[Federal Register Volume 68, Number 21 (Friday, January 31, 2003)]
[Rules and Regulations]
[Pages 4904-4905]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-2093]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NE-06-AD; Amendment 39-13036; AD 2003-03-12]
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: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), that 
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. This amendment requires the insertion of a 
sleeve in the attachment boss of the compressor bleed valve, and 
bonding the sleeve in the bleed-valve mounting pad. This amendment is 
prompted by several cases of contained centrifugal compressor impeller 
blade ruptures that occurred in service. The actions specified by this 
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: Effective March 7, 2003. The incorporation by reference of 
certain publications listed in the regulations is approved by the 
Director of the Federal Register as of March 7, 2003.

ADDRESSES: The service information referenced in this AD 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 Federal Aviation Administration (FAA), 
New England Region, Office of the Regional Counsel, 12 New England 
Executive Park, Burlington, MA; or at the Office of the Federal 
Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Antonio Cancelliere, Aerospace 
Engineer, Engine Certification Office, FAA, Engine and Propeller 
Directorate, 12 New England Executive Park, Burlington, MA 01803-5299; 
telephone (781) 238-7751; fax (781) 238-7199.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) to include an AD that is 
applicable to Turbomeca S.A. Arriel 1 D, 1 D1, 1 S, 1 S1, and -2B 
series turboshaft engines was published in the Federal Register on 
September 6, 2001 (66 FR 46562). That proposal was revised by a 
supplemental notice of proposed rulemaking (SNPRM) to amend part 39 of 
the Federal Aviation Regulations (14 CFR part 39) to include an AD that 
expanded the applicability 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. That SNPRM was published in the 
Federal Register on September 20, 2002 (67 FR 59217). That action 
proposed to require the insertion of a sleeve in the attachment boss of 
the compressor bleed valve, and bonding the sleeve in the bleed-valve 
mounting pad, in accordance with Turbomeca S.A. Mandatory Service 
Bulletin (MSB) No. 292 72 2054, dated September 20, 1999; MSB No. 292 
72 0261, dated September 20, 1999; MSB No. 292 72 2070, Update No. 1, 
dated October 5, 2001; and MSB No. 292 72 0275, Update No. 1, dated 
October 2, 2001. Since the publication of the SNPRM, MSB No. 292 72 
0275 has been reissued as Update No. 2, dated April 15, 2002. This MSB 
expands the engine model applicability of this AD by referencing MSB 
No. 292 72 0261, dated September 20, 1999, and Service Bulletin (SB) 
No. 292 72 0262, dated September 28, 1999. Accordingly, a new paragraph 
(b) has been added to reflect the updated MSB.

Comments

    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. The FAA 
has determined that air safety and the public interest require the 
adoption of the rule as proposed.

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 will be affected by this AD, that it will take approximately 
1.0 work hour per engine to perform the required actions, and that the 
average labor rate is $60 per work hour. Required parts will cost 
approximately $430 per engine. Based on these figures, the total cost 
of the AD to U.S. operators is estimated to be $233,240.

Regulatory Analysis

    This final 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 final rule.
    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 the 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 
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, Incorporation by 
reference, 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. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

    2. Section 39.13 is amended by adding a new airworthiness directive 
to read as follows:

2003-03-12 Turbomeca S.A.: Amendment 39-13036. Docket No. 2001-NE-
06-AD.

    Applicability: This airworthiness directive (AD) is applicable 
to Turbomeca S.A. Arriel

[[Page 4905]]

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 (f) 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) No. 
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 No. 292 72 0275, 
Update No. 2, dated April 15, 2002.
    (b) For Arriel 1 A2, 1 C, 1 C1, 1 C2, 1 E2, 1K, 1 K1 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 service bulletin (SB) No. 292 72 
0262, dated September 28, 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 No. 292 72 0275, 
Update No. 2, dated April 15, 2002.

Modification TU 300 Incorporated

    (c) 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 No. 292 72 0275, Update No. 2, dated April 15, 
2002.

Modification TU 54 Not Incorporated

    (d) 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 No. 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 No. 292 72 2070, 
Update No. 1, dated October 5, 2001.

Modification TU 54 Incorporated

    (e) 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 No. 292 72 2070, 
Update No. 1, dated October 5, 2001.

Alternative Methods of Compliance

    (f) 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

    (g) 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 aircraft to a location where 
the requirements of this AD can be done.

Documents That Have Been Incorporated by Reference

    (h) The actions must be done in accordance with the following 
Turbomeca S.A. Mandatory Service Bulletins (MSB's) and Service 
Bulletin (SB):

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            Document No.                      Pages                 Revision                     Date
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MSB No. 292 72 2054................  All...................  Original..............  Sept. 20, 1999.
    Total Pages: 6
MSB No. 292 72 0261................  All...................  Original..............  Sept. 20, 1999.
    Total Pages: 6
SB No. 292 72 0262.................  All...................  Original..............  Sept. 28, 1999.
    Total Pages: 6
MSB No. 292 72 2070................  All...................  1.....................  Oct. 5, 2001.
    Total Pages: 9
MSB No. 292 72 0275................  All...................  2.....................  April 15, 2002.
    Total Pages: 9
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    This incorporation by reference was approved by the Director of 
the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR 
part 51. Copies 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. 
Copies may be inspected at the FAA, New England Region, Office of 
the Regional Counsel, 12 New England Executive Park, Burlington, MA; 
or at the Office of the Federal Register, 800 North Capitol Street, 
NW., suite 700, Washington, DC.

    Note 3: The subject of this AD is addressed in Direction 
Generale de L'Aviation Civile (DGAC) Airworthiness Directives No. 
2002-126(A) and 2002-127(A), dated March 6, 2002 that replaced DGAC 
AD's 1999-391(A) and 1999-392(A), dated October 6, 1999.

Effective Date

    (i) This amendment becomes effective on March 7, 2003.

    Issued in Burlington, Massachusetts, on January 22, 2003.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 03-2093 Filed 1-30-03; 8:45 am]
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