[Federal Register: January 31, 2003 (Volume 68, Number 21)]
[Rules and Regulations]
[Page 4904-4905]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr31ja03-6]
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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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