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selection
- Slats*: leading edge flap (slat) position, cockpit control
selection
- Landing gear*: landing gear, gear selector position
- Yaw trim surface position*
- Roll trim surface position*
- Cockpit trim control input position pitch*
- Cockpit trim control input position roll*
- Cockpit trim control input position yaw*
- Ground spoiler and speed brake*: Ground spoiler
position, ground spoiler selection, speed brake position,
speed brake selection
- De-icing andlor anti-icing systems selection*
- Hydraulic pressure (each system)*
- Fuel quantity*
- AC electrical bus status*
- DC electrical bus status*
- APU bleed valve position*
- Computed centre of gravity*
6.3.1.8.5 The following parameters satisfy the requirements
for operation:
- Warnings
- Primary flight control surface and primary flight control
pilot input: pitch axis, roll axis, yaw axis
- Marker beacon passage
- Each navigation receiver frequency selection
- Manual radio transmission keying and CVRIFDR
synchronization reference
- Autopilot/autothrottlelAFCS mode and engagement
status*
- Selected barometric setting*: pilot, first officer
- Selected altitude (all pilot selectable modes of operation)*
- Selected speed (all pilot selectable modes of operation)*
- Selected Mach (all pilot selectable modes of operation)*
- Selected vertical speed (all pilot selectable modes of
operation)*
- Selected heading (all pilot selectable modes of operation)*
- Selected flight path (all pilot selectable modes of
operation)*: courseIDSTRK, path angle
- Selected decision height*
- EFIS display format*: pilot, first officer
- Multi-function/enginelalerts display format*
- GPWSflAWSIGCAS status*: selection of terrain
display mode including pop-up display status, terrain
alerts, both cautions and warnings, and advisories,
odoff switch position
- Low pressure warning*: hydraulic pressure, pneumatic
pressure
- Computer failure*
- Loss of cabin pressure*
- TCASIACAS (traffic alert and collision avoidance
systemlairborne collision avoidance system)*
- Ice detection*
- Engine warning each engine vibration*
- Engine warning each engine over temperature*
- Engine warning each engine oil pressure low*
- Engine warning each engine over speed*
- Wind shear warning*
- Operational stall protection, stick shaker and pusher
activation*
- All cockpit flight control input forces*: control wheel,
control column, rudder pedal cockpit input forces
- Vertical deviation*: ILS glide path, MLS elevation,
GNSS approach path
- Horizontal deviation*: ILS localizer, MLS azimuth,
GNSS approach path
- DME 1 and 2 distances*
- Primary navigation system reference*: GNSS, INS,
VORIDME, MLS, Loran C, ILS
- Brakes*: left and right brake pressure, left and right
brake pedal position
- Date*
- Event marker*
- Head up display in use*
- Para visual display on*
Note I.- Parameter requirements, including range,
sampling, accuracy and resolution, as contained in the
Minimum Operational Performance Specijication (MOPS)
document for Flight Recorder Systems of the European
Organization for Civil Aviation Equipment (EUROCAE) or
equivalent documents.
Note 2.- The number of parameters to be recorded will
depend on aeroplane complexity. Parameters without an (*)
are to be recorded regardless of aeroplane complexity. Those
parameters designated by an (*) are to be recorded if an
information source for the parameter is used by aeroplane
systems a d o r flight crew to operate the aeroplane.
6.3.2 Flight data recorders - duration
All FDRs shall be capable of retaining the information
recorded during at least the last 25 hours of their operation,
except for the Type IIA FDR which shall be capable of
retaining the information recorded during at least the last 30
minutes of its operation.
6.3.3 Flight data recorders - aeroplanes for which
the individual certificate of airworthiness is first
issued on or after 1 January 1989
6.3.3.1 All aeroplanes of a maximum certificated take-off
mass of over 27 000 kg shall be equipped with a Type I FDR.
6.3.3.2 All aeroplanes of a maximum certificated take-off
mass of over 5 700 kg, up to and including 27 000 kg, shall be
equipped with a Type I1 FDR.
6.3.3.3 Recommendation.- All multi-engined turbinepowered
aeroplanes of a maximum certificated take-off mass
Chapter 6 Annex 6 - Operation of Aircraft
of 5 700 kg or less for which the individual certijicate of
airworthiness isfirst issued on or after I January 1990 should
　
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