Airworthiness Directives; The Boeing Company Airplanes, 26331-26334 [2019-11790]

Download as PDF 26331 Rules and Regulations Federal Register Vol. 84, No. 109 Thursday, June 6, 2019 This section of the FEDERAL REGISTER contains regulatory documents having general applicability and legal effect, most of which are keyed to and codified in the Code of Federal Regulations, which is published under 50 titles pursuant to 44 U.S.C. 1510. The Code of Federal Regulations is sold by the Superintendent of Documents. DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2018–1004; Product Identifier 2018–NM–106–AD; Amendment 39–19642; AD 2019–10–03] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: 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 of cracks caused by corrosion of the edge of the bore of the spot face and corrosion of the lug bore of certain sidestrut support fitting lugs. This AD requires repetitive detailed inspections of the left and right side-strut support fitting lugs with bushings installed for any corrosion, any crack, or any severed lug; repetitive detailed and high frequency eddy current (HFEC) inspections of the left and right sidestrut support fitting lugs with bushings removed for any corrosion or any crack; and applicable on-condition actions. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective July 11, 2019. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of July 11, 2019. ADDRESSES: For service information identified in this final rule, contact Boeing Commercial Airplanes, Attention: Contractual & Data Services (C&DS), 2600 Westminster Blvd., MC 110–SK57, Seal Beach, CA 90740–5600; phone: 562–797–1717; internet: https:// www.myboeingfleet.com. You may view khammond on DSKBBV9HB2PROD with RULES SUMMARY: VerDate Sep<11>2014 15:44 Jun 05, 2019 Jkt 247001 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 https://www.regulations.gov by searching for and locating Docket No. FAA–2018– 1004. Examining the AD Docket You may examine the AD docket on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2018– 1004; 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 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: George Garrido, Aerospace Engineer, Airframe Section, FAA, Los Angeles ACO Branch, 3960 Paramount Boulevard, Lakewood, CA 90712–4137; phone: 562–627–5232; fax: 562–627– 5210; email: george.garrido@faa.gov. We are issuing this AD to address cracks caused by corrosion, which could result in sudden loss of the side-strut support fitting joint and main landing gear attachment to the airplane, resulting in the collapse of a main landing gear. Comments We gave the public the opportunity to participate in developing this final rule. The following presents the comments received on the NPRM and the FAA’s response to each comment. Effect of Winglets on Accomplishment of the Proposed Actions Aviation Partners Boeing stated that accomplishing Supplemental Type Certificate (STC) ST01219SE does not affect the actions specified in the proposed AD. We concur with the commenter. We have redesignated paragraph (c) of the proposed AD as paragraph (c)(1) of this AD and added paragraph (c)(2) to this AD to state that installation of 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. Discussion Request To Change Format of Paragraphs (g) and (h) of the Proposed AD 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 December 6, 2018 (83 FR 62741). The NPRM was prompted by reports of cracks caused by corrosion of the edge of the bore of the spot face and corrosion of the lug bore of certain sidestrut support fitting lugs. The NPRM proposed to require repetitive detailed inspections of the left and right sidestrut support fitting lugs with bushings installed for any corrosion, any crack, or any severed lug; repetitive detailed and HFEC inspections of the left and right side-strut support fitting lugs with bushings removed for any corrosion or any crack; and applicable on-condition actions. Boeing requested that we eliminate paragraph (h) of the proposed AD and incorporate the information as paragraph (g)(2) of this AD. Boeing pointed out that the title of paragraph (g) of the proposed AD would change to ‘‘Required Actions,’’ and that paragraphs (g)(1) and (g)(2) of this AD would apply to Group 7 and Groups 1 through 6, respectively. Boeing stated that this request is for consistency with previous ADs for Boeing airplanes. We disagree that elimination of paragraph (h) of the proposed AD and incorporating the information as paragraph (g)(2) of this AD is necessary. Over time we have used both formats, but most recently we have been using the format that was utilized in the NPRM. We do not find that there is a difference in clarity of the required actions. We also find that the requested change does not affect the requirements SUPPLEMENTARY INFORMATION: PO 00000 Frm 00001 Fmt 4700 Sfmt 4700 E:\FR\FM\06JNR1.SGM 06JNR1 26332 Federal Register / Vol. 84, No. 109 / Thursday, June 6, 2019 / Rules and Regulations of this final rule in this case. We have not changed this AD in this regard. Request To Clarify ACO Branch Authority Boeing requested that we clarify the ACO branch that has the authority to approve AMOCs for this group of airplanes. Boeing pointed out that previous final rules for The Boeing Company Model 737–100, –200, –200C, –300, –400, and –500 series airplanes have identified The Manager, Los Angeles ACO Branch, FAA, had the authority to approve AMOCs, even when the service bulletin was submitted for approval through the Seattle ACO Branch. Additionally, Boeing pointed out that previous ADs for The Boeing Company Model 737–100, –200, –200C, –300, –400, and –500 series airplanes identified a Los Angeles ACO Branch specialist in the ‘‘Related Information’’ paragraph of the proposed rule, even when the service bulletin was submitted for approval through the Seattle ACO Branch. We agree that clarification is necessary. Normally, in NPRMs for The Boeing Company Model 737–100, –200, –200C, –300, –400, and –500 series airplanes, we include the Manager, Los Angeles ACO Branch, as the designated approval authority for AMOCs. We have updated paragraph (j) of this AD to specify The Manager, Los Angeles ACO Branch. The Seattle ACO Branch is responsible during drafting of the NPRM and final rule of an AD for The Boeing Company Model 737–100, –200, –200C, –300, –400, and –500 series airplanes. After publication of the final rule, responsibility for the product is transferred to the Los Angeles ACO Branch. Therefore, when we draft the final rule of an AD for The Boeing Company Model 737–100, –200, –200C, –300, –400, and –500 series airplanes, we also specify a specialist from the Los Angeles ACO Branch. We have updated paragraph (k) of this AD to include the responsible specialist from the Los Angeles ACO Branch. Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this final rule 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 addressing 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 final rule. Related Service Information Under 1 CFR Part 51 We reviewed Boeing Service Bulletin 737–53–1246, Revision 1, dated May 30, 2018. This service information describes procedures for repetitive detailed inspections of the left and right sidestrut support fitting lugs at body station (BS) 685 with bushings installed for any corrosion, any crack, or any severed lug; repetitive detailed and HFEC inspections of the left and right sidestrut support fitting lugs at BS 685 with bushings removed for any corrosion or any crack; and applicable on-condition actions. On-condition actions include, among other things, inspections, corrosion removal, and a preventative modification. Doing the repetitive detailed and HFEC inspections of the side-strut support fitting lugs at BS 685 with bushings removed terminates the repetitive detailed inspections of the side-strut support fitting lugs at BS 685 with bushings installed. 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 302 airplanes of U.S. registry. We estimate the following costs to comply with this AD: ESTIMATED COSTS FOR REQUIRED ACTIONS Action Labor cost Repetitive detailed inspection of left and right side lugs with bushings installed. Repetitive detailed and HFEC inspections of left and right side lugs with bushings removed. 17 work-hours × $85 per hour = $1,445 per inspection cycle. 29 work-hours × $85 per hour = $2,465 per inspection cycle. We estimate the following costs to do any necessary on-condition actions that would be required. We have no way of Cost per product Cost on U.S. operators $1,445 per inspection cycle. $2,465 per inspection cycle. $436,390 per inspection cycle. $744,430 per inspection cycle. Parts cost $0 0 determining the number of aircraft that might need these on-condition actions: khammond on DSKBBV9HB2PROD with RULES ESTIMATED COSTS OF ON-CONDITION ACTIONS Labor cost Parts cost Cost per product Up to 18 work-hour × $85 per hour = $1,530 per inspection cycle ........ Unknown ........................................ Up to $1,530 per inspection cycle. We have received no definitive data that would enable us to provide parts cost estimates for the on-condition inspections and repairs specified in this AD. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue VerDate Sep<11>2014 15:44 Jun 05, 2019 Jkt 247001 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, PO 00000 Frm 00002 Fmt 4700 Sfmt 4700 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 E:\FR\FM\06JNR1.SGM 06JNR1 Federal Register / Vol. 84, No. 109 / Thursday, June 6, 2019 / Rules and Regulations 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 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 1. The authority citation for part 39 continues to read as follows: khammond on DSKBBV9HB2PROD with RULES ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ 2019–10–03 The Boeing Company: Amendment 39–19642; Docket No. VerDate Sep<11>2014 15:44 Jun 05, 2019 Jkt 247001 FAA–2018–1004; Product Identifier 2018–NM–106–AD. (a) Effective Date This AD is effective July 11, 2019. (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 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 53, Fuselage. (e) Unsafe Condition This AD was prompted by reports of cracks caused by corrosion of the edge of the bore of the spot face and corrosion of the lug bore of the body station (BS) 685 side-strut support fitting lugs. We are issuing this AD to address cracks caused by corrosion, which could result in sudden loss of the side-strut support fitting joint and main landing gear attachment to the airplane, resulting in the collapse of a main landing gear. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Required Actions for Group 7 Airplanes For airplanes identified as Group 7 in Boeing Service Bulletin 737–53–1246, Revision 1, dated May 30, 2018: Within 120 days after the effective date of this AD, inspect the left and right side-strut support fitting lugs at BS 685 and do all applicable on-condition actions using a method approved in accordance with the procedures specified in paragraph (j) of this AD. (h) Required Actions for Groups 1 Through 6 Airplanes For airplanes identified as Groups 1 through 6 in Boeing Service Bulletin 737–53– 1246, Revision 1, dated May 30, 2018, except as specified in paragraph (i) of this AD: At the applicable times specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Service Bulletin 737–53–1246, Revision 1, dated May 30, 2018, do all applicable actions identified as ‘‘RC’’ (required for compliance) in, and in accordance with, the Accomplishment Instructions of Boeing Service Bulletin 737– 53–1246, Revision 1, dated May 30, 2018. (i) Exceptions to Service Information Specifications (1) For purposes of determining compliance with the requirements of this AD: Where Boeing Service Bulletin 737–53–1246, Revision 1, dated May 30, 2018, uses the PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 26333 phrase ‘‘the Revision 1 date of this service bulletin,’’ this AD requires using ‘‘the effective date of this AD.’’ (2) Where Boeing Service Bulletin 737–53– 1246, Revision 1, dated May 30, 2018, specifies contacting Boeing for repair instructions or for work instructions: This AD requires doing the repair or the work instructions and doing applicable oncondition actions using a method approved in accordance with the procedures specified in paragraph (j) of this AD. (j) Alternative Methods of Compliance (AMOCs) (1) The Manager, Los Angeles ACO Branch, 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 certification office, send it to the attention of the person identified in paragraph (k) of this AD. Information may be emailed to: 9-ANMLAACO-AMOC-Requests@faa.gov. (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, FAA, 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 (i) of this AD: For service information that contains steps that are labeled as RC, the provisions of paragraphs (j)(4)(i) and (j)(4)(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 substep is labeled ‘‘RC Exempt,’’ then the RC requirement is removed from that step or substep. 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. (k) Related Information For more information about this AD, contact George Garrido, Aerospace Engineer, Airframe Section, FAA, Los Angeles ACO Branch, 3960 Paramount Boulevard, Lakewood, CA 90712–4137; phone: 562–627– 5232; fax: 562–627–5210; email: george.garrido@faa.gov. E:\FR\FM\06JNR1.SGM 06JNR1 26334 Federal Register / Vol. 84, No. 109 / Thursday, June 6, 2019 / Rules and Regulations (l) 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 Service Bulletin 737–53–1246, Revision 1, dated May 30, 2018. (ii) [Reserved] (3) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Contractual & Data Services (C&DS), 2600 Westminster Blvd., MC 110–SK57, Seal Beach, CA 90740–5600; phone: 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: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Des Moines, Washington, on May 20, 2019. Michael Kaszycki, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2019–11790 Filed 6–5–19; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2018–0801; Product Identifier 2017–NM–147–AD; Amendment 39–19632; AD 2019–08–11] RIN 2120–AA640 Airworthiness Directives; Bombardier, Inc., Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are superseding Airworthiness Directive (AD) 2008–24– 14, which applied to all Bombardier, Inc., Model CL–600–2B19 (Regional Jet Series 100 & 440) airplanes. AD 2008– 24–14 required revising the instructions for continued airworthiness to incorporate certain airworthiness limitations for the main landing gear (MLG) trunnion fitting assembly. This AD requires revising the maintenance or inspection program, as applicable, to khammond on DSKBBV9HB2PROD with RULES SUMMARY: VerDate Sep<11>2014 15:44 Jun 05, 2019 Jkt 247001 incorporate certain airworthiness limitations (AWLs). This AD also requires reworking the trunnion fitting in order to meet new structural safe-life limits. This AD was prompted by reports of cracks on the MLG trunnion fitting during fatigue testing; the introduction of new AWL tasks with revised inspection, modification, and safe-life requirements; and a determination that the trunnion fitting lower flange and both forward and aft bore holes are also subject to fatigue cracking. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective July 11, 2019. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of July 11, 2019. The Director of the Federal Register approved the incorporation by reference of a certain other publication listed in this AD as of December 19, 2008 (73 FR 73785, December 4, 2008). ADDRESSES: For service information identified in this final rule, contact Bombardier, Inc., 400 Coˆte-Vertu Road West, Dorval, Que´bec H4S 1Y9, Canada; Widebody Customer Response Center North America toll-free telephone 1– 866–538–1247 or direct-dial telephone 1–514–855–2999; fax 514–855–7401; email ac.yul@aero.bombardier.com; internet https://www.bombardier.com. You may view this referenced 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 https:// www.regulations.gov by searching for and locating Docket No. FAA–2018– 0801. Examining the AD Docket You may examine the AD docket on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2018– 0801; 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 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: Aziz Ahmed, Aerospace Engineer, Airframe PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 and Mechanical Systems Section, FAA, New York ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516–228–7329; fax 516–794–5531. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2008–24–14, Amendment 39–15758 (73 FR 73785, December 4, 2008) (‘‘AD 2008–24–14’’). AD 2008–24–14 applied to all Bombardier, Inc., Model CL–600–2B19 (Regional Jet Series 100 & 440) airplanes. The NPRM published in the Federal Register on October 1, 2018 (83 FR 49317). The NPRM was prompted by reports of cracks on the MLG trunnion fitting during fatigue testing; the introduction of new AWL tasks with revised inspection, modification, and safe-life requirements; and a determination that the trunnion fitting lower flange and both forward and aft bore holes are also subject to fatigue cracking. The NPRM proposed to require revising the maintenance or inspection program, as applicable, to incorporate certain AWLs. The NPRM also proposed to require reworking the trunnion fitting in order to meet new structural safe-life limits. We are issuing this AD to address fatigue cracking of the MLG trunnion fitting. Failure of the MLG trunnion fitting could result in MLG collapse. Transport Canada Civil Aviation (TCCA), which is the aviation authority for Canada, has issued Canadian AD CF–2017–27, dated August 2, 2017 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Bombardier, Inc., Model CL–600–2B19 (Regional Jet Series 100 & 440) airplanes. The MCAI states: Cracks on the main landing gear (MLG) trunnion fitting web discovered during fatigue testing led to the issuance of [Canadian] AD CF–2008–21 [which corresponds to FAA AD 2008–24–14], which mandated new inspection requirements to ensure that fatigue cracking of the trunnion web would be detected and corrected. Additional fatigue test article findings and in-service findings have shown that the trunnion fitting lower flange and both forward and aft bore holes are also subject to fatigue cracking. Failure of the main landing gear trunnion fitting could result in the collapse of the main landing gear. Bombardier Inc. has decided to implement a series of design changes to improve the fatigue life of the trunnion fitting that is now a safe-life assembly. New and revised Airworthiness Limitation (AWL) tasks for the MLG trunnion fitting E:\FR\FM\06JNR1.SGM 06JNR1

Agencies

[Federal Register Volume 84, Number 109 (Thursday, June 6, 2019)]
[Rules and Regulations]
[Pages 26331-26334]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-11790]



========================================================================
Rules and Regulations
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains regulatory documents 
having general applicability and legal effect, most of which are keyed 
to and codified in the Code of Federal Regulations, which is published 
under 50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by the Superintendent of Documents. 

========================================================================


Federal Register / Vol. 84, No. 109 / Thursday, June 6, 2019 / Rules 
and Regulations

[[Page 26331]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-1004; Product Identifier 2018-NM-106-AD; Amendment 
39-19642; AD 2019-10-03]
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 of cracks caused by 
corrosion of the edge of the bore of the spot face and corrosion of the 
lug bore of certain side-strut support fitting lugs. This AD requires 
repetitive detailed inspections of the left and right side-strut 
support fitting lugs with bushings installed for any corrosion, any 
crack, or any severed lug; repetitive detailed and high frequency eddy 
current (HFEC) inspections of the left and right side-strut support 
fitting lugs with bushings removed for any corrosion or any crack; and 
applicable on-condition actions. We are issuing this AD to address the 
unsafe condition on these products.

DATES: This AD is effective July 11, 2019.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of July 11, 
2019.

ADDRESSES: For service information identified in this final rule, 
contact Boeing Commercial Airplanes, Attention: Contractual & Data 
Services (C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 
90740-5600; phone: 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 https://www.regulations.gov by searching for and locating Docket No. FAA-2018-
1004.

Examining the AD Docket

    You may examine the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2018-
1004; 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 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: George Garrido, Aerospace Engineer, 
Airframe Section, FAA, Los Angeles ACO Branch, 3960 Paramount 
Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5232; 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 December 6, 2018 (83 FR 
62741). The NPRM was prompted by reports of cracks caused by corrosion 
of the edge of the bore of the spot face and corrosion of the lug bore 
of certain side-strut support fitting lugs. The NPRM proposed to 
require repetitive detailed inspections of the left and right side-
strut support fitting lugs with bushings installed for any corrosion, 
any crack, or any severed lug; repetitive detailed and HFEC inspections 
of the left and right side-strut support fitting lugs with bushings 
removed for any corrosion or any crack; and applicable on-condition 
actions.
    We are issuing this AD to address cracks caused by corrosion, which 
could result in sudden loss of the side-strut support fitting joint and 
main landing gear attachment to the airplane, resulting in the collapse 
of a main landing gear.

Comments

    We gave the public the opportunity to participate in developing 
this final rule. The following presents the comments received on the 
NPRM and the FAA's response to each comment.

Effect of Winglets on Accomplishment of the Proposed Actions

    Aviation Partners Boeing stated that accomplishing Supplemental 
Type Certificate (STC) ST01219SE does not affect the actions specified 
in the proposed AD.
    We concur with the commenter. We have redesignated paragraph (c) of 
the proposed AD as paragraph (c)(1) of this AD and added paragraph 
(c)(2) to this AD to state that installation of 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.

Request To Change Format of Paragraphs (g) and (h) of the Proposed AD

    Boeing requested that we eliminate paragraph (h) of the proposed AD 
and incorporate the information as paragraph (g)(2) of this AD. Boeing 
pointed out that the title of paragraph (g) of the proposed AD would 
change to ``Required Actions,'' and that paragraphs (g)(1) and (g)(2) 
of this AD would apply to Group 7 and Groups 1 through 6, respectively. 
Boeing stated that this request is for consistency with previous ADs 
for Boeing airplanes.
    We disagree that elimination of paragraph (h) of the proposed AD 
and incorporating the information as paragraph (g)(2) of this AD is 
necessary. Over time we have used both formats, but most recently we 
have been using the format that was utilized in the NPRM. We do not 
find that there is a difference in clarity of the required actions. We 
also find that the requested change does not affect the requirements

[[Page 26332]]

of this final rule in this case. We have not changed this AD in this 
regard.

Request To Clarify ACO Branch Authority

    Boeing requested that we clarify the ACO branch that has the 
authority to approve AMOCs for this group of airplanes. Boeing pointed 
out that previous final rules for The Boeing Company Model 737-100, -
200, -200C, -300, -400, and -500 series airplanes have identified The 
Manager, Los Angeles ACO Branch, FAA, had the authority to approve 
AMOCs, even when the service bulletin was submitted for approval 
through the Seattle ACO Branch. Additionally, Boeing pointed out that 
previous ADs for The Boeing Company Model 737-100, -200, -200C, -300, -
400, and -500 series airplanes identified a Los Angeles ACO Branch 
specialist in the ``Related Information'' paragraph of the proposed 
rule, even when the service bulletin was submitted for approval through 
the Seattle ACO Branch.
    We agree that clarification is necessary. Normally, in NPRMs for 
The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 
series airplanes, we include the Manager, Los Angeles ACO Branch, as 
the designated approval authority for AMOCs. We have updated paragraph 
(j) of this AD to specify The Manager, Los Angeles ACO Branch. The 
Seattle ACO Branch is responsible during drafting of the NPRM and final 
rule of an AD for The Boeing Company Model 737-100, -200, -200C, -300, 
-400, and -500 series airplanes. After publication of the final rule, 
responsibility for the product is transferred to the Los Angeles ACO 
Branch. Therefore, when we draft the final rule of an AD for The Boeing 
Company Model 737-100, -200, -200C, -300, -400, and -500 series 
airplanes, we also specify a specialist from the Los Angeles ACO 
Branch. We have updated paragraph (k) of this AD to include the 
responsible specialist from the Los Angeles ACO Branch.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
this final rule 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 addressing 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 final 
rule.

Related Service Information Under 1 CFR Part 51

    We reviewed Boeing Service Bulletin 737-53-1246, Revision 1, dated 
May 30, 2018. This service information describes procedures for 
repetitive detailed inspections of the left and right side-strut 
support fitting lugs at body station (BS) 685 with bushings installed 
for any corrosion, any crack, or any severed lug; repetitive detailed 
and HFEC inspections of the left and right side-strut support fitting 
lugs at BS 685 with bushings removed for any corrosion or any crack; 
and applicable on-condition actions. On-condition actions include, 
among other things, inspections, corrosion removal, and a preventative 
modification. Doing the repetitive detailed and HFEC inspections of the 
side-strut support fitting lugs at BS 685 with bushings removed 
terminates the repetitive detailed inspections of the side-strut 
support fitting lugs at BS 685 with bushings installed. 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 302 airplanes of U.S. registry. We 
estimate the following costs to comply with this AD:

                                      Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
             Action                     Labor cost          Parts cost     Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Repetitive detailed inspection   17 work-hours x $85 per              $0  $1,445 per          $436,390 per
 of left and right side lugs      hour = $1,445 per                        inspection cycle.   inspection cycle.
 with bushings installed.         inspection cycle.
Repetitive detailed and HFEC     29 work-hours x $85 per               0  $2,465 per          $744,430 per
 inspections of left and right    hour = $2,465 per                        inspection cycle.   inspection cycle.
 side lugs with bushings          inspection cycle.
 removed.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary on-condition 
actions that would be required. We have no way of determining the 
number of aircraft that might need these on-condition actions:

                 Estimated Costs of On-Condition Actions
------------------------------------------------------------------------
           Labor cost                 Parts cost       Cost per product
------------------------------------------------------------------------
Up to 18 work-hour x $85 per      Unknown...........  Up to $1,530 per
 hour = $1,530 per inspection                          inspection cycle.
 cycle.
------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
parts cost estimates for the on-condition inspections and repairs 
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

[[Page 26333]]

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 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):

2019-10-03 The Boeing Company: Amendment 39-19642; Docket No. FAA-
2018-1004; Product Identifier 2018-NM-106-AD.

(a) Effective Date

    This AD is effective July 11, 2019.

(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 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 53, Fuselage.

(e) Unsafe Condition

    This AD was prompted by reports of cracks caused by corrosion of 
the edge of the bore of the spot face and corrosion of the lug bore 
of the body station (BS) 685 side-strut support fitting lugs. We are 
issuing this AD to address cracks caused by corrosion, which could 
result in sudden loss of the side-strut support fitting joint and 
main landing gear attachment to the airplane, resulting in the 
collapse of a main landing gear.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Required Actions for Group 7 Airplanes

    For airplanes identified as Group 7 in Boeing Service Bulletin 
737-53-1246, Revision 1, dated May 30, 2018: Within 120 days after 
the effective date of this AD, inspect the left and right side-strut 
support fitting lugs at BS 685 and do all applicable on-condition 
actions using a method approved in accordance with the procedures 
specified in paragraph (j) of this AD.

(h) Required Actions for Groups 1 Through 6 Airplanes

    For airplanes identified as Groups 1 through 6 in Boeing Service 
Bulletin 737-53-1246, Revision 1, dated May 30, 2018, except as 
specified in paragraph (i) of this AD: At the applicable times 
specified in paragraph 1.E., ``Compliance,'' of Boeing Service 
Bulletin 737-53-1246, Revision 1, dated May 30, 2018, do all 
applicable actions identified as ``RC'' (required for compliance) 
in, and in accordance with, the Accomplishment Instructions of 
Boeing Service Bulletin 737-53-1246, Revision 1, dated May 30, 2018.

(i) Exceptions to Service Information Specifications

    (1) For purposes of determining compliance with the requirements 
of this AD: Where Boeing Service Bulletin 737-53-1246, Revision 1, 
dated May 30, 2018, uses the phrase ``the Revision 1 date of this 
service bulletin,'' this AD requires using ``the effective date of 
this AD.''
    (2) Where Boeing Service Bulletin 737-53-1246, Revision 1, dated 
May 30, 2018, specifies contacting Boeing for repair instructions or 
for work instructions: This AD requires doing the repair or the work 
instructions and doing applicable on-condition actions using a 
method approved in accordance with the procedures specified in 
paragraph (j) of this AD.

(j) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Los Angeles ACO Branch, 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 certification office, send it to the attention of 
the person identified in paragraph (k) 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, FAA, 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 (i) of this AD: For service 
information that contains steps that are labeled as RC, the 
provisions of paragraphs (j)(4)(i) and (j)(4)(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 substep is labeled ``RC Exempt,'' then the 
RC requirement is removed from that step or substep. 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.

(k) Related Information

    For more information about this AD, contact George Garrido, 
Aerospace Engineer, Airframe Section, FAA, Los Angeles ACO Branch, 
3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-
5232; fax: 562-627-5210; email: [email protected].

[[Page 26334]]

(l) 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 Service Bulletin 737-53-1246, Revision 1, dated May 
30, 2018.
    (ii) [Reserved]
    (3) For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Contractual & Data Services 
(C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740-
5600; phone: 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: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Des Moines, Washington, on May 20, 2019.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2019-11790 Filed 6-5-19; 8:45 am]
 BILLING CODE 4910-13-P