TCDS G00074CE

Page No. 1 2 3 4 5 6 Rev. No. 1 1 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION G00074CE Revision 1 Alexander Schleicher GmbH ASG 32 ASG 32 Mi May 18, 2022 TYPE CERTIFICATE DATA SHEET No. G00074CE This data sheet, which is a part of Type Certificate No. G00074CE, 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. Alexander Schleicher GmbH & Co. Segelflugzeugbau Alexander-Schleicher-Str. 1 36163 Poppenhausen Germany I. Model ASG 32, Glider, Utility Category, approved January 26, 2018. Description. The ASG 32 is a two-seat (tandem), mid-wing, all composite glider with a retractable main landing gear and a conventional T-type tailplane. It has a wing with a span of 65 ft (20 m), flaps, winglets, double panel Schempp-Hirth type airbrakes on the upper surface, and water ballast tanks. km/h kts mph Airspeed Limits (IAS). VNE Never exceed 0 - 15,999 ft 270 146 168 16,000 - 19,499 ft 256 138 159 19,500 - 22,999 ft 242 130 150 23,000 - 26,199 ft 228 123 142 26,200 - 29,499 ft 215 116 134 29,500 - 32,000 ft 202 109 126 VRA Rough air 180 97 111 VA Maneuvering 180 97 111 VFE Max flap extended: 1 – 2 – 3 – 4 position 270 146 168 5 – 6 position 180 97 111 L position 150 81 93 VW Max winch-launch 140 75 87 VT Max aero-tow 180 97 111 VLO Max landing gear operating 180 97 111 C.G. Range. 6.14 in. to 15.15 in. (156 mm to 385 mm) (aft of datum) Empty Weight C.G. Range. Refer to Maintenance Manual, Section 6 Datum. Leading edge of the wing at the root rib Leveling Means. Wedge 1000: 27 and level on upper face of tailboom in front of vertical fin (see Maintenance Manual Figure 6.2-1) Maximum Weight. Max take-off: 1874 lbs (850 kg) Max landing: 1874 lbs (850 kg) Max non-lifting parts: 1212 lbs (550 kg) Minimum Crew. One pilot. When operated solo, the front seat is for the pilot in charge. G00074CE 2 No. of Seats. Two seats Front: Moment arm -56.30 to -61.02 in (-1430 to -1550 mm) forward of datum Rear: Moment arm -17.72 to -18.90 in (-450 to -480 mm) forward of datum Maximum Baggage. Baggage compartment: 20 lbs at 4.3 in. (9 kg at 110 mm) Engine bay stowage: 4 lbs at 88.6 in. (1.8 kg at 2,250 mm) Tail battery compartment: 22 lbs at 221.1 in. (10 kg at 5,617 mm) Water Ballast. Two wing tanks totaling 31.7 gallons at 5.71 in. (120 liters at 145 mm); One vertical tail tank totaling 1.32 gallon at 223.5 in (5 liters at 5,678 mm) Control Surface Movements. Aileron: Up: 1.85 ± 0.16 in. (47 ± 4 mm) (Flap Setting 3) Down: 0.51 ± 0.16 in. (13 ± 4 mm) Measuring radius 4.88 in. (124 mm) from hinge axis Wing Flaps: Up: 0.43 ± 0.16 in. (11 ± 4 mm) (Flap Setting 3) Down: 0.51 ± 0.16 in. (13 ± 4 mm) Measuring radius 6.26 in. (159 mm) from hinge axis Elevator: Up: 1.61 ± 0.08 in. (41 ± 2 mm) Down: 1.61 ±0.08 in. (41± 2 mm) Measuring radius 4.65 in. (118 mm) from hinge axis Rudder: Right: 6.5 ± 0.4 in. (166 ± 10 mm) Left: 6.5 ± 0.4 in. (166 ± 10 mm) Measuring radius 12.24 in. (311 mm) from hinge axis All measured from trailing edge. See Maintenance Manual Section 3. II. Model ASG 32 Mi, Self-Launching (Powered) Glider, Utility Category, approved January 26, 2018. Description. The ASG 32 Mi is a two-seat (tandem), mid-wing, self-launching, all composite glider with a retractable engine and fixed pitch propeller mounted in the center fuselage behind the cockpit. It has a wing with a span of 65 ft (20 m), flaps, winglets, double panel Schempp-Hirth type airbrakes on the upper surface, and water ballast tanks. The glider also has a retractable main landing gear and a conventional T-type tailplane. Engine. Austro Engine IAE50R-AA Fuel. AVGAS 100LL preferred. Fuel grades with a minimum 94 Octane, such as EN 228 Car Super, Euro-Super, or Super-plus are also permissible, but only with an Ethanol content of not more than 5%. Engine Limits. Takeoff (maximum 3 minutes) 7750 r.p.m. (37.3 kW) Continuous Operation: 7100 r.p.m. (35.8 kW) Propeller and Propeller Limits. Alexander Schleicher GmbH & Co. AS 2 F1-1 / R153 – 92 – N1 Diameter 60.24 in. ± 0.2 in. (1530 ± 5 mm) 2 right-hand turning blades Fixed pitch at 0.75 blade radius: 36.22 in (920 mm), km/h kts mph Airspeed Limits (IAS). VNE Never exceed 0 - 15,999 ft 270 146 168 16,000 - 19,499 ft 256 138 159 19,500 - 22,999 ft 242 130 150 23,000 - 26,199 ft 228 123 142 26,200 - 29,499 ft 215 116 134 3 G00074CE Airspeed Limits (IAS) (cont’d). 29,500 - 32,000 ft 202 109 126 VRA Rough air 180 97 111 VA Maneuvering 180 97 111 VFE Max flaps extended: 1 – 2 – 3 – 4 position 270 146 168 5 – 6 position 180 97 111 L position 150 81 93 VW Max winch-launch 140 75 87 VT Max aero-tow 180 97 111 VLO Max landing gear operating 180 97 111 VPE Max with propeller extended 180 97 111 VPOmax Max extend/retract propeller 120 64 74 VPOmin Min extend/retract propeller 95 51 59 C.G. Range. 6.14 in. to 15.15 in. (156 mm to 385 mm) (aft of datum) Empty Weight C.G. Range. Refer to Maintenance Manual, Section 6 Datum. Leading edge of the wing at the root rib Leveling Means. Wedge 1000: 27 and level on upper face of tailboom in front of vertical fin (see Maintenance Manual Figure 6.2.-1) Maximum Weight. Max take-off: 1874 lbs (850 kg) Max landing: 1874 lbs (850 kg) Max non-lifting parts: 1212 lbs (550 kg) Minimum Crew. One pilot. When operated solo, the front seat is for the pilot in charge. No. of Seats. Two seats Front: Moment arm -56.30 to -61.02 in (-1430 to -1550 mm) forward of datum Rear: Moment arm -17.72 to -18.90 in (-450 to -480 mm) forward of datum Maximum Baggage. Baggage compartment: 20 lbs at 4.3 in. (9 kg at 110 mm) Engine bay stowage: 4 lbs at 88.6 in. (1.8 kg at 2,250 mm) Tail battery compartment: 22 lbs at 221.1 in. (10 kg at 5,617 mm) Water Ballast. Two wing tanks totaling 31.7 gallons at 5.71 in. (120 liters at 145 mm); One vertical tail tank totaling 1.32 gallons at 223.5 in. (5 liters at 5,678 mm) Fuel Capacity. One fuselage tank of 3.7 gallons at 11.4 in. (14 liters at 290 mm); Optional one or two wing tanks of 3.9 gallons each at 7.1 in. (15 liters each at 180 mm); 0.1 gallons (0.4 liters) non-usable fuel Oil Capacity. 0.713 quarts (0.675 liters) total; 0.032 quarts (0.03 liters) non-usable oil Maximum Operating Altitude. 16,400 ft (5,000 m) MSL with engine running; at higher altitudes, engine restart cannot be guaranteed. Control Surface Movements. Aileron: Up: 1.85 ± 0.16 in. (47 ± 4 mm) (Flap Setting 3) Down: 0.51 ± 0.16 in. (13 ± 4 mm) Measuring radius 4.88 in. (124 mm) from hinge axis Wing Flaps: Up: 0.43 ± 0.16 in. (11 ± 4 mm) (Flap Setting 3) Down: 0.51 ± 0.16 in. (13 ± 4 mm) Measuring radius 6.26 in. (159 mm) from hinge axis G00074CE 4 Control Surface Movements (cont’d). Elevator: Up: 1.61 ± 0.08 in. (41 ± 2 mm) Down: 1.61 ± 0.08 in. (41 ± 2 mm) Measuring radius 4.65 in. (118 mm) from hinge axis Rudder: Right: 6.5 ± 0.4 in. (166 ± 10 mm) Left: 6.5 ± 0.4 in. (166 ± 10 mm) Measuring radius 12.24 in. (311 mm) from hinge axis All measured from trailing edge. See Maintenance Manual Section 3. Data Pertinent to All Models: Serial Nos. Eligible. 32045 and up. See Import Requirements Import Requirements. A U.S. Standard Airworthiness Certificate may be issued on the basis of 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 glider covered by this certificate has been examined, tested and found to conform to the type design approved under FAA Type Certificate No. G00074CE and is in condition for safe operation.” Serial numbers 32008, 32011, 32016, 32019, 32027, 32028, 32029 and 32033 w ere imported to the U.S. prior to FAA type certificate approval, therefore the original Export C of A for these gliders will certify that they conform to the European Aviation Safety Agency (EASA) type certificate number EASA.A.599. They are eligible for a U.S. Standard Airworthiness Certificate when Alexander Schleicher GmbH Technical Note No. 3, Original Revision, dated October 04, 2017, or later approved version and Technical Note No. 4, Original Revision, dated October 31, 2017, or later approved version are accomplished and they are found 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 21, effective February 1, 1965, Amendments 21-1 through 21-98, as applicable. 2) EASA Certification Specifications for Sailplanes and Powered Sailplanes (CS-22), Amendment 2, dated March 05, 2009. 3) EASA Special Condition No. SC-A.22.1.01, “Increase in maximum mass for sailplanes and powered sailplanes.” A maximum mass of 900 kg for powered gliders and 850 kg for gliders may be accepted if the following requirements can be complied with: • Demonstration of compliance with all paragraphs of the applicable Type Certification Basis CS-22/JAR 22 for the higher MTOM. • Important compliance demonstration is related to stalling speeds, emergency landing condition, and environmental protection requirements. 5 G00074CE Certification Basis (cont’d). • In case of existing special conditions or equivalent safety findings in the certification basis, the applicability of this Special Condition has to be checked. 4) EASA Equivalent Safety Finding to CS 22.335(f) – Design Maximum Speed VD Design Maximum Speed (VD) calculation in accordance with the Organisation Scientifique et Technique International du Vol á Voile (OSTIV), Airworthiness Standards for Sailplanes, Issued July 1997, paragraph 3.246 ‘Design Diving Speed VD ‘. 5) EASA Equivalent Safety Finding to CS 22.585(a) – Strength of launching hook attachment The rated ultimate strength of the towing cable (Qnom) as defined in CS 22.581(b) is reduced by factor 1.2 under the precondition that only textile ropes are used. 6) “Standards for Structural Substantiation of Sailplane and Powered Sailplane Parts Consisting of Glass or Carbon Fiber Reinforcced Plasticcs,” LBA document no. I4- FVK/91, issued July 1991. 7) “Guideline for the analysis of the electrical system for powered sailplanes,” LBA document no. I334-MS 92, issued September 15, 1992. 8) The following kinds of operation are allowed: VFR-Day. 9) EASA Type Certificate Data Sheet no. EASA.A.599, Issue 02, dated March 17, 2016. 10) Date of Application for FAA Type Certificate, August 23, 2016. Production Basis. Alexander Schleicher GmbH & Co. Segelflugzeugbau Alexander-Schleicher-Straße 1 D-36163 Poppenhausen, Germany EASA Production Organization Approval Number: DE.21G.0010 Equipment. The minimum required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the glider for certification. For both ASG 32 and ASG 32 Mi: 1 Airspeed indicator up to 300 km/h (162 kts, 187 mph), in front instrument panel 1 Altimeter in front instrument panel 1 Outside air temperature gauge in front instrument panel (if water ballast tanks are installed) 2 4-part safety harness (symmetrical) 1 Parachute or cushion for the back rest (~ 3.15 in (80 mm)) for each occupant Additional requirements for instruction or if the pilot in command sits in rear seat: 1 Airspeed indicator up to 300 km/h (162 kts, 187 mph), in rear instrument panel 1 Altimeter in rear instrument panel In addition, for ASG 32, add: 1 FAA-approved Flight Manual for the Model ASG 32 In addition, for ASG 32 Mi add: 1 Magnetic Compass in front instrument panel 1 Power-plant instrument in front instrument panel 1 Rear view mirror 1 FAA-approved Flight Manual for the Model ASG 32 Mi G00074CE 6 Service Information. Each of the documents listed below must state that it is approved by the European Aviation Safety Agency (EASA): • Service bulletins • 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 exists: • 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. ASG 32 Operating and Service Instructions: 1) Flight Manual for Model ASG 32, Issue September 15, 2017, or later approved revision. 2) Maintenance Manual for Model ASG 32, Issue January 15, 2016, Revision TN 4 dated October 31, 2017, or later approved revision. 3) Repair Manaul, Amendment dated July 1999, or later approved revision. ASG 32 Mi Operating and Service Instructions: 1) Flight Manual for Model ASG 32 Mi, Issue September 15, 2017, or later approved revision. 2) Maintenance Manual for Model ASG 32 Mi, Issue January 15, 2016, Revision TN 4 dated October 31, 2017, or later approved revision. 3) Repair Manaul, Amendment dated July 1999, or later approved revision. 4) Engine Manual, Austro Engine IAE50R-AA, Document No. E1.01.05-E, Revision 8 dated December 18, 2014, or later approved revision. 5) Operating and Maintenance Manual for Propeller AS2F1, Issue February 2000, or later approved revision. NOTES. NOTE 1. Current weight and balance report including list of equipment included 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 location must account for the items from Section 6 of the Maintenance Manual. NOTE 2. All placards required by Section 2 of the applicable FAA-approved Flight Manual, must be installed in the appropriate location. Complete listing of all placards is shown in Section 9 of the applicable Maintenance Manual. The Flight Manual airworthiness limitations may not be changed without FAA approval. NOTE 3. Section 4 of the approved Maintenance Manual specifies mandatory replacement times. These Maintenance Manual airworthiness limitations may not be changed without FAA approval. A Maintenance Manual acceptable to the FAA must be issued prior to the issuance of a Standard Airworthiness Certificate. NOTE 4. All external portions of the glider exposed to solar radiation must be painted white, except for areas provided for registration and warning markings as specified by the manufacturer. - END-