Airworthiness Directives; Twin Commander Aircraft Corporation Models 690, 690A, and 690B Airplanes, 44308-44311 [E9-20789]
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jlentini on DSKJ8SOYB1PROD with PROPOSALS
44308
Federal Register / Vol. 74, No. 166 / Friday, August 28, 2009 / Proposed Rules
As part of its priority-setting activities
for fiscal year 2006, DOE conducted
analyses for residential clothes washers
to estimate the energy savings potential
of amended standards. DOE determined
that amended standards could result in
energy savings for residential clothes
washers of 5.5 quads cumulative over
the period of 2004–2030. A summary of
these analyses is available on DOE’s
Web site at https://
www1.eere.energy.gov/buildings/
appliance_standards/pdfs/
2006_activities_data_sheets.pdf.
Subsequently, Congress enacted the
Energy Independence and Security Act
of 2007 (EISA 2007), Public Law 110–
140, which revised the energy
conservation standards for residential
clothes washers. The revised standards
established a maximum water factor of
9.5 and become effective on January 1,
2011. See EISA 2007, Section 311(a)(2),
codified at 42 U.S.C. 6295(g)(9). EISA
2007 further required that DOE publish
a final rule no later than December 31,
2011, to determine whether to amend
the standards in effect for clothes
washers manufactured on or after
January 1, 2015. (42 U.S.C.
6295(g)(9)(B)(i)) DOE is embarking on a
standards rulemaking for these products
to comply with these EISA 2007
requirements.
To begin the required rulemaking
process, the Department has prepared a
framework document to explain the
issues, analyses, and process that it is
considering for the development of
amended energy conservation standards
for residential clothes washers. This
document will be publicly available for
review. Additionally, DOE will hold a
public meeting to focus on the analyses
and issues contained in various sections
of the framework document. For each
item listed, the Department will make a
presentation with discussion to follow.
The Department will also make a brief
presentation on the rulemaking process
for these products.
The Department encourages anyone
who wishes to participate in the public
meeting to obtain the framework
document and to be prepared to discuss
its contents. A copy of the draft
framework document is available at
https://www1.eere.energy.gov/buildings/
appliance_standards/residential/
clothes_washers.html. However, public
meeting participants need not limit their
comments to the topics identified in the
framework document. The Department
is also interested in receiving views on
other relevant issues that participants
believe would affect energy
conservation standards for these
products. The Department welcomes all
interested parties, whether or not they
VerDate Nov<24>2008
17:19 Aug 27, 2009
Jkt 217001
participate in the public meeting, to
submit in writing by September 28,
2009, comments and information on
matters addressed in the framework
document and on other matters relevant
to consideration of standards for
residential clothes washers.
DOE will conduct the public meeting
in an informal, conference style. A court
reporter will record the minutes of the
meeting. The discussion will not
include proprietary information, costs
or prices, market shares, or other
commercial matters regulated by U.S.
antitrust laws.
After the public meeting and the
expiration of the period for submitting
written statements, the Department will
begin collecting data, conducting the
analyses as discussed at the public
meeting, and reviewing public
comments.
Anyone who wishes to participate in
the public meeting, receive meeting
materials, or be added to the DOE
mailing list to receive future notices and
information about residential clothes
washers should contact Ms. Brenda
Edwards at (202) 586–2945.
Issued in Washington, DC, on August 21,
2009.
Cathy Zoi,
Assistant Secretary, Energy Efficiency and
Renewable Energy.
[FR Doc. E9–20803 Filed 8–27–09; 8:45 am]
BILLING CODE 6450–01–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2009–0778; Directorate
Identifier 2009–CE–040–AD]
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: Notice of proposed rulemaking
(NPRM).
SUMMARY: We propose to adopt a new
airworthiness directive (AD) for certain
Twin Commander Aircraft Corporation
Models 690, 690A, and 690B airplanes.
This proposed AD would require you to
inspect between the surface of the lefthand (LH) and right-hand (RH) upper
wing skins and the engine mount beam
support straps for any signs of
corrosion, replace the upper steel straps
with parts of improved design, and
PO 00000
Frm 00009
Fmt 4702
Sfmt 4702
modify both wings. This proposed AD
results from reports that corrosion was
found between the mating surfaces of
the wing upper skin surface and the
engine mount beam support straps. We
are proposing this AD to detect and
correct corrosion on the engine mount
beam support straps and the upper wing
skins, which could result in failure of
the engine mount beam support straps.
This failure could lead to loss of the
engine and possible loss of control of
the airplane.
DATES: We must receive comments on
this proposed AD by October 13, 2009.
ADDRESSES: Use one of the following
addresses to comment on this proposed
AD:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: (202) 493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590, between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays.
For service information identified in
this proposed AD, contact Twin
Commander Aircraft, LLC, 19010 59th
Drive, NE., Arlington, WA 98223,
telephone: (360) 435–9797; fax: (360)
435–1112; Internet:
www.twincommander.com.
FOR FURTHER INFORMATION CONTACT:
Vince Massey, Aerospace Engineer,
FAA, Seattle Aircraft Certification
Office, 1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone:
(425) 917–6475; fax: (425) 917–6590;
e-mail: vince.massey@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments
regarding this proposed AD. Send your
comments to an address listed under the
ADDRESSES section. Include the docket
number, ‘‘FAA–2009–0778; Directorate
Identifier 2009–CE–040–AD’’ at the
beginning of your comments. We
specifically invite comments on the
overall regulatory, economic,
environmental, and energy aspects of
the proposed AD. We will consider all
comments received by the closing date
and may amend the proposed AD in
light of those comments.
We will post all comments we
receive, without change, to https://
E:\FR\FM\28AUP1.SGM
28AUP1
Federal Register / Vol. 74, No. 166 / Friday, August 28, 2009 / Proposed Rules
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
concerning this proposed AD.
Discussion
We have received a report that
corrosion was found between the mating
surfaces of the wing upper skin surface
and the engine mount beam support
straps. These straps carry engine loads
from the support beams into the upper
wing skins and wing internal support
structure. Severe corrosion of the straps
can lead to inability to carry engine
loads.
This condition, if not corrected, could
result in failure of the engine mount
beam support straps. This failure could
lead to loss of the engine and possible
loss of control of the airplane.
Relevant Service Information
We have reviewed Twin Commander
Aircraft LLC Alert Service Bulletin No.
237, dated May 13, 2005. The service
information describes procedures for
inspecting the surface of the LH and RH
upper wing skins and the engine mount
beam support straps for any signs of
corrosion, replacing the upper steel
straps with parts of improved design,
and modifying both wings.
We have reviewed Twin Commander
Aircraft Corporation Custom Kit No.
150, dated July 8, 1994. The service
information describes procedures for
installing inspection access holes in the
LH and RH upper wing skins.
We have reviewed Gulfstream
American Corporation Service Bulletin
No. 182, dated March 2, 1981. The
service information describes
procedures for installing additional
wing fasteners on the LH and RH wing.
FAA’s Determination and Requirements
of the Proposed AD
We are proposing this AD because we
evaluated all information and
determined the unsafe condition
described previously is likely to exist or
develop on other products of the same
type design. This proposed AD would
require you to inspect between the
surface of the LH and RH upper wing
skins and the engine mount beam
support straps for any signs of
corrosion, replace the upper steel straps
with parts of improved design, and
modify both wings.
Costs of Compliance
We estimate that this proposed AD
would affect 275 airplanes in the U.S.
registry.
We estimate the following costs to do
the proposed inspection:
Total cost
per airplane
Labor cost
Parts cost
80 work-hours × $80 per hour = $6,400 ......................................................
Not applicable ...................................
We estimate the following costs to do
any necessary repairs/replacements that
would be required based on the results
of the proposed inspection. We have no
way of determining the number of
44309
Total cost on
U.S. operators
$6,400
$1,760,000
airplanes that may need this repair/
replacement:
SHORT MODIFICATION—OPTION A*
Labor cost
Parts cost
250 work-hours × $80 per hour = $20,000 per side ......................................................
$9,170 per kit per side ...............................
Total cost
per airplane
per side
$29,170
MIDDLE MODIFICATION—OPTION B*
Labor cost
Parts cost
280 work-hours × $80 per hour = $22,400 per side ......................................................
$9,170 per kit per side ...............................
Total cost
per airplane
per side
$31,570
LONG MODIFICATION—OPTION C*
Labor cost
Parts cost
320 work-hours × $80 per hour = $25,600 per side ......................................................
$9,170 per kit per side ...............................
jlentini on DSKJ8SOYB1PROD with PROPOSALS
Note: *Depending on airplane
configuration, airplanes with rectangular
plates would need the Plate and Hardware
Kit (SB237–4) at $2,090 per side. Labor to
Total cost
per airplane
per side
$34,770
install this kit is included in Options A, B,
and C.
STRAP ONLY REPLACEMENT—OPTION D
Labor cost
Parts cost
75 work-hours × $80 per hour = $6,000 per side ..........................................................
$6,190 per strap per side ...........................
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Total cost
per airplane
per side
$12,190
44310
Federal Register / Vol. 74, No. 166 / Friday, August 28, 2009 / Proposed Rules
We estimate the following costs to do
the proposed installation of access
holes:
Labor cost
Parts cost
30 work-hours × $80 per hour = $2,400 .............................................................................................
Total cost
per airplane
Total cost on
U.S. operators
$3,693
$1,015,575
Total cost
per airplane
Total cost on
U.S. operators
$930
$255,750
$1,293
We estimate the following costs to do
the proposed wing fastener
modification:
Labor cost
Parts cost
8.5 work-hours × $80 per hour = $680 ...............................................................................................
jlentini on DSKJ8SOYB1PROD with PROPOSALS
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
Section 106, describes the authority of
the FAA Administrator. Subtitle VII,
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in Subtitle VII,
Part A, Subpart III, Section 44701,
‘‘General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
We have determined that this
proposed AD would not have federalism
implications under Executive Order
13132. This proposed AD would not
have a substantial direct effect on the
States, on the relationship between the
national Government and the States, or
on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that the proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
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Jkt 217001
3. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared a regulatory evaluation
of the estimated costs to comply with
this proposed AD and placed it in the
AD docket.
Examining the AD Docket
You may examine the AD docket that
contains the proposed AD, the
regulatory evaluation, any comments
received, and other information on the
Internet at https://www.regulations.gov;
or in person at the Docket Management
Facility between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal
holidays. The Docket Office (telephone
(800) 647–5527) is located at the street
address stated in the ADDRESSES section.
Comments will be available in the AD
docket shortly after receipt.
$250
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
Twin Commander Aircraft Corporation:
Docket No. FAA–2009–0778; Directorate
Identifier 2009–CE–040–AD.
Comments Due Date
(a) We must receive comments on this
airworthiness directive (AD) action by
October 13, 2009.
Affected ADs
(b) None.
Applicability
(c) This AD applies to the following
airplane models and serial numbers that are
certificated in any category:
Models
Serial Nos. (S/Ns)
690 .....................
690A ...................
All S/Ns.
All S/N except 11195 and
11279.
All S/Ns except 11361,
11383, 11527, and
11536.
690B ...................
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
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Frm 00011
Fmt 4702
Sfmt 4702
Unsafe Condition
(d) This AD results from reports that
corrosion was found between the mating
surfaces of the wing upper skin surface and
the engine mount beam support straps. We
are issuing this AD to detect and correct
corrosion on the engine mount beam support
straps and upper wing skins, which could
result in failure of the engine mount beam
support straps. This failure could lead to loss
of the engine and possible loss of control of
the airplane.
Compliance
(e) To address this problem, you must do
the following, unless already done:
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Federal Register / Vol. 74, No. 166 / Friday, August 28, 2009 / Proposed Rules
44311
Actions
Compliance
Procedures
(1) Inspect between the surface of the left-hand
(LH) and right-hand (RH) upper wing skins
and the engine mount beam support straps
for any signs of corrosion and determine the
extent of any corrosion found.
(2) Install modification access holes in the LH
and RH lower wing skins.
Within the next 150 hours time-in-service after
the effective date of this AD or within the
next 12 months after the effective date of
this AD, whichever occurs first.
Follow Twin Commander Aircraft LLC Alert
Service Bulletin No. 237, dated May 13,
2005, pages 1 through 14.
Before further flight after the inspection required in paragraph (e)(1) of this AD.
(3) If corrosion damage is found during the inspection required in paragraph (e)(1) of this
AD, perform necessary modification.
Before further flight after the inspection required in paragraph (e)(1) of this AD.
(4) If corrosion damage is not found during the
inspection required in paragraph (e)(1) of this
AD, do the upper steel strap replacements.
Before further flight after the inspection required in paragraph (e)(1) of this AD.
(5) Install additional wing fasteners on the LH
and RH wing.
Before further flight after the inspection required in paragraph (e)(1) of the AD.
Follow the Accomplishment Instructions, steps
1 through 4 and 6 through 9, of Twin Commander Aircraft Corporation Custom Kit No.
150, dated July 8, 1994, as specified in
Twin Commander Aircraft LLC Alert Service
Bulletin No. 237, dated May 13, 2005.
Follow Twin Commander Aircraft LLC Alert
Service Bulletin No. 237, dated May 13,
2005, Part II, Options A, B, or C, on pages
15 through 29, and 31.
Follow Twin Commander Aircraft LLC Alert
Service Bulletin No. 237, dated May 13,
2005, Part II, Option D, on pages 30 and
31.
Follow Gulfstream American Corporation
Service Bulletin No. 182, dated March 2,
1981.
Note: Although not required by this AD,
we highly recommend compliance with Twin
Commander Aircraft Corporation Service
Bulletin No. 217, Revision No. 1, dated May
26, 1993, Engine Nacelle Firewall
Reinforcement; and Twin Commander
Aircraft LLC Alert Service Bulletin No. 239,
dated February 13, 2006, Outboard Flap—
Inboard Hinge Inspection & Reinforcement.
jlentini on DSKJ8SOYB1PROD with PROPOSALS
Alternative Methods of Compliance
(AMOCs)
(f) The Manager, Seattle Aircraft
Certification Office (ACO), 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: Vince
Massey, Aerospace Engineer, FAA, Seattle
ACO, 1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone: (425)
917–6475; fax: (425) 917–6590; e-mail:
vince.massey@faa.gov. 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.
Related Information
(g) To get copies of the service information
referenced in this AD, contact Twin
Commander Aircraft, LLC, 19010 59th Drive,
NE., Arlington, WA 98223, telephone: (360)
435–9797; fax: (360) 435–1112; Internet:
www.twincommander.com. 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
https://www.regulations.gov.
Issued in Kansas City, Missouri, on August
21, 2009.
Kim Smith,
Manager, Small Airplane Directorate, Aircraft
Certification Service.
[FR Doc. E9–20789 Filed 8–27–09; 8:45 am]
BILLING CODE 4910–13–P
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17:19 Aug 27, 2009
Jkt 217001
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2009–0797; Directorate
Identifier 2009–CE–032–AD]
RIN 2120–AA64
Airworthiness Directives; Hawker
Beechcraft Corporation Models 58,
58A, 58P, 58PA, 58TC, 58TCA, 95–B55,
95–B55A, A36, A36TC, B36TC, E55,
E55A, F33A, and V35B Airplanes
AGENCY: Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
SUMMARY: We propose to supersede
Airworthiness Directive (AD) 91–18–19,
which applies to certain Hawker
Beechcraft Corporation (Hawker) (Type
Certificate Numbers 3A15, 3A16, and
A23CE formerly held by Raytheon
Aircraft Company; formerly held by
Beech Aircraft Corporation) Models 58,
58A, 58P, 58PA, 58TC, 58TCA, 95–B55,
95–B55A, A36, A36TC, B36TC, E55,
E55A, F33A, and V35B airplanes. AD
91–18–19 currently requires you to do a
one-time inspection of the pilot and
copilot shoulder harnesses for an
incorrect washer and replace any
incorrect washer with the correct
washer. Since we issued AD 91–18–19,
we have found that the applicability of
AD 91–18–19 was incorrectly stated
when the Model A36TC airplane was
omitted from the Applicability section.
Consequently, this proposed AD would
retain the actions and the serial number
PO 00000
Frm 00012
Fmt 4702
Sfmt 4702
(SN) applicability of AD 91–18–19 and
realign the SN applicability for Models
A36TC and B36TC airplanes. We are
proposing this AD to detect and correct
an incorrect washer installed in the
pilot and copilot shoulder harnesses.
This failure could result in a
malfunctioning shoulder harness. Such
a failure could lead to occupant injury.
DATES: We must receive comments on
this proposed AD by October 27, 2009.
ADDRESSES: Use one of the following
addresses to comment on this proposed
AD:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: (202) 493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590, between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays.
For service information identified in
this proposed AD, contact Hawker
Beechcraft Corporation, P.O. Box 85,
Wichita, Kansas 67201–0085; telephone:
(800) 429–5372 or (316) 676–3140;
Internet: https://
pubs.hawkerbeechcraft.com.
FOR FURTHER INFORMATION CONTACT:
Steve Potter, Aerospace Engineer, ACE–
118W, Wichita Aircraft Certification
Office (ACO), 1801 Airport Road, Room
100, Wichita, Kansas 67209; telephone:
(316) 946–4124; fax: (316) 946–4107.
SUPPLEMENTARY INFORMATION:
E:\FR\FM\28AUP1.SGM
28AUP1
]]>Agencies
[Federal Register Volume 74, Number 166 (Friday, August 28, 2009)]
[Proposed Rules]
[Pages 44308-44311]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-20789]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2009-0778; Directorate Identifier 2009-CE-040-AD]
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: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to adopt a new airworthiness directive (AD) for
certain Twin Commander Aircraft Corporation Models 690, 690A, and 690B
airplanes. This proposed AD would require you to inspect between the
surface of the left-hand (LH) and right-hand (RH) upper wing skins and
the engine mount beam support straps for any signs of corrosion,
replace the upper steel straps with parts of improved design, and
modify both wings. This proposed AD results from reports that corrosion
was found between the mating surfaces of the wing upper skin surface
and the engine mount beam support straps. We are proposing this AD to
detect and correct corrosion on the engine mount beam support straps
and the upper wing skins, which could result in failure of the engine
mount beam support straps. This failure could lead to loss of the
engine and possible loss of control of the airplane.
DATES: We must receive comments on this proposed AD by October 13,
2009.
ADDRESSES: Use one of the following addresses to comment on this
proposed AD:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: (202) 493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
For service information identified in this proposed AD, contact
Twin Commander Aircraft, LLC, 19010 59th Drive, NE., Arlington, WA
98223, telephone: (360) 435-9797; fax: (360) 435-1112; Internet:
www.twincommander.com.
FOR FURTHER INFORMATION CONTACT: Vince Massey, Aerospace Engineer, FAA,
Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton,
Washington 98057-3356; telephone: (425) 917-6475; fax: (425) 917-6590;
e-mail: vince.massey@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments regarding this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include the docket number, ``FAA-
2009-0778; Directorate Identifier 2009-CE-040-AD'' at the beginning of
your comments. We specifically invite comments on the overall
regulatory, economic, environmental, and energy aspects of the proposed
AD. We will consider all comments received by the closing date and may
amend the proposed AD in light of those comments.
We will post all comments we receive, without change, to https://
[[Page 44309]]
www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive concerning this proposed AD.
Discussion
We have received a report that corrosion was found between the
mating surfaces of the wing upper skin surface and the engine mount
beam support straps. These straps carry engine loads from the support
beams into the upper wing skins and wing internal support structure.
Severe corrosion of the straps can lead to inability to carry engine
loads.
This condition, if not corrected, could result in failure of the
engine mount beam support straps. This failure could lead to loss of
the engine and possible loss of control of the airplane.
Relevant Service Information
We have reviewed Twin Commander Aircraft LLC Alert Service Bulletin
No. 237, dated May 13, 2005. The service information describes
procedures for inspecting the surface of the LH and RH upper wing skins
and the engine mount beam support straps for any signs of corrosion,
replacing the upper steel straps with parts of improved design, and
modifying both wings.
We have reviewed Twin Commander Aircraft Corporation Custom Kit No.
150, dated July 8, 1994. The service information describes procedures
for installing inspection access holes in the LH and RH upper wing
skins.
We have reviewed Gulfstream American Corporation Service Bulletin
No. 182, dated March 2, 1981. The service information describes
procedures for installing additional wing fasteners on the LH and RH
wing.
FAA's Determination and Requirements of the Proposed AD
We are proposing this AD because we evaluated all information and
determined the unsafe condition described previously is likely to exist
or develop on other products of the same type design. This proposed AD
would require you to inspect between the surface of the LH and RH upper
wing skins and the engine mount beam support straps for any signs of
corrosion, replace the upper steel straps with parts of improved
design, and modify both wings.
Costs of Compliance
We estimate that this proposed AD would affect 275 airplanes in the
U.S. registry.
We estimate the following costs to do the proposed inspection:
----------------------------------------------------------------------------------------------------------------
Total cost
Labor cost Parts cost per Total cost on
airplane U.S. operators
----------------------------------------------------------------------------------------------------------------
80 work-hours x $80 per hour = $6,400.......... Not applicable.................... $6,400 $1,760,000
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary repairs/
replacements that would be required based on the results of the
proposed inspection. We have no way of determining the number of
airplanes that may need this repair/replacement:
Short Modification--Option A*
------------------------------------------------------------------------
Total cost
per
Labor cost Parts cost airplane
per side
------------------------------------------------------------------------
250 work-hours x $80 per hour = $9,170 per kit per $29,170
$20,000 per side. side.
------------------------------------------------------------------------
Middle Modification--Option B*
------------------------------------------------------------------------
Total cost
per
Labor cost Parts cost airplane
per side
------------------------------------------------------------------------
280 work-hours x $80 per hour = $9,170 per kit per $31,570
$22,400 per side. side.
------------------------------------------------------------------------
Long Modification--Option C*
------------------------------------------------------------------------
Total cost
per
Labor cost Parts cost airplane
per side
------------------------------------------------------------------------
320 work-hours x $80 per hour = $9,170 per kit per $34,770
$25,600 per side. side.
------------------------------------------------------------------------
Note: *Depending on airplane configuration, airplanes with
rectangular plates would need the Plate and Hardware Kit (SB237-4)
at $2,090 per side. Labor to install this kit is included in Options
A, B, and C.
Strap Only Replacement--Option D
------------------------------------------------------------------------
Total cost
per
Labor cost Parts cost airplane
per side
------------------------------------------------------------------------
75 work-hours x $80 per hour = $6,190 per strap per $12,190
$6,000 per side. side.
------------------------------------------------------------------------
[[Page 44310]]
We estimate the following costs to do the proposed installation of
access holes:
------------------------------------------------------------------------
Total cost
Labor cost Parts cost per Total cost on
airplane U.S. operators
------------------------------------------------------------------------
30 work-hours x $80 per hour = $1,293 $3,693 $1,015,575
$2,400.......................
------------------------------------------------------------------------
We estimate the following costs to do the proposed wing fastener
modification:
------------------------------------------------------------------------
Total cost
Labor cost Parts cost per Total cost on
airplane U.S. operators
------------------------------------------------------------------------
8.5 work-hours x $80 per hour $250 $930 $255,750
= $680.......................
------------------------------------------------------------------------
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We have determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify that the proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this proposed AD and placed it in the AD docket.
Examining the AD Docket
You may examine the AD docket that contains the proposed AD, the
regulatory evaluation, any comments received, and other information on
the Internet at https://www.regulations.gov; or in person at the Docket
Management Facility between 9 a.m. and 5 p.m., Monday through Friday,
except Federal holidays. The Docket Office (telephone (800) 647-5527)
is located at the street address stated in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. The FAA amends Sec. 39.13 by adding the following new AD:
Twin Commander Aircraft Corporation: Docket No. FAA-2009-0778;
Directorate Identifier 2009-CE-040-AD.
Comments Due Date
(a) We must receive comments on this airworthiness directive
(AD) action by October 13, 2009.
Affected ADs
(b) None.
Applicability
(c) This AD applies to the following airplane models and serial
numbers that are certificated in any category:
------------------------------------------------------------------------
Models Serial Nos. (S/Ns)
------------------------------------------------------------------------
690....................................... All S/Ns.
690A...................................... All S/N except 11195 and
11279.
690B...................................... All S/Ns except 11361,
11383, 11527, and 11536.
------------------------------------------------------------------------
Unsafe Condition
(d) This AD results from reports that corrosion was found
between the mating surfaces of the wing upper skin surface and the
engine mount beam support straps. We are issuing this AD to detect
and correct corrosion on the engine mount beam support straps and
upper wing skins, which could result in failure of the engine mount
beam support straps. This failure could lead to loss of the engine
and possible loss of control of the airplane.
Compliance
(e) To address this problem, you must do the following, unless
already done:
[[Page 44311]]
------------------------------------------------------------------------
Actions Compliance Procedures
------------------------------------------------------------------------
(1) Inspect between the Within the next 150 Follow Twin
surface of the left-hand hours time-in- Commander Aircraft
(LH) and right-hand (RH) service after the LLC Alert Service
upper wing skins and the effective date of Bulletin No. 237,
engine mount beam support this AD or within dated May 13, 2005,
straps for any signs of the next 12 months pages 1 through 14.
corrosion and determine the after the effective
extent of any corrosion date of this AD,
found. whichever occurs
first.
(2) Install modification Before further Follow the
access holes in the LH and flight after the Accomplishment
RH lower wing skins. inspection required Instructions, steps
in paragraph (e)(1) 1 through 4 and 6
of this AD. through 9, of Twin
Commander Aircraft
Corporation Custom
Kit No. 150, dated
July 8, 1994, as
specified in Twin
Commander Aircraft
LLC Alert Service
Bulletin No. 237,
dated May 13, 2005.
(3) If corrosion damage is Before further Follow Twin
found during the inspection flight after the Commander Aircraft
required in paragraph inspection required LLC Alert Service
(e)(1) of this AD, perform in paragraph (e)(1) Bulletin No. 237,
necessary modification. of this AD. dated May 13, 2005,
Part II, Options A,
B, or C, on pages
15 through 29, and
31.
(4) If corrosion damage is Before further Follow Twin
not found 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 No. 237,
AD, do the upper steel of this AD. dated May 13, 2005,
strap replacements. Part II, Option D,
on pages 30 and 31.
(5) Install additional wing Before further Follow Gulfstream
fasteners on the LH and RH flight after the American
wing. inspection required Corporation Service
in paragraph (e)(1) Bulletin No. 182,
of the AD. dated March 2,
1981.
------------------------------------------------------------------------
Note: Although not required by this AD, we highly recommend
compliance with Twin Commander Aircraft Corporation Service Bulletin
No. 217, Revision No. 1, dated May 26, 1993, Engine Nacelle Firewall
Reinforcement; and Twin Commander Aircraft LLC Alert Service
Bulletin No. 239, dated February 13, 2006, Outboard Flap--Inboard
Hinge Inspection & Reinforcement.
Alternative Methods of Compliance (AMOCs)
(f) The Manager, Seattle Aircraft Certification Office (ACO),
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: Vince Massey, Aerospace Engineer, FAA, Seattle ACO, 1601 Lind
Avenue, SW., Renton, Washington 98057-3356; telephone: (425) 917-
6475; fax: (425) 917-6590; e-mail: vince.massey@faa.gov. 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.
Related Information
(g) To get copies of the service information referenced in this
AD, contact Twin Commander Aircraft, LLC, 19010 59th Drive, NE.,
Arlington, WA 98223, telephone: (360) 435-9797; fax: (360) 435-1112;
Internet: www.twincommander.com. 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 https://www.regulations.gov.
Issued in Kansas City, Missouri, on August 21, 2009.
Kim Smith,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. E9-20789 Filed 8-27-09; 8:45 am]
BILLING CODE 4910-13-P
