Airworthiness Directives; The Boeing Company Airplanes, 54387-54391 [2013-21397]
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Federal Register / Vol. 78, No. 171 / Wednesday, September 4, 2013 / Rules and Regulations
(2) During the inspection required in
paragraph (f)(1) of this AD, if excessive
deposits (oil or carbon) are found on the
spark plugs, before further flight, replace the
affected cylinder head assembly with a
serviceable one. Do the replacement
following Section 3 of Rotax Aircraft Engines
BRP Alert Service Bulletin ASB–912–062R2
and ASB–914–044R2 (co-published as one
document), Revision 2, dated May 29, 2013.
(3) As of September 24, 2013 (the effective
date of this AD), only install an engine
affected by this AD provided it has been
inspected as specified in paragraph (f)(1) of
this AD and corrected as specified in
paragraph (f)(2) of this AD.
(4) As September 24, 2013 (the effective
date of this AD), any spare cylinder head
assembly P/N 623682 installed must be
inspected within 5 hour TIS after installation
following Section 3 of Rotax Aircraft Engines
BRP Alert Service Bulletin ASB–912–062R2
and ASB–914–044R2 (co-published as one
document), Revision 2, dated May 29, 2013,
and corrected as necessary.
(g) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, Standards Office,
FAA, has the authority to approve AMOCs
for this AD, if requested using the procedures
found in 14 CFR 39.19. Send information to
ATTN: Sarjapur Nagarajan, Aerospace
Engineer, FAA, Small Airplane Directorate,
901 Locust, Room 301, Kansas City, Missouri
64106; telephone: (816) 329–4145; fax: (816)
329–4090; email: sarjapur.nagarajan@
faa.gov. Before using any approved AMOC on
any airplane to which the AMOC applies,
notify your appropriate principal inspector
(PI) in the FAA Flight Standards District
Office (FSDO), or lacking a PI, your local
FSDO.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
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(h) Related Information
Refer to MCAI European Aviation Safety
Agency (EASA) AD No. 2013–0117–E, dated
May 30, 2013, for related information, which
can be found in the AD docket on the
Internet at https://www.regulations.gov.
(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) Rotax Aircraft Engines BRP Alert
Service Bulletin ASB–912–062R2, Revision
2, dated May 29, 2013.
(ii) Rotax Aircraft Engines BRP Alert
Service Bulletin ASB–914–044R2, Revision
2, dated May 29, 2013.
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Note 1 to paragraph (i)(2): Rotax Aircraft
Engines BRP Alert Service Bulletins ASB–
912–062R2, Revision 2, dated May 29, 2013;
and ASB–914–044R2, Revision 2, dated May
29, 2013, are co-published as one document.
(3) For Rotax Aircraft Engines service
information identified in this AD, contact
BRP-Powertrain GmbH & Co. KG, Welser
Strasse 32, A–4623 Gunskirchen, Austria;
phone: +43 7246 601 0; fax: +43 7246 601
9130; Internet: https://www.rotax-aircraftengines.com.
(4) You may review copies of the
referenced service information at the FAA,
Small Airplane Directorate, 901 Locust,
Kansas City, Missouri 64106. For information
on the availability of this material at the
FAA, call (816) 329–4148.
(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 Kansas City, Missouri on August
14, 2013.
John Colomy,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2013–21329 Filed 9–3–13; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–0364; Directorate
Identifier 2011–NM–114–AD; Amendment
39–17562; AD 2013–16–24]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are superseding
airworthiness directive (AD) 90–23–14
for certain The Boeing Company Model
747 series airplanes. AD 90–23–14
required inspections of the fuselage skin
lap splice between body station (BS) 340
and BS 400 at stringers (S)–6L and S–
6R, and repair if necessary. This new
AD adds new repetitive inspections for
cracking in the S–6 skin lap splice,
which terminates the inspections
required by AD 90–23–14; eventual
modification of the lap splice, which
terminates the repetitive inspections;
post-modification inspections; and
corrective actions if necessary. This AD
also adds airplanes to the applicability.
This AD was prompted by a report of
cracks up to 18.5 inches that were found
SUMMARY:
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54387
at S–6L and S–6R on several airplanes,
and subsequent analysis results that
indicated that the protruding head
fastener modification and related postmodification inspections required by
AD 90–23–14 are not adequate to
prevent cracking at the upper row of
fasteners in the S–6 lap joint before the
cracks reach a critical length. We are
issuing this AD to detect and correct
cracking at the upper row of fasteners in
the S–6 lap joint, which could result in
a sudden loss of cabin pressurization
and the inability of the fuselage to
withstand failsafe loads.
DATES: This AD is effective October 9,
2013.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of October 9, 2013.
ADDRESSES: For service information
identified in this AD, contact Boeing
Commercial Airplanes, Attention: Data
& Services Management, P.O. Box 3707,
MC 2H–65, Seattle, WA 98124–2207;
telephone 206–544–5000, extension 1;
fax 206–766–5680; Internet https://
www.myboeingfleet.com. You may
review copies of the 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 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
Aircraft Certification Office, 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 90–23–14,
Amendment 39–6801 (Docket No. 90–
NM–110–AD; 55 FR 46652, November 6,
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1990), (‘‘AD 90–23–14’’). AD 90–23–14
applied to the specified products. The
NPRM published in the Federal
Register on May 3, 2013 (78 FR 25898).
The NPRM proposed to continue to
require inspections of the fuselage skin
lap splice between BS 340 and BS 400
at S–6L and S–6R, and repair if
necessary. The NPRM also proposed to
add new repetitive inspections for
cracking in the stringer 6 skin lap splice,
which would terminate the inspections
required by AD 90–23–14; eventual
modification of the lap splice, which
would terminate the new repetitive
inspections; post-modification
inspections; and corrective actions if
necessary. The NPRM also proposed to
add airplanes to the applicability.
Comments
We gave the public the opportunity to
participate in developing this AD. We
received no comments on the NPRM (78
FR 25898, May 3, 2013) or on the
determination of the cost to the public.
Clarification
We have revised the wording of
paragraphs (i) and (j) of this AD to
clarify that certain compliance time
adjustment factors were allowed in AD
90–23–14 (Docket No. 90–NM–110–AD;
55 FR 46652, November 6, 1990), but are
no longer allowed in this new AD.
Conclusion
We reviewed the relevant data and
determined that air safety and the
public interest require adopting this AD
with the changes described previously—
and minor editorial changes. We have
determined that these minor changes:
• Are consistent with the intent that
was proposed in the NPRM (78 FR
25898, May 3, 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 25898,
May 3, 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 76
airplanes of U.S. registry.
We estimate the following costs to
comply with this AD:
ESTIMATED COSTS
Action
Labor cost
Retained inspections from AD 90–
23–14 (Docket No. 90–NM–110–
AD; 55 FR 46652, November 6,
1990).
New pre-modification inspections .....
8 work-hours × $85 per hour =
$680 per inspection cycle.
$0
8 work-hours × $85 per hour =
$680 per inspection cycle.
204 work-hours × $85 per hour =
$17,340.
12 work-hours × $85 per hour =
$1,020 per inspection cycle.
0
New modification ..............................
New post-modification inspections ...
We have received no definitive data
that would enable us to provide cost
estimates for the on-condition actions
specified in this AD.
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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.
15:42 Sep 03, 2013
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Cost per product
0
0
Cost on U.S. operators
$680 per inspection
cycle.
$51,680 per inspection
cycle.
680 per inspection
cycle.
17,340 ..........................
$51,680 per inspection
cycle.
$1,317,840.
1,020 per inspection
cycle.
$77,520.
Regulatory Findings
Authority for This Rulemaking
VerDate Mar<15>2010
Parts cost
Adoption of the Amendment
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.
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
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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)
90–23–14, Amendment 39–6801 (Docket
No. 90–NM–110–AD; 55 FR 46652,
November 6, 1990), and adding the
following new AD:
■
2013–16–24 The Boeing Company:
Amendment 39–17562; Docket No.
FAA–2013–0364; Directorate Identifier
2011–NM–114–AD.
(a) Effective Date
This AD is effective October 9, 2013.
(b) Affected ADs
This AD supersedes AD 90–23–14,
Amendment 39–6801 (55 FR 46652,
November 6, 1990).
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(c) Applicability
This AD applies to The Boeing Company
Model 747–100, 747–100B, 747–200B, 747–
200C, 747–200F, 747–300, 747SR, and 747SP
series airplanes, certificated in any category,
as identified in Boeing Special Attention
Service Bulletin 747–53–2253, Revision 4,
dated September 9, 2010.
(d) Subject
Joint Aircraft System Component (JASC)/
Air Transport Association (ATA) of America
Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by a report of
cracks up to 18.5 inches that were found at
stringer (S)-6L and S–6R on several airplanes,
and subsequent analysis results that
indicated that the protruding head fastener
modification and related post-modification
inspections required by AD 90–23–14,
Amendment 39–6801 (Docket No. 90–NM–
110–AD; 55 FR 46652, November 6, 1990) are
not adequate to prevent cracking at the upper
row of fasteners in the S–6 lap joint before
the cracks reach a critical length. We are
issuing this AD to detect and correct cracking
at the upper row of fasteners in the S–6 lap
joint, which could result in a sudden loss of
cabin pressurization and the inability of the
fuselage to withstand failsafe loads.
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(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Retained Inspection for Unmodified
Airplanes With Revised Service Information
This paragraph restates the requirements of
paragraph (A) of AD 90–23–14, Amendment
39–6801 (Docket No. 90–NM–110–AD; 55 FR
46652, November 6, 1990), with revised
service information. For airplanes identified
in Boeing Service Bulletin 747–53–2253,
including Addendum, Revision 2, dated
March 29, 1990, and that have not been
modified as specified in Boeing Service
Bulletin 747–53–2253, including Addendum,
Revision 2, dated March 29, 1990; in
accordance with the schedule indicated in
paragraphs (g)(1)(i) and (g)(1)(ii) of this AD,
perform a high frequency eddy current
(HFEC) inspection of the fuselage lap joint for
cracks between body station (BS) 340 and BS
400, or aft as far as the crew door, at stringer
S–6L and S–6R, in accordance with Boeing
Service Bulletin 747–53–2253, including
Addendum, Revision 2, dated March 29,
1990; or Boeing Special Attention Service
Bulletin 747–53–2253, Revision 4, dated
September 9, 2010. As of the effective date
of this AD, only Boeing Special Attention
Service Bulletin 747–53–2253, Revision 4,
dated September 9, 2010, may be used to
accomplish the actions required by this
paragraph.
(1) The inspection schedule is specified in
paragraphs (g)(1)(i) and (g)(1)(ii) of this AD.
(i) Unless previously accomplished within
the last 2,750 landings, perform the initial
inspection within the next 250 landings after
December 11, 1990 (the effective date of AD
90–23–14, Amendment 39–6801 (Docket No.
90–NM–110–AD; 55 FR 46652, November 6,
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54389
1990)), or prior to the accumulation of 10,000
landings after the modification, whichever
occurs later.
(ii) Repeat the inspection thereafter at
intervals not to exceed 3,000 landings.
(2) If cracks are found, repair prior to
further flight, in accordance with Boeing
Service Bulletin 747–53–2253, including
Addendum, Revision 2, dated March 29,
1990; or Boeing Special Attention Service
Bulletin 747–53–2253, Revision 4, dated
September 9, 2010. As of the effective date
of this AD, only Boeing Special Attention
Service Bulletin 747–53–2253, Revision 4,
dated September 9, 2010, may be used to
accomplish the actions required by this
paragraph.
(i) Retained Landing Determination
This paragraph restates the provisions of
paragraph (C) of AD 90–23–14, Amendment
39–6801 (Docket No. 90–NM–110–AD; 55 FR
46652, November 6, 1990), with a
compliance time limitation. On or before the
effective date of this AD: For purposes of
complying with paragraphs (g) and (h) of this
AD, the number of landings may be
determined to be equal to the number of
pressurization cycles where the cabin
pressure differential was greater than 1.5
pounds per square inch (psi). After the
effective date of this AD, every landing must
be used for compliance with paragraphs (g)
and (h) of this AD, regardless of cabin
pressure differential cycles.
(h) Retained Inspection for Modified
Airplanes With Revised Service Information
(j) Retained Inspection Adjustment Factor
This paragraph restates the requirements of
paragraph (D) of AD 90–23–14, Amendment
39–6801 (Docket No. 90–NM–110–AD; 55 FR
46652, November 6, 1990), with a
compliance time limitation. For Model
747SR airplanes only: On or before the
effective date of this AD, based on a
continued mixed operation of lower cabin
differentials, the initial inspection thresholds
and the repetitive inspection intervals
specified in paragraphs (g) and (h) of this AD
may be multiplied by a 1.2 adjustment factor.
After the effective date of this AD, the 1.2
adjustment factor is not allowed.
This paragraph restates the requirements of
paragraph (B) of AD 90–23–14, Amendment
39–6801 (Docket No. 90–NM–110–AD; 55 FR
46652, November 6, 1990), with revised
service information. For airplanes identified
in Boeing Service Bulletin 747–53–2253,
including Addendum, Revision 2, dated
March 29, 1990, and that have been modified
as specified in Boeing Service Bulletin 747–
53–2253, including Addendum, Revision 2,
dated March 29, 1990: In accordance with the
schedule specified in paragraphs (h)(1)(i) and
(h)(1)(ii) of this AD, perform an HFEC
inspection of the fuselage lap joint for cracks
between BS 340 and BS 400, or aft as far as
the crew door, at S–6L and S–6R, in
accordance with Boeing Service Bulletin
747–53–2253, including Addendum,
Revision 2, dated March 29, 1990, or Boeing
Special Attention Service Bulletin 747–53–
2253, Revision 4, dated September 9, 2010.
As of the effective date of this AD, use only
Boeing Special Attention Service Bulletin
747–53–2253, Revision 4, dated September 9,
2010, to accomplish the action required by
this paragraph. Accomplishment of the
actions required by paragraph (k) of this AD
terminates the requirements of this
paragraph.
(1) The inspection schedule is specified in
paragraphs (h)(1)(i) and (h)(1)(ii) of this AD.
(i) Unless previously accomplished within
the last 2,750 landings, perform the initial
inspection within the next 250 landings after
December 11, 1990 (the effective date of AD
90–23–14, Amendment 39–6801 (Docket No.
90–NM–110–AD; 55 FR 46652, November 6,
1990)), or prior to the accumulation of 10,000
landings after the modification, whichever
occurs later.
(ii) Repeat the inspection thereafter at
intervals not to exceed 3,000 landings.
(2) If cracks are found, repair prior to
further flight, in accordance with Boeing
Service Bulletin 747–53–2253, including
Addendum, Revision 2, dated March 29,
1990; or Boeing Special Attention Service
Bulletin 747–53–2253, Revision 4, dated
September 9, 2010. As of the effective date
of this AD, only Boeing Special Attention
Service Bulletin 747–53–2253, Revision 4,
dated September 9, 2010, may be used to
accomplish the actions required by this
paragraph.
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(k) New Inspections: Groups 1 Through 5
Airplanes
For airplanes in Groups 1 through 5, as
identified in Boeing Special Attention
Service Bulletin 747–53–2253, Revision 4,
dated September 9, 2010: At the time
specified in Table 1 of paragraph 1.E.,
‘‘Compliance,’’ of Boeing Special Attention
Service Bulletin 747–53–2253, Revision 4,
dated September 9, 2010—except that where
Table 1 of paragraph 1.E., ‘‘Compliance,’’ of
Boeing Special Attention Service Bulletin
747–53–2253, Revision 4, dated September 9,
2010, refers to a compliance time of 250
flight cycles after December 11, 1990 (the
effective date of AD 90–23–14, Amendment
39–6801 (Docket No. 90–NM–110–AD; 55 FR
46652, November 6, 1990)), the compliance
time is 250 flight cycles after the effective
date of this AD—do external detailed and
HFEC inspections for cracks in the stringer 6
skin lap splice, and do all applicable
corrective actions, as applicable, in
accordance with the Accomplishment
Instructions of Boeing Special Attention
Service Bulletin 747–53–2253, Revision 4,
dated September 9, 2010, except as required
by paragraph (o) of this AD. Do all applicable
corrective actions at the applicable time
specified in paragraph 1.E., ‘‘Compliance,’’ of
Boeing Special Attention Service Bulletin
747–53–2253, Revision 4, dated September 9,
2010. Accomplishment of the actions
required by this paragraph terminates the
requirements of paragraphs (g) and (h) of this
AD.
(l) New Repetitive Pre-Modification
Inspections: Groups 1 Through 5 Airplanes
For airplanes in Groups 1 through 5, as
identified in Boeing Special Attention
Service Bulletin 747–53–2253, Revision 4,
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dated September 9, 2010: Repeat the
inspections required by paragraph (k) of this
AD at the applicable time specified in
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Special Attention Service Bulletin 747–53–
2253, Revision 4, dated September 9, 2010,
until accomplishment of the modification
required by paragraph (m) of this AD.
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(m) New Modification: Groups 1 Through 5
Airplanes
(1) For airplanes in Groups 1 through 5, as
identified in Boeing Special Attention
Service Bulletin 747–53–2253, Revision 4,
dated September 9, 2010, on which the
structural repair manual (SRM) repair
specified in Part 1 of the Accomplishment
Instructions of Boeing Special Attention
Service Bulletin 747–53–2253, Revision 4,
dated September 9, 2010, has not been done:
Before the accumulation of 20,000 total flight
cycles, or within 1,000 flight cycles after the
effective date of this AD, whichever occurs
later, install the doubler modification, and do
all applicable related investigative and
corrective actions, in accordance with Part 3
of the Accomplishment Instructions of
Boeing Special Attention Service Bulletin
747–53–2253, Revision 4, dated September 9,
2010. All applicable related investigative and
corrective actions must be done before
further flight. Compliance with the
requirements of this paragraph terminates the
requirements of paragraphs (k) and (l) of this
AD.
(2) For airplanes in Groups 1 through 5, as
identified in Boeing Special Attention
Service Bulletin 747–53–2253, Revision 4,
dated September 9, 2010, on which the SRM
repair specified in Part 1 of the
Accomplishment Instructions of Boeing
Special Attention Service Bulletin 747–53–
2253, Revision 4, dated September 9, 2010,
has been done: Within 3,000 flight cycles
after accomplishing the SRM repair or within
1,000 flight cycles after the effective date of
this AD, whichever occurs later, install the
doubler modification, and do all applicable
related investigative and corrective actions,
in accordance with Part 3 of the
Accomplishment Instructions of Boeing
Special Attention Service Bulletin 747–53–
2253, Revision 4, dated September 9, 2010.
All applicable related investigative and
corrective actions must be done before
further flight. Compliance with the
requirements of this paragraph terminates the
requirements of paragraphs (k) and (l) of this
AD.
(n) New Repetitive Post-Modification
Inspections: Modified Airplanes
For airplanes modified as specified in Part
3 of the Accomplishment Instructions of
Boeing Special Attention Service Bulletin
747–53–2253, Revision 4, dated September 9,
2010, at the applicable time specified in
Table 3 or 4 of paragraph 1.E., ‘‘Compliance,’’
of Boeing Special Attention Service Bulletin
747–53–2253, Revision 4, dated September 9,
2010: Do detailed and eddy current
inspections to detect cracking of the skin,
frames, and tear straps, as applicable, in
accordance with Part 4 of the
Accomplishment Instructions of Boeing
Special Attention Service Bulletin 747–53–
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2253, Revision 4, dated September 9, 2010.
If any crack is found, repair before further
flight using a method approved in
accordance with the procedures specified in
paragraph (q) of this AD. Repeat the
applicable inspections thereafter at the
applicable times specified in paragraph 1.E.,
‘‘Compliance,’’ of Boeing Special Attention
Service Bulletin 747–53–2253, Revision 4,
dated September 9, 2010.
(o) Exceptions to Service Information
Specifications
(1) If any cracking is found during any
inspection required by this AD, and Boeing
Special Attention Service Bulletin 747–53–
2253, Revision 4, dated September 9, 2010,
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 (q) of
this AD.
(2) Although Boeing Special Attention
Service Bulletin 747–53–2253, Revision 4,
dated September 9, 2010, specifies to submit
certain information to the manufacturer, this
AD does not include that requirement.
(3) As of the effective date of this AD, if
any cracking is found during any inspection
required by this AD, and Boeing Service
Bulletin 747–53–2253, including Addendum,
Revision 2, dated March 29, 1990, 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 (q) of this
AD.
(p) Credit for Previous Actions
This paragraph provides credit for the
repairs and doubler modifications required
by paragraphs (k) and (m) of this AD, if those
actions were performed before the effective
date of this AD using the service information
specified in paragraphs (p)(1) through (p)(4)
of this AD. Post-modification inspections
must continue, as required by paragraph (n)
of this AD.
(1) Boeing Service Bulletin 747–53–2253,
dated December 14, 1984, which is not
incorporated by reference in this AD.
(2) Boeing Service Bulletin 747–53–2253,
Revision 1, dated January 25, 1990, which is
not incorporated by reference in this AD.
(3) Boeing Service Bulletin 747–53–2253,
including Addendum, Revision 2, dated
March 29, 1990.
(4) Boeing Service Bulletin 747–53–2253,
Revision 3, dated March 24, 1994, which is
not incorporated by reference in this AD.
(q) 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 the
Related Information section of this AD.
Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov.
PO 00000
Frm 00018
Fmt 4700
Sfmt 4700
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair
required by this AD if it is approved by the
Boeing Commercial Airplanes Organization
Designation Authorization (ODA) that has
been authorized by the Manager, Seattle
ACO, to make those findings. For a repair
method to be approved, the repair must meet
the certification basis of the airplane, and the
approval must specifically refer to this AD.
(4) AMOCs approved previously in
accordance with AD 90–23–14, Amendment
39–6801 (Docket No. 90–NM–110–AD; 55 FR
46652, November 6, 1990), are approved as
AMOCs for the corresponding provisions of
this AD.
(5) AMOCs approved previously for the
ADs specified in paragraphs (q)(5)(i) through
(q)(5)(vi) of this AD, for repair and doubler
modification installations in the area affected
by Boeing Special Attention Service Bulletin
747–53–2253, Revision 4, dated September 9,
2010, are approved as AMOCs for the actions
specified in paragraphs (g), (h), (k), (l), and
(m) of this AD. The post-modification
inspections required by paragraph (n) of this
AD must be accomplished.
(i) AD 2010–10–05, Amendment 39–16284
(75 FR 27424, May 17, 2010).
(ii) AD 2010–09–03, Amendment 39–16268
(75 FR 22514, April 29, 2010).
(iii) AD 2009–04–16, Amendment 39–
15822 (74 FR 8737, February 26, 2009).
(iv) AD 91–11–01, Amendment 39–6997
(56 FR 22306, May 15, 1991).
(v) AD 90–06–06, Amendment 39–6490 (55
FR 8374, March 7, 1990).
(vi) AD 2006–24–02, Amendment 39–
14831 (71 FR 67445, November 22, 2006).
(r) 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 referenced
in this AD that is not incorporated by
reference may be obtained at the addresses
specified in paragraphs (s)(4) and (s)(5) of
this AD.
(s) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(3) The following service information was
approved for IBR on October 9, 2013.
(i) Boeing Service Bulletin 747–53–2253,
including Addendum, Revision 2, dated
March 29, 1990.
(ii) Boeing Special Attention Service
Bulletin 747–53–2253, Revision 4, dated
September 9, 2010.
(4) For Boeing service information
identified in this AD, contact Boeing
E:\FR\FM\04SER1.SGM
04SER1
Federal Register / Vol. 78, No. 171 / Wednesday, September 4, 2013 / Rules and Regulations
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.
(5) You may view this service information
at FAA, Transport Airplane Directorate, 1601
Lind Avenue SW., Renton, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
(6) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on August
2, 2013.
Ross Landes,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2013–21397 Filed 9–3–13; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF THE TREASURY
Internal Revenue Service
26 CFR Part 1
[TD 9634]
RIN 1545–BK41
Determining the Amount of Taxes Paid
for Purposes of the Foreign Tax Credit
Internal Revenue Service (IRS),
Treasury.
ACTION: Final regulations and removal of
temporary regulations.
AGENCY:
This document contains final
regulations providing guidance relating
to the determination of the amount of
taxes paid for purposes of the foreign
tax credit. These regulations address
certain highly structured arrangements
that produce inappropriate foreign tax
credit results. The regulations affect
individuals and corporations that claim
direct and indirect foreign tax credits.
DATES: Effective date: These regulations
are effective on September 4, 2013.
Applicability date: For dates of
applicability, see § 1.901–2(h)(3).
FOR FURTHER INFORMATION CONTACT:
Jeffrey P. Cowan, at (202) 622–3850.
SUPPLEMENTARY INFORMATION:
sroberts on DSK5SPTVN1PROD with RULES
SUMMARY:
Background
This document contains amendments
to 26 CFR part 1. On July 18, 2011, a
notice of proposed rulemaking (REG–
126519–11) under section 901 of the
Internal Revenue Code (Code) relating to
the determination of the amount of taxes
VerDate Mar<15>2010
15:42 Sep 03, 2013
Jkt 229001
paid for purposes of the foreign tax
credit was published in the Federal
Register (76 FR 42076). In the same
issue of the Federal Register, final and
temporary regulations were also issued.
The text of those temporary regulations
served as the text of the proposed
regulations. No comments were received
in response to the notice of proposed
rulemaking. No public hearing was
requested or held. This Treasury
Decision adopts the proposed
regulations with no substantive change,
and the corresponding temporary
regulations are removed.
Special Analyses
It has been determined that this
Treasury decision is not a significant
regulatory action as defined in
Executive Order 12866. Therefore, a
regulatory assessment is not required. It
is hereby certified that these regulations
will not have a significant economic
impact on a substantial number of small
entities. This certification is based on
the fact that these regulations will
primarily affect affiliated groups of
corporations that have foreign
operations, which tend to be larger
businesses. Moreover the number of
taxpayers affected and the average
burden are minimal. Therefore, a
Regulatory Flexibility Analysis is not
required. Pursuant to section 7805(f) of
the Code, the notice of proposed
rulemaking preceding this regulation
was submitted to the Chief Counsel for
Advocacy of the Small Business
Administration for comment on its
impact on small business.
Drafting Information
The principal author of these
regulations is Jeffrey P. Cowan, Office of
Associate Chief Counsel (International).
However, other personnel from the IRS
and the Treasury Department
participated in their development.
List of Subjects in 26 CFR Part 1
Income taxes, Reporting and
recordkeeping requirements.
Adoption of Amendments to the
Regulations
Accordingly, 26 CFR part 1 is
amended as follows:
Paragraph 1. The authority citation
for part 1 continues to read in part as
follows:
■
Authority: 26 U.S.C. 7805 * * *
Par. 2. Section 1.901–2 is amended
by:
■ 1. Adding a sentence at the end of
paragraph (e)(5)(iv)(B)(1)(ii).
■
PO 00000
Frm 00019
Fmt 4700
Sfmt 9990
2. Removing paragraph
(e)(5)(iv)(B)(1)(iii).
■ 3. Revising the first sentence of
paragraph (h)(2).
■ 4. Revising paragraph (h)(3).
The revisions and addition read as
follows:
■
§ 1.901–2 Income, war profits, or excess
profits tax paid or accrued.
*
*
*
*
*
(e) * * *
(5) * * *
(iv) * * *
(B) * * *
(1) * * *
(ii) * * * A foreign payment
attributable to income of the entity also
includes a withholding tax (within the
meaning of section 901(k)(1)(B))
imposed on a dividend or other
distribution (including distributions
made by a pass-through entity or an
entity that is disregarded as an entity
separate from its owner for U.S. tax
purposes) with respect to the equity of
the entity.
*
*
*
*
*
(h) * * *
(2) Except as provided in paragraph
(h)(3) of this section, paragraph (e)(5)(iv)
of this section applies to foreign
payments that, if such payments were
an amount of tax paid, would be
considered paid or accrued under
§ 1.901–2(f) on or after July 13, 2011.
* * *
(3) The last sentence of paragraph
(e)(5)(iv)(B)(1)(ii) of this section applies
to foreign payments that, if such
payments were an amount of tax paid,
would be considered paid or accrued
under § 1.901–2(f) on or after September
4, 2013. See 26 CFR 1.901–
2T(e)(5)(iv)(B)(1)(iii) (revised as of April
1, 2013) for rules applicable to foreign
payments that, if such payments were
an amount of tax paid, would be
considered paid or accrued under
§ 1.901–2(f) before September 4, 2013.
*
*
*
*
*
§ 1.901–2T
■
PART 1—INCOME TAXES
54391
[Removed]
Par. 3. Section 1.901–2T is removed.
Beth Tucker,
Deputy Commissioner for Operations
Support.
Approved: August 6, 2013.
Mark J. Mazur,
Assistant Secretary of the Treasury (Tax
Policy).
[FR Doc. 2013–21401 Filed 9–3–13; 8:45 am]
BILLING CODE 4830–01–P
E:\FR\FM\04SER1.SGM
04SER1
]]>Agencies
[Federal Register Volume 78, Number 171 (Wednesday, September 4, 2013)]
[Rules and Regulations]
[Pages 54387-54391]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-21397]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-0364; Directorate Identifier 2011-NM-114-AD;
Amendment 39-17562; AD 2013-16-24]
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) 90-23-14 for
certain The Boeing Company Model 747 series airplanes. AD 90-23-14
required inspections of the fuselage skin lap splice between body
station (BS) 340 and BS 400 at stringers (S)-6L and S-6R, and repair if
necessary. This new AD adds new repetitive inspections for cracking in
the S-6 skin lap splice, which terminates the inspections required by
AD 90-23-14; eventual modification of the lap splice, which terminates
the repetitive inspections; post-modification inspections; and
corrective actions if necessary. This AD also adds airplanes to the
applicability. This AD was prompted by a report of cracks up to 18.5
inches that were found at S-6L and S-6R on several airplanes, and
subsequent analysis results that indicated that the protruding head
fastener modification and related post-modification inspections
required by AD 90-23-14 are not adequate to prevent cracking at the
upper row of fasteners in the S-6 lap joint before the cracks reach a
critical length. We are issuing this AD to detect and correct cracking
at the upper row of fasteners in the S-6 lap joint, which could result
in a sudden loss of cabin pressurization and the inability of the
fuselage to withstand failsafe loads.
DATES: This AD is effective October 9, 2013.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of October 9,
2013.
ADDRESSES: For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-
5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. You may review copies of the 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 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 Aircraft Certification Office,
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 90-23-14, Amendment 39-6801 (Docket No. 90-NM-
110-AD; 55 FR 46652, November 6,
[[Page 54388]]
1990), (``AD 90-23-14''). AD 90-23-14 applied to the specified
products. The NPRM published in the Federal Register on May 3, 2013 (78
FR 25898). The NPRM proposed to continue to require inspections of the
fuselage skin lap splice between BS 340 and BS 400 at S-6L and S-6R,
and repair if necessary. The NPRM also proposed to add new repetitive
inspections for cracking in the stringer 6 skin lap splice, which would
terminate the inspections required by AD 90-23-14; eventual
modification of the lap splice, which would terminate the new
repetitive inspections; post-modification inspections; and corrective
actions if necessary. The NPRM also proposed to add airplanes to the
applicability.
Comments
We gave the public the opportunity to participate in developing
this AD. We received no comments on the NPRM (78 FR 25898, May 3, 2013)
or on the determination of the cost to the public.
Clarification
We have revised the wording of paragraphs (i) and (j) of this AD to
clarify that certain compliance time adjustment factors were allowed in
AD 90-23-14 (Docket No. 90-NM-110-AD; 55 FR 46652, November 6, 1990),
but are no longer allowed in this new AD.
Conclusion
We reviewed the relevant data and determined that air safety and
the public interest require adopting this AD with the changes described
previously--and minor editorial changes. We have determined that these
minor changes:
Are consistent with the intent that was proposed in the
NPRM (78 FR 25898, May 3, 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 25898, May 3, 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 76 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
----------------------------------------------------------------------------------------------------------------
Retained inspections from AD 90- 8 work-hours x $85 $0 $680 per inspection $51,680 per
23-14 (Docket No. 90-NM-110-AD; per hour = $680 cycle. inspection cycle.
55 FR 46652, November 6, 1990). per inspection
cycle.
New pre-modification inspections. 8 work-hours x $85 0 680 per inspection $51,680 per
per hour = $680 cycle. inspection cycle.
per inspection
cycle.
New modification................. 204 work-hours x 0 17,340............. $1,317,840.
$85 per hour =
$17,340.
New post-modification inspections 12 work-hours x $85 0 1,020 per $77,520.
per hour = $1,020 inspection cycle.
per inspection
cycle.
----------------------------------------------------------------------------------------------------------------
We have received no definitive data that would enable us to provide
cost estimates for the on-condition actions specified in this AD.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We have determined that this AD will not have federalism
implications under Executive Order 13132. This AD will not have a
substantial direct effect on the States, on the relationship between
the national government and the States, or on the distribution of power
and responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation in Alaska, and
(4) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing airworthiness directive (AD)
90-23-14, Amendment 39-6801 (Docket No. 90-NM-110-AD; 55 FR 46652,
November 6, 1990), and adding the following new AD:
2013-16-24 The Boeing Company: Amendment 39-17562; Docket No. FAA-
2013-0364; Directorate Identifier 2011-NM-114-AD.
(a) Effective Date
This AD is effective October 9, 2013.
(b) Affected ADs
This AD supersedes AD 90-23-14, Amendment 39-6801 (55 FR 46652,
November 6, 1990).
[[Page 54389]]
(c) Applicability
This AD applies to The Boeing Company Model 747-100, 747-100B,
747-200B, 747-200C, 747-200F, 747-300, 747SR, and 747SP series
airplanes, certificated in any category, as identified in Boeing
Special Attention Service Bulletin 747-53-2253, Revision 4, dated
September 9, 2010.
(d) Subject
Joint Aircraft System Component (JASC)/Air Transport Association
(ATA) of America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by a report of cracks up to 18.5 inches
that were found at stringer (S)-6L and S-6R on several airplanes,
and subsequent analysis results that indicated that the protruding
head fastener modification and related post-modification inspections
required by AD 90-23-14, Amendment 39-6801 (Docket No. 90-NM-110-AD;
55 FR 46652, November 6, 1990) are not adequate to prevent cracking
at the upper row of fasteners in the S-6 lap joint before the cracks
reach a critical length. We are issuing this AD to detect and
correct cracking at the upper row of fasteners in the S-6 lap joint,
which could result in a sudden loss of cabin pressurization and the
inability of the fuselage to withstand failsafe loads.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Inspection for Unmodified Airplanes With Revised Service
Information
This paragraph restates the requirements of paragraph (A) of AD
90-23-14, Amendment 39-6801 (Docket No. 90-NM-110-AD; 55 FR 46652,
November 6, 1990), with revised service information. For airplanes
identified in Boeing Service Bulletin 747-53-2253, including
Addendum, Revision 2, dated March 29, 1990, and that have not been
modified as specified in Boeing Service Bulletin 747-53-2253,
including Addendum, Revision 2, dated March 29, 1990; in accordance
with the schedule indicated in paragraphs (g)(1)(i) and (g)(1)(ii)
of this AD, perform a high frequency eddy current (HFEC) inspection
of the fuselage lap joint for cracks between body station (BS) 340
and BS 400, or aft as far as the crew door, at stringer S-6L and S-
6R, in accordance with Boeing Service Bulletin 747-53-2253,
including Addendum, Revision 2, dated March 29, 1990; or Boeing
Special Attention Service Bulletin 747-53-2253, Revision 4, dated
September 9, 2010. As of the effective date of this AD, only Boeing
Special Attention Service Bulletin 747-53-2253, Revision 4, dated
September 9, 2010, may be used to accomplish the actions required by
this paragraph.
(1) The inspection schedule is specified in paragraphs (g)(1)(i)
and (g)(1)(ii) of this AD.
(i) Unless previously accomplished within the last 2,750
landings, perform the initial inspection within the next 250
landings after December 11, 1990 (the effective date of AD 90-23-14,
Amendment 39-6801 (Docket No. 90-NM-110-AD; 55 FR 46652, November 6,
1990)), or prior to the accumulation of 10,000 landings after the
modification, whichever occurs later.
(ii) Repeat the inspection thereafter at intervals not to exceed
3,000 landings.
(2) If cracks are found, repair prior to further flight, in
accordance with Boeing Service Bulletin 747-53-2253, including
Addendum, Revision 2, dated March 29, 1990; or Boeing Special
Attention Service Bulletin 747-53-2253, Revision 4, dated September
9, 2010. As of the effective date of this AD, only Boeing Special
Attention Service Bulletin 747-53-2253, Revision 4, dated September
9, 2010, may be used to accomplish the actions required by this
paragraph.
(h) Retained Inspection for Modified Airplanes With Revised Service
Information
This paragraph restates the requirements of paragraph (B) of AD
90-23-14, Amendment 39-6801 (Docket No. 90-NM-110-AD; 55 FR 46652,
November 6, 1990), with revised service information. For airplanes
identified in Boeing Service Bulletin 747-53-2253, including
Addendum, Revision 2, dated March 29, 1990, and that have been
modified as specified in Boeing Service Bulletin 747-53-2253,
including Addendum, Revision 2, dated March 29, 1990: In accordance
with the schedule specified in paragraphs (h)(1)(i) and (h)(1)(ii)
of this AD, perform an HFEC inspection of the fuselage lap joint for
cracks between BS 340 and BS 400, or aft as far as the crew door, at
S-6L and S-6R, in accordance with Boeing Service Bulletin 747-53-
2253, including Addendum, Revision 2, dated March 29, 1990, or
Boeing Special Attention Service Bulletin 747-53-2253, Revision 4,
dated September 9, 2010. As of the effective date of this AD, use
only Boeing Special Attention Service Bulletin 747-53-2253, Revision
4, dated September 9, 2010, to accomplish the action required by
this paragraph. Accomplishment of the actions required by paragraph
(k) of this AD terminates the requirements of this paragraph.
(1) The inspection schedule is specified in paragraphs (h)(1)(i)
and (h)(1)(ii) of this AD.
(i) Unless previously accomplished within the last 2,750
landings, perform the initial inspection within the next 250
landings after December 11, 1990 (the effective date of AD 90-23-14,
Amendment 39-6801 (Docket No. 90-NM-110-AD; 55 FR 46652, November 6,
1990)), or prior to the accumulation of 10,000 landings after the
modification, whichever occurs later.
(ii) Repeat the inspection thereafter at intervals not to exceed
3,000 landings.
(2) If cracks are found, repair prior to further flight, in
accordance with Boeing Service Bulletin 747-53-2253, including
Addendum, Revision 2, dated March 29, 1990; or Boeing Special
Attention Service Bulletin 747-53-2253, Revision 4, dated September
9, 2010. As of the effective date of this AD, only Boeing Special
Attention Service Bulletin 747-53-2253, Revision 4, dated September
9, 2010, may be used to accomplish the actions required by this
paragraph.
(i) Retained Landing Determination
This paragraph restates the provisions of paragraph (C) of AD
90-23-14, Amendment 39-6801 (Docket No. 90-NM-110-AD; 55 FR 46652,
November 6, 1990), with a compliance time limitation. On or before
the effective date of this AD: For purposes of complying with
paragraphs (g) and (h) of this AD, the number of landings may be
determined to be equal to the number of pressurization cycles where
the cabin pressure differential was greater than 1.5 pounds per
square inch (psi). After the effective date of this AD, every
landing must be used for compliance with paragraphs (g) and (h) of
this AD, regardless of cabin pressure differential cycles.
(j) Retained Inspection Adjustment Factor
This paragraph restates the requirements of paragraph (D) of AD
90-23-14, Amendment 39-6801 (Docket No. 90-NM-110-AD; 55 FR 46652,
November 6, 1990), with a compliance time limitation. For Model
747SR airplanes only: On or before the effective date of this AD,
based on a continued mixed operation of lower cabin differentials,
the initial inspection thresholds and the repetitive inspection
intervals specified in paragraphs (g) and (h) of this AD may be
multiplied by a 1.2 adjustment factor. After the effective date of
this AD, the 1.2 adjustment factor is not allowed.
(k) New Inspections: Groups 1 Through 5 Airplanes
For airplanes in Groups 1 through 5, as identified in Boeing
Special Attention Service Bulletin 747-53-2253, Revision 4, dated
September 9, 2010: At the time specified in Table 1 of paragraph
1.E., ``Compliance,'' of Boeing Special Attention Service Bulletin
747-53-2253, Revision 4, dated September 9, 2010--except that where
Table 1 of paragraph 1.E., ``Compliance,'' of Boeing Special
Attention Service Bulletin 747-53-2253, Revision 4, dated September
9, 2010, refers to a compliance time of 250 flight cycles after
December 11, 1990 (the effective date of AD 90-23-14, Amendment 39-
6801 (Docket No. 90-NM-110-AD; 55 FR 46652, November 6, 1990)), the
compliance time is 250 flight cycles after the effective date of
this AD--do external detailed and HFEC inspections for cracks in the
stringer 6 skin lap splice, and do all applicable corrective
actions, as applicable, in accordance with the Accomplishment
Instructions of Boeing Special Attention Service Bulletin 747-53-
2253, Revision 4, dated September 9, 2010, except as required by
paragraph (o) of this AD. Do all applicable corrective actions at
the applicable time specified in paragraph 1.E., ``Compliance,'' of
Boeing Special Attention Service Bulletin 747-53-2253, Revision 4,
dated September 9, 2010. Accomplishment of the actions required by
this paragraph terminates the requirements of paragraphs (g) and (h)
of this AD.
(l) New Repetitive Pre-Modification Inspections: Groups 1 Through 5
Airplanes
For airplanes in Groups 1 through 5, as identified in Boeing
Special Attention Service Bulletin 747-53-2253, Revision 4,
[[Page 54390]]
dated September 9, 2010: Repeat the inspections required by
paragraph (k) of this AD at the applicable time specified in
paragraph 1.E., ``Compliance,'' of Boeing Special Attention Service
Bulletin 747-53-2253, Revision 4, dated September 9, 2010, until
accomplishment of the modification required by paragraph (m) of this
AD.
(m) New Modification: Groups 1 Through 5 Airplanes
(1) For airplanes in Groups 1 through 5, as identified in Boeing
Special Attention Service Bulletin 747-53-2253, Revision 4, dated
September 9, 2010, on which the structural repair manual (SRM)
repair specified in Part 1 of the Accomplishment Instructions of
Boeing Special Attention Service Bulletin 747-53-2253, Revision 4,
dated September 9, 2010, has not been done: Before the accumulation
of 20,000 total flight cycles, or within 1,000 flight cycles after
the effective date of this AD, whichever occurs later, install the
doubler modification, and do all applicable related investigative
and corrective actions, in accordance with Part 3 of the
Accomplishment Instructions of Boeing Special Attention Service
Bulletin 747-53-2253, Revision 4, dated September 9, 2010. All
applicable related investigative and corrective actions must be done
before further flight. Compliance with the requirements of this
paragraph terminates the requirements of paragraphs (k) and (l) of
this AD.
(2) For airplanes in Groups 1 through 5, as identified in Boeing
Special Attention Service Bulletin 747-53-2253, Revision 4, dated
September 9, 2010, on which the SRM repair specified in Part 1 of
the Accomplishment Instructions of Boeing Special Attention Service
Bulletin 747-53-2253, Revision 4, dated September 9, 2010, has been
done: Within 3,000 flight cycles after accomplishing the SRM repair
or within 1,000 flight cycles after the effective date of this AD,
whichever occurs later, install the doubler modification, and do all
applicable related investigative and corrective actions, in
accordance with Part 3 of the Accomplishment Instructions of Boeing
Special Attention Service Bulletin 747-53-2253, Revision 4, dated
September 9, 2010. All applicable related investigative and
corrective actions must be done before further flight. Compliance
with the requirements of this paragraph terminates the requirements
of paragraphs (k) and (l) of this AD.
(n) New Repetitive Post-Modification Inspections: Modified Airplanes
For airplanes modified as specified in Part 3 of the
Accomplishment Instructions of Boeing Special Attention Service
Bulletin 747-53-2253, Revision 4, dated September 9, 2010, at the
applicable time specified in Table 3 or 4 of paragraph 1.E.,
``Compliance,'' of Boeing Special Attention Service Bulletin 747-53-
2253, Revision 4, dated September 9, 2010: Do detailed and eddy
current inspections to detect cracking of the skin, frames, and tear
straps, as applicable, in accordance with Part 4 of the
Accomplishment Instructions of Boeing Special Attention Service
Bulletin 747-53-2253, Revision 4, dated September 9, 2010. If any
crack is found, repair before further flight using a method approved
in accordance with the procedures specified in paragraph (q) of this
AD. Repeat the applicable inspections thereafter at the applicable
times specified in paragraph 1.E., ``Compliance,'' of Boeing Special
Attention Service Bulletin 747-53-2253, Revision 4, dated September
9, 2010.
(o) Exceptions to Service Information Specifications
(1) If any cracking is found during any inspection required by
this AD, and Boeing Special Attention Service Bulletin 747-53-2253,
Revision 4, dated September 9, 2010, 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 (q) of this AD.
(2) Although Boeing Special Attention Service Bulletin 747-53-
2253, Revision 4, dated September 9, 2010, specifies to submit
certain information to the manufacturer, this AD does not include
that requirement.
(3) As of the effective date of this AD, if any cracking is
found during any inspection required by this AD, and Boeing Service
Bulletin 747-53-2253, including Addendum, Revision 2, dated March
29, 1990, 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 (q) of this
AD.
(p) Credit for Previous Actions
This paragraph provides credit for the repairs and doubler
modifications required by paragraphs (k) and (m) of this AD, if
those actions were performed before the effective date of this AD
using the service information specified in paragraphs (p)(1) through
(p)(4) of this AD. Post-modification inspections must continue, as
required by paragraph (n) of this AD.
(1) Boeing Service Bulletin 747-53-2253, dated December 14,
1984, which is not incorporated by reference in this AD.
(2) Boeing Service Bulletin 747-53-2253, Revision 1, dated
January 25, 1990, which is not incorporated by reference in this AD.
(3) Boeing Service Bulletin 747-53-2253, including Addendum,
Revision 2, dated March 29, 1990.
(4) Boeing Service Bulletin 747-53-2253, Revision 3, dated March
24, 1994, which is not incorporated by reference in this AD.
(q) 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 the Related Information
section of this AD. Information may be emailed to: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
(3) An AMOC that provides an acceptable level of safety may be
used for any repair required by this AD if it is approved by the
Boeing Commercial Airplanes 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 previously in accordance with AD 90-23-14,
Amendment 39-6801 (Docket No. 90-NM-110-AD; 55 FR 46652, November 6,
1990), are approved as AMOCs for the corresponding provisions of
this AD.
(5) AMOCs approved previously for the ADs specified in
paragraphs (q)(5)(i) through (q)(5)(vi) of this AD, for repair and
doubler modification installations in the area affected by Boeing
Special Attention Service Bulletin 747-53-2253, Revision 4, dated
September 9, 2010, are approved as AMOCs for the actions specified
in paragraphs (g), (h), (k), (l), and (m) of this AD. The post-
modification inspections required by paragraph (n) of this AD must
be accomplished.
(i) AD 2010-10-05, Amendment 39-16284 (75 FR 27424, May 17,
2010).
(ii) AD 2010-09-03, Amendment 39-16268 (75 FR 22514, April 29,
2010).
(iii) AD 2009-04-16, Amendment 39-15822 (74 FR 8737, February
26, 2009).
(iv) AD 91-11-01, Amendment 39-6997 (56 FR 22306, May 15, 1991).
(v) AD 90-06-06, Amendment 39-6490 (55 FR 8374, March 7, 1990).
(vi) AD 2006-24-02, Amendment 39-14831 (71 FR 67445, November
22, 2006).
(r) 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 referenced in this AD that is
not incorporated by reference may be obtained at the addresses
specified in paragraphs (s)(4) and (s)(5) of this AD.
(s) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(3) The following service information was approved for IBR on
October 9, 2013.
(i) Boeing Service Bulletin 747-53-2253, including Addendum,
Revision 2, dated March 29, 1990.
(ii) Boeing Special Attention Service Bulletin 747-53-2253,
Revision 4, dated September 9, 2010.
(4) For Boeing service information identified in this AD,
contact Boeing
[[Page 54391]]
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.
(5) You may view this service information at FAA, Transport
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For
information on the availability of this material at the FAA, call
425-227-1221.
(6) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on August 2, 2013.
Ross Landes,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2013-21397 Filed 9-3-13; 8:45 am]
BILLING CODE 4910-13-P
