[Federal Register Volume 80, Number 181 (Friday, September 18, 2015)]
[Proposed Rules]
[Pages 56407-56413]
[FR Doc No: 2015-23420]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0774; Directorate Identifier 2013-NM-154-AD]
RIN 2120-AA64

Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Supplemental notice of proposed rulemaking (SNPRM); reopening
of comment period.

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SUMMARY: We are revising an earlier proposed airworthiness directive
(AD) that proposed to supersede AD 2006-22-15 for all The Boeing
Company Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-
200F, 747-300, 747-400, 747-400D, 747-400F, 747SR, and 747SP series
airplanes. AD 2006-22-15 requires repetitive inspections for cracking
of certain panel webs and stiffeners of the nose wheel well (NWW), and
corrective actions if necessary; and replacement of certain panels with
new panels, which terminates the repetitive inspections. The notice of
proposed rulemaking (NPRM) proposed to reduce a compliance time and add
certain inspections and applicable repair. The NPRM was prompted by
reports of fatigue cracking in the panel webs and stiffeners of the NWW
found prior to the inspection threshold of AD 2006-22-15. This action
revises the NPRM by specifying a repetitive inspection interval for a
certain NWW area inspection. We are proposing this SNPRM to prevent
fatigue cracking of the NWW side and top panels, which could result in
a NWW depressurization event severe enough to reduce the structural
integrity of the fuselage. Since these actions impose an additional
burden over that proposed in the NPRM, we are reopening the comment
period to allow the public the chance to comment on these proposed
changes.

DATES: We must receive comments on this SNPRM by November 2, 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:<PHONE_NUMBER>.
     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: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590, 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<PHONE_NUMBER>,
extension 1; fax<PHONE_NUMBER>; 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<PHONE_NUMBER>. It is also
available on the Internet at http://www.regulations.gov by searching
for and locating Docket No. FAA-2014-0774.

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-2014-
0774; 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:<PHONE_NUMBER>) is in the ADDRESSES section. Comments will
be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Bill Ashforth, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office
(ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-
6432; fax:<PHONE_NUMBER>; email<EMAIL_ADDRESS>
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-2014-0774;
Directorate Identifier 2013-NM-154-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

    We issued an NPRM to amend 14 CFR part 39 to supersede AD 2006-22-
15, Amendment 39-14812 (71 FR 64884, November 6, 2006). AD 2006-22-15
applies to all Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-
200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F, 747SR, and 747SP
series airplanes. The NPRM published in the Federal Register on
November 17, 2014 (79 FR 68388). The NPRM was prompted by reports of
fatigue cracking in the panel webs and stiffeners of the NWW found
prior to the inspection threshold of AD 2006-22-15. The NPRM proposed
to continue to require repetitive inspections for cracking of certain
panel webs and stiffeners of the NWW, and corrective actions if
necessary. The NPRM also proposed to continue to require replacing
certain panels with new panels, which would terminate the repetitive
inspections. The NPRM proposed to reduce a compliance time and add
certain inspections and applicable repair.

Actions Since Previous NPRM (79 FR 68388, November 17, 2014) Was Issued

    Since we issued the NPRM (79 FR 68388, November 17, 2014), we have
determined that it is necessary to revise the NPRM by specifying a
certain repetitive inspection interval for Area 2 for airplanes with
less than 15,000 total flight cycles. This interval is not clearly
indicated in table 1 of paragraph 1.E., ``Compliance,'' of Boeing
Service Bulletin 747-53A2465, Revision 5, dated July 11, 2013, and was
not specifically stated in the NPRM.

Related Service Information Under 1 CFR Part 51

    We reviewed the following Boeing service information. Refer to this
service information for information on the procedures and compliance
times.
     Boeing Service Bulletin 747-53A2465, Revision 5, dated
July 11, 2013, which describes procedures for inspections for cracks of
certain top and sidewall panel webs and stiffeners of the NWW; and
repairs.
     Boeing Service Bulletin 747-53A2562, Revision 3, dated
July 11, 2013. This service bulletin describes procedures for
replacement of the side and top panel webs and certain stiffeners of
the NWW; an inspection for cracks in attaching structural elements that
are common to the removed top panel and side panels; repetitive post-
modification inspections for cracks in the top and side panel webs and
stiffeners; and contacting Boeing for repairs.
     Boeing Alert Service Bulletin 747-53A2808, dated November
30, 2012. This service bulletin describes procedures for replacement of
the side and top panel webs, support beams, and stiffeners of the NWW;
an inspection for cracks of the attaching structural elements that are
common to the removed top and side panels of the NWW; repetitive post-
modification inspections for cracks in the top and side panel webs and
stiffeners; and contacting Boeing for repairs.
    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.

Comments

    We gave the public the opportunity to comment on the NPRM (79 FR
68388, November 17, 2014). The following presents the comments received
on the NPRM and the FAA's response to each comment.

Requests To Specify Repetitive Inspection Interval for Area 2

    United Airlines (UAL) and United Parcel Service (UPS) requested
that we specify the repetitive inspection interval for Area 2 for
airplanes with less than 15,000 total flight cycles. The commenters
point out that this is not clearly indicated in table 1 of paragraph
1.E., ``Compliance,'' of Boeing Service Bulletin 747-53A2465, Revision
5, dated July 11, 2013, and was not specifically stated in the NPRM (79
FR 68388, November 17, 2014). The commenters stated that Boeing has
issued a service bulletin information notice to inform operators that
the repetitive inspection interval for Area 2 should be 1,000 flight
cycles.
    We agree with the commenters' requests to specify the repeat
interval for Area 2. We have revised paragraph (g) of this SNPRM to
specify this interval.

Request To Specify Repair Procedures

    UAL asked whether paragraph (h)(3) of the proposed AD (79 FR 68388,
November 17, 2014) should be revised to specify repair requirements for
each area, instead of contacting the FAA or the Boeing Commercial
Airplanes Organization Designation Authorization (ODA) for repair
instructions for any cracking or damage found during the inspection
specified in paragraph (g) of the proposed AD. UAL explained that
Boeing Service Bulletin 747-53A2465, Revision 5, dated July 11, 2013,
specifies repairing web cracks in Area 1 or 2 per the ``747 Structural
Repair Manuals.''
    We agree to provide clarification. The intent of paragraph (h)(3)
of this SNPRM is to make sure that for those conditions for which
Boeing Service Bulletin 747-53A2465, Revision 5, dated July 11, 2013,
specifies that the operator is to contact Boeing for repair data, the
operator would be required to use a repair method approved by the FAA
or Boeing Commercial Airplanes ODA. We have not changed this SNPRM in
this regard.

Request To Clarify Certain Compliance Times

    UAL requested clarification of why the footnotes in table 2 of
paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin 747-53A2465,
Revision 5, dated July 11, 2013, reverted back to 6,000 flight cycles
for Area 3 inspections for cracks of the sidewall panel and top panel
stiffeners. UAL also asked why the 6,000-flight-cycle time is just for
the first repeat inspection and then Area 3 has to be reinspected every
1,500 flight cycles thereafter.
    We agree that clarification is necessary. Paragraph (f)(2) of AD
2006-22-15, Amendment 39-14812 (71 FR 64884, November 6, 2006),
specifies the 6,000-flight-cycle and 1,500-flight-cycle inspection
times. Boeing Service Bulletin 747-53A2465, Revision 5, dated July 11,
2013, states that inspections and corrective actions defined therein
are an alternative method of compliance (AMOC) to the requirements of
paragraphs (f), (g), (h), (i), and (j) of AD 2006-22-15. In order to be
approved as an AMOC to certain requirements of AD 2006-22-15, Boeing
Service Bulletin 747-53A2465, Revision 5, dated July 11, 2013, must
state the compliance times required by AD 2006-22-15 to address the
identified unsafe condition. We have not changed this SNPRM in this
regard.

Request To Revise Certain Headers To Clarify Intent of Requirements

    Boeing requested that we revise the heading of paragraph (g) of the
proposed AD (79 FR 68388, November 17, 2014) to either change
``Repetitive Inspections'' to ``Initial and Repetitive Inspections'' or
delete ``Repetitive.'' Boeing stated that paragraph (g) of the proposed
AD contains both initial and repetitive inspections.
    Boeing requested that we delete ``Repetitive'' from the headings of
paragraphs (j) and (m) of the proposed AD (79 FR 68388, November 17,
2014). Boeing stated that paragraphs (j) and (m) of the proposed AD
specify not only repetitive inspections, but also the initial post-
modification inspections.
    We agree that clarification is necessary. We do not consider that
the term ``repetitive'' necessarily excludes the initial action. An
action cannot be repeated without accomplishment of the initial action.
Many existing ADs refer to ``repetitive'' actions, which we intend as
including the initial action. In addition, changing ``Repetitive
Inspections'' to simply ``Inspections'' could result in the
misinterpretation that multiple different inspections are required. We
have not changed this SNPRM regarding this issue.

Request To Clarify Inspection Location

    Boeing requested that, at the end of paragraph (g)(3) of the
proposed AD (79 FR 68388, November 17, 2014), we add ``of the NWW
(specified as Area 1 and Area 2 in Boeing Service Bulletin 747-53A2465,
Revision 5, dated July 11, 2013)'' for the ultrasonic inspection.
    We agree with the commenter's request. This revision will make the
wording in paragraph (g)(3) of this proposed AD consistent with the
wording of each of the areas specified in paragraphs (g)(1) and (g)(2)
of this proposed AD. We have revised paragraph (g)(3) of this proposed
AD accordingly.

Request To Add New AMOC Limitation

    Boeing requested that we add a new paragraph (p)(6) to the NPRM (79
FR 68388, November 17, 2014), which would state that ``New provisions
(inspection threshold and interval) in this AD must be complied with as
given in this AD.'' Boeing stated that this statement will make it
clear that prior AMOCs do not exempt the operators from compliance with
new requirements added by this new proposed AD. Boeing also stated that
the wording of ``corresponding provisions'' in paragraph (p)(4) of the
proposed AD (79 FR 68388, November 17, 2014) might not be precise
enough, when ADs get superseded and paragraphs change. Boeing explained
that adding this statement will reduce the ambiguity of paragraphs (o)
and (p) of the proposed AD.
    We partially agree with the commenter's request. We have revised
paragraph (p)(4) of this proposed AD to state that AMOC actions
approved previously for AD 2006-22-15, Amendment 39-14812 (71 FR 64884,
November 6, 2006), are approved as AMOCs for the corresponding actions
of this AD. The compliance times in AMOCs approved previously for AD
2006-22-15 are not approved for the corresponding actions and
compliance times in this AD. We have removed paragraph (p)(5) of this
proposed AD as it is no longer necessary. We consider this language to
be sufficiently clear. Adding the commenter's requested language would
be redundant to the language specified in revised paragraph (p)(4) of
this proposed AD.

Requests for Certain Editorial Changes

    Boeing noted that paragraph (m) of the proposed AD (79 FR 68388,
November 17, 2014) incorrectly referred to paragraphs ``(l)(1), (l)(2),
and (l)(3).'' Boeing asked that we change these references to ``(m)(1),
(m)(2), and (m)(3).''
    Boeing requested that we correct the AD citation in paragraph
(o)(1)(i) of the proposed AD (79 FR 68388, November 17, 2014). Boeing
stated that the identified effective date of January 27, 2005, is for
AD 2004-25-23, Amendment 39-13911 (69 FR 76839, December 23, 2004); not
AD 2005-09-02, Amendment 39-14070 (70 FR 21141, April 25, 2005;
corrected May 25, 2005, 70 FR 29940)); as stated in the NPRM.
    Boeing requested that we correct the date of Boeing Service
Bulletin 747-53A2465, Revision 4, from February 25, 2004, to February
24, 2005, in paragraph (o)(2) of the proposed AD (79 FR 68388, November
17, 2014).
    UPS requested that we revise paragraph (p)(1) of the proposed AD
(79 FR 68388, November 17, 2014) to correct the paragraph identifier
for the contact person, which should be paragraph ``(q)(1).''
    We agree with the requests and have revised this SNPRM accordingly.

FAA's Determination

    We are proposing this SNPRM because we evaluated all the relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of this same type design.
Certain changes described above expand the scope of the NPRM (79 FR
68388, November 17, 2014). As a result, we have determined that it is
necessary to reopen the comment period to provide additional
opportunity for the public to comment on this SNPRM.

Proposed Requirements of This SNPRM

    Although this proposed AD does not explicitly restate certain
requirements of AD 2006-22-15, Amendment 39-14812 (71 FR 64884,
November 6, 2006), this proposed AD would retain all of the
requirements of AD 2006-22-15.
    The requirements specified in paragraphs (f), (g), (h), (i), (j),
and (l) of AD 2006-22-15, Amendment 39-14812 (71 FR 64884, November 6,
2006), are referenced in Boeing Service Bulletin 747-53A2465, Revision
5, dated July 11, 2013, which, in turn, is referenced in paragraphs (g)
and (h)(3) of this proposed AD.
    The requirement specified in paragraph (n) of AD 2006-22-15,
Amendment 39-14812 (71 FR 64884, November 6, 2006), is referenced in
Boeing Service Bulletin 747-53A2562, Revision 3, dated July 11, 2013,
which, in turn, is referenced in paragraph (i) of this proposed AD.

    For Group 2 airplanes identified in Boeing Service Bulletin 747-
53A2562, Revision 1, dated July 28, 2005, and certain airplanes not
identified in Boeing Service Bulletin 747-53A2562, Revision 1, dated
July 28, 2005, the requirement specified in paragraph (o) of AD 2006-
22-15, Amendment 39-14812 (71 FR 64884, November 6, 2006), to
accomplish a repair using a method approved by the FAA is now specified
in paragraph (i) of this proposed AD. However, for these airplanes, one
method of compliance for accomplishing the replacement is Boeing
Service Bulletin 747-53A2562, Revision 3, dated July 11, 2013.
Therefore, we have referred to Boeing Service Bulletin 747-53A2562,
Revision 3, dated July 11, 2013, in paragraph (i) of this proposed AD.
Operators may still request an alternative method of compliance (AMOC)
using the procedures provided in paragraph (p) of this AD.
    For certain other airplanes not identified in Boeing Service
Bulletin 747-53A2562, Revision 1, dated July 28, 2005, the requirement
specified in paragraph (o) of AD 2006-22-15, Amendment 39-14812 (71 FR
64884, November 6, 2006), to accomplish a repair using a method
approved by the FAA is now specified in paragraph (l) of this proposed
AD. However, for these airplanes, one method of compliance for
accomplishing the replacement is Boeing Alert Service Bulletin 747-
53A2808, dated November 30, 2012. Therefore, we have referred to Boeing
Alert Service Bulletin 747-53A2808, dated November 30, 2012, in
paragraph (l) of this proposed AD. Operators may still request an AMOC
using the procedures provided in paragraph (p) of this AD.
    This proposed AD would require accomplishing the actions specified
in the service information identified previously, except as discussed
under ``Differences Between the Proposed AD and the Service
Information.'' Refer to this service information for information on the
procedures and compliance times.
    The phrase ``related investigative actions'' is used in this
proposed AD. ``Related investigative actions'' are follow-on actions
that (1) are related to the primary actions, and (2) further
investigate the nature of any condition found. Related investigative
actions in an AD could include, for example, inspections.
    The phrase ``corrective actions'' is 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 the Proposed AD and the Service Information

    For airplanes with fewer than 15,000 total flight cycles, Boeing
Service Bulletin 747-53A2465, Revision 5, dated July 11, 2013,
recommends, in part, accomplishing a detailed inspection before the
accumulation of 13,000 total flight cycles. However, we have determined
that the 13,000-total-flight-cycle compliance time is insufficient to
address the identified unsafe condition soon enough to ensure an
adequate level of safety for the affected fleet. Instead, we are
proposing a compliance time of 10,000 total flight cycles. In
developing an appropriate compliance time for this detailed inspection,
we considered the degree of urgency associated with the subject unsafe
condition, and the fact that we have received a report of a 13-inch
crack adjacent to a 2-inch crack in the NWW right-hand side panel on an
airplane with 11,428 total flight cycles. This difference has been
coordinated with The Boeing Company.
    Boeing Service Bulletin 747-53A2465, Revision 5, dated July 11,
2013; Boeing Service Bulletin 747 53A2562, Revision 3, dated July 11,
2013; and Boeing Alert Service Bulletin 747-53A2808, dated November 30,
2012; specify 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 ODA whom we have authorized to make those findings.

Explanation of Compliance Time

    The compliance time for the modification specified in paragraphs
(i) and (l) of this proposed AD for addressing widespread fatigue
damage (WFD) was established to ensure that discrepant structure is
modified before WFD develops in airplanes. Standard inspection
techniques cannot be relied on to detect WFD before it becomes a hazard
to flight. We will not grant any extensions of the compliance time to
complete any AD-mandated service bulletin related to WFD without
extensive new data that would substantiate and clearly warrant such an
extension.

Costs of Compliance

    We estimate that this proposed AD affects 255 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
----------------------------------------------------------------------------------------------------------------
Inspections [actions retained   119 work-hours x   $0......................  $10,115 per        $2,579,325 per
 from AD 2006-22-15, Amendment   $85 per hour =                               inspection cycle.  inspection
 39-14812 (71 FR 64884,          $10,115 per                                                     cycle.
 November 6, 2006)].             inspection cycle.
Modification [actions retained  Up to 1,346 work-  Up to $144,248..........  Up to $258,658...  Up to
 from AD 2006-22-15, Amendment   hours x $85 per                                                 $65,957,790.
 39-14812 (71 FR 64884,          hour = $114,410.
 November 6, 2006)].
Post-modification Inspections   119 work-hours x   $0......................  $10,115 per        $2,579,325 per
 [new proposed action].          $85 per hour =                               inspection cycle.  inspection
                                 $10,115 per                                                     cycle.
                                 inspection cycle.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide
cost estimates for the on-condition actions 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,

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 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 this 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 adding the following new airworthiness
directive (AD):

The Boeing Company: Docket No. FAA-2014-0774; Directorate Identifier
2013-NM-154-AD.

(a) Comments Due Date

    We must receive comments by November 2, 2015.

(b) Affected ADs

    This AD replaces AD 2006-22-15, Amendment 39-14812 (71 FR 64884,
November 6, 2006).

(c) Applicability

    This AD applies to all Boeing Model 747-100, 747-100B, 747-100B
SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-
400F, 747SR, and 747SP series airplanes, certificated in any
category.

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by multiple reports of cracking in the nose
wheel well (NWW) top panel and side panel webs and stiffeners caused
by fatigue. We are issuing this AD to prevent fatigue cracking of
the NWW side and top panels, which could result in a NWW
depressurization event severe enough to reduce the structural
integrity of the fuselage.

(f) Compliance

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

(g) Repetitive Inspections and Corrective Actions With New Compliance
Times

    Except as specified in paragraphs (h)(1) and (h)(2) of this AD,
at the applicable time specified in paragraph 1.E., ``Compliance,''
of Boeing Service Bulletin 747-53A2465, Revision 5, dated July 11,
2013: Do the actions specified in paragraphs (g)(1), (g)(2), and
(g)(3) of this AD, and do all applicable related investigative and
corrective actions; in accordance with the Accomplishment
Instructions of Boeing Service Bulletin 747-53A2465, Revision 5,
dated July 11, 2013, except as specified in paragraph (h)(3) of this
AD. Do all applicable related investigative and corrective actions
before further flight. Repeat the inspections specified in
paragraphs (g)(1), (g)(2), and (g)(3) of this AD thereafter at the
applicable intervals specified in paragraph 1.E., ``Compliance,'' of
Boeing Service Bulletin 747-53A2465, Revision 5, dated July 11,
2013. The repetitive interval for the inspection of Area 2 specified
in table 1 in paragraph 1.E., ``Compliance,'' of Boeing Service
Bulletin 747-53A2465, Revision 5, dated July 11, 2013, is 1,000
flight cycles. In table 2 and table 3 in paragraph 1.E.,
``Compliance,'' of Boeing Service Bulletin 747-53A2465, Revision 5,
dated July 11, 2013, the date ``January 27, 2005'' is the effective
date of AD 2004-25-23, Amendment 39-13911 (69 FR 76839, December 23,
2004); and the date ``May 10, 2005'' is the effective date of AD
2005-09-02, Amendment 39-14070 (70 FR 21141, April 25, 2005;
corrected May 25, 2005 (70 FR 29940)).
    (1) Do an external detailed inspection for cracks of the top and
sidewall panel webs of the NWW (specified as Area 1 and Area 2 in
Boeing Service Bulletin 747-53A2465, Revision 5, dated July 11,
2013).
    (2) Do internal detailed and surface high frequency eddy current
(HFEC) inspections for cracks of the sidewall panel and top panel
stiffeners of the NWW (specified as Area 3 in Boeing Service
Bulletin 747-53A2465, Revision 5, dated July 11, 2013).
    (3) Do an external detailed and ultrasonic testing (UT)
inspection for cracks of the top and sidewall panel webs of the NWW
(specified as Area 1 and Area 2 in Boeing Service Bulletin 747 -
53A2465, Revision 5, dated July 11, 2013).

(h) Exceptions to Boeing Service Bulletin 747-53A2465, Revision 5,
dated July 11, 2013

    (1) Table 1 in paragraph 1.E., ``Compliance,'' of Boeing Service
Bulletin 747-53A2465, Revision 5, dated July 11, 2013, applies to
airplanes with less than 15,000 total flight cycles ``as of the
Revision 5 date of this service bulletin.'' For this AD, however,
table 1 applies to airplanes with the specified total flight cycles
as of the effective date of this AD.
    (2) Table 1 in paragraph 1.E., ``Compliance,'' of Boeing Service
Bulletin 747-53A2465, Revision 5, dated July 11, 2013, specifies a
compliance time of ``13,000 total flight-cycles,'' or ``within 1,000
flights cycles after the Revision 5 date of this service bulletin,''
whichever occurs later. This AD requires compliance before the
accumulation of 10,000 total flight cycles or within 1,000 flight
cycles after the effective date of this AD, whichever occurs later.
    (3) If any cracking or damage is found during any inspection
required by paragraph (g) of this AD, and Boeing Service Bulletin
747-53A2465, Revision 5, dated July 11, 2013, specifies to contact
Boeing for appropriate action: Before further flight, repair the
cracking or damage using a method approved in accordance with the
procedures specified in paragraph (p) of this AD.

(i) NWW Modification

    For airplanes identified in Boeing Service Bulletin 747-53A2562,
Revision 3, dated July 11, 2013: At the applicable time specified in
paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin 747-
53A2562, Revision 3, dated July 11, 2013, replace the left-side,
right-side, and top panels of the NWW, as applicable, with new
panels, in accordance with the Accomplishment Instructions of Boeing
Service Bulletin 747-53A2562, Revision 3, dated July 11, 2013. As of
the effective date of this AD, concurrently with doing the
replacement specified in Boeing Service Bulletin 747-53A2562,
Revision 3, dated July 11, 2013, do a detailed inspection for any
cracks or damage (including, but not limited to, dents and
corrosion) in all attaching structural elements that are common to
the removed top panel and side panels, as applicable, and do all
applicable corrective actions, in accordance with the Accomplishment
Instructions of Boeing Service Bulletin 747-53A2562, Revision 3,
dated July 11, 2013. If any crack or damage is found, before further
flight, repair the cracking or damage using a method approved in
accordance with the procedures specified in paragraph (p) of this
AD. In paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin
747-53A2562, Revision 3, dated July 11, 2013, the date ``December
11, 2006,'' is the

effective date of AD 2006-22-15, Amendment 39-14812 (71 FR 64884,
November 6, 2006).

(j) Repetitive Post-Modification Inspections

    For airplanes on which the replacement specified in paragraph
(i) of this AD has been done: Except as required by paragraph (k) of
this AD, at the applicable time specified in paragraph 1.E.,
``Compliance,'' of Boeing Service Bulletin 747-53A2562, Revision 3,
dated July 11, 2013, do the actions specified in paragraphs (j)(1),
(j)(2), and (j)(3) of this AD. If any crack is found: Before further
flight, repair the cracking using a method approved in accordance
with the procedures specified in paragraph (p) of this AD. Repeat
the inspections specified in paragraphs (j)(1), (j)(2), and (j)(3)
of this AD thereafter at the applicable intervals specified in
paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin 747-
53A2562, Revision 3, dated July 11, 2013.
    (1) Do an external detailed inspection for cracks in the side
panel webs, in accordance with the Accomplishment Instructions of
Boeing Service Bulletin 747-53A2562, Revision 3, dated July 11,
2013.
    (2) Do an internal detailed inspection and high frequency eddy
current (HFEC) inspection for cracks in the top and side panel
stiffeners, in accordance with the Accomplishment Instructions of
Boeing Service Bulletin 747-53A2562, Revision 3, dated July 11,
2013.
    (3) Do an external detailed inspection for cracks in the top
panel web, in accordance with the Accomplishment Instructions of
Boeing Service Bulletin 747-53A2562, Revision 3, dated July 11,
2013.

(k) Exception to Boeing Service Bulletin 747-53A2562, Revision 3, Dated
July 11, 2013

    Where paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin
747-53A2562, Revision 3, dated July 11, 2013, specifies a compliance
time relative to the ``Revision 3 date of this service bulletin,''
this AD requires compliance within the specified compliance time
after the effective date of this AD.

(l) NWW Modification for Certain Airplanes

    For airplanes identified in Boeing Alert Service Bulletin 747-
53A2808, dated November 30, 2012: At the applicable time specified
in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
747-53A2808, dated November 30, 2012, replace the left side, right
side, and top panels of the NWW, as applicable, with new panels, in
accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 747-53A2808, dated November 30, 2012. Concurrently
with doing the replacement specified in this paragraph, do a
detailed inspection for cracks of the attaching structural elements
that are common to the removed top, left-side, and right-side panels
of the NWW, in accordance with the Accomplishment Instructions of
Boeing Alert Service Bulletin 747-53A2808, dated November 30, 2012.
If any crack is found, before further flight, repair the cracking
using a method approved in accordance with the procedures specified
in paragraph (p) of this AD.

(m) Repetitive Post-Modification Inspections for Certain Airplanes

    For airplanes on which the replacement specified in paragraph
(l) of this AD has been done: At the applicable time specified in
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
747-53A2808, dated November 30, 2012, do the actions specified in
paragraphs (m)(1), (m)(2), and (m)(3) of this AD. If any crack is
found: Before further flight, repair the cracking using a method
approved in accordance with the procedures specified in paragraph
(p) of this AD. Repeat the inspections specified in paragraphs
(m)(1), (m)(2), and (m)(3) of this AD thereafter at the applicable
intervals specified in paragraph 1.E., ``Compliance,'' of Boeing
Alert Service Bulletin 747-53A2808, dated November 30, 2012.
    (1) Do an external detailed inspection for cracks in the side
panel webs, in accordance with the Accomplishment Instructions of
Boeing Alert Service Bulletin 747-53A2808, dated November 30, 2012.
    (2) Do an internal detailed inspection and HFEC inspection for
cracks in the top and side panel stiffeners, in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2808, dated November 30, 2012.
    (3) Do an external detailed inspection for cracks in the top
panel web, in accordance with the Accomplishment Instructions of
Boeing Alert Service Bulletin 747-53A2808, dated November 30, 2012.

(n) Terminating Action for Certain Repetitive Inspections

    Replacing the left side, right side, and top panels of the NWW
with new panels as specified in paragraph (i) or (l) of this AD
terminates the repetitive inspections required by paragraph (g) of
this AD.

(o) Credit for Previous Actions

    (1) This paragraph restates the credit given in paragraph (k) of
AD 2006-22-15, Amendment 39-14812 (71 FR 64884, November 6, 2006).
    (i) This paragraph provides credit for the actions required by
paragraph (g)(1) of this AD, if those actions were performed before
January 27, 2005 (the effective date of AD 2004-25-23, Amendment 39-
13911 (69 FR 76839, December 23, 2004)), using Boeing Alert Service
Bulletin 747-53A2465, dated April 5, 2001, which is not incorporated
by reference in this AD.
    (ii) This paragraph provides credit for actions required by
paragraphs (g)(1) and (g)(2) of this AD, if those actions were
performed before December 11, 2006 (the effective date of AD 2006-
22-15, Amendment 39-14812 (71 FR 64884, November 6, 2006)), using a
service bulletin identified in paragraph (o)(1)(ii)(A),
(o)(1)(ii)(B), or (o)(1)(ii)(C) of this AD, which are not
incorporated by reference in this AD.
    (A) Boeing Alert Service Bulletin 747-53A2465, Revision 1, dated
October 16, 2003.
    (B) Boeing Alert Service Bulletin 747-53A2465, Revision 2, dated
November 11, 2004.
    (C) Boeing Alert Service Bulletin 747-53A2465, Revision 3, dated
December 23, 2004.
    (2) This paragraph provides credit for the actions required by
paragraph (g) of this AD, if those actions were performed before the
effective date of this AD using Boeing Alert Service Bulletin 747-
53A2465, Revision 4, dated February 24, 2005, which is not
incorporated by reference in this AD.
    (3) This paragraph provides credit for the actions required by
paragraphs (i) and (j) of this AD, if those actions were performed
before the effective date of this AD using Boeing Service Bulletin
747-53A2562, Revision 1, dated July 28, 2005; or Boeing Service
Bulletin 747-53A2562, Revision 2, dated May 31, 2007; which are not
incorporated by reference in this AD.

(p) 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 (q)(1) of this AD.
Information may be emailed to<EMAIL_ADDRESS>    (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 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) AMOC actions approved previously for AD 2006-22-15,
Amendment 39-14812 (71 FR 64884, November 6, 2006), are approved as
AMOCs for the corresponding actions of this AD. The compliance times
in AMOCs approved previously for AD 2006-22-15 are not approved for
the corresponding actions and compliance times in this AD.

(q) Related Information

    (1) For more information about this AD, contact Bill Ashforth,
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle ACO,
1601 Lind Avenue SW., Renton, WA 98057-3356; phone:<PHONE_NUMBER>;
fax:<PHONE_NUMBER>; email<EMAIL_ADDRESS>    (2) For service information identified in this AD, Boeing
Commercial Airplanes, Attention: Data & Services Management, P. O.
Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone<PHONE_NUMBER>,
extension 1; fax<PHONE_NUMBER>; 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<PHONE_NUMBER>.

    Issued in Renton, Washington, on September 1, 2015.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2015-23420 Filed 9-17-15; 8:45 am]
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