Airworthiness Directives; The Boeing Company Airplanes, 21645-21649 [2015-08407]
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Federal Register / Vol. 80, No. 75 / Monday, April 20, 2015 / Rules and Regulations
inspection required by paragraphs (g)(2) and
(g)(3) of this AD: Within 6 months after the
inspection required by paragraph (g)(2) of
this AD, replace the LH shock mount pickup fitting P/N S54210394200 with a
serviceable LH shock mount pick-up fitting
having a serial number equal to or higher
than 2451, in accordance with a method
approved by the Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA; or EASA; or ATR—GIE
´
Avions de Transport Regional’s EASA DOA.
(i) Parts Installation Limitation
As of the effective date of this AD, do not
install on any airplane a LH shock mount
pick-up fitting P/N S54210394200, unless it
is serviceable and has been determined to
have an S/N equal to or higher than 2451, in
accordance with the requirements of
paragraph (g)(1) of this AD.
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(j) Reporting Requirement
Submit a report of the findings (both
positive and negative) of the inspections
required by paragraphs (g)(1), (g)(2), and
(g)(3) of this AD to ATR at techdesk@atr.fr
and continued.airworthiness@atr.fr at the
applicable time specified in paragraph (j)(1)
or (j)(2) of this AD. The report must include
the airplane serial number, registration,
inspection date, inspection results, and
engine pick-up serial numbers.
(1) If the inspection was done on or after
the effective date of this AD: Submit the
report within 30 days after the inspection.
(2) If the inspection was done before the
effective date of this AD: Submit the report
within 30 days after the effective date of this
AD.
(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, 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:
Tom Rodriguez, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone 425–227–1137; 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
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
EASA; or ATR–GIE Avions de Transport
´
Regional’s EASA DOA. If approved by the
DOA, the approval must include the DOAauthorized signature.
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(3) Reporting Requirements: A federal
agency may not conduct or sponsor, and a
person is not required to respond to, nor
shall a person be subject to a penalty for
failure to comply with a collection of
information subject to the requirements of
the Paperwork Reduction Act unless that
collection of information displays a current
valid OMB Control Number. The OMB
Control Number for this information
collection is 2120–0056. Public reporting for
this collection of information is estimated to
be approximately 5 minutes per response,
including the time for reviewing instructions,
completing and reviewing the collection of
information. All responses to this collection
of information are mandatory. Comments
concerning the accuracy of this burden and
suggestions for reducing the burden should
be directed to the FAA at: 800 Independence
Ave. SW., Washington, DC 20591, Attn:
Information Collection Clearance Officer,
AES–200.
Issued in Renton, Washington, on March
19, 2015.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
(l) Related Information
AGENCY:
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2012–0192, dated
September 21, 2012 (corrected September 24,
2012), for related information. You may
examine the MCAI on the Internet at https://
www.regulations.gov by searching for and
locating Docket No. FAA–2015–0497.
(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) ATR ATR72 Airplane Maintenance
Manual (AMM) Job Instruction Card 54–11–
61 DVI 10000, Detailed Visual Inspection of
Forward Engine Mount, dated March 1, 2012.
(ii) ATR ATR72 AMM Job Instruction Card
71–20–00 DVI 10000, Detailled (sic) Visual
Inspec[tion] of Engine Shockmounts, dated
March 1, 2012.
(3) For service information identified in
this AD, contact ATR—GIE Avions de
´
´
Transport Regional, 1, Allee Pierre Nadot,
31712 Blagnac Cedex, France; telephone +33
(0) 5 62 21 62 21; fax +33 (0) 5 62 21 67 18;
email continued.airworthiness@atr.fr;
Internet https://www.aerochain.com.
(4) You may view this service information
at the FAA, Transport Airplane Directorate,
1601 Lind Avenue SW., Renton, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://www.archives.
gov/federal-register/cfr/ibr-locations.html.
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[FR Doc. 2015–07162 Filed 4–17–15; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2011–0475; Directorate
Identifier 2010–NM–199–AD; Amendment
39–18137; AD 2015–08–01]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
We are adopting a new
airworthiness directive (AD) for certain
The Boeing Company Model 757–200,
–200PF, –200CB, and –300 series
airplanes. This AD was prompted by
numerous reports of unintended lateral
oscillations during final approach, just
before landing. This AD requires,
depending on airplane configuration,
installing new relays and bracket
assemblies, inspecting to ensure that the
new relays do not contact adjacent wire
bundles, torquing the bracket assembly
installation nuts and ground stud nuts,
doing bond resistance tests between the
bracket assemblies and the terminal lugs
on the ground studs, and related
investigative and corrective actions if
necessary. We are issuing this AD to
reduce the chance of unintended lateral
oscillations near touchdown, which
could result in loss of lateral control of
the airplane, and consequent airplane
damage or injury to flightcrew and
passengers.
SUMMARY:
This AD is effective May 26,
2015.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of May 26, 2015.
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.,
DATES:
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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 2011–
0475.
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–2011–
0475; 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:
Jeffrey Palmer, Aerospace Engineer,
Systems and Equipment Branch, ANM–
130L, Los Angeles Aircraft Certification
Office (ACO), FAA, 3960 Paramount
Boulevard, Lakewood, CA 90712–4137;
phone: 562–627–5351; fax: 562–627–
5210; email: jeffrey.w.palmer@faa.gov.
SUPPLEMENTARY INFORMATION:
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Discussion
We issued a supplemental notice of
proposed rulemaking (SNPRM) to
amend 14 CFR part 39 by adding an AD
that would apply to certain The Boeing
Company Model 757–200, –200PF,
–200CB, and –300 series airplanes. The
SNPRM published in the Federal
Register on July 1, 2014 (79 FR 37239).
We preceded the SNPRM with a notice
of proposed rulemaking (NPRM) that
published in the Federal Register on
May 24, 2011 (76 FR 30043). The NPRM
proposed to require, for certain
airplanes, installing new relays adjacent
to two of the spoiler control modules.
For certain other airplanes, the NPRM
proposed to require torquing the bracket
assembly installation nuts and ground
stud nuts, and doing bond resistance
tests between the bracket assemblies
and the terminal lugs on the ground
studs. The NPRM was prompted by
numerous reports of unintended lateral
oscillations during final approach, just
before landing. In addition to the
actions proposed in the NPRM, the
SNPRM proposed to require installing
three new relays on the opposite side of
the same relay bracket assembly; and for
certain airplanes, doing an additional
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inspection to ensure that the three new
relays do not contact adjacent wire
bundles, and related investigative and
corrective actions if necessary. We are
issuing this AD to reduce the chance of
unintended lateral oscillations near
touchdown, which could result in loss
of lateral control of the airplane, and
consequent airplane damage or injury to
flightcrew and passengers.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comments
received on the SNPRM (79 FR 37239,
July 1, 2014) and the FAA’s response to
each comment.
Support for the SNPRM (79 FR 37239,
July 1, 2014)
American Airlines (AAL) stated that it
agrees with the intent of the SNPRM (79
FR 37239, July 1, 2014). Boeing stated
that it agrees with the NPRM (76 FR
30043, May 24, 2011). We infer that
Boeing’s comment refers to the SNPRM.
Request To Withdraw the SNPRM (79
FR 37239, July 1, 2014)
United Airlines (United Engineering)
requested data to justify the release of a
new AD. United Engineering stated that
it has not received any reports of pilotinduced oscillations since
implementation of AD 2006–23–15,
Amendment 39–14827 (71 FR 66657,
November 16, 2006). United
Engineering stated that AD 2006–23–15
requires, among other actions, installing
a control wheel damper assembly and
vortex generators (vortilons) on the
leading edge of the outboard main flap.
United Engineering also stated that the
required work is extensive and that the
impact to operations and the cost of this
modification is considerable.
From these statements, we infer that
United Engineering requested we
withdraw the SNPRM (79 FR 37239,
July 1, 2014). We do not agree with the
commenter’s request to withdraw the
SNPRM. AD 2006–23–15, Amendment
39–14827 (71 FR 66657, November 16,
2006), was considered interim action.
To effectively manage the risk, the FAA
determined an interim action needed to
be mandated to reduce the risk, while a
solution that fully addresses the unsafe
condition was identified and could be
implemented.
The manufacturer has identified an
additional modification that is needed
to correct the unsafe condition
identified in AD 2006–23–15. We have
determined that this design change not
only corrects the unsafe condition by
removing excessive airplane roll
authority during landing, but it will also
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improve safety by making the Model
757 handling characteristics more
consistent with the other Boeing
airplane models. Also, even though
there have only been 12 reports of
unintended lateral oscillations near
touchdown, the FAA considers it likely
that there may have been other events
that have been unrecognized and/or
unreported.
Finally, in developing the compliance
time for this AD, we did consider not
only the safety implications of the
identified unsafe condition, but also the
practical aspects of an orderly
modification of the fleet including the
work required and the impact on
operations. We have determined that it
is necessary to proceed with this AD
action.
Request To Delay Final Rule Pending
Revised Service Information
AAL requested that we delay this
final rule until Boeing releases Boeing
Service Bulletin 757–27A0152, Revision
4. AAL noted that Boeing intended to
release Boeing Service Bulletin 757–
27A0152, Revision 4, which would
address its concerns regarding certain
procedures and figures in Boeing
Service Bulletin 757–27A0152, Revision
1, Dated June 30, 2010.
Since the issuance of the SNPRM (79
FR 37239, July 1, 2014), Boeing has
issued Service Bulletin 757–27A0152,
Revision 4, dated August 26, 2014. We
have revised this AD to incorporate
Boeing Service Bulletin 757–27A0152,
Revision 4, dated August 26, 2014, as an
appropriate source of service
information for accomplishing the
actions required by this AD. This
service bulletin includes a change to a
footnote listed in Figures 15, 16, 17, 19,
and 21; this footnote addresses AAL’s
concerns regarding certain procedures
and figures in Boeing Service Bulletin
757–27A0152, Revision 1, dated June
30, 2010. Boeing Service Bulletin 757–
27A0152, Revision 4, dated August 26,
2014, states that no more work is
necessary on airplanes changed in
accordance with Boeing Service Bulletin
757–27A0152, Revision 2, dated May
25, 2012; or Boeing Service Bulletin
757–27A0152, Revision 3, dated
October 28, 2013.
We have changed paragraphs (c) and
(g) of this AD to reference Boeing
Service Bulletin 757–27A0152, Revision
3, dated October 28, 2013, as revised by
Boeing Service Bulletin 757–27A0152,
Revision 4, dated August 26, 2014.
Effect of Winglets on AD
Aviation Partners Boeing stated that
the installation of winglets per
Supplemental Type Certificate (STC)
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ST01518SE (https://rgl.faa.gov/
Regulatory_and_Guidance_Library/
rgstc.nsf/0/312bc296830a925c86257c
85006d1b1f/$FILE/ST01518SE.pdf) does
not affect the accomplishment of the
manufacturer’s service instructions. No
change is necessary to this AD in this
regard.
Related Service Information Under 1
CFR Part 51
We reviewed Boeing Service Bulletin
757–27A0152, Revision 3, dated
October 28, 2013, which describes
procedures for installing new relays;
inspecting to ensure that the new relays
do not contact adjacent wire bundles,
and related investigative and corrective
actions if necessary; torquing the
bracket assembly installation nuts and
ground stud nuts; and doing bond
resistance tests between the bracket
assemblies and the terminal lugs on the
ground studs.
We have also reviewed Boeing Service
Bulletin 757–27A0152, Revision 4,
dated August 26, 2014, which provides
some revised text in footnotes of certain
figures.
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 of
this AD.
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 and minor
editorial changes. We have determined
that these minor changes:
• Are consistent with the intent that
was proposed in the SNPRM (79 FR
37239, July 1, 2014) for correcting the
unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the SNPRM (79 FR 37239,
July 1, 2014).
We also determined that these
changes will not increase the economic
burden on any operator or increase the
scope of this AD.
Costs of Compliance
We estimate that this AD affects 676
airplanes of U.S. registry.
We estimate the following costs to
comply with this AD:
ESTIMATED COSTS
Action
Labor cost
Installation Group 1, Configuration 1 (48 airplanes).
Installation Group 2, Configuration 1 (588
airplanes).
Installation Group 3, Configuration 1 (12 airplanes).
Installation Group 4, Configuration 1 (24 airplanes).
Installation Group 5, Configuration 1 (4 airplanes).
Torque Bracket Assembly and Bond Tests
Groups 1–5, Configuration 2 (Up to 676
airplanes).
General Visual Inspection Groups 1–5, Configuration 3 (Up to 676 airplanes).
We estimate the following costs to do
any necessary repairs that would be
required based on the results of the
inspection. We have no way of
Cost on U.S.
operators
Parts cost
Cost per product
36 work-hours × $85 per hour = $3,060 ......
$4,691
$7,751 ................
$372,048.
33 work-hours × $85 per hour = $2,805 ......
4,610
7,415 ..................
4,360,020.
33 work-hours × $85 per hour = $2,805 ......
4,619
7,424 ..................
89,088.
33 work-hours × $85 per hour = $2,805 ......
4,610
7,415 ..................
177,960.
36 work-hours × $85 per hour = $3,060 ......
4,701
7,761 ..................
31,044.
12 work-hours × $85 per hour = $1,020 ......
0
Up to $1,020 ......
Up to $689,520.
7 work-hours × $85 per hour = $595 ...........
0
Up to $595 .........
Up to $402,220.
determining the number of aircraft that
might need these repairs:
ON-CONDITION COSTS
Action
Labor cost
Adjust Wire Bundle and Install Sleeve, Group 1–5, Configuration 1 .............
Inspection, Repair, and Installation Change, Group 1–5, Configuration 2 ....
Inspection, Repair, Installation Change, and Test, Group 1–5, Configuration 3.
1 work-hour × $85 per hour = $85 .........
1 work-hour × $85 per hour = $85 .........
5 work-hours × $85 per hour = $425 .....
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We have received no definitive data
that would enable us to provide cost
estimates for the parts needed 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
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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
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Parts cost
$0
0
0
Cost per
product
$85
85
425
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
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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
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
2015–08–01 The Boeing Company:
Amendment 39–18137; Docket No.
FAA–2011–0475; Directorate Identifier
2010–NM–199–AD.
(a) Effective Date
This AD is effective May 26, 2015.
(b) Affected ADs
None.
(c) Applicability
This AD applies to The Boeing Company
Model 757–200, –200PF, –200CB, and –300
series airplanes; certificated in any category;
as identified in Boeing Service Bulletin 757–
27A0152, Revision 3, dated October 28, 2013,
as revised by Boeing Service Bulletin 757–
27A0152, Revision 4, dated August 26, 2014.
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(d) Subject
Air Transport Association (ATA) of
America Code 27, Flight Controls.
(e) Unsafe Condition
This AD was prompted by numerous
reports of unintended lateral oscillations
during the final approach, just before
landing. We are issuing this AD to reduce the
chance of unintended lateral oscillations near
touchdown, which could result in loss of
lateral control of the airplane, and
consequent airplane damage or injury to
flightcrew and passengers.
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(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Installation and Inspection
Within 60 months after the effective date
of this AD, do the applicable actions
specified in paragraph (g)(1), (g)(2), or (g)(3)
of this AD.
(1) For Configuration 1 airplanes defined in
Boeing Service Bulletin 757–27A0152,
Revision 3, dated October 28, 2013, as
revised by Boeing Service Bulletin 757–
27A0152, Revision 4, dated August 26, 2014:
Install three bracket assemblies and three
new relays, and make changes to the wire
bundles, in accordance with the
Accomplishment Instructions of Boeing
Service Bulletin 757–27A0152, Revision 3,
dated October 28, 2013, as revised by Boeing
Service Bulletin 757–27A0152, Revision 4,
dated August 26, 2014.
(2) For Configuration 2 airplanes defined in
Boeing Service Bulletin 757–27A0152,
Revision 3, dated October 28, 2013, as
revised by Boeing Service Bulletin 757–
27A0152, Revision 4, dated August 26, 2014:
Torque the bracket assembly nuts and ground
stud nuts, do bond resistance tests to verify
that bonding requirements are met, do a
general visual inspection to ensure that the
three new relays do not touch the adjacent
wire bundles, and do all applicable related
investigative and corrective actions, in
accordance with the Accomplishment
Instructions of Boeing Service Bulletin 757–
27A0152, Revision 3, dated October 28, 2013,
as revised by Boeing Service Bulletin 757–
27A0152, Revision 4, dated August 26, 2014.
Do all applicable related investigative and
corrective actions before further flight.
(3) For Configuration 3 airplanes defined in
Boeing Service Bulletin 757–27A0152,
Revision 3, dated October 28, 2013, as
revised by Boeing Service Bulletin 757–
27A0152, Revision 4, dated August 26, 2014:
Do a general visual inspection to ensure that
the three new relays do not touch the
adjacent wire bundles, and do all applicable
related investigative and corrective actions,
in accordance with the Accomplishment
Instructions of Boeing Service Bulletin 757–
27A0152, Revision 3, dated October 28, 2013,
as revised by Boeing Service Bulletin 757–
27A0152, Revision 4, dated August 26, 2014.
Do all applicable related investigative and
corrective actions before further flight.
(h) Credit for Previous Actions
This paragraph provides credit for actions
required by paragraph (g) of this AD, if those
actions were performed before the effective
date of this AD using Boeing Service Bulletin
757–27A0152, Revision 2, dated May 25,
2012 (which is not incorporated by reference
in this AD); or Boeing Service Bulletin 757–
27A0152, Revision 3, dated October 28, 2013.
(i) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Los Angeles 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,
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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 (j)(1) of this AD. Information may
be emailed to: 9-ANM-LAACO-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, Los Angeles
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.
(j) Related Information
(1) For more information about this AD,
contact Jeffrey Palmer, Aerospace Engineer,
Systems and Equipment Branch, ANM–130L,
Los Angeles Aircraft Certification Office
(ACO), FAA, 3960 Paramount Boulevard,
Lakewood, CA 90712–4137; phone: 562–627–
5351; fax: 562–627–5210; email:
jeffrey.w.palmer@faa.gov.
(2) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (k)(3) and (k)(4) of this AD.
(k) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(i) Boeing Service Bulletin 757–27A0152,
Revision 3, dated October 28, 2013.
(ii) Boeing Service Bulletin 757–27A0152,
Revision 4, dated August 26, 2014.
(3) For Boeing service information
identified in this AD, contact Boeing
Commercial Airplanes, Attention: Data &
Services Management, P. O. Box 3707, MC
2H–65, Seattle, WA 98124–2207; telephone
206–544–5000, extension 1; fax 206–766–
5680; Internet https://www.myboeing
fleet.com.
(4) You may view this service information
at FAA, Transport Airplane Directorate, 1601
Lind Avenue SW., Renton, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://www.archives.
gov/federal-register/cfr/ibr-locations.html.
E:\FR\FM\20APR1.SGM
20APR1
Federal Register / Vol. 80, No. 75 / Monday, April 20, 2015 / Rules and Regulations
Issued in Renton, Washington, on April 3,
2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2015–08407 Filed 4–17–15; 08:45 am]
BILLING CODE 4910–13–P
SECURITIES AND EXCHANGE
COMMISSION
17 CFR Part 232
[Release Nos. 33–9746; 34–74714; 39–2502;
IC–31551]
Adoption of Updated EDGAR Filer
Manual
Securities and Exchange
Commission.
ACTION: Final rule.
AGENCY:
The Securities and Exchange
Commission (the Commission) is
adopting revisions to the Electronic Data
Gathering, Analysis, and Retrieval
System (EDGAR) Filer Manual and
related rules to reflect updates to the
EDGAR system. The updates are being
made primarily to support the 2015 US
GAAP financial reporting and 2015
EXCH taxonomies; add new form types
for registration of Security-based swap
data repositories (SDR); revise the Form
ID Application Confirmation screen;
remove references to the Paper Form ID;
and revise Item 1 on submission form
type MA–A. The EDGAR system was
upgraded to support the new 2015
taxonomies and revised MA–A form
functionalities on March 9, 2015. The
EDGAR system is scheduled to be
upgraded to support the other
functionalities on April 13, 2015.
DATES: Effective April 20, 2015. The
incorporation by reference of the
EDGAR Filer Manual is approved by the
Director of the Federal Register as of
April 20, 2015.
FOR FURTHER INFORMATION CONTACT: In
the Division of Trading and Markets, for
questions concerning Form SDR and the
revisions for Form MA–A, contact Kathy
Bateman at (202) 551–4345, and in the
Office of Information Technology,
contact Tammy Borkowski at (202) 551–
7208.
SUPPLEMENTARY INFORMATION: We are
adopting an updated EDGAR Filer
Manual, Volume I and Volume II. The
Filer Manual describes the technical
formatting requirements for the
preparation and submission of
electronic filings through the EDGAR
system.1 It also describes the
mstockstill on DSK4VPTVN1PROD with RULES
SUMMARY:
1 We originally adopted the Filer Manual on April
1, 1993, with an effective date of April 26, 1993.
VerDate Sep<11>2014
16:33 Apr 17, 2015
Jkt 235001
requirements for filing using
EDGARLink Online and the Online
Forms/XML Web site.
The revisions to the Filer Manual
reflect changes within Volume I entitled
EDGAR Filer Manual, Volume I:
‘‘General Information,’’ Version 20
(April 2015), and Volume II entitled
EDGAR Filer Manual, Volume II:
‘‘EDGAR Filing,’’ Version 30 (April
2015). The updated manual will be
incorporated by reference into the Code
of Federal Regulations.
The Filer Manual contains all the
technical specifications for filers to
submit filings using the EDGAR system.
Filers must comply with the applicable
provisions of the Filer Manual in order
to assure the timely acceptance and
processing of filings made in electronic
format.2 Filers may consult the Filer
Manual in conjunction with our rules
governing mandated electronic filing
when preparing documents for
electronic submission.3
The EDGAR system will be upgraded
to Release 15.1 on April 13, 2015 and
will introduce the following changes:
EDGAR will be updated to add new
submission form types SDR, SDR/A,
SDR–A, and SDR–W. These submission
form types can be accessed by selecting
the ‘‘File SDR’’ link on the EDGAR
Filing Web site. Additionally,
applicants may construct XML
submissions for these submission types
by following the ‘‘EDGAR SDR XML
Technical Specification’’ document
available on the SEC’s Public Web site
(https://www.sec.gov/info/edgar.shtml).
Submission form types SDR, SDR/A,
SDR–A, and SDR–W will include the
‘‘Request Confidentiality’’ check box to
allow applicants to select which
information to request confidential
treatment. After a Form SDR is
submitted, SEC staff will review the
submission and make a determination of
whether the information for which
confidential treatment is requested
should be made public. EDGAR will
disseminate only the content and
attached exhibits of the submission that
the SEC staff has determined to be
public.
The ‘‘Form ID Application
Confirmation’’ screen will display four
additional labels: ‘‘Signature of
Authorized Person,’’ ‘‘Printed Name of
Release No. 33–6986 (April 1, 1993) [58 FR 18638].
We implemented the most recent update to the Filer
Manual on December 15, 2014. See Release No. 33–
9692 (December 23, 2014) [79 FR 76878].
2 See Rule 301 of Regulation S–T (17 CFR
232.301).
3 See Release No. 33–9692 in which we
implemented EDGAR Release 14.3. For additional
history of Filer Manual rules, please see the cites
therein.
PO 00000
Frm 00011
Fmt 4700
Sfmt 4700
21649
Signature,’’ ‘‘Title of Person Signing,’’
and ‘‘Notary Signature & Seal to be
Placed Here.’’ This screen will also be
updated to include a ‘‘Print Window’’
button to print the completed online
Form ID application. The printed
application can be signed and notarized
by the filer to serve as the
authentication document when
applying for EDGAR access.
All references to the Paper Form ID
have been removed from the Filer
Manual. Filers can print the electronic
Form ID and use this as the
authentication document as explained
above.
EDGAR was updated to support the
2015 US GAAP financial reporting
taxonomy and the 2015 EXCH
taxonomy. A complete listing of
supported standard taxonomies is
available on https://www.sec.gov/info/
edgar/edgartaxonomies.shtml.
Item 1 ‘‘Identifying Information’’ on
submission type MA–A was updated for
the following question: ‘‘Changes: Are
there any changes in this annual update
to information provided in the
municipal advisor’s most recent Form
MA, other than the updated Execution
Page?’’ If filers select ‘‘No’’ as a response
to the question, then all fields will be
disabled on submission type MA–A
with the exception of ‘‘Execution’’ and
‘‘Filer Information’’ tabs and the ‘‘Fiscal
Year End Information’’ field on Item 1.
Alternatively, if filers select ‘‘Yes’’ to
the question, then they must update
applicable items on submission type
MA–A.
Along with the adoption of the Filer
Manual, we are amending Rule 301 of
Regulation S–T to provide for the
incorporation by reference into the Code
of Federal Regulations of today’s
revisions. This incorporation by
reference was approved by the Director
of the Federal Register in accordance
with 5 U.S.C. 552(a) and 1 CFR part 51.
The updated EDGAR Filer Manual
will be available for Web site viewing
and printing; the address for the Filer
Manual is https://www.sec.gov/info/
edgar.shtml. You may also obtain paper
copies of the EDGAR Filer Manual from
the following address: Public Reference
Room, U.S. Securities and Exchange
Commission, 100 F Street NE.,
Washington, DC 20549, on official
business days between the hours of
10:00 a.m. and 3:00 p.m.
Since the Filer Manual and the
corresponding rule changes relate solely
to agency procedures or practice,
publication for notice and comment is
not required under the Administrative
E:\FR\FM\20APR1.SGM
20APR1
]]>Agencies
[Federal Register Volume 80, Number 75 (Monday, April 20, 2015)]
[Rules and Regulations]
[Pages 21645-21649]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2015-08407]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2011-0475; Directorate Identifier 2010-NM-199-AD;
Amendment 39-18137; AD 2015-08-01]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for certain
The Boeing Company Model 757-200, -200PF, -200CB, and -300 series
airplanes. This AD was prompted by numerous reports of unintended
lateral oscillations during final approach, just before landing. This
AD requires, depending on airplane configuration, installing new relays
and bracket assemblies, inspecting to ensure that the new relays do not
contact adjacent wire bundles, torquing the bracket assembly
installation nuts and ground stud nuts, doing bond resistance tests
between the bracket assemblies and the terminal lugs on the ground
studs, and related investigative and corrective actions if necessary.
We are issuing this AD to reduce the chance of unintended lateral
oscillations near touchdown, which could result in loss of lateral
control of the airplane, and consequent airplane damage or injury to
flightcrew and passengers.
DATES: This AD is effective May 26, 2015.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of May 26, 2015.
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.,
[[Page 21646]]
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 2011-
0475.
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-2011-
0475; 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: Jeffrey Palmer, Aerospace Engineer,
Systems and Equipment Branch, ANM-130L, Los Angeles Aircraft
Certification Office (ACO), FAA, 3960 Paramount Boulevard, Lakewood, CA
90712-4137; phone: 562-627-5351; fax: 562-627-5210; email:
jeffrey.w.palmer@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a supplemental notice of proposed rulemaking (SNPRM) to
amend 14 CFR part 39 by adding an AD that would apply to certain The
Boeing Company Model 757-200, -200PF, -200CB, and -300 series
airplanes. The SNPRM published in the Federal Register on July 1, 2014
(79 FR 37239). We preceded the SNPRM with a notice of proposed
rulemaking (NPRM) that published in the Federal Register on May 24,
2011 (76 FR 30043). The NPRM proposed to require, for certain
airplanes, installing new relays adjacent to two of the spoiler control
modules. For certain other airplanes, the NPRM proposed to require
torquing the bracket assembly installation nuts and ground stud nuts,
and doing bond resistance tests between the bracket assemblies and the
terminal lugs on the ground studs. The NPRM was prompted by numerous
reports of unintended lateral oscillations during final approach, just
before landing. In addition to the actions proposed in the NPRM, the
SNPRM proposed to require installing three new relays on the opposite
side of the same relay bracket assembly; and for certain airplanes,
doing an additional inspection to ensure that the three new relays do
not contact adjacent wire bundles, and related investigative and
corrective actions if necessary. We are issuing this AD to reduce the
chance of unintended lateral oscillations near touchdown, which could
result in loss of lateral control of the airplane, and consequent
airplane damage or injury to flightcrew and passengers.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the SNPRM (79
FR 37239, July 1, 2014) and the FAA's response to each comment.
Support for the SNPRM (79 FR 37239, July 1, 2014)
American Airlines (AAL) stated that it agrees with the intent of
the SNPRM (79 FR 37239, July 1, 2014). Boeing stated that it agrees
with the NPRM (76 FR 30043, May 24, 2011). We infer that Boeing's
comment refers to the SNPRM.
Request To Withdraw the SNPRM (79 FR 37239, July 1, 2014)
United Airlines (United Engineering) requested data to justify the
release of a new AD. United Engineering stated that it has not received
any reports of pilot-induced oscillations since implementation of AD
2006-23-15, Amendment 39-14827 (71 FR 66657, November 16, 2006). United
Engineering stated that AD 2006-23-15 requires, among other actions,
installing a control wheel damper assembly and vortex generators
(vortilons) on the leading edge of the outboard main flap. United
Engineering also stated that the required work is extensive and that
the impact to operations and the cost of this modification is
considerable.
From these statements, we infer that United Engineering requested
we withdraw the SNPRM (79 FR 37239, July 1, 2014). We do not agree with
the commenter's request to withdraw the SNPRM. AD 2006-23-15, Amendment
39-14827 (71 FR 66657, November 16, 2006), was considered interim
action. To effectively manage the risk, the FAA determined an interim
action needed to be mandated to reduce the risk, while a solution that
fully addresses the unsafe condition was identified and could be
implemented.
The manufacturer has identified an additional modification that is
needed to correct the unsafe condition identified in AD 2006-23-15. We
have determined that this design change not only corrects the unsafe
condition by removing excessive airplane roll authority during landing,
but it will also improve safety by making the Model 757 handling
characteristics more consistent with the other Boeing airplane models.
Also, even though there have only been 12 reports of unintended lateral
oscillations near touchdown, the FAA considers it likely that there may
have been other events that have been unrecognized and/or unreported.
Finally, in developing the compliance time for this AD, we did
consider not only the safety implications of the identified unsafe
condition, but also the practical aspects of an orderly modification of
the fleet including the work required and the impact on operations. We
have determined that it is necessary to proceed with this AD action.
Request To Delay Final Rule Pending Revised Service Information
AAL requested that we delay this final rule until Boeing releases
Boeing Service Bulletin 757-27A0152, Revision 4. AAL noted that Boeing
intended to release Boeing Service Bulletin 757-27A0152, Revision 4,
which would address its concerns regarding certain procedures and
figures in Boeing Service Bulletin 757-27A0152, Revision 1, Dated June
30, 2010.
Since the issuance of the SNPRM (79 FR 37239, July 1, 2014), Boeing
has issued Service Bulletin 757-27A0152, Revision 4, dated August 26,
2014. We have revised this AD to incorporate Boeing Service Bulletin
757-27A0152, Revision 4, dated August 26, 2014, as an appropriate
source of service information for accomplishing the actions required by
this AD. This service bulletin includes a change to a footnote listed
in Figures 15, 16, 17, 19, and 21; this footnote addresses AAL's
concerns regarding certain procedures and figures in Boeing Service
Bulletin 757-27A0152, Revision 1, dated June 30, 2010. Boeing Service
Bulletin 757-27A0152, Revision 4, dated August 26, 2014, states that no
more work is necessary on airplanes changed in accordance with Boeing
Service Bulletin 757-27A0152, Revision 2, dated May 25, 2012; or Boeing
Service Bulletin 757-27A0152, Revision 3, dated October 28, 2013.
We have changed paragraphs (c) and (g) of this AD to reference
Boeing Service Bulletin 757-27A0152, Revision 3, dated October 28,
2013, as revised by Boeing Service Bulletin 757-27A0152, Revision 4,
dated August 26, 2014.
Effect of Winglets on AD
Aviation Partners Boeing stated that the installation of winglets
per Supplemental Type Certificate (STC)
[[Page 21647]]
ST01518SE (https://rgl.faa.gov/Regulatory_and_Guidance_Library/
rgstc.nsf/0/312bc296830a925c86257c85006d1b1f/$FILE/ST01518SE.pdf) does
not affect the accomplishment of the manufacturer's service
instructions. No change is necessary to this AD in this regard.
Related Service Information Under 1 CFR Part 51
We reviewed Boeing Service Bulletin 757-27A0152, Revision 3, dated
October 28, 2013, which describes procedures for installing new relays;
inspecting to ensure that the new relays do not contact adjacent wire
bundles, and related investigative and corrective actions if necessary;
torquing the bracket assembly installation nuts and ground stud nuts;
and doing bond resistance tests between the bracket assemblies and the
terminal lugs on the ground studs.
We have also reviewed Boeing Service Bulletin 757-27A0152, Revision
4, dated August 26, 2014, which provides some revised text in footnotes
of certain figures.
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 of this
AD.
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 and minor editorial changes. We have
determined that these minor changes:
Are consistent with the intent that was proposed in the
SNPRM (79 FR 37239, July 1, 2014) for correcting the unsafe condition;
and
Do not add any additional burden upon the public than was
already proposed in the SNPRM (79 FR 37239, July 1, 2014).
We also determined that these changes will not increase the
economic burden on any operator or increase the scope of this AD.
Costs of Compliance
We estimate that this AD affects 676 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
----------------------------------------------------------------------------------------------------------------
Installation Group 1, 36 work-hours x $85 per $4,691 $7,751............. $372,048.
Configuration 1 (48 airplanes). hour = $3,060.
Installation Group 2, 33 work-hours x $85 per 4,610 7,415.............. 4,360,020.
Configuration 1 (588 airplanes). hour = $2,805.
Installation Group 3, 33 work-hours x $85 per 4,619 7,424.............. 89,088.
Configuration 1 (12 airplanes). hour = $2,805.
Installation Group 4, 33 work-hours x $85 per 4,610 7,415.............. 177,960.
Configuration 1 (24 airplanes). hour = $2,805.
Installation Group 5, 36 work-hours x $85 per 4,701 7,761.............. 31,044.
Configuration 1 (4 airplanes). hour = $3,060.
Torque Bracket Assembly and Bond 12 work-hours x $85 per 0 Up to $1,020....... Up to $689,520.
Tests Groups 1-5, Configuration hour = $1,020.
2 (Up to 676 airplanes).
General Visual Inspection Groups 7 work-hours x $85 per 0 Up to $595......... Up to $402,220.
1-5, Configuration 3 (Up to 676 hour = $595.
airplanes).
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary repairs that
would be required based on the results of the inspection. We have no
way of determining the number of aircraft that might need these
repairs:
On-Condition Costs
------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
------------------------------------------------------------------------
Adjust Wire Bundle and Install 1 work-hour x $0 $85
Sleeve, Group 1-5, $85 per hour =
Configuration 1. $85.
Inspection, Repair, and 1 work-hour x 0 85
Installation Change, Group 1- $85 per hour =
5, Configuration 2. $85.
Inspection, Repair, 5 work-hours x 0 425
Installation Change, and $85 per hour =
Test, Group 1-5, $425.
Configuration 3.
------------------------------------------------------------------------
We have received no definitive data that would enable us to provide
cost estimates for the parts needed 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
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
[[Page 21648]]
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):
2015-08-01 The Boeing Company: Amendment 39-18137; Docket No. FAA-
2011-0475; Directorate Identifier 2010-NM-199-AD.
(a) Effective Date
This AD is effective May 26, 2015.
(b) Affected ADs
None.
(c) Applicability
This AD applies to The Boeing Company Model 757-200, -200PF, -
200CB, and -300 series airplanes; certificated in any category; as
identified in Boeing Service Bulletin 757-27A0152, Revision 3, dated
October 28, 2013, as revised by Boeing Service Bulletin 757-27A0152,
Revision 4, dated August 26, 2014.
(d) Subject
Air Transport Association (ATA) of America Code 27, Flight
Controls.
(e) Unsafe Condition
This AD was prompted by numerous reports of unintended lateral
oscillations during the final approach, just before landing. We are
issuing this AD to reduce the chance of unintended lateral
oscillations near touchdown, which could result in loss of lateral
control of the airplane, and consequent airplane damage or injury to
flightcrew and passengers.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Installation and Inspection
Within 60 months after the effective date of this AD, do the
applicable actions specified in paragraph (g)(1), (g)(2), or (g)(3)
of this AD.
(1) For Configuration 1 airplanes defined in Boeing Service
Bulletin 757-27A0152, Revision 3, dated October 28, 2013, as revised
by Boeing Service Bulletin 757-27A0152, Revision 4, dated August 26,
2014: Install three bracket assemblies and three new relays, and
make changes to the wire bundles, in accordance with the
Accomplishment Instructions of Boeing Service Bulletin 757-27A0152,
Revision 3, dated October 28, 2013, as revised by Boeing Service
Bulletin 757-27A0152, Revision 4, dated August 26, 2014.
(2) For Configuration 2 airplanes defined in Boeing Service
Bulletin 757-27A0152, Revision 3, dated October 28, 2013, as revised
by Boeing Service Bulletin 757-27A0152, Revision 4, dated August 26,
2014: Torque the bracket assembly nuts and ground stud nuts, do bond
resistance tests to verify that bonding requirements are met, do a
general visual inspection to ensure that the three new relays do not
touch the adjacent wire bundles, and do all applicable related
investigative and corrective actions, in accordance with the
Accomplishment Instructions of Boeing Service Bulletin 757-27A0152,
Revision 3, dated October 28, 2013, as revised by Boeing Service
Bulletin 757-27A0152, Revision 4, dated August 26, 2014. Do all
applicable related investigative and corrective actions before
further flight.
(3) For Configuration 3 airplanes defined in Boeing Service
Bulletin 757-27A0152, Revision 3, dated October 28, 2013, as revised
by Boeing Service Bulletin 757-27A0152, Revision 4, dated August 26,
2014: Do a general visual inspection to ensure that the three new
relays do not touch the adjacent wire bundles, and do all applicable
related investigative and corrective actions, in accordance with the
Accomplishment Instructions of Boeing Service Bulletin 757-27A0152,
Revision 3, dated October 28, 2013, as revised by Boeing Service
Bulletin 757-27A0152, Revision 4, dated August 26, 2014. Do all
applicable related investigative and corrective actions before
further flight.
(h) Credit for Previous Actions
This paragraph provides credit for actions required by paragraph
(g) of this AD, if those actions were performed before the effective
date of this AD using Boeing Service Bulletin 757-27A0152, Revision
2, dated May 25, 2012 (which is not incorporated by reference in
this AD); or Boeing Service Bulletin 757-27A0152, Revision 3, dated
October 28, 2013.
(i) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Los Angeles 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 (j)(1) of this AD.
Information may be emailed to: 9-ANM-LAACO-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, Los Angeles 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.
(j) Related Information
(1) For more information about this AD, contact Jeffrey Palmer,
Aerospace Engineer, Systems and Equipment Branch, ANM-130L, Los
Angeles Aircraft Certification Office (ACO), FAA, 3960 Paramount
Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5351; fax: 562-
627-5210; email: jeffrey.w.palmer@faa.gov.
(2) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (k)(3) and (k)(4) of this AD.
(k) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(i) Boeing Service Bulletin 757-27A0152, Revision 3, dated
October 28, 2013.
(ii) Boeing Service Bulletin 757-27A0152, Revision 4, dated
August 26, 2014.
(3) For Boeing service information identified in this AD,
contact Boeing Commercial Airplanes, Attention: Data & Services
Management, P. O. Box 3707, MC 2H-65, Seattle, WA 98124-2207;
telephone 206-544-5000, extension 1; fax 206-766-5680; Internet
https://www.myboeingfleet.com.
(4) You may view this service information at FAA, Transport
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For
information on the availability of this material at the FAA, call
425-227-1221.
(5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
[[Page 21649]]
Issued in Renton, Washington, on April 3, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2015-08407 Filed 4-17-15; 08:45 am]
BILLING CODE 4910-13-P
