Text in force at CS29-12: from CS29-0, effective 14 Nov 2003.
(a) The rot orcraft, al though i t may be damaged in emergency landing conditions on l and or wat er, m ust be desi gned as prescribed in this paragraph t o prot ect t he occupant s under those conditions.
(b) The st ructure m ust be designed to give each occupant every reasonable chance of escaping serious injury in a crash landing when:
(1) Proper use i s m ade of seat s, bel ts, and other safety design provisions;
(2) The wheels are retracted (where applicable); and
(3) Each occupant and each item of mass inside the cabin th at co uld in jure an occupant i s rest rained when subjected to the following u ltimate in ertial lo ad factors relative to the surrounding structure:
(i) Upward – 4 g (ii) Forward – 16 g (iii) Sideward – 8 g (iv) Downward – 20g, aft er t he intended displacement of the seat device (v) Rearward – 1.5 g.
(c) The supporting st ructure m ust be designed to restrain under any ultim ate inertial load factor up to those specified in this paragraph, any i tem of m ass above and/ or behind the crew and passenger com partment t hat could injure an occupant if it came loose in an emergency landing. Items of mass to be considered include, but are not limited to, rotors, tran smission an d en gines. Th e items of mass must be restrained for the following ultimate inertial load factors:
(1) Upward – 1.5 g (2) Forward – 12 g (3) Sideward – 6 g (4) Downward – 12 g (5) Rearward – 1.5 g.
(d) Any fuselage structure in the area of internal fuel tanks below the passenger floor level must be d esigned to resist th e fo llowing u ltimate inertia factors and loads, and to protect the fuel tanks from rupture, if rupture is likely when those loads are applied to that area:
(1) Upward – 1.5 g (2) Forward – 4.0 g (3) Sideward – 2.0 g (4) Downward – 4.0 g
ED Decision 2003/016/RM · Source