AD 63-24-03

AD Final Rules - DRS_63-24-03.html
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AD Number:
63-24-03
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; Piper All Models PA-23 and PA-23-160 Aircraft
Subject:
Rudder Trim Tab Control Rod Assembly
Status:
Current
Citation:
Federal Register: November 27, 1963
Citation Publish Date:
11/27/1963
Effective Date:
11/27/1963
Make:
Piper Aircraft Inc.
Model:
PA-23 | PA-23-160
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Superseded AD: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Superseded By: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: 63-24-03
CITATION:   [Federal Register: November 27, 1963]

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:  

AD NUMBER:   63-24-03

SUBJECT HEADING:   Airworthiness Directives; Piper All Models PA-23 and PA-23-160 Aircraft

ACTION:  

SUMMARY:  

DATES:   Effective November 27, 1963.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
63-24-03 PIPER: Amdt. 649 Part 507 Federal Register November 27, 1963. Applies to All Models PA-23 and PA-23-160 Aircraft.

Compliance required within the next 50 hours' time in service after the effective date of this AD, unless already accomplished within the past 50 hours' time in service. Every 100 hours' time in service thereafter comply with paragraphs (b), (c), and (d).

Several failures of the rudder trim tab actuating rod, Piper P/N 17271-00, through the bend radius of the forward hooked end and a disconnection due to a lost cotter pin have resulted in free trim tabs oscillating the rudder. Therefore, the following must be accomplished:

(a) Remove the rudder trim tab control rod assembly from the aircraft.

(b) Visually inspect for cracks in the area of the hooked end using a magnifying lens of at least 10-power.

(c) Check the hooked end for wear in excess of 0.040 inch in the area of contact with the jackscrew.

(d) Rudder trim tab control rods with cracks, or wear in excess of 0.040 inch shall be replaced before further flight.

(e) Redrill the cotter pin hole in the hooked end to 0.081 inch-diameter and reinstall the rudder trim tab control rod assembly using a roll pin, Piper P/N 480728, and 0.032 inch- diameter steel safety wire, in lieu of the cotter pin.

(Piper Service Letter No. 407, dated October 4, 1963, which pertains to this same subject, outlines and illustrates inspection and installation methods.)

This directive effective November 27, 1963.

FOOTER: