AD 2015-23-11

[Federal Register Volume 80, Number 224 (Friday, November 20, 2015)]
[Rules and Regulations]
[Pages 72573-72576]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2015-28891]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-1266; Directorate Identifier 2014-NM-151-AD; 
Amendment 39-18327; AD 2015-23-11]
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 adopting a new airworthiness directive (AD) for certain 
The Boeing Company Model 747-100, 747-100B, 747-100B SUD, 747-200B, 
747-300, 747SR, and 747SP series airplanes. This AD was prompted by an 
evaluation by the design approval holder (DAH) indicating that certain 
fuselage skin lap joints are subject to widespread fatigue damage 
(WFD). This AD requires repetitive post-modification inspections for 
cracking of the skin or internal doubler along the edge fastener rows 
of the modification, and repair if necessary. We are issuing this AD to 
detect and correct fatigue cracking in certain fuselage skin lap 
joints, which could result in rapid depressurization of the airplane.

DATES: This AD is effective December 28, 2015.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of December 28, 
2015.

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 <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-2015-1266.

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-
1266; 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, 
1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6428; fax: 
425-917-6590; email: <a href="/cdn-cgi/l/email-protection#a0cec1d4c8c1ce8ed08ed7c5c9c7c1cec4e0c6c1c18ec7cfd6"><span class="__cf_email__" data-cfemail="cda3acb9a5aca3e3bde3baa8a4aaaca3a98dabacace3aaa2bb">[email&#160;protected]</span></a>.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to certain The Boeing Company 
Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-300, 747SR, and 
747SP series airplanes. The NPRM published in the Federal Register on 
May 5, 2015 (80 FR 25630). The NPRM was prompted by an evaluation by 
the DAH indicating that certain fuselage skin lap joints are subject to 
WFD. The NPRM proposed to require repetitive post-modification 
inspections for cracking of the skin or internal doubler along the edge 
fastener rows of the modification, and repair if necessary. We are 
issuing this AD to detect and correct fatigue cracking in certain 
fuselage skin lap joints, which could result in rapid depressurization 
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 (80 
FR 25630, May 5, 2015) and the FAA's response to each comment.

Request To Remove Warranty Statement

    Boeing requested that we remove the statement that ``some of the 
costs of this proposed AD may be covered under warranty'' in the Costs 
of Compliance section of the NPRM (80 FR 25630, May 5, 2015). Boeing 
stated that the actions in the NPRM are not covered by warranty.
    We agree with the commenter's request. We have revised the Costs of 
Compliance section of this final rule accordingly.

Request To Revise Paragraph Headings

    Boeing requested that we revise the headings of paragraphs (g), 
(h), (j), and (k) of the proposed AD (80 FR 25630, May 5, 2015) by 
removing reference to the inspections as ``repetitive'' or ``initial.'' 
Boeing stated that these revisions will provide consistency among 
paragraph headings because paragraphs (g), (j), and (k) of the proposed 
AD do not have an initial inspection program, yet paragraph (h) of the 
proposed AD has only an initial inspection.
    We acknowledge the commenter's concern and agree to clarify the 
headings. We do not presume that the term ``repetitive'' necessarily 
excludes the initial action. An action cannot be repeated without 
accomplishment of the initial action. In addition, in many ADs we use 
the term ``repetitive'' actions for paragraphs that include the initial 
action and repetitive actions. Paragraphs (g), (j), and (k) of this AD 
include both a sentence specifying the initial inspection and a 
sentence specifying the repetitive inspections. We have not changed 
this AD in this regard.

Request To Clarify Compliance Time

    Boeing requested that we clarify the compliance time in paragraphs 
(g), (h), (j), and (k) of the proposed AD (80 FR

[[Page 72574]]

25630, May 5, 2015) by revising ``at the applicable time'' to ``at the 
applicable time and repeat intervals.'' Boeing stated that these 
revisions would clarify that the applicable time also includes the 
repeat intervals per Boeing Alert Service Bulletin 747-53A2367, 
Revision 5, dated July 8, 2014.
    We do not agree to combine the initial inspection and the 
repetitive inspection times into one statement because ADs typically 
call out initial inspections and repetitive inspections in separate 
sentences. Paragraph (h) of this AD specifies only an initial 
inspection. Paragraphs (g), (j), and (k) of this AD specifies an 
initial inspection and states that the repetitive inspections are for 
the unrepaired areas, which are to be done at the applicable times 
specified in Boeing Alert Service Bulletin 747-53A2367, Revision 5, 
dated July 8, 2014. We have not changed this AD in this regard.

Request To Delete the Unrepaired Area Statement From Paragraphs (g) (j) 
and (k) of the Proposed AD (80 FR 25630, May 5, 2015)

    Boeing requested that we delete the last sentence in paragraphs 
(g), (j), and (k) of the proposed AD (80 FR 25630, May 5, 2015), which 
states ``In unrepaired areas, repeat the . . . inspections for cracks . 
. . .'' Boeing stated that the sentence is confusing as the unrepaired 
area case is actually for no cracks found in the modification area 
after doing the inspection as specified in the applicable tables 3, 5, 
and 6 of Boeing Alert Service Bulletin 747-53A2367, Revision 5, dated 
July 8, 2014. Boeing explained that the proposed AD wording may cause 
confusion when information is provided in a different format than the 
service bulletin tables.
    We do not agree with the commenter's request because the text ``in 
unrepaired areas'' matches the text in Boeing Alert Service Bulletin 
747-53A2367, Revision 5, dated July 8, 2014. Paragraphs (g), (j), and 
(k) of this AD specify doing actions at the applicable time specified 
in tables 3, 5, and 6 of paragraph 1.E., ``Compliance,'' of Boeing 
Alert Service Bulletin 747-53A2367, Revision 5, dated July 8, 2014. In 
these tables, the compliance time is specified for the actions required 
for the unrepaired area. We have not revised this AD in this regard.

Request To Combine Paragraphs

    Boeing requested that we combine paragraphs (h) and (i) of the 
proposed AD (80 FR 25630, May 5, 2015) by deleting paragraph (i) of the 
proposed AD and revising paragraph (h) of the proposed AD from ``at the 
applicable time'' to ``at the applicable time and repeat intervals.'' 
Boeing explained that it is confusing to have separate paragraphs 
address initial and repetitive inspections for a particular aircraft as 
both initial and repetitive inspections are addressed within table 4 of 
Boeing Alert Service Bulletin 747-53A2367, Revision 5, dated July 8, 
2014.
    We acknowledge that table 4 of Boeing Alert Service Bulletin 747-
53A2367, Revision 5, dated July 8, 2014, contains compliance times for 
both initial and repetitive inspections. However, we do not agree with 
the commenter's request because the AD includes separate paragraphs in 
order to clarify the repetitive inspection intervals. For the initial 
inspections, table 4 of paragraph 1.E., ``Compliance,'' of Boeing Alert 
Service Bulletin 747-53A2367, Revision 5, dated July 8, 2014, specifies 
two crack conditions, which are based on the number of fight cycles on 
the airplane since stringer 6 external doublers were installed. To aid 
the operators in determining which repetitive inspection(s) they are 
required to do, this AD provides the repetitive inspections (as 
restated from the NPRM (80 FR 25630, May 5, 2015)), depending on the 
applicable condition, in separate repetitive inspection paragraphs 
(paragraphs (i)(1) and (i)(2) of this AD). We have not changed this AD 
in this regard.

Request To Revise External Inspection Wording

    Boeing requested that we remove the word ``external'' from 
paragraph (h) of the proposed AD (80 FR 25630, May 5, 2015), which 
specified ``external detailed, low frequency eddy current, and high 
frequency eddy current inspections.'' Boeing explained that if 
paragraphs (h) and (i) of the proposed AD are combined, both external 
and internal detailed inspections are required. Boeing stated that 
removing ``external'' from the inspection direction would therefore 
cover all airplane conditions.
    As stated previously, we do not agree to combine paragraphs (h) and 
(i) of this AD into one paragraph. Therefore, the terminology in 
paragraph (h) of this AD matches Boeing Alert Service Bulletin 747-
53A2367, Revision 5, dated July 8, 2014, which specifies doing external 
detailed, low frequency eddy current (LFEC), and high frequency eddy 
current (HFEC) inspections for cracks. We have not changed this AD in 
this regard.

Request To Revise Headings of Paragraphs (h), (i), and (j) of the 
Proposed AD (80 FR 25630, May 5, 2015)

    Boeing requested that we revise the headings of paragraphs (h), 
(i), and (j) of the proposed AD (80 FR 25630, May 5, 2015) by adding a 
reference to the applicable service information. Boeing stated that 
these changes will add consistency among paragraphs (h), (i), and (j) 
of the proposed AD in identifying an installed external doubler 
modification.
    We agree with the commenter's request. We have revised the headings 
of paragraphs (h), (i), and (j) of this AD accordingly.

Request To Correct Typographical Error

    Boeing noted that a phrase describing the major action in paragraph 
(j) of the proposed AD (80 FR 25630, May 5, 2015) was duplicated and 
asked that we correct this.
    We agree with the commenter's request. We have revised paragraph 
(j) of this AD accordingly.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
this AD with the changes described previously and minor editorial 
changes. We have determined that these minor changes:
    <bullet> [Agr]re consistent with the intent that was proposed in 
the NPRM (80 FR 25630, May 5, 2015) for correcting the unsafe 
condition; and
    <bullet> Do not add any additional burden upon the public than was 
already proposed in the NPRM (80 FR 25630, May 5, 2015).
    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 747-53A2367, Revision 5, 
dated July 8, 2014. This service information describes procedures for 
inspections and repair for cracks in the skin and doublers along the 
edge fastener rows of modifications in the fuselage. 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 of this AD.

[[Page 72575]]

Costs of Compliance

    We estimate that this AD affects 50 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
----------------------------------------------------------------------------------------------------------------
Post-modification inspection...  124 work-hours x $85                 $0   $10,540 per         $527,000 per
                                  per hour = $10,540 per                    inspection cycle.   inspection
                                  inspection cycle.                                             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

    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 adding the following new airworthiness 
directive (AD):

2015-23-11 The Boeing Company: Amendment 39-18327; Docket No. FAA-
2015-1266; Directorate Identifier 2014-NM-151-AD.

(a) Effective Date

    This AD is effective December 28, 2015.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to The Boeing Company Model 747-100, 747-100B, 
747-100B SUD, 747-200B, 747-300, 747SR, and 747SP series airplanes, 
certificated in any category, as identified in Boeing Alert Service 
Bulletin 747-53A2367, Revision 5, dated July 8, 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 fuselage skin lap joints are subject 
to widespread fatigue damage. We are issuing this AD to detect and 
correct fatigue cracking in certain fuselage skin lap joints, which 
could result in rapid depressurization of the airplane.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Repetitive Post-Modification Inspections for Airplane Groups 1 
Through 3, 7, and 8

    For airplanes identified as Groups 1 through 3, 7, and 8 in 
Boeing Alert Service Bulletin 747-53A2367, Revision 5, dated July 8, 
2014: Except as provided by paragraph (m) of this AD, at the 
applicable time specified in table 3 of paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 747-53A2367, 
Revision 5, dated July 8, 2014, do internal detailed and surface 
high frequency eddy current (HFEC) inspections for cracks in the 
skin and internal doubler along the edge fastener rows of the 
modification, in accordance with the Accomplishment Instructions of 
Boeing Alert Service Bulletin 747-53A2367, Revision 5, dated July 8, 
2014. In unrepaired areas, repeat the internal detailed and surface 
HFEC inspections for cracks in the skin or internal doubler along 
the edge fastener rows of the modification thereafter at the 
applicable intervals specified in paragraph 1.E., ``Compliance,'' of 
Boeing Alert Service Bulletin 747-53A2367, Revision 5, dated July 8, 
2014.

(h) Initial Post-Modification Inspections for Airplane Groups 4 Through 
6, and 9 Through 11, With External Doublers Installed as Specified in 
Boeing Service Bulletin 747-53-2272

    For airplanes identified as Groups 4 through 6, and 9 through 
11, in Boeing Alert Service Bulletin 747-53A2367, Revision 5, dated 
July 8, 2014, with external doublers installed as specified in 
Boeing Service Bulletin 747-53-2272: Except as provided by paragraph 
(m) of this AD, at the applicable time specified in table 4 of 
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 
747-53A2367, Revision 5, dated July 8, 2014, do external detailed, 
low frequency eddy current (LFEC), and HFEC inspections for cracks 
in the skin and external doubler, in accordance with the 
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2367, Revision 5, dated July 8, 2014.

(i) Repetitive Post-Modification Inspections for Airplane Groups 4 
Through 6, and 9 Through 11 With External Doublers Installed as 
Specified in Boeing Service Bulletin 747-53-2272

    For airplanes with no crack findings during the inspections 
required by paragraph (h) of this AD: Do the applicable actions 
required by paragraphs (i)(1) and (i)(2) of this AD.
    (1) For airplanes with less than 15,000 flight cycles since 
stringer 6 external doublers were installed, as specified in Boeing 
Service Bulletin 747-53-2272: At the applicable intervals specified 
in table 4 of

[[Page 72576]]

paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 
747-53A2367, Revision 5, dated July 8, 2014, in unrepaired areas, 
repeat the external detailed and LFEC inspections for cracks in the 
skin, and the external detailed and HFEC inspections for cracks in 
the external doubler, in accordance with the Accomplishment 
Instructions of Boeing Alert Service Bulletin 747-53A2367, Revision 
5, dated July 8, 2014.
    (2) For airplanes with 15,000 or more flight cycles since the 
stringer 6 external doublers were installed, as specified in Boeing 
Service Bulletin 747-53-2272: At the applicable intervals specified 
in table 4 of paragraph 1.E., ``Compliance,'' of Boeing Alert 
Service Bulletin 747-53A2367, Revision 5, dated July 8, 2014, in 
unrepaired areas, do external detailed and LFEC inspections for 
cracks in the skin; and do internal and external detailed and HFEC 
inspections for cracks in the skin and external doubler; in 
accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin 747-53A2367, Revision 5, dated July 8, 2014.

(j) Repetitive Post-Modification Inspections for Airplane Groups 4 
Through 6, and 9 Through 11 With External Doublers Installed as 
Specified in Boeing Alert Service Bulletin 747-53A2367

    For airplanes identified as Groups 4 through 6, and 9 through 
11, in Boeing Alert Service Bulletin 747-53A2367, Revision 5, dated 
July 8, 2014, with external doublers installed as specified in 
Boeing Alert Service Bulletin 747-53A2367: Except as provided by 
paragraph (m) of this AD, at the applicable time specified in table 
5 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service 
Bulletin 747-53A2367, Revision 5, dated July 8, 2014, do internal 
detailed and surface HFEC inspections for cracks in the skin and 
internal doubler along the edge fastener rows of the modification, 
in accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin 747-53A2367, Revision 5, dated July 8, 2014. In 
unrepaired areas, repeat the internal detailed and surface HFEC 
inspections for cracks in the skin or internal doubler along the 
edge fastener rows of the modification thereafter at the applicable 
interval specified in paragraph 1.E., ``Compliance,'' of Boeing 
Alert Service Bulletin 747-53A2367, Revision 5, dated July 8, 2014.

(k) Repetitive Post-Modification Inspections for Airplane Groups 12 and 
13

    For airplanes identified as Groups 12 and 13 in Boeing Alert 
Service Bulletin 747-53A2367, Revision 5, dated July 8, 2014: Except 
as provided by paragraph (m) of this AD, at the applicable time 
specified in table 6 of paragraph 1.E., ``Compliance,'' of Boeing 
Alert Service Bulletin 747-53A2367, Revision 5, dated July 8, 2014, 
do internal detailed and surface HFEC inspections for cracks in the 
skin and internal doubler along the edge fastener rows of the 
modification, in accordance with the Accomplishment Instructions of 
Boeing Alert Service Bulletin 747-53A2367, Revision 5, dated July 8, 
2014. In unrepaired areas, repeat the internal detailed and surface 
HFEC inspections for cracks in the skin or internal doubler along 
the edge fastener rows of the modification thereafter at the 
applicable interval specified in paragraph 1.E., ``Compliance,'' of 
Boeing Alert Service Bulletin 747-53A2367, Revision 5, dated July 8, 
2014.

(l) Corrective Actions

    If any cracking is found during any inspection required by this 
AD: Before further flight, repair the cracking using a method 
approved in accordance with the procedures specified in paragraph 
(n) of this AD.

(m) Exception to Boeing Alert Service Bulletin 747-53A2367, Revision 5, 
Dated July 8, 2014

    Where paragraph 1.E., ``Compliance,'' of Boeing Alert Service 
Bulletin 747-53A2367, Revision 5, dated July 8, 2014, specifies a 
compliance time ``after the Revision 5 date of this service 
bulletin,'' this AD requires compliance within the specified 
compliance time ``after the effective date of this AD.''

(n) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Seattle Aircraft Certification Office (ACO), 
FAA, has the authority to approve AMOCs for this AD, if requested 
using the procedures found in 14 CFR 39.19. In accordance with 14 
CFR 39.19, send your request to your principal inspector or local 
Flight Standards District Office, as appropriate. If sending 
information directly to the manager of the ACO, send it to the 
attention of the person identified in paragraph (o) of this AD. 
Information may be emailed to: <a href="/cdn-cgi/l/email-protection#f4cdd9b5bab9d9a7919580809891d9b5b7bbd9b5b9bbb7d9a691858191878087b4929595da939b82"><span class="__cf_email__" data-cfemail="340d19757a7919675155404058511975777b1975797b77196651454151474047745255551a535b42">[email&#160;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.

(o) Related Information

    For more information about this AD, contact Nathan Weigand, 
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft 
Certification Office, 1601 Lind Avenue SW., Renton, WA 98057-3356; 
phone: 425-917-6428; fax: 425-917-6590; email: 
<a href="/cdn-cgi/l/email-protection#7e101f0a161f10500e50091b17191f101a3e181f1f50191108"><span class="__cf_email__" data-cfemail="c1afa0b5a9a0afefb1efb6a4a8a6a0afa581a7a0a0efa6aeb7">[email&#160;protected]</span></a>.

(p) 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 747-53A2367, Revision 5, dated 
July 8, 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; telephone 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 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 November 4, 2015.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-28891 Filed 11-19-15; 8:45 am]
 BILLING CODE 4910-13-P