[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]
BILLING CODE 4910-13-P