Airworthiness Directives; The Boeing Company Airplanes, 46902-46905 [2018-19840]

Download as PDF 46902 Federal Register / Vol. 83, No. 180 / Monday, September 17, 2018 / Proposed Rules (b) Affected ADs None. (c) Applicability This AD applies to GA 8 Airvan (Pty) Ltd Models GA8 and GA8–TC320 airplanes, certificated in any category, with a strut or strut fitting installed that has a part number and serial number listed in table 1 of GippsAero Service Bulletin SB–GA8–2017– 174, Issue 2, dated May 23, 2018 (GippsAero SB–GA8–2017–174, Issue 2). (d) Subject Air Transport Association of America (ATA) Code 57: Wings. daltland on DSKBBV9HB2PROD with PROPOSALS (e) Reason This AD was prompted by mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as certain wing strut fittings manufactured with incorrect grain orientation, which has an unknown effect on fatigue-related concerns. We are issuing this AD to detect and address fatigue-related damage to the wing strut fittings, which could lead to failure of the wing with consequent loss of control of the airplane. (f) Actions and Compliance Unless already done, do the following actions in paragraphs (f)(1) through (6) of this AD: (1) Within 3 months after the effective date of this AD or within 100 hours time-inservice (TIS) after the effective date of this AD, whichever occurs first, with the wing struts removed, visually inspect each forward and aft wing strut fitting and fuselage attachment point for cracks, corrosion, and damage. If a crack, corrosion, or damage is found during the inspection, before further flight, do the applicable corrective actions (check torque, restore surface protection, rework areas with fouling, and replace any part with a crack, corrosion, or damage). Follow the procedures in Parts C1, C2, and D or E, as applicable, in the Accomplishment Instructions in GippsAero SB–GA8–2017– 174, Issue 2. (2) Within 3 months after the effective date of this AD or within 100 hours TIS after the effective date of this AD, whichever occurs first, and thereafter at intervals not to exceed 100 hours TIS, visually inspect each strut and strut fitting for cracks, corrosion, and damage. If a crack, corrosion, or damage is found during any of the inspections, before further flight, do the applicable corrective actions (check torque, restore surface protection, and replace any part with a crack, corrosion, or damage). Follow the procedures in Parts B and D or E, as applicable, in the Accomplishment Instructions of GippsAero SB–GA8–2017–174, Issue 2. (3) Within 1,000 hours TIS after doing the inspections required in paragraph (f)(1) of this AD and thereafter at intervals not to exceed 1,000 hours TIS, with the wing struts installed, visually inspect each forward and aft wing strut, strut fitting, and strut fitting lug hole for cracks, corrosion, and damage. If VerDate Sep<11>2014 16:40 Sep 14, 2018 Jkt 244001 a crack, corrosion, or damage is found during any of the inspections, before further flight, do the applicable corrective actions (do additional inspections, replace hardware, and replace any part with a crack, corrosion, or damage). Follow the procedures in Parts C3 and D or E, as applicable, in the Accomplishment Instructions of GippsAero SB–GA8–2017–174, Issue 2. (4) To use an eddy current or fluorescent liquid penetrant inspection method instead of a visual inspection for the requirements in paragraphs (f)(1) of this AD, the Manager, Small Airplane Standards Branch, FAA must approve your inspection method, and the Manager’s approval letter must specifically refer to this AD. Send your approval request to the contact information found in paragraph (g)(1) of this AD. (5) Remove from service each part listed in Parts D and E of table 3 on or before the part exceeds its specified replacement time and replace with an airworthy part. On the effective date of this AD, any part listed in table 3 of GippsAero SB–GA8–2017–174, Issue 2, that has exceeded its replacement time, within 100 hours TIS after the effective date of this AD or within 12 months after the effective date of this AD, whichever occurs first, remove the part from service and replace with an airworthy part. Follow the replacement procedures in Part D or Part E, as applicable, in the Accomplishment Instructions of GippsAero SB–GA8–2017– 174, Issue 2. (6) Within 24 hours after each inspection required in paragraphs (f)(1) and (2) of this AD, submit a report of the inspection results, even if no damage is found, to the Civil Aviation Safety Authority (CASA) and GA 8 Airvan (Pty) Ltd. Use the Document Compliance Notice of GippsAero SB–GA8– 2017–174, Issue 2, and include in the report the total hours TIS on the airplane and the type of operation. You may use the contact information found in paragraph (h) of this AD to contact GA 8 Airvan (Pty) Ltd. To contact CASA, use the online CASA Defect Reporting Service at the following internet address: https://drs.casa.gov.au/. (g) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, Small Airplane Standards Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Doug Rudolph, Aerospace Engineer, FAA, Small Airplane Standards Branch, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4059; fax: (816) 329–4090; email: doug.rudolph@faa.gov. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must instead be accomplished using a method approved by the Manager, Small Airplane Standards Branch, FAA; or CASA. PO 00000 Frm 00017 Fmt 4702 Sfmt 4702 (3) Reporting Requirements: A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a currently valid OMB Control Number. The OMB Control Number for this information collection is 2120–0731. Public reporting for this collection of information is estimated to be approximately 1 hour per response, including the time for reviewing instructions, searching existing data sources, gathering and maintaining the data needed, completing and reviewing the collection of information. All responses to this collection of information are voluntary; the nature and extent of confidentiality to be provided, if any. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing this burden to: Information Collection Clearance Officer, Federal Aviation Administration, 10101 Hillwood Parkway, Fort Worth, TX 76177–1524. (h) Related Information Refer to MCAI issued by CASA, AD No. AD/GA8/9, Amendment 1, dated May 29, 2018. You may examine the MCAI on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA– 2018–0771. For service information related to this AD, contact GA 8 Airvan (Pty) Ltd, c/o GippsAero Pty Ltd, Attn: Technical Services, P.O. Box 881, Morwell Victoria 3840, Australia; telephone: +61 03 5172 1200; fax: +61 03 5172 1201; email: aircraft.techpubs@ mahindraaerospace.com. You may review this referenced service information at the FAA, Policy and Innovation Division, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329–4148. Issued in Kansas City, Missouri, on August 31, 2018. Melvin J. Johnson, Deputy Director, Policy & Innovation Division, Aircraft Certification Service. [FR Doc. 2018–19889 Filed 9–14–18; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2018–0793; Product Identifier 2018–NM–057–AD] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: E:\FR\FM\17SEP1.SGM 17SEP1 Federal Register / Vol. 83, No. 180 / Monday, September 17, 2018 / Proposed Rules We propose to adopt a new airworthiness directive (AD) for all The Boeing Company Model 737–100, –200, –200C, –300, –400, and –500 series airplanes. This proposed AD was prompted by a report of cracks in the body station (STA) 303.9 frame web and doubler at fastener holes common to the stop fitting at stringer 16 left (S–16L). This proposed AD would require repetitive surface high frequency eddy current (HFEC) inspections for cracking of the STA 303.9 frame web and doubler at the stop fitting at S–16L, and applicable on-condition actions. We are proposing this AD to address the unsafe condition on these products. DATES: We must receive comments on this proposed AD by November 1, 2018. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this NPRM, 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 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 http://www.regulations.gov by searching for and locating Docket No. FAA–2018– 0793. daltland on DSKBBV9HB2PROD with PROPOSALS SUMMARY: available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Galib Abumeri, Aerospace Engineer, Airframe Section, FAA, Los Angeles ACO Branch, 3960 Paramount Boulevard, Lakewood, CA 90712–4137; phone: 562–627–5324; fax: 562–627– 5210; email: galib.abumeri@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA– 2018–0793; Product Identifier 2018– NM–057–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this NPRM. We will consider all comments received by the closing date and may amend this NPRM because of those comments. We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion We have received a report indicating cracks in the STA 303.9 frame web and doubler at fastener holes common to the stop fitting at S–16L. The cracks were found during accomplishment of Boeing Service Bulletin 737–53A1188. We have determined that the existing inspection programs are not sufficient to find any crack in the STA 303.9 frame web and doubler at the stop fitting at S–16L. This condition, if not addressed, could result in the inability of a principal structural element to sustain limit loads and possible rapid decompression of the airplane. Examining the AD Docket Related Service Information Under 1 CFR Part 51 You may examine the AD docket on the internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2018– 0793; 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 NPRM, the regulatory evaluation, any comments received, and other information. The street address for Docket Operations (phone: 800–647–5527) is in the ADDRESSES section. Comments will be We reviewed Boeing Requirements Bulletin 737–53A1375 RB, dated March 12, 2018. The service information describes procedures for repetitive surface HFEC inspections for cracking of the STA 303.9 frame web and doubler at the stop fitting at S–16L, 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. VerDate Sep<11>2014 16:40 Sep 14, 2018 Jkt 244001 PO 00000 Frm 00018 Fmt 4702 Sfmt 4702 46903 FAA’s Determination We are proposing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. Proposed AD Requirements This proposed AD would require accomplishment of the actions identified in Boeing Requirements Bulletin 737–53A1375 RB, dated March 12, 2018, described previously, except for any differences identified as exceptions in the regulatory text of this proposed AD. For information on the procedures and compliance times, see this service information at http:// www.regulations.gov by searching for and locating Docket No. FAA–2018– 0793. Explanation of Applicability Model 737 airplanes having line numbers 1 through 291 have a limit of validity (LOV) of 34,000 total flight cycles, and the actions proposed in this NPRM, as specified in Boeing Requirements Bulletin 737–53A1375 RB, dated March 12, 2018, would be required at a compliance time occurring after that LOV. Although operation of an airplane beyond its LOV is prohibited by 14 CFR 121.1115 and 129.115, this NPRM would include those airplanes in the applicability so that these airplanes are tracked in the event the LOV is extended in the future. Explanation of Requirements Bulletin The FAA worked in conjunction with industry, under the Airworthiness Directives Implementation Aviation Rulemaking Committee (AD ARC), to enhance the AD system. One enhancement is a process for annotating which steps in the service information are ‘‘required for compliance’’ (RC) with an AD. Boeing has implemented this RC concept into Boeing service bulletins. In an effort to further improve the quality of ADs and AD-related Boeing service information, a joint process improvement initiative was worked between the FAA and Boeing. The initiative resulted in the development of a new process in which the service information more clearly identifies the actions needed to address the unsafe condition in the ‘‘Accomplishment Instructions.’’ The new process results in a Boeing Requirements Bulletin, which contains only the actions needed to address the unsafe condition (i.e., only the RC actions). E:\FR\FM\17SEP1.SGM 17SEP1 46904 Federal Register / Vol. 83, No. 180 / Monday, September 17, 2018 / Proposed Rules Costs of Compliance estimate the following costs to comply with this proposed AD: We estimate that this proposed AD affects 67 airplanes of U.S. registry. We ESTIMATED COSTS FOR REQUIRED ACTIONS Action Labor cost HFEC Inspections ........ 13 work-hours × $85 per hour = $1,105 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 proposed AD. daltland on DSKBBV9HB2PROD with PROPOSALS Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. Subtitle VII: Aviation Programs, describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701: ‘‘General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. This proposed 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 We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 this proposed regulation: VerDate Sep<11>2014 16:40 Sep 14, 2018 Jkt 244001 Parts cost $0 Cost per product $1,105 per inspection cycle .... (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Is not a ‘‘significant rule’’ under the 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. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 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): ■ The Boeing Company: Docket No. FAA– 2018–0793; Product Identifier 2018– NM–057–AD. (a) Comments Due Date We must receive comments by November 1, 2018. (b) Affected ADs None. (c) Applicability This AD applies to all The Boeing Company Model 737–100, –200, –200C, –300, –400, and –500 series airplanes, certificated in any category. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Unsafe Condition This AD was prompted by a report of cracks in the body station (STA) 303.9 frame PO 00000 Frm 00019 Fmt 4702 Cost on U.S. operators Sfmt 4702 $74,035 per inspection cycle. web and doubler at fastener holes common to the stop fitting at stringer 16 left (S–16L). We are issuing this AD to address cracks in the STA 303.9 frame web and doubler at the stop fitting at S–16L, which, if not addressed, could result in the inability of a principal structural element to sustain limit loads and possible rapid decompression of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Required Actions for Group 1 For airplanes identified as Group 1 in Boeing Requirements Bulletin 737–53A1375 RB, dated March 12, 2018: Within 120 days after the effective date of this AD, inspect the airplane 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 2 Through 5 Except as specified in paragraph (i) of this AD: For airplanes identified as Groups 2 through 5 in Boeing Requirements Bulletin 737–53A1375 RB, dated March 12, 2018, at the applicable times specified in the ‘‘Compliance’’ paragraph of Boeing Requirements Bulletin 737–53A1375 RB, dated March 12, 2018, do all applicable actions identified in, and in accordance with, the Accomplishment Instructions of Boeing Requirements Bulletin 737–53A1375 RB, dated March 12, 2018. Note 1 to paragraph (h) of this AD: Guidance for accomplishing the actions required by this AD can be found in Boeing Alert Service Bulletin 737–53A1375, dated March 12, 2018, which is referred to in Boeing Requirements Bulletin 737–53A1375 RB, dated March 12, 2018. (i) Exceptions to Service Information Specifications (1) For purposes of determining compliance with the requirements of this AD: Where Boeing Requirements Bulletin 737– 53A1375 RB, dated March 12, 2018, uses the phrase ‘‘the original issue date of Requirements Bulletin 737–53A1375 RB,’’ this AD requires using ‘‘the effective date of this AD.’’ (2) Where Boeing Requirements Bulletin 737–53A1375 RB, dated March 12, 2018, specifies contacting Boeing for repair instructions, this AD requires repair using a method approved in accordance with the procedures specified in paragraph (j) of this AD. E:\FR\FM\17SEP1.SGM 17SEP1 daltland on DSKBBV9HB2PROD with PROPOSALS Federal Register / Vol. 83, No. 180 / Monday, September 17, 2018 / Proposed Rules (j) Alternative Methods of Compliance (AMOCs) DEPARTMENT OF TRANSPORTATION (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: 9-ANM-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, 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. Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2018–0795; Product Identifier 2018–NM–076–AD] RIN 2120–AA64 Airworthiness Directives; Airbus SAS Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to supersede Airworthiness Directive (AD) 2014–20– 04, which applies to all Airbus SAS Model A318 series airplanes; Airbus SAS Model A319 series airplanes; Airbus SAS Model A320–111, –211, –212, –214, –231, –232, and –233 airplanes; and Airbus SAS Model A321– 111, –112, –131, –211, –212, –213, –231, and –232 airplanes. AD 2014–20–04 requires repetitive inspections for cracking of the four titanium angles between the belly fairing and the keel beam side panel, an inspection for cracking of the open holes if any cracking is found in the titanium angles, (k) Related Information and repair or replacement if necessary. (1) For more information about this AD, Since we issued AD 2014–20–04, we contact Galib Abumeri, Aerospace Engineer, have determined that additional work is Airframe Section, FAA, Los Angeles ACO necessary for certain airplanes. This Branch, 3960 Paramount Boulevard, proposed AD would continue to require Lakewood, CA 90712–4137; phone: 562–627– repetitive inspections for cracking of the 5324; fax: 562–627–5210; email: four titanium angles between the belly galib.abumeri@faa.gov. fairing and the keel beam side panel, an (2) For service information identified in inspection for cracking of the open this AD, contact Boeing Commercial holes if any cracking is found in the Airplanes, Attention: Contractual & Data titanium angles, and repair or Services (C&DS), 2600 Westminster Blvd., replacement if necessary. This proposed MC 110–SK57, Seal Beach, CA 90740–5600; AD would also revise the applicability phone: 562–797–1717; internet: https:// by adding Model A320–216 airplanes. www.myboeingfleet.com. You may view this This proposed AD would also require a referenced service information at the FAA, detailed inspection for and replacement Transport Standards Branch, 2200 South of certain rivets (including a rotating 216th St., Des Moines, WA. For information probe test for cracks in the open holes), on the availability of this material at the and corrective actions if necessary. We FAA, call 206–231–3195. are proposing this AD to address the unsafe condition on these products. Issued in Des Moines, Washington, on August 30, 2018. DATES: We must receive comments on this proposed AD by November 1, 2018. Jeffrey E. Duven, ADDRESSES: You may send comments, Director, System Oversight Division, Aircraft using the procedures found in 14 CFR Certification Service. 11.43 and 11.45, by any of the following [FR Doc. 2018–19840 Filed 9–14–18; 8:45 am] methods: BILLING CODE 4910–13–P • Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. VerDate Sep<11>2014 16:40 Sep 14, 2018 Jkt 244001 SUMMARY: PO 00000 Frm 00020 Fmt 4702 Sfmt 4702 46905 • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this NPRM, contact Airbus SAS, Airworthiness Office—EIAS, RondPoint Emile Dewoitine No: 2, 31700 Blagnac Cedex, France; phone: +33 5 61 93 36 96; fax: +33 5 61 93 44 51; email: account.airworth-eas@airbus.com; internet: http://www.airbus.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. Examining the AD Docket You may examine the AD docket on the internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2018– 0795; 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 NPRM, the regulatory evaluation, any comments received, and other information. The street address for Docket Operations (phone: 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; phone and fax 206–231–3223. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA– 2018–0795; Product Identifier 2018– NM–076–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments. We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion We issued AD 2014–20–04, Amendment 39–17977 (79 FR 59636, E:\FR\FM\17SEP1.SGM 17SEP1

Agencies

[Federal Register Volume 83, Number 180 (Monday, September 17, 2018)]
[Proposed Rules]
[Pages 46902-46905]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-19840]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0793; Product Identifier 2018-NM-057-AD]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

[[Page 46903]]

SUMMARY: We propose to adopt a new airworthiness directive (AD) for all 
The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 
series airplanes. This proposed AD was prompted by a report of cracks 
in the body station (STA) 303.9 frame web and doubler at fastener holes 
common to the stop fitting at stringer 16 left (S-16L). This proposed 
AD would require repetitive surface high frequency eddy current (HFEC) 
inspections for cracking of the STA 303.9 frame web and doubler at the 
stop fitting at S-16L, and applicable on-condition actions. We are 
proposing this AD to address the unsafe condition on these products.

DATES: We must receive comments on this proposed AD by November 1, 
2018.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE, Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this NPRM, 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 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 http://www.regulations.gov by searching 
for and locating Docket No. FAA-2018-0793.

Examining the AD Docket

    You may examine the AD docket on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2018-
0793; 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 NPRM, the regulatory evaluation, any comments received, and other 
information. The street address for Docket Operations (phone: 800-647-
5527) is in the ADDRESSES section. Comments will be available in the AD 
docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Galib Abumeri, Aerospace Engineer, 
Airframe Section, FAA, Los Angeles ACO Branch, 3960 Paramount 
Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5324; fax: 562-627-
5210; email: [email protected].

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2018-0793; 
Product Identifier 2018-NM-057-AD'' at the beginning of your comments. 
We specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this NPRM. We will consider all 
comments received by the closing date and may amend this NPRM because 
of those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    We have received a report indicating cracks in the STA 303.9 frame 
web and doubler at fastener holes common to the stop fitting at S-16L. 
The cracks were found during accomplishment of Boeing Service Bulletin 
737-53A1188. We have determined that the existing inspection programs 
are not sufficient to find any crack in the STA 303.9 frame web and 
doubler at the stop fitting at S-16L. This condition, if not addressed, 
could result in the inability of a principal structural element to 
sustain limit loads and possible rapid decompression of the airplane.

Related Service Information Under 1 CFR Part 51

    We reviewed Boeing Requirements Bulletin 737-53A1375 RB, dated 
March 12, 2018. The service information describes procedures for 
repetitive surface HFEC inspections for cracking of the STA 303.9 frame 
web and doubler at the stop fitting at S-16L, 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.

FAA's Determination

    We are proposing this AD because we evaluated all the relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of the same type design.

Proposed AD Requirements

    This proposed AD would require accomplishment of the actions 
identified in Boeing Requirements Bulletin 737-53A1375 RB, dated March 
12, 2018, described previously, except for any differences identified 
as exceptions in the regulatory text of this proposed AD.
    For information on the procedures and compliance times, see this 
service information at http://www.regulations.gov by searching for and 
locating Docket No. FAA-2018-0793.

Explanation of Applicability

    Model 737 airplanes having line numbers 1 through 291 have a limit 
of validity (LOV) of 34,000 total flight cycles, and the actions 
proposed in this NPRM, as specified in Boeing Requirements Bulletin 
737-53A1375 RB, dated March 12, 2018, would be required at a compliance 
time occurring after that LOV. Although operation of an airplane beyond 
its LOV is prohibited by 14 CFR 121.1115 and 129.115, this NPRM would 
include those airplanes in the applicability so that these airplanes 
are tracked in the event the LOV is extended in the future.

Explanation of Requirements Bulletin

    The FAA worked in conjunction with industry, under the 
Airworthiness Directives Implementation Aviation Rulemaking Committee 
(AD ARC), to enhance the AD system. One enhancement is a process for 
annotating which steps in the service information are ``required for 
compliance'' (RC) with an AD. Boeing has implemented this RC concept 
into Boeing service bulletins.
    In an effort to further improve the quality of ADs and AD-related 
Boeing service information, a joint process improvement initiative was 
worked between the FAA and Boeing. The initiative resulted in the 
development of a new process in which the service information more 
clearly identifies the actions needed to address the unsafe condition 
in the ``Accomplishment Instructions.'' The new process results in a 
Boeing Requirements Bulletin, which contains only the actions needed to 
address the unsafe condition (i.e., only the RC actions).

[[Page 46904]]

Costs of Compliance

    We estimate that this proposed AD affects 67 airplanes of U.S. 
registry. We estimate the following costs to comply with this proposed 
AD:

                                      Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
                                                                                                Cost on U.S.
              Action                    Labor cost        Parts cost    Cost per product          operators
----------------------------------------------------------------------------------------------------------------
HFEC Inspections.................  13 work-hours x $85            $0  $1,105 per            $74,035 per
                                    per hour = $1,105                  inspection cycle.     inspection cycle.
                                    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 proposed 
AD.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII: Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701: ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.
    This proposed 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

    We determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 this proposed 
regulation:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under the 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.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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):

The Boeing Company: Docket No. FAA-2018-0793; Product Identifier 
2018-NM-057-AD.

(a) Comments Due Date

    We must receive comments by November 1, 2018.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all The Boeing Company Model 737-100, -200, -
200C, -300, -400, and -500 series airplanes, certificated in any 
category.

(d) Subject

    Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Unsafe Condition

    This AD was prompted by a report of cracks in the body station 
(STA) 303.9 frame web and doubler at fastener holes common to the 
stop fitting at stringer 16 left (S-16L). We are issuing this AD to 
address cracks in the STA 303.9 frame web and doubler at the stop 
fitting at S-16L, which, if not addressed, could result in the 
inability of a principal structural element to sustain limit loads 
and possible rapid decompression of the airplane.

(f) Compliance

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

(g) Required Actions for Group 1

    For airplanes identified as Group 1 in Boeing Requirements 
Bulletin 737-53A1375 RB, dated March 12, 2018: Within 120 days after 
the effective date of this AD, inspect the airplane 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 2 Through 5

    Except as specified in paragraph (i) of this AD: For airplanes 
identified as Groups 2 through 5 in Boeing Requirements Bulletin 
737-53A1375 RB, dated March 12, 2018, at the applicable times 
specified in the ``Compliance'' paragraph of Boeing Requirements 
Bulletin 737-53A1375 RB, dated March 12, 2018, do all applicable 
actions identified in, and in accordance with, the Accomplishment 
Instructions of Boeing Requirements Bulletin 737-53A1375 RB, dated 
March 12, 2018.

    Note 1 to paragraph (h) of this AD:  Guidance for accomplishing 
the actions required by this AD can be found in Boeing Alert Service 
Bulletin 737-53A1375, dated March 12, 2018, which is referred to in 
Boeing Requirements Bulletin 737-53A1375 RB, dated March 12, 2018.

(i) Exceptions to Service Information Specifications

    (1) For purposes of determining compliance with the requirements 
of this AD: Where Boeing Requirements Bulletin 737-53A1375 RB, dated 
March 12, 2018, uses the phrase ``the original issue date of 
Requirements Bulletin 737-53A1375 RB,'' this AD requires using ``the 
effective date of this AD.''
    (2) Where Boeing Requirements Bulletin 737-53A1375 RB, dated 
March 12, 2018, specifies contacting Boeing for repair instructions, 
this AD requires repair using a method approved in accordance with 
the procedures specified in paragraph (j) of this AD.

[[Page 46905]]

(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, 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.

(k) Related Information

    (1) For more information about this AD, contact Galib Abumeri, 
Aerospace Engineer, Airframe Section, FAA, Los Angeles ACO Branch, 
3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-
5324; fax: 562-627-5210; email: [email protected].
    (2) 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. 
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.

    Issued in Des Moines, Washington, on August 30, 2018.
Jeffrey E. Duven,
Director, System Oversight Division, Aircraft Certification Service.
[FR Doc. 2018-19840 Filed 9-14-18; 8:45 am]
 BILLING CODE 4910-13-P