83 FR 38951 - Airworthiness Directives; Safran Helicopter Engines, S.A., Turboshaft Engines
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 83, Issue 153 (August 8, 2018)
Federal Aviation Administration
Federal Register Volume 83, Issue 153 (August 8, 2018)
| Page Range | 38951-38953 | |
| FR Document | 2018-16652 |
[Federal Register Volume 83, Number 153 (Wednesday, August 8, 2018)] [Rules and Regulations] [Pages 38951-38953] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2018-16652] ======================================================================== Rules and Regulations Federal Register ________________________________________________________________________ This section of the FEDERAL REGISTER contains regulatory documents having general applicability and legal effect, most of which are keyed to and codified in the Code of Federal Regulations, which is published under 50 titles pursuant to 44 U.S.C. 1510. The Code of Federal Regulations is sold by the Superintendent of Documents. ======================================================================== Federal Register / Vol. 83, No. 153 / Wednesday, August 8, 2018 / Rules and Regulations [[Page 38951]] DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2009-0889; Product Identifier 2009-NE-35-AD; Amendment 39-19305; AD 2018-12-01] RIN 2120-AA64 Airworthiness Directives; Safran Helicopter Engines, S.A., Turboshaft Engines AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are superseding Airworthiness Directive (AD) 2012-03-11 for all Safran Helicopter Engines, S.A., Arriel 2B and 2B1 turboshaft engines. AD 2012-03-11 required checking the transmissible torque between the low-pressure (LP) pump impeller and the high-pressure (HP) pump shaft on the HP/LP pump and metering valve assembly, hereafter referred to as the hydro-mechanical metering unit (HMU). Since we issued AD 2012-03-11, the manufacturer determined that incorporating Modification TU 178 is a more effective method to reduce the risk of uncoupling between the LP fuel pump impeller and the HP fuel pump shaft than the prior Modification TU 147. This AD requires inspection and possible replacement of the HMU. This AD was prompted by three cases of uncoupling of the HMU LP fuel pump impeller and the HP fuel pump shaft since AD 2012-03-11 was issued. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective September 12, 2018. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of March 11, 2010 (75 FR 5689, February 4, 2010). The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of March 20, 2012 (77 FR 8092, February 14, 2012). ADDRESSES: For service information identified in this final rule, contact Safran Helicopter Engines, S.A., 40220 Tarnos, France; phone: (33) 05 59 74 40 00; fax: (33) 05 59 74 45 15. You may view this service information at the FAA, Engine and Propeller Standards Branch, 1200 District Avenue, Burlington, MA 01803. For information on the availability of this material at the FAA, call 781-238-7759. It is also available on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2009-0889. Examining the AD Docket You may examine the AD docket on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2009- 0889; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this final rule, the mandatory continuing airworthiness information, regulatory evaluation, any comments received, and other information. The address for Docket Operations (phone: 800-647-5527) is Document Operations, U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: John Frost, Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781- 238-7756; fax: 781-238-7199; email: [email protected]. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2012-03-11, Amendment 39-16953 (77 FR 8092, February 14, 2012), (``AD 2012-03-11''). AD 2012-03-11 applied to all Safran Helicopter Engines, S.A., Arriel 2B and 2B1 turboshaft engines. The NPRM published in the Federal Register on October 6, 2017 (82 FR 46727). The NPRM was prompted by instances of uncoupling between the LP fuel pump impeller and the HP fuel pump shaft. The NPRM proposed to require inspection and, depending on the results of the inspection, possible replacement of the HMU. The NPRM also proposed to require replacement of pre-Modification TU 178 HMUs with an HMU incorporating Modification TU 178 within 2,200 engine flight hours or 72 months, whichever occurs first, after the effective date of this AD. We are issuing this AD to address the unsafe condition on these products. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM and the FAA's response to the comment. Request To Clarify Reason for AD An individual commenter questioned how the new modification in this AD is better and different from the actions required by the previous AD 2012-03-11. AD 2012-03-11 required a check of the transmissible torque between the LP fuel pump impeller and the HP fuel pump shaft and replacement of the HMU if it does not pass the torque check. Since we issued AD 2012- 03-11, Safran Service Bulletin (SB) 292 73 2178, Version A, dated April 1, 2015 introduced Modification TU 178. This AD accepts Modification TU 178 as a more robust drive link between the LP fuel pump impeller and the HP fuel pump shaft that ensures the LP impeller pump is driven even if the link with the drive shaft loosens. This AD requires installation of a Modification TU 178 HMU for any HMU that fails the torque sensor check and as a mandatory terminating action for the inspections required by this AD, as well as purging the fleet of the pre- and post- TU 147 configuration parts. We did not change this AD. Clarification to Service Information for Torque Check We updated paragraphs (g)(1)(i) and (ii) of this AD to clarify that only paragraph 2.A, rather than paragraph 2, in Turbomeca Alert Mandatory SB (MSB) A292 73 2830, Version B, dated July 10, 2009, and Turbomeca Alert MSB A292 73 2836, Version A, dated August 17, 2010, is used to perform the torque check. [[Page 38952]] Conclusion We reviewed the relevant data, considered the comment received, and determined that air safety and the public interest require adopting this AD as proposed except for minor editorial changes. We have determined that these minor changes:Are consistent with the intent that was proposed in the NPRM for addressing the unsafe condition; and Do not add any additional burden upon the public than was already proposed in the NPRM. Related Service Information Under 1 CFR Part 51 We reviewed Turbomeca, S.A., Alert MSB A292 73 2830, Version B, dated July 10, 2009, and Alert MSB A292 73 2836, Version A, dated August 17, 2010. Turbomeca Alert MSB A292 73 2830, Version B, describes procedures for inspecting pre-Modification TU 147 HMUs. Turbomeca Alert MSB A292 73 2836, Version A, dated August 17, 2010, describes procedures for inspecting HMUs that have incorporated Modification TU 147. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. Other Related Service Information We reviewed Safran Helicopter Engines MSB 292 73 2178, Version B, dated March 23, 2017. Safran Helicopter Engines MSB 292 73 2178, Version B, describes HMU improvements that includes a reinforced drive link between the LP impeller and HP fuel pump shaft (Modification TU 178). Safran Helicopter Engines has also issued MSB A292 73 2830, Version C; and A292 73 2836, Version B, both dated April 5, 2017, which exempt HMUs incorporating Modification TU 178 from the inspections previously recommended by Safran Helicopter Engines. Costs of Compliance We estimate that this AD affects 417 engines installed on helicopters of U.S. registry. We estimate the following costs to comply with this AD: Estimated Costs ---------------------------------------------------------------------------------------------------------------- Cost per Cost on U.S. Action Labor cost Parts cost product operators ---------------------------------------------------------------------------------------------------------------- Remove and replace the HP/LP fuel pump 2 work-hours x $85 per $17,400 $17,570 $7,326,690 metering unit. hour = $170. ---------------------------------------------------------------------------------------------------------------- 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. This AD is issued in accordance with authority delegated by the Executive Director, Aircraft Certification Service, as authorized by FAA Order 8000.51C. In accordance with that order, issuance of ADs is normally a function of the Compliance and Airworthiness Division, but during this transition period, the Executive Director has delegated the authority to issue ADs applicable to engines, propellers, and associated appliances to the Manager, Engine and Propeller Standards Branch, Policy and Innovation Division. 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: (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. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA 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 Airworthiness Directive (AD) 2012-03-11, Amendment 39-16953 (77 FR 8092, February 14, 2012), and adding the following new AD: 2018-12-01 Safran Helicopter Engines (Type Certificate previously held by Turbomeca, S.A.): Amendment 39-19305; Docket No. FAA-2009- 0889; Product Identifier 2009-NE-35-AD. (a) Effective Date This AD is effective September 12, 2018. (b) Affected ADs This AD replaces AD 2012-03-11, Amendment 39-16953 (77 FR 8092, February 14, 2012). (c) Applicability This AD applies to Safran Helicopter Engines, S.A., Arriel 2B and 2B1 turboshaft engines, except those incorporating Modification TU 178. (d) Subject Joint Aircraft System Component (JASC) Code 7300, Engine Fuel and Control. (e) Unsafe Condition This AD was prompted by analysis that indicated the modification of an engine to incorporate Modification TU 178 provides a more effective method than Modification TU [[Page 38953]] 147 to reduce the risk of uncoupling between the low-pressure (LP) fuel pump impeller and the high-pressure (HP) fuel pump shaft of the HP/LP pump and hydro-mechanical metering unit (HMU). We are issuing this AD to prevent failure of the HMU. The unsafe condition, if not corrected, could result in failure of the engine, in-flight shutdown, and loss of the helicopter. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Required Actions (1) Check the transmissible torque between the LP fuel pump impeller and the HP fuel pump shaft as follows: (i) For pre-Modification TU 147 HMUs, check the torque before accumulating 500 engine flight hours (FHs) since March 11, 2010 or before the next flight after the effective date of this AD, whichever occurs later. Use Paragraph 2.A. of Turbomeca Alert Mandatory Service Bulletin (MSB) A292 73 2830, Version B, dated July 10, 2009 to do the check. (ii) For HMUs that incorporated Modification TU 147 on or before March 31, 2010, and those HMUs not listed in Figure 2 or 3 of Turbomeca Alert MSB A292 73 2836, Version A, dated August 17, 2010, check the torque before the next flight after the effective date of this AD. Use Paragraph 2.A. of Turbomeca Alert MSB A292 73 2836, Version A, dated August 17, 2010, to do the check. (2) If the HMU does not pass the torque check, replace the HMU with a post-Modification TU 178 HMU before the next flight after the effective date of this AD. (h) Mandatory Terminating Action Within 2,200 engine FHs or 72 months after the effective date of this AD, whichever occurs first, replace any pre-Modification TU 178 HMU with a post-Modification TU 178 configuration HMU. (i) Installation Prohibition After the effective date of this AD, do not install a pre- Modification TU 178 HMU on engines incorporating a post-Modification TU 178 HMU. (j) Alternative Methods of Compliance (AMOCs) (1) The Manager, ECO Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the certification office, send it to the attention of the person identified in paragraph (k)(1) of this AD. You may email your request to: [email protected]. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. (k) Related Information (1) For more information about this AD, contact John Frost, Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781-238-7756; fax: 781-238-7199; email: [email protected]. (2) Refer to European Aviation Safety Agency (EASA) AD 2017- 0102, dated June 13, 2017, for more information. You may examine the EASA AD on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2009-0889. (l) Material Incorporated by Reference (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. (3) The following service information was approved for IBR on March 11, 2010 (75 FR 5689, February 4, 2010). (i) Turbomeca Alert Mandatory Service Bulletin (MSB) No. A292 73 2830, Version B, dated July 10, 2009. (ii) Reserved. (4) The following service information was approved for IBR on March 20, 2012 (77 FR 8092, February 14, 2012). (i) Turbomeca Alert MSB No. A292 73 2836, Version A, dated August 17, 2010. (ii) Reserved. (5) For Safran Helicopter Engines, S.A, service information identified in this AD, contact Safran Helicopter Engines, S.A., 40220 Tarnos, France; phone: (33) 05 59 74 40 00; fax: (33) 05 59 74 45 15. (6) You may view this service information at FAA, Engine and Propeller Standards Branch, 1200 District Avenue, Burlington, MA 01803. For information on the availability of this material at the FAA, call 781-238-7759. (7) You may view this service information that is incorporated by reference 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. Issued in Burlington, Massachusetts, on July 31, 2018. Robert J. Ganley, Manager, Engine and Propeller Standards Branch, Aircraft Certification Service. [FR Doc. 2018-16652 Filed 8-7-18; 8:45 am] BILLING CODE 4910-13-P
![38951
Rules and Regulations Federal Register
Vol. 83, No. 153
Wednesday, August 8, 2018
This section of the FEDERAL REGISTER The Director of the Federal Register The NPRM proposed to require
contains regulatory documents having general approved the incorporation by reference inspection and, depending on the
applicability and legal effect, most of which of a certain publication listed in this AD results of the inspection, possible
are keyed to and codified in the Code of as of March 20, 2012 (77 FR 8092, replacement of the HMU. The NPRM
Federal Regulations, which is published under February 14, 2012). also proposed to require replacement of
50 titles pursuant to 44 U.S.C. 1510.
ADDRESSES: For service information pre-Modification TU 178 HMUs with an
The Code of Federal Regulations is sold by identified in this final rule, contact HMU incorporating Modification TU
the Superintendent of Documents. Safran Helicopter Engines, S.A., 40220 178 within 2,200 engine flight hours or
Tarnos, France; phone: (33) 05 59 74 40 72 months, whichever occurs first, after
00; fax: (33) 05 59 74 45 15. You may the effective date of this AD. We are
DEPARTMENT OF TRANSPORTATION view this service information at the issuing this AD to address the unsafe
FAA, Engine and Propeller Standards condition on these products.
Federal Aviation Administration Branch, 1200 District Avenue,
Comments
Burlington, MA 01803. For information
14 CFR Part 39 on the availability of this material at the We gave the public the opportunity to
[Docket No. FAA–2009–0889; Product FAA, call 781–238–7759. It is also participate in developing this AD. The
Identifier 2009–NE–35–AD; Amendment 39– available on the internet at http:// following presents the comments
19305; AD 2018–12–01] www.regulations.gov by searching for received on the NPRM and the FAA’s
RIN 2120–AA64 and locating Docket No. FAA–2009– response to the comment.
0889.
Airworthiness Directives; Safran Request To Clarify Reason for AD
Examining the AD Docket
Helicopter Engines, S.A., Turboshaft An individual commenter questioned
Engines You may examine the AD docket on
the internet at http:// how the new modification in this AD is
AGENCY: Federal Aviation www.regulations.gov by searching for better and different from the actions
Administration (FAA), DOT. and locating Docket No. FAA–2009– required by the previous AD 2012–03–
ACTION: Final rule. 0889; or in person at Docket Operations 11.
between 9 a.m. and 5 p.m., Monday AD 2012–03–11 required a check of
SUMMARY: We are superseding through Friday, except Federal holidays. the transmissible torque between the LP
Airworthiness Directive (AD) 2012–03– The AD docket contains this final rule, fuel pump impeller and the HP fuel
11 for all Safran Helicopter Engines, the mandatory continuing airworthiness pump shaft and replacement of the
S.A., Arriel 2B and 2B1 turboshaft information, regulatory evaluation, any HMU if it does not pass the torque
engines. AD 2012–03–11 required comments received, and other check. Since we issued AD 2012–03–11,
checking the transmissible torque information. The address for Docket Safran Service Bulletin (SB) 292 73
between the low-pressure (LP) pump Operations (phone: 800–647–5527) is 2178, Version A, dated April 1, 2015
impeller and the high-pressure (HP) Document Operations, U.S. Department introduced Modification TU 178. This
pump shaft on the HP/LP pump and of Transportation, Docket Operations, AD accepts Modification TU 178 as a
metering valve assembly, hereafter M–30, West Building Ground Floor, more robust drive link between the LP
referred to as the hydro-mechanical Room W12–140, 1200 New Jersey fuel pump impeller and the HP fuel
metering unit (HMU). Since we issued Avenue SE, Washington, DC 20590. pump shaft that ensures the LP impeller
AD 2012–03–11, the manufacturer FOR FURTHER INFORMATION CONTACT: John pump is driven even if the link with the
determined that incorporating Frost, Aerospace Engineer, ECO Branch, drive shaft loosens. This AD requires
Modification TU 178 is a more effective FAA, 1200 District Avenue, Burlington, installation of a Modification TU 178
method to reduce the risk of uncoupling MA 01803; phone: 781–238–7756; fax: HMU for any HMU that fails the torque
between the LP fuel pump impeller and 781–238–7199; email: john.frost@ sensor check and as a mandatory
the HP fuel pump shaft than the prior faa.gov. terminating action for the inspections
Modification TU 147. This AD requires required by this AD, as well as purging
SUPPLEMENTARY INFORMATION:
inspection and possible replacement of the fleet of the pre- and post-TU 147
the HMU. This AD was prompted by Discussion configuration parts. We did not change
three cases of uncoupling of the HMU We issued a notice of proposed this AD.
LP fuel pump impeller and the HP fuel rulemaking (NPRM) to amend 14 CFR
pump shaft since AD 2012–03–11 was Clarification to Service Information for
part 39 to supersede AD 2012–03–11, Torque Check
issued. We are issuing this AD to Amendment 39–16953 (77 FR 8092,
address the unsafe condition on these February 14, 2012), (‘‘AD 2012–03–11’’). We updated paragraphs (g)(1)(i) and
products. AD 2012–03–11 applied to all Safran (ii) of this AD to clarify that only
DATES: This AD is effective September Helicopter Engines, S.A., Arriel 2B and paragraph 2.A, rather than paragraph 2,
amozie on DSK3GDR082PROD with RULES
12, 2018. 2B1 turboshaft engines. The NPRM in Turbomeca Alert Mandatory SB
The Director of the Federal Register published in the Federal Register on (MSB) A292 73 2830, Version B, dated
approved the incorporation by reference October 6, 2017 (82 FR 46727). The July 10, 2009, and Turbomeca Alert
of a certain publication listed in this AD NPRM was prompted by instances of MSB A292 73 2836, Version A, dated
as of March 11, 2010 (75 FR 5689, uncoupling between the LP fuel pump August 17, 2010, is used to perform the
February 4, 2010). impeller and the HP fuel pump shaft. torque check.
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![38952 Federal Register / Vol. 83, No. 153 / Wednesday, August 8, 2018 / Rules and Regulations
Conclusion 2836, Version A, dated August 17, 2010. describes HMU improvements that
We reviewed the relevant data, Turbomeca Alert MSB A292 73 2830, includes a reinforced drive link between
considered the comment received, and Version B, describes procedures for the LP impeller and HP fuel pump shaft
determined that air safety and the inspecting pre-Modification TU 147 (Modification TU 178). Safran
public interest require adopting this AD HMUs. Turbomeca Alert MSB A292 73 Helicopter Engines has also issued MSB
as proposed except for minor editorial 2836, Version A, dated August 17, 2010, A292 73 2830, Version C; and A292 73
changes. We have determined that these describes procedures for inspecting 2836, Version B, both dated April 5,
minor changes: HMUs that have incorporated 2017, which exempt HMUs
• Are consistent with the intent that Modification TU 147. This service incorporating Modification TU 178 from
was proposed in the NPRM for information is reasonably available the inspections previously
addressing the unsafe condition; and because the interested parties have recommended by Safran Helicopter
• Do not add any additional burden access to it through their normal course Engines.
upon the public than was already of business or by the means identified
proposed in the NPRM. in the ADDRESSES section. Costs of Compliance
Related Service Information Under 1 Other Related Service Information We estimate that this AD affects 417
CFR Part 51 We reviewed Safran Helicopter engines installed on helicopters of U.S.
We reviewed Turbomeca, S.A., Alert Engines MSB 292 73 2178, Version B, registry.
MSB A292 73 2830, Version B, dated dated March 23, 2017. Safran Helicopter We estimate the following costs to
July 10, 2009, and Alert MSB A292 73 Engines MSB 292 73 2178, Version B, comply with this AD:
ESTIMATED COSTS
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
Remove and replace the HP/LP fuel pump 2 work-hours × $85 per hour = $170 ............. $17,400 $17,570 $7,326,690
metering unit.
Authority for This Rulemaking Regulatory Findings PART 39—AIRWORTHINESS
DIRECTIVES
Title 49 of the United States Code We have determined that this AD will
specifies the FAA’s authority to issue not have federalism implications under ■ 1. The authority citation for part 39
rules on aviation safety. Subtitle I, Executive Order 13132. This AD will continues to read as follows:
Section 106, describes the authority of not have a substantial direct effect on Authority: 49 U.S.C. 106(g), 40113, 44701.
the FAA Administrator. Subtitle VII, the States, on the relationship between
Aviation Programs, describes in more the national government and the States, § 39.13 [Amended]
detail the scope of the Agency’s or on the distribution of power and ■ 2. The FAA amends § 39.13 by
authority. responsibilities among the various removing Airworthiness Directive (AD)
We are issuing this rulemaking under levels of government. 2012–03–11, Amendment 39–16953 (77
the authority described in Subtitle VII, FR 8092, February 14, 2012), and adding
Part A, Subpart III, Section 44701, For the reasons discussed above, I
certify that this AD: the following new AD:
‘‘General requirements.’’ Under that
2018–12–01 Safran Helicopter Engines
section, Congress charges the FAA with (1) Is not a ‘‘significant regulatory
(Type Certificate previously held by
promoting safe flight of civil aircraft in action’’ under Executive Order 12866, Turbomeca, S.A.): Amendment 39–
air commerce by prescribing regulations (2) Is not a ‘‘significant rule’’ under 19305; Docket No. FAA–2009–0889;
for practices, methods, and procedures DOT Regulatory Policies and Procedures Product Identifier 2009–NE–35–AD.
the Administrator finds necessary for (44 FR 11034, February 26, 1979), (a) Effective Date
safety in air commerce. This regulation
is within the scope of that authority (3) Will not affect intrastate aviation This AD is effective September 12, 2018.
because it addresses an unsafe condition in Alaska, and (b) Affected ADs
that is likely to exist or develop on (4) Will not have a significant This AD replaces AD 2012–03–11,
products identified in this rulemaking economic impact, positive or negative, Amendment 39–16953 (77 FR 8092, February
action. on a substantial number of small entities 14, 2012).
This AD is issued in accordance with under the criteria of the Regulatory (c) Applicability
authority delegated by the Executive Flexibility Act. This AD applies to Safran Helicopter
Director, Aircraft Certification Service, Engines, S.A., Arriel 2B and 2B1 turboshaft
as authorized by FAA Order 8000.51C. List of Subjects in 14 CFR Part 39
engines, except those incorporating
In accordance with that order, issuance Air transportation, Aircraft, Aviation Modification TU 178.
of ADs is normally a function of the safety, Incorporation by reference, (d) Subject
Compliance and Airworthiness
Safety. Joint Aircraft System Component (JASC)
Division, but during this transition
amozie on DSK3GDR082PROD with RULES
period, the Executive Director has Adoption of the Amendment Code 7300, Engine Fuel and Control.
delegated the authority to issue ADs (e) Unsafe Condition
applicable to engines, propellers, and Accordingly, under the authority
This AD was prompted by analysis that
associated appliances to the Manager, delegated to me by the Administrator, indicated the modification of an engine to
Engine and Propeller Standards Branch, the FAA amends 14 CFR part 39 as incorporate Modification TU 178 provides a
Policy and Innovation Division. follows: more effective method than Modification TU
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![Federal Register / Vol. 83, No. 153 / Wednesday, August 8, 2018 / Rules and Regulations 38953
147 to reduce the risk of uncoupling between (k) Related Information DEPARTMENT OF TRANSPORTATION
the low-pressure (LP) fuel pump impeller (1) For more information about this AD,
and the high-pressure (HP) fuel pump shaft Federal Aviation Administration
contact John Frost, Aerospace Engineer, ECO
of the HP/LP pump and hydro-mechanical
Branch, FAA, 1200 District Avenue,
metering unit (HMU). We are issuing this AD 14 CFR Part 39
to prevent failure of the HMU. The unsafe Burlington, MA 01803; phone: 781–238–
condition, if not corrected, could result in 7756; fax: 781–238–7199; email: john.frost@ [Docket No. FAA–2018–0640; Product
failure of the engine, in-flight shutdown, and faa.gov. Identifier 2018–NM–075–AD; Amendment
loss of the helicopter. (2) Refer to European Aviation Safety 39–19343; AD 2018–16–03]
Agency (EASA) AD 2017–0102, dated June
(f) Compliance RIN 2120–AA64
13, 2017, for more information. You may
Comply with this AD within the examine the EASA AD on the internet at
compliance times specified, unless already
Airworthiness Directives; Airbus SAS
http://www.regulations.gov by searching for
done. Airplanes
and locating Docket No. FAA–2009–0889.
(g) Required Actions AGENCY: Federal Aviation
(l) Material Incorporated by Reference
(1) Check the transmissible torque between
Administration (FAA), DOT.
(1) The Director of the Federal Register
the LP fuel pump impeller and the HP fuel ACTION: Final rule; request for
approved the incorporation by reference
pump shaft as follows: comments.
(IBR) of the service information listed in this
(i) For pre-Modification TU 147 HMUs,
paragraph under 5 U.S.C. 552(a) and 1 CFR SUMMARY: We are adopting a new
check the torque before accumulating 500
engine flight hours (FHs) since March 11, part 51. airworthiness directive (AD) for all
2010 or before the next flight after the (2) You must use this service information Airbus SAS Model A319–133 airplanes
effective date of this AD, whichever occurs as applicable to do the actions required by and Model A321–232 airplanes. This
later. Use Paragraph 2.A. of Turbomeca Alert this AD, unless the AD specifies otherwise. AD requires modification and re-
Mandatory Service Bulletin (MSB) A292 73 (3) The following service information was identification, or replacement, of certain
2830, Version B, dated July 10, 2009 to do approved for IBR on March 11, 2010 (75 FR engine fan cowl doors (FCDs) and
the check. 5689, February 4, 2010). installation of a placard in the flight
(ii) For HMUs that incorporated (i) Turbomeca Alert Mandatory Service deck. This AD was prompted by reports
Modification TU 147 on or before March 31, Bulletin (MSB) No. A292 73 2830, Version B,
2010, and those HMUs not listed in Figure of in-service engine FCD losses, and the
dated July 10, 2009.
2 or 3 of Turbomeca Alert MSB A292 73 development of a new FCD front latch
(ii) Reserved.
2836, Version A, dated August 17, 2010, and keeper assembly that addresses this
(4) The following service information was
check the torque before the next flight after unsafe condition. We are issuing this
approved for IBR on March 20, 2012 (77 FR
the effective date of this AD. Use Paragraph AD to address the unsafe condition on
8092, February 14, 2012).
2.A. of Turbomeca Alert MSB A292 73 2836, these products.
(i) Turbomeca Alert MSB No. A292 73
Version A, dated August 17, 2010, to do the DATES: This AD becomes effective
check. 2836, Version A, dated August 17, 2010.
(ii) Reserved. August 23, 2018.
(2) If the HMU does not pass the torque
(5) For Safran Helicopter Engines, S.A, The Director of the Federal Register
check, replace the HMU with a post-
Modification TU 178 HMU before the next service information identified in this AD, approved the incorporation by reference
flight after the effective date of this AD. contact Safran Helicopter Engines, S.A., of a certain publication listed in this AD
40220 Tarnos, France; phone: (33) 05 59 74 as of August 3, 2017 (82 FR 29371, June
(h) Mandatory Terminating Action 29, 2017).
40 00; fax: (33) 05 59 74 45 15.
Within 2,200 engine FHs or 72 months (6) You may view this service information We must receive comments on this
after the effective date of this AD, whichever at FAA, Engine and Propeller Standards AD by September 24, 2018.
occurs first, replace any pre-Modification TU Branch, 1200 District Avenue, Burlington, ADDRESSES: You may send comments,
178 HMU with a post-Modification TU 178 MA 01803. For information on the using the procedures found in 14 CFR
configuration HMU.
availability of this material at the FAA, call 11.43 and 11.45, by any of the following
(i) Installation Prohibition 781–238–7759. methods:
After the effective date of this AD, do not (7) You may view this service information • Federal eRulemaking Portal: Go to
install a pre-Modification TU 178 HMU on that is incorporated by reference at the http://www.regulations.gov. Follow the
engines incorporating a post-Modification TU National Archives and Records instructions for submitting comments.
178 HMU. Administration (NARA). For information on • Fax: 202–493–2251.
(j) Alternative Methods of Compliance
the availability of this material at NARA, call • Mail: U.S. Department of
202–741–6030, or go to: http:// Transportation, Docket Operations, M–
(AMOCs)
www.archives.gov/federal-register/cfr/ibr- 30, West Building Ground Floor, Room
(1) The Manager, ECO Branch, FAA, has locations.html.
the authority to approve AMOCs for this AD, W12–140, 1200 New Jersey Avenue SE,
if requested using the procedures found in 14 Issued in Burlington, Massachusetts, on Washington, DC 20590.
CFR 39.19. In accordance with 14 CFR 39.19, July 31, 2018. • Hand Delivery: U.S. Department of
send your request to your principal inspector Robert J. Ganley, Transportation, Docket Operations, M–
or local Flight Standards District Office, as 30, West Building Ground Floor, Room
Manager, Engine and Propeller Standards
appropriate. If sending information directly W12–140, 1200 New Jersey Avenue SE,
Branch, Aircraft Certification Service.
to the manager of the certification office, Washington, DC, between 9 a.m. and 5
send it to the attention of the person [FR Doc. 2018–16652 Filed 8–7–18; 8:45 am]
p.m., Monday through Friday, except
identified in paragraph (k)(1) of this AD. You BILLING CODE 4910–13–P
Federal holidays.
amozie on DSK3GDR082PROD with RULES
may email your request to: ANE-AD-AMOC@
faa.gov.
For service information identified in
(2) Before using any approved AMOC, this final rule, contact Airbus SAS,
notify your appropriate principal inspector, Airworthiness Office—EIAS, Rond-
or lacking a principal inspector, the manager Point Emile Dewoitine No: 2, 31700
of the local flight standards district office/ Blagnac Cedex, France; telephone +33 5
certificate holding district office. 61 93 36 96; fax +33 5 61 93 44 51; email
VerDate Sep<11>2014 16:30 Aug 07, 2018 Jkt 244001 PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 E:\FR\FM\08AUR1.SGM 08AUR1](https://thefederalregister.org/doc/83_FR_39104/page/3.svg)
Document Created: 2018-08-08 02:06:16
Document Modified: 2018-08-08 02:06:16
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Rules and Regulations | |
| Action | Final rule. | |
| Dates | This AD is effective September 12, 2018. | |
| Contact | John Frost, Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781- 238-7756; fax: 781-238-7199; email: [email protected] | |
| FR Citation | 83 FR 38951 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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