TCDS G31EU

Page No. 1 2 3 4 5 6 7 Rev. No. 6 6 6 6 5 5 5 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION G31EU Revision 6 EIRIAVION OY PIK-20 PIK-20B PIK-20D March 1, 2012 TYPE CERTIFICATE DATA SHEET NO. G31EU This data sheet which is a part of the Type Certificate No. G31EU 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 EIRIAVION OY (formerly MOLINO OY) 38800 Jami jarvi Finland Type Certificate Ownership Record (1) This TC was considered not valid by the state of design on August 22, 2007, and has been replaced by European Aviation Safety Agency (EASA) Specific Airworthiness Specification (SAS) numbers EASA.SAS.A.023, (for the models PIK-20 and PIK-20B) and EASA.SAS.A.024 (for the model PIK - 20D), issued August 22, 2007. 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 PIK-20, approved June 20, 1975 Airspeed Limits (I.A.S.) Never Exceed (VNE) 262 km/h 163 mph 142 kts Maximum speed in rough air (VB) 242 km/h 150 mph 131 kts Maneuvering (VA) 185 km/h 115 mph 100 kts On aerotow (VT) 185 km/h 115 mph 100 kts On winch tow (VW) 125 km/h 77 mph 67 kts Flaps-airbrakes deflected, 45° or less 262 km/h 163 mph 142 kts Flaps-airbrakes deflected, more than 45° 200 km/h 124 mph 108 kts C.G. Range 20% to 40% MAC; 82.1 in. to 87.6 in. (2085 mm to 2225mm) aft of datum. Empty Weight c.g. None. Datum 1900 mm (74.8 in.) forward of wing leading edge at wing root rib Leveling Means Slope of rear top surface of fusela ge between stations 140 in. and 180 in. 1000 to 28 tail down. (See Flight Manual, Service Manual Section 2). Maximum Weight 400 kg (880 lb) incl uding water ballast. (See Note 8.) No. of Seats One adjustable seat, pilot's C.G. range 1400 mm to 1460 mm; 55.2 in. to 57.5 in. Ballast, Fixed Station 230 mm; 9 in. Max (See Flight Manual) Max 10 kg (22 lb.) lead plates, attaching by bolts and nuts or inserts. G31EU 2 Water Ballast Two water ballast ta nks at station 2130 mm (83.9 in.), each 40 kg (88-lb.) + 10° Control Surface Movements Flaps-airbrakes Up 8° ± 1° Down 80° - 5° Ailerons Up 25° ± 2° Down 16° ± 2° Elevator Up 20° ± 1° Down 20° ± 1° Rudder Right 27° ± 2° Left 27° ± 2° Rated Load on Winch and 500 kg (1100 lb.) Aero. Tow Serial Nos. Eligible 20004 thru 20067, 20074, 20076, 20077, and 20080 (See Import Requirements; Notes 6, 7, 8, and 9). Only those aircraft serials holding a standard airworthiness certificate issued prior to March 1, 2012 are eligible. II. Model PIK-20B, approved January 15, 1976 Airspeed Limits (I.A.S.) Never exceed (VNE) 262 km/h 163 mph 142 kts Maximum speed in rough air (VB) 242 km/h 150 mph 131 kts Maneuvering (VA) 185 km/h 115 mph 100 kts On Aerotow (VT) 185 km/h 115 mph 100 kts On winch tow (VW) 125 km/h 77 mph 67 kts Flaps-airbrakes deflected, 45° or less 262 km/h 163 mph 142 kts Flaps-airbrakes deflected, more than 45° 200 km/h 124 mph 108 kts C.G. Range 20% to 40% MAC; 82.1 in. to 87.6 in. (2085 mm to 2225 mm) aft of datum. Empty Weight C.G. Range None Datum 1900 mm (74.8 in.) forward of wi ng leading edge at wing root rib. Leveling Means Slope of rear top surface of fusela ge between stations 140 in. and 180 in. 1000 to 28 tail down. (See Flight Manual, Service Manual Section 2). Maximum Weight 450 kg (990 lb .) including water ballast. No. of Seats One adjustable seat, pilot's C.G. range. 1400 mm to 1460 mm; 55.2 in. to 57.5 in. Fixed Ballast Station 230 mm; 9 in. (See Flight Manual) Max 10 kg (22 lb.) lead plates, attaching by bolts and nuts or inserts. Water Ballast Two water ballast tanks at station 2130 mm (83.9 in.) each 70 kg (154 lb.) Control Surface Movements Flaps-airbrakes Up 9° ±2° Down 80°+ 10° - 5° Ailerons Up 21°-24°±2° Down 21° -17°±2° Aileron neutral position travels with flaps- airbrakes Up 9° ± 2° thru Down 9° ± 2° Elevator Up 20°± 1° Down 20°± 1° Rudder Right 27°±2° Left 27°±2° Rated Load on Winch and Aero Tow 500 kg (1100 lb.) 3 G31EU Serial Nos. Eligible 20068 and up, except 20074, 20076, 20077, and 20080 (See Import Requirements; Notes 7, 8, 9, and 10). Only those aircraft serials holding a standard airworthiness certificate issued prior to March 1, 2012 are eligible. II. Model PIK-20D, approved January 13, 1977 Airspeed Limits (I.A.S.) Never exceed (VNE) 292 km/h 181 mph 158 kts Maximum speed in rough air (VB) (with full water ballast or maximum gross weight) 240 km/h 149 mph 130 kts (without water ballast) 200 km/h 124 mph 108 kts (airspeed limit changes linearly depending on amount of water ballast) Maneuvering (VA) 190 km/h 118 mph 103 kts On aerotow (VT) 190 km/h 118 mph 103 kts On winch tow (VW) 125 km/h 77 mph 67 kts Flaps down (VF) 150 km/h 93 mph 81 kts C.G. Range 20% to 40% MAC; 82.1 in. to 87.6 in. (2085 mm to 2225 mm) aft of datum. Empty Weight C.G. Range None. Datum 1900 mm (74.8 in.) forward of wi ng leading edge at wing root rib. Leveling Means Slope of rear top surface of fu selage between stations 3500 mm (140 in.) and 4500 mm (180 in.) 1000 to 28 tail down. (See F light Manual, Service Manual Section 2.) Maximum Weight 450 kg (990 lb .) including water ballast. No. of Seats One adjustable seat, pilot's c. g. range 1400 mm to 1460 mm (55.2 in. to 57.5 in.) Fixed Ballast Station 230 mm (9 in.) (See Flight Manual) Max 10 kg (22 lb.) lead plates, attaching by bolts and nuts or inserts. Water Ballast Two water ballast tanks at station 2130 mm (83.9 in.) each 70 kg (154 lb.) Control Surface Movements Up Down Flaps 12°±1° 16°±1° +16° Flap 13°±2° 12.5°±2° Ailerons (0° Flap) 12°±2° 11°±2° (-12° Flap) 11°±2° 9.5°±2° (Aileron neutral position travels with flaps 1° 1° up 12° ± 1° thru down (6° ±1°) Elevator 20° ±1° 20°±1° Rudder Right and Left 33° ±2° Rated Load on Winch and Aero Tow 500 kg (1100 lb.) Serial Nos. Eligible 20504 and up. The National Board of Aviation of Finla nd (NBA) Certificate of Airworthiness for Export endorsed as noted below under "Im port Requirements" must be submitted for each individual glider for which applicati on for certification of airworthiness is made. (See Import Requirements; Notes 7, 8, 9, and 10) Only those aircraft serials holding a standard airworthiness certificate issued prior to March 1, 2012 are eligible. G31EU 4 Data Pertinent to all Models Certification Basis FAR 21.23 and FA R 21.29 effective February 1, 1965. Type Certificate No. G31EU Issued June 20, 1975. Date of Application for Type Certificate: June 24, 1974. Validation Basis Type Certificate No. G31EU issued in accordance to FAR 21.29(a)(1) in validation of the National Board of Aviation (NBA) of Finland certification of compliance with the International Scientific and Technical Or ganization for Sailplanes (OSTIV) airworthiness requirements for sailpla nes dated September 1971 utility category for gliders and sailplanes. Required Equipment. The basic require d equipment as prescribed in the applicable airworthiness regulations (as listed in Flight Manual Service Section 2) must be installed in the glider for standard airworthiness certification. In addition th e following equipment must be installed: (See NOTE 11) 1. Instruments (non-cloud flying) (a) Airspeed indicator (b) Altimeter (c) Magnetic compass 2. Additional instruments for cloud flying (a) Turn and slip indicator (b) Variometer 3. An accelerometer for aerobatic flying 4. PIK-20, PIK-20B, or PIK-20D Fli ght Manual (containing Flight and Service Manual approved by the Nationa l Board of Aviation, Finland. The requirements for instruments are approve d by National Board of Aviation in Finland according to the Master Equipment List of all PIK-20 models, dated January 20, 1977. 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 repres entative of the National Board of Aviation of Finland (NBA), containing the following st atement: "The gilder covered by this certificate has been examined, tested, and found to conform to the type design approved under FAA Type Certificate G31EU a nd is in condition for safe operation". NOTE 1: Weight: Current weight and balance report includi ng list of equipment in certificated empty weight, and loading instructions when necessary must be provided at the time of original certification. NOTE 2: A. The following placards and markings must be displayed in full view of the pilot: Applicable to PIK-20 and PIK-20B (1) Maximum airspeed k m / h mph kts In calm weather (VNE) 262 163 142 In turbulent weather (VB) 242 150 131 Maneuvering (VA) 185 115 100 On aerotow (VT) 185 115 100 On winch tow (VW) 125 77 67 Flaps-airbrakes deflected, 45° or less 262 163 142 Flaps-airbrakes deflected, more than 45° 200 124 108 5 G31EU NOTE 2 (cont’d) Applicable to PIK-20D Maximum airspeed In calm weather (VNE) 292 181 158 In rough air (VB) With full water ballast or 450 kg (990 lb.) flying weight 240 149 130 Without water ballast 200 124 108 Maneuvering (VA) 190 118 103 In aero tow (VT) 190 118 103 On winch tow (VW) 125 77 67 Down deflected flaps (VF) 150 93 81 (2) Weights P I K - 2 0 PIK-20B & 20D Gross weight including water ballast 400 kg (880 lb.) 450 kg (990 lb.) If the pilot's weight with the parachute is belo w 75 kg (165 lb.) ballast weight must be installed in the nose (see Flight Manual and Weight and Balance Data Sheet) (3) Preflight check Applicable to PIK-20 and PIK-20B Tail dolly removed Parachute secured Seat and pedals adjusted Safety belts secured Canopy locked Altimeter set Flaps-airbrakes in takeoff position(8° up) Trim set for takeoff Tow rope coupled in Controls free Applicable to PIK-20D Tail dolly removed Barograph (if installed) on Loading and ballast checked Parachute secured Seat and rudder pedals adjusted Safety belts secured Canopy locked Altimeter set Electrical instruments on Flaps in takeoff position Airbrakes closed and locked Trim Set for takeoff Tow rope coupled on Controls free (4) Before landing P I K - 2 0 PIK-20B PIK-20D Water ballast - drained drained Landing gear down down down Flaps as desired as desired 12°...16° down Trim - - set for landing G31EU 6 NOTE 2 (cont’d) (5) Operating limitations This sailplane must be operated in compliance with the operating limitations as stated in the form of markings, placards and Flight Manual. Cloud flying is only permitted when the following instruments are installed: airspeed indicator, altimeter, magnetic compass, turn and slip indicator and variometer. Approved aerobatic maneuvers, maximum entry speeds and maximum load factors: Applicable to PIK-20 and PIK-20B Maneuver Entry speed k m / h mph kts Steep turn 185 115 100 Looping 185 115 100 Lazy eight 185 115 100 Chandelle 185 115 100 Stall turn 185 115 100 Spin Use slow deceleration Stall (except whip stall) Use slow deceleration Maximum load factors +5.3 -2.65 Maximum positive load factor, flaps-ai rbrakes deflected more than 45° +4.0 Aerobatic maneuvers prohibited with flaps-airbrakes deflected more than 45° All aerobatic maneuvers including spins must be accomplished in accordance with the approved PIK-20 or PIK-20B Flight Manual. Accelerometer must be installed. Night flying prohibited. Applicable to PIK-20D Refer to PIK-20D Airplane Flight Manual fo r approved aerobatic maneuvers, flight load factors and related operating limitations. Night flying prohibited. B. Other Markings or Placards Applicable to PIK-20, PIK-20B, PIK-20D Near the tow coupling Rated load 500 kg (1100 lb.) Above the main wheel 2.5 Aty (35 p.s.i.) Above the tail wheel 2.0 Aty (28 p.s.i.) Applicable to PIK-20D On fuselage nose (inside) "BALLAST" Adjacent to static pressure entry on fuselage skin "STATIC PRESSURE KEEP CLEAR" On rudder, elevator and flaps "DO NOT PUSH" Adjacent to oxygen control valve (if installed) "DURATION TABLE" NOTE 2: The controls or handles for tow coupling re lease, canopy opening and jettisoning, landing gear, flaps airbrakes, trim tab, pedals, ventilating and wate r ballast draining must be equipped with unmistakable symbol or text placards. The flight speed limitations must be marked on the dial of the airspeed indicator in accordance with the Flight Manual. The load factor limitations must be mark ed on the accelerometer with red radial lines. 7 G31EU NOTE 3: Inspections, Maintenance, Repairs and Repainti ng must be accomplished in accordance with manufacturer's PIK-20, PIK-20B, or PIK-20D Flight Manual, Service Manual Section 2, and Repair Manual. NOTE 4: For painting exterior surfaces use only two component paints with ultra-violet protection as listed in Repair Manual. NOTE 5: Major repairs must be performed in accordance with manufacturer's repair methods and approved by NBA is not covered in Repair Manual. NOTE 6: PIK-20 Serial Numbers 20004 thru 200011 are eligible for Standard Airworthiness Certification only if the manufacturer's Service Bulletins M1 and M3 are accomplished. NOTE 7: Data plate for PIK-20 sailplane must be insta lled in accordance with manufacturer's Service Bulletin M2. NOTE 8: Sailplanes S/Ns 20004 thru 20067, 20074, 20076, 20077, and 20080 are eligible for a maximum weight of 450 kg (990 lb.) when enlarged water ballast tanks are installed per manufacturer's PIK-20 drawings Nos. 704B and 704-05. NOTE 9: Aileron control system of PIK-20 sailp lanes S/N 20004 thru 20067, 20074, 20076, 20077, and 20080 may be modified to PIK-20B control surface movements per manufacturer's Service Bulletin M9. NOTE 10: PIK-20B sailplanes which bear the letter "C" af ter serial number (E.G. 20127C) have wing spar flanges which incorporate carbon fiber elem ents as the reinforcing agent and as such eligible for standard airworthiness certification based on the ba sic serial number effectivity noted hereon. NOTE 11: For required instrument installati on, refer to Master Equipment List (Instruments) which contains a list of the installed instruments approved during initial type cer tification testing, and information concerning acceptable alternate replacement instruments. NOTE 12: Tailplane and rudder of sailplanes S/Ns 20566 a nd up have been modified according to manufacturer's Drawings Nos. 0-20D-52-100a, 1-20D-53-100b, 1-20D-58-100b and 1-20D-59-100c. ...END...