Part VI - General Operating and Flight Rules

Canadian Aviation Regulations (CARs) 2017-2

Standard 625 Schedule 3 - Aeroplane Digital Flight Data Recorder (DFDR) Specifications

Content last revised: 2009/12/01

(Ref. CAR 605.33)
(amended 2009/12/01)

Parameters Range Accuracy sensor input to DFDR read-out Sampling interval (in seconds) Resolution read-out
4
Time (GMT or Frame Counter) (range 0 to 4095, sampled 1 per frame) 24 hrs ±0.125% per hour 0.25 (1 per 4 seconds) 1 sec.
Altitude -1,000 ft. to maximum certificated altitude of aircraft ±100 ft. to ±700 ft. (See table 1 in CAN-TSO-C51a)
1 5 ft. to 35 ft. 1
Airspeed 50 KIAS to VSO and VSO to 1.2 VD ±5%, ±3% 1 1kt
Heading 360° ±2° 1 0.5°
Normal (vertical) acceleration -3g to +6g ±1% of max range excluding datum error of ±5% 8 0.01g
Pitch attitude ±75° ±2° 1 0.5°
Roll attitude ±180° ±2° 1 0.5°
Radio transmitter keying On/off (discrete)   1  
Thrust/power on each engine Full range forward ±2% 1 (per engine) 0.2% 2
Trailing edge flap or cockpit control selection Full range or each discrete position ±3° or as pilot's indicator 0.5 0.5% 2
Leading edge flap on or cockpit control selection Full range or each discrete position ±3° or as pilot's indicator 0.5 0.5% 2
Thrust reverser position Stowed, in transit, and reverse (discrete)   1 (per 4 seconds per engine)  
Ground spoiler position/speed brake selection Full range or each discrete position ±2% unless higher accuracy required 1 0.2% 2
  Marker beacon passage   1  
Autopilot engagement discrete   1  
Longitudinal acceleration ±1g ±1.5% max. range excluding datum error of ±5% 4 0.01g
Pilot input and/or surface position-primary controls (Pitch, Roll, Yaw) 3 Full range ±2° unless higher accuracy uniquely required 1 0.2% 2
Lateral acceleration ±1g ±1.5% max. range excluding datum error of ±5% 4 0.01g
Pitch trim position Full range ±3% unless higher accuracy uniquely required 1 0.3% 2
Glideslope deviation ±400 Microamps ±3% 1 0.3% 2
Localizer deviation ±400 Microamps ±3% 1 0.3% 2
AFCS mode and engagement status discrete   1  
Radio altitude -20 ft. to 2,500 ft. ±2 ft. or ±3% whichever is greater below 500 ft. and ±5% above 500 ft 1 1 ft. + 5% above 500 ft.
2
Master warning discrete   1  
Main gear squat switch status discrete   1  
Angle of attack (if recorded directly) As installed As installed 1 0.3% 2
Outside air temperature or total air temperature -50°C to +90°C ±2°C 1 0.3°C
Hydraulics, each system low pressure discrete   0.5 0.5% 2
Groundspeed As installed Most accurate system installed (IMS equipped a/c only) 1 0.2% 2
If additional recording capacity is available, recording of the following parameters is recommended. The parameters are listed in order of significance:
Drift Angle When available. As installed. As installed 4  
Wind Speed and Direction When available. As installed. As installed 4  
Latitude and Longitude When available. As installed. As installed 4  
Brake pressure/Brake pedal position As installed As installed 1  

Additional engine parameters

Parameters Range Accuracy sensor input to DFDR read-out Sampling interval (in seconds) Resolution read-out
4
EPR

N1

N2 EGT
As installed

As installed

As installed
As installed

As installed

As installed
1 (per engine)

1 (per engine)

1 (per engine)
 
EGT As installed As installed 1 (per engine)  
Throttle Lever Position As installed As installed 1 (per engine)  
Fuel Flow As installed As installed 1 (per engine)  

TCAS

Parameters Range Accuracy sensor input to DFDR read-out Sampling interval (in seconds) Resolution read-out
4
TA

RA

Sensitivity level (as selected by crew)
As installed

As installed

As installed
As installed

As installed

As installed
1

1

2
 
GPWS (ground proximity warning system). Discrete   1  
Landing gear or gear selector position Discrete   0.25 (1 per 4 seconds)  
DME 1 and 2 Distance 0 - 200 NM As installed 0.25 1 mile
Nav 1 and 2 Frequency Selection Full range As installed 0.25  

Notes for Schedule 3

1 When altitude rate is recorded. Altitude rate must have sufficient resolution and sampling to permit the derivation of altitude to 5 feet.

2 Percent of full range.

3 For airplanes that can demonstrate the capability of deriving either the control input on control movement (one from the other) for all modes of operation and flight regimes, the “or” applies. For aeroplanes with non-mechanical control systems (fly-by-wire) the “and” applies. In aeroplanes with split surfaces, suitable combination of inputs is acceptable in lieu of recording each surface separately.

4 This column applies to aeroplanes manufactured after October 11, 1991.

Date modified: