[Federal Register Volume 78, Number 106 (Monday, June 3, 2013)]
[Proposed Rules]
[Pages 33012-33015]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2013-13002]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-0461; Directorate Identifier 2012-NM-169-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 supersede an existing airworthiness directive
(AD) that applies to certain The Boeing Company Model 747-100, 747-
100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400,
747SR, and 747SP series airplanes. The existing AD currently requires
repetitive inspections for skin cracks at the shear tie end fastener
locations of the fuselage frames, and repairing cracks if necessary.
Since we issued that AD, additional cracking has been found on an
airplane not affected by the existing AD. This proposed AD would also
require repetitively inspecting for skin cracks next to the shear tie
on airplanes with certain existing repair doublers, and corrective
actions if necessary. This proposed AD would also revise the
applicability to include additional airplanes. We are proposing this AD
to detect and correct fatigue cracks in the fuselage skin that can
propagate and grow, and result in reduced structural integrity and
sudden decompression of the airplane in flight.
DATES: We must receive comments on this proposed AD by July 18, 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 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,
Washington. 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: Roger Caldwell, Aerospace Engineer,
Technical Operations Center, ANM-100D, FAA, Denver Aircraft
Certification Office (ACO), 26805 East 68th Avenue, Room 214, Denver,
Colorado 80249-6361; phone: 303-342-1086; fax: 303-342-1088; email:
[email protected].
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2013-0461;
Directorate Identifier 2012-NM-169-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
On February 27, 2009, we issued AD 2009-06-02, Amendment 39-15838
(74 FR 11013, March 16, 2009), for certain The Boeing Company Model
747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300,
747-400, 747SR, and 747SP series airplanes.
[[Page 33013]]
That AD requires inspecting for skin cracks at the shear tie end
fastener locations of the fuselage frames, and repairing cracks if
necessary. That AD resulted from a widespread fatigue damage (WFD)
assessment of Model 747 airplanes. We issued that AD to detect and
correct cracks in the fuselage skin that can propagate and grow,
resulting in a loss of structural integrity and sudden decompression of
the airplane during flight.
WFD Program
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
widespread fatigue damage (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 design
approval holders (DAHs) and applicants 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 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.
Fuselage frame shear ties, located between longitudinal stringers,
are an integral part of the load-bearing airframe structure. Cracks in
the skin at fuselage frame shear tie end fastener locations, if not
corrected, could result in cracks in the fuselage skin, which can
propagate and become large, and result in loss of structural integrity
and sudden decompression of the airplane in flight.
Actions Since Existing AD (AD 2009-06-02, Amendment 39-15838 (74 FR
11013, March 16, 2009)) Was Issued
Since we issued AD 2009-06-02, Amendment 39-15838 (74 FR 11013,
March 16, 2009), we have received a report indicating that three skin
cracks were found on one airplane at fastener holes common to the
station (STA) 540 frame shear tie between stringer 23L and stringer
25L. The affected airplane had T-shaped shear ties in the area of the
inspection required by AD 2009-06-02, but was not included in the
applicability. Based on the reports of cracks in T-shaped shear ties,
we have determined that the unsafe condition may exist on additional
airplanes, including airplane line numbers 758 through 1419 inclusive
(except large cargo freighter airplanes).
It has also been determined that post-repair inspections of certain
existing repair doublers are necessary.
Relevant Service Information
We reviewed Boeing Alert Service Bulletin 747-53A2682, Revision 1,
dated May 24, 2012. For information on the procedures and compliance
times, see this service information at http://www.regulations.gov by
searching for Docket No. FAA-2013-0461.
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
Although this proposed AD does not explicitly restate the
requirements of AD 2009-06-02, Amendment 39-15838 (74 FR 11013, March
16, 2009), this proposed AD would retain all of the requirements of AD
2009-06-02. Those requirements are referenced in the service
information identified previously, which, in turn, is referenced in
paragraph (g) of this proposed AD. This proposed AD would also require
repetitively inspecting for skin cracks next to the shear tie on
airplanes with certain existing doublers, and corrective action if
necessary. This proposed AD would also revise the applicability to
include additional airplanes. This proposed AD would require
accomplishing the actions specified in the service information
described previously.
This proposed AD would also require that requests for approval of
alternative methods of compliance (AMOCs) be directed to the Seattle
Aircraft Certification Office.
The phrase ``corrective actions'' is 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.
Difference Between Proposed AD and 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 234 airplanes of U.S.
registry. We estimate the following costs to comply with this proposed
AD:
[[Page 33014]]
Estimated Costs
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Cost on U.S.
Action Labor cost Parts cost Cost per product operators
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Inspection................. 30 or 49 work-hours $0 $2,550 or $4,165 per Up to $974,610 per
(depending on inspection cycle. inspection cycle.
inspection) x $85
per hour = $2,550 or
$4,165 per
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.
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 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 that the 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 removing airworthiness directive (AD)
2009-06-02, Amendment 39-15838 (74 FR 11013, March 16, 2009), and
adding the following new AD:
The Boeing Company: Docket No. FAA-2013-0461; Directorate Identifier
2012-NM-169-AD.
(a) Comments Due Date
The FAA must receive comments on this AD action by July 18,
2013.
(b) Affected ADs
This AD supersedes AD 2009-06-02, Amendment 39-15838 (74 FR
11013, March 16, 2009).
(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, as identified in
Boeing Alert Service Bulletin 747-53A2682, Revision 1, dated May 24,
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 an evaluation by the design approval
holder (DAH) indicating that certain fuselage frame shear ties are
subject to widespread fatigue damage (WFD). The actions were
developed to support the airplane's limit of validity (LOV) of the
engineering data that support the established structural maintenance
program. We are issuing this AD to detect and correct fatigue cracks
in the fuselage skin that can propagate and grow, and result in
reduced structural integrity and sudden decompression of the
airplane in flight.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Repetitive Inspections
At the applicable compliance time specified in paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 747-53A2682,
Revision 1, dated May 24, 2012, except as provided by paragraphs
(i)(1) and (i)(2) of this AD, do an external detailed or high
frequency eddy current (HFEC) inspection for skin cracks at
specified shear tie end fastener locations of the fuselage frames,
and do all applicable corrective actions, in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2682, Revision 1, dated May 24, 2012, except as required by
paragraph (i)(3) of this AD. Do all applicable corrective actions
before further flight. Repeat the external detailed or HFEC
inspection thereafter at the applicable time specified in paragraph
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2682,
Revision 1, dated May 24, 2012.
(h) Post-Repair Inspections
For any external repair doubler in the inspection area specified
in the Accomplishment Instructions of Boeing Alert Service Bulletin
747-53A2682, Revision 1, dated May 24, 2012, that has an upper or
lower fastener row that is common to a shear tie end fastener: At
the applicable time specified in paragraph (h)(1) or (h)(2) of this
AD, whichever occurs later, do an internal HFEC inspection for
cracks in the skin next to the shear tie, and do all applicable
corrective actions, in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin 747-53A2682, Revision
1, dated May 24, 2012, except as required by paragraph (i)(3) of
this AD. Do all corrective actions before further flight. Repeat the
external detailed inspection thereafter at the time specified in
Table 4 or Table 5 of paragraph 1.E., ``Compliance,'' of Boeing
Alert Service Bulletin 747-53A2682, Revision 1, dated May 24, 2012,
as applicable.
(1) Before further flight after an inspection required by
paragraph (g) of this AD.
(2) Within 2,000 flight cycles after the effective date of this
AD.
(i) Service Information Clarifications and Exceptions
(1) Paragraph 1.E., ``Compliance,'' of Boeing Alert Service
Bulletin 747-53A2682, Revision 1, dated May 24, 2012, specifies
certain compliance times in terms of the effective date of AD 2009-
06-02,
[[Page 33015]]
Amendment 39-15838 (74 FR 11013, March 16, 2009). The effective date
of AD 2009-06-02 is April 20, 2009.
(2) Where paragraph 1.E. of Boeing Alert Service Bulletin 747-
53A2682, Revision 1, dated May 24, 2012, specifies counting the
compliance time ``after the revision 1 date of this service
bulletin,'' this AD requires compliance within the applicable time
after the effective date of this AD.
(3) Where Boeing Alert Service Bulletin 747-53A2682, Revision 1,
dated May 24, 2012, specifies to contact Boeing for repair
instructions, this AD requires repair before further flight using a
method approved in accordance with the procedures specified in
paragraph (l) of this AD.
(j) Credit for Previous Actions
This paragraph provides credit for the actions specified in
paragraph (g) of this AD, if those actions were performed before the
effective date of this AD using Boeing Alert Service Bulletin 747-
53A2682, dated May 8, 2008.
(k) Special Flight Permit
Special flight permits, as described in Section 21.197 and
Section 21.199 of the Federal Aviation Regulations (14 CFR 21.197
and 21.199), are not allowed.
(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 paragraph (m)(2) of this AD.
Information may be emailed to: [email protected].
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
(3) An AMOC that provides an acceptable level of safety may be
used for any repair required by this AD if it is approved by the
Boeing Commercial Airplanes Organization Designation Authorization
(ODA) that has been authorized by the Manager, Seattle ACO, to make
those findings. For a repair method to be approved, the repair must
meet the certification basis of the airplane, and the approval must
specifically refer to this AD.
(m) Related Information
(1) For more information about this AD, contact Roger Caldwell,
Aerospace Engineer, Technical Operations Center, ANM-100D, FAA,
Denver ACO, 26805 East 68th Avenue, Room 214, Denver, Colorado
80249-6361; phone: 303-342-1086; fax: 303-342-1088; email:
[email protected].
(2) For information about AMOCs, contact Bill Ashforth,
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle ACO,
1601 Lind Avenue SW., Renton, Washington 98057-3356; phone: 425-917-
6432; fax: 425-917-6590; email: [email protected].
(3) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-
5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. You may review copies of the referenced
service information at the FAA, Transport Airplane Directorate, 1601
Lind Avenue SW., Renton, Washington. For information on the
availability of this material at the FAA, call 425-227-1221.
Issued in Renton, Washington, on May 22, 2013.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2013-13002 Filed 5-31-13; 8:45 am]
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