[Federal Register Volume 78, Number 171 (Wednesday, September 4, 2013)]
[Rules and Regulations]
[Pages 54387-54391]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2013-21397]
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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.
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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 http://www.regulations.gov; or in person at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this AD, the regulatory evaluation,
any comments received, and other information. The address for the
Docket Office (phone: 800-647-5527) is Document Management Facility,
U.S. Department of Transportation, Docket Operations, M-30, West
Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: 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: [email protected].
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: [email protected].
(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: [email protected].
(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: http://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