Airworthiness Directives; The Boeing Company Airplanes, 70441-70445 [2014-27358]
Download as PDF
<![CDATA[
Federal Register / Vol. 79, No. 228 / Wednesday, November 26, 2014 / Rules and Regulations
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.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://www.regulations.
gov/#!docketDetail;D=FAA-2014-0191;
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 street address for the
Docket Operations office (telephone
800–647–5527) is in the ADDRESSES
section.
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 adding
the following new airworthiness
directive (AD):
■
2014–23–14 Bombardier, Inc.: Amendment
39–18030. Docket No. FAA–2014–0191;
Directorate Identifier 2013–NM–256–AD.
(a) Effective Date
This AD becomes effective December 31,
2014.
(b) Affected ADs
None.
mstockstill on DSK4VPTVN1PROD with RULES
(c) Applicability
This AD applies to Bombardier, Inc. Model
DHC–8–400, –401, and –402 airplanes;
certificated in any category; serial numbers
4001, and 4003 through 4417 inclusive, with
installed engine fuel feed ejector pump
having part number (P/N) 2960008–102.
(d) Subject
Air Transport Association (ATA) of
America Code 28, Fuel.
(e) Reason
This AD was prompted by reports of swing
arm assemblies of engine fuel feed ejector
pumps detaching from the outlet port of the
engine fuel feed ejector pump and partially
blocking the engine fuel feed line. We are
VerDate Sep<11>2014
16:25 Nov 25, 2014
Jkt 235001
issuing this AD to prevent blocked engine
fuel flow and possible engine flameout.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Installation
Within 6,000 flight hours or 36 months,
whichever occurs first, after the effective date
of this AD, install a restrictor into the engine
fuel feed line, in accordance with paragraph
3.B., ‘‘Procedure,’’ of the Accomplishment
Instructions of Bombardier Service Bulletin
84–28–16, Revision B, dated June 17, 2013.
(h) Credit for Previous Actions
This paragraph provides credit for actions
required by paragraph (g) of this AD, if those
actions were performed before the effective
date of this AD using Bombardier Service
Bulletin 84–28–16, dated July 16, 2012; or
Bombardier Service Bulletin 84–28–16,
Revision A, dated May 23, 2013; which are
not incorporated by reference in this AD.
(i) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, New York ACO,
ANE–170, 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 ACO, send it to ATTN: Program
Manager, Continuing Operational Safety,
FAA, New York ACO, 1600 Stewart Avenue,
Suite 410, Westbury, NY 11590; telephone
516–228–7300; fax 516–794–5531. 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. The AMOC approval
letter must specifically reference this AD.
(2) Contacting the Manufacturer: For any
requirement in this AD to obtain corrective
actions from a manufacturer, the action must
be accomplished using a method approved
by the Manager, New York ACO, ANE–170,
Engine and Propeller Directorate, FAA; or
TCCA; or Bombardier, Inc.’s TCCA Design
Approval Organization (DAO). If approved by
the DAO, the approval must include the
DAO-authorized signature.
(j) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) Canadian
Airworthiness Directive CF–2013–35, dated
November 15, 2013, for related information.
This MCAI may be found in the AD docket
on the Internet at https://www.regulations.
gov/#!documentDetail;D=FAA-2014-01910002.
(2) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (k)(3) and (k)(4) of this AD.
(k) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
PO 00000
Frm 00015
Fmt 4700
Sfmt 4700
70441
(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 this AD specifies otherwise.
(i) Bombardier Service Bulletin 84–28–16,
Revision B, dated June 17, 2013.
(ii) Reserved.
(3) For service information identified in
this AD, contact Bombardier, Inc., Q-Series
Technical Help Desk, 123 Garratt Boulevard,
Toronto, Ontario M3K 1Y5, Canada;
telephone 416–375–4000; fax 416–375–4539;
email thd.qseries@aero.bombardier.com;
Internet https://www.bombardier.com.
(4) You may view this 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.
(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 Renton, Washington, on
November 6, 2014.
Jeffrey E. Duven
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2014–27357 Filed 11–25–14; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–0170; Directorate
Identifier 2013–NM–169–AD; Amendment
39–18027; AD 2014–23–11]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are superseding
Airworthiness Directive (AD) 2005–13–
05, which applied to certain Boeing
Model 747–400F series airplanes. AD
2005–13–05 required inspections for
cracking of the web, upper chord, and
upper chord strap of the upper deck
floor beams, and repair of any cracking.
AD 2005–13–05 also required a
preventive modification of the upper
deck floor beams, and repetitive
inspections for cracking after
accomplishing the modification. This
new AD retains these actions and
requires a second modification,
repetitive inspections for cracking, and
SUMMARY:
E:\FR\FM\26NOR1.SGM
26NOR1
70442
Federal Register / Vol. 79, No. 228 / Wednesday, November 26, 2014 / Rules and Regulations
repair if necessary. This AD was
prompted by a determination that the
upper chords of the upper deck floor
beams at certain stations are structures
that are susceptible to widespread
fatigue damage, and that certain
airplanes with an initial modification
require a second modification for the
airplane to meet its limit of validity
(LOV). We are issuing this AD to detect
and correct fatigue cracking in certain
upper chords of the upper deck floor
beam, which could result in reduced
structural integrity of the airplane and
rapid decompression or reduced
controllability of the airplane.
DATES: This AD is effective December
31, 2014.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of December 31, 2014.
The Director of the Federal Register
approved the incorporation by reference
of a certain other publication listed in
this AD as of July 27, 2005 (70 FR
35989, June 22, 2005).
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, 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 by searching for
and locating Docket No. FAA–2014–
0170; 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
Docket 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 2005–13–05,
Amendment 39–14141 (70 FR 35989,
June 22, 2005). AD 2005–13–05 applied
to certain Boeing Model 747–400F series
airplanes. The NPRM published in the
Federal Register on March 25, 2014 (79
FR 16241). The NPRM was prompted by
a determination that the upper chords of
the upper deck floor beams at certain
stations are structures that are
susceptible to widespread fatigue
damage, and that certain airplanes with
an initial modification require a second
modification for the airplane to meet its
LOV. The NPRM proposed to continue
to require inspections for cracking of the
web, upper chord, and upper chord
strap of the upper deck floor beams, and
repair of any cracking; a preventive
modification of the upper deck floor
beams; and repetitive inspections for
cracking after accomplishing the
modification. The NPRM proposed to
also require a second modification,
repetitive inspections for cracking, and
repair if necessary. We are issuing this
AD to detect and correct fatigue
cracking in certain upper chords of the
upper deck floor beam, which could
result in reduced structural integrity of
the airplane and rapid decompression or
reduced controllability of the airplane.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comments
received on the NPRM (79 FR 16241,
March 25, 2014) and the FAA’s response
to each comment.
Request To Clarify Post-Modification
Inspection Options
Boeing requested that we revise
paragraphs (j) and (l) of the NPRM (79
FR 16241, March 25, 2014) to clarify
that the inspection options of
paragraphs (j)(2) and (l)(2) are
applicable only when the primary
preventative modification option has
been accomplished. Boeing stated that
Boeing Service Bulletin 747–53A2443,
Revision 2, dated August 2, 2013, added
an alternative preventative modification
option for which the inspection options
of paragraphs (j)(2) and (l)(2) of this AD
are not viable.
We agree with the commenter’s
request because these words add clarity
as to which inspection option should be
used. We have revised paragraphs (j)
and (l) of this AD by stating that, as of
the effective date of this AD, for
airplanes on which the alternative
preventive modification has been
accomplished, only the inspection
methods specified by paragraphs (j)(1)
and (l)(1), respectively, of this AD may
be used.
Conclusion
We reviewed the relevant data,
considered the comment 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 (79 FR
16241, March 25, 2014) for correcting
the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM (79 FR 16241,
March 25, 2014).
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 13
airplanes of U.S. registry.
We estimate the following costs to
comply with this AD:
mstockstill on DSK4VPTVN1PROD with RULES
ESTIMATED COSTS
Cost per
product
Action
Labor cost
Parts cost
Pre-modification inspections (retained actions from
AD 2005–13–05, Amendment 39–14141 (70 FR
35989, June 22, 2005)).
Modification/inspections done during modification
(retained actions from AD 2005–13–05, Amendment 39–14141 (70 FR 35989, June 22, 2005)).
11 work-hours × $85 per hour =
$935.
$0 .....................
$935
Up to 524 work-hours × $85 per
hour = $44,540.
Up to $14,874 ..
59,414
VerDate Sep<11>2014
16:25 Nov 25, 2014
Jkt 235001
PO 00000
Frm 00016
Fmt 4700
Sfmt 4700
E:\FR\FM\26NOR1.SGM
26NOR1
Cost on U.S.
operators
$12,155.
$772,382.
Federal Register / Vol. 79, No. 228 / Wednesday, November 26, 2014 / Rules and Regulations
70443
ESTIMATED COSTS—Continued
Cost per
product
Cost on U.S.
operators
Action
Labor cost
Parts cost
Post-modification inspections (retained actions from
AD 2005–13–05, Amendment 39–14141 (70 FR
35989, June 22, 2005)).
Zero-Timing Procedure Option 1 (including inspections) (new action).
Zero-Timing Procedure Option 2 (including inspections) (new action).
66 work-hours × $85 per hour =
$5,610.
$0 .....................
5,610
$72,930.
71 work-hours × $85 per hour =
$6,035.
103 work-hours × $85 per hour =
$8,755.
$0 .....................
6,035
Up to $78,455.
$0 .....................
8,755
Up to $113,815.
We have received no definitive data
that would enable us to provide cost
estimates for the on-condition actions
specified in this AD.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Authority for This Rulemaking
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
issuing this AD to detect and correct fatigue
cracking in certain upper chords of the upper
deck floor beam, which could result in
reduced structural integrity of the airplane
and rapid decompression or reduced
controllability of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
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.
mstockstill on DSK4VPTVN1PROD with RULES
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.
VerDate Sep<11>2014
16:25 Nov 25, 2014
Jkt 235001
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)
2005–13–05, Amendment 39–14141 (70
FR 35989, June 22, 2005), and adding
the following new AD:
■
2014–23–11 The Boeing Company:
Amendment 39–18027 ; Docket No.
FAA–2014–0170; Directorate Identifier
2013–NM–169–AD.
(a) Effective Date
This AD is effective December 31, 2014.
(b) Affected ADs
This AD replaces AD 2005–13–05,
Amendment 39–14141 (70 FR 35989, June
22, 2005).
(c) Applicability
This AD applies to The Boeing Company
Model 747–400F series airplanes, certificated
in any category, as identified in Boeing
Service Bulletin 747–53A2443, Revision 2,
dated August 2, 2013.
(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by a report
indicating that the upper chords of the upper
deck floor beams at stations (STA) 340
through 520 have been determined to be
structures that are susceptible to widespread
fatigue damage, and airplanes that had an
initial modification done before 15,000 total
flight cycles require a second fastener hole
zero-timing modification for the airplane to
meet its limit of validity (LOV). We are
PO 00000
Frm 00017
Fmt 4700
Sfmt 4700
(g) Retained Inspections With Revised
Service Information
This paragraph restates the requirements of
paragraph (g) of AD 2005–13–05,
Amendment 39–14141 (70 FR 35989, June
22, 2005), with revised service information.
Before the accumulation of 15,000 total flight
cycles, or within 1,000 flight cycles after July
27, 2005 (the effective date of AD 2005–13–
05), whichever is later: Accomplish detailed
and open-hole high frequency eddy current
(HFEC) inspections for cracking of the web,
upper chord, and upper chord strap of the
upper deck floor beams, by doing all the
applicable actions in accordance with Part
3.B.1. of the Accomplishment Instructions of
Boeing Service Bulletin 747–53A2443, dated
May 9, 2002; or Part 1 of the
Accomplishment Instructions of Boeing
Service Bulletin 747–53A2443, Revision 2,
dated August 2, 2013. As of the effective date
of this AD, only Boeing Service Bulletin 747–
53A2443, Revision 2, dated August 2, 2013,
may be used.
(h) Retained Repair With Revised Service
Information and Revised Repair Approval
Language
This paragraph restates the requirements of
paragraph (h) of AD 2005–13–05,
Amendment 39–14141 (70 FR 35989, June
22, 2005), with revised service information
and revised repair approval language. If any
crack is found during any inspection
required by paragraph (g) of this AD: Before
further flight, accomplish the actions
required by paragraph (h)(1) and (h)(2) of this
AD.
(1) Repair in accordance with the
Accomplishment Instructions of Boeing
Service Bulletin 747–53A2443, dated May 9,
2002; or the Accomplishment Instructions of
Boeing Service Bulletin 747–53A2443,
Revision 2, dated August 2, 2013; except
where these service bulletins specify to
contact Boeing for appropriate action, before
further flight, repair the cracking using a
method approved in accordance with the
procedures specified in paragraph (o) of this
AD. As of the effective date of this AD, only
E:\FR\FM\26NOR1.SGM
26NOR1
70444
Federal Register / Vol. 79, No. 228 / Wednesday, November 26, 2014 / Rules and Regulations
mstockstill on DSK4VPTVN1PROD with RULES
Boeing Service Bulletin 747–53A2443,
Revision 2, dated August 2, 2013, may be
used.
(2) Accomplish the inspections and
preventive modification of the floor beams by
doing all the actions in accordance with Part
3.B.2. or Part 3.B.3., as applicable, of the
Accomplishment Instructions of Boeing
Service Bulletin 747–53A2443, dated May 9,
2002; or Part 2 or Part 3, as applicable, of the
Accomplishment Instructions of Boeing
Service Bulletin 747–53A2443, Revision 2,
dated August 2, 2013. If any crack is found
during any inspection, before further flight,
repair as required by paragraph (h)(1) of this
AD. As of the effective date of this AD, only
Boeing Service Bulletin 747–53A2443,
Revision 2, dated August 2, 2013, may be
used.
(i) Retained Modification With Revised
Service Information
This paragraph restates the requirements of
paragraph (i) of AD 2005–13–05, Amendment
39–14141 (70 FR 35989, June 22, 2005), with
revised service information. If no crack is
found during any inspection required by
paragraph (g) of this AD: Accomplish the
actions required by either paragraph (i)(1) or
(i)(2) of this AD, at the time specified.
(1) Before further flight: Accomplish the
inspections and preventive modification of
the floor beam by doing all the actions in
accordance with Part 3.B.2 or Part 3.B.3., as
applicable, of the Accomplishment
Instructions of Boeing Service Bulletin 747–
53A2443, dated May 9, 2002; or Part 2 or Part
3, as applicable, of the Accomplishment
Instructions of Boeing Service Bulletin 747–
53A2443, Revision 2, dated August 2, 2013.
If the preventive modification is performed
concurrently with the inspections required
by paragraph (g) of this AD, the upper chord
straps must be removed when performing the
open-hole HFEC inspection. If any crack is
found during any inspection, before further
flight, repair as required by paragraph (h)(1)
of this AD. As of the effective date of this AD,
only Boeing Service Bulletin 747–53A2443,
Revision 2, dated August 2, 2013, may be
used.
(2) Before the accumulation of 20,000 total
flight cycles, or within 1,000 flight cycles
after July 27, 2005 (the effective date of AD
2005–13–05, Amendment 39–14141 (70 FR
35989, June 22, 2005), whichever is later:
Accomplish the inspections and preventive
modification of the upper deck floor beams,
by doing all the actions in accordance with
Part 3.B.2. or 3.B.3. as applicable, of the
Accomplishment Instructions of Boeing
Service Bulletin 747–53A2443, dated May 9,
2002; or Part 2 or Part 3, as applicable, of the
Accomplishment Instructions of Boeing
Service Bulletin 747–53A2443, Revision 2,
dated August 2, 2013. If any crack is found
during any inspection, before further flight,
repair as required by paragraph (h)(1) of this
AD. As of the effective date of this AD, only
Boeing Service Bulletin 747–53A2443,
Revision 2, dated August 2, 2013, may be
used.
(j) Retained Post-Modification Inspections
With Revised Service Information
This paragraph restates the requirements of
paragraph (j) of AD 2005–13–05, Amendment
VerDate Sep<11>2014
16:25 Nov 25, 2014
Jkt 235001
39–14141 (70 FR 35989, June 22, 2005), with
revised service information. Within 15,000
flight cycles after accomplishing the
applicable preventive modification required
by paragraph (h)(2), (i)(1), or (i)(2) of this AD:
Accomplish the applicable inspections
required by either paragraph (j)(1) or (j)(2) of
this AD; if any crack is found during any
inspection, before further flight, repair as
required by paragraph (h)(1) of this AD. As
of the effective date of this AD, for airplanes
on which the alternative preventive
modification, as identified in the NOTE after
step 3. of ‘‘PART 2—INSPECTION AND
PREVENTIVE MODIFICATION,’’ or as
identified in the NOTE after step 4. of ‘‘PART
3—INSPECTION AND PREVENTIVE
MODIFICATION,’’ of the Accomplishment
Instructions of Boeing Service Bulletin 747–
53A2443, Revision 2, dated August 2, 2013,
has been done, only the inspection specified
by paragraph (j)(1) of this AD may be used.
(1) Accomplish detailed and surface HFEC
inspections for cracking of the web, upper
chord, and upper chord strap of the upper
deck floor beams, by doing all the applicable
actions in accordance with Part 3.B.4. of the
Accomplishment Instructions of Boeing
Service Bulletin 747–53A2443, dated May 9,
2002; or Part 4 of the Accomplishment
Instructions of Boeing Service Bulletin 747–
53A2443, Revision 2, dated August 2, 2013.
If no crack is found, repeat the inspections
at intervals not to exceed 1,000 flight cycles.
As of the effective date of this AD, only
Boeing Service Bulletin 747–53A2443,
Revision 2, dated August 2, 2013, may be
used.
(2) Accomplish detailed and open-hole
HFEC inspections for cracking of the web,
upper chord, and strap of the upper deck
floor beams, by doing all the applicable
actions in accordance with Part 3.B.5. of the
Accomplishment Instructions of Boeing
Service Bulletin 747–53A2443, dated May 9,
2002; or Part 5 of the Accomplishment
Instructions of Boeing Service Bulletin 747–
53A2443, Revision 2, dated August 2, 2013.
If no crack is found, repeat the inspections
at intervals not to exceed 5,000 flight cycles.
As of the effective date of this AD, only
Boeing Service Bulletin 747–53A2443,
Revision 2, dated August 2, 2013, may be
used.
(k) New Floor Beam Hole Zero-Timing
Within 20,000 flight cycles after
accomplishing the preventive modification of
the Station 340 to Station 520 upper deck
floor beams specified in paragraph (h)(2),
(i)(1), or (i)(2) of this AD, or within 1,000
flight cycles after the effective date of this
AD, whichever occurs later: Accomplish the
floor beam hole zero-timing, in accordance
with Part 6 of the Accomplishment
Instructions of Boeing Service Bulletin 747–
53A2443, Revision 2, dated August 2, 2013.
(l) New Post-Modification Floor Beam Hole
Zero-Timing Inspections
Within 15,000 flight cycles after
accomplishing the floor beam hole zerotiming required by paragraph (k) of this AD:
Accomplish the applicable inspections
required by paragraph (l)(1) or (l)(2) of this
AD; if any cracking is found during any
PO 00000
Frm 00018
Fmt 4700
Sfmt 4700
inspection, before further flight, repair as
required by paragraph (h)(1) of this AD. As
of the effective date of this AD, for airplanes
on which the alternative preventive
modification, as identified in the NOTE after
step 3. of ‘‘PART 2—INSPECTION AND
PREVENTIVE MODIFICATION,’’ or as
identified in the NOTE after step 4. of ‘‘PART
3—INSPECTION AND PREVENTIVE
MODIFICATION,’’ of the Accomplishment
Instructions of Boeing Service Bulletin 747–
53A2443, Revision 2, dated August 2, 2013,
has been done, only the inspection method
specified by paragraph (l)(1) of this AD may
be used.
(1) Accomplish detailed and surface HFEC
inspections for cracking of the web, upper
chord, and straps of the Station 340 to
Station 520 upper deck floor beams, by doing
all the applicable actions, in accordance with
Part 4 of the Accomplishment Instructions of
Boeing Service Bulletin 747–53A2443,
Revision 2, dated August 2, 2013. If no
cracking is found, repeat the inspections at
intervals not to exceed 1,000 flight cycles.
(2) Accomplish detailed and open-hole
HFEC inspections for cracking of the web,
upper chord, and straps of the Station 340 to
Station 520 upper deck floor beams, by doing
all the applicable actions, in accordance with
Part 5 of the Accomplishment Instructions of
Boeing Service Bulletin 747–53A2443,
Revision 2, dated August 2, 2013. If no
cracking is found, repeat the inspections at
intervals not to exceed 5,000 flight cycles.
(m) Exception to Service Information
Where Boeing Service Bulletin 747–
53A2443, Revision 2, dated August 2, 2013,
specifies a compliance time ‘‘after the
revision date on this service bulletin,’’ this
AD requires compliance within the specified
compliance time after the effective date of
this AD.
(n) Credit for Previous Actions
This paragraph provides credit for the
inspections, repairs, and modification
required by paragraphs (g) through (j) of this
AD, if the corresponding actions were
performed before the effective date of this AD
using Boeing Service Bulletin 747–53A2443,
Revision 1, dated June 25, 2009.
(o) 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 (p)(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
E:\FR\FM\26NOR1.SGM
26NOR1
Federal Register / Vol. 79, No. 228 / Wednesday, November 26, 2014 / Rules and Regulations
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.
(4) AMOCs approved for AD 2005–13–05,
Amendment 39–14141 (70 FR 35989, June
22, 2005), are approved as AMOCs for the
corresponding requirements of paragraphs (g)
through (j) (the retained actions) of this AD.
(p) Related Information
(1) 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.
(2) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (q)(5) and (q)(6) of this AD.
mstockstill on DSK4VPTVN1PROD with RULES
(q) 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 31, 2014.
(i) Boeing Service Bulletin 747–53A2443,
Revision 2, dated August 2, 2013.
(ii) Reserved.
(4) The following service information was
approved for IBR on July 27, 2005 (70 FR
35989, June 22, 2005).
(i) Boeing Service Bulletin 747–53A2443,
dated May 9, 2002.
(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 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.
(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
November 6, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2014–27358 Filed 11–25–14; 8:45 am]
BILLING CODE 4910–13–P
VerDate Sep<11>2014
16:25 Nov 25, 2014
Jkt 235001
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–0174; Directorate
Identifier 2013–NM–212–AD; Amendment
39–18028; AD 2014–23–12]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
The Boeing Company Model 787–8
airplanes. This AD was prompted by a
report indicating that, on a different
Boeing airplane model, there was an
oxygen-fed fire, which caused extensive
damage to the flight deck. This AD
requires replacing the low-pressure
oxygen hoses with non-conductive
hoses in the crew oxygen system. We
are issuing this AD to prevent
inadvertent electrical current from
passing through an internal, anticollapse spring of the low pressure
oxygen hose, which can cause the lowpressure oxygen hose to melt or burn,
leading to an oxygen-fed fire and/or
smoke beneath the flight deck in the
forward electronics equipment bay.
DATES: This AD is effective December
31, 2014.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of December 31, 2014.
ADDRESSES: 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. For B/E
Aerospace service information
identified in this AD, contact B/E
Aerospace, Inc., Commercial Aircraft
Products Group, 10800 Pfluum Road,
Lenexa, KS 66215; phone: 913–338–
9800; fax: 913–469–8419. You may view
this 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.
SUMMARY:
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
PO 00000
Frm 00019
Fmt 4700
Sfmt 4700
70445
and locating Docket No. FAA–2014–
0174; 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
Docket 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:
Susan Monroe, Aerospace Engineer,
Cabin Safety and Environmental
Systems Branch, ANM–150S, Seattle
Aircraft Certification Office, FAA, 1601
Lind Avenue SW., Renton, WA 98057–
3356; phone: 425–917–6457; fax: 425–
917–6590; email: susan.l.monroe@
faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to certain The Boeing Company
Model 787–8 airplanes. The NPRM
published in the Federal Register on
March 28, 2014 (79 FR 17457). The
NPRM was prompted by a report
indicating that, on a different Boeing
airplane model, there was an oxygen-fed
fire, which caused extensive damage to
the flight deck. The NPRM proposed to
require replacing the low-pressure
oxygen hoses with non-conductive
hoses in the crew oxygen system. We
are issuing this AD to prevent
inadvertent electrical current from
passing through an internal, anticollapse spring of the low pressure
oxygen hose, which can cause the lowpressure oxygen hose to melt or burn,
leading to an oxygen-fed fire and/or
smoke beneath the flight deck in the
forward electronics equipment bay.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comments
received on the NPRM (79 FR 17457,
March 28, 2014) and the FAA’s response
to each comment.
Boeing, United Airlines, and John
Johnson stated that they support the
NPRM (79 FR 17457, March 28, 2014).
Request To Shorten Compliance Time
The Air Line Pilots Association
(ALPA) stated that it supports the intent
of the NPRM (79 FR 17457, March 28,
2014) but that the 60-month compliance
E:\FR\FM\26NOR1.SGM
26NOR1
]]>Agencies
[Federal Register Volume 79, Number 228 (Wednesday, November 26, 2014)]
[Rules and Regulations]
[Pages 70441-70445]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-27358]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2014-0170; Directorate Identifier 2013-NM-169-AD;
Amendment 39-18027; AD 2014-23-11]
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) 2005-13-05,
which applied to certain Boeing Model 747-400F series airplanes. AD
2005-13-05 required inspections for cracking of the web, upper chord,
and upper chord strap of the upper deck floor beams, and repair of any
cracking. AD 2005-13-05 also required a preventive modification of the
upper deck floor beams, and repetitive inspections for cracking after
accomplishing the modification. This new AD retains these actions and
requires a second modification, repetitive inspections for cracking,
and
[[Page 70442]]
repair if necessary. This AD was prompted by a determination that the
upper chords of the upper deck floor beams at certain stations are
structures that are susceptible to widespread fatigue damage, and that
certain airplanes with an initial modification require a second
modification for the airplane to meet its limit of validity (LOV). We
are issuing this AD to detect and correct fatigue cracking in certain
upper chords of the upper deck floor beam, which could result in
reduced structural integrity of the airplane and rapid decompression or
reduced controllability of the airplane.
DATES: This AD is effective December 31, 2014.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of December 31,
2014.
The Director of the Federal Register approved the incorporation by
reference of a certain other publication listed in this AD as of July
27, 2005 (70 FR 35989, June 22, 2005).
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, 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 by searching for and locating Docket No. FAA-2014-
0170; 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 Docket 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 2005-13-05, Amendment 39-14141 (70 FR 35989,
June 22, 2005). AD 2005-13-05 applied to certain Boeing Model 747-400F
series airplanes. The NPRM published in the Federal Register on March
25, 2014 (79 FR 16241). The NPRM was prompted by a determination that
the upper chords of the upper deck floor beams at certain stations are
structures that are susceptible to widespread fatigue damage, and that
certain airplanes with an initial modification require a second
modification for the airplane to meet its LOV. The NPRM proposed to
continue to require inspections for cracking of the web, upper chord,
and upper chord strap of the upper deck floor beams, and repair of any
cracking; a preventive modification of the upper deck floor beams; and
repetitive inspections for cracking after accomplishing the
modification. The NPRM proposed to also require a second modification,
repetitive inspections for cracking, and repair if necessary. We are
issuing this AD to detect and correct fatigue cracking in certain upper
chords of the upper deck floor beam, which could result in reduced
structural integrity of the airplane and rapid decompression or reduced
controllability of the airplane.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the NPRM (79
FR 16241, March 25, 2014) and the FAA's response to each comment.
Request To Clarify Post-Modification Inspection Options
Boeing requested that we revise paragraphs (j) and (l) of the NPRM
(79 FR 16241, March 25, 2014) to clarify that the inspection options of
paragraphs (j)(2) and (l)(2) are applicable only when the primary
preventative modification option has been accomplished. Boeing stated
that Boeing Service Bulletin 747-53A2443, Revision 2, dated August 2,
2013, added an alternative preventative modification option for which
the inspection options of paragraphs (j)(2) and (l)(2) of this AD are
not viable.
We agree with the commenter's request because these words add
clarity as to which inspection option should be used. We have revised
paragraphs (j) and (l) of this AD by stating that, as of the effective
date of this AD, for airplanes on which the alternative preventive
modification has been accomplished, only the inspection methods
specified by paragraphs (j)(1) and (l)(1), respectively, of this AD may
be used.
Conclusion
We reviewed the relevant data, considered the comment 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 (79 FR 16241, March 25, 2014) for correcting the unsafe condition;
and
Do not add any additional burden upon the public than was
already proposed in the NPRM (79 FR 16241, March 25, 2014).
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 13 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
Pre-modification inspections 11 work-hours x $0.................... $935 $12,155.
(retained actions from AD $85 per hour =
2005-13-05, Amendment 39- $935.
14141 (70 FR 35989, June 22,
2005)).
Modification/inspections done Up to 524 work- Up to $14,874......... 59,414 $772,382.
during modification (retained hours x $85 per
actions from AD 2005-13-05, hour = $44,540.
Amendment 39-14141 (70 FR
35989, June 22, 2005)).
[[Page 70443]]
Post-modification inspections 66 work-hours x $0.................... 5,610 $72,930.
(retained actions from AD $85 per hour =
2005-13-05, Amendment 39- $5,610.
14141 (70 FR 35989, June 22,
2005)).
Zero-Timing Procedure Option 1 71 work-hours x $0.................... 6,035 Up to $78,455.
(including inspections) (new $85 per hour =
action). $6,035.
Zero-Timing Procedure Option 2 103 work-hours x $0.................... 8,755 Up to $113,815.
(including inspections) (new $85 per hour =
action). $8,755.
----------------------------------------------------------------------------------------------------------------
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)
2005-13-05, Amendment 39-14141 (70 FR 35989, June 22, 2005), and adding
the following new AD:
2014-23-11 The Boeing Company: Amendment 39-18027 ; Docket No. FAA-
2014-0170; Directorate Identifier 2013-NM-169-AD.
(a) Effective Date
This AD is effective December 31, 2014.
(b) Affected ADs
This AD replaces AD 2005-13-05, Amendment 39-14141 (70 FR 35989,
June 22, 2005).
(c) Applicability
This AD applies to The Boeing Company Model 747-400F series
airplanes, certificated in any category, as identified in Boeing
Service Bulletin 747-53A2443, Revision 2, dated August 2, 2013.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by a report indicating that the upper
chords of the upper deck floor beams at stations (STA) 340 through
520 have been determined to be structures that are susceptible to
widespread fatigue damage, and airplanes that had an initial
modification done before 15,000 total flight cycles require a second
fastener hole zero-timing modification for the airplane to meet its
limit of validity (LOV). We are issuing this AD to detect and
correct fatigue cracking in certain upper chords of the upper deck
floor beam, which could result in reduced structural integrity of
the airplane and 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 With Revised Service Information
This paragraph restates the requirements of paragraph (g) of AD
2005-13-05, Amendment 39-14141 (70 FR 35989, June 22, 2005), with
revised service information. Before the accumulation of 15,000 total
flight cycles, or within 1,000 flight cycles after July 27, 2005
(the effective date of AD 2005-13-05), whichever is later:
Accomplish detailed and open-hole high frequency eddy current (HFEC)
inspections for cracking of the web, upper chord, and upper chord
strap of the upper deck floor beams, by doing all the applicable
actions in accordance with Part 3.B.1. of the Accomplishment
Instructions of Boeing Service Bulletin 747-53A2443, dated May 9,
2002; or Part 1 of the Accomplishment Instructions of Boeing Service
Bulletin 747-53A2443, Revision 2, dated August 2, 2013. As of the
effective date of this AD, only Boeing Service Bulletin 747-53A2443,
Revision 2, dated August 2, 2013, may be used.
(h) Retained Repair With Revised Service Information and Revised Repair
Approval Language
This paragraph restates the requirements of paragraph (h) of AD
2005-13-05, Amendment 39-14141 (70 FR 35989, June 22, 2005), with
revised service information and revised repair approval language. If
any crack is found during any inspection required by paragraph (g)
of this AD: Before further flight, accomplish the actions required
by paragraph (h)(1) and (h)(2) of this AD.
(1) Repair in accordance with the Accomplishment Instructions of
Boeing Service Bulletin 747-53A2443, dated May 9, 2002; or the
Accomplishment Instructions of Boeing Service Bulletin 747-53A2443,
Revision 2, dated August 2, 2013; except where these service
bulletins specify to contact Boeing for appropriate action, before
further flight, repair the cracking using a method approved in
accordance with the procedures specified in paragraph (o) of this
AD. As of the effective date of this AD, only
[[Page 70444]]
Boeing Service Bulletin 747-53A2443, Revision 2, dated August 2,
2013, may be used.
(2) Accomplish the inspections and preventive modification of
the floor beams by doing all the actions in accordance with Part
3.B.2. or Part 3.B.3., as applicable, of the Accomplishment
Instructions of Boeing Service Bulletin 747-53A2443, dated May 9,
2002; or Part 2 or Part 3, as applicable, of the Accomplishment
Instructions of Boeing Service Bulletin 747-53A2443, Revision 2,
dated August 2, 2013. If any crack is found during any inspection,
before further flight, repair as required by paragraph (h)(1) of
this AD. As of the effective date of this AD, only Boeing Service
Bulletin 747-53A2443, Revision 2, dated August 2, 2013, may be used.
(i) Retained Modification With Revised Service Information
This paragraph restates the requirements of paragraph (i) of AD
2005-13-05, Amendment 39-14141 (70 FR 35989, June 22, 2005), with
revised service information. If no crack is found during any
inspection required by paragraph (g) of this AD: Accomplish the
actions required by either paragraph (i)(1) or (i)(2) of this AD, at
the time specified.
(1) Before further flight: Accomplish the inspections and
preventive modification of the floor beam by doing all the actions
in accordance with Part 3.B.2 or Part 3.B.3., as applicable, of the
Accomplishment Instructions of Boeing Service Bulletin 747-53A2443,
dated May 9, 2002; or Part 2 or Part 3, as applicable, of the
Accomplishment Instructions of Boeing Service Bulletin 747-53A2443,
Revision 2, dated August 2, 2013. If the preventive modification is
performed concurrently with the inspections required by paragraph
(g) of this AD, the upper chord straps must be removed when
performing the open-hole HFEC inspection. If any crack is found
during any inspection, before further flight, repair as required by
paragraph (h)(1) of this AD. As of the effective date of this AD,
only Boeing Service Bulletin 747-53A2443, Revision 2, dated August
2, 2013, may be used.
(2) Before the accumulation of 20,000 total flight cycles, or
within 1,000 flight cycles after July 27, 2005 (the effective date
of AD 2005-13-05, Amendment 39-14141 (70 FR 35989, June 22, 2005),
whichever is later: Accomplish the inspections and preventive
modification of the upper deck floor beams, by doing all the actions
in accordance with Part 3.B.2. or 3.B.3. as applicable, of the
Accomplishment Instructions of Boeing Service Bulletin 747-53A2443,
dated May 9, 2002; or Part 2 or Part 3, as applicable, of the
Accomplishment Instructions of Boeing Service Bulletin 747-53A2443,
Revision 2, dated August 2, 2013. If any crack is found during any
inspection, before further flight, repair as required by paragraph
(h)(1) of this AD. As of the effective date of this AD, only Boeing
Service Bulletin 747-53A2443, Revision 2, dated August 2, 2013, may
be used.
(j) Retained Post-Modification Inspections With Revised Service
Information
This paragraph restates the requirements of paragraph (j) of AD
2005-13-05, Amendment 39-14141 (70 FR 35989, June 22, 2005), with
revised service information. Within 15,000 flight cycles after
accomplishing the applicable preventive modification required by
paragraph (h)(2), (i)(1), or (i)(2) of this AD: Accomplish the
applicable inspections required by either paragraph (j)(1) or (j)(2)
of this AD; if any crack is found during any inspection, before
further flight, repair as required by paragraph (h)(1) of this AD.
As of the effective date of this AD, for airplanes on which the
alternative preventive modification, as identified in the NOTE after
step 3. of ``PART 2--INSPECTION AND PREVENTIVE MODIFICATION,'' or as
identified in the NOTE after step 4. of ``PART 3--INSPECTION AND
PREVENTIVE MODIFICATION,'' of the Accomplishment Instructions of
Boeing Service Bulletin 747-53A2443, Revision 2, dated August 2,
2013, has been done, only the inspection specified by paragraph
(j)(1) of this AD may be used.
(1) Accomplish detailed and surface HFEC inspections for
cracking of the web, upper chord, and upper chord strap of the upper
deck floor beams, by doing all the applicable actions in accordance
with Part 3.B.4. of the Accomplishment Instructions of Boeing
Service Bulletin 747-53A2443, dated May 9, 2002; or Part 4 of the
Accomplishment Instructions of Boeing Service Bulletin 747-53A2443,
Revision 2, dated August 2, 2013. If no crack is found, repeat the
inspections at intervals not to exceed 1,000 flight cycles. As of
the effective date of this AD, only Boeing Service Bulletin 747-
53A2443, Revision 2, dated August 2, 2013, may be used.
(2) Accomplish detailed and open-hole HFEC inspections for
cracking of the web, upper chord, and strap of the upper deck floor
beams, by doing all the applicable actions in accordance with Part
3.B.5. of the Accomplishment Instructions of Boeing Service Bulletin
747-53A2443, dated May 9, 2002; or Part 5 of the Accomplishment
Instructions of Boeing Service Bulletin 747-53A2443, Revision 2,
dated August 2, 2013. If no crack is found, repeat the inspections
at intervals not to exceed 5,000 flight cycles. As of the effective
date of this AD, only Boeing Service Bulletin 747-53A2443, Revision
2, dated August 2, 2013, may be used.
(k) New Floor Beam Hole Zero-Timing
Within 20,000 flight cycles after accomplishing the preventive
modification of the Station 340 to Station 520 upper deck floor
beams specified in paragraph (h)(2), (i)(1), or (i)(2) of this AD,
or within 1,000 flight cycles after the effective date of this AD,
whichever occurs later: Accomplish the floor beam hole zero-timing,
in accordance with Part 6 of the Accomplishment Instructions of
Boeing Service Bulletin 747-53A2443, Revision 2, dated August 2,
2013.
(l) New Post-Modification Floor Beam Hole Zero-Timing Inspections
Within 15,000 flight cycles after accomplishing the floor beam
hole zero-timing required by paragraph (k) of this AD: Accomplish
the applicable inspections required by paragraph (l)(1) or (l)(2) of
this AD; if any cracking is found during any inspection, before
further flight, repair as required by paragraph (h)(1) of this AD.
As of the effective date of this AD, for airplanes on which the
alternative preventive modification, as identified in the NOTE after
step 3. of ``PART 2--INSPECTION AND PREVENTIVE MODIFICATION,'' or as
identified in the NOTE after step 4. of ``PART 3--INSPECTION AND
PREVENTIVE MODIFICATION,'' of the Accomplishment Instructions of
Boeing Service Bulletin 747-53A2443, Revision 2, dated August 2,
2013, has been done, only the inspection method specified by
paragraph (l)(1) of this AD may be used.
(1) Accomplish detailed and surface HFEC inspections for
cracking of the web, upper chord, and straps of the Station 340 to
Station 520 upper deck floor beams, by doing all the applicable
actions, in accordance with Part 4 of the Accomplishment
Instructions of Boeing Service Bulletin 747-53A2443, Revision 2,
dated August 2, 2013. If no cracking is found, repeat the
inspections at intervals not to exceed 1,000 flight cycles.
(2) Accomplish detailed and open-hole HFEC inspections for
cracking of the web, upper chord, and straps of the Station 340 to
Station 520 upper deck floor beams, by doing all the applicable
actions, in accordance with Part 5 of the Accomplishment
Instructions of Boeing Service Bulletin 747-53A2443, Revision 2,
dated August 2, 2013. If no cracking is found, repeat the
inspections at intervals not to exceed 5,000 flight cycles.
(m) Exception to Service Information
Where Boeing Service Bulletin 747-53A2443, Revision 2, dated
August 2, 2013, specifies a compliance time ``after the revision
date on this service bulletin,'' this AD requires compliance within
the specified compliance time after the effective date of this AD.
(n) Credit for Previous Actions
This paragraph provides credit for the inspections, repairs, and
modification required by paragraphs (g) through (j) of this AD, if
the corresponding actions were performed before the effective date
of this AD using Boeing Service Bulletin 747-53A2443, Revision 1,
dated June 25, 2009.
(o) 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 (p)(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
[[Page 70445]]
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.
(4) AMOCs approved for AD 2005-13-05, Amendment 39-14141 (70 FR
35989, June 22, 2005), are approved as AMOCs for the corresponding
requirements of paragraphs (g) through (j) (the retained actions) of
this AD.
(p) Related Information
(1) 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.
(2) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (q)(5) and (q)(6) of this AD.
(q) 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 31, 2014.
(i) Boeing Service Bulletin 747-53A2443, Revision 2, dated
August 2, 2013.
(ii) Reserved.
(4) The following service information was approved for IBR on
July 27, 2005 (70 FR 35989, June 22, 2005).
(i) Boeing Service Bulletin 747-53A2443, dated May 9, 2002.
(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 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.
(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 November 6, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2014-27358 Filed 11-25-14; 8:45 am]
BILLING CODE 4910-13-P
