81 FR 43475 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 128 (July 5, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 128 (July 5, 2016)
| Page Range | 43475-43479 | |
| FR Document | 2016-15355 |
[Federal Register Volume 81, Number 128 (Tuesday, July 5, 2016)] [Rules and Regulations] [Pages 43475-43479] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-15355] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-8131; Directorate Identifier 2015-NM-073-AD; Amendment 39-18575; AD 2016-13-11] 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) 2008-05-06 for certain The Boeing Company Model 737-100, -200, -300, -400, and -500 series airplanes. AD 2008-05-06 required repetitive inspections for fatigue cracking in the longitudinal floor beam web, upper chord, and lower chord located at certain body stations, and repair if necessary. This new AD requires, for certain airplanes, an inspection to determine if tapered fillers are installed, and related investigative and corrective actions if necessary. This AD was prompted by reports of cracks in the center wing box longitudinal floor beams, upper chord, and lower chord. We are issuing this AD to detect and correct fatigue cracking of the upper and lower chords and web of the longitudinal floor beams, which could result in rapid loss of cabin pressure. [[Page 43476]] DATES: This AD is effective August 9, 2016. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of August 9, 2016. The Director of the Federal Register approved the incorporation by reference of a certain other publication listed in this AD as of April 8, 2008 (73 FR 11538, March 4, 2008). ADDRESSES: For service information identified in this final rule, 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- 8131. 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- 8131; 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: Galib Abumeri, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5324; fax: 562-627-5210; email: [email protected]. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2008-05-06, Amendment 39-15400 (73 FR 11538, March 4, 2008) (``AD 2008-05-06''). AD 2008-05-06 applied to certain The Boeing Company Model 737-100, -200, -300, -400, and -500 series airplanes. The NPRM published in the Federal Register on January 12, 2016 (81 FR 1345) (``the NPRM''). The NPRM was prompted by reports of cracks in the center wing box longitudinal floor beams, upper chord, and lower chord. The NPRM proposed to continue to require repetitive inspections for fatigue cracking in the longitudinal floor beam web, upper chord, and lower chord located at certain body stations, and repair if necessary. The NPRM also proposed to require, for certain airplanes, an inspection to determine if tapered fillers are installed, and related investigative and corrective actions if necessary. We are issuing this AD to detect and correct fatigue cracking of the upper and lower chords and web of the longitudinal floor beams, which could result in rapid loss of cabin pressure. 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 stated that it has reviewed the NPRM and concurs with the contents. Ms. Kathleen Whitworth stated that the NPRM is a good idea because the safety of airline passengers outweighs the extra cost of the added inspection and that she is in full support of the NPRM. Effect of Winglets on Accomplishment of the Proposed Actions Aviation Partners Boeing stated that accomplishing the Supplemental Type Certificate (STC) ST01219SE (http://rgl.faa.gov/ Regulatory_and_Guidance_Library/rgstc.nsf/0/ ebd1cec7b301293e86257cb30045557a/$FILE/ST01219SE.pdf) does not affect accomplishment of the actions specified in the NPRM. We concur with the commenter. We have redesignated paragraph (c) of the proposed AD as paragraph (c)(1) and added a new paragraph (c)(2) to this AD to state that installation of STC ST01219SE (http:// rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/ ebd1cec7b301293e86257cb30045557a/$FILE/ST01219SE.pdf) does not affect the ability to accomplish the actions required by this AD. Therefore, for airplanes on which STC ST01219SE 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. 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 Boeing Alert Service Bulletin 737-57A1296, Revision 2, dated April 1, 2015. The service information describes procedures for various inspections for fatigue cracks in the longitudinal floor beam web, upper chord, and lower chord, located at the applicable body stations, repairs (including related investigative and corrective actions), and preventive modifications (including related investigative and corrective actions) that terminate the repetitive inspections. The service information also describes procedures for an inspection to determine if tapered fillers are installed, and related investigative and corrective actions. 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 652 airplanes of U.S. registry. We estimate the following costs to comply with this AD: [[Page 43477]] Estimated Costs ---------------------------------------------------------------------------------------------------------------- Cost on U.S. Action Labor cost Parts cost Cost per product operators ---------------------------------------------------------------------------------------------------------------- Inspections [retained actions Up to 25 work-hours x $0 $2,125 per $1,385,500 per from AD 2008-05-06]. $85 per hour = $2,125 inspection cycle. inspection cycle. per inspection cycle. Tapered filler inspection [new 4 work-hours x $85 per $0 $340.............. $221,680. action]. hour = $340. ---------------------------------------------------------------------------------------------------------------- We estimate the following costs to do any necessary repairs that would 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 ---------------------------------------------------------------------------------------------------------------- Floor beam repair and optional Up to 198 work-hours x $85 (\1\) Up to $16,830 preventative modification. per hour = $16,830. Tapered filler repair............... 174 work-hours x $85 per (\1\) $14,790 hour = $14,790. ---------------------------------------------------------------------------------------------------------------- \1\ We have received no definitive data that would enable us to provide parts cost estimates for the 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 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) 2008-05-06, Amendment 39-15400 (73 FR 11538, March 4, 2008), and adding the following new AD: 2016-13-11 The Boeing Company: Amendment 39-18575; Docket No. FAA- 2015-8131; Directorate Identifier 2015-NM-073-AD. (a) Effective Date This AD is effective August 9, 2016. (b) Affected ADs This AD replaces AD 2008-05-06, Amendment 39-15400 (73 FR 11538, March 4, 2008) (``AD 2008-05-06''). (c) Applicability (1) This AD applies to The Boeing Company Model 737-100, -200, - 300, -400, and -500 series airplanes; certificated in any category; as identified in Boeing Alert Service Bulletin 737-57A1296, Revision 2, dated April 1, 2015. (2) Installation of Supplemental Type Certificate (STC) ST01219SE (http://rgl.faa.gov/Regulatory_and_Guidance_Library/ rgstc.nsf/0/ebd1cec7b301293e86257cb30045557a/$FILE/ST01219SE.pdf) does not affect the ability to accomplish the actions required by this AD. Therefore, for airplanes on which STC ST01219SE 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 57, Wings. (e) Unsafe Condition This AD was prompted by reports of cracks in the center wing box longitudinal floor beams, upper chord, and lower chord. We are issuing this AD to detect and correct fatigue cracking of the upper and lower chords and web of the longitudinal floor beams, which could result in rapid loss of cabin pressure. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Inspections, With Revised Service Information and Revised Affected Airplanes This paragraph restates the requirements of paragraph (f) of AD 2008-05-06, with revised service information and revised affected airplanes. For Groups 1 through 4 airplanes identified in Boeing Alert Service Bulletin 737-57A1296, Revision 2, dated April 1, 2015, do the various inspections for fatigue cracks in the longitudinal floor beam web, upper chord, and lower chord, located at the applicable body stations specified in the Accomplishment Instructions of Boeing Service Bulletin 737-57-1296, dated June 13, 2007; or Boeing Alert Service Bulletin 737-57A1296, Revision 2, dated April 1, 2015; by doing all the actions in accordance with the Accomplishment Instructions of Boeing [[Page 43478]] Service Bulletin 737-57A1296, dated June 13, 2007; or Boeing Alert Service Bulletin 737-57A1296, Revision 2, dated April 1, 2015; except as provided by paragraph (h) of this AD. Do the inspections at the time specified in paragraph (g)(1) or (g)(2) of this AD, as applicable. As of the effective date of this AD, only use Boeing Alert Service Bulletin 737-57A1296, Revision 2, dated April 1, 2015, for accomplishing the actions required by this paragraph. Note 1 to paragraphs (g) and (h) of this AD: The airplane groups identified in Boeing Service Bulletin 737-57-1296, dated June 13, 2007, do not, in all cases, match the airplane groups identified in Boeing Alert Service Bulletin 737-57A1296, Revision 2, dated April 1, 2015 (Group 4 airplanes in Boeing Alert Service Bulletin 737- 57A1296, Revision 2, dated April 1, 2015, coincide with certain Group 2 airplanes in Boeing Service Bulletin 737-57-1296, dated June 13, 2007). (1) For Groups 1 and 2 airplanes, except for line numbers 1 through 291, identified in Boeing Service Bulletin 737-57-1296, dated June 13, 2007: Do the inspections at the applicable initial compliance time listed in paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin 737-57-1296, dated June 13, 2007, except where Boeing Service Bulletin 737-57-1296, dated June 13, 2007, specifies a compliance time after the date on the service bulletin, this AD requires compliance within the specified compliance time after April 8, 2008 (the effective date of AD 2008-05-06). Repeat the inspections thereafter at the intervals specified in paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin 737-57-1296, dated June 13, 2007. (2) For Group 3 airplanes identified in Boeing Service Bulletin 737-57-1296, dated June 13, 2007: Do the inspections at the applicable initial compliance time listed in paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin 737-57-1296, dated June 13, 2007, except where Boeing Service Bulletin 737-57-1296, dated June 13, 2007, specifies a compliance time after the date on the service bulletin, this AD requires compliance within the specified compliance time after April 8, 2008 (the effective date of AD 2008- 05-06). Repeat the inspections thereafter at the intervals specified in paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin 737- 57-1296, dated June 13, 2007. (h) Retained Repair Instructions, With Revised Service Information That Contains New Repair Actions This paragraph restates the requirements of paragraph (g) of AD 2008-05-06, with revised service information that contains new repair actions. If any crack is found during any inspection required by paragraph (g) of this AD, do the applicable actions specified in paragraph (h)(1) or (h)(2) of this AD. (1) For inspections done using Boeing Service Bulletin 737-57- 1296, dated June 13, 2007: If any crack is found during any inspection required by paragraph (g) of this AD, and Boeing Service Bulletin 737-57-1296, dated June 13, 2007, specifies contacting Boeing for repair instructions, before further flight, repair using a method approved in accordance with the procedures specified in paragraph (n) of this AD. (2) For inspections done using Boeing Alert Service Bulletin 737-57A1296, Revision 2, dated April 1, 2015: If any crack is found during any inspection required by paragraph (g) of this AD, before further flight, repair, including doing all applicable related investigative actions and corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737- 57A1296, Revision 2, dated April 1, 2015; except where Boeing Alert Service Bulletin 737-57A1296, Revision 2, dated April 1, 2015, specifies contacting Boeing for repair instructions, before further flight, repair using a method approved in accordance with the procedures specified in paragraph (n) of this AD. Accomplishing a repair specified in Boeing Alert Service Bulletin 737-57A1296, Revision 2, dated April 1, 2015, terminates the repetitive inspections required by paragraph (g) of this AD for the repaired area only. (i) New Requirement of This AD: Inspection for Tapered Fillers for Certain Airplanes, Related Investigative Actions, and Corrective Actions For Groups 1 through 4, Configuration 1 airplanes identified in Boeing Alert Service Bulletin 737-57A1296, Revision 2, dated April 1, 2015: Except as provided by paragraph (k) of this AD, at the applicable time specified in table 5 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-57A1296, Revision 2, dated April 1, 2015, do an inspection to determine if tapered fillers are installed; and do all applicable related investigative and corrective actions; in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737- 57A1296, Revision 2, dated April 1, 2015; except where Boeing Alert Service Bulletin 737-57A1296, Revision 2, dated April 1, 2015, specifies contacting Boeing for repair instructions, before further flight, repair using a method approved in accordance with the procedures specified in paragraph (n) of this AD. Do all applicable related investigative and corrective actions before further flight. A review of the maintenance records is acceptable in lieu of this inspection if the installation of tapered fillers can be conclusively determined from that review. (j) New Requirement of This AD: Inspections and Corrective Actions for Group 5 Airplanes For Group 5 airplanes identified in Boeing Alert Service Bulletin 737-57A1296, Revision 2, dated April 1, 2015: Except as provided by paragraph (k) of this AD, at the applicable time specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-57A1296, Revision 2, dated April 1, 2015; accomplish inspections and applicable corrective actions using a method approved in accordance with the procedures specified in paragraph (n) of this AD. (k) Exception to Service Information Where paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-57A1296, Revision 2, dated April 1, 2015, 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.'' (l) Optional Terminating Action Accomplishing the applicable preventative modification specified in paragraph 3.B.4., ``Preventive Modification'' of the Accomplishment Instructions of Boeing Alert Service Bulletin 737- 57A1296, Revision 2, dated April 1, 2015, terminates the applicable repetitive inspection required by paragraph (g) of this AD. The preventative modification, including related investigative and corrective actions, must be done in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737- 57A1296, Revision 2, dated April 1, 2015; except where Boeing Alert Service Bulletin 737-57A1296, Revision 2, dated April 1, 2015, specifies contacting Boeing for repair instructions, before further flight, repair using a method approved in accordance with the procedures specified in paragraph (n) of this AD. (m) Credit for Previous Actions This paragraph provides credit for actions required by paragraphs (g) and (h)(2) of this AD, if those actions were performed before the effective date of this AD using Boeing Service Bulletin 737-57-1296, Revision 1, dated September 26, 2012. This document is not incorporated by reference in this AD. (n) Alternative Methods of Compliance (AMOCs) (1) The Manager, Los Angeles 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)(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, Los Angeles 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 as specified in the fourth paragraph (related to AD 2008-05-06) of Section 1.F., Approval, of Boeing Service Bulletin 737-57-1296, Revision 1, dated September 26, 2012, for repairs and modifications are not approved for any provision of this AD. All other AMOCs approved for AD 2008-05-06 are approved as AMOCs for the corresponding provisions of this AD. [[Page 43479]] (o) Related Information (1) For more information about this AD, contact Galib Abumeri, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5324; fax: 562-627-5210; email: [email protected]. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (p)(5) and (p)(6) of this AD. (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. (3) The following service information was approved for IBR on August 9, 2016. (i) Boeing Alert Service Bulletin 737-57A1296, Revision 2, dated April 1, 2015. (ii) Reserved. (4) The following service information was approved for IBR on April 8, 2008 (73 FR 11538, March 4, 2008). (i) Boeing Service Bulletin 737-57-1296, dated June 13, 2007. (ii) Reserved. (5) For Boeing 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. (6) 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. (7) 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 June 21, 2016. Dorr M. Anderson, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-15355 Filed 7-1-16; 8:45 am] BILLING CODE 4910-13-P
![Federal Register / Vol. 81, No. 128 / Tuesday, July 5, 2016 / Rules and Regulations 43475
A300–57–6115, dated April 4, 2014, refers to (j) Other FAA AD Provisions (ii) Airbus Service Bulletin A300–57–6115,
Structural Repair Manual (SRM) 51–40–13 The following provisions also apply to this dated April 4, 2014.
for applying special protection, the correct AD: (3) For Airbus service information
reference is SRM 51–23–20; and to SRM 51– (1) Alternative Methods of Compliance identified in this final rule, contact Airbus
40–12 for applying paint coatings, the correct (AMOCs): The Manager, International SAS, Airworthiness Office—EAW, 1 Rond
reference is SRM 51–23–10. Branch, ANM–116, Transport Airplane Point Maurice Bellonte, 31707 Blagnac
Directorate, FAA, has the authority to Cedex, France; telephone +33 5 61 93 36 96;
(h) Repetitive Rototest Inspections fax +33 5 61 93 44 51; email
approve AMOCs for this AD, if requested
Within 36 months after the effective date using the procedures found in 14 CFR 39.19. account.airworth-eas@airbus.com; Internet
of this AD: Remove the fasteners and In accordance with 14 CFR 39.19, send your http://www.airbus.com.
measure the diameter of the fastener holes; request to your principal inspector or local (4) You may view this service information
and, before further flight, do the applicable Flight Standards District Office, as at the FAA, Transport Airplane Directorate,
actions required by paragraph (h)(1) or (h)(2) appropriate. If sending information directly 1601 Lind Avenue SW., Renton, WA. For
of this AD, in accordance with the to the International Branch, send it to ATTN: information on the availability of this
Accomplishment Instructions of Airbus Dan Rodina, Aerospace Engineer, material at the FAA, call 425–227–1221.
International Branch, ANM–116, Transport (5) You may view this service information
Service Bulletin A300–57–0257, excluding
Airplane Directorate, FAA, 1601 Lind that is incorporated by reference at the
Appendix 01 and including Appendix 02,
Avenue SW., Renton, WA 98057–3356; National Archives and Records
dated April 4, 2014 (for Model A300 B2–1A,
telephone 425–227–2125; fax 425–227–1149. Administration (NARA). For information on
B2–1C, B2K–3C, B2–203, B4–2C, B4–103, the availability of this material at NARA, call
and B4–203 airplanes); or Airbus Service Information may be emailed to: 9-ANM-116-
AMOC-REQUESTS@faa.gov. Before using 202–741–6030, or go to: http://
Bulletin A300–57–6115, dated April 4, 2014 www.archives.gov/federal-register/cfr/ibr-
(for Model A300 B4–601, B4–603, B4–620, any approved AMOC, notify your appropriate
principal inspector, or lacking a principal locations.html.
B4–622, B4–605R, B4–622R, F4–605R, F4–
622R, and C4–605R Variant F airplanes). inspector, the manager of the local flight Issued in Renton, Washington, on June 21,
(1) If one or more of the hole diameters is standards district office/certificate holding 2016.
outside the tolerance of the nominal district office. The AMOC approval letter Dorr M. Anderson,
diameter, and outside the tolerance of the must specifically reference this AD.
Acting Manager, Transport Airplane
first and second oversize: Do the applicable (2) Contacting the Manufacturer: For any
Directorate, Aircraft Certification Service.
corrective actions required by paragraph (i) of requirement in this AD to obtain corrective
actions from a manufacturer, the action must [FR Doc. 2016–15356 Filed 7–1–16; 8:45 am]
this AD.
(2) If all of the hole diameters are within be accomplished using a method approved BILLING CODE 4910–13–P
by the Manager, International Branch, ANM–
the tolerance of the nominal diameter or the
116, Transport Airplane Directorate, FAA; or
first or second oversize: Do detailed and
the EASA; or Airbus’s EASA DOA. If DEPARTMENT OF TRANSPORTATION
rototest inspections for cracking of the
approved by the DOA, the approval must
fastener holes at the left-hand and right-hand
include the DOA-authorized signature. Federal Aviation Administration
sides of the FR40 lower junction, in
(3) Required for Compliance (RC): Except
accordance with the Accomplishment
as required by paragraph (i) of this AD: If any 14 CFR Part 39
Instructions of Airbus Service Bulletin A300–
service information contains procedures or
57–0257, excluding Appendix 01 and [Docket No. FAA–2015–8131; Directorate
tests that are identified as RC, those
including Appendix 02, dated April 4, 2014 Identifier 2015–NM–073–AD; Amendment
procedures and tests must be done to comply
(for Model A300 B2–1A, B2–1C, B2K–3C, 39–18575; AD 2016–13–11]
with this AD; any procedures or tests that are
B2–203, B4–2C, B4–103, and B4–203 not identified as RC are recommended. Those
airplanes); or Airbus Service Bulletin A300– RIN 2120–AA64
procedures and tests that are not identified
57–6115, dated April 4, 2014 (for Model as RC may be deviated from using accepted
A300 B4–601, B4–603, B4–620, B4–622, B4– methods in accordance with the operator’s
Airworthiness Directives; The Boeing
605R, B4–622R, F4–605R, F4–622R, and C4– maintenance or inspection program without Company Airplanes
605R Variant F airplanes). If no cracking is obtaining approval of an AMOC, provided
found, before further flight, install new AGENCY: Federal Aviation
the procedures and tests identified as RC can Administration (FAA), DOT.
fasteners of the same diameter in special be done and the airplane can be put back in
clearance fit for fasteners 1 through 3 of the an airworthy condition. Any substitutions or ACTION: Final rule.
FR40 lower junction, in accordance with the changes to procedures or tests identified as
Accomplishment Instructions of Airbus SUMMARY: We are superseding
RC require approval of an AMOC.
Service Bulletins A300–57–0257, excluding Airworthiness Directive (AD) 2008–05–
Appendix 01 and including Appendix 02, (k) Related Information 06 for certain The Boeing Company
dated April 4, 2014; or Airbus Service Refer to Mandatory Continuing Model 737–100, –200, –300, –400, and
Bulletin A300–57–6115, dated April 4, 2014. Airworthiness Information (MCAI) EASA –500 series airplanes. AD 2008–05–06
Repeat the rototest inspection thereafter at Airworthiness Directive 2014–0272, dated required repetitive inspections for
intervals not to exceed 7,000 flight cycles. December 12, 2014, for related information. fatigue cracking in the longitudinal floor
Accomplishment of a rototest inspection This MCAI may be found in the AD docket
required by this paragraph terminates the
beam web, upper chord, and lower
on the Internet at http://www.regulations.gov
repetitive HFEC inspections required by chord located at certain body stations,
by searching for and locating Docket No.
paragraph (g) of this AD. FAA–2015–8134. and repair if necessary. This new AD
requires, for certain airplanes, an
(i) Corrective Actions (l) Material Incorporated by Reference inspection to determine if tapered fillers
If, during any inspection required by this (1) The Director of the Federal Register are installed, and related investigative
AD, any crack is found, or one or more of the approved the incorporation by reference and corrective actions if necessary. This
hole diameters is outside the tolerance of the (IBR) of the service information listed in this AD was prompted by reports of cracks
sradovich on DSK3GDR082PROD with RULES
nominal diameter, and outside the tolerance paragraph under 5 U.S.C. 552(a) and 1 CFR in the center wing box longitudinal floor
of the first and second oversize: Repair before part 51.
further flight in accordance with a method
beams, upper chord, and lower chord.
(2) You must use this service information
approved by the Manager, International as applicable to do the actions required by We are issuing this AD to detect and
Branch, ANM–116, Transport Airplane this AD, unless this AD specifies otherwise. correct fatigue cracking of the upper and
Directorate, FAA; or the European Aviation (i) Airbus Service Bulletin A300–57–0257, lower chords and web of the
Safety Agency (EASA); or Airbus’s EASA excluding Appendix 01 and including longitudinal floor beams, which could
Design Organization Approval (DOA). Appendix 02, dated April 4, 2014. result in rapid loss of cabin pressure.
VerDate Sep<11>2014 16:06 Jul 01, 2016 Jkt 238001 PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 E:\FR\FM\05JYR1.SGM 05JYR1](https://thefederalregister.org/doc/81_FR_43603/page/1.svg)
![Federal Register / Vol. 81, No. 128 / Tuesday, July 5, 2016 / Rules and Regulations 43477
ESTIMATED COSTS
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
Inspections [retained actions from AD Up to 25 work-hours × $85 per hour = $0 $2,125 per inspec- $1,385,500 per in-
2008–05–06]. $2,125 per inspection cycle. tion cycle. spection cycle.
Tapered filler inspection [new action] .... 4 work-hours × $85 per hour = $340 ..... $0 $340 ....................... $221,680.
We estimate the following costs to do required based on the results of the determining the number of aircraft that
any necessary repairs that would be inspection. We have no way of might need these repairs:
ON-CONDITION COSTS
Cost per
Action Labor cost Parts cost product
Floor beam repair and optional preventative modi- Up to 198 work-hours × $85 per hour = $16,830 ...... (1) Up to $16,830
fication.
Tapered filler repair ..................................................... 174 work-hours × $85 per hour = $14,790 ................ (1) $14,790
1 We have received no definitive data that would enable us to provide parts cost estimates for the actions specified in this AD.
Authority for This Rulemaking on a substantial number of small entities (2) Installation of Supplemental Type
under the criteria of the Regulatory Certificate (STC) ST01219SE (http://
Title 49 of the United States Code rgl.faa.gov/Regulatory_and_Guidance_
specifies the FAA’s authority to issue Flexibility Act.
Library/rgstc.nsf/0/
rules on aviation safety. Subtitle I, List of Subjects in 14 CFR Part 39 ebd1cec7b301293e86257cb30045557a/$FILE/
Section 106, describes the authority of ST01219SE.pdf) does not affect the ability to
Air transportation, Aircraft, Aviation
the FAA Administrator. Subtitle VII, accomplish the actions required by this AD.
safety, Incorporation by reference, Therefore, for airplanes on which STC
Aviation Programs, describes in more
Safety. ST01219SE is installed, a ’’change in
detail the scope of the Agency’s
authority. Adoption of the Amendment product’’ alternative method of compliance
We are issuing this rulemaking under (AMOC) approval request is not necessary to
Accordingly, under the authority comply with the requirements of 14 CFR
the authority described in Subtitle VII,
delegated to me by the Administrator, 39.17.
Part A, Subpart III, Section 44701,
the FAA amends 14 CFR part 39 as (d) Subject
‘‘General requirements.’’ Under that
follows:
section, Congress charges the FAA with Air Transport Association (ATA) of
promoting safe flight of civil aircraft in PART 39—AIRWORTHINESS America Code 57, Wings.
air commerce by prescribing regulations DIRECTIVES (e) Unsafe Condition
for practices, methods, and procedures
This AD was prompted by reports of cracks
the Administrator finds necessary for ■ 1. The authority citation for part 39 in the center wing box longitudinal floor
safety in air commerce. This regulation continues to read as follows: beams, upper chord, and lower chord. We are
is within the scope of that authority Authority: 49 U.S.C. 106(g), 40113, 44701. issuing this AD to detect and correct fatigue
because it addresses an unsafe condition cracking of the upper and lower chords and
that is likely to exist or develop on § 39.13 [Amended] web of the longitudinal floor beams, which
products identified in this rulemaking ■ 2. The FAA amends § 39.13 by could result in rapid loss of cabin pressure.
action. removing Airworthiness Directive (AD) (f) Compliance
Regulatory Findings 2008–05–06, Amendment 39–15400 (73 Comply with this AD within the
FR 11538, March 4, 2008), and adding compliance times specified, unless already
We have determined that this AD will
the following new AD: done.
not have federalism implications under
Executive Order 13132. This AD will 2016–13–11 The Boeing Company: (g) Retained Inspections, With Revised
not have a substantial direct effect on Amendment 39–18575; Docket No. Service Information and Revised Affected
the States, on the relationship between FAA–2015–8131; Directorate Identifier Airplanes
2015–NM–073–AD.
the national government and the States, This paragraph restates the requirements of
or on the distribution of power and (a) Effective Date paragraph (f) of AD 2008–05–06, with revised
responsibilities among the various This AD is effective August 9, 2016. service information and revised affected
levels of government. airplanes. For Groups 1 through 4 airplanes
(b) Affected ADs identified in Boeing Alert Service Bulletin
For the reasons discussed above, I
certify that this AD: This AD replaces AD 2008–05–06, 737–57A1296, Revision 2, dated April 1,
(1) Is not a ‘‘significant regulatory Amendment 39–15400 (73 FR 11538, March 2015, do the various inspections for fatigue
4, 2008) (‘‘AD 2008–05–06’’). cracks in the longitudinal floor beam web,
action’’ under Executive Order 12866,
sradovich on DSK3GDR082PROD with RULES
upper chord, and lower chord, located at the
(2) Is not a ‘‘significant rule’’ under (c) Applicability applicable body stations specified in the
DOT Regulatory Policies and Procedures (1) This AD applies to The Boeing Accomplishment Instructions of Boeing
(44 FR 11034, February 26, 1979), Company Model 737–100, –200, –300, –400, Service Bulletin 737–57–1296, dated June 13,
(3) Will not affect intrastate aviation and –500 series airplanes; certificated in any 2007; or Boeing Alert Service Bulletin 737–
in Alaska, and category; as identified in Boeing Alert 57A1296, Revision 2, dated April 1, 2015; by
(4) Will not have a significant Service Bulletin 737–57A1296, Revision 2, doing all the actions in accordance with the
economic impact, positive or negative, dated April 1, 2015. Accomplishment Instructions of Boeing
VerDate Sep<11>2014 16:06 Jul 01, 2016 Jkt 238001 PO 00000 Frm 00015 Fmt 4700 Sfmt 4700 E:\FR\FM\05JYR1.SGM 05JYR1](https://thefederalregister.org/doc/81_FR_43603/page/3.svg)
![Federal Register / Vol. 81, No. 128 / Tuesday, July 5, 2016 / Rules and Regulations 43479
(o) Related Information DEPARTMENT OF TRANSPORTATION Operations Office between 9 a.m. and 5
(1) For more information about this AD, p.m., Monday through Friday, except
contact Galib Abumeri, Aerospace Engineer, Federal Aviation Administration Federal holidays. The AD docket
Airframe Branch, ANM–120L, FAA, Los contains this AD, the European Aviation
Angeles Aircraft Certification Office (ACO), 14 CFR Part 39 Safety Agency (EASA) AD, the
3960 Paramount Boulevard, Lakewood, CA [Docket No. FAA–2016–8032; Directorate economic evaluation, any comments
90712–4137; phone: 562–627–5324; fax: 562– Identifier 2016–SW–037–AD; Amendment received, and other information. The
627–5210; email: galib.abumeri@faa.gov. 39–18578; AD 2016–12–51] street address for the Docket Operations
(2) Service information identified in this Office (telephone 800–647–5527) is in
RIN 2120–AA64
AD that is not incorporated by reference is the ADDRESSES section. Comments will
available at the addresses specified in Airworthiness Directives; Airbus be available in the AD docket shortly
paragraphs (p)(5) and (p)(6) of this AD. Helicopters after receipt.
(p) Material Incorporated by Reference FOR FURTHER INFORMATION CONTACT: Gary
AGENCY: Federal Aviation Roach, Aviation Safety Engineer,
(1) The Director of the Federal Register Administration (FAA), Department of Regulations and Policy Group,
approved the incorporation by reference Transportation (DOT). Rotorcraft Directorate, FAA, 10101
(IBR) of the service information listed in this
ACTION: Final rule; request for Hillwood Pkwy., Fort Worth, TX 76177;
paragraph under 5 U.S.C. 552(a) and 1 CFR
comments. telephone (817) 222–5110, email
part 51.
(2) You must use this service information
gary.b.roach@faa.gov.
SUMMARY: We are publishing a new
as applicable to do the actions required by SUPPLEMENTARY INFORMATION:
airworthiness directive (AD) for Airbus
this AD, unless the AD specifies otherwise. Helicopters Model AS332L2 and Model Comments Invited
(3) The following service information was EC225LP helicopters, which was sent
approved for IBR on August 9, 2016. This AD is a final rule that involves
previously to all known U.S. owners
(i) Boeing Alert Service Bulletin 737– requirements affecting flight safety, and
and operators of these helicopters. This
57A1296, Revision 2, dated April 1, 2015. we did not provide you with notice and
AD immediately prohibits flight of all
(ii) Reserved. an opportunity to provide your
Model AS332L2 and EC225LP
(4) The following service information was comments prior to it becoming effective.
helicopters. This AD is prompted by an
approved for IBR on April 8, 2008 (73 FR However, we invite you to participate in
accident involving an EC225LP
11538, March 4, 2008). this rulemaking by submitting written
helicopter in which the main rotor hub
(i) Boeing Service Bulletin 737–57–1296, comments, data, or views. We also
(MRH) detached from the main gearbox
dated June 13, 2007. invite comments relating to the
(MGB). These actions are intended to
(ii) Reserved. economic, environmental, energy, or
prevent failure of the main rotor system
(5) For Boeing service information federalism impacts that resulted from
and subsequent loss of control of the
identified in this AD, contact Boeing adopting this AD. The most helpful
helicopter.
Commercial Airplanes, Attention: Data & comments reference a specific portion of
Services Management, P.O. Box 3707, MC DATES: This AD becomes effective July the AD, explain the reason for any
2H–65, Seattle, WA 98124–2207; telephone 20, 2016 to all persons except those recommended change, and include
206–544–5000, extension 1; fax 206–766– persons to whom it was made supporting data. To ensure the docket
5680; Internet https:// immediately effective by Emergency AD does not contain duplicate comments,
www.myboeingfleet.com. 2016–12–51, issued on June 3, 2016, commenters should send only one copy
(6) You may view this service information which contains the requirements of this of written comments, or if comments are
at the FAA, Transport Airplane Directorate, AD. filed electronically, commenters should
1601 Lind Avenue SW., Renton, WA. For We must receive comments on this submit them only one time. We will file
information on the availability of this AD by September 6, 2016. in the docket all comments that we
material at the FAA, call 425–227–1221. ADDRESSES: You may send comments by receive, as well as a report summarizing
(7) You may view this service information any of the following methods: each substantive public contact with
that is incorporated by reference at the • Federal eRulemaking Docket: Go to FAA personnel concerning this
National Archives and Records http://www.regulations.gov. Follow the rulemaking during the comment period.
Administration (NARA). For information on online instructions for sending your We will consider all the comments we
the availability of this material at NARA, call comments electronically. receive and may conduct additional
202–741–6030, or go to: http:// • Fax: 202–493–2251. rulemaking based on those comments.
www.archives.gov/federal-register/cfr/ibr- • Mail: Send comments to the U.S.
locations.html. Discussion
Department of Transportation, Docket
Issued in Renton, Washington, on June 21, Operations, M–30, West Building On June 3, 2016, we issued
2016. Ground Floor, Room W12–140, 1200 Emergency AD 2016–12–51 to correct an
Dorr M. Anderson, New Jersey Avenue SE., Washington, unsafe condition for Model AS332L2
DC 20590–0001. and EC225LP helicopters. Emergency
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service. • Hand Delivery: Deliver to the AD 2016–12–51 immediately prohibits
‘‘Mail’’ address between 9 a.m. and 5 further flight of Model AS332L2 and
[FR Doc. 2016–15355 Filed 7–1–16; 8:45 am]
p.m., Monday through Friday, except EC225LP helicopters. The emergency
BILLING CODE 4910–13–P AD was sent previously to all known
Federal holidays.
sradovich on DSK3GDR082PROD with RULES
U.S. owners and operators of these
Examining the AD Docket helicopters.
You may examine the AD docket on Emergency AD 2016–12–51 was
the Internet at http:// prompted by Emergency AD No. 2016–
www.regulations.gov by searching for 0104–E, dated June 2, 2016, issued by
and locating Docket No. FAA–2016– EASA, which is the Technical Agent for
8032; or in person at the Docket the Member States of the European
VerDate Sep<11>2014 16:06 Jul 01, 2016 Jkt 238001 PO 00000 Frm 00017 Fmt 4700 Sfmt 4700 E:\FR\FM\05JYR1.SGM 05JYR1](https://thefederalregister.org/doc/81_FR_43603/page/5.svg)
Document Created: 2016-07-01 23:49:50
Document Modified: 2016-07-01 23:49:50
| 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 August 9, 2016. | |
| Contact | Galib Abumeri, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5324; fax: 562-627-5210; email: [email protected] | |
| FR Citation | 81 FR 43475 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
2025 Federal Register | Disclaimer | Privacy Policy
USC | CFR | eCFR