AD 68-20-04

AD Final Rules - DRS_68-20-04.html
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AD Number:
68-20-04
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; PIPER Model Piper PA-31 and PA-31-300 Aircraft.
Subject:
Elevator Torque Tube
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
09/27/1968
Effective Date:
09/27/1968
Make:
Piper Aircraft Inc.
Model:
PA-31 | PA-31-300
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Superseded AD: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Superseded By: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: 68-20-04
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-660

AD NUMBER:   68-20-04

SUBJECT HEADING:   Airworthiness Directives; PIPER Model Piper PA-31 and PA-31-300 Aircraft.

ACTION:  

SUMMARY:  

DATES:   Effective September 27, 1968.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
68-20-04 PIPER: Amendment 39-660. Applies to Piper PA-31 and PA-31-300 type aircraft. Serial Numbers: 31-2 to 31-74 inclusive; 31-76 to 31-131 inclusive; 31-133 to 31-144 inclusive; 31-146 to 31-184 inclusive; 31-186 to 31-247 inclusive; 31-249 to 31-299 inclusive.

To detect cracks in the elevator torque tube P/N 40070-02 in elevator torque tube assembly P/N 40070-00 accomplish the following on aircraft with 100 hours or more total time in service:

(a) Prior to next flight, unless already accomplished, remove the fuselage tail fairing and visually inspect the elevator torque tube P/N 40070-02 for any deformation or cracking.

(b) Within the next 25 hours' time in service after the effective date of this Airworthiness Directive, unless already accomplished within the last 75 hours' time in service, remove the torque tube assembly P/N 40070-00 from the aircraft. Remove the horn assembly and two (2) brackets and inspect the torque tube P/N 40070-02 for evidence of cracks using the dye penetrant method in conjunction with a glass of at least 10 power, or magnetic particle Inspection or x-ray or an FAA approved equivalent inspection. Inspections must be repeated within 100 hours time in service from the last inspection.

(c) If no cracks are found at the inspection at 500 hours' time in service, visually inspect thereafter at intervals not to exceed 100 hours' time in service from the last inspection for any deformation or cracking.

(d) Prior to further flight, replace any cracked or deformed torque tube with a new part, which if P/N 40070-02 then such new part must be inspected in accordance with paragraph (b) and (c). Any other part number would not be covered by this Airworthiness Directive.

This amendment is effective September 27, 1968, and was effective upon receipt for all recipients of the telegram dated July 31, 1968, which contained this amendment. This Airworthiness Directive supersedes the referenced telegram.


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