566 

14 CFR Ch. I (1–1–24 Edition) 

§ 27.1585 

(3) Information necessary for mark-

ing the instruments required by 
§§ 27.1549 through 27.1553. 

(c) 

Weight and loading distribution. 

The weight and center of gravity limits 
required by §§ 27.25 and 27.27, 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 § 27.1523 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) [Reserved] 
(g) 

Altitude.  The altitude established 

under § 27.1527 and an explanation of 
the limiting factors 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) of the 
Dept. of Transportation Act (49 U.S.C. 
1655(c))) 

[Doc. No. 5074, 29 FR 15695, Nov. 24, 1964, as 
amended by Amdt. 27–2, 33 FR 965, Jan. 26, 
1968; Amdt. 27–14, 43 FR 2325, Jan. 16, 1978; 
Amdt. 27–16, 43 FR 50599, Oct. 30, 1978] 

§ 27.1585

Operating procedures. 

(a) Parts of the manual containing 

operating procedures must have infor-
mation concerning any normal and 
emergency procedures and other infor-
mation necessary for safe operation, 
including takeoff and landing proce-
dures and associated airspeeds. The 
manual must contain any pertinent in-
formation including— 

(1) The kind of takeoff surface used 

in the tests and each appropriate 
climbout speed; and 

(2) The kind of landing surface used 

in the tests and appropriate approach 
and glide airspeeds. 

(b) For multiengine rotorcraft, infor-

mation identifying each operating con-
dition in which the fuel system inde-
pendence prescribed in § 27.953 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 
§ 27.1505(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 § 27.1353 (g)(2) or (g)(3), the 
operating procedures for disconnecting 
the battery from its charging source 
must be furnished. 

(e) If the unusable fuel supply in any 

tank exceeds five percent of the tank 
capacity, or one gallon, whichever is 
greater, 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) The airspeeds and rotor speeds for 

minimum rate of descent and best glide 
angle as prescribed in § 27.71 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) of the 
Dept. of Transportation Act (49 U.S.C. 
1655(c))) 

[Amdt. 27–1, 32 FR 6914, May 5, 1967, as 
amended by Amdt. 27–14, 43 FR 2326, Jan. 16, 
1978; Amdt. 27–16, 43 FR 50599, Oct. 30, 1978; 
Amdt. 27–21, 49 FR 44435, Nov. 6, 1984] 

§ 27.1587

Performance information. 

(a) The Rotorcraft Flight Manual 

must contain the following informa-
tion, determined in accordance with 
§§ 27.49 through 27.87 and 27.143(c) and 
(d): 

(1) Enough information to determine 

the limiting height-velocity envelope. 

(2) Information relative to— 
(i) The steady rates of climb and de-

scent, in-ground effect and out-of- 
ground effect hovering ceilings, to-
gether with the corresponding air-
speeds and other pertinent information 
including the calculated effects of alti-
tude and temperatures; 

(ii) The maximum weight for each al-

titude and temperature condition at 
which the rotorcraft can safely hover 
in-ground effect and out-of-ground ef-
fect in winds of not less than 17 knots 

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