曝光台 注意防骗
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PDU to ensure proper operation.
POWER PLANT
For Training Purposes Only
May 03
18-23
P I LOT T R A I N I N G GU I D E
Thrust Reverser Operation
Figure 18-13
Bypass
Airflow
Bypass
Airflow
Core
Airflow
Blocker Door
Deployed
WITH REVERSER DEPLOYED
Cascade
Vanes
Blocker
Door Stowed
Translating
Cowl
Bypass
Airflow
Bypass
Airflow
Core
Airflow
NORMAL OPERATION
THRUST REVERSER
LEVER
P604_18_009
THRUST REVERSER
LEVER
POWER PLANT
18-24 For Training Purposes Only
May 03
P I LOT T R A I N I N G GU I D E
GND SPOILERS/THRUST REVERSER Panel
Figure 18-14
The thrust reverse system incorporates the following safety features:
• In-flight protection - The reversers are locked out in flight. WOW (weight-onwheels)
signals from the Proximity Sensing Electronics Unit (PSEU) or wheel
spin-up (from the anti-skid control unit) must be sensed in order to energize the
thrust reverser deploy relays
• Flexshaft lockpin and lock cam - The reverse thrust PDU flexshaft is equipped
with a lock pin and lock cam, as well as a brake, which act to prevent
uncommanded travel of the reverser by more than 1/4 of an inch from the fully
stowed position
• Auto stow - In the event of flexshaft lock cam failure resulting in uncommanded
movement of the thrust reverser away from the fully stowed position, the stow
solenoid will energize, and provided 14th-stage bleed air is available, the thrust
reverser will be returned to the fully stowed position
• Automatic thrust lever retard system - An auto-retarding thrust lever
mechanism ensures that the thrust lever is at idle whenever the thrust reverser is in
transit. In flight, should a thrust reverser inadvertently deploy, the affected thrust
lever is automatically retarded to IDLE and locked to minimize asymmetric thrust
• Emergency Stow - A thrust reverse emergency stow system is installed to stow an
unlocked thrust reverser. Selecting the respective UNLK switch/light on the
THRUST REVERSER panel directs 14th-stage bleed air to the PDU to stow the
unlocked reverser
While the UNLK switch/light is selected, 14th-stage bleed air is
continuously applied to the PDU even if the reverser returns to
the stowed position.
NOTE
L ARMED
EMER STOW
OFF
R ARMED
OFF
GND SPOILERS
THRUST
REVERSER
ARM
AUTO
DISARM
UNLK UNLK
L R
P604_18_023
POWER PLANT
For Training Purposes Only
Jan 04
18-25
P I LOT T R A I N I N G GU I D E
Controls and Indicators
The CF 34-3B engine controls consist of the following:
• Thrust levers
• Thrust reversers
• Engine start/Ignition panel
• Engine control panel
The EICAS Primary and Secondary pages provide analog and digital engine
information and system warning/caution and advisory messages.
Engine Starting
Engine Start/Ignition Panel
Figure 18-15
IGNITION
S
T
A
R
T
S
T
A
R
T
S
T
O
P
S
T
O
P
A
B
ARM
ON
ARM
ON
STOP STOP
START
L-ENG-R
START
ON
IGNITION
S
T
A
R
T
S
T
A
R
T
S
T
O
P
S
T
O
P
CONT
A
B
ARM
ON
ARM
ON
STOP STOP
START
L-ENG-R
START
ON
L (R) ENGINE START Switch/Lights
Press momentary
START Light
Illuminated
- Initiates engine start sequence
- Indicates associated air turbine start (ATS) valve is open
L (R) ENGINE STOP Switches (momentary-action)
Press momentary - Stops the engine start sequence (acts as an ATS
cutout switch)
CONT
IGNITION A (B) Switch/Lights
(alternate-action)
Press
ARM Light
Illuminated
ON Light
Illuminated
- Arms associated
engine ignition system
- Indicates
associated ignition has been
armed (IGN A (B) switch/light
selected)
- Indicates
associated ignition is energized
: IGN A or B switch/lights
do not have to be armed for
continuous ignition
Note
CONTINUOUS IGNITION
Switch/Light (alternateaction)
Press
ON Light
Illuminated
- Manually energizes
ignition system A and B
- Indicates that
continuous ignition is being
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