[Federal Register: February 20, 2008 (Volume 73, Number 34)]
[Proposed Rules]
[Page 9239-9241]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr20fe08-26]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-0177; Directorate Identifier 2007-CE-093-AD]
RIN 2120-AA64
Airworthiness Directives; Taylorcraft Models A, B, and F Series
Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: We propose to adopt a new airworthiness directive (AD) for
certain Taylorcraft Models A, B, and F series airplanes. This proposed
AD would require inspection of the wing strut attach fittings for
corrosion or cracks and would require repair or replacement if
corrosion or cracks are found. This proposed AD results from data
collected from an accident involving a Taylorcraft Model BF12-65
airplane. The wing separated from the airplane after the wing strut
attach fitting failed due to corrosion. We are proposing this AD to
detect and correct corrosion or cracks in the wing strut attach
fittings. This condition, if not corrected, could result in failure of
the wing strut attach fittings and lead to wing separation and loss of
control.
DATES: We must receive comments on this proposed AD by March 21, 2008.
ADDRESSES: Use one of the following addresses to comment on this
proposed AD:
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: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
For service information identified in this proposed AD, contact
Taylorcraft Aviation, LLC, 2124 North Central Avenue, Brownsville,
Texas 78521; telephone: 956-986-0700.
FOR FURTHER INFORMATION CONTACT: Andy McAnaul, Aerospace Engineer,
10100 Reunion Place, San Antonio, Texas 78216; telephone: (210) 308-
3365; fax: (210) 308-3370.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments regarding this proposed AD. Send your comments to an address
listed under the
[[Page 9240]]
ADDRESSES section. Include the docket number, ``FAA-2007-0177;
Directorate Identifier 2007-CE-093-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the proposed AD. We will
consider all comments received by the closing date and may amend the
proposed AD in light 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 concerning this proposed AD.
Discussion
This proposed AD results from data collected after a double
fatality accident involving a Taylorcraft Model BF12-65 airplane near
Oregon City, Oregon in July 2007. The fitting was corroded
approximately 70 percent through the fracture surface. The airplane's
fabric was wrapped around the lugs of the wing strut attach fitting
with the ends of the fabric stuffed into the fitting itself. The fabric
plugged the drain hole on the bottom of the fitting and prevented water
from draining out the front and back ends of the fitting. The fabric
also did not allow for easy visual inspection of the exterior and
interior of the fitting. In addition to fabric, the drain hole was
blocked by other foreign debris as well.
The corrosion or cracking is most likely to occur in the section
between where the front and rear lift strut attach fittings are bolted
to the fuselage fitting. This condition, if not corrected, could result
in failure of the wing strut attach fittings and lead to wing
separation and loss of control.
Relevant Service Information
We have reviewed Taylorcraft Aviation, LLC Service Bulletin No.
2007-002, dated November 8, 2007.
The service information describes procedures for inspecting the
wing strut attach fitting part number A-A11 for cracks or corrosion and
procedures for any required repair or replacement.
FAA's Determination and Requirements of the Proposed AD
We are proposing this AD because we evaluated all information and
determined the unsafe condition described previously is likely to exist
or develop on other products of the same type design. This proposed AD
would require inspection of the wing strut attach fitting for cracks
and corrosion and repair or replacement if cracks or corrosion are
found.
Costs of Compliance
We estimate that this proposed AD would affect 3,119 airplanes in
the U.S. registry.
We estimate the following costs to do the proposed inspection:
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Total cost per Total cost on
Labor cost Parts cost airplane U.S. operators
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2 work-hours x $80 per hour = $160........................ $0 $160 $499,040
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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 airplanes that may need
this replacement:
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Total cost per
Labor cost per fitting Parts cost per airplane (for
fitting two fittings)
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30 work-hours x $80 per hour = $200 $5,200
$2,400.............................
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We have no way of determining the number of airplanes that may
require repair as a result of the proposed inspection or the extent of
repair that may be required.
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); and
3. 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.
We prepared a regulatory evaluation of the estimated costs to
comply with this proposed AD and placed it in the AD docket.
Examining the AD Docket
You may examine the AD docket that contains the proposed AD, the
regulatory evaluation, any comments received, and other information 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 Docket Office (telephone (800) 647-5527)
is located at the street address stated in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
[[Page 9241]]
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
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]
2. The FAA amends Sec. 39.13 by adding the following new AD:
Taylorcraft: Docket No. FAA-2007-0177; Directorate Identifier 2007-
CE-093-AD.
Comments Due Date
(a) We must receive comments on this airworthiness directive
(AD) action by March 21, 2008.
Affected ADs
(b) None.
Applicability
(c) This AD applies to all serial numbers of Taylorcraft Models
A, BC, BCS12-D, BCS, BC12-D1, BC-65, BCS12-D1, BCS-65, BC12D-85,
BC12-65 (Army L-2H), BCS12D-85, BCS12-65, BC12D-4-85, BC12-D,
BCS12D-4-85, (Army L-2G) BF, BFS, BF-60, BFS-60, BF-65, BFS-65,
(Army L-2K) BF 12-65, BFS-65, BL, BLS, (Army L-2F) BL-65, BLS-65,
(Army L-2J) BL12-65, BLS12-65, 19, F19, F21, F21A, F21B, F22, F22A,
F22B, and F22C airplanes that are certificated in any category.
Note: This AD applies to all Taylorcraft models listed above,
including those models not listed in Taylorcraft Aviation, LLC
Service Bulletin No. 2007-002, dated November 8, 2007. If there are
any other differences between this AD and the above service
bulletin, this AD takes precedence.
Unsafe Condition
(d) This AD results from data collected from an accident
involving a Taylorcraft Model BF12-65 airplane. The wing separated
from the airplane after the wing strut attach fitting failed due to
corrosion. We are proposing this AD to detect and correct corrosion
or cracks in the wing strut attach fittings. This condition, if not
corrected, could result in failure of the wing strut attach fittings
and lead to wing separation and loss of control.
Compliance
(e) To address this problem, you must do the following, unless
already done:
(1) Initially inspect the left and right wing lift strut attach
fittings, part number (P/N) A-A11, for corrosion or cracking
following Taylorcraft Aviation, LLC Service Bulletin No. 2007-002,
dated November 8, 2007, using the following compliance times:
(i) For airplanes that have never been equipped with floats or
snow skis: Within the next 90 days after the effective date of this
AD.
(ii) For airplanes equipped with or that have ever been equipped
with floats or snow skis: Within the next 30 days after the
effective date of this AD.
(2) If the airplane is equipped with floats or snow skis at the
time of the initial inspection required by paragraph (e)(1) of this
AD or at any time after the initial inspection required by paragraph
(e)(1) of this AD, you must repeat the inspection required in
paragraph (e)(1) of this AD as follows:
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If the following exists: Then:
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(i) The airplane is equipped with Inspect no later than 48 months
floats or snow skis at the time of the following the initial
initial inspection required by inspection and repetitively
paragraph (e)(1) of this AD. inspect thereafter at
intervals not to exceed 48
months. Continue these
repetitive inspections until
removal of floats or snow
skis, at which time you must
follow paragraph (e)(2)(ii) of
this AD.
(ii) You remove floats or snow skis at Inspect no later than 48 months
any time following the initial following the last inspection.
inspection required by paragraph After the inspection following
(e)(1) of this AD. removal of floats or snow
skis, no further inspections
are required unless floats or
snow skis are re-installed at
a later date, at which time
you must follow paragraph
(e)(2)(iii) of this AD.
(iii) You install floats or snow skis Inspect no later than 48 months
at any time since the initial following the last inspection
inspection required by paragraph or before further flight after
(e)(1) of this AD. installation of floats or snow
skis, whichever occurs later,
and repetitively inspect
thereafter at intervals not to
exceed 48 months. Continue
these repetitive inspections
until removal of floats or
snow skis, at which time you
must follow paragraph
(e)(2)(ii) of this AD.
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(3) If you find cracking or material loss due to corrosion
during any of the inspections required in paragraph (e)(1) or (e)(2)
of this AD, before further flight, do the following:
(i) Contact Taylorcraft Aviation, LLC at 2124 North Central
Avenue, Brownsville, Texas 78521; telephone: 956-986-0700 to obtain
an FAA-approved repair scheme or replacement procedure; and
(ii) Repair following the FAA-approved repair scheme or replace
the left and/or right wing lift strut attach fitting(s), P/N A-A11,
following the replacement procedure.
Alternative Methods of Compliance (AMOCs)
(f) The Manager, Fort Worth Airplane Certification Office, FAA,
has the authority to approve AMOCs for this AD, if requested using
the procedures found in 14 CFR 39.19. Send information to ATTN: Andy
McAnaul, Aerospace Engineer, 10100 Reunion Place, San Antonio, Texas
78216; telephone: (210) 308-3365; fax: (210) 308-3370. Before using
any approved AMOC on any airplane to which the AMOC applies, notify
your appropriate principal inspector (PI) in the FAA Flight
Standards District Office (FSDO), or lacking a PI, your local FSDO.
Related Information
(g) To get copies of the service information referenced in this
AD, contact Taylorcraft Aviation, LLC, 2124 North Central Avenue,
Brownsville, Texas 78521; telephone: 956-986-0700. To view the AD
docket, go to U.S. Department of Transportation, Docket Operations,
M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey
Avenue, SE., Washington, DC 20590, or on the Internet at http://www.regulations.gov
.
Issued in Kansas City, Missouri, on February 12, 2008.
David R. Showers,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E8-2995 Filed 2-19-08; 8:45 am]
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