Amdt. 23-45, E.. 09/07/93
FAR 23.673 : Primary .ight controls.
Primary.ightcontrolsarethoseusedby thepilotfortheimmediate control ofpitch, roll, and yaw. Amdt. 23-48, E.. 03/11/96
FAR 23.675 : Stops.
(a)
[Each control system must have stops that positively limit the range of motion of each movable aerodynamic surface controlled by the system.

(b)
Each stop must be so located so that wear, slackness, or take-up adjustments will not adversely a.ect the control characteristics of the airplane because of a change in the range of surface travel.

(c)
Eachstop mustbe ableto withstand anyloads correspondingtothedesign conditions for the control system.]

Amdt. 23-17, E.. 02/01/77
FAR 23.677 : Trim systems.
(a) [Properprecautions must be taken topreventinadvertent, improper, or abrupt trim tab operation. There must be means near the trim control to indicate to the pilot the direction of trim control movement relative to airplane motion. In addition, there must be means to indicate to the pilot the position of the trim device with respect to both the range of adjustment and, in the case of lateral and directional trim, the neutral position. This means must be visible to the pilot and must be locatedanddesigned toprevent confusion.Thepitch trimindicator mustbe clearly marked with aposition or range within whichithasbeendemonstrated thattake-o. is safe for all center of gravity positions and each .ap position approved for takeo..]
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Elodie Roux. Septembre 2003
Subpart D : Design and Construction
(b)
Trimmingdevices mustbedesignedso that, when any one connecting ortransmitting element in the primary .ight control system fails, adequate control for safe .ight and landing is available with–

(1)
For single-engine airplanes, the longitudinal trimming devices; or

(2)
For multiengine airplanes, the longitudinal and directional trimming devices.

(c)
Tab controls must be irreversible unless the tab is properly balanced and has no unsafe .utter characteristics. Irreversible tab systems must have adequate rigidity and reliability in the portion of the system from the tab to the attachment of the irreversible unit to the airplane structure.

(d)
It mustbedemonstrated thatthe airplaneis safely controllableand that apilotcan perform all maneuvers and operations necessary to e.ect a safe landing following any probable powered trim system runaway that reasonably might be expected in service, allowing for appropriate time delay after pilot recognition of the trim system runaway. The demonstration must be conducted at the critical airplane weights and center ofgravitypositions.

Amdt. 23-49, E.. 03/11/96
FAR 23.679 : Control system locks.
[If there is a device to lockthe control system on the ground or water :
(a)
There must be a means to–

(1)
Give unmistakable warning to the pilot when the lock is engaged; or

(2)
Automatically disengagethedevicewhenthepilotoperatestheprimary .ight controls in a normal manner.

(b)
The device must be installed to limit the operation of the airplane so that, when the device is engaged, the pilot receives unmistakable warning at the start of takeo..

(c)
Thedevice musthave a meanstoprecludethepossibilityofitbecominginadvertently

engaged in .ight.] Amdt. 23-45, E.. 09/07/93
FAR 23.681 : Limit load static tests.
(a)
Compliance with the limit load requirements of this part must be shown by tests in which–

(1)
Thedirection of thetestloadsproducesthe most severeloadinginthe control system; and

(2)
Each .tting, pulley, and bracket used in attaching the system to the main structure is included.
　
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本文鏈接地址：FAA規(guī)章 美國聯(lián)邦航空規(guī)章 Federal Aviation Regulations 2(27)