AD 81-06-08

AD Final Rules - DRS_81-06-08.html
Copy URL
Print/Save as PDF
Document Versions
 Feedback
Details
AD Number:
81-06-08
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; Piper Model PA-18-150 Airplanes
Subject:
Lower Fuselage Attachment Tab
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
11/16/1981
Effective Date:
11/19/1981
Make:
Piper Aircraft Inc.
Model:
PA-18-150
Product Type:
Aircraft
Product Subtype:
Small Airplane
Affected AD:
Superseded AD:
Affected By:
Superseded By:
Service/Office:
AIR-700: Compliance & Airworthiness Division
Office of Primary Responsibility:
AIR-720: Operational Safety Branch
CFR Part Reference:
Part 39
Comments:
AIRWORTHINESS DIRECTIVES FINAL RULES: 81-06-08
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-4264

AD NUMBER:   81-06-08

SUBJECT HEADING:   Airworthiness Directives; Piper Model PA-18-150 Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective November 19, 1981.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
81-06-08 PIPER: Amendment 39-4264. Applies to Piper PA-18-150 Airplanes, S/N 18- 8602 thru 18-8109013, certificated in all categories.

Compliance required as indicated.

To prevent failure of the lower fuselage attachment tab which connects the lower horizontal stabilizer brace wire to the fuselage, accomplish the following:

(a) Within the next 10 hours in service after the effective date of this AD, unless already accomplished, conduct a visual inspection of the lower fuselage attachment tab, Piper P/N 80292-15, in the area of the welds for cracks. If cracks are found, install the tail brace wire support in accordance with the Instructions Section of Piper Service Bulletin 706 dated February 23, 1981, or approved alternate method, prior to further flight. If no cracks are found, install the tail brace wire support in accordance with (b) or (c), as appropriate.

(b) For airplanes with less than 500 hours in service on the effective date of this AD, within the next 10 hours in service, unless already accomplished, install the tail brace wire support in accordance with the Instructions Section of Piper Service Bulletin 706 dated February 23, 1981.

(c) For airplanes with 500 hours or more time in service on the effective date of this AD, within the next 100 hours in service, unless already accomplished, install the tail brace wire support in accordance with the Instructions Section of Piper Service Bulletin 706 dated February 23, 1981.

(d) Report findings of cracked parts to the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region, within five days of the inspection; include the time on the part and aircraft serial number. (Reporting approved by the Office of Management and Budget under OMB No. 04-R0174.)

(e) Alternative inspections, alterations, or repairs which provide an equivalent level of safety may be used when approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region.

(f) Upon submission of substantiating data by an owner or operator through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region may adjust the compliance times specified in this AD.

NOTE: Retention of original tab fitting P/N 80292-15 on the airplane is optional.

This amendment is effective November 19, 1981, for all persons except those to whom it was made effective immediately by airmail letter dated March 13, 1981.

FOOTER: