TCDS A42CE

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