AD 2017-12-14

[Federal Register Volume 82, Number 117 (Tuesday, June 20, 2017)]
[Rules and Regulations]
[Pages 27970-27972]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2017-12397]


=======================================================================
-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-9502; Directorate Identifier 2016-NM-128-AD; 
Amendment 39-18929; AD 2017-12-14]
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 and -200PF series airplanes. This AD 
was prompted by an evaluation by the design approval holder (DAH) 
indicating that certain areas of the frame webs are subject to 
widespread fatigue damage (WFD). This AD requires inspections of the 
frame webs for any crack of any open coordinating holes, tooling holes, 
and insulation blanket attachment holes; repair if necessary; and 
modification of the frame webs at all open hole locations, which would 
terminate the repetitive inspections. We are issuing this AD to address 
the unsafe condition on these products.

DATES: This AD is effective July 25, 2017.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of July 25, 
2017.

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 <a href="https://www.myboeingfleet.com">https://www.myboeingfleet.com</a>. You may view this service information at the 
FAA, Transport Airplane Directorate, 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 <a href="http://www.regulations.gov">http://www.regulations.gov</a> by searching for and locating Docket No. FAA-2016-
9502.

Examining the AD Docket

    You may examine the AD docket on the Internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a> by searching for and locating Docket No. FAA-2016-
9502; 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 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 Branch, ANM-120L, FAA, Los Angeles Aircraft Certification 
Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 
562-627-5205; fax: 562-627-5210; email: <a href="/cdn-cgi/l/email-protection#513c243e387f27243e3f36113730307f363e27"><span class="__cf_email__" data-cfemail="e78a92888ec99192888980a7818686c9808891">[email&#160;protected]</span></a>.

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 and -200PF series airplanes. The NPRM published in the 
Federal Register on December 20, 2016 (81 FR 92742) (``the NPRM''). The 
NPRM was prompted by an evaluation by the DAH indicating that certain 
areas of the frame webs are subject to WFD. The NPRM proposed to 
require high frequency eddy current (HFEC) inspections of the frame 
webs for any crack in any open coordinating holes, tooling holes, and 
insulation blanket attachment holes; repair if necessary; and 
modification of the frame webs at all open hole locations, which would 
terminate the repetitive inspections. We are issuing this AD to prevent 
fatigue cracking that could result in reduced structural integrity of 
the airplane.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We have considered the comments received. Boeing Commercial 
Airplanes, 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 proposed AD.
    We concur with the commenter. We have redesignated paragraph (c) of 
the proposed AD as paragraph (c)(1) of this AD and added paragraph 
(c)(2) to this AD to state that installation of STC 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.

Additional Change to Proposed AD

    We have revised paragraph (g) of this AD to specify all compliance 
times, rather than referring to the service information because a 
certain compliance time specified in the service information is 
relative to the issue date of the service information. For this AD, 
that compliance time is relative to the effective date of this AD.

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:
    <bullet> Are consistent with the intent that was proposed in the 
NPRM for correcting the unsafe condition; and

[[Page 27971]]

    <bullet> 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 757-53A0103, dated June 
22, 2016. The service information describes procedures for performing 
repetitive HFEC inspections of the frame webs for any crack of any open 
coordinating holes, tooling holes, and insulation blanket attachment 
holes; and modifying the frame webs between stringers S-20 and S-25. 
This service information is reasonably available because the interested 
parties have access to it through their normal course of business or by 
the means identified in the ADDRESSES section.

Costs of Compliance

    We estimate that this AD affects 74 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                Cost on U.S.
              Action                    Labor cost        Parts cost    Cost per product          operators
----------------------------------------------------------------------------------------------------------------
HFEC inspection..................  68 work-hours x $85            $0  $5,780 per            $427,720 per
                                    per hour = $5,780                  inspection cycle.     inspection cycle.
                                    per inspection
                                    cycle.
Modification.....................  1 work-hour x $85           \1\ 0  85..................  85.
                                    per hour = $85.
----------------------------------------------------------------------------------------------------------------
\1\ Parts supplied by the operator.

    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.

Regulatory Findings

    This AD will not have federalism implications under Executive Order 
13132. This AD will not have a substantial direct effect on the States, 
on the relationship between the national government and the States, or 
on the distribution of power and responsibilities among the various 
levels of government.
    For the reasons discussed above, I certify that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979),
    (3) Will not affect intrastate aviation in Alaska, and
    (4) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

2017-12-14 The Boeing Company: Amendment 39-18929; Docket No. FAA-
2016-9502; Directorate Identifier 2016-NM-128-AD.

(a) Effective Date

    This AD is effective July 25, 2017.

(b) Affected ADs

    None.

(c) Applicability

    (1) This AD applies to The Boeing Company Model 757-200 and -
200PF series airplanes, certificated in any category, as identified 
in Boeing Alert Service Bulletin 757-53A0103, dated June 22, 2016.
    (2) Installation of Supplemental Type Certificate (STC) 
ST01518SE (<a href="http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgSTC.nsf/0/38B606833BBD98B386257FAA00602538?OpenDocument&Highlight=st01518se">http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgSTC.nsf/0/38B606833BBD98B386257FAA00602538?OpenDocument&Highlight=st01518se</a>) 
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 an evaluation by the design approval 
holder (DAH) indicating that the frame webs between stringers S-20 
and S-25 on the left side and right side, from station (STA) 440 to 
STA 820 and from STA 1300 to STA 1701, are subject to widespread 
fatigue damage (WFD). We are issuing this AD to prevent fatigue 
cracking that could result in reduced structural integrity of the 
airplane.

(f) Compliance

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

(g) Repetitive High Frequency Eddy Current (HFEC) Inspections of the 
Frame Webs

    Before the accumulation of 28,000 total flight cycles, or within 
3,000 flight cycles after the effective date of this AD, whichever 
occurs later, do an HFEC inspection of the frame webs for any crack 
in any open coordinating holes, tooling holes, and insulation 
blanket attachment holes, in accordance with the Accomplishment 
Instructions of Boeing Alert Service Bulletin 757-53A0103, dated 
June 22, 2016. If any cracking is found, repair before further 
flight

[[Page 27972]]

using a method approved in accordance with the procedures specified 
in paragraph (i) of this AD. Repeat the inspection at intervals not 
to exceed 12,000 flight cycles.

(h) Modification of the Frame Webs

    Before the accumulation of 59,000 total flight cycles, modify 
the frame webs at all open hole locations, in accordance with the 
Accomplishment Instructions of Boeing Alert Service Bulletin 757-
53A0103, dated June 22, 2016. Accomplishment of this modification 
terminates the repetitive inspection requirements of paragraph (g) 
of this AD at the modified locations only.

(i) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Los Angeles Aircraft Certification Office 
(ACO), 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 (j) of this AD. 
Information may be emailed to <a href="/cdn-cgi/l/email-protection#86bfabc7c8cbabcac7c7c5c9abc7cbc9c5abd4e3f7f3e3f5f2f5c6e0e7e7a8e1e9f0"><span class="__cf_email__" data-cfemail="a39a8ee2edee8eefe2e2e0ec8ee2eeece08ef1c6d2d6c6d0d7d0e3c5c2c28dc4ccd5">[email&#160;protected]</span></a>.
    (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.
    (4) Except as required by paragraph (g) of this AD: For service 
information that contains steps that are labeled as Required for 
Compliance (RC), the provisions of paragraphs (i)(4)(i) and 
(i)(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.

(j) Related Information

    For more information about this AD, contact Muoi Vuong, 
Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles ACO, 
3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-
5205; fax: 562-627-5210; email: <a href="/cdn-cgi/l/email-protection#8be6fee4e2a5fdfee4e5eccbedeaeaa5ece4fd"><span class="__cf_email__" data-cfemail="3558405a5c1b43405a5b52755354541b525a43">[email&#160;protected]</span></a>.

(k) 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 757-53A0103, dated June 22, 
2016.
    (ii) Reserved.
    (3) For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Contractual & Data Services 
(C&DS), 2600 Westminster Blvd., MC 110 SK57, Seal Beach, CA 90740-
5600; telephone 562-797-1717; Internet <a href="https://www.myboeingfleet.com">https://www.myboeingfleet.com</a>.
    (4) You may view this service information at the FAA, Transport 
Airplane Directorate, 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: <a href="http://www.archives.gov/federal-register/cfr/ibr-locations.html">http://www.archives.gov/federal-register/cfr/ibr-locations.html</a>.

    Issued in Renton, Washington, on June 7, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2017-12397 Filed 6-19-17; 8:45 am]
 BILLING CODE 4910-13-P