[Federal Register Volume 67, Number 183 (Friday, September 20, 2002)]
[Proposed Rules]
[Pages 59217-59219]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-23881]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NE-06-AD]
RIN 2120-AA64


Airworthiness Directives; Turbomeca S.A. Arriel 1 A2, 1 C, 1 C1, 
1 C2, 1 D, 1 D1, 1 E2, 1 K, 1 K1, 1 S, 1 S1 and Arriel 2 B, 2 B1, 2 C, 
2 C1, 2 S1 Series Turboshaft Engines

AGENCY: Federal Aviation Administration, DOT.

ACTION: Supplemental notice of proposed rulemaking (NPRM); reopening of 
comment period.

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SUMMARY: This notice revises an earlier proposed airworthiness 
directive (AD), applicable to Turbomeca S.A. Arriel- 1 D, 1 D1, 1S, 1 
S1, 2 S1, and -2B series turboshaft engines. That proposal would have 
required the insertion of a sleeve in the attachment boss of the 
compressor bleed valve. That proposal was prompted by several cases of 
contained centrifugal compressor impeller blade ruptures that occurred 
in service. This proposed action revises the proposed rule by retaining 
the insertion of a sleeve in the attachment boss of the compressor 
bleed valve, adding requirements for bonding the sleeve in the bleed-
valve mounting pad, and expanding the applicability to Turbomeca Arriel 
1 A2, 1 C, 1 C1, 1 C2, 1 D, 1 D1, 1 E2, 1 K, 1 K1, 1 S, 1 S1, and 
Arriel 2 B, 2 B1, 2 C, 2 C1, 2 S1 series turboshaft engines. The 
actions specified by this proposed AD are intended to prevent acoustic 
excitation of the centrifugal compressor impeller blades resulting in 
contained compressor impeller blade ruptures and power loss that could 
lead to an uncommanded in-flight shutdown.

DATES: Comments must be received by November 19, 2002.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), New England Region, Office of the Regional 
Counsel, Attention: Rules Docket No. 2001-NE-06-AD, 12 New England 
Executive Park, Burlington, MA 01803-5299. Comments may be inspected at 
this location, by appointment, between 8 a.m. and 4:30 p.m., Monday 
through Friday, except Federal holidays. Comments may also be sent via 
the Internet using the following address: ``[email protected]''. 
Comments sent via the Internet must contain the docket number in the 
subject line.
    The service information referenced in the proposed rule may be 
obtained from Turbomeca S.A, 64511 Bordes Cedex, France; telephone 33 
05 59 64 40 00; fax 33 05 59 64 60 80. This information may be 
examined, by appointment, at the FAA, New England Region, Office of the 
Regional Counsel, 12 New England Executive Park, Burlington, MA.

FOR FURTHER INFORMATION CONTACT: Richard Woldan, Aerospace Engineer, 
Engine Certification Office, FAA, Engine and Propeller Directorate, 12 
New

[[Page 59218]]

England Executive Park, Burlington, MA 01803-5299; telephone (781) 238-
7136; fax (781) 238-7199.

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 action 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 action must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2001-NE-06-AD.'' The postcard will be date stamped and 
returned to the commenter.

Availability of NPRM's

    Any person may obtain a copy of this NPRM by submitting a request 
to the FAA, New England Region, Office of the Regional Counsel, 
Attention: Rules Docket No. 2001-NE-06-AD, 12 New England Executive 
Park, Burlington, MA 01803-5299.

Discussion

    A proposal to amend part 39 of the Federal Aviation Regulations (14 
CFR part 39) to add an airworthiness directive (AD), applicable to 
Turbomeca S.A. Arriel 1 D, 1 D1, 1S, 1 S1, 2 S1, and 2B series 
turboshaft engines, was published as a notice of proposed rulemaking 
(NPRM) in the Federal Register on September 6, 2001 (66 FR 46562). That 
NPRM required installing a sleeve into the attachment boss of the 
compressor bleed valve. That NPRM was prompted by several cases of 
contained centrifugal compressor impeller blade ruptures that occurred 
in service. That condition, if not corrected, could result in contained 
compressor impeller blade ruptures and power loss that could lead to an 
uncommanded in-flight shutdown.
    Since that NPRM was issued, the Direction Generale de L'Aviation 
Civile (DGAC), which is the airworthiness authority for France, has 
notified the FAA that the sleeve inserted in the attachment boss of the 
compressor bleed valve must be bonded in the bleed-valve mounting pad, 
and that the affected population of Turbomeca S.A. engines is expanded.
    Since these changes expand the scope of the originally proposed 
rule, the FAA has determined that it is necessary to reopen the comment 
period to provide additional opportunity for public comment.

Manufacturer's Service Information

    The FAA has reviewed and approved the technical contents of the 
following Turbomeca S.A. Arriel 1 A2, 1 C, 1 C1, 1 C2, 1 D, 1 D1, 1 E2, 
1 K, 1 K1, 1 S, 1 S1 and Arriel 2 B, 2 B1, 2 C, 2 C1, 2 S1 series 
turboshaft engine Mandatory Service Bulletins (MSB's):
    [sbull] MSB No. 292 72 2054, dated September 20, 1999, that 
incoporates Modification TU 54 and provides instructions for the 
removal of the compressor bleed valve, installation of the sleeve, and 
reinstallation of the compressor bleed valve on Arriel 2 B and 2 S1 
engines.
    [sbull] MSB No. 292 72 0261, dated September 20, 1999, that 
incorporates Modification TU 300 and provides instructions for the 
removal of the compressor bleed valve, installation of the sleeve, and 
reinstallation of the compressor bleed valve on Arriel 1 D, 1 D1, 1 S, 
and 1 S1 engines.
    [sbull] MSB No. 292 72 2070, Update 1, dated October 5, 2001, that 
incorporates Modification TU 70A, and provides instructions for bonding 
the sleeve in the bleed-valve mounting boss on Arriel 2 B, 2 B1, 2 C, 2 
C1, and 2 S1 engines.
    [sbull] MSB No. 292 72 0275, Update 1, dated October 2, 2001, that 
incorporates Modification TU 316A, and provides instructions for 
bonding the sleeve in the bleed-valve mounting boss on Arriel 1 A2, 1 
C, 1 C1, 1 2, 1 D, 1 D1, 1 E2, 1 K, 1 K1, 1 S, and 1 S1 engines.

Bilateral Agreement Information

    This engine model is manufactured in France and is 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 DGAC has kept the FAA informed 
of the situation described above. The FAA has examined the findings of 
the DGAC, 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.

FAA's Determination of an Unsafe Condition and Proposed Actions

    Since an unsafe condition has been identified that is likely to 
exist or develop on other Turbomeca S.A. Arriel 1 A2, 1 C, 1 C1, 1 C2, 
1 D, 1 D1, 1 E2, 1 K, 1 K1, 1 S, 1 S1 and Arriel 2 B, 2 B1, 2 C, 2 C1, 
2 S1 series turboshaft engines of the same type design that are used on 
helicopters registered in the United States, the proposed AD would 
require bonding a sleeve in the compressor bleed-valve mounting pad. 
The actions would be required to be done in accordance with the MSB's 
described previously.

Economic Analysis

    There are approximately 1,406 Turbomeca S.A. Arriel 1 and Arriel 2 
model turboshaft engines of the affected design in the worldwide fleet. 
The FAA estimates that 476 engines installed on helicopters of U.S. 
registry would be affected by this proposed AD. The FAA also estimates 
that it would take approximately 1.0 work hour per engine to perform 
the proposed actions, and that the average labor rate is $60 per work 
hour. Required parts would cost approximately $430 per engine. Based on 
these figures, the total cost of the proposed AD to U.S. operators is 
estimated to be $233,240.

Regulatory Analysis

    This proposed rule does not have federalism implications, as 
defined in Executive Order 13132, because it would not have a 
substantial direct effect 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. 
Accordingly, the FAA has not consulted with state authorities prior to 
publication of this proposed rule.
    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

[[Page 59219]]

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. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

    2. Section 39.13 is amended by adding the following new 
airworthiness directive:

Turbomeca S.A: Docket No. 2001-NE-06-AD.

Applicability

    This airworthiness directive (AD) is applicable to Turbomeca 
S.A. Arriel 1 A2, 1 C, 1 C1, 1 C2, 1 D, 1 D1, 1 E2, 1 K, 1 K1, 1 S, 
1 S1 and Arriel 2 B, 2 B1, 2 C, 2 C1, 2 S1 series turboshaft 
engines. These engines are installed on, but not limited to, 
Eurocopter France AS350B1, AS350B2, AS350B3; Astar 350D, Fennic 
AD550U2 and Sikorsky S-76A and S-76C series helicopters.

    Note 1: This AD applies to each engine identified in the 
preceding applicability provision, regardless of whether it has been 
modified, altered, or repaired in the area subject to the 
requirements of this AD. For engines that have been modified, 
altered, or repaired so that the performance of the requirements of 
this AD is affected, the owner/operator must request approval for an 
alternative method of compliance in accordance with paragraph (e) of 
this AD. The request should include an assessment of the effect of 
the modification, alteration, or repair on the unsafe condition 
addressed by this AD; and, if the unsafe condition has not been 
eliminated, the request should include specific proposed actions to 
address it.

Compliance

    Compliance with this AD is required within 30 days after the 
effective date of this AD, unless already done.
    To prevent acoustic excitation of the centrifugal compressor 
impeller blades, resulting in contained blade ruptures and power 
loss that could lead to an uncommanded in-flight shutdown, do the 
following:

Modification TU 300 Not Incorporated

    (a) For Arriel 1 D, 1 D1, 1 S, and 1 S1 engines that do not have 
TU 300 incorporated, incorporate TU 300 and TU 316A as follows:
    (1) Remove the bleed valve in accordance with the Instructions 
to be Incorporated of Turbomeca mandatory service bulletin (MSB) 292 
72 0261, dated September 20, 1999.
    (2) Install sleeve part number (P/N) 0 292 15 333 0 and the 
bleed valve in accordance with 2.B.(1)(d) through 2.B.(1)(g) of the 
Instructions to be Incorporated of Turbomeca MSB 292 72 0275, Update 
No. 1, dated October 2, 2001.

Modification TU 300 Incorporated

    (b) For Arriel 1 A2, 1 C, 1 C1, 1 C2, 1 D, 1 D1, 1 E2, 1 K, 1 
K1, 1 S and 1 S1 engines that have modification TU 300 incorporated, 
incorporate modification TU 316A in accordance with 2.B.(1)(a) 
through 2.B.(1)(g) or 2.B.(2) of the Instructions to be Incorporated 
of Turbomeca. MSB 292 72 0275, Update 1, dated October 2, 2001.

Modification TU 54 Not Incorporated

    (c) For Arriel 2 B and 2 S1 engines that do not have 
modification TU 54 incorporated, incorporate TU 54 and TU 70A as 
follows:
    (1) Remove the bleed valve in accordance with the Instructions 
to be Incorporated of Turbomeca MSB 292 72 2054, dated September 20, 
1999.
    (2) Install sleeve P/N 0 292 15 333 0 and the bleed valve in 
accordance with the 2.B.(1)(d) through 2.B.(1)(g) or 2.B.(2)of the 
Instructions to be Incorporated of Turbomeca MSB 292 72 2070, Update 
1, dated October 5, 2001.

Modification TU 54 Incorporated

    (d) For Arriel 2 B, 2 B1, 2 C, 2 C1 and 2 S1 engines that have 
modification TU 54 incorporated, incorporate modification TU 70A in 
accordance with 2.B.(1)(a) through 2.B.(1)(g) or 2.B.(2) of the 
Instructions to be Incorporated of Turbomeca MSB 292 72 2070, Update 
1, dated October 5, 2001.

Alternative Methods of Compliance

    (e) An alternative method of compliance or adjustment of the 
compliance time that provides an acceptable level of safety may be 
used if approved by the Manager, Engine Certification Office (ECO). 
Operators must submit their request through an appropriate FAA 
Principal Maintenance Inspector, who may add comments and then send 
it to the Manager, ECO.

    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this airworthiness directive, 
if any, may be obtained from the ECO.

Special Flight Permits

    (f) Special flight permits may be issued in accordance with 
Sec. Sec.  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 done.

    Note 3: The subject of this AD is addressed in Direction 
Generale de L'Aviation Civile (DGAC) Airworthiness Directives No. 
2002-126(A) and 2002-27(A), dated March 6, 2002 that replaced DGAC 
AD's 1999-391(A) and 1999-392(A), dated October 6, 1999.


    Issued in Burlington, Massachusetts, on September 12, 2002.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 02-23881 Filed 9-19-02; 8:45 am]
BILLING CODE 4910-13-P