[Federal Register Volume 59, Number 207 (Thursday, October 27, 1994)]
[Unknown Section]
[Page 0]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 94-26599]
[[Page Unknown]]
[Federal Register: October 27, 1994]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 92-ASW-03; Amendment 39-9053; AD 94-22-04]
Airworthiness Directives; Costruzioni Aeronautiche Giovanni
Agusta S.p.A. Model A109A and A109AII Series Helicopters
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment supersedes an existing airworthiness directive
(AD), applicable to Costruzioni Aeronautiche Giovanni Agusta S.p.A.
Model A109A and A109AII series helicopters, that currently imposes a
calendar life limit of 10 years and 6 months on the main rotor
retention strap assemblies (strap assemblies). This amendment requires
reducing the calendar life limit to 8 years. This amendment is prompted
by additional service experience and analyses, that show the current
life limit needs to be reduced from 10 years and 6 months to 8 years to
prevent deterioration and subsequent failure of the strap assemblies.
The actions specified by this AD are intended to prevent failure of the
strap assemblies, loss of a main rotor blade, and subsequent loss of
control of the helicopter.
EFFECTIVE DATE: December 1, 1994.
ADDRESSES: This AD and any related information may be examined in the
Rules Docket at the Federal Aviation Administration (FAA), Office of
the Assistant Chief Counsel, 2601 Meacham Blvd., Room 663, Fort Worth,
Texas.
FOR FURTHER INFORMATION CONTACT: Mr. Mike Mathias, Aerospace Engineer,
Rotorcraft Standards Staff, FAA, Rotorcraft Directorate, 2601 Meacham
Blvd., Fort Worth, Texas 76137, telephone (817) 222-5123, fax (817)
222-5961.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) by superseding AD 87-15-10,
Amendment 39-5681, (52 FR 27787, July 24, 1987), which is applicable to
Costruzioni Aeronautiche Giovanni Agusta S.p.A. Model A109A and A109AII
series helicopters, was published in the Federal Register on August 21,
1992 (57 FR 37914). That action proposed to require an 8-year calendar
life instead of a 10 years and 6 months life limit on the strap
assemblies, part numbers 2601521 and 109-0101-95-1, -3, and -105.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. No comments were received on the
proposal or the FAA's determination of the cost to the public. However,
the words ``since installation'' have been removed and the word
``total'' has been added to paragraph (a)(2) to further clarify that
the TIS and the calendar years relate to the total time on the strap
assemblies and not to the time since they were installed on the
helicopter. Also, the terms ``calendar year'' and ``calendar month''
have now been defined in paragraph (a)(3). Finally, the average labor
rate was raised from $55 to $60. The FAA has determined that air safety
and the public interest require the adoption of the rule as proposed
with the noted changes. The FAA has determined that these changes will
neither increase the economic burden on any operator nor increase the
scope of the AD.
The FAA estimates that 46 helicopters of U.S. registry will be
affected by this AD, that it will take approximately 4 work hours per
helicopter to accomplish the required actions, and that the average
labor rate is $60 per work hour. Required parts will cost approximately
$1,931 per helicopter. Based on these figures, the total cost impact of
the AD on U.S. operators is estimated to be $99,866.
The regulations adopted herein will not have substantial direct
effects on the States, on the relationship between the national
government and the States, or on the distribution of power and
responsibilities among the various levels of government. Therefore, in
accordance with Executive Order 12612, it is determined that this final
rule does not have sufficient federalism implications to warrant the
preparation of a Federalism Assessment.
For the reasons discussed above, I certify that this action (1) Is
not a ``significant regulatory action'' under Executive Order 12866;
(2) is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979); and (3) will not have a
significant economic impact, positive or negative, on a substantial
number of small entities under the criteria of the Regulatory
Flexibility Act. A final evaluation has been prepared for this action
and it is contained in the Rules Docket. A copy of it may be obtained
from the Rules Docket at the location provided under the caption
ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
Adoption of the Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration amends part 39 of
the Federal Aviation Regulations (14 CFR part 39) as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. App. 1354(a), 1421 and 1423; 49 U.S.C.
106(g); and 14 CFR 11.89.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by removing Amendment 39-5681 (52 FR
27787, July 24, 1987), and by adding a new airworthiness directive
(AD), Amendment 39-9053, to read as follows:
AD 94-22-04 Costruzioni Aeronautiche Giovanni Agusta S.p.A.:
Amendment 39-9053. Docket Number 92-ASW-03. Supersedes AD 87-15-10,
Amendment 30-5681.
Applicability: Model A109A and A109AII series helicopters,
certificated in any category.
Compliance: Required as indicated, unless accomplished
previously.
To prevent failure of the main rotor retention strap assemblies
(strap assemblies), accomplish the following:
(a) Replace the strap assemblies, part numbers (P/N) 2061521 and
109-0101-95-1, -3, and -105, with airworthy strap assemblies in
accordance with the applicable maintenance manual and the following:
(1) For strap assemblies that have 7\1/2\ or more calendar years
time-in-service (TIS) on the effective date of this AD, replace the
strap assemblies within the next 6 calendar months or before
accumulating 5,000 hours total TIS on the strap assemblies,
whichever occurs first.
(2) For strap assemblies that have less than 7\1/2\ calendar
years TIS on the effective date of this AD, replace the strap
assemblies before accumulating 8 calendar years TIS or before
accumulating 5,000 hours total TIS on the strap assemblies,
whichever occurs first.
(3) For the purposes of this AD, the calendar compliance times
begin on the day the strap assemblies are installed on any
helicopter. Additionally, a calendar year is a 365-day period of
time. Also, a calendar month is a 30-day period of time.
(b) An alternative method of compliance or adjustment of the
compliance time that provides an acceptable level of safety may be
used when approved by the Manager, Rotorcraft Standards Staff, FAA,
Rotorcraft Directorate, or by the Manager, Brussels Aircraft
Certification Office, AEU-100, FAA, Europe, Africa, and Middle East
Office, c/o American Embassy, Brussels, Belgium. Operators shall
submit their requests through an FAA Principal Maintenance
Inspector, who may concur or comment and then send it to the
Manager, Rotorcraft Standards Staff.
Note: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Rotorcraft Standards Staff or the Brussels
Aircraft Certification Office.
(c) Special flight permits may be issued in accordance with
Secs. 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR
21.197 and 21.199) to operate the helicopter to a location where the
requirements of this AD can be accomplished.
(d) This amendment becomes effective on December 1, 1994.
Issued in Fort Worth, Texas, on October 21, 1994.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 94-26599 Filed 10-26-94; 8:45 am]
BILLING CODE 4910-13-P
