STC SA2445WE

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

Reissued on July 31, 2017 to supersede the original STC, which has been lost or misplaced.

Number: SA2445WE

Part 3 of the Civil Air Regulations, dated 11-1-49, including Amendments 3-1 to 3-9 and 3.242(a) of Amendment 3-14 dated 3-13-56.

Original Product – Type Certificate Number: 1A10 Make: Piper Model: PA 23-235, PA 23-250 and PA E23-250 PA 23-250 (Serial No. 27-7654001 & up)

Installation of recontoured inboard wing leading edge, stall fences, drooped ailerons in flaps down mode, rudder anti - servo tab system and optional installation of raked wing tips. All in accordance with the drawings listed on FAA Sealed Robertson Aircraft Drawing List No. 20.

Date of Application: September 29, 1971 Date Reissued: 11/8/84; 10/10/86; 9/8/05; 7/31/17 Date of Issuance: November 16, 1971 Date Amended: December 15, 1975

Signature

Title Jim Grigg Manager, Fort Worth A CO Branch, Compliance & Airworthiness Division Sierra Industries, Ltd.

122 Howard Langford Drive Uvalde, TX 78801

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

Transfer the ownership of Supplemental Type Certificate Number: SA2445WE

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: SA2445WE

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

Date of Issuance: November 16, 1971 Amended Date: December 15, 1975 Date of Reissuance: July 31, 2017

Supplemental Type Certificate Addendum No. SA2455WE is a part of this certificate. A copy of this certificate shall be maintained as part of the permanent records for each aircraft so modified. The approval of this change in type design applies basically to the above model aircraft only. This approval should not be extended to other aircraft of th ese models 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 these aircraft.

The conditions and limitations of Aircraft Specification No. 1A10 apply except as follows:

This Addendum which is part of Supplemental Type Certificate No. SA2445WE prescribes conditions and limitations under which the product for which the STC was issued meets the airworthiness requirements of the Civil Air Regulations. A copy of this Addendum shall be maintained as part of the modified aircraft permanent records.

Supplemental Type Certificate Holder: R/STOL SYSTEMS, INC.

III. Model PA 23-250 (Serial No. 27-1 through 27-7554168) (Navy UO-1) (Normal Category) as modified by STC SA244WE.

Control Surface Main Aileron UP ± 2° DN ± 2° Droop from Movements Surfaces Neutral @ Flaps up (0°) 30° 15° 0° ±2° @ Flaps ¼ (12.5°) --- --- 8° ±2° @ Flaps ½ (25°) --- --- 13° ±2° *This is not a flap *@ Flaps 32° 13.5° 33° 15° ±2° setting for flight, @ Flaps Full 15° 33° 14° +1 -2° it is for aileron (46°-48°) rigging only.

TABS

Rudder Main Surface Trim Position Tab Position 0° 0° 0° 35° 0° 15.5° R 30° 0° 13.0° L 0° Full Right 25° L 0° Full Left 19° R

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: SA2445WE

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

Date of Issuance: November 16, 1971 Amended Date: December 15, 1975 Date of Reissuance: July 31, 2017

REQUIRED EQUIPMENT In addition to the equipment applicable and required by Aircraft Specification 1A10, the following item of equipment must be installed:

For the PA 23-250 at maximum gross weight of 4800 lbs.,

“Robertson Aircraft FAA Approved Airplane Flight Manual Supplement 20-1.”

For the PA 23-250 at maximum gross weight of 5200 lbs.,

“Robertson Aircraft FAA Approved Airplane Flight Manual Supplement 20-2.”

IV. Model PA23-235 (Normal Category) as modified by STC SA2445WE

Control Surface Main Surfaces Ailerons Movements Identical to Section III of this STC Addendum.

TABS

Identical to Section III of this STC Addendum.

REQUIRED EQUIPMENT In addition to the equipment applicable and required by Aircraft Specification 1A10, the following item of equipment must be installed:

“Robertson Aircraft FAA Approved Airplane Flight Manual Supplement 20-1.”

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: SA2445WE

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

Date of Issuance: November 16, 1971 Amended Date: December 15, 1975 Date of Reissuance: July 31, 2017

V. Model PA E23-250 (Normal Category) as modified by STC SA2445WE

Control Surface Main Surfaces Ailerons Movements Identical to Section III of this STC Addendum.

TABS

Identical to Section III of this STC Addendum.

REQUIRED EQUIPMENT In addition to the equipment applicable and required by Aircraft Specification 1A10, the following item of equipment must be installed:

“Robertson Aircraft FAA Approved Airplane Flight Manual Supplement AFMS 20-3.”

VI. Model PA23-250 (Serial No. 27-7654001 & up) (Normal Category) as modified by STC SA2445WE

Control Surface Main Surfaces Ailerons Movements Identical to Section III of this STC Addendum.

Horizontal 9° ± 1° Leading Edge Up and Down

TABS

Identical to Section III of this STC Addendum.

REQUIRED EQUIPMENT In addition to the equipment applicable and required by Type Certificate 1A10, the following items of equipment must be installed:

“Robertson Aircraft FAA Approved Airplane Flight Manual Supplement AFMS 20-4.”

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: SA2445WE

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

Date of Issuance: November 16, 1971 Amended Date: December 15, 1975 Date of Reissuance: July 31, 2017

NOTE 2. In addition to the placards required by Aircraft Specification 1A10, the following placard must be displayed in lieu of the existing similar one:

On the engine instrument panel

For PA 23-235 and PA 23-250 at 4800 lbs. maximum gross weight

“Minimum Single Engine Control Speed 72 MPH”

For PA 23-250 at 5200 lbs. maximum gross weight

“Minimum Single Engine Control Speed 75 MPH”

For PA E23-250 at 4995 lbs. maximum gross weight

“Minimum Single Engine Control Speed 73 MPH”

For PA 23-250 (Serial No. 27-7654001 and up) At 5200 lbs. maximum gross weight

“Minimum Single Engine Control Speed 60 KIAS”

-END-

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: SA2445WE

FAA Form 8110-2 (5/14) Page 7 of 6