Airworthiness Directives; Twin Commander Aircraft Corporation Models 690, 690A, and 690B Airplanes, 40385-40387 [06-6225]
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40385
Rules and Regulations
Federal Register
Vol. 71, No. 136
Monday, July 17, 2006
This section of the FEDERAL REGISTER
contains regulatory documents having general
applicability and legal effect, most of which
are keyed to and codified in the Code of
Federal Regulations, which is published under
50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by
the Superintendent of Documents. Prices of
new books are listed in the first FEDERAL
REGISTER issue of each week.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–23785; Directorate
Identifier 2006–CE–10–AD; Amendment 39–
14681; AD 2006–15–01]
RIN 2120–AA64
Airworthiness Directives; Twin
Commander Aircraft Corporation
Models 690, 690A, and 690B Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: We are adopting a new
airworthiness directive (AD) for all
Twin Commander Aircraft Corporation
(Twin Commander) Models 690, 690A,
and 690B airplanes. This AD requires
you to inspect, visually and using
fluorescent dye penetrant, the support
structures for the inboard and center
aileron hinge fittings on both wings for
cracks and replace any cracked support
structure. This AD requires you to
reinforce the support structures for the
inboard and center aileron hinge fittings
on both wings. This AD results from
reports that cracks were found in the
support structures for the inboard and
center aileron hinge fittings on both
wings. We are issuing this AD to detect
and correct cracks in the support
structures for the inboard and center
aileron hinge fittings on both wings,
which could result in aileron failure.
This failure could lead to reduced
controllability or loss of control of the
airplane.
DATES: This AD becomes effective on
August 21, 2006.
As of August 21, 2006, the Director of
the Federal Register approved the
incorporation by reference of certain
publications listed in the regulation.
ADDRESSES: For service information
identified in this AD, contact Twin
Commander Aircraft LLC, 19010 59th
Drive Northeast, Arlington, Washington
98223, telephone: (360) 435–9797;
facsimile: (360) 435–1112.
To view the AD docket, go to the
Docket Management Facility, U.S.
Department of Transportation, 400
Seventh Street, SW., Nassif Building,
Room PL–401, Washington, DC 20590–
001 or on the Internet at https://
dms.dot.gov. The docket number is
FAA–2006–23785; Directorate Identifier
2006–CE–10–AD.
FOR FURTHER INFORMATION CONTACT:
Vince Massey, Aerospace Engineer,
FAA, Seattle Aircraft Certification
Office, 1601 Lind Avenue, SW., Renton,
WA 98057; telephone: (425) 917–6475;
facsimile: (425) 917–6590.
SUPPLEMENTARY INFORMATION:
Discussion
On March 10, 2006, 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 all
Twin Commander Models 690, 690A,
and 690B, airplanes. This proposal was
published in the Federal Register as a
notice of proposed rulemaking (NPRM)
on March 16, 2006 (71 FR 13558). The
NPRM proposed to require you to
inspect, visually and using fluorescent
dye penetrant, the support structures for
the inboard and center aileron hinge
fittings on both wings for cracks and
replace any cracked support structure.
The NPRM proposed to require you to
reinforce the support structures for the
inboard and center aileron hinge fittings
on both wings.
Comments
We provided the public the
opportunity to participate in developing
this AD. We received no comments on
the proposal or on the determination of
the cost to the public.
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
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 affects 275
airplanes in the U.S. registry.
We estimate the following costs to do
the inspection of the support structures
of the inboard aileron hinge fittings on
both wings:
Labor cost
Parts cost
10 work-hours × $80 an hour = $800 ............................................
Not applicable ............................
We estimate the following costs to do
the inspection of the support structure
$800
Parts cost
12 work-hours × $80 an hour = $960 ............................................
Total cost for
each airplane
Not applicable ............................
VerDate Aug<31>2005
15:22 Jul 14, 2006
Jkt 208001
Total cost on U.S.
operators
$800 × 275 = $220,000
of the center aileron hinge fittings on
both wings:
Labor cost
rmajette on PROD1PC67 with RULES
Total cost for
each airplane
PO 00000
Frm 00001
Fmt 4700
Sfmt 4700
E:\FR\FM\17JYR1.SGM
$960
17JYR1
Total cost on U.S.
operators
$960 × 275 = $264,000
40386
Federal Register / Vol. 71, No. 136 / Monday, July 17, 2006 / Rules and Regulations
We estimate the following costs to do
the reinforcement to the support
structures on the inboard aileron hinge
fittings on both wings:
Labor cost
Parts cost
25 work-hours × $80 an hour = $2,000 ...............................
We estimate the following costs to do
the reinforcement of the support
Total cost for each airplane
$1,526
$2,000 + $1,526 = $3,526 ..........
Parts cost
50 work-hours × $80 an hour = $4,000 ...............................
Total cost for each airplane
$551
Total cost on U.S. operators
$4,000 + $551 = $4,551 .............
fittings on both wings that may be
required based on the results of the
inspection. We have no way of
Parts cost
62 work-hours × $80 an hour = $4,960 ..................................................................................................
both wings that may be required based
on the results of the inspection. We
have no way of determining the number
Labor cost
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 requirement.’’ 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.
rmajette on PROD1PC67 with RULES
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.
VerDate Aug<31>2005
15:22 Jul 14, 2006
Jkt 208001
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 Federal Aviation Administration
amends part 39 of the Federal Aviation
Regulations (14 CFR part 39) as follows:
I
PO 00000
$2,320
Parts cost
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–2006–23785;
Directorate Identifier 2006–CE–10–AD’’
in your request.
Frm 00002
Fmt 4700
Sfmt 4700
Total cost for each airplane
$4,960 + $2,320 = $7,280
of airplanes that may need this
replacement.
176 work-hours × $80 an hour = $14,080 .....................................................................................
Authority for This Rulemaking
$4,551 × 275 = $1,251,525
determining the numb er of airplanes
that may need this replacement:
Labor cost
We estimate the following costs to do
any replacements of support structure
for the center aileron hinge fittings on
$3,526 × 275 = $969,650
structure of the center aileron hinge
fittings on both wings:
Labor cost
We estimate the following costs to do
any replacements of the support
structures for the inboard aileron hinge
Total cost on U.S. operators
$3,330
Total cost for each airplane
$14,080 + $3,330 = $17,410
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
[Amended]
2. FAA amends § 3913 by adding the
following new AD:
I
2006–15–01 Twin Commander Aircraft
Corporation: Amendment 39–14681;
Docket No. FAA–2006–23785;
Directorate Identifier 2006–CE–10–AD.
Effective Date
(a) This AD becomes effective on August
21, 2006.
Affected ADs
(b) None.
Applicability
(c) This AD affects Models 690, 690A, and
690B airplanes, all serial numbers, that are
certificated in any category.
Unsafe Condition
(d) This AD results from reports of cracks
found in the support structures for the
inboard and center aileron hinge fittings on
both wings. The actions specified in this AD
are intended to detect and correct cracks in
the support structures for the inboard and
center aileron hinge fittings on both wings,
which could result in aileron failure. This
failure could lead to reduced controllability
or loss of control of the airplane.
E:\FR\FM\17JYR1.SGM
17JYR1
Federal Register / Vol. 71, No. 136 / Monday, July 17, 2006 / Rules and Regulations
40387
Compliance
(e) To address this problem, you must do
the following:
Actions
Compliance
Procedures
(1) Inspect, visually and using fluorescent dye
penetrant, the support structures for the inboard and center aileron hinge fittings on
both wings for cracks.
(2) If you do not find cracks during the inspection required in paragraph (e)(1) of this AD,
reinforce the support structures for the inboard and center aileron hinge fittings on
both wings that are crack free.
(3) If you find cracks during the inspection required in paragraph (e)(1) of this AD, replace
and reinforce the cracked support structure.
Within the next 150 hours time-in-service or
12 months after August 21, 2006 (the effective date of this AD), whichever occurs first.
Before further flight after the inspection required in paragraph (e)(1) of this AD. After
doing the reinforcement, no further action is
required.
Follow Twin Commander Aircraft LLC Alert
Service Bulletin 236A and Alert Service Bulletin 238, both dated December 21, 2004,
as applicable.
Follow Twin Commander Aircraft LLC Alert
Service Bulletin 236A and Alert Service Bulletin 238, both dated December 21, 2004,
as applicable.
Before further flight after the inspection required in paragraph (e)(1) of this AD. After
doing the replacement and reinforcement,
no further action is required.
Follow Twin Commander Aircraft LLC Alert
Service Bulletin 236A and Alert Service Bulletin 238, both dated December 21, 2004,
as applicable.
Alternative Methods of Compliance
(AMOCs)
DEPARTMENT OF TRANSPORTATION
(f) The Manager, Seattle Aircraft
Certification Office (ACO), FAA, ATTN:
Vince Massey, Aerospace Engineer, Seattle,
ACO, 1601 Lind Avenue SW., Renton, WA
98057; telephone: (425) 917–6475; facsimile:
(425) 917–6590, has the authority to approve
AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19.
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–24522; Directorate
Identifier 2006–NM–002–AD; Amendment
39–14680; AD 2006–14–09]
RIN 2120–AA64
Material Incorporated by Reference
rmajette on PROD1PC67 with RULES
(g) You must do the actions required by
this AD following Twin Commander Aircraft
LLC Alert Service Bulletin 236A and Twin
Commander Aircraft LLC Alert Service
Bulletin 238, both dated December 21, 2004.
The Director of the Federal Register approved
the incorporation by reference of these
service bulletins in accordance with 5 U.S.C.
552(a) and 1 CFR part 51. To get a copy of
this service information, contact Twin
Commander Aircraft LLC, 19010 59th Drive
NE., Arlington, WA 98223, telephone: (360)
435–9797; facsimile: (360) 435–1112. To
review copies of this service information, go
to the National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, go
to: https://www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html or call (202) 741–6030. To
view the AD docket, go to the Docket
Management Facility; US Department of
Transportation, 400 Seventh Street, SW.,
Nassif Building, Room PL–401, Washington,
DC 20590–001 or on the Internet at https://
dms.dot.gov. The docket number is FAA–
2006–23785; Directorate Identifier 2006–CE–
10–AD.
Issued in Kansas City, Missouri, on July 7,
2006.
Kim Smith,
Manager, Small Airplane Directorate, Aircraft
Certification Service.
[FR Doc. 06–6225 Filed 7–14–06; 8:45 am]
BILLING CODE 4910–13–M
VerDate Aug<31>2005
15:22 Jul 14, 2006
Jkt 208001
Airworthiness Directives; Airbus Model
A330–200 and –300, and A340–200 and
–300 Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for certain
Airbus Model A330–200 and –300, and
A340–200 and –300 series airplanes.
This AD requires modifying certain
rotary actuator assemblies for the
leading edge slat. This AD results from
a leak found at the seal of the torque
limiter output shaft of the Type A rotary
actuator of leading edge slat No. 1. We
are issuing this AD to prevent a decrease
in the torque limiter function, which
could result in degradation and damage
to the attachment bolts of the leading
edge slat, loss of the slat, and
consequent reduced control of the
airplane.
This AD becomes effective
August 21, 2006.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of August 21, 2006.
ADDRESSES: You may examine the AD
docket on the Internet at https://
dms.dot.gov or in person at the Docket
Management Facility, U.S. Department
of Transportation, 400 Seventh Street,
DATES:
PO 00000
Frm 00003
Fmt 4700
Sfmt 4700
SW., Nassif Building, Room PL–401,
Washington, DC.
Contact Airbus, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France,
for the service information identified in
this AD.
Tim
Backman, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton,
Washington 98055–4056; telephone
(425) 227–2797; fax (425) 227–1149.
FOR FURTHER INFORMATION CONTACT:
SUPPLEMENTARY INFORMATION:
Examining the Docket
You may examine the airworthiness
directive (AD) docket on the Internet at
https://dms.dot.gov or in person at the
Docket Management Facility office
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The Docket Management Facility office
(telephone (800) 647–5227) is located on
the plaza level of the Nassif Building at
the street address stated in the
ADDRESSES section.
Discussion
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
apply to certain Airbus Model A330–
200 and –300, and A340–200 and –300
series airplanes. That NPRM was
published in the Federal Register on
April 21, 2006 (71 FR 20599). That
NPRM proposed to require modifying
certain rotary actuator assemblies for the
leading edge slat.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the single comment
received.
E:\FR\FM\17JYR1.SGM
17JYR1
]]>Agencies
[Federal Register Volume 71, Number 136 (Monday, July 17, 2006)]
[Rules and Regulations]
[Pages 40385-40387]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 06-6225]
========================================================================
Rules and Regulations
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains regulatory documents
having general applicability and legal effect, most of which are keyed
to and codified in the Code of Federal Regulations, which is published
under 50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by the Superintendent of Documents.
Prices of new books are listed in the first FEDERAL REGISTER issue of each
week.
========================================================================
Federal Register / Vol. 71, No. 136 / Monday, July 17, 2006 / Rules
and Regulations
[[Page 40385]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-23785; Directorate Identifier 2006-CE-10-AD;
Amendment 39-14681; AD 2006-15-01]
RIN 2120-AA64
Airworthiness Directives; Twin Commander Aircraft Corporation
Models 690, 690A, and 690B Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for all
Twin Commander Aircraft Corporation (Twin Commander) Models 690, 690A,
and 690B airplanes. This AD requires you to inspect, visually and using
fluorescent dye penetrant, the support structures for the inboard and
center aileron hinge fittings on both wings for cracks and replace any
cracked support structure. This AD requires you to reinforce the
support structures for the inboard and center aileron hinge fittings on
both wings. This AD results from reports that cracks were found in the
support structures for the inboard and center aileron hinge fittings on
both wings. We are issuing this AD to detect and correct cracks in the
support structures for the inboard and center aileron hinge fittings on
both wings, which could result in aileron failure. This failure could
lead to reduced controllability or loss of control of the airplane.
DATES: This AD becomes effective on August 21, 2006.
As of August 21, 2006, the Director of the Federal Register
approved the incorporation by reference of certain publications listed
in the regulation.
ADDRESSES: For service information identified in this AD, contact Twin
Commander Aircraft LLC, 19010 59th Drive Northeast, Arlington,
Washington 98223, telephone: (360) 435-9797; facsimile: (360) 435-1112.
To view the AD docket, go to the Docket Management Facility, U.S.
Department of Transportation, 400 Seventh Street, SW., Nassif Building,
Room PL-401, Washington, DC 20590-001 or on the Internet at https://
dms.dot.gov. The docket number is FAA-2006-23785; Directorate
Identifier 2006-CE-10-AD.
FOR FURTHER INFORMATION CONTACT: Vince Massey, Aerospace Engineer, FAA,
Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton,
WA 98057; telephone: (425) 917-6475; facsimile: (425) 917-6590.
SUPPLEMENTARY INFORMATION:
Discussion
On March 10, 2006, 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 all Twin Commander Models 690, 690A, and 690B,
airplanes. This proposal was published in the Federal Register as a
notice of proposed rulemaking (NPRM) on March 16, 2006 (71 FR 13558).
The NPRM proposed to require you to inspect, visually and using
fluorescent dye penetrant, the support structures for the inboard and
center aileron hinge fittings on both wings for cracks and replace any
cracked support structure. The NPRM proposed to require you to
reinforce the support structures for the inboard and center aileron
hinge fittings on both wings.
Comments
We provided the public the opportunity to participate in developing
this AD. We received no comments on the proposal or on the
determination of the cost to the public.
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 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 affects 275 airplanes in the U.S.
registry.
We estimate the following costs to do the inspection of the support
structures of the inboard aileron hinge fittings on both wings:
----------------------------------------------------------------------------------------------------------------
Total cost for
Labor cost Parts cost each airplane Total cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
10 work-hours x $80 an hour = $800. Not applicable....... $800 $800 x 275 = $220,000
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do the inspection of the support
structure of the center aileron hinge fittings on both wings:
----------------------------------------------------------------------------------------------------------------
Total cost for
Labor cost Parts cost each airplane Total cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
12 work-hours x $80 an hour = $960. Not applicable....... $960 $960 x 275 = $264,000
----------------------------------------------------------------------------------------------------------------
[[Page 40386]]
We estimate the following costs to do the reinforcement to the
support structures on the inboard aileron hinge fittings on both wings:
--------------------------------------------------------------------------------------------------------------------------------------------------------
Labor cost Parts cost Total cost for each airplane Total cost on U.S. operators
--------------------------------------------------------------------------------------------------------------------------------------------------------
25 work-hours x $80 an hour = $2,000. $1,526 $2,000 + $1,526 = $3,526......................... $3,526 x 275 = $969,650
--------------------------------------------------------------------------------------------------------------------------------------------------------
We estimate the following costs to do the reinforcement of the
support structure of the center aileron hinge fittings on both wings:
--------------------------------------------------------------------------------------------------------------------------------------------------------
Labor cost Parts cost Total cost for each airplane Total cost on U.S. operators
--------------------------------------------------------------------------------------------------------------------------------------------------------
50 work-hours x $80 an hour = $4,000. $551 $4,000 + $551 = $4,551........................... $4,551 x 275 = $1,251,525
--------------------------------------------------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any replacements of the
support structures for the inboard aileron hinge fittings on both wings
that may be required based on the results of the inspection. We have no
way of determining the numb er of airplanes that may need this
replacement:
----------------------------------------------------------------------------------------------------------------
Labor cost Parts cost Total cost for each airplane
----------------------------------------------------------------------------------------------------------------
62 work-hours x $80 an hour = $4,960.......... $2,320 $4,960 + $2,320 = $7,280
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any replacements of support
structure for the center aileron hinge fittings on both wings that may
be required based on the results of the inspection. We have no way of
determining the number of airplanes that may need this replacement.
----------------------------------------------------------------------------------------------------------------
Labor cost Parts cost Total cost for each airplane
----------------------------------------------------------------------------------------------------------------
176 work-hours x $80 an hour = $14,080..... $3,330 $14,080 + $3,330 = $17,410
----------------------------------------------------------------------------------------------------------------
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
requirement.'' 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-2006-23785; Directorate Identifier 2006-CE-10-AD'' in your
request.
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. FAA amends Sec. 3913 by adding the following new AD:
2006-15-01 Twin Commander Aircraft Corporation: Amendment 39-14681;
Docket No. FAA-2006-23785; Directorate Identifier 2006-CE-10-AD.
Effective Date
(a) This AD becomes effective on August 21, 2006.
Affected ADs
(b) None.
Applicability
(c) This AD affects Models 690, 690A, and 690B airplanes, all
serial numbers, that are certificated in any category.
Unsafe Condition
(d) This AD results from reports of cracks found in the support
structures for the inboard and center aileron hinge fittings on both
wings. The actions specified in this AD are intended to detect and
correct cracks in the support structures for the inboard and center
aileron hinge fittings on both wings, which could result in aileron
failure. This failure could lead to reduced controllability or loss
of control of the airplane.
[[Page 40387]]
Compliance
(e) To address this problem, you must do the following:
------------------------------------------------------------------------
Actions Compliance Procedures
------------------------------------------------------------------------
(1) Inspect, visually and Within the next 150 Follow Twin
using fluorescent dye hours time-in- Commander Aircraft
penetrant, the support service or 12 LLC Alert Service
structures for the inboard months after August Bulletin 236A and
and center aileron hinge 21, 2006 (the Alert Service
fittings on both wings for effective date of Bulletin 238, both
cracks. this AD), whichever dated December 21,
occurs first. 2004, as
applicable.
(2) If you do not find Before further Follow Twin
cracks during the flight after the Commander Aircraft
inspection required in inspection required LLC Alert Service
paragraph (e)(1) of this in paragraph (e)(1) Bulletin 236A and
AD, reinforce the support of this AD. After Alert Service
structures for the inboard doing the Bulletin 238, both
and center aileron hinge reinforcement, no dated December 21,
fittings on both wings that further action is 2004, as
are crack free. required. applicable.
(3) If you find cracks Before further Follow Twin
during the inspection flight after the Commander Aircraft
required in paragraph inspection required LLC Alert Service
(e)(1) of this AD, replace in paragraph (e)(1) Bulletin 236A and
and reinforce the cracked of this AD. After Alert Service
support structure. doing the Bulletin 238, both
replacement and dated December 21,
reinforcement, no 2004, as
further action is applicable.
required.
------------------------------------------------------------------------
Alternative Methods of Compliance (AMOCs)
(f) The Manager, Seattle Aircraft Certification Office (ACO),
FAA, ATTN: Vince Massey, Aerospace Engineer, Seattle, ACO, 1601 Lind
Avenue SW., Renton, WA 98057; telephone: (425) 917-6475; facsimile:
(425) 917-6590, has the authority to approve AMOCs for this AD, if
requested using the procedures found in 14 CFR 39.19.
Material Incorporated by Reference
(g) You must do the actions required by this AD following Twin
Commander Aircraft LLC Alert Service Bulletin 236A and Twin
Commander Aircraft LLC Alert Service Bulletin 238, both dated
December 21, 2004. The Director of the Federal Register approved the
incorporation by reference of these service bulletins in accordance
with 5 U.S.C. 552(a) and 1 CFR part 51. To get a copy of this
service information, contact Twin Commander Aircraft LLC, 19010 59th
Drive NE., Arlington, WA 98223, telephone: (360) 435-9797;
facsimile: (360) 435-1112. To review copies of this service
information, go to the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, go to: https://www.archives.gov/federal_register/code_of_
federal_regulations/ibr_locations.html or call (202) 741-6030. To
view the AD docket, go to the Docket Management Facility; US
Department of Transportation, 400 Seventh Street, SW., Nassif
Building, Room PL-401, Washington, DC 20590-001 or on the Internet
at https://dms.dot.gov. The docket number is FAA-2006-23785;
Directorate Identifier 2006-CE-10-AD.
Issued in Kansas City, Missouri, on July 7, 2006.
Kim Smith,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 06-6225 Filed 7-14-06; 8:45 am]
BILLING CODE 4910-13-M
