BOEING737

ID: US-2017-23-02
Issue date: 2017-11-29
Effective date: 2017-12-20
Source: FAA
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 AD_US-2017-23-02_1

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Fuselage - Fuselage Crown Skin Panels - Repetitive Inspections / Replacement

[Federal Register Volume 82, Number 219 (Wednesday, November 15, 2017)]
[Rules and Regulations]
[Pages 52835-52838]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-24164]

––––––––––––––––––––––––––––––––––

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0715; Product Identifier 2017-NM-073-AD; Amendment 39-19096; AD
2017-23-02]

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 737-200, -200C, -300, -400, and -500 series airplanes. This AD was prompted by an
evaluation by the design approval holder (DAH) indicating that the fuselage crown skin panels are
subject to widespread fatigue damage (WFD). This AD requires repetitive inspections, replacement,
and applicable on-condition actions for certain fuselage crown skin panels. We are issuing this AD to
address the unsafe condition on these products.

Dates:
This AD is effective December 20, 2017.
The Director of the Federal Register approved the incorporation by reference of a certain
publication listed in this AD as of December 20, 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 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-2017-0715.

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-2017-0715; 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

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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: Jennifer Tsakoumakis, Aerospace Engineer,
Airframe Section, FAA, Los Angeles ACO Branch, 3960 Paramount Boulevard, Lakewood, CA
90712-4137; phone: 562-627-5264; fax: 562-627-5210; email: Jennifer.Tsakoumakis@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 737-200, -200C, -300, -400, and -500 series
airplanes. The NPRM published in the Federal Register on August 10, 2017 (82 FR 37366). The
NPRM was prompted by an evaluation by the DAH indicating that the fuselage crown skin panels are
subject to WFD. The NPRM proposed to require repetitive inspections, replacement, and applicable
on-condition actions for certain fuselage crown skin panels.
We are issuing this AD to detect and correct cracking in the fuselage crown skin panels. Multiple
adjacent cracks in the fuselage crown skin could link up and lead to decompression or loss of
structural integrity of the airplane.

Comments

We gave the public the opportunity to participate in developing this final rule. We have
considered the comments received.

Support for the NPRM

Boeing concurred with the NPRM.

Effect of Winglets on Accomplishment of the Proposed Actions

Aviation Partners Boeing stated that accomplishing Supplemental Type Certificate (STC)
ST01219SE does not affect the ability to accomplish the actions specified in the NPRM.
We concur with the commenter. We have redesignated paragraph (c) of the proposed AD as
paragraph (c)(1) and added paragraph (c)(2) to this AD to state that installation of STC ST01219SE
does not affect the ability to accomplish the actions required by this AD. Therefore, for airplanes on
which STC ST01219SE 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.

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.


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Related Service Information Under 1 CFR Part 51

We reviewed Boeing Alert Service Bulletin 737-53A1358, dated April 27, 2017. This service
information describes procedures for repetitive inspections, replacement, and applicable on-condition
actions for certain fuselage crown skin panels. 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 200 airplanes of U.S. registry. We estimate the following costs
to comply with this AD:

Estimated Costs
Action Labor cost Parts Cost per product Cost on U.S.
cost operators
Inspection Up to 507 work-hours × $85 $0 Up to $43,095 per Up to $8,619,000 per
per hour = $43,095 per inspection cycle inspection cycle.
inspection cycle
Replacement 304 work-hours × $85 per hour 95,000 $120,840 per skin Up to $24,168,000.
= $25,840 per skin panel panel

We have received no definitive data that will 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,

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(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

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):




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


2017-23-02 The Boeing Company: Amendment 39-19096; Docket No. FAA-2017-0715; Product
Identifier 2017-NM-073-AD.

(a) Effective Date

This AD is effective December 20, 2017.

(b) Affected ADs

None.

(c) Applicability

(1) This AD applies to The Boeing Company Model 737-200, -200C, -300, -400, and -500 series
airplanes, certificated in any category, as identified in Boeing Alert Service Bulletin 737-53A1358,
dated April 27, 2017.
(2) Installation of Supplemental Type Certificate (STC) ST01219SE
(http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/EBD1CEC7B301293E86257CB30
045557A?OpenDocument&Highlight=st01219se) does not affect the ability to accomplish the
actions required by this AD. Therefore, for airplanes on which STC ST01219SE 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 indicating that the
fuselage crown skin panels are subject to widespread fatigue damage. We are issuing this AD to
detect and correct cracking in the fuselage crown skin panels. Multiple adjacent cracks in the fuselage
crown skin could link up and lead to decompression or loss of structural integrity of the airplane.

(f) Compliance

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

(g) Required Actions

Except as required by paragraph (h) of this AD: At the applicable times specified in paragraph
1.E., “Compliance,” of Boeing Alert Service Bulletin 737-53A1358, dated April 27, 2017, do all
applicable actions identified as “RC” (required for compliance) in, and in accordance with, the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1358, dated April 27, 2017.

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(h) Exceptions to Service Information Specifications

(1) For purposes of determining compliance with the requirements of this AD, the phrase “the
effective date of this AD” may be substituted for “the original issue date of this service bulletin,” as
specified in Boeing Alert Service Bulletin 737-53A1358, dated April 27, 2017.
(2) Where Boeing Alert Service Bulletin 737-53A1358, dated April 27, 2017, specifies
contacting Boeing, and specifies that action as RC: This AD requires using a method approved in
accordance with the procedures specified in paragraph (j) of this AD.
(3) Part 7 of Boeing Alert Service Bulletin 737-53A1358, dated April 27, 2017, specifies post-
modification airworthiness limitation inspections in compliance with 14 CFR 25.571(a)(3) at the
modified locations to support compliance with 14 CFR 121.1109(c)(2) or 129.109(b)(2). Although
Part 7 is identified as RC, this AD does not require accomplishment of Part 7. As airworthiness
limitations, these inspections are required by maintenance and operational rules. It is therefore
unnecessary to mandate them in this AD. Deviations from these inspections require FAA approval,
but do not require approval of an alternative method of compliance.

(i) Terminating Action for Repetitive Inspections

(1) Replacement of a skin panel, in accordance with Part 8 of the Accomplishment Instructions
of Boeing Alert Service Bulletin 737-53A1358, dated April 27, 2017, except as required by
paragraph (h)(2) of this AD, terminates the actions specified in Parts 1, 4, and 6 of the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1358, dated April 27, 2017,
as required by paragraph (g) of this AD, for that replaced skin panel only. To be acceptable as
terminating action, the replacement may not be done prior to the applicable time specified in Table 4
of paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 737-53A1358, dated April 27,
2017.
(2) Completion of a structural repair manual repair to repair cracking, in accordance with Part 2
of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1358, dated April 27,
2017, except as required by paragraph (h)(2) of this AD, terminates the repetitive inspections
specified in Part 1 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-
53A1358, dated April 27, 2017, as required by paragraph (g) of this AD, for that repair location only.
(3) Completion of a “Category C repair” to repair cracking, in accordance with Part 3 of the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1358, dated April 27, 2017,
except as required by paragraph (h)(2) of this AD, terminates the repetitive inspections specified in
Part 1 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1358, dated
April 27, 2017, as required by paragraph (g) of this AD, for that repair location only.
(4) Completion of a “Change Category C Repair to SB Repair,” in accordance with Part 6 of the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1358, dated April 27, 2017,
except as required by paragraph (h)(2) of this AD, terminates the inspections specified in Part 4 of the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1358, dated April 27, 2017,
as required by paragraph (g) of this AD, for that repair location only.

(j) Alternative Methods of Compliance (AMOCs)

(1) The Manager, Los Angeles ACO Branch, FAA, has the authority to approve AMOCs for this
AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19,
send your request to your principal inspector or local Flight Standards District Office, as appropriate.
If sending information directly to the manager of the certification office, send it to the attention of the
person identified in paragraph (k) of this AD. Information may be emailed to: 9-ANM-LAACO-
AMOC-Requests@faa.gov.


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(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, 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 paragraphs (h)(2) and (h)(3) 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 Jennifer Tsakoumakis, Aerospace Engineer,
Airframe Section, FAA, Los Angeles ACO Branch, 3960 Paramount Boulevard, Lakewood, CA
90712-4137; phone: 562-627-5264; fax: 562-627-5210; email: Jennifer.Tsakoumakis@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 737-53A1358, dated April 27, 2017.
(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 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 October 27, 2017.
Jeffrey E. Duven,
Director, System Oversight Division,
Aircraft Certification Service.




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This is a partial extract of the full document - please refer to the actual report for full information.
Sources as credited.