81 FR 5893 - Airworthiness Directives; the Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 23 (February 4, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 23 (February 4, 2016)
| Page Range | 5893-5896 | |
| FR Document | 2016-01827 |
[Federal Register Volume 81, Number 23 (Thursday, February 4, 2016)] [Rules and Regulations] [Pages 5893-5896] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-01827] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-1983; Directorate Identifier 2015-NM-020-AD; Amendment 39-18388; AD 2016-03-01] RIN 2120-AA64 Airworthiness Directives; the Boeing Company Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD was prompted by a report of a crack of the forward leg of the left front spar lower chord and cracks on the lower wing skin at three fastener holes common to the nacelle outboard side load fitting. This AD requires repetitive inspections for cracks on the front spar lower chord, inspar skin, and wing skin, and corrective action if necessary. We are issuing this AD to detect and correct fatigue cracking of the forward leg of the front spar lower chord, inspar skin, and wing skin common to the nacelle outboard side load fitting, which could adversely affect the structural integrity of the wing. DATES: This AD is effective March 10, 2016. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of March 10, 2016. 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- 1983. 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- [[Page 5894]] 1983; 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: Jennifer Tsakoumakis, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5264; fax: 562-627-5210; email: [email protected]. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to all The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. The NPRM published in the Federal Register on June 24, 2015 (80 FR 36258) (``the NPRM''). The NPRM was prompted by a report of a crack of the forward leg of the left front spar lower chord and cracks on the lower wing skin at three fastener holes common to the nacelle outboard side load fitting. The NPRM proposed to require repetitive inspections for cracks on the front spar lower chord, inspar skin, and wing skin, and corrective action if necessary. We are issuing this AD to correct the unsafe condition on these products. 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 concurs with the NPRM. Effect of Winglets on Accomplishment of the NPRM Southwest Airlines (SWA) requested clarification whether the installation of Aviation Partners Boeing (APB) Supplemental Type Certificate (STC) ST01219SE (http://rgl.faa.gov/ Regulatory_and_Guidance_Library/rgstc.nsf/0/ ebd1cec7b301293e86257cb30045557a/$FILE/ST01219SE.pdf) has any affect to the ability of accomplishment of the action of this proposed AD (80 FR 36258, June 24, 2015). APB stated that the installation of winglets per STC ST01219SE does not affect the accomplishment of the manufacturer's service instructions. We concur with APB's comment and agree to clarify. We have redesignated paragraph (c) of the proposed AD (80 FR 36258, June 24, 2015) as paragraph (c)(1) and added new paragraph (c)(2) to this AD to state that installation of STC ST01219SE (http://rgl.faa.gov/ Regulatory_and_Guidance_Library/rgstc.nsf/0/ ebd1cec7b301293e86257cb30045557a/$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. Request for Critical Design Configuration Control Limitation (CDCCL) Instructions SWA requested that we add instructions to paragraph (i) of the proposed AD (80 FR 36258, June 24, 2015) to specify that important CDCCL information must be observed during access and close-up while performing the actions specified in paragraph (i) of the proposed AD. SWA explained that Boeing Alert Service Bulletin 737-57A1323, dated December 5, 2014, does not contain any references to CDCCLs, despite the required access to the fuel tank, in order to perform either option 1 or option 2 non-destructive test inspection requirements. SWA stated that the access and close-up steps indicate, as a reference, the maintenance planning document (section 4), which does not provide a clear path to the airplane maintenance manual section that addresses CDCCL requirements. We agree with the commenter's request. Boeing Alert Service Bulletin 737-57A1323, dated December 5, 2014, does not contain any references to CDCCLs that are part of the airworthiness limitations (AWLs). All applicable AWLs must still be observed while performing the actions mandated by this AD. We have revised paragraph (i) of this AD to state that while accomplishing the actions required by paragraph (i) of this AD, operators must ensure that all applicable CDCCLs are complied with. Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this AD with the changes described previously and minor editorial changes. We have determined that these minor changes:[Agr]re consistent with the intent that was proposed in the NPRM 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 737-57A1323, dated December 5, 2014. The service information describes procedures for repetitive inspections for cracks on the left and right wing front spar lower chord, inspar skin, and wing skin, and corrective action. The 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 331 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 (28 Group 2 7 work[dash]hours $0................ $595 per $16,660 per airplanes). x $85 per hour = inspection cycle. inspection cycle. $595 per inspection cycle. Inspection and fastener Up to 94 0................. Up to $7,990 per Up to $2,412,980 installation (302 Group 3 work[dash]hours x inspection cycle. per inspection airplanes). $85 per hour = cycle. $7,990 per inspection cycle. ---------------------------------------------------------------------------------------------------------------- [[Page 5895]] We have received no definitive data that will enable us to provide cost estimates for the actions specified for the Group 1 airplane in this AD. We also have received no definitive data that will enable us to provide cost estimates for the on-condition actions specified in this AD. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. Subtitle VII: Aviation Programs, describes in more detail the scope of the Agency's authority. We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701: ``General requirements.'' Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings This AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: (1) Is not a ``significant regulatory action'' under Executive Order 12866, (2) Is not a ``significant rule'' under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation in Alaska, and (4) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39--AIRWORTHINESS DIRECTIVES 0 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by adding the following new airworthiness directive (AD): 2016-03-01 the Boeing Company: Amendment 39-18388; Docket No. FAA- 2015-1983; Directorate Identifier 2015-NM-020-AD. (a) Effective Date This AD is effective March 10, 2016. (b) Affected ADs None. (c) Applicability (1) This AD applies to all The Boeing Company Model 737-100, - 200, -200C, -300, -400, and -500 series airplanes, certificated in any category. (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 a report of a crack in the forward leg of the left front spar lower chord and cracks on the lower wing skin at three fastener holes common to the nacelle outboard side load fitting. We are issuing this AD to detect and correct fatigue cracking of the forward leg of the front spar lower chord, inspar skin, and wing skin common to the nacelle outboard side load fitting, which could adversely affect the structural integrity of the wing. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspections and Corrective Actions for Group 1 Airplanes For Group 1 airplanes identified in Boeing Alert Service Bulletin 737-57A1323, dated December 5, 2014: Within 120 days after the effective date of this AD, do inspections of the left and right wing front spar lower chord and inspar skin, and the left and right wing nacelle outboard side load fitting fastener holes common to the front spar lower chord and skin, and do all applicable corrective actions, using a method approved in accordance with the procedures specified in paragraph (k) of this AD. (h) Repetitive Detailed Inspections and Corrective Actions For Group 2 and 3 airplanes identified in Boeing Alert Service Bulletin 737-57A1323, dated December 5, 2014: Except as provided by paragraph (j)(1) of this AD, at the applicable time specified in Table 1 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-57A1323, dated December 5, 2014, do a detailed inspection for cracks on the left and right wing front spar lower chord and inspar skin, and do all applicable corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737-57A1323, dated December 5, 2014, except as specified in paragraph (j)(2) of this AD. Do all applicable corrective actions before further flight. Repeat the inspection thereafter at the applicable interval specified in Table 1 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-57A1323, dated December 5, 2014, except in areas repaired in accordance with the procedures specified in paragraph (k) of this AD. (i) Repetitive High Frequency Eddy Current (HFEC) Inspections and Corrective Actions For Group 3 airplanes identified in Boeing Alert Service Bulletin 737-57A1323, dated December 5, 2014: Except as provided by paragraph (j)(1) of this AD, at the applicable time specified in Table 2 or Table 3 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-57A1323, dated December 5, 2014, do the actions specified in paragraphs (i)(1) or (i)(2) of this AD. Repeat the inspection specified in either paragraph (i)(1) or (i)(2) of this AD thereafter at the applicable interval specified in Table 2 or Table 3 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin737-57A1323, dated December 5, 2014. While accomplishing the actions required by this paragraph, ensure that all applicable critical design configuration control limitations are complied with. (1) Do an HFEC open hole probe inspection for cracks of the left and right wing nacelle outboard side load fitting fastener holes common to the front spar lower chord and skin, and perform all applicable corrective actions, in accordance with Part 2, Option 1 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-57A1323, dated December 5, 2014, except as provided by paragraph (j)(2) of this AD. Do all applicable corrective actions before further flight. (2) Do an HFEC surface probe inspection for cracks in the wing inspar skin, and perform all applicable corrective actions, in accordance with Part 2, Option 2 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-57A1323, dated December 5, 2014, except as provided by paragraph (j)(2) of this AD. Do all applicable corrective actions before further flight. (j) Exceptions to Service Information Specifications (1) Where paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-57A1323, dated December 5, 2014, specifies a compliance time ``after the original issue date of this service bulletin,'' this AD requires [[Page 5896]] compliance within the specified compliance time ``after the effective date of this AD.'' (2) Although Boeing Alert Service Bulletin 737-57A1323, dated December 5, 2014, specifies to contact Boeing for repair instructions, and specifies that action as ``RC'' (Required for Compliance), this AD requires repair before further flight using a method approved in accordance with the procedures specified in paragraph (k) of this AD. (k) 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 (l) 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) Except as required by paragraph (j)(2) of this AD: For service information that contains steps that are labeled as Required for Compliance (RC), the provisions of paragraphs (k)(4)(i) and (k)(4)(ii) apply. (i) The steps labeled as RC, including substeps under an RC step and any figures identified in an RC step, must be done to comply with the AD. An AMOC is required for any deviations to RC steps, including substeps and identified figures. (ii) Steps not labeled as RC may be deviated from using accepted methods in accordance with the operator's maintenance or inspection program without obtaining approval of an AMOC, provided the RC steps, including substeps and identified figures, can still be done as specified, and the airplane can be put back in an airworthy condition. (l) Related Information For more information about this AD, contact Jennifer Tsakoumakis, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles ACO, 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5264; fax: 562-627-5210; email: [email protected]. (m) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) Boeing Alert Service Bulletin 737-57A1323, dated December 5, 2014. (ii) Reserved. (3) 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. (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 25, 2016. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-01827 Filed 2-3-16; 8:45 am] BILLING CODE 4910-13-P
![Federal Register / Vol. 81, No. 23 / Thursday, February 4, 2016 / Rules and Regulations 5893
Service Bulletin A300–53–6123, Revision 06, accomplished using a method approved by DEPARTMENT OF TRANSPORTATION
dated September 28, 2011, except as the Manager, International Branch, ANM–
provided by paragraph (m) of this AD. 116, Transport Airplane Directorate, FAA; or Federal Aviation Administration
(m) New Requirement of This AD: Exception the EASA; or Airbus’s EASA DOA. If
to Service Information approved by the DOA, the approval must 14 CFR Part 39
If any crack is found during any inspection include the DOA-authorized signature.
[Docket No. FAA–2015–1983; Directorate
required by paragraph (j) or (k) of this AD (p) Related Information Identifier 2015–NM–020–AD; Amendment
and Airbus Service Bulletin A300–53–6123, 39–18388; AD 2016–03–01]
Revision 06, dated September 28, 2011; or (1) Refer to Mandatory Continuing
Airbus Service Bulletin A300–53–0350, Airworthiness Information (MCAI) RIN 2120–AA64
Revision 03, dated July 26, 2007; specifies to Airworthiness Directive 2013–0184R1, dated
contact Airbus: Before further flight, repair August 22, 2013, for related information. Airworthiness Directives; the Boeing
the crack using a method approved by the This MCAI may be found in the AD docket Company Airplanes
Manager, International Branch, ANM–116, on the Internet at http://www.regulations.gov
Transport Airplane Directorate, FAA; or the by searching for and locating Docket No. AGENCY: Federal Aviation
EASA; or Airbus’s EASA DOA. FAA–2015–1417. Administration (FAA), DOT.
(n) Credit for Previous Actions (2) Service information identified in this ACTION: Final rule.
This paragraph provides credit for actions AD that is not incorporated by reference is
available at the addresses specified in SUMMARY: We are adopting a new
required by paragraphs (j) and (l) of this AD, airworthiness directive (AD) for all The
if those actions were performed before the paragraphs (q)(5) and (q)(6) of this AD.
effective date of this AD using the applicable
Boeing Company Model 737–100, –200,
(q) Material Incorporated by Reference –200C, –300, –400, and –500 series
service information specified in paragraphs
(n)(1) through (n)(6) of this AD. (1) The Director of the Federal Register airplanes. This AD was prompted by a
(1) Airbus Service Bulletin A300–53–0350, approved the incorporation by reference report of a crack of the forward leg of
Revision 01, dated December 18, 2001, which (IBR) of the service information listed in this the left front spar lower chord and
is not incorporated by reference in this AD. paragraph under 5 U.S.C. 552(a) and 1 CFR cracks on the lower wing skin at three
(2) Airbus Service Bulletin A300–53–0350, part 51. fastener holes common to the nacelle
Revision 02, excluding Appendix 01, dated (2) You must use this service information outboard side load fitting. This AD
November 12, 2002, which was incorporated as applicable to do the actions required by
by reference in AD 2004–20–14, Amendment
requires repetitive inspections for cracks
this AD, unless this AD specifies otherwise. on the front spar lower chord, inspar
39–13819 (69 FR 60809, October 13, 2004).
(3) Airbus Service Bulletin A300–53–6123, (3) The following service information was skin, and wing skin, and corrective
Revision 01, dated December 18, 2001, which approved for IBR on March 10, 2016. action if necessary. We are issuing this
is not incorporated by reference in this AD. (i) Airbus Service Bulletin A300–53–0350, AD to detect and correct fatigue
(4) Airbus Service Bulletin A300–53–6123, Revision 03, dated July 26, 2007. cracking of the forward leg of the front
Revision 03, dated August 20, 2004, which is (ii) Airbus Service Bulletin A300–53–6123, spar lower chord, inspar skin, and wing
not incorporated by reference in this AD. Revision 06, dated September 28, 2011. skin common to the nacelle outboard
(5) Airbus Service Bulletin A300–53–6123, (4) The following service information was
Revision 04, dated April 25, 2008, which is
side load fitting, which could adversely
approved for IBR on November 17, 2004 (69
not incorporated by reference in this AD. affect the structural integrity of the
FR 60809, October 13, 2004).
(6) Airbus Service Bulletin A300–53–6123, wing.
(i) Airbus Service Bulletin A300–53–6123,
Revision 05, dated August 1, 2011, which is Revision 02, excluding Appendix 01, dated DATES: This AD is effective March 10,
not incorporated by reference in this AD. 2016.
November 12, 2002.
(o) Other FAA AD Provisions (ii) Reserved. The Director of the Federal Register
The following provisions also apply to this (5) For service information identified in approved the incorporation by reference
AD: this AD, contact Airbus SAS, Airworthiness of a certain publication listed in this AD
(1) Alternative Methods of Compliance Office—EAW, 1 Rond Point Maurice as of March 10, 2016.
(AMOCs): The Manager, International Bellonte, 31707 Blagnac Cedex, France; ADDRESSES: For service information
Branch, ANM–116, Transport Airplane telephone +33 5 61 93 36 96; fax +33 5 61 identified in this final rule, contact
Directorate, FAA, has the authority to 93 44 51; email account.airworth-eas@
approve AMOCs for this AD, if requested Boeing Commercial Airplanes,
airbus.com; Internet http://www.airbus.com.
using the procedures found in 14 CFR 39.19. Attention: Data & Services Management,
(6) You may view this service information
In accordance with 14 CFR 39.19, send your P.O. Box 3707, MC 2H–65, Seattle, WA
at the FAA, Transport Airplane Directorate,
request to your principal inspector or local 1601 Lind Avenue SW., Renton, WA. For
98124–2207; telephone 206–544–5000,
Flight Standards District Office, as
information on the availability of this extension 1; fax 206–766–5680; Internet
appropriate. If sending information directly https://www.myboeingfleet.com. You
to the International Branch, send it to ATTN: material at the FAA, call 425–227–1221.
(7) You may view this service information may view this referenced service
Dan Rodina, Aerospace Engineer, information at the FAA, Transport
International Branch, ANM–116, Transport that is incorporated by reference at the
Airplane Directorate, FAA, 1601 Lind National Archives and Records Airplane Directorate, 1601 Lind Avenue
Avenue SW., Renton, WA 98057–3356; Administration (NARA). For information on SW., Renton, WA. For information on
telephone 425–227–2125; fax 425–227–1149. the availability of this material at NARA, call the availability of this material at the
Information may be emailed to: 9-ANM-116- 202–741–6030, or go to: http:// FAA, call 425–227–1221. It is also
AMOC-REQUESTS@faa.gov. Before using www.archives.gov/federal-register/cfr/ibr- available on the Internet at http://
any approved AMOC, notify your appropriate locations.html. www.regulations.gov by searching for
asabaliauskas on DSK5VPTVN1PROD with RULES
principal inspector, or lacking a principal and locating Docket No. FAA–2015–
inspector, the manager of the local flight Issued in Renton, Washington, on
December 31, 2015. 1983.
standards district office/certificate holding
district office. The AMOC approval letter Phil Forde, Examining the AD Docket
must specifically reference this AD. Acting Manager, Transport Airplane
(2) Contacting the Manufacturer: As of the You may examine the AD docket on
Directorate, Aircraft Certification Service. the Internet at http://
effective date of this AD, for any requirement
in this AD to obtain corrective actions from [FR Doc. 2016–00379 Filed 2–3–16; 8:45 am] www.regulations.gov by searching for
a manufacturer, the action must be BILLING CODE 4910–13–P and locating Docket No. FAA–2015–
VerDate Sep<11>2014 16:15 Feb 03, 2016 Jkt 238001 PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 E:\FR\FM\04FER1.SGM 04FER1](https://thefederalregister.org/doc/81_FR_5916/page/1.svg)
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We have received no definitive data PART 39—AIRWORTHINESS (h) Repetitive Detailed Inspections and
that will enable us to provide cost DIRECTIVES Corrective Actions
estimates for the actions specified for For Group 2 and 3 airplanes identified in
the Group 1 airplane in this AD. ■ 1. The authority citation for part 39 Boeing Alert Service Bulletin 737–57A1323,
We also have received no definitive continues to read as follows: dated December 5, 2014: Except as provided
data that will enable us to provide cost by paragraph (j)(1) of this AD, at the
Authority: 49 U.S.C. 106(g), 40113, 44701.
applicable time specified in Table 1 of
estimates for the on-condition actions
§ 39.13 [Amended] paragraph 1.E., ‘‘Compliance,’’ of Boeing
specified in this AD. Alert Service Bulletin 737–57A1323, dated
■ 2. The FAA amends § 39.13 by adding December 5, 2014, do a detailed inspection
Authority for This Rulemaking
the following new airworthiness for cracks on the left and right wing front
Title 49 of the United States Code directive (AD): spar lower chord and inspar skin, and do all
specifies the FAA’s authority to issue applicable corrective actions, in accordance
2016–03–01 the Boeing Company:
rules on aviation safety. Subtitle I, Amendment 39–18388; Docket No. with the Accomplishment Instructions of
section 106, describes the authority of FAA–2015–1983; Directorate Identifier Boeing Alert Service Bulletin 737–57A1323,
the FAA Administrator. Subtitle VII: 2015–NM–020–AD. dated December 5, 2014, except as specified
Aviation Programs, describes in more in paragraph (j)(2) of this AD. Do all
(a) Effective Date applicable corrective actions before further
detail the scope of the Agency’s flight. Repeat the inspection thereafter at the
authority. This AD is effective March 10, 2016.
applicable interval specified in Table 1 of
We are issuing this rulemaking under (b) Affected ADs paragraph 1.E., ‘‘Compliance,’’ of Boeing
the authority described in Subtitle VII, None. Alert Service Bulletin 737–57A1323, dated
Part A, Subpart III, Section 44701: December 5, 2014, except in areas repaired in
‘‘General requirements.’’ Under that (c) Applicability accordance with the procedures specified in
section, Congress charges the FAA with (1) This AD applies to all The Boeing paragraph (k) of this AD.
promoting safe flight of civil aircraft in Company Model 737–100, –200, –200C,
(i) Repetitive High Frequency Eddy Current
–300, –400, and –500 series airplanes,
air commerce by prescribing regulations (HFEC) Inspections and Corrective Actions
certificated in any category.
for practices, methods, and procedures (2) Installation of Supplemental Type For Group 3 airplanes identified in Boeing
the Administrator finds necessary for Certificate (STC) ST01219SE (http:// Alert Service Bulletin 737–57A1323, dated
safety in air commerce. This regulation rgl.faa.gov/Regulatory_and_Guidance_ December 5, 2014: Except as provided by
is within the scope of that authority Library/rgstc.nsf/0/ebd1cec7b301293e86257 paragraph (j)(1) of this AD, at the applicable
because it addresses an unsafe condition cb30045557a/$FILE/ST01219SE.pdf) does time specified in Table 2 or Table 3 of
that is likely to exist or develop on not affect the ability to accomplish the paragraph 1.E., ‘‘Compliance,’’ of Boeing
products identified in this rulemaking actions required by this AD. Therefore, for Alert Service Bulletin 737–57A1323, dated
airplanes on which STC ST01219SE is December 5, 2014, do the actions specified in
action. installed, a ’’change in product’’ alternative paragraphs (i)(1) or (i)(2) of this AD. Repeat
Regulatory Findings method of compliance (AMOC) approval the inspection specified in either paragraph
request is not necessary to comply with the (i)(1) or (i)(2) of this AD thereafter at the
This AD will not have federalism requirements of 14 CFR 39.17. applicable interval specified in Table 2 or
implications under Executive Order Table 3 of paragraph 1.E., ‘‘Compliance,’’ of
(d) Subject
13132. This AD will not have a Boeing Alert Service Bulletin737–57A1323,
substantial direct effect on the States, on Air Transport Association (ATA) of dated December 5, 2014. While
the relationship between the national America Code 57, Wings. accomplishing the actions required by this
government and the States, or on the (e) Unsafe Condition paragraph, ensure that all applicable critical
distribution of power and design configuration control limitations are
This AD was prompted by a report of a complied with.
responsibilities among the various crack in the forward leg of the left front spar
(1) Do an HFEC open hole probe inspection
levels of government. lower chord and cracks on the lower wing
for cracks of the left and right wing nacelle
For the reasons discussed above, I skin at three fastener holes common to the
outboard side load fitting fastener holes
certify that this AD: nacelle outboard side load fitting. We are
common to the front spar lower chord and
(1) Is not a ‘‘significant regulatory issuing this AD to detect and correct fatigue
cracking of the forward leg of the front spar skin, and perform all applicable corrective
action’’ under Executive Order 12866, lower chord, inspar skin, and wing skin actions, in accordance with Part 2, Option 1
(2) Is not a ‘‘significant rule’’ under common to the nacelle outboard side load of the Accomplishment Instructions of
DOT Regulatory Policies and Procedures fitting, which could adversely affect the Boeing Alert Service Bulletin 737–57A1323,
(44 FR 11034, February 26, 1979), structural integrity of the wing. dated December 5, 2014, except as provided
(3) Will not affect intrastate aviation by paragraph (j)(2) of this AD. Do all
(f) Compliance applicable corrective actions before further
in Alaska, and
Comply with this AD within the flight.
(4) Will not have a significant (2) Do an HFEC surface probe inspection
compliance times specified, unless already
economic impact, positive or negative, for cracks in the wing inspar skin, and
done.
on a substantial number of small entities perform all applicable corrective actions, in
under the criteria of the Regulatory (g) Inspections and Corrective Actions for accordance with Part 2, Option 2 of the
Flexibility Act. Group 1 Airplanes Accomplishment Instructions of Boeing Alert
For Group 1 airplanes identified in Boeing Service Bulletin 737–57A1323, dated
List of Subjects in 14 CFR Part 39 Alert Service Bulletin 737–57A1323, dated December 5, 2014, except as provided by
Air transportation, Aircraft, Aviation December 5, 2014: Within 120 days after the paragraph (j)(2) of this AD. Do all applicable
asabaliauskas on DSK5VPTVN1PROD with RULES
safety, Incorporation by reference, effective date of this AD, do inspections of corrective actions before further flight.
Safety. the left and right wing front spar lower chord
and inspar skin, and the left and right wing (j) Exceptions to Service Information
nacelle outboard side load fitting fastener Specifications
Adoption of the Amendment
holes common to the front spar lower chord (1) Where paragraph 1.E., ‘‘Compliance,’’ of
Accordingly, under the authority and skin, and do all applicable corrective Boeing Alert Service Bulletin 737–57A1323,
delegated to me by the Administrator, actions, using a method approved in dated December 5, 2014, specifies a
the FAA amends 14 CFR part 39 as accordance with the procedures specified in compliance time ‘‘after the original issue date
follows: paragraph (k) of this AD. of this service bulletin,’’ this AD requires
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![5896 Federal Register / Vol. 81, No. 23 / Thursday, February 4, 2016 / Rules and Regulations
compliance within the specified compliance (i) The steps labeled as RC, including (5) You may view this service information
time ‘‘after the effective date of this AD.’’ substeps under an RC step and any figures that is incorporated by reference at the
(2) Although Boeing Alert Service Bulletin identified in an RC step, must be done to National Archives and Records
737–57A1323, dated December 5, 2014, comply with the AD. An AMOC is required Administration (NARA). For information on
specifies to contact Boeing for repair for any deviations to RC steps, including the availability of this material at NARA, call
instructions, and specifies that action as substeps and identified figures. 202–741–6030, or go to: http://
‘‘RC’’ (Required for Compliance), this AD (ii) Steps not labeled as RC may be www.archives.gov/federal-register/cfr/ibr-
requires repair before further flight using a deviated from using accepted methods in locations.html.
method approved in accordance with the accordance with the operator’s maintenance
procedures specified in paragraph (k) of this or inspection program without obtaining Issued in Renton, Washington, on January
AD. approval of an AMOC, provided the RC steps, 25, 2016.
including substeps and identified figures, can Michael Kaszycki,
(k) Alternative Methods of Compliance
still be done as specified, and the airplane Acting Manager, Transport Airplane
(AMOCs)
can be put back in an airworthy condition. Directorate, Aircraft Certification Service.
(1) The Manager, Los Angeles Aircraft
(l) Related Information [FR Doc. 2016–01827 Filed 2–3–16; 8:45 am]
Certification Office (ACO), FAA, has the
authority to approve AMOCs for this AD, if BILLING CODE 4910–13–P
For more information about this AD,
requested using the procedures found in 14 contact Jennifer Tsakoumakis, Aerospace
CFR 39.19. In accordance with 14 CFR 39.19, Engineer, Airframe Branch, ANM–120L,
send your request to your principal inspector FAA, Los Angeles ACO, 3960 Paramount DEPARTMENT OF TRANSPORTATION
or local Flight Standards District Office, as Boulevard, Lakewood, CA 90712–4137;
appropriate. If sending information directly phone: 562–627–5264; fax: 562–627–5210; Federal Aviation Administration
to the manager of the ACO, send it to the email: jennifer.tsakoumakis@faa.gov.
attention of the person identified in 14 CFR Parts 61 and 183
paragraph (l) of this AD. Information may be (m) Material Incorporated by Reference
emailed to: 9-ANM-LAACO-AMOC- (1) The Director of the Federal Register
Requests@faa.gov. approved the incorporation by reference [Docket No.: FAA–2010–1127; Amdt. Nos.
(2) Before using any approved AMOC, (IBR) of the service information listed in this 61–135 and 183–15]
notify your appropriate principal inspector, paragraph under 5 U.S.C. 552(a) and 1 CFR
or lacking a principal inspector, the manager part 51. RIN 2120–AJ42
of the local flight standards district office/ (2) You must use this service information
certificate holding district office. as applicable to do the actions required by Student Pilot Application
(3) An AMOC that provides an acceptable this AD, unless the AD specifies otherwise. Requirements
level of safety may be used for any repair, (i) Boeing Alert Service Bulletin 737–
modification, or alteration required by this 57A1323, dated December 5, 2014. Correction
AD if it is approved by the Boeing (ii) Reserved.
Commercial Airplanes Organization (3) For Boeing service information In rule document 2016–00199
Designation Authorization (ODA) that has identified in this AD, contact Boeing beginning on page 1292 in the issue of
been authorized by the Manager, Los Angeles Commercial Airplanes, Attention: Data & Tuesday, January 12, 2016, make the
ACO, to make those findings. To be Services Management, P.O. Box 3707, MC following correction:
approved, the repair method, modification 2H–65, Seattle, WA 98124–2207; telephone 1. On pages 1293–1294, table ‘‘B.
deviation, or alteration deviation must meet 206–544–5000, extension 1; fax 206–766– Student Pilot Application
the certification basis of the airplane, and the 5680; Internet https:// Requirements: Summary of Current,
approval must specifically refer to this AD. www.myboeingfleet.com.
(4) Except as required by paragraph (j)(2) (4) You may view this service information
Proposed, and Finalized Provisions’’ is
of this AD: For service information that at the FAA, Transport Airplane Directorate, corrected as set forth below.
contains steps that are labeled as Required 1601 Lind Avenue SW., Renton, WA. For B. Student Pilot Application
for Compliance (RC), the provisions of information on the availability of this Requirements: Summary of Current,
paragraphs (k)(4)(i) and (k)(4)(ii) apply. material at the FAA, call 425–227–1221. Proposed, and Finalized Provisions
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Document Created: 2016-02-04 00:30:45
Document Modified: 2016-02-04 00:30:45
| 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 10, 2016. | |
| Contact | Jennifer Tsakoumakis, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5264; fax: 562-627-5210; email: [email protected] | |
| FR Citation | 81 FR 5893 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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