# TCDS A00003SE: Textron Aviation Inc. - Type: Type certificate data sheet - Status: Current - Holder: Textron Aviation Inc. - Revision: 27 - Revised: June 22, 2016 - Product: Aircraft, Small Airplane - Certification basis: Part 23 - Registered aircraft: 827, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/e5/73/e5732b813b751899cc2517b1b10000d2722e8aca3279e8f458520cb3e942bc0a - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/C50383E299DB7B3786257FDB0059CC6F.0001 - Page: https://openairdocs.org/tcds/A00003SE ## Models (4) As the data sheet lists them. - LC42-550FG - LC41-550FG (Columbia 400) - T240 - LC40-550FG ## 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 Rev. No. 27 24 27 24 23 25 25 23 25 25 23 25 26 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A00003SE Revision 27 Textron Aviation Inc. LC40-550FG LC41-550FG LC42-550FG T240 June 22, 2016 TYPE CERTIFICATE DATA SHEET A00003SE This data sheet, which is part of Type Certificate No. A00003SE, prescribes conditions and limitations under which the product for which the type certificate was issued meets the airworthiness requirements of the Federal Aviation Regulations. Type Certificate Holder: Textron Aviation Inc. One Cessna Boulevard Wichita, Kansas 67215 Type Certificate Holder Record: Columbia Aircraft Manufacturing (previously The Lancair Company) 22550 Nelson Road Bend, Oregon 97701 Cessna Aircraft Company transferred to Textron Aviation Inc. on July 29, 2015 I. Model LC40-550FG (Utility Category), Approved September 18, 1998 Engine: Teledyne Continental Model IO-550-N (See NOTE 5), Engine Type Certificate E3SO. Fuel: 100 (green) or 100LL (blue) grade aviation fuel. Engine Limits: Maximum takeoff power and maximum continuous power = 310 horsepower at 2700 rpm. See Engine Type Certificate Data Sheet E3SO for additional limitations. Propeller: Hartzell Model PHC-J3YF-1RF/F7691D-1, Propeller Type Certificate P36EA Hartzell Spinner Assembly, Part No. C-6446-1 or C-6446-2(P) Propeller Limits: Minimum diameter = 76 inches Maximum diameter = 77 inches Low Pitch = 14.1° ± 0.2° High Pitch = 34.7° ± 1.0° Pitch limits measured at 30 inches radial distance. Do not exceed 20 inches manifold pressure with propeller RPM below 2200. See Propeller Type Certificate Data Sheet P36EA for additional limits. Airspeed Limits: VO (3400 lbs) 149 KCAS (148 KIAS) VO (2500 lbs) 128 KCAS (127 KIAS) VFE (Fully Extended) 120 KCAS (119 KIAS) VFE (Intermediate Setting) 130 KCAS (129 KIAS) VNO 180 KCAS (178 KIAS) VNE 235 KCAS (232 KIAS) Note: VNO decreases by 4 KIAS and VNE decreases by 5 KIAS for each 1000 feet above 12,000 feet (pressure altitude). A00003SE Page 2 of 13 Rev. 27 I. Model LC40-550FG (cont’d) C.G. Range: Straight line variation between points. Aft Limits 110 inches aft of datum from 2500 lbs to 3400 lbs. Forward Limits 103 inches aft of datum from 2240 lbs to 2500 lbs then to 107 inches aft of datum at 3400 lbs. Maximum zero fuel weight 103 inches aft of datum at 2725 lbs to 110 inches at 3228 lbs. Minimum flying weight 103 inches aft of datum at 2240 lbs to110 inches at 2500 lbs. Datum: The forward edge of the wing saddle is located 97.05 inches aft of the reference datum. Refer to “Model LC40-550FG Maintenance Manual,” Document No. 300MM02 or later revision for detailed instructions. Leveling Means: Plumb target and plumb line hanger are located in the rear seat area. Weight limits: Maximum ramp and takeoff = 3400 lbs. Maximum landing weight = 3230 lbs. Maximum empty weight = 2568 lbs. Maximum zero fuel weight = 2725 lbs at 103 inches varying linearly to 3228 lbs at 110 inches. Minimum flying weight = 2240 lbs at 103 inches varying linearly to 2500 lbs at 110 inches. Minimum Crew: 1 Pilot. No. of Seats: 4 seats total: 2 located at 110 inches aft of datum. 2 located at 141.4 inches aft of datum. Maximum Baggage: 20 pounds allowed on the hat shelf. 120 pounds total. Fuel Capacity: 106 gallons total; 98 gallons useable. (Two 53 gallon tanks in wings at 118.0 inches aft of datum). Oil Type and Capacity: 8 qts drainable. See Engine Type Certificate Data Sheet E3SO. Maximum Operating Altitude: 14,000 feet without FAA approved oxygen system installed. 18,000 feet with FAA approved oxygen system installed. Control Surface Movements: Wing flaps: Cruise 0° ±1° Take off 12° ±1° Landing 40° ±1° Ailerons: Up 21.6° ±1° Down 17.7° ±1° Aileron Trim Tab: Up 22.4° ±1° Down 19.6° ±1° Aileron Servo Tab: Up 13° ±2° at 17.7° aileron deflection Down 19° ±2° at 21.6° aileron deflection Elevator: Up 13° +0°-0.5° Down 12° ±1° Elevator trim tab: Up 21° ±1° Down 30° ±1° Rudder: Right 17° ±1° Left 17° ±1° Left, rudder limiter 11.5° ±0.5° Additional Limitations: Airframe life limit: 25200 flight hours. Kinds of operations: Day and Night, Visual Flight Rules (VFR) and Instrument Flight Rules (IFR). Required Maintenance: The airplane must be maintained in accordance with the instructions for continued airworthiness contained in the FAA approved Chapter 4 of “Model LC40-550FG Maintenance Manual,” Document No. 300MM02 or later revision. Rev. 27 Page 3 of 13 A00003SE I. Model LC40-550FG (cont’d) Required Equipment: The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the aircraft for airworthiness certification. In addition to the above required equipment, the following equipment is also required: The latest FAA Approved/Accepted Revision of “Pilots Operating Handbook and FAA Approved Flight Manual,” Document No. RA050001. The required equipment for various types of operations is specified in Appendix A to Section 6 of the latest FAA Approved Revision of Document No. RA050001. Design Data: The airplane shall be manufactured in accordance with the latest FAA approved revision of “Master Drawing List”, Document No. RA011002, or other FAA approved data. Serial Numbers Eligible: 40004 through 40079. Certification Basis: Part 23 of the Federal Aviation Regulations (FAR) effective February 1, 1965, as amended by 23-1 through 23-46. FAR 36 as amended on the date of certification. Application for type certificate, dated June 14, 1995. Equivalent Level of Safety (ELOS) Findings: Stall and spin requirements of FAR’s 23.201, 23.203, and 23.221 in accordance with ELOS No. ACE-98-1 as detailed in the FAA memo dated September 3, 1998 (FAA memo reference no. 98-190S-581) and ELOS No. ACE-98-2 as detailed in the FAA memo dated October 7, 1998 (FAA memo reference no. 98-190S-608). Emergency exit requirements of FAR 23.807 in accordance with ELOS No. ACE-99-02 as detailed in FAA memo dated February 2, 1999 (FAA memo reference no. 99-190S-64). Production Basis: Production Certificate No. 719NM, dated November 1, 2005. NOTE 1: A current weight and balance report with a list of equipment included in the certificated empty weight must be provided for each aircraft at the time of original airworthiness certification. NOTE 2: The placards specified in the latest FAA approved revision of “Pilots Operating Handbook and FAA Approved Flight Manual,” Document No. RA050001 must be displayed. NOTE 3: Major structural repairs must be accomplished by an appropriate FAA certified person qualified to perform maintenance on composite aircraft structure, using materials and processes in accordance with the FAA approved Cessna Aircraft Company “LC-550FG Series Structural Repair Manual,” Document No. 30/40SR00 or later revision, or other methods approved by the FAA and coordinated with Cessna Aircraft Company. Material compatibility, environmental effects, strength, fatigue, lightning protection, and flutter must be addressed in any major structural repair. NOTE 4: Exterior colors are limited to those specified in the FAA approved Chapter 4 of “Model LC40-550FG Maintenance Manual,” Document No. 300MM02 or later revision. NOTE 5: Engine accessory packages are defined by a suffix added to the end of the engine model number (example: IO-550-N (2)). A listing of engine model numbers with suffix defining approved accessory packages can be found in C300PC. II. Model LC42-550FG (Utility Category), Approved May 30, 2003 Engine: Teledyne Continental Model IO-550-N (See NOTE 5), Engine Type Certificate E3SO. Fuel: 100 (green) or 100LL (blue) grade aviation fuel. Engine Limits: Maximum takeoff power and maximum continuous power = 310 horsepower at 2700 rpm. See Engine Type Certificate Data Sheet E3SO for additional limitations. A00003SE Page 4 of 13 Rev. 27 II. Model LC42-550FG (cont’d) Propeller: Hartzell Model PHC-J3YF-1RF/F7691D-1 or PHC-J3YF-1RF/F7691DK-1, Propeller Type Certificate P36EA Hartzell Spinner Assembly, Part No. C-6446-1 or C-6446-2(P) Propeller Limits: Minimum diameter = 76 inches Maximum diameter = 77 inches Low Pitch = 14.1° ± 0.2° High Pitch = 34.7° ± 1.0° Pitch limits measured at 30 inches radial distance. Do not exceed 20 inches manifold pressure with propeller RPM below 2200. See Propeller Type Certificate Data Sheet P36EA for additional limits. Airspeed Limits: VO (3400 lbs) 149 KCAS (148 KIAS) VO (2500 lbs) 128 KCAS (127 KIAS) VFE (Fully Extended) 120 KCAS (119 KIAS) VFE (Intermediate Setting) 130 KCAS (129 KIAS) VNO 180 KCAS (178 KIAS) VNE 235 KCAS (235 KIAS) Note: VNO decreases by 4 KIAS and VNE decreases by 5 KIAS for each 1000 feet above 12,000 feet (pressure altitude). C.G. Range: Straight line variation between points. Aft Limits 110 inches aft of datum from 2500 lbs to 3400 lbs. Forward Limits 103 inches aft of datum from 2240 lbs to 2500 lbs then to 107 inches aft of datum at 3400 lbs. Maximum zero fuel weight 103 inches aft of datum at 2725 lbs to 110 inches at 3228 lbs. Minimum flying weight 103 inches aft of datum at 2240 lbs to110 inches at 2500 lbs. Datum: The forward edge of the wing saddle is located 97.05 inches aft of the reference datum. Refer to the “Model LC42-550FG Maintenance Manual,” Document No. 350MM02 or later revision for detailed instructions. Leveling Means: Plumb target and plumb line hanger are located in the rear seat area. Weight limits: Maximum ramp and takeoff = 3400 lbs. Maximum landing weight = 3230 lbs. Maximum empty weight = 2568 lbs. Maximum zero fuel weight = 2725 lbs at 103 inches varying linearly to 3228 lbs at 110 inches. Minimum flying weight = 2240 lbs at 103 inches varying linearly to 2500 lbs at 110 inches. Minimum Crew: 1 Pilot. No. of Seats: 4 seats total: 2 located at 110 inches aft of datum. 2 located at 141.4 inches aft of datum. Maximum Baggage: 20 pounds allowed on the hat shelf. 120 pounds total. Fuel Capacity: 106 gallons total; 98 gallons useable. (Two 53 gallon tanks in wings at 118.0 inches aft of datum). Oil Type and Capacity: 8 qts drainable. See Engine Type Certificate Data Sheet E3SO. Maximum Operating Altitude: 14,000 feet without FAA approved oxygen system installed. 18,000 feet with FAA approved oxygen system installed. Rev. 27 Page 5 of 13 A00003SE II. Model LC42-550FG (cont’d) Control Surface Movements: Wing flaps: Cruise 0° ±1° Take off 12° ±1° Landing 40° ±1° Ailerons: Up 21.6° ±1° Down 17.7° ±1° Aileron Trim Tab: Up 22.4° ±1° Down 19.6° ±1° Aileron Servo Tab: Up 13° ±2° at 17.7° aileron deflection Down 19° ±2° at 21.6° aileron deflection Elevator: Up 13° +0°-0.5° Down 12° ±1° Elevator trim tab: Up 21° ±1° Down 30° ±1° Rudder: Right 17° ±1° Left 17° ±1° Left, rudder limiter 11.5° ±0.5° Additional Limitations: Airframe life limit: 25,200 flight hours. Kinds of operations: Day and Night, Visual Flight Rules (VFR) and Instrument Flight Rules (IFR). Required Maintenance: The airplane must be maintained in accordance with the instructions for continued airworthiness contained in the FAA approved Chapter 4 of “Model LC42-550FG Maintenance Manual,” Document No. 350MM02 or later revision. Required Equipment: The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the aircraft for airworthiness certification. In addition to the above required equipment, the following equipment is also required: The latest FAA Approved/Accepted Revision of “Pilots Operating Handbook and FAA Approved Flight Manual,” Document No. RB050000 or RB050005 as appropriate for the avionics package installed when the airplane was produced. The required equipment for various types of operations is specified in Appendix A to Section 6 of the latest FAA Approved Revision of Document No. RB050000 or RB050005. Design Data: The airplane shall be manufactured in accordance with the latest FAA approved revision of “Master Drawing List”, Document No. RB011000 or RB011003 (as appropriate for the avionics package installed) , or other FAA approved data. Serial Numbers Eligible: 42001 through 42084, 42501 through 42569, and 421001 through 421020. Certification Basis: Part 23 of the Federal Aviation Regulations (FAR) effective February 1, 1965, as amended by 23-1 through 23-46, except for FAR 23.1305 and FAR 23.1359. FAR 23.1305 as amended through 23-52 and FAR 23.1359 as amended through 23-49. FAR 36 as amended on the date of certification. Application for type certificate, dated October 24, 2002. For LC42-550FG aircraft equipped with Columbia factory installed Garmin G-1000 system the additional certification basis for installation specific items only is: FAR 23.143 as amended through 23-50; FAR 23.301 (a) (b) (c) as amended through 23-48; FAR 23.561 (a) (b)(3) as amended through 23-48; FAR 23.611as amended through 23-48; FAR 23.777 (a) (b) (c)(3) (d) (f)(1) as amended through 23-51; FAR 23.867 as amended through 23-49; FAR 23.1303 (a) (b) (c) (f) as amended through 23-49; FAR 23.1305 (a)(1)(2)(3) (b)(2)(3)(i)(4)(i)(5)(6)(i) as amended through 23-52; FAR 23.1307 as amended through 23-49; FAR 23.1309 (a)(1)(2) (b) (c)(1)(2)(iii)(3) (d) (e) as amended through 23-49; FAR 23.1311 as amended through 23-49; FAR 23.1321 (a) (c) (d) (e) as amended through 23-49; FAR 23.1323 (a) as amended through 23-49; FAR 23.1325 (b)(1)(ii)(iii)(2)(i) as amended through 23-50; FAR 23.1329 as amended through 23- 49; FAR 23.1337 (b)(1) as amended through 23-51; FAR 23.1351(a)(1)(2)(i) (b)(1)(2)(3) (c)(4)(d)(1) (g) as amended through 23-49; FAR 23.1353 (h) as amended through 23-49; FAR 23.1365 (a) (b) (d) (e) as amended through 23-49; FAR 23.1431 (a) (b) (d) (e) as amended through 23-49; FAR 23.1543 (b) (c) as amended through 23-50; FAR 23.1545 (a) (b)(1)(2)(3)(4) as amended through 23-50; FAR 23.1553 through amendment. 23-50; FAR 23.1555 (a) (b) (e)(2) as amended through 23-50; FAR 23.1563 (a) as amended through 23-50; FAR 23.1567 (a) as amended through 23-50; FAR 23.1581 (a) (b)(2)(3) (c) (f) as amended through 23-50; FAR 23.1583 (h) (m) (n) as amended through 23-50; FAR 23.1585 (j) through amendment. 23-50. A00003SE Page 6 of 13 Rev. 27 II. Model LC42-550FG (cont’d) Special Condition: Special Condition 23-160-SC is applicable to all airplanes regardless of which avionics package is installed. Equivalent Level of Safety (ELOS) Findings: Stall and spin requirements of FAR’s 23.201, 23.203, and 23.221 in accordance with ELOS No. ACE-98-1 as detailed in the FAA memo dated September 3, 1998 (FAA memo reference no. 98-190S-581) and ELOS No. ACE-98-2 as detailed in the FAA memo dated October 7, 1998 (FAA memo reference no. 98-190S-608). Emergency exit requirements of FAR 23.807 in accordance with ELOS No. ACE-99-02 as detailed in FAA memo dated February 2, 1999 (FAA memo reference no. 99-190S-64). Production Basis: Production Certificate No. PC-4, dated December 5, 2007, for serial numbers 421001 and up. Previously Production Certificate No. 719NM, dated November 1, 2005. NOTE 1: A current weight and balance report with a list of equipment included in the certificated empty weight must be provided for each aircraft at the time of original airworthiness certification. NOTE 2: The placards specified in the latest FAA approved revision of “Pilots Operating Handbook and FAA Approved Flight Manual,” Document No. RB050000 or RB050005, must be displayed. NOTE 3: Major structural repairs must be accomplished by an appropriate FAA certified person qualified to perform maintenance on composite aircraft structure, using materials and processes in accordance with the FAA approved Cessna Aircraft Company “LC-550FG Series Structural Repair Manual,” Document No. 30/40SR00 or later revision, or other methods approved by the FAA and coordinated with Cessna Aircraft Company. Material compatibility, environmental effects, strength, fatigue, lightning protection, and flutter must be addressed in any major structural repair. NOTE 4: Exterior colors are limited to those specified in the FAA approved Chapter 4 of the “Model LC42-550FG Maintenance Manual,” Document No. 350MM02 or later revision. NOTE 5: Engine accessory packages are defined by a suffix added to the end of the engine model number (example: IO-550-N (15)). A listing of engine model numbers with suffix defining approved accessory packages can be found in C350PC. III. Model LC41-550FG (Utility Category), Approved April 8, 2004 Engine: Teledyne Continental Model TSIO-550-C (See NOTE 5), Engine Type Certificate E5SO. Fuel: 100 (green) or 100LL (blue) grade aviation fuel. Engine Limits: Maximum takeoff power and maximum continuous power = 310 horsepower at 2600 rpm. See Engine Type Certificate Data Sheet E5SO for additional limitations. Propeller: Hartzell Model HC-H3YF-1RF/F7693DF or HC-H3YF-1RF/F7693DFK, Propeller Type Certificate P35EA Hartzell Spinner Assembly, Part No. C-6446-1 or C-6446-2(P) or McCauley Model D3A34C447/78MLB-0, Propeller Type Certificate P47GL McCauley Spinner Assembly, Part No. E-7819 Rev. 27 Page 7 of 13 A00003SE III. Model LC41-550FG (cont’d) Propeller Limits: Hartzell Model HC-H3YF-1RF/F7693DF or HC-H3YF-1RF/F7693DFK Minimum diameter = 77 inches Maximum diameter = 78 inches Low Pitch = 16.5° ± 0.1° High Pitch = 43.0° ± 1.0° Pitch limits measured at 30 inches radial distance. See Propeller Type Certificate Data Sheet P35EA for additional limits. or McCauley Model D3A34C447/78MLB-0 Minimum diameter = 76.5 inches Maximum diameter = 78.0 inches Low Pitch = 14.9° ± 0.2° High Pitch = 36.5° ± 0.5° Pitch limits measured at 30 inches radial distance. See Propeller Type Certificate Data Sheet P47GL for additional limits. Airspeed Limits: VO (3600 lbs) 162 KCAS (158 KIAS) VO (2600 lbs) 138 KCAS (135 KIAS) VFE (Fully Extended) 120 KCAS (117 KIAS) VFE (Intermediate Setting) 130 KCAS (127 KIAS) VNO 185 KCAS (181 KIAS) VNE 235 KCAS (230 KIAS) Note: VFE decreases by 2.4 KIAS for each 1000 feet above 12,000 feet (pressure altitude) VNO decreases by 3.5 KIAS for each 1000 feet above 12,000 feet (pressure altitude) VNE decreases by 4.4 KIAS for each 1000 feet above 12,000 feet (pressure altitude). C.G. Range: Straight line variation between points. Aft Limits 112.0 inches aft of datum from 2900 lbs to 3600 lbs. Forward Limits 105.0 inches aft of datum from 2600 lbs to 2900 lbs then to 108.8 inches aft of datum at 3600 lbs. Maximum zero fuel weight 107.2 inches aft of datum at 3300 lbs to 112.0 inches at 3300 lbs. Minimum flying weight 105 inches aft of datum at 2600 lbs to 112 inches at 2900 lbs. Datum: The forward edge of the wing saddle is located 97.05 inches aft of the reference datum. Refer to the “Model LC41-550FG/T240 Maintenance Manual,” Document No. 400MM02 or later revision for detailed instructions. Leveling Means: Plumb target and plumb line hanger are located in the rear seat area. Weight limits: Maximum ramp and takeoff = 3600 lbs. Maximum landing weight = 3420 lbs. Maximum empty weight = 2708 lbs. Maximum zero fuel weight = 3300 lbs at 107.2 inches varying linearly to 3300 lbs at 112.0 inches. Minimum flying weight = 2600 lbs at 105.0 inches varying linearly to 2900 lbs at 112.0 inches. Minimum Crew: 1 Pilot. No. of Seats: 4 seats total: 2 located at 110 inches aft of datum. 2 located at 141.4 inches aft of datum. Maximum Baggage: 20 pounds allowed on the hat shelf. 120 pounds total. Fuel Capacity: 106 gallons total (Two 53 gallon tanks in wings at 118.0 inches aft of datum); S/N 41002 thru 41799 – 98 gallons, S/N 41800 and On – 102 gallons. A00003SE Page 8 of 13 Rev. 27 III. Model LC41-550FG (cont’d) Oil Type and Capacity: 8 qts drainable. See Engine Type Certificate Data Sheet E5SO. Maximum Operating Altitude: 14,000 feet without FAA approved oxygen system installed. 18,000 or 25,000 feet with FAA approved oxygen system installed (See the airplane flight manual for the specific limitation for the airplane as equipped). Control Surface Movements: Wing flaps: Cruise 0° ±1° Take off 12° ±1° Landing 40° ±1° Ailerons: Up 21.6° ±1° Down 17.7° ±1° Aileron Trim Tab: Up 22.4° ±1° Down 19.6° ±1° Aileron Servo Tab: Up 13° ±2° at 17.7° aileron deflection Down 19° ±2° at 21.6° aileron deflection Elevator: Up 23° ±1° Down 14° ±1° Elevator trim tab: Up 21° ±2° Down 30° ±2° Rudder: Right 30° ±1° Left 30° ±1° Additional Limitations: Airframe life limit: 25,200 flight hours. Kinds of operations: Day and Night, Visual Flight Rules (VFR) and Instrument Flight Rules (IFR). Required Maintenance: The airplane must be maintained in accordance with the instructions for continued airworthiness contained in the FAA approved Chapter 4 of the “Model LC41-550FG/T240 Maintenance Manual,” Document No. 400MM02 or later revision. Required Equipment: The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the aircraft for airworthiness certification. In addition to the above required equipment, the following equipment is also required: Airplane Serial Numbers 41002 through 41041 (18,000 feet MSL max. operating altitude): The latest FAA Approved/Accepted Revision of “Pilots Operating Handbook and FAA Approved Flight Manual,” Document No. RC050000. (NOTE: Maximum operating altitude is increased to 25,000 feet MSL if modified in accordance with Lancair Service Letter SL-04-010 and equipped with the latest FAA Approved/Accepted Revision of “Pilots Operating Handbook and FAA Approved Flight Manual,” Document No. RC050002.) Airplane Serial Numbers 41042 and on (25,000 feet MSL max. operating altitude): The latest FAA Approved/Accepted Revision of “Pilots Operating Handbook and FAA Approved Flight Manual,” Document No. RC050002 or RC050005 as appropriate for the avionics package installed when the airplane was produced. The required equipment for various types of operations is specified in Appendix A to Section 6 of the latest FAA Approved Revision of Document No. RC050000, RC050002, or RC050005 (as required above). Design Data: The airplane shall be manufactured in accordance with the latest FAA approved revision of “Master Drawing List”, Document No. RC011000, or other FAA approved data. Serial Numbers Eligible: 41002 through 41108, 41501 through 41533, 41563 through 41800, and 411001 through 411161. Certification Basis: Part 23 of the Federal Aviation Regulations (FAR) effective February 1, 1965, as amended by 23-1 through 23-46, except for FAR 23.1305 and FAR 23.1359. FAR 23.1305 as amended through 23-52, and FAR 23.1359 as amended through 23-49. FAR 36 as amended on the date of certification. Application for type certificate, dated October 24, 2002. Rev. 27 Page 9 of 13 A00003SE III. Model LC41-550FG (cont’d) Certification Basis: (cont’d) For LC41-550FG aircraft equipped with Columbia factory installed Garmin G-1000 system the additional certification basis for installation specific items only is: FAR 23.143 as amended through 23-50; FAR 23.301 (a) (b) (c) as amended through 23-48; FAR 23.561 (a) (b)(3) as amended through 23-48; FAR 23.611as amended through 23-48; FAR 23.777 (a) (b) (c)(3) (d) (f)(1) as amended through 23-51; FAR 23.867 as amended through 23-49; FAR 23.1303 (a) (b) (c) (f) as amended through 23-49; FAR 23.1305 (a)(1)(2)(3) (b)(2)(3)(i)(4)(i)(5)(6)(i) as amended through 23-52; FAR 23.1307 as amended through 23-49; FAR 23.1309 (a)(1)(2) (b) (c)(1)(2)(iii)(3) (d) (e) as amended through 23-49; FAR 23.1311 as amended through 23-49; FAR 23.1321 (a) (c) (d) (e) as amended through 23-49; FAR 23.1323 (a) as amended through 23-49; FAR 23.1325 (b)(1)(ii)(iii)(2)(i) as amended through 23-50; FAR 23.1329 as amended through 23- 49; FAR 23.1337 (b)(1) as amended through 23-51; FAR 23.1351(a)(1)(2)(i) (b)(1)(2)(3) (c)(4)(d)(1) (g) as amended through 23-49; FAR 23.1353 (h) as amended through 23-49; FAR 23.1365 (a) (b) (d) (e) as amended through 23-49; FAR 23.1431 (a) (b) (d) (e) as amended through 23-49; FAR 23.1543 (b) (c) through amendment. 23-50; FAR 23.1545 (a) (b)(1)(2)(3)(4) as amended through 23-50; FAR 23.1553 through amendment. 23-50; FAR 23.1555 (a) (b) (e)(2) as amended through 23-50; FAR 23.1563 (a) as amended through 23-50; FAR 23.1567 (a) as amended through 23-50; FAR 23.1581 (a) (b)(2)(3) (c) (f) as amended through 23-50; FAR 23.1583 (h) (m) (n) as amended through 23-50; FAR 23.1585 (j) through amendment. 23-50. Special Condition: Special Condition 23-160-SC is applicable to all airplanes regardless of which avionics package is installed. Equivalent Level of Safety (ELOS) Findings: Emergency exit requirements of FAR 23.807 in accordance with ELOS No. ACE-99-02 as detailed in FAA memo dated February 2, 1999 (FAA memo reference no. 99-190S-64). Production Basis: Production Certificate No. PC-4, dated December 5, 2007, for serial numbers 411001 and up. Previously Production Certificate No. 719NM, dated November 1, 2005. NOTE 1: A current weight and balance report with a list of equipment included in the certificated empty weight must be provided for each aircraft at the time of original airworthiness certification. NOTE 2: The placards specified in the latest FAA approved revision of “Pilots Operating Handbook and FAA Approved Flight Manual,” Document No. RC050000, RC050002, or RC050005, must be displayed. NOTE 3: Major structural repairs must be accomplished by an appropriate FAA certified person qualified to perform maintenance on composite aircraft structure, using materials and processes in accordance with the FAA approved Cessna Aircraft Company “LC-550FG Series Structural Repair Manual,” Document No. 30/40SR00 or later revision, or other methods approved by the FAA and coordinated with Cessna Aircraft Company. Material compatibility, environmental effects, strength, fatigue, lightning protection, and flutter must be addressed in any major structural repair. NOTE 4: Exterior colors are limited to those specified in the FAA approved Chapter 4 of the “Model LC41- 550FG/T240 Maintenance Manual,” Document No. 400MM02 or later revision. NOTE 5: Engine accessory packages are defined by a suffix added to the end of the engine model number (example: TSIO-550-C (7)). A listing of engine model numbers with suffix defining approved accessory packages can be found in C400PC. IV. Model T240 (Utility Category), Approved January 23, 2013 Engine: Teledyne Continental Model TSIO-550-C (See NOTE 5), Engine Type Certificate E5SO. Fuel: 100.0 octane minimum (Aviation Lean Rating) Aviation Gasoline per ASTM D910. Engine Limits: Maximum takeoff power and maximum continuous power = 310 horsepower at 2600 rpm. See Engine Type Certificate Data Sheet E5SO for additional limitations. A00003SE Page 10 of 13 Rev. 27 IV. Model T240 (cont’d) Propeller: Hartzell Model HC-H3YF-1RF/F7693DF or HC-H3YF-1RF/F7693DFK, Propeller Type Certificate P35EA Hartzell Spinner Assembly, Part No. C-6446-1 or C-6446-2(P) or McCauley Model D3A34C447/78MLB-0, Propeller Type Certificate P47GL McCauley Spinner Assembly, Part No. E-7819 or E-8064 Propeller Limits: Hartzell Model HC-H3YF-1RF/F7693DF or HC-H3YF-1RF/F7693DFK Minimum diameter = 77 inches Maximum diameter = 78 inches Low Pitch = 16.5° ± 0.1° High Pitch = 43.0° ± 1.0° Pitch limits measured at 30 inches radial distance. See Propeller Type Certificate Data Sheet P35EA for additional limits. or McCauley Model D3A34C447/78MLB-0 Minimum diameter = 76.5 inches Maximum diameter = 78.0 inches Low Pitch = 14.9° ± 0.2° High Pitch = 36.5° ± 0.5° Pitch limits measured at 30 inches radial distance. See Propeller Type Certificate Data Sheet P47GL for additional limits. Airspeed Limits: VO (3600 lbs) 162 KCAS (158 KIAS) VO (2600 lbs) 138 KCAS (135 KIAS) VFE (Fully Extended) 120 KCAS (117 KIAS) VFE (Intermediate Setting) 130 KCAS (127 KIAS) VNO 185 KCAS (181 KIAS) VNE 235 KCAS (230 KIAS) Note: VFE decreases by 2.4 KIAS for each 1000 feet above 12,000 feet (pressure altitude) VNO decreases by 3.5 KIAS for each 1000 feet above 12,000 feet (pressure altitude) VNE decreases by 4.4 KIAS for each 1000 feet above 12,000 feet (pressure altitude). C.G. Range: Straight line variation between points. Aft Limits 112.0 inches aft of datum from 2900 lbs to 3600 lbs. Forward Limits 105.0 inches aft of datum from 2600 lbs to 2900 lbs then to 108.8 inches aft of datum at 3600 lbs. Maximum zero fuel weight 107.2 inches aft of datum at 3300 lbs to 112.0 inches at 3300 lbs. Minimum flying weight 105 inches aft of datum at 2600 lbs to 112 inches at 2900 lbs. Datum: The forward edge of the wing saddle is located 97.05 inches aft of the reference datum. Refer to “Model LC41-550FG/T240 Maintenance Manual,” Document No. 400MM02 or later revision for detailed instructions. Leveling Means: Plumb target and plumb line hanger are located in the rear seat area. Weight limits: Maximum ramp and takeoff = 3600 lbs. Maximum landing weight = 3420 lbs. Maximum empty weight = 2708 lbs. Maximum zero fuel weight = 3300 lbs at 107.2 inches varying linearly to 3300 lbs at 112.0 inches. Minimum flying weight = 2600 lbs at 105.0 inches varying linearly to 2900 lbs at 112.0 inches. Minimum Crew: 1 Pilot. No. of Seats: 4 seats total: 2 located at 110 inches aft of datum. 2 located at 141.4 inches aft of datum. Rev. 27 Page 11 of 13 A00003SE IV. Model T240 (cont’d) Maximum Baggage: 20 pounds allowed on the hat shelf. 120 pounds total. Fuel Capacity: 106 gallons total; 102 gallons useable. (Two 53 gallon tanks in wings at 118.0 inches aft of datum). Oil Type and Capacity: 8 qts drainable. See Engine Type Certificate Data Sheet E5SO. Maximum Operating Altitude: 14,000 feet without FAA approved oxygen system installed. 18,000 or 25,000 feet with FAA approved oxygen system installed (See the airplane flight manual for the specific limitation for the airplane as equipped). Control Surface Movements: Wing flaps: Cruise 0° ±1° Take off 12° ±1° Landing 40° ±1° Ailerons: Up 21.6° ±1° Down 17.7° ±1° Aileron Trim Tab: Up 22.4° ±1° Down 19.6° ±1° Aileron Servo Tab: Up 13° ±2° at 17.7° aileron deflection Down 19° ±2° at 21.6° aileron deflection Elevator: Up 23° ±1° Down 14° ±1° Elevator trim tab: Up 21° ±2° Down 30° ±2° Rudder: Right 30° ±1° Left 30° ±1° Additional Limitations: Airframe life limit: 25,200 flight hours. Kinds of operations: Day and Night, Visual Flight Rules (VFR) and Instrument Flight Rules (IFR). Required Maintenance: The airplane must be maintained in accordance with the instructions for continued airworthiness contained in the FAA approved Chapter 4 of the “Model LC41-550FG/T240 Maintenance Manual,” Document No. 400MM02 or later revision. Required Equipment: The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the aircraft for airworthiness certification. In addition to the above required equipment, the FAA Approved/Accepted “Pilots Operating Handbook and FAA Approved Flight Manual,” Document No. T240PHCUS-00 or later revision, the following equipment is also required. The required equipment for various types of operations is specified in Appendix A to Section 6 of the latest FAA Approved Revision of Document No. T240PHCUS-00. Design Data: The airplane shall be manufactured in accordance with the latest FAA approved revision of “Airplane Assy, Turbo”, Drawing No. 2800000-1, or other FAA approved data. Serial Numbers Eligible: T24002001 and up. Certification Basis: Part 23 of the Federal Aviation Regulations (FAR) effective February 1, 1965, as amended by 23-1 through 23-46, except for FAR 23.1305 and FAR 23.1359. FAR 23.1305 as amended through 23-52, 23.1308(a)(b) and (c) as amended through 23-57 and FAR 23.1359 as amended through 23-49. FAR 36 as amended on the date of certification. Application for type certificate, dated September 15, 2010. A00003SE Page 12 of 13 Rev. 27 IV. Model T240 (cont’d) Certification Basis: (cont’d) For T240 aircraft equipped with Cessna factory installed Garmin G-2000 system the additional certification basis for installation specific items only is: FAR 23.143 as amended through 23-50; FAR 23.301 (a) (b) (c) as amended through 23-48; FAR 23.561 (a) (b)(3) as amended through 23-48; FAR 23.611as amended through 23-48; FAR 23.777 (a) (b) (c)(3) (d) (f)(1) as amended through 23-51; FAR 23.867 as amended through 23-49; FAR 23.1303 (a) (b) (c) (f) as amended through 23-49; FAR 23.1305 (a)(1)(2)(3) (b)(2)(3)(i)(4)(i)(5)(6)(i) as amended through 23-52; FAR 23.1307 as amended through 23-49; FAR 23.1308 (a) (b) (c) as amended through 23-57; FAR 23.1309 (a)(1)(2) (b) (c)(1)(2)(iii)(3) (d) (e) as amended through 23-49; FAR 23.1311 as amended through 23-49; FAR 23.1321 (a) (c) (d) (e) as amended through 23-49; FAR 23.1323 (a) as amended through 23-49; FAR 23.1325 (b)(1)(ii)(iii)(2)(i) as amended through 23- 50; FAR 23.1329 as amended through 23-49; FAR 23.1337 (b)(1) as amended through 23-51; FAR 23.1351(a)(1)(2)(i) (b)(1)(2)(3) (c)(4)(d)(1) (g) as amended through 23-49; FAR 23.1353 (h) as amended through 23-49; FAR 23.1365 (a) (b) (d) (e) as amended through 23-49; FAR 23.1431 (a) (b) (d) (e) as amended through 23-49; FAR 23.1543 (b) (c) through amendment. 23-50; FAR 23.1545 (a) (b)(1)(2)(3)(4) as amended through 23-50; FAR 23.1553 through amendment. 23-50; FAR 23.1555 (a) (b) (e)(2) as amended through 23-50; FAR 23.1563 (a) as amended through 23- 50; FAR 23.1567 (a) as amended through 23-50; FAR 23.1581 (a) (b)(2)(3) (c) (f) as amended through 23-50; FAR 23.1583 (h) (m) (n) as amended through 23-50; FAR 23.1585 (j) through amendment. 23-50. For T240 aircraft serial numbers T24002049 and on the additional certification basis is: CFR 23.201, 23.203 and 23.207 as amended through 23-50; CFR 23.1091 and 23.1093 as amended through 23-51. Compliance with ice protection has been demonstrated in accordance with 23.1419 when ice protection equipment is installed in accordance with the airplane equipment list and is operated per the Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual. Special Condition: Special Condition 23-160-SC is applicable to all airplanes regardless of which avionics package is installed. Equivalent Level of Safety (ELOS) Findings: Emergency exit requirements of FAR 23.807 in accordance with ELOS No. ACE-99-02 as detailed in FAA memo dated February 2, 1999 (FAA memo reference no. 99-190S-64). Exemption: Exemption No. 10605 to allow exemption from 23.49c stall speed requirement of 23.1419a Production Basis: Production Certificate No. PC-4, dated December 5, 2007, for serial numbers T240002001 and On. NOTE 1: A current weight and balance report with a list of equipment included in the certificated empty weight must be provided for each aircraft at the time of original airworthiness certification. NOTE 2: The placards specified in the latest FAA approved revision of “Pilots Operating Handbook and FAA Approved Flight Manual,” Document No. T240PHCUS-00. NOTE 3: Major structural repairs must be accomplished by an appropriate FAA certified person qualified to perform maintenance on composite aircraft structure, using materials and processes in accordance with the FAA approved Cessna Aircraft Company “LC-550FG Series Structural Repair Manual,” Document No. 30/40SR00 or later revision, or other methods approved by the FAA and coordinated with Cessna Aircraft Company. Material compatibility, environmental effects, strength, fatigue, lightning protection, and flutter must be addressed in any major structural repair. NOTE 4: Exterior colors are limited to those specified in the FAA approved Chapter 4 of the “Model LC41- 550FG/T240 Maintenance Manual,” Document No. 400MM02 or later revision. NOTE 5: Engine accessory packages are defined by a suffix added to the end of the engine model number (example: TSIO-550-C (10)). A listing of engine model numbers with suffix defining approved accessory packages can be found in CT240PC. Rev. 27 Page 13 of 13 A00003SE IV. Model T240 (cont’d) NOTE 6: The following serials are manufactured under the name Cessna Aircraft Company: T240: T24002001 thru T24002066, T24002068 thru T24002072, T24002074, T24002075, and T24002079. NOTE 7: Company name change effective 7/29/15. The following serials are manufactured under the name Textron Aviation Inc.: T240: T24002067, T24002073, T24002076 thru T24002078, T24002080 and On. --- END --- ``` ## ADs (19, in force first) - [AD 2023-09-09](https://openairdocs.org/ad/2023-09-09): Exhaust Turbine System (Recip) · Aerostar PA-60-600 (Aerostar 600), PA-60-601 (Aerostar 601), PA-60-601P (Aerostar 601P) and 292 more. Effective Jul 17, 2023 - [AD 2023-10-02](https://openairdocs.org/ad/2023-10-02): Indicating/Recording System, Navigation · Boeing 18, 23, 35 and 1,060 more. Effective May 26, 2023 - [AD 2022-03-15](https://openairdocs.org/ad/2022-03-15): Fuel Quantity Indicator · Garmin G3X Touch Electronic Flight Instrument System (STC SA01899WI or SA02658SE). Effective Mar 21, 2022 - [AD 2013-11-10](https://openairdocs.org/ad/2013-11-10): Fuselage Structure (General) · Cessna LC40-550FG, LC41-550FG and LC42-550FG. Effective Jul 26, 2013 - [AD 2011-03-04](https://openairdocs.org/ad/2011-03-04): Stabilizers · Cessna LC40-550FG, LC41-550FG and LC42-550FG. Effective Mar 14, 2011 - [AD 2010-26-54](https://openairdocs.org/ad/2010-26-54): Wings · Cessna LC41-550FG and LC42-550FG. Effective Jan 10, 2011 - [AD 2009-05-05](https://openairdocs.org/ad/2009-05-05): Primary Flight Displays · Avidyne Primary Flight Display (S-TEC STC SA09543AC-D or 2 others). Effective Apr 3, 2009 - [AD 2007-07-06 R1](https://openairdocs.org/ad/2007-07-06-R1): Aileron and elevator control systems · Cessna LC40-550FG, LC41-550FG and LC42-550FG. Effective Dec 5, 2008 - [AD 2008-02-06](https://openairdocs.org/ad/2008-02-06): GSM 85 servo gearbox units · Cessna 182T, 206H, LC40-550FG and 11 more. Effective Feb 26, 2008 - [AD 2006-25-08](https://openairdocs.org/ad/2006-25-08): Deice system · Cessna LC41-550FG and LC42-550FG with STC SA02260CH. Effective Dec 21, 2006 - [AD 2005-12-20](https://openairdocs.org/ad/2005-12-20): Elevator torque tube assembly · Cessna LC41-550FG. Effective Jun 21, 2005 - [AD 2005-01-19](https://openairdocs.org/ad/2005-01-19): Mode S transponders · GARMIN International GTX 330D, GTX 330, GTX 33D and 830 more. Effective Feb 23, 2005 - [AD 2005-02-01](https://openairdocs.org/ad/2005-02-01): Takeoff chart distance values · Cessna LC40-550FG and LC42-550FG. Effective Jan 21, 2005 - [AD 2004-06-09](https://openairdocs.org/ad/2004-06-09): Fuel pressure transducer · Cessna LC40-550FG and LC42-550FG. Effective May 3, 2004 - [AD 2009-09-09](https://openairdocs.org/ad/2009-09-09) (historical): Rudder hinge brackets · Cessna LC40-550FG, LC41-550FG and LC42-550FG. Effective May 11, 2009 - [AD 2008-06-28](https://openairdocs.org/ad/2008-06-28) (historical): Primary flight display · Avidyne Primary Flight Display (S-TEC STC SA09543AC-D or 2 others). Effective Apr 10, 2008 - [AD 2008-06-28 R1](https://openairdocs.org/ad/2008-06-28-R1) (historical): Primary Flight Displays (PFDs) · Avidyne Primary Flight Displays, 441, LC41-550FG and 22 more. Effective Apr 10, 2008 - [AD 2007-07-06](https://openairdocs.org/ad/2007-07-06) (historical): Aileron and the elevator linear bearings and control rods · Cessna LC40-550FG, LC41-550FG and LC42-550FG. Effective Apr 9, 2007 - [AD 2010-26-53](https://openairdocs.org/ad/2010-26-53) (historical): Wings · Cessna LC41-550FG and LC42-550FG ## Registered aircraft by registry model (OpenAirDocs) - [Columbia Aircraft Mfg LC41-550FG](https://openairdocs.org/model/columbia-aircraft-mfg-lc41-550fg): 207 aircraft (registry code 5150011) - [Cessna LC41-550FG](https://openairdocs.org/model/cessna-lc41-550fg): 144 aircraft (registry codes 2073320, 2073323) - [Lancair LC41-550FG](https://openairdocs.org/model/lancair-lc41-550fg): 122 aircraft (registry code 5150001) - [Lancair LC42-550FG](https://openairdocs.org/model/lancair-lc42-550fg): 75 aircraft (registry code 5150002) - [Cessna T240](https://openairdocs.org/model/cessna-t240): 68 aircraft (registry code 2073460) - [Textron T240](https://openairdocs.org/model/textron-t240): 68 aircraft (registry code 2073461) - [Lancair LC-40-550FG](https://openairdocs.org/model/lancair-lc-40-550fg): 64 aircraft (registry code 5150000) - [Columbia Aircraft Mfg LC42-550FG](https://openairdocs.org/model/columbia-aircraft-mfg-lc42-550fg): 61 aircraft (registry code 5150012) - [Cessna LC42-550FG](https://openairdocs.org/model/cessna-lc42-550fg): 16 aircraft (registry code 2073321) - [Pacific Aviation Composites US LC 40-550FG](https://openairdocs.org/model/pacific-aviation-composites-us-lc-40-550fg): 2 aircraft (registry code 05603A4) - [Cessna LC 40-550FG](https://openairdocs.org/model/cessna-lc-40-550fg): 0 aircraft (registry code 05629G4) - [Columbia Aircraft Mfg LC40-550FG](https://openairdocs.org/model/columbia-aircraft-mfg-lc40-550fg): 0 aircraft (registry code 5150010) ## STCs approved under this data sheet (98, first 50) - [STC SA02571SE](https://openairdocs.org/stc/SA02571SE): Installation of Garmin G500/G600 TXi Integrated Avionics System (Primary Flight Display, Multi-Function Display, and Engine Indicating System Display).. Garmin International Inc. - [STC SA01800SE](https://openairdocs.org/stc/SA01800SE): Fabrication and installation of new or replacement of existing instrument panel lights dimmer control.. TCW Technologies, LLC - [STC SA01861SE](https://openairdocs.org/stc/SA01861SE): Fabrication and installation of Landing Light Controller. TCW Technologies, LLC - [STC SA02279AT](https://openairdocs.org/stc/SA02279AT): Installation of a Boom Beam bulb, starter, and ballast. Whelen Aerospace Technologies - [STC SA04837NY](https://openairdocs.org/stc/SA04837NY): Installation of AeroLED's Holdings, LLC., position lights, navigation lights, strobe lights and beacon lights. AeroLED's Holdings, LLC - [STC SA01134DE](https://openairdocs.org/stc/SA01134DE): Installation of EarthX ETX680-24-TSO Lithium Battery. EarthX Inc. - [STC SA12406WI](https://openairdocs.org/stc/SA12406WI): Installation of a Garmin AXIS Flight Display System. Garmin International Inc. - [STC SA02636SE](https://openairdocs.org/stc/SA02636SE): Installation of Garmin GPS 175 Navigation System and GNX 375 Navigation System with ADS-B In/Out Transponder.. Garmin International Inc. - [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 SA00079NY](https://openairdocs.org/stc/SA00079NY): Installation of Airwolf remote mounted engine oil filter kit AFC-K008 on single and multi engine fixed wing light aircraft incorporating Teledyne Continental reciprocating engines of 450 horsepower or less.. Airwolf Filter Corporation - [STC SA02511SE](https://openairdocs.org/stc/SA02511SE): Installation of replacement fuel quantity indicator sending unit(s). CiES Inc. - [STC SA02738CH](https://openairdocs.org/stc/SA02738CH): Installation of L-3 Communications Avionics Systems. Acron Aviation Inc. - [STC SA04046CH PAGE 1](https://openairdocs.org/stc/SA04046CH%20PAGE%201): Installation of L-3 GENESIS (TM) Electronic Standby Instrument System (ESI-500/MAG-500). Acron Aviation Inc. - [STC SA04378CH](https://openairdocs.org/stc/SA04378CH): Installation of an engine modified per STC SE04349CH. SureFly Partners Ltd. - [STC SA02658SE](https://openairdocs.org/stc/SA02658SE): Installation of Garmin GI 275 Multi-Function Display System. Garmin International Inc. - [STC SA02010WI](https://openairdocs.org/stc/SA02010WI): Installation of the Mid-Continent Instruments & Avionics MD23 FLEX Custom Function Display (CFD). Mid-Continent Instruments and Avionics - [STC SA00076IB](https://openairdocs.org/stc/SA00076IB): Installation of Photo luminescent Safety Systems. STG AEROSPACE GERMANY GmbH - [STC SA01967WI](https://openairdocs.org/stc/SA01967WI): Use of GAMI G100UL High Octane Unleaded Avgas. General Aviation Modifications Inc. - [STC SA02444AK](https://openairdocs.org/stc/SA02444AK): Approval of the L-3 Communications NGT 9000/9000R ADS-B system installed. ADS-B Technologies LLC - [STC SA11174SC PAGE 1](https://openairdocs.org/stc/SA11174SC%20PAGE%201): Installation of BendixKing by Honeywell KSN 770 and KSN 765 WAAS LPV approach capable nav/comm systems. Honeywell International Inc (Bendix King) - [STC SA10822SC](https://openairdocs.org/stc/SA10822SC): Installation of EFD1000 Primary Flight Display. Aspen Avionics Inc. - [STC SA00401BO](https://openairdocs.org/stc/SA00401BO): Installation of a SkyTrax100B UAT receiver. Avidyne Corporation - [STC SA10236SC](https://openairdocs.org/stc/SA10236SC): Installation of a GDC 31 Roll Steering Converter. DAC International Inc - [STC SA02268CH](https://openairdocs.org/stc/SA02268CH): Installation of Airwolf Filter Corp. Air Oil Separator. Airwolf Filter Corporation - [STC SA11188SC](https://openairdocs.org/stc/SA11188SC): Installation of a McCauley Propeller System. McCauley Propeller Systems - [STC SA01714WI](https://openairdocs.org/stc/SA01714WI): Installation of a Garmin transponders: (a) GTX 330/330D/33/33D with ADS-B Out functionality; (b) GTX 335/335R/345/345R with ADS-B Out and In functionality; or (c) GTX 335R/345R with ADS-B Out functionality in select airplanes installed with G950/G1000 systems.. Garmin International Inc - [STC SA03286CH](https://openairdocs.org/stc/SA03286CH): Install an electronic engine ignition system. Electroair Acquisition Corporation - [STC SA04032CH](https://openairdocs.org/stc/SA04032CH): Install rocker switch assemblies. Electroair Acquisition Corporation - [STC SA00344BO PAGE 1](https://openairdocs.org/stc/SA00344BO%20PAGE%201): Installation of Parmetheus Plus LED PAR36 and PAR46 taxi and landing lights.. Whelen Aerospace Technologies - [STC SA01435SE](https://openairdocs.org/stc/SA01435SE): Installation of J.P. Instruments (JPI) Primary Engine Data Management System. J. P. Instruments - [STC SA02153LA-D PAGE 1](https://openairdocs.org/stc/SA02153LA-D%20PAGE%201): Installation of Garmin G600 Primary Flight Display (PFD) and Multifunction Display (MFD) System. Garmin International Inc. - [STC SA02013CH](https://openairdocs.org/stc/SA02013CH): Installation of Avidyne Corporation Traffic Advisory System (TAS). Avidyne Corporation - [STC SA04067NY](https://openairdocs.org/stc/SA04067NY): Installation of MT-Propeller Entwicklung GmbH's Model# MTV-14-D/195-30b 4-Blade constant speed propeller and spinner on Textron Aviation Inc. Model LC41-550FG aircraft. MT- Propeller Entwicklung GmbH - [STC SA01933LA-D](https://openairdocs.org/stc/SA01933LA-D): Installation of Garmin Model 400W / 500W Series GPS-WAAS Navigation System. Garmin International Inc - [STC SA02212AK](https://openairdocs.org/stc/SA02212AK): Replacement of existing landing and/or taxi light reflector and bulbs with high intensity discharge (HID) lighting systems. Seaplanes North LLC - [STC SA2586NM](https://openairdocs.org/stc/SA2586NM): Installation of J.P. Instruments temperature monitoring systems.. J P Instruments - [STC ST03151CH](https://openairdocs.org/stc/ST03151CH): Installation of heat exchanger kit, Kelly Aerospace kit #KATS-11-006,. Kelly Aerospace Thermal Systems, LLC - [STC SA00343BO](https://openairdocs.org/stc/SA00343BO): Installation of a single configuration or a dual configuration Avidyne Corporation Integrated Flight Display, Model IFD540 loaded with Release 10.0 software (or later FAA approved release). Avidyne Corporation - [STC SA00353BO](https://openairdocs.org/stc/SA00353BO): Installation of an auto lean system. Flight Enhancements LLC - [STC SA00352BO PAGE 1](https://openairdocs.org/stc/SA00352BO%20PAGE%201): Installation of an Avidyne Corporation Mode A/C/S Transponder with ADS-B Out capability, Model AXP340 loaded with Version 3.13 software (or later FAA approved version),. Avidyne Corporation - [STC SA01734SE](https://openairdocs.org/stc/SA01734SE): Application of Stewart Systems synthetic fabric covering system to aircraft fuselage, wings, tail surfaces, control surfaces and related parts.. Andrew D. Humphrey - [STC SA11172SC](https://openairdocs.org/stc/SA11172SC): Installation of an ADS600-B Automatic Dependent Surveillance-Broadcast (ADS-B) Universal Access Transceiver (UAT) and Global Positioning System (GPS) antenna. NavWorx Inc - [STC SA02119SE PAGE 1](https://openairdocs.org/stc/SA02119SE%20PAGE%201): Installation of Garmin GDL 88 ADS-B UAT Transceiver System. Garmin International Inc - [STC SA01969SE](https://openairdocs.org/stc/SA01969SE): Installation of a Mid-Continent MD302 Standby Attitude Module. Mid-Continent Instruments and Avionics - [STC SA01229SE PAGE 1](https://openairdocs.org/stc/SA01229SE%20PAGE%201): Installation of GNS 480 (CNX80) GPS WAAS Navigator with integrated VHF Navigation and Communication radios. Garmin International Inc - [STC SA01435WI](https://openairdocs.org/stc/SA01435WI): Installation of TKS Ice Protection System Components, with placard stating, 'INTENTIONAL FLIGHT INTO KNOWN ICING IS PROHIBITED'. CAV Ice Protection Inc - [STC SA02442AK PAGE 1](https://openairdocs.org/stc/SA02442AK%20PAGE%201): Approval of the L-3 Communications NGT 2000/2500 ADS-B system. ADS-B Technologies, LLC - [STC SA01933LA-D PAGE 1](https://openairdocs.org/stc/SA01933LA-D%20PAGE%201): Installation of Garmin Model 400W / 500W Series GPS-WAAS Navigation System. Garmin International Inc - [STC SA02930NY](https://openairdocs.org/stc/SA02930NY): Installation of Insight Instrument Corporation Graphic Engine Monitor (GEM 610C) models G3, G2, and G1 and 1200C model G4 as primary Cylinder Head Temperature (CHT), Exhaust Gas Temperature (EGT), and Turbine Inlet Temperature (TIT) Instruments. Insight Instrument Corporation - [STC SA02283SE PAGE 1](https://openairdocs.org/stc/SA02283SE%20PAGE%201): Installation of Electronics International Inc. Glass Panel Engine Monitor (with In Flight Data) CGR-30P. Electronics International Inc. All 98: https://openairdocs.org/tcds/A00003SE/stcs.md --- 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.