# TCDS G50EU: Valentin GmbH & Co. - Type: Type certificate data sheet - Status: Current - Holder: Valentin GmbH & Co. - Revision: 3 - Revised: May 23, 2002 - Product: Aircraft, Glider - Certification basis: Part 21, Part 23 - Registered aircraft: 20, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/74/89/748964b5387304118d9c2bf14e8c5db560f0669d1145f9027efbfe5aaa3c382f - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/5D016C2A388B630B86256BCE006F61A4.0001 - Page: https://openairdocs.org/tcds/G50EU ## Models (1) As the data sheet lists them. - Taifun 17E ## What the data sheet says From the PDF's text layer, line by line; tables lose their columns. The PDF is the record. ```text P a g e N o .1234 R e v . N o .2121 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION G50EU VALENTIN GmbH VALENTIN 17E Revision 3 May 23, 2002 TYPE CERTIFICATE DATA SHEET NO. G50EU This data sheet which is a part of Type Certificate No. G50EU 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 VALENTIN GmbH & Co. Flugzeugbau KG Postfach 26 D-8728 Hassfurt Federal Republic of Germany I. VALENTIN Model TAIFUN 17E (Utility Category), approved March 26, 1985 Engine Limbach L 2000 EB 1.B or L 2400 EB 1.B Fuel Aviation gasoline 100 LL or minimum ROZ 96 octane. Engine Limits For all operations 3400 RPM (79 hp) for Limbach L 2000 3200 RPM (87 hp) for Limbach L 2400 Propeller Hoffman HO - V 62 R/L 160 T or HO - V 62 R/L 160 BT Diameter range 65" maximum 61" minimum (No further reduction permitted) Blade angle settings - 3 fixed positions: start, cruise, feather. Spinner: Hoffman VP 30-82 Airspeed limits (I.A.S.) Maximum Airspeeds In Calm Air Never Exceed (VNE) (flap setting -8°, 0, +8°) 0 - 6500 ft. alt. 132 kts 152 mph 245 km/h 6501 - 10,000 ft. alt. 126 kts 145 mph 234 km/h 10,001 - 15,000 ft. alt. 117 kts 135 mph 217 km/h 15,001 - 20,000 ft. alt. 107 kts 123 mph 198 km/h Never exceed All Altitudes with airbrakes extended 132 kts 152 mph 245 km/h Flap Extension Speed (VE) 81 kts 93 mph 150 km/h flap setting +15°, +30° In Rough Air (VB) 100 kts 115 mph 185 km/h Maximum Landing Gear Extended Operating Speed (VLE) 65 kts 75 mph 120 km/h C.G. range 17.7 in to 21.3 in (400 mm to 540 mm) G50EU Page 2 of 4 Empty Weight C.G. See Glider Flight Manual, pages 20-21 and Instructions for Continued Airworthiness, page 34. Datum Wing leading edge at wing root rib. Leveling Means Level on top surface of fuselage in front of the vertical stabilizer, according to the procedure in Instructions for Continued Airworthiness. Maximum weight 1,804 lbs (820 kg) Minimum Crew One pilot No. of seats Two, 14.75 in (370 mm) aft of datum. Maximum Baggage 55 lbs (25 kg), 34.65 ins (880 mm) aft of datum. Fuel Capacity 23.8 USgals. (90 l), 12.99 in (330 mm) aft of datum. Oil Capacity 0.66 USgals (2.5 l) total Control surface movements Aileron: Up 2.84 + 0.28 in (72 + 7 mm). Down 1.42 + 0.16 in (36 + 4 mm). Measurement radius 6.48 ins (164 mm) on inboard side of the aileron. Elevator: + 4.41 + 0.43 in (112 + 11 mm). Measurement radius 8.46 in (215 mm) on center of stabilizer. Rudder: + 8.58 in + 0.2/-0.59 in (218 mm + 5 mm/ 15 mm). Measurement radius 16.4 in (420 mm) on bottom of the rudder. Flap: Up 0.83 + 0.12 in (21 + 3 mm). Down 3.39 + 0.35 in (86 + 9 mm). Measurement radius 6.46 in (164 mm) on outboard side of the flap. Trim: Up 1.02 + 0.12 in (26 + 3 mm). Down 1.65 + 0.2 in (42 + 5 mm). Measurement radius 4.0 in (100 mm) on inboard of the trim tab. All measured from hinge line. (See also Valentin TAIFUN 17 E Instructions for Continued Airworthiness). Serial Nos. Eligible See Import Requirements Certification Basis FAR 21.23, 21.29 and 21.50 effective February 1, 1965 including Amendments 21-1 through 21-49. Compliance with FAR 21.23 through Amendment 21-49 has been shown utilizing the provisions of Advisory Circular 21.23-1 dated 12 January 1981, Section 5, paragraph a. The airworthiness requirements met under this provision are the Joint Airworthiness Requirements for Sailplanes and Powered Sailplanes (JAR-22) dated 1 April 1980 including Amendment 1, and Section 5, paragraph (e)(6) of Advisory Circular 21.23-1 dated 12 January 1981. FAR 23.479, 23.481, 23.483, 23.485, 23.493, 23.499, 23.723 and 23.725 effective 1 February 1965 including amendments 23-1 through 23-23. Type Certificate No. G50EU, issued March 26, 1985. Date of application for Type Certificate: 6 December 1979. Page 3 of 4 G50EU Certification Basis (Cont'd) The applicable airworthiness requirements for U.S. certification under FAR 21.29 identified above were established considering the airworthiness requirements applied by the exporting country under the provisions of paragraphs 4 and 9(h)(ii) of the agreement between the United States of America and the Federal Republic of Germany, dated 31 May 1974 titled Certificates of Airworthiness for Imported Aeronautical Products and Components. Import Requirement To be considered eligible for operation in the United States, each aircraft manufactured under this type certificate must be accompanied by a certificate of airworthiness for export or certifying statement endorsed by the exporting foreign civil airworthiness authority which states (in the English language): This aircraft conforms to its U.S. type design (Type Certificate No. G50EU) and is in a condition for safe operation. The U.S. airworthiness certification basis for aircraft type certificated under FAR Section 21.29 and exported by the country of manufacture is FAR Sections 21.183(c) or 21.185(c). The U.S. airworthiness certification basis for aircraft type certificated under FAR Section 21.29 exported from countries other than the country of manufacture (e.g., third party country) is FAR Sections 21.183(d) or 21.183(b). VALENTIN TAIFUN 17E, Serial Numbers 1005, 1012, 1025, 1026, 1030, 1031, 1033, 1034, 1038, 1039, 1040, 1043, 1044, 1046, 1051 ,1054 and 1056 are eligible for U.S. Standard Airworthiness Certification when: 1) The FAA inspector is provided with the original Export Certificate of Airworthiness issued by the LBA which certifies that the glider conforms to the U.S. type certificate and, 2) The glider has been modified in accordance with the LBA-approved VALENTIN Technical Information TM6/818 and, 3) The glider is found to be in condition for safe operation by the FAA inspector. Modification pre-dating the issuance of this Type Certificate and not included in paragraph 1 and 2 of this note and modifications dated after the issuance of this Type Certificate not covered by the note contained in the Service Information paragraph of this Type Certificate must be assumed not to be approved under this Type Certificate. Equipment The equipment approved for the VALENTIN TAIFUN 17E is listed in the VALENTIN TAIFUN 17E Master Equipment List dated 27 February 1984. The required equipment for the kinds of approved operations are listed in the LBA- approved VALENTIN TAIFUN 17E Glider Flight Manual, dated 28 November 1983. VALENTIN TAIFUN 17E Glider Flight manual, LBA-approved 28 November 1983. Service Information VALENTIN Technical Information (Service Bulletins), published in the English language for the U.S. Type Design that carry a statement "Approved by the Luftfahrt- Bundesamt (LBA)" may be interpreted as "FAA-Approved." Available documents for VALENTIN TAIFUN 17E: - Flight Manual, LBA-approved 28 November 1983 - Instructions for Continued Airworthiness dated November 1983 G50EU Page 4 of 4 NOTES NOTE 1. Current weight and balance report including list of equipment in certificated empty weight, and loading instructions, when necessary, must be provided for each glider at the time of original certification. The certificated empty weight and corresponding center of gravity locations must include the following: a) unusable fuel of 3 lbs b) undrainable engine oil of 0.2 lbs NOTE 2. The placards listed in Section 13 of the LBA-approved VALENTIN TAIFUN 17E Glider Flight Manual must be displayed. NOTE 3. Section 6 of the VALENTIN TAIFUN 17E Instructions for Continued Airworthiness (LBA- approved 28 November 1983) specifies mandatory replacement times, structural inspection intervals, and related structural procedures. These airworthiness limitations may not be changes without FAA approval. NOTE 4. All external portions of the glider exposed to sunlight must be painted white except for wing tips, nose of fuselage and rudder. NOTE 5. Major structural repairs must be accomplished at FAA certificated repair stations rated for composite aircraft structure work, in accordance with VALENTIN repair methods approved by FAA. ...END... ``` ## ADs (5, in force first) - [AD 2004-20-10](https://openairdocs.org/ad/2004-20-10): Wing and fuselage side root ribs · Valentin Taifun 17E. Effective Nov 24, 2004 - [AD 2001-05-08](https://openairdocs.org/ad/2001-05-08): Central Wing Bolts · Valentin Taifun 17E. Effective Apr 13, 2001 - [AD 88-15-01](https://openairdocs.org/ad/88-15-01): Stall Warning System · Valentin Taifun 17E. Effective Jul 14, 1988 - [AD 87-25-01](https://openairdocs.org/ad/87-25-01): Welded Joints-Axles · Valentin Taifun 17E. Effective Dec 3, 1987 - [AD 87-06-01](https://openairdocs.org/ad/87-06-01): Tailplane Front Mounting · Valentin Taifun 17E. Effective Mar 27, 1987 ## Registered aircraft by registry model (OpenAirDocs) - [Valentin TAIFUN 17E](https://openairdocs.org/model/valentin-taifun-17e): 20 aircraft (registry code 9370100) --- 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.