
[Federal Register Volume 78, Number 95 (Thursday, May 16, 2013)]
[Proposed Rules]
[Pages 28767-28770]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-11687]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0420; Directorate Identifier 2011-NM-241-AD]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
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. This proposed AD was prompted by a report 
of a disbonded doubler and a skin crack in section 41 of the fuselage, 
and multiple reports of cracked or missing fastener heads. This 
proposed AD would require repetitive inspections for cracking of the 
fuselage skin, discrepant fasteners, and for disbonds at the doublers; 
and related investigative and corrective actions if necessary. For 
certain airplanes, this proposed AD would also require a terminating 
repair for repair doublers. We are proposing this AD to prevent rapid 
decompression and loss of structural integrity of the airplane due to 
such disbonding and subsequent cracking of the skin panels.

DATES: We must receive comments on this proposed AD by July 1, 2013.

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: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-
5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. You may review copies of the 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 
(ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-
6428; fax: 425-917-6590; email: Nathan.P.Weigand@faa.gov.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2013-0420; 
Directorate Identifier 2011-NM-241-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

[[Page 28768]]

personal information you provide. We will also post a report 
summarizing each substantive verbal contact we receive about this 
proposed AD.

Discussion

    We have received a report of a disbonded doubler and a 10-inch 
crack found at 21,800 total flight cycles in the skin in section 41 of 
the fuselage; and two reports of cracked or missing fastener heads 
found on four airplanes. Cracked and/or missing fastener heads were 
found at station (STA) 480 and STA 520 between stringers S-8 and S-10 
on airplanes with 10,529 and 10,531 total flight cycles. Also, missing 
fastener heads were found between STA 400 and 420 at stringer S-24AL on 
airplanes with 28,153 and 28,319 total flight cycles.
    Fatigue cracks can start in the body skin at fastener holes where 
internal doublers have disbonded from the skin panel. Fatigue cracks 
that are not found and repaired could extend with continued use of the 
airplane and could cause a rapid decompression and loss of structural 
integrity.

Relevant Service Information

    We reviewed Boeing Service Bulletin 747-53A2747, Revision 2, dated 
February 22, 2012. For information on the procedures and compliance 
times, see this service information at http://www.regulations.gov by 
searching for Docket No. FAA-2013-0420.

Terminating Action for Other ADs

     Accomplishing the requirements of this proposed AD 
terminates the requirements of paragraphs (f), (g), and (h) of AD 2006-
20-02, Amendment 39-14771 (71 FR 56861, September 28, 2006).
     Accomplishing the requirements of this proposed AD 
terminates the requirements of paragraphs (f), (k), and (l) of AD 2006-
24-02, Amendment 39-14831 (71 FR 67445, November 22, 2006).
     Accomplishing the requirements of this proposed AD 
terminates the requirements of paragraphs (f) and (i) of AD 2006-24-05, 
Amendment 39-14834 (71 FR 68434, November 27, 2006).

FAA's Determination

    We are proposing this AD because we evaluated all the relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of the same type design.

Proposed AD Requirements

    This proposed AD would require accomplishing the actions specified 
in the service information described previously, except as discussed 
under ``Differences Between the Proposed AD and the Service 
Information''.
    The phrase ``related investigative actions'' might be used in this 
proposed AD. ``Related investigative actions'' are follow-on actions 
that: (1) Are related to the primary actions, and (2) are actions that 
further investigate the nature of any condition found. Related 
investigative actions in an AD could include, for example, inspections.
    In addition, the phrase ``corrective actions'' might be used in 
this proposed AD. ``Corrective actions'' are actions that correct or 
address any condition found. Corrective actions in an AD could include, 
for example, repairs.

Differences Between the Proposed AD and the Service Information

    The service bulletin specifies to contact the manufacturer for 
instructions on how to repair certain conditions, but this proposed AD 
would require repairing those conditions in one of the following ways:
     In accordance with a method that we approve; or
     Using data that meet the certification basis of the 
airplane, and that have been approved by the Boeing Commercial 
Airplanes Organization Designation Authorization (ODA) whom we have 
authorized to make those findings.

Costs of Compliance

    We estimate that this proposed AD affects 98 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                Cost on U.S.
          Action                 Labor cost           Parts cost       Cost per product          operators
----------------------------------------------------------------------------------------------------------------
Inspections..............  878 work-hours x $85                $0   $74,630 per            $7,313,740 per
                            per hour = $74,630                       inspection cycle.      inspection cycle.
                            per inspection cycle.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this proposed 
AD.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII: Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701: ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

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

List of Subjects in 14 CFR Part 39

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

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator,

[[Page 28769]]

the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13  [Amended]

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

The Boeing Company: Docket No. FAA-2013-0420; Directorate Identifier 
2011-NM-241-AD.

(a) Comments Due Date

    We must receive comments by July 1, 2013.

(b) Affected ADs

    This AD affects AD 2006-20-02, Amendment 39-14771 (71 FR 56861, 
September 28, 2006); AD 2006-24-02, Amendment 39-14831 (71 FR 67445, 
November 22, 2006); and AD 2006-24-05, Amendment 39-14834 (71 FR 
68434, November 27, 2006).

 (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 Service Bulletin 747-53A2747, 
Revision 2, dated February 22, 2012.

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by a disbonded doubler and a skin crack in 
section 41 of the fuselage, and multiple reports of cracked or 
missing fastener heads. We are issuing this AD to prevent rapid 
decompression and loss of structural integrity of the airplane due 
to such disbonding and subsequent cracking of the skin panels.

(f) Compliance

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

(g) Repetitive Skin Panel, Fastener, and Doubler Inspection

    At the applicable time specified in paragraph 1.E., 
``Compliance,'' of Boeing Service Bulletin 747-53A2747, Revision 2, 
dated February 22, 2012, except as required by paragraphs (i)(1) and 
(i)(3) of this AD: Do the applicable inspections (including 
detailed, high frequency eddy current (HFEC), and low frequency eddy 
current (LFEC)) for any cracking of the fuselage skin, for 
discrepant fasteners, and for disbonds at the doublers; and do all 
applicable related investigative and corrective actions in 
accordance with the Accomplishment Instructions of Boeing Service 
Bulletin 747-53A2747, Revision 2, dated February 22, 2012, except as 
provided by paragraph (i)(2) of this AD. Repeat the applicable 
inspections thereafter at intervals not to exceed those specified in 
paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin 747-
53A2747, Revision 2, dated February 22, 2012. Do all applicable 
related investigative and corrective actions at the applicable time 
specified in paragraph 1.E., ``Compliance,'' of Boeing Service 
Bulletin 747-53A2747, Revision 2, dated February 22, 2012. Options 
provided in Boeing Service Bulletin 747-53A2747, Revision 2, dated 
February 22, 2011, for accomplishing the disbond inspection are 
acceptable for the corresponding requirements of this paragraph 
provided that the inspection is done at the applicable times in 
paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin 747-
53A2747, Revision 2, dated February 22, 2011.
    (1) Replacing a skin panel, in accordance with the 
Accomplishment Instructions of Boeing Service Bulletin 747-53A2747, 
Revision 2, dated February 22, 2012, is an acceptable alternative to 
doing the service repair manual (SRM) skin panel repairs and the 
repetitive skin panel inspections specified in tables 1, 2, and 3 of 
paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin 747-
53A2747, Revision 2, dated February 22, 2012, for only the skin 
panel that has been replaced.
    (2) Accomplishment of the terminating repair identified in 
tables 4 and 5 of paragraph 1.E., ``Compliance,'' of Boeing Service 
Bulletin 747-53A2747, Revision 2, dated February 22, 2012, 
terminates the repetitive inspections identified in tables 4 and 5 
of paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin 747-
53A2747, Revision 2, dated February 22, 2012, for only the area on 
which the terminating repair has been done.

(h) Terminating Action for Repairs

    For airplanes identified in tables 4 and 5 of paragraph 1.E., 
``Compliance,'' of Boeing Service Bulletin 747-53A2747, Revision 2, 
dated February 22, 2012: At the applicable compliance time specified 
in paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin 747-
53A2747, Revision 2, dated February 22, 2012, do the terminating 
action for the repair doubler, including doing an open hole HFEC 
inspection for skin cracks at the fastener holes common to the 
inspection area and an inspection for disbond of the internal 
doubler; and as applicable, replacing the existing external repair 
doubler with a new extended external repair doubler, in accordance 
with the Accomplishment Instructions of Boeing Service Bulletin 747-
53A2747, Revision 2, dated February 22, 2012, except as provided by 
paragraph (i)(2) of this AD. Accomplishment of the terminating 
action identified in tables 4 and 5 of paragraph 1.E., 
``Compliance,'' of Boeing Service Bulletin 747-53A2747, Revision 2, 
dated February 22, 2012, terminates the repetitive inspections 
identified in tables 4 and 5 of paragraph 1.E., ``Compliance,'' of 
Boeing Service Bulletin 747-53A2747, Revision 2, dated February 22, 
2012, for only areas on which the terminating action has been done.

(i) Exceptions to Certain Service Information Instructions

    This paragraph specifies exceptions to certain instructions in 
Boeing Service Bulletin 747-53A2747, Revision 2, dated February 22, 
2012.
    (1) Where Boeing Service Bulletin 747-53A2747, Revision 2, dated 
February 22, 2012, specifies a compliance time after the ``original 
issue date of this service bulletin,'' this AD requires compliance 
within the specified compliance time after the effective date of 
this AD.
    (2) Where Boeing Service Bulletin 747-53A2747, Revision 2, dated 
February 22, 2012, specifies to contact Boeing for special repair 
instructions, this AD requires using a method approved in accordance 
with the procedures specified in paragraph (l) of this AD.
    (3) The Condition column of paragraph 1.E., ``Compliance,'' of 
Boeing Service Bulletin 747-53A2747, Revision 2, dated February 22, 
2012, refers to certain conditions ``as of the original issue date 
of this service bulletin.'' This AD, however, applies to the 
airplanes with the specified condition as of the effective date of 
this AD.

(j) Credit for Previous Actions

    This paragraph provides credit for the actions required by 
paragraphs (g) and (h) of this AD, if those actions were performed 
before the effective date of this AD using Boeing Service Bulletin 
747-53A2747, Revision 1, dated October 12, 2011, which is not 
incorporated by reference in this AD.

(k) Terminating Action for Other ADs

    (1) Accomplishing the requirements of this AD terminates the 
requirements of paragraphs (f), (g), and (h) of AD 2006-20-02, 
Amendment 39-14771 (71 FR 56861, September 28, 2006).
    (2) Accomplishing the requirements of this AD terminates the 
requirements of paragraphs (f), (k), and (l) of AD 2006-24-02, 
Amendment 39-14831 (71 FR 67445, November 22, 2006).
    (3) Accomplishing the requirements of this AD terminates the 
requirements of paragraphs (f) and (i) of AD 2006-24-05, Amendment 
39-14834 (71 FR 68434, November 27, 2006).

(l) 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 the Related Information 
section 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

[[Page 28770]]

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.

(m) Related Information

    (1) For more information about this AD, contact Nathan Weigand, 
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft 
Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-
3356; phone: 425-917-6428; fax: 425-917-6590; email: 
Nathan.P.Weigand@faa.gov.
    (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 review copies of the 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, WA, on May 8, 2013.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2013-11687 Filed 5-15-13; 8:45 am]
BILLING CODE 4910-13-P


