AD 2016-07-31
Recurring
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | The Boeing Company | 747-400 Series | Airworthiness Directives; The Boeing Company Airplanes |
| aircraft | The Boeing Company | 747-400D Series | Airworthiness Directives; The Boeing Company Airplanes |
Unsafe Condition
Fatigue cracking in certain upper chords of the upper deck floor beam, which could become large and cause the floor beams to become severed, resulting in rapid decompression or reduced controllability of the airplane.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Conduct repetitive inspections to detect cracks in the floor panel attachment fastener holes of certain upper deck floor beam upper chords. Perform corrective actions if necessary, including replacement of the upper deck floor beam upper chords.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Within the compliance times specified in Boeing Alert Service Bulletin 747-53A2688, Revision 2, dated August 21, 2014.
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
The Boeing Company Model 747-400 and -400D series airplanes.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
We are superseding Airworthiness Directive (AD) 2013-22-11 for certain The Boeing Company Model 747-400 and -400D series airplanes. AD 2013-22-11 required repetitive inspections to detect cracks in the floor panel attachment fastener holes of certain upper deck floor beam upper chords, repetitive inspections, corrective actions if necessary, and replacement of the upper deck floor beam upper chords. Since we issued AD 2013-22-11, we received a report that certain fastener holes in the upper deck floor beam upper chords may not have been inspected in accordance with AD 2013-22-11. This AD adds additional repetitive inspections for cracks for certain airplanes, and corrective actions if necessary. We are issuing this AD to detect and correct fatigue cracking in certain upper chords of the upper deck floor beam. Such cracks could become large and cause the floor beams to become severed and result in rapid decompression or reduced controllability of the airplane.
Applicability Source Text
Show captured applicability text from the source AD
(c) Applicability
This AD applies to The Boeing Company Model 747-400 and -400D
series airplanes, certificated in any category, as identified in
Boeing Alert Service Bulletin 747-53A2688, Revision 2, dated August
21, 2014.
Document Text
Show stored source text (verify against official source)
[Federal Register Volume 81, Number 71 (Wednesday, April 13, 2016)]
[Rules and Regulations]
[Pages 21726-21729]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2016-08271]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2015-2464; Directorate Identifier 2014-NM-195-AD;
Amendment 39-18476; AD 2016-07-31]
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) 2013-22-11 for
certain The Boeing Company Model 747-400 and -400D series airplanes. AD
2013-22-11 required repetitive inspections to detect cracks in the
floor panel attachment fastener holes of certain upper deck floor beam
upper chords, repetitive inspections, corrective actions if necessary,
and replacement of the upper deck floor beam upper chords. Since we
issued AD 2013-22-11, we received a report that certain fastener holes
in the upper deck floor beam upper chords may not have been inspected
in accordance with AD 2013-22-11. This AD adds additional repetitive
inspections for cracks for certain airplanes, and corrective actions if
necessary. We are issuing this AD to detect and correct fatigue
cracking in certain upper chords of the upper deck floor beam. Such
cracks could become large and cause the floor beams to become severed
and result in rapid decompression or reduced controllability of the
airplane.
DATES: This AD is effective May 18, 2016.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of May 18,
2016.
ADDRESSES: For service information identified in this final rule,
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 <a href="https://www.myboeingfleet.com">https://www.myboeingfleet.com</a>. You may view this referenced service information
at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW.,
Renton, WA. For information on the availability of this material at the
FAA, call 425-227-1221. It is also available on the Internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a> by searching for and locating Docket No. FAA-2015-
2464.
[[Page 21727]]
Examining the AD Docket
You may examine the AD docket on the Internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a> by searching for and locating Docket No. FAA-2015-
2464; or in person at the Docket Management Facility between 9 a.m. and
5 p.m., Monday through Friday, except Federal holidays. The AD docket
contains this AD, the regulatory evaluation, any comments received, and
other information. The address for the Docket Office (phone: 800-647-
5527) is Docket Management Facility, U.S. Department of Transportation,
Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200
New Jersey Avenue SE., Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Nathan Weigand, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office
(ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-
6428; fax: 425-917-6590; email: <a href="/cdn-cgi/l/email-protection#0a446b7e626b64245a245d6f636d6b646e4a6c6b6b246d657c"><span class="__cf_email__" data-cfemail="1e507f6a767f70304e30497b77797f707a5e787f7f30797168">[email protected]</span></a>.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2013-22-11, Amendment 39-17643 (78 FR 66254,
November 5, 2013), (``AD 2013-22-11''). AD 2013-22-11 applied to
certain The Boeing Company Model 747-400 and -400D series airplanes.
The NPRM published in the Federal Register on July 23, 2015 (80 FR
43648) (``the NPRM''). The NPRM was prompted by a report that certain
fastener holes in the upper deck floor beam upper chords may not have
been inspected in accordance with AD 2013-22-11. The NPRM proposed to
continue to require repetitive inspections to detect cracks in the
floor panel attachment fastener holes of certain upper deck floor beam
upper chords, repetitive inspections, corrective actions if necessary,
and replacement of the upper deck floor beam upper chords. The NPRM
also proposed to require additional repetitive inspections for cracks
for certain airplanes, and corrective actions if necessary. We are
issuing this AD to detect and correct fatigue cracking in certain upper
chords of the upper deck floor beam. Such cracking could become large
and cause the floor beams to become severed and result in rapid
decompression or reduced controllability of the airplane.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the NPRM and
the FAA's response to each comment. United Airlines supported the NPRM.
Request To Revise ``Exceptions to Service Information Specifications''
Boeing requested that paragraph (m)(4), ``Exceptions to Service
Information Specifications,'' of the proposed AD be revised. Boeing
stated that Boeing Alert Service Bulletin 747-53A2688, Revision 1,
dated September 19, 2012, which is included in paragraph (m)(4), has
the same compliance time as table 3 in Boeing Alert Service Bulletin
747-53A2688, Revision 2, dated August 21, 2014; therefore, Boeing Alert
Service Bulletin 747-53A2688, Revision 2, dated August 21, 2014, should
also be included in paragraph (m)(4) of the proposed AD.
For the reason provided by the commenter we agree to include Boeing
Alert Service Bulletin 747-53A2688, Revision 2, dated August 21, 2014,
in paragraph (m)(4) of this AD. We have also revised paragraph (m)(4)
of this AD by removing the reference to Boeing Alert Service Bulletin
747-53A2688, Revision 1, dated September 19, 2012, because this AD only
refers to Boeing Alert Service Bulletin 747-53A2688, Revision 2, dated
August 21, 2014, for compliance times.
Conclusion
We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
this AD with the change described and minor editorial changes. We have
determined that these minor changes:
<bullet> Are consistent with the intent that was proposed in the
NPRM for correcting the unsafe condition; and
<bullet> Do not add any additional burden upon the public than was
already proposed in the NPRM.
We also determined that these changes will not increase the
economic burden on any operator or increase the scope of this AD.
Related Service Information Under 1 CFR Part 51
We reviewed Boeing Alert Service Bulletin 747-53A2688, Revision 2,
dated August 21, 2014. The service information describes procedures for
upper deck floor beam upper chord inspection and repair at floor panel
attachment fastener holes in section 41 and section 42. This service
information is reasonably available because the interested parties have
access to it through their normal course of business or by the means
identified in the ADDRESSES section.
Costs of Compliance
We estimate that this AD affects 84 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Inspection (retained actions from Up to 309 work- $0 Up to $26,265 per Up to $2,206,260
AD 2013-22-11). hours x $85 per inspection cycle. per inspection
hour = $26,265 per cycle.
inspection cycle.
New inspections.................. Up to 241 work- 0 Up to $20,485 per Up to $1,720,740
hours x $85 per inspection cycle. per inspection
hour = $20,485. cycle.
----------------------------------------------------------------------------------------------------------------
We have received no definitive data that will enable us to provide
a cost estimate for the repair or modification specified in this AD.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation
[[Page 21728]]
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)
2013-22-11, Amendment 39-17643 (78 FR 66254, November 5, 2013), and
adding the following new AD:
2016-07-31 The Boeing Company: Amendment 39-18476; Docket No. FAA-
2015-2464; Directorate Identifier 2014-NM-195-AD.
(a) Effective Date
This AD is effective May 18, 2016.
(b) Affected ADs
This AD replaces AD 2013-22-11, Amendment 39-17643 (78 FR 66254,
November 5, 2013) (``AD 2013-22-11'').
(c) Applicability
This AD applies to The Boeing Company Model 747-400 and -400D
series airplanes, certificated in any category, as identified in
Boeing Alert Service Bulletin 747-53A2688, Revision 2, dated August
21, 2014.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by an evaluation by the design approval
holder indicating that certain upper chords of the upper deck floor
beam are subject to widespread fatigue damage. This AD was also
prompted by reports that certain fastener holes in the upper deck
floor beam upper chords in Section 41, may not have been inspected
in accordance with AD 2013-22-11. We are issuing this AD to detect
and correct fatigue cracking in certain upper chords of the upper
deck floor beam, which could become large and cause the floor beams
to become severed and result in rapid decompression or reduced
controllability of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Section 41--Repetitive Inspections, and Corrective Actions
At the applicable time specified in table 1 of paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 747-53A2688,
Revision 2, dated August 21, 2014, do open hole or surface high
frequency eddy current inspections (HFEC) for cracking of the floor
panel attachment holes in the upper deck floor beam upper chords, in
accordance with Part 1 of the Accomplishment Instructions of Boeing
Alert Service Bulletin 747-53A2688, Revision 2, dated August 21,
2014. If any crack is found during any inspection, before further
flight, repair in accordance with Part 2 of the Accomplishment
Instructions of Boeing Alert Service Bulletin 747-53A2688, Revision
2, dated August 21, 2014, or repair using a method approved in
accordance with the procedures specified in paragraph (o) of this
AD. Repeat the inspections thereafter at the applicable time
specified in table 1 of paragraph 1.E., ``Compliance,'' of Boeing
Alert Service Bulletin 747-53A2688, Revision 2, dated August 21,
2014, until an action specified in paragraph (g)(1) or (g)(2) of
this AD is done.
(1) Doing a repair as a hole modification in accordance with
Part 2 of the Accomplishment Instructions of Boeing Alert Service
Bulletin 747-53A2688, Revision 2, dated August 21, 2014, except as
required by paragraph (m)(2) of this AD, terminates the inspections
required by paragraph (g) of this AD for the modified hole only.
(2) Doing a modification in accordance with Figure 5 of the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2688, Revision 2, dated August 21, 2014, except as required by
paragraph (m)(2) of this AD, terminates the inspections required by
paragraph (g) of this AD for the modification only.
(h) Section 41--Repetitive Inspection of Repaired or Modified Holes,
and Corrective Actions
For airplanes on which a repair specified in Part 2 of the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2688, Revision 2, dated August 21, 2014, is done, or a
modification specified in Figure 5 of the Accomplishment
Instructions of Boeing Alert Service Bulletin 747-53A2688, Revision
2, dated August 21, 2014, is done: At the applicable time specified
in table 2 of paragraph 1.E., ``Compliance,'' of Boeing Alert
Service Bulletin 747-53A2688, Revision 2, dated August 21, 2014,
except as required by paragraph (m)(3) of this AD, do open hole or
surface HFEC for cracking of repaired or modified floor panel
attachment holes in the upper deck floor beam upper chords, in
accordance with Part 1 or Part 3, as applicable, of the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2688, Revision 2, dated August 21, 2014. If any crack is found
during any inspection required by this paragraph, before further
flight, repair using a method approved in accordance with the
procedures specified in paragraph (o) of this AD. Repeat the
inspections thereafter at the applicable time specified in table 2
of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
747-53A2688, Revision 2, dated August 21, 2014.
(i) Section 44--Repetitive Inspection, and Corrective Actions
For airplanes identified in Group 1 in Boeing Alert Service
Bulletin 747-53A2688, Revision 2, dated August 21, 2014: At the
applicable time specified in table 3 of paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 747-53A2688,
Revision 2, dated August 21, 2014, except as required by paragraph
(m)(4) of this AD, do open hole or surface HFEC inspections of the
floor panel attachment holes in the upper deck floor beam upper
chords, in accordance with Part 4 of the Accomplishment Instructions
of Boeing Alert Service Bulletin 747-53A2688, Revision 2, dated
August 21, 2014. If any crack is found during any inspection
required by this paragraph, before further flight, repair in
accordance with Part 5 of the Accomplishment Instructions of Boeing
Alert Service Bulletin 747-53A2688, Revision 2, dated August 21,
2014, except as required by paragraph (m)(2) of this AD. Repeat the
inspections thereafter at the applicable time specified in table 3
of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
747-53A2688, Revision 2, dated August 21, 2014, until an action
specified in paragraph (i)(1) or (i)(2) of this AD is done.
(1) Doing a repair as a hole modification in accordance with
Part 5 of the Accomplishment Instructions of Boeing Alert Service
Bulletin 747-53A2688, Revision 2, dated August 21, 2014, except as
required by paragraph (m)(2) of this AD, terminates the inspections
required by paragraph (i) of this AD for that modified hole only.
(2) Doing a modification in accordance with Figure 21 of the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2688, Revision 2, dated August 21,
[[Page 21729]]
2014, except as required by paragraph (m)(2) of this AD, terminates
the inspections required by paragraph (i) of this AD for that
modified hole only.
(j) Section 44--Repetitive Inspection of Repaired or Modified Holes,
and Corrective Actions
For airplanes identified in Group 1 in Boeing Alert Service
Bulletin 747-53A2688, Revision 2, dated August 21, 2014, on which a
repair specified in Part 5 of Boeing Alert Service Bulletin 747-
53A2688, Revision 2, dated August 21, 2014, is done or the
modification specified in Figure 21 of the Accomplishment
Instructions of Boeing Alert Service Bulletin 747-53A2688, Revision
2, dated August 21, 2014, is done: At the applicable time specified
in table 4 of paragraph 1.E., ``Compliance,'' of Boeing Alert
Service Bulletin 747-53A2688, Revision 2, dated August 21, 2014,
except as required by paragraph (m)(3) of this AD, do open hole or
surface HFEC inspections of repaired or modified floor panel
attachment holes in the upper deck floor beam upper chords, in
accordance with Part 4 or Part 6, as applicable, of the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2688, Revision 2, dated August 21, 2014. If any crack is found
during any inspection by this paragraph, before further flight,
repair using a method approved in accordance with the procedures
specified in paragraph (o) of this AD. Repeat the inspections
thereafter at the applicable time specified in table 4 of paragraph
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2688,
Revision 2, dated August 21, 2014.
(k) Sections 41 and 44--Replacement and Post-Replacement Repetitive
Inspections
At the applicable time specified in table 5 of paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 747-53A2688,
Revision 2, dated August 21, 2014: Replace all upper deck floor beam
upper chords, in accordance with Part 7 of the Accomplishment
Instructions of Boeing Alert Service Bulletin 747-53A2688, Revision
2, dated August 21, 2014. Within 20,000 flight cycles after doing
the replacement, do the inspections specified in paragraphs (g) and
(i) of this AD, as applicable. Thereafter, repeat the inspections
required by paragraphs (g) and (i) of this AD, as applicable, at the
times specified in paragraphs (g) and (i) of this AD.
(l) Section 41--Repetitive Inspection of Plugged or Re-Used Holes, and
Corrective Actions
For airplanes identified in Group 2 in Boeing Alert Service
Bulletin 747-53A2688, Revision 2, dated August 21, 2014: At the
applicable time specified in table 6 of paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 747-53A2688,
Revision 2, dated August 21, 2014, except as required by paragraph
(m)(1) of this AD, at all plugged or reused floor panel attachment
holes in the affected floor beam upper chords, do a surface HFEC
inspection of the upper deck floor beam upper chords and detailed
inspection for cracks on the vertical flange, in accordance with
Part 8 of the Accomplishment Instructions of Boeing Alert Service
Bulletin 747-53A2688, Revision 2, dated August 21, 2014. If any
crack is found during any inspection required by this paragraph,
before further flight, repair using a method approved in accordance
with the procedures specified in paragraph (o) of this AD. Repeat
the inspections thereafter at the applicable time specified in table
6 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service
Bulletin 747-53A2688, Revision 2, dated August 21, 2014.
(m) Exceptions to Service Information Specifications
(1) Where Boeing Alert Service Bulletin 747-53A2688, Revision 2,
dated August 21, 2014, specifies a compliance time ``after the
Revision 2 date of this service bulletin,'' this AD requires
compliance within the specified compliance time after the effective
date of this AD.
(2) Where Boeing Alert Service Bulletin 747-53A2688, Revision 2,
dated August 21, 2014; specifies to contact Boeing for certain
procedures: Do the specified actions before further flight using a
method approved in accordance with the procedures specified in
paragraph (o) of this AD.
(3) Where table 2 or table 4 of paragraph 1.E., ``Compliance,''
of Boeing Alert Service Bulletin 747-53A2688, Revision 2, dated
August 21, 2014, specifies to contact Boeing for inspections and
compliance times: Before further flight, contact the Manager,
Seattle Aircraft Certification Office (ACO), FAA, for inspections
and compliance times and accomplish the inspections at the given
times.
(4) Where Boeing Alert Service Bulletin 747-53A2688, Revision 2,
dated August 21, 2014, specifies a compliance time ``after the
Revision 1 date of this service bulletin,'' this AD requires
compliance within the specified compliance time after December 10,
2013 (the effective date of AD 2013-22-11).
(n) Credit for Previous Actions
(1) This paragraph restates the requirements of paragraph (o) of
AD 2013-22-11, with new reference to paragraph (h) of this AD. This
paragraph provides credit for the actions required by paragraphs (g)
and (h) of this AD, if those actions were performed before December
10, 2013 (the effective date of AD 2013-22-11), using Boeing Alert
Service Bulletin 747-53A2688, dated August 21, 2008, which was
incorporated by reference in AD 2009-10-16, Amendment 39-15901 (74
FR 22424, May 13, 2009).
(2) This paragraph provides credit for the actions required by
paragraphs (g) through (k) of this AD, if those actions were
performed before the effective date of this AD using Boeing Alert
Service Bulletin 747-53A2688, Revision 1, dated September 19, 2012,
which was incorporated by reference in AD 2013-22-11.
(o) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Seattle ACO, FAA, has the authority to approve
AMOCs for this AD, if requested using the procedures found in 14 CFR
39.19. In accordance with 14 CFR 39.19, send your request to your
principal inspector or local Flight Standards District Office, as
appropriate. If sending information directly to the manager of the
ACO, send it to the attention of the person identified in paragraph
(p) of this AD. Information may be emailed to: <a href="/cdn-cgi/l/email-protection#d9e0f4989794f48abcb8adadb5bcf4989a96f49894969af48bbca8acbcaaadaa99bfb8b8f7beb6af"><span class="__cf_email__" data-cfemail="6d54402c2320403e080c19190108402c2e22402c20222e403f081c18081e191e2d0b0c0c430a021b">[email protected]</span></a>.
(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, modification, or alteration 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. To be approved, the
repair method, modification deviation, or alteration deviation must
meet the certification basis of the airplane and the approval must
specifically refer to this AD.
(4) AMOCs approved for AD 2013-22-11 are approved as AMOCs for
the corresponding provisions of paragraphs (g) through (k) of this
AD.
(p) Related Information
For more information about this AD, contact Nathan Weigand,
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft
Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-
3356; phone: 425-917-6428; fax: 425-917-6590; email:
<a href="/cdn-cgi/l/email-protection#a0eec1d4c8c1ce8ef08ef7c5c9c7c1cec4e0c6c1c18ec7cfd6"><span class="__cf_email__" data-cfemail="8cc2edf8e4ede2a2dca2dbe9e5ebede2e8cceaededa2ebe3fa">[email protected]</span></a>.
(q) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(i) Boeing Alert Service Bulletin 747-53A2688, Revision 2, dated
August 21, 2014.
(ii) Reserved.
(3) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; phone: 206-544-
5000, extension 1; fax: 206-766-5680; Internet <a href="https://www.myboeingfleet.com">https://www.myboeingfleet.com</a>.
(4) You may view this service information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For
information on the availability of this material at the FAA, call
425-227-1221.
(5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: <a href="http://www.archives.gov/federal-register/cfr/ibr-locations.html">http://www.archives.gov/federal-register/cfr/ibr-locations.html</a>.
Issued in Renton, Washington, on March 30, 2016.
Victor Wicklund,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2016-08271 Filed 4-12-16; 8:45 am]
BILLING CODE 4910-13-P
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Retrieved: Apr 6, 2026
Rights: U.S. Government Public Domain
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