AMC3 CAT.IDE.H.190 Flight data recorder    

CAA ORS9 Decision No. 1

PERFORMANCE SPECIFICATIONS FOR THE PARAMETERS TO BE RECORDED FOR HELICOPTERS HAVING AN MCTOM OF MORE THAN 3 175 KG AND FIRST ISSUED WITH AN INDIVIDUAL COFA ON OR AFTER 1 AUGUST 1999 AND BEFORE 1 JANUARY 2016 AND HELICOPTERS HAVING AN MCTOM OF MORE THAN 7 000 KG OR AN MOPSC OF MORE THAN 9 AND FIRST ISSUED WITH AN INDIVIDUAL COFA ON OR AFTER 1 JANUARY 1989 AND BEFORE 1 AUGUST 1999

 

Table 1

Helicopters with an MCTOM of 7 000 kg or less

No

Parameter

Range

Sampling interval in seconds

Accuracy Limits (sensor input compared to FDR read out)

Minimum Resolution in read out

Remarks

1

Time or relative time count

 

 

 

 

 

1a or

Time

24 hours

4

± 0.125 % per hour

1 second

(a) UTC time preferred where available.

1b

Relative Time Count

0 to 4 095

4

± 0.125 % per hour

 

(b) Counter increments every 4 seconds of system operation.

2

Pressure altitude

-1 000 ft to 20 000 ft

1

±100 ft to ±700 ft Refer to table II.A-2 of EUROCAE Document ED-112

25 ft

 

3

Indicated airspeed or calibrated airspeed

As the installed measuring system

1

± 5 % or ± 10 kt, whichever is greater

1 kt

 

4

Heading

360 °

1

± 5°

1°

 

5

Normal acceleration

- 3 g to + 6 g

0.125

± 0.2 g in addition to a maximum offset of ± 0.3 g

0.01 g

The resolution may be rounded from 0.01 g to 0.05 g, provided that one sample is recorded at full resolution at least every 4 seconds.

6

Pitch attitude

100 % of usable range

0.5

± 2 degrees

0.8 degree

 

7

Roll attitude

± 60 ° or 100 % of usable range from installed system if greater

0.5

± 2 degrees

0.8 degree

.

8

Manual radio transmission keying

Discrete(s)

1

-

-

Preferably each crew member but one discrete acceptable for all transmissions.

9

Power on each engine

Full range

Each engine each second

± 5 %

1 % of full range

Sufficient parameters, e.g. Power Turbine Speed and Engine Torque should be recorded to enable engine power to be determined. A margin for possible overspeed should be provided. Data may be obtained from cockpit indicators used for aircraft certification. Parameter 9c is required for helicopters with non-mechanically linked cockpit-engine controls 

9a

Power turbine speed

Maximum range

9b

Engine torque

Maximum range

9c

Cockpit power control position

Full range or each discrete position

Each control each second

±2 % or sufficient to determine any gated position

2 % of full range

10

Rotor

 

 

 

 

 

10a

Main rotor speed

Maximum range

1

± 5 %

1 % of full range

 

10b

Rotor brake

Discrete

1

-

 

Where available

11

Primary flight controls - Pilot input and/or* control output position

 

 

 

 

* For helicopters that can demonstrate the capability of deriving either the control input or control movement (one from the other) for all modes of operation and flight regimes, the ‘or’ applies. For helicopters with non- mechanical control systems the ‘and’ applies. Where the input controls for each pilot can be operated independently, both inputs will need to be recorded. 

11a

Collective pitch

Full range

0.5

± 3 %

1 % of full range

11b

Longitudinal cyclic pitch

0.5

11c

Lateral cyclic pitch

0.5

11d

Tail rotor pedal

0.5

11e

Controllable stabiliser

0.5

11f

Hydraulic selection

Discretes

1

-

-

12

Outside air temperature

Available range from installed system

2

± 2 °C

0.3°C

 

13

Autopilot engagement status

Discrete(s)

1

 

 

Where practicable, discretes should show which primary modes are controlling the flight path of the helicopter

14

Stability augmentation system engagement

Discrete(s)

1

 

 

 

15

Warnings

Discrete(s)

1

-

-

A discrete should be recorded for the master warning, low hydraulic pressure (each system) gearbox low oil pressure and SAS fault status. Other ‘red’ warnings should be recorded where the warning condition cannot be determined from other parameters or from the cockpit voice recorder.

 

Table 2

Helicopters with an MCTOM of more than 7 000 kg

No

Parameter

Range

Sampling interval in seconds

Accuracy Limits (sensor input compared to FDR read out)

Minimum Resolution in read out

Remarks

1

Time or relative time count

 

 

 

 

 

1a or

Time

24 hours

4

± 0.125 % per hour

1 second

(a) UTC time preferred where available.

1b

Relative time count

0 to 4095

4

± 0.125 % per hour

 

(b) Counter increments every 4 seconds of system operation.

2

Pressure altitude

-1 000 ft to maximum certificated altitude of

1

± 100 ft to ± 700 ft Refer to table II-A.3

5 ft

Should be obtained from the air data computer when installed.

aircraft +5 000 ft

EUROCAE Document ED-112

3

Indicated airspeed or calibrated airspeed

As the installed measuring system

1

± 3 %

1 kt

Should be obtained from the air data computer when installed.

4

Heading

360 degrees

1

± 2 degrees

0.5 degree

 

5 

Normal acceleration 

-3 g to +6 g 

0.125 

1 % of range excluding a datum error of 5 % 

0.004 g 

The recording resolution may be rounded from 0.004 g to 0.01 g provided that one sample is recorded at full resolution at least every 4 seconds.

6

Pitch attitude

± 75 degrees

0.5

± 2 degrees

0.5 degree

 

7

Roll attitude

± 180 degrees

0.5

± 2 degrees

0.5 degree

.

8

Manual radio transmission Keying and CVR/FDR synchronisation reference

Discrete(s)

1

-

-

Preferably each crew member but one discrete acceptable for all transmissions provided that the replay of a recording made by any required recorder can be synchronised in time with any other required recording to within 1 second.

9

Power on each engine

Full range

Each engine each second

± 2 %

0.2 % of full range

Sufficient parameters e.g. Power Turbine Speed and engine torque should be recorded to enable engine power to be determined. A margin for possible overspeed should be provided. 

9a

Free power turbine speed(NF)

0-130 %

9b

Engine torque

Full range

9c

Cockpit power control position

Full range or each discrete position

Each control each second

± 2 % or sufficient to determine any gated position

2 % of full range

Parameter 9c is required for helicopters with non-mechanically linked cockpit-engine controls

10

10a

Rotor

Main rotor speed

50 to 130 %

0.5

2%

0.3 % of full range

.

10b

Rotor brake

Discrete

1

 

 

Where available

11

Primary flight controls - Pilot input and/or* control output position

 

 

 

 

* For helicopters that can demonstrate the capability of deriving either the control input or control movement (one from the other) for all modes of operation and flight regimes, the ‘or’ applies. For helicopters with non- mechanical control systems, the ‘and’ applies.

Where the input controls for each pilot can be operated independently, both inputs will need to be recorded.

11a

Collective pitch

Full range

0.5

± 3 % unless higher accuracy is uniquely required

0.5 % of operating range

11b

Longitudinal cyclic pitch

0.5

11c

Lateral cyclic pitch

0.5

11d

Tail rotor pedal

0.5

11e

Controllable stabiliser

 

0.5

 

 

11f

Hydraulic selection

Discrete(s)

1

-

-

12

Hydraulics low pressure

Discrete(s)

1

-

-

Each essential system should be recorded.

13

Outside air temperature

-50° to +90°C or available sensor range

2

± 2°C

0.3°C

 

14

AFCS mode and engagement status

A suitable combination of discretes

1

-

-

Discretes should show which systems are engaged and which primary modes are controlling the flight path of the helicopter.

15

Stability augmentation system engagement

Discrete

1

-

-

 

16

Main gearbox oil pressure

As installed

1

As installed

6.895 kN/m² (1 psi)

 

17

Main gearbox oil temperature

As installed

2

As installed

1°C

 

18

Yaw rate

± 400 degrees/second

0.25

± 1 %

2 degrees per second

An equivalent yaw acceleration is an acceptable alternative.

19

Indicated sling load force

0 to 200 % of maximum certified load

0.5

± 3 % of maximum certified load

0.5 % for maximum certified load

With reasonable practicability if sling load indicator is installed.

20

Longitudinal acceleration (body axis)

± 1 g

0.25

±1.5 % of range excluding a datum error of ±5 %

0.004 g

See comment to parameter 5.

21

Lateral acceleration

± 1 g

0.25

±1.5 % of range excluding a datum error of ±5 %

0.004 g

See comment to parameter 5.

22

Radio altitude

-20 ft to +2 500 ft

1

As installed. ± 2 ft or ± 3 % whichever is greater below 500 ft and ± 5 % above 500 ft recommended  

1 ft below 500 ft, 1 ft + 0.5 % of full range above 500 ft

 

23

Vertical beam deviation

 

1

As installed ± 3 % recommended

0.3 % of full range

Data from both the ILS and MLS systems need not to be recorded at the same time. The approach aid in use should be recorded.

23a

ILS glide path

± 0.22 DDM or available sensor range as installed

 

 

 

 

23b

MLS elevation

+0.9 to +30 degrees

 

 

 

 

24

Horizontal beam deviation

 

1

As installed. ± 3 % recommended

0.3 % of full range

See comment to parameter 23

24a

ILS localiser

± 0.22 DDM or available sensor range as installed

 

 

 

 

24b

MLS azimuth

± 62 degrees

 

 

 

 

25

Marker beacon passage

Discrete

1

-

-

One discrete is acceptable for all markers.

26

Warnings

Discretes

1

-

-

A discrete should be recorded for the master warning, gearbox low oil pressure and SAS failure. Other ‘red’ warnings should be recorded where the warning condition cannot be determined from other parameters or from the cockpit voice recorder.

27

Reserved

 

 

 

 

 

28

Reserved

 

 

 

 

 

29

Reserved

 

 

 

 

 

30

Landing gear or gear selector position

Discrete(s)

4

-

-

Where installed.

 

Table 3

Helicopters equipped with electronic display systems

No

Parameter

Range

Sampling interval in seconds

Accuracy Limits (sensor input compared to FDR read out)

Minimum Resolution in read out

 Remarks

38

Selected barometric setting (each pilot station)

As installed

64

As installed

1 mb

Where practicable, a sampling interval of 4 seconds is recommended.

38a

Pilot

 

 

 

 

 

38b

Co-pilot

 

 

 

 

 

39

Selected altitude

As installed

1

As installed

100 ft

Where capacity is limited, a sampling interval of 64 seconds is permissible.

39a

Manual

 

 

 

 

 

39b

Automatic

 

 

 

 

 

40

Selected speed

As installed

1

As installed

1 kt

Where capacity is limited, a sampling interval of 64 seconds is permissible.

40a

Manual

 

 

 

 

 

40b

Automatic

 

 

 

 

 

41

Selected Mach

As installed

1

As installed

0.01

Where capacity is limited, a sampling interval of 64 seconds is permissible.

41a

Manual

 

 

 

 

 

41b

Automatic

 

 

 

 

 

42

Selected vertical speed

As installed

1

As installed

100 ft/min

Where capacity is limited, a sampling interval of 64 seconds is permissible.

42a

Manual

 

 

 

 

 

42b

Automatic

 

 

 

 

 

43

Selected heading

360 degrees

1

As installed

100 ft /min

Where capacity is limited, a sampling interval of 64 seconds is permissible.

44

Selected flight path

 

1

As installed

 

 

44a

Course/DSTRK

 

 

 

1 degree

 

44b

Path angle

 

 

 

0.1 degree

 

 

The term ‘where practicable’ used in the remarks column of Table 3 means that account should be taken of the following:

(a) if the sensor is already available or can be easily incorporated;

(b) sufficient capacity is available in the flight recorder system;

(c) for navigational data (nav frequency selection, DME distance, latitude, longitude, groundspeed and drift) the signals are available in digital form;

(d) the extent of modification required;

(e) the down-time period; and

(f) equipment software development.