TCDS A57EU

Page No. 1 2 3 4 5 6 7 Rev. No. 16 10 10 10 16 15 15 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A57EU Revision 16 GROB Aircraft SE G 115 G 115A G 115B G 115C G 115C2 G 115D G 115D2 G 115EG July 19, 2021 TYPE CERTIFICATE DATA SHEET NO. A57EU This Data Sheet which is a part of Type Certificate No. A57EU 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 SE Lettenbachstrasse 9 86874 Tussenhausen-Mattsies Germany Type Certificate Ownership Record: Grob Werke GmbH & Co. KG Unternehmensbereich Burkhart Grob Fleugzeugbau transferred TC A57EU to BURKHART GROB Luft- und Raumfahrt GmbH & Co. KG on November, 1989. BURKHART GROB Luft- und Raumfahrt GmbH & Co. KG transferred TC A57EU to GROB Aerospace GmbH on December, 2006. GROB Aerospace GmbH transferred TC A57EU to GROB Aerospace GmbH i.l. on August, 2008. GROB Aerospace GmbH i.l. transferred TC A57EU to GROB Aircraft AG on February, 2009. GROB Aircraft AG transferred TC A57EU to GROB Aircraft SE on September 01, 2017. I. Model G 115 (Normal and Utility Category), approved December 21, 1988. Model G 115A (Normal and Utility Category), approved December 06, 1990. Model G 115B (Normal and Utility Category), approved July 19, 1993. Model G 115C (Utility Category), approved August 13, 1993. Model G 115C (Utility and Acrobatic Category), approved February 8, 1996. Model G 115C2 (Utility Category), approved September 14, 1994 Model G 115D (Utility and Acrobatic Category), approved October 28, 1993 Model G 115D2 (Utility and Acrobatic Category), approved September 14, 1994 Model G 115EG (Acrobatic Category), approved February 6, 2001 Engine Avco Lycoming O-235-H2C (G 115 and G 115A) Avco Lycoming O-320-D1A or -D2A or -D3G (G 115B) Avco Lycoming O-320-D1A (G 115C) Avco Lycoming O-360-A1F6 (G 115C2) Avco Lycoming AEIO-360-B1F (G 115D) Avco Lycoming AEIO-320-D1B (G 115D2) Avco Lycoming AEIO-360-B1B (G 115EG) Fuel AVGAS 100 or 100 LL. Page 2 of 7 A57EU Engine Limits G 115,G 115A(O-235): G 115B,G 115C, G 115D2, (O-320, AEIO-320): Max. power 115 HP (85.8 KW) 160 HP (119.3 KW) Max. permitted RPM 2800 RPM 2700 RPM Max. continuous power 112 HP (83.5 KW) 160 HP (119.3 KW) Max. continuous RPM 2700 RPM 2700 RPM Engine Limits G 115D, G 115C2, G 115EG (O-360, AEIO-360): Max. power 180 HP (134.2 KW) Max. permitted RPM 2700 RPM Max. continuous power 180 HP (134.2 KW) Max. continuous RPM 2700 RPM Propeller and Propeller G 115, G 115A G 115, G 115A G 115B G 115C Limits Hoffmann Sensenich Sensenich Sensenich HO 14-175 120 72 CKS6-2-53 74 DM6S5-2-64 74 DM7S14-2-64 or HO 14 HM -175 120 Diameter max. 5.74 ft (1.75 m) 5.84 ft (1.78 m) 6.00 ft (1.83 m) 6.00 ft (1.83 m) Pitch at 0.75 R 3.94 ft (1.20 m) 4.43 ft (1.35 m) 5.35 ft (1.63 m) 5.35 ft (1.63 m) Propeller RPM Limits 2900 2800 2800 2800 Static RPM Limits 2400 2350 2250 2250 Propeller and Propeller Limits G 115C2 G 115D G 115D2 G 115EG Hartzell Hoffmann Hoffmann MT-Propeller HC-F2YR-1F/F7666A-3R HO-V 343 K()-V/180 FP HO23CHM-() 188 156 MTV-12-B-C/C- 183-17e Diameter max. 6.09 ft (1.86 m) 5.90 ft (1.80 m) 6.17 ft (1.88 m) 6.004 ft (1.83 m) Pitch at .75 R 13° ± 0.2° 4.43 ft (1.35 m) 5.12 ft (1.56 m) 5.36 ft (1.635 m) Propeller RPM Limits 2900 2700 2700 2800 Static RPM Limits 2600 2550 2200 2600 Airspeed Limits G 115, G 115A G 115B G 115C, G 115C2 G 115C* G 115D G 115D2 VNE (never exceed) 164 kts (303 km/h) 159 kts (295 km/h) 184 kts (341 km/h) 184 kts (341 km/h) 166 kts (308 km/h) VNO (normal operating) 135 kts (250 km/h) 129 kts (240 km/h) 134 kts (248 km/h) 134 kts (248 km/h) 134 kts (248 km/h) VA (maneuvering) normal aircraft 95 kts (176 km/h) 100 kts (186 km/h) utility aircraft 99 kts (184 km/h) 104 kts (192 km/h) 114 kts (212 km/h) 114 kts (212 km/h) 114 kts (212 km/h) acrobatic aircraft 128 kts (237 km/h) 128 kts (237 km/h) VFE (flaps extended) 94 kts (175 km/h) 94 kts (175 km/h) 112 kts (208 km/h) 112 kts (208 km/h) 112 kts (208 km/h) * G 115C only if used for limited acrobatics according to Service Bulletin 1078-55. Airspeed Limits G115EG VNE (never exceed) 184 kts (341 km/h) VNO (normal operating) 150 kts (278 km/h) VA (maneuvering) acrobatic aircraft 130 kts (241 km/h) VFE (flaps extended) 112 kts (208 km/h) Page 3 of 7 A57EU C.G. Range. G 115, G 115A G 115B G 115C, G 115C2 G 115C*, G 115D, Most Forward C.G. (Between the given values linear change) G 115D2 Normal aircraft 8.70 in (221 mm) 10.04 in (255 mm) aft of datum at aft of datum at 1874.0 lbs (850 kg) 2028.2 lbs (920 kg) 7.83 in (199 mm) 7.83 in (199 mm) aft of datum at aft of datum at 1818.8 lbs (825 kg) 1851.4 lbs (840 kg) or less or less Utility aircraft 7.83 in (199 mm) 10.04 in (255 mm) 8.94 in (227 mm) 8.94 in (227 mm) aft of datum aft of datum aft of datum at aft of datum at at 1873.9 lbs (850 kg) 2182 lbs (990 kg) 2182 lbs (990 kg) 7.83 in (199 mm) 7.76 in (197 mm) 7.76 in (197 mm) aft of datum at aft of datum at aft of datum at 1763.7 lbs (800 kg) 1653 lbs (750 kg) 1653 lbs (750 kg) or less Acrobatic aircraft 8.62 in (219 mm) aft of datum at 2028 lbs (920 kg) 7.76 in (197 mm) aft of datum at 1653 lbs (750 kg) C.G. Range. G 115EG Most Forward C.G. (Between the given values linear change) Acrobatic aircraft 8.46 in (215 mm) aft of datum at 2183.0 lbs (990 kg) 7.76 in (197 mm) aft of datum at 1653 lbs (750 kg) or less Most rearward C.G. G 115, G 115A G 115B G 115C, G 115C2 G 115C*, G 115D, G 115D2 Normal aircraft 11.72 in (298 mm) 11.72 in (298 mm) aft of datum aft of datum Utility aircraft 11.72 in (298 mm) 11.72 in (298 mm) 11.72 in (298 mm) 11.72 in (298 mm) aft of datum aft of datum aft of datum at aft of datum at 2182 lbs (990 kg) 2182 lbs (990 kg) 11.34 in (288 mm) 11.34 in (288 mm) aft of datum at aft of datum at 1653 lbs (750 kg) 1653 lbs (750 kg) Acrobatic aircraft 11.61 in (295 mm) aft of datum at 2028 lbs (920 kg) 11.34 in (288 mm) aft of datum at 1653 lbs (750 kg) Page 4 of 7 A57EU Most rearward C.G.: G 115EG Acrobatic aircraft 11.73 in (298 mm) aft of datum at 2183 lbs (990 kg) 11.48 in (292 mm) aft of datum at 1653 lbs (750 kg) Empty Weight C.G. See Flight Manual (weight and balance, Section 6) Datum Wing leading edge Leveling Means Canopy sill Maximum Weight G 115,G 115A G 115B G 115C, G 115C2 G 115C*, G 115D, G 115D2 G 115EG Normal aircraft 1873.9 lbs (850 kg) 2028.2 lbs (920 kg) Utility aircraft 1763.7 lbs (800 kg) 1873.9 lbs (850 kg) 2182.6 lbs (990 kg) 2182.6 lbs (990 kg) Acrobatic aircraft 2028.2 lbs (920 kg) 2183 lbs (990 kg) Minimum Crew 1 pilot Number of Seats 2 (side by side) 9.84 in (250 mm) aft of datum Maximum Baggage 44.1 lbs (20 kg) 35.43 in (900 mm) aft of datum (for G115, G115A, G115B) 121 lbs (55 kg) 38.98 in (990 mm) aft of datum (for G115C, G115C2, G115D, G115D2, G115EG) Fuel Capacity G 115,G 115A: G 115B: G 115C, G 115C2, G 115D, G 115D2, G 115EG: Total Contents 26.42 U.S. gal (100 l) 29.59 U.S. gal (112 l) 39.63 U.S. gal (150 l) 35.04 in (890 mm) 35.04 in (890 mm) 13.19 in (335 mm) aft of datum aft of datum aft of datum Usable 24.23 U.S. gal (91.7 l) 28.27 U.S. gal (107 l) 37.77 U.S. gal (143 l) Oil Capacity G 115, G 115A: G 115B: G 115C, G 115C2, G 115D, G 115D2, G 115EG: G 115EG: 6 quarts (5.7 l) 8 quarts (7.6 l) 8 quarts (7.6 l) 8 quarts (7.6 l) 52.36 in (1330 mm) 52.36 in (1330 mm) 52.36 in (1330 mm) 50.79 in (1290 mm) fwd of datum fwd of datum fwd of datum fwd of datum Page 5 of 7 A57EU Control Surface Movements G 115 G 115A G 115B G 115C, G 115C2 G 115D, G 115D2 G 115EG (in) (mm) (in) (mm) (in) (mm) (in) (mm) (in) (mm) Flaps UP 0 0 0 0 0 0 0 0 0 0 DOWN 6.97± 0.35 177± 9 6.97±0.35 177±9 6.97±0.35 177±9 9.96+0. 2 -0.39 253 +5 -10 10.11 -0.39 257 +0 -10 Aileron UP 2.76±0.28 70±7 2.76±0.28 70±7 2.76±0.20 70±5 2.83±0.12 72±3 2.99±0.12 76±3 DOWN 1.42±0.28 36±7 1.42±0.28 36±7 2.36±0.20 60±5 2.56±0.12 65±3 2.79±0.12 71±3 Aileron servo only S/N UP (aileron on stop) 3.54±0.12 90±3 if installed, same movements as G 115 8008 through 8031 DOWN (aileron on stop) 1.54±0.12 39±3 Elevator UP 3.46±0.28 88±7 3.46±0.28 88±7 3.46±0.28 88±7 6.69±0.20 170±5 7.0±0.20 178±5 DOWN 2.80±0.28 71±7 2.52±0.20 64±5 2.52±0.20 64±5 3.94±0.20 100±5 4.13±0.20 105±5 Trim tab UP 1.14±0.08 29±2 1.14±0.08 29±2 1.14±0.08 29±2 1.69±0.12 43±3 0.6±0.08 15±2 (elevator neutral) DOWN 2.01±0.08 51±2 2.01±0.08 51±2 2.01±0.08 51±2 2.36±0.12 60±3 2.36±0.12 65±3 Rudder up to S/N 8065 LH 11.42±0.79 290±20 11.42±0.39 290±10 11.42±0.39 290±10 10.28±0.20 261±5 10.83 +0 -0.39 275±10 RH 11.42±0.79 290±20 11.42±0.39 290±10 11.42±0.39 290±10 10.28±0.20 261±5 as of S/N 8066 and for LH 11.06±0.75 281±19 replacement RH 11.06±0.75 281±19 Serial Nos. Eligible Model G 115 Serial No. 8008 through 8088 Model G 115A Serial No. 8090 through 8109 Serial No. 8008 through 8109 must be modified according to GROB Service Bulletin TM 1078-5 "Special equipment of GROB G 115 for the export to the USA". Model G 115B is formed by modification of Serial No. 8008 through 8088 and 8090 through 8109 according to GROB Service Bulletin TM 1078-27/2 "Modification of the G 115/G 115A to the G 115B standard". Model G 115C as of Serial No. 82001/C. Model G 115C2 as of Serial No. 82015/C2. Model G 115D as of Serial No. 82003/D. Model G 115D2 as of Serial No.82002/D2. Model G 115EG as of Serial No. 82200. Import Requirements The FAA can issue a U.S. Standard Airworthiness Certificate based on an Export Certificate of Airworthiness (Export C of A) signed by a representative of the German civil airworthiness authority, the Luftfahrt Bundesamt (LBA), 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 Part 23 approved under U.S. Type Certificate No. A57EU 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 1) 14 CFR Sections 21.29, 21.183(c) and 14 CFR 23, effective February 1, 1965, including Amendments 23-1 through 23-32, and 2) 14 CFR Section 36, effective November 18, 1969, including Amendments 36-1 through amendment in effect at the time of U.S. Type Certification, and Page 6 of 7 A57EU Certification Basis, continued 3) Special Conditions; GROB Model G 115 - Series Airplanes, published in Federal Register 53FR39448, and 4) Section 611(b) of the FAA Act of 1958 The LBA originally type certificated this aircraft under its Type Certificate No. 1078. The FAA validated this product under U.S. Type Certificate No. A57EU. Effective September 28, 2003, the European Aviation Safety Agency (EASA) began oversight of this product on behalf of Germany. The EASA type certificate for the G115 series models is EASA.A.364. Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the airplane for certification. Service Information Service bulletins, aircraft flight manuals, maintenance and overhaul manuals, structural repair manuals, and vendor manuals which contain a statement that the document is approved by the EASA, are accepted by the FAA and are considered FAA approved. (These approvals pertain to the design data only.) NOTES Note 1. Current weight and balance data together with a list of equipment included in the certificated empty weight, and loading instructions, when necessary, must be provided for each powered aircraft at the time of original certification. The certificated empty weight and corresponding center of gravity locations must include the following: a) unusable fuel of 13.18 lbs (G 115, G 115A), 7.94 lbs (G 115B) at 35.04 in aft of datum, 11.10 lbs (G 115C, G 115C2, G115D, G 115D2, G 115EG) at 13.19 in aft of datum. b) engine oil of 11.18 lbs (G 115, G 115A) respectively 14.91 lbs (G 115B, G 115C, G 115C2, G 115D, G 115D2) at 52.36 in and 50.79 in (G 115EG) fwd of datum. Note 2. The placards listed in Section 2 of the LBA-approved Airplane Flight Manual GROB G 115, G 115B, G 115C, G 115C2, G 115D, G 115D2, G 115EG must be displayed. See Note 9. Note 3. Service Life Limited components airframe: 12,000 flight hours for G 115, G 115A, G 115B, G 115C, G 115C2; extended to 22,900 flight hours if inspected in accordance with AMM chapter 05-41 (see also Service Bulletin MSB1078-161) 4,000 flight hours for the G 115D, G 115D2 and for the G 115C if certified for limited acrobatics in accordance with Service Bulletin 1078-55. This Service Life Limit can be extended to 12,000 flight hours, if an inspection in accordance with Service Bulletin OSB1078-105 is performed before reaching 4,000 flight hours. Every 3000 flight hours for the G 115, G 115A, G 115B, G 115C, G 115C2 a scheduled inspection must be performed in accordance with the Maintenance Manual. After 2,000, 6,000, 8,000 and 10,000 flight hours for the G 115D, G 115D2 and for the G 115C if certified for limited acrobatics in accordance with Service Bulletin 1078-55, a scheduled inspection must be performed in accordance with the Maintenance Manual, including a fuel tank pressure test after 8,000 flight hours. 24,000 flight hours for G 115EG. Note 4. Changes to the factory delivered paint schemes have to be coordinated with the TC Holder or the FAA's Certificate Management Office responsible for this type certificate. Note 5. Major structural repairs must be accomplished by a properly certificated mechanic in accordance with data approved by the FAA. Note 6. All G 115 models are approved for VFR day and night. G 115C, G 115C2, G 115D and G 115D2 models are approved for IFR when equipped with Service Bulletin 1078-50 and the associated Airplane Flight Manual Supplement as shown in Service Bulletin 1078-50 or later (LBA) approved AFM Supplement Revision. Page 7 of 7 A57EU Note 7. Only G 115, G 115A, G 115B: Normal Category: Acrobatic maneuvers inclusive spins are not approved. Utility Category: Spins with equipment according to Service Bulletin TM 1078-9/2 and with flap setting 0° are approved. Spins without wheel fairings are not approved. Control Surface Movements (restricted): (in) (mm) Elevator Down 2.52±0.20 64 ±5 Rudder LH 11.42±0.39 290±10 RH 11.42±0.39 290±10 Note 8. Airplanes of the model G 115C may be operated in the acrobatic category for limited acrobatics after embodiment of Service Bulletin 1078-55. The equipment required by Service Bulletin 1078-55 may be installed already complete or partly by the manufacturer. So modified airplanes are marked with the suffix “/C1” to the S/N and the sales designation is “G 115C1 ACRO”. The G 115C must be operated in the acrobatic category according to Supplement 2 to the Airplane Flight Manual G 115C, LBA approved. Note 9. In addition to all other requirements of this type certificate data sheet, G 115EG airplanes must additionally have the following instruments marked in US units: 1) EGT and OAT indicator in degrees centigrade (or Fahrenheit). 2) Manifold pressure in inches of mercury pressure, fuel flow indicator in gallons. 3) Fuel quantity in gallons. 4) Oil temperature and pressure in degrees centigrade (or Fahrenheit) and in pounds per square inch, (psi). 5) Fuel pressure and cylinder head temperature, in psi and degrees centigrade (or Fahrenheit). The following placards must be shown in US units: 1) Limitations must be in US units, weight in pounds. 2) Fuel Filler Cap, gallons. 3) Fuel Tank Selector, consistent with fuel quantity indicator. 4) Fuel Flow, gallons per hour. 5) Manifold Pressure, inches of mercury Procedures and methods for accomplishing this remarking should be obtained from the manufacturer. - END -