(b) For functions whose failure would contribute to or cause a condition that would reduce the capability of the airplane or the ability of the flightcrew to cope with adverse operating conditions, each electrical and electronic system that performs these functions must be designed and installed to ensure that these functions can be recovered in a timely manner after the airplane is exposed to lightning.
(c) Compliance with the lightning protection criteria prescribed in paragraphs (a) and (b) of this section must be shown for exposure to a severe lightning environment. The applicant must design for and verify that aircraft electrical/electronic systems are protected against the effects of lightning by:
(1) Determining the lightning strike zones for the airplane;
(2) Establishing the external lightning environment for the zones;
(3) Establishing the internal environment;
(4) Identifying all the electrical and electronic systems that are subject to the requirements of this section, and their locations on or within the airplane;
(5) Establishing the susceptibility of the systems to the internal and external lightning environment;
(6) Designing protection; and
(7) Verifying that the protection is adequate.
[Doc. No. 25912, 59 FR 22116, Apr. 28, 1994]