STC SA03303AT

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate The STC’s supporting documentation (drawings, instructions, specifications, flight manual supplements, etc.) is the property of the ST C holder.

FAA Form 8110-2 (5/14) Page 1 of 6

IMPORT Number: SA03303AT

Part 3 of the Civil Air Regulations.

Original Product – Type Certificate Number: Make: Piper Aircraft, Inc.

2A13 Model: PA-28-140, PA-28-150, PA-28-151, PA-28-160, PA-28-161, PA-28-180, and PA-28-181 (Archer III)

Option 1: TAE 125-01 Engine Installation on PA-28-161 model:

1. Installation of Technify Motors GmbH aircraft diesel engine model TAE 125 -01 and MT-Propeller model MTV -6-A/187-129 propeller, with FADEC backup battery installation and other minor modifications per Thielert Aircraft Engines “Design Change 40-0078,” dated July 16, 2010 (including the replacement of the alternator circuit breaker by a guarded switch) in accordance with “Installation Manual, Installation of a TAE 125 -01 Engine in a Piper PA28-161,” IM -40-01 161, Issue 2, Revision 0, Technify Motors Document No. 40-0312-45332, dated January 20, 2015, or later EASA approved revisions, and Thielert...

(See Description of Type Design Change continued on Page 3 of 6)

1. Power/Rotational Speed:

a. For TAE 125-01 and 125-02-99 installations:

(1) Take-Off Power: 135 HP at 2300 RPM propeller speed.

(2) Max. Continuous Power: 135 HP at 2300 RPM propeller speed.

(See Limitations and Conditions continued on Page 5 of 6)

Date of Application: February 11, 2002 Date Reissued: April 2, 2015, April 7, 2015 Date of Issuance: July 24, 2006 Date Amended: April 16, 2015 By Direction of the Administrator

Signature

Title Gaetano Sciortino Manager New York Aircraft Certification Office Technify Motors GmbH Platanenstrasse 14 09356 St. Egidien, Germany

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate Possession of this Su pplemental Type Certificate (STC) document by persons other than the STC holder does not constitute rights to the design data nor to alter an aircraft, aircraft engine, or propeller.

FAA Form 8110-2 (5/14) Page 2 of 6

Transfer the ownership of Supplemental Type Certificate Number: SA03303AT

To (Name and address of transferee)

From (Name and address of grantor)

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: SA03303AT

Possession of this Su pplemental Type Certificate (STC) document by persons other than the STC holder does not constitute rights to the design data nor to alter an aircraft, aircraft engine, or propeller.

FAA Form 8110-2 (5/14) Page 3 of 6

Date Amended: April 16, 2015

Description of Type Design Change (continued):

Option 1: TAE 125-01 Engine Installation on PA-28-161 Model (continued)

1. ...Aircraft Engines “Type Design Definition TAE 125 / PA 28,” Doc. No. TDD -40-01, Issue 3, Revision 0, dated August 26, 2004.

2. “Supplement Airplane Maintenance Manual Piper PA28, TAE 125-01,” AMM -40-01 (US -Version), Issue 2, Revision 0, Technify Motors Document No. 40-0311-40342, dated January 20, 2015, or later EASA accepted revisions are required with this installation.

3. “Supplemental Airplane Flight Manual or Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual Supplement (as applicable) for Piper, Piper PA -28-140 – Cherokee Cruiser, Piper PA -28-150/160/180 – Cherokee, Piper PA -28-151 – Cherokee Warrior, Piper PA -28-161 – Cadet, Warrior II & III, Eq uipped with TAE 125-01/TAE 125 -02-99 Installation, “ Issue 5, Revision 0, Technify Motors Document No. 40-0310 -40045, dated December 15, 2014, or later EASA approved revisions is required with this installation.

Option 2 : TAE 125-02-99 Engine Installatio n on PA -28-140, PA-28-150, PA -28-151, PA-28-160, PA-28-161, and PA -28-180 Models

1. Installation of Technify Motors GmbH aircraft diesel engine model TAE 125-02- 99 and MT -Propeller model MTV -6-A/187- 129 propeller, with FADEC backup battery installation an d other minor modifications per Thielert Aircraft Engines “Design Change 40-0078,” dated July 16, 2010 (including the installation of an undamped exhaust pipe and the replacement of the alternator circuit breaker by a guarded switch) in accordance with:

a. “Installation Manual, Installation of a TAE 125 -02-99 Engine in a Piper PA28- 140/-150/-160/-180, 14V onboard electrical system,” IM -40-02 140/150/160/180, Issue 2, Revision 2, Technify Motors Document No. 40-0312 -41032, dated December 2, 2014 or later EASA approved revisions.

b. “Installation Manual, Installation of a TAE 125 -02-99 Engine in a Piper PA28-151, 14V onboard electrical system,” IM - 40-02 151, Issue 2, Revision 2, Technify Motors Document No. 40-0312 -42032, dated December 2, 2014 or later EASA approved revisions.

c. “Installation Manual, Installation of a TAE 125 -02-99 Engine in a Piper PA28-161, 14V and 28V onboard electrical system,” IM-40-02 161, Issue 2, Revision 2, Technify Motors Document No. 40- 0312-43032, dated December 2, 2014 or later EASA approved revisions.

and Thielert Aircraft Engines “Type Design Definition PA 28 / TAE 125-02- 99,” Doc. No. TDD-40-02, Issue 1, dated February 21, 2007.

2. “Supplement Airplane Maintenance Manual Piper PA28, TAE 125 -02-99, TAE-02-114” AMM-40-02 (US-Version), Issue 2, Revision 0, Technify Motors Document No. 40-0311 -40242, dated December 2, 2014, or later EASA accepted revisions is required with this installation.

(See Description of Type Design Change continued on Page 4 of 6)

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: SA03303AT

Possession of this Su pplemental Type Certificate (STC) document by persons other than the STC holder does not constitute rights to the design data nor to alter an aircraft, aircraft engine, or propeller.

FAA Form 8110-2 (5/14) Page 4 of 6

Date Amended: April 16, 2015

Description of Type Design Change (continued):

Option 2: TAE 125 -02-99 Engine Installation on PA -28-140, PA-28-150, PA-28-151, PA-28-160, PA-28-161, and PA -28-180 Models (continued)

3. “Supplemental Airplane Flight Manual or Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual Supplement (as applicable) for Piper, Piper PA -28-140 – Cherokee Cruiser, Piper PA-28-150/160/180 – Cherokee, Piper PA- 28-151 – Cherokee Warrior, Piper PA -28-161 – Cadet, Warrior II & III, Equipped with TAE 125 -01/TAE 125-02- 99 Installation, “ Issue 5, Revision 0, Technify Motors Document No. 40- 0310-40045, dated December 15, 2014, or later EASA approved revisions is required with this installation.

Option 3: TAE 125-02-114 Engine Installation on PA-28-151, PA-28-161, and PA-28-181 (Archer III) Models

1. Installation of Technify Motors aircraft diesel engine model TAE 125 -02-114 and MT -Propeller model MTV -6-A/187-129 propeller installed on PA-28-151 and PA-28-161 models, or MT -Propeller model MTV -6-A/190-69 propeller installed on the PA-28-181 (Archer III) model, and backup battery installation and other minor modifications per Thielert Aircraft Engines “Design Change dated July 16, 2010 (including the repla cement of the alternator circuit breaker by a guarded switch) in accordance with:

a. “Installation Manual, Installation of a TAE 125 -02-114 Engine in a Piper PA28-151 Cherokee Warrior, PA28-161 Cadet, PA-161 Warrior II, 14V onboard electrical system,” IM -40-02S 151/161, Issue 2, Revision 2, Technify Motors Document No. 40-0312-42132, dated December 2, 2014 or later EASA accepted revisions

b. “Installation Manual, Installation of a TAE 125 -02-114 Engine in a Piper PA28-161 Warrior III, 28V onboard electri cal system,” IM-40-02S 161, Issue 2, Revision 2, Technify Motors Document No. 40- 0312-43132, dated December 2, 2014 or later EASA accepted revisions

c. “Installation Manual, Installation of a TAE 125-02- 114 Engine in a Piper PA28- 181 Archer III, 28V onboa rd electrical system,” IM-40-02S 181, Issue 1, Revision 5, Technify Motors Document No. 40- 0312-4413 1, dated December 2, 2014 or later EASA accepted revisions

and Thielert Aircraft Engines “Type Design Definition PA 28 / TAE 125- 02-99,” Doc. No. TDD-40-02, Issue 1, dated February 21, 2007.

2. “Supplement Airplane Maintenance Manual Piper PA28, TAE 125 -02-99, TAE-02-114” AMM-40-02 (US-Version), Issue 2, Revision 0, Technify Motors Document No. 40-0311 -40242, dated December 2, 2014, or later EASA accepted revisions is required with this installation.

3. “Supplemental Airplane Flight Manual or Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual Supplement (as applicable) for Piper, Piper PA -28-151 – Cherokee Warrior, Piper PA-28-161 – Cadet, Warrior II & III, Piper PA-28-181 – Archer III, Equipped with TAE 125-02 -114 Installation, “ Issue 1, Revision 0, Technify Motors Document No.

40-0310-40141, dated December 15, 2014, or later EASA approved revisions is required with this installation.

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: SA03303AT

Possession of this Su pplemental Type Certificate (STC) document by persons other than the STC holder does not constitute rights to the design data nor to alter an aircraft, aircraft engine, or propeller.

FAA Form 8110-2 (5/14) Page 5 of 6

Date Amended: April 16, 2015

1. Power/Rotational Speed (continued):

b. For TAE 125-02-114 installations:

(1) Take-Off Power: 155 HP at 2300 RPM propeller speed.

(2) Max. Continuous Power: 155 HP at 2300 RPM propeller speed.

2. Fuel:

Service Bulletin TM TAE 651-0005

3. Maximum Take-Off Weight (MTOW):

a. For TAE 125-01 and 125-02-99 installations:

(1) PA-28-160 (Normal Category, reduced weight): Maximum Take-Off Weight 976 kg (2152 lb).

(2) PA-28-161 (Normal Category, reduced weight): Maximum Take-Off Weight 1055 kg (2326 lb).

(3) PA-28-180 (Normal Category, reduced weight): Maximum Take-Off Weight 976 kg (2152 lb).

b. For TAE 125-02-114 installations, the Maximum Take-Off Weight is the same as the original limitations.

4. Mandatory replacement time and/or inspection intervals are defined in the FAA Approved “Airworthiness Limitation” section of the applicable Supplemental Airplane Maintenance Manual:

a. “Supplement Airplane Maintenance Manual Piper PA28, TAE 125-01,” AMM-40-01 (US-Version), Issue 2, Revision 0, Technify Motors Document No. 40-0311-40342, dated January 20, 2015, or later EASA accepted revisions.

b. “Supplement Airplane Maintenance Manual Piper PA28, TAE 125-02-99, TAE-02-114” AMM-40-02 (US-Version), Issue 2, Revision 0, Technify Motors Document No. 40-0311-40242, dated December 2, 2014, or later EASA accepted revisions.

5. The installer must determine whether this design change is compatible with previously approved modifications.

6. If the holder agrees to permit another person to use the cert ificate to alter the product, the holder must give the other person written evidence of that permission.

Certification Basis:

Based on 14 CFR §§ 21.115 and 21.101, and FAA Order 8110.48, the certification basis for the Piper Aircraft Inc. models PA -28- 140, PA -28-150, PA -28-151, PA -28-160, PA -28-161, PA -28-180, and PA -28-181 Archer III modified with the installation of Technify Motors GmbH diesel engines is as follows:

a. The type certification basis for Piper PA -28 series airplanes is shown on TCDS No. 2A13 for parts not changed or not affected by the change.

b. The type certification basis for parts changed or affected by the change Piper since the reference date of the application, February 11, 2002, is based upon 14 CFR §§ Part 23 as amended by Amendment 23-51. Based on 14 CFR §§ 21.115 and

21.101, and FAA Order 8110.48, the certification basis for this modification is determined to be:

Regulations at the latest amendment 23-0 through 23-51:

14 CFR Part 23, §§ 23.1, 23.3, 23.21, 23.23, 23.25, 23.29, 23.33, 23.45, 23.49, 23.51, 23.53, 23.63, 23.65, 23.69, 23.71,

23.73, 23.77, 23.141, 23.143, 23.145, 23.151, 23.153, 23.155, 23.171, 23.173, 23.175, 23.177, 23.201, 23.221, 23.231, …

(See Certification Basis continued on Page 6 of 6)

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: SA03303AT

Possession of this Su pplemental Type Certificate (STC) document by persons other than the STC holder does not constitute rights to the design data nor to alter an aircraft, aircraft engine, or propeller.

FAA Form 8110-2 (5/14) Page 6 of 6

Date Amended: April 16, 2015

Certification Basis (continued):

Regulations at the latest amendment 23-0 through 23-51 (continued):

23.251, 23.301, 23.303, 23.305, 23.307, 23.321, 23.335, 23.337, 23.341, 23.343, 23.361, 23.363, 23.371, 23.572, 23.573,

23.574, 23.601, 23.603, 23.605, 23.607, 23.609, 23.611, 23.613, 23.619, 23.621, 23.623, 23.625, 23.627, 23.773, 23.777,

23.779, 23.781, 23.831, 23.863, 23.865, 23.867, 23.901, 23.903, 23.905, 23.907, 23.909, 23.925, 23.929, 23.939, 23.943,

23.951, 23.954, 23.955, 23. 959, 23.961, 23.963, 23.965, 23.967, 23.969, 23.971, 23.973, 23.975, 23.977, 23.991, 23.993,

23.994, 23.995, 23.997, 23.999, 23.1011, 23.1013, 23.1015, 23.1017, 23.1019, 23.1021, 23.1023, 23.1041, 23.1043,

23.1047, 23.1061, 23.1063, 23.1091, 23.1093, 23.11 03, 23.1107, 23.1121, 23.1123, 23.1141, 23.1143, 23.1145, 23.1163,

23.1165, 23.1181, 23.1182, 23.1183, 23.1191, 23.1193, 23.1301, 23.1305, 23.1309, 23.1311, 23.1321, 23.1322, 23.1327,

23.1331, 23.1337, 23.1351, 23.1353, 23.1357, 23.1359, 23.1361, 23.1365, 23.1367, 23.1381, 23.1431, 23.1461, 23.1501,

23.1519, 23.1521, 23.1527, 23.1529, 23.1541, 23.1543, 23.1549, 23.1551, 23.1555, 23.1557, 23.1567, 23.1581, 23.1583,

23.1585, 23.1587, 23.1589.

Regulations at the amendment level in TCDS 2A13:

CAR 3.159.

14 CFR §§ Part 36 - Noise Standards:

Amendment 36-28.

Equivalent Level of Safety (ELOS) Finding:

23.777(d) Cockpit Controls (documented in ELOS memorandum ACE-05-27)

23.779(b) Motion and effect of cockpit controls (documented in ELOS memorandum ACE-05-27)

23.1061 Liquid Cooling - Installation (documented in ELOS memorandum ACE-05-22)

23.1145 Ignition switches (documented in ELOS memorandum ACE-05-21)

Special Conditions:

1. FAA Special Condition No. 23-187-SC, “Thielert Aircraft Engines, Piper PA 28-161 Cadet, Warrior II and Warrior III Series Airplanes, Installation of Thielert TAE-125-01 Aircraft Diesel Engine for Full Authority Digital Engine Control (FADEC) System and the Protection of the System From the Effects of High Intensity Radiated Fields (HIRF)”, issued June 7, 2006

2. FAA Special Condition No. 23-188-SC, “Thielert Aircraft Engines (TAE) GmbH, Piper PA 28-161 Cadet, Warrior II and Warrior III Series Airplanes, Diesel Cycle Engine Using Turbine (Jet) Fuel”, issued July 29, 2006.

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