|
cacnhasdffaliern cjiBr
OPERATING MANUAL
PSP 601A-6
SECTION 13
HYDRAULICS
TABLE OF CONTENTS
Page
GENERAL 1
HYDRAULIC SYSTEM COMPONENTS 1
A. Engine Pumps (2) 1
B. Electric Pumps (4) 1
C. Reservoirs (3) 2
D. Accumulators (3) 2
E. Heat Exchanger 2
LANDING GEAR 2
A. Landing Gear Control Unit 3
B. Landing Gear Control Lever 3
MAIN LANDING GEAR BAY OVERHEAT DETECTION SYSTEM 3
NOSE WHEEL STEERING 4
BRAKES AND ANTI-SKID SYSTEM 4
A. Brakes 4
B. Anti-Skid System 5
C. Parking Brake 5
LIST OF ILLUSTRATIONS
Figure Title Page
Number
1 Hydraulic System - Schematic (3 Sheets) 6
2 Hydraulic System Controls and Indicators 9
3 Landing Gear Controls and Indicators 10
4 Main Landing Gear Bay Overheat Warning Lights 11
5 Nose Wheel Steering Controls and Indicators 12
6 Brake and Anti-Skid Controls and Indicators 13
13-CONTENTS
Page 1
Aug 14/02
cacnhaadJalsirn qer
OPERATING MANUAL
PSP 601A-6
SECTION 13
HYDRAULICS
GENERAL (Figure 1)
Hydraulic power for operation of the flight controls, landing gear, nose
wheel steering and brakes is supplied by three independent hydraulic systems,
designated No. 1, No. 2 and No. 3.
No. 1 system is pressurized by an engine pump on the left engine and/or by an
electric pump. A system reservoir and an accumulator complete the system,
and are located with the electric pump on the left side of the rear equipment
bay.
No. 2 system is similar to No. 1 system except that its engine pump is on the
right engine and its electric pump, reservoir and accumulator are located on
the right side of the rear equipment bay.
No. 3 system is pressurized by either of two electric pumps, designated 3A
and 3B, and supplied by a system reservoir and an accumulator, all located in
or near the main landing gear bay. The pumps are on either side of the
fuselage aft of the main landing gear bay, the reservoir is between the wheel
bins, and the accumulator is forward and outboard of the right wheel bin.
HYDRAULIC SYSTEM COMPONENTS (Figures 1 and 2)
A. Engine Pumps (2)
The engine pumps are driven by their associated engine accessory gearbox.
Each pump automatically varies its displacement to control fluid outlet
pressure at a nominal 3000 psi. A shutoff valve in each pump supply line
closes when operated by its associated LH (or RH) ENG FIRE PUSH
switch/light on the glareshield.
On aircraft 5041 and 5146,
the shutoff valves can be closed if the EDP SHUT/SOV FAULT switch lights
on the HYDRAULIC SYSTEMS panel are selected.
B. Electric Pumps (4)
The electric pumps have the same mechanical operation as the engine
pumps. No. 1 pump is supplied by ac main bus No. 2, and No. 2 pump is
supplied by ac main bus No. 1. This cross-side power supply arrangement
ensures continued pressurization of both No. 1 and No. 2 hydraulic
systems by at least one pump on each system (one electric pump, one
engine pump) should one engine fail or be shut down (refer to Figure 1
for operation of generator line contactors). No. 3B pump is supplied by
ac main bus No. 1. Should this bus become unpowered in flight as a
r e s u l t of a l l ac power being l o s t , the a i r driven generator (ADC)
automatically deploys and powers the pump directly, bypassing the pump
ON/OFF control switch. This arrangement ensures continued operation of
No. 3 hydraulic system using pump 3B only.
SECTION 13
Page 1
Aug 14/02
canadair
chsuiencjBr
OPERATING MANUAL
PSP 601A-6
C. Reservoirs (3)
The hydraulic system reservoirs are of the self-pressurizing, bootstrap
type. A suction pressure of 55 psi is maintained by associated system
pressure acting on a piston within each reservoir. Each reservoir has a
direct reading fluid level indicator, a fluid temperature probe and an
overflow line connected to an overflow tank.
D. Accumulators (3)
Each piston-type accumulator maintains pressure when rapid increases in
demand are made on the associated system. The accumulator pre-charged
pressure can be read on a gauge located near the accumulator. Should a
double engine failure occur, No. 3 system accumulator would also cater to
the flight control requirements until the air-driven generator (ADG) came
on line.
E. Heat Exchanger
A ram air heat exchanger, with separate cores for No. 1 and No. 2
systems, is located aft of the rear equipment bay door. Ram air from the
dorsal fin inlet cools the cores in flight. An automatic,
temperature-controlled, electric blower cools the cores if an overheat
condition occurs. The No. 3 system is cooled by its hydraulic lines
running through the fuel in the wing tanks.
3. LANDING GEAR (Figure 3)
The main landing gear retracts inward into a recess in the wing and centre
fuselage, and the nose landing gear retracts forward beneath the flight
compartment. Normal extension and retraction is electrically controlled and
hydraulically operated. Hydraulic pressure for normal landing gear operation
is supplied by No. 3 hydraulic system.
For emergency landing gear operation, the gear may be extended by pulling the
landing gear manual release T-handle in the flight compartment. The handle
mechanically releases the landing gear uplocks and dumps hydraulic pressure,
allowing the gear to free-fall. The gear is assisted by a combination of
airflow and spring pressure on the nose gear, and by a down-lock assist
actuator, supplied by No. 2 hydraulic system, on the main gear.
The landing gear control lever is positioned on the right side of the centre
instrument panel. Landing gear position indications are given by three green
lights above the landing gear selector and flashing red lights in the landing
gear handle. An aural warning is also provided to warn of unsafe gear
configuration for the flight conditions.
SECTION 13
Page 2
Apr 02/87
ctianencjer
OPERATING MANUAL
PSP 601A-6
A, Landing Gear Control Unit
The landing gear control unit contains two circuits: a landing gear
control circuit and a weight-on wheels circuit,
The landing gear control circuit processes landing gear control information
using inputs from the landing gear proximity switches, the landing gear
control lever and the throttle levers. Outputs from the circuit consist of
landing gear command signals* landing gear control lever indicator/interlock
signals and aural warning signals.
The weight-on-wheels (WOW) circuit provides two independent outputs
designated WOW 1 and WOW 2. Each WOW output circuit receives proximity
switch signals and passes either a weight-on-wheels or a weight-off-wheels
signal to aircraft systems using WOW information. A comparator circuit
causes the appropriate light below the landing gear lever to come on to
warn of system malfunctions.
B. Landing Gear Control Lever
The landing gear control lever has a solenoid-operated downlock which
prevents inadvertent selection of gear UP with a weight-on-wheels signal
input. A release button adjacent to the control lever permits the landing
gear to be retracted if the downlocks fail to disengage normally, due to a
fault in the solenoid circuit, when gear UP is selected.
4. MAIN LANDING GEAR BAY OVERHEAT DETECTION SYSTEM (Figure 4)
Overheat and fire detection is provided for the main landing gear bay by
fire-sensing cables, which are routed around the top inner surface of each main
wheel bin and connected to a detection control unit. Two switch/lights marked
OVHT and OVHT WARN FAIL, located below the landing gear lever, provide the
required warnings and test functions.
The detection control unit, which has two channels, overheat and
short-to-ground, discriminates between an actual overheat condition and a short
circuit.
SECTION 13
Page 3
Apr 02/87
OPERATING MANUAL
PSP 601A-6
NOSE WHEEL STEERING (Figure 5)
The nose wheel steering system is an electro-hydraulic system controlled by an
electronic control module (ECM). With the nose gear down and locked, weight on
wheels, and the N/W STEER switch ARMED, the nose wheel steering is available
using the steering quadrant or the pilot's or copilot's rudder pedals. Full
movement of the steering quadrant commands 55 degrees of nose wheel steering
and full deflection of the rudder pedals commands 7 degrees of nose wheel
steering. Steering quadrant inputs and rudder pedal inputs are cumulative but
will not command steering angles greater than 55 degrees. Thus, if the
steering controls are crossed, nose wheel rotation equals the difference
between the two steering signals. If the steering controls are coordinated,
the nose wheel rotates to an angle equal to the sum of the steering commands.
With steering command capabilities of 55 degrees from the steering quadrant and
of 7 degrees from the rudder pedals, the steering quadrant can override the
rudder pedals by a 55 to 7 ratio.
When the N/W STEER switch is OFF, if hydraulic power is removed from the system
or if an automatic shutdown has been commanded by the ECM, the system reverts
to a free castoring mode. In this mode, the nose wheel is free to castor up to
99 degrees from the centered position. Free castoring can be used during
towing or when asymmetric thrust and braking must be used to obtain a low
turning radius.
With the system operating and the nose wheel near the maximum steering angle,
steering angles greater than 55 degrees can be obtained on rough terrain or
when normal steering inputs are augmented by differential application of brakes
or engine thrust. In this case, the ECM automatically places the system in the
free castoring mode and steering can only be re-engaged by reducing the
steering angle to below 55 degrees and cycling the N/W STEER switch between OFF
and ARMED.
BRAKES AND ANTI-SKID SYSTEM (Figure 6)
A. Brakes
Each main wheel is fitted with a hydraulic disc brake unit. The inboard
brakes are powered by the No. 3 hydraulic system and the outboard brakes by
the No- 2 hydraulic system. Each hydraulic system has a brake accumulator
which provides sufficient hydraulic pressure for approximately eight brake
applications in the event of hydraulic power failure or shutdown. A
hydraulic fuse in each brake line prevents complete loss of fluid should a
leak in the brake area occur. Blowout plugs installed in the wheels
prevent tire blowouts should the heat generated by the brakes become
excessive- Pre-charge pressure gauges, for both brake system accumulators,
are located in the nose landing gear bay on the forward left-hand side.
SECTION 13
Page 4
Apr 02/87
cacnhaaduaeinr Qer
OPERATING MANUAL
PSP 601A-6
Anti-Skid System
The anti-skid system consists of a skid control unit, two dual anti-skid
control valves and wheel speed sensors in each main wheel. The system
independently controls the braking of each main wheel by automatically
varying the hydraulic pressure output of each dual brake control valve
before these outputs reach the brakes.
An arming switch on the anti-skid panel controls power to the skid
control unit.
Inputs received by the control unit are weight-on-wheels and wheel
velocity information. The control unit outputs consist of control
signals to the anti-skid valves, warning signals to failure indication
lights and a logic wheel spin-up signal to the ground spoiler control
unit.
The anti-skid system has the following features:
Modulated skid prevention of each wheel through the primary anti-skid
circuits.
Locked wheel protection, which prevents a deep skid or failure of a
wheel to spin-up at touchdown, also provides a coarse backup circuit
in the event of failure of the primary anti-skid circuit.
Pre-landing protection prevents brake application at all wheels while
the aircraft is still airborne, but is overridden to allow normal
skid-controlled braking as soon as the wheels have spun up.
Built-in test equipment provides a system check both on the ground
(pre-take-off) and in the air (pre-landing).
Parking Brake
The parking brake system consists of a parking brake handle mounted at
the lower right edge of the pilot's instrument panel connected, via a
push-pull cable assembly, to the lever of the dual brake valve control
mechanism.
Fully depressing both brake pedals on either the pilot's or copilot's
side, and pulling then rotating the brake handle, latches the brake valve
control mechanism, thereby securing both dual brake valves in the on
position.
SECTION 13
Page 5
Mar 10/95
chzfliencjer
OPERATING MANUAL
PSP 601A-6
FROM LEFT ENGINE
AC GENERATOR
SWITCH/
LIGHT
SHUT
SOV
FAULT
EFFECTIVITY:
A/C5041 AND 5146 \
SWITCH/
LIGHT
c AC BUS 2
LH ENG
FIRE
PUSH
RESERVOIR WARNING
LIGHT
-Ar HI
TEMP
ELECT A *
PUMP / | \ K GLC 2
OFF/ ^
0 N ^ WARNING
LIGHT
j
NOTE
A Generator Line Contactor 2 (GLC 2); only energized (contact made)
when right engine generator is powering AC Bus 2 or when
a weight-on-wheels signal is present.
HYDRAULIC
SYSTEM
NO. 1
Hydraulic System - Schematic
Figure 1 (Sheet 1)
SECTION 13
Page 6
Aug 14/02
cacnhaaduaeinr qer
OPERATING MANUAL
PSP 601A-6
FROM RIGHT ENGINE
AC GENERATOR
SWITCH/
LIGHT
Generator Line Contactor 1 (GLC 1); only energized (contact made)
when left engine generator is powering AC Bus 1 Or when
a weight-on-wheels signal is present.
PRE-CHARGE
PRESSURE
HYDRAULIC
SYSTEM
NO. 2
Hydraulic System - Schematic SECTION 13
Figure 1 (Sheet 2) page 7
Aug 14/02
_ _ _ j a i r chauBnQer
OPERATING MANUAL
PSP 601A-6
FROM LEFT ENGINE
AC GENERATOR
FROM RIGHT ENGINE
AC GENERATOR
A NOTE
ADG AC Emergency Transfer Contactor (ADG AC EMER TC)
automatically connects ADG Bus to No. 3 hydraulic system
pump 3B when both primary AC Busses fail.
LH ELEVATOR
m LHMLG
ACTUATOR
LHMLG
UPLOCK
i n NLG
UPLCK
NLG
DNLCK
RUDDER
RH ELEVATOR
nz\ RHMLG
UPLOCK
RHMLG
ACTUATOR
NLG
STEERING
LIZI NLG
ACTUATOR
NLGDR
ACTUATOR
PRE-CHARGE
PRESSURE
ACCUMULATOR
LH INBD
BRAKE
RH INBD
BRAKE
HYDRAULIC
SYSTEM
NO. 3
Hydraulic System - Schematic SECTION 13
Figure 1 (Sheet 3) Page 8
Mar 10/95
chanfUecn per
OPERATING MANUAL
PSP 601A-6
5 HYDRAULIC SYSTEMS 2
HI TEMP HI TEMP HI TEMP
ELECT
PUMP
L. ENG
PUMP
ELECT
PUMP
ELECT
PUMP
R. ENGI
PUMP
ELECT
PUMP
EDP SHUT/SOV FAULT SWITCH/LIGHT
White SHUT light comet on whenever engine
driven pump shutoff valve it in doted position.
Amber SOV FAULT light comet on to indicate
fault in engine driven pump control circuit.
HI TEMP
•EPP
ELECT " ™
PUMP -
L. ENG
PUMP
© EFFECTIVITY : A/C 5041 AND 5146
HIGH TEMPERATURE WARNING LIGHT
Light comes on to indicate that hydraulic fluid
temperature has exceeded upper limit.
AC ELECTRIC PUMP LOW PRESSURE
WARNING LIGHT
Warning light comes on at 1800 psi decreasing
pump discharge pressure and goes out at 2300
psi increasing pump discharge pressure. Warning
light is armed when AC electric pump control
switch is set to ON and/or wing flaps are
extended.
ELECT I I L. ENG
PUMP I PUMP
RESERVOIR QUANTITY INDICATOR
Gauge indicates the hydraulic fluid quantity in
the system reservoir. Normal quantity, with the
system operating, is 40% to 80% full (green
band). Gauge indicates 0% when electric power
is removed.
HYDRAULIC SYSTEM PRESSURE INDICATOR
Gauge indicates hydraulic pressure in the system.
Normal operating pressure is 3000 psi ± 150 psi.
Gauge indicates 0 psi when electrical power is
removed.
AC ELECTRIC PUMP ON-OFF SWITCH
Switch provides control of AC pump.
ENGINE DRIVEN PUMP LOW PRESSURE
WARNING LIGHT
Warning light comes on at 1800 psi decreasing
pump discharge pressure and goes out at 2300
psi increasing pump discharge pressure.
Hydraulic System Controls and Indicators SECTION 13
Figure 2 Page 9
Aug 14/02
, _ ™ - j a i r chaJlenqer
OPERATING MANUAL
PSP 601A-6
LANDING GEAR SAFE LIGHTS
NOSE, LEFT and RIGHT green lights
come on when respective landing gear
legs are down and locked.
LANDING GEAR HANDLE
Two-position handle. Controls landing
gear hydraulic operation.
UP - Pulling handle out then up retracts
landing gear, applies in-flight brakes and
closes nose wheel doors.
DN - Pulling handle out then down opens
nose wheel doors and extends and locks
nose and main landing gear legs.
DOWN LOCK RELEASE BUTTON
For manual override of landing gear
handle solenoid lock.
Pushing and holding DN LCK REL button
down allows normal landing gear
retraction with landing gear handle.
^ ^
LANDING GEAR UNSAFE LIGHTS
Two flashing red lights in landing gear
handle come on when landing gear leg
position does not agree with landing gear
handle position and while gear is in
transit.
GEAR WARNING MUTE HORN SWITCH
Landing gear warning horn sounds when
either throttle is retarded to IDLE and
down and locked signals are not received
from all three landing gear downlocks.
Pressing pushbutton switch mutes
landing gear warning horn. Pushbutton
amber light comes on to indicate mute
condition and will remain so until one or
both throttles are advanced beyond IDLE.
Aural warning also sounds when more
than 30 degrees of flap are selected in
absence of down and locked signals from
all three downlocks. Under these
conditions, warning cannot be muted by
pressing MUTE HORN button.
LANDING GEAR TEST SWITCH
When TEST pushbutton is pressed,
LEFT, NOSE and RIGHT green lights,
landing gear selector handle red lights,
MUTE HORN amber light and NO
SMOKING and FASTEN SEAT BELT
lights come on.
WEIGHT-ON-WHEELS (WOW) FAIL
LIGHTS
The appropriate caption comes on to
indicate a failure in either the WOW input
or WOW output system. The WOW input
system receives a WOW signal from
independent sensors, two on each
landing gear shock strut.
NOSE
DOOR
OPEN
NOSE LANDING GEAR DOORS OPEN
LIGHT
Light comes on when hydraulically
operated nose landing gear doors are
unlocked.
CENTRE INSTRUMENT RANEL
LANDING GEAR MANUAL RELEASE
HANDLE
Pulling handle releases landing gear legs
and nose wheel door up-locks, to allow
landing gear to free-fall and also supplies
No. 2 hydraulic system pressure to the
main landing gear free-fall down lock
assist actuators. Landing gear position
indicators and warnings operate normally
and gear cannot be retracted.
UENIKE PEDESTAL
Landing Gear Controls and Indicators SECTION 13
Figure 3 page 10
Apr 02/87
cttauenaer
OPERATING MANUAL
PSP 601A-6
OVHT SWITCH/LIGHT
When pressed, checks integrity of
circuit and causes red OVHT tight to
come on.
Red OVHT light comes on when
overheat condition is detected in the
main landing gear bay. Light goes
out. and system resets, when
overheat condition no longer
present.
MLG BAY
OVHT DETECT
OVHT WARN FAIL SWITCH/LIGHT
When pressed, checks system fault
detection capability and causes
amber OVHT WARN FAIL light to
come on.
Amber OVHT WARN FAIL light
comes on when a short in the
system is detected by the detection
control unit.
CENTRE INSTRUMENT PANEL
Main Landing Gear Bay Overheat Warning Lights
Figure 4
SECTION 13
Page 11
Apr 02/87
OPERATING MANUAL
PSP 601A-6
NW
STEER
FAIL
CENTRE INSTRUMENT PANEL
NW STEERL FAIL LIGHT
Red NW STEER FAIL light comes on if any
failure in steering system is detected by ECM.
ECM internal fault is detected or steering angle
exceeds 55 degrees. System reverts to free
castormg mode whenever light is on.
NOSE WHEEL STEERING ARM SWITCH
Switch provides ARMED-OFF control of hydraulic
nose wheel steering.
ARMED - Nose wheel steering will operate when
landing gear is down and locked and weight-on*
wheels signals are present from one or both
WOW systems.
OFF - Nose wheel hydraulic steering off. Nose
wheel will castor.
PILOTS FACIA PANEL
NOSE WHEEL STEERING QUADRANT
Steering quadrant rotates nose wheel (maximum
55°) when landing gear is down and locked.
wetght-on-wheeis signals are present from one or
both WOW systems and N/W STEER switch is
ARMED. Hose wheel is automatically centered
when nose landing gear strut is extended on
take-off.
PILOTS CONSOLE
RUDDER PEDAL STEERING
Rudder pedals (pact's and copilot's) rotate nose
wheel (maximum 7°) when conditions above for
nose wheel quadrant steering are met.
PILOTS RUDDER AND BRAKE PEDALS
Nose Wheel Steering Controls and Indicators SECTION 13
Figure 5 Page 12
Apr 02/87
cacnftaaauaeirn per
OPERATING MANUAL
PSP 601A-6
PARKING BRAKE LIGHT
Red light comes on when parking brake is
applied.
PILOT'S INSTRUMENT PANEL
PILOT'S INSTRUMENT PANEL
C PARKING BRAKE J
BRAKE PRESSURE INDICATOR
Indicates hydraulic pressure in the inner and
outer main wheel independent brake system.
Normal brake pressure is 3000 psi. Indicates 0 psi
when electrical power is removed.
PARKING BRAKE HANDLE
PARKING BRAKE ON - Apply and maintain full
brake pedal travel. Pulling parking brake handle
then causes a pair of latches in brake valve
control mechanism to engage, securing both
dual brake valves in the brake applied condition.
Rotating handle locks latches, at which point
pedal pressure may be relaxed.
PARKING BRAKE OFF - Parking brake is
released by applying pressure to brake pedals
until parking brake unloads. Handle is then
rotated 90 degrees to release is to stowed
position. Pressure on brake pedals is then
released.
PILOT'S INSTRUMENT PANEL
LOWER RIGHT EDGE
CENTRE PEDESTAL
INBD FAIL AND OUTBD FAIL LIGHTS
Amber lights come on to indicate failure of
associated brake anti-skid systems.
INBD TEST AND OUTBD TEST LIGHTS
White lights come on during test.
ANTI-SKID TEST BUTTON
When pressed for one second, tests anti-ckid
circuitry provided parking brake is off and antiskid
is ARMED. INBD FAIL, OUTBD FAIL, INBD
TET and OUTBD TEST lights coming on indicate
correct system operation. On releasing TEST
button, all four lights should go out.
ANTI-SKID ARM SWITCH
Switch provides ARM-OFF control of anti-skid
system.
ARM - Anti-skid system armed provided parking
brake is off.
OFF - Anti-skid sytstem is off.
Brake and Anti-Skid Controls and Indicators
Figure 6
SECTION 13
Page 13
Apr 02/87 |
IP卡
狗仔卡
发表于 2010-5-9 09:07:19
分享
收藏
提升卡
置顶卡
沉默卡
喧嚣卡
变色卡
显身卡
发表于 2010-5-18 10:34:35