Airworthiness Directives; The Boeing Company Airplanes, 66254-66258 [2013-25950]
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66254
Federal Register / Vol. 78, No. 214 / Tuesday, November 5, 2013 / Rules and Regulations
(i) Revise the Operating Limitations section
of the Model 206L RFM by inserting Section
1, Operating Limitations, page 1–4B, of Bell
BHT–206L–FM–1, revision 28, dated
December 8, 2008.
(ii) Remove placard P/N 230–075–213–123,
if installed.
(ii) Install placard P/N 230–075–213–127,
or equivalent, on the instrument panel below
the dual tachometer.
(f) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Safety Management
Group, FAA, may approve AMOCs for this
AD. Send your proposal to: Chinh Vuong,
Aviation Safety Engineer, Safety Management
Group, Rotorcraft Directorate, FAA, 2601
Meacham Blvd., Fort Worth, Texas 76137;
telephone (817) 222–5110; email
chinh.vuong@faa.gov.
(2) For operations conducted under a 14
CFR part 119 operating certificate or under
14 CFR part 91, subpart K, we suggest that
you notify your principal inspector, or
lacking a principal inspector, the manager of
the local flight standards district office or
certificate holding district office, before
operating any aircraft complying with this
AD through an AMOC.
(g) Additional Information
(1) Bell Alert Service Bulletin (ASB) No.
206–07–115, Revision C, dated February 4,
2009, and Bell ASB No. 206L–07–146,
Revision B, dated March 3, 2009, which are
not incorporated by reference, contain
additional information about the subject of
this AD. For service information identified in
this AD, contact Bell Helicopter Textron
Canada Limited, 12,800 Rue de l’Avenir,
Mirabel, Quebec J7J1R4; telephone (450)
437–2862 or (800) 363–8023; fax (450) 433–
0272; or at https://www.bellcustomer.com/
files/. You may review a copy of the service
information at the FAA, Office of the
Regional Counsel, Southwest Region, 2601
Meacham Blvd., Room 663, Fort Worth,
Texas 76137.
(2) The subject of this AD is addressed in
Transport Canada Civil Aviation (TCCA) AD
No. CF–2007–13R2, dated December 9, 2009.
You may view the TCCA AD on the internet
in the AD Docket at https://
www.regulations.gov.
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(h) Subject
Joint Aircraft Service Component (JASC)
Code: 7250: Turbine Section.
(i) 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) Page 1–2A of Section 1, Operating
Limitations, of Bell Rotorcraft Flight Manual
BHT–206B–FM–1, Revision B–50, dated
December 8, 2008.
(ii) Page 1–4B of Section 1, Operating
Limitations, of Bell Rotorcraft Flight Manual
BHT–206L–FM–1, Revision 28, dated
December 8, 2008.
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(3) For Bell service information identified
in this AD, contact Bell Helicopter Textron
Canada Limited, 12,800 Rue de l’Avenir,
Mirabel, Quebec J7J1R4; telephone (450)
437–2862 or (800) 363–8023; fax (450) 433–
0272; or at https://www.bellcustomer.com/
files/.
(4) You may view this service information
at FAA, Office of the Regional Counsel,
Southwest Region, 2601 Meacham Blvd.,
Room 663, Fort Worth, Texas 76137. For
information on the availability of this
material at the FAA, call (817) 222–5110.
(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.
Issued in Fort Worth, Texas, on September
25, 2013.
Lance T. Gant,
Acting Directorate Manager, Rotorcraft
Directorate, Aircraft Certification Service.
[FR Doc. 2013–24037 Filed 11–4–13; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–0328; Directorate
Identifier 2012–NM–184–AD; Amendment
39–17643; AD 2013–22–11]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are superseding
Airworthiness Directive (AD) 2009–10–
06 for certain The Boeing Company
Model 747–400 and –400D series
airplanes. AD 2009–10–06 required
repetitive inspections to detect cracks in
the floor panel attachment fastener
holes of the Section 41 upper deck floor
beam upper chords, and corrective
actions if necessary; and repetitive postrepair and post-modification
inspections, and corrective actions if
necessary. This new AD adds repetitive
inspections of Section 44 upper deck
floor beam upper chords, and corrective
actions if necessary; repetitive postrepair and post-modification
inspections, and corrective actions if
necessary; and replacement of the upper
deck floor beam upper chords. This AD
was prompted by an evaluation by the
design approval holder (DAH)
indicating that certain upper chords of
SUMMARY:
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the upper deck floor beam are subject to
widespread fatigue damage (WFD). We
are issuing this AD to detect and correct
fatigue cracking in certain upper chords
of the upper deck floor beam, which
could become large and cause the floor
beams to become severed and result in
rapid decompression or reduced
controllability of the airplane.
DATES: This AD is effective December
10, 2013.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of December 10, 2013.
The Director of the Federal Register
approved the incorporation by reference
of a certain other publication listed in
this AD as of June 17, 2009 (74 FR
22424, May 13, 2009).
ADDRESSES: For service information
identified in this AD, contact Boeing
Commercial Airplanes, Attention: Data
& Services Management, P.O. Box 3707,
MC 2H–65, Seattle, WA 98124–2207;
telephone 206–544–5000, extension 1;
fax 206–766–5680; Internet https://
www.myboeingfleet.com. You may view
this referenced service information at
the FAA, 1601 Lind Avenue SW.,
Renton, WA. For information on the
availability of this material at the FAA,
call 425–227–1221.
Examining the AD Docket
You may examine the AD docket on
the Internet at 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: Bill
Ashforth, Aerospace Engineer, Airframe
Branch, ANM–120S, FAA, Seattle ACO,
1601 Lind Avenue SW., Renton, WA
98057–3356; phone: 425–917–6432; fax:
425–917–6590; email: bill.ashforth@
faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2009–10–06,
Amendment 39–15901 (74 FR 22424,
May 13, 2009). AD 2009–10–06 applied
to the specified products. The NPRM
published in the Federal Register on
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Federal Register / Vol. 78, No. 214 / Tuesday, November 5, 2013 / Rules and Regulations
April 16, 2013 (78 FR 22435). The
NPRM proposed to continue to require
repetitive inspections to detect cracks in
the floor panel attachment fastener
holes of the Section 41 upper deck floor
beam upper chords, and corrective
actions if necessary; and repetitive postrepair and post-modification
inspections, and corrective actions if
necessary. The NPRM also proposed to
add repetitive inspections of Section 44
upper deck floor beam upper chords,
and corrective actions if necessary;
repetitive post-repair and postmodification inspections, and corrective
actions if necessary; and replacement of
the upper deck floor beam upper
chords.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comments
received on the proposal (78 FR 22435,
April 16, 2013) and the FAA’s response
to each comment.
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Request To Eliminate Duplicate
Reference to Post-Repair and PostModification Repetitive Inspections
Boeing requested that we delete the
reference to post-repair and postmodification repetitive inspections from
paragraph (g) of the NPRM (78 FR
22435, April 16, 2013). Boeing stated
that the post-repair and postmodification inspections are required by
paragraph (i) of the NPRM, and need to
be deleted from paragraph (g) of the
NPRM to avoid confusion.
We agree to remove the duplicate
reference to post-repair and postmodification repetitive inspections from
paragraph (g) of this final rule. We have
changed paragraph (g) of this final rule
accordingly.
Request To Revise the Heading and
Clarify Paragraph (k) of the NPRM (78
FR 22435, April 16, 2013)
Boeing requested that we revise the
heading of paragraph (k) of the NPRM
(78 FR 22435, April 16, 2013) to clarify
that the modification specified in Table
2 of paragraph 1.E., ‘‘Compliance,’’ of
Boeing Service Bulletin 747–53A2688,
Revision 1, dated September 19, 2012, is
not new and is not fully terminating.
Boeing also requested that we add text
concerning terminating inspections
required by paragraphs (g) and (j) of the
NPRM, and also for the resumption of
inspections required by paragraphs (i)
and (l) of the NPRM.
We agree with the request. We have
revised the heading of paragraph (k) of
this final rule to ‘‘New Terminating
Action for Certain Conditions.’’ We also
agree with adding text to paragraph (k)
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of this final rule to clarify which
modifications or repairs as
modifications terminate which
inspections required by this final rule.
We have revised paragraph (k) of this
final rule to add new paragraph (k)(1) to
this final rule to specify that, for Section
41, doing a hole modification or repair
as a hole modification, in accordance
with ‘‘Part 2—Section 41—Repair,’’ of
the Accomplishment Instructions of
Boeing Alert Service Bulletin 747–
53A2688, Revision 1, dated September
19, 2012, terminates the repetitive
inspections specified in paragraph (g) of
this final rule. We have also included
clarification in paragraph (k)(1) of this
final rule to indicate that the repetitive
inspections specified in paragraph (i) of
this final rule must be done.
We have also moved the content of
paragraph (k) of the NPRM (78 FR
22435, April 16, 2013) to new paragraph
(k)(2) of this final rule to specify that,
for Section 44, doing a hole
modification or repair as a hole
modification, in accordance with ‘‘Part
5—Section 44—Repair,’’ of the
Accomplishment Instructions of Boeing
Alert Service Bulletin 747–53A2688,
Revision 1, dated September 19, 2012,
terminates the repetitive inspections
specified in paragraph (j) of this final
rule. We have also included clarification
in paragraph (k)(2) of this final rule to
indicate that the repetitive inspections
specified in paragraph (l) of this final
rule must be done.
Request To Restart Inspections After
Replacement of Upper Deck Floor
Beam Upper Chords
Boeing requested that we revise
paragraph (m) of the NPRM (78 FR
22435, April 16, 2013) to add a note
concerning the new inspection
threshold, equal to the original
threshold, to restart inspections after
replacement of the upper deck floor
beam upper chords. Boeing stated that
paragraph (m) of the NPRM requires the
replacement of upper deck floor beam
upper chords in Sections 41 and 44, as
given in Table 5 of Boeing Service
Bulletin 747–53A2688, Revision 1,
dated September 19, 2012. Boeing stated
that the new inspection threshold needs
to be provided in paragraph (m) of this
NPRM.
We agree with the request to include
a relieving compliance time for the
inspections required by this final rule
for airplanes on which the upper deck
floor beam upper chords are replaced.
Paragraphs (g), (i), (j), and (l) of this final
rule require repetitive inspections at the
applicable times specified in Tables 1
through 4 of paragraph 1.E.,
‘‘Compliance,’’ of Boeing Service
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66255
Bulletin 747–53A2688, Revision 1,
dated September 19, 2012. However,
Boeing Service Bulletin 747–53A2688,
Revision 1, dated September 19, 2012,
does not specify that accomplishing the
replacement terminates the repetitive
inspections, nor does it provide a longer
compliance time for the next inspection
done after accomplishing the
replacement. We also agree that the next
inspection after accomplishing the
replacement may be done within 20,000
flight cycles. We have determined that
this compliance time will provide an
adequate level of safety. We have
revised paragraph (m) of this final rule
to add the first interval for the repetitive
inspections required by this final rule
for airplanes on which a replacement
required by paragraph (m) of this final
rule is done.
Request To Add References to
Paragraph (n)(1) of the NPRM (78 FR
22435, April 16, 2013)
Boeing requested that we revise
paragraph (n)(1) of the NPRM (78 FR
22435, April 16, 2013) to refer to
paragraphs (j) and (l) of the NPRM.
Boeing stated that since paragraph (n) of
the NPRM is referring to new
exceptions, it should refer to cracks
found as part of the new inspections
specified in paragraph (i), (j), or (l) of
the NPRM (reference Compliance Tables
2, 3, or 4 of Boeing Service Bulletin
747–53A2688, Revision 1, dated
September 19, 2012).
We partially agree with the request.
We have added a reference to paragraph
(j) of this final rule in paragraph (n)(1)
of this final rule. Paragraph (j) of this
final rule already references paragraph
(n)(1) of this final rule as an exception.
However, we do not agree to add a
reference to paragraph (l) of this final
rule in paragraph (n)(1) of this final rule,
because paragraph (l) of this final rule
does not include a reference to the
service information for the corrective
action. Paragraph (l) of this final rule
specifies to refer to the procedures in
paragraph (p) of this final rule for
airplanes on which any cracking is
found.
Request To Allow Boeing Organization
Designation Authorization (ODA)
Approval
Boeing requested we revise paragraph
(n)(3) of the NPRM (78 FR 22435, April
16, 2013) to allow the full provisions of
Boeing ODA approval. Boeing stated
that alternative method of compliance
(AMOC) approval provisions allowed in
paragraph (p) of the NPRM should apply
to all sections of the NPRM.
We disagree. Paragraph (p)(3) of this
final rule already allows for ODA
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Federal Register / Vol. 78, No. 214 / Tuesday, November 5, 2013 / Rules and Regulations
approval of repairs. We have not
changed this final rule in this regard.
However, we have revised paragraph
(n)(3) of this final rule to clarify where
the service information specifies to
contact the FAA, operators must contact
the Seattle Aircraft Certification Office
(ACO).
Conclusion
We reviewed the relevant data,
considered the comments received, and
determined that air safety and the
public interest require adopting this AD
with the changes described previously
except for minor editorial changes. We
have determined that these minor
changes:
• Are consistent with the intent that
was proposed in the NPRM (78 FR
22435, April 16, 2013) for correcting the
unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM (78 FR 22435,
April 16, 2013).
We also determined that these
changes will not increase the economic
burden on any operator or increase the
scope of this AD.
Costs of Compliance
We estimate that this AD affects 84
airplanes of U.S. registry. We estimate
the following costs to comply with this
AD:
ESTIMATED COSTS
Action
Inspection (retained actions
from AD 2009–10–06,
Amendment 39-15901 (74
FR 22424, May 13, 2009)).
Inspection (new action) ..........
Labor cost
Up to 50 work-hours × $85
per hour = Up to $4,250
per inspection cycle.
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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,
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Jkt 232001
Cost per product
Up to $4,250 per inspection
cycle.
Up to $357,000 per inspection
cycle.
0
$22,015 per inspection cycle
$1,849,260 per inspection
cycle.
(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
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)
2009–10–06, Amendment 39–15901 (74
FR 22424, May 13, 2009), and adding
the following new AD:
■
2013–22–11 The Boeing Company:
Amendment 39–17643; Docket No.
FAA–2013–0328; Directorate Identifier
2012–NM–184–AD.
(a) Effective Date
This AD is effective December 10, 2013.
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Cost on U.S. operators
$0
259 work-hours × $85 per
hour = $22,015 per inspection cycle.
We have received no definitive data
that would enable us to provide a cost
estimate for the repair or modification
specified in this AD.
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Parts cost
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(b) Affected ADs
This AD supersedes AD 2009–10–06,
Amendment 39–15901 (74 FR 22424, May 13,
2009).
(c) Applicability
This AD applies to The Boeing Company
Model 747–400 and –400D series airplanes;
certificated in any category; as identified in
Boeing Alert Service Bulletin 747–53A2688,
Revision 1, dated September 19, 2012.
(d) Subject
Joint Aircraft System Component (JASC)/
Air Transport Association (ATA) of America
Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by an evaluation by
the design approval holder (DAH) indicating
that certain upper chords of the upper deck
floor beam are subject to widespread fatigue
damage (WFD). We are issuing this AD to
detect and correct fatigue cracking in certain
upper chords of the upper deck floor beam,
which could become large and cause the
floor beams to become severed and result in
rapid decompression or reduced
controllability of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Retained Inspections and Corrective
Actions With Revised Service Information
and Compliance Times
This paragraph restates the actions
required by paragraph (g) of AD 2009–10–06,
Amendment 39–15901 (74 FR 22424, May 13,
2009), with revised service information and
compliance times. Except as required by
paragraphs (h)(1) and (h)(2) of this AD: At the
applicable times in paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 747–53A2688, dated August 21,
2008, do an inspection (open-hole or surface
high frequency eddy current (HFEC)) to
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(h) Retained Exceptions
(1) This paragraph restates the exception
stated in paragraph (h) of AD 2009–10–06,
Amendment 39–15901 (74 FR 22424, May 13,
2009). If any crack is found during any
inspection required by paragraph (g) of this
AD, and Boeing Alert Service Bulletin 747–
53A2688, dated August 21, 2008; or Revision
1, dated September 19, 2012; specifies to
contact Boeing for appropriate action: Before
further flight, repair the crack using a method
approved in accordance with the procedures
specified in paragraph (p) of this AD.
(2) This paragraph restates the exception
stated in paragraph (i) of AD 2009–10–06,
Amendment 39–15901 (74 FR 22424, May 13,
2009). Where Boeing Alert Service Bulletin
747–53A2688, dated August 21, 2008,
specifies a compliance time after the date on
the service bulletin, this AD requires
compliance within the specified compliance
time after June 17, 2009 (the effective date of
AD 2009–10–06).
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detect cracks in the floor panel attachment
fastener holes of the Section 41 upper deck
floor beam upper chords, and do applicable
corrective actions, by accomplishing all the
applicable actions specified in the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–53A2688, dated August
21, 2008; or Revision 1, dated September 19,
2012. Repeat the inspections thereafter at the
applicable times specified in paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 747–53A2688, dated August 21,
2008, except as required by paragraphs (i)
and (m) of this AD. As of the effective date
of this AD, use only Boeing Alert Service
Bulletin 747–53A2688, Revision 1, dated
September 19, 2012, to accomplish the
actions in this paragraph.
Bulletin 747–53A2688, Revision 1, dated
September 19, 2012, except as specified in
paragraph (n)(2) of this AD, do an open-hole
or surface HFEC inspection to detect cracking
in the floor panel attachment fastener holes
of the Section 44 upper deck floor beam
upper chords, and all applicable corrective
actions, in accordance with the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–53A2688, Revision 1,
dated September 19, 2012, except as required
by paragraph (n)(1) of this AD. Repeat the
inspections thereafter at the applicable
intervals specified in paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 747–53A2688, Revision 1, dated
September 19, 2012, except as provided by
paragraph (m) of this AD. Do all applicable
corrective actions before further flight.
(k) New Terminating Action for Certain
Conditions
(1) For Section 41: Doing a hole
modification or repair as a hole modification,
in accordance with ‘‘Part 2—Section 41—
Repair,’’ of the Accomplishment Instructions
of Boeing Alert Service Bulletin 747–
53A2688, Revision 1, dated September 19,
2012, terminates the repetitive inspections
specified in paragraph (g) of this AD.
However, the repetitive inspections specified
in paragraph (i) of this AD must be done.
(2) For Section 44: Doing a hole
modification or repair as a hole modification,
in accordance with ‘‘Part 5—Section 44—
Repair,’’ of the Accomplishment Instructions
of Boeing Alert Service Bulletin 747–
53A2688, Revision 1, dated September 19,
2012, terminates the repetitive inspections
specified in paragraph (j) of this AD.
However, the repetitive inspections specified
in paragraph (l) of this AD must be done.
(i) Inspections and Corrective Actions for
Airplanes on Which a Repair or
Modification Is Done (for Section 41)
For airplanes on which a repair or
modification identified in Table 2 of 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 747–53A2688, Revision 1, dated
September 19, 2012, has been done: At the
times specified in Table 2 of paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 747–53A2688, Revision 1, dated
September 19, 2012, except as required by
paragraph (n)(3) of this AD, do open-hole and
surface HFEC inspections, as applicable, for
cracking, in accordance with the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–53A2688, Revision 1,
dated September 19, 2012. Repeat at the
applicable intervals specified in Table 2 of
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 747–53A2688,
Revision 1, dated September 19, 2012. If any
cracking is found in the repaired or modified
locations, before further flight, repair the
crack using a method approved in
accordance with the procedures specified in
paragraph (p) of this AD.
(j) New Inspections and Repair
For Group 1 airplanes identified in Boeing
Alert Service Bulletin 747–53A2688,
Revision 1, dated September 19, 2012: At the
applicable times specified in paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
(l) New Inspections and Corrective Actions
for Airplanes on Which a Repair or
Modification Is Done (for Section 44)
For airplanes on which a repair or
modification specified in the ‘‘Condition’’
column of Table 4 of paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 747–53A2688, Revision 1, dated
September 19, 2012, has been done: At the
times specified in Table 4 of paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 747–53A2688, Revision 1, dated
September 19, 2012, except as required by
paragraph (n)(3) of this AD, do open hole and
surface HFEC inspections, as applicable, for
cracking, in accordance with the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–53A2688, Revision 1,
dated September 19, 2012. Repeat at the
applicable intervals specified in Table 4 of
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 747–53A2688,
Revision 1, dated September 19, 2012. If any
cracking is found in the repaired or modified
locations, before further flight, repair the
crack using a method approved in
accordance with the procedures specified in
paragraph (p) of this AD.
(m) New Replacement and Post-Replacement
Inspections
At the time specified in paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 747–53A2688, Revision 1, dated
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66257
September 19, 2012: Replace Section 41 and
44 upper deck floor beam upper chords, in
accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
747–53A2688, Revision 1, dated September
19, 2012. Repeat the inspections required by
paragraphs (g) and (j) of this AD within
20,000 flight cycles after doing the
replacement. Thereafter, repeat the
inspection required by paragraphs (g) and (j)
of this AD at the times specified in
paragraphs (g) and (j) of this AD.
(n) New Exceptions
(1) If any crack is found during any
inspection required by paragraph (i), (j), or (l)
of this AD, and Boeing Alert Service Bulletin
747–53A2688, Revision 1, dated September
19, 2012, specifies to contact Boeing for
appropriate action: Before further flight,
repair the crack using a method approved in
accordance with the procedures specified in
paragraph (p) of this AD.
(2) Where Boeing Alert Service Bulletin
747–53A2688, Revision 1, dated September
19, 2012, specifies a compliance time ‘‘after
the Revision 1 date of this service bulletin,’’
this AD requires compliance within the
specified compliance time after the effective
date of this AD.
(3) Where Table 2 or Table 4 of paragraph
1.E., ‘‘Compliance,’’ of Boeing Alert Service
Bulletin 747–53A2688, Revision 1, dated
September 19, 2012, specifies to contact
Boeing for inspections and compliance times:
Before further flight, contact the Manager,
FAA, Seattle Aircraft Certification Office
(ACO), for inspections and compliance times
and accomplish the inspections at the given
times.
(o) Credit for Previous Actions
This paragraph provides credit for the
actions required by paragraph (g) of this AD,
if those actions were performed before the
effective date of this AD using Boeing Alert
Service Bulletin 747–53A2688, dated August
21, 2008.
(p) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Seattle Aircraft
Certification Office (ACO), FAA, has the
authority to approve AMOCs for this AD, if
requested using the procedures found in 14
CFR 39.19. In accordance with 14 CFR 39.19,
send your request to your principal inspector
or local Flight Standards District Office, as
appropriate. If sending information directly
to the manager of the ACO, send it to the
attention of the person identified in
paragraph (q)(1) of this AD. Information may
be emailed to: 9-ANM-Seattle-ACO-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
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Federal Register / Vol. 78, No. 214 / Tuesday, November 5, 2013 / Rules and Regulations
the certification basis of the airplane, and the
approval must specifically refer to this AD.
(4) AMOCs approved for AD 2009–10–06,
Amendment 39–15901 (74 FR 22424, May 13,
2009), are approved as AMOCs for the
corresponding actions of this AD.
(q) Related Information
(1) For more information about this AD,
contact Bill Ashforth, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA, Seattle
ACO, 1601 Lind Avenue SW., Renton, WA
98057–3356; phone: 425–917–6432; fax: 425–
917–6590; email: bill.ashforth@faa.gov.
(2) Service information that is not
incorporated by reference in this AD may be
obtained at the addresses identified in
paragraph (r)(5) of this AD.
(r) Material Incorporated by Reference
wreier-aviles on DSK5TPTVN1PROD with RULES
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(3) The following service information was
approved for IBR on December 10, 2013.
(i) Boeing Alert Service Bulletin 747–
53A2688, Revision 1, dated September 19,
2012.
(ii) Reserved.
(4) The following service information was
approved for IBR on June 17, 2009 (74 FR
22424, May 13, 2009).
(i) Boeing Alert Service Bulletin 747–
53A2688, dated August 21, 2008.
(ii) Reserved.
(5) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Data & Services
Management, P.O. Box 3707, MC 2H–65,
Seattle, WA 98124–2207; telephone 206–
544–5000, extension 1; fax 206–766–5680;
Internet https://www.myboeingfleet.com.
(6) You may view this service information
at FAA, 1601 Lind Avenue SW., Renton, WA.
For information on the availability of this
material at the FAA, call 425–227–1221.
(7) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on October
17, 2013.
Jeffrey E. Duven,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2013–25950 Filed 11–4–13; 8:45 am]
BILLING CODE 4910–13–P
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–0868; Directorate
Identifier 2013–NM–194–AD; Amendment
39–17650; AD 2013–22–18]
RIN 2120–AA64
Airworthiness Directives; Empresa
Brasileira de Aeronautica S.A.
(EMBRAER) Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final Rule; request for
comments.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
Empresa Brasileira de Aeronautica S.A.
(EMBRAER) Model EMB–135ER,
–135KE, –135KL, and –135LR airplanes;
and Model EMB–145, –145ER, –145MR,
–145LR, –145XR, –145MP, and –145EP
airplanes. This AD requires repetitive
detailed inspections to detect
discrepancies on the attaching parts of
the lower eyelet fitting of the cockpit
windshield center-post, and, if no
discrepancy is found, a check to make
sure the bolts are tight, and replacement
of the attaching parts if necessary. This
AD also provides an option to
accomplish the replacement of the
attaching parts, which terminates the
repetitive inspections. This AD was
prompted by reports of failure of the
bolts that connect the lower eyelet
fitting of the cockpit windshield centerpost to the forward fuselage. We are
issuing this AD to detect and correct
failed bolts and attaching parts of the
lower eyelet fitting of the cockpit
windshield center-post, which could
lead to loss of structural integrity of the
airplane.
DATES: This AD becomes effective
November 20, 2013.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of November 20, 2013.
We must receive comments on this
AD by December 20, 2013.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: (202) 493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations,
M–30, West Building Ground Floor,
Room W12–140, 1200 New Jersey
Avenue SE., Washington, DC 20590.
SUMMARY:
PO 00000
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• Hand Delivery: U.S. Department of
Transportation, Docket Operations,
M–30, West Building Ground Floor,
Room W12–140, 1200 New Jersey
Avenue SE., Washington, DC, between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays.
For service information identified in
this AD, contact Empresa Brasileira de
Aeronautica S.A. (EMBRAER),
Technical Publications Section (PC
060), Av. Brigadeiro Faria Lima, 2170—
˜
Putim—12227–901 Sao Jose dos
Campos—SP—BRASIL; telephone +55
12 3927–5852 or +55 12 3309–0732; fax
+55 12 3927–7546; email distrib@
embraer.com.br; Internet https://
www.flyembraer.com. You may review
copies of the referenced 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 Operations office between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this AD, the Mandatory
Continuing Airworthiness Information
(MCAI), the regulatory evaluation, any
comments received, and other
information. The street address for the
Docket Operations office (telephone
(800) 647–5527) is in the ADDRESSES
section. Comments will be available in
the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT:
Todd Thompson, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA
98057–3356; telephone 425–227–1175;
fax 425–227–1149.
SUPPLEMENTARY INFORMATION:
Discussion
ˆ
The Agencia Nacional de Aviacao
¸˜
Civil (ANAC), which is the aviation
authority for Brazil, has issued Brazilian
Emergency Airworthiness Directive
2013–10–01, effective October 3, 2013
(referred to after this as ‘‘the MCAI’’), to
correct an unsafe condition for the
specified products. The MCAI states:
This [Brazilian] EAD [emergency AD] was
prompted by reports of failure of the bolts
that connect the lower eyelet fitting of the
cockpit windshield center-post to the
forward fuselage. We are issuing this EAD to
detect failed bolts and correct the attaching
parts of the lower eyelet fitting of the cockpit
windshield center-post, which could lead to
loss of structural integrity of the airplane.
E:\FR\FM\05NOR1.SGM
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]]>Agencies
[Federal Register Volume 78, Number 214 (Tuesday, November 5, 2013)]
[Rules and Regulations]
[Pages 66254-66258]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-25950]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-0328; Directorate Identifier 2012-NM-184-AD;
Amendment 39-17643; AD 2013-22-11]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are superseding Airworthiness Directive (AD) 2009-10-06 for
certain The Boeing Company Model 747-400 and -400D series airplanes. AD
2009-10-06 required repetitive inspections to detect cracks in the
floor panel attachment fastener holes of the Section 41 upper deck
floor beam upper chords, and corrective actions if necessary; and
repetitive post-repair and post-modification inspections, and
corrective actions if necessary. This new AD adds repetitive
inspections of Section 44 upper deck floor beam upper chords, and
corrective actions if necessary; repetitive post-repair and post-
modification inspections, and corrective actions if necessary; and
replacement of the upper deck floor beam upper chords. This AD was
prompted by an evaluation by the design approval holder (DAH)
indicating that certain upper chords of the upper deck floor beam are
subject to widespread fatigue damage (WFD). We are issuing this AD to
detect and correct fatigue cracking in certain upper chords of the
upper deck floor beam, which could become large and cause the floor
beams to become severed and result in rapid decompression or reduced
controllability of the airplane.
DATES: This AD is effective December 10, 2013.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of December 10,
2013.
The Director of the Federal Register approved the incorporation by
reference of a certain other publication listed in this AD as of June
17, 2009 (74 FR 22424, May 13, 2009).
ADDRESSES: For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-
5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. You may view this referenced service information
at the FAA, 1601 Lind Avenue SW., Renton, WA. For information on the
availability of this material at the FAA, call 425-227-1221.
Examining the AD Docket
You may examine the AD docket on the Internet at 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: Bill Ashforth, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle ACO, 1601 Lind Avenue SW.,
Renton, WA 98057-3356; phone: 425-917-6432; fax: 425-917-6590; email:
bill.ashforth@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2009-10-06, Amendment 39-15901 (74 FR 22424,
May 13, 2009). AD 2009-10-06 applied to the specified products. The
NPRM published in the Federal Register on
[[Page 66255]]
April 16, 2013 (78 FR 22435). The NPRM proposed to continue to require
repetitive inspections to detect cracks in the floor panel attachment
fastener holes of the Section 41 upper deck floor beam upper chords,
and corrective actions if necessary; and repetitive post-repair and
post-modification inspections, and corrective actions if necessary. The
NPRM also proposed to add repetitive inspections of Section 44 upper
deck floor beam upper chords, and corrective actions if necessary;
repetitive post-repair and post-modification inspections, and
corrective actions if necessary; and replacement of the upper deck
floor beam upper chords.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the proposal
(78 FR 22435, April 16, 2013) and the FAA's response to each comment.
Request To Eliminate Duplicate Reference to Post-Repair and Post-
Modification Repetitive Inspections
Boeing requested that we delete the reference to post-repair and
post-modification repetitive inspections from paragraph (g) of the NPRM
(78 FR 22435, April 16, 2013). Boeing stated that the post-repair and
post-modification inspections are required by paragraph (i) of the
NPRM, and need to be deleted from paragraph (g) of the NPRM to avoid
confusion.
We agree to remove the duplicate reference to post-repair and post-
modification repetitive inspections from paragraph (g) of this final
rule. We have changed paragraph (g) of this final rule accordingly.
Request To Revise the Heading and Clarify Paragraph (k) of the NPRM (78
FR 22435, April 16, 2013)
Boeing requested that we revise the heading of paragraph (k) of the
NPRM (78 FR 22435, April 16, 2013) to clarify that the modification
specified in Table 2 of paragraph 1.E., ``Compliance,'' of Boeing
Service Bulletin 747-53A2688, Revision 1, dated September 19, 2012, is
not new and is not fully terminating. Boeing also requested that we add
text concerning terminating inspections required by paragraphs (g) and
(j) of the NPRM, and also for the resumption of inspections required by
paragraphs (i) and (l) of the NPRM.
We agree with the request. We have revised the heading of paragraph
(k) of this final rule to ``New Terminating Action for Certain
Conditions.'' We also agree with adding text to paragraph (k) of this
final rule to clarify which modifications or repairs as modifications
terminate which inspections required by this final rule. We have
revised paragraph (k) of this final rule to add new paragraph (k)(1) to
this final rule to specify that, for Section 41, doing a hole
modification or repair as a hole modification, in accordance with
``Part 2--Section 41--Repair,'' of the Accomplishment Instructions of
Boeing Alert Service Bulletin 747-53A2688, Revision 1, dated September
19, 2012, terminates the repetitive inspections specified in paragraph
(g) of this final rule. We have also included clarification in
paragraph (k)(1) of this final rule to indicate that the repetitive
inspections specified in paragraph (i) of this final rule must be done.
We have also moved the content of paragraph (k) of the NPRM (78 FR
22435, April 16, 2013) to new paragraph (k)(2) of this final rule to
specify that, for Section 44, doing a hole modification or repair as a
hole modification, in accordance with ``Part 5--Section 44--Repair,''
of the Accomplishment Instructions of Boeing Alert Service Bulletin
747-53A2688, Revision 1, dated September 19, 2012, terminates the
repetitive inspections specified in paragraph (j) of this final rule.
We have also included clarification in paragraph (k)(2) of this final
rule to indicate that the repetitive inspections specified in paragraph
(l) of this final rule must be done.
Request To Restart Inspections After Replacement of Upper Deck Floor
Beam Upper Chords
Boeing requested that we revise paragraph (m) of the NPRM (78 FR
22435, April 16, 2013) to add a note concerning the new inspection
threshold, equal to the original threshold, to restart inspections
after replacement of the upper deck floor beam upper chords. Boeing
stated that paragraph (m) of the NPRM requires the replacement of upper
deck floor beam upper chords in Sections 41 and 44, as given in Table 5
of Boeing Service Bulletin 747-53A2688, Revision 1, dated September 19,
2012. Boeing stated that the new inspection threshold needs to be
provided in paragraph (m) of this NPRM.
We agree with the request to include a relieving compliance time
for the inspections required by this final rule for airplanes on which
the upper deck floor beam upper chords are replaced. Paragraphs (g),
(i), (j), and (l) of this final rule require repetitive inspections at
the applicable times specified in Tables 1 through 4 of paragraph 1.E.,
``Compliance,'' of Boeing Service Bulletin 747-53A2688, Revision 1,
dated September 19, 2012. However, Boeing Service Bulletin 747-53A2688,
Revision 1, dated September 19, 2012, does not specify that
accomplishing the replacement terminates the repetitive inspections,
nor does it provide a longer compliance time for the next inspection
done after accomplishing the replacement. We also agree that the next
inspection after accomplishing the replacement may be done within
20,000 flight cycles. We have determined that this compliance time will
provide an adequate level of safety. We have revised paragraph (m) of
this final rule to add the first interval for the repetitive
inspections required by this final rule for airplanes on which a
replacement required by paragraph (m) of this final rule is done.
Request To Add References to Paragraph (n)(1) of the NPRM (78 FR 22435,
April 16, 2013)
Boeing requested that we revise paragraph (n)(1) of the NPRM (78 FR
22435, April 16, 2013) to refer to paragraphs (j) and (l) of the NPRM.
Boeing stated that since paragraph (n) of the NPRM is referring to new
exceptions, it should refer to cracks found as part of the new
inspections specified in paragraph (i), (j), or (l) of the NPRM
(reference Compliance Tables 2, 3, or 4 of Boeing Service Bulletin 747-
53A2688, Revision 1, dated September 19, 2012).
We partially agree with the request. We have added a reference to
paragraph (j) of this final rule in paragraph (n)(1) of this final
rule. Paragraph (j) of this final rule already references paragraph
(n)(1) of this final rule as an exception. However, we do not agree to
add a reference to paragraph (l) of this final rule in paragraph (n)(1)
of this final rule, because paragraph (l) of this final rule does not
include a reference to the service information for the corrective
action. Paragraph (l) of this final rule specifies to refer to the
procedures in paragraph (p) of this final rule for airplanes on which
any cracking is found.
Request To Allow Boeing Organization Designation Authorization (ODA)
Approval
Boeing requested we revise paragraph (n)(3) of the NPRM (78 FR
22435, April 16, 2013) to allow the full provisions of Boeing ODA
approval. Boeing stated that alternative method of compliance (AMOC)
approval provisions allowed in paragraph (p) of the NPRM should apply
to all sections of the NPRM.
We disagree. Paragraph (p)(3) of this final rule already allows for
ODA
[[Page 66256]]
approval of repairs. We have not changed this final rule in this
regard. However, we have revised paragraph (n)(3) of this final rule to
clarify where the service information specifies to contact the FAA,
operators must contact the Seattle Aircraft Certification Office (ACO).
Conclusion
We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
this AD with the changes described previously except for minor
editorial changes. We have determined that these minor changes:
Are consistent with the intent that was proposed in the
NPRM (78 FR 22435, April 16, 2013) for correcting the unsafe condition;
and
Do not add any additional burden upon the public than was
already proposed in the NPRM (78 FR 22435, April 16, 2013).
We also determined that these changes will not increase the
economic burden on any operator or increase the scope of this AD.
Costs of Compliance
We estimate that this AD affects 84 airplanes of U.S. registry. We
estimate the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Inspection (retained actions from Up to 50 work-hours $0 Up to $4,250 per Up to $357,000 per
AD 2009-10-06, Amendment x $85 per hour = inspection cycle. inspection cycle.
39[dash]15901 (74 FR 22424, May Up to $4,250 per
13, 2009)). inspection cycle.
Inspection (new action).......... 259 work-hours x 0 $22,015 per $1,849,260 per
$85 per hour = inspection cycle. inspection cycle.
$22,015 per
inspection cycle.
----------------------------------------------------------------------------------------------------------------
We have received no definitive data that would enable us to provide
a cost estimate for the repair or modification specified in this AD.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We have determined that this AD will not have federalism
implications under Executive Order 13132. This AD will not have a
substantial direct effect on the States, on the relationship between
the national government and the States, or on the distribution of power
and responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation in Alaska, and
(4) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing airworthiness directive (AD)
2009-10-06, Amendment 39-15901 (74 FR 22424, May 13, 2009), and adding
the following new AD:
2013-22-11 The Boeing Company: Amendment 39-17643; Docket No. FAA-
2013-0328; Directorate Identifier 2012-NM-184-AD.
(a) Effective Date
This AD is effective December 10, 2013.
(b) Affected ADs
This AD supersedes AD 2009-10-06, Amendment 39-15901 (74 FR
22424, May 13, 2009).
(c) Applicability
This AD applies to The Boeing Company Model 747-400 and -400D
series airplanes; certificated in any category; as identified in
Boeing Alert Service Bulletin 747-53A2688, Revision 1, dated
September 19, 2012.
(d) Subject
Joint Aircraft System Component (JASC)/Air Transport Association
(ATA) of America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by an evaluation by the design approval
holder (DAH) indicating that certain upper chords of the upper deck
floor beam are subject to widespread fatigue damage (WFD). We are
issuing this AD to detect and correct fatigue cracking in certain
upper chords of the upper deck floor beam, which could become large
and cause the floor beams to become severed and result in rapid
decompression or reduced controllability of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Inspections and Corrective Actions With Revised Service
Information and Compliance Times
This paragraph restates the actions required by paragraph (g) of
AD 2009-10-06, Amendment 39-15901 (74 FR 22424, May 13, 2009), with
revised service information and compliance times. Except as required
by paragraphs (h)(1) and (h)(2) of this AD: At the applicable times
in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
747-53A2688, dated August 21, 2008, do an inspection (open-hole or
surface high frequency eddy current (HFEC)) to
[[Page 66257]]
detect cracks in the floor panel attachment fastener holes of the
Section 41 upper deck floor beam upper chords, and do applicable
corrective actions, by accomplishing all the applicable actions
specified in the Accomplishment Instructions of Boeing Alert Service
Bulletin 747-53A2688, dated August 21, 2008; or Revision 1, dated
September 19, 2012. Repeat the inspections thereafter at the
applicable times specified in paragraph 1.E., ``Compliance,'' of
Boeing Alert Service Bulletin 747-53A2688, dated August 21, 2008,
except as required by paragraphs (i) and (m) of this AD. As of the
effective date of this AD, use only Boeing Alert Service Bulletin
747-53A2688, Revision 1, dated September 19, 2012, to accomplish the
actions in this paragraph.
(h) Retained Exceptions
(1) This paragraph restates the exception stated in paragraph
(h) of AD 2009-10-06, Amendment 39-15901 (74 FR 22424, May 13,
2009). If any crack is found during any inspection required by
paragraph (g) of this AD, and Boeing Alert Service Bulletin 747-
53A2688, dated August 21, 2008; or Revision 1, dated September 19,
2012; specifies to contact Boeing for appropriate action: Before
further flight, repair the crack using a method approved in
accordance with the procedures specified in paragraph (p) of this
AD.
(2) This paragraph restates the exception stated in paragraph
(i) of AD 2009-10-06, Amendment 39-15901 (74 FR 22424, May 13,
2009). Where Boeing Alert Service Bulletin 747-53A2688, dated August
21, 2008, specifies a compliance time after the date on the service
bulletin, this AD requires compliance within the specified
compliance time after June 17, 2009 (the effective date of AD 2009-
10-06).
(i) Inspections and Corrective Actions for Airplanes on Which a Repair
or Modification Is Done (for Section 41)
For airplanes on which a repair or modification identified in
Table 2 of 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
747-53A2688, Revision 1, dated September 19, 2012, has been done: At
the times specified in Table 2 of paragraph 1.E., ``Compliance,'' of
Boeing Alert Service Bulletin 747-53A2688, Revision 1, dated
September 19, 2012, except as required by paragraph (n)(3) of this
AD, do open-hole and surface HFEC inspections, as applicable, for
cracking, in accordance with the Accomplishment Instructions of
Boeing Alert Service Bulletin 747-53A2688, Revision 1, dated
September 19, 2012. Repeat at the applicable intervals specified in
Table 2 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service
Bulletin 747-53A2688, Revision 1, dated September 19, 2012. If any
cracking is found in the repaired or modified locations, before
further flight, repair the crack using a method approved in
accordance with the procedures specified in paragraph (p) of this
AD.
(j) New Inspections and Repair
For Group 1 airplanes identified in Boeing Alert Service
Bulletin 747-53A2688, Revision 1, dated September 19, 2012: At the
applicable times specified in paragraph 1.E., ``Compliance,'' of
Boeing Alert Service Bulletin 747-53A2688, Revision 1, dated
September 19, 2012, except as specified in paragraph (n)(2) of this
AD, do an open-hole or surface HFEC inspection to detect cracking in
the floor panel attachment fastener holes of the Section 44 upper
deck floor beam upper chords, and all applicable corrective actions,
in accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 747-53A2688, Revision 1, dated September 19, 2012,
except as required by paragraph (n)(1) of this AD. Repeat the
inspections thereafter at the applicable intervals specified in
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
747-53A2688, Revision 1, dated September 19, 2012, except as
provided by paragraph (m) of this AD. Do all applicable corrective
actions before further flight.
(k) New Terminating Action for Certain Conditions
(1) For Section 41: Doing a hole modification or repair as a
hole modification, in accordance with ``Part 2--Section 41--
Repair,'' of the Accomplishment Instructions of Boeing Alert Service
Bulletin 747-53A2688, Revision 1, dated September 19, 2012,
terminates the repetitive inspections specified in paragraph (g) of
this AD. However, the repetitive inspections specified in paragraph
(i) of this AD must be done.
(2) For Section 44: Doing a hole modification or repair as a
hole modification, in accordance with ``Part 5--Section 44--
Repair,'' of the Accomplishment Instructions of Boeing Alert Service
Bulletin 747-53A2688, Revision 1, dated September 19, 2012,
terminates the repetitive inspections specified in paragraph (j) of
this AD. However, the repetitive inspections specified in paragraph
(l) of this AD must be done.
(l) New Inspections and Corrective Actions for Airplanes on Which a
Repair or Modification Is Done (for Section 44)
For airplanes on which a repair or modification specified in the
``Condition'' column of Table 4 of paragraph 1.E., ``Compliance,''
of Boeing Alert Service Bulletin 747-53A2688, Revision 1, dated
September 19, 2012, has been done: At the times specified in Table 4
of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
747-53A2688, Revision 1, dated September 19, 2012, except as
required by paragraph (n)(3) of this AD, do open hole and surface
HFEC inspections, as applicable, for cracking, in accordance with
the Accomplishment Instructions of Boeing Alert Service Bulletin
747-53A2688, Revision 1, dated September 19, 2012. Repeat at the
applicable intervals specified in Table 4 of paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 747-53A2688,
Revision 1, dated September 19, 2012. If any cracking is found in
the repaired or modified locations, before further flight, repair
the crack using a method approved in accordance with the procedures
specified in paragraph (p) of this AD.
(m) New Replacement and Post-Replacement Inspections
At the time specified in paragraph 1.E., ``Compliance,'' of
Boeing Alert Service Bulletin 747-53A2688, Revision 1, dated
September 19, 2012: Replace Section 41 and 44 upper deck floor beam
upper chords, in accordance with the Accomplishment Instructions of
Boeing Alert Service Bulletin 747-53A2688, Revision 1, dated
September 19, 2012. Repeat the inspections required by paragraphs
(g) and (j) of this AD within 20,000 flight cycles after doing the
replacement. Thereafter, repeat the inspection required by
paragraphs (g) and (j) of this AD at the times specified in
paragraphs (g) and (j) of this AD.
(n) New Exceptions
(1) If any crack is found during any inspection required by
paragraph (i), (j), or (l) of this AD, and Boeing Alert Service
Bulletin 747-53A2688, Revision 1, dated September 19, 2012,
specifies to contact Boeing for appropriate action: Before further
flight, repair the crack using a method approved in accordance with
the procedures specified in paragraph (p) of this AD.
(2) Where Boeing Alert Service Bulletin 747-53A2688, Revision 1,
dated September 19, 2012, specifies a compliance time ``after the
Revision 1 date of this service bulletin,'' this AD requires
compliance within the specified compliance time after the effective
date of this AD.
(3) Where Table 2 or Table 4 of paragraph 1.E., ``Compliance,''
of Boeing Alert Service Bulletin 747-53A2688, Revision 1, dated
September 19, 2012, specifies to contact Boeing for inspections and
compliance times: Before further flight, contact the Manager, FAA,
Seattle Aircraft Certification Office (ACO), for inspections and
compliance times and accomplish the inspections at the given times.
(o) Credit for Previous Actions
This paragraph provides credit for the actions required by
paragraph (g) of this AD, if those actions were performed before the
effective date of this AD using Boeing Alert Service Bulletin 747-
53A2688, dated August 21, 2008.
(p) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Seattle Aircraft Certification Office (ACO),
FAA, has the authority to approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19. In accordance with 14
CFR 39.19, send your request to your principal inspector or local
Flight Standards District Office, as appropriate. If sending
information directly to the manager of the ACO, send it to the
attention of the person identified in paragraph (q)(1) of this AD.
Information may be emailed to: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
(3) An AMOC that provides an acceptable level of safety may be
used for any repair required by this AD if it is approved by the
Boeing Commercial Airplanes Organization Designation Authorization
(ODA) that has been authorized by the Manager, Seattle ACO, to make
those findings. For a repair method to be approved, the repair must
meet
[[Page 66258]]
the certification basis of the airplane, and the approval must
specifically refer to this AD.
(4) AMOCs approved for AD 2009-10-06, Amendment 39-15901 (74 FR
22424, May 13, 2009), are approved as AMOCs for the corresponding
actions of this AD.
(q) Related Information
(1) For more information about this AD, contact Bill Ashforth,
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle ACO,
1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6432;
fax: 425-917-6590; email: bill.ashforth@faa.gov.
(2) Service information that is not incorporated by reference in
this AD may be obtained at the addresses identified in paragraph
(r)(5) of this AD.
(r) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(3) The following service information was approved for IBR on
December 10, 2013.
(i) Boeing Alert Service Bulletin 747-53A2688, Revision 1, dated
September 19, 2012.
(ii) Reserved.
(4) The following service information was approved for IBR on
June 17, 2009 (74 FR 22424, May 13, 2009).
(i) Boeing Alert Service Bulletin 747-53A2688, dated August 21,
2008.
(ii) Reserved.
(5) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-
5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com.
(6) You may view this service information at FAA, 1601 Lind
Avenue SW., Renton, WA. For information on the availability of this
material at the FAA, call 425-227-1221.
(7) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on October 17, 2013.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2013-25950 Filed 11-4-13; 8:45 am]
BILLING CODE 4910-13-P
