| AD Number | 84-13-06 R2 | Status | Active |
| Effective Date | August 30, 1987 | Issue Date | Not specified |
| Docket Number | Unknown | Amendment | 39-5682 |
| Product Type | ["Aircraft"] | Product Subtype | ["Rotorcraft"] |
| CFR Part | --- - Part 39 | CFR Section | N/A |
| Citation | This information is not available. | ||
| Manufacturer(s) | Agusta S.p.A. |
| Model(s) | A109A A109A II |
84-13-06 R2 COSTRUZIONI AERONAUTICHE GIOVANNI AGUSTA S.p.A.: Priority letter AD 84-13-06 as amended by Amendment 39-5043 is further amended by Amendment 39- 5682. Applies to Model A109A and A109A II series helicopters certificated in any category and equipped with P/N 109-0132-02-11 or -15 tail rotor blades.
Compliance is required as indicated unless already accomplished.
To prevent possible hazards in flight associated with cracking of the tail rotor blade grip, accomplish the following:
(a) Within the next 10 hours time in service, inspect the tail rotor blade grip in accordance with Part I of Agusta Service Bulletin (SB) 109-51, Revision A, or an FAA-approved equivalent, and at each additional 25 hours time in service, accomplish the inspection of Part III of Agusta SB 109-51, Revision A, or an FAA-approved equivalent.
(b) Prior to the first flight of each day, comply with Part II of the accomplishment instructions of Agusta SB 109-51, Revision A, or an FAA-approved equivalent. This accomplishment may be conducted by the pilot.
(c) Remove from service any tail rotor blade where cracking is found and replace with a serviceable part prior to next flight.
(d) An equivalent method of compliance with this AD may be used when approved by the Manager, Brussels Aircraft Certification Office.
Priority letter AD 84-13-06 was effective June 29, 1984.
Amendment 39-5043 was effective May 13, 1985.
This amendment, 39-5682, becomes effective August 30, 1987.