Airworthiness Directives; The Boeing Company Airplanes, 25891-25894 [2018-11427]
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Federal Register / Vol. 83, No. 108 / Tuesday, June 5, 2018 / Rules and Regulations
in paragraph 1.E., ‘‘Compliance,’’ of Aviation
Partners Boeing Service Bulletin AP767–57–
014, Revision 1, dated April 12, 2017, except
as required by paragraph (j)(2) of this AD, do
a post-repair HFEC inspection for cracking,
in accordance with Part 3 of the
Accomplishment Instructions of Aviation
Partners Boeing Service Bulletin AP767–57–
014, Revision 1, dated April 12, 2017, and
repeat the inspection thereafter at the
applicable times specified in paragraph 1.E.,
‘‘Compliance,’’ of Aviation Partners Boeing
Service Bulletin AP767–57–014, Revision 1,
dated April 12, 2017.
(iii) If any crack is found during any
inspection required by paragraph (h)(3)(ii) of
this AD, repair before further flight using a
method approved in accordance with the
procedures specified in paragraph (k) of this
AD.
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(i) Repair Approval
Repairs of the lower outboard wing skin
that were approved after June 15, 2017, and
before the effective date of this AD, by the
Boeing Commercial Airplanes Organization
Designation Authorization (ODA) that has
been authorized by the Manager, Seattle ACO
Branch, are approved for the applicable
repairs required by paragraphs (g) and (h) of
this AD. The ODA repairs will have postinstallation inspection requirements in lieu
of the post-inspection instructions specified
in Aviation Partners Boeing Service Bulletin
AP767–57–010, Revision 11, dated April 3,
2017; and Aviation Partners Boeing Service
Bulletin AP767–57–014, Revision 1, dated
April 12, 2017.
(j) Exceptions to Service Information
Specifications
(1) Where paragraph 1.E., ‘‘Compliance,’’ of
Aviation Partners Boeing Service Bulletin
AP767–57–010, Revision 11, dated April 3,
2017, specifies a compliance time ‘‘after the
issue date of Revision 11 of this service
bulletin,’’ this AD requires compliance
within the specified compliance time after
the effective date of this AD.
(2) Where paragraph 1.E., ‘‘Compliance,’’ of
Aviation Partners Boeing Service Bulletin
AP767–57–014, Revision 1, dated April 12,
2017, specifies a compliance time ‘‘after the
initial issue date of this service bulletin,’’ this
AD requires compliance within the specified
compliance time after the effective date of
this AD.
(3) For Condition 1 and Condition 2
airplanes: Where paragraph 1.E.,
‘‘Compliance,’’ of Aviation Partners Boeing
Service Bulletin AP767–57–014, Revision 1,
dated April 12, 2017, specifies a compliance
time for accomplishing the Part 3 HFEC
inspection of 18 months ‘‘after the initial
issue date of this service bulletin,’’ the
required compliance time is 6,000 flight
cycles or 18,000 flight hours, whichever
occurs first, after doing the Part 2 repair.
(4) For airplanes on which a stringer L–9.5
replacement was accomplished per Part 11 of
Aviation Partners Boeing Service Bulletin
AP767–57–010, Revision 11, dated April 3,
2017: Where Aviation Partners Boeing
Service Bulletin AP767–57–010, Revision 11,
dated April 3, 2017, specifies repeating the
post-repair HFEC inspection ‘‘in Part 9,’’ this
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AD requires repeating the post-repair HFEC
inspection in Part 13.
(k) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Seattle 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 (l) of this
AD. Information may be emailed to: 9-ANMSeattle-ACO-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 ODA that has been
authorized by the Manager, Seattle 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
(g)(1)(i)(B)(3), (g)(1)(i)(C)(3), (g)(1)(i)(D)(3),
(g)(1)(ii)(A)(3), (g)(1)(ii)(B)(3), (g)(1)(iii)(A)(3),
(g)(1)(iii)(B)(3), (g)(1)(iv), (g)(2), (h)(2)(iii),
and (h)(3)(iii) of this AD: For service
information that contains steps that are
labeled as Required for Compliance (RC), the
provisions of paragraphs (k)(4)(i) and
(k)(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.
(l) Related Information
For more information about this AD,
contact Allen Rauschendorfer, Aerospace
Engineer, Airframe Section, FAA, Seattle
ACO Branch, 2200 South 216th St., Des
Moines, WA; phone and fax: 206–231–3528;
email: allen.rauschendorfer@faa.gov.
(m) 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.
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25891
(i) Aviation Partners Boeing Service
Bulletin AP767–57–010, Revision 11, dated
April 3, 2017.
(ii) Aviation Partners Boeing Service
Bulletin AP767–57–014, Revision 1, dated
April 12, 2017.
(3) For service information identified in
this AD, contact Aviation Partners Boeing,
2811 S. 102nd Street, Suite 200, Seattle, WA
98168; telephone 206–762–1171; internet
https://www.aviationpartnersboeing.com.
(4) You may view this service information
at the FAA, Transport Standards Branch,
2200 South 216th St., Des Moines, WA. For
information on the availability of this
material at the FAA, call 206–231–3195.
(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: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Des Moines, Washington, on May
21, 2018.
James Cashdollar,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2018–11825 Filed 6–4–18; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–1099; Product
Identifier 2017–NM–093–AD; Amendment
39–19296; AD 2018–11–08]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
The Boeing Company Model 767–200
and –300 series airplanes. This AD was
prompted by a report of two cracks at
a certain frame inner chord. This AD
requires a detailed inspection for any
material review board (MRB) filler
installed in the area from the frame web
to the stub-beam fitting at certain
stations to determine if the filler extends
above the frame-to-stub-beam joint, and
applicable on-condition actions. We are
issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective July 10,
2018.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of July 10, 2018.
SUMMARY:
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Federal Register / Vol. 83, No. 108 / Tuesday, June 5, 2018 / Rules and Regulations
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, 2200
South 216th St., Des Moines, WA. For
information on the availability of this
material at the FAA, call 206–231–3195.
It is also available on the internet at
https://www.regulations.gov by searching
for and locating Docket No. FAA–2017–
1099.
ADDRESSES:
Examining the AD Docket
You may examine the AD docket on
the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2017–
1099; or in person at Docket Operations
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 Docket
Operations (phone: 800–647–5527) is
Docket Operations, 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:
Wayne Lockett, Aerospace Engineer,
Airframe Section, FAA, Seattle ACO
Branch, 2200 S. 216th St., Des Moines,
WA 98198; phone and fax: 206–231–
3524; email: wayne.lockett@faa.gov.
SUPPLEMENTARY INFORMATION:
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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 767–200 and –300 series
airplanes. The NPRM was published in
the Federal Register on December 6,
2017 (82 FR 57552). The NPRM was
prompted by a report of a crack on the
transition radius of the station (STA)
883.5 frame inner chord and an
additional crack indication at a fastener
hole in the frame inner chord common
to a material review board (MRB) filler
that extended above the frame-to-stubbeam joint. The NPRM proposed to
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require a detailed inspection for any
MRB filler installed in the area from the
frame web to the stub-beam fitting at
certain stations to determine if the filler
extends above the frame-to-stub-beam
joint, and applicable on-condition
actions.
We are issuing this AD to detect and
correct cracking of the frame inner
chord, which could result in the
inability of one or more overwing stub
frames between STA 808 and STA 933,
each a principal structural element, to
sustain limit loads; this condition could
adversely affect the structural integrity
of the airplane.
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. Boeing
concurred with the NPRM.
Effect of Winglets on Accomplishment
of the Proposed Actions
Aviation Partners Boeing stated that
accomplishing the Supplemental Type
Certificate (STC) ST01920SE does not
affect the actions specified in the
NPRM.
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
ST01920SE does not affect the ability to
accomplish the actions required by this
AD. Therefore, for airplanes on which
STC ST01920SE 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 Confirm Intent of
Compliance Time
Paragraph (h)(1) of the proposed AD
allowed operators to substitute ‘‘the
effective date of this AD’’ for ‘‘the
original issue date of Requirements
Bulletin 767–53A0278 RB.’’ United
Airlines noted that this wording is
different from that of recent NPRMs,
where the AD effective date is the sole
compliance date. United added that the
proposed wording suggested that the
operator can choose to use either the AD
effective date or the original issue date
of the RB when determining the
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compliance timeline. United requested
that we clarify the intent of the
provision of paragraph (h)(1) of the
proposed AD.
We agree with the commenter. We
have revised paragraph (h)(1) of this AD
to specify use of the effective date of
this AD in determining the compliance
time.
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
addressing 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
Requirements Bulletin 767–53A0278
RB, dated June 30, 2017. This service
information describes procedures for a
detailed inspection for any MRB filler
installed in the area from the frame web
to the stub-beam fitting on the left and
right side at STA 859.5, 883.5, and 903.5
to determine if the filler extends above
the frame-to-stub-beam joint, and
applicable on-condition actions. The
applicable on-condition actions include
repetitive surface high frequency eddy
current inspections and repair for
cracking in the frame inner chord
around the end fastener common to
each affected MRB filler. 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 51
airplanes of U.S. registry. We estimate
the following costs to comply with this
AD:
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Federal Register / Vol. 83, No. 108 / Tuesday, June 5, 2018 / Rules and Regulations
ESTIMATED COSTS FOR REQUIRED ACTIONS
Action
Labor cost
Parts cost
Cost per
product
Cost on U.S.
operators
Detailed Inspection ..........................................................................................
20 work-hours
× $85 per hour
= $1,700
$0
$1,700
$86,700
We estimate the following costs to do
any necessary on-condition actions that
would be required. We have no way of
determining the number of aircraft that
might need these on-condition actions:
ESTIMATED COSTS OF ON-CONDITION INSPECTIONS
Labor cost
Parts cost
Cost per product
3 work-hours × $85 per hour = $255 per inspection cycle ..................................................................
$0
$255 per inspection cycle.
We have received no definitive data
that would enable us to provide cost
estimates for the on-condition repairs
specified in this AD.
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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 and associated appliances 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
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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.
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.
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
2018–11–08 The Boeing Company:
Amendment 39–19296; Docket No.
FAA–2017–1099; Product Identifier
2017–NM–093–AD.
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This AD is effective July 10, 2018.
(b) Affected ADs
None.
(c) Applicability
(1) This AD applies to The Boeing
Company Model 767–200 and –300 series
airplanes, as identified in Boeing Alert
Requirements Bulletin 767–53A0278 RB,
dated June 30, 2017, certificated in any
category.
(2) Installation of Supplemental Type
Certificate (STC) ST01920SE (https://
rgl.faa.gov/Regulatory_and_Guidance_
Library/rgstc.nsf/0/59027F43B9A7486E86257
B1D006591EE?OpenDocument&Highlight=
st01920se) does not affect the ability to
accomplish the actions required by this AD.
Therefore, for airplanes on which STC
ST01920SE 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.
Adoption of the Amendment
§ 39.13
(a) Effective Date
(e) Unsafe Condition
This AD was prompted by a report of a
crack on the transition radius of the station
(STA) 883.5 frame inner chord and an
additional crack indication at a fastener hole
in the frame inner chord common to a
material review board (MRB) filler that
extended above the frame-to-stub-beam joint.
We are issuing this AD to detect and correct
cracking of the frame inner chord, which
could result in the inability of one or more
overwing stub frames between STA 808 and
STA 933, each a principal structural element,
to sustain limit loads; this condition could
adversely affect the structural integrity of the
airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
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Federal Register / Vol. 83, No. 108 / Tuesday, June 5, 2018 / Rules and Regulations
(g) Required Actions
Except as required by paragraph (h) of this
AD: At the applicable times specified in the
‘‘Compliance’’ paragraph of Boeing Alert
Requirements Bulletin 767–53A0278 RB,
dated June 30, 2017, do all applicable actions
identified in, and in accordance with, the
Accomplishment Instructions of Boeing Alert
Requirements Bulletin 767–53A0278 RB,
dated June 30, 2017.
Note 1 to paragraph (g) of this AD:
Guidance for accomplishing the actions
required by this AD can be found in Boeing
Alert Service Bulletin 767–53A0278, dated
June 30, 2017, which is referred to in Boeing
Alert Requirements Bulletin 767–53A0278
RB, dated June 30, 2017.
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(h) Exceptions to Service Information
Specifications
(1) For purposes of determining
compliance with the requirements of this AD:
Where Boeing Alert Requirements Bulletin
767–53A0278 RB, dated June 30, 2017, uses
the phrase ‘‘the original issue date of
Requirements Bulletin 767–53A0278 RB,’’
this AD requires using ‘‘the effective date of
this AD.’’
(2) Where Boeing Alert Requirements
Bulletin 767–53A0278 RB, dated June 30,
2017, specifies contacting Boeing, this AD
requires repair using a method approved in
accordance with the procedures specified in
paragraph (i) of this AD.
(3) For airplanes identified as Group 1,
Configuration 1, in Boeing Alert
Requirements Bulletin 767–53A0278 RB,
dated June 30, 2017, that have been modified
to a freighter configuration: The actions
specified in Boeing Alert Requirements
Bulletin 767–53A0278 RB, dated June 30,
2017, for Group 1, Configuration 2, must be
done instead of the actions for Group 1,
Configuration 1, except as required by
paragraph (h)(2) of this AD.
(4) For airplanes identified as Group 2,
Configuration 1, in Boeing Alert
Requirements Bulletin 767–53A0278 RB,
dated June 30, 2017, that have been modified
to a freighter configuration: The actions
specified in Boeing Alert Requirements
Bulletin 767–53A0278 RB, dated June 30,
2017, for Group 2, Configuration 2, must be
done instead of the actions for Group 2,
Configuration 1, except as required by
paragraph (h)(2) of this AD.
(i) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Seattle 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 (j) of this
AD. Information may be emailed to: 9-ANMSeattle-ACO-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.
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(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
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.
(j) Related Information
For more information about this AD,
contact Wayne Lockett, Aerospace Engineer,
Airframe Section, FAA, Seattle ACO Branch,
2200 S. 216th St., Des Moines, WA 98198;
phone and fax: 206–231–3524; email:
wayne.lockett@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 Requirements Bulletin
767–53A0278 RB, dated June 30, 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,
2200 South 216th St., Des Moines, WA. For
information on the availability of this
material at the FAA, call 206–231–3195.
(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: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Des Moines, Washington, on May
18, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2018–11427 Filed 6–4–18; 8:45 am]
BILLING CODE 4910–13–P
PO 00000
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–0779; Product
Identifier 2017–NM–040–AD; Amendment
39–19301; AD 2018–11–13]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
The Boeing Company Model 787–8
airplanes. This AD was prompted by a
report of possible degraded bond-line
performance of co-bonded upper wing
stringer-to-skin joints. This AD requires
repetitive inspections of certain upper
wing stringers for any disbond and
corrective actions, if necessary; and a
terminating preventive modification of
installing disbond arrestment (DBA)
fasteners. This AD also requires revising
the inspection or maintenance program
to incorporate an airworthiness
limitation. We are issuing this AD to
address the unsafe condition on these
products.
SUMMARY:
This AD is effective July 10,
2018.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of July 10, 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, 2200
South 216th St., Des Moines, WA. For
information on the availability of this
material at the FAA, call 206–231–3195.
It is also available on the internet at
https://www.regulations.gov by searching
for and locating Docket No. FAA–2017–
0779.
DATES:
Examining the AD Docket
You may examine the AD docket on
the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2017–
0779; or in person at Docket Operations
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The AD docket contains this final rule,
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[Federal Register Volume 83, Number 108 (Tuesday, June 5, 2018)]
[Rules and Regulations]
[Pages 25891-25894]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-11427]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2017-1099; Product Identifier 2017-NM-093-AD; Amendment
39-19296; AD 2018-11-08]
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 adopting a new airworthiness directive (AD) for certain
The Boeing Company Model 767-200 and -300 series airplanes. This AD was
prompted by a report of two cracks at a certain frame inner chord. This
AD requires a detailed inspection for any material review board (MRB)
filler installed in the area from the frame web to the stub-beam
fitting at certain stations to determine if the filler extends above
the frame-to-stub-beam joint, and applicable on-condition actions. We
are issuing this AD to address the unsafe condition on these products.
DATES: This AD is effective July 10, 2018.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of July 10,
2018.
[[Page 25892]]
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, 2200 South 216th St., Des Moines, WA.
For information on the availability of this material at the FAA, call
206-231-3195. It is also available on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2017-
1099.
Examining the AD Docket
You may examine the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2017-
1099; or in person at Docket Operations 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 Docket Operations (phone: 800-647-
5527) is Docket Operations, 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: Wayne Lockett, Aerospace Engineer,
Airframe Section, FAA, Seattle ACO Branch, 2200 S. 216th St., Des
Moines, WA 98198; phone and fax: 206-231-3524; email:
[email protected].
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 767-200 and -300 series airplanes. The NPRM was published in the
Federal Register on December 6, 2017 (82 FR 57552). The NPRM was
prompted by a report of a crack on the transition radius of the station
(STA) 883.5 frame inner chord and an additional crack indication at a
fastener hole in the frame inner chord common to a material review
board (MRB) filler that extended above the frame-to-stub-beam joint.
The NPRM proposed to require a detailed inspection for any MRB filler
installed in the area from the frame web to the stub-beam fitting at
certain stations to determine if the filler extends above the frame-to-
stub-beam joint, and applicable on-condition actions.
We are issuing this AD to detect and correct cracking of the frame
inner chord, which could result in the inability of one or more
overwing stub frames between STA 808 and STA 933, each a principal
structural element, to sustain limit loads; this condition could
adversely affect the structural integrity of the airplane.
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. Boeing concurred with the
NPRM.
Effect of Winglets on Accomplishment of the Proposed Actions
Aviation Partners Boeing stated that accomplishing the Supplemental
Type Certificate (STC) ST01920SE does not affect the actions specified
in the NPRM.
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 ST01920SE does not
affect the ability to accomplish the actions required by this AD.
Therefore, for airplanes on which STC ST01920SE 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 Confirm Intent of Compliance Time
Paragraph (h)(1) of the proposed AD allowed operators to substitute
``the effective date of this AD'' for ``the original issue date of
Requirements Bulletin 767-53A0278 RB.'' United Airlines noted that this
wording is different from that of recent NPRMs, where the AD effective
date is the sole compliance date. United added that the proposed
wording suggested that the operator can choose to use either the AD
effective date or the original issue date of the RB when determining
the compliance timeline. United requested that we clarify the intent of
the provision of paragraph (h)(1) of the proposed AD.
We agree with the commenter. We have revised paragraph (h)(1) of
this AD to specify use of the effective date of this AD in determining
the compliance time.
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 addressing 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 Requirements Bulletin 767-53A0278 RB,
dated June 30, 2017. This service information describes procedures for
a detailed inspection for any MRB filler installed in the area from the
frame web to the stub-beam fitting on the left and right side at STA
859.5, 883.5, and 903.5 to determine if the filler extends above the
frame-to-stub-beam joint, and applicable on-condition actions. The
applicable on-condition actions include repetitive surface high
frequency eddy current inspections and repair for cracking in the frame
inner chord around the end fastener common to each affected MRB filler.
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 51 airplanes of U.S. registry. We
estimate the following costs to comply with this AD:
[[Page 25893]]
Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
Detailed Inspection......................... 20 work-hours x $0 $1,700 $86,700
$85 per hour =
$1,700
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary on-condition
actions that would be required. We have no way of determining the
number of aircraft that might need these on-condition actions:
Estimated Costs of On-Condition Inspections
----------------------------------------------------------------------------------------------------------------
Labor cost Parts cost Cost per product
----------------------------------------------------------------------------------------------------------------
3 work-hours x $85 per hour = $255 per $0 $255 per inspection cycle.
inspection cycle.
----------------------------------------------------------------------------------------------------------------
We have received no definitive data that would enable us to provide
cost estimates for the on-condition repairs 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 and
associated appliances 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.
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):
2018-11-08 The Boeing Company: Amendment 39-19296; Docket No. FAA-
2017-1099; Product Identifier 2017-NM-093-AD.
(a) Effective Date
This AD is effective July 10, 2018.
(b) Affected ADs
None.
(c) Applicability
(1) This AD applies to The Boeing Company Model 767-200 and -300
series airplanes, as identified in Boeing Alert Requirements
Bulletin 767-53A0278 RB, dated June 30, 2017, certificated in any
category.
(2) Installation of Supplemental Type Certificate (STC)
ST01920SE (https://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/59027F43B9A7486E86257B1D006591EE?OpenDocument&Highlight=st01920se)
does not affect the ability to accomplish the actions required by
this AD. Therefore, for airplanes on which STC ST01920SE 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 a crack on the transition
radius of the station (STA) 883.5 frame inner chord and an
additional crack indication at a fastener hole in the frame inner
chord common to a material review board (MRB) filler that extended
above the frame-to-stub-beam joint. We are issuing this AD to detect
and correct cracking of the frame inner chord, which could result in
the inability of one or more overwing stub frames between STA 808
and STA 933, each a principal structural element, to sustain limit
loads; this condition could adversely affect the structural
integrity of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
[[Page 25894]]
(g) Required Actions
Except as required by paragraph (h) of this AD: At the
applicable times specified in the ``Compliance'' paragraph of Boeing
Alert Requirements Bulletin 767-53A0278 RB, dated June 30, 2017, do
all applicable actions identified in, and in accordance with, the
Accomplishment Instructions of Boeing Alert Requirements Bulletin
767-53A0278 RB, dated June 30, 2017.
Note 1 to paragraph (g) of this AD: Guidance for accomplishing
the actions required by this AD can be found in Boeing Alert Service
Bulletin 767-53A0278, dated June 30, 2017, which is referred to in
Boeing Alert Requirements Bulletin 767-53A0278 RB, dated June 30,
2017.
(h) Exceptions to Service Information Specifications
(1) For purposes of determining compliance with the requirements
of this AD: Where Boeing Alert Requirements Bulletin 767-53A0278 RB,
dated June 30, 2017, uses the phrase ``the original issue date of
Requirements Bulletin 767-53A0278 RB,'' this AD requires using ``the
effective date of this AD.''
(2) Where Boeing Alert Requirements Bulletin 767-53A0278 RB,
dated June 30, 2017, specifies contacting Boeing, this AD requires
repair using a method approved in accordance with the procedures
specified in paragraph (i) of this AD.
(3) For airplanes identified as Group 1, Configuration 1, in
Boeing Alert Requirements Bulletin 767-53A0278 RB, dated June 30,
2017, that have been modified to a freighter configuration: The
actions specified in Boeing Alert Requirements Bulletin 767-53A0278
RB, dated June 30, 2017, for Group 1, Configuration 2, must be done
instead of the actions for Group 1, Configuration 1, except as
required by paragraph (h)(2) of this AD.
(4) For airplanes identified as Group 2, Configuration 1, in
Boeing Alert Requirements Bulletin 767-53A0278 RB, dated June 30,
2017, that have been modified to a freighter configuration: The
actions specified in Boeing Alert Requirements Bulletin 767-53A0278
RB, dated June 30, 2017, for Group 2, Configuration 2, must be done
instead of the actions for Group 2, Configuration 1, except as
required by paragraph (h)(2) of this AD.
(i) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Seattle 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 (j) 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 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.
(j) Related Information
For more information about this AD, contact Wayne Lockett,
Aerospace Engineer, Airframe Section, FAA, Seattle ACO Branch, 2200
S. 216th St., Des Moines, WA 98198; phone and fax: 206-231-3524;
email: [email protected].
(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 Requirements Bulletin 767-53A0278 RB, dated
June 30, 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, 2200 South 216th St., Des Moines, WA. For
information on the availability of this material at the FAA, call
206-231-3195.
(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: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Des Moines, Washington, on May 18, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2018-11427 Filed 6-4-18; 8:45 am]
BILLING CODE 4910-13-P
