Airworthiness Directives; Cessna Aircraft Company (Type Certificate Previously Held by Columbia Aircraft Manufacturing (Previously the Lancair Company)) Models LC40-550FG, LC41-550FG, and LC42-550FG Airplanes, 6525-6529 [2011-2008]
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Federal Register / Vol. 76, No. 25 / Monday, February 7, 2011 / Rules and Regulations
(2) The service information allows flight
with known cracks provided they do not
exceed a certain limit. FAA policy does not
allow flight with cracks in primary structure.
Since the fuselage is considered primary
structure, we are mandating repair before
further flight after any crack is found.
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Other FAA AD Provisions
(h) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, Standards Office,
FAA, has the authority to approve AMOCs
for this AD, if requested using the procedures
found in 14 CFR 39.19. Send information to
Attn: Greg Davison, Aerospace Engineer,
FAA, Small Airplane Directorate, 901 Locust,
Room 301, Kansas City, Missouri 64106;
telephone: (816) 329–4130; fax: (816) 329–
4090. 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.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
(3) Reporting Requirements: For any
reporting requirement in this AD, a federal
agency may not conduct or sponsor, and a
person is not required to respond to, nor
shall a person be subject to a penalty for
failure to comply with a collection of
information subject to the requirements of
the Paperwork Reduction Act unless that
collection of information displays a current
valid OMB Control Number. The OMB
Control Number for this information
collection is 2120–0056. Public reporting for
this collection of information is estimated to
be approximately 5 minutes per response,
including the time for reviewing instructions,
completing and reviewing the collection of
information. All responses to this collection
of information are mandatory. Comments
concerning the accuracy of this burden and
suggestions for reducing the burden should
be directed to the FAA at: 800 Independence
Ave. SW., Washington, DC 20591, Attn:
Information Collection Clearance Officer,
AES–200.
Related Information
(i) Refer to MCAI European Aviation Safety
Agency (EASA) AD No.: 2009–0085, dated
April 14, 2009; RUAG Alert Service Bulletin
No. ASB–228–266, dated December 1, 2006;
and Dornier 228 Time Limits/Maintenance
Checks Manual, Temporary Revision No. 05–
27, dated August 4, 2008, for related
information. For service information related
to this AD, contact RUAG Aerospace Services
GmbH, Dornier 228 Customer Support, P.O.
Box 1253, 82231 Wessling, Germany;
telephone: + 49 (0) 8153–302280; fax: + 49
(0) 8153–303030. You may review copies of
the referenced service information at the
FAA, Small Airplane Directorate, 901 Locust,
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14:36 Feb 04, 2011
Jkt 223001
Kansas City, Missouri 64106. For information
on the availability of this material at the
FAA, call 816–329–4148.
Material Incorporated by Reference
(h) You must use RUAG Alert Service
Bulletin No. ASB–228–266, dated December
1, 2006; and Dornier 228 Time Limits/
Maintenance Checks Manual, Temporary
Revision No. 05–27, dated August 4, 2008, 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
Dornier 228 Time Limits/Maintenance
Checks Manual, Temporary Revision No. 05–
27, dated August 4, 2008, under 5 U.S.C.
552(a) and 1 CFR part 51.
(2) On June 26, 2007 (72 FR 28591, May
22, 2007), the Director of the Federal Register
previously approved the incorporation by
reference of RUAG Alert Service Bulletin No.
ASB–228–266, dated December 1, 2006.
(3) For service information identified in
this AD, contact RUAG Aerospace Services
GmbH, Dornier 228 Customer Support, P.O.
Box 1253, 82231 Wessling, Germany;
telephone: + 49 (0) 8153–302280; fax: + 49
(0) 8153–303030.
(4) You may review copies of the
referenced service information at the FAA,
Small Airplane Directorate, 901 Locust,
Kansas City, Missouri 64106. For information
on the availability of this material at the
FAA, call 816–329–4148.
(5) 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 January
25, 2011.
John Colomy,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2011–2006 Filed 2–4–11; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2009–1186; Directorate
Identifier 2009–CE–065–AD; Amendment
39–16588; AD 2011–03–04]
RIN 2120–AA64
Airworthiness Directives; Cessna
Aircraft Company (Type Certificate
Previously Held by Columbia Aircraft
Manufacturing (Previously the Lancair
Company)) Models LC40–550FG,
LC41–550FG, and LC42–550FG
Airplanes
Federal Aviation
Administration (FAA), DOT.
AGENCY:
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Fmt 4700
Sfmt 4700
ACTION:
6525
Final rule.
We are superseding an
existing airworthiness directive (AD) for
the products listed above. AD 2009–09–
09 currently requires repetitive
inspections of the rudder hinges and the
rudder hinge brackets for damage, i.e.,
cracking, deformation, and
discoloration. If damage is found during
any inspection, AD 2009–09–09 also
requires replacing the damaged rudder
hinge and/or rudder hinge bracket. This
new AD retains the inspection
requirements of AD 2009–09–09, adds
airplanes to the Applicability section,
and adds a terminating action for the
repetitive inspection requirements. This
AD resulted from the manufacturer
developing a modification that
terminates the repetitive inspections
and from the manufacture adding
airplane serial numbers into the
Applicability section. We are issuing
this AD to detect and correct damage in
the rudder hinges and the rudder hinge
brackets, which could result in failure of
the rudder. This failure could lead to
loss of control.
DATES: This AD is effective March 14,
2011.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of March 14, 2011.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of May 11, 2009 (74 FR 19873, April
30, 2009).
ADDRESSES: For service information
identified in this AD, contact Cessna
Aircraft Company, Product Support,
P.O. Box 7706; Wichita, Kansas 67277;
telephone: (316) 517–5800; fax: (316)
942–9006; Internet: https://
www.cessna.com. You may review
copies of the referenced service
information at the FAA, Small Airplane
Directorate, 901 Locust, Kansas City,
Missouri 64106. For information on the
availability of this material at the FAA,
call (816) 329–4148.
SUMMARY:
Examining the AD Docket
You may examine the AD docket 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 AD
docket contains this AD, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (phone: 800–647–5527) is
Document Management Facility, U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
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Federal Register / Vol. 76, No. 25 / Monday, February 7, 2011 / Rules and Regulations
New Jersey Avenue SE., Washington,
DC 20590.
FOR FURTHER INFORMATION CONTACT: Gary
Park, Aerospace Engineer, Wichita
Aircraft Certification Office, FAA, 1801
Airport Road, Room 100, Wichita,
Kansas 67209; telephone: (316) 946–
4123; fax: (316) 946–4107; e-mail:
gary.park@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a supplemental notice of
proposed rulemaking (SNPRM) to
amend 14 CFR part 39 to supersede AD
2009–09–09, Amendment 39–15895 (74
FR 19873, April 30, 2009). That AD
applies to the specified products. The
SNPRM published in the Federal
public interest require adopting the AD
as proposed except for minor editorial
changes. We have determined that these
minor changes:
• Are consistent with the intent that
was proposed in the SNPRM for
correcting the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the SNPRM.
Register on October 27, 2010 (75 FR
66009). That SNPRM proposed to retain
the inspection requirements of AD
2009–09–09, add airplanes to the
Applicability section, and add a
terminating action for the repetitive
inspection requirements using revised
service information.
Comments
We gave the public the opportunity to
participate in developing this AD. We
received no comments on the SNPRM or
on the determination of the cost to the
public.
Costs of Compliance
We estimate that this proposed AD
affects 790 airplanes of U.S. registry.
We estimate the following costs to
comply with this AD:
Conclusion
We reviewed the relevant data and
determined that air safety and the
ESTIMATED COSTS
Action
Labor cost
Parts cost
Cost per product
Inspecting the rudder hinges and
rudder hinge brackets for damage
with rudder removed (affects 570
airplanes).
Inspecting the rudder hinges and
rudder hinge brackets for damage
without rudder removed (affects
570 airplanes).
Incorporating the modification kit for
Models LC40–550FG and LC42–
550FG airplanes (affects 247 airplanes).
Incorporating the modification kit for
Model LC41–550FG airplanes (affects 523 airplanes).
Inspecting the rudder hinge and the
rudder brackets attachment hardware for correct thread engagement (affects 20 airplanes).
Inspecting the rudder travel (affects
20 airplanes).
1.5 work-hours × $85 per hour =
$127.50 per inspection cycle.
Not applicable ....
$127.50 per inspection cycle.
$72,675 per inspection
cycle.
.5 work-hour × $85 per hour =
$42.50 per inspection cycle.
Not applicable ....
$42.50 per inspection cycle.
$24,225 per inspection
cycle.
1 work-hour × $85 per hour = $85
$739 ...................
$824 ...................
$203,528.
1 work-hour × $85 per hour = $85
$848 ...................
$933 ...................
$487,959.
.5 work-hour × $85 per hour =
$42.50.
Not applicable ....
$42.50 ................
$850.
1 work-hour × $85 per hour = $85
Not applicable ....
$85 .....................
$1,700.
We estimate the following costs to do
any necessary repairs that will be
required based on the results of the
inspection of the rudder hinge and the
rudder brackets attachment hardware
for correct thread engagement and the
Cost on U.S. operators
rudder travel. We have no way of
determining the number of aircraft that
might need these repairs:
ON-CONDITION COSTS
Labor cost
Repair the rudder hinge and the rudder brackets attachment hardware
thread engagement (could affect 20 airplanes).
Repair the rudder travel (could affect 20 airplanes) .................................
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Action
.5 work-hour × $85 per hour =
$42.50.
.5 work-hour × $85 per hour =
$42.50.
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
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Jkt 223001
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
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Cost per
product
Parts cost
$14
$56.50
14
56.50
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.
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Federal Register / Vol. 76, No. 25 / Monday, February 7, 2011 / Rules and Regulations
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
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation
in Alaska, and
(4) 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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
2011–03–04 Cessna Aircraft Company
(Type Certificate Previously Held by
Columbia Aircraft Manufacturing
(Previously The Lancair Company)):
Amendment 39–16588; Docket No.
FAA–2009–1186; Directorate Identifier
2009–CE–065–AD.
Effective Date
(a) This airworthiness directive (AD) is
effective March 14, 2011.
Affected ADs
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
6527
[Amended]
2. The FAA amends § 39.13 by
removing Airworthiness Directive (AD)
2009–09–09, Amendment 39–15895 (74
FR 19873, April 30, 2009), and adding
the following new AD:
■
(b) This AD supersedes AD 2009–09–09,
Amendment 39–15895.
Applicability
(c) This AD applies to the following Cessna
Aircraft Company (type certificate previously
held by Columbia Aircraft Manufacturing
(previously The Lancair Company)) airplane
models and serial numbers that are
certificated in any category:
GROUP 1 AIRPLANES
Model
Serial Nos.
LC40–550FG (300) .........................
LC41–550FG (400) .........................
40001, 40002, and 40004 through 40079.
41001 through 41569, 41571 through 41800, 411001 through 411087, 411089 through 411110, 411112
through 411138, 411140, 411142, and 411147.
42001 through 42009, 42011 through 42558, 42560 through 42569, 421001 through 421013, 421015
through 421017, and 421019.
LC42–550FG (350) .........................
GROUP 2 AIRPLANES
Model
Serial Nos.
LC41–550FG (400) .........................
LC42–550FG (350) .........................
41570, 411088, 411111, 411139, 411141, 411143 through 411146, and 411148 through 411153.
42010, 42559, 421014, 421018, and 421020.
the rudder hinges and the rudder hinge
brackets, which could result in failure of the
rudder. This failure could lead to loss of
control.
Unsafe Condition
(e) This AD is the result of reports received
of a cracked lower rudder hinge bracket on
two of the affected airplanes. We are issuing
this AD to detect and correct damage, i.e.,
cracking, deformation, and discoloration, in
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Subject
(d) Joint Aircraft System Component
(JASC)/Air Transport Association (ATA) of
America Code 55, Stabilizers.
Compliance
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(f) To address this problem, you must do
the following, unless already done:
(1) For Group 1 airplanes specified in
paragraph (c) of this AD: Using the
compliance times specified in table 1 of this
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AD, inspect the rudder hinges and rudder
hinge brackets for damage, i.e., cracking,
deformation, and discoloration. Do the
inspections following Cessna Single Engine
Service Bulletin SB09–27–01, dated April 13,
2009; Cessna Single Engine Service Bulletin
SB09–27–01, Revision 2, dated November 23,
2009; or Cessna Single Engine Service
Bulletin SB09–27–01, Revision 3, dated July
20, 2010.
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Federal Register / Vol. 76, No. 25 / Monday, February 7, 2011 / Rules and Regulations
TABLE 1—INSPECTION COMPLIANCE TIMES
Initially inspect . . .
Repetitively inspect . . .
(i) For airplanes with 25
hours time-in-service (TIS)
or more as of May 11,
2009 (the effective date of
AD 2009–09–09).
With the rudder removed and using 10X visual magnification, inspect all three rudder hinges and rudder
hinge brackets at whichever of the following occurs
first
(A) Within the next 10 hours TIS after May 11, 2009
(the effective date of AD 2009–09–09); or
(B) Within the next 30 days after May 11, 2009 (the effective date of AD 009–09–09).
(ii) For airplanes with less
than 25 hours TIS as of
May 11, 2009 (the effective date of AD 2009–09–
09).
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Condition
Without removing the rudder, visually inspect all three
rudder hinges and rudder hinge brackets, at whichever of the following occurs later.
(A) Upon accumulating 25 hours TIS; or
(B) Within the next 10 hours TIS after May 11, 2009
(the effective date of AD 2009–09–09).
Thereafter inspect as follows until the modification required in paragraph (f)(5) of this AD is done:
(A) Every 25 hours TIS or 3 months, whichever occurs
first, without removing the rudder, visually inspect all
three rudder hinges and rudder hinge brackets; and
(B) Every 50 hours TIS or 6 months, whichever occurs
first, with the rudder removed and using 10X visual
magnification, inspect all three rudder hinges and
rudder hinge brackets.
Thereafter inspect as follows until the modification required in paragraph (f)(5) of this AD is done:
(A) Every 25 hours TIS or 3 months, whichever occurs
first, without removing the rudder, visually inspect all
three rudder hinges and rudder hinge brackets; and
(B) Every 50 hours TIS or 6 months, whichever occurs
first, with the rudder removed and using 10X visual
magnification, inspect all three rudder hinges and
rudder hinge brackets.
(2) For Group 1 airplanes specified in
paragraph (c) of this AD: Before further flight
after any inspection required in paragraphs
(f)(1)(i) or (f)(1)(ii) of this AD in which
damage is found on any of the rudder hinges
and/or rudder hinge brackets, incorporate
Cessna Single Engine Modification Kit
MK400–27–01, dated November 23, 2009; or
Cessna Single Engine Modification Kit
MK400–27–01A dated July 20, 2010, as
specified in Cessna Single Engine Service
Bulletin SB09–27–01, Revision 2, dated
November 23, 2009; and Cessna Single
Engine Service Bulletin SB09–27–01,
Revision 3, dated July 20, 2010. Incorporating
either Modification Kit MK400–27–01 or
Modification Kit MK400–27–01A, terminates
the repetitive inspections required in
paragraphs (f)(1)(i) and (f)(1)(ii) of this AD.
(3) For Group 1 airplanes specified in
paragraph (c) of this AD: If the repetitive
inspections required in paragraphs (f)(1)(i)
and (f)(1)(ii) of this AD become due at the
same time, credit for both inspections will be
given by doing the rudder removal and 10X
visual inspection.
(4) For Group 1 airplanes specified in
paragraph (c) of this AD: Within the next 24
months after March 14, 2011 (the effective
date of this AD), incorporate Cessna Single
Engine Modification Kit MK400–27–01,
dated November 23, 2009; or Cessna Single
Engine Modification Kit MK400–27–01A,
dated July 20, 2010, as specified in Cessna
Single Engine Service Bulletin SB09–27–01,
Revision 2, dated November 23, 2009; and
Cessna Single Engine Service Bulletin SB09–
27–01, Revision 3, dated July 20, 2010,
unless already done as specified in paragraph
(f)(2) of this AD. Incorporating either
Modification Kit MK400–27–01 or
Modification Kit MK400–27–01A, terminates
the repetitive inspections required in
paragraphs (f)(1)(i) and (f)(1)(ii) of this AD.
(5) For Group 1 airplanes specified in
paragraph (c) of this AD: At any time after
the initial inspections required in paragraphs
(f)(1)(i) and (f)(1)(ii) of this AD, as long as no
damage is found, and no later than the
compliance time specified in paragraph (f)(4)
of this AD, you may incorporate Cessna
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Single Engine Modification Kit MK400–27–
01, dated November 23, 2009; or Cessna
Single Engine Modification Kit MK400–27–
01A, dated July 20, 2010, as specified in
Cessna Single Engine Service Bulletin SB09–
27–01, Revision 2, dated November 23, 2009;
and Cessna Single Engine Service Bulletin
SB09–27–01, Revision 3, dated July 20, 2010,
to terminate the repetitive inspections
required in paragraphs (f)(1)(i) and (f)(1)(ii) of
this AD.
(6) For any Group 1 airplane with Cessna
Single Engine Service Bulletin SB09–27–01,
Revision 1, dated August 31, 2009, already
incorporated and for all Group 2 airplanes:
Within the next 30 days after March 14, 2011
(the effective date of this AD), inspect for
proper rudder hinge and rudder bracket
hardware thread engagement and inspect the
rudder travel. Do these inspections following
the Accomplishment Instructions in Cessna
Single Engine Modification Kit MK400–27–
01, dated November 23, 2009; or the
Accomplishment Instructions in Cessna
Single Engine Modification Kit MK400–27–
01A, dated July 20, 2010.
(i) Before further flight after the inspection
required in paragraph (f)(6) of this AD, if any
discrepancies are found in the rudder hinge
or rudder bracket hardware, replace the
affected hardware. Do the replacements
following the Accomplishment Instructions
in Cessna Single Engine Modification Kit
MK400–27–01, dated November 23, 2009; or
the Accomplishment Instructions in Cessna
Single Engine Modification Kit MK400–27–
01A, dated July 20, 2010.
(ii) Before further flight after the inspection
required in paragraph (f)(6) of this AD, if the
rudder travel is outside the limits specified
in the Accomplishment Instructions in
Cessna Single Engine Modification Kit
MK400–27–01, dated November 23, 2009; or
the Accomplishment Instructions in Cessna
Single Engine Modification Kit MK400–27–
01A, dated July 20, 2010, reinstall the rudder
following the Accomplishment Instructions
in either Cessna Single Engine Modification
Kit MK400–27–01, dated November 23, 2009;
or Cessna Single Engine Modification Kit
MK400–27–01A, dated July 20, 2010.
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(iii) After the inspection and any necessary
corrective actions required in paragraphs
(f)(6), (f)(6)(i), and (f)(6)(ii) of this AD, no
further action is required.
Credit for Actions Accomplished in
Accordance With Previous Service
Information
(g) For all airplanes specified in paragraph
(c) of this AD: As of March 14, 2011 (the
effective date of this AD), if Cessna Single
Engine Service Bulletin SB09–27–01,
Revision 2, dated November 23, 2009, has
already been incorporated, no further action
is required.
Alternative Methods of Compliance
(AMOCs)
(h)(1) The Manager, Wichita 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. In accordance with 14 CFR 39.19,
send your request to your principal inspector
or local Flight Standards District Office, as
appropriate. If sending information directly
to the manager of the ACO, send it to the
attention of the person identified in the
Related Information section of this AD.
(2) Before using any approved AMOC,
notify your Principal Maintenance Inspector
or Principal Avionics Inspector, as
appropriate, or lacking a principal inspector,
your local Flight Standards District Office.
(3) AMOCs approved for AD 2009–09–09
are approved for this AD.
Related Information
(i) For more information about this AD,
contact Gary Park, Aerospace Engineer,
Wichita ACO, FAA, 1801 Airport Road,
Room 100, Wichita, Kansas 67209; telephone:
(316) 946–4123; fax: (316) 946–4107; e-mail:
gary.park@faa.gov.
Material Incorporated by Reference
(j) You must use Cessna Single Engine
Service Bulletin SB09–27–01, dated April 13,
2009; Cessna Single Engine Service Bulletin
SB09–27–01, Revision 2, dated November 23,
2009; Cessna Single Engine Service Bulletin
SB09–27–01, Revision 3, dated July 20, 2010;
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Federal Register / Vol. 76, No. 25 / Monday, February 7, 2011 / Rules and Regulations
Cessna Single Engine Modification Kit
MK400–27–01, dated November 23, 2009;
and Cessna Single Engine Modification Kit
MK400–27–01A, dated July 20, 2010, 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
Cessna Single Engine Service Bulletin SB09–
27–01, Revision 2, dated November 23, 2009;
and Cessna Single Engine Service Bulletin
SB09–27–01, Revision 3, dated July 20, 2010;
Cessna Single Engine Modification Kit
MK400–27–01, dated November 23, 2009;
and Cessna Single Engine Modification Kit
MK400–27–01A, dated July 20, 2010, under
5 U.S.C. 552(a) and 1 CFR part 51.
(2) The Director of the Federal Register
previously approved the incorporation by
reference of Cessna Single Engine Service
Bulletin SB09–27–01, dated April 13, 2009,
on May 11, 2009 (74 FR 19873, April 30,
2009).
(3) For service information identified in
this AD, contact Cessna Aircraft Company,
Product Support, P.O. Box 7706; Wichita,
Kansas 67277; telephone: (316) 517–5800;
fax: (316) 942–9006; Internet: https://
www.cessna.com.
(4) You may review copies of the service
information at the FAA, Small Airplane
Directorate, 901 Locust, Kansas City,
Missouri 64106. For information on the
availability of this material at the FAA, call
816–329–4148.
(5) You may also review copies of the
service information that is incorporated by
reference at the National Archives and
Records Administration (NARA). For
information on the availability of this
material at an NARA facility, 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 January
25, 2011.
John Colomy,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2011–2008 Filed 2–4–11; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
wwoods2 on DSK1DXX6B1PROD with RULES_PART 1
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Model 737–100, –200, –200C,
–300, –400, and –500 Series Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
We are adopting a new
airworthiness directive (AD) for the
SUMMARY:
VerDate Mar<15>2010
14:36 Feb 04, 2011
Jkt 223001
Ground Floor, Room W12–140, 1200
New Jersey Avenue, SE., Washington,
DC 20590.
FOR FURTHER INFORMATION CONTACT:
Jeffrey W. Palmer, Aerospace Engineer,
Systems and Equipment Branch, ANM–
130S, FAA, Seattle Aircraft Certification
Office, 1601 Lind Avenue, SW., Renton,
Washington 98057–3356; phone: (425)
917–6472; fax: (425) 917–6590; e-mail:
Jeffrey.W.Palmer@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an airworthiness
directive (AD) that would apply to the
specified products. That NPRM
published in the Federal Register on
August 11, 2010 (75 FR 48620). That
NPRM proposed to require installing
two warning level indicator lights on
the P2–2 center instrument panel in the
flight compartment for certain airplanes.
For a certain other airplane, that NPRM
proposed to require activating the cabin
altitude warning and takeoff
configuration warning lights. For all
airplanes, that NPRM proposed to also
require revising the airplane flight
manual (AFM) to remove certain
requirements included by previous AD
actions, to require new pressure altitude
limitations for certain airplanes, and to
advise the flightcrew of the following
changes: revised emergency procedures
to use when a cabin altitude warning or
rapid depressurization occurs, and
revised cabin pressurization procedures
for normal operations.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comments
received on the proposal and the FAA’s
response to each comment.
Support for the NPRM
The Air Line Pilots Association,
International supports the proposed AD.
Examining the AD Docket
[Docket No. FAA–2010–0761; Directorate
Identifier 2010–NM–069–AD; Amendment
39–16598; AD 2011–03–14]
AGENCY:
products listed above. This AD requires
installing two warning level indicator
lights on the P2–2 center instrument
panel in the flight compartment for
certain airplanes. For a certain other
airplane, this AD requires activating the
cabin altitude warning and takeoff
configuration warning lights. For all
airplanes, this AD also requires revising
the airplane flight manual to remove
certain requirements included by
previous AD actions, requires new
pressure altitude limitations for certain
airplanes, and advises the flightcrew of
the following changes: revised
emergency procedures to use when a
cabin altitude warning or rapid
depressurization occurs, and revised
cabin pressurization procedures for
normal operations. This AD was
prompted by a design change in the
cabin altitude warning system that
would address the identified unsafe
condition. We are issuing this AD to
prevent failure of the flightcrew to
recognize and react properly to a valid
cabin altitude warning horn, which
could result in incapacitation of the
flightcrew due to hypoxia (lack of
oxygen in body), and consequent loss of
control of the airplane.
DATES: This AD is effective March 14,
2011.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of March 14, 2011.
ADDRESSES: For service information
identified in this AD, contact Boeing
Commercial Airplanes, Attention: Data
& Services Management, P.O. Box 3707,
MC 2H–65, Seattle, Washington 98124–
2207; telephone 206–544–5000,
extension 1; fax 206–766–5680; e-mail
me.boecom@boeing.com; Internet
https://www.myboeingfleet.com. You
may review copies of the referenced
service information at the FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington.
For information on the availability of
this material at the FAA, call 425–227–
1221.
6529
Request to Delay Rule Pending
Additional Service Information
You may examine the AD docket 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 AD
docket contains this AD, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (phone: 800–647–5527) is
Document Management Facility, U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Lufthansa requested that the FAA
consider the release of Boeing Service
Bulletin 737–21–1164 before releasing
the AD. Lufthansa stated that Boeing has
recommended that operators consider
doing the modifications specified in
Boeing Service Bulletin 737–21–1164
and Boeing Alert Service Bulletin 737–
31A1325, dated January 11, 2010, at the
same time, because both modifications
require access to the same area of the
airplane and extensive airplane
downtime. However, Lufthansa pointed
PO 00000
Frm 00007
Fmt 4700
Sfmt 4700
E:\FR\FM\07FER1.SGM
07FER1
]]>Agencies
[Federal Register Volume 76, Number 25 (Monday, February 7, 2011)]
[Rules and Regulations]
[Pages 6525-6529]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-2008]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2009-1186; Directorate Identifier 2009-CE-065-AD;
Amendment 39-16588; AD 2011-03-04]
RIN 2120-AA64
Airworthiness Directives; Cessna Aircraft Company (Type
Certificate Previously Held by Columbia Aircraft Manufacturing
(Previously the Lancair Company)) Models LC40-550FG, LC41-550FG, and
LC42-550FG Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are superseding an existing airworthiness directive (AD)
for the products listed above. AD 2009-09-09 currently requires
repetitive inspections of the rudder hinges and the rudder hinge
brackets for damage, i.e., cracking, deformation, and discoloration. If
damage is found during any inspection, AD 2009-09-09 also requires
replacing the damaged rudder hinge and/or rudder hinge bracket. This
new AD retains the inspection requirements of AD 2009-09-09, adds
airplanes to the Applicability section, and adds a terminating action
for the repetitive inspection requirements. This AD resulted from the
manufacturer developing a modification that terminates the repetitive
inspections and from the manufacture adding airplane serial numbers
into the Applicability section. We are issuing this AD to detect and
correct damage in the rudder hinges and the rudder hinge brackets,
which could result in failure of the rudder. This failure could lead to
loss of control.
DATES: This AD is effective March 14, 2011.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of March 14,
2011.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of May 11, 2009
(74 FR 19873, April 30, 2009).
ADDRESSES: For service information identified in this AD, contact
Cessna Aircraft Company, Product Support, P.O. Box 7706; Wichita,
Kansas 67277; telephone: (316) 517-5800; fax: (316) 942-9006; Internet:
https://www.cessna.com. You may review copies of the referenced service
information at the FAA, Small Airplane Directorate, 901 Locust, Kansas
City, Missouri 64106. For information on the availability of this
material at the FAA, call (816) 329-4148.
Examining the AD Docket
You may examine the AD docket 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 AD docket contains this AD, the regulatory evaluation,
any comments received, and other information. The address for the
Docket Office (phone: 800-647-5527) is Document Management Facility,
U.S. Department of Transportation, Docket Operations, M-30, West
Building Ground Floor, Room W12-140, 1200
[[Page 6526]]
New Jersey Avenue SE., Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Gary Park, Aerospace Engineer, Wichita
Aircraft Certification Office, FAA, 1801 Airport Road, Room 100,
Wichita, Kansas 67209; telephone: (316) 946-4123; fax: (316) 946-4107;
e-mail: gary.park@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a supplemental notice of proposed rulemaking (SNPRM) to
amend 14 CFR part 39 to supersede AD 2009-09-09, Amendment 39-15895 (74
FR 19873, April 30, 2009). That AD applies to the specified products.
The SNPRM published in the Federal Register on October 27, 2010 (75 FR
66009). That SNPRM proposed to retain the inspection requirements of AD
2009-09-09, add airplanes to the Applicability section, and add a
terminating action for the repetitive inspection requirements using
revised service information.
Comments
We gave the public the opportunity to participate in developing
this AD. We received no comments on the SNPRM or on the determination
of the cost to the public.
Conclusion
We reviewed the relevant data and determined that air safety and
the public interest require adopting the AD as proposed except for
minor editorial changes. We have determined that these minor changes:
Are consistent with the intent that was proposed in the
SNPRM for correcting the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the SNPRM.
Costs of Compliance
We estimate that this proposed AD affects 790 airplanes of U.S.
registry.
We estimate the following costs to comply with this AD:
Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Action Labor cost Parts cost Cost per product Cost on U.S. operators
--------------------------------------------------------------------------------------------------------------------------------------------------------
Inspecting the rudder hinges and 1.5 work-hours x $85 per Not applicable........ $127.50 per $72,675 per inspection cycle.
rudder hinge brackets for damage hour = $127.50 per inspection cycle.
with rudder removed (affects 570 inspection cycle.
airplanes).
Inspecting the rudder hinges and .5 work-hour x $85 per hour Not applicable........ $42.50 per inspection $24,225 per inspection cycle.
rudder hinge brackets for damage = $42.50 per inspection cycle.
without rudder removed (affects cycle.
570 airplanes).
Incorporating the modification kit 1 work-hour x $85 per hour $739.................. $824................. $203,528.
for Models LC40-550FG and LC42- = $85.
550FG airplanes (affects 247
airplanes).
Incorporating the modification kit 1 work-hour x $85 per hour $848.................. $933................. $487,959.
for Model LC41-550FG airplanes = $85.
(affects 523 airplanes).
Inspecting the rudder hinge and the .5 work-hour x $85 per hour Not applicable........ $42.50............... $850.
rudder brackets attachment = $42.50.
hardware for correct thread
engagement (affects 20 airplanes).
Inspecting the rudder travel 1 work-hour x $85 per hour Not applicable........ $85.................. $1,700.
(affects 20 airplanes). = $85.
--------------------------------------------------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary repairs that
will be required based on the results of the inspection of the rudder
hinge and the rudder brackets attachment hardware for correct thread
engagement and the rudder travel. We have no way of determining the
number of aircraft that might need these repairs:
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
----------------------------------------------------------------------------------------------------------------
Repair the rudder hinge and the rudder .5 work-hour x $85 per hour = $14 $56.50
brackets attachment hardware thread $42.50.
engagement (could affect 20 airplanes).
Repair the rudder travel (could affect 20 .5 work-hour x $85 per hour = 14 56.50
airplanes). $42.50.
----------------------------------------------------------------------------------------------------------------
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.
[[Page 6527]]
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 DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation in Alaska, and
(4) 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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD)
2009-09-09, Amendment 39-15895 (74 FR 19873, April 30, 2009), and
adding the following new AD:
2011-03-04 Cessna Aircraft Company (Type Certificate Previously Held
by Columbia Aircraft Manufacturing (Previously The Lancair
Company)): Amendment 39-16588; Docket No. FAA-2009-1186; Directorate
Identifier 2009-CE-065-AD.
Effective Date
(a) This airworthiness directive (AD) is effective March 14,
2011.
Affected ADs
(b) This AD supersedes AD 2009-09-09, Amendment 39-15895.
Applicability
(c) This AD applies to the following Cessna Aircraft Company
(type certificate previously held by Columbia Aircraft Manufacturing
(previously The Lancair Company)) airplane models and serial numbers
that are certificated in any category:
Group 1 Airplanes
------------------------------------------------------------------------
Model Serial Nos.
------------------------------------------------------------------------
LC40-550FG (300).................. 40001, 40002, and 40004 through
40079.
LC41-550FG (400).................. 41001 through 41569, 41571 through
41800, 411001 through 411087,
411089 through 411110, 411112
through 411138, 411140, 411142, and
411147.
LC42-550FG (350).................. 42001 through 42009, 42011 through
42558, 42560 through 42569, 421001
through 421013, 421015 through
421017, and 421019.
------------------------------------------------------------------------
Group 2 Airplanes
------------------------------------------------------------------------
Model Serial Nos.
------------------------------------------------------------------------
LC41-550FG (400).................. 41570, 411088, 411111, 411139,
411141, 411143 through 411146, and
411148 through 411153.
LC42-550FG (350).................. 42010, 42559, 421014, 421018, and
421020.
------------------------------------------------------------------------
Subject
(d) Joint Aircraft System Component (JASC)/Air Transport
Association (ATA) of America Code 55, Stabilizers.
Unsafe Condition
(e) This AD is the result of reports received of a cracked lower
rudder hinge bracket on two of the affected airplanes. We are
issuing this AD to detect and correct damage, i.e., cracking,
deformation, and discoloration, in the rudder hinges and the rudder
hinge brackets, which could result in failure of the rudder. This
failure could lead to loss of control.
Compliance
(f) To address this problem, you must do the following, unless
already done:
(1) For Group 1 airplanes specified in paragraph (c) of this AD:
Using the compliance times specified in table 1 of this AD, inspect
the rudder hinges and rudder hinge brackets for damage, i.e.,
cracking, deformation, and discoloration. Do the inspections
following Cessna Single Engine Service Bulletin SB09-27-01, dated
April 13, 2009; Cessna Single Engine Service Bulletin SB09-27-01,
Revision 2, dated November 23, 2009; or Cessna Single Engine Service
Bulletin SB09-27-01, Revision 3, dated July 20, 2010.
[[Page 6528]]
Table 1--Inspection Compliance Times
------------------------------------------------------------------------
Initially inspect . Repetitively inspect
Condition . . . . .
------------------------------------------------------------------------
(i) For airplanes with 25 With the rudder Thereafter inspect
hours time-in-service (TIS) removed and using as follows until
or more as of May 11, 2009 10X visual the modification
(the effective date of AD magnification, required in
2009-09-09). inspect all three paragraph (f)(5) of
rudder hinges and this AD is done:
rudder hinge (A) Every 25 hours
brackets at TIS or 3 months,
whichever of the whichever occurs
following occurs first, without
first removing the
(A) Within the next rudder, visually
10 hours TIS after inspect all three
May 11, 2009 (the rudder hinges and
effective date of rudder hinge
AD 2009-09-09); or. brackets; and
(B) Within the next (B) Every 50 hours
30 days after May TIS or 6 months,
11, 2009 (the whichever occurs
effective date of first, with the
AD 009-09-09). rudder removed and
using 10X visual
magnification,
inspect all three
rudder hinges and
rudder hinge
brackets.
(ii) For airplanes with less Without removing the Thereafter inspect
than 25 hours TIS as of May rudder, visually as follows until
11, 2009 (the effective inspect all three the modification
date of AD 2009-09-09). rudder hinges and required in
rudder hinge paragraph (f)(5) of
brackets, at this AD is done:
whichever of the (A) Every 25 hours
following occurs TIS or 3 months,
later. whichever occurs
(A) Upon first, without
accumulating 25 removing the
hours TIS; or. rudder, visually
(B) Within the next inspect all three
10 hours TIS after rudder hinges and
May 11, 2009 (the rudder hinge
effective date of brackets; and
AD 2009-09-09). (B) Every 50 hours
TIS or 6 months,
whichever occurs
first, with the
rudder removed and
using 10X visual
magnification,
inspect all three
rudder hinges and
rudder hinge
brackets.
------------------------------------------------------------------------
(2) For Group 1 airplanes specified in paragraph (c) of this
AD: Before further flight after any inspection required in
paragraphs (f)(1)(i) or (f)(1)(ii) of this AD in which damage is
found on any of the rudder hinges and/or rudder hinge brackets,
incorporate Cessna Single Engine Modification Kit MK400-27-01, dated
November 23, 2009; or Cessna Single Engine Modification Kit MK400-
27-01A dated July 20, 2010, as specified in Cessna Single Engine
Service Bulletin SB09-27-01, Revision 2, dated November 23, 2009;
and Cessna Single Engine Service Bulletin SB09-27-01, Revision 3,
dated July 20, 2010. Incorporating either Modification Kit MK400-27-
01 or Modification Kit MK400-27-01A, terminates the repetitive
inspections required in paragraphs (f)(1)(i) and (f)(1)(ii) of this
AD.
(3) For Group 1 airplanes specified in paragraph (c) of this AD:
If the repetitive inspections required in paragraphs (f)(1)(i) and
(f)(1)(ii) of this AD become due at the same time, credit for both
inspections will be given by doing the rudder removal and 10X visual
inspection.
(4) For Group 1 airplanes specified in paragraph (c) of this AD:
Within the next 24 months after March 14, 2011 (the effective date
of this AD), incorporate Cessna Single Engine Modification Kit
MK400-27-01, dated November 23, 2009; or Cessna Single Engine
Modification Kit MK400-27-01A, dated July 20, 2010, as specified in
Cessna Single Engine Service Bulletin SB09-27-01, Revision 2, dated
November 23, 2009; and Cessna Single Engine Service Bulletin SB09-
27-01, Revision 3, dated July 20, 2010, unless already done as
specified in paragraph (f)(2) of this AD. Incorporating either
Modification Kit MK400-27-01 or Modification Kit MK400-27-01A,
terminates the repetitive inspections required in paragraphs
(f)(1)(i) and (f)(1)(ii) of this AD.
(5) For Group 1 airplanes specified in paragraph (c) of this AD:
At any time after the initial inspections required in paragraphs
(f)(1)(i) and (f)(1)(ii) of this AD, as long as no damage is found,
and no later than the compliance time specified in paragraph (f)(4)
of this AD, you may incorporate Cessna Single Engine Modification
Kit MK400-27-01, dated November 23, 2009; or Cessna Single Engine
Modification Kit MK400-27-01A, dated July 20, 2010, as specified in
Cessna Single Engine Service Bulletin SB09-27-01, Revision 2, dated
November 23, 2009; and Cessna Single Engine Service Bulletin SB09-
27-01, Revision 3, dated July 20, 2010, to terminate the repetitive
inspections required in paragraphs (f)(1)(i) and (f)(1)(ii) of this
AD.
(6) For any Group 1 airplane with Cessna Single Engine Service
Bulletin SB09-27-01, Revision 1, dated August 31, 2009, already
incorporated and for all Group 2 airplanes: Within the next 30 days
after March 14, 2011 (the effective date of this AD), inspect for
proper rudder hinge and rudder bracket hardware thread engagement
and inspect the rudder travel. Do these inspections following the
Accomplishment Instructions in Cessna Single Engine Modification Kit
MK400-27-01, dated November 23, 2009; or the Accomplishment
Instructions in Cessna Single Engine Modification Kit MK400-27-01A,
dated July 20, 2010.
(i) Before further flight after the inspection required in
paragraph (f)(6) of this AD, if any discrepancies are found in the
rudder hinge or rudder bracket hardware, replace the affected
hardware. Do the replacements following the Accomplishment
Instructions in Cessna Single Engine Modification Kit MK400-27-01,
dated November 23, 2009; or the Accomplishment Instructions in
Cessna Single Engine Modification Kit MK400-27-01A, dated July 20,
2010.
(ii) Before further flight after the inspection required in
paragraph (f)(6) of this AD, if the rudder travel is outside the
limits specified in the Accomplishment Instructions in Cessna Single
Engine Modification Kit MK400-27-01, dated November 23, 2009; or the
Accomplishment Instructions in Cessna Single Engine Modification Kit
MK400-27-01A, dated July 20, 2010, reinstall the rudder following
the Accomplishment Instructions in either Cessna Single Engine
Modification Kit MK400-27-01, dated November 23, 2009; or Cessna
Single Engine Modification Kit MK400-27-01A, dated July 20, 2010.
(iii) After the inspection and any necessary corrective actions
required in paragraphs (f)(6), (f)(6)(i), and (f)(6)(ii) of this AD,
no further action is required.
Credit for Actions Accomplished in Accordance With Previous Service
Information
(g) For all airplanes specified in paragraph (c) of this AD: As
of March 14, 2011 (the effective date of this AD), if Cessna Single
Engine Service Bulletin SB09-27-01, Revision 2, dated November 23,
2009, has already been incorporated, no further action is required.
Alternative Methods of Compliance (AMOCs)
(h)(1) The Manager, Wichita 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. In accordance with 14
CFR 39.19, send your request to your principal inspector or local
Flight Standards District Office, as appropriate. If sending
information directly to the manager of the ACO, send it to the
attention of the person identified in the Related Information
section of this AD.
(2) Before using any approved AMOC, notify your Principal
Maintenance Inspector or Principal Avionics Inspector, as
appropriate, or lacking a principal inspector, your local Flight
Standards District Office.
(3) AMOCs approved for AD 2009-09-09 are approved for this AD.
Related Information
(i) For more information about this AD, contact Gary Park,
Aerospace Engineer, Wichita ACO, FAA, 1801 Airport Road, Room 100,
Wichita, Kansas 67209; telephone: (316) 946-4123; fax: (316) 946-
4107; e-mail: gary.park@faa.gov.
Material Incorporated by Reference
(j) You must use Cessna Single Engine Service Bulletin SB09-27-
01, dated April 13, 2009; Cessna Single Engine Service Bulletin
SB09-27-01, Revision 2, dated November 23, 2009; Cessna Single
Engine Service Bulletin SB09-27-01, Revision 3, dated July 20, 2010;
[[Page 6529]]
Cessna Single Engine Modification Kit MK400-27-01, dated November
23, 2009; and Cessna Single Engine Modification Kit MK400-27-01A,
dated July 20, 2010, 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 Cessna Single Engine Service Bulletin
SB09-27-01, Revision 2, dated November 23, 2009; and Cessna Single
Engine Service Bulletin SB09-27-01, Revision 3, dated July 20, 2010;
Cessna Single Engine Modification Kit MK400-27-01, dated November
23, 2009; and Cessna Single Engine Modification Kit MK400-27-01A,
dated July 20, 2010, under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) The Director of the Federal Register previously approved the
incorporation by reference of Cessna Single Engine Service Bulletin
SB09-27-01, dated April 13, 2009, on May 11, 2009 (74 FR 19873,
April 30, 2009).
(3) For service information identified in this AD, contact
Cessna Aircraft Company, Product Support, P.O. Box 7706; Wichita,
Kansas 67277; telephone: (316) 517-5800; fax: (316) 942-9006;
Internet: https://www.cessna.com.
(4) You may review copies of the service information at the FAA,
Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106.
For information on the availability of this material at the FAA,
call 816-329-4148.
(5) You may also review copies of the service information that
is incorporated by reference at the National Archives and Records
Administration (NARA). For information on the availability of this
material at an NARA facility, 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 January 25, 2011.
John Colomy,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2011-2008 Filed 2-4-11; 8:45 am]
BILLING CODE 4910-13-P
