Provisions Concerning Acceptance For Flights

Original Language Title: Noteikumi par gaisa kuģa atzīšanu par derīgu lidojumiem

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Read the untranslated law here: https://www.vestnesis.lv/ta/id/139856

Cabinet of Ministers Regulations No. 573, Riga, 11 July 2006 (pr. No 37 20. §) rules for aircraft acceptance for flights Issued in accordance with the law "on the air" of article 16 i. General questions 1. determines the order in which the aircraft is recognised as valid for flights, and procedures for the issue and revoke the certificate for validity of aircraft flights and extend its validity period. 2. these provisions shall apply to the Latvian Civil Aviation aircraft registered aircraft that meets the criteria referred to in the European Parliament and of the Council of 15 July 2002, Regulation (EC) No 1592/2002 on common rules in the field of civil aviation and establishing a European Aviation Safety Agency (hereinafter Regulation No 1592/2002) (II) of the annex. 3. the competent authority of this provision and the Commission of 24 September 2003 Regulation (EC) No 1702/2003 laying down implementing rules for the certification of aircraft and related products, parts and appliances, airworthiness and environmental requirements, as well as of design and production organisations, in matters within the scope of the national agency of Civil Aviation Agency "(hereinafter referred to as the Civil Aviation Agency). 4. The rules referred to in paragraph 2 of the air operations in the territory of the Republic of Latvia made is allowed when: 4.1 amateur built aircraft, which is planned to offer the countries of the European economic area market, complies with this provision listed in annex 1. the continuing airworthiness of the aircraft;
4.2. the aircraft complies with the other Member States of the European economic area, flew the validity of requirements applicable to the aircraft or aircraft type;
4.3. the aircraft was issued a certificate of fitness for the flights. 5. in order to implement this provision in paragraph 9 and 19 requirements and pulled dad that the aircraft complies with Regulation No 1592/2002 annex II "C" and "E" in subparagraph these requirements, the Civil Aviation Agency consulted independent experts for an opinion on the matter. Expert opinion is not binding on the Civil Aviation Agency. 6. in paragraph 5 of these provisions that the expert opinion is not necessary if there is any other European economic area Member State notified body issued a document certifying aircraft or aircraft type compliance with this provision in point 4.2. II. Certificate for aircraft flights service validity 7. for a certificate concerning the validity of the flights, the aircraft owner or operator shall submit to the appropriate Civil Aviation Agency application (annex 2) and the application of the annex (annex 3). These documents include: 7.1. documents certifying the aircraft compliance with this provision, the bottom paragraph 4.1 and 4.2 in the airworthiness requirements;
7.2. aircraft flight manual or equivalent document for the file;
7.3. the mass of the aircraft and centre of gravity position supporting doc file;
7.4. the report on the inspection of the aircraft flight (new aircraft);
7.5. documents certifying that the aircraft is taken for all maintenance work (according to the technical documentation of the operation) and mandatory modifications, as well as take into account the State of the manufacturer and the manufacturer's mandatory instructions;
7.6. documents certifying that the aircraft, its engine, Assembly and components with a limited life is sufficient resource balance. 8. for reasons of safety of Civil Aviation, the Agency may request this rule 7.4. review also referred to the service of the former aircraft. 9. After all this rule 7. receipt of documents referred to in paragraph 1 of the Civil Aviation Agency to carry out the inspection of the aircraft, which includes a Visual inspection of the external and the internal, as well as documentation and aircraft equipment. In the course of the inspection of the aircraft is fixed in the Protocol of the inspection. 10. If the aircraft is detected during inspections deficiencies or if the documentation submitted for the aircraft is incomplete, make the relevant entries in the Protocol and inform the viewing aircraft owners or operators. 11. If within six months of the aircraft owner or operator referred to in the Protocol of the inspection prevents deficiencies and submit all the necessary documents, inspection of the aircraft are not. 12. When the aircraft while viewing notes that the aircraft and its documentation complies with the airworthiness requirements tation!, view recommendations recorded in the issue of a certificate for validity of aircraft flights. 13. Civil Aviation Agency after this provision referred to in paragraph 12 of the report of inspection shall be issued by the aircraft owner or operator standard certificate for validity of aircraft flights (annex 4) or special certificate for validity of aircraft flights (annex 5). The two certificate validity period is one year. 14. the standard certificate for validity of flight of the aircraft shall be issued to aircraft for which the aircraft is approved type design. 15. Special concerning the certificate validity issued to aircraft flight in which there have been individual aircraft conformity assessment. 16. With the aircraft, which has been issued that certificate referred to in point 15, flights can be made only in the territory of the Republic of Latvia for non-commercial purposes. The Civil Aviation Agency, given the aircraft's design and parameter characteristics, you can also specify other restrictions. 17. The provisions referred to in paragraph 13 of the certificate during a flight in an aircraft. III. Certificate on the validity of the extension and cancellation of flights 18. To extend the standard certificate validity of the aircraft flew tions or special certificates for aircraft flights validity validity period, the aircraft owner or operator concerned 30 days before the expiry date of the bass in the envelope are present in the Civil Aviation Agency submission (annex 6). The application shall be accompanied by the following: 18.1. Overview of aircraft maintenance work carried out in the period from the issue of the licence or previous extended the term of validity of the day;
18.2. documents showing details of aircraft Modifi cations and carried out repairs, as well as all the works mentioned in the mandatory airworthiness maintenance instructions;
18.3. documents certifying that the aircraft, its components and assemblies with limited duration is sufficient resource balance. 19. by paragraph 18 of these rules of receipt of documents in Civil Aviation Agency to carry out inspections of the aircraft in accordance with these rules 9, 10 and 11. 20. In order to assess compliance with the airworthiness of the aircraft, the Civil Aviation Agency may require to take control of the aircraft in flight. 21. With the aircraft, which issued a special certificate for air flights, the validity of the provisions referred to in paragraph 20 of the flight controls to be performed at least every three years. 22. When the aircraft while viewing notes that the aircraft and its documentation complies with the airworthiness requirements tation!, view recorded in the recommendation to extend the passport validity of aircraft flights a validity period of one year. 23. on the basis of this provision, paragraph 22 minutes of viewing, the Civil Aviation Agency takes a decision on the standard certificate validity of the aircraft flights or special passport the validity of aircraft flying in the extension of the period of validity of one year. 24. The provisions referred to in paragraph 13 of the cards cancelled Civil Aviation Agency law "For aviation" in article 19 in those cases. IV. Permission to carry a special flight 25. If the aircraft is not in force, the provisions of the certificate referred to in paragraph 13 or if it does not comply with airworthiness requirements, the Civil Aviation Agency issued a special flight permits, to: 25.1. the aircraft could take a flight to its maintenance, Modifi cations, repair or conservation site, if the work is not the location of the aircraft;
25.2. to perform aircraft assessment of compliance with airworthiness requirements;
25.3. aircraft have been imported or exported;
25.4. aircraft evacuated from areas where there are exceptional circumstances. 26. in order to obtain permission for conducting a special flight, the aircraft owner or operator shall submit to the appropriate Civil Aviation Agency submissions. The application shall state: 26.1. aircraft owner or operator name (name), a personal code (registration number) and residential address (legal address);
26.2. aircraft type, serial number, national mark and registration mark;
26.3. the purpose of the flight;
26.4. the flight route.
26.5. flight require aircraft crew;
16.5. detailed information on non-compliance with airworthiness requirements;
16.6. operating limits that the aircraft owner or operator considers necessary for safe flight. 27. following the provisions referred to in paragraph 26 of document receipt Civil Aviation Agency shall check the documents submitted and, if necessary, the appropriate aircraft. 28. If the aircraft, due to its non-compliance with this rule 4.1 the requirements referred to in paragraph below, is able to perform safe flight, the Civil Aviation Agency issued a special flight permit and the authorisation shall specify the to the flight restrictions. 29. If with the aircraft, which the Civil Aviation Agency has issued these rules permit referred to in paragraph 28, the flight is carried out outside the territory of the Republic of Latvia made by the aircraft owner or operator prior to taking a flight gets permission from the appropriate foreign competent authorities, above which the territory will be made in flight. V. export a certificate relating to the validity of the aircraft flight 30. If the Civil Aviation Agency excludes the aircraft of the Republic of Latvia to the Civil aircraft register and the aircraft are intended for export to another country, the Civil Aviation Agency, on request, issue the aircraft export certificate to show that the aircraft complies with the Republic of Latvia the applicable airworthiness requirements and airworthiness of the importing country's requirements, if any. 31. aircraft export certificate issued by the Civil Aviation Agency after the aircraft owner or operator's receipt of a written application and these rules 9, 10 and 11 of the aircraft mentioned in the survey. 32. If inspection of the aircraft is made 90 days prior to the aircraft owner or operator's receipt of the written application, the examination of the aircraft did not carry out. 33. aircraft export certificate shall state the airworthiness of the aircraft position on the date of issue of the certificate. 34. aircraft export certificate does not give the right to operate the aircraft. Prime Minister a. Halloween traffic Minister k. Peters annex 1: Cabinet of Ministers of 11 July 2006, regulations no 573 aircraft airworthiness requirements 1. flight characteristics, stability and handling 1.1. aircraft designer or Builder for each aircraft type or elaborate instructions: 1.1.1. flights. At that point the aircraft or types of aircraft technical specifications, operational conditions and limitations; 1.1.2. the airworthiness of the aircraft maintenance (including maintenance). 1.2. The aircraft in all phases of flight must be such that it will not pass beyond the arbitrary flight operating restrictions laid down in the instructions. Piloting the aircraft characteristics must be such that it would be acceptable for beginner amateur pilot well. Piloting the aircraft must be simple taking off, maneuvering and landing. Aircraft piloting methods must not conflict with the accepted methods of piloting. 1.3. The aircraft must comply with the following speed limits: 1.3.1. Abruption speed off in – not less than 1.2 iekritien speeds (Vatr. ≥ 1.2 Viekr.); 1.3.2. the speed before landing-not less than 1.3 iekritien speeds (≥ 1.3 Vpnol. Viekr); 1.3.3. the landing speed-not less than 0.95 iekritien speeds (≥ 0.95 Viekr Vnol.); 1.3.4. cruising speed-not less than 1.3 iekritien speeds (≥ 1.3 Vpnol. Viekr). 1.4. Iekritien speed (Viekr.) – the speed at which arises intense air flow norāvum signs on the wing, in the form of, for example, warning and management of the design of the handle trepidation, parašutēšan aircraft. If iekritien is not for iekritien speed can take the smallest aircraft flight speed without heeling that matches the control handle extreme deviation smallest speed position, the engine working the flight idle mode. Iekritien is typical of the sinking the bow of the aircraft without tilting, followed by speed increase. If this does not happen, a pilot must feel the signs of the coming of iekritien. 1.5. To ensure that the aircraft engine stopping in case the pilot can nolīdzsvar the aircraft stabilized in flight and make travelling safe in the stranger away. 1.6. The aircraft must be such as to: 1.6.1. stop-it could make a pilot that doesn't have high mastery; 1.6.2. the landing pilot could take without increased concentration; 1.6.3. the settlement should not need good weather; 1.6.4. it ieskrienot and after landing a steady maintain a certain direction, without trends diverge. 1.7. The aircraft vertical speed by detachment from the ground must not be less than 1.5 m/sec, but estimated the height of the obstacle at the end of the runway must not be less than 10 m aircraft structure must be such that it would be possible to take off or landing at airports with a concrete or asphalt surface of the runway, as well as the aerodromes without artificial surface of the runway, if its strength is less than 5 kg/cm2. 1.8. The longitudinal static stability of the aircraft should be able to take the following disturbance agents in prevention alone to return to the nolīdzsvarot position (relative to the surge of speed and angle) without pilot intervention. 1.9. Route static stability of the aircraft should be manifested in the ability of independent exit slip if the aircraft direction corner returns to neutral. 1.10. A transverse static stability must take the aircraft's ability to lift the deviation in the case of the wing to the ground nosvērušo. 1.11. The aircraft banked must change according to the direction the aircraft steering movements and should be direct depending on them. Large slip angle on the Steering direction of the pedals may not be reversible. 1.12. The forces applied to the aircraft control levers and pedals must be: 1.12.1. tangāž-from 2.5 kg (continued) up to 25 kg (temporarily); 1.12.2. banked from 1.5 kg to 15 kg (continued) (temporarily); 1.12.3. the course-from 3 kg up to 50 kg (continued) (temporarily). 2. strength 2.1. Flight over the circle with heel that is not greater than 35 °, allowed to aircraft operating overloading is not more than 3 g (g-free fall acceleration) and not less than 1.5 g, if the safety factor is 1.5. More complex flights can be performed by aircraft with a maximum overload is less than 6 g. Main elements of the air force (the connection node part of the installation, the spar, engine mounts, the control surface, corner suspension Assembly, cast, ropes and savilktņ) the recommended safety factor is 3. calculated overload and load is determined by multiplying the running load with overload and safety factor. 2.2. the pilot of the aircraft seat belt system, as well as cargo mounting that can injure the pilot must be capable of operating overload 9 g longitudinal and transverse +/-2.5 g. 2.3. The aerodynamic of the aircraft steering mounting surfaces must be calculated node overpressure, not less than 20 g. 3. Organization 3.1. If the design of the aircraft did not ensure the safety of the aircraft the pilot a complete or partial rollover case, aircraft must be equipped with a circular bar of security that excludes the possibility of injury to the pilot. Calculated aircraft complete overpressure in the event of rollover must be 3 g 3.2. Air Force elements must be designed so that the plane of rotation of the propeller is the crew of the aircraft, fuel tanks and pipelines. The aircraft's structure prohibited to provide engines, fuel tanks and the aircraft position over existing cargo aircraft crew members. 3.3. aircraft crew members seats on the aircraft must be equipped with the waist and shoulder belts, which switches guarantee a secure grip and is easy to open. 3.4. Aircraft with two or more engines, their positions should be designed so that if one of the engines stopped, the pilot, using aerodynamic control, to prevent any deviation of the aircraft from its normal position. 3.5. the space between aircraft propeller blade tip and ground any chassis damping capacity, must be not less than 150 mm. Space between the propeller aircraft and aircraft construction must be not less than 25 mm. 4. Construction 4.1 All aircraft design elements be of industrial izgat's vote and their physical-mechanical characteristics must comply with the approved motor voltage level. Of unknown origin, the use of components in the construction of aircraft. 4.2. If the aircraft used in the construction of wooden parts, they must be made to them from taisnšķiedr wood free of knots, fungi, mold and degradation and decay characteristics. 4.3. All aircraft parts and compartments, which can accumulate moisture, be provided with drainage at the lowest place. 4.4. All structural components of the aircraft, made of wood, with a protective coating to prevent wood decay. The design of the aircraft's metal parts should be coated with an anti-corrosion coating. 4.5. Air Force elements of the structure may not be cracks, fissures and other mechanical damage. Aircraft structure must be such that, if necessary, be it the main element force Visual inspection. 4.6. use of curved pipe air force elements and control systems is only permitted if their use is justified, targeted and meets the real motor voltage level. 4.7. All connections must be secured against their pašatvienošano. The design of the aircraft moving items (such as the lever, control bars, steering element mounts), as well as elements that are exposed to high vibration level (for example, force element mounts), may be used only by mechanical pašatvienošan of countermeasures (such as šķelttap, wire). The Paškontrējoš wrenches and retaining the use of paplākšņ in these cases. Strengthening wire should be made so, to unscrew the nut case, wire nostiepto. 4.8. the design of the aircraft damaged in use (concave, with grooves, scratches, with signs of wear, with thread damage) bolts and studs. Bolts, which are applied to the combined forces, nogriezoš load effects on the thread. 4.9. If the design of the aircraft's pipes, linked together by bolts or studs, make sure that the tubing is not twisted and the inner surface is coated with anti-corrosion material. 4.10. the design of the aircraft and control systems can only be used in the manufacture of steel wire cable harness. Ropes must be nodes and going wire must be secured against corrosion. 4.11. the design of the aircraft were used in the headline must be fought all over the smooth surface of the tip. The nozzle or hose ambivalent oppression is not permissible. If the rope can be used for dining, it tube ambivalent quench is allowed, but twisting the tube then is mandatory. 4.12. The aircraft structure must be such that, in any case, should be able to check the wire headline space (for example, cover it with colored lacquer). 4.13. The aircraft design at savilktņo the ends of the wire to secure the wire savijumo, which is the same diameter as the savilktņ wire. Wire warp strands must not be less than 8 wires for Warp twist. after to the jamb, but short free wire end must be literal behind warp. 5. installation 5.1 Force aircraft engines must operate in such a way that after five minutes of warm-up develop aircraft take-off power and ensure the smooth operation of the engine of the aircraft of external air temperature range from 30 ° C to-30 ° C without overheating, as well as to ensure the smooth operation of the engine idle mode 15 minutes without cooling. 5.2. aircraft engine mounting must be effectively absorbs vibrations. Aircraft engine must be mounted with at least four nodes located attachment to one of the nodes in the case of damage to the engine not to lose capacity. 5.3. Improvised aircraft propeller must be monolithic. 5.4. aircraft propeller may not be observable material split fucking signs, cracks, cuts, metal damage. Fairing may not be in direct contact with the propeller blade. Cowl can be cracks and other mechanical damage. 5.5. aircraft engines must be equipped with a choke. Forbidden to operate the aircraft engines, turning the propeller by hand. Aircraft engine must stop by turning the ignition system with switch, which has a fixed position. 5.6. Should not be used battery type ignition system. If the battery type used in the ignition system, the battery capacity must be such as to ensure a continuous operation of the engine of the aircraft for at least eight hours. 5.7. If starting the engine of the aircraft used in the ignition system of the divdzirksteļ, each divdzirksteļ ignition system of the candle must have a separate power source. 5.8. in the construction of the aircraft must use all possible means to reduce aircraft engine noise levels. Recommended for aircraft engine fitted with a silencer. 5.9. The air force equipment (system consisting of one or more engines and palīgagregāt, which together create the aircraft thrust required) must be separated by fireproof partitions. 5.10. the accumulation of fuel or oil in the engine area of the aircraft and other aircraft, structures of the partitions are not permitted. 6. Fuel System 6.1. aircraft fuel tank must be positioned so that the leaked fuel in case of defect does not go to the hot parts of the engine. The aircraft fuel tank capacity must ensure continuous operation of the engine in the cell mode Maximus for at least 30 minutes. 6.2. The aircraft fuel system must: 6.2.1 fuel level or device level control of fuel on the ground and in flight; 6.2.2. fuel shut off valve (fire hydrants); 6.2.3 fuel spilling tap; 6.2.4. the fuel fine filter cleaning; 6.2.5. the drainage system, which eliminates the pressure fall in fuel tank, the fuel level tumbled. 6.3. The fuel spilling tap must be located in the fuel system at the lowest point, the aircraft while on the ground. Spilling fuel, it may not get to the aircraft design elements. 6.4. Fire tap handle must be in the pilot area, available to him would not be left to the seats. Between the fire and the aircraft engine must be fireproof separation. 6.5. fuel supply must be such as to ensure the normal operation of the engine in all the manoeuvre, which may for the aircraft. If the fuel supply is going to pump aid, must be excluded the possibility of crowded to the carburettor float Chamber that would cause fuel outflow. Try not to use the float-type carburettor. 6.6. fuel tanks must be sprādziendroš. All fuel tanks pipelines must be made of metal or flexible rubber that will not degrade the fuel effect. A fuel spill is not allowed. Fuel tanks pipelines must be protected from direct exposure to vibration. 7. Management System 7.1. All aircraft control devices must be secured with a movement or deflection limiters. 7.2. Minimum space between aircraft control devices the existing cables and rods, as well as between other aircraft parts and elements of the design must be at least 5 mm. It is not permissible for the transmission management system iestrēgum, aircraft structure deflection allowable operating loads. Those limits may not be observed also in the control rods permanent deformation. 7.3. Calculation of the aircraft's control system of operational loads that Act on control devices be adopted the following loads: 7.3.1. tangāž-65 kg; 7.3.2. banked-32.5 kg; 7.3.3. the course (per pedal) – 90 kg. 7.4. If the aircraft is carrying the management system uses ropes, it changes direction to adjust the roller. The diameter of the roller must be 20 times the rope diameter. Rolls shall be equipped with a fuse elements, which prevents the wire from sagging of the rolls. Rolls must not be mechanical damage, and they must turn freely. 7.5. Air transport management system elements in the cockpit of the aircraft must be secured against other articles getting to them. 8. Chassis 8.1. Aircraft regardless of type and size (excluding the classic schema Sailplanes and motoplanier) we recommend that you use three-wheel diagram to the front wheel. It is recommended that the main pillars and the front wheel diameter base should be at least 300 mm. 8.2 calculate the aircraft landing gear must be made on landing, in case the aircraft vertical speed of at least 2.5 m/sec. 9. Electrical System 9.1. Electrical power generated should be appropriate for all the electricity consumed in the total capacity of the equipment. 9.2. The aircraft electrical wire cross sectional area must be such that the power density shall not exceed three to ampērkilovat mm square. Mains assembling must be done so that the electrical wires could not get gasoline, oil and water. Electrical wires must be covered with water, gasoline and oil safe insulation. 9.3. the aircraft must be to interface to power. Not recommended for aircraft structural metal elements to use on the Earth. Electric wire them so as to strengthen the influence of friction would not be damaged by their isolation. Electric wires, which are passed through partitions, you must delimit of metal parts with rubber inserts. 9.4. External power supply connection should be avoided in case of possibility to connect these sources with the wrong polarity. 9.5. If the aircraft battery is installed, you must ensure that the electrolyte does not fall out of it and not go to the other elements of the design of the aircraft. 9.6. Electrical System turn on fuse, which protects the network from overloads and short circuits. 10. measuring apparatus and equipment 10.1 aircraft must be set up in the following instruments: 10.1.1. speed indicator; 10.1.2. height gauge; 10.1.3. engine tachometer; 10.1.4. engine cylinder head temperature indicator, or engines with liquid cooling-liquid temperature indicator. 10.2. Gliders with limited height and time of flight rules 10.1. bottom-measuring apparatus referred to in paragraph 1 may not be installed. 10.3. the scale of the measuring apparatus must be displayed in red color signs, which indicate the maximum flight parameters. On the speed dial of the contents must include the iekritien speed and maximum speed, to piloting the tachometer scale, maximum engine revs on the temperature indicators – the maximum permitted temperatures. 10.4. it is recommended that you set the ultraīsviļņ aircraft radio station or aircraft cockpit space for its installation. 11. Rescue features 11.1. aircraft structure must be such that the aircraft crew members during an emergency on the ground and in the air You can comfortably and quickly to evacuate. Aircraft design must provide for the safe evacuation during the flight, the way excluding the possibility that the aircraft crew members could face evakuējot to aircraft design elements (CAB, wings, stabilizers, wing struts or propeller). 11.2. The aircraft cabin side door or dome (if any) must be equipped with a fast shutter, which ensure the side door or dome (if any) separation from the aircraft in an emergency. The seals must be opened with the red handle, which must be located at the pilot's left arm. 11.3. the surface must include firefighting equipment instruments and medicine cabinet.
Traffic Minister k. Peters annex 2 Cabinet of 11 July 2006, the regulations no licence application for 540 aircraft flights for validity of annex 2 in Word format traffic Minister k. Peters annex 3 of the Cabinet of Ministers of 11 July 2006, regulations no 573 annex submission certificate for aircraft flights for validity of annex 3 Word traffic Minister k. Peters annex 4 of the Cabinet of Ministers of 11 July 2006, regulations no 573 model of certificate annex 4 Word traffic Minister k. Peters annex 5 Prime Minister the Cabinet of 11 July 2006, regulations no 573 Annex 5 model of certificate in Word format traffic Minister k. Peters annex 6 Cabinet of 11 July 2006, the regulations no licence application for 540 aircraft flights extension of validity 6. attachment in Word format traffic Minister k. Peters