80 FR 72565 - Airworthiness Directives; Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 80, Issue 224 (November 20, 2015)
Federal Aviation Administration
Federal Register Volume 80, Issue 224 (November 20, 2015)
| Page Range | 72565-72569 | |
| FR Document | 2015-28464 |
[Federal Register Volume 80, Number 224 (Friday, November 20, 2015)] [Rules and Regulations] [Pages 72565-72569] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2015-28464] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2014-0427; Directorate Identifier 2013-NM-218-AD; Amendment 39-18316; AD 2015-22-11] RIN 2120-AA64 Airworthiness Directives; Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are superseding Airworthiness Directive (AD) 2011-09-04 for all Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Model 382, 382B, 382E, 382F, and 382G airplanes. AD 2011-09-04 required repetitive inspections for damage to the lower surface of the center wing box (CWB), and corrective actions if necessary. This new AD adds related investigative actions, and corrective actions if necessary. This AD was prompted by an evaluation by the design approval holder (DAH) that indicated that the CWB is subject to widespread fatigue damage (WFD). We are issuing this AD to detect and correct fatigue cracking of the lower surface of the CWB, which could result in structural failure of the wings. DATES: This AD is effective December 28, 2015. The Director of the Federal Register approved the incorporation by reference [[Page 72566]] of a certain publication listed in this AD as of December 28, 2015. The Director of the Federal Register approved the incorporation by reference of a certain other publication listed in this AD as of June 22, 2011 (76 FR 28626, May 18, 2011). ADDRESSES: For service information identified in this AD, contact Lockheed Martin Corporation/Lockheed Martin Aeronautics Company, Airworthiness Office, Dept. 6A0M, Zone 0252, Column P-58, 86 S. Cobb Drive, Marietta, GA 30063; telephone 770-494-5444; fax 770-494-5445; email ams.portal@lmco.com; Internet http://www.lockheedmartin.com/ams/tools/TechPubs.html. 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-2014- 0427. Examining the AD Docket You may examine the AD docket on the Internet at http://www.regulations.govby searching for and locating Docket No. FAA-2014- 0427; 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 (phone: 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: Carl Gray, Aerospace Engineer, Airframe Branch, ACE-117A, FAA, Atlanta Aircraft Certification Office, 1701 Columbia Avenue, College Park, GA 30337; telephone 404-474-5554; fax 404-474-5605; email: carl.w.gray@faa.gov. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2011-09-04, Amendment 39-16666 (76 FR 28626, May 18, 2011). AD 2011-09-04 applied to all Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Model 382, 382B, 382E, 382F, and 382G airplanes. The NPRM published in the Federal Register on July 1, 2014 (79 FR 37248). The NPRM was prompted by an evaluation by the DAH that indicated that the CWB is subject to WFD. The NPRM proposed to continue to require repetitive inspections for any damage of the lower surface of the CWB, and corrective actions if necessary. The NPRM also proposed to require replacement of the CWB, and to add, for the repetitive inspections, concurrent related investigative actions, and corrective actions if necessary. We are issuing this AD to detect and correct fatigue cracking of the lower surface of the CWB, which could result in structural failure of the wings. Actions Since Issuance of the NPRM (79 FR 37248, July 1, 2014) The CWB replacement, proposed in the NPRM (79 FR 37248, July 1, 2014), has been removed from this final rule, and is instead required by AD 2015-18-02, Amendment 39-18260 (80 FR 52941, September 2, 2015). We determined that the proposed compliance time for the CWB replacement would not adequately address the unsafe condition, because the risk of undetected WFD rises rapidly for CWBs that have accumulated 50,000 total flight hours. Therefore, for airplanes over the 50,000-flight- hour threshold, AD 2015-18-02 provides a shorter grace period than that proposed in the NPRM. In this AD, we have removed paragraph (k) of the proposed AD and Note 1 to paragraph (k) of the proposed AD, and redesignated subsequent paragraphs accordingly. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments to the NPRM (79 FR 37248, July 1, 2014) related to the proposed inspection requirements, and the FAA's response to those comments. Since this AD does not include the CWB replacement proposed in paragraph (k) of the NPRM, this AD does not address comments regarding the CWB replacement. Those comments are addressed in AD 2015-18-02, Amendment 39-18260 (80 FR 52941, September 2, 2015). Support for the NPRM (79 FR 37248, July 1, 2014) Lynden Air Cargo (Lynden) stated that it concurs that the proposed inspections are beneficial and enhance safety. Request To Revise Proposed Applicability Lynden questioned whether the FAA considered the safety risk factor for ``restricted category type certificated Model C-130A through H airplanes'' and whether those airplanes should be included in the applicability. We did consider the safety risk factor for those airplanes. The FAA issued restricted-category type certificates only for Model C-130A and C-130B airplanes, and these are low-usage airplanes. The wings on Model C-130A airplanes are different from those of other models; the CWBs have previously been replaced on all Model C-130A airplanes. There are no civil registered Model C-130B airplanes in service. We might consider further rulemaking for Model C-130 airplanes. We have not changed this AD regarding this issue. Request To Revise Repair Approval Procedures Safair requested that we revise the NPRM (79 FR 37248, July 1, 2014) to authorize the DAH or designated engineering representative (DER) to develop and approve repairs under international operator support agreements with the state-of-registration civil authorities. We agree with the commenter's request. We have revised paragraphs (h), (i)(1)(ii), (j), and (k)(1) of this AD to require that certain repairs, alternative compliance times, and inspection methods be approved in accordance with the procedures specified in paragraph (m) of this AD, which allows DER approval for repairs as specified in new paragraph (m)(3) of this AD. Request To Require a Report of Inspection Findings Noting that the NPRM (79 FR 37248, July 1, 2014) would not require inspection reports, Safair suggested that Lockheed build a database of inspection findings. The commenter asserted that the data would not be collected unless mandated. It is not necessary to require operators to report inspection findings, as the Atlanta Aircraft Certification Office (ACO) already maintains a database for tracking repairs. The database includes repair reports from the U.S. as well as DER reports for airplanes outside of the U.S. We have not changed this AD in this regard. Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this AD with the changes described previously and minor editorial changes. We have determined that these minor changes:Are consistent with the intent that was proposed in the NPRM (79 FR 37248, July 1, 2014) for correcting the unsafe condition; and [[Page 72567]] Do not add any additional burden upon the public than was already proposed in the NPRM (79 FR 37248, July 1, 2014). We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. Related Service Information Under 1 CFR Part 51 We reviewed Lockheed Service Bulletin 382-57-85 (82-790), Revision 3, dated July 8, 2013, including Appendix A, Revision 3, dated July 8, 2013, and Appendixes B, C, D, E, F, and G, all Revision 1, all dated March 8, 2007. The service information describes procedures for inspecting the lower surface of the CWB. 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 of this AD. Costs of Compliance We estimate that this AD affects 15 airplanes of U.S. registry. We estimate the following costs to comply with this AD: Estimated Costs ---------------------------------------------------------------------------------------------------------------- Cost on U.S. Action Labor cost Parts cost Cost per product operators ---------------------------------------------------------------------------------------------------------------- Inspection [retained action from 2,000 work-hours x N/A $170,000 per $2,550,000 per AD 2011-09-04, Amendment 39- $85 per hour = inspection cycle. inspection cycle. 16666 (76 FR 28626, May 18, $170,000 per 2011)]. inspection cycle. ---------------------------------------------------------------------------------------------------------------- We have received no definitive data that would enable us to provide cost estimates for the related investigative actions specified in this AD. We estimate the following costs to do any necessary repair that would be required. We have no way of determining the number of aircraft that might need this repair: On-Condition Costs ---------------------------------------------------------------------------------------------------------------- Action Labor cost Parts cost Cost per product ---------------------------------------------------------------------------------------------------------------- Repair [retained from AD 2011-09-04, 1,000 to 3,000 work-hours $30,000 $115,000 to $285,000. Amendment 39-16666 (76 FR 28626, May x $85 per hour = $85,000 18, 2011)]. to $255,000. ---------------------------------------------------------------------------------------------------------------- Authority for This Rulemaking Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, Section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency's authority. We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701, ``General requirements.'' Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We have determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: (1) Is not a ``significant regulatory action'' under Executive Order 12866, (2) Is not a ``significant rule'' under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation in Alaska, and (4) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39--AIRWORTHINESS DIRECTIVES 0 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD) 2011-09-04, Amendment 39-16666 (76 FR 28626, May 18, 2011), and adding the following new AD: 2015-22-11 Lockheed Martin Corporation/Lockheed Martin Aeronautics Company: Amendment 39-18316; Docket No. FAA-2014-0427; Directorate Identifier 2013-NM-218-AD. (a) Effective Date This AD is effective December 28, 2015. (b) Affected ADs This AD replaces AD 2011-09-04, Amendment 39-16666 (76 FR 28626, May 18, 2011). (c) Applicability This AD applies to all Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Model 382, 382B, 382E, 382F, and 382G airplanes, certificated in any category. (d) Subject Air Transport Association (ATA) of America Code 57, Wings. (e) Unsafe Condition This AD was prompted by an evaluation by the design approval holder (DAH) that indicated the center wing box (CWB) is subject to widespread fatigue damage (WFD). We are issuing this AD to detect and correct [[Page 72568]] fatigue cracking of the lower surface of the CWB, which could result in structural failure of the wings. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Inspection, With Revised Service Information This paragraph restates the actions required by paragraph (g) of AD 2011-09-04, Amendment 39-16666 (76 FR 28626, May 18, 2011), with revised service information. At the time specified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD, whichever occurs latest: Do a nondestructive inspection of the lower surface of the CWB for any damage, in accordance with Lockheed Service Bulletin 382-57-85 (82- 790), Revision 2, dated August 23, 2007, including Appendixes A, B, C, D, E, F, and G, all Revision 1, all dated March 8, 2007; or Lockheed Service Bulletin 382-57-85 (82-790), Revision 3, dated July 8, 2013, including Appendix A, Revision 3, dated July 8, 2013, and Appendixes B, C, D, E, F, and G, all Revision 1, all dated March 8, 2007. Repeat the inspections thereafter at intervals not to exceed 10,000 flight hours. As of the effective date of this AD, use only Lockheed Service Bulletin 382-57-85 (82-790), Revision 3, dated July 8, 2013, including Appendix A, Revision 3, dated July 8, 2013, and Appendixes B, C, D, E, F, and G, all Revision 1, all dated March 8, 2007, for the actions required by this paragraph. (1) Prior to the accumulation of 40,000 total flight hours on the center wing. (2) Within 365 days after June 22, 2011 (the effective date of AD 2011-09-04, Amendment 39-16666 (76 FR 28626, May 18, 2011)). (3) Within 10,000 flight hours on the CWB after the accomplishment of the inspection specified in paragraph (g) of this AD, if done before June 22, 2011 (the effective date of AD 2011-09- 04, Amendment 39-16666 (76 FR 28626, May 18, 2011)). (h) Retained Corrective Action, With Revised Repair Instructions This paragraph restates the actions required by paragraph (h) of AD 2011-09-04, Amendment 39-16666 (76 FR 28626, May 18, 2011), with revised repair instructions. If any damage is found before the effective date of this AD during any inspection required by paragraph (g) of this AD: Before further flight, repair any damage, using a method approved by the Manager, Atlanta Aircraft Certification Office (ACO), FAA. If any damage is found as of the effective date of this AD, during any inspection required by paragraph (g) of this AD: Before further flight, repair using a method approved in accordance with the procedures specified in paragraph (m) of this AD. (i) Retained Exceptions to Service Information Specifications, With Revised Repair Instructions (1) This paragraph restates the exception specified in paragraph (i) of AD 2011-09-04, Amendment 39-16666 (76 FR 28626, May 18, 2011), with revised repair instructions. Lockheed Service Bulletin 382-57-85 (82-790), Revision 2, dated August 23, 2007, including Appendixes A, B, C, D, E, F, and G, all Revision 1, all dated March 8, 2007, specifies that operators may adjust thresholds and intervals, use alternative repetitive inspection intervals, and use alternative inspection methods, if applicable. However, this AD requires the applicable approval specified in paragraph (i)(1)(i) or (i)(1)(ii) of this AD. (i) Before the effective date of this AD: This AD requires that any alternative methods or intervals be approved by the Manager, Atlanta ACO. For any alternative methods or intervals to be approved by the Manager, Atlanta ACO, as required by this paragraph, the Manager's approval letter must specifically refer to this AD. (ii) As of the effective date of this AD, this AD requires that any alternative methods or intervals be approved in accordance with the procedures specified in paragraph (m) of this AD. (2) This paragraph restates the exception stated in paragraph (j) of AD 2011-09-04, Amendment 39-16666 (76 FR 28626, May 18, 2011), with no changes. Where Lockheed Service Bulletin 382-57-85 (82-790), Revision 2, dated August 23, 2007, including Appendixes A, B, C, D, E, F, and G, all Revision 1, all dated March 8, 2007, specifies that alternative repetitive inspection intervals may be used for cold-worked holes, this AD does not allow the longer interval. This AD requires that all cold-worked and non-cold-worked holes be reinspected at 10,000-flight-hour intervals. (3) This paragraph restates the exception stated in paragraph (k) of AD 2011-09-04, Amendment 39-16666 (76 FR 28626, May 18, 2011), with no changes. Where Lockheed Service Bulletin 382-57-85 (82-790), Revision 2, dated August 23, 2007, including Appendixes A, B, C, D, E, F, and G, all Revision 1, all dated March 8, 2007, describes procedures for submitting a report of any damages, this AD does not require such action. (j) New Inspection and Corrective Actions As of the effective date of this AD, concurrently with accomplishing the inspection required by paragraph (g) of this AD: Do all applicable related investigative actions, in accordance with Appendix A, Revision 3, dated July 8, 2013, of Lockheed Service Bulletin 382-57-85 (82-790), Revision 3, dated July 8, 2013, including Appendix A, Revision 3, dated July 8, 2013, and Appendixes B, C, D, E, F, and G, all Revision 1, all dated March 8, 2007. If any cracking or damage is found during any related investigative action: Before further flight, repair all cracking and damage, using a method approved in accordance with the procedures specified in paragraph (m) of this AD. (k) New Exceptions to Service Information Specifications (1) Lockheed Service Bulletin 382-57-85 (82-790), Revision 3, dated July 8, 2013, including Appendix A, Revision 3, dated July 8, 2013, and Appendixes B, C, D, E, F, and G, all Revision 1, all dated March 8, 2007, specifies that operators may adjust thresholds and intervals, use alternative repetitive inspection intervals, and use alternative inspection methods. However, this AD requires that any alternative thresholds, intervals, or inspection methods be approved in accordance with the procedures specified in paragraph (m) of this AD. (2) Where Lockheed Service Bulletin 382-57-85 (82-790), Revision 3, dated July 8, 2013, including Appendix A, Revision 3, dated July 8, 2013, and Appendixes B, C, D, E, F, and G, all Revision 1, all dated March 8, 2007, describes procedures for submitting a report of any damages, this AD does not require such action. (l) Credit for Previous Actions (1) This paragraph restates the credit provided in paragraph (l) of AD 2011-09-04, Amendment 39-16666 (76 FR 28626, May 18, 2011). This paragraph provides credit for the actions required by paragraph (g) of this AD, if those actions were performed before June 22, 2011 (the effective date of AD 2011-09-04), using Lockheed Service Bulletin 382-57-85 (82-790), Revision 1, dated March 8, 2007, which is not incorporated by reference in this AD. (2) This paragraph restates the credit provided in paragraph (m) of AD 2011-09-04, Amendment 39-16666 (76 FR 28626, May 18, 2011). This paragraph provides credit for the actions required by paragraph (g) of this AD, if those actions were performed before June 22, 2011 (the effective date of AD 2011-09-04), using Lockheed Service Bulletin 382-57-85 (82-790), dated August 4, 2005, which is not incorporated by reference in this AD. (m) Alternative Methods of Compliance (AMOCs) (1) The Manager, Atlanta ACO, 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 ACO, send it to the attention of the person identified in paragraph (n)(1) of this AD. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. (3) An AMOC that provides an acceptable level of safety may be used for any repair required by this AD, if it is approved by a Delegated Engineering Representative (DER) for the Lockheed Martin Aeronautics Company who has been authorized by the Manager, Atlanta ACO, to make those findings. For a repair method to be approved, the repair approval must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (n) Related Information (1) For more information about this AD, contact Carl Gray, Aerospace Engineer, Airframe Branch, ACE-117A, FAA, Atlanta Aircraft Certification Office, 1701 Columbia Avenue, College Park, GA 30337; telephone 404-474-5554; fax 404-474-5605; email: carl.w.gray@faa.gov. [[Page 72569]] (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (o)(5) and (o)(6) of this AD. (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 the AD specifies otherwise. (3) The following service information was approved for IBR on December 28, 2015. (i) Lockheed Service Bulletin 382-57-85 (82-790), Revision 3, dated July 8, 2013, including Appendix A, Revision 3, dated July 8, 2013, and Appendixes B, C, D, E, F, and G, all Revision 1, all dated March 8, 2007. (ii) Reserved. (4) The following service information was approved for IBR on June 22, 2011 (76 FR 28626, May 18, 2011). (i) Lockheed Service Bulletin 382-57-85 (82-790), Revision 2, dated August 23, 2007, including Appendixes A, B, C, D, E, F, and G, all Revision 1, all dated March 8, 2007. (ii) Reserved. (5) For Lockheed Martin Corporation/Lockheed Martin Aeronautics Company service information identified in this AD, contact Lockheed Martin Corporation/Lockheed Martin Aeronautics Company, Airworthiness Office, Dept. 6A0M, Zone 0252, Column P-58, 86 S. Cobb Drive, Marietta, GA 30063; telephone 770-494-5444; fax 770-494-5445; email ams.portal@lmco.com; Internet http://www.lockheedmartin.com/ams/tools/TechPubs.html. (6) 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. (7) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to http://www.archives.gov/federal-register/cfr/ibr-locations.html. Issued in Renton, Washington, on October 29, 2015. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015-28464 Filed 11-19-15; 8:45 am] BILLING CODE 4910-13-P
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(c) Applicability FAA, has the authority to approve AMOCs 49 18 57; email: none; Internet: http://asi-
This AD applies to Reims Aviation S.A. for this AD, if requested using the procedures aviation.fr/asi-aviation-support/1.html
Model F406 airplanes, serial numbers 0001 found in 14 CFR 39.19. Send information to (requires user name and password).
through 0098, certificated in any category. ATTN: Albert J. Mercado, Aerospace (5) You may view this service information
Engineer, FAA, Small Airplane Directorate, at the FAA, Small Airplane Directorate, 901
(d) Subject 901 Locust, Room 301, Kansas City, Missouri Locust, Kansas City, Missouri 64106. For
Air Transport Association of America 64106; telephone: (816) 329–4119; fax: (816) information on the availability of this
(ATA) Code 27: Flight Controls. 329–4090; email: albert.mercado@faa.gov. material at the FAA, call (816) 329–4148. It
Before using any approved AMOC on any is also available on the Internet at http://
(e) Reason airplane to which the AMOC applies, notify www.regulations.gov by searching for
This AD was prompted by mandatory your appropriate principal inspector (PI) in locating Docket No. FAA–2015–3398.
continuing airworthiness information (MCAI) the FAA Flight Standards District Office (6) You may view this service information
originated by an aviation authority of another (FSDO), or lacking a PI, your local FSDO. that is incorporated by reference at the
country to identify and correct an unsafe (2) Airworthy Product: For any requirement National Archives and Records
condition on an aviation product. The MCAI in this AD to obtain corrective actions from Administration (NARA). For information on
describes the unsafe condition as detachment a manufacturer or other source, use these the availability of this material at NARA, call
of the pilot’s rudder control pedal in flight. actions if they are FAA-approved. Corrective 202–741–6030, or go to: http://
We are issuing this AD to detect and correct actions are considered FAA-approved if they www.archives.gov/federal-register/cfr/ibr-
cracking of the pilot rudder control pedal are approved by the State of Design Authority locations.html.
which, if not corrected, could result in (or their delegated agent). You are required
Issued in Kansas City, Missouri, on
detachment of the pedal with possible loss of to assure the product is airworthy before it
November 6, 2015.
airplane directional control. is returned to service.
(3) Reporting Requirements: For any Melvin Johnson,
(f) Actions and Compliance Acting Manager, Small Airplane Directorate,
reporting requirement in this AD, a federal
Unless already done, do the actions in agency may not conduct or sponsor, and a Aircraft Certification Service.
paragraphs (f)(1) through (f)(4) of this AD. person is not required to respond to, nor [FR Doc. 2015–29200 Filed 11–19–15; 8:45 am]
(1) Before further flight after August 18, shall a person be subject to a penalty for BILLING CODE 4910–13–P
2015 (the effective date retained from AD failure to comply with a collection of
2015–16–07), do a visual inspection and a information subject to the requirements of
dye or fluorescent penetrant inspection of the the Paperwork Reduction Act unless that
rudder control pedal torque tubes, LH (Part DEPARTMENT OF TRANSPORTATION
collection of information displays a current
Number (P/N) 5115260–1) and RH (P/N valid OMB Control Number. The OMB
5115260–2), following the instructions of Federal Aviation Administration
Control Number for this information
PART A of ASI AVIATION Service Bulletin collection is 2120–0056. Public reporting for
No.: F406–104, dated July 28, 2015. this collection of information is estimated to 14 CFR Part 39
(2) If no crack is detected during the be approximately 5 minutes per response, [Docket No. FAA–2014–0427; Directorate
inspection required by paragraph (f)(1) of this including the time for reviewing instructions, Identifier 2013–NM–218–AD; Amendment
AD, within 100 hours time-in-service (TIS) completing and reviewing the collection of 39–18316; AD 2015–22–11]
after August 18, 2015 (the effective date information. All responses to this collection
retained from AD 2015–16–07), do a of information are mandatory. Comments RIN 2120–AA64
magnetic particle inspection of the rudder concerning the accuracy of this burden and
control pedal torque tubes, LH (P/N suggestions for reducing the burden should Airworthiness Directives; Lockheed
5115260–1) and RH (P/N 5115260–2), be directed to the FAA at: 800 Independence Martin Corporation/Lockheed Martin
following the instructions of PART B of ASI Ave. SW., Washington, DC 20591, Attn: Aeronautics Company Airplanes
AVIATION Service Bulletin No.: F406–104, Information Collection Clearance Officer,
dated July 28, 2015. AES–200. AGENCY: Federal Aviation
(3) If any crack is detected on a rudder Administration (FAA), DOT.
control pedal torque tube during the (h) Related Information
ACTION: Final rule.
inspection required by paragraph (f)(1) or Refer to MCAI European Aviation Safety
(f)(2) of this AD, before further flight, replace Agency (EASA) AD No.: 2015–0159–E, dated SUMMARY: We are superseding
the affected part with a serviceable part July 31, 2015, and EASA AD No.: 2015– Airworthiness Directive (AD) 2011–09–
following the instructions of ASI AVIATION 0159R1, dated August 24, 2015, for related 04 for all Lockheed Martin Corporation/
Service Bulletin No.: F406–104, dated July information. You may examine the MCAI on
28, 2015. the Internet at http://www.regulations.gov by
Lockheed Martin Aeronautics Company
(4) For the purpose of this AD, a searching for and locating Docket No. FAA– Model 382, 382B, 382E, 382F, and 382G
serviceable part is: 2015–3398. airplanes. AD 2011–09–04 required
(i) A rudder control pedal torque tube (LH repetitive inspections for damage to the
P/N 5115260–1 or RH P/N 5115260–2) that (i) Material Incorporated by Reference lower surface of the center wing box
has had a magnetic particle inspection (1) The Director of the Federal Register (CWB), and corrective actions if
following the instructions of PART B of ASI approved the incorporation by reference necessary. This new AD adds related
AVIATION Service Bulletin No.: F406–104, (IBR) of the service information listed in this investigative actions, and corrective
dated July 28, 2015, and no cracks were paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
actions if necessary. This AD was
found; or
(ii) A new rudder control pedal torque tube (2) You must use this service information prompted by an evaluation by the
(LH P/N 5115260–1 or RH P/N 5115260–2) as applicable to do the actions required by design approval holder (DAH) that
that has never been installed on an airplane. this AD, unless the AD specifies otherwise. indicated that the CWB is subject to
(5) You may install a rudder control pedal (3) The following service information was widespread fatigue damage (WFD). We
torque tube P/N 5115260–1 (LH) or P/N approved for IBR on August 18, 2015 (80 FR are issuing this AD to detect and correct
5115260–2 (RH) on an airplane, provided it 49127). fatigue cracking of the lower surface of
tkelley on DSK3SPTVN1PROD with RULES
is a serviceable part. (i) ASI AVIATION Service Bulletin No.: the CWB, which could result in
F406–104, dated July 28, 2015. structural failure of the wings.
(g) Other FAA AD Provisions (ii) Reserved.
The following provisions also apply to this (4) For service information identified in DATES: This AD is effective December
AD: this AD, contact ASI Aviation, Aérodrome de 28, 2015.
(1) Alternative Methods of Compliance Reims Prunay, 51360 Prunay, FRANCE; The Director of the Federal Register
(AMOCs): The Manager, Standards Office, telephone: +33 3 26 48 46 65; fax: +33 3 26 approved the incorporation by reference
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• Do not add any additional burden Related Service Information Under 1 information is reasonably available
upon the public than was already CFR Part 51 because the interested parties have
proposed in the NPRM (79 FR 37248, We reviewed Lockheed Service access to it through their normal course
July 1, 2014). Bulletin 382–57–85 (82–790), Revision of business or by the means identified
We also determined that these 3, dated July 8, 2013, including in the ADDRESSES section of this AD.
changes will not increase the economic Appendix A, Revision 3, dated July 8, Costs of Compliance
burden on any operator or increase the 2013, and Appendixes B, C, D, E, F, and
G, all Revision 1, all dated March 8, We estimate that this AD affects 15
scope of this AD.
2007. The service information describes airplanes of U.S. registry.
procedures for inspecting the lower We estimate the following costs to
surface of the CWB. This service comply with this AD:
ESTIMATED COSTS
Action Labor cost Parts cost Cost per product Cost on U.S. operators
Inspection [retained action 2,000 work-hours × $85 per N/A $170,000 per inspection cycle $2,550,000 per inspection
from AD 2011–09–04, hour = $170,000 per in- cycle.
Amendment 39–16666 (76 spection cycle.
FR 28626, May 18, 2011)].
We have received no definitive data estimates for the related investigative required. We have no way of
that would enable us to provide cost actions specified in this AD. determining the number of aircraft that
We estimate the following costs to do might need this repair:
any necessary repair that would be
ON-CONDITION COSTS
Action Labor cost Parts cost Cost per product
Repair [retained from AD 2011–09–04, 1,000 to 3,000 work-hours × $85 per $30,000 $115,000 to $285,000.
Amendment 39–16666 (76 FR 28626, hour = $85,000 to $255,000.
May 18, 2011)].
Authority for This Rulemaking responsibilities among the various § 39.13 [Amended]
Title 49 of the United States Code levels of government. ■ 2. The FAA amends § 39.13 by
specifies the FAA’s authority to issue For the reasons discussed above, I removing Airworthiness Directive (AD)
rules on aviation safety. Subtitle I, certify that this AD: 2011–09–04, Amendment 39–16666 (76
(1) Is not a ‘‘significant regulatory FR 28626, May 18, 2011), and adding
Section 106, describes the authority of
action’’ under Executive Order 12866, the following new AD:
the FAA Administrator. Subtitle VII, (2) Is not a ‘‘significant rule’’ under
Aviation Programs, describes in more DOT Regulatory Policies and Procedures 2015–22–11 Lockheed Martin Corporation/
detail the scope of the Agency’s (44 FR 11034, February 26, 1979), Lockheed Martin Aeronautics Company:
authority. (3) Will not affect intrastate aviation Amendment 39–18316; Docket No.
We are issuing this rulemaking under in Alaska, and
FAA–2014–0427; Directorate Identifier
the authority described in Subtitle VII, 2013–NM–218–AD.
(4) Will not have a significant
Part A, Subpart III, Section 44701, economic impact, positive or negative, (a) Effective Date
‘‘General requirements.’’ Under that on a substantial number of small entities This AD is effective December 28, 2015.
section, Congress charges the FAA with under the criteria of the Regulatory
promoting safe flight of civil aircraft in (b) Affected ADs
Flexibility Act.
air commerce by prescribing regulations This AD replaces AD 2011–09–04,
for practices, methods, and procedures List of Subjects in 14 CFR Part 39 Amendment 39–16666 (76 FR 28626, May 18,
the Administrator finds necessary for Air transportation, Aircraft, Aviation 2011).
safety in air commerce. This regulation safety, Incorporation by reference, (c) Applicability
is within the scope of that authority Safety. This AD applies to all Lockheed Martin
because it addresses an unsafe condition Corporation/Lockheed Martin Aeronautics
that is likely to exist or develop on Adoption of the Amendment
Company Model 382, 382B, 382E, 382F, and
products identified in this rulemaking Accordingly, under the authority 382G airplanes, certificated in any category.
action. delegated to me by the Administrator,
(d) Subject
the FAA amends 14 CFR part 39 as
Regulatory Findings Air Transport Association (ATA) of
follows:
We have determined that this AD will America Code 57, Wings.
tkelley on DSK3SPTVN1PROD with RULES
not have federalism implications under PART 39—AIRWORTHINESS (e) Unsafe Condition
Executive Order 13132. This AD will DIRECTIVES This AD was prompted by an evaluation by
not have a substantial direct effect on the design approval holder (DAH) that
the States, on the relationship between ■ 1. The authority citation for part 39
indicated the center wing box (CWB) is
the national government and the States, continues to read as follows: subject to widespread fatigue damage (WFD).
or on the distribution of power and Authority: 49 U.S.C. 106(g), 40113, 44701. We are issuing this AD to detect and correct
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![Federal Register / Vol. 80, No. 224 / Friday, November 20, 2015 / Rules and Regulations 72569
(2) Service information identified in this DEPARTMENT OF TRANSPORTATION SW., Renton, WA. For information on
AD that is not incorporated by reference is the availability of this material at the
available at the addresses specified in Federal Aviation Administration FAA, call 425–227–1221. It is also
paragraphs (o)(5) and (o)(6) of this AD. available on the Internet at http://
(o) Material Incorporated by Reference
14 CFR Part 39 www.regulations.gov by searching for
[Docket No. FAA–2014–1043; Directorate and locating Docket No. FAA–2014–
(1) The Director of the Federal Register 1043.
approved the incorporation by reference Identifier 2013–NM–079–AD; Amendment
39–18321; AD 2015–23–05] FOR FURTHER INFORMATION CONTACT:
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR RIN 2120–AA64 Vladimir Ulyanov, Aerospace Engineer,
part 51. International Branch, ANM–116,
(2) You must use this service information Airworthiness Directives; Airbus Transport Airplane Directorate, FAA,
as applicable to do the actions required by Airplanes 1601 Lind Avenue SW., Renton, WA
this AD, unless the AD specifies otherwise. 98057–3356; telephone 425–227–1138;
AGENCY: Federal Aviation fax 425–227–1149.
(3) The following service information was
Administration (FAA), Department of
approved for IBR on December 28, 2015. SUPPLEMENTARY INFORMATION:
(i) Lockheed Service Bulletin 382–57–85
Transportation (DOT).
(82–790), Revision 3, dated July 8, 2013, ACTION: Final rule. Discussion
including Appendix A, Revision 3, dated July We issued a notice of proposed
SUMMARY: We are adopting a new rulemaking (NPRM) to amend 14 CFR
8, 2013, and Appendixes B, C, D, E, F, and
airworthiness directive (AD) for all part 39 by adding an AD that would
G, all Revision 1, all dated March 8, 2007.
Airbus Model A330–200, A330–200 apply to all Airbus Model A330–200,
(ii) Reserved.
(4) The following service information was
Freighter, and A330–300 series A330–200 Freighter, and A330–300
approved for IBR on June 22, 2011 (76 FR
airplanes; and Model A340–200 and series airplanes; and Model A340–200
28626, May 18, 2011). A340–300 series airplanes. This AD was and A340–300 series airplanes. The
(i) Lockheed Service Bulletin 382–57–85 prompted by reports of cracked support NPRM published in the Federal
(82–790), Revision 2, dated August 23, 2007, strut body ends at a certain frame Register on January 23, 2015 (80 FR
including Appendixes A, B, C, D, E, F, and location of the trimmable horizontal 3510). The NPRM was prompted by
G, all Revision 1, all dated March 8, 2007. stabilizer (THS). This AD requires reports of cracked support strut body
(ii) Reserved. repetitive inspections for cracking of the ends at a certain frame location of the
(5) For Lockheed Martin Corporation/ strut ends of the THS support located at THS. The NPRM proposed to require
Lockheed Martin Aeronautics Company a certain frame in the tail cone, and repetitive inspections for cracking of the
service information identified in this AD, replacement if necessary; and strut ends of the THS support located at
contact Lockheed Martin Corporation/ reinstallation or installation of a certain frame in the tail cone, and
Lockheed Martin Aeronautics Company, reinforcing clamps on certain strut ends. replacement if necessary; and
Airworthiness Office, Dept. 6A0M, Zone We are issuing this AD to detect and reinstallation or installation of
0252, Column P–58, 86 S. Cobb Drive, correct cracked support strut body ends reinforcing clamps on certain strut ends.
Marietta, GA 30063; telephone 770–494– of the THS, which could lead to the loss We are issuing this AD to detect and
5444; fax 770–494–5445; email ams.portal@ of all four THS support struts, making correct cracked support strut body ends
lmco.com; Internet http:// the remaining structure unable to carry of the THS, which could lead to the loss
www.lockheedmartin.com/ams/tools/ limit loads, resulting in the loss of the of all four THS support struts, making
TechPubs.html. horizontal tail plane. the remaining structure unable to carry
(6) You may view this referenced service DATES: This AD becomes effective limit loads, resulting in the loss of the
information at the FAA, Transport Airplane December 28, 2015. horizontal tail plane.
Directorate, 1601 Lind Avenue SW., Renton, The Director of the Federal Register The European Aviation Safety Agency
WA. For information on the availability of approved the incorporation by reference (EASA), which is the Technical Agent
this material at the FAA, call 425–227–1221. of certain publications listed in this AD for the Member States of the European
(7) You may view this service information as of December 28, 2015. Union, has issued EASA Airworthiness
that is incorporated by reference at the
ADDRESSES: You may examine the AD Directive 2014–0068, dated March 18,
National Archives and Records
docket on the Internet at http:// 2014 (referred to after this as the
Administration (NARA). For information on
www.regulations.gov/ Mandatory Continuing Airworthiness
the availability of this material at NARA, call
#!docketDetail;D=FAA-2014-1043 or in Information, or ‘‘the MCAI’’), to correct
202–741–6030, or go to http://
person at the Docket Management an unsafe condition for all Airbus
www.archives.gov/federal-register/cfr/ibr-
Facility, U.S. Department of Model A330–200, A330–200 Freighter,
locations.html.
Transportation, Docket Operations, M– and A330–300 series airplanes; and
Issued in Renton, Washington, on October 30, West Building Ground Floor, Room Model A340–200 and A340–300 series
29, 2015. W12–140, 1200 New Jersey Avenue SE., airplanes. The MCAI states:
Jeffrey E. Duven, Washington, DC. During scheduled maintenance on A330
Manager, Transport Airplane Directorate, For service information identified in aeroplanes, several Trimmable Horizontal
Aircraft Certification Service. this AD, contact Airbus SAS, Stabilizer (THS) support struts at frame (FR)
[FR Doc. 2015–28464 Filed 11–19–15; 8:45 am] Airworthiness Office—EAL, 1 Rond 91 were found cracked at strut body ends.
Point Maurice Bellonte, 31707 Blagnac The THS is supported and articulated at FR
BILLING CODE 4910–13–P
Cedex, France; telephone +33 5 61 93 36 91 by four struts to fix the hinges (Y-bolts)
tkelley on DSK3SPTVN1PROD with RULES
and keep the structural integrity in lateral
96; fax +33 5 61 93 45 80; email
direction.
airworthiness.A330–A340@airbus.com; Analysis revealed that cracks can reduce
Internet http://www.airbus.com. You ability of the support struts to carry specified
may view this referenced service tension loads.
information at the FAA, Transport This condition, if not detected and
Airplane Directorate, 1601 Lind Avenue corrected, could lead to the loss of all four
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Document Created: 2015-12-14 13:58:58
Document Modified: 2015-12-14 13:58:58
| 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 December 28, 2015. | |
| Contact | Carl Gray, Aerospace Engineer, Airframe Branch, ACE-117A, FAA, Atlanta Aircraft Certification Office, 1701 Columbia Avenue, College Park, GA 30337; telephone 404-474-5554; fax 404-474-5605; email: [email protected] | |
| FR Citation | 80 FR 72565 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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