STC SA98AL

Number SA98AL

This certificate, issued to Cub Crafters, Inc.

1918 South 16th Avenue Yakima, WA 98903-1212

Part 3 of the Civil Air Regulations.

Original ProductType Certificate Number: 1A2 Make: Piper Model: See Page 3

Description of the Type Design Change: Installation of two (2) Stoddard Aero Service Model 17 auxiliary fuel tanks in the PA-18A, PA-18S, PA-18-125, and PA-18-135 models and installation of two (2) model 18 and/or two

(2) model 19 auxiliary fuel tanks in the -150 models. Fabrication and installation must be in accordance with Stoddard Aero Service Drawing List No. 98, dated February 7, 1975, or later Federal Aviation Administration approved revision. Stoddard Aero Service Airplane Flight Manual Supplement is required with -150 models having four (4) auxiliary tanks installed.

Limitations and Conditions: 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.

Date of application: January 21, 1964 Date reissued: May 14, 1998; January 26, 2012 Date of issuance: March 6, 1964 Date amended: February 7, 1975

(Signature) Acting Manager, Seattle Aircraft Certification Office (Title)

Number SA98AL

Cub Crafters, Inc.

Issued: March 6, 1964 Reissued: May 14, 1998; January 26, 2012 Amended: February 7, 1975

Limitations and Conditions continued: EDO 89-2000 floats, specification item No. 209(b) is required on seaplane models modified to this STC.

The approval of this change in type design applies basically to Piper models PA-18-125, PA-18S-125, PA-18A, PA-18AS, PA-18-135, PA-18S-135, PA-18A-135, PA-18AS-135, PA-18-150, PA-18S-150, PA-18A-150, and PA-18AS-150 only. This approval should not be extended to other aircraft of this model on which 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. This determination should include consideration of significant changes in weight distribution such as an increase in the fixed disposable weight in the fuselage.

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