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POWER PLANT Description Vol. 2 19.10.20
Oct 05/06
Reverse thrust is generated by blocking fan bypass airflow, and redirecting it forward through a series of cascade vanes. Bleed air, from the 14th stage of the compressor, pneumatically activates a power drive unit (PDU), which mechanically moves the engine translating cowls rearward by means of a flexible driveshaft and ballscrew actuators. As the translating cowl moves rearward, blocker doors rotate to redirect fan airflow forward through the cascade vanes.
Reverser deployment is accomplished by squeezing the thrust reverser triggers and applying upward pressure on the thrust reverse levers. Thrust reverse lever movement is initially restricted to approximately 20 degrees by a solenoid stop and a reverse thrust lever lock. This locks the thrust lever in the IDLE position, and prevents thrust from being applied. When the translating cowl reaches full aft travel, the solenoid stop is released, allowing the reverse lever to be operated though its full range, and reverse thrust to be applied.
During normal thrust reverser deployment, an amber REV icon appears in the engine N1 gauge while the reverser is in transit. When the reverser is fully deployed, the REV icon changes to green. Reverser deployment is achieved in approximately 5 seconds.
Anti-Ice Disable
On touchdown, or during rejected takeoff with the wing and/or cowl anti-ice system on, the anti-ice systems are automatically disabled while the thrust reversers are activated. This disabling action redirects all 14th-stage bleed air to the thrust reverser PDU to ensure proper operation.
POWER PLANT Description Vol. 2 19.10.21
Oct 05/06
Thrust Reverser Operation
Figure 19.10.13
POWER PLANT Description Vol. 2 19.10.22
Oct 05/06
GND SPOILERS/THRUST REVERSER Panel Figure 19.10.14
The thrust reverse system incorporates the following safety features:
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In-flight protection – The reversers are locked out in flight. WOW (weight-on-wheels) 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.
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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.
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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.
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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.
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