Airworthiness Directives; The Boeing Company Airplanes, 57053-57057 [2013-22408]
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Federal Register / Vol. 78, No. 180 / Tuesday, September 17, 2013 / Rules and Regulations
(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: 9-ANM-Seattle-ACO-AMOCRequests@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
the certification basis of the airplane, and the
approval must specifically refer to this AD.
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(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: berhane.alazar@faa.gov.
(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: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
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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
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
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
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.
SUMMARY:
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
DATES:
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57053
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 https://
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
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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
Action
Inspections [actions retained
from AD 2010–20–08,
Amendment 39–16442 (75
FR 61337, October 5,
2010)].
Inspections [new action] .........
Labor cost
Parts cost
Up to 44 work-hours × $85
per hour = $3,740 per inspection cycle.
$0
Up to $3,740 per inspection
cycle.
Up to $564,740 per inspection
cycle.
Up to 121 work-hours × $85
per hour = $10,285 per inspection cycle.
0
Up to $10,285 per inspection
cycle.
Up to $1,553,035 per inspection cycle.
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We have received no definitive data
that would enable us to provide cost
estimates for the on-condition actions
specified in this AD.
that is likely to exist or develop on
products identified in this rulemaking
action.
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
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
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16:48 Sep 16, 2013
Cost on U.S.
operators
Cost per product
Jkt 229001
Regulatory Findings
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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
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing airworthiness directive (AD)
2010–20–08, Amendment 39–16442 (75
■
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Federal Register / Vol. 78, No. 180 / Tuesday, September 17, 2013 / Rules and Regulations
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
57055
airplanes that have been modified into the
Model 747–400 large cargo freighter
configuration.
(g) Retained Repetitive Inspections for
Frame Segment Between Stringers 23 and 31
(No Terminating Action)
(d) Subject
Joint Aircraft System Component (JASC)/
Air Transport Association (ATA) of America
Code 53, Fuselage.
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.
(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.
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.
Station 2231 inner chord angles at lower main sill interface per Figure 5 or Figure 6 of the
service bulletins specified in paragraph (g) or (h) of this AD, as applicable.
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.
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.
Station 2231 frame strap in areas covered by the reveal 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 Eddy Current
(HFEC).
(3) Open Hole HFEC ..........................................
(4) Surface HFEC ...............................................
(5) Low Frequency Eddy Current (LFEC) ..........
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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
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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
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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.
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(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.
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(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
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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
PO 00000
Frm 00024
Fmt 4700
Sfmt 4700
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-ANMSeattle-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
E:\FR\FM\17SER1.SGM
17SER1
Federal Register / Vol. 78, No. 180 / Tuesday, September 17, 2013 / Rules and Regulations
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: https://
www.archives.gov/federal-register/cfr/ibrlocations.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
DEPARTMENT OF HEALTH AND
HUMAN SERVICES
Food and Drug Administration
21 CFR Part 520
[Docket No. FDA–2013–N–0002]
Oral Dosage Form New Animal Drugs;
Amprolium; Meloxicam
AGENCY:
Food and Drug Administration,
HHS.
ACTION:
Final rule.
The Food and Drug
Administration (FDA) is amending the
animal drug regulations to reflect
approval actions for new animal drug
applications (NADAs) and abbreviated
SUMMARY:
57057
new animal drug applications
(ANADAs) during August 2013. FDA is
also informing the public of the
availability of summaries of the basis of
approval and of environmental review
documents, where applicable.
This rule is effective September
17, 2013.
DATES:
FOR FURTHER INFORMATION CONTACT:
George K. Haibel, Center for Veterinary
Medicine (HFV–6), Food and Drug
Administration, 7519 Standish Pl.,
Rockville, MD 20855, 240–276–9019,
george.haibel@fda.hhs.gov.
FDA is
amending the animal drug regulations to
reflect approval actions for NADAs and
ANADAs during August 2013, as listed
in table 1. In addition, FDA is informing
the public of the availability, where
applicable, of documentation of
environmental review required under
the National Environmental Policy Act
(NEPA) and, for actions requiring
review of safety or effectiveness data,
summaries of the basis of approval (FOI
Summaries) under the Freedom of
Information Act (FOIA). These public
documents may be seen in the Division
of Dockets Management (HFA–305),
Food and Drug Administration, 5630
Fishers Lane, Rm. 1061, Rockville, MD
20852, between 9 a.m. and 4 p.m.,
Monday through Friday. Persons with
access to the Internet may obtain these
documents at the CVM FOIA Electronic
Reading Room: https://www.fda.gov/
AboutFDA/CentersOffices/
OfficeofFoods/CVM/
CVMFOIAElectronicReadingRoom/
default.htm.
This rule does not meet the definition
of ‘‘rule’’ in 5 U.S.C. 804(3)(A) because
it is a rule of ‘‘particular applicability.’’
Therefore, it is not subject to the
congressional review requirements in 5
U.S.C. 801–808.
SUPPLEMENTARY INFORMATION:
TABLE 1—ORIGINAL AND SUPPLEMENTAL NADAS AND ANADAS APPROVED DURING AUGUST 2013
NADA/
ANADA
Sponsor
200–514 ...
Phibro Animal Health Corp.,
GlenPointe Centre East,
3d floor, 300 Frank W.
Burr Blvd., Suite 21, Teaneck, NJ 07666.
Ceva Sante Animale, 10 Av´
enue de la Ballastiere
33500 Libourne, France.
mstockstill on DSK4VPTVN1PROD with RULES
200–550 ...
New Animal Drug Product
Name
21 CFR
Section
Action
FOIA
Summary
NEPA
Review
BOVIPROL (amprolium)
9.6% Oral Solution.
Original approval as a generic copy of NADA 13–
149.
520.100
Yes .....
CE 1.
MELOXIDYL (meloxicam)
Oral Suspension.
Original approval as a generic copy of NADA 141–
213.
520.1350
Yes .....
CE 1.
1 The Agency has determined under 21 CFR 25.33(a)(1) that this action is categorically excluded (CE) from the requirement to submit an environmental assessment or an environmental impact statement because it is of a type that does not individually or cumulatively have a significant
effect on the human environment.
VerDate Mar<15>2010
16:48 Sep 16, 2013
Jkt 229001
PO 00000
Frm 00025
Fmt 4700
Sfmt 4700
E:\FR\FM\17SER1.SGM
17SER1
]]>Agencies
[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]
-----------------------------------------------------------------------
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.
-----------------------------------------------------------------------
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 https://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: https://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
