[Federal Register Volume 82, Number 27 (Friday, February 10, 2017)]
[Rules and Regulations]
[Pages 10258-10262]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-01824]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2016-6670; Directorate Identifier 2016-NM-006-AD;
Amendment 39-18789; AD 2017-02-10]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
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SUMMARY: We are superseding Airworthiness Directive (AD) 2013-19-04 for
certain The Boeing Company Model 737-600, -700, -700C, -800, and -900
series airplanes. AD 2013-19-04 required repetitive inspections for
cracking of the skin around the fasteners common to the ends of certain
bulkhead chords, and related investigative actions and corrective
actions if necessary; and
[[Page 10259]]
provided an optional terminating modification. This new AD reduces the
inspection threshold and repetitive inspection intervals. This AD was
prompted by a report of cracks found in the skin at fasteners of
certain bulkhead chords. We are issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective March 17, 2017.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of March 17,
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-
6670.
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-
6670; 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: Alan Pohl, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6450; fax:
425-917-6590; email: [email protected].
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2013-19-04, Amendment 39-17586 (78 FR 59801,
September 30, 2013) (``AD 2013-19-04''). AD 2013-19-04 applied to
certain The Boeing Company Model 737-600, -700, -700C, -800, and -900
series airplanes. The NPRM published in the Federal Register on May 12,
2016 (81 FR 29505) (``the NPRM''). The NPRM was prompted by a report of
cracks found in the skin at body station (STA) 540 just below stringer
S-22L. The NPRM proposed to continue to require repetitive detailed and
high frequency eddy current inspections for cracking of the skin around
the eight fasteners common to the ends of the STA 540 bulkhead chords
between stringers S-22 and S-23, left and right sides; related
investigative actions and corrective actions, if necessary; and to
provide an optional terminating modification. The NPRM also proposed to
reduce the inspection threshold and repetitive inspection intervals. We
are issuing this AD to detect and correct fatigue cracking in the
fuselage skin around the eight fasteners securing the STA 540 bulkhead
chords, which could result in rapid decompression of the cabin.
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 had no objections to the NPRM.
Effect of Winglets on Accomplishment of the Proposed Actions
Aviation Partners Boeing stated that installation of winglets, as
provided in Supplemental Type Certificate (STC) ST00830SE, does not
affect the ability to accomplish the actions proposed in the NPRM.
We concur with the commenter. We have redesignated paragraph (c) of
the proposed AD as (c)(1) and added paragraph (c)(2) to this AD to
state that installation of STC ST00830SE does not affect the ability to
accomplish the actions required by this AD. Therefore, for airplanes on
which STC ST00830SE 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 To Clarify Access and Restoration Requirements
All Nippon Airways requested that we clarify if the access and
restoration instructions specified in the service information
referenced in paragraph (k) of the proposed AD are required actions.
We agree to clarify this issue. Access and restoration actions are
not part of the actions required to correct the unsafe condition
identified in this AD. Therefore, access and restoration actions were
excluded from the required actions in AD 2013-19-04 and are excluded
from the required actions in this AD. We have added the service
information referenced in paragraph (k) of this AD to paragraph (i)(4)
of this AD. Paragraph (i)(4) of this AD specifies that the access and
restoration actions specified in the referenced service information are
not required by this AD.
Request To Clarify Corrective Action
Southwest Airlines (SWA) requested that we clarify the corrective
action for drilling the new drag link assembly. SWA stated that the
service information only provides instructions for parts constructed of
aluminum and that the drag link assembly is made from titanium.
We agree that clarification is necessary. Boeing has informed us
that revised service information is forthcoming. However, since the
revised service information is not yet available, we do not consider
that delaying this action until after the release of the manufacturer's
revised service bulletin is warranted. When this service information
becomes available, and upon satisfactory review, we plan to approve it
as a global alternative method of compliance (AMOC) to the appropriate
requirements of this AD. The issue raised by SWA affects only the on-
condition repair instructions and not the required inspection to detect
the identified unsafe condition. We have added paragraph (i)(5) to this
AD to specify that repairs provided in Part 4 or Part 5 of the
Accomplishment Instructions of Boeing Special Attention Service
Bulletin 737-53-1294, Revision 2, dated December 9, 2015 (``SASB 737-
53-1294 R2''), must be done before further flight, using a method
approved in accordance with the procedures specified in paragraph (l)
of this AD. We have revised paragraphs (g) and (h) of this AD
accordingly.
Clarification of Exception to Repetitive Intervals
For clarity, we have changed the format of paragraph (g) of this AD
to make it clear the exceptions apply to the entire paragraph,
including the repetitive inspection sentence specified in paragraph (g)
of this AD.
Clarification of Terminating Actions
We have clarified paragraph (h) of this AD to specify that
accomplishing the skin repair or preventive modification,
[[Page 10260]]
as specified in the applicable part of the Accomplishment Instructions
of Boeing SASB 737-53-1294 R2, is terminating action for the side on
which the skin repair or preventive modification is done.
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 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 AD.
Related Service Information Under 1 CFR Part 51
We reviewed SASB 737-53-1294 R2. The service information describes
procedures for inspecting the skin around the eight fasteners common to
the ends of the STA 540 bulkhead chords between stringers S-22 and S-
23, left and right sides, for cracking, repairing cracks, and
installing a chord splice as a preventive modification. 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 903 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
Estimated Costs
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Cost on U.S.
Action Labor cost Parts cost Cost per product operators
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Inspection (left and right 12 work-hours x $85 per $0 $1,020 per $921,060 per
sides). hour = $1,020 per inspection cycle. inspection cycle.
inspection cycle.
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We estimate the following costs to do any necessary repairs and
inspections that will be required based on the results of the
inspection. We have no way of determining the number of aircraft that
might need these repairs:
On-Condition Costs
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Action Labor cost Parts cost Cost per product
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Preventive modification (each 7 work-hours x $85 per $894................ $1,489.
side). hour = $595.
Skin repair (each side).......... 39 work-hours x $85 per Up to $5,635........ Up to $8,950.
hour = $3,315.
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According to the manufacturer, some of the costs of this AD may be
covered under warranty, thereby reducing the cost impact on affected
individuals. We do not control warranty coverage for affected
individuals. As a result, we have included all costs in our cost
estimate.
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
We have determined that 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 removing Airworthiness Directive (AD)
2013-19-04, Amendment 39-17586 (78 FR 59801, September 30, 2013), and
adding the following new AD:
2017-02-10 The Boeing Company: Amendment 39-18789; Docket No. FAA-
2016-6670; Directorate Identifier 2016-NM-006-AD.
(a) Effective Date
This AD is effective March 17, 2017.
(b) Affected ADs
This AD replaces AD 2013-19-04, Amendment 39-17586 (78 FR 59801,
September 30, 2013) (``AD 2013-19-04'').
[[Page 10261]]
(c) Applicability
(1) This AD applies to The Boeing Company Model 737-600, -700, -
700C, -800, and -900 series airplanes, certificated in any category,
as identified in Boeing Special Attention Service Bulletin 737-53-
1294, Revision 2, dated December 9, 2015 (``SASB 737-53-1294 R2'').
(2) Installation of Supplemental Type Certificate (STC)
ST00830SE [http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/184DE9A71EC3FA5586257EAE00707DA6?OpenDocument&Highlight=st00830se]
does not affect the ability to accomplish the actions required by
this AD. Therefore, for airplanes on which STC ST00830SE 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 a report of cracks found in the skin at
body station (STA) 540 just below the left side of stringer S-22. We
are issuing this AD to detect and correct fatigue cracking in the
fuselage skin around the eight fasteners securing the STA 540
bulkhead chords, which could result in rapid decompression of the
cabin.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Inspection and Corrective Action
Except as required by paragraphs (i)(1) and (i)(2) of this AD:
At the applicable time specified in table 1 of paragraph 1.E.,
``Compliance,'' of SASB 737-53-1294 R2, do detailed and high
frequency eddy current (HFEC) inspections for cracking of the skin
in the area around the eight fasteners securing the STA 540 bulkhead
chords between stringers S-22 and S-23; and do all applicable
related investigative and corrective actions; in accordance with
Parts 1, 2, 3, 4, and 5 of the Accomplishment Instructions of SASB
737-53-1294 R2, except as required by paragraphs (i)(3), (i)(4), and
(i)(5) of this AD. Do all applicable related investigative and
corrective actions before further flight. Except as required by
paragraph (i)(2) of this AD, repeat the detailed and HFEC
inspections thereafter at the intervals specified in table 1 of
paragraph 1.E., ``Compliance,'' of SASB 737-53-1294 R2, until the
optional preventive modification specified in paragraph (h) of this
AD is done.
(h) Skin Repair or Optional Preventive Modification
Accomplishing the skin repair or preventive modification,
including an HFEC inspection for cracking of the skin and STA 540
bulkhead chords, and all applicable repairs, in accordance with
paragraph 3.B, Part 2 or Part 4 (left side), or Part 3 or Part 5
(right side), as applicable, of the Accomplishment Instructions of
SASB 737-53-1294 R2, except as required by paragraphs (i)(2) and
(i)(5) of this AD, terminates the inspection requirements of
paragraph (g) of this AD for the side on which the skin repair or
preventive modification is done.
(i) Exceptions to Service Bulletin Specifications
(1) Where paragraph 1.E., ``Compliance,'' of SASB 737-53-1294
R2, specifies a compliance time ``after the Revision 2 date of this
service bulletin,'' this AD requires compliance within the specified
compliance time after the effective date of this AD.
(2) For airplanes on which Boeing Business Jet Lower Cabin
Altitude Supplemental Type Certificate (STC) ST01697SE (http://
rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/
0812969a86af879b8625766400600105/$FILE/ST01697SE.pdf) (6,500 feet
maximum cabin altitude in lieu of 8,000 feet) has been incorporated,
the flight-cycle related compliance times for the inspection
required by paragraph (g) of this AD are different from those
specified in paragraph 1.E., ``Compliance,'' of SASB 737-53-1294 R2.
All initial compliance times specified in total flight cycles or
flight cycles must be reduced to half of those specified in SASB
737-53-1294 R2. All repetitive interval compliance times specified
in flight cycles must be reduced to one-quarter of those specified
in paragraph 1.E., ``Compliance,'' of SASB 737-53-1294 R2.
(3) If any cracking is found during any inspection required by
this AD, and SASB 737-53-1294 R2, specifies to contact Boeing for
appropriate action: Before further flight, repair using a method
approved in accordance with the procedures specified in paragraph
(l) of this AD.
(4) The access and restoration actions identified in the
Accomplishment Instructions of Boeing Special Attention Service
Bulletin 737-53-1294, dated March 31, 2011; Boeing Special Attention
Service Bulletin 737-53-1294, Revision 1, dated June 14, 2013; or
SASB 737-53-1294 R2; are not required by this AD. Operators may
perform those actions in accordance with accepted maintenance
procedures.
(5) For doing repairs specified in Part 4 or Part 5 of the
Accomplishment Instructions of SASB 737-53-1294 R2: Before further
flight, repair using a method approved in accordance with the
procedures specified in paragraph (l) of this AD.
(j) Supplemental Inspections Not Required by This AD
Table 2 of paragraph 1.E., ``Compliance,'' of SASB 737-53-1294
R2, specifies post-modification airworthiness limitation inspections
in compliance with 14 CFR 25.571(a)(3) at the modified locations,
which support compliance with 14 CFR 121.1109(c)(2) or
129.109(b)(2). 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 an AMOC.
(k) Credit for Previous Actions
This paragraph provides credit for the actions required by
paragraphs (g) and (h) of this AD, if those actions were performed
before the effective date of this AD using Boeing Special Attention
Service Bulletin 737-53-1294, dated March 31, 2011, which is not
incorporated by reference in this AD; or Boeing Special Attention
Service Bulletin 737-53-1294, Revision 1, dated June 14, 2013, which
was incorporated by reference in AD 2013-19-04.
(l) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Seattle 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 (m)(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, Seattle 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) AMOCs approved previously for the optional preventive
modification installed in accordance with paragraph (h) of AD 2013-
19-04, and AMOCs approved previously for repairs for AD 2013-19-04,
are approved as AMOCs for the corresponding provisions of this AD,
provided that such modification or repair included installation of
the splice plate as specified in Boeing Special Attention Service
Bulletin 737-53-1294, except as provided by paragraph (l)(5) of this
AD.
(5) The time-limited repair approved as specified in FAA Letter
120S-15-140, dated June 3, 2015, is approved as an AMOC to the
corresponding requirements of this AD.
(m) Related Information
(1) For more information about this AD, contact Alan Pohl,
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft
Certification Office, 1601 Lind Avenue SW., Renton, WA 98057-3356;
phone: 425-917-6450; fax: 425-917-6590; email: [email protected].
(2) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (n)(3) and (n)(4) of this AD.
(n) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference
[[Page 10262]]
(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 Special Attention Service Bulletin 737-53-1294,
Revision 2, dated December 9, 2015.
(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
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.
Issued in Renton, Washington, on January 18, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2017-01824 Filed 2-9-17; 8:45 am]
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