(ii)
Thelandinggear extended; and

(iii) The takeo. safety speed selected by the applicant.

(2)
[The steady rate of climb without ground e.ect, 1000 feet above the takeo. surface must be at least 150 feet per minute, for each weight, altitude, and temperature for which takeo. data are to be scheduled with–

(i)
The critical engine inoperative and the remaining engines at maximum continuouspowerincluding continuousOEIpower,if approved, or at30-minute OEI power for rotorcraft for which certi.cation for use of 30-minuteOEIpoweris requested;]

(ii)
The most unfavorable center of gravity for climb following takeo.;

(iii) The landing gear retracted; and
(iv) The speed selected by the applicant.

(3)
The steady rate of climb (or descent) in feet per minute, at each altitude and temperature at which the rotorcraft is expected to operate and at any weight within the range of weights for which certi.cation is requested, must be determined with–

(i)
[The critical engine inoperative and the remaining engines at maximum continuous power including continuous OEI power, if approved, and at 30-minute OEI power for rotorcraft for which certi.cation for the use of 30-minute OEI power is requested;]

(ii)
The landing gear retracted; and

(iii) The speed selected by the applicant.

(b)
[For multiengine Category B rotorcraft meeting the Category A engine isolation requirements, the steady rate of climb(ordescent) mustbedetermined at the speed forbest rate of climb(or minimum rate ofdescent) at each altitude,temperature, and weight at which the rotorcraft is expected to operate, with the critical engine inoperative and the remaining engines at maximum continuous power including continuousOEIpower,if approved,and at30-minuteOEIpowerfor rotorcraftfor which certi.cation for the use of 30-minute OEI power is requested.]

Amdt. 29-44, E.. 11/17/99
FAR 29.71 : Helicopter angle of glide : Category B.
[For eachcategory B helicopter, except multiengine helicopters meeting the require-ments of Sec. 29.67(b) and the powerplant installation requirements of category A, the steady angle of glide must be determined in autorotation–
(a)
At the forward speed for minimum rate of descent as selected by the applicant;

(b)
At the forward speed for best glide angle;

(c)
At maximum weight; and

(d)
At the rotor speed or speeds selected by the applicant.] Amdt. 29-12, E.. 2/1/77

FAR29.73 :[Redesignated.]
Section 29.73 is redesignated as Sec. 29.49. The section number ”29.73” is no longer used in Part 29. Amdt. 29-39, E.. 6/10/96
FAR29.75 :Landing :[general.]
(a)
[For eachrotorcraft–

(1)
The corrected landing data must be determined for a smooth, dry, hard, and level surface;

(2)
The approach andlanding must not require exceptionalpiloting skill or excep-tionally favorable conditions; and

(3)
The landing must be made without excessive vertical acceleration or tendency tobounce, nose over,groundloop,porpoise, or waterloop.

(b)
The landing data required by Secs. 29.77, 29.79, 29.81, 29.83, and 29.85 must be determined–

(1)
Ateach weight, altitude, andtemperaturefor whichlandingdata are approved;

(2)
With each operating engine within approved operating limitations; and

(3)
Withthe most unfavorable center ofgravity.]

Amdt. 29-39, E.. 6/10/96
′
Elodie Roux. Septembre 2003
Subpart B : Flight
FAR29.77 :LandingDecisionPoint(LDP) :CategoryA.
(a)
[The LDP is the last point in the approachand landing path from which a balked landing can be accomplished in accordance with Sec. 29.85.

(b)
　
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