76-10-01 BELL: Amendment 39-2610 as amended by Amendment 39-2927. Applies to Bell Models 205A and 205A-1 helicopters certificated in all categories.
Compliance required as indicated.
To prevent possible loss of the tail boom as a result of possible fatigue cracks in the tail boom and fuselage attach fittings in the tail boom and fuselage, accomplish the following.
(a) For helicopters with less than 500 hours' total time in service after the effective date of this AD, conduct the visual inspections of this AD prior to attaining 550 hours' total time in service and thereafter at intervals not to exceed 50 hours' time in service from the last inspection.
(b) For helicopters with 500 or more hours' total time in service on the effective date of this AD, conduct the visual inspections of this AD within the next 50 hours' time in service and thereafter at intervals not to exceed 50 hours' time in service from the last inspection.
(c) Inspect the upper tail boom attach fittings for cracks, using a light and mirror, by removing the forward dome light of the baggage compartment. Inspect the fittings in the area of the most forward rivets. Special attention must be given to inspecting the upper left-hand fitting.
(d) Inspect the lower tail boom attach fittings for cracks, using a light and mirror, by removing the forward access door on the tail boom.
(e) Inspect the four tail boom attach fittings on the fuselage bulkhead, using a light and mirror, for cracks around the tail boom attach bolt and most aft fasteners. Special attention must be given to inspecting the lower left-hand fitting.
(f) Inspect, visually, the four tail boom barrel nut bores for cracks, after removing the plug buttons. Determine that not less than one thread or more than two threads of the tail boom attachment bolts protrude through each barrel nut.
(g) If cracks are found, replace the affected fitting prior to further flight in accordance with an FAA approved procedure.
(h) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, Flight Standards Division, FAA Southwest Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for that operator.
(i) This AD no longer applies to tailbooms that have been modified, repaired, and sealed as specified in Part II of Bell Helicopter Textron Service Bulletin No. 205-77-4 dated March 11, 1977, or later approved revisions.
(j) This AD does not apply to helicopters having S/N 30260 or higher.
(k) 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 the Service Manager, Bell Helicopter Textron, P.O. Box 482, Fort Worth, Texas 76101. These documents may also be examined at the Office of the Regional Counsel, Southwest Region, FAA, 4400 Blue Mound Road, Fort Worth, Texas, and at FAA Headquarters, 800 Independence Avenue, S.W., Washington, D.C. 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 the Southwest Regional Office in Fort Worth, Texas.
(Bell Helicopter message dated April 29, 1976, to all 205A/205A-1 operators pertains to this subject.)
Amendment 39-2610 became effective May 18, 1976.
This Amendment 39-2927 becomes effective July 1, 1977.