Airworthiness Directives; The Boeing Company Airplanes, 80242-80247 [2015-30881]
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80242
Federal Register / Vol. 80, No. 247 / Thursday, December 24, 2015 / Rules and Regulations
modification Number 55128S18242; or P/N
F2511373420000, post-modification Number
55128S18242) of the cockpit instrument
panel does not constitute terminating action
for the repetitive inspections required by
paragraph (g) of this AD.
(ii) If, during the inspection required by
paragraph (h)(2) of this AD, any cracking is
found in bracket No. 7 of the cockpit
instrument panel: Although Airbus Service
Bulletin A330–25–3538, Revision 02, dated
April 24, 2014; and Airbus Service Bulletin
A340–25–4351, Revision 01, dated January
31, 2014; specify to contact Airbus for repair
instructions, and specify that action as ‘‘RC’’
(Required for Compliance), repair the
cracking before further flight using a repair
method approved by the Manager,
International Branch, ANM–116, Transport
Airplane Directorate, FAA; or the European
Aviation Safety Agency (EASA); or Airbus’s
EASA Design Organization Approval (DOA).
(i) Optional Terminating Modification for
Paragraph (g) of This AD
Modifying an airplane by replacing bracket
No. 6 of the cockpit instrument panel with
a new, reinforced bracket, in accordance with
the Accomplishment Instructions of Airbus
Service Bulletin A330–25–3548, dated
October 31, 2013; or Airbus Service Bulletin
A340–25–4354, dated October 31, 2013; as
applicable; terminates the repetitive
inspections required by paragraph (g) of this
AD.
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(j) Credit for Previous Actions
This paragraph provides credit for actions
required by paragraphs (g) and (h) of this AD,
if those actions were performed before the
effective date of this AD using the service
information identified in paragraph (j)(1),
(j)(2), or (j)(3) of this AD, which is not
incorporated by reference in this AD.
(1) Airbus Service Bulletin A330–25–3538,
dated September 10, 2013.
(2) Airbus Service Bulletin A330–25–3538,
Revision 01, dated April 24, 2014.
(3) Airbus Service Bulletin A340–25–4351,
dated September 10, 2014.
(k) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane
Directorate, 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 International Branch, send it to ATTN:
Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone 425–227–1138; fax 425–227–1149.
Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov. 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
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district office. The AMOC approval letter
must specifically reference this AD.
(2) Contacting the Manufacturer: For any
requirement in this AD to obtain corrective
actions from a manufacturer, the action must
be accomplished using a method approved
by the Manager, International Branch, ANM–
116, Transport Airplane Directorate, FAA; or
the EASA; or Airbus’s EASA DOA. If
approved by the DOA, the approval must
include the DOA-authorized signature.
(3) Required for Compliance (RC): Except
as required by paragraph (h)(2)(ii) of this AD,
if Airbus Service Bulletin A330–25–3538,
Revision 02, dated April 24, 2014; or Airbus
Service Bulletin A340–25–4351, Revision 01,
dated January 31, 2014; contain procedures
or tests that are identified as RC, those
procedures and tests must be done to comply
with this AD; any procedures and tests that
are not identified as RC are recommended.
Those procedures and tests that are not
identified as RC may be deviated from, using
accepted methods in accordance with the
operators maintenance or inspection program
without obtaining approval of an AMOC,
provided the procedures and tests identified
as RC can be done and the airplane can be
put back in an airworthy condition. Any
substitutions or changes to procedures or
tests identified as RC require approval of an
AMOC.
(l) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2014–0127, dated
May 15, 2014, for related information. This
MCAI may be found in the AD docket on the
Internet at https://www.regulations.gov/
#!documentDetail;D=FAA-2015-0083-0002.
(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 this AD specifies otherwise.
(i) Airbus Service Bulletin A330–25–3538,
Revision 02, dated April 24, 2014.
(ii) Airbus Service Bulletin A330–25–3548,
dated October 31, 2013.
(iii) Airbus Service Bulletin A340–25–
4351, Revision 01, dated January 31, 2014.
(iv) Airbus Service Bulletin A340–25–
4354, dated October 31, 2013.
(3) For service information identified in
this AD, contact Airbus SAS, Airworthiness
Office—EAL, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33
5 61 93 36 96; fax +33 5 61 93 45 80; email
airworthiness.A330-A340@airbus.com;
Internet https://www.airbus.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
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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
December 9, 2015.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2015–31714 Filed 12–23–15; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–0828; Directorate
Identifier 2014–NM–146–AD; Amendment
39–18341; AD 2015–25–03]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are superseding
Airworthiness Directive (AD) 2013–23–
03, which applies to certain The Boeing
Company Model 747–100, 747–100B,
747–100B SUD, 747–200B, 747–200C,
747–200F, 747–300, 747–400, 747–
400D, 747–400F, and 747SR series
airplanes. AD 2013–23–03 required a
detailed inspection of certain attach
fittings for a cylindrical defect, and
replacement if necessary. For certain
airplanes, this new AD requires new
inspections of the inboard actuator
attach fittings for machining defects,
and overhaul or replacement if
necessary. This new AD also limits the
compliance time for doing the
replacement for certain other airplanes.
This AD was prompted by a report that
a machining defect was also found on
some of the actuator assemblies
inspected during manufacture. This
defect could lead to fatigue cracking and
subsequent fracture. We are issuing this
AD to detect and correct defective
inboard actuator attach fittings which,
combined with loss of the outboard
actuator load path, could result in
uncontrolled retraction of the outboard
flap, damage to flight control systems,
and consequent reduced controllability
of the airplane.
DATES: This AD is effective January 28,
2016.
The Director of the Federal Register
approved the incorporation by reference
SUMMARY:
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Federal Register / Vol. 80, No. 247 / Thursday, December 24, 2015 / Rules and Regulations
of a certain publication listed in this AD
as of January 28, 2016.
The Director of the Federal Register
approved the incorporation by reference
of a certain other publication listed in
this AD as of November 29, 2013 (78 FR
68345, November 14, 2013).
ADDRESSES: 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. 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–
0828.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.govby searching for
and locating Docket No. FAA–2015–
0828; 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:
Nathan Weigand, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue SW., Renton, WA
98057–3356; phone: 425–917–6428; fax:
425–917–6590; email:
nathan.p.weigand@faa.gov.
SUPPLEMENTARY INFORMATION:
20178). The NPRM was prompted by a
report that a machining defect was also
found on some of the actuator
assemblies inspected during
manufacture. The NPRM proposed to
continue to require doing a detailed
inspection of certain attach fittings for a
cylindrical defect and replacing if
necessary. This defect could lead to
fatigue cracking and subsequent
fracture. For certain airplanes, the
NPRM proposed to mandate new
inspections of the inboard actuator
attach fittings for machining defects,
and overhaul or replacement, if
necessary. The NPRM also proposed to
limit the compliance time for doing the
replacement for certain other airplanes.
We are issuing this AD to detect and
correct defective inboard actuator attach
fittings which, combined with loss of
the outboard actuator load path, could
result in uncontrolled retraction of the
outboard flap, damage to flight control
systems, and consequent reduced
controllability 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 (80 FR 20178,
April 15, 2015) and the FAA’s response
to each comment.
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Discussion
Request to Add Terminating Action
Boeing asked that we revise the
NPRM (80 FR 20178, April 15, 2015) to
specify that no additional action is
required for a wall thickness of 0.140
inch or greater with no machining
defect present, as also provided in Table
1 of Boeing Alert Service Bulletin 747–
57A2443, Revision 1, dated June 23,
2014.
We agree with the commenter that no
additional action is required for a wall
thickness of 0.140 inch or greater with
no machining defect present. However,
we do not agree with the request to
revise the AD because if this condition
exists, no action is required by this AD.
Only actions that are required to address
the identified unsafe condition are
specified in this AD. We have made no
change to the AD in this regard.
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2013–23–03,
Amendment 39–17658 (78 FR 68345,
November 14, 2013). AD 2013–23–03
applied to certain The Boeing Company
Model 747–100, 747–100B, 747–100B
SUD, 747–200B, 747–200C, 747–200F,
747–300, 747–400, 747–400D, 747–
400F, and 747SR series airplanes. The
NPRM published in the Federal
Register on April 15, 2015 (80 FR
Request to Revise Certain Requirements
Paragraph (k) of the proposed AD (80
FR 20178, April 15, 2015) would have
affected certain inboard actuator attach
fittings that were inspected using
Boeing Alert Service Bulletin 747–
57A2443, dated September 12, 2013.
United Airlines (UAL) requested that we
remove this inspection criterion. UAL
noted that there was no requirement to
identify the actuators; therefore,
operators would not be likely to
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80243
positively identify them. UAL added
that actuators are not likely to be
tracked in position, and could have
been moved between airplanes as a
result of maintenance. UAL also stated
that, in general, it would be better if the
AD as a whole was worded not to
depend on a record of previous
inspection accomplishment, but rather
on parts identification.
We acknowledge the commenter’s
concerns. We realize that paragraph (k)
of this AD is predicated on the fact that
operators kept records from the
inspection specified in Boeing Alert
Service Bulletin 747–57A2443, dated
September 12, 2013. The intent of this
AD is to either replace inboard actuator
attach fittings having part number (P/N)
65B08564–7, or to inspect P/N
65B08564–7 for cylindrical defects,
machining defects, and wall thickness,
and accomplish applicable corrective
actions. For that reason we have
changed the introductory text of
paragraph (k) of this AD so that it
applies to airplanes on which doing the
detailed inspection required by
paragraph (h)(1) of this AD was done
before the effective date of this AD and
a cylindrical defect was found but a
replacement was not done. We have also
revised paragraph (k)(1) of this AD to
require an ultrasonic inspection to
determine the minimum thickness or
mechanically determine the minimum
thickness and to allow a records review
for the inspections. This change ensures
all inspections are done on airplanes
with P/N 65B08564–7 that did not
replace P/N 65B08564–7 after
complying with AD 2013–23–03,
Amendment 39–17658 (78 FR 68345,
November 14, 2013).
To address airplanes on which
inboard actuator attach fittings were
replaced after complying with
paragraph (h)(1) of AD 2013–23–03,
Amendment 39–17658 (78 FR 68345,
November 14, 2013), we have added
new paragraph (m) to this AD, which
specifies that for airplanes on which the
detailed inspection required by
paragraph (h)(1) of this AD is done
before the effective date of this AD and
the inboard actuator attach fitting has
been replaced since that inspection, the
inspection to determine the part number
specified in paragraph (g) of this AD
must be done within 90 days after the
effective date of this AD, and the
applicable actions specified in
paragraphs (h), (i), and (j) of this AD
must be done within the applicable
times specified in paragraphs (h), (i),
and (j) of this AD. We have also added
a records review as an option if records
are available that can conclusively
determine the part number. We
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Federal Register / Vol. 80, No. 247 / Thursday, December 24, 2015 / Rules and Regulations
redesignated subsequent paragraphs
accordingly.
Request to Add Inspection
UAL stated that the actions specified
in paragraph (l) of the proposed AD (80
FR 20178, April 15, 2015) would also
depend on the record of findings from
inspections made in accordance with
AD 2013–23–03, Amendment 39–17658
(78 FR 68345, November 14, 2013). UAL
added that there was no AD requirement
to record these findings. UAL noted that
operators conducted the inspections and
took actions that were required. UAL
stated that it would be better to call out
a new inspection in the AD to determine
which condition the actuator is in, and
then take action as appropriate.
We acknowledge the commenter’s
concerns. We have revised paragraph (l)
of this AD to specify that no actuator
attach fitting having P/N 65B08564–7
may be installed on any airplane unless
the inspection specified in paragraph
(h)(1) of this AD is done prior to
installation and the applicable actions
specified in paragraphs (i) and (j) of this
AD are done within the applicable times
specified in paragraphs (i) and (j) of this
AD. We have also added a records
review as an option if records are
available that can conclusively
determine if the actions have been done.
Change to Paragraph (h)(2) of the
Proposed AD ((80 FR 20178, April 15,
2015)
We have revised paragraph (h)(2) of
this AD by referring to Boeing Alert
Service Bulletin 747–57A2443, Revision
1, dated June 23, 2014, as an appropriate
source of service information for
accomplishing the required actions.
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 (80 FR
20178, April 15, 2015) for correcting the
unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM (80 FR 20178,
April 15, 2015).
We also determined that this change
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 747–57A2443, dated September
12, 2013; and Boeing Alert Service
Bulletin 747–57A2443, Revision 1,
dated June 23, 2014. The service
information describes procedures for
new inspections of the inboard actuator
attach fittings for machining defects,
and overhaul or replacement, 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 184
airplanes of U.S. registry.
We estimate the following costs to
comply with this AD:
ESTIMATED COSTS
Cost per
product
Labor cost
Retained inspection for part number in AD
2013-23–03, Amendment 39-17658 (78 FR
68345, November 14, 2013).
New proposed inspections for machining defect.
Replacement for airplanes without any defect
7 work-hours × $85 per hour = $595 .............
$0
$595
$109,480
8 work-hours × $85 per hour = $680 .............
0
680
$125,120
6 work-hours × $85 per hour = $510 .............
13,720
14,230
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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
17:12 Dec 23, 2015
Jkt 238001
$14,230 per
airplane
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.
We have received no definitive data
that would enable us to provide a cost
estimate for the on-condition actions
specified in this AD.
VerDate Sep<11>2014
Parts cost
Cost on U.S.
operators
Action
(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.
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
List of Subjects in 14 CFR Part 39
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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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Federal Register / Vol. 80, No. 247 / Thursday, December 24, 2015 / Rules and Regulations
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Airworthiness Directive (AD)
2013–23–03, Amendment 39–17658 (78
FR 68345, November 14, 2013), and
adding the following new AD:
■
2015–25–03 The Boeing Company:
Amendment 39–18341; Docket No.
FAA–2015–0828; Directorate Identifier
2014–NM–146–AD.
(a) Effective Date
This AD is effective January 28, 2016.
(b) Affected ADs
This AD replaces AD 2013–23–03,
Amendment 39–17658 (78 FR 68345,
November 14, 2013).
(c) Applicability
This AD applies to The Boeing Company
Model 747–100, 747–100B, 747–100B SUD,
747–200B, 747–200C, 747–200F, 747–300,
747–400, 747–400D, 747–400F, and 747SR
series airplanes, certificated in any category,
as identified in Boeing Alert Service Bulletin
747–57A2443, Revision 1, dated June 23,
2014.
(d) Subject
Air Transport Association (ATA) of
America Code 57, Wings.
(e) Unsafe Condition
This AD was prompted by a report of the
fracture of an inboard actuator attach fitting
of the outboard flap. An inspection of the
attach fitting revealed that it was incorrectly
machined with a cylindrical profile instead
of a conical profile, resulting in reduced wall
thickness. A machining defect was also
found on some actuator assemblies inspected
during manufacture at the point where the
tapered machining transitioned to the
hemispherical machining at the top of the
inner surface. This defect could lead to
fatigue cracking and subsequent fracture. We
are issuing this AD to detect and correct
defective inboard actuator attach fittings
which, combined with loss of the outboard
actuator load path, could result in
uncontrolled retraction of the outboard flap,
damage to flight control systems, and
consequent reduced controllability of the
airplane.
tkelley on DSK3SPTVN1PROD with RULES
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Retained Part Number Inspection With
Revised Service Information
This paragraph restates the requirements of
paragraph (g) of AD 2013–23–03,
Amendment 39–17658 (78 FR 68345,
November 14, 2013), with revised service
information. Within 90 days after November
29, 2013 (the effective date of AD 2013–23–
03): Inspect to determine the part number of
the inboard actuator attach fittings of the
outboard flaps, in accordance with Part 1 of
the Accomplishment Instructions of Boeing
Alert Service Bulletin 747–57A2443, dated
September 12, 2013; or Boeing Alert Service
Bulletin 747–57A2443, Revision 1, dated
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17:12 Dec 23, 2015
Jkt 238001
June 23, 2014. As of the effective date of this
AD, only Boeing Alert Service Bulletin 747–
57A2443, Revision 1, dated June 23, 2014,
may be used.
(h) Retained Actions for Certain Attach
Fittings With Revised Service Information
This paragraph restates the requirements of
paragraph (h) of AD 2013–23–03,
Amendment 39–17658 (78 FR 68345,
November 14, 2013), with revised service
information. If, during the inspection
required by paragraph (g) of this AD, any
inboard actuator attach fitting having part
number (P/N) 65B08564–7 is found, before
further flight, do the actions specified in
paragraph (h)(1) or (h)(2) of this AD.
(1) Do a detailed inspection of the inboard
actuator attach fitting for a cylindrical defect,
in accordance with Part 2 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–57A2443, dated
September 12, 2013; or Boeing Alert Service
Bulletin 747–57A2443, Revision 1, dated
June 23, 2014. As of the effective date of this
AD, only Boeing Alert Service Bulletin 747–
57A2443, Revision 1, dated June 23, 2014,
may be used. For airplanes on which the
detailed inspection is done before the
effective date of this AD: If any cylindrical
defect is found, before further flight, do the
actions specified in paragraph (h)(1)(i) or
(h)(1)(ii) of this AD.
(i) Do a minimum thickness inspection of
the inboard actuator attach fitting to
determine minimum wall thickness of the
actuator fitting assembly, in accordance with
Part 3 of the Accomplishment Instructions of
Boeing Alert Service Bulletin 747–57A2443,
dated September 12, 2013; or Boeing Alert
Service Bulletin 747–57A2443, Revision 1,
dated June 23, 2014. If the minimum
thickness of the wall is less than 0.130 inch:
Before further flight, replace the inboard
actuator attach fitting of the outboard flap, in
accordance with Part 4 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–57A2443, dated
September 12, 2013.
(ii) Replace the inboard actuator attach
fitting of the outboard flap, in accordance
with Part 4 of the Accomplishment
Instructions of Boeing Alert Service Bulletin
747–57A2443, dated September 12, 2013.
(2) Replace the inboard actuator attach
fitting of the outboard flap, in accordance
with Part 4 of the Accomplishment
Instructions of Boeing Alert Service Bulletin
747–57A2443, dated September 12, 2013; or
Boeing Alert Service Bulletin 747–57A2443,
Revision 1, dated June 23, 2014. As of the
effective date of this AD, only Boeing Alert
Service Bulletin 747–57A2443, Revision 1,
dated June 23, 2014, may be used.
(i) New Actions for Certain Airplanes on
Which Any Cylindrical Defect Is Found
For airplanes on which the detailed
inspection required by paragraph (h)(1) of
this AD is done on or after the effective date
of this AD: If any cylindrical defect is found
during any inspection required by paragraph
(h)(1) of this AD, before further flight, do the
actions specified in paragraph (i)(1) or (i)(2)
of this AD.
(1) Determine the minimum wall thickness
of the actuator attach fitting either by doing
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80245
an ultrasonic inspection or by mechanically
measuring the thickness and do a detailed
inspection of the inner conical section to
determine if the machining defect is present,
in accordance with Part 3 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–57A2443, Revision 1,
dated June 23, 2014.
(i) If the minimum thickness of the wall is
less than 0.130 inch: Before further flight,
replace the inboard actuator attach fitting of
the outboard flap, in accordance with Part 4
of the Accomplishment Instructions of
Boeing Alert Service Bulletin 747–57A2443,
Revision 1, dated June 23, 2014.
(ii) If the minimum thickness of the wall
is 0.140 inch or greater and the machining
defect is present, before further flight, do the
actions specified in paragraph (i)(1)(ii)(A) or
(i)(1)(ii)(B) of this AD.
(A) Overhaul the inboard actuator attach
fitting of the outboard flap, in accordance
with Part 5 of the Accomplishment
Instructions of Boeing Alert Service Bulletin
747–57A2443, Revision 1, dated June 23,
2014.
(B) Replace the inboard actuator attach
fitting of the outboard flap, in accordance
with Part 4 of the Accomplishment
Instructions of Boeing Alert Service Bulletin
747–57A2443, Revision 1, dated June 23,
2014.
(iii) If the minimum thickness of the wall
is 0.130 inch or greater and less than 0.140
inch and the machining defect is not present,
within 48 months or 3,000 flight cycles after
the effective date of this AD, whichever
occurs first, replace the inboard actuator
attach fitting of the outboard flap, in
accordance with Part 4 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–57A2443, Revision 1,
dated June 23, 2014.
(iv) If the minimum thickness of the wall
is 0.130 inch or greater and less than 0.140
inch and the machining defect is present,
before further flight, replace the inboard
actuator attach fitting of the outboard flap, in
accordance with Part 4 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–57A2443, Revision 1,
dated June 23, 2014.
(2) Replace the inboard actuator attach
fitting of the outboard flap, in accordance
with Part 4 of the Accomplishment
Instructions of Boeing Alert Service Bulletin
747–57A2443, Revision 1, dated June 23,
2014.
(j) New Actions for Airplanes on Which No
Cylindrical Defects Are Found
If no cylindrical defect is found during any
inspection required by paragraph (h)(1) of
this AD, within 24 months after the effective
date of this AD, do the actions specified in
paragraph (j)(1) or (j)(2) of this AD.
(1) Determine the minimum wall thickness
of the actuator attach fitting either by doing
an ultrasonic inspection or by mechanically
measuring the thickness and do a detailed
inspection of the inner conical section to
determine if the machining defect is present,
in accordance with Part 3 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–57A2443, Revision 1,
dated June 23, 2014.
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tkelley on DSK3SPTVN1PROD with RULES
(i) If the minimum thickness of the wall is
less than 0.130 inch: Before further flight,
replace the inboard actuator attach fitting of
the outboard flap, in accordance with Part 4
of the Accomplishment Instructions of
Boeing Alert Service Bulletin 747 57A2443,
Revision 1, dated June 23, 2014.
(ii) If the minimum thickness of the wall
is 0.140 inch or greater and the machining
defect is present, before further flight, do the
actions specified in paragraph (j)(1)(ii)(A) or
(j)(1)(ii)(B) of this AD.
(A) Overhaul the inboard actuator attach
fitting of the outboard flap, in accordance
with Part 5 of the Accomplishment
Instructions of Boeing Alert Service Bulletin
747–57A2443, Revision 1, dated June 23,
2014.
(B) Replace the inboard actuator attach
fitting of the outboard flap, in accordance
with Part 4 of the Accomplishment
Instructions of Boeing Alert Service Bulletin
747–57A2443, Revision 1, dated June 23,
2014.
(iii) If the minimum thickness of the wall
is 0.130 inch or greater and less than 0.140
inch and the machining defect is not present,
within 48 months or 3,000 flight cycles after
the effective date of this AD, whichever
occurs first, replace the inboard actuator
attach fitting of the outboard flap, in
accordance with Part 4 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–57A2443, Revision 1,
dated June 23, 2014.
(iv) If the minimum thickness of the wall
is 0.130 inch or greater and less than 0.140
inch and the machining defect is present,
before further flight, replace the inboard
actuator attach fitting of the outboard flap, in
accordance with Part 4 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–57A2443, Revision 1,
dated June 23, 2014
(2) Replace the inboard actuator attach
fitting of the outboard flap, in accordance
with Part 4 of the Accomplishment
Instructions of Boeing Alert Service Bulletin
747–57A2443, Revision 1, dated June 23,
2014.
(k) New Inspection or Replacement for
Certain Fittings That Were Previously
Inspected
For airplanes on which the detailed
inspection required by paragraph (h)(1) of
this AD is done before the effective date of
this AD, except as required by paragraph (m)
of this AD: If any cylindrical defect is found
during any inspection required by paragraph
(h)(1) of this AD and the replacement of the
inboard actuator attach fitting of the outboard
flap was not done as specified in Part 4 of
the Accomplishment Instructions of Boeing
Alert Service Bulletin 747–57A2443, within
24 months after the effective date of this AD,
do the actions specified in paragraph (k)(1)
or (k)(2) of this AD.
(1) Do a detailed inspection of the inner
conical section for machining defects and do
an ultrasonic inspection to determine the
minimum thickness or mechanically
determine the minimum thickness, in
accordance with Part 3 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–57A2443, Revision 1,
VerDate Sep<11>2014
17:12 Dec 23, 2015
Jkt 238001
dated June 23, 2014. A review of airplane
maintenance records, if available, is
acceptable to determine the wall thickness
and to determine if there are machining
defects, provided wall thickness and
machining defects can be positively
determined from the records review.
(i) If any machining defect is found and the
minimum thickness of the wall is 0.140 inch
or greater: Before further flight, do the actions
specified in paragraph (k)(1)(i)(A) or
(k)(1)(i)(B) of this AD.
(A) Overhaul the inboard actuator attach
fitting of the outboard flap, in accordance
with Part 5 of the Accomplishment
Instructions of Boeing Alert Service Bulletin
747–57A2443, Revision 1, dated June 23,
2014.
(B) Replace the inboard actuator attach
fitting of the outboard flap, in accordance
with Part 4 of the Accomplishment
Instructions of Boeing Alert Service Bulletin
747–57A2443, Revision 1, dated June 23,
2014.
(ii) If any machining defect is found and
the minimum thickness of the wall is 0.130
inch or greater and less than 0.140 inch:
Before further flight, replace the inboard
actuator attach fitting of the outboard flap, in
accordance with Part 4 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–57A2443, Revision 1,
dated June 23, 2014.
(iii) If no machining defect is found and
the minimum thickness of the wall is 0.130
inch or greater and less than 0.140 inch:
Within 48 months or 3,000 flight cycles after
the effective date of this AD, whichever
occurs first, replace the inboard actuator
attach fitting of the outboard flap, in
accordance with Part 4 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–57A2443, Revision 1,
dated June 23, 2014.
(iv) If a machining defect is or is not found
and the minimum thickness of the wall is
less than 0.130 inch: Before further flight,
replace the inboard actuator attach fitting of
the outboard flap, in accordance with Part 4
of the Accomplishment Instructions of
Boeing Alert Service Bulletin 747–57A2443,
Revision 1, dated June 23, 2014.
(2) Replace the inboard actuator attach
fitting of the outboard flap, in accordance
with Part 4 of the Accomplishment
Instructions of Boeing Alert Service Bulletin
747–57A2443, Revision 1, dated June 23,
2014.
(l) Parts Installation Limitation
As of the effective date of this AD, no
actuator attach fitting having P/N 65B08564–
7 may be installed on any airplane unless the
inspection specified in paragraph (h)(1) of
this AD is done prior to installation and the
applicable actions specified in paragraphs (i)
and (j) of this AD are done within the
applicable times specified in paragraphs (i)
and (j) of this AD. A review of airplane
maintenance records, if available, is
acceptable to determine if the inspection and
applicable actions have been done, provided
the inspection and actions can be positively
determined from the records review.
PO 00000
Frm 00040
Fmt 4700
Sfmt 4700
(m) Action for Parts Installed After AD
2013–23–03, Amendment 39–17658 (78 FR
68345, November 14, 2013) Was
Accomplished
For airplanes on which the detailed
inspection required by paragraph (h)(1) of
this AD is done before the effective date of
this AD and the inboard actuator attach
fitting was replaced since that inspection:
Within 90 days after the effective date of this
AD, inspect to determine the part number of
the inboard actuator attach fittings of the
outboard flaps and, for inboard actuator
attach fittings having P/N 65B08564–7, do
the applicable actions specified in
paragraphs (h), (i), and (j) of this AD within
the applicable times specified in paragraphs
(h), (i), and (j) of this AD. A review of
airplane maintenance records, if available, is
acceptable to determine the part number,
provided the part number can be positively
determined from the records review.
(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) 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
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. For a repair
method to be approved, the repair must meet
the certification basis of the airplane, and the
approval must specifically refer to this AD.
(4) If any service information contains
steps that are identified as RC (Required for
Compliance), those steps must be done to
comply with this AD; any steps that are not
identified as RC are recommended. Those
steps that are not identified 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 steps
identified as RC can be done and the airplane
can be put back in an airworthy condition.
Any substitutions or changes to steps
identified as RC require approval of an
AMOC.
(5) AMOCs approved for AD 2013–23–03,
Amendment 39–17658 (78 FR 68345,
November 14, 2013) are approved as AMOCs
for the corresponding provisions of this AD.
(o) Related Information
For more information about this AD,
contact Nathan Weigand, Aerospace
E:\FR\FM\24DER1.SGM
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Federal Register / Vol. 80, No. 247 / Thursday, December 24, 2015 / Rules and Regulations
Engineer, Airframe Branch, ANM–120S,
FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue SW., Renton, WA 98057–
3356; phone: 425–917–6428; fax: 425–917–
6590; email: nathan.p.weigand@faa.gov.
(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.
(3) The following service information was
approved for IBR on January 28, 2016.
(i) Boeing Alert Service Bulletin 747–
57A2443, Revision 1, dated June 23, 2014.
(ii) Reserved.
(4) The following service information was
approved for IBR on November 29, 2013 (78
FR 68345, November 14, 2013).
(i) Boeing Alert Service Bulletin 747–
57A2443, dated September 12, 2013.
(ii) Reserved.
(5) 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.
(6) 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.
(7) 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 24, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane
Directorate,Aircraft Certification Service.
[FR Doc. 2015–30881 Filed 12–23–15; 8:45 am]
BILLING CODE 4910–13–P
COMMODITY FUTURES TRADING
COMMISSION
17 CFR Part 1
RIN 3038–AE23
Records of Commodity Interest and
Related Cash or Forward Transactions
Commodity Futures Trading
Commission.
ACTION: Final rule.
tkelley on DSK3SPTVN1PROD with RULES
AGENCY:
The Commodity Futures
Trading Commission (the
‘‘Commission’’ or ‘‘CFTC’’) is amending
Commission Regulation 1.35(a) to:
Provide that all records required to be
SUMMARY:
VerDate Sep<11>2014
17:12 Dec 23, 2015
Jkt 238001
maintained under this regulation must
be maintained in a form and manner
which permits prompt, accurate and
reliable location, access, and retrieval of
any particular record, data, or
information; clarify that all records,
except records of oral and written
communications leading to the
execution of a commodity interest
transaction and related cash or forward
transactions, must be kept in a form and
manner that allows for identification of
a particular transaction; exclude
members of designated contract markets
(‘‘DCMs’’) and of swap execution
facilities (‘‘SEFs’’) that are not registered
or required to register with the
Commission (‘‘Unregistered Members’’)
from the requirements to keep written
communications that lead to the
execution of a commodity interest
transaction and related cash or forward
transactions, keep text messages, and
keep records in a particular form and
manner; and exclude commodity
trading advisors (‘‘CTAs’’) from the oral
recordkeeping requirement (‘‘Final
Rule’’).
DATES: Effective December 24, 2015.
FOR FURTHER INFORMATION CONTACT:
Katherine Driscoll, Associate Chief
Counsel, (202) 418–5544, kdriscoll@
cftc.gov; August A. Imholtz III, Special
Counsel, (202) 418–5140, aimholtz@
cftc.gov; or Lauren Bennett, Special
Counsel, (202) 418–5290, lbennett@
cftc.gov, Division of Swap Dealer and
Intermediary Oversight, Commodity
Futures Trading Commission, 1155 21st
Street NW., Washington, DC 20581.
SUPPLEMENTARY INFORMATION:
I. Background
The Commission amended Regulation
1.35(a) in December 2012 as part of a
series of rulemakings intended to
integrate certain existing Commission
rules more fully with the framework
created by the Dodd-Frank Wall Street
Reform and Consumer Protection Act
for swap dealers and major swap
participants (the ‘‘2012 Amendment’’).1
Regulation 1.35(a) requires each
futures commission merchant (‘‘FCM’’),
retail foreign exchange dealer (‘‘RFED’’),
introducing broker (‘‘IB’’), and member
of a DCM or of a SEF to keep full,
complete, and systematic records of all
transactions relating to its business of
dealing in commodity interest and
related cash or forward transactions.2
The Commodity Exchange Act (‘‘CEA’’)
defines ‘‘member’’ as an individual,
1 See Adaptation of Regulations to Incorporate
Swaps—Records of Transactions, 77 FR 75523
(December 21, 2012) (‘‘2012 Amendment Adopting
Release’’).
2 17 CFR 1.35(a)(1).
PO 00000
Frm 00041
Fmt 4700
Sfmt 4700
80247
association, partnership, corporation, or
trust—(i) owning or holding
membership in, or admitted to
membership representation on, the
registered entity 3 or derivatives
transaction execution facility; or (ii)
having trading privileges on the
registered entity or derivatives
transaction execution facility.4
Regulation 1.35(a) requires FCMs,
RFEDs, IBs, and members of a DCM or
of a SEF to keep records of written
communications that lead to the
execution of a commodity interest
transaction and related cash or forward
transactions. Additionally, Regulation
1.35(a) includes a requirement to keep
records of certain oral communications,
which applies to each FCM, RFED, large
IB (defined as an IB that has generated
over $5 million in aggregate gross
revenues over the preceding three years
from its activities as an IB), and member
of a DCM or of a SEF that is registered
or required to register with the
Commission as a floor broker (‘‘FB’’)
(only with regard to acting as an agent
for a non-affiliated client) or as a CTA.5
Unlike the written recordkeeping
requirement that applies to both
commodity interest transactions and
related cash or forward transactions, the
oral recordkeeping requirement is
limited to commodity interest
transactions.6 The scope of records
covered by Regulation 1.35(a) includes
communications by telephone,
voicemail, facsimile, instant messaging,
chat rooms, electronic mail, mobile
device, or other digital or electronic
media.7 These communications include
text messages. Regulation 1.35(a) also
mandates that all records be kept in a
form and manner identifiable and
searchable by transaction.
3 The term ‘‘registered entity’’ is defined in CEA
section 1a(40) to include both DCMs and SEFs. See
CEA sections 1a(40)(A) (DCMs) and (D) (SEFs).
4 7 U.S.C. 1a(34).
5 As stated in the 2012 Amendment, the oral
recordkeeping requirement in Regulation 1.35(a)
does not apply to: (i) Oral communications that lead
solely to the execution of a related cash or forward
transaction; (ii) oral communications provided or
received by a floor broker that do not lead to the
purchase or sale for any person other than the floor
broker of any commodity for future delivery,
security futures product, swap, or commodity
option authorized under section 4c of the
Commodity Exchange Act; (iii) an introducing
broker that has generated over the preceding three
years $5 million or less in aggregate gross revenues
from its activities as an introducing broker; (iv) a
floor trader; (v) a commodity pool operator; (vi) a
swap dealer; (vii) a major swap participant; or (viii)
a member of a DCM or SEF that is not registered
or required to be registered with the Commission
in any capacity. 17 CFR 1.35(a)(1).
6 17 CFR 1.35(a)(1).
7 Id.
E:\FR\FM\24DER1.SGM
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]]>Agencies
[Federal Register Volume 80, Number 247 (Thursday, December 24, 2015)]
[Rules and Regulations]
[Pages 80242-80247]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-30881]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2015-0828; Directorate Identifier 2014-NM-146-AD;
Amendment 39-18341; AD 2015-25-03]
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) 2013-23-03,
which applies to certain The Boeing Company Model 747-100, 747-100B,
747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D,
747-400F, and 747SR series airplanes. AD 2013-23-03 required a detailed
inspection of certain attach fittings for a cylindrical defect, and
replacement if necessary. For certain airplanes, this new AD requires
new inspections of the inboard actuator attach fittings for machining
defects, and overhaul or replacement if necessary. This new AD also
limits the compliance time for doing the replacement for certain other
airplanes. This AD was prompted by a report that a machining defect was
also found on some of the actuator assemblies inspected during
manufacture. This defect could lead to fatigue cracking and subsequent
fracture. We are issuing this AD to detect and correct defective
inboard actuator attach fittings which, combined with loss of the
outboard actuator load path, could result in uncontrolled retraction of
the outboard flap, damage to flight control systems, and consequent
reduced controllability of the airplane.
DATES: This AD is effective January 28, 2016.
The Director of the Federal Register approved the incorporation by
reference
[[Page 80243]]
of a certain publication listed in this AD as of January 28, 2016.
The Director of the Federal Register approved the incorporation by
reference of a certain other publication listed in this AD as of
November 29, 2013 (78 FR 68345, November 14, 2013).
ADDRESSES: 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. 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-
0828.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.govby searching for and locating Docket No. FAA-2015-
0828; 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: Nathan Weigand, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6428; fax:
425-917-6590; email: nathan.p.weigand@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2013-23-03, Amendment 39-17658 (78 FR 68345,
November 14, 2013). AD 2013-23-03 applied to certain The Boeing Company
Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F,
747-300, 747-400, 747-400D, 747-400F, and 747SR series airplanes. The
NPRM published in the Federal Register on April 15, 2015 (80 FR 20178).
The NPRM was prompted by a report that a machining defect was also
found on some of the actuator assemblies inspected during manufacture.
The NPRM proposed to continue to require doing a detailed inspection of
certain attach fittings for a cylindrical defect and replacing if
necessary. This defect could lead to fatigue cracking and subsequent
fracture. For certain airplanes, the NPRM proposed to mandate new
inspections of the inboard actuator attach fittings for machining
defects, and overhaul or replacement, if necessary. The NPRM also
proposed to limit the compliance time for doing the replacement for
certain other airplanes. We are issuing this AD to detect and correct
defective inboard actuator attach fittings which, combined with loss of
the outboard actuator load path, could result in uncontrolled
retraction of the outboard flap, damage to flight control systems, and
consequent reduced controllability 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 (80
FR 20178, April 15, 2015) and the FAA's response to each comment.
Request to Add Terminating Action
Boeing asked that we revise the NPRM (80 FR 20178, April 15, 2015)
to specify that no additional action is required for a wall thickness
of 0.140 inch or greater with no machining defect present, as also
provided in Table 1 of Boeing Alert Service Bulletin 747-57A2443,
Revision 1, dated June 23, 2014.
We agree with the commenter that no additional action is required
for a wall thickness of 0.140 inch or greater with no machining defect
present. However, we do not agree with the request to revise the AD
because if this condition exists, no action is required by this AD.
Only actions that are required to address the identified unsafe
condition are specified in this AD. We have made no change to the AD in
this regard.
Request to Revise Certain Requirements
Paragraph (k) of the proposed AD (80 FR 20178, April 15, 2015)
would have affected certain inboard actuator attach fittings that were
inspected using Boeing Alert Service Bulletin 747-57A2443, dated
September 12, 2013. United Airlines (UAL) requested that we remove this
inspection criterion. UAL noted that there was no requirement to
identify the actuators; therefore, operators would not be likely to
positively identify them. UAL added that actuators are not likely to be
tracked in position, and could have been moved between airplanes as a
result of maintenance. UAL also stated that, in general, it would be
better if the AD as a whole was worded not to depend on a record of
previous inspection accomplishment, but rather on parts identification.
We acknowledge the commenter's concerns. We realize that paragraph
(k) of this AD is predicated on the fact that operators kept records
from the inspection specified in Boeing Alert Service Bulletin 747-
57A2443, dated September 12, 2013. The intent of this AD is to either
replace inboard actuator attach fittings having part number (P/N)
65B08564-7, or to inspect P/N 65B08564-7 for cylindrical defects,
machining defects, and wall thickness, and accomplish applicable
corrective actions. For that reason we have changed the introductory
text of paragraph (k) of this AD so that it applies to airplanes on
which doing the detailed inspection required by paragraph (h)(1) of
this AD was done before the effective date of this AD and a cylindrical
defect was found but a replacement was not done. We have also revised
paragraph (k)(1) of this AD to require an ultrasonic inspection to
determine the minimum thickness or mechanically determine the minimum
thickness and to allow a records review for the inspections. This
change ensures all inspections are done on airplanes with P/N 65B08564-
7 that did not replace P/N 65B08564-7 after complying with AD 2013-23-
03, Amendment 39-17658 (78 FR 68345, November 14, 2013).
To address airplanes on which inboard actuator attach fittings were
replaced after complying with paragraph (h)(1) of AD 2013-23-03,
Amendment 39-17658 (78 FR 68345, November 14, 2013), we have added new
paragraph (m) to this AD, which specifies that for airplanes on which
the detailed inspection required by paragraph (h)(1) of this AD is done
before the effective date of this AD and the inboard actuator attach
fitting has been replaced since that inspection, the inspection to
determine the part number specified in paragraph (g) of this AD must be
done within 90 days after the effective date of this AD, and the
applicable actions specified in paragraphs (h), (i), and (j) of this AD
must be done within the applicable times specified in paragraphs (h),
(i), and (j) of this AD. We have also added a records review as an
option if records are available that can conclusively determine the
part number. We
[[Page 80244]]
redesignated subsequent paragraphs accordingly.
Request to Add Inspection
UAL stated that the actions specified in paragraph (l) of the
proposed AD (80 FR 20178, April 15, 2015) would also depend on the
record of findings from inspections made in accordance with AD 2013-23-
03, Amendment 39-17658 (78 FR 68345, November 14, 2013). UAL added that
there was no AD requirement to record these findings. UAL noted that
operators conducted the inspections and took actions that were
required. UAL stated that it would be better to call out a new
inspection in the AD to determine which condition the actuator is in,
and then take action as appropriate.
We acknowledge the commenter's concerns. We have revised paragraph
(l) of this AD to specify that no actuator attach fitting having P/N
65B08564-7 may be installed on any airplane unless the inspection
specified in paragraph (h)(1) of this AD is done prior to installation
and the applicable actions specified in paragraphs (i) and (j) of this
AD are done within the applicable times specified in paragraphs (i) and
(j) of this AD. We have also added a records review as an option if
records are available that can conclusively determine if the actions
have been done.
Change to Paragraph (h)(2) of the Proposed AD ((80 FR 20178, April 15,
2015)
We have revised paragraph (h)(2) of this AD by referring to Boeing
Alert Service Bulletin 747-57A2443, Revision 1, dated June 23, 2014, as
an appropriate source of service information for accomplishing the
required actions.
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 (80 FR 20178, April 15, 2015) for correcting the unsafe condition;
and
Do not add any additional burden upon the public than was
already proposed in the NPRM (80 FR 20178, April 15, 2015).
We also determined that this change 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 747-57A2443, dated
September 12, 2013; and Boeing Alert Service Bulletin 747-57A2443,
Revision 1, dated June 23, 2014. The service information describes
procedures for new inspections of the inboard actuator attach fittings
for machining defects, and overhaul or replacement, 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 184 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product Cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
Retained inspection for part 7 work-hours x $85 $0 $595 $109,480
number in AD 2013[dash]23-03, per hour = $595.
Amendment 39[dash]17658 (78 FR
68345, November 14, 2013).
New proposed inspections for 8 work-hours x $85 0 680 $125,120
machining defect. per hour = $680.
Replacement for airplanes without 6 work-hours x $85 13,720 14,230 $14,230 per airplane
any defect. per hour = $510.
----------------------------------------------------------------------------------------------------------------
We have received no definitive data that would enable us to provide
a cost estimate for the on-condition actions specified in this AD.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
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.
[[Page 80245]]
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD)
2013-23-03, Amendment 39-17658 (78 FR 68345, November 14, 2013), and
adding the following new AD:
2015-25-03 The Boeing Company: Amendment 39-18341; Docket No. FAA-
2015-0828; Directorate Identifier 2014-NM-146-AD.
(a) Effective Date
This AD is effective January 28, 2016.
(b) Affected ADs
This AD replaces AD 2013-23-03, Amendment 39-17658 (78 FR 68345,
November 14, 2013).
(c) Applicability
This AD applies to The Boeing Company Model 747-100, 747-100B,
747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-
400D, 747-400F, and 747SR series airplanes, certificated in any
category, as identified in Boeing Alert Service Bulletin 747-
57A2443, Revision 1, dated June 23, 2014.
(d) Subject
Air Transport Association (ATA) of America Code 57, Wings.
(e) Unsafe Condition
This AD was prompted by a report of the fracture of an inboard
actuator attach fitting of the outboard flap. An inspection of the
attach fitting revealed that it was incorrectly machined with a
cylindrical profile instead of a conical profile, resulting in
reduced wall thickness. A machining defect was also found on some
actuator assemblies inspected during manufacture at the point where
the tapered machining transitioned to the hemispherical machining at
the top of the inner surface. This defect could lead to fatigue
cracking and subsequent fracture. We are issuing this AD to detect
and correct defective inboard actuator attach fittings which,
combined with loss of the outboard actuator load path, could result
in uncontrolled retraction of the outboard flap, damage to flight
control systems, and consequent reduced controllability of the
airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Part Number Inspection With Revised Service Information
This paragraph restates the requirements of paragraph (g) of AD
2013-23-03, Amendment 39-17658 (78 FR 68345, November 14, 2013),
with revised service information. Within 90 days after November 29,
2013 (the effective date of AD 2013-23-03): Inspect to determine the
part number of the inboard actuator attach fittings of the outboard
flaps, in accordance with Part 1 of the Accomplishment Instructions
of Boeing Alert Service Bulletin 747-57A2443, dated September 12,
2013; or Boeing Alert Service Bulletin 747-57A2443, Revision 1,
dated June 23, 2014. As of the effective date of this AD, only
Boeing Alert Service Bulletin 747-57A2443, Revision 1, dated June
23, 2014, may be used.
(h) Retained Actions for Certain Attach Fittings With Revised Service
Information
This paragraph restates the requirements of paragraph (h) of AD
2013-23-03, Amendment 39-17658 (78 FR 68345, November 14, 2013),
with revised service information. If, during the inspection required
by paragraph (g) of this AD, any inboard actuator attach fitting
having part number (P/N) 65B08564-7 is found, before further flight,
do the actions specified in paragraph (h)(1) or (h)(2) of this AD.
(1) Do a detailed inspection of the inboard actuator attach
fitting for a cylindrical defect, in accordance with Part 2 of the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
57A2443, dated September 12, 2013; or Boeing Alert Service Bulletin
747-57A2443, Revision 1, dated June 23, 2014. As of the effective
date of this AD, only Boeing Alert Service Bulletin 747-57A2443,
Revision 1, dated June 23, 2014, may be used. For airplanes on which
the detailed inspection is done before the effective date of this
AD: If any cylindrical defect is found, before further flight, do
the actions specified in paragraph (h)(1)(i) or (h)(1)(ii) of this
AD.
(i) Do a minimum thickness inspection of the inboard actuator
attach fitting to determine minimum wall thickness of the actuator
fitting assembly, in accordance with Part 3 of the Accomplishment
Instructions of Boeing Alert Service Bulletin 747-57A2443, dated
September 12, 2013; or Boeing Alert Service Bulletin 747-57A2443,
Revision 1, dated June 23, 2014. If the minimum thickness of the
wall is less than 0.130 inch: Before further flight, replace the
inboard actuator attach fitting of the outboard flap, in accordance
with Part 4 of the Accomplishment Instructions of Boeing Alert
Service Bulletin 747-57A2443, dated September 12, 2013.
(ii) Replace the inboard actuator attach fitting of the outboard
flap, in accordance with Part 4 of the Accomplishment Instructions
of Boeing Alert Service Bulletin 747-57A2443, dated September 12,
2013.
(2) Replace the inboard actuator attach fitting of the outboard
flap, in accordance with Part 4 of the Accomplishment Instructions
of Boeing Alert Service Bulletin 747-57A2443, dated September 12,
2013; or Boeing Alert Service Bulletin 747-57A2443, Revision 1,
dated June 23, 2014. As of the effective date of this AD, only
Boeing Alert Service Bulletin 747-57A2443, Revision 1, dated June
23, 2014, may be used.
(i) New Actions for Certain Airplanes on Which Any Cylindrical Defect
Is Found
For airplanes on which the detailed inspection required by
paragraph (h)(1) of this AD is done on or after the effective date
of this AD: If any cylindrical defect is found during any inspection
required by paragraph (h)(1) of this AD, before further flight, do
the actions specified in paragraph (i)(1) or (i)(2) of this AD.
(1) Determine the minimum wall thickness of the actuator attach
fitting either by doing an ultrasonic inspection or by mechanically
measuring the thickness and do a detailed inspection of the inner
conical section to determine if the machining defect is present, in
accordance with Part 3 of the Accomplishment Instructions of Boeing
Alert Service Bulletin 747-57A2443, Revision 1, dated June 23, 2014.
(i) If the minimum thickness of the wall is less than 0.130
inch: Before further flight, replace the inboard actuator attach
fitting of the outboard flap, in accordance with Part 4 of the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
57A2443, Revision 1, dated June 23, 2014.
(ii) If the minimum thickness of the wall is 0.140 inch or
greater and the machining defect is present, before further flight,
do the actions specified in paragraph (i)(1)(ii)(A) or (i)(1)(ii)(B)
of this AD.
(A) Overhaul the inboard actuator attach fitting of the outboard
flap, in accordance with Part 5 of the Accomplishment Instructions
of Boeing Alert Service Bulletin 747-57A2443, Revision 1, dated June
23, 2014.
(B) Replace the inboard actuator attach fitting of the outboard
flap, in accordance with Part 4 of the Accomplishment Instructions
of Boeing Alert Service Bulletin 747-57A2443, Revision 1, dated June
23, 2014.
(iii) If the minimum thickness of the wall is 0.130 inch or
greater and less than 0.140 inch and the machining defect is not
present, within 48 months or 3,000 flight cycles after the effective
date of this AD, whichever occurs first, replace the inboard
actuator attach fitting of the outboard flap, in accordance with
Part 4 of the Accomplishment Instructions of Boeing Alert Service
Bulletin 747-57A2443, Revision 1, dated June 23, 2014.
(iv) If the minimum thickness of the wall is 0.130 inch or
greater and less than 0.140 inch and the machining defect is
present, before further flight, replace the inboard actuator attach
fitting of the outboard flap, in accordance with Part 4 of the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
57A2443, Revision 1, dated June 23, 2014.
(2) Replace the inboard actuator attach fitting of the outboard
flap, in accordance with Part 4 of the Accomplishment Instructions
of Boeing Alert Service Bulletin 747-57A2443, Revision 1, dated June
23, 2014.
(j) New Actions for Airplanes on Which No Cylindrical Defects Are Found
If no cylindrical defect is found during any inspection required
by paragraph (h)(1) of this AD, within 24 months after the effective
date of this AD, do the actions specified in paragraph (j)(1) or
(j)(2) of this AD.
(1) Determine the minimum wall thickness of the actuator attach
fitting either by doing an ultrasonic inspection or by mechanically
measuring the thickness and do a detailed inspection of the inner
conical section to determine if the machining defect is present, in
accordance with Part 3 of the Accomplishment Instructions of Boeing
Alert Service Bulletin 747-57A2443, Revision 1, dated June 23, 2014.
[[Page 80246]]
(i) If the minimum thickness of the wall is less than 0.130
inch: Before further flight, replace the inboard actuator attach
fitting of the outboard flap, in accordance with Part 4 of the
Accomplishment Instructions of Boeing Alert Service Bulletin 747
57A2443, Revision 1, dated June 23, 2014.
(ii) If the minimum thickness of the wall is 0.140 inch or
greater and the machining defect is present, before further flight,
do the actions specified in paragraph (j)(1)(ii)(A) or (j)(1)(ii)(B)
of this AD.
(A) Overhaul the inboard actuator attach fitting of the outboard
flap, in accordance with Part 5 of the Accomplishment Instructions
of Boeing Alert Service Bulletin 747-57A2443, Revision 1, dated June
23, 2014.
(B) Replace the inboard actuator attach fitting of the outboard
flap, in accordance with Part 4 of the Accomplishment Instructions
of Boeing Alert Service Bulletin 747-57A2443, Revision 1, dated June
23, 2014.
(iii) If the minimum thickness of the wall is 0.130 inch or
greater and less than 0.140 inch and the machining defect is not
present, within 48 months or 3,000 flight cycles after the effective
date of this AD, whichever occurs first, replace the inboard
actuator attach fitting of the outboard flap, in accordance with
Part 4 of the Accomplishment Instructions of Boeing Alert Service
Bulletin 747-57A2443, Revision 1, dated June 23, 2014.
(iv) If the minimum thickness of the wall is 0.130 inch or
greater and less than 0.140 inch and the machining defect is
present, before further flight, replace the inboard actuator attach
fitting of the outboard flap, in accordance with Part 4 of the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
57A2443, Revision 1, dated June 23, 2014
(2) Replace the inboard actuator attach fitting of the outboard
flap, in accordance with Part 4 of the Accomplishment Instructions
of Boeing Alert Service Bulletin 747-57A2443, Revision 1, dated June
23, 2014.
(k) New Inspection or Replacement for Certain Fittings That Were
Previously Inspected
For airplanes on which the detailed inspection required by
paragraph (h)(1) of this AD is done before the effective date of
this AD, except as required by paragraph (m) of this AD: If any
cylindrical defect is found during any inspection required by
paragraph (h)(1) of this AD and the replacement of the inboard
actuator attach fitting of the outboard flap was not done as
specified in Part 4 of the Accomplishment Instructions of Boeing
Alert Service Bulletin 747-57A2443, within 24 months after the
effective date of this AD, do the actions specified in paragraph
(k)(1) or (k)(2) of this AD.
(1) Do a detailed inspection of the inner conical section for
machining defects and do an ultrasonic inspection to determine the
minimum thickness or mechanically determine the minimum thickness,
in accordance with Part 3 of the Accomplishment Instructions of
Boeing Alert Service Bulletin 747-57A2443, Revision 1, dated June
23, 2014. A review of airplane maintenance records, if available, is
acceptable to determine the wall thickness and to determine if there
are machining defects, provided wall thickness and machining defects
can be positively determined from the records review.
(i) If any machining defect is found and the minimum thickness
of the wall is 0.140 inch or greater: Before further flight, do the
actions specified in paragraph (k)(1)(i)(A) or (k)(1)(i)(B) of this
AD.
(A) Overhaul the inboard actuator attach fitting of the outboard
flap, in accordance with Part 5 of the Accomplishment Instructions
of Boeing Alert Service Bulletin 747-57A2443, Revision 1, dated June
23, 2014.
(B) Replace the inboard actuator attach fitting of the outboard
flap, in accordance with Part 4 of the Accomplishment Instructions
of Boeing Alert Service Bulletin 747-57A2443, Revision 1, dated June
23, 2014.
(ii) If any machining defect is found and the minimum thickness
of the wall is 0.130 inch or greater and less than 0.140 inch:
Before further flight, replace the inboard actuator attach fitting
of the outboard flap, in accordance with Part 4 of the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
57A2443, Revision 1, dated June 23, 2014.
(iii) If no machining defect is found and the minimum thickness
of the wall is 0.130 inch or greater and less than 0.140 inch:
Within 48 months or 3,000 flight cycles after the effective date of
this AD, whichever occurs first, replace the inboard actuator attach
fitting of the outboard flap, in accordance with Part 4 of the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
57A2443, Revision 1, dated June 23, 2014.
(iv) If a machining defect is or is not found and the minimum
thickness of the wall is less than 0.130 inch: Before further
flight, replace the inboard actuator attach fitting of the outboard
flap, in accordance with Part 4 of the Accomplishment Instructions
of Boeing Alert Service Bulletin 747-57A2443, Revision 1, dated June
23, 2014.
(2) Replace the inboard actuator attach fitting of the outboard
flap, in accordance with Part 4 of the Accomplishment Instructions
of Boeing Alert Service Bulletin 747-57A2443, Revision 1, dated June
23, 2014.
(l) Parts Installation Limitation
As of the effective date of this AD, no actuator attach fitting
having P/N 65B08564-7 may be installed on any airplane unless the
inspection specified in paragraph (h)(1) of this AD is done prior to
installation and the applicable actions specified in paragraphs (i)
and (j) of this AD are done within the applicable times specified in
paragraphs (i) and (j) of this AD. A review of airplane maintenance
records, if available, is acceptable to determine if the inspection
and applicable actions have been done, provided the inspection and
actions can be positively determined from the records review.
(m) Action for Parts Installed After AD 2013-23-03, Amendment 39-17658
(78 FR 68345, November 14, 2013) Was Accomplished
For airplanes on which the detailed inspection required by
paragraph (h)(1) of this AD is done before the effective date of
this AD and the inboard actuator attach fitting was replaced since
that inspection: Within 90 days after the effective date of this AD,
inspect to determine the part number of the inboard actuator attach
fittings of the outboard flaps and, for inboard actuator attach
fittings having P/N 65B08564-7, do the applicable actions specified
in paragraphs (h), (i), and (j) of this AD within the applicable
times specified in paragraphs (h), (i), and (j) of this AD. A review
of airplane maintenance records, if available, is acceptable to
determine the part number, provided the part number can be
positively determined from the records review.
(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) 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 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. For a repair method to be approved, the repair must
meet the certification basis of the airplane, and the approval must
specifically refer to this AD.
(4) If any service information contains steps that are
identified as RC (Required for Compliance), those steps must be done
to comply with this AD; any steps that are not identified as RC are
recommended. Those steps that are not identified 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 steps identified as RC can be done
and the airplane can be put back in an airworthy condition. Any
substitutions or changes to steps identified as RC require approval
of an AMOC.
(5) AMOCs approved for AD 2013-23-03, Amendment 39-17658 (78 FR
68345, November 14, 2013) are approved as AMOCs for the
corresponding provisions of this AD.
(o) Related Information
For more information about this AD, contact Nathan Weigand,
Aerospace
[[Page 80247]]
Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft
Certification Office, 1601 Lind Avenue SW., Renton, WA 98057-3356;
phone: 425-917-6428; fax: 425-917-6590; email:
nathan.p.weigand@faa.gov.
(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.
(3) The following service information was approved for IBR on
January 28, 2016.
(i) Boeing Alert Service Bulletin 747-57A2443, Revision 1, dated
June 23, 2014.
(ii) Reserved.
(4) The following service information was approved for IBR on
November 29, 2013 (78 FR 68345, November 14, 2013).
(i) Boeing Alert Service Bulletin 747-57A2443, dated September
12, 2013.
(ii) Reserved.
(5) 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.
(6) 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.
(7) 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 24, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate,Aircraft Certification Service.
[FR Doc. 2015-30881 Filed 12-23-15; 8:45 am]
BILLING CODE 4910-13-P
