[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: [email protected].
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
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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..
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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.
[[Page 25632]]
(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: [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 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:
[email protected].
[[Page 25633]]
(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]
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