Document ID: FAA-2016-9566-0007
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: The Boeing Company Airplanes
Posted Date: 2017-06-20T04:00Z

[Federal Register Volume 82, Number 117 (Tuesday, June 20, 2017)]
[Rules and Regulations]
[Pages 27972-27975]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-12176]

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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-9566; Directorate Identifier 2016-NM-191-AD; 
Amendment 39-18927; AD 2017-12-12]
RIN 2120-AA64

Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for all The 
Boeing Company Model 757-200, -200PF, and -200CB series airplanes. This 
AD was prompted by an evaluation by the design approval holder (DAH) 
indicating that certain fuselage circumferential splice plates are 
subject to widespread fatigue damage (WFD). This AD requires repetitive 
low frequency eddy current (LFEC) inspections for cracks of certain 
circumferential splice plates, and repairs if necessary. 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: https://www.myboeingfleet.com. You may view this referenced 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 http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
9566.

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-2016-
9566; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this AD, the regulatory evaluation, any comments received, and 
other information. The 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: Eric Schrieber, Aerospace Engineer, 
Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification 
Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 
562-627-5348; fax: 562-627-5210; email: eric.schrieber@faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to all The Boeing Company 
Model 757-200, -200PF, and -200CB series airplanes. The NPRM published 
in the Federal Register on January 5, 2017 (82

[[Page 27973]]

FR 1262). The NPRM was prompted by a report indicating that the 
fuselage circumferential splice plates along the center fastener rows, 
forward and aft of station 900 and station 1180 splice centerlines, are 
susceptible to WFD. The NPRM proposed to require repetitive LFEC 
inspections for cracks of certain circumferential splice plates, and 
repairs if necessary. We are issuing this AD to detect and correct any 
such cracks, which could lead to the failure of a principal structural 
element and could adversely affect the structural integrity of the 
airplane.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the NPRM and 
the FAA's response to each comment.

Support for the NPRM

    Boeing and United Airlines stated that they support the NPRM.

Effect of Winglets on Accomplishment of the Proposed Actions

    Aviation Partners Boeing (APB) stated that the installation of 
winglets per Supplemental Type Certificate (STC) ST01518SE does not 
affect the accomplishment of the manufacturer's service instructions.
    We concur with the commenter's statement. 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 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.

Effects of Modification From Passenger to Freighter Configuration on 
the Proposed Actions

    FedEx Express (FedEx) stated that VT Aerospace, which holds STC 
ST03562AT for modification of an airplane from a passenger to a 
freighter configuration, confirmed that STC ST03562AT does not affect 
the accomplishment of the manufacturer's service instructions. FedEx 
otherwise had no objection to the NPRM.
    We agree with the commenter's statement that STC ST03562AT does not 
affect the accomplishment of the manufacturer's service instructions. 
Therefore, the installation of STC ST03562AT does not affect the 
ability to accomplish the actions required by this AD. Because this STC 
is installed on a limited number of airplanes, we have determined that 
it is not necessary to revise this AD to include a provision that 
explicitly states the effect of this STC on compliance.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
this AD with the change 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 AD.

Related Service Information Under 1 CFR Part 51

    We reviewed Boeing Alert Service Bulletin 757-53A0105, dated June 
10, 2016. The service information describes procedures for repetitive 
LFEC inspections and repairs of the circumferential splice plates at 
station 900 and station 1180, from stringer S-6L to stringer S-6R, for 
any cracks. 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 634 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
----------------------------------------------------------------------------------------------------------------
LFEC inspection..................  6 work-hours x $85             $0  $510 per inspection   $323,340 per
                                    per hour = $510 per                cycle.                inspection cycle.
                                    inspection cycle.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this AD.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue 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.

[[Page 27974]]

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):

2017-12-12 The Boeing Company: Amendment 39-18927; Docket No. FAA-
2016-9566; Directorate Identifier 2016-NM-191-AD.

(a) Effective Date

    This AD is effective July 25, 2017.

(b) Affected ADs

    This AD affects AD 2006-11-11, Amendment 39-14615 (71 FR 30278, 
May 26, 2006) (``AD 2006-11-11'').

(c) Applicability

    (1) This AD applies to all The Boeing Company Model 757-200, -
200PF, and -200CB series airplanes, certificated in any category.
    (2) Installation of Supplemental Type Certificate (STC) 
ST01518SE (http://rgl.faa.gov/Regulatory_and_Guidance_Library/
rgstc.nsf/0/48e13cdfbbc32cf4862576a4005d308b/$FILE/ST01518SE.pdf) 
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 fuselage circumferential splice 
plates along the center fastener rows, forward and aft of station 
900 and station 1180 splice centerlines, are subject to widespread 
fatigue damage (WFD). We are issuing this AD to detect and correct 
cracks of certain circumferential splice plates, which could lead to 
the failure of a principal structural element and could adversely 
affect the structural integrity of the airplane.

(f) Compliance

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

(g) Repetitive Low Frequency Eddy Current (LFEC) Inspections and 
Corrective Actions

    At the applicable time specified in paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 757-53A0105, dated 
June 10, 2016, except as required by paragraph (h)(1) of this AD: Do 
an LFEC inspection for cracking of the circumferential splice plates 
at station 900 and station 1180, from stringer S-6L to stringer S-
6R, and do all applicable corrective actions, in accordance with the 
Accomplishment Instructions of Boeing Alert Service Bulletin 757-
53A0105, dated June 10, 2016, except as required by paragraph (h)(2) 
of this AD. Do all applicable corrective actions before further 
flight. Repeat the inspections thereafter at the applicable times 
specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service 
Bulletin 757-53A0105, dated June 10, 2016. Accomplishing these 
inspections terminates the requirements of paragraph (h) of AD 2006-
11-11 for the inspections of structurally significant item (SSI) 53-
40-05, circumferential skin splice body station BS900 stringer S-6L 
to stringer S-6R and circumferential skin splice body station BS1180 
stringer S-6L to stringer S-6R, as specified in Section 9 of Boeing 
Maintenance Planning Data (MPD) Document D622N001-9, May 2003 or 
June 2005 revisions. All other requirements of AD 2006-11-11 remain 
fully applicable and must be complied with.

(h) Service Information Exceptions

    (1) Where Boeing Alert Service Bulletin 757-53A0105, dated June 
10, 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 757-53A0105, dated June 
10, 2016, specifies to contact Boeing for repair instructions, and 
specifies that action as Required for Compliance (RC), this AD 
requires repair using a method approved in accordance with the 
procedures specified in paragraph (i) of this AD.

(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: 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.
    (4) Except as required by paragraph (h)(2) of this AD: For 
service information that contains steps that are labeled as 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 Eric Schrieber, 
Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles ACO, 
3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-
5348; fax: 562-627-5210; email: eric.schrieber@faa.gov.

(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 757-53A0105, dated June 10, 
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: https://www.myboeingfleet.com.
    (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: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

[[Page 27975]]

    Issued in Renton, Washington, on June 6, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2017-12176 Filed 6-19-17; 8:45 am]
BILLING CODE 4910-13-P