TCDS A00072CE

Page No. 1 2 3 4 5 6 7 8 9 10 Rev. No. 12 11 11 11 8 12 4 11 11 12 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A00072CE Revision 12 Pilatus PC-24 June 18, 2024 TYPE CERTIFICATE DATA SHEET NO. A00072CE This data sheet which is a part of Type Certificate No. A00072CE prescribes conditions and limitations under which the product for which the Type Certificate was issued meets the airworthiness requirements of the Federal Aviation Regulations. TC Holder. Pilatus Aircraft Ltd Stans, Switzerland Type Certificate Holder Record: Pilatus Aircraft Ltd Stans, Switzerland I. Model PC-24 (Commuter Category), Approved: December 7, 2017 Engine. Number of Engines: 2 Engine Manufacturer: Williams International Engine Model Number: FJ44-4A-QPM Fuel. J et A, Jet A1, JP-8 and TS-1. Engine Limits. Operating condition Thrust lbs. N1% N2% ITT °C Oil Pressure psi Oil Temp. °C Normal Takeoff 3420 104.7 100.8 855 40 - 120 10 - 135 Max Takeoff (ATR) 3600 104.7 100.8 855 40 - 120 10 - 135 Maximum Cont/Climb 104.7 100.8 835 40 - 120 10 - 135 Ground or Flight Idle (cont) 30 Min 120 Max -40 - 135 QPM 45.4 30 - 120 10 - 135 Starting See Airplane Flight Manual -40 - 135 Transient High 105.7 (2min) 101.5 (2min) 855 (0s) 130 149 Transient Low 23 Page 2 of 10 A00072CE Airspeed Limits. Center of Gravity (C.G). Range. For Aircraft MSN 101 - 130 Post SB 42-002, and MSN 131 – 500: (NOTE 6) Condition Limit (design) Limit (IAS) VMO (maximum operating speed) 290 KEAS 290 KIAS MMO (maximum operating Mach number) 0.74 Mach 0.74 Mach VD (maximum dive speed) 360 KEAS MD (maximum operating Mach number) 0.81 Mach VA (maneuvering speed) at MTOW For aircraft MSN 101 - 500 For aircraft MSN 501 - Up 185 KEAS 187 KEAS VC (design cruising speed) 290 KEAS VFE (max. flap extended speed): - 8° (Take-Off) Flap - 15° (Approach) Flap - 33° (Landing) Flap 200 KEAS 200 KEAS 175 KEAS 200 KIAS 200 KIAS 175 KIAS VLO (maximum landing gear operating speed) - Extension - Retraction 250 KEAS 200 KEAS 250 KIAS 200 KIAS VLE (maximum landing gear extended speed) 250 KEAS 250 KIAS VSO (Stall speed (ISA, sea level, max. landing weight, landing configuration)) For aircraft MSN 101-130 Pre SB 42-002 For aircraft MSN 101 - 130 Post SB 42-002, and 131 – Up For aircraft with Design Weight Increase MSN 501 – Up (NOTE 8) ≤ 82 KCAS 82 KCAS 83KCAS Page 3 of 10 A00072CE PC-24 Weight & CG Envelope 8600 8400 - Trimmed Flight Envelope 8000 7800 7600 7400 7200 7000 6800 56 6600 5800 5600 5400 5200 5000 4800 4600 4400 4200 4000 20 21 22 25 24 25 26 27 28 32 35 34 35 36 37 40 42 43 44 45 46 47 48 49 50 CG (%MAC) For aircraft MSN 101 - 130 Pre SB 42-002: PC-24 Weight & CG Envelope 8600 8400 8200 - Trimmed Flight Envelope 8000 7800 7600 7400 7200 7000 6800 6600 6400 6200 6000 5800 5600 5400 5200 5000 4800 4200 4000 20 21 22 23 24 26 29 30 31 32 33 34 35 36 37 38 39 40 41 42 43 44 45 46 47 48 49 50 CG (%MAC) Page 4 of 10 A00072CE For aircraft with Design Weight Increase MSN 501 – Up: (NOTE 8) Empty Weight C.G. Range. None. Datum. The Datum is 146.1 in (3,711 mm) forward of forward jacking point. Leveling Means. Levelling datum which is the seat rail behind the cargo door Maximum Weights. For aircraft MSN 101 - 130 Post SB 42-002, and 131 – 500 (NOTE 6): Parameter Metric Imperial Maximum Ramp Weight (MRW) 8,345 kg 18,400 lb. Maximum certified Take-Off Weight (MTOW) 8,300 kg 18,300 lb. Useable fuel[1] 2,705 kg 5,964 lb. Maximum Zero-Fuel Weight (MZFW) 6,450 kg 14,220 lb. Maximum Landing Weight (MLW) 7,665 kg 16,900 lb. Minimum Flying Weight (MFW) 4,988 kg 11,000 lb. For aircraft MSN 101 - 130 Pre SB 42-002: Parameter Metric Imperial Maximum Ramp Weight (MRW) 8,050 kg 17,750 lb. Maximum certified Take-Off Weight (MTOW) 8,005 kg 17,650 lb. Useable fuel[1] 2,705 kg 5,964 lb. Maximum Zero-Fuel Weight (MZFW) 6,100 kg 13,450 lb. Maximum Landing Weight (MLW) 7,370 kg 16,250 lb. Minimum Flying Weight (MFW) 4,814 kg 10,613 lb. For aircraft with Design Weight Increase MSN 501 – Up (NOTE 8): Parameter Metric Imperial Maximum Ramp Weight (MRW) 8,545 kg 18,840 lb. Maximum certified Take-Off Weight (MTOW) 8,500 kg 18,740 lb. Page 5 of 10 A00072CE Useable fuel[1] 2,705 kg 5,964 lb. Maximum Zero-Fuel Weight (MZFW) 6,650 kg 14,660 lb. Maximum Landing Weight (MLW) 7,865 kg 17,340 lb. Minimum Flying Weight (MFW) 4,988 kg 11,000 lb. Minimum Crew. One (1) pilot (left seat) -OR- Two (2) pilots Number of Seats. Executive Interiors Configuration: 8 seats excluding pilot seats. Commuter Interiors Configuration: 10 seats excluding pilot seats NOTE: Refer to the Airplane Flight Manual (02371) section 6 “Weight & Balance” for seat locations and moment arms. Maximum Compartment Weights. 1000 lb. (454 kg) The standard cabin compartment configuration includes only 1 compartment. The moment arms, depending on the restraint system (baggage net) used are. moment arm maximum capacity Small Net 413.8in (10510mm) 180kg Large Net 408in (10363mm) 240kg To reach the full baggage of 1000lb (454kg) a combination of the large net and tie down bars is required and the moment arm is 408in (10363mm). Fuel Capacity. Total capacity: 895 US gal (3389 Liters). (5999.8 lb or 2721kg) Usable quantity: 890 US gal (3369 Liters or 2705 kg) Usable quantity each tank: 445 US gal Moment arm for each usable fuel tank: 317 in (8052mm) when full Unusable quantity: 5.3 US gal (20 Liters or 16 kg) Unusable quantity each tank: 2.65 US gal Moment arm for each unusable fuel tank: 318.5 in (8089mm) (see Note 1) Oil Capacity. Total capacity: 5.85 US qts. Usable quantity: 4.32 qts. Moment arm for oil: 480.3 in (12200mm) (see Note 1) Hydraulic Capacity. Total capacity: 1.14 US gal. Usable quantity: 1.14 US gal. Moment arm for hydraulic: 316.9 in (8048mm) Maximum Operating Altitude. 45000ft (13716m) Control Surface Movements. Elevator: Up 25° +1°/-0° Down 15° +1°/-0° Aileron: Up 25° ± 0.5o Down 15o ±0.5o Rudder: Right 28° ± 0.5o Left -28 ± 0.5o Stabilizer: A/C Nose up direction -10 o neutral 0o A/C Nose down direction +05 o Flaps: Up 0o Down 33° ± 0.5o Manufacturer’s Serial Numbers MSN 101 and up Page 6 of 10 A00072CE Import Requirements. A U.S. airworthiness certificate may be issued on the basis of the Swiss Certificate of Airworthiness for Export signed by a representative of the Swiss Federal Office of Civil Aviation (FOCA) on behalf of the European Community, containing the following statement: ‘The aircraft covered by this certificate has been examined, and found to comply with U.S. 14 CFR Part 23 covered under U.S. Type Certificate No. A00072CE and to be in a condition for safe operation.’ The U.S. airworthiness certification basis for this aircraft type certificated under FAR § 21.29 and exported by the country of manufacture is FAR § 21.183 (c). Per 21.50(b), Instructions for Continued Airworthiness (ICA) complying with FAR 23.1529, must be furnished before delivery of the first airplane or issuance of a US standard certificate of airworthiness, whichever occurs later. (NOTE 4) 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 part 21.29, part 21.183(c) and 14 CFR Part 23, effective December 18, 1964, with amendments 1 through amendment 62 “Airworthiness Standards for Commuter Category Airplanes” Additional airplanes with main rechargeable Lithium Batteries (NOTE 7) comply with §23.2010 and §23.2525 at amendment 23-64. Airplanes with the optional two-place side facing divan (NOTE 9) comply with §23.2010, §23.2270, and §23.2525 at amendment 23-64. The detailed design standards used as a means of compliance in accordance with § 23.2010 are documented in Pilatus PC-24 DDS summary document PC24-DDS-001, Issue 01, dated 18 June 2024. 2) 14 CFR Part 34, effective September 10, 1990 including Amendments 34-1 through Amendment 34-5A “Fuel Venting and Exhaust Emission Requirements For Turbine Engine Powered Airplanes” 3) 14 CFR Part 36, effective December 1, 1969 with Amendments 36-1 through Amendment 36-30, Stage 4, “Noise Standards: Aircraft Type and Airworthiness Certification”. For aircraft MSN 501 and up (NOTE 8), 14 CFR part 36 effective December 1, 1969 with Amendments 36-1 through Amendment 36-31, Stage 4, “Noise Standards: Aircraft Type and Airworthiness Certification”. 4) 14 CFR Part 21.16 Special Conditions (SC) issued in accordance with 14 CFR Part 11: (a) SC 23-282-SC effective July 17, 2017 - Electronic Engine Control (EEC) (b) SC 23-283-SC effective July 17, 2017 - Autothrust System (c) SC 23-284-SC effective July 17, 2017 - Pressure Defuel System 5) Equivalent Safety Findings (ELOS) according to the provisions of 14 CFR part 21.21(b)(1) for the following subjects: ELOS No., date and Subject Regulation modified by ELOS Page 7 of 10 A00072CE (a) TC00607CE-A-G-9, dated Feb. 14, 2017: Amendment 23-62 Corrections §§ 23.45, 23.51, 23.63, 23.67, 23.73, 23.77, 23.161, 23.181, 23.221, 23.251; 23.253, 23.571, 23.785, 23.831, 23.1195, 23.1197, 23.1199, 23.1201; 23.1527, 23.1545, and 23.1583. (b) TC00607CE-A-F-3, dated April 18, 2017: Use of 1-g Stall Speed Criteria §§ 1.1, 1.2, 23.49, 23.69, 23.143, 23.145, 23.147, 23.149, 23.157, 23.175, 23.177, 23.201, 23.203, 23.207, 23.233, 23.729, 23.735, 23.1001, 23.1323, 23.1325, and 23.1587. ELOS Memo TC00607CE-A-G-9 ES23.51, ES23.67, ES23.73, ES23.161, and ES23.1545. c) TC00607CE-A-E-14, dated Feb. 24, 2017: Storage Battery Design and Installation § 23.1353(h)(1)(ii) (d) TC00607CE-A-E-6, dated Mar. 21, 2017: Integrated Modular Avionics (IMA) circuit protection § 23.1357(b) (e) TC00607CE-A-S-8, dated June 29, 2017: Digital Only Powerplant Indications §§ 23.1305(a)(2), (a)(3), (c)(2), and (c)(5); and 23.1549(a), (b), and (c) (f) TC00607CE-A-S-9, dated Oct. 26, 2017: Airspeed Indicator - Flap Markings § 23.1545(b)(4) (g) TC00607CE-A-S-15, Oct. 26 2017: Third Attitude Instrument Without Independent Power Source §§ 23.1303 (g)(3)(i), (ii), and (iv) (h) TC00607CE-A-S-21, Nov. 6, 2017: Pressurization and Pneumatic Systems §23.1438(b) 6) No Exemptions. 7) The airplane is approved for flight into known or forecasted icing. Compliance has been demonstrated in accordance with 14 CFR § 23.1416 and 23.1419. 8). The airplane is approved for ditching. Compliance with the provisions for ditching equipment has been demonstrated in accordance with 14 CFR §§ 23.807 and 23.1415(a)(b). EASA issued EASA type certificate EASA.A.594 dated December 7, 2017. Date of Application for FAA Type Certificate: July 27, 2012. Type Certificate No. A00072CE, issued December 7, 2017. RVSM capability for PC-24 MSN P03, 101 and subsequent: All airplanes equipped with Honeywell APEX system are RVSM approved provided the operator follows the Airplane Flight Manual (AFM) Issue 003 Revision 01 dated 12 July 2018 (or later revisions), and the Aircraft Maintenance Manual (AMM) Issue 005 Revision 00 dated 06 June 2018 (or later revisions). (NOTE 5) Page 8 of 10 A00072CE Production Basis. No FAA production certificate. PC-24 airplanes, all series and models, are produced under production approval CH.21G.0002, issued by the Swiss Federal Office of Civil Aviation (FOCA). Equipment. The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the aircraft for certification. An FAA approved (M)MEL may be used to operate the aircraft with inoperative equipment. Service Information. Each of the documents listed below must state that it is approved by the European Aviation Safety Agency (EASA): • 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-24 are: Airplane Flight Manual Suite: (NOTE 6) • Airplane Flight Manual (AFM) Report No. 02371, Issue 003 Revision 00 date d 24 January 2018 or later EASA approved revisions. (See NOTE 2) • Flight Crew Operating Manual (FCOM) Report No. 02383, Issue 003 Revision 00 dated 24 January 2018 or later EASA approved revisions. • Quick Reference Handbook (QRH) Report No. 02382, Issue 003 Revision 00 dated 24 January 2018 or later EASA approved revisions. Instructions for Continued Airworthiness (ICA): (NOTE 4) • Air Vehicle Maintenance (AM) / Aircraft Maintenance Manual (AMM) Report No. 02378, Issue 00 3 Revision 00 date d 24 January 2018 or later EASA approved revisions (Chapter 4 is FAA and EASA approved). (See Note 3) • Illustrated Parts Data (IPD) / Illustrated Parts Catalogue (IPC) Report No. 02377, Issue 003 Revision 00 dated 24 January 2018 or later revisions. • Air Vehicle Structural Repair (ASR) / Structural Repair Manual (SRM) Report No. 02379, Issue 003 Revision 00 dated 24 January 2018 or later revisions. • Illustrated Tools and Equipment (ITE) / Illustrated Tools and Equipment Manual (ITEM) Report No. 02380, Issue 003 Revision 00 date d 24 January 2018 or later revisions. • Wiring Data (WD) / Wiring Diagram Manual (WDM) Report No. 02381, Issue 003 Revision 00 dated 24 January 2018 or later revisions. For Aircraft with Design Weight Increase MSN 501 – Up (NOTE 8) Page 9 of 10 A00072CE • Airplane Flight Manual (AFM) Report No. 02371, Issue 003 Revision 07, or later EASA approved revisions. (See Note 2) • Air Vehicle Maintenance (AM) / Aircraft Maintenance Manual (AMM) Report No. 02378, Issue 006 Revision 00, or later EASA approved revisions (Chapter 4 is FAA and EASA approved). (See Note 3) NOTES NOTE 1 A current weight and balance report, including a list of equipment included in the certificated empty weight, and loading instructions when necessary, must be provided for each airplane at the time of original certification. The Manufacturers Empty Weight (MEW) is the weighed weight of the aircraft without any fuel or oil. Unusable fuel quantity and unusable oil quantity shall be added to the certified empty a/c weight. NOTE 2 All required placards are contained in Chapter 2 of the Airplane Flight Manual (AFM) Report No. 02371, Issue 003 Revision 00 dated 24 January 2018 or later approved revisions and must be installed in the appropriate locations. Revisions to this report may be approved by EASA on behalf of the FAA, unless they are changes to the limitation section. These changes require FAA approval for the US version. NOTE 3 Mandatory retirement lives, required inspections, and inspection intervals of components are listed in the Airworthiness Limitations Section, Chapter 4, of the Airplane Maintenance Manual, document 02378, Issue 003 Revision 00 dated 24 January 2018 or later approved revisions. The Airworthiness Limitations Section was approved by EASA and the FAA. Revisions to this section must be approved by EASA and the FAA. NOTE 4 On January 19, 2018, the complete set of ICAs have been FAA accepted per 21.50 (b). The revised ALS Chapter 4, of the Airplane Maintenance Manual, document 02378, Issue 003 Revision 00 dated 24 January 2018 is part of the complete ICAs that will be effective for the first airplane delivery MSN 101. History - The ALS section of the ICA, chapter 4, dated November 29, 2017 was FAA approved on December 4, 2017, which was before the TC was issued, but the rest of the ICAs at that time had not been accepted yet per allowance of 21.50 (b). The complete set of ICAs are identified above in section “Service Information”. NOTE 5 Operational approval to fly in RVSM airspace must still be granted by the cognizant Flight Standards organization and each operator must obtain RVSM operating approval directly from the FAA. NOTE 6 FAA Project AT00993CE-A - Pilatus increased the Maximum Take-off Weight and Max Zero Fuel Weight for MSN 101-130 when SB 42-002 is accomplished and for MSN 131 and subsequent at the factory. For these higher weights, the following AFM Report No. 02371 Temporary Revisions (TR) dated Oct. 1, 2018 or later AFM revisions must be followed. TR-003-01-03 - AFM section 2, TR-003-01-04 - AFM section 5, TR-003-01- 05 - AFM section 6, TR-003-01-10 - AFM section 5, TR-003-01-11 - AFM section 2, TR-003-01-12 - AFM section 3A NOTE 7 Pilatus has incorporated optional type design for installation of main ship Rechargeable Lithium Battery. This requires AMM Issue 005 revision 23 or later EASA approved revisions and AFM TR 02371-021 “Changes for Li-Ion Batteries” or later EASA approved revisions. . NOTE 8 FAA Project AT01146CE-A - the PC-24 with design weight increase MSN 501 – Up: These airplanes are structurally modified. This MSN range must be operated and maintained in accordance with the following AFM Report No. 02371 Temporary Revisions (TR) dated July 7, 2023 or later AFM revisions must be followed. TR 02371- 061 - AFM sections 2, 3A and 6, TR 02371-062 - AFM section 5. This MSN range of airplane must use Air Vehicle Maintenance (AM) / Aircraft Maintenance Manual (AMM) Report No. 02378, Issue 006 Revision 00 or later EASA Page 10 of 10 A00072CE approved revisions. (Chapter 4 Temporary Revision TR-00-01 dated July 7, 2023) is FAA and EASA approved). The complete set of ICAs are identified above in section “Service Information”. NOTE 9 FAA project AT11261IB-A installed an optional side-facing divan currently limited to two-place. .....END......