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it will not Ieod to serious injury or loss of life, wen though the
aeroplane may incur extensive damage.
Note 2.- Operation over routes and in weather conditwns
that permit a safe forced landing in the went of an engine
failure, as specified in Chapter 5, 5.1.2, is not required by
Appendix 3, 6.1 and 6.2 for aeroplanes approved in accordance
with Chapter 5, 5.4. The availability of forced landing
areas at all points along a route is not specified for these
aerophnes because of the very high engine reliability, d i -
tional systems and operational equipment, procedures and
training requirements specified in this Appendix.
7. Fllght crew experience, training and checking
7.1 The State of the Operator shall prescribe the
minimum flight crew experience required for nightmMC
operations by single-engine turbinepowered aeroplanes.
7.2 An operator's flight crew training and checking shall
be appropriate to night andlor IMC operations by singleengine
turbine-powered aeroplanes, covering nonnal,
abnormal and emergency procedures and, in particular, engine
failure, including descent to a forced landing in night andm in
IMC conditions.
8. Route limitatbus over water
The State of the Operator shall apply route limitation aikria
for single-engine turbine-powered aeroplanes operating at
night andor in IMC on over water operations if beyond
gliding distance from an area suitable for a safe forced
landinglditching having regard to the characteristics of the
aeroplane, seasonal weather influences, including likely sea
state and temperature, and the availability of search and rescue
services.
24111m
No. 29
APP 5 2
Annex 6 - Operation of Aircraft
9. Operator certification or validation
The operator shall demonstrate the ability to conduct
operations by single-engine turbine-powered aeroplanes at
night and/or in MC through a certification and approval
process specified by the State of the Operator.
Note.- Guidance on the airworthiness and operational
requirements is contained in Attachment I.
APP 3-3 24/11/05
No. 29
APPENDIX 4. ALTIMETRY SYSTEM PERFORMANCE REQUIREMENTS
FOR OPERATIONS IN RVSM AIRSPACE
(Note.- See Chapter 7, 7.2.5)
1. In respect of groups of aeroplanes that are nominally of
identical design and build with respect to all details that could
influence the accuracy of height-keeping performance, the
height-keeping performance capability shall be such that the
total vertical error (TVE) for the group of aeroplanes shall
have a mean no greater than 25 m (80 ft) in magnitude and
shall have a standard deviation no greater than 28 - 0.013z2
for 0 s z s 25 when z is the magnitude of the mean TVE in
metres, or 92 - 0.0042 for 0 s z s 80 where z is in feet. In
addition, the components of TVE shall have the following
characteristics:
about a mean of 0 m, with a standard deviation no
greater than 13.3 m (43.7 ft), and in addition, the
decrease in the frequency of differences with increasing
difference magnitude shall be at least exponential.
2. In respect of aeroplanes for which the characteristics of
the airframe and altimezry system fit are unique and so cannot
be classified as belonging to a group of aeroplanes
encompassed by paragraph 1, the height-keeping performance
capability shall be such that the components of the 'I'VE of the
aeroplane have the following characteristics:
a) the mean altimetry system error (ASE) of the group a) the ASE of the aeroplane shall not exceed 60 m (200 ft)
shall not exceed 25 m (80 ft) in magnitude; in magnitude under all flight conditions; and
b) the sum of the absolute value of the mean ASE and of b) the differences between the cleared flight level and the
three standard deviations of ASE shall not exceed 75 m indicated pressure altitude actually flown shall be sym-
(245 ft); and metric about a mean of 0 m, with a standard deviation
no greater 'than 13.3 m (43.7 ft), and in addition, the
C) the differences between cleared flight level and the indi- decrease in the frequency of mfferences with increasing
cated pressure altitude actually flown shall be symmetric difference magnitude shall be at least exponential.
ANNEX 6 - PART I APP 4-1 24111J05
No. 29
ATTACHMENT H. FLIGHT SAFETY DOCUMENTS SYSTEM
Supplementary to Chapter 3, 3.3
1. Introduction
1.1 The following material provides guidance on the
organization and development of an operator's flight safety
documents system. It should be understood that the
development of a flight safety documents system is a complete
process, and changes to each document comprising the system
may affect the entire system. Guidelines applicable to the
　
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