TCDS G25EU

DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET G25EU This data sheet which is a part of type certificate No. G25EU 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 Pilatus Aircraft Limited Stans, Switzerland I - Model B4-PC11, Standard Category Sailplane, approved September 1, 1972. Airspeed Limits (CAS) Never Exceed (Vne) 130 kts (149 mph) Maneuvering (Va) 78 kts (90 mph) Airplane Tow (Vat) 78 kts (90 mph) Auto-winch Tow (Vwt) 70 kts (81 mph) Dive Brakes (Spoilers) 130 kts (149 mph) II. Model B4-PC11A, Acrobatic Category Sailplane, approved March 16, 1977. (Same as B4-PC11 except with increased downward elevator deflection and rudder modified in accordance with Pilatus Drawing No. 113.40.11.001(g) or Pilatus Document No. 01575. See Data pertinent to all models and notes for limitations and required equipment.) III. Model B4-PC11AF, Acrobatic Category Sailplane (including flick-snap maneuvers), approved March 16, 1977. (Same as B4-PC11A except with reinforced fuselage rear structure in accordance with Pilatus Drawing No. 112.35.11.136/137(e) or Pilatus Document No. 01582. See Data pertinent to all models and notes for limitations and required equipment.) DATA PERTINENT TO ALL MODELS Airspeed Limits (CAS) B4-PC11 B4-PC11A B4-PC11AF Never Exceed (Vne) 130 kts 130 kts 130 kts (149 mph) (149 mph) (149 mph) Maneuvering (Va) 78 kts 88 kts 88 kts (90 mph) (101 mph) (101 mph) Airplane Tow (Vat) 78 kts 88 kts 88 kts (90 mph) (101 mph) (101 mph) Auto-winch Tow (Vwt) 70 kts 70 kts 70 kts (81 mph) (81 mph) (81 mph) Dive Brakes (Spoilers) 130 kts 130 kts 130 kts (149 mph) (149 mph) (149 mph) Flick (Snap) Maneuvers - - 81 kts (93 mph) C.G. range (+11.0 in.) to (+16.5 in.) (30% to 45% M.A.C.) at all weights. Page No. 1 2 3 4 Rev. No. 3 3 2 2 G25EU Revision 3 PILATUS B4-PC11 B4-PC11A B4-PC11AF July 7, 2021 G25EU 2 Empty weight C.G. range None Datum Wing leading edge near root. Leveling means Slope of rear top surface of fuselage between stations 1512 mm (59.5 in.) and 2772 mm (109.1 in.) : 1000 to 80. Maximum weight 770 lb. No. of seats 1 (Adjustable from 20.9 in. to 24.0 in.) Ballast Pilatus standard ballast weight (at 143.7 in.) including attachment bolt and nut: (a) lb., small weight only (b) 10 lb., large weight only. (c) 14 lb., large and small weight combined. Control surface movements Elevator UP 3.94 + 0.2 in. Measured as a chord segment at B4-PC11 DOWN 2.75 + 0.2 in. middle of elevator. B4-PC11A & AF DOWN 3.35 + 0.2 in. Rudder RIGHT 9.05 + 0.4 in. Measured as a chord segment on LEFT 9.05 + 0.4 in. lower end rib. Aileron UP 4.72 + 0.2 in. Measured as a chord segment on DOWN 2.28 + 0.2 in. inboard rib. Spoiler UP 6.50 + 0.2 in. Weak Links for Towing 1100 lb. + 110 lb. max. Serial Nos. eligible A Swiss Federal Air Office (FAO) Certificate of Airworthiness for Export endorsed as noted below under "Import Requirements" must be submitted for each individual glider for which application for standard airworthiness certification is made. 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 Swiss Federal Air Office (FAO), containing 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 G25EU and is in 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 FAR 21.29 and FAR 21.23, effective February 1, 1965. Type Certificate G25EU, issued September 1, 1972. Date of Application for Type Certificate B4-PC11, July 5, 1971. Validation Basis Type Certificate G25EU was issued pursuant to FAR 21.29(a)(1)(ii) in validation of the Swiss Federal Air Office (FAO) certification of compliance with the Federal Republic of Germany "Airworthiness Requirements for Sailplanes" Edition: February 1966, (Swiss Certification Basis) which were found to provide a level of safety equivalent to the aforementioned FAA certification basis. Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the glider for standard airworthiness certification. In addition the following equipment must be installed: 3 G25EU Equipment (Cont’d) 1. Instruments B4-PC11 B4-PC11A B4-PC11AF (non-cloud flying) (a) Airspeed indicator - - - marked as follows: Red Radial 130 kts 130 kts 130 kts (149 mph) (149 mph) (149 mph) Yellow Arc 130-78 kts (149-90 mph) 130-88 kts (149-101 mph) 130-88 kts (149-101 mph) Green Arc 78-36 kts (90-42 mph) 88-36 kts (101-42 mph) 88-36 kts (101-42 mph) (b) Altimeter - - - (c) Magnetic compass - - - 2. Additional Instruments req'd for cloud flying: (a) Turn and bank indicator - - - (b) Variometer - - - 3. Additional equipment req'd for acrobatics: (a) Accelerometer marked as follows Red Radials at +6.32g +7.0g +7.0g -4.32g -4.7g -4.7g (b) Pedal straps - - - 4. Swiss FAO "Approved Flight Manuals and Operating Manuals" for Model B4-PC11 Doc. No. 23-11-00-01473 for Model B4-PC11A Doc. No. 23-11-00-01574E for Model B4-PC11AF Doc. No. 23-11-00-01574E including Supplement Doc. No. 01580E for all Models Supplement Doc. No. 01533E 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 following placards must be installed in full view of the pilot: (a) "This glider must be operated in compliance with the Operating Limitations stated in the form of placards, markings, and manuals." (b) "Cloud flying: Permitted only when the following instruments are installed: (1) Airspeed Indicator (2) Altimeter (3) Magnetic Compass (4) Turn and Bank Indicator (5) Variometer" G25EU 4 NOTE 2 (Cont’d) (c) "Approved Aerobatic Maneuvers: Figures Entry Speed Expected Acceleration kts Lazy eight 92 +2g Steep spiral 65 +3g Looping positive 97 +3g Wing over 97-103 +2.5g Roll off the top 97 +3g (Immelmann) Climbing half roll 75 +2g Roll controlled 75-86 - Inverted flight 65 -1g Tail slide 97 +2.5g Looping negative, starting from 38 -2.5g normal attitude Looping negative, starting from inverted flight Spin Flick (snap) roll 108 See Flight Manual 70 -2.5g +4g" (d) "Night flying is prohibited." (e) B4-PC11 B4-PC11A and AF "Never exceed speed 130 kts 130 kts Maneuvering speed 78 kts 88 kts Airplane tow speed 78 kts 88 kts Auto-winch tow speed 70 kts 70 kts Dive brakes extended 130 kts 130 kts" (f) "Maximum weight: 770 lb." NOTE 3. Conversion from Model B4-PC11 to Model B4-PC11A in accordance with Pilatus Document No. 01575. The modification denoted in Pilatus Document No. 01582 is required to convert the Model B4 -PC11A to Model B4-PC11AF. NOTE 4. Information essential for the proper maintenance, inspection and repair of the glider is contained in the Pilatus Model B4-PC11 Maintenance and Repair Manual, Doc. No. 23- 11-00-01482. ...END...