Airworthiness Directives; The Boeing Company Model 757 Airplanes, 10226-10230 [2011-4013]
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Federal Register / Vol. 76, No. 37 / Thursday, February 24, 2011 / Rules and Regulations
European regulatory process upon issuance
by the type certificate holder. The FAA must
mandate any such changes through
rulemaking, specifically in this case an
airworthiness directive.
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Other FAA AD Provisions
(g) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, Standards Office,
FAA, has the authority to approve AMOCs
for this AD, if requested using the procedures
found in 14 CFR 39.19. Send information to
ATTN: Sarjapur Nagarajan, Aerospace
Engineer, FAA, Small Airplane Directorate,
901 Locust, Room 301, Kansas City, Missouri
64106; telephone: (816) 329–4145; fax: (816)
329–4090. Before using any approved AMOC
on any airplane to which the AMOC applies,
notify your appropriate principal inspector
(PI) in the FAA Flight Standards District
Office (FSDO), or lacking a PI, your local
FSDO.
(2) Airworthy Product: For any
requirement in this AD to obtain corrective
actions from a manufacturer or other source,
use these actions if they are FAA-approved.
Corrective actions are considered FAAapproved if they are approved by the State
of Design Authority (or their delegated
agent). You are required to assure the product
is airworthy before it is returned to service.
(3) Reporting Requirements: For any
reporting requirement in this AD, 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.
Related Information
(h) Refer to Piaggio Aero Industries S.p.A.
Service Bulletin (Mandatory)
N.: SB 80–0275, Rev. N. 0, dated June 15,
2009; Piaggio Aero P.180 AVANTI
Temporary Change No. 7 to the Pilot’s
Operating Handbook and EASA Approved
Airplane Flight Manual Rep. 6591, issued:
February 24, 2009; and Piaggio Aero P.180
AVANTI II Temporary Change No. 11 to the
EASA Approved Airplane Flight Manual
Rep. 180–MAN–0010–01100, issued:
February 24, 2009, for related information.
For service information related to this AD,
contact Piaggio Aero Industries S.p.A., Via
Cibrario, 4–16154 Genoa, Italy; phone: +39
010 6481 353; fax: +39 010 6481 881; e-mail:
airworthiness@piaggioaero.it; Internet: https://
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www.piaggioaero.com. You may review
copies of the referenced service information
at the FAA, Small Airplane Directorate, 901
Locust, Kansas City, Missouri 64106. For
information on the availability of this
material at the FAA, call 816–329–4148.
Material Incorporated by Reference
(i) You must use Piaggio Aero Industries
S.p.A. Service Bulletin (Mandatory) N.: SB
80–0275, Rev. N. 0, dated June 15, 2009;
Piaggio Aero P.180 AVANTI Temporary
Change No. 7 to the Pilot’s Operating
Handbook and EASA Approved Airplane
Flight Manual Rep. 6591, issued: February
24, 2009; and Piaggio Aero P.180 AVANTI II
Temporary Change No. 11 to the EASA
Approved Airplane Flight Manual Rep. 180–
MAN–0010–01100, issued: February 24,
2009, to do the actions required by this AD,
unless the AD specifies otherwise.
(1) The Director of the Federal Register
approved the incorporation by reference of
this service information under 5 U.S.C.
552(a) and 1 CFR part 51.
(2) For service information identified in
this AD, contact Piaggio Aero Industries
S.p.A., Via Cibrario, 4–16154 Genoa, Italy;
phone: +39 010 6481 353; fax: +39 010 6481
881; e-mail: airworthiness@piaggioaero.it;
Internet: https://www.piaggioaero.com.
(3) You may review copies of the
referenced service information at the FAA,
Small Airplane Directorate, 901 Locust,
Kansas City, Missouri 64106. For information
on the availability of this material at the
FAA, call 816–329–4148.
(4) You may also review copies of the
service information incorporated by reference
for this AD 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/
code_of_federal_regulations/ibr_
locations.html.
Issued in Kansas City, Missouri, on
February 14, 2011.
Earl Lawrence,
Manager, Small Airplane Directorate, Aircraft
Certification Service.
[FR Doc. 2011–3923 Filed 2–23–11; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2010–0698; Directorate
Identifier 2009–NM–264–AD; Amendment
39–16613; AD 2011–05–04]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Model 757 Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are superseding an
existing airworthiness directive (AD) for
SUMMARY:
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the products listed above. That AD
currently requires sealing the fasteners
on the front and rear spars inside the
left and right main fuel tanks and on the
rear spar and lower panel of the center
fuel tank. That AD also requires
inspections of the wire bundle support
installations to verify if certain clamps
are installed and if Teflon sleeving
covers the wire bundles inside the left
and right equipment cooling system
bays, on the left and right rear spars,
and on the left and right front spars; and
corrective actions if necessary. This new
AD also requires sealing the additional
fasteners on the rear spar inside the left
and right main fuel tanks. This AD was
prompted by a fuel system review
conducted by the manufacturer. We
have received reports from the
manufacturer that additional fasteners
in the main fuel tanks must be sealed for
lightning strike protection. We are
issuing this AD to detect and correct
improper wire bundle support
installation and sleeving and to prevent
improperly sealed fasteners in the main
and center fuel tanks from becoming an
ignition source, in the event of a fault
current or lightning strike, which could
result in a fuel tank explosion and
consequent loss of the airplane.
DATES: This AD is effective March 31,
2011.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of March 31, 2011.
ADDRESSES: For service information
identified in this AD, contact Boeing
Commercial Airplanes, Attention: Data
& Services Management, P.O. Box 3707,
MC 2H–65, Seattle, Washington 98124–
2207; telephone 206–544–5000,
extension 1; fax 206–766–5680; e-mail
me.boecom@boeing.com; Internet
https://www.myboeingfleet.com. You
may review copies of the referenced
service information at the FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington.
For information on the availability of
this material at the FAA, call 425–227–
1221.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; 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
Document Management Facility, U.S.
Department of Transportation, Docket
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Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue, SE., Washington,
DC 20590.
FOR FURTHER INFORMATION CONTACT: Tak
Kobayashi, Aerospace Engineer,
Propulsion Branch, ANM–140S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 917–6499; fax (425) 917–6590.;
e-mail: Takahisa.Kobayashi@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede airworthiness
directive (AD) 2008–23–19, Amendment
39–15740 (73 FR 71534, November 25,
2008). That AD applies to the specified
products. The NPRM published in the
Federal Register on July 23, 2010 (75 FR
43097). That NPRM proposed to
continue to require sealing the fasteners
on the front and rear spars inside the
left and right main fuel tanks and on the
rear spar and lower panel of the center
fuel tank. That NPRM also proposed to
require inspections of the wire bundle
support installations to verify if certain
clamps are installed and if Teflon
sleeving covers the wire bundles inside
the left and right equipment cooling
system bays, on the left and right rear
spars, and on the left and right front
spars; corrective actions if necessary;
and sealing of additional fasteners on
the rear spar inside the left and right
main fuel tanks.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comments
received on the proposal and the FAA’s
response to each comment.
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Concurrence With the NPRM
Boeing concurs with the contents of
the proposed rule.
Request To Revise the Compliance
Time
FedEx, US Airways, Delta, European
Air Transport Leipzig GmbH (European
Air)/DHL Air requested a change in the
compliance time. FedEx, Delta, and US
Airways requested that we change the
compliance time from ‘‘60 months after
December 30, 2008,’’ to ‘‘60 months after
the effective date of the final rule’’ in
paragraph (h) of the NPRM. European
Air/DHL Air requested an extension of
the compliance time from 60 months to
a minimum of 72 months for airplanes
that have already been modified in
accordance with Boeing Alert Service
Bulletin 757–57A0064, dated July 16,
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16:10 Feb 23, 2011
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2007. FedEx and Delta stated that fuel
tank access occurs at 72-month
intervals. European Air/DHL Air stated
that they purge the fuel tanks during a
4C-check corresponding to 72 months,
12,000 flight cycles, or 24,000 flight
hours, whichever occurs first. European
Air/DHL Air stated that the proposed
compliance time does not allow a
suitable maintenance opportunity to
accomplish the additional work without
disturbing the scheduled maintenance
activities. Delta stated that the proposed
compliance time allows approximately
3 years from the effective date of the
final rule. Delta considered this
requirement an undue burden that is not
justified. Delta stated that the SFAR88
initiative and the Aging Aircraft
initiatives generally have a timeline of
60 months to upgrade the airplanes
based on the FAA harmonization policy
of the aging airplane programs per ‘‘Fuel
Tank Safety Compliance Extension
(Final Rule) and Aging Airplane
Program Update (Request for
Comments)’’ (69 FR 45936, July 30,
2004).
We agree that the compliance time in
paragraph (h) of this AD should be
changed to ‘‘within 60 months after the
effective date of this AD’’ to avoid
causing an undue burden on operators
who have already accomplished the
modification in accordance with Boeing
Alert Service Bulletin 757–57A0064,
dated July 16, 2007. In addition, we
consider the following condition may
warrant this change in the compliance
time. The additional work specified in
Boeing Alert Service Bulletin 757–
57A0064, Revision 1, dated October 5,
2009, is intended to provide an
additional layer of protection to the
main fuel tanks to prevent ignition
sources from occurring inside those
tanks under a lightning strike event. The
existing fastener installation is able to
tolerate lightning current without
introducing ignition sources inside the
main fuel tanks if no failure conditions
exist. The additional work of sealing the
affected fasteners will add a fail-safe
design feature to the existing fastener
installation so that no ignition sources
are introduced under the presence of
single failures. Because of this, we
consider that an acceptable level of
safety would still be provided with this
change in the compliance time. We have
also limited the airplanes affected by
paragraph (h) of this AD to airplanes on
which Boeing Alert Service Bulletin
757–57A0064, dated July 16, 2007, was
done before the effective date of this
AD.
We have also revised paragraph (g) of
this AD to add the following sentence:
‘‘As of the effective date of this AD, only
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Boeing Alert Service Bulletin 757–
57A0064, Revision 1, dated October 5,
2009, may be used.’’
We do not agree with extending the
compliance time to 72 months. In
developing an appropriate compliance
time, we considered the safety
implications, parts availability, and
normal maintenance schedules for
timely replacement of the fasteners. In
consideration of all of these factors, we
determined that the 60-month
compliance time represents an
acceptable interval in which the
fasteners can be sealed in a timely
manner, while still maintaining an
acceptable level of safety. According to
the provisions of paragraph (j) of this
AD, operators may request an
alternative method of compliance
(AMOC) to request a longer compliance
time, if the request is submitted with
substantiating data that proves that the
longer compliance time will provide an
acceptable level of safety. We have not
changed the AD further in this regard.
Request To Allow Modification in
Accordance With Original Issue of
Service Bulletin
European Air/DHL Air requested that
we allow the modification, in
accordance with Boeing Alert Service
Bulletin 757–57A0064, dated July 16,
2007, and Boeing Multi Operator
Message (MOM)
1–1046487761, dated November 6, 2008,
as an accepted means of compliance.
European Air stated that they started
incorporating the modifications
specified in Boeing Alert Service
Bulletin 757–57A0064, dated July 16,
2007, and Boeing MOM 1–1046487761,
dated November 6, 2008, before AD
2008–23–19 was issued.
We infer that European Air/DHL Air
are requesting that we allow the
modification done in accordance with
Boeing Alert Service Bulletin 757–
57A0064, dated July 16, 2007, and
Boeing MOM 1–1046487761, dated
November 6, 2008, as a means of
compliance with paragraphs (g) and (h)
of this AD. We do not agree. Boeing
Alert Service Bulletin 757–57A0064,
dated July 16, 2007, is not sufficient to
address the unsafe condition, and
Boeing MOM 1–1046487761, dated
November 6, 2008, merely informs
operators of a forthcoming revision to
Boeing Alert Service Bulletin 757–
57A0064, dated July 16, 2007, which
will include additional work of sealing
40 fasteners that are not identified in
Boeing Alert Service Bulletin 757–
57A0064, dated July 16, 2007. Boeing
MOM 1–1046487761, dated November
6, 2008, refers to two sketches that
provide the locations of additional
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fasteners that must be sealed. Those
sketches can help operators to
accomplish the additional work, but
they only provide figures that are
applicable to certain airplane groups
identified in Boeing Alert Service
Bulletin 757–57A0064, dated July 16,
2007. In addition, those sketches are not
a published document and cannot be
incorporated by reference in the AD. We
have determined that it is inappropriate
to include Boeing MOM 1–1046487761,
dated November 6, 2008, as an accepted
means to comply with the actions
required by this AD. However, operators
who have used those data can still
request approval of an AMOC, in
accordance with paragraph (j) of this
AD. No change has been made to the AD
in this regard.
Request To Clarify Instructions for
Continued Airworthiness (ICA)
Continental stated that proper ICA
must be provided in order to prevent
inadvertent reversal of implemented
changes that can lead to violation of
requirements of the SFAR88 program as
well as the final rule. Continental
Airlines requested that we coordinate
with Boeing to ensure proper
instructions are provided.
We acknowledge the commenter’s
concern. Operators and owners are
responsible for ensuring that the
configuration mandated by this AD is
maintained in accordance with section
39.7 of the Federal Aviation Regulations
(14 CFR 39.7). If any new airworthiness
limitations (AWLs) related to any of the
design features mandated by this AD are
developed, we may consider additional
rulemaking to mandate incorporation of
those AWLs into operators’ maintenance
programs. The FAA is working with
industry to evaluate potential changes to
the AD process that are intended to
more clearly identify how to maintain
configurations that are required for AD
compliance. We have not changed the
AD regarding this issue.
Request To Allow Alternative Color of
Lacing Tape
Continental raised a question
regarding the color of lacing tape
specified in Boeing Alert Service
Bulletins 757–57A0064, dated July 16,
2007; and Revision 1, dated October 5,
2009. Continental stated that those
service bulletins require use of a lacing
tape identified as BMS 13–54, Type III,
Class 1, Finish C, Black. Continental
stated that a specific color of the lacing
tape should not be mandated.
Continental stated that Boeing Standard
Wiring Process Manual 20–10–11 makes
no distinction regarding the color of the
lacing tape for sleeve installation.
We infer that Continental is
requesting that we allow any color as
long as the lacing tape is BMS 13–54,
Type III, Class 1, Finish C. We agree to
allow the use of white lacing tape
because white is a neutral color that is
not associated with any specific color
code requirement. However, we disagree
with allowing the use of lacing tape
with colors other than black or white
because use of colors other than black
or white may be inconsistent with colorcoding used by the manufacturer or
operator, and could create confusion in
wiring identification. We have granted a
global AMOC to allow the use of lacing
tape BMS 13–54, Type III, Class 1,
Finish C, with white color in place of
black color when accomplishing the
actions specified in Boeing Alert Service
Bulletin 757–57A0064, dated July 16,
2007, as required by paragraph (f) of AD
2008–23–19, Amendment 39–15740.
Paragraph (i) has been added to this AD
to reflect these changes.
Conclusion
We reviewed the relevant data,
considered the comments received, and
determined that air safety and the
public interest require adopting the AD
with the changes described previously.
We have determined that these changes:
• Are consistent with the intent that
was proposed in the NPRM for
correcting the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM.
We also determined that these
changes will not increase the economic
burden on any operator or increase the
scope of the AD.
Costs of Compliance
We estimate that this AD affects 667
airplanes of U.S. registry.
We estimate the following costs to
comply with this AD:
ESTIMATED COSTS
Action
Labor cost
Fastener Sealing and Inspections (required by AD 2008–23–19).
Up to 545 work-hours × $85 per hour
= Up to $46,325 per airplane depending on configuration.
Up to 30 work-hours × $85 per hour =
Up to $2,550.
Main Tank Fastener Sealing (new proposed action).
We estimate the following costs to do
any necessary replacements that would
Parts cost
Cost per product
Cost on U.S.
operators
$325
Up to $46,650 ..........
Up to $31,115,550.
$0
Up to $2,550 ............
Up to $1,700,850.
be required based on the results of the
proposed inspection. We have no way of
determining the number of aircraft that
might need these replacements:
ON-CONDITION COSTS
Labor cost
Clamp Replacement ................................................
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Action
Up to 6 work-hours × $85 per hour = $510 ............
According to the manufacturer, some
of the costs of this AD may be covered
under warranty, thereby reducing the
cost impact on affected individuals. We
do not control warranty coverage for
affected individuals. As a result, we
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16:10 Feb 23, 2011
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Parts cost
have included all costs in our cost
estimate.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
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Cost per product
$0
Up to $510.
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,
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Federal Register / Vol. 76, No. 37 / Thursday, February 24, 2011 / Rules and Regulations
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.
Effective Date
Regulatory Findings
(d) Air Transport Association (ATA) of
America Code 57: Wings.
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.
(a) This airworthiness directive (AD) is
effective March 31, 2011.
Affected ADs
(b) This AD supersedes AD 2008–23–19,
Amendment 39–15740.
Applicability
(c) This AD applies to all The Boeing
Company Model 757–200, –200CB, –200PF,
and –300 series airplanes, certificated in any
category.
Subject
Unsafe Condition
(e) This AD results from a fuel system
review conducted by the manufacturer. We
have received reports from the manufacturer
that additional fasteners in the main fuel
tanks must be sealed for lightning strike
protection. The Federal Aviation
Administration is issuing this AD to detect
and correct improper wire bundle support
installation and sleeving and to prevent
improperly sealed fasteners in the main and
center fuel tanks from becoming an ignition
source, in the event of a fault current or
lightning strike, which could result in a fuel
tank explosion and consequent loss of the
airplane.
Compliance
(f) You are responsible for having the
actions required by this AD performed within
the compliance times specified, unless the
actions have already been done.
Restatement of Requirements of AD 2008–
23–19, With Revised Service Information
List of Subjects in 14 CFR Part 39
Fastener Sealing and Inspections
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
(g) Within 60 months after December 30,
2008 (the effective date of AD 2008–23–19),
seal the applicable fasteners and do the
general visual inspections of the wire bundle
support installations, and do all the
applicable corrective actions before further
flight, by accomplishing all of the applicable
actions specified in the Accomplishment
Instructions of Boeing Alert Service Bulletin
757–57A0064, dated July 16, 2007; or Part 1
through Part 10 of the Work Instructions of
Boeing Alert Service Bulletin 757–57A0064,
Revision 1, dated October 5, 2009. As of the
effective date of this AD, only Boeing Alert
Service Bulletin 757–57A0064, Revision 1,
dated October 5, 2009, may be used.
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
2. The FAA amends § 39.13 by
removing airworthiness directive (AD)
2008–23–19, Amendment 39–15740
(73 FR 71534, November 25, 2008), and
adding the following new AD:
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■
2011–05–04 The Boeing Company:
Amendment 39–16613; Docket No.
FAA–2010–0698; Directorate Identifier
2009–NM–264–AD.
VerDate Mar<15>2010
16:10 Feb 23, 2011
New Requirements of This AD
Fastener Sealing on the Rear Spar
[Amended]
Jkt 223001
(h) For airplanes on which the actions in
Boeing Alert Service Bulletin 757–57A0064,
dated July 16, 2007, were accomplished
before the effective date of this AD: Within
60 months after the effective date of this AD,
seal the fasteners on the rear spar inside the
left and right main fuel tanks, in accordance
with Part 11 of the Work Instructions of
Boeing Alert Service Bulletin 757–57A0064,
Revision 1, dated October 5, 2009.
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10229
Acceptable Lacing Tape for Repair Actions
(i) Where Boeing Alert Service Bulletin
757–57A0064, Revision 1, dated October 5,
2009, describes the use of lacing tape BMS
13–54, Type III, Class 1, Finish C, Black, this
AD also allows the use of lacing tape BMS
13–54, Type III, Class 1, Finish C, White, as
an alternative.
Alternative Methods of Compliance
(AMOCs)
(j)(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. Send information to ATTN: Tak
Kobayashi, Aerospace Engineer, Propulsion
Branch, ANM–140S, FAA, Seattle Aircraft
Certification Office, 1601 Lind Avenue, SW.,
Renton, Washington 98057–3356; telephone
(425) 917–6499; fax (425) 917–6590.
Information may be e-mailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov.
(2) To request a different method of
compliance or a different compliance time
for this AD, follow the procedures in 14 CFR
39.19. Before using any approved AMOC,
notify your 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.
(3) AMOCs approved previously in
accordance with AD 2008–23–19,
Amendment 39–15740, are approved as
AMOCs for the corresponding provisions of
paragraph (g) of this AD.
Related Information
(k) For more information about this AD,
contact Tak Kobayashi, Aerospace Engineer,
Propulsion Branch, ANM–140S, FAA, Seattle
Aircraft Certification Office, 1601 Lind
Avenue, SW., Renton, Washington 98057–
3356; telephone (425) 917–6499; fax (425)
917–6590; e-mail:
Takahisa.Kobayashi@faa.gov.
Material Incorporated by Reference
(l) You must use Boeing Alert Service
Bulletin 757–57A0064, Revision 1, dated
October 5, 2009, to do the actions required
by this AD, unless the AD specifies
otherwise.
(1) The Director of the Federal Register
approved the incorporation by reference of
this service information under 5 U.S.C.
552(a) and 1 CFR part 51.
(2) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Data & Services
Management, P.O. Box 3707, MC 2H–65,
Seattle, Washington 98124–2207; telephone
206–544–5000, extension 1; fax 206–766–
5680; e-mail me.boecom@boeing.com;
Internet https://www.myboeingfleet.com.
(3) You may review copies of the service
information at the FAA, 1601 Lind Avenue,
SW., Renton, Washington. For information
on the availability of this material at the
FAA, call 425–227–1221.
(4) You may also review copies of the
service information that is incorporated by
reference at the National Archives and
Records Administration (NARA). For
information on the availability of this
E:\FR\FM\24FER1.SGM
24FER1
10230
Federal Register / Vol. 76, No. 37 / Thursday, February 24, 2011 / Rules and Regulations
material at an NARA facility, call 202–741–
6030, or go to https://www.archives.gov/
federal_register/code_of_federal_regulations/
ibr_locations.html.
Issued in Renton, Washington, on February
14, 2011.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2011–4013 Filed 2–23–11; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2010–0859; Directorate
Identifier 2010–NM–113–AD; Amendment
39–16614; AD 2011–05–05]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A330–200 and –300 Series Airplanes
and Model A340–200, –300, –500, and
–600 Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for the
products listed above. This AD results
from mandatory continuing
airworthiness information (MCAI)
originated by an aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as:
*
*
*
*
*
SUMMARY:
* * * [T]here is a possible path for fluid
ingress, resulting in connector internal arcing
and hydraulic system malfunction. In
addition, as the connectors are located in
areas adjacent to fuel tanks, such arcing
associated with the presence of a fuel leakage
could lead to an uncontrolled fire.
*
*
*
*
*
We are issuing this AD to require
actions to correct the unsafe condition
on these products.
DATES: This AD becomes effective
March 31, 2011.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of March 31, 2011.
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov or in person at the
U.S. Department of Transportation,
Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue, SE.,
Washington, DC.
FOR FURTHER INFORMATION CONTACT:
Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 227–1138; fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
apply to the specified products. That
NPRM was published in the Federal
Register on September 29, 2010 (75 FR
60010). That NPRM proposed to correct
an unsafe condition for the specified
products. The MCAI states:
Several A330 and A340 operators have
reported in service occurrences of hydraulic
pump electrical motor connector internal
arcing, resulting in:
—Either false hydraulic system overheat
Electronic Centralized Aircraft Monitoring
(ECAM) warnings
—and/or hydraulic pump electrical motor
malfunction.
Investigations have shown that, due to the
manufacturing tolerances of the cables and
the connectors rear grommet, there is a
possible path for fluid ingress, resulting in
connector internal arcing and hydraulic
system malfunction. In addition, as the
connectors are located in areas adjacent to
fuel tanks, such arcing associated with the
presence of a fuel leakage could lead to an
uncontrolled fire.
In order to protect the hydraulic pump
electrical motor connectors against fluid
ingress from the rear of the connector
grommet and prevent false hydraulic system
overheat ECAM warnings and/or hydraulic
pump electrical motor malfunction, this AD
requires modification of the three hydraulic
pump electrical motor connectors associated
to the Blue, Yellow and Green hydraulic
systems.
This Revision 1 is issued to delete Airbus
modifications 55923S18878 and
55924S19452 from the applicability of this
AD.
The modification adds heat shrink
sleeves to certain cable contacts and a
sealing plug to the connector free cavity.
You may obtain further information by
examining the MCAI in the AD docket.
Relevant Service Information
The NPRM referred to the service
information in the following table as the
applicable sources of service
information.
TABLE—SERVICE INFORMATION CITED IN THE NPRM
Airplane
model—
Airbus Mandatory Service Bulletin—
A330 .................
A340 .................
A340 .................
A330–92–3088, including Appendix 01 ........................................................................
A340–92–4081, including Appendix 01 ........................................................................
A340–92–5053, including Appendix 01 ........................................................................
Airbus has released the service
information in the following table. No
additional work is necessary for
airplanes on which earlier revisions of
Revision—
the service information are done. We
have updated Tables 1 and 3 of the final
rule to refer to these sources of service
information. We have also updated
Dated—
01
01
01
February 22, 2010.
February 22, 2010.
February 22, 2010.
Table 2 of the final rule to give credit
for using Revision 01 of the service
information.
jlentini on DSKJ8SOYB1PROD with RULES
TABLE—REVISED SERVICE INFORMATION
Airplane
model—
Airbus Mandatory Service Bulletin—
A330 .................
A340 .................
A340 .................
A330–92–3088, including Appendix 01 ........................................................................
A340–92–4081, including Appendix 01 ........................................................................
A340–92–5053, including Appendix 01 ........................................................................
VerDate Mar<15>2010
16:10 Feb 23, 2011
Jkt 223001
PO 00000
Frm 00026
Revision—
Fmt 4700
Sfmt 4700
E:\FR\FM\24FER1.SGM
Dated—
02
02
02
24FER1
September 1, 2010.
September 1, 2010.
September 1, 2010.
]]>Agencies
[Federal Register Volume 76, Number 37 (Thursday, February 24, 2011)]
[Rules and Regulations]
[Pages 10226-10230]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-4013]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2010-0698; Directorate Identifier 2009-NM-264-AD;
Amendment 39-16613; AD 2011-05-04]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Model 757 Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are superseding an existing airworthiness directive (AD)
for the products listed above. That AD currently requires sealing the
fasteners on the front and rear spars inside the left and right main
fuel tanks and on the rear spar and lower panel of the center fuel
tank. That AD also requires inspections of the wire bundle support
installations to verify if certain clamps are installed and if Teflon
sleeving covers the wire bundles inside the left and right equipment
cooling system bays, on the left and right rear spars, and on the left
and right front spars; and corrective actions if necessary. This new AD
also requires sealing the additional fasteners on the rear spar inside
the left and right main fuel tanks. This AD was prompted by a fuel
system review conducted by the manufacturer. We have received reports
from the manufacturer that additional fasteners in the main fuel tanks
must be sealed for lightning strike protection. We are issuing this AD
to detect and correct improper wire bundle support installation and
sleeving and to prevent improperly sealed fasteners in the main and
center fuel tanks from becoming an ignition source, in the event of a
fault current or lightning strike, which could result in a fuel tank
explosion and consequent loss of the airplane.
DATES: This AD is effective March 31, 2011.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in the AD as of March 31,
2011.
ADDRESSES: For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone 206-
544-5000, extension 1; fax 206-766-5680; e-mail me.boecom@boeing.com;
Internet https://www.myboeingfleet.com. You may review copies of the
referenced service information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information
on the availability of this material at the FAA, call 425-227-1221.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov; 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 Document Management Facility,
U.S. Department of Transportation, Docket
[[Page 10227]]
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Tak Kobayashi, Aerospace Engineer,
Propulsion Branch, ANM-140S, FAA, Seattle Aircraft Certification
Office, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone
(425) 917-6499; fax (425) 917-6590.; e-mail:
Takahisa.Kobayashi@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to supersede airworthiness directive (AD) 2008-23-19, Amendment
39-15740 (73 FR 71534, November 25, 2008). That AD applies to the
specified products. The NPRM published in the Federal Register on July
23, 2010 (75 FR 43097). That NPRM proposed to continue to require
sealing the fasteners on the front and rear spars inside the left and
right main fuel tanks and on the rear spar and lower panel of the
center fuel tank. That NPRM also proposed to require inspections of the
wire bundle support installations to verify if certain clamps are
installed and if Teflon sleeving covers the wire bundles inside the
left and right equipment cooling system bays, on the left and right
rear spars, and on the left and right front spars; corrective actions
if necessary; and sealing of additional fasteners on the rear spar
inside the left and right main fuel tanks.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the proposal
and the FAA's response to each comment.
Concurrence With the NPRM
Boeing concurs with the contents of the proposed rule.
Request To Revise the Compliance Time
FedEx, US Airways, Delta, European Air Transport Leipzig GmbH
(European Air)/DHL Air requested a change in the compliance time.
FedEx, Delta, and US Airways requested that we change the compliance
time from ``60 months after December 30, 2008,'' to ``60 months after
the effective date of the final rule'' in paragraph (h) of the NPRM.
European Air/DHL Air requested an extension of the compliance time from
60 months to a minimum of 72 months for airplanes that have already
been modified in accordance with Boeing Alert Service Bulletin 757-
57A0064, dated July 16, 2007. FedEx and Delta stated that fuel tank
access occurs at 72-month intervals. European Air/DHL Air stated that
they purge the fuel tanks during a 4C-check corresponding to 72 months,
12,000 flight cycles, or 24,000 flight hours, whichever occurs first.
European Air/DHL Air stated that the proposed compliance time does not
allow a suitable maintenance opportunity to accomplish the additional
work without disturbing the scheduled maintenance activities. Delta
stated that the proposed compliance time allows approximately 3 years
from the effective date of the final rule. Delta considered this
requirement an undue burden that is not justified. Delta stated that
the SFAR88 initiative and the Aging Aircraft initiatives generally have
a timeline of 60 months to upgrade the airplanes based on the FAA
harmonization policy of the aging airplane programs per ``Fuel Tank
Safety Compliance Extension (Final Rule) and Aging Airplane Program
Update (Request for Comments)'' (69 FR 45936, July 30, 2004).
We agree that the compliance time in paragraph (h) of this AD
should be changed to ``within 60 months after the effective date of
this AD'' to avoid causing an undue burden on operators who have
already accomplished the modification in accordance with Boeing Alert
Service Bulletin 757-57A0064, dated July 16, 2007. In addition, we
consider the following condition may warrant this change in the
compliance time. The additional work specified in Boeing Alert Service
Bulletin 757-57A0064, Revision 1, dated October 5, 2009, is intended to
provide an additional layer of protection to the main fuel tanks to
prevent ignition sources from occurring inside those tanks under a
lightning strike event. The existing fastener installation is able to
tolerate lightning current without introducing ignition sources inside
the main fuel tanks if no failure conditions exist. The additional work
of sealing the affected fasteners will add a fail-safe design feature
to the existing fastener installation so that no ignition sources are
introduced under the presence of single failures. Because of this, we
consider that an acceptable level of safety would still be provided
with this change in the compliance time. We have also limited the
airplanes affected by paragraph (h) of this AD to airplanes on which
Boeing Alert Service Bulletin 757-57A0064, dated July 16, 2007, was
done before the effective date of this AD.
We have also revised paragraph (g) of this AD to add the following
sentence: ``As of the effective date of this AD, only Boeing Alert
Service Bulletin 757-57A0064, Revision 1, dated October 5, 2009, may be
used.''
We do not agree with extending the compliance time to 72 months. In
developing an appropriate compliance time, we considered the safety
implications, parts availability, and normal maintenance schedules for
timely replacement of the fasteners. In consideration of all of these
factors, we determined that the 60-month compliance time represents an
acceptable interval in which the fasteners can be sealed in a timely
manner, while still maintaining an acceptable level of safety.
According to the provisions of paragraph (j) of this AD, operators may
request an alternative method of compliance (AMOC) to request a longer
compliance time, if the request is submitted with substantiating data
that proves that the longer compliance time will provide an acceptable
level of safety. We have not changed the AD further in this regard.
Request To Allow Modification in Accordance With Original Issue of
Service Bulletin
European Air/DHL Air requested that we allow the modification, in
accordance with Boeing Alert Service Bulletin 757-57A0064, dated July
16, 2007, and Boeing Multi Operator Message (MOM) 1-1046487761, dated
November 6, 2008, as an accepted means of compliance. European Air
stated that they started incorporating the modifications specified in
Boeing Alert Service Bulletin 757-57A0064, dated July 16, 2007, and
Boeing MOM 1-1046487761, dated November 6, 2008, before AD 2008-23-19
was issued.
We infer that European Air/DHL Air are requesting that we allow the
modification done in accordance with Boeing Alert Service Bulletin 757-
57A0064, dated July 16, 2007, and Boeing MOM 1-1046487761, dated
November 6, 2008, as a means of compliance with paragraphs (g) and (h)
of this AD. We do not agree. Boeing Alert Service Bulletin 757-57A0064,
dated July 16, 2007, is not sufficient to address the unsafe condition,
and Boeing MOM 1-1046487761, dated November 6, 2008, merely informs
operators of a forthcoming revision to Boeing Alert Service Bulletin
757-57A0064, dated July 16, 2007, which will include additional work of
sealing 40 fasteners that are not identified in Boeing Alert Service
Bulletin 757-57A0064, dated July 16, 2007. Boeing MOM 1-1046487761,
dated November 6, 2008, refers to two sketches that provide the
locations of additional
[[Page 10228]]
fasteners that must be sealed. Those sketches can help operators to
accomplish the additional work, but they only provide figures that are
applicable to certain airplane groups identified in Boeing Alert
Service Bulletin 757-57A0064, dated July 16, 2007. In addition, those
sketches are not a published document and cannot be incorporated by
reference in the AD. We have determined that it is inappropriate to
include Boeing MOM 1-1046487761, dated November 6, 2008, as an accepted
means to comply with the actions required by this AD. However,
operators who have used those data can still request approval of an
AMOC, in accordance with paragraph (j) of this AD. No change has been
made to the AD in this regard.
Request To Clarify Instructions for Continued Airworthiness (ICA)
Continental stated that proper ICA must be provided in order to
prevent inadvertent reversal of implemented changes that can lead to
violation of requirements of the SFAR88 program as well as the final
rule. Continental Airlines requested that we coordinate with Boeing to
ensure proper instructions are provided.
We acknowledge the commenter's concern. Operators and owners are
responsible for ensuring that the configuration mandated by this AD is
maintained in accordance with section 39.7 of the Federal Aviation
Regulations (14 CFR 39.7). If any new airworthiness limitations (AWLs)
related to any of the design features mandated by this AD are
developed, we may consider additional rulemaking to mandate
incorporation of those AWLs into operators' maintenance programs. The
FAA is working with industry to evaluate potential changes to the AD
process that are intended to more clearly identify how to maintain
configurations that are required for AD compliance. We have not changed
the AD regarding this issue.
Request To Allow Alternative Color of Lacing Tape
Continental raised a question regarding the color of lacing tape
specified in Boeing Alert Service Bulletins 757-57A0064, dated July 16,
2007; and Revision 1, dated October 5, 2009. Continental stated that
those service bulletins require use of a lacing tape identified as BMS
13-54, Type III, Class 1, Finish C, Black. Continental stated that a
specific color of the lacing tape should not be mandated. Continental
stated that Boeing Standard Wiring Process Manual 20-10-11 makes no
distinction regarding the color of the lacing tape for sleeve
installation.
We infer that Continental is requesting that we allow any color as
long as the lacing tape is BMS 13-54, Type III, Class 1, Finish C. We
agree to allow the use of white lacing tape because white is a neutral
color that is not associated with any specific color code requirement.
However, we disagree with allowing the use of lacing tape with colors
other than black or white because use of colors other than black or
white may be inconsistent with color-coding used by the manufacturer or
operator, and could create confusion in wiring identification. We have
granted a global AMOC to allow the use of lacing tape BMS 13-54, Type
III, Class 1, Finish C, with white color in place of black color when
accomplishing the actions specified in Boeing Alert Service Bulletin
757-57A0064, dated July 16, 2007, as required by paragraph (f) of AD
2008-23-19, Amendment 39-15740. Paragraph (i) has been added to this AD
to reflect these changes.
Conclusion
We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
the AD with the changes described previously. We have determined that
these changes:
Are consistent with the intent that was proposed in the
NPRM for correcting the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM.
We also determined that these changes will not increase the
economic burden on any operator or increase the scope of the AD.
Costs of Compliance
We estimate that this AD affects 667 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Action Labor cost Parts cost Cost per product Cost on U.S. operators
--------------------------------------------------------------------------------------------------------------------------------------------------------
Fastener Sealing and Inspections Up to 545 work-hours x $325 Up to $46,650..................... Up to $31,115,550.
(required by AD 2008-23-19). $85 per hour = Up to
$46,325 per airplane
depending on
configuration.
Main Tank Fastener Sealing (new Up to 30 work-hours x $0 Up to $2,550...................... Up to $1,700,850.
proposed action). $85 per hour = Up to
$2,550.
--------------------------------------------------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary replacements
that would be required based on the results of the proposed inspection.
We have no way of determining the number of aircraft that might need
these replacements:
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Action Labor cost Parts cost Cost per product
----------------------------------------------------------------------------------------------------------------
Clamp Replacement................... Up to 6 work-hours x $0 Up to $510.
$85 per hour = $510.
----------------------------------------------------------------------------------------------------------------
According to the manufacturer, some of the costs of this AD may be
covered under warranty, thereby reducing the cost impact on affected
individuals. We do not control warranty coverage for affected
individuals. As a result, we have included all costs in our cost
estimate.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
subtitle VII,
[[Page 10229]]
part A, subpart III, section 44701, ``General requirements.'' Under
that section, Congress charges the FAA with promoting safe flight of
civil aircraft in air commerce by prescribing regulations for
practices, methods, and procedures the Administrator finds necessary
for safety in air commerce. This regulation is within the scope of that
authority because it addresses an unsafe condition that is likely to
exist or develop on products identified in this rulemaking action.
Regulatory Findings
We have determined that this AD will not have federalism
implications under Executive Order 13132. This AD will not have a
substantial direct effect on the States, on the relationship between
the national government and the States, or on the distribution of power
and responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation in Alaska, and
(4) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing airworthiness directive (AD)
2008-23-19, Amendment 39-15740 (73 FR 71534, November 25, 2008), and
adding the following new AD:
2011-05-04 The Boeing Company: Amendment 39-16613; Docket No. FAA-
2010-0698; Directorate Identifier 2009-NM-264-AD.
Effective Date
(a) This airworthiness directive (AD) is effective March 31,
2011.
Affected ADs
(b) This AD supersedes AD 2008-23-19, Amendment 39-15740.
Applicability
(c) This AD applies to all The Boeing Company Model 757-200, -
200CB, -200PF, and -300 series airplanes, certificated in any
category.
Subject
(d) Air Transport Association (ATA) of America Code 57: Wings.
Unsafe Condition
(e) This AD results from a fuel system review conducted by the
manufacturer. We have received reports from the manufacturer that
additional fasteners in the main fuel tanks must be sealed for
lightning strike protection. The Federal Aviation Administration is
issuing this AD to detect and correct improper wire bundle support
installation and sleeving and to prevent improperly sealed fasteners
in the main and center fuel tanks from becoming an ignition source,
in the event of a fault current or lightning strike, which could
result in a fuel tank explosion and consequent loss of the airplane.
Compliance
(f) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Restatement of Requirements of AD 2008-23-19, With Revised Service
Information
Fastener Sealing and Inspections
(g) Within 60 months after December 30, 2008 (the effective date
of AD 2008-23-19), seal the applicable fasteners and do the general
visual inspections of the wire bundle support installations, and do
all the applicable corrective actions before further flight, by
accomplishing all of the applicable actions specified in the
Accomplishment Instructions of Boeing Alert Service Bulletin 757-
57A0064, dated July 16, 2007; or Part 1 through Part 10 of the Work
Instructions of Boeing Alert Service Bulletin 757-57A0064, Revision
1, dated October 5, 2009. As of the effective date of this AD, only
Boeing Alert Service Bulletin 757-57A0064, Revision 1, dated October
5, 2009, may be used.
New Requirements of This AD
Fastener Sealing on the Rear Spar
(h) For airplanes on which the actions in Boeing Alert Service
Bulletin 757-57A0064, dated July 16, 2007, were accomplished before
the effective date of this AD: Within 60 months after the effective
date of this AD, seal the fasteners on the rear spar inside the left
and right main fuel tanks, in accordance with Part 11 of the Work
Instructions of Boeing Alert Service Bulletin 757-57A0064, Revision
1, dated October 5, 2009.
Acceptable Lacing Tape for Repair Actions
(i) Where Boeing Alert Service Bulletin 757-57A0064, Revision 1,
dated October 5, 2009, describes the use of lacing tape BMS 13-54,
Type III, Class 1, Finish C, Black, this AD also allows the use of
lacing tape BMS 13-54, Type III, Class 1, Finish C, White, as an
alternative.
Alternative Methods of Compliance (AMOCs)
(j)(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. Send information to
ATTN: Tak Kobayashi, Aerospace Engineer, Propulsion Branch, ANM-
140S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue,
SW., Renton, Washington 98057-3356; telephone (425) 917-6499; fax
(425) 917-6590. Information may be e-mailed to: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
(2) To request a different method of compliance or a different
compliance time for this AD, follow the procedures in 14 CFR 39.19.
Before using any approved AMOC, notify your 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.
(3) AMOCs approved previously in accordance with AD 2008-23-19,
Amendment 39-15740, are approved as AMOCs for the corresponding
provisions of paragraph (g) of this AD.
Related Information
(k) For more information about this AD, contact Tak Kobayashi,
Aerospace Engineer, Propulsion Branch, ANM-140S, FAA, Seattle
Aircraft Certification Office, 1601 Lind Avenue, SW., Renton,
Washington 98057-3356; telephone (425) 917-6499; fax (425) 917-6590;
e-mail: Takahisa.Kobayashi@faa.gov.
Material Incorporated by Reference
(l) You must use Boeing Alert Service Bulletin 757-57A0064,
Revision 1, dated October 5, 2009, to do the actions required by
this AD, unless the AD specifies otherwise.
(1) The Director of the Federal Register approved the
incorporation by reference of this service information under 5
U.S.C. 552(a) and 1 CFR part 51.
(2) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone
206-544-5000, extension 1; fax 206-766-5680; e-mail
me.boecom@boeing.com; Internet https://www.myboeingfleet.com.
(3) You may review copies of the service information at the FAA,
1601 Lind Avenue, SW., Renton, Washington. For information on the
availability of this material at the FAA, call 425-227-1221.
(4) You may also review copies of the service information that
is incorporated by reference at the National Archives and Records
Administration (NARA). For information on the availability of this
[[Page 10230]]
material at an NARA facility, call 202-741-6030, or go to https://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.
Issued in Renton, Washington, on February 14, 2011.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2011-4013 Filed 2-23-11; 8:45 am]
BILLING CODE 4910-13-P
