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minimize the production of smoke and toxic gases in the
event of a fire and to delay the occurrence of flashover D.5.1 Electrical bonding and protection against lightning
in the cabin. and static electricity shall be such as to:
g) Cargo compartment protection.
1) Sources of heat within the compartment which are
capable of igniting the cargo or baggage shall be
shielded or insulated to prevent such ignition; and
2) Each cargo and baggage compartment shall be
constructed of materials which are at least flame
resistant.
h) Incapacitation of occupants. Design precautions shall be
taken to protect against possible instances of cabin
depressurization and against the presence of smoke or
other toxic gases that could incapacitate the occupants
of the aeroplane.
a) protect the aeroplane, its systems, its occupants and
those who come in contact with the aeroplane on the
ground or water from the dangerous effects of lightning
discharge and electrical shock; and
b) prevent dangerous accumulation of electrostatic charge.
D.5.2 The aeroplane shall also be protected against
catastrophic effects of lightning. Due account shall be taken of
the material used in the construction of the aeroplane.
D.6 Emergency landing provisions
D.6.1 Provisions shall be made in the design of the aero-
D.3 Aeroelasticity plane to protect the occupants, in the event of an emergency
landing, from fire and from the direct effects of deceleration
The aeroplane shall be free from flutter, stntctural divergence, forces as well as from injuries arising from the effect of decelcontrol
reversal. loss of control due to structural deformation eration forces On the equipment.
and aeroelastic effects, at all speeds within and sufficiently
beyond the design envelope to comply with A.2.1. Account D.6.2 Facilities shall be provided for the rapid evacuation
shall be taken of the characteristics of the aeroplane. of the aeroplane in conditions likely to occur following an
emergency landing. Such facilities shall be related to the passenger
aid crew capacity of the aeroplane and shall be shown
D.4 Occupant accommodation features to be suitable for their intended purpose.
D.4.1 Seating and restraints
D.7 Ground handlin-g
Adequate seating and restraints shall be provided for the
occupants, taking account of the likely flight and emergency Design provisions and procedures for safe ground-handling
landing loads to be encountered. Attention shall be paid to (e.g, towing, jacking) shall be defined. The protection that any
minimizing injury to occupants due to contact with surround- limitations and instructions for such operations might provide
ing structure during the operation of the aeroplane. may be taken into account.
E.l Engines
SUB-PART E. POWERPLANT
E.3.4 Engine restarting
The Standards of Part VI of this Annex shall apply to each
engine that is used on the aeroplane as a primary propulsion
unit.
Means shall be provided for restarting an engine in flight at
altitudes up to a declared maximum altitude.
E.3.5 Arrangement and functioning
E.2 Propellers
The Standards of Part VII of this Annex shall apply to each
propeller that is used on the aeroplane.
E.3 Powerplant installation
E.3.1 Compliance with engine and
propeller limitations
The powerplant installation shall be so designed that the
engines and propellers (if applicable) are capable of functioning
reliably in the anticipated operating conditions. In conditions
established in the flight manual, the aeroplane shall be
capable of being operated without exceeding the limitations
established for the engines and propellers in accordance with
this sub-part.
E.3.2 Control of engine rotation
In those installations where continued rotation of a failed
engine would increase the hazard of fire or of a serious structural
failure, means shall be provided for the crew to stop the
rotation of the engine in flight or to reduce it to a safe level.
Note.- In the case of propeller blade separation it may be
impossible to stop engine rotation.
E.3.3 Turbine engine
For a turbine engine installation:
a) the design shall minimize the hazards to the aeroplane in
the event of failure of engine rotating parts, or an engine
fire which burns through the engine case; and
b) the power-unit together with the associated engine control
devices, systems and instrumentation shall be designed to
give reasonable assurance that those engine operating
limitations that adversely affect the structural integrity of
rotating parts shall not be exceeded in service.
E.3.5.1 Independence of power-units. The powerplant
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附件8--航空器适航性 Airworthiness of Aircraft(68)
