Airworthiness Directives; The Boeing Company Model 777-200, -300, and -300ER Series Airplanes, 22305-22308 [2011-9283]
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Federal Register / Vol. 76, No. 77 / Thursday, April 21, 2011 / Rules and Regulations
Parts Installation
(l) As of the effective date of this AD, no
person may install, on any airplane, a THSA,
unless it is in compliance with the
requirements of this AD.
FAA AD Differences
Note 1: This AD differs from the MCAI
and/or service information as follows: The
MCAI does not include a reporting
requirement; however, the service bulletin
recommends reporting. Paragraph (k) of this
AD specifies a reporting requirement.
WReier-Aviles on DSKGBLS3C1PROD with RULES
Other FAA AD Provisions
(m) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, FAA, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
In accordance with 14 CFR 39.19, send your
request to your principal inspector or local
Flight Standards District Office, as
appropriate. If sending information directly
to the International Branch, send it to ATTN:
Dan Rodina, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue, SW., Renton, Washington 98057–
3356; telephone (425) 227–2125; fax (425)
227–1149. Information may be e-mailed to:
9-ANM-116-AMOC-REQUESTS@faa.gov.
Before using any approved AMOC, notify
your appropriate principal inspector, or
lacking a principal inspector, the manager of
the local flight standards district office/
certificate holding district office. The AMOC
approval letter must specifically reference
this AD.
(2) 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: 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.
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Related Information
(n) Refer to MCAI EASA Airworthiness
Directive 2010–0092, dated May 21, 2010;
Airbus Mandatory Service Bulletin A300–
27A6067, Revision 02, including Appendix
01, dated October 18, 2010; Airbus
Mandatory Service Bulletin A310–27A2104,
Revision 02, including Appendix 01, dated
October 18, 2010; and Goodrich Actuation
Systems Component Maintenance Manual
with Illustrated Parts List, Horizontal
Stabilizer Actuator, P/N 47142 Series,
Document 27–44–13, Revision 8, dated
December 12, 2008, for related information.
material at NARA, call 202–741–6030, or go
to: https://www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html.
Material Incorporated by Reference
(o) You must use Airbus Mandatory
Service Bulletin A310–27A2104, Revision 02,
including Appendix 01, dated October 18,
2010; and Airbus Mandatory Service Bulletin
A300–27A6067, Revision 02, including
Appendix 01, dated October 18, 2010; to do
the actions required by this AD, unless the
AD specifies otherwise. If you accomplish
the optional terminating actions specified by
this AD, you must use Goodrich Actuation
Systems Component Maintenance Manual
with Illustrated Parts List, Horizontal
Stabilizer Actuator, P/N 47142 Series,
Document 27–44–13, Revision 8, dated
December 12, 2008, to perform those actions
unless the AD specifies otherwise. (The
LOEP in Goodrich Actuation Systems
Component Maintenance Manual with
Illustrated Parts List, Horizontal Stabilizer
Actuator, P/N 47142 Series, Document 27–
44–13, Revision 8, dated December 12, 2008,
specifies that page 749 is placed after page
748a; the correct placement of page 749 is
between pages 748 and 747a. The LOEP of
this document identifies two pages for the
Illustrated Parts List section; there is only
one page for that section (page 1001–1). The
date on page 1014–1 of this document is
incorrect; the correct date is March 6, 1998.)
(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 Airbus service information
identified in this AD, contact Airbus SAS—
EAW (Airworthiness Office), 1 Rond Point
Maurice Bellonte, 31707 Blagnac Cedex,
France; telephone +33 5 61 93 36 96; fax +33
5 61 93 44 51; e-mail: account.airwortheas@airbus.com; Internet https://
www.airbus.com.
(3) For Goodrich service information
identified in this AD, contact Goodrich
Corporation Actuation Systems, Stafford
Road, Fordhouses, Wolverhampton WV10
7EH, England; telephone +44 (0) 1902
624938; fax: +44 (0) 1902 788100; e-mail
techpubs.wolverhampton@goodrich.com;
Internet https://www.goodrich.com/TechPubs.
(4) 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.
(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
DEPARTMENT OF TRANSPORTATION
PO 00000
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Issued in Renton, Washington, on March
23, 2011.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2011–8279 Filed 4–20–11; 8:45 am]
BILLING CODE 4910–13–P
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2010–1271; Directorate
Identifier 2010–NM–187–AD; Amendment
39–16667; AD 2011–09–05]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Model 777–200, –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
installing an auto shutoff feature for the
center override/jettison fuel pumps, and
installing power control circuitry for the
center override/jettison and main
jettison fuel pumps. This AD also
requires installing new software in the
electrical load management system
(ELMS) electronics units in certain
power management panels; installing
airplane information management
system 2 (AIMS–2) software in the
AIMS–2 hardware; and making certain
wiring changes. This AD was prompted
by results from 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.
SUMMARY:
This AD is effective May 26,
2011.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of May 26, 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
DATES:
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Federal Register / Vol. 76, No. 77 / Thursday, April 21, 2011 / Rules and Regulations
me.boecom@boeing.com; Internet
https://www.myboeingfleet.com. For GE
Aviation service information identified
in this AD, contact GE Aviation,
Customer Services—Clearwater, P.O.
Box 9013, Clearwater, Florida 33758;
telephone 727–539–1631; fax 727–539–
0680; e-mail cs.support@ge.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 30, 2010 (75 FR 82337). That
NPRM proposed to require installing an
auto shutoff feature for the center
override/jettison fuel pumps, and
installing power control circuitry for the
center override/jettison and main
jettison fuel pumps. That NPRM also
proposed to require installing new
software in the electrical load
management system (ELMS) electronics
units in certain power management
panels; installing airplane information
management system 2 (AIMS–2)
software in the AIMS–2 hardware; and
making certain wiring changes.
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
supports the NPRM.
Request To Delay Issuance of AD To
Specify Spring Washers Instead of
Conical Springs
Japan Airlines (JAL) requested that we
delay issuance of the AD until GE
Aviation Service Bulletins 5000ELM–
28–456 and 6000ELM–28–457, both
Revision 1, both dated January 7, 2010,
are revised to correct Figure 8. JAL
stated that Figure 8 shows conical
springs rather than spring washers in
the diagram. JAL stated that without this
change, operators will be required to
request an alternate method of
compliance (AMOC).
We disagree with delaying issuance of
this AD. However, we agree that
clarification is needed in regard to the
use of spring washers. Certain airplanes
may use spring washers in lieu of
conical springs in their relay assembly.
Both the conical springs and spring
washers are retained from the existing
relay assembly to be used with the new
relay. Either one of them is considered
acceptable for use. New paragraph (m)
has been added to the AD to identify the
use of spring washers as an acceptable
method of compliance if they are part of
the existing relay assembly.
Request To Delay Issuance of AD To
Specify Label Installation
JAL requested that we delay the
issuance of this AD until GE Aviation
publishes new revisions to their service
information (referenced in the NPRM) 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.
We disagree with the request to delay
this AD until GE Aviation issues revised
service information. However, 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 GE
Aviation Service Bulletins 5000ELM–
28–456 and 6000ELM–28–457, both
Revision 1, both dated January 7, 2010,
to be accomplished. We have added
paragraph (n) to this AD to provide an
optional method of labeling.
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 2
airplanes of U.S. registry.
We estimate the following costs to
comply with this AD:
ESTIMATED COSTS
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Labor cost
Installation: Groups 1 and 2,
Configuration 2.
Installation: Groups 1 and 2,
Configuration 1.
Concurrent requirement: Install
ELMS software.
Concurrent requirement: Upgrade
AIMS–2 software.
Concurrent requirement: P110
wiring changes.
149 work-hours × $85 per hour = $12,665 ...................
$15,719
$28,384 ...............
$56,768.
2 work-hours × $85 per hour = $170 ............................
15,719
$15,889 ...............
$31,778.
3 work-hours × $85 per hour = $255 ............................
0
$255 ....................
$510.
Up to 2 work-hours × $85 per hour = Up to $170 ........
0
Up to $170 ..........
Up to $340.
3 work-hours × $85 per hour = $255 ............................
$1,164
$1,419 .................
$2,838.
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Parts cost
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Cost per product
Cost on U.S.
operators
Action
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Federal Register / Vol. 76, No. 77 / Thursday, April 21, 2011 / Rules and Regulations
ESTIMATED COSTS—Continued
Action
Concurrent requirement:
wiring changes.
Labor cost
P210
3 work-hours × $85 per hour = $255 ............................
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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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:
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PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
2011–09–05 The Boeing Company:
Amendment 39–16667; Docket No.
FAA–2010–1271; Directorate Identifier
2010–NM–187–AD.
Effective Date
(a) This AD is effective May 26, 2011.
Affected ADs
(b) None.
Applicability
(c) The Boeing Company Model 777–200,
–300, and –300ER series airplanes;
certificated in any category; as identified in
Boeing Service Bulletin 777–28A0047,
Revision 5, dated September 20, 2010.
Subject
(d) Joint Aircraft System Component
(JASC)/Air Transport Association (ATA) of
America Code 28, Fuel.
Unsafe Condition
(e) This AD was prompted by results from
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.
Compliance
(f) Comply with this AD within the
compliance times specified, unless already
done.
Installation
(g) For airplanes in Groups 1 and 2,
Configuration 2, as identified in Boeing
Service Bulletin 777–28A0047, Revision 5,
dated September 20, 2010: Within 36 months
after the effective date of this AD, install a
new P301 panel on the left side of the
airplane, install a new P302 panel on the
right side of the airplane, and change the
wiring, in accordance with the
Accomplishment Instructions of Boeing
Service Bulletin 777–28A0047, Revision 5,
dated September 20, 2010, except as required
by paragraphs (m) and (n) of this AD.
(h) For airplanes in Groups 1 and 2,
Configuration 1, as identified in Boeing
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1,164
Cost per product
$1,419 .................
Cost on U.S.
operators
$2,838.
Service Bulletin 777–28A0047, Revision 5,
dated September 20, 2010: Within 36 months
after the effective date of this AD, perform
bonding resistance measurements and rework
the airplane installation as applicable,
depending on airplane configuration, in
accordance with the Accomplishment
Instructions of Boeing Service Bulletin 777–
28A0047, Revision 5, dated September 20,
2010.
Concurrent Requirements
(i) Prior to or concurrently with
accomplishing the requirements of paragraph
(g) of this AD, do the actions specified in
paragraphs (i)(1), (i)(2), (i)(3), and (i)(4) of
this AD.
(1) Install new software in the electrical
load management system (ELMS) electronics
units in the P110, P210, and P310 power
management panels, in accordance with the
Accomplishment Instructions of Boeing
Service Bulletin 777–28A0040, Revision 1,
dated March 18, 2010.
(2) Install airplane information
management system 2 (AIMS–2) software in
the AIMS–2 hardware, in accordance with
the Accomplishment Instructions of Boeing
Special Attention Service Bulletin 777–31–
0097, Revision 3, dated February 22, 2007.
(3) Modify the P110 left power
management panel by incorporating wiring
changes, in accordance with the
Accomplishment Instructions of GE Aviation
Service Bulletin 5000ELM–28–456, Revision
1, dated January 7, 2010, except as provided
by paragraphs (m) and (n) of this AD.
(4) Modify the P210 right power
management panel by incorporating wiring
changes, in accordance with the
Accomplishment Instructions of GE Aviation
Service Bulletin 6000ELM–28–457, Revision
1, dated January 7, 2010, except as provided
by paragraphs (m) and (n) of this AD.
Credit for Actions Accomplished in
Accordance With Previous Service
Information
(j) Installations done before the effective
date of this AD in accordance with Boeing
Alert Service Bulletin 777–28A0040, dated
April 13, 2007, are acceptable for compliance
with the requirements of paragraph (i)(1) of
this AD.
(k) Installations done before the effective
date of this AD in accordance with Boeing
Service Bulletin 777–28A0047, Revision 3,
dated June 11, 2009; or Revision 4, dated
May 20, 2010; are acceptable for compliance
with the requirements of paragraphs (g) and
(h) of this AD.
(l) Installations done before the effective
date of this AD in accordance with Boeing
Special Attention Service Bulletin 777–31–
0097, dated March 30, 2006; Revision 1,
dated August 10, 2006; or Revision 2, dated
October 26, 2006; are acceptable for
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compliance with the requirements of
paragraph (i)(2) of this AD.
Optional Methods of Compliance With
Certain Actions
(m) Where paragraph 2.A.(16) and Figure 8
of GE Aviation Service Bulletins 5000ELM–
28–456 and 6000ELM–28–457, both Revision
1, both dated January 7, 2010, identify the
installation of conical springs for the relay to
relay base fixing, installation of spring
washers is an acceptable method of
compliance when they are part of the existing
relay assembly.
(n) Where paragraphs 2.A.(24) and 2.A.(25)
of GE Aviation Service Bulletins 5000ELM–
28–456 and 6000ELM–28–457, both Revision
1, both dated January 7, 2010, specify the
installation of a label to identify work carried
out and to identify the appropriate service
bulletin, an acceptable method of compliance
is to use a suitable method to indelibly mark
the appropriate service bulletin number on
the reworked panel. Boeing Standard
BAC5307 may be used as an additional
source of guidance for part marking.
(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.
Alternative Methods of Compliance
(AMOCs)
(o)(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-ANMSeattle-ACO-AMOC-Requests@faa.gov.
Related Information
(p) 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; phone:
425–917–6482; fax: 425–917–6590; e-mail:
Georgios.Roussos@faa.gov.
Material Incorporated by Reference
(q) You must use the applicable service
information contained in table 1 of this AD
to do the actions required by this AD, unless
the AD specifies otherwise.
TABLE 1—ALL MATERIAL INCORPORATED BY REFERENCE
Document
Revision
WReier-Aviles on DSKGBLS3C1PROD with RULES
Boeing Service Bulletin 777–28A0047 ........................................................................................................
Boeing Service Bulletin 777–28A0040 ........................................................................................................
Boeing Special Attention Service Bulletin 777–31–0097 ............................................................................
GE Aviation Service Bulletin 5000ELM–28–456 .........................................................................................
GE Aviation Service Bulletin 6000ELM–28–457 .........................................................................................
(1) The Director of the Federal Register
approved the incorporation by reference of
the service information contained in Table 1
of this AD 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
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 GE Aviation
service information identified in this AD,
contact GE Aviation, Customer Services—
Clearwater, P.O. Box 9013, Clearwater,
Florida 33758; telephone 727–539–1631; fax
727–539–0680; e-mail cs.support@ge.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 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 12,
2011.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2011–9283 Filed 4–20–11; 8:45 am]
BILLING CODE 4910–13–P
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2011–0310; Directorate
Identifier 2010–NM–133–AD; Amendment
39–16663; AD 2011–09–01]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A340–541 and –642 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
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:
* * * [S]ome Allowable Damage Limits
and Repairs published in SRM Chapters 57–
61–12 PB101 and 57–61–12 PB201 were devalidated starting from the SRM revision
issued on January 2009. The terminology
‘‘De-validated SRM’’ used in this AD text
refers to the SRM chapters mentioned above.
In order to prevent complete inner aileron
split due to possible failure or disbonding of
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Date
5
1
3
1
1
September 20, 2010.
March 18, 2010.
February 22, 2007.
January 7, 2010.
January 7, 2010.
the repairs on the inner aileron panels
performed as per ‘‘devalidated SRM’’, which
may result in flutter coupling of the free
aileron part, this AD requires a one time
inspection of the inner aileron panels to
identify the presence of ‘‘de-validated SRM’’
repairs and, if necessary, to apply the
associated corrective actions [repair].
The flutter coupling of the free aileron
part might result in separation of the
aileron from the airplane, degradation of
airplane control, and increased
workload for the flight crew. This AD
requires actions that are intended to
address the unsafe condition described
in the MCAI.
DATES: This AD becomes effective May
6, 2011.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of May 6, 2011.
We must receive comments on this
AD by June 6, 2011.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: (202) 493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations,
M–30, West Building Ground Floor,
Room W12–140, 1200 New Jersey
Avenue, SE., Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations,
M–30, West Building Ground Floor,
Room W12–40, 1200 New Jersey
E:\FR\FM\21APR1.SGM
21APR1
]]>Agencies
[Federal Register Volume 76, Number 77 (Thursday, April 21, 2011)]
[Rules and Regulations]
[Pages 22305-22308]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-9283]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2010-1271; Directorate Identifier 2010-NM-187-AD;
Amendment 39-16667; AD 2011-09-05]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Model 777-200, -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 installing an auto shutoff
feature for the center override/jettison fuel pumps, and installing
power control circuitry for the center override/jettison and main
jettison fuel pumps. This AD also requires installing new software in
the electrical load management system (ELMS) electronics units in
certain power management panels; installing airplane information
management system 2 (AIMS-2) software in the AIMS-2 hardware; and
making certain wiring changes. This AD was prompted by results from
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 May 26, 2011.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of May 26, 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
[[Page 22306]]
me.boecom@boeing.com; Internet https://www.myboeingfleet.com. For GE
Aviation service information identified in this AD, contact GE
Aviation, Customer Services--Clearwater, P.O. Box 9013, Clearwater,
Florida 33758; telephone 727-539-1631; fax 727-539-0680; e-mail
cs.support@ge.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 30, 2010 (75 FR 82337). That NPRM proposed to require
installing an auto shutoff feature for the center override/jettison
fuel pumps, and installing power control circuitry for the center
override/jettison and main jettison fuel pumps. That NPRM also proposed
to require installing new software in the electrical load management
system (ELMS) electronics units in certain power management panels;
installing airplane information management system 2 (AIMS-2) software
in the AIMS-2 hardware; and making certain wiring changes.
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 supports the NPRM.
Request To Delay Issuance of AD To Specify Spring Washers Instead of
Conical Springs
Japan Airlines (JAL) requested that we delay issuance of the AD
until GE Aviation Service Bulletins 5000ELM-28-456 and 6000ELM-28-457,
both Revision 1, both dated January 7, 2010, are revised to correct
Figure 8. JAL stated that Figure 8 shows conical springs rather than
spring washers in the diagram. JAL stated that without this change,
operators will be required to request an alternate method of compliance
(AMOC).
We disagree with delaying issuance of this AD. However, we agree
that clarification is needed in regard to the use of spring washers.
Certain airplanes may use spring washers in lieu of conical springs in
their relay assembly. Both the conical springs and spring washers are
retained from the existing relay assembly to be used with the new
relay. Either one of them is considered acceptable for use. New
paragraph (m) has been added to the AD to identify the use of spring
washers as an acceptable method of compliance if they are part of the
existing relay assembly.
Request To Delay Issuance of AD To Specify Label Installation
JAL requested that we delay the issuance of this AD until GE
Aviation publishes new revisions to their service information
(referenced in the NPRM) 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.
We disagree with the request to delay this AD until GE Aviation
issues revised service information. However, 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 GE Aviation Service Bulletins
5000ELM-28-456 and 6000ELM-28-457, both Revision 1, both dated January
7, 2010, to be accomplished. We have added paragraph (n) to this AD to
provide an optional method of labeling.
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 2 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Parts Cost on U.S.
Action Labor cost cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Installation: Groups 1 and 2, 149 work-hours x $85 per $15,719 $28,384............ $56,768.
Configuration 2. hour = $12,665.
Installation: Groups 1 and 2, 2 work-hours x $85 per 15,719 $15,889............ $31,778.
Configuration 1. hour = $170.
Concurrent requirement: Install 3 work-hours x $85 per 0 $255............... $510.
ELMS software. hour = $255.
Concurrent requirement: Upgrade Up to 2 work-hours x $85 0 Up to $170......... Up to $340.
AIMS-2 software. per hour = Up to $170.
Concurrent requirement: P110 3 work-hours x $85 per $1,164 $1,419............. $2,838.
wiring changes. hour = $255.
[[Page 22307]]
Concurrent requirement: P210 3 work-hours x $85 per 1,164 $1,419............. $2,838.
wiring changes. hour = $255.
----------------------------------------------------------------------------------------------------------------
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):
2011-09-05 The Boeing Company: Amendment 39-16667; Docket No. FAA-
2010-1271; Directorate Identifier 2010-NM-187-AD.
Effective Date
(a) This AD is effective May 26, 2011.
Affected ADs
(b) None.
Applicability
(c) The Boeing Company Model 777-200, -300, and -300ER series
airplanes; certificated in any category; as identified in Boeing
Service Bulletin 777-28A0047, Revision 5, dated September 20, 2010.
Subject
(d) Joint Aircraft System Component (JASC)/Air Transport
Association (ATA) of America Code 28, Fuel.
Unsafe Condition
(e) This AD was prompted by results from 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.
Compliance
(f) Comply with this AD within the compliance times specified,
unless already done.
Installation
(g) For airplanes in Groups 1 and 2, Configuration 2, as
identified in Boeing Service Bulletin 777-28A0047, Revision 5, dated
September 20, 2010: Within 36 months after the effective date of
this AD, install a new P301 panel on the left side of the airplane,
install a new P302 panel on the right side of the airplane, and
change the wiring, in accordance with the Accomplishment
Instructions of Boeing Service Bulletin 777-28A0047, Revision 5,
dated September 20, 2010, except as required by paragraphs (m) and
(n) of this AD.
(h) For airplanes in Groups 1 and 2, Configuration 1, as
identified in Boeing Service Bulletin 777-28A0047, Revision 5, dated
September 20, 2010: Within 36 months after the effective date of
this AD, perform bonding resistance measurements and rework the
airplane installation as applicable, depending on airplane
configuration, in accordance with the Accomplishment Instructions of
Boeing Service Bulletin 777-28A0047, Revision 5, dated September 20,
2010.
Concurrent Requirements
(i) Prior to or concurrently with accomplishing the requirements
of paragraph (g) of this AD, do the actions specified in paragraphs
(i)(1), (i)(2), (i)(3), and (i)(4) of this AD.
(1) Install new software in the electrical load management
system (ELMS) electronics units in the P110, P210, and P310 power
management panels, in accordance with the Accomplishment
Instructions of Boeing Service Bulletin 777-28A0040, Revision 1,
dated March 18, 2010.
(2) Install airplane information management system 2 (AIMS-2)
software in the AIMS-2 hardware, in accordance with the
Accomplishment Instructions of Boeing Special Attention Service
Bulletin 777-31-0097, Revision 3, dated February 22, 2007.
(3) Modify the P110 left power management panel by incorporating
wiring changes, in accordance with the Accomplishment Instructions
of GE Aviation Service Bulletin 5000ELM-28-456, Revision 1, dated
January 7, 2010, except as provided by paragraphs (m) and (n) of
this AD.
(4) Modify the P210 right power management panel by
incorporating wiring changes, in accordance with the Accomplishment
Instructions of GE Aviation Service Bulletin 6000ELM-28-457,
Revision 1, dated January 7, 2010, except as provided by paragraphs
(m) and (n) of this AD.
Credit for Actions Accomplished in Accordance With Previous Service
Information
(j) Installations done before the effective date of this AD in
accordance with Boeing Alert Service Bulletin 777-28A0040, dated
April 13, 2007, are acceptable for compliance with the requirements
of paragraph (i)(1) of this AD.
(k) Installations done before the effective date of this AD in
accordance with Boeing Service Bulletin 777-28A0047, Revision 3,
dated June 11, 2009; or Revision 4, dated May 20, 2010; are
acceptable for compliance with the requirements of paragraphs (g)
and (h) of this AD.
(l) Installations done before the effective date of this AD in
accordance with Boeing Special Attention Service Bulletin 777-31-
0097, dated March 30, 2006; Revision 1, dated August 10, 2006; or
Revision 2, dated October 26, 2006; are acceptable for
[[Page 22308]]
compliance with the requirements of paragraph (i)(2) of this AD.
Optional Methods of Compliance With Certain Actions
(m) Where paragraph 2.A.(16) and Figure 8 of GE Aviation Service
Bulletins 5000ELM-28-456 and 6000ELM-28-457, both Revision 1, both
dated January 7, 2010, identify the installation of conical springs
for the relay to relay base fixing, installation of spring washers
is an acceptable method of compliance when they are part of the
existing relay assembly.
(n) Where paragraphs 2.A.(24) and 2.A.(25) of GE Aviation
Service Bulletins 5000ELM-28-456 and 6000ELM-28-457, both Revision
1, both dated January 7, 2010, specify the installation of a label
to identify work carried out and to identify the appropriate service
bulletin, an acceptable method of compliance is to use a suitable
method to indelibly mark the appropriate service bulletin number on
the reworked panel. Boeing Standard BAC5307 may be used as an
additional source of guidance for part marking.
Alternative Methods of Compliance (AMOCs)
(o)(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
(p) 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; phone: 425-917-6482; fax: 425-917-
6590; e-mail: Georgios.Roussos@faa.gov.
Material Incorporated by Reference
(q) You must use the applicable service information contained in
table 1 of this AD to do the actions required by this AD, unless the
AD specifies otherwise.
Table 1--All Material Incorporated by Reference
------------------------------------------------------------------------
Document Revision Date
------------------------------------------------------------------------
Boeing Service Bulletin 777- 5 September 20, 2010.
28A0047.
Boeing Service Bulletin 777- 1 March 18, 2010.
28A0040.
Boeing Special Attention 3 February 22, 2007.
Service Bulletin 777-31-
0097.
GE Aviation Service Bulletin 1 January 7, 2010.
5000ELM-28-456.
GE Aviation Service Bulletin 1 January 7, 2010.
6000ELM-28-457.
------------------------------------------------------------------------
(1) The Director of the Federal Register approved the
incorporation by reference of the service information contained in
Table 1 of this AD 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 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 GE
Aviation service information identified in this AD, contact GE
Aviation, Customer Services--Clearwater, P.O. Box 9013, Clearwater,
Florida 33758; telephone 727-539-1631; fax 727-539-0680; e-mail
cs.support@ge.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 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 12, 2011.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2011-9283 Filed 4-20-11; 8:45 am]
BILLING CODE 4910-13-P
