Airworthiness Directives; The Boeing Company Airplanes, 9749-9751 [2016-03886]
Download as PDF
Federal Register / Vol. 81, No. 38 / Friday, February 26, 2016 / Rules and Regulations
´
(i) Avions de Transport Regional Service
Bulletin ATR42–92–0024, Revision 03, dated
January 21, 2015.
´
(ii) Avions de Transport Regional Service
Bulletin ATR72–92–1032, Revision 03, dated
January 21, 2015.
(3) For service information identified in
this AD, contact ATR–GIE Avions de
´
´
Transport Regional, 1, Allee Pierre Nadot,
31712 Blagnac Cedex, France; telephone +33
(0) 5 62 21 62 21; fax +33 (0) 5 62 21 67 18;
email continued.airworthiness@atr.fr;
Internet https://www.aerochain.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: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on February
16, 2016.
Dionne Palermo,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2016–03689 Filed 2–25–16; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–3146; Directorate
Identifier 2014–NM–249–AD; Amendment
39–18411; AD 2016–04–17]
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 777–200
series airplanes. This AD was prompted
by an evaluation by the design approval
holder (DAH) indicating that the skin
lap splices at certain stringers in certain
fuselage sections are subject to
widespread fatigue damage (WFD) on
aging Model 777 airplanes that have
accumulated at least 45,000 total flight
cycles. This AD requires inspections to
detect cracking of fuselage skin lap
splices in certain fuselage sections, and
corrective actions if necessary;
modification of left-side and right-side
lap splices; and post-modification
repetitive inspections for cracks in the
modified lap splices, and corrective
mstockstill on DSK4VPTVN1PROD with RULES
SUMMARY:
VerDate Sep<11>2014
17:33 Feb 25, 2016
Jkt 238001
actions if necessary. We are issuing this
AD to detect and correct fatigue
cracking of the skin lap splices, and
consequent risk of sudden
decompression and the inability to
sustain limit flight and pressure loads.
DATES: This AD is effective April 1,
2016.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of April 1, 2016.
ADDRESSES: For service information
identified in this final rule, contact
Boeing Commercial Airplanes,
Attention: Data & Services Management,
P. O. Box 3707, MC 2H–65, Seattle, WA
98124–2207; telephone 206–544–5000,
extension 1; fax 206–766–5680; 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 https://
www.regulations.gov by searching for
and locating Docket No. FAA–2015–
3146.
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–2015–
3146; 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
Lin, Aerospace Engineer, Airframe
Branch, ANM–120S, FAA, Seattle
Aircraft Certification Office (ACO), 1601
Lind Avenue SW., Renton, WA 98057–
3356; phone: 425–917–6412; fax: 425–
917–6590; email: Eric.Lin@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 777–200 series airplanes. The
NPRM published in the Federal
Register on August 25, 2015 (80 FR
51488) (‘‘the NPRM’’). The NPRM was
PO 00000
Frm 00009
Fmt 4700
Sfmt 4700
9749
prompted by an evaluation by the DAH
indicating that the skin lap splices at
certain stringers in certain fuselage
sections are subject to WFD on aging
airplanes (airplanes that have
accumulated at least 45,000 total flight
cycles). The NPRM proposed to require
inspections to detect cracking of
fuselage skin lap splices in certain
fuselage sections, and corrective actions
if necessary; modification of left-side
and right-side lap splices; and postmodification repetitive inspections for
cracks in the modified lap splices, and
corrective actions if necessary. We are
issuing this AD to detect and correct
fatigue cracking of the skin lap splices,
and consequent risk of sudden
decompression and the inability to
sustain limit flight and pressure loads.
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
An anonymous commenter expressed
support for the NPRM.
Request To Revise WFD Criteria
Definition
Boeing requested that we revise the
NPRM to specify that DAH analysis
indicates that potential multi-site
damage that could lead to WFD does not
occur until at least 45,000 total flight
cycles on aging Model 777 airplanes.
We agree with the commenter’s
request. We have revised the SUMMARY
and Discussion sections of this final rule
and paragraph (e) of this AD to specify
that this AD was prompted by an
evaluation by the DAH indicating that
the skin lap splices at certain stringers
in certain fuselage sections are subject
to WFD on aging Model 777 airplanes
that have accumulated at least 45,000
total flight cycles.
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
E:\FR\FM\26FER1.SGM
26FER1
9750
Federal Register / Vol. 81, No. 38 / Friday, February 26, 2016 / Rules and Regulations
burden on any operator or increase the
scope of this AD.
course of business or by the means
identified in the ADDRESSES section.
procedures for inspections to detect
cracking of fuselage skin lap splices,
modification to the skin lap splices,
repetitive inspections for cracks in the
modified lap splices, and repairs. This
service information is reasonably
available because the interested parties
have access to it through their normal
Related Service Information Under 1
CFR Part 51
We reviewed Boeing Alert Service
Bulletin 777–53A0052, dated October
10, 2014. The service bulletin describes
Costs of Compliance
We estimate that this AD affects 21
airplanes of U.S. registry.
We estimate the following costs to
comply with this AD:
ESTIMATED COSTS
Action
Labor cost
Parts cost
Cost per product
Inspection and modification.
Post-modification inspection.
2,713 work-hours × $85 per hour = $230,605 ...
$0
$230,605 ......................
$4,842,705.
1,391 work-hours × $85 per hour = $118,235
per inspection cycle.
0
$118,235 per inspection
cycle.
$2,482,935 per 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.
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 available costs in our
cost estimate.
(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.
Authority for This Rulemaking
List of Subjects in 14 CFR Part 39
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.
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
mstockstill on DSK4VPTVN1PROD with RULES
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:
VerDate Sep<11>2014
17:33 Feb 25, 2016
Jkt 238001
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):
■
2016–04–17 The Boeing Company:
Amendment 39–18411; Docket No.
FAA–2015–3146; Directorate Identifier
2014–NM–249–AD.
(a) Effective Date
This AD is effective April 1, 2016.
(b) Affected ADs
None.
(c) Applicability
This AD applies to The Boeing Company
Model 777–200 series airplanes, certificated
in any category, as identified in Boeing Alert
Service Bulletin 777–53A0052, dated October
10, 2014.
PO 00000
Frm 00010
Fmt 4700
Sfmt 4700
Cost on U.S. operators
(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 skin lap splices at certain stringers in
certain fuselage sections are subject to
widespread fatigue damage on aging Model
777 airplanes that have accumulated at least
45,000 total flight cycles. We are issuing this
AD to detect and correct fatigue cracking of
the skin lap splices, and consequent risk of
sudden decompression and the inability to
sustain limit flight and pressure loads.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Inspections and Corrective Actions
Except as provided by paragraph (h)(1) of
this AD, at the applicable time specified in
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 777–53A0052, dated
October 10, 2014: Do Part 1, inspection ‘‘A,’’
of the modification area for cracks; Part 2,
inspection ‘‘B,’’ of the modification area for
cracks; and Part 3, inspection ‘‘C,’’ of the
modification area for scribe lines and cracks;
as applicable; and do all applicable
corrective actions; in accordance with the
Accomplishment Instructions of Boeing Alert
Service Bulletin 777–53A0052, dated October
10, 2014, except as provided by paragraph
(h)(2) of this AD. Do all applicable corrective
actions before further flight.
(1) Inspection ‘‘A’’ includes an external
phased array ultrasonic inspection for cracks
in the lower/overlapped skin of the stringer
S–14 left and right (L/R) lap splices between
fuselage station 655 and station 1434, and an
open hole high frequency eddy current
(HFEC) inspection for skin cracks at the
upper and lower fastener rows of the stringer
S–14 L/R lap splices.
(2) Inspection ‘‘B’’ includes the inspections
specified in paragraphs (g)(2)(i) through
(g)(2)(iv) of this AD.
(i) A detailed inspection for cracks of any
skin panel common to a stringer S–14 L/R lap
splice between fuselage station 655 and
station 1434 that has a scribe line 0.001 inch
or deeper.
E:\FR\FM\26FER1.SGM
26FER1
Federal Register / Vol. 81, No. 38 / Friday, February 26, 2016 / Rules and Regulations
(ii) Either an ultrasonic inspection or a
surface HFEC inspection for cracks
(depending on the location of the scribe
line(s)) of any skin panel common to a
stringer S–14 L/R lap splice between fuselage
station 655 and station 1434 that has a scribe
line 0.001 inch or deeper.
(iii) An external phased array ultrasonic
inspection for cracks in the lower/overlapped
skin of the stringer S–14 L/R lap splices
between fuselage station 655 and station
1434.
(iv) An open hole HFEC inspection for skin
cracks at the upper and lower fastener rows
of the stringer S–14 L/R lap splices.
(3) Inspection ‘‘C’’ includes the inspections
for scribe lines and cracks specified in
paragraphs (g)(3)(i), (g)(3)(ii), and (g)(3)(iii) of
this AD on stringer S–14 L/R lap splice
between fuselage station 655 and station
1434 on both sides of the airplane.
(i) A detailed inspection for scribe lines. If
any scribe line is found during the inspection
required by this paragraph, the actions
include the inspections specified in
paragraphs (g)(3)(i)(A) and (g)(3)(i)(B) of this
AD.
(A) A detailed inspection for cracks of the
scribe line area(s).
(B) Either an ultrasonic inspection or a
surface HFEC inspection for cracks
(depending on the location of the scribe
line(s)).
(ii) An external phased array ultrasonic
inspection for cracks in the lower/overlapped
skin of the stringer S–14 L/R lap splices
between fuselage station 655 and station
1434.
(iii) An open hole HFEC inspection for skin
cracks at the upper and lower fastener rows
of the stringer S–14 L/R lap splices.
(h) Exceptions to Service Information
Specifications
(1) Where Paragraph 1.E., ‘‘Compliance,’’ of
Boeing Alert Service Bulletin 777–53A0052,
dated October 10, 2014, 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) If, during accomplishment of any
inspection required by this AD, any
condition is found for which Boeing Alert
Service Bulletin 777–53A0052, dated October
10, 2014, specifies to contact Boeing for
special repair instructions or supplemental
instructions for the modification, and
specifies that action as ‘‘RC’’ (Required for
Compliance): Before further flight, do the
repair or modification using a method
approved in accordance with the procedures
specified in paragraph (k) of this AD.
mstockstill on DSK4VPTVN1PROD with RULES
(i) Lap Splice Modification
At the applicable time specified in
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 777–53A0052, dated
October 10, 2014: Do the left-side and rightside lap splice modification, in accordance
with the Accomplishment Instructions of
Boeing Alert Service Bulletin 777–53A0052,
dated October 10, 2014, except as provided
by paragraph (h)(2) of this AD.
VerDate Sep<11>2014
17:33 Feb 25, 2016
Jkt 238001
(j) Post-Modification Inspections and
Corrective Action
At the applicable time specified in
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 777–53A0052, dated
October 10, 2014: Do a post-modification
internal surface HFEC inspection for skin
cracks in the modified lap splices on both
sides of the airplane; and do all applicable
corrective actions; in accordance with the
Accomplishment Instructions of Boeing Alert
Service Bulletin 777–53A0052, dated October
10, 2014, except as provided by paragraph
(h)(2) of this AD. Do all applicable corrective
actions before further flight. Repeat the
inspection of the modified lap splices
thereafter at the applicable intervals specified
in paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 777–53A0052, dated
October 10, 2014.
(k) 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 (l) of this AD. Information may be
emailed to: 9-ANM-Seattle-ACO-AMOCRequests@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, 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) Except as required by paragraph (h)(2)
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) 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. 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 Eric Lin, Aerospace Engineer,
PO 00000
Frm 00011
Fmt 4700
Sfmt 4700
9751
Airframe Branch, ANM–120S, FAA, Seattle
ACO, 1601 Lind Avenue SW., Renton, WA
98057–3356; phone: 425–917–6412; fax: 425–
917–6590; email: Eric.Lin@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.
(i) Boeing Alert Service Bulletin 777–
53A0052, dated October 10, 2014.
(ii) Reserved.
(3) For Boeing service information
identified in this AD, contact Boeing
Commercial Airplanes, Attention: Data &
Services Management, P.O. Box 3707, MC
2H–65, Seattle, WA 98124–2207; telephone
206–544–5000, extension 1; fax 206–766–
5680; Internet https://
www.myboeingfleet.com.
(4) You may view this service information
at 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: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on February
16, 2016.
Dionne Palermo,
Acting Manager,
Transport Airplane Directorate, Aircraft
Certification Service.
[FR Doc. 2016–03886 Filed 2–25–16; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–2984; Directorate
Identifier 2015–NE–21–AD; Amendment 39–
18405; AD 2016–04–11]
RIN 2120–AA64
Airworthiness Directives; General
Electric Company Turbofan Engines
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for all
General Electric Company (GE) GEnx–
1B54, –1B58, –1B64, –1B67, and –1B70
turbofan engine models. This AD was
prompted by reports of two separate,
single engine in-flight shutdowns
SUMMARY:
E:\FR\FM\26FER1.SGM
26FER1
Agencies
[Federal Register Volume 81, Number 38 (Friday, February 26, 2016)]
[Rules and Regulations]
[Pages 9749-9751]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-03886]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2015-3146; Directorate Identifier 2014-NM-249-AD;
Amendment 39-18411; AD 2016-04-17]
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 777-200 series airplanes. This AD was prompted
by an evaluation by the design approval holder (DAH) indicating that
the skin lap splices at certain stringers in certain fuselage sections
are subject to widespread fatigue damage (WFD) on aging Model 777
airplanes that have accumulated at least 45,000 total flight cycles.
This AD requires inspections to detect cracking of fuselage skin lap
splices in certain fuselage sections, and corrective actions if
necessary; modification of left-side and right-side lap splices; and
post-modification repetitive inspections for cracks in the modified lap
splices, and corrective actions if necessary. We are issuing this AD to
detect and correct fatigue cracking of the skin lap splices, and
consequent risk of sudden decompression and the inability to sustain
limit flight and pressure loads.
DATES: This AD is effective April 1, 2016.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of April 1,
2016.
ADDRESSES: For service information identified in this final rule,
contact Boeing Commercial Airplanes, Attention: Data & Services
Management, P. O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone
206-544-5000, extension 1; fax 206-766-5680; 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 https://www.regulations.gov by searching for and locating Docket No. FAA-2015-
3146.
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-2015-
3146; 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 Lin, Aerospace Engineer, Airframe
Branch, ANM-120S, FAA, Seattle Aircraft Certification Office (ACO),
1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6412; fax:
425-917-6590; email: Eric.Lin@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 777-200 series airplanes. The NPRM published in the Federal
Register on August 25, 2015 (80 FR 51488) (``the NPRM''). The NPRM was
prompted by an evaluation by the DAH indicating that the skin lap
splices at certain stringers in certain fuselage sections are subject
to WFD on aging airplanes (airplanes that have accumulated at least
45,000 total flight cycles). The NPRM proposed to require inspections
to detect cracking of fuselage skin lap splices in certain fuselage
sections, and corrective actions if necessary; modification of left-
side and right-side lap splices; and post-modification repetitive
inspections for cracks in the modified lap splices, and corrective
actions if necessary. We are issuing this AD to detect and correct
fatigue cracking of the skin lap splices, and consequent risk of sudden
decompression and the inability to sustain limit flight and pressure
loads.
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
An anonymous commenter expressed support for the NPRM.
Request To Revise WFD Criteria Definition
Boeing requested that we revise the NPRM to specify that DAH
analysis indicates that potential multi-site damage that could lead to
WFD does not occur until at least 45,000 total flight cycles on aging
Model 777 airplanes.
We agree with the commenter's request. We have revised the SUMMARY
and Discussion sections of this final rule and paragraph (e) of this AD
to specify that this AD was prompted by an evaluation by the DAH
indicating that the skin lap splices at certain stringers in certain
fuselage sections are subject to WFD on aging Model 777 airplanes that
have accumulated at least 45,000 total flight cycles.
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
[[Page 9750]]
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 777-53A0052, dated
October 10, 2014. The service bulletin describes procedures for
inspections to detect cracking of fuselage skin lap splices,
modification to the skin lap splices, repetitive inspections for cracks
in the modified lap splices, and repairs. 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 21 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
----------------------------------------------------------------------------------------------------------------
Inspection and modification.... 2,713 work-hours x $85 $0 $230,605.......... $4,842,705.
per hour = $230,605.
Post-modification inspection... 1,391 work-hours x $85 0 $118,235 per $2,482,935 per
per hour = $118,235 inspection cycle. inspection cycle.
per 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.
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 available 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
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):
2016-04-17 The Boeing Company: Amendment 39-18411; Docket No. FAA-
2015-3146; Directorate Identifier 2014-NM-249-AD.
(a) Effective Date
This AD is effective April 1, 2016.
(b) Affected ADs
None.
(c) Applicability
This AD applies to The Boeing Company Model 777-200 series
airplanes, certificated in any category, as identified in Boeing
Alert Service Bulletin 777-53A0052, dated October 10, 2014.
(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 skin lap splices at certain stringers in
certain fuselage sections are subject to widespread fatigue damage
on aging Model 777 airplanes that have accumulated at least 45,000
total flight cycles. We are issuing this AD to detect and correct
fatigue cracking of the skin lap splices, and consequent risk of
sudden decompression and the inability to sustain limit flight and
pressure loads.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Inspections and Corrective Actions
Except as provided by paragraph (h)(1) of this AD, at the
applicable time specified in paragraph 1.E., ``Compliance,'' of
Boeing Alert Service Bulletin 777-53A0052, dated October 10, 2014:
Do Part 1, inspection ``A,'' of the modification area for cracks;
Part 2, inspection ``B,'' of the modification area for cracks; and
Part 3, inspection ``C,'' of the modification area for scribe lines
and cracks; as applicable; and do all applicable corrective actions;
in accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 777-53A0052, dated October 10, 2014, except as
provided by paragraph (h)(2) of this AD. Do all applicable
corrective actions before further flight.
(1) Inspection ``A'' includes an external phased array
ultrasonic inspection for cracks in the lower/overlapped skin of the
stringer S-14 left and right (L/R) lap splices between fuselage
station 655 and station 1434, and an open hole high frequency eddy
current (HFEC) inspection for skin cracks at the upper and lower
fastener rows of the stringer S-14 L/R lap splices.
(2) Inspection ``B'' includes the inspections specified in
paragraphs (g)(2)(i) through (g)(2)(iv) of this AD.
(i) A detailed inspection for cracks of any skin panel common to
a stringer S-14 L/R lap splice between fuselage station 655 and
station 1434 that has a scribe line 0.001 inch or deeper.
[[Page 9751]]
(ii) Either an ultrasonic inspection or a surface HFEC
inspection for cracks (depending on the location of the scribe
line(s)) of any skin panel common to a stringer S-14 L/R lap splice
between fuselage station 655 and station 1434 that has a scribe line
0.001 inch or deeper.
(iii) An external phased array ultrasonic inspection for cracks
in the lower/overlapped skin of the stringer S-14 L/R lap splices
between fuselage station 655 and station 1434.
(iv) An open hole HFEC inspection for skin cracks at the upper
and lower fastener rows of the stringer S-14 L/R lap splices.
(3) Inspection ``C'' includes the inspections for scribe lines
and cracks specified in paragraphs (g)(3)(i), (g)(3)(ii), and
(g)(3)(iii) of this AD on stringer S-14 L/R lap splice between
fuselage station 655 and station 1434 on both sides of the airplane.
(i) A detailed inspection for scribe lines. If any scribe line
is found during the inspection required by this paragraph, the
actions include the inspections specified in paragraphs (g)(3)(i)(A)
and (g)(3)(i)(B) of this AD.
(A) A detailed inspection for cracks of the scribe line area(s).
(B) Either an ultrasonic inspection or a surface HFEC inspection
for cracks (depending on the location of the scribe line(s)).
(ii) An external phased array ultrasonic inspection for cracks
in the lower/overlapped skin of the stringer S-14 L/R lap splices
between fuselage station 655 and station 1434.
(iii) An open hole HFEC inspection for skin cracks at the upper
and lower fastener rows of the stringer S-14 L/R lap splices.
(h) Exceptions to Service Information Specifications
(1) Where Paragraph 1.E., ``Compliance,'' of Boeing Alert
Service Bulletin 777-53A0052, dated October 10, 2014, 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) If, during accomplishment of any inspection required by this
AD, any condition is found for which Boeing Alert Service Bulletin
777-53A0052, dated October 10, 2014, specifies to contact Boeing for
special repair instructions or supplemental instructions for the
modification, and specifies that action as ``RC'' (Required for
Compliance): Before further flight, do the repair or modification
using a method approved in accordance with the procedures specified
in paragraph (k) of this AD.
(i) Lap Splice Modification
At the applicable time specified in paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 777-53A0052, dated
October 10, 2014: Do the left-side and right-side lap splice
modification, in accordance with the Accomplishment Instructions of
Boeing Alert Service Bulletin 777-53A0052, dated October 10, 2014,
except as provided by paragraph (h)(2) of this AD.
(j) Post-Modification Inspections and Corrective Action
At the applicable time specified in paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 777-53A0052, dated
October 10, 2014: Do a post-modification internal surface HFEC
inspection for skin cracks in the modified lap splices on both sides
of the airplane; and do all applicable corrective actions; in
accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 777-53A0052, dated October 10, 2014, except as
provided by paragraph (h)(2) of this AD. Do all applicable
corrective actions before further flight. Repeat the inspection of
the modified lap splices thereafter at the applicable intervals
specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service
Bulletin 777-53A0052, dated October 10, 2014.
(k) 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 (l) of this AD.
Information may be emailed to: 9-ANM-Seattle-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 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) Except as required by paragraph (h)(2) 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) 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. 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 Eric Lin, Aerospace
Engineer, Airframe Branch, ANM-120S, FAA, Seattle ACO, 1601 Lind
Avenue SW., Renton, WA 98057-3356; phone: 425-917-6412; fax: 425-
917-6590; email: Eric.Lin@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.
(i) Boeing Alert Service Bulletin 777-53A0052, dated October 10,
2014.
(ii) Reserved.
(3) For Boeing service information identified in this AD,
contact Boeing Commercial Airplanes, Attention: Data & Services
Management, P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207;
telephone 206-544-5000, extension 1; fax 206-766-5680; Internet
https://www.myboeingfleet.com.
(4) You may view this service information at 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: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on February 16, 2016.
Dionne Palermo,
Acting Manager,
Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2016-03886 Filed 2-25-16; 8:45 am]
BILLING CODE 4910-13-P