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The design of the aeroplane shall take into consideration the
flight crew operating environment including:
a) effect of aeromedical factors such as level of oxygen,
temperature, humidity, noise and vibration;
b) effect of physical forces during normal flight;
c) effect of prolonged operation at high altitude; and
d) physical comfort.
ANNEX 8
SUB-PART K. SECURITY
K.1 Aeroplanes used for domestic
commercial operations
Recommendation.- International Standards and Recommended
Practices set forth in this chapter should be
applied by all Contracting States for aeroplanes engaged in
domestic commercial operations (air services).
K.2 Least-risk bomb location
For aeroplanes of a maximum certificated take-off mass in
excess of 45 500 kg or with a passenger seating capacity
greater than 60, consideration shall be given during the design
of the aeroplane to the provision of a least-risk bomb location
so as to minimize the effects of a bomb on the aeroplane and
its occupants.
penetration by small arms fire and grenade shrapnel and to
resist forcible intrusions, if these areas are accessible in flight
to passengers and cabin crew.
K.3.2 Recommendation.- In all aeroplanes, which are
required by Annex 6, Part I, Chapter 13 to have an approved
flight crew compartment door; and for which an application
for amending the Type Certificate to include a derivative type
design is submitted to the appropriate national authority on or
after 20 May 2006, consideration should be given to
reinforcing the flight crew compartment bulkheads, floors and
ceilings so as to resist penetration by small arms fire and
grenade shrapnel and to resist forcible intrusions, if these
areas are accessible in flight to passengers and cabin crew.
Note.- Standards and Recommended Practices concerning
the requirements for the flight crew compartment door in all
commercial passenger-carrying aeroplanes are contained in
Annex 6, Pari I, Chapter 13.
K.3 Protection of the flight crew compartment K.4 Interior design
K.3.1 In all aeroplanes, which are required by Annex 6, For aeroplanes of a maximum certificated take-off mass in
Part I, Chapter 13 to have an approved flight crew compart- excess of 45 500 kg or with a passenger seating capacity
ment door, and for which an application for the issue of a Type greater than 60, consideration shall be given to design features
Certificate is first submitted to the appropriate national that will deter the easy concealment of weapons, explosives or
authority on or after 20 May 2006, the flight crew compart- other dangerous objects on board aircraft and that will
ment bulkheads, floors and ceilings shall be designed to resist facilitate search procedures for such objects.
ANNEX 8
PART IV. HELICOPTERS
PART IVA. HELICOPTERS FOR WHICH APPLICATION FOR CERTIFICATION
WAS SUBMITTED ON OR AFTER 22 MARCH 1991 BUT BEFORE
13 DECEMBER 2007
Note.- The provisions of Part NA are the same as those contained in Part N of Annex 8, Ninth Edition except for modified
applicability clauses and cross references.
CHAPTER 1. GENERAL
1.1 Applicability
1.1.1 The Standards of this part are applicable in respect
of all helicopters designated in 1.1.2 that are of types of which
the prototype was submitted to the appropriate national authorities
for certification on or after 22 March 1991 but before
13 December 2007.
1.1.2 The Standards of this part shall apply to helicopters
intended for the carriage of passengers or cargo or mail in
international air navigation.
Note.- The following Standards do not include quantitative
specifications comparable to those found in national
airworthiness codes. In accordance with 1.2.1 of Part 11, these
Standards are to be supplemented by requirements established,
adopted or accepted by Contracting States.
1.1.3 The level of airworthiness defined by the appropriate
parts of the comprehensive and detailed national code referred
to in 1.2.1 of Part 11 for the helicopters designated in 1.1.2
shall be at least substantially equivalent to the overall level
intended by the broad Standards of this part.
1.1.4 Unless otherwise stated, the Standards apply to the
complete helicopter including power-units, systems and
equipment.
1.2 Limitations
1.2.1 Limiting conditions shall be established for the
helicopter, its power-units and its equipment (see 9.2).
Compliance with the Standards of this Part shall be established
assuming that the helicopter is operated within the limitations
specified. The limitations shall be sufficiently removed from
any conditions prejudicial to the safety of the helicopter to
　
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