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4.9.1.2 A Type V FDR shall record the parameters
required to determine accurately the helicopter flight path,
speed, attitude and engine power.
4.9.1.3 The use of engraving metal foil FDRs shall be
discontinued by 1 January 1995.
4.9.1.4 Recommendation.— The use of analogue FDRs
using frequency modulation (FM) should be discontinued by
5 November 1998.
4.9.1.4.1 The use of photographic film FDRs shall be
discontinued from 1 January 2003.
4.9.1.5 All helicopters for which the individual certificate
of airworthiness is first issued after 1 January 2005, which
utilize data link communications and are required to carry a
CVR, shall record on a flight recorder all data link
communications to and from the helicopter. The minimum
recording duration shall be equal to the duration of the CVR,
and shall be correlated to the recorded cockpit audio.
4.9.1.5.1 From 1 January 2007, all helicopters which
utilize data link communications and are required to carry a
CVR, shall record on a flight recorder, all data link
communications to and from the helicopter. The minimum
recording duration shall be equal to the duration of the CVR,
and shall be correlated to the recorded cockpit audio.
4.9.1.5.2 Sufficient information to derive the content of
the data link communications message, and, whenever
practical, the time the message was displayed to or generated
by the crew shall be recorded.
Note.— Data link communications include, but are not
limited to, automatic dependent surveillance (ADS),
controller-pilot data link communications (CPDLC), data linkflight
information services (D-FIS) and aeronautical
operational control (AOC) messages.
4.9.1.6 Recommendation.— All helicopters of a
maximum certificated take-off mass over 2 730 kg, required to
be equipped with an FDR and/or a CVR, may alternatively be
equipped with one combination recorder (FDR/CVR).
4.9.1.7 A Type IVA FDR shall record the parameters
required to determine accurately the helicopter flight path,
speed, attitude, engine power, configuration and operation.
The parameters that satisfy the requirements for a Type IVA
FDR are listed in the paragraphs below. The parameters
23/11/06
No. 11
Section III, Chapter 4 Annex 6 — Operation of Aircraft
III-4-5 1/11/01
without an asterisk (*) are mandatory parameters which shall
be recorded. In addition, the parameters designated by an
asterisk (*) shall be recorded if an information data source for
the parameter is used by helicopter systems or the flight crew
to operate the helicopter.
4.9.1.7.1 The following parameters satisfy the requirements
for flight path and speed:
– Pressure altitude
– Indicated airspeed
– Outside air temperature
– Heading
– Normal acceleration
– Lateral acceleration
– Longitudinal acceleration (body axis)
– Time or relative time count
– Navigation data*: drift angle, wind speed, wind direction,
latitude/longitude
– Radio altitude*
4.9.1.7.2 The following parameters satisfy the requirements
for attitude:
– Pitch attitude
– Roll attitude
– Yaw rate
4.9.1.7.3 The following parameters satisfy the requirements
for engine power:
– Power on each engine: free power turbine speed (Nf),
engine torque, engine gas generator speed (Ng), cockpit
power control position
– Rotor: main rotor speed, rotor brake
– Main gearbox oil pressure*
– Gearbox oil temperature*: main gearbox oil temperature,
intermediate gearbox oil temperature, tail rotor gearbox
oil temperature
– Engine exhaust gas temperature (T4)*
– Turbine inlet temperature (TIT)*
4.9.1.7.4 The following parameters satisfy the requirements
for configuration:
– Landing gear or gear selector position*
– Fuel contents*
– Ice detector liquid water content*
4.9.1.7.5 The following parameters satisfy the requirements
for operation:
– Hydraulics low pressure
– Warnings
– Primary Flight Controls — Pilot input and/or control
output position: collective pitch, longitudinal cyclic
pitch, lateral cyclic pitch, tail rotor pedal, controllable
stabilator, hydraulic selection
– Marker beacon passage
– Each navigation receiver frequency selection
– AFCS mode and engagement status*
– Stability augmentation system engagement*
– Indicated sling load force*
– Vertical deviation*: ILS glide path, MLS elevation,
　
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