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information from the State of Design, adopt the mandatory
information directly or assess the information
received and take appropriate action;
e) ensure the transmission to the State of Design of all
mandatory continuing airworthiness information which
it, as the State of Registry, originated in respect of that
aircraft; and
f) ensure that, in respect of aeroplanes over 5 700 kg and
helicopters over 3 175 kg maximum certificated take-off
mass, there exists a system whereby information on
faults, malfunctions, defects and other occurrences that
cause or might cause adverse effects on the continuing
airworthiness of the aircraft is transmitted to the organization
responsible for the type design of that aircraft.
Note.- Guidance on interpretation of "the organization
responsible for the type design" is contained in the Airworthiness
Manual (Doc 9760).
4.2.4 All Contracting States
Each Contracting State shall establish, in respect of aeroplanes
over 5 700 kg and helicopters over 3 175 kg maximum certificated
take-off mass, the type of service information that is to
be reported to its airworthiness authority by operators, organizations
responsible for type design and maintenance organizations.
Procedures for reporting this information shall also be
established.
PART 111. LARGE AEROPLANES
PART IIIA. AEROPLANES OVER 5 700 KG FOR WHICH APPLICATION FOR
CERTIFICATION WAS SUBMITTED ON OR AFTER 13 JUNE 1960
BUT BEFORE 2 MARCH 2004
Note.- The provisions of Part IIIA are the same as those contained in Part III of Annex 8, Ninth Edition (including
Amendment 99), except for modified applicability clauses and cross-references.
CHAPTER 1. GENERAL
1.1 Applicability 13 Operating limitations
1.1.1 The Standards of this part, except for those
specified in 8.4, are applicable in respect of all aeroplanes
designated in 1.1.3 that are of types of which the prototype
was submitted to the appropriate national authorities for certification
on or after 13 June 1960, but before 2 March 2004.
1.1.2 The Standards specified in 8.4 of this part are
applicable in respect of all aeroplanes designated in 1.1.3 that
are of types of which the prototype was submitted to the
appropriate national authorities for certification on or after
22 March 1985, but before 2 March 2004.
1.1.3 Except for those Standards and Recommended
Practices which specify a different applicability, the Standards
and Recommended Practices of this part shall apply to
aeroplanes of over 5 700 kg maximum certificated take-off
mass intended for the carriage of passengers or cargo or mail
in international air navigation.
Note.- The following Standards do not include quantitative
speczflcations comparable to those found in national
airworthiness codes. In accordance with 1.2.1 of Part II, these
Standarcis are to be supplemented by requirements established,
adopted or accepted by Contracting States.
1.1.4 The level of airworthiness defined by the appropriate
parts of the comprehensive and detailed national code
referred to in 1.2.1 of Part I1 for the aeroplanes designated in
1.1.3 shall be at least substantially equivalent to the overall
level intended by the broad Standards of this part.
1.3.1 Limiting conditions shall be established for the
aeroplane, its power-units and its equipment (see 9.2). Compliance
with the Standards of this part shall be established
assuming that the aeroplane is operated within the [imitations
specified. The limitations shall be sufficiently removed from
any condition(s) prejudicial to the safety of the aeroplane to
render the likelihood of accidents arising therefrom extremely
remote.
Note.- Guidance material concerning the expression
"extremely remote" is contained in the Airworthiness Manual
(Doc 9760).
1.3.2 Limiting ranges of any parameter whose variation
may compromise the safe operation of the aeroplane, e.g.
mass, centre of gravity location, load distribution, speeds, and
altitude or pressure-altitude, shall be established within which
compliance with all the pertinent Standards in this part is
shown, except that combinations of conditions which are
fundamentally impossible to achieve need not be considered.
Note I.- The maximum operating mass and centre of
gravity limits may vary, for example, with each altitude and
with each separate operating condition, e.g. take-oft; en route,
landing.
Note 2.- The following items, for instance, may be
considered as basic aeroplane limitations:
1.1.5 Unless otherwise stated, the Standards apply to the - maximum certificated take-of mass;
　
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