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       45~.
CCM ALL
┏━━━━━━━━━━━━━━━━┳━━━━━━━━━━━━━━━━┳━━━━━━━━━━━┓
┃                                ┃                                ┃1.27.30     P 6       ┃
┃                                ┃                                ┣━━━━━┳━━━━━┫
┃I  -~ A318                      ┃I RECONFIGURATIONOCONTROL LAWS  ┃SEQ 001 1 ┃I REV 23  ┃
┃  .,,,.8, ,, ~L,~ A319          ┃                                ┃          ┃          ┃
┃ Lli,~ A320                     ┃                                ┃          ┃          ┃
┃      A~7-~'M" A321             ┃                                ┃          ┃          ┃
┃   FLIGHT CREW OPERATING MANUAL ┃                                ┃          ┃          ┃
┗━━━━━━━━━━━━━━━━┻━━━━━━━━━━━━━━━━┻━━━━━┻━━━━━┛
ALTERNATE LAW WITHOUT REDUCED PROTECTION
This is identical to alternate law except that it does not include the low-speed stability or
the high-speed stability. It includes only the load factor limitation.
PITCH CONTROL
The pitch direct law is a direct stick-to-elevator relationship (elevator deflection is
proportional to stick deflection).
In all configurations the maximum elevator deflection varies as a function of CG.
It is a compromise between adequate controllability with the CG forward, and
not-too-sensitive control with the CG aft.
There is no automatic trim : the pilot must trim manually.
The PFD displays in amber the message "USE MAN PITCH TRIM"
No protections are operative.
The ~ floor function is inoperative.
Overspeed and stall warnings are available as for alternate law.
LATERAL CONTROL
When flying in "direct law", the roll direct law associated with mechanical yaw contro
governs lateral control.
ROLL DIRECT LAW
The roll direct law is a direct stick-to-surface-position relationship. System gains are set
automatically to correspond to slat/flap configuration.
With the aircraft in the clean configuration, the maximum roll rate is about 30~ per second.
With slats extended, it is about 25~ per second.
To limit roll rate, the roll direct law uses only ailerons and spoilers N~ 4 and 5.
If spoiler N~ 4 has failed, spoiler N~3 replaces it.
If the ailerons have failed, all roll spoilers become active.
YAW MECHANICAL CONTROL
The pilot controls yaw with the rudder pedals.
The yaw damping and turn coordination functions are lost
CCM ALL
┏━━━━━━━━━━━━━━━━┳━━━━━━━━━━━━━━━┳━━━━━━━━━┓
┃I  -~ A318                      ┃         FLIGHT CONTROLS      ┃1.27.30     P 7   ┃
　
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本文鏈接地址：AIRBUS A320 Flight Crew Operating Manual3(92)