# TCDS G43EU: GROB Aircraft AG - Type: Type certificate data sheet - Status: Current - Holder: GROB Aircraft AG - Revision: 6 - Revised: May 29, 2015 - Product: Aircraft, Glider - Certification basis: Part 21, Part 23 - Registered aircraft: 42, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/7d/fd/7dfd917ad52c5c90c9a36556296215b542226ca2cf9e50235e732c5b7115aaf3 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DA3A27FF09E592F486257E5A004A3746.0001 - Page: https://openairdocs.org/tcds/G43EU ## Models (2) As the data sheet lists them. - GROB G 109B - GROB G 109 ## 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 Rev. No. 6 6 4 6 6 6 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION G43EU Revision 6 Grob Aircraft AG GROB G 109 GROB G 109B May 29, 2015 TYPE CERTIFICATE DATA SHEET No. G43EU This data sheet, which is part of Type Certificate No. G43EU 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: GROB Aircraft AG Lettenbachstrasse 9 86874 Tussenhausen-Mattsies Germany Type Certificate Holder Record: Grob Aerospace GmbH i.l. transferred TC G43EU to GROB Aircraft AG on February 2009. Grob Aerospace GmbH transferred TC G43EU to Grob Aerospace GmbH i.l. on August 2008. Burkhart Grob Luft – und Raumfahrt GmbH & Co. KG transferred TC G43EU to Grob Aerospace GmbH on December 2006. GROB-WERKE GMBH & Co. KG transferred TC G43EU to Burkhart Grob Luft – und Raumfahrt GmbH & Co. KG on November 1989. I. Model GROB G 109, Self-Launching (Powered) Glider, Utility Category, approved 9 August 1982 Engine. Limbach L 2000 1.A Fuel. Aviation gasoline 100LL or minimum ROZ 96 octane Engine Limits. For all operations 3400 r.p.m. (80 hp) Propeller and Propeller Limits. Hoffman HO-V 62-R/L 160 T Diameter range maximum 65 in minimum 61 in (No further reductions permitted) Blade Angle settings - 3 fixed positions: start, cruise, and feather Spinner: Hoffman VP 30-81 Airspeed Limits (IAS). Maximum Airspeeds in calm air VNE (never exceed) kts mph km/h 0 - 6500 ft 130 149 240 6,501-10,000 ft 122 140 225 10,001-13,000 ft 116 133 214 13,001-16,500 ft 110 126 203 16,501-20,000 ft 104 119 192 With Airbrakes extended 130 149 240 G43EU 2 Airspeed Limits (IAS), cont’d. Vb (in rough air) 100 115 185 VA (maneuvering) 100 115 185 C.G. Range. 15.0 in. to 18.3 in. (380 mm to 465 mm) aft of datum. Empty Weight C.G. See Flight Manual Datum. Wing leading edge at root rib Leveling Means. Level on top surface of fuselage between 20 in. in front of vertical stabilizer, see Flight Manual. Maximum Weight. 1820 lbs (825 kg) Minimum Crew One pilot No. of Seats. Two, (3.6 in. (90 mm) aft of datum). Maximum Baggage. 44 lbs (39 in. aft of datum). Fuel Capacity. Total: 21.1 U.S. gal. (41 in. aft of datum) (See Note 1.) Oil capacity 2.6 qt. total (54 in. forward of datum) Control Surface Movements. Aileron: Up 4.21 ± 0.40 in. (107 ± 10 mm) Measurement radius 9.5 in. (242 mm) on inboard of aileron Down 2.50 +0.20/-0.40 (63 +5/-10 mm) Stabilizer: Up 4.3 ± 0.45 in. (108 ± 12 mm) Measurement radius 11.0 in. (282 mm) on middle of stabilizer Down 3.9 ± 0.40 in. (97 ± 10 mm) Rudder: Left 8.6 ± 0.60 in. (215 ± 15 mm) Measurement radius 16.4 in. (420 mm) on bottom of rudder Right 8.6 ± 0.60 in. (215 ± 15 mm) Trim: Up 1.6 ± 0.20 in. (40 ± 5 mm) Measurement radius 4.0 in. (100 mm) on inboard of trim tab Down 1.2 ± 0.20 in. (31 ± 5 mm) All measured from hinge line. (See GROB G 109 Instructions for Continued Airworthiness). Serial Nos. Eligible. See Import Requirements II. Model GROB G 109B, Self-Launching (Powered) Glider, Utility Category, approved 2 April 1984 (Similar to G 109 except for engine, wing, and cockpit configuration) Engine. GROB 2500 E 1 Fuel. Aviation gasoline 100LL or minimum ROZ 96 octane Engine Limits. For all operations 3400 r.p.m. (80 hp) Propeller and Propeller Limits. Hoffman HO-V 62-R/L 160 BT 3 G43EU Propeller and Propeller Limits, cont’d. Diameter range maximum 63 in minimum 62.5 in (No further reductions permitted) Blade Angle settings - 3 fixed positions: start, cruise, and feather Spinner: Hoffman VP 30-82 Airspeed Limits (IAS). Maximum Airspeeds in calm air VNE (never exceed) kts mph km/h 0- 6500 ft 130 149 240 6,501-10,000 ft 122 140 225 10,001-13,000 ft 116 133 214 13,001-16,500 ft 110 126 203 16,501-20,000 ft 104 119 192 With Airbrakes extended 130 149 240 Vb (in rough air) 92 106 170 VA (maneuvering) 92 106 170 C.G. Range. 11.1 in. to 16.8 in. (232 mm to 427 mm) aft of datum. Empty Weight C.G. See Flight Manual Datum. Wing leading edge at span distance of 4.3 ft 91.3 M) out of oblique wing- fuselage fairing. Leveling Means. Level on edge of door frame. (See flight manual.) Maximum Weight. 1874 lbs (850 kg) Minimum Crew One pilot No. of Seats. Two, 3.3 in. (83 mm) aft of datum. Maximum Baggage. 44 lbs (39 kg) (28.3 in. aft of datum). Fuel Capacity. Total: 26.4 U.S. gal. (39.4 in. aft of datum) (See Note 1.) Oil capacity 3.7 qt. total (58.3 in. forward of datum) Control Surface Movements. Aileron: Up 4.0 ± 0.40 in. (102 ± 10 mm) Measurement radius 9.25 in. (235 mm) on inboard of aileron Down 2.0 ± 0.20 (51 ± 5 mm) Stabilizer: Up 4.4 ± 0.43 in. (112 ± 11 mm) Measurement radius 11.54 in. (293 mm) on middle of stabilizer Down 4.0 ± 0.40 in. (102 ± 10 mm) Rudder: Left 8.3 ± 0.60 in. (210 ± 15 mm) Measurement radius 16.54 in. (420 mm) on bottom of rudder Right 8.3 ± 0.60 in. (210 ± 15 mm) Trim: Up 0.94 ± 0.16 in. (24 ± 4 mm) Measurement radius 2.68 in. (68 mm) on inboard of trim tab Down 0.94 ± 0.16 in. (24 ± 4 mm) All measured from hinge line. (See GROB G 109B Instructions for Continued Airworthiness). G43EU 4 Serial Nos. Eligible. See Import Requirements Data Pertinent to all Models Certification Basis. FAR 21.23, 21.29, and 21.50 effective February 1, 1965, Amendment 21-1 through 21-53. For Model GROB G 109 Compliance with FAR 21.23 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 (JAR22) dated 1 April, 1980, and Section 5, paragraph (e)(6) of Advisory Circular 21.23-1 dated 12 January, 1981. FAR 23.471, 23.473, 23.477, 23.479, 23.481, 23.483, 23.485, 23.493, and 23.497 in effect on 23 June, 1981. Type Certificate No. G43EU issued 9 August, 1982. Date of Application for Type Certificate 23 June, 1981. For Model GROB G 109B Compliance with FAR 21.23 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 (JAR22) dated 1 April, 1980, including Amendments 1 through 2, and Section 5, paragraph (e)(6) of Advisory Circular 21.23-1 dated 12 January, 1981. FAR 23.471, 23.473, 23.477, 23.479, 23.481, 23.483, 23.485, 23.493, and 23.497 in effect on 11 November, 1983. Type Certificate No. G43EU issued 2 April, 1984. Date of Application for Type Certificate 11 November, 1983. For all Models The German Airworthiness Authority, the Luftfahrt -Bundesamt (LBA), originally type certificated glider Models GROB G 109, and GROB G 109B under i ts Type Certi f i cate No. 817. The FAA validated these products under U.S. Type Certi f i cate No. G43EU. Ef f ecti ve September 28, 2003, the European Aviation Safety Agency (EASA) began oversight of these products on behalf of Germany. EA SA rel eased Type Certi f i cate No. EASA.A.249 for these glider models but at this time, EAS A has mai ntai ned the L BA Type Certi f i cate Data Sheet No. 817. Import Requirements. For Model GROB G 109 Model G 109 gliders: Serial numbers 6001 through 6159 are eligible for a U.S. Standard Airworthiness Certificate when: 1) Either: (a) The FAA inspector is provided with the original Export Certificate of Airworthiness issued by a representative of the German Civil Aviation Authority, the LBA, on behalf of the European Community, containing the following statement: “The glider covered by this certificate has been examined, tested, and found to conform to the type design approved under FAA Type Certificate G43EU and is in a condition for safe operation.” Or, (b) The glider has been modified in accordance with the LBA approved GROB Technical Information TM817-5. 5 G43EU Import Requirements, cont’d. 2) The glider is found to be in condition for safe operation by the FAA inspector. 3) All other import requirements for the G 109 of this TCDS are satisfied. Modifications 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 note contained in the Service Information paragraph of this Type Certificate must be assumed not to be approved under this Type Certificate. For Model GROB G 109B Model G 109B gliders: Serial numbers 6200 through 6445, and 6501 through 6579, except 6577 (fatigue test vehicle) are eligible for a U.S. Standard Airworthiness Certificate when: 1) Either: (a) The FAA inspector is provided with the original Export Certificate of Airworthiness issued by a representative of the German Civil Aviation Authority, the LBA on behalf of the European Community, containing the following statement: “The glider covered by this certificate has been examined, tested, and found to conform to the type design approved under FAA Type Certificate G43EU and is in a condition for safe operation.” Or, (b) The glider has been modified in accordance with the LBA approved GROB Technical Information TM817- 14. 2) The glider is found to be in condition for safe operation by the FAA inspector. 3) All other import requirements for the G 109B of this TCDS are satisfied. Modifications 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 note contained in the Service Information paragraph of this Type Certificate must be assumed not to be approved under this Type Certificate. Equipment. For Model GROB G 109 The equipment approved for the GROB G 109 is listed in the GROB G 109 Master Equipment. The Required Equipment for the kinds of Approved Operations are listed in the LBA approved GROB Flight Manual, dated 15 June, 1982. LBA approved GROB G 109 Flight Manual, dated 15 June, 1982, is required. For Model GROB G 109B The equipment approved for the GROB G 109B is listed in the GROB G 109B Master Equipment List dated 21 November, 1983. The Required Equipment for the kinds of Approved Operations are listed in the LBA approved GROB G 109B Flight Manual, LBA approved 1 February, 1984. GROB G 109B Flight Manual, LBA approved 1 February, 1984, is required. Service Information. Each of the documents listed below may state that it is approved by the European Aviation Safety Agency (EASA) or – for approvals made before September 28, 2003 – by the German Airworthiness Authority (LBA). • Service bulletins G43EU 6 Service Information, cont’d. • Structural repair manuals • Vendor manuals • Aircraft flight manuals • Overhaul and maintenance manuals The FAA accepts such documents and considers them FAA-approved for type design data unless one of the following conditions exist: • The documents change the limitations, performance, or procedures of the FAA approved manuals. The FAA uses the post type validation procedures to approve these documents. The FAA may delegate case-by-case approval to EASA on behalf of the FAA for the U.S. type certificate. If this is the case it will be noted on the document. Available Documents for Model GROB G 109: Flight Manual, LBA Approved 15 June, 1982. Instructions for Continued Airworthiness dated 5 April, 1982. Available Documents for Model GROB G 109:B Flight Manual, LBA Approved 1 February, 1983. Instructions for Continued Airworthiness dated 1 October, 1983. NOTES NOTE 1. Current weight and balance data including list of equipment included in the certificated empty weight, and loading instructions, when necessary, must be provided for each glider at the time of original certification, and at all times thereafter. The certificated empty weight and corresponding center of gravity locations must include the following: For Model GROB G 109 a) Unusable fuel of 3 lb. (41 in. aft of datum). b) Undrainable engine oil of o.2 lb. (54 in. forward of datum) For Model GROB G 109B a) Unusable fuel of 3 lb. (34.4 in. aft of datum). b) Undrainable engine oil of o.1 lb. (58.3. forward of datum) NOTE 2. The placards listed in section II of the LBA approved GROB G 109 or GROB G 109B Flight Manual must be displayed. NOTE 3. Section 6 of the GROB G 109/G 109B Instructions for Continued Airworthiness (LBA Approved 15 June, 1982 for Model G 109 and 1 October, 1983, for Model G 109B) specifies mandatory replacement times, structured inspection intervals, and related structural procedures. The Airworthiness Limitations may not be changed without FAA approval. NOTE 4. All external portions of the powered glider exposed to sunlight must be painted white except wing tips, nose of fuselage and rudder. NOTE 5. Removed. .....END..... ``` ## ADs (14, in force first) - [AD 2017-08-12](https://openairdocs.org/ad/2017-08-12): Landing Gear · GROB GROB G 109 and GROB G 109B. Effective May 31, 2017 - [AD 2012-26-09](https://openairdocs.org/ad/2012-26-09): Flight Controls · Burkhart Grob Luft-Und GROB G 109 and GROB G 109B. Effective Feb 13, 2013 - [AD 2012-10-11](https://openairdocs.org/ad/2012-10-11): Stabilizer · Burkhart Grob Luft-Und GROB G 109 and GROB G 109B. Effective Jul 9, 2012 - [AD 98-24-20](https://openairdocs.org/ad/98-24-20): Landing Gear Legs · Burkhart Grob Luft-Und GROB G 109 and GROB G 109B. Effective Jan 9, 1999 - [AD 98-24-09](https://openairdocs.org/ad/98-24-09): Elevator And Trim Tab · Burkhart Grob Luft-Und GROB G 109B. Effective Dec 28, 1998 - [AD 98-23-10](https://openairdocs.org/ad/98-23-10): Engine Mount Frame · Burkhart Grob Luft-Und GROB G 109B. Effective Dec 17, 1998 - [AD 97-15-12](https://openairdocs.org/ad/97-15-12): Damper Unit And Rudder Bell Crank Lever · Burkhart Grob Luft-Und GROB G 109 and GROB G 109B. Effective Sep 19, 1997 - [AD 97-08-06 R1](https://openairdocs.org/ad/97-08-06-R1): Quick Connectors · Alexander Schleicher AS-K 13, AS 12, ASK 21 and 39 more. Effective Aug 1, 1997 - [AD 95-08-13](https://openairdocs.org/ad/95-08-13): Elevator Inner Hinges · Burkhart Grob Luft-Und GROB G 109B. Effective Jun 2, 1995 - [AD 94-17-06](https://openairdocs.org/ad/94-17-06): Airbrake Stops Inspection · Burkhart Grob Luft-Und G 103 C Twin III SL, G103 Twin Astir, G103 Twin II and 8 more. Effective Sep 30, 1994 - [AD 91-12-06](https://openairdocs.org/ad/91-12-06): Rib Stud Plate · Burkhart Grob Luft-Und GROB G 109B. Effective Jul 5, 1991 - [AD 86-15-09](https://openairdocs.org/ad/86-15-09): Placard-Limitation Section · Burkhart Grob Luft-Und GROB G 109B. Effective Jul 31, 1986 - [AD 85-19-07 R1](https://openairdocs.org/ad/85-19-07-R1): Landing Gear Legs · Burkhart Grob Luft-Und GROB G 109 and GROB G 109B. Effective Jan 10, 1986 - [AD 85-19-05](https://openairdocs.org/ad/85-19-05): Placard -Spinning Prohibited · Burkhart Grob Luft-Und GROB G 109 and GROB G 109B. Effective Sep 25, 1985 ## Registered aircraft by registry model (OpenAirDocs) - [Burkhart Grob G-109B](https://openairdocs.org/model/burkhart-grob-g-109b): 25 aircraft (registry code 1660205) - [Burkhart Grob Flugzeugbau G109](https://openairdocs.org/model/burkhart-grob-flugzeugbau-g109): 17 aircraft (registry code 1660204) - [Burkhart Grob G 109](https://openairdocs.org/model/burkhart-grob-g-109): 0 aircraft (registry code 1660199) ## STCs approved under this data sheet (2) - [STC SA00401BO](https://openairdocs.org/stc/SA00401BO): Installation of a SkyTrax100B UAT receiver. Avidyne Corporation - [STC SA593CH](https://openairdocs.org/stc/SA593CH): Install Champion SlickSTART magneto booster system.. Champion Aerospace LLC --- 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.