[Federal Register Volume 82, Number 232 (Tuesday, December 5, 2017)]
[Rules and Regulations]
[Pages 57343-57346]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-26040]

––––––––––––––––––––––––––––––––––

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0340; Product Identifier 2017-NM-002-AD; Amendment 39-19114; AD
2017-24-10]

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 certain The Boeing Company
Model 757-200, -200PF, and -300 series airplanes. This AD was prompted by reports of cracking
found at a certain fuselage frame inner chord. This AD requires repetitive inspections for any
cracking of a certain fuselage frame inner chord; identification of the material of a certain fuselage
frame inner chord for certain airplanes; and applicable corrective actions. We are issuing this AD to
address the unsafe condition on these products.

DATES: This AD is effective January 9, 2018.
    The Director of the Federal Register approved the incorporation by reference of certain
publications listed in this AD as of January 9, 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, 1601 Lind Avenue
SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221.
It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket
No. FAA-2017-0340.

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-2017-0340; 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 final
rule, the regulatory evaluation, any comments received, and other information. The address for the

                                                  1

Docket Office (phone: 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: Muoi Vuong, Aerospace Engineer, Airframe
Section, FAA, Los Angeles ACO Branch, 3960 Paramount Boulevard, Lakewood, CA 90712-4137;
phone: 562-627-5205; fax: 562-627-5210; email: Muoi.Vuong@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 certain The Boeing Company Model 757-200, -200PF, and -300 series airplanes.
The NPRM published in the Federal Register on May 19, 2017 (82 FR 22915). The NPRM was
prompted by reports of cracking found at a certain fuselage frame inner chord. The NPRM proposed
to require repetitive inspections for any cracking of a certain fuselage frame inner chord,
identification of the material of a certain fuselage frame inner chord for certain airplanes, and
applicable corrective actions. We are issuing this AD to detect and correct such cracks, which could
result in the cargo door opening during flight, and result in rapid decompression of the airplane and
the inability to sustain loads required for continued safe flight and landing.

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. FedEx and
United Airlines supported the NPRM.

Effect of Winglets on Accomplishment of the Proposed Actions

     Aviation Partners Boeing stated that accomplishing the supplemental type certificate (STC)
ST01518SE does not affect the actions specified in the NPRM.
     We concur with the commenter. We have redesignated paragraph (c) of the proposed AD (82 FR
22915, May 19, 2017) as paragraph (c)(1) of this AD and added paragraph (c)(2) to this AD to state
that installation of STC ST01518SE does not affect the ability to accomplish the actions required by
this AD. Therefore, for airplanes on which STC ST01518SE is installed, a “change in product”
alternative method of compliance (AMOC) approval request is not necessary to comply with the
requirements of 14 CFR 39.17.

Request for Credit for Previous Actions Accomplished

     Boeing requested credit for previous accomplishment of the inspections in the NPRM. Boeing
stated that Boeing Alert Service Bulletin 757-53A0101, dated November 8, 2016 (referenced in the
NPRM as the appropriate source of service information), was published on November 8, 2016.
Boeing commented that the effective date of the AD could be more than 7 months later than
publication date of the service information. Boeing stated that it is likely that some Model 757
operators have already accomplished the inspections in accordance with the service information by
the time the AD takes effect; therefore, the AD should provide credit for those inspections.
     We acknowledge the commenter's request and agree to clarify. Paragraph (f) of this AD states to
accomplish the actions within the compliance times specified, unless those actions are already done.
Therefore, if operators have accomplished the inspections in accordance with the Accomplishment


                                                  2

Instructions of Boeing Alert Service Bulletin 757-53A0101, dated November 8, 2016, before the
effective date of this AD, no further action is necessary. We have not revised this AD in this regard.

Request To Include Repair Information and Inspection Instructions

     Delta Airlines (DAL) stated that it has concerns that the Accomplishment Instructions provided
in Boeing Alert Service Bulletin 757-53A0101, dated November 8, 2016, do not include the
corrective action. DAL commented that it will likely accomplish the inspections during 10-day
maintenance visit checks, which would not be sufficient time for repair development if a crack is
found. DAL also commented that operators would benefit from having corrective actions provided in
the service information.
     DAL stated that Boeing Alert Service Bulletin 757-53A0101, dated November 8, 2016, requires
operators to repetitively inspect the inner chord, and the service information does not provide an
option for an inspection should there be a previously installed FAA-approved repair. DAL
commented that a previous repair of the frame has the potential to inhibit the ability to accomplish the
inspection. DAL also commented that this leaves operators unable to accomplish the inspection as
specified in Boeing Alert Service Bulletin 757-53A0101, dated November 8, 2016, and will require
additional instruction as an AMOC.
     We infer that DAL is requesting to delay issuance of the final rule until a revision of the service
information includes repair data and alternative inspection instructions for previously accomplished
repairs.
     We disagree with the commenter's request. Including the repair data would delay issuance of this
AD. Unique repair configurations may be necessary depending on the cracking that is detected. It is
not possible to address each individual repair configuration in one AD. The various repair
configurations and locations are unknown and therefore cannot be addressed at this time. Therefore,
if cracking is found, it must be repaired before further flight using the corrective actions specified in
Boeing Alert Service Bulletin 757-53A0101, dated November 8, 2016, or in accordance with
paragraph (i)(2) of this AD. For previously approved repairs that prevent accomplishment of the
inspections required by this AD, operators may request approval of an AMOC using the procedures
in paragraph (j) of this AD. We have not revised this AD in this regard.

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 correcting 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 Service Bulletin 757-53A0101, dated November 8, 2016. The service
information describes procedures for repetitive surface high frequency eddy current (HFEC)
inspections for any cracking of the fuselage station (STA) 1380 frame inner chord; an identification
of the material (an inspection or measurement) of the fuselage STA 1380 frame inner chord; and
applicable corrective actions. This service information is reasonably available because the interested
parties have access to it through their normal course of business or by the means identified in the
ADDRESSES section.


                                                   3

Costs of Compliance

     We estimate that this AD affects 588 airplanes of U.S. registry. We estimate the following costs
to comply with this AD:

                                           Estimated Costs
      Action                  Labor cost               Parts        Cost per             Cost on U.S.
                                                        cost        product               operators
Surface HFEC       5 work-hours × $85 per hour =       $0       $425 per           $249,900 per
inspection         $425 per inspection cycle                    inspection cycle   inspection cycle.
Identify the       Up to 2 work-hours × $85 per        0        Up to $170         Up to $99,960.
material           hour = $170

    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 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 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.

                                                   4

Adoption of the Amendment

     Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR
part 39 as follows:

PART 39–AIRWORTHINESS DIRECTIVES

1. The authority citation for part 39 continues to read as follows:

    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):




                                                    5

AIRWORTHINESS
                 FAA                                  DIRECTIVE
                 Aviation Safety
                                                      www.faa.gov/aircraft/safety/alerts/
                                                      www.gpoaccess.gov/fr/advanced.html


2017-24-10 The Boeing Company: Amendment 39-19114; Docket No. FAA-2017-0340; Product
Identifier 2017-NM-002-AD.

(a) Effective Date

    This AD is effective January 9, 2018.

(b) Affected ADs

    None.

(c) Applicability

     (1) This AD applies to The Boeing Company Model 757-200, -200PF, and -300 series airplanes,
certificated in any category, as identified in Boeing Alert Service Bulletin 757-53A0101, dated
November 8, 2016.
     (2) Installation of Supplemental Type Certificate (STC) ST01518SE does not affect the ability to
accomplish the actions required by this AD. Therefore, for airplanes on which STC ST01518SE is
installed, a “change in product” alternative method of compliance (AMOC) approval request is not
necessary to comply with the requirements of 14 CFR 39.17.

(d) Subject

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

(e) Unsafe Condition

     This AD was prompted by reports of cracking found at the fuselage station (STA) 1380 frame
inner chord. We are issuing this AD to detect and correct such cracks, which could result in the cargo
door opening during flight, and result in rapid decompression of the airplane and the inability to
sustain loads required for continued safe flight and landing.

(f) Compliance

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

(g) Inspection for Group 1 Airplanes

     For Group 1 airplanes as identified in Boeing Alert Service Bulletin 757-53A0101, dated
November 8, 2016: At the applicable time specified in paragraph 1.E., “Compliance,” of Boeing
Alert Service Bulletin 757-53A0101, dated November 8, 2016; except as specified in paragraph (i)(1)
of this AD, do a surface high frequency eddy current (HFEC) inspection for any cracking of the
fuselage STA 1380 frame inner chord, and do all applicable corrective actions, in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 757-53A0101, dated November 8,

                                                  6

2016; except as specified in paragraph (i)(2) of this AD. Do all applicable corrective actions before
further flight. Repeat the surface HFEC inspection, thereafter, at the times specified in paragraph
1.E., “Compliance,” of Boeing Alert Service Bulletin 757-53A0101, dated November 8, 2016.

(h) Inspection for Group 2 Airplanes

     For Group 2 airplanes as identified in Boeing Alert Service Bulletin 757-53A0101, dated
November 8, 2016: At the applicable time specified in paragraph 1.E., “Compliance,” of Boeing
Alert Service Bulletin 757-53A0101, dated November 8, 2016, except as specified in paragraph (i)(1)
of this AD, identify the material of the fuselage STA 1380 frame inner chord, in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 757-53A0101, dated November 8,
2016.
     (1) If the fuselage STA 1380 frame inner chord material 2024-T42 aluminum alloy is found
during any identification required by paragraph (h) of this AD: No further action is required by this
AD for that airplane.
     (2) If the fuselage STA 1380 frame inner chord material 7075-T73 aluminum alloy is found
during any identification required by the introductory text of paragraph (h) of this AD: Before further
flight, do a surface HFEC inspection for any cracking of the fuselage STA 1380 frame inner chord,
and do all applicable corrective actions, in accordance with the Accomplishment Instructions of
Boeing Alert Service Bulletin 757-53A0101, dated November 8, 2016; except as specified in
paragraph (i)(2) of this AD. Do all applicable corrective actions before further flight. Repeat the
surface HFEC inspection thereafter at the times specified in paragraph 1.E., “Compliance,” of Boeing
Alert Service Bulletin 757-53A0101, dated November 8, 2016.

(i) Exceptions to the Service Information

    (1) Where Boeing Alert Service Bulletin 757-53A0101, dated November 8, 2016, specifies a
compliance time “after the original issue date of this service bulletin,” this AD requires compliance
within the specified compliance time after the effective date of this AD.
    (2) Where Boeing Alert Service Bulletin 757-53A0101, dated November 8, 2016, specifies to
contact Boeing for appropriate action and identifies that action as “RC” (Required for Compliance):
Before further flight, repair the crack 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 ACO, send it to the attention of the person
identified in paragraph (k) 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, 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.


                                                     7

(4) Except as required by paragraph (i)(2) of this AD: For service information that contains steps
that are labeled as RC, the provisions of paragraphs (j)(4)(i) and (j)(4)(ii) of this AD apply.
     (i) The steps labeled as RC, including substeps under an RC step and any figures identified in an
RC step, must be done to comply with the AD. If a step or substep is labeled “RC Exempt,” then the
RC requirement is removed from that step or substep. An AMOC is required for any deviations to RC
steps, including substeps and identified figures.
     (ii) Steps not labeled as RC may be deviated from using accepted methods in accordance with
the operator's maintenance or inspection program without obtaining approval of an AMOC, provided
the RC steps, including substeps and identified figures, can still be done as specified, and the airplane
can be put back in an airworthy condition.

(k) Related Information

    For more information about this AD, contact Muoi Vuong, Aerospace Engineer, Airframe
Section, FAA, Los Angeles ACO, 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone:
562-627-5205; fax: 562-627-5210; email: Muoi.Vuong@faa.gov.

(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 Service Bulletin 757-53A0101, dated November 8, 2016.
     (ii) Reserved.
     (3) For Boeing service information identified in this AD, contact Boeing Commercial Airplanes,
Attention: Contractual & Data Services (C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal
Beach, CA 90740-5600; telephone 562-797-1717; Internet https://www.myboeingfleet.com.
     (4) You may view this service information at the FAA, Transport Standards Branch, 1601 Lind
Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-
227-1221.
     (5) You may view this service information that is incorporated by reference at the National
Archives and Records Administration (NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

     Issued in Renton, Washington, on November 22, 2017.
Jeffrey E. Duven,
Director, System Oversight Division,
Aircraft Certification Service.




                                                   8

Lufttüchtigkeitsanweisung                     Luftfahrt-Bundesamt
                                                                                       - Sachgebiet T23 -
                                               D-2017-297                            38144 Braunschweig
                                       EASA AD 2017-0249 vom 14.12.2017              Fax: +49-531-2355-5298
                                                                                     email: ad@LBA.de

AIRBUS                                                                                      15.12.2017

Betroffenes Luftfahrtgerät:
Art des Luftfahrtgerätes:       Flugzeug
Inhaber der Musterzulassung:    AIRBUS S.A.S
Hersteller:                     Airbus

Muster:                         A380

Baureihen:                      A380-841, A380-842 und
                                A380-861

Werknummern:                    Alle

Gerätenummer:                   EASA.A.110

Revisionsstand:
Originalausgabe
Airworthiness Directive der ausländischen Behörde:
EASA AD 2017-0249 vom 14.12.2017

Genannte Airworthiness Directives unter dieser Rubrik, die nicht durch die EASA herausgegeben worden sind,
wurden durch die EASA über die Entscheidung Nr. 02/2003 übernommen und sind somit ebenfalls Airworthiness
Directives der EASA.
Die genannte Airworthiness Directive wird im Luftfahrt-Bundesamt unter der Nummer 2017-297 geführt.
Betrifft:
(ATA 32) Landing Gear - Nose Landing Gear Components - Replacement (Life Limit)

Anmerkungen:
Gemäß M.A.303 und M.A.301 5.i) des Anhang I der Verordnung (EU) Nr. 1321/2014 (Teil-M) dürfen Luftfahr-
zeuge nach dem in der Lufttüchtigkeitsanweisung angegebenen Termin nur in Betrieb genommen werden,
wenn die angeordneten Maßnahmen ordnungsgemäß durchgeführt worden sind.
Die Europäische Agentur für Flugsicherheit (EASA) hat die oben referenzierte Lufttüchtigkeitsanweisung
EASA AD 2017-0249 vom 14.12.2017 herausgegeben oder per Entscheidung Nr. 02/2003 übernommen.
Gemäß § 14 Abs. 2 der Betriebsordnung für Luftfahrtgerät (LuftBO) sind diese Lufttüchtigkeitsanweisun-
gen direkt in der Bundesrepublik Deutschland gültig und bedürfen keiner Umsetzung durch das Luftfahrt-
Bundesamt.
Mit Hilfe dieser Übersichtsseite veröffentlicht das Luftfahrt-Bundesamt ebenfalls die über § 14 Abs. 2 direkt
gültigen Lufttüchtigkeitsanweisungen der EASA in den Nachrichten für Luftfahrer und im Internet unter
www2.LBA.de/LTAs/. Dieser Service dient reinen Informationszwecken und liegt keinem Verwaltungsver-
fahren zu Grunde. Rechtsmittel sind damit ausgeschlossen.




D-2017-297                                     Seite 1 von 1                                          540/2017

EASA AD No.: 2017-0249


                                                                  Airworthiness Directive
                                                                  AD No.:              2017-0249
                                                                  Issued:              14 December 2017
                                                                  Note: This Airworthiness Directive (AD) is issued by EASA, acting in accordance with Regulation
                                                                  (EC) 216/2008 on behalf of the European Union, its Member States and of the European third
                                                                  countries that participate in the activities of EASA under Article 66 of that Regulation.

         This AD is issued in accordance with Regulation (EU) 748/2012, Part 21.A.3B. In accordance with Regulation (EU) 1321/2014 Annex I, Part M.A.301, the
         continuing airworthiness of an aircraft shall be ensured by accomplishing any applicable ADs. Consequently, no person may operate an aircraft to which
         an AD applies, except in accordance with the requirements of that AD, unless otherwise specified by the Agency [Regulation (EU) 1321/2014 Annex I,
         Part M.A.303] or agreed with the Authority of the State of Registry [Regulation (EC) 216/2008, Article 14(4) exemption].


         Design Approval Holder’s Name:                                                      Type/Model designation(s):
         AIRBUS                                                                              A380 aeroplanes

         Effective Date:                 28 December 2017
         TCDS Number(s): EASA.A.110
         Foreign AD:                     Not applicable
         Supersedure:                    None


         ATA 32 – Landing Gear – Nose Landing Gear Components – Replacement [Life Limit]


         Manufacturer(s):
         Airbus

         Applicability:
         Airbus A380-841, A380-842 and A380-861 aeroplanes, all manufacturer serial numbers.

         Reason:
         The A380 nose landing gear (NLG) manufacturer has determined that a certain batch of NLG main
         fittings and NLG sliding tubes was subject to improper preparation of 300M material used in the
         manufacturing process.

         This condition, if not corrected, could lead to structural failure of an NLG component and consequent
         NLG collapse, possibly resulting in loss of control of the aeroplane during take-off or landing.

         To address this potential unsafe condition, Airbus established reduced fatigue lives for the NLG main
         fittings and NLG sliding tubes affected by the degradation of 300M material quality.

         For the reasons described above, this AD requires removal from service of the affected NLG main
         fittings and NLG sliding tubes before exceeding the reduced life limit.




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An agency of the European Union