TCDS G28EU

Page No. 1 2 3 4 Rev. No. 5 5 4 2 DEPARTMENT OF TRANSPORATION FEDERAL AVIATION ADMINISTRATION G28EU Revision 5 START + FLUG H101 "Salto" March 1, 2012 TYPE CERTIFICATE DATA SHEET NO. G28EU This data sheet which is a part of type certificate No. G28EU 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 Ursula Hanle Doktor Fiberglas GFK-FLUGZEUG-SERVICE 5438 Westerburg Postfach 1112 Type Certificate Ownership Record (1) This TC was considered not valid by the state of design on January 22, 2009, and has been replaced by European Aviation Safety Agency (EASA) Specific Airworthiness Specification (SAS) number EASA.SAS.A.028, issued January 22, 2009. Only standard airworthiness certificates issued prior to March 1, 2012 are valid. (2) Future unsafe conditions existing in the aircraft may result in the revocation of the airworthiness certificates of the aircraft if there is no entity to comply with 14 CFR § 21.99(a), “Required design changes.” (3) Replacement parts may not be available in the future. I. Model H101 "Salto" Sailplane, approved 7 November 1972 Airspeed limits (I.A.S.) N A Vne (Never Exceed) 135 knots (155 mph) 151 knots (174 mph) Va (Maneuvering) 81 knots (93 mph) 86 knots (99 mph) Airplane tow 81 knots (93 mph) 81 knots (93 mph) Auto-winch tow 70 knots (81 mph) 70 knots (81 mph) Dive brakes 135 knots (155 mph) 135 knots (155 mph) C.G. range (+9.25 in.) to (+13.19 in.) at all weights. Empty Weight C.G. Range None Datum Wing leading edge measured 19.7 in. outboard of fuselage center line. (6.4 in. fwd of main wheel axle center line). Leveling means Slope of rear top surface of fuselage: 100 to 6 tail down. Maximum weight N A 683 lb. (310 Kgs.) 617 lb. (280 Kgs.) No. of seats 1 (at +9.58 in., most aft position) Maximum Baggage 33 lbs in baggage compartment Control Surface Movements Tail surfaces acting as: Elevators Up 1.85 + 0.16 in. - Measured as a chord G28EU 2 Down 1.85 + 0.16 in. Segment at root rib Rudders Up 3.07 + 0.16 in. - Measured as a chord Down 2.76 + 0.16 in. - Segment at root rib with elevators in "zero" position. Aileron Up 1.18 + 0.08 in. - Measured at trailing edge of tip rib Down 0.59 + 0.08 in. Weak Links for Towing Auto-winch tow: 1323 lb. (600 Kgs) Airplane tow: 1102 lb. (500 Kgs) Serial Nunbers Eligible Only those aircraft serials hol ding a standard airworthiness certificate issued prior to March 1, 2012 are eligible. Import Requirements None elig ible after March 1, 2012. Previous to this date: A U.S. Standard Airworthiness Certificate may be issued on the basis of a Certificate of Airworthiness for Export signed by a represen tative of the Federal Republic of Germany, Luftfahrt- Bundesamt (LBA), c ontaining 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 G28EU and is in a condition for safe operation." Certification Basis FAR 21.29 and FA R 21.23, effective 1 February 1965. Type Certificate No. G28EU issued 7 November 1972. Date of Application for Type Certificate: 9 August 1971. Validation Basis Type Certificate G28EU was issued pursuant to FAR 21.29 (a)(1)(ii) in validation of the Luftfahrt-Bundesamt (LBA) certification of compliance with the Federal Republic of Germany "Airworthiness Re quirements for Sailplanes", Edition: February 1966, which were found to provide a level of safety equivalent to the aforementioned FAA certification basis. Equipment The basic required equipm ent as prescribed in the applicable airworthiness regulations (see Certification basis) must be installe d in the glider for standard airworthiness certification. In addition the following equipment must be installed: 1. Instruments (non-cloud flying): (a) Airspeed Indicator marked as follows: Red Radial 135 knots (155 mph) Yellow Arc 81 - 135 knots (93-155 mph) Green Arc 40 - 81 knots (46-93 mph) (b) Altimeter (c) Magnetic Compass 2. Additional Instruments for cloud flying: (a) Turn and Bank Indicator (b) Variometer 3. Additional for Cat. A: (a) G-Meter capable of retaining maximum values of positive and negative acceleration for any selected period of flight (b) Pedal loops. Service Information "Service bulletins, structural repair manuals, vendor manuals, aircraft flight manuals, and overhaul and maintenance manuals, which cont ain a statement that the document is LBA approved, are accepted by the FAA and are considered FAA approved. These approvals pertain to the type design only." Information essential for the proper operation, maintenance, inspection, and repair of the glider is contained in the "Flight- and Se rvice Manual, Sailplane Type H101 "Salto". Repair information is supplemented by the document: "Petite Plastic Plane Patch Primer", by Ursula Hanle and available from Ursula Hanle, Doktor Fiberglas, GFK- 3 G28EU FLUGZEUG-SERVICE, 5438 Westerburg. Doktor Fiberglas should be consulted for all major repairs. NOTES NOTE 1. Current weight and balance data together with a lis t of equipment included in certificated empty weight, and loading instructions, when necessary, must be provided for each glider at the time of original airworthiness certification. NOTE 2. a) The following placards must be installed in full view of the pilot: (1) "This glider must be operated in compliance w ith the operating limitations stated in the form of placards, markings, and manuals." (2) "Cloud flying: Permitted only when the following instruments are installed: (1) Airspeed Indicator (2) Altimeter (3) Magnetic Compass (4) Turn and Bank (5) Variometer (3) The following acrobatic maneuvers are appr oved and the limitations, minimum equipment and procedures for acrobatic flight are given in the LBA December 1972 approved Airplane Flight Manual or later revisions. Spin: Entry speed = V IN = 5-10 km/hr (3-6 mph) above VMIN Max g = N MAX pullout = +3.5g NOTE: Height loss one spin = 80-100 m (260 to 300 ft) + pull out Inside Loop: V IN = 180-200 km/hr (97-108 kts) N MAX = +3g to 4g Roll of Top: V IN = 200-220 km/hr (108-119 kts) (Immelman Turn) V MIN at loop crest = 120 km/hr (65 kts) V MAX = 4g to 5g Roll to Inverted: V IN = 160-180 km/hr (86-97 kts) With pull through: V IN = 100-110 km/hr (54-59 kts) Slow Roll: V IN = 160-170 km/hr (86-92 kts) (Aileron roll) Tailslide: Positive and negative: V IN = 180-200 km/hr (97-108 kts) N MAX = +3.5g Half loop negative from inverted flight: V IN = 250 km/hr (135 kts) N MAX = -4.5g At crest V MIN = 80-90 km/hr (43-48 kts) Forward Loop: V IN = 80 km/hr (43 kts) (Negative) V Inverted MIN = 250 km/hr (135 kts) N MAX = -4.5g Snap Roll (Flicked roll): V IN = 150-160 km/hr (81-86 kts) Negative Snap Roll (Push roll): V IN 150 km/hr (81 kts) Inverted Spin: V IN = 110 km/hr (59 kts) G28EU 4 NOTE 2. (Cont'd) Lying 8: V lower part of position loop = 200 km/hr (108 kts) V lower part of negative loop = 250 km/hr (135 kts) V crest of negative loop = 70-80 km/hr (38-45 kts) N MAX = +4g, -4.5g (4) "Night flying is prohibited." N A (5) "Maneuvering speed 81 knots (93 mph) 86 kts (99 mph) Airplane tow speed 81 knots (93 mph) Auto-winch tow speed 70 knots (61 mph) Stall Speed - Dive brakes extended 45 knots (52 mph)" (6) "Maximum weight: 683 lbs 616 lbs b) The following placard must be visible in the cockpit area: "Weak Link - Airplane Tow 1102 lb. (600 kgs) Auto-winch Tow 1323 lb. (500 Kgs) NOTE 3. All external portions of the g lider exposed to sunlight must be painted white. Registration and competition numbers must be painted blue-gra y or in any other light color. NOTE 4. The installation of a brake chute must be accomplished in accordance with Technical Bulletin 101-7. NOTE 5. The optional installation of wingtips with a span of 15 or 15.5 m must be accomplished in accordance with Technical Bulletin 101-14/2. NOTE 6. S/No 59 and subsequent: The following aileron de flections are permissible in accordance with Technical Bulletin 101-23: up 26  2 mm (1.02  0.08 in) down 22  2 mm (0.86  0.08 in) measured on trailing edge of tip rib. ...END...