80 FR 19013 - Airworthiness Directives; Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 80, Issue 68 (April 9, 2015)
Federal Aviation Administration
Federal Register Volume 80, Issue 68 (April 9, 2015)
| Page Range | 19013-19017 | |
| FR Document | 2015-06785 |
[Federal Register Volume 80, Number 68 (Thursday, April 9, 2015)] [Rules and Regulations] [Pages 19013-19017] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2015-06785] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2014-0627; Directorate Identifier 2013-NM-217-AD; Amendment 39-18126; AD 2015-06-08] 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) 2011-09-03 for all Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Model 382, 382B, 382E, 382F, and 382G airplanes. AD 2011-09-03 required repetitive eddy current inspections to detect cracks in the center wing upper and lower rainbow fittings, and corrective actions if necessary; and repetitive replacement of rainbow fittings, which would extend the repetitive interval for the next inspection. This new AD requires reduced intervals for inspections of the upper rainbow fittings. This AD was prompted by analysis of in-service cracking, which has shown that a reduction in the inspection intervals is necessary for the upper rainbow fittings. We are issuing this AD to detect and correct fatigue cracking of the upper and lower rainbow fittings on the center wings, which could grow large and lead to the failure of the fitting and a catastrophic failure of the center wing. DATES: This AD is effective May 14, 2015. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of May 14, 2015. The Director of the Federal Register approved the incorporation by reference of a certain other publication listed in this AD as of May 26, 2011 (76 FR 22311, April 21, 2011). ADDRESSES: For service information identified in this AD, contact Lockheed Martin Corporation/Lockheed Martin Aeronautics Company, Airworthiness [[Page 19014]] Office, Dept. 6A0M, Zone 0252, Column P-58, 86 S. Cobb Drive, Marietta, GA 30063; telephone 770-494-5444; fax 770-494-5445; email [email protected]; 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- 0627. 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-2014- 0627; 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 (ACO), 1701 Columbia Avenue, College Park, GA 30337; phone: 404-474- 5554; fax: 404-474-5606; email: [email protected]. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2011-09-03, Amendment 39-16665 (76 FR 22311, April 21, 2011). AD 2011-09-03 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 September 17, 2014 (79 FR 55675). The NPRM was prompted by analysis of in-service cracking, which has shown that the initial and repetitive inspection schedules for the upper rainbow fitting need to be revised to reduce the probability of failure until the rainbow fitting is replaced. The NPRM proposed to continue to require repetitive eddy current inspections to detect cracks in the center wing upper and lower rainbow fittings, and corrective actions if necessary; and repetitive replacement of rainbow fittings, which would extend the repetitive interval for the next inspection. This AD reduces compliance times for initial and repetitive inspections of the upper rainbow fitting. We are issuing this AD to detect and correct fatigue cracking of the upper and lower rainbow fittings on the center wings, which could grow large and lead to the failure of the fitting and a catastrophic failure of the center wing. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM (79 FR 55675, September 17, 2014) or on the determination of the cost to the public. Conclusion We reviewed the relevant 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 (79 FR 55675, September 17, 2014) for correcting the unsafe condition; and Do not add any additional burden upon the public than was already proposed in the NPRM (79 FR 55675, September 17, 2014). Related Service Information Under 1 CFR Part 51 We reviewed Lockheed Martin Aeronautics Company Service Bulletin 382-57-82, Revision 6, including Appendixes A, B, and C, dated July 11, 2013. The service information describes procedures for repetitive eddy current inspections of the upper and lower rainbow fittings of the center wing; repetitive replacement of the upper and lower rainbow fittings; and related investigative and corrective actions. This service information is reasonably available; see ADDRESSES for ways to access this service information. Costs of Compliance We estimate that this AD affects 14 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 of upper and lower 20 work-hours x None.............. $1,700, per $23,800, per fitting [retained actions from $85 per hour = inspection cycle. inspection cycle. AD 2011[dash]09[dash]03, $1,700 per Amendment 39[dash]16665 (76 FR inspection cycle. 22311, April 21, 2011)]. Fitting replacement [retained 2,438 work-hours x $40,000........... $247,230, per $3,461,220, per actions from AD $85 per hour = replacement. replacement. 2011[dash]09[dash]03, Amendment $207,230 per 39[dash]16665 (76 FR 22311, replacement. April 21, 2011)]. ---------------------------------------------------------------------------------------------------------------- This AD reduces the compliance times for the upper rainbow fitting inspections and adds no additional economic burden. 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, [[Page 19015]] 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) 2011-09-03, Amendment 39-16665 (76 FR 22311, April 21, 2011), and adding the following new AD: 2015-06-08 Lockheed Martin Corporation/Lockheed Martin Aeronautics Company: Amendment 39-18126; Docket No. FAA-2014-0627; Directorate Identifier 2013-NM-217-AD. (a) Effective Date This AD is effective May 14, 2015. (b) Affected ADs This AD replaces AD 2011-09-03, Amendment 39-16665 (76 FR 22311, April 21, 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 analysis of in-service cracking that has shown that the rainbow fittings are susceptible to multiple site fatigue damage. We are issuing this AD to detect and correct fatigue cracking of the upper and lower rainbow fittings on the center wings, which could grow large and lead to the failure of the fitting and a catastrophic failure of the center wing. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Initial Inspections This paragraph restates the requirements of paragraph (g) of AD 2011-09-03, Amendment 39-16665 (76 FR 22311, April 21, 2011), with revised service information. Except as required by paragraph (m) of this AD, at the later of the times specified in paragraphs (g)(1) and (g)(2) of this AD: Do eddy current inspections to detect cracking of the center wing upper and lower rainbow fittings on the left and right side of the airplane. Do the actions in accordance with the Accomplishment Instructions of Lockheed Service Bulletin 382-57-82, Revision 4, including Appendixes A and B, dated May 20, 2009; or Lockheed Martin Aeronautics Company Service Bulletin 382- 57-82, Revision 6, including Appendixes A and B, dated July 11, 2013. If any crack is found during the inspections required by this paragraph, before further flight, do the actions required by paragraph (k) of this AD. Doing the requirements of paragraph (m) of this AD terminates the requirements of this paragraph for the affected upper rainbow fitting only. As of the effective date of this AD, only use Lockheed Martin Aeronautics Company Service Bulletin 382-57-82, Revision 6, including Appendixes A and B, dated July 11, 2013, for accomplishing the actions specified in this paragraph. (1) Before the accumulation of 15,000 total flight hours on the rainbow fitting. (2) Within 365 days or 600 flight hours on the rainbow fitting after May 26, 2011, (the effective date of AD 2011-09-03, Amendment 39-16665 (76 FR 22311, April 21, 2011)), whichever occurs first. (h) Retained Repetitive Inspection Schedule This paragraph restates the requirements of paragraph (h) of AD 2011-09-03, Amendment 39-16665 (76 FR 22311, April 21, 2011), with a new exception. Except as required by paragraph (n) of this AD, repeat the inspection required by paragraph (g) of this AD at intervals not to exceed 3,600 flight hours on the center wing, until the rainbow fitting has accumulated 30,000 total flight hours. If any crack is found during the inspections required by this paragraph, before further flight, do the actions required by paragraph (k) of this AD. Doing the requirements of paragraph (n) of this AD terminates the requirements of this paragraph for the affected upper rainbow fitting only. (i) Retained Rainbow Fitting Replacements This paragraph restates the requirements of paragraph (i) of AD 2011-09-03, Amendment 39-16665 (76 FR 22311, April 21, 2011), with revised service information. Before the accumulation of 30,000 flight hours on the rainbow fitting, or within 600 flight hours after May 26, 2011, (the effective date of AD 2011-09-03, Amendment 39-16665 (76 FR 22311, April 21, 2011)), whichever occurs later: Replace the rainbow fitting with a new rainbow fitting, do all related investigative actions, and do all applicable corrective actions, in accordance with paragraph 2.C. of the Accomplishment Instructions of Lockheed Service Bulletin 382-57-82, Revision 4, including Appendix C, dated May 20, 2009, except as required by paragraph (l) of this AD; or Lockheed Martin Aeronautics Company Service Bulletin 382-57-82, Revision 6, including Appendix C, dated July 11, 2013, except as required by paragraph (l) of this AD. Replace the rainbow fitting thereafter at intervals not to exceed 30,000 flight hours. As of the effective date of this AD, only use Lockheed Martin Aeronautics Company Service Bulletin 382-57-82, Revision 6, including Appendix C, dated July 11, 2013, for accomplishing the actions specified in this paragraph. (j) Retained Post-Replacement Repetitive Inspections This paragraph restates the requirements of paragraph (j) of AD 2011-09-03, Amendment 39-16665 (76 FR 22311, April 21, 2011), with a new exception. For upper and lower rainbow fittings replaced in accordance with paragraph (i) or (k) of this AD: Except as required by paragraph (o) of this AD, do the eddy current inspections specified in paragraph (g) of this AD within 15,000 flight hours after doing the replacement and repeat the eddy current inspections specified in paragraph (h) of this AD thereafter at intervals not to exceed 3,600 flight hours until the rainbow fittings are replaced in accordance with paragraph (i) or (k) of this AD. Doing the requirements of paragraph (o) of this AD terminates the requirements of this paragraph for the affected upper rainbow fitting only. (k) Retained Replacement, Related Investigative Actions, and Corrective Actions This paragraph restates the requirements of paragraph (k) of AD 2011-09-03, Amendment 39-16665 (76 FR 22311, April 21, 2011), with revised service information and revised references to inspection paragraphs. If, during any inspection required by paragraph (g), (h), (m), or (n) of this AD, any crack is detected in the rainbow fitting, before further flight, replace the rainbow fitting with a new rainbow fitting, do all related investigative actions, and do all applicable corrective actions, in accordance with Paragraph 2.C. of the Accomplishment Instructions of Lockheed Service Bulletin 382- 57-82, Revision 4, including Appendix C, dated May 20, 2009, except as provided by paragraph (l) of this AD; or Lockheed Martin Aeronautics Company Service Bulletin 382-57-82, Revision 6, including Appendix C, dated July 11, 2013, except as required by paragraph (l) of this AD. As of the effective date of this AD, only use Lockheed Martin Aeronautics Company Service Bulletin 382-57-82, Revision 6, including Appendix C, dated July 11, 2013, for accomplishing the actions specified in this paragraph. (l) Retained Exceptions to Service Information This paragraph restates the requirements of paragraph (l) of AD 2011-09-03, Amendment [[Page 19016]] 39-16665 (76 FR 22311, April 21, 2011), with revised service information. Where Lockheed Service Bulletin 382-57-82, Revision 4, including Appendixes A, B, and C, dated May 20, 2009; or Lockheed Martin Aeronautics Company Service Bulletin 382-57-82, Revision 6, including Appendixes A, B, and C, dated July 11, 2013; specifies to contact the manufacturer for disposition of certain repair conditions or does not specify corrective actions if certain conditions are found, this AD requires repairing those conditions using a method approved by the Manager, Atlanta Aircraft Certification Office (ACO), FAA. For a repair method to be approved by the Manager, Atlanta ACO, as required by this paragraph, the Manager's approval letter must specifically refer to this AD. (m) New Requirement: Reduced Initial Compliance Time for Upper Rainbow Fittings At the applicable compliance time specified in paragraphs (m)(1) and (m)(2) of this AD, do eddy current inspections to detect cracking of the center wing upper rainbow fittings on the left and right side of the airplane. Do the actions in accordance with the Accomplishment Instructions of Lockheed Martin Aeronautics Company Service Bulletin 382-57-82, Revision 6, including Appendixes A and B, dated July 11, 2013. If any crack is found during the inspections required by this paragraph, before further flight, do the actions required by paragraph (k) of this AD. Doing the requirements of this paragraph terminates the requirements of paragraph (g) of this AD for that upper rainbow fitting only. Repeat the inspection thereafter at the interval required by paragraph (n) of this AD. (1) For upper rainbow fittings that have accumulated less than 10,000 total flight hours as of the effective date of this AD, the compliance time is at the later of the times in paragraphs (m)(1)(i) and (m)(1)(ii) of this AD. (i) Before the accumulation of 10,000 total flight hours. (ii) Within 365 days or 600 flight hours after the effective date of this AD, whichever occurs first. (2) For upper rainbow fittings that have accumulated 10,000 total flight hours or more, but less than 15,000 total flight hours as of the effective date of this AD, the compliance time is the earlier of the times specified in paragraphs (m)(2)(i) and (m)(2)(ii) of this AD. (i) Within 365 days or 600 flight hours after the effective date of this AD, whichever occurs first. (ii) Before the accumulation of 15,000 total flight hours on the rainbow fitting. (n) New Requirement: Reduced Repetitive Inspection Intervals For upper rainbow fittings on which the requirements of paragraph (g), (h), or (m) of this AD were done, do the next inspection at the earlier of the times required in paragraphs (n)(1) and (n)(2) of this AD. Thereafter, repeat the inspection required by paragraph (m) of this AD at intervals not to exceed 2,500 flight hours until the upper rainbow fitting has accumulated 30,000 total flight hours. If any crack is found during the inspections required by this paragraph, before further flight, do the actions required by paragraph (k) of this AD. Doing an inspection required by this paragraph terminates the requirements of paragraph (h) of this AD for the affected upper rainbow fitting only. (1) Within 3,600 flight hours since the last inspection done in accordance with paragraph (g), (h), or (m) of this AD, whichever occurs latest. (2) At the later of the times specified in paragraphs (n)(2)(i) and (n)(2)(ii) of this AD. (i) Within 2,500 flight hours after the last inspection done in accordance with paragraph (g), (h), or (m) of this AD, whichever occurs latest. (ii) Within 365 days or 600 flight hours after the effective date of this AD, whichever occurs first. (o) New Requirement: Reduced Post-Replacement Repetitive Inspections For upper rainbow fittings replaced in accordance with paragraph (i) or (k) of this AD, do the inspection required by paragraph (m) of this AD at the earlier of the compliance times required in paragraph (o)(1) and (o)(2) of this AD. Repeat the inspection thereafter at intervals not to exceed 2,500 flight hours. Doing the inspections required by this paragraph terminates the requirements of paragraph (j) of this AD for the affected upper rainbow fitting only. (1) At the later of the times in paragraphs (o)(1)(i) and (o)(1)(ii) of this AD. (i) Within 10,000 total flight hours on the upper rainbow fitting. (ii) Within 365 days or 600 flight hours after the effective date of this AD, whichever occurs first. (2) Within 15,000 total flight hours on the upper rainbow fitting. (p) Credit for Previous Actions The service information identified in paragraphs (p)(1)(i), (p)(1)(ii), (p)(1)(iii), (p)(2), and (p)(3) is not incorporated by reference in this AD. (1) This paragraph provides credit for actions required by paragraphs (g), (h), (i), (j), and (k) of this AD, if those actions were performed before the effective date of this AD using the service information identified in paragraphs (p)(1)(i), (p)(1)(ii), and (p)(1)(iii) of this AD. (i) Lockheed Service Bulletin 382-57-82, including Appendixes A and B, dated December 7, 2004. (ii) Lockheed Service Bulletin 382-57-82, Revision 1, including Appendixes A and B, dated February 24, 2005. (iii) Lockheed Service Bulletin 382-57-82, Revision 2, including Appendixes A and B, dated February 15, 2007. (2) This paragraph restates paragraph (m) of AD 2011-09-03, Amendment 39-16665 (76 FR 22311, April 21, 2011). This paragraph provides credit for actions required by paragraphs (g), (h), (i), (j), and (k) of this AD, if those actions were performed before May 26, 2011 (the effective date of AD 2011-09-03), using Lockheed Service Bulletin 382-57-82, Revision 3, including Appendixes A, B, and C, dated April 25, 2008. (3) This paragraph provides credit for actions required by paragraphs (g), (h), (i), (j), (k), (m), (n), and (o) of this AD, if those actions were performed before the effective date of this AD using Lockheed Service Bulletin 382-57-82, Revision 5, including Appendixes A, B, and C, dated August 12, 2010. (q) 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 (r)(2) 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) AMOCs approved for AD 2011-09-03, Amendment 39-16665 (76 FR 22311, April 21, 2011), are approved as AMOCs for the corresponding provisions of this AD. (r) Related Information (1) For more information about this AD, contact Carl Gray, Aerospace Engineer, Airframe Branch, ACE-117A, FAA, Atlanta Aircraft Certification Office (ACO), 1701 Columbia Avenue, College Park, GA 30337; phone: 404-474-5554; fax: 404-474-5606; email: [email protected]. (2) For information about AMOCs, contact Hal Horsbough, Aerospace Engineer, Airframe Branch, ACE-117A, FAA, Atlanta Aircraft Certification Office (ACO), 1701 Columbia Avenue, College Park, GA 30337; phone: 404-474-5554; fax: 404-474-5606; email: [email protected]. (s) 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 May 14, 2015. (i) Lockheed Martin Aeronautics Company Service Bulletin 382-57- 82, Revision 6, including Appendixes A, B, and C, dated July 11, 2013. (ii) Reserved. (4) The following service information was approved for IBR on May 26, 2011 (76 FR 22311, April 21, 2011). (i) Lockheed Service Bulletin 382-57-82, Revision 4, including Appendixes A, B, and C, dated May 20, 2009. (ii) Reserved. (5) For service information identified in this AD, contact Lockheed Martin Corporation/Lockheed Martin Aeronautics Company, Airworthiness Office, Dept. 6A0M, [[Page 19017]] Zone 0252, Column P-58, 86 S. Cobb Drive, Marietta, GA 30063; telephone 770-494-5444; fax 770-494-5445; email [email protected]; Internet http://www.lockheedmartin.com/ams/tools/TechPubs.html. (6) You may view this service information at 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 March 12, 2015. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015-06785 Filed 4-8-15; 8:45 am] BILLING CODE 4910-13-P
![Federal Register / Vol. 80, No. 68 / Thursday, April 9, 2015 / Rules and Regulations 19013
(i) Repair Avenue SW., Renton, WA 98057–3356; Issued in Renton, Washington, on March
(1) If any disbonding is confirmed during telephone 425–227–2125; fax 425–227–1149. 27, 2015.
any inspection required by paragraphs Information may be emailed to: 9-ANM-116- Michael Kaszycki,
(h)(1)(i) and (h)(1)(ii) of this AD, before AMOC-REQUESTS@faa.gov. Before using Acting Manager, Transport Airplane
further flight, repair as specified in any approved AMOC, notify your appropriate Directorate, Aircraft Certification Service.
paragraphs (i)(1)(i) and (i)(1)(ii) of this AD, as principal inspector, or lacking a principal [FR Doc. 2015–07799 Filed 4–8–15; 08:45 am]
applicable. inspector, the manager of the local flight BILLING CODE 4910–13–P
(i) If disbonding is less than or equal to 50 standards district office/certificate holding
millimeters (mm) in width and less than or
district office. The AMOC approval letter
equal to 150 mm in length, before further
flight, vent the core, using a method must specifically reference this AD. DEPARTMENT OF TRANSPORTATION
approved by either the Manager, (2) Contacting the Manufacturer: For any
International Branch, ANM–116, Transport requirement in this AD to obtain corrective Federal Aviation Administration
Airplane Directorate, FAA; or EASA; or actions from a manufacturer, the action must
Airbus’s EASA DOA. Within 100 flight cycles be accomplished using a method approved 14 CFR Part 39
after the UT inspection specified in by the Manager, International Branch, ANM–
paragraph (h) of this AD is done, repair using 116, Transport Airplane Directorate, FAA; or [Docket No. FAA–2014–0627; Directorate
a method approved by the Manager, Identifier 2013–NM–217–AD; Amendment
EASA; or Airbus’s EASA DOA. If approved
International Branch, ANM–116, Transport 39–18126; AD 2015–06–08]
by the DOA, the approval must include the
Airplane Directorate, FAA; or EASA; or RIN 2120–AA64
DOA-authorized signature.
Airbus’s EASA DOA.
(ii) If disbonding is greater than 50 mm in (m) Related Information Airworthiness Directives; Lockheed
width or greater than 150 mm in length,
before further flight, repair using a method Refer to Mandatory Continuing Martin Corporation/Lockheed Martin
approved by the Manager, International Airworthiness Information (MCAI) EASA Aeronautics Company Airplanes
Branch, ANM–116, Transport Airplane Airworthiness Directive 2013–0039, dated
February 26, 2013, for related information. AGENCY: Federal Aviation
Directorate, FAA; or EASA; or Airbus’s EASA
DOA. This MCAI may be found in the AD docket Administration (FAA), DOT.
(2) If liquid ingress is confirmed during on the Internet at http:// ACTION: Final rule.
any inspection required by paragraphs www.regulations.gov/
(h)(1)(i) and (h)(1)(ii) of this AD, before #!documentDetail;D=FAA-2014-0123-0002. SUMMARY: We are superseding
further flight, repair using a method Airworthiness Directive (AD) 2011–09–
approved by the Manager, International (n) Material Incorporated by Reference 03 for all Lockheed Martin Corporation/
Branch, ANM–116, Transport Airplane (1) The Director of the Federal Register Lockheed Martin Aeronautics Company
Directorate, FAA; or EASA; or Airbus’s EASA approved the incorporation by reference Model 382, 382B, 382E, 382F, and 382G
DOA. (IBR) of the service information listed in this airplanes. AD 2011–09–03 required
(j) Inspection after Re-Installation paragraph under 5 U.S.C. 552(a) and 1 CFR repetitive eddy current inspections to
If any rudder has been inspected as part 51. detect cracks in the center wing upper
specified in Airbus Service Bulletin A300– (2) You must use this service information and lower rainbow fittings, and
55–6043, Revision 01, dated December 3, as applicable to do the actions required by corrective actions if necessary; and
2007; or A310–55–2044, Revision 01, dated this AD, unless this AD specifies otherwise. repetitive replacement of rainbow
December 3, 2007; as applicable; and has (i) Airbus Alert Operators Transmission fittings, which would extend the
been removed and re-installed on any (AOT) A55W002–12, dated December 13, repetitive interval for the next
airplane after this inspection, that rudder 2012, including Inspection Flowchart. The inspection. This new AD requires
must be re-inspected as required by inspection flowchart attached to this AOT is reduced intervals for inspections of the
paragraph (g) of this AD; and all applicable referred to in the AOT as ‘‘Appendix 1’’;
actions required by paragraphs (h) and (i) of upper rainbow fittings. This AD was
however, the flowchart page does not prompted by analysis of in-service
this AD must be done.
identify itself as an appendix. While the cracking, which has shown that a
(k) Parts Installation Limitation inspection flowchart page does specify the reduction in the inspection intervals is
As of the effective date of this AD, no AOT document number, it does not specify necessary for the upper rainbow fittings.
person may install, on any airplane, a rudder a revision level or an issue date. We are issuing this AD to detect and
assembly having a part number starting with (ii) Reserved. correct fatigue cracking of the upper and
A55471500, unless it has been inspected as (3) For service information identified in lower rainbow fittings on the center
required by paragraph (h) of this AD, and all this AD, contact Airbus SAS, Airworthiness
applicable actions required by paragraph (i) wings, which could grow large and lead
Office—EAW, 1 Rond Point Maurice to the failure of the fitting and a
of this AD have been done. Bellonte, 31707 Blagnac Cedex, France; catastrophic failure of the center wing.
(l) Other FAA AD Provisions telephone +33 5 61 93 36 96; fax +33 5 61
DATES: This AD is effective May 14,
The following provisions also apply to this 93 44 51; email account.airworth-eas@
airbus.com; Internet http://www.airbus.com.
2015.
AD:
(4) You may view this service information The Director of the Federal Register
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International at the FAA, Transport Airplane Directorate, approved the incorporation by reference
Branch, ANM–116, Transport Airplane 1601 Lind Avenue SW., Renton, WA. For of a certain publication listed in this AD
Directorate, FAA, has the authority to information on the availability of this as of May 14, 2015.
approve AMOCs for this AD, if requested material at the FAA, call 425–227–1221. The Director of the Federal Register
using the procedures found in 14 CFR 39.19. (5) You may view this service information approved the incorporation by reference
In accordance with 14 CFR 39.19, send your of a certain other publication listed in
Rmajette on DSK2VPTVN1PROD with RULES
that is incorporated by reference at the
request to your principal inspector or local this AD as of May 26, 2011 (76 FR
National Archives and Records
Flight Standards District Office, as 22311, April 21, 2011).
appropriate. If sending information directly Administration (NARA). For information on
to the International Branch, send it to ATTN: the availability of this material at NARA, call ADDRESSES: For service information
Dan Rodina, Aerospace Engineer, 202–741–6030, or go to: http:// identified in this AD, contact Lockheed
International Branch, ANM–116, Transport www.archives.gov/federal-register/cfr/ibr- Martin Corporation/Lockheed Martin
Airplane Directorate, FAA, 1601 Lind locations.html. Aeronautics Company, Airworthiness
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![19014 Federal Register / Vol. 80, No. 68 / Thursday, April 9, 2015 / Rules and Regulations
Office, Dept. 6A0M, Zone 0252, Column 30337; phone: 404–474–5554; fax: 404– received no comments on the NPRM (79
P–58, 86 S. Cobb Drive, Marietta, GA 474–5606; email: carl.w.gray@faa.gov. FR 55675, September 17, 2014) or on the
30063; telephone 770–494–5444; fax SUPPLEMENTARY INFORMATION: determination of the cost to the public.
770–494–5445; email ams.portal@ Conclusion
Discussion
lmco.com; Internet http://
www.lockheedmartin.com/ams/tools/ We issued a notice of proposed We reviewed the relevant data and
TechPubs.html. You may view this rulemaking (NPRM) to amend 14 CFR determined that air safety and the
referenced service information at the part 39 to supersede AD 2011–09–03, public interest require adopting this AD
FAA, Transport Airplane Directorate, Amendment 39–16665 (76 FR 22311, as proposed except for minor editorial
1601 Lind Avenue SW., Renton, WA. April 21, 2011). AD 2011–09–03 applied changes. We have determined that these
For information on the availability of to all Lockheed Martin Corporation/ minor changes:
this material at the FAA, call 425–227– Lockheed Martin Aeronautics Company • Are consistent with the intent that
1221. It is also available on the Internet Model 382, 382B, 382E, 382F, and 382G was proposed in the NPRM (79 FR
at http://www.regulations.gov by airplanes. The NPRM published in the 55675, September 17, 2014) for
Federal Register on September 17, 2014 correcting the unsafe condition; and
searching for and locating Docket No.
(79 FR 55675). The NPRM was
FAA–2014–0627. • Do not add any additional burden
prompted by analysis of in-service
upon the public than was already
Examining the AD Docket cracking, which has shown that the
proposed in the NPRM (79 FR 55675,
initial and repetitive inspection
You may examine the AD docket on September 17, 2014).
schedules for the upper rainbow fitting
the Internet at http:// need to be revised to reduce the Related Service Information Under 1
www.regulations.gov by searching for probability of failure until the rainbow CFR Part 51
and locating Docket No. FAA–2014– fitting is replaced. The NPRM proposed
0627; or in person at the Docket to continue to require repetitive eddy We reviewed Lockheed Martin
Management Facility between 9 a.m. current inspections to detect cracks in Aeronautics Company Service Bulletin
and 5 p.m., Monday through Friday, the center wing upper and lower 382–57–82, Revision 6, including
except Federal holidays. The AD docket rainbow fittings, and corrective actions Appendixes A, B, and C, dated July 11,
contains this AD, the regulatory if necessary; and repetitive replacement 2013. The service information describes
of rainbow fittings, which would extend procedures for repetitive eddy current
evaluation, any comments received, and
the repetitive interval for the next inspections of the upper and lower
other information. The address for the
inspection. This AD reduces compliance rainbow fittings of the center wing;
Docket Office (phone: 800–647–5527) is
times for initial and repetitive repetitive replacement of the upper and
Docket Management Facility, U.S.
inspections of the upper rainbow fitting. lower rainbow fittings; and related
Department of Transportation, Docket
We are issuing this AD to detect and investigative and corrective actions.
Operations, M–30, West Building
correct fatigue cracking of the upper and This service information is reasonably
Ground Floor, Room W12–140, 1200 available; see ADDRESSES for ways to
New Jersey Avenue SE., Washington, lower rainbow fittings on the center
wings, which could grow large and lead access this service information.
DC 20590.
to the failure of the fitting and a Costs of Compliance
FOR FURTHER INFORMATION CONTACT: Carl catastrophic failure of the center wing.
Gray, Aerospace Engineer, Airframe We estimate that this AD affects 14
Branch, ACE–117A, FAA, Atlanta Comments airplanes of U.S. registry.
Aircraft Certification Office (ACO), 1701 We gave the public the opportunity to We estimate the following costs to
Columbia Avenue, College Park, GA participate in developing this AD. We comply with this AD:
ESTIMATED COSTS
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
Inspection of upper and lower fitting [retained actions from 20 work-hours × $85 per hour None .............. $1,700, per in- $23,800, per
AD 2011-09-03, Amendment 39-16665 (76 FR 22311, = $1,700 per inspection spection inspection
April 21, 2011)]. cycle. cycle. cycle.
Fitting replacement [retained actions from AD 2011-09-03, 2,438 work-hours × $85 per $40,000 .......... $247,230, per $3,461,220,
Amendment 39-16665 (76 FR 22311, April 21, 2011)]. hour = $207,230 per re- replacement. per replace-
placement. ment.
This AD reduces the compliance detail the scope of the Agency’s is within the scope of that authority
times for the upper rainbow fitting authority. because it addresses an unsafe condition
inspections and adds no additional We are issuing this rulemaking under that is likely to exist or develop on
economic burden. the authority described in Subtitle VII, products identified in this rulemaking
action.
Authority for this Rulemaking Part A, Subpart III, Section 44701,
‘‘General requirements.’’ Under that Regulatory Findings
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Title 49 of the United States Code section, Congress charges the FAA with We have determined that this AD will
specifies the FAA’s authority to issue promoting safe flight of civil aircraft in not have federalism implications under
rules on aviation safety. Subtitle I, air commerce by prescribing regulations Executive Order 13132. This AD will
Section 106, describes the authority of for practices, methods, and procedures not have a substantial direct effect on
the FAA Administrator. Subtitle VII, the Administrator finds necessary for the States, on the relationship between
Aviation Programs, describes in more safety in air commerce. This regulation the national government and the States,
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![Federal Register / Vol. 80, No. 68 / Thursday, April 9, 2015 / Rules and Regulations 19015
or on the distribution of power and upper and lower rainbow fittings on the later: Replace the rainbow fitting with a new
responsibilities among the various center wings, which could grow large and rainbow fitting, do all related investigative
levels of government. lead to the failure of the fitting and a actions, and do all applicable corrective
catastrophic failure of the center wing. actions, in accordance with paragraph 2.C. of
For the reasons discussed above, I the Accomplishment Instructions of
certify that this AD: (f) Compliance Lockheed Service Bulletin 382–57–82,
(1) Is not a ‘‘significant regulatory Comply with this AD within the Revision 4, including Appendix C, dated
action’’ under Executive Order 12866, compliance times specified, unless already May 20, 2009, except as required by
(2) Is not a ‘‘significant rule’’ under done. paragraph (l) of this AD; or Lockheed Martin
DOT Regulatory Policies and Procedures Aeronautics Company Service Bulletin 382–
(g) Retained Initial Inspections 57–82, Revision 6, including Appendix C,
(44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation This paragraph restates the requirements of dated July 11, 2013, except as required by
paragraph (g) of AD 2011–09–03, paragraph (l) of this AD. Replace the rainbow
in Alaska, and
Amendment 39–16665 (76 FR 22311, April fitting thereafter at intervals not to exceed
(4) Will not have a significant 21, 2011), with revised service information. 30,000 flight hours. As of the effective date
economic impact, positive or negative, Except as required by paragraph (m) of this of this AD, only use Lockheed Martin
on a substantial number of small entities AD, at the later of the times specified in Aeronautics Company Service Bulletin 382–
under the criteria of the Regulatory paragraphs (g)(1) and (g)(2) of this AD: Do 57–82, Revision 6, including Appendix C,
Flexibility Act. eddy current inspections to detect cracking of dated July 11, 2013, for accomplishing the
the center wing upper and lower rainbow actions specified in this paragraph.
List of Subjects in 14 CFR Part 39 fittings on the left and right side of the
airplane. Do the actions in accordance with (j) Retained Post-Replacement Repetitive
Air transportation, Aircraft, Aviation Inspections
safety, Incorporation by reference, the Accomplishment Instructions of
Lockheed Service Bulletin 382–57–82, This paragraph restates the requirements of
Safety. paragraph (j) of AD 2011–09–03, Amendment
Revision 4, including Appendixes A and B,
Adoption of the Amendment dated May 20, 2009; or Lockheed Martin 39–16665 (76 FR 22311, April 21, 2011), with
Aeronautics Company Service Bulletin 382– a new exception. For upper and lower
Accordingly, under the authority 57–82, Revision 6, including Appendixes A rainbow fittings replaced in accordance with
delegated to me by the Administrator, and B, dated July 11, 2013. If any crack is paragraph (i) or (k) of this AD: Except as
the FAA amends 14 CFR part 39 as found during the inspections required by this required by paragraph (o) of this AD, do the
follows: paragraph, before further flight, do the eddy current inspections specified in
actions required by paragraph (k) of this AD. paragraph (g) of this AD within 15,000 flight
PART 39—AIRWORTHINESS Doing the requirements of paragraph (m) of hours after doing the replacement and repeat
DIRECTIVES this AD terminates the requirements of this the eddy current inspections specified in
paragraph for the affected upper rainbow paragraph (h) of this AD thereafter at
■ 1. The authority citation for part 39 fitting only. As of the effective date of this intervals not to exceed 3,600 flight hours
continues to read as follows: AD, only use Lockheed Martin Aeronautics until the rainbow fittings are replaced in
Company Service Bulletin 382–57–82, accordance with paragraph (i) or (k) of this
Authority: 49 U.S.C. 106(g), 40113, 44701. Revision 6, including Appendixes A and B, AD. Doing the requirements of paragraph (o)
dated July 11, 2013, for accomplishing the of this AD terminates the requirements of this
§ 39.13 [Amended] actions specified in this paragraph. paragraph for the affected upper rainbow
■ 2. The FAA amends § 39.13 by (1) Before the accumulation of 15,000 total fitting only.
removing Airworthiness Directive (AD) flight hours on the rainbow fitting.
(k) Retained Replacement, Related
2011–09–03, Amendment 39–16665 (76 (2) Within 365 days or 600 flight hours on
Investigative Actions, and Corrective
the rainbow fitting after May 26, 2011, (the
FR 22311, April 21, 2011), and adding Actions
effective date of AD 2011–09–03,
the following new AD: Amendment 39–16665 (76 FR 22311, April This paragraph restates the requirements of
2015–06–08 Lockheed Martin Corporation/ 21, 2011)), whichever occurs first. paragraph (k) of AD 2011–09–03,
Lockheed Martin Aeronautics Company: Amendment 39–16665 (76 FR 22311, April
(h) Retained Repetitive Inspection Schedule 21, 2011), with revised service information
Amendment 39–18126; Docket No.
FAA–2014–0627; Directorate Identifier This paragraph restates the requirements of and revised references to inspection
2013–NM–217–AD. paragraph (h) of AD 2011–09–03, paragraphs. If, during any inspection
Amendment 39–16665 (76 FR 22311, April required by paragraph (g), (h), (m), or (n) of
(a) Effective Date 21, 2011), with a new exception. Except as this AD, any crack is detected in the rainbow
This AD is effective May 14, 2015. required by paragraph (n) of this AD, repeat fitting, before further flight, replace the
the inspection required by paragraph (g) of rainbow fitting with a new rainbow fitting,
(b) Affected ADs this AD at intervals not to exceed 3,600 flight do all related investigative actions, and do all
This AD replaces AD 2011–09–03, hours on the center wing, until the rainbow applicable corrective actions, in accordance
Amendment 39–16665 (76 FR 22311, April fitting has accumulated 30,000 total flight with Paragraph 2.C. of the Accomplishment
21, 2011). hours. If any crack is found during the Instructions of Lockheed Service Bulletin
inspections required by this paragraph, 382–57–82, Revision 4, including Appendix
(c) Applicability before further flight, do the actions required C, dated May 20, 2009, except as provided by
This AD applies to all Lockheed Martin by paragraph (k) of this AD. Doing the paragraph (l) of this AD; or Lockheed Martin
Corporation/Lockheed Martin Aeronautics requirements of paragraph (n) of this AD Aeronautics Company Service Bulletin 382–
Company Model 382, 382B, 382E, 382F, and terminates the requirements of this paragraph 57–82, Revision 6, including Appendix C,
382G airplanes, certificated in any category. for the affected upper rainbow fitting only. dated July 11, 2013, except as required by
paragraph (l) of this AD. As of the effective
(d) Subject (i) Retained Rainbow Fitting Replacements date of this AD, only use Lockheed Martin
Air Transport Association (ATA) of This paragraph restates the requirements of Aeronautics Company Service Bulletin 382–
paragraph (i) of AD 2011–09–03, Amendment
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America Code 57, Wings. 57–82, Revision 6, including Appendix C,
39–16665 (76 FR 22311, April 21, 2011), with dated July 11, 2013, for accomplishing the
(e) Unsafe Condition revised service information. Before the actions specified in this paragraph.
This AD was prompted by an analysis of accumulation of 30,000 flight hours on the
in-service cracking that has shown that the rainbow fitting, or within 600 flight hours (l) Retained Exceptions to Service
rainbow fittings are susceptible to multiple after May 26, 2011, (the effective date of AD Information
site fatigue damage. We are issuing this AD 2011–09–03, Amendment 39–16665 (76 FR This paragraph restates the requirements of
to detect and correct fatigue cracking of the 22311, April 21, 2011)), whichever occurs paragraph (l) of AD 2011–09–03, Amendment
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![Federal Register / Vol. 80, No. 68 / Thursday, April 9, 2015 / Rules and Regulations 19017
Zone 0252, Column P–58, 86 S. Cobb Drive, ADDRESSES: You may send comments, Model 402C airplanes. The cracks found
Marietta, GA 30063; telephone 770–494– using the procedures found in 14 CFR run across the beam and extend beyond
5444; fax 770–494–5445; email ams.portal@ 11.43 and 11.45, by any of the following the doubler located under the aft engine
lmco.com; Internet http:// methods: mount and aft of the forward engine
www.lockheedmartin.com/ams/tools/
TechPubs.html.
• Federal eRulemaking Portal: Go to mount. Investigation revealed that the
(6) You may view this service information http://www.regulations.gov. Follow the cause of the cracks is fatigue.
at FAA, Transport Airplane Directorate, 1601 instructions for submitting comments. The engine beam mounts of the
Lind Avenue SW., Renton, WA. For • Fax: 202–493–2251. Cessna Model 402C airplanes are the
information on the availability of this • Mail: U.S. Department of same type design as that of the Cessna
material at the FAA, call 425–227–1221. Transportation, Docket Operations, M– Model 414A airplanes.
(7) You may view this service information 30, West Building Ground Floor, Room This condition, if not detected and
that is incorporated by reference at the W12–140, 1200 New Jersey Avenue SE., corrected, could result in failure of an
National Archives and Records Washington, DC 20590. engine mount beam and could lead to
Administration (NARA). For information on • Hand Delivery: U.S. Department of engine separation with consequent loss
the availability of this material at NARA, call
202–741–6030, or go to: http://
Transportation, Docket Operations, M– of power and loss of control. We are
www.archives.gov/federal-register/cfr/ibr- 30, West Building Ground Floor, Room issuing this AD to correct the unsafe
locations.html. W12–140, 1200 New Jersey Avenue SE., condition on these products.
Washington, DC 20590, between 9 a.m.
Issued in Renton, Washington, on March Relevant Service Information Under 1
12, 2015.
and 5 p.m., Monday through Friday,
CFR Part 51
except Federal holidays.
Jeffrey E. Duven, We reviewed Cessna Aircraft
For service information identified in
Manager, Transport Airplane Directorate, this AD, contact Cessna Aircraft Company Multi-engine Service Letter
Aircraft Certification Service. No. MEL–54–01, dated March 20, 2015,
Company, Customer service, P.O. Box
[FR Doc. 2015–06785 Filed 4–8–15; 8:45 am] including the undated Attachment,
7706, Wichita, KS 67277; telephone:
BILLING CODE 4910–13–P (316) 517–5800; fax: (316) 517–7271; ‘‘Inspection Results Form.’’ The Cessna
email: customercare@ Aircraft Company Multi-engine Service
cessna.textron.com; Internet: http:// Letter describes procedures for
DEPARTMENT OF TRANSPORTATION www.cessnasupport.com. You may inspecting the engine mount beams for
review this referenced service cracks and reporting the inspection
Federal Aviation Administration
information at the FAA, Small Airplane results to Cessna. This information is
Directorate, 901 Locust, Kansas City, reasonably available at http://
14 CFR Part 39
Missouri 64106. For information on the www.regulations.gov by searching for
[Docket No. FAA–2015–0839; Directorate availability of this material at the FAA, and locating Docket No. FAA–2015–
Identifier 2015–CE–006–AD; Amendment call (816) 329–4148. It is also available 0839, or you may see ADDRESSES for
39–18131; AD 2015–07–03] on the Internet at http:// other ways to access this service
www.regulations.gov by searching for information.
RIN 2120–AA64 and locating Docket No. FAA–2015– FAA’s Determination
0839.
Airworthiness Directives; Cessna We are issuing this AD because we
Aircraft Company Airplanes Examining the AD Docket evaluated all the relevant information
You may examine the AD docket on and determined the unsafe condition
AGENCY: Federal Aviation
the Internet at http:// described previously is likely to exist or
Administration (FAA), DOT.
www.regulations.gov by searching for develop in other products of the same
ACTION: Final rule; request for type design.
and locating Docket No. FAA–2015–
comments.
0839; or in person at the Docket AD Requirements
SUMMARY: We are adopting a new Management Facility between 9 a.m.
and 5 p.m., Monday through Friday, This AD requires repetitively
airworthiness directive (AD) for certain
except Federal holidays. The AD docket inspecting the engine mount beams for
Cessna Aircraft Company (Cessna)
contains this AD, the regulatory cracks and contacting Cessna for an
Model 402C and 414A airplanes. This
evaluation, any comments received, and FAA-approved corrective action if
AD requires repetitively inspecting the
other information. The street address for cracks are found. This AD also requires
engine mount beams for cracks and
the Docket Office (phone: 800–647– sending the inspection results to the
contacting Cessna for FAA-approved
5527) is in the ADDRESSES section. FAA and to Cessna.
corrective action if cracks are found.
This AD also requires sending an Comments will be available in the AD Differences Between This AD and the
inspection report to the FAA and to docket shortly after receipt. Service Information
Cessna. This AD was prompted by FOR FURTHER INFORMATION CONTACT: Gary
Cessna Aircraft Company Multi-
reports of cracks found across the Park, Aerospace Engineer, Wichita engine Service Letter No. MEL–54–01,
engine mount beams. We are issuing Aircraft Certification Office, FAA, 1801 dated March 20, 2015, including the
this AD to correct the unsafe condition S. Airport Road, Room 100, Wichita, undated Attachment, ‘‘Inspection
on these products. Kansas 67209; phone: (316) 946–4123; Results Form,’’ specifies reporting the
DATES: This AD is effective April 24, fax: (316) 946–4107; email: gary.park@ inspection results to Cessna. In this AD,
faa.gov.
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2015. we also require that the inspection
The Director of the Federal Register SUPPLEMENTARY INFORMATION: results be reported to the FAA.
approved the incorporation by reference
of a certain publication listed in this AD Discussion FAA’s Justification and Determination
as of April 24, 2015. We received reports of cracks found of the Effective Date
We must receive comments on this on the engine mount beams of certain An unsafe condition exists that
AD by May 26, 2015. Cessna Aircraft Company (Cessna) requires the immediate adoption of this
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Document Created: 2015-12-18 11:23:22
Document Modified: 2015-12-18 11:23:22
| 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 May 14, 2015. | |
| Contact | Carl Gray, Aerospace Engineer, Airframe Branch, ACE-117A, FAA, Atlanta Aircraft Certification Office (ACO), 1701 Columbia Avenue, College Park, GA 30337; phone: 404-474- 5554; fax: 404-474-5606; email: [email protected] | |
| FR Citation | 80 FR 19013 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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