Airworthiness Directives; the Boeing Company Airplanes

[Federal Register Volume 78, Number 180 (Tuesday, September 17, 2013)]
[Rules and Regulations]
[Pages 57049-57053]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2013-22414]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0301; Directorate Identifier 2013-NM-025-AD; 
Amendment 39-17575; AD 2013-18-02]
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 adopting a new airworthiness directive (AD) for certain 
The Boeing Company Model 767-200, -300, -300F, and -400ER series 
airplanes. This AD was prompted by reports of cracked and corroded nuts 
on an outboard flap support rib. This AD requires, for certain 
airplanes, repetitive inspections of the cap seal for damaged sealant 
on nuts common to certain outboard flap support ribs, and related 
investigative and corrective actions if necessary. For certain other 
airplanes, this AD also requires repetitive inspections of the cap seal 
for damaged sealant on nuts common to certain outboard flap support 
ribs, related investigative and corrective actions if necessary, and if 
necessary, a detailed inspection to determine the nut type installed in 
the outboard flap support rib and corrective actions. This AD also 
provides terminating action for the repetitive inspections under 
certain conditions. We are issuing this AD to detect and correct 
cracked and corroded nuts and bolts and the installation of incorrect 
nuts on certain outboard flap support ribs, which could lead to 
additional nut and bolt damage in the joint, result in loss of an 
outboard flap, and adversely affect continued safe flight and landing 
of the airplane.

DATES: This AD is effective October 22, 2013.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of October 22, 
2013.

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; fax 206-766-5680; 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: Berhane Alazar, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue SW., Renton, Washington 98057-3356; phone: 425-917-
6577; 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 include an AD that would apply to the specified products. 
The NPRM published in the Federal Register on April 10, 2013 (78 FR 
21276). The NPRM proposed to require, for certain airplanes, repetitive 
inspections of the cap seal for damaged sealant on nuts common to 
certain outboard flap support ribs, related investigative and 
corrective actions if necessary, and replacement of all fasteners in 
the support ribs, which terminates the repetitive inspections. For 
certain other airplanes, the NPRM proposed to require repetitive

[[Page 57050]]

inspections of the cap seal for damaged sealant on nuts common to 
certain outboard flap support ribs, related investigative and 
corrective actions if necessary, and if necessary, a detailed 
inspection to determine the nut type installed in the outboard flap 
support rib and corrective actions. For those airplanes, the NPRM also 
proposed to provide for optional replacement of all fasteners in the 
support ribs, which would terminate the repetitive inspections.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the proposal 
(78 FR 21276, April 10, 2013) and the FAA's response to each comment.

Request To Refer to Revised Service Information

    Japan Airlines, UPS, and Boeing stated that Boeing has issued 
revised service information and requested that the service information 
referenced in the NPRM (78 FR 21276, April 10, 2013) be updated to 
refer to Boeing Service Bulletin 767-57A0131, Revision 1, dated May 8, 
2013.
    We agree with the commenters' requests and have revised paragraphs 
(c), (g), (h), (i), and (j) of this final rule to include Boeing 
Service Bulletin 767-57A0131, Revision 1, dated May 8, 2013. We have 
also added a new paragraph (k) of this AD to provide credit for actions 
accomplished before the effective date of this AD using Boeing Alert 
Service Bulletin 767-57A0131, dated October 30, 2012, and reidentified 
the subsequent paragraphs.

Clarification Regarding the Installation of Winglets

    Aviation Partners Boeing and UPS stated that the installation of 
winglets per Supplemental Type Certificate (STC) ST01920SE (http://
rgl.faa.gov/Regulatory--and--Guidance--Library/rgstc.nsf/0/
59027f43b9a7486e86257b1d006591ee/$FILE/ST01920SE.pdf) does not affect 
the accomplishment of the manufacturer's service instructions.
    We agree with the commenters' statements that the installation of 
winglets as specified in STC ST01920SE (http://rgl.faa.gov/Regulatory--
and--Guidance--Library/rgstc.nsf/0/59027f43b9a7486e86257b1d006591ee/
$FILE/ST01920SE.pdf) does not affect accomplishment of the requirements 
of this AD, and for airplanes on which STC ST01920SE is installed, a 
``change in product'' AMOC approval request is not necessary to comply 
with the requirements of section 39.17 of the Federal Aviation 
Regulations (14 CFR 39.17). We have added this provision in new 
paragraph (c)(2) of this final rule.

Request To Correct a Reference to a Table Number

    UPS noted a typographical error in paragraph (h)(1)(i) of the NPRM 
(78 FR 21276, April 10, 2013). The inspection intervals are identified 
in table 2 of paragraph 1.E., ``Compliance,'' of Boeing Service 
Bulletin 767-57A0131, Revision 1, dated May 8, 2013, and the NPRM 
erroneously referred to table 1.
    We agree there is an error and have revised paragraph (h)(1)(i) of 
this AD to refer to table 2 of paragraph 1.E., ``Compliance,'' of 
Boeing Service Bulletin 767-57A0131, Revision 1, dated May 8, 2013.

Request To Clarify Terminating Action

    UPS noted that paragraph (i) of the NPRM (78 FR 21276, April 10, 
2013) implies that the only terminating action for the repetitive 
inspections proposed by paragraph (h) of the NPRM is replacement of all 
fasteners within a support rib. UPS stated that the Boeing service 
information provides terminating action by replacing fasteners at all 
discrepant or corroded locations and/or the verification of correct nut 
type at all other locations. UPS requested that these corrective 
actions be identified as terminating action for the inspections 
proposed by paragraph (h) of the NPRM for the associated support rib.
    We agree that clarification is needed regarding terminating action 
for the repetitive inspections required by paragraph (h) of this final 
rule. We have changed the header of paragraph (i) of this final rule to 
``Terminating Action for Repetitive Inspections'' and split the 
paragraph into three subparagraphs. Paragraph (i)(1) of this final rule 
states that, if during any inspection required by paragraphs (g) or (h) 
of this AD, any cracking is found, all fasteners within a support rib 
must be replaced to terminate the repetitive inspections for that 
support rib only. New paragraph (i)(2) of this final rule states that 
if a discrepancy other than cracking is found (e.g., corrosion) during 
any inspection required by paragraph (g) of this final rule, all 
fasteners within a support rib must be replaced to terminate the 
repetitive inspections for that support rib only. New paragraph (i)(3) 
of this final rule states that if a discrepancy other than cracking is 
found (e.g., corrosion) during any inspection required by paragraph (h) 
of this final rule, replacing the affected fastener terminates the 
repetitive inspections for only that fastener within that support rib.

Request To Combine Paragraphs (h)(1) and (h)(2) of the NPRM (78 FR 
21276, April 10, 2013)

    UPS stated that the intent of paragraph (h) of the NPRM (78 FR 
21276, April 10, 2013) is to identify the requirements of the initial 
inspection, and the intent of paragraphs (h)(1) and (h)(2) of the NPRM 
is to identify the requirements of the repetitive inspections based on 
the findings of the initial inspection. UPS stated that the 
investigative and corrective actions applicable to paragraph (h)(1) of 
the NPRM are the same as those in paragraph (h)(2) of the NPRM and 
suggested that these two paragraphs could be combined without affecting 
the intent of this AD.
    We do not agree that paragraphs (h)(1) and (h)(2) of this final 
rule can be combined. Paragraph (h)(1) of this final rule describes 
actions based on the findings of the cap seal detailed inspections, and 
paragraph (h)(2) of this final rule addresses actions based on the 
findings of the inspections for the nuts, bolts, and washers on the 
support ribs. We have not changed this final rule in this regard.

Request To Change Compliance Time for Initial Detailed Inspection

    UPS requested that the threshold for conducting the initial 
detailed inspection of the cap seal required by paragraphs (g) and (h) 
of the NPRM (78 FR 21276, April 10, 2013) be extended from 12 months to 
24 months. UPS commented that if it is not possible to extend the 
threshold for the initial inspection, then the text should be revised 
to read ``12 months after the AD effective date or within the 
appropriate total years of aircraft service-life''--whichever occurs 
later. UPS requested this change to reflect the reported technical data 
as well as to give operators time to schedule the task at a facility 
capable of accomplishing the scope of the work.
    We do not agree with UPS's request to extend the threshold for the 
initial detailed inspection. We have determined that the compliance 
time, as proposed, represents the maximum interval of time allowable 
for the affected airplanes to continue to safely operate before the 
initial inspection is done. Since maintenance schedules vary among 
operators, there would be no assurance that the airplane would be 
modified during that maximum interval. We have not changed this final 
rule in this regard.

[[Page 57051]]

    Furthermore, we do not agree with UPS's request to revise the 
compliance time text to include ``or within the appropriate total years 
of aircraft service-life''--whichever occurs later. The installation of 
an incorrect nut during production, and the possibility of the nut 
cracking due to being overtorqued, is unrelated to the age of the 
airplane. We have not changed this final rule in this regard.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
this AD with the changes described previously--and minor editorial 
changes. We have determined that these minor changes:
    <bullet> Are consistent with the intent that was proposed in the 
NPRM (78 FR 21276, April 10, 2013) for correcting the unsafe condition; 
and
    <bullet> Do not add any additional burden upon the public than was 
already proposed in the NPRM (78 FR 21276, April 10, 2013).
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this AD.

Costs of Compliance

    We estimate that this AD affects 440 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
               Action                         Labor cost            Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Detailed inspections...............  1 work-hour x $85 per hour               $0             $85         $37,400
                                      = $85.
Replacement of all fasteners (Group  2 work-hours x $85 per hour           2,553           2,723       1,198,120
 1 airplanes).                        = $170.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary related 
investigative and corrective actions and detailed inspections for nut 
type 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 
actions.

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                 Action                          Labor cost             Parts cost         Cost per product
----------------------------------------------------------------------------------------------------------------
Related investigative and corrective     Up to 3 work-hours x $85            $2,553   Up to $2,808.
 actions and detailed inspection for      per hour = $255.
 nut type.
----------------------------------------------------------------------------------------------------------------

    According to the manufacturer, some of the costs of this AD may be 
covered under warranty, thereby reducing the cost impact on affected 
individuals. We do not control warranty coverage for affected 
individuals. As a result, we have included all costs in our cost 
estimate.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII: Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, 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, 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):

2013-18-02 The Boeing Company: Amendment 39-17575; Docket No. FAA-
2013-0301; Directorate Identifier 2013-NM-025-AD.

(a) Effective Date

    This AD is effective October 22, 2013.

(b) Affected ADs

    None.

(c) Applicability

    (1) This AD applies to The Boeing Company Model 767-200, 767-
300, 767-300F, and 767-400ER series airplanes; certificated in any 
category; as identified in Boeing Service Bulletin 767-57A0131, 
Revision 1, dated May 8, 2013.
    (2) Installation of Supplemental Type Certificate (STC) 
ST01920SE (http://rgl.faa.gov/Regulatory--and--Guidance--Library/
rgstc.nsf/0/59027f43b9a7486e86257b1d006591ee/

[[Page 57052]]

$FILE/ST01920SE.pdf) does not affect the ability to accomplish the 
actions required by this AD. Therefore, for airplanes on which STC 
ST01920SE is installed, a ``change in product'' alternative method 
of compliance (AMOC) approval request is not necessary to comply 
with the requirements of 14 CFR 39.17.

(d) Subject

    Joint Aircraft System Component (JASC)/Air Transport Association 
(ATA) of America Code 57, Wings.

(e) Unsafe Condition

    This AD was prompted by reports of cracked and corroded nuts on 
an outboard flap support rib. We are issuing this AD to detect and 
correct cracked and corroded nuts and bolts and the installation of 
incorrect nuts on certain outboard flap support ribs, which could 
lead to additional nut and bolt damage in the joint, result in loss 
of an outboard flap, and adversely affect continued safe flight and 
landing of the airplane.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) For Group 1 Airplanes: Repetitive Inspections of the Support Ribs, 
Related Investigative and Corrective Actions, and Fastener Replacement

    For Group 1 airplanes, as specified in Boeing Service Bulletin 
767-57A0131, Revision 1, dated May 8, 2013: Except as required by 
paragraph (j) of this AD, at the time specified in table 1 of 
paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin 767-
57A0131, Revision 1, dated May 8, 2013, do a detailed inspection of 
the cap seal for damaged sealant on the nuts common to outboard flap 
support rib numbers 1, 2, 7, and 8, and do all applicable related 
investigative and corrective actions, in accordance with the 
Accomplishment Instructions of Boeing Service Bulletin 767-57A0131, 
Revision 1, dated May 8, 2013. Do all applicable related 
investigative and corrective actions before further flight, except 
as specified in paragraphs (g)(1)(ii) and (g)(2)(ii) of this AD.
    (1) If, during any detailed inspection of the cap seal required 
by paragraph (g) of this AD, no damaged sealant is found on any 
support rib, do the actions specified in paragraphs (g)(1)(i) and 
(g)(1)(ii) of this AD.
    (i) Repeat the detailed inspection of the cap seal on that 
support rib thereafter at the intervals specified in table 1 of 
paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin 767-
57A0131, Revision 1, dated May 8, 2013, until all fasteners are 
replaced within that support rib as required by paragraph (g)(1)(ii) 
of this AD.
    (ii) Except as required by paragraph (j) of this AD, at the time 
specified in table 1 of paragraph 1.E., ``Compliance,'' of Boeing 
Service Bulletin 767-57A0131, Revision 1, dated May 8, 2013: Replace 
all fasteners within the support rib, in accordance with the 
Accomplishment Instructions of Boeing Service Bulletin 767-57A0131, 
Revision 1, dated May 8, 2013.
    (2) If, during any related investigative action required by 
paragraph (g) of this AD, no cracking and no corrosion is found on 
the nut, bolt, and washers of any support rib, do the actions 
specified in paragraphs (g)(2)(i) and (g)(2)(ii) of this AD.
    (i) Repeat the detailed inspection of the cap seal on that 
support rib thereafter at the intervals specified in table 1 of 
paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin 767-
57A0131, Revision 1, dated May 8, 2013, until all fasteners are 
replaced within that support rib as required by paragraph (g)(2)(ii) 
of this AD.
    (ii) Except as required by paragraph (j) of this AD, at the time 
specified in table 1 of paragraph 1.E., ``Compliance,'' of Boeing 
Service Bulletin 767-57A0131, Revision 1, dated May 8, 2013: Replace 
all fasteners within the support rib, in accordance with the 
Accomplishment Instructions of Boeing Service Bulletin 767-57A0131, 
Revision 1, dated May 8, 2013.

(h) For Group 2 and 3 Airplanes: Repetitive Inspections of the Support 
Ribs, Related Investigative and Corrective Actions, and Fastener 
Replacement

    For Group 2 and 3 airplanes, as specified in Boeing Service 
Bulletin 767-57A0131, Revision 1, dated May 8, 2013: Except as 
required by paragraph (j) of this AD, at the time specified in table 
2 of paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin 767-
57A0131, Revision 1, dated May 8, 2013, do a detailed inspection of 
the cap seal for damaged sealant on the nuts common to outboard flap 
support rib numbers 1, 2, 7, and 8, and do all applicable related 
investigative and corrective actions, in accordance with the 
Accomplishment Instructions of Boeing Service Bulletin 767-57A0131, 
Revision 1, dated May 8, 2013. Do all applicable related 
investigative and corrective actions before further flight.
    (1) If, during any detailed inspection of the cap seal required 
by paragraph (h) of this AD, no damaged sealant is found on any 
support rib, do the actions specified in paragraphs (h)(1)(i) and 
(h)(1)(ii) of this AD.
    (i) Repeat the detailed inspection of the cap seal on that 
support rib thereafter at the intervals specified in table 2 of 
paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin 767-
57A0131, Revision 1, dated May 8, 2013, until the actions required 
by paragraph (h)(1)(ii) of this AD are done or until all fasteners 
are replaced within that support rib as specified in paragraph (i) 
of this AD.
    (ii) Except as required by paragraph (j) of this AD, at the time 
specified in table 2 of paragraph 1.E., ``Compliance,'' of Boeing 
Service Bulletin 767-57A0131, Revision 1, dated May 8, 2013: Do a 
detailed inspection to determine the nut type installed in the 
outboard flap support rib and do all applicable corrective actions, 
in accordance with the Accomplishment Instructions of Boeing Service 
Bulletin 767-57A0131, Revision 1, dated May 8, 2013. Do all 
applicable corrective actions before further flight.
    (2) If, during any related investigative action required by 
paragraph (h) of this AD, no cracking and no corrosion is found on 
the nut, bolt, and washers of any support rib, do the actions 
specified in paragraphs (h)(2)(i) and (h)(2)(ii) of this AD.
    (i) Repeat the detailed inspection of the cap seal on that 
support rib thereafter at the intervals specified in table 2 of 
paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin 767-
57A0131, Revision 1, dated May 8, 2013, until the actions required 
by paragraph (h)(2)(ii) of this AD are done or until all fasteners 
are replaced within that support rib as specified in paragraph (i) 
of this AD.
    (ii) Except as required by paragraph (j) of this AD, at the time 
specified in table 2 of paragraph 1.E., ``Compliance,'' of Boeing 
Service Bulletin 767-57A0131, Revision 1, dated May 8, 2013: Do a 
detailed inspection to determine the nut type installed in the 
outboard flap support rib and do all applicable corrective actions, 
in accordance with the Accomplishment Instructions of Boeing Service 
Bulletin 767-57A0131, Revision 1, dated May 8, 2013. Do all 
applicable corrective actions before further flight.

(i) Terminating Action for Repetitive Inspections

    (1) If cracking is found during any inspection required by 
paragraph (g) or (h) of this AD: Replacing all the fasteners within 
the outboard flap support rib number 1, 2, 7, or 8, in accordance 
with the Accomplishment Instructions of Boeing Service Bulletin 767-
57A0131, Revision 1, dated May 8, 2013, terminates the inspections 
required by paragraph (g) or (h) of this AD for that support rib 
only.
    (2) If a discrepancy other than cracking is found (e.g., 
corrosion) during any inspection required by paragraph (g) of this 
AD: Replacing all the fasteners within the outboard flap support rib 
number 1, 2, 7, or 8, in accordance with the Accomplishment 
Instructions of Boeing Service Bulletin 767-57A0131, Revision 1, 
dated May 8, 2013, terminates the inspections required by paragraph 
(g) of this AD for that support rib only.
    (3) If a discrepancy other than cracking is found (e.g., 
corrosion) during any inspection required by paragraph (h) of this 
AD: Replacing the affected fastener terminates the repetitive 
inspections for only that fastener within that support rib.

(j) Exception to Service Information

    Where Boeing Service Bulletin 767-57A0131, Revision 1, dated May 
8, 2013, specifies a compliance time relative to the issue date of 
that service bulletin, this AD requires compliance within the 
specified compliance time after the effective date of this AD.

(k) Credit for Previous Actions

    This paragraph provides credit for the applicable actions 
required by paragraphs (g), (h), and (i) of this AD, if those 
actions were performed before the effective date of this AD using 
Boeing Alert Service Bulletin 767-57A0131, dated October 30, 2012, 
which is not incorporated by reference in this AD.

[[Page 57053]]

(l) 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 paragraph (m) 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.

(m) Related Information

    (1) For more information about this AD, contact Berhane Alazar, 
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft 
Certification Office, 1601 Lind Avenue SW., Renton, Washington 
98057-3356; phone: 425-917-6577; fax: 425-917-6590; email: 
[email protected].
    (2) Service information identified in this AD that is not 
incorporated by reference may be obtained at the addresses specified 
in paragraphs (n)(3) and (n)(4) of this AD.

(n) 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.
    (i) Boeing Service Bulletin 767-57A0131, Revision 1, dated May 
8, 2013.
    (ii) Reserved.
    (3) 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.
    (4) You may view this service information at 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 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 August 23, 2013.
Stephen P. Boyd,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2013-22414 Filed 9-16-13; 8:45 am]
BILLING CODE 4910-13-P

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