TCDS G26EU

DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION G26EU Revision 3 Schempp-Hirth Flugzeugbau GmbH NIMBUS-2 NIMBUS-2B February 10, 2022 TYPE CERTIFICATE DATA SHEET NO. G26EU This data sheet which is a part of Type Certificate No. G26EU 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: Schempp-Hirth Flugzeugbau GmbH Krebenstrasse 25 73230 Kirchheim/Teck Germany Type Certificate Holder Record: SHK Segelflugzeugbau GmbH transferred TC G26EU to Schempp-Hirth Flugzeugbau GmbH on January 16, 1981. Schempp-Hirth K.G. transferred TC G26EU to SHK Segelflugzeugbau GmbH on April 6, 1976. I - Model NIMBUS-2 Glider (Utility Category), approved January 16, 1974 Airspeed Limits: (I.A.S.) Maximum Airspeeds In Calm Air Never Exceed (Vne) 0 - 9800 ft alt. 146 kts 168 mph* 270 km/h 9801 - 19700 ft alt. 113 kts 130 mph* 209 km/h 19701 - 32800 ft alt. 89 kts 103 mph* 165 km/h Never Exceed With Airbrakes Extended 146 kts 168 mph* 270 km/h With Landing Gear Extended (Vle) 146 kts 168 mph* 270 km/h Maneuvering Speed (VA) 86 kts 99 mph 160 km/h With Flaps Extended (Vfe) Positions L, +6, or +4 (down) or * L, +10, +6 86 kts 99 mph 160 km/h Positions 0, -4, or -7 (up) 146 kts 168 mph* 270 km/h *see NOTE 6 C.G. Range: (+11.4 in) to (16.1 in) at all weights. Empty Weight C.G. Range: See C.G. Range. Datum: Wing leading edge at root rib. Leveling Means: Slope of rear top surface of fuselage: 100 to 4.5 tail down. Page No. 1 2 3 4 5 6 Rev. No. 3 3 3 3 3 3 G26EU 2 Maximum Weight: Maximum takeoff weight without water ballast 1036 lbs Maximum takeoff weight with water ballast** 1278 lbs. See NOTE 6 (**Total weight of glider must not exceed 1036 lbs before water ballast is added. Gliders without water ballast tanks installed therefore have a maximum takeoff weight limitation of 1036 lbs.) No. of Seats: 1 at 22.44 inches ahead of datum. Maximum Baggage: None. Control Surface Movements: Ailerons with wing flaps in Ailerons with wing flaps in Position 0 Position 0 - See NOTE 6 Elevators Up 1.85 + .40 in Elevators Up 1.85 + .40 in Down 2.83 + .40 in Down 2.83 + .40 in Radius measures 11.3 inches from hinge axis at inboard edge. Rudder Left 8.86 + .80 in Rudder Left 8.86 + .80 in Right 8.86 + .80 in Right 8.86 + .80 in Radius measures 15.7 inches from hinge axis at base of rudder. Ailerons Up 2.20 + .40 in Ailerons Up 2.20 + .40 in - .20 in - .20 in Down 0.87 + .20 in Down 1.22 + .20 in - .12 in - .12 in Radius measures 5.52 inches from hinge axis at inboard edge. Flap Position -7 7° + 0° Up Flap Position -7 7° + 0° Up -1° -1° -4 4° + 0° Up -4 4° + 0° Up -1° -1° 0 0° 0 0° +4 4° + 0° Down +6 6° + 1° Down - 1° +6 6° + 0° Down +10 10° + 1° Down - 1° L 11° + 2° Down L 17° + 2° Down Radius measures 6.4 inches at inboard edge. Weak Links for Towing: 1320 lbs max. (600 kg). II. - Model NIMBUS-2B Glider (Utility Category), approved September 21, 1984 (Similar to the NIMBUS-2 except for a horizontal stabilizer and elevator instead of a movable stabilizer) Airspeed Limits: (I.A.S.) Maximum Airspeeds In Calm Air Never Exceed (Vne) 0 - 9800 ft alt. 146 kts 168 mph 270 km/h 9801 - 19700 ft alt. 113 kts 130 mph 209 km/h 19701 - 32800 ft alt. 89 kts 103 mph 165 km/h Never Exceed With Airbrakes Extended 146 kts 168 mph* 270 km/h With Landing Gear Extended (Vle) 146 kts 168 mph* 270 km/h G26EU 3 Maneuvering Speed (VA) With Flaps Extended (Vfe) Positions L, +10, or +6 (down) Positions 0, -4, or -7 (up) 86 kts 86 kts 146 kts 99 mph 99 mph 168 mph 160 km/h 160 km/h 270 km/h *see NOTE 6 C.G. Range: (+11.4 in) to (16.5 in) at all weights. Empty Weight C.G. Range: See C.G. Range. Datum: Wing leading edge at root rib. Leveling Means: Slope of rear top surface of fuselage: 100 to 4.5 tail down. Maximum Weight: Maximum takeoff weight without water ballast 1036 lbs Maximum takeoff weight with water ballast** 1278 lbs See NOTE 6 (** Total weight of glider must not exceed 1036 lbs before water ballast is added.) No. of Seats: 1 at 22.44 inches ahead of datum. Maximum Baggage: None. Control Surface Movements: Ailerons with wing flaps in Position 0 Elevators Up 1.85 + .40 in Down 1.93 + .20 in Radius measures 6.38 inches from hinge axis at inboard edge. Rudder Left 10.00 + .80 in Right 10.00 + .80 in Radius measures 17.7 inches from hinge axis at base of rudder. Ailerons Up 2.20 + .40 in - .20 in Down 1.22 + .20 in - .12 in Radius measures 5.52 inches from hinge axis at inboard edge. Flaps Position -7 7° + 0° Up - 1° -4 4° + 0° Up - 1° 0 0° +6 6° + 1° Down +10 10° + 1° Down L 17° + 2° Down Radius measures 6.4 inches at inboard edge. Weak Links for Towing: 1320 lbs max. (600 kg). G26EU 4 Data Pertinent to All Models: Serial Numbers Eligible: Import Requirements: Certification Basis: See Import Requirements. A U.S. Standard Airworthiness Certificate may be issued on the basis of an NAA Export Certificate of Airworthiness (Export C of A) signed by a representative of the German Airworthiness Authority, the Luftfahrt-Bundesamt (LBA), containing the following statement: For the Model NIMBUS-2: "The glider covered by this certificate has been examined, tested, and found to conform to the type design approved under FAA Type Certificate No. G26EU and is in condition for safe operation," and the FAA inspector finds that the glider conforms to the U.S. Type Design and is in condition for safe operation. For the Model NIMBUS-2B: “The glider covered by this certificate has been examined, tested, and found to conform to the type design approved under FAA Type Certificate G26EU and is in condition for safe operation," and the FAA inspector finds that the glider conforms to the U.S. Type Design and is in condition for safe operation. Schempp-Hirth Model NIMBUS-2B glider serial numbers 136 and 145 are eligible for U.S. Standard Airworthiness Certification when: 1) The FAA inspector is provided with the original Export Certificate of Airworthiness issued by the LBA, which certifies the glider conforms to the U.S. type certificate, 2) The glider has been modified in accordance with the LBA- approved Schempp-Hirth Technical Notes 286-14, 286-18, and 286/77/1, and 3) The glider is found to be in condition for safe operation by the FAA inspector. 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. 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. FAR 21.23 and FAR 21.29 effective February 1, 1965. For Model NIMBUS-2: Federal Republic of Germany "Airworthiness Requirements for Sailplanes" dated February 1966 which has been found to provide a level of safety equivalent to that provided by the airworthiness requirements of FAR 23 through amendment 14 appropriate to gliders. Type Certificate G26EU issued January 16, 1974. Date of application for Type Certificate: December 10, 1971. G26EU 5 For Model NIMBUS-2B: Federal Republic of Germany "Airworthiness Requirements for Sailplanes" dated February 1966 which has been found to provide a level of safety equivalent to that provided by the airworthiness requirements of FAR 23 through amendment 18 appropriate to gliders. Type Certificate G26EU amended September 21, 1984. Date of Application for amendment of the Type Certificate: May 2, 1977. Equipment: For Model NIMBUS-2: Schempp-Hirth Model NIMBUS-2 Glider Flight Manual dated December 1972. The minimum required equipment for the kinds of approved operations are listed in the Glider Flight Manual. For the Model NIMBUS-2B: Schempp-Hirth Model NIMBUS-2B Glider Flight Manual dated July 1979. The Equipment approved for the Schempp-Hirth Model NIMBUS-2B is listed on the Schempp-Hirth Master Equipment List dated July 23, 1984. The minimum required equipment for the kinds of approved operations are listed in the Glider Flight Manual. Service Information: Schempp-Hirth Technical Information (Service Bulletins), published in the English language for the U.S. Type Design that carry a statement "Approved by the Luftfahrt-Bundesamt (LBA)" may be interpreted as "FAA-Approved." Available documents for Model NIMBUS-2: - Flight and Service Manual, dated December 1972, LBA-approved January 18, 1973. Available Documents for Model NIMBUS-2B: - Flight and Service Manual, dated July 1979, LBA-approved January 10, 1984. NOTES. NOTE 1. Current weight and balance report including list of equipment in certificated empty weight, and loading instructions, when necessary, must be provided for each glider at the time of original airworthiness certification. NOTE 2. The placards listed in the LBA-approved Schempp-Hirth Flight Manual must be displayed in the location defined. NOTE 3. Information essential for proper operation, maintenance, inspection, and repair of the glider is contained in the Schempp-Hirth "Flight and Service Manual for Model Nimbus-2" and the Schempp-Hirth "Flight and Service Manual for Model Nimbus-2B". Schempp-Hirth should be consulted for all major repairs. The service life of the Schempp-Hirth Model NIMBUS-2 and Model NIMBUS-2B is limited to 3000 flight hours without repetitive inspections other than the obligatory annual inspections. Extension of the service life beyond 3000 flight hours may be obtained provided the structural inspection procedures and limitations contained in the LBA- approved Schempp-Hirth Technical Information (Service Bulletin) No. XXXX (number to be provided at a later date) are used. NOTE 4. All external portions of the glider exposed to sunlight must be painted white except wing tips, nose of fuselage and rudder. NOTE 5. Major airframe repairs must be accomplished in accordance with repair methods approved by Schempp-Hirth or by the FAA. G26EU 6 NOTE 6. Maximum permitted airspeed increased from 250 km/h (135 kts) (155 mph) to 270 km/h (146 kts) (168 mph) and maximum gross weight with water ballast increased from 530 kg (1168 lbs) to 580 kg (1278 lbs) per LBA approved and FAA validated Schempp-Hirth Technical Note 286-8, dated February 20, 1976. Aileron flap control system improvements resulted in changes to control movement measurements for S/N 86, 104 through 109, 111 and subsequent. ...END...