Airworthiness Directives; Taylorcraft A, B, and F Series Airplanes, 45153-45156 [E7-15581]
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Federal Register / Vol. 72, No. 155 / Monday, August 13, 2007 / Rules and Regulations
Regulatory Findings
Unsafe Condition
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 the 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 AD and placed it in the AD docket.
See the ADDRESSES section for a location
to examine the regulatory evaluation.
(d) This AD results from cracks found in
the aft tension tie channels at four station
locations, on a Model 747–200B series
airplane that had been modified to a special
freighter. We are issuing this AD to detect
and correct cracking of the aft tension tie
channels; failure of more than one tension tie
could result in rapid depressurization of the
airplane.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
I
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by adding the following new
airworthiness directive (AD):
I
2007–16–19 Boeing: Amendment 39–15158.
Docket No. FAA–2007–28940;
Directorate Identifier 2007–NM–131–AD.
Effective Date
(a) This AD becomes effective August 28,
2007.
jlentini on PROD1PC65 with RULES
Affected ADs
(b) None.
Applicability
(c) This AD applies to Boeing Model 747–
200B, 747–300, and 747–400 series airplanes,
certificated in any category; as identified in
Boeing Alert Service Bulletin 747–53A2610,
dated May 10, 2007.
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16:17 Aug 10, 2007
Jkt 211001
Repetitive Inspections
(f) At the applicable times specified in
paragraph 1.E. of Boeing Alert Service
Bulletin 747–53A2610, dated May 10, 2007,
except as provided by paragraph (g) of this
AD: Do repetitive detailed inspections for
cracking of the aft tension tie channels from
body station (BS) 1120 to BS 1220 and from
BS 880 to BS 1100, and do all applicable
corrective actions, by accomplishing all of
the applicable actions specified in the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–53A2610, dated May
10, 2007, except as provided by paragraph (h)
of this AD.
Exception to Compliance Times
(g) Where Boeing Alert Service Bulletin
747–53A2610, dated May 10, 2007, specifies
counting the compliance time from ‘‘* * *
after the date on this service bulletin,’’ this
AD requires counting the compliance time
from the effective date of this AD.
Exception for Bolt Hole Cracks
(h) If any crack is found in a bolt hole
during any inspection required by this AD,
and Boeing Alert Service Bulletin 747–
53A2610, dated May 10, 2007, specifies to
contact Boeing for appropriate action: Before
further flight, repair the crack using a method
approved in accordance with the procedures
specified in paragraph (j) of this AD.
PART 39—AIRWORTHINESS
DIRECTIVES
§ 39.13
Compliance
(e) You are responsible for having the
actions required by this AD performed within
the compliance times specified, unless the
actions have already been done.
Optional Terminating Action
(i) Except as provided by paragraph (h) of
this AD, accomplishing the applicable repairs
or modifications at all tension tie locations,
in accordance with Part 3 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–53A2610, dated May
10, 2007, terminates the repetitive
inspections required by paragraph (f) of this
AD.
Alternative Methods of Compliance
(AMOCs)
(j)(1) The Manager, Seattle Aircraft
Certification Office (ACO), FAA, has the
authority to approve AMOCs for this AD, if
requested in accordance with the procedures
found in 14 CFR 39.19.
(2) To request a different method of
compliance or a different compliance time
for this AD, follow the procedures in 14 CFR
39.19. 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
PO 00000
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Fmt 4700
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45153
Office (FSDO), or lacking a PI, your local
FSDO.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair
required by this AD, if it is approved by an
Authorized Representative for the Boeing
Commercial Airplanes Delegation Option
Authorization Organization who has been
authorized by the Manager, Seattle ACO, to
make those findings. For a repair method to
be approved, the repair must meet the
certification basis of the airplane, and the
approval must specifically refer to this AD.
Material Incorporated by Reference
(k) You must use Boeing Alert Service
Bulletin 747–53A2610, dated May 10, 2007,
to perform the actions that are required by
this AD, unless the AD specifies otherwise.
The Director of the Federal Register approved
the incorporation by reference of this
document in accordance with 5 U.S.C. 552(a)
and 1 CFR part 51. Contact Boeing
Commercial Airplanes, P.O. Box 3707,
Seattle, Washington 98124–2207, for a copy
of this service information. You may review
copies at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton,
Washington; 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: https://www.archives.gov/federal-register/
cfr/ibr-locations.html.
Issued in Renton, Washington, on August
2, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–15582 Filed 8–10–07; 8:45 am]
BILLING CODE 4910–13–P
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
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
AGENCY:
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
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45154
Federal Register / Vol. 72, No. 155 / Monday, August 13, 2007 / Rules and Regulations
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 inflight 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
https://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
https://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 https://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:
jlentini on PROD1PC65 with RULES
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-thethickness corrosion. The struts
exhibited corrosion severe enough to
require strut replacement. Additional
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16:17 Aug 10, 2007
Jkt 211001
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 nonsealed 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
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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 https://
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:
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Federal Register / Vol. 72, No. 155 / Monday, August 13, 2007 / Rules and Regulations
(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.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
I
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
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
https://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.
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
I
2007–16–14 Taylorcraft: Amendment 39–
15153; Docket No. FAA–2007–28478;
Directorate Identifier 2007–CE–057–AD.
45155
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 FAAapproved 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
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,
(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
Effective Date
(a) This AD becomes effective on August
20, 2007.
(e) To address this problem, you must do
the following, unless already done:
Compliance
Procedures
(1) Visual Inspection: Visually inspect for corrosion or cracking in the lower 12 inches of the
left and right wing front lift struts (part number (P/N) A–A815 or FAA-approved equivalent P/N) and aft lift struts (P/N A–A854 or
FAA-approved equivalent P/N) and then inspect per paragraph (e)(2) of this AD.
jlentini on PROD1PC65 with RULES
Actions
Within the next 5 hours time-in-service after
August 20, 2007 (the effective date of this
AD), unless the strut has:
(i) Been replaced with parts specified in
either paragraph (e)(4)(i); or
(ii) Been replaced with parts specified by
paragraph (e)(4)(ii) of this AD and been
installed on an airplane for less than 24
months.
Initially inspect any original design (vented)
strut or FAA-approved equivalent part number at whichever of the following that applies:
(A) Before further flight when corrosion or
cracking is found during the visual inspection required in paragraph (e)(1) of
this AD; or
(B) If no corrosion or cracking is found
during the visual inspection in paragraph (e)(1) of this AD, within the next
3 months after August 20, 2007 (the effective date of this AD) or within 24
months of installation of the strut,
whichever occurs later.
Follow Part 1 of the Instructions in Taylorcraft
Aviation, LLC Service Bulletin No. 2007–
001, Revision A, dated August 1, 2007.
(2) Initial Eddy Current or Ultrasound Inspection: Inspect using the eddy current or
ultrasound inspection methods to detect corrosion or cracking in the lower 12 inches of
the left and right wing front lift struts (P/N A–
A815 or FAA-approved equivalent P/N) and
aft lift struts (P/N A–A854 or FAA-approved
equivalent P/N). The eddy current or
ultrasound inspection must be done by one
of the following:
(i) A Level II or III inspector certified in the
applicable eddy current or ultrasound 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) A qualified FAA Repair Station or a
qualified Testing/Inspection Laboratory.
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16:17 Aug 10, 2007
Jkt 211001
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Follow Part 2 of the Instructions in Taylorcraft
Aviation, LLC Service Bulletin No. 2007–
001, Revision A, dated August 1, 2007.
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45156
Federal Register / Vol. 72, No. 155 / Monday, August 13, 2007 / Rules and Regulations
Actions
Compliance
Procedures
(3) Repetitive Eddy Current or Ultrasound Inspections: Inspect using the eddy current or
ultrasound inspection methods to detect corrosion or cracking in the lower 12 inches of
the left and right wing front lift struts (P/N A–
A815 or FAA-approved equivalent P/N) and
aft lift struts (P/N A–A854 or FAA-approved
equivalent P/N). The eddy current or
ultrasound inspection must be done by one
of the following:
(i) A Level II or III inspector certified in the
applicable Eddy Current or Ultrasound
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) A qualified FAA Repair Station or a
qualified Testing/Inspection Laboratory.
(4) Replacement: Replace the original design
(vented) front lift struts (P/N A–A815 or FAAapproved equivalent P/N) and original design
(vented) aft lift struts (P/N A–A854 or FAAapproved equivalent P/N) with one of the following:
(i) 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);
or
(ii) New original design (vented) 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).
(A) For original or replacement left and right
wing front lift struts (P/N A–A815 or FAAapproved equivalent P/N) and aft lift struts
(P/N A–A854 or FAA-approved equivalent
P/N) of original design (vented), repetitively
inspect at intervals not to exceed 24
months after the initial inspection required
in paragraph (e)(2) of this AD.
(B) Replacement of all struts with 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) eliminates the repetitive inspection requirement of this AD.
(C) If not all the vented lift struts are replaced
with new sealed units, then the lift struts
that are not new sealed units are still subject to the repetitive inspection requirement
of this AD.
Follow Part 2 of the Instructions in Taylorcraft
Aviation, LLC Service Bulletin No. 2007–
001, Revision A, dated August 1, 2007.
Replace before further flight any time cracking
or corrosion is found during any required
eddy current or ultrasound inspection that
exceeds the acceptance/rejection criteria
limits in Taylorcraft Aviation, LLC Service
Bulletin No. 2007–001, Revision A, dated
August 1, 2007. After replacing with an
original design (vented) strut, begin the repetitive inspections of paragraph (e)(3) within 24 months after installation.
Follow Taylorcraft Aviation, LLC Service Bulletin No. 2007–001, Revision A, dated August 1, 2007.
jlentini on PROD1PC65 with RULES
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.
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16:17 Aug 10, 2007
Jkt 211001
(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: https://www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html.
DEPARTMENT OF TRANSPORTATION
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]
Amendment to Restricted Areas
R–3702A and R–3702B; Fort Campbell,
KY
BILLING CODE 4910–13–P
PO 00000
Federal Aviation Administration
14 CFR Part 73
[Docket No. FAA–2007–27850; Airspace
Docket No. 07–ASO–5]
RIN 2120–AA66
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
SUMMARY: This action amends the
designated altitudes of restricted areas
R–3702A and R–3702B, Fort Campbell,
KY, to revise the internal altitude
boundary separating the two restricted
areas. This change is necessary to better
accommodate training requirements and
provide greater access to the airspace for
nonparticipating aircraft flying through
the area above 10,000 feet MSL.
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]]>Agencies
[Federal Register Volume 72, Number 155 (Monday, August 13, 2007)]
[Rules and Regulations]
[Pages 45153-45156]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-15581]
-----------------------------------------------------------------------
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.
-----------------------------------------------------------------------
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 https://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 https://
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 https://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 https://
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 https://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:
----------------------------------------------------------------------------------------------------------------
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: https://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]
BILLING CODE 4910-13-P
