Airworthiness Directives; Revo, Incorporated Models Colonial C-2, Lake LA-4, Lake LA-4A, Lake LA-4P, and Lake LA-4-200 Airplanes, 33820-33825 [05-11361]
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Federal Register / Vol. 70, No. 111 / Friday, June 10, 2005 / Rules and Regulations
PART 171—[AMENDED]
§ 171.15
[Corrected]
6. On page 30548, in § 171.15(b)(1), the
number ‘‘$3,115,000’’ is corrected to
read ‘‘$3,155,000.’’
I
§ 171.16
[Corrected]
7. In § 171.16 (c), the table entitled
SCHEDULE OF MATERIALS ANNUAL
FEES AND FEES FOR GOVERNMENT
AGENCIES LICENSED BY NRC, the
Annual Fees column entry for 15. C. On
page 30552, the entry ‘‘0N/A8’’ is
corrected to ‘‘8 N/A.’’
I
Dated in Rockville, Maryland, this 2nd day
of June, 2005.
For the Nuclear Regulatory Commission.
Jesse L. Funches,
Chief Financial Officer.
[FR Doc. 05–11495 Filed 6–9–05; 8:45 am]
BILLING CODE 7590–01–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–21092; Directorate
Identifier 2005–CE–20–AD; Amendment 39–
14118; AD 2005–12–02]
RIN 2120–AA64
Airworthiness Directives; Revo,
Incorporated Models Colonial C–2,
Lake LA–4, Lake LA–4A, Lake LA–4P,
and Lake LA–4–200 Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) to
supersede Airworthiness Directive (AD)
98–10–12, which applies to all Revo,
Incorporated (REVO) (Type Certificate
1A13 formerly held by Colonial Aircraft
Company, Lake Aircraft Corporation,
Consolidated Aeronautics, Inc., and
Global Amphibians LLC) Models
Colonial C–2, Lake LA–4, Lake LA–4A,
Lake LA–4P, and Lake LA–4–200
airplanes. AD 98–10–12 currently
requires you to ensure adequate
clearance between the attachment fitting
and the horizontal stabilizer rear beam
and between the attachment fitting and
the stabilizer skin with inspections,
possible replacement, and adjustments
as necessary. This new AD is the result
of several reports of fatigue cracks found
in the horizontal stabilizer attachment
fitting (part number 2–2200–21) of
Model LA–4–200 airplanes that were in
compliance with AD 98–10–12. This
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includes an airplane accident with a
fatality attributed to a fatigue crack in
the horizontal stabilizer attachment
fitting. Consequently, this AD requires
either a dye penetrant inspection of the
horizontal stabilizer attachment fitting
for any evidence of fretting, cracking, or
corrosion (with necessary replacement
and modification) or replacement of the
fittings depending on the number of
operational hours on the fitting. The AD
also requires you to repetitively replace
the fitting every 850 hours time-inservice (TIS), repetitively inspect
(visually) the fittings between
replacement times, and report to FAA
the results of the initial inspection and
any cracks found on repetitive
inspections. We are issuing this AD to
detect, correct, and prevent future
cracks in the horizontal stabilizer
attachment fitting, which could result in
failure of the horizontal stabilizer
attachment fitting. This failure could
result in loss of control of the airplane.
DATES: This AD becomes effective on
July 8, 2005.
As of July 8, 2005, the Director of the
Federal Register approved the
incorporation by reference of certain
publications listed in the regulation.
We must receive any comments on
this AD by August 8, 2005.
ADDRESSES: Use one of the following to
submit comments on this AD:
• DOT Docket Web site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically.
• Mail: Docket Management Facility;
U.S. Department of Transportation, 400
Seventh Street, SW., Nassif Building,
Room PL–401, Washington, DC 20590–
001.
• Fax: 1–202–493–2251.
• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
400 Seventh Street, SW., Washington,
DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
To get the service information
identified in this proposed AD, contact
Revo, Incorporated, 1396 Grandview
Boulevard, Kissimmee, FL 34744.
To view the comments to this AD, go
to https://dms.dot.gov. The docket
number is FAA–2005–21092;
Directorate Identifier 2005–CE–20–AD.
FOR FURTHER INFORMATION CONTACT:
Cindy Lorenzen, Aerospace Engineer,
FAA, Atlanta Aircraft Certification
Office, 1895 Phoenix Boulevard, suite
450, Atlanta, Georgia 30349; telephone:
(770) 703–6078; facsimile: (770) 703–
6097.
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SUPPLEMENTARY INFORMATION:
Has FAA taken any action to this
point? A report of loss of control on a
Revo, Incorporated (REVO) Lake LA–4
series airplane during flight caused us to
issue AD 98–10–12, Amendment 39–
10524 (63 FR 26964, May 15, 1998). AD
98–10–12 currently requires the
following on all REVO (Type Certificate
1A13 formerly held by Colonial Aircraft
Company, Lake Aircraft Corporation,
Consolidated Aeronautics, Inc., and
Global Amphibians LLC) Models
Colonial C–2, Lake LA–4, Lake LA–4A,
Lake LA–4P, and Lake LA–4–200
airplanes:
• Measuring for a clearance of 5⁄32 of
an inch between the attachment fitting
and the horizontal stabilizer rear beam.
• If this minimum measurement is
not met, removing the affected
horizontal tail half from the airplane
and inspecting the attachment fitting for
any evidence of fretting, cracking, or
corrosion.
• If cracks, fretting, or corrosion are/
is present, replacing the attachment
fitting with a new fitting, ensuring a
clearance of 1⁄16 of an inch exists
between the attachment fitting, and, if
needed, trimming the stabilizer skin to
provide a positive clearance for the
fitting.
What has happened since AD 98–10–
12 to initiate this AD action? The FAA
has received more reports of fatigue
cracks found in the horizontal stabilizer
attachment fitting (part number (P/N) 2–
2200–21) of REVO Model LA–4–200
airplanes. These airplanes were in
compliance with AD 98–10–12. This
includes one report of a REVO Model
LA–4–200 airplane accident with a
fatality attributed to a fatigue crack in
the horizontal stabilizer attachment
fitting.
The cracks occurred with as little as
942 hours time-in-service (TIS) on the
horizontal stabilizer attachment fitting.
What is the potential impact if FAA
took no action? Failure of the horizontal
stabilizer attachment fitting (P/N 2–
2200–21) could result in loss of control
of the airplane.
Is there service information that
applies to this subject? REVO has issued
Service Bulletin B–78, dated April 3,
1998.
What are the provisions of this service
information? The service bulletin
includes procedures for:
—Removing the fitting and inspecting
(both visual and dye penetrant) for
cracks, fretting, or corrosion;
—Replacing the attachment fitting with
a new fitting;
—Measuring the gap between the
attachment fitting and the horizontal
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stabilizer skin for proper clearance;
and
—Trimming the stabilizer skin to
provide proper clearance.
FAA’s Determination and Requirements
of the AD
What has FAA decided? We have
evaluated all pertinent information and
identified an unsafe condition that is
likely to exist or develop on other
products of this same type design.
Since the unsafe condition described
previously is likely to exist or develop
on other REVO (Type Certificate 1A13
formerly held by Colonial Aircraft
Company, Lake Aircraft Corporation,
Consolidated Aeronautics, Inc., and
Global Amphibians LLC) Models
Colonial C–2, Lake LA–4, Lake LA–4A,
Lake LA–4P, and Lake LA–4–200
airplanes of the same type design, we
are issuing this AD to detect, correct,
and prevent future cracks in the
horizontal stabilizer attachment fitting
(P/N 2–2200–21), which could result in
failure of the horizontal stabilizer
attachment fitting. This failure could
result in loss of control of the airplane.
What does this AD require? This AD
supersedes AD 98–10–12 by requiring
the following:
• Dye penetrant inspection of the
horizontal stabilizer attachment fitting
for any evidence of fretting, cracking, or
corrosion (with necessary replacement
and modification) for those airplanes
with less than 825 hours TIS on the
fitting;
• Replacement of the fittings for those
airplanes with 825 or more hours TIS on
the fittings;
• Repetitive replacement of the fitting
every 850 hours time-in-service (TIS);
• Repetitive visual inspections of the
fitting every 50 hours TIS (or at the next
annual inspection) between the fitting
replacements; and
• Submittal of a report to FAA on the
findings of the initial inspection and
report of any cracks found for the
repetitive inspections.
In preparing this rule, we contacted
type clubs and aircraft operators to get
technical information and information
on operational and economic impacts.
As a result of this contact, we received
a report of an additional airplane with
a crack in the fitting. This airplane had
942 hours total TIS. Consequently, we
adjusted the compliance times in the
AD based on this information.
How does the revision to 14 CFR part
39 affect this AD? On July 10, 2002, we
published a new version of 14 CFR part
39 (67 FR 47997, July 22, 2002), which
governs FAA’s AD system. This
regulation now includes material that
relates to altered products, special flight
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permits, and alternative methods of
compliance. This material previously
was included in each individual AD.
Since this material is included in 14
CFR part 39, we will not include it in
future AD actions.
Comments Invited
Will I have the opportunity to
comment before you issue the rule? This
AD is a final rule that involves
requirements affecting flight safety and
was not preceded by notice and an
opportunity for public comment;
however, we invite you to submit any
written relevant data, views, or
arguments regarding this AD. Send your
comments to an address listed under
ADDRESSES. Include ‘‘Docket No. FAA–
2005–21092; Directorate Identifier
2005–CE–20–AD’’ in the subject line of
your comments. If you want us to
acknowledge receipt of your mailed
comments, send us a self-addressed,
stamped postcard with the docket
number written on it; we will datestamp your postcard and mail it back to
you. We specifically invite comments
on the overall regulatory, economic,
environmental, and energy aspects of
the rule that might suggest a need to
modify it. If a person contacts us
through a nonwritten communication,
and that contact relates to a substantive
part of this AD, we will summarize the
contact and place the summary in the
docket. We will consider all comments
received by the closing date and may
amend the AD in light of those
comments.
Authority for This Rulemaking
What authority does FAA have for
issuing this rulemaking action? 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
Will this AD impact various entities?
We have determined that this AD will
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33821
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.
Will this AD involve a significant rule
or regulatory action? 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 ‘‘AD Docket FAA–2005–21092;
Directorate Identifier 2005–CE–20–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,
the Federal Aviation Administration
amends part 39 of the Federal Aviation
Regulations (14 CFR part 39) as follows:
I
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Airworthiness Directive (AD)
98–10–12, Amendment 39–10524 (63 FR
26964, May 15, 1998), and by adding a
new AD to read as follows:
I
2005–12–02 Revo, Incorporated (Type
Certificate 1A13 formerly held by
Colonial Aircraft Company, Lake
Aircraft Corporation, Consolidated
Aeronautics, Inc., and Global
Amphibians LLC): Amendment 39–
14118; Docket No. FAA–2005–21092;
Directorate Identifier 2005–CE–20–AD.
When Does This AD Become Effective?
(a) This AD becomes effective on July 8,
2005.
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Are Any Other ADs Affected By This Action?
(b) Yes. This AD supersedes AD 98–10–12;
Amendment 39–10524.
What Airplanes Are Affected by This AD?
(c) This AD affects Models Colonial C–2,
Lake LA–4, Lake LA–4A, Lake LA–4P, and
Lake LA–4–200, all serial numbers, that are
certificated in any category.
What is the Unsafe Condition Presented in
This AD?
(d) This AD is the result of several reports
of fatigue cracks found in the horizontal
stabilizer attachment fitting (part number (P/
N) 2–2200–21) of Model LA–4–200 airplanes
and one report of a Model LA–4–200 airplane
accident with a fatality attributed to a fatigue
crack in the horizontal stabilizer attachment
fitting. We are issuing this AD to detect,
correct, and prevent future cracks in the
horizontal stabilizer attachment fitting (P/N
2–2200–21), which could result in failure of
the horizontal stabilizer attachment fitting.
This failure could result in loss of control of
the airplane.
What Must I Do To Address This Problem?
(e) To address this problem, you must do
the following:
Actions
Compliance
Procedures
(1) For airplanes with 825 hours time-in-service
(TIS) or more on any horizontal stabilizer attachment fitting as of July 8, 2005 (the effective date of this AD):
(i) Replace the horizontal stabilizer attachment
fitting (part number (P/N) 2–2200–21).
(ii) If necessary, trim the horizontal stabilizer
rear beam doubler flange to provide positive
clearance to the fitting.
Within the next 25 hours TIS after July 8,
2005 (the effective date of this AD) Repetitively replace any horizontal stabilizer attachment fitting (P/N 2–2200–21) thereafter
following paragraph (e)(3) of this AD.
Follow Revo, Inc. Service Bulletin B–78, dated
April 3, 1998, paragraphs 2 and 3 of the INSPECTION and REPAIR section and the
APPENDIX.
(2) For airplanes with less than 825 hours TIS
on any horizontal stabilizer attachment fitting
as of July 8, 2005 (the effective date of this
AD):
(i) Remove the horizontal stabilizer attachment
fitting (P/N 2–2200–21) from the airplane
and inspect for cracks (using dye penetrant),
fretting, or corrosion. To take ‘‘already done’’
credit for this, you must have removed the
fitting from the airplane when the inspection
was done.
(ii) Replace any horizontal stabilizer attachment
fitting if you find any cracks, fretting, or corrosion.
Inspect within the next 25 hours TIS after July
8, 2005 (the effective date of this AD), unless already done. If cracks, fretting, or corrosion is found, replace before further flight
after the inspection.
Follow Revo, Inc. Service Bulletin B–78, dated
April 3, 1998, INSPECTION and REPAIR
section and the APPENDIX.
(3) For all airplanes: Repetitively replace the
horizontal stabilizer attachment fittings upon
accumulating 850 hours TIS on the fittings.
Every 850 hours TIS ........................................
Follow Revo, Inc. Service Bulletin B–78, dated
April 3, 1998, paragraphs 2 and 3 of the INSPECTION and REPAIR section and the
APPENDIX.
(4) For all airplanes: Measure the gap between
the horizontal skin and the horizontal stabilizer attachment fitting (P/N 2–2200–21). If
gap is less than 1⁄16-inch, trim the skin to
provide at least 1⁄16-inch gap.
Before further flight after any replacement of
the fitting required by paragraphs (e)(1),
(e)(2), and (e)(3) of this AD.
Follow Revo, Inc. Service Bulletin B–78, dated
April 3, 1998.
(5) For all airplanes: Repetitively inspect (visual) the horizontal stabilizer attachedment fitting using the following procedures.
(i) Move the elevator as required to see the fitting, ensuring that the aft face of the fitting is
visible.
(ii) Clean the fitting. Pay special attention to
the radius edges of the fitting just outboard
of the fitting ear.
(iii) Visually inspect the fitting for cracks using
a flashlight (a small magnifying glass or
borescope is recommended). Pay special attention again to the radius edges just outboard of the fitting ear. Also, inspect as far
forward on the edge that is possible because
some cracks progress along the forward face
of the fitting that is mostly hidden by the horizontal stabilizer rear beam.
(iv) Reference the sketch on page 1 of the
Service Bulletin B–78 to see where the crack
is likely to begin.
(v) Replace the fitting prior to further flight if
cracks are found during any of these inspections.
Repetitively inspect at whichever of the following that occurs first (first repetitive starts
after the initial inspection or replacement):
• 50 hours TIS; or
• the next annual inspection
Replace the fitting prior to further flight after
any inspection where cracks are found.
Follow the procedures presented in the Actions column of this paragraph, including the
sketch on page 1 of the Service Bulletin B–
78.
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33823
Actions
Compliance
Procedures
(6) For all airplanes: Report to FAA the results
of the initial inspection required by paragraph
(e)(2) of this AD even if no damage is found,
and report the results of the repetitive inspections required by paragraph (e)(2) of
this AD only if cracks are found. The Office
of Management and Budget (OMB) approved
the information collection requirements contained in this regulation under the provisions
of Paperwork Reduction Act of 1980 (44
U.S.C. 3501 and those following sections)
and assigned OMB Control Number 2120–
0056.
Within 10 days after the inspection required
by paragraph (e)(2) or (e)(5) of this AD or
within 10 days after July 8, 2005 (the effective date of this AD), whichever occurs later.
Send the form (Figure 1 of this AD) to FAA,
Atlanta ACO, 1895 Phoenix Boulevard,
suite 450, Atlanta, Georgia 30349; telephone: (770) 703–6078; facsimile: (770)
703–6097.
(7) For all airplanes: Do not install used serviceable fittings, unless you know the number
of accumulated hours TIS and have inspected following the requirements of paragraph (e)(2) of this AD.
As of July 8, 2005 (the effective date of this
AD).
Not Applicable.
BILLING CODE 4910–13–P
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BILLING CODE 4910–13–C
Federal Register / Vol. 70, No. 111 / Friday, June 10, 2005 / Rules and Regulations
May I Request an Alternative Method of
Compliance?
DEPARTMENT OF COMMERCE
(f) You may request a different method of
compliance or a different compliance time
for this AD by following the procedures in 14
CFR 39.19. Unless FAA authorizes otherwise,
send your request to your principal
inspector. The principal inspector may add
comments and will send your request to the
Manager, Atlanta Aircraft Certification Office
(ACO), FAA. For information on any already
approved alternative methods of compliance,
contact Cindy Lorenzen, Aerospace Engineer,
FAA, Atlanta ACO, 1895 Phoenix Boulevard,
suite 450, Atlanta, Georgia 30349; telephone:
(770) 703–6078; facsimile: (770) 703–6097.
International Trade Administration
May I Obtain a Special Flight Permit for the
Initial Inspection or Replacement
Requirement of This AD?
(g) Yes. Special flight permits are allowed
for this AD with these limitations:
(1) Vne reduced to 121 m.p.h. (105 knots);
and
(2) No flight into known turbulence.
Does This AD Incorporate Any Material by
Reference?
(h) You must do the actions required by
this AD following the instructions in Revo,
Inc. Service Bulletin B–78, dated April 3,
1998. The Director of the Federal Register
approved the incorporation by reference of
this service bulletin in accordance with 5
U.S.C. 552(a) and 1 CFR part 51. To get a
copy of this service information, contact
Revo, Incorporated, 1396 Grandview
Boulevard, Kissimmee, FL 34744. To review
copies of this service information, go to the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, go
to: https://www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html or call (202) 741–6030. To
view the AD docket, go to the Docket
Management Facility; U.S. Department of
Transportation, 400 Seventh Street, S.W.,
Nassif Building, Room PL–401, Washington,
DC 20590–001 or on the Internet at https://
dms.dot.gov. The docket number is FAA–
2005–21092; Directorate Identifier 2005–CE–
20–AD.
Issued in Kansas City, Missouri, on June 2,
2005.
Kim Smith,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–11361 Filed 6–9–05; 8:45 am]
BILLING CODE 4910–13–P
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15 CFR part 335 and 340
Docket Number: 001229368-5150-03
RIN: 0625-AA58
Imports of Certain Worsted Wool
Fabric: Implementation of Tariff Rate
Quota Established Under Title V of the
Trade and Development Act of 2000
Department of Commerce,
International Trade Administration.
ACTION: Final rule; withdrawal.
AGENCY:
SUMMARY: The Department of Commerce
(‘‘Commerce’’) is withdrawing its final
rule entitled ‘‘Imports of Certain
Worsted Wool Fabric: Implementation
of Tariff Rate Quota Established Under
Title V of the Trade and Development
Act of 2000’’ published on May 12, 2005
(70 FR 24941). That rule finalized tariff
rate quotas (TRQ) for a limited quantity
of worsted wool fabrics pursuant to
Title V of the Trade and Development
Act of 2000 (‘‘the Act’’) as amended by
the Trade Act of 2002. The rule is being
withdrawn due to an incorrect effective
date.
DATES: The final rule published on May
12, 2005 at 70 FR 24941 is withdrawn
as of June 10, 2005.
FOR FURTHER INFORMATION CONTACT:
Sergio Botero, Office of Textiles and
Apparel, U.S. Department of Commerce,
(202) 482-4058.
SUPPLEMENTARY INFORMATION: The
Department of Commerce (‘‘Commerce’’)
is withdrawing its final rule published
on May 12, 2005 at 70 FR 24941. That
rule finalized tariff rate quotas (TRQ) for
a limited quantity of worsted wool
fabrics pursuant to Title V of the Trade
and Development Act of 2000 (‘‘the
Act’’) as amended by the Trade Act of
2002. The rule is being withdrawn
because the effective date of the rule is
incorrect. The effective date for the final
rule was incorrectly established for June
13, 2005.
Commerce currently has open for
comment a related interim final rule
that implements amendments made by
the Miscellaneous Trade Act of 2004 (70
FR 25774). Comments may be submitted
until 5:00 p.m. on July 15, 2005. Please
see the interim final rule for background
information and instructions for
submitting comments.
Classification: It has been determined
that this notice is not significant for
purposes of E.O. 12866.
The Department finds good cause to
waive prior notice and an opportunity
for public comment required by the
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33825
Administrative Procedure Act because it
is unnecessary and contrary to the
public interest. Prior notice and
opportunity for public comment is
unnecessary because this rule will not
have a substantive impact on the
affected industry. The provisions
implemented by the May 12, 2005 rule
are not currently in effect and have not
impacted the regulated industry. The
withdrawal of the May 12, 2005 rule
will, therefore, not substantively change
the requirements currently imposed on
the regulated industry. It would be
contrary to the public interest to allow
for prior notice and an opportunity for
public comment because the published
effective date of the May 12, 2005 rule
conflicts with an interim final rule that
implemented recently enacted statutory
amendments. Consequently, if the May
12, 2005 rule is allowed to go into effect,
it would create confusion in the
industry. Therefore, it is unnecessary
and contrary to the public interest to
provide prior notice and an opportunity
for public comment.
The Department finds that the 30-day
in effectiveness is inapplicable because
this rule is not a substantive rule. The
provisions implemented by the May 12,
2005 rule are not currently in effect and
its withdrawal will not substantively
change the requirements currently
imposed on the regulated industry.
Because notice and opportunity for
comment are not required pursuant to 5
USC 553 or any other law, the analytical
requirements of the Regulatory
Flexibility Act (5 USC 601 et seq.) are
inapplicable. Therefore, a regulatory
flexibility analysis is not required and
has not been prepared.
Dated: June 7, 2005.
Joseph A. Spetrini
Acting Assistant Secretary for Import
Administration.
[FR Doc. 05–11595 Filed 6–9–05; 8:45 am]
BILLING CODE 3510–DS–S
DEPARTMENT OF ENERGY
Federal Energy Regulatory
Commission
18 CFR Part 4
[Docket No. RM05–18–000; Order No. 655]
Modification of Hydropower
Procedural Regulations, Including the
Deletion of Certain Outdated or NonEssential Regulations
May 27, 2005.
Federal Energy Regulatory
Commission.
ACTION: Final rule.
AGENCY:
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[Federal Register Volume 70, Number 111 (Friday, June 10, 2005)]
[Rules and Regulations]
[Pages 33820-33825]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-11361]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-21092; Directorate Identifier 2005-CE-20-AD;
Amendment 39-14118; AD 2005-12-02]
RIN 2120-AA64
Airworthiness Directives; Revo, Incorporated Models Colonial C-2,
Lake LA-4, Lake LA-4A, Lake LA-4P, and Lake LA-4-200 Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments.
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SUMMARY: The FAA is adopting a new airworthiness directive (AD) to
supersede Airworthiness Directive (AD) 98-10-12, which applies to all
Revo, Incorporated (REVO) (Type Certificate 1A13 formerly held by
Colonial Aircraft Company, Lake Aircraft Corporation, Consolidated
Aeronautics, Inc., and Global Amphibians LLC) Models Colonial C-2, Lake
LA-4, Lake LA-4A, Lake LA-4P, and Lake LA-4-200 airplanes. AD 98-10-12
currently requires you to ensure adequate clearance between the
attachment fitting and the horizontal stabilizer rear beam and between
the attachment fitting and the stabilizer skin with inspections,
possible replacement, and adjustments as necessary. This new AD is the
result of several reports of fatigue cracks found in the horizontal
stabilizer attachment fitting (part number 2-2200-21) of Model LA-4-200
airplanes that were in compliance with AD 98-10-12. This includes an
airplane accident with a fatality attributed to a fatigue crack in the
horizontal stabilizer attachment fitting. Consequently, this AD
requires either a dye penetrant inspection of the horizontal stabilizer
attachment fitting for any evidence of fretting, cracking, or corrosion
(with necessary replacement and modification) or replacement of the
fittings depending on the number of operational hours on the fitting.
The AD also requires you to repetitively replace the fitting every 850
hours time-in-service (TIS), repetitively inspect (visually) the
fittings between replacement times, and report to FAA the results of
the initial inspection and any cracks found on repetitive inspections.
We are issuing this AD to detect, correct, and prevent future cracks in
the horizontal stabilizer attachment fitting, which could result in
failure of the horizontal stabilizer attachment fitting. This failure
could result in loss of control of the airplane.
DATES: This AD becomes effective on July 8, 2005.
As of July 8, 2005, the Director of the Federal Register approved
the incorporation by reference of certain publications listed in the
regulation.
We must receive any comments on this AD by August 8, 2005.
ADDRESSES: Use one of the following to submit comments on this AD:
DOT Docket Web site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to https://www.regulations.gov and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility; U.S. Department of
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401,
Washington, DC 20590-001.
Fax: 1-202-493-2251.
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
To get the service information identified in this proposed AD,
contact Revo, Incorporated, 1396 Grandview Boulevard, Kissimmee, FL
34744.
To view the comments to this AD, go to https://dms.dot.gov. The
docket number is FAA-2005-21092; Directorate Identifier 2005-CE-20-AD.
FOR FURTHER INFORMATION CONTACT: Cindy Lorenzen, Aerospace Engineer,
FAA, Atlanta Aircraft Certification Office, 1895 Phoenix Boulevard,
suite 450, Atlanta, Georgia 30349; telephone: (770) 703-6078;
facsimile: (770) 703-6097.
SUPPLEMENTARY INFORMATION:
Has FAA taken any action to this point? A report of loss of control
on a Revo, Incorporated (REVO) Lake LA-4 series airplane during flight
caused us to issue AD 98-10-12, Amendment 39-10524 (63 FR 26964, May
15, 1998). AD 98-10-12 currently requires the following on all REVO
(Type Certificate 1A13 formerly held by Colonial Aircraft Company, Lake
Aircraft Corporation, Consolidated Aeronautics, Inc., and Global
Amphibians LLC) Models Colonial C-2, Lake LA-4, Lake LA-4A, Lake LA-4P,
and Lake LA-4-200 airplanes:
Measuring for a clearance of \5/32\ of an inch between the
attachment fitting and the horizontal stabilizer rear beam.
If this minimum measurement is not met, removing the
affected horizontal tail half from the airplane and inspecting the
attachment fitting for any evidence of fretting, cracking, or
corrosion.
If cracks, fretting, or corrosion are/is present,
replacing the attachment fitting with a new fitting, ensuring a
clearance of \1/16\ of an inch exists between the attachment fitting,
and, if needed, trimming the stabilizer skin to provide a positive
clearance for the fitting.
What has happened since AD 98-10-12 to initiate this AD action? The
FAA has received more reports of fatigue cracks found in the horizontal
stabilizer attachment fitting (part number (P/N) 2-2200-21) of REVO
Model LA-4-200 airplanes. These airplanes were in compliance with AD
98-10-12. This includes one report of a REVO Model LA-4-200 airplane
accident with a fatality attributed to a fatigue crack in the
horizontal stabilizer attachment fitting.
The cracks occurred with as little as 942 hours time-in-service
(TIS) on the horizontal stabilizer attachment fitting.
What is the potential impact if FAA took no action? Failure of the
horizontal stabilizer attachment fitting (P/N 2-2200-21) could result
in loss of control of the airplane.
Is there service information that applies to this subject? REVO has
issued Service Bulletin B-78, dated April 3, 1998.
What are the provisions of this service information? The service
bulletin includes procedures for:
--Removing the fitting and inspecting (both visual and dye penetrant)
for cracks, fretting, or corrosion;
--Replacing the attachment fitting with a new fitting;
--Measuring the gap between the attachment fitting and the horizontal
[[Page 33821]]
stabilizer skin for proper clearance; and
--Trimming the stabilizer skin to provide proper clearance.
FAA's Determination and Requirements of the AD
What has FAA decided? We have evaluated all pertinent information
and identified an unsafe condition that is likely to exist or develop
on other products of this same type design.
Since the unsafe condition described previously is likely to exist
or develop on other REVO (Type Certificate 1A13 formerly held by
Colonial Aircraft Company, Lake Aircraft Corporation, Consolidated
Aeronautics, Inc., and Global Amphibians LLC) Models Colonial C-2, Lake
LA-4, Lake LA-4A, Lake LA-4P, and Lake LA-4-200 airplanes of the same
type design, we are issuing this AD to detect, correct, and prevent
future cracks in the horizontal stabilizer attachment fitting (P/N 2-
2200-21), which could result in failure of the horizontal stabilizer
attachment fitting. This failure could result in loss of control of the
airplane.
What does this AD require? This AD supersedes AD 98-10-12 by
requiring the following:
Dye penetrant inspection of the horizontal stabilizer
attachment fitting for any evidence of fretting, cracking, or corrosion
(with necessary replacement and modification) for those airplanes with
less than 825 hours TIS on the fitting;
Replacement of the fittings for those airplanes with 825
or more hours TIS on the fittings;
Repetitive replacement of the fitting every 850 hours
time-in-service (TIS);
Repetitive visual inspections of the fitting every 50
hours TIS (or at the next annual inspection) between the fitting
replacements; and
Submittal of a report to FAA on the findings of the
initial inspection and report of any cracks found for the repetitive
inspections.
In preparing this rule, we contacted type clubs and aircraft
operators to get technical information and information on operational
and economic impacts. As a result of this contact, we received a report
of an additional airplane with a crack in the fitting. This airplane
had 942 hours total TIS. Consequently, we adjusted the compliance times
in the AD based on this information.
How does the revision to 14 CFR part 39 affect this AD? On July 10,
2002, we published a new version of 14 CFR part 39 (67 FR 47997, July
22, 2002), which governs FAA's AD system. This regulation now includes
material that relates to altered products, special flight permits, and
alternative methods of compliance. This material previously was
included in each individual AD. Since this material is included in 14
CFR part 39, we will not include it in future AD actions.
Comments Invited
Will I have the opportunity to comment before you issue the rule?
This AD is a final rule that involves requirements affecting flight
safety and was not preceded by notice and an opportunity for public
comment; however, we invite you to submit any written relevant data,
views, or arguments regarding this AD. Send your comments to an address
listed under ADDRESSES. Include ``Docket No. FAA-2005-21092;
Directorate Identifier 2005-CE-20-AD'' in the subject line of your
comments. If you want us to acknowledge receipt of your mailed
comments, send us a self-addressed, stamped postcard with the docket
number written on it; we will date-stamp your postcard and mail it back
to you. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the rule that might
suggest a need to modify it. If a person contacts us through a
nonwritten communication, and that contact relates to a substantive
part of this AD, we will summarize the contact and place the summary in
the docket. We will consider all comments received by the closing date
and may amend the AD in light of those comments.
Authority for This Rulemaking
What authority does FAA have for issuing this rulemaking action?
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
Will this AD impact various entities? 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.
Will this AD involve a significant rule or regulatory action? 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 ``AD
Docket FAA-2005-21092; Directorate Identifier 2005-CE-20-AD'' in your
request.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the Federal Aviation Administration amends part 39 of the Federal
Aviation Regulations (14 CFR part 39) as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD)
98-10-12, Amendment 39-10524 (63 FR 26964, May 15, 1998), and by adding
a new AD to read as follows:
2005-12-02 Revo, Incorporated (Type Certificate 1A13 formerly held
by Colonial Aircraft Company, Lake Aircraft Corporation,
Consolidated Aeronautics, Inc., and Global Amphibians LLC):
Amendment 39-14118; Docket No. FAA-2005-21092; Directorate
Identifier 2005-CE-20-AD.
When Does This AD Become Effective?
(a) This AD becomes effective on July 8, 2005.
[[Page 33822]]
Are Any Other ADs Affected By This Action?
(b) Yes. This AD supersedes AD 98-10-12; Amendment 39-10524.
What Airplanes Are Affected by This AD?
(c) This AD affects Models Colonial C-2, Lake LA-4, Lake LA-4A,
Lake LA-4P, and Lake LA-4-200, all serial numbers, that are
certificated in any category.
What is the Unsafe Condition Presented in This AD?
(d) This AD is the result of several reports of fatigue cracks
found in the horizontal stabilizer attachment fitting (part number
(P/N) 2-2200-21) of Model LA-4-200 airplanes and one report of a
Model LA-4-200 airplane accident with a fatality attributed to a
fatigue crack in the horizontal stabilizer attachment fitting. We
are issuing this AD to detect, correct, and prevent future cracks in
the horizontal stabilizer attachment fitting (P/N 2-2200-21), which
could result in failure of the horizontal stabilizer attachment
fitting. This failure could result in loss of control of the
airplane.
What Must I Do To Address This Problem?
(e) To address this problem, you must do the following:
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Actions Compliance Procedures
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(1) For airplanes with 825 hours Within the next 25 Follow Revo, Inc.
time-in-service (TIS) or more hours TIS after Service Bulletin
on any horizontal stabilizer July 8, 2005 (the B-78, dated April
attachment fitting as of July effective date of 3, 1998,
8, 2005 (the effective date of this AD) paragraphs 2 and
this AD): Repetitively 3 of the
(i) Replace the horizontal replace any INSPECTION and
stabilizer attachment fitting horizontal REPAIR section
(part number (P/N) 2-2200-21).. stabilizer and the APPENDIX.
(ii) If necessary, trim the attachment
horizontal stabilizer rear beam fitting (P/N 2-
doubler flange to provide 2200-21)
positive clearance to the thereafter
fitting.. following
paragraph (e)(3)
of this AD.
---------------------------------
(2) For airplanes with less than Inspect within the Follow Revo, Inc.
825 hours TIS on any horizontal next 25 hours TIS Service Bulletin
stabilizer attachment fitting after July 8, B-78, dated April
as of July 8, 2005 (the 2005 (the 3, 1998,
effective date of this AD): effective date of INSPECTION and
(i) Remove the horizontal this AD), unless REPAIR section
stabilizer attachment fitting already done. If and the APPENDIX.
(P/N 2-2200-21) from the cracks, fretting,
airplane and inspect for cracks or corrosion is
(using dye penetrant), found, replace
fretting, or corrosion. To take before further
``already done'' credit for flight after the
this, you must have removed the inspection.
fitting from the airplane when
the inspection was done..
(ii) Replace any horizontal
stabilizer attachment fitting
if you find any cracks,
fretting, or corrosion.
---------------------------------
(3) For all airplanes: Every 850 hours Follow Revo, Inc.
Repetitively replace the TIS. Service Bulletin
horizontal stabilizer B-78, dated April
attachment fittings upon 3, 1998,
accumulating 850 hours TIS on paragraphs 2 and
the fittings. 3 of the
INSPECTION and
REPAIR section
and the APPENDIX.
---------------------------------
(4) For all airplanes: Measure Before further Follow Revo, Inc.
the gap between the horizontal flight after any Service Bulletin
skin and the horizontal replacement of B-78, dated April
stabilizer attachment fitting the fitting 3, 1998.
(P/N 2-2200-21). If gap is less required by
than \1/16\-inch, trim the skin paragraphs
to provide at least \1/16\-inch (e)(1), (e)(2),
gap. and (e)(3) of
this AD.
---------------------------------
(5) For all airplanes: Repetitively Follow the
Repetitively inspect (visual) inspect at procedures
the horizontal stabilizer whichever of the presented in the
attachedment fitting using the following that Actions column of
following procedures. occurs first this paragraph,
(i) Move the elevator as (first repetitive including the
required to see the fitting, starts after the sketch on page 1
ensuring that the aft face of initial of the Service
the fitting is visible. inspection or Bulletin B-78.
(ii) Clean the fitting. Pay replacement):
special attention to the radius 50 hours
edges of the fitting just TIS; or.
outboard of the fitting ear. the next
(iii) Visually inspect the annual inspection.
fitting for cracks using a Replace the
flashlight (a small magnifying fitting prior to
glass or borescope is further flight
recommended). Pay special after any
attention again to the radius inspection where
edges just outboard of the cracks are found.
fitting ear. Also, inspect as
far forward on the edge that is
possible because some cracks
progress along the forward face
of the fitting that is mostly
hidden by the horizontal
stabilizer rear beam.
(iv) Reference the sketch on
page 1 of the Service Bulletin
B-78 to see where the crack is
likely to begin.
(v) Replace the fitting prior to
further flight if cracks are
found during any of these
inspections.
---------------------------------
[[Page 33823]]
(6) For all airplanes: Report to Within 10 days Send the form
FAA the results of the initial after the (Figure 1 of this
inspection required by inspection AD) to FAA,
paragraph (e)(2) of this AD required by Atlanta ACO, 1895
even if no damage is found, and paragraph (e)(2) Phoenix
report the results of the or (e)(5) of this Boulevard, suite
repetitive inspections required AD or within 10 450, Atlanta,
by paragraph (e)(2) of this AD days after July Georgia 30349;
only if cracks are found. The 8, 2005 (the telephone: (770)
Office of Management and Budget effective date of 703-6078;
(OMB) approved the information this AD), facsimile: (770)
collection requirements whichever occurs 703-6097.
contained in this regulation later.
under the provisions of
Paperwork Reduction Act of 1980
(44 U.S.C. 3501 and those
following sections) and
assigned OMB Control Number
2120-0056.
---------------------------------
(7) For all airplanes: Do not As of July 8, 2005 Not Applicable.
install used serviceable (the effective
fittings, unless you know the date of this AD).
number of accumulated hours TIS
and have inspected following
the requirements of paragraph
(e)(2) of this AD.
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[[Page 33824]]
[GRAPHIC] [TIFF OMITTED] TR10JN05.002
BILLING CODE 4910-13-C
[[Page 33825]]
May I Request an Alternative Method of Compliance?
(f) You may request a different method of compliance or a
different compliance time for this AD by following the procedures in
14 CFR 39.19. Unless FAA authorizes otherwise, send your request to
your principal inspector. The principal inspector may add comments
and will send your request to the Manager, Atlanta Aircraft
Certification Office (ACO), FAA. For information on any already
approved alternative methods of compliance, contact Cindy Lorenzen,
Aerospace Engineer, FAA, Atlanta ACO, 1895 Phoenix Boulevard, suite
450, Atlanta, Georgia 30349; telephone: (770) 703-6078; facsimile:
(770) 703-6097.
May I Obtain a Special Flight Permit for the Initial Inspection or
Replacement Requirement of This AD?
(g) Yes. Special flight permits are allowed for this AD with
these limitations:
(1) Vne reduced to 121 m.p.h. (105 knots); and
(2) No flight into known turbulence.
Does This AD Incorporate Any Material by Reference?
(h) You must do the actions required by this AD following the
instructions in Revo, Inc. Service Bulletin B-78, dated April 3,
1998. The Director of the Federal Register approved the
incorporation by reference of this service bulletin in accordance
with 5 U.S.C. 552(a) and 1 CFR part 51. To get a copy of this
service information, contact Revo, Incorporated, 1396 Grandview
Boulevard, Kissimmee, FL 34744. To review copies of this service
information, go to the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, go to: https://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html or call (202) 741-6030. To
view the AD docket, go to the Docket Management Facility; U.S.
Department of Transportation, 400 Seventh Street, S.W., Nassif
Building, Room PL-401, Washington, DC 20590-001 or on the Internet
at https://dms.dot.gov. The docket number is FAA-2005-21092;
Directorate Identifier 2005-CE-20-AD.
Issued in Kansas City, Missouri, on June 2, 2005.
Kim Smith,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-11361 Filed 6-9-05; 8:45 am]
BILLING CODE 4910-13-P
