Document ID: FAA-2007-0286-0025
Agency: faa
Document Type: Rule
Title: Airworthiness Directives; Taylorcraft A, B, and F Series Airplanes
Posted Date: 2008-02-22T05:00Z

[Federal Register: February 22, 2008 (Volume 73, Number 36)]
[Rules and Regulations]               
[Page 9655-9659]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr22fe08-1]                         

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[[Page 9655]]

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-0286; Directorate Identifier 2007-CE-086-AD; 
Amendment 39-15381; AD 2008-04-09]
RIN 2120-AA64

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

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

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) to 
supersede AD 2007-16-14, which applies to all Taylorcraft (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 AD retains 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 AD to detect and correct cracks and 
corrosion in the left and right 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: This AD becomes effective on March 28, 2008.
    On March 28, 2008, the Director of the Federal Register approved 
the incorporation by reference of Taylorcraft Aviation, LLC Service 
Bulletin No. 2007-001, Revision B, dated October 15, 2007, listed in 
this AD.
    As of August 20, 2007 (72 FR 45153, August 13, 2007), the Director 
of the Federal Register approved the incorporation by reference of 
Taylorcraft Aviation, LLC Service Bulletin No. 2007-001, Revision A, 
dated August 1, 2007, listed in this AD.

ADDRESSES: For service information identified 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. The docket number is FAA-2007-0286; 
Directorate Identifier 2007-CE-086-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

    On December 3, 2007, we issued a proposal to amend part 39 of the 
Federal Aviation Regulations (14 CFR part 39) to include an AD that 
would apply to certain Taylorcraft (Taylorcraft) A, B, and F series 
airplanes. This proposal was published in the Federal Register as a 
notice of proposed rulemaking (NPRM) on December 10, 2007 (72 FR 
69630). The NPRM proposed to supersede AD 2007-16-14 with a new AD that 
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 to remove Models FA-III 
and TG-6 airplanes; and
     Changes the compliance time between the repetitive 
inspections.

Comments

    We provided the public the opportunity to participate in developing 
this AD. The following presents the comments received on the proposal 
and FAA's response to each comment:

Comment Issue No. 1: Approve Installing Univair Part Numbers (P/N) UA-
A815 and UA-854 as a Terminating Action for the Repetitive Inspection 
Requirement for All Affected Taylorcraft Airplanes

    Univair Aircraft Corporation (Univair) requests that we expand the 
airplane model applicability for installation of P/Ns UA-A815 and UA-
854 as a terminating action for the repetitive inspection requirement 
from Taylorcraft Models BC12-D/D1 and BCS12-D/D1 airplanes (as 
currently approved in an alternative method of compliance (AMOC) to AD 
2007-16-14) to include all affected Taylorcraft airplanes.
    On January 2, 2008, Univair received parts manufacturer approval 
(PMA) under PMA Supplement Numbers 198 and 199 expanding the 
eligibility to install P/Ns UA-A815 and UA-854 on all Taylorcraft 
airplane models affected by the proposed AD. Installation of these 
sealed struts provides an acceptable level of safety for terminating 
action to the AD for all affected Taylorcraft airplane models.
    We agree with the commenter. We will change the final rule AD 
action to incorporate this change.

Comment Issue No. 2: Extend or Eliminate Repetitive Inspection 
Intervals

    Richard W. Gross and seven other commenters request that the 
repetitive inspection interval be either extended from 4 years to 10 
years or terminated altogether if no corrosion is found during the 
initial inspection.
    Some of the commenters base their request on service history of 
some struts having been in service for 60 years without any signs of 
corrosion.
    We do not agree with the commenters. We have not received any data 
to support extending the repetitive inspection interval. We have 
received reports of several corroded vented wing

[[Page 9656]]

lift struts from different Taylorcraft series airplanes. Repetitive 
inspections are necessary to detect and correct corrosion that can 
develop after the initial inspection. Based on the inspection methods 
used and the application of corrosion inhibitor at each inspection, 48 
months is the appropriate repetitive inspection interval.
    We are not changing the final rule AD action based on these 
comments.

Comment Issue No. 3: Remove F-Model Airplanes From the Applicability 
Section

    Shawn Coleman and three other commenters request that the newer F-
Model Taylorcraft airplanes be removed from the Applicability section. 
This request is based on these models being the most recent airplanes 
produced and the expectation that they should not have a corrosion 
problem.
    We do not agree with the commenters. We do not have any data to 
support excluding these airplane models from the AD. These models use 
the same strut design and material as the earlier produced Taylorcraft 
model airplanes. We have received reports of one Model F-21 airplane 
and three Model F-22 airplanes having one or more struts that failed 
inspection due to corrosion.
    We are not changing the final rule AD action based on these 
comments.

Conclusion

    We have carefully reviewed the available data and determined that 
air safety and the public interest require adopting the AD as proposed 
except for the changes previously discussed and minor editorial 
corrections. We have determined that these minor corrections:
     Are consistent with the intent that was proposed in the 
NPRM for correcting the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM.

Costs of Compliance

    We estimate that this AD will affect 3,119 airplanes in the U.S. 
registry.
    We estimate the following costs to do the 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 repetitive ultrasound or 
radiograph inspection:

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

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

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

Regulatory Findings

    We have 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:
    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 summary of the costs to comply with this AD (and 
other information as included in the Regulatory Evaluation) and placed 
it in the AD Docket. You may get a copy of this summary by sending a 
request to us at the address listed under ADDRESSES. Include ``Docket 
No. FAA-2007-0286; Directorate Identifier 2007-CE-086-AD'' in your 
request.

[[Page 9657]]

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 Federal Aviation Administration amends part 39 of the Federal 
Aviation Regulations (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 removing Airworthiness Directive (AD) 
2007-16-14, Amendment 39-15153 (72 FR 45153, August 13, 2007), and 
adding the following new AD:

2008-04-09 Taylorcraft: Amendment 39-15381; Docket No. FAA-2007-
0286; Directorate Identifier 2007-CE-086-AD.

Effective Date

    (a) This AD becomes effective on March 28, 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, or FAA-approved 
equivalent P/N, and sealed aft lift struts, P/N MA-A854, Univair P/N 
UA-854, 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 
left and right 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 left and     Within the next 5 hours TIS after     Follow Part 1 of the Instructions in
 right wing front and aft lift         August 20, 2007 (the effective date   Taylorcraft Aviation, LLC Service
 struts, (P/N A-A815 and P/N A-A854,   of AD 2007-16-14), unless one of      Bulletin No. 2007-001, Revision A,
 or FAA-approved equivalent P/Ns),     the following conditions is met:      dated August 1, 2007; or
 along the entire bottom 12 inches    (i) The struts have been replaced      Taylorcraft Aviation, LLC Service
 of each strut for cracks and          with parts specified in paragraph     Bulletin No. 2007-001, Revision B,
 corrosion.                            (e)(2)(i) of this AD. No further      dated October 15, 2007.
                                       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 during    Before further flight after the       Following the Instructions in
 the visual inspection required in     visual inspection required in         Taylorcraft Aviation, LLC Service
 paragraph (e)(1) of this AD,          paragraph (e)(1) of this AD.          Bulletin No. 2007-001, Revision B,
 replace the cracked strut with the                                          dated October 15, 2007.
 following applicable strut:
(i) A sealed front lift strut, P/N
 MA-A815, Univair P/N UA-A815, or
 FAA-approved equivalent P/N, a
 sealed aft lift strut, P/N MA-A854,
 Univair P/N UA-854, 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.
    (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.

[[Page 9658]]

(3) If corrosion is found during the  Before further flight after the       Follow Part 2 of the Instructions in
 inspection required in paragraph      visual inspection required in         Taylorcraft Aviation, LLC Service
 (e)(1) of this AD, do an ultrasound   paragraph (e)(1) of this AD.          Bulletin No. 2007-001, Revision B,
 or radiograph inspection to                                                 dated October 15, 2007. All
 determine if the corrosion exceeds                                          ultrasound or radiograph
 the Acceptance/Rejection Criteria                                           inspections required by this AD
 specified in Taylorcraft Aviation,                                          must be done by one of the
 LLC Service Bulletin No. 2007-001,                                          following:
 Revision B, dated October 15, 2007.                                        (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 are     (i) Initially inspect within the      Follow Part 2 of the Instructions in
 found during the visual inspection    next 3 months after August 20, 2007   Taylorcraft Aviation, LLC Service
 required in paragraph (e)(1) of       (the effective date of AD 2007-16-    Bulletin No. 2007-001, Revision B,
 this AD, or if the inspection         14) or within 48 months after         dated October 15, 2007, using the
 required in paragraph (e)(3)          installing a lift strut specified     ultrasound or radiograph inspection
 reveals that the corrosion does not   in paragraph (e)(2)(ii) of this AD,   method.
 exceed the Acceptance/Rejection       whichever occurs later.
 Criteria specified in Taylorcraft    (ii) Repetitively inspect thereafter
 Aviation, LLC Service Bulletin No.    at intervals not to exceed 48
 2007-001, Revision B, dated October   months, except as required by
 15, 2007, repetitively inspect        paragraph (e)(4)(iii) of this AD.
 thereafter using the ultrasound or   (iii) If the initial inspection was
 radiograph inspection method and      done using the eddy current method
 treat with internal corrosion         as specified in AD 2007-16-14, the
 protection until all struts are       first ultrasound or radiograph
 replaced with the sealed struts       repetitive inspection must be done
 specified in paragraph (e)(2)(i) of   within the next 24 months after
 this AD. If any cracks are found or   doing the eddy current inspection.
 corrosion is found that exceeds the   Repetitively inspect thereafter at
 Acceptance/Rejection Criteria         intervals not to exceed 48 months
 specified in Taylorcraft Aviation,    using the ultrasound or radiograph
 LLC Service Bulletin No. 2007-001,    inspection method.
 Revision B, dated October 15, 2007,
 during any of the repetitive
 inspections required by this AD,
 take the necessary corrective
 actions as applicable in paragraph
 (e)(5) of this AD.
(5) If, during any inspection         Before further flight after the       Following the Instructions in
 required in paragraphs (e)(3) or      inspection required in paragraph      Taylorcraft Aviation, LLC Service
 (e)(4) of this AD, any cracks are     (e)(3) or (e)(4) of this AD.          Bulletin No. 2007-001, Revision B,
 found or it is determined that the                                          dated October 15, 2007.
 corrosion exceeds the Acceptance/
 Rejection Criteria specified in
 Taylorcraft Aviation, LLC 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/N A- As of 5 hours TIS after March 28,     Not applicable.
 A854, or FAA-approved equivalent P/   2008 the effective date of this AD.
 N, unless:
(i) Within the last 48 months it has
 been inspected using the ultrasound
 or radiograph method;
    (ii) It meets the Acceptance/
     Rejection Criteria; and
    (iii) It is treated with
     internal corrosion protection
     as specified in Taylorcraft
     Aviation, LLC Service Bulletin
     No. 2007-001, Revision B, dated
     October 15, 2007.
(7) As a terminating action for the   At any time after March 28, 2008 the  Not applicable.
 repetitive inspections required by    effective date of this AD.
 this AD, all vented 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, MA-A854, UA-854, or
 FAA-approved equivalent P/Ns).
----------------------------------------------------------------------------------------------------------------

[[Page 9659]]

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.

Material Incorporated by Reference

    (h) You must use Taylorcraft Aviation, LLC Service Bulletin No. 
2007-001, Revision A, dated August 1, 2007; and Taylorcraft 
Aviation, LLC Service Bulletin No. 2007-001, Revision B, dated 
October 15, 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 Taylorcraft Aviation, LLC Service 
Bulletin No. 2007-001, Revision B, dated October 15, 2007, under 5 
U.S.C. 552(a) and 1 CFR part 51.
    (2) On August 20, 2007 (72 FR 45153, August 13, 2007), the 
Director of the Federal Register approved the incorporation by 
reference of Taylorcraft Aviation, LLC Service Bulletin No. 2007-
001, Revision A, dated August 1, 2007.
    (3) For service information identified in this AD, contact 
Taylorcraft Aviation, LLC, 2124 North Central Avenue, Brownsville, 
Texas 78521; telephone: 956-986-0700.
    (4) 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 February 13, 2008.
David R. Showers,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E8-3074 Filed 2-21-08; 8:45 am]

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