82 FR 24035 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 82, Issue 100 (May 25, 2017)
Federal Aviation Administration
Federal Register Volume 82, Issue 100 (May 25, 2017)
| Page Range | 24035-24039 | |
| FR Document | 2017-10266 |
[Federal Register Volume 82, Number 100 (Thursday, May 25, 2017)] [Rules and Regulations] [Pages 24035-24039] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2017-10266] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-8428; Directorate Identifier 2014-NM-032-AD; Amendment 39-18898; AD 2017-10-24] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are superseding Airworthiness Directive (AD) 2011-17- [[Page 24036]] 09 for all Airbus Model A330-200, -200 Freighter, and -300 series airplanes; and AD 2012-25-12 for all Airbus Model A330-200 and -300 series airplanes. AD 2011-17-09 required revisions to certain operator maintenance documents to include new inspections. AD 2012-25-12 required replacing certain main landing gear (MLG) bogie beams before reaching new reduced life limits. This new AD requires revising the maintenance or inspection program, as applicable, to incorporate new, more restrictive, or revised instructions and/or airworthiness limitation requirements. This AD was prompted by revisions to certain airworthiness limitation item (ALI) documents, which specify more restrictive instructions and/or airworthiness limitations. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective June 29, 2017. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of June 29, 2017. The Director of the Federal Register approved the incorporation by reference of a certain other publication listed in this AD as of January 30, 2013 (77 FR 75825, December 26, 2012). The Director of the Federal Register approved the incorporation by reference of a certain other publication listed in this AD as of September 30, 2011 (76 FR 53305, August 26, 2011). ADDRESSES: For Airbus service information identified in this final rule, contact Airbus SAS--Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email [email protected]; Internet http://www.airbus.com. For Messier-Bugatti-Dowty service information identified in this final rule, contact Messier-Bugatti USA, One Carbon Way, Walton, KY 41094; telephone 859-525-8583; fax 859-485 8827; email [email protected]. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425- 227-1221. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015- 8428. 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-2015- 8428; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (telephone 800- 647-5527) is Docket Management Facility, 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: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1138; fax 425-227-1149. SUPPLEMENTARY INFORMATION: Discussion We issued a supplemental notice of proposed rulemaking (SNPRM) to amend 14 CFR part 39 to supersede AD 2011-17-09, Amendment 39-16773 (76 FR 53305, August 26, 2011) (``AD 2011-17-09''); and AD 2012-25-12, Amendment 39-17293 (77 FR 75825, December 26, 2012) (``AD 2012-25- 12''). AD 2011-17-09 applied to all Airbus Model A330-200, -200 Freighter, and -300 series airplanes. AD 2012-25-12 applied to all Airbus Model A330-200 and -300 series airplanes. The SNPRM published in the Federal Register on December 16, 2016 (81 FR 91062). We preceded the SNPRM with a notice of proposed rulemaking (NPRM) that published in the Federal Register on January 13, 2016 (81 FR 1570). The NPRM was prompted by a determination that more restrictive instructions and/or airworthiness limitations should be incorporated into the maintenance or inspection program, as applicable. The NPRM proposed to require revising the maintenance or inspection program, as applicable, to incorporate new or revised airworthiness limitation requirements. The SNPRM proposed to require revising the maintenance or inspection program, as applicable, to incorporate more restrictive instructions and/or airworthiness limitations that the manufacturer has recently issued. We are issuing this AD to detect and correct fatigue cracking, accidental damage, or corrosion in principal structural elements, and possible failure of certain life limited parts, which could result in reduced structural integrity of the airplane. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive, 2014-0009, dated January 8, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for all Airbus Model A330-200, -200 Freighter, and -300 series airplanes; and Model A340- 200, -300, -500, and -600 series airplanes. The MCAI states: The airworthiness limitations for Airbus aeroplanes are currently published in Airworthiness Limitations Section (ALS) documents. The instructions and airworthiness limitations applicable to the Safe Life Airworthiness Limitation Items (SL ALI) are given in Airbus A330 ALS Part 1 and A340 ALS Part 1, which are approved by EASA. The revision 07 of Airbus A330 and A340 ALS Part 1 introduces more restrictive instructions and/or airworthiness limitations. Failure to comply with this revision could result in an unsafe condition. For the reason described above, this [EASA] AD retains the requirements of EASA AD 2012-0179, which is superseded, and requires accomplishment of the actions specified in Airbus A330 or A340 ALS Part 1 revision 07. In addition, this [EASA] AD also supersedes EASA AD 2011-0122-E and EASA AD 2011-0212, whose requirements have been transferred into Airbus A330 and A340 ALS Part 1 revision 07. The unsafe condition is fatigue cracking, accidental damage, or corrosion in certain principal structural elements, and possible failure of certain life limited parts, which could result in reduced structural integrity of the airplane. You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-8428. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the SNPRM or on the determination of the cost to the public. Conclusion We reviewed the available data 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 SNPRM for correcting the unsafe condition; and Do not add any additional burden upon the public than was already proposed in the SNPRM. [[Page 24037]] Related Service Information Under 1 CFR Part 51 Airbus has issued Airbus A330 ALS Part 1, SL-ALI, Revision 08, dated April 11, 2016. Messier-Bugatti-Dowty has issued Service Letter A33-34 A20, Revision 7, including Appendixes A through F, dated July 20, 2012. This service information describes SL-ALI for the landing gear. This service information is distinct since it was issued by two different manufacturers for different purposes. 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. Costs of Compliance We estimate that this AD affects 82 airplanes of U.S. registry. The actions that are required by AD 2011-17-09, and retained in this AD, take about 1 work-hour per product, at an average labor rate of $85 per work-hour. Based on these figures, the estimated cost of the actions that are required by AD 2011-17-09 is $85 per product. The actions that are required by AD 2012-25-12, and retained in this AD, take about 16 work-hours, at an average labor rate of $85 per work-hour, with required parts cost of about $255,000 per MLG bogie beam. Based on these figures, the estimated cost of the actions that are required by AD 2012-25-12 is up to $256,360 per MLG bogie beam. We also estimate that it would take about 1 work-hour per product to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this AD on U.S. operators to be $6,970, or $85 per product. 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 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 the 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) 2011-17-09, Amendment 39-16773 (76 FR 53305, August 26, 2011); and AD 2012-25-12, Amendment 39-17293 (77 FR 75825, December 26, 2012); and adding the following new AD: 2017-10-24 Airbus: Amendment 39-18898; Docket No. FAA-2015-8428; Directorate Identifier 2014-NM-032-AD. (a) Effective Date This AD is effective June 29, 2017. (b) Affected ADs This AD replaces AD 2011-17-09, Amendment 39-16773 (76 FR 53305, August 26, 2011) (``AD 2011-17-09''); and AD 2012-25-12, Amendment 39-17293 (77 FR 75825, December 26, 2012) (``AD 2012-25-12''). (c) Applicability This AD applies to the Airbus airplanes identified in paragraphs (c)(1), (c)(2), and (c)(3) of this AD, certificated in any category, with an original certificate of airworthiness or original export certificate of airworthiness issued on or before April 11, 2016. (1) Airbus Model A330-201, -202, -203, -223, and -243 airplanes. (2) Airbus Model A330-223F and -243F airplanes. (3) Airbus Model A330-301, -302, -303, -321, -322, -323, -341, - 342, and -343 airplanes. (d) Subject Air Transport Association (ATA) of America Code 05, Periodic inspections. (e) Reason This AD was prompted by revisions to certain airworthiness limitation item documents, which specify more restrictive instructions and/or airworthiness limitations. We are issuing this AD to detect and correct fatigue cracking, accidental damage, or corrosion in principal structural elements, and possible failure of certain life limited parts, which could result in reduced structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Maintenance Program Revision, With New Terminating Action This paragraph restates the requirements of paragraph (h) of AD 2011-17-09, with new terminating action. Within 3 months after September 30, 2011 (the effective date of AD 2011-17-09): Revise the maintenance program by incorporating Airbus A330 Airworthiness Limitations Section (ALS) Part 1, Safe Life Airworthiness Limitation Items (SL-ALI), Revision 05, dated July 29, 2010. Comply with all ALIs in Airbus A330 ALS Part 1, SL-ALI, Revision 05, dated July 29, 2010, at the times specified therein. Accomplishing the actions specified in paragraph (k) of this AD terminates the requirements of this paragraph. (h) Retained Limitation of No Alternative Intervals or Limits, With Additional Exception This paragraph restates the requirements of paragraph (i) of AD 2011-17-09, with additional exception. Except as provided by paragraphs (k) and (m)(1) of this AD, after accomplishment of the actions specified in paragraph (g) of this AD, no alternatives to the maintenance tasks, intervals, or limitations specified in paragraph (g) of this AD may be used. (i) Retained Bogie Beam Replacement, With Specific Delegation Approval Language, New Terminating Action, and New Service Information This paragraph restates the requirements of paragraph (g) of AD 2012-25-12, with specific delegation approval language and terminating action and new service information. For airplanes identified in paragraphs (c)(1) and (c)(3) of this AD: At the [[Page 24038]] later of the times specified in paragraphs (i)(1) and (i)(2) of this AD, replace all main landing gear (MLG) bogie beams having part number (P/N) 201485300, 201485301, 201272302, 201272304, 201272306, or 201272307, except those that have serial number (S/N) S2A, S2B, or S2C, as identified in Messier-Dowty Service Letter A33-34 A20, Revision 5, including Appendixes A through F, dated July 31, 2009; or Messier-Bugatti-Dowty Service Letter A33-34 A20, Revision 7, including Appendixes A through F, dated July 20, 2012; with a new or serviceable part, using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA). As of the effective date of this AD, the applicable MLG bogie beams specified in this paragraph must be replaced using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA. Accomplishing the actions specified in paragraph (k) of this AD terminates the requirements of this paragraph. (1) At the applicable time specified in paragraphs (i)(1)(i), (i)(1)(ii), and (i)(1)(iii) of this AD. (i) For Model A330-201, -202, -203, -223, -243 series airplanes, weight variant (WV)02x, WV05x (except WV058), and WV06x series: Before the accumulation of a life limit of 50,000 landings or 72,300 total flight hours, whichever occurs first from the first installation of a MLG bogie beam on the airplane. (ii) For Model A330-201, -202, -203, -223, -243 WV058 series airplanes: Before the accumulation of a life limit of 50,000 landings or 57,900 total flight hours, whichever occurs first from the first installation of a MLG bogie beam on the airplane. (iii) For Model A330-301, -302, -303, -321, -322, -323, -341, - 342, -343 series airplanes, WV00x, WV01x, WV02x, and WV05x series: Before the accumulation of a life limit of 46,000 landings or 75,000 total flight hours, whichever occurs first from the first installation of a MLG bogie beam on the airplane. (2) Within 6 months after January 30, 2013 (the effective date of AD 2012-25-12). (j) Retained Parts Installation Limitation, With New Terminating Action This paragraph restates the requirements of paragraph (h) of AD 2012-25-12, with new terminating action. For airplanes identified in paragraphs (c)(1) and (c)(3) of this AD, as of January 30, 2013 (the effective date of AD 2012-25-12), a MLG bogie beam having any part number identified in paragraph (i) of this AD may be installed on an airplane, provided its life has not exceeded the life limit specified in paragraphs (i)(1)(i), (i)(1)(ii), and (i)(1)(iii) of this AD, and it is replaced with a new or serviceable part before reaching the life limit specified in paragraphs (i)(1)(i), (i)(1)(ii), and (i)(1)(iii) of this AD. Accomplishing the actions specified in paragraph (k) of this AD terminates the requirements of this paragraph. (k) New Maintenance or Inspection Program Revision Within 3 months after the effective date of this AD: Revise the maintenance or inspection program, as applicable, by incorporating the information in Airbus A330 ALS Part 1, SL-ALI, Revision 08, dated April 11, 2016. The initial compliance times for the actions specified in Airbus A330 ALS Part 1, SL-ALI, Revision 08, dated April 11, 2016, are at the times specified in Airbus A330 ALS Part 1, SL-ALI, Revision 08, dated April 11, 2016, or within 3 months after the effective date of this AD, whichever occurs later. Accomplishing the actions specified in this paragraph terminates the requirements specified in paragraphs (g) through (j) of this AD. (l) New Limitation of No Alternative Actions or Intervals After the maintenance or inspection program, as applicable, has been revised, as required by paragraph (k) of this AD, no alternative actions (e.g., inspections) or intervals may be used unless the actions or intervals are approved as an alternative method of compliance (AMOC) in accordance with the procedures specified in paragraph (m)(1) of this AD. (m) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM-116, Transport Airplane Directorate, 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 International Branch, send it to the attention of the person identified in paragraph (n)(2) of this AD. Information may be emailed to: [email protected]. 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. (2) Contacting the Manufacturer: As of the effective date of this AD, for any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (n) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2014-0009, dated January 8, 2014, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-8428. (2) For more information about this AD, contact Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1138; fax 425-227-1149. (o) 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 this AD specifies otherwise. (3) The following service information was approved for IBR on June 29, 2017. (i) Airbus A330 Airworthiness Limitations Section Part 1, Safe Life Airworthiness Limitation Items, Revision 08, dated April 11, 2016. (ii) Messier-Bugatti-Dowty Service Letter A33-34 A20, Revision 7, including Appendixes A through F, dated July 20, 2012. (4) The following service information was approved for IBR on January 30, 2013 (77 FR 75825, December 26, 2012). (i) Messier-Dowty Service Letter A33-34 A20, Revision 5, including Appendixes A through F, dated July 31, 2009. (ii) Reserved. (5) The following service information was approved for IBR on September 30, 2011 (76 FR 53305, August 26, 2011). (i) Airbus A330 Airworthiness Limitations Section, Part 1, Safe Life Airworthiness Limitation Items, Revision 05, dated July 29, 2010. The revision level of this document is indicated only on the title page and in the Record of Revisions; the revision date of this document is not indicated on the title page of this document. (ii) Reserved. (6) For Airbus service information identified in this AD, contact Airbus SAS--Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email [email protected]; Internet http://www.airbus.com. (7) For Messier-Bugatti-Dowty service information identified in this AD, contact Messier-Bugatti USA, One Carbon Way, Walton, KY 41094; telephone 859-525-8583; fax 859-485 8827; email [email protected]. (8) You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. (9) 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. [[Page 24039]] Issued in Renton, Washington, on May 10, 2017. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017-10266 Filed 5-24-17; 8:45 am] BILLING CODE 4910-13-P
![Federal Register / Vol. 82, No. 100 / Thursday, May 25, 2017 / Rules and Regulations 24035
that is likely to exist or develop on (d) Subject 7754; fax: 781–238–7199; email:
products identified in this rulemaking Joint Aircraft System Component (JASC) Robert.Green@faa.gov.
action. 7230, Turbine Engine Compressor Section. (2) Refer to MCAI European Aviation
Safety Agency (EASA), AD 2017–0071, dated
Regulatory Findings (e) Reason April 26, 2017, for more information. You
This AD was prompted by CICs that were may examine the MCAI in the AD docket on
We determined that this AD will not the Internet at http://www.regulations.gov by
weld repaired and have a higher probability
have federalism implications under of cracking due to increased residual stresses searching for and locating it in Docket No.
Executive Order 13132. This AD will as a result of the weld repair process. We are FAA–2017–0114.
not have a substantial direct effect on issuing this AD to prevent CIC failure, engine (m) Material Incorporated by Reference
the States, on the relationship between separation and loss of the airplane.
the national government and the States, (1) The Director of the Federal Register
(f) Compliance approved the incorporation by reference
or on the distribution of power and (IBR) of the service information listed in this
responsibilities among the various Comply with this AD within the
compliance times specified, unless already paragraph under 5 U.S.C. 552(a) and 1 CFR
levels of government. done. part 51.
For the reasons discussed above, I (2) You must use this service information
certify this AD: (g) Required Actions as applicable to do the actions required by
(1) Is not a ‘‘significant regulatory (1) Inspect repaired CICs during the next this AD, unless the AD specifies otherwise.
action’’ under Executive Order 12866, shop visit, or within 6,000 engine flight (i) Rolls-Royce plc Alert Non-Modification
cycles, whichever occurs first, after the Service Bulletin RB.211–72–AH976, Revision
(2) Is not a ‘‘significant rule’’ under
effective date of this AD, using paragraph 2, dated March 16, 2017.
the DOT Regulatory Policies and (ii) Reserved.
3.B.(1)(c) of the Accomplishment
Procedures (44 FR 11034, February 26, Instructions, of RR Alert Non-Modification (3) For Rolls-Royce plc service information
1979), Service Bulletin (NMSB) RB.211–72–AH976, identified in this AD, contact Rolls-Royce
(3) Will not affect intrastate aviation Revision 2, dated March 16, 2017. plc, Corporate Communications, P.O. Box 31,
in Alaska to the extent that it justifies (2) If a CIC fails inspection required by Derby, England, DE24 8BJ; phone: 011–44–
making a regulatory distinction, and paragraph (g)(1) of this AD, either repair the 1332–242424; fax: 011–44–1332–249936;
(4) Will not have a significant CIC using paragraph 3.B.(2)(b) of the email: http://www.rolls-royce.com/contact/
economic impact, positive or negative, Accomplishment Instructions, of RR Alert civil_team.jsp; Internet: https://
NMSB RB.211–72–AH976, Revision 2, dated customers.rolls-royce.com/public/
on a substantial number of small entities
March 16, 2017, or, replace the CIC with a rollsroycecare.
under the criteria of the Regulatory part eligible for installation, before next (4) You may view this service information
Flexibility Act. flight. at FAA, Engine & Propeller Directorate, 1200
List of Subjects in 14 CFR Part 39 District Avenue, Burlington, MA 01803. For
(h) Definitions information on the availability of this
Air transportation, Aircraft, Aviation For the purpose of this AD, a shop visit is material at the FAA, call 781–238–7125.
safety, Incorporation by reference, the induction of an engine into the shop for (5) You may view this service information
Safety. maintenance or overhaul that requires the at the National Archives and Records
separation of major mating engine module Administration (NARA). For information on
Adoption of the Amendment flanges. The separation of engine flanges the availability of this material at NARA, call
solely for the purpose of transporting the 202–741–6030, or go to: http://
Accordingly, under the authority engine without subsequent engine www.archives.gov/federal-register/cfr/ibr-
delegated to me by the Administrator, maintenance does not constitute an engine locations.html.
the FAA amends 14 CFR part 39 as shop visit.
follows: Issued in Burlington, Massachusetts, on
(i) Installation Prohibition May 4, 2017.
PART 39—AIRWORTHINESS After the effective date of this AD, do not Robert J. Ganley,
DIRECTIVES install an affected intermediate module on an Acting Assistant Manager, Engine & Propeller
engine unless the CIC has passed the Directorate, Aircraft Certification Service.
■ 1. The authority citation for part 39 inspection required by paragraph (g)(1) of
[FR Doc. 2017–10438 Filed 5–24–17; 8:45 am]
continues to read as follows: this AD.
BILLING CODE 4910–13–P
Authority: 49 U.S.C. 106(g), 40113, 44701. (j) Credit for Previous Actions
You may take credit for the inspections
§ 39.13 [Amended] and corrective action required by paragraph DEPARTMENT OF TRANSPORTATION
■ 2. The FAA amends § 39.13 by adding (g) of this AD, if you performed these actions
before the effective date of this AD using RR Federal Aviation Administration
the following new airworthiness
Alert NMSB RB.211–72–AH976, original
directive (AD): issue, dated November 3, 2016 or RR Alert 14 CFR Part 39
2017–10–06 Rolls-Royce plc: Amendment NMSB RB.211–72–AH976, Revision 1, dated
39–18880; Docket No. FAA–2017–0114; November 17, 2016. [Docket No. FAA–2015–8428; Directorate
Directorate Identifier 2017–NE–03–AD. Identifier 2014–NM–032–AD; Amendment
(k) Alternative Methods of Compliance 39–18898; AD 2017–10–24]
(a) Effective Date (AMOCs)
This AD is effective June 9, 2017. The Manager, Engine Certification Office, RIN 2120–AA64
FAA, may approve AMOCs for this AD. Use
(b) Affected ADs the procedures found in 14 CFR 39.19 to Airworthiness Directives; Airbus
None. make your request. You may email your Airplanes
request to: ANE-AD-AMOC@faa.gov.
(c) Applicability AGENCY: Federal Aviation
This AD applies to Rolls-Royce plc (RR) (l) Related Information Administration (FAA), Department of
RB211 Trent 768–60, RB211 Trent 772–60, (1) For more information about this AD, Transportation (DOT).
and RB211 Trent 772B–60 turbofan engines contact Robert Green, Aerospace Engineer, ACTION: Final rule.
that have a compressor intermediate case Engine Certification Office, FAA, Engine &
(CIC) that was repaired using RR Repair Propeller Directorate, 1200 District Avenue, SUMMARY: We are superseding
FRSC005. Burlington, MA 01803; phone: 781–238– Airworthiness Directive (AD) 2011–17–
VerDate Sep<11>2014 15:57 May 24, 2017 Jkt 241001 PO 00000 Frm 00037 Fmt 4700 Sfmt 4700 E:\FR\FM\25MYR1.SGM 25MYR1](https://thefederalregister.org/doc/82_FR_24135/page/1.svg)
![24036 Federal Register / Vol. 82, No. 100 / Thursday, May 25, 2017 / Rules and Regulations
09 for all Airbus Model A330–200, –200 www.regulations.gov by searching for The European Aviation Safety Agency
Freighter, and –300 series airplanes; and and locating Docket No. FAA–2015– (EASA), which is the Technical Agent
AD 2012–25–12 for all Airbus Model 8428; or in person at the Docket for the Member States of the European
A330–200 and –300 series airplanes. AD Management Facility between 9 a.m. Union, has issued EASA Airworthiness
2011–17–09 required revisions to and 5 p.m., Monday through Friday, Directive, 2014–0009, dated January 8,
certain operator maintenance except Federal holidays. The AD docket 2014 (referred to after this as the
documents to include new inspections. contains this AD, the regulatory Mandatory Continuing Airworthiness
AD 2012–25–12 required replacing evaluation, any comments received, and Information, or ‘‘the MCAI’’), to correct
certain main landing gear (MLG) bogie other information. The address for the an unsafe condition for all Airbus
beams before reaching new reduced life Docket Office (telephone 800–647–5527) Model A330–200, –200 Freighter, and
limits. This new AD requires revising is Docket Management Facility, U.S. –300 series airplanes; and Model A340–
the maintenance or inspection program, Department of Transportation, Docket 200, –300, –500, and –600 series
as applicable, to incorporate new, more Operations, M–30, West Building airplanes. The MCAI states:
restrictive, or revised instructions and/ Ground Floor, Room W12–140, 1200 The airworthiness limitations for Airbus
or airworthiness limitation New Jersey Avenue SE., Washington, aeroplanes are currently published in
requirements. This AD was prompted by DC 20590. Airworthiness Limitations Section (ALS)
revisions to certain airworthiness FOR FURTHER INFORMATION CONTACT: documents.
limitation item (ALI) documents, which Vladimir Ulyanov, Aerospace Engineer, The instructions and airworthiness
specify more restrictive instructions International Branch, ANM–116, limitations applicable to the Safe Life
and/or airworthiness limitations. We are Airworthiness Limitation Items (SL ALI) are
Transport Airplane Directorate, FAA, given in Airbus A330 ALS Part 1 and A340
issuing this AD to address the unsafe 1601 Lind Avenue SW., Renton, WA ALS Part 1, which are approved by EASA.
condition on these products. 98057–3356; telephone 425–227–1138; The revision 07 of Airbus A330 and A340
DATES: This AD is effective June 29, fax 425–227–1149. ALS Part 1 introduces more restrictive
2017. SUPPLEMENTARY INFORMATION: instructions and/or airworthiness limitations.
The Director of the Federal Register Failure to comply with this revision could
approved the incorporation by reference Discussion result in an unsafe condition.
of certain publications listed in this AD We issued a supplemental notice of For the reason described above, this
as of June 29, 2017. proposed rulemaking (SNPRM) to [EASA] AD retains the requirements of EASA
AD 2012–0179, which is superseded, and
The Director of the Federal Register amend 14 CFR part 39 to supersede AD requires accomplishment of the actions
approved the incorporation by reference 2011–17–09, Amendment 39–16773 (76 specified in Airbus A330 or A340 ALS Part
of a certain other publication listed in FR 53305, August 26, 2011) (‘‘AD 2011– 1 revision 07.
this AD as of January 30, 2013 (77 FR 17–09’’); and AD 2012–25–12, In addition, this [EASA] AD also
75825, December 26, 2012). Amendment 39–17293 (77 FR 75825, supersedes EASA AD 2011–0122–E and
The Director of the Federal Register December 26, 2012) (‘‘AD 2012–25– EASA AD 2011–0212, whose requirements
approved the incorporation by reference 12’’). AD 2011–17–09 applied to all have been transferred into Airbus A330 and
of a certain other publication listed in Airbus Model A330–200, –200 A340 ALS Part 1 revision 07.
this AD as of September 30, 2011 (76 FR Freighter, and –300 series airplanes. AD The unsafe condition is fatigue
53305, August 26, 2011). 2012–25–12 applied to all Airbus Model cracking, accidental damage, or
ADDRESSES: For Airbus service A330–200 and –300 series airplanes. corrosion in certain principal structural
information identified in this final rule, The SNPRM published in the Federal elements, and possible failure of certain
contact Airbus SAS—Airworthiness Register on December 16, 2016 (81 FR life limited parts, which could result in
Office—EAL, 1 Rond Point Maurice 91062). We preceded the SNPRM with reduced structural integrity of the
Bellonte, 31707 Blagnac Cedex, France; a notice of proposed rulemaking airplane. You may examine the MCAI in
telephone +33 5 61 93 36 96; fax +33 5 (NPRM) that published in the Federal the AD docket on the Internet at http://
61 93 45 80; email airworthiness.A330- Register on January 13, 2016 (81 FR www.regulations.gov by searching for
A340@airbus.com; Internet http:// 1570). The NPRM was prompted by a and locating Docket No. FAA–2015–
www.airbus.com. determination that more restrictive 8428.
For Messier-Bugatti-Dowty service instructions and/or airworthiness
limitations should be incorporated into Comments
information identified in this final rule,
contact Messier-Bugatti USA, One the maintenance or inspection program, We gave the public the opportunity to
Carbon Way, Walton, KY 41094; as applicable. The NPRM proposed to participate in developing this AD. We
telephone 859–525–8583; fax 859–485 require revising the maintenance or received no comments on the SNPRM or
8827; email americascsc@ inspection program, as applicable, to on the determination of the cost to the
safranmbd.com. incorporate new or revised public.
You may view this referenced service airworthiness limitation requirements.
Conclusion
information at the FAA, Transport The SNPRM proposed to require
Airplane Directorate, 1601 Lind Avenue revising the maintenance or inspection We reviewed the available data and
SW., Renton, WA. For information on program, as applicable, to incorporate determined that air safety and the
the availability of this material at the more restrictive instructions and/or public interest require adopting this AD
FAA, call 425–227–1221. It is also airworthiness limitations that the as proposed except for minor editorial
available on the Internet at http:// manufacturer has recently issued. We changes. We have determined that these
www.regulations.gov by searching for are issuing this AD to detect and correct minor changes:
and locating Docket No. FAA–2015– fatigue cracking, accidental damage, or • Are consistent with the intent that
8428. corrosion in principal structural was proposed in the SNPRM for
elements, and possible failure of certain correcting the unsafe condition; and
Examining the AD Docket life limited parts, which could result in • Do not add any additional burden
You may examine the AD docket on reduced structural integrity of the upon the public than was already
the Internet at http:// airplane. proposed in the SNPRM.
VerDate Sep<11>2014 15:57 May 24, 2017 Jkt 241001 PO 00000 Frm 00038 Fmt 4700 Sfmt 4700 E:\FR\FM\25MYR1.SGM 25MYR1](https://thefederalregister.org/doc/82_FR_24135/page/2.svg)
![Federal Register / Vol. 82, No. 100 / Thursday, May 25, 2017 / Rules and Regulations 24037
Related Service Information Under 1 because it addresses an unsafe condition (c) Applicability
CFR Part 51 that is likely to exist or develop on This AD applies to the Airbus airplanes
Airbus has issued Airbus A330 ALS products identified in this rulemaking identified in paragraphs (c)(1), (c)(2), and
action. (c)(3) of this AD, certificated in any category,
Part 1, SL–ALI, Revision 08, dated April with an original certificate of airworthiness
11, 2016. Messier-Bugatti-Dowty has Regulatory Findings or original export certificate of airworthiness
issued Service Letter A33–34 A20, issued on or before April 11, 2016.
Revision 7, including Appendixes A We determined that this AD will not (1) Airbus Model A330–201, –202, –203,
through F, dated July 20, 2012. This have federalism implications under –223, and –243 airplanes.
service information describes SL–ALI Executive Order 13132. This AD will (2) Airbus Model A330–223F and –243F
for the landing gear. This service not have a substantial direct effect on airplanes.
the States, on the relationship between (3) Airbus Model A330–301, –302, –303,
information is distinct since it was –321, –322, –323, –341, –342, and –343
issued by two different manufacturers the national government and the States,
airplanes.
for different purposes. or on the distribution of power and
This service information is reasonably responsibilities among the various (d) Subject
available because the interested parties levels of government. For the reasons Air Transport Association (ATA) of
have access to it through their normal discussed above, I certify that this AD: America Code 05, Periodic inspections.
course of business or by the means 1. Is not a ‘‘significant regulatory (e) Reason
identified in the ADDRESSES section. action’’ under Executive Order 12866; This AD was prompted by revisions to
Costs of Compliance 2. Is not a ‘‘significant rule’’ under the certain airworthiness limitation item
DOT Regulatory Policies and Procedures documents, which specify more restrictive
We estimate that this AD affects 82 (44 FR 11034, February 26, 1979); instructions and/or airworthiness limitations.
airplanes of U.S. registry. We are issuing this AD to detect and correct
3. Will not affect intrastate aviation in
The actions that are required by AD fatigue cracking, accidental damage, or
Alaska; and corrosion in principal structural elements,
2011–17–09, and retained in this AD,
4. Will not have a significant and possible failure of certain life limited
take about 1 work-hour per product, at
economic impact, positive or negative, parts, which could result in reduced
an average labor rate of $85 per work- structural integrity of the airplane.
on a substantial number of small entities
hour. Based on these figures, the
under the criteria of the Regulatory (f) Compliance
estimated cost of the actions that are
Flexibility Act.
required by AD 2011–17–09 is $85 per Comply with this AD within the
product. List of Subjects in 14 CFR Part 39 compliance times specified, unless already
The actions that are required by AD done.
2012–25–12, and retained in this AD, Air transportation, Aircraft, Aviation
(g) Retained Maintenance Program Revision,
take about 16 work-hours, at an average safety, Incorporation by reference, With New Terminating Action
labor rate of $85 per work-hour, with Safety.
This paragraph restates the requirements of
required parts cost of about $255,000 Adoption of the Amendment paragraph (h) of AD 2011–17–09, with new
per MLG bogie beam. Based on these terminating action. Within 3 months after
figures, the estimated cost of the actions Accordingly, under the authority September 30, 2011 (the effective date of AD
that are required by AD 2012–25–12 is delegated to me by the Administrator, 2011–17–09): Revise the maintenance
up to $256,360 per MLG bogie beam. the FAA amends 14 CFR part 39 as program by incorporating Airbus A330
follows: Airworthiness Limitations Section (ALS) Part
We also estimate that it would take 1, Safe Life Airworthiness Limitation Items
about 1 work-hour per product to (SL–ALI), Revision 05, dated July 29, 2010.
PART 39—AIRWORTHINESS
comply with the basic requirements of Comply with all ALIs in Airbus A330 ALS
DIRECTIVES
this AD. The average labor rate is $85 Part 1, SL–ALI, Revision 05, dated July 29,
per work-hour. Based on these figures, 2010, at the times specified therein.
■ 1. The authority citation for part 39 Accomplishing the actions specified in
we estimate the cost of this AD on U.S.
continues to read as follows: paragraph (k) of this AD terminates the
operators to be $6,970, or $85 per
product. Authority: 49 U.S.C. 106(g), 40113, 44701. requirements of this paragraph.
(h) Retained Limitation of No Alternative
Authority for This Rulemaking § 39.13 [Amended]
Intervals or Limits, With Additional
Title 49 of the United States Code ■ 2.The FAA amends § 39.13 by Exception
specifies the FAA’s authority to issue removing Airworthiness Directive (AD) This paragraph restates the requirements of
rules on aviation safety. Subtitle I, 2011–17–09, Amendment 39–16773 (76 paragraph (i) of AD 2011–17–09, with
section 106, describes the authority of FR 53305, August 26, 2011); and AD additional exception. Except as provided by
the FAA Administrator. ‘‘Subtitle VII: 2012–25–12, Amendment 39–17293 (77 paragraphs (k) and (m)(1) of this AD, after
Aviation Programs,’’ describes in more accomplishment of the actions specified in
FR 75825, December 26, 2012); and
paragraph (g) of this AD, no alternatives to
detail the scope of the Agency’s adding the following new AD: the maintenance tasks, intervals, or
authority. 2017–10–24 Airbus: Amendment 39–18898; limitations specified in paragraph (g) of this
We are issuing this rulemaking under Docket No. FAA–2015–8428; Directorate AD may be used.
the authority described in ‘‘Subtitle VII, Identifier 2014–NM–032–AD.
Part A, Subpart III, Section 44701: (i) Retained Bogie Beam Replacement, With
(a) Effective Date Specific Delegation Approval Language,
General requirements.’’ Under that New Terminating Action, and New Service
section, Congress charges the FAA with This AD is effective June 29, 2017.
Information
promoting safe flight of civil aircraft in (b) Affected ADs This paragraph restates the requirements of
air commerce by prescribing regulations This AD replaces AD 2011–17–09, paragraph (g) of AD 2012–25–12, with
for practices, methods, and procedures Amendment 39–16773 (76 FR 53305, August specific delegation approval language and
the Administrator finds necessary for 26, 2011) (‘‘AD 2011–17–09’’); and AD 2012– terminating action and new service
safety in air commerce. This regulation 25–12, Amendment 39–17293 (77 FR 75825, information. For airplanes identified in
is within the scope of that authority December 26, 2012) (‘‘AD 2012–25–12’’). paragraphs (c)(1) and (c)(3) of this AD: At the
VerDate Sep<11>2014 15:57 May 24, 2017 Jkt 241001 PO 00000 Frm 00039 Fmt 4700 Sfmt 4700 E:\FR\FM\25MYR1.SGM 25MYR1](https://thefederalregister.org/doc/82_FR_24135/page/3.svg)
![Federal Register / Vol. 82, No. 100 / Thursday, May 25, 2017 / Rules and Regulations 24039
Issued in Renton, Washington, on May 10, Examining the AD Docket A330 aeroplanes with Pratt & Whitney (PW)
2017. PW4000 engines, are made from MP159
You may examine the AD docket on material. Analysis made by PW identified
Michael Kaszycki,
the Internet at http:// that MP159 material pylon bolts do not meet
Acting Manager, Transport Airplane www.regulations.gov by searching for the full life cycle torque check interval
Directorate, Aircraft Certification Service. and locating Docket No. FAA–2016– requirement, in a bolt-out condition.
[FR Doc. 2017–10266 Filed 5–24–17; 8:45 am] 8849; or in person at the Docket Consequently, PW issued Alert Service
BILLING CODE 4910–13–P Management Facility between 9 a.m. Bulletin (ASB) PW4G–100–A71–32, and the
and 5 p.m., Monday through Friday, U.S. Federal Aviation Administration (FAA),
except Federal holidays. The AD docket as Engine Certification Authority, issued
DEPARTMENT OF TRANSPORTATION FAA AD 2006–16–05 [Amendment 39–14705
contains this AD, the regulatory (71 FR 44185, August 4, 2006) (‘‘AD 2006–
evaluation, any comments received, and 16–05’’)] to require repetitive torque checks
Federal Aviation Administration
other information. The address for the of MP159 material forward mount pylon
Docket Office (telephone 800–647–5527) bolts fitted on certain PW4000 series engines.
14 CFR Part 39
is Docket Management Facility, U.S. However, the engine mount system is
Department of Transportation, Docket considered to be part of aeroplane
[Docket No. FAA–2016–8849; Directorate Operations, M–30, West Building certification rather than the engine
Identifier 2015–NM–174–AD; Amendment Ground Floor, Room W12–140, 1200 certification. Following further fatigue load
39–18892; AD 2017–10–18] New Jersey Avenue SE., Washington, analysis by Airbus of the A330 engine mount
system, it was determined that the torque
DC 20590. check interval for MP159 material forward
RIN 2120–AA64 FOR FURTHER INFORMATION CONTACT: mount pylon bolts, as required by FAA AD
Vladimir Ulyanov, Aerospace Engineer, 2006–16–05 (2,700 flight cycles (FC)),
Airworthiness Directives; Airbus International Branch, ANM–116, provided an insufficient level of safety for
Airplanes Transport Airplane Directorate, FAA, Airbus A330 aeroplanes.
1601 Lind Avenue SW., Renton, WA This condition, if not detected and
AGENCY: Federal Aviation
98057–3356; telephone: 425–227–1138; corrected, could ultimately lead to
Administration (FAA), Department of detachment of the engine from the aeroplane,
Transportation (DOT). fax: 425–227–1149.
possibly resulting in damage to the aeroplane
SUPPLEMENTARY INFORMATION: and/or injury to persons on the ground.
ACTION: Final rule.
Discussion Consequently, EASA issued AD 2012–0094
SUMMARY: We are adopting a new [which corresponds to FAA AD 2013–14–04]
airworthiness directive (AD) for all We issued a notice of proposed to require accomplishment of repetitive
rulemaking (NPRM) to amend 14 CFR torque checks of the forward mount pylon
Airbus Model A330–223F, –223, –321,
part 39 by adding an AD that would bolts installed on affected A330 aeroplanes
–322, and –323 airplanes. This AD was
apply to all Airbus Model A330–223F, and, depending on findings, replacement of
prompted by fatigue load analysis that all four bolts and associated nuts, in
–223, –321, –322, and –323 airplanes.
determined the need for reduced accordance with PW ASB PW4G–100–A71–
The NPRM published in the Federal
inspection intervals and updated torque 32 Revision 01 and Airbus Service Bulletin
Register on August 30, 2016 (81 FR
values of the bolts. This AD requires (SB) A330–71–3028.
59535). The NPRM was prompted by
repetitive torque checks of the forward Since that AD was issued, it has been
fatigue load analysis that determined concluded that a new torque value must be
engine mount bolts, an inspection of the
the need for reduced inspection applied.
forward mount assembly, and
intervals (for torque checks required by Consequently, Airbus issued SB A330–71–
replacement of the bolts or repair of the
AD 2013–14–04, Amendment 39–17509 3028 Revision 02 and PW issued ASB
forward mount assembly as necessary.
(78 FR 68352, November 14, 2013) (‘‘AD PW4G–100–A71–32 Revision 02 to update
We are issuing this AD to address the the torque value. Additional forward mount
2013–14–04’’)) and updated torque
unsafe condition on these products. inspections are also provided in case of one
values of the bolts. The NPRM proposed
DATES: This AD is effective June 29, to require repetitive torque checks to or more forward engine mount bolts is found
2017. loose, broken or missing.
determine if there are any loose or For the reasons described above, this
The Director of the Federal Register broken forward engine mount bolts, [EASA] AD retains the requirements of EASA
approved the incorporation by reference and, if necessary, replacement of all four AD 2012–0094, which is superseded,
of a certain publication listed in this AD forward engine mount bolts and introduces a new torque value, and requires
as of June 29, 2017. associated nuts, inspection of the additional inspections and, depending on
ADDRESSES: For service information forward mount assembly, and repair. findings, corrective action(s).
identified in this final rule, contact We are issuing this AD to detect and Corrective actions include repetitive
Airbus SAS, Airworthiness Office— correct loose and broken bolts, which torque checks to determine if there are
EAL, 1 Rond Point Maurice Bellonte, could lead to engine detachment in any loose or broken forward engine
31707 Blagnac Cedex, France; telephone flight and damage to the airplane. mount bolts on both engines, and, if
+33 5 61 93 36 96; fax +33 5 61 93 45 The European Aviation Safety Agency necessary, replacement of all four
80; email airworthiness.A330-A340@ (EASA), which is the Technical Agent forward engine mount bolts and
airbus.com; Internet http:// for the Member States of the European associated nuts, inspection of the
www.airbus.com. You may view this Union, has issued EASA AD 2015–0214, forward mount assembly, and repair.
referenced service information at the dated October 19, 2015 (referred to after You may examine the MCAI in the AD
FAA, Transport Airplane Directorate, this as the Mandatory Continuing docket on the Internet at http://
1601 Lind Avenue SW., Renton, WA. Airworthiness Information, or ‘‘the www.regulations.gov by searching for
For information on the availability of MCAI’’), to correct an unsafe condition and locating Docket No. FAA–2016–
this material at the FAA, call 425–227– for all Airbus Model A330–223F, –223, 8849.
1221. It is also available on the Internet –321, –322, and –323 airplanes. The
at http://www.regulations.gov by MCAI states: Comments
searching for and locating Docket No. The forward mount engine pylon bolts, We gave the public the opportunity to
FAA–2016–8849. Part Number (P/N) 51U615, fitted on Airbus participate in developing this AD. The
VerDate Sep<11>2014 15:57 May 24, 2017 Jkt 241001 PO 00000 Frm 00041 Fmt 4700 Sfmt 4700 E:\FR\FM\25MYR1.SGM 25MYR1](https://thefederalregister.org/doc/82_FR_24135/page/5.svg)
Document Created: 2018-11-08 08:53:02
Document Modified: 2018-11-08 08:53:02
| 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 June 29, 2017. | |
| Contact | Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1138; fax 425-227-1149. | |
| FR Citation | 82 FR 24035 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
2025 Federal Register | Disclaimer | Privacy Policy
USC | CFR | eCFR