Text in force at CS29-12: from CS29-0, effective 14 Nov 2003.
For rotorcraft with retractable landing gear, the following apply:
(a) Loads. The landing gear, retracting mechanism, wheel well doors, and supporting structure must be designed for:
(1) The loads occurring in any manoeuvring condition with the gear retracted;
(2) The combined friction, inertia, and air loads occurring during retraction and extension at any airspeed up to the design m aximum landing gear operating speed; and
(3) The flight loads, including those in yawed flight, occurring with the gear extended at any airspeed up to the design m aximum landing gear extended speed.
(b) Landing gear lock. A positive m eans m ust be provided to keep the gear extended.
(c) Emergency operation. W hen other than manual power is used to operate the gear, emergency means must be provided for extending the gear in the event of:
(1) Any reasonably probable failure in the normal retraction system; or
(2) The failure of any single source of hydraulic, electric, or equivalent energy.
(d) Operation tests. The proper functioning of the retracting m echanism m ust be shown by operation tests.
(e) Position indicator. There m ust be m eans to indicate to the pilot when the gear is secured in the extreme positions.
(f) Control. The location and operation of the retraction control m ust m eet the requirem ents of CS 29.777 and 29.779.
(g) Landing gear warning. An aural or equally effective landing gear warning device m ust be provided that functions continuously when the rotorcraft is in a norm al landing m ode and the landing gear is not fully extended and locked. A manual shutoff capability m ust be provided for the warning device and the warning system must automatically reset when the rotorcraft is no longer in the landing mode.
ED Decision 2003/016/RM · Source