[Federal Register Volume 79, Number 82 (Tuesday, April 29, 2014)]
[Rules and Regulations]
[Pages 23893-23897]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2014-07339]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0425; Directorate Identifier 2012-NM-224-AD; 
Amendment 39-17815; AD 2014-07-01]
RIN 2120-AA64


Airworthiness Directives; the Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
The Boeing Company Model 747 airplanes. This AD was prompted by reports 
of cracking in particular areas of the bulkhead structure at body 
station (BS) 2598. 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. 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 June 3, 2014.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of June 3, 2014

ADDRESSES: 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 by searching for and locating Docket No. FAA-2013-
0425; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this AD, the regulatory evaluation, any comments received, and 
other information. The address for the Docket Office (phone: 800-647-
5527) is Docket Management Facility, U.S. Department of Transportation, 
Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 
New Jersey Avenue SE., Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Nathan Weigand, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6428; fax: 
425-917-6590; email: [email protected].

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a supplemental notice of proposed rulemaking (SNPRM) to 
amend 14 CFR part 39 by adding an AD that would apply to certain The 
Boeing Company Model 747 airplanes. The SNPRM published in the Federal 
Register on January 2, 2014 (79 FR 65). We preceded the SNPRM with a 
notice of proposed rulemaking (NPRM) that published in the Federal 
Register on May 28, 2013 (78 FR 31867).

[[Page 23894]]

    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; and repetitive post-repair inspections of the support frame, 
and corrective actions, if necessary. For certain airplanes, the NPRM 
proposed to require:
     Inspections for cracking in the repaired area of the 
bulkhead, and corrective actions if necessary;
     A support frame modification and inspections, and related 
investigative and corrective actions, if necessary;
     Repetitive post-repair inspections of the support frame 
and inspections for cracking in the hinge support, and related 
investigative and corrective actions if necessary;
     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;
     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; and
     A one-time inspection of the support frame outer chord for 
cracking, and repair if necessary.
    The NPRM was prompted by 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.
    The SNPRM proposed to add an optional terminating action for 
certain inspections and expand the inspection area for certain surface 
and open-hole high frequency eddy current (HFEC) inspections. 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.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We have considered the comment received. Boeing supported the 
SNPRM (79 FR 65, January 2, 2014).

Conclusion

    We reviewed the relevant data, considered the comment received, and 
determined that air safety and the public interest require adopting 
this AD as proposed except for minor editorial changes. We have 
determined that these minor changes:
     Are consistent with the intent that was proposed in the 
SNPRM (79 FR 65, January 2, 2014) for correcting the unsafe condition; 
and
     Do not add any additional burden upon the public than was 
already proposed in the SNPRM (79 FR 65, January 2, 2014).

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

    We estimate the following costs to do any necessary interim 
modification that would be required based on the results of inspection 
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:

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

[[Page 23895]]

13132. This AD will not have a substantial direct effect on the States, 
on the relationship between the national government and the States, or 
on the distribution of power and responsibilities among the various 
levels of government.
    For the reasons discussed above, I certify that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979),
    (3) Will not affect intrastate aviation in Alaska, and
    (4) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

2014-07-01 The Boeing Company: Amendment 39-17815; Docket No. FAA-
2013-0425; Directorate Identifier 2012-NM-224-AD.

(a) Effective Date

    This AD is effective June 3, 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

    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) Inspections of the Bulkhead (Support Frame)

    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) 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 
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) Post-Repair Inspection or Post-Interim Modification Inspection

    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: 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) Bulkhead (Support Frame) Modification and Inspections

    For airplanes on which the bulkhead (support frame) 
modification, as specified in Boeing Service Bulletin 747-53A2473 
has not been done as of the effective date of this AD: At the 
applicable time specified 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, 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

[[Page 23896]]

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) Post-Modification and Post-Repair Inspections

    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 747-53A2473, 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 to Service Information

    (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 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 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 the effective date of 
this AD.''

(n) Optional Terminating Modification

    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) 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 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-

[[Page 23897]]

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.
    (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) 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. 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: [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 in accordance with 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 (g), (h), (i), (j), (k), 
and (l) of this AD that are not identified in a previously approved 
AMOC 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 ACO, 
1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6428; 
fax: 425-917-6590; email: [email protected].
    (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)(3) and (s)(4) 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.
    (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.
    (3) For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-
5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com.
    (4) You may view this service information at FAA, Transport 
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For 
information on the availability of this material at the FAA, call 
425-227-1221.
    (5) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on March 17, 2014.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-07339 Filed 4-28-14; 8:45 am]
BILLING CODE 4910-13-P