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| Contents | Quantity |
|---|---|
| Adhesive bandage compresses, 1-inch | 16 |
| Antiseptic swabs | 20 |
| Ammonia inhalants | 10 |
| Bandage compresses, 4-inch | 8 |
| Triangular bandage compresses, 40-inch | 5 |
| Arm splint, noninflatable | 1 |
| Leg splint, noninflatable | 1 |
| Roller bandage, 4-inch | 4 |
| Adhesive tape, 1-inch standard roll | 2 |
| Bandage scissors | 1 |
| Protective nonpermeable gloves or equivalent | 1 pair |
| Total seating capacity | Minimum main passenger aisle width | |
|---|---|---|
| Less than 25 inches from floor | 25 inches and more from floor | |
| 10 through 23 | 9 inches | 15 inches. |
| Parameters | Range | Installed system 1 minimum accuracy (to recovered data) | Sampling interval (per second) | Resolution 4 read out |
|---|---|---|---|---|
| Relative time (from recorded on prior to takeoff) | 25 hr minimum | ±0.125% per hour | 1 | 1 sec. |
| Indicated airspeed | V so to V D (KIAS) | ±5% or ±10 kts., whichever is greater. Resolution 2 kts. below 175 KIAS | 1 | 1% 3 . |
| Altitude | −1,000 ft. to max cert. alt. of A/C | ±100 to ±700 ft. (see Table 1, TSO C51-a) | 1 | 25 to 150 |
| Magnetic heading | 360° | ±5° | 1 | 1° |
| Vertical acceleration | −3g to + 6g | ±0.2g in addition to ±0.3g maximum datum | 4 (or 1 per second where peaks, ref. to 1g are recorded) | 0.03g. |
| Longitudinal acceleration | ±1.0g | ±1.5% max. range excluding datum error of ±5% | 2 | 0.01g. |
| Pitch attitude | 100% of usable | ±2° | 1 | 0.8° |
| Roll attitude | ±60° or 100% of usable range, whichever is greater | ±2° | 1 | 0.8° |
| Stabilizer trim position | Full range | ±3% unless higher uniquely required | 1 | 1% 3 . |
| Or | ||||
| Pitch control position | Full range | ±3% unless higher uniquely required | 1 | 1% 3 . |
| Engine Power, Each Engine | ||||
| Fan or N 1 speed or EPR or cockpit indications used for aircraft certification | Maximum range | ±5% | 1 | 1% 3 . |
| Or | ||||
| Prop. speed and torque (sample once/sec as close together as practicable) | 1 (prop speed), 1 (torque) | |||
| Altitude rate 2 (need depends on altitude resolution) | ±8,000 fpm | ±10%. Resolution 250 fpm below 12,000 ft. indicated | 1 | 250 fpm Below 12,000 |
| Angle of attack 2 (need depends on altitude resolution) | −20° to 40° or of usable range | ±2° | 1 | 0.8% 3 |
| Radio transmitter keying (discrete) | On/off | 1 | ||
| TE flaps (discrete or analog) | Each discrete position (U, D, T/O, AAP) | 1 | ||
| Or | ||||
| Analog 0-100% range | ±3° | 1 | 1% 3 | |
| LE flaps (discrete or analog) | Each discrete position (U, D, T/O, AAP) | 1 | ||
| Or | ||||
| Analog 0-100% range | ±3° | 1 | 1% 3 . | |
| Thrust reverser, each engine (Discrete) | Stowed or full reverse | 1 | ||
| Spoiler/speedbrake (discrete) | Stowed or out | 1 | ||
| Autopilot engaged (discrete) | Engaged or disengaged | 1 | ||
| 1 When data sources are aircraft instruments (except altimeters) of acceptable quality to fly the aircraft the recording system excluding these sensors (but including all other characteristics of the recording system) shall contribute no more than half of the values in this column. | ||||
| 2 If data from the altitude encoding altimeter (100 ft. resolution) is used, then either one of these parameters should also be recorded. If however, altitude is recorded at a minimum resolution of 25 feet, then these two parameters can be omitted. | ||||
| 3 Per cent of full range. | ||||
| 4 This column applies to aircraft manufacturing after October 11, 1991. | ||||
| Parameters | Range | Installed system 1 minimum accuracy (to recovered data) | Sampling interval (per second) | Resolution 3 read out |
|---|---|---|---|---|
| Relative time (from recorded on prior to takeoff) | 25 hr minimum | ±0.125% per hour | 1 | 1 sec. |
| Indicated airspeed | V m in to V D (KIAS) (minimum airspeed signal attainable with installed pilot-static system) | ±5% or ±10 kts., whichever is greater | 1 | 1 kt. |
Code of Federal Regulations /
Title 14 - Aeronautics and Space /
Vol. 3 / 2024-01-01538 | ||||
| Altitude | −1,000 ft. to 20,000 ft. pressure altitude | ±100 to ±700 ft. (see Table 1, TSO C51-a) | 1 | 25 to 150 ft. |
| Magnetic heading | 360° | ±5° | 1 | 1°. |
| Vertical acceleration | −3g to + 6g | ±0.2g in addition to ±0.3g maximum datum | 4 (or 1 per second where peaks, ref. to 1g are recorded) | 0.05g. |
| Longitudinal acceleration | ±1.0g | ±1.5% max. range excluding datum error of ±5% | 2 | 0.03g. |
| Pitch attitude | 100% of usable range | ±2° | 1 | 0.8°. |
| Roll attitude | ±60° or 100% of usable range, whichever is greater | ±2° | 1 | 0.8°. |
| Altitude rate | ±8,000 fpm | ±10% Resolution 250 fpm below 12,000 ft. indicated | 1 | 250 fpm below 12,000. |
| Engine Power, Each Engine | ||||
| Main rotor speed | Maximum range | ±5% | 1 | 1% 2 |
| Free or power turbine | Maximum range | + 5% | 1 | 1% 2 |
| Engine torque | Maximum range | ±5% | 1 | 1% 2 |
| Flight Control—Hydraulic Pressure | ||||
| Primary (discrete) | High/low | 1 | ||
| Secondary—if applicable (discrete) | High/low | 1 | ||
| Radio transmitter keying (discrete) | On/off | 1 | ||
| Autopilot engaged (discrete) | Engaged or disengaged | 1 | ||
| SAS status—engaged (discrete) | Engaged/disengaged | 1 | ||
| SAS fault status (discrete) | Fault/OK | 1 | ||
| Flight Controls | ||||
| Collective 4 | Full range | ±3% | 2 | 1% 2 |
| Pedal Position 4 | Full range | ±3% | 2 | 1% 2 |
| Lat. Cyclic 4 | Full range | ±3% | 2 | 1% 2 |
| Long. Cyclic 4 | Full range | ±3% | 2 | 1% 2 |
| Controllable Stabilator Position 4 | Full range | ±3% | 2 | 1% 2 |
| 1 When data sources are aircraft instruments (except altimeters) of acceptable quality to fly the aircraft the recording system excluding these sensors (but including all other characteristics of the recording system) shall contribute no more than half of the values in this column. | ||||
| 2 Per cent of full range. | ||||
| 3 This column applies to aircraft manufactured after October 11, 1991. | ||||
| 4 For all aircraft manufactured on or after December 6, 2010, the sampling interval per second is 4. | ||||
| Parameters | Range | Accuracy sensor input to DFDR readout | Sampling interval (per second) | resolution 4 read out |
|---|---|---|---|---|
| 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 max certificated altitude of aircraft | ±100 to ±700 ft (See Table 1, TSO-C51a) | 1 | 5′ to 35′ 1 . |
| Airspeed | 50 KIAS to V so , and V so to 1.2 V D | ±5%, ±3% | 1 | 1kt |
| Heading | 360° | ±2° | 1 | 0.5° |
| Normal Acceleration (Vertical) | −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°. |
Code of Federal Regulations /
Title 14 - Aeronautics and Space /
Vol. 3 / 2024-01-01539 | ||||
| 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 (discretion) | 1 (per 4 seconds per engine) | ||
| Ground Spoiler Position/Speed Brake Selection | Full range or each discrete position | ±2% unless higher accuracy uniquely required | 1 | 0.22 2 . |
| Marker Beacon Passage | Discrete | 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% 2 above 500′. |
| Master Warning | Discrete | 1 | ||
| Main Gear Squat Switch Status | Discrete | 1 | ||
| Angle of Attack (if recorded directly) | As installed | As installed | 2 | 0.3% 2 . |
| Outside Air Temperature or Total Air Temperature | −50 °C to + 90 °C | ±2° c | 0.5 | 0.3° c |
| Hydraulics, Each System Low Pressure | Discrete | 0.5 | or 0.5% 2 . | |
| Groundspeed | As installed | Most accurate systems installed (IMS equipped aircraft 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: | ||||
| EPR | As installed | As installed | 1 (per engine) | |
| N 1 | As installed | As installed | 1 (per engine) | |
| N 2 | As installed | As installed | 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: | ||||
| TA | As installed | As installed | 1 | |
| RA | As installed | As installed | 1 | |
| Sensitivity level (as selected by crew) | As installed | As installed | 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 | 1mi. |
| Nav 1 and 2 Frequency Selection | Full range | As installed | 0.25 | |
Code of Federal Regulations /
Title 14 - Aeronautics and Space /
Vol. 3 / 2024-01-01540 | ||||
| 1 When altitude rate is recorded. Altitude rate must have sufficient resolution and sampling to permit the derivation of altitude to 5 feet. | ||||
| 2 Per cent 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 airplanes with non-mechanical control systems (fly-by-wire) the “and” applies. In airplanes with split surfaces, suitable combination of inputs is acceptable in lieu of recording each surface separately. | ||||
| 4 This column applies to aircraft manufactured after October 11, 1991. | ||||
| Parameters | Range | Accuracy sensor input to DFDR readout | Sampling interval (per second) | Resolution 2 read out |
|---|---|---|---|---|
| Time (GMT) | 24 Hrs | ±0.125% Per Hour | 0.25 (1 per 4 seconds) | 1 sec |
| Altitude | −1,000 ft to max certificated altitude of aircraft | ±100 to ±700 ft (See Table 1, TSO-C51a) | 1 | 5′ to 30′. |
| Airspeed | As the installed measuring system | ±3% | 1 | 1 kt |
| Heading | 360° | ±2° | 1 | 0.5°. |
| Normal Acceleration (Vertical) | −3g to + 6g | ±1% of max range excluding datum error of ±5% | 8 | 0.01g |
| Pitch Attitude | ±75° | ±2° | 2 | 0.5° |
| Roll Attitude | ±180° | ±2° | 2 | 0.5°. |
| Radio Transmitter Keying | On-Off (Discrete) | 1 | 0.25 sec | |
| Power in Each Engine: Free Power Turbine Speed and Engine Torque | 0-130% (power Turbine Speed) Full range (Torque) | ±2% | 1 speed 1 torque (per engine) | 0.2% 1 to 0.4% 1 |
| Main Rotor Speed | 0-130% | ±2% | 2 | 0.3% 1 |
| Altitude Rate | ±6,000 ft/min | As installed | 2 | 0.2% 1 |
| Pilot Input—Primary Controls (Collective, Longitudinal Cyclic, Lateral Cyclic, Pedal) 3 | Full range | ±3% | 2 | 0.5% 1 |
| Flight Control Hydraulic Pressure Low | Discrete, each circuit | 1 | ||
| Flight Control Hydraulic Pressure Selector Switch Position, 1st and 2nd stage | Discrete | 1 | ||
| AFCS Mode and Engagement Status | Discrete (5 bits necessary) | 1 | ||
| Stability Augmentation System Engage | Discrete | 1 | ||
| SAS Fault Status | Discrete | 0.25 | ||
| Main Gearbox Temperature Low | As installed | As installed | 0.25 | 0.5% 1 |
| Main Gearbox Temperature High | As installed | As installed | 0.5 | 0.5% 1 |
| Controllable Stabilator Position | Full Range | ±3% | 2 | 0.4% 1 . |
| Longitudinal Acceleration | ±1g | ±1.5% max range excluding datum error of ±5% | 4 | 0.01g. |
| Lateral Acceleration | ±1g | ±1.5% max range excluding datum of ±5% | 4 | 0.01g. |
| Master Warning | Discrete | 1 | ||
| Nav 1 and 2 Frequency Selection | Full range | As installed | 0.25 | |
| Outside Air Temperature | −50 °C to + 90 °C | ±2° c | 0.5 | 0.3° c |
| 1 Per cent of full range. | ||||
| 2 This column applies to aircraft manufactured after October 11, 1991. | ||||
| 3 For all aircraft manufactured on or after December 6, 2010, the sampling interval per second is 4. | ||||
| The recorded values must meet the designated range, resolution and accuracy requirements during static and dynamic conditions. Dynamic condition means the parameter is experiencing change at the maximum rate attainable, including the maximum rate of reversal. All data recorded must be correlated in time to within one second. | |||||
| Parameters | Range | Accuracy (sensor input) | Seconds per sampling interval | Resolution | Remarks |
|---|---|---|---|---|---|
| 1. Time or Relative Time Counts 1 | 24 Hrs, 0 to 4095 | ±0.125% Per Hour | 4 | 1 sec | UTC time preferred when available. Counter increments each 4 seconds of system operation. |
| 2. Pressure Altitude | −1000 ft to max certificated altitude of aircraft. + 5000 ft | ±100 to ±700 ft (see table, TSO C124a or TSO C51a) | 1 | 5′ to 35″ | Data should be obtained from the air data computer when practicable. |
| 3. Indicated airspeed or Calibrated airspeed | 50 KIAS or minimum value to Max V so≢ and V so to 1.2 V. D | ±5% and ±3% | 1 | 1 kt | Data should be obtained from the air data computer when practicable. |
| 4. Heading (Primary flight crew reference) | 0−360° and Discrete “true” or “mag” | ±2° | 1 | 0.5° | When true or magnetic heading can be selected as the primary heading reference, a discrete indicating selection must be recorded. |
| 5. Normal Acceleration (Vertical) 9 | −3g to + 6g | ±1% of max range excluding datum error of ±5% | 0.125 | 0.004g | |
| 6. Pitch Attitude | ±75% | ±2° | 1 or 0.25 for airplanes operated under § 135.152(j) | 0.5° | A sampling rate of 0.25 is recommended. |
| 7. Roll Attitude 2 | ±180° | ±2° | 1 or 0.5 0.5 airplanes operated under § 135.152(j) | 0.5° | A sampling rate of 0.5 is recommended. |
| 8. Manual Radio Transmitter Keying or CVR/DFDR synchronization reference | On-Off (Discrete) None | 1 | Preferably each crew member but one discrete acceptable for all transmission provided the CVR/FDR system complies with TSO C124a CVR synchronization requirements (paragraph 4.2.1 ED-55). | ||
| 9. Thrust/Power on each engine—primary flight crew reference | Full Range Forward | ±2% | 1 (per engine) | 0.3% of full range | Sufficient parameters (e.g. EPR, N1 or Torque, NP) as appropriate to the particular engine being recorded to determine power in forward and reverse thrust, including potential overspeed condition. |
| 10. Autopilot Engagement | Discrete “on” or “off” | 1 | |||
| 11. Longitudinal Acceleration | ±1g | ±1.5% max. range excluding datum error of ±5% | 0.25 | 0.004g. | |
| 12a. Pitch control(s) position (nonfly-by-wire systems) 18 | Full Range | ±2° unless higher accuracy uniquely required | 0.5 or 0.25 for airplanes operated under § 135.152(j) | 0.5% of full range | For airplanes that have a flight control breakaway capability that allows either pilot to operate the controls independently, record both control inputs. The control inputs may be sampled alternately once per second to produce the sampling interval of 0.5 or 0.25, as applicable. |
| 12b. Pitch control(s) position (fly-by-wire systems) 3 18 | Full Range | ±2° unless higher accuracy uniquely required | 0.5 or 0.25 for airplanes operated under § 135.152(j) | 0.2% of full range | |
| 13a. Lateral control position(s) (nonfly-by-wire) 18 | Full Range | ±2° unless higher accuracy uniquely required | 0.5 or 0.25 for airplanes operated under § 135.152(j) | 0.2% of full range | For airplanes that have a flight control breakaway capability that allows either pilot to operate the controls independently, record both control inputs. The control inputs may be sampled alternately once per second to produce the sampling interval of 0.5 or 0.25, as applicable. |
Code of Federal Regulations /
Title 14 - Aeronautics and Space /
Vol. 3 / 2024-01-01542 | |||||
| 13b. Lateral control position(s) (fly-by-wire) 4 18 | Full Range | ±2° unless higher accuracy uniquely required | 0.5 or 0.25 for airplanes operated under § 135.152(j) | 0.2% of full range | |
| 14a. Yaw control position(s) (nonfly-by-wire) 5 18 | Full Range | ±2° unless higher accuracy uniquely required | 0.5 | 0.3% of full range | For airplanes that have a flight control breakaway capability that allows either pilot to operate the controls independently, record both control inputs. The control inputs may be sampled alternately once per second to produce the sampling of 0.5 or 0.25, as applicable. |
| 14b. Yaw control position(s) (fly-by-wire) 18 | Full Range | ±2° unless higher accuracy uniquely required | 0.5 | 0.2% of full range | |
| 15. Pitch control surface(s) position 6 18 | Full Range | ±2° unless higher accuracy uniquely required | 0.5 or 0.25 for airplanes operated under § 135.152(j). | 0.3% of full range | For airplanes fitted with multiple or split surfaces, a suitable combination of inputs is acceptable in lieu of recording each surface separately. The control surfaces may be sampled alternately to produce the sampling interval of 0.5 or 0.25, as applicable. |
| 16. Lateral control surface(s) position 7 18 | Full Range | ±2° unless higher accuracy uniquely required | 0.5 or 0.25 for airplanes operated under § 135.152(j) | 0.2% of full range | A suitable combination of surface position sensors is acceptable in lieu of recording each surface separately. The control surfaces may be sampled alternately to produce the sampling interval of 0.5 or 0.25, as applicable. |
| 17. Yaw control surface(s) position 8 18 | Full Range | ±2° unless higher accuracy uniquely required | 0.5 | 0.2% of full range | For airplanes with multiple or split surfaces, a suitable combination of surface position sensors is acceptable in lieu of recording each surface separately. The control surfaces may be sampled alternately to produce the sampling interval of 0.5. |
| 18. Lateral Acceleration | ±1g | ±1.5% max. range excluding datum error of ±5% | 0.25 | 0.004g | |
| 19. Pitch Trim Surface Position | Full Range | ±3° Unless Higher Accuracy Uniquely Required | 1 | 0.6% of full range | |
| 20. Trailing Edge Flap or Cockpit Control Selection 10 | Full Range or Each Position (discrete) | ±3° or as Pilot's Indicator | 2 | 0.5% of full range | Flap position and cockpit control may each be sampled alternately at 4 second intervals, to give a data point every 2 seconds. |
Code of Federal Regulations /
Title 14 - Aeronautics and Space /
Vol. 3 / 2024-01-01543 | |||||
| 21. Leading Edge Flap or Cockpit Control Selection 11 | Full Range or Each Discrete Position | ±3° or as Pilot's Indicator and sufficient to determine each discrete position | 2 | 0.5% of full range | Left and right sides, of flap position and cockpit control may each be sampled at 4 second intervals, so as to give a data point to every 2 seconds. |
| 22. Each Thrust reverser Position (or equivalent for propeller airplane) | Stowed, In Transit, and reverse (Discrete) | 1 (per engine | Turbo-jet—2 discretes enable the 3 states to be determined Turbo-prop—1 discrete | ||
| 23. Ground Spoiler Position or Speed Brake Selection 12 | Full Range or Each Position (discrete) | ±2° Unless Higher Accuracy Uniquely Required | 1 or 0.5 for airplanes operated under § 135.152(j) | 0.5% of full range | |
| 24. Outside Air Temperature or Total Air Temperature 13 | −50 °C to + 90 °C | ±2 °C | 2 | 0.3 °C | |
| 25. Autopilot/Autothrottle/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 and speed of the aircraft. | ||
| 26. Radio Altitude 14 | −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 | For autoland/category 3 operations. Each radio altimeter should be recorded, but arranged so that at least one is recorded each second. |
| 27. Localizer Deviation, MLS Azimuth, or GPS Lateral Deviation | ±400 Microamps or available sensor range as installed ±62° | As installed ±3% recommended. | 1 | 0.3% of full range | For autoland/category 3 operations. Each system should be recorded but arranged so that at least one is recorded each second. It is not necessary to record ILS and MLS at the same time, only the approach aid in use need be recorded. |
| 28. Glideslope Deviation, MLS Elevation, or GPS Vertical Deviation | ±400 Microamps or available sensor range as installed 0.9 to + 30° | As installed ±3% recommended | 1 | 0.3% of full range | For autoland/category 3 operations. Each system should be recorded but arranged so that at least one is recorded each second. It is not necessary to record ILS and MLS at the same time, only the approach aid in use need be recorded. |
| 29. Marker Beacon Passage | Discrete “on” or “off” | 1 | A single discrete is acceptable for all markers. | ||
| 30. Master Warning | Discrete | 1 | Record the master warning and record each “red” warning that cannot be determined from other parameters or from the cockpit voice recorder. | ||
| 31. Air/ground sensor (primary airplane system reference nose or main gear) | Discrete “air” or “ground” | 1 (0.25 recommended.) | |||
| 32. Angle of Attack (If measured directly) | As installed | As installed | 2 or 0.5 for airplanes operated under § 135.152(j) | 0.3% of full range | If left and right sensors are available, each may be recorded at 4 or 1 second intervals, as appropriate, so as to give a data point at 2 seconds or 0.5 second, as required. |
Code of Federal Regulations /
Title 14 - Aeronautics and Space /
Vol. 3 / 2024-01-01544 | |||||
| 33. Hydraulic Pressure Low, Each System | Discrete or available sensor range, “low” or “normal” | ±5% | 2 | 0.5% of full range. | |
| 34. Groundspeed | As installed | Most Accurate Systems Installed | 1 | 0.2% of full range. | |
| 35. GPWS (ground proximity warning system) | Discrete “warning” or “off” | 1 | A suitable combination of discretes unless recorder capacity is limited in which case a single discrete for all modes is acceptable. | ||
| 36. Landing Gear Position or Landing gear cockpit control selection | Discrete | 4 | A suitable combination of discretes should be recorded. | ||
| 37. Drift Angle 15 | As installed | As installed | 4 | 0.1° | |
| 38. Wind Speed and Direction | As installed | As installed | 4 | 1 knot, and 1.0°. | |
| 39. Latitude and Longitude | As installed | As installed | 4 | 0.002°, or as installed | Provided by the Primary Navigation System Reference. Where capacity permits latitude/longitude resolution should be 0.0002°. |
| 40. Stick shaker and pusher activation | Discrete(s) “on” or “off” | 1 | A suitable combination of discretes to determine activation. | ||
| 41. Windshear Detection | Discrete “warning” or “off” | 1. | |||
| 42. Throttle/power lever position 16 | Full Range | ±2% | 1 for each lever | 2% of full range | For airplanes with non-mechanically linked cockpit engine controls. |
| 43. Additional Engine Parameters | As installed | As installed | Each engine each second | 2% of full range | Where capacity permits, the preferred priority is indicated vibration level, N2, EGT, Fuel Flow, Fuel Cut-off lever position and N3, unless engine manufacturer recommends otherwise. |
| 44. Traffic Alert and Collision Avoidance System (TCAS) | Discretes | As installed | 1 | A suitable combination of discretes should be recorded to determine the status of—Combined Control, Vertical Control, Up Advisory, and down advisory. (ref. ARINC Characteristic 735 Attachment 6E, TCAS VERTICAL RA DATA OUTPUT WORD.) | |
| 45. DME 1 and 2 Distance | 0-200 NM; | As installed | 4 | 1 NM | 1 mile. |
| 46. Nav 1 and 2 Selected Frequency | Full range | As installed | 4 | Sufficient to determine selected frequency. | |
| 47. Selected barometric setting | Full Range | ±5% | (1 per 64 sec.) | 0.2% of full range. | |
| 48. Selected altitude | Full Range | ±5% | 1 | 100 ft. | |
| 49. Selected speed | Full Range | ±5% | 1 | 1 knot. | |
Code of Federal Regulations /
Title 14 - Aeronautics and Space /
Vol. 3 / 2024-01-01545 | |||||
| 50. Selected Mach | Full Range | ±5% | 1 | .01. | |
| 51. Selected vertical speed | Full Range | ±5% | 1 | 100 ft./min. | |
| 52. Selected heading | Full Range | ±5% | 1 | 1°. | |
| 53. Selected flight path | Full Range | ±5% | 1 | 1°. | |
| 54. Selected decision height | Full Range | ±5% | 64 | 1 ft. | |
| 55. EFIS display format | Discrete(s) | 4 | Discretes should show the display system status (e.g., off, normal, fail, composite, sector, plan, nav aids, weather radar, range, copy. | ||
| 56. Multi-function/Engine Alerts Display format | Discrete(s) | 4 | Discretes should show the display system status (e.g., off, normal, fail, and the identity of display pages for emergency procedures, need not be recorded. | ||
| 57. Thrust comand 17 | Full Range | ±2% | 2 | 2% of full range | |
| 58. Thrust target | Full Range | ±2% | 4 | 2% of full range. | |
| 59. Fuel quantity in CG trim tank | Full Range | ±5% | (1 per 64 sec.) | 1% of full range. | |
| 60. Primary Navigation System Reference | Discrete GPS, INS, VOR/DME, MLS, Localizer Glideslope | 4 | A suitable combination of discretes to determine the Primary Navigation System reference. | ||
| 61. Ice Detection | Discrete “ice” or “no ice” | 4. | |||
| 62. Engine warning each engine vibration | Discrete | 1. | |||
| 63. Engine warning each engine over temp. | Discrete | 1. | |||
| 64. Engine warning each engine oil pressure low | Discrete | 1. | |||
| 65. Engine warning each engine over speed | Discrete | 1. | |||
| 66. Yaw Trim Surface Position | Full Range | ±3% Unless Higher Accuracy Uniquely Required | 2 | 0.3% of full range. | |
| 67. Roll Trim Surface Position | Full Range | ±3% Unless Higher Accuracy Uniquely Required | 2 | 0.3% of full range. | |
| 68. Brake Pressure (left and right) | As installed | ±5% | 1 | To determine braking effort applied by pilots or by autobrakes. | |
| 69. Brake Pedal Application (left and right) | Discrete or Analog “applied” or “off” | ±5% (Analog) | 1 | To determine braking applied by pilots. | |
| 70. Yaw or sideslip angle | Full Range | ±5% | 1 | 0.5°. | |
| 71. Engine bleed valve position | Discrete “open” or “closed” | 4. | |||
| 72. De-icing or anti-icing system selection | Discrete “on” or “off” | 4. | |||
| 73. Computed center of gravity | Full Range | ±5% | (1 per 64 sec.) | 1% of full range. | |
Code of Federal Regulations /
Title 14 - Aeronautics and Space /
Vol. 3 / 2024-01-01546 | |||||
| 74. AC electrical bus status | Discrete “power” or “off” | 4 | Each bus. | ||
| 75. DC electrical bus status | Discrete “power” or “off” | 4 | Each bus. | ||
| 76. APU bleed valve position | Discrete “open” or “closed” | 4. | |||
| 77. Hydraulic Pressure (each system) | Full range | ±5% | 2 | 100 psi. | |
| 78. Loss of cabin pressure | Discrete “loss” or “normal” | 1. | |||
| 79. Computer failure (critical flight and engine control systems) | Discrete “fail” or “normal” | 4. | |||
| 80. Heads-up display (when an information source is installed) | Discrete(s) “on” or “off” | 4. | |||
| 81. Para-visual display (when an information source is installed) | Discrete(s) “on” or “off” | 1. | |||
| 82. Cockpit trim control input position—pitch | Full Range | ±5% | 1 | 0.2% of full range | Where mechanical means for control inputs are not available, cockpit display trim positions should be recorded. |
| 83. Cockpit trim control input position—roll | Full Range | ±5% | 1 | 0.7% of full range | Where mechanical means for control inputs are not available, cockpit display trim position should be recorded. |
| 84. Cockpit trim control input position—yaw | Full Range | ±5% | 1 | 0.3% of full range | Where mechanical means for control input are not available, cockpit display trim positions should be recorded. |
| 85. Trailing edge flap and cockpit flap control position | Full Range | ±5% | 2 | 0.5% of full range | Trailing edge flaps and cockpit flap control position may each be sampled alternately at 4 second intervals to provide a sample each 0.5 second. |
| 86. Leading edge flap and cockpit flap control position | Full Range or Discrete | ±5% | 1 | 0.5% of full range. | |
| 87. Ground spoiler position and speed brake selection | Full Range or Discrete | ±5% | 0.5 | 0.3% of full range | |
| 88. All cockpit flight control input forces (control wheel, control column, rudder pedal) 18 | Full Range Control wheel ±70 lbs. Control column ±85 lbs. Rudder pedal ±165 lbs | ±5° | 1 | 0.3% of full range | For fly-by-wire flight control systems, where flight control surface position is a function of the displacement of the control input device only, it is not necessary to record this parameter. For airplanes that have a flight control breakaway capability that allows either pilot to operate the control independently, record both control force inputs. The control force inputs may be sampled alternately once per 2 seconds to produce the sampling interval of 1. |
Code of Federal Regulations /
Title 14 - Aeronautics and Space /
Vol. 3 / 2024-01-01547 | |||||
| 1 For A300 B2/B4 airplanes, resolution = 6 seconds. | |||||
| 2 For A330/A340 series airplanes, resolution = 0.703°. | |||||
| 3 For A318/A319/A320/A321 series airplanes, resolution = 0.275% (0.088°>0.064°). For A330/A340 series airplanes, resolution = 2.20% (0.703°>0.064°). | |||||
| 4 For A318/A319/A320/A321 series airplanes, resolution = 0.22% (0.088°>0.080°). For A330/A340 series airplanes, resolution = 1.76% (0.703°>0.080°). | |||||
| 5 For A330/A340 series airplanes, resolution = 1.18% (0.703°>0.120°). | |||||
| 6 For A330/A340 series airplanes, resolution = 0.783% (0.352°>0.090°). | |||||
| 7 For A330/A340 series airplanes, aileron resolution = 0.704% (0.352°>0.100°). For A330/A340 series airplanes, spoiler resolution = 1.406% (0.703°>0.100°). | |||||
| 8 For A330/A340 series airplanes, resolution = 0.30% (0.176°>0.12°). For A330/A340 series airplanes, seconds per sampling interval = 1. | |||||
| 9 For B-717 series airplanes, resolution = .005g. For Dassault F900C/F900EX airplanes, resolution = .007g. | |||||
| 10 For A330/A340 series airplanes, resolution = 1.05% (0.250°>0.120°). | |||||
| 11 For A330/A340 series airplanes, resolution = 1.05% (0.250°>0.120°). For A300 B2/B4 series airplanes, resolution = 0.92% (0.230°>0.125°). | |||||
| 12 For A330/A340 series airplanes, spoiler resolution = 1.406% (0.703°>0.100°). | |||||
| 13 For A330/A340 series airplanes, resolution = 0.5 °C. | |||||
| 14 For Dassault F900C/F900EX airplanes, Radio Altitude resolution = 1.25 ft. | |||||
| 15 For A330/A340 series airplanes, resolution = 0.352 degrees. | |||||
| 16 For A318/A319/A320/A321 series airplanes, resolution = 4.32%. For A330/A340 series airplanes, resolution is 3.27% of full range for throttle lever angle (TLA); for reverse thrust, reverse throttle lever angle (RLA) resolution is nonlinear over the active reverse thrust range, which is 51.54 degrees to 96.14 degrees. The resolved element is 2.8 degrees uniformly over the entire active reverse thrust range, or 2.9% of the full range value of 96.14 degrees. | |||||
| 17 For A318/A319/A320/A321 series airplanes, with IAE engines, resolution = 2.58%. | |||||
| 18 For all aircraft manufactured on or after December 6, 2010, the seconds per sampling interval is 0.125. Each input must be recorded at this rate. Alternately sampling inputs (interleaving) to meet this sampling interval is prohibited. | |||||