[Federal Register Volume 59, Number 235 (Thursday, December 8, 1994)]
[Unknown Section]
[Page 0]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 94-30181]
[[Page Unknown]]
[Federal Register: December 8, 1994]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 94-SW-12-AD]
Airworthiness Directives; Costruzioni Aeronautiche Giovanni
Agusta S.p.A. Model A109A, A109AII, and A109C Series Helicopters
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes the adoption of a new airworthiness
directive (AD) that is applicable to certain Costruzioni Aeronautiche
Giovanni Agusta S.p.A. Model A109A, A109AII, and A109C series
helicopters. This proposal would require a modification of the tail
boom vertical fin to create inspection openings that permit initial and
repetitive visual inspections for cracks in the vertical fin rear spar
attachment area. This proposal is prompted by four reports of cracks in
the tail boom vertical fin rear spar attachment area. The actions
specified by the proposed AD are intended to prevent failure of the
vertical fin attachment caused by cracks in the tail boom vertical fin
rear spar attachment area, and subsequent loss of control of the
helicopter.
DATES: Comments must be received by February 6, 1995.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Office of the Assistant Chief Counsel, 2601
Meacham Blvd., Room 663, Fort Worth, Texas 76137. Comments may be
inspected at this location between 9:00 a.m. and 3:00 p.m., Monday
through Friday, except Federal holidays.
The service information referenced in the proposed rule may be
obtained from Agusta, Direzione Supporto Prodotto E Servizi, 21019
Somma Lombardo (VA), Via per Tornavento, 15. This information may be
examined at the FAA, Office of the Assistant Chief Counsel, 2601
Meacham Blvd., Room 663, Fort Worth, Texas.
FOR FURTHER INFORMATION CONTACT: Mr. James Major, Aerospace Engineer,
Rotorcraft Standards Staff, FAA, Rotorcraft Directorate, 2601 Meacham
Blvd., Fort Worth, Texas, 76137, telephone (817) 222-5117, fax (817)
222-5961.
SUPPLEMENTARY INFORMATION:
Comments Invited
Interested persons are invited to participate in the making of the
proposed rule by submitting such written data, views, or arguments as
they may desire. Communications should identify the Rules Docket number
and be submitted in triplicate to the address specified above. All
communications received on or before the closing date for comments,
specified above, will be considered before taking action on the
proposed rule. The proposals contained in this notice may be changed in
light of the comments received.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the proposed rule. All
comments submitted will be available, both before and after the closing
date for comments, in the Rules Docket for examination by interested
persons. A report summarizing each FAA-public contact concerned with
the substance of this proposal will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this notice must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket No. 94-SW-12-AD.'' The postcard will be date stamped and
returned to the commenter.
Availability of NPRMs
Any person may obtain a copy of this NPRM by submitting a request
to the FAA, Office of the Assistant Chief Counsel, Attention: Rules
Docket No. 94-SW-12-AD, 2601 Meacham Blvd., Room 663, Fort Worth,
Texas, 76137.
Discussion
The Registro Aeronautico Italiano (RAI), which is the airworthiness
authority for Italy, recently notified the FAA that an unsafe condition
may exist on Costruzioni Aeronautiche Giovanni Agusta S.p.A. Model
A109A, A109AII, and A109C series helicopters. The RAI advises that
there have been four reports of cracks in the tail boom vertical fin
rear spar attachment area, which is currently not accessible for
inspection.
Costruzioni Aeronautiche Giovanni Agusta S.p.A. has issued Agusta
Bollettino Tecnico No. 109-96, dated March 30, 1994 (service bulletin),
which specifies a modification of the tail boom vertical fin on certain
helicopters to create inspection openings that permit visual inspection
for cracks in the vertical fin rear spar attachment area, and specifies
initial and repetitive visual inspections for cracks in the vertical
fin rear spar attachment area. The RAI classified this service bulletin
as mandatory and issued RAI AD 94-098, dated April 22, 1994, in order
to assure the continued airworthiness of these helicopters in Italy.
These helicopter models are manufactured in Italy and are type
certificated for operation in the United States under the provisions of
Sec. 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the
applicable bilateral airworthiness agreement. Pursuant to this
bilateral airworthiness agreement, the RAI has kept the FAA informed of
the situation described above. The FAA has examined the findings of the
RAI, reviewed all available information, and determined that AD action
is necessary for products of this type design that are certificated for
operation in the United States.
Since an unsafe condition has been identified that is likely to
exist or develop on other Costruzioni Aeronautiche Giovanni Agusta
S.p.A. Model A109A, A109AII, and A109C series helicopters of the same
type design registered in the United States, the proposed AD would
require, within the next 100 hours time-in-service (TIS), an initial
visual inspection for cracks in the vertical fin rear spar attachment
area and modification of the tail boom vertical fin to create
inspection openings that permit recurring visual inspections.
Thereafter, it would require repetitive visual inspections for cracks
in the vertical fin rear spar attachment area at intervals not to
exceed 300 hours TIS. This proposal is prompted by four reports of
cracks in the tail boom vertical fin rear spar attachment area. The
actions would be required to be accomplished in accordance with the
service bulletin described previously.
The FAA estimates that 73 helicopters of U.S. registry would be
affected by this proposed AD, 14 helicopters with tail boom, part
number (P/N) 109-0370-01 installed, and 59 helicopters with tail boom,
P/N 109-0370-17 installed, that it would take (1) approximately 4 work
hours per helicopter to initially modify and inspect those helicopters
with tail boom, part number (P/N) 109-0370-01; (2) approximately 6 work
hours per helicopter to initially modify and inspect those helicopters
with tail boom, P/N 109-0370-17; and, (3) approximately 1 work hour per
helicopter to conduct the repetitive inspection regardless of which
tail boom is installed, and that the average labor rate is $60 per work
hour. Required parts would cost approximately $140 for helicopters with
tail boom, P/N 109-0370-01 and $280 for helicopters with tail boom, P/N
109-0370-17. Based on these figures, the total cost impact of the
proposed AD on U.S. operators during the first year is estimated to be
$5,320 for helicopters with tail boom, P/N 109-0370-01, and $37,760 for
helicopters with tail boom, P/N 109-0370-17, and for each subsequent
year, regardless of the type of tail boom installed, $180, assuming
that three helicopters are subject to the repetitive inspection each
year.
The regulations proposed herein would 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
proposal would not have sufficient federalism implications to warrant
the preparation of a Federalism Assessment.
For the reasons discussed above, I certify that this proposed
regulation (1) is not a ``significant regulatory action'' under
Executive Order 12866; (2) is not a ``significant rule'' under the DOT
Regulatory Policies and Procedures (44 FR 11034, February 26, 1979);
and (3) if promulgated, 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 copy of the draft
regulatory evaluation prepared for this action is contained in the
Rules Docket. A copy of it may be obtained by contacting 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.
The Proposed Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend
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 adding a new airworthiness directive
to read as follows:
Costruzioni Aeronautiche Giovanni Agusta S.P.A.: Docket No. 94-SW-
12-AD.
Applicability: Model A109A, A109AII, and A109C series
helicopters, serial number (S/N) 7670 and lower, excluding S/N 7630,
7633, 7645, 7651, 7654, 7663, 7665, 7666, 7667, 7668, and 7669,
certificated in any category.
Compliance: Required as indicated, unless accomplished previously.
To prevent failure of the vertical fin attachment caused by
cracks in the tail boom vertical fin rear spar attachment area, and
subsequent loss of control of the helicopter, accomplish the
following:
(a) Within the next 100 hours time-in-service (TIS), modify the
tail boom vertical fin and perform a visual inspection for cracks in
the vertical fin rear spar attachment area in accordance with Part I
of the Accomplishment Instructions of Agusta Bollettino Tecnico No.
109-96, dated March 30, 1994.
(1) For helicopters with tail boom, part number (P/N) 109-0370-
01, perform the modification using modification kit, P/N 109-0822-
38-101, in accordance with steps 5 through 8 of Part I of the
Accomplishment Instructions of Agusta Bollettino Tecnico No. 109-96,
dated March 30, 1994.
(2) For helicopters with tail boom, P/N 109-0370-17, perform the
modification using modification kit, P/N 109-0822-38-103, in
accordance with steps 9 through 12 of Part I of the Accomplishment
Instructions of Agusta Bollettino Tecnico No. 109-96, dated March
30, 1994.
(b) Thereafter, at intervals not to exceed 300 hours TIS from
the last inspection, remove the vertical fin leading edge fairing
assembly and visually inspect the vertical fin rear spar attachment
area for cracks in accordance with Part II of the Accomplishment
Instructions of Agusta Bollettino Tecnico No. 109-96, dated March
30, 1994.
(c) 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. 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.
(d) 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.
Issued in Fort Worth, Texas, on December 2, 1994.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 94-30181 Filed 12-7-94; 8:45 am]
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