Federal Aviation Administration, DOT

Section 29.143

complete power failure occurs during
normal cruise.
[Doc. No. 24802, 61 FR 21900, May 10, 1996; 61
FR 33963, July 1, 1996]

Section 29.85

Balked landing: Category A.

For Category A rotorcraft, the
balked landing path with the critical
engine inoperative must be established
so that - 
(a) The transition from each stage of
the maneuver to the next stage can be
made smoothly and safely;
(b) From the LDP on the approach
path selected by the applicant, a safe
climbout can be made at speeds allowing compliance with the climb requirements of Section 29.67(a)(1) and (2); and
(c) The rotorcraft does not descend
below 15 feet above the landing surface.
For elevated heliport operations, descent may be below the level of the
landing surface provided the deck edge
clearance of Section 29.60 is maintained and
the descent (loss of height) below the
landing surface is determined.
[Doc. No. 24802, 64 FR 45338, Aug. 19, 1999]

spaschal on DSK3GDR082PROD with CFR

Section 29.87

Height-velocity envelope.

(a) If there is any combination of
height and forward velocity (including
hover) under which a safe landing cannot be made after failure of the critical
engine and with the remaining engines
(where applicable) operating within approved limits, a height-velocity envelope must be established for - 
(1) All combinations of pressure altitude and ambient temperature for
which takeoff and landing are approved; and
(2) Weight from the maximum weight
(at sea level) to the highest weight approved for takeoff and landing at each
altitude. For helicopters, this weight
need not exceed the highest weight allowing hovering out-of-ground effect at
each altitude.
(b) For single-engine or multiengine
rotorcraft that do not meet the Category A engine isolation requirements,
the height-velocity envelope for complete power failure must be established.
[Doc. No. 24802, 61 FR 21901, May 10, 1996; 61
FR 33963, July 1, 1996]

FLIGHT CHARACTERISTICS
Section 29.141 General.
The rotorcraft must - 
(a) Except as specifically required in
the applicable section, meet the flight
characteristics requirements of this
subpart - 
(1) At the approved operating altitudes and temperatures;
(2) Under any critical loading condition within the range of weights and
centers of gravity for which certification is requested; and
(3) For power-on operations, under
any condition of speed, power, and
rotor r.p.m. for which certification is
requested; and
(4) For power-off operations, under
any condition of speed, and rotor r.p.m.
for which certification is requested
that is attainable with the controls
rigged in accordance with the approved
rigging instructions and tolerances;
(b) Be able to maintain any required
flight condition and make a smooth
transition from any flight condition to
any other flight condition without exceptional piloting 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
multiengine rotorcraft meeting Transport Category A engine isolation requirements;
(2) Sudden, complete power failure,
for other rotorcraft; and
(3) Sudden, complete control system
failures specified in Section 29.695 of this part;
and
(c) Have any additional characteristics required for night or instrument
operation, if certification for those
kinds of operation is requested. Requirements for helicopter instrument
flight are contained in appendix B of
this part.
[Doc. No. 5084, 29 FR 16150, Dec. 8, 1964, as
amended by Amdt. 29-3, 33 FR 905, Jan. 26,
1968; Amdt. 29-12, 41 FR 55471, Dec. 20, 1976;
Amdt. 29-21, 48 FR 4391, Jan. 31, 1983; Amdt.
29-24, 49 FR 44436, Nov. 6, 1984]

Section 29.143 Controllability and maneuverability.
(a) The rotorcraft must be safely controllable and maneuverable - 

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