[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]


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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.

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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