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Operator ID: |
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UAS Operating Safety Case |
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Document reference number: |
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Document version and date: |
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Amendment Number |
Date |
Amended by |
Details of changes |
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CAP722A Table 6
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UAS Model |
Agras T50 |
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UAS design & manufaturing organisations |
DJI |
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Empty Mass |
Weight: |
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Maximum Take-Off Mass (MTOM) |
Max Takeoff Weight: |
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Dimensions for Rotorcraft / Multirotor |
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Length of aircraft body |
Dimensions: |
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Width of aircraft body |
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Height of aircraft body |
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Propeller Configuration |
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Propeller Dimensions |
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Sound power level |
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Any other relevant information |
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CAP722A Table 7
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Maximum airspeed |
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Minimum airspeed to maintain safe flight |
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Normal/typical operating height |
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Maximum operating height |
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Maximum flight time during normal operation |
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Maximum flight time on an ISA day at cruising speed at normal/typical operating height. |
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Maximum flight range on an ISA day (normal and emergency conditions) |
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Glide distances |
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Maximum radio range of the C2 Link |
Max Transmission Distance (unobstructed, free of interference): |
CAP722A Table 8
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Wind speed limits |
Max Wind Resistance: |
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Turbulence restrictions |
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Precipitation limits |
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OAT limits |
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In-flight icing condition limits |
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Any other relevant information |
CAP722A Table 9
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Type of material |
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Material characteristics or properties |
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Any other relevant information |
CAP722A Table 10
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Batteries: |
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Battery type, model and manufacturer |
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Quantity |
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Arrangement |
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Generator: |
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Generator type, model and manufacturer |
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Specification |
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Electrical loads |
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Electrical load shedding functionality |
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Power supply redundancy |
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Procedures to charge and discharge batteries. |
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Safety provisions with regards to hazards inherent to high-voltage storage devices: |
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Procedures in place for safe handling by any person who may come into contact with high-voltage storage devices |
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Means of identifying high-voltage storage |
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Safety provisions for any person discovering the UA following an accident. |
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Procedures and safety provisions to mitigate the risk of battery thermal runaway. |
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Procedures for monitoring high-voltage storage devices. |
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HMI: |
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Information indicated to the remote pilot. |
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Alert messages indicated to the remote pilot. |
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Any other relevant information |
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CAP722A Table 11
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Propulsion type |
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Engines: |
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Type, model and manufacturer |
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Propeller type, model and manufacturer |
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Quantity |
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Arrangement |
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Power output |
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Propeller guards |
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In-flight restart functionality |
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Performance monitoring |
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Health monitoring |
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Safety features and redundancy in the system that allow maintaining flight after a failure or degradation has occurred in the propulsion system. |
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Fuel-powered propulsion system – Safety features to mitigate the risk of engine loss when the following hazards occur: |
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Fuel starvation |
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Fuel contamination |
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Failed signal input from the control station |
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Engine controller failure |
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Indication to the remote pilot |
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Electric-powered propulsion system: |
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Power source and supply management with regards to other systems in the UA |
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Redundant power sources |
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Maximum continuous power output of the motor |
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Maximum peak power output of the motor |
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Electrical distribution architecture |
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Electrical load shedding functionality |
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HMI: |
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Information indicated to the remote pilot. |
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Alert messages indicated to the remote pilot. |
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Any other relevant information |
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CAP722A Table 12
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Fuel type |
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Safety provisions with regards to hazardous substances within the fuel system: |
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List of hazardous substances and their characteristics. |
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Procedures in place for safe handling of the UA by any person who may come into contact with the hazardous substances. |
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Means of identifying the hazardous substances. |
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Safety provisions for any person discovering the UA following an accident. |
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HMI: |
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Information indicated to the remote pilot. |
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Alert messages indicated to the remote pilot. |
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Any other relevant information |
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CAP722A Table 13
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Design and operation of flight control units, surfaces, actuators, control linkages, etc. |
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Flight controller: |
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Type, model and manufacturer |
Model: |
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Functions |
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Flight modes available |
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Automatic functions: |
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Take-off and landing |
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Stabilisation |
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Autopilot |
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Return to home |
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If functions are provided by COTS equipment, provide type, model and manufacturer. |
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Safety features and redundancy in the system which allow maintaining flight after a failure or degradation of the flight control system, including indication to the remote pilot. |
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HMI: |
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Information indicated to the remote pilot. |
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Alert messages indicated to the remote pilot. |
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Any other relevant information |
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CAP722A Table 14
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Sensors |
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Type, model and manufacturer |
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Quantity |
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Telemetry links |
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Method to determine current position. |
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Method to navigate to intended destination. |
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Automatic/automated navigation functions |
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Geo-awareness functions |
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Containment functions |
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Safety features and redundancy in the system which allow maintaining flight after a failure or degradation has occurred in the navigation system: |
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Backup means of navigation |
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Detection of and response to loss of primary means and secondary means of navigation. |
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Indication to the remote pilot |
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HMI: |
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Information indicated to the remote pilot. |
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Alert messages indicated to the remote pilot. |
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Any other relevant information |
GNSS: |
CAP722A Table 15
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DAA system functions |
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Devices used |
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Technology used |
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Interface between the DAA system and the flight control computer |
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Limitations of the DAA system |
Effective Sensing Speed: FOV: |
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Evidence of equipment qualification and approval. |
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DAA event sequence: |
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Level of automation |
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Actions required by the remote pilot |
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Means to verify normal system operation. |
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HMI: |
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Information indicated to the remote pilot. |
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Alert messages indicated to the remote pilot. |
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Any other relevant information |
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CAP722A Table 16
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Power sources, supply management and redundancy. |
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Radio signal: |
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Determination of the signal strength and health value. |
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Threshold values which represent a critically degraded signal. |
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Control handover between two CUs |
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Safety features to mitigate the risk of inadvertent command activation: |
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List of critical commands |
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Mitigation means |
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Safety features to mitigate the risk of display or HMI lock-up. |
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Safety features to maintain flight-critical processing when multiple programs are running concurrently. |
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HMI: |
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Information indicated to the remote pilot. |
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Radio signal strength and/or health indication to the remote pilot. |
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Alert messages indicated to the remote pilot. |
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Any other relevant information |
Operating Temperature: |
CAP722A Table 17
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RLOS |
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BRLOS |
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Antennas: |
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Type, model and manufacturer |
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Locations on the UAS |
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Transceivers / Modems: |
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Power levels |
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Transmission schemes |
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Operating frequencies |
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Details of frequency spectrum approvals |
Operating Frequency: |
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Maximum power output/range |
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Type of signal processing |
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Datalink margin in terms of the overall link bandwidth at the maximum anticipated distance from the CU. |
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Operational C2 link management: |
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Frequency switchovers |
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Contingency situations |
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Third party link service provider |
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Radio signal: |
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Determination of the signal strength and health value |
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Threshold values which represent a critically degraded signal. |
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Minimum and average assured data rates |
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Minimum and average assured latencies |
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Design features and procedures to maintain availability, continuity, and integrity of the datalink: |
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RF or other interference |
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Flight beyond communications range |
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Antenna masking |
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Loss of CU functionality |
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Loss of UA functionality |
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Atmospheric attenuation |
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Safety features to mitigate the risk of loss of C2 link: |
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C2 links redundancy |
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Automatic triggering of an emergency recovery function |
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Automatic return to home |
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Safety features to mitigate the risk of harmful interference. |
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HMI: |
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Information indicated to the remote pilot. |
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Radio signal strength and/or health indication to the remote pilot. |
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Alert messages indicated to the remote pilot. |
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Any other relevant information |
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CAP722A Table 18
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Antennas: |
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Type, model and manufacturer |
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Locations on the UAS |
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Communication method: |
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VHF |
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GSM network |
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Satellite |
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Safety features to mitigate the loss of communication function: |
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Primary communication means |
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Secondary / back-up communication means |
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HMI: |
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Information indicated to the remote pilot. |
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Radio signal strength and/or health indication to the remote pilot. |
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Alert messages indicated to the remote pilot. |
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Any other relevant information |
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CAP722A Table 19
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Wheels, skids, rails, launchers, etc. |
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If various mechanisms can be fitted: |
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Primary mechanism |
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Secondary mechanisms |
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Operational conditions/requirements for each mechanism. |
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Any other relevant information |
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CAP722A Table 20
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Mode of operation |
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Safety features which mitigate the risk of loss of control or situational awareness. |
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Means to verify normal system operation. |
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HMI: |
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Information indicated to the remote pilot. |
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Alert messages indicated to the remote pilot. |
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Any other relevant information |
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CAP722A Table 21
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Type, model and manufacturer |
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Locations on the UA |
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Colour |
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Operation |
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Operating modes |
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Purpose |
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HMI: |
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Information indicated to the remote pilot. |
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Alert messages indicated to the remote pilot. |
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Any other relevant information |
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CAP722A Table 22
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Types |
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Mass |
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Interfaces with the UA: |
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Mechanical interface |
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Electrical interface |
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Data interface |
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Release mechanism |
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Any other interface |
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Procedures to install the payload onto the UA. |
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Effects of the payload on the UA |
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Sensors |
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Safety features to mitigate the risk of the payload affecting the flight of the UA: |
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Effects on aerodynamics |
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Effects of electro-magnetic interference. |
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Effects of electrical power and / or data connection failures on the UAS. |
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Effects of complete detachment of the payload from the UA (either caused by a failure or through intentional lowering / dropping of the payload). |
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Effects of partial detachment of the payload from the UA. |
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Distraction of the remote pilot generated by the payload during flight. |
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Procedures to verify the attachment points to the UA. |
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Procedures to verify the UA MTOM and CG location. |
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Procedures to detect and mitigate any failure of the payload in flight. |
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Safety provisions with regards to hazards inherent to the payload |
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Procedures in place for safe handling of the payload. |
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Means of identifying hazards. |
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HMI: |
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Information indicated to the remote pilot. |
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Alert messages indicated to the remote pilot. |
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Any other relevant information |
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CAP722A Table 23
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UAS launch and recovery systems |
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Power sources |
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Transportation equipment |
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Backup or emergency equipment |
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Procedures to transport UA, CU, battery/fuel, and other equipment between operation sites and from the loading/off-loading area to the take-off/landing area. |
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Storage of ground support equipment. |
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Suitability of the ground support equipment and transportation method with regards to the UAS components’ fragility, sensitivity or inherent hazards. |
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Ground support equipment standards |
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Ground support equipment manufacturer's recommendations. |
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Any other relevant information |
CAP722A Table 24
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Maintenance manual: |
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Structure |
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Maintenance procedures: |
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Inspections |
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Overhaul |
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Repairs |
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Assurance of repair procedures |
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Batteries maintenance during storage periods |
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Origin of each procedure |
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Maintenance schedules |
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Procedures to record maintenance that has been carried out. |
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Storage of maintenance records |
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Staff qualification and levels of approval. |
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Procedures to use the manual by the Maintenance staff |
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Configuration control |
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Any other relevant information |
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CAP722A Table 25
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Sources of procurement |
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Process to confirm the suitability of the part. |
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Any other relevant information |
CAP722A Table 26
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Hardware, software, and firmware version control |
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Modification standards |
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Modification records storage |
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Safety assessment associated with the modification |
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Any other relevant information |
CAP722A Table 27
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Step 1 – Identify the main functions of the UAS. |
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Step 2 – Identify the sub-functions. |
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Step 3 – Consider the ways each function may fail. |
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Step 4 – Identify the failure conditions. |
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Step 5 – Select those failure conditions that may lead to mid-air collision or harm to uninvolved people on the ground. (Identified Hazard) |
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Step 6 – Assurance |
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Step 7 – Describe the consequence of the failure condition. |
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Step 8 – Describe the failure modes. (Unmitigated Failures) |
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Step 9 – Identify the single points of failure. |
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Step 10 – Describe the risk mitigation means. |
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CAP722A Table 28
Aircraft | |
| Weight | 39.9 kg (excl. battery) 52 kg (incl. battery) |
| Max Takeoff Weight | Max takeoff weight for spraying: 92 kg (at sea level) Max takeoff weight for spreading: 103 kg (at sea level) |
| Max Diagonal Wheelbase | 2200 mm |
| Dimensions | 2800 x 3085 x 820 mm (arms and propellers unfolded) 1590 x 1900 x 820 mm (arms unfolded and propellers folded) 1115 x 750 x 900 mm (arms and propellers folded) |
| Hovering Accuracy Range | D-RTK enabled: Horizontal: ±10 cm, Vertical: ±10 cm D-RTK disabled: Horizontal: ±60 cm, Vertical: ±30 cm (radar module enabled: ±10 cm) |
| RTK/GNSSOperating Frequency | RTK: GPS L1/L2, GLONASS F1/F2, BeiDou B1I/B2I/B3I, Galileo E1/E5b, QZSS L1/L2 GNSS: GPS L1, GLONASS F1, BeiDou B1I, Galileo E1, QZSS L1 |
| Max Configurable Flight Radius | 2000 m |
| Max Wind Resistance | 6 m/s |
Propulsion System - Motors | |
| Stator Size | 100 x 33 mm |
| KV | 48 rpm/V |
| Power | 4000 W/rotor |
Propulsion System - Propellers | |
| Material | Nylon carbon fiber filament |
| Dimension | 54 in (1371.6 mm) |
| Propeller Rotation Diameter | 1375 mm |
| Quantity | 8 |
Dual Atomizing Spraying System - Spray Tank | |
| Material | Plastic (HDPE) |
| Volume | 40 L |
| Operating Payload [1] | 40 kg[1] |
| Quantity | 1 |
Dual Atomizing Spraying System - Sprinklers | |
| Model | LX8060SZ |
| Quantity | 2 |
| Nozzle Distance | 1570 mm（Rear Nozzles) |
| Droplet Size | 50-500 μm |
| Effective Spray Width [2] | 4-11 m (at a height of 3 m above the crops) |
Dual Atomizing Spraying System - Delivery Pumps | |
| Type | Impreller pump (magnetic drive) |
| Quantity | 2 |
| Single Pump Flow Rate | 0-12 L/min |
| Max Flow Rate | 16 L/min (2 nozzles); 24 L/min (4 nozzles) |
T50 Spreading System | |
| Compatible Material Diameter | 0.5-5 mm dry granules |
| Spread Tank Volume | 75 L |
| Spread Tank Internal Load [10] | 50 kg |
| Spread Width | 8 m |
Phased Array Radar System | |
| Model | RD241608RF (forward phased array radar); RD241608RB (rear phased array radar) |
| Terrain Follow | Max slope in Mountain mode: 20 Deg. Altitude detection range: 1-50 m Stabilization working range: 1.5-30 m |
| Obstacle Avoidance [4] | Obstacle sensing range (multidirectional): 1-50 m FOV: Forward phased array radar: horizontal 360 Deg., vertical ±45 Deg., upward ±45 Deg. (cone) Rear phased array radar: vertical 360 Deg., horizontal ±45 Deg. Working conditions: flying higher than 1.5 m over the obstacle at a horizontal speed no more than 10 m/s and vertical speed no more than 3 m/s. Safety limit distance: 2.5 m (distance between the front of propellers and the obstacle after braking) Sensing direction: 360 Deg. multidirectional sensing |
Binocular Vision System | |
| Measurement range | 0.5-29 m |
| Effective Sensing Speed | <=10 m/s |
| FOV | Horizontal: 90 Deg., Vertical: 106 Deg. |
| Operating Environment | Adequate light and discernible surroundings |
Remote Controller | |
| Model | RM700B |
| Operating Frequency | 2.4000-2.4835 GHz, 5.725-5.850 GHz |
| Max Transmission Distance (unobstructed, free of interference) | 7 km (FCC), 5 km (SRRC), 4 km (MIC/CE); (unobstructed, free of interference, and at an altitude of 2.5 m) |
| Wi-Fi Protocol | Wi-Fi 6 |
| Wi-Fi Operating Frequency | 2.4000-2.4835 GHz, 5.150-5.250 GHz, 5.725-5.850 GHz |
| Bluetooth Protocol | Bluetooth 5.1 |
| Bluetooth Operating Frequency | 2.4000-2.4835 GHz |
| GNSS | GPS+Galileo+BeiDou |
| Screen | 7.02-in LCD touchscreen, with a resolution of 1920 x 1200 pixels, and high brightness of 1200 cd/m2 |
| Operating Temperature | -20 Deg. to 50 Deg. C (-4 Deg. to 122 Deg. F) |
| Storage Temperature Range | Less than one month: -30 Deg. to 45 Deg. C (-22 Deg. to 113 Deg. F) One to three months: -30 Deg. to 35 Deg. C (-22 Deg. to 95 Deg. F) Six months to one year: -30 Deg. to 30 Deg. C (-22 Deg. to 86 Deg. F) |
| Charging Temperature | 5 Deg. to 40 Deg. C (41 Deg. to 104 Deg. F) |
| Internal Battery Runtime | 3 hours 18 minutes |
| External Battery Runtime | 2 hours 42 minutes |
| Charging Type | It is recommended to use a locally certified USB-C charger at a maximum rated power of 65 W and maximum voltage of 20 V such as the DJI 65W Portable Charger. |
| Charging Time | 2 hours for internal battery or internal and external battery (when remote controller is powered off and using a standard DJI charger) |
DB1560 Intelligent Flight Battery | |
| Model | DB1560 Intelligent Flight Battery (BAX702-30000mAh-52.22V) |
| Weight | Approx. 12.1 kg |
| Capacity | 30000 mAh |
| Nominal Voltage | 52.22 V |
D12000i Multifunctional Inverter Generator | |
| Output Channel | 1. DC charging output 42-59.92V/9000W 2.Power supply for air-cooled heat sink 12 V/6 A 3.AC output 230V/1500W or 120V/750W [8] |
| Battery Charging Time | To fully charge one battery (T40 battery) takes 9-12 mins |
| Fuel Tank Capacity | 30 L |
| Starting Method | Starting the Generator via the One-Button Start Switch |
| Max Power of Engine | 12000 W |
| Fuel Type | Unleaded gasoline with RON ≥91 (AKI ≥87) and alcohol content less than 10% (*Brazil: unleaded gasoline with RON ≥ 91 and alcohol content of 27%) |
| Reference Fuel Consumption [9] | 500 ml/kWh |
| Engine Oil Model | SJ 10W-40 |
C10000 Intelligent Power Supply | |
| Model Number | CSX702-9500 |
| Dimensions | 400 x 266 x 120 mm |
| Weight | Approx. 11.4 kg |
| Input/Output | Input (Main): 220-240 VAC, 50/60 Hz, 24 A MAX Input (Auxiliary): 220-240 VAC, 50/60 Hz, 24 A MAX Output: 59.92 VDC MAX, 175 A MAX, 9000 W MAX Input (Main): 100-120 VAC, 50/60 Hz, 16 A MAX Input (Auxiliary): 100-120 VAC, 50/60 Hz, 16 A MAX Output: 59.92 VDC MAX, 60 A MAX, 3000 W MAX |
| Charging Time | Fully charges a battery in 9 to 12 minutes (DB1560 Intelligent Flight Battery) |
| Protection Functions | Over-voltage, over-charge, under-voltage and over-temperature protection. |
| Charging Safety | AC wire protection, power wire protection, and charge connector protection |
Relay | |
| Model | RL01-65 |
| Dimensions | 120 x 110 x 100 mm |
| Weight | <=575 g |
| Input Voltage [6] | 9 V3 A / 12 V2.5 A / 15 V2 A |
| Power Consumption | 9 W (SRRC), 12 W (FCC) |
| Capacity | 6500 mAh |
| Operating Time | 4 hours |
| Operating Frequency [5] | 2.4000-2.4835 GHz, 5.725-5.850 GHz |
| Max Transmission Distance | 5 km (SRRC), 4 km (MIC/KCC/CE), 7 km (FCC) (unobstructed, free of interference, and at a flight altitude of 2.5 m) |
| Charging Time | 2 hours and 20 minutes (when using a standard DJI charger) |
| IP Rating [6] | IP55 |
Data source: https://www.dji.com/t50/specs
Generated using dronespec.info
Source data acquired 2024-04-26 10:03:42