Airworthiness Directives; The Boeing Company Airplanes, 89371-89373 [2016-29246]
Download as PDF
Federal Register / Vol. 81, No. 238 / Monday, December 12, 2016 / Rules and Regulations
Issued in Renton, Washington, on
November 17, 2016.
Phil Forde,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
call 425–227–1221. It is also available
on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2016–
5598.
[FR Doc. 2016–28597 Filed 12–9–16; 8:45 am]
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–2016–
5598; 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: Bill
Ashforth, Aerospace Engineer, Airframe
Branch, ANM–120S, FAA, Seattle
Aircraft Certification Office (ACO), 1601
Lind Avenue SW., Renton, WA 98057–
3356; phone: 425–917–6432; fax: 425–
917–6590; email: Bill.Ashforth@faa.gov.
SUPPLEMENTARY INFORMATION:
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–5598; Directorate
Identifier 2016–NM–001–AD; Amendment
39–18735; AD 2016–25–09]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are superseding
Airworthiness Directive (AD) 2012–22–
02 for certain The Boeing Company
Model 747–400, –400D, and –400F
series airplanes. AD 2012–22–02
required measuring the web at station
(STA) 320 and, depending on findings,
various inspections for cracks and
missing fasteners, web and fastener
replacement, and related investigative
and corrective actions if necessary. This
new AD requires, for certain airplanes,
replacement of the web, including
related investigative and corrective
actions if necessary. This AD was
prompted by a determination that there
were no inspection or repair procedures
included in AD 2012–22–02 for
airplanes with a certain crown frame
web thickness. We are issuing this AD
to address the unsafe condition on these
products.
DATES: This AD is effective January 17,
2017.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of January 17, 2017.
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,
mstockstill on DSK3G9T082PROD with RULES
SUMMARY:
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Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2012–22–02,
Amendment 39–17238 (77 FR 69739,
November 21, 2012) (‘‘AD 2012–22–
02’’). AD 2012–22–02 applied to certain
The Boeing Company Model 747–400,
–400D, and –400F series airplanes. The
NPRM published in the Federal
Register on April 28, 2016 (81 FR
25357) (‘‘the NPRM’’). The NPRM was
prompted by a determination that there
were no inspection or repair procedures
included in AD 2012–22–02 for
airplanes with a STA 320 crown frame
web thickness less than 0.078 inch, or
greater than or equal to 0.084 inch and
less than or equal to 0.135 inch. The
NPRM proposed to continue to require
certain actions required by AD 2012–
22–02. The NPRM also proposed to
require, for certain airplanes,
replacement of the web, including
related investigative and corrective
actions if necessary. We are issuing this
AD to prevent complete fracture of the
crown frame assembly, and consequent
damage to the skin. Such damage could
result in in-flight decompression of the
airplane.
Comments
We gave the public the opportunity to
participate in developing this AD. The
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Fmt 4700
Sfmt 4700
89371
following presents the comments
received on the NPRM and the FAA’s
response to each comment.
Support for the NPRM
United Airlines stated that it concurs
with the NPRM.
Request To Remove Redundant
Requirements
Boeing requested we change
paragraph (i) of the proposed AD to
remove redundant language. Boeing
requested we remove the second half of
the paragraph and subparagraphs (i)(1)
and (i)(2) of the proposed AD because
they include redundant requirements.
Boeing also noted that the redundant
requirements include an exception that
does not apply to table 3 of paragraph
1.E., ‘‘Compliance,’’ of Boeing Alert
Service Bulletin 747–53A2784, Revision
2, dated August 20, 2015.
We agree to revise paragraph (i) of this
AD for the reasons provided by Boeing.
We have revised paragraph (i) of this AD
accordingly.
Conclusion
We reviewed the relevant data,
considered the comments received, and
determined that air safety and the
public interest require adopting this AD
with the change described previously,
and minor editorial changes. We have
determined that these minor changes:
• Are consistent with the intent that
was proposed in the NPRM for
correcting the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM.
We also determined that these
changes will not increase the economic
burden on any operator or increase the
scope of this AD.
Related Service Information Under 1
CFR Part 51
We reviewed Boeing Alert Service
Bulletin 747–53A2784, Revision 2,
dated August 20, 2015. The service
information describes procedures for
various inspections for cracks and
missing fasteners, web and fastener
replacement, and related investigative
and corrective actions, if necessary. 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 29
airplanes.
We estimate the following costs to
comply with this AD:
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89372
Federal Register / Vol. 81, No. 238 / Monday, December 12, 2016 / Rules and Regulations
ESTIMATED COSTS
Action
Labor cost
Parts cost
Cost per product
Cost on U.S.
operators
Measurement, inspection, and web replacement [retained actions from AD
2012–22–02].
Post-replacement inspection [retained
actions from AD 2012–22–02].
219 work-hours × $85 per hour =
$18,615 per inspection and replacement.
135 work-hours × $85 per hour =
$11,475 per inspection cycle.
Up to $21,887 .......
Up to $40,502 per
inspection and
replacement.
$11,475 per inspection cycle.
Up to $1,174,558
per inspection
and replacement.
$332,775 per inspection cycle.
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.
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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.
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16:18 Dec 09, 2016
Jkt 241001
$0 ..........................
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
removing Airworthiness Directive (AD)
2012–22–02, Amendment 39–17238 (77
FR 69739, November 21, 2012), and
adding the following new AD:
■
2016–25–09 The Boeing Company:
Amendment 39–18735; Docket No.
FAA–2016–5598; Directorate Identifier
2016–NM–001–AD.
(a) Effective Date
This AD is effective January 17, 2017.
(b) Affected ADs
This AD replaces AD 2012–22–02,
Amendment 39–17238 (77 FR 69739,
November 21, 2012) (‘‘AD 2012–22–02’’).
(c) Applicability
This AD applies to The Boeing Company
Model 747–400, –400D, and –400F series
airplanes, certificated in any category, as
specified in Boeing Alert Service Bulletin
747–53A2784, Revision 2, dated August 20,
2015.
(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by a determination
that there were no inspection or repair
procedures included in AD 2012–22–02 for
airplanes with a station (STA) 320 crown
frame web thickness less than 0.078 inch, or
greater than or equal to 0.084 inch and less
than or equal to 0.135 inch. We are issuing
this AD to prevent complete fracture of the
crown frame assembly, and consequent
damage to the skin. Such damage could
result in in-flight decompression of the
airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
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Frm 00016
Fmt 4700
Sfmt 4700
(g) Crown Frame Web Measurement for
Certain Airplanes
For Group 1, Configuration 3 airplanes,
identified in Boeing Alert Service Bulletin
747–53A2784, Revision 2, dated August 20,
2015: At the compliance time specified in
table 1 of paragraph 1.E., ‘‘Compliance,’’ of
Boeing Alert Service Bulletin 747–53A2784,
Revision 2, dated August 20, 2015, measure
the thickness of the crown frame web at STA
320, and do all applicable related
investigative and corrective actions, in
accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
747–53A2784, Revision 2, dated August 20,
2015, except as required by paragraph (l)(2)
of this AD. Do all related investigative and
corrective actions at the applicable times
specified in tables 2 and 3 of paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 747–53A2784, Revision 2, dated
August 20, 2015.
(h) Inspections (Web With No Repair
Doubler) and Related Investigative and
Corrective Actions (Including Web
Replacement)
For Group 1, Configuration 1 airplanes,
identified in Boeing Alert Service Bulletin
747–53A2784, Revision 2, dated August 20,
2015: For airplanes with a web thickness less
than 0.136 inch and no repair doubler
installed on the web, at the time specified in
table 2 of paragraph 1.E., ‘‘Compliance,’’ of
Boeing Alert Service Bulletin 747–53A2784,
Revision 2, dated August 20, 2015, do a
detailed inspection for cracks and a general
visual inspection for missing fasteners of the
crown frame web at STA 320, and do all
applicable related investigative and
corrective actions, in accordance with the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–53A2784, Revision 2,
dated August 20, 2015, except as specified in
paragraph (l)(2) of this AD. Do the applicable
related investigative and corrective actions at
the applicable times specified in paragraph
1.E., ‘‘Compliance,’’ of Boeing Alert Service
Bulletin 747–53A2784, Revision 2, dated
August 20, 2015.
(i) Inspection (Web With Repair Doubler)
and Related Investigative and Corrective
Actions (Including Web Replacement)
For Group 1, Configuration 1 airplanes,
identified in Boeing Alert Service Bulletin
747–53A2784, Revision 2, dated August 20,
2015: For airplanes with a web thickness less
than 0.136 inch and a repair doubler
installed on the web, at the time specified in
table 3 of paragraph 1.E., ‘‘Compliance,’’ of
Boeing Alert Service Bulletin 747–53A2784,
Revision 2, dated August 20, 2015, do a
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Federal Register / Vol. 81, No. 238 / Monday, December 12, 2016 / Rules and Regulations
detailed inspection for any crack in the upper
chord and lower chord of the STA 320 crown
frame, and do all applicable related
investigative and corrective actions, in
accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
747–53A2784, Revision 2, dated August 20,
2015, except as specified in paragraph (l)(2)
of this AD. Do the applicable related
investigative and corrective actions at the
applicable times specified in paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 747–53A2784, Revision 2, dated
August 20, 2015.
(j) Web Replacement for Certain Airplanes
For Group 1, Configuration 2 airplanes,
identified in Boeing Alert Service Bulletin
747–53A2784, Revision 2, dated August 20,
2015: At the applicable time specified in
table 5 of paragraph 1.E., ‘‘Compliance,’’ of
Boeing Alert Service Bulletin 747–53A2784,
Revision 2, dated August 20, 2015, except as
provided by paragraph (l)(1) of this AD,
replace the web, including doing related
investigative and corrective actions, in
accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
747–53A2784, Revision 2, dated August 20,
2015, except as required by paragraph (l)(2)
of this AD. Do all applicable related
investigative and corrective actions before
further flight.
mstockstill on DSK3G9T082PROD with RULES
(k) Post-Replacement Repetitive Inspections
of Replaced Web
Following any web replacement required
by this AD, at the time specified in paragraph
1.E., ‘‘Compliance,’’ of Boeing Alert Service
Bulletin 747–53A2784, Revision 2, dated
August 20, 2015: Do a detailed inspection for
cracks of the web, upper chord, lower chord,
and lower chord splice, and do all applicable
corrective actions, in accordance with the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–53A2784, Revision 2,
dated August 20, 2015, except as required by
paragraph (l)(2) of this AD. Do all applicable
corrective actions before further flight. If no
crack is found, repeat the inspection
thereafter at the intervals specified in
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 747–53A2784,
Revision 2, dated August 20, 2015.
Accomplishment of the inspections required
by AD 2009–19–05, Amendment 39–16022
(74 FR 48138, September 22, 2009),
terminates the requirements of this
paragraph.
(l) Exceptions to the Service Information,
With Updated Service Information
(1) Where Boeing Alert Service Bulletin
747–53A2784, Revision 2, dated August 20,
2015, specifies a compliance time ‘‘after the
Revision 2 date of the service bulletin,’’ this
AD requires compliance within the specified
compliance time after the effective date of
this AD.
(2) Where Boeing Alert Service Bulletin
747–53A2784, Revision 2, dated August 20,
2015, specifies to contact Boeing for
appropriate action, accomplish applicable
actions before further flight using a method
approved in accordance with the procedures
specified in paragraph (n) of this AD.
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(m) Credit for Previous Actions
(1) This paragraph provides credit for the
actions required by paragraphs (h), (i), and
(k) of this AD, if those actions were
performed before December 26, 2012 (the
effective date of AD 2012–22–02), using
Boeing Service Bulletin 747–53A2784, dated
August 27, 2009.
(2) This paragraph provides credit for the
actions required by paragraphs (h), (i), and
(k) of this AD, if those actions were
performed before the effective date of this AD
using Boeing Service Bulletin 747–53A2784,
Revision 1, dated September 14, 2011. This
service information was incorporated by
reference in AD 2012–22–02.
(n) 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 (o)(1) of this AD.
(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.
(o) Related Information
(1) For more information about this AD,
contact Bill Ashforth, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA, Seattle
Aircraft Certification Office (ACO), 1601 Lind
Avenue SW., Renton, WA 98057–3356;
phone: 425–917–6432; fax: 425–917–6590;
email: bill.Ashforth@faa.gov.
(2) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (p)(3) and (p)(4) of this AD.
(p) 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 747–
53A2784, Revision 2, dated August 20, 2015.
(ii) Reserved.
(3) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Data & Services
PO 00000
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Fmt 4700
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89373
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 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
November 25, 2016.
John P. Piccola, Jr.,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2016–29246 Filed 12–9–16; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–7530; Directorate
Identifier 2014–NM–257–AD; Amendment
39–18730; AD 2016–25–04]
RIN 2120–AA64
Airworthiness Directives; Fokker
Services B.V. Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for all
Fokker Services B.V. Model F28 Mark
0070 and 0100 airplanes. This AD was
prompted by a report of cracking in a
certain section of the secondary
structure of the wing. This AD requires
a one-time inspection of the trailing
edge rib, and corrective action if
necessary. We are issuing this AD to
address the unsafe condition on these
products.
SUMMARY:
This AD is effective January 17,
2017.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of January 17, 2017.
ADDRESSES: For service information
identified in this final rule, contact
Fokker Services B.V., Technical
Services Dept., P.O. Box 1357, 2130 EL
Hoofddorp, the Netherlands; telephone
+31 (0)88–6280–350; fax +31 (0)88–
6280–111; email technicalservices@
DATES:
E:\FR\FM\12DER1.SGM
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Agencies
[Federal Register Volume 81, Number 238 (Monday, December 12, 2016)]
[Rules and Regulations]
[Pages 89371-89373]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-29246]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2016-5598; Directorate Identifier 2016-NM-001-AD;
Amendment 39-18735; AD 2016-25-09]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are superseding Airworthiness Directive (AD) 2012-22-02 for
certain The Boeing Company Model 747-400, -400D, and -400F series
airplanes. AD 2012-22-02 required measuring the web at station (STA)
320 and, depending on findings, various inspections for cracks and
missing fasteners, web and fastener replacement, and related
investigative and corrective actions if necessary. This new AD
requires, for certain airplanes, replacement of the web, including
related investigative and corrective actions if necessary. This AD was
prompted by a determination that there were no inspection or repair
procedures included in AD 2012-22-02 for airplanes with a certain crown
frame web thickness. We are issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective January 17, 2017.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of January 17,
2017.
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-2016-
5598.
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-2016-
5598; 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: Bill Ashforth, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office
(ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-
6432; fax: 425-917-6590; email: Bill.Ashforth@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2012-22-02, Amendment 39-17238 (77 FR 69739,
November 21, 2012) (``AD 2012-22-02''). AD 2012-22-02 applied to
certain The Boeing Company Model 747-400, -400D, and -400F series
airplanes. The NPRM published in the Federal Register on April 28, 2016
(81 FR 25357) (``the NPRM''). The NPRM was prompted by a determination
that there were no inspection or repair procedures included in AD 2012-
22-02 for airplanes with a STA 320 crown frame web thickness less than
0.078 inch, or greater than or equal to 0.084 inch and less than or
equal to 0.135 inch. The NPRM proposed to continue to require certain
actions required by AD 2012-22-02. The NPRM also proposed to require,
for certain airplanes, replacement of the web, including related
investigative and corrective actions if necessary. We are issuing this
AD to prevent complete fracture of the crown frame assembly, and
consequent damage to the skin. Such damage could result in in-flight
decompression of the airplane.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the NPRM and
the FAA's response to each comment.
Support for the NPRM
United Airlines stated that it concurs with the NPRM.
Request To Remove Redundant Requirements
Boeing requested we change paragraph (i) of the proposed AD to
remove redundant language. Boeing requested we remove the second half
of the paragraph and subparagraphs (i)(1) and (i)(2) of the proposed AD
because they include redundant requirements. Boeing also noted that the
redundant requirements include an exception that does not apply to
table 3 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service
Bulletin 747-53A2784, Revision 2, dated August 20, 2015.
We agree to revise paragraph (i) of this AD for the reasons
provided by Boeing. We have revised paragraph (i) of this AD
accordingly.
Conclusion
We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
this AD with the change described previously, and minor editorial
changes. We have determined that these minor changes:
Are consistent with the intent that was proposed in the
NPRM for correcting the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM.
We also determined that these changes will not increase the
economic burden on any operator or increase the scope of this AD.
Related Service Information Under 1 CFR Part 51
We reviewed Boeing Alert Service Bulletin 747-53A2784, Revision 2,
dated August 20, 2015. The service information describes procedures for
various inspections for cracks and missing fasteners, web and fastener
replacement, and related investigative and corrective actions, if
necessary. 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 29 airplanes.
We estimate the following costs to comply with this AD:
[[Page 89372]]
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product Cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
Measurement, inspection, and 219 work-hours x $85 Up to $21,887... Up to $40,502 Up to $1,174,558 per
web replacement [retained per hour = $18,615 per inspection inspection and
actions from AD 2012-22-02]. per inspection and and replacement.
replacement. replacement.
Post-replacement inspection 135 work-hours x $85 $0.............. $11,475 per $332,775 per inspection
[retained actions from AD per hour = $11,475 inspection cycle.
2012-22-02]. per inspection cycle. cycle.
----------------------------------------------------------------------------------------------------------------
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)
2012-22-02, Amendment 39-17238 (77 FR 69739, November 21, 2012), and
adding the following new AD:
2016-25-09 The Boeing Company: Amendment 39-18735; Docket No. FAA-
2016-5598; Directorate Identifier 2016-NM-001-AD.
(a) Effective Date
This AD is effective January 17, 2017.
(b) Affected ADs
This AD replaces AD 2012-22-02, Amendment 39-17238 (77 FR 69739,
November 21, 2012) (``AD 2012-22-02'').
(c) Applicability
This AD applies to The Boeing Company Model 747-400, -400D, and
-400F series airplanes, certificated in any category, as specified
in Boeing Alert Service Bulletin 747-53A2784, Revision 2, dated
August 20, 2015.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by a determination that there were no
inspection or repair procedures included in AD 2012-22-02 for
airplanes with a station (STA) 320 crown frame web thickness less
than 0.078 inch, or greater than or equal to 0.084 inch and less
than or equal to 0.135 inch. We are issuing this AD to prevent
complete fracture of the crown frame assembly, and consequent damage
to the skin. Such damage could result in in-flight decompression of
the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Crown Frame Web Measurement for Certain Airplanes
For Group 1, Configuration 3 airplanes, identified in Boeing
Alert Service Bulletin 747-53A2784, Revision 2, dated August 20,
2015: At the compliance time specified in table 1 of paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 747-53A2784,
Revision 2, dated August 20, 2015, measure the thickness of the
crown frame web at STA 320, and do all applicable related
investigative and corrective actions, in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2784, Revision 2, dated August 20, 2015, except as required by
paragraph (l)(2) of this AD. Do all related investigative and
corrective actions at the applicable times specified in tables 2 and
3 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service
Bulletin 747-53A2784, Revision 2, dated August 20, 2015.
(h) Inspections (Web With No Repair Doubler) and Related Investigative
and Corrective Actions (Including Web Replacement)
For Group 1, Configuration 1 airplanes, identified in Boeing
Alert Service Bulletin 747-53A2784, Revision 2, dated August 20,
2015: For airplanes with a web thickness less than 0.136 inch and no
repair doubler installed on the web, at the time specified in table
2 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service
Bulletin 747-53A2784, Revision 2, dated August 20, 2015, do a
detailed inspection for cracks and a general visual inspection for
missing fasteners of the crown frame web at STA 320, and do all
applicable related investigative and corrective actions, in
accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 747-53A2784, Revision 2, dated August 20, 2015,
except as specified in paragraph (l)(2) of this AD. Do the
applicable related investigative and corrective actions at the
applicable times specified in paragraph 1.E., ``Compliance,'' of
Boeing Alert Service Bulletin 747-53A2784, Revision 2, dated August
20, 2015.
(i) Inspection (Web With Repair Doubler) and Related Investigative and
Corrective Actions (Including Web Replacement)
For Group 1, Configuration 1 airplanes, identified in Boeing
Alert Service Bulletin 747-53A2784, Revision 2, dated August 20,
2015: For airplanes with a web thickness less than 0.136 inch and a
repair doubler installed on the web, at the time specified in table
3 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service
Bulletin 747-53A2784, Revision 2, dated August 20, 2015, do a
[[Page 89373]]
detailed inspection for any crack in the upper chord and lower chord
of the STA 320 crown frame, and do all applicable related
investigative and corrective actions, in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2784, Revision 2, dated August 20, 2015, except as specified in
paragraph (l)(2) of this AD. Do the applicable related investigative
and corrective actions at the applicable times specified in
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
747-53A2784, Revision 2, dated August 20, 2015.
(j) Web Replacement for Certain Airplanes
For Group 1, Configuration 2 airplanes, identified in Boeing
Alert Service Bulletin 747-53A2784, Revision 2, dated August 20,
2015: At the applicable time specified in table 5 of paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 747-53A2784,
Revision 2, dated August 20, 2015, except as provided by paragraph
(l)(1) of this AD, replace the web, including doing related
investigative and corrective actions, in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2784, Revision 2, dated August 20, 2015, except as required by
paragraph (l)(2) of this AD. Do all applicable related investigative
and corrective actions before further flight.
(k) Post-Replacement Repetitive Inspections of Replaced Web
Following any web replacement required by this AD, at the time
specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service
Bulletin 747-53A2784, Revision 2, dated August 20, 2015: Do a
detailed inspection for cracks of the web, upper chord, lower chord,
and lower chord splice, and do all applicable corrective actions, in
accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 747-53A2784, Revision 2, dated August 20, 2015,
except as required by paragraph (l)(2) of this AD. Do all applicable
corrective actions before further flight. If no crack is found,
repeat the inspection thereafter at the intervals specified in
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
747-53A2784, Revision 2, dated August 20, 2015. Accomplishment of
the inspections required by AD 2009-19-05, Amendment 39-16022 (74 FR
48138, September 22, 2009), terminates the requirements of this
paragraph.
(l) Exceptions to the Service Information, With Updated Service
Information
(1) Where Boeing Alert Service Bulletin 747-53A2784, Revision 2,
dated August 20, 2015, specifies a compliance time ``after the
Revision 2 date of the service bulletin,'' this AD requires
compliance within the specified compliance time after the effective
date of this AD.
(2) Where Boeing Alert Service Bulletin 747-53A2784, Revision 2,
dated August 20, 2015, specifies to contact Boeing for appropriate
action, accomplish applicable actions before further flight using a
method approved in accordance with the procedures specified in
paragraph (n) of this AD.
(m) Credit for Previous Actions
(1) This paragraph provides credit for the actions required by
paragraphs (h), (i), and (k) of this AD, if those actions were
performed before December 26, 2012 (the effective date of AD 2012-
22-02), using Boeing Service Bulletin 747-53A2784, dated August 27,
2009.
(2) This paragraph provides credit for the actions required by
paragraphs (h), (i), and (k) of this AD, if those actions were
performed before the effective date of this AD using Boeing Service
Bulletin 747-53A2784, Revision 1, dated September 14, 2011. This
service information was incorporated by reference in AD 2012-22-02.
(n) 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 (o)(1) of this AD.
(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.
(o) Related Information
(1) For more information about this AD, contact Bill Ashforth,
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft
Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-
3356; phone: 425-917-6432; fax: 425-917-6590; email:
bill.Ashforth@faa.gov.
(2) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (p)(3) and (p)(4) of this AD.
(p) 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 747-53A2784, Revision 2, dated
August 20, 2015.
(ii) Reserved.
(3) For 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 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/ibr-locations.html.
Issued in Renton, Washington, on November 25, 2016.
John P. Piccola, Jr.,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2016-29246 Filed 12-9-16; 8:45 am]
BILLING CODE 4910-13-P