84-16-02 SIAI-MARCHETTI: Amendment 39-4898. Applies to Model S205, S208 and S208A Series (all serial numbers) airplanes certificated in any category.
Compliance: Required as indicated, unless already accomplished.
To preclude the collapse of the main landing gear by the failure of the reinforcement plate welds of the long arm cross-member of the main landing gear (MLG) accomplish the following:
(a) Visually inspect the MLG cross-member long arm reinforcement plate weld for cracks in accordance with the "INSTRUCTION FOR THE VISUAL INSPECTION" section of SIAI-Marchetti Service Bulletin SB No. 205B48E, dated May 14, 1984, hereinafter referred to as the SB, in accordance with the following applicable inspection schedules:
(1) Within 100 hours time-in-service, after the effective date of this AD, and thereafter every 100 hours time-in-service, for MLG reinforcement plates with less than 500 hours time-in-service.
(2) Within 50 hours time-in-service, after the effective date of this AD, and thereafter every 50 hours time-in-service for MLG reinforcement plates with more than 500 hours time-in-service and less than 1,000 hours time-in-service.
(3) Within 25 hours time-in-service, after the effective date of this AD, and thereafter every 25 hours time-in-service for MLG reinforcement plates with more than 1,000 hours time-in-service.
(4) Prior to further flight, after each hard landing, regardless of time-in-service.
(b) Inspect, using a dye-penetrant method, the MLG cross-member long arm reinforcement plate weld in accordance with the "INSTRUCTIONS FOR THE DYE CHECK INSPECTION" section of the SB in accordance with the following applicable inspection schedules:
(1) Within the next 100 hours time-in-service on those MLG braces having 400 or more hours time-in-service, after the effective date of this AD, or prior to the accumulation of 500 hours time-in-service on those MLG reinforcement plates with less than 400 hourstime-in-service on the effective date of this AD and thereafter at intervals not to exceed 500 hours time-in-service, or
(2) Within the next 500 hours time-in-service, since accomplishing the last dye penetrant inspection in accordance with AD 83-07-23.
(c) If cracks are found during inspections required by either paragraph (a) or (b) of this AD, prior to further flight;
(1) If the cracks are within the limits specified in Figure 2 of the SB, repair in accordance with SIAI-Marchetti Service Instructions (SI) No. 205-1S26, 14 May 1984, is authorized.
(2) If the cracks exceed the limits specified in Figure 2 of the SB replace the MLG brace in accordance with the following table:
INSTALLED P/N
REPLACEMENT P/N
205-9-012 Modified per SB 205B36
205-9-012-07
205-9-013 Modified per SB 205B36
205-9-013-08
205-9-012
205-9-012-07
205-9-013
205-9-013-08
205-9-012-05
205-9-012-07
205-9-013-05
205-9-013-08
205-9-502-01
205-9-502-03
205-9-502-02205-9-502-04
205-9-012-07
205-9-012-07
205-9-013-08
205-9-013-08
205-9-502-03
205-9-502-03
205-9-502-04
205-9-502-04
(d) 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.
(e) Operators who have not kept records of hours time-in-service of the MLG long arm cross-member must substitute airplane hours time-in-service in lieu thereof.
(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 may be used, if approved, by the Manager, Aircraft Certification Staff, AEU-100, Europe, Africa and Middle East Office, FAA, c/o American Embassy, 1000 Brussels, Belgium.
This AD supersedes AD 83-07-23, Amendment 39-4627, dated April 11, 1983.
This amendment becomes effective on August 23, 1984. AGUSTA SpA 3