[Federal Register Volume 73, Number 34 (Wednesday, February 20, 2008)]
[Proposed Rules]
[Pages 9239-9241]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E8-2995]


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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:

----------------------------------------------------------------------------------------------------------------
                                                                               Total cost per     Total cost on
                        Labor cost                             Parts cost         airplane       U.S.  operators
----------------------------------------------------------------------------------------------------------------
2 work-hours x $80 per hour = $160........................                $0              $160          $499,040
----------------------------------------------------------------------------------------------------------------

    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:

------------------------------------------------------------------------
                                                         Total cost per
       Labor cost per fitting          Parts cost per    airplane  (for
                                           fitting        two fittings)
------------------------------------------------------------------------
30 work-hours x $80 per hour =                    $200            $5,200
 $2,400.............................
------------------------------------------------------------------------

    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:

------------------------------------------------------------------------
        If the following exists:                      Then:
------------------------------------------------------------------------
(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.
------------------------------------------------------------------------

    (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]
BILLING CODE 4910-13-P