# TCDS A69EU: Airbus Poland S.A. - Type: Type certificate data sheet - Status: Current - Holder: Airbus Poland S.A. - Revision: 6 - Revised: July 14, 2022 - Product: Aircraft, Small Airplane - Certification basis: Part 23 - Data sheet PDF: https://openairdocs.org/files/sha256/bd/96/bd961a418497ffdda7a003391d51ffd6c7d899ab85ebc5b1c76de518c707e58c - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/A8342EAB89299BB786258883004BBE3C.0001 - Page: https://openairdocs.org/tcds/A69EU ## Models (2) As the data sheet lists them. - PZL-KOLIBER 150A - PZL-KOLIBER 160A ## 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 Rev. No. 6 1 4 5 2 4 5 2 2 4 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A69EU Revision 6 AIRBUS POLAND S.A. PZL-KOLIBER 150A PZL-KOLIBER 160A July 14, 2022 TYPE CERTIFICATE DATA SHEET NO. A69EU This data sheet, which is part of the Type Certificate No. A69EU 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. AIRBUS POLAND S.A. Al. Krakowska 110/114 02-256 Warsaw Poland Type Certificate Holder. Panstwowe Zaklady Lotnicze transferred TC A69EU to EADS-PZL "Warszawa- Okęcie" S.A. on April 9, 2004. EADS-PZL “Warszawa-Okęcie” S.A. transferred TC A69EU to AIRBUS POLAND Spolka Akcyjna (S.A.) on July 14, 2022. I. PZL-KOLIBER 150A (Normal and Utility Category), approved February 18, 1994. Engine. LYCOMING O-320-E2A. Fuel. 80/87 minimum grade aviation gasoline AVGAS 100/100 LL Oil. over 60ºF (+15ºC) SAE 50 30º to 90ºF (-1º to +32ºC) SAE 40 0º to 70ºF (-17º to +21ºC) SAE 30 below 10ºF (-12ºC) SAE 20 Engine Limits. For all operations: 2700 r.p.m. (150 HP) Maximum Cylinder Head Temperature: 500ºF (260ºC) Minimum Oil Pressure: 25 psi Maximum Oil Pressure: 100 psi Maximum Oil Temperature: 245ºF Propeller and Propeller Limits. 1. SENSENICH 74DM6-0-58 R.P.M. at maximum permissible throttle setting: 2700 Static r.p.m. - 2280. At idle - 600 r.p.m. No additional tolerances permitted. Blade pitch (at 27.75 in.) 18.4º. A69EU Page 2 of 10 Diameter: maximum - 74 in. (1880 mm), min. allowed for repairs - 72 in. (1829 mm) No further diameter reduction permitted. Spinner: PZL IC-50.210.00-0. 2. SENSENICH 74DM6-0-56 R.P.M. at maximum permissible throttle setting: 2700 Static r.p.m. - 2300. At idle - 600 r.p.m. No additional tolerances permitted. Blade pitch (at 27.75 in.) 17.8º. Diameter: maximum - 74 in. (1880 mm), min. allowed for repairs - 72 in. (1829 mm) No further diameter reduction permitted. Spinner: PZL IC-50.210.00-0. 3. SENSENICH 74DM6-0-54 R.P.M. at maximum permissible throttle setting: 2700 Static r.p.m. - 2320. At idle - 600 r.p.m. No additional tolerances permitted. Blade pitch (at 27.75 in.) 17.2º. Diameter: maximum - 74 in. (1880 mm), min. allowable for repairs - 72 in. (1829 mm) No further diameter reduction permitted. Spinner: PZL IC-50.210.00-0. Airspeed Limits (CAS). Category Normal/Utility Never exceed - VNE 156 m.p.h. (251 km/h) Max. structural cruising - VNO 124 m.p.h. (200 km/h) Maneuvering - VA 102 m.p.h. (164 km/h) Flap extended - VFE 87 m.p.h. (140 km/h) Maximum speed with canopy open beyond 4 inches: 100 mph. C.G. Range. Normal Category Forward limit at 1874 lb. (850 kg): 32.7 in. (0.830 m) from the ref. datum (13.3% MAC) Forward limit at 1433 lb. (650 kg): 31.2 in. (0.792 m) from the ref. datum (10.4% MAC) Rear limit: 40.2 in. (1.021 m) from the ref. datum (28% MAC) Utility Category Forward limit at 1698 lb. (770 kg): 32.2 in. (0.817 m) from the ref. datum (12.3% MAC) Forward limit at 1433 lb. (650 kg): 31.2 in. (0.792 m) from the ref. datum (10.4% MAC) Rear limit: 37.7 in. (0.956 m) from the ref. datum (23% MAC) Straight line variation between points given. A69EU Page 3 of 10 M.A.C. length 51.2 in. (1.3 m) Distance of M.A.C. leading edge from the reference datum 25.9 in. (0.657 m) Empty Weight C.G. Range None Maximum Weight. Normal Category - 1874 lb. (850 kg) Utility Category - 1698 lb. (770 kg) Number of Seats. 4 2 at +36.9 in. (0.937 m); 2 at +70.0 in. (1.777 m) - See NOTE 4 Minimum Crew. One pilot. Equipment and Baggage See NOTE 4. Weight. Fuel Capacity. 46.7 U.S. gal. (two 23.35 gal. tanks) at 41.6 in. 42.5 U.S. gal. - usable fuel (4.2 U.S. gal. unusable) [two 21.25 gal. tanks at +41.6 in.] (See NOTE 1). Oil Capacity. 8 qt. at -22.6 in. (See NOTE 1) Control Surface Movements. Aileron Up 17º30' (±1º) Down 13º30' (±1º) Elevator Up 30º (±1º) Down 25º (+0, -2º) Elevator Up 20º (±1º) Down 28º (±1º) Trim Tab Rudder Right 30º (+0, -2º) Left 30º (+0, -2º) Wing flaps Up 0º (±1.5º) Down 30º (±1.5º) Reference Datum. Front face of firewall. Leveling Means. Longitudinal fuselage longerons at canopy rails. Serial Numbers Eligible. Each individual aircraft manufactured under this type certificate must be accompanied by a Certificate of Airworthiness for Export (or certifying statement endorsed by the Exporting Civil Airworthiness Authority (ECAA) as noted below under "Import Requirements") when an application for U.S. airworthiness is made. PZL-KOLIBER 150A: 04940059 and subsequent. Import Requirements. 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 Office (CAO) of Poland 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. A69EU and to be in a condition for safe operation.’ Model Koliber 150A airplanes (SN: 0 393 0057 and 0 393 0058) modified by PZL Modification Kit No. 1 are eligible for a Standard Airworthiness Certificate under the U.S. Type Certificate. A69EU Page 4 of 10 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 certificate 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. Certification Basis. FAR 23 dated February 1, 1965, as amended through Amendment 23-23 effective December 1, 1978; FAR 23.2 and 23.561(b) (2) as amended through Amendment 23-36 effective September 14, 1988; FAR 23 Subpart F amended through Amendment 23-30 effective March 29, 1984; FAR 23 Appendix G amended through Amendment 23-37 effective August 18, 1990; FAR 36 dated December 1,1969, through Amendment 36-20 effective September 16, 1992. The Civil Aviation Office (CAO) of Poland originally type certificated this aircraft under its type certificate Number BB-193. The FAA validated this product under U.S. Type Certificate Number A69EU. Effective July 4, 2006, the European Aviation Safety Agency (EASA) began oversight of this product on behalf of Poland. The EASA TCDS number is EASA.A.091. Validation Basis. Type Certificate A69EU was issued pursuant to FAR 21.29 in validation of the General Inspectorate of Civil Aviation certification of compliance with the aforementioned certification basis, and in accordance with the standard airworthiness certificate provisions of FAR 21.183(c). 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, the following items of equipment are required: Model PZL-KOLIBER 150A - CAIB approved (for the FAA); Airplane Flight Manual, Ref. PZL Warszawa-Okecie Document No. LD-153-10/150A, dated January 1994, or later CAIB approved revision. II. PZL-KOLIBER 160A (Normal and Utility Category), approved February 13, 2001. Engine. LYCOMING 0-320-D2A Fuel. 91/96 minimum grade aviation gasoline AVGAS 100/100 LL Oil. over 80ºF (+26ºC) SAE 60 over 60ºF (+15ºC) SAE 50 30º to 90ºF ( -1º to +32ºC) SAE 40 0º to 70ºF ( -17º to +21ºC) SAE 30 below 10ºF ( -12ºC) SAE 20 Engine Limits. For all operations: 2700 r.p.m. (160 HP) Maximum Cylinder Head Temperature: 500ºF (260ºC) Minimum Oil Pressure: 25 psi Maximum Oil Pressure: 100 psi Maximum Oil Temperature: 245ºF A69EU Page 5 of 10 Propeller and Propeller Limits. 1. SENSENICH 74DM6-0-58 R.P.M. at maximum permissible throttle setting: 2700 Static r.p.m. 2280 Idle r.p.m. 600 (No additional tolerances permitted.) Blade pitch (at 27.75 in.) 18.4º. Diameter: maximum 74 in. (1880 mm) minimum (allowed for repairs) 72 in. (1829 mm) (No further diameter reduction permitted.) Spinner: PZL IC-50.210.00-0. Airspeed Limits (CAS). Category Normal (850 kg.) Utility (770 kg) Never exceed - VNE 156 mph (251 km/h) 168 mph (270 km/h) Max. structural cruising – VNO 124 mph (200 km/h) 124 mph (200 km/h) Maneuvering - VA 102 mph (164 km/h) 104 mph (168 km/h) Flap extended - VFE 87 mph (140 km/h) 87 mph (140 km/h) Maximum speed with canopy open beyond 4 inches: 100 mph. See NOTE 5 Category Normal (950 kg.) Utility (770 kg) Never exceed - VNE 143 mph (230 km/h) 143 mph (230 km/h) Max. structural cruising – VNO 114 mph (183 km/h) 114 mph (183 km/h) Maneuvering - VA 103 mph (165 km/h) 100 mph (161 km/h) Flap extended - VFE 89 mph (143 km/h) 89 mph (143 km/h) Maximum speed with canopy open beyond 4 inches: 100 mph. See NOTES 5, 6 C.G. Range. Normal Category (See NOTE 6) Forward limit at 2094 lb. (950 kg): 33.4 in. (0.849 m) from the ref. datum (14.8% MAC) Forward limit at 1874 lb. (850 kg): 32.7 in. (0.830 m) from the ref. datum (13.3% MAC) Forward limit at 1433 lb. (650 kg): 31.2 in. (0.792 m) from the ref. datum (10.4% MAC) Rear limit: 2094 lb. (950 kg) 40.2 in. (1.021 m) from the ref. datum (28% MAC) Rear limit: 1874 lb. (850 kg) 40.2 in. (1.021 m) from the ref. datum (28% MAC) Utility Category Forward limit at 1698 lb. (770 kg): 32.2 in. (0.817 m) from the ref. datum (12.3% MAC) Forward limit at 1433 lb. (650 kg): 31.2 in. (0.792 m) from the ref. datum (10.4% MAC) Rear limit: 1698 lb. (770 kg) 37.7 in. (0.956 m) from the ref. datum (23% MAC) A69EU Page 6 of 10 Straight line variation between points given. M.A.C. length 51.2 in. (1.3 m) Distance of M.A.C. leading edge from the reference datum 25.9 in. (0.657 m). Empty Weight C.G. Range None Maximum Weight. Normal Category 2094 lb. (950 kg) See NOTE 6 Normal Category 1874 lb. (850 kg) Utility Category 1698 lb. (770 kg) Number of Seats. 4 2 at +36.9 in. (0.937 m); 2 at +70.0 in. (1.777 m) See NOTE 4 Minimum Crew. One pilot. Equipment and Baggage See NOTE 4. Weight. Fuel Capacity. 46.7 U.S. gal. (two 23.35 gal. tanks) at 41.6 in. 42.5 U.S. gal. usable fuel (4.2 U.S. gal. unusable) [two 21.25 gal. tanks at +41.6 in.] (See NOTE 1). Oil Capacity. 8 qt. at -22.6 in. (See NOTE 1) Control Surface Movements. (Maximum Weight) 1874 lb.(850 kg) 2094 lb. (950 kg) (See NOTE 6) Aileron Up 17º30' (±1º) 14˚30' (±1º) Down 13º30' (±1º) 11º30' (±1º) Elevator Up 30º (±1º) 30º (±1º) Down 25º (+0, -2º) 25º (+0, - 2º) Elevator Trim Tab Up 20º (±1º) 20º (±1º) Down 28º (±1º) 28º (±1º) Rudder Right 30º (+0, -2º) 30º (+0, - 2º) Left 30º (+0, -2º) 30º (+0, - 2º) Wing flaps Up 0º (±1.5º) 6º (- 1º) Down 30º (±1.5º) 30º (±1.5º) Reference Datum. Front face of firewall. Leveling Means. Longitudinal fuselage longerons at canopy rails. Serial Numbers Eligible. Each individual aircraft manufactured under this type certificate must be accompanied by a Certificate of Airworthiness for Export (or certifying statement endorsed by the Exporting Civil Airworthiness Authority (ECAA) as noted below under "Import Requirements") when an application for U.S. airworthiness is made. PZL-KOLIBER 160A: 04980077 and subsequent. Import Requirements. 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 Office (CAO) of Poland on behalf of the European Community. The Export C of A should contain the following statement: ‘The aircraft covered A69EU Page 7 of 10 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. A69EU and to be in a condition for safe operation.’ 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 certificate 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. Certification Basis. FAR 23 dated February 1, 1965, as amended through Amendment 23-23 effective December 1, 1978; FAR 23.2 and 23.561(b) (2) as amended through Amendment 23-36 effective September 14, 1988; FAR 23 Subpart F amended through Amendment 23-30 effective March 29, 1984; FAR 23 Appendix G amended through Amendment 23-37 effective August 18, 1990; FAR 36 dated December 1, 1969, through Amendment 36-22 effective October 13, 1999. The Civil Aviation Office (CAO) of Poland originally type certificated this aircraft under its type certificate Number BB-193. The FAA validated this product under U.S. Type Certificate Number A69EU. Effective July 4, 2006, the European Aviation Safety Agency (EASA) began oversight of this product on behalf of Poland. The EASA TCDS number is EASA.A.091. Validation Basis. Type Certificate A69EU was amended pursuant to FAR 21.29 in validation of the General Inspectorate of Civil Aviation certification of compliance with the aforementioned certification basis, and in accordance with the standard airworthiness certificate provisions of FAR 21.183(c). 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, the following items of equipment are required: Model PZL-KOLIBER 160A - CAIB approved (for the FAA); Airplane Flight Manual, Ref. PZL Warszawa-Okecie Document No. LD-153-10(USA)/160A, dated April, 1998, or later CAIB approved revision. Service Information for Both Models Each of the documents listed below must state that it is approved by the European Aviation Safety Agency (EASA) or – for approvals made before July 4, 2006 – by the Civil Aviation Office (CAO) of Poland. (See Note 7) • 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: A69EU Page 8 of 10 • 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. NOTES. Applicable to both models unless otherwise stated NOTE 1. A current weight and balance report including list of equipment, certificated empty weight, and loading instructions, must be provided with each aircraft at the time of original airworthiness certification, and carried in the airplane at all times thereafter. The certificated empty weight and the corresponding center of gravity location must include full oil (15.4 lbs. at -22.6 inches), and unusable fuel (25.4 lbs. at +41.6 inches). NOTE 2. Placards (Refer to Manufacturer's Specifications for a complete listing): All required placards as listed in the approved Airplane Flight Manual must be installed in the appropriate locations. (1) The following placard must be displayed for PZL-KOLIBER 150A airplane in clear view of the pilot: KOLIBER 150A THIS AIRPLANE IN THE UTILITY CATEGORY MUST BE OPERATED IN COMPLIANCE WITH PLACARDS, MARKINGS AND FLIGHT MANUAL. LIMITATIONS IN CATEGORY "U" GROSS WEIGHT _______________________________________1698 LBS REAR C.G. POSITION LIMIT ____________________ 37.7 in. (23.0% MAC) NEVER EXCEED SPEED Vne ______________________160 MPH (139 KTS) LOAD FACTOR (FLAPS RETRACTED) _____________________+4.4 : - 1.8 ABRUPT USE OF CONTROLS PROHIBITED ABOVE VA ___________________________________106 MPH (92 KTS) MAX AIRSPEED IN ROUGH AIR VNO ______________128 MPH (111 KTS) MAX SPEED WITH FLAPS EXTENDED VFE __________91 MPH (79 KTS) ACROBATIC MANOEUVERS ARE LIMITED TO THE FOLLOWING: MANOEUVER ENTRY SPEED MANOEUVER ENTRY SPEED CHANDELLES ___130MPH (113 KTS) STEEP TURNS ___103MPH (89 KTS) LAZY EIGHTS ___130MPH (113 KTS) INVERTED ACROBATIC AND SPINS PROHIBITED REFER TO AFM FOR THE OPERATION IN NORMAL CATEGORY A69EU Page 9 of 10 (2) Refer to the Airplane Flight Manual of PZL-KOLIBER 150A airplane, Section 2, Limitations for a listing of other required placards. (3) The appropriate following placard must be displayed for PZL-KOLIBER 160A (1874 lb gross weight) airplane in clear view of the pilot: (4) Refer to the Airplane Flight Manual of PZL-KOLIBER 160A airplane, Section 2, Limitations for a listing of other required placards. NOTE 3. Instructions for Continued Airworthiness and Service Life Limits of components are contained in the Koliber 150A or 160A Maintenance Manual. Revisions to Airworthiness Limitations must be FAA approved. All service bulletins classified as mandatory by the General Inspectorate of Civil Aviation are identified to that effect and are mandatory for U.S. registered aircraft only if made the subject of an Airworthiness Directive issued by the FAA. NOTE 4. Total weight on the rear seats at station +70 inches aft of datum must not exceed 340 lbs. (154.2 kg). NOTE 5 To achieve uniformity, the Airplane Flight Manual assumes the same airspeed limits for the Utility Category as those determined for the Normal Category for the PZL-Koliber 150A and PZL-Koliber 160A (1874 lb. Gross weight) airplanes. NOTE 6 Operation of the Koliber 160A airplane at 2094 lbs. in the Normal Category is approved, providing Service Bulletin No. 11099048 and Mandatory Bulletin No. 11099050 or Service Bulletin No. 11000053 have been implemented. Operation will be in accordance with Supplement 3 of Model PZL -KOLIBER 160A - CAIB KOLIBER 160A THIS AIRPLANE IN THE UTILITY CATEGORY MUST BE OPERATED IN COMPLIANCE WITH PLACARDS, MARKINGS AND FLIGHT MANUAL. LIMITATIONS IN CATEGORY "U" GROSS WEIGHT _______________________________________1698 LBS REAR C.G. POSITION LIMIT ____________________ 37.7 in. (23.0% MAC) NEVER EXCEED SPEED Vne ______________________160 MPH (139 KTS) LOAD FACTOR (FLAPS RETRACTED) _____________________+4.4 : - 1.8 ABRUPT USE OF CONTROLS PROHIBITED ABOVE VA _____________________________________106 MPH (92 KTS) MAX AIRSPEED IN ROUGH AIR VNO ______________128 MPH (111 KTS) MAX SPEED WITH FLAPS EXTENDED VFE __________91 MPH (79 KTS) ACROBATIC MANOEUVERS ARE LIMITED TO THE FOLLOWING: MANOEUVER ENTRY SPEED MANOEUVER ENTRY SPEED CHANDELLES ___130MPH (113 KTS) STEEP TURNS ___103MPH (89 KTS) LAZY EIGHTS ___130MPH (113 KTS) INVERTED ACROBATIC AND SPINS PROHIBITED REFER TO AFM FOR THE OPERATION IN NORMAL CATEGORY A69EU Page 10 of 10 approved (for the FAA); Airplane Flight Manual, Ref. PZL Warszawa- Okecie Document No. LD -153-10(USA)/160A, dated April, 1998, or later CAIB approved revision. The following placard must be displayed for the PZL-Koliber 160A (2094 lb. gross weight) airplane in clear view of the pilot: NOTE 7 The national airworthiness authority (NAA) for this airplane is the Civil Aviation Office (CAO) of Poland. The CAO was previously known as CAIB, CACA and General Inspectorate of Civil Aviation (GICA). ...END... KOLIBER 160A THIS AIRPLANE IN THE UTILITY CATEGORY MUST BE OPERATED IN COMPLIANCE WITH PLACARDS, MARKINGS AND FLIGHT MANUAL. LIMITATIONS IN CATEGORY "U" GROSS WEIGHT _______________________________________1698 LBS REAR C.G. POSITION LIMIT ____________________ 37.7 in. (23.0% MAC) NEVER EXCEED SPEED Vne ______________________147 MPH (127 KTS) LOAD FACTOR (FLAPS RETRACTED) _____________________+4.4 : - 1.8 ABRUPT USE OF CONTROLS PROHIBITED ABOVE VA _____________________________________106 MPH (92 KTS) MAX AIRSPEED IN ROUGH AIR VNO ______________119 MPH (103 KTS) MAX SPEED WITH FLAPS EXTENDED VFE __________91 MPH (79 KTS) ACROBATIC MANOEUVERS ARE LIMITED TO THE FOLLOWING: MANOEUVER ENTRY SPEED MANOEUVER ENTRY SPEED CHANDELLES ___119 MPH (103 KTS) STEEP TURNS ___106 MPH (92 KTS) LAZY EIGHTS ___119 MPH (103 KTS) INVERTED ACROBATIC AND SPINS PROHIBITED REFER TO AFM FOR THE OPERATION IN NORMAL CATEGORY ``` ## ADs (4, in force first) - [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 2006-12-07](https://openairdocs.org/ad/2006-12-07): ECi cylinder assemblies · Aerostar AEIO-320-D1B, AEIO-320-D2B, AEIO-320-E1A and 386 more. Effective Jul 11, 2006 - [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 96-09-06](https://openairdocs.org/ad/96-09-06): Air Filter Assemblies · Maule Aerospace Technology 7ACA, 7ECA, 7FC and 180 more. Effective Jun 7, 1996 ## STCs approved under this data sheet (57, first 50) - [STC SA04652CH](https://openairdocs.org/stc/SA04652CH): To allow use of 100R grade aviation fuel meeting Swift Fuel, LLC specification. Swift Fuels LLC - [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 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 SA02594SE](https://openairdocs.org/stc/SA02594SE): SkyView HDX Instrumentation and Autopilot System manufactured. Dynon Avionics - [STC SA01757WI](https://openairdocs.org/stc/SA01757WI): To allow the use of UL91 or UL94 (minimum) grade aviation fuel. Swift Fuels LLC - [STC SA02658SE](https://openairdocs.org/stc/SA02658SE): Installation of Garmin GI 275 Multi-Function Display System. Garmin International Inc. - [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 SA01899WI](https://openairdocs.org/stc/SA01899WI): Installation of Garmin G3X Touch Electronic Flight Instrument System. Garmin International Inc. - [STC SA02019WI](https://openairdocs.org/stc/SA02019WI): Installation of the Trig Avionics TX56, TX56A, TX57, or TX57A VHF Nav-Com Radio.. Peregrine - [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 SA01818WI](https://openairdocs.org/stc/SA01818WI): Installation of Garmin G5 Electronic Flight Instrument. Garmin International Inc. - [STC SA09902AC](https://openairdocs.org/stc/SA09902AC): Installation of BendixKing KFD 900 Flight Display System. Honeywell International Inc. (Bendix King) - [STC SA11174SC PAGE 2](https://openairdocs.org/stc/SA11174SC%20PAGE%202): 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 SA00410BO](https://openairdocs.org/stc/SA00410BO): Installation of an AV-30-C Multi-Mode Indicator. uAvionix Corporation - [STC SA01831WI](https://openairdocs.org/stc/SA01831WI): To allow the use of UL91 (minimum) grade aviation fuel. Petersen Aviation Inc - [STC SA02268CH](https://openairdocs.org/stc/SA02268CH): Installation of Airwolf Filter Corp. Air Oil Separator. Airwolf Filter Corporation - [STC SA01560WI-D](https://openairdocs.org/stc/SA01560WI-D): Installation of the Honeywell KFD 840 Primary Flight Display System.. Honeywell International Inc - [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 SA00744DE](https://openairdocs.org/stc/SA00744DE): Installation of the Automatic Dependent Surveillance Broadcast (ADS-B) Out Equipment using a Trig Avionics TT31 Transponder and an approved position sensor. Peregrine - [STC SA00765DE](https://openairdocs.org/stc/SA00765DE): Installation of Automatic Dependent Surveillance Broadcast (ADS-B) Out functionality using the BendixKing KT74 Transponder and qualified position sensor. Peregrine - [STC SA04165NY](https://openairdocs.org/stc/SA04165NY): Installation of Latitude Technologies Skynode S200 Satcom system must be performed. Latitude Technologies Corporation - [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 SA01835WI](https://openairdocs.org/stc/SA01835WI): Installation of Trig Avionics TY-96 or TY-97 VHF Communications Radio. Peregrine - [STC SA00024NY](https://openairdocs.org/stc/SA00024NY): Installation of Airwolf remote mounted engine oil filter kit AFC-K007 on single or multi-engine fixed wing light aircraft incorporating Lycoming reciprocating engines of 450 horsepower or less.. Airwolf Filter Corporation - [STC SA01933LA-D](https://openairdocs.org/stc/SA01933LA-D): Installation of Garmin Model 400W / 500W Series GPS-WAAS Navigation System. Garmin International Inc - [STC SA00382BO](https://openairdocs.org/stc/SA00382BO): Installation of Globalstar Antenna and Cradle provisions to support a Globalstar GPS-1700 in non-composite airplanes. Avidyne Corporation - [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 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 SA02119SE PAGE 1](https://openairdocs.org/stc/SA02119SE%20PAGE%201): Installation of Garmin GDL 88 ADS-B UAT Transceiver System. Garmin International Inc - [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 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 SA02121SE](https://openairdocs.org/stc/SA02121SE): Installation of Garmin GTS 825 (TAS) or GTS 855 (TCAS I) Traffic System. Garmin International Inc - [STC SA02717NY PAGE 1](https://openairdocs.org/stc/SA02717NY%20PAGE%201): Installation of VoiceFlight Systems LLC VFS101 Speech Recognition Module. VoiceFlight Systems LLC - [STC SA02015SE-D](https://openairdocs.org/stc/SA02015SE-D): Installation of Garmin G500 Primary Flight Display (PFD) and Multifunction Display (MFD) System.. Garmin International Inc - [STC SA01692SE](https://openairdocs.org/stc/SA01692SE): Installation of a Garmin GMX 200 Multi-Function Display. Garmin International Inc - [STC SA03148NY](https://openairdocs.org/stc/SA03148NY): The installation of the Latitude Technologies Corporation S100 Tracking System. Latitude Technologies Corporation - [STC SA02016SE-D](https://openairdocs.org/stc/SA02016SE-D): Installation of Garmin GTS 800, GTS 820 or GTS 850 Traffic System. Garmin International Inc - [STC SA01487SE-D](https://openairdocs.org/stc/SA01487SE-D): Installation of a GDL 69 or GDL 69A XM Satellite Receiver. Garmin International Inc - [STC SA593CH](https://openairdocs.org/stc/SA593CH): Install Champion SlickSTART magneto booster system.. Champion Aerospace LLC - [STC SA01473SE](https://openairdocs.org/stc/SA01473SE): Installation of a GTX 32 (mode C), GTX 33 (mode S), or GTX 33D (mode S with diversity) Remote Transponde. Garmin AT Inc. - [STC SA01695SE](https://openairdocs.org/stc/SA01695SE): Installation of an antenna. Garmin AT Inc. - [STC SA01487SE](https://openairdocs.org/stc/SA01487SE): Installation of a GDL 69 or GDL 69A XM Satellite Receiver in accordance with Garmin Supplemental Type Certificate Master Data List, P/N 005-C0217-00, Revision A, dated December 20, 2004, or later FAA approved revision.. Garmin AT Inc. - [STC SA02154AK](https://openairdocs.org/stc/SA02154AK): Installation of the UPS Aviation Technologies Inc. Apollo MX20 multi-function display, P/N 430-0270-500.. Garmin AT Inc. - [STC SA02217AK](https://openairdocs.org/stc/SA02217AK): Installation of Garmin AT Model GDL90 UAT Data Link System, in accordance with Garmin AT, Inc., GDL 90 UAT Master Data List, P/N 560-0278-01, Revision A, dated November 12, 2004, or later FAA approved revision.. Garmin AT Inc. All 57: https://openairdocs.org/tcds/A69EU/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.