Airworthiness Directives; The Boeing Company Airplanes, 56407-56413 [2015-23420]

Download as PDF Federal Register / Vol. 80, No. 181 / Friday, September 18, 2015 / Proposed Rules shock injury to persons contacting the cockpit door. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Door Modification and Installation Within 24 months after the effective date of this AD, modify the cockpit door frame structure and install bonding-leads to the upper cockpit door frame, in accordance with the Accomplishment Instructions of the applicable service information identified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD. (1) Airbus Service Bulletin A330–25–3534, Revision 01, dated October 23, 2014. (2) Airbus Service Bulletin A340–25–4349, Revision 01, dated October 27, 2014. (3) Airbus Service Bulletin A340–25–5212, Revision 01, dated October 27, 2014. tkelley on DSK3SPTVN1PROD with PROPOSALS (h) Cover Plate Modification of the Upper Flight Deck Door Except for airplanes on which Airbus Modification 52869 or Modification 53292 has been embodied in production: Before or concurrently with accomplishing the modification required by paragraph (g) of this AD, modify the upper cockpit door plate cover, in accordance with the Accomplishment Instructions of the applicable service information identified in paragraphs (h)(1), (h)(2), and (h)(3) of this AD. (1) Airbus Service Bulletin A330–25–3534, Revision 01, dated October 23, 2014. (2) Airbus Service Bulletin A340–25–4349, Revision 01, dated October 27, 2014. (3) Airbus Service Bulletin A340–25–5212, Revision 01, dated October 27, 2014. (i) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1138; fax 425–227–1149. Information may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. The AMOC approval letter must specifically reference this AD. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM– 116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency VerDate Sep<11>2014 17:14 Sep 17, 2015 Jkt 235001 (EASA); or Airbus’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. (3) Required for Compliance (RC): If any service information contains procedures or tests that are identified as RC, those procedures and tests must be done to comply with this AD; any procedures or tests that are not identified as RC are recommended. Those procedures and tests that are not identified as RC may be deviated from using accepted methods in accordance with the operator’s maintenance or inspection program without obtaining approval of an AMOC, provided the procedures and tests identified as RC can be done and the airplane can be put back in a serviceable condition. Any substitutions or changes to procedures or tests identified as RC require approval of an AMOC. (j) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2015–0037, dated March 2, 2015, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA– 2015–3631. (2) For service information identified in this AD, contact Airbus SAS, Airworthiness Office—EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email airworthiness.A330–A340@airbus.com; Internet http://www.airbus.com. 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. Issued in Renton, Washington, on September 11, 2015. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–23409 Filed 9–17–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2014–0774; Directorate Identifier 2013–NM–154–AD] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Supplemental notice of proposed rulemaking (SNPRM); reopening of comment period. AGENCY: We are revising an earlier proposed airworthiness directive (AD) that proposed to supersede AD 2006– SUMMARY: PO 00000 Frm 00009 Fmt 4702 Sfmt 4702 56407 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 requires 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. The notice of proposed rulemaking (NPRM) proposed to reduce a compliance time and add certain inspections and applicable repair. 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. This action revises the NPRM by specifying a repetitive inspection interval for a certain NWW area inspection. We are proposing this SNPRM 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. Since these actions impose an additional burden over that proposed in the NPRM, we are reopening the comment period to allow the public the chance to comment on these proposed changes. DATES: We must receive comments on this SNPRM by November 2, 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: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590, 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 E:\FR\FM\18SEP1.SGM 18SEP1 56408 Federal Register / Vol. 80, No. 181 / Friday, September 18, 2015 / Proposed Rules 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 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: 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: Bill.Ashforth@faa.gov. SUPPLEMENTARY INFORMATION: tkelley on DSK3SPTVN1PROD with PROPOSALS 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–2014–0774; Directorate Identifier 2013–NM–154–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 We issued an NPRM 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 applies to all 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 NPRM published in the Federal Register on November 17, 2014 (79 FR 68388). The NPRM was VerDate Sep<11>2014 17:14 Sep 17, 2015 Jkt 235001 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 NPRM proposed to continue to require repetitive inspections for cracking of certain panel webs and stiffeners of the NWW, and corrective actions if necessary. The NPRM also proposed to continue to require replacing certain panels with new panels, which would terminate the repetitive inspections. The NPRM proposed to reduce a compliance time and add certain inspections and applicable repair. Actions Since Previous NPRM (79 FR 68388, November 17, 2014) Was Issued Since we issued the NPRM (79 FR 68388, November 17, 2014), we have determined that it is necessary to revise the NPRM by specifying a certain repetitive inspection interval for Area 2 for airplanes with less than 15,000 total flight cycles. This interval is not clearly indicated in table 1 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Service Bulletin 747–53A2465, Revision 5, dated July 11, 2013, and was not specifically stated in the NPRM. Related Service Information Under 1 CFR Part 51 We reviewed the following Boeing service information. Refer to this service information for information on the procedures and compliance times. • Boeing Service Bulletin 747– 53A2465, Revision 5, dated July 11, 2013, which describes procedures for inspections for cracks of certain top and sidewall panel webs and stiffeners of the NWW; and repairs. • Boeing Service Bulletin 747– 53A2562, Revision 3, dated July 11, 2013. This service bulletin 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 postmodification inspections for cracks in the top and side panel webs and stiffeners; and contacting Boeing for repairs. • Boeing Alert Service Bulletin 747– 53A2808, dated November 30, 2012. This service bulletin describes procedures for replacement of the side and top panel webs, support beams, and stiffeners of the NWW; an inspection for cracks 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 contacting Boeing for repairs. PO 00000 Frm 00010 Fmt 4702 Sfmt 4702 This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section of this AD. Comments We gave the public the opportunity to comment on the NPRM (79 FR 68388, November 17, 2014). The following presents the comments received on the NPRM and the FAA’s response to each comment. Requests To Specify Repetitive Inspection Interval for Area 2 United Airlines (UAL) and United Parcel Service (UPS) requested that we specify the repetitive inspection interval for Area 2 for airplanes with less than 15,000 total flight cycles. The commenters point out that this is not clearly indicated in table 1 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Service Bulletin 747–53A2465, Revision 5, dated July 11, 2013, and was not specifically stated in the NPRM (79 FR 68388, November 17, 2014). The commenters stated that Boeing has issued a service bulletin information notice to inform operators that the repetitive inspection interval for Area 2 should be 1,000 flight cycles. We agree with the commenters’ requests to specify the repeat interval for Area 2. We have revised paragraph (g) of this SNPRM to specify this interval. Request To Specify Repair Procedures UAL asked whether paragraph (h)(3) of the proposed AD (79 FR 68388, November 17, 2014) should be revised to specify repair requirements for each area, instead of contacting the FAA or the Boeing Commercial Airplanes Organization Designation Authorization (ODA) for repair instructions for any cracking or damage found during the inspection specified in paragraph (g) of the proposed AD. UAL explained that Boeing Service Bulletin 747–53A2465, Revision 5, dated July 11, 2013, specifies repairing web cracks in Area 1 or 2 per the ‘‘747 Structural Repair Manuals.’’ We agree to provide clarification. The intent of paragraph (h)(3) of this SNPRM is to make sure that for those conditions for which Boeing Service Bulletin 747– 53A2465, Revision 5, dated July 11, 2013, specifies that the operator is to contact Boeing for repair data, the operator would be required to use a repair method approved by the FAA or Boeing Commercial Airplanes ODA. We have not changed this SNPRM in this regard. E:\FR\FM\18SEP1.SGM 18SEP1 Federal Register / Vol. 80, No. 181 / Friday, September 18, 2015 / Proposed Rules Request To Clarify Certain Compliance Times required. We have not changed this SNPRM regarding this issue. UAL requested clarification of why the footnotes in table 2 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Service Bulletin 747–53A2465, Revision 5, dated July 11, 2013, reverted back to 6,000 flight cycles for Area 3 inspections for cracks of the sidewall panel and top panel stiffeners. UAL also asked why the 6,000-flight-cycle time is just for the first repeat inspection and then Area 3 has to be reinspected every 1,500 flight cycles thereafter. We agree that clarification is necessary. Paragraph (f)(2) of AD 2006– 22–15, Amendment 39–14812 (71 FR 64884, November 6, 2006), specifies the 6,000-flight-cycle and 1,500-flight-cycle inspection times. Boeing Service Bulletin 747–53A2465, Revision 5, dated July 11, 2013, states that inspections and corrective actions defined therein are an alternative method of compliance (AMOC) to the requirements of paragraphs (f), (g), (h), (i), and (j) of AD 2006–22–15. In order to be approved as an AMOC to certain requirements of AD 2006–22–15, Boeing Service Bulletin 747–53A2465, Revision 5, dated July 11, 2013, must state the compliance times required by AD 2006– 22–15 to address the identified unsafe condition. We have not changed this SNPRM in this regard. Request To Clarify Inspection Location Boeing requested that, at the end of paragraph (g)(3) of the proposed AD (79 FR 68388, November 17, 2014), we add ‘‘of the NWW (specified as Area 1 and Area 2 in Boeing Service Bulletin 747– 53A2465, Revision 5, dated July 11, 2013)’’ for the ultrasonic inspection. We agree with the commenter’s request. This revision will make the wording in paragraph (g)(3) of this proposed AD consistent with the wording of each of the areas specified in paragraphs (g)(1) and (g)(2) of this proposed AD. We have revised paragraph (g)(3) of this proposed AD accordingly. tkelley on DSK3SPTVN1PROD with PROPOSALS Request To Revise Certain Headers To Clarify Intent of Requirements Boeing requested that we revise the heading of paragraph (g) of the proposed AD (79 FR 68388, November 17, 2014) to either change ‘‘Repetitive Inspections’’ to ‘‘Initial and Repetitive Inspections’’ or delete ‘‘Repetitive.’’ Boeing stated that paragraph (g) of the proposed AD contains both initial and repetitive inspections. Boeing requested that we delete ‘‘Repetitive’’ from the headings of paragraphs (j) and (m) of the proposed AD (79 FR 68388, November 17, 2014). Boeing stated that paragraphs (j) and (m) of the proposed AD specify not only repetitive inspections, but also the initial post-modification inspections. We agree that clarification is necessary. We do not consider that the term ‘‘repetitive’’ necessarily excludes the initial action. An action cannot be repeated without accomplishment of the initial action. Many existing ADs refer to ‘‘repetitive’’ actions, which we intend as including the initial action. In addition, changing ‘‘Repetitive Inspections’’ to simply ‘‘Inspections’’ could result in the misinterpretation that multiple different inspections are VerDate Sep<11>2014 17:14 Sep 17, 2015 Jkt 235001 Request To Add New AMOC Limitation Boeing requested that we add a new paragraph (p)(6) to the NPRM (79 FR 68388, November 17, 2014), which would state that ‘‘New provisions (inspection threshold and interval) in this AD must be complied with as given in this AD.’’ Boeing stated that this statement will make it clear that prior AMOCs do not exempt the operators from compliance with new requirements added by this new proposed AD. Boeing also stated that the wording of ‘‘corresponding provisions’’ in paragraph (p)(4) of the proposed AD (79 FR 68388, November 17, 2014) might not be precise enough, when ADs get superseded and paragraphs change. Boeing explained that adding this statement will reduce the ambiguity of paragraphs (o) and (p) of the proposed AD. We partially agree with the commenter’s request. We have revised paragraph (p)(4) of this proposed AD to state that AMOC actions approved previously for AD 2006–22–15, Amendment 39–14812 (71 FR 64884, November 6, 2006), 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. We have removed paragraph (p)(5) of this proposed AD as it is no longer necessary. We consider this language to be sufficiently clear. Adding the commenter’s requested language would be redundant to the language specified in revised paragraph (p)(4) of this proposed AD. Requests for Certain Editorial Changes Boeing noted that paragraph (m) of the proposed AD (79 FR 68388, November 17, 2014) incorrectly referred to paragraphs ‘‘(l)(1), (l)(2), and (l)(3).’’ PO 00000 Frm 00011 Fmt 4702 Sfmt 4702 56409 Boeing asked that we change these references to ‘‘(m)(1), (m)(2), and (m)(3).’’ Boeing requested that we correct the AD citation in paragraph (o)(1)(i) of the proposed AD (79 FR 68388, November 17, 2014). Boeing stated that the identified effective date of January 27, 2005, is for AD 2004–25–23, Amendment 39–13911 (69 FR 76839, December 23, 2004); not AD 2005–09– 02, Amendment 39–14070 (70 FR 21141, April 25, 2005; corrected May 25, 2005, 70 FR 29940)); as stated in the NPRM. Boeing requested that we correct the date of Boeing Service Bulletin 747– 53A2465, Revision 4, from February 25, 2004, to February 24, 2005, in paragraph (o)(2) of the proposed AD (79 FR 68388, November 17, 2014). UPS requested that we revise paragraph (p)(1) of the proposed AD (79 FR 68388, November 17, 2014) to correct the paragraph identifier for the contact person, which should be paragraph ‘‘(q)(1).’’ We agree with the requests and have revised this SNPRM accordingly. FAA’s Determination We are proposing this SNPRM because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of this same type design. Certain changes described above expand the scope of the NPRM (79 FR 68388, November 17, 2014). As a result, we have determined that it is necessary to reopen the comment period to provide additional opportunity for the public to comment on this SNPRM. Proposed Requirements of This SNPRM Although this proposed AD does not explicitly restate certain requirements of AD 2006–22–15, Amendment 39–14812 (71 FR 64884, November 6, 2006), this proposed AD would retain all of the requirements of AD 2006–22–15. The requirements specified in paragraphs (f), (g), (h), (i), (j), and (l) of AD 2006–22–15, Amendment 39–14812 (71 FR 64884, November 6, 2006), are referenced in Boeing Service Bulletin 747–53A2465, Revision 5, dated July 11, 2013, which, in turn, is referenced in paragraphs (g) and (h)(3) of this proposed AD. The requirement specified in paragraph (n) of AD 2006–22–15, Amendment 39–14812 (71 FR 64884, November 6, 2006), is referenced in Boeing Service Bulletin 747–53A2562, Revision 3, dated July 11, 2013, which, in turn, is referenced in paragraph (i) of this proposed AD. E:\FR\FM\18SEP1.SGM 18SEP1 56410 Federal Register / Vol. 80, No. 181 / Friday, September 18, 2015 / Proposed Rules For Group 2 airplanes identified in Boeing Service Bulletin 747–53A2562, Revision 1, dated July 28, 2005, and certain airplanes not identified in Boeing Service Bulletin 747–53A2562, Revision 1, dated July 28, 2005, the requirement specified in paragraph (o) of AD 2006–22–15, Amendment 39– 14812 (71 FR 64884, November 6, 2006), to accomplish a repair using a method approved by the FAA is now specified in paragraph (i) of this proposed AD. However, for these airplanes, one method of compliance for accomplishing the replacement is Boeing Service Bulletin 747–53A2562, Revision 3, dated July 11, 2013. Therefore, we have referred to Boeing Service Bulletin 747–53A2562, Revision 3, dated July 11, 2013, in paragraph (i) of this proposed AD. Operators may still request an alternative method of compliance (AMOC) using the procedures provided in paragraph (p) of this AD. For certain other airplanes not identified in Boeing Service Bulletin 747–53A2562, Revision 1, dated July 28, 2005, the requirement specified in paragraph (o) of AD 2006–22–15, Amendment 39–14812 (71 FR 64884, November 6, 2006), to accomplish a repair using a method approved by the FAA is now specified in paragraph (l) of this proposed AD. However, for these airplanes, one method of compliance for accomplishing the replacement is Boeing Alert Service Bulletin 747– 53A2808, dated November 30, 2012. Therefore, we have referred to Boeing Alert Service Bulletin 747–53A2808, dated November 30, 2012, in paragraph (l) of this proposed AD. Operators may still request an AMOC using the procedures provided in paragraph (p) of this AD. This proposed AD would require accomplishing the actions specified in the service information identified previously, except as discussed under ‘‘Differences Between the Proposed AD and the Service Information.’’ Refer to this service information for information on the procedures and compliance times. The phrase ‘‘related investigative actions’’ is used in this proposed AD. ‘‘Related investigative actions’’ are follow-on actions that (1) are related to the primary actions, and (2) further investigate the nature of any condition found. Related investigative actions in an AD could include, for example, inspections. The phrase ‘‘corrective actions’’ is 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. right-hand side panel on an airplane with 11,428 total flight cycles. This difference has been coordinated with The Boeing Company. Boeing Service Bulletin 747– 53A2465, Revision 5, dated July 11, 2013; Boeing Service Bulletin 747 53A2562, Revision 3, dated July 11, 2013; and Boeing Alert Service Bulletin 747–53A2808, dated November 30, 2012; specify 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 ODA whom we have authorized to make those findings. Differences Between the Proposed AD and the Service Information For airplanes with fewer than 15,000 total flight cycles, Boeing Service Bulletin 747–53A2465, Revision 5, dated July 11, 2013, recommends, in part, accomplishing a detailed inspection before the accumulation of 13,000 total flight cycles. However, we have determined that the 13,000-totalflight-cycle compliance time is insufficient to address the identified unsafe condition soon enough to ensure an adequate level of safety for the affected fleet. Instead, we are proposing a compliance time of 10,000 total flight cycles. In developing an appropriate compliance time for this detailed inspection, we considered the degree of urgency associated with the subject unsafe condition, and the fact that we have received a report of a 13-inch crack adjacent to a 2-inch crack in the NWW Explanation of Compliance Time The compliance time for the modification specified in paragraphs (i) and (l) of this proposed AD for addressing widespread fatigue damage (WFD) was established to ensure that discrepant structure is modified before WFD develops in airplanes. Standard inspection techniques cannot be relied on to detect WFD before it becomes a hazard to flight. We will not grant any extensions of the compliance time to complete any AD-mandated service bulletin related to WFD without extensive new data that would substantiate and clearly warrant such an extension. Costs of Compliance We estimate that this proposed AD affects 255 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: ESTIMATED COSTS Labor cost Parts cost Cost per product Cost on U.S. operators Inspections [actions retained from AD 2006– 22–15, Amendment 39–14812 (71 FR 64884, November 6, 2006)]. Modification [actions retained from AD 2006– 22–15, Amendment 39–14812 (71 FR 64884, November 6, 2006)]. Post-modification Inspections [new proposed action]. tkelley on DSK3SPTVN1PROD with PROPOSALS Action 119 work-hours × $85 per hour = $10,115 per inspection cycle. Up to 1,346 work-hours × $85 per hour = $114,410. 119 work-hours × $85 per hour = $10,115 per inspection cycle. $0 ........................ $10,115 per inspection cycle. $2,579,325 per inspection cycle. Up to $144,248 ... Up to $258,658 ........... Up to $65,957,790. $0 ........................ $10,115 per inspection cycle. $2,579,325 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 proposed AD. Authority for This Rulemaking VerDate Sep<11>2014 17:14 Sep 17, 2015 Jkt 235001 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 PO 00000 Frm 00012 Fmt 4702 Sfmt 4702 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, E:\FR\FM\18SEP1.SGM 18SEP1 Federal Register / Vol. 80, No. 181 / Friday, September 18, 2015 / Proposed Rules Part A, Subpart III, Section 44701: ‘‘General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this 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 this 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 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): tkelley on DSK3SPTVN1PROD with PROPOSALS ■ The Boeing Company: Docket No. FAA– 2014–0774; Directorate Identifier 2013– NM–154–AD. (a) Comments Due Date We must receive comments by November 2, 2015. VerDate Sep<11>2014 17:14 Sep 17, 2015 Jkt 235001 (b) Affected ADs This AD replaces AD 2006–22–15, Amendment 39–14812 (71 FR 64884, November 6, 2006). (c) Applicability This AD applies to all Boeing 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 caused by fatigue. 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 PO 00000 Frm 00013 Fmt 4702 Sfmt 4702 56411 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 flights 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 E:\FR\FM\18SEP1.SGM 18SEP1 56412 Federal Register / Vol. 80, No. 181 / Friday, September 18, 2015 / Proposed Rules effective date of AD 2006–22–15, Amendment 39–14812 (71 FR 64884, November 6, 2006). (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. tkelley on DSK3SPTVN1PROD with PROPOSALS (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. VerDate Sep<11>2014 17:14 Sep 17, 2015 Jkt 235001 (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, Amendment 39–14812 (71 FR 64884, November 6, 2006). (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, Amendment 39–14812 (71 FR 64884, November 6, 2006)), 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. PO 00000 Frm 00014 Fmt 4702 Sfmt 4702 (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 Boeing Service Bulletin 747–53A2562, Revision 1, dated July 28, 2005; or Boeing Service Bulletin 747–53A2562, Revision 2, dated May 31, 2007; which are 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: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov. (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 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) AMOC actions approved previously for AD 2006–22–15, Amendment 39–14812 (71 FR 64884, November 6, 2006), 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. (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: Bill.Ashforth@faa.gov. (2) For service information identified in this AD, 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. E:\FR\FM\18SEP1.SGM 18SEP1 Federal Register / Vol. 80, No. 181 / Friday, September 18, 2015 / Proposed Rules Issued in Renton, Washington, on September 1, 2015. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–23420 Filed 9–17–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–3633; Directorate Identifier 2014–NM–097–AD] RIN 2120–AA64 Airworthiness Directives; Fokker Services B.V. Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for all Fokker Services B.V. Model F.27 Mark 200, 300, 400, 500, 600, and 700 airplanes. This proposed AD was prompted by a design review conducted by Fokker Services B.V. that indicated no controlled bonding provisions were present on many critical locations outside the fuel tank or connected to the fuel tank wall. This proposed AD would require installing the additional bonding provisions, and revising the maintenance or inspection program, as applicable, by incorporating fuel airworthiness limitation items and critical design configuration control limitations. We are proposing this AD to prevent an ignition source in the fuel tank vapor space, which could result in a fuel tank explosion and consequent loss of the airplane. DATES: We must receive comments on this proposed AD by November 2, 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: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 tkelley on DSK3SPTVN1PROD with PROPOSALS SUMMARY: VerDate Sep<11>2014 17:14 Sep 17, 2015 Jkt 235001 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact Fokker Services B.V., Technical Services Dept., P.O. Box 1357, 2130 EL Hoofddorp, the Netherlands; telephone +31 (0)88–6280– 350; fax +31 (0)88–6280–111; email technicalservices@fokker.com; Internet http://www.myfokkerfleet.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. 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– 3633; 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 Operations office (telephone 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Tom Rodriguez, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1137; fax 425–227–1149. 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–2015–3633; Directorate Identifier 2014–NM–097–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 based on 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 The European Aviation Safety Agency (EASA), which is the Technical Agent PO 00000 Frm 00015 Fmt 4702 Sfmt 4702 56413 for the Member States of the European Union, has issued EASA Airworthiness Directive 2014–0100, dated April 30, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for all Fokker Services B.V. Model F.27 Mark 200, 300, 400, 500, 600, and 700 airplanes. The MCAI states: Prompted by an accident * * *, the FAA published Special Federal Aviation Regulation (SFAR) 88 [(66 FR 23086, May 7, 2001)], and the Joint Aviation Authorities (JAA) published Interim Policy INT/POL/25/ 12. The review conducted by Fokker Services on the Fokker 27 design in response to these regulations revealed that no controlled bonding provisions are present on a number of critical locations outside the fuel tanks. This condition, if not corrected, could create an ignition source in the fuel tank vapour space, possibly resulting in a fuel tank explosion and consequent loss of the aeroplane. To address this potential unsafe condition, Fokker Services developed a set of bonding modifications, introduced with [a service bulletin] * * *, that do[es] not require opening of the fuel tank access panels. More information on this subject can be found in Fokker Services All Operators Message AOF27.043#03. For the reasons described above, this [EASA] AD requires installation of additional bonding provisions that do not require opening of the fuel tank access panels. Required actions also include revising the maintenance or inspection program, as applicable, by incorporating fuel airworthiness limitation items and critical design configuration control limitations. You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2015– 3633. The FAA has examined the underlying safety issues involved in fuel tank explosions on several large transport airplanes, including the adequacy of existing regulations, the service history of airplanes subject to those regulations, and existing maintenance practices for fuel tank systems. As a result of those findings, we issued a regulation titled ‘‘Transport Airplane Fuel Tank System Design Review, Flammability Reduction and Maintenance and Inspection Requirements’’ (66 FR 23086, May 7, 2001). In addition to new airworthiness standards for transport airplanes and new maintenance requirements, this rule included Special Federal Aviation Regulation No. 88 (‘‘SFAR 88,’’ Amendment 21–78, and subsequent Amendments 21–82 and 21–83). Among other actions, SFAR 88 (66 FR 23086, May 7, 2001) requires certain E:\FR\FM\18SEP1.SGM 18SEP1

Agencies

[Federal Register Volume 80, Number 181 (Friday, September 18, 2015)]
[Proposed Rules]
[Pages 56407-56413]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-23420]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0774; Directorate Identifier 2013-NM-154-AD]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Supplemental notice of proposed rulemaking (SNPRM); reopening 
of comment period.

-----------------------------------------------------------------------

SUMMARY: We are revising an earlier proposed airworthiness directive 
(AD) that proposed to supersede 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 requires 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. The notice of 
proposed rulemaking (NPRM) proposed to reduce a compliance time and add 
certain inspections and applicable repair. 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. This action 
revises the NPRM by specifying a repetitive inspection interval for a 
certain NWW area inspection. We are proposing this SNPRM 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. Since these actions impose an additional 
burden over that proposed in the NPRM, we are reopening the comment 
period to allow the public the chance to comment on these proposed 
changes.

DATES: We must receive comments on this SNPRM by November 2, 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: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590, 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

[[Page 56408]]

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 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: 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: Bill.Ashforth@faa.gov.

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-2014-0774; 
Directorate Identifier 2013-NM-154-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

    We issued an NPRM 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 
applies to all 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 NPRM published in the Federal Register on 
November 17, 2014 (79 FR 68388). 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 NPRM proposed 
to continue to require repetitive inspections for cracking of certain 
panel webs and stiffeners of the NWW, and corrective actions if 
necessary. The NPRM also proposed to continue to require replacing 
certain panels with new panels, which would terminate the repetitive 
inspections. The NPRM proposed to reduce a compliance time and add 
certain inspections and applicable repair.

Actions Since Previous NPRM (79 FR 68388, November 17, 2014) Was Issued

    Since we issued the NPRM (79 FR 68388, November 17, 2014), we have 
determined that it is necessary to revise the NPRM by specifying a 
certain repetitive inspection interval for Area 2 for airplanes with 
less than 15,000 total flight cycles. This interval is not clearly 
indicated in table 1 of paragraph 1.E., ``Compliance,'' of Boeing 
Service Bulletin 747-53A2465, Revision 5, dated July 11, 2013, and was 
not specifically stated in the NPRM.

Related Service Information Under 1 CFR Part 51

    We reviewed the following Boeing service information. Refer to this 
service information for information on the procedures and compliance 
times.
     Boeing Service Bulletin 747-53A2465, Revision 5, dated 
July 11, 2013, which describes procedures for inspections for cracks of 
certain top and sidewall panel webs and stiffeners of the NWW; and 
repairs.
     Boeing Service Bulletin 747-53A2562, Revision 3, dated 
July 11, 2013. This service bulletin 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 contacting Boeing for repairs.
     Boeing Alert Service Bulletin 747-53A2808, dated November 
30, 2012. This service bulletin describes procedures for replacement of 
the side and top panel webs, support beams, and stiffeners of the NWW; 
an inspection for cracks 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 contacting Boeing for 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 of this 
AD.

Comments

    We gave the public the opportunity to comment on the NPRM (79 FR 
68388, November 17, 2014). The following presents the comments received 
on the NPRM and the FAA's response to each comment.

Requests To Specify Repetitive Inspection Interval for Area 2

    United Airlines (UAL) and United Parcel Service (UPS) requested 
that we specify the repetitive inspection interval for Area 2 for 
airplanes with less than 15,000 total flight cycles. The commenters 
point out that this is not clearly indicated in table 1 of paragraph 
1.E., ``Compliance,'' of Boeing Service Bulletin 747-53A2465, Revision 
5, dated July 11, 2013, and was not specifically stated in the NPRM (79 
FR 68388, November 17, 2014). The commenters stated that Boeing has 
issued a service bulletin information notice to inform operators that 
the repetitive inspection interval for Area 2 should be 1,000 flight 
cycles.
    We agree with the commenters' requests to specify the repeat 
interval for Area 2. We have revised paragraph (g) of this SNPRM to 
specify this interval.

Request To Specify Repair Procedures

    UAL asked whether paragraph (h)(3) of the proposed AD (79 FR 68388, 
November 17, 2014) should be revised to specify repair requirements for 
each area, instead of contacting the FAA or the Boeing Commercial 
Airplanes Organization Designation Authorization (ODA) for repair 
instructions for any cracking or damage found during the inspection 
specified in paragraph (g) of the proposed AD. UAL explained that 
Boeing Service Bulletin 747-53A2465, Revision 5, dated July 11, 2013, 
specifies repairing web cracks in Area 1 or 2 per the ``747 Structural 
Repair Manuals.''
    We agree to provide clarification. The intent of paragraph (h)(3) 
of this SNPRM is to make sure that for those conditions for which 
Boeing Service Bulletin 747-53A2465, Revision 5, dated July 11, 2013, 
specifies that the operator is to contact Boeing for repair data, the 
operator would be required to use a repair method approved by the FAA 
or Boeing Commercial Airplanes ODA. We have not changed this SNPRM in 
this regard.

[[Page 56409]]

Request To Clarify Certain Compliance Times

    UAL requested clarification of why the footnotes in table 2 of 
paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin 747-53A2465, 
Revision 5, dated July 11, 2013, reverted back to 6,000 flight cycles 
for Area 3 inspections for cracks of the sidewall panel and top panel 
stiffeners. UAL also asked why the 6,000-flight-cycle time is just for 
the first repeat inspection and then Area 3 has to be reinspected every 
1,500 flight cycles thereafter.
    We agree that clarification is necessary. Paragraph (f)(2) of AD 
2006-22-15, Amendment 39-14812 (71 FR 64884, November 6, 2006), 
specifies the 6,000-flight-cycle and 1,500-flight-cycle inspection 
times. Boeing Service Bulletin 747-53A2465, Revision 5, dated July 11, 
2013, states that inspections and corrective actions defined therein 
are an alternative method of compliance (AMOC) to the requirements of 
paragraphs (f), (g), (h), (i), and (j) of AD 2006-22-15. In order to be 
approved as an AMOC to certain requirements of AD 2006-22-15, Boeing 
Service Bulletin 747-53A2465, Revision 5, dated July 11, 2013, must 
state the compliance times required by AD 2006-22-15 to address the 
identified unsafe condition. We have not changed this SNPRM in this 
regard.

Request To Revise Certain Headers To Clarify Intent of Requirements

    Boeing requested that we revise the heading of paragraph (g) of the 
proposed AD (79 FR 68388, November 17, 2014) to either change 
``Repetitive Inspections'' to ``Initial and Repetitive Inspections'' or 
delete ``Repetitive.'' Boeing stated that paragraph (g) of the proposed 
AD contains both initial and repetitive inspections.
    Boeing requested that we delete ``Repetitive'' from the headings of 
paragraphs (j) and (m) of the proposed AD (79 FR 68388, November 17, 
2014). Boeing stated that paragraphs (j) and (m) of the proposed AD 
specify not only repetitive inspections, but also the initial post-
modification inspections.
    We agree that clarification is necessary. We do not consider that 
the term ``repetitive'' necessarily excludes the initial action. An 
action cannot be repeated without accomplishment of the initial action. 
Many existing ADs refer to ``repetitive'' actions, which we intend as 
including the initial action. In addition, changing ``Repetitive 
Inspections'' to simply ``Inspections'' could result in the 
misinterpretation that multiple different inspections are required. We 
have not changed this SNPRM regarding this issue.

Request To Clarify Inspection Location

    Boeing requested that, at the end of paragraph (g)(3) of the 
proposed AD (79 FR 68388, November 17, 2014), we add ``of the NWW 
(specified as Area 1 and Area 2 in Boeing Service Bulletin 747-53A2465, 
Revision 5, dated July 11, 2013)'' for the ultrasonic inspection.
    We agree with the commenter's request. This revision will make the 
wording in paragraph (g)(3) of this proposed AD consistent with the 
wording of each of the areas specified in paragraphs (g)(1) and (g)(2) 
of this proposed AD. We have revised paragraph (g)(3) of this proposed 
AD accordingly.

Request To Add New AMOC Limitation

    Boeing requested that we add a new paragraph (p)(6) to the NPRM (79 
FR 68388, November 17, 2014), which would state that ``New provisions 
(inspection threshold and interval) in this AD must be complied with as 
given in this AD.'' Boeing stated that this statement will make it 
clear that prior AMOCs do not exempt the operators from compliance with 
new requirements added by this new proposed AD. Boeing also stated that 
the wording of ``corresponding provisions'' in paragraph (p)(4) of the 
proposed AD (79 FR 68388, November 17, 2014) might not be precise 
enough, when ADs get superseded and paragraphs change. Boeing explained 
that adding this statement will reduce the ambiguity of paragraphs (o) 
and (p) of the proposed AD.
    We partially agree with the commenter's request. We have revised 
paragraph (p)(4) of this proposed AD to state that AMOC actions 
approved previously for AD 2006-22-15, Amendment 39-14812 (71 FR 64884, 
November 6, 2006), 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. We have removed paragraph (p)(5) of this 
proposed AD as it is no longer necessary. We consider this language to 
be sufficiently clear. Adding the commenter's requested language would 
be redundant to the language specified in revised paragraph (p)(4) of 
this proposed AD.

Requests for Certain Editorial Changes

    Boeing noted that paragraph (m) of the proposed AD (79 FR 68388, 
November 17, 2014) incorrectly referred to paragraphs ``(l)(1), (l)(2), 
and (l)(3).'' Boeing asked that we change these references to ``(m)(1), 
(m)(2), and (m)(3).''
    Boeing requested that we correct the AD citation in paragraph 
(o)(1)(i) of the proposed AD (79 FR 68388, November 17, 2014). Boeing 
stated that the identified effective date of January 27, 2005, is for 
AD 2004-25-23, Amendment 39-13911 (69 FR 76839, December 23, 2004); not 
AD 2005-09-02, Amendment 39-14070 (70 FR 21141, April 25, 2005; 
corrected May 25, 2005, 70 FR 29940)); as stated in the NPRM.
    Boeing requested that we correct the date of Boeing Service 
Bulletin 747-53A2465, Revision 4, from February 25, 2004, to February 
24, 2005, in paragraph (o)(2) of the proposed AD (79 FR 68388, November 
17, 2014).
    UPS requested that we revise paragraph (p)(1) of the proposed AD 
(79 FR 68388, November 17, 2014) to correct the paragraph identifier 
for the contact person, which should be paragraph ``(q)(1).''
    We agree with the requests and have revised this SNPRM accordingly.

FAA's Determination

    We are proposing this SNPRM because we evaluated all the relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of this same type design. 
Certain changes described above expand the scope of the NPRM (79 FR 
68388, November 17, 2014). As a result, we have determined that it is 
necessary to reopen the comment period to provide additional 
opportunity for the public to comment on this SNPRM.

Proposed Requirements of This SNPRM

    Although this proposed AD does not explicitly restate certain 
requirements of AD 2006-22-15, Amendment 39-14812 (71 FR 64884, 
November 6, 2006), this proposed AD would retain all of the 
requirements of AD 2006-22-15.
    The requirements specified in paragraphs (f), (g), (h), (i), (j), 
and (l) of AD 2006-22-15, Amendment 39-14812 (71 FR 64884, November 6, 
2006), are referenced in Boeing Service Bulletin 747-53A2465, Revision 
5, dated July 11, 2013, which, in turn, is referenced in paragraphs (g) 
and (h)(3) of this proposed AD.
    The requirement specified in paragraph (n) of AD 2006-22-15, 
Amendment 39-14812 (71 FR 64884, November 6, 2006), is referenced in 
Boeing Service Bulletin 747-53A2562, Revision 3, dated July 11, 2013, 
which, in turn, is referenced in paragraph (i) of this proposed AD.

[[Page 56410]]

    For Group 2 airplanes identified in Boeing Service Bulletin 747-
53A2562, Revision 1, dated July 28, 2005, and certain airplanes not 
identified in Boeing Service Bulletin 747-53A2562, Revision 1, dated 
July 28, 2005, the requirement specified in paragraph (o) of AD 2006-
22-15, Amendment 39-14812 (71 FR 64884, November 6, 2006), to 
accomplish a repair using a method approved by the FAA is now specified 
in paragraph (i) of this proposed AD. However, for these airplanes, one 
method of compliance for accomplishing the replacement is Boeing 
Service Bulletin 747-53A2562, Revision 3, dated July 11, 2013. 
Therefore, we have referred to Boeing Service Bulletin 747-53A2562, 
Revision 3, dated July 11, 2013, in paragraph (i) of this proposed AD. 
Operators may still request an alternative method of compliance (AMOC) 
using the procedures provided in paragraph (p) of this AD.
    For certain other airplanes not identified in Boeing Service 
Bulletin 747-53A2562, Revision 1, dated July 28, 2005, the requirement 
specified in paragraph (o) of AD 2006-22-15, Amendment 39-14812 (71 FR 
64884, November 6, 2006), to accomplish a repair using a method 
approved by the FAA is now specified in paragraph (l) of this proposed 
AD. However, for these airplanes, one method of compliance for 
accomplishing the replacement is Boeing Alert Service Bulletin 747-
53A2808, dated November 30, 2012. Therefore, we have referred to Boeing 
Alert Service Bulletin 747-53A2808, dated November 30, 2012, in 
paragraph (l) of this proposed AD. Operators may still request an AMOC 
using the procedures provided in paragraph (p) of this AD.
    This proposed AD would require accomplishing the actions specified 
in the service information identified previously, except as discussed 
under ``Differences Between the Proposed AD and the Service 
Information.'' Refer to this service information for information on the 
procedures and compliance times.
    The phrase ``related investigative actions'' is used in this 
proposed AD. ``Related investigative actions'' are follow-on actions 
that (1) are related to the primary actions, and (2) further 
investigate the nature of any condition found. Related investigative 
actions in an AD could include, for example, inspections.
    The phrase ``corrective actions'' is 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 the Proposed AD and the Service Information

    For airplanes with fewer than 15,000 total flight cycles, Boeing 
Service Bulletin 747-53A2465, Revision 5, dated July 11, 2013, 
recommends, in part, accomplishing a detailed inspection before the 
accumulation of 13,000 total flight cycles. However, we have determined 
that the 13,000-total-flight-cycle compliance time is insufficient to 
address the identified unsafe condition soon enough to ensure an 
adequate level of safety for the affected fleet. Instead, we are 
proposing a compliance time of 10,000 total flight cycles. In 
developing an appropriate compliance time for this detailed inspection, 
we considered the degree of urgency associated with the subject unsafe 
condition, and the fact that we have received a report of a 13-inch 
crack adjacent to a 2-inch crack in the NWW right-hand side panel on an 
airplane with 11,428 total flight cycles. This difference has been 
coordinated with The Boeing Company.
    Boeing Service Bulletin 747-53A2465, Revision 5, dated July 11, 
2013; Boeing Service Bulletin 747 53A2562, Revision 3, dated July 11, 
2013; and Boeing Alert Service Bulletin 747-53A2808, dated November 30, 
2012; specify 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 ODA whom we have authorized to make those findings.

Explanation of Compliance Time

    The compliance time for the modification specified in paragraphs 
(i) and (l) of this proposed AD for addressing widespread fatigue 
damage (WFD) was established to ensure that discrepant structure is 
modified before WFD develops in airplanes. Standard inspection 
techniques cannot be relied on to detect WFD before it becomes a hazard 
to flight. We will not grant any extensions of the compliance time to 
complete any AD-mandated service bulletin related to WFD without 
extensive new data that would substantiate and clearly warrant such an 
extension.

Costs of Compliance

    We estimate that this proposed AD affects 255 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
----------------------------------------------------------------------------------------------------------------
Inspections [actions retained   119 work-hours x   $0......................  $10,115 per        $2,579,325 per
 from AD 2006-22-15, Amendment   $85 per hour =                               inspection cycle.  inspection
 39-14812 (71 FR 64884,          $10,115 per                                                     cycle.
 November 6, 2006)].             inspection cycle.
Modification [actions retained  Up to 1,346 work-  Up to $144,248..........  Up to $258,658...  Up to
 from AD 2006-22-15, Amendment   hours x $85 per                                                 $65,957,790.
 39-14812 (71 FR 64884,          hour = $114,410.
 November 6, 2006)].
Post-modification Inspections   119 work-hours x   $0......................  $10,115 per        $2,579,325 per
 [new proposed action].          $85 per hour =                               inspection cycle.  inspection
                                 $10,115 per                                                     cycle.
                                 inspection cycle.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions 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 56411]]

Part A, Subpart III, Section 44701: ``General requirements.'' Under 
that section, Congress charges the FAA with promoting safe flight of 
civil aircraft in air commerce by prescribing regulations for 
practices, methods, and procedures the Administrator finds necessary 
for safety in air commerce. This regulation is within the scope of that 
authority because it addresses an unsafe condition that is likely to 
exist or develop on products identified in this rulemaking action.

Regulatory Findings

    We determined that this 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 this 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 adding the following new airworthiness 
directive (AD):

The Boeing Company: Docket No. FAA-2014-0774; Directorate Identifier 
2013-NM-154-AD.

(a) Comments Due Date

    We must receive comments by November 2, 2015.

(b) Affected ADs

    This AD replaces AD 2006-22-15, Amendment 39-14812 (71 FR 64884, 
November 6, 2006).

(c) Applicability

    This AD applies to all Boeing 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 caused 
by fatigue. 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 
flights 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

[[Page 56412]]

effective date of AD 2006-22-15, Amendment 39-14812 (71 FR 64884, 
November 6, 2006).

(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, Amendment 39-14812 (71 FR 64884, November 6, 2006).
    (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, Amendment 39-14812 (71 FR 64884, November 6, 2006)), 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 Boeing Service Bulletin 
747-53A2562, Revision 1, dated July 28, 2005; or Boeing Service 
Bulletin 747-53A2562, Revision 2, dated May 31, 2007; which are 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: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
    (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 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) AMOC actions approved previously for AD 2006-22-15, 
Amendment 39-14812 (71 FR 64884, November 6, 2006), 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.

(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: Bill.Ashforth@faa.gov.
    (2) For service information identified in this AD, 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.


[[Page 56413]]


    Issued in Renton, Washington, on September 1, 2015.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-23420 Filed 9-17-15; 8:45 am]
BILLING CODE 4910-13-P