TCDS 7A15

Page No. 1 2 3 4 5 6 7 8 9 10 11 Rev. No. 15 6 14 14 6 14 7 15 14 14 12 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION 7A15 Revision 15 PILATUS PC-6, PC-6-H1, PC-6-H2 PC-6/350, PC-6/350-H1, PC-6/350-H2 PC-6/A, PC-6/A-H1, PC-6/A-H2 PC-6/B-H2, PC-6/B1-H2, PC-6/B2-H2 PC-6/B2-H4, PC-6/C-H2, PC-6/C1-H2 July 07, 2021 TYPE CERTIFICATE DATA SHEET NO. 7A15 This data sheet which is a part of Type Certificate No. 7A15 prescribes conditions and limitations under which the product for which the Type Certificate was issued meets the airworthiness requirements of the Civil Air Regulations. Type Certificate Holder. Pilatus Aircraft Ltd. Stans, Switzerland I. Model PC-6, 11 PCLM (Normal Category), Approved: November 9, 1961 Model PC-6-H1, 11 PCLM (Normal Category), Approved: January 7, 1964 Model PC-6-H2, 11 PCLSM (Normal Category), Approved: October 16, 1964. Engine. Lycoming GSO-480-B1A6 Fuel. 100/130 Minimum grade aviation gasoline. Engine Limits. (Straight line manifold pressure variation with altitude shown) HP R.P.M. M.P. Altitude Take-off 340 3400 48.0 S.L. Take-off 340 3400 44.5 7900' Max. Continuous 320 3200 45.5 S.L. Max. Continuous 320 3200 43.0 8000' Propeller and Hartzell constant speed propeller Propeller Limits. Hub HC-83X20-1B or HC-A3X20-1D, blades 9333C-0 to -5 Diameter maximum 93 in. minimum 88 in. (no further reduction permitted) Pitch setting at 30 in. station: low 15 o, high 36o. Fuel Capacity. Total capacity 105 US gal. or 127 US gal. (2 tanks of 52.5 or 63.5 US gal.) (+31.1) Usable capacity 104 US gal. or 126 US gal. (2 tanks of 52.0 or 63.0 US gal.) (+31.1) Oil Capacity. 3.5 US gal. (-43.9). Page 2 of 11 7A15 II. Model PC-6/350, 11 PCLM (Normal Category), Approved: September 12, 1962 Model PC-6/350-H1, 11 PCLSM (Normal Category), Approved: January 7, 1964 Model PC-6/350-H2, 11 PCLSM (Normal Category), Approved: October 16, 1964. Engine. Lycoming IGO-540-A1A. Fuel. 100/130 Minimum grade aviation gasoline. Engine Limits. (Straight line manifold pressure variation with altitude shown) HP R.P.M. Take-off (Max. 5 min) 350 3400 full throttle at S.L. Max. Continuous 325 3000 full throttle at S.L. Propeller and Hartzell constant speed feathering propeller Propeller Limits. Hub HC-B3Z-30-2B, blades 9349 + 1/2 Diameter maximum 93.5 in. minimum 93.5 in. (no reduction permitted) Pitch setting at 30 in. station: low 15o, high 87o. Fuel Capacity. Total capacity 105 US gal. or 127 US gal. (2 tanks of 52.5 or 63.5 US gal.) (+31.1) Usable capacity 104 US gal. or 126 US gal. (2 tanks of 52.0 or 63.0 US gal.) (+31.1). Oil Capacity. 3.5 US gal. (-43.9) III. Model PC-6/A, 11 PCLM (Normal Category), Approved: November 27, 1962 Model PC-6/A-H1, 11 PCLM (Normal Category), Approved: January 7, 1964 Model PC-6/A-H2, 11 PCLSM (Normal Category), Approved: October 16, 1964 Engine. Turbomeca Astazou II E or Astazou II G Fuel. ASTM-D-1655 Spec. Jet A or Jet A1 (French Air 3405, TR.0) Jet B (French Air 3407, TR.4) MIL-T-5624 Spec. JP-4 JP-5, Spec. gravity not over 0.8 (French Air 3404, TR.5) SHP RPM Alt. Power Max. EGT % (C) Take-off (max. 5 min) 523 43500 S.L. 100 525 Max. Continuous 473 43500 S.L. 88 500 Starting transient 30 sec. 550 less than 3 sec. 630 Propeller and Ratier Figeac turbine propeller, electrically controllable Propeller Limits. feathering and reversing. Hub FH 76-1-07, blades FH 76.207. Diameter maximum 98.4 in. minimum 97.4 in. (no further reduction permitted) Pitch setting at 34.44 in. station: Reverse -14o (mechanical stop) Starting - 1.5o Flight minimum + 2.5o (electrical stop) Feathering + 87o (mechanical stop) Page 3 of 11 7A15 III. Model PC-6/A, Model PC-6/A-H1, Model PC-6/A-H2 (cont’d) Fuel Capacity. Total capacity: 130 US gal. or 173 US gal. (2 tanks of 63.5 or 85 US gal.) (+31.1) plus 1 booster pump tank of 3 US gal. (+ 111.0) Usable capacity: 128 US gal. or 170 US gal. (2 tanks of 62.5 or 83.5 US gal.) (+31.1) plus 1 booster pump tank of 3 US gal. (+ 111.0) Oil Capacity. 2.11 US gal. (-94.8) (engine integral) IV. Model PC-6/B-H2, 11 PCLSM (Normal Category), Approved: March 10, 1967 Engine. United Aircraft of Canada Ltd. PT6A-6A Fuel. JP-1, JP-4 and JP-5 fuels conforming to UACL Specification No. 522 and later revisions. Engine Limits. SHP Torque G.G. Prop. TIT (psi) RPM RPM ( oC) Take-off (max. 5 min) 550 42.5 38.100 2.200 994 (101.5%) (100%) Max. Continuous 500 38.5 38.100 2.200 952 (101.5%) (100%) Starting (max. 2 sec) --- --- --- --- 1038 Max. reverse 500 42.5 994 Propeller and Hartzell feathering and reversing constant speed propeller Propeller Limits. Hub: HC-B3TN-3C, blades T-10173C or T-10173CH Diameter: max. 101 in., min. 99 in. (no further reduction permitted) Pitch setting at 30 in. station: Reverse -11.5o Feathering +85.5o Minimum in flight 0o Fuel Capacity. Total capacity: 130 US gal. or 173 US gal. (2 tanks of 63.5 or 85 US gal.) (+31.1) plus 1 booster pump tank of 3 US gal. (+ 111.0) Usable capacity: 128 US gal. or 170 US gal. (2 tanks of 62.5 or 83.5 US gal.) (+31.1) plus 1 booster pump tank of 3 US gal. (+ 111.0) Oil Capacity. Total capacity: 2.3 US gal. (-80) (engine integral) Usable capacity: 1.5 US gal. V. Model PC-6/B1-H2, 11 PCLSM (Normal Category), Approved: March 10, 1967 Engine. United Aircraft of Canada Ltd. PT6A-20 Fuel. JP-1, JP-4 and JP-5 fuels conforming to UACL Specification No. 522 and later revisions. Engine Limits. SHP Torque G.G. Prop. ITT (psi) RPM RPM ( oC) Take-off and maximum 550 42.5 38.100 2.200 750 continuous up to (101.5%) (100%) 21o at S.L. Starting (max. 2 sec) --- --- --- --- 1090 Max. reverse 500 42.5 750 Page 4 of 11 7A15 V. Model PC-6/B1-H2 (cont’d) Propeller and Hartzell feathering and reversing constant speed propeller Propeller Limits. Hub: HC-B3TN-3C or HC-B3TN-3D, blades; T-10173C or T-10173CH or T-10178C or T-10178CH. Diameter: max. 101 in., min. 99 in. (no further reduction permitted). Pitch setting at 30 in. station: Reverse -11.5o Feathering +85.5o Minimum in flight 0o Fuel Capacity. Total capacity: 130 US gal. or 173 US gal. (2 tanks of 63.5 or 85 US gal.) (+31.1) plus 1 booster pump tank of 3 US gal. (+ 111.0) Usable capacity: 128 US gal. or 170 US gal. (2 tanks of 62.5 or 83.5 US gal.) (+31.1) plus 1 booster pump tank of 3 US gal. (+ 111.0) Oil Capacity. Total capacity: 2.3 US gal. (-80) (engine integral) Usable capacity: 1.5 US gal. VI. Model PC-6/B2-H2, 11 PCSLM (Normal Category), Approved: August 21, 1973. Engine. United Aircraft of Canada Ltd. PT6A-27 Fuel. JP-1, JP-4 and JP-5 fuels conforming to UACL Specification No. 522 and later revisions. Engine Limits. SHP Torque G.G. Prop. ITT (psi) RPM RPM ( oC) Take-off 550 42.5 38.100 2.200 725 (101.5%) (100%) Max. Continuous 550 42.5 38.100 2.200 725 (101.5%) (100%) Starting (max. 2 sec) --- --- --- --- 1090 Max. reverse 550 42.5 725 Propeller and Hartzell feathering and reversing constant speed propeller Propeller Limits. Hub: HC-B3TN-3C or HC-B3TN-3D, blades T-10178C or T-10178CH or T-10173C or T-10173CH. Diameter: max. 101 in., min. 99 in. (no further reduction permitted) Pitch setting at 30 in. station: Reverse -10.0o Feathering +85.5o Minimum in flight 0.5o Fuel Capacity. Total capacity: 130 US gal. or 173 US gal. (2 tanks of 63.5 or 85 US gal.) (+31.1) plus 1 booster pump tank of 3 US gal. (+ 111.0) Usable capacity: 128 US gal. or 170 US gal. (2 tanks of 62.5 or 83.5 US gal.) (+31.1) plus 1 booster pump tank of 3 US gal. (+ 111.0) Oil Capacity. Total capacity: 2.3 US gal. (-80) (engine integral) Usable capacity: 1.5 US gal. Page 5 of 11 7A15 VII. Model PC-6/C-H2, 11 PCLSM (Normal Category), Approved: March 10, 1967. Engine. Airesearch TPE 331-25D. Fuel. JP-1, JP-4 and JP-5 fuels conforming to Airesearch Manufacturing Company of Arizona Report PE-5064 R. Engine Limits. SHP Torque RPM EGT (psi) (0oC) Take-off 575 57.7 41.730 571 (100%) Max. Continuous 500 51.7 41.730 535 (100%) Absolute Maximum --- --- 43.820 (max. 5 sec) (105%) Starting (max. 10 sec) --- --- --- 815 Propeller and Hartzell feathering and reversing constant speed propeller Propeller Limits. Hub: HC-B3TN-5C, blades T-10178C or T-10178CH Diameter: max. 101 in., min. 99 in. (no further reduction permitted) Pitch setting at 30 in. station: Reverse - 9.5o Feathering +87o Start + 2o Minimum in flight + 5o Fuel Capacity. Total capacity: 130 US gal. or 173 US gal. (2 tanks of 63.5 or 85 US gal.) (+31.1) plus 1 booster pump tank of 3 US gal. (+ 111.0) Usable capacity: 128 US gal. or 170 US gal. (2 tanks of 62.5 or 83.5 US gal.) (+31.1) plus 1 booster pump tank of 3 US gal. (+ 111.0) Oil Capacity. 2.9 US gal. (-103) (engine integral) VIII. Model PC-6/C1-H2, 11 PCLSM (Normal Category), Approved: August 21, 1973. Engine. Airesearch TPE 331-1-100 Fuel. Fuels conforming to Airesearch Manufacturing Company of Arizona Report PE-5064R. Engine Limits. SHP Torque RPM EGT (psi) (o) Take-off 576 53.2 41.730 561 (100%) Max. Continuous 576 53.2 41.730 561 (100%) Absolute Maximum --- --- 43.816 (max. 5 sec) --- --- (105%) Starting (max. 1 sec) --- --- --- 815 Page 6 of 11 7A15 Propeller and Hartzell feathering and reversing constant speed propeller Propeller Limits. Hub HC-B3TN-5C, blades T-10178C or T-10178CH Diameter: max. 101 in. minimum 99 in. (no further reduction permitted) Pitch setting at 30 in. station: Reverse - 9.5o Feathering +87o Start + 2o Minimum in flight + 5o Fuel Capacity. Total capacity: 130 US gal. or 173 US gal. (2 tanks of 63.5 or 85 US gal.) (+31.1) plus 1 booster pump tank of 3 US gal. (+ 111.0) Usable capacity: 128 US gal. or 170 US gal. (2 tanks of 62.5 or 83.5 US gal.) (+31.1) plus 1 booster pump tank of 3 US gal. (+ 111.0) Oil Capacity. 2.9 US gal. (-103) (engine integral). IX. Model PC-6/B2-H4, 11 PCLSM (Normal Category), Approved July 31, 1992 Engine. United Aircraft of Canada Ltd. PT6A-27 Fuel. JP-1, JP-4 and JP-5 fuels conforming to UACL Specification No. 522 and later revisions. Engine Limits. SHP Torque C.G. Prop. ITT (psi) RPM RPM ( oC) Take-off 550 47.3 38.100 2000 725 (101.5%) (100%) Max. Continuous 550 47.3 38.100 2000 725 (101.5%) (100%) Starting (max. 2 sec) --- --- --- --- 1090 Max. reverse 550 47.3 725 Propeller and Hartzell feathering and reversing constant speed propeller Propeller Limits. Hub: HC-B3TN-3C or HC-B3TN-3D, blades T-10178CNR, T-101778CNRK, T-10178CR, T-10178CRK or T-101778C, T-10178CK, T-10178CH modified according to Pilatus Service Bulletin No. SB 149. Diameter: max. 101 in., min. 99 in. (No further reduction permitted). Pitch setting at 30 in. station: Reverse -10.5o Feathering +85.5o Minimum in flight + 0.5o Fuel Capacity. Total capacity: 130 US gal. or 173 US gal. (2 tanks of 63.5 or 85 US gal. (+ 31.1) plus 1 booster pump tank of 2 US gal. (+ 111.0) Usable capacity: 128 US gal. or 170 US gal. (2 tanks of 62.5 or 83.5 US gal. (+ 31.1) plus 1 booster pump tank of 3 US gal (+ 111.0) Oil Capacity. Total capacity : 2.3 US gal. (-80) (engine integral) Usable capacity : 1.5 US gal. Page 7 of 11 7A15 DATA PERTINENT TO ALL MODELS Airspeed Limits (IAS). All models except B2-H4 B2-H4 Vne (Never exceed) Vno (Max. structural cruising) Vp (Maneuvering) Vfe (Flaps extended) Vsk (Ski system operation) 174 mph (151 kts) 137 mph (118 kts) 122 mph (106 kts) 94 mph ( 82 kts) 84 mph ( 73 kts) 174 mph (151 kts) 138 mph (119 kts) 138 mph (119 kts) 109 mph ( 95 kts) ---- --- C.G. Range. All Models except B2-H4 Model B2-H4 + 18.7” to + 25.4” at 4850 lb. + 8.2” to + 25.4” at 3200 lb. or less + 23.9” to + 28.4” at 6173 lbs. + 8.2” to 28.4” at 3200 lbs. Straight line variation between points given. Empty Weight C.G. Range. None. Datum. Leading edge of wing Leveling Means. Marks on each side of the fuselage. Also T-rails on cabin floor horizontal. Max. weights (take-off) PC-6, PC-6/350 and PC-6/A 4322 lb. and landing weights PC-6-H1, PC-6/350-H1, PC-6/A-H1 4444 lb. PC-6-H2, PC-6/350-H2, PC-6/A-H2 4850 lb. PC-6/B-H2, PC-6/B1-H2, PC-6/B2-H2 PC-6/C-H2, PC-6/C1-H2. PC-6/B2-H4 6173 lb MTOW/5864 lb KLW NOTE: AFM Supplements as listed on page 8 show increased take-off weights. Number of Seats. 8 - 2 at (+ 4.5), 2 at (+34.4), 2 at (+63.0), 2 at (+91.3), or 11 - 2 single seats at (+ 4.5) and 3 triple seats at (+32.7, +60.3, and +85.8). NOTE: 6 seats can be stowed in compartment behind cabin, accessible through a door in fuselage RH side. Maximum Baggage. Main cabin, after removal of seats. See approved loading instructions. Max. floor loading 100 lb. per sq. ft. Control Surface Movements. Elevator: Up 30o ± 1o Down 25o ± 1o Flettner tab: Down 57o ± 2o Up 32o ± 2o Stabilizer: Nose Down 10o ± .5o Nose up 2o ± .5o (Serial No. 552 and all H2 models) Nose Down 8o ± .5o Nose up 2o ± .5o (Serial No. 524 and up except H2 models) Rudder: Right 30o ± 1.5o Left 30o ± 1.5o Rudder tab: Right 6o ± 1o Left 6o ± 1o Aileron: Up 20o ± 1o Down 13.5o ± 1o Flettner tab: Down 20o ± 1o Up 13.5o ± 1o Aileron tab (r.h.) Up 20o ± 2o Down 18o Neutral 2o Up Flaps: Up 0o Down 45o ± 2o (Ser. No. 522) Up 0o Down 38o ± 2o (Ser. No. 524 and up) Page 8 of 11 7A15 NOTE: Flettner tabs on aileron and elevator are optional; if not installed, fixed tabs on elevator (up 36o) and aileron (neutral) are mandatory. Stabilizer in neutral position is 3o nose down. For B2-H4 on elevator one flettner tab (set to 0o) and two fixed trim tabs (set 10o up) are mandatory. Maximum Operating Altitude. 25.000 ft. Certification Basis. CAR 10. CAR 3 dated May 15, 1956 including amendments 3-1 through 3-5. Type Certificate No. 7A15, issued November 9, 1961. Date of Application for Type Certificate: October 11, 1960. The Swiss Federal Office of Civil Aviation (FOCA) originally type certificated this aircraft under its type certificate Number F-56-10. The FAA validated this product under U.S. Type Certificate Number 7A15. Effective December 1, 2006, the European Aviation Safety Agency (EASA) began oversight of this product on behalf of Switzerland. The EASA TCDS No. has not been issued at this time. The Swiss Federal Air Office "Certificate of Airworthiness for Export" endorsed as noted below under "Import Requirements" must be submitted for each individual aircraft for which application for certification is made. (See NOTE 4). Import Requirements. The FAA can issue a U.S. airworthiness certificate based on an NAA Export Certificate of Airworthiness (Export C of A) signed by a representative of the Swiss Federal Office of Civil Aviation (FOCA) on behalf of the European Community. The Export C of A should contain the following statement: ‘The aircraft covered by this certificate has been examined, tested, and found to comply with U.S. Civil Air Regulation Part 3 U.S. Type Certificate No. 7A15 and to be in a condition for safe operation.’ Model PC-6 and PC-6/350 series: "The airplane covered by this certificate has been examined and found to comply with U.S. Civil Air Regulations Part 3, dated May 15, 1956 including Amendment 3-1 through 3-5 and conforms to T.C. 7A15". Model PC-6/A series: "The airplane covered by this certificate has been examined and found to comply with U.S. Civil Air Regulation Part 3, dated May 15, 1956 including Amendment 3-1 through 3-5 and Special Conditions notified by FAA, letter dated November 14, 1962 to the Swiss Federal Air Office, and conforms to T.C. 7A15". Models PC-6/B, /B1, /B2, /C, and /C1 series: "The airplane covered by this certificate has been examined and found to comply with U.S. Civil Air Regulation Part 3, dated May 15, 1956 including Amendments 3-1 through 3-5 and Special Conditions notified by FAA, letter dated January 4, 1967 and conforms to T.C. 7A15". 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. Equipment. The basic required 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: (a) Swiss Federal Air Office approved Airplane Flight Manual (as limited below) (b) Stall warning indicator, Safe Flight 1-02-0005, or 164 (c) Ratier Figeac Spinner FH 76-400 (PC-6/A series only) (d) Clogged fuel filter warning light (PC-6/A, /B, /B1, /B2, /C, and /C1 series only). Page 9 of 11 7A15 (e) Stabilizer dual motor trim actuator Electro Mech EM 483 Mandatory for PC-6/B2-H4 only. Service Information Each of the documents listed below must state that it is approved by the European Aviation Safety Agency (EASA) or – for approvals made before December 1, 2006 – Swiss Federal Office of Civil Aviation (FOCA). • Service bulletins, • Structural repair manuals, • Vendor manuals, • Aircraft flight manuals, and • Overhaul and maintenance manuals. The FAA accepts such documents and considers them FAA-approved for type design data only unless one of the following conditions exists: • The documents change the limitations, performance, or procedures of the FAA approved manuals; or •The documents make an acoustical or emissions changes to this product’s U.S. type certificate as defined in 14 CFR § 21.93. The FAA uses the post type validation procedures to approve these documents. The FAA may delegate on case-by-case to EASA to approve on behalf of the FAA for the U.S. type certificate. If this is the case it will be noted on the document. Airplane Flight Manual. (a) Swiss Federal Air Office approved Airplane Flight Manuals: Model Report No. PC-6 902 PC-6-H1 902-1 PC-6-H2 902-2 Model Report No. PC-6/350 920 PC-6/350-H1 920-1 PC-6/350-H2 920-2 Model Report No. PC-6A 921 PC-6/A-H1 921-1 PC-6/A-H2 921-2 Model Report No. PC-6/B-H2 1072 PC-6/B1-H2 1072-1 PC-6/B2-H2 1072-2 or 1791 Model Report No. PC-6/C-H2 1161 PC-6/C1-H2 1161-1 Model Report No. PC-6/B2-H4 up to MSN 824 1072-20 Model Report No. PC-6/B2-H4 from MSN 825 1820 (b) List of Supplements (Swiss Federal Air Office approved). Report No. Applicable for PORTER Model Subject Operating Category 1029 PC-6/350-H1 Seaplane with floats EDO 39-4000 Normal 1140 PC-6-H2 PC-6/350-H2 Seaplane with floats EDO 58-4580 Normal 1141 1141-1 PC-6/A-H2 PC-6/B-H2 PC-6/B1-H2 PC-6/B2-H2` Seaplane with floats EDO 58-4580 EDO 58-4580 or EDO 679-4930 Normal Page 10 of 11 7A15 1104 PC-6/B1-H2 PC-6/B2-H2 Fuel ferry tank installation Restricted* 1143-1 1143-B 1143-C 1143-D PC-6/C-H2 PC-6/C1-H2 Agriculture version Restricted* 1186 All models except B2-H4 Cabin doors removed, sliding door and/or hatch door open (parachuting) Normal 1242 All models “H2” Wing fuel tanks 2 x 85 US-gal. Normal 1320 All models except B2-H4 Ski operation Normal 1347-1 All models “H2” External fuel Restricted* 1421 All models Electrically operated landing flaps Normal 1422 PC-6/B1-H2 PC-6/B2-H2 Engine Air Intake Filter Mk. 38 Normal 1424 All models Aileron Trim System Normal 1490 All TURBO PORTER model except B2-H4 Fuel Ferry tank V-43593 Restricted* Report No. Applicable for PORTER Model Subject Operating Category 1504 PC-6/B-H2 PC-6/B1-H2 PC-6/B2-H2