83 FR 22351 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 83, Issue 94 (May 15, 2018)
Federal Aviation Administration
Federal Register Volume 83, Issue 94 (May 15, 2018)
| Page Range | 22351-22354 | |
| FR Document | 2018-09864 |
[Federal Register Volume 83, Number 94 (Tuesday, May 15, 2018)] [Rules and Regulations] [Pages 22351-22354] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2018-09864] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-9523; Product Identifier 2016-NM-134-AD; Amendment 39-19270; AD 2018-09-13] 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 reports indicating additional cracking in the inspar upper skin at wing buttock line (WBL) 157 and in the skin at two holes common to the rear spar in the same area, and rear spar web cracks were also noted on both wings. Subsequent inspections revealed that the right rear spar upper chord was almost completely severed and the left rear spar upper chord was completely severed. Additional reports identified cracking in the main landing gear (MLG) beam forward support fitting. This AD requires the installation of standard-size fasteners for a certain configuration and inspections for any crack in certain locations of the rear spar. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective June 19, 2018. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of June 19, 2018. 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; telephone 562-797-1717; internet https://www.myboeingfleet.com. You may view this service information at the FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206-231-3195. It is also available on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-9523. 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- 9523; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this final rule, the regulatory evaluation, any comments received, and other information. The address for Docket Operations (phone: 800-647- 5527) is Docket Operations, 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: Payman Soltani, Aerospace Engineer, Airframe Section, FAA, Los Angeles ACO Branch, 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5313; 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 January 5, 2017 (82 FR 1254). The NPRM was prompted by reports of cracking in locations outside the inspection area identified in AD 2014-12-13, Amendment 39-17874 (79 FR 39300, July 10, 2014) (``AD 2014-12-13''), in the inspar upper skin at WBL 157 and in the skin at two holes common to the rear spar in the same area, and in the rear spar web on both wings. Subsequent inspections revealed that the right rear spar upper chord was almost completely severed and the left rear spar upper chord was completely severed. Operators also reported cracking in the MLG beam forward support fitting. We subsequently issued a supplemental notice of proposed rulemaking (SNPRM) which was published in the Federal Register on August 11, 2017 (83 FR 37549) (``the first SNPRM''). The first SNPRM proposed to require expanding the inspection area, add applicable related investigative and corrective actions, and to terminate (rather than supersede) the requirements of AD 2014-12-13 after accomplishment of the initial inspections. We issued a second SNPRM which was published in the Federal Register on January 17, 2018 (83 FR 2378) (``the 2018 SNPRM''). The 2018 SNPRM proposed to require the installation of standard-size fasteners for a certain [[Page 22352]] configuration. We are issuing this AD to address cracking of the forward and aft support fittings for the main landing gear beam, and the rear spar upper chord and rear spar web in the area of rear spar station 224.14, which could grow and result in a fuel leak and possible fire. Comments We gave the public the opportunity to participate in developing this final rule. We have considered the comment received. Boeing supported the 2018 SNPRM. Conclusion We reviewed the relevant data, considered the comment received, and determined that air safety and the public interest require adopting this final rule as proposed, except for minor editorial changes. We have determined that these minor changes:Are consistent with the intent that was proposed in the 2018 SNPRM for addressing the unsafe condition; and Do not add any additional burden upon the public than was already proposed in the 2018 SNPRM. Related Service Information Under 1 CFR Part 51 We reviewed Boeing Alert Service Bulletin 737-57A1318, Revision 1, dated July 22, 2016. This service information describes procedures for repetitive high frequency eddy current (HFEC) open hole inspections for any cracking in the forward support fitting, the aft support fitting, the rear spar upper chord, and the rear spar web at the 12 fastener holes (locations 1-12). This service information also describes procedures for optional HFEC open hole inspections for any cracking in the forward support fitting, the aft support fitting, the rear spar upper chord, and the rear spar web, and HFEC surface inspections for any cracking in the rear spar upper chord and rear spar upper web, as applicable. This service information also describes procedures for related investigative and corrective actions. We also reviewed Boeing Alert Service Bulletin 737-57A1328, dated July 22, 2016. This service information describes procedures for repetitive eddy current inspections of the left and right wing for any cracking in the inspar upper skin and at the repair parts if applicable, 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 471 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 ---------------------------------------------------------------------------------------------------------------- HFEC open hole inspections....... 82 work-hours x $85 $0 $6,970 per $3,282,870 per per hour = $6,970 inspection cycle. inspection cycle. per inspection cycle. Eddy current inspection.......... 14 work-hours x $85 $0 $1,190 per $560,490 per per hour = $1,190 inspection cycle. inspection cycle. per inspection cycle. ---------------------------------------------------------------------------------------------------------------- Estimated Costs for Optional Actions ---------------------------------------------------------------------------------------------------------------- Action Labor cost Parts cost Cost per product ---------------------------------------------------------------------------------------------------------------- Inspection.............................. Up to 41 work-hours x $85 $0 Up to $1,641,435 per per hour = $3,485 per inspection cycle. inspection cycle. ---------------------------------------------------------------------------------------------------------------- We 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. This AD is issued in accordance with authority delegated by the Executive Director, Aircraft Certification Service, as authorized by FAA Order 8000.51C. In accordance with that order, issuance of ADs is normally a function of the Compliance and Airworthiness Division, but during this transition period, the Executive Director has delegated the authority to issue ADs applicable to transport category airplanes and associated appliances to the Director of the System Oversight Division. 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 [[Page 22353]] 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): 2018-09-13 The Boeing Company: Amendment 39-19270; Docket No. FAA- 2016-9523; Product Identifier 2016-NM-134-AD. (a) Effective Date This AD is effective June 19, 2018. (b) Affected ADs This AD affects AD 2014-12-13, Amendment 39-17874 (79 FR 39300, July 10, 2014) (``AD 2014-12-13''); and AD 2015-21-08, Amendment 39- 18301 (80 FR 65921, October 28, 2015) (``AD 2015-21-08''). (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 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 additional cracking in the inspar upper skin at wing buttock line 157 and in the skin at two holes common to the rear spar in the same area; rear spar web cracks were also noted on both wings. Subsequent inspections revealed that the right rear spar upper chord was almost completely severed and the left rear spar upper chord was completely severed. Additional reports identified cracking in the main landing gear (MLG) beam forward support fitting. We are issuing this AD to detect and correct cracking of the forward and aft support fittings for the MLG beam, and the rear spar upper chord and rear spar web in the area of rear spar station 224.14, which could grow and result in a fuel leak and possible fire. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Required Actions for Group 1 Airplanes (MLG Support Fittings and Rear Spar) For airplanes identified as Group 1 in Boeing Alert Service Bulletin 737-57A1318, Revision 1, dated July 22, 2016: At the applicable time specified in table 1 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-57A1318, Revision 1, dated July 22, 2016, do applicable inspections and corrective actions using a method approved in accordance with the procedures specified in paragraph (l) of this AD. (h) Required Actions for Groups 2-7 Airplanes (MLG Support Fittings and Rear Spar) For airplanes identified as Groups 2-7 in Boeing Alert Service Bulletin 737-57A1318, Revision 1, dated July 22, 2016: At the applicable time specified in table 2 through table 9 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-57A1318, Revision 1, dated July 22, 2016, except as required by paragraph (j)(3) of this AD, do high frequency eddy current (HFEC) open hole inspections for any cracking in the forward support fitting, the aft support fitting, the rear spar upper chord, and the rear spar web at the 12 fastener holes (locations 1-12); or HFEC open hole inspections for any cracking in the forward support fitting, the aft support fitting, the rear spar upper chord, and the rear spar web, and an HFEC surface inspection for any cracking in the rear spar upper chord and rear spar upper web; as applicable; and do all applicable related investigative and corrective actions; in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737-57A1318, Revision 1, dated July 22, 2016, except as provided by paragraph (h)(1) of this AD, and except as required by paragraphs (h)(2) and (j)(1) of this AD. Do all applicable related investigative and corrective actions before further flight. Thereafter, repeat the HFEC inspection at the applicable time specified in table 2 through table 9 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-57A1318, Revision 1, dated July 22, 2016. (1) Options provided in Boeing Alert Service Bulletin 737- 57A1318, Revision 1, dated July 22, 2016, for accomplishing the inspection are acceptable for the corresponding requirements in the introductory text of paragraph (h) of this AD, provided that the inspections are done at the applicable times in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-57A1318, Revision 1, dated July 22, 2016. (2) For Group 7, Configuration 1, airplanes identified in Boeing Alert Service Bulletin 737-57A1318, Revision 1, dated July 22, 2016: Install standard-size fasteners in accordance with figures 29 and 30 of Boeing Alert Service Bulletin 737-57A1318, Revision 1, dated July 22, 2016. If the existing fastener holes exceed the permitted hole diameter, repair before further flight using a method approved in accordance with the procedures specified in paragraph (l) of this AD. (i) Eddy Current Inspection (Inspar Upper Skin) For airplanes identified in Boeing Alert Service Bulletin 737- 57A1328, dated July 22, 2016: At the applicable time specified in table 1 and table 2 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-57A1328, dated July 22, 2016, except as required by paragraph (j)(2) of this AD, do an eddy current inspection of the left and right wings for any cracking in the inspar upper skin, and at the repair parts if installed, and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737-57A1328, dated July 22, 2016, except as required by paragraph (j)(1) of this AD. Do all related investigative and corrective actions before further flight. Thereafter, repeat the eddy current inspection at the applicable time specified in table 1 and table 2 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-57A1328, dated July 22, 2016. (j) Exceptions to the Service Information (1) If any cracking is found during any inspection required by this AD, and Boeing Alert Service Bulletin 737-57A1318, Revision 1, dated July 22, 2016; or Boeing Alert Service Bulletin 737-57A1328, dated July 22, 2016; 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. (2) Where Boeing Alert Service Bulletin 737-57A1328, dated July 22, 2016, specifies a compliance time ``after the Original Issue date of this service bulletin,'' this AD requires compliance within the specified compliance time after the effective date of this AD. (3) Where Boeing Alert Service Bulletin 737-57A1318, Revision 1, dated July 22, 2016, specifies a compliance time ``after the Revision 1 date of this service bulletin, whichever occurs later,'' this AD requires compliance within the specified compliance time after the effective date of this AD. (k) Terminating Action (1) Accomplishing the initial inspections and applicable related investigative and corrective actions required by paragraphs (g), (h), and (i) of this AD, as applicable, terminates all requirements of AD 2015-21-08. (2) Accomplishing the initial inspections and applicable related investigative and corrective actions required by paragraphs (g) and (h) of this AD, as applicable, terminates all requirements of AD 2014-12-13. (l) Alternative Methods of Compliance (AMOCs) (1) The Manager, Los Angeles ACO Branch, FAA, has the authority to approve AMOCs [[Page 22354]] 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 certification office, send it to the attention of the person identified in paragraph (m) 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 Branch, 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 AD 2014-12-13 are approved as AMOCs for the corresponding provisions of paragraphs (g) and (h) of this AD. (5) Except as required by paragraph (j)(1) of this AD: For service information that contains steps that are labeled as Required for Compliance (RC), the provisions of paragraphs (l)(5)(i) and (l)(5)(ii) of this AD 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. If a step or sub-step is labeled ``RC Exempt,'' then the RC requirement is removed from that step or sub-step. 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. (m) Related Information For more information about this AD, contact Payman Soltani, Aerospace Engineer, Airframe Section, FAA, Los Angeles ACO Branch, 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627- 5313; fax: 562-627-5210; email: [email protected]. (n) 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 737-57A1318, Revision 1, dated July 22, 2016. (ii) Boeing Alert Service Bulletin 737-57A1328, dated July 22, 2016. (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; telephone 562-797-1717; internet https://www.myboeingfleet.com. (4) You may view this service information at the FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206-231-3195. (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 Des Moines, Washington, on April 27, 2018. Michael Kaszycki, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2018-09864 Filed 5-14-18; 8:45 am] BILLING CODE 4910-13-P
![Federal Register / Vol. 83, No. 94 / Tuesday, May 15, 2018 / Rules and Regulations 22351
(816) 329–4144; fax: (816) 329–4090; email: DEPARTMENT OF TRANSPORTATION www.regulations.gov by searching for
mike.kiesov@faa.gov. Before using any and locating Docket No. FAA–2016–
approved AMOC on any airplane to which Federal Aviation Administration 9523; or in person at Docket Operations
the AMOC applies, notify your appropriate between 9 a.m. and 5 p.m., Monday
principal inspector (PI) in the FAA Flight 14 CFR Part 39 through Friday, except Federal holidays.
Standards District Office (FSDO), or lacking The AD docket contains this final rule,
[Docket No. FAA–2016–9523; Product
a PI, your local FSDO. the regulatory evaluation, any
Identifier 2016–NM–134–AD; Amendment
(2) Contacting the Manufacturer: For any 39–19270; AD 2018–09–13] comments received, and other
requirement in this AD to obtain corrective information. The address for Docket
actions from a manufacturer, the action must RIN 2120–AA64
Operations (phone: 800–647–5527) is
be accomplished using a method approved Docket Operations, U.S. Department of
by the Manager, Standards Office, FAA; or Airworthiness Directives; The Boeing
Company Airplanes Transportation, Docket Operations, M–
the Civil Aviation Authority of New Zealand 30, West Building Ground Floor, Room
(CAA). AGENCY: Federal Aviation W12–140, 1200 New Jersey Avenue SE,
(h) Related Information Administration (FAA), DOT. Washington, DC 20590.
Refer to the MCAI by the CAA, AD DCA/ ACTION: Final rule. FOR FURTHER INFORMATION CONTACT:
750XL/22A, dated February 28, 2018; and for Payman Soltani, Aerospace Engineer,
SUMMARY: We are adopting a new Airframe Section, FAA, Los Angeles
related information. You may examine the
MCAI on the internet at http://
airworthiness directive (AD) for all The ACO Branch, 3960 Paramount
www.regulations.gov by searching for and
Boeing Company Model 737–100, –200, Boulevard, Lakewood, CA 90712–4137;
locating Docket No. FAA–2018–0372.
–200C, –300, –400, and –500 series phone: 562–627–5313; fax: 562–627–
airplanes. This AD was prompted by 5210; email: payman.soltani@faa.gov.
(i) Material Incorporated by Reference reports indicating additional cracking in
SUPPLEMENTARY INFORMATION:
(1) The Director of the Federal Register the inspar upper skin at wing buttock
approved the incorporation by reference line (WBL) 157 and in the skin at two Discussion
(IBR) of the service information listed in this holes common to the rear spar in the We issued a notice of proposed
paragraph under 5 U.S.C. 552(a) and 1 CFR same area, and rear spar web cracks rulemaking (NPRM) to amend 14 CFR
part 51. were also noted on both wings. part 39 by adding an AD that would
(2) You must use this service information Subsequent inspections revealed that apply to all The Boeing Company Model
as applicable to do the actions required by the right rear spar upper chord was 737–100, –200, –200C, –300, –400, and
this AD, unless the AD specifies otherwise. almost completely severed and the left –500 series airplanes. The NPRM
(i) Pacific Aerospace Mandatory Service rear spar upper chord was completely published in the Federal Register on
Bulletin PACSB/XL/083, Issue 2, dated severed. Additional reports identified January 5, 2017 (82 FR 1254). The
January 16, 2018. cracking in the main landing gear (MLG) NPRM was prompted by reports of
(ii) Reserved. beam forward support fitting. This AD cracking in locations outside the
(3) For service information identified in requires the installation of standard-size inspection area identified in AD 2014–
this AD, contact Pacific Aerospace Limited, fasteners for a certain configuration and 12–13, Amendment 39–17874 (79 FR
Airport Road, Hamilton, Private Bag 3027, inspections for any crack in certain 39300, July 10, 2014) (‘‘AD 2014–12–
Hamilton 3240, New Zealand; phone: +64 locations of the rear spar. We are issuing 13’’), in the inspar upper skin at WBL
7843 6144; fax: +64 843 6134; email: pacific@ this AD to address the unsafe condition 157 and in the skin at two holes
aerospace.co.nz; internet: on these products. common to the rear spar in the same
www.aerospace.co.nz. DATES: This AD is effective June 19,
(4) You may view this service information
area, and in the rear spar web on both
2018. wings. Subsequent inspections revealed
at the FAA, Policy and Innovation Division,
The Director of the Federal Register that the right rear spar upper chord was
901 Locust, Kansas City, Missouri 64106. For
approved the incorporation by reference almost completely severed and the left
information on the availability of this
of certain publications listed in this AD rear spar upper chord was completely
material at the FAA, call (816) 329–4148. It
as of June 19, 2018. severed. Operators also reported
is also available on the internet at http://
www.regulations.gov by searching for ADDRESSES: For service information cracking in the MLG beam forward
locating Docket No. FAA–2018–0372. identified in this final rule, contact support fitting.
(5) You may view this service information Boeing Commercial Airplanes, We subsequently issued a
that is incorporated by reference at the Attention: Contractual & Data Services supplemental notice of proposed
National Archives and Records (C&DS), 2600 Westminster Blvd., MC rulemaking (SNPRM) which was
Administration (NARA). For information on 110–SK57, Seal Beach, CA 90740; published in the Federal Register on
the availability of this material at NARA, call telephone 562–797–1717; internet August 11, 2017 (83 FR 37549) (‘‘the
202–741–6030, or go to: http:// https://www.myboeingfleet.com. You first SNPRM’’). The first SNPRM
www.archives.gov/federal-register/cfr/ibr- may view this service information at the proposed to require expanding the
locations.html. FAA, Transport Standards Branch, 2200 inspection area, add applicable related
South 216th St., Des Moines, WA. For investigative and corrective actions, and
Issued in Kansas City, Missouri, on May 4,
information on the availability of this to terminate (rather than supersede) the
2018.
material at the FAA, call 206–231–3195. requirements of AD 2014–12–13 after
Melvin J. Johnson, It is also available on the internet at accomplishment of the initial
Deputy Director, Policy & Innovation Division, inspections.
daltland on DSKBBV9HB2PROD with RULES
http://www.regulations.gov by searching
Aircraft Certification Service. for and locating Docket No. FAA–2016– We issued a second SNPRM which
[FR Doc. 2018–10025 Filed 5–14–18; 8:45 am] 9523. was published in the Federal Register
BILLING CODE 4910–13–P on January 17, 2018 (83 FR 2378) (‘‘the
Examining the AD Docket 2018 SNPRM’’). The 2018 SNPRM
You may examine the AD docket on proposed to require the installation of
the internet at http:// standard-size fasteners for a certain
VerDate Sep<11>2014 16:07 May 14, 2018 Jkt 244001 PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 E:\FR\FM\15MYR1.SGM 15MYR1](https://thefederalregister.org/doc/83_FR_22445/page/1.svg)
![Federal Register / Vol. 83, No. 94 / Tuesday, May 15, 2018 / Rules and Regulations 22353
under the criteria of the Regulatory beam, and the rear spar upper chord and rear Alert Service Bulletin 737–57A1318,
Flexibility Act. spar web in the area of rear spar station Revision 1, dated July 22, 2016. If the
224.14, which could grow and result in a fuel existing fastener holes exceed the permitted
List of Subjects in 14 CFR Part 39 leak and possible fire. hole diameter, repair before further flight
Air transportation, Aircraft, Aviation using a method approved in accordance with
(f) Compliance
the procedures specified in paragraph (l) of
safety, Incorporation by reference, Comply with this AD within the this AD.
Safety. compliance times specified, unless already
done. (i) Eddy Current Inspection (Inspar Upper
Adoption of the Amendment Skin)
Accordingly, under the authority (g) Required Actions for Group 1 Airplanes
For airplanes identified in Boeing Alert
(MLG Support Fittings and Rear Spar)
delegated to me by the Administrator, Service Bulletin 737–57A1328, dated July 22,
the FAA amends 14 CFR part 39 as For airplanes identified as Group 1 in 2016: At the applicable time specified in
Boeing Alert Service Bulletin 737–57A1318, table 1 and table 2 of paragraph 1.E.,
follows:
Revision 1, dated July 22, 2016: At the ‘‘Compliance,’’ of Boeing Alert Service
applicable time specified in table 1 of Bulletin 737–57A1328, dated July 22, 2016,
PART 39—AIRWORTHINESS
paragraph 1.E., ‘‘Compliance,’’ of Boeing except as required by paragraph (j)(2) of this
DIRECTIVES Alert Service Bulletin 737–57A1318, AD, do an eddy current inspection of the left
Revision 1, dated July 22, 2016, do applicable and right wings for any cracking in the inspar
■ 1. The authority citation for part 39 inspections and corrective actions using a upper skin, and at the repair parts if
continues to read as follows: method approved in accordance with the installed, and do all applicable related
Authority: 49 U.S.C. 106(g), 40113, 44701. procedures specified in paragraph (l) of this investigative and corrective actions, in
AD. accordance with the Accomplishment
§ 39.13 [Amended] Instructions of Boeing Alert Service Bulletin
(h) Required Actions for Groups 2–7
■ 2. The FAA amends § 39.13 by adding Airplanes (MLG Support Fittings and Rear 737–57A1328, dated July 22, 2016, except as
the following new airworthiness Spar) required by paragraph (j)(1) of this AD. Do all
related investigative and corrective actions
directive (AD): For airplanes identified as Groups 2–7 in before further flight. Thereafter, repeat the
2018–09–13 The Boeing Company: Boeing Alert Service Bulletin 737–57A1318, eddy current inspection at the applicable
Amendment 39–19270; Docket No. Revision 1, dated July 22, 2016: At the time specified in table 1 and table 2 of
FAA–2016–9523; Product Identifier applicable time specified in table 2 through paragraph 1.E., ‘‘Compliance,’’ of Boeing
2016–NM–134–AD. table 9 of paragraph 1.E., ‘‘Compliance,’’ of Alert Service Bulletin 737–57A1328, dated
Boeing Alert Service Bulletin 737–57A1318, July 22, 2016.
(a) Effective Date Revision 1, dated July 22, 2016, except as
This AD is effective June 19, 2018. required by paragraph (j)(3) of this AD, do (j) Exceptions to the Service Information
high frequency eddy current (HFEC) open (1) If any cracking is found during any
(b) Affected ADs hole inspections for any cracking in the inspection required by this AD, and Boeing
This AD affects AD 2014–12–13, forward support fitting, the aft support Alert Service Bulletin 737–57A1318,
Amendment 39–17874 (79 FR 39300, July 10, fitting, the rear spar upper chord, and the Revision 1, dated July 22, 2016; or Boeing
2014) (‘‘AD 2014–12–13’’); and AD 2015–21– rear spar web at the 12 fastener holes Alert Service Bulletin 737–57A1328, dated
08, Amendment 39–18301 (80 FR 65921, (locations 1–12); or HFEC open hole July 22, 2016; specifies to contact Boeing for
October 28, 2015) (‘‘AD 2015–21–08’’). inspections for any cracking in the forward appropriate action: Before further flight,
support fitting, the aft support fitting, the rear repair using a method approved in
(c) Applicability
spar upper chord, and the rear spar web, and accordance with the procedures specified in
(1) This AD applies to all The Boeing an HFEC surface inspection for any cracking paragraph (l) of this AD.
Company Model 737–100, –200, –200C, in the rear spar upper chord and rear spar (2) Where Boeing Alert Service Bulletin
–300, –400, and –500 series airplanes, upper web; as applicable; and do all 737–57A1328, dated July 22, 2016, specifies
certificated in any category. applicable related investigative and a compliance time ‘‘after the Original Issue
(2) Installation of Supplemental Type corrective actions; in accordance with the date of this service bulletin,’’ this AD
Certificate (STC) ST01219SE does not affect Accomplishment Instructions of Boeing Alert requires compliance within the specified
the ability to accomplish the actions required Service Bulletin 737–57A1318, Revision 1, compliance time after the effective date of
by this AD. Therefore, for airplanes on which dated July 22, 2016, except as provided by this AD.
STC ST01219SE is installed, a ‘‘change in paragraph (h)(1) of this AD, and except as (3) Where Boeing Alert Service Bulletin
product’’ alternative method of compliance required by paragraphs (h)(2) and (j)(1) of this 737–57A1318, Revision 1, dated July 22,
(AMOC) approval request is not necessary to AD. Do all applicable related investigative 2016, specifies a compliance time ‘‘after the
comply with the requirements of 14 CFR and corrective actions before further flight. Revision 1 date of this service bulletin,
39.17. Thereafter, repeat the HFEC inspection at the whichever occurs later,’’ this AD requires
applicable time specified in table 2 through compliance within the specified compliance
(d) Subject table 9 of paragraph 1.E., ‘‘Compliance,’’ of time after the effective date of this AD.
Air Transport Association (ATA) of Boeing Alert Service Bulletin 737–57A1318,
America Code 57, Wings. Revision 1, dated July 22, 2016. (k) Terminating Action
(1) Options provided in Boeing Alert (1) Accomplishing the initial inspections
(e) Unsafe Condition
Service Bulletin 737–57A1318, Revision 1, and applicable related investigative and
This AD was prompted by reports of dated July 22, 2016, for accomplishing the corrective actions required by paragraphs (g),
additional cracking in the inspar upper skin inspection are acceptable for the (h), and (i) of this AD, as applicable,
at wing buttock line 157 and in the skin at corresponding requirements in the terminates all requirements of AD 2015–21–
two holes common to the rear spar in the introductory text of paragraph (h) of this AD, 08.
same area; rear spar web cracks were also provided that the inspections are done at the (2) Accomplishing the initial inspections
noted on both wings. Subsequent inspections applicable times in paragraph 1.E., and applicable related investigative and
revealed that the right rear spar upper chord ‘‘Compliance,’’ of Boeing Alert Service corrective actions required by paragraphs (g)
daltland on DSKBBV9HB2PROD with RULES
was almost completely severed and the left Bulletin 737–57A1318, Revision 1, dated July and (h) of this AD, as applicable, terminates
rear spar upper chord was completely 22, 2016. all requirements of AD 2014–12–13.
severed. Additional reports identified (2) For Group 7, Configuration 1, airplanes
cracking in the main landing gear (MLG) identified in Boeing Alert Service Bulletin (l) Alternative Methods of Compliance
beam forward support fitting. We are issuing 737–57A1318, Revision 1, dated July 22, (AMOCs)
this AD to detect and correct cracking of the 2016: Install standard-size fasteners in (1) The Manager, Los Angeles ACO Branch,
forward and aft support fittings for the MLG accordance with figures 29 and 30 of Boeing FAA, has the authority to approve AMOCs
VerDate Sep<11>2014 16:07 May 14, 2018 Jkt 244001 PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 E:\FR\FM\15MYR1.SGM 15MYR1](https://thefederalregister.org/doc/83_FR_22445/page/3.svg)
![22354 Federal Register / Vol. 83, No. 94 / Tuesday, May 15, 2018 / Rules and Regulations
for this AD, if requested using the procedures (3) For Boeing service information damage (WFD). This AD requires
found in 14 CFR 39.19. In accordance with identified in this AD, contact Boeing modifying the holes of the upper cleat
14 CFR 39.19, send your request to your Commercial Airplanes, Attention: to upper stringer attachments at certain
principal inspector or local Flight Standards Contractual & Data Services (C&DS), 2600
District Office, as appropriate. If sending Westminster Blvd., MC 110–SK57, Seal
areas of the left- and right-hand wings.
information directly to the manager of the Beach, CA 90740; telephone 562–797–1717; We are issuing this AD to address the
certification office, send it to the attention of internet https://www.myboeingfleet.com. unsafe condition on these products.
the person identified in paragraph (m) of this (4) You may view this service information DATES: This AD is effective June 11,
AD. Information may be emailed to: 9-ANM- at the FAA, Transport Standards Branch, 2018.
LAACO-AMOC-Requests@faa.gov. 2200 South 216th St., Des Moines, WA. For The Director of the Federal Register
(2) Before using any approved AMOC, information on the availability of this approved the incorporation by reference
notify your appropriate principal inspector, material at the FAA, call 206–231–3195.
or lacking a principal inspector, the manager of a certain publication listed in this AD
(5) You may view this service information
of the local flight standards district office/ that is incorporated by reference at the as of June 11, 2018.
certificate holding district office. National Archives and Records ADDRESSES: For service information
(3) An AMOC that provides an acceptable Administration (NARA). For information on identified in this final rule, contact
level of safety may be used for any repair, the availability of this material at NARA, call Airbus, Airworthiness Office—EIAS, 1
modification, or alteration required by this 202–741–6030, or go to: http:// Rond Point Maurice Bellonte, 31707
AD if it is approved by the Boeing www.archives.gov/federal-register/cfr/ibr-
Commercial Airplanes Organization
Blagnac Cedex, France; telephone: +33 5
locations.html. 61 93 36 96; fax: +33 5 61 93 44 51;
Designation Authorization (ODA) that has
been authorized by the Manager, Los Angeles Issued in Des Moines, Washington, on email: account.airworth-eas@
ACO Branch, to make those findings. To be April 27, 2018. airbus.com; internet: http://
approved, the repair method, modification Michael Kaszycki, www.airbus.com. You may view this
deviation, or alteration deviation must meet Acting Director, System Oversight Division, referenced service information at the
the certification basis of the airplane, and the Aircraft Certification Service. FAA, Transport Standards Branch, 2200
approval must specifically refer to this AD. South 216th St., Des Moines, WA. For
[FR Doc. 2018–09864 Filed 5–14–18; 8:45 am]
(4) AMOCs approved previously for AD
2014–12–13 are approved as AMOCs for the BILLING CODE 4910–13–P information on the availability of this
corresponding provisions of paragraphs (g) material at the FAA, call 206–231–3195.
and (h) of this AD. It is also available on the internet at
(5) Except as required by paragraph (j)(1) DEPARTMENT OF TRANSPORTATION http://www.regulations.gov by searching
of this AD: For service information that for and locating Docket No. FAA–2017–
contains steps that are labeled as Required Federal Aviation Administration 1245.
for Compliance (RC), the provisions of
paragraphs (l)(5)(i) and (l)(5)(ii) of this AD 14 CFR Part 39 Examining the AD Docket
apply. You may examine the AD docket on
(i) The steps labeled as RC, including [Docket No. FAA–2017–1245; Product
Identifier 2017–NM–099–AD; Amendment the internet at http://
substeps under an RC step and any figures
identified in an RC step, must be done to 39–19266; AD 2018–09–09] www.regulations.gov by searching for
comply with the AD. If a step or sub-step is and locating Docket No. FAA–2017–
RIN 2120–AA64 1245; or in person at the Docket
labeled ‘‘RC Exempt,’’ then the RC
requirement is removed from that step or Management Facility between 9 a.m.
Airworthiness Directives; Airbus
sub-step. An AMOC is required for any and 5 p.m., Monday through Friday,
deviations to RC steps, including substeps Airplanes Republication
except Federal holidays. The AD docket
and identified figures. Republication contains this AD, the regulatory
(ii) Steps not labeled as RC may be evaluation, any comments received, and
deviated from using accepted methods in Editorial Note: Rule document 2018–09280
accordance with the operator’s maintenance other information. The street address for
was originally published on pages 19925 the Docket Office (telephone 800–647–
or inspection program without obtaining through 19928 in the issue of Monday, May
approval of an AMOC, provided the RC steps, 5527) is Docket Management Facility,
7, 2018. In that publication, on page 19927,
including substeps and identified figures, can U.S. Department of Transportation,
in Table 1 to paragraph (g) of this AD, the last
still be done as specified, and the airplane
line was omitted from the table. The Docket Operations, M–30, West
can be put back in an airworthy condition. Building Ground Floor, Room W12–140,
corrected document is published here in its
(m) Related Information entirety. 1200 New Jersey Avenue SE,
For more information about this AD, AGENCY: Federal Aviation Washington, DC 20590.
contact Payman Soltani, Aerospace Engineer, Administration (FAA), Department of FOR FURTHER INFORMATION CONTACT:
Airframe Section, FAA, Los Angeles ACO Transportation (DOT). Sanjay Ralhan, Aerospace Engineer,
Branch, 3960 Paramount Boulevard,
ACTION: Final rule. International Section, Transport
Lakewood, CA 90712–4137; phone: 562–627– Standards Branch, FAA, 2200 South
5313; fax: 562–627–5210; email: SUMMARY: We are adopting a new 216th St, Des Moines, WA 98198;
payman.soltani@faa.gov. airworthiness directive (AD) for certain telephone and fax 206–231–3223.
(n) Material Incorporated by Reference Airbus Model A318 series airplanes and SUPPLEMENTARY INFORMATION:
(1) The Director of the Federal Register Model A319 series airplanes; all Model
approved the incorporation by reference A320–211, –212, –214, –216, –231, Discussion
(IBR) of the service information listed in this –232, and –233 airplanes; and all Model We issued a notice of proposed
paragraph under 5 U.S.C. 552(a) and 1 CFR A321–111, –112, –131, –211, –212, rulemaking (NPRM) to amend 14 CFR
part 51. –213, –231, and –232 airplanes. This AD part 39 by adding an AD that would
daltland on DSKBBV9HB2PROD with RULES
(2) You must use this service information was prompted by an evaluation by the apply to certain Airbus Model A318
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
design approval holder (DAH) series airplanes and Model A319 series
(i) Boeing Alert Service Bulletin 737– indicating that the holes of the upper airplanes; all Model A320–211, –212,
57A1318, Revision 1, dated July 22, 2016. cleat to upper stringer attachments at –214, –216, –231, –232, and –233
(ii) Boeing Alert Service Bulletin 737– certain areas of the left- and right-hand airplanes; and all Model A321–111,
57A1328, dated July 22, 2016. wings are subject to widespread fatigue –112, –131, –211, –212, –213, –231, and
VerDate Sep<11>2014 16:07 May 14, 2018 Jkt 244001 PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 E:\FR\FM\15MYR1.SGM 15MYR1](https://thefederalregister.org/doc/83_FR_22445/page/4.svg)
Document Created: 2018-05-15 00:34:10
Document Modified: 2018-05-15 00:34:10
| 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 June 19, 2018. | |
| Contact | Payman Soltani, Aerospace Engineer, Airframe Section, FAA, Los Angeles ACO Branch, 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5313; fax: 562-627- 5210; email: [email protected] | |
| FR Citation | 83 FR 22351 | |
| 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