Airworthiness Directives; the Boeing Company Airplanes, 26556-26559 [2018-12279]

Download as PDF amozie on DSK3GDR082PROD with RULES 26556 Federal Register / Vol. 83, No. 111 / Friday, June 8, 2018 / Rules and Regulations (v) Add together the amounts computed in paragraphs (c)(3)(i) through (v) of this section and from that sum deduct any payment made pursuant to paragraph (c)(1) of this section. (d) Handler underpayment proration. If a handler has not received full payment from the market administrator pursuant to § 1051.72 by the payment date specified in paragraph (a), (b), or (c) of this section, the handler may reduce pro rata its payments to producers or to the cooperative association (with respect to receipts described in paragraph (b) of this section, prorating the underpayment to the volume of milk received from the cooperative association in proportion to the total milk received from producers by the handler), but not by more than the amount of the underpayment. The payments shall be completed on the next scheduled payment date after receipt of the balance due from the market administrator. (e) Payments to missing or deceased producers. If a handler claims that a required payment to a producer cannot be made because the producer is deceased or cannot be located, or because the cooperative association or its lawful successor or assignee is no longer in existence, the payment shall be made to the producer-settlement fund, and in the event that the handler subsequently locates and pays the producer or a lawful claimant, or in the event that the handler no longer exists and a lawful claim is later established, the market administrator shall make the required payment from the producersettlement fund to the handler or to the lawful claimant, as the case may be. (f) Producer payment record. In making payments to producers pursuant to this section, each handler shall furnish each producer, except a producer whose milk was received from a cooperative association handler described in § 1000.9(a) or (c), a supporting statement in a form that may be retained by the recipient which shall show: (1) The name, address, Grade A identifier assigned by a duly constituted regulatory agency, and payroll number of the producer; (2) The daily and total pounds, and the month and dates such milk was received from that producer; (3) The total pounds of butterfat, protein, and other solids contained in the producer’s milk; (4) The minimum rate or rates at which payment to the producer is required pursuant to the order in this part; VerDate Sep<11>2014 16:08 Jun 07, 2018 Jkt 244001 (5) The rate used in making payment if the rate is other than the applicable minimum rate; (6) The amount, or rate per hundredweight, or rate per pound of component, and the nature of each deduction claimed by the handler; and (7) The net amount of payment to the producer or cooperative association. § 1051.74 [Reserved] For purposes of making payments for producer milk and nonpool milk, a plant location adjustment shall be determined by subtracting the Class I price specified in § 1051.51 from the Class I price at the plant’s location. The difference, plus or minus as the case may be, shall be used to adjust the payments required pursuant to §§ 1051.73 and 1000.76. § 1051.76 Payments by a handler operating a partially regulated distributing plant. See § 1000.76. See § 1000.86. Subpart D—Miscellaneous Provisions § 1051.90 Dates. Dated: June 4, 2018. Bruce Summers, Administrator, Agricultural Marketing Service. [FR Doc. 2018–12245 Filed 6–7–18; 8:45 am] BILLING CODE 3410–02–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2018–0074; Product Identifier 2017–NM–148–AD; Amendment 39–19309; AD 2018–12–05] RIN 2120–AA64 Airworthiness Directives; the Boeing Company Airplanes Charges on overdue accounts. Administrative Assessment and Marketing Service Deduction On or before the payment receipt date specified under § 1051.71, each handler shall pay to the market administrator its pro rata share of the expense of administration of the order at a rate specified by the market administrator that is no more than 8 cents per hundredweight with respect to: (a) Receipts of producer milk (including the handler’s own production) other than such receipts by a handler described in § 1000.9(c) that were delivered to pool plants of other handlers; (b) Receipts from a handler described in § 1000.9(c); (c) Receipts of concentrated fluid milk products from unregulated supply plants and receipts of nonfluid milk products assigned to Class I use pursuant to § 1000.43(d) and other source milk allocated to Class I pursuant to § 1000.44(a)(3) and (8) and the corresponding steps of § 1000.44(b), except other source milk that is excluded from the computations pursuant to § 1051.60(h) and (i); and (d) Route disposition in the marketing area from a partially regulated distributing plant that exceeds the skim Fmt 4700 Sfmt 4700 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 found in the rear spar web and lower chord on the left and right wings. This AD requires repetitive detailed inspections for cracking of the rear spar web and lower chord, and applicable on-condition actions. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective July 13, 2018. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of July 13, 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 90740–5600; 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. SUMMARY: § 1051.85 Assessment for order administration. Frm 00010 Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: See § 1000.78. PO 00000 Deduction for marketing Adjustment of accounts. See § 1000.77. § 1051.78 § 1051.86 services. See § 1000.90. § 1051.75 Plant location adjustments for producer milk and nonpool milk. § 1051.77 milk and butterfat subtracted pursuant to § 1000.76(a)(1)(i) and (ii). E:\FR\FM\08JNR1.SGM 08JNR1 Federal Register / Vol. 83, No. 111 / Friday, June 8, 2018 / Rules and Regulations flight loads and adversely affect the structural integrity of the airplane. It is also available on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2018– 0074. 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– 0074; 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: payman.soltani@faa.gov. 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 February 9, 2018 (83 FR 5743). The NPRM was prompted by reports of cracks found in the rear spar web and lower chord on the left and right wings. The NPRM proposed to require repetitive detailed inspections for cracking of the rear spar web and lower chord, and applicable on-condition actions. We are issuing this AD to address cracks in the rear spar of the left and right wing between wing buttock line (WBL) 91 and WBL 155, which could lead to the inability of a principal structural element to sustain required 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. Support for the NPRM The Boeing Company stated its support for the NPRM. Request To Require the Same Grace Period Regardless of Inspection Method Southwest Airlines (Southwest), requested that we revise paragraph (h) of the proposed AD, which refers to the ‘‘Compliance’’ section of Boeing Alert Requirements Bulletin 737–57A1337 RB, dated September 14, 2017, regarding the different compliance times for the two inspection methods given in Table 1 of the ‘‘Compliance’’ section for Group 2 airplanes. Southwest stated that the planned inspection method should have no bearing on the timing of the inspection, and therefore the compliance times should be the same for both options. They did not specify which of the two compliance times they would favor. We acknowledge the commenter’s request. While the compliance times for inspections are not normally dependent on the planned inspection method, in this case, the initial compliance times were adjusted to account for differences in the probability of detection using a visual inspection versus an eddy current inspection. Because an eddy current inspection is more capable of detecting smaller cracks than a visual inspection, the initial compliance time was shortened for those airplanes that are inspected using the visual inspection option. We have not changed this AD in this regard. Effect of Winglets on Accomplishment of the Proposed Actions Aviation Partners Boeing stated that the installation of winglets using Supplemental Type Certificate (STC) ST01219SE does not affect the actions specified in the NPRM. 26557 We agree 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. 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 Alert Requirements Bulletin 737–57A1337 RB, dated September 14, 2017. This service information describes procedures for repetitive detailed or surface High Frequency Eddy Current (HFEC) inspections for cracking of the rear spar web and lower chord, and applicable on-condition 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 160 airplanes of U.S. registry. We estimate the following costs to comply with this AD: ESTIMATED COSTS FOR REQUIRED ACTIONS Labor cost Inspections ............. amozie on DSK3GDR082PROD with RULES Action Up to 22 work-hours × $85 per hour = up to $1,870 per inspection cycle. We have received no definitive data that would enable us to provide cost VerDate Sep<11>2014 16:08 Jun 07, 2018 Jkt 244001 Parts cost $0 estimates for the on-condition actions specified in this AD. PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 Cost per product Cost on U.S. operators Up to $1,870 per Up to $299,200 per ininspection cycle. spection cycle. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue E:\FR\FM\08JNR1.SGM 08JNR1 26558 Federal Register / Vol. 83, No. 111 / Friday, June 8, 2018 / Rules and Regulations 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. amozie on DSK3GDR082PROD with RULES 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, VerDate Sep<11>2014 16:08 Jun 07, 2018 Jkt 244001 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: ■ 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): ■ 2018–12–05 The Boeing Company: Amendment 39–19309; Docket No. FAA–2018–0074; Product Identifier 2017–NM–148–AD. (a) Effective Date This AD is effective July 13, 2018. (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 (https:// rgl.faa.gov/Regulatory_and_Guidance_ Library/rgstc.nsf/0/ebd1cec7b301293 e86257cb30045557a/$FILE/ST01219SE.pdf) does not affect the ability to accomplish the actions required by this AD. Therefore, for airplanes on which STC ST01219SE is installed, a ‘‘change in product’’ alternative method of compliance (AMOC) approval request is not necessary to comply with the requirements of 14 CFR 39.17. (d) Subject Air Transport Association (ATA) of America Code 57, Wings. (e) Unsafe Condition This AD was prompted by reports of cracks found in the rear spar web and lower chord on the left and right wings. We are issuing this AD to detect and correct cracks in the rear spar of the left and right wing between wing buttock line (WBL) 91 and WBL 155, which could lead to the inability of a principal structural element to sustain required flight loads and adversely affect the structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Required Actions for Group 1 Airplanes For airplanes identified as Group 1 in Boeing Alert Requirements Bulletin 737– 57A1337 RB, dated September 14, 2017: Within 120 days after the effective date of this AD, inspect the airplane and do all applicable corrective actions using a method approved in accordance with the procedures specified in paragraph (j) of this AD. PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 (h) Required Actions for Group 2 Airplanes For airplanes identified as Group 2 in Boeing Alert Requirements Bulletin 737– 57A1337 RB, dated September 14, 2017: Except as required by paragraph (i) of this AD, at the applicable times specified in the ‘‘Compliance’’ section of Boeing Alert Requirements Bulletin 737–57A1337 RB, dated September 14, 2017, do all applicable actions identified in, and in accordance with, the Accomplishment Instructions of Boeing Alert Requirements Bulletin 737–57A1337 RB, dated September 14, 2017. Note 1 to paragraph (h) of this AD: Guidance for accomplishing the actions required by this AD is included in Boeing Alert Service Bulletin 737–57A1337, dated September 14, 2017, which is referred to in Boeing Alert Requirements Bulletin 737– 57A1337 RB, dated September 14, 2017. (i) Exceptions to Service Information Specifications (1) For purposes of determining compliance with the requirements of this AD: Where Boeing Alert Requirements Bulletin 737–57A1337 RB, dated September 14, 2017, uses the phrase ‘‘the original issue date of Requirements Bulletin 737–57A1337 RB,’’ this AD requires using ‘‘the effective date of this AD.’’ (2) Where Boeing Alert Requirements Bulletin 737–57A1337 RB, dated September 14, 2017, specifies contacting Boeing, this AD requires repair 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)(1) of this AD. Information may be emailed to: 9ANM-LAACO-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, 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. (k) Related Information (1) 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– E:\FR\FM\08JNR1.SGM 08JNR1 Federal Register / Vol. 83, No. 111 / Friday, June 8, 2018 / Rules and Regulations 5313; fax: 562–627–5210; email: payman.soltani@faa.gov. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (l)(3) and (l)(4) of this AD. (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 Alert Requirements Bulletin 737–57A1337 RB, dated September 14, 2017. (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; 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: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Des Moines, Washington, on May 31, 2018. Michael Kaszycki, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2018–12279 Filed 6–7–18; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2017–1020; Product Identifier 2017–NM–114–AD; Amendment 39–19306; AD 2018–12–02] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. amozie on DSK3GDR082PROD with RULES AGENCY: We are adopting a new airworthiness directive (AD) for all Airbus Model A318–111 and –112 airplanes; Model A319–111, –112, –113, –114, and –115 airplanes; Model A320– 211, –212, –214, and –216 airplanes; SUMMARY: VerDate Sep<11>2014 16:08 Jun 07, 2018 Jkt 244001 and Model A321–111, –112, –211, –212, and –213 airplanes. This AD was prompted by a review of maintenance instructions for a blend repair of the snout diameter of the main beam assembly of the forward engine mount that would create an excessive gap between the bearing mono-ball and the snout. This AD requires modifying the main beam assembly of the forward engine mount. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective July 13, 2018. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of July 13, 2018. ADDRESSES: For Airbus service information identified in this final rule, contact Airbus, Airworthiness Office– EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96; fax: +33 5 61 93 44 51; email: account.airwortheas@airbus.com; internet: https:// www.airbus.com. For Goodrich service information identified in this final rule, contact Goodrich Corporation, Aerostructures, 850 Lagoon Drive, Chula Vista, CA 91910–2098; phone: 619–691– 2719; email: jan.lewis@goodrich.com; internet: https://www.goodrich.com/ TechPubs. 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–2017– 1020. 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–2017– 1020; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (telephone 800–647– 5527) is Docket Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 26559 216th St., Des Moines, WA 98198–6547; telephone 425–227–1405; fax 425–227– 1149. 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 Airbus Model A318–111 and –112 airplanes; Model A319–111, –112, –113, –114, and –115 airplanes; Model A320–211, –212, –214, and –216 airplanes; and Model A321–111, –112, –211, –212, and –213 airplanes. The NPRM published in the Federal Register on October 24, 2017 (82 FR 49146) (‘‘the NPRM’’). The NPRM was prompted by a review of maintenance instructions for a blend repair of the snout diameter of the main beam assembly of the forward engine mount that would create an excessive gap between the bearing mono-ball and the snout. The NPRM proposed to require modifying the main beam assembly of the forward engine mount. We are issuing this AD to prevent in-flight failure of a forward engine mount, and consequent detachment of an engine, which could result in reduced controllability of the airplane. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2017– 0132R1, dated November 22, 2017 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for all Airbus Model A318– 111 and –112 airplanes; Model A319– 111, –112, –113, –114, and –115 airplanes; Model A320–211, –212, –214, and –216 airplanes; and Model A321– 111, –112, –211, –212, and –213 airplanes. The MCAI states: A review of maintenance instructions revealed that the Goodrich Aerospace CFM56–5B, Forward Engine Mount Component Maintenance Manual (CMM) 71– 21–08, revision (rev.) 1 up to 46 (inclusive), repair 10 (Blend Repair-Beam Assembly Snout Diameter), provides instructions to blend the wear on the forward engine mount assembly, Part Number (P/N) 642–2000–9, 642–2000–13, or 642–2000–25, creating an excessive gap between the bearing mono-ball and the snout of the forward engine mount main beam assembly, P/N 642–2006–501, or P/N 642–2006–503. This condition, if not detected and corrected, could lead to in-flight failure of a forward engine mount and consequent detachment of an engine, possibly resulting in reduced control of the aeroplane and injury to persons on the ground. To address this potential unsafe condition, Airbus issued Service Bulletin (SB) A320– 71–1065 and SB A320–71–1066, and E:\FR\FM\08JNR1.SGM 08JNR1

Agencies

[Federal Register Volume 83, Number 111 (Friday, June 8, 2018)]
[Rules and Regulations]
[Pages 26556-26559]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-12279]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0074; Product Identifier 2017-NM-148-AD; Amendment 
39-19309; AD 2018-12-05]
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 found in the rear 
spar web and lower chord on the left and right wings. This AD requires 
repetitive detailed inspections for cracking of the rear spar web and 
lower chord, and applicable on-condition actions. We are issuing this 
AD to address the unsafe condition on these products.

DATES: This AD is effective July 13, 2018.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of July 13, 
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 
90740-5600; 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.

[[Page 26557]]

It is also available on the internet at https://www.regulations.gov by 
searching for and locating Docket No. FAA-2018-0074.

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-
0074; 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 February 9, 2018 (83 FR 
5743). The NPRM was prompted by reports of cracks found in the rear 
spar web and lower chord on the left and right wings. The NPRM proposed 
to require repetitive detailed inspections for cracking of the rear 
spar web and lower chord, and applicable on-condition actions.
    We are issuing this AD to address cracks in the rear spar of the 
left and right wing between wing buttock line (WBL) 91 and WBL 155, 
which could lead to the inability of a principal structural element to 
sustain required flight loads and adversely affect the structural 
integrity of the airplane.

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.

Support for the NPRM

    The Boeing Company stated its support for the NPRM.

Request To Require the Same Grace Period Regardless of Inspection 
Method

    Southwest Airlines (Southwest), requested that we revise paragraph 
(h) of the proposed AD, which refers to the ``Compliance'' section of 
Boeing Alert Requirements Bulletin 737-57A1337 RB, dated September 14, 
2017, regarding the different compliance times for the two inspection 
methods given in Table 1 of the ``Compliance'' section for Group 2 
airplanes. Southwest stated that the planned inspection method should 
have no bearing on the timing of the inspection, and therefore the 
compliance times should be the same for both options. They did not 
specify which of the two compliance times they would favor.
    We acknowledge the commenter's request. While the compliance times 
for inspections are not normally dependent on the planned inspection 
method, in this case, the initial compliance times were adjusted to 
account for differences in the probability of detection using a visual 
inspection versus an eddy current inspection. Because an eddy current 
inspection is more capable of detecting smaller cracks than a visual 
inspection, the initial compliance time was shortened for those 
airplanes that are inspected using the visual inspection option. We 
have not changed this AD in this regard.

Effect of Winglets on Accomplishment of the Proposed Actions

    Aviation Partners Boeing stated that the installation of winglets 
using Supplemental Type Certificate (STC) ST01219SE does not affect the 
actions specified in the NPRM.
    We agree 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.

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 Alert Requirements Bulletin 737-57A1337 RB, 
dated September 14, 2017. This service information describes procedures 
for repetitive detailed or surface High Frequency Eddy Current (HFEC) 
inspections for cracking of the rear spar web and lower chord, and 
applicable on-condition 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 160 airplanes of U.S. registry. We 
estimate the following costs to comply with this AD:

                                      Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
         Action              Labor cost      Parts cost       Cost per product         Cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
Inspections.............  Up to 22 work-               $0  Up to $1,870 per        Up to $299,200 per inspection
                           hours x $85                      inspection cycle.       cycle.
                           per hour = up
                           to $1,870 per
                           inspection
                           cycle.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would 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

[[Page 26558]]

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 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):

2018-12-05 The Boeing Company: Amendment 39-19309; Docket No. FAA-
2018-0074; Product Identifier 2017-NM-148-AD.

(a) Effective Date

    This AD is effective July 13, 2018.

(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 (https://rgl.faa.gov/Regulatory_and_Guidance_Library/
rgstc.nsf/0/ebd1cec7b301293e86257cb30045557a/$FILE/ST01219SE.pdf) 
does not affect the ability to accomplish the actions required by 
this AD. Therefore, for airplanes on which STC ST01219SE is 
installed, a ``change in product'' alternative method of compliance 
(AMOC) approval request is not necessary to comply with the 
requirements of 14 CFR 39.17.

(d) Subject

    Air Transport Association (ATA) of America Code 57, Wings.

(e) Unsafe Condition

    This AD was prompted by reports of cracks found in the rear spar 
web and lower chord on the left and right wings. We are issuing this 
AD to detect and correct cracks in the rear spar of the left and 
right wing between wing buttock line (WBL) 91 and WBL 155, which 
could lead to the inability of a principal structural element to 
sustain required flight loads and adversely affect the structural 
integrity of the airplane.

(f) Compliance

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

(g) Required Actions for Group 1 Airplanes

    For airplanes identified as Group 1 in Boeing Alert Requirements 
Bulletin 737-57A1337 RB, dated September 14, 2017: Within 120 days 
after the effective date of this AD, inspect the airplane and do all 
applicable corrective actions using a method approved in accordance 
with the procedures specified in paragraph (j) of this AD.

(h) Required Actions for Group 2 Airplanes

    For airplanes identified as Group 2 in Boeing Alert Requirements 
Bulletin 737-57A1337 RB, dated September 14, 2017: Except as 
required by paragraph (i) of this AD, at the applicable times 
specified in the ``Compliance'' section of Boeing Alert Requirements 
Bulletin 737-57A1337 RB, dated September 14, 2017, do all applicable 
actions identified in, and in accordance with, the Accomplishment 
Instructions of Boeing Alert Requirements Bulletin 737-57A1337 RB, 
dated September 14, 2017.

    Note 1 to paragraph (h) of this AD: Guidance for accomplishing 
the actions required by this AD is included in Boeing Alert Service 
Bulletin 737-57A1337, dated September 14, 2017, which is referred to 
in Boeing Alert Requirements Bulletin 737-57A1337 RB, dated 
September 14, 2017.

(i) Exceptions to Service Information Specifications

    (1) For purposes of determining compliance with the requirements 
of this AD: Where Boeing Alert Requirements Bulletin 737-57A1337 RB, 
dated September 14, 2017, uses the phrase ``the original issue date 
of Requirements Bulletin 737-57A1337 RB,'' this AD requires using 
``the effective date of this AD.''
    (2) Where Boeing Alert Requirements Bulletin 737-57A1337 RB, 
dated September 14, 2017, specifies contacting Boeing, this AD 
requires repair 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)(1) of this AD. Information 
may be emailed to: [email protected].
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.
    (3) An AMOC that provides an acceptable level of safety may be 
used for any repair, modification, or alteration required by this AD 
if it is approved by the Boeing Commercial Airplanes Organization 
Designation Authorization (ODA) that has been authorized by the 
Manager, Los Angeles ACO 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.

(k) Related Information

    (1) 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-

[[Page 26559]]

5313; fax: 562-627-5210; email: [email protected].
    (2) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (l)(3) and (l)(4) of this AD.

(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 Alert Requirements Bulletin 737-57A1337 RB, dated 
September 14, 2017.
    (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; 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: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Des Moines, Washington, on May 31, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2018-12279 Filed 6-7-18; 8:45 am]
BILLING CODE 4910-13-P
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