STC SA154NW

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: SA154NW

Part 23 of the Federal Aviation Regulations, including Amendment 23-6.

Original Product – Type Certificate Number: A7SO Make: Piper Model: PA34-200, PA34-200T

Installation of full span flaps by removing aileron and changing the deployment route of all flaps, spoilers mounted above flap, conical cambered wing tips (optional), and anti-balance rudder tab (PA34-200 only) in accordance with the FAA sealed Robertson Aircraft Drawing List No. 27.

Date of Application: December 16, 1974 Date Reissued: 11/8/84; 10/10/86; 9/8/05; 7/31/17 Date of Issuance: January 28, 1975 Date Amended: 4/29/75; 4/13/76; 7/12/77

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: SA154NW

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: SA154NW

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

Date of Issuance: January 28, 1975 Amended Date: July 12, 1977 Date of Reissuance: July 31, 2017

An Robertson Aircraft FAA Approved Airplane Flight Manual Supplement is required for each model. (See STC Addendum)

The approval of this change in type design applies basically to Piper PA34-200/PA34-200T models only. This approval should not be extended to other aircraft of these models whose type design differs significantly or on which other previously approved modifications are incorporated unless it is determined that the interrelationship between this change and any other type design changes or previously approved modifications will introduce no adverse effect upon airworthiness of that aircraft. This determination should include consideration of significant changes in weight distribution such as an increase in the fixed disposable weight in the fuselage. A copy of this Certificate and STC Addendum SA154NW shall be maintained as part of the permanent records for the modified aircraft.

SUPPLEMENTAL TYPE CERTIFICATE ADDENDUM NO. SA154NW

The conditions and limitations of Type Certificate Data Sheet No. A7SO apply except as follows:

This STC Addendum, which is part of Supplemental Type Certificate SA154NW, prescribes conditions and limitations under which the product for which the STC was issued meets the airworthiness requirements of the Federal Air Regulations. A copy of this STC Addendum is required to be maintained as part of the modified aircraft’s permanent records.

SUPPLEMENTAL TYPE CERTIFICATE HOLDER: R/STOL SYSTEMS, INC.

MODEL PA34-200 (Normal Category); MODEL PA34-200T (Normal Category)

DATA PERTINENT TO ALL MODELS:

Equipment – The following Robertson Aircraft FAA Approved Airplane Flight Manual Supplement (AFMS) is required:

AFMS: 27-1 dated January 28, 1975, or later FAA approved revisions, for the modified PA34- 200.

AFMS: 27-2 dated April 13, 1976, or later FAA approved revisions for the modified PA34-200T, Serial number 34-7570001 to 34-7670371.

AFMS: 27-5 dated June 29, 1977 or later FAA approved revisions for the modified PA34- 200T, Serial number 37-7770001 and up.

NOTE 3. VMc placard Robertson Aircraft P/N 450-55. (On PA34-200) A450-80 (On PA34-200T) S/N 34-7570001 to 34-7670371

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: SA154NW

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

Date of Issuance: January 28, 1975 Amended Date: July 12, 1977 Date of Reissuance: July 31, 2017

NOTE 1. The Weight and Balance Report must be revised as follows:

For PA34-200 – Add 30 pounds at Station 129.

For PA34-200T – Add 25 pounds at Station 129.

NOTE 2. Flap placards Robertson Aircraft P/N A450-59, A450-58, A450-57. (On PA34-200) P/N A450-57, -58, -81 (On PA34-200T) S/N 34-7570001 to 34-7670371 P/N A450-57A, -58, -81 (On PA34-200T) S/N 34-7770001and up. 450-80A (On PA34-200T) S/N 34-7770001 and up NOTE 3. VMc placard Robertson Aircraft P/N 450-55. (On PA34-200) A450-80 (On PA34-200T) S/N 34-7570001 to 34-7670371 450-80A (On PA34-200T) S/N 34-7770001 and up NOTE 4. Placard Robertson Aircraft P/N A450-64 required if autopilot is installed.

NOTE 5. (Information only) – Potentiometer settings used in FCS-810 autopilot controller for preliminary bench calibration are as listed below.

(Ref. Bendix Service Manual for pin numbers.)

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: SA154NW

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

Date of Issuance: January 28, 1975 Amended Date: July 12, 1977 Date of Reissuance: July 31, 2017

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: SA154NW

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

Date of Issuance: January 28, 1975 Amended Date: July 12, 1977 Date of Reissuance: July 31, 2017

WING FLAP PERMISSIBLE WEAR TOLERANCES

The wing flap maximum free play measured at flap trailing edge is 0.15 inches total. Flap travel is determined by application of 10 lbs. force up and 10 lbs. force down on trailing edge where deflection is measured.

-END-

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: SA154NW

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