AD 80-19-14

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AD Number:
80-19-14
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; PIPER (Ted Smith) Model 600, 601 and 601P Airplanes
Subject:
Horizontal/Vertical Stabilizer
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
09/25/1980
Make:
Aerostar Aircraft Corporation
Model:
PA-60-600 (Aerostar 600) | PA-60-601 (Aerostar 601) | PA-60-601P (Aerostar 601P)
Product Type:
Aircraft
Product Subtype:
Small Airplane
Affected AD:
Superseded AD:
Affected By:
Superseded By:
Service/Office:
Office of Primary Responsibility:
CFR Part Reference:
Part 39
Comments:
AIRWORTHINESS DIRECTIVES FINAL RULES: 80-19-14
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-3915

AD NUMBER:   80-19-14

SUBJECT HEADING:   Airworthiness Directives; PIPER (Ted Smith) Model 600, 601 and 601P Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective September 25, 1980.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
80-19-14 PIPER (Ted Smith): Amendment 39-3915. Applies to Aerostar Model 600, 601 and 601P airplanes Serial Nos. 0001 through 0807 certificated in all categories.

To prevent possible loss of control due to structural failure of the vertical and horizontal stabilizer aft attach fittings, accomplish the following.

(a) Within 100 hours' time in service since the last dye penetrant or visual inspection or within 5 hours' time in service from the effective date of this AD, if no dye penetrant or visual inspection previously accomplished, visually inspect the aft horizontal and vertical stabilizer attach fittings for cracks per part I.A. of Piper Service Bulletin 600-88A dated July 29, 1980.

(b) If any crack extends into the web area of the fitting, replace cracked part with like serviceable part and replace fasteners using fasteners specified in Piper Kit 59 600-88 or Kit 59 600-88A.

(c) If more than 3 cracks are found in the flange area, replace cracked part with like serviceable part and replace attach fitting flange fasteners using fasteners specified in Piper Kit 59 600-88 or Kit SB 600-88A.

(d) If three (3) or less cracks are found in the flanges in any one fitting and do not extend into the web area of the fitting, within 200 hours' time in service or 180 days whichever occurs sooner from discovery of cracks, replace the fitting and fitting fasteners using fasteners specified in Piper Kit 59600-88 or Kit 59600-88A.

(e) Alternative inspections, modifications or other actions which provide an equivalent level of safety may be used when approved by the Chief, Aircraft Engineering Division, FAA Western Region.

This supersedes Amend. 39-3835 (45 FR 46346), AD 80-12-08.

This amendment becomes effective September 25, 1980.

FOOTER: