# TCDS A55EU: Airbus Poland S.A. - Type: Type certificate data sheet - Status: Current - Holder: Airbus Poland S.A. - Revision: 8 - Revised: July 14, 2022 - Product: Aircraft, Small Airplane - Certification basis: Part 21, Part 23, Part 36 - Registered aircraft: 24, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/22/9b/229b152a3877331e96c02dc3d02e305999e4f34887ad8f35ba9eab476780ffc7 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/1E0DFEE5EF62E61686258883004C3316.0001 - Page: https://openairdocs.org/tcds/A55EU ## Models (3) As the data sheet lists them. - PZL-104MA WILGA 2000 - PZL-104 WILGA 80 (PZL-Warszama-Okecie) - PZL-104M WILGA 2000 (PZL-Warszama-Okecie) ## 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 Rev. No. 8 2 4 5 7 6 6 6 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A55EU Revision 8 AIRBUS POLAND S.A. PZL-104 WILGA 80 PZL-104M WILGA 2000 PZL-104MA WILGA 2000 July 14, 2022 TYPE CERTIFICATE DATA SHEET A55EU This data sheet which is part of Type Certificate No. A55EU 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 A55EU to EADS-PZL "Warszawa- Okęcie" S.A. on April 9, 2004. EADS-PZL “Warszawa-Okęcie” S.A. transferred TC A55EU to AIRBUS POLAND Spolka Akcyjna (S.A.) on July 14, 2022 I. Model PZL-104 WILGA 80 (Normal Category), approved March 12, 1987 Engine AI-14RA nine cylinder air cooled radial. Reduction gear ratio: 0.787:1. Fuel 91 (minimum grade aviation fuel) (maximum tetraethyl lead (Tel) 0.04 oz/lb) Engine limits Manifold Cyl Head Rating S.H.P . R.P.M. Pressure (in-Hg) Altitude (Ft.) Temp °F (°C) Maximum continuous 220 2050 31.10 ± 0.1 S.L. 446 (230) Takeoff (5 min.) 260 2350 31.30 ± 0.4 S.L. 482 (250) Propeller US-122000 two blade constant speed. Diameter: 104.33 inches (2.65m) (no reduction permitted) Airspeed limits (CAS) V A (Maneuvering) 96 knots (178 km/h) VFE (Maximum flap extended) 84 knots (156 km/h) VNO (Maximum structural cruising) 112 knots (208 km/h) VNE (Never exceed) 126 knots (234 km/h) See CACA (or CAIB) Polish-approved AFM for airspeed limits when parachuting equipment is installed. C.G. range 16.73 in. (30.35% MAC) to 24.25 in. (44.0% MAC) aft of datum. Datum Wing slat leading edge M.A.C. 55.12 inches (1.4 m) aft of datum Leveling Means Longitudinal - By adjusting the elevation of fuselage Bench Mark 6 to be 26.77 inches above the elevation of Bench Mark 5 (left side of the fuselage.) (See ICA) A55EU Page 2 of 8 Maximum Weight Takeoff 2866 lb. (1300 kg) Landing 2789 lb. (1265 kg) Number of seats 4 (2 at 21.06 in. (0.535 m) aft of datum in the forward position and 2 at 58.54 in. (1.487 m) aft of datum) Maximum Baggage 66 lb. (30 kg) (91.38 inches (2.321m) aft of datum). Fuel Capacity (U.S. gal.) Usable - LH tank 22 U.S. gallons RH tank 22 U.S. gallons Total - 44 (moment arm 15.75 in. (0.4 m) aft of datum). See Note 1 for unusable fuel weight & C.G. data. Oil capacity Total - 4.1 U.S. gal (moment arm 15.94 in. forward of datum). See Note 1 for system oil weight & C.G. data. Control surface movements Aileron Up 26° (± 2°) Down 16° (± 2°) Elevator Up 38° (± 1°) Down 18° (± 2°) Elevator trim tab Up 30° (± 2°) Down 30° (± 2°) Rudder Left 26° (± 2°) Right 26° (± 2°) Flaps Up 0° Down 21° (± 2°) and 44° (± 2°) II. Model PZL-104M WILGA 2000 (Normal Category), approved February 25, 2002 Engine Lycoming IO-540 K1J5D Lycoming IO-540 K1D5 Lycoming IO-540 K1B5 Fuel 100/100LL minimum grade aviation gasoline Engine limits Cyl Head Rating S.H.P . R.P.M. Altitude (Ft.) Temp °F (°C) Maximum continuous 300 2700 S.L. 500 (260) Takeoff 300 2700 S.L. 500 (260) Propeller Hartzell HC-C3YR-1RF/F8468A-6R three blade constant speed. Maximum Diameter: 80.0 inches (2.032 m) Minimum Diameter (allowed for repairs): 76.0 inches (1.930 m) Optional propeller as installed per EADS PZL Service Bulletin No. 104M03037 Hartzell HC-C3YR-1RF/F8068 three blade constant speed. Maximum Diameter: 82.0 inches (2.083 m) Airspeed limits (CAS) V A (Maneuvering) 100 knots (185 km/h) VFE (Maximum flap extended) 87 knots (162 km/h) VNO (Maximum structural cruising) 112 knots (208 km/h) VNE (Never exceed) 131 knots (243 km/h) See CAIB Polish-approved AFM for airspeed limits when parachuting equipment is installed. C.G. range 16.0 in. (29.0% MAC) to 24.8 in. (45.0% MAC) aft of datum. Datum Wing slat leading edge M.A.C. 55.12 inches (1.4 m) aft of datum Leveling Means Longitudinal - By adjusting the elevation of fuselage Bench Mark 6 to be 26.77 inches above the elevation of Bench Mark 5 (left side of the fuselage.) (See ICA) A55EU Page 3 of 8 Maximum Weights Takeoff 3086 lb. (1400 kg) Landing 3086 lb. (1400 kg) Maximum zero fuel weight 2998 lb. (1360 kg) Number of seats 4 (2 at 21.06 in. (0.535 m) aft of datum in the forward position and 2 at 58.54 in. (1.487 m) aft of datum) Maximum Baggage 66 lb. (30 kg) 91.38 inches (2.321m) aft of datum. Fuel Capacity (U.S. gal.) Usable - LH tank 50.2 U.S. gallons RH tank 50.2 U.S. gallons Total – 100.4 gallons (moment arm 16.5 in. (0.42 m) aft of datum.) See Note 1 for unusable fuel weight & C.G. data. Oil capacity Total – 12.0 U.S. quarts (moment arm 41.54 in. (1.055m) forward of datum). See Note 1 for system oil Wt. & C.G. data. Control surface movements Aileron Up 26° (± 2°) Down 16° (± 2°) Elevator Up 38° (± 1°) Down 18° (± 2°) Elevator trim tab Up 20° (± 2°) Down 20° (± 2°) Rudder Left 26° (± 2°) Right 26° (± 2°) Flaps Up 0° Down 21° (± 2°) and 44° (± 2°) III. Model PZL-104MA WILGA 2000 (Normal Category), approved June 12, 2006 (See Note 4) Engine Lycoming IO-540 K1D5 Lycoming IO-540 K1B5 Fuel 100/100LL minimum grade aviation gasoline Engine limits Cyl Head Rating S.H.P . R.P.M. Altitude (Ft.) Temp °F (°C) Maximum continuous 290 2575 S.L. 500 (260) Takeoff 290 2575 S.L. 500 (260) Propeller Hartzell HC-E3YR-1RF/F8068 +2 (FAA Certificate No. P33EA) Three blade constant speed. Maximum Diameter: 84.0 inches (2.1336 m) Minimum Diameter (allowed for repairs): 80.0 inches (2.032 m) Fuel 100/100LL minimum grade aviation gasoline Fuel Capacity (U.S. gal.) Usable – 100.4 US gallons (380 l) Total – 103.6 US gallons (392 l) See Note 1 for unusable fuel weight & C.G. data. Oil Outside Temperature MIL-L-6082B Spec. Mineral Grades MIL-L-22851 Spec. Ashless Dispersant Grades full range of temperatures SAE 15W50 or 20W50 above +27°C (80°F) SAE 60 SAE 60 above +16°C (60° F) SAE 50 SAE 40 or SAE 50 -1° to 32°C (30° to 90° F) SAE 40 SAE 40 -18° to 21°C ( 0° to 70° F) SAE 30 SAE 30, 40, 20W40 below -12°C (10° F) SAE 20 SAE 30 , 20W30 A55EU Page 4 of 8 Oil capacity Total – 12.0 U.S. quarts (11.4 l) (integrated with engine) See Note 1 for system oil Wt. & C.G. data. Airspeed limits (CAS) V A (Maneuvering) 104 knots (192 km/h) VFE (Maximum flap extended) 87 knots (162 km/h) VNO (Maximum structural cruising) 112 knots (208 km/h) VNE (Never exceed) 131 knots (243 km/h) VSO (Stalling speed) 48 knots (89 km/h) Maximum Weights Takeoff 3307 lb. (1500 kg) Landing 3307 lb. (1500 kg) Maximum zero fuel weight 3146 lb. (1427 kg) Minimum in flight 2377 lb. (1078 kg) Flight load factors Flaps retracted positive factor +3.8 negative factor -1.52 Flaps extended 44° positive factor +2.0 negative factor 0.0 C.G. range Minimum front centre of gravity location: Q = 1500 kg (3307 lb) 34.0 % MAC − 0.476 m (18.74 in) aft of datum Q ≤ 1400 kg (3086 lb) 29.5 % MAC − 0.413 m (16.3 in) aft of datum linear variation between these points Maximum rear centre of gravity location: Q = 1500 kg (3307 lb) 44.0 % MAC − 0.616 m (24.25 in) aft of datum Q ≤ 1400 kg (3086 lb) 45.0 % MAC − 0.630 m (24.8 in) aft of datum linear variation between these points Length of MAC 1.4 m (55.1 in.) Position of leading edge of MAC aft of datum 0.0 m ( 0.0 in.) Datum A plane tangent to the leading edge of the wing slat and perpendicular to the mean aerodynamic chord (MAC) 34.0% 29.5% 44% 45% 1400 kg (3086 lb) 1500 kg (3307 lb) Minimum weight 1078 kg (2377 lb) A55EU Page 5 of 8 Leveling Means Acc. to rigging points, elevation of point 6 over point 5: 680 mm (26.8 in.) (refer to AFM section 6.1) Minimum crew 1 (pilot) Number of seats 4 (2 front and 2 rear) Maximum Baggage 66 lb. (30 kg) in baggage compartment. Control surface movements Aileron Up 26° (± 2°) Down 16° (± 2°) Elevator Up 38° (± 1°) Down 18° (± 2°) Elevator trim tab Up 20° (± 2°) Down 20° (± 2°) Rudder Left 22° (± 1°) Right 22° (± 1°) Flaps take-off 21° (± 2°) landing 44° (± 2°) Wheels and Tires Main wheel CLEVELAND 40-75D Main wheel tire/size GOODYEAR 8.00-6TT 486 x 191 mm (19.1 x 7.5 in.) or 8.50-6TT 549 x 218 mm (21.6 x 8.6 in.) Tail wheel/size STOMIL 255 x 110 mm (10.0 x 4.3 in.) Glider and banner towing Minimum towing speed (IAS) (CAS) gliders δKL = 0° 125 km/h (67 kts) 124 km/h (67 kts) δKL = 21° 110 km/h (59 kts) 108 km/h (58 kts) Maximum towing speed δKL = 0° 165 km/h (89 kts) 167 km/h (90 kts) Maximum take-off and landing weight of the airplane 1400 kg (3086 lb.) Maximum total weight of airplane + glider system 1890 kg (4167 lb.) Maximum number of gliders towed 2 Maximum number of persons aboard 2 (on front seats) Safety link between the rope and the towing hook with the breaking force not more than 9320 N (950 kg) (2094 lb) DATA PERTINENT TO ALL MODELS Serial numbers eligible See “Import Requirements.” 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. A55EU 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. A55EU Page 6 of 8 Certification Basis For Model PZL-104 Wilga 80 FAR 21.29 using the airworthiness requirements of FAR Part 23 effective 1 February 1965, including Amendments 23-1 through 23-20. Compliance has been shown with FAR 36, Amendments 36-1 through 36-12. Type Certificate No. A55EU issued March 12, 1987. Effective date of application for Type Certificate per FAR 21.17 (c)(2) December 5, 1980.For Model PZL-104M Wilga 2000 FAR 21.29 using the airworthiness requirements of FAR Part 23 dated February 1, 1965, as amended through Amendment 23-20 effective September 1, 1977; FAR Part 23 Subpart B as amended through Amendment 23-45 effective September 7, 1993; FAR Part 23 Subparts E and F as amended through Amendment 23-30 effective March 29, 1984; FAR Part 23 Appendices F and G as amended through Amendment 23-34 effective February 17, 1987. Compliance has been shown with FAR 36, Amendments 36-1 through 36-22. Amended Type Certificate No. A55EU rev. 1 issued February 25, 2002. Effective date of application for Amended Type Certificate October 2, 1996. For Model PZL-104MA Wilga 2000 FAR 21.29 using the airworthiness requirements of FAR Part 23 dated February 1, 1965, as amended through Amendment 23-20 effective September 1, 1977; FAR Part 23 Subpart B as amended through Amendment 23-45 effective September 7, 1993; FAR Part 23 Subparts E and F as amended through Amendment 23-30 effective March 29, 1984; FAR Part 23 Appendices F and G as amended through Amendment 23-34 effective February 17, 1987. Compliance has been shown with FAR 36, Amendments 36-1 through 36-27 effective September 6, 2005. Amended Type Certificate No. A55EU rev. 4 issued June 12, 2006. Date of application for Amended Type Certificate for model PZL-104MA is November 28, 2005. The Civil Aviation Office (CAO) of Poland originally type certificated these aircraft models under its type certificate Number BB-130. The FAA validated this product under U.S. Type Certificate Number A55EU. Effective November 16, 2005, the European Aviation Safety Agency (EASA) began oversight of this product on behalf of Poland. The EASA TCDS number is EASA.A.061. Equipment The basic required equipment as described in the applicable airworthiness regulations (see Certification Basis) must be installed in the airplane for certification. For Model PZL-104 Wilga 80: Approved Airplane Flight Manual dated June 15, 1979, or later approved revisions, signed by the Polish CACA (or CAIB) is required. (See below – Service Information section) For Model PZL-104M Wilga-2000: CAIB Approved Airplane Flight Manual dated September 15, 1999 or later CAIB approved revision is required. (See below – Service Information section) For Model PZL-104M Wilga-2000 with optional propeller per EADS PZL SB No. 104M03037: CAIB Approved Airplane Flight Manual, Revision No. 18, dated April 22, 2003 or later CAIB approved revision is required. (See below – Service Information section) For Model PZL-104MA Wilga-2000: CAO/EASA Approved Airplane Flight Manual, A55EU Page 7 of 8 document No. WMA-01-US, dated May 2006 or later CAO/EASA approved revision is required. (See below – Service Information section) Service Information For Model PZL-104 Wilga 80: Section 25 of the Maintenance Instruction for the PZL-104 Wilga 80 aircraft and all mandatory service bulletins that indicate applicability to the U.S. approved Model PZL-104 Wilga 80 and are approved by the CACA (or CAIB) and include a statement to that effect, may be interpreted as FAA approved. (See below) For Model PZL-104M Wilga 2000: Instructions for Continued Airworthiness for the PZL-104M Wilga 2000 aircraft and all mandatory service bulletins that indicate applicability to the U.S. approved Model PZL-104M Wilga 2000 and are approved by the General Inspectorate of Civil Aviation (GICA) and include a statement to that effect, may be interpreted as FAA approved. (See below) For Model PZL-104MA Wilga 2000: Instructions for Continued Airworthiness (ICA) for the PZL-104MA Wilga 2000 aircraft and all mandatory service bulletins that indicate applicability to the U.S. approved Model PZL-104MA Wilga 2000 and are approved by the CAO/EASA and include a statement to that effect, may be interpreted as FAA approved. (See below) The required ICA for the PZL-104MA Wilga 2000 are contained in PZL- 104MA Wilga 2000 Maintenance Manual, document No. WMA-02-US, dated May 16, 2006 or later CAO approved revision. Each of the documents listed below must state that it is approved by the European Aviation Safety Agency (EASA) or – for approvals made before November 16, 2005 – by the Civil Aviation Office (CAO) of Poland. (See Note 5) • Service bulletins, • Structural repair manuals, • Vendor manuals, • Aircraft flight manuals, and • Overhaul and maintenance manuals. The FAA accepts such documents and considers them FAA-approved for type design data only unless one of the following conditions exists: • The documents change the limitations, performance, or procedures of the FAA approved manuals; or •The documents make an acoustical or emissions changes to this product’s U.S. type certificate as defined in 14 CFR § 21.93. The FAA uses the post type validation procedures to approve these documents. The FAA may delegate on case-by-case to EASA to approve on behalf of the FAA for the U.S. type certificate. If this is the case it will be noted on the document. NOTES: Note 1 Weight and Balance: A current Weight and Balance Report must be in each aircraft at the time of original airworthiness certification and at all times afterwards. For Model PZL-104 Wilga 80: Unusable fuel in the fuel tank is 0.52 U.S. gallons (moment arm 13.8 inches aft of datum.) Undrainable oil in the system is 0.132 U.S. gallons (moment arm 13.43 inches aft of datum) For Model PZL-104M Wilga-2000 and Model PZL-104MA Wilga 2000 The certificated empty weight and corresponding center of gravity location must include full oil of 12.0 U.S. quarts (23.1lbs at 41.54 in. forward of datum) and unusable fuel in each fuel tank of 1.60 U.S. gallons (moment arm 16.5 in. aft of datum). Note 2 All placards required in the Limitations section of the CAO/EASA approved Airplane Flight Manual must A55EU Page 8 of 8 be installed in the appropriate locations. Note 3 Instructions for Continued Airworthiness and Service Life Limits of components are contained: For Model PZL-104 Wilga 80: In the Maintenance Instruction for the PZL-104 Wilga Aircraft. For Model PZL-104M Wilga-2000: In the PZL-104M Wilga 2000 Maintenance Manual. For Model PZL-104MA Wilga-2000: In the PZL-104MA Wilga 2000 Maintenance Manual document No. WMA-02-US, dated May 16, 2006 or later revision. Revisions to Airworthiness Limitations must be EASA and FAA approved. All service bulletins classified as mandatory by the CAO/EASA are identified to that effect and may be subject to an Airworthiness Directive issued by the FAA. Note 4 Serial number eligibility for the PZL-104 MAWilga 2000 model starts with manufacturer serial number 000050019, 00050021and up. The certification process has been run on airplane serial No. 00050019. Note 5 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..... ``` ## ADs (5, 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 2009-14-10](https://openairdocs.org/ad/2009-14-10): Fuselage · EADS-PZL Warszawa-Okecie PZL-104 WILGA 80. Effective Aug 12, 2009 - [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 2000-16-51](https://openairdocs.org/ad/2000-16-51): Front Tailplane to Fuselage Joint Connector · EADS-PZL Warszawa-Okecie PZL-104 WILGA 80. Effective Aug 21, 2000 - [AD 2009-09-04](https://openairdocs.org/ad/2009-09-04) (historical): Fuselage · EADS-PZL Warszawa-Okecie PZL-104 WILGA 80. Effective May 18, 2009 ## Registered aircraft by registry model (OpenAirDocs) - [Wsk-Pzl Warzawa-Okecie PZL-104 WILGA 80](https://openairdocs.org/model/wsk-pzl-warzawa-okecie-pzl-104-wilga-80): 16 aircraft (registry code 9810280) - [EADS PZL Warszawa-Okecie PZL-104MA WILGA 2000](https://openairdocs.org/model/eads-pzl-warszawa-okecie-pzl-104ma-wilga-2000): 4 aircraft (registry code 7360321) - [EADS PZL Warszawa-Okecie PZL-104M WILGA 2000](https://openairdocs.org/model/eads-pzl-warszawa-okecie-pzl-104m-wilga-2000): 3 aircraft (registry code 7360320) - [PZL Warszawa-Okecie PZL-104M WILGA 2000](https://openairdocs.org/model/pzl-warszawa-okecie-pzl-104m-wilga-2000): 1 aircraft (registry code 7360322) ## STCs approved under this data sheet (65, first 50) - [STC SA12428CH](https://openairdocs.org/stc/SA12428CH): Installation of the Lycoming Engines Electronic Ignition System (EIS). Lycoming Engines, An Operating Division of AVCO Corporation - [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 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 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 SA01435LA](https://openairdocs.org/stc/SA01435LA): Installation of engines modified with Firewall Forward Technologies LLC modified camshaft. Centri-Lube Technologies LLC - [STC SA00756DE](https://openairdocs.org/stc/SA00756DE): Installation of Automatic Dependent Surveillance Broadcast (ADS-B) Out Equipment using a Trig Avionics TT22 Transponder and an approved Global Positioning System (GPS) Position Sensor. 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 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 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 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 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 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 SA2586NM](https://openairdocs.org/stc/SA2586NM): Installation of J.P. Instruments temperature monitoring systems.. J P Instruments - [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 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 SA01487SE-D](https://openairdocs.org/stc/SA01487SE-D): Installation of a GDL 69 or GDL 69A XM Satellite Receiver. Garmin International Inc - [STC ST00961LA](https://openairdocs.org/stc/ST00961LA): Installation of MASS Systems fire extinguisher cartridges as replacements for Walter Kidde Aerospace fire extinguisher cartridges in fire extinguisher bottles installed in the airplane models noted on the FAA Approved Model List dated June 29, 2000, or later FAA approved revisions. These fire extinguisher cartridges are in accordance with the MASS Systems Master Drawing List No. 30980-1, "Slug Thrower Cartridges Master Drawing List", Revision N/C, dated June 26, 2000, or later FAA approved revisions.. AMETEK AMERON LLC d/b/a MASS Systems - [STC SA02033AT](https://openairdocs.org/stc/SA02033AT): Modification to install an air-oil separator to prevent oil from being aspirated from the engine breather line.. M-20 Oil Separators 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 ST02481CH](https://openairdocs.org/stc/ST02481CH): Installation of camera quick disconnect mounting.. NASS-EAC - [STC SA01695SE](https://openairdocs.org/stc/SA01695SE): Installation of an antenna. Garmin AT Inc. - [STC SA02337CH](https://openairdocs.org/stc/SA02337CH): Installation of fuselage mounted high definition television camera. NASS-EAC All 65: https://openairdocs.org/tcds/A55EU/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.