83 FR 51887 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 83, Issue 199 (October 15, 2018)
Federal Aviation Administration
Federal Register Volume 83, Issue 199 (October 15, 2018)
| Page Range | 51887-51889 | |
| FR Document | 2018-21966 |
[Federal Register Volume 83, Number 199 (Monday, October 15, 2018)] [Proposed Rules] [Pages 51887-51889] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2018-21966] ======================================================================== Proposed Rules Federal Register ________________________________________________________________________ This section of the FEDERAL REGISTER contains notices to the public of the proposed issuance of rules and regulations. The purpose of these notices is to give interested persons an opportunity to participate in the rule making prior to the adoption of the final rules. ======================================================================== Federal Register / Vol. 83, No. 199 / Monday, October 15, 2018 / Proposed Rules [[Page 51887]] DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2018-0899; Product Identifier 2018-NM-099-AD] RIN 2120-AA64 Airworthiness Directives; The Boeing Company Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). ----------------------------------------------------------------------- SUMMARY: We propose to adopt a new airworthiness directive (AD) for certain The Boeing Company Model 757 airplanes. This proposed AD was prompted by an evaluation by the design approval holder (DAH) indicating that the inner skin at the lower fastener row is subject to widespread fatigue damage (WFD). This proposed AD would require a general visual inspection of certain lap splice inspection areas for any repair common to the fuselage skin lap splice inspection areas, repetitive dual frequency eddy current (DFEC) inspections of a certain lap splice inner skin for any crack, 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 29, 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; telephone 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-2018-0899. 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- 0899; 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: David Truong, Aerospace Engineer, Airframe Section, FAA, Los Angeles ACO Branch, 3960 Paramount Boulevard, Lakewood, CA 90712 4137; phone: 562-627-5224; 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-2018-0899; Product Identifier 2018-NM-099-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 Fatigue damage can occur locally, in small areas or structural design details, or globally, in widespread areas. Multiple-site damage is widespread damage that occurs in a large structural element such as a single rivet line of a lap splice joining two large skin panels. Widespread damage can also occur in multiple elements such as adjacent frames or stringers. Multiple-site damage and multiple-element damage cracks are typically too small initially to be reliably detected with normal inspection methods. Without intervention, these cracks will grow, and eventually compromise the structural integrity of the airplane. This condition is known as WFD. It is associated with general degradation of large areas of structure with similar structural details and stress levels. As an airplane ages, WFD will likely occur, and will certainly occur if the airplane is operated long enough without any intervention. The FAA's WFD final rule (75 FR 69746, November 15, 2010) became effective on January 14, 2011. The WFD rule requires certain actions to prevent structural failure due to WFD throughout the operational life of certain existing transport category airplanes and all of these airplanes that will be certificated in the future. For existing and future airplanes subject to the WFD rule, the rule requires that DAHs establish a limit of validity (LOV) of the engineering data that support the structural maintenance program. Operators affected by the WFD rule may not fly an airplane beyond its LOV, unless an extended LOV is approved. The WFD rule (75 FR 69746, November 15, 2010) does not require identifying and developing maintenance actions if the DAHs can show that such actions are not necessary to prevent WFD before the airplane reaches the LOV. Many LOVs, however, do depend on accomplishment of future maintenance actions. As stated in the WFD rule, any maintenance actions necessary to reach the LOV will be mandated by airworthiness directives through separate rulemaking actions. [[Page 51888]] In the context of WFD, this action is necessary to enable DAHs to propose LOVs that allow operators the longest operational lives for their airplanes, and still ensure that WFD will not occur. This approach allows for an implementation strategy that provides flexibility to DAHs in determining the timing of service information development (with FAA approval), while providing operators with certainty regarding the LOV applicable to their airplanes. We have received a report indicating the inner skin at the lower fastener row is subject to WFD. The inner skin at the lap splice could also have scratches that can grow into scratch cracks, which could interact with multi-site damage (MSD) fastener hole fatigue cracking. This condition, if not addressed, could result in accelerated crack growth rate, which could result in reduced structural integrity of the airplane. Related Service Information Under 1 CFR Part 51 We reviewed Boeing Alert Requirements Bulletin 757-53A0111 RB, dated May 21, 2018. The service information describes procedures for a general visual inspection of certain lap splice inspection areas for any repair common to the fuselage skin lap splice inspection areas, repetitive DFEC inspections of the S-14 lap splice inner skin for any crack, 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 Alert Requirements Bulletin 757-53A0111 RB, dated May 21, 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-2018-0899. 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). Costs of Compliance We estimate that this proposed AD affects 451 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 ---------------------------------------------------------------------------------------------------------------- General visual inspection...... Up to 6 work-hours x $0 Up to $510........ Up to $230,010. $85 per hour = up to $510. Repetitive DFEC inspections.... Up to 124 work-hours x 0 Up to $10,540 per Up to $4,753,540 $85 per hour = up to inspection cycle. per inspection $10,540 per inspection cycle. 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. [[Page 51889]] 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-2018-0899; Product Identifier 2018-NM-099-AD. (a) Comments Due Date We must receive comments by November 29, 2018. (b) Affected ADs None. (c) Applicability This AD applies to The Boeing Company Model 757-200, -200PF, - 200CB, and -300 series airplanes, certificated in any category, as identified in Boeing Alert Requirements Bulletin 757-53A0111 RB, dated May 21, 2018. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Unsafe Condition This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the inner skin at the lower fastener row is subject to widespread fatigue damage (WFD). We are issuing this AD to address scratches that can grow into scratch cracks, which could interact with multi-site damage (MSD) fastener hole fatigue cracking. This condition, if not addressed, could result in accelerated crack growth rate, which could result in reduced structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Required Actions Except as specified by paragraph (h) of this AD: At the applicable times specified in the ``Compliance'' paragraph of Boeing Alert Requirements Bulletin 757-53A0111 RB, dated May 21, 2018, do all applicable actions identified in, and in accordance with, the Accomplishment Instructions of Boeing Alert Requirements Bulletin 757-53A0111 RB, dated May 21, 2018. Note 1 to paragraph (g) of this AD: Guidance for accomplishing the actions required by this AD can be found in Boeing Alert Service Bulletin 757-53A0111, dated May 21, 2018, which is referred to in Boeing Alert Requirements Bulletin 757-53A0111 RB, dated May 21, 2018. (h) Exceptions to Service Information Specifications (1) For purposes of determining compliance with the requirements of this AD: Where Boeing Alert Requirements Bulletin 757-53A0111 RB, dated May 21, 2018, uses the phrase ``the original issue date of Requirements Bulletin 757-53A0111 RB,'' this AD requires using ``the effective date of this AD.'' (2) Where Boeing Alert Requirements Bulletin 757-53A0111 RB, dated May 21, 2018, specifies contacting Boeing for alternative inspections or repair instructions, this AD requires alternative inspection or repair before further flight using a method approved in accordance with the procedures specified in paragraph (i) of this AD. (3) Inspections performed in accordance with Boeing Alert Requirements Bulletin 757-53A0111 RB, dated May 21, 2018, are not necessary in areas where existing FAA approved repairs cover the affected inspection areas; provided the outermost repair doubler extends a minimum of three rows of fasteners above and below the original group of lap splice fasteners subject to the inspection. Damage tolerance inspections specified for existing repairs must continue. Inspections outside of the repaired boundaries are still required as specified in Boeing Alert Requirements Bulletin 757- 53A0111 RB, dated May 21, 2018. (i) 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 (j)(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. (j) Related Information (1) For more information about this AD, contact David Truong, Aerospace Engineer, Airframe Section, FAA, Los Angeles ACO Branch, 3960 Paramount Boulevard, Lakewood, CA 90712 4137; phone: 562-627- 5224; 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; telephone 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 September 20, 2018. John P. Piccola, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2018-21966 Filed 10-12-18; 8:45 am] BILLING CODE 4910-13-P
![51887
Proposed Rules Federal Register
Vol. 83, No. 199
Monday, October 15, 2018
This section of the FEDERAL REGISTER p.m., Monday through Friday, except www.regulations.gov, including any
contains notices to the public of the proposed Federal holidays. personal information you provide. We
issuance of rules and regulations. The For service information identified in will also post a report summarizing each
purpose of these notices is to give interested this NPRM, contact Boeing Commercial substantive verbal contact we receive
persons an opportunity to participate in the Airplanes, Attention: Contractual & Data about this proposed AD.
rule making prior to the adoption of the final
rules.
Services (C&DS), 2600 Westminster
Discussion
Blvd., MC 110–SK57, Seal Beach, CA
90740–5600; telephone 562–797–1717; Fatigue damage can occur locally, in
DEPARTMENT OF TRANSPORTATION internet https:// small areas or structural design details,
www.myboeingfleet.com. You may view or globally, in widespread areas.
Federal Aviation Administration this referenced service information at Multiple-site damage is widespread
the FAA, Transport Standards Branch, damage that occurs in a large structural
14 CFR Part 39 2200 South 216th St., Des Moines, WA. element such as a single rivet line of a
For information on the availability of lap splice joining two large skin panels.
[Docket No. FAA–2018–0899; Product
Identifier 2018–NM–099–AD] this material at the FAA, call 206–231– Widespread damage can also occur in
3195. It is also available on the internet multiple elements such as adjacent
RIN 2120–AA64 at http://www.regulations.gov by frames or stringers. Multiple-site
searching for and locating Docket No. damage and multiple-element damage
Airworthiness Directives; The Boeing FAA–2018–0899. cracks are typically too small initially to
Company Airplanes be reliably detected with normal
Examining the AD Docket
AGENCY: Federal Aviation inspection methods. Without
Administration (FAA), DOT. You may examine the AD docket on intervention, these cracks will grow,
ACTION: Notice of proposed rulemaking
the internet at http:// and eventually compromise the
(NPRM). www.regulations.gov by searching for structural integrity of the airplane. This
and locating Docket No. FAA–2018– condition is known as WFD. It is
SUMMARY: We propose to adopt a new 0899; or in person at Docket Operations associated with general degradation of
airworthiness directive (AD) for certain between 9 a.m. and 5 p.m., Monday large areas of structure with similar
The Boeing Company Model 757 through Friday, except Federal holidays. structural details and stress levels. As
airplanes. This proposed AD was The AD docket contains this NPRM, the an airplane ages, WFD will likely occur,
prompted by an evaluation by the regulatory evaluation, any comments and will certainly occur if the airplane
design approval holder (DAH) received, and other information. The is operated long enough without any
indicating that the inner skin at the street address for Docket Operations intervention.
lower fastener row is subject to (phone: 800–647–5527) is in the The FAA’s WFD final rule (75 FR
widespread fatigue damage (WFD). This ADDRESSES section. Comments will be 69746, November 15, 2010) became
proposed AD would require a general available in the AD docket shortly after effective on January 14, 2011. The WFD
visual inspection of certain lap splice receipt. rule requires certain actions to prevent
inspection areas for any repair common FOR FURTHER INFORMATION CONTACT: structural failure due to WFD
to the fuselage skin lap splice inspection David Truong, Aerospace Engineer, throughout the operational life of
areas, repetitive dual frequency eddy Airframe Section, FAA, Los Angeles certain existing transport category
current (DFEC) inspections of a certain ACO Branch, 3960 Paramount airplanes and all of these airplanes that
lap splice inner skin for any crack, and Boulevard, Lakewood, CA 90712 4137; will be certificated in the future. For
applicable on-condition actions. We are phone: 562–627–5224; fax: 562–627– existing and future airplanes subject to
proposing this AD to address the unsafe 5210; email: david.truong@faa.gov. the WFD rule, the rule requires that
condition on these products. SUPPLEMENTARY INFORMATION: DAHs establish a limit of validity (LOV)
DATES: We must receive comments on of the engineering data that support the
this proposed AD by November 29, Comments Invited structural maintenance program.
2018. We invite you to send any written Operators affected by the WFD rule may
ADDRESSES: You may send comments, relevant data, views, or arguments about not fly an airplane beyond its LOV,
using the procedures found in 14 CFR this proposal. Send your comments to unless an extended LOV is approved.
11.43 and 11.45, by any of the following an address listed under the ADDRESSES The WFD rule (75 FR 69746,
methods: section. Include ‘‘Docket No. FAA– November 15, 2010) does not require
• Federal eRulemaking Portal: Go to 2018–0899; Product Identifier 2018– identifying and developing maintenance
http://www.regulations.gov. Follow the NM–099–AD’’ at the beginning of your actions if the DAHs can show that such
instructions for submitting comments. comments. We specifically invite actions are not necessary to prevent
khammond on DSK30JT082PROD with PROPOSAL
• Fax: 202–493–2251. comments on the overall regulatory, WFD before the airplane reaches the
• Mail: U.S. Department of economic, environmental, and energy LOV. Many LOVs, however, do depend
Transportation, Docket Operations, M– aspects of this NPRM. We will consider on accomplishment of future
30, West Building Ground Floor, Room all comments received by the closing maintenance actions. As stated in the
W12–140, 1200 New Jersey Avenue SE, date and may amend this NPRM WFD rule, any maintenance actions
Washington, DC 20590. because of those comments. necessary to reach the LOV will be
• Hand Delivery: Deliver to Mail We will post all comments we mandated by airworthiness directives
address above between 9 a.m. and 5 receive, without change, to http:// through separate rulemaking actions.
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![Federal Register / Vol. 83, No. 199 / Monday, October 15, 2018 / Proposed Rules 51889
List of Subjects in 14 CFR Part 39 Note 1 to paragraph (g) of this AD: (j) Related Information
Guidance for accomplishing the actions (1) For more information about this AD,
Air transportation, Aircraft, Aviation required by this AD can be found in Boeing
safety, Incorporation by reference, contact David Truong, Aerospace Engineer,
Alert Service Bulletin 757–53A0111, dated Airframe Section, FAA, Los Angeles ACO
Safety. May 21, 2018, which is referred to in Boeing Branch, 3960 Paramount Boulevard,
The Proposed Amendment Alert Requirements Bulletin 757–53A0111 Lakewood, CA 90712 4137; phone: 562–627–
RB, dated May 21, 2018. 5224; fax: 562–627–5210; email:
Accordingly, under the authority david.truong@faa.gov.
delegated to me by the Administrator, (h) Exceptions to Service Information
(2) For service information identified in
the FAA proposes to amend 14 CFR part Specifications
this AD, contact Boeing Commercial
39 as follows: (1) For purposes of determining Airplanes, Attention: Contractual & Data
compliance with the requirements of this AD: Services (C&DS), 2600 Westminster Blvd.,
PART 39—AIRWORTHINESS Where Boeing Alert Requirements Bulletin MC 110–SK57, Seal Beach, CA 90740–5600;
DIRECTIVES 757–53A0111 RB, dated May 21, 2018, uses telephone 562–797–1717; internet https://
the phrase ‘‘the original issue date of www.myboeingfleet.com. You may view this
■ 1. The authority citation for part 39 Requirements Bulletin 757–53A0111 RB,’’ referenced service information at the FAA,
continues to read as follows: this AD requires using ‘‘the effective date of Transport Standards Branch, 2200 South
this AD.’’ 216th St., Des Moines, WA. For information
Authority: 49 U.S.C. 106(g), 40113, 44701. (2) Where Boeing Alert Requirements on the availability of this material at the
§ 39.13 [Amended] Bulletin 757–53A0111 RB, dated May 21, FAA, call 206–231–3195.
2018, specifies contacting Boeing for
■ 2. The FAA amends § 39.13 by adding alternative inspections or repair instructions, Issued in Des Moines, Washington, on
the following new airworthiness this AD requires alternative inspection or September 20, 2018.
directive (AD): repair before further flight using a method John P. Piccola,
The Boeing Company: Docket No. FAA– approved in accordance with the procedures Acting Director, System Oversight Division,
2018–0899; Product Identifier 2018– specified in paragraph (i) of this AD. Aircraft Certification Service.
NM–099–AD. (3) Inspections performed in accordance
[FR Doc. 2018–21966 Filed 10–12–18; 8:45 am]
with Boeing Alert Requirements Bulletin
(a) Comments Due Date 757–53A0111 RB, dated May 21, 2018, are BILLING CODE 4910–13–P
We must receive comments by November not necessary in areas where existing FAA
29, 2018. approved repairs cover the affected
inspection areas; provided the outermost DEPARTMENT OF TRANSPORTATION
(b) Affected ADs repair doubler extends a minimum of three
None. rows of fasteners above and below the Federal Aviation Administration
(c) Applicability original group of lap splice fasteners subject
to the inspection. Damage tolerance 14 CFR Part 39
This AD applies to The Boeing Company inspections specified for existing repairs
Model 757–200, –200PF, –200CB, and –300 must continue. Inspections outside of the [Docket No. FAA–2018–0807; Product
series airplanes, certificated in any category, repaired boundaries are still required as Identifier 2018–NM–003–AD]
as identified in Boeing Alert Requirements specified in Boeing Alert Requirements
Bulletin 757–53A0111 RB, dated May 21, Bulletin 757–53A0111 RB, dated May 21,
2018. RIN 2120–AA64
2018.
(d) Subject (i) Alternative Methods of Compliance Airworthiness Directives; Airbus
Air Transport Association (ATA) of (AMOCs) Airplanes
America Code 53, Fuselage. (1) The Manager, Los Angeles ACO Branch, AGENCY: Federal Aviation
(e) Unsafe Condition FAA, has the authority to approve AMOCs Administration (FAA), DOT.
for this AD, if requested using the procedures
This AD was prompted by an evaluation by ACTION: Notice of proposed rulemaking
found in 14 CFR 39.19. In accordance with
the design approval holder (DAH) indicating (NPRM).
14 CFR 39.19, send your request to your
that the inner skin at the lower fastener row
principal inspector or local Flight Standards
is subject to widespread fatigue damage SUMMARY: We propose to adopt a new
District Office, as appropriate. If sending
(WFD). We are issuing this AD to address airworthiness directive (AD) for certain
information directly to the manager of the
scratches that can grow into scratch cracks, Airbus Model A330–200, A330–300,
certification office, send it to the attention of
which could interact with multi-site damage
(MSD) fastener hole fatigue cracking. This
the person identified in paragraph (j)(1) of A340–200, and A340–300 series
this AD. Information may be emailed to: 9- airplanes. This proposed AD was
condition, if not addressed, could result in
accelerated crack growth rate, which could ANM-LAACO-AMOC-Requests@faa.gov. prompted by a report that revealed the
result in reduced structural integrity of the (2) Before using any approved AMOC, wheel axles of the main landing gear
airplane. notify your appropriate principal inspector, (MLG) were machined with a radius as
or lacking a principal inspector, the manager
(f) Compliance of the local flight standards district office/
small as 0.4 millimeters and a
certificate holding district office. determination that the life limit for the
Comply with this AD within the affected wheel axles of the MLG must be
compliance times specified, unless already (3) An AMOC that provides an acceptable
done. level of safety may be used for any repair, reduced. This proposed AD would
modification, or alteration required by this require an inspection to determine the
(g) Required Actions AD if it is approved by the Boeing part number and serial number of each
khammond on DSK30JT082PROD with PROPOSAL
Except as specified by paragraph (h) of this Commercial Airplanes Organization MLG wheel axle and replacement of
AD: At the applicable times specified in the Designation Authorization (ODA) that has affected parts prior to exceeding the
‘‘Compliance’’ paragraph of Boeing Alert been authorized by the Manager, Los Angeles reduced life limits. We are proposing
Requirements Bulletin 757–53A0111 RB, ACO Branch, FAA, to make those findings. this AD to address the unsafe condition
dated May 21, 2018, do all applicable actions To be approved, the repair method,
modification deviation, or alteration
on these products.
identified in, and in accordance with, the
Accomplishment Instructions of Boeing Alert deviation must meet the certification basis of DATES: We must receive comments on
Requirements Bulletin 757–53A0111 RB, the airplane, and the approval must this proposed AD by November 29,
dated May 21, 2018. specifically refer to this AD. 2018.
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Document Created: 2018-10-13 10:03:15
Document Modified: 2018-10-13 10:03:15
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Proposed Rules | |
| Action | Notice of proposed rulemaking (NPRM). | |
| Dates | We must receive comments on this proposed AD by November 29, 2018. | |
| Contact | David Truong, Aerospace Engineer, Airframe Section, FAA, Los Angeles ACO Branch, 3960 Paramount Boulevard, Lakewood, CA 90712 4137; phone: 562-627-5224; fax: 562-627- 5210; email: [email protected] | |
| FR Citation | 83 FR 51887 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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