[Federal Register Volume 78, Number 76 (Friday, April 19, 2013)]
[Rules and Regulations]
[Pages 23468-23472]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2013-08742]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2012-0803; Directorate Identifier 2011-NM-214-AD;
Amendment 39-17419; AD 2013-08-02]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are superseding an existing airworthiness directive (AD)
that applies to all The Boeing Company Model 777-200, -200LR, -300, and
-300ER series airplanes. That AD currently requires repetitive
inspections for cracking of the elevator actuator fittings. This new AD
requires, for previously modified airplanes, repetitive inspections for
movement of the fittings or fastener heads, and eventual replacement of
certain bolts (including related investigative and corrective actions
if necessary). For all airplanes, this replacement, with corrected
torque values, would terminate the requirements of the existing AD.
This new AD also removes certain airplanes from the applicability. This
AD was prompted by the manufacturer's development of a modification
that was approved as an optional terminating action to the existing
AD's required repetitive inspections. We have been advised that the
modification procedures include certain incorrect torque values. We are
issuing this AD to detect and correct a cracked actuator fitting or
incorrectly installed bolts to the actuator fitting, which could lead
to the elevator becoming detached and unrestrained, and a consequent
unacceptable flutter condition and loss of control of the airplane.
DATES: This AD is effective May 24, 2013.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of May 24, 2013.
The Director of the Federal Register approved the incorporation by
reference of a certain other publication listed in this AD as of
January 22, 2008 (72 FR 71212, December 17, 2007).
ADDRESSES: For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-
5000, extension 1; fax206-766-5680; 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 http://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: Melanie Violette, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue SW., Renton, WA 985057-3356; phone: 425-917-6422; fax:
425-917-6590; email: [email protected].
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2007-26-05, Amendment 39-15307 (72 FR 71212,
December 17, 2007). That AD applies to the specified products. The NPRM
published in the Federal Register on August 3, 2012 (77 FR 46340). The
NPRM proposed to continue to require repetitive dye penetrant or high-
frequency eddy current (HFEC) inspections, or detailed inspections for
cracking of the elevator actuator fittings, and replacement of any
cracked fitting. The NPRM also proposed to require, for previously
modified airplanes, repetitive inspections for movement of the fittings
or fastener heads, and eventual replacement of certain bolts (including
related investigative and corrective actions if necessary). For all
airplanes, this replacement, with corrected torque values, would
terminate the requirements of the existing AD. The NPRM also proposed
to remove certain airplanes from the applicability.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the proposal
(77 FR 46340, August 3, 2012) and the FAA's response to each comment.
Support for the NPRM (77 FR 46340, August 3, 2012)
Boeing supports the NPRM (77 FR 46340, August 3, 2012).
Request To Amend Installed Part Number (P/N)
Air New Zealand requested that we revise the NPRM (77 FR 46340,
August 3, 2012) to require that the installed part number be amended to
reflect accomplishment of Boeing Alert Service Bulletin 777-55A0016,
Revision 1, dated August 25, 2011, instead of the current data plate
modification. Air New Zealand explained that the benefits of Boeing re-
numbering the modified elevator assembly would be to ensure that the
airplane shows clear pre/post modification configuration of the
elevator assemblies, and also that the part number changes would add
clarity. Air New Zealand reasoned that, otherwise, installing a pre-
modified elevator and not re-instating the repeat inspection per Boeing
Alert Service Bulletin 777-55A0015 would be an unsafe condition and
that the airplane would be out of compliance with the NPRM.
Air New Zealand also indicated that accomplishment of Boeing Alert
Service Bulletin 777-55A0016, Revision 1, dated August 25, 2011, leaves
the elevator assembly part number unaffected, but the elevator data
plate has the service bulletin added to it. Air New Zealand also noted
that Boeing Alert Service Bulletin 777-55A0016, Revision 1, dated
August 25, 2011, modifies the elevator as a stand-alone component and
does not affect the airframe. Further, Air New Zealand stated that the
elevator assembly is an interchangeable component, but the current
illustrated parts catalog (IPC) does not show a one-way part
interchangeability with pre- and post-embodiment of Boeing Alert
Service Bulletin 777-55A0016, Revision 1, dated August 25, 2011,
terminating action assemblies due to the part number remaining
unchanged.
Air New Zealand expressed that, if an operator accomplishes Boeing
Alert
[[Page 23469]]
Service Bulletin 777-55A0016, Revision 1, dated August 25, 2011, the
repeat inspections of Boeing Alert Service Bulletin 777-55A0015 are
terminated. Air New Zealand stated that the risk is that if an
unscheduled maintenance occurs that replaces the elevator, the operator
could potentially install a pre-modified elevator and not reinstate the
repeat mandatory inspections specified in Boeing Alert Service Bulletin
777-55A0015, because no part number changed and no IPC
interchangeability information was available.
We do not agree to revise this AD to require that the installed
part number be amended instead of the current data plate modification.
The operator is responsible for ensuring that each airplane is
maintained in an airworthy condition, and is in compliance with all
regulations. FAA Advisory Circular 39-9, ``Airworthiness Directives
Management Process,'' Change 2, dated December 7, 2012 (http://
rgl.faa.gov/Regulatory--and--Guidance--Library/rgAdvisoryCircular.nsf/
0/31573c7680b14363862578a80051646f/$FILE/AC%2039-9%20CHG%202.pdf),
describes acceptable means for complying with Part 39 requirements for
ADs. Boeing has amended the elevator part number, effective with
airplane line number 718, which had the modified fitting installed in
production. The IPC currently shows that the new elevator (P/N
183W0061-17/18) may not be replaced by an older one (e.g., P/N
183W0061-15/16).
However, we have discovered the existence of a P/N 183W0001
elevator interchangeability drawing, internal to Boeing, which
potentially could permit parts covered within the scope of this AD to
be installed on airplanes beyond the scope of this AD. Therefore, we
have added new paragraph (m) to this AD that explicitly prohibits the
use of the elevator interchangeability drawing with this AD, to
preclude its use in the event that the drawing becomes available to
operators.
Request To Allow for Optional Replacement
American Airlines (AA) requested that we revise the NPRM (77 FR
46340, August 3, 2012) to allow for optional replacement of the
fittings with new, improved fittings using Boeing Alert Service
Bulletin 777-55A0016, Revision 1, dated August 25, 2011.
We agree with the request to allow for optional replacement of the
fittings with new, improved fittings using Boeing Alert Service
Bulletin 777-55A0016, Revision 1, dated August 25, 2011. Paragraph (i)
of the NPRM (77 FR 46340, August 3, 2012) already allows for the
optional replacement of the fittings with new fittings using Boeing
Alert Service Bulletin 777-55A0016, Revision 1, dated August 25, 2011.
No change is necessary in this regard.
Request To Exclude Requirement From Service Bulletin in NPRM (77 FR
46340, August 3, 2012)
AA requested that we revise the NPRM (77 FR 46340, August 3, 2012)
to state that the instruction to ``Put the airplane back to serviceable
condition,'' which is found in Boeing Alert Service Bulletin 777-
55A0016, Revision 1, dated August 25, 2011, is not required by the
NPRM. AA explained that this requirement does not affect the condition
that the NPRM seeks to address. AA reasoned that, as most operators
will accomplish these modifications as part of a maintenance visit,
returning the airplane to a serviceable condition will not be possible
in the context of that statement, but would occur instead at a point in
time well after this work is complete.
We agree with the request to state that the phrase ``Put the
airplane back to serviceable condition,'' which is referenced in the
service information specified in this AD, is not mandated by this final
rule. Other regulations require restoring the airplane to serviceable
condition before further flight. Therefore, we added an exception in a
new paragraph (j)(2) of this AD regarding the language in the service
information. In addition, we added a reference to paragraph (j)(2) in
paragraphs (g)(1), (g)(2), (h), (h)(1)(ii), (h)(2) and (i) of this AD.
Request for Credit for Elevator Installation
United Airlines (UA) requested that we revise the NPRM (77 FR
46340, August 3, 2012) to include terminating action credit for the
installation of a new elevator, as specified by Boeing Alert Service
Bulletin 777-55A0016, dated October 27, 2009, including the correct
torque values specified in Boeing Alert Service Bulletin 777-55A0016,
Revision 1, dated August 25, 2011. UA explained that paragraph (k) of
the NPRM (paragraph (l) of this final rule) does not provide credit for
installation of a new elevator that has complied with the actions
specified in Boeing Alert Service Bulletin 777-55A0016, dated October
27, 2009, including the correct torque values specified in Boeing Alert
Service Bulletin 777-55A0016, Revision 1, dated August 25, 2011. UA
expressed that, following accomplishment of Boeing Alert Service
Bulletin 777-55A0016, dated October 27, 2009, using the higher torque
values, it removed both elevators and inspected the fasteners using
Boeing procedures. UA stated that damage was found on the right-hand
elevator and it elected to replace the existing elevator (-2B) with a
new production elevator (-18B), which had the post-service bulletin
configuration with the new actuator fittings installed from production
using the correct torque values for the fasteners.
We agree to allow replacement of elevators, as an additional method
of compliance for this AD. We have added paragraph (k) to this final
rule to allow replacement.
Explanation of Change Made to This AD
We have clarified in paragraph (g)(2) of this final rule, that
after the effective date of this AD, Boeing Service Bulletin 777-
55A0015, Revision 3, dated November 24, 2009, must be used to
accomplish the actions required by paragraph (g)(2) of this final rule.
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--and minor editorial
changes. We have determined that these minor changes:
Are consistent with the intent that was proposed in the
NPRM (77 FR 46340, August 3, 2012) for correcting the unsafe condition;
and
Do not add any additional burden upon the public than was
already proposed in the NPRM (77 FR 46340, August 3, 2012)
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 139 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
[[Page 23470]]
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Inspection (retained actions from 10 work-hours x $85 $0 $850, per $118,150, per
AD 2007-26-05, Amendment 39- per hour = $850, inspection cycle. inspection cycle.
15307 (72 FR 71212, December 17, per inspection
2007)). cycle.
Inspection (new action).......... 14 work-hours x $85 0 $1,190............. Up to $165,410, per
per hour = $1,190, inspection cycle.
per inspection
cycle.
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary replacements
that would be required based on the results of the inspections. We have
no way of determining the number of aircraft that might need these
replacements:
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Action Labor cost Parts cost Cost per product
----------------------------------------------------------------------------------------------------------------
Fitting replacement......................... 132 work-hours x $85 per hour $21,643 $32,863
= $11,220.
Bolt replacement............................ 105 work-hours x $85 per hour $65 $8,990
= $8,925.
----------------------------------------------------------------------------------------------------------------
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We have determined that this AD will not have federalism
implications under Executive Order 13132. This AD will not have a
substantial direct effect on the States, on the relationship between
the national government and the States, or on the distribution of power
and responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation in Alaska, and
(4) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing airworthiness directive (AD)
2007-26-05, Amendment 39-15307 (72 FR 71212, December 17, 2007), and
adding the following new AD:
2013-08-02 The Boeing Company: Amendment 39-17419; Docket No. FAA-
2012-0803; Directorate Identifier 2011-NM-214-AD.
(a) Effective Date
This airworthiness directive (AD) is effective May 24, 2013.
(b) Affected ADs
This AD supersedes AD 2007-26-05, Amendment 39-15307 (72 FR
71212, December 17, 2007).
(c) Applicability
This AD applies to The Boeing Company Model 777-200, -200LR, -
300, and -300ER series airplanes, certificated in any category, as
identified in Boeing Alert Service Bulletin 777-55A0016, Revision 1,
dated August 25, 2011.
(d) Subject
Joint Aircraft System Component (JASC)/Air Transport Association
(ATA) of America Code 55, Stabilizers.
(e) Unsafe Condition
This AD was prompted by a report of a cracked left elevator
actuator fitting, and the recent determination that certain
incorrect torque values had been specified for an alternative method
of compliance intended to terminate the requirements of AD 2007-26-
05, Amendment 39-15307 (72 FR 71212, December 17, 2007). We are
issuing this AD to detect and correct a cracked actuator fitting or
incorrectly installed bolts to the actuator fitting, which could
lead to the elevator becoming detached and unrestrained, and a
consequent unacceptable flutter condition and loss of control of the
airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Inspections and Corrective Actions With Revised Service
Information
This paragraph restates the inspections and corrective actions
required by paragraph (f) of AD 2007-26-05, Amendment 39-15307 (72
FR 71212, December 17, 2007), with revised service information.
(1) Except as provided by paragraph (j)(2) of this AD: Do all
inspections and actions described in paragraphs (g)(1) and (g)(2) of
this AD, in accordance with the Accomplishment Instructions of
Boeing Alert Service Bulletin 777-55A0015, dated April 19, 2007; or
Boeing Service Bulletin 777-55A0015, Revision 3, dated November 24,
2009. At the applicable time specified in paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 777-55A0015, dated
[[Page 23471]]
April 19, 2007, except as provided by paragraph (g)(3) of this AD,
do an initial dye penetrant or high frequency eddy current (HFEC)
inspection for cracking of the elevator actuator fittings, and,
thereafter, do repetitive dye penetrant, HFEC, or detailed
inspections at the applicable times specified in paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 777-55A0015, dated
April 19, 2007. As of the effective date of this AD, Boeing Service
Bulletin 777-55A0015, Revision 3, dated November 24, 2009, must be
used to accomplish the actions required by this paragraph.
(2) Before further flight, replace any fitting found to be
cracked during any inspection required by paragraph (g)(1) of this
AD with a new fitting having the same part number, or an optional
part number, as identified in Boeing Alert Service Bulletin 777-
55A0015, dated April 19, 2007; or Boeing Service Bulletin 777-
55A0015, Revision 3, dated November 24, 2009; except as provided by
paragraph (j)(2) of this AD. Thereafter, do initial and repetitive
inspections of the replacement fitting at the time specified in
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
777-55A0015, dated April 19, 2007. As of the effective date of this
AD, Boeing Service Bulletin 777-55A0015, Revision 3, dated November
24, 2009, must be used to accomplish the actions required by this
paragraph.
(3) Where Boeing Alert Service Bulletin 777-55A0015, dated April
19, 2007, specifies a compliance time after the date on that service
bulletin, this AD requires compliance within the specified
compliance time after January 22, 2008 (the effective date of AD
2007-26-05, Amendment 39-15307 (72 FR 71212, December 17, 2007)).
(h) New Additional Actions for Certain Airplanes
For airplanes on which the elevator actuator fitting assemblies
have been replaced using the fastener torque values specified in
Boeing Alert Service Bulletin 777-55A0016, dated October 27, 2009:
Within 180 days after the effective date of this AD, do a detailed
inspection of the elevator actuator fitting assemblies to detect
discrepancies (including indications of fastener head movement and
fitting movement along the spar web), in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 777-
55A0016, Revision 1, dated August 25, 2011, except as provided by
paragraph (j)(2) of this AD.
(1) If no discrepancy is detected, do the actions specified in
paragraphs (h)(1)(i) and (h)(1)(ii) of this AD.
(i) Repeat the inspection thereafter at intervals not to exceed
90 days or 360 flight cycles, whichever occurs first, until the
actions specified in paragraph (h)(1)(ii) of this AD are done.
(ii) Within 4,200 flight cycles or 750 days after the effective
date of this AD, whichever occurs first, replace the 12 bolts common
to the elevator actuator fitting and the spar web, and do all
applicable related investigative and corrective actions, in
accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 777-55A0016, Revision 1, dated August 25, 2011,
except as provided by paragraphs (j)(1) and (j)(2) of this AD. Do
all applicable related investigative and corrective actions before
further flight. The replacement of all 12 bolts in accordance with
the Accomplishment Instructions of Boeing Alert Service Bulletin
777-55A0016, Revision 1, dated August 25, 2011, terminates the
requirements of paragraphs (g) and (h) of this AD for that fitting
only.
(2) If any discrepancy is detected, before further flight,
replace the 12 bolts common to the elevator actuator fitting and the
spar web using new parts, and do all applicable related
investigative and corrective actions, in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 777-
55A0016, Revision 1, dated August 25, 2011, except as provided by
paragraphs (j)(1) and (j)(2) of this AD. Do all applicable related
investigative and corrective actions before further flight. The
replacement of all 12 bolts in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin 777-55A0016, Revision
1, dated August 25, 2011, terminates the requirements of paragraphs
(g) and (h) of this AD for that fitting only.
(i) New Optional Replacement of Elevator Actuator Fitting Assembly
For airplanes on which the elevator actuator fitting assemblies
have not been replaced as specified in Boeing Alert Service Bulletin
777-55A0016, dated October 27, 2009: Replacement of these fitting
assemblies with new parts, in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin 777-55A0016, Revision
1, dated August 25, 2011, except as provided by paragraphs (j)(1)
and (j)(2) of this AD, terminates the requirements of paragraphs (g)
and (h) of this AD.
(j) Exceptions
(1) If any discrepancy or cracking is found during any
inspection required by this AD, and Boeing Alert Service Bulletin
777-55A0016, Revision 1, dated August 25, 2011, specifies to contact
Boeing for appropriate action: Before further flight, repair using a
method approved in accordance with the procedures specified in
paragraph (n) of this AD.
(2) Where the service bulletins identified in paragraphs
(j)(2)(i), (j)(2)(ii), and (j)(2)(iii) of this AD specify to ``Put
airplane back in a serviceable condition,'' this AD does not require
that action.
(i) Boeing Alert Service Bulletin 777-55A0015, dated April 19,
2007.
(ii) Boeing Service Bulletin 777-55A0015, Revision 3, dated
November 24, 2009.
(iii) Boeing Alert Service Bulletin 777-55A0016, Revision 1,
dated August 25, 2011.
(k) New Optional Replacement of Elevator
Replacing the elevator with a new elevator terminates the
requirements of paragraphs (g) and (h) of this AD, provided that the
elevator actuator fitting configuration on the new elevator complies
with the modification and bolt torque values defined in the
Accomplishment Instructions of Boeing Alert Service Bulletin 777-
55A0016, Revision 1, dated August 25, 2011.
(l) Credit for Previous Actions
This paragraph provides credit for inspecting and replacing
actuator fittings, as required by paragraph (g) of this AD, if the
inspection and replacement were performed before the effective date
of this AD using a service bulletin specified in paragraph (l)(1) or
(l)(2) of this AD, and using the correct torque values as specified
in Boeing Alert Service Bulletin 777-55A0016, Revision 1, dated
August 25, 2011.
(1) Boeing Service Bulletin 777-55A0015, Revision 1, dated
January 31, 2008, which is not incorporated by reference in this AD.
(2) Boeing Service Bulletin 777-55A0015, Revision 2, dated
December 4, 2008, which is not incorporated by reference in this AD.
(m) Parts Installation Prohibition
As of the effective date of this AD, no person may use the
interchangeability table on Boeing Elevator Assembly Drawing
183W0001 (Table 1, Sheet 1), to install an elevator or elevator part
on any airplane.
(n) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Seattle Aircraft Certification Office (ACO),
FAA, has the authority to approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19. In accordance with 14
CFR 39.19, send your request to your principal inspector or local
Flight Standards District Office, as appropriate. If sending
information directly to the manager of the ACO, send it to the
attention of the person identified in the Related Information
section of this AD. Information may be emailed to: [email protected].
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
(3) An AMOC that provides an acceptable level of safety may be
used for any repair required by this AD if it is approved by The
Boeing Commercial Airplanes Organization Designation Authorization
(ODA) that has been authorized by the Manager, Seattle ACO, to make
those findings. For a repair method to be approved, the repair must
meet the certification basis of the airplane, and the approval must
specifically refer to this AD.
(4) AMOCs approved previously in accordance with AD 2007-26-05,
Amendment 39-15307 (72 FR 71212, December 17, 2007), are not
approved as AMOCs for this AD.
(o) Related Information
(1) For more information about this AD, contact Melanie
Violette, Aerospace Engineer, Airframe Branch, ANM-120S, FAA,
Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton,
WA 985057-3356; phone: 425-917-6422; fax: 425-917-6590; email:
[email protected].
(2) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-
5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. You
[[Page 23472]]
may review copies of the referenced service information at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue SW., Renton,
Washington 985057-3356. For information on the availability of this
material at the FAA, call 425-227-1221
(p) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(3) The following service information was approved for IBR on
May 24, 2013.
(i) Boeing Service Bulletin 777-55A0015, Revision 3, dated
November 24, 2009.
(ii) Boeing Alert Service Bulletin 777-55A0016, Revision 1,
dated August 25, 2011.
(4) The following service information was approved for IBR on
January 22, 2008 (72 FR 71212, December 17, 2007).
(i) Boeing Alert Service Bulletin 777-55A0015, dated April 19,
2007.
(ii) Reserved.
(5) For Boeing service information identified in this AD,
contact Boeing Commercial Airplanes, Attention: Data & Services
Management, P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207;
telephone 206-544-5000, extension 1; fax 206-766-5680; Internet
https://www.myboeingfleet.com.
(6) You may view this service information at FAA, 1601 Lind
Avenue SW., Renton, Washington. For information on the availability
of this material at the FAA, call 425-227-1221.
(7) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on April 2, 2013.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2013-08742 Filed 4-18-13; 8:45 am]
BILLING CODE 4910-13-P