Daily Rules, Proposed Rules, and Notices of the Federal Government
The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of January 7, 2013.
You may examine the AD docket on the Internet at
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2003-12-14, Amendment 39-13199 (68 FR 36900, June 20, 2003). That AD applies to the specified products. The NPRM published in the
We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the proposal and the FAA's response to each comment.
Charles E. Greenberg requested that the FAA consider modifying the AD to accommodate operators of helicopters with barrier filter installations for the engine intakes. If operator records can show that specific serial number engines have always operated with filtered air, the requirement for cleaning the gas generator hollow shaft should be superseded by a requirement to maintain records of operation with barrier filter protection. The commenter stated that no dirt can be ingested by an engine downstream of the filter, as long as the barrier filter has never gone into bypass mode.
We disagree. The FAA cannot anticipate all of the available barrier filter designs installed on helicopter models. Each barrier filter design and helicopter combination would require its own assessment of the filter's use and effectiveness. We did not change the AD.
However, the substantiated continuous use of a barrier filter may be proposed as an alternative method of compliance (AMOC) to this AD, using the standard AMOC request procedure.
We reviewed the relevant data, considered the comment received, and determined that air safety and the public interest require adopting the AD as proposed.
We estimate that this AD will affect about 1,421 engines installed on helicopters of U.S. registry. We also estimate that it will take about 24 work-hours per engine to inspect and clean the gas generator module. The average labor rate is $85 per work-hour. A replacement gas generator rear bearing would cost about $4,128 per engine and take about 8 work-hours to replace. Based on these figures, we estimate the cost of the AD on U.S. operators to be $2,898,840.
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.
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:
(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),
(3) Will not affect intrastate aviation in Alaska, and
(4) 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.
Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.
Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows:
49 U.S.C. 106(g), 40113, 44701.
This airworthiness directive (AD) is effective January 7, 2013.
This AD supersedes AD 2003-12-14, Amendment 39-13199 (68 FR 36900, June 20, 2003).
This AD applies to all Turbomeca S.A. Arriel 1A, 1A1, 1A2, 1B, 1C, 1C1, 1C2, 1D, 1D1, 1E2, 1K1, 1S, and 1S1 turboshaft engines that have not incorporated Turbomeca S.A. Modification TU360.
This AD was prompted by in-service experience showing that dust inside the gas generator hollow shaft may be found when the axial compressor wheel has less erosion than initially assessed. We are issuing this AD to prevent an unbalance of the gas generator rotating assembly, which may lead to deterioration of the gas generator rear bearing and uncommanded engine shutdown.
Comply with this AD within the compliance times specified, unless already done.
(1) Within 50 engine hours after the effective date of this AD, determine the engine history and perform the maintenance actions at the specified schedules. Use paragraphs 1.A. and 2.A. through 2.C. of Turbomeca S.A. Alert Mandatory Service Bulletin (MSB) No. A292 72 0230, Version C, dated February 29, 2012 to perform the maintenance actions and to establish the cleaning schedule.
(2) If during any of the cleanings, the dust weight collected inside the gas generator hollow shaft is more than 8 grams, replace the gas generator rear bearing before further flight.
(3) After the effective date of this AD, if there are any changes in accordance with paragraph 1.A.(1)(a)1.3 of Turbomeca S.A. Alert MSB No. A292 72 0230, Version C, dated February 29, 2012, within 50 engine hours time-in-service after such a change, accomplish the actions as specified in paragraphs (e)(1) and (e)(2) of this AD.
(4) After the effective date of this AD, do not install any gas generator (module M03) on an engine unless it is in compliance with this AD.
(5) After the effective date of this AD, do not install any gas generator rear bearing that has operated on an engine with a hollow shaft that has been found to have a dust weight more than 8 grams.
As optional terminating action to the repetitive actions in this AD, modify the engine by incorporating Turbomeca S.A. Modification TU360.
The Manager, Engine Certification Office, may approve AMOCs for this AD. Use the procedures found in 14 CFR 39.19 to make your request.
(1) For more information about this AD, contact Rose Len, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; phone: 781-238-7772; fax: 781-238-7199; email:
(2) Refer to European Aviation Safety Agency AD 2012-0071, dated April 26, 2012, and Turbomeca S.A. Alert MSB No. A292 72 0230, Version C, dated February 29, 2012, for related information.
(1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise.
(i) Turbomeca S.A. Alert Mandatory Service Bulletin No. A292 72 0230, Version C, dated February 29, 2012.
(3) For Turbomeca S.A. service information identified in this AD, contact Turbomeca S.A., 40220 Tarnos, France; phone: 33 05 59 74 40 00; telex: 570 042; fax: 33 05 59 74 45 15.
(4) You may view this service information at FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA. For information on the availability of this material at the FAA, call 781-238-7125.
(5) You may view this service information 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: