81 FR 14707 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 53 (March 18, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 53 (March 18, 2016)
| Page Range | 14707-14711 | |
| FR Document | 2016-06001 |
[Federal Register Volume 81, Number 53 (Friday, March 18, 2016)] [Rules and Regulations] [Pages 14707-14711] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-06001] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2014-0774; Directorate Identifier 2013-NM-154-AD; Amendment 39-18438; AD 2016-06-07] RIN 2120-AA64 Airworthiness Directives; The Boeing Company Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are superseding Airworthiness Directive (AD) 2006-22-15 for all The Boeing Company Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F, 747SR, and 747SP series airplanes. AD 2006-22-15 required repetitive inspections for cracking of certain panel webs and stiffeners of the nose wheel well (NWW), and corrective actions if necessary; and replacement of certain panels with new panels, which terminates the repetitive inspections. This new AD reduces a compliance time and adds certain inspections and an applicable repair. This AD was prompted by multiple reports of fatigue cracking in the NWW top panel and side panel webs and stiffeners. We are issuing this AD to prevent fatigue cracking of the NWW side and top panels, which could result in a NWW depressurization event severe enough to reduce the structural integrity of the fuselage. DATES: This AD is effective April 22, 2016. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of April 22, 2016. ADDRESSES: For service information identified in this final rule, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2014- 0774. 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- 0774; 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: Bill Ashforth, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917- 6432; fax: 425-917-6590; email: [email protected]. SUPPLEMENTARY INFORMATION: Discussion We issued a supplemental notice of proposed rulemaking (SNPRM) to amend 14 CFR part 39 to supersede AD 2006-22-15, Amendment 39-14812 (71 FR 64884, November 6, 2006) (``AD 2006-22-15''). AD 2006-22-15 applied to all The Boeing Company Model 747-100, 747-100B, 747-100B SUD, 747- 200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F, 747SR, and 747SP series airplanes. The SNPRM published in the Federal Register on September 18, 2015 (80 FR 56407) (``the SNPRM''). We preceded the SNPRM with a notice of proposed rulemaking (NPRM) that published in the Federal Register on November 17, 2014 (79 FR 68388) (``the NPRM''). The NPRM proposed to continue to require repetitive inspections for cracking of [[Page 14708]] certain panel webs and stiffeners of the NWW, and corrective actions if necessary; and replacement of certain panels with new panels, which terminates the repetitive inspections. The NPRM proposed to reduce a compliance time and add certain inspections and repair if necessary. The NPRM was prompted by reports of fatigue cracking in the panel webs and stiffeners of the NWW found prior to the inspection threshold of AD 2006-22-15. The SNPRM revised the NPRM by specifying a repetitive inspection interval for a certain NWW area inspection. We are issuing this AD to prevent fatigue cracking of the NWW side and top panels, which could result in a NWW depressurization event severe enough to reduce the structural integrity of the fuselage. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the SNPRM and the FAA's response to each comment. Support for the SNPRM Two commenters supported the SNPRM. One commenter stated that the FAA should continue to execute its administrative power to ensure traveler safety and industry compliance, adding that while the original rule was good, ensuring that specifics are covered and timetables are available is an important improvement. Request for Credit for Compliance Times in Previously Approved Alternative Methods of Compliance (AMOCs) Boeing requested that we allow credit for the compliance times in previously approved AMOCs, if the compliance times are acceptable according to the SNPRM. We agree with the commenter's request. We have revised paragraph (p)(4) of this AD to state that: AMOC actions approved previously for AD 2006-22-15 are approved as AMOCs for the corresponding actions of this AD. In addition, paragraph (p)(4) of this AD states that the compliance times in AMOCs approved previously for AD 2006-22-15 are not approved for the corresponding actions and compliance times in this AD, if this AD specifies an earlier compliance time than that specified in AD 2006-22-15; and that compliance times in AMOCs approved previously for AD 2006-22-15 that meet the requirements of this AD are acceptable. 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 change described previously and minor editorial changes. We have determined that these minor changes:Are consistent with the intent that was proposed in the SNPRM for correcting the unsafe condition; and Do not add any additional burden upon the public than was already proposed in the SNPRM. 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 the following Boeing service bulletins. Boeing Alert Service Bulletin 747-53A2808, dated November 30, 2012. This service information describes procedures for replacement of the side and top panel webs, support beams, and stiffeners of the NWW; an inspection for cracking of the attaching structural elements that are common to the removed top and side panels of the NWW; repetitive post-modification inspections for cracks in the top and side panel webs and stiffeners; and repairs. Boeing Service Bulletin 747-53A2465, Revision 5, dated July 11, 2013. This service information describes procedures for doing inspections for cracking of the NWW side panel and top panel webs and longitudinal stiffeners for cracks, and related investigative and corrective actions. Boeing Service Bulletin 747-53A2562, Revision 3, dated July 11, 2013. This service information describes procedures for replacement of the side and top panel webs and certain stiffeners of the NWW; an inspection for cracks in attaching structural elements that are common to the removed top panel and side panels; repetitive post- modification inspections for cracks in the top and side panel webs and stiffeners; and repairs. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. Costs of Compliance We estimate that this AD will affect 255 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 ---------------------------------------------------------------------------------------------------------------- Inspections [actions retained 119 work-hours x $0................ $10,115 per $2,579,325 per from AD 2006-22-15]. $85 per hour = inspection cycle. inspection cycle. $10,115 per inspection cycle. Modification [actions retained Up to 1,346 work- Up to $144,248.... Up to $258,658.... Up to $65,957,790. from AD 2006-22-15]. hours x $85 per hour = $114,410. Post-modification Inspections 119 work-hours x $0................ $10,115 per $2,579,325 per [new action]. $85 per hour = inspection cycle. inspection cycle. $10,115 per inspection cycle. ---------------------------------------------------------------------------------------------------------------- We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in this AD. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, Section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency's authority. We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701, ``General requirements.'' Under that section, Congress charges the FAA with [[Page 14709]] 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) 2006-22-15, Amendment 39-14812 (71 FR 64884, November 6, 2006) (``AD 2006-22-15''), and adding the following new AD: 2016-06-07 The Boeing Company: Amendment 39-18438; Docket No. FAA- 2014-0774; Directorate Identifier 2013-NM-154-AD. (a) Effective Date This AD is effective April 22, 2016. (b) Affected ADs This AD replaces AD 2006-22-15, Amendment 39-14812 (71 FR 64884, November 6, 2006) (``AD 2006-22-15''). (c) Applicability This AD applies to all The Boeing Company Model 747-100, 747- 100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F, 747SR, and 747SP series airplanes, certificated in any category. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Unsafe Condition This AD was prompted by multiple reports of cracking in the nose wheel well (NWW) top panel and side panel webs and stiffeners. We are issuing this AD to prevent fatigue cracking of the NWW side and top panels, which could result in a NWW depressurization event severe enough to reduce the structural integrity of the fuselage. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Repetitive Inspections and Corrective Actions With New Compliance Times Except as specified in paragraphs (h)(1) and (h)(2) of this AD, at the applicable time specified in paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin 747-53A2465, Revision 5, dated July 11, 2013: Do the actions specified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD, and do all applicable related investigative and corrective actions; in accordance with the Accomplishment Instructions of Boeing Service Bulletin 747-53A2465, Revision 5, dated July 11, 2013, except as specified in paragraph (h)(3) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the inspections specified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD thereafter at the applicable intervals specified in paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin 747-53A2465, Revision 5, dated July 11, 2013. The repetitive interval for the inspection of Area 2 specified in table 1 in paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin 747-53A2465, Revision 5, dated July 11, 2013, is 1,000 flight cycles. In table 2 and table 3 in paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin 747-53A2465, Revision 5, dated July 11, 2013, the date ``January 27, 2005,'' is the effective date of AD 2004-25-23, Amendment 39-13911 (69 FR 76839, December 23, 2004); and the date ``May 10, 2005,'' is the effective date of AD 2005-09-02, Amendment 39-14070 (70 FR 21141, April 25, 2005; corrected May 25, 2005 (70 FR 29940)). (1) Do an external detailed inspection for cracks of the top and sidewall panel webs of the NWW (specified as Area 1 and Area 2 in Boeing Service Bulletin 747-53A2465, Revision 5, dated July 11, 2013). (2) Do internal detailed and surface high frequency eddy current (HFEC) inspections for cracks of the sidewall panel and top panel stiffeners of the NWW (specified as Area 3 in Boeing Service Bulletin 747-53A2465, Revision 5, dated July 11, 2013). (3) Do an external detailed and ultrasonic testing (UT) inspection for cracks of the top and sidewall panel webs of the NWW (specified as Area 1 and Area 2 in Boeing Service Bulletin 747- 53A2465, Revision 5, dated July 11, 2013). (h) Exceptions to Boeing Service Bulletin 747-53A2465, Revision 5, Dated July 11, 2013 (1) Table 1 in paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin 747-53A2465, Revision 5, dated July 11, 2013, applies to airplanes with less than 15,000 total flight cycles ``as of the Revision 5 date of this service bulletin.'' For this AD, however, table 1 applies to airplanes with the specified total flight cycles as of the effective date of this AD. (2) Table 1 in paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin 747-53A2465, Revision 5, dated July 11, 2013, specifies a compliance time of ``13,000 total flight-cycles,'' or ``within 1,000 flight cycles after the Revision 5 date of this service bulletin,'' whichever occurs later. This AD requires compliance before the accumulation of 10,000 total flight cycles or within 1,000 flight cycles after the effective date of this AD, whichever occurs later. (3) If any cracking or damage is found during any inspection required by paragraph (g) of this AD, and Boeing Service Bulletin 747-53A2465, Revision 5, dated July 11, 2013, specifies to contact Boeing for appropriate action: Before further flight, repair the cracking or damage using a method approved in accordance with the procedures specified in paragraph (p) of this AD. (i) NWW Modification For airplanes identified in Boeing Service Bulletin 747-53A2562, Revision 3, dated July 11, 2013: At the applicable time specified in paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin 747- 53A2562, Revision 3, dated July 11, 2013, replace the left-side, right-side, and top panels of the NWW, as applicable, with new panels, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 747-53A2562, Revision 3, dated July 11, 2013. As of the effective date of this AD, concurrently with doing the replacement specified in Boeing Service Bulletin 747-53A2562, Revision 3, dated July 11, 2013, do a detailed inspection for any cracks or damage (including, but not limited to, dents and corrosion) in all attaching structural elements that are common to the removed top panel and side panels, as applicable, and do all applicable corrective actions, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 747-53A2562, Revision 3, dated July 11, 2013. If any crack or damage is found, before further flight, repair the cracking or damage using a method approved in accordance with the procedures specified in paragraph (p) of this AD. In paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin 747-53A2562, Revision 3, dated July 11, 2013, the date ``December 11, 2006,'' is the effective date of AD 2006-22-15. [[Page 14710]] (j) Repetitive Post-Modification Inspections For airplanes on which the replacement specified in paragraph (i) of this AD has been done: Except as required by paragraph (k) of this AD, at the applicable time specified in paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin 747-53A2562, Revision 3, dated July 11, 2013, do the actions specified in paragraphs (j)(1), (j)(2), and (j)(3) of this AD. If any crack is found: Before further flight, repair the cracking using a method approved in accordance with the procedures specified in paragraph (p) of this AD. Repeat the inspections specified in paragraphs (j)(1), (j)(2), and (j)(3) of this AD thereafter at the applicable intervals specified in paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin 747- 53A2562, Revision 3, dated July 11, 2013. (1) Do an external detailed inspection for cracks in the side panel webs, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 747-53A2562, Revision 3, dated July 11, 2013. (2) Do an internal detailed inspection and high frequency eddy current (HFEC) inspection for cracks in the top and side panel stiffeners, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 747-53A2562, Revision 3, dated July 11, 2013. (3) Do an external detailed inspection for cracks in the top panel web, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 747-53A2562, Revision 3, dated July 11, 2013. (k) Exception to Boeing Service Bulletin 747-53A2562, Revision 3, Dated July 11, 2013 Where paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin 747-53A2562, Revision 3, dated July 11, 2013, specifies a compliance time relative to the ``Revision 3 date of this service bulletin,'' this AD requires compliance within the specified compliance time after the effective date of this AD. (l) NWW Modification for Certain Airplanes For airplanes identified in Boeing Alert Service Bulletin 747- 53A2808, dated November 30, 2012: At the applicable time specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2808, dated November 30, 2012, replace the left side, right side, and top panels of the NWW, as applicable, with new panels, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747-53A2808, dated November 30, 2012. Concurrently with doing the replacement specified in this paragraph, do a detailed inspection for cracks of the attaching structural elements that are common to the removed top, left side, and right side panels of the NWW, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747-53A2808, dated November 30, 2012. If any crack is found, before further flight, repair the cracking using a method approved in accordance with the procedures specified in paragraph (p) of this AD. (m) Repetitive Post-Modification Inspections for Certain Airplanes For airplanes on which the replacement specified in paragraph (l) of this AD has been done: At the applicable time specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2808, dated November 30, 2012, do the actions specified in paragraphs (m)(1), (m)(2), and (m)(3) of this AD. If any crack is found: Before further flight, repair the cracking using a method approved in accordance with the procedures specified in paragraph (p) of this AD. Repeat the inspections specified in paragraphs (m)(1), (m)(2), and (m)(3) of this AD thereafter at the applicable intervals specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2808, dated November 30, 2012. (1) Do an external detailed inspection for cracks in the side panel webs, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747-53A2808, dated November 30, 2012. (2) Do an internal detailed inspection and HFEC inspection for cracks in the top and side panel stiffeners, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747- 53A2808, dated November 30, 2012. (3) Do an external detailed inspection for cracks in the top panel web, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747-53A2808, dated November 30, 2012. (n) Terminating Action for Certain Repetitive Inspections Replacing the left side, right side, and top panels of the NWW with new panels as specified in paragraph (i) or (l) of this AD terminates the repetitive inspections required by paragraph (g) of this AD. (o) Credit for Previous Actions (1) This paragraph restates the credit given in paragraph (k) of AD 2006-22-15. (i) This paragraph provides credit for the actions required by paragraph (g)(1) of this AD, if those actions were performed before January 27, 2005 (the effective date of AD 2004-25-23, Amendment 39- 13911 (69 FR 76839, December 23, 2004)), using Boeing Alert Service Bulletin 747-53A2465, dated April 5, 2001, which is not incorporated by reference in this AD. (ii) This paragraph provides credit for actions required by paragraphs (g)(1) and (g)(2) of this AD, if those actions were performed before December 11, 2006 (the effective date of AD 2006- 22-15), using a service bulletin identified in paragraph (o)(1)(ii)(A), (o)(1)(ii)(B), or (o)(1)(ii)(C) of this AD, which are not incorporated by reference in this AD. (A) Boeing Alert Service Bulletin 747-53A2465, Revision 1, dated October 16, 2003. (B) Boeing Alert Service Bulletin 747-53A2465, Revision 2, dated November 11, 2004. (C) Boeing Alert Service Bulletin 747-53A2465, Revision 3, dated December 23, 2004. (2) This paragraph provides credit for the actions required by paragraph (g) of this AD, if those actions were performed before the effective date of this AD using Boeing Alert Service Bulletin 747- 53A2465, Revision 4, dated February 24, 2005, which is not incorporated by reference in this AD. (3) This paragraph provides credit for the actions required by paragraphs (i) and (j) of this AD, if those actions were performed before the effective date of this AD using the service information identified in paragraph (o)(3)(i) or (o)(3)(ii) of this AD. (i) Boeing Service Bulletin 747-53A2562, Revision 1, dated July 28, 2005, which was incorporated by reference in AD 2006-22-15. (ii) Boeing Service Bulletin 747-53A2562, Revision 2, dated May 31, 2007, which is not incorporated by reference in this AD. (p) Alternative Methods of Compliance (AMOCs) (1) The Manager, Seattle Aircraft Certification Office (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 (q)(1) of this AD. Information may be emailed to: [email protected]. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. (3) An AMOC that provides an acceptable level of safety may be used for any repair, modification, or alteration required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle ACO, to make those findings. To be approved, the repair method, modification deviation, or alteration deviation must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (4) AMOC actions approved previously for AD 2006-22-15 are approved as AMOCs for the corresponding actions of this AD. The compliance times in AMOCs approved previously for AD 2006-22-15 are not approved for the corresponding actions and compliance times in this AD, if this AD specifies an earlier compliance time than that specified in AD 2006-22-15. Compliance times in AMOCs approved previously for AD 2006-22-15 that meet the requirements of this AD are acceptable. (q) Related Information (1) For more information about this AD, contact Bill Ashforth, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle ACO, 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6432; fax: 425-917-6590; email: [email protected]. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (r)(3) and (r)(4) of this AD. (r) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference [[Page 14711]] (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. (i) Boeing Alert Service Bulletin 747-53A2808, dated November 30, 2012. (ii) Boeing Service Bulletin 747-53A2465, Revision 5, dated July 11, 2013. (iii) Boeing Service Bulletin 747-53A2562, Revision 3, dated July 11, 2013. (3) For Boeing service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. (4) You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. (5) 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 9, 2016. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-06001 Filed 3-17-16; 8:45 am] BILLING CODE 4910-13-P
![Federal Register / Vol. 81, No. 53 / Friday, March 18, 2016 / Rules and Regulations 14707
1.A., ‘‘Effectivity,’’ of GE GEnx–1B Service information on the availability of this ADDRESSES: For service information
Bulletin 72–0309 R00, dated March 11, 2016, material at the FAA, call 425–227–1221. identified in this final rule, contact
unless at least one engine has been reworked (5) You may view this service information Boeing Commercial Airplanes,
in accordance with paragraph 3.A.(1)(b), 3.B., that is incorporated by reference at the
Attention: Data & Services Management,
or 3.C. of the Accomplishment Instructions of National Archives and Records
GE GEnx–1B Service Bulletin 72–0309 R00, Administration (NARA). For information on P.O. Box 3707, MC 2H–65, Seattle, WA
dated March 11, 2016. the availability of this material at NARA, call 98124–2207; telephone 206–544–5000,
202–741–6030, or go to: http:// extension 1; fax 206–766–5680; Internet
(k) Reporting Provisions www.archives.gov/federal-register/cfr/ibr- https://www.myboeingfleet.com. You
Although GE GEnx Service Bulletin GEnx– locations.html. may view this referenced service
1B 72–0309 R00, dated March 11, 2016, information at the FAA, Transport
specifies reporting certain tip clearance Issued in Renton, Washington, on March Airplane Directorate, 1601 Lind Avenue
measurements to GE, this AD does not 14, 2016.
SW., Renton, WA. For information on
require any report. Michael Kaszycki, the availability of this material at the
(l) Alternative Methods of Compliance Acting Manager, Transport Airplane FAA, call 425–227–1221. It is also
(AMOCs) Directorate, Aircraft Certification Service. available on the Internet at http://
(1) The Manager, Seattle Aircraft [FR Doc. 2016–06117 Filed 3–17–16; 8:45 am] www.regulations.gov by searching for
Certification Office (ACO), FAA, has the BILLING CODE 4910–13–P and locating Docket No. FAA–2014–
authority to approve AMOCs for this AD, if 0774.
requested using the procedures found in 14
CFR 39.19. In accordance with 14 CFR 39.19, DEPARTMENT OF TRANSPORTATION Examining the AD Docket
send your request to your principal inspector You may examine the AD docket on
or local Flight Standards District Office, as Federal Aviation Administration the Internet at http://
appropriate. If sending information directly
www.regulations.gov by searching for
to the manager of the ACO, send it to the 14 CFR Part 39
attention of the person identified in and locating Docket No. FAA–2014–
paragraph (m) of this AD. Information may be [Docket No. FAA–2014–0774; Directorate 0774; or in person at the Docket
emailed to: 9-ANM-Seattle-ACO-AMOC- Identifier 2013–NM–154–AD; Amendment Management Facility between 9 a.m.
Requests@faa.gov. 39–18438; AD 2016–06–07] and 5 p.m., Monday through Friday,
(2) Before using any approved AMOC, except Federal holidays. The AD docket
notify your appropriate principal inspector, RIN 2120–AA64
contains this AD, the regulatory
or lacking a principal inspector, the manager evaluation, any comments received, and
of the local flight standards district office/ Airworthiness Directives; The Boeing
Company Airplanes other information. The address for the
certificate holding district office.
Docket Office (phone: 800–647–5527) is
(3) An AMOC that provides an acceptable
level of safety may be used for any repair,
AGENCY: Federal Aviation Docket Management Facility, U.S.
modification, or alteration required by this Administration (FAA), DOT. Department of Transportation, Docket
AD if it is approved by the Boeing ACTION: Final rule. Operations, M–30, West Building
Commercial Airplanes Organization Ground Floor, Room W12–140, 1200
Designation Authorization (ODA) that has SUMMARY: We are superseding New Jersey Avenue SE., Washington,
been authorized by the Manager, Seattle Airworthiness Directive (AD) 2006–22– DC 20590.
ACO, to make those findings. To be 15 for all The Boeing Company Model FOR FURTHER INFORMATION CONTACT: Bill
approved, the repair method, modification 747–100, 747–100B, 747–100B SUD,
deviation, or alteration deviation must meet Ashforth, Aerospace Engineer, Airframe
747–200B, 747–200C, 747–200F, 747– Branch, ANM–120S, FAA, Seattle
the certification basis of the airplane, and the
300, 747–400, 747–400D, 747–400F, Aircraft Certification Office (ACO), 1601
approval must specifically refer to this AD.
747SR, and 747SP series airplanes. AD Lind Avenue SW., Renton, WA 98057–
(m) Related Information 2006–22–15 required repetitive 3356; phone: 425–917–6432; fax: 425–
For more information about this AD, inspections for cracking of certain panel 917–6590; email: Bill.Ashforth@faa.gov.
contact Sue Lucier, Aerospace Engineer, webs and stiffeners of the nose wheel
SUPPLEMENTARY INFORMATION:
Propulsion Branch, ANM–140S, FAA, Seattle well (NWW), and corrective actions if
ACO, 1601 Lind Avenue SW., Renton, WA necessary; and replacement of certain Discussion
98057–3356; phone: 425–917–6438; fax: 425– panels with new panels, which
917–6590; email: Suzanne.Lucier@faa.gov. We issued a supplemental notice of
terminates the repetitive inspections. proposed rulemaking (SNPRM) to
(n) Material Incorporated by Reference This new AD reduces a compliance time amend 14 CFR part 39 to supersede AD
(1) The Director of the Federal Register and adds certain inspections and an 2006–22–15, Amendment 39–14812 (71
approved the incorporation by reference applicable repair. This AD was FR 64884, November 6, 2006) (‘‘AD
(IBR) of the service information listed in this prompted by multiple reports of fatigue 2006–22–15’’). AD 2006–22–15 applied
paragraph under 5 U.S.C. 552(a) and 1 CFR cracking in the NWW top panel and side
part 51. to all The Boeing Company Model 747–
panel webs and stiffeners. We are 100, 747–100B, 747–100B SUD, 747–
(2) You must use this service information issuing this AD to prevent fatigue
as applicable to do the actions required by 200B, 747–200C, 747–200F, 747–300,
cracking of the NWW side and top 747–400, 747–400D, 747–400F, 747SR,
this AD, unless the AD specifies otherwise.
(i) GE GEnx–1B Service Bulletin 72–0309 panels, which could result in a NWW and 747SP series airplanes. The SNPRM
R00, dated March 11, 2016. depressurization event severe enough to published in the Federal Register on
reduce the structural integrity of the
asabaliauskas on DSK3SPTVN1PROD with RULES
(ii) Reserved. September 18, 2015 (80 FR 56407) (‘‘the
(3) For service information identified in fuselage. SNPRM’’). We preceded the SNPRM
this AD, contact General Electric Company,
DATES: This AD is effective April 22, with a notice of proposed rulemaking
GE Aviation, Room 285, 1 Neumann Way,
Cincinnati, OH 45215; phone: 513–552–3272; 2016. (NPRM) that published in the Federal
email: geae.aoc@ge.com. The Director of the Federal Register Register on November 17, 2014 (79 FR
(4) You may view this service information approved the incorporation by reference 68388) (‘‘the NPRM’’). The NPRM
at the FAA, Transport Airplane Directorate, of certain publications listed in this AD proposed to continue to require
1601 Lind Avenue SW., Renton, WA. For as of April 22, 2016. repetitive inspections for cracking of
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![14708 Federal Register / Vol. 81, No. 53 / Friday, March 18, 2016 / Rules and Regulations
certain panel webs and stiffeners of the approved AMOCs, if the compliance • Boeing Alert Service Bulletin 747–
NWW, and corrective actions if times are acceptable according to the 53A2808, dated November 30, 2012.
necessary; and replacement of certain SNPRM. This service information describes
panels with new panels, which We agree with the commenter’s procedures for replacement of the side
terminates the repetitive inspections. request. We have revised paragraph and top panel webs, support beams, and
The NPRM proposed to reduce a (p)(4) of this AD to state that: AMOC stiffeners of the NWW; an inspection for
compliance time and add certain actions approved previously for AD cracking of the attaching structural
inspections and repair if necessary. The 2006–22–15 are approved as AMOCs for elements that are common to the
NPRM was prompted by reports of the corresponding actions of this AD. In removed top and side panels of the
fatigue cracking in the panel webs and addition, paragraph (p)(4) of this AD NWW; repetitive post-modification
stiffeners of the NWW found prior to the states that the compliance times in inspections for cracks in the top and
inspection threshold of AD 2006–22–15. AMOCs approved previously for AD side panel webs and stiffeners; and
The SNPRM revised the NPRM by 2006–22–15 are not approved for the repairs.
specifying a repetitive inspection corresponding actions and compliance • Boeing Service Bulletin 747–
interval for a certain NWW area times in this AD, if this AD specifies an 53A2465, Revision 5, dated July 11,
inspection. We are issuing this AD to earlier compliance time than that 2013. This service information describes
prevent fatigue cracking of the NWW specified in AD 2006–22–15; and that procedures for doing inspections for
side and top panels, which could result compliance times in AMOCs approved cracking of the NWW side panel and top
in a NWW depressurization event severe previously for AD 2006–22–15 that meet panel webs and longitudinal stiffeners
enough to reduce the structural integrity the requirements of this AD are for cracks, and related investigative and
of the fuselage. acceptable. corrective actions.
Comments Conclusion • Boeing Service Bulletin 747–
We gave the public the opportunity to 53A2562, Revision 3, dated July 11,
We reviewed the relevant data,
participate in developing this AD. The 2013. This service information describes
considered the comments received, and
following presents the comments procedures for replacement of the side
determined that air safety and the
received on the SNPRM and the FAA’s and top panel webs and certain
public interest require adopting this AD
response to each comment. stiffeners of the NWW; an inspection for
with the change described previously
cracks in attaching structural elements
Support for the SNPRM and minor editorial changes. We have
that are common to the removed top
Two commenters supported the determined that these minor changes:
panel and side panels; repetitive post-
SNPRM. One commenter stated that the • Are consistent with the intent that modification inspections for cracks in
FAA should continue to execute its was proposed in the SNPRM for the top and side panel webs and
administrative power to ensure traveler correcting the unsafe condition; and stiffeners; and repairs.
safety and industry compliance, adding • Do not add any additional burden
upon the public than was already This service information is reasonably
that while the original rule was good, available because the interested parties
ensuring that specifics are covered and proposed in the SNPRM.
We also determined that these have access to it through their normal
timetables are available is an important course of business or by the means
improvement. changes will not increase the economic
burden on any operator or increase the identified in the ADDRESSES section.
Request for Credit for Compliance scope of this AD. Costs of Compliance
Times in Previously Approved
Alternative Methods of Compliance Related Service Information Under We estimate that this AD will affect
(AMOCs) 1 CFR Part 51 255 airplanes of U.S. registry.
Boeing requested that we allow credit We reviewed the following Boeing We estimate the following costs to
for the compliance times in previously service bulletins. comply with this AD:
ESTIMATED COSTS
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
Inspections [actions re- 119 work-hours × $85 per $0 ...................................... $10,115 per inspection $2,579,325 per inspection
tained from AD 2006– hour = $10,115 per in- cycle. cycle.
22–15]. spection cycle.
Modification [actions re- Up to 1,346 work-hours × Up to $144,248 ................. Up to $258,658 ................. Up to $65,957,790.
tained from AD 2006– $85 per hour =
22–15]. $114,410.
Post-modification Inspec- 119 work-hours × $85 per $0 ...................................... $10,115 per inspection $2,579,325 per inspection
tions [new action]. hour = $10,115 per in- cycle. cycle.
spection cycle.
asabaliauskas on DSK3SPTVN1PROD with RULES
We have received no definitive data Authority for This Rulemaking detail the scope of the Agency’s
that would enable us to provide cost Title 49 of the United States Code authority.
estimates for the on-condition actions specifies the FAA’s authority to issue We are issuing this rulemaking under
specified in this AD. rules on aviation safety. Subtitle I, the authority described in Subtitle VII,
Section 106, describes the authority of Part A, Subpart III, Section 44701,
the FAA Administrator. Subtitle VII, ‘‘General requirements.’’ Under that
Aviation Programs, describes in more section, Congress charges the FAA with
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![Federal Register / Vol. 81, No. 53 / Friday, March 18, 2016 / Rules and Regulations 14709
promoting safe flight of civil aircraft in (b) Affected ADs for cracks of the sidewall panel and top panel
air commerce by prescribing regulations This AD replaces AD 2006–22–15, stiffeners of the NWW (specified as Area 3 in
for practices, methods, and procedures Amendment 39–14812 (71 FR 64884, Boeing Service Bulletin 747–53A2465,
November 6, 2006) (‘‘AD 2006–22–15’’). Revision 5, dated July 11, 2013).
the Administrator finds necessary for (3) Do an external detailed and ultrasonic
safety in air commerce. This regulation (c) Applicability testing (UT) inspection for cracks of the top
is within the scope of that authority and sidewall panel webs of the NWW
This AD applies to all The Boeing
because it addresses an unsafe condition Company Model 747–100, 747–100B, 747– (specified as Area 1 and Area 2 in Boeing
that is likely to exist or develop on 100B SUD, 747–200B, 747–200C, 747–200F, Service Bulletin 747–53A2465, Revision 5,
products identified in this rulemaking 747–300, 747–400, 747–400D, 747–400F, dated July 11, 2013).
action. 747SR, and 747SP series airplanes, (h) Exceptions to Boeing Service Bulletin
certificated in any category. 747–53A2465, Revision 5, Dated July 11,
Regulatory Findings
2013
(d) Subject
We have determined that this AD will (1) Table 1 in paragraph 1.E.,
not have federalism implications under Air Transport Association (ATA) of
‘‘Compliance,’’ of Boeing Service Bulletin
America Code 53, Fuselage.
Executive Order 13132. This AD will 747–53A2465, Revision 5, dated July 11,
not have a substantial direct effect on (e) Unsafe Condition 2013, applies to airplanes with less than
the States, on the relationship between 15,000 total flight cycles ‘‘as of the Revision
This AD was prompted by multiple reports
5 date of this service bulletin.’’ For this AD,
the national government and the States, of cracking in the nose wheel well (NWW)
however, table 1 applies to airplanes with the
or on the distribution of power and top panel and side panel webs and stiffeners.
specified total flight cycles as of the effective
responsibilities among the various We are issuing this AD to prevent fatigue
date of this AD.
levels of government. cracking of the NWW side and top panels,
(2) Table 1 in paragraph 1.E.,
which could result in a NWW
For the reasons discussed above, I ‘‘Compliance,’’ of Boeing Service Bulletin
depressurization event severe enough to 747–53A2465, Revision 5, dated July 11,
certify that this AD: reduce the structural integrity of the fuselage. 2013, specifies a compliance time of ‘‘13,000
(1) Is not a ‘‘significant regulatory
(f) Compliance total flight-cycles,’’ or ‘‘within 1,000 flight
action’’ under Executive Order 12866, cycles after the Revision 5 date of this service
(2) Is not a ‘‘significant rule’’ under Comply with this AD within the
bulletin,’’ whichever occurs later. This AD
DOT Regulatory Policies and Procedures compliance times specified, unless already
requires compliance before the accumulation
done.
(44 FR 11034, February 26, 1979), of 10,000 total flight cycles or within 1,000
(3) Will not affect intrastate aviation (g) Repetitive Inspections and Corrective flight cycles after the effective date of this
in Alaska, and Actions With New Compliance Times AD, whichever occurs later.
Except as specified in paragraphs (h)(1) (3) If any cracking or damage is found
(4) Will not have a significant during any inspection required by paragraph
economic impact, positive or negative, and (h)(2) of this AD, at the applicable time
(g) of this AD, and Boeing Service Bulletin
on a substantial number of small entities specified in paragraph 1.E., ‘‘Compliance,’’ of
747–53A2465, Revision 5, dated July 11,
Boeing Service Bulletin 747–53A2465,
under the criteria of the Regulatory Revision 5, dated July 11, 2013: Do the
2013, specifies to contact Boeing for
Flexibility Act. appropriate action: Before further flight,
actions specified in paragraphs (g)(1), (g)(2),
repair the cracking or damage using a method
List of Subjects in 14 CFR Part 39 and (g)(3) of this AD, and do all applicable
approved in accordance with the procedures
related investigative and corrective actions;
specified in paragraph (p) of this AD.
Air transportation, Aircraft, Aviation in accordance with the Accomplishment
safety, Incorporation by reference, Instructions of Boeing Service Bulletin 747– (i) NWW Modification
Safety. 53A2465, Revision 5, dated July 11, 2013, For airplanes identified in Boeing Service
except as specified in paragraph (h)(3) of this Bulletin 747–53A2562, Revision 3, dated July
Adoption of the Amendment AD. Do all applicable related investigative 11, 2013: At the applicable time specified in
and corrective actions before further flight. paragraph 1.E., ‘‘Compliance,’’ of Boeing
Accordingly, under the authority Repeat the inspections specified in
delegated to me by the Administrator, Service Bulletin 747–53A2562, Revision 3,
paragraphs (g)(1), (g)(2), and (g)(3) of this AD dated July 11, 2013, replace the left-side,
the FAA amends 14 CFR part 39 as thereafter at the applicable intervals specified right-side, and top panels of the NWW, as
follows: in paragraph 1.E., ‘‘Compliance,’’ of Boeing applicable, with new panels, in accordance
Service Bulletin 747–53A2465, Revision 5, with the Accomplishment Instructions of
PART 39—AIRWORTHINESS dated July 11, 2013. The repetitive interval Boeing Service Bulletin 747–53A2562,
DIRECTIVES for the inspection of Area 2 specified in table Revision 3, dated July 11, 2013. As of the
1 in paragraph 1.E., ‘‘Compliance,’’ of Boeing effective date of this AD, concurrently with
■ 1. The authority citation for part 39 Service Bulletin 747–53A2465, Revision 5, doing the replacement specified in Boeing
continues to read as follows: dated July 11, 2013, is 1,000 flight cycles. In Service Bulletin 747–53A2562, Revision 3,
table 2 and table 3 in paragraph 1.E., dated July 11, 2013, do a detailed inspection
Authority: 49 U.S.C. 106(g), 40113, 44701. ‘‘Compliance,’’ of Boeing Service Bulletin for any cracks or damage (including, but not
§ 39.13 [Amended] 747–53A2465, Revision 5, dated July 11, limited to, dents and corrosion) in all
2013, the date ‘‘January 27, 2005,’’ is the attaching structural elements that are
■ 2. The FAA amends § 39.13 by effective date of AD 2004–25–23, common to the removed top panel and side
removing Airworthiness Directive (AD) Amendment 39–13911 (69 FR 76839, panels, as applicable, and do all applicable
2006–22–15, Amendment 39–14812 (71 December 23, 2004); and the date ‘‘May 10, corrective actions, in accordance with the
FR 64884, November 6, 2006) (‘‘AD 2005,’’ is the effective date of AD 2005–09– Accomplishment Instructions of Boeing
02, Amendment 39–14070 (70 FR 21141, Service Bulletin 747–53A2562, Revision 3,
2006–22–15’’), and adding the following
asabaliauskas on DSK3SPTVN1PROD with RULES
April 25, 2005; corrected May 25, 2005 (70 dated July 11, 2013. If any crack or damage
new AD: FR 29940)). is found, before further flight, repair the
2016–06–07 The Boeing Company: (1) Do an external detailed inspection for cracking or damage using a method approved
Amendment 39–18438; Docket No. cracks of the top and sidewall panel webs of in accordance with the procedures specified
FAA–2014–0774; Directorate Identifier the NWW (specified as Area 1 and Area 2 in in paragraph (p) of this AD. In paragraph 1.E.,
2013–NM–154–AD. Boeing Service Bulletin 747–53A2465, ‘‘Compliance,’’ of Boeing Service Bulletin
Revision 5, dated July 11, 2013). 747–53A2562, Revision 3, dated July 11,
(a) Effective Date (2) Do internal detailed and surface high 2013, the date ‘‘December 11, 2006,’’ is the
This AD is effective April 22, 2016. frequency eddy current (HFEC) inspections effective date of AD 2006–22–15.
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![Federal Register / Vol. 81, No. 53 / Friday, March 18, 2016 / Rules and Regulations 14711
(IBR) of the service information listed in this actions if necessary. This AD also Discussion
paragraph under 5 U.S.C. 552(a) and 1 CFR provides an optional preventive
part 51. We issued a notice of proposed
modification that terminates the rulemaking (NPRM) to amend 14 CFR
(2) You must use this service information
as applicable to do the actions required by
inspections at the modified location. We part 39 by adding an AD that would
this AD, unless the AD specifies otherwise. are issuing this AD to detect and correct apply to certain The Boeing Company
(i) Boeing Alert Service Bulletin 747– fatigue cracking around fastener Model 737–300, –400, and –500 series
53A2808, dated November 30, 2012. locations that could cause multiple airplanes. The NPRM published in the
(ii) Boeing Service Bulletin 747–53A2465, window corner skin cracks, which Federal Register on March 24, 2015 (80
Revision 5, dated July 11, 2013. could result in rapid decompression and FR 15523) (‘‘the NPRM’’). The NPRM
(iii) Boeing Service Bulletin 747–53A2562, loss of structural integrity of the
Revision 3, dated July 11, 2013.
was prompted by reports of cracking at
airplane. certain fastener locations in the window
(3) For Boeing service information
identified in this AD, contact Boeing corners of the window belt area. The
DATES: This AD is effective April 22, NPRM proposed to require repetitive
Commercial Airplanes, Attention: Data &
Services Management, P.O. Box 3707, MC
2016. HFEC inspections for fatigue cracking in
2H–65, Seattle, WA 98124–2207; telephone The Director of the Federal Register certain fastener locations in the window
206–544–5000, extension 1; fax 206–766– approved the incorporation by reference corners of the window belt area, and
5680; Internet https:// of a certain publication listed in this AD related investigative and corrective
www.myboeingfleet.com. as of April 22, 2016. actions if necessary. We are issuing this
(4) You may view this service information
at the FAA, Transport Airplane Directorate,
AD to detect and correct fatigue
ADDRESSES: For service information
1601 Lind Avenue SW., Renton, WA. For cracking around fastener locations that
identified in this final rule, contact
information on the availability of this could cause multiple window corner
Boeing Commercial Airplanes,
material at the FAA, call 425–227–1221. skin cracks, which could result in rapid
Attention: Data & Services Management,
(5) You may view this service information decompression and loss of structural
that is incorporated by reference at the P.O. Box 3707, MC 2H–65, Seattle, WA integrity of the airplane.
National Archives and Records 98124–2207; telephone 206–544–5000,
Administration (NARA). For information on extension 1; fax 206–766–5680; Internet Comments
the availability of this material at NARA, call https://www.myboeingfleet.com. You We gave the public the opportunity to
202–741–6030, or go to: http:// may view this referenced service participate in developing this AD. The
www.archives.gov/federal-register/cfr/ibr- information at the FAA, Transport following presents the comments
locations.html. Airplane Directorate, 1601 Lind Avenue received on the NPRM and the FAA’s
Issued in Renton, Washington, on March 9, SW., Renton, WA. For information on response to each comment.
2016. the availability of this material at the
Michael Kaszycki, FAA, call 425–227–1221. It is also Request for Clarification of Location of
Acting Manager, Transport Airplane available on the Internet at http:// the Twelve Fastener Inspections
Directorate, Aircraft Certification Service. www.regulations.gov by searching for Southwest Airlines (SWA) requested
[FR Doc. 2016–06001 Filed 3–17–16; 8:45 am] and locating Docket No. FAA–2015– that a correction be made to paragraph
BILLING CODE 4910–13–P 0495. (g) of the proposed AD to clarify the
areas for the inspection of the twelve
Examining the AD Docket fastener locations. SWA noted that
DEPARTMENT OF TRANSPORTATION You may examine the AD docket on paragraph (g) of the proposed AD stated
the Internet at http:// to inspect locations ‘‘at the upper
Federal Aviation Administration forward and lower aft corners of each
www.regulations.gov by searching for
and locating Docket No. FAA–2015– window between station (STA) 360 and
14 CFR Part 39 STA 540 and between STA 727 and
0495; or in person at the Docket
[Docket No. FAA–2015–0495; Directorate Management Facility between 9 a.m. STA 908.’’ SWA stated that between
Identifier 2014–NM–172–AD; Amendment and 5 p.m., Monday through Friday, STA 727 and STA 908, Boeing Alert
39–18435; AD 2016–06–04] except Federal holidays. The AD docket Service Bulletin 737–53A1328, dated
contains this AD, the regulatory July 22, 2014, specifies the location as
RIN 2120–AA64 the lower forward and upper aft corners.
evaluation, any comments received, and
We agree with the commenter for the
Airworthiness Directives; The Boeing other information. The address for the
reason provided. We have revised
Company Airplanes Docket Office (phone: 800–647–5527) is
paragraph (g) of this AD to require an
Docket Management Facility, U.S. inspection of the twelve fastener
AGENCY: Federal Aviation
Department of Transportation, Docket locations at the upper forward and
Administration (FAA), DOT.
Operations, M–30, West Building lower aft corners of each window
ACTION: Final rule.
Ground Floor, Room W12–140, 1200 between STA 360 and STA 540 and at
SUMMARY: We are adopting a new New Jersey Avenue SE., Washington, the upper aft and lower forward corners
airworthiness directive (AD) for certain DC 20590. of each window between STA 727 and
The Boeing Company Model 737–300, FOR FURTHER INFORMATION CONTACT: STA 908.
–400, and –500 series airplanes. This Jennifer Tsakoumakis, Aerospace
AD was prompted by reports of cracking Request for Clarification of the Intent of
Engineer, Airframe Branch, ANM–120L,
asabaliauskas on DSK3SPTVN1PROD with RULES
at certain fastener locations in the the Inspection Requirements in
FAA, Los Angeles Aircraft Certification Paragraph (g) of the Proposed AD
window corners of the window belt Office (ACO), 3960 Paramount
area. This AD requires repetitive high Boulevard, Lakewood, CA 90712–4137; SWA requested that we clarify the
frequency eddy current (HFEC) phone: 562–627–5264; fax: 562–627– intent of paragraph (g) of the proposed
inspections for fatigue cracking in 5210; email: jennifer.tsakoumakis@ AD. SWA stated that paragraph (g) of
certain fastener locations in the window faa.gov. the proposed AD states to accomplish
corners of the window belt area, and the inspections at the times specified in
related investigative and corrective SUPPLEMENTARY INFORMATION: tables 1 and 2 of paragraph 1.E.,
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Document Created: 2018-02-02 15:14:14
Document Modified: 2018-02-02 15:14:14
| 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 April 22, 2016. | |
| Contact | Bill Ashforth, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917- 6432; fax: 425-917-6590; email: [email protected] | |
| FR Citation | 81 FR 14707 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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