# TCDS A50EU: Pilatus Aircraft Ltd. - Type: Type certificate data sheet - Status: Current - Holder: Pilatus Aircraft Ltd. - Revision: 4 - Revised: July 7, 2021 - Product: Aircraft, Small Airplane - Certification basis: Part 23, Part 21 - Registered aircraft: 19, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/b5/9b/b59b81ac4afff2a8f96fb4e3cac429797626339c683546abb4351ae71db3d75c - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/4077DBB4D21CC1CB8625870B00624147.0001 - Page: https://openairdocs.org/tcds/A50EU ## Models (1) As the data sheet lists them. - PC-7 ## What the data sheet says From the PDF's text layer, line by line; tables lose their columns. The PDF is the record. ```text DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET No. A50EU This data sheet, which is a part of Type Certificate No. A50EU, prescribes conditions and limitations under which the products for which the type certificate was issued meets the airworthiness requirements of the Federal Aviation Administration. Type Certificate Holder. Pilatus Aircraft Ltd CH-6370 STANS (Switzerland) Model PC-7 (Acrobatic Category) Approved August 12, 1983. Engine. Pratt & Whitney Aircraft of Canada Ltd. PT6A-25 or PT6A-25A Turboprop. Fuel. See Airplane Flight Manual for approved fuels and additives. Oil. See Airplane Flight Manual for approved oils. (Engine & Gearbox) Engine Limits. Maximum Permissible N1Gas Prop. Turbine Shaft Torque Generator Shaft Interstage Power Pressure Speed Speed Temperature SHP Psi % RPM ºC Takeoff and Max. Continuous 550 42.5 101.5 2200 695 Starting Transient 101.5 2200 1090* Max. Acceleration 48.5 102.6 2420 825 * These values are time limited to NOTE: 100% Gas Generator Speed = 37,468 rpm two seconds Engine torque is limited by a torque controller to 1315 lb-ft (42,5 psi) at sea level. Oil temperatures: Starting - 40º minimum idle - 40º to +99ºC max. continuous + 10º to +99ºC Inverted flight (less than zero g) is limited to 30 seconds. Page No. 1 2 3 4 5 Rev. No. 4 1 4 3 3 A50EU Revision 4 Pilatus PC-7 July 07, 2021 2 A50EU Propeller and Propeller Limits. Hartzell HC-B3TN-2 hubs with Hartzell T 10173C-8 or 10173CH-8 blades, three blade constant speed type. Diameter: 92 3/8 to 93 3/8 inches (cropping of blade tip not permitted) Pitch settings at: (measure at 30 inch station) Minimum pitch +14º Feathered +83.5º ± 1.5º Propeller blade life limit: 9700 hours Spinner: Hartzell C 3065 P Airspeed Limits (CAS). Max. operating speed (VMO) 270 knots up to 15,000 ft altitude above 15,000 ft limited to (VMO) 0.55 max. operating Mach. No. Maneuvering speed (VA) 175 knots at MTOW = 4189 lbs. Max. speed with flaps (VFE) 135 knots Max. speed with landing gear extended (VLO) 135 knots Maneuvering Load Factors. Acrobatic Max. positive up to VMO + 6.00 Max. negative up to VMO - 3.00 C.G. Range. (Landing Gear 13.707 ft to 14.232 at 4189 lbs or less (18% - 28% MGC) Extended). Maximum Weight. Ramp 4213 lbs Takeoff 4189 lbs Landing 4189 lbs Zero fuel 3668.5 lbs Number of Seats. Two, front seat at 13.494 ft. rear seat at 17.611 ft. For solo flight the pilot must occupy the front seat. Maximum Baggage. 55 lb at 21.981 ft in baggage compartment. Fuel Capacity. Total Usable Arm 129.4 gals 125.2 gals 13.83 ft. Oil Capacity. Total Arm 4.22 gals 7.66 ft 3 A50EU Control Surface Movements. Wing flap Takeoff 23º ± 2º Landing 50º ± 2º Ailerons Up 20º ± 1º Down 11º ± 1º Aileron tab Up 12.5º ± 1.5º Down 18º ± 1.5º Elevator Up 18.5º ± 1º Down 16º ± 1º Elevator tab Up 15º ± 2º Down 20º ± 2º Rudder Right 24º ± 1º Left 24º ± 1º Rudder tab Right 11º ± 1.5º Left 17.75º ± 1.5º Rudder tab At 24º rudder deflection to the right, Anti-Flettner deflection: Right 7±1º At 24º rudder deflection to the left, Anti-Flettner deflection: Left 7±1º Maximum Operating Altitude. 25,000 ft Datum. 9.84 ft. in front of firewall. Leveling Means. Marks (rivet heads) on each side of fuselage. Canopy rails horizontal. See Section 8 of Airplane Maintenance Manual. Certification Basis. Type certification under 14 CFR Section 21-29 including the following requirements: - 14 CFR Part 23 effective February 1, 1965, including amendments 23-1 through 23-16 plus FAR 23.977 Amendment 23-17, FAR 25.393 Amendment 25-37 and - 14 CFR Part 36 effective December 1, 1969, including Amendments 36-1 through 36-12 and - SFAR 27 effective December 12, 1973, including Amendments SFAR 27-1 through SFAR 27-4 (see Note 5) and - Exemption No. 3748 from Section 23.49(b)(1). Date of application: December 21, 1981. Type Certificate issued on August 12, 1983. Import Requirements. An FAA Standard Airworthiness Certificate may be issued on the basis of a Certificate of Airworthiness for Export signed by a representative of the Swiss Federal Air Office, containing the following statement: "The airplane covered by this certificate has been examined, tested and found to conform to the type design approved under Type Certificate No. A50EU, and to be in condition for safe operation." Airplane S/N 395 is eligible for a U.S. standard Airworthiness Certificate when the requirements of 14 CFR Sections 45.11 and 45.13, and all other import requirements of this type certificate data sheet are satisfied. 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. 4 A50EU Serial Nos. Eligible. A Certificate of Airworthiness for Export endorsed as noted under "Import Requirements" must be submitted for each individual aircraft for which application for U.S. Certification is made. Service Information. Service bulletins, structural repair manuals, vendor manuals, aircraft flight manuals, and overhaul and maintenance manuals, should contain a statement that the document is approved by the Swiss Federal Office of Civil Aviation (FOCA). (NOTE 2, NOTE 3 and NOTE 4) 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 FOCA 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. Current weight and balance report including list of equipment in certificated empty weight, and loading instructions, must be provided for each aircraft at the time of original certification. The certificated empty weight and corresponding center of gravity location must include full oil (31.65 lbs at + 7.66 ft), and unusable fuel (28.66 lbs. at + 15.39 ft). NOTE 2. All placards required in the approved Airplane Flight Manual must be installed on the airplane in the appropriate location. Revisions to this report may be approved by FOCA on behalf of the FAA, unless they are changes to the limitation section. These changes require FAA approval for the US version. NOTE 3. The Chapter 5 of the Swiss Federal Office of Civil Aviation (FOCA) approved PC -7 Aircraft Maintenance Manual, Document No. 01715, presents the airworthiness limitations, overhaul limitations (TBO), scheduled and unscheduled maintenance checks. The “Airframe Fatigue Life” is presented in paragraph 3 of section 05-10-00, and the “Time Limited Inspection Requirements” are presented in section 05-10-20. The Airworthiness Limitations are presented in section 05-10-10 “Lifed and Overhauled Components” and was approved by FOCA and the FAA. Revisions to this section must be approved by FOCA and the FAA. NOTE 4. Information essential for the proper operation and maintenance of the airplane are contained in the following Pilatus Aircraft Ltd. documents: (a) Airplane Flight Manual: Swiss Federal Office of Civil Aviation (FOCA) approved Document No. 01678 including actual weight and balance data and equipment list for the individual airplane (Report No. 01603-A). 5 A50EU NOTE 4. (cont.) (b) Airplane Flight Manual: Swiss Federal Office of Civil Aviation (FOCA) approved Document No. 01678 including actual weight and balance data and equipment list for the individual airplane (Report No. 01603-A). (c) Maintenance Manual: PC-7 Maintenance Manual Document No. 01715. Pages of the document 01715 applicable to the US N-registered aircraft are identified with either • “ALL” followed by no letter in the footer, or • “ALL” followed by a “U” in the footer (maybe be in combination with other letters e.g. “U, HU, HMU. etc…) (d) PC-7 Structural Repair Manual: Document No. 01720 (e) PC-7 Wiring Manual: Document No. 01718 (f) PC-7 Illustrated Parts Catalog: Document No. 01719 (g) PC-7 Tool and Equipment Manual: Document No. 01724 NOTE 5. Compliance with the fuel venting provisioned of SFAR-27 is achieved by incorporation of the components listed on Pilatus Drawing No. 119.35.07.008. NOTE 6. Each seat is to be equipped with Pilatus PC-7 Harness Assembly, Part No. G.Q.D. 14081, manufactured by G.Q. Defence Equipment, Ltd., Woking, England. (Ref. Exemption No. 3748) NOTE 7. This airplane is not FAA approved for use with underwing stores or underwing fuel tanks. .....END..... ``` ## ADs (29, in force first) - [AD 2026-13-02](https://openairdocs.org/ad/2026-13-02): Navigation · Airbus Canada Limited Partnership 18, 49-46, 80-A and 555 more. Effective Jul 1, 2026 - [AD 2020-26-19](https://openairdocs.org/ad/2020-26-19): Time Limits/Maintenance Checks · Pilatus PC-7. Effective Mar 29, 2021 - [AD 2021-04-06](https://openairdocs.org/ad/2021-04-06): Flight Compartment, Emergency Equipment · Pilatus PC-7. Effective Feb 12, 2021 - [AD 2019-05-15](https://openairdocs.org/ad/2019-05-15): Electric Power · Pilatus PC-7. Effective Apr 23, 2019 - [AD 2018-04-10](https://openairdocs.org/ad/2018-04-10): Landing Gear · Pilatus PC-7. Effective Apr 12, 2018 - [AD 2016-17-07](https://openairdocs.org/ad/2016-17-07): Fuselage · Pilatus PC-7. Effective Sep 30, 2016 - [AD 2015-07-04](https://openairdocs.org/ad/2015-07-04): Air Conditioning · Pilatus PC-7. Effective May 19, 2015 - [AD 2015-01-03](https://openairdocs.org/ad/2015-01-03): Standard Practices/Structures · Pilatus PC-7. Effective Mar 2, 2015 - [AD 2013-22-13](https://openairdocs.org/ad/2013-22-13): Electrical Power · Pilatus PC-7. Effective Nov 29, 2013 - [AD 2013-13-10](https://openairdocs.org/ad/2013-13-10): Engine Controls · Pilatus PC-7. Effective Aug 14, 2013 - [AD 2013-01-06](https://openairdocs.org/ad/2013-01-06): Fuselage · Pilatus PC-7. Effective Feb 7, 2013 - [AD 2010-22-09](https://openairdocs.org/ad/2010-22-09): Wings · Pilatus PC-7. Effective Dec 3, 2010 - [AD 2010-12-04](https://openairdocs.org/ad/2010-12-04): Fuselage · Pilatus PC-7. Effective Jul 13, 2010 - [AD 2009-26-05](https://openairdocs.org/ad/2009-26-05): Landing Gear. · Pilatus PC-7. Effective Feb 1, 2010 - [AD 2009-16-02](https://openairdocs.org/ad/2009-16-02): Fuselage. · Pilatus PC-7. Effective Sep 9, 2009 - [AD 2006-23-01](https://openairdocs.org/ad/2006-23-01): Main landing gear bay · Pilatus PC-7. Effective Dec 13, 2006 - [AD 2005-18-20](https://openairdocs.org/ad/2005-18-20): "FASTprop" propeller de-icers · Hartzell PHC-C3YF-1RF/F8468A(B,K)-8R constant speed propeller (STC SA00718LA or 17 others). Effective Oct 14, 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 2004-23-01](https://openairdocs.org/ad/2004-23-01): Fuel Booster pumps · Pilatus PC-7. Effective Dec 27, 2004 - [AD 2004-04-01](https://openairdocs.org/ad/2004-04-01): Engine-driven pump housing · Pilatus PC-12, PC-12/45 and PC-7. Effective Mar 29, 2004 - [AD 2003-20-05](https://openairdocs.org/ad/2003-20-05): Forward and Aft Dihedral Fittings · Pilatus PC-7. Effective Nov 14, 2003 - [AD 2002-22-03](https://openairdocs.org/ad/2002-22-03): Main Landing Gear Front Attachment Brackets · Pilatus PC-7. Effective Dec 20, 2002 - [AD 2001-26-13](https://openairdocs.org/ad/2001-26-13): Emergency Landing-gear Extension System · Pilatus PC-7. Effective Feb 12, 2002 - [AD 2001-05-02](https://openairdocs.org/ad/2001-05-02): Elevator and Rudder Attachment Brackets · Pilatus PC-7. Effective Apr 27, 2001 - [AD 2000-01-10](https://openairdocs.org/ad/2000-01-10): Elevator and Rudder Trim Tab Pivot Arms · Pilatus PC-7. Effective Mar 3, 2000 - [AD 98-16-16](https://openairdocs.org/ad/98-16-16): Main Lainding Gear And Nose Landing Gear Leg Seal Unit · Pilatus PC-7. Effective Sep 21, 1998 - [AD 2002-01-09](https://openairdocs.org/ad/2002-01-09) (historical): Gasket Material and Relief Valve Attachment Screws · Pilatus PC-12, PC-12/45 and PC-7. Effective Feb 28, 2002 - [AD 98-08-22](https://openairdocs.org/ad/98-08-22) (historical): Elevator and Rudder Attachment Brackets · Pilatus PC-7. Effective May 31, 1998 - [AD 98-08-07](https://openairdocs.org/ad/98-08-07) (historical): Elevator and Rudder Trim Tab Pivot Arms · Pilatus PC-7. Effective Apr 28, 1998 ## Registered aircraft by registry model (OpenAirDocs) - [Pilatus PC-7](https://openairdocs.org/model/pilatus-pc-7): 19 aircraft (registry code 7090401) ## STCs approved under this data sheet (54, first 50) - [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 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 SA12406WI](https://openairdocs.org/stc/SA12406WI): Installation of a Garmin AXIS Flight Display System. Garmin International Inc. - [STC SA02738CH](https://openairdocs.org/stc/SA02738CH): Installation of L-3 Communications Avionics Systems. Acron Aviation Inc. - [STC SA04046CH PAGE 2](https://openairdocs.org/stc/SA04046CH%20PAGE%202): Installation of L-3 GENESIS (TM) Electronic Standby Instrument System (ESI-500/MAG-500). Acron Aviation Inc. - [STC SA02587AK](https://openairdocs.org/stc/SA02587AK): Installation of Electronic Flight Information System (EFIS) and avionics. Genesys Aerosystems 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 SA04264CH](https://openairdocs.org/stc/SA04264CH): Installation of Parker Hannifin Corporation, Aircraft Wheel & Brake Division 199-282 Conversion Kit for main wheels and brakes. Kaman Corporation Aircraft Wheel and Brake LLC - [STC SA02203AK](https://openairdocs.org/stc/SA02203AK): Installation of FlightLogic Synthetic Vision Electronic Flight Information System (EFIS-SV).. Genesys Aerosystems 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 SA00401BO](https://openairdocs.org/stc/SA00401BO): Installation of a SkyTrax100B UAT receiver. Avidyne 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 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 SA02135SE](https://openairdocs.org/stc/SA02135SE): Installation of Electronics International Inc. Glass Panel Engine Monitor (with In-Flight Data). Electronics International Inc. - [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 SA01933LA-D](https://openairdocs.org/stc/SA01933LA-D): Installation of Garmin Model 400W / 500W Series GPS-WAAS Navigation System. Garmin International Inc - [STC SA8323SW](https://openairdocs.org/stc/SA8323SW): Install Pratt & Whitney Canada PT6A-25C engine and Hartzell HC-B3TN-2/T10178(N)-8R propeller.. Sierra Industries Ltd. - [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 2](https://openairdocs.org/stc/SA00352BO%20PAGE%202): 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 2](https://openairdocs.org/stc/SA02119SE%20PAGE%202): 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 SA02442AK PAGE 2](https://openairdocs.org/stc/SA02442AK%20PAGE%202): 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 SA00674WI-D](https://openairdocs.org/stc/SA00674WI-D): Modification of Collins VHF-22A/VHF-22B VHF COMM Receiver Transmitter with CTL-22 Control Pro Line II System Installation to a Collins VHF-22C/VHF-22D VHF COMM Receiver Transmitter with CTL-22C Control 8.33 kHz Pro Line II system installation.. Rockwell Collins 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 SA00681WI-D](https://openairdocs.org/stc/SA00681WI-D): Modification of Collins VHF-20/VHF-20A/VHF-20B VHF COMM Receiver Transmitter with CTL-20 Control Pro Line I System Installation to a Collins VHF-22C/VHF-22D VHF COMM Receiver Transmitter with CTL-22C Control 8.33 kHz Pro Line II System Installation. Rockwell Collins Inc - [STC SA02018SE-D](https://openairdocs.org/stc/SA02018SE-D): Provisions installation of Garmin GPS/XM Antennas in accordance with FAA Approved Model List (AML) SA02018SE-D, dated January 4, 2011, or later FAA approved revision, and FAA Approved GPS/XM Antenna STC Master Drawing List, Document No.: 005-00638-01, Revision 1 , approved on January 4, 2011, or later FAA approved revision.. Garmin International Inc - [STC SA00068SE](https://openairdocs.org/stc/SA00068SE): Installation of fuel flow/pressure instruments. (W/TSIO-360-MB1). Electronics International Inc. - [STC SA02293AK](https://openairdocs.org/stc/SA02293AK): Installation of FlightLogic Synthetic Vision Electronic Flight Information System (EFIS-SV).. Chelton Flight Systems Inc. - [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 SA01306WI-D](https://openairdocs.org/stc/SA01306WI-D): Modification of a Collins ALT-50A or ALT-55B Radio Altimeter system installation to a Collins ALT-1000 or ALT-4000 Radio Altimeter system installation.. Rockwell Collins Inc - [STC SA01695SE](https://openairdocs.org/stc/SA01695SE): Installation of an antenna. Garmin AT Inc. - [STC ST01468CH](https://openairdocs.org/stc/ST01468CH): Installation of various SMR Technologies electrical propeller deicer models.. SMR Technologies - [STC SA01141WI-D](https://openairdocs.org/stc/SA01141WI-D): Modification of a single or dual Collins TDR-94 or TDR-94D Mode S Transponder System installation with CTL-92 control head to a Flight ID capable Collins TDR-94 or TDR-94 Mode S Transponder System installation with CTL-92E control head.. Rockwell Collins Inc - [STC SA01668SE](https://openairdocs.org/stc/SA01668SE): Schroth Pilot and Copilot seat harness installation.. Western Aircraft - [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. - [STC SA8545SW-D](https://openairdocs.org/stc/SA8545SW-D): Installation of a Century Automatic flight system kit no. AK1067, consisting of a Century 41 autopilot/flight director. (when modified by STC SA8323SW, increased shaft horsepower). Century Flight Systems Inc - [STC SA8546SW-D](https://openairdocs.org/stc/SA8546SW-D): Installatio of a Century yaw damper system, kit no. YK1068 consisting of a Century yaw damper per bulletin no. 2133 dtd 3/28/01, and master drawing list no. 87A1292 dtd 3/28/01 (28-volt system) and/or later FAA/DAS approved revision.. Century Flight Systems Inc - [STC SA688NE](https://openairdocs.org/stc/SA688NE): Installation of Safeway Model 6900 deicer boot.. Safeway Products, Inc All 54: https://openairdocs.org/tcds/A50EU/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.