# TCDS A42CE: Aircraft Industries a.s. - Type: Type certificate data sheet - Status: Current - Holder: Aircraft Industries a.s. - Revision: 14 - Revised: July 23, 2021 - Product: Aircraft, Small/Large Airplane - Certification basis: Part 21, Part 23 - Data sheet PDF: https://openairdocs.org/files/sha256/1e/f9/1ef93d1b29960870401df4c447961cef2274e01cc25730b9300a981c2f32e9f6 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/03074ACC36424B8F8625872000571853.0001 - Page: https://openairdocs.org/tcds/A42CE ## Models (4) As the data sheet lists them. - L-420 - L 410 UVP-E20 - L 410 UVP-E20 CARGO - L 410 NG ## What the data sheet says From the PDF's text layer, line by line; tables lose their columns. The PDF is the record. ```text Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 Rev. No. 14 1 0 7 3 7 7 10 13 12 12 12 12 12 12 12 14 12 12 12 13 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A42CE Revision 14 Aircraft Industries a.s. L-420 L 410 UVP-E20 L 410 UVP-E20 CARGO L 410 NG July 23, 2021 TYPE CERTIFICATE DATA SHEET NUMBER A42CE This data sheet, which is part of Type Certificate No. A42CE prescribes conditions and limitations under which the product for which the Type Certificate was issued meets the airworthiness requirements of the Federal Av iation Regulations. Type Certificate Holder Aircraft Industries, a.s. 686 04 Kunovice 1177 Czech Republic Type Certificate Holder Record: LETECKÉ ZÁVODY a.s. transferred TC A42CE to Aircraft Industries a.s. on September 26, 2005. LET Aeronautical Works transferred TC A42CE to LETECKÉ ZÁVODY a.s. on October 15, 2002. I. Model L-420 (Commuter Category) approved March 11, 1998. Engines Walter, a.s. WALTER M601F Type Certificate E00048EN Quantity Two (2) Fuel T-1 according to ST SEV 5024-85 or GOST 10227-86 TS-1 according to ST SEV 5024-85 or GOST 10227-86 or CSN 656 520 RT according to ST SEV 5024-85 or GOST 10227-86 or CSN 656 520 PL-6 according to PND 25005-76 PL-7 according to PND 25005-92 JET-A according to ASTM-D1655-89 JET A-1 according to ASTM-D1655-89 or DERD 2494 PSM 2 according to PN-86/C-96026 Engine Limits Maximum propeller shaft horsepower Maximum propeller speed (rpm) Maximum propeller shaft torque (lb-ft) Maximum gas generator speed (% of 36,660 rpm) Interturbine temperature (°C) Maximum Takeoff (5 minutes) 777 2,080 1,964 101.0 765 Maximum Continuous 777 2,080 1,964 100.0 750 Takeoff with water injection (5 minutes) 777 2,080 1,964 100.0 735 Page 2 of 21 Notes: The engine ratings are based on the following conditions: Compressor intake screen installed Static (V = 0 knots) operation No air bleed No external accessory loads Maximum Takeoff (5 minutes) Compressor inlet air at 29.43 in.-hg, 86°F/30°C Maximum Continuous Compressor inlet air at 29.92 in.-hg, 77°F/25°C Takeoff with water injection (5 minutes) Compressor inlet air at 28.74 in.-hg, 80.6°F/27°C Propeller and Propeller Limits Propeller AVIA-Hamilton Standard Aviation Ltd. Five blade V510 Type Certificate P2BO Quantity Two (2) Pitch setting measured at 68.82 inch diameter Feather +79.5 o Low +14 o High +79.5o Reverse - 24 o Diameter: Maximum 90.63 inches Minimum 90.47 inches No further reduction permitted below minimum diameter. Speed Maximum 2080 rpm Power Maximum 779 hp Pitch- Control Speed Limiter 065-2600 Hydraulic Regulator LUN 7816-8 Electro-Hydraulic Actuator LUN 7880-01-8 De-ice Auxiliary Pump LUN 7840-8 Pressure Switch LUN 1492.04-8 Timing Relay LUN 2601.01-8 Timer LUN 3193.1-8 Brush Block Assembly LUN 7850-7 Rotation Clockwise viewed from slip stream Spinner 068-4000 Note: Certified propeller assembly number is VJ8.510 and includes all listed components. Page 3 of 21 Airspeed Limits All speeds are indicated airspeeds. Maximum operating speed VMO 202 knots 232 mph Maximum maneuvering speed VA 147 knots 169 mph Maximum speed in turbulence VB 140 knots 161 mph Maximum dive speed VD 236 knots 271 mph Maximum landing gear operating speed VLO 160 knots 184 mph Maximum landing gear extended speed VLE 160 knots 184 mph Maximum flaps extended speed for flaps 18o VFE 160 knots 184 mph for flaps 42o VFE 113 knots 130 mph Maximum flaps operating speed for flaps 18o VFO 160 knots 184 mph for flaps 42o VFO 113 knots 130 mph Minimum control speed, OEI, (air) for flaps 18o VMCA 84 knots 96 mph for flaps 0o VMCA 95 knots 109 mph Minimum control speed OEI, (ground) for flaps 18o VMCG 76 knots 87 mph for flaps 0o VMCG 89 knots 102 mph Center of Gravity (C.G.) Range All C.G.’s are with landing gear extended. Mean Aerodynamic Chord (MAC) 75.50 inches MAC leading edge located at station 86.26 Forward C.G. at 9,920 lbs 19 percent of MAC Station 100.59 Forward C.G. at 14,550 lbs 26 percent of MAC Station 105.91 Aft C.G. at 14,550 lbs 30 percent of MAC Station 108.90 Notes: Forward C.G. ranges linearly between 11,020 and 14,550 lbs For weights below 11,020 the forward C.G. is constant at 19 percent MAC. Effect of landing gear retraction is 0.217 percent MAC forward. See Note 1 for additional information on weight and balance. Empty Weight C.G. Range None Datum Reference point No. 2 marked on fuselage, located 107.48 in. behind the fuselage nose. Station locations are numbered aft positive and forward negative. Leveling Means With empty aircraft on jacks in basic configuration with extended landing gear: Lateral direction Set by means of leveling points No. 19 on the left and right wing with a maximum difference of 0.039 inch (1 mm). Longitudinal direction Set by means of leveling points No. 1 and 7 on the fuselage with a maximum difference of 0.039 inch (1 mm). Page 4 of 21 Maximum Weight Maximum ramp weight 14,594 lbs Maximum takeoff weight 14,550 lbs Maximum landing weight 14,109 lbs Maximum zero fuel weight 13,007 lbs Note: All maximum weights listed above include the following fluids: unusable fuel, engine oil, hydraulic fluid, and water for injection (see Note 1 for fluid weights). Minimum Crew 2 pilots. Pilot-in-Command is on the left viewed looking forwards except for training and checking Number of Seats. Passenger Version Cargo Version Seat Moment Arm 19 seats 17 seats 3 seats Station 48.62 3 3 - Station 78.54 3 3 - Station 108.46 3 3 - Station 138.39 3 3 - Station 168.31 3 3 - Station 198.23 2 2 1 Station 228.15 2 - 2 Maximum Baggage All versions (front) 234 lbs at station -52.48. Maximum baggage floor loading density 81.9 lb/ft2 Maximum passenger floor loading density 81.9 lb/ft2 19 passenger version (rear) 331 lbs at station 261.81. 17 passenger version with small baggage compartment and toilet (rear) 331 lbs at station 237.60. 17 passenger version with large baggage compartment and toilet (rear) 331 lbs at station 261.81. 17 passenger version with large baggage compartment without toilet (rear) 500 lbs at station 249.61. Cargo version (rear) 331 lbs at station 261.81. 2,204 lbs total cargo located at 1,102 lbs at station 138.39. 1,102 lbs at station 78.74. Fuel Capacity Wing tanks 2,204 lbs at station 123.39. 20 lbs unusable fuel. Optional wing tip tanks 692 lbs at station 122.20 8 lbs unusable fuel. Page 5 of 21 Oil Capacity Oil tank capacity per engine maximum 1.85 gallons at station 72.56. minimum 1.45 gallons at station 72.56. Maximum Operation Altitude Pressure altitude for Normal operations 20,000 ft (14,000 ft. for S/N 922729A see Note 4) Pressure altitude for takeoff and landing 13,120 ft Control Surface Movements Unless otherwise specified, the angle of deflection is between the control surface chord and the [wing, stabilizer, fin] chord. Reference (0°) is the neutral position. Aileron Up 27o + 1o - 1° Down 14o + 1o - 1° Left aileron trim tab Up 20o + 2o - 2° Down 20o + 2o - 2° Wing Flaps outer sections Takeoff Down 18o + 1o - 1° Landing Down 42o + 1o - 1° inner sections Landing Down 52o + 1.5o - 0° Ground spoilers Up 72.5o + 2o - 2° Automatic Bank Control Tab Up 55o + 2o - 2° Elevator Up 30o + 1o - 1° Down 14o + 1o - 1° Elevator trim tab Up 10o + 1o - 1° Down 16o + 1o - 1° Rudder Left 17o + 0° - 0.5o (measured parallel to 0.0 W.L.) Right 17o + 0° - 0.5o Rudder trim tab Left 10o + 0° - 1o (measured parallel to 0.0 W.L.) Right 10o + 0° - 1.5o Nose Wheel Steering Manual Left 50o approx. Right 50o approx. Pedal (Takeoff, Landing) Left 4.5o + 1.5o - 0° Right 4.5o + 1.5o - 0° Manufacturer’s Serial Numbers 92-27-29A and subsequent. When eligible, each airplane must have unique manufacturer’s serial number in the format: YY-BB-NNA; where “YY” is the year of manufacture, “BB” is the batch number, “NN” is the aircraft number (in the batch), immediately followed by the letter A. Certification Basis The regulations (unless otherwise stated) are Title 14 of the Code of Federal Regulations (14 CFR): 1) Date of original application for U.S. Type Certificate, March 11, 1991 2) 14 CFR 21.29, 21.183(c), and 21.50(b) effective February 1, 1965, including Amendments 21-1 through 21-70 effective December 31, 1992. 3) 14 CFR part 23 effective February 1, 1965, including amendments 23-1 through 23-41 effective November 26, 1990. 4) 14 CFR part 36 effective November 18, 1969, including Amendments 36-1 through Amendment 36-20. 5) 14 CFR part 34 effective September 10, 1990 Page 6 of 21 6) Czech Republic Civil Aviation Authority (CAA) issued Czech Republic Type Certificate No 98-01, dated March 11, 1998. 7) Exemptions: None 8) Equivalent Level of Safety: None 9) The airplane is approved for ditching. 10) The airplane is approved for flight in the full range of icing conditions according to 14 CFR part 25, Appendix C. The Civil Aviation Authority of the Czech Republic (CAA-CZ) originally type certificated this aircraft under its type certificate Number 71-04. The FAA validated this product under U.S. Type Certificate Number A42CE. The European Aviation Safety Agency (EASA) issued their type certificate on August 19, 2005 and began oversight of this product on behalf of the Czech Republic. The EASA TCDS number is EASA.A.026 . Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the aircraft for airworthiness certification, (FAA Master Minimum Equipment List, LET-420, Revision Original or later approved revision). In addition, the following items of equipment are required: Czech CAA approved Airplane Flight Manual Do-L410-1311.2 dated March 11, 1998 or later approved revisions. II. Models L 410 UVP-E20 and L 410 UVP-E20 CARGO (Commuter Category) approved June 30, 2015. Engines GE Aviation Czech s.r.o. GE H80-200 Type Certificate E00048EN Quantity Two (2) Fuel T-1 according to ST SEV 5024-85 or GOST 10227-86 TS-1 according to ST SEV 5024-85 or GOST 10227-86 or CSN 656 520 RT according to ST SEV 5024-85 or GOST 10227-86 or CSN 656 520 PL-6 according to PND 25005-76 PL-7 according to PND 25005-92 JET-A according to ASTM-D1655-89 JET A-1 according to ASTM-D1655-89 or DERD 2494 PSM 2 according to PN-86/C-96026 Engine Limits Maximum power (kW) Maximum gas generator speed (%) Maximum propeller speed (rpm) Maximum ITT °C Maximum continuous power rating 522 98.4 1,700-2,080 720 Take-off power rating 597 101.5 2,080 780 Continuous OEI power rating 597 101.5 2,080 780 Propeller and Propeller Limits Propeller Avia Propeller, s.r.o. Five blade AV-725-1 Type Certificate P34BO Quantity Two (2) Pitch setting measured at 68.82 inch diameter Feather +79.7° Minimum +13.5° High +79.7° Page 7 of 21 Reverse - 25.4° Diameter: Maximum 90.63 inches Minimum 90.47 inches No further reduction permitted below minimum diameter. Speed Maximum 2,080 RPM Power Maximum 635 kW Pitch- Control Hydraulic Regulator P-W22-1 Electro-Hydraulic Actuator LUN 7880.01-8 De-ice Auxiliary Pump AFP-28-3 Timing Relay LUN 2601A-8 Timer LUN 3193.1-8 Brush Block Assembly P/N 300-399 Rotation Clockwise viewed from slip stream Note: Certified propeller assembly number is AV-725-1-E-C-F-R(W)/CFR230-433 and includes all listed components. Airspeed Limits All speeds are indicated airspeeds. Maximum operating limit speed VMO 182 KIAS 337 km/hr IAS Operating maneuvering speed VO 147 KIAS 273 km/hr IAS Design speed for maximum gust intensity VB 147 KIAS 273 km/hr IAS Maximum landing gear operated speed VLO 140 KIAS 260 km/hr IAS Maximum landing gear extended speed VLE 140 KIAS 260 km/hr IAS Maximum flaps extended speed for flaps 18o VFE 135 KIAS 250 km/hr IAS for flaps 42o VFE 116 KIAS 216 km/hr IAS Maximum flaps operated speed for flaps 18o VFO 135 KIAS 250 km/hr IAS for flaps 42o VFO 111 KIAS 205 km/hr IAS Minimum control speed for take-off run (the same for flaps 0° and 18°) VMCG 66 KIAS 120 km/hr IAS for take-off, flaps 18° VMCA 77 KIAS 142 km/hr IAS for take-off, flaps 0° VMCA 89 KIAS 164 km/hr IAS for landing VMCL 74 KIAS 136 km/hr IAS Center of Gravity (C.G.) Range All C.G.’s are with landing gear extended. Mean Aerodynamic Chord (MAC) 75.50 inches MAC leading edge located at station 86.26 Forward C.G. at 9,920 lbs 19 percent of MAC Station 100.59 Forward C.G. at 14,550 lbs 26 percent of MAC Station 105.91 Aft C.G. at 14,550 lbs 30 percent of MAC Station 108.90 Page 8 of 21 Notes: Forward C.G. ranges linearly between 11,020 and 14,550 lbs For weights below 11,020 the forward C.G. is constant at 19 percent MAC. Effect of landing gear retraction is 0.217 percent MAC forward. See Note 1 for additional information on weight and balance. Empty Weight C.G. Range None Datum Reference point No. 2 marked on fuselage, located 107.48 in. behind the fuselage nose. Station locations are numbered aft positive and forward negative. Leveling Means With empty aircraft on jacks in basic configuration with extended landing gear: Lateral direction Set by means of leveling points No. 19 on the left and right wing with a maximum difference of 0.039 inch (1 mm). Longitudinal direction Set by means of leveling points No. 1 and 7 on the fuselage with a maximum difference of 0.039 inch (1 mm). Maximum Weight Maximum ramp weight 14,594 lbs 6,620 kg Maximum takeoff weight 14,550 lbs 6,600 kg Maximum landing weight 14,109 lbs 6,400 kg Maximum zero fuel weight without WTT with WTT 13,227 lbs 13,360 lbs 6,000 kg 6,060 kg Note: All maximum weights listed above include the following fluids: unusable fuel, engine oil, hydraulic fluid, and water for injection (see Note 1 for fluid weights). Minimum Crew 2 pilots. Pilot-in-Command is on the left viewed looking forwards except for training and checking Number of Seats. L 410 UVP-E20 Seat Moment Arm 19 seats Station 48.62 3 Station 78.54 3 Station 108.46 3 Station 138.39 3 Station 168.31 3 Station 198.23 2 Station 228.15 2 Maximum Baggage L 410 UVP-E20 and L 410 UVP-E20 CARGO (front) 234 lbs at station -52.48. Maximum baggage floor loading density 81.9 lb/ft2 Maximum passenger floor loading density 81.9 lb/ft2 L 410 UVP-E20 (rear) 331 lbs at station 261.81. L 410 UVP-E20 CARGO (rear) 331 lbs at station 261.81. 3,747 lbs total cargo located at 2,094 lbs at station 92.17. 1,653 lbs at station 182.00. Fuel Capacity Wing tanks 2,204 lbs at station 123.39. Page 9 of 21 20 lbs unusable fuel. Optional wing tip tanks 692 lbs at station 122.20 8 lbs unusable fuel. Oil Capacity Oil tank capacity per engine maximum 1.85 gallons at station 72.56. minimum 1.45 gallons at station 72.56. Maximum Operation Altitude Pressure altitude for Normal operations 14,000 ft Pressure altitude for takeoff and landing 13,120 ft Control Surface Movements Unless otherwise specified, the angle of deflection is between the control surface chord and the [wing, stabilizer, fin] chord. Reference (0°) is the neutral position. Aileron Up 27o + 1o - 1° Down 14o + 1o - 1° Left aileron trim tab Up 20o + 2o - 2° Down 20o + 2o - 2° Wing Flaps Takeoff Down 18o + 1o - 1° Landing Down 42o + 1o - 1° Ground spoilers Up 72.5° + 2o - 2° Automatic Bank Control Tab Up 55o + 2o - 2° Elevator Up 30o + 1o - 1° Down 14o + 1o - 0° Elevator trim tab Up 10o + 1o - 1° Down 16o + 1o - 1° Rudder Left 17o + 0° - 0.5o (measured parallel to 0.0 W.L.) Right 17o + 0° - 0.5o Rudder trim tab Left 10o + 0° - 1o (measured parallel to 0.0 W.L.) Right 10o + 0° - 1.5o Nose Wheel Steering Manual Left 50o approx. Right 50o approx. Pedal (Takeoff, Landing) Left 4.5o + 1.5o - 0° Right 4.5o + 1.5o - 0° Manufacturer’s Serial Numbers When eligible, each airplane must have unique manufacturer’s serial number in the format: BB-NNF, where BB is the batch number, NN is the aircraft number in the batch, immediately followed by the letter F. (Note 7 and Note 11) Certification Basis (Note 8) The regulations (unless otherwise stated) are Title 14 of the Code of Federal Regulations (14 CFR): 1) 14 CFR part 21 section 21.20 (a) and (b), including amendments 21-1 through 21-92, effective April 16, 2011 14 CFR Part 21.21(b), including amendments 21-1 through 21-92, effective April 16, 2011. 2) The regulations (unless otherwise stated) are Title 14 of the Code of Federal Regulations (14CFR): Page 10 of 21 14 CFR Part 23 dated February 1, 1965, as amended through Amendment 23- 41 effective November 26, 1990 with the exception of: 14 CFR Part 23 Sections 23.831, 23.939 which are at Amendment 42; 14 CFR Part 23 Sections 23.937, 23.961, 23.1011, 23.1322, 23.1331, 23.1357 which are at Amendment 43; 14 CFR Part 23 Sections 23.23, 23.181, 23.305, 23.361, 23.613, 23.655, 23.851, 23.1525, 23.1527, 23.1549 which are at Amendment 45; 14 CFR Part 23 Sections 23.803, 23.807, 23.813 are at Amendment 46; 14 CFR Part 23 Sections 23.301, 23.337, 23.341, 23.371, 23.393, 23.415, 23.561, 23.607, 23.611, 23.657, 23.865 which are at Amendment 48; 14 CFR Part 23 Sections 23.785, 23.787, 23.855, 23.1303, 23.1307, 23.1309, 23.1311, 23.1321, 23.1323, 23.1329, 23.1351, 23.1359, 23.1361, 23.1365, 23.1431, 23.1457, 23.1459 which are at Amendment 49; 14 CFR Part 23 Sections 23.3, 23.25, 23.51, 23.55, 23.57, 23.59, 23.67, 23.77, 23.145, 23.147, 23.149, 23.177, 23.201, 23.203, 23.1325, 23.1521, 23.1543, 23.1545, 23.1563, 23.1581, 23.1583, 23.1585, 23.1587, 23.1589 which are at Amendment 50; 14 CFR Part 23 Sections 23.925, 23.929, 23.933, 23.937, 23.955, 23.1041, 23.1043, 23.1045 which are at Amendment 51; 14 CFR Part 23 Sections 23.1305 which is at Amendment 52; 14 CFR Part 23 Sections 23.901 which is at Amendment 53; 14 CFR Part 23 Sections 23.903 which is at Amendment 54; 14 CFR Part 23 Sections 23.1308 which is at Amendment 57; 14 CFR Part 23 Sections 23.905, 23.907 which are at Amendment 59, The L 410 UVP-E20 CARGO model is identical to the L 410 UVP-E20 with the addition of the following regulation at a higher amendment level: 14 CFR Part 23 Section 23.1557 which are at Amendment 45; 3) 14 CFR Part 36 dated December 1, 1969, as amended through amendment in effect on the date of issuance of the U.S. type certificate (currently Amendment 36-30 effective May 5, 2014). 4) 14 CFR Part 34 dated September 10, 1990, as amended through Amendment 34-5A effective October 23, 2014. 5) Exemptions: None 6) Equivalent Level of Safety per 21.21(b)(1): a) ELOS ACE-14-13 dated Dec. 04, 2014, Cockpit Controls, 14 CFR 23.777(d) at Amendment 23-33. b) ELOS ACE-14-14 dated Nov. 25, 2014, Airspeed Indication, 14 CFR 23.1545 (b)(4), (b)(5) and (d) at amendment 23-50. 7) The airplane is approved for ditching. 8) The airplane is approved for flight in the full range of icing conditions according to 14 CFR part 25, Appendix C. Page 11 of 21 9) European Aviation Safety Agency (EASA) issued Type Certificate No. EASA.A.026, dated March 28, 2007. Date of Application for U.S. Amended Type Certificate for L 410 UVP -E20 and L 410 UVP-E20 CARGO – November 25, 2013 The Civil Aviation Authority of the Czech Republic (CAA-CZ) originally type certificated this aircraft under its type certificate Number 71-04. The European Aviation Safety Agency (EASA) issued their type certificate for these models on February 4, 2005 and began oversight of this product on behalf of the Czech Republic. The EASA TCDS number is EASA.A.026. Equipment (Note 9) The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the aircraft for airworthiness certification, (FAA Master Minimum Equipment List, Aircraft Industries L 410/L-420, Revision 2 or later approved revision). In addition, the following items of equipment are required: Airplane Flight Manual, Do-L410-1218.2-FAA, dated December 12, 2014, Initial Release or later approved revisions., Supplement to the AFM No. 94, L 410 UVP-E20 CARGO, December 6, 2006, Initial Release or later approved revisions. III. Models L 410 NG (Commuter Category) approved January 10, 2018. Engines GE Aviation Czech s.r.o. GE H85-200 BC04 Type Certificate E00048EN Quantity Two (2) Fuel JET A1 according to ASTM D 1655 or DERD 2494 RT according to ST SEV 5024 or GOST 10227 or CSN 65 6520 TS−1 according to ST SEV 5024 or GOST 10227 or CSN 65 6520 PSM 2 according to PN 86/C 96026 T−1 according to ST SEV 5024 or GOST 10227 PL−6 according to PND 25 005 76 PL−7 according to PND 25 005 92 JET A according to ASTM D 1655 or DERD 2494 Engine Limits Maximum power (kW) Maximum gas generator speed (%) Maximum propeller speed (rpm) Maximum ITT °C Take-off power rating 634 101.5 1950 780 Maximum continuous power rating 634 101.2 1950 770 Page 12 of 21 Propeller and Propeller Limits Propeller Avia Propeller, s.r.o. Five blade AV-725-1-E-C-F-R(W)- A/CFR230-433 Type Certificate P34BO Quantity Two (2) Pitch setting measured at 68.82 inch diameter Feather +79.7° Minimum +13.5° High +79.7° Reverse - 25.4° Diameter: Maximum 90.63 inches Minimum 90.47 inches No further reduction permitted below minimum diameter. Speed Maximum 2,080 RPM Power Maximum 635 kW Pitch- Control Hydraulic Regulator P-W25-2 Electro-Hydraulic Actuator LUN 7880.01-8 De-ice Auxiliary Pump AFP-28-3A Timing Relay LUN 2601A-8 Timer LUN 3193.1-8 Brush Block Assembly P/N 300-399 Rotation Clockwise viewed from slip stream Note: Certified propeller assembly number is AV-725-1-E-C-F-R(W)/CFR230-433 and includes all listed components. Airspeed Limits All speeds are indicated airspeeds. Max. operating speed (14,000 ft) VMO 210 KIAS 389 km/hr IAS Operating maneuvering speed (7,000 kg) VO 154 KIAS 285 km/hr IAS Maximum speed in turbulence (7,000 kg) VB 157 KIAS 292 km/hr IAS Maximum landing gear operated speed VLO 164 KIAS 304 km/hr IAS Maximum landing gear extended speed VLE 164 KIAS 304 km/hr IAS Maximum flaps extended speed for flaps 18o VFE 150 KIAS 278 km/hr IAS for flaps 42o VFE 124 KIAS 230 km/hr IAS Maximum flaps operated speed for flaps 18o VFO 150 KIAS 278 km/hr IAS for flaps 42o VFO 124 KIAS 230 km/hr IAS Minimum control speed for take-off run (the same for flaps 0° and 18°) VMCG 66 KIAS 122 km/hr IAS for take-off, flaps 18° VMCA 77 KIAS 143 km/hr IAS for take-off, flaps 0° VMCA 87 KIAS 161 km/hr IAS for landing VMCL 73 KIAS 134 km/hr IAS Page 13 of 21 Center of Gravity (C.G.) Range All C.G.’s are with landing gear extended. Mean Aerodynamic Chord (MAC) 75.50 inches MAC leading edge located at station 86.26 Forward C.G. at 11,023 lbs 19 percent of MAC Station 100.6 Forward C.G. at 15,432 lbs 27,8 percent of MAC Station 107.2 Aft C.G. at 15,432 lbs 30 percent of MAC Station 108.9 Notes: Forward C.G. ranges linearly between 11,464 and 15,432 lbs. For weights below 11,464 the forward C.G. is constant at 18 percent MAC. Effect of landing gear retraction is 0.331 percent MAC forward. Empty Weight C.G. Range None Datum Reference point No. 2 marked on fuselage, located 107.48 in. behind the fuselage nose. Station locations are numbered aft positive and forward negative. Leveling Means With empty aircraft on jacks in basic configuration with extended landing gear: Lateral direction Set by means of leveling points No. 19 on the left and right wing with a maximum difference of 0.039 inch (1 mm). Longitudinal direction Set by means of leveling points No. 1 and 7 on the fuselage with a maximum difference of 0.039 inch (1 mm). Maximum Weight Maximum ramp weight 15,476 lbs 7,020 kg Maximum takeoff weight 15,432 lbs 7,000 kg Maximum landing weight 14,991 lbs 6,800 kg Maximum zero fuel weight without WTT with WTT 14,550 lbs 14,683 lbs 6,600 kg 6,660 kg Note: All maximum weights listed above include the following fluids: unusable fuel, engine oil, hydraulic fluid, and water for injection (see Note 1 for fluid weights). Minimum Crew 2 pilots. Pilot-in-Command is on the left viewed looking forwards except for training and checking Number of Seats. L 410 NG Seat Moment Arm 19 seats Station 48.6 3 Station 78.5 3 Station 108.5 3 Station 138.4 3 Station 168.3 3 Station 198.2 2 Station 227.8 2 Page 14 of 21 Maximum Baggage L 410 NG (front A) 287 lbs at station -86.2 (front B) 375 lbs at station -52.5 Maximum baggage floor loading density 81.9 lb/sq.ft Maximum passenger floor loading density 81.9 lb/sq.ft (rear) 331 lbs at station 261.8. Fuel Capacity Wing tanks 4,122 lbs at station 123.4. 35 lbs unusable fuel. Optional wing tip tanks 868 lbs at station 105.3 8 lbs unusable fuel. Oil Capacity Oil tank capacity per engine maximum 1.85 gallons at station 72.56. minimum 1.45 gallons at station 72.56. Maximum Operation Altitude Pressure altitude for Normal operations 20,000 ft Pressure altitude for takeoff and landing 13,100 ft Control Surface Movements Unless otherwise specified, the angle of deflection is between the control surface chord and the [wing, stabilizer, fin] chord. Reference (0°) is the neutral position. Aileron Up 27o + 1o - 1° Down 14o + 1o - 1° Aileron trim tab (left aileron only) Up 20o + 2o - 2° Down 20o + 2o - 2° Wing Flaps Takeoff Down 18o + 1o - 1° Landing Down 42o + 1o - 1° Ground spoilers Up 72.5° + 2o - 2° Automatic Bank Control Tab Up 55o + 2o - 2° Elevator Up 30o + 1o - 1° Down 14o + 1o - 0° Elevator trim tab Up 10o + 1o - 1° Down 20o + 1.5o - 0° Rudder Left 25o + 1° - 0o (measured parallel to 0.0 W.L.) Right 25o + 1° - 0o Rudder trim tab Left 28o + 1.5° - 0o (measured parallel to 0.0 W.L.) Right 28o + 1.5° - 0o Nose Wheel Steering Manual Left 50o approx. Right 50o approx. Pedal (Takeoff, Landing) Left 4.5o + 1.5o - 0° Right 4.5o + 1.5o - 0° Page 15 of 21 Manufacturer’s Serial Numbers When eligible, each airplane must have unique manufacturer’s serial number in the format: XXYY, where XX is number of the batch starting with 50 and YY is a number of the airplane in the batch. Except S/N 2820 which is the first prototype L410NG. Certification Basis The regulations (unless otherwise stated) are Title 14 of the Code of Federal Regulations (14 CFR): 1) 14 CFR part 21.29 and part 21.183(c) 2) 14 CFR Part 23 dated February 1, 1965, as amended through Amendment 23- 41 effective November 26, 1990 with the exception of: 14 CFR Part 23 Sections 23.331, 23.351, 23.421, 23.423, 23.425, 23.427, 23.831, 23.939 which are at Amendment 42; 14 CFR Part 23 Sections, 23.937, 23.943, 23.951, 23.953, 23.957, 23.961, 23.967, 23.971, 23.977, 23.991, 23.993, 23.997, 23.999, 23.1011, 23.1147, 23.1189, 23.1322, 23.1357, 23.1441 which are at Amendment 43; 14 CFR Part 23 Sections 23.23, 23.141, 23.305, 23.321, 23.361, 23. 479, 23.485, 23.613, 23.655, 23.672, 23.731, 23.733, 23.773, 23.851, 23.1507, 23.1525, 23.1527, 23.1549, 23.1557 which are at Amendment 45; 14 CFR Part 23 Sections 23.803, 23.807, 23.813 are at Amendment 46; 14 CFR Part 23 Sections 23.301, 23.335, 23.337, 23.341, 23.343,23.3 47, 23.349, 23.371, 23.393, 23.415, 23.441, 23.443, 23.455, 23.473, 23.499, 23.561, 23.572, 23.573, 23.574, 23.575, 23.607, 23.611, 23.621, 23.657, 23.725, 23.865 which are at Amendment 48; 14 CFR Part 23 Sections 23.677, 23.723, 23.729, 23.745, 23.785, 2 3.787, 23.791, 23.855, 23.867, 23.1307, 23.1321, 23.1326, 23.1329, 23.1351, 23.1359, 23.1361, 23.1365, 23.1435, 23.1457, 23.1459 which are at Amendment 49; 14 CFR Part 23 Sections, 23.25, 23.69, 23.75, 23.145, 23.147, 23.149, 23.153, 23.155, 23.157, 23.161, 23.175, 23.207, 23.233, 23.235, 23.1325, 23.1511, 23.1521, 23.1543, 23.1553, 23.1581, 23.1589 which are at Amendment 50; 14 CFR Part 23 Sections 23.779, 23.925, 23.929, 23.933, 23.955, 23.959, 23.963, 23.965, 23.973, 23.975, 23.979, 23.1041, 23.1043, 23.1045, 23.1141, 23.1143, 23.1191, 23.1337 which are at Amendment 51; 14 CFR Part 23 Sections 23.1305 which is at Amendment 52; 14 CFR Part 23 Sections 23.901 which is at Amendment 53; 14 CFR Part 23 Sections 23.1308, 23.1457, 23.1459 which is at Amendment 57; 14 CFR Part 23 Sections 23.905, 23.907 which are at Amendment 59; 14 CFR Part 23 sections 23.1306 at amendment 61; Page 16 of 21 14 CFR Part 23 sections 23.3, 23.45, 23.49, 23.51, 23.53, 23.55, 23.57, 23.59, 23.61, 23.63, 23.67, 23.73, 23.77, 23.177, 23.181, 23.201, 23.203, 23.251, 23.253, 23.561, 23.629, 23.703, 23.735, 23.777, 23.853, 23.903, 23.1301, 23.1303, 23.1309,23.1310, 23.1311,23.1323, 23.1331, 23.1353, 23.1431, 23.1443, 23.1447, 23.1505, 23.1545, 23.1555, 23.1559, 23.1563, 23.1583, 23.1585, 23.1587 at amendment 62 3) 14 CFR Part 36 dated December 1, 1969, as amended through amendment in effect on the date of issuance of the U.S. type certificate (currently Amendment 36-30 effective May 5, 2014). 4) 14 CFR Part 34 dated September 10, 1990, as amended through Amendment 34-5A effective October 23, 2014. 5) Special Conditions: None 6) Exemptions: None 7) Equivalent Level of Safety per 21.21(b)(1): a) ELOS AT00724CE-A-F-2 dated January 19, 2016, Amendment 23-62, 14 CFR 23.45, 23.51, 23.63, 23.67, 23.73, 23.77, 23.161, 23.181, 23.221, 23.251, 23.253, 23.571, 23.785, 23.831, 23.1195, 23.1197, 23.1199, 23.1201, 23.1527, 23.1545, and 23.1583; b) ELOS AT00724CE-A-S-2 dated November 29, 2016, Airspeed Indication –Flap Marking, 14 CFR 23.1545 (b)(4), amendment 23-62; c) ELOS AT00724CE-A-P-1 dated January 23, 2017, Digital Only Powerplant Indications, 14 CFR 23.1305(a)(2), (a)(3), (c)(2), and (c)(5), amendment 23-52; 23.1549(a), (b), and (c), amendment 23-45; d) ELOS AT00724CE-A-S-1 dated February 6, 2017, Cockpit Controls, 14 CFR 23.777(d), amendment 23-62 e) ELOS AT00724CE-A-S-3 dated October 6, 2017, Landing Gear Control, 14 CFR 23.777(g), amendment 23-62 8) The airplane is approved for flight into known or forecasted icing. Compliance has been demonstrated in accordance with 14 CFR § 23.1416 and 23.1419 . 9) The airplane is approved for ditching. Compliance with the provisions for ditching equipment in accordance with 14 CFR § 23.807 and § 23.1415(a)(b) has been demonstrated. 10) European Aviation Safety Agency (EASA) issued Type Certificate No. EASA.A.026, Issue 24, dated December 19, 2017. Date of Application for U.S. Amended Type Certificate for L 410 NG – November 7, 2014. Page 17 of 21 Equipment (Note 9) The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the aircraft for airworthiness certification, (FAA Master Minimum Equipment List, Do-L410NG-3000.2, IR or later approved revisions). In addition, the following items of equipment are required: Airplane Flight Manual, Do-L410NG-1210.2, Revision IR, dated Nov. 30, 2017 or later approved revisions. Cargo kit with cargo restrain system for 1700 kg (Do-L410NG-1210.2 AFM Supplement No. 1, IR, dated August 30, 2017, or later approved revisions) Ambulance kit (9 lying patients) (Do-L410NG-1210.2 AFM Supplement No. 2, IR, dated August 30, 2017, or later approved revisions) Sport parachuting kit (Do-L410NG-1210.2 AFM Supplement No. 3, IR, dated August 30, 2017, or later approved revisions) Passenger to cargo quick change configuration with foldable seats (Do-L410NG- 1210.2 AFM Supplement No. 4, IR, dated August 30, 2017, or later approved revisions) DATA PERTINENT TO ALL MODELS – L-420, L 410 UVP-E20 ,L 410 UVP-E20 CARGO and L 410 NG Validation Basis Type Certificate for the L 420 was issued pursuant to FAR 21.29(a) in validation of a Civil Aviation Authority of the Czech Republic (CAA-CZ) certification of compliance with the above mentioned Certification Basis. The L 410 UVP-E20, L 410 UVP-E20 CARGO and L 410 NG models were issued pursuant to FAR 21.29(a) in validation of a European Aviation Safety Agency (EASA) certification of compliance with the above mentioned Certification Basis. Import Requirements (Note 7 and Note 11) The FAA can issue a U.S. airworthiness certificate based on an NAA Export Certificate of Airworthiness (Export C of A) signed by a representative of the Civil Aviation Authority of the Czech Republic (CAA-CZ) on behalf of the European Community. The Export C of A should contain the following statement: ‘The aircraft covered by this certificate has been examined, tested, and found to comply with U.S. airworthiness regulations 14 CFR Federal Aviation Regulations Part 23, U.S. Type Certificate No. A42CE and to be in a condition for safe operation.’ For eligible aircraft with previous time in service, the airframe, engine, and propeller total times and times since overhaul, where appropriate, must be furnished. In addition, the status of all life-limited components must also be furnished. Refer to the applicable bilateral agreement to verify eligibility for import into the United States of both new and used aircraft based on the scope of the agreement, to identify any required statements by the exporting authority on the export cer tificate of airworthiness (or equivalent document), and for procedures for coordinating exceptions to conformity statements on these documents. Refer to FAA Order 8130.2, Airworthiness Certification of Aircraft, for requirements for issuance of an airworthiness certificate for imported aircraft. Page 18 of 21 The U.S. airworthiness certification basis for this aircraft type certificated under FAR § 21.29 and exported by the country of manufacture is FAR § 21.183 (c). Per 21.50(b), Instructions for Continued Airworthiness complying with 14 CFR 23.1529, must be furnished before delivery of the first airplane or issuance of a U.S. standard certificate of airworthiness, whichever occurs later. Service Information Each of the documents listed below must state that it is approved by the European Aviation Safety Agency (EASA) or – for approvals made before May 17, 2006 – by the Civil Aviation Authority of the Czech Republic (CAA-CZ). • Service bulletins, • Structural repair manuals, • Vendor manuals, • Aircraft flight manuals, and • Overhaul and maintenance manuals. The FAA accepts such documents and considers them FAA-approved for type design data only unless one of the following conditions exists: • The documents change the limitations, performance, or procedures of the FAA approved manuals; or •The documents make an acoustical or emissions changes to this product’s U.S. type certificate as defined in 14 CFR § 21.93. The FAA uses the post type validation procedures to approve these documents. The FAA may delegate on case-by-case to EASA to approve on behalf of the FAA for the U.S. type certificate. If this is the case it will be noted on the document. Each LET Model L-420 series airplane is provided with the following documents: Airplane Flight Manual Do-L410-1311.2 dated March 11, 1998 or later approved revisions. Maintenance Manual, Do-L410-1233.2, Revision No. 3 dated June 29, 2007 or later approved revisions. Maintenance Schedule, Do-L420-1224.2, dated August 17, 2012 or later approved revisions. Each LET Model L 410 UVP-E20 and L 410 UVP-E20 CARGO airplane is provided with the following documents: (Note 6) and (Note 9) Airplane Flight Manual, Do-L410-1218.2-FAA, dated December 12, 2014, Initial Release or later approved revisions. Supplement to the AFM No. 94, L 410 UVP-E20 CARGO, December 6, 2006, Initial Release or later approved revisions. Instruction for Continued Airworthiness (ICAs) include: Maintenance Schedule for the L 410 UVP-E20 Airplane, Do-L410-1223.2-FAA, IR, December 12, 2014 or later approved revisions. (Note 3) Maintenance Manual for the L410 UVP-E, -E9, -E20 Aeroplane, Do-L410-1232.2, April 15, 2015, Revision 30 or later approved revisions. Page 19 of 21 AMM Supplement No. 124: L 410 UVP-E20 CARGO, Do-L410-1232.2, August 12, 2013, Revision 1 or later approved revisions. AMM Supplement No. 270: FAA VALIDATED L 410 UVP-E20 MODEL WITH GE H80-200 ENGINES AND AV-725 PROPELLERS, Do-L410-1232.2, IR, June 20, 2014 or later approved revisions. Each LET Model L 410 NG airplane is provided with the following documents: Airplane Flight Manual, Do-L410NG-1210.2, dated November 30, 2017, Initial Release or later approved revisions. Instruction for Continued Airworthiness (ICAs) include: (Note 10) Maintenance Schedule for the L 410 NG Airplane, Do-L410NG-1220.2, IR, dated November 30, 2017 or later approved revisions. (Note 3) Maintenance Manual for the L410 NG Airplane, Do-L410NG-1230.2, IR, dated November 30, 2017 or later approved revisions. Notes Note 1 Current weight and balance report including list of equipment in certificated empty weight, and loading instructions, when necessary, must be provided for each aircraft at the time of original certification The certificated empty weight and corresponding center of gravity positions include the weight of unusable fuel, engine oil, hydraulic fluid in tanks and in the systems as noted below: (L 410 NG see above) Unusable fuel 20 lbs if wing tip tanks installed + 8 lbs Oil 47.6 lbs Hydraulic fluid 39.4 lbs Water for Water Injection Tank (not included in empty weight), maximum (L 410 NG engines do not have water injection) Station 101.1 49.6 lbs Note 2 Airplane operation must be in accordance with the EASA approved Airplane Flight Manual listed above. All placards listed in Section 2 must be displayed in clear view of the pilot. Note 3 Airworthiness Limitations are specified in the Section 2 LIMITATIONS chapter of the Flight Manual and Chapter 2 of the Maintenance Schedule (Do-L410-1223.2- FAA for the L 410 and Do-L420-1224.2 for the L-420 and Do-L410NG-1220.2 for L 410 NG)) that are part of the Instructions for Continued Airworthiness and are approved by EASA and the FAA. These LIMITATIONS specify mandatory replacement times, and operating limitations, and may not be changed without FAA approval. Revisions to the Airworthiness Limitations must be approved by the FAA. The inspections, maintenance, repair and painting must be accomplished according to the Maintenance Manual or other procedures acceptable to the FAA. Page 20 of 21 Note 4 The Czech CAA issued AD No. CAA-AD-T-037/2001R2, dated October 20, 2004, which included Model L-420 with serial number S/N 922729A that has not had mandatory Service Bulletin No. L-420/009a accomplished. Per the CAA issued AD, the following must be accomplished, before further flight, limit the maximum flight level from 20000 ft. to 14000 ft. Operators affected by this CAA AD should insert this AD into Aircraft flight Manual Section 2 page 2-4. Values of flight levels and Maximum Operating Limit Speeds mentioned in placard located near air speed indicator (in range from 14000 ft to 20000 ft) should be sealed up by foil with red color notice “DO NOT USE”. Modify by installing a placard in clear view to both pilots stating: “MAXIMUM FLIGHT LEVEL 14000 ft”. Reason for CAA AD: Incorrect indication of Maximum Operating Limit Speed Vmo in flight levels from 14000 to 20000 ft. Note 5 The following kits installation on the L 410 UVP-E20 model only and not the L 410 UVP-E20 CARGO model is approved: 1. Cargo kit determined for transport of 1700 kg of payload (TCDS EASA.A.026 Section EIII. 20) - EASA approved changes at amendment 23-55. 2. Ambulance kit determined for transport of 9 lying patients (TCDS EASA.A.026 Section EIII. 2) – EASA approved changes at amendment 23-50. 3. Sport parachuting kit (TCDS EASA.A.026 Section EIII. 2.) - EASA approved changes at amendment 23-50. 4. Passenger to cargo quick change configuration with foldable seats – EASA approved this change at amendment 23-50. List of approved L 410 NG Flight Manual Supplements for the following kits: 1. Cargo kit with cargo restrain system for 1700 kg (Do-L410NG-1210.2 AFM Supplement No. 1, IR, or later approved revisions); 2. Ambulance kit (9 lying patients) (Do-L410NG-1210.2 AFM Supplement No. 2, IR, or later approved revisions); 3. Sport parachuting kit (Do-L410NG-1210.2 AFM Supplement No. 3, IR, or later approved revisions); 4. Passenger to cargo quick change configuration with foldable seats (Do- L410NG-1210.2 AFM Supplement No. 4, IR, or later approved revisions). All above stated kits can be easily installed into each serial airplane after removal of standard passenger seats provided that provision for kits installation are incorporated into the aircraft during manufacturing process. Note 6 Additional service documents delivered with the L-420 and L 410 UVP-E20 and L 410 UVP-E20 CARGO airplanes are shown on the EASA TCDS Number EASA.A.026 Issue 18 dated May 13, 2015 or later issues. Note 7 Only Models L 410 UVP-E20 and L 410 UVP-E20 CARGO with the “F” included in the S/N BB-NNF are eligible for FAA standard airworthiness certificate. The L 410 UVP-E20 and L 410 UVP-E20 CARGO models with this S/N show that they have the required FAA modifications incorporated during the FAA validation project AT00682CE-A. These modifications are identified with AI top level drawing B 500 385 N for the L 410 UVP-E20 model, B 500 386 N for the l 410 UVP-E20 CARGO model and are incorporated during the production of the airplanes. AI will develop a Service Bulletin No. L 410 UVP-E / 413b for conversion of the existing EASA model versions of the L 410 UVP-E20 and L 410 UVP-E20 CARGO that Page 21 of 21 only AI can accomplish at their factory. No FAA Supplemental Type Certificates (STC) are allowed to make this conversion. Additionally no other L 410 or L 420 models without the above mentioned S/N identifier “F” are eligible for an FAA standard airworthiness certificate if they are converted to the L 410 UVP -E20 and L 410 UVP-E20 CARGO models. Note 8 TDC-186-E20-420 Design change Replacement of mechanical STBY instruments by ESI-2000 with MAG-3100 Magnetometers and replacement of dual GNS 430W by one GTN 750 and one GTN 650 was FAA validated on September 2, 2015. The certification basis for this change that was above the L 410 UVP-E20 base model certification basis: 14 CFR Part 23 Sections 23.773 at Amendment 45; 14 CFR Part 23 Sections 23.1555 at Amendment 50; 14 CFR Part 23 Sections 23.1306 at Amendment 61; 14 CFR Part 23 Sections 23.777, 23.1301, 23.1303, 23.1309, 23.1310, 23.1311, 23.1323, 23.1431 at Amendment 62; Note 9 Airplanes with type design change TDC-186-E20-420 (Note 8 above) must have the following additional documents: Supplement to the AFM No. 187, GARMIN GTN 650/750, dated March 23, 2015 or later approved revisions and Supplement to the AFM No. 188, ELECTRONIC STANDBY INDICATOR ESI-2000, Revision 1 dated August 27, 2015 or later approved revisions. ICAs: L 410 UVP-E, E9,E20 Maintenance Manual Supplement No. 281, Rev. 1, Dated August 03, 2015 or later approved revision and Appendix No. 70 of Maintenance Schedule (Do-L410-1223.2) for the ESI-2000 dated November 12, 2014 or later approved revision and Appendix No. 71 of Maintenance Schedule (Do-L410-1223.2) for the Garmin GTN 750 and GTN 650 Installation dated November 12, 2014 or later approved revision. Note 10 The rest of the L 410 NG ICAs are listed below and are all dated November 30, 2017 or later revisions: Illustrated Parts Catalogue Do-L410NG-1250.2 Wiring Manual Do-L410NG-1240.2 Structural Repair Manual Do-L410NG-2020.2 Album of Production, Operation and Repair Tolerances Do-L410NG-2030.2 Inspection Manual Do-L410NG-2010.2 Note 11 L 410 UVP-E20 and L 410 UVP-E20 CARGO models with the “R” included in The serial number, i.e. RBBNN, where BB is a batch number and NN is a number of an aircraft in the batch, are manufactured in Russia. Those serial numbers are not eligible for an FAA standard airworthiness certificate in the USA or registration in the EU Member States. (Ref: EASA TCDS EASA.A.026 Issue 24 Note 6) - END - ``` ## ADs (4, in force first) - [AD 2023-19-04](https://openairdocs.org/ad/2023-19-04): Landing Gear Brake System · Aircraft Industries a.s. L 410 UVP-E20, L 410 UVP-E20 CARGO and L-420. Effective Oct 10, 2023 - [AD 2021-14-02](https://openairdocs.org/ad/2021-14-02): Landing Gear Steering System · Aircraft Industries a.s. L-420, L 410 NG, L 410 UVP-E20 and 1 more. Effective Aug 2, 2021 - [AD 2018-11-04](https://openairdocs.org/ad/2018-11-04): Propellers/Propulsors · Aircraft Industries a.s. L 410 UVP-E20 and L 410 UVP-E20 CARGO. Effective Jun 27, 2018 - [AD 2013-11-02](https://openairdocs.org/ad/2013-11-02): Water Injection · Aircraft Industries a.s. L-420. Effective Jun 18, 2013 ## Registered aircraft by registry model (OpenAirDocs) - [Let L420](https://openairdocs.org/model/let-l420): 0 aircraft (registry code 1360313) ## STCs approved under this data sheet (7) - [STC SA02019SE-D](https://openairdocs.org/stc/SA02019SE-D): Installation of Garmin Model GTN 625/635/650; 725/750 Navigation System. Garmin International Inc. - [STC SA09887AC](https://openairdocs.org/stc/SA09887AC): Installation of an Avionica MK-III mini Quick Access Recorder (QAR) and optional 4G or LTE Avionica Cellular Module (avCM. Aircraft Systems and Manufacturing Inc. - [STC SA04514NY](https://openairdocs.org/stc/SA04514NY): Single/Dual Transponder System ADS-B Upgrade. Scandinavian Avionics Design ApS - [STC SA02677LA](https://openairdocs.org/stc/SA02677LA): Modification to upgrade the existing Mode S Transponder system by installing the ACSS NXT-700 Transponder with ADS-B Out and optionally install the ACSS NXG-900 GPS as the position source for ADS-B Out. Aviation Communication and Surveillance Systems (ACSS) LLC - [STC SA02678LA](https://openairdocs.org/stc/SA02678LA): Modification to upgrade the existing Mode S Transponder system by installing the ACSS NXT-600 Transponder with ADS-B Out and optionally install the ACSS NXG-900 GPS as the position source for ADS-B Out. Aviation Communication and Surveillance Systems (ACSS) LLC - [STC SA04165NY](https://openairdocs.org/stc/SA04165NY): Installation of Latitude Technologies Skynode S200 Satcom system must be performed. Latitude Technologies Corporation - [STC SA03973NY](https://openairdocs.org/stc/SA03973NY): Replacement of existing TCAS 7.0 by TCAS 7.1. Scandinavian Avionics Design ApS --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.