TCDS A00067CE

Page No. 1 2 3 4 5 Rev. No. 3 2 3 2 2 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A00067CE Revision 3 GROB Aircraft SE G 120TP-A July 19, 2021 TYPE CERTIFICATE DATA SHEET NO. A00067CE This Data Sheet which is a part of Type Certificate No. A00067CE 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 Holder Record: GROB Aircraft AG transferred TC A00067CE to GROB Aircraft SE on September 01, 2017. I. Model G 120TP-A (Utility and Aerobatic Category), approved November 04, 2015 Engine One Rolls Royce Corporation 250-B17F, TCDS E10CE Fuel ASTMD-1655: JET A, JET A-1 MIL-DTL-83133: JP-8 MIL-DTL-5624: JP-5 UK Defence Standard 91-91: Semi- and Fully Synthetic GOST 10277-86: Grades TS-1 and RT STAS 5639-88: Grade TH GSTU 320.00149943.007-97: Grade RT (Ukraine) GSTU 320.00149943.011-99: Grade TS-1(Ukraine) GB 6537-94 and -2006: Grade No. 3 See Airplane Flight Manual for required fuel system icing inhibitor additive. Engine Limits Maximum take-off power 450 shp (335.6 kW) @ 2030 rpm Maximum transient RPM 2233 rpm Maximum continuous power 380 shp (283.4 kW) Maximum continuous RPM 2132 rpm Propeller MT-Propeller Entwicklung GmbH MTV-5-1-D-C-F-R(A) hub CFR210-56 blade Propeller Limits Maximum Diameter 82.68 in (2.10 m) Propeller Maximum RPM Limit 2233 rpm Low Pitch 8º ± 0.2º High Pich 79º ± 1º Pitch Radius at 31.1 in (790 mm) Airspeed Limits VMO (maximum operating speed) 235 KCAS (238 KIAS) (SL to 13000 ft) MMO (maximum operating Mach number) 0.45 (13000 ft to 25000 ft) VO (maneuvering speed) Utility Category 142 KCAS (143 KIAS) Aerobatic Category 162 KCAS (164 KIAS) Page 2 of 5 A00067CE Airspeed Limits, continued VFE-TO (flaps extended speed, takeoff) 150 KCAS (151 KIAS) VFE (flaps extended speed, full flaps) 113 KCAS (114 KIAS) VLE (maximum speed landing gear extended) 180 KCAS (182 KIAS) VLOE (maximum speed landing gear extension) 180 KCAS (182 KIAS) VLOR (maximum speed landing gear retraction) 135 KCAS (137 KIAS) C.G. Range Utility Category Forward Limits: 105.4 in (2676 mm) (25% MAC) aft of datum for 3340 lbs (1515 kg) Aft Limits: 107.6 in (2732 mm) (29% MAC) aft of datum to 108.9 in (2766 mm) (31.5 MAC) aft of datum for 2579 lbs (1170 kg) to 3020 lbs (1370 kg) 108.9 in (2766 mm) (31.5% MAC) aft of datum for 3020 lbs (1370 kg) to 3340 lbs (1515 kg) If equipped per Note 6: Forward Limits: 105.4 in (2676 mm) (25% MAC) aft of datum for 2579 lbs (1170 kg) to 3417 lbs (1550 kg) 105.4 in (2676 mm) (25% MAC) aft of datum to 105.6 in (2683 mm) (25.5% MAC) aft of datum for 3417 lbs (1550 kg) to 3582 lbs (1625 kg) Aft Limits: 107.6 in (2732 mm) (29% MAC) aft of datum to 108.9 in (2766 mm) (31.5% MAC) aft of datum for 2579 lbs (1170 kg) to 3020 lbs (1370 kg) 108.9 in (2766 mm) (31.5% MAC) aft of datum for 3020 lbs (1370 kg to 3340 lbs (1515 kg) 108.9 in (2766 mm) (31.5% MAC) aft of datum to 108.6 in (2759 mm) (31.0% MAC) aft of datum for 3340 lbs (1515 kg) to 3582 lbs (1625 kg) Aerobatic Category Forward Limits: 105.4 in (2676 mm) (25% MAC) aft of datum for 3175 lbs (1440 kg) Aft Limits: 107.6 in (2732 mm) (29% MAC) aft of datum for 3175 lbs (1440 kg) Straight-line variation between points Empty Weight C.G. Range See Airplane Flight Manual (weight and balance, Section 6) Reference Datum 91.9 in (2.335 m) in front of wing leading edge at 45.3 in (1.150 m) outside the symmetry axis Leveling Means Canopy frame bottom edge Maximum Weight Utility Category 3340 lbs (1515 kg) 3582 lbs (1625 kg), see Note 6 Aerobatic Category 3175 lbs (1440 kg) Page 3 of 5 A00067CE 3340 lbs (1515 kg), see Note 6 Minimum Crew 1 Pilot, on right seat Number of Seats 2 Seats Maximum Baggage 110 lbs (50 kg) 150.4 in (3820 mm) aft of datum Fuel Capacity 92.7 U.S. gallons (351 liters) total 105.4 in (2676 mm) aft of datum 90.2 U.S. gallons usable (341.4 liters) (see AFM page 2-10.) 47.6 U.S. gallons (180.2 liters) left wing tank 105.9 in (2690 mm) aft of datum 45.1 U.S. gallons (170.6 liters) right wing tank 104.8 in (2662 mm) aft of datum Add unusable fuel to empty weight of airplane. Oil Capacity 11.6 U.S. quarts (11.0 liters) 59.8 in (1519 mm) aft of datum Maximum Operating Altitude Utility Category 25000 ft Aerobatic Category 20000 ft Control Surface Movements (inches from neutral) Aileron UP 4.02 + 0.16 / - 0.24 DOWN 4.02 + 0.16 / - 0.24 Elevator UP 4.09 ± 0.20 DOWN 3.78 ± 0.20 Trim tab UP 0.47 ± 0.08 (elevator neutral) DOWN 0.79 ± 0.08 Rudder LH 10.35 ± 0.39 RH 10.35 ± 0.39 Flaps UP 0 DOWN 12.09 + 0.20/ - 0.39 Serial Numbers Eligible Serial number 11082 and on. Import Requirements The FAA can issue a U.S. 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. A00067CE 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 Type certification under 14 CFR Section 21.29 including the following requirements: - 14 CFR 23, effective February 01, 1965, including Amendments 23-1 through 23-61 - 14 CFR Section 34, effective September 10, 1990, including Amendment 34-1 through Amendment 34-5A - 14 CFR Section 36, effective December 01, 1969, including Amendments 36-1 through Amendment 36-29 Page 4 of 5 A00067CE Equivalent Level of Safety (ELOS) findings per the provisions of 14 CFR Part 21.21(b)(1) as follows: - ELOS ACE-15-13: 14 CFR §23.777 (g), Location of Landing Gear Control Lever; Refer to FAA letter dated August 18, 2015 Certification Basis, continued Compliance with optional ditching provisions has not been established. Compliance not shown for 14 CFR Part 23.1419: not approved for flight in known icing operations. Type Certificate No. A00067CE issued November 04, 2015 Date of application April 25, 2014 Approved for Day, Night, VFR, IFR The EASA originally type certificated this aircraft under its Type Certificate No. EASA.A.565. The FAA validated this product under U.S. Type Certificate No. A00067CE. Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the airplane for certification. In addition, the following items of equipment are required: - Airplane Flight Manual GROB G 120TP-A, Doc. No. 1T-120TPA-1, Issue 1, Revision 7, or later approved revision. - If equipped in accordance with option OÄM 565-17: Airplane Flight Manual GROB G 120TP-A, Doc. No. 1T-120TPAD-1, Issue 1, Revision 2 or later approved revision. See Note 5 for options and modifications approved as of the date of original type certification, November 04, 2015. 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 17.0 lbs (2.6 U.S. gallons) at 106.9 in (2716 mm) aft of datum b) engine oil of 19.8 lbs (9.5 U.S. quarts) at 59.8 in (1519 mm) aft of datum Note 2. The placards listed in Section 2 of the EASA-approved Airplane Flight Manual 1T-120TPA-1 or 1T- 120TPAD-1 (if equipped in accordance with option OÄM 565-17) must be displayed. Note 3. FAA approved Airworthiness Limitations for inspection time limits and maintenance checks are included in Chapter 4 of the Aircraft Maintenance Manual (AMM) Document No. Doc.-No. 1T-120TPA-2, latest FAA approved revision. Service Life Limited components airframe: 15,000 flight hours for G 120TP-A 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. Page 5 of 5 A00067CE NOTES, continued Note 5. Approved Options and Modifications as of date of original type certification: Option Number Description Comment OÄM 565-01 Air Condition System Initial TC OÄM 565-02 Electric Rudder Trim OÄM 565-03 Electric Aileron Trim OÄM 565-04 Becker ADF OÄM 565-05 Flight Data Recording Unit OÄM 565-06 UHF KFS599A OÄM 565-07 Oxygen System OÄM 565-08 Duplicated Instruments, Panel Arrangement B OÄM 565-09 Additional LH Power Lever OÄM 565-14 Reduced Power Major Change OÄM 565-17 Digital Cockpit Baseline Major Change: Identified as “Digital Cockpit” OÄM 565-18 Additional two Displays combined with OÄM 565-17 OÄM 565-19 Becker ADF combined with OÄM 565-17 OÄM 565-20 UHF combined with OÄM 565-17 OÄM 565-21 Avidyne TAS combined with OÄM 565-17 OÄM 565-22 Flight Data Recorder combined with OÄM 565-17 OÄM 565-24 Radar Altimeter combined with OÄM 565-17 OÄM 565-25 Cowling with Doors Minor Change OÄM 565-26 Oxygen Indication combined with Digital Cockpit Minor Change OÄM 565-27 Rudder trim indication combined with Digital Cockpit Minor Change OÄM 565-28 Aileron trim indication combined with Digital Cockpit Minor Change OÄM 565-29 S-Tec elevator trim servo Minor Change OÄM 565-30 Increased Maximum Empty Weight Major Change OÄM 565-31 Sandel device SN3500 add MOD A and software version A4.06 Minor Change OÄM 565-32 Optional Stormscope L3 WX-500 combined with Digital Cockpit Minor Change OÄM 565-34 Optional Turn & Slip Indicator Mid Conti for analogue cockpit Minor Change Note 6. If equipped with option OCN 565-74 or OSB 565-094, ‘Maximum Mass Increase’. …..END…..