826 

14 CFR Ch. I (1–1–14 Edition) 

§ 29.1587 

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 
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— 

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