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that malfunctioning of the metering component results in a severe restriction to fuel flow.

(d) Oil quantity indicator. (1) Means shall be provided to indicate the quantity of oil in each tank when the rotorcraft is on the ground. (See § 6.735.)

(2) If an oil transfer system or a reserve oil supply system is installed, means shall be provided to indicate to the crew during flight the quantity of oil in each tank.

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

ELECTRICAL SYSTEMS AND EQUIPMENT § 6.620

Installation.

(a) Electrical systems and equipment shall be free from hazards in themselves, in their method of operation, and in their effects on other parts of the rotorcraft. They shall be protected from fuel, oil, water, other detrimental substances, and from mechanical damage.

(b) The design of all components of the electrical system shall be appropriate for the intended use, and the components shall be capable of satisfactory operation over the entire range of environmental conditions encountered in the operation of the rotorcraft.

(c) Electrical sources of power shall have sufficient capacity during all normal flight operating conditions to supply the electrical load requirements without electrical or thermal distress. For emergency operating conditions the capacity of electrical power sources shall be sufficient for all electrical loads necessary to permit a safe landing.

§ 6.621 Storage battery design and installation.

Storage batteries shall be of such design and so installed that:

(a) Safe cell temperatures and pressures are maintained during any probable charging or discharging condition. No uncontrolled increase in cell temperature shall result when the storage battery is recharged (after previous complete discharge) at maximum regulated voltage, during a flight of maximum duration, under the most adverse cooling condition likely to occur in service. Tests to demonstrate compliance with this regulation shall not be required if satisfactory operating experience with similar batteries and installations has

shown that maintaining safe cell temperatures and pressures presents no problem.

(b) Explosive or toxic gases emitted by the storage battery in normal operation, or as the result of any probable malfunction in the charging system or battery installation, shall not accumulate in hazardous quantities within the rotorcraft.

(c) Corrosive fluids or gases which may be emitted or spilled from the storage battery shall not damage surrounding rotorcraft structure or adjacent essential equipment.

[Amdt. 604, 24 F.R. 7074, Sept. 1, 1959] § 6.622

Generator system.

(a) Generator. Sources of electrical power (including the battery) shall be designed to function coordinately, and shall also be capable of independent operation. The generator(s) shall be capable of delivering sufficient power to keep the batteries charged, and in addition shall provide for the normal electrical power requirements of the rotorcraft.

(b) Generator controls. Generator voltage control equipment shall be capable of regulating the generator output within rated limits.

(c) Reverse current cut-off. A generator reverse current cut-off shall disconnect the generator from the battery and from other generators when the generator is developing a voltage of such value that current sufficient to cause malfunctioning can flow into the gen

erator.

§ 6.623 Master switch.

A master switch arrangement shall be provided which will disconnect all sources of electrical power from the main distribution system at a point adjacent to the power sources.

§ 6.623-1 Loud circuit connections with respect to the master switch (FAA policies which apply to § 6.623).

All load circuits, except those circuits where interruption of service would result in the inability to maintain controlled flight or to effect a safe landing, should be connected to the electric power sources in such a manner that the master switch can interrupt the service. [Supp. 12, 22 F. R. 4879, July 11, 1957]

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Protective devices (fuses or circuit breakers) shall be installed in the circuits to all electrical equipment, except that such items need not be installed in the main circuits of starter motors or in other circuits where no hazard is presented by their omission. If fuses are used, one spare of each rating or 50 percent spare fuses of each rating, whichever is the greater, shall be provided. § 6.625-1 Automatic reset circuit breakers (FAA policies which apply to § 6.625).

Automatic reset circuit breakers (which automatically reset themselves periodically) should not be applied as circuit protective devices.' They may be used as integral protectors for electrical equipment (e. g., thermal cut-outs) provided that circuit protection is also installed to protect the cable to the equipment.

[Supp. 10, 19 F. R. 8140, Dec. 10, 1954]

§ 6.625-2 Circuit breakers (FAA policies which apply to § 6.625).

All resettable type circuit protective devices should be so designed that, when an overload or circuit fault exists, they will open the circuit irrespective of the position of the operating control." [Supp. 11, 21 F. R. 2585, Apr. 20, 1956]

'Circuit protective devices are normally installed to limit the hazardous consequences of overloaded or faulted circuits. These devices are resettable (circuit breakers) or replaceable (fuses) to permit the crew to restore service when nuisance trips occur or when the abnormal circuit condition can be corrected in flight. If the abnormal circuit condition can not be corrected in flight, the decision to restore power to the circuit involves a careful analysis of the flight situation. It is necessary to weigh the essentiality of the circuit for continued safe flight against the hazards of resetting on a possibly faulted circuit. Such evaluation is properly an aircraft crew function which can not be performed by automatic reset circuit breakers. To assure crew supervision over the reset operation, circuit protective devices should be of such design that a manual operation is required to restore service after tripping.

§ 6.626 Protective devices installation.

Protective devices in circuits essential to safety in flight shall be conveniently located and properly identified to facilitate replacement of fuses or resetting of circuit breakers in flight.

§ 6.627 Electric cables.

The electric cables used shall be in accordance with approved standards for aircraft electric cable of a slow-burning type. They shall have current-carrying capacity sufficient to deliver the necessary power to the items of equipment to which they are connected.

§ 6.627-1 Electric cable for power distribution (FAA policies which apply to § 6.627).

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The design for power distribution cable should be such that probable environmental conditions' will not produce hazardous deterioration of the cable insulation, or cause a failure of the conductor. Cable insulation should be flame-resistant and should not emit toxic fumes when overheated. Cable conforming to Military Specification MILW-5086 or the equivalent is acceptable for this specification.

[Supp. 13, 22 F. R. 6963, Aug. 29, 1957] § 6.628 Switches.

Switches shall be capable of carrying their rated current. They shall be accessible to the crew and shall be labeled as to operation and the circuit controlled.

2 Circuit protective devices which conform to the above description are known commercially as "trip-free," that is, the tripping mechanism cannot be overridden by the operating control. Such circuit protective devices can be reset on an overload or circuit fault, but will trip subsequently in accordance with their current-time characteristics.

For the purpose of this section, the term "power distribution cable" includes all electrical cable transmitting electric power from generators or batteries to load equipment, but does not include cable confined within metallic enclosures, such as in radio equipment.

Environmental conditions which should be considered: Ambient temperature range which may exceed design limits of the cable; vibration leading to abrasive wear of cable insulation or conductor failure; presence of aircraft fluids, such as oil, gasoline, or water, which may have detrimental effects on cable insulation or increase its inflammability. (See § 6.620)

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(a) Instrument lights shall provide sufficient illumination to make all instruments, switches, etc., easily readable.

(b) Instrument lights shall be so installed that their direct rays are shielded from the pilot's eyes and so that no objectionable reflections are visible to him. § 6.631 Landing lights.

(a) When landing or hovering lights are required, they shall be of an approved type.

(b) Landing lights shall be installed so that there is no objectionable glare visible to the pilot and so that the pilot is not adversely affected by halation.

(c) Landing lights shall be installed in a location where they provide the necessary illumination for night operation including hovering and landing.

(d) A switch for each light shall be provided, except that where multiple lights are installed at one location a single switch for the multiple lights shall be acceptable.

§ 6.632 Position light system installation.

The provisions

of

(a) General. §§ 6.632 through 6.635 shall be applicable to the position light system as a whole. The position light system shall include the items specified in paragraphs (b) through (e) of this section.

NOTE: Requirements for dual circuit position light systems are contained in Part 4b of this subchapter.

(b) Forward position lights. Forward position lights shall consist of a red and a green light spaced laterally as far apart as practicable and installed forward on the rotorcraft in such a location that, with the rotorcraft in normal flying position, the red light is displayed on the left side and the green light is displayed on the right side. The individual lights shall be of an approved type.

(c) Rear position light. The rear position light shall be a white light mounted as far aft as practicable. The light shall be of an approved type.

(d) Circuit. The two forward position lights and the rear position light shall constitute a single circuit.

(e) Light covers and color filters. Light covers or color filters used shall be of flame resistant material and shall be constructed so that they will not change color or shape or suffer any appreciable loss of light transmission during normal

use.

[21 F.R. 10291, Dec. 22, 1956, as amended by Amdt. 6-1, 22 F.R. 1275, Mar. 1, 1957] § 6.633 Position light system dihedral angles.

The forward and rear position lights as installed on the rotorcraft shall show unbroken light within dihedral angles specified in paragraphs (a) through (c) of this section.

(a) Dihedral angle L (left) shall be considered formed by two intersecting vertical planes, one parallel to the longitudinal axis of the rotorcraft and the other at 110° to the left of the first, when looking forward along the longitudinal axis.

(b) Dihedral angle R (right) shall be considered formed by two intersecting vertical planes, one parallel to the longitudinal axis of the rotorcraft and the other at 110° to the right of the first, when looking forward along the longitudinal axis.

(c) Dihedral angle A (aft) shall be considered formed by two intersecting vertical planes making angles of 70° to the right and 70° to the left, respectively, looking aft along the longitudinal axis, to a vertical plane passing through the longitudinal axis.

§ 6.634 Position light distribution and intensities.

(a) General. The intensities prescribed in this section are those to be provided by new equipment with all light covers and color filters in place. Intensities shall be determined with the light source operating at a steady value equal to the average luminous output of the light source at the normal operating voltage of the rotorcraft. The light distribution and intensities of position lights shall comply with the provisions of paragraph (b) of this section.

(b) Forward and rear position lights. The light distribution and intensities of forward and rear position lights shall be expressed in terms of minimum intensities in the horizontal plane, minimum intensities in any vertical plane, and maximum intensities in overlapping beams,

§ 6.624 Master switch installation.

The master switch or its controls shall be so installed that it is easily discernible and accessible to a member of the crew in flight.

§ 6.625 Protective devices.

Protective devices (fuses or circuit breakers) shall be installed in the circuits to all electrical equipment, except that such items need not be installed in the main circuits of starter motors or in other circuits where no hazard is presented by their omission. If fuses are used, one spare of each rating or 50 percent spare fuses of each rating, whichever is the greater, shall be provided. § 6.625-1 Automatic reset circuit breakers (FAA policies which apply to § 6.625).

Automatic reset circuit breakers (which automatically reset themselves periodically) should not be applied as circuit protective devices.' They may be used as integral protectors for electrical equipment (e. g., thermal cut-outs) provided that circuit protection is also installed to protect the cable to the equipment.

[Supp. 10, 19 F. R. 8140, Dec. 10, 1954]

§ 6.625-2

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Circuit breakers (FAA poli-15

cies which apply to § 6.625).

All resettable type circuit protective devices should be so designed that, when an overload or circuit fault exists, they will open the circuit irrespective of the position of the operating control.2 [Supp. 11, 21 F. R. 2585, Apr. 20, 1956]

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FIGURE 6-4-Minimum effective intensities for anticollision lights.

[Amdt. 6-1, 22 F. R. 1275, Mar. 1, 1957]

§ 6.637-1 Anti-collision light standards (FAA policies which apply to § 6.637).

The anti-collision light standards in § 6.637 apply to rotorcraft for which an application for a type certificate is made on or after April 1, 1957. When anticollision lights are installed on rotorcraft for which an application for a type certificate was made before April 1, 1957, the applicant may conform either to § 6.637 or the standards listed below:

(a) Anti-collision lights (when installed) should be of the rotating beacon type installed on top of the fuselage in such a location that the light will not be detrimental to the crew's vision and will not detract from the conspicuity of the position lights. If there is no acceptable location on top of the fuselage, a bottom fuselage installation may be used.

(b) The color of the anti-collision light should be aviation red in accordance with the specifications of § 6.635.

(c) The arrangement of the anti-collision light, i. e., number of light sources, beam width, speed of rotation, etc., should be such as to give an effective flash frequency of not less than 40 and

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