(b)
Theprobable range ofvariations,during service, ofthedamping action oftheground resonance prevention means must be established and must be investigated during the test required by Sec. 29.241.]

Amdt. 29-30, E.. 4/5/90
′
Elodie Roux. Septembre 2003
Subpart D : Design and Construction
74.3 Control Systems
FAR 29.671 : General.
(a)
Each control and control system must operate with the ease, smoothness, and posi-tiveness appropriate to its function.

(b)
Each element of each .ight control system must be designed, or distinctively and permanently marked, to minimize the probability of any incorrect assembly that could result in the malfunction of the system.

(c)
[A means must be provided to allow full control movement of all primary .ight controls prior to .ight, or a means must be provided that will allow the pilot to determinethatfull control authority isavailablepriorto .ight.

Amdt. 29-24, E.. 12/6/84
FAR 29.672 : [Stability augmentation, automatic, and power-operated sys-tems.]
[If the functioning of stability augmentation or other automatic or power-operated system is necessary to show compliance with the .ight characteristics requirements of this Part, the system must comply with Sec. 29.671 of this Part and the following :
(a)
A warning which is clearly distinguishable to the pilot under expected .ight condi-tionswithout requiring thepilot’sattentionmustbeprovidedforanyfailureinthe stability augmentation system orin any other automatic orpower-operated system which could result in an unsafe condition if the pilot is unaware of the failure. Warning systems must not activate the control systems.

(b)
Thedesign of the stability augmentation system or of any other automatic orpower-operated system must allowinitial counteraction offailures without requiring excep-tionalpilotskill orstrength,by overriding thefailureby moving the .ightcontrols in the normal sense, and by deactivating the failed system.

(c)
It must be shown that after any single failure of the stability augmentation system or any other automatic or power-operated system,–

(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 allow continued safe .ight and landing.]

Amdt. 29-24, E.. 12/6/84
FAR29.673:[Primary .ightcontrols.]
[Primary .ight controls are those used by the pilot for immediate control of pitch, roll, yaw, and vertical motion of the rotorcraft.] Amdt. 29-24, E.. 12/6/84
FAR29.674 :[Interconnected controls.]
[Each primary .ight control system must provide for safe .ight and landing and operateindependently after a malfunction,failure, orjam or any auxiliaryinterconnected control.] Amdt. 29-30, E.. 4/5/90
FAR 29.675 : 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

(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]
　
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