STC SA1416NM

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate Number SA1416NM This certificate issued to: C & P Aircraft Certifies that the change in the type design fer the felling product with the livitations and conditions thereferas specifulherenmutathenireshinss requirementarf Purt 3 of the CIVII Air Regulations.

Original Product -Type bertificute Number: 1A4 Make: Piper Alertel: PA-20 Station 85 accordance with C & P Aircraft photograph 1 and Document No. STU Surcamp/PA-20.

Limitations and Conditions: Data pertaining to this modification are considered inadequate for duplication in other aircraft. This approval is limited to the installation in Piper Model PA-20, Serial Number 20-525 only. A copy of this Certificate and Addendum shall be maintained as part of the permanent records for the modified aircraft.

Date of Application: September 8, 1981 Date Reissued:

I ate ef issuence December 28, 1981 Date Amended:

FEDERAL AVIATION By Direction of the Administrator Vanell Mclemen (Signature ) *MINISTRATOR Certification Office, ANM-100S (Title)

FAA FoR 8110-2 (10-68)

RAnited States of SUnctica Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number SA1416NM Supplemental Type Certificate ADDENDUM NO SA1416NM The conditions and limitations of Type Certificate Data Sheet Number 1A4 apply except where superseded by the following:

Supplemental Type Certificate Data Sheet, which is part of STC SA1416NM, prescribes the conditions and limitations under which the product for which the STC was issued meets the airworthiness requirements of the Civil Air Regulations:

Supplemental Type Certificate HOLDER: C & P AIRCRAFT Insert in the aircraft log book, the following:

Without disassembling the splice, inspect the right wing front spar splice and neighboring web area from stations 80 through 106 for fatigue cracks at each annual or every 100 hours time in service whichever occurs first. If cracks are found, replace the subject spar with a serviceable one.

FAA FORM 8110-2-1 (10-69) PAGE 3 OF 3 PAGES C FAA AC 73-2651