Republic of Latvia Cabinet Regulation No. 573 Adopted 11 July 2006

Regulations regarding Recognition of Aircraft Airworthiness

Issued pursuant to
Section 16
of the Law On Aviation

I. General Provisions

1. These Regulations prescribe the procedures, by which an aircraft shall be recognised as airworthy, and the procedures, by which a certificate of aircraft airworthiness shall be issued and revoked and the period of validity thereof shall be extended.

2. These Regulations shall be applicable to the aircraft registered in the Civil Aviation Aircraft Register of the Republic of Latvia, which comply with the criteria referred to in Annex II to Regulation (EC) No. 1592/2002 of the European Parliament and of the Council of 15 July 2002 on common rules in the field of civil aviation and establishing a European Aviation Safety Commission (hereinafter - Regulation No. 1592/2002).

3. The State Agency "Civilās aviācijas aģentūra" [Civil Aviation Agency] (hereinafter - Civil Aviation Agency) shall be the competent authority in the Republic of Latvia in issues related to the scope of application of these Regulations and of Commission Regulation (EC) No. 1702/2003 of 24 September 2003 laying down implementing rules for the airworthiness and environmental certification of aircraft and related products, parts and appliances, as well as for the certification of design and production organisations.

4. Operation of the aircraft referred to in Paragraph 2 of these Regulations is allowed in the territory of the Republic of Latvia if:

4.1. the amateur built aircraft, which are not intended for offer on the market of the States of the European Economic Area, comply with the aircraft airworthiness requirements referred to in Annex 1 to these Regulations;

4.2. the aircraft complies with the airworthiness requirements of another Member State of the European Economic Area applicable to the relevant aircraft or the type of the aircraft; or

4.3. the aircraft has been issued a Certificate of Airworthiness.

5. In order to implement the requirements referred to in Paragraphs 9 and 19 of these Regulations and to assess whether the relevant aircraft complies with the requirements referred to in Sub-paragraphs "C" and "E" of Annex II to Regulation No. 1592/2002, the Civil Aviation Agency shall invite independent experts for the provision of an opinion regarding the relevant issue. The expert's opinion shall not be binding to the Civil Aviation Agency.

6. The opinion of the experts referred to in Paragraph 5 of these Regulations shall not be required, if there is a document issued by an authorised institution of another European Economic Area Member State confirming the compliance of the aircraft or the type of the aircraft with the requirements referred to in Sub-paragraph 4.2 of these Regulations.

II. Issuance of an Aircraft Certificate of Airworthiness

7. In order to receive an aircraft Certificate of Airworthiness, an owner or an operator of an aircraft shall submit to the Civil Aviation Agency a relevant application (Annex 2) and annex to the application (Annex 3). The following shall be appended to the referred to documents:

7.1. documents confirming the compliance of the aircraft with the airworthiness requirements referred to in Sub-paragraphs 4.1 and 4.2 of these Regulations;

7.2. an aircraft flight manual or a document equal thereto;

7.3. documents confirming the weight and the centre of gravity of the aircraft;

7.4. a report on the aircraft's test flight (for new aircraft);

7.5. documents confirming that all maintenance works (in accordance with the technical operation documentation thereof) and mandatory modifications have been performed, as well as mandatory instructions of the manufacturer and the State of manufacture have been taken into account; and

7.6. documents confirming that the aircraft, engines, parts and appliances and components thereof with a limited period of operation have a sufficient remainder of resource.

8. Due to flight safety reasons the Civil Aviation Agency may also request the report referred to in Sub-paragraph 7.4 of these Regulations on previously operated aircraft.

9. After receipt of all the documents referred to in Paragraph 7 of these Regulations, the Civil Aviation Agency shall conduct an inspection of the relevant aircraft, which includes visual external and internal inspection, as well as the examination of the documentation and equipment of the aircraft. The process of aircraft inspection shall be documented in an inspection protocol.

10. If defects are detected during inspection of the aircraft or if the submitted aircraft documentation is incomplete, a relevant entry shall be made in the inspection protocol and the owner or operator of the aircraft shall be informed.

11. If the owner or operator of the aircraft eliminates the defects referred to in the inspection protocol and submits all the necessary documents within a time period of six months, a repeated inspection of the aircraft shall not be conducted.

12. If during inspection of the aircraft it is detected that the aircraft and documentation thereof complies with airworthiness requirements, a recommendation to issue an aircraft Certificate of Airworthiness shall be written in the inspection protocol.

13. After receipt of the inspection protocol referred to in Paragraph 12 of these Regulations, the Civil Aviation Agency shall issue a standard aircraft Certificate of Airworthiness (Annex 4) or a special aircraft Certificate of Airworthiness (Annex 5) to the owner or operator of the aircraft. Both referred to certificates shall be valid for the time period of one year.

14. A standard aircraft Certificate of Airworthiness shall be issued to the aircraft, which have an approved design of the aircraft type.

15. A special aircraft Certificate of Airworthiness shall be issued to the aircraft, to which an individual conformity assessment of the aircraft has been performed.

16. Flights involving aircraft, to which a certificate referred to in Paragraph 15 of these Regulations has been issued, may be performed only in the territory of the Republic of Latvia for non-commercial purposes. The Civil Aviation Agency may also determine other restrictions, taking into account the design and parametric special features of such aircraft.

17. The certificate referred to in Paragraph 13 of these Regulations shall be on board of the aircraft during a flight.

III. Extension and Revocation of an Aircraft Certificate of Airworthiness

18. In order to extend the period of validity of a standard aircraft Certificate of Airworthiness or special aircraft Certificate of Airworthiness, the owner or operator of the aircraft shall submit to the Civil Aviation Agency a relevant application (Annex 6) within a time period of 30 days before the expiry date of the relevant certificate. The following shall be attached to the application:

18.1. a report on the maintenance works carried out to the aircraft during the time period from the issuance of the certificate or the date of extension of the previous validity period;

18.2. documents confirming information regarding modifications and repair work carried out to the aircraft, as well as all work carried out, which are referred to in the mandatory airworthiness maintenance instructions; and

18.3. documents confirming that the aircraft, parts and appliances and components thereof with a limited period of operation have a sufficient remainder of resource.

19. After receipt of the documents referred to in Paragraph 18 of these Regulations, the Civil Aviation Agency shall conduct an inspection of the aircraft in accordance with Paragraphs 9, 10 and 11 of these Regulations.

20. In order to assess the conformity of the aircraft with airworthiness requirements, the Civil Aviation Agency may request a test flight of the aircraft.

21. The test flight referred to in Paragraph 20 of these Regulations involving aircraft, to which a special aircraft Certificate of Airworthiness has been issued, shall be made not less than once every three years.

22. If during inspection of the aircraft it is detected that the aircraft and documentation thereof complies with airworthiness requirements, a recommendation to extend the period of validity of the aircraft Certificate of Airworthiness for one year shall be written in the inspection protocol.

23. On the basis of the inspection protocol referred to in Paragraph 22 of these Regulations, the Civil Aviation Agency shall take a decision regarding extension of the period of validity of a standard aircraft Certificate of Airworthiness or a special aircraft Certificate of Airworthiness for one year.

24. The Civil Aviation Agency shall revoke the certificates referred to in Paragraph 13 of these Regulations in the cases referred to in Section 19 of the Law On Aviation.

IV. Special Flight Permit

25. If an aircraft does not have a valid certificate referred to in Paragraph 13 of these Regulations or it does not comply with airworthiness requirements, the Civil Aviation Agency shall issue a special flight permit for:

25.1. the aircraft could fly to the location of maintenance, modification, repairs or conservation, if it is not possible to perform such work at the location of the aircraft;

25.2. assessment of the aircraft as regards conformity with airworthiness requirements could be performed;

25.3. the aircraft could be imported or exported; or

25.4. the aircraft could be evacuated from a district involving an emergency situation.

26. In order to receive a permit for special flight operations, an owner or an operator of an aircraft shall submit to the Civil Aviation Agency a relevant application. The application shall indicate:

26.1. the given name, surname (name), personal identification number (registration number) and address of the place of residence (legal address) of the owner or the operator of the aircraft;

26.2. the type, serial number, nationality mark and registration mark of the aircraft;

26.3. the purpose of the flight;

26.4. the route of the flight;

26.5. the composition of the flight crew necessary for the flight operation;

26.6. detailed information regarding non-conformity with airworthiness requirements; and

26.7. operation restrictions, which the owner or operator of the aircraft considers necessary for safe flight operation.

27. After receipt of the documents referred to in Paragraph 26 of these Regulations, the Civil Aviation Agency shall examine the documents submitted and, where necessary, inspect the relevant aircraft.

28. If an aircraft, taking into account the non-conformity thereof with the requirements referred to in Sub-paragraph 4.1 of these Regulations, is able to make a safe flight, the Civil Aviation Agency shall issue a permit for special flight operations and indicate the restrictions of the flight to be made.

29. If a flight with an aircraft, to which the Civil Aviation Agency has issued the permit referred to in Paragraph 28 of these Regulations, is made outside the territory of the Republic of Latvia, prior to the flight operation the owner or the operator of the aircraft shall receive a relevant permit from the competent authorities of those foreign states, above the territory of which the flight will be made.

V. Aircraft Certificate of Airworthiness for Export

30. If the Civil Aviation Agency excludes an aircraft from the Civil Aviation Aircraft Register of the Republic of Latvia and it is intended to export the aircraft to another state, the Civil Aviation Agency upon a request shall issue an export certificate of the aircraft confirming that the relevant aircraft complies with the airworthiness requirements valid in the Republic of Latvia and, where appropriate, the airworthiness requirements of the importing state.

31. The Civil Aviation Agency shall issue an export certificate of the aircraft after receipt of the written submission of the owner or the operator of the aircraft and conducting of the aircraft inspection referred to in Paragraphs 9, 10 and 11 of these Regulations.

32. If an aircraft inspection is conducted within a time period of 90 days after receipt of the written submission of the owner or the operator of the aircraft, inspection of the aircraft shall not be repeated.

33. Airworthiness of an aircraft on the day of issuance of the certificate shall be indicated in the export certificate of the aircraft.

34. An export certificate of the aircraft does not provide rights to operate the aircraft.

Prime Minister A. Kalvītis

Minister for Transport K. Peters

 

Annex 1
Cabinet Regulation No. 573
11 July 2006

Aircraft Airworthiness Requirements

1. Flight Characteristics, Stability and Controllability

1.1. The designer or constructor of an aircraft shall develop instructions for each aircraft or type thereof:

1.1.1. for flight operation. Technical parameters, operating conditions and restrictions of the aircraft or aircraft type shall be indicated therein;

1.1.2. for continued airworthiness of the aircraft (also maintenance).

1.2. The aircraft in all stages of flight shall not go arbitrarily outside the range of operating restrictions specified in the flight instruction. Aircraft flight properties shall be acceptable also to an amateur beginner pilot. Piloting of the aircraft upon taking off, taxiing and landing shall be simple. Methods for piloting of the aircraft shall not contradict with common methods.

1.3. The aircraft shall comply with the following speed limits:

1.3.1. take-off speed upon taking off - not less than 1,2 stall speeds (V_LOF. = 1,2 V_S1.);

1.3.2. speed before landing - not less than 1,3 stall speeds (V_{before landing.} = 1,3 V_S1.);

1.3.3. landing speed - not less than 0,95 stall speeds (V_landingl. = 0.95 V_S1.);

1.3.4. cruising speed - not less than 1,3 stall speeds (V_cruising. = 1,3 V_S1.).

1.4. Stall speed (V_S1.) - the speed, at which indications of intense air flow stall emerge on the wing, expressing, for example, as a warning quake of the structure and control handle, parachuting of the aircraft. If there is no stall, the slowest flight speed of the aircraft without roll, which complies with the extreme position of the control handle at the slowest speed in flight with the engine working in idling regime, may be regarded the stall speed. Sinking of the nose of the aircraft without roll followed by an increase of speed shall be characteristic to a stall. If it does not happen, the pilot shall feel indications attesting to the approach of a stall.

1.5. It shall be ensured that in case of the engine stopping the pilot may balance the aircraft in stabilised rectilinear flight and perform a safe landing.

1.6. The aircraft shall be in such condition so that:

1.6.1. landing thereof could be performed by a pilot without high proficiency;

1.6.2. a pilot could perform landing thereof without any over concentration;

1.6.3. landing thereof would not require good weather conditions;

1.6.4. in the take-off run and after landing, it could maintain a stable specified direction, without a tendency to deviate.

1.7. Vertical speed of the aircraft after leaving the ground shall be not less than 1.5 m/sec, but the height of flying over obstacles at the end of the runway shall be not less than 10 m. Design of the aircraft shall be such as to make possible taking off or landing thereof in aerodromes with concrete or asphalt runway pavement, as well as in aerodromes without an artificial runway pavement, if the strength thereof is not less than 5 kg/cm².

1.8. Longitudinal static stability shall express in the ability of the aircraft to return into a balanced state (as regards speed and angle of attack) without assistance after rectification of the cause of the disturbances without participation of the pilot.

1.9. Static stability of the route shall express in the ability of the aircraft to exit slipping without assistance, if the directional steering wheel of the aircraft is returned to the neutral position.

1.10. Transverse static stability shall express in the ability of the aircraft to bring up the wing inclined in the direction of land in case of roll of the aircraft.

1.11. Roll of the aircraft shall alter according to the movements of the directional steering wheel of the aircraft and shall be directly dependent on them. In case of a large roll angle, reverse force shall not act on rudder pedals.

1.12. Forces applied to the control levers and pedals of the aircraft shall be as follows:

1.12.1. pitch - from 2.5 kg (continuing) to 25 kg (temporary);

1.12.2. roll - from 1.5 kg (continuing) to 15 kg (temporary); and

1.12.3. heading - from 3 kg (continuing) to 50 kg (temporary).

2. Strength

2.1. Circle flights with a roll not greater than 35° shall be admissible to aircraft, the operation overload of which is not more than 3 g (g - gravity acceleration) and is not less than 1.5 g, if the safety coefficient is 1.5. More complicated flights may be made with an aircraft, the maximum overload of which is not less than 6 g. The advisable safety coefficient of the main force elements of the aircraft (connection units, longer on installation units, engine attachments, control surfaces, rudder suspension units, castings, cables and bracings) shall be 3. The calculated overloads and loads shall be determined, multiplying operation overloads and loads by the safety coefficient.

2.2. The safety belt system of the pilot of the aircraft, as well as attachment of such cargo, which may injure the pilot, shall endure an exploitation overload 9 g longitudinally and +/- 2.5 g transversely.

2.3. The attachment knots of the aerodynamic steering surfaces of the aircraft shall be calculated for an overload of not less than 20 g.

3. Construction

3.1. If the design of the aircraft does not ensure the safety of the pilot in case of complete or partial stopping of the aircraft, the aircraft shall be equipped with a circular safety rod, which excludes the possibility of pilot injury. The calculated overload in case of a complete stop of the aircraft shall be 3 g.

3.2. Arrangement of force elements of the aircraft shall be planned so that the workplaces of the aircraft crew, fuel tanks and lines are not located in the rotation plane of propellers. It is prohibited to intend arrangement of engines, fuel tanks and placement of cargo aboard the aircraft above the workplaces of aircraft crew in the design of the aircraft.

3.3. The seats of the aircraft crew in the aircraft shall be equipped with waist and shoulder safety belts, the buckles of which guarantee safe fixation and are easily opened.

3.4. Arrangement of engines for an aircraft with two or more engines shall be planned so that in case of the stopping of any engine, the pilot could prevent any deviation of the aircraft from normal condition thereof by using aerodynamic control devices.

3.5. Spacing between the end of the propeller blade of the aircraft and land in any case of shock absorbing of landing gear shall be not less than 150 mm. Spacing between the propeller of the aircraft and design of the aircraft shall be not less than 25 mm

4. Design

4.1. Any design elements of the aircraft shall be industrially manufactured, and physical mechanical properties thereof shall comply with the approved stress level. Utilisation of details of unknown origin in the design of an aircraft shall not be permissible.

4.2. If wooden pieces are used in the design of the aircraft, they shall be manufactured from straight-grown timber without branches, fungi, mould and signs of decomposition and decay.

4.3. All elements and compartments of the aircraft, in which moisture may accumulate, shall be provided with drainage at the lowest point thereof.

4.4. All design details of the aircraft, which are made of wood, shall be covered with a protecting coating that prevents decay of the wood. Any metal details of aircraft design shall be covered with an anticorrosion coating.

4.5. The strengthening elements of the aircraft design shall not have fractures, cavities and other mechanical damage. Design of the aircraft shall be such so that, where necessary, visual inspection of the main force elements would be possible.

4.6. Utilisation of curved pipes in strengthening elements and control device systems of the aircraft is allowed only if the utilisation thereof is justified, purposeful and complies with the actual stress level.

4.7. Any joints shall be ensured against self-disconnection. Only mechanical self-disconnection prevention equipment (for example, cotter-pins, wires) shall be used in moveable elements of the aircraft design (for example, levers, control rods, steering element fastenings), as well as elements subject to a high level of vibration (for example, strengthening element attachments). Utilisation of self-locking nuts and spring washers is not permissible in such cases. Fixation using wire shall be carried out so that in case of unscrewing of a nut the wire would strain.

4.8. It is prohibited to use damaged (concave, with cavities, with scrapes, with signs of wear, with damage of thread) bolts and studs in the design of aircraft. Effect of load on the thread is not permissible in bolt joints, to which cutting force is applied.

4.9. If pipes, which are interconnected with bolts or rivets, are included in the design of the aircraft, it shall be provided that the pipes are not deformed and internal surfaces thereof are covered with an anticorrosion material.

4.10. Only industrially manufactured multi-wire steel cables shall be used in the design and control device systems of aircraft. Knots and torn wires shall not be used in cables, they shall be ensured against corrosion.

4.11. Fixing of the cable used in the design of the aircraft shall provide even reduction on all the surface of the head. Two-sided reduction of a head or a tube is not permissible. If a copper tube is used for fixation of a cable, two-sided reduction thereof is allowed, but warping twist of the tube is mandatory afterwards.

4.12. Design of the aircraft shall be such as in any case it would be possible to examine the fixation point of a cable (for example, by covering it with coloured varnish).

4.13. In the design of aircraft stay wires, the ends thereof shall be fixed in splices of wire, which have the same diameter as the wire of the bracing. The number of turns of the wire splices shall not be less than 8. After splicing of the wire, the splice shall be brazed and the short free end of the wire shall be bent behind the splice.

5. Powerplant

5.1. Engines of aircraft shall operate so as after five-minute warming up they would develop take-off power and ensure even operation of the aircraft engine in the temperature range of external air from 30°C to -30°C without excessive heating, as well as ensure even operation of the engine in idle regime for 15 minutes without cooling.

5.2. Attachment of the aircraft engine shall efficiently dampen vibrations. An aircraft engine shall be attached with at least four attachment points arranged so that in case of damage of one attachment point the engine would not lose the capacity to operate.

5.3. The design of a self-made aircraft propeller shall be monolithic.

5.4. An aircraft propeller shall not have signs of material decomposition, fractures, incisions, damage of metal parts. Fairing shall not be in direct contact with propeller blades. Fairing shall not have fractures and other mechanical damage.

5.5. The aircraft engine shall be equipped with a starting device. It is prohibited to start an aircraft engine by turning the propeller by hand. An aircraft engine shall be stopped by switching off the ignition system with a switch, which has a fixed position.

5.6. It shall not be advisable to use a battery ignition system. If a battery ignition system is used, the capacity of the battery shall be such as to ensure continuous operation of the aircraft engine for at least eight hours.

5.7. If a double-spark ignition system is used for starting an aircraft engine, each plug of the double-spark ignition system shall be provided with a separate energy source.

5.8. Any possible means for the reduction of the noise level of an aircraft engine shall be used in the design of the aircraft. It shall be advisable to equip the aircraft engine with a silencer.

5.9. The powerplant of an aircraft (system consisting of one or several engines and auxiliaries, which jointly create the propulsion necessary for the aircraft) shall be separated with a firewall.

5.10. Accumulation of fuel or oil in the area of the aircraft engine and other compartments of the aircraft design is not permissible.

6. Fuel System

6.1. The fuel tank of an aircraft shall be arranged so that in case of damage thereof the fuel discharged would not reach the hot details of the engine. The capacity of aircraft fuel tank shall ensure continuous operation of the engine in the maximum regime for at least 30 minutes.

6.2. The fuel system of an aircraft shall include:

6.2.1. a fuel level gauge or a device for the control of fuel level on land and during flight;

6.2.2. a fuel feed stop-valve (fire safety tap);

6.2.3. a tap for draining of fuel;

6.2.4. a fine filter for purifying of fuel;

6.2.5. a drainage system, which prevents decrease of the pressure in the fuel tank during decline of the fuel level therein.

6.3. The tap for draining fuel shall be located at the lowest point of the fuel system when the aircraft is on land. In draining fuel, it shall not reach the design elements of the aircraft.

6.4. The handle of fire safety tap shall be located in an area accessible to the pilot so that he or she would not have to leave his or her seat. There shall be a firewall between fire safety tap and the aircraft engine.

6.5. The fuel feed shall be such as to ensure normal operation of engine in any manoeuvres that are possible for the relevant aircraft. If the fuel feed involves a pump, a possibility of flooding of the carburettor float chamber causing discharge of fuel shall be excluded. It is not advisable to use a float-type carburettor.

6.6. The design of fuel tank shall be explosion-proof. All the fuel tank lines shall be made of metal or flexible rubber, which does not degrade due to the effects of fuel. Fuel leakage is not permitted. The fuel tank lines shall be protected against the effects of direct vibration.

7. Flight Controls (System)

7.1. Any control devices of the aircraft shall be provided with movement or deviation limitation devices.

7.2. The minimum space between cables and rods present in the control devices of the aircraft, as well as other details and elements of the aircraft design shall be at least 5 mm. Seizures of the flight control (system) drives are not permitted if the aircraft design deforms within the range of permissible exploitation loads. Permanent deformation of the control rods shall also not be observed within this range.

7.3. In calculating the flight control (system) of the aircraft, the following loads shall be assumed as operation loads acting upon the control devices:

7.3.1. pitch - 65 kg;

7.3.2. roll - 32.5 kg; and

7.3.3. path (per pedal) - 90 kg.

7.4. If the flight control (system) of an aircraft use cables in transmission, change of direction thereof shall be regulated with the aid of rollers. The diameter of a roller shall be at least 20 time larger than the diameter of the cable. The rollers shall be equipped with elements of safety elements, which prevent sliding of the cable from rollers. The rollers shall not have mechanic damage, and they shall rotate freely.

7.5. The elements of the transmission of the aircraft flight control (system) in the aircraft cabin shall be provided against the placing of other objects on them.

8. Undercarriage

8.1. It is advisable to use a three-wheel scheme with a nose wheel in an aircraft regardless of the type and dimensions thereof (except for classical gliders and motor gliders). It is advisable that the diameter of main stays and front wheel stay is at least 300 mm.

8.2. Calculations of an aircraft undercarriage shall be made with regard to landing when the vertical speed of the aircraft is at least 2.5 m/sec.

9. Electrical System

9.1. The power generated by the electrical system shall comply with the total power of all devices of electricity consumption.

9.2. The cross-sectional area of the wires of the aircraft electricity grid shall be such that the density of the current would not exceed three ampere-kilowatts per square millimetre. Assembling of electricity grid shall be performed so that fuel, oil and water could not reach electricity wires. Electric wires shall be covered with water, fuel and oil proof insulation.

9.3. The aircraft shall have two-wire wiring. It is not advisable to use the metal elements of the aircraft design as earthing. Electric wires shall be attached so that insulation thereof would not be damaged due to friction. Electric wires, which are run through separating walls, shall be insulated from metal details with rubber inlays.

9.4. In case of connecting external power supplies, possibility to connect such sources with the wrong polarity shall be prevented.

9.5. If an accumulator is being installed in an aircraft, it shall be ensured that the electrolytes do not pour out of it and reach other elements of the aircraft design.

9.6. Safety fuses, which protect the network against overloads and short-circuits, shall be included in the electrical system.

10. Instruments

10.1. The following instruments shall be installed in aircraft:

10.1.1. a speed indicator;

10.1.2. an altimeter;

10.1.3. an engine tachometer; and

10.1.4. an indicator of temperature of the cylinder head of the engine or - for engines with liquid cooling - an indicator of liquid temperature.

10.2. It is allowed not to install the instruments referred to in Sub-paragraph 10.1 of these Regulations in gliders with a limited flight altitude and duration.

10.3. Red signs indicating maximum parameters of flight regimes shall be displayed on the scales of instruments. Stall speed and maximum piloting speed shall be indicated on the scale of the speed indicator, maximum permissible turns of engine - on the scale of the tachometer, maximum permissible temperatures - in temperature indicators.

10.4. It is advisable to install an ultra-short-wave radio station on board the aircraft or to intend a place for installation thereof in the aircraft cabin.

11. Means of Rescue

11.1. Aircraft design shall be such that the flight crew could evacuate comfortably and quickly on land and in air in case of accident. Safe evacuation types during flight shall be intended during aircraft designing, excluding a possibility that upon evacuation members of the flight crew might come in contact with elements of the aircraft design (cabin, wing, stabiliser, wing support or propeller).

11.2. The side door of the aircraft cabin or dome (where such exists) shall be equipped with rapid acting locks, which ensure separation of the side doors or dome (where such exists) from the aircraft in case of an accident. Locks shall be opened with a red handle located at the left hand of the pilot.

11.3. Ground equipment shall include fire extinguishing means and medical kit.

Minister for Transport K. Peters

 

Annex 2
Cabinet Regulation No. 573
11 July 2006

IESNIEGUMS
apliecības par gaisa kuģa derīgumu lidojumiem saņemšanai

APPLICATION FOR A CERTIFICATE OF AIRWORTHINESS

1. Gaisa kuģa īpašnieka nosaukums

Name of aircraft owner

2. Īpašnieka adrese

Address of owner

3. Nacionālā piederība, reģistrācijas zīmes

Nationality, registration marks

4. Iesnieguma iesniedzēja nosaukums un adrese (ja tas nav gaisa kuģa īpašnieks)

Name and address of applicant (if other than the owner of aircraft)

5. Izgatavotāja nosaukums un adrese

Manufacturer and address

6. Izgatavošanas vieta un gads

Place and year of manufacture

7. Izgatavotājvalsts

State of manufacture

8. Gaisa kuģa raksturojums:

Description of aircraft:

a. jauns vai lietots

New or used

b. tips

Type

c. sērija

Series

d. izgatavotāja sērijas numurs

Manufacturer's serial number

e. dzinēja tips

Type of engine

f.. dzinēju skaits

Number of engines fitted

g. gaisa kuģa konstrukcijas veids

Type of aircraft design

h. vietu skaits (ieskaitot apkalpes vietas)

Seating accommodation (including that of the crew)

i.. radioaprīkojums un elektroniskais aprīkojums

Avionics installed

9. Gaisa kuģa maksimālā pacelšanās masa:

Maximum take-off mass of the aircraft:

a. tukšs svars

Empty weight

b. smaguma centra izvietojums

Balance

10. Gaisa kuģis ir (vietējā ražojuma gaisa kuģiem):

Is the aircraft (for domestically manufactured aircraft):

a. paraugeksemplārs (jauna konstrukcija)

Sample (new design)

b. paraugeksemplārs (modifikācija)

Sample (modification)

c. sērijveida (norādot lidojumderīguma prasības)

Serial (indicating airworthiness code)

11. Ārzemēs izgatavotiem gaisa kuģiem:

For foreign manufactured aircraft:

a. valsts, kas izdevusi apliecību par derīgumu lidojumiem

State of Origin of the Certificate of Airworthiness

b. apliecības numurs

Number of the Certificate of Airworthiness presented

c. apliecības tips (nacionālā vai ārzemju)

Type of certificate (Domestic or Export)

d. izsniegšanas datums

Date of issue

12. Paredzētais gaisa kuģa izmantošanas veids:

Types of operations envisage:

a. pasažieru pārvadājumi

Transport of passengers

b. kravas pārvadājumi

Transport of cargo

c. vispārēja lietošana

General purpose

d. speciālie aviācijas darbi

Aerial work

e. privāta lietošana

Private

f. speciālie pārvadājumi (norādīt, kādi)

Special operations (specify)

13. Apstiprināta tehniskās apkopes organizācija vai speciālisti, kas nodrošina gaisa kuģa inspekcijas pārbaudes veikšanu (norādīt nosaukumu un adresi)

Name and address of the Approved Organisation/Licensed Aircraft Maintenance personnel with whom the aircraft is available for inspection

14. APLIECINĀJUMS

DECLARATION

Apliecinu, ka visas šajā iesniegumā un tā pielikumā norādītās ziņas ir pareizas.

I declare that the particulars entered on this Application and this Appendix are accurate in every respect.

Datums	Paraksts
Date ………………………………………………	Signature of Applicant …………………………

Minister for Transport K. Peters

 

Annex 3
Cabinet Regulation No. 573
11 July 2006

Pielikums iesniegumam
apliecības par gaisa kuģa derīgumu lidojumiem saņemšanai

APPENDIX TO THE APPLICATION
FOR A CERTIFICATE OF AIRWORTHINESS

Iesnieguma iesniedzēja nosaukums

Name of applicant

Gaisa kuģa tips

Aircraft type

Sērija

Series

Reģistrācijas zīmes

Registration marks

Iepriekšējās reģistrācijas zīmes (ja tādas bijušas)

Previous registration marks (if any)

Izgatavotāja sērijas numurs

Manufacturer's serial number

I. GAISA KUĢA SISTĒMAS UN IEKĀRTAS

SYSTEMS, INSTALLATIONS AND EQUIPMENT DETAILS

1. Hermetizācijas sistēma

Pressurisation system

2. Lidojuma automatizētās vadības sistēmas

Automatic flight control and guidance system

3. Runas reģistrators pilotu kabīnē

Cockpit voice recorder

4. Elektriskās strāvas ģeneratori:

Electric power generators:

4.1. ar piedziņu no dzinēja:

Engine driven:

a. tikai līdzstrāvas ( ieskaitot ģeneratorus ar iebūvētu taisngriezi)

DC only (including alternators with built-in rectification)

b. līdzstrāvas un maiņstrāvas

DC and AC

c. tikai maiņstrāvas (frekvenču diapazons)

AC only (frequency range)

4.2. ar piedziņu no celsmes propellera:

Helicopter transmission driven:

a. tikai līdzstrāvas ( ieskaitot ģeneratorus ar iebūvētu taisngriezi)

DC only (including alternators with built-in rectification)

b. līdzstrāvas un maiņstrāvas

DC and AC

c. tikai maiņstrāvas (frekvenču diapazons)

AC only (frequency range)

5. Akumulatoru baterijas:

Main batteries:

a. tips un veids

Type and form

b. skaits

Number fitted

6. Skābekļa sistēma:

Oxygen:

a. stacionārā

Installed

b. pārnēsājamā

Portable

7. Dzinēju ugunsgrēka signalizācijas sistēma

Engine fire detection system

8. Pārnēsājamie ugunsdzēšanas aparāti (tips un skaits)

Portable fire extinguishers

9. Avārijas signalizācijas sistēma

Stall detection and warning system

10. Degvielas daudzuma indikācijas sistēma

Fuel quantity indicating systems

11. Pretapledojuma un pretnokrišņu sistēma

Ice and rain protection systems

12. Lidojuma parametru reģistrācijas sistēma

Flight data recording system

13. Avārijas apgaismojuma sistēma

Emergency lighting system

14. Pretsadursmes ugunis:

Anti-collision lighting:

a. rotējošas ugunis

Rotating beacons

b. impulsu ugunis

Strobe lights

15. Magnētiskā kursa indikācijas sistēma

Magnetic heading indication system

16. Automātiskās navigācijas sistēmas

Automatic navigation system

17. Celsmes propellera kritiski mazo apgriezienu avārijas signalizācijas sistēma (tikai helikopteriem)

Rotor low rpm warning system (helicopters only)

18. Lauksaimniecības ierīces

Systems installed for agricultural purpose

II. CITA INFORMĀCIJA

OTHER INFORMATION

19. Drošības jostu uzstādīšana:

Are there provisions for the installation of safety harness at:

a. apkalpes darba vietās

Flight crew seat position

b. stjuartu darba vietās

Cabin crew seat position

c. pasažieru sēdekļos

Passenger seat position

20. Vai paredzēta ārējo kravu pārvadāšana

Are there provisions for carrying external loads

21. Vai paredzēta planieru buksēšana

Are there provisions for glider towing

22. Degvielas tilpņu kopējā ietilpība

State total fuel capacity

23. Modifikācijas rezultātā uzstādītās papildu ierīces

Give details of equipment, other than that listed in 1 to 18, which has been introduced by modification (state manufacturer and type)

24. Modifikācijas rezultātā ieviestās izmaiņas lidojumu ekspluatācijas instrukcijā

Give details of changes, if any, introduced in the Flight Manuals, as a result of modification action

Minister for Transport K. Peters

 

Annex 4
Cabinet Regulation No. 573
11 July 2006

Sample of Certificate

(A5 size sheet)

STANDARTA APLIECĪBA PAR GAISA KUĢA DERĪGUMU LIDOJUMIEM STANDARD CERTIFICATE OF AIRWORTHINESS
SĒRIJA SERIES	LATVIJAS REPUBLIKA REPUBLIC OF LATVIA SATIKSMES MINISTRIJAS CIVILĀS AVIĀCIJAS AĢENTŪRA CIVIL AVIATION AGENCY OF THE MINISTRY OF TRANSPORT	NUMURS NUMBER

1. Valsts piederība un reģistrācijas zīmes Nationality and registration marks	2. Gaisa kuģa izgatavotājs un tā piešķirtais gaisa kuģa apzīmējums Manufacturer and manufacturer's designation of aircraft	3. Gaisa kuģa sērijas numurs Aircraft serial number
4. Klasifikācija Classification
5. Izsniegšanas tiesības un pamats Authority and basis for issuance Šī apliecība par gaisa kuģa derīgumu lidojumiem ir izdota saskaņā ar 1944.gada 7.decembra Konvencijas par starptautisko civilo aviāciju un visaptverošu un detalizētu Latvijas Republikas teritorijā spēkā esošu normu un parametru saraksta prasībām, kas nosaka attiecīgā gaisa kuģa derīgumu lidojumiem, un, ja tā tehniskā apkope un ekspluatācija tiek veikta saskaņā ar minēto aviācijas normatīvo aktu prasībām un šim gaisa kuģim piemērojamiem ekspluatācijas ierobežojumiem, tad ar šo apliecību gaisa kuģis tiek atzīts par derīgu lidojumiem. This Certificate of Airworthiness is issued pursuant to the Convention on International Civil Aviation dated 7 December 1944 and according to the comprehensive and detailed airworthiness code being in force in the territory of the Republic of Latvia and the Type Certificate Data Sheet issued by in respect of the above-mentioned aircraft which is considered to be airworthy when maintained and operated in accordance with the foregoing and the pertinent operating limitations.
Pirmo reizi izsniegta Civilās aviācijas aģentūras vārdā: Date of initial issue For Civil Aviation Agency: Atjaunota Renewed Derīga līdz Date of expiry

LCAA form 200-82 Address, telephone number, and fax number of the Civil Aviation Agency (in Latvian and English)

Minister for Transport K. Peters

 

Annex 5
Cabinet Regulation No. 573
11 July 2006

Sample of Certificate

(A5 size sheet)

SPECIĀLĀ APLIECĪBA PAR GAISA KUĢA DERĪGUMU LIDOJUMIEM SPECIAL CERTIFICATE OF AIRWORTHINESS
SĒRIJA SERIES	LATVIJAS REPUBLIKA REPUBLIC OF LATVIA SATIKSMES MINISTRIJAS CIVILĀS AVIĀCIJAS AĢENTŪRA CIVIL AVIATION AGENCY OF THE MINISTRY OF TRANSPORT	NUMURS NUMBER

1. Valsts piederība un reģistrācijas zīmes Nationality and registration marks	2. Gaisa kuģa izgatavotājs un tā piešķirtais gaisa kuģa apzīmējums Manufacturer and manufacturer's designation of aircraft	3. Gaisa kuģa sērijas numurs Aircraft serial number
4. Klasifikācija Classification
5. Nolūks Purpose
6. Izsniegšanas tiesības un pamats Authority and basis for issuance Šī apliecība par gaisa kuģa derīgumu lidojumiem ir izdota saskaņā ar Latvijas Republikas likuma "Par aviāciju" un uz tā pamata izstrādāto normatīvo aktu prasībām attiecībā uz attiecīgo gaisa kuģi, kas ir pārbaudīts un apliecības izsniegšanas brīdī ir atzīts par atbilstošu minēto aviācijas normatīvo aktu prasībām. Minētais gaisa kuģis neatbilst visaptverošu un detalizētu Latvijas Republikas teritorijā spēkā esošo normu prasībām, kas nosaka tā derīgumu lidojumiem saskaņā ar 1944.gada 7.decembra Konvencijas par starptautisko civilo aviāciju 8.pielikumu. This Certificate of Airworthiness is issued under the authority of the Law on Aviation of the Republic of Latvia, and the Orders and Regulations made there under, in respect of the above mentioned aircraft, which has been inspected and as of the date of issuance is found to meet the requirements of the foregoing. The aircraft does not meet the requirements of the applicable comprehensive and detailed airworthiness code being in force in the territory of the Republic of Latvia as provided by Annex 8 to the Convention on International Civil Aviation dated 7 December 1944.
7. ____________________ IZDOTIE EKSPLUATĀCIJAS IEROBEŽOJUMI IR ŠĪS APLIECĪBAS (gads, diena, mēnesis) NEATŅEMAMA SASTĀVDAĻA THE OPERATING LIMITATIONS ISSUED ON __________________ ARE AN INTEGRAL PART OF THIS CERTIFICATE (day, month, year)
Pirmo reizi izsniegta Civilās aviācijas aģentūras vārdā: Date of initial issue For Civil Aviation Agency: Atjaunota Renewed Derīga līdz Date of expiry
Ierobežojumi Restrictions Lidojumus virs jebkuras ārvalsts teritorijas nedrīkst veikt bez šīs valsts izdotas atļaujas. Flight over any foreign country is not permitted without the permission issued by the appropriate country.

LCAA form 200-69 Address, telephone number, and fax number of the Civil Aviation Agency (in Latvian and English)

Minister for Transport K. Peters

 

Annex 6
Cabinet Regulation No. 573
11 July 2006

IESNIEGUMS
apliecības par gaisa kuģa derīgumu lidojumiem pagarināšanai

APPLICATION FOR EXTENSION OF A CERTIFICATE OF AIRWORTHINESS

1. Gaisa kuģa īpašnieka nosaukums

Name of aircraft owner

2. Īpašnieka adrese

Address of owner

3. Nacionālā piederība, reģistrācijas zīmes

Nationality, registration marks

4. Iesnieguma iesniedzēja nosaukums un adrese (ja tas nav gaisa kuģa īpašnieks)

Name and address of applicant (if other than the owner of the aircraft)

5. Izgatavotāja nosaukums un adrese

Manufacturer and address

6. Izgatavošanas vieta un gads

Place and year of manufacture

7. Izgatavotājvalsts

State of manufacture

8. Gaisa kuģa raksturojums:

Description of aircraft:

a. jauns vai lietots

New or used

b. tips

Type

c. sērija

Series

d. izgatavotāja sērijas numurs

Manufacturer's serial number

e. dzinēja tips

Type of engine

f. dzinēju skaits

Number of engines fitted

g. gaisa kuģa konstrukcijas veids

Form of design

h. vietu skaits (ieskaitot apkalpes vietas)

Seating accommodation (including crew seating)

i. radioaprīkojums un elektroniskais aprīkojums

Avionics installed

9. Gaisa kuģa maksimālā pacelšanās masa:

Maximum take-off mass of the aircraft:

a. tukšs svars

Empty weight

b. smaguma centra izvietojums

Balance

10. Gaisa kuģis ir (vietējā ražojuma gaisa kuģiem):

Is the aircraft (for domestically manufactured aircraft):

a. paraugeksemplārs (jauna konstrukcija)

Sample (new design)

b. paraugeksemplārs (modifikācija)

Sample (modification)

c. sērijveida (norādot lidojumderīguma prasības)

Serial (indicating airworthiness code)

11. Ārzemēs izgatavotiem gaisa kuģiem:

For foreign manufactured aircraft:

a. valsts, kas izdevusi apliecību par derīgumu lidojumiem

State of Origin of Certificate of Airworthiness

b. apliecības numurs

Number of the Certificate of Airworthiness presented

c. apliecības tips (nacionālā vai ārzemju)

Type of certificate (Domestic or Export)

d. izsniegšanas datums

Date of issue

12. Paredzētais gaisa kuģa izmantošanas veids:

Types of operations envisaged:

a. pasažieru pārvadājumi

Transport of passengers

b. kravas pārvadājumi

Transport of cargo

c. vispārēja lietošana

General purpose

d. speciālie aviācijas darbi

Special aerial work

e. privāta lietošana

Private use

f.. speciālie pārvadājumi (norādīt, kādi)

Special operations (specify what kind)

13. Apstiprināta tehniskās apkopes organizācija vai speciālisti, kas nodrošina gaisa kuģa inspekcijas pārbaudes veikšanu (norādīt nosaukumu un adresi)

Name and address of the Approved Organisation/Licensed Aircraft Maintenance personnel with whom the aircraft is available for inspection

14. APLIECINĀJUMS

DECLARATION

Apliecinu, ka visas šajā iesniegumā un tā pielikumā norādītās ziņas ir pareizas.

I declare that the particulars entered on this Application and this Appendix are accurate in every respect.

Datums	Paraksts
Date ………………………………………………	Signature of Applicant …………………………

Minister for Transport K. Peters

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Translation © 2007 Tulkošanas un terminoloģijas centrs (Translation and Terminology Centre)