Airworthiness Directives; Twin Commander Aircraft LLC Models 690, 690A, and 690B Airplanes, 63565-63568 [E9-28548]
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Federal Register / Vol. 74, No. 232 / Friday, December 4, 2009 / Rules and Regulations
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 an economic evaluation
of the estimated costs to comply with
this AD. See the AD docket to examine
the economic evaluation.
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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, pursuant to 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:
jlentini on DSKJ8SOYB1PROD with RULES
■
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.
VerDate Nov<24>2008
17:09 Dec 03, 2009
Jkt 220001
§ 39.13
[Amended]
2. Section 39.13 is amended by adding
a new airworthiness directive to read as
follows:
■
2009–25–10 Sikorsky Aircraft Corp.:
Amendment 39–16130. Docket No.
FAA–2009–1130; Directorate Identifier
2009–SW–40–AD.
Applicability: Model S–92A helicopters,
serial numbers 920006 through 920109,
certificated in any category.
Compliance: Required as indicated, unless
done previously.
To prevent complete loss of oil from the
main gearbox (MGB), failure of the MGB, and
subsequent loss of control of the helicopter,
do the following:
(a) Within 7 days, inspect the MGB lube
system filter assembly for damage to the
primary and secondary oil filters by
following the Accomplishment Instructions,
paragraphs 3.A.(4) and through 3.A.(6) of
Sikorsky Alert Service Bulletin (ASB) No.
92–63–018, dated July 1, 2009 (ASB No. 92–
63–018). For purposes of this AD, ‘‘damage’’
is the presence of those conditions described
in paragraphs 3.A.(5) and 3.A.(8) of the
Accomplishment Instructions of ASB No. 92–
63–018.
(b) If you find damage in the primary oil
filter element (part number (P/N) 70351–
38801–102) as follows: ‘‘wavy pleats’’ as
depicted in Figure 1, internal buckling or a
crack as depicted in Figure 2, or indented
dimples as depicted in Figure 3 of ASB No.
92–63–018 or damage in the secondary oil
filter element (P/N 70351–38801–103) as
follows: ‘‘wavy pleats’’ as depicted in Figure
4 or an elongated cup as depicted in Figure
5 of ASB No. 92–63–018, replace both the
primary and secondary filters, packings, and
filter bowl mounting studs, service the
transmission and perform a functional test
before further flight by following the
Accomplishment Instructions, paragraphs
3.C.(1) through 3.C.(23), of ASB No. 92–63–
018, except this AD does not require you to
return removed studs to HSI nor does it
require you to contact the manufacturer. If
you find damage in the tapped holes or in the
MGB housing lockring counterbore, contact
the Boston Aircraft Certification Office for an
approved repair.
(c) If you find no damage in the primary
or secondary oil filter element, before further
flight, replace the packings, service the
transmission, and perform a functional test
by following the Accomplishment
Instructions, paragraphs 3.B.(1) through
3.B.(4) of ASB No. 92–63–018.
(d) For those helicopters on which the
primary or secondary oil filter element and
filter bowl mounting studs were replaced as
required by paragraph (b) of this AD:
(1) Before the first flight of each day until
the oil filter bowl, P/N AAC367–16D2A, is
replaced, inspect the MGB lube system filter
assembly for any oil leak.
(2) Before further flight after any oil leak
is detected as required by paragraph (d)(1) of
this AD or within 30 days, whichever is
earlier, replace the oil filter bowl.
Note: Sikorsky ASB No. 92–63–019, dated
July 1, 2009, pertains to the subject of this
AD.
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63565
(e) To request a different method of
compliance or a different compliance time
for this AD, follow the procedures in 14 CFR
39.19. Contact the Manager, Boston Aircraft
Certification Office, FAA, ATTN: Kirk
Gustafson, Aviation Safety Engineer, Engine
and Propeller Directorate, FAA, 12 New
England Executive Park, Burlington, MA
01803, telephone (781) 238–7190, fax (781)
238–7170, for information about previously
approved alternative methods of compliance.
(f) The Joint Aircraft System/Component
(JASC) Code is 6300: Main Rotor System.
(g) Inspecting and replacing the main
gearbox lube system assembly parts shall be
done by following the specified portions of
Sikorsky Alert Service Bulletin (ASB) No.
92–63–018, dated July 1, 2009. The Director
of the Federal Register approved this
incorporation by reference under 5 U.S.C.
552(a) and 1 CFR part 51. Copies may be
obtained from Sikorsky Aircraft Corporation,
Attn: Manager, Commercial Technical
Support, mailstop s581a, 6900 Main Street,
Stratford, CT, telephone (203) 383–4866, email address tsslibrary@sikorsky.com, or at
https://www.sikorsky.com. Copies may be
inspected at the FAA, Office of the Regional
Counsel, Southwest Region, 2601 Meacham
Blvd., Room 663, Fort Worth, Texas 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.
(h) This amendment becomes effective on
December 21, 2009.
Issued in Fort Worth, Texas, on November
25, 2009.
Lance T. Gant,
Acting Manager, Rotorcraft Directorate,
Aircraft Certification Service.
[FR Doc. E9–28863 Filed 12–3–09; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2009–0778; Directorate
Identifier 2009–CE–040–AD; Amendment
39–16119; AD 2009–25–02]
RIN 2120–AA64
Airworthiness Directives; Twin
Commander Aircraft LLC Models 690,
690A, and 690B Airplanes
AGENCY: Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
SUMMARY: We are adopting a new
airworthiness directive (AD) for certain
Twin Commander Aircraft LLC Models
690, 690A, and 690B airplanes. This AD
requires you to inspect between the
surface of the left-hand (LH) and right-
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Federal Register / Vol. 74, No. 232 / Friday, December 4, 2009 / Rules and Regulations
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 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 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: This AD becomes effective on
January 8, 2010.
On January 8, 2010, the Director of the
Federal Register approved the
incorporation by reference of certain
publications listed in this AD.
ADDRESSES: To get the service
information identified in this AD,
contact Twin Commander Aircraft LLC,
18933–59th Avenue, NE., Suite 115,
Arlington, WA 98223, telephone: (360)
435–9797; fax: (360) 435–1112; Internet:
https://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. The docket
number is FAA–2009–0778; Directorate
Identifier 2009–CE–040–AD.
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; email: vince.massey@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
On August 21, 2009, we issued a
proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) to
include an AD that would apply to
certain Twin Commander Aircraft LLC
Models 690, 690A, and 690B airplanes.
This proposal was published in the
Federal Register as a notice of proposed
rulemaking (NPRM) on August 28, 2009
(74 FR 44308). The NPRM proposed to
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.
Comments
We provided the public the
opportunity to participate in developing
this AD. The following presents the
comments received on the proposal and
FAA’s response to each comment:
Comment Issue: Extend Compliance
Time
Michael Curtis Pidek, William I.
Smith, and Tom Bayer all state that with
275 airplanes affected by this AD and
only 15 service centers available to do
the actions required in this AD, there is
not enough time to comply with the AD.
All three commenters request an
extension of the compliance time to
allow enough time for the service
centers to schedule the work without
grounding airplanes until the work can
be done.
We do not agree with the commenters.
Over 65 airplanes are already in
compliance with this AD. We have
consulted with Twin Commander
Aircraft LLC and they have covered this
issue with the service centers. The
service centers know how much work is
required since they have already done
the work on over 65 of the affected
airplanes. The service centers plan on
using multiple teams to work on several
airplanes at the same time. They have
confirmed they can perform the actions
required in this AD in the compliance
time as proposed.
Part of the alternative method of
compliance (AMOC) provisions of 14
CFR 39.19 is an extension of the
compliance time provided a level of
safety acceptable to the FAA is met. The
FAA will review any AMOCs of this
nature on a case-by-case basis. If we
determine the proposal presents an
acceptable level of safety, we will
approve it as an AMOC to the AD.
We are not changing the final rule AD
action based on these comments.
Conclusion
We have carefully reviewed the
available data and determined that air
safety and the public interest require
adopting the AD as proposed except for
minor editorial corrections. We have
determined that these minor
corrections:
• Are consistent with the intent that
was proposed in the NPRM for
correcting the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM.
Costs of Compliance
We estimate that this AD will affect
275 airplanes in the U.S. registry.
We estimate the following costs to do
the inspection:
Labor cost
Parts cost
Total cost per
airplane
Total cost on
U.S. operators
80 work-hours × $80 per hour = $6,400 ......................
Not applicable ...............................................................
$6,400
$1,760,000
We estimate the following costs to do
any necessary repairs/replacements that
will be required based on the results of
the inspection. We have no way of
determining the number of airplanes
that may need this repair/replacement:
SHORT MODIFICATION—OPTION A *
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Labor cost
Parts cost
Total cost per
airplane per
side
250 work-hours × $80 per hour = $20,000 per side ..................
$9,170 per kit per side ...............................................................
$29,170
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17:09 Dec 03, 2009
Jkt 220001
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Federal Register / Vol. 74, No. 232 / Friday, December 4, 2009 / Rules and Regulations
MIDDLE MODIFICATION—OPTION B *
Labor cost
Parts cost
Total cost per
airplane per
side
280 work-hours × $80 per hour = $22,400 per side ..................
$9,170 per kit per side ...............................................................
$31,570
LONG MODIFICATION—OPTION C *
Labor cost
Parts cost
Total cost per
airplane per
side
320 work-hours × $80 per hour = $25,600 per side ..................
$9,170 per kit per side ...............................................................
$34,770
Note: * Depending on airplane
configuration, airplanes with rectangular
plates will 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
Labor cost
Parts cost
Total cost per
airplane per
side
75 work-hours × $80 per hour = $6,000 per side ......................
$6,190 per strap per side ...........................................................
$12,190
We estimate the following costs to do
the installation of access holes:
Labor cost
Parts cost
Total cost per
airplane
Total cost on
U.S. operators
30 work-hours × $80 per hour = $2,400 .....................................................................................
$1,293
$3,693
$1,015,575
Labor cost
Parts cost
Total cost per
airplane
Total cost on
U.S. operators
8.5 work-hours × $80 per hour = $680 .......................................................................................
$250
$930
$255,750
We estimate the following costs to do
the wing fastener modification:
jlentini on DSKJ8SOYB1PROD with RULES
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
VerDate Nov<24>2008
17:09 Dec 03, 2009
Jkt 220001
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,
PO 00000
Frm 00037
Fmt 4700
Sfmt 4700
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–2009–0778;
Directorate Identifier 2009–CE–040–
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
Accordingly, under the authority
delegated to me by the Administrator,
■
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Federal Register / Vol. 74, No. 232 / Friday, December 4, 2009 / Rules and Regulations
the Federal Aviation Administration
amends part 39 of the Federal Aviation
Regulations (14 CFR part 39) as follows:
Effective Date
(a) This AD becomes effective on January
8, 2010.
PART 39—AIRWORTHINESS
DIRECTIVES
Affected ADs
(b) None.
1. The authority citation for part 39
continues to read as follows:
Applicability
(c) This AD applies to the following
airplane models and serial numbers that are
certificated in any category:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
Models
2. FAA amends § 39.13 by adding a
new AD to read as follows:
Serial Nos. (S/Ns)
690 .........
690A ......
All S/Ns
All S/Ns except 11195 and
11279.
All S/Ns except 11361, 11383,
11527, and 11536.
■
2009–25–02 Twin Commander Aircraft
LLC: Amendment 39–16119; Docket No.
FAA–2009–0778; Directorate Identifier
2009–CE–040–AD.
690B ......
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:
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
January 8, 2010 (the effective date of this
AD) or within the next 12 months after January 8, 2010 (the effective date of this AD),
whichever occurs first.
Before further flight after the inspection required in paragraph (e)(1) of this AD.
Follow Twin Commander Aircraft LLC Alert
Service Bulletin No. 237, dated May 13,
2005, pages 1 through 14.
(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.
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.
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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; email:
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.
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17:09 Dec 03, 2009
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Material Incorporated by Reference
(g) You must use Twin Commander
Aircraft LLC Alert Service Bulletin No. 237,
dated May 13, 2005; Twin Commander
Aircraft Corporation Custom Kit No. 150,
dated July 8, 1994; and Gulfstream American
Corporation Service Bulletin No. 182, dated
March 2, 1981, 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 Twin Commander Aircraft
LLC, 18933—59th Avenue, NE., Arlington,
WA 98223, telephone: (360) 435–9797; fax:
(360) 435–1112; Internet: https://
www.twincommander.com.
(3) You may review copies of the service
information incorporated by reference for
this AD at the FAA, Central Region, Office of
the Regional Counsel, 901 Locust, Kansas
City, Missouri 64106. For information on the
availability of this material at the Central
Region, call (816) 329–3768.
(4) You may also review copies of the
service information incorporated by reference
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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.
for this AD 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
November 20, 2009.
Margaret Kline,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E9–28548 Filed 12–3–09; 8:45 am]
BILLING CODE 4910–13–P
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]]>Agencies
[Federal Register Volume 74, Number 232 (Friday, December 4, 2009)]
[Rules and Regulations]
[Pages 63565-63568]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-28548]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2009-0778; Directorate Identifier 2009-CE-040-AD;
Amendment 39-16119; AD 2009-25-02]
RIN 2120-AA64
Airworthiness Directives; Twin Commander Aircraft LLC Models 690,
690A, and 690B Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for certain
Twin Commander Aircraft LLC Models 690, 690A, and 690B airplanes. This
AD requires you to inspect between the surface of the left-hand (LH)
and right-
[[Page 63566]]
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 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 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: This AD becomes effective on January 8, 2010.
On January 8, 2010, the Director of the Federal Register approved
the incorporation by reference of certain publications listed in this
AD.
ADDRESSES: To get the service information identified in this AD,
contact Twin Commander Aircraft LLC, 18933-59th Avenue, NE., Suite 115,
Arlington, WA 98223, telephone: (360) 435-9797; fax: (360) 435-1112;
Internet: https://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. The docket number is FAA-2009-0778;
Directorate Identifier 2009-CE-040-AD.
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:
Discussion
On August 21, 2009, we issued a proposal to amend part 39 of the
Federal Aviation Regulations (14 CFR part 39) to include an AD that
would apply to certain Twin Commander Aircraft LLC Models 690, 690A,
and 690B airplanes. This proposal was published in the Federal Register
as a notice of proposed rulemaking (NPRM) on August 28, 2009 (74 FR
44308). The NPRM proposed to 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.
Comments
We provided the public the opportunity to participate in developing
this AD. The following presents the comments received on the proposal
and FAA's response to each comment:
Comment Issue: Extend Compliance Time
Michael Curtis Pidek, William I. Smith, and Tom Bayer all state
that with 275 airplanes affected by this AD and only 15 service centers
available to do the actions required in this AD, there is not enough
time to comply with the AD.
All three commenters request an extension of the compliance time to
allow enough time for the service centers to schedule the work without
grounding airplanes until the work can be done.
We do not agree with the commenters. Over 65 airplanes are already
in compliance with this AD. We have consulted with Twin Commander
Aircraft LLC and they have covered this issue with the service centers.
The service centers know how much work is required since they have
already done the work on over 65 of the affected airplanes. The service
centers plan on using multiple teams to work on several airplanes at
the same time. They have confirmed they can perform the actions
required in this AD in the compliance time as proposed.
Part of the alternative method of compliance (AMOC) provisions of
14 CFR 39.19 is an extension of the compliance time provided a level of
safety acceptable to the FAA is met. The FAA will review any AMOCs of
this nature on a case-by-case basis. If we determine the proposal
presents an acceptable level of safety, we will approve it as an AMOC
to the AD.
We are not changing the final rule AD action based on these
comments.
Conclusion
We have carefully reviewed the available data and determined that
air safety and the public interest require adopting the AD as proposed
except for minor editorial corrections. We have determined that these
minor corrections:
Are consistent with the intent that was proposed in the
NPRM for correcting the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM.
Costs of Compliance
We estimate that this AD will affect 275 airplanes in the U.S.
registry.
We estimate the following costs to do the inspection:
----------------------------------------------------------------------------------------------------------------
Total cost per Total cost on
Labor cost Parts cost 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 will be required based on the results of the
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.
------------------------------------------------------------------------
[[Page 63567]]
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 will 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.
------------------------------------------------------------------------
We estimate the following costs to do the installation of access
holes:
----------------------------------------------------------------------------------------------------------------
Total cost per Total cost on
Labor cost Parts cost airplane U.S. operators
----------------------------------------------------------------------------------------------------------------
30 work-hours x $80 per hour = $2,400........................ $1,293 $3,693 $1,015,575
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do the wing fastener
modification:
----------------------------------------------------------------------------------------------------------------
Total cost per Total cost on
Labor cost Parts cost airplane U.S. operators
----------------------------------------------------------------------------------------------------------------
8.5 work-hours x $80 per hour = $680......................... $250 $930 $255,750
----------------------------------------------------------------------------------------------------------------
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106 describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this AD.
Regulatory Findings
We have determined that this AD will not have federalism
implications under Executive Order 13132. This AD will not have a
substantial direct effect on the States, on the relationship between
the national government and the States, or on the distribution of power
and responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a summary of the costs to comply with this AD (and
other information as included in the Regulatory Evaluation) and placed
it in the AD Docket. You may get a copy of this summary by sending a
request to us at the address listed under ADDRESSES. Include ``Docket
No. FAA-2009-0778; Directorate Identifier 2009-CE-040-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,
[[Page 63568]]
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. 39.13 by adding a new AD to read as follows:
2009-25-02 Twin Commander Aircraft LLC: Amendment 39-16119; Docket
No. FAA-2009-0778; Directorate Identifier 2009-CE-040-AD.
Effective Date
(a) This AD becomes effective on January 8, 2010.
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/Ns 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:
------------------------------------------------------------------------
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 LLC Alert Service
upper wing skins and the January 8, 2010 Bulletin No. 237,
engine mount beam support (the effective date dated May 13, 2005,
straps for any signs of of this AD) or pages 1 through 14.
corrosion and determine the within the next 12
extent of any corrosion months after
found. January 8, 2010
(the effective date
of this AD),
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; email: 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.
Material Incorporated by Reference
(g) You must use Twin Commander Aircraft LLC Alert Service
Bulletin No. 237, dated May 13, 2005; Twin Commander Aircraft
Corporation Custom Kit No. 150, dated July 8, 1994; and Gulfstream
American Corporation Service Bulletin No. 182, dated March 2, 1981,
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 Twin
Commander Aircraft LLC, 18933--59th Avenue, NE., Arlington, WA
98223, telephone: (360) 435-9797; fax: (360) 435-1112; Internet:
https://www.twincommander.com.
(3) You may review copies of the service information
incorporated by reference for this AD at the FAA, Central Region,
Office of the Regional Counsel, 901 Locust, Kansas City, Missouri
64106. For information on the availability of this material at the
Central Region, call (816) 329-3768.
(4) You may also review copies of the service information
incorporated by reference for this AD 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 November 20, 2009.
Margaret Kline,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E9-28548 Filed 12-3-09; 8:45 am]
BILLING CODE 4910-13-P
