STC SA1593GL

This certificate issued to: McCauley Propeller Systems 7751 East Pawnee Wichita, KS 67207

Part 3 of the Civil Air Regulations.

Original Product - Type Certificate Number : A8EA

Make : Piper

Model : PA-31T, PA-31T1

Installation of McCauley Propeller Model 4HFR34C766/94LNA-2 in accordance with McCauley Technical Report No. 758, Revision B, dated March 26, 1991, and McCauley Drawing No. D-60071-X, Letter A, Engineering Change Number 8113, dated March 26, 1991, or later FAA approved revisions.

1. This approval should not be extended to other aircraft of this model on which other previously approved modifications are incorporated, unless it is determined by the installer that the interrelationship between this change and any of those other previously approved modifications will introduce no adverse effect upon the airworthiness of that aircraft.

2. FAA Approved Airplane Flight Manual Supplements, Technical Report Numbers 757 or 764, both dated May 1, 1991, or later FAA approved revisions are required.

Date reissued: September 21, 2005; October 30, 2009

Date amended: May 7, 1991; March 27, 1996

Original signed by Steven Litke

( Signature) Steven Litke Program Manager Wichita Aircraft Certification Office (Title) Date of application: March 13, 1991

Date of issuance: May 3, 1991

FAA FORM 8110-2-1(10-69) PAGE 3 of 3 PAGES

Number SA1593GL

Date of Issuance: May 3, 1991 Date Amended: March 27, 1996 Date Reissued: October 30, 2009

Limitations and Conditions: (cont’d)

3. Aircraft specifications are the same as listed on Ty pe Certificate Data Sheet No. A8EA, except as follows:

Aircraft Model Serial Number Applicability Engine Model All Operation RPM (HP) PA-31T ALL P&W PT6A-28 2200 (620 SHP) PA-31T1 31T-7804001 to 31T-8104101 P&W PT6A-11 2000 (455 SHP) inclusive, limited to aircraft with tip tank option only

Propeller and Propeller Limits 2 McCauley 4HFR34C766 hubs with 94LNA-2 blades and E-6747 spinners

Diameter: 92 to 91 inches

Propeller blade angle at 30 inches:

Feathered: +84.5 ° ± 0.2° Low Pitch: +19.1 ° ± 0.2° Full Reverse: -10.0 ° ± 0.2°

Minimum propeller ground idle RPM for continuous operation shell not be less than 1100 RPM.

WARNING

STABILIZED GROUND OPERATION WITHIN TH E PROPELLER RESTRICTED RPM RANGE CAN

GENERATE HIGH PROPELLER STRESSES AND RESULT IN FATIGUE DAMAGE TO THE PROPELLER. THIS DAMAGE CAN LEAD TO A REDUCED PROPELLER FATIGUE LIFE, PROPELLER FAILURE, AND LOSS OF CONTROL OF THE AIRCRAFT. THE PROPELLER RESTRICTED RPM RANGE IS DEFINED IN TH E AIRPLANE FLIGHT MANUAL. CONTACT THE

AIRCRAFT OR PROPELLER MANUFACTURER FO R CORRECTIVE ACTIONS IF A PROPELLER RESTRICTION OR LIMITATION IS VIOLATED.

4. The Limitations and Conditions are as defined on this certificate.

5. Later FAA approved revisions to the above data may be incorporated without further revision to this certificate.

6. Compatibility of this design change with previously approved modifications must be determined by the installer.

7. If the STC 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.

8. Approval of this change in type design applies to the above model airplanes only.

9. A copy of the approved data shall be maintained in the airplane permanent records.

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