Document ID: FAA-2015-1270-0006
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: The Boeing Company Airplanes
Posted Date: 2016-03-01T05:00Z

[Federal Register Volume 81, Number 40 (Tuesday, March 1, 2016)]
[Rules and Regulations]
[Pages 10468-10472]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-03884]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-1270; Directorate Identifier 2014-NM-222-AD; 
Amendment 39-18412; AD 2016-04-18]
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, -200B, -200C, -200F, -300, -400, -
400D, and -400F series airplanes. This AD was prompted by reports of 
significant fuselage skin damage at certain parts of the dorsal 
fairing, due to wear from the dorsal fairing. This AD requires 
repetitive detailed inspections for wear and cracks of the fuselage 
skin under the dorsal fairing, and related investigative and corrective 
actions if necessary. This AD also requires repetitive post-repair 
external surface high frequency eddy current inspections of the blended 
areas of the skin and detailed inspections of the unrepaired areas, and 
related investigative and corrective actions if necessary. We are 
issuing this AD to detect and correct fuselage skin damage of the 
dorsal fairing area, which could result in skin cracking and consequent 
depressurization of the airplane.

DATES: This AD is effective April 5, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of April 5, 
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 https://www.myboeingfleet.com. You may view this referenced service information 
at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., 
Renton, WA. For information on the availability of this material at the 
FAA, call 425-227-1221. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
1270.

[[Page 10469]]

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
1270; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this AD, the regulatory evaluation, any comments received, and 
other information. The address for the Docket Office (phone: 800-647-
5527) is Docket Management Facility, U.S. Department of Transportation, 
Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 
New Jersey Avenue SE., Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Nathan Weigand, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office 
(ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-
6428; fax: 425-917-6590; email: nathan.p.weigand@faa.gov.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to certain The Boeing Company 
Model 747-100, -200B, -200C, -200F, -300, -400, -400D, and -400F series 
airplanes. The NPRM published in the Federal Register on May 5, 2015 
(80 FR 25627). The NPRM was prompted by reports of significant fuselage 
skin damage at certain parts of the dorsal fairing, due to wear from 
the dorsal fairing. The NPRM proposed to require repetitive detailed 
inspections for wear and cracks of the fuselage skin under the dorsal 
fairing, and related investigative and corrective actions if necessary. 
The NPRM also proposed to require repetitive post-repair external 
surface high frequency eddy current inspections of the blended areas of 
the skin and detailed inspections of the unrepaired areas, and related 
investigative and corrective actions if necessary. We are issuing this 
AD to detect and correct fuselage skin damage of the dorsal fairing 
area, which could result in skin cracking and consequent 
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 25627, May 5, 2015) and the FAA's response to each comment.

Request To Clarify Exclusion of Certain Post-Modification Inspections

    Boeing asked that we clarify paragraph (i) of the proposed AD (80 
FR 25627, May 5, 2015). Boeing stated that paragraph (i) of the 
proposed AD correctly states that post-modification inspections would 
not be required by the AD, but the proposed AD does not clearly state 
that those inspections are still required per operating rules, which 
has caused confusion for operators in the past. Boeing suggested that 
we revise the proposed AD to state that post-modification inspections 
are already required by 14 CFR 121.1109(c)(2) and 14 CFR 129.109(b)(2).
    We agree to clarify paragraph (i) of this AD. We have revised 
paragraph (i) of this AD to clarify that the post-modification 
inspections are airworthiness limitations that are required by 
maintenance and operational rules; therefore, these inspections are not 
required by this AD.

Request To Require Post-Modification Inspections Currently Excluded

    United Airlines (UAL) asked that the post-modification inspections 
excluded from the requirements of paragraph (i) of the proposed AD (80 
FR 25627, May 5, 2015) instead be required. UAL stated that there is a 
conflict between the proposed AD and tables 3, 6, and 7 of paragraph 
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2876, 
dated October 22, 2014. UAL noted that the post-modification 
inspections specified in tables 3, 6, and 7 are not required in 
paragraph (i) of the proposed AD; however, compliance tables 1 and 2 of 
paragraph 1.E. of the service information instruct operators to 
accomplish those post-modification inspections using tables 3, 6, and 7 
of paragraph 1.E.
    UAL added that Note 1 to paragraph (i) of the proposed AD (80 FR 
25627, May 5, 2015) specifies that the post-modification inspections 
may be used in support of compliance with section 121.1109(c)(2) or 
129.109(b)(2) of the Federal Aviation Regulations (14 CFR 
121.1109(c)(2) or 14 CFR 129.109(b)(2)). UAL pointed out that sections 
121.1109(c)(2) and 129.109(b)(2) require operators to inspect damage-
tolerant reinforcing repairs to fatigue critical structures; however, 
rub strips protect the skin from contact with the dorsal fairing and 
are not considered a reinforcing repair.
    We disagree with the commenter's request to require post-
modification inspections; however we acknowledge there is a conflict. 
Paragraph (i) of this AD states that tables 3, 6, and 7 of paragraph 
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2876, 
dated October 22, 2014, specify post-modification airworthiness 
limitation inspections in compliance to 14 CFR 25.571(a)(3) at the 
modified locations, which support compliance with 14 CFR 121.1109(c)(2) 
or 129.109(b)(2). These two regulations require damage-tolerance-based 
inspections to be added as airworthiness limitations in order to 
prevent the adverse effects of repairs, alterations, and modifications. 
The rub strips are considered a modification to fatigue-critical 
structure and meet the intent of section 121.1109(c)(2) or 
129.109(b)(2) of the Federal Aviation Regulations. Where compliance 
tables 1 and 2 of paragraph 1.E. of Boeing Alert Service Bulletin 747-
53A2876, dated October 22, 2014, instruct operators to accomplish post-
modification inspections using tables 3, 6, and 7 of paragraph 1.E., 
``Compliance,'' of the service information, those post-modification 
inspections are not required by this AD. We have added a reference to 
paragraph (i) of this AD in paragraphs (g) and (h) of this AD to 
clarify tables 3, 6, and 7 of paragraph 1.E., ``Compliance,'' of the 
service information are not required by paragraphs (g) and (h) of this 
AD.

Request To Delete Certain Actions

    UAL asked that we delete Options 1 and 2 of table 3 of paragraph 
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2876, 
dated October 22, 2014. UAL stated that Option 1 is for post-
modification of blend-out repairs without a rub strip installed, and 
added that table 3 is for post-modification inspections for airplanes 
with a rub strip previously installed. UAL added that the Option 2 
blend-out repair is redundant information if the Option 1 action is 
deleted.
    We do not agree with the commenter's request. Paragraph (i) of this 
AD specifies that table 3, as well as tables 6 and 7, are not required 
by this AD. Therefore, no further change to the AD is necessary in this 
regard.

Request To Add Certain Requirements

    UAL asked that instructions be added to Part 3 of the Work 
Instructions of Boeing Alert Service Bulletin 747-53A2876, dated 
October 22, 2014, to apply Teflon coating on top of the rub strips. UAL 
stated that this will further enhance protection and will reduce wear 
and cracking of the rub strip due to contact with the dorsal fairing.
    We do not agree with the commenter's request. Boeing Alert Service 
Bulletin 747-53A2876, dated October 22, 2014

[[Page 10470]]

(and the associated repairs and modifications), was coordinated with 
the FAA before it was issued. This coordination included a damage-
tolerance analysis supporting the inspection thresholds and intervals 
specified in the service information. Operators preferring to use a 
method other than that specified in the referenced service information 
may request approval for an alternative method of compliance (AMOC) and 
provide supporting data, which, if approved, may be used instead of the 
procedures specified in the service information. We have made no change 
to the AD in this regard.

Request To Add Exception to the Proposed AD (80 FR 25627, May 5, 2015)

    United Parcel Service (UPS) asked that we add another exception to 
paragraph (j) of the proposed AD (80 FR 25627, May 5, 2015) to clarify 
that Section 3.B., Part 6, sub-step 2, of Boeing Alert Service Bulletin 
747-53A2876, dated October 22, 2014, is not required. UPS stated that 
paragraph (g) of the proposed AD requires operators to perform 
applicable related investigative and corrective actions, in accordance 
with the Accomplishment Instructions of Boeing Alert Service Bulletin 
747-53A2876, dated October 22, 2014. UPS added that there is an 
inconsistency in those Accomplishment Instructions. UPS noted that 
tables 2 and 3 of paragraph 1.E., ``Compliance,'' of Boeing Alert 
Service Bulletin 747-53A2876, dated October 22, 2014, specify 
performing the actions in Parts 6 and 7, and those sections include 
instructions labeled ``Required for Compliance'' (RC). UPS stated that 
performing the same action in both Parts 6 and 7 results in a 
duplication of work. UPS added that it submitted a service request to 
Boeing and asked for clarification on this duplication of work. UPS 
stated that Boeing agreed that corrective actions could result in 
duplication and that it would evaluate the steps in the Work 
Instructions and clarify them as necessary.
    We do not agree with the commenter's request. Boeing Alert Service 
Bulletin 747-53A2876, dated October 22, 2014, specifies that if, during 
the accomplishment of Part 6, obtaining the gap identified in Condition 
6 is not possible, the operator must perform the actions associated 
with Condition 7, including trimming and re-shimming the dorsal fin 
fairing to obtain that gap by following the instructions in Part 7 of 
Boeing Alert Service Bulletin 747-53A2876, dated October 22, 2014. 
After this is done, the operator must re-measure, as specified in Part 
7, to make sure the gap dimensions are correct. Following 
accomplishment of Part 7, the operator must complete the actions in 
Part 6 at the repetitive intervals specified in table 2 or table 3 of 
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-
53A2876, dated October 22, 2014 (table 2 is required by paragraph (g) 
of this AD; table 3 specifies post-modification airworthiness 
limitation inspections in compliance to 14 CFR 25.571(a)(3) at the 
modified locations, which support compliance with 14 CFR 121.1109(c)(2) 
or 129.109(b)(2)). In light of these facts, we have determined that 
there is no duplication of work. We have not changed the AD in this 
regard.

Change To the Proposed AD (80 FR 25627, May 5, 2015)

    Paragraph (g) of this AD refers to initial and repetitive 
inspections of the unrepaired structure. Paragraph (h) of this AD 
refers to doing the inspections specified at the applicable times in 
tables 4 and 5 of paragraph 1.E., ``Compliance,'' of Boeing Alert 
Service Bulletin 747-53A2876, dated October 22, 2014. These tables 
include compliance times for both the repaired and unrepaired areas. 
The proposed AD (80 FR 25627, May 5, 2015) specified to require the 
inspections in both paragraphs (g) and (h) of this AD, since there is 
no terminating action identified in paragraph (h) of this AD. We have 
determined that further clarification of these inspection requirements 
is necessary. Therefore, we have added a sentence to paragraph (h) of 
this AD clarifying that the inspections required by paragraph (h) of 
this AD do not terminate the inspections required by paragraph (g) of 
this AD.

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:
     Are consistent with the intent that was proposed in the 
NPRM (80 FR 25627, May 5, 2015) for correcting the unsafe condition; 
and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (80 FR 25627, 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 747-53A2876, dated 
October 22, 2014. This service information describes procedures for 
repetitive inspections of the fuselage skin under the dorsal fairing, 
the blended areas of the skin, and unrepaired areas, and related 
investigative and corrective actions, if necessary. 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.

Explanation of ``RC'' Steps in Service Information

    The FAA worked in conjunction with industry, under the 
Airworthiness Directive Implementation Aviation Rulemaking Committee 
(ARC), to enhance the AD system. One enhancement was a new process for 
annotating which steps in the service information are required for 
compliance with an AD. Differentiating these steps from other tasks in 
the service information is expected to improve an owner's/operator's 
understanding of crucial AD requirements and help provide consistent 
judgment in AD compliance. The steps identified as Required for 
Compliance (RC) in any service information identified previously have a 
direct effect on detecting, preventing, resolving, or eliminating an 
identified unsafe condition.
    For service information that contains steps that are labeled as RC, 
the following provisions apply: (1) The steps labeled as RC, including 
substeps under an RC step and any figures identified in an RC step, 
must be done to comply with the AD, and an AMOC is required for any 
deviations to RC steps, including substeps and identified figures; and 
(2) steps not labeled as RC may be deviated from using accepted methods 
in accordance with the operator's maintenance or inspection program 
without obtaining approval of an AMOC, provided the RC steps, including 
substeps and identified figures, can still be done as specified, and 
the airplane can be put back in an airworthy condition.

Costs of Compliance

    We estimate that this AD affects 93 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

[[Page 10471]]

                                                 Estimated costs
----------------------------------------------------------------------------------------------------------------
                                                                                                Cost on U.S.
          Action                  Labor cost          Parts cost       Cost per product          operators
----------------------------------------------------------------------------------------------------------------
Inspections...............  Up to 15 work-hours x              $0   Up to $1,275 per       Up to $118,575 per
                             $85 per hour =                          inspection cycle.      inspection cycle.
                             $1,275.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that will 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):

2016-04-18 The Boeing Company: Amendment 39-18412 ; Docket No. FAA-
2015-1270; Directorate Identifier 2014-NM-222-AD.

(a) Effective Date

    This AD is effective April 5, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to The Boeing Company Model 747-100, -200B, -
200C, -200F, -300, -400, -400D, and -400F series airplanes; 
certificated in any category, as identified in Boeing Alert Service 
Bulletin 747-53A2876, dated October 22, 2014.

(d) Subject

    Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Unsafe Condition

    This AD was prompted by reports of significant fuselage skin 
damage at the dorsal fairing forward of station (STA) 2280 due to 
wear from the dorsal fairing. We are issuing this AD to detect and 
correct fuselage skin damage of the dorsal fairing area, which could 
result in skin cracking and consequent depressurization of the 
airplane.

(f) Compliance

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

(g) Inspections and Repair

    At the applicable time specified in tables 1 and 2 of paragraph 
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2876, 
dated October 22, 2014, except as provided by paragraph (j)(1) of 
this AD, do a detailed inspection of the fuselage skin under the 
dorsal fairing for wear or cracks, and do all applicable related 
investigative and corrective actions, in accordance with the 
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2876, dated October 22, 2014, except as provided by paragraph (i) 
of this AD and except as required by paragraph (j)(2) of this AD. Do 
all applicable related investigative and corrective actions at the 
time specified in paragraph 1.E., ``Compliance,'' of Boeing Alert 
Service Bulletin 747-53A2876, dated October 22, 2014. Repeat the 
applicable inspections of the fuselage skin thereafter at the 
applicable times specified in paragraph 1.E., ``Compliance,'' of 
Boeing Alert Service Bulletin 747-53A2876, dated October 22, 2014.

(h) Post-Repair Inspections

    At the applicable time specified in tables 4 and 5 of paragraph 
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2876, 
dated October 22, 2014, except as provided by paragraph (j)(1) of 
this AD, do an external surface high frequency eddy current 
inspection of the blended areas of the skin and a detailed 
inspection of the unrepaired areas, and do all applicable related 
investigative and corrective actions, in accordance with Part 8 of 
the Accomplishment Instructions of Boeing Alert Service Bulletin 
747-53A2876, dated October 22, 2014, except as provided by paragraph 
(i) of this AD and except as required by paragraph (j)(2) of this 
AD. Do all applicable related investigative and corrective actions 
at the time specified in paragraph 1.E., ``Compliance,'' of Boeing 
Alert Service Bulletin 747-53A2876, dated October 22, 2014. Repeat 
the applicable inspections of the blended areas of the skin 
thereafter at the applicable times specified in paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 747-53A2876, dated 
October 22, 2014. Accomplishing the inspections required by this 
paragraph does not terminate the inspections required by paragraph 
(g) of this AD.

(i) Post-Modification Inspections

    Tables 3, 6, and 7 of paragraph 1.E., ``Compliance,'' of Boeing 
Alert Service Bulletin 747-53A2876, dated October 22, 2014, specify 
post-modification airworthiness limitation inspections in compliance 
to 14 CFR 25.571(a)(3) at the modified locations, which support 
compliance with 14 CFR 121.1109(c)(2) or 129.109(b)(2). As 
airworthiness limitations, these inspections are required by 
maintenance and operational rules. It is therefore unnecessary to 
mandate them in this AD. Deviations from these inspections require 
FAA approval, but do not require an alternative method of 
compliance.

(j) Exceptions to Service Information Specifications

    (1) Where Boeing Alert Service Bulletin 747-53A2876, dated 
October 22, 2014, specifies a compliance time ``after the

[[Page 10472]]

Original Issue date of this service bulletin,'' this AD requires 
compliance within the specified compliance time after the effective 
date of this AD.
    (2) Although Boeing Alert Service Bulletin 747-53A2876, dated 
October 22, 2014, specifies to contact Boeing for repair data, and 
specifies that action as ``RC'' (Required for Compliance), this AD 
requires repair before further flight using a method approved in 
accordance with the procedures specified in paragraph (k) of this 
AD.

(k) 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 (l)(1) of this AD. 
Information may be emailed to: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.
    (3) An AMOC that provides an acceptable level of safety may be 
used for any repair, 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) Except as required by paragraph (j)(2) of this AD: For 
service information that contains steps that are labeled as Required 
for Compliance (RC), the provisions of paragraphs (k)(4)(i) and 
(k)(4)(ii) apply.
    (i) The steps labeled as RC, including substeps under an RC step 
and any figures identified in an RC step, must be done to comply 
with the AD. An AMOC is required for any deviations to RC steps, 
including substeps and identified figures.
    (ii) Steps not labeled as RC may be deviated from using accepted 
methods in accordance with the operator's maintenance or inspection 
program without obtaining approval of an AMOC, provided the RC 
steps, including substeps and identified figures, can still be done 
as specified, and the airplane can be put back in an airworthy 
condition.

(l) 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: 
nathan.p.weigand@faa.gov.

(m) 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 747-53A2876, dated October 22, 
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 https://www.myboeingfleet.com.
    (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: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on February 15, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-03884 Filed 2-29-16; 8:45 am]
BILLING CODE 4910-13-P