STC SA00863SE

Part 3 of the Civil Air Regulations.

Description of Type Design Change: Installation of two Pratt and Whitney PT6A-135 or -135A engines and two Hartzell HC-B3TN-3B/T10178B-8R propellers, or as an option, two Hartzell HC-E4N-3N/D8990SB propellers in accordance with Master Drawing List MDL-87120 Rev. A, dated February 19, 2009, or later FAA approved revision.

Installation on the model PA-31T2 of two Hartzell HC-E4N-3N/D8990SB propellers in accordance with Master Drawing List MDL-87120 Rev. A, dated February 19, 2009, or later FAA approved revision.

Limitations and Conditions: Approval of this change in type design to the above model aircraft only. This approval should not be extended other aircraft of these models on which other previously approved modifications are incorporated unless it is determined that the relationship between this change and any of those other previously approved modifications, including changes in type design, will introduce no adverse effect upon the airworthiness of that aircraft. A copy of this Certificate, and (See continuation sheet 3 of 4)

Blackhawk Modifications, Inc.

7601 Karl May Drive Waco, TX 76708-5570 A8EA Make: Piper Aircraft, Inc.

Model: PA-31T; PA-31T1; PA-31T2 Date of application : January 27, 1999

Date of issuance : December 21, 2000

Date reissued : June 07, 2007

Date amended : March 16, 2009; January 28, 2002;

November 15, 2001; March 09, 2001

( Signature) S. Frances Cox Manager, Special Certification Office Southwest Region

( Title)

FAA Form 8110-2-1(10-69) Page 2 of 4

FAA Form 8110-2-1(10-69) Page 3 of 4

Number SA00863SE Date of Issuance: December 21, 2000 Date Amended: March 16, 2009

Limitations and Conditions (Continued): Airplane Flight Manual Supplement AFMS-150T-135, Revision IR, AFMS-150T-135A, Revision IR, AFMS-151T-135, Revision IR, AFMS-151T-135A, Revision IR, or AFMS-152T, Revision 2, as appropriate, all dated February 25, 2009, or later FAA approved revision to any of these documents, must be maintained as part of the permanent records for the modified aircraft. Instructions for Continued Airworthiness are contained in Document No. ICA-150-5b, Revision A, dated June 05, 2008, or later FAA accepted revision is required. The installer must determine whether this design change is compatible with previously approved modifications. If the holder agrees to permit another person to use this certificate to alter the product, the holder shall give the other person written evidence of that permission.

ADDITIONAL LIMITATIONS:

ENGINES:

(a) Number of engines 2

(b) Engine Manufacturer Pratt and Whitney (UACL)

(c) Engine Model Number PT6A-135 or PT6A-135A

(d) Engine Operating Limits

(PA-31T and PA31T2 Only) Condition Shaft Horsepower Torque Ft-lb Prop Shaft Speed Maximum Permissible Turbine Interstate Temp (deg C) Takeoff 620 1714 1900 805 Maximum Continuous

1714

1900

(PA31T-1 Only) Condition Shaft Horsepower Torque Ft-lb Prop Shaft Speed Maximum Permissible Turbine Interstate Temp (deg C) Takeoff 500 1382 1900 805 Maximum Continuous

1382

1900

PROPELLERS: (PA-31T and PA-31T1).

(a) Number of propellers 2

(b) Propeller Manufacturer Hartzell

(c) Blade Model T10178B-8R

(d) Number of Blades 3

(e) Hub Model HC-B3TN-3B

(f) Propeller Diameter (inches) 93 inches

(g) Propeller Type Hydraulically Operated, Constant S p e e d , F u l l F e a t h e r i n g , R e v e r s i b l e

FAA Form 8110-2-1(10-69) Page 4 of 4

Number SA00863SE Date of Issuance: December 21, 2000 Date Amended: March 16, 2009

PROPELLERS (PA-31T2) OR OPTIONAL PROPELLERS (PA-31T AND PA-31T1)

(h) Number of propellers 2

(i) Propeller Manufacturer Hartzell

(j) Blade Model D8990SB

(k) Number of Blades 4

(l) Hub Model HC-E4N-3N

(m) Propeller Diameter (inches) 90 inches

(n) Propeller Type Hydraulically Operated, Constant S p e e d , F u l l F e a t h e r i n g , R e v e r s i b l e

If the holder agrees to permit another person to use this certificate to alter the product, the holder shall give the other person written evidence of that permission.

The certification basis for this STC is the same as for the original certification basis for these model airplanes as defined in TCDS A8EA except for

14 CFR 23 Paragraphs 23.1, 23.21, 23.51, 23.53, 23.143, 23.149, 23.711, 23.905, 23.925, 23.929, 23.933, 23.939,

23.1027, 23.1041, 23.1045, 23.1141, 23.1163, 23.1183, 23.1301, 23.1513, 23.1521, 23.1541, 23.1543, 23.1545,

23.1549 which are amended by Amendment 23-57.