[Federal Register Volume 78, Number 70 (Thursday, April 11, 2013)]
[Proposed Rules]
[Pages 21569-21571]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2013-08454]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-0299; Directorate Identifier 2012-NM-072-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 727 airplanes. This proposed AD was prompted
by reports of cracks on the elevator rear spar stiffener assembly. This
proposed AD would require repetitive detailed inspections for cracking
of the elevator rear spar stiffener assembly, and corrective actions if
necessary. We are proposing this AD to detect and correct cracking of
the elevator rear spar stiffener assembly, which could adversely affect
elevator structural stiffness, that could lead to elevator vibration
and possible interference with the tab control rod and which could
result in flutter and consequent loss of control of the airplane.
DATES: We must receive comments on this proposed AD by May 28, 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. 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: Berhane Alazar, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6577; 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-2013-0299;
Directorate Identifier 2012-NM-072-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://
[[Page 21570]]
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 of cracks on the elevator rear spar stiffener
assembly. An operator reported finding a crack on the rear spar
stiffener assembly while accomplishing Boeing Service Bulletin 727-55-
0089 to address cracking of the elevator rear spar web at the elevator
tab hinge fittings. A cracked elevator rear spar stiffener assembly, if
not detected and corrected, could adversely affect elevator structural
stiffness, which could result in elevator vibration and possible
interference with the tab control rod and could lead to flutter and
consequent loss of control of the airplane.
Relevant Service Information
We reviewed Boeing Special Attention Service Bulletin 727-55-0094,
dated March 21, 2012. For information on the procedures and compliance
times, see this service information at http://www.regulations.gov by
searching for Docket No. FAA-2013-0299.
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.
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 actions, 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.
Costs of Compliance
We estimate that this proposed AD affects 98 airplanes of U.S.
registry. We estimate the following costs to comply with this proposed
AD:
Estimated Costs
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Cost on U.S.
Action Labor cost Parts cost Cost per product operators
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Inspection........... 5 work-hours x $85 per None................ $425 per inspection $41,650 per
hour = $425 per cycle. inspection cycle
inspection 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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Cost per
Action Labor cost Parts cost product
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Replacement............................ 7 work-hours x $85 per hour = Unknown.................. $595
$595.
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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-2013-0299; Directorate Identifier
2012-NM-072-AD.
[[Page 21571]]
(a) Comments Due Date
We must receive comments by May 28, 2013.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all The Boeing Company Model 727, 727C, 727-
100, 727-100C, 727-200, and 727-200F series airplanes, certificated
in any category.
(d) Subject
Joint Aircraft System Component (JASC)/Air Transport Association
(ATA) of America Code 55, Stabilizers.
(e) Unsafe Condition
This AD was prompted by reports of cracks on the elevator rear
spar stiffener assembly. We are issuing this AD to detect and
correct cracking of the elevator rear spar stiffener assembly, which
could adversely affect elevator structural stiffness, that could
lead to elevator vibration and possible interference with the tab
control rod and which could result in elevator flutter and
consequent loss of control of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Repetitive Inspections and Corrective Actions
Except as provided by paragraph (h) of this AD, at the
applicable time specified in table 1 of paragraph 1.E.,
``Compliance,'' of Boeing Special Attention Service Bulletin 727-55-
0094, dated March 21, 2012, do a detailed inspection for any
cracking of the elevator rear spar stiffener assembly, and all
applicable corrective actions, in accordance with the Accomplishment
Instructions of Boeing Special Attention Service Bulletin 727-55-
0094, dated March 21, 2012. Do all applicable corrective actions
before further flight. Repeat the inspection thereafter at the
applicable time specified in table 1 of paragraph 1.E.,
``Compliance,'' of Boeing Special Attention Service Bulletin 727-55-
0094, dated March 21, 2012, except as provided by paragraph (j) of
this AD.
(h) Exception
Where Boeing Special Attention Service Bulletin 727-55-0094,
dated March 21, 2012, specifies a compliance time ``from the
original issue date of this service bulletin,'' this AD requires
compliance within the specified compliance time after the effective
date of this AD.
(i) Optional Replacement
Replacing the elevator rear spar stiffener assembly with a new
assembly in accordance with Part 4 or 5, as applicable, of the
Accomplishment Instructions of Boeing Special Attention Service
Bulletin 727-55-0094, dated March 21, 2012, terminates the
inspections required by paragraph (g) of this AD for that assembly,
except as required by paragraph (j) of this AD.
(j) Post-Replacement Inspection Compliance Time
For any elevator rear spar stiffener assembly replaced as
required by paragraph (g) of the AD or as specified in paragraph (i)
of this AD: Do the next inspection required by paragraph (g) of this
AD for that assembly within 96 months after accomplishing the
replacement and repeat thereafter at the times specified in
paragraph (g) of this AD.
(k) 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.
(l) Related Information
(1) For more information about this AD, contact Berhane Alazar,
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft
Certification Office, 1601 Lind Avenue SW., Renton, WA 98057-3356;
phone: 425-917-6577; 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. SW., Renton, WA. For information on the availability of
this material at the FAA, call 425-227-1221.
Issued in Renton, Washington, on March 28, 2013.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2013-08454 Filed 4-10-13; 8:45 am]
BILLING CODE 4910-13-P