AD 78-08-03

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AD Number:
78-08-03
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; Piper Models PA-23 and PA-23-160 Airplanes
Subject:
Rudder Hinge Bracket Assembly
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
11/09/1978
Effective Date:
11/10/1978
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Superseded AD: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Superseded By: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: 78-08-03
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-3339

AD NUMBER:   78-08-03

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

ACTION:  

SUMMARY:  

DATES:   Effective November 10, 1978.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
78-08-03 PIPER: Amendment 39-3178 as amended by Amendment 39-3339. Applies to Piper Models PA-23 and PA-23-160, Serial Nos. 23-1 and up certificated in all categories.

To prevent hazards in flight associated with cracks in the rudder upper hinge reinforcing bracket or rudder lower hinge bracket assembly, accomplish the following:

(a) Within the next 25 hours in service from the effective date of this AD or upon the attainment of 1000 total hours in service, whichever is later, remove the rudder upper hinge P/N 17063-03 and inspect the rudder upper hinge reinforcement bracket P/N 17067-18 or equivalent for cracks using a dyne penetrant or equivalent method. Also inspect the rudder lower hinge bracket assembly P/N 17289-00 in the bearing area for cracks using a dye penetrant or equivalent method.

(b) Within 1000 hours in service after the inspection in (a), and thereafter at intervals not to exceed 1000 hours since the last inspection accomplish the inspections required in (a).

(c) If cracks are found in the reinforcing bracket during the inspections of paragraphs (a) or (b) remove it and inspect the spar web for cracks using a dye penetrant method or equivalent.

(d) Cracked parts must be replaced using undamaged parts of the same part number or equivalent before further flight.

(e) Equivalent inspections and repairs must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region or accomplished in accordance with Advisory Circular 43.13-1A and approved by an FAA Maintenance Inspector.

(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 inspection intervals specified in this AD.

(g) Report positive findings from paragraph (a) to Chief, Engineering and Manufacturing Section, FAA, Eastern Region within ten days of inspection. (Reporting approved by Office of Management and Budget under OMB No. 04-R0174).

Amendment 39-3178 was effective April 14, 1978.

This amendment 39-3339 is effective November 10, 1978.

FOOTER: