Document ID: FAA-2015-2961-0006
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: The Boeing Company Airplanes
Posted Date: 2016-03-18T04:00Z

[Federal Register Volume 81, Number 53 (Friday, March 18, 2016)]
[Rules and Regulations]
[Pages 14693-14698]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-05249]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-2961; Directorate Identifier 2014-NM-145-AD; 
Amendment 39-18430; AD 2016-05-12]
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 superseding Airworthiness Directive (AD) 2012-15-13, 
for certain The Boeing Company Model 747-100B SUD, 747-300, 747-400, 
and 747-400D series airplanes; and Model 747-200B series airplanes 
having a stretched upper deck. AD 2012-15-13 required inspections for 
cracking and discrepancies of certain fasteners; modification of the 
frame-to-tension-tie joints; repetitive post-modification inspections; 
related investigative and corrective actions if necessary; and 
repetitive inspections for cracking in the tension tie channels, and 
repair if necessary. For certain airplanes, AD 2012-15-13 also required 
an inspection to determine if the angle is installed correctly, and re-
installation if necessary; and an inspection at the fastener locations 
where the tension tie previously attached to the frame prior to certain 
modifications, and repair if necessary. This new AD adds a new 
inspection for cracking in the tension tie channels and post-
modification inspections of the modified tension ties for cracking, and 
repair if necessary. This AD was prompted by an evaluation indicated 
that the upper deck is subject to widespread fatigue damage (WFD). We 
are issuing this AD to prevent fatigue cracking of the tension ties, 
shear webs, and frames of the upper deck, which could result in rapid 
decompression and reduced structural integrity of the airplane.

DATES: This AD is effective April 22, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of April 22, 
2016.
    The Director of the Federal Register approved the incorporation by 
reference of certain other publications listed in this AD as of 
September 12, 2012 (77 FR 47267, August 8, 2012).
    The Director of the Federal Register approved the incorporation by 
reference of a certain other publication listed in this AD as of 
November 28, 2007 (72 FR 65655, November 23, 2007).

ADDRESSES: For service information identified in this final rule, 
contact Boeing Commercial Airplanes, Attention: Data & Services 
Management, P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 
206-544-5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. You may view this referenced service information 
at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., 
Renton, WA. For information on the availability of this material at the 
FAA, call 425-227-1221. It is also available on the Internet at https:/
/

[[Page 14694]]

www.regulations.gov by searching for and locating Docket No. FAA-2015-
2961.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.govby searching for and locating Docket No. FAA-2015-
2961; 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: Bill Ashforth, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6432; fax: 
425-917-6590; email: bill.ashforth@faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2012-15-13, Amendment 39-17142 (77 FR 47267, 
August 8, 2012) (``AD 2012-15-13''). AD 2012-15-13 applied to certain 
The Boeing Company Model 747-100B SUD, 747-300, 747-400, and 747-400D 
series airplanes; and Model 747-200B series airplanes having a 
stretched upper deck. The NPRM published in the Federal Register on 
July 24, 2015 (80 FR 43974) (``the NPRM''). The NPRM was prompted by an 
evaluation that indicated that the upper deck is subject to WFD. The 
NPRM proposed to continue to require inspections for cracking and 
discrepancies of certain fasteners; modification of the frame-to-
tension-tie joints; repetitive post-modification inspections; related 
investigative and corrective actions if necessary; and repetitive 
inspections for cracking in the tension tie channels, and repair if 
necessary. For certain airplanes, the NPRM also proposed to continue to 
require an inspection to determine if the angle is installed correctly, 
and re-installation if necessary; and an inspection at the fastener 
locations where the tension tie previously attached to the frame prior 
to certain modifications, and repair if necessary. The NPRM also 
proposed to add a new inspection for cracking in the tension tie 
channels and post-modification inspections of the modified tension ties 
for cracking, and repair if necessary. We are issuing this AD to 
prevent fatigue cracking of the tension ties, shear webs, and frames of 
the upper deck, which could result in rapid decompression and reduced 
structural integrity of the airplane.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the NPRM and 
the FAA's response to each comment.

Support for the NPRM

    United Airlines concurred with the contents of the NPRM.

Requests To Include Options To Perform Inspections in Revised Service 
Information

    Boeing and United Parcel Service (UPS) asked that we add a new 
paragraph to the proposed AD that includes an option to perform the 
inspections specified in Boeing Alert Service Bulletin 747-53A2507, 
Revision 2, dated May 9, 2014. Boeing stated that these inspections are 
equivalent to the inspections done in accordance with Boeing Alert 
Service Bulletin 747-53A2507, Revision 1, dated January 14, 2010. UPS 
recommended that Boeing Alert Service Bulletin 747-53A2507, Revision 2, 
dated May 9, 2014, be added to paragraphs (g) through (o) of the 
proposed AD. UPS noted that, for clarity, the proposed AD should refer 
to the revised service information rather than relying on paragraph 
(t)(4) of the proposed AD, which allows alternative methods of 
compliance (AMOCs) previously approved for AD 2012-15-13 to be approved 
as AMOCs for the proposed AD.
    We acknowledge the commenters' requests and note that we normally 
add reference to later revisions of service information in the restated 
paragraphs of supersedure ADs. However, in most cases, the later 
revisions do not include new compliance times and the procedures are 
closely aligned with those in the previous service information. Boeing 
Alert Service Bulletin 747-53A2507, Revision 2, dated May 9, 2014, adds 
alternative compliance times for certain airplanes and refers to 
different procedures in the Accomplishment Instructions of Boeing Alert 
Service Bulletin 747-53A2507, Revision 2, dated May 9, 2014, for 
accomplishing the actions required by AD 2012-15-13. Therefore, we 
cannot simply add a reference to paragraphs (g) through (o) of this AD 
as requested by the commenter. We have determined that, in this case, 
adding additional paragraphs to this AD to specify the alternative 
method of compliance, including new compliance times and procedures, is 
not necessary since Boeing Alert Service Bulletin 747-53A2507, Revision 
2, dated May 9, 2014, was already approved as an AMOC to AD 2012-15-13. 
As stated by the commenter, paragraph (t)(4) of this AD already allows 
the use of previous AMOCs, such as Boeing Alert Service Bulletin 747-
53A2507, Revision 2, dated May 9, 2014, as AMOCs for the corresponding 
provisions of this AD. We have made no change to this AD in this 
regard.

Request To Include an Alternative Compliance Time for the Modification

    Boeing and UPS asked that we add a new paragraph to allow an 
alternative compliance time for airplanes on which the station (STA) 
1120, 1160, 1200, and 1220 tension ties were modified during a 
freighter conversion, as provided in table 4 of paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 747-53A2559, Revision 
2, dated May 13, 2014. Boeing stated that the compliance time for 
modification of those airplanes can be increased because the 
modification has been done during a freighter conversion. UPS noted 
that paragraph (p) of the proposed AD should be changed to require 
modification and all related inspections and corrective actions be 
accomplished in accordance with Boeing Alert Service Bulletin 747-
53A2559, Revision 2, dated May 13, 2014, at the applicable time 
specified in Boeing Service Bulletin 747-53A2559, Revision 1, dated 
August 4, 2011; or Boeing Alert Service Bulletin 747-53A2559, Revision 
2, dated May 13, 2014.
    We agree with the commenter to include the alternative compliance 
times for certain airplanes to accomplish the actions required by 
paragraph (p) of this AD. We have added a new paragraph (p)(3) to this 
AD for Group 3 through 5, Configuration 1 airplanes identified in 
Boeing Alert Service Bulletin 747-53A2559, Revision 2, dated May 13, 
2014, to specify that operators may accomplish the actions required by 
paragraph (p) of this AD within the applicable compliance times 
specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service 
Bulletin 747-53A2559, Revision 2, dated May 13, 2014.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the

[[Page 14695]]

public interest require adopting this AD with the changes described 
previously and minor editorial changes. We have determined that these 
minor changes:
     Are consistent with the intent that was proposed in the 
NPRM for correcting the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM.
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this AD.

Related Service Information Under 1 CFR Part 51

    We reviewed Boeing Alert Service Bulletin 747-53A2559, Revision 2, 
dated May 13, 2014. The service information describes procedures for 
modifying the tension tie and frame at certain center sections, 
including related investigative and corrective actions; post-
modification inspections for cracking of the tension tie and frame 
structure and corrective actions; an additional modification; an 
inspection of all areas of the modified tension ties for cracking; an 
inspection of the tension tie center section for cracking in certain 
tension tie channels; and repair.
    This service information is reasonably available because the 
interested parties have access to it through their normal course of 
business or by the means identified in the ADDRESSES section.

Costs of Compliance

    We estimate that this AD affects 120 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
----------------------------------------------------------------------------------------------------------------
Retained modification in AD 2012- Between 257 and     Between $341,334    Between $363,179    Between
 15-13 (67 airplanes).             263 work-hours x    and $345,490.       and $367,845.       $24,332,993 and
                                   $85 per hour =                                              $24,645,615.
                                   between $21,845
                                   and $22,355.
Retained post[dash]modification   6 work[dash]hours   $0................  $510 per            $34,170 per
 inspections in AD 2012-15-13      x $85 per hour =                        inspection cycle.   inspection cycle.
 (67 airplanes).                   $510 per
                                   inspection cycle.
New inspection..................  10 work[dash]hours  $0................  $850..............  $102,000.
                                   x $85 per hour =
                                   $850.
New post[dash]modification eddy   216 work-hours x    $0................  $18,360 per         $2,203,200 per
 current inspections.              $85 per hour =                          inspection cycle.   inspection cycle.
                                   $18,360 per
                                   inspection cycle.
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    We have received no definitive data that will enable us to provide 
a cost estimate for the on-condition 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

    We have determined that 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 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) 
2012-15-13, Amendment 39-17142 (77 FR 47267, August 8, 2012), and 
adding the following new AD:

2016-05-12 The Boeing Company: Amendment 39-18430; Docket No. FAA-
2015-2961; Directorate Identifier 2014-NM-145-AD.

(a) Effective Date

    This AD is effective April 22, 2016.

(b) Affected ADs

    This AD replaces AD 2012-15-13, Amendment 39-17142 (77 FR 47267, 
August 8, 2012) (``AD 2012-15-13'').

(c) Applicability

    This AD applies to The Boeing Company Model 747-100B SUD, 747-
300, 747-400, and 747-400D series airplanes; and Model 747-200B 
series airplanes having a stretched upper deck; certificated in any 
category; excluding airplanes that have been converted to a large 
cargo freighter configuration.

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by reports of cracked and severed tension 
ties, broken fasteners, and cracks in the frame, shear web, and 
shear ties adjacent to tension ties for the upper deck. This AD was 
also prompted by an evaluation by the design approval holder,

[[Page 14696]]

which indicated that the upper deck is subject to widespread fatigue 
damage. We are issuing this AD to prevent fatigue cracking of the 
tension ties, shear webs, and frames of the upper deck, which could 
result in rapid decompression and reduced structural integrity of 
the airplane.

(f) Compliance

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

(g) Retained Repetitive Stage 1 Inspections, With No Changes

    This paragraph restates the requirements of paragraph (g) of AD 
2012-15-13, with no changes. For all airplanes: Do detailed 
inspections for cracking or discrepancies of the fasteners in the 
tension ties, shear webs, and frames at body stations (STA) 1120 
through 1220, and related investigative and corrective actions as 
applicable, by doing all actions specified in and in accordance with 
``Stage 1 Inspection'' of the Accomplishment Instructions of Boeing 
Alert Service Bulletin 747-53A2507, dated April 21, 2005, except as 
provided by paragraph (k) of this AD; or Boeing Alert Service 
Bulletin 747-53A2507, Revision 1, dated January 14, 2010. As of 
September 12, 2012 (the effective date of AD 2012-15-13), only 
Boeing Alert Service Bulletin 747-53A2507, Revision 1, dated January 
14, 2010, may be used to do the actions required by this paragraph. 
Do the Stage 1 inspections at the applicable times specified in 
paragraphs (h) and (i) of this AD, except as provided by paragraphs 
(g)(1) and (g)(2) of this AD. Accomplishment of the initial Stage 2 
inspection required by paragraph (j) of this AD terminates the 
requirements of this paragraph. Any applicable related investigative 
and corrective actions must be done before further flight. Doing the 
modification required by paragraph (p) of this AD terminates the 
repetitive inspection requirements of this paragraph.
    (1) Where paragraph 1.E., ``Compliance,'' of Boeing Alert 
Service Bulletin 747-53A2507, dated April 21, 2005, specifies a 
compliance time relative to ``the original issue date on this 
service bulletin,'' this AD requires compliance before the specified 
compliance time after April 26, 2006 (the effective date of AD 2006-
06-11, Amendment 39-14520 (71 FR 14367, March 22, 2006)).
    (2) For any airplane that reaches the applicable compliance time 
for the initial Stage 2 inspection (as specified in Table 1, 
Compliance Recommendations, under paragraph 1.E., of Boeing Alert 
Service Bulletin 747-53A2507, dated April 21, 2005) before reaching 
the applicable compliance time for the initial Stage 1 inspection: 
Accomplishment of the initial Stage 2 inspection terminates the 
Stage 1 inspections.

(h) Retained Compliance Time for Initial Stage 1 Inspection, With No 
Changes

    This paragraph restates the requirements of paragraph (h) of AD 
2012-15-13, with no changes. Do the initial Stage 1 inspection at 
the earlier of the times specified in paragraphs (h)(1) and (h)(2) 
of this AD.
    (1) Inspect at the earlier of the times specified in paragraphs 
(h)(1)(i) and (h)(1)(ii) of this AD.
    (i) At the applicable time specified in paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 747-53A2507, dated 
April 21, 2005.
    (ii) Before the accumulation of 10,000 total flight cycles, or 
within 250 flight cycles after November 28, 2007 (the effective date 
of AD 2007-23-18, Amendment 39-15266 (72 FR 65655, November 23, 
2007)), whichever occurs later.
    (2) Inspect at the later of the times specified in paragraphs 
(h)(2)(i) and (h)(2)(ii) of this AD.
    (i) Before the accumulation of 12,000 total flight cycles.
    (ii) Within 50 flight cycles or 20 days, whichever occurs first, 
after November 28, 2007 (the effective date of AD 2007-23-18, 
Amendment 39-15266 (72 FR 65655, November 23, 2007)).

(i) Retained Compliance Times for Repetitive Stage 1 Inspections, With 
No Changes

    This paragraph restates the requirements of paragraph (i) of AD 
2012-15-13, with no changes. Repeat the Stage 1 inspection specified 
in paragraph (g) of this AD at the time specified in paragraph 
(i)(1) or (i)(2) of this AD, as applicable. Repeat the inspection 
thereafter at intervals not to exceed 250 flight cycles, until the 
initial Stage 2 inspection required by paragraph (j) of this AD has 
been done.
    (1) For airplanes on which the initial Stage 1 inspection has 
not been accomplished as of November 28, 2007 (the effective date of 
AD 2007-23-18, Amendment 39-15266 (72 FR 65655, November 23, 2007)): 
Do the next inspection before the accumulation of 10,000 total 
flight cycles, or within 250 flight cycles after the initial Stage 1 
inspection done in accordance with paragraph (g) of this AD, 
whichever occurs later.
    (2) For airplanes on which the initial Stage 1 inspection has 
been accomplished as of November 28, 2007 (the effective date of AD 
2007-23-18, Amendment 39-15266 (72 FR 65655, November 23, 2007)): Do 
the next inspection at the applicable time specified in paragraph 
(i)(2)(i) or (i)(2)(ii) of this AD.
    (i) For airplanes that have accumulated fewer than 12,000 total 
flight cycles as of November 28, 2007 (the effective date of AD 
2007-23-18, Amendment 39-15266 (72 FR 65655, November 23, 2007)): Do 
the next inspection before the accumulation of 10,000 total flight 
cycles, or within 250 flight cycles after November 28, 2007, 
whichever occurs later.
    (ii) For airplanes that have accumulated 12,000 total flight 
cycles or more as of November 28, 2007 (the effective date of AD 
2007-23-18, Amendment 39-15266 (72 FR 65655, November 23, 2007)): Do 
the next inspection at the later of the times specified in 
paragraphs (i)(2)(ii)(A) and (i)(2)(ii)(B) of this AD.
    (A) Within 250 flight cycles after accomplishment of the initial 
Stage 1 inspection.
    (B) Within 50 flight cycles or 20 days, whichever occurs first, 
after November 28, 2007 (the effective date of AD 2007-23-18, 
Amendment 39-15266 (72 FR 65655, November 23, 2007)).

(j) Retained Repetitive Stage 2 Inspections, With No Changes

    This paragraph restates the requirements of paragraph (j) of AD 
2012-15-13, with no changes. For all airplanes: Do detailed and high 
frequency eddy current inspections for cracking or discrepancies of 
the fasteners in the tension ties, shear webs, and frames at STAs 
1120 through 1220, and related investigative and corrective actions 
as applicable, by doing all actions specified in and in accordance 
with ``Stage 2 Inspection'' of the Accomplishment Instructions of 
Boeing Alert Service Bulletin 747-53A2507, dated April 21, 2005; or 
Boeing Alert Service Bulletin 747-53A2507, Revision 1, dated January 
14, 2010; except as provided by paragraph (k) of this AD. Do the 
initial inspections at the earlier of the times specified in 
paragraphs (j)(1) and (j)(2) of this AD. Repeat the Stage 2 
inspection thereafter at the applicable times specified in paragraph 
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2507, 
dated April 21, 2005; or Boeing Alert Service Bulletin 747-53A2507, 
Revision 1, dated January 14, 2010. As of September 12, 2012 (the 
effective date of AD 2012-15-13), only Boeing Alert Service Bulletin 
747-53A2507, Revision 1, dated January 14, 2010, may be used. Any 
applicable related investigative and corrective actions must be done 
before further flight. Accomplishment of the initial Stage 2 
inspection ends the repetitive Stage 1 inspections. Doing the 
modification required by paragraph (p) of this AD terminates the 
repetitive inspection requirements of this paragraph.
    (1) Before the accumulation of 16,000 total flight cycles, or 
within 1,000 flight cycles after November 28, 2007 (the effective 
date of AD 2007-23-18, Amendment 39-15266 (72 FR 65655, November 23, 
2007)), whichever occurs later.
    (2) Before the accumulation of 10,000 total flight cycles, or 
within 1,000 flight cycles after September 12, 2012 (the effective 
date of AD 2012-15-13, Amendment 39-17142 (77 FR 47267, August 8, 
2012)), whichever occurs later.

(k) Retained Exception to Corrective Action Instructions, With No 
Changes

    This paragraph restates the requirements of paragraph (k) of AD 
2012-15-13, with no changes. If any discrepancy, including but not 
limited to any crack, broken fastener, loose fastener, or missing 
fastener is found during any inspection required by paragraph (g), 
(h), (i), or (j) of this AD, and Boeing Alert Service Bulletin 747-
53A2507, dated April 21, 2005; or Boeing Alert Service Bulletin 747-
53A2507, Revision 1, dated January 14, 2010; specifies to contact 
Boeing for appropriate action: Before further flight, repair the 
discrepancy using a method approved in accordance with the 
procedures specified in paragraph (t) of this AD.

(l) Retained Stage 2 Inspection: Work at STA 1140, With No Changes

    This paragraph restates the requirements of paragraph (l) of AD 
2012-15-13, with no changes. For all airplanes: Except as

[[Page 14697]]

provided by paragraph (o) of this AD, at the time specified in 
paragraph 1.E, ``Compliance,'' of Boeing Alert Service Bulletin 747-
53A2507, Revision 1, dated January 14, 2010, do an open hole high 
frequency eddy current (HFEC) inspection for cracking in the forward 
and aft tension tie channels at 12 fastener locations inboard of the 
aluminum straps at STA 1140, and before further flight do all 
applicable repairs. Do all actions in accordance with the 
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2507, Revision 1, dated January 14, 2010. Repeat the inspections 
thereafter at the time specified in paragraph 1.E., ``Compliance,'' 
of Boeing Alert Service Bulletin 747-53A2507, Revision 1, dated 
January 14, 2010. Doing the modification required by paragraph (p) 
of this AD terminates the inspection requirements in this paragraph.

(m) Retained One-Time Inspection for Incorrectly Installed Angles, With 
No Changes

    This paragraph restates the requirements of paragraph (m) of AD 
2012-15-13, with no changes. For Group 1, Configuration 1, airplanes 
as identified in Boeing Alert Service Bulletin 747-53A2507, Revision 
1, dated January 14, 2010: Except as provided by paragraph (o) of 
this AD, at the time specified in paragraph 1.E, ``Compliance,'' of 
Boeing Alert Service Bulletin 747-53A2507, Revision 1, dated January 
14, 2010, do a detailed inspection to determine if the angle is 
installed correctly, and before further flight re-install all angles 
that were installed incorrectly. Do all actions in accordance with 
the Accomplishment Instructions of Boeing Alert Service Bulletin 
747-53A2507, Revision 1, dated January 14, 2010.

(n) Retained One-Time Inspection for Cracks in Frames at Previous 
Tension Tie Locations, With No Changes

    This paragraph restates the requirements of paragraph (n) of AD 
2012-15-13, with no changes. For Group 1, Configuration 2, 
airplanes; and Groups 2 and 3 airplanes; as identified in Boeing 
Alert Service Bulletin 747-53A2507, Revision 1, dated January 14, 
2010: Except as provided by paragraph (o) of this AD, at the time 
specified in paragraph 1.E, ``Compliance,'' of Boeing Alert Service 
Bulletin 747-53A2507, Revision 1, dated January 14, 2010, do an open 
hole HFEC inspection for cracks at the fastener locations (STAs 
1120, 1160, 1200, and 1220) where the tension tie previously 
attached to the frame prior to modification to the Boeing Special 
Freighter or Boeing Converted Freighter configuration, and before 
further flight do all applicable repairs. Do all actions in 
accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin 747-53A2507, Revision 1, dated January 14, 2010. 
Doing the modification required by paragraph (p) of this AD 
terminates the one-time inspection requirements in this paragraph.

(o) Retained Exception to Boeing Alert Service Bulletin 747-53A2507, 
Revision 1, Dated January 14, 2010, With No Changes

    This paragraph restates the requirements of paragraph (o) of AD 
2012-15-13, with no changes. Where paragraph 1.E., ``Compliance,'' 
of Boeing Alert Service Bulletin 747-53A2507, Revision 1, dated 
January 14, 2010, specifies a compliance time relative to ``the 
Revision 1 date of this service bulletin,'' this AD requires 
compliance within the specified compliance time after September 12, 
2012 (the effective date of AD 2012-15-13).

(p) Retained Modification and Post-Modification Repetitive Inspections, 
With Revised Service Information and a New Exception

    This paragraph restates the requirements of paragraph (p) of AD 
2012-15-13, with revised service information and a new exception. 
Except as provided by paragraphs (p)(1), (p)(2), and (p)(3) of this 
AD: At the applicable times specified in paragraph 1.E, 
``Compliance,'' of Boeing Service Bulletin 747-53A2559, Revision 1, 
dated August 4, 2011, modify the frame-to-tension-tie joints at STAs 
1120 through 1220; do all related investigative and applicable 
corrective actions; do the repetitive post-modification detailed 
inspections for cracking of the tension tie and frame structure and 
all applicable corrective actions; and do the additional 
modification. Do all actions in accordance with the Accomplishment 
Instructions of Boeing Service Bulletin 747-53A2559, Revision 1, 
dated August 4, 2011; or Boeing Alert Service Bulletin 747-53A2559, 
Revision 2, dated May 13, 2014. Modifying the frame-to-tension-tie 
joints at STAs 1120 through 1220 terminates the repetitive 
inspection requirements of paragraphs (g) and (j) of this AD, the 
inspection requirements of paragraph (l) of this AD, and the one-
time inspection requirement of paragraph (n) of this AD. As of the 
effective date of this AD, only Boeing Alert Service Bulletin 747-
53A2559, Revision 2, dated May 13, 2014, may be used to accomplish 
the actions specified in this paragraph.
    (1) Where paragraph 1.E., ``Compliance,'' of Boeing Service 
Bulletin 747-53A2559, Revision 1, dated August 4, 2011, specifies a 
compliance time relative to ``the original issue date of this 
service bulletin,'' this AD requires compliance within the specified 
compliance time after September 12, 2012 (the effective date of AD 
2012-15-13).
    (2) Where Boeing Service Bulletin 747-53A2559, Revision 1, dated 
August 4, 2011; or Boeing Alert Service Bulletin 747-53A2559, 
Revision 2, dated May 13, 2014; specifies to contact Boeing for 
repair instructions or additional modification requirements: Before 
further flight, repair the cracking or do the additional actions 
using a method approved in accordance with the procedures specified 
in paragraph (t) of this AD.
    (3) For Group 3 through 5, Configuration 1 airplanes identified 
in Boeing Alert Service Bulletin 747-53A2559, Revision 2, dated May 
13, 2014: Operators may accomplish the actions required by paragraph 
(p) of this AD within the applicable compliance times specified in 
paragraph 1.E., ``Compliance'' of Boeing Alert Service Bulletin 747-
53A2559, Revision 2, dated May 13, 2014.

(q) Retained Credit for Previous Actions, With No Changes

    This paragraph restates the credit provided by paragraph (q) of 
AD 2012-15-13, with no changes. This paragraph provides credit for 
the corresponding actions required by paragraph (p) of this AD, if 
those actions were done before September 12, 2012 (the effective 
date of AD 2012-15-13), using Boeing Alert Service Bulletin 747-
53A2559, dated January 8, 2009, which is not incorporated by 
reference in this AD.

(r) New Repetitive Post-Modification Eddy Current Inspections

    Do an eddy current inspection of all areas of the modified 
tension ties for cracking, in accordance with Part 3 of the 
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2559, Revision 2, dated May 13, 2014. Do the inspection at the 
time specified in Table 2 of paragraph 1.E, ``Compliance,'' of 
Boeing Alert Service Bulletin 747-53A2559, Revision 2, dated May 13, 
2014, except where paragraph 1.E., ``Compliance,'' of Boeing Alert 
Service Bulletin 747-53A2559, Revision 2, dated May 13, 2014, 
specifies a compliance time relative to ``the Revision 2 date of 
this service bulletin,'' this AD requires compliance within the 
specified compliance time after the effective date of this AD. If 
any crack is found, before further flight, repair the crack using a 
method approved in accordance with the procedures specified in 
paragraph (t) of this AD. If no crack is found, repeat the 
inspection thereafter at the intervals specified in paragraph 1.E, 
``Compliance,'' of Boeing Alert Service Bulletin 747-53A2559, 
Revision 2, dated May 13, 2014.

(s) New One-Time Surface HFEC Inspections

    Do a surface HFEC inspection of the tension tie center section, 
for cracking in the forward and aft tension tie channels between 
STAs 1120 through 1220, in accordance with Part 4 of the 
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2559, Revision 2, dated May 13, 2014. Do the inspection at the 
applicable time specified in Table 1 or Table 3 of paragraph 1.E, 
``Compliance,'' of Boeing Alert Service Bulletin 747-53A2559, 
Revision 2, dated May 13, 2014, except where paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 747-53A2559, 
Revision 2, dated May 13, 2014, specifies a compliance time relative 
to ``the Revision 2 date of this service bulletin,'' this AD 
requires compliance within the specified compliance time after the 
effective date of this AD. If any crack is found, before further 
flight, repair the crack using a method approved in accordance with 
the procedures specified in paragraph (t) of this AD.

(t) 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

[[Page 14698]]

to the manager of the ACO, send it to the attention of the person 
identified in paragraph (u)(1) of this AD. Information may be 
emailed to: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
    (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, alteration, or modification 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 method, modification deviation, or 
alteration deviation must meet the certification basis of the 
airplane, and the approval must specifically refer to this AD.
    (4) AMOCs approved previously for AD 2012-15-13, are approved as 
AMOCs for the corresponding provisions of this AD.

(u) Related Information

    (1) For more information about this AD, contact Bill Ashforth, 
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft 
Certification Office, 1601 Lind Avenue SW., Renton, WA 98057-3356; 
phone: 425-917-6432; fax: 425-917-6590; email: 
bill.ashforth@faa.gov.
    (2) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (v)(6) and (v)(7) of this AD.

(v) 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 
April 22, 2016.
    (i) Boeing Alert Service Bulletin 747-53A2559, Revision 2, dated 
May 13, 2014.
    (ii) Reserved.
    (4) The following service information was approved for IBR on 
September 12, 2012 (77 FR 47267, August 8, 2012).
    (i) Boeing Alert Service Bulletin 747-53A2507, Revision 1, dated 
January 14, 2010.
    (ii) Boeing Service Bulletin 747-53A2559, Revision 1, dated 
August 4, 2011.
    (5) The following service information was approved for IBR on 
November 28, 2007 (72 FR 65655, November 23, 2007).
    (i) Boeing Alert Service Bulletin 747-53A2507, dated April 21, 
2005.
    (ii) Reserved.
    (6) 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.
    (7) You may view this 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.
    (8) 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 February 29, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-05249 Filed 3-17-16; 8:45 am]
BILLING CODE 4910-13-P