80 FR 43648 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 80, Issue 141 (July 23, 2015)
Federal Aviation Administration
Federal Register Volume 80, Issue 141 (July 23, 2015)
| Page Range | 43648-43651 | |
| FR Document | 2015-17932 |
[Federal Register Volume 80, Number 141 (Thursday, July 23, 2015)] [Proposed Rules] [Pages 43648-43651] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2015-17932] [[Page 43648]] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-2464; Directorate Identifier 2014-NM-195-AD] RIN 2120-AA64 Airworthiness Directives; The Boeing Company Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). ----------------------------------------------------------------------- SUMMARY: We propose to supersede Airworthiness Directive (AD) 2013-22- 11, which applies to certain The Boeing Company Model 747-400 and -400D series airplanes. AD 2013-22-11 currently requires repetitive inspections to detect cracks in the floor panel attachment fastener holes of certain upper deck floor beam upper chords, repetitive inspections, corrective actions if necessary, and replacement of the upper deck floor beam upper chords. Since we issued AD 2013-22-11, we received a report that certain fastener holes in the upper deck floor beam upper chords may not have been inspected in accordance with AD 2013-22-11. This proposed AD would add additional repetitive inspections for cracks for certain airplanes, and corrective actions if necessary. We are proposing this AD to detect and correct fatigue cracking in certain upper chords of the upper deck floor beam, which could become large and cause the floor beams to become severed and result in rapid decompression or reduced controllability of the airplane. DATES: We must receive comments on this proposed AD by September 8, 2015. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods:Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. Fax: 202-493-2251. Mail: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590. Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed 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. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015- 2464. Examining the AD Docket You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015- 2464; 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 proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (phone: 800-647-5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Nathan Weigand, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917- 6428; fax: 425-917-6590; email: [email protected]. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ``Docket No. FAA-2015-2464; Directorate Identifier 2014-NM-195-AD'' at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD because of those comments. We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion Structural fatigue damage is progressive. It begins as minute cracks, and those cracks grow under the action of repeated stresses. This can happen because of normal operational conditions and design attributes, or because of isolated situations or incidents such as material defects, poor fabrication quality, or corrosion pits, dings, or scratches. Fatigue damage can occur locally, in small areas or structural design details, or globally. Global fatigue damage is general degradation of large areas of structure with similar structural details and stress levels. Multiple-site damage is global damage that occurs in a large structural element such as a single rivet line of a lap splice joining two large skin panels. Global damage can also occur in multiple elements such as adjacent frames or stringers. Multiple- site-damage and multiple-element-damage cracks are typically too small initially to be reliably detected with normal inspection methods. Without intervention, these cracks will grow, and eventually compromise the structural integrity of the airplane, in a condition known as widespread fatigue damage (WFD). As an airplane ages, WFD will likely occur, and will certainly occur if the airplane is operated long enough without any intervention. The FAA's WFD final rule (75 FR 69746, November 15, 2010), became effective on January 14, 2011. The WFD rule requires certain actions to prevent structural failure due to WFD throughout the operational life of certain existing transport category airplanes and all of these airplanes that will be certificated in the future. For existing and future airplanes subject to the WFD rule, the rule requires that design approval holders (DAH) establish a limit of validity (LOV) of the engineering data that support the structural maintenance program. Operators affected by the WFD rule may not fly an airplane beyond its LOV, unless an extended LOV is approved. The WFD rule (75 FR 69746, November 15, 2010), does not require identifying and developing maintenance actions if the DAHs can show that such actions are not necessary to prevent WFD before the airplane reaches the LOV. Many LOVs, however, do depend on accomplishment of future maintenance actions. As stated in the WFD rule, any maintenance actions necessary to reach the LOV will be mandated by airworthiness directives through separate rulemaking actions. In the context of WFD, this action is necessary to enable DAHs to propose LOVs that allow operators the longest operational lives for their airplanes, and still ensure that WFD will not occur. [[Page 43649]] This approach allows for an implementation strategy that provides flexibility to DAHs in determining the timing of service information development (with FAA approval), while providing operators with certainty regarding the LOV applicable to their airplanes. On October 17, 2013, we issued AD 2013-22-11, Amendment 39-17643 (78 FR 66254, November 5, 2013), for certain The Boeing Company Model 747-400 and -400D series airplanes. AD 2013-22-11 requires repetitive inspections to detect cracks in the floor panel attachment fastener holes of the Section 41 upper deck floor beam upper chords, and corrective actions if necessary; repetitive post-repair and post- modification inspections, and corrective actions if necessary; repetitive inspections of Section 44 upper deck floor beam upper chords, and corrective actions if necessary; repetitive post-repair and post-modification inspections, and corrective actions if necessary; and replacement of the upper deck floor beam upper chords. AD 2013-22-11 superseded AD 2009-10-06, Amendment 39-15901 (74 FR 22424, May 13, 2009). AD 2013-22-11 resulted from an evaluation by the design approval holder (DAH) indicating that certain upper chords of the upper deck floor beam are subject to widespread fatigue damage (WFD). We issued AD 2013-22-11 to detect and correct fatigue cracking in certain upper chords of the upper deck floor beam, which could become large and cause the floor beams to become severed and result in rapid decompression or reduced controllability of the airplane. Actions Since AD 2013-22-11, Amendment 39-17643 (78 FR 66254, November 5, 2013), Was Issued Since we issued AD 2013-22-11, Amendment 39-17643 (78 FR 66254, November 5, 2013), an evaluation by the DAH indicated that certain fastener holes in the upper deck floor beam upper chords in Section 41, that were plugged or re-used during the conversion to a Boeing Converted Freighter, may not have been inspected in accordance with the requirements of AD 2013-22-11, because the locations may be hidden and not recognized as inspection locations. We have determined that, for certain airplanes, it is necessary to add additional repetitive inspections for cracks in the Section 41 upper deck floor beam upper chords and repair if necessary. Related Service Information Under 1 CFR Part 51 We reviewed Boeing Alert Service Bulletin 747-53A2688, Revision 2, dated August 21, 2014. The service information describes procedures for upper deck floor beam upper chord inspection and repair at floor panel attachment fastener holes in section 41 and section 42. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section of this NPRM. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-2464. FAA's Determination We are proposing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. Proposed AD Requirements Although this proposed AD does not explicitly restate the requirements of AD 2013-22-11, Amendment 39-17643 (78 FR 66254, November 5, 2013), this proposed AD would retain all of the requirements of AD 2013-22-11. Those requirements are referenced in the service information identified previously, which, in turn, is referenced in paragraphs (g) through (k) of this proposed AD. This proposed AD would add new actions. This proposed AD would require accomplishing the actions specified in the service information identified previously, except as discussed under ``Differences Between this Proposed AD and the Service Information.'' Refer to this service information for information on the procedures and compliance times. In addition, the phrase ``corrective actions'' might be used in this proposed AD. ``Corrective actions'' are actions that correct or address any condition found. Corrective actions in an AD could include, for example, repairs. Differences Between This Proposed AD and the Service Information Boeing Alert Service Bulletin 747-53A2688, Revision 2, dated August 21, 2014, specifies to contact the manufacturer for instructions on how to repair certain conditions, but this proposed AD would require repairing those conditions in one of the following ways: In accordance with a method that we approve; or Using data that meet the certification basis of the airplane, and that have been approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) whom we have authorized to make those findings. Costs of Compliance We estimate that this proposed AD affects 84 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: Estimated Costs ---------------------------------------------------------------------------------------------------------------- Cost on U.S. Action Labor cost Parts cost Cost per product operators ---------------------------------------------------------------------------------------------------------------- Inspection (retained actions from Up to 309 work- $0 Up to $26,265 per Up to $2,206,260 AD 2013-22-11, Amendment 39- hours x $85 per inspection cycle. per inspection 17643 (78 FR 66254, November 5, hour = $26,265 per cycle. 2013)). inspection cycle. New Inspections.................. Up to 241 work- $0 Up to $20,485 per Up to $1,720,740 hours x $85 per inspection cycle. per inspection hour = $20,485. cycle. ---------------------------------------------------------------------------------------------------------------- We have received no definitive data that would enable us to provide a cost estimate for the repair or modification specified in this proposed 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, [[Page 43650]] 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 proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 the proposed regulation: (1) Is not a ``significant regulatory action'' under Executive Order 12866, (2) Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation in Alaska, and (4) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 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) 2013-22-11, Amendment 39-17643 (78 FR 66254, November 5, 2013), and adding the following new AD: The Boeing Company: Docket No. FAA-2015-2464; Directorate Identifier 2014-NM-195-AD. (a) Comments Due Date The FAA must receive comments on this AD action by September 8, 2015. (b) Affected ADs This AD replaces AD 2013-22-11, Amendment 39-17643 (78 FR 66254, November 5, 2013). (c) Applicability (1) This AD applies to The Boeing Company Model 747-400 and - 400D series airplanes, certificated in any category, as identified in Boeing Alert Service Bulletin 747-53A2688, Revision 2, dated August 21, 2014. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Unsafe Condition This AD was prompted by an evaluation by the design approval holder (DAH) indicating that certain upper chords of the upper deck floor beam are subject to widespread fatigue damage (WFD). This AD was also prompted by reports that certain fastener holes in the upper deck floor beam upper chords in Section 41, may not have been inspected in accordance with AD 2013-22-11, Amendment 39-17643 (78 FR 66254, November 5, 2013). We are issuing this AD to detect and correct fatigue cracking in certain upper chords of the upper deck floor beam, which could become large and cause the floor beams to become severed and result in rapid decompression or reduced controllability of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Section 41--Repetitive Inspections, and Corrective Actions At the applicable time specified in table 1 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2688, Revision 2, dated August 21, 2014, do open hole or surface high frequency eddy current inspections for cracking of the floor panel attachment holes in the upper deck floor beam upper chords, in accordance with Part 1 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747-53A2688, Revision 2, dated August 21, 2014. If any crack is found during any inspection, before further flight, repair in accordance with Part 2 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747-53A2688, Revision 2, dated August 21, 2014, or repair using a method approved in accordance with procedures specified in paragraph (o) of this AD. Repeat the inspections thereafter at the applicable time specified in table 1 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2688, Revision 2, dated August 21, 2014, until an action specified in paragraph (g)(1) or (g)(2) of this AD is done. (1) Doing a repair as a hole modification in accordance with Part 2 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747-53A2688, Revision 2, dated August 21, 2014, except as required by paragraph (m)(2) of this AD, terminates the inspections required by paragraph (g) of this AD for the modified hole only. (2) Doing a modification in accordance with Figure 5 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747- 53A2688, Revision 2, dated August 21, 2014, except as required by paragraph (m)(2) of this AD, terminates the inspections required by paragraph (g) of this AD for the modification only. (h) Section 41--Repetitive Inspection of Repaired or Modified Holes, and Corrective Actions For airplanes on which a repair specified in Part 2 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747- 53A2688 is done or a modification specified in Figure 5 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747- 53A2688 is done: At the applicable time specified in table 2 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2688, Revision 2, dated August 21, 2014, except as required by paragraph (m)(3) of this AD, do open hole or surface high frequency eddy current inspections for cracking of repaired or modified floor panel attachment holes in the upper deck floor beam upper chords, in accordance with Part 1 or Part 3, as applicable, of the Accomplishment Instructions of Boeing Alert Service Bulletin 747-53A2688, Revision 2, dated August 21, 2014. If any crack is found during any inspection required by this paragraph, before further flight, repair using a method approved in accordance with the procedures specified in paragraph (o) of this AD. Repeat the inspections thereafter at the applicable time specified in table 2 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2688, Revision 2, dated August 21, 2014. (i) Section 44--Repetitive Inspection, and Corrective Actions For airplanes identified in Group 1 in Boeing Alert Service Bulletin 747-53A2688, Revision 2, dated August 21, 2014: At the applicable time specified in table 3 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2688, Revision 2, dated August 21, 2014, except as required by paragraph (m)(4) of this AD, do open hole or surface high frequency eddy current inspections of the floor panel attachment holes in the upper deck floor beam upper chords, in accordance with Part 4 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747- 53A2688, Revision 2, dated August 21, 2014. If any crack is found during any inspection required by this paragraph, before further flight, repair in accordance with Part 5 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747-53A2688, Revision 2, dated August 21, 2014, except as required by paragraph (m)(2) of this AD. Repeat the inspections thereafter at the applicable time specified in table 3 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2688, Revision 2, dated August 21, 2014, until an action specified in paragraph (i)(1) or (i)(2) of this AD is done. [[Page 43651]] (1) Doing a repair as a hole modification in accordance with Part 5 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747-53A2688, Revision 2, dated August 21, 2014, except as required by paragraph (m)(2) of this AD, terminates the inspections required by paragraph (i) of this AD for that modified hole only. (2) Doing a modification in accordance with Figure 21 of Boeing Alert Service Bulletin 747-53A2688, Revision 2, dated August 21, 2014, except as required by paragraph (m)(2) of this AD, terminates the inspections required by paragraph (i) of this AD for that modified hole only. (j) Section 44--Repetitive Inspection of Repaired or Modified Holes, and Corrective Actions For airplanes identified in Group 1 in Boeing Alert Service Bulletin 747-53A2688, Revision 2, dated August 21, 2014, on which a repair specified in Part 5 of Boeing Alert Service Bulletin 747- 53A2688 is done or a modification specified in Figure 21 of Boeing Alert Service Bulletin 747-53A2688 is done: At the applicable time specified in table 4 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2688, Revision 2, dated August 21, 2014, except as required by paragraph (m)(3) of this AD, do open hole or surface high frequency eddy current inspections of repaired or modified floor panel attachment holes in the upper deck floor beam upper chords, in accordance with Part 4 or Part 6, as applicable, of the Accomplishment Instructions of Boeing Alert Service Bulletin 747-53A2688, Revision 2, dated August 21, 2014. If any crack is found during any inspection by this paragraph, before further flight, repair using a method approved in accordance with the procedures specified in paragraph (o) of this AD. Repeat the inspections thereafter at the applicable time specified in table 4 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2688, Revision 2, dated August 21, 2014. (k) Section 41 and 44--Replacement and Post-Replacement Repetitive Inspections At the applicable time specified in table 5 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2688, Revision 2, dated August 21, 2014: Replace all upper deck floor beam upper chords, in accordance with Part 7 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747-53A2688, Revision 2, dated August 21, 2014. Within 20,000 flight cycles after doing the replacement, do the inspections specified in paragraphs (g) and (i) of this AD, as applicable. Thereafter, repeat the inspections required by paragraphs (g) and (i) of this AD, as applicable, at the times specified in paragraphs (g) and (i) of this AD. (l) Section 41--Repetitive Inspection of Plugged or Re-Used Holes, and Corrective Actions For airplanes identified in Group 2 in Boeing Alert Service Bulletin 747-53A2688, Revision 2, dated August 21, 2014: At the applicable time specified in table 6 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2688, Revision 2, dated August 21, 2014, except as required by paragraph (m)(1) of this AD, at all plugged or re-used floor panel attachment holes in the affected floor beam upper chords, do a surface high frequency eddy current inspection of the upper deck floor beam upper chords and detailed inspection for cracks on the vertical flange, in accordance with Part 8 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747-53A2688, Revision 2, dated August 21, 2014. If any crack is found during any inspection required by this paragraph, before further flight, repair using a method approved in accordance with the procedures specified in paragraph (o) of this AD. Repeat the inspections thereafter at the applicable time specified in table 6 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2688, Revision 2, dated August 21, 2014. (m) Exceptions to Service Information Specifications (1) Where Boeing Alert Service Bulletin 747-53A2688, Revision 2, dated August 21, 2014, specifies a compliance time ``after the Revision 2 date of this service bulletin,'' this AD requires compliance within the specified compliance time after the effective date of this AD. (2) Where Boeing Alert Service Bulletin 747-53A2688, Revision 2, dated August 21, 2014; specifies to contact Boeing for certain procedures: Do the specified actions before further flight using a method approved in accordance with the procedures specified in paragraph (o) of this AD. (3) Where table 2 or table 4 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2688, Revision 2, dated August 21, 2014, specifies to contact Boeing for inspections and compliance times: Before further flight, contact the Manager, FAA, Seattle Aircraft Certification Office (ACO), for inspections and compliance times and accomplish the inspections at the given times. (4) Where Boeing Alert Service Bulletin 747-53A2688, Revision 1, dated September 19, 2012, specifies a compliance time ``after the Revision 1 date of this service bulletin,'' this AD requires compliance within the specified compliance time after December 10, 2013 (the effective date of AD 2013-22-11, Amendment 39-17643 (78 FR 66254, November 5, 2013)). (n) Credit for Previous Actions (1) This paragraph restates the requirements of paragraph (o) of AD 2013-22-11, Amendment 39-17643 (78 FR 66254, November 5, 2013), with new paragraph (h). This paragraph provides credit for the actions required by paragraphs (g) and (h) of this AD, if those actions were performed before December 10, 2013 (the effective date of AD 2013-22-11) using Boeing Alert Service Bulletin 747-53A2688, dated August 21, 2008. (2) This paragraph provides credit for the actions required by paragraphs (g) through (k) of this AD, if those actions were performed before the effective date of this AD using Boeing Alert Service Bulletin 747-53A2688, Revision 1, dated September 19, 2012, which is not incorporated by reference in this AD. (o) 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 (p)(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 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. For a repair method to be approved, the repair must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (4) AMOCs approved for AD 2013-22-11, Amendment 39-17643 (78 FR 66254, November 5, 2013), are approved as AMOCs for the corresponding provisions of paragraphs (g) through (k) of this AD. (p) Related Information (1) For more information about this AD, contact Nathan Weigand, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057- 3356; phone: 425-917-6428; fax: 425-917-6590; email: [email protected]. (2) For 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; phone: 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. Issued in Renton, Washington, on July 15, 2015. Suzanne Masterson, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015-17932 Filed 7-22-15; 8:45 am] BILLING CODE 4910-13-P
![43648 Federal Register / Vol. 80, No. 141 / Thursday, July 23, 2015 / Proposed Rules
DEPARTMENT OF TRANSPORTATION MC 2H–65, Seattle, WA 98124–2207; and those cracks grow under the action
telephone 206–544–5000, extension 1; of repeated stresses. This can happen
Federal Aviation Administration fax 206–766–5680; Internet https:// because of normal operational
www.myboeingfleet.com. You may view conditions and design attributes, or
14 CFR Part 39 this referenced service information at because of isolated situations or
[Docket No. FAA–2015–2464; Directorate the FAA, Transport Airplane incidents such as material defects, poor
Identifier 2014–NM–195–AD] Directorate, 1601 Lind Avenue SW., fabrication quality, or corrosion pits,
Renton, WA. For information on the dings, or scratches. Fatigue damage can
RIN 2120–AA64 availability of this material at the FAA, occur locally, in small areas or
call 425–227–1221. It is also available structural design details, or globally.
Airworthiness Directives; The Boeing on the Internet at http:// Global fatigue damage is general
Company Airplanes www.regulations.gov by searching for degradation of large areas of structure
AGENCY: Federal Aviation and locating Docket No. FAA–2015– with similar structural details and stress
Administration (FAA), DOT. 2464. levels. Multiple-site damage is global
ACTION: Notice of proposed rulemaking
damage that occurs in a large structural
Examining the AD Docket
(NPRM). element such as a single rivet line of a
You may examine the AD docket on lap splice joining two large skin panels.
SUMMARY: We propose to supersede the Internet at http:// Global damage can also occur in
Airworthiness Directive (AD) 2013–22– www.regulations.gov by searching for multiple elements such as adjacent
11, which applies to certain The Boeing and locating Docket No. FAA–2015– frames or stringers. Multiple-site-
Company Model 747–400 and –400D 2464; or in person at the Docket damage and multiple-element-damage
series airplanes. AD 2013–22–11 Management Facility between 9 a.m. cracks are typically too small initially to
currently requires repetitive inspections and 5 p.m., Monday through Friday, be reliably detected with normal
to detect cracks in the floor panel except Federal holidays. The AD docket inspection methods. Without
attachment fastener holes of certain contains this proposed AD, the intervention, these cracks will grow,
upper deck floor beam upper chords, regulatory evaluation, any comments and eventually compromise the
repetitive inspections, corrective actions received, and other information. The structural integrity of the airplane, in a
if necessary, and replacement of the street address for the Docket Office condition known as widespread fatigue
upper deck floor beam upper chords. (phone: 800–647–5527) is in the damage (WFD). As an airplane ages,
ADDRESSES section. Comments will be WFD will likely occur, and will
Since we issued AD 2013–22–11, we
received a report that certain fastener available in the AD docket shortly after certainly occur if the airplane is
holes in the upper deck floor beam receipt. operated long enough without any
upper chords may not have been FOR FURTHER INFORMATION CONTACT: intervention.
inspected in accordance with AD 2013– Nathan Weigand, Aerospace Engineer, The FAA’s WFD final rule (75 FR
22–11. This proposed AD would add Airframe Branch, ANM–120S, FAA, 69746, November 15, 2010), became
additional repetitive inspections for Seattle Aircraft Certification Office effective on January 14, 2011. The WFD
cracks for certain airplanes, and (ACO), 1601 Lind Avenue SW., Renton, rule requires certain actions to prevent
corrective actions if necessary. We are WA 98057–3356; phone: 425–917–6428; structural failure due to WFD
proposing this AD to detect and correct fax: 425–917–6590; email: throughout the operational life of
fatigue cracking in certain upper chords Nathan.P.Weigand@faa.gov. certain existing transport category
of the upper deck floor beam, which SUPPLEMENTARY INFORMATION: airplanes and all of these airplanes that
could become large and cause the floor will be certificated in the future. For
Comments Invited existing and future airplanes subject to
beams to become severed and result in
rapid decompression or reduced We invite you to send any written the WFD rule, the rule requires that
relevant data, views, or arguments about design approval holders (DAH) establish
controllability of the airplane.
this proposed AD. Send your comments a limit of validity (LOV) of the
DATES: We must receive comments on to an address listed under the engineering data that support the
this proposed AD by September 8, 2015. ADDRESSES section. Include ‘‘Docket No. structural maintenance program.
ADDRESSES: You may send comments, FAA–2015–2464; Directorate Identifier Operators affected by the WFD rule may
using the procedures found in 14 CFR 2014–NM–195–AD’’ at the beginning of not fly an airplane beyond its LOV,
11.43 and 11.45, by any of the following your comments. We specifically invite unless an extended LOV is approved.
methods: comments on the overall regulatory, The WFD rule (75 FR 69746,
• Federal eRulemaking Portal: Go to economic, environmental, and energy November 15, 2010), does not require
http://www.regulations.gov. Follow the aspects of this proposed AD. We will identifying and developing maintenance
instructions for submitting comments. consider all comments received by the actions if the DAHs can show that such
• Fax: 202–493–2251. closing date and may amend this actions are not necessary to prevent
• Mail: U.S. Department of proposed AD because of those WFD before the airplane reaches the
Transportation, Docket Operations, M– comments. LOV. Many LOVs, however, do depend
30, West Building Ground Floor, Room We will post all comments we on accomplishment of future
W12–140, 1200 New Jersey Avenue SE., receive, without change, to http:// maintenance actions. As stated in the
Washington, DC 20590. WFD rule, any maintenance actions
mstockstill on DSK4VPTVN1PROD with PROPOSALS
www.regulations.gov, including any
• Hand Delivery: Deliver to Mail personal information you provide. We necessary to reach the LOV will be
address above between 9 a.m. and 5 will also post a report summarizing each mandated by airworthiness directives
p.m., Monday through Friday, except substantive verbal contact we receive through separate rulemaking actions.
Federal holidays. about this proposed AD. In the context of WFD, this action is
For service information identified in necessary to enable DAHs to propose
this proposed AD, contact Boeing Discussion LOVs that allow operators the longest
Commercial Airplanes, Attention: Data Structural fatigue damage is operational lives for their airplanes, and
& Services Management, P.O. Box 3707, progressive. It begins as minute cracks, still ensure that WFD will not occur.
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![43650 Federal Register / Vol. 80, No. 141 / Thursday, July 23, 2015 / Proposed Rules
Part A, Subpart III, Section 44701, (a) Comments Due Date paragraph (m)(2) of this AD, terminates the
‘‘General requirements.’’ Under that The FAA must receive comments on this inspections required by paragraph (g) of this
section, Congress charges the FAA with AD action by September 8, 2015. AD for the modified hole only.
(2) Doing a modification in accordance
promoting safe flight of civil aircraft in (b) Affected ADs with Figure 5 of the Accomplishment
air commerce by prescribing regulations Instructions of Boeing Alert Service Bulletin
This AD replaces AD 2013–22–11,
for practices, methods, and procedures Amendment 39–17643 (78 FR 66254, 747–53A2688, Revision 2, dated August 21,
the Administrator finds necessary for November 5, 2013). 2014, except as required by paragraph (m)(2)
safety in air commerce. This regulation of this AD, terminates the inspections
is within the scope of that authority (c) Applicability required by paragraph (g) of this AD for the
because it addresses an unsafe condition (1) This AD applies to The Boeing modification only.
that is likely to exist or develop on Company Model 747–400 and –400D series
airplanes, certificated in any category, as (h) Section 41—Repetitive Inspection of
products identified in this rulemaking Repaired or Modified Holes, and Corrective
identified in Boeing Alert Service Bulletin
action. 747–53A2688, Revision 2, dated August 21, Actions
Regulatory Findings 2014. For airplanes on which a repair specified
in Part 2 of the Accomplishment Instructions
We have determined that this (d) Subject
of Boeing Alert Service Bulletin 747–
proposed AD would not have federalism Air Transport Association (ATA) of 53A2688 is done or a modification specified
implications under Executive Order America Code 53, Fuselage. in Figure 5 of the Accomplishment
13132. This proposed AD would not (e) Unsafe Condition Instructions of Boeing Alert Service Bulletin
have a substantial direct effect on the 747–53A2688 is done: At the applicable time
This AD was prompted by an evaluation by specified in table 2 of paragraph 1.E.,
States, on the relationship between the the design approval holder (DAH) indicating ‘‘Compliance,’’ of Boeing Alert Service
national Government and the States, or that certain upper chords of the upper deck Bulletin 747–53A2688, Revision 2, dated
on the distribution of power and floor beam are subject to widespread fatigue August 21, 2014, except as required by
responsibilities among the various damage (WFD). This AD was also prompted paragraph (m)(3) of this AD, do open hole or
levels of government. by reports that certain fastener holes in the surface high frequency eddy current
For the reasons discussed above, I upper deck floor beam upper chords in inspections for cracking of repaired or
Section 41, may not have been inspected in modified floor panel attachment holes in the
certify that the proposed regulation: accordance with AD 2013–22–11,
(1) Is not a ‘‘significant regulatory upper deck floor beam upper chords, in
Amendment 39–17643 (78 FR 66254, accordance with Part 1 or Part 3, as
action’’ under Executive Order 12866, November 5, 2013). We are issuing this AD applicable, of the Accomplishment
(2) Is not a ‘‘significant rule’’ under to detect and correct fatigue cracking in Instructions of Boeing Alert Service Bulletin
the DOT Regulatory Policies and certain upper chords of the upper deck floor 747–53A2688, Revision 2, dated August 21,
Procedures (44 FR 11034, February 26, beam, which could become large and cause
2014. If any crack is found during any
the floor beams to become severed and result
1979), inspection required by this paragraph, before
in rapid decompression or reduced
(3) Will not affect intrastate aviation further flight, repair using a method
controllability of the airplane.
in Alaska, and approved in accordance with the procedures
(f) Compliance specified in paragraph (o) of this AD. Repeat
(4) Will not have a significant
Comply with this AD within the the inspections thereafter at the applicable
economic impact, positive or negative, time specified in table 2 of paragraph 1.E.,
on a substantial number of small entities compliance times specified, unless already
done. ‘‘Compliance,’’ of Boeing Alert Service
under the criteria of the Regulatory Bulletin 747–53A2688, Revision 2, dated
Flexibility Act. (g) Section 41—Repetitive Inspections, and August 21, 2014.
Corrective Actions
List of Subjects in 14 CFR Part 39 (i) Section 44—Repetitive Inspection, and
At the applicable time specified in table 1 Corrective Actions
Air transportation, Aircraft, Aviation of paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 747–53A2688, For airplanes identified in Group 1 in
safety, Incorporation by reference,
Revision 2, dated August 21, 2014, do open Boeing Alert Service Bulletin 747–53A2688,
Safety. Revision 2, dated August 21, 2014: At the
hole or surface high frequency eddy current
The Proposed Amendment inspections for cracking of the floor panel applicable time specified in table 3 of
attachment holes in the upper deck floor paragraph 1.E., ‘‘Compliance,’’ of Boeing
Accordingly, under the authority beam upper chords, in accordance with Part Alert Service Bulletin 747–53A2688,
delegated to me by the Administrator, 1 of the Accomplishment Instructions of Revision 2, dated August 21, 2014, except as
the FAA proposes to amend 14 CFR part Boeing Alert Service Bulletin 747–53A2688, required by paragraph (m)(4) of this AD, do
39 as follows: Revision 2, dated August 21, 2014. If any open hole or surface high frequency eddy
crack is found during any inspection, before current inspections of the floor panel
PART 39—AIRWORTHINESS further flight, repair in accordance with Part attachment holes in the upper deck floor
DIRECTIVES 2 of the Accomplishment Instructions of beam upper chords, in accordance with Part
Boeing Alert Service Bulletin 747–53A2688, 4 of the Accomplishment Instructions of
■ 1. The authority citation for part 39 Revision 2, dated August 21, 2014, or repair Boeing Alert Service Bulletin 747–53A2688,
using a method approved in accordance with Revision 2, dated August 21, 2014. If any
continues to read as follows: crack is found during any inspection
procedures specified in paragraph (o) of this
Authority: 49 U.S.C. 106(g), 40113, 44701. AD. Repeat the inspections thereafter at the required by this paragraph, before further
applicable time specified in table 1 of flight, repair in accordance with Part 5 of the
§ 39.13 [Amended] paragraph 1.E., ‘‘Compliance,’’ of Boeing Accomplishment Instructions of Boeing Alert
mstockstill on DSK4VPTVN1PROD with PROPOSALS
■ 2. The FAA amends § 39.13 by Alert Service Bulletin 747–53A2688, Service Bulletin 747–53A2688, Revision 2,
removing Airworthiness Directive (AD) Revision 2, dated August 21, 2014, until an dated August 21, 2014, except as required by
2013–22–11, Amendment 39–17643 (78 action specified in paragraph (g)(1) or (g)(2) paragraph (m)(2) of this AD. Repeat the
of this AD is done. inspections thereafter at the applicable time
FR 66254, November 5, 2013), and
(1) Doing a repair as a hole modification in specified in table 3 of paragraph 1.E.,
adding the following new AD: accordance with Part 2 of the ‘‘Compliance,’’ of Boeing Alert Service
The Boeing Company: Docket No. FAA– Accomplishment Instructions of Boeing Alert Bulletin 747–53A2688, Revision 2, dated
2015–2464; Directorate Identifier 2014– Service Bulletin 747–53A2688, Revision 2, August 21, 2014, until an action specified in
NM–195–AD. dated August 21, 2014, except as required by paragraph (i)(1) or (i)(2) of this AD is done.
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![Federal Register / Vol. 80, No. 141 / Thursday, July 23, 2015 / Proposed Rules 43651
(1) Doing a repair as a hole modification in required by paragraph (m)(1) of this AD, at (o) Alternative Methods of Compliance
accordance with Part 5 of the all plugged or re-used floor panel attachment (AMOCs)
Accomplishment Instructions of Boeing Alert holes in the affected floor beam upper
(1) The Manager, Seattle Aircraft
Service Bulletin 747–53A2688, Revision 2, chords, do a surface high frequency eddy
dated August 21, 2014, except as required by current inspection of the upper deck floor Certification Office (ACO), FAA, has the
paragraph (m)(2) of this AD, terminates the beam upper chords and detailed inspection authority to approve AMOCs for this AD, if
inspections required by paragraph (i) of this for cracks on the vertical flange, in requested using the procedures found in 14
AD for that modified hole only. accordance with Part 8 of the CFR 39.19. In accordance with 14 CFR 39.19,
(2) Doing a modification in accordance Accomplishment Instructions of Boeing Alert send your request to your principal inspector
with Figure 21 of Boeing Alert Service Service Bulletin 747–53A2688, Revision 2, or local Flight Standards District Office, as
Bulletin 747–53A2688, Revision 2, dated dated August 21, 2014. If any crack is found appropriate. If sending information directly
August 21, 2014, except as required by during any inspection required by this to the manager of the ACO, send it to the
paragraph (m)(2) of this AD, terminates the paragraph, before further flight, repair using attention of the person identified in
inspections required by paragraph (i) of this a method approved in accordance with the
AD for that modified hole only. paragraph (p)(1) of this AD. Information may
procedures specified in paragraph (o) of this
be emailed to: 9-ANM-Seattle-ACO-AMOC-
(j) Section 44—Repetitive Inspection of AD. Repeat the inspections thereafter at the
Requests@faa.gov.
Repaired or Modified Holes, and Corrective applicable time specified in table 6 of
paragraph 1.E., ‘‘Compliance,’’ of Boeing (2) Before using any approved AMOC,
Actions notify your appropriate principal inspector,
Alert Service Bulletin 747–53A2688,
For airplanes identified in Group 1 in Revision 2, dated August 21, 2014. or lacking a principal inspector, the manager
Boeing Alert Service Bulletin 747–53A2688, of the local flight standards district office/
Revision 2, dated August 21, 2014, on which (m) Exceptions to Service Information certificate holding district office.
a repair specified in Part 5 of Boeing Alert Specifications
(3) An AMOC that provides an acceptable
Service Bulletin 747–53A2688 is done or a (1) Where Boeing Alert Service Bulletin
modification specified in Figure 21 of Boeing level of safety may be used for any repair
747–53A2688, Revision 2, dated August 21, required by this AD if it is approved by the
Alert Service Bulletin 747–53A2688 is done: 2014, specifies a compliance time ‘‘after the
At the applicable time specified in table 4 of Boeing Commercial Airplanes Organization
Revision 2 date of this service bulletin,’’ this
paragraph 1.E., ‘‘Compliance,’’ of Boeing Designation Authorization (ODA) that has
AD requires compliance within the specified
Alert Service Bulletin 747–53A2688, compliance time after the effective date of been authorized by the Manager, Seattle
Revision 2, dated August 21, 2014, except as this AD. ACO, to make those findings. For a repair
required by paragraph (m)(3) of this AD, do (2) Where Boeing Alert Service Bulletin method to be approved, the repair must meet
open hole or surface high frequency eddy 747–53A2688, Revision 2, dated August 21, the certification basis of the airplane, and the
current inspections of repaired or modified 2014; specifies to contact Boeing for certain approval must specifically refer to this AD.
floor panel attachment holes in the upper
procedures: Do the specified actions before (4) AMOCs approved for AD 2013–22–11,
deck floor beam upper chords, in accordance
further flight using a method approved in Amendment 39–17643 (78 FR 66254,
with Part 4 or Part 6, as applicable, of the
accordance with the procedures specified in November 5, 2013), are approved as AMOCs
Accomplishment Instructions of Boeing Alert
paragraph (o) of this AD. for the corresponding provisions of
Service Bulletin 747–53A2688, Revision 2,
(3) Where table 2 or table 4 of paragraph paragraphs (g) through (k) of this AD.
dated August 21, 2014. If any crack is found
1.E., ‘‘Compliance,’’ of Boeing Alert Service
during any inspection by this paragraph,
Bulletin 747–53A2688, Revision 2, dated (p) Related Information
before further flight, repair using a method
August 21, 2014, specifies to contact Boeing
approved in accordance with the procedures (1) For more information about this AD,
for inspections and compliance times: Before
specified in paragraph (o) of this AD. Repeat contact Nathan Weigand, Aerospace
the inspections thereafter at the applicable further flight, contact the Manager, FAA,
Seattle Aircraft Certification Office (ACO), for Engineer, Airframe Branch, ANM–120S,
time specified in table 4 of paragraph 1.E., FAA, Seattle Aircraft Certification Office
‘‘Compliance,’’ of Boeing Alert Service inspections and compliance times and
accomplish the inspections at the given (ACO), 1601 Lind Avenue SW., Renton, WA
Bulletin 747–53A2688, Revision 2, dated
times. 98057–3356; phone: 425–917–6428; fax: 425–
August 21, 2014.
(4) Where Boeing Alert Service Bulletin 917–6590; email: Nathan.P.Weigand@
(k) Section 41 and 44—Replacement and 747–53A2688, Revision 1, dated September faa.gov.
Post-Replacement Repetitive Inspections 19, 2012, specifies a compliance time ‘‘after (2) For service information identified in
At the applicable time specified in table 5 the Revision 1 date of this service bulletin,’’ this AD, contact Boeing Commercial
of paragraph 1.E., ‘‘Compliance,’’ of Boeing this AD requires compliance within the Airplanes, Attention: Data & Services
Alert Service Bulletin 747–53A2688, specified compliance time after December 10,
Management, P. O. Box 3707, MC 2H–65,
Revision 2, dated August 21, 2014: Replace 2013 (the effective date of AD 2013–22–11,
Amendment 39–17643 (78 FR 66254, Seattle, WA 98124–2207; phone: 206–544–
all upper deck floor beam upper chords, in 5000, extension 1; fax: 206–766–5680;
accordance with Part 7 of the November 5, 2013)).
Internet https://www.myboeingfleet.com. You
Accomplishment Instructions of Boeing Alert (n) Credit for Previous Actions
Service Bulletin 747–53A2688, Revision 2, may view this referenced service information
dated August 21, 2014. Within 20,000 flight (1) This paragraph restates the at the FAA, Transport Airplane Directorate,
cycles after doing the replacement, do the requirements of paragraph (o) of AD 2013– 1601 Lind Avenue SW., Renton, WA. For
inspections specified in paragraphs (g) and (i) 22–11, Amendment 39–17643 (78 FR 66254, information on the availability of this
of this AD, as applicable. Thereafter, repeat November 5, 2013), with new paragraph (h). material at the FAA, call 425–227–1221.
the inspections required by paragraphs (g) This paragraph provides credit for the actions
and (i) of this AD, as applicable, at the times required by paragraphs (g) and (h) of this AD, Issued in Renton, Washington, on July 15,
specified in paragraphs (g) and (i) of this AD. if those actions were performed before 2015.
December 10, 2013 (the effective date of AD Suzanne Masterson,
(l) Section 41—Repetitive Inspection of 2013–22–11) using Boeing Alert Service
mstockstill on DSK4VPTVN1PROD with PROPOSALS
Plugged or Re-Used Holes, and Corrective Acting Manager, Transport Airplane
Bulletin 747–53A2688, dated August 21,
Actions 2008. Directorate, Aircraft Certification Service.
For airplanes identified in Group 2 in (2) This paragraph provides credit for the [FR Doc. 2015–17932 Filed 7–22–15; 8:45 am]
Boeing Alert Service Bulletin 747–53A2688, actions required by paragraphs (g) through (k) BILLING CODE 4910–13–P
Revision 2, dated August 21, 2014: At the of this AD, if those actions were performed
applicable time specified in table 6 of before the effective date of this AD using
paragraph 1.E., ‘‘Compliance,’’ of Boeing Boeing Alert Service Bulletin 747–53A2688,
Alert Service Bulletin 747–53A2688, Revision 1, dated September 19, 2012, which
Revision 2, dated August 21, 2014, except as is not incorporated by reference in this AD.
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Document Created: 2015-12-15 12:53:42
Document Modified: 2015-12-15 12:53:42
| 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 | Proposed Rules | |
| Action | Notice of proposed rulemaking (NPRM). | |
| Dates | We must receive comments on this proposed AD by September 8, 2015. | |
| Contact | Nathan Weigand, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917- 6428; fax: 425-917-6590; email: [email protected] | |
| FR Citation | 80 FR 43648 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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