Document ID: chunk:federal_register_of_legislation:F2005B00951:body:0:p5
Version: federal_register_of_legislation:F2005B00951
Segment Type: other
Provision Reference: 
Character Range: 10046–12823

components shall be manufactured in accordance with specifications acceptable to CASA.
3.13 Wooden aeroplanes, in which the integrity of the primary structure depends on glued joints, shall not be assembled with acid catalysed phenolics and/or urea formaldehyde glues.
3.14 Cockpit and cabin
The design of the cockpit and cabin shall be such as to give each occupant every reasonable chance of escaping serious injury in a crash.
3.15 Seats
Seats shall not have hard edges or protruding parts which in a crash would be in a position likely to cause serious head injuries to a person seated and wearing correctly adjusted restraint equipment.
3.16 Flight manual stowage
Stowage shall be provided for the flight manual either in a container of the glove box type or in a special fixed container readily accessible to the pilot.
3.17 Bonding
 (1) A positive method of bonding re-fuelling equipment to the aeroplane shall be, provided at each fuel filling point.
 (2) A clearly identified external bonding point suitable for the attachments of ground connections shall be provided on each main undercarriage assembly or on the nose gear.
POWERPLANT
3.18 Engines and propellers
Each engine, including any additional shafting, gearing or other components connecting it with a propeller, and each propeller, shall be:
 (1) type certificated or similarly approved for use in aircraft by a member state of the International Civil Aviation Organization in accordance with an appropriate national code of requirements acceptable to CASA; or

 (2) otherwise accepted by CASA as providing adequate levels of safety and reliability for the intended application.
3.19 Fuel tanks

 (1) Where a fuel tank is located in, or immediately to, the rear of the cabin or cockpit, the tank shall be so designed and installed that it will not be ruptured or torn loose by inertia forces when the tank and its contents are subjected separately to the maximum of the flight load factors and the following emergency load factors applied separately:
 (a) 9g forward;
 (b) 3g upward;
 (c) 1.5g sideward;
 (d) 4g downward.

 (1A) A factor of 1.33 shall apply to the fittings attaching the tank to the fuselage structure.

 (2) All drain cocks or valves shall be of an approved wire-locked or self‑closing type and be readily accessible. Drain plugs are not permitted.

 (3) The design shall be such as to prevent water which may accumulate in the tank from being conveyed to the engine(s) in any normal attitude of the aeroplane.
        Note: Where a conventional tank sump arrangement is impracticable a separate sediment bowl may be accepted provided it can be clearly demonstrated that the capacity of the sediment bowl is adequate for the purpose and that water will automatically drain from all parts of