FLIGHT CONTROLS
CH 27
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ATA 27 FLIGHT CONTROLS TABLE OF CONTENTS
INTRODUCTION ................................................................................... 4
ACTUATORS AND SERVOS ................................................................ 6
HYDRAULIC SHUTOFF VALVES - CONTROL AND INDICATION........8
HYDRAULIC SHUTOFF VALVES ...................................................... 10
CONTROL SYSTEM ELECTRONIC UNITS - (CSEU)........................ 12
CSEU BLOCK DIAGRAM.................................................................... 14
CONTROL SYSTEM ELECTRONIC UNITS POWER DISTRIBUTION 16
AILERON CONTROLS AND INDICATIONS ....................................... 18
AILERON COMPONENT LOCATIONS............................................... 20
AILERON MANUAL CONTROL .......................................................... 22
AILERON TRIM CONTROL................................................................. 24
AILERON DROOP MECHANISM........................................................ 26
AILERON OUTBOARD LOCKOUT ..................................................... 28
AILERON POSITION INDICATING SYSTEM ..................................... 30
SPOILER CONTROLS AND INDICATORS...........................................32
SPEEDBRAKE MECHANISM AND LVDT UNITS............................... 34
SPOILERS AND SPEEDBRAKES - OVERVIEW................................ 36
AUTO SPEEDBRAKE ACTUATOR..................................................... 38
AUTO SPEEDBRAKE SYSTEM.......................................................... 40
AUTO SPEEDBRAKE ELECTRICAL SCHEMATIC ............................ 42
RUDDER CONTROLS AND INDICATORS......................................... 44
RUDDER YAW CONTROL.................................................................. 46
RUDDER SYSTEM.............................................................................. 48
RUDDER TRIM SYSTEM.................................................................... 50
RATIO CHANGER OPERATION......................................................... 52
RUDDER RATIO CHANGER MECHANISM..........................................54
YAW DAMPER SYSTEM .................................................................... 56
ELEVATOR GENERAL DESCRIPTION................................................58
ELEVATOR CONTROL SCHEMATIC................................................. 60
ELEVATOR FEEL FORCE SYSTEM .................................................. 62
STALL WARNING SYSTEM COMPONENTS..................................... 64
STALL WARNING COMPUTER............................................................66
STALL WARNING BITE.........................................................................68
STABILIZER CONTROLS AND INDICATORS ................................... 70
STABILIZER TRIM BLOCK DIAGRAM ............................................... 72
STABILIZER TRIM CONTROL MODULE (STCM).............................. 74
STABILIZER HYDRAULIC CUTOUT SWITCHES .............................. 76
STAB TRIM LIMIT SWITCH AND POS. TRANSMITTER MODULES. 78
HIGH LIFT DEVICES........................................................................... 80
FLAP CONTROL AND INDICATION ................................................... 82
FLAPS GENERAL DESCRIPTION........................................................84
FLAP PRIMARY DRIVE CONTROL .................................................... 86
FLAP POWER DRIVE UNIT (PDU) ..................................................... 88
FLAP PDU COMPONENTS................................................................. 90
FLAP/SLAT SHUTOFF VALVE MODULE ........................................... 92
FLAP ROTARY ACTUATOR ............................................................... 94
INBOARD FLAPS ................................................................................. 96
OUTBOARD FLAPS ............................................................................. 98
FLAP / SLAT ELECTRONIC UNIT (FSEU) ........................................ 100
FLAP SYSTEM INTERFACE.............................................................. 102
FLAP HYDRAULIC OPERATION ....................................................... 104
FLAP LOAD RELIEF MECHANISM.................................................... 106
FLAP LOAD RELIEF SYSTEM........................................................... 108
FLAP ALTERNATE DRIVE CONTROL .............................................. 110
FLAP POSITION TRANSMITTER ..................................................... 112
FLAP POSITION TRANSMITTER ASSEMBLIES .............................. 114
FLAP POSITION INDICATION ........................................................... 116
FLAP/STAB POSITION MODULES (FSPM) ...................................... 118
FLAP ASYMMETRY PROTECTION SYSTEM....................................120
LEADING EDGE SLATS.................................................................... 122
SLAT POWER DRIVE UNITS (PDU)................................................. 124
KRUEGER SEAL FLAP DRIVE SYSTEM (INBD SLATS)................. 126
INBOARD SLAT DRIVE AND TRACKS ............................................ 128
OUTBOARD SLAT DRIVE AND TRACKS ........................................ 130
SLAT FSEU/PSEU INTERFACE ....................................................... 132
SLAT SYSTEM INTERFACE............................................................. 134
SLAT HYDRAULIC OPERATION ...................................................... 136
SLAT ALTERNATE DRIVE CONTROL ............................................. 138
SLAT SENSOR/TARGET POSITIONS.............................................. 140
SLAT PDU TRANSMITTERS ............................................................ 142
SLAT PSEU BITE .............................................................................. 144
STUDENT NOTES:
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FLIGHT CONTROL INTRODUCTION
General
Flight control systems can be grouped as primary or secondary control systems.
Primary flight controls are those which are used to provide continuous control of
the airplane about the pitch, roll and yaw axes, and include the aileron, rudder,
elevator and spoiler systems. Secondary flight controls are those used
intermittently, to modify the basic aerodynamic configuration of the airplane to
improve its performance at a particular flight condition, and include the leading
edge slat, trailing edge flap, spoilers (when used as air or ground speedbrakes)
and stabilizer trim systems.
Wing Systems
The aileron and spoiler systems provide control about the roll axis through
differential operation (up on one wing and down on the other). The leading
edge slat, trailing edge flap and spoiler (when raised symmetrically on both
wings) systems modify wing lift characteristics.
Tail Systems
The elevator system provides control about the pitch axis and stabilizer position
is varied to trim the airplane about the pitch axis. The rudder provides control
about the yaw axis.
RUDDER
ROLL
AXIS
YAW
AXIS
OUTBD
AILERON
PITCH
AXIS
ELEVATOR
INBD AILERON
SPOILERS
(6 EACH SIDE)
STABILIZER
INBOARD FLAP
OUTBOARD FLAP
LEADING EDGE SLATS
(6 EACH SIDE)
FLIGHT CONTROL INTRODUCTION
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FLIGHT CONTROL ACTUATORS AND SERVOS
General
All primary flight controls are driven by hydraulically operated Power Control
Actuators (PCA) with no manual reversion capability. A total of twenty nine
actuators are employed with eight in the aileron system, twelve in the spoiler
system, six in the elevator system and three in the rudder system. In addition
the aileron system has three additional Lateral Central Control Actuators
(LCCA) to power the wing cable systems to the PCA located at the aileron.
Nine autopilot servos, three on each axis, provide triple redundancy required for
category three autoland capability. The aileron servos are part of the LCCA
with the three elevator and three rudder servos as individual units.
Two Yaw Damper Servos (YDS) provide rudder inputs independent of pilot or
autoflight control inputs.
The trailing edge flaps and leading edge slats, which are secondary flight
controls, are operated by power drive units (PDU). The PDU will rotate torque
tubes to power two rotary actuators (mechanical) at each control surface.
Hydraulic Distribution
Three hydraulic systems operate power control actuators in the primary flight
control systems which include the aileron, elevator, rudder and spoiler systems.
The secondary flight control systems are powered by a combination of one, two,
or three hydraulic systems.
Roll (LCCA), pitch (elevator) and yaw (rollout guidance) autopilot actuators are
powered by each of the three hydraulic systems. The ram air turbine pump in
the center hydraulic system can power all center hydraulic system flight controls
except the flap and slat systems.
The stabilizer trim system is normally powered by the left and center hydraulic
systems. A Power Transfer Unit (PTU) can provide right hydraulic system
power to operate the left stabilizer trim system.
An elevator feel computer and yaw damper servo are powered by the left
hydraulic system with identical components powered by the center hydraulic
system.
The rudder ratio changer, the leading edge slats and trailing edge flap systems
are each powered by one hydraulic system.
FLIGHT CONTROL ACTUATORS AND SERVOS
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HYDRAULIC SHUTOFF VALVES - CONTROL AND INDICATION
General
Six control switches located on the HYD/GEN FIELD CONT panel (P61). The
switches are intended for ground use only and are normally on.
These alternate action switches contain white ON lights that are illuminated
whenever the switch is in the open position.
Each control switch is guarded by a cover, which will not close, in the switch off
position (switch protruding).
The shutoff valve position is monitored by switch lights and EICAS messages.
An amber light in the lower half of the control switch illuminates as soon as the
valve moves from the fully open position.
An amber EICAS advisory message appears on the upper display when a
shutoff valve is not open (i.e. L WING HYD VAL). If more than one valve is not
open, EICAS will display a single FLT. CONT VALS message.
HYDRAULIC SHUTOFF VALVES - CONTROL AND INDICATION
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FLIGHT CONTROL HYDRAULIC SHUTOFF VALVES
Description
Six identical shutoff valves are used to isolate flight control components from
their hydraulic source during ground maintenance. Hydraulic shutoff valves
control pressure to all flight control systems except the flaps, slats and stabilizer
systems.
An electrical actuator and a rotary selector valve are joined together to form a
single LRU. The actuator has a single electrical connector, and position decals
to show the actual valve position. The rotary selector valve has three fluid ports
and an override handle. The override permits power-off manual operation, and
it also functions as a visual indicator.
The two-position shutoff valve (open - position 1; closed - position 2) is normally
open.
Shutoff Valve Locations
Left and right wing shutoff valves are mounted on a bracket between the rear
wing spar and the spoiler beam adjacent to the inboard corner of the inboard
ailerons.
The center wing shutoff valve is located on the aft bulkhead in the left wheel
well.
Tail shutoff valves are located in the stabilizer compartment. Access is through
a service door in the bottom of the compartment, just forward of the stabilizer
jackscrew.
Dispatch Deviation
• Flight Control Shutoff Valves INOP Lights: Verify that the related flight
control shutoff valve is open.
• Pressurize the hydraulic system related to inop valve/light and operate the
flight control surface, while observing the flight control deflections on
EICAS.
Note:
It is possible for valve to fail closed with override and position lever
indicating open. Visual and flight control operational checks must
be accomplished.
FLIGHT CONTROL HYDRAULIC SHUTOFF VALVES
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CONTROL SYSTEM ELECTRONIC UNITS - (CSEU)
General
Two identical, left (E1-1) and right (E2-1), CSEU are located in the main
equipment center. Each CSEU contains six modules:
• Power Supply Modules (PSM) (2)
• Spoiler Control Modules (SCM) (3)
• Yaw Damper/Stabilizer Module (YSM) (2)
CONTROL SYSTEM ELECTRONIC UNITS - (CSEU)
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CSEU BLOCK DIAGRAM
Components
Each CSEU has four flight control modules and two power supply modules.
The CSEU interfaces with other primary airplane systems to provide the
calculation and control functions for these functions:
•
•
•
•
•
Yaw damping
Stabilizer trim
Aileron lockout
Rudder ratio changer
Spoiler deployment
Inputs
Three air/ground systems discrete inputs allow the CSEU to perform control
functions and ground test function.
Three ADIRU provide airspeed inputs for aileron lock-out and rudder ratio
changer control.
Each CSEU module receives hydraulic pressure switch signals from the
hydraulic systems. These inputs are used for control of fault annunciation and
reset fault latches.
The CSEU receives flaps position inputs from three Flap Stabilizer Position
Modules (FSPM), located in the P50 card file. Flaps positions are used for
spoiler scheduling and stabilizer trim control.
Auto pilot system(s) controls the stabilizer trim function via the CSEU.
Speed brake lever and control wheel positions allow the CSEU to control spoiler
panels.
Manual electric stabilizer trim switches send electrical signals through the
CSEU for control and indication.
CSEU
Two PSMs supply power to these components:
• Three Spoiler Control Modules (SCM)
• Yaw Damper/Stabilizer Trim Module (YSM)
• Excitation for LVDT and RVDT for the above LRUs
Outputs
The following items are controlled by the CSEU:
•
•
•
•
•
Twelve spoiler PCA
Two stabilizer trim control modules
Two aileron lock-out actuators
Two yaw damper servos
The rudder ratio changer actuator
AIR
GND
AIR GROUND
SYSTEMS (3)
SPOILER PCA
AIR SPEED
ADIRU (3)
PSM (2)
(P50)
HYD PRESS
SWITCHES
FLAP POSITIONS
STAB TRIM
CONTROL MODULE
FSPM (3)
200
270
+2300
17000
AUTO PILOT SYSTEMS (3)
AILERON
LOCKOUT ACTUATOR
SCM (3)
YAW DAMPER
SERVOS
SPEED BRAKE
LEVER
YSM
CONTROL WHEEL
CSEU (2)
CSEU BLOCK DIAGRAM
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RATIO
CHANGER
ACTUATOR
RUDDER MECHANISM
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CONTROL SYSTEM ELECTRONIC UNITS POWER
DISTRIBUTION
Description
The left CSEU power supply modules (PSM) get power from the standby ac/dc
buses. The right CSEU PSM get power from the left and right buses. The dual
PSM in each CSEU send out 26v ac, +5 vdc and +/-15 vdc to the four operating
modules.
26v ac goes to the yaw damper/stabilizer trim module (YSM), and spoiler control
modules (SCM) for reference power and for excitation power for the control
wheel and speedbrake lever RVDT and LVDT.
The spoiler actuator LVDT receive excitation power from the PSM through the
SCM. PSM 1 in each CSEU supplies 26v ac power with automatic failure
changeover to PSM 2. +/- 15v dc goes to all the modules for card and
electrohydraulic servo valve operation. 28v dc goes to all the modules for
solenoid valve, actuator, relay, fault monitor and fault ball control.
115V AC
STBY BUS
POWER
SUPPLY
MODULE 1L
28V DC
STBY BUS
26V AC
|15V DC
+5V DC
CAPT WHL
RVDTS (3)
28V DC
STBY BUS
26V AC
L YAW
DAMP/
STAB
TRIM
MODULE
SCM 3L
RUDDER RATIO
CHANGER LVDT
CSEU (E1-1 SHELF)
28V DC
LEFT BUS
SPD BRK
LVDTS (3)
SCM 2L
POWER
|15V DC
SUPPLY
MODULE 2L
+5V DC
28V DC
STBY BUS
SPOIL
CONT
MODULE
1L
SPOILER PWR
CONT ACT LVDTS
POWER SUPPLY INTERNAL WIRING SAME AS E1-1 SHELF
MODULE 1R
28V DC
RIGHT BUS
28V DC
LEFT BUS
115V AC
RIGHT BUS
26V AC
28V DC
POWER SUPPLY
MODULE 2R
26V AC
CSEU (E2-1 SHELF)
P11
SPOILER PWR
CONT UNIT LVDTS
CONTROL SYSTEM ELECTRONIC UNITS POWER DISTRIBUTION
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YAW DMPR
SERVO LVDT
(2)
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AILERON CONTROLS AND INDICATIONS
Control
Dual control wheels provide manual control of the aileron system. The wheels
are mechanically connected by overrides and normally operate together. The
ailerons are controlled during autoflight by switches on the mode control panel.
Trim switches on the control stand control an electric actuator which operates
the aileron system.
Indication
Aileron position is shown by pointers on the EICAS Status page. There is a trim
indicator placard on top of each control column. Aileron lockout system faults
are shown by an EICAS advisory message, an amber light and an EICAS
maintenance message.
AILERON CONTROLS AND INDICATION
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AILERON COMPONENT LOCATIONS
Ailerons
Forward Quadrants
Inboard aileron located on trailing edge of both wings behind engine struts.
Outboard aileron located on both wings outboard section, trailing edge.
Located under the flight compartment floor just aft of the base of the control
columns. They incorporate bus rod, drum position transducers (spoiler lateral
control RVDT’s), override and lost motion assemblies, and a control wheel force
transducer (autopilot).
Primary And Backup Cable System
Located under passenger cabin floor along side of the fuselage. Primary along
left side to wheel well and backup along right side to right wheel well.
Droop Mechanism
Located on left and right wing spar, inboard corner inboard ailerons (2 total).
Provides inboard aileron droop with first 15 degrees of flap extension for
increased lift during take-off and approach.
Outboard Aileron Lockout Mechanism
Left Wheel Well Components
Located on left and right wing rear spar, inboard corner outboard aileron (2
total). Locks-out outboard ailerons at cruise speeds. Locks-out as a function of
airspeed and altitude (Mach Number).
Consist of feel-centering and trim mechanism, left LCCA torque tube, two
LCCA’s (one above the other), and the left LCCA output quadrant.
Position Transmitters
Right Wheel Well Components
Located on the outboard corner of the Inboard ailerons and on outboard section
of each outboard aileron (four total). Input is to EICAS status page only.
Consists of right wheel well quadrant, right LCCA torque tube/aileron control
override mechanism, right LCCA, the right LCCA output quadrant and right
aileron control output quadrant.
Aileron and Spoiler Hydraulic Shutoff Valves
Wing Cable System
Routed along left and right wing rear spars from LCCA output quadrants to
outboard aileron lockout mechanism.
Power Control Actuators (PCA)
Consists of two PCA located in the mid-section, leading edge of each aileron
(eight total). Each PCA is powered by one hydraulic system and has NO
electronic input.
Located adjacent to inboard edge of left and right inboard ailerons, (L & R HYD),
and on aft bulkhead left wheel well (C HYD). Three shutoff valves total for
lateral control. These are designed for ground/maintenance use only.
AILERON COMPONENT LOCATIONS
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AILERON MANUAL CONTROL
Control Wheels
Outboard Aileron Lockout Mechanism
The captain and first officer's yokes each drive respective control column
cables. Rotation of either control wheel drives the primary (left) cable system.
The outboard aileron lockout mechanism disables (fairs) the outboard ailerons
at cruise speeds; controlled by YSM. The electric actuator re-positions linkage
which mechanically nulls the outboard aileron PCA inputs.
Forward/Aft Quadrants
Override
The forward quadrants control operation of the primary (left) and backup (right)
cable systems. They contain input and drive drums, bus cranks, position
transducers (lateral control spoiler RVDT’s), force transducer (control wheel
steering), and lost motion and load limiter assemblies.
There are seven override mechanisms in the aileron control system. Three
overrides function to separate the primary and backup control systems in event
of a jam in either system. Four overrides, two in each wing, function to separate
inboard and outboard aileron control inputs.
The aft quadrants provide an interface between the primary and backup cable
system and the wing cable system. The left aft quadrant incorporates a "feel
and centering" mechanism for cable system feel force and an electric trim
actuator. Both quadrants have control input rods to Lateral Central Control
Actuators (LCCA).
Inputs are provided through each override by a cam and roller (cam follower)
which are held together by spring force. Inputs are from the cam to the roller or
the roller to the cam, depending on the installation, and normal or non-normal
operation. Normally the cam and roller operate as a unit and move together.
Lateral Central Control Actuators (LCCA)
The LCCA’s hydraulically power the wing cable system which controls the
Power Control Actuators (PCA). LCCA can also be controlled electrically by
signals from the Flight Control Computers (FCC) in autopilot operation.
Power Control Actuators (PCA)
The PCA's position the ailerons hydraulically and are controlled mechanically.
There are two PCA's on each aileron (8 total). Each PCA has a single hydraulic
system source.
Droop Mechanism
The droop mechanism positions the inboard ailerons 10 degrees down with the
trailing edge flaps equal to or greater than 15 degrees. The flap drive-angle
gearbox mechanically positions input rods to the inboard PCA's.
If a jam occurs on either side of the override, and sufficient force is applied on
the side that is not jammed, the roller is forced up on the cam face. This
separates the aileron control system allowing partial system operation.
Lost Motion
Two lost motion devices are installed between the primary and backup control
systems. These devices permit operation of the primary control system during
normal operation by preventing contact with the backup control system.
The lost motion devices engage during jams or disconnects in the primary
control system. This enables full or partial backup cable system operation of
the ailerons and spoilers.
The devices consist of an arm in a slot with gaps between the arm and slot.
Primary control inputs move the arm or slot with the other side of the device
moved by aileron system response. Normally there is no contact between the
arm and slot. When a jam or disconnect occurs in the primary control system,
the lost motion devices are engaged by operation of the backup cable system.
AILERON MANUAL CONTROL
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AILERON TRIM CONTROL
The aileron trim arm and control switches are located on the aft end of the
control stand. Both switches must be operated to power the trim actuator on the
feel, centering and trim mechanism.
Maximum aileron trim is 30 degrees of control wheel rotation. Aileron trim
indicator placards are located on top of each control column. Each unit of trim
represents five degrees of control wheel rotation.
AILERON TRIM CONTROL
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AILERON DROOP MECHANISM
Description
Both inboard ailerons are lowered (drooped) to improve lift when the trailing
edge flaps are extended.
The droop mechanism is mechanically operated by the aileron droop angle
gearbox as the flaps extend between up and 5 units causing the inboard
ailerons to lower 10 degrees. As the flaps are raised, the ailerons return to the
neutral position. Extending the flaps from 25 to 30 units causes the inboard
ailerons to retract approximately 5 degrees.
A droop mechanism for each inboard aileron is located on the left and right wing
rear spars inboard of the inboard ailerons.
The droop mechanism inboard and outboard quadrants have override
mechanisms to separate a jammed inboard or outboard aileron control input
from the aileron system.
Because the droop mechanism does not operate the body cable systems the
only flight deck indication of aileron droop is the position pointers on the EICAS
Status page.
The aileron droop angle gearbox output crank rotates the droop summing lever
as flaps extend from up to 5 units, operating the control rod to the inboard
aileron Power Control Actuator (PCA) causing the inboard ailerons to lower
(droop) 10 . The output crank cam follower is moved by a cam, operated by a
drive shaft, which has a shear out to permit flap operation with a jam in the
inboard aileron PCA input mechanism. The droop summing lever pivots on the
control rod from the inboard quadrant during droop operation, thus the only
input is to the inboard aileron PCAs.
When the flaps move from 25 to 30 units, the inboard ailerons move up to
approximately five degrees drooped due to the shape of the cam.
AILERON DROOP MECHANISM
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OUTBOARD AILERON LOCKOUT
An airspeeds schedule has been established (YSM software) to permit the
outboard ailerons to be locked out (faired) at cruise airspeeds. Aileron lockout
prevents over-control and control reversal at high airspeeds. Airspeed is
continuously monitored, compared to a lockout schedule in the YSM, and
appropriate signals are sent to the lockout actuator. The schedule is a function
of calibrated airspeeds and pressure altitude (Mach Number).
S.L. to 10,000 ft
= 275 + 5 kts
10,000 ft to 18,000 ft
= m 0.50 + 0.02
18,000 ft to 27,000 ft
= 235 + 5 kts
27,000 ft to ceiling
= m 0.58 + 0.02
The schedule includes a transition band to insure gradual, controllable changes.
Lockout commences when the airspeed exceeds the high side of the bank for
increasing speeds (i.e. m 0.60 at cruise altitude). Unlock begins when the
airspeeds slows to the low side of the bank for decreasing airspeeds (i.e. m0.56
at cruise altitude).
Lockout extension/retraction time is 15 seconds in either direction. The aileron
is faired/unfaired gradually to avoid abrupt control responses.
The outboard ailerons are locked out at high speed to reduce roll control
sensitivity about the longitudinal axis of the airplane.
An aileron lockout mechanism is mounted on the wing rear spar, inboard of
each outboard aileron. The mechanism is operated by an electric actuator
which positions linkages to prevent quadrant rotation from operating the control
rod to the PCA's. The lockout actuators are electronically controlled by
stabilizer trim aileron lockout modules (YSM) using speed inputs from the Air
Data Inertial Reference Units (ADIRU).
OUTBOARD AILERON LOCKOUT
B767-3S2F
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B767-3S2F
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ATA 27-10
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TRAINING MANUAL
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AILERON POSITION INDICATING SYSTEM
Aileron Position Transmitters
Each of the four ailerons has a transmitter located near its outboard ends. The
transmitter case is mounted on the rear wing spar. A crank with an adjustable
rod is attached to the aileron. Aileron motion rotates the crank and generates
an output signal to the EICAS computers. The adjustable control rod is used to
rig the transmitter to electrical zero (minimum voltage) with the aileron faired to
structure. Access is by panels on the lower wing surface just forward of the
aileron leading edge.
Aileron Position Indicator
Aileron position is displayed on the lower EICAS display on the status page
only. Triangular pointers arranged on vertical scales indicate each aileron
position on a vertical scale.
Dispatch Deviation
If the Flight Control Surface Indication is INOP it is necessary to provide a visual
flight control check prior to each departure.
28V AC
R BUS
R AILERON
POSITION
P11 CB PANEL
CX
LC FILTER
RIGHT OUTBD
AILERON POSITION
XMTR
LC FILTER
INTERNALS
SAME AS
RIGHT OUTBD
POS XMTR
RIGHT INBD
AILERON POSITION
XMTR
28V AC
L BUS
L AILERON
POSITION
P11 CB PANEL
1
OUTBD AIL
INBD AIL
INBD AIL
OUTBD AIL
LOWER EICAS
DISPLAY
INTERNALS
SAME AS
RIGHT OUTBD
POS XMTR
LEFT INBD
AILERON POSITION
XMTR
INTERNALS
SAME AS
RIGHT OUTBD
POS XMTR
LEFT OUTBD
AILERON POSITION
XMTR
EICAS 28V AC REFERENCE POWER:
LEFT AIL POSN - LEFT ENG OIL PRESS (L9)
RIGHT AIL POSN - RIGHT ENG OIL PRESS (L36)
L/R EICAS CMPTR
RUD
LC FILTER
AIL
LC FILTER
POSITION
POINTERS
AILERON POSITION INDICATING SYSTEM
B767-3S2F
Page - 31
ATA 27-10
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AILERON
POSITION
INDICATION
TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
ELEV
AIL
1
STATUS PAGE
B767-3S2F
Page - 32
ATA 27-60
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TRAINING MANUAL
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SPOILER CONTROL AND INDICATION
SPEEDBRAKES Light
Control
Electronic control of hydraulic Power Control Actuators (PCA) is by control
wheel Rotary Variable Differential Transformers (RVDT) and speedbrake lever
Linear Variable Differential Transformer (LVDT) inputs to Spoiler Control
Modules (SCM). Each SCM outputs control signals to an Electro-Hydraulic
Servo Valve (EHSV) on two PCA’s. Spoiler panel position signals from a piston
operated internal PCA LVDT provide a feedback signal to the SCM for panel
control and fault detection.
RVDT lateral control inputs are from aileron system operation. LVDT
speedbrake control inputs are from speedbrake lever operation.
Indication
Spoiler system faults cause a maintenance message to be displayed.
Faults causing auto shutdown of a panel pair cause display of the amber
SPOILERS light and an advisory message. Additional fault information is
available from the built in test function of the SCM.
Speedbrake Lever Positions
DOWN - Is a detent position that signals all spoiler panels to retract.
ARMED - Allows automatic deployment of speedbrake upon landing.
UP - Speedbrake lever moves to the UP position after both trucks in a no-tilt
position.
AUTO SPDBRK Light
This light illuminates to indicate a fault in the auto speedbrake system. For
aircraft equipped with winglets, the AUTO SPDBRK light will indicate a fault in
the autostow system.
SPOILERS Light
This light iIlluminates when one or more spoiler panels are not in the
commanded positioned. A failed spoiler PCA could cause this light.
This light illuminates to indicate the speedbrake lever is beyond the ARMED
detent with radio altitude between 15’ to 800' or radio altitude above 15' with
flaps extended beyond 20 degrees.
SPOILER CONTROL AND INDICATION
B767-3S2F
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B767-3S2F
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ATA 27-60
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TRAINING MANUAL
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SPEEDBRAKE MECHANISM AND LVDT UNITS
Location
The Speedbrake Lever is connected to the Speedbrake Mechanism in the
control stand by a rod. The Linear Variable Differential Transformers (LVDT)
are connected to the speedbrake mechanism. The LVDTs are accessed by
opening the left side panel of the control stand.
Description
Three LVDT units are attached to the speedbrake mechanism inner shaft.
Rotation of the speedbrake lever moves the connecting rod attached to the
inner shaft of the speedbrake mechanism. An auto speedbrake actuator can
also operate the inner shaft and LVDT's through an outer shaft and no-back
clutch. The inner shaft then operates both the LVDT moveable core rods. The
LVDT’s output a variable voltage to the Spoiler Control Modules (SCM’s). LVDT
1 of each LVDT pair outputs to the SCM’s in the left Control System Electronic
Unit (CSEU). LVDT 2 outputs to the SCM’s in the right CSEU.
Maintenance Practices
The LVDT’s are removed and installed in pairs as they have a common rod end.
To adjust the LVDT unit, the speedbrake lever is placed in the arm detent, the
jam nut is loosened, and the wrench flat is rotated until a voltage of not more
than 50 mv is attained on both LVDT's (Null Position).
ARM (8.5 DEGREES)
DOWN (DETENT)
FROM REVERSE
THRUST CAM
UP (78 DEGREES)
SPEEDBRAKE LEVER
(LIFT TO MOVE AFT)
REVERSE THRUST AUTO
SPEEDBRAKE DEPLOY MECHANISM
PIVOT SHAFT
NO-BACK CLUTCH
FLIGHT
COMPARTMENT
FLOOR
AUTO-SPEEDBRAKE
ACTUATOR
SPEEDBRAKE LVDT
(3 PAIRS)
SPEEDBRAKE MECHANISM AND LVDT UNITS
B767-3S2F
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ATA 27-60
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TRAINING MANUAL
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B767-3S2F
Page - 36
ATA 27-60
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TRAINING MANUAL
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SPOILERS AND SPEEDBRAKES - OVERVIEW
Spoiler/Speedbrake Operation
Spoilers deploy as a function of control wheel deflection, speedbrake lever
position, flap position, and air/ground logic. All twelve spoilers are programmed
to provide roll control, in-flight speedbrakes, and ground spoiler speedbrakes.
Each symmetrical pair of spoilers is controlled by a Spoiler Control Module
(SCM). Each spoiler is driven by a Power Control Actuator (PCA).
The output of each SCM and the feedback from the pair of PCA's being
controlled by that SCM form a closed loop electro-hydraulic servo control
system.
Lateral control inputs to each SCM is by control wheel Rotary Variable
Displacement Transducers (RVDT). Speedbrake inputs are by speedbrake
lever Linear Variable Displacement Transducers (LVDT).
RVDT and LVDT control inputs are demodulated, amplified, and modified by
SCM programs. The lateral control and speedbrake commands are mixed to
provide approximately the same roll-rates with or without speedbrakes.
Each SCM has two output signals - one to the left wing and one to the right
wing. The two outputs will cause the spoiler pair to deploy asymmetrically
during roll-control and symmetrically during speedbrake operation. These
modes are modified within the SCM if a roll is initiated while speedbrakes are
deployed.
Spoiler panel limits are determined for each Spoiler Control Module by pin
programming.
Spoilers 4 and 9 are INHIBITED as in-flight speedbrakes.
Spoilers 4, 5, 8, and 9 are INHIBITED as lateral control spoilers at cruise
speeds (flaps 20 degrees or less).
LEFT CONTROL WHEEL
SPEEDBRAKE
LEVER
SPEED BRAKE
LEVER LVDT UNITS
(3 PLCS)
RIGHT CONTROL WHEEL
DEPLOY
SPOILER
RVDT UNIT
2
SPOILERS
ANNUNCIATOR PANEL
(P5)
3L
3R
1L
1R
CSEU DC PWR
1
RIGHT FWD QUADRANT
3
LEFT FWD QUADRANT
2L
2R
2
1
3
SPOILER
RVDT UNIT
SPOILERS (W)
POWER
POWER
FAULTS
ACTIVE CHAN (A)
STBY CHAN (B)
MODEL CHAN (C)
FAULT MON
CSEU AC PWR
FLAP POSITION
FSPM
AIR/GND
& HYD DISCRETES
LOCK/UNLOCK
2L (E1-1)
L CSEU
POWER
FAULTS
SPDBK
HANDLE POS
FLAP
DISCRETES
INTLK
3L (E1-1)
FAULTS
FLAP
DISCRETES
INTLK
1L (E1-1)
POWER
POWER
FAULTS
POWER
DISCRETES
FLAP
INTLK
FLAP
DISCRETES
1R (E2-1)
INTERNALS
SAME AS
1L
FLAP
INTLK
DISCRETES
2R (E2-1)
R CSEU
SPOILERS (Y)
FAULTS
FAULTS
L & R EICAS COMPUTER (E8)
3R (E2-1)
1
60
45
OUTBD
1
45
45
PANELS 4, 5, 8 & 9 DO NOT OPERATE FOR
LATERAL CONTROL WITH OUBOARD AILERONS
LOCKED OUT
2
45
45
45
45
0
0
GROUND
SPEED BRAKE
MAX LIMIT (DEG)
LOW SPEED
LATERAL CONTROL
MAX LIMIT (DEG)
17
17
XX
XX
XX
17
60
OUTBD
45
HIGH SPEED
LATERAL CONTROL
MAX LIMIT (DEG)
1
SPOILER SPEEDBRAKES - OVERVIEW
B767-3S2F
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TRAINING MANUAL
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LVDT
PCA
0
0
PCA
60
9
INFLIGHT
SPEED BRAKE
MAX LIMIT (DEG)
SPOILER
PANEL NO.
EHSV
LVDT
PCA
17
8
0
EHSV
LVDT
60
INBD
17
X
XX
EHSV
LVDT
17
7
45
60
OUTBD
45
LVDT
6
17
10
45
LVDT
17
INBD
INBD
INBD
PCA
60
EHSV
17
5
OUTBD
4
OUTBD
45
0
17
60
C HYD PWR
OUTBD
45
11
45
45
PCA
60
OUTBD
45
PANELS 4 AND 9
LOCKED OUT DURING
IN-FLIGHT SPEED BRAKES
EHSV
45
3
OUTBD
LVDT
EHSV
EHSV
60
1
LVDT
EHSV
EHSV
EHSV
PCA
60
45
60
60
PCA
FWD
PCA
PCA
PCA
LVDT
PRESSURE
PCA
LVDT
R HYD PWR
PCA
LVDT
C HYD PWR
R HYD PWR
EHSV
EHSV
L HYD PWR
LVDT
YSM
12
45
45
L HYD PWR
B767-3S2F
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ATA 27-60
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TRAINING MANUAL
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AUTO SPEEDBRAKE ACTUATOR
Auto Speedbrake Actuator
The Auto Speedbrake Actuator drives the speedbrake lever and the speedbrake
LVDT's through a no-back clutch. The clutch allows the flight crew to move the
speedbrake lever without moving the actuator output shaft. Access to the
actuator is through a side panel in the captain's side of the control stand.
REVERSE
THRUST
LEVER
ACCESS
PANEL
THRUST
LEVER
DOWN
ARMED
SPEEDBRAKE LEVER
(LIFT TO MOVE)
REVERSE THRUST
LEVER POSITION
SWITCH (S374)
NO BACK
CLUTCH
ASSEMBLY
P10 CONTROL STAND
UP
INNER SHAFT
AUTOSPEEDBRAKE
ACTUATOR
SWITCH CAM
SPEEDBRAKE
SWITCHES
(S371 & S493)
LVDT (3)
AUTO SPEEDBRAKE ACTUATOR
B767-3S2F
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B767-3S2F
Page - 40
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TRAINING MANUAL
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AUTO SPEEDBRAKE SYSTEM
Purpose
The auto speedbrake system operates the speedbrake
lever mechanism to extend the spoilers at touchdown or
during a refused takeoff and to retract the spoilers
when a go-around starts after touchdown.
System Description
Auto speedbrake relays control operation of the autospeedbrake
electric motor-operated actuator that moves
the speedbrake lever mechanism.
These inputs control the relays:
- Thrust lever position switches (two thrust levers)
- Arm switch (speedbrake lever)
- Thrust reverse switch (a reverse thrust lever)
- Air-ground (YSM).
Indication
Operation of the auto speedbrake system shows by the
position of the speedbrake lever on the P10 control
stand.
Fault indication shows by the advisory AUTO SPEEDBRAKE
on EICAS and the amber AUTO SPDBRK light on P5.
AUTO SPEEDBRAKE SYSTEM
B767-3S2F
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B767-3S2F
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EFF - ALL
AUTO SPEEDBRAKE ELECTRICAL SCHEMATIC
Operation
A 28v dc motor-driven actuator extends and retracts the
speedbrakes.
Extend
The auto-speedbrake actuator moves to the full extend
position when the auto-speedbrake extend relay
energizes.
The extend relay energizes when the auto-speedbrake
air/gnd system 1 and 2 relays energize.
The auto-speedbrake air/gnd system 1 and 2 relays
energize when all of these conditions are correct:
- YSM shows the airplane is on the ground
- Thrust levers are < 8.5 degrees
- Speedbrake lever is armed or a reverse thrust
lever is at idle.
The YSM shows the airplane is on the ground when at
least two air/ground inputs show on ground and at least
one radio altimeter shows less than ten feet.
Retract
The auto-speedbrake actuator moves to the full retract
position when the retract relay energizes.
The retract relay energizes for one or more of these
conditions:
- A thrust lever moves forward
- An auto-speedbrake air/gnd sys relay deenergizes
- Speedbrake lever is less than the arm position,
and the reverse thrust levers are in the stowed
position.
TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
Speedbrake Faults
These conditions cause the amber AUTO SPDBRK light on
P5 and AUTO SPEEDBRAKE EICAS (level C alert) message
when the speedbrake lever is in the arm position:
- Disagreement between system 1 and system 2 auto
speedbrake air/ground relays
- Left and right YSM auto-speedbrake invalid signals
are correct
- Auto-speedbrake extend and retract relays energize
or deenergize at the same time.
The auto-speedbrake light and message also show when
the actuator is not fully retracted, and the speedbrake
handle is in the down detent.
AUTO SPEEDBRAKE ELECTRICAL SCHEMATIC
B767-3S2F
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ATA 27-60
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B767-3S2F
Page - 44
ATA 27-20
11/11/13
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TRAINING MANUAL
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RUDDER CONTROLS AND INDICATORS
Trim Control and Indication
A trim control knob on the control stand operates the electric trim actuator on
the aft quadrant assembly. A trim indicator shows the trim actuator position in
units of trim.
Rudder Position Indication
The rudder position is displayed on the EICAS status page.
Yaw Damper Controls
The Yaw Damper system is controlled by two switches on the P5 overhead
panel. An ON light shows the switch position. An amber INOP light indicates
the yaw damper function is inoperative.
A three position yaw damper test switch on the P61 panel tests both Yaw
Damper systems.
EICAS Indications
A RUDDER RATIO amber light on the P5 overhead panel indicates the loss of
rudder ratio changer function.
EICAS advisory and maintenance messages indicate various levels of ratio
changer and yaw damper faults. Advisory messages indicate loss of function.
Maintenance messages indicate faults in the associated system.
TEST
L
YAW DAMPER
R
ON
ON
INOP
INOP
OVERHEAD PANEL (P5)
GND RPROX
L
C
L
C
INERTIAL REFERENCE
INOP
INOP
R
DUCT
LEAK
RUDDER
RATIO
OVERHEAD PANEL (P5)
TEST PANEL MODULE (P61)
RUDDER RATIO
R YAW DAMPER
L YAW DAMPER
PRIMARY DISPLAY
15
10
5
NOSE LEFT
AILERON
LEFT
WING
DOWN
0
UNITS
5
10
15
NOSE
LEFT
RIGHT
WING
DOWN
RUDDER RATIO
YAW DAMPER
NOSE RIGHT
NOSE
RIGHT
ECS/MSG PAGE
R
U
D
D
E
R
RUD
AIL/RUD TRIM CONTROL (P8)
AIL
ELEV
AIL
STATUS PAGE
EICAS DISPLAY UNIT (P2)
RUDDER CONTROLS AND INDICATORS
B767-3S2F
Page - 45
ATA 27-20
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B767-3S2F
Page - 46
ATA 27-20
11/11/13
EFF - ALL
TRAINING MANUAL
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RUDDER YAW CONTROL
Yaw Control
The function of the rudder system is to provide directional control and stability
around the vertical axis.
Pilot inputs via the rudder pedals drive a single cable run from the forward
quadrants located beneath the flight compartment floor to the aft quadrant at the
base of the vertical stabilizer.
Electrical control inputs at the aft quadrant are:
• Rudder trim actuation by the flight compartment trim switch
• Auto Pilot inputs from the flight control computers
Rudder control authority is varied in response to airspeed by the ratio changer
mechanism and actuator.
Two yaw damper servos each driven by a control module provide turn
coordination and protection against uncommanded yaw inputs.
The rudder is powered by three actuators, each served by a separate hydraulic
system. A surface position signal is developed by a transmitter which provides
position indication through the EICAS system to the flight compartment for
display on the status page only.
RUDDER YAW CONTROL
B767-3S2F
Page - 47
ATA 27-20
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TRAINING MANUAL
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B767-3S2F
Page - 48
ATA 27-20
11/11/13
EFF - ALL
TRAINING MANUAL
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RUDDER SYSTEM
Description
Two sets of adjustable rudder pedals mechanically drive a pair of forward half
quadrants. The quadrants are tied together by a bus rod to enable rudder
control by either set of pedals. The quadrants and linkages are located beneath
the flight compartment floor and accessed through the forward access door,
forward of the nose wheel well. A single pair of rudder control cables from the
forward quadrants run under the flight compartment floor, up the aft bulkhead of
the flight compartment, along the ceiling of the passenger compartment and
terminates at the aft quadrant in the base of the vertical stabilizer. The aft
quadrant assembly receives control inputs from the pilots' rudder pedals
through the cables, from the directional autopilot servos and from the electric
trim system. Output is through two control rods to the ratio changer assembly.
Yaw Damper Summing Lever Assembly
Sums ratio changer and yaw damper inputs to provide control input to rudder
actuators. Incorporates a pogo assembly, and a secondary control path
override. The assembly is mounted above the ratio changer and receives
inputs from the primary and secondary control path linkages, and from the yaw
damper servos. Two yaw damper servos receive inputs from control modules
and provide turn coordination and protection against uncommanded yaw inputs.
Position Transmitter
The rudder position transmitter is mounted just below the lower PCA. Rudder
surface movement drives a synchro-transmitter which provides a position signal
through the EICAS computers and is displayed on the status page.
Directional Autopilot Servos
Dispatch Deviation
Three directional autopilot servos receive control inputs from the flight control
computers and provide directional control in autoland mode only on final
approach and during runway rollout.
Flight Control Surface Indication INOP:
Trim Actuator/Feel And Centering Unit
One Trim Actuator mounted directly above the aft quadrant drives the rudder to
selected trim position by positioning the trim, feel and centering unit. The trim
actuator is driven by electrical trim signals from the flight compartment. A cam
and roller and springs provide feel force to rudder pedal input and the centering
force to return pedals to neutral when input is removed.
Rudder Ratio Changer
The rudder ratio changer is located directly above the aft quadrant and driven
by the aft quadrant output rods. The purpose is to vary the rudder control
authority as a function of airplane speed.
An electro hydraulic actuator, controlled by signals from control modules, drives
the ratio changer mechanism. Ratio changer output is through the primary and
secondary control paths.
• Flight control surface indication may be INOP provided a visual flight
control check is accomplished prior to each departure.
Power Control Actuators
Three PCAs receive control valve inputs from the primary and secondary
control paths. Each actuator is powered by a separate single hydraulic system.
UPPER RUDDER PCA
C HYD SYS
MIDDLE RUDDER PCA
L HYD SYS
RUD
A
ELEV
AIL
LOWER RUDDER PCA
R HYD SYS
YAW DAMPER SUMMING
MECHANISM
AIL
LOWER EICAS DISPLAY (P2)
15
10
NOSE LEFT
AILERON
LEFT
WING
DOWN
5
0
5
UNITS
10
NOSE RIGHT
NOSE
LEFT
RIGHT
WING
DOWN
TEMPERATURE
COMPENSATION
LINKAGE
15
MAIN EQUIPMENT CENTER
NOSE
RIGHT
R
U
D
D
E
R
LT
YSM
SINGLE FCC
AIL/RUD CONTROL (P8)
PEDAL
ADJUSTMENT
CRANKS
RT
YSM
CAPTAIN'S
RUDDER
PEDALS
YAW DAMPER
SERVOS
RT
YSM
RUDDER
POSITION
TRANSMITTER
RATIO CHANGER
ACTUATOR
LT
YSM
PRIMARY
CONTROL ROD
SECONDARY
CONTROL ROD
TRIM ACTUATOR
RUDDER RATIO CHANGER
MECHANISM
FIRST OFFICER'S
RUDDER PEDALS
FWD
FORWARD
QUADRANT
FWD
TO NOSEWHEEL
STEERING
AFT QUADRANT
ASSEMBLY
DIRECTIONAL ROLLOUT
AUTOPILOT SERVOS (3)
RUDDER SYSTEM
B767-3S2F
Page - 49
A
ATA 27-20
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TRAINING MANUAL
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FEEL CENTERING AND TRIM MECHANISM
AUTO LAND
ONLY
FCC
(3)
B767-3S2F
Page - 50
ATA 27-20
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RUDDER TRIM SYSTEM
Trim Switch
Trim control is by a pilot operated trim switch located on the aft edge of the
center console (P8). The rotary switch is spring loaded to the neutral position.
The switch is part of the aileron/rudder trim control module and is powered by
28 volt dc from the left dc bus through a circuit breaker located on the p-11
panel. Rotation of the trim switch through the 5 degree position removes the
system ground. Rotation through the 15 degree position arms the trim motor
circuit. Rotation through the 25 degree position closes the control switch and
selects the extend (left rudder trim) or retract (right rudder trim) mode of
operation. There is a mechanical stop at the 30 degree position. Only one trim
rate exists and is not a function of the trim switch operation.
Trim Actuator
The rudder trim actuator is a linear actuator powered by a self contained dc
motor. The unit contains an electromagnetic brake to limit overrun. Internal limit
switches control actuator stroke. Positive mechanical stops prevent over travel
in the event of limit switch malfunction.
Power is applied by the trim switch and energizes the motor until the switch is
released or the limit switch is activated. The brake releases during motor
operation and resets by spring force when power is interrupted.
Trim Position Indicator
The rudder trim position indicator is powered by 28 volt ac from left AC bus and
controlled by a circuit breaker on the P-11 panel.
The signal to drive the trim indicator is generated by a gear driven RVDT
integral to the trim actuator. The transmitter signal drives a DC motor in the
receiver unit in the aileron/rudder trim control module to position the trim
indicator. The indicator registers 17 units of left or right rudder trim.
Nulling of the indicator is done with hydraulic power off and rudder trim to
neutral (rudder trailing edge within index groove and cam centered in detent). If
the indicator is not at zero, remove the aileron/rudder trim control module and
adjust it by rotating the adjusting screw on the aft face of the until the indicator
reads zero.
Note:
An inoperative rudder trim indicator does not affect the ability of
the rudder trim actuator to provide trim inputs to the rudder system.
15
10
NOSE LEFT
AILERON
RUDDER
TRIM
POSITION
(K17)
0
5
UNITS
10
15
NOSE RIGHT
NOSE
LEFT
NOSE
RIGHT
R
U
D
D
E
R
RIGHT
WING
DOWN
LEFT
WING
DOWN
28V AC
BUS L
5
POWER
SUPPLY
ZERO
ADJUST
FWD
INDICATOR ADJUSTMENT
PANEL 324 BL
TAPE
DRIVE
A
N83 RUDDER TRIM INDICATOR
TRIM
ACTUATOR
NOSE LEFT
25L°
28V DC
BUS L
15L°
RUDDER
TRIM
CONTROL
(K18)
P11 OVHD CB PANEL
A
LEFT (EXT)
5L°
5R°
15R°
RIGHT (RET)
25R°
NOSE RIGHT
M515 RUDDER TRIM ACTR
RUDDER TRIM SW (S3)
M74 AIL/RUD TRIM CONTROL MODULE (P8)
RUDDER TRIM SYSTEMS
B767-3S2F
Page - 51
ATA 27-20
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TRAINING MANUAL
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FWD
B767-3S2F
Page - 52
ATA 27-20
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EFF - ALL
TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
RUDDER CHANGER OPERATION
General
The Ratio Changer System varies the amount of maximum rudder travel as a
function of airspeed. The system provides for constant rudder pedal response
over the entire airplane operating speed range. The Rudder Ratio Changer
Actuator (RRCA) is electro-hydraulic and is driven by two separate analog
channels.
Description
The ratio changer actuator, on the ratio changer mechanism, consists of an
unbalanced actuator with a solenoid valve, a bypass valve and an
Electro-Hydraulic Servo Valve (EHSV). The bypass valve, operated by the
solenoid valve, and the EHSV control left hydraulic system pressure to the ratio
changer actuator.
Ratio Changer Actuator Operation
When the ratio changer is inoperative, the solenoid valve is de-energized and
the bypass valve is spring loaded closed. In the closed position, the bypass
valve shuts off hydraulic pressure to the EHSV and the middle PCA. Left
hydraulic system pressure, if available, fully retracts the actuator to the low
speed position.
When the ratio changer system is in operation, the solenoid valve is energized
and opens the bypass valve providing pressure to the EHSV and the middle
PCA. As airspeed increases, signals are sent to the EHSV to increase pressure
to the extend side of the unbalanced actuator. As the actuator extends, it
positions the ratio changer mechanism to a high speed position.
Failure Conditions
Actuator faults, or ratio changer system failures causing loss of control,
de-energize the solenoid valve which closes the bypass valve. Left hydraulic
pressure moves the mechanism to the low speed position.
SER
-CAUTIONREMOVE THE FRONT PANEL
SLOWLY TO PREVENT DAMAGE
TO INTERNAL CABLE
MFR
A/S
MENU
YES
ON/OFF
TO MIDDLE POWER
CONTROL ACTUATOR
NO
YAW DAMPER/STABILIZER TRIM
MODULE (YSM)
P/N 285T1122SERIAL NUMBER
MOD A B C D
LEVEL
E F G H
L ADIRU
BYPASS
VALVE
LOGIC
CROSSFEED
LEFT HYD
SYS PRESS
SW
PRIMARY & SECONDARY
CONTROL PATHS
LEFT YSM
SOLENOID
VALVE
EHSV
RATIO
CHANGER
MECHANISM
LVDT
A/G SYS
1&2
RATIO
CHANGER
ACTUATOR
SER
-CAUTIONREMOVE THE FRONT PANEL
SLOWLY TO PREVENT DAMAGE
TO INTERNAL CABLE
MFR
L HYD
SYSTEM
MENU
YES
A/S
R ADIRU
ON/OFF
NO
YAW DAMPER/STABILIZER TRIM
MODULE (YSM)
P/N 285T1122SERIAL NUMBER
MOD A B C D
LEVEL
E F G H
LEGEND
RIGHT YSM
ELECTRICAL
MECHANICAL
HYDRAULIC
RATIO CHANGER OPERATION
B767-3S2F
Page - 53
ATA 27-20
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AFT QUADRANT
MECHANISM
EFF - ALL
TRAINING MANUAL
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B767-3S2F
Page - 54
ATA 27-20
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TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
RUDDER RATIO CHANGER MECHANISM
General Description
The purpose of the rudder ratio changer mechanism is to vary the rudder
authority (amount of control surface displaced into the airstream) from
commands by the rudder pedals, autopilot servos or rudder trim as a function of
airspeed. At low airspeed, the mechanism provides high authority to the rudder,
at high airspeed, the mechanism provides low authority to the rudder.
The ratio changer mechanism is located on the aft spar of the vertical stabilizer.
It is connected to the aft quadrant mechanism and the yaw damper summing
mechanism.
primary and secondary control rods. Maximum rudder authority is
approximately 26 degrees.
High Speed Position Operation
As the actuator extends, the bellcranks are rotated towards the torque tube
decreasing the radius of the primary and secondary control rods from the
rotational axis of the torque tube. This reduces the output from the aft quadrant
mechanism to the primary and secondary control rods. Maximum rudder
authority in the high speed position is approximately 2 degrees. Authority is
reduced incrementally as speed increases.
Ground Test
The ratio changer mechanism consists of an offset torque tube containing two
bearing mounted bellcranks. The end of the bellcranks are attached to the
primary and secondary control rods. The bellcranks are rotated on the torque
tube by the ratio changer actuator. The actuator is connected to the left
bellcrank and a bus rod interconnects the two bellcranks. A cartridge containing
two Linear Variable Differential Transformers (LVDT) is mounted on the ratio
changer mechanism structure at one end and connected to the right bellcrank at
the other end. A rig pin hole in each bell crank aligns with a rig pin hole in the
torque tube to allow adjustments.
Ratio Changer Operation
When the actuator is retracted, the bellcranks are rotated away from the torque
tube. Movement of the torque tube by the aft quadrant provides a maximum
input to the primary and secondary control rods. As the actuator extends, the
bellcranks are rotated towards the torque tube which decreases the movement
of the control rods.
If the ratio changer control system fails three springs drive the bellcranks away
from the torque tube ensuring full authority of the rudder control system.
Low Speed Position Operation
When the actuator is retracted the bellcranks are moved away from the torque
tube. This is the low speed position. In this position the ratio changer
mechanism can transmit a full input from the aft quadrant mechanism to the
A ground test positions the actuator to a 360 knots position for system
adjustment. In the test position, rig pin 6 can be inserted when the ratio changer
mechanism is properly rigged. The LVDT is adjusted to position the mechanism
for rig pin fit.
RIGHT
BELLCRANK
RIG PINS
ACTUATOR
LUG
LEFT
BELLCRANK
YAW DAMPER SUMMING MECHANISM
TEMPERATURE COMPENSATION LINKAGE
LVDT
PCA'S
CENTERING AND BIAS SPRING
OFFSET
TORQUE TUBE
YAW DAMPER SERVOS (2)
SUPPORT BEARING CRANK
ADJUSTING NUT
FWD
BUS ROD
(ADJUSTABLE)
RETURN SPRINGS(3)
RATIO CHANGER ACTUATOR
SECONDARY
CONTROL PATH
ACTUATOR EXTENDED
PRIMARY
CONTROL
ROD
RATIO CHANGER
ACTUATOR
ROTATIONAL AXIS
LOAD LIMITER
WITH CRUSH CORE
RUDDER RATIO
CHANGER LVDT
AFT QUADRANT
MECHANISM
TORQUE TUBE
SECONDARY
CONTROL ROD
ACTUATOR RETRACTED
AFT QUADRANT
MECHANISM
RATIO CHANGER MECHANISM
B767-3S2F
Page - 55
PRIMARY CONTROL
PATH
ATA 27-20
11/11/13
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TRAINING MANUAL
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RUDDER RATIO CHANGER MECHANISM
B767-3S2F
Page - 56
ATA 27-20
11/11/13
EFF - ALL
TRAINING MANUAL
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RUDDER YAW DAMPER SYSTEM
System Description
The yaw damper system provides automatic rudder control to improve airplane
ride quality, dampen gust loads on the vertical stabilizer, dampen undesirable
sideslip and roll (Dutch roll), and with any one autopilot engaged provide
coordinate turns.
The yaw damper system includes two Yaw Damper Stab Trim Modules (YSM)
each controlling a yaw damper servo actuator. The system uses inputs from the
Air Data Inertial Reference Computers (ADIRU), servo actuator LVDT’s, modal
suppression accelerometers, and air/ground relays to command rudder
movement. Pressure switches in the left and center hydraulic systems input for
fault detection and indication.
Movements of the yaw damper servos are summed by a summing lever before
transfer to the yaw summing mechanism which commands the rudder. When
both yaw damper servos are operative in flight, maximum yaw damper input to
the rudder is approximately 6 degrees in each direction. When one servo is
operative, maximum rudder movement is approximately 3 degrees. The
maximum amount of rudder command available for yaw damping depends on
airspeed and the number of ADIRU supplying data.
Controls and Indications
Two yaw damper control switches are located on the yaw damper control panel.
The switches control engage power to the YSMs and to the yaw damper servo
actuators. When a system is inoperative or during test, an INOP amber light
illuminates in the switch and an advisory L (R) YAW DAMPER message
appears on EICAS.
CAUTION: WITH ANY HYDRAULIC SYSTEM POWERED THE RUDDER
WILL MOVE DURING THE TEST
YSM
The YSM’s command rudder movement and monitor yaw damper for faults.
Failures are detected by automatic BITE and are stored in the module memory
for ground recall. Faults are recalled with YSM 6 button front face BITE.
YAW DAMPER
L
R
ON
INOP
ON
w
INOP
a
w
a
YAW DAMPER CONT PANEL (P5)
YAW DAMPER
TEST SWITCH
(P61)
YAWDMPR
L
R
SER
CSEU PWR SUPPLIES
1L AND 2L
S29 ADU CONTROL
PRESS SWITCH
(C HYD)
28V DC
STBY BUS
MENU
YES
TO PCA(S)
-CAUTION-
REMOVETHEFRONTPANEL
SLOWLYTOPREVENTDAMAGE
TOINTERNALCABLE
MFR
ON/OFF
NO
A
YAWDAMPER/STABILIZERTRIM
MODULE(YSM)
P/N285T1122SERIALNUMBER
MOD
LEVEL
A
E
B
F
C
G
D
H
L YSM
SER
28V DC
R DC BUS
-CAUTION-
INTERNAL
LVDT
MENU
YES
AIR/GND SYS
S27 ACMP CONTROL
PRESS SWITCH
(L HYD)
ON/OFF
NO
P/N285T1122SERIALNUMBER
MOD
LEVEL
A
E
B
F
C
G
D
H
R YSM
Page - 57
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EHSV
FWD
L HYD
RUDDER YAW DAMPER SYSTEM
B767-3S2F
TO RUDDER
RATIO
CHANGER
B
YAWDAMPER/STABILIZERTRIM
MODULE(YSM)
CSEU PWR SUPPLIES
1R AND 2R
RUDDER SUMMING
LINKAGE ASSY
YAW DAMPER SERVOS
SUMMING LEVER
REMOVETHEFRONTPANEL
SLOWLYTOPREVENTDAMAGE
TOINTERNALCABLE
MFR
ADIRU L, C, R
MODAL SUPPRESSION
ACCELEROMETERS
(AFT OF CARGO COMP)
TRAINING MANUAL
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C HYD
B767-3S2F
Page - 58
ATA 27-30
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ELEVATOR GENERAL DESCRIPTION
General Description
The elevator control system gives primary control of the airplane around its pitch
axis. The elevators change pitch attitude for climb, descend, and altitude hold.
Control
The elevator control system has two equivalent systems in parallel. The
captains control column supplies inputs to the left elevator PCA through the left
aft quadrant. The first officers control column supplies inputs to the right
elevator PCA through the right aft quadrant. The two control systems connect
through override mechanisms at the control columns and aft quadrants.
The autopilot system gives automatic elevator control. The autopilot servos
move the aft quadrant assemblies through rods and cranks. The left and center
autopilot servos move the left aft quadrant. The right autopilot servo moves the
right aft quadrant.
The feel and centering unit gives control column feel. The elevator feel
computer changes the feel at the column as a function of airspeed. The
airspeed is from the pitot system.
A stick nudger command from the stall warning computers moves the elevators
and the control columns to cause a nose down attitude of the airplane.
The slave cable system lets the movement of one elevator make a control input
into the opposite elevator PCA. This gives elevator asymmetry protection if the
PCA on one side disconnect from the aft quadrant.
Forward Controls
The two control column torque tubes connect together by a control column
override mechanism. A stick shaker is on each torque tube. The torque tubes
connect to the tension regulator quadrants. Two pairs of cables connect the
tension regulator quadrants to the aft quadrants. The left cables (captain control
column) go between the cabin floor beams and connect to the left aft quadrant.
The right cables (first officer control column) go up in the flight compartment
bulkhead and then in the cabin ceiling and connect to the right aft
quadrant. The aft quadrant torque tubes are aft of the horizontal stabilizer. An
interconnect rod connects the two aft torque tubes at the override mechanisms.
Three elevator autopilot servos are on the aft fuselage structure and connect to
the two aft quadrants by rods. Two servos connect to the left aft quadrant and
one servo connects to the right aft quadrant.
A feel computer, in the stabilizer compartment, makes dual hydraulic pressures
that change as a function of airspeed and stabilizer position. This variable
hydraulic pressure goes to the feel actuator on the feel and centering unit and
also to the stabilizer trim control modules (STCM).
A feel and centering unit connects by rods to the two aft quadrant torque tubes.
The feel and centering unit has a dual hydraulic actuator supplied with variable
pressure from the elevator feel computer. A cam roller spring mechanism and
hydraulic feel pressure move the elevator system to center.
A stick nudger is on the feel and centering unit.
An override mechanism is on the upper aft fuselage structure. The override
mechanism gives a neutral position for the feel and centering unit. The aft
quadrants output connect by rods to all three PCAs on each outboard elevator.
The movement of the elevators moves a slave cable through lost motions and
overrides. Position transmitters connect by cranks and linkages to each inboard
elevator to give elevator position to the EICAS computers.
Operation
The elevator control system has two equal systems that operate in parallel.
Usually, the two systems operate together. A break-out of the override
mechanisms lets the captain column operate the left elevator and the first officer
column operate the right elevator independently. In the command mode of the
autopilot, the FCC give commands for elevator movement and cause a
backdrive of the control columns. Feel force at the control columns changes by
the feel computer as a function of airspeed and stabilizer position. The override
mechanism lets the elevator system operate if there is a jam in the feel and
centering mechanism. The slave cable system gives an alternate means to
control one elevator if the linkage disconnects between the aft quadrant torque
tube and the PCA. Dual stick shakers give stall warning. A stick nudger on the
feel and centering unit gives a forward force to the control columns for stall
recovery. Two stall warning computers control the shakers and nudger.
FLIGHT
CONTROL
COMPUTERS
CONTROL
COLUMN (2)
FLIGHT DECK
INDICATION
AUTOPILOT
SERVO
AUTOPILOT
SERVO
AUTOPILOT
SERVO
LEFT AFT
QUADRANT
A
RIGHT AFT
QUADRANT
POSITION
XMTR (2)
B
PCA (3)
RIGHT ELEVATOR
SLAVE CABLE
INTERCONNECT
STALL
WARNING
STABILIZER
STICK
NUDGER
NEUTRAL
SHIFT
FEEL AND
CENTERING
UNIT
SLAVE
CABLES
DUAL FEEL
ACTUATOR
SLAVE CABLE
INTERCONNECT
ELEVATOR
FEEL
COMPUTER
PNEUMATIC
HYDRAULIC
MECHANICAL
ELECTRICAL
HYDRAULIC
SYSTEM L
A
PITOT
TUBE (2)
ELEVATOR GENERAL DESCRIPTION
B767-3S2F
Page - 59
ATA 27-30
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TRAINING MANUAL
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B
PCA (3)
LEFT ELEVATOR
HYDRAULIC
SYSTEM C
B767-3S2F
Page - 60
ATA 27-30
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EFF - ALL
TRAINING MANUAL
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ELEVATOR CONTROL SCHEMATIC
Dual Path Controls
The elevator control system consists of two equal systems in parallel.
The captain control column is hard connected to power control actuator (PCA)
input levers to the left outboard elevator.
The first officers control column is hard connected to PCA input levers to the
right outboard elevator.
The left and right elevator control systems are interconnected through override
mechanisms at the control columns and the elevator aft quadrants in the tail
compartment just forward of the APU.
The outboard elevators are connected to each other by slave cable
interconnects.
The captain's and first officers' elevator systems have equal authority.
The two systems will normally act together as one system because of
interconnection through override mechanisms.
One system will control independent of the other (after override) if one system is
immobilized.
One system is sufficient to control the airplane.
The inboard and outboard elevators are even (faired) and a mach trim system is
provided and used.
CONTROL
COLUMNS
OVERRIDE
MECHANISM
CAPTAIN
CONTROL
COLUMN
FIRST OFFICER
CONTROL COLUMN
TENSION
REGULATOR
QUADRANT
(2)
ELEVATOR
FEEL
COMPUTER
FEEL AND
CENTERING
UNIT
OVERRIDE
MECHANISM
STICK
NUDGER
HORIZONTAL
STABILIZER
ELEVATOR A/P
SERVO (3)
AFT QUADRANT
INTERCONNECT
ROD
SLAVE
CABLE
INTERCONNECT
STICK
SHAKER
(2)
SLAVE CABLE
CENTER LINE OF
QUADRANT
STABILIZER REAR
(2)
SPAR HINGES
LEFT AFT QUADRANT
OUTPUT ARM
CONTROL ROD
LOST MOTION AND
OVERRIDE DEVICE
(2)
PCA (3 ON EACH
OUTBOARD ELEVATOR)
FWD
LEFT OUTBOARD
ELEVATOR
(RIGHT SIDE
SIMILAR)
LEFT INBOARD
ELEVATOR
(RIGHT SIDE
SIMILAR)
OUTBD
ELEVATOR CONTROL SCHEMATIC
B767-3S2F
Page - 61
ATA 27-30
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TRAINING MANUAL
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AFT QUADRANTS
OVERRIDE
MECHANISM
LEFT AFT
QUADRANT
TORQUE TUBE
POSITION
TRANSMITTER
(2)
RIGHT AFT
QUADRANT
OUTPUT ARM
CONTROL ROD
RIGHT AFT
QUADRANT
TORQUE TUBE
B767-3S2F
Page - 62
ATA 27-30
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TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
ELEVATOR FEEL FORCE SYSTEM
General Description
The two control columns have their torque tubes connected together by a
control column override mechanism. A stick shaker is installed on each torque
tube. The torque tubes output to the tension regulator quadrants.
Two pairs of cables are connected to the tension regulator quadrants. The left
cables (captain's control column) are routed between the cabin floor beams to
the aft fuselage; the right cables (first officer's control column) are routed up in
the flight deck bulkhead and then in the cabin ceiling. The left cables are
connected to the left aft quadrant (captain's) and the right cables to the right aft
quadrant (first officer's). The aft quadrant torque tubes pivot on the airplane
structure. They are located directly aft of the horizontal stabilizer. The two aft
quadrants are interconnected by a rod and an override mechanism.
Three autopilot servos are mounted on the aft fuselage structure and input to
the two aft quadrants by connecting rods. Two servos input to the left aft
quadrant and one to the right aft quadrant.
Feel and Centering Unit
A feel and centering unit, pivoted on the aft fuselage structure, is connected by
rods to both aft quadrant torque tubes. The feel and centering unit contains a
dual hydraulic actuator supplied with variable pressure from the elevator feel
computer. A cam roller spring mechanism and hydraulic pressure provide for
centering of the elevator system. A stick nudger is installed on the feel and
centering unit.
Elevator Feel Computer
A feel computer, installed in the stabilizer compartment, generates dual
hydraulic pressures which vary as a function of airspeed and stabilizer position.
This variable hydraulic pressure is supplied to the feel cylinder of the feel and
centering unit and to the stabilizer trim control modules
Override Mechanism
An override mechanism is installed on the upper aft fuselage structure.
Elevator Controls
The aft quadrants output by connecting rods to all three power control actuators
(PCAs) on each outboard elevator.
Slave Cable Interconnect
The movement of the elevators drives a slave cable interconnect through lost
motions and overrides.
Position Transmitters
Position transmitters are connected by cranks and linkages to each inboard
elevator to provide elevator position signals to the EICAS computers.
1
2 CONNECTIONS ON THIS SCHEMATIC
A
B CONNECTIONS TO STABILIZER TRIM
CONTROL MODULE (STCM)
ELEVATOR
FEEL COMPUTER
STABILIZER
FWD
PITOT
SYSTEM
FLT CONTROLS
HYD DISTR LFT
RELIEF
VALVE
ELEV FEEL (S,M)
PITOT PRESSURE
BELLOWS
BELLOWS
STATIC
RELIEF
VALVE
STATIC
SOURCE
SOURCE
RUD
FLT CONTROLS
HYD DISTR CTR
PITOT
SYSTEM
APL
APL
NOSE UP NOSE UP
BIAS
SPRING
AIL ELEV AIL
1
EICAS DISPLAY
(P2) STATUS
AND MAINTENANCE
PAGES)
CENTERING
SPRING
F/O
INPUT
2
A
S1
S2
1
1
LEGEND
PRESSURE L/R EICAS
COMPTR (E8)
RETURN
METERED PRESSURE
1
2
ELEVATOR FEEL COMPUTER
- PRESSURE DIFF (>25%)
- L, C, R HYD SYS PRESSURIZED
- 30 SEC TD
ELEVATOR FEEL FORCE SYSTEM
B767-3S2F
Page - 63
ATA 27-30
11/11/13
CAPT
INPUT
B
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TRAINING MANUAL
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FEEL
ACTUATOR
ELEV FEEL AND
CENTERING UNIT
TIES
AND
LINKS
B767-3S2F
Page - 64
ATA 27-30
11/11/13
EFF - ALL
TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
STALL WARNING SYSTEM COMPONENTS
Stick Shakers
Captain's and first officer's stick shakers are located on the elevator torque tube
sections under the flight compartment floor. Shakers are accessible from the
access door forward of the nose wheel well.
Stick Nudger
A single stick nudger actuator, located on the elevator feel and centering unit
provides a column forward force by repositioning the feel and centering unit
input levers.
Stall Warning Computers
The left and right stall warning computers are located in the warning electronics
unit (P51 panel) accessible from the main equipment area.
Test Panel
Left and right stall warning test switches are located on the P61 side panel.
Each switch is a momentary toggle switch for testing a stall warning system.
Interfacing System Components:
•
•
•
•
•
•
Center and right Flap/Stabilizer Position Modules (P50)
Proximity Switch Electronic Unit (E1-2)
Flap/Slat Electronic Unit (E2-4)
Air Data Inertial Reference Units (E2-6)
Spoiler Control Modules 2L and 1R (E1-1), (E2-1)
Air ground relays (controlled by the PSEU) (P36/P37 panels)
L
STALL
R
MISC TEST
PANEL
ELEVATOR
TORQUE
TUBES
P61 RIGHT SIDE PANEL
P50
FLAP/STAB
POSITION
MODULES
(FSPM)
COLUMN SHAKER (2)
STALL
WARNING
COMPUTERS
ELECTRICAL SYSTEM
CARD FILE (P50)
STICK NUDGER ACTUATOR
WEU BITE
MODULE
WARNING ELECTRONIC
UNIT (WEU) (P51)
AFT ELEVATOR CONTROL CENTER
STALL WARNING SYSTEM COMPONENTS
B767-3S2F
Page - 65
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B767-3S2F
Page - 66
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STALL WARNING COMPUTER
Purpose
Each of the dual digital stall warning computers (SWC) is powered by dual
power supplies in the warning electronic unit (WEU). The SWC's calculate data
required for stick shaker and stick nudger operation and provide inputs to the
electronic flight instrument system (EFIS) and enhanced ground proximity
warning computer (EGPWC) for operation of the windshear detection and
guidance system.
Input/Output
Stick shaker: Each SWC computes two angle of attacks (AOA) to compare for
activation of the stick shaker discrete. The indicated AOA from the air data
computer (ADC) is modified by pitch rate from the inertial reference system
(IRS) and true airspeed (TAS) from the ADC to compute a corrected AOA. A
shaker AOA, calculated from static flap and slat position (slat motion uses the
most retracted position), is modified by mach and computed air speed (CAS)
inputs to determine an upper limit for the shaker AOA. If shaker AOA is
exceeded by the corrected AOA the SWC will activate the stick shaker output
discrete. Each stick shaker is operated by a 28 volt dc motor. The left shaker is
operated by the left SWC and the right shaker is operated by the right SWC to
provide redundant stall warning indications. The shakers are automatically
activated only in the air mode. Test switches (P61) provide for individual testing
of each shaker motor on the ground.
Stick nudger: A 28 volt dc motor operated actuator, mounted on the elevator
feel unit, is controlled by two relays each operated by one of the SWC's.
Actuator extension will result in forward pressure on the control columns to
reduce the AOA. Each SWC compares the corrected AOA (also used for
shaker operation) with a trip value based on current mach (M) input.
Nudger operation also requires air mode with both the flaps and slats retracted.
The control column will remain in a pushed forward position for the duration of
the nudger output discrete.
The stick nudger system can be tested by simultaneously activating both the left
and right stall warning test switches with the airplane in the ground mode and
flaps and slats retracted. The control columns should move forward and remain
until either switch is released.
Windshear Guidance and Detection System
The SWC's provide inputs to the electronic flight indication system (EFIS) and
ground proximity warning computer (GPWC) for windshear detection and
guidance indications. The use of dynamic inputs such as pitch rate, mach and
airspeed as well as static flap/slat configuration enables the SWC to compute
an upper limit for the shaker AOA which permits an increased maneuver margin
for the airplane to recover from windshear conditions without encountering
premature stick shaker warnings. Data words are provided to the EFIS for
display of the shaker AOA as a pitch limit indication and for a speed tape display
indicating stall speed for the wing configuration. (Additional operating and limit
speeds not associated with windshear detection are also provided EFIS by the
SWC's.) Shaker AOA, corrected AOA and flap position are input by the SWC's
to the GPWC for use in computation of windshear detection and annunciation.
(GPWC also uses self generated pitch rate/angle, roll attitude and vertical
speed and ADC input true airspeed and computed airspeed in the windshear
computation.) Windshear warning is red lights, red message on EFIS, siren and
voice annunciation.
BITE
A warning electronics unit (WEU) built-in-test (BITE) module provides
continuous monitoring of the SWC's, WEU power supplies and interfacing
component inputs. Faults are annunciated by a WARN ELEX status/
maintenance message.
28V DC
STBY BUS
STICK SHAKER
STALL TEST SW
FLAP/STAB
POSITION
MODULE (FSPM)
FLAPS/SLATS
ELECTRONIC
UNIT (FSEU)
STICK SHAKER
PROXIMITY SW
ELECTRONICS
UNIT (PSEU)
STALL
WARNING
COMPUTER
(SWC)
SPOILER CONT
MODULE (SCM)
GND PROXIMITY
WARN COMPUTER
(GPWC)
INERTIAL
DATA
(ADIRU)
Large Display
System
POWER SUPPLY
MODULES (PSM)
AIR DATA
(ADIRU)
AIR/GND
RELAYS
WEU BITE
DISPLAY
MODULE
STALL WARNING COMPUTERS
B767-3S2F
Page - 67
ATA 27-30
11/11/13
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B767-3S2F
Page - 68
ATA 27-30
11/11/13
EFF - ALL
TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
STALL WARNING COMPUTER BITE
Purpose
The warning electronic unit (WEU) built-in-test (BITE) module is located in the
P51 panel below the stall warning computers (SWC). It is a printed circuit board
equipped with faultballs for WEU power supplies A and B, a power reset switch
and two pairs of indicators to display fault codes. Alphanumeric codes are
displayed for SWC circuit board faults (on board fault), stall warning system
interface anomalies, airplane configuration/options, and software version.
Power-Up
On power up the SWC's initiate a self test of output drivers, input discrete
components, decoders and BITE memories. If a fault or anomaly is detected
WARN ELEX status/maintenance messages will be displayed on EICAS, and
the appropriate alphanumeric fault code will be displayed on the BITE module.
The fault code will be cleared only by a good power up test. If no faults are
detected ON power-up, no messages will appear, and the BITE will contain the
airplane configuration and option code.
Continuous Monitoring
Continuous monitoring tests determine circuit board operational capability on a
non-operational interference basis. Any on board faults preventing stick shaker,
stick nudger and angle of attack (AOA) outputs or interface anomalies such as
loss of voltage at the stick shaker and air data inertial reference unit (ADIRU)
AOA input will cause the status/maintenance messages WARN ELEX to
annunciate. Faults detected during continuous monitoring are not latched and
will clear with the fault. An opposite channel (other SWC) failure can also cause
a failure code to appear on the good SWC.
BITE Test
Activation of the appropriate STALL test switch on the miscellaneous test panel
(P61), in the ground mode only, will cause the associated SWC to verify the air/
ground discrete and the ADIRU AOA input and then conduct the stall warning
BITE test. During this test (approximately 10 seconds), the WARN ELEX
messages will be displayed and all segments of the BITE indicators will
illuminate. All computer functions, except RAM/ROM memories and all
interface components are tested. In addition the associated column shaker will
operate and the pitch limit indicator (PLI) will position at ten degrees on the
EADI. If installed the stall speed portion of the speed tape will display. If no
faults or anomalies are detected a software code will display for one second
then the configuration and option code will be displayed and the associated
stick shaker will operate until the test switch is released. The other SWC will
display code D9 during the test.
If faults exist the BITE will display the software code, then each fault code for 1
to 3 seconds in order of priority, with the highest priority fault remaining.
Interface anomaly faults will not be displayed if an on board (SWC) fault exists.
When a fault is detected the WARN ELEX messages remains after test switch
release. The stick shaker will not be activated.
CAUTION: IF BOTH TEST SWITCHES ARE ACTIVATED, WITH NO FAULTS,
ANY HYDRAULIC SYSTEM PRESSURIZED AND THE FLAPS/
SLATS RETRACTED, THE STICK NUDGER WILL CAUSE THE
ELEVATORS TO MOVE.
PITCH
LIMIT
INDICATOR
SPD
A/T
SPEED
TAPE
DISPLAY
180
G/S
FLARE
LOC
ROLLOUT CMD
F
160
140
SHAKER
SPEED
120
DH100
.730
150
GS
170
TEST
EADI DISPLAY (TYPICAL)
L
POWER
SUPPLY B
FAULTBALL
RESET SWITCH
B
A
LEFT STALL
RIGHT STALL
MISC TEST PANEL (P61)
RIGHT STALL
WARNING
COMPUTER
LEFT SWC FAULT RIGHT SWC FAULT
INDICATORS
INDICATORS
WARNING ELECTRONICS UNIT
(WEU) (P51)
STALL WARNING COMPUTER BITE
Page - 69
ATA 27-30
11/11/13
EFF - ALL
R
LEFT STALL
WARNING
COMPUTER
POWER SUPPLY STATUS
B767-3S2F
STALL
POWER
SUPPLY A
FAULTBALL
TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
B767-3S2F
Page - 70
ATA 27-40
11/11/13
EFF - ALL
TRAINING MANUAL
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STABILIZER CONTROLS AND INDICATORS
Stabilizer Trim Switches
Electrically signals the stabilizer to trim in the desired direction when
simultaneously pushed.
Alternate Stabilizer Trim Switches
Electrically signals the stabilizer to trim in the desired direction when
simultaneously pushed.
Stabilizer Trim Indicator
Indicates stabilizer position in UNITS of trim. Green band indicates allowable
TAKEOFF setting. OFF FLAG appears if trim indicator is INOP.
Stabilizer Trim Cutout Switches
NORM position allows hydraulic power to the stabilizer trim.
CUTOUT position shuts off respective hydraulic system power to the stabilizer
trim.
STAB TRIM Light
Illuminates when stabilizer is trimming at half the signaled rate.
UNSCHED STAB TRIM Light
Illuminates if the stabilizer moves opposite to elevator during autopilot
operations or during uncommanded stabilizer movement when autopilot is
disconnected.
MANUAL ELECTRIC
TRIM SWITCHES
STAB
TRIM
P5 OVERHEAD PANEL
- ANNUNCIATOR
PANEL
UNSCHED STAB TRIM (B)
STAB TRIM (C)
UNSCHED
STAB TRIM
FCC SWITCHES
UPPER EICAS DISPLAY
STAB TRIM (M)
CONTROL COLUMN
CUTOUT SWITCHES
LOWER EICAS DISPLAY
ALTERNATE
ELECTRIC
TRIM
SWITCHES
APL
NOSE
DN
S
T
A
B
T
R
I
M
APL
NOSE
UP
HYDRAULIC
CUTOUT
SWITCHES
POSITION
INDICATOR
CONTROL STAND
P10
POSITION
INDICATOR
SER
0
-CAUTION-
REMOVE THE FRONT PANEL
SLOWLY TO PREVENT DAMAGE
TO INTERNAL CABLE
MFR
2
4
6
8
10
12
MENU
ON/OFF
14
STABILIZER POSITION
INDICATOR (2) (P10)
YES
NO
YAW DAMPER/STABILIZER TRIM
MODULE (YSM)
P/N 285T1122SERIAL NUMBER
MOD
LEVEL
A
E
B
F
C D
G H
YSM (2)
STABILIZER CONTROLS AND INDICATORS
B767-3S2F
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B767-3S2F
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TRAINING MANUAL
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STABILIZER TRIM BLOCK DIAGRAM
Manual Electric Trim System
The control wheel stabilizer trim control switches provide up or down ARM and
CONTROL signals to the two yaw damp / stabilizer trim modules (YSM). The
YSMs provide up or down ARM and CONTROL signals to solenoids on the
stabilizer trim control modules (STCM). ARM AND CONTROL hydraulic valves
function in series and allow hydraulic flow to the two hydraulic motors and two
hydraulically released brakes on the stabilizer trim ball screw actuator
assembly. Two hydraulic cutout switches provide electrical power to the STCM
shutoff valve motors, isolating hydraulic power from the control modules.
Hydraulic inputs from the elevator feel computers control the rate of stabilizer
trim. The left and right limit switch and position transmitter modules provide
position feedback through Flap/Stabilizer Position Modules (FSPM) in the P50,
to the Flight Control Computers (FCC). The Position and Limit Switch Modules
also drive the flight compartment position indicators, and limit stabilizer travel by
cam actuated micro-switches which break the ARM electrical paths from the
YSM to the STCM. Column operated cutout switches also break the electrical
ARM paths from the YSM to the STCM when the control columns are moved in
a direction opposing stabilizer trim.
Autopilot Trim System (Autotrim)
One of three Flight Control Computers ( FCC ) provide autopilot input signals to
the YSM to trim the stabilizer based on elevator out of neutral position, using
only 1 motor (half speed). The function of the YSM, the STCM, the stabilizer
trim ballscrew actuator assembly and the limit switch and position transmitter
modules is identical to the manual electric system described above.
Alternate Electric Trim System
Two alternate trim switches provide ARM and CONTROL commands directly to
solenoids inside the STCM. The SCTM'S provide hydraulic pressure to release
the hydraulic brakes and drive the hydraulic motors to trim the stabilizer.
Mach Trim System
One of two YSM will automatically trim the stabilizer according to airspeed
signals from the Air Data Inertial Reference Units (ADIRU), located on shelves
E1-3 and E2-3 in the main electronic compartment. The
flap/stabilizer position modules, located in the P-50 card file, signal the YSM for
mach (flaps retracted) trim selection. Air/ground logic from the air/ground relays
inhibits mach trim on the ground. Any autopilot engagement also inhibits mach
trim.
Stabilizer Trim Fault Indication System
The YSM control the logic associated with flight compartment amber
annunciation the P5 pilot's overhead panel and the readout on EICAS. The
YSM can record Existing Faults on the status of various system LRUS.
HYDRAULICS
(L/C)
A POSITION
INDICATORS
STAB
TRIM
UNSCHED
STAB TRIM
ELEV FEEL
COMPUTER
P5 PANEL
MANUAL ELECTRIC
TRIM COMMANDS
HYDRAULIC
RELEASED
BRAKE (2) BALL SCREW
ACTUATOR
ASSY
EICAS COMPUTERS
STABILIZER
HYDRAULIC
MOTOR (2)
ADIRU (2)
COLUMN
CUTOUT
SWITCHES A
STCM (2)
FCC (3)
YSM (2)
FSPM (3)
LIMIT SWITCH AND
POSITION TRANSMITTER
MODULE (3)
STABILIZER TRIM BLOCK DIAGRAM
B767-3S2F
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ATA 27-40
11/11/13
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B767-3S2F
Page - 74
ATA 27-40
11/11/13
EFF - ALL
TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
STABILIZER TRIM CONTROL MODULE (STCM)
Operation
The STCM receive electric command inputs to control the porting of hydraulic
fluid to the stabilizer trim ballscrew actuator assembly hydraulic motors and
hydraulically released brakes.
Location And Access
There are two interchangeable STCM (right and left) mounted on the bulkhead
above the stabilizer ballscrew actuator assembly. Access to the STCM is
through the stabilizer service access door.
Components
There are seven hydraulic ports and four electrical connectors on each STCM.
There is a cleanable 100 micron in-line filter screen in the system pressure port.
There are four dual coil solenoid valve assemblies for nose up and nose down
ARM and CONTROL electrical inputs on each STCM. A pressure switch set at
750 to 1000 psi signals pressure to the hydraulically released brakes for use by
the digital stabilizer trim and aileron lockout modules (YSM). A 28 volt DC
motor operated shutoff valve, with manual override, controlled by the flight
compartment hydraulic cutout switches, is located on each STCM. Each STCM
has a manually operated bypass valve to test the brake reaction torque. The
test is performed by pressing a button protruding from the outside of the
module.
Maintenance Practices
Several of the components mounted on the two STCM are line replaceable
units. These include the four dual coil solenoid valves; the motor operated
hydraulic shutoff valve; the brake bypass test switch assembly, and the
hydraulic pressure switch assembly.
APL NOSE
DOWN PORT
ARM NOSE DOWN
SOLENOID
ARM NOSE UP
SOLENOID
CONTROL NOSE
DOWN SOLENOID
CONTROL NOSE
UP SOLENOID
APL NOSE
UP PORT
BRAKE
RELEASE
PORT
STABILIZER AFT COMPONENTS
PRESSURE
SWITCH
RETURN
PORT
FWD
MOTOR-OPERATED
SHUTOFF VALVE
(MANUAL OVERRIDE
NOT SHOWN)
STABILIZER TRIM CONTROL MODULE (STCM)
B767-3S2F
Page - 75
ATA 27-40
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TRAINING MANUAL
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BRAKE
BYPASS
BUTTON
B767-3S2F
Page - 76
ATA 27-40
11/11/13
EFF - ALL
TRAINING MANUAL
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STABILIZER HYDRAULIC CUTOUT SWITCHES
General Description
The hydraulic cutout switches control power to the hydraulic shutoff valves on
the STCMs. The valves stop hydraulic flow through the STCMs for maintenance
or in a runaway trim condition.
Cutout Switches and Shutoff Valves
Two guarded cutout switches are on the top left side of the control stand. The
shutoff valves on the lower side of each STCM operate by 28v dc electric
motors.
Operation
The left switch controls the shutoff valve on the left STCM. The right switch
controls the valve on the right STCM.
When the guard is down, the switches are in the NORM position, and the shutoff
valves are open. You put the cutout switches in the CUTOUT position to close
the shutoff valves.
Maintenance Practices
Access to the switch wiring is by removal of the fuel control panel.
The hydraulic cutout switches also do functional tests of the stabilizer trim
system. When the two cutout switches are in the CUTOUT position, hydraulic
power to the STCMs stops, and the stabilizer operation disables. When only
one cutout switch is in the CUTOUT position, the stabilizer operates at half
speed because only one hydraulic motor can move.
STABILIZER HYDRAULIC
CUTOUT SWITCHES
HYD SHUTOFF
VALVE (SOV)
CUT
OUT
28V DC
STBY
CLOSE
NORM
C STAB TRIM
OPEN
CUT
OUT
28V DC
STBY
SOV
R STAB TRIM CONTROL MODULE
NORM
L STAB TRIM
CLOSE
NORM
CUT
OUT
L
OPEN
C
STAB TRIM
SOV
L STAB TRIM CONTROL MODULE
STABILIZER HYDRAULIC CUTOUT SWITCHES
B767-3S2F
Page - 77
ATA 27-40
11/11/13
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B767-3S2F
Page - 78
ATA 27-40
11/11/13
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STAB TRIM LIMIT SWITCH AND POSITION TRANSMITTER
MODULES
General
Each module contains four cam actuated micro-switches, one synchro, and one
Rotary Variable Displacement Transducer (RVDT). Although all three modules
are identical and interchangeable, each services different functions as
determined by the wiring of the electrical connectors.
Limit Switches
Operation
A drum connected by a cable to the stabilizer drives each stabilizer trim limit
switch and position transmitter module. As the stabilizer moves, the cables
drive the drum which rotate the module input shaft.
Maintenance Practices
Access to the stabilizer trim and position transmitter modules is by opening the
access door to the stabilizer compartment.
These switches will interrupt the electrical trim signal to the hydraulic Stabilizer
Trim Control Modules (STCM) solenoids, providing the limits for electrical
stabilizer trim.
The three modules are line replaceable units and are interchangeable. No field
adjustment is required on the modules. Each module is replaced without
disturbing the cable drive system. The module spline shaft has a missing tooth
which is aligned with the missing tooth of the splined drum.
• The up limit switch will open at 1.5 units (flaps down) or 0.5 units (flaps up)
of trim.
• The down limit switch will open at 13 units (300) of trim.
The cables are rigged with the stabilizer set to a specific position and the drums
positioned by rig pins.
Greenband Switch
The switch provides a signal (switch closed) to the configuration warning card
when the stabilizer is within the takeoff trim limits. Outside of these limits, the
switch will open and the appropriate configuration warning will be annunciated if
the plane is in a Takeoff configuration.
0.25 to 7.0 units of trim is available.
RVDT
The RVDT sends an AC voltage signal, corresponding to stabilizer position, to
the flap/stabilizer position module (FSPM) in the P-50 card file for conversion to
a usable DC signal for various digital user systems.
Synchro
The synchro signals stabilizer position to the flight compartment position
indicators and the Flight Data Recorder.
STABILIZER
PIVOT POINT
STABILIZER
CENTER
SECTION
STABILIZER TRIM
CONTROL MODULES
HYDRAULIC
BRAKES (2)
STABILIZER TRIM
CONTROL MODULES
STABILIZER TRIM
BALLSCREW ACTUATOR
ASSEMBLY
HYDRAULIC
MOTORS (2)
LIMIT SWITCH AND
POSITION TRANSMITTER
MODULES (3)
STABILIZER TRIM
BALLSCREW ACTUATOR
ASSEMBLY
L
COMPONENT
C
FUNCTION
R
COMPONENT FUNCTION
COMPONENT FUNCTION
SWITCH 1
UP LIMIT
SWITCH 1
NOT USED
SWITCH 1
UP LIMIT
SWITCH 2
UP LIMIT
SWITCH 2
NOT USED
SWITCH 2
UP LIMIT
SWITCH 3
NOT USED
SWITCH 3
DOWN LIMIT
SWITCH 4
GREEN
BAND
SWITCH 4
NOT USED
SWITCH 3
DOWN LIMIT
NOT USED
SWITCH 4
RVDT
FSPM ( L)
SYNCHRO
CAPT IND &
FLT DATA REC
RVDT
SYNCHRO
ELECTRICAL
CONNECTOR
STABILIZER
TORQUE BOX
FSPM (C)
NOT USED
ELECTRICAL
CONNECTOR
RVDT
FSPM (R)
SYNCHRO
F/O
INDICATOR
FWD
ELECTRICAL
CONNECTOR
LIMIT SWITCH AND
POSITION TRANSMITTER
MODULE (3)
(VIEW LOOKING FORWARD)
STAB TRIM LIMIT SWITCH AND POSITION TRANSMITTER MODULES
B767-3S2F
Page - 79
ATA 27-40
11/11/13
EFF - ALL
TRAINING MANUAL
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LIMIT SWITCH
AND POSITION
TRANSMITTER
MODULES (3)
B767-3S2F
Page - 80
ATA 27-50
11/11/13
EFF - ALL
TRAINING MANUAL
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HIGH LIFT DEVICES
Introduction
The high lift devices include the trailing edge flaps and leading edge slats
systems. The high lift devices are extended to improve wing lift and drag
characteristics for takeoff and landing operations and to provide increased stall
operating margins.
There are four trailing edge flaps which have six operating positions. The
inboard flaps have main and aft sections and are double slotted when fully
extended. The outboard flaps have one section and are always single slotted
when extended.
There are twelve leading edge slats which have three operating positions. A
krueger flap, extending from the bottom of the wing, operates with the inboard
leading edge slats.
Operation
The leading edge slat and trailing edge flap systems are usually operated
together by the flap control lever. The trailing edge flaps are operated by one
drive system and power drive unit (PDU) with two rotary actuators at each flap.
The leading edge slat system has separate drives for the inboard and outboard
devices with the two inboard slats operated by one drive and PDU, and the ten
outboard slats operated by another drive and PDU. There are two rotary
actuators at each slat.
A flap/slat electronic unit (FSEU) provides position indication, failure protection
and control functions. A flap/slat shutoff valve module is controlled by the FSEU
to sequence flap and slat operation. The FSEU also provides separate flap and
slat alternate operation for non-normal high lift systems operation.
High Lift Configurations
The flaps and slats are controlled by the flap control lever during primary
(hydraulic motor) operation and by the alternate flap selector and arm switches
during alternate (electric motor) operation. Alternate operation is about six
times slower than normal operation. The flap lever and alternate position
selector switch have positions showing units of trailing edge flap extension. The
trailing edge flaps are retracted at both the up and one positions of the lever or
switch. The leading edge slats have three positions of retracted (up),
intermediate (takeoff/sealed), extended (landing/gapped) and operate between
lever, or switch, positions of up to one and 20 to 25.
The inboard and outboard flaps and inboard and outboard slats have different
degrees of extension at each position. The inboard and outboard slats have
different operating times due to large differences in the amount of extension at
the intermediate and full extension positions.
The alternate position selector switch has a NORM (normal) position which
does not provide an output command.
This is a safety position to prevent inadvertent alternate drive operation in event
either arm switch is actuated and flap or slat position disagrees with the selector
switch.
The Flap/Slat Electronics Unit controls the Interlock/Sequencing between the
Flaps and Slats as follows:
• Initial Hydraulic Extension: slats extend to take-off position then flaps
extend
• Last Hydraulic Retraction: flaps must fully retract then slats will Retract
from take-off to up position
• Initial Electric Extension: no interlock
• Last Electric Retraction: flaps must fully retract then Slats will retract
from take-off to up position
KRUEGER SEAL
FLAP
INBOARD DOUBLE
SLOTTED FLAP
OUTBOARD SINGLE
SLOTTED FLAP
INBOARD LEADING
EDGE SLAT
OUTBOARD LEADING
EDGE SLAT
HIGH LIFT DEVICES
B767-3S2F
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B767-3S2F
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FLAPS CONTROL AND INDICATION
TE Flap Control And Indication
The flap control lever provides control during primary (hydraulic motor)
operation of the flap system. Alternate (electric motor) operation is controlled
by the ALTN FLAPS position selector and arm switches. Two needles on the
flap position indicator show left and right wing flap drive positions. Flap drive
position is shown in units with indicated airspeed (IAS) limits shown for each
extended position.
A TRAILING EDGE amber light, master CAUTION lights and EICAS caution
alert, advisory alert, status and maintenance messages show flap system faults.
LE Slat Control And Indication
The flap lever provides control during primary (hydraulic motor) operation of the
slat system. Alternate (electric motor) operation is controlled by the ALTN
FLAPS position selector and LE arm switches. Two needles on the flap position
indicator show slat position at the up and one unit positions.
A LEADING EDGE amber light, master CAUTION lights and EICAS caution,
and status and maintenance messages show slat system faults.
TRAILING
EDGE
LEADING
EDGE
TE FLAP ASYM (B)
TE FLAP DISAGREE (B)
FLAP LOAD RELIEF (C)
FLAP LIMIT (IAS)
220K
240K
210K
5
1
15
UP
FLAPS
20
FLAP/SLAT ELEC (S,M)
195K
25
TE FLAP SHUTDOWN (S,M)
30
190K
162K
ALTN FLAPS
5
1
15
EICAS DISPLAY UNITS (P2)
1 UNIT (GATE)
5 UNIT
15 UNIT
20 UNIT (GATE)
FLAP LEVER
0 (FLAPS UP)
25 UNIT
30 UNIT
(FLAPS AND SLATS
FULLY EXTENDED)
FWD
Page - 83
ATA 27-50
11/11/13
POSITION
SELECTOR
20
NORM
25
30
LE
ALTN
TE FLAP
ARM SW
FLAPS CONTROL AND INDICATION
B767-3S2F
UP
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TE
ALTN
B767-3S2F
Page - 84
ATA 27-50
11/11/13
EFF - ALL
TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
FLAPS GENERAL DESCRIPTION
Introduction
Two trailing edge flaps are mounted on each wing. The inboard flaps are
double slotted and the outboard are single slotted. A single power drive unit
(PDU) powers eight rotary drive actuators (two on each flap assembly) through
gearboxes and drive shafts.
Control of primary (hydraulic) flap operation is by a flap control lever connected
by cables to the flap aft quadrant. A load relief (alleviation) actuator is
connected to the PDU input linkage to limit extension if airspeed limits are
exceeded at landing flap settings.
A flap slat electronic unit (FSEU) controls position indicating, failure protection
and alternate (electric) operations. Position transmitters on the flap drive
actuators and flap control lever are used by the FSEU for its control functions.
The FSEU controls the flap/slat shutoff valve module to sequence flap and slat
drive operation and to remove hydraulic pressure to the PDU during cruise flight
operations.
FLAP
INDICATION
FLIGHT
DECK
OUTBD
FLAP
ALT POS
SELECT SW
EICAS
FLAP LEVER
INBD
FLAP
FSPM (3)
ALT ARM
SW
MEC
FLAP LEVER
POSITION
TRANSMITTERS
(2)
SLAT AFT
QUADRANT (REF)
DRIVE SHAFT
FLAP LOAD
RELIEF ACTUATOR
FSEU
FLAP AFT
QUADRANT
OUTBOARD
MAIN FLAP
FLAP/SLAT
SHUTOFF
VALVE MODULE
INBOARD MAIN
FLAP SECTION
GEARBOX
FLAP POWER
DRIVE UNIT
INBOARD AFT
FLAP SECTION
ROTARY
ACTUATOR (8)
FLAP POSITION
TRANSMITTERS
(8)
FLAPS GENERAL DESCRIPTION
B767-3S2F
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ATA 27-50
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B767-3S2F
Page - 86
ATA 27-50
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TRAINING MANUAL
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FLAP PRIMARY DRIVE CONTROL
Operation
The hydraulic motor on the flap power drive unit (PDU) is the primary power
source for the flap drive. Inputs to the PDU control unit for hydraulic motor
operation are from cables and control rods operated by the flap control lever or
by operation of the control rods by the flap load relief actuator. Drive shaft
operation of the control unit provides hydraulic motor shutdown at the
commanded position (closed loop). Cables from the flap control lever are
routed through the forward cargo compartment to a flap aft quadrant in the aft
cargo compartment. A control rod from the quadrant extends through the right
wheel well aft wall. Controls shafts connect the control rod to the PDU.
Turnbuckles are provided at two locations for cable rigging.
Flap Control Lever
The spring loaded flap lever has seven detent positions.
The detents show units of primary drive command input. Gates at the 1 and 20
unit positions prevent lever movement directly through these positions. These
gates show lever positions for critical flap and slat configuration changes during
flight operations.
Two rotary variable differential transformers (RVDT) are operated by a flap lever
gearbox in the control stand. RVDT number 1 inputs flap lever position to flap
slat electronic unit (FSEU) section 2 and RVDT number 2 to inputs FSEU
section 1.
Flap Detent
Degrees
1
0
5
13.8
15
20.0
20
25.4
25
35.0
30
41.4
CABLES
(RIGHT SIDE
UNDER FLOOR)
LOAD RELIEF
ACTUATOR
PDU
TURNBUCKLES
(2 LOCATIONS)
(AFT CARGO COMPT)
FLAP
LEVER
FLAP AFT
QUADRANT
SLAT AFT
QUADRANT
(REF)
FLAP LOAD
RELIEF
ACTUATOR
ND
TE
X
E
FLAP
LEVER
FWD WALL OF AFT
CARGO COMPT
CONTROL
RODS
CABLES
FWD
FLAP LEVER
QUADRANT
CABLES
POWER DRIVE UNIT
(RIGHT WHEEL WELL - AFT BULKHEAD)
FLAP PRIMARY DRIVE CONTROL
B767-3S2F
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TRAINING MANUAL
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B767-3S2F
Page - 88
ATA 27-50
11/11/13
EFF - ALL
TRAINING MANUAL
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FLAP POWER DRIVE UNIT (PDU)
General
The trailing edge flap power drive unit (PDU) is on the aft bulkhead of the right
main gear wheel well. Hydraulic and electric motors are installed on a gearbox
which operates the left and right wing drive shafts. Primary operation is by the
hydraulic motor, alternate operation is by the electric motor. A control unit and
control valve module with bypass valve, control pressure to the hydraulic motor.
Maintenance Practices
A tool can be installed on the PDU to lock the gearbox so the flap drive cannot
be operated with either the hydraulic or the electric motor.
LOAD
RELIEF
MECHANISM
(REF)
HYDRAULIC
MOTOR
GEARBOX
ASSEMBLY
CONTROL RODS
GEARBOX
ASSEMBLY
ELECTRIC
MOTOR
UP POSITION
HYDRAULIC
MOTOR
PILOT
INPUT ARM
PDU GEARBOX
ASSEMBLY
DRIVE
SHAFT
CONTROL
UNIT
OUTPUT
ARM
UP
POSITION
CONTROL
UNIT
CONTROL
UNIT
CONTROL
VALVE
MODULE
UP POSITION
CONTROL
VALVE
MODULE
CONTROL VALVE
INPUT ARM
INBD
TE FLAP PDU
(LOOKING AFT)
PDU LOCK
OUTBD
Page - 89
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EFF - ALL
FWD
TE FLAP PDU
(RIGHT WHEEL WELL, AFT BULKHEAD)
FLAP POWER DRIVE UNIT (PDU)
B767-3S2F
BALL
LOCKPIN
TRAINING MANUAL
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B767-3S2F
Page - 90
ATA 27-50
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EFF - ALL
TRAINING MANUAL
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FLAP PDU COMPONENTS
PDU General
The major components of the flap power drive unit (PDU) are hydraulic and
electric motors; gearbox; control unit; and control valve module with control and
bypass valves.
Control Unit
The control unit input cam is operated by an internal input crank connected to
the pilot input arm. The follow up cam is operated by a quill shaft driven by the
PDU gearbox. A summing lever, operated by both cams through cam followers,
operates a control unit output arm and input rod to the control valve module.
Operation of the primary control system moves the input cam, with the follow-up
cam held by the gearbox, causing the summing lever to input to the control
valve. Operation of the gearbox drives the follow-up cam with the input cam
held by the flap control lever in detent, with the summing lever nulling the
control valve when the drive reaches the commanded position. There is a rig
pin hole for each cam defining their neutral positions.
Control Valve Module
The control valve module has control and bypass valves. The control valve
provides center hydraulic system pressure to a reversible hydraulic motor
through the bypass valve. The bypass valve has a manual override lever which
also shows the valve position. The bypass valve shuts off pressure to the
hydraulic motor and opens both ports of the motor to center hydraulic system
return. The valve is moved from the normal position "two" to bypass position
"one" during electric motor operation, to remove the hydraulic motor lock on the
gearbox, and during flap system faults to shut down primary control operation.
CONTROL
VALVE MODULE
CONTROL UNIT
INPUT CAM
PRESS
SUMMING
LEVER
UP
PILOT
INPUT ARM
RETURN
DN
NUL
FOLLOW-UP
CAM
FSEU/
ALT ARM
SW
CONT VALVE
ELECTRIC HYDRAULIC
MOTOR
MOTOR
BYPASS
NORM
BYPASS VLV UP
GEARBOX
DN
C1 C2
CD
DRIVE
SHAFT
CONTROL
UNIT
CD
NORM
CLOSED
HYDRAULIC MOTOR
ALTERNATE DRIVE
ELECTRIC MOTOR
(ARROWS = EXTEND)
GEARBOX
DRIVE SHAFT
CONNECTION
CONTROL UNIT
OUTPUT ARM
OPEN
BYPASS
C SYS
HYDRAULIC
RETURN PORT
BYPASS
VALVE
C SYS
HYDRAULIC
PRESSURE PORT
CONTROL VALVE
MODULE INPUT
ROD
MANUAL
OVERRIDE
LEVER
BYPASS
VALVE
HYDRAULIC MOTOR
CASE DRAIN
HYDRAULIC
MOTOR RETURN
HYDRAULIC
MOTOR PRESSURE
CONTROL
VALVE MODULE
INBD
TE FLAP PDU
(LOOKING AFT)
CONTROL VALVE MODULE
FLAP PDU COMPONENTS
B767-3S2F
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B767-3S2F
Page - 92
ATA 27-50
11/11/13
EFF - ALL
TRAINING MANUAL
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FLAP/SLAT SHUTOFF VALVE MODULE
Description
The flap/slat shutoff valve module provides center hydraulic system pressure to
the flap and slat power drive units (PDU). The module has a priority valve, a
flow regulator, and flap and slat solenoid-operated shutoff valves. The module
is installed on the aft bulkhead in the right main gear wheel well, outboard of the
PDU.
The priority valve permits flow only when center hydraulic pressure exceeds
1200 psi. The flow regulator, installed downstream of the priority valve, limits
hydraulic flow to the flap and slat hydraulic motors to regulate maximum motor
speed to control the rate of flap and slat extension or retraction. The flow
regulator provides a maximum flow of 24 gpm.
The flap solenoid-operated shutoff valve depressurizes the hydraulic motor
when the flaps are retracted and for flap/slat interlock (sequencing). The valve
is spring-loaded open and electrically closed by flap/slat electronic unit (FSEU)
control signals.
The slat solenoid-operated shutoff valve depressurizes both PDU hydraulic
motors when the slats are in the commanded position and on retraction until the
trailing edge flaps are retracted (interlock). The valve is spring-loaded open and
electrically closed by flap/slat electronic unit (FSEU) control signals.
C HYDRAULIC
SYSTEM
FLOW
REGULATOR
FROM FLAP
POWER DRIVE UNIT
RTN
PRESS
FLAP LOAD
RELIEF
ACTUATOR (REF)
PRIORITY
VALVE
FSEU
TE FLAP
PDU (REF)
SLAT
SOLENOID
VALVE
RIGHT WHEEL WELL
AFT BULKHEAD
SLAT SHUTOFF
VALVE
FLAP SOLENOID
VALVE
SLAT SOLENOID
VALVE (REF)
FSEU
FLAP
SOLENOID
VALVE
C2
TO SLAT
POWER
DRIVE UNITS
C1
FLAP SHUTOFF
VALVE
TO FLAP
POWER
DRIVE UNIT
RETURN
PRESSURE
FLAP SHUTOFF
VALVE
SLAT SHUTOFF
VALVE (REF)
C HYD SYSTEM
PRESSURE PORT
VALVE PRIORITY
FLAP
PRESSURE
FLOW REGULATOR
FLAP/SLAT SHUTOFF
VALVE MODULE
C HYD SYS
RETURN PORT
FLAP / SLAT SHUTOFF VALVE MODULE
B767-3S2F
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TRAINING MANUAL
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TOP VIEW
SLAT
PRESSURE
B767-3S2F
Page - 94
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TRAINING MANUAL
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FLAP ROTARY ACTUATOR
General Description
The wing rotary actuators are installed in two support ribs mounted in the spoiler
beam or wing rear spar. Three mounting brackets hold the actuator which is
installed using a missing tooth reference on a reaction ring on a support rib.
The actuator output shaft is splined into a drive shaft installed in the support
ribs. The drive shaft is connected to a flap drive arm. A flap position transmitter
is mounted on the opposite side of the support ribs. The flap transmitter drive
frame tangs fit in channels in the splined drive shaft, causing the drive frame to
rotate with the drive shaft/drive arm and operate the transmitter.
A torque limit indicator pivots out of spring clips if the actuator torque limit is
exceeded.
SPOILER
BEAM
ACTUATOR MOUNTING
BRACKET (3)
SUPPORT
RIBS
REACTION
RING (SPLINED)
DRIVER FRAME
TANGS (2)
(FIT IN CHANNELS
IN SPLINED
DRIVE SHAFT)
SUPPORT
RIBS
TRANSMITTER
DRIVER FRAME
FLAP
LINKAGE
ATTACH
POINTS
FLAP DRIVE
ARM
FLAP
TRANSMITTER
SPLINED
DRIVE
SHAFT
ACTUATOR
OUTPUT
SHAFT
TRANSMITTER
HOUSING MOUNTING
FRAME
TRANSMITTER
SUPPORT
BRACKETS
ACTUATOR
MOUNTING
BRACKET
ACTUATOR
(3)
FLAP
DRIVE
ARM
OUTBD
REDUCTION
GEAR
OUTPUT RING
GEAR
INPUT SHAFT
TORQUE
LIMITER
TRIP GEAR
(DISK)
OUTPUT
SHAFT
TORQUE LIMIT
INDICATOR
FWD
ACTUATOR 3 INSTALLATION
(ACTUATOR 6 SIMILAR)
TORQUE
LIMITER
TRIP GEAR
(DISK)
FIRST GEAR
INPUT
SHAFT
NO-BACK BRAKE
TORQUE
LIMITER
TORQUE LIMIT INDICATOR
INDICATOR
RETAINING CLIP
(BOTTOM HALF)
(HOLDS TORQUE
LIMITER INDICATOR)
FLAP ROTARY ACTUATOR
B767-3S2F
Page - 95
ATA 27-50
11/11/13
STRUCTURALLY
MOUNTED REACTION
RING (MISSING
TOOTH REFERENCE)
EFF - ALL
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B767-3S2F
Page - 96
ATA 27-50
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TRAINING MANUAL
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INBOARD FLAPS
Flap Inboard Drive
The inboard flap inboard drive mechanisms are in the aft body fairings with the
other six drive mechanisms in fairings on each wing. The flap support tube,
extending outboard through the fairing, is attached to a track roller carriage
mounted on a support track. Forward, mid and aft fairing doors are operated by
drive rods to close the opening in the fairing when the flaps are retracted or fully
extended. The door driver rods are connected to bell cranks operated by a door
actuation cam track. The forward and aft doors, operated by the upper drive
rod, are spring loaded closed. When the flaps are retracted the forward door is
held open by the flap support tube with the mid and aft doors closed. All doors
are open when the flaps are not fully retracted or extended. When the flaps are
fully extended the aft door is held open by the flap support tube with the mid and
forward doors closed.
The rotary actuator drive arm operates drive arms and linkage to move the flap
section. Only the inboard flap drive mechanisms have roller carriages and
support tracks, the other drive mechanisms use only the linkage for support.
Flap Outboard Drive
The inboard flap outboard drive mechanism is in a three section fairing on the
wing structure. The rotary actuator in the support structure, operates drive arms
and linkage connected to the main flap. A support beam holds the flap sections
and drive mechanism.
The aft flap is operated by two pushrods, two bell cranks and a cam in the
fairing. As the main flap extends, the forward bell crank, attached to support
structure, pivots to push on the forward pushrod. This pivots the aft bell crank,
mounted on the main flap, which pulls on the aft pushrod to rotate the cam
counterclockwise. The cam roller, on the aft flap, then moves on the lower cam
lobe which is concentric with the cam pivot point and the aft flap remains faired
to the main flap. As the main flap approaches full extension, the forward bell
crank pulls on the control rod causing the aft bell crank to push on the aft
pushrod and rotate the cam clockwise. The roller then moves up on the
non-concentric upper cam lobe pushing the aft flap away from the main flap.
This occurs as the flap fully extend from 25 to 30 units. The aft flap drive
operates a slave rod assembly in the main flap connected to the other end of
the aft flap. This drives both ends of the aft flap evenly to the gapped position.
The aft flap is supported by two deflection control tracks, attached to the main
flap aft spar, that ride on rollers in recesses in the aft flap.
4
3
6
5
2
1
MID-DOOR OUTLINE
RETRACTED
(DOOR CLOSED)
SUPPORT
FWD/AFT DOOR
FWD-DOOR OUTLINE
TRACK
DRIVE ROD
FLAP SUPPORT
(DOOR CLOSED)
TUBE
AFT-DOOR OUTLINE
3
(DOOR OPEN)
DRIVE
ARM
4
TRACK ROLLER
CARRIAGE
5
6
MID-DOOR
DRIVE ROD
1
MAIN FLAP
LINK
DOOR
ACTUATION
CAM TRACK
2
ACTUATOR
DRIVE
DOOR DRIVE
BELL CRANKS
FULLY EXTENDED
INBOARD FLAP
B767-3S2F
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TRAINING MANUAL
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AFT
FLAP
B767-3S2F
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OUTBOARD FLAP
The outboard flap is driven by two rotary actuators. Each actuator rotates a
drive arm which operates drive arms and links to move the flap. A flap
deflection control track and rollers are installed at the outboard end of the flap to
prevent flap deflection from the wing. A roller on the inboard end of the flap
engages in a fishmouth slot in the wing structure to prevent flap deflection when
the flap is retracted.
An aerodynamic fairing covers both outboard flap mechanisms. The fairing
consists of three sections.
DEFLECTION CONTROL
CARRIAGE AND TRACK
REAR
SPAR
FISHMOUTH SLOT
(IN STRUCTURE)
TRACK
ROLLERS
(ON STRUCTURE) (ON CARRIAGE)
FLAP
(RETRACTED)
OUTBOARD FLAP
(EXTENDED)
ROLLER
(ON FLAP)
CARRIAGE
(ON FLAP)
REAR SPAR
INBOARD END
ACTUATOR
SUPPORT RIB
FLAP
(EXTENDED)
DEFLECTION CONTROL TRACK
(ON WING)
MAIN FLAP
ASSEMBLY
ACTUATOR
SPOILER
FWD FAIRING
SECTION
CENTER FAIRING
SECTION
AFT FAIRING
SECTION
DRIVE ARM
FLAP RETRACTED
FLAP EXTENDED
OUTBOARD FLAP
B767-3S2F
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B767-3S2F
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TRAINING MANUAL
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FLAPS / SLAT ELECTRONIC UNIT (FSEU)
General
The Flap / Slat Electronics Unit (FSEU) is the primary electronic control unit in
the high lift system. It provides sequencing control, failure/asymmetry
protection, system annunciation outputs, and flap load relief. During the
alternate mode of operation, it does closed loop flap/slat positioning function.
The FSEU can help you find and isolate a failure in the TE flap system and the
LE flap and slat system. Front panel BITE on the FSEU gives you an interface
with the BITE functions in the FSEU.
The FSEU has a BITE panel with six switches. These are the functions of each
switch:
•
•
•
•
ON/OFF - starts or stops BITE display
MENU - shows the menu
YES or NO - response to question
Down arrow or up arrow - scrolls through menu or results
If you do not push a switch on the FSEU BITE panel in 5 minutes, the FSEU
stops the BITE function and puts the display off.
These are the items in the main menu of the FSEU BITE:
•
•
•
•
EXISTING FAULTS?
FAULT HISTORY?
GROUND TESTS?
OTHER FUNCTIONS?
EXISTING FAULTS?
The EXISTING FAULTS selection shows existing faults in the system and does
a check of the interfaces to the FSEU.
FAULT HISTORY?
The FAULT HISTORY? selection shows past faults by flight leg. This fault data
is in the non-volatile memory (NVM) in the FSEU.
GROUND TESTS?
The GROUND TESTS? selection lets you do these tests:
•
•
•
•
TE flap load relief actuator test
TE flap load relief system test
Sensor checks
Display test
OTHER FUNCTIONS?
The OTHER FUNCTIONS? selection lets you do these functions:
•
•
•
•
LRU configuration
Input/output monitor
Change FSEU output discretes
Erase faults
SECTION 1
- FLAP SHUTOFF VALVE CONTROL
- BYPASS VALVE CONTROL
- FLAP LOAD RELIEF CONTROL
- UNCOMMANDED MOTION DETECTION
AND SHUTDOWN
- ASYMMETRY/SKEW DETECTION AND
SHUTDOWN
SECTION 2
- FLAP DISAGREE DETECTION
- FLAP LOAD RELIEF FAILURE
DETECTION
- MONITOR/ANNUNCIATION
CONTROL
- OUTPUT HYDRAULIC DEMAND
DISCRETE
BITE INSTRUCTIONS:
Push ON/OFF to start or end BITE display.
Push YES or NO to reply to questions(?).
Push to move down in list.
Push to move up in list.
Push MENU to return to previous menu.
BITE MAIN MENU:
MENU
ON
OFF
YES
NO
EXISTING FAULTS-Shows existing faults.
FAULT HISTORY-Shows past faults by
flight leg.
GROUND TESTS-Shows list of ground tests.
OTHER FUNCTIONS-Shows other functions.
FLAP/SLAT ELECTRONIC UNIT
P/N 285T0049SER NO.
MOD LEVEL
FMG DATE
CAGE CODE 81205
MFR
SER
PMR
MOD
FSEU
FLAP / SLAT ELECTRONIC UNIT (FSEU)
B767-3S2F
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SECTION 3
- ALTERNATE MODE CONTROL
B767-3S2F
Page - 102
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TRAINING MANUAL
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FLAP SYSTEM INTERFACE
Hydraulic Motor Operation
Failure protection shutdown, flap/slat sequencing, long-term pressure shutoff,
and load relief during hydraulic motor operation are provided by flap slat
electronic unit (FSEU) section 1 through control of the flap shutoff valve, load
relief actuator and bypass valve. These control functions require inputs from a
flap lever rotary variable differential transformer (RVDT), a flap position
transmitter RVDT (from a Flap stabilizer position module (FSPM)), flap position
transmitter resolvers and slat power drive unit (PDU) RVDTs. Alternate arm
switch input inhibits failure protection shutdown and load relief functions in
FSEU 1.
Electric Motor Operation
FSEU section 3 controls the electric motor using inputs from the alternate flap
selector switch and a flap position transmitter RVDT (from a FSPM). The flap
alternate arm switch operates the PDU bypass valve and engages the electric
motor clutch.
Position Indication
Flap position transmitter syncros operate the flap indicator syncros. FSEU
section 3 controls a flap reference transfer relay using inputs from a flap position
transmitter RVDT (from a FSPM) and slat PDU RVDT.
Fault Annunciation
A fault light and messages are control by FSEU section 2 using inputs from a
flap lever RVDT, alternate arm and position selector switches, flap position
transmitter RVDT (from a FSPM) and slat position (from FSEU sections 1 and
3). FSEU section 1 controls a single fault message and inputs to section 2 for
existing faults.
CENTER
HYD SYS
TRAILING
EDGE
LEADING
EDGE
FLAP LIMIT (IAS)
220K
240K
1
FLAP
LEVER
210K
5
15
UP
FLAPS
20
30
FLAP/SLAT
SOV MODULE
CONTROL
VALVE
195K
25
190K
RVDT (2)
162K
B
ALTN FLAPS
5
1
15
UP
LOAD
RELIEF
ACTUATOR
EICAS
20
NORM
30
HYDRAULIC
ELECTRICAL
MECHANICAL
ARINC 429
SHUTOFF
VALVE
25
LE
TE
ALTN
ALTN
ADIRU
- ADP LOGIC
BYPASS
VALVE
A
E
FLAP
DRIVE
- ECS
A
- CNFIG WARN
C
HYDRAULIC
MOTOR
FDR
TE FLAPS
GEAR
BOX
PSEU
D
ROTARY
ACTUATORS
C
ELECTRIC
MOTOR
FLAP REF
XFR RLY
RVDT (4)
INBD/OUTBD
SLAT PDU
E
FLAP PDU
FSEU
B
FLAP SYSTEM INTERFACE
B767-3S2F
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CLUTCH
FSPM
L/C/R
FLAP XMTR
ASSEMBLY
D
B767-3S2F
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FLAP HYDRAULIC OPERATION
Flap control lever, or load relief actuator, operation of the power drive unit (PDU)
control unit input cam, moves the control valve module control valve from the
null position. Center hydraulic system pressure is then provided to the hydraulic
motor through the control valve module bypass valve. Flap drive shaft rotation
operates the control unit follow-up cam to return the control valve to null. When
the control valve is at null and the bypass valve is at normal, there is a hydraulic
lock on the motor to hold the gearbox and flap drive.
Hydraulic pressure to the motor can be shutoff by the Flap/Slat Shutoff Valve
module flap shutoff valve or by the bypass valve in the PDU control valve
module. .
Pressure is shutoff to the motor as follows using the Flap/Slat Shutoff Module:
• The flap solenoid valve is powered by the flap/slat electronic unit (FSEU) to
close the flap shutoff valve when the flaps and flap lever are up or, on
extension, until the leading edge slats have moved to their intermediate
position.
• If pressure is shutoff at the Flap/Slat Shutoff Valve Module the hydraulic
lock remains on the motor
Pressure is shutoff to the motor as follows using the Bypass valve:
• The bypass valve is positioned to bypass when the alternate flap system
arm switch is actuated or by the FSEU during flap system failure.
• If pressure is shutoff by the bypass valve the motor can be rotated by the
gearbox.
C HYDRAULIC
SYSTEM
FSEU
SLAT
SOLENOID
VALVE
SLAT
SHUTOFF
VALVE
PRESS
FLOW
REG
PRIORITY
VALVE
RETURN
FSEU
FLAP
SOLENOID
VALVE
C1
C2
TO SLAT POWER
DRIVE UNITS
FLAP
SHUTOFF
VALVE
CONTROL
VALVE
MODULE
INPUT CAM
PRESS
CONT UNIT
ASSY
RETURN
DN
UP
PILOT INPUT
ARM
OPEN
BYPASS
NUL
FSEU/
ALT ARM
SW
CONT VALVE
BYPASS
SUMMING LEVER
BYPASS VLV UP
FOLLOW-UP
CAM
DN
C1 C2
CD
QUILL SHAFT
(WORM GEAR)
GEARBOX
LEGEND
PRESSURE
RETURN
B767-3S2F
(ARROWS = EXTEND)
ATA 27-50
11/11/13
EFF - ALL
CD
NORM
CLOSED
HYDRAULIC MOTOR
DRIVE SHAFT
ALTERNATE DRIVE
ELECTRIC MOTOR
FLAP HYDRAULIC OPERATION
Page - 105
NORM
TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
B767-3S2F
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ATA 27-50
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EFF - ALL
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FLAP LOAD RELIEF MECHANISM
The flap load relief (alleviation) mechanism is on the aft wall of the right wheel
well above the Power Drive Unit (PDU). The mechanism is comprised of a bell
crank and electric actuator connected to two control rods which operate the pilot
input arm of the PDU control unit.
When the actuator is retracted the control rods are aligned between the aft
quadrant crank and pilot input arm. When the actuator is extended, the bell
crank moves the control rods out of alignment, pulling up on the pilot input arm.
This inputs to the control unit and control valve to position the flap drive to 20
units with the lever at 25 or 30 units.
The actuator in controlled by the Flap Slat Electronic Unit (FSEU).
AFT QUAD CRANK
(LEVER 30)
LOAD RELIEF
ACTUATOR
INPUT RODS
(FLAPS 30)
AFT QUADRANT
CRANK (LEVER UP)
INPUT SHAFT
FROM TE FLAP
AFT QUADRANT
AFT QUADRANT
CRANK UP STOP
(FLAP 20)
LOAD RELIEF
BELLCRANK
LOAD RELIEF
ACTUATOR
CONTROL
RODS
PILOT
INPUT ARM
IN LOAD RELIEF
LOAD RELIEF MECHANISM
FLAP LOAD RELIEF MECHANISM
B767-3S2F
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B767-3S2F
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ATA 27-50
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FLAP LOAD RELIEF SYSTEM
General Description
The load relief (alleviation) system prevents excessive air loads on the flaps by
automatically limiting flap extension when airspeed is too high for flaps 25 or 30.
The system will limit flap position to a maximum of 20 units when the airspeed
equals or exceeds 172.5 knots with the flap lever at 30 units or 182.5 knots with
the flap lever at 25 units. Operation requires a valid airspeed input from either
Air Data Inertial Reference Unit (ADIRU).
Load relief system operation is inhibited when:
•
•
•
•
Alternate Flap System is ARMED
Center Flap Stabilizer Position Module (FSPM) failure
Flap lever transmitter (RVDT) failure
Loss of 26 volt ac power supply
Load relief operation is latched after actuation and is reset by reduction in
airspeed to 168.5 knots for flap extension to 30 units and to 178.5 knots for
extension to 25 units. Airspeed must be valid from either ADIRU to reset. If
both ADIRUs are invalid the latches can be reset by moving the flap lever to 25
or 20 units.
The only indication during flap load relief is the position indicator needles
indicating flap movement.
The trailing edge amber light and the FLAP LOAD RELIEF advisory message
will illuminate if the system fails when load relief is required. Disagreement
annunciation between flap lever and flap position and the flap failure protection
shutdown system are inhibited during load relief operation.
Load relief operation is controlled by Section 1 of the FSEU, fault annunciation
is controlled by section 2.
A FLAP LOAD RELIEF (C) message is displayed, when there is a failure of the
flaps to relieve from 30 to 25 units. FSEU section 2 provides the fail input for
the EICAS computers, and illuminates the TRAILING EDGE light. If the flaps fail
to return to 30 from 25 units when the airspeed decreases below 168.5 knots,
FSEU section 2 provides a TE FLAP DISAGREE message and illuminates the
TRAILING EDGE light.
Load Relief System operation is Inhibited when:
•
•
•
•
Alternate Flap System is ARMED
Center Flap Stabilizer Position Module (FSPM) failure
Flap lever transmitter (RVDT) failure
Loss of 26 volt ac power supply.
28V DC
115V AC
SENSOR PWR
TRANSFORMER
POWER
SUPPLY
28V AC FAIL
FLAP LEVER RVDT FAIL
FLAP/SLAT
ELEC (S,M)
LOAD
RELIEF
INHIBIT
EICAS CMPTR(S)
FSPM FAIL
NOT
RETRACT
RETRACTED
ALTN FLAP ARMED INHIBIT
ARM SW
POSN
ALT FLAP
FAIL PROT
& FLAP
DISAGREE
ARM SW
(P3-1)
XMTR 4
FLAP POSN
>20
LOAD
RELIEF
C FSPM (P50)
25
30
<20
VALID
P10
AIRSPEED
DATA BUS 4
R ADC INPUT
>182.5
>172.5
AIRSPEED
DATA BUS 4
L ADIRU (E1-3)
ARINC
429
(SECT 1)
FSEU (E2-4)
L ADC INPUT
VALID
<168.5
VALID
<25
FLAP LOAD RELIEF SYSTEM
B767-3S2F
Page - 109
ATA 27-50
11/11/13
RESET
VALID
R ADIRU (E2-3)
EFF - ALL
EXTENDED
FLAP LOAD
RELIEF ACTUATOR
<178.5
ARINC
429
CONT
FLAP LOAD
RELIEF
(P33)
NOT
EXTEND
EXTENDED
FLAP LEVER
POSITION
FLAP LEVER POSN
RVDT 2
RETRACTED
BRAKE
TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
LATCH
LATCH
RESET
B767-3S2F
Page - 110
ATA 27-50
11/11/13
EFF - ALL
TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
FLAP ALTERNATE DRIVE CONTROL
The flap Power Drive Unit (PDU) alternate drive electric motor is controlled by
the Flap Slat Electronic Unit (FSEU). The FSEU receives command inputs from
the alternate flaps position selector switch. Alternate flap arm switch inputs are
also used by the FSEU for relay control as well as for direct control of the PDU
bypass valve.
The FSEU controls alternate flap relays to provide power to the reversible PDU
electric motor.
A right wing drive position transmitter inputs to a flap stabilizer position module
(FSPM) which provides flap drive position to the FSEU. This provides an FSEU
closed loop control system, similar to primary drive, to turn off the electric motor
when flap drive and selector switch inputs agree.
UP
BITE INSTRUCTIONS:
TRAILING
EDGE
LEADING
EDGE
Push ON/OFF to start or end BITE display.
Push YES or NO to reply to questions(?).
Push to move down in list.
OFF
FLAP LIMIT (IAS)
ALT FLAPS
POSITION
SELECTOR
SWITCH
ALTERNATE
FLAP ARM
SWITCH
RETRACT
270K
Push to move up in list.
Push MENU to return to previous menu.
220K
240K
210K
5
1
15
UP
FLAPS
20
30
195K
DN
LOCK OVRD
UP
MENU
ON
OFF
YES
NO
ALTN GEAR
EXTENSION
P33
OFF
FLAP/SLAT ELECTRONIC UNIT
20
30
EXISTING FAULTS-Shows existing faults.
FAULT HISTORY-Shows past faults by
flight leg.
GROUND TESTS-Shows list of ground tests.
OTHER FUNCTIONS-Shows other functions.
190K
162K
NORM
BITE MAIN MENU:
25
ALTN FLAPS
5
1
15
INPUT TO
FLAP PDU
BYPASS VLV
EXTENDED
270K-.82M
EXTENDED
320K-.82M
25
LE
TE
ALTN
ALTN
P/N 285T0049SER NO.
DN
MOD LEVEL
GND PROX
FLAP OVRD
GND PROX/CONFIG
GEAR OVRD
OVRD
FMG DATE
CAGE CODE 81205
MFR
SER
PMR
MOD
OVRD
ALT FLAP
RELAYS
ALTERNATE FLAP CONTROL
(P3-1)
FSEU
GEARBOX
RIGHT WING
DRIVE SHAFT
ALTERNATE
DRIVE
ELECTRIC
MOTOR
FSPM
BYPASS
VALVE
1
ELECTRICAL
CONNECTOR
P50 ELECTRICAL
SYSTEMS CARD FILE
1
FLAP POSITION
TRANSMITTER, POSITION 5
(OUTBOARD VIEW)
CONTROLLED BY ALT FLAP ARM SW
FLAP ALTERNATE DRIVE CONTROL
B767-3S2F
Page - 111
ATA 27-50
11/11/13
EFF - ALL
TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
OUTBD
FWD
TE FLAPS POWER DRIVE UNIT
(RIGHT WHEEL WELL)
B767-3S2F
Page - 112
ATA 27-50
11/11/13
EFF - ALL
TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
FLAPS POSITION TRANSMITTER
Flap position transmitters are installed on the support ribs for all eight flap drive
mechanisms and connected to the splined drive shaft operated by the rotary
actuator. Two types of flap transmitters are used which have different faces to
insure correct installation. The two types of transmitters contain different
components.
The transmitters are rotated internally by a driver frame engaged, by tangs, in
the splined drive shaft. The two tangs are different size with one having a rig pin
hole to insure correct installation. A cutout in the transmitter assembly face fits
around an adjustment fitting on the mounting structure. The adjustment fitting
and mounting bolts hold the transmitter in position. There are three rig pin holes
in the transmitter with a placard identifying the flaps 30 position.
The transmitter is installed with a rig pin through the flaps 30 rig pin hole and the
tang with the flaps hydraulically extended to 30 units. With the mounting bolts
finger tight in the elongated mounting holes, the adjustment fitting is used to
center the tang in the splined drive shaft.
TRANSMITTER 4
TRANSMITTER 1
TRANSMITTER 7
TRANSMITTER 2
TRANSMITTER 8
P
D
U
TRANSMITTER 5
TRANSMITTER 6
N
TRANSMITTER 3
F L A PS 3 0
S
PO
TRANSMITTER ASSEMBLY
2, 3, 4, 5, 6 AND 7
TRANSMITTER
ASSY 1 AND 8
FLAP POSITION TRANSMITTER
(TYPICAL)
FLAP POSITION TRANSMITTER
B767-3S2F
Page - 113
ATA 27-50
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EFF - ALL
TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
B767-3S2F
Page - 114
ATA 27-50
11/11/13
EFF - ALL
TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
FLAP POSITION TRANSMITTER ASSEMBLIES
Transmitter Assemblies 1 and 8
Transmitter assemblies at the 1 and 8 flap drive positions contain a resolver and
a Syncro. The syncros are powered directly from the 28 VAC buses and drive
syncros in the flap indicator. Syncro failures are shown by flap needle
operation. The resolvers are powered by 28 VAC from Flap Slat Electronic Unit
(FSEU) section 1. Failures are shown by FLAP/SLAT ELEC status/
maintenance messages and by the associated FSEU XMTR fault light during
Built-in-test (BITE) operation. Resolver failure causes loss of flap asymmetry
shutdown protection by FSEU section 1.
Transmitter Assemblies 3, 4 and 5 for Flap Stabilizer Position Modules
Transmitter assemblies at the 3, 4 and 5 flap drive positions contain resolvers
and rotary variable differential transformers (RVDT). The resolver in the
transmitter assembly at drive position number 3 is unpowered. Resolvers 4 and
5 operate the same as 1 and 8. The RVDT's are powered and monitored by
Flap Stabilizer Position Modules (FSPM) which input flap drive position to the
FSEU. RVDT or FSPM faults are shown by FLAP/SLAT ELEC status/
maintenance messages and by FSPM fault lights on the FSEU during BIT
operation. The FSPM's have BITE to identify RVDT or module faults.
Flap Lever Transmitters
Two rotary variable differential transformers (RVDT) are operated by a flap lever
gearbox in the control stand. Access is through the right side of the control
stand. RVDT number 1 inputs flap lever position to flap slat electronic unit
(FSEU) section 2 and RVDT number 2 to inputs FSEU section 1.
The RVDT's are installed in electrical null alignment with the lever at fifteen units
plus 4.5 degrees. The RVDT signal voltage is then checked at each lever
position and adjusted as required by rotating the RVDT in its clamp.
A failure of either transmitter is indicated by FLAP SLAT ELEC status/
maintenance messages. FSEU testing indicates the failed RVDT by a fault
light.
RVDT number 2 is also monitored for correct rig voltage with the flaps and slats
up and the altitude is above 20,000 feet or airspeed is greater than 270 knots.
A BIT/verify test will display the faulted flap lever RVDT voltage by displaying
the MISRIG light. The flap lever and flaps must be in the UP position when
testing for this fault.
The RVDT misrig condition will be indicated by the FLAP SLAT ELEC message.
A
A
B
C
LEFT
FSPM
CENTER
FSPM
RIGHT
FSPM
RVDT NO.3
FLAP
LEVER
RVDT NO.5
RVDT NO.4
PRESS/
TEST
RESOLVER
(TE FLAP
DISAGREE)
RIGHT (SECT 3)
M603 FLAP LEVER
POSITION XMTR 2 (SECT 1)
M492 FLAP POSITION
XMTR 5-RIGHT (SECT 1)
M604M603
FLAPFLAP
LEVERLEVER
POSITION XMTR 1 (SECT 2)
M473 FLAP POSITION
XMTR 1-LEFT (SECT 1)
BITE INSTRUCTIONS:
M548 OUTBD SLAT
PDU
RVDT MISRIG (SECT 3)
S846 HYD PRESSURE
SWITCH (SECT BITE
1) MAIN MENU:
TRANSMITTER NO. 3
XMTR
NO.1
XMTR
NO.2
Push ON/OFF to start or end BITE display.
Push YES or NO to reply to questions(?).
Push to move down in list.
Push to move up in list.
Push MENU to return to previous menu.
B
RVDT
(FSPM)
EXISTING FAULTS-Shows existing faults.
FAULT HISTORY-Shows past faults by
flight leg.
GROUND TESTS-Shows list of ground tests.
OTHER FUNCTIONS-Shows other functions.
M476 FLAP POSITION
XMTR 4-LEFT (SECT 1)
M100 AIR DATA
COMPUTER-LEFT (SECT 1)
M483 INBD SLAT PDU
POSITION XMTR 1 (SECT 1)
M544 OUTBD SLAT PDU
POSITION XMTR 1 (SECT 1)
M545 FLAP/SLAT
ELECTRONIC UNIT (SECT 2)
FLAP/SLAT ELECTRONIC UNIT
P/N 285T0049SER NO.
MOD LEVEL
RESOLVER
(TE ASSYM)
(TE SHUTDOWN)
CAGE CODE 81205
FMG DATE
BIT/
VERIFY
(XMTER FAIL)
M603 FLAP LEVER
RVDT MISRIG (SECT 1)
M489 FLAP POSITION
XMTR 8-RIGHT (SECT 1)
M101 AIR DATA
COMPUTER-RIGHT (SECT 1)
M549 INBD SLAT PDU
MFR
POSITION
XMTR 2 (SECT 3)
SER
PMR
M548 OUTBD SLAT PDU
MOD
POSITION XMTR 2 (SECT 3)
MENU
ON
OFF
YES
NO
XMITR
NO.3
FLAP SHUTDOWN
XMITER
NO.4
S/M
FLAP/SLAT ELEC
EICAS
C
TEST COMPLETE
(SECT 2)
FSEU
FLAP/SLAT
ELECTRONIC UNIT
FLAP DISAGREE
RESOLVER
(TE ASSYM)
TESTING
(SECT 2)
TRANSMITTER NO. 4
TRANSMITTER NO. 5
FLAP LIMIT
230K
RESOLVER
(TE ASSYM)
TRANSMITTER NO. 1
10
15
L
R
1
SYNCRO
(INDICATION)
RESOLVER
(TE ASSYM)
210K
250K
210K
20
UP
FLAPS
30
25
SYNCRO
(INDICATION)
180K
170K
FLAP POSITION TRANSMITTER ASSEMBLIES
B767-3S2F
Page - 115
ATA 27-50
11/11/13
EFF - ALL
TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
TRANSMITTER NO. 8
B767-3S2F
Page - 116
ATA 27-50
11/11/13
EFF - ALL
TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
FLAPS POSITION INDICATION
General
The flap position indicator syncro receivers (needles) are driven by the syncro
transmitters in the flap position transmitter assemblies at flap drives one and
eight. Flap drive transmitter one operates the left needle, flap drive transmitter
eight operates the right needle.
The syncro transmitters drive the syncro receivers to show flap position
whenever the flap/ref. transfer relay is de-energized. This relay is controlled by
the FSEU using flap and slat drive position transmitter inputs and is
de-energized when the slats or flaps are extended. The flaps are retracted
when needles are at up or 1. The Flap position transmitters position the
needles at 1 through 30 to show flap positions of up, 5, 15, 20, 25 or 30 units.
The flap position indicator up position shows that all the leading edge slats are
retracted.
Slat Position Indication
Left and right needles are operated by synchro receivers in the flap position
indicator that are driven by synchro transmitters in flap position transmitters one
and eight. Both synchro receivers can also be driven by two fixed reference
signal transmitters that position the needles at up and one-half unit. An
intermediate/retract relay, controlled by the Proximity Switch Electronic Unit
(PSEU), and a flaps/reference transfer relay, controlled by the Flap/Slat
Electronic Unit (FSEU), switch the indicator synchro receivers between the flap
position synchro transmitters and the reference signal transmitters.
Operation
With the flaps and slats retracted both relays are energized and both needles
are driven by the retracted reference signal transmitter. When any of the 24 slat
proximity sensors show a target far the PSEU de-energizes the flap
intermediate/retract relay and switches the needles to the intermediate
reference signal transmitter.
When both slat power drive unit (PDU) position transmitters show the PDU’s at
their intermediate, or takeoff position, the FSEU de-energizes the flaps
reference transfer relay and the needles are switched to the one and eight flap
position transmitters which position the needles to one unit with the flaps
retracted. From one to 30 units the needles are driven by their respective flap
position transmitter.
On retraction the FSEU energizes the transfer relay when the flaps are retracted
and either slat PDU is less than takeoff to move the needles to one-half unit.
The PSEU energizes the intermediate/retract relay when all slat sensors (24)
have near targets to move the needles to up.
28V DC
28V AC
P11
FIXED 1/2
XMTR 8
SLATS INTMD
REF SIGNAL
XMTR (P33)
5
1
XMTR 1
UP
FLAPS
30
SLATS RET
REF SIGNAL
XMTR (P33)
FLAPS INTMD/
RETRAC (P33)
28V AC
R BUS
FLAPS REF
TRANSFER
(P33)
ALL SLAT
LE SLATS RETRACTED
POSN IND
115V AC
R BUS
PSEU (E1-2)
P11
R FSPM
POWER
SUPPLY
P50
28V AC EXC GOOD
= RETRACTED
FLAP POSN
FSPM GOOD
LOGIC
INBD SLAT PDU 2
TRANSMITTER
REF XMTR
SELEC
< T/O
INBD SLAT
POSN LOGIC RVDT GOOD
< T/O
OUTBD SLAT
POSN LOGIC RVDT GOOD
OUTBD SLAT PDU 2
TRANSMITTER
FSEU (E2-4)
FLAP POSITION INDICATION
B767-3S2F
Page - 117
ATA 27-50
11/11/13
EFF - ALL
20
25
FIXED UP
XMTR 5
15
TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
(SECT 3)
B767-3S2F
Page - 118
ATA 27-50
11/11/13
EFF - ALL
TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
FLAP/STAB POSITION MODULES (FSPM)
Three identical Flap Stabilizer Position Modules (FSPM) power the flap position
transmitter assembly rotary variable differential transformers (RVDT) at flap
drive positions 3, 4, and 5. The FSPM receive an analog AC voltage signal from
the RVDT and output flap position analog DC voltage signals and flap position
discrete signals to various airplane systems. Each Flap Slat Electronic Unit
(FSEU) section receives flap position from a different FSPM. The alignment of
FSPM to FSEU section is shown on the FSEU with the left FSPM to section 2,
center FSPM to section 1 and right FSPM to section 3.
The RVDT input is monitored by the FSPM to detect a failed transformer. FSPM
primary and monitor channels both generate signals which are compared by an
outputs monitor to detect a module failure. Only the primary signal is output
from the FSPM. RVDT or module faults shut down the FSPM analog and
discrete outputs. A low voltage signal caused by a failed RVDT or FSPM
causes the associated FSEU section to initiate a FLAP/SLAT ELEC message.
The faulted FSPM input is then identified by the FSEU built-in-test.
Testing of the FSPM is done by selecting Existing Faults on the six button front
face bite as per the aircraft maintenance manual.
MODULE
STAB TRIM
AFDS
TMS
FSEU (SECT 2)
ENG IGN CNTL
EEC
SPLR CNTL
28V AC
TEST GOOD
STAB XMTR
FLAP XMTR
GND PROX
FLAP POS
XMTR 3
BIT/VERIFY
L FSPM (P50)
AFDS
STAB TRIM
115V AC
AFDS
XFMR
STAB TRIM
28V AC
STALL WARNING
STALL WARNING
SAME AS
L FSPM
FSEU (SECT 1)
SAME AS
L FSPM
PACK FLOW CNTL
LAND CONF WARN
SPLR CNTL
Page - 119
11/11/13
EFF - ALL
SPLR CNTL
R FSPM (P50)
FLAP / STAB POSITION MODULES (FSPM)
ATA 27-50
EEC
FLAP POS
XMTR 5
C FSPM (P50)
B767-3S2F
ENG IGN CNTL
PACK FLOW CNTL
T/O CONF WARN
FLAP POS
XMTR 4
FSEU (SECT 3)
TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
B767-3S2F
Page - 120
ATA 27-50
11/11/13
EFF - ALL
TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
FLAPS ASYMMETRY PROTECTION SYSTEM
The flap asymmetry protection system shuts down (bypasses) the flap primary
drive and illuminates the TE FLAP ASYM message and produces the
appropriate Existing Fault when a flap drive asymmetry condition is detected.
Resolvers in flap position transmitter assemblies one and eight and four and
five are compared by the flap slat electronic unit (FSEU) section 1 to detect a
disconnect in the flap drive system. A difference in resolver degree input
between resolvers one and eight or between four and five equivalent to 43 1/4
drive shaft revolutions causes immediate system shutdown and fault
annunciation (approximately 12% of flap drive full travel). If the resolver
difference remains for five seconds the fault and annunciation are latched.
If the asymmetry no longer exists, the latch can be reset by pushing the flap
alternate arm switch on and off, by opening and closing the FSEU 1 control
circuit breaker, or by moving the flaps and flap lever to the retracted position.
LE
TE
ALTN
CYCLED
FLAP LEVER = UP
FLAP = UP
ALTN
FLAP/SLAT ELEC (S,M)
115V AC
STBY BUS
POWER
SUPPLY
28V AC
VEXC
28V AC EXC FAIL
COMPARE:
1&8, 2&7,
3&6, 4&5
RESET
2
ASYM
COMPARE:
1&2, 3&4,
5&6, 7&8
5 SEC
TE FLAP ASYM (B)
LATCH
EICAS COMPUTERS (E8)
FLAP
SHUTDOWN
SKEW
(SECTION 1)
RS
RS
XMTR 1
RS
RS
XMTR 2
XMTR 7
RS
RS
XMTR 3
5
1
UP
FLAPS
Page - 121
RS
FSEU (E2-4)
ATA 27-50
11/11/13
20
XMTR 5
25
1
FLAP DISAGREE/FLAP LIGHT (SECT 2)
2
43.25 DRIVE SHAFT REVOLUTION
DIFFERENCE
FLAP ASYMMETRY PROTECTION SYSTEM
B767-3S2F
15
XMTR 6
RS
XMTR 4
TRAILING
EDGE
LEADING
EDGE
XMTR 8
EFF - ALL
TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
30
FLAP INDICATOR
1
B767-3S2F
Page - 122
ATA 27-80
11/11/13
EFF - ALL
TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
LEADING EDGE SLATS
General Description
Extension of the leading edge slats improves wing stall characteristics enabling
higher angles of attack for takeoff and climb and increased maneuvering
margins during approach and landing.
There are five outboard and one inboard slat surfaces on each wing. The slats
are numbered from the left to the right wing tip. The slats extend from the top of
the wing and have three positions.
A Krueger seal flap extends from the bottom of each wing between the inboard
slat and the engine strut to reduce drag with the slats extended.
Primary Control
The leading edge slats are controlled by inputs from the flap lever. The flap
lever operates a cable system to the slat aft quadrant which is connected to the
inboard and outboard slat Power Drive Units (PDU).
A hydraulic motor powers each PDU gearbox, which operates drive shafts,
gearboxes and rotary actuators connected to the slats. There is a separate
PDU and drive system for the inboard and outboard slats.
Krueger seal flaps, operated by the inboard slat drive system, are fully extended
when the inboard slats are in takeoff (sealed) position.
Slat Alternate Control
The PDU gearbox can also be operated by an electric motor for alternate
system operation. The electric motor is controlled by the flap slat electronic unit
(FSEU).
CAUTION: BEFORE OPERATING FLAPS OR SLATS, ENSURE THAT
ENGINE STRUT ACCESS DOORS, INBOARD FAN COWLING,
AND THRUST REVERSER COWLING ARE NOT IN THE PATH OF
SLATS, TO PREVENT DAMAGE.
FLAP INDICATION
ALT POS SEL SW
ALT ARM SW
FLIGHT
DECK
EICAS
MEC
FLAP LEVER
FLAP LEVER
POSITION
TRANSMITTERS
(2)
INBD PDU
FSEU
PSEU
CONTROL SHAFT
SLAT AFT
QUADRANT
ANGLE GEARBOX
(4)
GEARBOX
BEARING
SUPPORT
OUTBD PDU
KRUEGER
FLAP DRIVE
KRUEGER
FLAP DRIVE
ACTUATOR
(2)
INBD SLAT ROTARY
ACTUATOR (4)
INBD
SLAT (2)
FSPM (3)
DRIVE
SHAFT
FLAP PDU
(REF)
ANGLE
GEARBOX
OUTBD SLAT
ROTARY
ACTUATOR
(20)
LEADING EDGE SLATS
B767-3S2F
Page - 123
ATA 27-80
11/11/13
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TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
OUTBOARD
SLAT (10)
B767-3S2F
Page - 124
ATA 27-80
11/11/13
EFF - ALL
TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
SLAT POWER DRIVE UNITS (PDU)
General
The inboard and outboard slat power drive units (PDU) are located in the
forward wing/body fairings. The PDU are mounted on the wing front spar by a
support attachment with two fasteners and a support rod. The PDU are similar.
The outboard PDU is larger than the inboard with larger hydraulic and electric
motors required to drive ten slat surfaces.
Maintenance Practices
Access to each PDU is through panels on the bottom of the wing below each
PDU. A tool (ground lock) can be installed on the gearbox so the PDU cannot
be operated with either the electric or hydraulic motor.
SUPPORT ROD
ELECTRIC
MOTOR
HYDRAULIC
MOTOR
DRIVE
SHAFT
GEARBOX
GEARBOX
OUTBOARD SLAT PDU
(LOOKING INBOARD)
DRIVE
SHAFT
ELECTRIC
MOTOR
HYDRAULIC
MOTOR
GEARBOX
FWD
PDU
GROUNDLOCK
INBD
SLAT POWER DRIVE UNIT (PDU)
B767-3S2F
Page - 125
ATA 27-80
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EFF - ALL
TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
SUPPORT
ATTACHMENT
DRIVE
INBOARD SLAT PDU SHAFT
(BOTTOM VIEW)
B767-3S2F
Page - 126
ATA 27-80
11/11/13
EFF - ALL
TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
INBOARD SLAT KRUEGER SEAL FLAP DRIVE SYSTEM
Krueger Seal Flap Drive
A single Krueger seal flap is mounted between the inboard slat and engine strut
on each wing. The flap extends down and forward from beneath the wing
leading edge to form a seal between the inboard slat and engine strut.
The Krueger seal flap rotary actuator is connected to the inboard slat outboard
actuator by a drive shaft through two universal joints. The Krueger seal flap
extends fully as the leading edge slats extend from the fully retracted to the
intermediate (takeoff) position. The drive linkage allows for slat extension to the
fully extended position without further Krueger seal flap extension.
The Krueger seal flap is a two-section structure. The bull nose is operated by
linkage from the seal door.
Maintenance Practices
The Krueger seal flap rotary actuator can be removed by disconnecting at the
flap drive link and the drive shaft input universal joint. An adjustable stop screw
on leading edge structure is used to fair the Krueger seal flap with the wing
leading edge when retracted
INBOARD
SLAT (REF)
WING
LEADING
EDGE
ROTARY
ACTUATOR
ROTARY
ACTUATOR
BULL NOSE
DRIVE SHAFT
FROM INBD SLAT
OUTBD ROTARY
ACTUATOR
INBD
FWD
BULL NOSE
INBOARD SLAT KRUEGER SEAL FLAP DRIVE SYSTEM
B767-3S2F
Page - 127
ATA 27-80
11/11/13
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TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
B767-3S2F
Page - 128
ATA 27-80
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TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
INBOARD SLAT DRIVE AND TRACKS
Description
Each inboard slat is extended and retracted by two control rods each connected
to a rotary actuator arm and a fitting on the aft side of the slat. The main support
for the slat is by an "A" frame at the inboard end, a support arm at the center
and a main track, with emergency down stop, at the outboard end, all mounted
to the wing front spar. The slat is held in position on the main support
components and the control rods by three auxiliary track arms. The slat is
attached to each auxiliary track arm at two places to prevent slat rotation and
provide slat angle positioning by the profiled auxiliary track. The auxiliary tracks
position the inboard slats at 12 degrees when extended to the intermediate or
takeoff position and at 30.3 degrees when fully extended.
PIVOT POINTS
(MOUNTED TO FRONT
SPAR SUPPORT FITTING)
PIVOT POINT
(MOUNTED TO FRONT
SPAR SUPPORT FITTING)
ACTUATOR
CONTROL ROD
WING
LEADING
EDGE
SLAT SUPPORT
STRUCTURE
(INSIDE SLAT)
MAIN SUPPORT
STRUCTURE
(A-FRAME)
ACTUATOR
CONTROL ROD
AUXILIARY
MAIN SUPPORT
TRACK ARM
ARM
(3)
WING LEADING
EDGE
WING LEADING
EDGE
MAIN TRACK
AUXILIARY
TRACK ARM
SUPPORT LINK
ROTARY
ACTUATOR
ARM
ROLLERS
AUXILIARY TRACK
SUPPORT BRACKET
SLAT
EMERGENCY
DOWN STOP
MAIN TRACK
ROLLER
SLAT
MAIN SUPPORT TRACK
(OUTBOARD END)
AUXILIARY
TRACK ARM
AUXILIARY TRACK (3)
INBOARD SLAT DRIVE AND TRACKS
B767-3S2F
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TRAINING MANUAL
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ACTUATOR
CONTROL
ROD
SLAT CONTROL ROD (2)
(OUTBOARD SHOWN)
B767-3S2F
Page - 130
ATA 27-80
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TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
OUTBOARD SLAT DRIVE AND TRACKS
Description
Each outboard slat is extended and retracted by two control rods each
connected to a rotary actuator arm and a fitting on the aft side of the slat.
Two main tracks, with emergency down stops, support the slat. These tracks
extend into recesses in the wing fuel tanks when the slats are retracted.
The slat is held in position on the main tracks and control rods by two auxiliary
track arms. The slat is attached to the auxiliary track arms at two places to
prevent slat rotation and provide slat angle positioning by the profiled auxiliary
track. The auxiliary tracks position the outboard slats at 26 degrees when
extended to the intermediate (takeoff) position and at 35 degrees when fully
extended.
ACTUATOR
CONTROL ROD
ACTUATOR
CONTROL ROD
INBD
FWD
MAIN TRACK
MAIN
SLAT SUPPORT TRACK
AUXILIARY
STRUCTURE (TYP)
TRACKS
(INSIDE SLAT)
WING LEADING
EDGE
VIEW LOOKING UP THROUGH
BOTTOM OF WING
TYPICAL FOR ALL OUTBOARD SLATS
ALIGNMENT
FITTING
ROLLER
ROTARY
FRONT SPAR
WING LEADING
ACTUATOR
EDGE
FRONT SPAR
WING
AUXILIARY
LEADING EDGE
TRACK
FWD
SLAT
ROTARY ACTUATOR
ARM
ACTUATOR CONTROL
ROD (2)
FRONT
SPAR
SLAT
SUPPORT
BRACKET
SUPPORT
LINK
ROLLERS
MAIN TRACK
AUXILIARY
TRACK ARM
AUXILIARY TRACK (2)
OUTBOARD SLAT DRIVE AND TRACKS
B767-3S2F
Page - 131
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TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
MAIN TRACK (2)
EMERGENCY
DOWN STOP
B767-3S2F
Page - 132
ATA 27-80
11/11/13
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TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
SLAT FSEU / PSEU INTERFACE
Operation
FSEU:
The Flap/Slat Electronic Unit (FSEU) controls the slat shutoff valve during
hydraulic motor operation to sequence the flaps and slats and for long-term
system depressurization. The FSEU controls the PDU bypass valves for
hydraulic motor shutdown for uncommanded motion and asymmetry failures.
Inputs to the FSEU for PDU bypass valve operation for uncommanded motion
shutdown and for control of the slat shutoff valve are from flap lever and PDU
rotary variable differential transformers (RVDT). Inputs to the FSEU for PDU
bypass valve operation for asymmetry shutdown are from the proximity switch
electronic unit (PSEU) and a flap lever RVDT. The FSEU uses disagree and
asymmetry signals from the PSEU to control the leading edge fault light and
caution messages. Alternate position selector switch and PDU RVDT inputs
are used by the FSEU for electric motor operation.
PSEU:
The Proximity Switch Electronic Unit (PSEU) monitors proximity sensors on
each slat to detect disagree and asymmetry faults. The PSEU receives flap
lever and alternate position selector switch inputs from the FSEU for disagree
fault detection. The PSEU signals the FSEU when either fault is detected.
The flap position indicator is controlled by a transfer relay controlled by the
FSEU and an intermediate/retract relay controlled by the PSEU.
Maintenance Practices
The FSEU and the PSEU have built-in-test equipment to identify faulted
components in the slat control and indication system.
SECTION 1
- SLAT SHUTOFF VALVE CONTROL
- BYPASS VALVE CONTROL
- UNCOMMANDED MOTION DETECTION
AND SHUTDOWN
- ASYMMETRY/SKEW ANNUNCIATION AND
SHUTDOWN
- SLAT CMD DISCRETE TO PSEU
SECTION 2
- FLAP DISAGREE DETECTION
- SLAT DISAGREE INDICATION
- SLAT COMMAND DISCRETE OUTPUT
SECTION 3
- ALTERNATE MODE CONTROL
- SLAT DISCRETE TO STALL WARNING
BITE INSTRUCTIONS:
Push ON/OFF to start or end BITE display.
Push YES or NO to reply to questions(?).
Push to move down in list.
Push to move up in list.
Push MENU to return to previous menu.
BITE MAIN MENU:
EXISTING FAULTS-Shows existing faults.
FAULT HISTORY-Shows past faults by
flight leg.
GROUND TESTS-Shows list of ground tests.
OTHER FUNCTIONS-Shows other functions.
LE SLAT
PROXIMITY
SENSORS
FLAP LEVER & POSN
SEL SW POSITION
MENU
ON/OFF
YES
NO
FLAP/SLAT ELECTRONIC UNIT
P/N 285T0049SER NO.
MOD LEVEL
CAGE CODE 81205
FMG DATE
THE BOEING COMPANY
MFR
SER
PMR
MOD
PROXIMITY SWITCH
SYSTEM
FSEU (E2-4)
TARGET
NEAR
TARGET
FAR
7
PRESS/TEST
6
7
SLAT DISAGREE
SENSOR CHANNEL SELECT
SLAT ASYMMETRY
SLAT POSITION
SENSOR
VERIFY
BIT
CARD
TARGET
TARGET TEST
L/R STALL
WARNING
RESET
PSEU (E1-2)
LANDING
CONFIG
WARNING
SLAT FSEU / PSEU INTERFACE
B767-3S2F
Page - 133
ATA 27-80
11/11/13
EFF - ALL
TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
ENGINE
IGNITION
CONTROL
B767-3S2F
Page - 134
ATA 27-80
11/11/13
EFF - ALL
TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
SLAT SYSTEM INTERFACE
Hydraulic Motor Operation
Slat failure protection shutdown, flap/slat sequencing and long-term hydraulic
pressure shutoff are controlled by Flap Slat Electronic Unit (FSEU) section 1
operation of the slat shutoff valve or the power drive unit (PDU) bypass valves.
These control functions require inputs from a flap lever rotary variable
differential transformer (RVDT), PDU RVDT, Flap Stabilizer Position Module
(FSPM), and the Proximity Switch Electronic Unit (PSEU). An alternate arm
switch armed input inhibits failure protection shutdown in FSEU section 1.
Electric Motor Operation
FSEU section 3 controls the electric motors using inputs from the alternate flap
position selector switch and PDU RVDTs. The slat alternate arm switch
operates the PDU bypass valves and engages the electric motor clutches.
Position Indication
The PSEU controls slat position transmitters to position the flap position
indicator synchros to the up and one-half unit positions. The PSEU monitors
proximity sensors on each slat for flap position indication and fault detection.
Fault Annunciation
A leading edge fault light and EICAS disagree message are controlled by FSEU
section 2 using inputs from a flap lever RVDT, alternate arm and position
selector switches, an FSPM, FSEU section 1 and the PSEU. FSEU section 1
controls the asymmetry fault message and inputs to section 2 for illumination of
the leading edge fault light. FSEU section 2 provides flap lever/alternate
position selector switch position to the PSEU for disagree fault detection.
CENTER
HYD SYS
TRAILING
EDGE
LEADING
EDGE
FLAP
LEVER
FLAP LIMIT (IAS)
SHUTOFF
VALVE
FLAP/SLAT
SOV MODULE
CONTROL
VALVE
5
1
15
UP
FLAPS
20
25
RVDT (2)
30
B
ALTN FLAPS
5
1
15
UP
EICAS
A
20
NORM
BYPASS
VALVE
E
SLAT
DRIVE
ROTARY
ACTUATORS
25
30
LE
TE
ALTN
ALTN
HYDRAULIC
MOTOR
HYD
PRESS
LE SLATS
GEAR
BOX
L/C FSPM
ELECTRIC
MOTOR
E
A
CLUTCH
FSEU
C
PSEU
HYDRAULIC
ELECTRICAL
MECHANICAL
B
-STALL WARNING
-CONFIG WARNING
-ENGINE IGNITION
SLAT PDU (TYP)
SLAT SYSTEM INTERFACE
B767-3S2F
Page - 135
ATA 27-80
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TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
RVDT
(2)
PROX
SENSORS
(4 INBD)
(20 OUTBD)
C
B767-3S2F
Page - 136
ATA 27-80
11/11/13
EFF - ALL
TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
SLAT HYDRAULIC OPERATION
General
Flap lever operation of the power drive unit (PDU) pilot input arm operates the
control unit input cam, to move the control valve module control valve from the
null position. Center hydraulic system pressure is then provided to the hydraulic
motor through the control valve module bypass valve. Slat drive shaft rotation
operates the control unit follow-up cam to return the control valve to null. When
the control valve is at null and the bypass valve is at normal, there is a hydraulic
lock on the motor to hold the gearbox and slat drive.
Operation
Hydraulic pressure to the motor can be shutoff by the flap/slat shutoff valve
module slat shutoff valve or by the bypass valve in the PDU control valve
module.
Pressure is shutoff to the motor as follows using the Flap/slat shutoff valve
module:
• The slat solenoid valve is powered by the flap/slat electronic unit (FSEU) to
close the slat shutoff valve when the slat drive and flap lever are in
agreement or, on retraction, until the trailing edge flaps are up.
• If pressure is shutoff at the flap/slat shutoff valve module, the hydraulic lock
remains on the motor.
Pressure is shutoff to the motor as follows using the bypass valve:
• The bypass valve is positioned to bypass when the alternate slat system
arm switch is armed or by the FSEU during slat system failure.
• If pressure is shutoff by the bypass valve, the motor can be rotated by the
gearbox.
C HYDRAULIC
SYSTEM
PRESS
FSEU
SLAT
SOLENOID
VALVE
SLAT
SHUTOFF
VALVE
FLOW
REG
PRIORITY
VALVE
RETURN
FSEU
FLAP
SOLENOID
VALVE
C2
OUTBD
SLAT PDU
C1
FLAP
SHUTOFF
VALVE
FLAP PDU
CONTROL
VALVE
MODULE
CONT UNIT ASSY
EICAS
INPUT CAM
SLAT SOV
PRESS SW
PRESS
SUMMING
LEVER
PILOT INPUT ARM
UP
FOLLOW-UP CAM
RETURN
DN
OPEN
BYPASS
NULL
FSEU/
ALT ARM
SWITCH
CONT VALVE
1
PDU RVDT NOT SHOWN
FOR CLARITY REASONS
QUILL SHAFT
(WORM GEAR)
BYPASS
NORM
BYPASS VLV UP
DN
LEGEND
C1 C2
CD
PRESSURE
RETURN
NOTE: INBOARD PDU SHOWN
OUTBOARD IS SIMILAR
GEARBOX
1
SLAT HYDRAULIC OPERATION
B767-3S2F
Page - 137
ATA 27-80
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TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
CD
NORM
CLOSED
HYDRAULIC MOTOR
DRIVE SHAFT
ALTERNATE DRIVE
ELECTRIC MOTOR
B767-3S2F
Page - 138
ATA 27-80
11/11/13
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TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
SLAT ALTERNATE DRIVE CONTROL
General
The slat inboard and outboard Power Drive Unit (PDU) alternate drive electric
motors are controlled by the Flap Slat Electronic Unit (FSEU). The FSEU
receives command inputs from the alternate flaps position selector switch and
slat drive position from rotary variable differential transformers (RVDT) on each
PDU. Using these inputs, section 3 of the FSEU controls relays to provide
power to the reversible electric motors on both PDU.
Operation
The slat alternate arm switch directly controls the bypass valves on the PDU
during alternate drive operation to remove the hydraulic motor lock on the PDU
gearbox. The arm switch also controls power to the FSEU for relay control.
The FSEU compares the command and slat drive position inputs separately in
the inboard and outboard slat systems for individual, closed-loop motor control.
Electric motor turn off does not occur simultaneously on the inboard and
outboard slat systems due to different degrees of extension at the intermediate
(takeoff) and fully extended positions.
LEADING TRAILING
EDGE
EDGE
FLAP LIMIT (IAS)
225K
250K
ALT FLAPS
POSITION
SELECTOR
SWITCH
215K
5
1
205K
20
UP
FLAPS
190K
170K
ALTN FLAPS
5
1
15
UP
Push to move up in list.
Push MENU to return to previous menu.
BITE MAIN MENU:
25
30
ALTERNATE
SLAT ARM
SWITCH
P37
BITE INSTRUCTIONS:
Push ON/OFF to start or end BITE display.
Push YES or NO to reply to questions(?).
Push to move down in list.
15
EXISTING FAULTS-Shows existing faults.
FAULT HISTORY-Shows past faults by
flight leg.
GROUND TESTS-Shows list of ground tests.
OTHER FUNCTIONS-Shows other functions.
MENU
ON/OFF
YES
NO
20
FLAP/SLAT ELECTRONICS UNIT
NORM
P/N 285T0049SER NO.
25
30
LE
MOD LEVEL
TE
CAGE CODE 81205
FMG DATE
THE BOEING COMPANY
ALTN
MFR
SER
PMR
MOD
ALT SLAT RLYS (P37)
ALTN
ALTERNATE SLAT
CONTROL (P3-1)
FSEU (SECT 3) (E2-4)
TO SLAT PDU
BY-PASS VLV
PDU BYPASS
VALVE 1
PDU BY-PASS
VALVE
1
RVDT
ALT DRIVE
ELECTRIC
MOTOR
RVDT
ALT DRIVE
ELECTRIC
MOTOR
GEARBOX
1
CONTROLLED BY
ALT SLAT ARM SW
GEARBOX
INBOARD SLAT PDU
SLAT ALTERNATE DRIVE CONTROL
B767-3S2F
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TRAINING MANUAL
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OUTBOARD SLAT PDU
B767-3S2F
Page - 140
ATA 27-80
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SLAT SENSOR/TARGET POSITIONS
General
Each proximity sensor is powered and monitored by the Proximity Switch
Electronic Unit (PSEU) to detect a target near or far condition.
Sensor Location
On the outboard slats the sensor and retract target at the inboard auxiliary track
are mounted further aft on structure and the auxiliary track arm, respectively,
than the sensor/target on the outboard auxiliary track. On the inboard slats the
sensor/targets at the outboard auxiliary track are mounted further aft.
Operation
When the slat is fully retracted the retract target on the auxiliary track arm is
near to the proximity sensor. When the slat is in the intermediate (takeoff)
position the auxiliary track roller ball assembly target is near on the inboard
auxiliary track on the outboard slats and the outboard auxiliary track on the
inboard slats. When the slat is fully extended, the near sensor/targets are
reversed, with the roller ball assembly target near on the outboard auxiliary
track for the outboard slats and the inboard auxiliary track for the inboard slats.
Maintenance Practices
A target out of adjustment or a faulted sensor would be detected by the PSEU
as a slat asymmetry condition. The PSEU built-in test (BITE) would identify the
faulted component by a sensor/target code and sensor or target fault light.
Proximity Sensor/Target Installation
A proximity sensor is installed on wing leading edge structure near the inboard
and outboard auxiliary tracks on each slat. The sensor is actuated by either a
retract target, riveted on the auxiliary track arm, or a roller bolt assembly at the
aft end of the auxiliary track arm that holds the track arm on the track. On each
slat one sensor is installed farther aft on wing structure than the sensor near the
other auxiliary track with its retract target installed the same distance aft on the
auxiliary track arm.
Operation
When the slat is retracted both retract targets are near to their sensors due to
the offset (staggered) sensors and targets.
As the roller bolt assemblies (targets) are in the same position at the aft end of
each auxiliary track arm, one sensor/target is near and one far at the
intermediate slat position with the near/far target positions reversed at the slat
fully extended position.
SENSOR (NEAR)
SENSOR (NEAR)
SLAT 12
T
T
TAKEOFF
SLAT
MOTION
PS T
FWD
FULLY RETRACTED
POSITION
SENSOR (NEAR)
SENSOR (FAR)
LANDING
T PS
FULLY RETRACTED
POSITION
SLAT 1
TABLE 102
SLAT
NO.
INBD
INTERMEDIATE
FWD
POSITION
PROXIMITY SWITCH
SYSTEM
TARGET
NEAR
PRESS/TEST
6
7
SENSOR CHANNEL SELECT
SENSOR (FAR)
VERIFY
BIT
TARGET
FULLY EXTENDED
POSITION
(OUTBOARD SLAT SHOWN)
RESET
ATA 27-80
11/11/13
F
N1
N1
F
2
N2
N2
F
N1
N1
F
3
S278 (OUTBD)
S284 (INBD)
N2
N2
F
N1
N1
F
4
S279 (OUTBD)
S285 (INBD)
N2
N2
F
N1
N1
F
5
S280 (OUTBD)
S286 (INBD)
N2
N2
F
N1
N1
F
6
S281 (INBD)
S287 (OUTBD)
N2
N2
N1
F
F
N1
7
S299 (INBD)
S305 (OUTBD)
N2
N2
N1
F
F
N1
8
S298 (OUTBD)
S304 (INBD)
N2
N2
N1
F
F
N1
9
S297 (OUTBD)
S303 (INBD)
N2
N2
N1
F
F
N1
10
S296 (OUTBD)
S302 (INBD)
N2
N2
N1
F
F
N1
11
S295 (OUTBD)
S301 (INBD)
N2
N2
N1
F
F
N1
12
S294 (OUTBD)
S300 (INBD)
N2
N2
N1
F
F
N1
N1 = TARGET NEAR (TARGET ON AUXILIARY TRACK ROLLER BOLT OPPOSITE SWITCH)
F = TARGET FAR (TARGET ON AUXILIARY TRACK ROLLER BOLT OFFSET FROM SWITCH)
N2 = TARGET NEAR (TARGET ON AUXILIARY TRACK ARM OPPOSITE SWITCH)
SLAT SENSOR / TARGET POSITIONS
Page - 141
N2
N2
S277 (OUTBD)
S283 (INBD)
TARGET TEST
PSEU
B767-3S2F
S276 (OUTBD)
S282 (INBD)
SENSOR (NEAR)
SENSOR CARD
EFF - ALL
A
B
C
SLATS FULLY
SLATS
SLATS FULLY
INTERMEDIATE
RETR
EXTENDED
1
TARGET
FAR
7
SENSOR/
TARGET
CODE
TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
B767-3S2F
Page - 142
ATA 27-80
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TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
SLAT SENSORS AND TRANSMITTERS
PDU Position Transmitters
The slat Power Drive Unit (PDU) rotary variable differential transformers
(RVDT) are powered and monitored by the Flap Slat Electronic Unit (FSEU).
One RVDT on each PDU is powered by and inputs to FSEU section 1, RVDT
two is powered by and inputs to FSEU section 3. A failed RVDT causes display
of the FLAP/SLAT ELEC status/maintenance messages. FSEU testing
indicates the failed RVDT by a Existing Fault message.
RVDT two on the outboard PDU is also monitored for correct rig voltage when
the slats are retracted and altitude is above 20,000 feet or airspeed is above
270 knots. A Ground Test will display the RVDT Misrig Existing Fault message..
The flap lever and slats must be in the UP position when testing for this fault.
A misrig condition will be indicated by the FLAP SLAT ELEC message.
INBOARD
SLATS PDU
CONTROL
UNIT
RVDT COVER
A
RVDTS
A
CONTROL
UNIT
RVDT 1
CLAMP CLAMP BOLT
(2 ON EACH RVDT)
SCREW, WASHER
(6)
GEARBOX
OUTBOARD SLAT PDU
(VIEW LOOKING INBOARD)
INBD
RVDT 2
A-A
(RVDT COVER REMOVED)
NOTE: INBOARD PDU RVDT(S) ARE
SIMILAR TO OUTBOARD PDU RVDT(S)
ELECTRICAL NULL
ALIGNMENT MARKS
RVDT
SLAT SENSORS AND TRANSMITTERS
B767-3S2F
Page - 143
ATA 27-80
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TRAINING MANUAL
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B767-3S2F
Page - 144
ATA 27-80
11/11/13
EFF - ALL
TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
SLAT PSEU BITE
General Description
The Proximity Switch Electronics Unit (PSEU) monitors slat system proximity
sensors and targets to detect faults and signal the Flap/Slat Electronic Unit
(FSEU) for protective shutdown and display of the slat asymmetry and disagree
indications.
LE Slat Asymmetry
A slat system sensor or target fault causes the slat asymmetry fault indications.
The PSEU BITE will show the faulted component when tested.
System test code 506 is used to test only the leading edge slat system;
target test is used to test single sensor/target inputs.
LE Slat Disagree
A faulted slat normal or alternate command discrete input to the PSEU from the
FSEU can cause the slat disagree fault indications. PSEU BITE will show the
faulted input when tested.
BITE INSTRUCTIONS (AIRCRAFT MUST BE ON GROUND)
NOTE: IF NO BITE RESPONSE, PRESS PRESS/TEST & TARGET TEST
SWITCHES SIMULTANEOUSLY TO RESET.
A-MEMORY RECALL AND RESET
PRESS BIT SWITCH TO DISPLAY FAILED LRU.
PRESS BIT SWITCH AGAIN FOR NEXT LRU.
PRESS RESET SWITCH TO CLEAR MEMORY.
NOTE : LRU(S) ARE DISPLAYED ON A LAST IN - FIRST OUT BASIS.
B-SYSTEM TEST
SELECT TEST CODE WITH CHANNEL SELECT:
CODE 500 CARGO DOOR CONTROL
CODE 501* ALL T/R SYSTEMS
CODE 502* ENTRY DOOR CONTROL
CODE 503 DOOR SYSTEM
CODE 504 LG SYSTEM NO. 1
CODE 505 LG SYSTEM NO. 2
CODE 506 LE SLATS
CODE 507 ALL SYSTEMS
* NOT INSTALLED ON ALL AIRPLANES
ALL OTHER CODES = ALL SYSTEMS PLUS MEMORY TEST.
CODE
BITE INSTRUCTIONS:
Push ON/OFF to start or end BITE display.
Push YES or NO to reply to questions(?).
Push to move down in list.
Push to move up in list.
Push MENU to return to previous menu.
BITE MAIN MENU:
EXISTING FAULTS-Shows existing faults.
FAULT HISTORY-Shows past faults by
flight leg.
GROUND TESTS-Shows list of ground tests.
OTHER FUNCTIONS-Shows other functions.
MENU
ON/OFF
YES
NO
FLAP/SLAT ELECTRONICS UNIT
P/N 285T0049SER NO.
MOD LEVEL
MFR
SER
PMR
MOD
CAGE CODE 81205
FMG DATE
THE BOEING COMPANY
PRESS VERIFY SWITCH. FAILED LRU IS DISPLAYED AT END OF TEST.
PRESS VERIFY SWITCH AGAIN FOR NEXT LRU.
C-TARGET TEST(DISPLAY DELAYED APPROX. 5 SECONDS)
SELECT SENSOR CHANNEL WITH CHANNEL SELECT SWITCH.
PRESS TARGET TEST SWITCH TO DISPLAY POSITION OF TARGET.
FSEU (E2-4)
DISPLAY
CODE 000 MEMORY RECALL (BIT) COMPLETE.
CODE 001-016 FAILED CARD WITH CARD LIGHT. CODE INDICATES
CARD SLOT NUMBER (001-007 LEFT SIDE, 008 BITE
MODULE, 009-016 RIGHT SIDE). SEE NOTE BELOW
FOR CARD 001-004 OR 013-016 FAILURE.
CODE 150-305 FAILED SENSOR WITH SENSOR LIGHT OR FAILED TARGET
WITH TARGET LIGHT, CODE INDICATES SENSOR ITEM
NUMBER EXCEPT FOR RIGHT THRUST REVERSER.
CODE 400-409 SUBSYSTEM INPUT POWER FAILURE.
CODE 421-428 DISCRETE INPUT FAILURE.
CODE 888 LAMP TEST (PRESS/TEST).
CODE 999 SYSTEM TEST (VERIFY) COMPLETE.
CODE AAA AIRCRAFT IN AIR MODE.
CODE CCC SYSTEM TEST (VERIFY) IN PROGRESS. (FLASHING).
CODE DDD DEACTIVATED OR NOT INSTALLED ON THIS AIRPLANE.
CODE EEE MEMORY CLEARED (RESET).
NOTE: PROXIMITY CARD FAULT (CODES 001-004 OR 013-016)
DURING VERIFY TEST OR TARGET TEST MAY BE CAUSED
BY DAMAGED SENSOR OR TARGET BEING LESS THAN .03
INCHES FROM RECTANGULAR SENSOR. INTERCHANGE CARD
WITH GOOD CARD. REPLACE CARD IF FAULT FOLLOWS. IF
SAME SLOT IS FAULTED AGAIN, PERFORM TARGET TEST
ON EACH SENSOR FOR THAT CARD SLOT (SEE INSIDE TABLE).
THE CARD FAULT LIGHT WILL ILLUMINATE WHEN THE
MISRIGGED OR DAMAGED SENSOR IS TESTED.
TARGET
NEAR
TARGET
FAR
PRESS/TEST
7
6
7
SENSOR CHANNEL SELECT
Page - 145
ATA 27-80
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EFF - ALL
L SLAT #1 OUTBD
L SLAT #2 OUTBD
L SLAT #3 OUTBD
L SLAT #4 OUTBD
L SLAT #5 OUTBD
L SLAT #6 INBD
L SLAT #1 INBD
L SLAT #2 INBD
L SLAT #3 INBD
L SLAT #4 INBD
L SLAT #5 INBD
L SLAT #6 OUTBD
R SLAT #12 OUTBD
R SLAT #11 OUTBD
R SLAT #10 OUTBD
R SLAT #9 OUTBD
R SLAT #8 OUTBD
R SLAT #7 INBD
R SLAT #12 INBD
R SLAT #11 INBD
R SLAT #10 INBD
R SLAT #9 INBD
R SLAT #8 INBD
R SLAT #7 OUTBD
400
401*
402*
403*
404*
405*
406
407
408
409
CARGO DOOR CONTROL
T/R IND LEFT
T/R IND RIGHT
T/R AUTO RESTOW L
T/R AUTO RESTOW R
ENTRY DOOR CONTROL
DOOR SYSTEM
LG SYSTEM #1
LG SYSTEM #2
LE SLATS
421
422
423
424
425
426
427
428
LDG GR LVR DOWN 1
LDG GR LVR DOWN 2
SLAT CMD TO RET 1
SLAT CMD TO RET 2
SLAT CMD TO T/O 1
SLAT CMD TO T/O 2
SLAT CMD TO LDG 1
SLAT CMD TO LDG 2
28V DC INPUT POWER
DISCRETE INPUTS
SENSOR CARD
TARGET
VERIFY
TARGET TEST
BIT
RESET
SLAT PSEU BITE
B767-3S2F
276
277
278
279
280
281
282
283
284
285
286
287
294
295
296
297
298
299
300
301
302
303
304
305
PROXIMITY SWITCH
SYSTEM
PSEU (E1-2)
LEFT FRONT DOOR
SENSOR (TARGET)
LEADING EDGE SLATS
TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
CODES 423-428 FROM
FSEU M545
RIGHT FRONT DOOR
B767-3S2F
Page - 146
ATA 27-80
11/11/13
EFF - ALL
TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
SLAT ASYMMETRY INDICATION
General
The Proximity Switch Electronic Unit (PSEU) monitors each slat to detect a
difference between left and right wing slat positions (asymmetry). Inboard and
outboard slat system PSEU proximity card logic signals, based on sensor/target
near or far position, input to the PSEU logic card to detect an asymmetry
condition in either system. There are two logic position signals from the
proximity card to the logic card for each slat. On the logic card the two left
inboard and two right inboard position signals are grouped separately. On the
outboard slat system the ten left and ten right position signals are grouped
separately. The logic card also groups the position signals by slat position retracted, intermediate (takeoff) and fully extended.
Operation
The PSEU detects an inboard or outboard slat asymmetry condition when the
proximity card position signals to the logic card show a difference between the
left and right groups for any of the slat positions, e.g. the position signals for the
outboard slat system show all sensor/targets near in the left group and one
sensor/target far in the right group at the intermediate (takeoff) position.
When an asymmetry is detected, a PSEU driver inputs a signal to the flap slat
electronic unit (FSEU). The signal is latched until the asymmetry signal from
the PSEU is removed. If an asymmetry shutdown is latched, by moving the flap
lever, the asymmetry latch can be reset by cycling the alternate slat arm switch
if the PSEU has removed the asymmetry signal. If an asymmetry latch is set for
longer than four seconds (ten seconds in alternate drive), the slat light and LE
SLAT ASYM caution message are displayed. The indication will be displayed
until the FSEU asymmetry latch is reset.
Maintenance Practices
Slat asymmetry indication is caused by an actual asymmetry resulting from a
disconnected slat drive system or a slat sensor or target fault.
L/R STALL
WARNING
LANDING
CONFIG
WARNING
ENGINE
IGNITION
CONTROL
28V AC FAIL
LEVER OR SLAT
PDU XMTR FAIL
FLAP/SLAT ELEC (S,M)
LE SLAT ASYM (B)
OUTBD SLATS
L OUTBD SLAT
POSITION
R OUTBD SLAT
POSITION
SHUTDOWN
SLAT
ASYM
LEADING
EDGE
OUTBD ASYM
HYD OPER
PSEU
LE LIGHT
4S
OUTBD ASYM
ALT OPER
10 S
FSEU (SECT 1)
NOTE: OUTBOARD SHOWN
INBOARD IS SIMILAR
SLAT ASYMMETRY INDICATION
B767-3S2F
Page - 147
ATA 27-80
11/11/13
EICAS
ASYM S/D
EFF - ALL
TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
B767-3S2F
Page - 148
ATA 27-80
11/11/13
EFF - ALL
TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
SLAT DISAGREE INDICATION
General
The proximity switch electronic unit (PSEU) compares slat position signals from
proximity sensors at each slat with flap lever or alternate flap position selector
switch position inputs from the flap slat electronic unit (FSEU) to detect a slat
disagreement.
Operation
When the flap lever is moved during primary drive slat system operation or the
alternate flap position selector switch is moved during alternate operation, the
PSEU sends a disagree signal to the FSEU. When the proximity sensors show
agreement with slat command the PSEU removes the disagree signal. A PSEU
disagree input is inhibited in the FSEU when any of the following conditions
exist.
• Either inboard or outboard slat PDU is moving toward the flap lever or
alternate flap position selector switch position (command) in primary or
alternate operation
• The flap drive is moving toward the flap lever position in primary operation
• The slats are commanded up in primary or alternate operation and the
flaps are not retracted
• A slat asymmetry condition exists
If the PSEU disagree signal is present after the inhibits are removed, the FSEU
causes display of the LEADING EDGE light and LE SLAT DISAGREE caution
message after ten seconds.
Maintenance Practices
Slat disagree indications are displayed when the PSEU detects all sensors in
the inboard or outboard group in disagreement with command.
This condition is caused by a jammed slat drive, command input without
hydraulic or electrical drive power, or a faulted FSEU flap lever or alternate
position selector switch position input to the PSEU.
SLAT DISAGREE
INBD
SLAT
POSITION
SLAT SEQUENCE
DURING RETRACT
FLAPS MOVING
TOWARD CMD POSN
INBD SLATS PDU MOVING
TOWARD CMD POSN
10
FLAP/SLAT ELEC
(S,M)
COMMANDED
POSITION
28V AC FAIL
L FSPM FAIL
FLAP LEVER
POSN XMTR
FAIL
PSEU
LE SLAT DISAGREE
(B)
ALTN FLAPS
5
1
FLAP
LEVER
POSN
UP
20
SW = NORM
NORM
25
30
LE
ALTN
FLAP
POSN
SW
EICAS COMPUTERS
15
TE
ALTN
7
ARMED
LEADING TRAILING
EDGE
EDGE
FLAP LIMIT (IAS)
225K
ALTN
250K
SLAT ASYM
(SECT 1)
FSEU
(SECT 1)
15
20
UP
25
FSEU (SECT 2)
NOTE : INBOARD SLATS SHOWN
OUTBOARD SLATS SIMILAR
ATA 27-80
11/11/13
EFF - ALL
190K
170K
FLAP INDICATOR
(P3-1)
SLAT DISAGREE INDICATION
Page - 149
205K
FLAPS
30
B767-3S2F
215K
5
1
TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
B767-3S2F
Page - 150
ATA 27-80
11/11/13
EFF - ALL
TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
SLAT ASYMMETRY AND FAILURE PROTECTION SHUTDOWN
Operation
Asymmetry Protection Shutdown:
An asymmetry condition detected by the Proximity Switch Electronic Unit
(PSEU), in the inboard or outboard slat systems, is signaled to the Flap Slat
Electronic Unit (FSEU) for protective shutdown. The asymmetry signal is
latched in the FSEU and annunciated until the signal is removed by the PSEU.
If the flap lever is moved with a latched asymmetry, the FSEU energizes the
inboard or outboard slat fail protection and asymmetry relay to bypass the
hydraulic motor. The shutdown and asymmetry annunciation are latched and
will not reset if the PSEU removes the asymmetry signal. Cycling the alternate
slat arm switch on and off will reset the asymmetry shutdown latch, de-energize
the fail relay, and energize the bypass valve normal relay to restore hydraulic
motor operation and clear the asymmetry annunciation.
Failure Protection Shutdown when: The FSEU compares the flap lever and
power drive unit (PDU) transmitters (RVDT) to detect uncommanded movement
of the inboard or outboard slat systems. If the slats are moving away from the
flap lever position, the FSEU operates the fail relay to bypass the hydraulic
motor. The failure shutdown latch can be reset by cycling the alternate slat arm
switch to de-energize the fail relay, energize the normal relay and restore
hydraulic motor operation. The latch also resets when the flap lever is up and
the slats are retracted.
Maintenance Practices
When the inboard or outboard fail protection and asymmetry relay is energized,
other than by an asymmetry shutdown latch, LE SLAT SHUTDOWN status and
maintenance messages will be displayed. Cycling the alternate slat arm switch
on and off will clear the message and restore hydraulic motor operation by
positioning the bypass valve from the bypass to the normal position.
115V AC
STBY BUS
FSEU SENSOR
POWER XMTR
28V DC
SLAT ALT ARM SW
P37
NORM
SLAT BYPASS
VLV NORMAL
RELAY
UNCOMMANDED MOTION
XMTR 1
28V AC
POWER
SUPPLY
SLAT MOVING
BYPASS
1
AWAY FROM POSN
SLAT BYPASS
VALVE
SLATS = LEVER
SLAT PDU
2
ALT ARM SW ARMED
LATCH
TO ALT
ELEC MOTOR
(CLUTCH)
SLAT XMTR FAILURE
FLAP XMTR FAILURE
ASYMMETRY (SHUTDOWN)
1
A
XMTR 2
FLAP LEVER
LEVER MOVEMENT
S/D
LATCH
ALT ARM SW ARMED
SLAT XMTR FAILURE
INBD SLAT
FAIL PROT
AND ASYM
RELAY
FLAP XMTR FAILURE
ASYMMETRY (NO SHUTDOWN)
1
ALT ARM SW ARMED
LE SLAT
A
SHUTDOWN
PDU POSN = LEVER
PSEU (E1-2)
LEVER IN DETENT
LATCH
ASYMMETRY
ANNUNCIATION
SLAT ASYM
FSEU (SECT 1)
NOTE: INBD SHOWN
OUTBD IS SIMILAR
CYCLE THE ALT SLAT ARM SW TO RESET
1
SLAT ASYMMETRY & FAILURE PROTECTION SHUTDOWN
B767-3S2F
Page - 151
ATA 27-80
11/11/13
EFF - ALL
TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
(S/M)
EICAS