Airworthiness Directives; The Boeing Company Model 777-200, -200LR, -300, and -300ER Series Airplanes, 24345-24349 [2011-9917]
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Federal Register / Vol. 76, No. 84 / Monday, May 2, 2011 / Rules and Regulations
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 AD:
■
2011–09–12 Bombardier, Inc.: Amendment
39–16674. Docket No. FAA–2010–1157;
Directorate Identifier 2010–NM–137–AD.
Credit for Actions Accomplished in
Accordance With Previous Service
Information
Effective Date
(a) This airworthiness directive (AD)
becomes effective June 6, 2011.
Affected ADs
(b) None.
Applicability
(c) This AD applies to the Bombardier, Inc.
airplanes, certificated in any category,
identified in paragraphs (c)(1) and (c)(2) of
this AD.
(1) Model DHC–8–101, –102, –103, –106,
–201, –202, –301, –311, and –315, serial
numbers 003 through 566 inclusive.
(2) Model DHC–8–401, and –402 airplanes,
serial numbers 4001, 4003, 4004, 4006, and
4008 through 4274 inclusive.
Subject
(d) Air Transport Association (ATA) of
America Code 56: Windows.
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*
*
*
*
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.
Actions
(g) Within 6,000 flight hours or 36 months
after the effective date of this AD, whichever
occurs first, install a drain system in the
cockpit windshield lower frames, and do all
applicable related investigative and
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Jkt 223001
(h) For Models DHC–8–101, –102, –103,
–106, –201, –202, –301, –311, and –315
airplanes: Modification of the drain system is
also acceptable for compliance with the
requirements of paragraph (g) of this AD, if
done before the effective date of this AD, in
accordance with Bombardier Service Bulletin
8–53–78, dated December 23, 1999; Revision
A, dated June 7, 2001; Revision B, dated May
2, 2002; or Revision C, dated April 29, 2010.
FAA AD Differences
Note 1: This AD differs from the MCAI
and/or service information as follows: No
differences.
Other FAA AD Provisions
Reason
(e) The mandatory continuing
airworthiness information (MCAI) states:
There have been several in-service reports
of finding trapped water on the bottom of the
cockpit windshield frames (or lower
windshield frames) that resulted in either
corrosion or water ingress into the cockpit. In
one occurrence, the trapped water caused
severe corrosion of numerous anchor nuts
that secure the windshield to the lower
windshield frame, such that the intended
fastening function was seriously
compromised.
Corrosion of the lower windshield frames,
including the anchor nuts that secure the
windshield to the aircraft structure, can
result in a serious structural degradation
possibly leading to the loss of the windshield
during flight. Also, water could leak into the
cockpit and cause either a malfunction or
failure of the electrical and electronics
systems in the area of the cockpit instrument
panels.
*
corrective actions, in accordance with the
Accomplishment Instructions of Bombardier
Service Bulletin 8–53–78, Revision D, dated
July 6, 2010 (for Model DHC–8–101, –102,
–103, –106, –201, –202, –301, –311, and –315
airplanes); or 84–53–43, dated April 27, 2010
(for Model DHC–8–401 and –402 airplanes);
except where these service bulletins state to
contact the manufacturer, contact the New
York Aircraft Certification Office or
Transport Canada Civil Aviation (TCCA) or
its delegated agent. Do all applicable related
investigative and corrective actions before
further flight.
(i) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, New York Aircraft
Certification Office, ANE–170, 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 ACO, send it to ATTN: Program
Manager, Continuing Operational Safety,
FAA, New York ACO, 1600 Stewart Avenue,
Suite 410, Westbury, New York 11590;
telephone 516–228–7300; fax 516–794–5531.
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) 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 FAA-approved 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.
Related Information
(j) Refer to MCAI Canadian Airworthiness
Directive CF–2010–16, dated May 18, 2010;
Bombardier Service Bulletin 8–53–78,
Revision D, dated July 6, 2010; and
Bombardier Service Bulletin 84–53–43, dated
April 27, 2010; for related information.
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24345
Material Incorporated by Reference
(k) You must use Bombardier Service
Bulletin 8–53–78, Revision D, dated July 6,
2010; or Bombardier Service Bulletin 84–53–
43, dated April 27, 2010; as applicable; 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 Bombardier, Inc., Q-Series
Technical Help Desk, 123 Garratt Boulevard,
Toronto, Ontario M3K 1Y5, Canada;
telephone 416–375–4000; fax 416–375–4539;
e-mail thd.qseries@aero.bombardier.com;
Internet https://www.bombardier.com.
(3) You may review copies of the 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.
(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
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 Renton, Washington, on April 12,
2011.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2011–9673 Filed 4–29–11; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2010–1205; Directorate
Identifier 2010–NM–146–AD; Amendment
39–16677; AD 2011–09–15]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Model 777–200, –200LR,
–300, and –300ER Series Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for the
products listed above. This AD requires,
for certain airplanes, replacing certain
boost pump relays with ground fault
interrupter (GFI) relays. For certain
other airplanes, this AD requires
installing new panels in the main
equipment center, making certain
wiring changes, installing new GFI
relays in the new panels, and installing
SUMMARY:
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new electrical load management system
(ELMS) software. For certain other
airplanes, this AD requires doing certain
bond resistance measurements, and
corrective actions if necessary. This AD
was prompted by fuel system reviews
conducted by the manufacturer. We are
issuing this AD to prevent potential
ignition sources inside fuel tanks,
which, in combination with flammable
fuel vapors, could result in a fuel tank
explosion and consequent loss of the
airplane.
DATES: This AD is effective June 6, 2011.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of June 6, 2011.
ADDRESSES: For Boeing 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.
For Smiths and GE Aviation service
information identified in this AD,
contact GE Aviation, Customer Support
Center, 1 Neumann Way, Cincinnati,
Ohio 45215; telephone 513–552–3272;
e-mail cs.techpubs@ge.com; Internet
https://www.geaviation.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
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue, SE., Washington,
DC 20590.
FOR FURTHER INFORMATION CONTACT:
Georgios Roussos, Aerospace Engineer,
Systems and Equipment Branch, ANM–
130S, FAA, Seattle Aircraft Certification
Office, 1601 Lind Avenue, SW., Renton,
Washington 98057–3356; phone: 425–
917–6482; fax: 425–917–6590; e-mail:
georgios.roussos@faa.gov.
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SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an airworthiness
directive (AD) that would apply to the
specified products. That NPRM
published in the Federal Register on
December 28, 2010 (75 FR 81508). That
NPRM proposed to require, for certain
airplanes, replacing certain boost pump
relays with ground fault interrupter
(GFI) relays. For certain other airplanes,
that NPRM proposed to require
installing new panels in the main
equipment center, making certain
wiring changes, installing new GFI
relays in the new panels, and installing
new electrical load management system
(ELMS) software. For certain other
airplanes, that NPRM proposed to
require doing certain bond resistance
measurements, and corrective actions if
necessary.
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. Boeing
supported the NPRM.
Request to Extend Compliance Time
American Airlines (AAL) requested
that we extend the compliance time in
paragraphs (g) and (h) of the NPRM for
the work done in accordance with
Boeing Service Bulletin 777–28A0037,
Revision 2, dated September 20, 2010,
from 36 months to 60 months. AAL
stated that they have already
accomplished Boeing Service Bulletin
777–28A0037, Revision 1, dated June
15, 2009, on 75 percent of their Model
777 fleet. The proposed 36-month
compliance time would require special
scheduling for those airplanes. AAL
proposed that the compliance time for
all actions in the NPRM be extended to
60 months to be consistent with the 60month compliance time in paragraph (i)
of the NPRM for the GFI relay
replacement for the main tank boost
pumps specified in Boeing Service
Bulletin 737–28A0038, Revision 1,
dated September 20, 2010.
We disagree with the request to
extend the compliance time for the
actions required by paragraphs (g) and
(h) of the NPRM (bond resistance
measurements and the installation of
new panels, new fuel pump control GFI
relays, software, and wiring changes). In
developing appropriate compliance
times for those actions, we considered
the safety implications and practical
aspects of accomplishing these actions
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within a period of time that corresponds
to the normal scheduled maintenance
for most affected operators. In
consideration of these items, we have
determined that a 36-month compliance
time will ensure an acceptable level of
safety and allow those actions to be
done during scheduled maintenance
intervals for most affected operators.
However, under the provisions of
paragraph (k) of this AD, we will
consider requests for approval of an
alternative method of compliance
(AMOC) if sufficient data are submitted
to substantiate that the request would
provide an acceptable level of safety.
We have not changed this AD in this
regard.
Request To Delay Rule Pending Release
of New Service Bulletins
Japan Airlines (JAL) requested that we
delay the issuance of this AD until
Boeing and GE Aviation publish new
revisions to their service information
(referenced in the NPRM) to include
certain changes. JAL stated these
changes are to correct or add numbers
for wires, modules, connectors, and
figures. JAL also stated that, in addition,
certain GE Aviation service information
also needed to be revised to add another
procedure to install labels or separate
the labels from the conversion kit. JAL
explained that when it receives the
labels as part of the conversion kit, the
remaining shelf life of the labels is not
adequate to allow the labels to be
installed on the airplanes. JAL is
concerned that, unless the service
information is revised, these issues
could delay incorporation of this AD or
result in multiple AMOC requests. JAL
stated that they are in communication
with Boeing and GE Aviation in regard
to these issues with the service
information.
We agree with JAL’s concerns about
the shelf life of the labels possibly
affecting operators’ ability to comply
with this AD within the required
compliance times. This AD requires all
actions, including labeling, in the
Accomplishment Instructions of Boeing
Service Bulletins 777–28A0038,
Revision 1; and 777–28A0037, Revision
2; both dated September 20, 2010; to be
accomplished. We have added
paragraph (j) to this AD to provide an
optional method of labeling panels.
However, we disagree with the request
to delay this AD until Boeing and GE
Aviation issue revised service
information to correct or add numbers
for wires, modules, connectors, and
figures. No data or information to justify
that request was provided. However,
under the provisions of paragraph (k) of
this AD, we will consider requests for
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an AMOC if sufficient data are
submitted to substantiate that the
change would provide an acceptable
level of safety. We have not changed the
AD in this regard.
Conclusion
We reviewed the relevant data,
considered the comments received, and
determined that air safety and the
public interest require adopting the AD
burden on any operator or increase the
scope of the AD.
with the change described previously
and minor editorial changes. We have
determined that these minor changes:
• Are consistent with the intent that
was proposed in the NPRM for
correcting the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM.
We also determined that these
changes will not increase the economic
Costs of Compliance
We estimate that this AD will affect
130 airplanes of U.S. registry. The
following table provides the estimated
costs for U.S. operators to comply with
this AD.
TABLE—ESTIMATED COSTS
Action
Work hours
Replacements: Group 1 airplanes identified in
Boeing Service Bulletin 777-28A0038.
Replacements: Group 2 airplanes identified in
Boeing Service Bulletin 777-28A0038.
Replacements: Group 3 airplanes identified in
Boeing Service Bulletin 777-28A0038.
Replacements: Group 4 airplanes identified in
Boeing Service Bulletin 777-28A0038.
Installations and Measurement: Boeing Service Bulletin 777-28A0037.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. Subtitle VII:
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in Subtitle VII,
Part A, Subpart III, Section 44701:
‘‘General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
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Number of
U.S.registered
airplanes
Cost per
product
3
$85
$25,577
$25,832
126
3
85
52,545
52,800
0
4
85
37,257
37,597
4
4
85
17,816
18,156
0
76
85
29,934
36,394
130
(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:
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,
16:25 Apr 29, 2011
Parts
■
Regulatory Findings
VerDate Mar<15>2010
Average
labor rate
per hour
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):
■
2011–09–15 The Boeing Company:
Amendment 39–16677; Docket No.
FAA–2010–1205; Directorate Identifier
2010–NM–146–AD.
Effective Date
(a) This AD is effective June 6, 2011.
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Fleet cost
$3,254,832.
No airplanes currently
on U.S. Register.
$150,388.
No airplanes currently
on U.S. Register.
$4,731,220.
Affected ADs
(b) AD 2008–11–13, Amendment 39–
15536, affects this AD.
Applicability
(c) This AD applies to The Boeing
Company Model 777–200, –200LR, –300, and
–300ER series airplanes, certificated in any
category; as identified in the service
information specified in paragraphs (c)(1)
and (c)(2) of this AD.
(1) Boeing Service Bulletin 777–28A0038,
Revision 1, dated September 20, 2010.
(2) Boeing Service Bulletin 777–28A0037,
Revision 2, dated September 20, 2010.
Subject
(d) Air Transport Association (ATA) of
America Code 28: Fuel.
Unsafe Condition
(e) This AD was prompted by fuel system
reviews conducted by the manufacturer. The
Federal Aviation Administration is issuing
this AD to prevent potential ignition sources
inside fuel tanks, which, in combination with
flammable fuel vapors, 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.
Related Airworthiness Limitation
Note 1: AD 2008–11–13 requires a revision
of the Airworthiness Limitations (AWLs)
section of the Instructions for Continued
Airworthiness to include limitations for the
fuel tank systems. One of the limitations,
AWL 28–AWL–18, requires a repetitive
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Federal Register / Vol. 76, No. 84 / Monday, May 2, 2011 / Rules and Regulations
inspection of the ground fault interrupter
(GFI) functions.
2010, is an additional source of guidance for
installing ELMS software.
Installations and Software Changes
(g) For Groups 1 and 2 airplanes identified
as Configuration 2 in Boeing Service Bulletin
777–28A0037, Revision 2, dated September
20, 2010: Within 36 months after the effective
date of this AD, install new panels, P301 and
P302, in the main equipment center; make
certain wiring changes; install new GFI relays
in the P301 and P302 panels; and install new
electrical load management system (ELMS)
software; as applicable. Do the applicable
actions in accordance with the
Accomplishment Instructions of Boeing
Service Bulletin 777–28A0037, Revision 2,
dated September 20, 2010, except as
specified in paragraph (j) of this AD.
Note 2: Boeing Service Bulletin 777–
28A0039, Revision 2, dated September 20,
Note 3: Smiths Service Bulletin 5000ELM–
28–454, dated August 13, 2007; and GE
Aviation Service Bulletin 6000ELM–28–455,
Revision 1, dated February 1, 2010; are
additional sources of guidance for making a
wiring change in the P110 and P210 panels,
respectively.
(h) For Groups 1 and 2 airplanes identified
as Configuration 1 in Boeing Service Bulletin
777–28A0037, Revision 2, dated September
20, 2010: Within 36 months after the effective
date of this AD, do bonding resistance
measurements to verify bonding
requirements as specified in Boeing Service
Bulletin 777–28A0037, Revision 2, dated
September 20, 2010, are met, in accordance
with the Accomplishment Instructions of
Boeing Service Bulletin 777–28A0037,
Revision 2, dated September 20, 2010.
Replacement of GFI Relays
(i) For airplanes identified in Boeing
Service Bulletin 777–28A0038, Revision 1,
dated September 20, 2010: Within 60 months
after the effective date of this AD, replace 4
main tank boost pump relays in electrical
load management system panels P110, P210,
and P320 with new GFI relays, in accordance
with the Accomplishment Instructions of
Boeing Service Bulletin 777–28A0038,
Revision 1, dated September 20, 2010, except
as specified in paragraph (j) of this AD.
Note 4: Boeing Service Bulletin 777–
28A0038, Revision 1, dated September 20,
2010, references the service bulletins
identified in Table 1 of this AD as additional
sources of guidance for replacing the main
tank boost pump relays.
TABLE 1—ADDITIONAL SOURCES OF GUIDANCE FOR REPLACING THE MAIN TANK BOOST PUMP RELAYS
Group number of airplanes, as identified
in Boeing Service Bulletin 777–
28A0038, Revision 1, dated September
20, 2010
Panel No.
Group 1 ...................................................
P110
Group 1 ...................................................
P210
Group 1 ...................................................
P320
Group 2 ...................................................
P110
Group 2 ...................................................
P210
Group 2 ...................................................
P320
Group 3 ...................................................
P110
Group 3 ...................................................
P210
Group 3 ...................................................
P320
Group 4 ...................................................
P110
Group 4 ...................................................
P210
Group 4 ...................................................
P320
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Optional Method To Install a Label
(j) Where Boeing Service Bulletin 777–
28A0037, Revision 2, dated September 20,
2010; and Boeing Service Bulletin 777–
28A0038, Revision 1, dated September 20,
2010: specify installing a label, an operator’s
equivalent procedure may be used as a
method to indelibly mark the applicable
service bulletin number on the panel.
Note 5: Additional guidance on indelibly
marking the panel may also be found in
Boeing Standard BAC5307.
Alternative Methods of Compliance
(AMOCs)
(k)(1) The Manager, Seattle Aircraft
Certification Office (ACO), FAA, has the
authority to approve AMOCs for this AD, if
requested using the procedures found in 14
CFR 39.19. In accordance with 14 CFR 39.19,
VerDate Mar<15>2010
16:25 Apr 29, 2011
Jkt 223001
Service bulletin
Revision level
Smiths Service Bulletin 5000ELM–28–
443.
Smiths Service Bulletin 6000ELM–28–
444.
Smiths Service Bulletin 4000ELM–28–
445.
GE Aviation Service Bulletin 5000ELM–
28–446.
Smiths Service Bulletin 6000ELM–28–
447.
GE Aviation Service Bulletin 4000ELM–
28–448.
GE Aviation Service Bulletin 5000ELM–
28–449.
Smiths Service Bulletin 6000ELM–28–
450.
GE Aviation Service Bulletin 4000ELM–
28–451.
Smiths Service Bulletin 5000ELM–28–
463.
Smiths Service Bulletin 6000ELM–28–
464.
Smiths Service Bulletin 4000ELM–28–
465.
Original ...................
August 8, 2007.
Original ...................
August 8, 2007.
Original ...................
August 8, 2007.
1 .............................
January 7, 2010.
Original ...................
August 8, 2007.
1 .............................
January 7, 2010.
1 .............................
January 7, 2010.
Original ...................
August 8, 2007.
1 .............................
January 7, 2010.
Original ...................
August 8, 2007.
Original ...................
August 8, 2007.
Original ...................
August 8, 2007.
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 the
Related Information section of this AD.
Information may be e-mailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
Related Information
(l) For more information about this AD,
contact Georgios Roussos, Aerospace
Engineer, Systems and Equipment Branch,
ANM–130S, FAA, Seattle Aircraft
Certification Office, 1601 Lind Avenue, SW.,
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Date
Renton, Washington 98057–3356; telephone:
425–917–6482; fax: 425–917–6590; e-mail:
georgios.roussos@faa.gov.
Material Incorporated by Reference
(m) You must use Boeing Service Bulletin
777–28A0038, Revision 1, dated September
20, 2010; or Boeing Service Bulletin 777–
28A0037, Revision 2, dated September 20,
2010; as applicable; 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 Boeing service information
identified in this AD, contact Boeing
Commercial Airplanes, Attention: Data &
Services Management, P.O. Box 3707, MC
E:\FR\FM\02MYR1.SGM
02MYR1
Federal Register / Vol. 76, No. 84 / Monday, May 2, 2011 / Rules and Regulations
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) For Smiths and GE Aviation service
information identified in this AD, contact GE
Aviation, Customer Support Center, 1
Neumann Way, Cincinnati, Ohio 45215;
telephone 513–552–3272; e-mail
cs.techpubs@ge.com; Internet https://
www.geaviation.com.
(4) 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.
(5) 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
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 April 8,
2011.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2011–9917 Filed 4–29–11; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2010–1111; Directorate
Identifier 2010–NM–129–AD; Amendment
39–16676; AD 2011–09–14]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Model 747–200B, –300, –400,
–400D, and –400F Series Airplanes
Powered by Pratt and Whitney 4000 or
General Electric CF6–80C2 Series
Engines
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for the
products listed above. This AD requires
an inspection to determine the part
number of the mid-pivot access door
and to determine if the correct door is
installed, and the installation of a
marker on the mid-pivot access door,
and if necessary, repetitive ultrasonic
inspections for cracking of the midpivot bolt assembly and eventual
replacement of the mid-pivot bolt
assembly. This AD was prompted by a
report that the left and right access
doors of the spring beam mid-pivot bolt
jlentini on DSKJ8SOYB1PROD with RULES
SUMMARY:
VerDate Mar<15>2010
16:25 Apr 29, 2011
Jkt 223001
assembly for the No. 1 strut were
inadvertently installed in the incorrect
position during strut modification. We
are issuing this AD to detect and correct
incorrectly installed mid-pivot bolt
assemblies on the spring beam on the
outboard struts. Incorrectly installed
bolt assemblies could lead to fatigue
cracking and consequent fracturing of
the mid-pivot bolt assembly, which
could lead to loss of the spring beam
load path and the possible separation of
a strut and engine from the airplane
during flight.
DATES: This AD is effective June 6, 2011.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of June 6, 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
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue, SE., Washington,
DC 20590.
FOR FURTHER INFORMATION CONTACT:
Kenneth Paoletti, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office
(ACO), 1601 Lind Avenue, SW., Renton,
Washington 98057–3356; phone: (425)
917–6434; fax (425) 917–6590; e-mail:
Kenneth.Paoletti@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an airworthiness
directive (AD) that would apply to the
PO 00000
Frm 00007
Fmt 4700
Sfmt 4700
24349
specified products. That NPRM
published in the Federal Register on
November 15, 2010 (75 FR 69612). That
NPRM proposed to require an
inspection to determine the part number
of the mid-pivot access door and to
determine if the correct door is
installed, and the installation of a
marker on the mid-pivot access door,
and if necessary, repetitive ultrasonic
inspections for cracking of the midpivot bolt assembly and eventual
replacement of the mid-pivot bolt
assembly.
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.
Support for the NPRM
Boeing supported the contents of the
NPRM.
Request To Include References to
Airplane Maintenance Manual
United Airlines (UAL) stated that it is
concerned about the actions in Boeing
Alert Service Bulletin 747–54A2232,
dated April 15, 2010, being undone and
leading to the same condition. UAL
suggested that we revise the NPRM to
include airplane maintenance manual
(AMM) references, including a check for
marker BAC27EPP667 before installing
the access door. As an alternative, UAL
also suggested that the mid-pivot access
door part number could be changed
instead of keeping the same part
number. UAL stated that if the NPRM is
not changed to incorporate one of the
two options, then the required actions
could be undone if doors without the
marker are installed.
We disagree with the request to revise
this AD. Section 39.7 of the Federal
Aviation Regulations (14 CFR 39.7)
states the following: ‘‘Anyone who
operates a product that does not meet
the requirements of an applicable
airworthiness directive is in violation of
this section.’’ Therefore, operators are
prohibited from installing a door that
does not meet the requirements of this
AD. However, operators are permitted to
add a check to applicable AMM to
prevent installing the incorrect access
door. We have not changed the final
rule in regard to this issue.
Request To Clarify Figures in Service
Information
UPS requested that we clarify the
figures C–C and D–D on sheets 7 and 8
of Appendix B of Boeing Alert Service
Bulletin 747–54A2232, dated April 15,
2010. UPS stated that the transducer
E:\FR\FM\02MYR1.SGM
02MYR1
]]>Agencies
[Federal Register Volume 76, Number 84 (Monday, May 2, 2011)]
[Rules and Regulations]
[Pages 24345-24349]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-9917]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2010-1205; Directorate Identifier 2010-NM-146-AD;
Amendment 39-16677; AD 2011-09-15]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Model 777-200, -
200LR, -300, and -300ER Series Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for the
products listed above. This AD requires, for certain airplanes,
replacing certain boost pump relays with ground fault interrupter (GFI)
relays. For certain other airplanes, this AD requires installing new
panels in the main equipment center, making certain wiring changes,
installing new GFI relays in the new panels, and installing
[[Page 24346]]
new electrical load management system (ELMS) software. For certain
other airplanes, this AD requires doing certain bond resistance
measurements, and corrective actions if necessary. This AD was prompted
by fuel system reviews conducted by the manufacturer. We are issuing
this AD to prevent potential ignition sources inside fuel tanks, which,
in combination with flammable fuel vapors, could result in a fuel tank
explosion and consequent loss of the airplane.
DATES: This AD is effective June 6, 2011.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of June 6, 2011.
ADDRESSES: For Boeing 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.
For Smiths and GE Aviation service information identified in this
AD, contact GE Aviation, Customer Support Center, 1 Neumann Way,
Cincinnati, Ohio 45215; telephone 513-552-3272; e-mail
cs.techpubs@ge.com; Internet https://www.geaviation.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 Operations, M-30, West
Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Georgios Roussos, Aerospace Engineer,
Systems and Equipment Branch, ANM-130S, FAA, Seattle Aircraft
Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057-
3356; phone: 425-917-6482; fax: 425-917-6590; e-mail:
georgios.roussos@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to include an airworthiness directive (AD) that would apply to
the specified products. That NPRM published in the Federal Register on
December 28, 2010 (75 FR 81508). That NPRM proposed to require, for
certain airplanes, replacing certain boost pump relays with ground
fault interrupter (GFI) relays. For certain other airplanes, that NPRM
proposed to require installing new panels in the main equipment center,
making certain wiring changes, installing new GFI relays in the new
panels, and installing new electrical load management system (ELMS)
software. For certain other airplanes, that NPRM proposed to require
doing certain bond resistance measurements, and corrective actions if
necessary.
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. Boeing supported the NPRM.
Request to Extend Compliance Time
American Airlines (AAL) requested that we extend the compliance
time in paragraphs (g) and (h) of the NPRM for the work done in
accordance with Boeing Service Bulletin 777-28A0037, Revision 2, dated
September 20, 2010, from 36 months to 60 months. AAL stated that they
have already accomplished Boeing Service Bulletin 777-28A0037, Revision
1, dated June 15, 2009, on 75 percent of their Model 777 fleet. The
proposed 36-month compliance time would require special scheduling for
those airplanes. AAL proposed that the compliance time for all actions
in the NPRM be extended to 60 months to be consistent with the 60-month
compliance time in paragraph (i) of the NPRM for the GFI relay
replacement for the main tank boost pumps specified in Boeing Service
Bulletin 737-28A0038, Revision 1, dated September 20, 2010.
We disagree with the request to extend the compliance time for the
actions required by paragraphs (g) and (h) of the NPRM (bond resistance
measurements and the installation of new panels, new fuel pump control
GFI relays, software, and wiring changes). In developing appropriate
compliance times for those actions, we considered the safety
implications and practical aspects of accomplishing these actions
within a period of time that corresponds to the normal scheduled
maintenance for most affected operators. In consideration of these
items, we have determined that a 36-month compliance time will ensure
an acceptable level of safety and allow those actions to be done during
scheduled maintenance intervals for most affected operators. However,
under the provisions of paragraph (k) of this AD, we will consider
requests for approval of an alternative method of compliance (AMOC) if
sufficient data are submitted to substantiate that the request would
provide an acceptable level of safety. We have not changed this AD in
this regard.
Request To Delay Rule Pending Release of New Service Bulletins
Japan Airlines (JAL) requested that we delay the issuance of this
AD until Boeing and GE Aviation publish new revisions to their service
information (referenced in the NPRM) to include certain changes. JAL
stated these changes are to correct or add numbers for wires, modules,
connectors, and figures. JAL also stated that, in addition, certain GE
Aviation service information also needed to be revised to add another
procedure to install labels or separate the labels from the conversion
kit. JAL explained that when it receives the labels as part of the
conversion kit, the remaining shelf life of the labels is not adequate
to allow the labels to be installed on the airplanes. JAL is concerned
that, unless the service information is revised, these issues could
delay incorporation of this AD or result in multiple AMOC requests. JAL
stated that they are in communication with Boeing and GE Aviation in
regard to these issues with the service information.
We agree with JAL's concerns about the shelf life of the labels
possibly affecting operators' ability to comply with this AD within the
required compliance times. This AD requires all actions, including
labeling, in the Accomplishment Instructions of Boeing Service
Bulletins 777-28A0038, Revision 1; and 777-28A0037, Revision 2; both
dated September 20, 2010; to be accomplished. We have added paragraph
(j) to this AD to provide an optional method of labeling panels.
However, we disagree with the request to delay this AD until Boeing and
GE Aviation issue revised service information to correct or add numbers
for wires, modules, connectors, and figures. No data or information to
justify that request was provided. However, under the provisions of
paragraph (k) of this AD, we will consider requests for
[[Page 24347]]
an AMOC if sufficient data are submitted to substantiate that the
change would provide an acceptable level of safety. We have not changed
the AD in this regard.
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 change described previously and minor editorial
changes. We have determined that these minor changes:
[Agr]re 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 will affect 130 airplanes of U.S.
registry. The following table provides the estimated costs for U.S.
operators to comply with this AD.
Table--Estimated Costs
----------------------------------------------------------------------------------------------------------------
Number of
Average Cost per U.S.-
Action Work hours labor rate Parts product registered Fleet cost
per hour airplanes
----------------------------------------------------------------------------------------------------------------
Replacements: Group 1 3 $85 $25,577 $25,832 126 $3,254,832.
airplanes identified in
Boeing Service Bulletin
777[dash]28A0038.
Replacements: Group 2 3 85 52,545 52,800 0 No airplanes
airplanes identified in currently on
Boeing Service Bulletin U.S. Register.
777[dash]28A0038.
Replacements: Group 3 4 85 37,257 37,597 4 $150,388.
airplanes identified in
Boeing Service Bulletin
777[dash]28A0038.
Replacements: Group 4 4 85 17,816 18,156 0 No airplanes
airplanes identified in currently on
Boeing Service Bulletin U.S. Register.
777[dash]28A0038.
Installations and 76 85 29,934 36,394 130 $4,731,220.
Measurement: Boeing Service
Bulletin 777[dash]28A0037.
----------------------------------------------------------------------------------------------------------------
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII: Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701: ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
This AD will not have federalism implications under Executive Order
13132. This AD will not have a substantial direct effect on the States,
on the relationship between the national government and the States, or
on the distribution of power and responsibilities among the various
levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation in Alaska, and
(4) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
2011-09-15 The Boeing Company: Amendment 39-16677; Docket No. FAA-
2010-1205; Directorate Identifier 2010-NM-146-AD.
Effective Date
(a) This AD is effective June 6, 2011.
Affected ADs
(b) AD 2008-11-13, Amendment 39-15536, affects this AD.
Applicability
(c) This AD applies to The Boeing Company Model 777-200, -200LR,
-300, and -300ER series airplanes, certificated in any category; as
identified in the service information specified in paragraphs (c)(1)
and (c)(2) of this AD.
(1) Boeing Service Bulletin 777-28A0038, Revision 1, dated
September 20, 2010.
(2) Boeing Service Bulletin 777-28A0037, Revision 2, dated
September 20, 2010.
Subject
(d) Air Transport Association (ATA) of America Code 28: Fuel.
Unsafe Condition
(e) This AD was prompted by fuel system reviews conducted by the
manufacturer. The Federal Aviation Administration is issuing this AD
to prevent potential ignition sources inside fuel tanks, which, in
combination with flammable fuel vapors, 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.
Related Airworthiness Limitation
Note 1: AD 2008-11-13 requires a revision of the Airworthiness
Limitations (AWLs) section of the Instructions for Continued
Airworthiness to include limitations for the fuel tank systems. One
of the limitations, AWL 28-AWL-18, requires a repetitive
[[Page 24348]]
inspection of the ground fault interrupter (GFI) functions.
Installations and Software Changes
(g) For Groups 1 and 2 airplanes identified as Configuration 2
in Boeing Service Bulletin 777-28A0037, Revision 2, dated September
20, 2010: Within 36 months after the effective date of this AD,
install new panels, P301 and P302, in the main equipment center;
make certain wiring changes; install new GFI relays in the P301 and
P302 panels; and install new electrical load management system
(ELMS) software; as applicable. Do the applicable actions in
accordance with the Accomplishment Instructions of Boeing Service
Bulletin 777-28A0037, Revision 2, dated September 20, 2010, except
as specified in paragraph (j) of this AD.
Note 2: Boeing Service Bulletin 777-28A0039, Revision 2, dated
September 20, 2010, is an additional source of guidance for
installing ELMS software.
Note 3: Smiths Service Bulletin 5000ELM-28-454, dated August
13, 2007; and GE Aviation Service Bulletin 6000ELM-28-455, Revision
1, dated February 1, 2010; are additional sources of guidance for
making a wiring change in the P110 and P210 panels, respectively.
(h) For Groups 1 and 2 airplanes identified as Configuration 1
in Boeing Service Bulletin 777-28A0037, Revision 2, dated September
20, 2010: Within 36 months after the effective date of this AD, do
bonding resistance measurements to verify bonding requirements as
specified in Boeing Service Bulletin 777-28A0037, Revision 2, dated
September 20, 2010, are met, in accordance with the Accomplishment
Instructions of Boeing Service Bulletin 777-28A0037, Revision 2,
dated September 20, 2010.
Replacement of GFI Relays
(i) For airplanes identified in Boeing Service Bulletin 777-
28A0038, Revision 1, dated September 20, 2010: Within 60 months
after the effective date of this AD, replace 4 main tank boost pump
relays in electrical load management system panels P110, P210, and
P320 with new GFI relays, in accordance with the Accomplishment
Instructions of Boeing Service Bulletin 777-28A0038, Revision 1,
dated September 20, 2010, except as specified in paragraph (j) of
this AD.
Note 4: Boeing Service Bulletin 777-28A0038, Revision 1, dated
September 20, 2010, references the service bulletins identified in
Table 1 of this AD as additional sources of guidance for replacing
the main tank boost pump relays.
Table 1--Additional Sources of Guidance for Replacing the Main Tank Boost Pump Relays
----------------------------------------------------------------------------------------------------------------
Group number of airplanes, as
identified in Boeing Service
Bulletin 777-28A0038, Revision Panel No. Service bulletin Revision level Date
1, dated September 20, 2010
----------------------------------------------------------------------------------------------------------------
Group 1........................ P110 Smiths Service Original......... August 8, 2007.
Bulletin 5000ELM-
28-443.
Group 1........................ P210 Smiths Service Original......... August 8, 2007.
Bulletin 6000ELM-
28-444.
Group 1........................ P320 Smiths Service Original......... August 8, 2007.
Bulletin 4000ELM-
28-445.
Group 2........................ P110 GE Aviation 1................ January 7, 2010.
Service Bulletin
5000ELM-28-446.
Group 2........................ P210 Smiths Service Original......... August 8, 2007.
Bulletin 6000ELM-
28-447.
Group 2........................ P320 GE Aviation 1................ January 7, 2010.
Service Bulletin
4000ELM-28-448.
Group 3........................ P110 GE Aviation 1................ January 7, 2010.
Service Bulletin
5000ELM-28-449.
Group 3........................ P210 Smiths Service Original......... August 8, 2007.
Bulletin 6000ELM-
28-450.
Group 3........................ P320 GE Aviation 1................ January 7, 2010.
Service Bulletin
4000ELM-28-451.
Group 4........................ P110 Smiths Service Original......... August 8, 2007.
Bulletin 5000ELM-
28-463.
Group 4........................ P210 Smiths Service Original......... August 8, 2007.
Bulletin 6000ELM-
28-464.
Group 4........................ P320 Smiths Service Original......... August 8, 2007.
Bulletin 4000ELM-
28-465.
----------------------------------------------------------------------------------------------------------------
Optional Method To Install a Label
(j) Where Boeing Service Bulletin 777-28A0037, Revision 2, dated
September 20, 2010; and Boeing Service Bulletin 777-28A0038,
Revision 1, dated September 20, 2010: specify installing a label, an
operator's equivalent procedure may be used as a method to indelibly
mark the applicable service bulletin number on the panel.
Note 5: Additional guidance on indelibly marking the panel may
also be found in Boeing Standard BAC5307.
Alternative Methods of Compliance (AMOCs)
(k)(1) The Manager, Seattle Aircraft Certification Office (ACO),
FAA, has the authority to approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19. In accordance with 14
CFR 39.19, send your request to your principal inspector or local
Flight Standards District Office, as appropriate. If sending
information directly to the manager of the ACO, send it to the
attention of the person identified in the Related Information
section of this AD. Information may be e-mailed to: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
Related Information
(l) For more information about this AD, contact Georgios
Roussos, Aerospace Engineer, Systems and Equipment Branch, ANM-130S,
FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW.,
Renton, Washington 98057-3356; telephone: 425-917-6482; fax: 425-
917-6590; e-mail: georgios.roussos@faa.gov.
Material Incorporated by Reference
(m) You must use Boeing Service Bulletin 777-28A0038, Revision
1, dated September 20, 2010; or Boeing Service Bulletin 777-28A0037,
Revision 2, dated September 20, 2010; as applicable; 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 Boeing service information identified in this AD,
contact Boeing Commercial Airplanes, Attention: Data & Services
Management, P.O. Box 3707, MC
[[Page 24349]]
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) For Smiths and GE Aviation service information identified in
this AD, contact GE Aviation, Customer Support Center, 1 Neumann
Way, Cincinnati, Ohio 45215; telephone 513-552-3272; e-mail
cs.techpubs@ge.com; Internet https://www.geaviation.com.
(4) 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.
(5) 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
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 April 8, 2011.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2011-9917 Filed 4-29-11; 8:45 am]
BILLING CODE 4910-13-P
