Document ID: FAA-2007-0004-0028
Agency: faa
Document Type: Rule
Title: Airworthiness Directives; Taylorcraft A, B, and F Series Airplanes
Posted Date: 2007-08-13T04:00Z

[Federal Register: August 13, 2007 (Volume 72, Number 155)]
[Rules and Regulations]               
[Page 45153-45156]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr13au07-4]                         

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-28478; Directorate Identifier 2007-CE-057-AD; 
Amendment 39-15153; AD 2007-16-14]
RIN 2120-AA64

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

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for all 
Taylorcraft A, B, and F series airplanes. This AD requires you to 
initially inspect the left and right wing front and aft lift struts for 
corrosion and cracks, replace any cracked strut or strut with corrosion 
that exceeds certain limits with either sealed or non-sealed struts, 
and repetitively inspect any non-sealed struts. This AD results from 
inspections

[[Page 45154]]

where several different struts were found with moderate to severe 
corrosion and required strut replacement. We are issuing this AD to 
detect and correct corrosion or cracks 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 
with consequent loss of control.

DATES: This AD becomes effective on August 20, 2007.
    On August 20, 2007, the Director of the Federal Register approved 
the incorporation by reference of certain publications listed in this 
AD.
    We must receive any comments on this AD by October 12, 2007.

ADDRESSES: Use one of the following addresses to comment on this AD.
     DOT Docket Web site: Go to http://dms.dot.gov and follow 

the instructions for sending your comments electronically.
     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.
     Fax: (202) 493-2251.
     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.
     Federal eRulemaking Portal: Go to http://www.regulations.gov.
 Follow the instructions for submitting comments.

    To get the service information identified in this AD, contact 
Taylorcraft Aviation, LLC, 2124 North Central Avenue, Brownsville, 
Texas 78521; telephone: (956) 986-0700.
    To view the comments to this AD, go to http://dms.dot.gov. The 

docket number is FAA-2007-28478; Directorate Identifier 2007-CE-057-AD.

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:

Discussion

    The FAA has received reports of several corroded wing lift struts 
from different Taylorcraft series airplanes. Independent laboratory 
analysis of the struts revealed varying degrees of excessive internal 
and external corrosion, including through-the-thickness corrosion. The 
struts exhibited corrosion severe enough to require strut replacement. 
Additional Taylorcraft owners reported finding severe corrosion on wing 
struts during routine maintenance, which required strut replacement. 
These same findings confirm strut corrosion Taylorcraft reported to the 
FAA. The internal cavity of the original design (vented) lift struts is 
exposed to the external environment and can hide internal surface 
corrosion resulting from environmental exposure. External surface 
corrosion can be masked by the external paint coating.
    This condition, if not corrected, could result in failure of a wing 
lift strut due to corrosion and lead to separation of the wing from the 
airplane with consequent loss of control.

Relevant Service Information

    We reviewed Taylorcraft Aviation, LLC Service Bulletin (SB) No. 
2007-001, Revision A, dated August 1, 2007. The service information 
describes procedures for wing lift strut assembly corrosion inspection 
and/or replacement.

FAA's Determination and Requirements of This AD

    We are issuing this AD because we evaluated all the information and 
determined the unsafe condition described previously is likely to exist 
or develop on other products of the same type design. This AD requires 
you to initially inspect the left and right wing front and aft lift 
struts for corrosion and cracks, replace any cracked strut or strut 
with corrosion that exceeds certain limits with either sealed or non-
sealed struts, and repetitively inspect any non-sealed struts.
    The FAA is determining whether future rulemaking action is 
necessary. This could include inspection and/or modification or 
replacement in adjacent structure.
    In preparing this rule, we contacted type clubs and aircraft 
operators to get technical information and information on operational 
and economic impacts. We have included a discussion of information that 
may have influenced this action in the rulemaking docket.

FAA's Determination of the Effective Date

    An unsafe condition exists that requires the immediate adoption of 
this AD. The FAA has found that the risk to the flying public justifies 
waiving notice and comment prior to adoption of this rule because 
corrosion and/or cracks in the wing lift struts could result in 
separation of the wing from the airplane with consequent loss of 
control. Therefore, we determined that notice and opportunity for 
public comment before issuing this AD are impracticable and that good 
cause exists for making this amendment effective in fewer than 30 days.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not precede it by notice and an opportunity for 
public comment. We invite you to send any written relevant data, views, 
or arguments regarding this AD. Send your comments to an address listed 
under the ADDRESSES section. Include the docket number ``FAA-2007-
28478; Directorate Identifier 2007-CE-057-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the AD. We will consider 
all comments received by the closing date and may amend the AD in light 
of those comments.
    We will post all comments we receive, without change, to http://dms.dot.gov
, including any personal information you provide. We will 

also post a report summarizing each substantive verbal contact we 
receive concerning this 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 determined that this AD will not have federalism implications 
under Executive Order 13132. This AD will 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 this AD:

[[Page 45155]]

    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866;
    (2) Is not a ``significant rule'' under 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 AD and placed it in the AD docket.

Examining the AD Docket

    You may examine the AD docket that contains the AD, the regulatory 
evaluation, any comments received, and other information on the 
Internet at http://dms.dot.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, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends 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):

2007-16-14 Taylorcraft: Amendment 39-15153; Docket No. FAA-2007-
28478; Directorate Identifier 2007-CE-057-AD.

Effective Date

    (a) This AD becomes effective on August 20, 2007.

Affected ADs

    (b) None.

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, BFS-65, (Army L-2K) 
BF 12-65, BL, BLS, (Army L-2F) BL-65, BLS-65, (Army L-2J) BL12-65, 
BLS12-65, FA-III (Airphibian), 19, F19, F21, F21A, F21B, F22, F22A, 
F22B, F22C, and TG-6 Conversion airplanes that:
    (1) Are certificated in any category; and
    (2) Do not incorporate in all struts new sealed front lift 
struts (P/N MA-A815 or FAA-approved equivalent P/N) and new sealed 
aft lift struts (P/N MA-A854 or FAA-approved equivalent P/N).

    Note: This AD applies to all Taylorcraft models listed above, 
including those not listed in Taylorcraft Aviation, LLC Service 
Bulletin No. 2007-001, Revision A, dated August 1, 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 inspections where several different 
struts were found with moderate to severe corrosion and required 
strut replacement. 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:

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               Actions                             Compliance                            Procedures
----------------------------------------------------------------------------------------------------------------
(1) Visual Inspection: Visually       Within the next 5 hours time-in-      Follow Part 1 of the Instructions in
 inspect for corrosion or cracking     service after August 20, 2007 (the    Taylorcraft Aviation, LLC Service
 in the lower 12 inches of the left    effective date of this AD), unless    Bulletin No. 2007-001, Revision A,
 and right wing front lift struts      the strut has:                        dated August 1, 2007.
 (part number (P/N) A-A815 or FAA-    (i) Been replaced with parts
 approved equivalent P/N) and aft      specified in either paragraph
 lift struts (P/N A-A854 or FAA-       (e)(4)(i); or
 approved equivalent P/N) and then    (ii) Been replaced with parts
 inspect per paragraph (e)(2) of       specified by paragraph (e)(4)(ii)
 this AD.                              of this AD and been installed on an
                                       airplane for less than 24 months.
(2) Initial Eddy Current or           Initially inspect any original        Follow Part 2 of the Instructions in
 Ultrasound Inspection: Inspect        design (vented) strut or FAA-         Taylorcraft Aviation, LLC Service
 using the eddy current or             approved equivalent part number at    Bulletin No. 2007-001, Revision A,
 ultrasound inspection methods to      whichever of the following that       dated August 1, 2007.
 detect corrosion or cracking in the   applies:
 lower 12 inches of the left and      (A) Before further flight when
 right wing front lift struts (P/N A-  corrosion or cracking is found
 A815 or FAA-approved equivalent P/    during the visual inspection
 N) and aft lift struts (P/N A-A854    required in paragraph (e)(1) of
 or FAA-approved equivalent P/N).      this AD; or
 The eddy current or ultrasound       (B) If no corrosion or cracking is
 inspection must be done by one of     found during the visual inspection
 the following:                        in paragraph (e)(1) of this AD,
(i) A Level II or III inspector        within the next 3 months after
 certified in the applicable eddy      August 20, 2007 (the effective date
 current or ultrasound inspection      of this AD) or within 24 months of
 method using the guidelines           installation of the strut,
 established by the American Society   whichever occurs later.
 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) A qualified FAA Repair Station
 or a qualified Testing/Inspection
 Laboratory.

[[Page 45156]]

(3) Repetitive Eddy Current or        (A) For original or replacement left  Follow Part 2 of the Instructions in
 Ultrasound Inspections: Inspect       and right wing front lift struts (P/  Taylorcraft Aviation, LLC Service
 using the eddy current or             N A-A815 or FAA-approved equivalent   Bulletin No. 2007-001, Revision A,
 ultrasound inspection methods to      P/N) and aft lift struts (P/N A-      dated August 1, 2007.
 detect corrosion or cracking in the   A854 or FAA-approved equivalent P/
 lower 12 inches of the left and       N) of original design (vented),
 right wing front lift struts (P/N A-  repetitively inspect at intervals
 A815 or FAA-approved equivalent P/    not to exceed 24 months after the
 N) and aft lift struts (P/N A-A854    initial inspection required in
 or FAA-approved equivalent P/N).      paragraph (e)(2) of this AD.
 The eddy current or ultrasound       (B) Replacement of all struts with
 inspection must be done by one of     new sealed front lift struts (P/N
 the following:                        MA-A815 or FAA-approved equivalent
(i) A Level II or III inspector        P/N) and new sealed aft lift struts
 certified in the applicable Eddy      (P/N MA-A854 or FAA-approved
 Current or Ultrasound Inspection      equivalent P/N) eliminates the
 method using the guidelines           repetitive inspection requirement
 established by the American Society   of this AD.
 of Nondestructive Testing or NAS     (C) If not all the vented lift
 410 (formerly MIL-STD-410),           struts are replaced with new sealed
(ii) An Inspector certified to         units, then the lift struts that
 specific FAA or other acceptable      are not new sealed units are still
 government or industry standards,     subject to the repetitive
 such as Air Transport Association     inspection requirement of this AD.
 (ATA) Specifications 105--
 Guidelines for Training and
 Qualifying Personnel in
 Nondestructive Testing Methods, or
(iii) A qualified FAA Repair Station
 or a qualified Testing/Inspection
 Laboratory.
(4) Replacement: Replace the          Replace before further flight any     Follow Taylorcraft Aviation, LLC
 original design (vented) front lift   time cracking or corrosion is found   Service Bulletin No. 2007-001,
 struts (P/N A-A815 or FAA-approved    during any required eddy current or   Revision A, dated August 1, 2007.
 equivalent P/N) and original design   ultrasound inspection that exceeds
 (vented) aft lift struts (P/N A-      the acceptance/rejection criteria
 A854 or FAA-approved equivalent P/    limits in Taylorcraft Aviation, LLC
 N) with one of the following:         Service Bulletin No. 2007-001,
(i) new sealed front lift struts, (P/  Revision A, dated August 1, 2007.
 N MA-A815 or FAA-approved             After replacing with an original
 equivalent P/N) and new sealed aft    design (vented) strut, begin the
 lift struts, (P/N MA-A854 or FAA-     repetitive inspections of paragraph
 approved equivalent P/N); or          (e)(3) within 24 months after
(ii) New original design (vented)      installation.
 front lift struts (P/N A-815 or FAA-
 approved equivalent P/N) and new
 original design (vented) aft lift
 struts (P/N A-A854 or FAA-approved
 equivalent P/N).
----------------------------------------------------------------------------------------------------------------

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.

Material Incorporated by Reference

    (g) You must use Taylorcraft Aviation, LLC Service Bulletin No. 
2007-001, Revision A, dated August 1, 2007, to do the actions 
required by this AD, unless the AD specifies otherwise.
    (1) The Director of the Federal Register approved the 
incorporation by reference of this service information under 5 
U.S.C. 552(a) and 1 CFR part 51.
    (2) For service information identified in this AD, contact 
Taylorcraft Aviation, LLC, 2124 North Central Avenue, Brownsville, 
Texas 78521; telephone: 956-986-0700.
    (3) You may review copies at the FAA, Central Region, Office of 
the Regional Counsel, 901 Locust, Kansas City, Missouri 64106; or at 
the National Archives and Records Administration (NARA). For 
information on the availability of this material at NARA, call 202-
741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html
.

    Issued in Kansas City, Missouri, on August 3, 2007.
David R. Showers,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E7-15581 Filed 8-10-07; 8:45 am]

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