82 FR 10258 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 82, Issue 27 (February 10, 2017)
Federal Aviation Administration
Federal Register Volume 82, Issue 27 (February 10, 2017)
| Page Range | 10258-10262 | |
| FR Document | 2017-01824 |
[Federal Register Volume 82, Number 27 (Friday, February 10, 2017)] [Rules and Regulations] [Pages 10258-10262] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2017-01824] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-6670; Directorate Identifier 2016-NM-006-AD; Amendment 39-18789; AD 2017-02-10] RIN 2120-AA64 Airworthiness Directives; The Boeing Company Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are superseding Airworthiness Directive (AD) 2013-19-04 for certain The Boeing Company Model 737-600, -700, -700C, -800, and -900 series airplanes. AD 2013-19-04 required repetitive inspections for cracking of the skin around the fasteners common to the ends of certain bulkhead chords, and related investigative actions and corrective actions if necessary; and [[Page 10259]] provided an optional terminating modification. This new AD reduces the inspection threshold and repetitive inspection intervals. This AD was prompted by a report of cracks found in the skin at fasteners of certain bulkhead chords. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective March 17, 2017. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of March 17, 2017. ADDRESSES: For service information identified in this final rule, contact Boeing Commercial Airplanes, Attention: Contractual & Data Services (C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740-5600; telephone 562-797-1717; 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-2016- 6670. 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-2016- 6670; 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: Alan Pohl, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6450; fax: 425-917-6590; email: [email protected]. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2013-19-04, Amendment 39-17586 (78 FR 59801, September 30, 2013) (``AD 2013-19-04''). AD 2013-19-04 applied to certain The Boeing Company Model 737-600, -700, -700C, -800, and -900 series airplanes. The NPRM published in the Federal Register on May 12, 2016 (81 FR 29505) (``the NPRM''). The NPRM was prompted by a report of cracks found in the skin at body station (STA) 540 just below stringer S-22L. The NPRM proposed to continue to require repetitive detailed and high frequency eddy current inspections for cracking of the skin around the eight fasteners common to the ends of the STA 540 bulkhead chords between stringers S-22 and S-23, left and right sides; related investigative actions and corrective actions, if necessary; and to provide an optional terminating modification. The NPRM also proposed to reduce the inspection threshold and repetitive inspection intervals. We are issuing this AD to detect and correct fatigue cracking in the fuselage skin around the eight fasteners securing the STA 540 bulkhead chords, which could result in rapid decompression of the cabin. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM and the FAA's response to each comment. Support for the NPRM Boeing and United Airlines had no objections to the NPRM. Effect of Winglets on Accomplishment of the Proposed Actions Aviation Partners Boeing stated that installation of winglets, as provided in Supplemental Type Certificate (STC) ST00830SE, does not affect the ability to accomplish the actions proposed in the NPRM. We concur with the commenter. We have redesignated paragraph (c) of the proposed AD as (c)(1) and added paragraph (c)(2) to this AD to state that installation of STC ST00830SE does not affect the ability to accomplish the actions required by this AD. Therefore, for airplanes on which STC ST00830SE is installed, a ``change in product'' alternative method of compliance (AMOC) approval request is not necessary to comply with the requirements of 14 CFR 39.17. Request To Clarify Access and Restoration Requirements All Nippon Airways requested that we clarify if the access and restoration instructions specified in the service information referenced in paragraph (k) of the proposed AD are required actions. We agree to clarify this issue. Access and restoration actions are not part of the actions required to correct the unsafe condition identified in this AD. Therefore, access and restoration actions were excluded from the required actions in AD 2013-19-04 and are excluded from the required actions in this AD. We have added the service information referenced in paragraph (k) of this AD to paragraph (i)(4) of this AD. Paragraph (i)(4) of this AD specifies that the access and restoration actions specified in the referenced service information are not required by this AD. Request To Clarify Corrective Action Southwest Airlines (SWA) requested that we clarify the corrective action for drilling the new drag link assembly. SWA stated that the service information only provides instructions for parts constructed of aluminum and that the drag link assembly is made from titanium. We agree that clarification is necessary. Boeing has informed us that revised service information is forthcoming. However, since the revised service information is not yet available, we do not consider that delaying this action until after the release of the manufacturer's revised service bulletin is warranted. When this service information becomes available, and upon satisfactory review, we plan to approve it as a global alternative method of compliance (AMOC) to the appropriate requirements of this AD. The issue raised by SWA affects only the on- condition repair instructions and not the required inspection to detect the identified unsafe condition. We have added paragraph (i)(5) to this AD to specify that repairs provided in Part 4 or Part 5 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 737-53-1294, Revision 2, dated December 9, 2015 (``SASB 737- 53-1294 R2''), must be done before further flight, using a method approved in accordance with the procedures specified in paragraph (l) of this AD. We have revised paragraphs (g) and (h) of this AD accordingly. Clarification of Exception to Repetitive Intervals For clarity, we have changed the format of paragraph (g) of this AD to make it clear the exceptions apply to the entire paragraph, including the repetitive inspection sentence specified in paragraph (g) of this AD. Clarification of Terminating Actions We have clarified paragraph (h) of this AD to specify that accomplishing the skin repair or preventive modification, [[Page 10260]] as specified in the applicable part of the Accomplishment Instructions of Boeing SASB 737-53-1294 R2, is terminating action for the side on which the skin repair or preventive modification is done. 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 for correcting the unsafe condition; and Do not add any additional burden upon the public than was already proposed in the NPRM. 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 SASB 737-53-1294 R2. The service information describes procedures for inspecting the skin around the eight fasteners common to the ends of the STA 540 bulkhead chords between stringers S-22 and S- 23, left and right sides, for cracking, repairing cracks, and installing a chord splice as a preventive modification. 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. Costs of Compliance We estimate that this AD affects 903 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 ---------------------------------------------------------------------------------------------------------------- Inspection (left and right 12 work-hours x $85 per $0 $1,020 per $921,060 per sides). hour = $1,020 per inspection cycle. inspection cycle. inspection cycle. ---------------------------------------------------------------------------------------------------------------- We estimate the following costs to do any necessary repairs and inspections that will be required based on the results of the inspection. We have no way of determining the number of aircraft that might need these repairs: On-Condition Costs ---------------------------------------------------------------------------------------------------------------- Action Labor cost Parts cost Cost per product ---------------------------------------------------------------------------------------------------------------- Preventive modification (each 7 work-hours x $85 per $894................ $1,489. side). hour = $595. Skin repair (each side).......... 39 work-hours x $85 per Up to $5,635........ Up to $8,950. hour = $3,315. ---------------------------------------------------------------------------------------------------------------- According to the manufacturer, some of the costs of this AD may be covered under warranty, thereby reducing the cost impact on affected individuals. We do not control warranty coverage for affected individuals. As a result, we have included all costs in our cost estimate. 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 We have determined that 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 removing Airworthiness Directive (AD) 2013-19-04, Amendment 39-17586 (78 FR 59801, September 30, 2013), and adding the following new AD: 2017-02-10 The Boeing Company: Amendment 39-18789; Docket No. FAA- 2016-6670; Directorate Identifier 2016-NM-006-AD. (a) Effective Date This AD is effective March 17, 2017. (b) Affected ADs This AD replaces AD 2013-19-04, Amendment 39-17586 (78 FR 59801, September 30, 2013) (``AD 2013-19-04''). [[Page 10261]] (c) Applicability (1) This AD applies to The Boeing Company Model 737-600, -700, - 700C, -800, and -900 series airplanes, certificated in any category, as identified in Boeing Special Attention Service Bulletin 737-53- 1294, Revision 2, dated December 9, 2015 (``SASB 737-53-1294 R2''). (2) Installation of Supplemental Type Certificate (STC) ST00830SE [http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/184DE9A71EC3FA5586257EAE00707DA6?OpenDocument&Highlight=st00830se] does not affect the ability to accomplish the actions required by this AD. Therefore, for airplanes on which STC ST00830SE is installed, a ``change in product'' alternative method of compliance (AMOC) approval request is not necessary to comply with the requirements of 14 CFR 39.17. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Unsafe Condition This AD was prompted by a report of cracks found in the skin at body station (STA) 540 just below the left side of stringer S-22. We are issuing this AD to detect and correct fatigue cracking in the fuselage skin around the eight fasteners securing the STA 540 bulkhead chords, which could result in rapid decompression of the cabin. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspection and Corrective Action Except as required by paragraphs (i)(1) and (i)(2) of this AD: At the applicable time specified in table 1 of paragraph 1.E., ``Compliance,'' of SASB 737-53-1294 R2, do detailed and high frequency eddy current (HFEC) inspections for cracking of the skin in the area around the eight fasteners securing the STA 540 bulkhead chords between stringers S-22 and S-23; and do all applicable related investigative and corrective actions; in accordance with Parts 1, 2, 3, 4, and 5 of the Accomplishment Instructions of SASB 737-53-1294 R2, except as required by paragraphs (i)(3), (i)(4), and (i)(5) of this AD. Do all applicable related investigative and corrective actions before further flight. Except as required by paragraph (i)(2) of this AD, repeat the detailed and HFEC inspections thereafter at the intervals specified in table 1 of paragraph 1.E., ``Compliance,'' of SASB 737-53-1294 R2, until the optional preventive modification specified in paragraph (h) of this AD is done. (h) Skin Repair or Optional Preventive Modification Accomplishing the skin repair or preventive modification, including an HFEC inspection for cracking of the skin and STA 540 bulkhead chords, and all applicable repairs, in accordance with paragraph 3.B, Part 2 or Part 4 (left side), or Part 3 or Part 5 (right side), as applicable, of the Accomplishment Instructions of SASB 737-53-1294 R2, except as required by paragraphs (i)(2) and (i)(5) of this AD, terminates the inspection requirements of paragraph (g) of this AD for the side on which the skin repair or preventive modification is done. (i) Exceptions to Service Bulletin Specifications (1) Where paragraph 1.E., ``Compliance,'' of SASB 737-53-1294 R2, specifies a compliance time ``after the Revision 2 date of this service bulletin,'' this AD requires compliance within the specified compliance time after the effective date of this AD. (2) For airplanes on which Boeing Business Jet Lower Cabin Altitude Supplemental Type Certificate (STC) ST01697SE (http:// rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/ 0812969a86af879b8625766400600105/$FILE/ST01697SE.pdf) (6,500 feet maximum cabin altitude in lieu of 8,000 feet) has been incorporated, the flight-cycle related compliance times for the inspection required by paragraph (g) of this AD are different from those specified in paragraph 1.E., ``Compliance,'' of SASB 737-53-1294 R2. All initial compliance times specified in total flight cycles or flight cycles must be reduced to half of those specified in SASB 737-53-1294 R2. All repetitive interval compliance times specified in flight cycles must be reduced to one-quarter of those specified in paragraph 1.E., ``Compliance,'' of SASB 737-53-1294 R2. (3) If any cracking is found during any inspection required by this AD, and SASB 737-53-1294 R2, specifies to contact Boeing for appropriate action: Before further flight, repair using a method approved in accordance with the procedures specified in paragraph (l) of this AD. (4) The access and restoration actions identified in the Accomplishment Instructions of Boeing Special Attention Service Bulletin 737-53-1294, dated March 31, 2011; Boeing Special Attention Service Bulletin 737-53-1294, Revision 1, dated June 14, 2013; or SASB 737-53-1294 R2; are not required by this AD. Operators may perform those actions in accordance with accepted maintenance procedures. (5) For doing repairs specified in Part 4 or Part 5 of the Accomplishment Instructions of SASB 737-53-1294 R2: Before further flight, repair using a method approved in accordance with the procedures specified in paragraph (l) of this AD. (j) Supplemental Inspections Not Required by This AD Table 2 of paragraph 1.E., ``Compliance,'' of SASB 737-53-1294 R2, specifies post-modification airworthiness limitation inspections in compliance with 14 CFR 25.571(a)(3) at the modified locations, which support compliance with 14 CFR 121.1109(c)(2) or 129.109(b)(2). As airworthiness limitations, these inspections are required by maintenance and operational rules. It is therefore unnecessary to mandate them in this AD. Deviations from these inspections require FAA approval, but do not require an AMOC. (k) Credit for Previous Actions This paragraph provides credit for the actions required by paragraphs (g) and (h) of this AD, if those actions were performed before the effective date of this AD using Boeing Special Attention Service Bulletin 737-53-1294, dated March 31, 2011, which is not incorporated by reference in this AD; or Boeing Special Attention Service Bulletin 737-53-1294, Revision 1, dated June 14, 2013, which was incorporated by reference in AD 2013-19-04. (l) 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 (m)(1) of this AD. Information may be emailed to: [email protected]. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. (3) An AMOC that provides an acceptable level of safety may be used for any repair, 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. (4) AMOCs approved previously for the optional preventive modification installed in accordance with paragraph (h) of AD 2013- 19-04, and AMOCs approved previously for repairs for AD 2013-19-04, are approved as AMOCs for the corresponding provisions of this AD, provided that such modification or repair included installation of the splice plate as specified in Boeing Special Attention Service Bulletin 737-53-1294, except as provided by paragraph (l)(5) of this AD. (5) The time-limited repair approved as specified in FAA Letter 120S-15-140, dated June 3, 2015, is approved as an AMOC to the corresponding requirements of this AD. (m) Related Information (1) For more information about this AD, contact Alan Pohl, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6450; fax: 425-917-6590; email: [email protected]. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (n)(3) and (n)(4) of this AD. (n) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference [[Page 10262]] (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 737-53-1294, Revision 2, dated December 9, 2015. (ii) Reserved. (3) For Boeing service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Contractual & Data Services (C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740-5600; telephone 562-797-1717; Internet https://www.myboeingfleet.com. (4) You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. (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 January 18, 2017. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017-01824 Filed 2-9-17; 8:45 am] BILLING CODE 4910-13-P
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the fasteners and on the surface of the flight hours divided by the total accumulated available at the addresses specified in
forward and aft lower surface panels, in flight cycles at the time of the inspection paragraphs (o)(3) and (o)(4) of this AD.
accordance with the Accomplishment threshold.
Instructions of Airbus Service Bulletin A300– (o) Material Incorporated by Reference
(3) For all inspection intervals onward, the
57–0204, Revision 01, dated April 2, 1999; or AFT is the flight hours accumulated between (1) The Director of the Federal Register
Airbus Service Bulletin A300–57–6047, the two most recent inspections divided by approved the incorporation by reference
Revision 06, dated October 17, 2011; as the flight cycles accumulated between the (IBR) of the service information listed in this
applicable. Repeat the fatigue inspections two most recent inspections. paragraph under 5 U.S.C. 552(a) and 1 CFR
thereafter at the applicable interval specified part 51.
in paragraph B.(5) of Airbus Service Bulletin (l) Credit for Previous Actions (2) You must use this service information
A300–57–0204, Revision 01, dated April 2, This paragraph provides credit for the as applicable to do the actions required by
1999; or Figure A–FBGAA, Sheet 01, of inspections and corrective actions required this AD, unless this AD specifies otherwise.
Airbus Service Bulletin A300–57–6047, by paragraphs (h) and (i) of this AD, if those (i) Airbus Service Bulletin A300–57–0204,
Revision 06, dated October 17, 2011; as actions were performed before the effective Revision 01, dated April 2, 1999.
applicable; except as required by paragraph date of this AD using the applicable service (ii) Airbus Service Bulletin A300–57–6047,
(j)(2) of this AD. If any cracking is found information specified in paragraphs (l)(1) Revision 06, dated October 17, 2011.
during any fatigue inspection required by through (l)(3) of this AD. (3) For service information identified in
this paragraph: Before further flight, repair (1) Airbus Service Bulletin A300–57–6047, this AD, contact Airbus SAS, Airworthiness
using a method approved by the Manager, Revision 02, dated April 2, 1999. Office—EAW, 1 Rond Point Maurice
International Branch, ANM–116, Transport (2) Airbus Service Bulletin A300–57–6047, Bellonte, 31707 Blagnac Cedex, France;
Airplane Directorate, FAA; or the European Revision 03, dated September 28, 1999. telephone +33 5 61 93 36 96; fax +33 5 61
Aviation Safety Agency (EASA); or Airbus’s (3) Airbus Service Bulletin A300–57–6047, 93 44 51; email account.airworth-eas@
EASA Design Organization Approval (DOA). Revision 05, dated May 27, 2008. airbus.com; Internet http://www.airbus.com.
(i) For Model A300 series airplanes: Do the (4) You may view this service information
initial inspection at the applicable time (m) Other FAA AD Provisions at the FAA, Transport Airplane Directorate,
specified in paragraph B.(5) of Airbus Service The following provisions also apply to this 1601 Lind Avenue SW., Renton, WA. For
Bulletin A300–57–0204, Revision 01, dated AD: information on the availability of this
April 2, 1999. (1) Alternative Methods of Compliance material at the FAA, call 425–227–1221.
(ii) For Model A300–600 series airplanes: (AMOCs): The Manager, International (5) You may view this service information
Do the initial inspection at the later of the Branch, ANM–116, Transport Airplane that is incorporated by reference at the
times specified in paragraphs (i)(2)(ii)(A) and Directorate, FAA, has the authority to National Archives and Records
(i)(2)(ii)(B) of this AD. approve AMOCs for this AD, if requested Administration (NARA). For information on
(A) At the applicable time specified in using the procedures found in 14 CFR 39.19. the availability of this material at NARA, call
Figure A–FBGAA, Sheet 01, of Airbus In accordance with 14 CFR 39.19, send your 202–741–6030, or go to: http://
Service Bulletin A300–57–6047, Revision 06, request to your principal inspector or local www.archives.gov/federal-register/cfr/ibr-
dated October 17, 2011.
Flight Standards District Office, as locations.html.
(B) Within 500 flight cycles or 1,050 flight
appropriate. If sending information directly
hours after the effective date of this AD, Issued in Renton, Washington, on January
to the International Branch, send it to ATTN:
whichever occurs first, without exceeding the 18, 2017.
Dan Rodina, Aerospace Engineer,
compliance time specified in Airbus Service Michael Kaszycki,
International Branch, ANM–116, Transport
Bulletin A300–57–6047, Revision 05, dated Acting Manager, Transport Airplane
Airplane Directorate, FAA, 1601 Lind
May 27, 2008. Directorate, Aircraft Certification Service.
Avenue SW., Renton, WA 98057–3356;
(j) Exceptions to Service Bulletin telephone (425) 227–2125; fax (425) 227– [FR Doc. 2017–01776 Filed 2–9–17; 8:45 am]
Specifications 1149. Information may be emailed to: 9- BILLING CODE 4910–13–P
(1) Where Airbus Service Bulletin A300– ANM-116-AMOC-REQUESTS@faa.gov.
57–0204, Revision 01, dated April 2, 1999; or (i) Before using any approved AMOC,
Airbus Service Bulletin A300–57–6047, notify your appropriate principal inspector,
or lacking a principal inspector, the manager
DEPARTMENT OF TRANSPORTATION
Revision 06, dated October 17, 2011;
specifies to contact Airbus for appropriate of the local flight standards district office/
certificate holding district office. The AMOC
Federal Aviation Administration
corrective action, this AD requires repair
before further flight using a method approved approval letter must specifically reference
this AD. 14 CFR Part 39
by the Manager, International Branch, ANM–
116, Transport Airplane Directorate, FAA; or (ii) AMOCs approved previously for AD [Docket No. FAA–2016–6670; Directorate
EASA; or Airbus’s EASA DOA. 98–21–34 are approved as AMOCs for the Identifier 2016–NM–006–AD; Amendment
(2) Where Airbus Service Bulletin A300– corresponding provisions of paragraphs (h) 39–18789; AD 2017–02–10]
57–6047, Revision 06, dated October 17, and (i) of this AD.
2011, specifies to contact Airbus for the (2) Contacting the Manufacturer: For any RIN 2120–AA64
appropriate threshold or repetitive interval, requirement in this AD to obtain corrective
this AD requires that the compliance time be actions from a manufacturer, the action must Airworthiness Directives; The Boeing
determined using a method approved by the be accomplished using a method approved Company Airplanes
Manager, International Branch, ANM–116, by the Manager, International Branch, ANM–
Transport Airplane Directorate, FAA; or 116, Transport Airplane Directorate, FAA; or AGENCY: Federal Aviation
EASA; or Airbus’s EASA DOA. the EASA; or Airbus’s EASA DOA. If Administration (FAA), DOT.
approved by the DOA, the approval must ACTION: Final rule.
(k) Calculating Average Flight Time (AFT) include the DOA-authorized signature.
For the purposes of paragraph (i)(2) of this SUMMARY: We are superseding
(n) Related Information
AD, the AFT must be established as specified Airworthiness Directive (AD) 2013–19–
in paragraphs (k)(1), (k)(2), and (k)(3) of this (1) Refer to Mandatory Continuing 04 for certain The Boeing Company
AD. Airworthiness Information (MCAI) EASA AD Model 737–600, –700, –700C, –800, and
rmajette on DSK2TPTVN1PROD with RULES
(1) For the initial inspection, the AFT is 2013–0230, dated September 24, 2013, for
–900 series airplanes. AD 2013–19–04
the total accumulated flight hours, counted related information. This MCAI may be
from take-off to touch-down, divided by the found in the AD docket on the Internet at required repetitive inspections for
total accumulated flight cycles at the http://www.regulations.gov by searching for cracking of the skin around the fasteners
effective date of this AD. and locating Docket No. FAA–2016–5040. common to the ends of certain bulkhead
(2) For the first repeated inspection (2) Service information identified in this chords, and related investigative actions
interval, the AFT is the total accumulated AD that is not incorporated by reference is and corrective actions if necessary; and
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as specified in the applicable part of the • Are consistent with the intent that the ends of the STA 540 bulkhead
Accomplishment Instructions of Boeing was proposed in the NPRM for chords between stringers S–22 and S–
SASB 737–53–1294 R2, is terminating correcting the unsafe condition; and 23, left and right sides, for cracking,
action for the side on which the skin • Do not add any additional burden repairing cracks, and installing a chord
repair or preventive modification is upon the public than was already splice as a preventive modification. This
done. proposed in the NPRM. service information is reasonably
We also determined that these available because the interested parties
Conclusion changes will not increase the economic have access to it through their normal
burden on any operator or increase the course of business or by the means
We reviewed the relevant data, scope of this AD. identified in the ADDRESSES section.
considered the comments received, and
determined that air safety and the Related Service Information Under 1 Costs of Compliance
public interest require adopting this AD CFR Part 51
with the changes described previously, We reviewed SASB 737–53–1294 R2. We estimate that this AD affects 903
The service information describes airplanes of U.S. registry.
and minor editorial changes. We have
determined that these minor changes: procedures for inspecting the skin We estimate the following costs to
around the eight fasteners common to comply with this AD:
ESTIMATED COSTS
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
Inspection (left and right 12 work-hours × $85 per hour = $1,020 per in- $0 $1,020 per inspection $921,060 per inspection
sides). spection cycle. cycle. cycle.
We estimate the following costs to do that will be required based on the way of determining the number of
any necessary repairs and inspections results of the inspection. We have no aircraft that might need these repairs:
ON-CONDITION COSTS
Action Labor cost Parts cost Cost per product
Preventive modification (each side) .................... 7 work-hours × $85 per hour = $595 ............... $894 ............................ $1,489.
Skin repair (each side) ........................................ 39 work-hours × $85 per hour = $3,315 .......... Up to $5,635 ............... Up to $8,950.
According to the manufacturer, some products identified in this rulemaking Adoption of the Amendment
of the costs of this AD may be covered action.
under warranty, thereby reducing the Accordingly, under the authority
Regulatory Findings delegated to me by the Administrator,
cost impact on affected individuals. We
do not control warranty coverage for We have determined that this AD will the FAA amends 14 CFR part 39 as
affected individuals. As a result, we not have federalism implications under follows:
have included all costs in our cost Executive Order 13132. This AD will
not have a substantial direct effect on PART 39—AIRWORTHINESS
estimate.
the States, on the relationship between DIRECTIVES
Authority for This Rulemaking the national government and the States,
or on the distribution of power and ■ 1. The authority citation for part 39
Title 49 of the United States Code continues to read as follows:
specifies the FAA’s authority to issue responsibilities among the various
rules on aviation safety. Subtitle I, levels of government. Authority: 49 U.S.C. 106(g), 40113, 44701.
Section 106, describes the authority of For the reasons discussed above, I
certify that this AD: § 39.13 [Amended]
the FAA Administrator. Subtitle VII,
(1) Is not a ‘‘significant regulatory
Aviation Programs, describes in more ■ 2. The FAA amends § 39.13 by
action’’ under Executive Order 12866,
detail the scope of the Agency’s removing Airworthiness Directive (AD)
(2) Is not a ‘‘significant rule’’ under
authority. 2013–19–04, Amendment 39–17586 (78
DOT Regulatory Policies and Procedures
We are issuing this rulemaking under (44 FR 11034, February 26, 1979), FR 59801, September 30, 2013), and
the authority described in Subtitle VII, (3) Will not affect intrastate aviation adding the following new AD:
Part A, Subpart III, Section 44701, in Alaska, and 2017–02–10 The Boeing Company:
‘‘General requirements.’’ Under that (4) Will not have a significant Amendment 39–18789; Docket No.
section, Congress charges the FAA with economic impact, positive or negative, FAA–2016–6670; Directorate Identifier
promoting safe flight of civil aircraft in on a substantial number of small entities 2016–NM–006–AD.
air commerce by prescribing regulations
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under the criteria of the Regulatory (a) Effective Date
for practices, methods, and procedures Flexibility Act. This AD is effective March 17, 2017.
the Administrator finds necessary for
safety in air commerce. This regulation List of Subjects in 14 CFR Part 39 (b) Affected ADs
is within the scope of that authority Air transportation, Aircraft, Aviation This AD replaces AD 2013–19–04,
because it addresses an unsafe condition safety, Incorporation by reference, Amendment 39–17586 (78 FR 59801,
that is likely to exist or develop on Safety. September 30, 2013) (‘‘AD 2013–19–04’’).
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![Federal Register / Vol. 82, No. 27 / Friday, February 10, 2017 / Rules and Regulations 10261
(c) Applicability Accomplishment Instructions of SASB 737– (k) Credit for Previous Actions
(1) This AD applies to The Boeing 53–1294 R2, except as required by This paragraph provides credit for the
Company Model 737–600, –700, –700C, paragraphs (i)(2) and (i)(5) of this AD, actions required by paragraphs (g) and (h) of
–800, and –900 series airplanes, certificated terminates the inspection requirements of this AD, if those actions were performed
in any category, as identified in Boeing paragraph (g) of this AD for the side on before the effective date of this AD using
Special Attention Service Bulletin 737–53– which the skin repair or preventive Boeing Special Attention Service Bulletin
1294, Revision 2, dated December 9, 2015 modification is done. 737–53–1294, dated March 31, 2011, which
(‘‘SASB 737–53–1294 R2’’). is not incorporated by reference in this AD;
(i) Exceptions to Service Bulletin or Boeing Special Attention Service Bulletin
(2) Installation of Supplemental Type Specifications
Certificate (STC) ST00830SE [http:// 737–53–1294, Revision 1, dated June 14,
rgl.faa.gov/Regulatory_and_Guidance_ (1) Where paragraph 1.E., ‘‘Compliance,’’ of 2013, which was incorporated by reference in
Library/rgstc.nsf/0/184DE9A71EC3FA SASB 737–53–1294 R2, specifies a AD 2013–19–04.
5586257EAE00707DA6?Open compliance time ‘‘after the Revision 2 date of
(l) Alternative Methods of Compliance
Document&Highlight=st00830se] does not this service bulletin,’’ this AD requires
(AMOCs)
affect the ability to accomplish the actions compliance within the specified compliance
required by this AD. Therefore, for airplanes time after the effective date of this AD. (1) The Manager, Seattle Aircraft
on which STC ST00830SE is installed, a (2) For airplanes on which Boeing Business Certification Office (ACO), FAA, has the
Jet Lower Cabin Altitude Supplemental Type authority to approve AMOCs for this AD, if
‘‘change in product’’ alternative method of
Certificate (STC) ST01697SE (http:// requested using the procedures found in 14
compliance (AMOC) approval request is not
rgl.faa.gov/Regulatory_and_Guidance_ CFR 39.19. In accordance with 14 CFR 39.19,
necessary to comply with the requirements of
send your request to your principal inspector
14 CFR 39.17. Library/rgstc.nsf/0/0812969a86af879b86257
or local Flight Standards District Office, as
66400600105/$FILE/ST01697SE.pdf) (6,500
(d) Subject appropriate. If sending information directly
feet maximum cabin altitude in lieu of 8,000 to the manager of the ACO, send it to the
Air Transport Association (ATA) of feet) has been incorporated, the flight-cycle attention of the person identified in
America Code 53, Fuselage. related compliance times for the inspection paragraph (m)(1) of this AD. Information may
(e) Unsafe Condition required by paragraph (g) of this AD are be emailed to: 9-ANM-Seattle-ACO-AMOC-
different from those specified in paragraph Requests@faa.gov.
This AD was prompted by a report of 1.E., ‘‘Compliance,’’ of SASB 737–53–1294 (2) Before using any approved AMOC,
cracks found in the skin at body station R2. All initial compliance times specified in notify your appropriate principal inspector,
(STA) 540 just below the left side of stringer total flight cycles or flight cycles must be or lacking a principal inspector, the manager
S–22. We are issuing this AD to detect and reduced to half of those specified in SASB of the local flight standards district office/
correct fatigue cracking in the fuselage skin 737–53–1294 R2. All repetitive interval certificate holding district office.
around the eight fasteners securing the STA compliance times specified in flight cycles (3) An AMOC that provides an acceptable
540 bulkhead chords, which could result in must be reduced to one-quarter of those level of safety may be used for any repair,
rapid decompression of the cabin. specified in paragraph 1.E., ‘‘Compliance,’’ of modification, or alteration required by this
(f) Compliance SASB 737–53–1294 R2. AD if it is approved by the Boeing
(3) If any cracking is found during any Commercial Airplanes Organization
Comply with this AD within the Designation Authorization (ODA) that has
inspection required by this AD, and SASB
compliance times specified, unless already been authorized by the Manager, Seattle
737–53–1294 R2, specifies to contact Boeing
done. ACO, to make those findings. To be
for appropriate action: Before further flight,
(g) Inspection and Corrective Action repair using a method approved in approved, the repair method, modification
accordance with the procedures specified in deviation, or alteration deviation must meet
Except as required by paragraphs (i)(1) and the certification basis of the airplane, and the
(i)(2) of this AD: At the applicable time paragraph (l) of this AD.
(4) The access and restoration actions approval must specifically refer to this AD.
specified in table 1 of paragraph 1.E., (4) AMOCs approved previously for the
‘‘Compliance,’’ of SASB 737–53–1294 R2, do identified in the Accomplishment
Instructions of Boeing Special Attention optional preventive modification installed in
detailed and high frequency eddy current accordance with paragraph (h) of AD 2013–
(HFEC) inspections for cracking of the skin Service Bulletin 737–53–1294, dated March
31, 2011; Boeing Special Attention Service 19–04, and AMOCs approved previously for
in the area around the eight fasteners repairs for AD 2013–19–04, are approved as
securing the STA 540 bulkhead chords Bulletin 737–53–1294, Revision 1, dated June
14, 2013; or SASB 737–53–1294 R2; are not AMOCs for the corresponding provisions of
between stringers S–22 and S–23; and do all this AD, provided that such modification or
applicable related investigative and required by this AD. Operators may perform
those actions in accordance with accepted repair included installation of the splice
corrective actions; in accordance with Parts plate as specified in Boeing Special Attention
1, 2, 3, 4, and 5 of the Accomplishment maintenance procedures.
Service Bulletin 737–53–1294, except as
Instructions of SASB 737–53–1294 R2, (5) For doing repairs specified in Part 4 or
provided by paragraph (l)(5) of this AD.
except as required by paragraphs (i)(3), (i)(4), Part 5 of the Accomplishment Instructions of
(5) The time-limited repair approved as
and (i)(5) of this AD. Do all applicable related SASB 737–53–1294 R2: Before further flight,
specified in FAA Letter 120S–15–140, dated
investigative and corrective actions before repair using a method approved in
June 3, 2015, is approved as an AMOC to the
further flight. Except as required by accordance with the procedures specified in corresponding requirements of this AD.
paragraph (i)(2) of this AD, repeat the paragraph (l) of this AD.
detailed and HFEC inspections thereafter at (m) Related Information
(j) Supplemental Inspections Not Required
the intervals specified in table 1 of paragraph by This AD (1) For more information about this AD,
1.E., ‘‘Compliance,’’ of SASB 737–53–1294 contact Alan Pohl, Aerospace Engineer,
R2, until the optional preventive Table 2 of paragraph 1.E., ‘‘Compliance,’’ Airframe Branch, ANM–120S, FAA, Seattle
modification specified in paragraph (h) of of SASB 737–53–1294 R2, specifies post- Aircraft Certification Office, 1601 Lind
this AD is done. modification airworthiness limitation Avenue SW., Renton, WA 98057–3356;
inspections in compliance with 14 CFR phone: 425–917–6450; fax: 425–917–6590;
(h) Skin Repair or Optional Preventive 25.571(a)(3) at the modified locations, which email: alan.pohl@faa.gov.
Modification support compliance with 14 CFR (2) Service information identified in this
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Accomplishing the skin repair or 121.1109(c)(2) or 129.109(b)(2). As AD that is not incorporated by reference is
preventive modification, including an HFEC airworthiness limitations, these inspections available at the addresses specified in
inspection for cracking of the skin and STA are required by maintenance and operational paragraphs (n)(3) and (n)(4) of this AD.
540 bulkhead chords, and all applicable rules. It is therefore unnecessary to mandate
repairs, in accordance with paragraph 3.B, them in this AD. Deviations from these (n) Material Incorporated by Reference
Part 2 or Part 4 (left side), or Part 3 or Part inspections require FAA approval, but do not (1) The Director of the Federal Register
5 (right side), as applicable, of the require an AMOC. approved the incorporation by reference
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![10262 Federal Register / Vol. 82, No. 27 / Friday, February 10, 2017 / Rules and Regulations
(IBR) of the service information listed in this inspections. We are issuing this AD to skin inner surface along the upper
paragraph under 5 U.S.C. 552(a) and 1 CFR address the unsafe condition on these bulkhead at certain stations between
part 51. products. certain stringers. The NPRM proposed
(2) You must use this service information to require repetitive inspections of the
as applicable to do the actions required by DATES: This AD is effective March 17,
this AD, unless the AD specifies otherwise. 2017. fuselage crown skin inner surface, and
(i) Boeing Special Attention Service The Director of the Federal Register related investigative and corrective
Bulletin 737–53–1294, Revision 2, dated approved the incorporation by reference actions if necessary. The NPRM would
December 9, 2015. of a certain publication listed in this AD also allow for terminating actions for the
(ii) Reserved. as of March 17, 2017. repetitive inspections. We are issuing
(3) For Boeing service information this AD to detect and correct cracks and
ADDRESSES: For service information
identified in this AD, contact Boeing corrosion on the crown skin inner
Commercial Airplanes, Attention: identified in this final rule, contact
Boeing Commercial Airplanes, surface. If the cracks or corrosion are not
Contractual & Data Services (C&DS), 2600 repaired, the cracks can rapidly join
Westminster Blvd., MC 110–SK57, Seal Attention: Contractual & Data Services
Beach, CA 90740–5600; telephone 562–797– (C&DS), 2600 Westminster Blvd., MC together and can cause a sudden
1717; Internet https:// 110–SK57, Seal Beach, CA 90740; decompression and loss of structural
www.myboeingfleet.com. telephone 562–797–1717; Internet integrity of the airplane.
(4) You may view this service information https://www.myboeingfleet.com. You Comments
at the FAA, Transport Airplane Directorate, may view this referenced service
1601 Lind Avenue SW., Renton, WA. For We gave the public the opportunity to
information at the FAA, Transport
information on the availability of this participate in developing this AD. The
material at the FAA, call 425–227–1221. Airplane Directorate, 1601 Lind Avenue
following presents the comments
(5) You may view this service information SW., Renton, WA. For information on
received on the NPRM and the FAA’s
that is incorporated by reference at the the availability of this material at the
response to each comment.
National Archives and Records FAA, call 425–227–1221. It is also
Administration (NARA). For information on available on the Internet at http:// Support for the NPRM
the availability of this material at NARA, call www.regulations.gov by searching for United Airlines supported the content
202–741–6030, or go to: http:// and locating Docket No. FAA–2016–
www.archives.gov/federal-register/cfr/ibr- of the NPRM.
9050.
locations.html. Request To Clarify the Language in the
Issued in Renton, Washington, on January Examining the AD Docket Terminating Action Paragraph
18, 2017. You may examine the AD docket on Boeing asked that we add
Michael Kaszycki, the Internet at http:// accomplishment of Part 4 to the
Acting Manager, Transport Airplane www.regulations.gov by searching for terminating action language specified in
Directorate, Aircraft Certification Service. and locating Docket No. FAA–2016– paragraph (i) of the proposed AD for
[FR Doc. 2017–01824 Filed 2–9–17; 8:45 am] 9050; or in person at the Docket clarification purposes. Boeing stated
BILLING CODE 4910–13–P Management Facility between 9 a.m. that Tables 1 and 2 of paragraph 1.E.,
and 5 p.m., Monday through Friday, ‘‘Compliance,’’ of Boeing Alert Service
except Federal holidays. The AD docket Bulletin 747–53A2878, dated May 19,
DEPARTMENT OF TRANSPORTATION contains this AD, the regulatory 2016, specify that Action 1 is to
evaluation, any comments received, and complete Part 3: Skin Panel
Federal Aviation Administration other information. The address for the Modification or Repair; and Action 2 is
Docket Office (phone: 800–647–5527) is to complete Part 4: Surface Finish
14 CFR Part 39 Docket Management Facility, U.S. Restoration. Boeing noted that both
[Docket No. FAA–2016–9050; Directorate Department of Transportation, Docket actions must be completed before
Identifier 2016–NM–086–AD; Amendment Operations, M–30, West Building further flight.
39–18788; AD 2017–02–09] Ground Floor, Room W12–140, 1200 We agree with the commenter’s
New Jersey Avenue SE., Washington, request to add accomplishment of Part
RIN 2120–AA64 DC 20590. 4 of the referenced service information,
FOR FURTHER INFORMATION CONTACT: for the reason provided. We have
Airworthiness Directives; The Boeing
Company Airplanes Nathan Weigand, Aerospace Engineer, clarified the language in paragraph (i) of
Airframe Branch, ANM–120S, FAA, this AD to specify that both Part 3 and
AGENCY: Federal Aviation Seattle Aircraft Certification Office Part 4 of the referenced service
Administration (FAA), DOT. (ACO), 1601 Lind Avenue SW., Renton, information must be accomplished to
ACTION: Final rule. WA 98057–3356; phone: 425–917–6428; terminate the repetitive inspections
fax: 425–917–6590; email: required by paragraph (g) of this AD.
SUMMARY: We are adopting a new nathan.p.weigand@faa.gov. However, we do not agree that both
airworthiness directive (AD) for certain SUPPLEMENTARY INFORMATION: actions must be done before further
The Boeing Company Model 747–400, flight because the terminating action is
–400D, and –400F series airplanes. This Discussion
optional; therefore, no specific
AD was prompted by widespread We issued a notice of proposed compliance time is required.
corrosion damage that was found on the rulemaking (NPRM) to amend 14 CFR
skin inner surface along the upper part 39 by adding an AD that would Conclusion
bulkhead at certain stations between apply to certain The Boeing Company We reviewed the relevant data,
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certain stringers. This AD requires Model 747–400, –400D, and –400F considered the comments received, and
repetitive inspections of the fuselage series airplanes. The NPRM published determined that air safety and the
crown skin inner surface, and related in the Federal Register on August 30, public interest require adopting this AD
investigative and corrective actions if 2016 (81 FR 59532) (‘‘the NPRM’’). The with the change described previously
necessary. This AD also allows for NPRM was prompted by widespread and minor editorial changes. We have
terminating actions for the repetitive corrosion damage that was found on the determined that these minor changes:
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Document Created: 2017-02-11 18:15:23
Document Modified: 2017-02-11 18:15:23
| 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 March 17, 2017. | |
| Contact | Alan Pohl, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6450; fax: 425-917-6590; email: [email protected] | |
| FR Citation | 82 FR 10258 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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