AD 80-15-02

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AD Number:
80-15-02
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; Partenavia Costruzioni Model P.68 and P.68B Series Airplanes
Subject:
Rudder Control System
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
07/21/1980
Make:
Vulcanair S.p.A.
Model:
P 68 | P 68B
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Superseded AD: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Superseded By: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: 80-15-02
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-3839

AD NUMBER:   80-15-02

SUBJECT HEADING:   Airworthiness Directives; Partenavia Costruzioni Model P.68 and P.68B Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective July 21, 1980.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:   80-15-02 PARTENAVIA COSTRUZIONI AERONAUTICHE S.p.A.: Amendment 39- 3839. Applies to Partenavia Model P.68 and P.68B airplanes serial numbers 1 through 165, except serial number 40, certificated in all categories, which have rudder cable pulley brackets P/N 2.3097-1 installed.

Compliance required as indicated, unless already accomplished.

To prevent the loss of proper rudder cable tension and rudder control system failure, accomplish the following:

(a) For airplanes which have more than 500 hours time in service on the effective date of this AD, within the next 50 hours time in service after the effective date of this AD, accomplish paragraph (c) or paragraph (e) of this AD.

(b) For airplanes which have less than 500 hours time in service on the effective date of this AD, before accumulating a total of 500 hours time in service, or within the next 50 hours time in service after the effective date of this AD, whichever occurs later, accomplish paragraph (c) or paragraph (e) of this AD.

(c) Inspect the rudder pedal interconnecting bell crank bracket for cracks with special attention to the lower bracket and the rear face of aircraft frame number 3 for cracks and loose rivets in the area of the rudder cable pulley bracket attachment in accordance with PART II "Instructions" of Partenavia Service Bulletin 40, dated September 9, 1978, or an FAA-approved equivalent. If no cracks are found, repeat the inspection at intervals not to exceed 50 hours time in service since the last inspection until paragraph (e) of this AD is accomplished.

(d) If as a result of an inspection required by paragraph (c) of this AD, cracks or loose rivets are found, before further flight, except as provided in paragraph (g) of this AD,

(1) repair cracks in frame number 3 by stop drilling;

(2) remove any loose rivets and replace with new rivets; and

(3) replace any cracked brackets, P/N 2.3097-1, by compliance with paragraph (e) of this AD.

Upon compliance with subparagraphs (1), (2) and (3) of this paragraph, the repetitive inspections required by paragraph (c) are no longer required.

(e) Replace the rudder pedal interconnecting bell crank bracket, P/N 2.3097-1, with a new bracket, P/N 2.3111-1, in accordance with PART III "Instructions" of Partenavia Service Bulletin No. 40, dated September 9, 1978, or an FAA-approved equivalent.

(f) Equivalent means of compliance specified in this AD must be approved by the Chief, Aircraft Certification Staff, Europe, Africa and Middle East Office, c/o American Embassy, Brussels, Belgium.

(g) Aircraft may be flown in accordance with FAR 21.197 and 21.199 to a location where the repairs and replacement can be performed.

This amendment becomes effective July 21, 1980.

FOOTER: