AD 83-12-04

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AD Number:
83-12-04
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; Partenavia Model P68, P68B, P68C, P68C-TC, and P68 Observer Series Airplanes
Subject:
Flap Bellcrank Attach Mountings
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
06/23/1983
Make:
Vulcanair S.p.A.
Model:
P 68 | P 68 Observer | P 68B | P 68C | P 68C-TC
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Superseded AD: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Superseded By: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:
Updated RGL applicability to match AD applicability; CAR C-11-185
AIRWORTHINESS DIRECTIVES FINAL RULES: 83-12-04
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-4666

AD NUMBER:   83-12-04

SUBJECT HEADING:   Airworthiness Directives; Partenavia Model P68, P68B, P68C, P68C-TC, and P68 Observer Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective June 23, 1983.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:   83-12-04 PARTENAVIA S.p.A.: Amendment 39-4666. Applies to Models P68, P68B, P68C, P68C-TC, and P68 Observer (Serial Numbers 1 through 277) airplanes certificated in any category.

Compliance: Required as indicated, unless already accomplished.

To prevent failure of the flap bellcrank attachment mounting brackets, accomplish the following:

a) Within the next 100 hours time-in-service from the effective date of this AD, or upon the accumulation of 500 hours time-in-service, whichever occurs later, and thereafter at intervals not to exceed 100 hours time-in-service from the last inspection, visually inspect the flap bellcrank attachment mounting brackets (P/N 68-1.5035-1 and 68-1.5035-2) on both wings as described in Partenavia Service Bulletin (SB) No. 56, dated October 7, 1982 (herein referred to as the SB). Inspect for cracks in the area surrounding the pivot bolt hole by looking through the inspection door on the inboard side of the engine nacelles and by using a mirror to look at the upper bracket.

b) If any cracks are found, prior to further flight stop drill the crack and install reinforcement kit (P/N 025) in accordance with Drawing R-0059 of the SB.

c) Within the next 100 hours time-in-service from the effective date of this AD or upon accumulating 1,000 hours time-in-service whichever occurs later unless already accomplished per paragraph b) of this AD, install the reinforcement kit (P/N 025) in accordance with Drawing R-0059 of the SB.

d) The repetitive inspections of paragraph a) of this AD are no longer required when the reinforcement kit (P/N 025) is installed.

e) The intervals between the repetitive inspections required by this AD may be adjusted up to 10 percent of the specified interval to allow accomplishing these inspections concurrent with other scheduled maintenance of the airplane.

f) Aircraft may be flown in accordance with Federal Aviation Regulation 21.197 to a location where this AD can be accomplished.

g) An equivalent method of compliance with this AD, if used, must be approved by the Manager, Aircraft Certification Staff, AEU-100, Europe, Africa and Middle East Office, FAA, c/o American Embassy, 1000 Brussels, Belgium.

This amendment becomes effective on June 23, 1983.

FOOTER: