(3)
The approach and landing entered from steady autorotation.

(b)
Multienginedrotorcraft mustbe able tobelanded safely after completepowerfailure under normal operating conditions.

Amdt. 27-14, E.. 3/1/78
′
Elodie Roux. Septembre 2003
Subpart B : Flight
FAR 27.79 : Limiting height–speed envelope
(a)
If there is any combination of height and forward speed (including hover) under which a safelanding cannotbe made under the applicablepowerfailure conditionin paragraph(b) of this section, alimiting height-speed envelope mustbe established (includingall pertinent information) for that condition, throughout the ranges of–

(1)
Altitude, from standard sea level conditions to the maximum altitude capabi-lity of the rotorcraft, or 7,000 feet, whichever is less; and

(2)
[Weight,fromthe maximum weight(at sealevel)tothelesser weight selected by the applicantfor each altitude coveredbyparagraph(a)(1) of this section. For helicopters, the weight at altitudes above sea level may not be less than the maximum weight or the highest weight allowing hovering out of ground e.ect, which is lower.]

(b)
The applicable power failure conditions are–

(1)
For single-engine helicopters, full autorotation;

(2)
For multienginehelicopters, one engineinoperative(where engineisolationfea-tures ensure continued operation ofthe remaining engines); and the remaining engines atthegreatestpowerfor which certi.cationis requested; and

(3)
For other rotorcraft, conditions appropriate to the type. Amdt. 27-21, E.. 12/6/84

62.3 Flight Characteristics
FAR 27.141 : General
The rotorcraft must–
(a)
[Except as speci.callyrequired in the applicable section meet the .ight characteris-tics requirements of this subpart–

(1)
At the altitudes and temperatures expected in operation;]

(2)
Under any critical loading condition within the range of weights and centers ofgravity for which certi.cationis requested;

(3)
Forpower-on operations, under anycondition of speed,power, and rotor r.p.m. for which certi.cation is requested; and

(4)
For power-o. operations, under any condition of speed and rotor r.p.m. for which certi.cation is requested that is attainable with the controls rigged in accordance with the approved rigging instructions and tolerances;

(b)
Beabletomaintainanyrequired.ight conditionand makeasmooth transitionfrom any .ightconditiontoany other .ightconditionwithoutexceptionalpiloting skill, alertness, or strength, and without danger of exceeding the limit load factor under any operating condition probable for the type, including–

(1)
Sudden failure of one engine, for multiengined rotorcraft meeting Transport Category A engine isolation requirements of Part 29 of this chapter; and

(2)
Sudden, complete power failure, for other rotorcraft; and

(3)
Sudden, complete control system failures speci.ed in Sec. 27.695 of this Part; and

(c) Have any additional characteristic required for night or instrument operation, if certi.cation for those kinds of operation is requested. Requirements for helicopter instrument .ight are contained in Appendix B of this Part.
Amdt. 27-21, E.. 12/6/84
FAR 27.143 : Controllability and maneuverability
(a)
The rotorcraft must be safely controllable and maneuverable–

(1)
During steady .ight; and

(2)
During any maneuver appropriate to the type, including–

(i)
Takeo.;

(ii)
Climb;

(iii) Level .ight;
(iv)
Turning .ight;

(v)
Glide;

(vi)
Landing(power on andpower o.); and
　
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