[Federal Register: November 16, 2006 (Volume 71, Number 221)]
[Rules and Regulations]
[Page 66664-66665]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr16no06-6]
[[Page 66664]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-25970; Directorate Identifier 99-NE-12-AD;
Amendment 39-14829; AD 2006-23-17]
RIN 2120-AA64
Airworthiness Directives; Turbomeca Turmo IV A and IV C Series
Turboshaft Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is superseding an existing airworthiness directive
(AD) for Turbomeca Turmo IV A and IV C series turboshaft engines. That
AD currently requires borescope and eddy current inspections or
ultrasonic inspections of centrifugal compressor intake wheel blades
for cracks and evidence of corrosion pitting, and replacement with
serviceable parts. This AD requires the same actions, but would require
borescope inspections at more frequent intervals for certain engines.
This AD results from Turbomeca's review of the engines' service
experience that determined more frequent borescope inspections are
required on engines not modified to the TU 191, TU 197, or TU 224
standard. We are issuing this AD to prevent centrifugal compressor
intake wheel blade cracks, which can result in engine in-flight power
loss, engine shutdown, or forced landing.
DATES: This AD becomes effective December 21, 2006. The Director of the
Federal Register approved the incorporation by reference of certain
publications listed in the regulations as of December 21, 2006.
ADDRESSES: You can get the service information identified in this AD
from Turbomeca, 40220 Tarnos, France; telephone 33 05 59 74 40 00, fax
33 05 59 74 45 15.
You may examine the AD docket on the Internet at http://dms.dot.gov
or in Room PL-401 on the plaza level of the Nassif Building, 400
Seventh Street, SW., Washington, DC.
FOR FURTHER INFORMATION CONTACT: Christopher Spinney, Aerospace
Engineer, Engine Certification Office, FAA, Engine and Propeller
Directorate, 12 New England Executive Park, Burlington, MA 01803;
telephone (781) 238-7175; fax (781) 238-7199.
SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR Part 39
with a proposed AD. The proposed AD applies to Turbomeca Turmo IV A and
IV C series turboshaft engines. We published the proposed AD in the
Federal Register on February 9, 2006 (71 FR 6691). That action proposed
to require initial and repetitive borescope and eddy current
inspections or ultrasonic inspections of centrifugal compressor intake
wheel blades for cracks and evidence of corrosion pitting, and, if
found cracked or if there is evidence of corrosion pitting, replacement
with serviceable parts. Additionally, it proposed to require borescope
inspections at more frequent intervals for certain engines.
Examining the AD Docket
You may examine the docket that contains the AD, any comments
received, and any final disposition in person at the Docket Management
Facility Docket Office between 9 a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The Docket Office (telephone (800)
647-5227) is located on the plaza level of the Department of
Transportation Nassif Building at the street address stated in
ADDRESSES. Comments will be available in the AD docket shortly after
the DMS receives them.
Comments
We provided the public the opportunity to participate in the
development of this AD. We received no comments on the proposal or on
the determination of the cost to the public.
Docket Number Change
We are transferring the docket for this AD to the Docket Management
System as part of our on-going docket management consolidation efforts.
The new Docket No. is FAA-2006-25970. The old Docket No. became the
Directorate Identifier, which is 99-NE-12-AD. This final rule might get
logged into the DMS docket, ahead of the proposed AD and comments
received, as we are in the process of sending those items to the DMS.
Conclusion
We have carefully reviewed the available data and determined that
air safety and the public interest require adopting the AD as proposed.
Costs of Compliance
We estimate that this AD will affect 36 Turbomeca Turmo IV A and IV
C series turboshaft engines installed on helicopters of U.S. registry.
We also estimate that it will take about 41 work-hours per engine to
perform the inspections, including disassembling and assembling
engines, and that the average labor rate is $65 per work-hour. A
replacement centrifugal compressor assembly costs about $21,651. Based
on these figures, the cost per inspection and replacement is estimated
to be $24,316. Based on these figures, we estimate the total cost of
the AD to U.S. operators to be $875,390.
Special Flight Permits Paragraph Removed
Paragraph (e) of the current AD, AD 2003-11-09, contains a
paragraph pertaining to special flight permits. Even though this AD
does not contain a similar paragraph, we have made no changes with
regard to the use of special flight permits to operate the helicopter
to a repair facility to do the work required by this AD. In July 2002,
we published a new Part 39 that contains a general authority regarding
special flight permits and airworthiness directives; see Docket No.
FAA-2004-8460, Amendment 39-9474 (69 FR 47998, July 22, 2002). Thus,
when we now supersede ADs we will not include a specific paragraph on
special flight permits unless we want to limit the use of that general
authority granted in section 39.23.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We have determined that this AD will not have federalism
implications under Executive Order 13132. This AD will 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.
For the reasons discussed above, I certify that this AD:
[[Page 66665]]
(1) Is not a ``significant regulatory action'' under Executive
Order 12866;
(2) Is not a ``significant rule'' under 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.
We prepared a summary of the costs to comply with this AD and
placed it in the AD Docket. You may get a copy of this summary at the
address listed under ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the Federal Aviation Administration amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
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]
0
2. The FAA amends Sec. 39.13 by removing Amendment 39-13168 (68 FR
31970, May 29, 2003) and by adding a new airworthiness directive,
Amendment 39-14829, to read as follows:
2006-23-17 Turbomeca: Amendment 39-14829. Docket No. FAA-2006-25970;
Directorate Identifier 99-NE-12-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective December
21, 2006.
Affected ADs
(b) This AD supersedes AD 2003-11-09, Amendment 39-13168.
Applicability
(c) This AD applies to Turbomeca Turmo IV A and IV C series
turboshaft engines. These engines are installed on but not limited
to Aerospatiale SA 330--PUMA helicopters.
Unsafe Condition
(d) This AD results from Turbomeca's review of the engines'
service experience that determined more frequent borescope
inspections are required on engines not modified to the TU 191, TU
197, or TU 224 standard. The actions specified in this AD are
intended to prevent centrifugal compressor intake wheel blade
cracks, which can result in engine in-flight power loss, engine
shutdown, or forced landing.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified unless the
actions have already been done.
Engine Modification Before Further Flight
(f) For engines modified to the TU 197 standard, but not to the
TU 191 or TU 224 standard, before further flight, remove the TU 197
standard and install the TU 224 standard.
Initial Inspections
(g) For all engines, borescope-inspect, and either eddy current-
inspect (ECI) or ultrasonic-inspect (UI) the centrifugal compressor
intake wheel blades using paragraphs 2.B.(1)(a) through 2.B.(1)(g)
of Turbomeca Mandatory Service Bulletin A249 72 0100, Update No. 5,
dated February 25, 2005, and the criteria in the following Table 1:
Table 1.--Inspection Criteria
----------------------------------------------------------------------------------------------------------------
Then borescope-inspect Were traces of Then confirm corrosion
If engine modification level is: centrifugal compressor corrosion found at by performing ECI or UI
intake wheel blades: borescope-inspection? within:
----------------------------------------------------------------------------------------------------------------
(1) Pre TU 191 and Pre TU 224........ Within 200 flight hours- (i) Yes................ Six months-or 50 flight
since-last inspection. hours-since-borescope
inspection, whichever
occurs first.
(ii) No................ Two hundred flight
hours-since-borescope
inspection.
(2) Post TU 191 or Post TU 224....... Within 1,000 flight (i) Yes................ Six months-or 50 flight
hours-since-last hours-since-borescope
inspection. inspection, whichever
occurs first.
(ii) No................ One thousand flight
hours-since-borescope
inspection.
----------------------------------------------------------------------------------------------------------------
(h) Thereafter, perform repetitive inspections using the
criteria in Table 1 of this AD.
(i) Remove centrifugal compressor intake wheel blades confirmed
cracked or pitted.
Alternative Methods of Compliance
(j) The Manager, Engine Certification Office, has the authority
to approve alternative methods of compliance for this AD if
requested using the procedures found in 14 CFR 39.19.
Material Incorporated by Reference
(k) You must use Turbomeca Mandatory Service Bulletin A249 72
0100, Update No. 5, dated February 25, 2005, to perform the actions
required by this AD. The Director of the Federal Register approved
the incorporation by reference of this service bulletin in
accordance with 5 U.S.C. 552(a) and 1 CFR part 51. You can get a
copy of this service information from Turbomeca, 40220 Tarnos,
France; telephone 33 05 59 74 40 00, fax 33 05 59 74 45 15. You may
review copies at the FAA, New England Region, Office of the Regional
Counsel, 12 New England Executive Park, Burlington, MA; or at the
National Archives and Records Administration (NARA). For information
on the availability of this material at NARA, call 202-741-6030, or
go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html
.
Related Information
(l) Direction Generale de L'Aviation Civile airworthiness
directive F-2005-037, dated March 2, 2005, also addresses the
subject of this AD.
Issued in Burlington, Massachusetts, on November 7, 2006.
Peter A. White,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. E6-19274 Filed 11-15-06; 8:45 am]
BILLING CODE 4910-13-P