(1)
Dynamic and endurance tests of rotors, rotor drives, and rotor controls;

(2)
Limit load tests of the control system, including control surfaces;

(3)
Operationtests ofthe control system;

(4)
Flight stress measurementtests;

(5)
Landinggeardrop tests; and

(6)
Any additional tests required for new or unusual design features. Amdt. 29-30, E.. 4/5/90

′
Elodie Roux. Septembre 2003
Subpart C : Strength Requirements
FAR 29.309 : Design limitations.
The following values and limitations must be established to show compliance with the structural requirements of this subpart :
(a)
The design maximum and design minimum weights.

(b)
The main rotor r.p.m. ranges,power on andpower o..

(c)
The maximumforward speedsforeach main rotorr.p.m. withinthe rangesdetermi-ned underparagraph(b) of this section.

(d)
The maximum rearward and sideward .ight speeds.

(e)
The center of gravity limits corresponding to the limitations determined under pa-ragraphs(b),(c), and(d) of this section.

(f)
The rotational speed ratios between each powerplant and each connected rotating component.

(g)
The positive and negative limit maneuvering load factors.

73.2 Flight Loads
FAR 29.321 : General.
(a)
The .ight load factor must be assumed to act normal to the longitudinal axis of the rotorcraft, and to be equal in magnitude and opposite in direction to the rotorcraft inertialoadfactor atthe center ofgravity.

(b)
Compliance with the .ight load requirements of this subpart must be shown–

(1)
At each weight from the design minimum weight to the design maximum weight; and

(2)
With any practical distribution of disposable load within the operating limi-tations in the Rotorcraft Flight Manual.

FAR 29.337 : Limit maneuvering load factor.
The rotorcraft must be designed for–
(a)
[A limit maneuvering load factor ranging from a positive limit of 3.5 to a negative limit of -1.0; or

(b)
Anypositivelimit maneuvering loadfactor notlessthan2.0 and any negativelimit maneuvering load factor of not less than -0.5 for which–]

(1)
The probability of being exceeded is shown by analysis and .ight tests to be extremely remote; and

(2)
The selectedvalues are appropriateto each weight conditionbetweenthedesign

maximum and design minimum weights. Amdt. 29-30, E.. 4/5/90
FAR 29.339 : Resultant limit maneuvering loads.
Theloads resultingfromthe application oflimitmaneuveringloadfactors are assumed to act at the center of each rotor hub and at each auxiliary lifting surface, and to act in directions and with distributions of load among the rotors and auxiliary lifting surfaces, so asto representeach critical maneuvering condition,includingpower-onandpower-o. .ight with the maximum design rotor tip speed ratio. The rotor tip speed ratio is the ratio of the rotorcraft .ight velocity component in the plane of the rotor disc to the rotational tip speed of the rotor blades, and is expressed as follows :
V cosα
μ=
ΩR where–
The airspeed along .ight path  (ft/s)
α  The angle between the projection, in the plane of symmetry, of the axis (rad) of no feathering and a line perpendicular to the .ight path (positive when axis is pointing aft)
Ω The angular velocity of rotor (rad/s) R The rotor radius (ft)
FAR 29.341 : Gust loads.
Each rotorcraft must be designed to withstand, at each critical airspeed including hovering,theloads resulting from vertical andhorizontalgusts of30feetper second.
FAR 29.351 : Yawing conditions.
(a)
Eachrotorcraft mustbedesignedfortheloads resultingfrom the maneuvers speci.ed inparagraphs(b) and(c) of this section, with–
　
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