[Federal Register Volume 78, Number 45 (Thursday, March 7, 2013)]
[Proposed Rules]
[Pages 14731-14734]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2013-05189]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-0204; Directorate Identifier 2012-NM-229-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 747-400 and 747-400F series airplanes.
This proposed AD was prompted by reports of cracking in the outboard
flange of the longeron extension fittings, which attach to the wing-to-
body fairing support frame. This proposed AD would require repetitive
inspections of the longeron extension fittings for cracking, and
corrective actions if necessary. We are proposing this AD to detect and
correct cracks in the longeron extension fittings, which can become
large and adversely affect the structural integrity of the airplane.
DATES: We must receive comments on this proposed AD by April 22, 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 Boeing 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, 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: 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-2013-0204;
Directorate Identifier 2012-NM-229-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
We received reports that cracks were found in the outboard flanges
of the
[[Page 14732]]
longeron extension fittings installed on the left and right sides of
the airplane. Longeron extension fittings are installed on the fuselage
under the wing-to-body fairing and attach the overwing longeron to the
fuselage. The outboard flange of the fitting attaches to the wing-to-
body fairing support frame web. Subsequent analysis by Boeing indicated
that the cracks were caused by fatigue combined with preload stress
from improper fit-up during assembly. A manufacturing process change
that began at line number 1199 might have resulted in preloading the
longeron extension fittings. We are proposing this AD to detect and
correct cracks in the longeron extension fittings, which can become
large and adversely affect the structural integrity of the airplane.
Relevant Service Information
We reviewed Boeing Alert Service Bulletin 747-53A2860, dated
December 4, 2012. For information on the procedures and compliance
times, see this service information at http://www.regulations.gov by
searching for Docket No. FAA-2013-0204.
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 action, 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
This proposed AD includes airplanes that are not included in the
effectivity of Boeing Alert Service Bulletin 747-53A2860, dated
December 4, 2012. That service bulletin defines actions for airplanes
having line numbers 1199 through 1419 inclusive. Boeing recently
reported an event that involved a cracked longeron extension fitting on
the airplane having line number 1101. Based on this event we are
expanding the airplane applicability in this proposed AD from airplanes
having line numbers 1199 through 1419 inclusive to airplanes having
line numbers 1076 through 1419 inclusive. We have coordinated this
difference with Boeing.
Although Boeing Alert Service Bulletin 747-53A2860, dated December
4, 2012, specifies that operators may contact the manufacturer for the
disposition of certain repair conditions, 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 41 airplanes of U.S.
registry.
We estimate the following costs to comply with this proposed AD:
Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product Cost on U.S. operators
--------------------------------------------------------------------------------------------------------------------------------------------------------
High frequency eddy current inspection 32 work-hours x $85 per $0 $2,720 $111,520, per inspection cycle.
for cracking in longeron extension hour = $2,720, per
fittings. inspection cycle.
Option to do preventative modification 479 work-hours x $85 per 0 40,715 $1,669,315.
instead of repetitive inspections. hour = $40,715.
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We estimate the following costs to do any necessary replacements
that would be required based on the results of the proposed inspection.
We have no way of determining the number of aircraft that might need
this replacement:
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
----------------------------------------------------------------------------------------------------------------
Replacement................................ 464 work-hours x $85 per hour = $0 $39,440
$39,440.
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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
[[Page 14733]]
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-2013-0204; Directorate Identifier
2012-NM-229-AD.
(a) Comments Due Date
We must receive comments by April 22, 2013.
(b) Affected ADs
None.
(c) Applicability
This AD applies to The Boeing Company Model 747-400 and 747-400F
series airplanes, certificated in any category, line numbers 1076
through 1419 inclusive.
(d) Subject
Joint Aircraft System Component (JASC)/Air Transport Association
(ATA) of America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by reports of cracking in the outboard
flange of the longeron extension fittings, which attach to the wing-
to-body fairing support frame. We are issuing this AD to detect and
correct cracks in the longeron extension fittings, which can become
large and adversely affect the structural integrity of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Inspection of Longeron Extension Fitting
For all airplanes: Except as required by paragraphs (i)(1) and
(i)(4) of this AD, at the time specified in table 1 of paragraph
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2860,
dated December 4, 2012: Do a surface high frequency eddy current
(HFEC) inspection of the left and right longeron extension fittings
for cracking, and do all applicable corrective actions, in
accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 747-53A2860, dated December 4, 2012, except as
required by paragraphs (i)(2) and (i)(3) of this AD. Do all
applicable corrective actions before further flight. If no cracking
is found, repeat the inspection thereafter at the intervals
specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service
Bulletin 747-53A2860, dated December 4, 2012, until a permanent
repair, longeron extension fitting replacement, or preventative
modification is done, in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin 747-53A2860, dated
December 4, 2012.
(h) Inspection of Temporary Repair and Corrective Actions
For airplanes on which a temporary repair as specified in Boeing
Alert Service Bulletin 747-53A2860 has been done: At the times
specified in table 2 of paragraph 1.E., ``Compliance,'' of Boeing
Alert Service Bulletin 747-53A2860, dated December 4, 2012, do a
surface HFEC inspection of the temporary repair of the longeron
extension fittings for cracking, and all applicable corrective
actions, in accordance with the Accomplishment Instructions of
Boeing Alert Service Bulletin 747-53A2860, dated December 4, 2012,
except as required by paragraph (i)(3) of this AD. Do all applicable
corrective actions before further flight.
(i) Exceptions to Service Bulletin Specifications
The following exceptions apply to this AD.
(1) Where Boeing Alert Service Bulletin 747-53A2860, dated
December 4, 2012, specifies a compliance time relative to the issue
date of that service bulletin, this AD requires compliance within
the specified compliance time after the effective date of this AD.
(2) Where Boeing Alert Service Bulletin 747-53A2860, dated
December 4, 2012, specifies to contact Boeing for repair
information: Before further flight, repair using a method approved
in accordance with the procedures specified in paragraph (k) of this
AD.
(3) For airplanes not identified in Boeing Alert Service
Bulletin 747-53A2860, dated December 4, 2012: These airplanes are in
Group 1 for the purposes of this AD and are required to do the
applicable actions specified in the Accomplishment Instructions of
Boeing Alert Service Bulletin 747-53A2860, dated December 4, 2012.
(4) Where Boeing Alert Service Bulletin 747-53A2860, dated
December 4, 2012, specifies ``all airplanes,'' this means all
airplanes identified in paragraph (c) of this AD.
(j) Optional Terminating Action
Doing the permanent repair, longeron extension fitting
replacement, or preventative modification, in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2860, dated December 4, 2012, terminates the repetitive
inspection required by paragraph (g) of this AD.
(k) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Seattle Aircraft Certification Office, 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: [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.
(l) 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].
(2) For Boeing 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-
[[Page 14734]]
5680; Internet https://www.myboeingfleet.com. You may also 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 February 25, 2013.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2013-05189 Filed 3-6-13; 8:45 am]
BILLING CODE 4910-13-P