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2010-09-24
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Airworthiness Directives; Agusta S.p.A. Model A109A and A109A II Helicopters
Rules and Regulations
D09002ee1bdfb812d
D09002ee1bdfb81b8
United States
Department of Transportation
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org
United States Government Agency or Subagency
United States
Federal Aviation Administration
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org
United States Government Agency or Subagency
This amendment supersedes an existing airworthiness directive (AD), applicable to Agusta Model A109A and A109A II helicopters, that currently requires inspecting each tail rotor blade (blade) for a crack and replacing any cracked blade. This amendment requires, before further flight, inspecting any blade with 400 or more hours time-in- service (TIS) for a crack and replacing any cracked blade. This amendment is prompted by another report of a cracked blade since the issuance of the existing AD. Two of the three occurrences of cracked blades involved the loss of the tail rotor and 90-degree gearbox. The actions specified by this AD are intended to prevent fatigue failure of the blade, loss of the tail rotor, and subsequent loss of control of the helicopter.
64 FR 71009
https://www.govinfo.gov/app/details/FR-1999-12-20/99-32580
99-32580
fr20de99-11
RIN 2120-AA64
4910-13-U
Docket No. 99-SW-64-AD
Amendment 39-11472
AD 99-26-13
https://www.govinfo.gov/app/details/FR-1999-12-20/99-32580
https://www.govinfo.gov/content/pkg/FR-1999-12-20/html/99-32580.htm
https://www.govinfo.gov/content/pkg/FR-1999-12-20/pdf/99-32580.pdf
2 p.
71009
71010
64 FR 71009
Code of Federal Regulations
Title 14 Part 39
14 CFR Part 39
Regulation Identification Number 2120-AA64
RIN 2120-AA64
Airworthiness Directives; Agusta S.p.A. Model A109A and A109A II Helicopters; Federal Register Vol. 64, Issue
RULE
99-32580
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
2000-01-04
Docket No. 99-SW-64-AD
Amendment 39-11472
AD 99-26-13
4910-13-U
99-32580
Final rule; request for comments.
This amendment supersedes an existing airworthiness directive (AD), applicable to Agusta Model A109A and A109A II helicopters, that currently requires inspecting each tail rotor blade (blade) for a crack and replacing any cracked blade. This amendment requires, before further flight, inspecting any blade with 400 or more hours time-in- service (TIS) for a crack and replacing any cracked blade. This amendment is prompted by another report of a cracked blade since the issuance of the existing AD. Two of the three occurrences of cracked blades involved the loss of the tail rotor and 90-degree gearbox. The actions specified by this AD are intended to prevent fatigue failure of the blade, loss of the tail rotor, and subsequent loss of control of the helicopter.
Effective January 4, 2000. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of January 4, 2000.
Richard A. Monschke, Aerospace Engineer, FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, 2601 Meacham Blvd., Fort Worth, Texas 76137, telephone (817) 222-5116, fax (817) 222-5961.
Federal Register
Vol. 64, no. 243
Office of the Federal Register, National Archives and Records Administration
1999-12-20
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295 p.
Table of Contents:
AE 2.7:
GS 4.107:
AE 2.106:
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https://www.govinfo.gov/app/details/FR-1999-12-20
P0b002ee180a67176
0097-6326
0042-1219
0364-1406
769-004-00000-9
000582072
f:fr20de99
https://www.govinfo.gov/app/details/FR-1999-12-20
https://www.govinfo.gov/content/pkg/FR-1999-12-20/pdf/FR-1999-12-20.pdf
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2010-09-24
2023-05-05
FR-1999-12-20
machine generated
eng
FR
FR-1999-12-20
64
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