Airworthiness Directives; Costruzioni Aeronautiche Giovanni Agusta S.p.A. Model A109A and A109AII Series Helicopters

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]

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