
[Federal Register Volume 80, Number 86 (Tuesday, May 5, 2015)]
[Proposed Rules]
[Pages 25630-25633]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-10316]



[[Page 25630]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-1266; Directorate Identifier 2014-NM-151-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, 747-300, 747SR, and 747SP series airplanes. This proposed AD was 
prompted by an evaluation by the design approval holder (DAH) 
indicating that certain fuselage skin lap joints are subject to 
widespread fatigue damage (WFD). This proposed AD would require 
repetitive post-modification inspections for cracking of the skin or 
internal doubler along the edge fastener rows of the modification, and 
repair if necessary. We are proposing this AD to detect and correct 
fatigue cracking in certain fuselage skin lap joints, which could 
result in rapid depressurization of the airplane.

DATES: We must receive comments on this proposed AD by June 19, 2015.

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 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 http://www.regulations.gov by 
searching for and locating Docket No. FAA 2015-1266.

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-2015-
1266; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this proposed AD, the regulatory evaluation, any comments 
received, and other information. The street address for the Docket 
Office (phone: 800-647-5527) is in the ADDRESSES section. Comments will 
be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Nathan Weigand, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue SW., Renton, Washington 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-2015-1266; 
Directorate Identifier 2014-NM-151-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD because of those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    Structural fatigue damage is progressive. It begins as minute 
cracks, and those cracks grow under the action of repeated stresses. 
This can happen because of normal operational conditions and design 
attributes, or because of isolated situations or incidents such as 
material defects, poor fabrication quality, or corrosion pits, dings, 
or scratches. Fatigue damage can occur locally, in small areas or 
structural design details, or globally. Global fatigue damage is 
general degradation of large areas of structure with similar structural 
details and stress levels. Multiple-site damage is global damage that 
occurs in a large structural element such as a single rivet line of a 
lap splice joining two large skin panels. Global damage can also occur 
in multiple elements such as adjacent frames or stringers. Multiple-
site-damage and multiple-element-damage cracks are typically too small 
initially to be reliably detected with normal inspection methods. 
Without intervention, these cracks will grow, and eventually compromise 
the structural integrity of the airplane, in a condition known as WFD. 
As an airplane ages, WFD will likely occur, and will certainly occur if 
the airplane is operated long enough without any intervention.
    The FAA's WFD final rule (75 FR 69746, November 15, 2010) became 
effective on January 14, 2011. The WFD rule requires certain actions to 
prevent structural failure due to WFD throughout the operational life 
of certain existing transport category airplanes and all of these 
airplanes that will be certificated in the future. For existing and 
future airplanes subject to the WFD rule, the rule requires that DAHs 
establish a limit of validity (LOV) of the engineering data that 
support the structural maintenance program. Operators affected by the 
WFD rule may not fly an airplane beyond its LOV, unless an extended LOV 
is approved.
    The WFD rule (75 FR 69746, November 15, 2010) does not require 
identifying and developing maintenance actions if the DAHs can show 
that such actions are not necessary to prevent WFD before the airplane 
reaches the LOV. Many LOVs, however, do depend on accomplishment of 
future maintenance actions. As stated in the WFD rule, any maintenance 
actions necessary to reach the LOV will be mandated by airworthiness 
directives through separate rulemaking actions.
    In the context of WFD, this action is necessary to enable DAHs to 
propose LOVs that allow operators the longest operational lives for 
their airplanes, and still ensure that WFD will not occur. This 
approach allows for an implementation strategy that provides 
flexibility to DAHs in determining the timing of service information 
development (with FAA approval), while providing operators with 
certainty regarding the LOV applicable to their airplanes.
    This proposed AD was prompted by an evaluation by the DAH 
indicating

[[Page 25631]]

that certain fuselage skin lap joints are subject to WFD. We are 
proposing this AD to detect and correct fatigue cracking in certain 
fuselage skin lap joints, which could result in rapid depressurization 
of the airplane.

Related Service Information Under 1 CFR Part 51

    We reviewed Boeing Alert Service Bulletin 747-53A2367, Revision 5, 
dated July 8, 2014. This service information describes procedures for 
inspections for cracks in the skin and doublers along the edge fastener 
rows of modifications in the fuselage, and repairs. Refer to this 
service information for information on the procedures and compliance 
times. This service information is reasonably available at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
1266. Or see ADDRESSES for other ways to access this service 
information.

Related Rulemaking

    AD 2010-10-05, Amendment 39-16284 (75 FR 27424, May 17, 2010) 
requires, among other things, modification of certain lap joints in 
fuselage sections 41 and 42. This proposed AD would require repetitive 
post-modification inspections for cracking of the skin or internal 
doubler along the edge fastener rows of the modification, and repair if 
necessary.

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 these same type 
designs.

Proposed AD Requirements

    This proposed AD would require accomplishing the actions specified 
in the service information described previously, except as discussed 
under ``Difference Between this Proposed AD and the Service 
Information.''

Difference Between This Proposed AD and the Service Information

    Boeing Alert Service Bulletin 747-53A2367, Revision 5, dated July 
8, 2014, specifies to contact the manufacturer for instructions on how 
to repair cracking, 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 50 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

                                                                     Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
               Action                        Labor cost         Parts cost       Cost per product                   Cost on U.S. operators
--------------------------------------------------------------------------------------------------------------------------------------------------------
Post[dash]modification inspection...  124 work-hours x $85              $0   $10,540 per inspection   $527,000 per inspection cycle.
                                       per hour = $10,540 per                 cycle.
                                       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.
    According to the manufacturer, some of the costs of this proposed 
AD may be covered under warranty, thereby reducing the cost impact on 
affected individuals. We do not control warranty coverage for affected 
individuals. As a result, we have included all costs in our cost 
estimate.

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13  [Amended]

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

The Boeing Company: Docket No. FAA-2014-1266; Directorate Identifier 
2014-NM-151-AD.

(a) Comments Due Date

    We must receive comments by June 19, 2015.

(b) Affected ADs

    None.

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(c) Applicability

    This AD applies to The Boeing Company Model 747-100, 747-100B, 
747-100B SUD, 747-200B, 747-300, 747SR, and 747SP series airplanes, 
certificated in any category, as identified in Boeing Alert Service 
Bulletin 747-53A2367, Revision 5, dated July 8, 2014.

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by an evaluation by the design approval 
holder (DAH) indicating that certain fuselage skin lap joints are 
subject to widespread fatigue damage (WFD). We are issuing this AD 
to detect and correct fatigue cracking in certain fuselage skin lap 
joints, which could result in rapid depressurization of the 
airplane.

(f) Compliance

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

(g) Repetitive Post-Modification Inspections for Airplane Groups 1 
Through 3, 7, and 8

    For airplanes identified as Groups 1 through 3, 7, and 8 in 
Boeing Alert Service Bulletin 747-53A2367, Revision 5, dated July 8, 
2014: Except as provided by paragraph (m) of this AD, at the 
applicable time specified in table 3 of paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 747-53A2367, 
Revision 5, dated July 8, 2014, do internal detailed and surface 
high frequency eddy current (HFEC) inspections for cracks in the 
skin and internal doubler along the edge fastener rows of the 
modification; in accordance with the Accomplishment Instructions of 
Boeing Alert Service Bulletin 747-53A2367, Revision 5, dated July 8, 
2014. In unrepaired areas, repeat the internal detailed and surface 
HFEC inspections for cracks in the skin or internal doubler along 
the edge fastener rows of the modification thereafter at the 
applicable intervals specified in paragraph 1.E., ``Compliance,'' of 
Boeing Alert Service Bulletin 747-53A2367, Revision 5, dated July 8, 
2014.

(h) Initial Post-Modification Inspections for Airplane Groups 4 Through 
6, and 9 Through 11

    For airplanes identified as Groups 4 through 6, and 9 through 11 
in Boeing Alert Service Bulletin 747-53A2367, Revision 5, dated July 
8, 2014, with external doublers installed as specified in Boeing 
Service Bulletin 747-53-2272: Except as provided by paragraph (m) of 
this AD, at the applicable time specified in table 4 of paragraph 
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2367, 
Revision 5, dated July 8, 2014, do external detailed, low frequency 
eddy current (LFEC), and HFEC inspections for cracks in the skin and 
external doubler, in accordance with the Accomplishment Instructions 
of Boeing Alert Service Bulletin 747-53A2367, Revision 5, dated July 
8, 2014.

(i) Repetitive Post-Modification Inspections for Airplane Groups 4 
Through 6, and 9 through 11

    For airplanes with no crack findings during the inspections 
required by paragraph (h) of this AD: Do the applicable actions 
required by paragraphs (i)(1) and (i)(2) of this AD.
    (1) For airplanes with less than 15,000 flight cycles since 
stringer 6 external doublers were installed as specified in Boeing 
Service Bulletin 747-53-2272: At the applicable intervals specified 
in table 4 of paragraph 1.E., ``Compliance,'' of Boeing Alert 
Service Bulletin 747-53A2367, Revision 5, dated July 8, 2014, in 
unrepaired areas, repeat the external detailed and LFEC inspections 
for cracks in the skin, and the external detailed and HFEC 
inspections for cracks in the external doubler, in accordance with 
the Accomplishment Instructions of Boeing Alert Service Bulletin 
747-53A2367, Revision 5, dated July 8, 2014.
    (2) For airplanes with 15,000 or more flight cycles since the 
stringer 6 external doublers were installed as specified in Boeing 
Service Bulletin 747-53-2272: At the applicable intervals specified 
in table 4 of paragraph 1.E., ``Compliance,'' of Boeing Alert 
Service Bulletin 747-53A2367, Revision 5, dated July 8, 2014, in 
unrepaired areas, do external detailed and LFEC inspections for 
cracks in the skin; and do internal and external detailed and HFEC 
inspections for cracks in the skin and external doubler; in 
accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin 747-53A2367, Revision 5, dated July 8, 2014.

(j) Repetitive Post-Modification Inspections for Airplane Groups 4 
Through 6, and 9 Through 11 With External Doublers

    For airplanes identified as Groups 4 through 6, and 9 through 11 
in Boeing Alert Service Bulletin 747-53A2367, Revision 5, dated July 
8, 2014, with external doublers installed as specified in Boeing 
Alert Service Bulletin 747-53A2367: Except as provided by paragraph 
(m) of this AD, at the applicable time specified in table 5 of 
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 
747-53A2367, Revision 5, dated July 8, 2014, do internal detailed 
and surface HFEC inspections for cracks in the skin and internal 
doubler along the edge fastener rows of the modification; and do 
internal detailed and surface HFEC inspections for cracks in the 
skin or internal doubler along the edge fastener rows of the 
modification; in accordance with the Accomplishment Instructions of 
Boeing Alert Service Bulletin 747-53A2367, Revision 5, dated July 8, 
2014. In unrepaired areas, repeat the internal detailed and surface 
HFEC inspections for cracks in the skin or internal doubler along 
the edge fastener rows of the modification thereafter at the 
applicable interval specified in paragraph 1.E., ``Compliance,'' of 
Boeing Alert Service Bulletin 747-53A2367, Revision 5, dated July 8, 
2014.

(k) Repetitive Post-Modification Inspections for Airplane Groups 12 and 
13

    For airplanes identified as Groups 12 and 13 in Boeing Alert 
Service Bulletin 747-53A2367, Revision 5, dated July 8, 2014: Except 
as provided by paragraph (m) of this AD, at the applicable time 
specified in table 6 of paragraph 1.E., ``Compliance,'' of Boeing 
Alert Service Bulletin 747-53A2367, Revision 5, dated July 8, 2014, 
do internal detailed and surface HFEC inspections for cracks in the 
skin and internal doubler along the edge fastener rows of the 
modification, in accordance with the Accomplishment Instructions of 
Boeing Alert Service Bulletin 747-53A2367, Revision 5, dated July 8, 
2014. In unrepaired areas, repeat the internal detailed and surface 
HFEC inspections for cracks in the skin or internal doubler along 
the edge fastener rows of the modification thereafter at the 
applicable interval specified in paragraph 1.E., ``Compliance,'' of 
Boeing Alert Service Bulletin 747-53A2367, Revision 5, dated July 8, 
2014.

(l) Corrective Actions

    If any cracking is found during any inspection required by this 
AD: Before further flight, repair the cracking using a method 
approved in accordance with the procedures specified in paragraph 
(n) of this AD.

(m) Exception to Boeing Alert Service Bulletin 747-53A2367, Revision 5, 
Dated July 8, 2014

    Where paragraph 1.E., ``Compliance,'' of Boeing Alert Service 
Bulletin 747-53A2367, Revision 5, dated July 8, 2014, specifies a 
compliance time ``after the Revision 5 date of this service 
bulletin,'' this AD requires compliance within the specified 
compliance time ``after the effective date of this AD.''

(n) 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 (o)(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 required by this AD if it is approved 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.

(o) Related Information

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

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

    Issued in Renton, Washington, on April 28, 2015.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-10316 Filed 5-4-15; 8:45 am]
 BILLING CODE 4910-13-P


