Airworthiness Directive

Hide details for Federal Register InformationFederal Register Information
This information is not available.

Hide details for Header InformationHeader Information

Federal Aviation Administration

14 CFR Part 39

AD 55-21-02

Airworthiness Directives; Piper All Model PA-23 Aircraft
PDF Copy (If Available):

Hide details for Preamble InformationPreamble Information
AGENCY: Federal Aviation Administration, DOT

Hide details for Regulatory InformationRegulatory Information

55-21-02 PIPER: Applies to All Model PA-23 Aircraft Through Serial Number 23-321, Except Serial Numbers 23-310, -311, -315, and -319.

Compliance required as indicated.

The wing front spar attachment fitting P/N 17079 at the centerline of the fuselage must be inspected and reinforced as indicated below. This is a welded steel fitting bolted to the front face of the front spar web and is accessible through the wing bottom access panel.

I. Compliance required prior to next flight and at every 15 hours thereafter. Visually inspect the wing front spar attachment fitting and if any damage is found such as bent flanges or any other visible distortion contact the Piper Corp. for further instruction prior to returning airplane to flight status.

II. Compliance required prior to November 1, 1955. If inspection of item I discloses no defects install reinforcement fitting assembly in accordance with Piper reinforcement Kit 754112 or equivalent. The inspections required in item I are not required after incorporating the fitting reinforcement.

(Piper Service Bulletin No. 142 dated October 4, 1955, covers this same subject.)

Hide details for CommentsComments

Updated RGL applicability to match AD applicability; CAR C-11-185