80 FR 56407 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 80, Issue 181 (September 18, 2015)
Federal Aviation Administration
Federal Register Volume 80, Issue 181 (September 18, 2015)
| Page Range | 56407-56413 | |
| FR Document | 2015-23420 |
[Federal Register Volume 80, Number 181 (Friday, September 18, 2015)] [Proposed Rules] [Pages 56407-56413] From the Federal Register Online [www.thefederalregister.org] [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
![Federal Register / Vol. 80, No. 181 / Friday, September 18, 2015 / Proposed Rules 56407
shock injury to persons contacting the (EASA); or Airbus’s EASA Design 22–15 for all The Boeing Company
cockpit door. Organization Approval (DOA). If approved by Model 747–100, 747–100B, 747–100B
the DOA, the approval must include the SUD, 747–200B, 747–200C, 747–200F,
(f) Compliance DOA-authorized signature.
Comply with this AD within the 747–300, 747–400, 747–400D, 747–
(3) Required for Compliance (RC): If any
compliance times specified, unless already service information contains procedures or 400F, 747SR, and 747SP series
done. tests that are identified as RC, those airplanes. AD 2006–22–15 requires
procedures and tests must be done to comply repetitive inspections for cracking of
(g) Door Modification and Installation
with this AD; any procedures or tests that are certain panel webs and stiffeners of the
Within 24 months after the effective date not identified as RC are recommended. Those nose wheel well (NWW), and corrective
of this AD, modify the cockpit door frame procedures and tests that are not identified actions if necessary; and replacement of
structure and install bonding-leads to the as RC may be deviated from using accepted
upper cockpit door frame, in accordance with certain panels with new panels, which
methods in accordance with the operator’s terminates the repetitive inspections.
the Accomplishment Instructions of the maintenance or inspection program without
applicable service information identified in The notice of proposed rulemaking
obtaining approval of an AMOC, provided
paragraphs (g)(1), (g)(2), and (g)(3) of this AD. the procedures and tests identified as RC can (NPRM) proposed to reduce a
(1) Airbus Service Bulletin A330–25–3534, be done and the airplane can be put back in compliance time and add certain
Revision 01, dated October 23, 2014. (2) a serviceable condition. Any substitutions or inspections and applicable repair. The
Airbus Service Bulletin A340–25–4349, changes to procedures or tests identified as NPRM was prompted by reports of
Revision 01, dated October 27, 2014. (3) RC require approval of an AMOC. fatigue cracking in the panel webs and
Airbus Service Bulletin A340–25–5212,
Revision 01, dated October 27, 2014. (j) Related Information stiffeners of the NWW found prior to the
inspection threshold of AD 2006–22–15.
(h) Cover Plate Modification of the Upper (1) Refer to Mandatory Continuing
This action revises the NPRM by
Flight Deck Door Airworthiness Information (MCAI) EASA
Airworthiness Directive 2015–0037, dated specifying a repetitive inspection
Except for airplanes on which Airbus March 2, 2015, for related information. This interval for a certain NWW area
Modification 52869 or Modification 53292 inspection. We are proposing this
MCAI may be found in the AD docket on the
has been embodied in production: Before or SNPRM to prevent fatigue cracking of
Internet at http://www.regulations.gov by
concurrently with accomplishing the
modification required by paragraph (g) of this
searching for and locating Docket No. FAA– the NWW side and top panels, which
2015–3631. could result in a NWW depressurization
AD, modify the upper cockpit door plate
(2) For service information identified in event severe enough to reduce the
cover, in accordance with the
this AD, contact Airbus SAS, Airworthiness structural integrity of the fuselage. Since
Accomplishment Instructions of the
Office—EAL, 1 Rond Point Maurice Bellonte,
applicable service information identified in these actions impose an additional
31707 Blagnac Cedex, France; telephone +33
paragraphs (h)(1), (h)(2), and (h)(3) of this burden over that proposed in the NPRM,
5 61 93 36 96; fax +33 5 61 93 45 80; email
AD. we are reopening the comment period to
(1) Airbus Service Bulletin A330–25–3534, airworthiness.A330–A340@airbus.com;
Internet http://www.airbus.com. You may allow the public the chance to comment
Revision 01, dated October 23, 2014. (2)
view this service information at the FAA, on these proposed changes.
Airbus Service Bulletin A340–25–4349,
Revision 01, dated October 27, 2014. (3) Transport Airplane Directorate, 1601 Lind DATES: We must receive comments on
Airbus Service Bulletin A340–25–5212, Avenue SW., Renton, WA. For information this SNPRM by November 2, 2015.
Revision 01, dated October 27, 2014. on the availability of this material at the
FAA, call 425–227–1221. ADDRESSES: You may send comments,
(i) Other FAA AD Provisions using the procedures found in 14 CFR
Issued in Renton, Washington, on 11.43 and 11.45, by any of the following
The following provisions also apply to this September 11, 2015.
AD: methods:
Michael Kaszycki, • Federal eRulemaking Portal: Go to
(1) Alternative Methods of Compliance
(AMOCs): The Manager International Branch, Acting Manager, Transport Airplane http://www.regulations.gov. Follow the
ANM–116, Transport Airplane Directorate, Directorate, Aircraft Certification Service. instructions for submitting comments.
FAA, has the authority to approve AMOCs [FR Doc. 2015–23409 Filed 9–17–15; 8:45 am] • Fax: 202–493–2251.
for this AD, if requested using the procedures BILLING CODE 4910–13–P • Mail: U.S. Department of
found in 14 CFR 39.19. In accordance with Transportation, Docket Operations, M–
14 CFR 39.19, send your request to your
30, West Building Ground Floor, Room
principal inspector or local Flight Standards DEPARTMENT OF TRANSPORTATION
District Office, as appropriate. If sending W12–140, 1200 New Jersey Avenue SE.,
information directly to the International Washington, DC 20590.
Federal Aviation Administration • Hand Delivery: U.S. Department of
Branch, send it to ATTN: Vladimir Ulyanov,
Aerospace Engineer, International Branch, Transportation, Docket Operations, M–
ANM–116, Transport Airplane Directorate, 14 CFR Part 39 30, West Building Ground Floor, Room
FAA, 1601 Lind Avenue SW., Renton, WA [Docket No. FAA–2014–0774; Directorate W12–140, 1200 New Jersey Avenue SE.,
98057–3356; telephone 425–227–1138; fax Identifier 2013–NM–154–AD] Washington, DC 20590, between 9 a.m.
425–227–1149. Information may be emailed
and 5 p.m., Monday through Friday,
to: 9-ANM-116-AMOC-REQUESTS@faa.gov. RIN 2120–AA64
Before using any approved AMOC, notify except Federal holidays.
your appropriate principal inspector, or For service information identified in
Airworthiness Directives; The Boeing
lacking a principal inspector, the manager of this proposed AD, contact Boeing
Company Airplanes
the local flight standards district office/ Commercial Airplanes, Attention: Data
certificate holding district office. The AMOC AGENCY: Federal Aviation & Services Management, P. O. Box 3707,
approval letter must specifically reference
tkelley on DSK3SPTVN1PROD with PROPOSALS
Administration (FAA), DOT. MC 2H–65, Seattle, WA 98124–2207;
this AD. telephone 206–544–5000, extension 1;
(2) Contacting the Manufacturer: For any ACTION: Supplemental notice of
proposed rulemaking (SNPRM); fax 206–766–5680; Internet https://
requirement in this AD to obtain corrective
actions from a manufacturer, the action must reopening of comment period. www.myboeingfleet.com. You may view
be accomplished using a method approved this referenced service information at
by the Manager, International Branch, ANM– SUMMARY: We are revising an earlier the FAA, Transport Airplane
116, Transport Airplane Directorate, FAA; or proposed airworthiness directive (AD) Directorate, 1601 Lind Avenue SW.,
the European Aviation Safety Agency that proposed to supersede AD 2006– Renton, WA. For information on the
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![56410 Federal Register / Vol. 80, No. 181 / Friday, September 18, 2015 / Proposed Rules
For Group 2 airplanes identified in This proposed AD would require right-hand side panel on an airplane
Boeing Service Bulletin 747–53A2562, accomplishing the actions specified in with 11,428 total flight cycles. This
Revision 1, dated July 28, 2005, and the service information identified difference has been coordinated with
certain airplanes not identified in previously, except as discussed under The Boeing Company.
Boeing Service Bulletin 747–53A2562, ‘‘Differences Between the Proposed AD Boeing Service Bulletin 747–
Revision 1, dated July 28, 2005, the and the Service Information.’’ Refer to 53A2465, Revision 5, dated July 11,
requirement specified in paragraph (o) this service information for information 2013; Boeing Service Bulletin 747
of AD 2006–22–15, Amendment 39– on the procedures and compliance 53A2562, Revision 3, dated July 11,
14812 (71 FR 64884, November 6, 2006), times. 2013; and Boeing Alert Service Bulletin
to accomplish a repair using a method The phrase ‘‘related investigative 747–53A2808, dated November 30,
approved by the FAA is now specified actions’’ is used in this proposed AD. 2012; specify to contact the
in paragraph (i) of this proposed AD. ‘‘Related investigative actions’’ are manufacturer for instructions on how to
follow-on actions that (1) are related to repair certain conditions, but this
However, for these airplanes, one
the primary actions, and (2) further proposed AD would require repairing
method of compliance for
investigate the nature of any condition those conditions in one of the following
accomplishing the replacement is
found. Related investigative actions in ways:
Boeing Service Bulletin 747–53A2562, an AD could include, for example,
Revision 3, dated July 11, 2013. • In accordance with a method that
inspections. we approve; or
Therefore, we have referred to Boeing The phrase ‘‘corrective actions’’ is
Service Bulletin 747–53A2562, Revision • Using data that meet the
used in this proposed AD. ‘‘Corrective
3, dated July 11, 2013, in paragraph (i) actions’’ are actions that correct or certification basis of the airplane, and
of this proposed AD. Operators may still address any condition found. Corrective that have been approved by the Boeing
request an alternative method of actions in an AD could include, for Commercial Airplanes ODA whom we
compliance (AMOC) using the example, repairs. have authorized to make those findings.
procedures provided in paragraph (p) of Explanation of Compliance Time
this AD. Differences Between the Proposed AD
and the Service Information The compliance time for the
For certain other airplanes not modification specified in paragraphs (i)
identified in Boeing Service Bulletin For airplanes with fewer than 15,000
total flight cycles, Boeing Service and (l) of this proposed AD for
747–53A2562, Revision 1, dated July 28, addressing widespread fatigue damage
Bulletin 747–53A2465, Revision 5,
2005, the requirement specified in (WFD) was established to ensure that
dated July 11, 2013, recommends, in
paragraph (o) of AD 2006–22–15, discrepant structure is modified before
part, accomplishing a detailed
Amendment 39–14812 (71 FR 64884, inspection before the accumulation of WFD develops in airplanes. Standard
November 6, 2006), to accomplish a 13,000 total flight cycles. However, we inspection techniques cannot be relied
repair using a method approved by the have determined that the 13,000-total- on to detect WFD before it becomes a
FAA is now specified in paragraph (l) of flight-cycle compliance time is hazard to flight. We will not grant any
this proposed AD. However, for these insufficient to address the identified extensions of the compliance time to
airplanes, one method of compliance for unsafe condition soon enough to ensure complete any AD-mandated service
accomplishing the replacement is an adequate level of safety for the bulletin related to WFD without
Boeing Alert Service Bulletin 747– affected fleet. Instead, we are proposing extensive new data that would
53A2808, dated November 30, 2012. a compliance time of 10,000 total flight substantiate and clearly warrant such an
Therefore, we have referred to Boeing cycles. In developing an appropriate extension.
Alert Service Bulletin 747–53A2808, compliance time for this detailed Costs of Compliance
dated November 30, 2012, in paragraph inspection, we considered the degree of
(l) of this proposed AD. Operators may urgency associated with the subject We estimate that this proposed AD
still request an AMOC using the unsafe condition, and the fact that we affects 255 airplanes of U.S. registry.
procedures provided in paragraph (p) of have received a report of a 13-inch crack We estimate the following costs to
this AD. adjacent to a 2-inch crack in the NWW comply with this proposed AD:
ESTIMATED COSTS
Action Labor cost Parts cost Cost per product Cost on U.S. operators
Inspections [actions retained from AD 2006– 119 work-hours × $85 $0 ........................ $10,115 per inspection $2,579,325 per inspec-
22–15, Amendment 39–14812 (71 FR per hour = $10,115 cycle. tion cycle.
64884, November 6, 2006)]. per inspection cycle.
Modification [actions retained from AD 2006– Up to 1,346 work-hours Up to $144,248 ... Up to $258,658 ........... Up to $65,957,790.
22–15, Amendment 39–14812 (71 FR × $85 per hour =
64884, November 6, 2006)]. $114,410.
Post-modification Inspections [new proposed 119 work-hours × $85 $0 ........................ $10,115 per inspection $2,579,325 per inspec-
action]. per hour = $10,115 cycle. tion cycle.
per inspection cycle.
tkelley on DSK3SPTVN1PROD with PROPOSALS
We have received no definitive data Authority for This Rulemaking the FAA Administrator. ‘‘Subtitle VII:
that would enable us to provide cost Aviation Programs’’ describes in more
estimates for the on-condition actions Title 49 of the United States Code detail the scope of the Agency’s
specified in this proposed AD. specifies the FAA’s authority to issue authority.
rules on aviation safety. Subtitle I, We are issuing this rulemaking under
section 106, describes the authority of the authority described in Subtitle VII,
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![Federal Register / Vol. 80, No. 181 / Friday, September 18, 2015 / Proposed Rules 56411
Part A, Subpart III, Section 44701: (b) Affected ADs for cracks of the sidewall panel and top panel
‘‘General requirements.’’ Under that This AD replaces AD 2006–22–15, stiffeners of the NWW (specified as Area 3 in
section, Congress charges the FAA with Amendment 39–14812 (71 FR 64884, Boeing Service Bulletin 747–53A2465,
promoting safe flight of civil aircraft in November 6, 2006). Revision 5, dated July 11, 2013).
(3) Do an external detailed and ultrasonic
air commerce by prescribing regulations (c) Applicability testing (UT) inspection for cracks of the top
for practices, methods, and procedures and sidewall panel webs of the NWW
This AD applies to all Boeing Model 747–
the Administrator finds necessary for 100, 747–100B, 747–100B SUD, 747–200B, (specified as Area 1 and Area 2 in Boeing
safety in air commerce. This regulation 747–200C, 747–200F, 747–300, 747–400, Service Bulletin 747 -53A2465, Revision 5,
is within the scope of that authority 747–400D, 747–400F, 747SR, and 747SP dated July 11, 2013).
because it addresses an unsafe condition series airplanes, certificated in any category. (h) Exceptions to Boeing Service Bulletin
that is likely to exist or develop on 747–53A2465, Revision 5, dated July 11,
(d) Subject
products identified in this rulemaking 2013
action. Air Transport Association (ATA) of
America Code 53, Fuselage. (1) Table 1 in paragraph 1.E.,
Regulatory Findings ‘‘Compliance,’’ of Boeing Service Bulletin
(e) Unsafe Condition 747–53A2465, Revision 5, dated July 11,
We determined that this proposed AD This AD was prompted by multiple reports 2013, applies to airplanes with less than
would not have federalism implications of cracking in the nose wheel well (NWW) 15,000 total flight cycles ‘‘as of the Revision
under Executive Order 13132. This top panel and side panel webs and stiffeners 5 date of this service bulletin.’’ For this AD,
proposed AD would not have a caused by fatigue. We are issuing this AD to however, table 1 applies to airplanes with the
substantial direct effect on the States, on prevent fatigue cracking of the NWW side specified total flight cycles as of the effective
the relationship between the national and top panels, which could result in a date of this AD.
Government and the States, or on the NWW depressurization event severe enough (2) Table 1 in paragraph 1.E.,
to reduce the structural integrity of the ‘‘Compliance,’’ of Boeing Service Bulletin
distribution of power and
fuselage. 747–53A2465, Revision 5, dated July 11,
responsibilities among the various 2013, specifies a compliance time of ‘‘13,000
levels of government. (f) Compliance total flight-cycles,’’ or ‘‘within 1,000 flights
For the reasons discussed above, I Comply with this AD within the cycles after the Revision 5 date of this service
certify this proposed regulation: compliance times specified, unless already bulletin,’’ whichever occurs later. This AD
(1) Is not a ‘‘significant regulatory done. requires compliance before the accumulation
action’’ under Executive Order 12866, of 10,000 total flight cycles or within 1,000
(2) Is not a ‘‘significant rule’’ under (g) Repetitive Inspections and Corrective
flight cycles after the effective date of this
Actions With New Compliance Times
the DOT Regulatory Policies and AD, whichever occurs later.
Procedures (44 FR 11034, February 26, Except as specified in paragraphs (h)(1) (3) If any cracking or damage is found
1979), and (h)(2) of this AD, at the applicable time during any inspection required by paragraph
(3) Will not affect intrastate aviation specified in paragraph 1.E., ‘‘Compliance,’’ of (g) of this AD, and Boeing Service Bulletin
Boeing Service Bulletin 747–53A2465, 747–53A2465, Revision 5, dated July 11,
in Alaska, and Revision 5, dated July 11, 2013: Do the 2013, specifies to contact Boeing for
(4) Will not have a significant actions specified in paragraphs (g)(1), (g)(2), appropriate action: Before further flight,
economic impact, positive or negative, and (g)(3) of this AD, and do all applicable repair the cracking or damage using a method
on a substantial number of small entities related investigative and corrective actions; approved in accordance with the procedures
under the criteria of the Regulatory in accordance with the Accomplishment specified in paragraph (p) of this AD.
Flexibility Act. Instructions of Boeing Service Bulletin 747–
53A2465, Revision 5, dated July 11, 2013, (i) NWW Modification
List of Subjects in 14 CFR Part 39 except as specified in paragraph (h)(3) of this For airplanes identified in Boeing Service
Air transportation, Aircraft, Aviation AD. Do all applicable related investigative Bulletin 747–53A2562, Revision 3, dated July
safety, Incorporation by reference, and corrective actions before further flight. 11, 2013: At the applicable time specified in
Safety. Repeat the inspections specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing
paragraphs (g)(1), (g)(2), and (g)(3) of this AD Service Bulletin 747–53A2562, Revision 3,
The Proposed Amendment thereafter at the applicable intervals specified dated July 11, 2013, replace the left-side,
in paragraph 1.E., ‘‘Compliance,’’ of Boeing right-side, and top panels of the NWW, as
Accordingly, under the authority Service Bulletin 747–53A2465, Revision 5, applicable, with new panels, in accordance
delegated to me by the Administrator, dated July 11, 2013. The repetitive interval with the Accomplishment Instructions of
the FAA proposes to amend 14 CFR part for the inspection of Area 2 specified in table Boeing Service Bulletin 747–53A2562,
39 as follows: 1 in paragraph 1.E., ‘‘Compliance,’’ of Boeing Revision 3, dated July 11, 2013. As of the
Service Bulletin 747–53A2465, Revision 5, effective date of this AD, concurrently with
PART 39—AIRWORTHINESS dated July 11, 2013, is 1,000 flight cycles. In doing the replacement specified in Boeing
DIRECTIVES table 2 and table 3 in paragraph 1.E., Service Bulletin 747–53A2562, Revision 3,
‘‘Compliance,’’ of Boeing Service Bulletin dated July 11, 2013, do a detailed inspection
■ 1. The authority citation for part 39 747–53A2465, Revision 5, dated July 11, for any cracks or damage (including, but not
continues to read as follows: 2013, the date ‘‘January 27, 2005’’ is the limited to, dents and corrosion) in all
Authority: 49 U.S.C. 106(g), 40113, 44701. effective date of AD 2004–25–23, attaching structural elements that are
Amendment 39–13911 (69 FR 76839, common to the removed top panel and side
§ 39.13 [Amended] December 23, 2004); and the date ‘‘May 10, panels, as applicable, and do all applicable
■ 2. The FAA amends § 39.13 by adding 2005’’ is the effective date of AD 2005–09– corrective actions, in accordance with the
02, Amendment 39–14070 (70 FR 21141, Accomplishment Instructions of Boeing
the following new airworthiness April 25, 2005; corrected May 25, 2005 (70 Service Bulletin 747–53A2562, Revision 3,
tkelley on DSK3SPTVN1PROD with PROPOSALS
directive (AD): FR 29940)). dated July 11, 2013. If any crack or damage
The Boeing Company: Docket No. FAA– (1) Do an external detailed inspection for is found, before further flight, repair the
2014–0774; Directorate Identifier 2013– cracks of the top and sidewall panel webs of cracking or damage using a method approved
NM–154–AD. the NWW (specified as Area 1 and Area 2 in in accordance with the procedures specified
Boeing Service Bulletin 747–53A2465, in paragraph (p) of this AD. In paragraph 1.E.,
(a) Comments Due Date Revision 5, dated July 11, 2013). ‘‘Compliance,’’ of Boeing Service Bulletin
We must receive comments by November (2) Do internal detailed and surface high 747–53A2562, Revision 3, dated July 11,
2, 2015. frequency eddy current (HFEC) inspections 2013, the date ‘‘December 11, 2006,’’ is the
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![Federal Register / Vol. 80, No. 181 / Friday, September 18, 2015 / Proposed Rules 56413
Issued in Renton, Washington, on p.m., Monday through Friday, except for the Member States of the European
September 1, 2015. Federal holidays. Union, has issued EASA Airworthiness
Michael Kaszycki, For service information identified in Directive 2014–0100, dated April 30,
Acting Manager, Transport Airplane this proposed AD, contact Fokker 2014 (referred to after this as the
Directorate, Aircraft Certification Service. Services B.V., Technical Services Dept., Mandatory Continuing Airworthiness
[FR Doc. 2015–23420 Filed 9–17–15; 8:45 am] P.O. Box 1357, 2130 EL Hoofddorp, the Information, or ‘‘the MCAI’’), to correct
BILLING CODE 4910–13–P Netherlands; telephone +31 (0)88–6280– an unsafe condition for all Fokker
350; fax +31 (0)88–6280–111; email Services B.V. Model F.27 Mark 200, 300,
technicalservices@fokker.com; Internet 400, 500, 600, and 700 airplanes. The
DEPARTMENT OF TRANSPORTATION http://www.myfokkerfleet.com. You may MCAI states:
view this referenced service information
Prompted by an accident * * *, the FAA
Federal Aviation Administration at the FAA, Transport Airplane published Special Federal Aviation
Directorate, 1601 Lind Avenue SW., Regulation (SFAR) 88 [(66 FR 23086, May 7,
14 CFR Part 39 Renton, WA. For information on the 2001)], and the Joint Aviation Authorities
[Docket No. FAA–2015–3633; Directorate availability of this material at the FAA, (JAA) published Interim Policy INT/POL/25/
Identifier 2014–NM–097–AD] call 425–227–1221. 12.
The review conducted by Fokker Services
RIN 2120–AA64 Examining the AD Docket on the Fokker 27 design in response to these
You may examine the AD docket on regulations revealed that no controlled
Airworthiness Directives; Fokker the Internet at http:// bonding provisions are present on a number
Services B.V. Airplanes of critical locations outside the fuel tanks.
www.regulations.gov by searching for This condition, if not corrected, could
AGENCY: Federal Aviation and locating Docket No. FAA–2015– create an ignition source in the fuel tank
Administration (FAA), DOT. 3633; or in person at the Docket vapour space, possibly resulting in a fuel
Management Facility between 9 a.m. tank explosion and consequent loss of the
ACTION: Notice of proposed rulemaking
and 5 p.m., Monday through Friday, aeroplane.
(NPRM). except Federal holidays. The AD docket To address this potential unsafe condition,
contains this proposed AD, the Fokker Services developed a set of bonding
SUMMARY: We propose to adopt a new modifications, introduced with [a service
airworthiness directive (AD) for all regulatory evaluation, any comments
bulletin] * * *, that do[es] not require
Fokker Services B.V. Model F.27 Mark received, and other information. The opening of the fuel tank access panels.
200, 300, 400, 500, 600, and 700 street address for the Docket Operations More information on this subject can be
airplanes. This proposed AD was office (telephone 800–647–5527) is in found in Fokker Services All Operators
prompted by a design review conducted the ADDRESSES section. Comments will Message AOF27.043#03.
by Fokker Services B.V. that indicated be available in the AD docket shortly For the reasons described above, this
after receipt. [EASA] AD requires installation of additional
no controlled bonding provisions were bonding provisions that do not require
present on many critical locations FOR FURTHER INFORMATION CONTACT: Tom
opening of the fuel tank access panels.
outside the fuel tank or connected to the Rodriguez, Aerospace Engineer,
fuel tank wall. This proposed AD would International Branch, ANM–116, Required actions also include revising
require installing the additional bonding Transport Airplane Directorate, FAA, the maintenance or inspection program,
provisions, and revising the 1601 Lind Avenue SW., Renton, WA as applicable, by incorporating fuel
maintenance or inspection program, as 98057–3356; telephone 425–227–1137; airworthiness limitation items and
applicable, by incorporating fuel fax 425–227–1149. critical design configuration control
airworthiness limitation items and SUPPLEMENTARY INFORMATION: limitations. You may examine the MCAI
critical design configuration control in the AD docket on the Internet at
Comments Invited http://www.regulations.gov by searching
limitations. We are proposing this AD to
prevent an ignition source in the fuel We invite you to send any written for and locating Docket No. FAA–2015–
tank vapor space, which could result in relevant data, views, or arguments about 3633.
this proposed AD. Send your comments The FAA has examined the
a fuel tank explosion and consequent
to an address listed under the underlying safety issues involved in fuel
loss of the airplane.
ADDRESSES section. Include ‘‘Docket No. tank explosions on several large
DATES: We must receive comments on transport airplanes, including the
FAA–2015–3633; Directorate Identifier
this proposed AD by November 2, 2015. adequacy of existing regulations, the
2014–NM–097–AD’’ at the beginning of
ADDRESSES: You may send comments, your comments. We specifically invite service history of airplanes subject to
using the procedures found in 14 CFR comments on the overall regulatory, those regulations, and existing
11.43 and 11.45, by any of the following economic, environmental, and energy maintenance practices for fuel tank
methods: aspects of this proposed AD. We will systems. As a result of those findings,
• Federal eRulemaking Portal: Go to consider all comments received by the we issued a regulation titled ‘‘Transport
http://www.regulations.gov. Follow the closing date and may amend this Airplane Fuel Tank System Design
instructions for submitting comments. proposed AD based on those comments. Review, Flammability Reduction and
• Fax: 202–493–2251. We will post all comments we Maintenance and Inspection
• Mail: U.S. Department of receive, without change, to http:// Requirements’’ (66 FR 23086, May 7,
Transportation, Docket Operations, M– www.regulations.gov, including any 2001). In addition to new airworthiness
tkelley on DSK3SPTVN1PROD with PROPOSALS
30, West Building Ground Floor, Room personal information you provide. We standards for transport airplanes and
W12–140, 1200 New Jersey Avenue SE., will also post a report summarizing each new maintenance requirements, this
Washington, DC 20590. substantive verbal contact we receive rule included Special Federal Aviation
• Hand Delivery: U.S. Department of about this proposed AD. Regulation No. 88 (‘‘SFAR 88,’’
Transportation, Docket Operations, M– Amendment 21–78, and subsequent
30, West Building Ground Floor, Room Discussion Amendments 21–82 and 21–83).
W12–140, 1200 New Jersey Avenue SE., The European Aviation Safety Agency Among other actions, SFAR 88 (66 FR
Washington, DC, between 9 a.m. and 5 (EASA), which is the Technical Agent 23086, May 7, 2001) requires certain
VerDate Sep<11>2014 17:14 Sep 17, 2015 Jkt 235001 PO 00000 Frm 00015 Fmt 4702 Sfmt 4702 E:\FR\FM\18SEP1.SGM 18SEP1](https://thefederalregister.org/doc/80_FR_56588/page/7.svg)
Document Created: 2015-12-15 09:27:49
Document Modified: 2015-12-15 09:27:49
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Proposed Rules | |
| Action | Supplemental notice of proposed rulemaking (SNPRM); reopening of comment period. | |
| Dates | We must receive comments on this SNPRM by November 2, 2015. | |
| Contact | Bill Ashforth, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917- 6432; fax: 425-917-6590; email: [email protected] | |
| FR Citation | 80 FR 56407 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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