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which will assist the flight crew in attaining the performance
as scheduled.
servicing (towing, refuelling, etc.) that could pass unnoticed
and that could jeopardize the safety of the helicopter in subsequent
flights.
G7 Continuing airworthiness -
maintenance information
G7.1 General
Information for use in developing procedures for maintaining
the helicopter in an airworthy condition shall be made available.
The information shall include that described in G7.2,
G7.3 and G7.4.
G7.2 Maintenance information
Maintenance information shall include a description of the
helicopter and recommended methods for the accomplishment
of maintenance tasks. Such information shall include guidance
on defect diagnosis.
G.7.3 Maintenance programme information
Maintenance programme information shall include the maintenance
tasks and the recommended intervals at which these
tasks are to be performed.
G5 Flight manual
A flight manual shall be made available. It shall identify
clearly the specific helicopter or series of helicopters to which
it is related. The flight manual shall include at least the limitations,
information and procedures specified in G2, G3, G4
and G6.1.
6 6 Markings and placards
G6.1 Markings and placards on instruments, equipment,
controls, etc., shall include such limitations or information as
necessary for the direct attention of the flight crew during
flight.
G.6.2 Markings and placards or instructions shall be
provided to give any information that is essential to the ground
crew in order to preclude the possibility of mistakes in ground
Note.- The development of initial maintenance programme
information at the time of helicopter type certification is sometimes
referred to as the Maintenance Review Board (MRB)
process or the process of developing instructions for continued
airworthiness.
G7.4 Mandatory maintenance requirements
resulting from the type design approval
Mandatory maintenance requirements that have been specified
by the State of Design as part of the approval of the type
design shall be identified as such and included in the maintenance
information of G.7.3.
Note.- Mandatory requirements identified as part of the
type design approval are often referred to as Certification
Maintenance Requirements (CMR) and/or airworthiness
limitations.
SUB-PART H. SYSTEMS SOFTWARE
All systems software shall be designed and validated such as
to ensure that the systems in which software is used perform
their intended functions with a level of safety that complies
with the requirements of this part.
Note.- Some States accept the use of nationaUinternational
industry standards, such as RTCA /DO-178 or
EUROCAE EDJ2, for the design and testing of systems
software.
ANNEX 8
SUB-PART I. CRASHWORTHINESS AND CABIN SAFETY
1.1 General c) provision of safety features to allow for safe evacuation;
and
Crashworthiness shall be taken into account in the design of
helicopters to improve the probability of occupant survival. d) fire suppression equipment.
1.2 Design emergency landing conditions
Emergency landing (crash) loads shall be determined so that
the interiors, furnishings, support structure and safety equipment
can be designed to reasonably protect occupants under
emergency landing conditions. Items to be considered shall
include:
a) dynamic effects;
b) restraint criteria for items that could cause a hazard;
C) deformation of the fuselage in the areas of emergency
exits:
d) fuel cell integrity and position; and
e) integrity of electrical systems to avoid sources of
ignition in the area of fuel components.
1.4 Evacuation
The helicopter shall be equipped with sufficient emergency
exits to allow for cabin evacuation within an appropriate time
period. Items to be considered, appropriate to the size and
category of the helicopter, shall include:
a) number of seats and seating configuration;
b) number, location and size of exits;
c) marking of exits and provision of instructions for use;
d) likely blockages of exits;
e) operation of exits; and
f ) positioning and weight of evacuation equipment at exits,
e.g. slides and rafts.
1.5 Lighting and marking
1.3 Cabin fire protection
The cabin shall be so designed as to provide fire protection to
the occupants in the event of airborne systems failures or a
crash situation. Items to be considered shall include:
a) flammability of cabin interior materials;
b) fire resistance and, for helicopters of a maximum
certificated take-off mass greater than 3 175 kg, the
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附件8--航空器适航性 Airworthiness of Aircraft(61)
