678 

14 CFR Ch. I (1–1–19 Edition) 

§ 29.1589 

(a) 

Category A. 

For each category A 

rotorcraft, the Rotorcraft Flight Man-
ual must contain a summary of the 
performance data, including data nec-
essary for the application of any oper-
ating rule of this chapter, together 
with descriptions of the conditions, 
such as airspeeds, under which this 
data was determined, and must con-
tain— 

(1) The indicated airspeeds cor-

responding with those determined for 
takeoff, and the procedures to be fol-
lowed if the critical engine fails during 
takeoff; 

(2) The airspeed calibrations; 
(3) The techniques, associated air-

speeds, and rates of descent for auto-
rotative landings; 

(4) The rejected takeoff distance de-

termined under § 29.62 and the takeoff 
distance determined under § 29.61; 

(5) The landing data determined 

under § 29.81 and § 29.85; 

(6) The steady gradient of climb for 

each weight, altitude, and temperature 
for which takeoff data are to be sched-
uled, along the takeoff path deter-
mined in the flight conditions required 
in § 29.67(a)(1) and (a)(2): 

(i) In the flight conditions required in 

§ 29.67(a)(1) between the end of the 
takeoff distance and the point at which 
the rotorcraft is 200 feet above the 
takeoff surface (or 200 feet above the 
lowest point of the takeoff profile for 
elevated heliports); 

(ii) In the flight conditions required 

in § 29.67(a)(2) between the points at 
which the rotorcraft is 200 and 1000 feet 
above the takeoff surface (or 200 and 
1000 feet above the lowest point of the 
takeoff profile for elevated heliports); 
and 

(7) Out-of-ground effect hover per-

formance determined under § 29.49 and 
the maximum weight for each altitude 
and temperature condition at which 
the rotorcraft can safely hover out-of- 
ground effect in winds of not less than 
17 knots from all azimuths. These data 
must be clearly referenced to the ap-
propriate hover charts. 

(b) 

Category B. 

For each category B 

rotorcraft, the Rotorcraft Flight Man-
ual must contain— 

(1) The takeoff distance and the 

climbout speed together with the perti-
nent information defining the flight 

path with respect to autorotative land-
ing if an engine fails, including the cal-
culated effects of altitude and tempera-
ture; 

(2) The steady rates of climb and in- 

ground-effect hovering ceiling, to-
gether with the corresponding air-
speeds and other pertinent informa-
tion, including the calculated effects of 
altitude and temperature; 

(3) The landing distance, appropriate 

airspeed, and type of landing surface, 
together with all pertinent information 
that might affect this distance, includ-
ing the effects of weight, altitude, and 
temperature; 

(4) The maximum safe wind for oper-

ation near the ground; 

(5) The airspeed calibrations; 
(6) The height-speed envelope except 

for rotorcraft incorporating this as an 
operating limitation; 

(7) Glide distance as a function of al-

titude when autorotating at the speeds 
and conditions for minimum rate of de-
scent and best glide angle, as deter-
mined in § 29.71; 

(8) Out-of-ground effect hover per-

formance determined under § 29.49 and 
the maximum safe wind demonstrated 
under the ambient conditions for data 
presented. In addition, the maximum 
weight for each altitude and tempera-
ture condition at which the rotorcraft 
can safely hover out-of-ground-effect in 
winds of not less than 17 knots from all 
azimuths. These data must be clearly 
referenced to the appropriate hover 
charts; and 

(9) Any additional performance data 

necessary for the application of any op-
erating rule in this chapter. 

[Doc. No. 5084, 29 FR 16150, Dec. 3, 1964, as 
amended by Amdt. 29–21, 48 FR 4392, Jan. 31, 
1983; Amdt. 29–24, 49 FR 44440, Nov. 6, 1984; 
Amdt. 29–39, 61 FR 21901, May 10, 1996; Amdt. 
29–40, 61 FR 21908, May 10, 1996; Amdt. 29–44, 
64 FR 45338, Aug. 19, 1999; Amdt. 29–51, 73 FR 
11001, Feb. 29, 2008] 

§ 29.1589

Loading information. 

There must be loading instructions 

for each possible loading condition be-
tween the maximum and minimum 
weights determined under § 29.25 that 
can result in a center of gravity beyond 
any extreme prescribed in § 29.27, as-
suming any probable occupant weights. 

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