TCDS TG00004AT

Page No. 1 2 3 4 5 6 7 8 9 10 Rev. No. 6 5 5 4 3 6 3 3 3 5 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TG00004AT Revision 6 Aeromot AMT-100 AMT-200 AMT-300 AMT-200S April 14, 2022 TYPE CERTIFICATE DATA SHEET NO. TG00004AT This data sheet, which is part of Type Certificate No. TG00004AT prescribes conditions and limitations under which the product for which the Type Certificate was issued meets the airworthiness requirements of the Federal Aviation Regulations (FAR). Type Certificate Holder Aeromot-Indústria Mecânico-Metalúrgica Ltda Av. das Indústrias, 1290-Bairro Anchieta Caixa Postal 8031 90200-290-Porto Alegre-RS Brazil 1. Model AMT-100 (Ximango)(Utility Category), Approved December 29, 1993 Engine Limbach Motorenbau Model L2000 E 01 Fuel Aviation gasoline 100/130 LL Lubricating Oil For selection of suitable oil, consult the AFM or AMM Quantity: 0.66 U.S. gal or 2.64 quarts (2.5 liters) Engine Limits Takeoff: Max. Continous Power: 3400 rpm (76.4 hp/57kw), limited to 5 minutes. 3000 rpm (69hp/51kw) Propeller and Propeller Limits Hoffman HO-V62R/L 160 BT Diameter 63.0 in ± 2.0 in (1600 ± 50 mm) Blade angle settings have 3 positions: takeoff, cruise, and feather. C.G. Range +51.5 inches to +52.7 inches (1308 mm to 1340 mm) at 1764 lbs (800 kg). +51.5 inches to +54.0 inches (1308 mm to 1372 mm) at 1499 lbs (680 kg) or less. Straight line variation between given points. See Note 5. Empty Weight C.G. Range None. Maximum Weight 1764 lbs (800 kg) Fuel Capacity 2 Wing tanks, 11.62 U.S. gal. (45 liters) each at +48.8 in (1240 mm) of the reference plane. Oil Capacity 0.66 U.S. gal (2.5 liters) Serial Nos. Eligible 100.001 and up. See note 7. 2. Model AMT-200 (SuperXimango)(Utility Category), approved December 29, 1993. Engine Bombardier-ROTAX GMBH Model 912 A2 Fuel Aviation gasoline 100LL TG00004AT Page 2 Engine Lubricating Oil For selection of suitable oil, consult the AFM and/or Rotax Service Instruction SI-912-016 / SI-914-019, latest edition. Quantity: Maximum: 0.79 U.S. gal or 3.17 quarts (3 liters) Minimum 0.66 U.S. gal or 2.64 quarts (2.5 liters) Maximum per hour: 0.02 U.S. gal or 0.06 quart (0.06 liter) Engine Coolant See Note 9. Engine Limits Max. RPM: Max. Continuous RPM: Max. Takeoff Power: Max. Continous Power: 5800, limited to 3 minutes 5500 79.9 hp (59.6 kW) at 5500 RPM 77.8 hp (58 kW) at 5500 RPM Propeller and Hoffmann HO-V62R/170 FA; Propeller Limits Hoffmann HO-V62R-1/170 FA (installed on Rotax 912 A2 engines s/n 4.380.600 and up) Diameter 67 in (1700 mm) Blade angle settings have 3 positions: takeoff, cruise, and feather. C.G. Range +50.8 inches to +52.2 inches (1290 to 1326 mm) at 1874 lbs (850 kg). +50.8 inches to +54.0 inches (1290 to 1372 mm) at 1499 lbs (680 kg) or less. Straight line variation between given points. Empty Weight C.G. Range None. Maximum Weight 1874 lbs (850 kg) Fuel Capacity 2 Wing tanks, 11.62 U.S. gal. (45 liters) each at +48.8 in (1240mm) of the reference plane. Oil Capacity Max. 0.79 U.S. gallons or 3.17 quarts (3 liters) Serial Nos. Eligible 200.040 and up. See Note 7. 3. Model AMT-300 (Turbo Ximango Shark) (Utility Category), approved July 19, 1999. Engine Bombardier-Rotax GMBH Model 914 F3 Fuel Aviation gasoline 100 LL Engine Lubricating Oil For selection of suitable oil, consult the AFM and/or Rotax Service Instruction SI-912-016 / SI-914-019. Quantity: Maximum: 0.79 U.S. gal or 3.17 quarts (3 liters) Minimum 0.66 U.S. gal or 2.64 quarts (2.5 liters) Maximum per hour: 0.02 U.S. gal or 0.06 quart (0.06 liter) Engine Coolant See Note 9. Engine Limits Max RPM: 5800, limited to 5 minutes Max. Continuous RPM: 5500 Max. Takeoff Power: 113.3 hp (84.5 kW) at 5800 RPM, 38.4 in Hg manifold pressure Max. Continuous Power: 98.5 hp (73.5 kW) at 5500 RPM, 34.0 in Hg manifold pressure Propeller and MT-Propeller Model MTV-21-ACF/CF 165-05 Propeller Limits Diameter 65 in + 0,-5.9 in (1650 mm + 0,-150 mm) Variable pitch, Woodward, McCauley or MT-Propeller governor: Low pitch: 16.5 deg. + 0.2 deg. High pitch: 83.0 deg. + 1.0 deg. C. G. Range +50.8 inches to +52.2 inches (1290 to 1326 mm) at 1874 lbs (850 kg). +50.8 inches to +54.0 inches (1290 to 1372 mm) at 1499 lbs (680 kg) or less. Straight line variation between given points. TG00004AT Page 3 Empty Weight C.G. Range None Maximum Weight 1874 lbs (850kg) Fuel Capacity 2 Wing tanks, 11.62 U.S. gal. (45 liters) each at +48.8 in (1240mm) of the reference plane. Oil Capacity 0.79 U.S. gallons or 3.17 quarts (3 liters) Serial Nos. Eligible 300.106 and up. See Note 7. 4. Model AMT-200S Super Ximango (Utility Category), approved August 25, 2000 Engine Bombardier-Rotax GMBH Model 912 S4, 912 S2* and 912 S3** * Installed on motorglider S/N 200.168 and subsequent. ** Installed on motorglider S/N 200.177 and subsequent of same configuration (AMT- 200S Optional Version) Fuel Aviation gasoline 100 LL in accordance with ASTM D91 0. Lubricating Oil For selection of suitable oil, consult the AFM and/or Rotax Service Instruction SI-912-016 / SI-914-019 latest revision. Quantity: Maximum: 0.79 U.S. gal or 3.17 quarts (3 liters) Minimum 0.66 U.S. gal or 2.64 quarts (2.5 liters) Maximum per hour: 0.02 U.S. gal or 0.06 quart (0.06 liter) Engine Coolant See Note 9 Engine Limits Max RPM: 5800, limited to 5 minutes Max. Continuous RPM: 5500 Max. Takeoff Power: 99 hp (73.5 kW) at 5800 RPM Max. Continuous Power: 93 hp (69.4 kW) at 5500 RPM Propeller and Hoffmann Propeller Rosenhein Propeller Limits Model HO-V62R-1/170 FA* * Installed on motorglider S/N 200.119 and subsequent. Diameter 67 in (1700 mm) Type: two wood blades coated with fiberglass Blade angle settings (3 positions): takeoff, cruise and feather MT-Propeller Entwicklung GmbH & Co. KG Model MTV-21-A-C-F/CF 170-05** ** Installed on motorglider S/N 200.177 and subsequent of same configuration (AMT- 200S Optional Version). Diameter: 67 in (1700 mm) Type: Variable pitch, Woodward, McCauley or MT-Propeller governor. C. G. Range +50.8 inches to +52.2 inches (1290 to 1326 mm) at 1874 lbs (850 kg). +50.8 inches to +54.0 inches (1290 to 1372 mm) at 1499 lbs (680 kg) or less. Straight line variation between given points. Empty Weight C.G. Range None Maximum Weight 1874 lbs (850kg) Fuel Capacity 2 Wing tanks, 11.89 U.S. gal. (45 liters) each at +48.8 in (1240mm) of the reference plane. Oil Capacity 0.79 U.S. gallons or 3.17 quarts (3 liters) Serial Nos. Eligible 200.119 and up. See Note 7. TG00004AT Page 4 DATA PERTINENT TO ALL MODELS Control Surface Movements: Aileron: Up: Down: Neutral Pos. (**) Degrees 15 + 1 15 + 1 3 + 1/3 (AMT-100/200) 0 + 1/3 (AMT-300/200S) In (mm) (*) 2.91 + 0.16 in (74 + 4mm) 2.91 + 0.16 in (74 + 4mm) 0.59 + 0.08 in (15 + 2mm) 0.00 + 0.08 in ( 0 + 2 mm) (*) Measured at 10.83 in (275mm) from the aileron hingeline to the aileron trailing edge at the first aileron rib. (**) Measured down from the aligned position on the wing. Elevator: Up: Down: Degrees 21 + 2 23 + 2 In (mm) 2.72 + 0.24 in (69 + 6mm) 2.99 + 0.24 in (76 + 6mm) Neutral Position: Control surface aligned with the stabilizer profile. Measurement is made at 7.09 in (180mm) from the hinge line. Rudder: Left Right Degrees 28 + 2 28 + 2 In (mm) 7.32 + 0.47 in (186 + 12mm) 7.32 + 0.47 in (186 + 12mm) Neutral Position: Control surface aligned with the vertical fin profile. Measurement is made at 13.78 in (350mm) from the hinge line. Elevator Trim Tab (AMT-100 and AMT-200 only): Down: Up: Degrees 43 + 4 36 + 4 In (mm) 2.80 + 0.20 in (71 + 5mm) 2.17 + 0.20 in (55 + 5mm) Neutral Position: Control surface aligned with elevator profile. Measurement is made at 2.99 in (76mm) from the hinge line. Airspeed Limits (CAS) kts mph km/h VNE (Never exceed) 132 152 245 VB (Rough Air) 97 112 180 VA (Maneuvering) 97 112 180 VLE (Landing gear extended) 81 93 150 VLO (Landing gear operating) 81 93 150 VSB (Speed brakes extended) 132 152 245 Datum Front surface of engine firewall. Leveling Means Wedge of 19.7 x 0.96 in (500 x 24.5 mm) placed on canopy trail (see AFM). Minimum Crew One pilot. No. of Seats Two side-by-side at 41.3 in (1050mm) from datum for AMT-100 S/Ns 100.001 to 100.021 and all AMT-200, AMT-200S and AMT-300, and 38.8 in (985mm) from datum for AMT-100, S/N 100.022 and on. TG00004AT Page 5 Maximum Baggage 11.0 lbs (5kg) at +71.6 in (1.82m) for solo flight. 22.0 lbs (10kg) at 71.6 in (1.82m) for two occupants. Certification Basis Code of Federal Regulations (CFR), 14 CFR 21, Effective February 1, 1965, Amendments 21-1 through 21-68, Sections 21.17, 21.29, and 21.50; For the model AMT-100 and model AMT-200: Joint Airworthiness Requirements for Sailplanes and Powered Sailplanes, JAR-22 Amendment 2, effective September 13, 1982; Plus the following paragraphs of JAR-22, Change 4: 22.1, Applicability, Amdt. 22/85/1, eff. Dec. 12, 1985, 22.175, Demo. of static long. stab. Amdt. 22/85/1, eff. Dec. 12, 1985, 22.395, Control system loads, Amdt. 22/85/1, eff. Dec. 12, 1985, 22.397, Loads-limit pilot forces, Amdt. 22/85/1, eff. Dec. 12, 1985, 22.411, Control sys. stiffness and stretch, Amdt. 22/84/1, eff. Dec. 14, 1984, 22.441, Maneuvering Load, Amdt. 22/86/1, eff. Oct. 22, 1986, 22.443, Gust Loads, Amdt. 22/86/1, eff. Oct. 22, 1986, 22.477, Landing gear arrangement, Amdt. 22/86/1, eff. Oct. 22, 1986, 22.483, One-wheel landing, Amdt. 22/86/1, eff. Oct 22, 1986, 22.591, Rigging/de-rigging loads, Amdt. 22/86/1, eff. Oct. 22, 1986, 22.785, Seats and safety harnesses, Amdt. 22/86/1, eff. Oct. 22, 1986, 22.786, Protection from injury, Amdt. 22/86/1, eff. Oct. 22, 1986, 22.857, Elect. bonding, Amdt. 22/86/1, eff. Oct. 22, 1986, 22.1581, Flt. manual-general, Amdt. 22/86/1, eff. Oct. 22, 1986; Plus the following paragraphs to be incorporated in Change 5: 22.221, Spinning-general, Amdt. 22/90/1, eff. June 30, 1990, 22.779, Motion and effect of cockpit controls, Amdt. 22/90/1, eff. June 30, 1990; For the model AMT-300: Joint Airworthiness Requirements for Sailplanes and Powered Sailplanes, JAR-22 Change 5, effective October 28, 1995; For the model AMT-200S: Joint Airworthiness Requirements for Sailplanes and Powered Sailplanes, JAR-22 Amendment 2, effective September 13, 1982; Plus the following paragraphs of JAR-22, Change 4, effective May 7, 1987: 22.1, Applicability, Amdt. 22/85/1, eff. Dec. 12, 1985, 22.175, Demo. of static long. stab. Amdt. 22/85/1, eff. Dec. 12, 1985, 22.395, Control system loads, Amdt. 22/85/1, eff. Dec. 12, 1985, 22.397, Loads-limit pilot forces, Amdt. 22/85/1, eff. Dec. 12, 1985, 22.411, Control sys. stiffness and stretch, Amdt. 22/84/1, eff. Dec. 14, 1984, 22.441, Maneuvering Load, Amdt. 22/86/1, eff. Oct. 22, 1986, 22.443, Gust Loads, Amdt. 22/86/1, eff. Oct. 22, 1986, 22.477, Landing gear arrangement, Amdt. 22/86/1, eff. Oct. 22, 1986, 22.483, One-wheel landing, Amdt. 22/86/1, eff. Oct 22, 1986, 22.591, Rigging/de-rigging loads, Amdt. 22/86/1, eff. Oct. 22, 1986, 22.785, Seats and safety harnesses, Amdt. 22/86/1, eff. Oct. 22, 1986, 22.786, Protection from injury, Amdt. 22/86/1, eff. Oct. 22, 1986, 22.857, Elect. bonding, Amdt. 22/86/1, eff. Oct. 22, 1986, 22.925, Propeller clearance, Amdt. 22/85/1, eff. Dec. 12, 1985, 22.1529, Maintenance manual, Amdt. 22/84/1, eff. Dec. 14, 1984 22.1581, Flt. manual-general, Amdt. 22/86/1, eff. Oct. 22, 1986; Plus the following paragraphs incorporated in JAR 22 Change 5, effective on October 28, 1995: 22.221, Spinning-general, Amdt. 22/90/1, eff. June 30, 1990, 22.779, Motion and effect of cockpit controls, Amdt. 22/90/1, eff. June 30, 1990; TG00004AT Page 6 In addition, the following applies: RBHA/RBAC 91, Amdt. 91-05, paragraph 91.205, effective March 01, 1999, applicable to AMT-200S Optional Version. For all models: Plus the following means of compliance from FAA Advisory Circular 21.17-2, dated July 13, 1989: JAR 22.177(b), including AC 21.17-2 par. 6.c. (6)(i)(A), (B), (C), and (D), JAR 22.777, including AC 21.17-2 par. 6.c. (7)(i)(A), (B), (C), and (D), JAR 22.903(b), including AC 21.17-2 par. 6.c. (7)(iii), JAR 22.1093 including AC 21.17-2 par. 6.c. (7)(iv), FAR 23.1153, including AC 21.17-2 par. 6.c. (7)(vi), JAR 22.1555 including AC 21.17-2 par. 6.c. (7)(vii); Plus the special condition established in letter No. 54085 SFAT/TC, dated October 15, 1984 (established by the DGAC, airworthiness authority in France, to provide additional requirements for composites - high temperatures and an increased safety margin to account for aging of the structure). Exemption from FAR 45.11 (a) and (d) as specified in Exemption No. 4988 (external marking of gliders). Date of application for Type Certificate September 4, 1990. Type Certificate No. TG00004AT issued December 29, 1993. Import Requirements A U.S. Standard Airworthiness Certificate may be issued on the basis of a Certificate of Airworthiness for Export signed by a representative of the Agencia Nacional de Aviação Civil (ANAC), containing the following statement: "The powered glider covered by this certificate has been examined, tested and found to conform to the type design approved under FAA Type Certificate No. TG00004AT and is in condition for safe operation." Modifications pre-dating the issuance of this type certificate and not included in paragraph 1 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. 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 cer tificate for imported aircraft. The following AEROMOT Service Bulletin must be incorporated in Models AMT-100 or AMT-200 prior to issuance of a U.S. Airworthiness Certificate: Service Bulletin Date Subject S/N's Affected 100-11-001 Rev. Sep 10, '93 Placards 100.001- 100.007 100-24-003 Rev. Sep 10, '93 Landing Gear Warning 100.001- 100.009 100-24-005 Rev. Sep 10, '93 Alternator Control 100.001- 100.013 100-24-011 Rev. Oct 8, '93 Fusebox Cover 100.001- 100.012 TG00004AT Page 7 100-24-012 Rev. Sep 10, '93 Starter Button 100.001- 100.015 100-25-025 Rev. Sep 10, '93 Baggage Retaining Net 100.001- 100.039, 100.041- 100.044, 100.046, 200.040 100-27-024 Rev. Sep 10, '93 Elev Trim Tab Cable Connection 100.001- 100.039, 100.041- 100.044, 100.046, 200.040 100-28-002 Rev. Sep 10, '93 Fuel Filter 100.001- 100.008 100-28-027 No Dec 17, '93 Placard-Fuel Gage 100.001- 100.039, 100.041- 100.044, 100.046, 200.040 100-32-004 Rev. Sep 10, '93 Landing Gear Bolts 100.003- 100.006 100-32-015 Rev. Sep 10, '93 Landing Gear Locking Pin 100.001- 100.029 100-32-016 Rev. Sep 10, '93 Landing Gear Strut Spring 100.001- 100.032 100-32-017 Rev. Oct 8, '93 Landing Gear Additional Locking Device 100.001- 100.034 100-52-006 Rev. Sep 10, '93 Placard-Canopy Locking 100.001- 100.013 100-52-018 Rev. Sep 10, '93 Canopy Latches 100.001- 100.034 100-52-026 Rev. Oct 8, '93 Canopy Latches 100.035- 100.039, 100.041- 100.044, 100.046, 200.040, 200.045 100-55-001 Rev. Sep 10, '93 Elevator Interference 100.002, 100.005- 100.007 TG00004AT Page 8 100-57-23 Rev. 2 Sep 10, '93 Wing Drain Holes 100.001- 100.039, 100.041- 100.044, 100.046, 200.040, 200.045 100-57-028 No Dec 17, '93 Wing Red Mark and Guide Trim 100.001- 100.039, 100.041- 100.044, 100.046, 200.040 100-76-001 Rev. Sep 10, '93 Throttle Jam 100.001- 100.015 Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the powered glider for certification. In addition, the following items of equipment are required: 1. Basic equipment and instruments a) airspeed indicator (illuminated on AMT-200S Optional Version) b) altimeter (illuminated on AMT-200S Optional Version) c) magnetic compass (illuminated on AMT-200S Optional Version) d) variometer (illuminated on AMT-200S Optional Version) e) slip-skid indicator (illuminated on AMT-200S Optional Version) f) tachometer (illuminated on AMT-200S Optional Version) g) double fuel quantity indicator (illuminated on AMT-200S Optional Version) h) oil temperature indicator (illuminated on AMT-200S Optional Version) i) oil pressure indicator (illuminated on AMT-200S Optional Version) j) hourmeter k) cylinder head temperature (AMT 200, AMT-200S and AMT 300; illuminated on AMT-200S Optional Version l) manifold pressure indicator (AMT 300; illuminated on AMT-200S Optional Version) m) attitude gyro indicator (AMT 200S Optional Version) n) navigation/communication equipment (AMT 200S Optional Version) o) emergency locator transmitter (AMT 200S Optional Version) p) landing gear position indicator q) safety belt (including shoulder harness) r) navigation lights (AMT 200S Optional Version) s) anti-collision light (AMT 200S Optional Version) t) landing light (AMT 200S Optional Version) u) spare set of fuses v) fire extinguisher (AMT-200S Optional Version) 2. Operations Manual (containing Flight Manual, Repair and Maintenance Manual) approved by ANAC. Service Information Service bulletins, structural repair manuals, vendor manuals, aircraft flight manuals, and overhaul and maintenance manuals, which contain a statement that the document is ANAC approved are accepted by the FAA and are considered FAA approved. These approvals pertain to the type design only. Available documents for AMT-100: Flight Manual No. 100-04, Issued December 29, 1993, and subsequent revisions, ANAC approved. Maintenance Manual 100-10, September 1993. Parts Catalog 100-02, September 1993. TG00004AT Page 9 Engine Manual Limbach L2000 and Series Hoffman Owner's Manual No. E0107.72 Available documents for AMT-200: Flight Manual No. 200-07, Issued December 29, 1993, and subsequent revisions, ANAC approved. Maintenance Manual 200-13, September 1993. Parts Catalog 100-02, September 1993. ROTAX Operator's Manual, approved by Austria Federal Office of Civil Aviation. Available documents for AMT-300: Flight Manual No. 300-20, issued July 19, 1999, and subsequent revisions, ANAC approved. Maintenance Manual 300-22, March 1, 1999. Parts Catalog 300-23, April, 1999. ROTAX Operator's Manual, approved by Austria Federal Office of Civil Aviation. MT Propeller Operation and Installation Manual E-124 Available documents for AMT-200S: Flight Manual No. 200-24, issued June 26, 2000, and subsequent revisions, ANAC approved. For the AMT-200S Optional Version, “Operating Supplement – 01” must be included in the flight manual. Maintenance Manual 200-25, Revision 1, dated June 26, 2000, or later revisions. Parts Catalog 200-26, April 10, 2000. ROTAX Operator's Manual, approved by Austria Federal Office of Civil Aviation. Hoffman Owner’s Manual No. E0107.72 NOTES: NOTE 1 Current weight and balance report including the list of equipment included in the certified empty weight, and loading instructions, when necessary, must be provided for each motorglider at the time of original certification. The certificated empty weight and corresponding center of gravity locations must include the following: total motorglider unusable fuel of 0.52 U.S. gal at +48.8 in. NOTE 2 The placards listed in the Flight Manual must be displayed. A complete listing of all placards is shown in the applicable Maintenance Manuals. NOTE 3 The inspections, maintenance, repair and painting must be accomplished according to the Maintenance Manual. Major structural repairs can only be accomplished by the manufacturer. NOTE 4 All external surfaces of the motorglider exposed to the sunlight must be painted white, except for areas provided for registration marking and anticollision paint. NOTE 5 A variable ballast weight attached to the engine firewall of each aircraft is required to keep the cg range of the loaded aircraft within limits. (AMT-100 only). NOTE 6 The motorglider life limit may be extended from 3000 to 6000 hours, in steps of 1000 hours, if the Extension Life Limit Program specified in Service Bulletin No. 100-10-021, Rev. 1, September 10, 1993, or later ANAC approved revision, has been complied with. A copy of the inspection results must be sent to the FAA, Atlanta Aircraft Certification Office. NOTE 7 The Model AMT-200, AMT-200S and AMT-300 serial numbers will follow the sequence of the Model AMT-100, changing only the prefix. The last three digits of the serial number refer to the production sequence. The first three digits mean: 100, model AMT-100; 200, models AMT-200 and AMT-200S; 300, model AMT-300. TG00004AT Page 10 NOTE 8 The following Master Drawing Lists, or later ANAC approved revisions, apply: AMT-100 Master Drawing List No. LP-10000, Rev C, dated 08 April 1994. AMT-200 Master Drawing List No. LP-20000, Rev F, dated 21 September 1995. AMT-300 Master Drawing List No. 06000-3, Rev A, dated 24 February 1999. AMT-200S Master Drawing List No. 06000-4, Rev A, dated 02 May 2000. NOTE 9 For models imported after December 13, 2006, conventional coolant with 50% water content as described in Rotax Service Bulletin SB-912-043 R2 / SB-914-029 R2, dated November 10, 2006, must be incorporated prior to issuance of a U.S. Airworthiness Certificate. An approved selection of operating fluids is found in Rotax Service Instruction SI-912-016 / SI-914-019. NOTE 10 Night visual flight rule (VFR) operation is only authorized for the AMT-200S Optional Version. To conduct this kind of operation, it is mandatory that these motorgliders have the specified required equipment installed and all instruments (airspeed indicator, altimeter, magnetic compass, variometer, slip and skid indicator, tachometer, fuel quantity indicator, oil temperature indicator, oil pressure indicator, cylinder head temperature indicator, manifold pressure manometer) and radio navigation equipment must have illuminating devices. ....END....