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MHT2006-2013: A small aircraft flight record system performance specifications
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A small aircraft flight record system performance specifications
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MH/T 2006-2013
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Standard similar to MHT2006-2013 MH 5064 MH 5013 MH/T 5042 Basic data | Standard ID | MH/T 2006-2013 (MH/T2006-2013) | | Description (Translated English) | A small aircraft flight record system performance specifications | | Sector / Industry | Civil Aviation Industry Standard (Recommended) | | Word Count Estimation | 16,131 | | Date of Issue | 11/11/2013 | | Date of Implementation | 1/3/2014 | | Issuing agency(ies) | Civil Aviation Administration of China | MHT2006-2013: A small aircraft flight record system performance specifications---This is a DRAFT version for illustration, not a final translation. Full copy of true-PDF in English version (including equations, symbols, images, flow-chart, tables, and figures etc.) will be manually/carefully translated upon your order.
Specification for operational performance of small aircraft recording systems
ICS 49.090
V 45
MH
Civil Aviation Industry Standard of the People's Republic of China
Performance Specification for Small Aircraft Flight Recording System
2013-11-11 released
2014-03-01 implementation
Issued by Civil Aviation Administration of China
Foreword
This standard was drafted in accordance with the rules given in GB/T 1.1-2009.
This standard was proposed by the Aviation Safety Office of the Civil Aviation Administration of China.
This standard was approved by the Aircraft Airworthiness Certification Department of the Civil Aviation Administration of China.
This standard is under the jurisdiction of the China Academy of Civil Aviation Science and Technology.
Drafting organization of this standard. China Civil Aviation Science and Technology Research Institute.
Drafters of this standard. Wang Haofeng, Shu Ping, Miao Lingyun, Xiao Xianbo, Zhong Minzhu, Wang Chun.
Performance Specification for Small Aircraft Flight Recording System
1 Scope
This standard specifies the recording system that can record small aircraft flight data, cockpit audio, airborne video or data link information
Minimum performance requirements.
This standard applies to the development, design, installation and use of small aircraft flight record systems.
2 Terms and definitions
2.1
Small aircraft
In accordance with "Small Aircraft Commercial Transport Operator Operation Certification Rules" (CCAR-135) and "General Operation and Flight Rules"
(CCAR-91) Multi-engine airplanes, single-engine airplanes and maximum certified take-off weights not exceeding 5 700 kg in operation.
Rotorcraft over 3 180 kg.
2.2
Flight recorders
Installed inside an aircraft, used to record aircraft flight data, cockpit audio, airborne video or data link information to assist in accidents
Or incident investigation, and equipment with corresponding protection devices.
2.3
ADRS, aircraft data recording systems
Collect and record airborne equipment or equipment groups that reflect the aircraft status, performance and other parameters. It can accurately record and describe aircraft status and
Required parameters for pilot operations; at the same time, according to the complexity of the aircraft, the available data sources and the recording requirements of mandatory parameters
If required, it can also record other non-mandatory parameters.
2.4
Cockpit audio recording systems CARS, cockpit audio recording systems
Use microphones or other audio and digital inputs to collect and record various audio information in the cockpit, including land-air communications, crew calls,
Airborne equipment or equipment group such as cockpit background sound.
2.5
Airborne image recording systems AIRS, airborne image recording systems
Airborne equipment or equipment group that uses optical sensors to collect and record image information from different areas of the aircraft. It can record driving
The images in the cabin include operating inputs, instrumentation and control panel information, and can also record images from outside the cabin.
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2.6
DLRS, data-link recording systems
The onboard equipment or equipment group that records the interactive message information transmitted by the data link.
3 Basic requirements for flight recorders
3.1 Security requirements
The flight recorder should not impair the airworthiness of the aircraft, whether under normal or malfunctioning conditions. It should be ensured that the information source of the system interface is recorded
Critical flight systems are properly physically and electrically isolated.
3.2 Maintainability requirements
The flight recorder should be easy to maintain to ensure the availability and continued airworthiness of the flight recorder.
3.3 Flame retardancy requirements
In addition to a small amount of materials used for thermal isolation or heat dissipation (such as insulating paint, thermochemical compounds, etc.) and small components that will not significantly support combustion
(Such as handles, fasteners, seals, gaskets and small electronic components), all materials should be flame-retardant materials.
3.4 Fallability requirements
To ensure that the accident investigation authority can read the information stored in the recording medium of the flight recorder through the special method provided by the recorder manufacturer
Information, the flight recorder should meet and pass the following tests.
a) Impact vibration test. The test sample is subjected to impact vibration test along 3 mutually perpendicular directions (six axial directions). Impact energy
Should be greater than or equal to the impact of half a sine wave (the duration is 5 ms ± 1 ms, the peak acceleration of the sine wave should not be less than 1,000 g,
(g is the local gravitational acceleration); the trapezoidal shock wave with the same shock capacity can also be used for testing, and the shock pulse measurement should be
Using calibrated accelerometers and related instruments, the accuracy requires at least a 3 dB response in the range of 5 Hz～250 Hz;
b) Static extrusion test. A static pressure of 4.54 kN is applied to the test sample for a duration of 5 min. For spherical flight records
It needs to test at least 4 times; for a cube-shaped flight recorder, a total of 7 tests are required, including 3 faces and 4 diagonals;
c) High-temperature fire test. The heat flux generated by the fire source used for the test is at least 158 kw/m2.All external surfaces of the test sample (including
Wires) should be exposed to the flame for at least 15 minutes, and the surface temperature of the flame is 1 100 ℃ (the test sample may lead to
As a result, the local flame is cooled, and the turbulence of the air flow will also affect the flame temperature. Therefore, the flame temperature will usually be 950 ℃ ~
1 to 100 ℃). At the same time, the test sample should not be covered in any form during the measurement.
Before the high-temperature fire test, the test sample needs to be pretreated to obtain a stable internal temperature, that is, the test sample is in the standard
The internal temperature after normal operation under atmospheric pressure and 25 ℃±5 ℃ (you can remove the external electronics of the flight recorder storage module in advance)
Components). When the internal temperature difference of the equipment does not exceed 2 ℃/h, the internal temperature is considered stable; when the internal temperature cannot be measured
When measuring, the equipment must experience a stable temperature of at least 2 h.
When the temperature of the largest internal body cannot be measured, 2 hours is considered to be the minimum time for the equipment temperature to stabilize. On record
During normal operation or storage of the system, when the effectiveness of the fire protection material decreases, it should be pre-treated to simulate the effects of aging, such as
By expanding the pressure and temperature cycle.
3.5 Synchronization requirements
When feasible, all aircraft data recorders should refer to a uniform time, such as GPS time.
3.6 Operational requirements
Before the aircraft starts to move on its own power, the flight recorder should start to record data continuously until the aircraft cannot move on its own.
Continue to move under the driving force of the body. Where the electrical system allows, the flight recorder should be checked in the cockpit before the engine is started
The stage begins to record data and continues until the end of the flight and the end of the cockpit inspection stage after the engine is turned off.
3.7 Labeling requirements
Most areas on the outer surface of the flight recorder should be bright orange and sprayed with the black "FLIGHT RECORDER" logo as large as possible;
At the same time, reflective materials are required on the external surface.
3.8 Bit Error Rate Requirements
The bit error rate between the input and output of all data should not exceed 10-5.
3.9 Software Management
All software used by the flight recorder should comply with the relevant requirements in EUROCAE ED-12B, RTCA DO-178B and subsequent versions.
Regulations. Among them, the software used for the data recording function should reach the standard above E level.
4 Performance Specifications of Flight Data Recording System
4.1 Recording equipment
Depending on the type of aircraft, the flight data recording system may include the following equipment.
a) Necessary equipment for acquiring and processing analog and digital sensor signals;
b) A stable recording device should be synchronized with other recording systems on the aircraft and Coordinated Universal Time (UTC);
c) A stable recording medium used to store the recorded data;
d) Data bus or network required for communication between various components of the system.
4.2 Recording medium
The flight data recording system shall use digital means to record and store the signal in the solid-state storage module.
4.3 Recording ability
The flight data recording system must be able to save at least the last 25 hours of flight data of the aircraft, and it should not use data compression technology.
4.4 Recording delay
The recording delay between the acquisition of data and the start of recording of data on the solid-state recording medium cannot exceed 1 s.
4.5 Fault indication
The flight data recording system should have a self-check function and trigger corresponding fault indications.
4.6 Recording requirements
4.6.1 Data should be recorded in accordance with the requirements of Appendix A.
4.6.2 Any new design or operation of the aircraft should be evaluated to determine whether there are specific parameters that need to be added to the record parameters.
Count out, or replace existing parameters.
4.6.3 The recorder shall obtain accurate and reliable information from the data source in both static and dynamic conditions.
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4.7 Erasing protection of recorded data
4.7.1 The flight data recording system should not provide any technical means to erase recorded data.
4.7.2 Appropriate procedures should be established to avoid overwriting recorded data involving aviation unsafe events during aircraft maintenance.
4.8 Function test
The necessary methods or equipment shall be provided to detect whether the recording system is operating normally.
5 Performance specification for cockpit audio recording system
5.1 Recording equipment
Depending on the type of aircraft, the cockpit audio recording system may include the following equipment.
a) Cockpit equipment, including wipe function switch, fault indication device and area microphone with preamplifier;
b) A stable recording device should be synchronized with other recording systems on the aircraft and coordinated universal time (UTC);
c) Technology for converting analog audio signals into digital format;
d) Audio interface equipment, including signal amplifiers, etc.
5.2 Recording method
5.2.1 The cockpit audio recording system should use digital methods to record and store the signal in a stable storage module.
5.2.2 The audio information of the regional microphone needs to be converted into a digital format, and the audio information must be 16 bit, 44.1 kHz, unencrypted, uncompressed, and linear (no
μ-law or a-law) Pulse code modulation (PCM) mode storage.
5.2.3 The audio information in the driver's audio channel should be converted into a digital format and formatted as a 16 bit, 11.025 kHz, 22.050 kHz
Or 44.1 kHz unencrypted, uncompressed linear (no μ-law or a-law) pulse code modulation (PCM) storage.
5.2.4 It is not allowed to use encoding to replace silent segments.
5.3 Recording ability
The cockpit audio recording system should be able to save data records of at least 2 h during the last operation, and should keep different data during the entire recording period.
Channel record information.
5.4 Method of obtaining record information
5.4.1 When obtaining recorded information, the recorded content should not be erased, rewritten or changed.
5.4.2 Using standard computer interfaces and file formats (such as.wav format files) will not damage all undeleted audio.
5.4.3 For severely damaged recorder recording media, the supplier shall provide a method of recovering audio data that has been erased.
The work should be initiated by the accident investigation authority and the recording system should be sent to a specific place.
5.4.4 The decoding of audio information does not require a special key, otherwise it may affect the investigation of the accident investigation authority.
5.5 Recording delay and channel synchronization
5.5.1 Recording delay
The delay of the audio signal from the signal received by the zone microphone to the storage module shall not exceed 50 ms; for other
Channel, the delay from the time the recorder receives the signal input to the recording to the storage module cannot exceed 50 ms.
5.5.2 Channel synchronization
For the recording of each independent channel, during record playback, the relative time difference between channels should not exceed 4 ms during the entire recording process.
5.6 Erase operation
5.6.1 Rules for the use of the after-flight cabin sound erasing function for pilots should be formulated.
5.6.2 After the erase operation is performed, the erased audio data cannot be recovered using conventional playback or copying technology.
5.6.3 The installation of the erasing function should prevent it from being activated during flight, and at the same time, minimize the possibility of accidental activation caused by crash impact.
5.7 Quality and reliability of records
All newly installed cockpit audio recording systems should be played back on the ground to determine their system performance and recording quality (related audio recordings).
For recording quality requirements, see Appendix B).
5.8 Power interruption
After the system power supply is interrupted, the cockpit audio recording system (including all networks and buses, etc.) should meet the following requirements.
a) After the cockpit audio recording system is powered on and the initial logic is established, or after the interruption reaches more than 2 s and the power supply is restored, it should be within 5 s
Start and continue to store the information within, and all built-in test procedures should be completed within 60 s.
b) All available information within 2 s from the beginning of the interruption should be recorded in the storage module.
c) When the power supply returns to normal for 5 s, the power supply interruption below.200 m s should not respond to the cockpit audio recording system,
Zone microphones and cockpit audio recording system control panel (including any interconnected networks, buses, etc.) have any impact.
In the initial 5s period, the energy storage device can be recharged.
5.9 Record evaluation
The recording on each channel should be tested to ensure that all necessary input sources are connected to the cockpit audio recording system.
The recording level and signal quality have reached an acceptable level (see the relevant requirements in Appendix B).
6 Performance Specifications of Airborne Video Recording System
6.1 Recording equipment
Depending on the type of aircraft, the airborne image recording system may include the following equipment.
a) Cockpit recording equipment, including batch erasing function control, failure indication and one or more cameras (image source);
b) Video communication network;
c) Recording equipment synchronized with other airborne recording systems and Universal Coordinated Time (UTC);
d) Interface equipment required for communication between various parts of the system.
6.2 Recording requirements
6.2.1 The image recording system shall use digital methods to record and store data in the recording module.
6.2.2 Regardless of the storage format, the recorded information should be exportable to industry-standard digital formats, and the conversion will not affect
Image quality may cause relative time loss.
6.2.3 Image compression technology can be used to minimize the image recording file capacity.
6.3 Recording capacity
The image recording system can at least retain the recorded data of the last 2 hours of operation.
6.4 Recording delay
The delay from the acquisition of image data by the image sensor to the storage of the data on the recording medium should not exceed 3 s.
6.5 Image compression
6.5.1 The image compression technology is to compress the image recording data into the recording medium, each image (data frame or equivalent)
The compression loss should not cause an image loss of more than 1 s.
6.5.2 Under normal playback conditions, the images recorded on the storage module should be not only a set of data stream images that change over time, but also
Ensure that there is only one image corresponding to a certain moment.
6.6 Image security and encryption
6.6.1 For privacy and security requirements, double encryption or encryption key methods of the image playback system shall be used in the playback of recorded images.
6.6.2 For accident investigation authorities, special techniques can be used to directly play back the images.
6.7 Recording frequency
According to different types of image recording systems, the image information obtained from each sensor should be recorded at least in accordance with Table 1.
6.8 Mass erase
6.8.1 For Type A image recording systems, there should be provisions for the post-flight batch erasure processing function operated by the pilot.
6.8.2 When using category C image recording system instead of flight data recording system to capture parameter data from the instrument display, it should not be captured
The parameter data provided by the device can be mass erased.
Note. After the batch erasing function is applied, the recorded information will be modified, so that the recorded data cannot be directly obtained by ordinary playback or copy technology.
6.9 Optical characteristics of the lens
6.9.1 Spatial resolution
Different types of image recording systems need to be verified with different resolutions. Table 2 shows the types of image recording systems A, B, C, etc.
Resolution.
6.9.2 Depth of Field
According to the type of image recording system, its recording needs to have sufficient depth of field. For B or C type image recording system, the required depth of field
Only the instrument panel (from the farthest to the nearest instrument) is included; however, for the A-type image recording system, the required depth of field must be as large as possible.
Then all the movements in the cockpit are accurately focused.
6.9.3 Field of View
According to the type of image recording system, there should be sufficient field of view, see Table 2.
6.9.4 Contrast
According to the type of image recording system, the contrast between the lines in the test chart should be appropriate. See Table 2 for detailed requirements.
6.9.5 Distortion
In order to make the difference between the lines in the test chart according to the type of the image recording system as shown in Table 2, so as to ensure that the image distortion is minimized.
6.9.6 Digital Artifacts
The types of artifacts caused by distortion and system compression should meet the relevant regulations in Table 2.
7 Performance specification of data link information recording system
7.1 Recording equipment
According to different types of aircraft, the data link information recording system may include the following equipment.
a) A stable recording device should be synchronized with other recording systems on the aircraft and Coordinated Universal Time (UTC);
b) Digital interface equipment suitable for converting data link information into record format;
c) Provide a data bus or network for communication between various parts of the system.
7.2 Recording requirements
7.2.1 The data link recording system shall use digital methods to record and store data in the recording module.
7.2.2 The recording format of each information should be easily identifiable and can be decoded.
7.2.3 Data compression technology is not allowed.
7.3 Recording capacity
7.3.1 The recording system can save all necessary data link information at least within the last 2 hours, and the design of the recording system should consider the
New technologies may need to replace the bus transmission speed and expand the capacity of the recording medium and other factors.
7.3.2 In order to optimize the recording capacity, the data link information should be able to be recorded intermittently, for example, only when there is information communication.
7.4 Data link information access
7.4.1 When obtaining recorded information, the recorded content should not be erased, rewritten or changed.
7.4.2 A standard computer interface can be used to recover all data without loss.
7.4.3 When obtaining record information, it is not necessary to remove the record module from the aircraft installation position.
7.4.4 In the process of reading recorded data, the data link recording system is not required to record at the same time.
7.5 Recording delay
The recording delay of a valid message consisting of 103 ASCII (or equivalent) characters applied to the input of the recording system cannot be
More than 1 s, that is, the time from when the recording system starts receiving data input to when the data is stored in the recording module cannot exceed 1 s.
7.6 Data link applications and services
Regardless of whether automatic or manual methods are used, data link messages should be recorded on the aircraft and transmitted using an independent medium
the way.
7.7 Record content
include.
a) The content of the message issued and received by the pilot;
b) The priority of the message. For example, if a message has an associated priority, the ranking and display of the message may be
Influence by law or transmission;
c) The number of messages in any valid queue, that is, how many messages are received by the aircraft but not displayed to the aircraft at any given time.
How many messages from the crew or pilots have not reached the ground;
d) The display status of each message, that is, the information recorded based on the system construction contains the pilot’s selection status of the message, including
Including the new arrival, opening, acceptance, and rejection of the message.
7.8 Time scale
7.8.1 For each data link message, it should be possible to determine the corresponding time information, with a minimum resolution of 1 s.
7.8.2 Time information should include hours, minutes, seconds, day, month, and year if possible.
7.8.3 Time information can be realized by recording the time identifier of each message or recording the relative time based on the absolute time axis.
7.9 erasure of recorded data
7.9.1 The data link information recording system shall not provide any technical means to erase recorded data.
7.9.2 Appropriate procedures should be established to avoid overwriting recorded data involving aviation unsafe events during aircraft maintenance.
AA
Appendix A
(Normative appendix)
Record parameters
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