Code of Federal Regulations

Title 14 - Aeronautics and Space
Volume: 3Date: 2021-01-01Original Date: 2021-01-01Title: Section § 135.163 - Equipment requirements: Aircraft carrying passengers under IFR.Context: Title 14 - Aeronautics and Space. CHAPTER I - FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED). SUBCHAPTER G - AIR CARRIERS AND OPERATORS FOR COMPENSATION OR HIRE: CERTIFICATION AND OPERATIONS. PART 135 - OPERATING REQUIREMENTS: COMMUTER AND ON DEMAND OPERATIONS AND RULES GOVERNING PERSONS ON BOARD SUCH AIRCRAFT. Subpart C - Aircraft and Equipment.
§ 135.163 Equipment requirements: Aircraft carrying passengers under IFR. No person may operate an aircraft under IFR, carrying passengers, unless it has— (a) A vertical speed indicator; (b) A free-air temperature indicator; (c) A heated pitot tube for each airspeed indicator; (d) A power failure warning device or vacuum indicator to show the power available for gyroscopic instruments from each power source;
Code of Federal Regulations / Title 14 - Aeronautics and Space / Vol. 3 / 2021-01-01446
(e) An alternate source of static pressure for the altimeter and the airspeed and vertical speed indicators; (f) For a single-engine aircraft: (1) Two independent electrical power generating sources each of which is able to supply all probable combinations of continuous inflight electrical loads for required instruments and equipment; or (2) In addition to the primary electrical power generating source, a standby battery or an alternate source of electric power that is capable of supplying 150% of the electrical loads of all required instruments and equipment necessary for safe emergency operation of the aircraft for at least one hour; (g) For multi-engine aircraft, at least two generators or alternators each of which is on a separate engine, of which any combination of one-half of the total number are rated sufficiently to supply the electrical loads of all required instruments and equipment necessary for safe emergency operation of the aircraft except that for multi-engine helicopters, the two required generators may be mounted on the main rotor drive train; and (h) Two independent sources of energy (with means of selecting either) of which at least one is an engine-driven pump or generator, each of which is able to drive all required gyroscopic instruments powered by, or to be powered by, that particular source and installed so that failure of one instrument or source, does not interfere with the energy supply to the remaining instruments or the other energy source unless, for single-engine aircraft in all cargo operations only, the rate of turn indicator has a source of energy separate from the bank and pitch and direction indicators. For the purpose of this paragraph, for multi-engine aircraft, each engine-driven source of energy must be on a different engine. (i) For the purpose of paragraph (f) of this section, a continuous inflight electrical load includes one that draws current continuously during flight, such as radio equipment, electrically driven instruments, and lights, but does not include occasional intermittent loads. [Doc. No. 16097, 43 FR 46783, Oct. 10, 1978, as amended by Amdt. 135-70, 62 FR 42374, Aug. 6, 1997; Amdt. 135-72, 63 FR 25573, May 8, 1998]