EASA TCDS A.028 ZLIN Z 43 Series 06 02112010

TCDS No.EASA.A.028 Page 2 of 26 ZLIN Z 43 Series Issue 6, 2 November 2010

CONTENT

SECTION A: Z 43 AI. General AII. Certification Basis AIII. Technical Characteristics and Operational Limitations AIV. Operating and Service Instructions AV. Notes SECTION B: Z 143 L BI. General BII. Certification Basis BIII. Technical Characteristics and Operational Limitations BIV. Operating and Service Instructions BV. Notes SECTION C1: Z 143 LSi CI. General CII. Certification Basis CIII. Technical Characteristics and Operational Limitations CIV. Operating and Service Instructions CV. Notes ADMINISTRATIVE SECTION I. Acronyms II. Type Certificate Holder Record III. Change Record EASA Form NR 90 CS-23 Issue 01

TCDS No.EASA.A.028 Page 3 of 26 ZLIN Z 43 Series Issue 6, 2 November 2010 SECTION A: GENERAL, Z 43 Type Design AI. General 1. a) Type: Z 43 b) Model: --- 2. Airworthiness category: Normal (N) Utility (U) 3. Type Certificate Holder: ZLIN AIRCRAFT A.S.

Letišt ě 1578 765 81 Otrokovice Czech Republic 4. Manufacturer: MORAVAN n. p.

Letišt ě 1578, 765 81 Otrokovice CZECHOSLOVAKIA S/N: 0001-0084 MORAVAN a.s.

Letišt ě 1578, 765 81 Otrokovice CZECH REPUBLIC S/N: 0085-0114 5. Certification Application --- Date: 6. CAA CZ Type Certificate May 10, 1972 Date: 7. The EASA Type Certificate replaces the CAA CZ Type Certificate No. 72-03.

AII. Certification Basis 1. Reference Date for determining the applicable --- requirements: 2. (Reserved) 3. (Reserved) 4. Airworthiness Requirements: FAR PART 23, Amdt. 23-6 (including) 5. Requirements elected to None comply: 6. EASA Special Conditions: None 7. EASA Exceptions: None 8. EASA Equivalent Safety § 23.177(a) – Requirement for directional and Z 43 TCDS No.EASA.A.028 Page 4 of 26 ZLIN Z 43 Series Issue 6, 2 November 2010 Findings: lateral stability is not fully met. It is admitted with regard to the fact that both aileron and rudder control are of sufficient efficiency for instant stopping of aircraft rolling and leading to normal rectilinear flight.

§ 23.613(c); 23.615 – Materials and their characteristics according to Č SN and aviation specifications have been used for aircraft design and construction. It is admitted with regard to the fact that an intent of the requirement is met.

§ 23.905 – V 500 Propeller is certified according to BCAR, Section C Regulation instead of Far Part 35.

§ 23.955 – Requirement for flow rate of fuel supplied by fuel pump to the engine is not met. It is admitted with regard to the fact that fuel flow is constructed by fuel valve and is higher than engine consumption at maximum power.

§ 23.991 – The engine is equipped with high and low pressure pumps joined to a single aggregate.

Any failure of this aggregate could cause contemporaneous failure of both supply and injection pumps. In such case, no emergency pump could ensure sufficient fuel supply to finish the flight without abnormal pilot’s skills nor effort.

A failure of low-pressure pump has not been occurred yet and its occurrence is extremely improbable.

§ 23.1013 (e), § 23.1019 – A by-pass is missing at the screen of oil tank outlet. It is admitted with regard to the fact that a surface of the screen is multiply bigger than cross section of the outlet fitting, thus safety level is kept.

§ 23.1183(a) – Requirement for hoses fire resistance is not met. It is admitted with regard to experiences from operation of similar aircraft of this category.

§ 23.1381 – § 23.1401 – Has not been proved, the aircraft is not admitted for night operation.

9. EASA Environmental ICAO Annex. 16/I, Chapter 6 Standards: FAR PART 36, App. G (Amdt. 36-20) Z 43 TCDS No.EASA.A.028 Page 5 of 26 ZLIN Z 43 Series Issue 6, 2 November 2010 AIII. Technical Characteristics and Operational Limitations 1. Type Design Definition: The specification list of Aircraft Z 43 No. S- 43.0000; The specification drawing No. Z 43.0000 2. Description: The Z 43 aircraft is all-metal, four-seat, low wing, single-engine, cantilever monoplane.

3. Equipment: Master equipment list is stated in Airplane Flight Manual of the ZLIN Z 43 aircraft.

4. Dimensions: Span: 9.760 m Length: 7.750 m Height: 2.910 m Wing Area: 14.500 m 5. Engine: 5.1.1 Model: M 337 A 5.1.2 Type Certificate: EASA approved (see Note 2) 5.1.3 Limitations: Max. Take-off power (MT), and max. Continuous power (MC) Power 154 kW (210 HP) Engine rotational speed 2 750 RPM Consumption 83 l/h Manifold pressure 118 kPa Continuous Cruising power (75 % MC) Power 125 kW (170 HP) Engine rotational speed 2 600 RPM Consumption 54 l/h Manifold pressure 98 kPa Economic Cruising power (60 % MC) Power 103 kW (140 HP) Engine rotational speed 2 400 RPM Consumption 42 l/h Manifold pressure 90 kPa or 5.2.1 Model: M 337 AK 5.2.2 Type Certificate: EASA approved (see Note 3) 5.2.3 Limitations: Max. Take-off power (MT), and max. Continuous power (MC) Power 154 kW (210 HP) Engine rotational speed 2 750 RPM Consumption 83 l/h Manifold pressure 118 kPa Z 43 TCDS No.EASA.A.028 Page 6 of 26 ZLIN Z 43 Series Issue 6, 2 November 2010 Continuous Cruising power (75 % MC) Power 125 kW (170 HP) Engine rotational speed 2 600 RPM Consumption 54 l/h Manifold pressure 98 kPa Economic Cruising power (60 % MC) Power 103 kW (140 HP) Engine rotational speed 2 400 RPM Consumption 42 l/h Manifold pressure 90 kPa 6. Load factors: For category Utility (U) +4.4 g, -1.76 g For category Normal (N) +3.8 g, -1.52 g 7. Propeller: 7.1 Model: AVIA V 500A 7.2 Type Certificate: EASA approved (see Note 4) 7.3 Number of blades: 2 7.4 Diameter: 2 000 mm 7.5 Sense of Rotation: Anticlockwise in flight direction.

8. Fluids: 8.1 Fuel: Non-ethylated aviation gasoline, with minimum 72 octanes. Application of ethylated fuels is only permitted in case the T.E.L. content does not exceed the value of 0.06 % vol.

BL 78, BP 100L, Aviation gasoline AVGAS 80, AVGAS 100L, AVGAS 100LL (see service instruction of engine manufacturer).

8.2 Oil: The oil of kinematic viscosity of 20 mm /s min. at 100° C, the corbon residue does not exceed 0,4 % of weight.

Recommended oil types: running-in: AEROSHELL Oil 100 MS-20 Continual service: AEROSHELL Oil W 100 AEROSHELL Oil W 120 (tropic area) 8.3 Coolant: None 9. Fluid capacities: 9.1 Fuel: Z 43, serial number up to 0084 incl.: Total: 230 litres (2 x 65 litres in main tanks and 2 x 50 Z 43 TCDS No.EASA.A.028 Page 7 of 26 ZLIN Z 43 Series Issue 6, 2 November 2010 litres in wing tip tanks) Usable: 227 litres Z 43, serial number 0085 and subsequent: Total: 220 litres (2 x 60 litres in main tanks and 2 x 50 litres in wing tip tanks) Usable: 215 litres 9.2 Oil: Minimum 7 litres – Maximum 12 litres 9.3 Coolant system None capacity: 10. Air Speeds: Never Exceed Speed Limit v NE - category U 307 km/h IAS - category N 286 km/h IAS Normal Operating Speed Limit v NO - category U, N 222 km/h IAS Design Manoeuvring Speed Limit v A - category U 230 km/h IAS - category N 248 km/h IAS Maximum Flaps Extended Speed Limit v FE - category U, N 197 km/h IAS 11. Maximum Operating For category Utility (U) 5 500 m Altitude: For category Normal (N) 3 800 m 12. Allweather Operations The aircraft is approved for VFR-Day flights.

Capability: 13. Maximum Weights: Max. Take-off and Landing weight: For category Utility (U) 1 000 kg For category Normal (N) – Take-off weight 1 350 kg For category Normal (N) – Landing weight 1 280 kg Standard empty weight: 730 kg ± 3 % 14. Centre of Gravity 21.8 % ÷ 36 % MAC Range: (M.A.C. is 1 489 mm, 0 % M.A.C. is at 376 mm aft of reference datum) 15. Datum: The back part of fire wall; from it are measured, for purpose assignation of Gravity Centre, all horizontal length.

16. Control surface Elevator deflection up 30° ± 1° deflections: down 27° ± 1° Elevator trim tab up 15° ± 1° down 30° ± 2° Rudder deflection right and left 30° ± 2° Ailerons deflection up 21° ± 1° down 17° ± 1° Z 43 TCDS No.EASA.A.028 Page 8 of 26 ZLIN Z 43 Series Issue 6, 2 November 2010 Wing flaps positions retracted 0° take-off 14° ± 1° landing 37° ± 1° 17. Levelling Means: Levelling points on left and right side of airplane fuselage to be levelled. Measurement plane to be min.

600 mm below.

18. Minimum Flight Crew: 1 (Pilot) 19. Maximum Passenger 4 (including crew) Seating Capacity: 20. (Reserved) 21. Baggage/Cargo Upper baggage shelf 20 kg Compartments: Lower baggage compartment 2 x 30 kg Max. Weight 60 kg 22. Wheels and Tyres: Wheels of main gear K 22-0100-7 with tyre Barum 420 x 150 model 2, or Wheels of main gear K 22-3100-7 with tyre Mitas 420 x 150 model 2 or with tyre Goodyear 6.00-6.5, P/N 607C41-1.

Wheel of nose gear K 23-0000-7 with tyre Barum 350 x 135 model 2, or Wheel of nose gear K 51-1100-7 with tyre Mitas 350 x 135 or with tyre Goodyear 5.00-5, P/N 505C61-8 Z 43 TCDS No.EASA.A.028 Page 9 of 26 ZLIN Z 43 Series Issue 6, 2 November 2010 AIV. Operating and Service Instructions st rd Z 43 – 1 through 3 series (up to S/N 0084 incl.): 1. Flight Manual: – In Czech language Letová p ř íru č ka Z 43, date of issue 1972 – In English language Flight Manual Z 43, date of issue 1974 – In German language Flugzeug – Betriebhandbuch Z 43, date of issue 2. Technical Manual: – In Czech language Technický popis a návod k obsluze Z 43 date of issue 1972 – In English language Technical Manual Z 43, date of issue 1973 3. Repair Manual: – In Czech language Opravárenská p ř íru č ka letounu Z 43, date of issue 4. Manual for Operation: – In Czech language P ř íru č ka pro provoz letounu Z 43 bez generálních oprav Doc. No. 233.071 draku – č ást 1, č ást 2, prohlídka A, B, C date of issue 1997 – In English language Manual for Operation of Z 43 Aircraft without Airframe Doc. No. 233.071 Overhaul Part 1, Part 2, Revision A, B, C date of issue 1997 5. Spare Parts Catalogue: – In Russian, Czech, German and English language Katalog náhradních díl ů letounu Z 43, date of issue 6. Table of Dimensions, Limits and Clearances: − In Czech, German and English language Album rozm ě r ů , tolerancí a v ů lí Z 42, Z 42 M, Z 42 MU a Z 43, date of issue 1976 Album der Abmessungen, der Toleranz und Spielangaben Z 42, Z 42 M, Z 42 MU, Z 43 date of issue 1976 Table of Dimensions, Limits and Clearances Z 42, Z 43 TCDS No.EASA.A.028 Page 10 of 26 ZLIN Z 43 Series Issue 6, 2 November 2010 Z 42 M, Z 42 MU, Z 43, date of issue 1976 7. Instruments and aggregates: – In Czech language P ř ístroje a agregáty použité na letounech Z 42M Doc. No. PRA.081 Z 42MU, Z 142 a Z 43, date of issue 1996 th Z 43 – 4 series and subsequent (from S/N 0085 incl.): 1. Flight Manual: – In Czech language Letová p ř íru č ka Z 43, date of issue 1991 2. Technical Manual: – In Czech language Technický popis a návod k obsluze Z 43 date of issue 1991 3. Repair Manual: – In Czech language Opravárenská p ř íru č ka letounu Z 43, date of issue 4. Manual for Operation: – In Czech language P ř íru č ka pro provoz letounu Z 43 bez generálních oprav Doc. No. 233.071 draku – č ást 1, č ást 2, prohlídka A, B, C date of issue 1997 – In English language Manual for operation of Z 43 aircraft without airframe Doc. No. 233.071 overhaul Part 1, Part 2, Revision A, B, C date of issue 1997 5. Spare Parts Catalogue: – In Czech and English language Katalog náhradních díl ů letounu Z 43 (od 4. série) th Catalogue of spare parts Z 43 (from 4 séries) 6. Table of Dimensions, Limits and Clearances: − In Czech, German and English language Album rozm ě r ů , tolerancí a v ů lí Z 42, Z 42 M, Z 42 MU, Z 43, date of issue 1976 Album der Abmessungen, der Toleranz und Spielangaben Z 42, Z 42 M, Z 42 MU, Z 43 date of issue 1976 Table of Dimensions, Limits and Clearances Z 42, Z 43 TCDS No.EASA.A.028 Page 11 of 26 ZLIN Z 43 Series Issue 6, 2 November 2010 Z 42 M, Z 42 MU, Z 43, date of issue 1976 7. Instruments and aggregates: – In Czech language P ř ístroje a agregáty použité na letounech Z 42M Doc. No. PRA.081 Z 42MU, Z 142 a Z 43, date of issue 1996 Z 43 TCDS No.EASA.A.028 Page 12 of 26 ZLIN Z 43 Series Issue 6, 2 November 2010 AV. Notes: Note 1: The following Z 43 aircraft have been converted by the aircraft manufacturer to the Model Z 143 L: Serial numbers: 0092, 0093 Note 1A: The following Z 43 aircraft have been cobnverted by the aircraft manufacturer to the Model Z 43M: Serial number: 0031 Note 2: For the engine the EASA type certification standard includes the TCDS 72 - 05 (issued by CAA CZ) based on individual EU member state acceptance or certification of this standard prior to 28 September 2003.

Other standards confirming to TC/TCDS standards certificated by individual EU member state prior to 28 September 2003 are also acceptable.

Note 3: For the engine the EASA type certification standard includes the TCDS 94 - 06 (issued by CAA CZ) based on individual EU member state acceptance or certification of this standard prior to 28 September 2003.

Other standards confirming to TC/TCDS standards certificated by individual EU member state prior to 28 September 2003 are also acceptable.

Note 4: For the propeller the EASA type certification standard includes the TCDS 73 - 03 (issued by CAA CZ) based on individual EU member state acceptance or certification of this standard prior to 28 September 2003. Other standards confirming to TC/TCDS standards certificated by individual EU member state prior to 28 September 2003 are also acceptable.

Z 43

TCDS No.EASA.A.028 Page 13 of 26 ZLIN Z 43 Series Issue 6, 2 November 2010 SECTION B: Z 143 L BI. General 1. a) Type Z 43 b) Model: Z 143 L 2. Airworthiness category: Normal (N) Utility (U) 3. Type Certificate Holder: ZLIN AIRCRAFT a.s. .

Letišt ě 1578 765 81 Otrokovice CZECH REPUBLIC 4. Manufacturer: MORAVAN a.s.

Letišt ě 1578 765 81 Otrokovice CZECH REPUBLIC S/N: 0001-0012, 0014-0029 MORAVAN – AEROPLANES, a.s.

Letišt ě 1578 765 81 Otrokovice CZECH REPUBLIC S/N 0030-0032, 0034-0041, 0043-0054 MORAVAN AVIATION, s.r.o.

Letišt ě 1578 765 81 Otrokovice CZECH REPUBLIC S/N 0056-0058 5. Certification Application October 01, 1991 Date: 6. CAA CZ Type Certificate June 10, 1994 Date: 7. The EASA Type Certificate replaces the CAA CZ Type Certificate No. 94-08.

BII. Certification Basis 1. Reference Date for October 01, 1991 determining the applicable requirements: Z 143 L TCDS No.EASA.A.028 Page 14 of 26 ZLIN Z 43 Series Issue 6, 2 November 2010 2. (Reserved) 3. (Reserved) 4. Airworthiness Requirements: FAR PART 23, Amdt. 23-41 (including) 5. Requirements elected to None comply: 6. EASA Special Conditions: None 7. EASA Exemptions: None 8. EASA Equivalent Safety None Findings: 9. EASA Environmental ICAO Annex. 16/I, Chapter 10 Standards: FAR PART 36, App. G (Amdt. 36-20) BIII. Technical Characteristics and Operational Limitations 1. Type Design Definition: The specification list of Aircraft Z 143 L No. S-L 143.0000; The specification drawing No. L 143.0000.

2. Description: The Z 143 L aircraft is all-metal, four-seat, low wing, single-engine, cantilever monoplane.

3. Equipment: Master equipment list is stated in Airplane Flight Manual of the ZLIN Z 143 L aircraft.

4. Dimensions: Span: 10.136 m Length: 7.577 m Height: 2.910 m Wing Area: 14.776 m 5. Engine: 5.1. Model: TEXTRON Lycoming O-540-J3A5 5.2. Type Certificate: EASA approved (see Note 1) 5.3. Limitations: Max. Take-off power (MT), and Max. Continuous Power (MC) Power 175 kW Engine rotational speed 2 400 RPM Consumption by engine manufacturer 74 l/h Consumption measured at the aircraft 96 l/h Manifold pressure MAX Continuous Cruising pover (75 % MC) Power 130 kW Engine rotational speed 2 200 Z 143 L TCDS No.EASA.A.028 Page 15 of 26 ZLIN Z 43 Series Issue 6, 2 November 2010 RPM Consumption by engine manufacturer 53 l/h Consumption measured at the aircraft 55.5 l/h Manifold pressure 84.6 kPa Economic Cruising power (60 % MC) Power 104 kW Engine rotational speed 2 000 RPM Consumption by engine manufacturer 38.6 l/h Consumption measured at the aircraft 44 l/h Manifold pressure 78.6 kPa 6. Load factors: For category Utility (U) +4.4 g, - 1.76 g For category Normal (N) +3.8 g, - 1.52 g 7. Propeller: 7.1 Model: MTV-9-B/195-45a 7.2 Type Certificate: EASA approved (see Note 2) 7.3 Number of blades: 3 7.4 Diameter: 1950 mm 7.5 Sense of Rotation: Clockwise in flight direction.

8. Fluids: 8.1 Fuel: Aviation gasoline 100L, 100LL (see service instruction of engine manufacturer) 8.2 Oil: By average outside air temperature above + 27° C are recommended mineral oils with SAE 60 or dispersant oils with SAE 60.

By average outside air temperature above + 16° C are recommended mineral oils with SAE 50 or dispersant oils with SAE 40 or 50.

By average outside air temperature from - 1° C to + 32° C are recommended mineral oils with SAE 40 or dispersant oils with SAE 40.

By average outside air temperature from - 18° C to + 21° C are recommended mineral oils with SAE 30 or dispersant oils with SAE 40, 30 or 20W40.

By outside air temperature under - 12° C are recommended mineral oils with SAE 20 or dispersant oils with SAE 30 or 20W30.

8.3 Coolant: None Z 143 L TCDS No.EASA.A.028 Page 16 of 26 ZLIN Z 43 Series Issue 6, 2 November 2010 9. Fluid capacities: 9.1 Fuel: Category U: Total – 122 litre Usable – 116 litre Category N: Total – 224 litre Usable – 216 litre 9.2 Oil: Minimum 5.7 litres – Maximum 11.4 litres 9.3 Coolant system None capacity: 10. Air Speeds: Never exceed speed limit v NE (category U, N) 306 km/h IAS Normal operating speed limit v NO (category U, N) 258 km/h IAS Design manoeuvring speed limit v A (category U) 224 km/h IAS Design manoeuvring speed limit v A (category N) 236 km/h IAS Maximum flaps extended speed limit v FE (category U, N) 190 km/h IAS 11. Maximum Operating For category Utility (U) 5 760 m Altitude: For category Normal (N) 4 170 m 12. Allweather Operations VFR-Day and VFR-Night Capability: IFR, not in icing conditions 13. Maximum Weights: Take-of: Category Utility (U) 1 080 kg Category Normal (N) 1 350 kg Landing: Category Utility (U) 1 080 kg Category Normal (N) 1 280 kg Standard empty weight: 855 kg ± 3 % 14. Centre of Gravity 21 % ÷ 34 % MAC Range: (M.A.C. is 1 489 mm, 0% MAC is at 368 mm aft of reference datum) 15. Datum: The back part of fire wall; from it are measured, for purpose assignation of Gravity Centre, all horizontal length.

16. Control surface Elevator deflection up 30° ± 1° deflections: down 27° ± 1° Rudder deflection right and left 30° ± 2° Ailerons deflection up 21° ± 1° down 17° ± 1° Z 143 L TCDS No.EASA.A.028 Page 17 of 26 ZLIN Z 43 Series Issue 6, 2 November 2010 Wing flaps positions retracted 0° take-off 14° ± 1° landing 37° ± 1° 17. Leveling Means: Levelling points on left and right side of airplane fuselage to be levelled. Measurement plane to be min.

600 mm below.

18. Minimum Flight Crew: 1 (Pilot) 19. Maximum Passenger 4 (including crew) Seating Capacity: 20. (Reserved) 21. Baggage/Cargo Upper baggage shelf 20 kg Compartments: Lower baggage compartment 2 x 30 kg Max. Weight 60 kg 22. Wheels and Tyres: Wheels of main gear K 22-0100-7 with tyre Barum 420 x 150 model 2, or Wheels of main gear K 22-3100-7 with tyre Mitas 420 x 150 model 2 or with tyre Goodyear 6.00-6.5, P/N 607C41-1.

Wheel of nose gear K 23-0000-7 with tyre Barum 350 x 135 model 2, or Wheel of nose gear K 51-1100-7 with tyre Mitas 350 x 135 or with tyre Goodyear 5.00-5, P/N 505C61-8 Z 143 L TCDS No.EASA.A.028 Page 18 of 26 ZLIN Z 43 Series Issue 6, 2 November 2010 BIV. Operating and Service Instructions 1. Flight Manual: – In Czech language Letová p ř íru č ka letounu ZLIN 143 L Doc. No. 005.011 – In English language Doc. No. 005.012 ZLIN 143 L Airplane Flight Manual Doc. No. 005.012.US ZLIN 143 L Airplane Flight Manual – In German language Flughandbuch Z 143 L Doc. No. 005.013 2. Maintenance Manual: – In Czech language P ř íru č ka pro údržbu letounu ZLIN 143 L Doc. No. 005.021.1 – In English language Z 143 L Airplane Maintenance Manual Doc. No. 005.022.1 publication 3. Ilustrated parts catalogue: – In Czech language Katalog náhradních díl ů letounu Z 143 L Doc. No. 005.040 – In English language Ilustrated parts catalogue Z 143 L Doc. No. 005.040 BV. Notes: Note 1: For the engine the EASA type certification standard includes the TCDS E-295 (issued by FAA) based on individual EU member state acceptance or certification of this standard prior to 28 September 2003.

Other standards confirming to TC/TCDS standards certificated by individual EU member state prior to 28 September 2003 are also acceptable.

Note 2: For the engine the EASA type certification standard includes the TCDS 23.130/65 (issued by LBA) based on individual EU member state acceptance or certification of this standard prior to 28 September 2003.

Other standards confirming to TC/TCDS standards certificated by individual EU member state prior to 28 September 2003 are also acceptable.

Z 143 L

TCDS No.EASA.A.028 Page 19 of 26 ZLIN Z 43 Series Issue 6, 2 November 2010 SECTION C: Z 143 LSi CI. General 1. a) Type: Z 43 b) Model: Z 143 LSi 2. Airworthiness category: Normal (N) Utility (U) 3. Type Certificate Holder: ZLIN AIRCRAFT a.s.

Letišt ě 1578 765 81 Otrokovice CZECH REPUBLIC 4. Manufacturer: MORAVAN – AEROPLANES, a.s.

Letišt ě 1578 765 81 Otrokovice CZECH REPUBLIC S/N 0042, 0055 MORAVAN – AVIATION, s.r.o.

Letišt ě 1578 765 81 Otrokovice CZECH REPUBLIC S/N 0060 ZLIN AIRCRAFT a.s.

Letišt ě 1578 765 81 Otrokovice CZECH REPUBLIC S/N: 0059, 0061 and up 5. Certification Application June 30, 2000 Date: 6. CAA CZ Type Certificate April 30, 2004 Date: 7. The EASA Type Certificate replaces the CAA CZ Type Certificate No. 94-08.

CII. Certification Basis 1. Reference Date for September 12, 2000 determining the applicable requirements: Z 143 LSi TCDS No.EASA.A.028 Page 20 of 26 ZLIN Z 43 Series Issue 6, 2 November 2010 2. (Reserved) 3. (Reserved) 4. Airworthiness FAR PART 23, Amdt. 23-41 (including) Requirements: 5. Requirements elected to None comply: 6. EASA Special Conditions: None 7. EASA Exemptions: None 8. EASA Equivalent Safety None Findings: 9. EASA Environmental ICAO Annex 16/I, Chapter 10 Standards: FAR PART 36, App. G (Amdt. 36-20) CIII. Technical Characteristics and Operational Limitations 1. Type Design Definition: The specification list of Aircraft Z 143 L No. S-I 143.0000 2. Description: The Z 143 LSi aircraft is all-metal, four-seat, low wing, single-engine, cantilever monoplane.

3. Equipment: Master equipment list is stated in Airplane Flight manual of the Zlin Z 143 LSi aircraft.

4. Dimensions: Span: 10.136 m Length: 7.577 m Height: 2.910 m Wing Area: 14.776 m 5. Engine: 5.1. Model: TEXTRON Lycoming IO-540-C4D5 5.2. Type Certificate: EASA Approved (see Note 1) 5.3. Limitations: Max. Take-off power (MT) ), and Max. Continuous Power (MC) Power 175 kW Engine rotational speed 2 400 RPM Consumption by engine manufacturer 73.1 l/h Consumption measured at the aircraft 96 l/h Manifold pressure MAX Continuous Cruising power (75 % MC) Power 130 kW Engine rotational speed 2 200 RPM Consumption by engine manufacturer 55 l/h Consumption measured at the aircraft 55.5 l/h Z 143 LSi TCDS No.EASA.A.028 Page 21 of 26 ZLIN Z 43 Series Issue 6, 2 November 2010 Manifold pressure 84.4 kPa Economic Cruising power (60 % MC) Power 104 kW Engine rotational speed 2 000 RPM Consumption by engine manufacturer 39 l/h Consumption measured at the aircraft 43 l/h Manifold pressure 82.9 kPa 6. Load factorst: For category Utility (U) +4.4 g, - 1.76 g For category Normal (N) +3.8 g, - 1.52 g 7. Propeller: 7.1 Model: MTV-9-B/195-45a 7.2 Type Certificate: EASA approved (see Note 2) 7.3 Number of blades: 3 7.4 Diameter: 1 950 mm 7.5 Sense of Rotation: Clockwise in flight direction.

8. Fluids: 8.1 Fuel: Aviation gasoline 100L, 100LL (see service instruction of engine manufacturer) 8.2 Oil: By average outside air temperature above + 27° C are recommended mineral oils with SAE 60 or dispersant oils with SAE 60.

By average outside air temperature above + 16° C are recommended mineral oils with SAE 50 or dispersant oils with SAE 40 or 50.

By average outside air temperature from - 1° C to + 32° C are recommended mineral oils with SAE 40 or dispersant oils with SAE 40.

By average outside air temperature from - 18° C to + 21° C are recommended mineral oils with SAE 30 or dispersant oils with SAE 40, 30 or 20W40.

By outside air temperature under - 12° C are recommended mineral oils with SAE 20 or dispersant oils with SAE 30 or 20W30.

8.3 Coolant: None 9. Fluid capacities: 9.1 Fuel: Category U: Total – 122 litre Usable – 116 litre Category N: Total – 224 litre Usable – 216 litre Z 143 LSi TCDS No.EASA.A.028 Page 22 of 26 ZLIN Z 43 Series Issue 6, 2 November 2010 9.2 Oil: Minimum 5.7 litres – Maximum 11.4 litres 9.3 Coolant system None capacity: 10. Air Speeds: Never exceed speed limit v NE (category U, N) 306 km/h IAS Normal operating speed limit v NO (category U, N) 258 km/h IAS Design manoeuvring speed limit v A (category U) 224 km/h IAS Design manoeuvring speed limit v A (category N) 236 km/h IAS Maximum flaps extended speed limit v FE (category U, N) 190 km/h IAS 11. Maximum Operating For category Utility (U) 5 760 m Altitude: For category Normal (N) 4 170 m 12. Allweather Operations VFR-Day and VFR-Night Capability: IFR, not in icing conditions 13. Maximum Weights: Take-off: Category Utility (U) 1 080 kg Category Normal (N) 1 350 kg Landing: Category Utility (U) 1 080 kg Category Normal (N) 1 280 kg Standard empty weight: 855 kg ± 3 % 14. Centre of Gravity 21 % ÷ 34 % MAC Range: (M.A.C. is 1 489 mm, 0 % M.A.C. is at 368.4 mm aft of reference datum) 15. Datum: The back part of fire wall; from it are measured, for purpose assignation of Gravity Centre, all horizontal length.

16. Control surface Elevator deflection up 30° ± 1° deflections: down 27° ± 1° Rudder deflection right and left 30° ± 2° Ailerons deflection up 21° ± 1° down 17° ± 1° Wing flaps positions retracted 0° take-off 14° ± 1° landing 37° ± 1° 17. Leveling Means: Levelling points on left and right side of airplane fuselage to be levelled. Measurement plane to be min.

600 mm below.

Z 143 LSi TCDS No.EASA.A.028 Page 23 of 26 ZLIN Z 43 Series Issue 6, 2 November 2010 18. Minimum Flight Crew: 1 (Pilot) 19. Maximum Passenger 4 (including crew) Seating Capacity: 20. (Reserved) 21. Baggage/Cargo Upper baggage shelf 20 kg Compartments: Lower baggage compartment 2 x 30 kg Max. Weight 60 kg 22. Wheels and Tyres: Wheels of main gear K 22-0100-7 with tyre Barum 420 x 150 model 2, or Wheels of main gear K 22-3100-7 with tyre Mitas 420 x 150 model 2 or with tyre Goodyear 6.00-6.5, P/N 607C41-1.

Wheel of nose gear K 23-0000-7 with tyre Barum 350 x 135 model 2, or Wheel of nose gear K 51-1100-7 with tyre Mitas 350 x 135 or with tyre Goodyear 5.00-5, P/N 505C61-8 Z 143 LSi TCDS No.EASA.A.028 Page 24 of 26 ZLIN Z 43 Series Issue 6, 2 November 2010 CIV. Operating and Service Instructions 1. Flight Manual: – In Czech language Letová p ř íru č ka letounu ZLIN 143 LSi Doc. No. Si 005.011 – In English language Airplane Flight Manual ZLIN 143 LSi Doc. No. Si 005.012 2. Maintenance Manual: – In Czech language P ř íru č ka pro údržbu letounu Z 143 L - Doc. No. 005.021.1 Dodatek pro letoun Z 143 LSi Doc. No. Si 005.021.1 – In English language Z 143 L Airplane Maintenance Manual - Doc. No. 005.022.1 Supplement for Z 143 LSi Airplane Doc. No. Si 005.022.1 3. Ilustrated parts catalogue: – In Czech language Katalog náhradních díl ů letounu Z 143 L - Z 143 LSi Doc. No. 005.040.02 – In English language Illustrated parts catalogue Z 143 L-Z 143 LSi Doc. No. 005.040.02 CV. Notes: Note 1: For the engine the EASA type certification standard includes the TCDS 1E4 (issued by FAA) based on individual EU member state acceptance or certification of this standard prior to 28 September 2003. Other standards confirming to TC/TCDS standards certificated by individual EU member state prior to 28 September 2003 are also acceptable.

Note 2: For the propeller the EASA type certification standard includes the TCDS 23.130/65 (issued by LBA) based on individual EU member state acceptance or certification of this standard prior to 28 September 2003.

Other standards confirming to TC/TCDS standards certificated by individual EU member state prior to 28 September 2003 are also acceptable.

Z 143 LSi TCDS No.EASA.A.028 Page 25 of 26 ZLIN Z 43 Series Issue 6, 2 November 2010 ADMINISTRATIVE SECTION I Acronyms N/A II Type Certificate Holder Record Current: ZLIN AIRCRAFT a.s.

Letišt ě 1578 765 81 Otrokovice CZECH REPUBLIC Former: MORAVAN n. p.

Letišt ě 1578, 765 81 Otrokovice CZECHOSLOVAKIA MORAVAN a.s.

Letišt ě 1578, 765 81 Otrokovice CZECH REPUBLIC MORAVAN – AEROPLANES, a.s.

Letišt ě 1578 765 81 Otrokovice CZECH REPUBLIC MORAVAN – AVIATION, s.r.o.

Letišt ě 1578 765 81 Otrokovice CZECH REPUBLIC III Change Record Issue Date Changes Issue 1 04-Feb-2005 Transfer of ZLIN Z 143 L and Z 143 LSi Type Design to EASA Issue 2 14-Dec-2006 Transfer of ZLIN Z 43 as basic Type Design under this TC / TCDS Issue 3 02-May-2007 Introduction of changed Company Name of Moravan TCDS No.EASA.A.028 Page 26 of 26 ZLIN Z 43 Series Issue 6, 2 November 2010 Issue 4 24 Aug 2009 Change of Company name Issue 5 23 July 2010 Editorial corrections and revision into standard EASA TCDS format Issue 6 2 November Corrections to B.I.4 and C.I.4 to specify actual serial 2010 numbers manufactured by each company and to exclude airframes used specifically for test purposes.