AD 65-15-05

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AD Number:
65-15-05
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; Piper Models PA-25 and PA-25-235 Aircraft
Subject:
Elevator Control System
Status:
Current
Citation:
Federal Register: July 8, 1965
Citation Publish Date:
07/08/1965
Effective Date:
07/18/1965
Make:
Lavia Argentina S.A. (Laviasa)
Model:
PA-25 | PA-25-235
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Superseded AD: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Superseded By: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: 65-15-05
CITATION:   [Federal Register: July 8, 1965]

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-105

AD NUMBER:   65-15-05

SUBJECT HEADING:   Airworthiness Directives; Piper Models PA-25 and PA-25-235 Aircraft

ACTION:  

SUMMARY:  

DATES:   Effective July 18, 1965.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
65-15-05 PIPER: Amdt. 39-105 Part 39 Federal Register July 8, 1965. Applies to Models PA-25, Serial Numbers 25-1 through 25-731, and PA-25-235, Serial Numbers 25-2000 through 25-3565 Aircraft.

Compliance required as indicated.

To prevent loss of the elevator control system as a result of worn clevis bolts, accomplish the following:

(a) For aircraft with less than 250 hours' time in service on the effective date of this AD, comply with (c) before the accumulation of 260 hours' time in service unless already accomplished, and thereafter at intervals not to exceed 250 hours' time in service from the last inspection until modified in accordance with (d).

(b) For aircraft with 250 or more hours' time in service on the effective date of this AD, comply with (c) within the next 10 hours' time in service unless already accomplished within the last 240 hours' time in service, and thereafter at intervals not to exceed 250 hours' time in service from the last inspection until modified in accordance with (d).

(c) Remove the clevis bolt, AN-24-14, from the center hole of the elevator cable link assembly, P/N 81352-15, at the lower end of the control column and inspect it for wear. Replace any clevis bolt that is worn where it contacts the link assembly with a new clevis bolt, AN-24-14.

(d) Replace link assemblies, P/N 81352-15, and spacer, P/N 61402-5, shown on Piper Drawing No. 64374, Revision B, with link assembly, P/N 64748, and bushing, P/N 64749, in accordance with Piper Service Letter No. 455 or an equivalent approved by the Chief, Engineering and Manufacturing Branch, FAA Southern Region.

This directive effective July 18, 1965.

FOOTER: