584 

14 CFR Ch. I (1–1–24 Edition) 

§ 29.87 

(b) From the LDP on the approach 

path selected by the applicant, a safe 
climbout can be made at speeds allow-
ing compliance with the climb require-
ments of § 29.67(a)(1) and (2); and 

(c) The rotorcraft does not descend 

below 15 feet above the landing surface. 
For elevated heliport operations, de-
scent may be below the level of the 
landing surface provided the deck edge 
clearance of § 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] 

§ 29.87

Height-velocity envelope. 

(a) If there is any combination of 

height and forward velocity (including 
hover) under which a safe landing can-
not be made after failure of the critical 
engine and with the remaining engines 
(where applicable) operating within ap-
proved limits, a height-velocity enve-
lope must be established for— 

(1) All combinations of pressure alti-

tude and ambient temperature for 
which takeoff and landing are ap-
proved; and 

(2) Weight from the maximum weight 

(at sea level) to the highest weight ap-
proved for takeoff and landing at each 
altitude. For helicopters, this weight 
need not exceed the highest weight al-
lowing hovering out-of-ground effect at 
each altitude. 

(b) For single-engine or multiengine 

rotorcraft that do not meet the Cat-
egory A engine isolation requirements, 
the height-velocity envelope for com-
plete power failure must be estab-
lished. 

[Doc. No. 24802, 61 FR 21901, May 10, 1996; 61 
FR 33963, July 1, 1996] 

F

LIGHT

C

HARACTERISTICS

 

§ 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 alti-

tudes and temperatures; 

(2) Under any critical loading condi-

tion within the range of weights and 
centers of gravity for which certifi-
cation 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 ex-
ceptional piloting skill, alertness, or 
strength, and without danger of ex-
ceeding the limit load factor under any 
operating condition probable for the 
type, including— 

(1) Sudden failure of one engine, for 

multiengine rotorcraft meeting Trans-
port Category A engine isolation re-
quirements; 

(2) Sudden, complete power failure, 

for other rotorcraft; and 

(3) Sudden, complete control system 

failures specified in § 29.695 of this part; 
and 

(c) Have any additional characteris-

tics required for night or instrument 
operation, if certification for those 
kinds of operation is requested. Re-
quirements 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] 

§ 29.143

Controllability and maneuver-

ability. 

(a) The rotorcraft must be safely con-

trollable and maneuverable— 

(1) During steady flight; and 
(2) During any maneuver appropriate 

to the type, including— 

(i) Takeoff; 
(ii) Climb; 
(iii) Level flight; 
(iv) Turning flight; 
(v) Autorotation; and 
(vi) Landing (power on and power 

off). 

(b) The margin of cyclic control must 

allow satisfactory roll and pitch con-
trol at V

NE

with— 

(1) Critical weight; 

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