[Federal Register Volume 78, Number 77 (Monday, April 22, 2013)]
[Proposed Rules]
[Pages 23694-23696]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2013-09407]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-0334; Directorate Identifier 2013-NM-027-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 all
The Boeing Company Model 757 airplanes. This proposed AD was prompted
by a report of a broken forward support fitting at the inboard track of
the inboard flap. This proposed AD would require repetitive inspections
of the forward support fitting assemblies of the inboard track of the
left and right inboard flaps for cracking, and corrective actions if
necessary. We are proposing this AD to detect and correct cracking of
the forward support fitting assembly, which could result in loss of
inboard flap control and subsequent loss of airplane control.
DATES: We must receive comments on this proposed AD by June 6, 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 Ave
SW., Renton, WA 98057. 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: Nancy Marsh, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue SW., Renton, WA 98057-3356; phone: (425) 917-6440;
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-2013-0334;
Directorate Identifier 2013-NM-027-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 a report of a broken forward support fitting assembly
at the inboard track of the inboard flap. During a post-flight taxi,
pilots noticed a FLAP TE DISAGREE message on the engine indication and
crew alerting system (EICAS). Maintenance personnel found that both
components of the forward support fitting assembly had broken, causing
the inboard track and transmission to drop 8 inches into the wheel
well. The airplane had accumulated 22,328 total flight cycles.
Metallurgical analysis found that cracks had initiated at a compound
radius in each component flange common to the main landing gear (MLG)
beam. Each crack was propagated by fatigue and was followed by final
ductile rupture. This condition, if not detected and corrected, could
result in loss of inboard flap control and subsequent loss of airplane
control.
Relevant Service Information
We reviewed Boeing Special Attention Service Bulletin 757-57-0071,
dated September 12, 2012. For information on the procedures and
compliance times, see this service information at http://www.regulations.gov by searching for Docket No. FAA-2013-0334.
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.
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.
Costs of Compliance
We estimate that this proposed AD affects 690 airplanes of U.S.
registry.
We estimate the following costs to comply with this proposed AD:
[[Page 23695]]
Estimated Costs
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Cost on U.S.
Action Labor cost Parts cost Cost per product operators
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High-frequency eddy current 11 work-hours x $85 None................ $935, per $645,150, per
inspection. per hour = $935, inspection cycle. inspection
per inspection cycle.
cycle
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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
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Action Labor cost Parts cost Cost per product
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Replacement....................... 7 work-hours x $85 $10,000 $10,595, per assembly.
per hour = $595, per
assembly.
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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-2013-0334; Directorate Identifier
2013-NM-027-AD.
(a) Comments Due Date
We must receive comments by June 6, 2013.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all The Boeing Company Model 757-200, -200PF,
-200CB, and -300 series airplanes, certificated in any category.
(d) Subject
Joint Aircraft System Component (JASC)/Air Transport Association
(ATA) of America Code 5753, Trailing edge flaps.
(e) Unsafe Condition
This AD was prompted by a report of a broken forward support
fitting at the inboard track of the inboard flap. We are issuing
this AD to detect and correct cracking of the forward support
fitting assembly, which could result in loss of inboard flap control
and subsequent loss of airplane control.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Inspection and Corrective Action
Except as provided by paragraph (h) of this AD, at the
applicable time specified in paragraph 1.E., ``Compliance,'' of
Boeing Special Attention Service Bulletin 757-57-0071, dated
September 12, 2012: Do a high frequency eddy current (HFEC)
inspection for cracking in the forward support fitting assemblies of
the inboard track of the left and right inboard flaps, and do all
applicable corrective actions, in accordance with paragraph 3.B.2.
of the Accomplishment Instructions of Boeing Special Attention
Service Bulletin 757-57-0071, dated September 12, 2012. Do all
applicable corrective actions before further flight. Thereafter,
repeat the inspections at intervals not to exceed 6,000 flight
cycles, except as required by paragraphs (g)(1) and (g)(2) of this
AD.
(1) For Group 1 airplanes as identified in Boeing Special
Attention Service Bulletin 757-57-0071, dated September 12, 2012, on
which any forward support fitting assembly is replaced: Do the next
inspection before 15,000 flight cycles has accumulated on that
assembly.
(2) For Group 2 airplanes as identified in Boeing Special
Attention Service Bulletin 757-57-0071, dated September 12, 2012, on
which any forward support fitting assembly is replaced: Do the next
inspection before 18,000 flight cycles has accumulated on that
assembly.
(h) Exception to the Service Information
(1) Where Boeing Special Attention Service Bulletin 757-57-0071,
dated September 12, 2012, specifies compliance times ``after the
original issue date of this service bulletin,'' this AD requires
compliance within the specified compliance times ``after the
effective date of this AD.''
(2) Paragraphs 3.B.1. and 3.B.3. of the Accomplishment
Instructions of Boeing Special Attention Service Bulletin 757-57-
[[Page 23696]]
0071, dated September 12, 2012, are not required by this AD.
(i) 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: [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.
(j) Related Information
(1) For more information about this AD, contact Nancy Marsh,
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft
Certification Office, 1601 Lind Avenue SW., Renton, WA 98057-3356;
phone: (425) 917-6440; fax: (425) 917-6590; email:
[email protected].
(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 Ave. NW., Renton, WA. For information on the availability of
this material at the FAA, call 425-227-1221.
Issued in Renton, Washington, on April 12, 2013.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2013-09407 Filed 4-19-13; 8:45 am]
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