AD 63-07-03

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AD Number:
63-07-03
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 Tabs
Status:
Current
Citation:
Federal Register: April 4, 1963
Citation Publish Date:
04/04/1963
Effective Date:
04/15/1963
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Superseded AD: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Superseded By: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: 63-07-03
CITATION:   [Federal Register: April 4, 1963]

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:  

AD NUMBER:   63-07-03

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

ACTION:  

SUMMARY:  

DATES:   Effective April 15, 1963.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
63-07-03 PIPER: Amdt. 551 Part 507 Federal Register April 4, 1963. Applies to All Models PA-23 and PA-23-160 Aircraft.

Compliance required as indicated.

Cracks and loose or working rivets have been found in the attachment area of the rudder trim tab horn, P/N 17059-00, to the rudder trim tab skin, P/N 17068-27. Cracked rudder trim tab ribs P/N 17068-17 also have been found. To preclude the separation of the trim tab horn from the trim tab, accomplish the following:

(a) On aircraft having 690 or more hours time in service on the effective date of this AD, within the next 10 hours' time in service unless already accomplished within the last 90 hours' time in service and within each 100 hours' time in service thereafter from the last inspection, accomplish the inspection specified in (c).

(b) On aircraft having less than 690 hours' time in service on the effective date of this AD, accomplish the inspection specified in (c) between 600 and 700 hours' time in service and within each 100 hours' time in service thereafter from the last inspection.

(c) Visually inspect with at least a 10-power magnifying glass the rudder trim tab horn attach rivets for looseness or evidence of rivet working and the adjacent tab skin for cracks.

(d) If skin cracks, loose or working rivets are found, visually inspect the rudder trim tab support rib, P/N 17068-17 for cracks.

(e) If any of the defects mentioned herein are found, repair in accordance with Civil Air Regulations Part 18 or replace the affected part, or parts, with an airworthy assembly prior to further flight.

(Piper's Periodic Inspection Report pertains to this same subject.)

This directive effective April 15, 1963.

FOOTER: