80 FR 72573 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 80, Issue 224 (November 20, 2015)
Federal Aviation Administration
Federal Register Volume 80, Issue 224 (November 20, 2015)
| Page Range | 72573-72576 | |
| FR Document | 2015-28891 |
[Federal Register Volume 80, Number 224 (Friday, November 20, 2015)] [Rules and Regulations] [Pages 72573-72576] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2015-28891] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-1266; Directorate Identifier 2014-NM-151-AD; Amendment 39-18327; AD 2015-23-11] 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, 747-300, 747SR, and 747SP series airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that certain fuselage skin lap joints are subject to widespread fatigue damage (WFD). This AD requires repetitive post-modification inspections for cracking of the skin or internal doubler along the edge fastener rows of the modification, and repair if necessary. We are issuing this AD to detect and correct fatigue cracking in certain fuselage skin lap joints, which could result in rapid depressurization of the airplane. DATES: This AD is effective December 28, 2015. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of December 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. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-1266. Examining the AD Docket You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015- 1266; 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: Nathan Weigand, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6428; fax: 425-917-6590; email: [email protected]. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain The Boeing Company Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-300, 747SR, and 747SP series airplanes. The NPRM published in the Federal Register on May 5, 2015 (80 FR 25630). The NPRM was prompted by an evaluation by the DAH indicating that certain fuselage skin lap joints are subject to WFD. The NPRM proposed to require repetitive post-modification inspections for cracking of the skin or internal doubler along the edge fastener rows of the modification, and repair if necessary. We are issuing this AD to detect and correct fatigue cracking in certain fuselage skin lap joints, which could result in rapid depressurization of the airplane. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM (80 FR 25630, May 5, 2015) and the FAA's response to each comment. Request To Remove Warranty Statement Boeing requested that we remove the statement that ``some of the costs of this proposed AD may be covered under warranty'' in the Costs of Compliance section of the NPRM (80 FR 25630, May 5, 2015). Boeing stated that the actions in the NPRM are not covered by warranty. We agree with the commenter's request. We have revised the Costs of Compliance section of this final rule accordingly. Request To Revise Paragraph Headings Boeing requested that we revise the headings of paragraphs (g), (h), (j), and (k) of the proposed AD (80 FR 25630, May 5, 2015) by removing reference to the inspections as ``repetitive'' or ``initial.'' Boeing stated that these revisions will provide consistency among paragraph headings because paragraphs (g), (j), and (k) of the proposed AD do not have an initial inspection program, yet paragraph (h) of the proposed AD has only an initial inspection. We acknowledge the commenter's concern and agree to clarify the headings. We do not presume that the term ``repetitive'' necessarily excludes the initial action. An action cannot be repeated without accomplishment of the initial action. In addition, in many ADs we use the term ``repetitive'' actions for paragraphs that include the initial action and repetitive actions. Paragraphs (g), (j), and (k) of this AD include both a sentence specifying the initial inspection and a sentence specifying the repetitive inspections. We have not changed this AD in this regard. Request To Clarify Compliance Time Boeing requested that we clarify the compliance time in paragraphs (g), (h), (j), and (k) of the proposed AD (80 FR [[Page 72574]] 25630, May 5, 2015) by revising ``at the applicable time'' to ``at the applicable time and repeat intervals.'' Boeing stated that these revisions would clarify that the applicable time also includes the repeat intervals per Boeing Alert Service Bulletin 747-53A2367, Revision 5, dated July 8, 2014. We do not agree to combine the initial inspection and the repetitive inspection times into one statement because ADs typically call out initial inspections and repetitive inspections in separate sentences. Paragraph (h) of this AD specifies only an initial inspection. Paragraphs (g), (j), and (k) of this AD specifies an initial inspection and states that the repetitive inspections are for the unrepaired areas, which are to be done at the applicable times specified in Boeing Alert Service Bulletin 747-53A2367, Revision 5, dated July 8, 2014. We have not changed this AD in this regard. Request To Delete the Unrepaired Area Statement From Paragraphs (g) (j) and (k) of the Proposed AD (80 FR 25630, May 5, 2015) Boeing requested that we delete the last sentence in paragraphs (g), (j), and (k) of the proposed AD (80 FR 25630, May 5, 2015), which states ``In unrepaired areas, repeat the . . . inspections for cracks . . . .'' Boeing stated that the sentence is confusing as the unrepaired area case is actually for no cracks found in the modification area after doing the inspection as specified in the applicable tables 3, 5, and 6 of Boeing Alert Service Bulletin 747-53A2367, Revision 5, dated July 8, 2014. Boeing explained that the proposed AD wording may cause confusion when information is provided in a different format than the service bulletin tables. We do not agree with the commenter's request because the text ``in unrepaired areas'' matches the text in Boeing Alert Service Bulletin 747-53A2367, Revision 5, dated July 8, 2014. Paragraphs (g), (j), and (k) of this AD specify doing actions at the applicable time specified in tables 3, 5, and 6 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2367, Revision 5, dated July 8, 2014. In these tables, the compliance time is specified for the actions required for the unrepaired area. We have not revised this AD in this regard. Request To Combine Paragraphs Boeing requested that we combine paragraphs (h) and (i) of the proposed AD (80 FR 25630, May 5, 2015) by deleting paragraph (i) of the proposed AD and revising paragraph (h) of the proposed AD from ``at the applicable time'' to ``at the applicable time and repeat intervals.'' Boeing explained that it is confusing to have separate paragraphs address initial and repetitive inspections for a particular aircraft as both initial and repetitive inspections are addressed within table 4 of Boeing Alert Service Bulletin 747-53A2367, Revision 5, dated July 8, 2014. We acknowledge that table 4 of Boeing Alert Service Bulletin 747- 53A2367, Revision 5, dated July 8, 2014, contains compliance times for both initial and repetitive inspections. However, we do not agree with the commenter's request because the AD includes separate paragraphs in order to clarify the repetitive inspection intervals. For the initial inspections, table 4 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2367, Revision 5, dated July 8, 2014, specifies two crack conditions, which are based on the number of fight cycles on the airplane since stringer 6 external doublers were installed. To aid the operators in determining which repetitive inspection(s) they are required to do, this AD provides the repetitive inspections (as restated from the NPRM (80 FR 25630, May 5, 2015)), depending on the applicable condition, in separate repetitive inspection paragraphs (paragraphs (i)(1) and (i)(2) of this AD). We have not changed this AD in this regard. Request To Revise External Inspection Wording Boeing requested that we remove the word ``external'' from paragraph (h) of the proposed AD (80 FR 25630, May 5, 2015), which specified ``external detailed, low frequency eddy current, and high frequency eddy current inspections.'' Boeing explained that if paragraphs (h) and (i) of the proposed AD are combined, both external and internal detailed inspections are required. Boeing stated that removing ``external'' from the inspection direction would therefore cover all airplane conditions. As stated previously, we do not agree to combine paragraphs (h) and (i) of this AD into one paragraph. Therefore, the terminology in paragraph (h) of this AD matches Boeing Alert Service Bulletin 747- 53A2367, Revision 5, dated July 8, 2014, which specifies doing external detailed, low frequency eddy current (LFEC), and high frequency eddy current (HFEC) inspections for cracks. We have not changed this AD in this regard. Request To Revise Headings of Paragraphs (h), (i), and (j) of the Proposed AD (80 FR 25630, May 5, 2015) Boeing requested that we revise the headings of paragraphs (h), (i), and (j) of the proposed AD (80 FR 25630, May 5, 2015) by adding a reference to the applicable service information. Boeing stated that these changes will add consistency among paragraphs (h), (i), and (j) of the proposed AD in identifying an installed external doubler modification. We agree with the commenter's request. We have revised the headings of paragraphs (h), (i), and (j) of this AD accordingly. Request To Correct Typographical Error Boeing noted that a phrase describing the major action in paragraph (j) of the proposed AD (80 FR 25630, May 5, 2015) was duplicated and asked that we correct this. We agree with the commenter's request. We have revised paragraph (j) of this AD accordingly. 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:[Agr]re consistent with the intent that was proposed in the NPRM (80 FR 25630, May 5, 2015) for correcting the unsafe condition; and Do not add any additional burden upon the public than was already proposed in the NPRM (80 FR 25630, May 5, 2015). We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. Related Service Information Under 1 CFR Part 51 We reviewed Boeing Alert Service Bulletin 747-53A2367, Revision 5, dated July 8, 2014. This service information describes procedures for inspections and repair for cracks in the skin and doublers along the edge fastener rows of modifications in the fuselage. 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. [[Page 72575]] Costs of Compliance We estimate that this AD affects 50 airplanes of U.S. registry. We estimate the following costs to comply with this AD: Estimated Costs ---------------------------------------------------------------------------------------------------------------- Cost on U.S. Action Labor cost Parts cost Cost per product operators ---------------------------------------------------------------------------------------------------------------- Post-modification inspection... 124 work-hours x $85 $0 $10,540 per $527,000 per per hour = $10,540 per inspection cycle. inspection inspection cycle. cycle. ---------------------------------------------------------------------------------------------------------------- We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in this AD. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. Subtitle VII: Aviation Programs, describes in more detail the scope of the Agency's authority. We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701: ``General requirements.'' Under that section, Congress charges the FAA with 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): 2015-23-11 The Boeing Company: Amendment 39-18327; Docket No. FAA- 2015-1266; Directorate Identifier 2014-NM-151-AD. (a) Effective Date This AD is effective December 28, 2015. (b) Affected ADs None. (c) Applicability This AD applies to The Boeing Company Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-300, 747SR, and 747SP series airplanes, certificated in any category, as identified in Boeing Alert Service Bulletin 747-53A2367, Revision 5, dated July 8, 2014. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Unsafe Condition This AD was prompted by an evaluation by the design approval holder indicating that certain fuselage skin lap joints are subject to widespread fatigue damage. We are issuing this AD to detect and correct fatigue cracking in certain fuselage skin lap joints, which could result in rapid depressurization of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Repetitive Post-Modification Inspections for Airplane Groups 1 Through 3, 7, and 8 For airplanes identified as Groups 1 through 3, 7, and 8 in Boeing Alert Service Bulletin 747-53A2367, Revision 5, dated July 8, 2014: Except as provided by paragraph (m) of this AD, at the applicable time specified in table 3 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2367, Revision 5, dated July 8, 2014, do internal detailed and surface high frequency eddy current (HFEC) inspections for cracks in the skin and internal doubler along the edge fastener rows of the modification, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747-53A2367, Revision 5, dated July 8, 2014. In unrepaired areas, repeat the internal detailed and surface HFEC inspections for cracks in the skin or internal doubler along the edge fastener rows of the modification thereafter at the applicable intervals specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2367, Revision 5, dated July 8, 2014. (h) Initial Post-Modification Inspections for Airplane Groups 4 Through 6, and 9 Through 11, With External Doublers Installed as Specified in Boeing Service Bulletin 747-53-2272 For airplanes identified as Groups 4 through 6, and 9 through 11, in Boeing Alert Service Bulletin 747-53A2367, Revision 5, dated July 8, 2014, with external doublers installed as specified in Boeing Service Bulletin 747-53-2272: Except as provided by paragraph (m) of this AD, at the applicable time specified in table 4 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2367, Revision 5, dated July 8, 2014, do external detailed, low frequency eddy current (LFEC), and HFEC inspections for cracks in the skin and external doubler, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747- 53A2367, Revision 5, dated July 8, 2014. (i) Repetitive Post-Modification Inspections for Airplane Groups 4 Through 6, and 9 Through 11 With External Doublers Installed as Specified in Boeing Service Bulletin 747-53-2272 For airplanes with no crack findings during the inspections required by paragraph (h) of this AD: Do the applicable actions required by paragraphs (i)(1) and (i)(2) of this AD. (1) For airplanes with less than 15,000 flight cycles since stringer 6 external doublers were installed, as specified in Boeing Service Bulletin 747-53-2272: At the applicable intervals specified in table 4 of [[Page 72576]] paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2367, Revision 5, dated July 8, 2014, in unrepaired areas, repeat the external detailed and LFEC inspections for cracks in the skin, and the external detailed and HFEC inspections for cracks in the external doubler, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747-53A2367, Revision 5, dated July 8, 2014. (2) For airplanes with 15,000 or more flight cycles since the stringer 6 external doublers were installed, as specified in Boeing Service Bulletin 747-53-2272: At the applicable intervals specified in table 4 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2367, Revision 5, dated July 8, 2014, in unrepaired areas, do external detailed and LFEC inspections for cracks in the skin; and do internal and external detailed and HFEC inspections for cracks in the skin and external doubler; in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747-53A2367, Revision 5, dated July 8, 2014. (j) Repetitive Post-Modification Inspections for Airplane Groups 4 Through 6, and 9 Through 11 With External Doublers Installed as Specified in Boeing Alert Service Bulletin 747-53A2367 For airplanes identified as Groups 4 through 6, and 9 through 11, in Boeing Alert Service Bulletin 747-53A2367, Revision 5, dated July 8, 2014, with external doublers installed as specified in Boeing Alert Service Bulletin 747-53A2367: Except as provided by paragraph (m) of this AD, at the applicable time specified in table 5 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2367, Revision 5, dated July 8, 2014, do internal detailed and surface HFEC inspections for cracks in the skin and internal doubler along the edge fastener rows of the modification, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747-53A2367, Revision 5, dated July 8, 2014. In unrepaired areas, repeat the internal detailed and surface HFEC inspections for cracks in the skin or internal doubler along the edge fastener rows of the modification thereafter at the applicable interval specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2367, Revision 5, dated July 8, 2014. (k) Repetitive Post-Modification Inspections for Airplane Groups 12 and 13 For airplanes identified as Groups 12 and 13 in Boeing Alert Service Bulletin 747-53A2367, Revision 5, dated July 8, 2014: Except as provided by paragraph (m) of this AD, at the applicable time specified in table 6 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2367, Revision 5, dated July 8, 2014, do internal detailed and surface HFEC inspections for cracks in the skin and internal doubler along the edge fastener rows of the modification, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747-53A2367, Revision 5, dated July 8, 2014. In unrepaired areas, repeat the internal detailed and surface HFEC inspections for cracks in the skin or internal doubler along the edge fastener rows of the modification thereafter at the applicable interval specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2367, Revision 5, dated July 8, 2014. (l) Corrective Actions If any cracking is found during any inspection required by this AD: Before further flight, repair the cracking using a method approved in accordance with the procedures specified in paragraph (n) of this AD. (m) Exception to Boeing Alert Service Bulletin 747-53A2367, Revision 5, Dated July 8, 2014 Where paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2367, Revision 5, dated July 8, 2014, specifies a compliance time ``after the Revision 5 date of this service bulletin,'' this AD requires compliance within the specified compliance time ``after the effective date of this AD.'' (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: [email protected]. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. (3) An AMOC that provides an acceptable level of safety may be used for any repair, modification, or alteration required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle ACO, to make those findings. To be approved, the repair method, modification deviation, or alteration deviation must meet the certification basis of the airplane and the approval must specifically refer to this AD. (o) Related Information For more information about this AD, contact Nathan Weigand, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6428; fax: 425-917-6590; email: [email protected]. (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 Alert Service Bulletin 747-53A2367, Revision 5, dated July 8, 2014. (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 4, 2015. Dionne Palermo, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015-28891 Filed 11-19-15; 8:45 am] BILLING CODE 4910-13-P
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(2) You must use this service information could result in rapid depressurization of skin lap joints are subject to WFD. The
as applicable to do the actions required by the airplane. NPRM proposed to require repetitive
this AD, unless this AD specifies otherwise. post-modification inspections for
DATES: This AD is effective December
(i) Airbus Service Bulletin A330–53–3206, cracking of the skin or internal doubler
Revision 03, dated February 28, 2014. 28, 2015.
(ii) Airbus Service Bulletin A340–53–4208, The Director of the Federal Register along the edge fastener rows of the
Revision 03, dated February 28, 2014. approved the incorporation by reference modification, and repair if necessary.
(3) For service information identified in of a certain publication listed in this AD We are issuing this AD to detect and
this AD, contact Airbus SAS, Airworthiness as of December 28, 2015. correct fatigue cracking in certain
Office—EAL, 1 Rond Point Maurice Bellonte, ADDRESSES: For service information fuselage skin lap joints, which could
31707 Blagnac Cedex, France; telephone +33 identified in this AD, contact Boeing result in rapid depressurization of the
5 61 93 36 96; fax +33 5 61 93 45 80; email airplane.
Commercial Airplanes, Attention: Data
airworthiness.A330-A340@airbus.com;
Internet http://www.airbus.com. & Services Management, P. O. Box 3707, Comments
(4) You may view this service information MC 2H–65, Seattle, WA 98124–2207;
telephone 206–544–5000, extension 1; We gave the public the opportunity to
at the FAA, Transport Airplane Directorate,
fax 206–766–5680; Internet https:// participate in developing this AD. The
1601 Lind Avenue SW., Renton, WA. For
information on the availability of this www.myboeingfleet.com. You may view following presents the comments
material at the FAA, call 425–227–1221. this referenced service information at received on the NPRM (80 FR 25630,
(5) You may view this service information the FAA, Transport Airplane May 5, 2015) and the FAA’s response to
that is incorporated by reference at the Directorate, 1601 Lind Avenue SW., each comment.
National Archives and Records
Renton, WA. For information on the Request To Remove Warranty
Administration (NARA). For information on
the availability of this material at NARA, call availability of this material at the FAA, Statement
202–741–6030, or go to: http:// call 425–227–1221. It is also available Boeing requested that we remove the
www.archives.gov/federal-register/cfr/ibr- on the Internet at http:// statement that ‘‘some of the costs of this
locations.html. www.regulations.gov by searching for proposed AD may be covered under
Issued in Renton, Washington, on October and locating Docket No. FAA–2015– warranty’’ in the Costs of Compliance
30, 2015. 1266. section of the NPRM (80 FR 25630, May
Michael Kaszycki, Examining the AD Docket 5, 2015). Boeing stated that the actions
Acting Manager, Transport Airplane You may examine the AD docket on in the NPRM are not covered by
Directorate, Aircraft Certification Service.
the Internet at http:// warranty.
[FR Doc. 2015–28895 Filed 11–19–15; 8:45 am] We agree with the commenter’s
www.regulations.gov by searching for
BILLING CODE 4910–13–P request. We have revised the Costs of
and locating Docket No. FAA–2015–
Compliance section of this final rule
1266; or in person at the Docket
accordingly.
Management Facility between 9 a.m.
DEPARTMENT OF TRANSPORTATION and 5 p.m., Monday through Friday, Request To Revise Paragraph Headings
Federal Aviation Administration except Federal holidays. The AD docket Boeing requested that we revise the
contains this AD, the regulatory headings of paragraphs (g), (h), (j), and
14 CFR Part 39 evaluation, any comments received, and (k) of the proposed AD (80 FR 25630,
other information. The address for the May 5, 2015) by removing reference to
[Docket No. FAA–2015–1266; Directorate Docket Office (phone: 800–647–5527) is the inspections as ‘‘repetitive’’ or
Identifier 2014–NM–151–AD; Amendment Docket Management Facility, U.S. ‘‘initial.’’ Boeing stated that these
39–18327; AD 2015–23–11] Department of Transportation, Docket revisions will provide consistency
Operations, M–30, West Building among paragraph headings because
RIN 2120–AA64 Ground Floor, Room W12–140, 1200 paragraphs (g), (j), and (k) of the
New Jersey Avenue SE., Washington, proposed AD do not have an initial
Airworthiness Directives; The Boeing DC 20590.
Company Airplanes inspection program, yet paragraph (h) of
FOR FURTHER INFORMATION CONTACT: the proposed AD has only an initial
AGENCY: Federal Aviation Nathan Weigand, Aerospace Engineer, inspection.
Administration (FAA), DOT. Airframe Branch, ANM–120S, FAA, We acknowledge the commenter’s
ACTION: Final rule. Seattle Aircraft Certification Office, concern and agree to clarify the
1601 Lind Avenue SW., Renton, WA headings. We do not presume that the
SUMMARY: We are adopting a new 98057–3356; phone: 425–917–6428; fax: term ‘‘repetitive’’ necessarily excludes
airworthiness directive (AD) for certain 425–917–6590; email: the initial action. An action cannot be
The Boeing Company Model 747–100, nathan.p.weigand@faa.gov. repeated without accomplishment of the
747–100B, 747–100B SUD, 747–200B, SUPPLEMENTARY INFORMATION: initial action. In addition, in many ADs
747–300, 747SR, and 747SP series we use the term ‘‘repetitive’’ actions for
airplanes. This AD was prompted by an Discussion
paragraphs that include the initial
evaluation by the design approval We issued a notice of proposed action and repetitive actions. Paragraphs
holder (DAH) indicating that certain rulemaking (NPRM) to amend 14 CFR (g), (j), and (k) of this AD include both
fuselage skin lap joints are subject to part 39 by adding an AD that would a sentence specifying the initial
widespread fatigue damage (WFD). This apply to certain The Boeing Company inspection and a sentence specifying the
AD requires repetitive post-modification Model 747–100, 747–100B, 747–100B repetitive inspections. We have not
tkelley on DSK3SPTVN1PROD with RULES
inspections for cracking of the skin or SUD, 747–200B, 747–300, 747SR, and changed this AD in this regard.
internal doubler along the edge fastener 747SP series airplanes. The NPRM
rows of the modification, and repair if published in the Federal Register on Request To Clarify Compliance Time
necessary. We are issuing this AD to May 5, 2015 (80 FR 25630). The NPRM Boeing requested that we clarify the
detect and correct fatigue cracking in was prompted by an evaluation by the compliance time in paragraphs (g), (h),
certain fuselage skin lap joints, which DAH indicating that certain fuselage (j), and (k) of the proposed AD (80 FR
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Costs of Compliance We estimate the following costs to
We estimate that this AD affects 50 comply with this AD:
airplanes of U.S. registry.
ESTIMATED COSTS
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
Post-modification inspection ........ 124 work-hours × $85 per hour = $10,540 $0 $10,540 per inspec- $527,000 per inspec-
per inspection cycle. tion cycle. tion cycle.
We have received no definitive data List of Subjects in 14 CFR Part 39 (g) Repetitive Post-Modification Inspections
that would enable us to provide cost for Airplane Groups 1 Through 3, 7, and 8
Air transportation, Aircraft, Aviation
estimates for the on-condition actions safety, Incorporation by reference, For airplanes identified as Groups 1
specified in this AD. through 3, 7, and 8 in Boeing Alert Service
Safety. Bulletin 747–53A2367, Revision 5, dated July
Authority for This Rulemaking Adoption of the Amendment 8, 2014: Except as provided by paragraph (m)
of this AD, at the applicable time specified
Title 49 of the United States Code Accordingly, under the authority in table 3 of paragraph 1.E., ‘‘Compliance,’’
specifies the FAA’s authority to issue delegated to me by the Administrator, of Boeing Alert Service Bulletin 747–
rules on aviation safety. Subtitle I, the FAA amends 14 CFR part 39 as 53A2367, Revision 5, dated July 8, 2014, do
section 106, describes the authority of follows: internal detailed and surface high frequency
the FAA Administrator. Subtitle VII: eddy current (HFEC) inspections for cracks in
Aviation Programs, describes in more PART 39—AIRWORTHINESS the skin and internal doubler along the edge
detail the scope of the Agency’s DIRECTIVES fastener rows of the modification, in
accordance with the Accomplishment
authority. Instructions of Boeing Alert Service Bulletin
We are issuing this rulemaking under ■ 1. The authority citation for part 39
747–53A2367, Revision 5, dated July 8, 2014.
the authority described in Subtitle VII, continues to read as follows: In unrepaired areas, repeat the internal
Part A, Subpart III, Section 44701: Authority: 49 U.S.C. 106(g), 40113, 44701. detailed and surface HFEC inspections for
‘‘General requirements.’’ Under that cracks in the skin or internal doubler along
§ 39.13 [Amended] the edge fastener rows of the modification
section, Congress charges the FAA with
thereafter at the applicable intervals specified
promoting safe flight of civil aircraft in ■ 2. The FAA amends § 39.13 by adding
in paragraph 1.E., ‘‘Compliance,’’ of Boeing
air commerce by prescribing regulations the following new airworthiness Alert Service Bulletin 747–53A2367,
for practices, methods, and procedures directive (AD): Revision 5, dated July 8, 2014.
the Administrator finds necessary for 2015–23–11 The Boeing Company:
safety in air commerce. This regulation (h) Initial Post-Modification Inspections for
Amendment 39–18327; Docket No. Airplane Groups 4 Through 6, and 9
is within the scope of that authority FAA–2015–1266; Directorate Identifier Through 11, With External Doublers
because it addresses an unsafe condition 2014–NM–151–AD. Installed as Specified in Boeing Service
that is likely to exist or develop on (a) Effective Date Bulletin 747–53–2272
products identified in this rulemaking For airplanes identified as Groups 4
This AD is effective December 28, 2015.
action. through 6, and 9 through 11, in Boeing Alert
(b) Affected ADs Service Bulletin 747–53A2367, Revision 5,
Regulatory Findings
None. dated July 8, 2014, with external doublers
This AD will not have federalism installed as specified in Boeing Service
(c) Applicability Bulletin 747–53–2272: Except as provided by
implications under Executive Order
13132. This AD will not have a This AD applies to The Boeing Company paragraph (m) of this AD, at the applicable
Model 747–100, 747–100B, 747–100B SUD, time specified in table 4 of paragraph 1.E.,
substantial direct effect on the States, on ‘‘Compliance,’’ of Boeing Alert Service
747–200B, 747–300, 747SR, and 747SP series
the relationship between the national airplanes, certificated in any category, as Bulletin 747–53A2367, Revision 5, dated July
government and the States, or on the identified in Boeing Alert Service Bulletin 8, 2014, do external detailed, low frequency
distribution of power and 747–53A2367, Revision 5, dated July 8, 2014. eddy current (LFEC), and HFEC inspections
responsibilities among the various for cracks in the skin and external doubler,
(d) Subject in accordance with the Accomplishment
levels of government.
Air Transport Association (ATA) of Instructions of Boeing Alert Service Bulletin
For the reasons discussed above, I
America Code 53, Fuselage. 747–53A2367, Revision 5, dated July 8, 2014.
certify that this AD:
(1) Is not a ‘‘significant regulatory (e) Unsafe Condition (i) Repetitive Post-Modification Inspections
This AD was prompted by an evaluation by for Airplane Groups 4 Through 6, and 9
action’’ under Executive Order 12866,
the design approval holder indicating that Through 11 With External Doublers Installed
(2) Is not a ‘‘significant rule’’ under as Specified in Boeing Service Bulletin 747–
certain fuselage skin lap joints are subject to
DOT Regulatory Policies and Procedures widespread fatigue damage. We are issuing 53–2272
(44 FR 11034, February 26, 1979), this AD to detect and correct fatigue cracking For airplanes with no crack findings during
(3) Will not affect intrastate aviation in certain fuselage skin lap joints, which the inspections required by paragraph (h) of
tkelley on DSK3SPTVN1PROD with RULES
in Alaska, and could result in rapid depressurization of the this AD: Do the applicable actions required
airplane. by paragraphs (i)(1) and (i)(2) of this AD.
(4) Will not have a significant (1) For airplanes with less than 15,000
economic impact, positive or negative, (f) Compliance flight cycles since stringer 6 external
on a substantial number of small entities Comply with this AD within the doublers were installed, as specified in
under the criteria of the Regulatory compliance times specified, unless already Boeing Service Bulletin 747–53–2272: At the
Flexibility Act. done. applicable intervals specified in table 4 of
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![72576 Federal Register / Vol. 80, No. 224 / Friday, November 20, 2015 / Rules and Regulations
paragraph 1.E., ‘‘Compliance,’’ of Boeing the edge fastener rows of the modification (i) Boeing Alert Service Bulletin 747–
Alert Service Bulletin 747–53A2367, thereafter at the applicable interval specified 53A2367, Revision 5, dated July 8, 2014.
Revision 5, dated July 8, 2014, in unrepaired in paragraph 1.E., ‘‘Compliance,’’ of Boeing (ii) Reserved.
areas, repeat the external detailed and LFEC Alert Service Bulletin 747–53A2367, (3) For service information identified in
inspections for cracks in the skin, and the Revision 5, dated July 8, 2014. this AD, contact Boeing Commercial
external detailed and HFEC inspections for Airplanes, Attention: Data & Services
cracks in the external doubler, in accordance (l) Corrective Actions Management, P.O. Box 3707, MC 2H–65,
with the Accomplishment Instructions of If any cracking is found during any Seattle, WA 98124–2207; telephone 206–
Boeing Alert Service Bulletin 747–53A2367, inspection required by this AD: Before 544–5000, extension 1; fax 206–766–5680;
Revision 5, dated July 8, 2014. further flight, repair the cracking using a Internet https://www.myboeingfleet.com.
(2) For airplanes with 15,000 or more flight method approved in accordance with the (4) You may view this service information
cycles since the stringer 6 external doublers procedures specified in paragraph (n) of this at FAA, Transport Airplane Directorate, 1601
were installed, as specified in Boeing Service AD. Lind Avenue SW., Renton, WA. For
Bulletin 747–53–2272: At the applicable information on the availability of this
intervals specified in table 4 of paragraph (m) Exception to Boeing Alert Service material at the FAA, call 425–227–1221.
1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2367, Revision 5, Dated (5) You may view this service information
Bulletin 747–53A2367, Revision 5, dated July July 8, 2014 that is incorporated by reference at the
8, 2014, in unrepaired areas, do external Where paragraph 1.E., ‘‘Compliance,’’ of National Archives and Records
detailed and LFEC inspections for cracks in Boeing Alert Service Bulletin 747–53A2367, Administration (NARA). For information on
the skin; and do internal and external Revision 5, dated July 8, 2014, specifies a the availability of this material at NARA, call
detailed and HFEC inspections for cracks in compliance time ‘‘after the Revision 5 date of 202–741–6030, or go to: http://
the skin and external doubler; in accordance this service bulletin,’’ this AD requires www.archives.gov/federal-register/cfr/ibr-
with the Accomplishment Instructions of compliance within the specified compliance locations.html.
Boeing Alert Service Bulletin 747–53A2367, time ‘‘after the effective date of this AD.’’ Issued in Renton, Washington, on
Revision 5, dated July 8, 2014. November 4, 2015.
(n) Alternative Methods of Compliance
(j) Repetitive Post-Modification Inspections (AMOCs) Dionne Palermo,
for Airplane Groups 4 Through 6, and 9 (1) The Manager, Seattle Aircraft Acting Manager, Transport Airplane
Through 11 With External Doublers Installed Certification Office (ACO), FAA, has the Directorate, Aircraft Certification Service.
as Specified in Boeing Alert Service Bulletin authority to approve AMOCs for this AD, if [FR Doc. 2015–28891 Filed 11–19–15; 8:45 am]
747–53A2367 requested using the procedures found in 14 BILLING CODE 4910–13–P
For airplanes identified as Groups 4 CFR 39.19. In accordance with 14 CFR 39.19,
through 6, and 9 through 11, in Boeing Alert send your request to your principal inspector
Service Bulletin 747–53A2367, Revision 5, or local Flight Standards District Office, as DEPARTMENT OF TRANSPORTATION
dated July 8, 2014, with external doublers appropriate. If sending information directly
installed as specified in Boeing Alert Service to the manager of the ACO, send it to the Federal Aviation Administration
Bulletin 747–53A2367: Except as provided attention of the person identified in
by paragraph (m) of this AD, at the applicable paragraph (o) of this AD. Information may be 14 CFR Part 39
time specified in table 5 of paragraph 1.E., emailed to: 9-ANM-Seattle-ACO-AMOC-
‘‘Compliance,’’ of Boeing Alert Service Requests@faa.gov. [Docket No. FAA–2015–0927; Directorate
Bulletin 747–53A2367, Revision 5, dated July (2) Before using any approved AMOC, Identifier 2013–NM–172–AD; Amendment
8, 2014, do internal detailed and surface notify your appropriate principal inspector, 39–18325; AD 2015–23–09]
HFEC inspections for cracks in the skin and or lacking a principal inspector, the manager
internal doubler along the edge fastener rows RIN 2120–AA64
of the local flight standards district office/
of the modification, in accordance with the certificate holding district office.
Accomplishment Instructions of Boeing Alert Airworthiness Directives; Zodiac
(3) An AMOC that provides an acceptable
Service Bulletin 747–53A2367, Revision 5, level of safety may be used for any repair, Aerotechnics (Formerly Intertechnique
dated July 8, 2014. In unrepaired areas, modification, or alteration required by this Aircraft Systems)
repeat the internal detailed and surface HFEC AD if it is approved by the Boeing AGENCY: Federal Aviation
inspections for cracks in the skin or internal Commercial Airplanes Organization
doubler along the edge fastener rows of the Designation Authorization (ODA) that has
Administration (FAA), Department of
modification thereafter at the applicable been authorized by the Manager, Seattle Transportation (DOT).
interval specified in paragraph 1.E., ACO, to make those findings. To be ACTION: Final rule.
‘‘Compliance,’’ of Boeing Alert Service approved, the repair method, modification
Bulletin 747–53A2367, Revision 5, dated July deviation, or alteration deviation must meet SUMMARY: We are adopting a new
8, 2014. the certification basis of the airplane and the airworthiness directive (AD) for certain
approval must specifically refer to this AD. Zodiac Aerotechnics (formerly
(k) Repetitive Post-Modification Inspections
for Airplane Groups 12 and 13
Intertechnique Aircraft Systems)
(o) Related Information
flightcrew oxygen mask regulators as
For airplanes identified as Groups 12 and For more information about this AD, installed on, but not limited to, various
13 in Boeing Alert Service Bulletin 747– contact Nathan Weigand, Aerospace
53A2367, Revision 5, dated July 8, 2014:
transport and small airplanes. This AD
Engineer, Airframe Branch, ANM–120S,
Except as provided by paragraph (m) of this FAA, Seattle Aircraft Certification Office, was prompted by a report that improper
AD, at the applicable time specified in table 1601 Lind Avenue SW., Renton, WA 98057– maintenance on oxygen mask regulators
6 of paragraph 1.E., ‘‘Compliance,’’ of Boeing 3356; phone: 425–917–6428; fax: 425–917– was found. This AD requires the
Alert Service Bulletin 747–53A2367, 6590; email: nathan.p.weigand@faa.gov. identification and replacement of all
Revision 5, dated July 8, 2014, do internal potentially affected units. This AD also
detailed and surface HFEC inspections for (p) Material Incorporated by Reference
requires installation of a placard and
cracks in the skin and internal doubler along (1) The Director of the Federal Register revision of the airplane flight manual to
tkelley on DSK3SPTVN1PROD with RULES
the edge fastener rows of the modification, in approved the incorporation by reference
include an operational procedure for
accordance with the Accomplishment (IBR) of the service information listed in this
Instructions of Boeing Alert Service Bulletin paragraph under 5 U.S.C. 552(a) and 1 CFR use in case of depressurization. We are
747–53A2367, Revision 5, dated July 8, 2014. part 51. issuing this AD to detect and correct
In unrepaired areas, repeat the internal (2) You must use this service information affected oxygen mask regulators, which
detailed and surface HFEC inspections for as applicable to do the actions required by could lead to inadequate protection to
cracks in the skin or internal doubler along this AD, unless the AD specifies otherwise. the affected flightcrew against hypoxia.
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Document Created: 2015-12-14 13:58:29
Document Modified: 2015-12-14 13:58:29
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Rules and Regulations | |
| Action | Final rule. | |
| Dates | This AD is effective December 28, 2015. | |
| Contact | Nathan Weigand, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6428; fax: 425-917-6590; email: [email protected] | |
| FR Citation | 80 FR 72573 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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