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loads not required in controlled flight need not be considered for the two-engine inoperative condition on aeroplanes with three or more engines.
(4) if there is a fuel flowmeter, it must be blocked and the fuel must flow through the meter or its bypass.

when an item of equipment is discovered to be inoperative, it is reported by making an entry in the aircraft maintenance record/ journey logbook.
affected pump is selected off and is deactivated, and b.

loads not required for controlled flight need not be considered for the two-engine- inoperative condition on rotorcraft with three or more engines.
529.909 to 529.916 reserved rotor drive system 529.917 design (a) general. the rotor drive system includes any part necessary to transmit power from the engines to the rotor hubs.

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indicating indication inferior influence influenced influencing information information concerning en route weather phenomena which may affect the safety of aircraft operations infrared inland inoperative instability instead instrument instrument flight rules instruments intense intensely intensification intensified intensify intensifying intensity interior intermittent intermittently international internationally interrupt, interruption interrupted interrupting intersection intersections invade invaded invading invasion inversion iowa island islands isobar isobars isolate isolated isolating

(c) it must be shown by test that equipment containing high energy rotors can contain any failure of a high energy rotor that occurs at the highest speed obtainable with the normal speed control devices inoperative.
(d) there must be means to allow the crew to check, in flight, the functioning of each fire detector electric circuit. (e) wiring and other components of each fire detector system in a designated fire zone must be at least fire resistant.

(b) the indication provided must be designed to alert the flight crew if either of the following conditions exist: (1) the pitot heating system is switched "off". (2) the pitot heating system is switched "on" and any pitot tube heating element is inoperative.
(c) except where satisfactory operating experience with a similar tank in a similar installation is shown, non-metallic tanks must withstand the test specified in paragraph (b)(5) of this section, with fuel at a temperature of 110° f. during this test, a representative specimen of the tank must be installed in a supporting structure simulating the installation in the aeroplane.