he equipment requirements for seales and amphibians shall be the e as specified for landplanes 1a.532-4a.536) except that seaplanes amphibians shall not be certificated operation over water out of sight and unless they have at least the pment specified in § 4a.533, and exthat all certificated seaplanes and hibians shall also have an approved >reserver or flotation device for each ɔn for whom there is a seat, and pt that all seaplanes and amphibians ficated for night operation shall have a white anchor light.

CARRIER AIRPLANES; PASSENGER (ACP) 547 Air carrier airplanes; passengers (ACP).

planes certificated for use by an air er in passenger service shall have led at least the equipment set forth 4a.548-48.552.

May 31, 1938, as amended by Reg. -1, 3 F. R. 2055, Aug. 28, 1938]

§ 4a.548 ACP landplanes; visual contact day flying.

The same as specified in § 4a.533 and, in addition, the following:

(a) An electrical heated pitot tube, or equivalent, for the air-speed indicator. (b) One additional portable fire extinguisher of the type specified in § 4a.532 (j). (See § 4a.566 for installation requirements.)

(c) Fixed fire extinguishing apparatus of an approved type for each engine compartment.

(d) Type certificated radio equipment as specified in Part 40 of this subchapter. (e) A set of spare fuses. (See § 4a.572 for installation requirements.)

(f) A rate-of-climb indicator. (g) A § 4a.535 (f).

Same storage battery:

as

(h) A means for providing, without continuous manual operation, vision through the windshield adequate for executing take-offs and landings in rain. [Amdt. 129, 6 F. R. 4691, Sept. 13, 1941, as amended by Amdt. 04-15, 7 F. R. 6240, Aug. 12, 1942]

§ 4a.549

ACP landplanes; visual contact night flying.

The same as specified in § 4a.548 and, in addition, the following:

(a) A set of certificated air carrier airplane position lights. The forward lights may be air carrier forward position lights or a combination of standard forward position lights and a set of auxiliary forward position lights. (See Part 15 of this subchapter, 14 F. R. 4190, July 16, 1949, for light requirements and § 4a.578 for installation requirements.)

(b) A storage battery of sufficient capacity for such lights and radio as are installed.

CROSS REFERENCE: For installation requirements, see §§ 4a.571, 48.573.

(c) Two electric landing lights. CROSS REFERENCE: For installation requirements, see § 48.576.

(d) Certificated landing flares as follows: two Class 1 flares or three Class 2 flares and one Class 1 flare.

CROSS REFERENCES: For flare requirements, see Part 15 of this subchapter (14 F. R. 4190, July 16, 1949). For installation requirements, see § 48.568.

(e) Instrument lights.

CROSS REFERENCE: For installation requirements, see § 48.577.

(f) Cabin lights in all passenger cabins and compartments.

(g) A generator. (See § 4a.573 for requirements.)

(h) Radio equipment same as § 40.61 of this subchapter.

[CAR, May 31, 1938, as amended by Amdt. 04-9, 7 F. R. 1709, Mar. 5, 1942; Amdt. 04-2, 8 F. R. 13999, Oct. 14, 1943]

§ 4a.550 ACP landplanes; instrument day flying.

The same as specified in § 4a.548 except § 4a.548(b) and, in addition, the following:

(a) A gyroscopic rate-of-turn indicator combined with a bank indicator.

(b) A gyroscopic instrument showing bank and pitch.

(c) A gyroscopic direction finder.

(d) Two sensitive-type altimeters, both of which shall be adjustable for changes in barometric pressure and compensated for changes in temperatures: Provided, That aircraft in use on or before January 1, 1939, and thereafter replacements and additions of aircraft of the same make and model may, for purposes of standardization, be deemed to have met this requirement, if there are installed in each such aircraft one sensitive type altimeter and one standard type altimeter, provided each is adjustable for changes in barometric pressure and compensated for changes in temperature.

(e) A free air thermometer of the distance type with an indicating dial in the cockpit.

(f) A clock with a sweep second hand. (g) A vacuum gauge, installed in the lines leading to instruments in paragraphs (a), (b) and (c) of this section.

(h) Type certificated radio equipment as specified in Part 40 of this subchapter.

(i) Means shall be provided to indicate icing conditions, or the probability thereof, in the carburetor if the de-icing device specified in § 4a.616 requires the manual manipulation of controls.

(j) A storage battery suitable as a source of energy supply for the radio equipment installed.

CROSS REFERENCE: For installation requirements, see §§ 4a.571, 4a.573.

(k) A generator.

CROSS REFERENCE: For installation requirements, see § 4a.573.

The regulations in §§ 4a.559-4a.564 shall apply to the installation of instruments when such instruments are required by the regulations in this part. § 4a.559 Air-speed indicator.

This instrument shall be so installed as to indicate true air speed at sea level with the maximum practicable accuracy, but the instrument error shall not be more than plus or minus 3 percent, except that it need not be less than plus or minus 5 miles per hour, at the level flight speed corresponding to the design power (§ 4a.38 (b)), at Vz (§ 4a.40 (c)), or at the maximum attainable level flight speed, whichever is lowest.

[Amdt. 5, 4 F. R. 1171, Mar. 9, 1939]

§ 4a.560 Powerplant instruments and controls.

See § 4a.642, 4a.643.

§ 4a.561 Fuel quantity gauge.

See § 4a.609.

§ 4a.562 Magnetic compass.

This instrument shall be properly damped and compensated and shall be located where it is least affected by electrical disturbances and magnetic influences.

§4a.563 Navigational instruments.

Navigational instruments for use by the pilot shall be so installed as to be easily visible to him with the minimum practicable deviation from his normal position and line of vision when he is looking out and forward along the flight path, and they shall also be visible to the second pilot.

§ 4a.564 Gyroscopic instruments.

All gyroscopic instruments shall derive their energy from engine-driven pumps or from auxiliary power units. Each source of energy supply and its attendant complete installation shall comply with the instrument manufacturer's recommendations for satisfactory instrument operation. On multiengine aircraft each instrument shall have two separate sources of energy, either one of which shall be capable of carrying the required load. Engine-driven pumps, when used, shall be on separate engines. The installation shall be such that failure of one source of energy or breakage of one line will not interfere with proper functioning of the instruments by means of the other source.

SAFETY EQUIPMENT INSTALLATION

§ 4a.565 Safety belts.

Airplanes manufactured on or after January 1, 1951, shall be equipped with safety belts approved in accordance with § 4a.31. In no case shall the rated strength of the safety belt be less than that corresponding with the ultimate load factors specified in § 4a.193, taking due account of the dimensional characteristics of the safety belt installation for the specific seat or berth arrangement. Safety belts shall be attached so that no part of the anchorage will fail at a load lower than that corresponding with the ultimate load factors specified in §4a.193.

[Amdt. 4a-4, 15 F. R. 29, Jan. 6, 1950] § 4a.566 Fire extinguishers.

The portable fire extinguisher specified in § 4a.532(j) shall be so installed as to be accessible to the passengers. The two portable fire entinguishers specified in § 4a.548 shall be so installed that one is readily available to the crew and the other is near the main external cabin door where it shall be readily available to passengers and ground personnel.

Fuses shall be so located that they can readily be replaced in flight. They shall break the current in a generating system at a sufficiently small current flow adequately to protect the lights, radio equipment, and other parts of the circuit. § 4a.573 Generator.

When a generator is specified it shall have sufficient capacity to carry the entire running load. Such generator shall be engine-driven unless an approved equivalent system is provided. Auxiliary power units will be approved in lieu of batteries and engine-driven generators,

provided that they are at least two in number and that the supply system is capable of carrying the entire running load with any one unit out of action.

§ 4a.574 Running load.

The running load shall be defined as the electric consumption of all lights, radio equipment, and other electrical devices, except those which are designed only for occasional intermittent use. Examples of devices regarded as intermittent are radio broadcasting equipment, landing lights, and electrically operated landing gears and wing flaps. Radio range signal receivers and all other lights are considered a part of the constant load.

§ 4a.575 Anchor lights.

The anchor light specified for seaplanes and amphibians shall be so mounted and installed that, when the airplane is moored or drifting on the water, it will show a white light visible for at least 2 miles at night under clear atmospheric conditions.

[Amdt. 48, 5 F. R. 1836, May 22, 1940] § 4a.576 Landing lights.

Electric landing lights shall be so installed on multiengine aircraft that at least one shall be not less than 10 feet to the right or left of the first pilot's seat and beyond the swept disk of the outermost propeller. On single-engine aircraft such lights shall be so installed that no visible portion of the swept disk of the propeller, if of the tractor type, is illuminated thereby. Individual switches for each light shall be provided in the pilot compartment.

[Amdt. 5, 4 F. R. 1171, Mar. 9, 1939] § 4a.577 Instrument lights.

Instrument lights shall be so installed as to provide sufficient illumination to make all flight instruments easily readable and shall be equipped with rheostat control for dimming unless it can be shown that a nondimming light is satisfactory.

and right, respectively, of the airplane from dead ahead. Such forward position lights shall be spaced laterally as far apart as practicable. One rear position light shall be installed on the airplane at the rear and as far aft as possible and shall show a light visible aft throughout a dihedral angle of 140 degrees bisected by a vertical plane through the longitudinal axis of the airplane. Such light shall emit (a) in the case of a non-air carrier airplane, either a continuous white light as specified in § 15.20 (b) (5) of this subchapter, or alternate red and white flashes as specified in § 15.20 (b) (6) of this subchapter, and (b) in the case of an air carrier airplane, alternate red and white flashes as specified in § 15.20 (b) (6) of this subchapter (14 F. R. 4193, July 16, 1949). In lieu of such a single flashing rear position light, an airplane may carry two rear position lights, one red and one white, spaced as closely as possible to each other and in combination emitting the red and white flashes specified in § 15.20 (b) (6) of this subchapter.

[Amdt. 04-10, 7 F. R. 1709, Mar. 5, 1942, as amended by Amdt. 04-1, 9 F. R. 2772, Mar. 14, 1944; Amdt. 04-2, 9 F. R. 11462, Sept. 19, 1944]

Seats or chairs, even though adjustable, in open or closed airplanes, shall be securely fastened in place whether or not the safety belt load is transmitted through the seat.

§ 4a.581 Accessories.

Engine-driven accessories on multiengine aircraft shall be distributed among two or more engines.

Subpart G-Power-plant
Installation

SOURCE: § 4a.591 to 48.661 contained in Civil Air Regulations, May 31, 1938, as amended by Amendment 75, 5 F. R. 3946, Oct. 8, 1940, except as otherwise noted.

ENGINES

§ 4a.591 Engines.

Engines shall be of a type and design which has been type certificated, or found eligible for use in certificated air

craft, in accordance with the requirements of Part 13 of this subchapter (14 F.R. 4187, July 16, 1949) or shall have been approved as airworthy in accordance with previous regulations.

[Amdt. 116, 6 F.R. 2870, June 13, 1941]

PROPELLERS

4a.597 Propellers.

Propellers shall be of a type and design which has been certificated as airworthy in accordance with the requirements of Part 14 of this subchapter (14 F.R. 4188, July 16, 1949) or shall have been approved as airworthy in accordance with previous regulations, except that wood propellers of a conventional type for use in light airplanes need not be certificated. In certain cases maximum engine bore limitations are also assigned to propellers. Propellers may be used on any engine provided that the certified power ratings, speed ratings, and bore of the engine are not in excess of the limitations of the propeller as certificated, and further provided that the vibration characteristics of the combination are satisfactory to the Administrator.

[CAR, May 31, 1938, as amended by Amdt. 04-2, 8 F.R. 13999, Oct. 14, 1943]

§ 4a.598 Controllable pitch.

The control mechanism shall be designed and equipped with a positive stop which shall limit the minimum pitch so that the take-off crankshaft speed for which the aircraft is certificated is not exceeded during take-off with take-off power unless it is necessary to so locate the stop that a higher crankshaft speed nay be used in an emergency. The neans provided for controlling the pitch shall be so arranged as to minimize the ttention required from a pilot to prevent the engines from exceeding their rankshaft speed limitations under any light condition.

4a.599 Propeller clearance.

Propellers shall have a minimum round clearance of 9 inches when the irplane is in a horizontal position with he landing gear deflected as it would be nder the maximum authorized weight f the airplane. Propellers on seaplanes hall clear the water by at least 18 iches when the seaplane is at rest under he maximum authorized load condition. clearance of at least 1 inch shall be rovided between the tips of the proellers and any part of the structure.

The fuel capacity shall be at least 0.15 gallons per maximum (except take-off) horsepower for which the airplane is certificated. Air-pressure fuel systems shall not be used. Only straight gravity feed or mechanical pumping of fuel is permitted. The system shall be so arranged that the entire fuel supply may be utilized in the steepest climb and at the best gliding angle and so that the feed ports will not be uncovered during normal maneuvers involving moderate rolling or side slipping. The system shall also feed fuel promptly after one tank has run dry and another tank is turned on. If a mechanical pump is used, an emergency hand pump of equal capacity shall be installed and available for immediate use in case of a pump failure during take-off. Hand pumps of suitable capacity may also be used for pumping fuel from an auxiliary tank to a main fuel tank.

§ 4a.606 Tank installation.

No fuel tank shall be placed closer to an engine than the remote side of a fire wall. At least one-half inch clear air space shall be allowed between the tank and the fire wall. Spaces adjacent to the surfaces of the tank shall be ventilated so that fumes cannot accumulate or reach the crew or passengers in case of leakage. If two or more tanks have their outlets interconnected they shall be considered as one tank and the air space in the tanks shall also be interconnected to prevent differences in pressure at the air vents of each tank of sufficient magnitude to cause fuel flow between tanks. Mechanical pump systems shall not feed from more than one tank at a time except by special ruling from the Administrator.

Each fuel tank shall be provided with either a sump and drain located at the point which is lowest when the airplane is in a normal position on the ground or outlets at the bottom of the tank provided with large mesh finger strainers. If a sump is provided, the main fuel supply shall not be drawn from the bottom of this sump. If no sump is provided, the system drain shall be controllable from the pilot compartment and shall act as a tank drain. Each tank shall be suitably vented from the top