
[Federal Register Volume 78, Number 180 (Tuesday, September 17, 2013)]
[Rules and Regulations]
[Pages 57053-57057]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-22408]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0097; Directorate Identifier 2011-NM-243-AD; 
Amendment 39-17572; AD 2013-17-08]
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) 2010-20-08, 
which applied to certain The Boeing Company Model 747-100, 747-100B, 
747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 
747-400F, and 747SR series airplanes. AD 2010-20-08 required repetitive 
inspections to find cracking of the web, strap, inner chords, inner 
chord angle of the forward edge frame of the number 5 main entry door 
cutouts; the frame segment between stringers 16 and 31; repair if 
necessary; and repetitive inspections for cracking of repairs. This new 
AD expands the previous fuselage areas that are inspected for cracking. 
This AD was prompted by multiple reports of cracking outside of the 
previous inspection areas and a report of a crack that initiated at the 
aft edge of the inner chord rather than initiating at a fastener 
location. We are issuing this AD to detect and correct such cracks, 
which could cause damage to the adjacent body structure and could 
result in depressurization of the airplane in flight.

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.
    The Director of the Federal Register approved the incorporation by 
reference of a certain other publication listed in this AD as of 
November 9, 2010 (75 FR 61337, October 5, 2010).
    The Director of the Federal Register approved the incorporation by 
reference of a certain other publication listed in this AD as of 
September 12, 2001 (66 FR 41440, August 8, 2001).

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 service information 
at the FAA, Transport Airplane Directorate, 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: Nathan Weigand, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office 
(ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-
6428; fax: 425-917-6590; email: Nathan.P.Weigand@faa.gov.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2010-20-08, Amendment 39-16442 (75 FR 61337, 
October 5, 2010) (``AD 2010-20-08)''. AD 2010-20-08 applied to the 
specified products. The NPRM published in the Federal Register on March 
6, 2013 (78 FR 14469). The NPRM proposed to require repetitive 
inspections to find cracking of the web, strap, inner chords, inner 
chord angle of the forward edge frame of the number 5 main entry door 
cutouts; the frame segment between stringers 16 and 31; repair if 
necessary; and repetitive inspections for cracking of repairs. The NPRM 
also proposed to expand the previous fuselage areas that are inspected 
for cracking.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The

[[Page 57054]]

following presents the comments received on the proposal (78 FR 14469, 
March 6, 2013) and the FAA's response to each comment.

Support for the NPRM (78 FR 14469, March 6, 2013)

    Boeing stated that it concurs with the contents of the NPRM (78 FR 
14469, March 6, 2013).

Request To Change Repair Procedure

    UPS requested that we revise paragraph (q) of the NPRM (78 FR 
14469, March 6, 2013) to allow repairs in accordance with Boeing Alert 
Service Bulletin 747-53A2450, Revision 7, dated November 2, 2011, 
instead of only the alternative method of compliance process. UPS 
asserted that Boeing Alert Service Bulletin 747-53A2450, Revision 7, 
dated November 2, 2011, provides instructions to repair crack findings 
for the initial and post-repair inspections required by the NPRM.
    We partially agree with the commenter's request. We agree that the 
crack repair for the initial and repetitive inspections required by 
paragraph (o) of this final rule is addressed by Boeing Alert Service 
Bulletin 747-53A2450, Revision 7, dated November 2, 2011. However, 
post-repair cracking is not covered by Boeing Alert Service Bulletin 
747-53A2450, Revision 7, dated November 2, 2011. We have redesignated 
paragraph (q) of the NPRM as paragraphs (q)(1) and (q)(2) in this final 
rule. We have changed paragraph (q)(1) of this final rule to specify 
that the initial inspection crack repair for paragraph (o) of this 
final rule is to be done in accordance with Boeing Alert Service 
Bulletin 747-53A2450, Revision 7, dated November 2, 2011. We have not 
changed the crack repair procedure for the post-repair inspection 
required by paragraph (q)(2) of this final rule.

Changes Made to This Final Rule

    We have redesignated paragraph (r) of the NPRM (78 FR 14469, March 
6, 2013) as paragraph (r)(1) in this final rule, and have added 
paragraph (r)(2) in this final rule to clarify certain post-repair 
inspection procedures.

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:
     Are consistent with the intent that was proposed in the 
NPRM (78 FR 14469, March 6, 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 14469, March 6, 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 151 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
----------------------------------------------------------------------------------------------------------------
Inspections [actions retained      Up to 44 work-hours              $0  Up to $3,740 per     Up to $564,740 per
 from AD 2010-20-08, Amendment 39-  x $85 per hour =                     inspection cycle.    inspection cycle.
 16442 (75 FR 61337, October 5,     $3,740 per
 2010)].                            inspection cycle.
Inspections [new action].........  Up to 121 work-                   0  Up to $10,285 per    Up to $1,553,035
                                    hours x $85 per                      inspection cycle.    per inspection
                                    hour = $10,285 per                                        cycle.
                                    inspection cycle.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition 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

    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) 
2010-20-08, Amendment 39-16442 (75

[[Page 57055]]

FR 61337, October 5, 2010), and adding the following new AD:

2013-17-08 The Boeing Company: Amendment 39-17572; Docket No. FAA-
2013-0097; Directorate Identifier 2011-NM-243-AD.

(a) Effective Date

    This AD is effective October 22, 2013.

(b) Affected ADs

    This AD supersedes AD 2010-20-08, Amendment 39-16442 (75 FR 
61337, October 5, 2010).

(c) Applicability

    This AD applies to The Boeing Company Model 747-100, 747-100B, 
747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-
400D, 747-400F, and 747SR series airplanes, certificated in any 
category, having line numbers 1 through 1419 inclusive; except for 
Model 747-400 series airplanes that have been modified into the 
Model 747-400 large cargo freighter configuration.

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by multiple reports of cracking outside of 
the previous inspection areas and a report of a crack that initiated 
at the aft edge of the inner chord rather than initiating at a 
fastener location. We are issuing this AD to detect and correct such 
cracks, which could cause damage to the adjacent body structure and 
could result in depressurization of the airplane in flight.

(f) Compliance

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

(g) Retained Repetitive Inspections for Frame Segment Between Stringers 
23 and 31 (No Terminating Action)

    This paragraph restates the requirements of paragraph (g) of AD 
2010-20-08, Amendment 39-16442 (75 FR 61337, October 5, 2010). For 
airplanes having line numbers 1 through 1304 inclusive: Inspect the 
airplane for cracks between stringers 23 and 31 per Boeing Alert 
Service Bulletin 747-53A2450, Revision 2, including Appendix A, 
dated January 4, 2001; or Boeing Alert Service Bulletin 747-53A2450, 
Revision 5, dated January 29, 2009; at the later of the applicable 
times specified in paragraph (h) or (i) of this AD, per table 1 to 
paragraphs (g) and (h) of this AD. Where there are differences 
between the AD and Boeing Alert Service Bulletin 747-53A2450, 
Revision 2, including Appendix A, dated January 4, 2001; or Boeing 
Alert Service Bulletin 747-53A2450, Revision 5, dated January 29, 
2009; the AD prevails.

  Table 1 to Paragraphs (g) and (h) of this AD--Inspection Requirements
------------------------------------------------------------------------
      Type of Inspection                    Area to Inspect
------------------------------------------------------------------------
(1) Detailed Visual..........  Strap inner chords forward and aft of the
                                web, and exposed web adjacent to the
                                inner chords on station 2231 frame from
                                stringers 23 through 31 per Figure 5 or
                                Figure 6 of the service bulletins
                                specified in paragraph (g) or (h) of
                                this AD, as applicable.
(2) Surface High Frequency     Station 2231 inner chord angles at lower
 Eddy Current (HFEC).           main sill interface per Figure 5 or
                                Figure 6 of the service bulletins
                                specified in paragraph (g) or (h) of
                                this AD, as applicable.
(3) Open Hole HFEC...........  Station 2231 frame fastener locations per
                                Figures 4 and 7, and either Figure 5 or
                                6 of the service bulletins specified in
                                paragraph (g) or (h) of this AD, as
                                applicable.
(4) Surface HFEC.............  Around fastener locations on station 2231
                                inner chords from stringers 23 through
                                31 per Figure 5 or Figure 6 of the
                                service bulletins specified in paragraph
                                (g) or (h) of this AD, as applicable.
(5) Low Frequency Eddy         Station 2231 frame strap in areas covered
 Current (LFEC).                by the reveal per Figure 5 or Figure 6
                                of the service bulletins specified in
                                paragraph (g) or (h) of this AD, as
                                applicable.
------------------------------------------------------------------------


    Note 1 to paragraph (g) of this AD: There is no terminating 
action currently available for the inspections required by paragraph 
(g) of this AD.

(h) Retained Compliance Times

    This paragraph restates the requirements of paragraph (h) of AD 
2010-20-08, Amendment 39-16442 (75 FR 61337, October 5, 2010). Do 
the inspections specified in paragraph (g) of this AD at the 
applicable times specified in paragraph (h)(1) or (h)(2) of this AD. 
Repeat the inspections at intervals not to exceed 3,000 flight 
cycles until the inspections required by paragraph (m) or (o) of 
this AD are done. Where there are differences between the AD and 
Boeing Alert Service Bulletin 747-53A2450, Revision 2, including 
Appendix A, dated January 4, 2001; or Boeing Alert Service Bulletin 
747-53A2450, Revision 5, dated January 29, 2009; the AD prevails.
    (1) Do the inspections per table 1 to paragraphs (g) and (h) of 
this AD at the applicable time specified in the logic diagram in 
Figure 1 of Boeing Alert Service Bulletin 747-53A2450, Revision 2, 
including Appendix A, dated January 4, 2001. Where the compliance 
time in the logic diagram specifies a compliance time beginning 
``from receipt of this service bulletin,'' this AD requires that the 
compliance time begin ``after September 12, 2001 (the effective date 
of AD 2001-16-02, Amendment 39-12370 (66 FR 41440, August 8, 
2001)).''
    (2) After November 9, 2010 (the effective date of AD 2010-20-08, 
Amendment 39-16442 (75 FR 61337, October 5, 2010)), do the 
inspections per table 1 to paragraphs (g) and (h) of this AD at the 
applicable compliance time specified in paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 747-53A2450, 
Revision 5, dated January 29, 2009. Where the compliance time in 
Boeing Alert Service Bulletin 747-53A2450, Revision 2, including 
Appendix A, dated January 4, 2001, specifies a compliance time 
beginning ``after the date on Revision 2 of this service bulletin,'' 
this AD requires that the compliance time begin ``after September 
12, 2001 (the effective date of AD 2001-16-02, Amendment 39-12370 
(66 FR 41440, August 8, 2001)).''

(i) Retained Repetitive Inspections for Frame Segment Between Stringers 
23 and 31

    This paragraph restates the requirements of paragraph (i) of AD 
2010-20-08, Amendment 39-16442 (75 FR 61337, October 5, 2010). 
Within 3,000 flight cycles after accomplishment of the inspections 
specified in Figure 1 of Boeing Alert Service Bulletin 747-53A2450, 
dated May 4, 2000; or Boeing Alert Service Bulletin 747-53A2450, 
Revision 1, dated July 6, 2000; repeat the inspections specified in 
paragraph (g) of this AD at intervals not to exceed 3,000 flight 
cycles until the inspections required by paragraph (m) or (o) of 
this AD are done. Where there are differences between the AD and 
Boeing Alert Service Bulletin 747-53A2450, Revision 2, dated January 
4, 2001; or Boeing Alert Service Bulletin 747-53A2450, Revision 5, 
dated January 29, 2009; the AD prevails.

(j) Retained Additional Repetitive Inspections (For Frame Segment 
Between Stringers 16 and 23)

    This paragraph restates the requirements of paragraph (j) of AD 
2010-20-08, Amendment 39-16442 (75 FR 61337, October 5, 2010).
    (1) For all airplanes: Before the accumulation of 16,000 total 
flight cycles, or within 1,500 flight cycles after November 9, 2010 
(the effective date of AD 2010-20-08, Amendment 39-16442 (75 FR 
61337, October 5, 2010)), whichever occurs later, do a detailed 
inspection, an open hole HFEC inspection, a surface HFEC inspection, 
and a subsurface LFEC inspection for cracking of the forward edge 
frame of the number 5 main entry door cutouts, at station 2231, 
between stringers 16 and 23; in accordance with the Accomplishment 
Instructions of Boeing Alert Service Bulletin 747-53A2450, Revision 
5, dated January 29, 2009. Repeat the inspections thereafter at 
intervals not to exceed 3,000 flight cycles.

[[Page 57056]]

    (2) The part number of the nut for fastener code ``K'' in Figure 
7 of Boeing Alert Service Bulletin 747-53A2450, Revision 5, dated 
January 29, 2009, should be ``BACN10JC3CD,'' instead of 
``BACB30JC3CD.'' In addition, the part number of the optional nut 
for this fastener code should be ``BACN10YR3CD,'' instead of 
``BACN10YR4CD,'' in Boeing Alert Service Bulletin 747-53A2450, 
Revision 5, dated January 29, 2009.

(k) Retained Repetitive Inspections for Line Numbers 1305 and On (For 
Frame Segment Between Stringers 23 and 31)

    This paragraph restates the requirements of paragraph (k) of AD 
2010-20-08, Amendment 39-16442 (75 FR 61337, October 5, 2010). For 
airplanes having line numbers 1305 and on: Before the accumulation 
of 16,000 total flight cycles, or within 1,500 flight cycles after 
November 9, 2010 (the effective date of AD 2010-20-08, Amendment 39-
16442 (75 FR 61337, October 5, 2010)), whichever occurs later, do a 
detailed inspection, an open hole HFEC inspection, a surface HFEC 
inspection, and a subsurface LFEC inspection for cracking of the 
forward edge frame of the number 5 main entry door cutouts, at 
station 2231, between stringers 23 and 31; in accordance with the 
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2450, Revision 5, dated January 29, 2009. Repeat the inspections 
thereafter at intervals not to exceed 3,000 flight cycles.

(l) Retained Corrective Action for Paragraphs (g), (j), and (k) of This 
AD

    This paragraph restates the requirements of paragraph (l) of AD 
2010-20-08, Amendment 39-16442 (75 FR 61337, October 5, 2010). If 
any crack is found during any inspection required by paragraph (g), 
(j), or (k) of this AD, before further flight, repair the crack in 
accordance with a method approved by the Manager, Seattle Aircraft 
Certification Office (ACO), FAA, in accordance with data meeting the 
type certification basis of the airplane approved by the Boeing 
Commercial Airplanes Organization Designation Authorization (ODA) 
that has been authorized by the Manager, Seattle ACO, to make those 
findings; or in accordance with Boeing Alert Service Bulletin 747-
53A2450, Revision 5, dated January 29, 2009; as applicable. For a 
repair method to be approved by the Manager, Seattle ACO, as 
required by this paragraph, the approval letter must specifically 
reference this AD. As of November 9, 2010 (the effective date of AD 
2010-20-08), repair the crack using a method approved in accordance 
with the procedures specified in paragraph (s) of this AD.

(m) Retained Post-Repair Inspections

    This paragraph restates the requirements of paragraph (m) of AD 
2010-20-08, Amendment 39-16442 (75 FR 61337, October 5, 2010). 
Except as required by paragraph (n) of this AD, for airplanes on 
which the forward edge frame of the number 5 main entry door 
cutouts, at station 2231, between stringers 16 and 31, is repaired 
as specified in Boeing Alert Service Bulletin 747-53A2450: Within 
3,000 flight cycles after doing the repair, or within 1,500 flight 
cycles after November 9, 2010 (the effective date of AD 2010-20-08), 
whichever occurs later, do the detailed, LFEC, and HFEC inspections 
of the repaired area for cracks, in accordance with the 
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2450, Revision 5, dated January 29, 2009. If no cracking is 
found, repeat the inspections thereafter at intervals not to exceed 
3,000 flight cycles. If any crack is found: Before further flight, 
repair using a method approved in accordance with the procedures 
specified in paragraph (s) of this AD. Doing the inspections 
specified in paragraph (m) of this AD terminates the repetitive 
inspections required by paragraphs (g), (h), (i), (j), and (k) of 
this AD for the repaired area.

(n) Retained Post-Repair Inspection Restriction

    This paragraph restates the requirements of paragraph (n) of AD 
2010-20-08, Amendment 39-16442 (75 FR 61337, October 5, 2010). For 
any frame that is repaired in accordance with a method other than 
the Accomplishment Instructions of Boeing Alert Service Bulletin 
747-53A2450, Revision 5, dated January 29, 2009: Do the inspection 
in accordance with a method approved in accordance with the 
procedures specified in paragraph (s) of this AD.

(o) New Repetitive Inspections With Expanded Inspection Area

    Before the accumulation of 16,000 total flight cycles, or within 
3,000 flight cycles after the effective date of this AD, whichever 
occurs later, do the inspections required by paragraphs (o)(1) 
through (o)(5) of this AD, except as specified in paragraph (p) of 
this AD. Do all actions required by this paragraph in accordance 
with the Accomplishment Instructions of Boeing Alert Service 
Bulletin 747-53A2450, Revision 7, dated November 2, 2011. Repeat the 
inspections thereafter at the applicable times specified in 
Paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 
747-53A2450, Revision 7, dated November 2, 2011. Accomplishment of 
the initial inspections required by this paragraph terminates the 
requirements of paragraphs (g) through (k) of this AD.
    (1) Do a detailed inspection for cracking on the frame strap, 
inner chords forward and aft of the web, and exposed web adjacent to 
the inner chords from stringer 15 to 31.
    (2) Do an HFEC inspection of the station 2231 frame fastener 
locations for cracking from stringer 16 to 31, including locations 
common to the upper main sill strap and stringer clip at stringer 
16.
    (3) Do an HFEC inspection for cracking of the frame inner chords 
around the fastener heads from stringer 15 to 31.
    (4) Do an HFEC inspection for cracking of the aft edge of the 
aft inner chord, of the forward edge of the forward inner chord, and 
of the forward and aft edges of the frame strap from stringer 15 to 
31.
    (5) Do an LFEC inspection for cracking of the station 2231 frame 
strap from stringer 16 to 31 in areas covered by the reveal.

(p) New Post-Repair Inspection for Repaired Areas

    For airplanes on which the post-repair inspections are being 
done as specified in paragraph (m) of this AD: For the repaired area 
only, continue the inspections as specified in paragraph (m) of this 
AD in lieu of the inspections specified in paragraph (o) of this AD.

(q) New Corrective Action

    (1) If any cracking is found during any inspection required by 
paragraph (o) of this AD: Before further flight, repair the 
cracking, in accordance with the Accomplishment Instructions of 
Boeing Alert Service Bulletin 747-53A2450, Revision 7, dated 
November 2, 2011.
    (2) If any cracking is found during any inspection required by 
paragraph (p) or (r) of this AD: Before further flight, repair the 
cracking using a method approved in accordance with the procedures 
specified in paragraph (s) of this AD.

(r) New Post-Repair Repetitive Inspections and Corrective Action

    (1) For any airplane repaired as specified in paragraph (q)(1) 
of this AD: Within 3,000 flight cycles after doing the repair, do 
detailed, LFEC, and HFEC inspections of the repaired area for 
cracking, in accordance with the Accomplishment Instructions of 
Boeing Alert Service Bulletin 747-53A2450, Revision 7, dated 
November 2, 2011. If no cracking is found, repeat the inspections 
thereafter at intervals not to exceed 3,000 flight cycles. If any 
cracking is found: Before further flight, repair the cracking using 
a method approved in accordance with the procedures specified in 
paragraph (s) of this AD.
    (2) For any airplane repaired as specified in paragraph (q)(2) 
of this AD: Before further flight, contact the Manager, Seattle 
Aircraft Certification Office (ACO), FAA, for instructions and 
compliance times for doing an inspection of the repaired area for 
cracking. Do the inspection at the compliance times specified using 
the inspection procedures provided. If any cracking is found: Before 
further flight, repair the cracking using a method approved in 
accordance with the procedures specified in paragraph (s) of this 
AD.

(s) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Seattle 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: 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 ODA that has been authorized by the 
Manager, Seattle ACO, to make those findings. For a repair

[[Page 57057]]

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 2010-20-08, 
Amendment 39-16442 (75 FR 61337, October 5, 2010), are approved as 
AMOCs for the corresponding provisions of paragraphs (g) through (m) 
of this AD.
    (5) AMOCs approved previously in accordance with AD 2010-20-08, 
Amendment 39-16442 (75 FR 61337, October 5, 2010), that have post-
repair inspections are approved as AMOCs for the corresponding 
provisions of paragraph (o) of this AD for the repaired area only.

(t) Related Information

    For more information about this AD, contact Nathan Weigand, 
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft 
Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-
3356; phone: 425-917-6428; fax: 425-917-6590; email: 
Nathan.P.Weigand@faa.gov.

(u) 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 
October 22, 2013.
    (i) Boeing Alert Service Bulletin 747-53A2450, Revision 7, dated 
November 2, 2011.
    (ii) Reserved.
    (4) The following service information was approved for IBR on 
November 9, 2010 (75 FR 61337, October 5, 2010).
    (i) Boeing Alert Service Bulletin 747-53A2450, Revision 5, dated 
January 29, 2009.
    (ii) Reserved.
    (5) The following service information was approved for IBR on 
September 12, 2001 (66 FR 441440, August 8, 2001).
    (i) Boeing Alert Service Bulletin 747-53A2450, Revision 2, 
including Appendix A, dated January 4, 2001.
    (ii) Reserved.
    (6) 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.
    (7) You may view this service information at FAA, Transport 
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For 
information on the availability of this material at the FAA, call 
425-227-1221.
    (8) 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 16, 2013.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2013-22408 Filed 9-16-13; 8:45 am]
BILLING CODE 4910-13-P


