TCDS A78EU

Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 Rev. No. 39 36 39 34 38 38 34 33 38 38 38 39 39 38 39 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A78EU Revision 39 Pilatus PC-12 PC-12/45 PC-12/47 PC-12/47E PC-12/47G July 2, 2025 TYPE CERTIFICATE DATA SHEET No. A78EU This data sheet, which is a part of Type Certificate No. A78EU, 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. Pilatus Aircraft Ltd. Pilatusstrasse 1 6371 Stans Switzerland Type Certificate Holder Record: PILATUS AIRCRAFT LIMITED Ennetbürgerstrasse 101 CH-6370 STANS I. Model PC-12, Normal Category, approved July 15, 1994. Engine. Pratt & Whitney PT6A-67B Fuel. Approved fuels in accordance with AFM 01973-001 or AFM 02211 as applicable. Engine Limits. Shaft Power Torque N1 Gas Generator Speed Prop Shaft Speed Maximum Observed Inter Turbine Temp. shp PSI % RPM ºC Take-off Max. climb/Max. cruise Starting (5 seconds) Transient (20 seconds) 1200 1000 --- --- 44.34 36.95 --- 61.00 104 104 --- 104 1700 1700 --- 1870 800 760 1000 870 Note: 100% Gas Generator Speed = 37,468 RPM Propeller and Propeller Hartzell HC-E4A-3D hub with Hartzell E10477K aluminum blades; Limits. four blade constant speed type. (SEE NOTE 12) Spinner: Hartzell D5500-1 (Aluminum) Diameter: 104 in (2.642 m) to 105 in (2.667 m) cropping of blade tips not permitted. Pitch settings (measured at 42 in. station) Fine pitch 19.0º Min. pitch in flight 6.0º Max. reverse pitch -17.5º Feathered 79.6º Stabilized ground operation is prohibited between 350 and 950 RPM. A78EU Page 2 of 15 Airspeed Limits (EAS). Max. operating speed VMO 240 kts Max. operating Mach No. MMO 0.48 Max. diving speed VD 280 kts MD 0.60 Max. maneuvering design speed VA 170 kts Max. maneuvering operating speed VO 154 kts at 4100 kg (9039 lbs) VO 136 kts at 3200 kg (7060 lbs) VO 123 kts at 2600 kg (5730 lbs) Center of Gravity Limits. At 4100 kg (9039 lbs) 27% MAC to 44% MAC Forward cg limit varies linearly between: (landing gear extended) 4100 kg (9039 lbs) 27% MAC 3700 kg (8157 lbs) 17.8% MAC 2700 kg (5952 lbs) and less 13% MAC Rear cg limit varies linearly between: (landing gear retracted) 4100 kg (9039 lbs) 44% MAC 3600 kg (7937 lbs) 46% MAC 3000 kg (6614 lbs) 46% MAC 2550 kg (5622 lbs) and less 20% MAC Datum. 3000 mm (118 in.) forward of firewall (frame no. 10). Leveling Means. Cabin Seat Rails (see Section 8 of the Airplane Maintenance Manual). Maximum Weight. Ramp weight 4120 kg (9083 lbs) Take-off weight 4100 kg (9039 lbs) Landing weight 4100 kg (9039 lbs) Max. zero fuel weight 3700 kg (8159 lbs) Minimum Crew. One (1) pilot (left seat) -OR- Two (2) pilots Number of Seats. 9 PAX and 2 pilot seats (for seat locations see Airplane Flight Manual, Section 6, W & B). Maximum Baggage. 180 kg (400 lbs) (baggage compartment at rear of cabin). Maximum Loading. (Combi version) 1000 kg/m2 (205 lb/ft2) on seat rails 600 kg/m2 (125 lb/ft2) on cabin floor (for loading limitations/instructions see Section 6 of the Airplane Flight Manual). Fuel Capacity Total Usable Arm (Specific gravity 0.806 kg/ltr) 1540 ltr (1241 kg) 1516 ltr (1222 kg) 5.91 m (233 in) aft of datum (406 US gal) (400 US gal) 1522 ltr (1226 kg) (see NOTE 1) (402 US gal) Oil Capacity. Total Arm 13,6 ltr 2.41 m (95 in) aft of datum (3.6 US gal) A78EU Page 3 of 15 Control Surfaces Wing flap 15º + 0º /-1.5° Take-off 39.5º +/- 0.5º Landing (left/right asymmetry 1°) Ailerons 30º +/- 1º Up 10º +/- 1º down Elevator 28º +/- 1º Up 15º +/- 1º down Stabilizer (trim) 2.5º + 0.7º /- 0.2ºup 7.5º + 0.7º / - 0.2º down (with respect to stabilizer leading edge) Rudder 35º +/- 1º right 25º +/- 1º left (from centerline and measured horizontally) Rudder tab 7.5º + 1º /- 1.5º right 13º + 1º/- 1.5º left (trim) Aileron tab 16.5º + /-1º up 16.5º +/- 1º down (trim) Stick Pusher System. Stick shaker/stick pusher system, signaled by AOA vanes on left and right wing leading edges. Serial Numbers Eligible. MSN 101 and up (See NOTE 21). Import Requirements- All Models. a. 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. airworthiness regulations 14 CFR Federal Aviation Regulations Part 23 U.S. Type Certificate No. A78EU and to be in a condition for safe operation.’ b. An airplane maintenance manual in compliance with FAR 23.1529 must be furnished before delivery of the first airplane or issuance of standard certificate of airworthiness whichever occurs later. 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. Certification Basis. 1) 14 CFR Sections 21.29, 21.183(c) and 14 CFR 23, Normal Category, effective February 4, 1991, including Amendments 23-1 through 23-42 and 14 CFR 23, (23-43) 23.1305(c3) 14 CFR 23, (23-44) 23.49(c), 23.562(d) 14 CFR 23, (23-45) 23.851 (see Note 19), 23.1507 14 CFR 23, (23-49) 23.1311 2) 14 CFR Section 36, effective November 18, 1969, including Amendments 36-1 through amendment in effect at the time of U.S. Type Certification, and 3) 14 CFR Section 34, effective September 10, 1990, and 4) Equivalent Level of Safety, a) ACE-94-8 of June 21, 1994, Spin demonstration, FAR 23.221 a)2) b) Cabin pressure indicator, FAR 23.841b) 6). See NOTE 8. 5) Section 611(b) of the FAA Act of 1958 6) Certification Maintenance Requirement (CMR), manual pitch trim system annunciation 7) Special Conditions: High Energy Radiated Electromagnetic Fields, (HERF), Number 23-ACE-46, effective date May 29, 1990 8) Approved for Flight Into Known Icing. See NOTE 4. The Swiss Federal Office of Civil Aviation (FOCA) originally type certificated this aircraft under its type certificate Number F-56-30. The FAA validated this product under U.S. Type Certificate Number A78EU. Effective June 23, 2006, the European Aviation Safety Agency (EASA) began oversight of this product on behalf of Switzerland. The EASA TCDS No. EASA.A.089. Production Basis. No FAA production certificate. PC-12 airplanes, all series and models, are produced under production approval CH.21G.0002, issued by the Swiss Federal Office of Civil Aviation (FOCA). A78EU Page 4 of 15 Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the airplane for certification. In addition the following is required: Airplane Flight Manual (including Equipment list and applicable supplements) -S/N 101-400: (except S/N 321) Report No. 01973-001 -S/N 321 and 401 and subsequent Report No. 02211 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 June 23, 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. Available Documents for the PILATUS PC-12 are: Airplane Flight Manual For S/N 101 – 400 except 321: Doc. No. 01973-001 Revision 2, dated February 14, 1995 or later FOCA approved revisions. For S/N 321 and 401 and subsequent: Doc No. 02211 (PC-12 data is contained in AFMS No. 25; Doc. No. 02211/9-25) Aircraft Maintenance Manual Doc. No. 02049. (Chapter 4 FOCA approved) Structural Repair Manual Doc. No. 02050. Illustrated Parts Catalogue Doc. No. 02051. II. Model PC-12/45 (Normal Category), approved July 31, 1996. The data given above is valid except where mentioned below: Airspeed Limits (EAS): Max. diving speed VD 290 kts MD 0.62 (S/N 101 – 683) MD 0.58 (S/N 684 onwards) Max. maneuvering operating speed VO 161 kts at 4500 kg) Stall speed (at TOW) Flaps up 93 kts (CAS) (engine running flight idle) Flaps down 65 kts (CAS) Center of Gravity Limits. At 4500 kg 30% MAC to 43% MAC Forward cg limit varies linearly between: (landing gear extended) 4500 kg (9921 lbs) 30% MAC 3700 kg (8157 lbs) 18% MAC 2600 kg (5732 lbs) and less 13% MAC Rear cg limit varies linearly between: (landing gear retracted) A78EU Page 5 of 15 4500 kg (9921 lbs) 43% MAC 3600 kg (7937 lbs) 46% MAC 3000 kg (6614 lbs) 46% MAC 2600 kg (5732 lbs) and less 20% MAC Maximum Weights. Ramp weight 4520 kg (9965 lbs) Take-off weight 4500 kg (9921 lbs) Landing weight 4500 kg (9921 lbs) Max. zero fuel weight 4100 kg (9039 lbs) Control Surfaces. Wing flaps 15° +0°/-1.5° Normal Take-off 30° +0°/-1.5° Short Take-off 39.5° +/-0.5° Landing (left/right asymmetry 1°) S/N 684 Onwards: Ailerons 26.5º +/- 0.5º Up 13º +/- 0.5º down Aileron tab 13.9º + /-1.0º up 14.5º +/- 1.0º down (trim function only – left hand tab) Aileron tab 15.5º + /-1.0º up 15.8º +/- 1.0º down (balance function only – both tabs) Aileron tab 29.3º + /-1.0º up 28.4º +/- 1.0º down (combined trim and balance function – left hand tab) When the ailerons are in the neutral position, both tabs are deflected 5º+/- 0.5º up. Certification Basis 1) 14 CFR Sections 21.29, 21.183(c) and 14 CFR 23, Normal Category, effective February 4, 1991, including Amendments 23-1 through 23-42 and 14 CFR 23, (23-43) 23.1305(c3) 14 CFR 23, (23-44) 23.49(c), 23.562(d) 14 CFR 23, (23-45) 23.479(b)(c), 23.851 (see Note 19), 23.1507 14 CFR 23, (23-49) 23.1311 2) 14 CFR Section 36, effective November 18, 1969, including Amendments 36-1 through amendment in effect at the time of U.S. Type Certification, and 3) 14 CFR Section 34, effective September 10, 1990, and 4) Equivalent level of Safety, a) ACE-94-8 of June 21, 1994, Spin demonstration, FAR 23.221 a)2) b) Cabin pressure indicator, FAR 23.841b) 6). See NOTE 8. 5) Section 611(b) of the FAA Act of 1958 6) Certification Maintenance Requirement (CMR), manual pitch trim system annunciation 7) Special Conditions: High Energy Radiated Electromagnetic Fields, (HERF), Number 23- ACE-46, effective date May 29, 1990 8) Approved for Flight Into Known Icing. See NOTE 4. The Swiss Federal Office of Civil Aviation (FOCA) originally type certificated this aircraft under its type certificate Number F-56-30. The FAA validated this product under U.S. Type Certificate Number A78EU. Effective June 23, 2006, the European Aviation Safety Agency (EASA) began oversight of this product on behalf of Switzerland. The EASA TCDS No. EASA.A.089. 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 June 23, 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: A78EU Page 6 of 15 • 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. Available Documents for the PILATUS PC-12/45 are: For S/N 101 – 400, except 321: Airplane Flight Manual Supplement No. 8 (Doc. No. 01973-001 / 9-08) Initial issue, or later FOCA approved revisions. For S/N 321 and S/N 401and subsequent: Airplane Flight Manual Report No. 02211 Initial issue or later FOCA approved revisions. III. Model PC-12/47 (Normal Category), approved December 23, 2005. The data given for model PC-12 is valid except where mentioned below: Airspeed Limits (EAS): Max. diving speed VD 290 kts MD 0.58 Max. maneuvering operating speed VO 163 kts at 4740 kg (10450 lbs) Stall speed (at TOW) Flaps up 95 kts (CAS) (engine running flight idle) Flaps down 67 kts (CAS) Center of Gravity Limits. At 4740 kg 30% MAC to 42.2% MAC Forward cg limit varies linearly between: (landing gear extended) 4740 kg (10450 lbs) 30% MAC 4500 kg (9921 lbs) 30% MAC 3700 kg (8157 lbs) 18% MAC 2600 kg (5732 lbs) and less 13% MAC Rear cg limit varies linearly between: (landing gear retracted) 4740 kg (10450 lbs) 42.2% MAC 4500 kg (9921 lbs) 43% MAC 3600 kg (7937 lbs) 46% MAC 3000 kg (6614 lbs) 46% MAC 2600 kg (5732 lbs) and less 20% MAC Maximum Weights. Ramp weight 4760 kg (10495 lbs) Take-off weight 4740 kg (10450 lbs) Landing weight 4500 kg (9921 lbs) Max. zero fuel weight 4100 kg (9039 lbs) Control Surfaces. Wing flaps 15° +0°/-1.5° Normal Take-off 30° +0°/-1.5° Short Take-off 39.5° +/-0.5° Landing (left/right asymmetry 1°) Ailerons 26.5º +/- 0.5º Up 13º +/- 0.5º down Aileron tab 13.9º + /-1.0º up 14.5º +/- 1.0º down (trim function only – left hand tab) Aileron tab 15.5º + /-1.0º up 15.8º +/- 1.0º down (balance function only – both tabs) Aileron tab 29.3º + /-1.0º up 28.4º +/- 1.0º down (combined trim and balance function – left hand tab) When the ailerons are in the neutral position, both tabs are deflected 5º+/- 0.5º up. Certification Basis 1) 14 CFR Sections 21.29, 21.183(c) and 14 CFR 23, Normal Category, effective February 4, 1991, including Amendments 23-1 through 23-42 and 14 CFR 23, (23-43) 23.1305(c3) 14 CFR 23, (23-44) 23.49(c), 23.562(d) 14 CFR 23, (23-45) 23.479(b)(c), 23.851 (see Note 19), 23.1507 14 CFR 23, (23-49) 23.1311 A78EU Page 7 of 15 2) 14 CFR Section 36, effective November 18, 1969, including Amendments 36-1 through amendment 36-27, effective September 6, 2005, 3) 14 CFR Section 34, effective September 10, 1990, including amendments 34-1 as amended through Amendment 34-3 effective February 3, 1999; 4) Equivalent level of Safety findings per provision of 14 CFR 21.21(b)(1): a) ACE-94-8 of June 21, 1994, Spin demonstration, FAR 23.221 a)2) as extended by FAA memorandum dated November 29, 2005. b) ACE-05-18 of November 29, 2005, Cabin pressure indicator, FAR 23.841b) 6) 5) Special Conditions: High Energy Radiated Electromagnetic Fields, (HERF), Number 23- ACE-46, effective date May 29, 1990 6) Approved for Flight Into Known Icing. See NOTE 4. 7) Section 611(b) of the FAA Act of 1958 8) Certification Maintenance Requirement (CMR), manual pitch trim system annunciation Date of Application for U.S. Amended Type Certificate for PC-12/47 model December 1, 2004. The Swiss Federal Office of Civil Aviation (FOCA) originally type certificated this aircraft under its type certificate Number F-56-30. The FAA validated this product under U.S. Type Certificate Number A78EU. Effective June 23, 2006, the European Aviation Safety Agency (EASA) began oversight of this product on behalf of Switzerland. The EASA TCDS No. EASA.A.089. 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 June 23, 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. Available Documents for the PILATUS PC-12/47 are: Airplane Flight Manual Report No. 02211, Initial issue or later FOCA approved revisions. (specific PC-12/47 data is contained in AFM Supplement No. 33) Aircraft Maintenance Manual Doc. No. 02049 Revision 17, dated 31 Jan 2006 or higher. (Chapter 4 FAA and FOCA approved) IV. Model PC-12/47E (Normal Category), approved March 28, 2008. The data given for model PC-12 is valid except where mentioned below: Engine. Pratt & Whitney PT6A-67P Fuel. Approved fuels in accordance with AFM 02277 A78EU Page 8 of 15 Engine Limits. Shaft Power Torque N1 Gas Generator Speed Prop Shaft Speed Maximum Observed Inter Turbine Temp. shp PSI % RPM ºC Take-off Max. climb Max. cruise Starting (5 seconds) Transient (20 seconds) 1200 1200 1000 --- --- 44.34 44.34 36.95 --- 61.00 104 104 104 --- 104 1700 1700 1700 --- 1870 850 820 820 1000 870 Engine. Pratt & Whitney PT6E-67XP (NOTE 16) Fuel. Approved fuels in accordance with AFM 02406 Shaft Power Torque N1 Gas Generator Speed Prop Shaft Speed Maximum Observed Inter Turbine Temp. shp PSI % RPM ºC Take-off Max. climb Max. cruise Starting (5 seconds) Transient (20 seconds) 1200 1200 1100 --- --- 44.84 44.84 40.63 --- 61.00 104 104 104 --- 104 1700 1700 1700 --- 1870 850 825 820 1000 900 Propeller and Propeller Hartzell HC-E4A-3D hub with Hartzell E10477SK Shot Peened aluminum blades; Limits. four blade constant speed type. (See NOTE 12) Hartzell HC-E5A-3A hub with NC10245B, 5 Carbon composite blades (See NOTE 15) Hartzell HC-E5A-31A hub with NC10245B, 5 Carbon composite blades (See NOTE 16) Spinner: Hartzell D5500-1 (Aluminum) applicable to HC-E4A-3D hub. Spinner: Hartzell 105820 (Aluminum), applicable to HC-E5A-3A and HC-E5A-31A hubs. Diameter: 104 in (2.642 m) to 105 in (2.667 m) cropping of blade tips not permitted. Pitch settings (measured at 42 in. station) 4-Blade propeller 5-Blade propeller Fine pitch 19.0º 14.7º Min. pitch in flight 6.0º 6.0º Max. reverse pitch -17.5º -17.5º Feathered 79.6º 80.0º Stabilized ground operation is prohibited between 350 and 950 RPM. Stabilized ground operation is prohibited between 350 and 900 RPM (See NOTE 16). Airspeed Limits (EAS): Max. diving speed VD 290 kts MD 0.58 Max. maneuvering operating speed VO 163 kts at 4740 kg (10450 lbs) VO (See Note 16) 166 kts at 4740 kg (10450 lbs) Stall speed (at TOW) Flaps up 95 kts (CAS) (engine running flight idle) Flaps down 67 kts (CAS) A78EU Page 9 of 15 Center of Gravity Limits. At 4740 kg 30% MAC to 42.2% MAC Forward cg limit varies linearly between: (landing gear extended) 4740 kg (10450 lbs) 30% MAC 4500 kg (9921 lbs) 30% MAC 3700 kg (8157 lbs) 18% MAC 2600 kg (5732 lbs) and less 13% MAC Rear cg limit varies linearly between: (landing gear retracted) 4740 kg (10450 lbs) 42.2% MAC 4500 kg (9921 lbs) 43% MAC 3600 kg (7937 lbs) 46% MAC 3000 kg (6614 lbs) 46% MAC 2600 kg (5732 lbs) and less 20% MAC Maximum Weights. Ramp weight 4760 kg (10495 lbs) Take-off weight 4740 kg (10450 lbs) Landing weight 4500 kg (9921 lbs) Max. zero fuel weight 4100 kg (9039 lbs) Control Surfaces. Wing flaps 15° +0°/-1.5° Normal Take-off 30° +0°/-1.5° Short Take-off 39.5° +/-0.5° Landing (left/right asymmetry 1°) Ailerons 26.5º +/- 0.5º Up 13º +/- 0.5º down Aileron tab 13.9º + /-1.0º up 14.5º +/- 1.0º down (trim function only – left hand tab) Aileron tab 15.5º + /-1.0º up 15.8º +/- 1.0º down (balance function only – both tabs) Aileron tab 29.3º + /-1.0º up 28.4º +/- 1.0º down (combined trim and balance function – left hand tab) When the ailerons are in the neutral position, both tabs are deflected 5º+/- 0.5º up. Certification Basis 1) 14 CFR Sections 21.29, 21.183(c) and 14 CFR 23, Normal Category, effective February 4, 1991, including Amendments 23-1 through 23-42 and: 14 CFR 23, (23-43) 23.1305(c3), 23.1322(e), 23.1331(a)(b1)(b2)(c), 23.1357(a)(e) 14 CFR 23, (23-44) 23.49(c), 23.562(d) 14 CFR 23, (23-45) 23.305(a), 23.361 (a)(b2), 23.479(b)(c), 23.571(a), 23.572(a1)(b1), 23.613, 23.773(a1)(a2), 23.851 (See Note 19). 23.1507, 23.1525 14 CFR 23, (23-48) 23.301, 23.335(a)(b)(c)(d), 23.371(a), 23.561(b2)(b3)(c3), 23.607(c), 23.629(a)(b)(c)(d)(e)(f2) 14 CFR 23, (23-49) 23.1303(a)(b)(c)(d)(e)(f), 23.1307, 23.1311, 23.1323(c), 23.1326(a)(b), 23.1329, 23.1351(b2)(b3)(c)(c1)(c2)(c3)(c4)(c5)(g), 23.1353(h), 23.1359, 23.1361(a)(b)(c), 23.1365(b)(c)(c1)(d)(e)(f), 23.1431(a)(b)(c)(d)(e) 14 CFR 23, (23-50) 23.143(c), 23.562(d1), 23.1543(c), 23.1555(e2) 14 CFR 23, (23-62) 23.1303 (c) – (Airplanes where the Magnetic Standby Compass is not installed (Note 15) 2) 14 CFR Section 36, effective November 18, 1969, including Amendments 36-1 through amendment 36-28, effective January 4, 2006, 3) 14 CFR Section 34, effective September 10, 1990, including amendments 34-1 as amended through Amendment 34-3 effective February 3, 1999; 4) Equivalent level of Safety findings per provision of 14 CFR 21.21(b)(1): a) ACE-94-8 of June 21, 1994, Spin demonstration, FAR 23.221 a)2) as extended by FAA memorandum dated November 7, 2007. b) ACE-05-18 of November 29, 2005, Cabin pressure indicator, FAR 23.841b) 6) as extended by FAA memorandum dated November 7, 2007. c) ACE-07-14 of January 7, 2008, Probes OFF Caution, FAR 23.1326(b)(1) d) ACE-07-15 of January 8, 2008, ASI Flap Markings, FAR 23.1545(b)(4) e) ACE-08-02 of February 26, 2008, Circuit Protective Devices, FAR 23.1357(b) 5) Special Conditions: a) Protection of Systems for HIRF, Number 23-216-SC, effective date November 30, 2007 A78EU Page 10 of 15 6) Approved for Flight Into Known Icing. See NOTE 4. 7) Section 611(b) of the FAA Act of 1958 8) Certification Maintenance Requirement (CMR), manual pitch trim system annunciation Date of Application for U.S. Amended Type Certificate for PC-12/47E model December 6, 2004. The Swiss Federal Office of Civil Aviation (FOCA) originally type certificated this aircraft under its type certificate Number F-56-30. The FAA validated this product under U.S. Type Certificate Number A78EU. Effective June 23, 2006, the European Aviation Safety Agency (EASA) began oversight of this product on behalf of Switzerland. The EASA TCDS No. EASA.A.089. Certification Basis (NOTE 16)