(a) Except as provided in paragraph (b), a holder of an air operator certificate must ensure that an aeroplane operated under IFR is equipped with—
(1) the following that must be in addition to, and independent of, the instruments and equipment required under Subpart F of Part 91:
(i) a means of indicating airspeed, calibrated in knots, with a means of preventing malfunctioning due to either condensation or icing:
(ii) a means of indicating sensitive pressure altitude calibrated in feet; and
(2) spare bulbs for flight compartment instrument illumination; and
(3) spare fuses.
(b) An additional means of indicating aeroplane attitude, powered by a power source that is separate from the power source for the attitude indication required under Subpart F of Part 91, may be installed instead of the additional means of indicating air speed required by paragraph (a)(1)(i).
(c) A holder of an air operator certificate must ensure that an aeroplane used to conduct a SEIFR passenger operation is equipped with an emergency electrical supply system with sufficient capacity for the following in the event that all engine-powered electrical generating systems fail:
(1) the extension of landing gear, if appropriate:
(2) the extension of flaps:
(3) the operation of those aeroplane systems essential for continued safe IFR flight and landing, including those required by paragraphs (d)(3), (d)(4), and (d)(5):
(4) either of the following whichever requires the higher electrical load—
(i) the descent of the aeroplane from maximum operating altitude to sea level, assuming the aeroplane is configured in the optimum gliding configuration and operated at the optimum still air range gliding speed for the descent, plus one attempt at engine restart; or
(ii) the continuation of flight for a minimum of one hour.
(d) A holder of an air operator certificate must ensure that an aeroplane used to conduct a SEIFR passenger operation is equipped with—
(1) an additional independent engine-powered electrical generating system capable of supplying adequate electrical power for all the required electrically operated instruments and systems; and
(2) an additional attitude indicator, powered by an independent source; and
(3) an area navigation system capable of being programmed with the positions of aerodromes and emergency landing sites en-route that is—
(i) certified for IFR by the navigation system manufacturer; and
(ii) permanently installed in the aeroplane; and
(iii) powered by the aeroplane's emergency electrical supply system; and
(4) a radar altimeter or radio altimeter that is powered by the aeroplane's emergency electrical supply system; and
(5) a landing light that is powered by the aeroplane's emergency electrical supply system; and
(6) for a pressurised aeroplane, sufficient additional oxygen for every occupant for the period that is required for the aeroplane to descend safely from its cruising level to a cabin altitude of 14,000 feet following engine failure assuming—
(i) the maximum cabin leak rate; and
(ii) the best range gliding speed for the aeroplane; and
(iii) the best gliding configuration for the aeroplane; and
(7) a powerplant installation that has been certificated by an ICAO Contracting State to FAR 33, or equivalent airworthiness standards, and is equipped with—
(i) an ignition system that activates automatically, or is capable of being operated manually, for take-off and landing, and during flight in visible moisture and is designed to be capable of operation for the full duration of any flight; and
(ii) a magnetic particle detector system that monitors the engine and reduction gearbox lubrication systems, and includes a flight deck caution indicator; and
(iii) an engine control system that permits continued operation of the engine through a power range sufficient to allow diversion to a suitable aerodrome and landing in the event the fuel control unit fails or malfunctions; and
(iv) an engine fire warning system; and
(8) a means of displaying charts that enables them to be readable in all ambient light conditions.
(e) If the magnetic particle detector system required by paragraph (d)(7)(ii) incorporates a method to remove detected particles without the removal of the particle detector from the engine or without examining the particles, the holder of the air operator certificate must ensure that each particle detection occurrence indicated by the particle detection system is recorded in the technical log as soon as practicable after the indication.
