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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
Amendment 39-4204; AD 81-18-07

Airworthiness Directives; VOLPAR, INCORPORATED: Applies to Beech Models C-45G, TC-45G, C-45H, TC-45H, TC-45J (SNB-5), RC-45J (SNB-5P), D18C, D18S, E18S-9700, G18S, H18, JRB-6, 3N, 3NM, and 3TM Aircraft with Volpar Tricycle Landing Gear


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Regulatory Information

81-18-07 VOLPAR, INCORPORATED: Amendment 39-4204. Applies to Beech Models C-45G, TC-45G, C-45H, TC-45H, TC-45J (SNB-5), RC-45J (SNB-5P), D18C, D18S, E18S-9700, G18S, H18, JRB-6, 3N, 3NM, and 3TM Aircraft with Volpar Tricycle Landing Gear, (STC SA4-1531, STC SA111WE, STC SA1832WE or any other STC modification incorporating the provisions of this installation), certificated in all categories. Compliance required as indicated unless already accomplished. To prevent possible main landing gear collapse due to bolt failure, accomplish the following:

(a) Prior to further flight after the effective date of this AD, visually inspect the main landing gear Walking Beam upper attach bolt P/N AN179-46A for integrity and for adequate installation as specified in "Accomplishment Instructions", Part 1, Paragraphs (a) and (b) of Volpar, Inc. Service Bulletin Number 22 dated June 1, 1981. If the bolt has failed, replace with like serviceable part (or replacement part per paragraph (b) of this AD) prior to return to service.

(b) Prior to the accumulation of 200 additional hours' time in service, or at the next annual inspection, whichever occurs sooner, remove AN179-46A bolt and associated hardware and install NAS 149-80 bolt and associated hardware as specified in "Description of Change" section of Volpar, Inc. Service Bulletin Number 22, dated June 1, 1981.

(c) At intervals not to exceed 3,000 hours' time in service since the installation of Bolt P/N NAS 149-80, visually inspect the bolt installation for integrity and replace with like serviceable part, if necessary.

(d) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate aircraft to a base for the accomplishment of inspections or modifications required by this AD.

(e) Alternative inspections, modifications or other actions which provide an equivalent level of safety may be used when approved by the Chief, Engineering and Manufacturing Branch, FAA Western Region.

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 Volpar, Incorporated, Van Nuys, California 91406, telephone (213) 994-5023. These documents may also be examined at FAA Western Region Office, 15000 Aviation Boulevard, Hawthorne, California 90261 and at FAA Headquarters, 800 Independence Avenue, S.W., Washington, D.C. 20591. A historical file on this AD, which includes the incorporated material in full, is maintained by the FAA at its headquarters in Washington, D.C. and at FAA Western Region Office.

This amendment becomes effective September 10, 1981.



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