80 FR 43648 - Airworthiness Directives; The Boeing Company Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 80, Issue 141 (July 23, 2015)

We propose to supersede Airworthiness Directive (AD) 2013-22- 11, which applies to certain The Boeing Company Model 747-400 and -400D series airplanes. AD 2013-22-11 currently requires 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 proposed AD would add additional repetitive inspections for cracks for certain airplanes, and corrective actions if necessary. We are proposing 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.

[Federal Register Volume 80, Number 141 (Thursday, July 23, 2015)]
[Proposed Rules]
[Pages 43648-43651]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2015-17932]



[[Page 43648]]

-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-2464; Directorate Identifier 2014-NM-195-AD]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: We propose to supersede Airworthiness Directive (AD) 2013-22-
11, which applies to certain The Boeing Company Model 747-400 and -400D 
series airplanes. AD 2013-22-11 currently requires 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 proposed AD would add additional repetitive 
inspections for cracks for certain airplanes, and corrective actions if 
necessary. We are proposing 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.

DATES: We must receive comments on this proposed AD by September 8, 
2015.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this proposed 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 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-
2464.

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-
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 proposed AD, the regulatory evaluation, any comments 
received, and other information. The street address for the Docket 
Office (phone: 800-647-5527) is in the ADDRESSES section. Comments will 
be available in the AD docket shortly after receipt.

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: [email protected].

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2015-2464; 
Directorate Identifier 2014-NM-195-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD because of those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    Structural fatigue damage is progressive. It begins as minute 
cracks, and those cracks grow under the action of repeated stresses. 
This can happen because of normal operational conditions and design 
attributes, or because of isolated situations or incidents such as 
material defects, poor fabrication quality, or corrosion pits, dings, 
or scratches. Fatigue damage can occur locally, in small areas or 
structural design details, or globally. Global fatigue damage is 
general degradation of large areas of structure with similar structural 
details and stress levels. Multiple-site damage is global damage that 
occurs in a large structural element such as a single rivet line of a 
lap splice joining two large skin panels. Global damage can also occur 
in multiple elements such as adjacent frames or stringers. Multiple-
site-damage and multiple-element-damage cracks are typically too small 
initially to be reliably detected with normal inspection methods. 
Without intervention, these cracks will grow, and eventually compromise 
the structural integrity of the airplane, in a condition known as 
widespread fatigue damage (WFD). As an airplane ages, WFD will likely 
occur, and will certainly occur if the airplane is operated long enough 
without any intervention.
    The FAA's WFD final rule (75 FR 69746, November 15, 2010), became 
effective on January 14, 2011. The WFD rule requires certain actions to 
prevent structural failure due to WFD throughout the operational life 
of certain existing transport category airplanes and all of these 
airplanes that will be certificated in the future. For existing and 
future airplanes subject to the WFD rule, the rule requires that design 
approval holders (DAH) establish a limit of validity (LOV) of the 
engineering data that support the structural maintenance program. 
Operators affected by the WFD rule may not fly an airplane beyond its 
LOV, unless an extended LOV is approved.
    The WFD rule (75 FR 69746, November 15, 2010), does not require 
identifying and developing maintenance actions if the DAHs can show 
that such actions are not necessary to prevent WFD before the airplane 
reaches the LOV. Many LOVs, however, do depend on accomplishment of 
future maintenance actions. As stated in the WFD rule, any maintenance 
actions necessary to reach the LOV will be mandated by airworthiness 
directives through separate rulemaking actions.
    In the context of WFD, this action is necessary to enable DAHs to 
propose LOVs that allow operators the longest operational lives for 
their airplanes, and still ensure that WFD will not occur.

[[Page 43649]]

This approach allows for an implementation strategy that provides 
flexibility to DAHs in determining the timing of service information 
development (with FAA approval), while providing operators with 
certainty regarding the LOV applicable to their airplanes.
    On October 17, 2013, we issued AD 2013-22-11, Amendment 39-17643 
(78 FR 66254, November 5, 2013), for certain The Boeing Company Model 
747-400 and -400D series airplanes. AD 2013-22-11 requires repetitive 
inspections to detect cracks in the floor panel attachment fastener 
holes of the Section 41 upper deck floor beam upper chords, and 
corrective actions if necessary; repetitive post-repair and post-
modification inspections, and corrective actions if necessary; 
repetitive inspections of Section 44 upper deck floor beam upper 
chords, and corrective actions if necessary; repetitive post-repair and 
post-modification inspections, and corrective actions if necessary; and 
replacement of the upper deck floor beam upper chords. AD 2013-22-11 
superseded AD 2009-10-06, Amendment 39-15901 (74 FR 22424, May 13, 
2009). AD 2013-22-11 resulted from an evaluation by the design approval 
holder (DAH) indicating that certain upper chords of the upper deck 
floor beam are subject to widespread fatigue damage (WFD). We issued AD 
2013-22-11 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.

Actions Since AD 2013-22-11, Amendment 39-17643 (78 FR 66254, November 
5, 2013), Was Issued

    Since we issued AD 2013-22-11, Amendment 39-17643 (78 FR 66254, 
November 5, 2013), an evaluation by the DAH indicated that certain 
fastener holes in the upper deck floor beam upper chords in Section 41, 
that were plugged or re-used during the conversion to a Boeing 
Converted Freighter, may not have been inspected in accordance with the 
requirements of AD 2013-22-11, because the locations may be hidden and 
not recognized as inspection locations. We have determined that, for 
certain airplanes, it is necessary to add additional repetitive 
inspections for cracks in the Section 41 upper deck floor beam upper 
chords and repair if necessary.

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 of this NPRM. It is also available 
on the Internet at http://www.regulations.gov by searching for and 
locating Docket No. FAA-2015-2464.

FAA's Determination

    We are proposing this AD because we evaluated all the relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of the same type design.

Proposed AD Requirements

    Although this proposed AD does not explicitly restate the 
requirements of AD 2013-22-11, Amendment 39-17643 (78 FR 66254, 
November 5, 2013), this proposed AD would retain all of the 
requirements of AD 2013-22-11. Those requirements are referenced in the 
service information identified previously, which, in turn, is 
referenced in paragraphs (g) through (k) of this proposed AD. This 
proposed AD would add new actions. This proposed AD would require 
accomplishing the actions specified in the service information 
identified previously, except as discussed under ``Differences Between 
this Proposed AD and the Service Information.'' Refer to this service 
information for information on the procedures and compliance times.
    In addition, the phrase ``corrective actions'' might be used in 
this proposed AD. ``Corrective actions'' are actions that correct or 
address any condition found. Corrective actions in an AD could include, 
for example, repairs.

Differences Between This Proposed AD and the Service Information

    Boeing Alert Service Bulletin 747-53A2688, Revision 2, dated August 
21, 2014, specifies to contact the manufacturer for instructions on how 
to repair certain conditions, but this proposed AD would require 
repairing those conditions in one of the following ways:
     In accordance with a method that we approve; or
     Using data that meet the certification basis of the 
airplane, and that have been approved by the Boeing Commercial 
Airplanes Organization Designation Authorization (ODA) whom we have 
authorized to make those findings.

Costs of Compliance

    We estimate that this proposed AD affects 84 airplanes of U.S. 
registry. We estimate the following costs to comply with this proposed 
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, Amendment 39-       hours x $85 per                      inspection cycle.    per inspection
 17643 (78 FR 66254, November 5,    hour = $26,265 per                                        cycle.
 2013)).                            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 would enable us to provide 
a cost estimate for the repair or modification specified in this 
proposed 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,

[[Page 43650]]

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 proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 the proposed 
regulation:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under the 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.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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:

The Boeing Company: Docket No. FAA-2015-2464; Directorate Identifier 
2014-NM-195-AD.

(a) Comments Due Date

    The FAA must receive comments on this AD action by September 8, 
2015.

(b) Affected ADs

    This AD replaces AD 2013-22-11, Amendment 39-17643 (78 FR 66254, 
November 5, 2013).

(c) Applicability

    (1) 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 (DAH) indicating that certain upper chords of the upper deck 
floor beam are subject to widespread fatigue damage (WFD). 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, Amendment 39-17643 (78 
FR 66254, November 5, 2013). 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 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 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 is done or a modification specified in Figure 5 of the 
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2688 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 high 
frequency eddy current inspections 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 high frequency eddy 
current 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.

[[Page 43651]]

    (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 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.

(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 is done or a modification specified in Figure 21 of Boeing 
Alert Service Bulletin 747-53A2688 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 high frequency eddy current 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) Section 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 re-used floor panel attachment 
holes in the affected floor beam upper chords, do a surface high 
frequency eddy current 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, FAA, 
Seattle Aircraft Certification Office (ACO), for inspections and 
compliance times and accomplish the inspections at the given times.
    (4) Where Boeing Alert Service Bulletin 747-53A2688, Revision 1, 
dated September 19, 2012, 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, Amendment 39-17643 (78 FR 
66254, November 5, 2013)).

(n) Credit for Previous Actions

    (1) This paragraph restates the requirements of paragraph (o) of 
AD 2013-22-11, Amendment 39-17643 (78 FR 66254, November 5, 2013), 
with new paragraph (h). 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.
    (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 is not incorporated by reference in this AD.

(o) 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 (p)(1) 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 for AD 2013-22-11, Amendment 39-17643 (78 FR 
66254, November 5, 2013), are approved as AMOCs for the 
corresponding provisions of paragraphs (g) through (k) of this AD.

(p) Related Information

    (1) 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: 
[email protected].
    (2) 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 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.

    Issued in Renton, Washington, on July 15, 2015.
Suzanne Masterson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-17932 Filed 7-22-15; 8:45 am]
 BILLING CODE 4910-13-P