TCDS A32SO

Page No. 1 2 3 4 Rev. No. 3 2 3 2 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A32SO Revision 3 Piper Aircraft, Inc PA-42-720R October 13, 2014 TYPE CERTIFICATE DATA SHEET NO. A32SO This data sheet, which is part of Type Certificate No. A32SO, 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 Piper Aircraft, Inc. 2926 Piper Drive Vero Beach, Florida 32960 Type Certificate Holder Record The New Piper Aircraft, Inc transferred TC A32SO to Piper Aircraft, Inc on August 7, 2006. I. - Model PA-42-720R (Cheyenne III), 6 PCLM (Restricted Category Only), Approved March 31, 1986. Engine 2 United Aircraft of Canada, Ltd., or Pratt & Whitney, PT6A-61 (turboprop) Fuel JP-4, JP-5, commercial kerosene, Jet A, A-1 and B fuels conforming to P&W Specification 522, or Service Bulletin 13044. (Fuels shall conform to the specifications as listed or to subsequent revisions thereto). See NOTE 6(a) for emergency fuel. Oil (engine & gearbox) UACL PT6 Engine Service Bulletin No. 13001 lists approved brand oils Engine Limits Shaft Horsepower Nl Gas Generator Speed Prop Shaft Speed * Maximum Permissible Turbine Interstage Temp. (°C) Takeoff, Max. continuous and Max. Cruise 850 104.0% 2000 800 Max. climb Max. normal cruise; 850 104.0% 2000 775 Starting transient (5 sec.); - - - - - - - - - - - - 1000 Max. reverse (1 Min.) 200 - - - - 1900 760 *See NOTE 4 At most altitudes and low ambient temperatures the engines will produce more power at takeoff than that for which the airplane has been certificated. Under all conditions the placarded torquemeter limitations shall not be exceeded. Oil temperatures: -40°C: Minimum starting. -40°C to 104°C: Low idle. 0°C to 104°C: Max. continuous. Transient 110°C for 10 min. See NOTE 7. Propeller and Propeller Limits 2 Hartzell HC-B3TN-3K hubs with Hartzell T10173DB-6Q blades. Diameter: 95 in. No reduction permitted. Pitch settings at Low Pitch Stop - See NOTE 5(a) Reverse - See NOTE 5(b) Feathered - See NOTE 5(c) A32SO Page 2 of 4 Airspeed Limits KCAS KIAS Vmo (Max. Operating) 246 245 (Up to 22,200 ft; See Vmo Chart for speeds above 22,200 feet in Flight Manual) Va (Maneuvering) (Minimum Weight - 8,750 lb.) 159 158 (Max. Weight - 13,450 lb.) 177 176 Vfe (Max. Flaps Extended) (10° Flaps) 196 195 (30° Full Flaps) 143 143 Vlo (Max. Landing Gear Operating) (Extend) 174 173 (Retract) 156 155 Vle (Max. Landing Gear Extended) 174 173 Vmc (Minimum Control Speed without Autofeather) 116 113 Vmc (Minimum Control Speed Autofeather Operation) 110 106 C. G. Range (+127.50) to (+137.50) at 8,674 lb. or less (+133.78) to (+137.50) at 13,535 lb. Ramp weight -Takeoff Weight: 13,450 lb. at (+133.67) to (+137.50) Straight line variation between points given. Moment change due to retracting landing gear: (+1146 in.-lb.) Empty Weight C. G. Range None Maximum Weight Ramp: 13,535 lb. Takeoff: 13,450 lb. Landing: 13,450 lb. Zero Fuel: 9,850 lb. Centerline: 9,850 lb. Minimum Crew One pilot Number of Seats 5 Maximum Baggage 300 lb. Fuel Capacity 602 gallons See NOTE 1 for unusable fuel data Oil Capacity 26 quart total at (+86) (includes 12 quarts usable in two integral engine tanks) Control Surface Aileron (+1.0°,-0°) 29° Up 15° Down Movements Aileron Tab (+1.0°,-0°) 18.5° Up 18.5° Down (All measurements taken (Aileron Neutral) at trailing edge from neutral position for elevator Elevator (+0.5°,-0°) 12° Up 20° Down and rudder, neutral position (+1.0°,-0°) 20° Down for aileron down 2°) Elevator Tab (+1.0°,-2.0°) 7° Up (Elevator Neutral) (+1.0°,-0°) 30° Down Rudder (+1.0°,-0°) 30° Right 20° Left Rudder Tab (+1.0°,-0°) 10° Right 20° Left (Rudder Neutral) Flaps (±1.0°) 0° Up (±1.0°) 30° Down Page 3 of 4 A32SO Maximum Operating Altitude 35,000 feet Serial Numbers Eligible 42-5501024, 42-5501028, 42-5501032, 42-5501034 through 42-5501038 DATA PERTINENT TO ALL MODELS Datum 137 inches forward of the main spar centerline. Leveling Means Lateral: Seat tracks station 245 inside cabin doors. Longitudinal: Two rivnuts on right hand fuselage and forward of the wing leading edge. Certification Basis Application for Type Certificate, March 26, 1985. Type Certificate A32SO issued, March 31, 1986. FAR Part 23, effective February 1, 1965, as amended by Amendment 23-16, effective February 14, 1975, except as follows: Delete paragraphs 23.1, 23.45, 23.49, 23.65, 23.67, 23.77, 23.977, 23.1145, 23.1385(c), 23.1545(a), and 23.1581. Add paragraphs 23.45, 23.49, 23.65, 23.67, 23.77, 23.1145, 23.1385(c), 23.1447(c), 23.1447(d), and 23.1581, as amended by Amendment 23-21, effective March 1, 1978; and 23.1545(a), as amended by Amendment 23-23, effective December 1, 1978; and from FAR Part 25, effective February 1, 1965, as amended by Amendment 25-36, effective October 31, 1974, Paragraph 25.977, Special Condition No. 23-90-SO-3, Amendment 1, Docket Number 19591; SFAR 23, Paragraph 55, effective January 20, 1970, SFAR 27-1, effective January 1, 1975; FAR Part 36, including Amendments 1 through 6, effective January 25, 1977; and the FAA Atlanta Aircraft Certification Office letter of March 28, 1986, showing the equivalent level of safety findings to 23.201, 23.203, and 23.205. Compliance with ice protection requirements has been demonstrated in accordance with FAR 23.1419, as amended by Amendment 23-14, effective December 20, 1973. Regulations that are inappropriate: FAR 23.1, as amended by Amendment 23-10, effective March 13, 1971. Limitations required to show compliance with FAR's are specified in the Airplane Flight Manual (AFM) and in the Airworthiness limitations section of the Maintenance Manual, and may not be revised without approval by the FAA Atlanta Aircraft Certification Office. Production Basis Production Certificate No. 206 and the manufacturer is authorized to issue airworthiness certificates under the delegation option provisions of FAR 21. Equipment The basic equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the aircraft for certification. In addition, the following items of equipment are required: 1. FAA approved Airplane Flight Manual Report No. LK-1485. NOTE 1. Current weight and balance data, loading information, and a list of equipment included in empty weight must be provided for each airplane at the time of original certification. Basic empty weight includes unusable fuel of 13.4 lb. at (+128.0). NOTE 2. All placards required in the FAA Approved Airplane Flight Manual must be installed in the appropriate location. A32SO Page 4 of 4 NOTE 3. The Service Life Limits on components are contained in the Maintenance Manual and are listed below: (a) Engine mount bolts at Sta. 106.00: 7853 hrs. (b) Wing: 18,000 hrs. (c) Empennage: 18,000 hrs. (d) Fuselage: 18,000 hrs. NOTE 4. The maximum propeller shaft overspeed limit for the PT6A-61 is 100% (2200 r.p.m.) of all ratings. 91% propeller shaft speed is defined as 2000 r.p.m. and is the normal steady state operating limit. Gas generator speeds up to 104.0% are permissible for unlimited periods subject of applicable temperature and other limits. 100% gas generator speed is defined as 37,468 r.p.m. NOTE 5. (a) Propeller low pitch is set so that at 1900 r.p.m. there shall be an indicated 1154 ± 30 ft. -lb torque corrected to sea level standard day. (b) Propeller reversed pitch setting is adjusted to provide reversed power of 180 SHP ± 20 (SHP = torque x prop r.p.m. x 0.00019.) (c) Feathered angle shall be adjusted to prevent rotation while feathered at 132 KCAS. NOTE 6. (a) Aviation Gasoline MIL-G-5572 Grades 80/87, 91/98, 100/130 and 115/145 are permitted for a total time period not to exceed 150 hours time between turbine hot section inspections. It is not necessary to purge the unused fuel from the system when switching fuel types. (b) MIL-I-27686 Fuel System Icing Inhibitor or equivalent may be used in the fuel in amount up to 0.15% by volume. NOTE 7. Transient oil temperature is limited to 110° C for 10 minutes ground operating only. ...END...