EASA.SAS.A.085 Issue 01, 22/08/2007 PIK-20 E Page 1 of 15 European Aviation Safety Agency EASA SPECIFIC AIRWORTHINESS SPECIFICATION for PIK-20 E, PIK-20 E II as specified in Section I This Specific Airworthiness Specification is issued in accordance with Regulation (EC) 1592/2002 Article 15(1)(b). There is no valid Type Certificate for this aircraft type. The former type certificate holder was EIRI, Eino Riihelä Ky (former holder Eiriavion Oy (formerly Molino Oy)) List of effective Pages: Page 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 Issue 01 01 01 01 01 01 01 01 01 01 01 01 01 01 01 EASA.SAS.A.085 Issue 01, 22/08/2007 PIK-20 E CONTENT SECTION 1: Aircraft Design Definition Page 2 of 15 Variant 1 PIK-20 E 1.I General POWERED SAILPLANE SPECIFICATION No.P-7 This specification which is a part of the Type Certificate No.P-7 prescribes conditions and limitations under which the product, for which the Type Certificate was issued, meets the Airworthiness Requirements of Finland. Type Certificate Holder EIRI, Eino Riihelä Ky Kisällinkatu 8 FI-15170 Lahti Finland (Former Holder: Eiriavion Oy) 1.II Certification Basis OSTIV Airworthiness Requirements for Sailplanes, September 1976, Utility Category, Powered Sailplanes. German Airworthiness Requirements for Sailplanes and Powered Sailplanes (LFSM), October 1975, Utility Category, Powered Sailplanes. ICAO Annex 16, Third Edition, Chapter 6, July 1978. 1.III Technical Characteristics and Operational Limitations Model PIK-20 E, Approved December 27, 1978 Serial Nos. eligible 20203 to 20265 and 20267 to 20293 Maximum Weight 470 kg (1036 lbs) including water ballast Maximum weight of Non-Lifting Parts 328 kg (723 lbs) Water Ballast Two water ballast tanks at station 2270 mm (89.4 in). Tanks' capacity: S/N:S 20203 to 20246, 60 kg (132 lbs) each, S/N:S 20247 to 20265 and 20267 to 20293, 40 kg (88 lbs) each. Engine Manufacturer: Bombardier-Rotax GmbH, Gunskirchen, Austria Model: Rotax 501 Type: Retractable, aircooled, 500 ccm, two-stroke, two-cylinder, single-magneto ignition engine with 2:1 toothed belt transmission to the propeller Max rpm: 6800 Max continuous rpm: 6000 Max available take-off power: 31.7 kW (43 hp) at 6200 rpm and 100 km/h (62 mph, 54 knots) Fuel Two-stroke fuel. Normal automobile gasoline, min octane number 96, or aviation gasoline, AVGAS 100 LL, mixed with two-stroke super-quality oil. Mixture ratio 1:40 Propeller Manufacturer: Propellerwerk Hoffmann GmbH, Rosenheim, Federal Republic of Germany Model: H0 11* - 127 B 87 EASA.SAS.A.085 Issue 01, 22/08/2007 PIK-20 E Page 3 of 15 Manufacturer: Lentokonekorjaamo Pankkonen, Nummenkylä, Finland Model: EP P127/87 Diameter: 1270 mm (50 in) (both models) Type: Two-blade, wooden, fixed pitch propeller (both models) Control Surface Movements Up Down Flaps 12° ± 1° 16° ± 1° Ailerons +16° flap 13° +2° −1° 12,5° +2° −1° 0° flap -12° flap 12° +2° −1° 11° +2° −1° 11° +2° −1° 9,5° +2° −1° Aileron neutral position travels with flaps up 12° ±1° thru down 16° ±1° Elevator Up 20° ± 1° Down 20° ± 1° Rudder Right 33° ± 2° Left 33° ± 2° Airspeed Limits (I.A.S.) Never exceed (VNE) In rough air (VB) Maneuvering (VA) In aero tow (VT) *) In winch tow (VW) *) With engine extended 280 km/h 215 km/h 190 km/h 190 km/h 125 km/h 195 km/h (174 mph, 151 kts) (134 mph, 116 kts) (118 mph, 103 kts) (118 mph, 103 kts) (78 mph, 67 kts) (121 mph, 105 kts) Extending and retracting the engine 135 km/h (84 mph, 73 kts) *) Aerotow and winch tow are allowed only if the original tow hook kit is installed. Winch tow is allowed only with the tow hook at rear station 1850 mm (72,8 in), see note 4. With deflected flaps as follows: δf ° +16 +12...+2 km/h 155 215 0...-12 280 V mph 96 134 174 kts 84 116 151 C.G. Range 19 % to 44 % MAC, 2267 mm to 2443 mm (89.3 in to 96.2 in) Retracting the engine adds 16.5 kgm (1432 1b.in) to the mass moment. Empty Weight C.G. Range None EASA.SAS.A.085 Issue 01, 22/08/2007 PIK-20 E Page 4 of 15 Fuel Capacity S/N:s 20203 to 20214 and 20216 to 20220: Total 33 litres (8,72 gall U.S.), of which usable 32 litres (8,45 gall U.S.) S/N:s 20215, 20221 to 20265 and 20267 to 20293: Total 29 litres (7,66 gall U.S.) of which usable 28 litres (7,40 gall U.S.), see note 4. Fuel tank is at position 1900 mm (74.8 in). Datum Vertical plane 2113 mm (83.19 in) forwards of the first wing fitting tube forward surface. Levelling Means Slope of rear top surface of fuselage between stations 4500 mm (177.2 in) and 5500 mm (216.5 in), 1000 to 28 tail down No. of Seats One adjustable seat, pilot’s C.G. range 1420 mm to 1500 mm (56.0 in. to 59.0 in) Fixed Ballast 1. Nose station 255 mm (10.0 in), max 10 kg (22 lbs) 2. Tail wheel spring station 6100 mm (240.2 in), max 3 kg (6.6 lbs) 3. In addition on S/N:s 20203 to 20227: Battery compartment station 3730 mm (146,8 in), max 11 kg (24 lbs) including battery Ballast attaching by bolts and nuts or inserts. Rated Load on Winch and Aero Tow 6000 N (1320 lbs) 1.IV Operating and Service Instructions Required Equipment The basic required equipment as prescribed in the application airworthiness regulations (see Certification Basis) must be installed in the sailplane for standard airworthiness certification. In addition the following equipment must be installed: 1. Basic instruments and equipment (a) Airspeed indicator (b) Altimeter (c) Magnetic compass (d) Ball type slip indicator (e) Tachometer (f) Fuel quantity indicator (g) Cylinder head temperature indicator (h) Engine hourmeter (i) Seat belts (j) Seat cushion (k) Mirror for checking the propeller position 2. Additional instruments for cloud flying (a) Turn indicator (b) Variometer 3. PIK-20 E Flight Manual approved by the National Board of Aviation, Finland. Inspections, Maintenance, Repairs and Repainting must be accomplished in accordance with EIRI, Eino Riihelä Ky’s PIK-20 E Flight Manual and Service Manual and PIK-20 E Repair Manual. Major repairs must be performed in accordance with repair methods approved by EIRI, Eino Riihelä Ky. EASA.SAS.A.085 Issue 01, 22/08/2007 PIK-20 E Page 5 of 15 1.V Notes, including serial number applicability Note 1. The following placards and markings must be displayed in a conspicuous place on the sailplane: a. Maximum Speeds, Weights and Operational Limits i. S/N:s 20203 to 20214 and 20216 to 20220, same as the placard in ii), but without the winch tow limit. ii. S/N:s 20215, 20221 to 20265 and 20267 to 20293: Maximum speed In calm weather (VNE) In rough air (VB) Maneuvering (VA) 280 km/h 215 km/h 190 km/h 174 mph 151 kts 134 mph 116 kts 118 mph 103 kts On aero tow (VT) 190 km/h 118 mph 103 kts On winch tow (VW) With engine extended 125 km/h 195 km/h 78 mph 67 kts 121 mph 105 kts Extending and retracting the engine 135 km/h 84 mph 73 kts Weights Gross weight 470 kg (1036 lbs) including water ballast. If the pilot's weight with the parachute is below 70 kg (154 lbs) ballast weight must be installed in the nose (see Flight Manual and Weight and Balance Record). Operational Limitations This sailplane must be operated in compliance with the operating limits as stated in the form of markings, placards and in the PIK-20 E Flight Manual. All acrobatic maneuvers including spins must be accomplished in accordance with PIK-20 E Flight Manual NO SMOKING EASA.SAS.A.085 Issue 01, 22/08/2007 b. PIK-20 E Page 6 of 15 Maximum airspeed with deflected flaps δf ° +16 +12...+2 0...-12 km/h 155 215 280 V mph 96 134 174 kts 84 116 151 c. Other placards and markings Adjacent to tow coupling . . . . . . . . . . . RATED LOAD 6000 N (1320 lbs) Above the main wheel . . . . . . . . . . . . . . . . . . . . . . . . . 2.5 bar (35 psi) Adjacent to static pressure entry on fuselage skin . . . . . . . . .STATIC PRESSURE KEEP CLEAR Adjacent to oxygen control valve (if installed) . . . . . . . . . . . . . . . . . . . . . . DURATION TABLE On fuselage nose (inside) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .BALLAST Near the luggage compartment . . . . . . . . . . MAX RATED LOAD 15 kg (33 lbs) Near the fuel filler opening S/N:s 20203 to 20214 and 20216 to 20220: 2-STROKE FUEL OIL MIXTURE RATIO 1:40 MIN 96 OCTANE (RON) SUPER GASOLINE OR AVGAS 100 LL, USABLE CAPACITY 32 L. S/N:s 20215 and 20221 and up: same as above but USABLE CAPACITY 28 L Near the fuel valve . . . . . . . . . . . . . . . . . . . . . . . . . . . .ON. . . OFF Near the draining valve (S/N:s 20203 to 20214 and 20216 to 20220) . . . . . . . . . . . . . . . . . . . . . . . . .DRAIN. . . OFF Near the fuel tank vent (S/N:s 20215 and 20221 and up) . . . . . . . . . . . . . . . . . . . . VENT, KEEP CLEAN The controls or handles for tow coupling release, canopy opening and jettisoning, landing gear, flaps, airbrakes, trim, pedals, ventilation, water ballast draining, engine doors, engine retracting mechanism, fuel cock and engine controls and switches must be equipped with unmistakable symbols or text placards. The flight speed limitations must be marked on the air speed indicator in accordance with the Flight Manual. Engine gauges must be marked in accordance with the Flight Manual. EASA.SAS.A.085 Issue 01, 22/08/2007 PIK-20 E Page 7 of 15 Note 2. Inspections, Maintenance, Repairs and Repainting must be accomplished in accordance with EIRI, Eino Riihelä Ky’s PIK-20 E Flight Manual and Service Manual and PIK-20 E Repair Manual. Note 3. Major repairs must be performed in accordance with repair methods approved by EIRI, Eino Riihelä Ky. Note 4. On S/N:s 20215 and 20221 and up, the tow hook has been moved backwards to facilitate winch tow operations. Simultaneously the capacity of the fuel tank has been decreased and its vent and drain systems have been modified. Modification of S/N:s 20203 to 20214 and 20216 to 20220 is feasible in accordance with EIRI, Eino Riihelä Ky's drawings No:s 0-20E-51-100a, 120E-31-001a and 3-20E-21-200-26a. EASA.SAS.A.085 Issue 01, 22/08/2007 PIK-20 E Page 8 of 15 Variant 2 PIK-20E II 2.I General POWERED SAILPLANE SPECIFICATION No.P-7 This specification which is a part of the Type Certificate No.P-7 prescribes conditions and limitations under which the product, for which the Type Certificate was issued, meets the Airworthiness Requirements of Finland. Type Certificate Holder EIRI, Eino Riihelä Ky Kisällinkatu 8 FI-15170 Lahti Finland (Formerly Holder: Eiriavion Oy) 2.II Certification Basis OSTIV Airworthiness Requirements for Sailplanes, September 1976, Utility Category, Powered Sailplanes. German Airworthiness Requirements for Sailplanes and Powered Sailplanes (LFSM), October 1975, Utility Category, Powered Sailplanes. ICAO Annex 16, Third Edition, Chapter 6, July 1978. 2.III Technical Characteristics and Operational Limitations Model PIK-20 E II, Approved August 22, 1980 Serial Nos. eligible 20266, 20294 and up Maximum Weight 470 kg (1036 lbs) including water ballast Maximum weight of Non-Lifting Parts 328 kg (723 lbs) Water Ballast Two water ballast tanks at station 2270 mm (89.4 in). Tanks' capacity 40 kg (88 lbs) each. Engine Manufacturer: Bombardier-Rotax GmbH, Gunskirchen, Austria Model: Rotax 505 Type: Retractable, aircooled, 500 ccm, two-stroke, two-cylinder, dual-magneto ignition engine with 2:1 toothed belt transmission to the propeller Max rpm: 6800 Max continuous rpm: 6000 Max available take-off power: 31,7 kW (43 hp) at 6200 rpm and 100 km/h (62 mph, 54 knots) Fuel Two-stroke fuel. Normal automobile gasoline, min octane number 96, or aviation gasoline, AVGAS 100 LL, mixed with two-stroke super-quality oil. Mixture ratio 1:40 Propeller Manufacturer: Propellerwerk Hoffmann GmbH, Rosenheim, Federal Republic of Germany Model: H0 11* - 127 B 87 Manufacturer: Lentokonekorjaamo Pankkonen, Nummenkylä, Finland Model: EP P127/87 Diameter: 1270 mm (50 in) (both models) Type: Two-blade, wooden, fixed pitch propeller (both models) EASA.SAS.A.085 Issue 01, 22/08/2007 PIK-20 E Page 9 of 15 Control Surface Movements Up Down Flaps 12° ± 1° 16° ± 1° Ailerons +16° flap 13° +2° −1° 12,5° +2° −1° 0° flap 12° +2° −1° 11° +2° −1° -12° flap 11° +2° −1° 9,5° +2° −1° Aileron neutral position travels with flaps up 12° ±1° thru down 16° ±1° Elevator Up 20° ± 1° Down 20° ± 1° Rudder Right 33° ± 2° Left 33° ± 2° Airspeed Limits (I.A.S.) Never exceed (VNE) In rough air (VB) 280 km/h 215 km/h (174 mph, 151 kts) (134 mph, 116 kts) Maneuvering (VA) In aero tow (VT) *) In winch tow (VW) *) 190 km/h 190 km/h 125 km/h (118 mph, 103 kts) (118 mph, 103 kts) (78 mph, 67 kts) With engine extended 195 km/h (121 mph, 105 kts) Extending and retracting the engine 135 km/h (84 mph, 73 kts) *) Aerotow and winch tow are allowed only if the original tow hook kit is installed. With deflected flaps as follows: δf ° +16 +12...+2 km/h 155 215 0...-12 280 V mph 96 134 174 kts 84 116 151 C.G. Range 19 % to 44 % MAC, 2267 mm to 2443 mm (89.3 in to 96.2 in) Retracting the engine adds 16.5 kgm (1432 1b.in) to the mass moment. Empty Weight C.G. Range None Fuel Capacity Total 29 litres (7,66 gall U.S.) of which usable 28 litres (7,40 gall U.S.) Fuel tank is at position 1900 mm (74.8 in). Datum Vertical plane 2113 mm (83.19 in) forwards of the first wing fitting tube forward surface. EASA.SAS.A.085 Issue 01, 22/08/2007 PIK-20 E Page 10 of 15 Levelling Means Slope of rear top surface of fuselage between stations 4500 mm (177.2 in) and 5500 mm (216.5 in), 1000 to 28 tail down No. of Seats One adjustable seat, pilot’s C.G. range 1420 mm to 1500 mm (56.0 in. to 59.0 in) Fixed Ballast 1. Nose station 255 mm (10.0 in), max 10 kg (22 lbs) 2. Tail wheel spring station 6100 mm (240.2 in), max 3 kg (6.6 lbs) Ballast attaching by bolts and nuts or inserts. Rated Load on Winch and Aero Tow 6000 N (1320 lbs) 2.IV Operating and Service Instructions Required Equipment The basic required equipment as prescribed in the application airworthiness regulations (see Certification Basis) must be installed in the sailplane for standard airworthiness certification. In addition the following equipment must be installed: 1. Basic instruments and equipment (a) Airspeed indicator (b) Altimeter (c) Magnetic compass (d) Ball type slip indicator (e) Tachometer (f) Fuel quantity indicator (g) Cylinder head temperature indicator (h) Engine hourmeter (i) Seat belts (j) Seat cushion (k) Mirror for checking the propeller position 2. Additional instruments for cloud flying (a) Turn indicator (b) Variometer 3. PIK-20 E II Flight Manual approved by the National Board of Aviation, Finland. Inspections, Maintenance, Repairs and Repainting must be accomplished in accordance with EIRI, Eino Riihelä Ky’s PIK-20 E II Flight Manual and Service Manual and PIK-20 E Repair Manual. Major repairs must be performed in accordance with repair methods approved by EIRI, Eino Riihelä Ky. EASA.SAS.A.085 Issue 01, 22/08/2007 PIK-20 E Page 11 of 15 2.V Notes, including serial number applicability Note 1. The following placards and markings must be displayed in a conspicuous place on the sailplane: a. Maximum Speeds, Weights and Operational Limits Maximum speed In calm weather (VNE) In rough air (VB) 280 km/h 215 km/h 174 mph 134 mph 151 kts 116 kts Maneuvering (VA) In aero tow (VT) In winch tow (VW) With engine extended 190 km/h 190 km/h 125 km/h 195 km/h 118 mph 118 mph 78 mph 121 mph 103 kts 103 kts 67 kts 105 kts Extending and retracting the engine 135 km/h 84 mph 73 kts Weights Gross weight 470 kg (1036 lbs) including water ballast. If the pilot's weight with the parachute is below 70 kg (154 lbs) ballast weight must be installed in the nose (see Flight Manual and Weight and Balance Record). Operational Limitations This sailplane must be operated in compliance with the operating limits as stated in the form of markings, placards and in the PIK-20 E II Flight Manual. All acrobatic maneuvers including spins must be accomplished in accordance with PIK-20 E II Flight Manual NO SMOKING EASA.SAS.A.085 Issue 01, 22/08/2007 b. PIK-20 E Page 12 of 15 Maximum airspeed with deflected flaps δf ° +16 +12...+2 0...-12 km/h 155 215 280 V mph 96 134 174 kts 84 116 151 c. Other placards and markings Adjacent to tow coupling . . . . . . . . . . RATED LOAD 6000 N (1320 lbs) Above the main wheel . . . . . . . . . . . . . . . . . . . . . . . . 2.5 bar (35 psi) Adjacent to static pressure entry on fuselage skin . . . . . . . .STATIC PRESSURE KEEP CLEAR Adjacent to oxygen control valve (if installed) . . . . . . . . . . . . . . . . . . . . DURATION TABLE On fuselage nose (inside) . . . . . . . . . . . . . . . . . . . . . . . . . . . . .BALLAST Near the luggage compartment . . . . . . . . . MAX RATED LOAD 15 kg (33 lbs) Near the fuel filler opening 2-STROKE FUEL OIL MIXTURE RATIO 1:40 MIN 96 OCTANE (RON) SUPER GASOLINE OR AVGAS 100 LL, USABLE CAPACITY 28 L. Near the fuel valve . . . . . . . . . . . . . . . . . . . . . . . . . . . .ON. . . OFF Near the fuel tank vent . . . . . . . . . . . . . . . . . . . . VENT, KEEP CLEAN The controls or handles for tow coupling release, canopy opening and jettisoning, landing gear, flaps, airbrakes, trim, pedals, ventilation, water ballast draining, engine doors, engine retracting mechanism, fuel cock and engine controls and switches must be equipped with unmistakable symbols or text placards. The flight speed limitations must be marked on the air speed indicator in accordance with the Flight Manual. Engine gauges must be marked in accordance with the Flight Manual. Note 2. Inspections, Maintenance, Repairs and Repainting must be accomplished in accordance with EIRI, Eino Riihelä Ky’s PIK-20 E II Flight Manual and Service Manual and PIK-20 E Repair Manual. Note 3. Major repairs must be performed in accordance with repair methods approved by EIRI, Eino Riihelä Ky. Note 4. On S/N:s 20215 and 20221 and up, the tow hook has been moved backwards to facilitate winch tow operations. Simultaneously the capacity of the fuel tank has been decreased and its vent and drain systems have been modified. EASA.SAS.A.085 Issue 01, 22/08/2007 PIK-20 E SECTION 2: Airworthiness Directives The following ADs and additional data can be found at http://www.ilmailuhallinto.fi/PIK-20_support Page 13 of 15 Variant 1 PIK-20E AD 746 1200 1737-1 Date Heading 1.8.1977 Safety belts (sn: all) 9.7.1979 Special requirement for the United Kingdom (sn: 20213, 20214, 20217, 20218) 17.12.1979 Chafe of fuel tank (sn: 20215, 20221-20233, 20235) 14.2.1980 Flughandbuch, Betriebs- und Wartungshandbuch 17.3.1980 Insufficient fuel flow (sn: 20103-20259) 17.3.1980 Flight Manual 16.4.1980 Service Manual 14.10.1980 Saving battery power when soaring (sn: 20213, 20214, 20217-20265, 20267-20293) 6.11.1980 Warning system for the open engine doors (sn: 20203-20293) 10.11.1980 Lubricating and removing the propeller drive gear bearings (sn: all) 18.11.1980 Huolto-ohjekirja 20.11.1980 Auxiliary spring for safety cable (sn: 20203-20256) 24.11.1980 Transfer of cylinder head temperature (CHT) sensor (sn: 20203-20248) 31.10.1983 Inspection of the fuel system inlets (sn: all) 15.10.1990 Propeller hub mounting (sn: all) Ref. M15 M20E-2 M20E-3 M20E-4 H20E-1a H20E-2 H20E-3 H20E-4 H20E-5 LTA90-239 EASA.SAS.A.085 Issue 01, 22/08/2007 PIK-20 E Page 14 of 15 SECTION 3: Occurrence Reporting The Specific Airworthiness Specification may be used as a basis for the issue of a Restricted Certificate of Airworthiness in accordance with 21A.173(b)(2) under the following conditions: a) The holder of a Restricted Certificate of Airworthiness based on this Specific Airworthiness Specification shall report to the State of Registry all information related to occurrences associated with the operation of the aircraft which affects or could affect the safety of operation1. b) Such reports shall be despatched within 72 hours of the time when the occurrence was identified unless exceptional circumstances prevent this. c) The State of Registry shall forward the information received under (a) to the Agency when it relates to failures, malfunctions, defects or other occurrences which cause or might cause adverse effects on the continuing airworthiness of the aircraft. 1 AMC 20-8 contains guidance describing the occurrences which are to be reported EASA.SAS.A.085 Issue 01, 22/08/2007 PIK-20 E Page 15 of 15 SECTION 4: Other Limitations [This is reserved for EASA use. Additional limitations may be necessary, as found necessary to reduce the risks associated with deficiencies in the reporting chain in Section 3. These may be based on the expectation that specific maintenance may be required due to aircraft ageing, etc.]