Airworthiness Directives; The Boeing Company Airplanes, 77379-77384 [2014-30132]

Download as PDF Federal Register / Vol. 79, No. 247 / Wednesday, December 24, 2014 / Rules and Regulations Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2013–0366; Directorate Identifier 2011–NM–024–AD; Amendment 39–18038; AD 2014–24–05] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 747–100, 747–100B, 747–100B SUD, 747–200B, 747–200C, 747–300, 747–400, 747– 400D, and 747SR series airplanes. This AD was prompted by a report of a cracked reveal made from a casting found within a group of airplanes that should have machined reveals made only from 6061 aluminum. This AD requires an inspection to determine the material of the number 3 main entry door (MED) corner reveal, repetitive inspections of certain reveals for cracking, and corrective action if necessary. This AD also requires repetitive inspections for cracking of 6061 machined aluminum one-piece corner reveals, and replacement with 6061 machined aluminum two-piece corner reveals if necessary, which terminates certain repetitive inspections. We are issuing this AD to detect and correct fatigue cracking of the lower forward corner reveal of the number 3 MEDs, which could lead to the door escape slide departing the airplane when the door is opened and the slide is deployed, and consequent injuries to passengers and crew using the door escape slide during an emergency evacuation. DATES: This AD is effective January 28, 2015. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of January 28, 2015. ADDRESSES: For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; 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 mstockstill on DSK4VPTVN1PROD with RULES VerDate Sep<11>2014 16:05 Dec 23, 2014 Jkt 235001 availability of this material at the FAA, call 425–227–1221. crew using the door escape slide during an emergency evacuation. Examining the AD Docket DEPARTMENT OF TRANSPORTATION SUMMARY: 77379 Related AD AD 2008–18–07, Amendment 39– 15664 (73 FR 56960, October 1, 2008), requires, for The Boeing Company Model 747–100, 747–100B, 747–100B SUD, 747–200B, 747–200C, 747–300, 747–400, 747–400D, and 747SR series airplanes, an inspection to determine the material of a number 3 MED corner reveal, repetitive inspections of certain reveals for cracking, a detailed inspection of certain reveals for a sharp edge and cracking, and corrective action if necessary. AD 2008–18–07 allows reveal replacement as an option to certain inspections. AD 2008–18–07 was prompted by reports of cracking and/or a sharp edge in the lower forward corner reveal of the number 3 MEDs. AD 2008– 18–07 refers to Boeing Special Attention Service Bulletin 747–53–2460, Revision 1, dated February 13, 2007, as the appropriate source of service information for the required actions specified in that AD. You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2013– 0366; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (phone: 800–647–5527) is Docket Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. 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. FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2008–18–07, Amendment 39–15664 (73 FR 56960, October 1, 2008). AD 2008–18–07 applies to certain The Boeing Company Model 747–100, 747–100B, 747–100B SUD, 747–200B, 747–200C, 747–300, 747–400, 747–400D, and 747SR series airplanes. The NPRM published in the Federal Register on May 8, 2013 (78 FR 26720). The NPRM was prompted by a report of a cracked reveal made from a casting found within a group of airplanes that should have machined reveals made only from 6061 aluminum. The NPRM proposed to retain all the requirements of AD 2008–18–07. The NPRM also proposed to add, for certain airplanes, an inspection to determine the material of the number 3 MED corner reveal, repetitive inspections for cracking of 6061 machined aluminum one-piece corner reveals, and replacement with 6061 machined aluminum two-piece corner reveals if necessary, which terminates certain repetitive inspections. We are issuing this AD to detect and correct fatigue cracking of the lower forward corner reveal of the number 3 MEDs, which could lead to the door escape slide departing the airplane when the door is opened and the slide is deployed, and consequent injuries to passengers and PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 Explanation of Difference in Requirements Between the NPRM (78 FR 26720, May 8, 2013) and This Final Rule In the NPRM (78 FR 26720, May 8, 2013), the FAA proposed to supersede AD 2008–18–07, Amendment 39–15664 (73 FR 56960, October 1, 2008), to reflect the changes in airplane groups specified in revised service information, Boeing Special Attention Service Bulletin 747–53–2460, Revision 2, dated December 22, 2010. However, based on the comments received on the NPRM, it became evident that it was difficult to follow the numerous changes between Boeing Special Attention Service Bulletin 747–53–2460, Revision 1, dated February 13, 2007, and Boeing Special Attention Service Bulletin 747–53– 2460, Revision 2, dated December 22, 2010, as well as in following the corresponding actions specified in the NPRM. There are only two significant changes in Boeing Special Attention Service Bulletin 747–53–2460, Revision 2, dated December 22, 2010: (1) Airplanes having line numbers 1038 through 1270 were moved from Group 2 to Group 4; and (2) for Group 4 airplanes, there are additional actions. Therefore, for clarity, we have determined that a less burdensome approach is to revise this final rule to include only the new actions for Group 4 airplanes. Instead of superseding AD 2008–18–07, Amendment 39–15664 (73 FR 56960, October 1, 2008), this final rule is a stand-alone AD, applicable E:\FR\FM\24DER1.SGM 24DER1 77380 Federal Register / Vol. 79, No. 247 / Wednesday, December 24, 2014 / Rules and Regulations only to Group 4 airplanes as identified in Boeing Special Attention Service Bulletin 747–53–2460, Revision 2, dated December 22, 2010, except for those airplanes that have been converted to an all-cargo configuration. Airplanes identified in the applicability of AD 2008–18–07 are still required to continue to comply with the requirements of that AD. Since this AD does not supersede AD 2008–18–07, Amendment 39–15664 (73 FR 56960, October 1, 2008), paragraphs (g) through (m), (p), (q), and (v) of the NPRM (78 FR 26720, May 8, 2013) are not included in this AD. Also, the corresponding paragraph identifiers have been redesignated in this final rule, as listed in the following table: REDESIGNATED PARAGRAPH IDENTIFIERS Requirement in the proposed AD (78 FR 26720, May 8, 2013) paragraph paragraph paragraph paragraph paragraph paragraph paragraph (t) (s) (r) (u) (n) (o) (w) Corresponding requirement in this AD paragraph paragraph paragraph paragraph paragraph paragraph paragraph (g). (h). (i). (j). (k). (l). (n). mstockstill on DSK4VPTVN1PROD with RULES We have also revised paragraphs (n) and (o) of the proposed AD (78 FR 26720, May 8, 2013) (redesignated as paragraphs (k) and (l) of this AD) that referred to ‘‘AD 2008–18–07.’’ In paragraphs (k) and (l) of this AD, we have referred to the current service information, Boeing Special Attention Service Bulletin 747–53–2460, Revision 2, dated December 22, 2010, instead of AD 2008–18–07, Amendment 39–15664 (73 FR 56960, October 1, 2008), for the locations where cast 356 aluminum reveals and machined 6061 aluminum reveals may not be installed. Paragraphs (k) and (l) of this AD state that the parts installation prohibition ends the parts installation prohibitions specified in paragraphs (n) and (o) of AD 2008–18– 07, Amendment 39–15664 (73 FR 56960, October 1, 2008). Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM (78 FR 26720, May 8, 2013) and the FAA’s response to each comment. Request To Clarify the Cause of the Unsafe Condition Boeing asked that we clarify the cause of the unsafe condition identified in paragraph (e) of the proposed AD (78 FR VerDate Sep<11>2014 16:05 Dec 23, 2014 Jkt 235001 26720, May 8, 2013). Boeing stated that the report that prompted the proposed supersedure of AD 2008–18–07, Amendment 39–15664 (73 FR 56960, October 1, 2008), involved a cracked casting on an airplane that should have machined reveals made from only 6061 aluminum. We agree that the unsafe condition should be clarified for the reason provided. We have changed the wording for the unsafe condition identified in the SUMMARY section and in paragraph (e) of this final rule to specify that ‘‘This new AD was prompted by a report of a cracked reveal made from a casting found within a group of airplanes that should have machined reveals made only from 6061 aluminum.’’ We have also clarified the Discussion section of this final rule to specify that the NPRM (78 FR 26720, May 8, 2013) was prompted by that report. Request To Revise Wording in the NPRM (78 FR 26720, May 8, 2013) Boeing requested numerous changes related to the wording in paragraphs (g), (h), (j), (u) and (v) of the NPRM (78 FR 26720, May 8, 2013). We acknowledge the commenter’s concerns for clarity. However, as stated previously, this AD does not supersede AD 2008–18–07, Amendment 39–15664 (73 FR 56960, October 1, 2008). The changes requested by the commenter referred to the ‘‘retained’’ paragraphs of AD 2008–18–07, which are not restated in this AD; therefore, no action is necessary in this regard. Request To Revise Service Information Delta Airlines (Delta) requested that Boeing Special Attention Service Bulletin 747–53–2460, Revision 2, dated December 22, 2010, be revised prior to the issuance of this final rule. Delta stated that paragraphs (r) and (s) of the proposed AD (78 FR 26720, May 8, 2013) (redesignated as paragraphs (i) and (h) of this AD) are clear and understandable; however, when Delta reviewed the required actions in Table 1 of Boeing Special Attention Service Bulletin 747–53–2460, Revision 2, dated December 22, 2010, Delta was not able to clearly determine which conditions were linked with which actions. Delta stated that Boeing also agrees that the compliance tables of Boeing Special Attention Service Bulletin 747–53– 2460, Revision 2, dated December 22, 2010, should be clarified for operators’ use. We disagree with delaying this AD to wait for revised service information in light of the urgency of the identified unsafe condition. As Delta stated, the tables contained in Boeing Special PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 Attention Service Bulletin 747–53– 2460, Revision 2, dated December 22, 2010, are complicated and could be misinterpreted; however, we have addressed this concern by specifying the requirements and clarifying the appropriate actions in paragraphs (h) and (i) of this AD. When the service information is revised, we might consider approving it as an alternative method of compliance (AMOC) for these actions. We have not changed this final rule in this regard. Request To Address an Error in Service Information Delta stated that, in the last row under the ‘‘Action’’ column of Table 8 of paragraph 1.E., Compliance, of Boeing Special Attention Service Bulletin 747– 53–2460, Revision 2, dated December 22, 2010, there is a reference to ‘‘Table 9,’’ which does not exist. Delta stated that the correct paragraph reference is ‘‘Paragraph 3.B., Part 2,’’ as confirmed in Delta’s correspondence with Boeing. Delta requested that Boeing Special Attention Service Bulletin 747–53– 2460, Revision 2, dated December 22, 2010, be revised prior to the issuance of this final rule, or that we address this error in this final rule, or, at a minimum, address this error in a global AMOC. We partially agree. We disagree to wait for revised service information in light of the urgency of the identified unsafe condition. However, we agree that the reference to Table 9 in paragraph 1.E., Compliance, of Boeing Special Attention Service Bulletin 747– 53–2460, Revision 2, dated December 22, 2010, is incorrect. To address this error, we have added a new paragraph (m) in this AD to state that, where the Accomplishment Instructions of Boeing Special Attention Service Bulletin 747– 53–2460, Revision 2, dated December 22, 2010, specify a post-repair detailed inspection in accordance with Table 9, this AD requires a detailed inspection in accordance with paragraph 3.B., Part 2, of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 747–53–2460, Revision 2, dated December 22, 2010. When revised service information becomes available, we might consider approving it as an AMOC for the actions required by this AD. Request To Revise the Proposed AD To Include an Inspection for a Sharp Edge for Group 4 Airplanes Boeing asked that we revise paragraph (r)(2) of the proposed AD (78 FR 26720, May 8, 2013) (redesignated as paragraph (i)(2) of this AD) to include an inspection for a potential sharp edge E:\FR\FM\24DER1.SGM 24DER1 Federal Register / Vol. 79, No. 247 / Wednesday, December 24, 2014 / Rules and Regulations common to the reveal. Boeing stated that this inspection might be the first inspection performed and, therefore, it is possible that a sharp edge could be found on a machined reveal. We do not agree to revise the wording of paragraph (i)(2) of this AD (designated as paragraph (r)(2) of the proposed AD (78 FR 26720, May 8, 2013)). Paragraph (i)(2) of this AD requires, for previously inspected Group 4 airplanes, a material-type inspection to determine if the corner reveal is a casting, and, if a casting is found, continued inspections or replacement of the reveal with a two-piece machined reveal. Castings do not have sharp edges. Group 4 airplanes that were not previously inspected or changed, that have corner reveals found not to be castings, require inspections for a sharp edge in paragraph (g)(2) of this AD. We have not changed this final rule in this regard. mstockstill on DSK4VPTVN1PROD with RULES Request for Alternative Corrective Action for Group 4 Airplanes Boeing asked that we revise paragraph (t)(1) of the proposed AD (78 FR 26720, May 8, 2013) (redesignated as paragraph (g)(1) of this AD) to allow a weld repair for a cracked reveal made from a casting on Group 4 airplanes. Boeing stated that this would allow operators to repair the casting if they cannot obtain a machined reveal. We agree that paragraph (g)(1) of this AD should allow a weld repair as an alternative corrective action since this was a permitted action for Group 2 airplanes in AD 2008–18–07, Amendment 39–15664 (73 FR 56960, October 1, 2008). This alternative corrective action for Group 4 airplanes was contained in Boeing Special Attention Service Bulletin 747–53– 2460, Revision 2, dated December 22, 2010, but was inadvertently omitted in the proposed AD (78 FR 26720, May 8, 2013). Paragraph (t) of the NPRM is redesignated as paragraph (g) in this AD and we have revised paragraph (g)(1) by adding new paragraphs (g)(1)(i) and (g)(1)(ii) in order to allow a weld repair as an option to replacing the reveal if any cracking is found. In paragraph (g)(1)(ii) of this AD we specify repairing in accordance with Part 4 of Boeing Special Attention Service Bulletin 747– 53–2460, Revision 2, dated December 22, 2010. The inspection for cracking specified in paragraph (g)(1) of this AD VerDate Sep<11>2014 16:05 Dec 23, 2014 Jkt 235001 is to be repeated thereafter at intervals not to exceed 3,000 flight cycles until a new two-piece reveal is installed in accordance with the requirements of paragraph (g)(1)(i) of this AD. Request To Reference Service Bulletin Information Notices or Revise Service Bulletin Delta requested that Boeing Service Bulletin Information Notice 747–53– 2460 IN 03, dated March 24, 2011, be referenced as an approved deviation from Boeing Special Attention Service Bulletin 747–53–2460, Revision 2, dated December 22, 2010. Alternatively, Boeing requested that we delay the issuance of this final rule until Boeing revises Boeing Special Attention Service Bulletin 747–53–2460, Revision 2, dated December 22, 2010, to incorporate the changes outlined in that information notice. We partially agree. We agree that Boeing Service Bulletin Information Notice 747–53–2460 IN 03, dated March 24, 2011, contains acceptable information for the inspection and modification mandated in this AD. However, we disagree with delaying issuance of this final rule until revised service information becomes available. We have determined that to delay this final rule would be inappropriate, because the inspections of the number 3 MED reveals and corrective actions are needed to reduce the risk of the identified unsafe condition addressed in this AD. The information that Boeing Service Bulletin Information Notice 747–53–2460 IN 03, dated March 24, 2011, clarifies is for reference only and is not required to address the identified unsafe condition. When revised service information becomes available, we might consider approving it as an AMOC for the actions required by this AD. We have made no change to this AD in this regard. Explanation of Additional Changes Made to This Final Rule We redesignated paragraphs (r) and (r)(2) of the NPRM (78 FR 26720, May 8, 2013) as paragraphs (i) and (i)(2) of this final rule and removed the phrase ‘‘Boeing Special Attention Service Bulletin 747–53–2460, Revision 2, dated December 22, 2010,’’ from the initial compliance times listed in those paragraphs. In the proposed AD, we stated that the compliance times could be calculated from the most recent work PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 77381 performed in accordance with Boeing Special Attention Service Bulletin 747– 53–2460, Revision 1, dated February 13, 2007; or Revision 2, dated December 22, 2010; but this would introduce an error in paragraph (i) of this AD since it would require operators to complete the inspections required by Boeing Special Attention Service Bulletin 747–53– 2460, Revision 2, dated December 22, 2010, for a second time, if the reference to Boeing Special Attention Service Bulletin 747–53–2460, Revision 2, dated December 22, 2010, remained. Paragraph (i)(1) of this final rule specifies inspections for cracking of any corner reveal found to be a one-piece or two-piece casting. Boeing Special Attention Service Bulletin 747–53– 2460, Revision 2, dated December 22, 2010, provides inspection procedures for one-piece corner reveals, but not for the two-piece corner reveals. Because the inspection procedures for the twopiece corner reveals were not included in the service information, operators would have been unable to comply with the proposed requirement to inspect a two-piece corner reveal, and in this case would have been required to obtain approval of an alternative method of compliance for this inspection. We have therefore revised paragraph (i)(1) of this AD to provide the appropriate procedures for both scenarios. Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this AD with the changes described previously and minor editorial changes. We have determined that these minor changes: • Are consistent with the intent that was proposed in the NPRM (78 FR 26720, May 8, 2013) for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM (78 FR 26720, May 8, 2013). We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. Costs of Compliance We estimate that this AD affects 166 airplanes of U.S. registry. We estimate the following costs to comply with this AD: E:\FR\FM\24DER1.SGM 24DER1 77382 Federal Register / Vol. 79, No. 247 / Wednesday, December 24, 2014 / Rules and Regulations ESTIMATED COSTS Action Material type inspection and inspection for cracks. Labor cost Parts cost Cost per product 14 work-hours × $85 per hour = $1,190 per inspection cycle. $0 $1,190 per inspection cycle ... We estimate the following costs to do any necessary on-condition actions that would be required based on the results of the inspections. We have no way of Cost on U.S. operators $197,540 per inspection cycle. determining the number of aircraft that might need these actions: ON-CONDITION COSTS Action Labor cost Parts cost Corner reveal removal and replacement 17 work-hours × $85 per hour = $1,445 per inspection cycle. $9,525 mstockstill on DSK4VPTVN1PROD with RULES Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. Subtitle VII: Aviation Programs, describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701: ‘‘General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings This AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Is not a ‘‘significant rule’’ under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation in Alaska, and (4) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. VerDate Sep<11>2014 16:05 Dec 23, 2014 Jkt 235001 List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 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): ■ 2014–24–05 The Boeing Company: Amendment 39–18038; Docket No. FAA–2013–0366; Directorate Identifier 2011–NM–024–AD. (a) Effective Date This AD is effective January 28, 2015. (b) Affected ADs Certain requirements of this AD terminate certain requirements of AD 2008–18–07, Amendment 39–15664 (73 FR 56960, October 1, 2008). (c) Applicability This AD applies to The Boeing Company Model 747–100, 747–100B, 747–100B SUD, 747–200B, 747–200C, 747–300, 747–400, 747–400D, and 747SR series airplanes, certificated in any category, identified as Group 4 airplanes in Boeing Special Attention Service Bulletin 747–53–2460, Revision 2, dated December 22, 2010, except airplanes that have been converted to an allcargo configuration. Also, the requirements of this AD are applicable when a converted airplane operating in an all-cargo configuration is converted back to a passenger or passenger/cargo configuration. PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 Cost per product $10,970 per inspection cycle. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Unsafe Condition This AD was prompted by a report of a cracked reveal made from a casting found within a group of airplanes that should only have machined reveals made from 6061 aluminum. We are issuing this AD to detect and correct fatigue cracking of the lower forward corner reveal of the number 3 main entry doors (MEDs), which could lead to the door escape slide departing the airplane when the door is opened and the slide is deployed, and consequent injuries to passengers and crew using the door escape slide during an emergency evacuation. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Actions for Group 4 Airplanes: Not Previously Inspected or Changed For Group 4 airplanes identified in Boeing Special Attention Service Bulletin 747–53– 2460, Revision 2, dated December 22, 2010, that have not been previously inspected or changed in accordance with Boeing Special Attention Service Bulletin 747–53–2460, Revision 1, dated February 13, 2007: Before the accumulation of 1,500 total flight cycles, or within 1,000 flight cycles after the effective date of this AD, whichever occurs later, do a material type inspection to determine if the lower forward corner reveal is made from 6061 machined aluminum plate or 356 aluminum casting, in accordance with Part 6 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 747–53–2460, Revision 2, dated December 22, 2010. Doing the inspection specified in this paragraph terminates the inspections required by paragraph (j) of AD 2008–18–07, Amendment 38–15664 (73 FR 56960, October 1, 2008), for that airplane only. (1) If, during any inspection required by paragraph (g) of this AD, any corner reveal is found to be a casting: Before the accumulation of 7,000 total flight cycles; within 2,000 flight cycles after the effective date of this AD; or within 3,000 flight cycles after the most recent inspection of the E:\FR\FM\24DER1.SGM 24DER1 Federal Register / Vol. 79, No. 247 / Wednesday, December 24, 2014 / Rules and Regulations mstockstill on DSK4VPTVN1PROD with RULES number 3 MED corner reveal was done in accordance with Boeing Service Bulletin 747–53A2378, Revision 4, dated June 10, 2010; whichever occurs later; do a detailed inspection for cracking of the corner reveal, in accordance with Part 2 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 747–53– 2460, Revision 2, dated December 22, 2010. Repeat the inspection for cracking thereafter at intervals not to exceed 3,000 flight cycles until a new two-piece reveal is installed in accordance with the requirements of paragraph (g)(1)(i) of this AD. If any cracking is found, do the actions specified in paragraph (g)(1)(i) or (g)(1)(ii) of this AD. (i) Replace the cast reveal with a new 6061 machined aluminum two-piece corner reveal, before further flight, in accordance with Part 3 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 747–53–2460, Revision 2, dated December 22, 2010. (ii) Repair all cracking, before further flight, in accordance with Part 4 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 747–53– 2460, Revision 2, dated December 22, 2010. (2) If, during any inspection required by paragraph (g) of this AD, a corner reveal is found that is not a casting: Before further flight, do a detailed inspection for a sharp edge, in accordance with Part 1 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 747–53– 2460, Revision 2, dated December 22, 2010; and do a detailed inspection for cracking of the corner reveal, in accordance with Part 2 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 747–53–2460, Revision 2, dated December 22, 2010. Repeat the inspection for cracking thereafter at intervals not to exceed 6,000 flight cycles until the corner reveal is replaced with a 6061 machined aluminum two-piece corner reveal in accordance with the requirements of paragraph (j) of this AD. (i) If any sharp edge is found during any inspection required by paragraph (g)(2) of this AD, before further flight, rework the corner reveal, in accordance with Part 1 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 747–53– 2460, Revision 2, dated December 22, 2010. (ii) If any cracking is found during any inspection required by paragraph (g)(2) of this AD, before further flight, replace the corner reveal with a 6061 machined aluminum two-piece corner reveal, in accordance with Part 3 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 747–53– 2460, Revision 2, dated December 22, 2010. (h) Actions for Previously Inspected Group 4 Airplanes: Corner Reveal Replaced With One-Piece Reveal For Group 4 airplanes identified in Boeing Special Attention Service Bulletin 747–53– 2460, Revision 2, dated December 22, 2010, that have been inspected previously in accordance with Boeing Service Bulletin 747–53–2460, Revision 1, dated February 13, 2007, and on which the corner reveal has been replaced with a one-piece reveal: Within 10,000 flight cycles after the date the VerDate Sep<11>2014 16:05 Dec 23, 2014 Jkt 235001 reveal was replaced with a one-piece corner reveal, do a detailed inspection for cracking of the corner reveal, in accordance with Part 2 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 747–53–2460, Revision 2, dated December 22, 2010. Repeat the inspection for cracking thereafter at intervals not to exceed 6,000 flight cycles until the corner reveal is replaced with a 6061 machined aluminum two-piece corner reveal, in accordance with the requirements of paragraph (j) of this AD. If any cracking is found during any inspection required by this paragraph, before further flight, replace the one-piece corner reveal with a 6061 machined aluminum twopiece corner reveal, in accordance with Part 3 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 747–53–2460, Revision 2, dated December 22, 2010. (i) Actions for Previously Inspected Group 4 Airplanes: Corner Reveal Not Replaced, or Replaced With Two-Piece Reveal For Group 4 airplanes identified in Boeing Special Attention Service Bulletin 747–53– 2460, Revision 2, dated December 22, 2010, that have been inspected previously in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 747–53–2460, Revision 1, dated February 13, 2007; and on which the corner reveal either has not been replaced, or has been replaced with a two-piece reveal that was made by reworking an existing onepiece reveal: Before the accumulation of 7,000 total flight cycles; within 3,000 flight cycles after the most recent inspection or rework done in accordance with Boeing Special Attention Service Bulletin 747–53– 2460, Revision 1, dated February 13, 2007; or within 1,000 flight cycles after the effective date of this AD; whichever occurs later; do a material type inspection to determine if the corner reveal is a casting, in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 747–53– 2460, Revision 2, dated December 22, 2010. Doing the inspection specified in this paragraph terminates the inspections required by paragraph (j) of AD 2008–18–07, Amendment 39–15664 (73 FR 56960, October 1, 2008), for these airplanes. (1) If, during any inspection required by paragraph (i) of this AD, any corner reveal is found to be a casting: Before further flight, do a detailed inspection for cracking of the corner reveal. For one-piece reveals, inspect in accordance with Part 2 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 747–53– 2460, Revision 2, dated December 22, 2010; for two-piece reveals, inspect using a method approved in accordance with the procedures specified in paragraph (n) of this AD. Repeat the inspection thereafter at intervals not to exceed 3,000 flight cycles until a new twopiece reveal is installed in accordance with the requirements of paragraph (i)(1)(i) of this AD. If any cracking is found, do the actions specified in paragraph (i)(1)(i) or (i)(1)(ii) of this AD. (i) Replace the cast reveal with a new 6061 machined aluminum two-piece corner reveal, before further flight, in accordance with Part PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 77383 3 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 747–53–2460, Revision 2, dated December 22, 2010. (ii) Repair all cracking, before further flight, in accordance with Part 4 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 747–53– 2460, Revision 2, dated December 22, 2010. (2) If, during any inspection required by paragraph (i) of this AD, any one-piece corner reveal is found to be installed and is not a casting: Before the accumulation of 10,000 total flight cycles; or within 6,000 flight cycles after the most recent inspection done in accordance with Boeing Special Attention Service Bulletin 747–53–2460, Revision 1, dated February 13, 2007; whichever occurs later; do a detailed inspection of the corner reveal for cracking, in accordance with Part 2 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 747–53–2460, Revision 2, dated December 22, 2010. Repeat the inspection for cracking thereafter at intervals not to exceed 6,000 flight cycles until the corner reveal is replaced with a 6061 machined aluminum two-piece corner reveal. If any cracking is found during any inspection required by this paragraph, before further flight, replace the corner reveal with a 6061 machined aluminum two-piece corner reveal, in accordance with Part 3 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 747–53– 2460, Revision 2, dated December 22, 2010. (j) Terminating Action for Repetitive Inspections Installation of a 6061 machined aluminum two-piece corner reveal in accordance with Part 3 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 747–53–2460, Revision 2, dated December 22, 2010, terminates the repetitive inspections required by paragraphs (g), (h), and (i) of this AD. (k) Parts Installation Prohibition: (Cast 356 Aluminum) Reveals As of the effective date of this AD, no person may install a door lower forward corner reveal made of cast 356 aluminum on any airplane at a location specified in the Accomplishment Instructions of Boeing Special Attention Service Bulletin 747–53– 2460, Revision 2, dated December 22, 2010. This parts installation prohibition ends the parts installation prohibition specified in paragraph (n) of AD 2008–18–07, Amendment 39–15664 (73 FR 56960, October 1, 2008), for the airplanes identified in paragraph (c) of this AD. (l) Parts Installation Limitation: (Machined 6061 Aluminum) Reveals As of the effective date of this AD, no person may install a door lower forward corner reveal made of machined 6061 aluminum on any airplane at a location specified in the Accomplishment Instructions of Boeing Special Attention Service Bulletin 747–53–2460, Revision 2, dated December 22, 2010, unless it has been confirmed/reworked to be without a sharp edge, in accordance with Part 1 of the Accomplishment Instructions of Boeing E:\FR\FM\24DER1.SGM 24DER1 77384 Federal Register / Vol. 79, No. 247 / Wednesday, December 24, 2014 / Rules and Regulations Special Attention Service Bulletin 747–53– 2460, Revision 2, dated December 22, 2010. This parts installation prohibition ends the parts installation prohibition specified in paragraph (o) of AD 2008–18–07, Amendment 39–15664 (73 FR 56960, October 1, 2008), for the airplanes identified in paragraph (c) of this AD. (m) Exceptions to Service Information Specifications Where Boeing Special Attention Service Bulletin 747–53–2460, Revision 2, dated December 22, 2010, specifies a post-repair detailed inspection in accordance with Table 9, this AD requires a detailed inspection in accordance with paragraph 3.B., Part 2, of Boeing Special Attention Service Bulletin 747–53–2460, Revision 2, dated December 22, 2010. (n) 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 (o) 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 by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle ACO, to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane, and the approval must specifically refer to this AD. mstockstill on DSK4VPTVN1PROD with RULES (o) Related Information For more information about this AD, contact Bill Ashforth, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6432; fax: 425–917–6590; email: bill.ashforth@faa.gov. (p) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) Boeing Special Attention Service Bulletin 747–53–2460, Revision 2, dated December 22, 2010. (ii) Reserved. (3) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services VerDate Sep<11>2014 16:05 Dec 23, 2014 Jkt 235001 Management, P.O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; telephone 206– 544–5000, extension 1; fax 206–766–5680; Internet https://www.myboeingfleet.com. (4) You may view this service information at FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. 5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. www.regulations.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (phone: 800–647–5527) is Document Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. [FR Doc. 2014–30132 Filed 12–23–14; 8:45 am] JoAnn Theriault, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; phone: 781–238–7105; fax: 781–238– 7199; email: jo-ann.theriault@faa.gov. BILLING CODE 4910–13–P SUPPLEMENTARY INFORMATION: Issued in Renton, Washington, on November 19, 2014. Suzanne Masterson, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2013–0072; Directorate Identifier 2013–NE–04–AD; Amendment 39– 18017; AD 2014–23–01] RIN 2120–AA64 Airworthiness Directives; Pratt & Whitney Division Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Final rule; correction. AGENCY: The FAA is correcting an airworthiness directive (AD) that published in the Federal Register. That AD applies to all Pratt & Whitney Division (PW) PW4074, PW4074D, PW4077, PW4077D, PW4084D, PW4090, and PW4090–3 turbofan engine models with certain second-stage high-pressure turbine (HPT) air seals installed. The time required to perform the initial eddy current inspection (ECI) in the Compliance section is incorrect. This document corrects that error. In all other respects, the original document remains the same. DATES: This final rule is effective on December 26, 2014. The effective date of AD 2014–23–01, Amendment 39–18017 (79 FR 69369, November 21, 2014) remains December 26, 2014. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of September 17, 2013 (78 FR 49111, August 13, 2013). ADDRESSES: You may examine the AD docket on the Internet at http:// SUMMARY: PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 FOR FURTHER INFORMATION CONTACT: AD 2014– 23–01, Amendment 39–18017 (79 FR 69369, November 21, 2014), requires initial and repetitive inspections for cracks in second-stage HPT air seals, the removal of the mating hardware if the second-stage HPT air seal is found with a through-crack, and a mandatory terminating action for all PW PW4074, PW4074D, PW4077, PW4077D, PW4084D, PW4090, and PW4090–3 turbofan engine models with certain second-stage HPT air seals installed. As published, the time required to perform the initial ECI in the Compliance section is incorrect. AD 2014–23–01, paragraph (e)(2)(i), requires an initial ECI for cracks within 1,000 cycles-in-service after September 17, 2013, or before further flight, whichever occurs later. That compliance time is more restrictive than intended and will likely ground airplanes. The intent was to require an initial ECI for cracks before reaching 2,200 cycles since new, or within 1,000 cycles-in-service after September 17, 2013, or before further flight, whichever occurs later. No other part of the preamble or regulatory information has been changed. The effective date of AD 2014–23–01 remains December 26, 2014. Correction of Regulatory Text § 39.13 [Corrected] 2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 2013–15–09, Amendment 39–17525 (78 FR 49111, August 13, 2013), and adding the following new AD: ■ 2014–23–01 Pratt & Whitney Division: Amendment 39–18017; Docket No. FAA–2013–0072; Directorate Identifier 2013–NE–04–AD. E:\FR\FM\24DER1.SGM 24DER1

Agencies

[Federal Register Volume 79, Number 247 (Wednesday, December 24, 2014)]
[Rules and Regulations]
[Pages 77379-77384]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-30132]



[[Page 77379]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0366; Directorate Identifier 2011-NM-024-AD; 
Amendment 39-18038; AD 2014-24-05]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
The Boeing Company Model 747-100, 747-100B, 747-100B SUD, 747-200B, 
747-200C, 747-300, 747-400, 747-400D, and 747SR series airplanes. This 
AD was prompted by a report of a cracked reveal made from a casting 
found within a group of airplanes that should have machined reveals 
made only from 6061 aluminum. This AD requires an inspection to 
determine the material of the number 3 main entry door (MED) corner 
reveal, repetitive inspections of certain reveals for cracking, and 
corrective action if necessary. This AD also requires repetitive 
inspections for cracking of 6061 machined aluminum one-piece corner 
reveals, and replacement with 6061 machined aluminum two-piece corner 
reveals if necessary, which terminates certain repetitive inspections. 
We are issuing this AD to detect and correct fatigue cracking of the 
lower forward corner reveal of the number 3 MEDs, which could lead to 
the door escape slide departing the airplane when the door is opened 
and the slide is deployed, and consequent injuries to passengers and 
crew using the door escape slide during an emergency evacuation.

DATES: This AD is effective January 28, 2015.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of January 28, 
2015.

ADDRESSES: For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; 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.

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-2013-
0366; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this AD, the regulatory evaluation, any comments received, and 
other information. The address for the Docket Office (phone: 800-647-
5527) is Docket Management Facility, U.S. Department of Transportation, 
Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 
New Jersey Avenue SE., Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Bill Ashforth, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office 
(ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-
6432; fax: 425-917-6590; email: bill.ashforth@faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2008-18-07, Amendment 39-15664 (73 FR 56960, 
October 1, 2008). AD 2008-18-07 applies to certain The Boeing Company 
Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-300, 
747-400, 747-400D, and 747SR series airplanes. The NPRM published in 
the Federal Register on May 8, 2013 (78 FR 26720). The NPRM was 
prompted by a report of a cracked reveal made from a casting found 
within a group of airplanes that should have machined reveals made only 
from 6061 aluminum. The NPRM proposed to retain all the requirements of 
AD 2008-18-07. The NPRM also proposed to add, for certain airplanes, an 
inspection to determine the material of the number 3 MED corner reveal, 
repetitive inspections for cracking of 6061 machined aluminum one-piece 
corner reveals, and replacement with 6061 machined aluminum two-piece 
corner reveals if necessary, which terminates certain repetitive 
inspections. We are issuing this AD to detect and correct fatigue 
cracking of the lower forward corner reveal of the number 3 MEDs, which 
could lead to the door escape slide departing the airplane when the 
door is opened and the slide is deployed, and consequent injuries to 
passengers and crew using the door escape slide during an emergency 
evacuation.

Related AD

    AD 2008-18-07, Amendment 39-15664 (73 FR 56960, October 1, 2008), 
requires, for The Boeing Company Model 747-100, 747-100B, 747-100B SUD, 
747-200B, 747-200C, 747-300, 747-400, 747-400D, and 747SR series 
airplanes, an inspection to determine the material of a number 3 MED 
corner reveal, repetitive inspections of certain reveals for cracking, 
a detailed inspection of certain reveals for a sharp edge and cracking, 
and corrective action if necessary. AD 2008-18-07 allows reveal 
replacement as an option to certain inspections. AD 2008-18-07 was 
prompted by reports of cracking and/or a sharp edge in the lower 
forward corner reveal of the number 3 MEDs. AD 2008-18-07 refers to 
Boeing Special Attention Service Bulletin 747-53-2460, Revision 1, 
dated February 13, 2007, as the appropriate source of service 
information for the required actions specified in that AD.

Explanation of Difference in Requirements Between the NPRM (78 FR 
26720, May 8, 2013) and This Final Rule

    In the NPRM (78 FR 26720, May 8, 2013), the FAA proposed to 
supersede AD 2008-18-07, Amendment 39-15664 (73 FR 56960, October 1, 
2008), to reflect the changes in airplane groups specified in revised 
service information, Boeing Special Attention Service Bulletin 747-53-
2460, Revision 2, dated December 22, 2010. However, based on the 
comments received on the NPRM, it became evident that it was difficult 
to follow the numerous changes between Boeing Special Attention Service 
Bulletin 747-53-2460, Revision 1, dated February 13, 2007, and Boeing 
Special Attention Service Bulletin 747-53-2460, Revision 2, dated 
December 22, 2010, as well as in following the corresponding actions 
specified in the NPRM.
    There are only two significant changes in Boeing Special Attention 
Service Bulletin 747-53-2460, Revision 2, dated December 22, 2010: (1) 
Airplanes having line numbers 1038 through 1270 were moved from Group 2 
to Group 4; and (2) for Group 4 airplanes, there are additional 
actions. Therefore, for clarity, we have determined that a less 
burdensome approach is to revise this final rule to include only the 
new actions for Group 4 airplanes. Instead of superseding AD 2008-18-
07, Amendment 39-15664 (73 FR 56960, October 1, 2008), this final rule 
is a stand-alone AD, applicable

[[Page 77380]]

only to Group 4 airplanes as identified in Boeing Special Attention 
Service Bulletin 747-53-2460, Revision 2, dated December 22, 2010, 
except for those airplanes that have been converted to an all-cargo 
configuration. Airplanes identified in the applicability of AD 2008-18-
07 are still required to continue to comply with the requirements of 
that AD.
    Since this AD does not supersede AD 2008-18-07, Amendment 39-15664 
(73 FR 56960, October 1, 2008), paragraphs (g) through (m), (p), (q), 
and (v) of the NPRM (78 FR 26720, May 8, 2013) are not included in this 
AD. Also, the corresponding paragraph identifiers have been 
redesignated in this final rule, as listed in the following table:

                   Redesignated Paragraph Identifiers
------------------------------------------------------------------------
Requirement in the proposed AD (78
      FR 26720, May 8, 2013)        Corresponding requirement in this AD
------------------------------------------------------------------------
 paragraph (t)                       paragraph (g).
 paragraph (s)                       paragraph (h).
 paragraph (r)                       paragraph (i).
 paragraph (u)                       paragraph (j).
 paragraph (n)                       paragraph (k).
 paragraph (o)                       paragraph (l).
 paragraph (w)                       paragraph (n).
------------------------------------------------------------------------

    We have also revised paragraphs (n) and (o) of the proposed AD (78 
FR 26720, May 8, 2013) (redesignated as paragraphs (k) and (l) of this 
AD) that referred to ``AD 2008-18-07.'' In paragraphs (k) and (l) of 
this AD, we have referred to the current service information, Boeing 
Special Attention Service Bulletin 747-53-2460, Revision 2, dated 
December 22, 2010, instead of AD 2008-18-07, Amendment 39-15664 (73 FR 
56960, October 1, 2008), for the locations where cast 356 aluminum 
reveals and machined 6061 aluminum reveals may not be installed. 
Paragraphs (k) and (l) of this AD state that the parts installation 
prohibition ends the parts installation prohibitions specified in 
paragraphs (n) and (o) of AD 2008-18-07, Amendment 39-15664 (73 FR 
56960, October 1, 2008).

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the NPRM (78 
FR 26720, May 8, 2013) and the FAA's response to each comment.

Request To Clarify the Cause of the Unsafe Condition

    Boeing asked that we clarify the cause of the unsafe condition 
identified in paragraph (e) of the proposed AD (78 FR 26720, May 8, 
2013). Boeing stated that the report that prompted the proposed 
supersedure of AD 2008-18-07, Amendment 39-15664 (73 FR 56960, October 
1, 2008), involved a cracked casting on an airplane that should have 
machined reveals made from only 6061 aluminum.
    We agree that the unsafe condition should be clarified for the 
reason provided. We have changed the wording for the unsafe condition 
identified in the SUMMARY section and in paragraph (e) of this final 
rule to specify that ``This new AD was prompted by a report of a 
cracked reveal made from a casting found within a group of airplanes 
that should have machined reveals made only from 6061 aluminum.'' We 
have also clarified the Discussion section of this final rule to 
specify that the NPRM (78 FR 26720, May 8, 2013) was prompted by that 
report.

Request To Revise Wording in the NPRM (78 FR 26720, May 8, 2013)

    Boeing requested numerous changes related to the wording in 
paragraphs (g), (h), (j), (u) and (v) of the NPRM (78 FR 26720, May 8, 
2013).
    We acknowledge the commenter's concerns for clarity. However, as 
stated previously, this AD does not supersede AD 2008-18-07, Amendment 
39-15664 (73 FR 56960, October 1, 2008). The changes requested by the 
commenter referred to the ``retained'' paragraphs of AD 2008-18-07, 
which are not restated in this AD; therefore, no action is necessary in 
this regard.

Request To Revise Service Information

    Delta Airlines (Delta) requested that Boeing Special Attention 
Service Bulletin 747-53-2460, Revision 2, dated December 22, 2010, be 
revised prior to the issuance of this final rule. Delta stated that 
paragraphs (r) and (s) of the proposed AD (78 FR 26720, May 8, 2013) 
(redesignated as paragraphs (i) and (h) of this AD) are clear and 
understandable; however, when Delta reviewed the required actions in 
Table 1 of Boeing Special Attention Service Bulletin 747-53-2460, 
Revision 2, dated December 22, 2010, Delta was not able to clearly 
determine which conditions were linked with which actions. Delta stated 
that Boeing also agrees that the compliance tables of Boeing Special 
Attention Service Bulletin 747-53-2460, Revision 2, dated December 22, 
2010, should be clarified for operators' use.
    We disagree with delaying this AD to wait for revised service 
information in light of the urgency of the identified unsafe condition. 
As Delta stated, the tables contained in Boeing Special Attention 
Service Bulletin 747-53-2460, Revision 2, dated December 22, 2010, are 
complicated and could be misinterpreted; however, we have addressed 
this concern by specifying the requirements and clarifying the 
appropriate actions in paragraphs (h) and (i) of this AD. When the 
service information is revised, we might consider approving it as an 
alternative method of compliance (AMOC) for these actions. We have not 
changed this final rule in this regard.

Request To Address an Error in Service Information

    Delta stated that, in the last row under the ``Action'' column of 
Table 8 of paragraph 1.E., Compliance, of Boeing Special Attention 
Service Bulletin 747-53-2460, Revision 2, dated December 22, 2010, 
there is a reference to ``Table 9,'' which does not exist. Delta stated 
that the correct paragraph reference is ``Paragraph 3.B., Part 2,'' as 
confirmed in Delta's correspondence with Boeing. Delta requested that 
Boeing Special Attention Service Bulletin 747-53-2460, Revision 2, 
dated December 22, 2010, be revised prior to the issuance of this final 
rule, or that we address this error in this final rule, or, at a 
minimum, address this error in a global AMOC.
    We partially agree. We disagree to wait for revised service 
information in light of the urgency of the identified unsafe condition. 
However, we agree that the reference to Table 9 in paragraph 1.E., 
Compliance, of Boeing Special Attention Service Bulletin 747-53-2460, 
Revision 2, dated December 22, 2010, is incorrect. To address this 
error, we have added a new paragraph (m) in this AD to state that, 
where the Accomplishment Instructions of Boeing Special Attention 
Service Bulletin 747-53-2460, Revision 2, dated December 22, 2010, 
specify a post-repair detailed inspection in accordance with Table 9, 
this AD requires a detailed inspection in accordance with paragraph 
3.B., Part 2, of the Accomplishment Instructions of Boeing Special 
Attention Service Bulletin 747-53-2460, Revision 2, dated December 22, 
2010. When revised service information becomes available, we might 
consider approving it as an AMOC for the actions required by this AD.

Request To Revise the Proposed AD To Include an Inspection for a Sharp 
Edge for Group 4 Airplanes

    Boeing asked that we revise paragraph (r)(2) of the proposed AD (78 
FR 26720, May 8, 2013) (redesignated as paragraph (i)(2) of this AD) to 
include an inspection for a potential sharp edge

[[Page 77381]]

common to the reveal. Boeing stated that this inspection might be the 
first inspection performed and, therefore, it is possible that a sharp 
edge could be found on a machined reveal.
    We do not agree to revise the wording of paragraph (i)(2) of this 
AD (designated as paragraph (r)(2) of the proposed AD (78 FR 26720, May 
8, 2013)). Paragraph (i)(2) of this AD requires, for previously 
inspected Group 4 airplanes, a material-type inspection to determine if 
the corner reveal is a casting, and, if a casting is found, continued 
inspections or replacement of the reveal with a two-piece machined 
reveal. Castings do not have sharp edges. Group 4 airplanes that were 
not previously inspected or changed, that have corner reveals found not 
to be castings, require inspections for a sharp edge in paragraph 
(g)(2) of this AD. We have not changed this final rule in this regard.

Request for Alternative Corrective Action for Group 4 Airplanes

    Boeing asked that we revise paragraph (t)(1) of the proposed AD (78 
FR 26720, May 8, 2013) (redesignated as paragraph (g)(1) of this AD) to 
allow a weld repair for a cracked reveal made from a casting on Group 4 
airplanes. Boeing stated that this would allow operators to repair the 
casting if they cannot obtain a machined reveal.
    We agree that paragraph (g)(1) of this AD should allow a weld 
repair as an alternative corrective action since this was a permitted 
action for Group 2 airplanes in AD 2008-18-07, Amendment 39-15664 (73 
FR 56960, October 1, 2008). This alternative corrective action for 
Group 4 airplanes was contained in Boeing Special Attention Service 
Bulletin 747-53-2460, Revision 2, dated December 22, 2010, but was 
inadvertently omitted in the proposed AD (78 FR 26720, May 8, 2013). 
Paragraph (t) of the NPRM is redesignated as paragraph (g) in this AD 
and we have revised paragraph (g)(1) by adding new paragraphs (g)(1)(i) 
and (g)(1)(ii) in order to allow a weld repair as an option to 
replacing the reveal if any cracking is found. In paragraph (g)(1)(ii) 
of this AD we specify repairing in accordance with Part 4 of Boeing 
Special Attention Service Bulletin 747-53-2460, Revision 2, dated 
December 22, 2010. The inspection for cracking specified in paragraph 
(g)(1) of this AD is to be repeated thereafter at intervals not to 
exceed 3,000 flight cycles until a new two-piece reveal is installed in 
accordance with the requirements of paragraph (g)(1)(i) of this AD.

Request To Reference Service Bulletin Information Notices or Revise 
Service Bulletin

    Delta requested that Boeing Service Bulletin Information Notice 
747-53-2460 IN 03, dated March 24, 2011, be referenced as an approved 
deviation from Boeing Special Attention Service Bulletin 747-53-2460, 
Revision 2, dated December 22, 2010. Alternatively, Boeing requested 
that we delay the issuance of this final rule until Boeing revises 
Boeing Special Attention Service Bulletin 747-53-2460, Revision 2, 
dated December 22, 2010, to incorporate the changes outlined in that 
information notice.
    We partially agree. We agree that Boeing Service Bulletin 
Information Notice 747-53-2460 IN 03, dated March 24, 2011, contains 
acceptable information for the inspection and modification mandated in 
this AD. However, we disagree with delaying issuance of this final rule 
until revised service information becomes available. We have determined 
that to delay this final rule would be inappropriate, because the 
inspections of the number 3 MED reveals and corrective actions are 
needed to reduce the risk of the identified unsafe condition addressed 
in this AD. The information that Boeing Service Bulletin Information 
Notice 747-53-2460 IN 03, dated March 24, 2011, clarifies is for 
reference only and is not required to address the identified unsafe 
condition. When revised service information becomes available, we might 
consider approving it as an AMOC for the actions required by this AD. 
We have made no change to this AD in this regard.

Explanation of Additional Changes Made to This Final Rule

    We redesignated paragraphs (r) and (r)(2) of the NPRM (78 FR 26720, 
May 8, 2013) as paragraphs (i) and (i)(2) of this final rule and 
removed the phrase ``Boeing Special Attention Service Bulletin 747-53-
2460, Revision 2, dated December 22, 2010,'' from the initial 
compliance times listed in those paragraphs. In the proposed AD, we 
stated that the compliance times could be calculated from the most 
recent work performed in accordance with Boeing Special Attention 
Service Bulletin 747-53-2460, Revision 1, dated February 13, 2007; or 
Revision 2, dated December 22, 2010; but this would introduce an error 
in paragraph (i) of this AD since it would require operators to 
complete the inspections required by Boeing Special Attention Service 
Bulletin 747-53-2460, Revision 2, dated December 22, 2010, for a second 
time, if the reference to Boeing Special Attention Service Bulletin 
747-53-2460, Revision 2, dated December 22, 2010, remained.
    Paragraph (i)(1) of this final rule specifies inspections for 
cracking of any corner reveal found to be a one-piece or two-piece 
casting. Boeing Special Attention Service Bulletin 747-53-2460, 
Revision 2, dated December 22, 2010, provides inspection procedures for 
one-piece corner reveals, but not for the two-piece corner reveals. 
Because the inspection procedures for the two-piece corner reveals were 
not included in the service information, operators would have been 
unable to comply with the proposed requirement to inspect a two-piece 
corner reveal, and in this case would have been required to obtain 
approval of an alternative method of compliance for this inspection. We 
have therefore revised paragraph (i)(1) of this AD to provide the 
appropriate procedures for both scenarios.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
this AD with the changes described previously and minor editorial 
changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM (78 FR 26720, May 8, 2013) for correcting the unsafe condition; 
and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (78 FR 26720, May 8, 2013).
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this AD.

Costs of Compliance

    We estimate that this AD affects 166 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

[[Page 77382]]



                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
             Action                    Labor cost         Parts cost      Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Material type inspection and      14 work-hours x $85              $0   $1,190 per           $197,540 per
 inspection for cracks.            per hour = $1,190                     inspection cycle.    inspection cycle.
                                   per inspection
                                   cycle.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary on-condition 
actions that would be required based on the results of the inspections. 
We have no way of determining the number of aircraft that might need 
these actions:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                 Action                          Labor cost             Parts cost         Cost per product
----------------------------------------------------------------------------------------------------------------
Corner reveal removal and replacement..  17 work-hours x $85 per             $9,525   $10,970 per inspection
                                          hour = $1,445 per                            cycle.
                                          inspection cycle.
----------------------------------------------------------------------------------------------------------------

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII: Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701: ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    This AD will not have federalism implications under Executive Order 
13132. This AD will not have a substantial direct effect on the States, 
on the relationship between the national government and the States, or 
on the distribution of power and responsibilities among the various 
levels of government.
    For the reasons discussed above, I certify that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979),
    (3) Will not affect intrastate aviation in Alaska, and
    (4) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:


    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

2014-24-05 The Boeing Company: Amendment 39-18038; Docket No. FAA-
2013-0366; Directorate Identifier 2011-NM-024-AD.

(a) Effective Date

    This AD is effective January 28, 2015.

(b) Affected ADs

    Certain requirements of this AD terminate certain requirements 
of AD 2008-18-07, Amendment 39-15664 (73 FR 56960, October 1, 2008).

(c) Applicability

    This AD applies to The Boeing Company Model 747-100, 747-100B, 
747-100B SUD, 747-200B, 747-200C, 747-300, 747-400, 747-400D, and 
747SR series airplanes, certificated in any category, identified as 
Group 4 airplanes in Boeing Special Attention Service Bulletin 747-
53-2460, Revision 2, dated December 22, 2010, except airplanes that 
have been converted to an all-cargo configuration. Also, the 
requirements of this AD are applicable when a converted airplane 
operating in an all-cargo configuration is converted back to a 
passenger or passenger/cargo configuration.

(d) Subject

    Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Unsafe Condition

    This AD was prompted by a report of a cracked reveal made from a 
casting found within a group of airplanes that should only have 
machined reveals made from 6061 aluminum. We are issuing this AD to 
detect and correct fatigue cracking of the lower forward corner 
reveal of the number 3 main entry doors (MEDs), which could lead to 
the door escape slide departing the airplane when the door is opened 
and the slide is deployed, and consequent injuries to passengers and 
crew using the door escape slide during an emergency evacuation.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Actions for Group 4 Airplanes: Not Previously Inspected or Changed

    For Group 4 airplanes identified in Boeing Special Attention 
Service Bulletin 747-53-2460, Revision 2, dated December 22, 2010, 
that have not been previously inspected or changed in accordance 
with Boeing Special Attention Service Bulletin 747-53-2460, Revision 
1, dated February 13, 2007: Before the accumulation of 1,500 total 
flight cycles, or within 1,000 flight cycles after the effective 
date of this AD, whichever occurs later, do a material type 
inspection to determine if the lower forward corner reveal is made 
from 6061 machined aluminum plate or 356 aluminum casting, in 
accordance with Part 6 of the Accomplishment Instructions of Boeing 
Special Attention Service Bulletin 747-53-2460, Revision 2, dated 
December 22, 2010. Doing the inspection specified in this paragraph 
terminates the inspections required by paragraph (j) of AD 2008-18-
07, Amendment 38-15664 (73 FR 56960, October 1, 2008), for that 
airplane only.
    (1) If, during any inspection required by paragraph (g) of this 
AD, any corner reveal is found to be a casting: Before the 
accumulation of 7,000 total flight cycles; within 2,000 flight 
cycles after the effective date of this AD; or within 3,000 flight 
cycles after the most recent inspection of the

[[Page 77383]]

number 3 MED corner reveal was done in accordance with Boeing 
Service Bulletin 747-53A2378, Revision 4, dated June 10, 2010; 
whichever occurs later; do a detailed inspection for cracking of the 
corner reveal, in accordance with Part 2 of the Accomplishment 
Instructions of Boeing Special Attention Service Bulletin 747-53-
2460, Revision 2, dated December 22, 2010. Repeat the inspection for 
cracking thereafter at intervals not to exceed 3,000 flight cycles 
until a new two-piece reveal is installed in accordance with the 
requirements of paragraph (g)(1)(i) of this AD. If any cracking is 
found, do the actions specified in paragraph (g)(1)(i) or (g)(1)(ii) 
of this AD.
    (i) Replace the cast reveal with a new 6061 machined aluminum 
two-piece corner reveal, before further flight, in accordance with 
Part 3 of the Accomplishment Instructions of Boeing Special 
Attention Service Bulletin 747-53-2460, Revision 2, dated December 
22, 2010.
    (ii) Repair all cracking, before further flight, in accordance 
with Part 4 of the Accomplishment Instructions of Boeing Special 
Attention Service Bulletin 747-53-2460, Revision 2, dated December 
22, 2010.
    (2) If, during any inspection required by paragraph (g) of this 
AD, a corner reveal is found that is not a casting: Before further 
flight, do a detailed inspection for a sharp edge, in accordance 
with Part 1 of the Accomplishment Instructions of Boeing Special 
Attention Service Bulletin 747-53-2460, Revision 2, dated December 
22, 2010; and do a detailed inspection for cracking of the corner 
reveal, in accordance with Part 2 of the Accomplishment Instructions 
of Boeing Special Attention Service Bulletin 747-53-2460, Revision 
2, dated December 22, 2010. Repeat the inspection for cracking 
thereafter at intervals not to exceed 6,000 flight cycles until the 
corner reveal is replaced with a 6061 machined aluminum two-piece 
corner reveal in accordance with the requirements of paragraph (j) 
of this AD.
    (i) If any sharp edge is found during any inspection required by 
paragraph (g)(2) of this AD, before further flight, rework the 
corner reveal, in accordance with Part 1 of the Accomplishment 
Instructions of Boeing Special Attention Service Bulletin 747-53-
2460, Revision 2, dated December 22, 2010.
    (ii) If any cracking is found during any inspection required by 
paragraph (g)(2) of this AD, before further flight, replace the 
corner reveal with a 6061 machined aluminum two-piece corner reveal, 
in accordance with Part 3 of the Accomplishment Instructions of 
Boeing Special Attention Service Bulletin 747-53-2460, Revision 2, 
dated December 22, 2010.

(h) Actions for Previously Inspected Group 4 Airplanes: Corner Reveal 
Replaced With One-Piece Reveal

    For Group 4 airplanes identified in Boeing Special Attention 
Service Bulletin 747-53-2460, Revision 2, dated December 22, 2010, 
that have been inspected previously in accordance with Boeing 
Service Bulletin 747-53-2460, Revision 1, dated February 13, 2007, 
and on which the corner reveal has been replaced with a one-piece 
reveal: Within 10,000 flight cycles after the date the reveal was 
replaced with a one-piece corner reveal, do a detailed inspection 
for cracking of the corner reveal, in accordance with Part 2 of the 
Accomplishment Instructions of Boeing Special Attention Service 
Bulletin 747-53-2460, Revision 2, dated December 22, 2010. Repeat 
the inspection for cracking thereafter at intervals not to exceed 
6,000 flight cycles until the corner reveal is replaced with a 6061 
machined aluminum two-piece corner reveal, in accordance with the 
requirements of paragraph (j) of this AD. If any cracking is found 
during any inspection required by this paragraph, before further 
flight, replace the one-piece corner reveal with a 6061 machined 
aluminum two-piece corner reveal, in accordance with Part 3 of the 
Accomplishment Instructions of Boeing Special Attention Service 
Bulletin 747-53-2460, Revision 2, dated December 22, 2010.

(i) Actions for Previously Inspected Group 4 Airplanes: Corner Reveal 
Not Replaced, or Replaced With Two-Piece Reveal

    For Group 4 airplanes identified in Boeing Special Attention 
Service Bulletin 747-53-2460, Revision 2, dated December 22, 2010, 
that have been inspected previously in accordance with the 
Accomplishment Instructions of Boeing Special Attention Service 
Bulletin 747-53-2460, Revision 1, dated February 13, 2007; and on 
which the corner reveal either has not been replaced, or has been 
replaced with a two-piece reveal that was made by reworking an 
existing one-piece reveal: Before the accumulation of 7,000 total 
flight cycles; within 3,000 flight cycles after the most recent 
inspection or rework done in accordance with Boeing Special 
Attention Service Bulletin 747-53-2460, Revision 1, dated February 
13, 2007; or within 1,000 flight cycles after the effective date of 
this AD; whichever occurs later; do a material type inspection to 
determine if the corner reveal is a casting, in accordance with the 
Accomplishment Instructions of Boeing Special Attention Service 
Bulletin 747-53-2460, Revision 2, dated December 22, 2010. Doing the 
inspection specified in this paragraph terminates the inspections 
required by paragraph (j) of AD 2008-18-07, Amendment 39-15664 (73 
FR 56960, October 1, 2008), for these airplanes.
    (1) If, during any inspection required by paragraph (i) of this 
AD, any corner reveal is found to be a casting: Before further 
flight, do a detailed inspection for cracking of the corner reveal. 
For one-piece reveals, inspect in accordance with Part 2 of the 
Accomplishment Instructions of Boeing Special Attention Service 
Bulletin 747-53-2460, Revision 2, dated December 22, 2010; for two-
piece reveals, inspect using a method approved in accordance with 
the procedures specified in paragraph (n) of this AD. Repeat the 
inspection thereafter at intervals not to exceed 3,000 flight cycles 
until a new two-piece reveal is installed in accordance with the 
requirements of paragraph (i)(1)(i) of this AD. If any cracking is 
found, do the actions specified in paragraph (i)(1)(i) or (i)(1)(ii) 
of this AD.
    (i) Replace the cast reveal with a new 6061 machined aluminum 
two-piece corner reveal, before further flight, in accordance with 
Part 3 of the Accomplishment Instructions of Boeing Special 
Attention Service Bulletin 747-53-2460, Revision 2, dated December 
22, 2010.
    (ii) Repair all cracking, before further flight, in accordance 
with Part 4 of the Accomplishment Instructions of Boeing Special 
Attention Service Bulletin 747-53-2460, Revision 2, dated December 
22, 2010.
    (2) If, during any inspection required by paragraph (i) of this 
AD, any one-piece corner reveal is found to be installed and is not 
a casting: Before the accumulation of 10,000 total flight cycles; or 
within 6,000 flight cycles after the most recent inspection done in 
accordance with Boeing Special Attention Service Bulletin 747-53-
2460, Revision 1, dated February 13, 2007; whichever occurs later; 
do a detailed inspection of the corner reveal for cracking, in 
accordance with Part 2 of the Accomplishment Instructions of Boeing 
Special Attention Service Bulletin 747-53-2460, Revision 2, dated 
December 22, 2010. Repeat the inspection for cracking thereafter at 
intervals not to exceed 6,000 flight cycles until the corner reveal 
is replaced with a 6061 machined aluminum two-piece corner reveal. 
If any cracking is found during any inspection required by this 
paragraph, before further flight, replace the corner reveal with a 
6061 machined aluminum two-piece corner reveal, in accordance with 
Part 3 of the Accomplishment Instructions of Boeing Special 
Attention Service Bulletin 747-53-2460, Revision 2, dated December 
22, 2010.

(j) Terminating Action for Repetitive Inspections

    Installation of a 6061 machined aluminum two-piece corner reveal 
in accordance with Part 3 of the Accomplishment Instructions of 
Boeing Special Attention Service Bulletin 747-53-2460, Revision 2, 
dated December 22, 2010, terminates the repetitive inspections 
required by paragraphs (g), (h), and (i) of this AD.

(k) Parts Installation Prohibition: (Cast 356 Aluminum) Reveals

    As of the effective date of this AD, no person may install a 
door lower forward corner reveal made of cast 356 aluminum on any 
airplane at a location specified in the Accomplishment Instructions 
of Boeing Special Attention Service Bulletin 747-53-2460, Revision 
2, dated December 22, 2010. This parts installation prohibition ends 
the parts installation prohibition specified in paragraph (n) of AD 
2008-18-07, Amendment 39-15664 (73 FR 56960, October 1, 2008), for 
the airplanes identified in paragraph (c) of this AD.

(l) Parts Installation Limitation: (Machined 6061 Aluminum) Reveals

    As of the effective date of this AD, no person may install a 
door lower forward corner reveal made of machined 6061 aluminum on 
any airplane at a location specified in the Accomplishment 
Instructions of Boeing Special Attention Service Bulletin 747-53-
2460, Revision 2, dated December 22, 2010, unless it has been 
confirmed/reworked to be without a sharp edge, in accordance with 
Part 1 of the Accomplishment Instructions of Boeing

[[Page 77384]]

Special Attention Service Bulletin 747-53-2460, Revision 2, dated 
December 22, 2010. This parts installation prohibition ends the 
parts installation prohibition specified in paragraph (o) of AD 
2008-18-07, Amendment 39-15664 (73 FR 56960, October 1, 2008), for 
the airplanes identified in paragraph (c) of this AD.

(m) Exceptions to Service Information Specifications

    Where Boeing Special Attention Service Bulletin 747-53-2460, 
Revision 2, dated December 22, 2010, specifies a post-repair 
detailed inspection in accordance with Table 9, this AD requires a 
detailed inspection in accordance with paragraph 3.B., Part 2, of 
Boeing Special Attention Service Bulletin 747-53-2460, Revision 2, 
dated December 22, 2010.

(n) 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 (o) 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 by the 
Boeing Commercial Airplanes Organization Designation Authorization 
(ODA) that has been authorized by the Manager, Seattle ACO, to make 
those findings. For a repair method to be approved, the repair must 
meet the certification basis of the airplane, and the approval must 
specifically refer to this AD.

(o) Related Information

    For more information about this AD, contact Bill Ashforth, 
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft 
Certification Office, 1601 Lind Avenue SW., Renton, WA 98057-3356; 
phone: 425-917-6432; fax: 425-917-6590; email: 
bill.ashforth@faa.gov.

(p) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (i) Boeing Special Attention Service Bulletin 747-53-2460, 
Revision 2, dated December 22, 2010.
    (ii) Reserved.
    (3) For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-
5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com.
    (4) You may view this service information at FAA, Transport 
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For 
information on the availability of this material at the FAA, call 
425-227-1221.
    5) You may view this service information that is incorporated by 
reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.


    Issued in Renton, Washington, on November 19, 2014.
Suzanne Masterson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-30132 Filed 12-23-14; 8:45 am]
BILLING CODE 4910-13-P