TCDS A68EU

Page No. 1 2 3 4 5 Rev. No. 1 - 1 - - DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A68EU Revision 1 WSK “PZL-MIELEC” OBR PZL M20 03 March 1, 2012 TYPE CERTIFICATE DATA SHEET NO. A68EU This data sheet, which is a part of Type Certificate No. A68EU 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: WSK PZL MIELEC and OBR SK MIELEC U1. Wojska Polskiego 3 39-301 MIELEC POLAND Type Certificate Ownership Record (1) This TC was considered not valid by the state of design on March 27, 2007, and has been replaced by European Aviation Safety Agency (EASA) Specific Airworthiness Specification (SAS) number EASA.SAS.A.064, issued March 27, 2007.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 PZL M20 03 “MEWA” (Normal Category) Approved July 19, 1993 Aircraft manufactured from Polish-made assemblies (fuselage, wings, empennage, landing gear, control systems), from PA 34-200T SENECA II aircraft assemblie s (electro-navigation equipment, wing spar, accessories, hydraulic, - pneumatic, heating - and ventilation systems), and power ed by L/TSIO 360 KB Continental engines. Engines Teledyne Continental TSIO-360-KB (left side) Teledyne Continental LTSIO-360-KB (right side) with fuel injection, turbocharged. Rotation as viewed from the rear: TSIO-360-KB CW L/TSIO-360-KB CCW Fuel 100/100 LL minimum grade gasoline Engine Limits Takeoff (5 minutes), 2800 RP M and 40 in.Hg. Manifold Pressure (220 HP) Maximum continuous, 2600 RPM and 40 in .Hg. Manifold Pressure (200 HP) A68EU 2 Propeller and propeller limits Right Engine Hartze ll Hub Model BHC-C2YF-2CLKUF, Blade Model FJC 8459-8R, with Hartzell E-3-7L governor. Left Engine Hartzell Hub M odel BHC-C2YF-2CKUF, Blade Model FC 8459 - 8R, Hartzell Governor Model E3-7 (or Model E8-7L with synchrophasing system installed). Pitch Setting at 30” of Propeller Diameter : Low 12.9   0.2 High 80  to 81.5 Diameter: Two blade (constant speed) not over 76 in., not under 75 in. Airspeed Limits V NE - 195 Knots (CS) V NO - 165 Knots (CAS) V A - 138 Knots (CAS) for 4570 lbs weight - 122 Knots (CAS) for 3068 lbs weight V LE - 130 Knots (CAS) V LO - 130 Knots (CAS) Landing Gear Extended - 109 Knots (CAS) Landing Gear Retracted V FE - 109 Knots (CAS) Flaps Deflected 40  V MC - 69 Knots (CAS) Maneuvering speed (Va) is reduced as the airplane weight decreased Straight line interpolation is used for intermediate weight. Center of Gravity (C.G.) Range (in) (+90.6) to (+94.6) at 4570 lbs (+86.7) to (+94.6) at 4250 lbs ( 82.0) to (+94.6) at 3400 lbs Straight line variation between points given. Moment due to retracting landing gear (-32 in. lbs) Empty Weight C.G. Range None Datum 78.4 inches forward of wing leading edge at the inboard edge of the inboard fuel tank (outboard of the engine), with the airp lane in leveling position and the landing gear extended. Leveling Means With airplane on scales, block main gear oleo pistons in the fully extended position. Level airplane by deflating nose wheel tire (level point is a horizontal line between two screws on left side of fu selage below pilot’s window). Maximum Weight Takeoff 4570 lbs Landing 4342 lbs Zerofuel 4000 lbs All weight over 4000 lbs. must be fuel. Minimum Crew One (1) pilot Number of Seats 7 (2 at + 85.5; 3 at + 118.1; 2 at + 157.6) 6 (2 at + 85.5; 2* at + 119.1; 2 at + 157.6) 5**(2 at + 85.5; 1 at 119.9 (1 patient or 1 incubator on a stretcher at +133.8) * Optional equipment - Club Seats ** Allowable loading condition with the airplane in ambulance version. Maximum Baggage 200 lb. (100 lb at +22.5, 100 lb at +178.7) Fuel Capacity 98 gal. (2 wing tanks) at +93.6 (93 gal. usable) Optional Installation: 128 gal. (2 wing tanks) at +93.6 (123 gal. usable) See NOTE 1 on fuel system. Oil Capacity 8 qts. per engine (5 qts. per engine usable) See NOTE 1 for additional data on oil system. 3 A68EU Maximum Operating Altitude 25,000 feet Control Surface Movements Ailerons Up 35  2 Down 20  2 Stabilator Up 12.5  0 -1 Down 7.5  1 Stabilator Trim Tab Up 6.5  1 (Stabilator Neutral)*** Down 10.5  1 Rudder Left 35  1 Right 35  1 Rudder Trim Tab Left 25  1 (Rudder in Neutrum) Right 25  1 Wing Flaps Cruise 0  2 Landing 40  2 Nose Wheel Travel Left 27  1 Right 27  1 ***Stabilator is in neutral position when its chord is parallel to the front seat track upper position Serial Numbers Eligible 1AH002-07 and up. The General Inspectorate of Civil Aviation (G ICA) Certificate of Airworthiness endorsed as noted below under “Import Requirement s” must be submitted for each individual aircraft, for which application fo r airworthiness certification is made. Only those aircraft serials holding 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 Standard Airworthiness Certificate may be issued on the basis of a Certificate of Airworthiness for Export signed by a repres entative of General Inspectorate of Civil Aviation (GICA) containing the following stat ement: “The airplane covered by this certificate has been examined, tested and found to conform to the type design approved under Type Certificate No. A68EU a nd is in condition for safe operation.” Certification Basis FAR Part 23 e ffective 2-1-65, amended as follows: -Subparts A, B through Amendm ent 23-18 effective May 2, 1977; -Subpart C through Amendment 23-18 (e xcept 23.507 and 23.509 amended through Amendment 23-6 effective August 1, 1967); -Subpart D through Amendment 23-18 (ex cept 23.785 amended through Amendment 23-32 effective December 12, 1985); -Subpart E through Amendment 23-6 (except 23.901, 23.909, 23.959, 23.1041, 23.1043, 23.1047, and 23.1143, amended through Amendmen t 23-7 effective September 14, 1969); -Subpart F through Amendment 23-6 (ex cept 23.1305 amended through Amendment 23-7 effective September 14, 1969, 23.1323 amende d through Amendment 23-18 effective May 2, 1977, 23.1419 amended through Amendment 23-14 effective December 20, 1973, and 23.1441 amended through Amendmen t 23-9 effective June 17, 1970); -Subpart G through Amendment 23-18 (excep t 23.1545 (a) amended through Amendment 23-23 effective December 1, 1978, and 23.1529 amended through Amendment 23-26 effective October 14, 1980). FAR Part 36 effective December 1, 1969, thr ough Amendment 36-20 effective September 16, 1992. A68EU 4 Validation Basis Type Certificate A68E U was issued pursuant to FAR 21.29(a) in validation of General Inspectorate of Civil Aviation (GICA) certification of comp liance when aforementioned Certification Basis. Equipment The basic required equipm ent as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the airc raft for standard airworthiness certification. In addition, the following items of equipment are required. 1. Icing protection equipment as sp ecified by manufacturer’s Dwg. No. 37700. 2. Model PZL M20 “MEWA” - GICA approve d Airplane Flight Manual Ref. PZL Report M2003/OLP-5/002/88/FAA, dated May 20, 1993, or later GICA approved revision. NOTE 1. Current weight and balance report including list of equipment is certificated empty weight, and loading instructions, must be provided for each aircraft at the time of original airworthiness certification. The certificated empty weight and corresponding cente r-of-gravity positions must include undrainable oil and unusable fuel as noted below: Fuel 30.0 lbs at (+103.0) Oil 12.0 lbs at (+ 43.7) NOTE 2. Required Placards (Refer to Manufacturer’s Specifications for contents): (1) The following placard must be lo cated in clear view of the pilot: On side to left of pilot: Limitations This airplane must be operated as a normal categor y airplane in compliance with the operating limitations stated in the form of placards, markings, and manuals. No acrobatic maneuvers (including spins) approved. This aircraft approved for VFR, IFR, day, night a nd icing flight when equipped in accordance with FAR 91 or FAR 135. Minimum single engine control speed 66 KIAS. Single engine stalls not permitted. Can cause 500 ft. loss of altitude and 15  pitch angle. In addition, all placards required in the approved airplane flight manual must be installed in the appropriate location. Each individual airplane will be supplied with a placard that specifies the kinds of operation such as VFR, or IFR, DAY or NIGHT, to which the operation of the airplane is limited by the equipment installed. (2) Maximum Weight (3) Maneuver Speed (4) Demonstrated Crossword Component (5) Information (6) Flight with Doors Removed (7) Emergency Gear Extension (8) Door Latch (9) Door Release (10) Maximum Baggage (2) (11) Takeoff Checklist (12) Landing Checklist (13) Smoking (14) Storm Window Airspeed (15) Icing Conditions (if applicable) (16) Windshield Heat (17) Pitot Heat (18) Oil Cooler (2) (19) Prop Sync. (20) Table (21) RPM Limits (2) (22) Fire Extinguisher 5 A68EU (23) Heating/Ventilation Controls (24) Fuel (25) Flap Step NOTE 3. Instructions for continued airworthiness are cont ained in Section 3, PZL M-20 MEWA Maintenance Manual (dated December 15, 1992). Revisions to Airw orthiness Limitations must be FAA approved. ...END...