(i)
Atleast1:10ifthehorizontaldistance requiredto take o. andclimb over a 50-foot obstacle is determined for each weight, altitude, and temperature within the range for which certi.cation is requested; or

(ii)
[At least 1 :6under standard sea level conditions.]

(b)
Each helicopter must meet the following requirements :

(1)
VY must be determined–

(i)
For standard sea level conditions;

(ii)
At maximum weight; and

(iii) With maximum continuouspower on each engine.

(2)
[The steadyrate of climb must be determined–

(i)
At the climb speed selected by the applicant at or below VNE ;

(ii)
Within the range from sea level up to the maximum altitude for which certi.cation is requested;

(iii) For the weights and temperatures that correspond to the altitude range setforthinparagraph(b)(2)(ii) of this sectionandfor which certi.cation is requested; and
(iv) With maximum continuouspower on each engine.]
Amdt. 27-33, E.. 8/8/96
FAR 27.67 : Climb : one engine inoperative
For multienginedhelicopters,the steady rate of climb(ordescent), at VY (or at the speed for minimum rate of descent), must be determined with–
(a)
Maximum weight;

(b)
[The criticalengine inoperative and the remaining engines at either–

(1)
Maximum continuouspowerand,forhelicoptersfor which certi.cationforthe use of 30-minute OEI power is requested, at 30-minute OEI power; or

(2)
Continuous OEI power for helicopters for which certi.cation for the use of continuous OEI power is requested.]

Amdt. 27-23, E.. 10/3/88
FAR27.71 :[Glideperformance.]
[For single-engine helicopters andmultiengined helicopters that do not meet the Ca-tegory A engine isolation requirements of Part 29 of this chapter, the minimum rate of descent airspeed and the best angle-of-glide airspeed mustbedetermined in autorotation at–
(a)
Maximum weight; and

(b)
Rotor speed(s) selected by the applicant.] Amdt. 27-21, E.. 12/6/84

FAR 27.73 : Performance at minimum operating speed

(a)
For helicopters–

(1)
The hovering ceiling must be determined over the ranges of weight, altitude, and temperature for which certi.cation is requested, with–

(i)
Takeo.power;

(ii)
Thelandinggear extended; and

(iii) Thehelicopteringrounde.ect at aheight consistent with normaltakeo. procedures; and

(2)
The hovering ceiling determined under subparagraph (1) of this paragraph must be at least–

(i)
For reciprocatingenginepoweredhelicopters,4,000feet at maximum weight with a standard atmosphere; or

(ii)
For turbine engine powered helicopters, 2,500 feet pressure altitude at maximum weight at a temperature of standard +40 degrees F.

(b)
For rotorcraftother thanhelicopters, the steady rate of climb at the minimum opera-ting speed mustbedetermined, overthe ranges of weight, altitude, andtemperature for which certi.cation is requested, with–

(1)
Takeo. power; and

(2)
The landing gear extended.

FAR 27.75 : Landing
(a)
The rotorcraft must be able to be landed with no excessive vertical acceleration, no tendency to bounce, nose over, ground loop, porpoise, or water loop, and without exceptional piloting skills or exceptionally favorable conditions, with–

(1)
Approach orglide speeds appropriatetothetype of rotorcraft and selectedby the applicant;

(2)
The approach and landing made with–

(i)
Power o., for single-engine rotorcraft; and

(ii)
[For multiengined rotorcraft, one engine inoperative and with each ope-rating engine within approved operating limitations; and]
　
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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(69)