# TCDS A78EU: Pilatus Aircraft Ltd.

- Type: Type certificate data sheet
- Status: Current
- Holder: Pilatus Aircraft Ltd.
- Revision: 39
- Revised: July 2, 2025
- Product: Aircraft, Small Airplane
- Certification basis: Part 23, Part 21
- Registered aircraft: 1,443, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/6b/c2/6bc29bb4f262e315434298d97e1e5212f2dcb661ed8248c0f45a5d8766b4f7e3
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID189544976220250702193427.0001
- Page: https://openairdocs.org/tcds/A78EU

## Models (5)

As the data sheet lists them.

- PC-12
- PC-12/47E
- PC-12/45
- PC-12/47
- PC-12/47G

## What the data sheet says

From the PDF's text layer, line by line; tables lose their columns. The PDF is the record.

```text
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) 
  
[FAR 23 Paragraph (Amdt level)] - Below are the areas of change that are at a higher amendment than the PC-12/47E and are the 
new certification basis for airplanes with the Pratt and Whitney PT6E-67XP engine. 
 
14 CFR 23, (23-45) 23.361, 23.672 
14 CFR 23, (23-48) 23.337, 23.341, 23.347, 23.443, 23.572, 23.629 
14 CFR 23, (23-49) 23.677, 23.1321, 23.1365  
14 CFR 23, (23-50) 23.69, 23.147, 23.175, 23.1589  
14 CFR 23, (23-57) 23.1308 
14 CFR 23, (23-59) 23.905, 23.907(c) 
14 CFR 23, (23-61) 23.1306 
14 CFR 23, (23-62) 23.63, 23.177, 23.181, 23.1309, 23.1310  
 
 
 2)   14 CFR Section 34, effective September 10, 1990, including amendments 34-1  
                                                                as amended through Amendment 34-5A effective October 23, 2013;  
 
3)    14 CFR Part 21.16 Special Conditions (SC) issued in accordance with 14 CFR  
       Part 11:  
 
(a) SC 23-294-SC effective August 15, 2019 - Autothrust System –signed 8/1/2019; 
(b)   SC 23-295-SC effective August 15, 2019 - Electronic Engine Control (EEC) – 
8/8/2019   
 
4)     Equivalent Safety Findings (ELOS) per 21.21(b)(1) for the following subjects:  
 
(a) ELOS AT00923CE-A-P-3 dated August 16, 2019, Digital Only Display - 
Powerplant Indications, 14 CFR 23.1305(e) amendment 23-34; 23.1549(a), (b), 
and (c), amendment 23-28; 
(b)  ELOS AT00923CE-A-P-4 dated August 16, 2019, Use of Interconnected Fuel 
Tanks without Tank Airspaces, 14 CFR 23.975(a)(4), amendment 23-29; 
(c)  ELOS AT00923CE-A-S-4 dated August 16, 2019, AutoThrottle (AT) Engage 
When Not Installed, 14 CFR 23.1301(b), amendment 23-20; 23.1555(a), 
amendment 23-21. 
 
 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

A78EU Page 11 of 15 
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-12/47E are:   
  
 Airplane Flight Manual Report No. 02277, Revision 6, dated March 26, 2008 or later      
                                               EASA approved revisions.  (See Note 13 and Note 15) 
  
Aircraft Maintenance Manual Doc. No. 02300, 12-B-AM-00-00-00-1, dated April 11, 2008, 
or later EASA approved revisions.  (Chapter 4 is FAA and EASA approved)  
(See Note 13 and Note 15)    
                                                           
                                                         MSN 1720, 2001 and subsequent (Note 16) and (Note 17) 
  
 Airplane Flight Manual Report No. 02406, Issue 002 Revision 00, dated October 14, 2019   
 or later EASA approved revisions.   
Airplane Flight Manual Temporary Revision Report No. AFM TR 02406 01 dated 26 
November 2019 or later EASA approved revisions.  
Aircraft Maintenance Manual Doc. No. AMM 02436, Issue 01, Revision 00, dated Nov. 22, 
2019 or later EASA approved revisions. (Chapter 4 is FAA and EASA approved) 
 
V. Model PC-12/47G (Normal Category), approved January 13, 2025.   
The data given for model PC-12 is valid except where mentioned below:  
 
Engine. Pratt & Whitney PT6E-67XP  
 
Fuel. Approved fuels in accordance with AFM 02523. 
 
 
 
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 Limits  Hartzell HC-E5A-31A hub with NC10245B, 5 Carbon composite blades  
  
    Spinner: Hartzell 105820 (Aluminium), applicable to 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) 
 
 5-Blade propeller 
Fine pitch 14.7º 
Min. pitch in flight 1.0º 
Max. reverse pitch -17.5º 
Feathered 80.0º 
 
 Stabilized ground operation is prohibited between 350 and 900 RPM.  
 
 
 
Airspeed Limits (EAS): Max. diving speed VD 290 kts  
  MD 0.58  
 Max. maneuvering operating speed VO                   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 12 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.        
 
 
Manufacturer’s Serial Numbers            MSN 3001 and subsequent (NOTE 21) 
 
 
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, 23.1322, 23.1331, 23.1357 
14 CFR 23, (23-44) 23.49, 23.562(d) 
14 CFR 23, (23-45) 23.305(a), 23.361, 23.479 23.571(a), 23.613, 23.672, 23.773, 
23.851, 23.1507, 23.1525 
14 CFR 23, (23-48) 23.301, 23.335, 23.337, 23.341, 23.347, 23.371, 23.443, 
23.561(b2)(b3)(c3), 23.572, 23.607(c), 23.629 
14 CFR 23, (23-49) 23.691, 23.1307, 23.1311, 23.1321, 23.1323, 23.1326, 23.1329, 
23.1351, 23.1353, 23.1359, 23.1361, 23.1365, 23.1431 
14 CFR 23, (23-50) 23.69, 23.143, 23.147, 23.562(d1), 23.175, 23.1543, 23.1555, 
23.1589 
14 CFR 23, (23-57) 23.1308 
14 CFR 23, (23-59) 23.905, 23.907(c) 
14 CFR 23, (23-61) 23.1306 
14 CFR 23, (23-62) 23.63, 23.177, 23.181, 23.1303, 23.1309, 23.1310 
14 CFR 23, (23-64) 23.2010, 23.2525, 23.2605, 23.2610, 23.2615 
 
                    The detailed design standards used as a means of compliance in accordance with § 23.2010   
                    are documented in Pilatus PC-12 DDS summary document PC12-DDS-001, Issue 01, dated  
                    27 November 2024, or later revisions. See Note 20:  
 
 2)   14 CFR Section 36, effective November 18, 1969, including Amendments 36-1 through 
amendment 36-31, effective November 3, 2017. 
 
3)   14 CFR Section 34, effective September 10, 1990, including amendments 34-1  
  as amended through Amendment 34-5A effective October 23, 2013.  
 
4) 14 CFR Part 21.16 Special Conditions (SC) issued in accordance with 14 CFR Part 11:  
 
      (a)   SC 23-294-SC effective August 15, 2019 - Autothrust System – signed 8/1/2019. 
  (b)   SC 23-295-SC effective August 15, 2019 - Electronic Engine Control (EEC) –

A78EU Page 13 of 15 
           8/8/2019. 
 
 5)  Equivalent level of Safety findings per provision of 14 CFR 21.21(b)(1) of the PC- 
                                                                      12/47E are unchanged and still applicable and extended to the PC-12/47G: 
 
• ACE-94-8 of June 21, 1994, Spin demonstration, FAR 23.221 a)2) as extended      
by FAA memorandum dated November 7, 2007.  
• ACE-05-18 of November 29, 2005, Cabin pressure indicator, FAR 23.841b) 6) as 
extended by FAA memorandum dated November 7, 2007. 
•   ELOS AT00923CE-A-P-4 dated August 16, 2019, Use of Interconnected Fuel 
Tanks without Tank Airspaces, 14 CFR 23.975(a)(4), amendment 23-29. 
 
 6)  Approved for Flight Into Known Icing.  
 7)  Approved for RVSM – all PC-12/47G models with AFM 02523, Issue 02, Rev 00, 
                                                                     or later EASA approved revisions.  
 8)  Certification Maintenance Requirement (CMR), manual pitch trim system annunciation  
 
 
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 Report No. 02523 (and applicable supplements). 
 Additional Equipment, see Equipment List No. 02563 Issue 01 Revision 00 or later  
                                                                approved revisions.     
 
 
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-12/47G are:   
  
Airplane Flight Manual Report No. 02523, Issue 003, Rev 00 dated July 01, 2025 or later 
EASA approved revisions.  (See Note 21)  
  
Aircraft Maintenance Manual Doc. No. 02547, Issue 02, Rev 00, dated July 04, 2025, or 
later EASA approved revisions.  (Chapter 4 is FAA and EASA approved)  
(See Note 21 and Note 22) 
 
 
NOTES 
 
NOTE 1. Current weight and balance data together with 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 certificated empty weight and corresponding center of gravity 
locations must include the following: 
 
a) unusable fuel of 19.6 kg (43.2 lbs) at 5.73 m (225.6 in) on S/N 101 up to and including S/N 140. 
     unusable fuel of 14.9 kg (32.9 lbs) at 5.73 m (225.6 in) from S/N 141 on onwards. 
 
 b) engine oil of 9.2 kg (20.3 lbs) at 2.41 m (95.27 in.)

A78EU Page 14 of 15 
NOTE 2. Airplane operation must be in accordance with the EASA/FOCA-approved Airplane Flight Manual listed above. 
All placards listed in Section 2 of the AFM must be displayed in the appropriate location. 
 
NOTE 3. Airworthiness Limitations are contained in the FOCA/EASA approved Chapter 4 of the PC-12, PC-12/45, PC-
12/47 & PC-12/47E Aircraft Maintenance Manual. These Limitations may not be changed without EASA and 
FAA approval. 
 
NOTE 4. The models PC-12 and PC-12/45 up to S/N 683 may be operated in known icing conditions when equipped in 
accordance with Pilatus Modification PIL 12/00/001, Rev. 1, or later FOCA/EASA approved revision. The 
models PC-12/45, PC-12/47, and PC-12/47E from S/N 684 onwards are approved for operation in known icing 
conditions. S/N 545 is also approved for operation in known icing conditions.   
 
NOTE 5. The basic version PC-12 (S/N 101 - 683) may be converted to a version PC-12/45 by executing 
PILATUS Service Bulletin No. 04-001.  
 
NOTE 6. Only interior configurations described in the official Pilatus AFM/POH are approved for installation 
in the PC-12, PC-12/45, PC-12/47 and PC-12/47E aircraft. These configurations have been shown to meet the 
dynamic and HIC test requirements of FAR 23.562. Any alterations to these approved interior layouts must be 
shown to meet FAR 23.562. 
 
NOTE 7. All PC-12 models are eligible for import (with FOCA export certificate of airworthiness) into the USA in the no 
cabin interior configuration option installation per Pilatus Document 500.20.12.399 for ferry flight delivery to 
the USA, but carriage of passengers (other than those essential to the mission) in this configuration is prohibited.  
 
NOTE 8. An ELOS memorandum was inadvertently missed on the original PC-12 model and PC-12/45 model, but was 
evaluated during the validation of the PC-12/47. See FAA memorandum dated December 9, 2005 for details.   
 
NOTE 9. The PC-12/45 model incorporated an aerodynamic improvement modification (AIM) type design change that 
was approved at the same time the PC-12/47 model was approved. This modification is for production aircraft 
only and includes: modified wingtips, modified dorsal and ventral fins and modified ailerons (reduction of roll 
control forces). 
 
NOTE 10. Starting with Manufacture Serial Number (MSN) 684, and up to MSN 999, can be either a PC-12/45 with the 
AIM type design change or a PC-12/47 model. 
 
NOTE 11. Starting with Manufacture Serial Number (MSN) 1001 and subsequent will only be a PC-12/47E model.  MSN 
545 is also a PC-12/47E model. 
 
NOTE 12. Only the Hartzell E10477SK Shot Peened aluminum blades with the Hartzell HC-E4A-3D hub is allowed on the 
PC-12/47E model.  This Shot Peen Hartzell E10477SK propeller can be used on the PC-12, PC-12/45 and PC-
12/47 airplane, but the Hartzell E10477K “non-shot peened” cannot be used on the PC- 12/47E airplane. See the 
appropriate Pilatus Airworthiness limitation sections. 
 
NOTE 13. PC-12/47E MSN 545 and MSN 1001 up to 1944:  All airplanes equipped with Honeywell APEX system are 
RVSM capable provide the operator incorporates and follows airplane flight manual supplement (AFMS) No. 4 
Revision 1 dated May 28, 2009 or later version and Airplane Maintenance Manual document number 02300 
Revision 2, dated June 3, 2009 or later AMM version.  
 
NOTE 14. PC-12/47E MSN 1300, MSN 1451 up to 1944: These airplanes are fitted with the Electromechanical Landing 
Gear (eLDG) and must be operated and maintained in accordance with the Airplane Flight Manual, document 
no. 02277, Supplement 11, issue dated March 2, 2012 or later revisions and Airplane Maintenance Manual, 
document number 02300, Airworthiness Limitations  
12-B-04-00-00-00A-000A-A, dated November 26, 2013 or later EASA and FAA approved revisions. 
 
NOTE 15. The PC-12/47E aircraft is Transmitting-PED tolerant.  
 PC-12/47E MSN 1576 and subsequent as well as aircraft which have SB 34-042 (Introduction of the L3 ESIS) 
embodied, can have the standby magnetic compass removed (23.1303(c) at 23-62). 
 
 PC-12/47E MSN 1576 up to 1944: These airplanes are eligible to be fitted with the Hartzell 5-Blade Composite 
Propeller. The aircraft must be operated in accordance with the Airplane Flight Manual, document no. 02277 
revision 15, dated November 6, 2015 or later versions and airplane Maintenance Manual, document number 
02300 Revision 14, dated November 6, 2015 or later EASA and FAA approved revisions.  
 
NOTE 16. The PC-12/47E MSN 1720, MSN 2001 and subsequent: These airplanes are fitted with: 
-  Pratt and Whitney PT6E-67XP engine with Electronic Engine Control (EEC); 
-  APEX Build 12 or later versions, providing functions such as Autothrust (Optional), Tactile  
   Feedback and Emergency Descent Mode and Low Propeller Speed (Optional);  
-  New Executive Seats and Larger cabin windows; 
-  Revised Fuel System enabling the use of fuel without anti-icing additives within the certified outside 
temperature limits of the airplane with the fuel system basic architecture and means of operation are maintained;  
-  Electromechanical Landing Gear (eLDG).

A78EU Page 15 of 15 
-  The airplanes are RVSM capable.  
-  These airplanes are also Transmitting-PED tolerant.  
 
This MSN range of airplanes must be operated and maintained in accordance with the Airplane Flight Manual, 
document no. 02406 issue 02, revision 00 issue date October 14, 2019 or later revisions. Aircraft with the 
optional Low Propeller Speed in accordance with the AFM Supplement 02439 issue 01, revision 00 issue date 
October 14, 2019 or later revisions. This MSN range of airplanes must use Airplane Maintenance Manual, 
document no. 02436, Airworthiness Limitations 12-C-04-00-00-00A-000A-A, dated August 28, 2019 or later 
EASA and FAA approved revisions. 
 
NOTE 17.               On November 21, 2019, the FAA accepted the complete set of ICAs for MSN 1720, MSN 2001 and subsequent.  
                               The ALS section of the ICA, chapter 4, dated August 28, 2019 was FAA approved on September 04, 2019 which 
was before the FAA approval for these type design changes and allowed per 14 CFR part 21.50(b).   
 
NOTE 18.               Revision 34 of this TCDS was issued to correct a typographical error and correctly identify the PC-12 models in 
the title block of this TCDS and corresponding individual model sections by not including “PILATUS” before 
each model number to correctly match the actual FAA type certificate.   
 
NOTE 19.               Pilatus introduced Halon free fire extinguisher as an alternative on all PC-12 model aircraft per SB 26-005. This 
project introduced §23.851 at amendment 23-45 for all the PC-12 models.  
 
NOTE 20. Applicable for the Garmin GIFD3 digital display of the ASI Flap Marking, Prop RPM and Probes Heating OFF 
and the Li-Ion batteries. 
 
NOTE 21. The PC-12/47G - MSN 3001 and subsequent: These airplanes are fitted with: 
- Garmin GIFD 3 avionic system 
- The DV window has been removed 
- Optional Li-Ion main ship battery  
- 12” Diameter Weather Radar antenna 
- Pratt and Whitney PT6E-67XP engine with Electronic Engine Control (EEC)  
- Hartzell 5-Blade Composite Propeller 
- Revised Fuel System enabling the use of fuel without anti-icing additives with the fuel system basic  
  architecture and means of operation maintained 
- Electromechanical Landing Gear (eLDG) 
- The airplanes are RVSM capable. 
 
This MSN range of airplanes must be operated and maintained in accordance with the Airplane Fight Manual, 
document no. 02523, Issue 003, Rev 00 or later revisions and the Airplane Maintenance Manual, document no. 
02547, Issue 02, Rev 00, or later EASA approved revisions. 
 
NOTE 22.             On July 2, 2025, the complete set of ICAs have been FAA accepted per 21.50(b) for the PC-12/47G model.  
                              The ALS section of AMM document 02547, Issue 02, Rev 00, Chap 4, Airworthiness Limitations 12-D-04-00-
00-00A-000A-A, dated June 27, 2025, is part of the required ICAs for the FAA type certificate.    History - The 
ALS section of the ICAs, chapter 4, dated 12/18/2024, was FAA approved on December 18, 2024, which was 
before the Amended TC was issued, but the rest of the ICAs at that time had not been accepted yet per allowance 
of 21.50(b).  
 
…END…
```

## ADs (88, first 50, in force first)

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- [AD 2013-19-10](https://openairdocs.org/ad/2013-19-10): Navigation · Pilatus PC-12/47E. Effective Oct 30, 2013
- [AD 2008-07-11 R1](https://openairdocs.org/ad/2008-07-11-R1): Flight Controls · Pilatus PC-12, PC-12/45 and PC-12/47. Effective Mar 25, 2013
- [AD 2012-14-15](https://openairdocs.org/ad/2012-14-15): Navigation · Honeywell International PC-12/47E and KGS200 Mercury  wide area augmentation system (WAAS) global navigation satellite sensor units (GNSSU). Effective Jul 19, 2012
- [AD 2010-17-09](https://openairdocs.org/ad/2010-17-09): Engine Controls · Pilatus PC-12/47E. Effective Sep 22, 2010
- [AD 2010-09-04](https://openairdocs.org/ad/2010-09-04): Navigation · Embraer - Empresa Brasileira de Aeronautica ERJ 170-100 LR, ERJ 170-100 SE, ERJ 170-100 STD and 13 more. Effective May 14, 2010
- [AD 2010-05-02](https://openairdocs.org/ad/2010-05-02): Navigation · Pilatus PC-12/47E. Effective Apr 1, 2010
- [AD 2009-08-11](https://openairdocs.org/ad/2009-08-11): Ice and Rain Protection · Pilatus PC-12 and PC-12/45. Effective May 26, 2009
- [AD 2009-05-07](https://openairdocs.org/ad/2009-05-07): Rear stick-pusher cable · Pilatus PC-12, PC-12/45, PC-12/47 and 1 more. Effective Mar 30, 2009
- [AD 2008-07-11](https://openairdocs.org/ad/2008-07-11): Pitch trim actuator · Pilatus PC-12, PC-12/45 and PC-12/47. Effective May 9, 2008
- [AD 2008-02-03](https://openairdocs.org/ad/2008-02-03): MLG special bolts · Pilatus PC-12, PC-12/45 and PC-12/47. Effective Feb 20, 2008
- [AD 2007-21-11](https://openairdocs.org/ad/2007-21-11): Oil pile assemblies · Pilatus PC-12, PC-12/45 and PC-12/47. Effective Nov 5, 2007
- [AD 2007-03-06](https://openairdocs.org/ad/2007-03-06): Executive seats equipped with pedestal legs · Pilatus PC-12 and PC-12/45. Effective Mar 8, 2007
- [AD 2006-16-13](https://openairdocs.org/ad/2006-16-13): Lug fittings. · Pilatus PC-12 and PC-12/45. Effective Sep 18, 2006
- [AD 2006-08-11](https://openairdocs.org/ad/2006-08-11): Crew seat bucket assemblies · Pilatus PC-12 and PC-12/45. Effective Jun 2, 2006
- [AD 2005-22-13](https://openairdocs.org/ad/2005-22-13): Left and right main landing gear (MLG) assemblies · Pilatus PC-12 and PC-12/45. Effective Dec 19, 2005
- [AD 2005-22-04](https://openairdocs.org/ad/2005-22-04): Nose landing gear (NLG), main landing gear (MLG), and MLG shock absorber  
 assemblies · Pilatus PC-12 and PC-12/45. Effective Dec 12, 2005
- [AD 2005-11-06](https://openairdocs.org/ad/2005-11-06): Pitch actuator · Pilatus PC-12 and PC-12/45. Effective Jul 18, 2005
- [AD 2005-04-16](https://openairdocs.org/ad/2005-04-16): Windshield de-ice wiring system · Pilatus PC-12 and PC-12/45. Effective Mar 8, 2005
- [AD 2005-01-19](https://openairdocs.org/ad/2005-01-19): Mode S transponders · GARMIN International GTX 330D, GTX 330, GTX 33D and 830 more. Effective Feb 23, 2005
- [AD 2005-01-11](https://openairdocs.org/ad/2005-01-11): Main Landing Gear (MLG) Actuator · Pilatus PC-12 and PC-12/45. Effective Feb 22, 2005
- [AD 2004-12-11](https://openairdocs.org/ad/2004-12-11): Outboard flap flexshafts · Pilatus PC-12 and PC-12/45. Effective Jul 26, 2004
- [AD 2004-06-05](https://openairdocs.org/ad/2004-06-05): Main landing gear shock absorber · Pilatus PC-12 and PC-12/45. Effective May 6, 2004
- [AD 2004-04-01](https://openairdocs.org/ad/2004-04-01): Engine-driven pump housing · Pilatus PC-12, PC-12/45 and PC-7. Effective Mar 29, 2004
- [AD 2003-20-15](https://openairdocs.org/ad/2003-20-15): Fuel booster pump · Pilatus PC-12 and PC-12/45. Effective Oct 10, 2003
- [AD 2003-11-17](https://openairdocs.org/ad/2003-11-17): Pressure dome · Pilatus PC-12 and PC-12/45. Effective Jul 28, 2003
- [AD 2003-09-11](https://openairdocs.org/ad/2003-09-11): Pedestal Leg Assembly on Aft Facing Passenger Seats · Pilatus PC-12 and PC-12/45. Effective Jun 16, 2003
- [AD 2003-07-10](https://openairdocs.org/ad/2003-07-10): Push switch caps · Pilatus PC-12 and PC-12/45. Effective May 12, 2003
- [AD 2002-14-22](https://openairdocs.org/ad/2002-14-22): Main Landing Gear (MLG) Assembly Bolts · Pilatus PC-12 and PC-12/45. Effective Aug 29, 2002
- [AD 2002-06-10](https://openairdocs.org/ad/2002-06-10): Connector and Oxygen Tubing and Related Components in Rear Seat Bench · Pilatus PC-12 and PC-12/45. Effective May 6, 2002
- [AD 2001-25-10](https://openairdocs.org/ad/2001-25-10): Flap Control System · Pilatus PC-12 and PC-12/45. Effective Jan 25, 2002

All 88: https://openairdocs.org/tcds/A78EU/ads.md

## Registered aircraft by registry model (OpenAirDocs)

- [Pilatus PC-12/47E](https://openairdocs.org/model/pilatus-pc-12-47e): 833 aircraft (registry code 7090553)
- [Pilatus PC-12/45](https://openairdocs.org/model/pilatus-pc-12-45): 378 aircraft (registry codes 7090551, 7090051)
- [Pilatus PC-12/47](https://openairdocs.org/model/pilatus-pc-12-47): 119 aircraft (registry code 7090552)
- [Pilatus PC-12/47G](https://openairdocs.org/model/pilatus-pc-12-47g): 65 aircraft (registry code 7090463)
- [Pilatus PC-12](https://openairdocs.org/model/pilatus-pc-12): 32 aircraft (registry code 7090550)
- [Pilatus Flugzeugwerke PC-12/45](https://openairdocs.org/model/pilatus-flugzeugwerke-pc-12-45): 8 aircraft (registry code 7090503)
- [Pilatus Flugzeugwerke PC-12/47](https://openairdocs.org/model/pilatus-flugzeugwerke-pc-12-47): 6 aircraft (registry code 7090504)
- [Pilatus Flugzeugwerke PC-12](https://openairdocs.org/model/pilatus-flugzeugwerke-pc-12): 2 aircraft (registry code 7090512)
- [Pilatus PC-12/47E NGX](https://openairdocs.org/model/pilatus-pc-12-47e-ngx): 0 aircraft (registry code 7090653)

## STCs approved under this data sheet (193, first 50)

- [STC SA02571SE](https://openairdocs.org/stc/SA02571SE): Installation of Garmin G500/G600 TXi Integrated Avionics System (Primary Flight Display, Multi-Function Display, and Engine Indicating System Display).. Garmin International Inc.
- [STC SA01800SE](https://openairdocs.org/stc/SA01800SE): Fabrication and installation of new or replacement of  existing instrument panel lights dimmer control.. TCW Technologies, LLC
- [STC SA01861SE](https://openairdocs.org/stc/SA01861SE): Fabrication and installation of Landing Light Controller. TCW Technologies, LLC
- [STC SA01844WI](https://openairdocs.org/stc/SA01844WI): Installation of Garmin GFC 600 Automatic Flight Control System. Garmin International Inc.
- [STC SA02279AT](https://openairdocs.org/stc/SA02279AT): Installation of a Boom Beam bulb, starter, and ballast. Whelen Aerospace Technologies
- [STC SA04837NY](https://openairdocs.org/stc/SA04837NY): Installation of AeroLED's Holdings, LLC., position lights, navigation lights, strobe lights and beacon lights. AeroLED's Holdings, LLC
- [STC SA02019SE-D](https://openairdocs.org/stc/SA02019SE-D): Installation of Garmin Model GTN 625/635/650; 725/750 Navigation System. Garmin International Inc.
- [STC SA01123DE](https://openairdocs.org/stc/SA01123DE): Installation of the Emergency Medical Service (EMS) Power. Peregrine
- [STC SA1122DE](https://openairdocs.org/stc/SA1122DE): Installation of the EMS Cabin Audio and FM Radio. Peregrine
- [STC SA02742NY](https://openairdocs.org/stc/SA02742NY): Installation of MT-Propeller Entwicklung GmbH model MTV-27-1-N-C-F-R(P)/CFR260-65. MT- Propeller Entwicklung GmbH
- [STC SA04763NY](https://openairdocs.org/stc/SA04763NY): Installation of of Gogo Galileo HDX. Pro Star Aviation LLC.
- [STC SA03275CH](https://openairdocs.org/stc/SA03275CH): Installation of an antiskid brake system. Lee Air Inc.
- [STC SA11158SC](https://openairdocs.org/stc/SA11158SC): Demonstration of aircraft tolerance to potential electromagnetic interference from certain Transmitting Potable Electronic Devices (T-PEDS). Liberty Partners Inc.
- [STC SA04841NY](https://openairdocs.org/stc/SA04841NY): Installation of replacement LED recognition lights, LED wingtip lights, LED beacon lights, LED taxi lights, and LED landing lights. Whelen Aerospace Technologies
- [STC SA04278NY](https://openairdocs.org/stc/SA04278NY): Installation of the GPS/Iridium Antenna Provisions. SKYTRAC Systems Ltd.
- [STC SA02738CH](https://openairdocs.org/stc/SA02738CH): Installation of L-3 Communications Avionics Systems. Acron Aviation Inc.
- [STC SA04046CH PAGE 2](https://openairdocs.org/stc/SA04046CH%20PAGE%202): Installation of L-3 GENESIS  (TM) Electronic Standby Instrument System (ESI-500/MAG-500). Acron Aviation Inc.
- [STC SA09887AC](https://openairdocs.org/stc/SA09887AC): Installation of an Avionica MK-III mini Quick Access Recorder (QAR) and optional 4G or LTE Avionica
Cellular Module (avCM. Aircraft Systems and Manufacturing Inc.
- [STC SA01527CH](https://openairdocs.org/stc/SA01527CH): Installation of a Honeywell KMH 880 Multi-Hazard Awareness System or a Honeywell KTA 870 Traffic Advisory System. Amphenol Cable and Interconnect Technologies Inc.
- [STC SA04220NY](https://openairdocs.org/stc/SA04220NY): Installation of Retractable Camera Mount System. Trine Aerospace & Defense
- [STC SA02558SE](https://openairdocs.org/stc/SA02558SE): Installation of a Light Emitting Diode (LED) Landing and Taxi Light. AeroLED's Holdings LLC
- [STC SA04051CH](https://openairdocs.org/stc/SA04051CH): Certification of Automatic Dependent Surveillance - Broadcast (ADS-B) Out System with Rockwell Collins TDR-94/-94D Transponders. CMD Flight Solutions LLC
- [STC SA00028MC](https://openairdocs.org/stc/SA00028MC): Installation of non-essential antenna and radome. Sierra Nevada Company LLC
- [STC SA01946WI](https://openairdocs.org/stc/SA01946WI): Installation of multi-mission equipment, antennas, and interior configurations. Pilatus Business Aircraft, LTD
- [STC SA03316CH](https://openairdocs.org/stc/SA03316CH): Activation of an 802.11 a/b/g/n WiFi System. Elliott Aviation Technical Products Development Inc.
- [STC SA00229MC](https://openairdocs.org/stc/SA00229MC): Installation of Dual Mode Recognition Lights.. Sierra Nevada Company LLC
- [STC SA02658SE](https://openairdocs.org/stc/SA02658SE): Installation of Garmin GI 275 Multi-Function Display System. Garmin International Inc.
- [STC SA01104DE](https://openairdocs.org/stc/SA01104DE): Installation of a Send Solutions in Flight Entertainment System. Pilatus Business Aircraft, LTD
- [STC SA02266LA](https://openairdocs.org/stc/SA02266LA): Installation of a Pratt and Whitney PT6A-67P. Finnoff Aviation Products LLC
- [STC SA02010WI](https://openairdocs.org/stc/SA02010WI): Installation of the Mid-Continent Instruments & Avionics MD23 FLEX Custom Function Display (CFD). Mid-Continent Instruments and Avionics
- [STC SA00076IB](https://openairdocs.org/stc/SA00076IB): Installation of Photo luminescent Safety Systems. STG AEROSPACE GERMANY GmbH
- [STC SA00102MC](https://openairdocs.org/stc/SA00102MC): Installation of multiple mission configuration options, including an equipment rack, non-required communications equipment, mission power distribution system, antennas, optional sensor, optional operator console, optional casualty evacuation configuration, replacement of cockpit mounted audio control panels, and addition of audio control panels in the cabin. Sierra Nevada Corporation
- [STC SA03097AT](https://openairdocs.org/stc/SA03097AT): Installation of Cabin Interior Light Emitting Diode (LED) Reading and Wash Lights and Air Gaspers.. Woven Electronics, LLC
- [STC SA01044DE](https://openairdocs.org/stc/SA01044DE): This STC approves the Finnoff Aviation Products installation of the TB44 advanced lithium-ion battery manufactured by True Blue Power in the make and model listed above (Single Battery Configuration). Finnoff Aviation Products
- [STC SA01376CH](https://openairdocs.org/stc/SA01376CH): Installation of Parker Hannifin Wheel/Brake Assembly P/N 40-424/30-244 (conversion kit no. 199-241).. KAMAN Corporation Aircraft Wheel and Brake LLC
- [STC SA02203AK](https://openairdocs.org/stc/SA02203AK): Installation of FlightLogic Synthetic Vision Electronic Flight Information System (EFIS-SV).. Genesys Aerosystems Inc.
- [STC ST03660AT](https://openairdocs.org/stc/ST03660AT): Installation of a Flight Components/EMTEQ LED Position (Navigation) Lights. Woven Electronics LLC
- [STC SA02254AK](https://openairdocs.org/stc/SA02254AK): Installation of "Single Screen", "2 or 3 Screen", "Dual Screen", or "4 or 6 screen". Genesys Aerosystems Inc.
- [STC SA02444AK](https://openairdocs.org/stc/SA02444AK): Approval of the L-3 Communications NGT 9000/9000R ADS-B system installed. ADS-B Technologies LLC
- [STC SA01036DE](https://openairdocs.org/stc/SA01036DE): Avance L3 system installation. Pilatus Business Aircraft Ltd
- [STC SA02801NY](https://openairdocs.org/stc/SA02801NY): Relocation of Main Battery No 2. B/E Aerospace Limitedd
- [STC SA09856AC](https://openairdocs.org/stc/SA09856AC): Installation of BendixKing Aerowave 100 In-flight Data Link System for non-essential, non-required aircraft Cabin Systems & Equipments. Honeywell International Inc (Bendix King)
- [STC SA11174SC PAGE 1](https://openairdocs.org/stc/SA11174SC%20PAGE%201): Installation of BendixKing by Honeywell KSN 770 and KSN 765 WAAS LPV approach capable nav/comm systems. Honeywell International Inc (Bendix King)
- [STC SA02265SE](https://openairdocs.org/stc/SA02265SE): Installation of a camera housing. Airborne Sensor LLC
- [STC SA02075SE](https://openairdocs.org/stc/SA02075SE): Installation of a Mid-Continent MD835( ) Lithium Ion Battery. Mid-Continent Instrument Co. Inc.
- [STC SA04556NY](https://openairdocs.org/stc/SA04556NY): Installation of so-called Seat Slides JG into the cabin. J.G.A.
- [STC SA00272LA](https://openairdocs.org/stc/SA00272LA): Installation of a Patient Loading Utility System (PLUS). LifePort LLC
- [STC SA10236SC](https://openairdocs.org/stc/SA10236SC): Installation of a GDC 31 Roll Steering Converter. DAC International Inc
- [STC SA04514NY](https://openairdocs.org/stc/SA04514NY): Single/Dual Transponder System ADS-B Upgrade. Scandinavian Avionics Design ApS
- [STC SA02427AK](https://openairdocs.org/stc/SA02427AK): Installation of the Max-Viz® Enhanced Vision System (EVS) Model-1500 on Pilatus PC-12 aircraft equipped with a fixed-mounted or panel-mounted Multi-Function Display (MFD) with the ability to display video imagery. PECO Inc

All 193: https://openairdocs.org/tcds/A78EU/stcs.md

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OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.