shall be the frequency at which the rotorcraft's complete anti-collision light system is observed from a distance, and shall apply to all sectors of light including the overlaps which might exist when the system consists of more than one light source. In overlaps, flash frequencies higher than 100 cycles per minute shall be permissible, except that they shall not be higher than 180 cycles per minute.

(c) Color. The color of the anti-collision lights shall be aviation red in accordance with § 7.635 (a).

(d) Light intensity. The minimum light intensities in all vertical planes, measured with the red filter and expressed in terms of "effective" intensities, shall be in accordance with Figure 7-4. The following relation shall be assumed:

Safety belts shall be of an approved type (see § 7.355(c) (2)). When means are provided to indicate to the passengers when seat belts should be fastened, the device shall be so installed that it can be operated from the seat of either the pilot or copilot.

§ 7.644

Emergency flotation and signaling equipment. When emergency flotation and signaling equipment is required by the operating rules of the regulations in this subchapter, such equipment shall comply with the provisions of paragraphs (a) through (d) of this section.

(a) Life rafts. Life rafts shall be of an approved type. Unless excess rafts of sufficient capacity are provided, the buoyancy and seating capacity beyond the rated capacity of the rafts shall be such as to accommodate all occupants of the rotorcraft in the event of a loss of one life raft of the largest rated capacity on board. Each life raft shall be equipped with a trailing line and with a static line, the latter designed to hold the raft near the rotorcraft but to release it in case the rotorcraft becomes totally submerged. Each raft shall contain obvious markings of instruction on its operation.

(b) Life-raft equipment. Approved equipment intended for survival shall be attached to each life raft and marked for identification and method of operation.

NOTE: The extent and type of survival equipment will depend upon the route over which the rotorcraft is operated.

(c) Long-range signaling device. An approved long-range signaling device shall be provided for use in one of the life rafts.

(d) Life preservers. Life preservers shall be of an approved type.

[21 F.R. 3744, June 2, 1956, as amended by Amdt. 7-4, 24 F.R. 7076, Sept. 1, 1959]

§ 7.645 Stowage of safety equipment.

Special stowage provisions shall be made for all prescribed safety equipment to be used in emergencies. The stowage provisions shall be such that the equipment is directly accessible and its location is obvious. All safety equipment shall be protected against inadvertent damage. The stowage provisions shall be marked conspicuously to identify the contents and to facilitate removal of the equipment. In addition, the following shall specifically apply:

(a) Emergency exit means. The stowage provisions for the emergency exit descent device required by § 7.357 (d) (6) shall be located at the exits which they are intended to serve.

(b) Life rafts. Life rafts shall be stowed near exits through which the rafts can be launched during an unplanned ditching. Rafts automatically or remotely released on the outside of the rotorcraft shall be attached to the rotorcraft by means of the static line prescribed in § 7.644 (a).

(c) Long-range signaling device. The stowage provisions for the long-range signaling device required by § 7.644 (c) shall be located near an exit to be available during an unplanned ditching.

(d) Life preservers. Life preservers shall be so located that they are within easy reach of each occupant while seated. § 7.646 Oxygen equipment and supply. (a) Protective breathing equipment. When protective breathing equipment is required by the operating rules of the regulations in this subchapter, it shall be designed to protect the flight crew from the effects of smoke, carbon dioxide, and other harmful gases while on flight deck duty. The protective breathing equipment and the necessary supply of oxygen shall be in accordance with the following provisions:

(1) The protective breathing equipment shall include masks covering the eyes, nose, and mouth, or only the nose and mouth where accessory equipment is provided to protect the eyes.

(2) A supply of protective oxygen per crew member shall be of 10 minutes duration at a pressure altitude of 8,000 feet and a respiratory minute volume of 30 liters per minute BTPD.

NOTE: When a demand-type oxygen system is employed, a supply per crew member of 200 liters of free oxygen at 70° F. and 760 mm. Hg pressure is considered to be of 10 minutes duration at the prescribed altitude and minute volume. BTPD refers to body temperature conditions; 1. e., 37° C. at ambient pressure, dry.

§ 7.650

MISCELLANEOUS EQUIPMENT

Hydraulic systems; strength.

(a) Structural loads. All elements of the hydraulic system shall be designed to withstand, without detrimental permament deformation, all structural loads which may be imposed simultaneously with the maximum hydraulic loads occurring in operation.

(b) Proof pressure tests. All elements of the hydraulic system shall be tested to a proof pressure of 1.5 times the maximum pressure to which the part will be subjected in normal operation. In such test, no part of the hydraulic system shall fail, malfunction, or suffer detrimental deformation.

(c) Burst pressure strength. Individual hydraulic system elements shall be designed to withstand pressures which are sufficiently increased over the pressures prescribed in paragraph (b) of this section to safeguard against rupture under service conditions.

NOTE: The following pressures, in terms of percentages of maximum operating pressures for particular elements, in most instances are sufficient to insure against rupture in service: 250 percent in units under oil pressure; 400 percent in units containing air and oil under pressure and in lines, hoses, and fittings; and 300 percent in units of system subjected to back pressure.

§ 7.651

Hydraulic systems; design.

The provisions of § 7.606 shall apply to hydraulic systems and equipment.

(a) Pressure indication. A means shall be provided to indicate the pressure in each main hydraulic power system.

(b) Pressure limiting provisions. Provision shall be made to assure that pressures in any part of the system will not exceed a safe limit above the maximum operating pressure of the system and to insure against excessive pressures resulting from fluid volumetric changes in all lines which are likely to remain closed long enough for such changes to take place. In addition, consideration shall be given to the possible occurrence of

(a) Radio communication and navigational equipment installations in the rotorcraft should be free from hazards in themselves, in their method of operation, and in their effects on other components of the rotorcraft. In showing compliance with this requirement, consideration shall be given to critical environmental conditions.

NOTE: Critical environmental conditions may include temperature, pressure, humidity, ventilation, position, acceleration, vibration, and presence of detrimental substances.

(b) All radio communication and navigational equipment, controls, and wiring shall be so installed that operation of any one unit or system of units will not affect adversely the simultaneous operation of any other radio or electronic unit or system of units required by the regulations in this subchapter.

§ 7.654 Vacuum systems.

(a) Means, in addition to the normal pressure relief, shall be provided to relieve automatically the pressure in the discharge lines from the vacuum air pump if the delivery temperature of the air reaches an unsafe value.

(b) Vacuum air system lines and fittings on the discharge side of the pump which might contain flammable vapors or fluids shall comply with § 7.483 if they are located in a designated fire zone. Other vacuum air system components located in designated fire zones shall be fire-resistant.

§ 7.711

Never-exceed speed VNE.

(a) The never-exceed speed shall be established. It shall not be less than the best rate-of-climb speed with all engines operating at maximum continuous power, nor greater than either of the following:

(1) 0.9 V established in accordance with § 7.204, or

(2) 0.9 times the maximum speed demonstrated in accordance with § 7.140.

(b) It shall be permissible to vary the never-exceed speed with altitude and rotor rpm, provided that the ranges of these variables are sufficiently large to allow an operationally practical and safe variation of the never-exceed speeds. § 7.712 Operating speed range.

An operating speed range shall be established for each rotorcraft. § 7.713 Rotor speed.

Rotor rpm limitations shall be established as set forth in paragraphs (a) and (b) of this section. (See also § 7.710.)

(a) Maximum power off (autorotation). Not to exceed 95 percent of the maximum design rpm determined under § 7.204 (b) or 95 percent of the maximum rpm demonstrated during the type tests (see § 7.103 (b)), whichever is less.

(b) Minimum-(1) Power off. Not less than 105 percent of the higher of the following:

(i) The minimum demonstrated during the type test (see § 7.103 (b)), or

(ii) The minimum determined by design substantiation.

(2) Power on. Not less than the higher of the following:

(i) The minimum demonstrated during the type tests (see § 7.103 (a)), or

(ii) The minimum determined by design substantiation and not higher than a value determined in compliance with § 7.103 (a).

§ 7.714 Powerplant limitations.

The powerplant limitations set forth in paragraphs (a) through (d) of this section shall be established for the rotorcraft. They shall not exceed the corresponding limits established as a part of the type certification of the engine (s) installed on the rotorcraft.

(a) Take-off operation. operation shall be limited by:

The take-off

(1) The maximum rotational speed, which shall not be greater than the maximum value determined by the rotor design, nor greater than the maximum value demonstrated during type tests.

(2) The maximum permissible manifold pressure.

(3) The time limit for use of the power which corresponds with the values established in subparagraphs (1) and (2) of this paragraph.

(4) Where the time limit established in subparagraph (3) of this paragraph exceeds two minutes, the maximum allowable cylinder head or coolant outlet and oil temperatures.

(5) Maximum cylinder head or coolant outlet and oil temperatures, if these differ from the maximum limits for continuous operation.

(b) Continuous operation. The continuous operation shall be limited by:

(1) The maximum rotational speed, which shall not be greater than the maximum value determined by the rotor design, nor greater than the maximum value demonstrated during type tests.

(2) Maximum permissible manifold pressure.

(3) Maximum allowable cylinder head or coolant outlet and oil temperatures.

(4) The minimum rotational speed demonstrated in compliance with the rotor speed requirements as prescribed in § 7.713 (b) (2).

(c) Fuel octane rating. The minimum octane rating of fuel required for satisfactory operation of the powerplant within the limitations prescribed in paragraphs (a) and (b) of this section.

(d) Cooling limitations. The maximum sea level temperature for which satisfactory cooling has been demonstrated.

§ 7.715 Limiting height-speed envelope.

If a range of heights exists at any speed, including zero, within which it is not possible to make a safe landing following power failure, the range of heights and its variation with forward speed shall be established together with any other pertinent information, such as type of landing surface. (See §§ 7.111 (a), 7.111(b), and 7.741 (f).)

[21 F.R. 3744, June 2, 1956, as amended by Amdt. 7-4, 24 F.R. 7076, Sept. 1, 1959]

§ 7.716 Rotorcraft weight and center of gravity limitations.

The rotorcraft weight and center of gravity limitations to be established are those required to be determined by §§ 7.101 and 7.102.

§ 7.717 Minimum flight crew.

The minimum flight crew shall be established by the Administrator as that number of persons which he finds necessary for safety in the operations authorized under § 7.718. This finding shall be based upon the workload imposed upon individual crew members with due consideration given to the accessibility and the ease of operation of all necessary controls by the appropriate crew members.

§ 7.718 Types of operation.

The type of operation to which a rotorcraft is limited shall be established on the basis of flight characteristics and the equipment installed. (See the operating parts of this subchapter.)

§ 7.719 Maintenance manual.

The applicant shall furnish with each rotorcraft a maintenance manual to contain information which he considers essential for the proper maintenance of the rotorcraft. The maintenance manual shall include recommended limits on service life or retirement periods for

(a) The markings and placards specified in §§ 7.731 through 7.738 are required for all rotorcraft.

(b) Markings and placards shall be displayed in conspicuous places and shall be such that they cannot be easily erased, disfigured, or obscured.

(c) Additional information, placards, and instrument markings having a direct and important bearing on safe operation of the rotorcraft shall be required when unusual design, operating, or handling characteristics so warrant. § 7.731

Instrument markings; general.

(a) When markings are placed on the cover glass of the instrument, provision shall be made to maintain the correct alignment of the glass cover with the face of the dial.

(b) All arcs and lines shall be of sufficient width and so located that they are clearly visible to the pilot.

§ 7.732 Air-speed indicator.

Instrument indications shall be in terms of indicated air speed. The markings set forth in paragraphs (a) through (c) of this section shall be used to indicate to the pilot the maximum and minimum permissible speeds and the normal precautionary operating ranges. (See §§ 7.612 (a), 7.710, 7.711, 7.712, 7.713, and 7.715.)

(a) A red radial line shall be used to indicate the limit beyond which operation is dangerous.

(b) A yellow arc shall be used to indicate the precautionary operating range.

(c) A green arc shall be used to indicate the safe operating range.

§ 7.733 Magnetic direction indicator.

A placard shall be installed on or in close proximity to the magnetic direction indicator which shall comply with the requirements of paragraphs (a) through (c) of this section. (See § 7.612 (c).)

(a) The placard shall contain the calibration of the instrument in a level flight attitude with engine(s) operating.

(b) The placard shall state whether the calibration was made with radio receiver(s) on or off.

(c) The calibration readings shall be in terms of magnetic headings in not greater than 45° increments.

§ 7.734 Powerplant instruments; general.

All required powerplant instruments shall be marked as follows:

(a) The maximum and the minimum, if applicable, safe operational limits shall be marked with red radial lines.

(b) The normal operating ranges shall be marked with a green arc not extending beyond the maximum and minimum safe operational limits.

(c) The take-off and precautionary ranges shall be marked with a yellow

arc.

(d) Engine or rotor speed ranges which are restricted because of excessive vibration stresses shall be marked with red arcs.

§ 7.735 Oil quantity indicator.

Oil quantity indicators shall be marked in sufficient increments to indicate readily and accurately the quantity of oil. (See § 7.613(d).)

§ 7.736 Fuel quantity indicator.

When the unusable fuel supply for any tank exceeds 1 gallon or 5 percent of the tank capacity, whichever is greater, a red arc shall be marked on the indicator extending from the calibrated zero reading to the lowest reading obtainable in the level flight attitude. (See §§ 7.421 and 7.613(b).) A notation in the Rotorcraft Flight Manual shall be made to indicate that the fuel remaining in the tank when the quantity indicator reaches zero is not usable in flight. (See § 7.741 (g).) § 7.737 Control markings.

(a) General. All cockpit controls including those referred to in paragraphs (b) and (c) of this section shall be plainly marked as to their function and method of operation. (See § 7.353.)

(b) Powerplant fuel controls. The powerplant fuel controls shall be marked in accordance with subparagraphs (1) through (4) of this paragraph.

(1) Controls for fuel tank selector valves shall be marked to indicate the position corresponding with each tank with all existing cross-feed positions.

(2) When more than one fuel tank is provided, and if safe operation depends upon the use of tanks in a specific sequence, the fuel tank selector controls