AD 81-07-08

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AD Number:
81-07-08
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; Partenavia Model P68 and P68B Series Airplanes
Subject:
Longitudinal Trim Tab
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
04/06/1981
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Superseded AD: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Superseded By: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: 81-07-08
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-4074

AD NUMBER:   81-07-08

SUBJECT HEADING:   Airworthiness Directives; Partenavia Model P68 and P68B Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective April 6, 1981.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
81-07-08 PARTENAVIA COSTRUZIONI AERONAUTICHE S.p.A.: Amendment 39-4074. Applies to Model P68 and P68B series airplanes, Serial Numbers 1 to 75 inclusive which do not have Partenavia Kit P/N 68-010 installed, and Serial Numbers 76 to 159 inclusive which do not have Partenavia Kit P/N 68-009 installed, certificated in all categories.

Compliance is required as indicated, unless already accomplished.

To prevent inadvertent positioning of the longitudinal trim tab to an incorrect position for takeoff, accomplish the following:

(a) Before each flight, until the airplane is modified in accordance with paragraph (e) of this AD -

(1) Set the longitudinal trim tab position indicator to the zero position.

(2) Position the leading edge of the stabilator to the zero reference point on the left, aft side of the fuselage, as described in Partenavia Service Bulletin No. 41, dated October 5, 1978 (hereinafter referred to as the Service Bulletin), or an FAA-approved equivalent.

(b) If, as a result of the check in paragraph (a) of this AD, the longitudinal trim tab is streamlined, the longitudinal trim tab position indicator is positioned correctly.

(c) If, as a result of the check in paragraph (a) of this AD, the longitudinal trim tab is not streamlined with the stabilator:

(1) Reposition the longitudinal trim tab position indicator to read zero when the longitudinal trim tab and stabilator are streamlined with the stabilator leading edge set to its zero reference; or

(2) Set the stabilator leading edge to the zero reference as in paragraph (a)(2) of this AD, and rotate the trim wheel until the stabilator and the longitudinal trim tab are streamlined to obtain a new zero position for the trim tab position indicator. Note the amount and direction the new zero point varies from the originally marked zero point and install, adjacent to the longitudinal trim tab position indicator, a placard which shows the amount and direction of the correction that must be used when setting the longitudinal trim tab for takeoff.

(d) The check required by paragraph (a) of this AD and the repositioning required by paragraph (c) of this AD may be performed by the pilot and an entry made in the airplane maintenance records in accordance with Part 43 of the Federal Aviation Regulations.

(e) Within 50 hours time in service after the effective date of this AD

(1) For airplanes with Serial Numbers 1 to 75 inclusive, install Partenavia Kit P/N 68-010 in accordance with the kit manufacturer's instructions, or an FAA-approved equivalent.

(2) For airplanes with Serial Numbers 76 to 159 inclusive install Partenavia Kit P/N 68-009 in accordance with the kit manufacturer's instructions, or an FAA-approved equivalent.

(f) If an equivalent means of compliance is used in complying with this AD, that equivalent must be approved by the Chief, Aircraft Certification Staff, AEU-100, FAA, Europe, Africa and Middle East Office, c/o American Embassy, Brussels, Belgium.

The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Partenavia Costruzioni Aeronautiche S.p.A., Via Cava, Casoria - Napoli, Italy. These documents may be examined at FAA Headquarters, Room 916, 800 Independence Avenue, SW., Washington, DC 20591.

This amendment becomes effective April 6, 1981.

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