[Federal Register Volume 75, Number 207 (Wednesday, October 27, 2010)]
[Proposed Rules]
[Pages 66009-66013]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2010-27212]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2009-1186; Directorate Identifier 2009-CE-065-AD]
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: Supplemental notice of proposed rulemaking (NPRM); reopening of
comment period.
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SUMMARY: We are revising an earlier proposed airworthiness directive
(AD) for the products listed above. That NPRM proposed to retain the
inspection requirements of AD 2009-09-09 and add a terminating action
for the repetitive inspection requirements. That NPRM resulted from the
manufacturer developing a modification that, when incorporated, would
terminate the repetitive inspections required by AD 2009-09-09. Since
we issued the earlier NPRM, the manufacturer revised the service
information to include additional airplane serial numbers into the
Effectivity section and revised the modification kit instructions. This
action revises that NPRM by adding airplanes to the Applicability
section and incorporating new service information. We are proposing
this supplemental NPRM to retain the inspection requirements of AD
2009-09-09 and add a terminating action for the repetitive inspection
requirements using the revised service information. Since these actions
impose an additional burden over that proposed in the NPRM, we are
reopening the comment period to allow the public the chance to comment
on these proposed changes.
DATES: We must receive comments on this supplemental NPRM by December
13, 2010.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
For service information identified in this AD, contact Cessna
Aircraft Company, Product Support, P.O. Box 7706; Wichita, Kansas
67277; telephone: (316) 517-5800; fax: (316) 942-9006; Internet: http://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 http://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 proposed AD, the regulatory
evaluation, any comments received, and other information. The street
address for the Docket Office (phone: 800-647-5527) is in the ADDRESSES
section. Comments will be available in the AD docket shortly after
receipt.
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: [email protected].
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2009-1186;
Directorate Identifier 2009-CE-065-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD because of those comments.
We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
[[Page 66010]]
Discussion
We issued an NPRM to amend 14 CFR part 39 to include an
airworthiness directive (AD) that would apply to certain Cessna
Aircraft Company (Cessna) Models LC40-550FG, LC41-550FG, and LC42-550FG
airplanes. That NPRM was published in the Federal Register on December
17, 2009 (74 FR 66927). That NPRM proposed to supersede AD 2009-09-09
(74 FR 19873, April 30, 2009) with a new AD that would retain the
inspection requirements of AD 2009-09-09 and add a terminating action
for the repetitive inspection requirements.
Actions Since Previous NPRM Was Issued
Since we issued the previous NPRM, the manufacturer revised the
service information to include additional airplane serial numbers into
the Effectivity section and revised the modification kit instructions.
Comments
We gave the public the opportunity to comment on the original NPRM.
We received no comments on that NPRM or on the determination of the
cost to the public.
FAA's Determination
We are proposing this supplemental NPRM because we evaluated all
the relevant information and determined the unsafe condition described
previously is likely to exist or develop in other products of the same
type design. Certain changes described above expand the scope of the
original NPRM. As a result, we have determined that it is necessary to
reopen the comment period to provide additional opportunity for the
public to comment on this supplemental NPRM.
Proposed Requirements of the Supplemental NPRM
This supplemental NPRM would require retaining the inspection
requirements of AD 2009-09-09 and adding a terminating action for the
repetitive inspection requirements using the revised service
information.
Cessna has issued Single Engine Service Bulletin SB09-27-01,
Revision 3, dated July 20, 2010, which describes procedures for
repetitively inspecting the rudder hinges and the rudder hinge brackets
for damage, i.e., cracking, deformation, and discoloration. The service
information also describes procedures for incorporating Cessna Single
Engine Modification Kit MK400-07-01A, dated July 20, 2010, which when
incorporated, will terminate the required repetitive inspections.
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 proposed
AD:
Estimated Costs
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Cost on U.S.
Action Labor cost Parts cost Cost per product operators
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Inspecting the rudder hinges and 1.5 work-hours x Not applicable.... $127.50 per $72,675 per
rudder hinge brackets for $85 per hour = inspection cycle. inspection cycle.
damage with rudder removed $127.50 per
(affects 570 airplanes). inspection cycle.
Inspecting the rudder hinges and .5 work-hour x $85 Not applicable.... $42.50 per $24,225 per
rudder hinge brackets for per hour = $42.50 inspection cycle. inspection cycle.
damage without rudder removed per inspection
(affects 570 airplanes). cycle.
Incorporating the modification 1 work-hour x $85 $739.............. $824.............. $203,528.
kit for Models LC40-550FG and per hour = $85.
LC42-550FG airplanes (affects
247 airplanes).
Incorporating the modification 1 work-hour x $85 $848.............. $933.............. $487,959.
kit for Model LC41-550FG per hour = $85.
airplanes (affects 523
airplanes).
Inspecting the rudder hinge and .5 work-hour x $85 Not applicable.... $42.50............ $850.
the rudder brackets attachment per hour = $42.50.
hardware for correct thread
engagement (affects 20
airplanes).
Inspecting the rudder travel 1 work-hour x $85 Not applicable.... $85............... $1,700.
(affects 20 airplanes). per hour = $85.
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We estimate the following costs to do any necessary repairs that
would be required based on the results of the proposed 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
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Repair the rudder hinge and .5 work-hour x $14 $56.50
the rudder brackets $85 per hour =
attachment hardware thread $42.50.
engagement (could affect 20
airplanes).
Repair the rudder travel .5 work-hour x 14 56.50
(could affect 20 airplanes). $85 per hour =
$42.50.
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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.
[[Page 66011]]
We are issuing this rulemaking under the authority described in
subtitle VII, part A, subpart III, section 44701: ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify this proposed
regulation:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979),
(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.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. The FAA amends Sec. 39.13 by adding the following new
airworthiness directive (AD):
Cessna Aircraft Company (Type Certificate Previously Held by
Columbia Aircraft Manufacturing (Previously The Lancair Company)):
Docket No. FAA-2009-1186; Directorate Identifier 2009-CE-065-AD.
Comments Due Date
(a) We must receive comments by December 13, 2010.
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.
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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
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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.
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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.
Table 1--Inspection Compliance Times
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Initially inspect . Repetitively inspect
Condition . . . . .
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(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
brackets at
whichever of the
following occurs
first:
[[Page 66012]]
(A) Within the next (A) Every 25 hours
10 hours TIS after TIS or 3 months,
May 11, 2009 (the whichever occurs
effective date of first, without
AD 2009-09-09); or removing the
rudder, visually
inspect all three
rudder hinges and
rudder hinge
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
following occurs
later:
(A) Upon (A) Every 25 hours
accumulating 25 TIS or 3 months,
hours TIS; or. whichever occurs
first, without
removing the
rudder, visually
inspect all three
rudder hinges and
rudder hinge
brackets; and
(B) Within the next (B) Every 50 hours
10 hours TIS after TIS or 6 months,
May 11, 2009 (the whichever occurs
effective date of first, with the
AD 2009-09-09). 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 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 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 the effective date of this AD, if Cessna Single Engine Service
Bulletin SB09-27-01, Revision 2, dated November 23, 2009, has been
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,
[[Page 66013]]
Room 100, Wichita, Kansas 67209; telephone: (316) 946-4123; fax:
(316) 946-4107; e-mail: [email protected].
(j) 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: http://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.
Issued in Kansas City, Missouri, on October 21, 2010.
Christina L. Marsh,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2010-27212 Filed 10-26-10; 8:45 am]
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