Document ID: FAA-2013-0328-0005
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: The Boeing Company Airplanes
Posted Date: 2013-11-05T05:00Z

[Federal Register Volume 78, Number 214 (Tuesday, November 5, 2013)]
[Rules and Regulations]
[Pages 66254-66258]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-25950]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0328; Directorate Identifier 2012-NM-184-AD; 
Amendment 39-17643; AD 2013-22-11]
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 Airworthiness Directive (AD) 2009-10-06 for 
certain The Boeing Company Model 747-400 and -400D series airplanes. AD 
2009-10-06 required repetitive inspections to detect cracks in the 
floor panel attachment fastener holes of the Section 41 upper deck 
floor beam upper chords, and corrective actions if necessary; and 
repetitive post-repair and post-modification inspections, and 
corrective actions if necessary. This new AD adds repetitive 
inspections of Section 44 upper deck floor beam upper chords, and 
corrective actions if necessary; repetitive post-repair and post-
modification inspections, and corrective actions if necessary; and 
replacement of the upper deck floor beam upper chords. This AD was 
prompted by an evaluation by the design approval holder (DAH) 
indicating that certain upper chords of the upper deck floor beam are 
subject to widespread fatigue damage (WFD). We are issuing this AD to 
detect and correct fatigue cracking in certain upper chords of the 
upper deck floor beam, which could become large and cause the floor 
beams to become severed and result in rapid decompression or reduced 
controllability of the airplane.

DATES: This AD is effective December 10, 2013.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of December 10, 
2013.
    The Director of the Federal Register approved the incorporation by 
reference of a certain other publication listed in this AD as of June 
17, 2009 (74 FR 22424, May 13, 2009).

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 view this referenced service information 
at the FAA, 1601 Lind Avenue SW., Renton, WA. 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: Bill Ashforth, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle ACO, 1601 Lind Avenue SW., 
Renton, WA 98057-3356; phone: 425-917-6432; fax: 425-917-6590; email: 
bill.ashforth@faa.gov.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2009-10-06, Amendment 39-15901 (74 FR 22424, 
May 13, 2009). AD 2009-10-06 applied to the specified products. The 
NPRM published in the Federal Register on

[[Page 66255]]

April 16, 2013 (78 FR 22435). The NPRM proposed to continue to require 
repetitive inspections to detect cracks in the floor panel attachment 
fastener holes of the Section 41 upper deck floor beam upper chords, 
and corrective actions if necessary; and repetitive post-repair and 
post-modification inspections, and corrective actions if necessary. The 
NPRM also proposed to add repetitive inspections of Section 44 upper 
deck floor beam upper chords, and corrective actions if necessary; 
repetitive post-repair and post-modification inspections, and 
corrective actions if necessary; and replacement of the upper deck 
floor beam upper chords.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the proposal 
(78 FR 22435, April 16, 2013) and the FAA's response to each comment.

Request To Eliminate Duplicate Reference to Post-Repair and Post-
Modification Repetitive Inspections

    Boeing requested that we delete the reference to post-repair and 
post-modification repetitive inspections from paragraph (g) of the NPRM 
(78 FR 22435, April 16, 2013). Boeing stated that the post-repair and 
post-modification inspections are required by paragraph (i) of the 
NPRM, and need to be deleted from paragraph (g) of the NPRM to avoid 
confusion.
    We agree to remove the duplicate reference to post-repair and post-
modification repetitive inspections from paragraph (g) of this final 
rule. We have changed paragraph (g) of this final rule accordingly.

Request To Revise the Heading and Clarify Paragraph (k) of the NPRM (78 
FR 22435, April 16, 2013)

    Boeing requested that we revise the heading of paragraph (k) of the 
NPRM (78 FR 22435, April 16, 2013) to clarify that the modification 
specified in Table 2 of paragraph 1.E., ``Compliance,'' of Boeing 
Service Bulletin 747-53A2688, Revision 1, dated September 19, 2012, is 
not new and is not fully terminating. Boeing also requested that we add 
text concerning terminating inspections required by paragraphs (g) and 
(j) of the NPRM, and also for the resumption of inspections required by 
paragraphs (i) and (l) of the NPRM.
    We agree with the request. We have revised the heading of paragraph 
(k) of this final rule to ``New Terminating Action for Certain 
Conditions.'' We also agree with adding text to paragraph (k) of this 
final rule to clarify which modifications or repairs as modifications 
terminate which inspections required by this final rule. We have 
revised paragraph (k) of this final rule to add new paragraph (k)(1) to 
this final rule to specify that, for Section 41, doing a hole 
modification or repair as a hole modification, in accordance with 
``Part 2--Section 41--Repair,'' of the Accomplishment Instructions of 
Boeing Alert Service Bulletin 747-53A2688, Revision 1, dated September 
19, 2012, terminates the repetitive inspections specified in paragraph 
(g) of this final rule. We have also included clarification in 
paragraph (k)(1) of this final rule to indicate that the repetitive 
inspections specified in paragraph (i) of this final rule must be done.
    We have also moved the content of paragraph (k) of the NPRM (78 FR 
22435, April 16, 2013) to new paragraph (k)(2) of this final rule to 
specify that, for Section 44, doing a hole modification or repair as a 
hole modification, in accordance with ``Part 5--Section 44--Repair,'' 
of the Accomplishment Instructions of Boeing Alert Service Bulletin 
747-53A2688, Revision 1, dated September 19, 2012, terminates the 
repetitive inspections specified in paragraph (j) of this final rule. 
We have also included clarification in paragraph (k)(2) of this final 
rule to indicate that the repetitive inspections specified in paragraph 
(l) of this final rule must be done.

Request To Restart Inspections After Replacement of Upper Deck Floor 
Beam Upper Chords

    Boeing requested that we revise paragraph (m) of the NPRM (78 FR 
22435, April 16, 2013) to add a note concerning the new inspection 
threshold, equal to the original threshold, to restart inspections 
after replacement of the upper deck floor beam upper chords. Boeing 
stated that paragraph (m) of the NPRM requires the replacement of upper 
deck floor beam upper chords in Sections 41 and 44, as given in Table 5 
of Boeing Service Bulletin 747-53A2688, Revision 1, dated September 19, 
2012. Boeing stated that the new inspection threshold needs to be 
provided in paragraph (m) of this NPRM.
    We agree with the request to include a relieving compliance time 
for the inspections required by this final rule for airplanes on which 
the upper deck floor beam upper chords are replaced. Paragraphs (g), 
(i), (j), and (l) of this final rule require repetitive inspections at 
the applicable times specified in Tables 1 through 4 of paragraph 1.E., 
``Compliance,'' of Boeing Service Bulletin 747-53A2688, Revision 1, 
dated September 19, 2012. However, Boeing Service Bulletin 747-53A2688, 
Revision 1, dated September 19, 2012, does not specify that 
accomplishing the replacement terminates the repetitive inspections, 
nor does it provide a longer compliance time for the next inspection 
done after accomplishing the replacement. We also agree that the next 
inspection after accomplishing the replacement may be done within 
20,000 flight cycles. We have determined that this compliance time will 
provide an adequate level of safety. We have revised paragraph (m) of 
this final rule to add the first interval for the repetitive 
inspections required by this final rule for airplanes on which a 
replacement required by paragraph (m) of this final rule is done.

Request To Add References to Paragraph (n)(1) of the NPRM (78 FR 22435, 
April 16, 2013)

    Boeing requested that we revise paragraph (n)(1) of the NPRM (78 FR 
22435, April 16, 2013) to refer to paragraphs (j) and (l) of the NPRM. 
Boeing stated that since paragraph (n) of the NPRM is referring to new 
exceptions, it should refer to cracks found as part of the new 
inspections specified in paragraph (i), (j), or (l) of the NPRM 
(reference Compliance Tables 2, 3, or 4 of Boeing Service Bulletin 747-
53A2688, Revision 1, dated September 19, 2012).
    We partially agree with the request. We have added a reference to 
paragraph (j) of this final rule in paragraph (n)(1) of this final 
rule. Paragraph (j) of this final rule already references paragraph 
(n)(1) of this final rule as an exception. However, we do not agree to 
add a reference to paragraph (l) of this final rule in paragraph (n)(1) 
of this final rule, because paragraph (l) of this final rule does not 
include a reference to the service information for the corrective 
action. Paragraph (l) of this final rule specifies to refer to the 
procedures in paragraph (p) of this final rule for airplanes on which 
any cracking is found.

Request To Allow Boeing Organization Designation Authorization (ODA) 
Approval

    Boeing requested we revise paragraph (n)(3) of the NPRM (78 FR 
22435, April 16, 2013) to allow the full provisions of Boeing ODA 
approval. Boeing stated that alternative method of compliance (AMOC) 
approval provisions allowed in paragraph (p) of the NPRM should apply 
to all sections of the NPRM.
    We disagree. Paragraph (p)(3) of this final rule already allows for 
ODA

[[Page 66256]]

approval of repairs. We have not changed this final rule in this 
regard. However, we have revised paragraph (n)(3) of this final rule to 
clarify where the service information specifies to contact the FAA, 
operators must contact the Seattle Aircraft Certification Office (ACO).

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 except for minor 
editorial changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM (78 FR 22435, April 16, 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 22435, April 16, 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 84 airplanes of U.S. registry. We 
estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
              Action                    Labor cost        Parts cost      Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Inspection (retained actions from  Up to 50 work-hours              $0  Up to $4,250 per     Up to $357,000 per
 AD 2009-10-06, Amendment           x $85 per hour =                     inspection cycle.    inspection cycle.
 39[dash]15901 (74 FR 22424, May    Up to $4,250 per
 13, 2009)).                        inspection cycle.
Inspection (new action)..........  259 work-hours x                  0  $22,015 per          $1,849,260 per
                                    $85 per hour =                       inspection cycle.    inspection cycle.
                                    $22,015 per
                                    inspection cycle.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
a cost estimate for the repair or modification 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

    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) 
2009-10-06, Amendment 39-15901 (74 FR 22424, May 13, 2009), and adding 
the following new AD:

2013-22-11 The Boeing Company: Amendment 39-17643; Docket No. FAA-
2013-0328; Directorate Identifier 2012-NM-184-AD.

(a) Effective Date

    This AD is effective December 10, 2013.

(b) Affected ADs

    This AD supersedes AD 2009-10-06, Amendment 39-15901 (74 FR 
22424, May 13, 2009).

(c) Applicability

    This AD applies to The Boeing Company Model 747-400 and -400D 
series airplanes; certificated in any category; as identified in 
Boeing Alert Service Bulletin 747-53A2688, Revision 1, dated 
September 19, 2012.

(d) Subject

    Joint Aircraft System Component (JASC)/Air Transport Association 
(ATA) of America Code 53, Fuselage.

(e) Unsafe Condition

    This AD was prompted by an evaluation by the design approval 
holder (DAH) indicating that certain upper chords of the upper deck 
floor beam are subject to widespread fatigue damage (WFD). We are 
issuing this AD to detect and correct fatigue cracking in certain 
upper chords of the upper deck floor beam, which could become large 
and cause the floor beams to become severed and result in rapid 
decompression or reduced controllability 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 and Compliance Times

    This paragraph restates the actions required by paragraph (g) of 
AD 2009-10-06, Amendment 39-15901 (74 FR 22424, May 13, 2009), with 
revised service information and compliance times. Except as required 
by paragraphs (h)(1) and (h)(2) of this AD: At the applicable times 
in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 
747-53A2688, dated August 21, 2008, do an inspection (open-hole or 
surface high frequency eddy current (HFEC)) to

[[Page 66257]]

detect cracks in the floor panel attachment fastener holes of the 
Section 41 upper deck floor beam upper chords, and do applicable 
corrective actions, by accomplishing all the applicable actions 
specified in the Accomplishment Instructions of Boeing Alert Service 
Bulletin 747-53A2688, dated August 21, 2008; or Revision 1, dated 
September 19, 2012. Repeat the inspections thereafter at the 
applicable times specified in paragraph 1.E., ``Compliance,'' of 
Boeing Alert Service Bulletin 747-53A2688, dated August 21, 2008, 
except as required by paragraphs (i) and (m) of this AD. As of the 
effective date of this AD, use only Boeing Alert Service Bulletin 
747-53A2688, Revision 1, dated September 19, 2012, to accomplish the 
actions in this paragraph.

(h) Retained Exceptions

    (1) This paragraph restates the exception stated in paragraph 
(h) of AD 2009-10-06, Amendment 39-15901 (74 FR 22424, May 13, 
2009). If any crack is found during any inspection required by 
paragraph (g) of this AD, and Boeing Alert Service Bulletin 747-
53A2688, dated August 21, 2008; or Revision 1, dated September 19, 
2012; specifies to contact Boeing for appropriate action: Before 
further flight, repair the crack using a method approved in 
accordance with the procedures specified in paragraph (p) of this 
AD.
    (2) This paragraph restates the exception stated in paragraph 
(i) of AD 2009-10-06, Amendment 39-15901 (74 FR 22424, May 13, 
2009). Where Boeing Alert Service Bulletin 747-53A2688, dated August 
21, 2008, specifies a compliance time after the date on the service 
bulletin, this AD requires compliance within the specified 
compliance time after June 17, 2009 (the effective date of AD 2009-
10-06).

(i) Inspections and Corrective Actions for Airplanes on Which a Repair 
or Modification Is Done (for Section 41)

    For airplanes on which a repair or modification identified in 
Table 2 of 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 
747-53A2688, Revision 1, dated September 19, 2012, has been done: At 
the times specified in Table 2 of paragraph 1.E., ``Compliance,'' of 
Boeing Alert Service Bulletin 747-53A2688, Revision 1, dated 
September 19, 2012, except as required by paragraph (n)(3) of this 
AD, do open-hole and surface HFEC inspections, as applicable, for 
cracking, in accordance with the Accomplishment Instructions of 
Boeing Alert Service Bulletin 747-53A2688, Revision 1, dated 
September 19, 2012. Repeat at the applicable intervals specified in 
Table 2 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service 
Bulletin 747-53A2688, Revision 1, dated September 19, 2012. If any 
cracking is found in the repaired or modified locations, before 
further flight, repair the crack using a method approved in 
accordance with the procedures specified in paragraph (p) of this 
AD.

(j) New Inspections and Repair

    For Group 1 airplanes identified in Boeing Alert Service 
Bulletin 747-53A2688, Revision 1, dated September 19, 2012: At the 
applicable times specified in paragraph 1.E., ``Compliance,'' of 
Boeing Alert Service Bulletin 747-53A2688, Revision 1, dated 
September 19, 2012, except as specified in paragraph (n)(2) of this 
AD, do an open-hole or surface HFEC inspection to detect cracking in 
the floor panel attachment fastener holes of the Section 44 upper 
deck floor beam upper chords, and all applicable corrective actions, 
in accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin 747-53A2688, Revision 1, dated September 19, 2012, 
except as required by paragraph (n)(1) of this AD. Repeat the 
inspections thereafter at the applicable intervals specified in 
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 
747-53A2688, Revision 1, dated September 19, 2012, except as 
provided by paragraph (m) of this AD. Do all applicable corrective 
actions before further flight.

(k) New Terminating Action for Certain Conditions

    (1) For Section 41: Doing a hole modification or repair as a 
hole modification, in accordance with ``Part 2--Section 41--
Repair,'' of the Accomplishment Instructions of Boeing Alert Service 
Bulletin 747-53A2688, Revision 1, dated September 19, 2012, 
terminates the repetitive inspections specified in paragraph (g) of 
this AD. However, the repetitive inspections specified in paragraph 
(i) of this AD must be done.
    (2) For Section 44: Doing a hole modification or repair as a 
hole modification, in accordance with ``Part 5--Section 44--
Repair,'' of the Accomplishment Instructions of Boeing Alert Service 
Bulletin 747-53A2688, Revision 1, dated September 19, 2012, 
terminates the repetitive inspections specified in paragraph (j) of 
this AD. However, the repetitive inspections specified in paragraph 
(l) of this AD must be done.

(l) New Inspections and Corrective Actions for Airplanes on Which a 
Repair or Modification Is Done (for Section 44)

    For airplanes on which a repair or modification specified in the 
``Condition'' column of Table 4 of paragraph 1.E., ``Compliance,'' 
of Boeing Alert Service Bulletin 747-53A2688, Revision 1, dated 
September 19, 2012, has been done: At the times specified in Table 4 
of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 
747-53A2688, Revision 1, dated September 19, 2012, except as 
required by paragraph (n)(3) of this AD, do open hole and surface 
HFEC inspections, as applicable, for cracking, in accordance with 
the Accomplishment Instructions of Boeing Alert Service Bulletin 
747-53A2688, Revision 1, dated September 19, 2012. Repeat at the 
applicable intervals specified in Table 4 of paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 747-53A2688, 
Revision 1, dated September 19, 2012. If any cracking is found in 
the repaired or modified locations, before further flight, repair 
the crack using a method approved in accordance with the procedures 
specified in paragraph (p) of this AD.

(m) New Replacement and Post-Replacement Inspections

    At the time specified in paragraph 1.E., ``Compliance,'' of 
Boeing Alert Service Bulletin 747-53A2688, Revision 1, dated 
September 19, 2012: Replace Section 41 and 44 upper deck floor beam 
upper chords, in accordance with the Accomplishment Instructions of 
Boeing Alert Service Bulletin 747-53A2688, Revision 1, dated 
September 19, 2012. Repeat the inspections required by paragraphs 
(g) and (j) of this AD within 20,000 flight cycles after doing the 
replacement. Thereafter, repeat the inspection required by 
paragraphs (g) and (j) of this AD at the times specified in 
paragraphs (g) and (j) of this AD.

(n) New Exceptions

    (1) If any crack is found during any inspection required by 
paragraph (i), (j), or (l) of this AD, and Boeing Alert Service 
Bulletin 747-53A2688, Revision 1, dated September 19, 2012, 
specifies to contact Boeing for appropriate action: Before further 
flight, repair the crack using a method approved in accordance with 
the procedures specified in paragraph (p) of this AD.
    (2) Where Boeing Alert Service Bulletin 747-53A2688, Revision 1, 
dated September 19, 2012, specifies a compliance time ``after the 
Revision 1 date of this service bulletin,'' this AD requires 
compliance within the specified compliance time after the effective 
date of this AD.
    (3) Where Table 2 or Table 4 of paragraph 1.E., ``Compliance,'' 
of Boeing Alert Service Bulletin 747-53A2688, Revision 1, dated 
September 19, 2012, specifies to contact Boeing for inspections and 
compliance times: Before further flight, contact the Manager, FAA, 
Seattle Aircraft Certification Office (ACO), for inspections and 
compliance times and accomplish the inspections at the given times.

(o) Credit for Previous Actions

    This paragraph provides credit for the actions required by 
paragraph (g) of this AD, if those actions were performed before the 
effective date of this AD using Boeing Alert Service Bulletin 747-
53A2688, dated August 21, 2008.

(p) 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 (q)(1) of this AD. 
Information may be emailed to: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.
    (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

[[Page 66258]]

the certification basis of the airplane, and the approval must 
specifically refer to this AD.
    (4) AMOCs approved for AD 2009-10-06, Amendment 39-15901 (74 FR 
22424, May 13, 2009), are approved as AMOCs for the corresponding 
actions of this AD.

(q) Related Information

    (1) For more information about this AD, contact Bill Ashforth, 
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle ACO, 
1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6432; 
fax: 425-917-6590; email: bill.ashforth@faa.gov.
    (2) Service information that is not incorporated by reference in 
this AD may be obtained at the addresses identified in paragraph 
(r)(5) of this AD.

(r) 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 
December 10, 2013.
    (i) Boeing Alert Service Bulletin 747-53A2688, Revision 1, dated 
September 19, 2012.
    (ii) Reserved.
    (4) The following service information was approved for IBR on 
June 17, 2009 (74 FR 22424, May 13, 2009).
    (i) Boeing Alert Service Bulletin 747-53A2688, dated August 21, 
2008.
    (ii) Reserved.
    (5) 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.
    (6) You may view this service information at FAA, 1601 Lind 
Avenue SW., Renton, WA. 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 October 17, 2013.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2013-25950 Filed 11-4-13; 8:45 am]
BILLING CODE 4910-13-P