Airworthiness Directives; The Boeing Company Airplanes, 9489-9492 [2017-01341]
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9489
Rules and Regulations
Federal Register
Vol. 82, No. 24
Tuesday, February 7, 2017
This section of the FEDERAL REGISTER
contains regulatory documents having general
applicability and legal effect, most of which
are keyed to and codified in the Code of
Federal Regulations, which is published under
50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by
the Superintendent of Documents. Prices of
new books are listed in the first FEDERAL
REGISTER issue of each week.
DEPARTMENT OF AGRICULTURE
Grain Inspection, Packers and
Stockyards Administration
9 CFR Part 201
RIN 0580–AB25
Scope of Sections 202(a) and (b) of the
Packers and Stockyards Act
Grain Inspection, Packers and
Stockyards Administration, USDA.
AGENCY:
Interim final rule; notice of
delay of effective date and extension of
comment period.
ACTION:
Consistent with the
memorandum of January 20, 2017, to
the heads of executive departments and
agencies from the Assistant to the
President and Chief of Staff entitled
‘‘Regulatory Freeze Pending Review,’’
the Department of Agriculture’s Grain
Inspection, Packers and Stockyards
Administration (GIPSA) is extending the
public comment period and delaying
the effective date of the rule published
on December 20, 2016. This interim
final rule adds a paragraph to § 201.3
addressing the scope of sections 202(a)
and (b) of the Packers and Stockyards
Act, 1921, as amended and
supplemented (P&S Act) in order to
clarify that conduct or action may
violate sections 202(a) and (b) of the
P&S Act without adversely affecting, or
having a likelihood of adversely
affecting, competition. This rule was
originally set to take effect on February
21, 2017.
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SUMMARY:
Effective February 7, 2017, the
effective date of the interim final rule
amending 9 CFR part 201, published at
81 FR 92566, December 20, 2016 is
delayed until April 22, 2017. Interested
persons are invited to submit written
comments on this interim final rule on
or before March 24, 2017.
DATES:
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18:06 Feb 06, 2017
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We invite you to submit
comments on this interim final rule by
any of the following methods:
• Mail: M. Irene Omade, GIPSA,
USDA, 1400 Independence Avenue
SW., Room 2542A–S, Washington, DC
20250–3613.
• Hand Delivery or Courier: M. Irene
Omade, GIPSA, USDA, 1400
Independence Avenue SW., Room
2530–S, Washington, DC 20250–3613.
• Internet: https://
www.regulations.gov. Follow the on-line
instructions for submitting comments.
Instructions: All comments should
make reference to the date and page
number of this issue of the Federal
Register. All comments received will be
included in the public docket without
change, including any personal
information provided. Regulatory
analyses and other documents relating
to this rulemaking will be available for
public inspection in Room 2542A–S,
1400 Independence Avenue SW.,
Washington, DC 20250–3613 during
regular business hours. All comments
will be available for public inspection in
the above office during regular business
hours (7 CFR 1.27(b)). Please call the
Management and Budget Services staff
of GIPSA at (202) 720–8479 to arrange
a public inspection of comments or
other documents related to this
rulemaking.
FOR FURTHER INFORMATION CONTACT:
S. Brett Offutt, Director, Litigation and
Economic Analysis Division, P&SP,
GIPSA, 1400 Independence Ave. SW.,
Washington, DC 20250, (202) 720–7051,
s.brett.offutt@usda.gov.
SUPPLEMENTARY INFORMATION: Consistent
with the memorandum of January 20,
2017, to the heads of executive
departments and agencies from the
Assistant to the President and Chief of
Staff entitled ‘‘Regulatory Freeze
Pending Review,’’ GIPSA is extending
the public comment period and
delaying the effective date of the interim
final rule entitled ‘‘Scope of Sections
202(a) and (b) of the Packers and
Stockyards Act’’ that was published in
the Federal Register on December 20,
2016, 81 FR 92566.
This interim final rule states the
interpretation that not all violations of
the P&S Act require a showing of harm
or likely harm to competition. Section
201.3(a) specifically provides that the
scope of section 202(a) and (b)
encompasses conduct or action that,
ADDRESSES:
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depending on their nature and the
circumstances, can be found to violate
the P&S Act without a finding of harm
or likely harm to competition. This
interim final rule finalizes a proposed
§ 201.3(c) that GIPSA published on June
22, 2010, 75 FR 35338, with slight
modifications in order to allow
additional public comment on these
provisions.
To the extent that 5 U.S.C. 553(b)(A)
applies to this action, it is exempt from
notice and comment rulemaking for
good cause and for reasons cited above,
GIPSA finds that notice and solicitation
of comment regarding the brief
extension of the effective date of the
interim finalrule are impracticable,
unnecessary, or contrary to the public
interest pursuant to 5 U.S.C. 553(b)(B).
GIPSA believes that affected parties
need to be informed as soon as possible
of the extension and its length.
Marianne Plaus,
Acting Administrator, Grain Inspection,
Packers and Stockyards Administration.
[FR Doc. 2017–02496 Filed 2–6–17; 8:45 am]
BILLING CODE 3410–KD–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–7261; Directorate
Identifier 2016–NM–004–AD; Amendment
39–18783; AD 2017–02–04]
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 747–200B,
747–300, 747–400, 747–400D, and 747–
400F series airplanes. This AD was
prompted by a report of cracking in both
the aluminum strut side skin, and
corrosion resistant steel (CRES) outer
spring beam support fitting. This AD
requires inspections, related
investigative and corrective actions, and
a fastener installation modification. We
are issuing this AD to address the unsafe
condition on these products.
SUMMARY:
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Federal Register / Vol. 82, No. 24 / Tuesday, February 7, 2017 / Rules and Regulations
This AD is effective March 14,
2017.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of March 14, 2017.
ADDRESSES: For service information
identified in this final rule, contact
Boeing Commercial Airplanes,
Attention: Contractual & Data Services
(C&DS), 2600 Westminster Blvd., MC
110–SK57, Seal Beach, CA 90740–5600;
telephone 562–797–1717; Internet
https://www.myboeingfleet.com. You
may view this referenced service
information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue
SW., Renton, WA. For information on
the availability of this material at the
FAA, call 425–227–1221. It is also
available on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2016–
7261.
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–2016–
7261; 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:
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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 747–200B, 747–300, 747–400,
747–400D, and 747–400F series
airplanes. The NPRM published in the
Federal Register on June 21, 2016 (81
FR 40205). The NPRM was prompted by
a report of cracking in both the
aluminum strut side skin, and corrosion
resistant steel (CRES) outer spring beam
support fitting. The NPRM proposed to
require repetitive high frequency eddy
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current (HFEC) inspections for cracking
in the strut side skin, an open-hole
HFEC inspection for cracking,
applicable related investigative and
corrective actions, and a fastener
installation modification. We are issuing
this AD to detect and correct cracking of
the strut side skin and spring beam
support fitting; such cracking could
result in the failure of the outer spring
beam support fitting, which could cause
separation of a strut and engine from the
airplane during flight.
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.
Requests To Include Additional
Clarification of Service Information
Boeing, Delta Airlines (DAL), and
KLM Royal Dutch Airlines (KLM)
requested that we revise paragraphs (g),
(h), and (i) of the proposed AD to
include Boeing Service Bulletin
Information Notice 747–54A2245 IN 02,
dated February 11, 2016; and Boeing
Service Bulletin Information Notice
747–54A2245 IN 03, dated May 13,
2016. The commenters all mentioned
that without the information contained
in the requested information notices, the
requirements of the proposed AD cannot
be fully accomplished.
We partially agree with the request to
revise paragraphs (g), (h), and (i) of this
AD to include new information that
clarifies how to accomplish the required
tasks specified in this AD. However,
there is new service information that
includes the same additional
information. We have revised this AD to
refer to Boeing Alert Service Bulletin
747–54A2245, Revision 1, dated
September 20, 2016, as the appropriate
source of service information to use for
the actions required by this AD. Boeing
Alert Service Bulletin 747–54A2245,
Revision 1, dated September 20, 2016,
includes additional information
discovered during validation of Boeing
Alert Service Bulletin 747–54A2245,
dated December 18, 2015. Boeing Alert
Service Bulletin 747–54A2245, Revision
1, dated September 20, 2016, clarifies
the procedures for the fastener removal,
drill ream, and spot facing steps, and
provides additional access instructions,
but does not include any new actions.
Additionally, we have added a new
paragraph (j) to this AD to give credit for
actions performed before the effective
date of this AD, using Boeing Alert
Service Bulletin 747–54A2245, dated
December 18, 2015. We have
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redesignated subsequent paragraphs
accordingly.
Request To Clarify the Unsafe
Condition Statement
Boeing requested that we revise the
unsafe condition statement by clarifying
the location of the cracking. Boeing
reported that cracking has been found
not only in the strut side skin, but also
in the spring beam support fitting.
We agree with the request to clarify
the unsafe condition statement. We have
revised the Discussion section of this
final rule, and paragraph (e) of this AD
accordingly. The unsafe condition
statement has been removed from the
SUMMARY section of this final rule.
Request To Revise the Costs of
Compliance
Boeing requested that we revise the
Costs of Compliance to reflect updated
work-hours to do the inspection. Boeing
specified that the hours necessary to do
the inspection were re-evaluated to be 4
work-hours, and the new information
was disclosed in Boeing Service
Bulletin Information Notice 747–
54A2245 IN 01, dated December 23,
2015.
We agree with the request, and have
revised the Costs of Compliance section
of this final rule to reflect the updated
work-hours.
Request To Revise Compliance Time for
Repetitive Inspections
KLM requested that we revise the
compliance time for the repetitive
inspections from 500 flight cycles to
1,250 flight cycles. KLM pointed out
that during the 747 Structures Task
Group meetings organized to support
strut modification, Boeing had
established a design goal to tolerate one
major load path failure and still meet
regulatory requirements with a longer
inspection interval. KLM also indicated
that the time required for the repetitive
inspections is a large burden.
We disagree with the request to revise
the compliance time for the repetitive
inspections. In 1993, the Model 747
Structures Task Group did not foresee
this level of damage occurring. Through
damage tolerance analysis, the original
equipment manufacturer (OEM) has
determined that 500 flight cycles is the
maximum number of flight cycles that
provides an acceptable level of safety,
and the FAA agrees with that analysis.
Additionally, as discussed previously,
the OEM has revised the time required
to do the repetitive inspections from 291
work-hours to 4 work-hours in the new
service information referenced
previously, reducing the burden to
operators. We have not revised the
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Federal Register / Vol. 82, No. 24 / Tuesday, February 7, 2017 / Rules and Regulations
compliance time for the repetitive
inspections; however, we have revised
this AD to refer to the new service
information referenced previously.
321U2400–5601, and 321U2400–5602
may be used for airplanes with General
Electric CF6–80 engines and PW4000
engines.
Request To Clarify How Certain Parts
May Be Used for Terminating Action
Conclusion
DAL requested clarification of the use
of certain parts (fillers) for the
terminating action required for all
airplanes. DAL pointed out that certain
parts are specifically named to include
the airplane engine model (CF6–80C2),
and that this could preclude the
terminating action or lead to a noncompliant installation for airplanes with
Pratt & Whitney (PW) 4000 engines
installed.
We agree with the request for
clarification because it should make this
AD easier to interpret. We have revised
paragraph (h) of this AD to specify that
part numbers 321U2400–5600,
We reviewed the relevant data,
considered the comments received, and
determined that air safety and the
public interest require adopting this AD
with the changes described previously
and minor editorial changes. We have
determined that these minor changes:
• Are consistent with the intent that
was proposed in the NPRM for
correcting the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM.
We also determined that these
changes will not increase the economic
burden on any operator or increase the
scope of this AD.
9491
Related Service Information Under 1
CFR Part 51
We reviewed Boeing Alert Service
Bulletin 747–54A2245, Revision 1,
dated September 20, 2016. The service
information describes procedures for
repetitive HFEC inspections for cracking
in the strut side skin, an open-hole
HFEC inspection for cracking,
applicable related investigative and
corrective actions, and a fastener
installation modification. This service
information is reasonably available
because the interested parties have
access to it through their normal course
of business or by the means identified
in the ADDRESSES section.
Costs of Compliance
We estimate that this AD affects 320
airplanes of U.S. registry. We estimate
the following costs to comply with this
AD:
ESTIMATED COSTS
Action
Labor cost
Inspection ...............................
4 work-hours × $85 per hour
= $340 per inspection cycle.
Up to 490 work-hours × $85
per hour = $41,650.
Modification ............................
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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.
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.
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18:06 Feb 06, 2017
Jkt 241001
Parts cost
Cost per product
$0
$340 per inspection cycle ......
56,414
Up to $98,064 ........................
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
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
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Cost on U.S. operators
Fmt 4700
Sfmt 4700
§ 39.13
$108,800 per inspection
cycle.
Up to $31,380,480.
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
2017–02–04 The Boeing Company:
Amendment 39–18783; Docket No.
FAA–2016–7261; Directorate Identifier
2016–NM–004–AD.
(a) Effective Date
This AD is effective March 14, 2017.
(b) Affected ADs
None.
(c) Applicability
This AD applies to The Boeing Company
Model 747–200B, 747–300, 747–400, 747–
400D, and 747–400F series airplanes,
certificated in any category, equipped with
General Electric (GE) CF6–80 series engines
or Pratt & Whitney PW4000 series engines; as
identified in Boeing Alert Service Bulletin
747–54A2245, Revision 1, dated September
20, 2016.
(d) Subject
Air Transport Association (ATA) of
America Code 54; Nacelles/pylons.
(e) Unsafe Condition
This AD was prompted by a report of
cracking in both the aluminum strut side
skin, and corrosion resistant steel (CRES)
outer spring beam support fitting. We are
issuing this AD to detect and correct cracking
of the strut side skin and spring beam
support fitting; such cracking could result in
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07FER1
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Federal Register / Vol. 82, No. 24 / Tuesday, February 7, 2017 / Rules and Regulations
the failure of the outer spring beam support
fitting, which could cause separation of a
strut and engine from the airplane during
flight.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Repetitive Inspections
Except as provided by paragraphs (i)(1) and
(i)(2) of this AD, at the applicable compliance
time specified in paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 747–54A2245, Revision 1, dated
September 20, 2016, do a surface high
frequency eddy current (HFEC) inspection for
cracking of the strut side skin, in accordance
with the Accomplishment Instructions of
Boeing Alert Service Bulletin 747–54A2245,
Revision 1, dated September 20, 2016, except
as required by paragraph (i)(3) of this AD.
Repeat the inspection thereafter at the
applicable times specified in paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 747–54A2245, Revision 1, dated
September 20, 2016, until the actions
required by paragraph (h) of this AD are
done. If any cracking is found, do the actions
specified in paragraph (h) of this AD before
further flight.
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(h) Terminating Actions
Within the applicable compliance time
specified in paragraph 1.E., ‘‘Compliance,’’ of
Boeing Alert Service Bulletin 747–54A2245,
Revision 1, dated September 20, 2016, except
as provided by paragraphs (i)(1) and (i)(2) of
this AD: Do a fastener hole open-hole HFEC
inspection for cracking, applicable related
investigative and corrective actions, and a
fastener installation modification, in
accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
747–54A2245, Revision 1, dated September
20, 2016, except as required by paragraph
(i)(3) of this AD. Do all applicable related
investigative and corrective actions before
further flight. Part numbers 321U2400–5600,
321U2400–5601, and 321U2400–5602 may be
used for modification of airplanes with GE
CF6–80 engines and PW4000 engines. Doing
the actions required by this paragraph
terminates the repetitive inspections required
by paragraph (g) of this AD.
(i) Exceptions to Service Information
(1) Where Boeing Alert Service Bulletin
747–54A2245, Revision 1, dated September
20, 2016, 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) The Condition column in table 1 and
table 2 of paragraph 1.E., ‘‘Compliance,’’ of
Boeing Alert Service Bulletin 747–54A2245,
Revision 1, dated September 20, 2016, refers
to total flight cycles ‘‘at the original issue
date of this service bulletin.’’ This AD,
however, applies to the airplanes with the
specified total flight cycles as of the effective
date of this AD.
(3) Although Boeing Alert Service Bulletin
747–54A2245, Revision 1, dated September
20, 2016, specifies to contact Boeing for
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18:06 Feb 06, 2017
Jkt 241001
repair instructions, and specifies that action
as ‘‘RC’’ (Required for Compliance), this AD
requires repair before further flight using a
method approved in accordance with the
procedures specified in paragraph (k) of this
AD.
(j) Credit for Previous Actions
This paragraph provides credit for the
actions specified in paragraphs (g) and (h) of
this AD, if those actions were performed
before the effective date of this AD, using
Boeing Alert Service Bulletin 747–54A2245,
dated December 18, 2015.
(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)(1) 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 (i)(3)
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. 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
(1) For more information about this AD,
contact Bill Ashforth, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA, Seattle
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
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Fmt 4700
Sfmt 4700
available at the addresses specified in
paragraphs (m)(3) and (m)(4) of this AD.
(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 747–
54A2245, Revision 1, dated September 20,
2016.
(ii) Reserved.
(3) For Boeing service information
identified in this AD, contact Boeing
Commercial Airplanes, Attention:
Contractual & Data Services (C&DS), 2600
Westminster Blvd., MC 110–SK57, Seal
Beach, CA 90740–5600; telephone 562–797–
1717; Internet https://
www.myboeingfleet.com.
(4) You may view this service information
at the FAA, Transport Airplane Directorate,
1601 Lind Avenue SW., Renton, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on January
12, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2017–01341 Filed 2–6–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–8186; Directorate
Identifier 2016–NM–074–AD; Amendment
39–18784; AD 2017–02–05]
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 all The
Boeing Company Model 737–100, –200,
–200C, –300, –400, and –500 series
airplanes. This AD was prompted by
reports of skin cracking found at the
corners of the aft entry and aft galley
doorways. This AD requires repetitive
inspections for cracking of the fuselage
SUMMARY:
E:\FR\FM\07FER1.SGM
07FER1
Agencies
[Federal Register Volume 82, Number 24 (Tuesday, February 7, 2017)]
[Rules and Regulations]
[Pages 9489-9492]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-01341]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2016-7261; Directorate Identifier 2016-NM-004-AD;
Amendment 39-18783; AD 2017-02-04]
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 747-200B, 747-300, 747-400, 747-400D, and 747-
400F series airplanes. This AD was prompted by a report of cracking in
both the aluminum strut side skin, and corrosion resistant steel (CRES)
outer spring beam support fitting. This AD requires inspections,
related investigative and corrective actions, and a fastener
installation modification. We are issuing this AD to address the unsafe
condition on these products.
[[Page 9490]]
DATES: This AD is effective March 14, 2017.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of March 14,
2017.
ADDRESSES: For service information identified in this final rule,
contact Boeing Commercial Airplanes, Attention: Contractual & Data
Services (C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA
90740-5600; telephone 562-797-1717; Internet https://www.myboeingfleet.com. You may view this referenced service information
at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW.,
Renton, WA. For information on the availability of this material at the
FAA, call 425-227-1221. It is also available on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2016-
7261.
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-
7261; 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 by adding an AD that would apply to certain The Boeing Company
Model 747-200B, 747-300, 747-400, 747-400D, and 747-400F series
airplanes. The NPRM published in the Federal Register on June 21, 2016
(81 FR 40205). The NPRM was prompted by a report of cracking in both
the aluminum strut side skin, and corrosion resistant steel (CRES)
outer spring beam support fitting. The NPRM proposed to require
repetitive high frequency eddy current (HFEC) inspections for cracking
in the strut side skin, an open-hole HFEC inspection for cracking,
applicable related investigative and corrective actions, and a fastener
installation modification. We are issuing this AD to detect and correct
cracking of the strut side skin and spring beam support fitting; such
cracking could result in the failure of the outer spring beam support
fitting, which could cause separation of a strut and engine from the
airplane during flight.
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.
Requests To Include Additional Clarification of Service Information
Boeing, Delta Airlines (DAL), and KLM Royal Dutch Airlines (KLM)
requested that we revise paragraphs (g), (h), and (i) of the proposed
AD to include Boeing Service Bulletin Information Notice 747-54A2245 IN
02, dated February 11, 2016; and Boeing Service Bulletin Information
Notice 747-54A2245 IN 03, dated May 13, 2016. The commenters all
mentioned that without the information contained in the requested
information notices, the requirements of the proposed AD cannot be
fully accomplished.
We partially agree with the request to revise paragraphs (g), (h),
and (i) of this AD to include new information that clarifies how to
accomplish the required tasks specified in this AD. However, there is
new service information that includes the same additional information.
We have revised this AD to refer to Boeing Alert Service Bulletin 747-
54A2245, Revision 1, dated September 20, 2016, as the appropriate
source of service information to use for the actions required by this
AD. Boeing Alert Service Bulletin 747-54A2245, Revision 1, dated
September 20, 2016, includes additional information discovered during
validation of Boeing Alert Service Bulletin 747-54A2245, dated December
18, 2015. Boeing Alert Service Bulletin 747-54A2245, Revision 1, dated
September 20, 2016, clarifies the procedures for the fastener removal,
drill ream, and spot facing steps, and provides additional access
instructions, but does not include any new actions. Additionally, we
have added a new paragraph (j) to this AD to give credit for actions
performed before the effective date of this AD, using Boeing Alert
Service Bulletin 747-54A2245, dated December 18, 2015. We have
redesignated subsequent paragraphs accordingly.
Request To Clarify the Unsafe Condition Statement
Boeing requested that we revise the unsafe condition statement by
clarifying the location of the cracking. Boeing reported that cracking
has been found not only in the strut side skin, but also in the spring
beam support fitting.
We agree with the request to clarify the unsafe condition
statement. We have revised the Discussion section of this final rule,
and paragraph (e) of this AD accordingly. The unsafe condition
statement has been removed from the SUMMARY section of this final rule.
Request To Revise the Costs of Compliance
Boeing requested that we revise the Costs of Compliance to reflect
updated work-hours to do the inspection. Boeing specified that the
hours necessary to do the inspection were re-evaluated to be 4 work-
hours, and the new information was disclosed in Boeing Service Bulletin
Information Notice 747-54A2245 IN 01, dated December 23, 2015.
We agree with the request, and have revised the Costs of Compliance
section of this final rule to reflect the updated work-hours.
Request To Revise Compliance Time for Repetitive Inspections
KLM requested that we revise the compliance time for the repetitive
inspections from 500 flight cycles to 1,250 flight cycles. KLM pointed
out that during the 747 Structures Task Group meetings organized to
support strut modification, Boeing had established a design goal to
tolerate one major load path failure and still meet regulatory
requirements with a longer inspection interval. KLM also indicated that
the time required for the repetitive inspections is a large burden.
We disagree with the request to revise the compliance time for the
repetitive inspections. In 1993, the Model 747 Structures Task Group
did not foresee this level of damage occurring. Through damage
tolerance analysis, the original equipment manufacturer (OEM) has
determined that 500 flight cycles is the maximum number of flight
cycles that provides an acceptable level of safety, and the FAA agrees
with that analysis. Additionally, as discussed previously, the OEM has
revised the time required to do the repetitive inspections from 291
work-hours to 4 work-hours in the new service information referenced
previously, reducing the burden to operators. We have not revised the
[[Page 9491]]
compliance time for the repetitive inspections; however, we have
revised this AD to refer to the new service information referenced
previously.
Request To Clarify How Certain Parts May Be Used for Terminating Action
DAL requested clarification of the use of certain parts (fillers)
for the terminating action required for all airplanes. DAL pointed out
that certain parts are specifically named to include the airplane
engine model (CF6-80C2), and that this could preclude the terminating
action or lead to a non-compliant installation for airplanes with Pratt
& Whitney (PW) 4000 engines installed.
We agree with the request for clarification because it should make
this AD easier to interpret. We have revised paragraph (h) of this AD
to specify that part numbers 321U2400-5600, 321U2400-5601, and
321U2400-5602 may be used for airplanes with General Electric CF6-80
engines and PW4000 engines.
Conclusion
We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
this AD with the changes described previously and minor editorial
changes. We have determined that these minor changes:
Are consistent with the intent that was proposed in the
NPRM for correcting the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM.
We also determined that these changes will not increase the
economic burden on any operator or increase the scope of this AD.
Related Service Information Under 1 CFR Part 51
We reviewed Boeing Alert Service Bulletin 747-54A2245, Revision 1,
dated September 20, 2016. The service information describes procedures
for repetitive HFEC inspections for cracking in the strut side skin, an
open-hole HFEC inspection for cracking, applicable related
investigative and corrective actions, and a fastener installation
modification. This service information is reasonably available because
the interested parties have access to it through their normal course of
business or by the means identified in the ADDRESSES section.
Costs of Compliance
We estimate that this AD affects 320 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
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Inspection....................... 4 work-hours x $85 $0 $340 per inspection $108,800 per
per hour = $340 cycle. inspection cycle.
per inspection
cycle.
Modification..................... Up to 490 work- 56,414 Up to $98,064...... Up to $31,380,480.
hours x $85 per
hour = $41,650.
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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.
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):
2017-02-04 The Boeing Company: Amendment 39-18783; Docket No. FAA-
2016-7261; Directorate Identifier 2016-NM-004-AD.
(a) Effective Date
This AD is effective March 14, 2017.
(b) Affected ADs
None.
(c) Applicability
This AD applies to The Boeing Company Model 747-200B, 747-300,
747-400, 747-400D, and 747-400F series airplanes, certificated in
any category, equipped with General Electric (GE) CF6-80 series
engines or Pratt & Whitney PW4000 series engines; as identified in
Boeing Alert Service Bulletin 747-54A2245, Revision 1, dated
September 20, 2016.
(d) Subject
Air Transport Association (ATA) of America Code 54; Nacelles/
pylons.
(e) Unsafe Condition
This AD was prompted by a report of cracking in both the
aluminum strut side skin, and corrosion resistant steel (CRES) outer
spring beam support fitting. We are issuing this AD to detect and
correct cracking of the strut side skin and spring beam support
fitting; such cracking could result in
[[Page 9492]]
the failure of the outer spring beam support fitting, which could
cause separation of a strut and engine from the airplane during
flight.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Repetitive Inspections
Except as provided by paragraphs (i)(1) and (i)(2) of this AD,
at the applicable compliance time specified in paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 747-54A2245,
Revision 1, dated September 20, 2016, do a surface high frequency
eddy current (HFEC) inspection for cracking of the strut side skin,
in accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 747-54A2245, Revision 1, dated September 20, 2016,
except as required by paragraph (i)(3) of this AD. Repeat the
inspection thereafter at the applicable times specified in paragraph
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-54A2245,
Revision 1, dated September 20, 2016, until the actions required by
paragraph (h) of this AD are done. If any cracking is found, do the
actions specified in paragraph (h) of this AD before further flight.
(h) Terminating Actions
Within the applicable compliance time specified in paragraph
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-54A2245,
Revision 1, dated September 20, 2016, except as provided by
paragraphs (i)(1) and (i)(2) of this AD: Do a fastener hole open-
hole HFEC inspection for cracking, applicable related investigative
and corrective actions, and a fastener installation modification, in
accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 747-54A2245, Revision 1, dated September 20, 2016,
except as required by paragraph (i)(3) of this AD. Do all applicable
related investigative and corrective actions before further flight.
Part numbers 321U2400-5600, 321U2400-5601, and 321U2400-5602 may be
used for modification of airplanes with GE CF6-80 engines and PW4000
engines. Doing the actions required by this paragraph terminates the
repetitive inspections required by paragraph (g) of this AD.
(i) Exceptions to Service Information
(1) Where Boeing Alert Service Bulletin 747-54A2245, Revision 1,
dated September 20, 2016, 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) The Condition column in table 1 and table 2 of paragraph
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-54A2245,
Revision 1, dated September 20, 2016, refers to total flight cycles
``at the original issue date of this service bulletin.'' This AD,
however, applies to the airplanes with the specified total flight
cycles as of the effective date of this AD.
(3) Although Boeing Alert Service Bulletin 747-54A2245, Revision
1, dated September 20, 2016, specifies to contact Boeing for repair
instructions, and specifies that action as ``RC'' (Required for
Compliance), this AD requires repair before further flight using a
method approved in accordance with the procedures specified in
paragraph (k) of this AD.
(j) Credit for Previous Actions
This paragraph provides credit for the actions specified in
paragraphs (g) and (h) of this AD, if those actions were performed
before the effective date of this AD, using Boeing Alert Service
Bulletin 747-54A2245, dated December 18, 2015.
(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)(1) 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 (i)(3) 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. 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
(1) For more information about this AD, contact Bill Ashforth,
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle 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 (m)(3) and (m)(4) of this AD.
(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 747-54A2245, Revision 1, dated
September 20, 2016.
(ii) Reserved.
(3) For Boeing service information identified in this AD,
contact Boeing Commercial Airplanes, Attention: Contractual & Data
Services (C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA
90740-5600; telephone 562-797-1717; Internet https://www.myboeingfleet.com.
(4) You may view this service information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For
information on the availability of this material at the FAA, call
425-227-1221.
(5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on January 12, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2017-01341 Filed 2-6-17; 8:45 am]
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