

[Federal Register: December 10, 2007 (Volume 72, Number 236)]
[Proposed Rules]               
[Page 69630-69635]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr10de07-29]                         

-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-0286; Directorate Identifier 2007-CE-086-AD]
RIN 2120-AA64

 
Airworthiness Directives; Taylorcraft Aviation, LLC A, B, and F 
Series Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: We propose to supersede Airworthiness Directive (AD) AD 2007-
16-14, which applies to all Taylorcraft Aviation, LLC (Taylorcraft) A, 
B, and F series airplanes. AD 2007-16-14 currently requires you to do 
an initial visual inspection of the left and right wing front and aft 
lift struts for cracks and corrosion and replace any cracked strut or 
strut with corrosion that exceeds certain limits. If the strut is 
replaced with an original design vented strut, AD 2007-16-14 requires 
you to repetitively inspect those struts thereafter. Since we issued AD 
2007-16-14, we determined that the eddy current inspection method does 
not address the unsafe condition for the long term. We also determined 
that Models FA-III and TG-6 airplanes are not equipped with the 
affected struts. Consequently, this proposed AD would retain the 
actions required in AD 2007-16-14, except it removes the eddy current 
inspection method (provides 24-month credit if already done using this 
method), adds the radiograph method as an inspection method, changes 
the Applicability section, and changes the compliance time between the 
repetitive inspections. We are issuing this proposed AD to detect and 
correct cracks and corrosion in the right and left wing front and aft 
lift struts. This condition, if not corrected, could result in failure 
of the lift strut and lead to in-flight separation of the wing.

DATES: We must receive comments on this proposed AD by January 9, 2008.

[[Page 69631]]


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: Andrew McAnaul, Aerospace Engineer, 
ASW-150 (c/o MIDO-43), 10100 Reunion Place, Suite 650, 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 ADDRESSES section. Include the docket number, ``FAA-
2007-0286; Directorate Identifier 2007-CE-086-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

    Reports of several corroded vented wing lift struts from different 
Taylorcraft series airplanes caused us to issue AD 2007-16-14, 
Amendment 39-15153 (72 FR 45153, August 13, 2007). AD 2007-16-14 
currently requires the following on all Taylorcraft A, B, and F series 
airplanes:
     Initial visual inspection of the left and right wing front 
and aft lift struts for cracks and corrosion;
     Replacement of any cracked strut or strut with corrosion 
that exceeds certain limits with either sealed or vented struts; and
     Repetitive eddy current or ultrasound inspection of any 
vented lift struts.
    Since issuing AD 2007-16-14, we received several comments 
concerning the AD. We reviewed all comments submitted to the docket. 
The following are significant comments that influenced our decision to 
propose superseding AD 2007-16-14 with a new AD:

------------------------------------------------------------------------
                Comment                           FAA discussion
------------------------------------------------------------------------
We received several requests to use the  We approved the radiograph
 radiograph inspection method as an       inspection procedure as an
 alternative method of compliance         AMOC for the repetitive
 (AMOC) for doing the repetitive strut    inspections required in AD
 inspection.                              2007-16-14, and the
                                          manufacturer has added the
                                          procedures for the radiograph
                                          inspection to their revised
                                          service bulletin.
We received several requests to          Based on the inspection methods
 increase the compliance time between     used and the requirement to
 repetitive inspections because the       apply corrosion inhibitor to
 Taylorcraft service information          the strut interior at each
 requires the application of corrosion    inspection, we believe there
 inhibitor to the interior of the strut   is not an increased safety
 at each inspection. The commenters       risk to the public by
 also requested a longer compliance       increasing the compliance time
 time between repetitive inspections      between the repetitive
 for land planes compared to float        inspections from 24 months to
 equipped planes.                         48 months for all airplanes.
                                          We do not have sufficient
                                          information to determine if a
                                          different inspection interval
                                          for land and float equipped
                                          airplanes is valid.
We received a request to use Univair     We have approved using these
 part numbers (P/N) UA-A815 and UA-854    parts as an AMOC to AD 2007-16-
 as a terminating action for the          14.
 repetitive inspection requirement on
 Taylorcraft Models BC12-D/D1 and BCS12-
 D/D1 airplanes.
We received several requests to install  We did not intend to preclude
 used vented lift struts that have been   owners from installing these
 inspected using the criteria specified   parts. Vented lift struts that
 in paragraph (e)(2) of AD 2007-16-14.    are inspected using the
                                          ultrasound or radiograph
                                          inspection method, that meet
                                          the Acceptance/Rejection
                                          Criteria specified in
                                          Taylorcraft Aviation, LLC
                                          Service Bulletin No. 2007-001,
                                          Revision B, dated October 15,
                                          2007, and that are treated
                                          with internal corrosion
                                          protection are considered new
                                          struts.
------------------------------------------------------------------------

    In addition to the comments above, we also received several reports 
of the following:
     The eddy current inspection method currently required in 
AD 2007-16-14 may not adequately address the unsafe condition for the 
long term; and
     Models FA-III (Airphibian) and TG-6 Conversion airplanes 
do not have the affected struts installed.
    The following is a significant comment that did not influence our 
decision to propose superseding AD 2007-16-14 with a new AD:

------------------------------------------------------------------------
                Comment                           FAA discussion
------------------------------------------------------------------------
We received several requests to use the  Testing of Taylorcraft strut
 Maule Fabric Tester as an AMOC for       samples with the Maule Fabric
 doing the repetitive strut inspection.   Tester shows that both 1025
                                          steel material, and to a
                                          greater degree 4130 steel
                                          material, resist showing a
                                          positive dent indication until
                                          a major portion of the wall
                                          thickness is consumed.
                                          Taylorcraft used 4130 steel in
                                          a majority of their wing
                                          struts during production. We
                                          have not received any data
                                          substantiating that
                                          Taylorcraft wing struts can
                                          still carry required
                                          certification loads at the
                                          reduced strut wall material
                                          thickness indicated in the
                                          testing.
------------------------------------------------------------------------


[[Page 69632]]

    Cracks and corrosion in the right and left wing front and aft lift 
struts, if not detected and corrected, could result in failure of the 
wing lift strut and lead to in-flight separation of the wing.

Relevant Service Information

    We reviewed Taylorcraft Aviation, LLC Service Bulletin (SB) No. 
2007-001, Revision B, dated October 15, 2007.
    The service information describes procedures for wing lift strut 
assembly corrosion inspection and/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 supersede AD 2007-16-14 with a new AD that would do the 
following:
     Retain the actions of AD 2007-16-14;
     Remove the eddy current inspection method, but allow a 24-
month credit for those who already inspected once using the eddy 
current method;
     Remove Models FA-III (Airphibian) and TG-6 Conversion 
airplanes from the Applicability section;
     Add the radiograph inspection method;
     Increase the time interval between the repetitive 
inspections;
     Allow the installation of Univair P/Ns UA-A815 and UA-854 
on Taylorcraft Models BC12-D/D1 and BCS12-D/D1 airplanes as a 
terminating action for the repetitive inspection requirement; and
     Allow the installation of used vented lift struts that 
have been inspected using ultrasound or radiograph inspection methods, 
meet the Acceptance/Rejection Criteria specified in Taylorcraft 
Aviation, LLC Service Bulletin No. 2007-001, Revision B, dated October 
15, 2007, and have corrosion inhibitor applied to the interior of the 
strut. These lift struts are then subject to the repetitive 48-month 
inspection thereafter.
    We have determined that the Maule Fabric Tester is not a viable 
AMOC to this AD.
    This proposed AD would require you to use the service information 
described previously to perform these actions.

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 visual 
inspection:

----------------------------------------------------------------------------------------------------------------
                                                                                  Total cost per   Total cost on
                  Labor cost                               Parts cost                airplane     U.S. operators
----------------------------------------------------------------------------------------------------------------
1 work-hour x $80 per hour = $80..............  Not applicable..................             $80        $249,520
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do the proposed repetitive 
ultrasound or radiograph inspection:

------------------------------------------------------------------------
                                                          Total cost per
            Labor cost                   Parts cost          airplane
------------------------------------------------------------------------
4 work-hours x $80 per hour = $320  Not applicable......            $320
------------------------------------------------------------------------

    We estimate the following costs to do any necessary replacements 
that would be required based on the results of the proposed 
inspections. We have no way of determining the number of airplanes that 
may need this replacement:

------------------------------------------------------------------------
                                                        Total cost per
                                                          airplane to
           Labor cost                 Parts cost      replace all 4 wing
                                                          lift struts
------------------------------------------------------------------------
4 work-hours to replace all 4     Sealed front lift   $1,670 + $1,276 +
 struts x $80 per hour = $320.     strut: $835 per     $320 = $3,266.
                                   strut. 2 per
                                   airplane = $1,670.
                                  Sealed aft lift
                                   strut: $638 per
                                   strut. 2 per
                                   airplane = $1,276.
------------------------------------------------------------------------

    Original design vented lift struts are no longer manufactured. We 
have no way of determining the cost associated with obtaining a useable 
vented strut.
    The estimated total cost on U.S. operators includes the cumulative 
costs associated with AD 2007-16-14 and any actions being added in this 
proposed AD.

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;

[[Page 69633]]

    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.

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 removing Airworthiness Directive 
(AD) 2007-16-14, Amendment 39-15153 (72 FR 45153, August 13, 2007), and 
by adding a new AD to read as follows:

Taylorcraft Aviation, LLC: Docket No. FAA-2007-0286; Directorate 
Identifier 2007-CE-086-AD.

Comments Due Date

    (a) We must receive comments on this airworthiness directive 
(AD) action by January 9, 2008.

Affected ADs

    (b) This AD supersedes AD 2007-16-14, Amendment 39-15153.

Applicability

    (c) This AD applies to all serial numbers of Taylorcraft Models 
A, BC, BCS, BC-65, BCS-65, BC12-65 (Army L-2H), BCS12-65, BC12-D, 
BCS12-D, BC12-D1, BCS12-D1, BC12D-85, BCS12D-85, BC12D-4-85, BCS12D-
4-85, (Army L-2G) BF, BFS, BF-60, BFS-60, BF-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:
    (1) Are certificated in any category; and
    (2) Do not incorporate sealed wing front lift struts, part 
number (P/N) MA-A815, Univair P/N UA-A815 (for Models BC12-D/D1 and 
BCS12-D/D1 only), or FAA-approved equivalent P/N, and sealed aft 
lift struts, P/N MA-A854, Univair P/N UA-854 (for Models BC12-D/D1 
and BCS12-D/D1 only), or FAA-approved equivalent P/N, for all 
struts.

    Note 1: This AD applies to all Taylorcraft models listed above, 
including those models not listed in Taylorcraft Aviation, LLC 
Service Bulletin No. 2007-001, Revision B, dated October 15, 2007. 
If there are any other differences between this AD and the above 
service bulletin, this AD takes precedence.


    Note 2: For the purposes of this AD, a used strut that has been 
inspected using the ultrasound or radiograph inspection method, 
meets the Acceptance/Rejection Criteria specified in Taylorcraft 
Aviation, LLC Service Bulletin No. 2007-001, Revision B, dated 
October 15, 2007, and is treated with internal corrosion protection, 
is considered a new strut.

Unsafe Condition

    (d) This AD results from our determination that the radiograph 
inspection method should be used in place of the eddy current 
inspection method currently required in AD 2007-16-14. We are 
issuing this AD to detect and correct corrosion or cracks in the 
right and left wing front and aft lift struts, which could result in 
failure of the lift strut and lead to in-flight separation of the 
wing with consequent loss of control.

Compliance

    (e) To address this problem, you must do the following, unless 
already done:

------------------------------------------------------------------------
             Actions                  Compliance          Procedures
------------------------------------------------------------------------
(1) Visually inspect the right    Within the next 5   Follow Part 1 of
 and left wing front and aft       hours TIS after     the Instructions
 lift struts, (P/N A-A815 and P/   August 20, 2007     in Taylorcraft
 N A-A854, or FAA-approved         (the effective      Aviation, LLC
 equivalent P/Ns), along the       date of AD 2007-    Service Bulletin
 entire bottom 12 inches of each   16-14), unless      No. 2007-001,
 strut for cracks and corrosion.   one of the          Revision A, dated
                                   following           August 1, 2007;
                                   conditions is       or Taylorcraft
                                   met:                Aviation, LLC
                                  (i) The struts       Service Bulletin
                                   have been           No. 2007-001,
                                   replaced with       Revision B, dated
                                   parts specified     October 15, 2007.
                                   in paragraph
                                   (e)(2)(i) of this
                                   AD. No further
                                   action is
                                   required on those
                                   struts.
                                  (ii) The struts
                                   have been
                                   replaced with
                                   parts specified
                                   in paragraph
                                   (e)(2)(ii) of
                                   this AD and have
                                   been installed
                                   for less than 48
                                   months. No visual
                                   inspection is
                                   required. These
                                   parts are now
                                   subject to the
                                   repetitive
                                   inspection
                                   requirement
                                   specified in
                                   paragraph (e)(4)
                                   of this AD.
(2) If any cracks are found       Before further      Following the
 during the visual inspection      flight after the    Instructions in
 required in paragraph (e)(1) of   visual inspection   Taylorcraft
 this AD, replace the cracked      required in         Aviation, LLC
 strut with the following          paragraph (e)(1)    Service Bulletin
 applicable strut:                 of this AD.         No. 2007-001,
                                                       Revision B, dated
                                                       October 15, 2007.
    (i) A sealed front lift
     strut, P/N MA-A815, Univair
     P/N UA-A815 (for Models
     BC12-D/D1 and BCS12-D/D1
     only), or FAA-approved
     equivalent P/N, a sealed
     aft lift strut, P/N MA-
     A854, Univair P/N UA-854
     (for Models BC12-D/D1 and
     BCS12-D/D1 only), or FAA-
     approved equivalent P/N.
     Installing these lift
     struts terminates the
     repetitive inspections
     required by this AD for
     that strut and no further
     action is required.

[[Page 69634]]


    (ii) A new vented front lift
     strut, P/N A-A815, a new
     vented aft lift strut, P/N
     A-A854, or FAA-approved
     equivalent P/Ns, that is
     treated with internal
     corrosion protection
     specified in Taylorcraft
     Aviation, LLC Service
     Bulletin No. 2007-001,
     Revision B, dated October
     15, 2007. Installing one of
     these lift struts is
     subject to the repetitive
     inspections required in
     paragraph (e)(4) of this AD.
(3) If corrosion is found during  Before further      Follow Part 2 of
 the inspection required in        flight after the    the Instructions
 paragraph (e)(1) of this AD, do   visual inspection   in Taylorcraft
 an ultrasound or radiograph       required in         Aviation, LLC
 inspection to determine if the    paragraph (e)(1)    Service Bulletin
 corrosion exceeds the             of this AD.         No. 2007-001,
 Acceptance/Rejection Criteria                         Revision B, dated
 specified in Taylorcraft                              October 15, 2007.
 Aviation, LLC Service Bulletin                        All ultrasound or
 No. 2007-001, Revision B, dated                       radiograph
 October 15, 2007.                                     inspections
                                                       required by this
                                                       AD must be done
                                                       by one of the
                                                       following:
                                                      (i) A Level II or
                                                       III inspector
                                                       certified in the
                                                       applicable
                                                       ultrasound or
                                                       radiograph
                                                       inspection method
                                                       using the
                                                       guidelines
                                                       established by
                                                       the American
                                                       Society of
                                                       Nondestructive
                                                       Testing or NAS
                                                       410 (formerly MIL-
                                                       STD-410);
                                                      (ii) An inspector
                                                       certified to
                                                       specific FAA or
                                                       other acceptable
                                                       government or
                                                       industry
                                                       standards, such
                                                       as Air Transport
                                                       Association (ATA)
                                                       Specifications
                                                       105-Guidelines
                                                       for Training and
                                                       Qualifying
                                                       Personnel in
                                                       Nondestructive
                                                       Testing Methods;
                                                       or
                                                      (iii) An FAA
                                                       Repair Station or
                                                       a Testing/
                                                       Inspection
                                                       Laboratory
                                                       qualified to do
                                                       ultrasound or
                                                       radiograph
                                                       inspections.
(4) If no corrosion or cracks     (i) Initially       Follow Part 2 of
 are found during the visual       inspect within      the Instructions
 inspection required in            the next 3 months   in Taylorcraft
 paragraph (e)(1) of this AD, or   after August 20,    Aviation, LLC
 if the inspection required in     2007 (the           Service Bulletin
 paragraph (e)(3) reveals that     effective date of   No. 2007-001,
 the corrosion does not exceed     AD 2007-16-14) or   Revision B, dated
 the Acceptance/Rejection          within 48 months    October 15, 2007,
 Criteria specified in             after installing    using the
 Taylorcraft Aviation, LLC         a lift strut        ultrasound or
 Service Bulletin No. 2007-001,    specified in        radiograph
 Revision B, dated October 15,     paragraph           inspection
 2007, repetitively inspect        (e)(2)(ii) of       method.
 thereafter using the ultrasound   this AD,
 or radiograph inspection method   whichever occurs
 and treat with internal           later.
 corrosion protection until all   (ii) Repetitively
 struts are replaced with the      inspect
 sealed struts specified in        thereafter at
 paragraph (e)(2)(i) of this AD.   intervals not to
 If any cracks are found or        exceed 48 months,
 corrosion is found that exceeds   except as
 the Acceptance/Rejection          required by
 Criteria specified in             paragraph
 Taylorcraft Aviation, LLC         (e)(4)(iii) of
 Service Bulletin No. 2007-001,    this AD.
 Revision B, dated October 15,    (iii) If the
 2007, during any of the           initial
 repetitive inspections required   inspection was
 by this AD, take the necessary    done using the
 corrective actions as             eddy current
 applicable in paragraph (e)(5)    method as
 of this AD.                       specified in AD
                                   2007-16-14, the
                                   first ultrasound
                                   or radiograph
                                   repetitive
                                   inspection must
                                   be done within
                                   the next 24
                                   months after
                                   doing the eddy
                                   current
                                   inspection.
                                   Repetitively
                                   inspect
                                   thereafter at
                                   intervals not to
                                   exceed 48 months
                                   using the
                                   ultrasound or
                                   radiograph
                                   inspection method.
(5) If, during any inspection     Before further      Following the
 required in paragraphs (e)(3)     flight after the    Instructions in
 or (e)(4) of this AD, any         inspection          Taylorcraft
 cracks are found or it is         required in         Aviation, LLC
 determined that the corrosion     paragraph (e)(3)    Service Bulletin
 exceeds the Acceptance/           or (e)(4) of this   No. 2007-001,
 Rejection Criteria specified in   AD.                 Revision B, dated
 Taylorcraft Aviation, LLC                             October 15, 2007.
 Service Bulletin No. 2007-001,
 Revision B, dated October 15,
 2007, replace the lift strut
 with the applicable lift strut
 specified in paragraph
 (e)(2)(i) or (e)(2)(ii) of this
 AD.
(6) Do not install P/N A-A815, P/ As of 5 hours TIS   Not applicable.
 N A-A854, or FAA-approved         after the
 equivalent P/N, unless:           effective date of
                                   this AD.
    (i) within the last 48
     months it has been
     inspected using the
     ultrasound or radiograph
     method;
    (ii) meets the Acceptance/
     Rejection Criteria; and
    (iii) is treated with
     internal corrosion
     protection as specified in
     Taylorcraft Aviation, LLC
     Service Bulletin No. 2007-
     001, Revision B, dated
     October 15, 2007.

[[Page 69635]]


(7) As a terminating action for   At any time after   Not applicable.
 the repetitive inspections        the effective
 required by this AD, all vented   date of this AD.
 lift struts (P/Ns A-A815, A-
 A854, and FAA-approved
 equivalent P/Ns) may be
 replaced with sealed lift
 struts (P/Ns MA-A815, UA-A815
 (for Models BC12-D/D1 and BCS12-
 D/D1 only), MA-A854, UA-854
 (for Models BC12-D/D1 and BCS12-
 D/D1 only), or FAA-approved
 equivalent P/Ns).
------------------------------------------------------------------------

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: 
Andrew McAnaul, Aerospace Engineer, ASW-150 (c/o MIDO-43), 10100 
Reunion Place, Suite 650, 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.
    (g) AMOCs approved for AD 2007-16-14 are approved for this AD.

Related Information

    (h) 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 December 3, 2007.
John R. Colomy,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E7-23860 Filed 12-7-07; 8:45 am]

BILLING CODE 4910-13-P
