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tion shall be furnished with each rotorcraft.

(a) Air-speed and rotor limitations. Sufficient information shall include the information necessary for the marking of the limitations on or adjacent to the indicators as required. (See § 6.732.) In addition, the significance of the limitations and of the color coding used shall be explained.

(b) Powerplant limitations. Information shall be included to outline and to explain all powerplant limitations (see § 6.714) and to permit marking the instruments as required by §§ 6.734 through 6.736.

(c) Weight and loading distribution. The rotorcraft weights and center of gravity limits required by §§ 6.101 and 6.102 shall be included, together with the items of equipment on which the empty weight is based. Where the variety of possible loading conditions warrants, instructions shall be included to facilitate 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 in accordance with § 6.717 shall be described.

(e) Type of operation. The type(s) of operation(s) shall be listed for which the rotorcraft and its equipment installations have been approved. (See § 6.718.)

(f) Unusable fuel. If the unusable fuel supply in any tank exceeds one gallon or 5 percent of the tank capacity, whichever is the greater, warning shall be provided to indicate to the flight personnel that the fuel remaining in the tank when the quantity indicator reads zero cannot be used safely in flight. (See § 6.421.)

[21 F.R. 10291, Dec. 22, 1956, as amended by Amdt. 6-4, 24 F.R. 7074, Sept. 1, 1959]

§ 6.742 Operating procedures.

The section of the manual devoted to operating procedures shall contain information concerning normal and emergency procedures and other pertinent information, including take-off and landing procedures and their appropriate air speeds, peculiar to the rotorcraft's operating characteristics which are necessary for safe operation. § 6.743

Performance information.

Information relative to the items of performance set forth in paragraphs (a)

through (c) of this section shall be included.

(a) The steady rates of climb and hovering ceilings together with the corresponding air speeds and other pertinent information, including the calculated effect of altitude and temperature. (See §§ 6.112 and 6.113.)

(b) Maximum wind allowable for safe operation near the ground. (See § 6.121 (d).)

(c) Sufficient information to outline the limiting heights and corresponding speeds for safe landing after power failure. (See § 6.116.)

[21 F.R. 10291, Dec. 22, 1956, as amended by Amdt. 6-4, 24 F.R. 7074, Sept. 1, 1959]

§ 6.744 Marking and placard information.

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7.731 Instrument markings; general.

7.732 Air-speed indicator.

7.733 Magnetic direction indicator. 7.734 Powerplant instruments; general. 7.735 Oil quantity indicator.

7.736 Fuel quantity indicator.

7.737 Control markings.

7.738 Miscellaneous markings and placards.

7.740

7.741

ROTORCRAFT FLIGHT MANUAL

General.

Operating limitations.

7.742 Operating procedures.

7.743

Performance information.

7.744 Marking and placard information.

ROTORCRAFT IDENTIFICATION DATA

7.750 Identification plate. 7.751 Identification marks.

AUTHORITY: §§ 7.0 to 7.751 issued under sec. 205, 52 Stat. 984, as amended; 49 U. S. C. 425. Interpret or apply secs. 601, 603, 52 Stat. 1007, as amended, 1009, as amended; 49 U.S. C. 551, 553.

AUTHORITY NOTE: Additional citation of authority to Part 7 was appended by Amendment 7-4, 24 F.R. 7076, Sept. 1, 1959, as follows: "(Secs. 313(a), 601, 603, 72 Stat. 752, 775, 776; 49 U.S.C. 1354(a), 1421, 1423)"

SOURCE: 7.0 to 7.751 appear at 21 F. R. 3744, June 2, 1956, except as otherwise noted.

CROSS REFERENCES: For Special Civil Air Regulation with respect to facilitation of experiments with exterior lighting systems, see SR-392B in Part 3 of this subchapter.

For Special Civil Air Regulation with respect to Class I and Class II provisional type and airworthiness certificates for the operation of aircraft, see SR-425C in Part 1 of this subchapter.

Subpart A-General

APPLICABILITY AND DEFINITIONS § 7.0 Applicability of this part.

This part establishes standards with which compliance shall be demonstrated for the issuance of and changes to type certificates for Transport Category A and Transport Category B rotorcraft. This part, until superseded or rescinded, shall apply to all transport category rotorcraft for which applications for type certification in the transport categories are made after the effective date of this part (August 1, 1956).

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(b) Rotorcraft types—(1) Rotorcraft. A rotorcraft is any aircraft deriving its principal lift from one or more rotors.

(2) Helicopter. A helicopter is a rotorcraft which depends principally for its support and motion in the air upon the lift generated by one or more powerdriven rotors, rotating on substantially vertical axes.

(3) Gyroplane. A gyroplane is a rotorcraft which depends principally for its support upon the lift generated by one or more rotors which are not power driven, except for initial starting, and which are caused to rotate by the action of the air when the rotorcraft is in motion. The propulsion is independent of the rotor system and usually consists of conventional propellers.

(4) Gyrodyne. A gyrodyne is a rotorcraft which depends principally for its support upon the lift generated by one or more rotors, which are partially power driven, rotating on substantially vertical axes. The propulsion is independent of the rotor system and usually consists of conventional propellers.

(c) General design—(1) Standard atmosphere. The standard atmosphere is an atmosphere (see NACA Technical Report 1235) defined as follows:

(i) The air is a dry, perfect gas, (ii) The temperature at sea level is 59° F.,

(iii) The pressure at sea level is 29.92 inches Hg,

(iv) The temperature gradient from sea level to the altitude at which the temperature equals -69.7° F. is -0.003566° F./ft. and zero thereabove, and

(v) The density po at sea level under the above conditions is 0.002377 pound sec2/ft'.

(2) Maximum anticipated air temperature. The maximum anticipated air temperature is a temperature specified for the purpose of compliance with the powerplant cooling standards. (See § 7.451.)

(3) Aerodynamic coefficients. Aerodynamic coefficients are nondimensional coefficients for forces and moments. They correspond with those adopted by the National Aeronautics and Space Administration (formerly the National Advisory Committee for Aeronautics).

(4) Autorotation. Autorotation is a rotorcraft flight condition in which the lifting rotor is driven entirely by the action of the air when the rotorcraft is in motion.

(5) Autorotative landing. An autorotative landing is any ianding of a rotorcraft in which the entire maneuver is accomplished without the application of power to the rotor.

(6) [Reserved]

(7) Ground resonance. Ground resonance is the mechanical instability encountered when the rotorcraft is in contact with the ground.

(8) Mechanical instability. Mechanical instability is an unstable resonant condition due to the interaction between the rotor blades and the rotorcraft structure, while the rotorcraft is on the ground or airborne.

(d) Weights-(1) Maximum weight. The maximum weight of the rotorcraft is that maximum at which compliance with the requirements of this part is demonstrated. (See § 7.101.)

(2) Minimum weight. The minimum weight of the rotorcraft is that minimum at which compliance with the requirements of this part is demonstrated. (See § 7.101.)

(3) Empty weight. The empty weight of the rotorcraft is a readily reproducible weight which is used in the determination of the operating weights. (See § 7.104.)

(4) Design maximum weight. The design maximum weight is the maximum weight of the rotorcraft at which compliance is shown with the structural loading conditions. (See § 7.101.)

(5) Design minimum weight. The design minimum weight is the minimum weight of the rotorcraft at which compliance is shown with the structural loading conditions. (See § 7.101.)

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