677 

Federal Aviation Administration, DOT 

§ 29.1585 

(d) Each liferaft must have obviously 

marked operating instructions. 

(e) Approved survival equipment 

must be marked for identification and 
method of operation. 

§ 29.1565

Tail rotor. 

Each tail rotor must be marked so 

that its disc is conspicuous under nor-
mal daylight ground conditions. 

[Amdt. 29–3, 33 FR 971, Jan. 26, 1968] 

R

OTORCRAFT

F

LIGHT

M

ANUAL

 

§ 29.1581

General. 

(a) 

Furnishing information. A Rotor-

craft Flight Manual must be furnished 
with each rotorcraft, and it must con-
tain the following: 

(1) Information required by §§ 29.1583 

through 29.1589. 

(2) Other information that is nec-

essary for safe operation because of de-
sign, operating, or handling character-
istics. 

(b) 

Approved information. Each part of 

the manual listed in §§ 29.1583 through 
29.1589 that is appropriate to the rotor-
craft, must be furnished, verified, and 
approved, and must be segregated, 
indentified, and clearly distinguished 
from each unapproved part of that 
manual. 

(c) [Reserved] 
(d) 

Table of contents. Each Rotorcraft 

Flight Manual must include a table of 
contents if the complexity of the man-
ual indicates a need for it. 

(Secs. 313(a), 601, 603, 604, and 605 of the Fed-
eral Aviation Act of 1958 (49 U.S.C. 1354(a), 
1421, 1423, 1424, and 1425); and sec. 6(c), Dept. 
of Transportation Act (49 U.S.C. 1655(c))) 

[Amdt. 29–15, 43 FR 2327, Jan. 16, 1978] 

§ 29.1583

Operating limitations. 

(a) 

Airspeed and rotor limitations. In-

formation necessary for the marking of 
airspeed and rotor limitations on or 
near their respective indicators must 
be furnished. The significance of each 
limitation and of the color coding must 
be explained. 

(b) 

Powerplant limitations. The fol-

lowing information must be furnished: 

(1) Limitations required by § 29.1521. 
(2) Explanation of the limitations, 

when appropriate. 

(3) Information necessary for mark-

ing the instruments required by 
§§ 29.1549 through 29.1553. 

(c) 

Weight and loading distribution. 

The weight and center of gravity limits 
required by §§ 29.25 and 29.27, respec-
tively, must be furnished. If the vari-
ety of possible loading conditions war-
rants, instructions must be included to 
allow ready observance of the limita-
tions. 

(d) 

Flight crew. When a flight crew of 

more than one is required, the number 
and functions of the minimum flight 
crew determined under § 29.1523 must be 
furnished. 

(e) 

Kinds of operation. Each kind of 

operation for which the rotorcraft and 
its equipment installations are ap-
proved must be listed. 

(f) 

Limiting heights. Enough informa-

tion must be furnished to allow compli-
ance with § 29.1517. 

(g) 

Maximum allowable wind. For Cat-

egory A rotorcraft, the maximum al-
lowable wind for safe operation near 
the ground must be furnished. 

(h) 

Altitude.  The altitude established 

under § 29.1527 and an explanation of 
the limiting factors must be furnished. 

(i) 

Ambient temperature. Maximum 

and minimum ambient temperature 
limitations must be furnished. 

(Secs. 313(a), 601, 603, 604, and 605 of the Fed-
eral Aviation Act of 1958 (49 U.S.C. 1354(a), 
1421, 1423, 1424, and 1425); and sec. 6(c), Dept. 
of Transportation Act (49 U.S.C. 1655(c))) 

[Doc. No. 5084, 29 FR 16150, Dec. 3, 1964, as 
amended by Amdt. 29–3, 33 FR 971, Jan. 26, 
1968; Amdt. 29–15, 43 FR 2327, Jan. 16, 1978; 
Amdt. 29–17, 43 FR 50602, Oct. 30, 1978; Amdt. 
29–24, 49 FR 44440, Nov. 6, 1984] 

§ 29.1585

Operating procedures. 

(a) The parts of the manual con-

taining operating procedures must 
have information concerning any nor-
mal and emergency procedures, and 
other information necessary for safe 
operation, including the applicable pro-
cedures, such as those involving min-
imum speeds, to be followed if an en-
gine fails. 

(b) For multiengine rotorcraft, infor-

mation identifying each operating con-
dition in which the fuel system inde-
pendence prescribed in § 29.953 is nec-
essary for safety must be furnished, to-
gether with instructions for placing 

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14 CFR Ch. I (1–1–24 Edition) 

§ 29.1587 

the fuel system in a configuration used 
to show compliance with that section. 

(c) For helicopters for which a V

NE

 

(power-off) is established under 
§ 29.1505(c), information must be fur-
nished to explain the V

NE

(power-off) 

and the procedures for reducing air-
speed to not more than the V

NE

(power- 

off) following failure of all engines. 

(d) For each rotorcraft showing com-

pliance with § 29.1353 (c)(6)(ii) or 
(c)(6)(iii), the operating procedures for 
disconnecting the battery from its 
charging source must be furnished. 

(e) If the unusable fuel supply in any 

tank exceeds 5 percent of the tank ca-
pacity, or 1 gallon, whichever is great-
er, information must be furnished 
which indicates that when the fuel 
quantity indicator reads ‘‘zero’’ in 
level flight, any fuel remaining in the 
fuel tank cannot be used safely in 
flight. 

(f) Information on the total quantity 

of usable fuel for each fuel tank must 
be furnished. 

(g) For Category B rotorcraft, the 

airspeeds and corresponding rotor 
speeds for minimum rate of descent 
and best glide angle as prescribed in 
§ 29.71 must be provided. 

(Secs. 313(a), 601, 603, 604, and 605 of the Fed-
eral Aviation Act of 1958 (49 U.S.C. 1354(a), 
1421, 1423, 1424, and 1425); and sec. 6(c), Dept. 
of Transportation Act (49 U.S.C. 1655(c))) 

[Amdt. 29–2, 32 FR 6914, May 5, 1967, as 
amended by Amdt. 29–15, 43 FR 2328, Jan. 16, 
1978; Amdt. 29–17, 43 FR 50602, Oct. 30, 1978; 
Amdt. 29–24, 49 FR 44440, Nov. 6, 1984] 

§ 29.1587

Performance information. 

Flight manual performance informa-

tion which exceeds any operating limi-
tation may be shown only to the extent 
necessary for presentation clarity or to 
determine the effects of approved op-
tional equipment or procedures. When 
data beyond operating limits are 
shown, the limits must be clearly indi-
cated. The following must be provided: 

(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; 

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