[Federal Register Volume 79, Number 1 (Thursday, January 2, 2014)]
[Proposed Rules]
[Pages 65-70]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2013-31315]


 ========================================================================
 Proposed Rules
                                                 Federal Register
 ________________________________________________________________________
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 This section of the FEDERAL REGISTER contains notices to the public of 
 the proposed issuance of rules and regulations. The purpose of these 
 notices is to give interested persons an opportunity to participate in 
 the rule making prior to the adoption of the final rules.
 
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 

  Federal Register / Vol. 79, No. 1 / Thursday, January 2, 2014 / 
Proposed Rules  

[[Page 65]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0425; Directorate Identifier 2012-NM-224-AD]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

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

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

SUMMARY: We are revising an earlier proposed airworthiness directive 
(AD) for certain The Boeing Company Model 747 airplanes. The NPRM 
proposed to require repetitive inspections for cracking in the bulkhead 
splice fitting, frame supports, forward and aft inner chords, and floor 
support; an inspection for cracking in the bulkhead upper web, doubler, 
and bulkhead lower web; and corrective actions if necessary; for 
certain airplanes, inspections for cracking in the repaired area of the 
bulkhead, and corrective actions if necessary; for certain airplanes, 
support frame modification and support frame inspections, and related 
investigative and corrective actions, if necessary; for certain 
airplanes, repetitive support frame post-modification inspections and 
inspections for cracking in the hinge support, and related 
investigative and corrective actions if necessary; for certain 
airplanes, a one-time inspection of the frame web and upper shear deck 
(floor support) chord aft side for fasteners; and a one-time inspection 
of the upper forward inner chord, frame support fitting and splice 
fitting, for the installation of certain fasteners; and related 
investigative and corrective actions if necessary; for certain 
airplanes, a one-time inspection of the upper forward inner chord, 
frame support fitting and splice fitting for the installation of 
certain fasteners; a one-time inspection for any repair installed on 
the left and right side of the aft inner chord, and related 
investigative and corrective actions, if necessary; for certain 
airplanes, a one-time inspection of the support frame outer chords for 
cracking, and repair if necessary; and repetitive support frame post-
repair inspections, and corrective actions, if necessary. The NPRM was 
prompted by reports of cracking in the forward and aft inner chord of 
the body station (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. This action revises the NPRM by adding an optional 
terminating action for certain inspections and expanding the inspection 
area for certain surface and open-hole HFEC inspections. We are 
proposing this supplemental NPRM (SNPRM) 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. 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 February 18, 2014.

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: 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 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.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov; 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, 
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-2013-0425; 
Directorate Identifier 2012-NM-224-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 include an AD that 
would

[[Page 66]]

apply to certain 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. 
The NPRM published in the Federal Register on May 28, 2013 (78 FR 
31867). The NPRM proposed to require repetitive inspections for 
cracking in the bulkhead splice fitting, frame supports, forward and 
aft inner chords, and floor support; doing an inspection for cracking 
in the bulkhead upper web, doubler, and bulkhead lower web; and 
corrective actions if necessary; for certain airplanes, inspections for 
cracking in the repaired area of the bulkhead, and corrective actions 
if necessary; for certain airplanes, support frame modification and 
support frame inspections, and related investigative and corrective 
actions, if necessary; for certain airplanes, repetitive support frame 
post-modification inspections and inspections for cracking in the hinge 
support, and related investigative and corrective actions if necessary; 
for certain airplanes, a one-time inspection of the frame web and upper 
shear deck (floor support) chord aft side for fasteners; and a one-time 
inspection of the upper forward inner chord, frame support fitting and 
splice fitting, for the installation of certain fasteners; and related 
investigative and corrective actions if necessary; for certain 
airplanes, a one-time inspection of the upper forward inner chord, 
frame support fitting and splice fitting for the installation of 
certain fasteners; a one-time inspection for any repair installed on 
the left and right side of the aft inner chord, and related 
investigative and corrective actions, if necessary; for certain 
airplanes, a one-time inspection of the support frame outer chord for 
cracking, and repair if necessary; and repetitive support frame post-
repair inspections, and corrective actions, if necessary.

Actions Since Previous NPRM (78 FR 31867, May 28, 2013) Was Issued

    Since we issued the NPRM (78 FR 31867, May 28, 2013), we have 
received Boeing Alert Service Bulletin 747-53A2427, Revision 7, dated 
July 19, 2013, which extends the open-hole HFEC inspection for cracking 
to include more fastener holes common to the upper and lower splice 
fittings on both sides of the bulkhead, plus some additional fastener 
holes adjacent to the lower splice fitting. Boeing Alert Service 
Bulletin 747-53A2427, Revision 7, dated July 19, 2013, also extends the 
surface HFEC inspection for cracking to include the fillet radius area 
of the upper splice fitting. Boeing Alert Service Bulletin 747-53A2427, 
Revision 7, dated July 19, 2013, clarifies compliance times for the 
initial surface HFEC inspection of the upper web for airplanes modified 
or repaired before the upper web inspection was added. Boeing Alert 
Service Bulletin 747-53A2427, Revision 7, dated July 19, 2013, also 
adds an optional terminating modification for certain inspections.

Comments

    We gave the public the opportunity to comment on the NPRM (78 FR 
31867, May 28, 2013). The following presents the comments received on 
the NPRM (78 FR 31867, May 28, 2013) and the FAA's response to each 
comment.

Request To Replace the NPRM (78 FR 31867, May 28, 2013)

    Atlas Air, Inc. requested that the NPRM (78 FR 31867, May 28, 2013) 
be replaced with four separate ADs. The commenter stated that having a 
separate AD for Boeing Alert Service Bulletin 747-53A2427, Revision 7, 
dated July 19, 2013; Boeing Service Bulletin 747-53A2449, Revision 2, 
dated March 14, 2002; Boeing Alert Service Bulletin 747-53A2467, 
Revision 1, dated April 28, 2005; and Boeing Service Bulletin 747-
53A2473, Revision 4, dated December 1, 2011; would simplify the 
requirements and future supersedures. The commenter also stated that 
separate ADs will ease the burden on the operators.
    We disagree with replacing the NPRM (78 FR 31867, May 28, 2013). 
Increasing the number of ADs to four does not necessarily ease the 
operator burden. We find that delaying this action to resubmit as a 
separate AD, would be inappropriate in light of the urgency of the 
identified unsafe condition. No changes have been made to this SNPRM in 
this regard.

Request for Alternative Method of Compliance (AMOC) Approval for 
Previously Approved AMOCs

    Atlas Air, Inc. requested that AMOCs approved for paragraphs (i), 
(j), (m), (n), (o), (p), (q), (r), (s), (t), (u), and (v), of AD 2010-
14-07 (75 FR 38001, July 1, 2010), be approved as AMOCs to the 
corresponding actions of the NPRM (78 FR 31867, May 28, 2013).
    We agree with the request. Although the actions in some of the 
paragraphs referenced above carry over to paragraphs (g), (h), (i), 
(j), (k), and (l) of this SNPRM, AD 2010-14-07 (75 FR 38001, July 1, 
2010) was superseded and added new inspections and requirements, for 
which previously approved AMOCs would not provide coverage. We have 
added new paragraph (q)(4) to this SNPRM stating that previously 
approved AMOCs for AD 2010-14-07 are approved for the corresponding 
actions in this SNPRM. All actions specified in paragraphs (g), (h), 
(i), (j), (k), and (l) of this SNPRM that are not identified in the 
AMOC must still be done.

Request Authorization of Modification in Boeing Service Bulletin 747-
53A2837 as an AMOC to Requirements of Paragraphs (j), (k), and (l) of 
the NPRM (78 FR 31867, May 28, 2013)

    Atlas Air, Inc. requested that the NPRM (78 FR 31867, May 28, 2013) 
be revised to authorize the modification in Boeing Service Bulletin 
747-53A2837 as an AMOC to the requirements of paragraphs (j), (k), and 
(l) of the NPRM.
    We agree with the request. Boeing Service Bulletin 747-53A2837, 
dated July 13, 2012, was approved as an AMOC to AD 2010-14-07 (75 FR 
38001, July 1, 2010). Accomplishing the modification of the bulkhead at 
BS 2598, in accordance with the Accomplishment Instructions of Boeing 
Service Bulletin 747-53A2837, dated July 13, 2012, terminates the 
requirements of paragraphs (g), (h), (i), (j), (k), and (l) of this AD. 
We have added new paragraph (n) to this SNPRM to provide this optional 
terminating modification.

Request for Clarification of Language in Paragraph (g) of the NPRM (78 
FR 31867, May 28, 2013)

    Boeing requested that we delete the phrase, ``and doubler,'' and 
add the word, ``assembly'' to bulkhead upper web and bulkhead lower web 
in paragraph (g) of the NPRM (78 FR 31867, May 28, 2013). Boeing stated 
that the language in Boeing Alert Service Bulletin 747-53A2427, 
Revision 6, dated July 14, 2011, was in error and this requested change 
clarifies the NPRM to match the intent of this service bulletin.
    We agree to clarify the language and have made the requested 
changes to paragraph (g) of this SNPRM accordingly.

Request for Clarification of Language in Paragraph (m)(5) and (m)(6) of 
the NPRM (78 FR 31867, May 28, 2013)

    Boeing requested that we add the phrase ``bonded web'' to the word 
``doubler'' in paragraphs (m)(5) and (m)(6) of the NPRM (78 FR 31867, 
May 28, 2013). Boeing stated that the language in Boeing Alert Service 
Bulletin 747-53A2427, Revision 6, dated July 14, 2011, was in error and 
this requested change clarifies the

[[Page 67]]

NPRM to match the intent of this service bulletin. Boeing also 
requested that we add the phrase ``if present'' to paragraph (m)(6) of 
the NPRM.
    We agree to clarify the language and have made the requested 
changes to paragraphs (m)(5) and (m)(6) of this SNPRM accordingly. We 
have also added the phrase ``if present'' to paragraph (m)(6) of this 
SNPRM.

Request To Correct Compliance Time

    Boeing requested that we correct the compliance time specified in 
paragraph (m)(2) of the NPRM (78 FR 31867, May 28, 2013) to be from the 
effective date of AD 2010-14-07, Amendment 39-16352 (75 FR 38001, July 
1, 2010). Boeing Alert Service Bulletin 747-53A2427, Revision 6, dated 
July 14, 2011, was not mandated by AD 2006-05-06, Amendment 39-14503 
(71 FR 12125, March 9, 2006).
    We agree with the request and have made the change to paragraph 
(m)(2) of this SNPRM accordingly.

Other Changes to SNPRM

    We have updated paragraphs (c), (g), (h), (i), (m), and (o) of this 
SNPRM to refer to Boeing Alert Service Bulletin 747-53A2427, Revision 
7, dated July 19, 2013. We have also added the area of the upper and 
lower web panels to the open hole and surface HFEC inspections 
specified in paragraph (g) of this SNPRM. We have clarified the 
affected airplanes for paragraph (g) of this SNPRM by qualifying the 
airplanes to those on which an interim modification or aft inner chord 
repair has not been done, as specified in Boeing Alert Service Bulletin 
747-53A2427. We have also provided credit for 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 SNPRM.

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 these same type 
designs. Certain changes described above expand the scope of the NPRM 
(78 FR 31867, May 28, 2013). 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 the SNPRM

    This SNPRM would require accomplishing the actions specified in the 
service information described previously.

Costs of Compliance

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

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                  Cost per
            Action                Labor cost      Parts cost      product            Cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
Inspection...................  49 work-hours x            $0  $4,165 per       $766,360 per inspection cycle.
                                $85 per hour =                 inspection
                                $4,165 per                     cycle.
                                inspection
                                cycle.
Support frame modification...  315 work-hours x           $0  $26,775........  Up to $4,926,600.
                                $85 per hour =
                                $26,775.
Support frame upper corner     16 work-hours x            $0  $1,360.........  Up to $250,240.
 fastener inspection.           $85 per hour =
                                $1,360.
Support frame post-            200 work hours x           $0  $17,000........  $3,128,000.
 modification inspection.       $85 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 
proposed inspection. We have no way of determining the number of 
aircraft that might need this interim modification:

                                               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 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,

[[Page 68]]

    (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]

    2. The FAA amends Sec.  39.13 by adding the following new 
airworthiness directive (AD):

The Boeing Company: Docket No. FAA-2013-0425; Directorate Identifier 
2012-NM-224-AD.

(a) Comments Due Date

    We must receive comments by February 18, 2014.

(b) Affected ADs

    This AD affects AD 2010-14-07, Amendment 39-16352 (75 FR 38001, 
July 1, 2010).

(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

    Joint Aircraft System Component (JASC)/Air Transport Association 
(ATA) of America Code 53, Fuselage.

(e) Unsafe Condition

    This AD was prompted by reports of cracking in the forward and 
aft inner chord of the body station (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 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) Inspections of the Bulkhead (Support Frame)

    For airplanes on which the bulkhead (support frame) modification 
specified in Boeing Service Bulletin 747-53A2473 or 747-53A2837 has 
not been accomplished, and on which an interim modification or aft 
inner chord repair has not been done 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 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 (m)(4), (m)(5) and (m)(6) 
of this AD, and except as provided by paragraph (h) of this AD. Do 
all applicable corrective actions before further flight. Repeat the 
applicable inspections, thereafter, at the applicable times 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) Interim Modification

    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 inspections 
requirement of 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) Post-Repair Inspection or Post-Interim Modification Inspection

    For airplanes on which an interim modification, or aft inner 
chord repair, or upper web repair has been done as specified in 
paragraph (g) or (h) 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 specified in 
paragraph (m)(1), (m)(2), or (m)(3) of this AD, as applicable, do 
the actions specified in paragraph (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) Bulkhead (Support Frame) Modification and Inspections

    For airplanes on which the bulkhead (support frame) modification 
specified in Boeing Service Bulletin 747-53A2473, dated March 24, 
2005; Revision 1, dated February 20, 2007; Revision 2, dated August 
28, 2009; Revision 3, dated July 14, 2011; or Revision 4, dated 
December 1, 2011; has not been done as of the effective date of this 
AD: At the applicable time in tables 2 and 3 of paragraph 1.E., 
``Compliance,'' of Boeing Service Bulletin 747-53A2473, Revision 4, 
dated December 1, 2011, 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.

(k) Post Modification Inspections

    (1) For airplanes on which the bulkhead (support frame) 
modification has been done as specified in Boeing Service Bulletin 
747-53A2473, dated March 24, 2005; Revision 1, dated February 20, 
2007; Revision 2, dated August 28, 2009; Revision 3, dated July 14, 
2011; or Revision 4, dated December 1, 2011:

[[Page 69]]

Except as provided by paragraphs (m)(7) and (m)(8) of this AD, at 
the applicable time 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). Do 
all applicable related investigative and corrective actions before 
further flight. Repeat the inspections thereafter at the applicable 
times 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 has 
been done as specified in Boeing Service Bulletin 747-53A2473, 
Revision 1, dated February 20, 2007: Except as specified in 
paragraphs (m)(7) and (m)(8) of this AD, at the applicable time 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 has 
been done as specified in Boeing Service Bulletin 747-53A2473, dated 
March 24, 2005: Except as specified in paragraphs (m)(7) and (m)(8) 
of this AD, at the applicable time 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 in accordance with paragraph 3.B.8. of Part 1 of the 
Accomplishment Instructions of Boeing Service Bulletin 747-53A2473, 
Revision 3, dated July 14, 2011: 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) Post-Modification Post-Repair Inspections

    For airplanes on which post-modification inspection cracks were 
repaired by doing the installation of an upper or lower corner post-
modification web crack repair as specified in Boeing Service 
Bulletin 747-53A2473, 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) Exceptions

    (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 as of 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 as of 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 
Revision 6 or Revision 7 of this service bulletin, this AD requires 
compliance within the specified compliance time ``after the 
effective date of this AD.''
    (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 cracks for 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 that 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 or 4 of that service bulletin, this AD requires 
compliance within the specified compliance time ``after the 
effective date of this AD.''

(n) Optional Termination Modification

    Accomplishing the modification of the bulkhead at body station 
2598, in accordance with the Accomplishment Instructions of Boeing 
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 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) Terminating Action for Certain Requirements of AD 2010-14-07, 
Amendment 39-16352 (75 FR 38001, July 1, 2010)

    (1) Accomplishing the inspections, repairs, and modification in 
accordance with Boeing Service Bulletin 747-53A2473, Revision 4, 
dated December 1, 2011, is a terminating action for the 
corresponding inspections, repairs, and modification at the STA 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 by the FAA in accordance with 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.

[[Page 70]]

    (2) Accomplishing the inspections, repairs and interim 
modification in accordance with Boeing Alert Service Bulletin 747-
53A2427, Revision 7, dated July 19, 2013, is a terminating action 
for the corresponding inspections, repairs and interim modification 
at the STA 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). When 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 by the FAA in 
accordance with 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) Credit for Previous Actions

    This paragraph provides credit for the actions required by 
paragraphs (g), (h), (i), and (n)(2) of this AD, if those actions 
were performed before the effective date of this AD 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.

(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: [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) 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 related corresponding 
provisions of paragraphs (g), (h), (i), (j), (k), and (l) of this 
AD. All new actions specified in paragraphs (g), (h), (i), (j), (k), 
and (l) of this AD that are not identified in the AMOCs must still 
be done.

(r) Related Information

    (1) For more information about this AD, contact Nathan Weigand, 
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft 
Certification Office, 1601 Lind Avenue SW., Renton, WA 98057-3356; 
phone: 425-917-6428; fax: 425-917-6590; email: 
[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; 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.

    Issued in Renton, Washington, on December 20, 2013.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2013-31315 Filed 12-31-13; 8:45 am]
BILLING CODE 4910-13-P