AD 2014-14-03

[Federal Register Volume 79, Number 135 (Tuesday, July 15, 2014)]
[Rules and Regulations]
[Pages 41120-41125]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2014-16381]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0432; Directorate Identifier 2014-NM-099-AD; 
Amendment 39-17898; AD 2014-14-03]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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SUMMARY: We are superseding Airworthiness Directive (AD) 2014-07-01, 
for certain The Boeing Company Model 747 airplanes. AD 2014-07-01 
required repetitive inspections for cracking in certain bulkhead 
structure; inspections of certain fasteners and support frame 
modifications on certain airplanes; related investigative and 
corrective actions, if necessary; and an interim modification that 
would terminate certain repetitive inspections. This AD clarifies 
certain paragraph references and revises a compliance time. This AD was 
prompted by a determination that certain paragraph references are in 
error. We are issuing this AD to detect and correct fatigue cracking of 
the BS 2598 bulkhead structure, which could adversely affect the 
structural integrity of the bulkhead and the horizontal stabilizer 
support structure, and result in loss of controllability of the 
airplane.

DATES: This AD is effective July 15, 2014.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of June 3, 2014 
(79 FR 23893, April 29, 2014).
    We must receive any comments on this AD by August 29, 2014.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
    <bullet> Federal eRulemaking Portal: Go to <a href="http://www.regulations.gov">http://www.regulations.gov</a>. Follow the instructions for submitting comments.
    <bullet> Fax: 202-493-2251.
    <bullet> 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.
    <bullet> 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 AD, contact Boeing 
Commercial Airplanes, Attention: Data & Services Management, P.O. Box 
3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-5000, 
extension 1; fax 206-766-5680; Internet <a href="https://www.myboeingfleet.com">https://www.myboeingfleet.com</a>. 
You may view this referenced service information at the FAA, Transport 
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information 
on the availability of this material at the FAA, call 425-227-1221.

Examining the AD Docket

    You may examine the AD docket on the Internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a> by searching for and locating Docket No. FAA-2014-
0432; 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 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, 
1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6428; fax: 
425-917-6590; email: <a href="/cdn-cgi/l/email-protection#e68887928e8788c896c891838f81878882a6808787c8818990"><span class="__cf_email__" data-cfemail="3856594c5059561648164f5d515f59565c785e5959165f574e">[email&#160;protected]</span></a>.

SUPPLEMENTARY INFORMATION: 

Discussion

    On March 17, 2014, we issued AD 2014-07-01, Amendment 39-17815 (79 
FR 23893, April 29, 2014), for certain The Boeing Company Model 747 
airplanes. AD 2014-07-01 required repetitive inspections, including 
post-repair and post-modification inspections, for cracking in the 
bulkhead structure at body station (BS) 2598; certain one-time 
inspections of certain fasteners and support frame modifications on 
certain airplanes; related investigative and corrective

[[Page 41121]]

actions, if necessary; and an interim modification that would terminate 
certain repetitive inspections.
    AD 2014-07-01, Amendment 39-17815 (79 FR 23893, April 29, 2014), 
resulted from reports of cracking in the forward and aft inner chord of 
the BS 2598 bulkhead near the upper corners of the cutout for the 
horizontal stabilizer rear spar, and cracking in the bulkhead upper and 
lower web panels near the inner chord to shear deck connection. We 
issued AD 2014-07-01 to detect and correct fatigue cracking of the BS 
2598 bulkhead structure, which could adversely affect the structural 
integrity of the bulkhead and the horizontal stabilizer support 
structure, and result in loss of controllability of the airplane.

Actions Since AD 2014-07-01, Amendment 39-17815 (79 FR 23893, April 29, 
2014), Was Issued

    Paragraph (o)(1) of AD 2014-07-01, Amendment 39-17815 (79 FR 23893, 
April 29, 2014), terminated the actions in certain paragraphs of AD 
2010-14-07, Amendment 39-16352 (75 FR 38001, July 1, 2010). AD 2014-07-
01, however, incorrectly terminated ``paragraphs (k) and (l),'' which 
should have been ``paragraph (k)(1).'' Paragraph (o)(1) of this AD 
corrects that reference to ``paragraph (k)(1).'' All provisions of AD 
2010-14-07 that are not specifically referenced in paragraph (o)(1) of 
this AD remain fully applicable and must be complied with, including 
paragraph (k)(2) of AD 2010-14-07.
    We also found an additional incorrect paragraph reference. The 
first sentence of paragraph (p) of AD 2014-07-01 provides credit for 
the actions required by paragraphs (g), (h), (i), and (n)(2) of that 
AD. Paragraph (n)(2) of AD 2014-07-01 does not exist. The text of 
paragraph (p) of this AD has been revised to refer to paragraphs (g), 
(h), and (i) of this AD.
    We have also clarified that the airplanes affected by paragraph (i) 
of this AD include airplanes on which an interim modification, aft 
inner chord repair, or upper web repair has been previously 
accomplished as specified in Boeing Alert Service Bulletin 747-53A2427.

Compliance Time Change for Airplanes in Groups 4 and 5

    We have moved the compliance time specified in paragraph (j) of 
2014-07-01, Amendment 39-17815 (79 FR 23893, April 29, 2014), into new 
paragraphs (j)(1) and (j)(2) of this AD. Paragraph (j)(1) of this AD 
restates the compliance times for airplanes in Groups 1, 2, and 3. 
Paragraph (j)(2) of this AD provides a new compliance time for 
airplanes in Groups 4 and 5. We have added a compliance time (grace 
period) of ``18 months after the effective date of this AD'' for 
airplanes in Groups 4 and 5. We have determined that this new grace 
period will provide an acceptable level of safety.

FAA's Determination

    We are issuing 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.

AD Requirements

    This AD requires repetitive inspections, including post-repair and 
post-modification inspections, for cracking in the bulkhead structure 
at BS 2598; certain one-time inspections of certain fasteners and 
support frame modifications on certain airplanes; related investigative 
and corrective actions, if necessary; and an interim modification that 
would terminate certain repetitive inspections. This AD provides 
clarification of certain paragraph references and revises a compliance 
time.

FAA's Justification and Determination of the Effective Date

    Since this AD merely corrects incorrect paragraph references and 
includes a relieving grace period for certain airplanes, notice and 
opportunity for public comment before issuing this AD are unnecessary.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not provide you with notice and an opportunity to 
provide your comments before it becomes effective. However, we invite 
you to send any written data, views, or arguments about this AD. Send 
your comments to an address listed under the ADDRESSES section. Include 
``Docket No. FAA-2014-0432; Directorate Identifier 2014-NM-099-AD'' at 
the beginning of your comments. We specifically invite comments on the 
overall regulatory, economic, environmental, and energy aspects of this 
AD. We will consider all comments received by the closing date and may 
amend this AD because of those comments.
    We will post all comments we receive, without change, to <a href="http://www.regulations.gov">http://www.regulations.gov</a>, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this AD.

Costs of Compliance

    We estimate that this AD affects 184 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                Cost on U.S.
              Action                    Labor cost        Parts cost    Cost per product          operators
----------------------------------------------------------------------------------------------------------------
Bulkhead (support frame)           49 work-hours x $85            $0  $4,165 per            $766,360 per
 inspection.                        per hour = $4,165                  inspection cycle.     inspection cycle.
                                    per inspection
                                    cycle.
Support frame modification.......  315 work-hours x $85            0  $26,775.............  Up to $4,926,600.
                                    per hour = $26,775.
Support frame upper corner         16 work-hours x $85             0  $1,360..............  Up to $250,240.
 fastener inspection.               per hour = $1,360.
Support frame post-modification/   200 work hours x $85            0  $17,000.............  $3,128,000.
 post repair inspection.            per hour = $17,000.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary interim 
modification that would be required based on the results of the 
inspections of the bulkhead specified in paragraph (g) of this AD. We 
have no way of determining the number of aircraft that might need this 
interim modification:

[[Page 41122]]



                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Interim modification.........................  4 work-hours x $85 per hour =                $0             $340
                                                $340.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
a cost estimate for the corrective 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 part 39 of the Federal Aviation 
Regulations (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) 
2014-07-01, Amendment 39-17815 (79 FR 23893, April 29, 2014) and adding 
the following new AD:

2014-14-03 The Boeing Company: Amendment 39-17898; Docket No. FAA-
2014-0432; Directorate Identifier 2014-NM-099-AD.

(a) Effective Date

    This AD is effective July 15, 2014.

(b) Affected ADs

    This AD supersedes AD 2014-07-01, Amendment 39-17815 (79 FR 
23893, April 29, 2014).

(c) Applicability

    This AD applies to 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, certificated in 
any category, as identified in Boeing Alert Service Bulletin 747-
53A2427, Revision 7, dated July 19, 2013.

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by reports of cracking in particular areas 
of the bulkhead structure at body station (BS) 2598. We are issuing 
this AD to detect and correct fatigue cracking of the BS 2598 
bulkhead structure, which could adversely affect the structural 
integrity of the bulkhead and the horizontal stabilizer support 
structure, and result in loss of controllability of the airplane.

(f) Compliance

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

(g) Retained Inspections of the Bulkhead (Support Frame) With No 
Changes

    This paragraph restates the actions required by paragraph (g) of 
AD 2014-07-01, Amendment 39-17815 (79 FR 23893, April 29, 2014), 
with no changes. For airplanes on which the bulkhead (support frame) 
modification specified in Boeing Service Bulletin 747-53A2473 or 
Boeing Alert Service Bulletin 747-53A2837 has not been done, and on 
which an interim modification or aft inner chord repair specified in 
Boeing Alert Service Bulletin 747-53A2427 has not been done: At the 
applicable times specified in paragraph 1.E., ``Compliance,'' of 
Boeing Alert Service Bulletin 747-53A2427, Revision 7, dated July 
19, 2013, except as provided by paragraph (m)(1), (m)(2), or (m)(3) 
of this AD, as applicable, do an open-hole and surface high 
frequency eddy current (HFEC) inspection for cracking in the 
bulkhead (support frame), which includes the bulkhead splice 
fitting, frame supports, forward and aft inner chords, floor 
supports, and upper and lower web panels; do a surface HFEC 
inspection for cracking in the bulkhead upper web assembly; do an 
open-hole and surface HFEC inspection for cracking in the bulkhead 
lower web assembly; and do all applicable corrective actions; in 
accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin 747-53A2427, Revision 7, dated July 19, 2013, 
except as required by paragraphs (h), (m)(4), (m)(5), and (m)(6) of 
this AD. Do all applicable corrective actions before further flight. 
Repeat the applicable inspections, thereafter, at the applicable 
times specified in paragraph 1.E., ``Compliance,'' of Boeing Alert 
Service Bulletin 747-53A2427, Revision 7, dated July 19, 2013. Doing 
the modification required by paragraph (j) of this AD terminates the 
repetitive inspections required by this paragraph.

(h) Retained Interim Modification With No Changes

    This paragraph restates the actions required by paragraph (h) of 
AD 2014-07-01, Amendment 39-17815 (79 FR 23893, April 29, 2014), 
with no changes. For airplanes in Groups 1 and 2, as identified in 
Boeing Alert Service Bulletin 747-53A2427, Revision 7, dated July 
19, 2013, on which no cracking was found during any inspection 
required by paragraph (g) of this AD: At the applicable times 
specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service 
Bulletin 747-53A2427, Revision 7, dated July 19, 2013, except as 
provided by paragraph (m)(2) of this AD, do the interim 
modification, in accordance with the Accomplishment Instructions of 
Boeing Alert Service Bulletin 747-53A2427, Revision 7, dated July 
19, 2013. Doing the interim modification terminates the repetitive

[[Page 41123]]

inspections required by paragraph (g) of this AD in the area of the 
modification only. The repetitive inspections of the bulkhead lower 
web, as specified in paragraph (g) of this AD, must be done. If the 
aft inner chord repair or upper web repair specified in Boeing Alert 
Service Bulletin 747-53A2427, Revision 7, dated July 19, 2013, has 
been accomplished, an interim modification on the side of the 
airplane that has the repair is not required by this paragraph.

(i) Retained Post-Repair Inspection or Post-Interim Modification 
Inspection With a Clarification

    This paragraph restates the actions required by paragraph (i) of 
AD 2014-07-01, Amendment 39-17815 (79 FR 23893, April 29, 2014), 
with a clarification of the affected airplanes. For airplanes on 
which an interim modification, aft inner chord repair, or upper web 
repair has been done as specified in paragraph (g) or (h) of this 
AD, or has been previously accomplished as specified in Boeing Alert 
Service Bulletin 747-53A2427: At the applicable times specified in 
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 
747-53A2427, Revision 7, dated July 19, 2013, except as specified in 
paragraph (m)(1), (m)(2), or (m)(3) of this AD, as applicable, do 
the actions specified in paragraphs (i)(1) and (i)(2) of this AD, 
and all applicable corrective actions, in accordance with the 
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2427, Revision 7, dated July 19, 2013, except as required by 
paragraph (m)(4) of this AD. Do all applicable corrective actions 
before further flight. Repeat the inspections thereafter at the 
applicable intervals specified in paragraph 1.E., ``Compliance,'' of 
Boeing Alert Service Bulletin 747-53A2427, Revision 7, dated July 
19, 2013. Doing the modification required by paragraph (j) of this 
AD terminates the repetitive inspections required by this paragraph.
    (1) Do forward side surface HFEC inspections for cracking of the 
bulkhead forward inner chord, splice fitting, and frame support.
    (2) Do surface and open-hole HFEC inspections for cracking in 
the repaired and modified areas of the bulkhead, as applicable.

(j) Retained Bulkhead (Support Frame) Modification and Inspections With 
a Revised Compliance Time

    This paragraph restates the actions required by paragraph (j) of 
AD 2014-07-01, Amendment 39-17815 (79 FR 23893, April 29, 2014), 
with a revised compliance time. For airplanes on which the bulkhead 
(support frame) modification, as specified in Boeing Service 
Bulletin 747-53A2473 has not been done as of June 3, 2014 (the 
effective date of AD 2014-07-01): At the applicable time specified 
in paragraph (j)(1) or (j)(2) of this AD, do the bulkhead (support 
frame) modification and inspections, and all applicable related 
investigative and corrective actions; in accordance with steps 
3.B.3., 3.B.4., and 3.B.5. of the Accomplishment Instructions of 
Boeing Service Bulletin 747-53A2473, Revision 4, dated December 1, 
2011, except as required by paragraph (m)(4) of this AD. Do all 
applicable related investigative and corrective actions before 
further flight. Doing the modification in this paragraph terminates 
the inspections required by paragraphs (g) and (i) of this AD.
    (1) For Groups 1, 2, and 3 airplanes identified in Boeing 
Service Bulletin 747-53A2473, Revision 4, dated December 1, 2011: At 
the time specified in table 2 of paragraph 1.E., ``Compliance,'' of 
Boeing Service Bulletin 747-53A2473, Revision 4, dated December 1, 
2011.
    (2) For Groups 4 and 5 airplanes identified in Boeing Service 
Bulletin 747-53A2473, Revision 4, dated December 1, 2011: At the 
earlier of the times specified in paragraphs (j)(2)(i) and 
(j)(2)(ii) of this AD,
    (i) Before the accumulation of 20,000 total flight cycles or 
within 18 months after August 5, 2010 (the effective date of AD 
2010-14-07, Amendment 39-16352 (75 FR 38001, July 1, 2010), 
whichever occurs later.
    (ii) Before the accumulation of 12,000 total flight cycles or 
within 18 months after the effective date of this AD, whichever 
occurs later.

(k) Retained Post-Modification Inspections With No Changes

    This paragraph restates the actions required by paragraph (k) of 
AD 2014-07-01, Amendment 39-17815 (79 FR 23893, April 29, 2014), 
with no changes.
    (1) For airplanes on which the bulkhead (support frame) 
modification, as specified in Boeing Service Bulletin 747-53A2473 
has been done: Except as provided by paragraphs (m)(7) and (m)(8) of 
this AD, at the applicable time specified in tables 6, 7, 8, and 9 
of paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin 747-
53A2473, Revision 4, dated December 1, 2011, do support frame post-
modification inspections, and open-hole HFEC inspections for 
cracking in the hinge support, and do all applicable related 
investigative and corrective actions, in accordance with the 
Accomplishment Instructions of Boeing Service Bulletin 747-53A2473, 
Revision 4, dated December 1, 2011, except as required by paragraph 
(m)(4) of this AD. Do all applicable related investigative and 
corrective actions before further flight. Repeat the inspections 
thereafter at the applicable times specified in tables 6, 7, 8, and 
9 of paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin 747-
53A2473, Revision 4, dated December 1, 2011.
    (2) For airplanes on which the support frame modification, as 
specified in Boeing Service Bulletin 747-53A2473, Revision 1, dated 
February 20, 2007 (which is not incorporated by reference in this 
AD), has been done : Except as specified in paragraphs (m)(7) and 
(m)(8) of this AD, at the applicable time specified in tables 4 and 
5 of paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin 747-
53A2473, Revision 4, dated December 1, 2011, do a one-time general 
visual inspection of the frame web and upper shear deck (floor 
support) chord aft side for fasteners that were installed as part of 
an inner chord repair removal; and a one-time general visual 
inspection of the upper forward inner chord, frame support fitting, 
and splice fitting for the installation of certain fasteners; and do 
all applicable related investigative and corrective actions; in 
accordance with the Accomplishment Instructions of Boeing Service 
Bulletin 747-53A2473, Revision 4, dated December 1, 2011, except as 
required by paragraph (m)(4) of this AD. Do all applicable related 
investigative and corrective actions at the applicable times 
specified in tables 4 and 5 of paragraph 1.E., ``Compliance,'' of 
Boeing Service Bulletin 747-53A2473, Revision 4, dated December 1, 
2011.
    (3) For airplanes on which the support frame modification, as 
specified in Boeing Service Bulletin 747-53A2473, dated March 24, 
2005 (which was incorporated by reference in AD 2006-05-06, 
Amendment 39-14503 (71 FR 12125, March 9, 2006)), has been done: 
Except as specified in paragraphs (m)(7) and (m)(8) of this AD, at 
the applicable time specified in tables 5 and 10 of paragraph 1.E., 
``Compliance,'' of Boeing Service Bulletin 747-53A2473, Revision 4, 
dated December 1, 2011, do a one-time general visual inspection of 
the upper forward inner chord, frame support fitting, and splice 
fitting for the installation of certain fasteners; a one-time 
general visual inspection for any repair installed on the left and 
right side of the aft inner chord; and do all applicable related 
investigative and corrective actions; in accordance with the 
Accomplishment Instructions of Boeing Service Bulletin 747-53A2473, 
Revision 4, dated December 1, 2011, except as required by paragraph 
(m)(4) of this AD. Do all applicable related investigative and 
corrective actions at the applicable times specified in tables 5 and 
10 of paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin 
747-53A2473, Revision 4, dated December 1, 2011.
    (4) For airplanes on which a post-modification inspection was 
done using paragraph 3.B.8. of Part 1 of the Accomplishment 
Instructions of Boeing Service Bulletin 747-53A2473, Revision 3, 
dated July 14, 2011 (which is not incorporated by reference in this 
AD): Except as required by paragraphs (m)(7) and (m)(8) of this AD, 
at the applicable time in table 11 of paragraph 1.E., 
``Compliance,'' of Boeing Service Bulletin 747-53A2473, Revision 4, 
dated December 1, 2011, do a one-time surface HFEC inspection of the 
support frame outer chord for cracking, in accordance with Part 1 of 
the Accomplishment Instructions of Boeing Service Bulletin 747-
53A2473, Revision 4, dated December 1, 2011. If any cracking is 
found, repair before further flight, using a method approved in 
accordance with the procedures specified in paragraph (q) of this 
AD.

(l) Retained Post-Modification and Post-Repair Inspections With No 
Changes

    This paragraph restates the actions required by paragraph (l) of 
AD 2014-07-01, Amendment 39-17815 (79 FR 23893, April 29, 2014), 
with no changes. For airplanes on which cracking was found during a 
post-modification inspection and was repaired by doing the 
installation of an upper or lower corner post-modification web crack 
repair, as specified in Boeing Service Bulletin 747-

[[Page 41124]]

53A2473, Revision 4, dated December 1, 2011: At the applicable times 
specified in tables 6 and 8 of paragraph 1.E., ``Compliance,'' of 
Boeing Service Bulletin 747-53A2473, Revision 4, dated December 1, 
2011, do a bulkhead (support frame) post-repair inspection, and do 
all applicable corrective actions, in accordance with paragraph a., 
b., or c. of Part 4 of paragraph 3.B.8 of the Accomplishment 
Instructions of Boeing Service Bulletin 747-53A2473, Revision 4, 
dated December 1, 2011, as applicable, except as required by 
paragraph (m)(4) of this AD. Repeat the inspection, thereafter, at 
the applicable times specified in tables 6 and 8 of paragraph 1.E., 
``Compliance,'' of Boeing Service Bulletin 747-53A2473, Revision 4, 
dated December 1, 2011.

(m) Retained Exceptions to Service Information With No Changes

    This paragraph restates the exceptions specified in paragraph 
(m) of AD 2014-07-01, Amendment 39-17815 (79 FR 23893, April 29, 
2014), with no changes.
    (1) Where Boeing Alert Service Bulletin 747-53A2427, Revision 7, 
dated July 19, 2013, specifies a compliance time after ``the date on 
Revision 2 of this service bulletin,'' this AD requires compliance 
within the specified compliance time after August 28, 2001 (the 
effective date of AD 2001-15-03, Amendment 39-12337 (66 FR 38365, 
July 24, 2001)).
    (2) Where Boeing Alert Service Bulletin 747-53A2427, Revision 7, 
dated July 19, 2013, specifies a compliance time after ``the date on 
Revision 4 of this service bulletin,'' this AD requires compliance 
within the specified compliance time after August 5, 2010 (the 
effective date of AD 2010-14-07, Amendment 39-16352 (75 FR 38001, 
July 1, 2010)).
    (3) Where Boeing Alert Service Bulletin 747-53A2427, Revision 7, 
dated July 19, 2013, specifies a compliance time ``after the date on 
the respective service bulletin revision'' this AD requires 
compliance within the specified compliance time after June 3, 2014 
(the effective date of AD 2014-07-01 Amendment 39-17815 (79 FR 
23893, April 29, 2014)).
    (4) If any cracking is found during any inspection required by 
this AD, and Boeing Alert Service Bulletin 747-53A2427, Revision 7, 
dated July 19, 2013; or Boeing Service Bulletin 747-53A2473, 
Revision 4, dated December 1, 2011; specifies to contact Boeing for 
appropriate action: Before further flight, repair the crack using a 
method approved in accordance with the procedures specified in 
paragraph (q) of this AD.
    (5) If, during any inspection required by paragraph (g) of this 
AD, any cracking is found in the bonded web doubler, before further 
flight, repair using a method approved in accordance with the 
procedures specified in paragraph (q) of this AD.
    (6) Where Part 1 of the Accomplishment Instructions of Boeing 
Alert Service Bulletin 747-53A2427, Revision 7, dated July 19, 2013, 
specifies accomplishing inspections for cracking in the forward and 
aft inner chords, splice fittings, floor supports, and upper and 
lower web panels, this AD also requires doing an open-hole HFEC 
inspection of the bonded web doubler if present.
    (7) Where Boeing Service Bulletin 747-53A2473, Revision 4, dated 
December 1, 2011, specifies a compliance time ``after the date on 
Revision 2 of this service bulletin,'' this AD requires compliance 
within the specified compliance time as of August 5, 2010 (the 
effective date of AD 2010-14-07, Amendment 39-16352 (75 FR 38001, 
July 1, 2010)).
    (8) Where Boeing Service Bulletin 747-53A2473, Revision 4, dated 
December 1, 2011, specifies a compliance time ``after the date on 
Revision 3 of this service bulletin,'' or ``after the date on 
Revision 4 of this service bulletin,'' this AD requires compliance 
within the specified compliance time after June 3, 2014 (the 
effective date of AD 2010-14-07, Amendment 39-17815 (79 FR 23893, 
April 29, 2014)).

(n) Retained Optional Terminating Modification With No Changes

    This paragraph restates the actions required by paragraph (n) of 
AD 2014-07-01, Amendment 39-17815 (79 FR 23893, April 29, 2014), 
with no changes. Accomplishing the modification of the bulkhead at 
BS 2598 in accordance with the Accomplishment Instructions of Boeing 
Alert Service Bulletin 747-53A2837, dated July 13, 2012, terminates 
the requirements of paragraphs (g), (h), (i), (j), (k), and (l) of 
this AD, except where Boeing Alert Service Bulletin 747-53A2837, 
dated July 13, 2012, specifies to contact Boeing for appropriate 
action: Before further flight, repair the crack using a method 
approved in accordance with the procedures specified in paragraph 
(q) of this AD.

(o) Retained Terminating Action for Certain Requirements of AD 2010-14-
07, Amendment 39-16352 (75 FR 38001, July 1, 2010), With Revised 
Terminating Action

    This paragraph restates the terminating actions specified in 
paragraph (o) of AD 2014-07-01, Amendment 39-17815 (79 FR 23893, 
April 29, 2014), with revised terminating action within paragraph 
(o)(1) of this AD.
    (1) Accomplishing the inspections, repairs, and modification in 
accordance with the Accomplishment Instructions of Boeing Service 
Bulletin 747-53A2473, Revision 4, dated December 1, 2011, is an 
acceptable terminating action for the corresponding inspections, 
repairs, and modification at the BS 2598 support frame required by 
paragraphs (i), (j), (k)(1), (m), (n), (o), (p), (q), (r), (s), (t), 
(u), and (v) of AD 2010-14-07, Amendment 39-16352 (75 FR 38001, July 
1, 2010). Where Boeing Service Bulletin 747-53A2473, Revision 4, 
dated December 1, 2011, specifies to contact Boeing for repair 
instructions, the repair instructions must be approved in accordance 
with the procedures specified in paragraph (q) of this AD. All 
provisions of AD 2010-14-07 that are not specifically referenced in 
this paragraph remain fully applicable and must be complied with, 
including paragraph (k)(2) of AD 2010-14-07.
    (2) Accomplishing the inspections, repairs, and interim 
modification in accordance with Boeing Alert Service Bulletin 747-
53A2427, Revision 7, dated July 19, 2013, is an acceptable 
terminating action for the corresponding inspections, repairs and 
interim modification at the BS 2598 bulkhead required by paragraphs 
(i), (j), (o), (s), (t), (u), and (v) of AD 2010-14-07, Amendment 
39-16352 (75 FR 38001, July 1, 2010). Where Boeing Alert Service 
Bulletin 747-53A2427, Revision 7, dated July 19, 2013, specifies to 
contact Boeing for repair data, the repair data must be approved in 
accordance with the procedures specified in paragraph (q) of this 
AD. All provisions of AD 2010-14-07 that are not specifically 
referenced in this paragraph remain fully applicable and must be 
complied with.

(p) Retained Credit for Previous Actions With Change to Paragraph 
Reference

    This paragraph restates the credit specified in paragraph (p) of 
AD 2014-07-01, Amendment 39-17815 (79 FR 23893, April 29, 2014), 
with a change to a paragraph reference. This paragraph provides 
credit for the actions required by paragraphs (g), (h), and (i) of 
this AD, if those actions were performed before June 3, 2014 (the 
effective date of AD 2014-07-01) using Boeing Alert Service Bulletin 
747-53A2427, Revision 6, dated July 14, 2011, provided that the 
additional actions added in Boeing Alert Service Bulletin 747-
53A2427, Revision 7, dated July 19, 2013, are done within the 
applicable compliance times specified in paragraphs (g), (h), and 
(i) of this AD. Boeing Alert Service Bulletin 747-53A2427, Revision 
6, dated July 14, 2011, is not incorporated by reference in this AD.

(q) 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 (r)(1) of this AD. 
Information may be emailed to: <a href="/cdn-cgi/l/email-protection#e2dbcfa3acafcfb1878396968e87cfa3a1adcfa3afada1cfb087939787919691a2848383cc858d94"><span class="__cf_email__" data-cfemail="695044282724443a0c081d1d050c44282a26442824262a443b0c181c0c1a1d1a290f0808470e061f">[email&#160;protected]</span></a>.
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.
    (3) An AMOC that provides an acceptable level of safety may be 
used for any repair 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) Related portions or applicable paragraphs of AMOCs approved 
previously for AD 2010-14-07, Amendment 39-16352 (75 FR 38001, July 
1, 2010), are approved as AMOCs for the corresponding provisions of 
paragraphs (g), (h), (i), (j), (k), and (l) of this AD. All new 
actions specified in paragraphs

[[Page 41125]]

(g), (h), (i), (j), (k), and (l) of this AD that are not identified 
in a previously approved AMOC must still be done.
    (5) AMOCs approved for AD 2014-07-01, Amendment 39-17815 (79 FR 
23893, April 29, 2014), are approved as AMOCs for the corresponding 
provisions of this AD.

(r) Related Information

    (1) For more information about this AD, contact Nathan Weigand, 
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle ACO, 
1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6428; 
fax: 425-917-6590; email: <a href="/cdn-cgi/l/email-protection#e08e819488818ece90ce97858987818e84a0868181ce878f96"><span class="__cf_email__" data-cfemail="5836392c3039367628762f3d313f39363c183e3939763f372e">[email&#160;protected]</span></a>.
    (2) Service information identified in this AD that is not 
incorporated by reference in this AD may be viewed at the addresses 
specified in paragraphs (s)(4) and (s)(5) of this AD.

(s) 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.
    (3) The following service information was approved for IBR on 
June 3, 2014 (79 FR 23893).
    (i) Boeing Alert Service Bulletin 747-53A2427, Revision 7, dated 
July 19, 2013.
    (ii) Boeing Service Bulletin 747-53A2473, Revision 4, dated 
December 1, 2011.
    (iii) Boeing Alert Service Bulletin 747-53A2837, dated July 13, 
2012.
    (4) For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-
5000, extension 1; fax 206-766-5680; Internet <a href="https://www.myboeingfleet.com">https://www.myboeingfleet.com</a>.
    (5) 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.
    (6) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: <a href="http://www.archives.gov/federal-register/cfr/ibr-locations.html">http://www.archives.gov/federal-register/cfr/ibr-locations.html</a>.

    Issued in Renton, Washington, on July 3, 2014.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-16381 Filed 7-14-14; 8:45 am]
BILLING CODE 4910-13-P