81 FR 37488 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 112 (June 10, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 112 (June 10, 2016)
| Page Range | 37488-37492 | |
| FR Document | 2016-12324 |
[Federal Register Volume 81, Number 112 (Friday, June 10, 2016)] [Rules and Regulations] [Pages 37488-37492] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-12324] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-4813; Directorate Identifier 2013-NM-161-AD; Amendment 39-18532; AD 2016-11-05] 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) 99-16-01 for certain Airbus Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes). AD 99-16-01 required repetitive inspections of certain bolt holes where parts of the main landing gear (MLG) are attached to the wing rear spar, and repair if necessary. Since we issued AD 99-16-01, we have determined that the risk of cracking in the wing rear spar is higher than initially determined. This new AD adds airplanes to the applicability, reduces the compliance times and repetitive intervals for the inspections, and changes the inspection procedures. This AD was prompted by a determination that the risk of cracking in the wing rear spar is higher than initially determined. We are issuing this AD to detect and correct cracking of the rear spar of the wing, which could result in reduced structural integrity of the airplane. DATES: This AD becomes effective July 15, 2016. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of July 15, 2016. The Director of the Federal Register approved the incorporation by reference of a certain other publication listed in this AD as of November 9, 1995 (60 FR 52618, October 10, 1995). ADDRESSES: For service information identified in this final rule, contact Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email [email protected]; Internet http://www.airbus.com. 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- 4813. 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- 4813; 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: Dan Rodina, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone: 425-227-2125; fax: 425-227-1149. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 99-16-01, Amendment 39-11236 (64 FR 40743, July 28, 1999) (``AD 99-16-01''). AD 99-16-01 superseded AD 95-20-02, Amendment 39-9380 (60 FR 52618, October 10, 1995). AD 99-16-01 applied to certain Airbus Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes). The NPRM published in the Federal Register on November 17, 2015 (80 FR 71751) (``the NPRM''). The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2013-0180, dated August 9, 2013 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for certain Airbus Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4- 605R Variant F airplanes (collectively called Model A300-600 series airplanes). The MCAI states: During full-scale fatigue testing, cracks were found on the rear spar from certain bolt holes at the attachment of the Main Landing gear (MLG) forward pick-up fitting and the MLG Rib 5 aft. This condition, if not detected and corrected, could reduce the structural integrity of the aeroplane. DGAC [Direction G[eacute]n[eacute]rale de l'Aviation Civile] France issued * * * [an AD] (later revised) to require High Frequency Eddy Current (HFEC) or Ultrasonic (U/S) inspections of certain fastener holes where the MLG forward pick-up fitting and MLG Rib 5 aft are attached to the rear spar. Since DGAC France * * * [issued a revised AD, which corresponded to FAA AD 99-16-01, Amendment 39-11236 (64 FR 40743, July 28, 1999), which superseded FAA AD 95-20-02, Amendment 39-9380 (60 FR 52618, October 10, 1995)] * * *, a fleet survey and updated Fatigue and Damage Tolerance analyses have been performed in order to substantiate the second A300-600 Extended Service Goal (ESG2) exercise. The results of these analyses have shown that the threshold and interval must be reduced to allow timely detection of these cracks and accomplishment of an applicable corrective action. For the reasons described above, this [EASA] AD retains the requirements of [the revised DGAC France AD], which is superseded, but reduces the related compliance times. The new, reduced threshold for the initial inspection ranges between 8,900 [[Page 37489]] total flight cycles/20,000 total flight hours, and 34,600 total flight cycles/77,800 total flight hours, depending on the modification. The grace periods (750 or 1,500 landings) for airplanes that have exceeded the specified thresholds are unchanged from those provided in AD 99-16- 01. The new, reduced intervals for the repetitive inspections range between 4,000 flight cycles/9,000 flight hours (whichever occurs first), and 8,900 flight cycles/20,000 flight hours (whichever occurs first), depending on the modification. 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-2015-4813. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM 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 NPRM for correcting 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 Airbus Service Bulletin A300-57-6017, Revision 04, including Appendix 1, dated February 4, 2011. This service information describes procedures for repetitive inspections of certain bolt holes where parts of the MLG are attached to the wing rear spar, and repair. 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 71 airplanes of U.S. registry. The actions required by AD 99-16-01 and retained in this AD, take about 226 work-hours per product, at an average labor rate of $85 per work hour. Required parts cost about $0 per product. Based on these figures, the estimated cost of the actions that are required by AD 99- 16-01 is $19,210 per product, per inspection cycle. We also estimate that it will take about 226 work-hours per product to comply with the new 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 $1,363,910, or $19,210 per product. We have received no definitive data that will enable us to provide cost estimates for the on-condition actions specified in this AD. 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) 99-16-01, Amendment 39-11236 (64 FR 40743, July 28, 1999), and adding the following new AD: 2016-11-05 Airbus: Amendment 39-18532; Docket No. FAA-2015-4813; Directorate Identifier 2013-NM-161-AD. (a) Effective Date This AD becomes effective July 15, 2016. (b) Affected ADs This AD replaces AD 99-16-01, Amendment 39-11236 (64 FR 40743, July 28, 1999) (``AD 99-16-01''). (c) Applicability This AD applies to Airbus Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes; Model A300 B4-605R and B4-622R airplanes; Model A300 F4-605R airplanes; and Model A300 C4-605R Variant F airplanes; certificated in any category; all manufacturer serial numbers. (d) Subject Air Transport Association (ATA) of America Code 57, Wings. (e) Reason This AD was prompted by the results of a full-scale fatigue test when cracking was found on the rear spar of the wing, and the subsequent determination that the risk of such cracking is higher than initially determined. We are issuing this AD to detect and correct cracking of the rear spar of the wing, 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 Inspections and Corrective Actions, With Revised Service Information This paragraph restates the requirements of paragraphs (a), (b), (c), (d), (e), and (f) of AD 99-16-01 with revised service information and reduced thresholds and repetitive intervals, for Airbus Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes; manufacturer serial numbers (MSNs) 252 through 553 inclusive; except those airplanes on which Airbus Modification 07601 has been accomplished prior to delivery. (1) Perform a high frequency eddy current (HFEC) rototest inspection to detect cracks in [[Page 37490]] certain bolt holes where the main landing gear (MLG) forward pick-up fitting and MLG rib 5 aft are attached to the rear spar, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6017, Revision 01, including Appendix 1, dated July 25, 1994; or Airbus Service Bulletin A300-57-6017, Revision 04, including Appendix 1, dated February 24, 2011. As of the effective date of this AD, only Airbus Service Bulletin A300-57-6017, Revision 04, including Appendix 1, dated February 24, 2011, may be used for the actions required by this paragraph. (i) For airplanes that have accumulated 17,300 total landings or less as of November 9, 1995 (the effective date of AD 95-20-02, Amendment 39-9380 (60 FR 52618, October 10, 1995)) (``AD 95-20- 02''): Inspect prior to the accumulation of 17,300 total landings, or within 1,500 landings after November 9, 1995, whichever occurs later. (ii) For airplanes that have accumulated 17,301 or more total landings, but less than 19,300 total landings as of November 9, 1995 (the effective date of AD 95-20-02): Inspect within 1,500 landings after November 9, 1995. (iii) For airplanes that have accumulated 19,300 or more total landings as of November 9, 1995 (the effective date of AD 95-20-02): Inspect within 750 landings after November 9, 1995 (the effective date of AD 95-20-02). (2) If no crack is found during the inspection required by paragraph (g)(1) of this AD, repeat that inspection thereafter at the time specified in either paragraph (g)(2)(i) or (g)(2)(ii) of this AD, as applicable. (i) For airplanes on which Airbus Modification 07716 (as specified in Airbus Service Bulletin A300-57-6020) has not been accomplished: Inspect at the time specified in paragraph (g)(2)(i)(A) or (g)(2)(i)(B) of this AD, as applicable. (A) For airplanes having MSNs 465 through 553 inclusive: Repeat the inspection at intervals not to exceed 13,000 landings, until the inspection required by paragraph (g)(4)(ii)(A)(1) of this AD has been accomplished. (B) For airplanes having MSNs 252 through 464 inclusive: Repeat the inspection at intervals not to exceed 8,400 landings, until the inspection required by paragraph (g)(4)(ii)(A)(2) of this AD has been accomplished. (ii) For airplanes on which Airbus Modification 07716 has been accomplished: Inspect at the time specified in either paragraph (g)(2)(ii)(A) or (g)(2)(ii)(B) of this AD, as applicable. (A) For airplanes having MSNs 465 through 553 inclusive: Repeat the inspection at intervals not to exceed 11,800 landings, until the inspection required by paragraph (g)(4)(i)(B) of this AD has been accomplished. (B) For airplanes having MSNs 252 through 464 inclusive: Repeat the inspection within 10,700 landings following the initial inspection required by paragraph (g)(1) of this AD, and thereafter at intervals not to exceed 7,500 landings, until the inspection required by paragraph (g)(4)(ii)(B)(2) has been accomplished. (3) If any crack is found during the inspection required by either paragraph (g)(1) or (g)(2) of this AD, prior to further flight, accomplish the requirements of either paragraph (g)(3)(i) or (g)(3)(ii) of this AD, as applicable. (i) For airplanes on which Airbus Modification 07716 has not been accomplished: Oversize the bolt hole by 1/32 inch and repeat the HFEC inspection required by paragraph (g)(1) of this AD, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6017, Revision 01, including Appendix 1, dated July 25, 1994. After accomplishing the oversizing and HFEC inspection, repeat the inspection, as required by paragraph (g)(2) of this AD, at the applicable schedule specified in that paragraph, until the inspection required by paragraph (g)(4)(ii)(B)(1) or (g)(4)(ii)(B)(2) of this AD has been accomplished. (A) If no cracking is detected, install the second oversize bolt in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6017, Revision 01, including Appendix 1, dated July 25, 1994. (B) If any cracking is detected, repair in accordance with a method approved by the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate. (ii) For airplanes on which Airbus Modification 07716 has been accomplished: Repair in accordance with a method approved by the Manager, International Branch, ANM-116. After repair, repeat the inspections as required by paragraph (g)(2) of this AD at the applicable schedule specified in that paragraph, until the inspection required by paragraph (g)(4)(ii)(B)(1) or (g)(4)(ii)(B)(2) of this AD has been accomplished. (4) Perform an ultrasonic inspection to detect cracks in certain bolt holes where the MLG forward pick-up fitting and MLG rib 5 aft are attached to the rear spar, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6017, Revision 03, dated November 19, 1997; or Revision 04, including Appendix 1, dated February 24, 2011; at the time specified in paragraph (g)(4)(i) or (g)(4)(ii) of this AD, as applicable. As of the effective date of this AD, only Airbus Service Bulletin A300-57-6017, Revision 04, including Appendix 1, dated February 24, 2011, may be used for the actions in this paragraph. (i) For airplanes not inspected prior to September 1, 1999 (the effective date of AD 99-16-01), as specified in Airbus Service Bulletin A300-57-6017, dated November 22, 1993; or Revision 01, including Appendix 1, dated July 25, 1994: Inspect at the time specified in paragraph (g)(4)(i)(A), (g)(4)(i)(B), or (g)(4)(i)(C) of this AD, as applicable. Accomplishment of this inspection terminates the requirements of paragraph (g)(1) of this AD. (A) For airplanes that have accumulated 17,300 total landings or fewer as of the effective date of this AD: Inspect prior to the accumulation of 17,300 total landings, or within 1,500 landings after September 1, 1999 (the effective date of AD 99-16-01), whichever occurs later. (B) For airplanes that have accumulated 17,301 total landings or more but fewer than 19,300 total landings as of September 1, 1999 (the effective date of AD 99-16-01): Inspect within 1,500 landings after September 1, 1999 (the effective date of AD 99-16-01). (C) For airplanes that have accumulated 19,300 total landings or more as of September 1, 1999 (the effective date of AD 99-16-01): Inspect within 750 landings after September 1, 1999 (the effective date of AD 99-16-01). (ii) For airplanes on which an HFEC inspection was performed prior to September 1, 1999 (the effective date of AD 99-16-01), in accordance with the requirements of paragraph (g)(1) of this AD, or in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6017, dated November 22, 1993: Inspect at the time specified in paragraph (g)(4)(ii)(A) or (g)(4)(ii)(B) of this AD, as applicable. (A) If no cracking was detected during any HFEC inspection accomplished prior to September 1, 1999 (the effective date of AD 99-16-01), and if Airbus Modification 07716 has not been accomplished: Inspect at the time specified in paragraph (g)(4)(ii)(A)(1) or (g)(4)(ii)(A)(2) of this AD, as applicable. (1) For airplanes having MSNs 465 through 553 inclusive: Inspect within 13,000 landings after the most recent HFEC inspection, and thereafter at intervals not to exceed 8,900 landings. Accomplishment of this inspection constitutes terminating action for the repetitive inspection requirement of paragraph (g)(2)(i)(A) of this AD. (2) For airplanes having MSNs 252 through 464 inclusive: Inspect within 8,400 landings after the most recent HFEC inspection, and thereafter at intervals not to exceed 5,500 landings. Accomplishment of this inspection constitutes terminating action for the repetitive inspection requirement of paragraph (g)(2)(i)(B) of this AD. (B) If any cracking was detected during any HFEC inspection performed prior to the effective date of this AD, regardless of the method of repair, or if Airbus Modification 07716 has been accomplished: Inspect at the time specified in paragraph (g)(4)(ii)(B)(1) or (g)(4)(ii)(B)(2) of this AD, as applicable. (1) For airplanes having MSNs 465 through 553 inclusive: Inspect within 11,800 landings after the most recent HFEC inspection, and thereafter at intervals not to exceed 8,200 landings. Accomplishment of this inspection constitutes terminating action for the repetitive inspection requirement of paragraph (g)(3)(i) or (g)(3)(ii) of this AD, as applicable. (2) For airplanes having MSNs 252 through 464 inclusive: Inspect within 10,700 landings after the initial inspection in accordance with paragraph (g)(1) of this AD, or within 7,500 landings after the most recent HFEC inspection, whichever occurs later, and thereafter at intervals not to exceed 4,900 landings. Accomplishment of this inspection constitutes terminating action for the repetitive inspection requirement of paragraph (g)(3)(i) or (g)(3)(ii) of this AD, as applicable. (5) If no cracking is detected during the ultrasonic inspection required by paragraph (g)(4)(i) of this AD, repeat that inspection thereafter at the time specified in paragraph (g)(5)(i) or (g)(5)(ii) of this AD, as applicable, until the initial ultrasonic inspection required by paragraph (h) of this AD is done. [[Page 37491]] (i) For airplanes having MSNs 465 through 553 inclusive: Repeat the inspection at intervals not to exceed 8,900 landings. (ii) For airplanes having MSNs 232 through 464 inclusive: Repeat the inspection at intervals not to exceed 5,500 landings. (6) If any cracking is detected during any inspection performed in accordance with the requirements of paragraph (g)(4) or (g)(5) of this AD: Prior to further flight, repair in accordance with a method approved by the Manager, International Branch, ANM-116; or the Direction G[eacute]n[eacute]rale de l'Aviation Civile (or its delegated agent); or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA). Note 1 to paragraph (g) of this AD: Airbus Service Bulletin A300-57-6017, Revision 01, including Appendix 1, dated July 25, 1994; and Airbus Service Bulletin A300-57-6017, Revision 04, including Appendix 1, dated February 24, 2011; also reference Airbus Service Bulletin A300-57-6020, dated November 22, 1993, as an additional source of service information for installation of oversize studs in the bolt holes. (h) New Repetitive Inspections At the applicable times specified in paragraph 1.B.(5), ``Accomplishment Timescale,'' of Airbus Service Bulletin A300-57- 6017, Revision 04, including Appendix 1, dated February 24, 2011: Do ultrasonic inspections to detect cracks in the MLG attachment fitting holes on the wing rear spar, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6017, Revision 04, including Appendix 1, dated February 24, 2011. Repeat the inspections thereafter at the applicable intervals specified in paragraph 1.B.(5), ``Accomplishment Timescale,'' of Airbus Service Bulletin A300-57-6017, Revision 04, including Appendix 1, dated February 24, 2011. For airplanes modified as specified in Airbus Service Bulletin A300-57-6073, the initial inspection threshold is counted from the completion date of the modification. Clarification of compliance time terminology used in table 1, ``Structural Inspection Program,'' of Airbus Service Bulletin A300-57-6017, Revision 04, including Appendix 1, dated February 24, 2011, is provided in paragraphs (h)(1) through (h)(4) of this AD. Accomplishment of the initial inspection terminates the repetitive inspections required by paragraph (g)(5) of this AD. (1) For pre-Airbus Modification 07716 or pre-Airbus Modification 11440 airplanes: (i) The term ``flight cycles'' in the ``Inspection Threshold'' column is total flight cycles accumulated by the airplane. (ii) The term ``flight hours'' in the ``Inspection Threshold'' column is total flight hours accumulated by the airplane. (2) For post-Airbus Modification 07716 airplanes: (i) The term ``flight cycles'' in the ``Inspection Threshold'' column is total flight cycles accumulated by the airplane. (ii) The term ``flight hours'' in the ``Inspection Threshold'' column is total flight hours accumulated by the airplane. (3) For post-Airbus Modification 11440 (Airbus Service Bulletin A300-57-6073) airplanes: (i) The term ``flight cycles'' in the ``Inspection Threshold'' column is flight cycles accumulated by the airplane after the modification was done. (ii) The term ``flight hours'' in the ``Inspection Threshold'' column is flight hours accumulated by the airplane after the modification was done. (4) For post-Airbus Modification 07601 airplanes: (i) The term ``flight cycles'' in the ``Inspection Threshold'' column is total flight cycles accumulated by the airplane. (ii) The term ``flight hours'' in the ``Inspection Threshold'' column is total flight hours accumulated by the airplane. (i) Repairs If any crack is found during any inspection required by paragraph (h) of this AD: Before further flight, repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the EASA; or Airbus's EASA DOA. (j) Non-Terminating Repair Accomplishment of any repair as required by paragraph (i) of this AD is not terminating action for the repetitive inspections required by paragraph (g) or (h) of this AD. (k) Credit for Previous Actions This paragraph provides credit for actions required by paragraphs (g) and (h) of this AD, if those actions were performed before the effective date of this AD using any of the following service information. (1) Airbus Service Bulletin A300-57-6017, dated November 22, 1993, which is not incorporated by reference in this AD. (2) Airbus Service Bulletin A300-57-6017, Revision 01, including Appendix 1, dated July 25, 1994, which was incorporated by reference in AD 95-20-02 and is retained in this AD. (3) Airbus Service Bulletin A300-57-6017, Revision 02, dated January 14, 1997, including Appendix 1, dated July 25, 1994, which is not incorporated by reference in this AD. (4) Airbus Service Bulletin A300-57-6017, Revision 03, including Appendix 1, dated November 19, 1997, which was incorporated by reference in AD 99-16-01, but is not retained in this AD. (l) 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 International Branch, send it to ATTN: Dan Rodina, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057- 3356; telephone: 425-227-2125; fax: 425-227-1149. Information may be emailed to: [email protected]. (i) 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. The AMOC approval letter must specifically reference this AD. (ii) AMOCs approved previously for AD 99-16-01 are approved as AMOCs for the corresponding provisions of this AD. (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. (m) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2013-0180, dated August 9, 2013, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov searching for and locating Docket No. FAA-2015-4813. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (n)(5) and (n)(6) of this AD. (n) 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 July 15, 2016. (i) Airbus Service Bulletin A300-57-6017, Revision 04, including Appendix 1, dated February 24, 2011. (ii) Reserved. (4) The following service information was approved for IBR on November 9, 1995 (60 FR 52618, October 10, 1995). (i) Airbus Service Bulletin A300-57-6017, Revision 01, including Appendix 1, dated July 25, 1994. (ii) Reserved. (5) For service information identified in this AD, contact Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email [email protected]; Internet http://www.airbus.com. (6) 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. (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 [[Page 37492]] 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html. Issued in Renton, Washington, on May 18, 2016. Dionne Palermo, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-12324 Filed 6-9-16; 8:45 am] BILLING CODE 4910-13-P
![37488 Federal Register / Vol. 81, No. 112 / Friday, June 10, 2016 / Rules and Regulations
(i) Fokker Service Bulletin SBF28–28–053, than initially determined. This new AD 98057–3356; telephone: 425–227–2125;
Revision 3, dated January 9, 2014. adds airplanes to the applicability, fax: 425–227–1149.
(ii) Reserved. reduces the compliance times and SUPPLEMENTARY INFORMATION:
(4) The following service information was repetitive intervals for the inspections,
approved for IBR on September 16, 2011 (76 Discussion
FR 50111, August 12, 2011).
and changes the inspection procedures.
(i) Fokker Service Bulletin SBF28–28–053, This AD was prompted by a We issued a notice of proposed
Revision 1, dated September 20, 2010. determination that the risk of cracking rulemaking (NPRM) to amend 14 CFR
(ii) Reserved. in the wing rear spar is higher than part 39 to supersede AD 99–16–01,
(5) For service information identified in initially determined. We are issuing this Amendment 39–11236 (64 FR 40743,
this AD, contact Fokker Services B.V., AD to detect and correct cracking of the July 28, 1999) (‘‘AD 99–16–01’’). AD 99–
Technical Services Dept., P.O. Box 1357, rear spar of the wing, which could result 16–01 superseded AD 95–20–02,
2130 EL Hoofddorp, the Netherlands; in reduced structural integrity of the Amendment 39–9380 (60 FR 52618,
telephone +31 (0)88–6280–350; fax +31 airplane. October 10, 1995). AD 99–16–01 applied
(0)88–6280–111; email technicalservices@ to certain Airbus Model A300 B4–600,
fokker.com; Internet http:// DATES: This AD becomes effective July B4–600R, and F4–600R series airplanes,
www.myfokkerfleet.com. 15, 2016.
(6) You may view this service information and Model A300 C4–605R Variant F
The Director of the Federal Register airplanes (collectively called Model
at the FAA, Transport Airplane Directorate,
1601 Lind Avenue SW., Renton, WA. For
approved the incorporation by reference A300–600 series airplanes). The NPRM
information on the availability of this of a certain publication listed in this AD published in the Federal Register on
material at the FAA, call 425–227–1221. as of July 15, 2016. November 17, 2015 (80 FR 71751) (‘‘the
(7) You may view this service information The Director of the Federal Register NPRM’’).
that is incorporated by reference at the approved the incorporation by reference The European Aviation Safety Agency
National Archives and Records of a certain other publication listed in (EASA), which is the Technical Agent
Administration (NARA). For information on this AD as of November 9, 1995 (60 FR for the Member States of the European
the availability of this material at NARA, call 52618, October 10, 1995). Union, has issued EASA Airworthiness
202–741–6030, or go to: http://
www.archives.gov/federal-register/cfr/ibr- ADDRESSES: For service information Directive 2013–0180, dated August 9,
locations.html. identified in this final rule, contact 2013 (referred to after this as the
Airbus SAS, Airworthiness Office— Mandatory Continuing Airworthiness
Issued in Renton, Washington, on May 31, Information, or ‘‘the MCAI’’), to correct
2016. EAW, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone an unsafe condition for certain Airbus
Michael Kaszycki, Model A300 B4–600, B4–600R, and F4–
+33 5 61 93 36 96; fax +33 5 61 93 44
Acting Manager, Transport Airplane 600R series airplanes, and Model A300
Directorate, Aircraft Certification Service. 51; email account.airworth-eas@
airbus.com; Internet http:// C4–605R Variant F airplanes
[FR Doc. 2016–13545 Filed 6–9–16; 8:45 am] (collectively called Model A300–600
www.airbus.com. You may view this
BILLING CODE 4910–13–P
referenced service information at the series airplanes). The MCAI states:
FAA, Transport Airplane Directorate, During full-scale fatigue testing, cracks
1601 Lind Avenue SW., Renton, WA. were found on the rear spar from certain bolt
DEPARTMENT OF TRANSPORTATION holes at the attachment of the Main Landing
For information on the availability of
this material at the FAA, call 425–227– gear (MLG) forward pick-up fitting and the
Federal Aviation Administration MLG Rib 5 aft.
1221. It is also available on the Internet This condition, if not detected and
14 CFR Part 39 at http://www.regulations.gov by corrected, could reduce the structural
searching for and locating Docket No. integrity of the aeroplane.
[Docket No. FAA–2015–4813; Directorate FAA–2015–4813. DGAC [Direction Générale de l’Aviation
Identifier 2013–NM–161–AD; Amendment Civile] France issued * * * [an AD] (later
39–18532; AD 2016–11–05] Examining the AD Docket revised) to require High Frequency Eddy
RIN 2120–AA64 You may examine the AD docket on Current (HFEC) or Ultrasonic (U/S)
the Internet at http:// inspections of certain fastener holes where
Airworthiness Directives; Airbus the MLG forward pick-up fitting and MLG
www.regulations.gov by searching for Rib 5 aft are attached to the rear spar.
Airplanes and locating Docket No. FAA–2015– Since DGAC France * * * [issued a
AGENCY: Federal Aviation 4813; or in person at the Docket revised AD, which corresponded to FAA AD
Administration (FAA), Department of Management Facility between 9 a.m. 99–16–01, Amendment 39–11236 (64 FR
and 5 p.m., Monday through Friday, 40743, July 28, 1999), which superseded
Transportation (DOT). FAA AD 95–20–02, Amendment 39–9380 (60
except Federal holidays. The AD docket
ACTION: Final rule. FR 52618, October 10, 1995)] * * *, a fleet
contains this AD, the regulatory
survey and updated Fatigue and Damage
SUMMARY: We are superseding evaluation, any comments received, and Tolerance analyses have been performed in
Airworthiness Directive (AD) 99–16–01 other information. The address for the order to substantiate the second A300–600
for certain Airbus Model A300 B4–600, Docket Office (telephone 800–647–5527) Extended Service Goal (ESG2) exercise. The
B4–600R, and F4–600R series airplanes, is Docket Management Facility, U.S. results of these analyses have shown that the
and Model A300 C4–605R Variant F Department of Transportation, Docket threshold and interval must be reduced to
Operations, M–30, West Building allow timely detection of these cracks and
airplanes (collectively called Model accomplishment of an applicable corrective
asabaliauskas on DSK3SPTVN1PROD with RULES
A300–600 series airplanes). AD 99–16– Ground Floor, Room W12–140, 1200
action.
01 required repetitive inspections of New Jersey Avenue SE., Washington, For the reasons described above, this
certain bolt holes where parts of the DC 20590. [EASA] AD retains the requirements of [the
main landing gear (MLG) are attached to FOR FURTHER INFORMATION CONTACT: Dan revised DGAC France AD], which is
the wing rear spar, and repair if Rodina, Aerospace Engineer, superseded, but reduces the related
necessary. Since we issued AD 99–16– International Branch, ANM–116, compliance times.
01, we have determined that the risk of Transport Airplane Directorate, FAA, The new, reduced threshold for the
cracking in the wing rear spar is higher 1601 Lind Avenue SW., Renton, WA initial inspection ranges between 8,900
VerDate Sep<11>2014 16:32 Jun 09, 2016 Jkt 238001 PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 E:\FR\FM\10JNR1.SGM 10JNR1](https://thefederalregister.org/doc/81_FR_37600/page/1.svg)
![Federal Register / Vol. 81, No. 112 / Friday, June 10, 2016 / Rules and Regulations 37489
total flight cycles/20,000 total flight We also estimate that it will take Adoption of the Amendment
hours, and 34,600 total flight cycles/ about 226 work-hours per product to Accordingly, under the authority
77,800 total flight hours, depending on comply with the new basic delegated to me by the Administrator,
the modification. The grace periods (750 requirements of this AD. The average the FAA amends 14 CFR part 39 as
or 1,500 landings) for airplanes that labor rate is $85 per work-hour. Based follows:
have exceeded the specified thresholds on these figures, we estimate the cost of
are unchanged from those provided in this AD on U.S. operators to be PART 39—AIRWORTHINESS
AD 99–16–01. The new, reduced $1,363,910, or $19,210 per product. DIRECTIVES
intervals for the repetitive inspections We have received no definitive data
range between 4,000 flight cycles/9,000 that will enable us to provide cost ■ 1. The authority citation for part 39
flight hours (whichever occurs first), estimates for the on-condition actions continues to read as follows:
and 8,900 flight cycles/20,000 flight specified in this AD. Authority: 49 U.S.C. 106(g), 40113, 44701.
hours (whichever occurs first),
depending on the modification. You Authority for This Rulemaking § 39.13 [Amended]
may examine the MCAI in the AD Title 49 of the United States Code ■ 2. The FAA amends § 39.13 by
docket on the Internet at http:// specifies the FAA’s authority to issue removing Airworthiness Directive (AD)
www.regulations.gov by searching for rules on aviation safety. Subtitle I, 99–16–01, Amendment 39–11236 (64
and locating Docket No. FAA–2015– section 106, describes the authority of FR 40743, July 28, 1999), and adding the
4813. the FAA Administrator. ‘‘Subtitle VII: following new AD:
Comments Aviation Programs,’’ describes in more 2016–11–05 Airbus: Amendment 39–18532;
detail the scope of the Agency’s Docket No. FAA–2015–4813; Directorate
We gave the public the opportunity to authority. Identifier 2013–NM–161–AD.
participate in developing this AD. We
We are issuing this rulemaking under (a) Effective Date
received no comments on the NPRM or
the authority described in ‘‘Subtitle VII, This AD becomes effective July 15, 2016.
on the determination of the cost to the
Part A, Subpart III, Section 44701:
public. (b) Affected ADs
General requirements.’’ Under that
Conclusion section, Congress charges the FAA with This AD replaces AD 99–16–01,
promoting safe flight of civil aircraft in Amendment 39–11236 (64 FR 40743, July 28,
We reviewed the available data and 1999) (‘‘AD 99–16–01’’).
determined that air safety and the air commerce by prescribing regulations
public interest require adopting this AD for practices, methods, and procedures (c) Applicability
as proposed except for minor editorial the Administrator finds necessary for This AD applies to Airbus Model A300 B4–
changes. We have determined that these safety in air commerce. This regulation 601, B4–603, B4–620, and B4–622 airplanes;
is within the scope of that authority Model A300 B4–605R and B4–622R
minor changes: airplanes; Model A300 F4–605R airplanes;
• Are consistent with the intent that because it addresses an unsafe condition
that is likely to exist or develop on and Model A300 C4–605R Variant F
was proposed in the NPRM for airplanes; certificated in any category; all
correcting the unsafe condition; and products identified in this rulemaking manufacturer serial numbers.
• Do not add any additional burden action.
(d) Subject
upon the public than was already Regulatory Findings
proposed in the NPRM. Air Transport Association (ATA) of
We determined that this AD will not America Code 57, Wings.
Related Service Information Under 1 have federalism implications under (e) Reason
CFR Part 51 Executive Order 13132. This AD will This AD was prompted by the results of a
We reviewed Airbus Service Bulletin not have a substantial direct effect on full-scale fatigue test when cracking was
A300–57–6017, Revision 04, including the States, on the relationship between found on the rear spar of the wing, and the
Appendix 1, dated February 4, 2011. the national government and the States, subsequent determination that the risk of
This service information describes or on the distribution of power and such cracking is higher than initially
procedures for repetitive inspections of responsibilities among the various determined. We are issuing this AD to detect
certain bolt holes where parts of the levels of government. and correct cracking of the rear spar of the
wing, which could result in reduced
MLG are attached to the wing rear spar, For the reasons discussed above, I structural integrity of the airplane.
and repair. This service information is certify that this AD:
reasonably available because the (f) Compliance
1. Is not a ‘‘significant regulatory
interested parties have access to it action’’ under Executive Order 12866; Comply with this AD within the
through their normal course of business compliance times specified, unless already
2. Is not a ‘‘significant rule’’ under the done.
or by the means identified in the
DOT Regulatory Policies and Procedures
ADDRESSES section. (g) Retained Inspections and Corrective
(44 FR 11034, February 26, 1979);
Actions, With Revised Service Information
Costs of Compliance 3. Will not affect intrastate aviation in
This paragraph restates the requirements of
We estimate that this AD affects 71 Alaska; and
paragraphs (a), (b), (c), (d), (e), and (f) of AD
airplanes of U.S. registry. 4. Will not have a significant 99–16–01 with revised service information
The actions required by AD 99–16–01 economic impact, positive or negative, and reduced thresholds and repetitive
asabaliauskas on DSK3SPTVN1PROD with RULES
and retained in this AD, take about 226 on a substantial number of small entities intervals, for Airbus Model A300 B4–600,
work-hours per product, at an average under the criteria of the Regulatory B4–600R, and F4–600R series airplanes, and
labor rate of $85 per work hour. Flexibility Act. Model A300 C4–605R Variant F airplanes;
manufacturer serial numbers (MSNs) 252
Required parts cost about $0 per List of Subjects in 14 CFR Part 39 through 553 inclusive; except those airplanes
product. Based on these figures, the on which Airbus Modification 07601 has
estimated cost of the actions that are Air transportation, Aircraft, Aviation been accomplished prior to delivery.
required by AD 99–16–01 is $19,210 per safety, Incorporation by reference, (1) Perform a high frequency eddy current
product, per inspection cycle. Safety. (HFEC) rototest inspection to detect cracks in
VerDate Sep<11>2014 16:32 Jun 09, 2016 Jkt 238001 PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 E:\FR\FM\10JNR1.SGM 10JNR1](https://thefederalregister.org/doc/81_FR_37600/page/2.svg)
![37492 Federal Register / Vol. 81, No. 112 / Friday, June 10, 2016 / Rules and Regulations
202–741–6030, or go to: http:// and locating Docket No. FAA–2015– We do not agree with the commenter.
www.archives.gov/federal-register/cfr/ibr- 2134; or in person at the Docket We believe that the replacement
locations.html. Management Facility between 9 a.m. compliance time of 18 months after the
Issued in Renton, Washington, on May 18, and 5 p.m., Monday through Friday, effective date of this AD is sufficient
2016. except Federal holidays. The AD docket time since we are allowing even more
Dionne Palermo, contains this AD, the regulatory time than specified in the related
Acting Manager, Transport Airplane evaluation, any comments received, and service information. Also, the public has
Directorate, Aircraft Certification Service. other information. The address for the been aware of this safety issue since we
[FR Doc. 2016–12324 Filed 6–9–16; 8:45 am] Docket Office (phone: 800–647–5527) is first published the first NPRM on June
BILLING CODE 4910–13–P Document Management Facility, U.S. 16, 2015 (80 FR 34330). We have not
Department of Transportation, Docket changed the final rule AD action based
Operations, M–30, West Building on this comment.
DEPARTMENT OF TRANSPORTATION Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington, Request To Correct Service Information
Federal Aviation Administration DC 20590. John Barker of B/E Aerospace stated
FOR FURTHER INFORMATION CONTACT: that Service Bulletin 119003–35–009,
14 CFR Part 39 David Enns, Aerospace Engineer, dated November 9, 2015, is incorrectly
Wichita Aircraft Certification Office, referenced as Rev. 009 instead of Rev.
[Docket No. FAA–2015–2134; Directorate
Identifier 2015–CE–012–AD; Amendment FAA, 1801 S. Airport Road, Room 100, 000 in the preamble of the SNPRM (81
39–18547; AD 2016–11–20] Wichita, Kansas 67209; phone: (316) FR 2131, January 15, 2016). The
946–4147; fax: (316) 946–4107; email: commenter requested the reference to
RIN 2120–AA64 david.enns@faa.gov. the revision number be corrected.
SUPPLEMENTARY INFORMATION: We agree with the commenter.
Airworthiness Directives; B/E However, on April 12, 2016, Rev. 001 of
Aerospace Protective Breathing Discussion B/E Aerospace Service Bulletin 119003–
Equipment Part Number 119003–11 35–009 was released. We are
We issued a supplemental notice of
AGENCY: Federal Aviation proposed rulemaking (SNPRM) to incorporating the Revision 001, dated
Administration (FAA), DOT. amend 14 CFR part 39 by adding an AD April 12, 2016, into the final rule AD
ACTION: Final rule. that would apply to certain B/E action because the procedures for doing
Aerospace protective breathing the inspection and replacement of the
SUMMARY: We are adopting a new equipment (PBE) that is installed on PBE have not changed.
airworthiness directive (AD) for certain airplanes. The SNPRM published in the We have changed the final rule AD
B/E Aerospace protective breathing Federal Register on January 15, 2016 action to include the newly revised
equipment (PBE) that is installed on (81 FR 2131). We preceded the SNPRM service bulletin and to give credit to
airplanes. This AD was prompted by a with a notice of proposed rulemaking owners/operators who may have already
report of a PBE catching fire upon (NPRM) that published in the Federal done the required replacement
activation by a crewmember. This AD Register on June 16, 2015 (80 FR 34330). following B/E Aerospace Service
requires replacing the PBE. We are The NPRM proposed to require Bulletin No. 119003–35–009, Rev. 000,
issuing this AD to correct the unsafe inspecting the PBE to determine if the dated November 9, 2015, which was
condition on these products. pouch has the proper vacuum seal and correctly referenced in paragraph (h) of
DATES: This AD is effective July 15,
replacing if necessary. The NPRM was the regulatory text in the SNPRM (81 FR
2016. prompted by a report of a PBE catching 2131, January 15, 2016).
The Director of the Federal Register fire upon activation by a crewmember.
Conclusion
approved the incorporation by reference The SNPRM proposed to require
replacement of the PBE following newly We reviewed the relevant data,
of certain publications listed in this AD considered the comments received, and
as of July 15, 2016. issued service information, regardless of
inspection results. We are issuing this determined that air safety and the
ADDRESSES: For service information public interest require adopting this AD
AD to correct the unsafe condition on
identified in this final rule, contact B/ these products. as proposed except for minor editorial
E Aerospace, Inc., Commercial Aircraft changes. We have determined that these
Products Group, 10800 Pflumm Road, Comments minor changes:
Lenexa, Kansas 66215; phone: (913) We gave the public the opportunity to • Are consistent with the intent that
338–9800; fax: (913) 338–8419; Internet: participate in developing this AD. We was proposed in the SNPRM (81 FR
www.beaerospace.com. You may view have considered the comments received. 2131, January 15, 2016) for correcting
this referenced service information at We received one anonymous comment the unsafe condition; and
the FAA, Small Airplane Directorate, in support of the SNPRM (81 FR 2131, • Do not add any additional burden
901 Locust, Kansas City, Missouri January 15, 2016). upon the public than was already
64106. For information on the proposed in the SNPRM (81 FR 2131,
availability of this material at the FAA, Request To Change Compliance Time January 15, 2016).
call (816) 329–4148. It is also available Penney Baudin of United Airlines
on the Internet at http:// requested a change to the PBE Related Service Information Under 1
asabaliauskas on DSK3SPTVN1PROD with RULES
www.regulations.gov by searching for replacement compliance time. CFR Part 51
and locating Docket No. FAA–2015– The commenter requested a 12-month We reviewed B/E Aerospace Service
2134. repetitive inspection with a 36-month Bulletin No. 119003–35–011, Rev. 000,
terminating replacement action. The dated February 4, 2015, and B/E
Examining the AD Docket commenter stated that the change would Aerospace Service Bulletin 119003–35–
You may examine the AD docket on alleviate restrictive shipping means and 009, Rev. 001, dated April 12, 2016. B/
the Internet at http:// complex distribution of the PBEs since E Aerospace Service Bulletin No.
www.regulations.gov by searching for the units contain oxygen generators. 119003–35–011, Rev. 000, dated
VerDate Sep<11>2014 16:32 Jun 09, 2016 Jkt 238001 PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 E:\FR\FM\10JNR1.SGM 10JNR1](https://thefederalregister.org/doc/81_FR_37600/page/5.svg)
Document Created: 2018-02-08 07:35:32
Document Modified: 2018-02-08 07:35:32
| 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 becomes effective July 15, 2016. | |
| Contact | Dan Rodina, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone: 425-227-2125; fax: 425-227-1149. | |
| FR Citation | 81 FR 37488 | |
| 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