ED Decision 2003/16/RM
(a) Each cowling and engine compartment covering must be constructed and supported so that it can resist the vibration, inertia and air loads to which it may be subjected in operation.
(b) Cowling must meet the drainage and ventilation requirements of CS 29.1187.
(c) On rotorcraft with a diaphragm isolating the engine power section from the engine accessory section, each part of the accessory section cowling subject to flame in case of fire in the engine power section of the powerplant must:
(1) Be fireproof; and
(2) Meet the requirements of CS 29.1191.
(d) Each part of the cowling or engine compartment covering subject to high temperatures due to its nearness to exhaust system parts or exhaust gas impingement must be fireproof.
(e) Each rotorcraft must:
(1) Be designed and constructed so that no fire originating in any fire zone can enter, either through openings or by burning through external skin, any other zone or region where it would create additional hazards;
(2) Meet the requirements of sub-paragraph (e)(1) with the landing gear retracted (if applicable); and
(3) Have fireproof skin in areas subject to flame if a fire starts in or burns out of any designated fire zone.
(f) A means of retention for each openable or readily removable panel, cowling, or engine or rotor drive system covering must be provided to preclude hazardous damage to rotors or critical control components in the event of:
(1) Structural or mechanical failure of the normal retention means, unless such failure is extremely improbable; or
(2) Fire in a fire zone, if such fire could adversely affect the normal means of retention.
EASA CS 29.1193 mandates cowling and engine compartment covering design for load resistance, fireproofing, drainage, ventilation, and retention to prevent fire spread and hazardous damage.
* Summary by Aviation.Bot - Always consult the original document for the most accurate information.
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