status Monitoring
................................................................................................
109System Reset
.....................................................................................................................................
109Flap Position
Indicating.....................................................................................................................
109
27-60 SPOILERS 111GENERAL
............................................................................................................................................
111
Ground Spoilers
(optional)................................................................................................................
112Roll
Spoilers......................................................................................................................................
112Indications
.........................................................................................................................................
112
INTERFACE TO OTHER SYSTEMS
.................................................................................................
112Hydraulic Power (Chapter 29)
..........................................................................................................
112
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Dornier 328TRAINING MANUAL DORNIER LUFTFAHRTLINE /BASE
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GROUND SPOILERS (OPTIONAL) 113FUNCTIONAL
DESCRIPTION...........................................................................................................113
Valve Manifold 10CS
........................................................................................................................113Ground
Spoiler Actuators
..................................................................................................................115Restrictor
Relief
Valves.....................................................................................................................116Ground
Spoiler Arm/Disarm Switch/Light
2CS................................................................................117Microswitches
3CS/5CS/7CS/8CS
....................................................................................................117Proximity
Sensors 3CW/5CW (refer to Fig.
64)................................................................................118
OPERATION.........................................................................................................................................118Electrical
Power Supplies
..................................................................................................................118Hydraulic
Power
Supplies..................................................................................................................118System
Power-Up
..............................................................................................................................118System
Pre-Takeoff
Test....................................................................................................................118Spoiler
Inflight Inhibition
..................................................................................................................119Landing
Gear Circuit
.........................................................................................................................119Power
Lever
Circuit...........................................................................................................................119Spoilers
Disarm/Arm
.........................................................................................................................122Auto-Deployment
on Landing
...........................................................................................................122Auto-Deploy
on Aborted
Takeoff......................................................................................................122Auto-Stow..........................................................................................................................................122Spoiler
Lockout During Ground
Manoeuvring..................................................................................122
SYSTEM
INDICATIONS.....................................................................................................................123Ground
Spoiler Position
Indicating....................................................................................................123Spoiler
Proximity Sensor
Monitoring................................................................................................123Ground
Spoiler not
Stowed................................................................................................................123Ground
Spoiler Control Circuit Armed
.............................................................................................123
ROLL SPOILERS 125FUNCTIONAL
DESCRIPTION...........................................................................................................125
LH and RH Roll Spoiler
Actuators....................................................................................................125LH
(RH) Roll Spoiler Position Sensor 21CX
(22CX).......................................................................127Double
Shuttle
Valve.........................................................................................................................127
OPERATION.........................................................................................................................................128Hydraulic
Power
Supplies..................................................................................................................129Roll
Spoiler
Control...........................................................................................................................129
SYSTEM
INDICATIONS.....................................................................................................................130Spoiler
Position
Indicating.................................................................................................................130
27-70 GUST LOCK AND DAMPER
132GENERAL.............................................................................................................................................132
Aileron and Elevator Control Gust
Locks..........................................................................................132Rudder
Damper..................................................................................................................................133
FUNCTIONAL
DESCRIPTION...........................................................................................................133Gust
Lock Lever, Flexible Cables and Distribution
Box...................................................................133Aileron
Controls Gust
Lock...............................................................................................................134Elevator
Controls Gust
Lock..............................................................................................................134Rudder
Damper..................................................................................................................................135
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Dornier 328DORNIER LUFTFAHRT TRAINING MANUAL
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TM-Flight Controls
INDEX 137
LIST OF ILLUSTRATIONS 138
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Dornier 328TRAINING MANUAL DORNIER LUFTFAHRTLINE /BASE
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TM-Flight Controls
27-00 GENERAL
GENERAL
RudderTrim Tab
Spring Tab
Aileron
Servo Tab
Flap
Flap
Groundspoiler(Option)
Roll Spoiler
Trim/Servo Tab
Aileron
Elevator
TrimTabs
Roll Spoiler
TrimTabs
Elevator
Groundspoiler(Option)
Fig. 1 Flight Controls - General Arrangement
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Mod.10 Issue: 08/95 ETM/ETX
TM-Flight Controls
This chapter provides information on those units and components
which furnish a means of manuallycontrolling the flight attitude of
the aircraft. The chapter is divided into sections containing
detailedinformation 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 controlsurfaces are moved
manually by linkage systems consisting of cables, pulleys, levers
and rods. Dualcontrols are installed for the three primary
controls. The elevator and aileron control runs are eachequipped
with a disconnect unit. This allows the captain's and first
officer's controls to be disconnectedfrom each other should one
control run become jammed. The rudder pedals drive a Flettner-type
springtab on the trailing edge of the rudder. At airspeeds up to
160 knots the rudder is deflected by aerodynamicservo reaction from
the tab. The rudder itself is not connected to the rudder pedals
directly except atairspeeds 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 isachieved by a single actuator driving a tab on
the left aileron. Pitch trim is achieved by a tab on eachelevator,
each tab having its own actuator. Yaw trim is achieved by a single
actuator driving a tab on thetrailing 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 theailerons. 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 ruddercontrol system is equipped
with a hydraulic gust damper which prevents damage to the structure
when theaircraft is parked in gusty conditions
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Dornier 328TRAINING MANUAL DORNIER LUFTFAHRTLINE /BASE
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TM-Flight Controls
27-10 AILERON CONTROLS AND TRIM
General
RH Ail
eron P
osition
Transm
itter
Aileron
Discon
nect Un
it
LH Aile
ron Po
sition
Transm
itter
Control
Wheels
Cable T
ension
Regulat
ors
EICAS
position
status
position
30
25
30
25
Servo T
ab
Trim/Se
rvo Ta
b
Fig. 2 Aileron - General ArrangementThis section provides
information on that portion of the flight control system which
controls the aileronsand the aileron trim tab. Also included are
the aileron and trim tab position indicating systems and theaileron
disconnect indicating system.The section is divided into
subsections containing detailed information on the following
aileron and tabsubsystems:
- Aileron Controls- Aileron Trim
-
Dornier 328DORNIER LUFTFAHRT TRAINING MANUAL
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TM-Flight Controls
Aileron Controls
The aircraft is controlled about the roll axis by a conventional
aileron control system. Two ailerons areinstalled, one on the
outboard trailing edge of each wing. The ailerons are manually
operated by dualcontrol 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 and25 down. The captain's and first officer's aileron
control runs are joined by a disconnect unit. This unitallows the
two control runs to be separated by the application of higher than
normal input forces shouldone 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 ofthe left
aileron. The tab is driven by an electrically powered linear
actuator installed in the trailing edge ofthe wing. Due to the
actuator attachment geometry the tab also functions as a servo tab
to provideaerodynamic assistance to flight crew roll commands.The
actuator is powered by two separate DC motors and controlled by
either a main or a standby ailerontrim switch. Override circuits
are provided to protect against a trim runaway. Test facilities are
providedfor 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 aircraftis flying under automatic
control. Refer to (Chapter 22 - AUTO FLIGHT) for further
details.
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Dornier 328TRAINING MANUAL DORNIER LUFTFAHRTLINE /BASE
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TM-Flight Controls
AILERON CONTROLS
FUNCTIONAL DESCRIPTION
The aileron control subsystem consists of the following
components:FIN Component Panel Zone Access Door
LH and RH control wheels 210 211-FZF212-EZF
LH and RH cable tension regulators 120 211-LFZ212-KFZ
LH and RH fairlead brackets 120 221-MFZ222-EFZ
control cables 120130210
various+
furnishingpulleys 220 panels
control rods 220530630
various
levers and bellcranks 530630
various
LH and RH transition units 220 251-bt252-bt
furnishingpanels
aileron disconnect unit 250 251-btquadrant assembly 252-bt
7CW aileron disconnect microswitch4CX RH aileron position
transmitter 632 632-JB5CX LH aileron position transmitter 532
532-JB
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Dornier 328DORNIER LUFTFAHRT TRAINING MANUAL
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LH and RH Control Wheels
A
A
Double Pulley
Transition Unit
Turnbuckle
Pulley Cable Tension Regulator
Control Cable
Fig. 3 Aileron - Control Wheels to Transition UnitsThe control
wheels are of the horn type and are mounted with splined shafts on
the top of the controlcolumns. Wheel movement is transmitted to the
aileron control cable tension regulators beneath the
flightcompartment floor by cables and pulleys.
Control Cables
The aileron control cables transmit the movement of the control
wheels to the tension regulators and fromthere to the transition
units located on the passenger compartment roof between frames 25
and 26. Thecables are 7 x 19 flexible steel wire ropes made from
corrosion resistant steel and have a nominaldiameter of 3.2 mm
(0.13 in.).The LH and RH aileron control runs each consist of eight
separate cable sections. Each control wheel isconnected to its
associated tension regulator by four sections. Each tension
regulator is connected to itsassociated transition unit by a
further four sections. Cable sections are joined by turnbuckles
andterminated by swaged end fittings.
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Dornier 328TRAINING MANUAL DORNIER LUFTFAHRTLINE /BASE
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Pulleys
The control cables are guided by pulleys equipped with cable
guards. The pulleys are made of a phenolicmaterial and run in
sealed ball bearings.A double pulley connected to the control wheel
at the top of each control column and two single pulleysat the base
of the control column guide the cable run from the control wheel to
the associated tensionregulator. The cable run from each tension
regulator to the associated transition unit is guided by a totalof
fifteen pulleys.
LH and RH Cable Tension Regulators
Notch for Aileron Gust Lock
(LH Side Only)
Input Pulley
Lower Arm
Compression Springs
Sliding Lever Assembly
Compression Springs
Upper Arm
Fig. 4 Aileron - Cable Tension RegulatorThe tension of the
control cables installed in the flight control system must be
maintained within specifiedtolerances. Temperature effects cause
the cables and the aircraft structure to expand and contract.
Theexpansion coefficient of the aluminium structure is higher than
that of the steel cables. This means thatthe cables tighten at high
ambient temperatures and slacken at low ambient temperatures.
Control cabletension regulators compensate for these effects.A
control cable tension regulator is installed below the flight
compartment floor in the captain's and firstofficer's aileron
control runs. The two tension regulators are identical in
operation. Each regulatorautomatically regulates the tension of the
control cables between the regulator output quadrant and
theassociated cable termination quadrants in the upper center
fuselage. The tension regulator consists of ashaft to which an
input pulley and a spring compensator mechanism are firmly
attached. An outputquadrant with separate upper and lower sections
is installed on but not attached to the shaft. The twosections are
connected to each other by the compensator mechanism but are
otherwise free to rotate onthe shaft. The compensator mechanism
consists of two compression springs which act on a sliding
leverassembly. The sliding lever is connected to the upper and
lower sections of the output quadrant by twoarms. If the control
cables become tight the cables pull the two sections of the output
quadrant towardsthe shaft against the force of the springs. This
effectively shortens the length of the cable run. If the
cablesbecome 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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Dornier 328DORNIER LUFTFAHRT TRAINING MANUAL
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TM-Flight Controls
LH and RH Transition Units
The transition units are installed in the roof section of the
passenger compartment between frames 25 and26. 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 inthe fairing between the fuselage and the wing. The
quadrant and the lever are mounted on a commonshaft . The shaft
bearing is installed in the passenger compartment roof and acts as
the pressure seal. Thequadrant accepts the control inputs from the
fuselage control cables and the lever transmits the movementinto
the control rod run in the wing.
Aileron Disconnect Unit
A
A
Rod to RH Aileron Control
LH/RH Interconnect Rod
Autopilot Roll Servo Actuator
Cable Quadrant
Lever Assembly
Rod to LH Aileron
Lever Assy Drive Rod
Quadrant Output Lever
Roll Disconnect Unit
Quadrant Assembly
Fig. 5 Aileron - Transition Units to the Wingroot
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TM-Flight Controls
Output to RH Aileron
Transverse Rod to LH Control Circuit
Rear Half
Command Input from RH Control Circuit
Front Half
Fig. 6 Aileron - Disconnect UnitThe captain's and first
officer's aileron control cable runs are routed completely
separately along the leftand right sides of the fuselage
respectively. They are joined by an interconnect rod in the wing
centersection and an aileron disconnect unit located in the
trailing edge section of the RH wing root. Undernormal
circumstances the movement of one control wheel moves both ailerons
and the other controlwheel. Should one aileron control become
jammed the two control circuits can be separated by theapplication
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 haslevers for two push-pull rods. The lower lever is for
the command input from the RH aileron controlcircuit. The upper
lever is for the output rod to the RH aileron. The rear half has a
single lever for theinterconnect rod that joins the LH and RH
control circuits. Under normal operating conditions the twohalves
of the unit are firmly engaged and move together as a single unit.
Should one of the aileron controlcircuits jam, the two halves can
be disconnected from each other by the application of a higher
thannormal force at a control wheel. The disconnect force is 39 daN
(87.7 lb). The applied force causes thecam to override the spring
force and move out of its detent. The two halves of the unit are
nowdisengaged, effectively isolating the jammed control circuit. In
this situation the captain's control circuit isconnected 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,
thedisconnect unit can only be reset on the ground.The unit has an
integral microswitch 7CW which is operated if the disconnect unit
is activated. Theswitch sends a signal to EICAS
Quadrant AssemblyThe quadrant assembly is installed in the
trailing edge section of the LH wing root at rib 2. The
assemblyconsists of three levers and a cable quadrant all mounted
on a common shaft. The lower lever accepts thecontrol inputs from
the LH transition unit. The forward upper lever is the drive lever
for the LH aileroncontrol run. The aft upper lever forms the
connection point for the LH/RH aileron control interconnectrod. 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
andlower sections of the cable quadrant. Because the control cable
has no turnbuckles, the arms can beadjusted with screws for setting
the cable tension.
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TM-Flight Controls
Levers and Bellcranks
R 3
R 4
R 5
R 6
R 7
R 8
R 9
R 10
R 11
R 12
R 12
R 13
R 14
R 15
R 16
R 17
R 18
R 19R 20
R 0
A1
7
2
3
4
5
LH SIDE SHOWN, RH SIDE SIMILAR.
6
A
Fig. 7 Aileron - Wing Root to AileronThe 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 isformed by a series of
aluminium push-pull control rods. Another rod forms the
interconnection betweenthe LH (captain's) and RH (first officer's)
aileron controls. The Servo-tab on each aileron is alsocontrolled
by rods. Rod ends are either of the clevis or eye type. Eye type
rod ends are equipped with self-aligning sealed ball bearings.
1. Interconnection Rod2. Quadrant Assembly3. Position
Transducer4. Aileron Drive Rod5. Bellcrank6. Rollspoiler Drive
Rod7. Disconnect Unit
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TM-Flight Controls
Aileron Disconnect Microswitch 7CW
A microswitch located in the aileron disconnect unit monitors
the status of the unit and sends a discretesignal to the EICAS when
the disconnect unit is activated. The switch contacts are connected
to groundunder 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 theirassociated wing rear spar
between ribs 17 and 18. Each transmitter is driven by a short rod
connected tothe outboard idler lever in the aileron control run.
The transmitters are identical 0 to 10 k W three-wirepotentiometers
whose resistance changes as a function of the aileron position.
They send a variableresistance 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 systemis provided by the
EICAS
Aileron Controls
Note:The LH (captain's) and RH (first officer's) aileron
controls from the flight compartment to the uppercenter fuselage
are similar. The operation of the LH side is described. Differences
for the RH side arecovered 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 regulatorlocated at frame 9. The
tension of this short cable run can be adjusted by turnbuckles. A
notch is providedin the aft portion of the LH cable tension
regulator between the upper and lower quadrants. The ailerongust
lock engages with this notch to lock the aileron controls for gust
protection when the aircraft isparked.
Flight Compartment to Upper Center Fuselage Control Run
From the cable tension regulator, the control movement is
continued aft below the flight and passengercompartment floor by
control cables and pulleys. The cables pass through guides in some
frames underthe floor. Cable fairleads equipped with small pulleys
are used to guide the cables through the machinedpart of frame 24.
The cable run is virtually straight as far as a point between
frames 25 and 26. At thispoint the cables are routed outboard and
then upwards. The cable run now passes between the fuselageskin and
the passenger compartment furnishing panels and terminates at a
transition unit on the passengercompartment 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 passengercompartment roof is
approximately 9.5 m (31 ft) long. Approximately 6.5 m (21 ft) of
this is a virtuallystraight horizontal run. The expansion
coefficient of the aluminium structure is higher than that of
thesteel cables. This means that the cables tighten at high ambient
temperatures and slacken at low ambienttemperatures. The control
cable tension regulators compensate for these effects.
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Dornier 328DORNIER LUFTFAHRT TRAINING MANUAL
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Mod.10 Issue: 08/95 ETM/ETX
TM-Flight Controls
The shaft of the tension regulator (and thus the regulator
mechanism) is rotated by flight crew commandsacting on the input
pulley. The movement is transmitted to the upper and lower sections
of the outputquadrant by the arms of the regulator mechanism. The
control cable is a two-part cable, each part beingattached to its
associated quadrant section by a nipple. The two sections of the
output quadrant are thusallowed to move in relation to each
other.Under high ambient temperature conditions the control cables
tighten. The cable tension pulls on the twosections of the output
quadrant and moves them in opposite directions on the shaft. The
movement actsthrough the arms and pulls the sliding lever assembly
towards the shaft against the force of twocompression springs. This
effectively shortens the length of the cable run. The sliding
motion continuesuntil 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 outputquadrant 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 fuselagethrough a pressure tight
fitting. A lever is fixed to the shaft out-side the fuselage. A
push-pull rodconnected 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 autopilotroll 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 tothe aileron disconnect unit (at RH wing station Y 600
(rib 2). This rod forms the interconnection betweenthe LH
(captain's) and RH (first officer's) aileron controls. The forward
rod is the first of six push-pullrods which form the control run
from the wing root to the aileron drive bellcrank at LH wing
station Y7345.4 (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 thequadrant assembly in the
LH wing root to the LH aileron drive bellcrank. The six rods are
routed alongthe aft face of the rear spar. A further push-pull rod
is connected to the idler lever located on the rear sparbetween
ribs 15 and 16. This is the drive rod for the LH roll spoiler
actuator. A short push-pull rodconnects the aileron drive bellcrank
to the aileron control horn. The horn is attached to the underside
ofthe aileron.The aileron position transmitter is driven by the
outboard idler lever and indicates the aileron position onthe
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 LHwing control run.
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Dornier 328TRAINING MANUAL DORNIER LUFTFAHRTLINE /BASE
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TM-Flight Controls
RH Aileron Servo Tab
A
BB
Servo Tab Push-Pull Rods
Servo Tab Push-Pull Rods
Connection to Wing Trailing Edge
Reduction Lever in AileronLeading Edge
Connection to Servo Tab
Fig. 8 Aileron - Servo TabA Flettner-type servo tab is installed
on the inboard trailing edge of the RH aileron. The tab is
connectedby four short push-pull rods and a reduction lever to the
structure of the wing trailing edge atapproximately station Y 6880
(just outboard of rib 18). The reduction lever is installed in the
leading edgeof the aileron. The tab moves in the opposite direction
to the aileron to provide aerodynamic assistancefor reduced pilot
effort.
LH Aileron Trim/Servo Tab
A
Connection to Trim Tab
Aileron Trim Actuator
Connection to Wing Trailing Edge
Trim Tab Drive Rods
Reduction Lever in AileronLeading Edge
Fig. 9 Aileron - Trim/Servo Tab
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Dornier 328DORNIER LUFTFAHRT TRAINING MANUAL
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Mod.10 Issue: 08/95 ETM/ETX
TM-Flight Controls
An aileron trim tab is installed on the inboard trailing edge of
the LH aileron. The dual-shaft trim actuatoris installed in the
trailing edge of the wing. The actuator drives the tab through a
reduction lever installedin 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 itsfunction as a trim
tab.
SYSTEM INDICATIONS
Certain components of the aileron control system send signals to
EICAS. The signals are sent to dataacquisition units (DAUs) 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 FLIGHTCONTROL page. The caution message
is displayed on the CAS field of the primary EICAS page and onthe
FLIGHT CONTROL page.
Aileron Position Indicating
An aileron position transmitter is installed for each aileron.
Each transmitter is a three-wire potentiometerwhose resistance
changes as a function of the aileron position. The LH transmitter
sends resistance signalto DAU 1 in the EICAS system for processing.
The RH transmitter sends an identical signal DAU 2. Theresistance
values correspond to the following aileron deflections:
- 0.5 kW corresponds to an aileron up deflection of -30- 5 kW
corresponds to aileron neutral- 9.5 kW 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 theEICAS. If the transmitter signal is
invalid, the blue synoptic is replaced by an amber X. Under
normaloperating conditions the LH and RH aileron synoptics are
joined by a white bar. The bar changes toamber 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 discreteground or open signal to DAU
1 for processing. The signal line is connected to ground under
normaloperating conditions and open circuit if the disconnect unit
is activated. If the captain's and first officer'saileron control
runs are disconnected:
- an amber AIL DISCONNECT caution message is displayed on the
CAS field of the primary EICASpage and on the FLIGHT CONTROL
page
- on the FLIGHT CONTROL page the white bar which connects the LH
and RH aileron synopticschanges to amber.
CAS FIELD Indication MFD PAGE Indication Fault or
ConditionAMBER
AIL DISCONNECTAMBER
AIL DISCONNECTAMBER Bar
Aileron disconnect unit activated
- blueLH (RH) aileron synoptic
Invalid synoptic replaced byan amber X RH aileron similar
Indicates position of Aileron
white pointer against whiteaileron scale
white pointer against whiteaileron scale
Indicates aileron trim settings
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MAINTENANCE
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TM-Flight Controls
RUDDER LIMITED
TRIM SPEED FAST
FLAP ASYM
ELEV DISCONNECT
Honeywell
SYSTEM 1 / 3HYDR ENGINE FUEL NEXTFLIGHT
CONTROL
ROLL ROLL
0 0
NU
ND
AIL
RUD
ELEV
TRIM
RUDDERAILERON
ELEVATORLH RH
FLAPS
1220
AIL DISCONNECT
32
Fig. 10 Aileron - EICAS Indications - MFD System Page
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Dornier 328DORNIER LUFTFAHRT TRAINING MANUAL
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Effectivity: - FOR TRAINING PURPOSES ONLY - Page: 27-23328-100
Mod.10 Issue: 08/95 ETM/ETX
TM-Flight Controls
AILERON TRIM
FUNCTIONAL DESCRIPTION
The aileron trim subsystem consists of the following
components:FIN Component Panel Zone Access Door
1CC/11CC circuit breaker 12VE 2101CX circuit breaker 18VE 2102CC
main aileron trim switch 10CC 2104CC aileron trim actuator 532
532-JB5CC trim runaway interlock relay LH 23VE 2106CC trim runaway
override relay LH 23VE 2107CC trim runaway override relay RH 23VE
2108CC trim runaway interlock relay RH 23VE 2109CC aileron trim
test relay 23VE 21010CC trim control panel 21012CC standby aileron
trim switch 10CC 21014CC15CC
diodes 10CC 210
16CC standby aileron trim control relay 23VE 21017CC aileron
trim reset switch/light 10CC 21050CC trim test switch 30VE LH
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 (justoutboard of rib 18). The actuator
has two separate DC motors (main and standby). The main motor
iscontrolled by the main trim switch 2CC and the standby motor by
the standby trim switch 12CC. Onlyone motor can operate at a time.
An external electrical lockout circuit prevents the main motor
fromoperating when the standby motor is active. Internal limit
switches for both motors stop actuatormovement before the
mechanical limits are reached.The rotary output of each motor is
converted in a reduction gearbox to a dual shaft linear output.
Totalshaft travel between the electrical limits is 26.8 mm (1.05
in.). The twin shafts of the actuator areconnected to a reduction
lever arrangement in the leading edge of the aileron. Two push-pull
rodsconnected 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
indicatingsignal to the EICAS.
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Dornier 328TRAINING MANUAL DORNIER LUFTFAHRTLINE /BASE
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TM-Flight Controls
Trim Control Panel 10CC
RESET
ELEV
STBY
TRIM
UP
RH
RUD
LH
AILSTBY
OFF
PRESSTO
RESET
STBYELEV
UP
RHLH AILRHLH AIL
DN
NH OVSPENGLH
LHFITEST
OFF
1
TEST
PLA FI
PLA FI
ENGRH
SSEC DISABLE
MADC 2
TRIM TEST
Fig. 11 Aileron Trim Controls - Trim ControlThe trim control
panel is installed in the aft LH section of the center pedestal.
The panel interfaces withthe 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 switchis labelled LH AIL RH
and contains two three-position center biased rocker switches. Both
rockerswitches must be activated together to operate the aileron
trim actuator. The two switches have a total ofeight sets of
contacts (four per switch). Each contact of one rocker switch is
connected in either series orparallel with a contact in the other
switch, making a total of four contact pairs.
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Dornier 328DORNIER LUFTFAHRT TRAINING MANUAL
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Effectivity: - FOR TRAINING PURPOSES ONLY - Page: 27-25328-100
Mod.10 Issue: 08/95 ETM/ETX
TM-Flight Controls
Standby Aileron Trim Switch 12CC
The standby aileron trim switch is installed in the forward RH
section of the trim control panel. Theswitch is labelled LH AIL RH
and is identical to the main trim switch 2CC. It controls the
standby motorof the aileron trim actuator. A lockout circuit is
activated when the standby trim switch is operated. Thiscircuit
disables the main motor of the aileron trim actuator. The main
motor remains disabled until thereset 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 lockoutcircuit remains active even
after the trim operation has been completed. The main trim motor
can be re-enabled by pressing an aileron trim reset switch/light.
The switch is labelled PRESS TO RESET and isinstalled in the trim
control panel between the two aileron trim switches . A white STBY
AIL annunciatorin the front face of the switch comes on to indicate
when the standby trim circuit - and thus the lockoutcircuit - 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 forwardLH section
of the center pedestal. The switch is labelled TRIM TEST and is
used to test the trim runawayoverride 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 pressthe main aileron trim
switch to LH and then RH. If the runaway override circuits of the
actuator mainmotor are serviceable, the actuator will operate in
the reverse direction to that commanded. When the testswitch 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 No.
trim actuator main motor control andpower circuit
ESSENTIAL BUS 3PP AIL TRIM 1CC
trim actuator standby control and powercircuit
BUS 1 2PP STBY AIL TRIM 11CC
trim actuator position indicating circuit AC BUS 4XP AIL TRIM
IND 1CX
System Power-Up
The trim tab control and indicating circuits are energized when
28 VDC and 26 VAC are applied to theaircraft bus system.
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Dornier 328TRAINING MANUAL DORNIER LUFTFAHRTLINE /BASE
MAINTENANCE
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TM-Flight Controls
10 11 124 5 6 7 8 91 2 3
210
C O T
3
C O T 5
C O T1
4
6C O T
9
C O T 8
11
AILTRIMRH
B8
B6
A8
A6
2CCAILTRIMLH
B2
B4
A2
A4
2CC4CC
B
FILTER
M
R
LH RH
NORMAL OPERATIONBr
AILTRIMACTR
AILTRIMLH2CC
A1
A3
B1
B3
ESS BUS-3PP
3A 1CCAIL TRIM
A5
A72CC
AILTRIMRH B5
B7
A2
A1A38CC
A2
A1A39CC
B2
B1B3
C2
C1C3
8CC
5CCX1
X26CC
X1
X2
A1
7CCA3
A2
A3
6CCA1
A2
A1
A2
A3 B1
B2
B3
A2
A1A3
7CCX1
X2
B2
B1B3
8CCX1
X2
(9) (11) (5) (4) 5CCB2
B1B3
C2
C1C39CC 5CC (3)
16CC(18)
7
9CCX1
X2
A1
A2A3
TRIMMTEST
50CC
G3G2
50CCG1
C = closesO = opensT = change over(transition)
5
74 8
6
3
1 2
A
5
74 8
6
3
1 2
B
Electrical Schematic for:
Main Trim Switch 2CC andStby Trim Switch 12CC
Fig. 12 Aileron Trim - Electrical Diagram (Sheet 1 of 3)
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Dornier 328DORNIER LUFTFAHRT TRAINING MANUAL
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Effectivity: - FOR TRAINING PURPOSES ONLY - Page: 27-27328-100
Mod.10 Issue: 08/95 ETM/ETX
TM-Flight Controls
13 14 15 16 17 18 19 20
56
C O T
141518
AILTRIMSTBYRH
B8
B6
A8
A6
12CC
4CC
B
FILTER
M
R
LH RH
STBY OPERATION
16CCX1
X2
E
16CCE1
E2
E3
17CC
A2
A3
A1
RESET
2LF
STBYAIL
2CX
6CX3CX
LAMPTEST
D/N
A5
A712CC
AILTRIMSTBYRH B5
B7
16CCD1 D3
D2
C1 C3
C2
B2
B4
A2
A4
AILTRIMSTBYLH
12CC
AILTRIMSTBYLH
12CC
A1
A3
B1
B3
BUS 1-2PP
3A 11CCSTBYAILTRIM
Fig. 13 Aileron Trim - Electrical Diagram (Sheet 2 of 3)
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TM-Flight Controls
21 22 23 24 25
26VAC-BUS-6XP
1A 1CXAIL TRIM
IND
4CC
R1
R2
ACTR POSIT SENSOR
S3BK/W
S1S2
L W H
SIGN 41
1TU
H L
SIGN 34
DAU 1
AIL POSIT POTILH
CWCCW
W
5CX
R
H W L
SIGN 609
11TU DAU 2
AIL POSIT POTIRH
CWCCW
W
4CX
26 27
Fig. 14 Aileron Trim - Electrical Diagram (Sheet 3 of 3)
Aileron Trim
Main Trim CircuitThe main motor of the aileron trim actuator is
controlled by the main aileron trim switch 2CC. Ifboth 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:
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TM-Flight Controls
- 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 isreleased or until the LH
internal limit switch operates. The operation sequence is similar
in reversewhen right wing down is commanded.
Main Trim Runaway Override CircuitsAn 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 stoppedand reversed by
instinctive operation of the main trim switch in the opposite
direction to therunaway.The following example describes the
operation of the circuit in the event of a runaway towards leftwing
down.Relay 5CC is the LH trim runaway interlock relay. It is
energized when the main trim switch is heldto the LH position. If
contacts A1/A3 and B1/B3 of the main trim switch 2CC stick closed
when theswitch is released, the trim actuator will run uncommanded
towards left wing down and relay 5CCwill 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 ailerontrim position indicator on
the EICAS. The runaway can be stopped and reversed by holding the
maintrim 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 trimmotor
with a ground connection. 28 VDC is now supplied to the right wing
down side of the motorthrough:
- 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 theRH internal limit switch
operates. If the fault still exists on the main trim switch when
the switch isreleased, the actuator will again run uncommanded
towards left wing down. The main motor can bedisabled 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.
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Dornier 328TRAINING MANUAL DORNIER LUFTFAHRTLINE /BASE
MAINTENANCE
Page: 27-30 - FOR TRAINING PURPOSES ONLY - Effectivity:Issue:
08/95 ETM/ETX 328-100 Mod.10
TM-Flight Controls
Runaway Override Test CircuitThe TRIM TEST push switch 50CC is
used to test the trim runaway override circuits of thefollowing
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 thenpress the main aileron trim
switch 2CC to LH and then RH. If the runaway override circuits of
theactuator main motor are serviceable, the actuator will operate
in the reverse direction to thatcommanded. 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 themain aileron trim switch held to
LH.When the TRIM TEST switch is held pressed the trim test relay
9CC energizes. Relay 9CC has twosets of contacts, one for the LH
circuit and one for the RH. If the main trim switch is now held to
theL position, relay 5CC energizes. The RH trim runaway override
relay 7CC energizes through thefollowing 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 maintrim motor and replace it with a ground
connection. The actuator stops. 28 VDC is now supplied tothe 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) untileither:
- the TRIM TEST switch 50CC is releasedor
- the main aileron trim switch 2CC is releasedor
- 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 CircuitIf for any reason the aileron
main trim circuit is unserviceable, it can be disabled. This is
done bymomentarily pressing the standby trim switch 12CC to either
LH or RH. The standby aileron trimcontrol relay 16CC energizes and
self-latches through its contacts E2/E1. The ground circuit for
therelay 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
trimmotor. Contacts A and B disable the left and right wing down
sides of the main trim motor . Themain 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 standbyaileron trim subsystem
is active. The annunciator is controlled by contacts E2/E1 of relay
16CC .
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Dornier 328DORNIER LUFTFAHRT TRAINING MANUAL
LINE /BASE MAINTENANCE
Effectivity: - FOR TRAINING PURPOSES ONLY - Page: 27-31328-100
Mod.10 Issue: 08/95 ETM/ETX
TM-Flight Controls
Standby Trim CircuitThe 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 circuitand 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 LHinternal limit switch operates.
The operation sequence is similar in reverse when right wing down
iscommanded.
SYSTEM INDICATIONS
The aileron trim actuator has an integral synchro-type position
transmitter. The transmitter sends anaileron 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 andFLIGHT CONTROL pages of
the EICAS.
CAS FIELD Indication MFD PAGEIndication
Fault or Condition
white pointer against whiteaileron scale
Scale has white tic marksevery 25%.
white pointer againstwhite aileron scaleScale has white ticmarks
every 25%.
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 standbytrim circuit and the
main trim lockout circuit are active.
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Dornier 328TRAINING MANUAL DORNIER LUFTFAHRTLINE /BASE
MAINTENANCE
Page: 27-32 - FOR TRAINING PURPOSES ONLY - Effectivity:Issue:
08/95 ETM/ETX 328-100 Mod.10
TM-Flight Controls
27-20 RUDDER CONTROLS AND TRIM
GENERAL
Rudder Pedal Assemblies
Spring Tab Lock Actuator
Autopilot Servo
Spring Tab Drive Mechanism
Rudder Trim Actuator
Quadrant Assembly
Rudder Position Transmitter
Cable Quadrants
-24 20
Fig. 15 Rudder - General ArrangementThis section provides
information on that portion of the flight control system which
controls the positionand movement of the rudder and the rudder trim
tab. Also included are the indicating systems for therudder
position, the rudder limiter status and the trim tab position.The
section is divided into subsections containing detailed information
on the following rudder and tabsubsystems:
- Rudder Controls- Rudder Trim
Rudder Controls
The aircraft is controlled about the yaw axis by a rudder
control system. At airspeeds below 160 knots thedual rudder pedal
assemblies are connected to a Flettner-type tab on the lower
trailing edge of the rudderthrough a torsion bar and lever
assembly. Movement of the rudder pedals drives the tab in the
oppositesense to the yaw command and aerodynamic effects from the
tab move the rudder in the commandedsense.
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Dornier 328DORNIER LUFTFAHRT TRAINING MANUAL
LINE /BASE MAINTENANCE
Effectivity: - FOR TRAINING PURPOSES ONLY - Page: 27-33328-100
Mod.10 Issue: 08/95 ETM/ETX
TM-Flight Controls
At speeds above 160 knots the lever assembly is locked by an
actuator controlled by micro air datacomputers 1 and 2. The pedal
assemblies are then effectively connected directly to the rudder
and flightcrew commands are not assisted by the tab. This limits
the rudder deflection at high airspeeds andprevents structural
overload conditions. The tab can be unlocked and the limiter
actuator disabled bymanually 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
compartmentthrough 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 rudderimmediately above the
spring tab. The tab is driven by an electrically powered linear
actuator installed inthe 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
theoverride 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 controlcircuit.
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 SystemThe
following functions of the rudder and tab subsystem are indicated
on EICAS:
- the position of the