---
kind: "range"
citation: "14 C.F.R. §§ 29.1583–29.1589"
title: "14"
from: "29.1583"
to: "29.1589"
count: 4
url: "https://uscodex.org/cfr/14/29.1583..29.1589"
---

# §29.1583. Operating limitations.

- (a) **Airspeed and rotor limitations.** Information 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 following information must be furnished:
  - (1) Limitations required by [§ 29.1521](/cfr/14/29.1521.md).
  - (2) **Explanation of the limitations, when appropriate.**
  - (3) Information necessary for marking the instruments required by [§§ 29.1549 through 29.1553](/cfr/14/29.1549..29.1553.md).
- (c) **Weight and loading distribution.** The weight and center of gravity limits required by §§ [29.25](/cfr/14/29.25.md) and [29.27](/cfr/14/29.27.md), respectively, must be furnished. If the variety of possible loading conditions warrants, instructions must be included to allow ready observance of the limitations.
- (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](/cfr/14/29.1523.md) must be furnished.
- (e) **Kinds of operation.** Each kind of operation for which the rotorcraft and its equipment installations are approved must be listed.
- (f) **Limiting heights.** Enough information must be furnished to allow compliance with [§ 29.1517](/cfr/14/29.1517.md).
- (g) **Maximum allowable wind.** For Category A rotorcraft, the maximum allowable wind for safe operation near the ground must be furnished.
- (h) **Altitude.** The altitude established under [§ 29.1527](/cfr/14/29.1527.md) and an explanation of the limiting factors must be furnished.
- (i) **Ambient temperature.** Maximum and minimum ambient temperature limitations must be furnished.

# §29.1585. Operating procedures.

- (a) The parts of the manual containing operating procedures must have information concerning any normal and emergency procedures, and other information necessary for safe operation, including the applicable procedures, such as those involving minimum speeds, to be followed if an engine fails.
- (b) For multiengine rotorcraft, information identifying each operating condition in which the fuel system independence prescribed in [§ 29.953](/cfr/14/29.953.md) is necessary for safety must be furnished, together with instructions for placing the fuel system in a configuration used to show compliance with that section.
- (c) For helicopters for which a VNE (power-off) is established under [§ 29.1505(c)](/cfr/14/29.1505.md?p=c), information must be furnished to explain the VNE (power-off) and the procedures for reducing airspeed to not more than the VNE (power-off) following failure of all engines.
- (d) For each rotorcraft showing compliance with § [29.1353 (c)(6)(ii)](/cfr/14/29.1353.md?p=c-6-ii) or [(c)(6)(iii)](/cfr/14/29.1353.md?p=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 capacity, or 1 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) For Category B rotorcraft, the airspeeds and corresponding rotor speeds for minimum rate of descent and best glide angle as prescribed in [§ 29.71](/cfr/14/29.71.md) must be provided.

# §29.1587. Performance information.


Flight manual performance information which exceeds any operating limitation may be shown only to the extent necessary for presentation clarity or to determine the effects of approved optional equipment or procedures. When data beyond operating limits are shown, the limits must be clearly indicated. The following must be provided:

- (a) **Category A.** For each category A rotorcraft, the Rotorcraft Flight Manual must contain a summary of the performance data, including data necessary for the application of any operating rule of this chapter, together with descriptions of the conditions, such as airspeeds, under which this data was determined, and must contain—
  - (1) The indicated airspeeds corresponding with those determined for takeoff, and the procedures to be followed if the critical engine fails during takeoff;
  - (2) The airspeed calibrations;
  - (3) The techniques, associated airspeeds, and rates of descent for autorotative landings;
  - (4) The rejected takeoff distance determined under [§ 29.62](/cfr/14/29.62.md) and the takeoff distance determined under [§ 29.61](/cfr/14/29.61.md);
  - (5) The landing data determined under [§ 29.81](/cfr/14/29.81.md) and [§ 29.85](/cfr/14/29.85.md);
  - (6) The steady gradient of climb for each weight, altitude, and temperature for which takeoff data are to be scheduled, along the takeoff path determined in the flight conditions required in § [29.67(a)(1)](/cfr/14/29.67.md?p=a-1) and [(a)(2)](/cfr/14/29.67.md?p=a-2):
    - (i) In the flight conditions required in [§ 29.67(a)(1)](/cfr/14/29.67.md?p=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)](/cfr/14/29.67.md?p=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 performance determined under [§ 29.49](/cfr/14/29.49.md) 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 appropriate hover charts.
- (b) **Category B.** For each category B rotorcraft, the Rotorcraft Flight Manual must contain—
  - (1) The takeoff distance and the climbout speed together with the pertinent information defining the flight path with respect to autorotative landing if an engine fails, including the calculated effects of altitude and temperature;
  - (2) The steady rates of climb and in-ground-effect hovering ceiling, together with the corresponding airspeeds and other pertinent information, 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, including the effects of weight, altitude, and temperature;
  - (4) The maximum safe wind for operation near the ground;
  - (5) The airspeed calibrations;
  - (6) The height-velocity envelope except for rotorcraft incorporating this as an operating limitation;
  - (7) Glide distance as a function of altitude when autorotating at the speeds and conditions for minimum rate of descent and best glide angle, as determined in [§ 29.71](/cfr/14/29.71.md);
  - (8) Out-of-ground effect hover performance determined under [§ 29.49](/cfr/14/29.49.md) and the maximum safe wind demonstrated under the ambient conditions for data presented. In addition, 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 appropriate hover charts; and
  - (9) **Any additional performance data necessary for the application of any operating rule in this chapter.**

# §29.1589. Loading information.


There must be loading instructions for each possible loading condition between the maximum and minimum weights determined under [§ 29.25](/cfr/14/29.25.md) that can result in a center of gravity beyond any extreme prescribed in [§ 29.27](/cfr/14/29.27.md), assuming any probable occupant weights.