(1)
The rotorcraft is safely controllable when the failure or malfunction occurs at any speed or altitude withinthe approved operating limitations;

(2)
The controllability and maneuverability requirements of this Part are met within a practical operational .ight envelope (for example, speed, altitude, normal acceleration, and rotorcraft con.gurations) which is described in the Rotorcraft Flight Manual; and

(3)
The trim and stability characteristics are not impaired below a level needed to

permit continued safe .ight and landing.] Amdt. 27-21, E.. 12/6/84
FAR27.673:[Primary .ightcontrol.]
[Primary .ight controls are those used by the pilot for immediate control of pitch, roll, yaw, and vertical motion of the rotorcraft.] Amdt. 27-21, E.. 12/6/84
FAR27.674 :[Interconnected controls.]
[Each primary .ight control system must provide for safe .ight and landing and operateindependently after a malfunction,failure, orjam of any auxiliaryinterconnected control.] Amdt. 27-26, E.. 4/5/90
FAR 27.675 : Stops
(a)
Each control system must have stops thatpositivelylimit the range of motion of the pilot’s controls.

(b)
Each stop must be located in the system so that the range of travel of its control is not appreciably a.ected by–

(1)
Wear;

(2)
Slackness; or

′
Elodie Roux. Septembre 2003
Subpart D : Design and Construction
(3) Takeup adjustments.
(c)
Eachstop mustbe able to withstandtheloads correspondingto thedesign conditions for the system.

(d)
For each main rotor blade–

(1)
[Stops thatare appropriateto thebladedesign mustbeprovidedtolimit travel oftheblade aboutitshingepoints; and]

(2)
There must be means to keep the blade from hitting the droop stops during any operation other than starting and stopping the rotor.

Amdt. 27-16, E.. 12/1/78
FAR 27.679 : Control system locks
If there is a device to lock the control system with the rotorcraft on the ground or water, there must be means to–
(a)
Give unmistakable warning to the pilot when the lock is engaged; and

(b)
Prevent the lock from engaging in .ight.

FAR 27.681 : 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.

(b)
Compliance mustbe shown(by analyses orindividualload tests) with the special factor requirementsfor control systemjoints subjectto angular motion.

FAR 27.683 : Operation tests
It must be shown by operation tests that, when the controls are operated from the pilot compartment with the control system loaded to correspond with loads speci.ed for the system, the system is free from–
(a)
Jamming;

(b)
Excessive friction; and

(c)
Excessive de.ection.

FAR 27.685 : Control system details

(a)
Eachdetail of each control system mustbedesigned topreventjamming, cha.ng, andinterferencefrom cargo,passengers,loose objects, orthefreezing of moisture.

(b)
There must be means in the cockpit to prevent the entry of foreign objects into places wherethey wouldjamthe system.

(c)
There mustbe meanstopreventthe slapping of cables ortubes againstotherparts.

(d)
[Cable systems must be designedas follows :

(1) Cables,cable .ttings,turnbuckles,splices,andpulleysmustbeofanacceptable kind.
(2)
The design of the cable systems must prevent any hazardous change in cable tension throughout the range of travel under any operating conditions and temperature variations.
　
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本文鏈接地址：FAA規章 美國聯邦航空規章 Federal Aviation Regulations 4(90)