[Federal Register Volume 78, Number 192 (Thursday, October 3, 2013)]
[Rules and Regulations]
[Pages 61164-61168]
[FR Doc No: 2013-23898]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-1320; Directorate Identifier 2012-NM-095-AD;
Amendment 39-17618; AD 2013-20-12]
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 airplanes. This AD was prompted by reports
of cracks and heat damage on pivot joint components found during main
landing gear (MLG) overhaul. This AD requires, for certain airplanes,
repetitive inspections of the MLG pivots, truck beam bushings, and
inner cylinder bushings. For all airplanes, this AD requires a
maintenance program revision, one-time inspections of the MLG truck
beam, and related investigative and corrective actions (including
configuration changes) if necessary; accomplishment of these actions
terminates the repetitive inspections. We are issuing this AD to detect
and correct heat damage and cracks in the pivot pin, truck beam lugs,
and inner cylinder lugs, which could result in fracture of the pivot
joint components and consequent MLG collapse.

DATES: This AD is effective November 7, 2013.
    The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in the AD as of November 7,
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<PHONE_NUMBER>; 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<PHONE_NUMBER>.

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:<PHONE_NUMBER>) 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
(ACO), 1601 Lind Avenue SW., Renton, Washington 98057-3356; phone: 425-
917-6577; fax:<PHONE_NUMBER>; email<EMAIL_ADDRESS>
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 January 30, 2013 (78 FR
6251). For certain airplanes, the NPRM proposed to require repetitive
inspections of the MLG pivots, truck beam bushings, and inner cylinder
bushings. For all airplanes, the NPRM proposed to require a maintenance
program revision, one-time inspections of the MLG truck beam, and
related investigative and corrective actions (including configuration
changes) if necessary; accomplishment of these actions 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 6251, January 30, 2013) and the FAA's response to each comment.

Support for NPRM (78 FR 6251, January 30, 2013)

    American Airlines (American) noted no issue with this proposed AD
(78 FR 6251, January 30, 2013), and reported that the proposed
compliance time will allow the work to be done during normal gear
overhaul.

Request To Clarify Applicability

    Aviation Partners Boeing (APB) stated that the installation of
winglets per supplemental type certificate (STC) ST01920SE (http://
rgl.faa.gov/Regulatory--and--Guidance--Library/rgstc.nsf/0/
082838ee177dbf62862576a4005cdfc0/$FILE/ST01920SE.pdf) does not affect
the accomplishment of the manufacturer's service instructions. Delta
Airlines (Delta) noted that several previous ADs have included similar
information about the APB winglet modification, and requested that we
clarify the applicability of the NPRM (78 FR 6251, January 30, 2013) by
including this provision.
    We agree. We have re-designated paragraph (c) as (c)(1) and added
paragraph (c)(2) to this final rule, which states that STC ST01920SE
(http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/
082838ee177dbf62862576a4005cdfc0/$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 Section 39.17 of the
Federal Aviation Regulations (14 CFR 39.17). For all other AMOC
requests, the operator must request approval of an AMOC in accordance
with the procedures specified in paragraph (n) of this AD.

Request To Extend Compliance Time

    UPS requested that we revise paragraph (g) of the NPRM (78 FR 6251,
January 30, 2013) to specify the repetitive interval for the
lubrication schedule (as referenced in Boeing Service Bulletin 767-
32A0227, Revision 1, dated September 13, 2012). UPS stated that
changing the current interval (14 days or 50 flight cycles) to 650
flight hours would provide adequate lubrication and a simplified method
of tracking compliance with the lubrication interval. UPS stated that
the

lubrication could be scheduled along with the lubrication of other
components located in that area, which is required by AD 2006-07-14,
Amendment 39-14541 (71 FR 17691, April 7, 2006), for certain Model 767-
200, -300, and -300F series airplanes. UPS added that the NPRM's
proposed compliance time of 14 days/50 flight cycles to lubricate the
MLG truck pivot pin conflicts with the existing UPS maintenance
program, 14 days/30 flight cycles, and does not add any increased
benefit to safety.
    We disagree with the request, in light of the number of cracks that
have been found in inner cylinder pivot bores due to friction-generated
heat damage. More frequent lubrication reduces friction in the joint.
Also, the Boeing 767-200/-300/-300F maintenance planning document was
previously changed to specify 14 days/50 flight cycles for these
actions. Under the provisions of paragraph (n) of this final rule,
however, we may consider individual requests for adjustments to the
compliance time if data are submitted to substantiate that such an
adjustment would provide an acceptable level of safety. We have not
changed the final rule regarding this issue.

Request To Revise Inspection Requirements

    Paragraph (h) of the NPRM (78 FR 6251, January 30, 2013) specified
``detailed and etch inspections'' for Model 767-400ER airplanes. Boeing
requested that we limit this requirement to a ``detailed inspection.''
Boeing reported that the referenced service information for this
proposed requirement erroneously specifies ``detailed and etch
inspections'' in table 2 of paragraph 1.E., ``Compliance,'' of Boeing
Service Bulletin 767-32A0227, Revision 1, dated September 13, 2012.
Boeing explained that etch inspections do not apply to Model 767-400ER
airplanes (Group 1) because those truck and inner cylinder pivot lugs
are chrome plated. Boeing stated that affected operators will be
notified of this error, which will be corrected when this service
bulletin is revised. Boeing noted that the error appears only in
paragraph 1.E., ``Compliance''--and not the Work Instructions (Parts 6
and 7)--of this service bulletin.
    We agree with the request for the reasons provided by the
commenter. We have revised paragraph (h) in this final rule
accordingly.

Request To Revise Inspection Condition: Wear

    Paragraph (h) of the NPRM (78 FR 6251, January 30, 2013) specified
inspections to detect, among other things, ``wear'' of the MLG pivot
pins. Boeing asserted that, since wear is a normal occurrence, ``wear''
should be changed to ``wear beyond limits'' to correspond to this
condition as described in Boeing Service Bulletin 767-32A0227, Revision
1, dated September 13, 2012.
    We agree that clarification is necessary. Specific wear limits are
defined in condition 4, table 5, of paragraph 1.E., ``Compliance,'' of
Boeing Service Bulletin 767-32A0227, Revision 1, dated September 13,
2012. No change to this final rule is necessary.

Request To Revise Inspection Condition: Grease in Inner Diameters

    Paragraph (h) of the NPRM (78 FR 6251, January 30, 2013) also
specified inspections to detect ``grease not present in the bushing
inner diameter.'' Boeing contended this step is unnecessary, since
operators must clean the pivot joint before the inspection, so there
would be no grease present on the bushing inner diameters. (Boeing
Service Bulletin 767-32A0227, Revision 1, dated September 13, 2012,
specifies applying grease through the lube fittings as part of the
inspection process to check for clogged lube passages.) Boeing
therefore requested that we revise this condition to ``grease not
appearing in the bushing inner diameters when applied through the lube
fittings'' to more closely match the service bulletin description.
    We agree with the request, for the reasons provided by the
commenter. We have changed paragraph (h) in this final rule
accordingly.

Request To Revise Descriptive Heading

    The descriptive heading for paragraph (i) of the NPRM (78 FR 6251,
January 30, 2013) was ``MLG Truck Beam Inspections.'' Boeing requested
that we change this heading to ``MLG Truck Beam and Inner Cylinder
Configuration Change.'' Boeing contended that this change would
emphasize the main purpose of Boeing Service Bulletin 767-32A0227,
Revision 1, dated September 13, 2012--to replace the aluminum-nickel-
bronze bushings with copper-nickel-tin bushings.
    We agree with the commenter's request and rationale. Boeing Service
Bulletin 767-32A0227, Revision 1, dated September 13, 2012, specifies
this configuration change. We have revised the heading accordingly in
this final rule.

Request To Clarify Inspection Locations

    Paragraph (i) of the NPRM (78 FR 6251, January 30, 2013) specified
inspections of the ``truck beam.'' Boeing requested that we revise this
proposed requirement to add inspection of the ``inner cylinders.''
Boeing stated that the main purpose of Boeing Service Bulletin 767-
32A0227, Revision 1, dated September 13, 2012, is to replace the truck
beam and inner cylinder pivot-joint bushings, and asserted that the
NPRM omitted the inner cylinder bushings and emphasized the inspection
process rather than the configuration change.
    We agree with the request and have changed paragraph (i)
accordingly in this final rule.

Request To Include Heat Damage as an Inspection Condition

    Paragraph (i) of the NPRM (78 FR 6251, January 30, 2013) specified
inspections to detect, among other things, ``distress, corrosion, and
cracking.'' Boeing requested that we add ``heat damage'' to these
conditions to more closely match the language of Boeing Service
Bulletin 767-32A0227, Revision 1, dated September 13, 2012. Boeing
stated that heat damage, explicitly identified as a condition in this
service bulletin, is the primary type of damage to be expected.
    We agree to clarify the possible findings of the inspection. Boeing
Service Bulletin 767-32A0227, Revision 1, dated September 13, 2012,
specifies various conditions based on the airplane group, and heat
damage is identified as one of those conditions. We have changed
paragraph (i) in this final rule to clarify that the inspection is
intended to detect ``applicable discrepancies'' specified in Boeing
Service Bulletin 767-32A0227, Revision 1, dated September 13, 2012.

Request To Allow Terminating Action per Service Information

    Paragraph (k)(2) of the NPRM (78 FR 6251, January 30, 2013)
specified that overhaul of the MLG and installation of certain truck
beam and inner cylinder bushings terminate the inspection requirements,
if those actions are done using an FAA-approved alternative method of
compliance (AMOC). Boeing stated that the MLG overhaul includes
investigative and corrective actions that are equivalent to those found
in Boeing Service Bulletin 767-32A0227, Revision 1, dated September 13,
2012, so an overhaul should be an acceptable substitute for those
actions. Boeing stated that most or all operators are expected to use
the overhaul option, which is available in this service bulletin, so
FAA approval of this service bulletin would make the process for
requesting AMOC approval (as specified

in paragraph (k)(2) of the NPRM) unnecessary.
    We disagree with the request because the overhaul procedures
necessary to address the unsafe condition identified in this AD would
encompass significantly more work than the commenter described.
Operators must contact the FAA to obtain approval for an acceptable
method to ensure that the overhaul meets the requirement of this AD. We
have not changed the final rule regarding this issue.

Request To Include Part References

    Delta requested that we clarify the proposed actions specified in
paragraphs (h) and (i) of the NPRM (78 FR 6251, January 30, 2013) by
also identifying the applicable Parts of the Accomplishment
Instructions of Boeing Service Bulletin 767-32A0227, Revision 1, dated
September 13, 2012.
    We agree with the request. We have added references to ``Part 2''
in paragraph (h) of this final rule and ``Part 3'' in paragraph (i) of
this final rule.

Request To Account for Related AD

    UPS requested that we revise paragraph (b) of the NPRM (78 FR 6251,
January 30, 2013) to refer to AD 2006-07-14, Amendment 39-14541 (71 FR
17691, April 7, 2006). UPS stated that the new copper-nickel-tin
bushing material (identified in the NPRM and Boeing Service Bulletin
767-32A0227, Revision 1, dated September 13, 2012), replaces the
aluminum-nickel-bronze bushing material specified in AD 2006-07-14. UPS
asserted that compliance with both the NPRM and AD 2006-07-14 cannot be
concurrently satisfied because the NPRM, which would require use of
copper-nickel-tin material, conflicts with AD 2006-07-14, which
requires use of aluminum-nickel-bronze bushing material. UPS stated
that Boeing Service Bulletin 767-32A0227, Revision 1, dated September
13, 2012, explains that use of the new copper-nickel-tin bushing
material is an AMOC to AD 2006-07-14, and requested that we revise the
NPRM to include this AMOC.
    We find that clarification is necessary. Paragraph 1.F.,
``Approval,'' of Boeing Service Bulletin 767-32A0227, Revision 1, dated
September 13, 2012, already addresses the issue raised by the
commenter. Specifically, paragraph (j) of AD 2006-07-14, Amendment 39-
14541 (71 FR 17691, April 7, 2006), specifies installing aluminum-
nickel-bronze bushings as part of the terminating action. This final
rule requires replacement of those aluminum-nickel-bronze bushings with
bushings made of copper-nickel-tin material. Using a copper-nickel-tin
bushing is considered to be an AMOC for installing an aluminum-nickel-
bronze bushing, when installed as part of the terminating action for
paragraph (j) of AD 2006-07-14. As requested by the commenter, we
changed paragraph (b) of this final rule to clarify that this AD
affects AD 2006-07-14.

Requests To Correct Typographical Error

    Boeing and Delta noted a typographical error in paragraph (h) of
the NPRM (78 FR 6251, January 30, 2013), which incorrectly specified
inspecting ``pivots'' instead of ``pivot pins.''
    We acknowledge the error and have corrected paragraph (h) in this
final rule accordingly.

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:
     [Agr]re consistent with the intent that was proposed in
the NPRM (78 FR 6251, January 30, 2013) for correcting the unsafe
condition; and
     Do not add any additional burden upon the public than was
already proposed in the NPRM (78 FR 6251, January 30, 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 420 airplanes of U.S. registry. We
estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                Number of
                                                                                affected     Cost on U.S.
            Action                  Labor cost      Parts cost   Cost per product      U.S.         operators
                                                                                airplanes
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Maintenance program revision..  1 work-hour x $85           $0  $85..............          420  $35,700.
                                 per hour = $85.
Repetitive inspections........  59 work-hours x              0  $5,015 per                  38  $190,570 per
                                 $85 per hour =                  inspection cycle.               inspection
                                 $5,015 per                                                      cycle.
                                 inspection cycle.
One-time inspections..........  147 work-hours x             0  $12,495..........          420  $5,247,900.
                                 $85 per hour =
                                 $12,495.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide
cost estimates for the on-condition actions (including related
investigative actions, configuration changes, and corrective actions)
specified in this AD.

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):

2013-20-12 The Boeing Company: Amendment 39-17618 ; Docket No. FAA-
2012-1320; Directorate Identifier 2012-NM-095-AD.

(a) Effective Date

    This AD is effective November 7, 2013.

(b) Affected ADs

    AD 2006-07-14, Amendment 39-14541 (71 FR 17691, April 7, 2006),
is affected by this AD.

(c) Applicability

    (1) This AD applies to The Boeing Company Model 767-200, -300, -
300F, and -400ER series airplanes, certificated in any category, as
identified in Boeing Service Bulletin 767-32A0227, Revision 1, dated
September 13, 2012.
    (2) Installation of Supplemental Type Certificate (STC)
ST01920SE (http://rgl.faa.gov/Regulatory--and--Guidance--Library/
rgstc.nsf/0/082838ee177dbf62862576a4005cdfc0/$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 32, Landing Gear.

(e) Unsafe Condition

    This AD was prompted by reports of cracks and heat damage found
on pivot joint components found during main landing gear (MLG)
overhaul. We are issuing this AD to detect and correct heat damage
and cracks in the pivot pin, truck beam lugs, and inner cylinder
lugs, which could result in fracture of the pivot joint components
and consequent MLG collapse.

(f) Compliance

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

(g) Maintenance Program Revision

    At the applicable times specified in paragraph 1.E.,
``Compliance,'' of Boeing Service Bulletin 767-32A0227, Revision 1,
dated September 13, 2012, except as provided by paragraph (j) of
this AD, revise the maintenance program to incorporate the specified
maintenance review board (MRB) item, in accordance with Part 1 of
the Accomplishment Instructions of Boeing Service Bulletin 767-
32A0227, Revision 1, dated September 13, 2012.

(h) Repetitive Pivot Pin and Bushing Inspections

    For airplanes identified as Group 1 in Boeing Service Bulletin
767-32A0227, Revision 1, dated September 13, 2012: At the applicable
times specified in paragraph 1.E., ``Compliance,'' of Boeing Service
Bulletin 767-32A0227, Revision 1, dated September 13, 2012, except
as provided by paragraph (j) of this AD, do a detailed inspection to
detect discrepancies (including bronze transfer, heat discoloration,
darkened streaks, thermal spray coating distress, wear, cracking,
smearing of material into the lubrication grooves, or grease not
appearing in the bushing inner diameters when applied through the
lube fittings) of the MLG pivot pins, truck beam bushings, and inner
cylinder bushings, and do all applicable corrective actions, in
accordance with Part 2 of the Accomplishment Instructions of Boeing
Service Bulletin 767-32A0227, Revision 1, dated September 13, 2012.
Do all applicable corrective actions before further flight. Repeat
the inspection thereafter at the applicable times specified in
paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin 767-
32A0227, Revision 1, dated September 13, 2012.

(i) Inspections of MLG Truck Beam and Inner Cylinder Configuration
Change

    For all airplanes: At the applicable time specified in paragraph
1.E., ``Compliance,'' of Boeing Service Bulletin 767-32A0227,
Revision 1, dated September 13, 2012, except as provided by
paragraph (j) of this AD, inspect the MLG truck beam and inner
cylinders, using a detailed inspection, etch inspection, and
fluorescent penetrant inspection (FPI), as applicable, to detect
applicable discrepancies, and do all applicable related
investigative and corrective actions (including configuration
changes), in accordance with Part 3 of the Accomplishment
Instructions of Boeing Service Bulletin 767-32A0227, Revision 1,
dated September 13, 2012. Do all applicable related investigative
and corrective actions before further flight. Boeing Service
Bulletin 767-32A0227, Revision 1, dated September 13, 2012, provides
options for accomplishing certain corrective actions.

(j) Service Information Exception

    Where Boeing Service Bulletin 767-32A0227, Revision 1, dated
September 13, 2012, specifies a compliance time ``after the original
issue date of this service bulletin,'' this AD requires compliance
within the specified compliance time after the effective date of
this AD.

(k) Terminating Action

    (1) Accomplishment of the actions required by paragraphs (g) and
(i) of this AD terminates the requirements of paragraph (h) of this
AD.
    (2) Overhaul of the MLG and installation of truck beam and inner
cylinder bushings having applicable part numbers identified in
Appendix ``B'' of Boeing Service Bulletin 767-32A0227, Revision 1,
dated September 13, 2012, terminate the requirements of paragraphs
(h) and (i) of this AD, if the actions are done using a method
approved in accordance with the procedures specified in paragraph
(n) of this AD.

(l) No Alternative Actions or Intervals

    After accomplishing the revision required by paragraph (g) of
this AD, no alternative actions (e.g., inspections) or intervals may
be used unless the actions or intervals are approved as an AMOC in
accordance with the procedures specified in paragraph (n) of this
AD.

(m) Credit for Previous Actions

    This paragraph provides credit for the actions specified in
paragraphs (g), (h), (i), and (k) of this AD, if those actions were
performed before the effective date of this AD using Boeing Alert
Service Bulletin 767-32A0227, dated April 25, 2012, which is not
incorporated by reference in this AD.

(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 paragraph (o)(1) of this AD.
Information may be emailed to<EMAIL_ADDRESS>    (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.

(o) Related Information

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

(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.
    (i) Boeing Service Bulletin 767-32A0227, Revision 1, dated
September 13, 2012.
    (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, Washington 98124-2207; telephone
206-544-5000, extension 1; fax<PHONE_NUMBER>; Internet https://www.myboeingfleet.com.
    (4) You may view this service information at 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<PHONE_NUMBER>, or go to http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on September 16, 2013.
Ross Landes,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2013-23898 Filed 10-2-13; 8:45 am]
BILLING CODE 4910-13-P