RU2715516C1 - Automated expert system for assessing level of safety risks of aircraft of an airline company - Google Patents

Abstract

FIELD: computer equipment.

SUBSTANCE: system comprises a module for identifying a basic address of flight safety indicators of all types of aircraft of an airline, a module for identifying the relative address of aircraft safety risk indicators of a given type, modules for identifying rows and columns of the matrix of barriers preventing hazard factors and parrying intermediate events, module for subroutine calling of elements of barriers for prevention of hazard factors and parrying of intermediate events, safety risks level identification module, module for registration of matrix elements of hazard factors prevention barriers, module for recording elements of matrix of barriers of parrying of intermediate events, module for generation of bytes of alphanumerical indicators of safety risks, module for recording hazards, module for registration of parameters of types of aircrafts of an airline, module for control of completion of procedure of analysis of array of hazard factors with aircrafts of specified type, module for control of completion of procedure for analysis of array of types of aircrafts of an airline.

EFFECT: technical result is wider range of means.

1 cl, 15 dwg, 2 tbl

Description

The invention relates to computer technology, in particular, to an automated expert system for assessing the level of safety risks of airline flights, implementing the use of new information technologies in assessing the level of safety risks.

Currently, the Russian Federation does not have a standard for a safety management system (SMS), and airlines have to develop SMS independently. On the other hand, a modern approach to solving the problem of improving flight safety (BP) provides for the development of an SMS for each airline. At the same time, the basis of the SMS is the process of managing the risk of BP.

Under these conditions, in the absence of a common BP risk management methodology and a lack of guidelines for the development and implementation of methods, there is a wide and subjective interpretation of a number of provisions of the ICAO BP Management Manual (RBM) and the Russian Air Law. This leads to a conflict of priorities, misallocation of the resources of airlines, and, ultimately, does not allow to provide a satisfactory level of BP in the GA of the Russian Federation.

To avoid this, the Government of the Russian Federation by Decree No. 1215 of 11/18/2014 approved the Rules for the development and application of aircraft safety management systems, as well as the collection and analysis of data on hazard and risk factors that pose a threat to the safety of flights of civil aircraft, and the storage of these data and sharing them.

In accordance with this Decision, the SMS is considered as “a set of measures taken to identify potential and actual hazards, to assess the risk of their occurrence, to develop and take corrective actions necessary to maintain an acceptable level of safety, to assess the effectiveness of safety management measures” .

In this case, the hazard factor is “the result of an action or inaction, the circumstance, condition or a combination thereof that affect the safety of civil aircraft,” and the risk is the “predicted likelihood and severity of the consequences of the manifestation of one or more hazard factors”.

Known systems that could be used to solve the problem [1, 2].

The first known system contains an application loading tool, a hosting environment, an authorized administrator, a user interface, an assessment mechanism, an expert data storage unit, a risk optimization mechanism, a control mechanism, and a countermeasure mechanism [1].

A significant drawback of this system is the narrow limitation of safety risk assessments of only software applications and the impossibility of expanding these safety risk assessments for aircraft events.

Another system is known that contains a module for identifying the base address of aircraft operating data for an airline, a module for identifying a relative address for aircraft operating data of the same type, a module for selecting addresses of parameters for the class of special situations, a module for calling the subroutine for calculating the reciprocal of the total flight time, a module for registering parameters for the class of special situations , module for selecting the class of special situations without incidents, module for selecting the base address of the parameters of subclasses of the class of special situations module for recognizing the branch of the procedure for calculating the probabilities of occurrence of special situations, a module for deciding on the level of safety of flights according to the total probabilities of classes of special situations, a module for deciding on a level of safety for flights in terms of the signal probabilities of classes of special situations, a module for identifying signal probabilities of subclasses of a class of special situations, module decision-making on the level of safety of flights according to the signal probabilities of subclasses of the class of special situations, module for monitoring completion procedures for analyzing an array of subclasses of the class of special situations, a module for controlling the completion of the procedure for analyzing an array of classes of special situations [2].

The last of the above technical solutions is closest to the described.

Its disadvantage lies in the limited functionality of the system, due to the fact that a quantitative assessment of the flight safety level of an airline’s aircraft is defined as a combination of the probability (degree of possibility) of a hazardous event and the severity (damage) of its consequences without taking into account the effectiveness of hazard prevention barriers and each of the remaining intermediate events.

The purpose of the invention is to expand the functionality of the system by eliminating the assessment of the flight safety level of aircraft by the probabilities of damage from events and initializing the assessment of the level of safety risks based on the processing of conditional risk indicators of the matrix of safety barriers.

The goal is achieved by  what's in the system  containing a module for identifying the base address of safety risk indicators for all types of airline aircraft,  the information input of which is the first information input of the system,  designed to receive the request codogram from the workstation of the system user,  the synchronizing input of the identification module of the base address of the safety risk indicators of all types of airline aircraft is the first synchronizing input of the system,  intended for receiving synchronization signals of entering the request codogram from the workstation of the system user into the identification module of the base address of the safety risk indicators for all types of airline aircraft,  a module for identifying the relative address of the flight safety risk indicators of a given type,  the first and second information inputs of which are connected to the first and second information outputs of the identification module of the base address of the safety risk indicators for all types of airline aircraft, respectively,  the first synchronizing input of the identification module of the relative address of the flight safety risk indicators of a given type is connected to the synchronizing output of the identification module of the base address of the flight safety risk indicators of all types of airline aircraft,  module for identifying rows and columns of the matrix of barriers to prevent hazards,  the first information and first synchronizing inputs of which are connected to the information and to the synchronizing outputs of the identification module of the relative address of the flight safety indicators of aircraft of a given type, respectively,  the second information input of the module for identifying rows and columns of the matrix of barriers to preventing hazard factors is connected to the third information output of the module for identifying the base address of safety risk indicators for all types of airline aircraft,  module for identifying rows and columns of the matrix of barriers to parry intermediate events,  the information input of which is connected to the first information output of the module for identifying rows and columns of the matrix of barriers to prevent hazards,  safety risk level recognition module,  first,  second,  third,  fourth,  fifth,  sixth,  seventh,  eighth,  the ninth and tenth information inputs of which are connected to the fourth,  fifth  the sixth  the seventh  the eighth  the ninth  tenth  the eleventh  the twelfth and thirteenth information outputs of the identification module of the base address of the safety risk indicators for all types of airline aircraft, respectively,  the first signal output of the safety risk level recognition module is the first signal output of the system,  designed to issue a signal to an automated workstation of a user about an unacceptable level of safety risk for aircraft of the type in question with an existing hazard factor,  the second signal output of the safety risk level recognition module is the second signal output of the system,  designed to issue a signal to the user’s automated workstation about the acceptable level of safety risk for aircraft of the type in question with the existing hazard factor,  the third signal output of the safety risk level recognition module is the third signal output of the system,  designed to issue a signal to an automated workstation of a user of an acceptable level of flight safety risk of the aircraft of the type under consideration with the existing hazard factor,  module for registering elements of the matrix of barriers to prevent hazard factors,  the information input of which is the second information input of the system,  designed to receive codes for digital safety risk indicators,  read from the system server database,  the synchronizing input of the module for registering elements of the matrix of barriers to prevent hazard factors is the second synchronizing input of the system,  intended for receiving synchronization signals of entering codes of digital indicators of safety risks,  read from the system server database,  into the module for registering elements of the matrix of barriers to prevent hazard factors,  the information output of the module for registering elements of the matrix of barriers to prevent hazard factors is connected to the eleventh information input of the module for recognizing the level of safety risks,  and the synchronizing output of the module for registering elements of the matrix of barriers to prevent hazard factors is connected to the synchronizing input of the module for identifying rows and columns of the matrix of barriers to parry intermediate events,  module for registering elements of the matrix of barriers to parry intermediate events,  the information input of which is the third information input of the system,  designed to receive codes of alphabetic indicators of safety risks,  read from the system server database,  the synchronizing input of the module for registering the elements of the matrix of barriers to parry intermediate events is the third synchronizing input of the system,  intended for receiving synchronization signals of entering codes of alphabetic indicators of safety risks,  read from the system server database,  to the module for registering elements of the matrix of barriers to parry intermediate events,  the information and synchronizing outputs of the module for registering elements of the matrix of barriers to parry intermediate events are connected to the twelfth information and synchronizing inputs of the module for recognizing the level of flight safety risks, respectively,  hazard registration module  the information input of which is the fourth information input of the system,  designed to receive hazard codes from an automated workstation of a system user,  the clock input of the hazard registration module is the fourth clock input of the system,  intended for receiving synchronizing signals of entering hazard factor codes from the workstation of the system user into the hazard factor registration module,  the information and synchronization outputs of the hazard factor registration module are connected to the third information and second synchronization inputs of the row and column identification module of the hazard factor prevention barrier matrix, respectively,  module for registering types of airline aircraft  the information input of which is the fifth information input of the system,  designed to receive codes of type parameters of aircraft of an airline from an automated workstation of a system user,  the synchronizing input of the aircraft type parameters registration module is the fifth synchronizing input of the system,  intended for receiving synchronization signals of entering codes of airline type parameters codes from an automated workstation of a system user into the airline type parameters registration module,  the first information and synchronizing outputs of the module for registering the type parameters of aircraft of the airline are connected to the third information and second synchronizing inputs of the module for identifying the relative addresses of the flight safety indicators of aircraft of a given type, respectively,  the second information output of the aircraft type parameters registration module of the airline is connected to the fourth information input of the row and column identification module of the hazard factor prevention barrier matrix,  a control module for completing the analysis of an array of hazard factors with aircraft of a given type,  the first information input of which is connected to the fourteenth information output of the identification module of the base address of the safety risk indicators for all types of airline aircraft,  the second information input of the control module for completing the analysis of the array of hazard factors with aircraft of a given type is connected to the third information output of the module for registering the type parameters of aircraft of the airline,  the first signal output of the control module for completing the analysis of the array of hazard factors with aircraft of a given type is connected to the first installation input of the module for registering elements of the matrix of barriers to prevent hazard factors,  with the first installation input module registration elements of the matrix of barriers to parry intermediate events,  with the first installation input of the module for registering hazard factors and at the same time it is the fourth signal output of the system,  intended for the issuance of a signal for entering the code of the next hazard factor with aircraft of a given type at the user's automated workstation  the second signal output of the control module for completing the analysis of the array of hazard factors with aircraft of a given type is connected to the second installation input of the module for registering elements of the matrix of barriers to prevent hazard factors,  with the second installation input module registration elements of the matrix of barriers to parry intermediate events,  with the second installation input of the module for registering hazard factors and at the same time is the fifth signal output of the system,  designed to issue a signal to the user’s automated workstation for the completion of the analysis of an array of hazard factors with aircraft of a given type,  control module for completing the analysis of an array of types of airline aircraft  the information input of which is connected to the fifteenth information output of the identification module of the base address of the safety risk indicators for all types of airline aircraft,  and the synchronizing input of the control module for completing the analysis of the array of types of aircraft of the airline is connected to the second signal output of the control module for completing the analysis of the array of hazard factors with aircraft of a given type,  the first signal output of the control module for completing the analysis of the array of types of aircraft of the airline is connected to the first installation input of the module for registering the types of aircraft of the airline and is the sixth signal output of the system,  designed to issue to the user's workstation a system of a signal for requesting a code input of the following type of airline aircraft,  the second signal output of the control module for completing the analysis of the array of types of aircraft of the airline is connected to the second installation input of the module for registering the parameters of the types of aircraft of the airline,  with the installation input of the identification module of the base address of the safety risk indicators for all types of airline aircraft and is the seventh signal output of the system,  designed to issue a signal to the user’s automated workstation to complete the analysis procedure for an array of airline types of aircraft,  a module was introduced for calling the subroutine for reading the elements of the matrix of barriers to prevent hazards,  the first and second information and synchronization inputs of which are connected to the first and second information and synchronization outputs of the module for identifying rows and columns of the matrix of barriers to prevent hazard factors, respectively,  the first and second installation inputs of the call module of the subroutine for reading the elements of the matrix of hazards for preventing hazard factors are connected to the first and second signal outputs of the control module for completing the analysis of the array of hazard factors with aircraft of a given type,  the first and second information outputs of the call module of the subroutine for reading the elements of the matrix of barriers to prevent hazard factors are the first and second information outputs of the system,  designed to issue codes of the frequency of occurrence of the hazard factor and codes of the failure frequency of the barriers to prevent hazards to the first and second information inputs of the system database server, respectively,  and the synchronizing output of the call module of the subroutine for reading the elements of the matrix of barriers to prevent hazard factors is the first synchronizing output of the system,  intended for issuing call control signals of the subroutine for reading the elements of the matrix of barriers to prevent hazards to the input of the first channel of the server database system interrupt,  a module for calling the subroutine for reading the elements of the matrix of barriers to parry intermediate events,  the first and second information and synchronization inputs of which are connected to the first and second information and synchronization outputs of the module for identifying rows and columns of the matrix of barriers to parry intermediate events, respectively,  the first and second installation inputs of the call module of the subroutine for reading the elements of the matrix of barriers to parry intermediate events are connected to the first and second signal outputs of the control module of the completion of the analysis of the array of hazard factors with aircraft of a given type,  the first and second information outputs of the call module of the subroutine for reading the elements of the matrix of parry barriers of intermediate events are the third and fourth information outputs of the system, respectively,  designed to issue codes of probable damage from an intermediate event and codes of failure rates of barriers to parry an intermediate event to the third and fourth information inputs of the system database server, respectively,  and the synchronizing output of the call module of the subroutine for reading the elements of the matrix of barriers to parry intermediate events is the second synchronizing output of the system,  intended for issuing call control signals of the subroutine of reading the elements of the matrix of barriers to parry intermediate events to the input of the second channel of the server database system interrupt,  and a module for generating bytes of alphanumeric safety risk indicators,  the first information input of which is connected to the third information output of the module for identifying rows and columns of the matrix of barriers to prevent hazard factors,  the second information input of the module for generating bytes of alphanumeric safety risk indicators is connected to the information output of the module for registering elements of the matrix of barriers to prevent hazard factors,  the third information input of the module for generating bytes of alphanumeric safety risk indicators is connected to the fourth information output of the identification module for the base address of the safety risk indicators for all types of airline aircraft,  and the fourth information input of the module for generating bytes of alphanumeric safety risk indicators is connected to the information output of the module for registering elements of the matrix of barriers to parry intermediate events,  first,  the second and third synchronizing inputs of the module for generating bytes of alphanumeric safety risk indicators are connected to the first,  the second and third signal outputs of the module recognizing the level of safety risks, respectively,  the first and second installation inputs of the byte generation module of alphanumeric safety risk indicators are connected to the first and second installation outputs of the control module to complete the analysis of the array of hazard factors with aircraft of a given type, respectively,  the first information output of the byte generation module of alphanumeric safety risk indicators is the first address output of the system,  intended for issuing byte addresses of alphanumeric safety risk indicators to the address input of the database server,  the second information output of the module for generating bytes of alphanumeric safety risk indicators is the fifth information output of the system,  designed to issue bytes of alphanumeric safety risk indicators to the fifth information input of the system database server,  and the synchronizing output of the byte generation module for alphanumeric safety risk indicators is connected to the synchronizing input of the control module for completing the analysis of the array of hazard factors with aircraft of a given type and is the third synchronizing output of the system,  designed to issue control signals for recording bytes of alphanumeric safety risk indicators to the input of the third channel of the system database server interrupt.

The invention is illustrated by drawings, where in FIG. 1 is a structural diagram of a system; FIG. 2 shows an example of a specific constructive implementation of the identification module of the base address of the safety risk indicators for all types of airline aircraft, FIG. 3 is an example of a specific constructive implementation of a module for identifying a relative address of safety risk indicators for aircraft of a given type, FIG. 4 is an example of a specific constructive implementation of a module for identifying rows and columns of a matrix of barriers to prevent hazard factors, FIG. 5 is an example of a specific constructive implementation of a module for identifying rows and columns of a matrix of barriers to parry intermediate events, FIG. 6 is an example of a specific constructive implementation of a call module of a subroutine for reading elements of a matrix of barriers to prevent hazard factors, FIG. 7 is an example of a specific constructive implementation of a call subroutine module for reading elements of a matrix of barriers to parry intermediate events, FIG. 8 is an example of a specific constructive implementation of a safety risk level recognition module; FIG. 9 is an example of a specific constructive implementation of a module for registering elements of a matrix of barriers to preventing hazard factors, FIG. 10 is an example of a specific constructive implementation of a module for registering elements of a matrix of barriers to parry intermediate events, FIG. 11 is an example of a specific constructive implementation of a module for generating bytes of alphanumeric safety risk indicators; FIG. 12 is an example of a specific constructive implementation of a hazard factor registration module; FIG. 13 is an example of a specific constructive implementation of a module for registering type parameters of aircraft of an airline; FIG. 14 is an example of a specific constructive implementation of a control module for completing an analysis of an array of hazard factors with aircraft of a given type, FIG. 15 is an example of a specific constructive implementation of a control module for completing an analysis of an array of types of airline aircraft.

The system (Fig. 1) contains a module 1 for identifying the base address of the safety risk indicators for all types of airline aircraft, module 2 for identifying the relative address of the safety risk indicators for aircraft of a given type, module 3 for identifying rows and columns of the matrix of barriers to prevent hazard factors, module 4 identification of rows and columns of the matrix of barriers to parry intermediate events, module 5 call subroutine reading elements of the matrix of barriers to prevent factors hazard module 6 call subroutine reading the elements of the matrix of barriers to parry intermediate events, module 7 recognition of the level of safety risk barriers, module 8 registration of the elements of the matrix of barriers to prevent hazards, module 9 registration of the elements of the matrix of barriers of parrying intermediate events, module 10 of generating bytes of alphanumeric indicators safety risks, module 11 registration of hazards, module 12 registration parameters of the types of aircraft of the airline, fashion Only 13 controls the completion of the analysis of an array of hazard factors with aircraft of a given type, module 14 controls the completion of the analysis of an array of types of aircraft of the airline.

In FIG. 1 shows the first 15, second 16, third 17, fourth 18 and fifth 19 information inputs of the system, the first 20, second 21, third 22, fourth 23 and fifth 24 synchronizing inputs of the system, as well as address 25, information 26-30, synchronizing 31 -33 and alarm 34-40 system outputs.

The base address identification module 1 of the safety risk indicators for all types of airline aircraft (Fig. 2) contains a register 45, a decoder 46, a memory module 47 made in the form of read-only memory (ROM), elements 48-50 I, elements 51-52 delays. The drawing also shows information 53, synchronizing 54 and installation 55 inputs, information 71-85 and synchronizing 86 outputs.

Module 2 identifying the relative address of the flight safety risk indicators of a given type (Fig. 3) contains a decoder 90, a memory module 91, made in the form of read-only memory (ROM), adder 92, elements 93-95 AND, element 96 OR, group 97 elements OR, delay elements 98-99. The drawing also shows information 100-102 and synchronizing 103-104 inputs, information 105 and synchronizing 106 outputs.

Module 3 identification of rows and columns of the matrix of barriers to prevent hazard factors (Fig. 4) contains a decoder 110, a memory module 111, made in the form of read-only memory (ROM), adder 112, elements 113-115 AND, element 116 OR, group 117 elements OR, delay elements 118-120.

Module 4 identifying rows and columns of the matrix of barriers to parry intermediate events (Fig. 5) contains a decoder 140, a memory module 141, made in the form of read-only memory (ROM), elements 142-144 And, elements 145-146 delay. The drawing also shows information 147 and synchronizing 148 inputs, information 151-152 and synchronizing 153 outputs.

The module 5 call subroutine reading the elements of the matrix of barriers to prevent hazards (Fig. 6) contains registers 160-161, element 162 OR element 163 delay. The drawing also shows information 164-165, synchronizing 166 and installation inputs 167-168, information 169-170 and synchronizing 171 outputs.

Module 6 of the call subroutine for reading the elements of the matrix of barriers to parry intermediate events (Fig. 7) contains registers 175-176, OR element 177 and delay element 178. The drawing also shows information 179-180, synchronizing 181 and installation inputs 182-183, information 184-185 and synchronizing 186 outputs.

The safety risk level recognition module 7 (FIG. 8) contains comparators 190-200 and OR elements 201-203. The drawing also shows information 204-215 and synchronizing 216 inputs, signal outputs 239-241.

Module 8 registration of the matrix elements of the barriers to prevent hazards (Fig. 9) contains a register 245, an element 246 OR element 247 delay. The drawing also shows information 248, synchronizing 249 and installation inputs 250-251, information 252 and synchronizing 253 inputs.

The module 9 for registering the elements of the matrix of barriers to parry intermediate events (Fig. 10) contains a register 255, an OR element 256, and a delay element 257. The drawing also shows information 258, synchronizing 259 and installation inputs 260-261, information 262 and synchronizing 263 inputs.

Module 10 generating bytes of alphanumeric safety risk indicators (FIG. 11) comprises registers 269-270, multipliers 271-272, adder 273, OR elements 274-275 and delay elements 276-279. The drawing also shows information 280-283, synchronizing 284-286 and installation 287-288 inputs, information 289-290 and synchronizing 291 outputs.

Hazard factor registration module 11 (FIG. 12) comprises a register 300, an OR element 301, and a delay element 302. The drawing also shows information 303, synchronizing 304 and installation inputs 305-306, information 307 and synchronizing 308 outputs.

The airline type parameter registration module 12 (FIG. 13) comprises a register 310, an OR element 311, and a delay element 312. The drawing also shows information 313, synchronizing 314 and installation 315-316 inputs, information 317-319 and synchronizing 320 outputs.

Module 13 for monitoring the completion of the analysis of an array of hazard factors with aircraft of a given type (Fig. 14) contains a counter 350, a comparator 351, a group of 352 OR elements, and a delay element 353. The figure also shows information 354-355 and synchronizing 356 inputs, signal 339 -340 outputs.

The module 14 to control the completion of the analysis procedure for the array of types of aircraft of the airline (Fig. 15) contains a counter 350, a comparator 351, an element 352 delay. The drawing also shows information 353 and synchronizing 354 inputs, signal 357-358 outputs.

All nodes and elements of the system are made on standard potential-pulse elements.

The remote automated workstation (AWP) of the system user consists of a terminal having a screen for displaying the request codogram and system signals, and a personal computer keyboard. The presentation of the readable elements of the matrix of barriers to prevent hazard factors and the matrix of parrying intermediate events is controlled from the server (not shown in the drawing).

The system operates as follows.

The system associates with the airline code a certain memory address of the server’s database, called the base one, starting from which the database’s memory contains a set of safety risk indicators for all the airline’s aircraft (aircraft), divided into groups according to aircraft types so that the address of each group safety risk indicators, called relative, is shifted relative to the base address by an amount corresponding to the type of aircraft of this group.

In the address space of each relative address corresponding to the type of aircraft, the addresses of safety risk indicators are distributed for each hazard factor (FD) that threatens aircraft of this type. Moreover, the relative address of the flight safety risk indicators for each FS is determined by the offset of its address by the amount corresponding to the code of this FS.

To identify the risk of aircraft flight safety, the system associates with each FD the frequency of manifestations of FD and the failure rate of barriers to prevent FD. In this case, the frequency of manifestations of FD is considered as a row, and the failure rate of barriers to prevent FD - as a column of the matrix of barriers to prevent FD [3].

In turn, the system associates the selected numerical value of the failure frequency of the prevention barriers with the correlation between the damage from the most probable outcome of the intermediate event (PS) and the frequency of failure of the PS barriers, considered below as the row and column of the matrix of PS barriers, respectively.

By calling a standard program, the elements of the matrices are uniquely determined by row and column. In our case, each matrix element is a conditional indicator of risk. In the matrix of barriers to preventing FD, the conditional risk indicator is expressed by numbers from “1” to “5”, and in the matrix of barriers to parry FS, in capital letters from “A” to “E”.

The combined processing of digital and alphanumeric safety risk indicators allows not only to generate an alphanumeric byte of the safety risk and record it at the address generated by the system, but also to recognize its level for deciding on a given FD.

These procedures are performed for all hazards for all types of aircraft of the airline.

To start the system, the user at his workplace generates a request codogram, which indicates: the code (identifier) of the airline, the code of the type of aircraft, the code of the initial (starting) hazard factor for aircraft of a given type, the code of the total number of analyzed hazard factors for aircraft of a given type, code of the total number of types of airline aircraft, digital codes from 1 to 5 conditional indicators of safety risks in the matrix of barriers to prevent hazards and letter codes A, B, C, D, conventional indicators of safety risks in the matrix parry barriers intermediate events (Table 1):

The generated code from the automated workstation of the user of the system is fed to the information input 15 of the system, from where it goes to the information input 53 of module 1 for identifying the base address of safety risk indicators for all types of airline aircraft and is entered into register 45 with a synchronizing pulse supplied to synchronizing input 54 of module 1 from the synchronizing input 20 of the system.

The code (identifier) of the airline from the output 56 of the register 45 is fed to the input of the decoder 46. The decoder 46 decrypts the code of the airline and generates at one of its outputs a high potential supplied to the corresponding inputs of elements 48-50 I. For definiteness, we assume that the high potential from the output the decoder 46 will open the element 50 And one input.

In this case, the synchronizing pulse from the synchronizing input 54 of the module 1, delayed by the delay element 51 for the response time of the register 45 and the decoder 46, passes through the open element 50 And to the read input of a fixed cell of a read-only memory (ROM) 47.

A fixed cell in ROM 47 contains the code for the base address of the airline’s flight safety risk indicators, starting from which the system’s flight risk code for the airline’s aircraft risk indicators for all types of operating aircraft is stored in the system’s database.

The code (identifier) of the type of aircraft specified by the codogram from the information output 72 of module 1 is supplied to the information input 100 of module 2 for identifying the relative address of the flight safety risk indicators of a given type, passes through the OR elements of group 97, and enters the decoder 90. Decoder 90 decodes the aircraft type code and generates at one of its outputs a high potential supplied to the corresponding inputs of elements 93-95 I. For definiteness, let us assume that a high sweat tial output from the decoder 90 will open member 95 and one input.

In this case, the synchronizing pulse from the output of the delay element 51 is delayed by the delay element 52 for the response time of the ROM 47 of module 1 and the decoder 90 of module 2 and from the synchronizing output 86 of module 1 is supplied to the synchronizing input 103 of module 2, passes through the OR element 96, and through one input element 95 And to the read input of a fixed cell read-only memory (ROM) 91.

In a fixed cell of the ROM 91, the offset code of the relative address of the airline's flight safety risk indicators is stored for the type of aircraft whose code was received at the information input 100 of module 2.

The code for shifting the relative address of the airline's flight safety risk indicators for a given type of aircraft, read from the ROM 91, is supplied to one information input of the adder 92, the other information input 102 of which is the code of the base address of the airline's flight safety risk indicators from the information output of module 71 1.

By the synchronizing pulse from the output of the OR element 96, delayed by the delay element 98 for the read time of the fixed cell ROM 91, the adder 92 forms the relative address of the safety risk indicators for aircraft of a given type, issued from the information output 105 of module 2 to the information input 124 of module 3 identification of rows and columns of the matrix of barriers to prevent hazards.

The code of the first hazard factor (FD) requested by the codogram with the aircraft of a given type from the information output 73 of module 1 is supplied to the information input 121 of module 3, passes through the elements of group 117 and goes to the input of the decoder 110. The decoder 110 decrypts the code of the requested FD and generates one of its outputs has a high potential coming to the corresponding inputs of elements 113-115 I. For definiteness, let us assume that a high potential from the output of the decoder 110 will open the 115 And one input.

The synchronizing pulse from the output of the delay element 98 of module 2 is delayed by the delay element 99 for the response time of the adder 92 and from the synchronizing output 106 of module 2 is sent to the synchronizing input 125 of module 3, the element passes OR, is delayed by the delay element 118 for the duration of the operation of the decoder 110, passes through element I 115, which is open at one input, and is fed to the read input of a fixed cell of ROM 111. The fixed cell of ROM 111 contains the offset code for the storage address of the safety risk indicator of this FD, the code of the frequency of occurrence of the hazard factor and the code of the failure rate of the barriers to prevent the FD:

The offset code for the storage of the risk indicator FD is fed to one information input of the adder 112, to the other information input 124 of which, from the information output 105 of module 2, a code of the relative address of the flight safety risk indicators for the aircraft of a given type is supplied.

By the synchronizing pulse from the output of the delay element 118, delayed by the delay element 119 for the time of reading the fixed cell ROM 111, the adder 112 generates a relative storage address of the safety risk indicators for aircraft of a given type at a given FD, issued from the information output 132 of module 3 to the information input 283 of register 270 of module 10 for generating an byte of the alphanumeric safety risk indicator of a given FD.

The DF manifestation frequency code defining the matrix row of the DF prevention barriers from the information output 130 of module 3 is fed to the information input 164 of the register 160 of the module 5, and the DF prevention barrier failure code that defines the column of the DF prevention barriers matrix from the information output 131 of the module 3 is fed to information input 165 of register 161 of module 5.

In addition, the code of the failure frequency of the barriers to prevent DF from the information output 131 of the module 3 is fed to the information input 147 of the module 4 for identifying rows and columns of the matrix of parry barriers of intermediate events and is input to the decoder 140. The decoder 140 decrypts the code of the frequency of failures of the barriers to prevent the DF and generates one of its outputs has a high potential supplied to the corresponding inputs of elements 142-144 I. For definiteness, let us assume that high potential from the output of the decoder 140 will open ele ent 144 And on one input, waiting on the other input for a pulse to be received at the synchronizing input 148 of module 4.

In parallel, the clock from the output of the delay element 119 is delayed by the element 120 for the duration of the operation of the adder 112 and, coming from the synchronizing output 133 of the module 3 to the synchronizing input 166 of the module 5, provides the entry of the row code and column code of the matrix of barriers to prevent FD in registers 160 and 161 respectively.

In addition, the same clock pulse from the input 166 of the module 5 is delayed by the element 163 for the duration of the operation of the registers 160 and 161, and through the clock output 171 of the module 5 is issued to the clock output 31 of the system, from where it is fed to the input of the first channel of the server interrupt.

With the arrival of this impulse, the server polls its information inputs and takes from the system information output 26 the code of the row of the matrix of barriers to prevent the DF, issued from the output of the register 160 of the module 5, and from the information output 27 of the system, the code of the column matrix of the barriers to prevent the FD, issued from the output of the register of the 161 module 5, and returns from its database to the information input 16 of the system the correspondence in the form of an element of the matrix of barriers to prevent FD, represented by the code of the digital indicator of the risk of flight safety when given Mr. FO.

From the information input 16 of the system, the code of the digital safety risk indicator for a given FD is fed to the information input 248 of the register 245 of module 8 for recording the digital safety risk indicator for a given FD, where it is entered by the server synchronizing pulse received at the system input 21.

The code of the digital indicator of the safety risk of flight at a given FD from the information output 252 of module 8 is fed to the information input 206 of the module 7 for recognizing the level of safety risk and to the information input 280 of the module 10.

At the same time, the server clock from the input 249 of module 8 is delayed by the delay element 247 for the response time of the register 245 and from the synchronizing output 253 of the module 8 is supplied to the synchronizing input 148 of the module 4 for identifying rows and columns of the matrix of parry barriers of intermediate events, it is delayed by the delay element 145 for the response time of the decoder 140 and passes through the And 144 element open at one input to the read input of the fixed cell of the ROM 141.

The fixed cell of the ROM 141 contains a code of probable damage from an intermediate event and a code of the failure frequency of parry barriers of an intermediate event:

The code of probable damage from an intermediate event, specifying the row of the matrix of barriers to parry the PS, from the information output 151 of module 4 is fed to the information input 179 of the register 175 of module 6, and the code of the frequency of failure of the barriers to parry PS, which defines the column of the matrix of the barriers of parrying PS, from the information output 152 of the module 4 is fed to the information input 180 of the register 176 of the module 65

In parallel, the clock from the output of the delay element 145 is delayed by the element 146 for the time of reading the fixed cell of the ROM 141 and, coming from the synchronizing output 153 of the module 4 to the synchronizing input 181 of the module 6, provides the entry of the row code and the column code of the PS barrier matrix in the registers 175 and 176, respectively.

In addition, the same clock pulse from the input 181 of the module 6 is delayed by the element 178 for the response time of the registers 175 and 176, and through the clock output 186 of the module 6 is issued to the clock output 32 of the system, from where it enters the input of the first channel of the server interrupt.

With the arrival of this impulse, the server polls its information inputs and picks up the PS parry barrier matrix matrix row code output from the register output 175 of module 6 from the system information output 28, and the PS parry barrier matrix column code output from the module register 176 output from the system information output 29 6, and returns from its database to the information input 17 of the system the correspondence in the form of an element of the matrix of barriers to parry the PS, represented by the code of the alphabetic indicator of the risk of flight safety for a given FD.

From the information input 17 of the system, the code of the alphanumeric safety risk indicator for a given FD is fed to the information input 258 of register 255 of module 9 for registering the alphabetic safety risk indicator for a given FD, where it is entered by the server synchronizing pulse received at the system input 22.

The code of the alphanumeric safety risk indicator for a given FD from the information output 262 of module 9 is fed to the information input 204 of module 7 and to information input 282 of module 10.

At the same time, the server clock from the input 259 of module 9 is delayed by the delay element 257 for the response time of register 255 and from the synchronizing output 263 of module 9 is fed to the synchronizing input 216 of module 7, starting the procedure for recognizing the level of risk indicator by comparing the codes at the inputs of comparators 190-200.

According to the synchronizing pulse at the input 216 of module 7, the code of the alphanumeric risk indicator at the information input 204 of the comparator 190, read as an element of the MS parry matrix, is compared with the symbol code “E” received at the information input 205 of the comparator 190 from the information output 76 of module 1.

If the codes at the inputs of the comparator 190 coincide, then at its output 217 a signal is generated that, going to the synchronizing input of the comparator 191, allows the comparison of the code of the digital risk indicator, read as an element of the FO prevention matrix to its information input 206, with the digit code “3 "Taken at its information input 207 from the information output 83 of module 1.

If the code of the digital risk indicator at the input 206 of the comparator 191 turns out to be greater than or equal to 3, then at the output 219 of the comparator 191 a signal is generated that, passing through the OR element 201, passes to the synchronizing output 239 of module 7 and then from the signal output 34 of the system to the user's workstation the signal “Unacceptable risk level of flight safety of the aircraft of the type under consideration with the existing FD” is removed.

If the code of the digital risk indicator at the input 206 of the comparator 191 turns out to be less than 3, then the signal is generated at the output 220 of the comparator 191. This signal, passing through the OR element 202, passes to the synchronizing output 240 of the module 7 and then from the signal output of the system 35 to the user's workstation The signal “Permissible level of flight safety risk of the aircraft of the type under consideration with the available FS” is removed.

If the codes at the inputs of the comparator 190 do not match, then the signal is generated at its output 218. This signal, arriving at the synchronizing input of the comparator 192, allows the code to compare the alphabetic risk indicator, read as an element of the FD prevention matrix to its information input 204, with the code symbol "D", received at the information input 208 of the comparator 192 from the information output 77 of the module 1.

If the codes at the inputs of the comparator 192 coincide, then at its output 221 a signal is generated that, going to the synchronizing input of the comparator 193, allows the code to compare the digital risk indicator, read as an element of the FD prevention matrix to its information input 206, with the digit code “3 "Taken at its information input 207 from the information output 83 of module 1.

If the code of the digital risk indicator at the input 206 of the comparator 193 turns out to be more than 3, then at the output 223 of the comparator 193 a signal is generated that, passing through the OR element 201, passes to the synchronizing output 239 of module 7 and then is removed from the system signal output 34 to the system user workstation signal “Unacceptable risk level of flight safety of the aircraft of the type under consideration with the available FD”.

If the code of the digital risk indicator at the input 206 of the comparator 193 turns out to be less than or equal to 3, then the signal is generated at the output 224 of the comparator 193. This signal, passing through the OR element 202, passes to the synchronizing output 240 of the module 7 and then from the signal output 35 of the system to AWS of the system user removes the signal "Permissible level of flight safety risk of the aircraft of the type under consideration with the available FD".

If the codes at the inputs of the comparator 192 do not match, then the signal is generated at its output 222. This signal, arriving at the synchronizing input of the comparator 194, allows the code to compare the letter of the risk indicator, read as an element of the FD prevention matrix to its information input 204, with the code symbol "C", received at the information input 209 of the comparator 194 from the information output 78 of the module 1.

If the codes at the inputs of the comparator 194 coincide, then at its output 225 a signal is generated that, going to the synchronizing input of the comparator 195, allows the code to compare the digital risk indicator, read as an element of the FD prevention matrix to its information input 206, with the digit code “5 "Taken at its information input 210 from the information output 81 of module 1.

If the code of the digital risk indicator at the input 206 of the comparator 195 turns out to be 5, then a signal is generated at the output 227 of the comparator 195, which, passing through the OR element 202, passes to the synchronizing output 240 of module 7 and then is removed from the system signal output 35 to the system user workstation signal “Permissible level of the flight safety risk of the aircraft of the type under consideration with the available FS”.

If the code of the digital risk indicator at the input 206 of the comparator 193 turns out to be less than 5, then the signal is generated at the output 228 of the comparator 195. This signal, arriving at the synchronizing input of the comparator 197, allows comparing the code of the digital risk indicator, considered as an element of the FD prevention matrix on its information input 206, with the digit code “1”, received at its information input 211 from the information output 85 of module 1.

If the code of the digital risk indicator at the input 206 of the comparator 193 is greater than 1, then the signal is generated at the output 229 of the comparator 197. This signal, passing through the OR element 202, passes to the synchronizing output 240 of the module 7 and then from the signal output of the system 35 to the user's workstation The signal “Permissible level of flight safety risk of the aircraft of the type under consideration with the available FS” is removed.

If the code of the digital risk indicator at the input 206 of the comparator 193 turns out to be 1, then the signal is generated at the output 230 of the comparator 197. This signal, passing through the OR element 203, passes to the synchronizing output 241 of the module 7 and then from the signal output of the system 36 to the user's workstation the system receives a signal “An acceptable level of flight safety risk of the aircraft of the type under consideration with the available federal flag”

If the codes at the inputs of the comparator 194 do not match, then the signal is generated at its output 226. This signal, arriving at the synchronizing input of the comparator 196, allows the code to compare the letter of the risk indicator, read as an element of the FD prevention matrix to its information input 204, with the code symbol "B", received at the information input 212 of the comparator 196 from the information output 79 of the module 1.

If the codes at the inputs of the comparator 196 are the same, then at its output 231 a signal is generated that, going to the synchronizing input of the comparator 199, allows the code to compare the digital risk indicator, read as an element of the FD prevention matrix to its information input 206, with the digit code “2 "Adopted at its information input 213 from the information output 84 of module 1.

If the code of the digital risk indicator at the input 206 of the comparator 193 turns out to be more than 2, then the signal is generated at the output 233 of the comparator 199. This signal, passing through the OR element 202, passes to the synchronizing output 240 of the module 7 and then from the signal output of the system 35 to the user's workstation The signal “Permissible level of flight safety risk of the aircraft of the type under consideration with the available FS” is removed.

If the code of the digital risk indicator at the input 206 of the comparator 193 turns out to be less than or equal to 2, then the signal is generated at the output 234 of the comparator 199. This signal, passing through the OR element 203, passes to the synchronizing output 241 of the module 7 and then from the signal output 36 of the system to AWS of the user of the system, the signal “An acceptable level of the flight safety risk of the aircraft of the type under consideration with the existing FD” is removed.

If the codes at the inputs of the comparator 196 do not match, then the signal is generated at its output 232. This signal, arriving at the synchronizing input of the comparator 198, allows the code to compare the alphabetic risk indicator, read as an element of the FD prevention matrix to its information input 204, with the code symbol "A", received at the information input 214 of the comparator 198 from the information output 80 of the module 1.

If the codes at the inputs of the comparator 198 are equal, at its output 235 a signal is generated that, when transmitted to the synchronizing input of the comparator 200, allows the comparison of the code of the digital risk metric, read as an element of the MS parry matrix to its information input 206, with the symbol code “4”, adopted at its information input 215 from the information output 82 of the module 1.

If the code of the digital risk indicator at the input 206 of the comparator 200 turns out to be greater than or equal to 4, then the signal is generated at the output 237 of the comparator 200. This signal, passing through the OR element 202, passes to the synchronizing output 240 of the module 7 and then from the signal output of the system 35 to the AWP The user of the system is removed the signal “Permissible level of flight safety risk of the aircraft of the type under consideration with the available FD”.

If the code of the digital risk indicator at the input 206 of the comparator 193 is less than 4, then the signal is generated at the output 238 of the comparator 200. This signal, passing through the OR element 203, passes to the synchronizing output 241 of module 7 and then from the signal output 36 of the system to the user's workstation The system receives a signal “An acceptable level of flight safety risk of the aircraft of the type under consideration with the available financial information”.

The receipt on the user's workstation of the signal “Permissible level of flight safety risk of the aircraft of the type under consideration with the existing financial condition” means that a thorough investigation should be carried out in the federal state, review existing barriers and add new ones.

When the user of the signal system “Unacceptable level of flight safety risk of the aircraft of the type under consideration with the existing FD” arrives at the AWP, the user of the system takes emergency measures in the form of stopping the operation of the requested type of aircraft and terminating flights until the FD is completely neutralized, etc.

The receipt on the user's workstation of the signal “An acceptable level of flight safety risk of the aircraft of the type under consideration with an available financial statement” means that the resulting risk assessment and the hazard factor that generates it must be entered into the system database for further use and then continue with the scheduled routine safety work airline flight operations.

Each pulse from the synchronizing outputs 239-241 of module 7 is sent to the corresponding synchronizing inputs 284-286 of the module 10 for generating the byte of the alphanumeric safety risk metric, the OR element 274 passes, and arriving at the synchronizing input of the multiplier 271, it allows multiplying the digital risk metric code by its information input 280 with a code of 4, received from the information output 82 of module 1.

The result of multiplication in the form of a code of a quadruple digital risk indicator from the information output of the multiplier 271 is fed to one information input of the multiplier 272, on the other information input of which is the code of the digit 4, received from the information input 281 of the module 10.

By the synchronizing pulse from the output of the OR element 274, delayed by the delay element 276 for the response time of the multiplier 271 and applied to the synchronizing input of the multiplier 272, the multiplier 272 multiplies the codes received at its information inputs with the result of the multiplication by one information input of the adder 273. On the arc information input 282 of the adder 273 serves code alphabetic risk indicator from the information output 262 of module 9.

According to the synchronizing pulse from the output of the delay element 276, delayed by the element 277 for the duration of the multiplier 272 and applied to the synchronizing input of the adder 273, an byte alphanumeric safety risk indicator of the specified FD is generated in the adder 273.

Formed in the adder 273 bytes of the alphanumeric safety risk indicator of the specified FD is fed to the information input of the register 269, where it is entered by the synchronizing pulse supplied to its synchronizing input from the output of the delay element 277, the delayed delay element 278 for the operation time of the adder 273.

The same synchronizing pulse from the output of the delay element 278 enters into the register 270 the storage address code of the identified byte of the alphanumeric safety risk indicator of the specified FD, issued from the information output 290 of the module 10 to the address output 25 of the system, is delayed by the delay element 279 for the response time of the registers 269 -270, passes to the synchronizing output 291 of the module 10 and from the synchronizing output 33 of the system enters the input of the second interrupt channel of the system database server.

With the arrival of this impulse, the server switches to the recording routine at the address on the address output 25 of the system, issued from the information output 290 of register 270, the byte code of the alphanumeric safety risk indicator of the specified FD from the information output 30 of the system, issued from the information output 289 of the register 269.

The same pulse from the synchronizing output 291 of the module 10 is supplied to the synchronizing input 336 of the module 13 for monitoring the completion of the analysis of the array of hazard factors with aircraft of a given type and, increasing the counting input of the meter 330, increments it.

Counter 330 cumulatively counts the number of processed FDs of the considered aircraft type and transmits its contents each time to one information input of the comparator 331. The code of the total number of all FDs of the considered aircraft type is received from the information output 74 of module 1 to another information input 334 of the comparator 331.

The clock pulse from the clock input 336 of the module 13, delayed by the element 333 at the time of the increment of the counter 330, arriving at the clock input of the comparator 331, allows the comparison of codes received at its information inputs.

If the contents of the counter 330 will be less than the code of the total number of all FDs for the considered type of aircraft to be processed in the system, a signal is generated at the output 337 of the comparator 331. If the content of the counter is equal to the code of the total number of all FDs of the considered type of aircraft to be processed in the system, then the signal is generated at the output 338 of comparator 331.

Since in our case only the first unit was entered into the counter 330, which recorded the completion of the system’s processing of the first FD for the aircraft of the type in question, therefore, the contents of the counter 330 will be much less than the code of the total number of all events of the considered aircraft type to be processed in the system, and, therefore, output 337 of comparator 331 will generate a signal.

This signal from the output 339 of the module 13 is supplied:

- to the installation input 167 of module 5, passes through the OR element 162 and enters the installation input of the registers 160-161, resets their contents to zero and thereby prepares them for a new operation cycle;

- to the installation input 182 of module 6, passes through the OR element 177 and enters the installation input of registers 175-176, resets their contents to zero and thereby prepares them for a new operation cycle;

- to the installation input 287 of module 10, the OR element 275 passes and enters the installation input of registers 269-270, resets their contents to zero and thereby prepares them for a new operation cycle;

- to the installation input 250 of module 8, the OR element 246 passes and enters the installation input of the register 245, resets its contents to zero and thereby prepares it for a new operation cycle;

- to the installation input 260 of module 9, the OR element 256 passes and enters the installation input of the register 255, resets its contents to zero and thereby prepares it for a new operation cycle;

- to the installation input 305 of module 11, the OR element 301 passes and enters the installation input of the register 300, resets its contents to zero and thereby prepares it for a new operation cycle.

The same signal from the output 339 of the module 13 is removed in the form of a request signal "Enter the code of the next FD", which from the signal output 37 of the system is issued to the user's workstation.

Having received this request, the user of the system from his workplace sends the code for the next FD for the aircraft of the type in question to the information input 18 of the system, from where it goes to the information input 303 of the register 300 of module 11, where it is entered by the synchronizing pulse supplied to the synchronizing input 304 of module 11 with synchronizing input 23 of the system.

The received code of the next FD for the aircraft of the considered type from the information output 307 of module 11 is sent to the information input 122 of module 3, passes through the elements of group 117 and goes to the input of the decoder 110. The decoder 110 decrypts the code of the next FD and generates a high potential at one of its outputs arriving at the corresponding inputs of elements 113-115 I. For definiteness, suppose that high potential from the output of the decoder 110 will open element 114 AND at one input, waiting for the signal to arrive at the synchronizing stroke module 126 3.

The start pulse of the next FD code processing cycle for the aircraft of the type under consideration is a synchronizing pulse at the synchronizing input 304 of module 11, which is delayed by the delay element 302 for the response time of register 300 and from the synchronizing output 308 of module 11 is supplied to the synchronizing input 126 of module 3, passes through element 116 OR, it is delayed by the delay element 118 for the response time of the decoder 110 and through the element 114 open through one input, it arrives at the read input of a fixed cell th memory (ROM) 111.

The fixed cell ROM 111 contains the offset code of the storage address of the safety risk indicator at the specified next FD, the code of the frequency of occurrence of the hazard factor and the code of the failure rate of the FD prevention barriers.

The offset code for the storage of the risk indicator FD is fed to one information input of the adder 112, to the other information input 124 of which, from the information output 105 of module 2, a code of the relative address of the flight safety risk indicators for the aircraft of a given type is supplied.

By the synchronizing pulse from the output of the delay element 118, delayed by the delay element 119 for the time of reading the fixed cell ROM 111, the adder 112 generates a relative storage address of the safety risk indicators for aircraft of a given type at a given FD, issued from the information output 132 of module 3 to the information input 283 of register 270 of module 10.

The DF manifestation frequency code defining the matrix row of the DF prevention barriers from the information output 130 of module 3 is fed to the information input 164 of the register 160 of the module 5, and the DF prevention barrier failure code that defines the column of the DF prevention barriers matrix from the information output 131 of the module 3 is fed to information input 165 of register 161 of module 5.

In addition, the code of the failure frequency of the barriers to prevent DF from the information output 131 of the module 3 is fed to the information input 147 of the module 4 for identifying rows and columns of the matrix of parry barriers of intermediate events and is input to the decoder 140. The decoder 140 decrypts the code of the frequency of failures of the barriers to prevent the DF and generates one of its outputs has a high potential supplied to the corresponding inputs of elements 142-144 I. For definiteness, let us assume that high potential from the output of the decoder 140 will open ele ent 144 And on one input, waiting on the other input for a pulse to be received at the synchronizing input 148 of module 4.

In parallel, the clock from the output of the delay element 119 is delayed by the element 120 for the duration of the operation of the adder 112 and, coming from the synchronizing output 133 of the module 3 to the synchronizing input 166 of the module 5, provides the entry of the row code and column code of the matrix of barriers to prevent FD in registers 160 and 161 respectively.

In addition, the same clock pulse from the input 166 of the module 5 is delayed by the element 163 for the duration of the operation of the registers 160 and 161, and through the clock output 171 of the module 5 is issued to the clock output 31 of the system, from where it is fed to the input of the first channel of the server interrupt.

With the arrival of this impulse, the server polls its information inputs and takes from the system information output 26 the code of the row of the matrix of barriers to prevent the DF, issued from the output of the register 160 of the module 5, and from the information output 27 of the system, the code of the column matrix of the barriers to prevent the FD, issued from the output of the register of the 161 module 5, and returns from its database to the information input 16 of the system the correspondence in the form of an element of the matrix of barriers to prevent FD, represented by the code of the digital indicator of the risk of flight safety when given Mr. FO.

From the information input 16 of the system, the code of the digital indicator of the risk of flight safety for a given FD is fed to the information input 248 of the register 245 of module 8, where it is entered by the synchronizing pulse of the server received at the input of the system 21.

The code of the digital indicator of the safety risk of flight at a given FD from the information output 252 of module 8 is fed to the information input 206 of the module 7 for recognizing the level of safety risk and to the information input 280 of the module 10.

At the same time, the server clock from the input 249 of module 8 is delayed by the delay element 247 for the response time of the register 245 and from the synchronizing output 253 of the module 8 is supplied to the synchronization input 248 of the module 4, it is delayed by the delay element 145 for the response time of the decoder 140 and passes through one open input element 144 And the read input of a fixed cell ROM 141.

The fixed cell ROM 141 contains a code of probable damage from an intermediate event and a code of the failure rate of the parry barriers of the intermediate event.

The code of probable damage from an intermediate event, specifying the row of the matrix of barriers to parry the PS, from the information output 151 of module 4 is fed to the information input 179 of the register 175 of module 6, and the code of the frequency of failure of the barriers to parry PS, which defines the column of the matrix of the barriers of parrying PS, from the information output 152 of the module 4 is fed to the information input 180 of the register 176 of the module 65

In parallel, the clock from the output of the delay element 145 is delayed by the element 146 for the time of reading the fixed cell of the ROM 141 and, coming from the synchronizing output 153 of the module 4 to the synchronizing input 181 of the module 6, provides the entry of the row code and the column code of the PS barrier matrix in the registers 175 and 176, respectively.

In addition, the same clock pulse from the input 181 of the module 6 is delayed by the element 178 for the response time of the registers 175 and 176, and through the clock output 186 of the module 6 is issued to the clock output 32 of the system, from where it enters the input of the first channel of the server interrupt.

With the arrival of this impulse, the server polls its information inputs and picks up the PS parry barrier matrix matrix row code output from the register output 175 of module 6 from the system information output 28, and the PS parry barrier matrix column code output from the module register 176 output from the system information output 29 6, and returns from its database to the information input 17 of the system the correspondence in the form of an element of the matrix of barriers to parry the PS, represented by the code of the alphabetic indicator of the risk of flight safety for a given FD.

From the information input 17 of the system, the code of the alphanumeric safety risk indicator for a given FD is fed to the information input 258 of the register 255 of module 9, where it is entered by the synchronizing pulse of the server, which is input to the system 22.

The code of the alphanumeric safety risk indicator for a given FD from the information output 262 of module 9 is fed to the information input 204 of module 7 and to information input 282 of module 10.

At the same time, the server clock from the input 259 of module 9 is delayed by the delay element 257 for the response time of the register 255 and from the synchronizing output 263 of module 9 is supplied to the synchronizing input 216 of module 7, starting the procedure for recognizing the level of the safety risk indicator by comparing the code of the alphabetic safety risk indicator when the specified FD at the information input 204 of the comparator 190 with the codes of the letters E, D, C, B, A at the information inputs 205,208, 209,212 and 214 of the comparators 190, 192, 194, 196 and 198 of module 7, respectively, and the code Frova indicator of risk for a given FD on information input 206 of the module 7 with the codes of numbers 3, 5, 1, 2 and 4 in the information inputs 207, 210, 211, 213 and 215 of comparators 191, 192, 194, 196 and 198 of the module 7 respectively.

As already shown above, module 7 recognizes the level of safety risk by issuing a signal to one of the synchronizing outputs 239-241 of module 7.

Each pulse from the synchronizing outputs 239-241 of module 7 is sent to the corresponding synchronizing inputs 284-286 of module 10, the OR element 274 passes, and arriving at the synchronizing input of the multiplier 271, it allows multiplying the code of the digital risk indicator at its information input 280 with the code of digit 4 on its information input 281 received from the information output 80 of module 1.

The result of multiplication in the form of a code of a quadruple digital risk indicator from the information output of the multiplier 271 is fed to one information input of the multiplier 272, on the other information input of which is the code of the digit 4, received from the information input 281 of the module 10.

By the synchronizing pulse from the output of the OR element 274, delayed by the delay element 276 for the response time of the multiplier 271 and applied to the synchronizing input of the multiplier 272, the multiplier 272 multiplies the codes received at its information inputs with the result of the multiplication by one information input of the adder 273. On the arc information input 282 of the adder 273 serves code alphabetic risk indicator from the information output 262 of module 9.

According to the synchronizing pulse from the output of the delay element 276, delayed by the element 277 at the time of the operation of the multiplier 272 and applied to the synchronizing input of the adder 273, an alphanumeric safety risk indicator of the specified FD is generated in the adder 273.

Formed in adder 273, an alphanumeric safety risk indicator of a given FD is fed to the information input of register 269, where it is entered by a clock pulse supplied to its clock input from the output of delay element 277, delayed delay element 278 for the operation time of adder 273.

The same synchronizing pulse from the output of the delay element 278 enters into the register 270 the storage address code of the identified alphanumeric safety risk indicator of the specified FD, issued from the information output 290 of the module 10 to the address output 25 of the system, is delayed by the delay element 279 for the response time of the registers 269- 270, passes to the synchronizing output 291 of the module 10 and from the synchronizing output 33 of the system is fed to the input of the second interrupt channel of the system database server.

With the arrival of this impulse, the server switches to the recording routine at the address on the address output 25 of the system, issued from the information output 290 of register 270, the byte code of the alphanumeric safety risk indicator of the specified FD from the information output 30 of the system, issued from the information output 289 of the register 269.

The same pulse from the synchronizing output 291 of the module 10 is supplied to the synchronizing input 336 of the module 13 and, arriving at the counting input of the counter 330, increments it.

Counter 330 cumulatively counts the number of processed FDs of the considered aircraft type and transmits its contents each time to one information input of the comparator 331. The code of the total number of all FDs of the considered aircraft type is received from the information output 74 of module 1 to another information input 334 of the comparator 331.

The clock pulse from the clock input 336 of the module 13, delayed by the element 333 at the time of the increment of the counter 330, arriving at the clock input of the comparator 331, allows the comparison of codes received at its information inputs.

If the contents of the counter 330 will be less than the code of the total number of all FDs for the considered type of aircraft to be processed in the system, a signal is generated at the output 337 of the comparator 331. If the content of the counter is equal to the code of the total number of all FDs of the considered type of aircraft to be processed in the system, then the signal is generated at the output 338 of comparator 331.

The described process of sequential processing of FS in aircraft of a given type, including identification of rows and columns of the matrix of prevention and parry barriers, reading of their elements, which are digital and letter indicators of flight safety risks, respectively, recognition of their level with the subsequent generation of a byte of alphanumeric indicator of flight risk and writing it to the system server database memory will continue until all FDs with aircraft of this type are processed, the total number of Overhead toryh given request is accepted and the information input module 334 with data output 13 of the module 74 1.

As soon as the contents of the counter 330 of the module 13, supplied to one information input of the comparator 331, is equal to the code of all FD received on its other information input 334 from the information output 74 of module 1, the signal generated by the comparator at its output 338, firstly, immediately fed to the installation input of the meter 330, returning it to its original state.

Secondly, the same signal from the synchronizing output 340 of the module 13 is supplied:

- to the installation input 168 of module 5, passes through the OR element 162 and enters the installation input of the registers 160-161, resets their contents to zero and thereby prepares them for a new operation cycle;

- to the installation input 183 of module 6, passes through the OR element 177 and enters the installation input of registers 175-176, resets their contents to zero and thereby prepares them for a new operation cycle;

- to the installation input 288 of module 10, an OR element 275 passes through and enters the installation input of registers 269-270, resets their contents to zero and thereby prepares them for a new operation cycle;

- to the installation input 251 of module 8, the OR element 246 passes and enters the installation input of the register 245, resets its contents to zero and thereby prepares it for a new operation cycle;

- to the installation input 261 of module 9, the OR element 256 passes and enters the installation input of the register 255, resets its contents to zero and thereby prepares it for a new operation cycle;

- to the installation input 306 of module 11, the OR element 301 passes and enters the installation input of the register 300, resets its contents to zero and thereby prepares it for a new operation cycle.

In addition, this signal from the synchronizing output 340 of the module 13 is supplied to the synchronizing input 354 of the module 14 to control the completion of the analysis of the array of types of aircraft of the airline and arriving at the counter input of the counter 350, it increments.

The counter 350 of module 14 cumulatively counts the number of processed types of airline aircraft and transmits its contents each time to one information input of the comparator 351. To another information input 353 of the comparator 351, the code of the total number of all types of aircraft to be processed in the system is supplied from the information output 75 of module 1 .

The clock pulse from the clock input 354 of the module 14, delayed by the delay element 352 for the increment time of the counter 350, arriving at the clock input of the comparator 351, allows the comparison of the codes received at its information inputs.

If the contents of the counter 350 will be less than the code of the total number of all types of airline aircraft, then the output 355 of the comparator 351 produces a signal. If the contents of the counter is equal to the code of the total number of all types of aircraft of the airline, then the signal is generated at the output 356 of the comparator 351.

Since in our case only the first unit was entered into the counter 350, which recorded the completion of the processing of only the first type of aircraft by the system, therefore, the contents of the counter 350 will be much less than the code of the total number of all types of aircraft to be processed in the system, and, therefore, at the output 355 comparator 351 a signal will be generated.

This signal from the output 357 of the module 14 is supplied to the installation input 315 of the module 12, passes through the OR element 311, and enters the installation input of the register 310, resets its contents to zero and thereby prepares it for a new operation cycle.

The same signal from the output 357 of the module 14 is removed in the form of a request signal "Enter the parameters of the next type of aircraft", which from the signal output 39 of the system is issued to the user's workstation.

Having received this request, the user of the system from his workplace sends the parameter code for the next aircraft type (start code ФО, code number for the ФО and aircraft type identifier) to the information input 19 of the system, from where it goes to the information input 313 of the register 310 of module 12, where it is entered a synchronizing pulse supplied to the synchronizing input 314 of the module 12 from the synchronizing input 24 of the system.

The code of the starting FD from the aircraft of the following type from the information output 318 of module 12 is sent to the information input 123 of module 3, passes through the OR elements of group 117 and is input to the decoder 110. The decoder 110 decodes the FD code and generates a high potential at one of its outputs to the respective inputs of elements 113-115 I. For definiteness, suppose that a high potential from the output of the decoder 110 will open the element 113 And one input, waiting for a pulse from the output of the delay element 118.

The code of the number of all FDs from the aircraft of the next type from the information output 319 of module 12 is sent to the information input 335 of module 13, passes through the OR elements of group 332, and enters one information input of the comparator 331 of module 13.

The code for the next aircraft type from the information output 317 of module 12 is sent to the information input 101 of module 2, passes through the OR elements of group 97, and enters the input of the decoder 90. The decoder 90 decodes the code for the next type of aircraft and generates a high potential at one of its outputs. to the respective inputs of elements 93-95 I. For definiteness, suppose that high potential from the output of the decoder 90 will open element 93 And at one input, waiting for a pulse to arrive at the synchronizing input 104 of module 2.

The pulse of the start of the FD risk assessment procedure for each of the following aircraft types is the pulse at the synchronizing input 314 of module 12, which is delayed by the delay element 312 for the response time of register 310 and from the synchronizing output 320 of module 12 is sent to the synchronizing input 104 of module 2, passes through the OR element 96, and through element 73 open to one input, and to the read input of another fixed cell of read-only memory (ROM) 91. containing a completely different offset code for the relative address of the indicator n of the airline flight safety risks, defining a completely different memory area with an unchanged base address of the airline flight safety risk indicators at the information output 71 of module 1.

In the future, the entire process of the sequential transition of processing from one FD to another with the assessment of risk indicators for each FD for aircraft of each type will continue until the FD of all types of aircraft are processed, the total number of which is set by the request code and removed from the information output of module 75 1 to the information input 353 of the comparator 351 of the module 14.

In this case, the contents of the counter 350 of the module 14, supplied to another information input of the comparator 351, will be equal to the code of the total number of all types of aircraft, and therefore, a signal will be generated at the output 356 of the comparator 351, which is immediately fed to the installation input of the counter 350, returning it to the original state.

Further, the same signal from the synchronizing output 358 of the module 14 is supplied to the installation input 316 of the module 12, passes through the OR element 311, and enters the installation input of the register 310, resets its contents to zero and thereby prepares it for a new operation cycle.

The same signal from the synchronizing output 358 of module 14 is supplied to the installation input 55 of module 1 and is supplied to the installation input of register 45, resets its contents to zero and thereby prepares it for a new operation cycle.

The same signal from the output 358 of the module 14 is removed in the form of a signal "Assessment of the level of safety risks for all types of airline aircraft completed", which from the signal output 40 of the system is issued to the user's workstation.

A comparative analysis of the features of a specific design of the claimed technical solution and technical solution in [2] can be presented in the form of Table 2

In accordance with Table 2, the initialization of processing instead of the ratio of the number of special situations of one class (or class subclass) of special situations to the total flight time of aircraft of one type of conditional digital indicators of flight safety risks as elements of a matrix of barriers to the prevention of hazard factors and conditional alphabetic indicators of flight safety as elements of the matrix of barriers to parry intermediate events allows us to take into account in assessing the level of safety risks not only damage from the resulting consequences, but also the effectiveness of safety barriers that counter and counter their manifestation.

Thus, the introduction of new nodes and modules and new constructive connections made it possible to significantly expand the system’s functionality by initializing an assessment of the airline’s flight safety risk level under existing hazard factors using conditional digital safety risk indicators of the hazard prevention matrix of barriers and conditional alphabetic safety risk indicators matrices of parry barriers of the remaining intermediate events.

Sources of information taken into account when compiling the application materials:

1. RF patent No. 2500070, IPC H04L 1/00, 2013.

2. RF patent No. 2578756, IPC: G06F 17/40, G06F 12/02, G08B 23/00, M. G05D 1/00, G05B 23/02, B64D 45/00, 2016 (prototype).

3. Sharov V.D. Experience in developing a risk management system in an airline // XII All-Russian Meeting on Management Problems of VSPU-2014, Moscow, June 16-19, 2014: Transactions. [Electronic resource] M .: Institute for Management Problems named after V.A. Trapeznikova RAS, 2014, 9616 p. Electron, text given. (1074 file: 537 MB), 1 electron. opt. disc (DVD-ROM), ISBN 978-5-91450-151-5. State registration number: 0321401153. - S. 8228-8239.

Claims (1)

Automated expert system for assessing the level of airline flight safety risks,  containing a module for identifying the base address of safety risk indicators for all types of airline aircraft,  the information input of which is the first information input of the system,  designed to receive the request codogram from the workstation of the system user,  the synchronizing input of the identification module of the base address of the safety risk indicators of all types of airline aircraft is the first synchronizing input of the system,  intended for receiving synchronization signals of entering the request codogram from the workstation of the system user into the identification module of the base address of the safety risk indicators for all types of airline aircraft,  a module for identifying the relative address of the flight safety risk indicators of a given type,  the first and second information inputs of which are connected to the first and second information outputs of the identification module of the base address of the safety risk indicators for all types of airline aircraft, respectively,  the first synchronizing input of the identification module of the relative address of the flight safety risk indicators of a given type is connected to the synchronizing output of the identification module of the base address of the flight safety risk indicators of all types of airline aircraft,  module for identifying rows and columns of the matrix of barriers to prevent hazards,  the first information and first synchronizing inputs of which are connected to the information and to the synchronizing outputs of the identification module of the relative address of the flight safety indicators of aircraft of a given type, respectively,  the second information input of the module for identifying rows and columns of the matrix of barriers to preventing hazard factors is connected to the third information output of the module for identifying the base address of safety risk indicators for all types of airline aircraft,  module for identifying rows and columns of the matrix of barriers to parry intermediate events,  the information input of which is connected to the first information output of the module for identifying rows and columns of the matrix of barriers to prevent hazards,  safety risk level recognition module,  first,  second,  third,  fourth,  fifth,  sixth,  seventh,  eighth,  the ninth and tenth information inputs of which are connected to the fourth,  fifth  the sixth  the seventh  the eighth  the ninth  tenth  the eleventh  the twelfth and thirteenth information outputs of the identification module of the base address of the safety risk indicators for all types of airline aircraft, respectively,  the first signal output of the safety risk level recognition module is the first signal output of the system,  designed to issue a signal to an automated workstation of a user about an unacceptable level of safety risk for aircraft of the type in question with an existing hazard factor,  the second signal output of the safety risk level recognition module is the second signal output of the system,  designed to issue a signal to the user’s automated workstation about the acceptable level of safety risk for aircraft of the type in question with the existing hazard factor,  the third signal output of the safety risk level recognition module is the third signal output of the system,  designed to issue a signal to an automated workstation of a user of an acceptable level of flight safety risk of the aircraft of the type under consideration with the existing hazard factor,  module for registering elements of the matrix of barriers to prevent hazard factors,  the information input of which is the second information input of the system,  designed to receive codes for digital safety risk indicators,  read from the system server database,  the synchronizing input of the module for registering elements of the matrix of barriers to prevent hazard factors is the second synchronizing input of the system,  intended for receiving synchronization signals of entering codes of digital indicators of safety risks,  read from the system server database,  into the module for registering elements of the matrix of barriers to prevent hazard factors,  the information output of the module for registering elements of the matrix of barriers to prevent hazard factors is connected to the eleventh information input of the module for recognizing the level of safety risks,  and the synchronizing output of the module for registering elements of the matrix of barriers to prevent hazard factors is connected to the synchronizing input of the module for identifying rows and columns of the matrix of barriers to parry intermediate events,  module for registering elements of the matrix of barriers to parry intermediate events,  the information input of which is the third information input of the system,  designed to receive codes of alphabetic indicators of safety risks,  read from the system server database,  the synchronizing input of the module for registering the elements of the matrix of barriers to parry intermediate events is the third synchronizing input of the system,  intended for receiving synchronization signals of entering codes of alphabetic indicators of safety risks,  read from the system server database,  to the module for registering elements of the matrix of barriers to parry intermediate events,  the information and synchronizing outputs of the module for registering elements of the matrix of barriers to parry intermediate events are connected to the twelfth information and synchronizing inputs of the module for recognizing the level of flight safety risks, respectively,  hazard registration module  the information input of which is the fourth information input of the system,  designed to receive hazard codes from an automated workstation of a system user,  the clock input of the hazard registration module is the fourth clock input of the system,  intended for receiving synchronizing signals of entering hazard factor codes from the workstation of the system user into the hazard factor registration module,  the information and synchronization outputs of the hazard factor registration module are connected to the third information and second synchronization inputs of the row and column identification module of the hazard factor prevention barrier matrix, respectively,  module for registering types of airline aircraft  the information input of which is the fifth information input of the system,  designed to receive codes of type parameters of aircraft of an airline from an automated workstation of a system user,  the synchronizing input of the aircraft type parameters registration module is the fifth synchronizing input of the system,  intended for receiving synchronization signals of entering codes of airline type parameters codes from an automated workstation of a system user into the airline type parameters registration module,  the first information and synchronizing outputs of the module for registering the type parameters of aircraft of the airline are connected to the third information and second synchronizing inputs of the module for identifying the relative addresses of the flight safety indicators of aircraft of a given type, respectively,  the second information output of the aircraft type parameters registration module of the airline is connected to the fourth information input of the row and column identification module of the hazard factor prevention barrier matrix,  a control module for completing the analysis of an array of hazard factors with aircraft of a given type,  the first information input of which is connected to the fourteenth information output of the identification module of the base address of the safety risk indicators for all types of airline aircraft,  the second information input of the control module for completing the analysis of the array of hazard factors with aircraft of a given type is connected to the third information output of the module for registering the type parameters of aircraft of the airline,  the first signal output of the control module for completing the analysis of the array of hazard factors with aircraft of a given type is connected to the first installation input of the module for registering elements of the matrix of barriers to prevent hazard factors,  with the first installation input module registration elements of the matrix of barriers to parry intermediate events,  with the first installation input of the module for registering hazard factors and at the same time it is the fourth signal output of the system,  intended for the issuance of a signal for entering the code of the next hazard factor with aircraft of a given type at the user's automated workstation  the second signal output of the control module for completing the analysis of the array of hazard factors with aircraft of a given type is connected to the second installation input of the module for registering elements of the matrix of barriers to prevent hazard factors,  with the second installation input module registration elements of the matrix of barriers to parry intermediate events,  with the second installation input of the module for registering hazard factors and at the same time is the fifth signal output of the system,  designed to issue a signal to the user’s automated workstation for the completion of the analysis of an array of hazard factors with aircraft of a given type,  control module for completing the analysis of an array of types of airline aircraft  the information input of which is connected to the fifteenth information output of the identification module of the base address of the safety risk indicators for all types of airline aircraft,  and the synchronizing input of the control module for completing the analysis of the array of types of aircraft of the airline is connected to the second signal output of the control module for completing the analysis of the array of hazard factors with aircraft of a given type,  the first signal output of the control module for completing the analysis of the array of types of aircraft of the airline is connected to the first installation input of the module for registering the types of aircraft of the airline and is the sixth signal output of the system,  designed to issue to the user's workstation a system of a signal for requesting a code input of the following type of airline aircraft,  the second signal output of the control module for completing the analysis of the array of types of aircraft of the airline is connected to the second installation input of the module for registering the parameters of the types of aircraft of the airline,  with the installation input of the identification module of the base address of the safety risk indicators for all types of airline aircraft and is the seventh signal output of the system,  designed to issue a signal to the user’s automated workstation to complete the analysis procedure for an array of airline types of aircraft,  characterized in  that the system contains a module for calling the subroutine for reading the elements of the matrix of barriers to prevent hazards,  the first and second information and synchronization inputs of which are connected to the first and second information and synchronization outputs of the module for identifying rows and columns of the matrix of barriers to prevent hazard factors, respectively,  the first and second installation inputs of the call module of the subroutine for reading the elements of the matrix of hazard prevention factors barriers are connected to the first and second signal outputs of the control module of the completion of the analysis of the array of hazard factors with aircraft of a given type,  the first and second information outputs of the call module of the subroutine for reading the elements of the matrix of barriers to prevent hazard factors are the first and second information outputs of the system,  designed to issue codes of the frequency of occurrence of the hazard factor and codes of the failure frequency of the barriers to prevent hazards to the first and second information inputs of the system database server, respectively,  and the synchronizing output of the call module of the subroutine for reading the elements of the matrix of barriers to prevent hazard factors is the first synchronizing output of the system,  intended for issuing call control signals of the subroutine for reading the elements of the matrix of barriers to prevent hazards to the input of the first channel of the server database system interrupt,  a module for calling the subroutine for reading the elements of the matrix of barriers to parry intermediate events,  the first and second information and synchronization inputs of which are connected to the first and second information and synchronization outputs of the module for identifying rows and columns of the matrix of barriers to parry intermediate events, respectively,  the first and second installation inputs of the call module of the subroutine for reading the elements of the matrix of barriers to parry intermediate events are connected to the first and second signal outputs of the control module of the completion of the analysis of the array of hazard factors with aircraft of a given type,  the first and second information outputs of the call module of the subroutine for reading the elements of the matrix of parry barriers of intermediate events are the third and fourth information outputs of the system, respectively,  designed to issue codes of probable damage from an intermediate event and codes of failure rates of barriers to parry an intermediate event to the third and fourth information inputs of the system database server, respectively,  and the synchronizing output of the call module of the subroutine for reading the elements of the matrix of parry barriers of intermediate events is the second synchronizing output of the system,  intended for issuing call control signals of the subroutine of reading the elements of the matrix of barriers to parry intermediate events to the input of the second channel of the server database system interrupt,  and a module for generating bytes of alphanumeric safety risk indicators,  the first information input of which is connected to the third information output of the module for identifying rows and columns of the matrix of barriers to prevent hazard factors,  the second information input of the module for generating bytes of alphanumeric safety risk indicators is connected to the information output of the module for registering elements of the matrix of barriers to prevent hazard factors,  the third information input of the module for generating bytes of alphanumeric safety risk indicators is connected to the fourth information output of the identification module for the base address of the safety risk indicators for all types of airline aircraft,  and the fourth information input of the module for generating bytes of alphanumeric safety risk indicators is connected to the information output of the module for registering elements of the matrix of barriers to parry intermediate events,  first,  the second and third synchronizing inputs of the module for generating bytes of alphanumeric safety risk indicators are connected to the first,  the second and third signal outputs of the module recognizing the level of safety risks, respectively,  the first and second installation inputs of the byte generation module of alphanumeric safety risk indicators are connected to the first and second installation outputs of the control module to complete the analysis of the array of hazard factors with aircraft of a given type, respectively,  the first information output of the byte generation module of alphanumeric safety risk indicators is the first address output of the system,  intended for issuing byte addresses of alphanumeric safety risk indicators to the address input of the database server,  the second information output of the module for generating bytes of alphanumeric safety risk indicators is the fifth information output of the system,  designed to issue bytes of alphanumeric safety risk indicators to the fifth information input of the system database server,  and the synchronizing output of the byte generation module for alphanumeric safety risk indicators is connected to the synchronizing input of the control module for completing the analysis of the array of hazard factors with aircraft of a given type and is the third synchronizing output of the system,  designed to issue control signals for recording bytes of alphanumeric safety risk indicators to the input of the third channel of the system database server interrupt.

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