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b) prevent dangerous accumulation of electrostatic charge.
D.3 Flutter D.5.2 The helicopter shall also be protected against
catastrophic effects of lightning. Due account shall be taken of
Each aerodynamic surface of the helicopter shall be free from the material used in the construction of the helicopter.
flutter under each appropriate speed and power condition.
D.6 Emergency landing provisions
D.4 Occupant accommodation features
D.4.1 Seating and restraints
Adequate seating and restraints shall be provided for the
occupants, taking account of the likely flight and emergency
landing loads to be encountered. Attention shall be paid to
minimizing injury to occupants due to contact with surrounding
structure during the operation of the helicopter.
D.4.2 Cabin environment
D.6.1 Provisions shall be made in the design of the
helicopter to protect the occupants from fire and effects of
deceleration in the event of an emergency landing.
D.6.2 Facilities shall be provided for rapid evacuation of
the helicopter in conditions likely to occur following an
emergency landing, and such facilities shall be related to the
passenger and crew capacity of the helicopter. On helicopters
certificated for ditching conditions, provisions shall also be
made in the design to give reasonable assurance that safe
evacuation from the helicopter of passengers and crew can be
executed in case of ditching.
Ventilation systems shall be designed to provide the cabin with
an adequate environment during the anticipated flight and
ground operating conditions.
D.7 Ground handling
Adequate provisions shall be made in the design to minimize
D.5 Electrical bonding and protection against the risk that normal ground-handling operations (e.g. towing,
lightning and static electricity jacking) may cause damage, which could pass unnoticed, to
the parts of the helicopter essential for its safe operation. The
D.5.1 Electrical bonding and protection against lightning protection that any limitations and instructions for such
and static electricity shall be such as to: operations might provide may be taken into account.
SUB-PART E. ROTORS AND POWERPLANT
E.l Engines
The Standards of Part VI of this Annex shall apply to engines
of all types which are used on the helicopter as primary
propulsion units.
E.2 Rotors and powerplant installation
approved device for automatically increasing power
when an engine fails. When the helicopter approaches a
rotor rotational speed limit, with or without engines
inoperative, clear and distinctive warnings shall be
apparent to the pilot. The warnings or initial characteristics
of the condition shall be such as to enable the pilot
to arrest the development of the condition after the
warning begins and to recover the rotor rotational speed
to within prescribed normal limits and to maintain full
control of the helicopter.
E.2.1 General
E.2.4 Tests
The powerplant installation and rotors shall comply with the
Standards of Sub-Part D and with the Standards of E.2.
E.2.2 Design, construction and functioning
a) The rotors and rotor drive systems assembly complete
with accessories shall be designed and constructed so as
to function reliably within their operating limitations
under the anticipated operating conditions when
properly fitted to the engine and installed in the helicopter
in accordance with this sub-part.
b) For helicopters of maximum certificated take-off mass
greater than 3 175 kg or helicopters which are certificated
to Category A Standard, an assessment shall be
conducted for the rotors and rotor drive systems to
ensure that they function safely throughout the full
range of operating conditions. Where this assessment
identifies a failure which could prevent continued safe
flight or landing of the helicopter, means shall be
prescribed to minimize the likelihood of that failure.
E.2.3 Declared ratings, conditions and limitations
The power ratings and all operating conditions and limitations
which are intended to govern the operation of the rotors and
rotor drive systems shall be declared.
a) Maximum and minimum rotor rotational speed limitations.
Maximum and minimum speeds for the rotors in
both power-on and power-off conditions shall be established.
Any operating conditions (e.g. airspeed) that
affect such maxima or minima shall be declared.
b) Rotor underspeed warnings for single engine helicopters,
and for multi-engine helicopters not having an
Rotors and rotor drive systems shall complete satisfactorily
such tests as are necessary to ensure that they will operate
　
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